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SPER^Y RAI\D
EARTH ORBITAL WORKSHOP
CAPABILITIES BROCHURE
SPACE SUPPORT
DIVISION
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^SPER^Y RAfSD
SECTION I
INTRODUCTION
SPACE SUPPORT DIVISION
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�INTRODUCTION
The Sperry Rand Space Support Division presents t h i s brochure t o depict
a competence and capability in the area of
large earth-orbita I workshops.
Workshops that are:
®
In
fabrication (ATM)
•
Proposed
for Saturn V Vehicles (B0 6
• Conceptually designed
(Nuclear Power)
for specific advanced applications
Sperry's ability to offer a depth of
experience in the orbital workshop
area is directly attributable to the technical
Division is
technical
Mx)
support the Space Support
p r o v i d i n g t o t h e MSFC A s t r i o n i c s L a b o r a t o r y .
In this role a
foundation and competence in design and deveIopment of
orbital
workshops has been established. The Apollo Telescope Mount provided the
hardware, subsystem and system experience. Then
follow-on studies developed
the necessary mission analysis experience. Hence, an overall
capability has evolved.
The areas of demonstrated proficiency are:
I.
EXPERIMENTATION
X-Ray Telescope Design
X-Ray Camera Design
Television System Design
Laser Research
I I .
POWER
Solar Array Design
Nucleonics Analysis
Fuel Cell Design
I I I .
COMMUNICATIONS
Data Compression Studies
Information Coding Techniques Studies
Modulation Techniques Studies
Phase lock Loop Analysis
Phase Compensat ion Analysis
Hardware Design
Antenna Systems
Pulse Code Modulated Data Acquisition Systems
Telemetry Ground Station
i
workshop
��270-ChanneI
Multiplexer
Single Side Band Double Side Band Filters
Airborne Telemetry Pouier Supplies
IV.
CONTROL
Control Moment Gyro System Analysis
Experiment Pointing Control Analysis
Control
System Analysis and Design
ATM
Orbital Workshop
Reaction Control
Jets
Sizing
Fuel Consumption
Momentum Dumping
Optimal
Backup
Star Tracker Anulysis
A summary of
ience
the engineering effort related to orbital workshop exper
is presented in the Capabilities
tion there are
four
Section (Section
II). In that sec
s u b s e c t i o n s w h i c h a r e u n i q u e l y c a t e g o r i z e d by NASA's
Phased Project Planning. The
four steps of
Phased Project Planning are
Advanced Studies, Project Definition, Design. and DeueIopment and Ope
rations Categorized as Phase A. B. C and D respectiueIy.
The remainder of
the brochure
provides an insight
background, organization makeup and manpower
into the Division's
level.
The capabilities reported herein were developed by the Space Support
Division under Contract NAS8-20055 t o the National
Administration. George C. Marshall
oratory. Huntsv i I le . Alabama.
Aeronautics and Space
Space Flight Center. Astrionics Lab
����II.
WORKSHOP CAPABILITIES SUMMARY
TABLE OF CONTENTS
Phase
Page
A
Advanced Studies
2-1
B
Project Definition
2-0
C
Design
2-/5
0
Deuelopment and Operations
2-23
iu
��WORKSHOP CAPABILITIES SUMMARY
PHASE A - ADVANCED STUDIES
In the Advanced Study Phase concept
mission approaches are made. Requirements
feasibility studies of
for each are analyzed, engineer
ing assessed and exper iment programs grossly defined.
written detailing all
various
From t h i s a report
analytical work, alternate solutions, tradeoff
is
cri
teria and recommendations.
The Phase A definition adequate I y defines the work
Space Support Division's Advanced
onics
Studies Group
Laboratory's Advanced Studies Office.
performed by the
in support of
the Astri-
The recent studies as docu
mented by Sperry are:
/I S t u d y o f
Eq u i p m e n t s '
the Backup Saturn I Workshops
Potential
(AS2I0 Wet
Launch) Astr ionic
for use in an Austere Dry Launch Saturn V IVorbshop (B)
An investigation into the system and sub-system modifications required
t o ad a p t t h e S a t u r n I
u
Wet Launch" workshop's backup eauipment to an aus
tere Saturn V "Dry Launch" workshop was
performed. Convers ion time, cost
and mission scheduling were traded off against versatiIity and
l i f t capa
bility.
SP 590-0132
Completion date:
Selected Studies of
9/68
Some Conceptual Earth-OrbitaI Workshops
Systems analysis and trade-off
studies were made on a number of
con
ceptual earth-orbital workshops in an effort t o size systems and obtain the
best configuration. Areas studied
tems.
included experiment payload,
instrumentation and communications, thermal
power sys
controls, control and
display, and video imaging.
SP 590-0098
Completion date:
Attitude Control
System Synthesis
for Conceptual
7/68
Saturn V
Launched
Earth-Orbita I Workshop/Space Stations
Identified Eight Conceptual Workshop/Space Station configurations and
studied
in detail
four t o determine overall
attitude control
requirements
to be expected. Then, using these requirements two potential attitude con
trol
systems are synthesized.
2-1
��General concepts were derived
from NASA's current Saturn V Earth-Orbital
Workshop/Space Station planning a c t i v i t i e s .
Disturbance torques considered are gravity gradient, aerodynamic, solar,
magnetic and man motion. The c o n t r o l
jets, control
systems
included reaction control
moment gyros and various combinations of both.
SP 590-0097
7 68
Completion date:
Microwave Power Transmission Study for Space Applications
Considered the feasibility of transmission of
power by microwave beaming
from a master s a t e l l i t e t o one or more smaller s a t e l l i t e s . Theoretical
quantitative results are presented detailing the efficiency of
and
each sub
system plus total system efficiency using either the e l l i p t i c or the para
bolic reflector antenna.
SP 590-0072
Completion date:
4/68
Signal-to-Noise Considerations for Orbiting Astronomical
Presented data that helps provide fundamental
X-Ray Telescope
information on establish
ment of c r i t e r i a t o postulate on the temperature, density and composition
of matter
in the galactic and intergaI act i c space, presence and strength
of magnetic and electric fields in space, the origin and distribution of
cosmic rays and the creation of matter.
SP 599-0110
Completion date:
8 68
Large Aperture Telescope: Phase I , 2 , 3 . 4 and Summary
Performed control
system analysis on suggested high accuracy
large
aperture telescopes. The studies were confined t o the fine pointing control
cf
a one meter diameter
large aperture telescope mounted on an SIVB type
orbital workshop. The pointing accuracy of
the systems analyzed
is 0.01
arc second maintained for extended periods of time.
A two body analog simulation was developed t o t e s t the various hardware
configurations and evaluate the effects of disturbances,
motion, on pointing accuracy.
SP 5 9 0 - 0 0 3 4 - 0 . I . 2 . 3 . 4
Completion date:
2 - 3
including man
5/68
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�Phased Array Antenna Study - Phase
A comprehensive study of
I and
II
the characteristics of
phased arrays was per
formed. State-of-the-art information is presented
from the literature on
weight, s i z e . gain, number of elements, scan and efficiency. Also detailed
is the pattern effect due to radiator mis location caused by manufacturing
errors and thermal
gradients.
SP 590-0108
Completion date:
8 68
SP 590-0134
Completion date:
9/68
Boom Extended Nuclear (Orbiting) Reactor Control
In suggesting nuclear reactors
of
vehicle control
came t o the
for
Study
large space stations the question
forefront. This
study endeavers
to answer
that question by considering the reactor mounted on a boom extended
the side or end of
from
the vehicle.
An investigation into the
i n t e r r e l a t i o n s between the boom mounted re
actor and the vehicle control
system was
performed. Analog and Digital
s imulation programs were developed t o compute external disturbance torques,
composite mass and
inertia data.
In addition, a complete two-body vehicle
dynamic simulation containing a vehicle control
verify analytical
system was developed t o
results.
SP 209-01
Completion date:
An investigat ion of
Sensors
S trapdown inertial
stations of
the
12/68
Redundancy Concepts Applied to Strapdown
navigators appear to have a place
in large
put with the mean output of
trade-offs
<aturn
sensor out
all the sensors.
program was developed t o study various approaches and evaluate
in the detection and isolation of
SP 590-C084
Mod i f i e d
space
future. A study input, t o system development, was a method
to detect and isolate defective sensors by comparing individual
A digital
Inertial
sensor ma I f u n c t i o n s .
Completion date:
IV
Six Degree Dynamical
Simulations with
7/68
Iterative Guidance
for Advanced Vehicles and Missions
Strap-on solid
fuel e n g i n e s .
and variable thrust liquid
Saturn V vehicles without the SI I stage
fuel engines are analyzed to determine impact on
��the
present guidance modes.
veloped utilizing the
Full
scale digital
simulations haue been de
l a t e s t MARVESS t r a j e c t o r y techniques making l i f t - o f f
to injection studies possible.
SP 209-TD-04
Completion date:
I
69
��W O R K S H O P C A P A B I L I T I E S SUMMARY
PHASE 8 - PROJECT DEFINITION
In the project defin i t ion phase selected concepts are refined, assess
ments o f t o t a l miss ion requirements are made and a system analysis
prepared.
From the study results presented a project plan emerges which specifies a
single concept,
recommends a plan for
phase C and presents a preliminary
Project DeueIopment Plan.
The Sperry Rand Space Support Diuision by supporting the Astrionics
Laboratory on the Apollo Telescope Mount Vehicle (ATM) was an integral
part
of t h e ATM Phase B endeauor. T h i s produced e x p e r i e n c e by a s s o c i a t i o n w h i c h ,
in our opinion, gives a depth of
knowledge
in the area of
large orbital
space station technology obtainable only by day-to-day contact with the
cognizant NASA o r g a n i z a t i o n s . A sampling of r e p o r t s a p p l i c a b l e t o the phase
B planning process
is presented below.
Antenna Pattern Measurements
Analyzed three methods of measuring antenna patterns in relation t o the
antenna attitude
in a 200 nautical m i l e o r b i t . The study was made t o e v a l
uate a c o n t r a c t o r ' s proposal t o NASA f o r measuring the c h a r a c t e r i s t i c s of a
large space erectable parabolic antenna. Comparison studies were conducted
and recommendat ions submitted f o r the most accurate method of
measuring
antenna patterns.
RL # 16-022
Discussion of
Completion date:
5/66
t h e Torque R e c t i f i c a t i o n Dump Scheme
Scrutinized contractor's proposal
f o r a g r a v i t y gradient dump scheme
designed f o r momentum r e l i e f of the Control Moment Gyros. The scheme u t i
lized the rectification of the c y c l i c gravity gradient torques by changing
signs of
the commanded maneuver angles a t specified times
in the orbit.
T h e a t t r a c t i v e a n d u n a t t r a c t i v e f e a t u r e s o f t h e s c h e m e urns p r e s e n t e d
a f t e r a detailed analytical and computer simulation study was performed.
OWS-2-1
Completion date:
Double Gimbal Control Moment Gryos
The System for
4/67
in Vehicle Attitude Control
I n e r t i a l Experiment P o i n t i n g a n d A t t i t u d e C o n t r o l
PAC) os proposed by NASA (Langley F i e l d , V i r g i n i a )
2-9
is investigated.
(OIX-
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�The
fundamentals of
the equations
t h e CMG s y s t e m are
for a space v e h i c l e using t h e SIXPAC conf iguration is devel
oped. Along with this a block diagram of
developed
presented and the derivation of
t h e CMG a n d u e h i c l e d y n a m i c s a r e
for system study.
The characterist ics of
t h e CMG a s a n a t t i t u d e c o n t r o l d e v i c e a r e a l s o
discussed and a comparison with other attitude control
Then advantages of
the various systems are
SP 517-67-1
schemes
is made.
presented in cone I usion.
Completion date:
1/67
Charaer-batteru Regulator Module - Prototupe Test Model
4n engineering a n a l y s i s was
for the thermal, mechanical
performed to establish design requirements
and vibration prototype of
battery - regu I ator -modu I e . The
packaging design required compliance with
MSFC Document 50M02408. E n v i r o n m e n t a l
teria
t h e ATM c h a r g e r -
Design and Qualification Test Cri
f o r ATM C o m p o n e n t s . T h e t h e r m a l
and vibrational
analysis of
the
prototype charger-battery regulator was conducted t o v e r i f y the packaging
design per requirements of
50M02408.
RF # 10-004
Completion date:
Generation of
Orbital
7/68
Coordinate Systems and Aerodunamic and Gravitu
Gradient Torques
T o e v a l u a t e and c o n f i r m t h e ATM c o n t r o l
face a detailed soft mockup of
system configuration and
inter
the vehicle pointing and control system was
deve loped.
The developed
earth orbital
program
presents a complete MathematicaI
Model
space station. The Earth-sun-sate 11ite motion model
lated along with all
external
of
an
is simu
torques acting on the vehicle. The control
system containing control moment gyros and reaction
making i t possible to do detailed
jets is also simulated
fuel studies of any earth orbital
control
system. Presently this simulation
digital
and 8900 hybrid computers.
SP 522-0058
is
vehicle
programmed on both the 7094
Completed:
4/67
Updated:
4/68
ATM Command a n d T e l e m e t r y A n t e n n a s
Originated the design concept and
types of
ATM a n t e n n a s .
fabricated scale models and
proto
The antennas are mounted on t h e solar wings. An
edge-mounted scimitar antenna was used
2 - II
for t h e 450 MHz command s y s t e m and
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�an edge-mounted dipole antenna
was
for t h e VHF t e l e m e t r y . The d e s i g n c o n c e p t
formulated by building 1:20 scale models of
the proposed antennas and
checking the radiation characteristics on a 1:20 scale model
of
the Apollo
Telescope Mount cluster.
RL # 16-006
Completion date:
A—Techn i que
By use of
If
f o r S t a b i l i z i n g t h e ATM V e h i c l e
11/68
for Extended Time Periods
Momentum Exchange Devices
a n ATM r e u i s i t i s e n v i s i o n e d t h e r m a l
supply thermal
control
a source of
control will be necessary. To
power will be required.
If
t h i s power
is provided by solar cells
facing the sun a control system will
either active or inactive.
If an active system is used the system described
in this report
be required
is applicable.
The study presents a momentum management scheme t o permit control
t h e ATM w i t h c o n t r o l moment g y r o s d u r i n g t h e unmanned phase o f
The momentum management scheme reverses the direction of
of
the mission.
disturbance torque
through simple CMG-controlled maneuvers, thus eliminating the requirement
for reaction
control
jets to relieve the
unidirectional
stored momentum of
the
moment gyros.
Presented to
May 1967
American AstronauticaI
National
Society
Symposium
SIVB Stage Digital
An al I-digital
Filter
flight controller
detail. Several mechanizations of
and comparisons made by means of
for the SIVB stage is considered
the digital
in
compensator are designed
frequency response measurements and hybrid
simulation.
SP 551-0045
Completion date:
2-13
4/24/68
�2-14
�WORKSHOP CAPABILITIES SUMMARY
PHASE C - DESIGN
In this
phase the
final
concepts are developed: designs are made t o
required specifications: and a total
system analysis made. From this an ana
lytical report is assembled and the
(PDP) released.
finalized Project CeveIopment Plan
The Apollo Telescope Mount (ATM), as the
first
large orbital workshop,
has been through this phase. The Space Support Piuis ion's contribution in
this phase, as documented, is presented
ATM 50-56 X-Rau T e l e s c o p e :
Final analysis of
following paragraphs.
Final Report
the optical
is presented. Analysis
in the
the SO-56
X-Ray Telescope
includes ray tracing with special
emphasis on ray
diagrams, spot diagrams and
properties of
point spread
functions. All
aspects of
the
X-ray reflection dynamics were considered.
0BS-3-I
Completion date:
3/69
ATM Conf_[quration Manaqement
Established a system
for configuration control
for t h e ATM p r o g r a m . The c o n c e p t of
plan and documentation control
and documentation
a workable configuration management
plan was
presented t o and approved by the
MSFC ATM P r o j e c t O f f i c e ; t h e n d o c u m e n t e d and i m p l e m e n t e d . T e c h n i c a l
mentation is generated
determine a basic
flow
docu
from research and data gathering, as required, t o
for t h e ATM program. The c o n f i g u r a t i o n management
keeps engineering management
plan
informed on the program status.
RL # 18-002
Completion date:
This
i s a con
tinuing program.
ATM E x p e r i m e n t
Interface Control
Documents
R e v i e w e d and a n a l y z e d e x p e r i m e n t e r a n d ATM e l e c t r i c a l c i r c u i t s , a n d
maintained electrical
systems c o m p a t i b i l i t y between experimenters. MSFC.
and Manned Spacecraft Center by generating electrical
documents and electrical
interface control
interface defining documents. Reviewed experi
menter s proposed changes and recommended acceptance or refusal by the Con
figuration Control Board.
R L ft 0 9 - 0 1 2
Completion date:
2-15
4th Quarter/70
��Cable and D i s t r i b u t i o n Sus tern
A 700-cable distribution system
control, power
distribution. and data transmission
a 52-rack. 260-panel
ATM.
is currentIy being designed
electrical
support
An analysis has been made of
interconnections between
equipment checkout
the entire cable and
out system t o establish design goals and c r i t e r i a .
500FS system was
made t o determine u s a b i l i t y o f
continuing systems
control
is
interface study
is
to provide
system and
the
distribution check
A study of
cables
for
the Saturn V,
the design.
being performed and cable
A
interface
being maintained.
RL # 09-006
Comp l e t ion d a t e :
11/68
ATM D i s t r i b u t o r s
Pre Iiminary studies of
bution requirements
ATM power, measuring, and command signal
established the
butors. The distributors route
need
commands,
between the command capsule control
and the electrical
of
the ATM.
especially designed distri
measurements,
panel,
and electrical
t h e ATM experiment
support equipment. both prior
Designed the complete distributors
and components. Thermal
reduction
for
distri
to
power
packages,
and subsequent to
include housing,
launch
cabling,
uacuum tests are performed t o v e r i f y the design.
i n the number
of
distributors required
is
A
achieved through the
u t i l i z a t i o n of TO-5 type relays.
R L if 9 - 0 0 4
Optimal
Completion date:
Desaturation of Control
Space vehicles
on missions
Moment Gyro Systems
that
u t i l i z e Control Moment Gyros (CMGs)
require
for a
precise pointing capabiIity offered by
systems. CMGs
by
do run out of
CMG g i m b a l
fuel
tank)
External
gimbal
angles).
torques must
angles.
problem of
CMG c o n t r o 1 1 e r s
problem.
in this application
condition (analogous
gimbal
angles
to the vehicle/CMG
free "fuel" source available
momentum desaturation of
is cast
into the
The system model
with a state and control
has
the
format of
form of
independent,
OWS-3-4
of
the
in the
to
an empty
a minimal
limits.
reset the
process
is de
gravity gradients.
pointing control
a linear
is measured
system to
systems with
energy optimization
time-varying equation
time-varying forcing function.
Completion date:
2-17
perhaps
approach their
A systematic approach to this "refueling"
scribed using the
The
pointing will
a continuous controller. Like other
The "saturated"
be applied
in Orbit
long time t o come because
"fuel" (which,
i s r e a c h e d w h e n t h e CMG
fine
8/68
1/69
�TELESCOPE TO WORKSHOP MAGNETIC SUSPENSION DYNAMICS
/.TELESCOPE
COUPLING FROM WORKSHOP TO
TELESCOPE THRU SUSPENSION
FORCE = K | i ( S )
K| [Ei(S)-(^jsd(S)]
(TS+I)
A magnetic
an almost
suspension of
perfect
this
T=
type can be
isolator, expecially when
L|
A +R|
feedback principles are applied. Coupled
K|=I.47
force due t o workshop motion
K2=l.65
open
loop gain A.
is reduced by
In addition, the
characteristics are essentially
isolation
frequency
invariant.
2-18
A > 1000
�ATM C l o c k
Designed the
logic and
stable time references
of
packaging of
t h e ATM c l o c k t o p r o v i d e u l t r a -
for u a r i o u s ATM e x p e r i m e n t s . The c l o c k
prouiding time references
days, with a stability of
I
in milliseconds,
is capable
seconds, minutes, hours, and
x 10^ throughout the temperature range of
-20
degrees to 85 degrees Celsius. The clock can be reset to any time period
by ground command signals, and has a r e l i a b i l i t y of
unit was fabricated and tested.
RL # 17-008
0.99965. One prototype
Completion date:
9 67
ATM S w i t c h S e l e c t o r Panel
Prepared Class
panel
is required
design of
I documentation of
t h e ATM s w i t c h s e l e c t o r p a n e l . T h e
f o r ATM s e l e c t o r s w i t c h t e s t and c h e c k o u t . The
the panel
(component layout) was
ments. Documentation was
00224A.
completed
Completion date:
12,67
System Networks
The electrical
circuitry to
perform switching, control,
interconnect all
five control
ATM s u b s y s t e m s a n d t o
power distribution, and
functions is currently being designed.
distributors .
prepared t o meet MSFC r e q u i r e
i n accordance w i t h MSFC Drawing 40M-
RL # 10-013
ATM E l e c t r i c a l
packaging
signal
conditioning
The system consists of
three power
d i stributors. three measuring distributors, a
transfer assembly, a controls and display logic distributor, and approxi
mately 500 interconnecting cables. The
specifications.
RL # 09-011
s u b s y s t e m s a r e d e s i g n e d t o ATM
Completion date:
1/69
Time - Division Multiplexer
A time-division multiplexer was designed to accept up t o 270 data inputs
of
0 to 5 volts
in amplitude, and to provide
two parallel
output wave
trains. The multiplexer has 30 primary channels with a sampling
120 samples per second. Principal
the dc dc converter and
subassemblies of
regulators that
provide
missile power grounds: an isolation amplifier
rate of
the multiplexer are:
isolation of
signal
and
for each output: main channel
multiplexer cards: calibrator: ana clock and timing subassembly. One multi
plexer was breadboarded and successfully tested. Documentation and
type
fabrication are
used o n t h e second ATM
RF # 16-025
in process. Several
of
these multiplexers
flight.
Completion date:
2-19
9/68
proto
shall
be
��Control Circuitry
for Data Acquisition Sustem
D e s i g n e d t h e a m p l i f i e r a n d s w i t c h a s s e m b l y t o b e u s e d o n t h e ATM t o
amplify and select the proper output of
r e d u n d a n t PCM d i g i t a l d a t a a c q u i s i
t i o n s u b s y s t e m s . S w i t c h i n g b e t w e e n t h e t w o PCM s u b s y s t e m s
is accomplished
by commands to internal control c i r c u i t r y . These control c i r c u i t s employ
electro-optical
devices t o provide maximum isolation between the external
command signal c i r c u i t r y and the control
RL # 17-005
circuits.
Completion date:
11/67
Charger-Batteru Regulator-Module Documentation
This effort
involves
preparation of
the specification. and the accept
ance preliminary and qualification test procedures
for the Apollo Telescope
Mount (ATM) charger-battery-regu I ator module. A review of
requirements and
prototype circuitry provided detail
three documents. The specif icat ion establishes
requirements; the acceptance test procedure sets
standards: and the qualifications test
operating requirements
t h e ATM
requirements
forth module acceptance
procedure details environmental
Completion date:
2-21
for the
purchasing manufacturing
for the modules.
RL # 10-001
power
4/68
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�WORKSHOP CAPABILITIES SUMMARY
PHASE D - DEVELOPMENT AND OPERATIONS
In this
final
phase the tasks of developing. manufacturing, testing and
operating the products designed to achieve the mission goals are carried
out. The Space Support Division s capabiIity in this area is readily demon
strated by presenting assigned tasks and describing the design deveIopment
and testing effort
put
forth on each. The
the Apollo Telescope Mount (ATM)
following paragraphs describe
Phase D effort.
X-Rau Telescope - Camera and E lectronics Desian:
The X-ray teIescope-camera and electronics
S-056 Design
for the S-056 X-ray telescope
experiment which will measure soft X-ray radiation originating in the solar
atmosphere has been designed, deve I oped. and produced. The X-ray telescope
system comprises
an X-ray telescope with
film camera and an X-ray event
analyzer (X-REA).
The X-REA and teIescope-camera are two independent measuring systems
w h i c h w i l l b e a t t a c h e d t o t h e ATM i n a m a n n e r w h i c h w i l l
to measure radiation
from the same source. The
these two measuring systems will
flares and the physical
allow both systems
information obtained
provide a better understanding of
processess which take place in the
OBS-4-1
Complet ion date :
from
solar
sun.
I 69
ATM T e l e v i s i o n S y s t e m D e s i g n
A television system
for the Apollo Telescope Mount (ATM) has been de
signed and developed. This
naut viewing of
system is installed
solar activity
telescopes and consists of
i n t h e ATM t o e n a b l e a s t r o
from earth orbit through several different
two (2)
Iow-light-1eve I
TV cameras, two ( 2 )
v i d i c o n T V c a m e r a s , a n F. I A s y n c g e n e r a t o r , a n d t w o ( 2 ) w i d e b a n d v i d e o
switches.
The
of
low-light-level
excellent
usable
t e l e v i s i o n camera u t i l i z e s a SEC v i d i c o n c a p a b l e
picture quality
p i c t u r e q u a l i t y ( 2 0 0 TV
can be used as a
candles .
( 6 0 0 TV
lines) at 3 x 10'3
lines) at 5 x /0"5
footcandles and
footcandles. The camera
Iight-integrating device down t o levels below 10'7
2-23
foot
��T h e ATM v i d i c o n camera i s a h i g h r e s o l u t i o n ( 8 0 0 TV l i n e s ) s y s t e m u t i l i
zing a standard 5403 ruggedized uidicon with excellent
I
x lO'l
footcandles. Usable
performance down t o
pictures can be obtained down t o 5 x
10
footcandles.
OBS-4-2
Completion date:
E l e c t r i c a l Power Subsystem
for Apollo Telescope Mount (ATM)
This task comprised the design and deuelopment of
power subsystem which
I 69
furnishes the electrical
t h e ATM e l e c t r i c a l
power required by all other
ATM s u b s y s t e m s a n d e x p e r i m e n t s .
T h e ATM e l e c t r i c a l poiuer s u b s y s t e m c o n s i s t s o f
energy conversion
and the required
sources.
interface
18
18
photovoltaic direct
power conditioning-energy storage groups.
interface networks and power distribution c i r
cuitry that provides remote system control
capability, system monitoring,
and power management information.
OWS-4-3
Completion date:
I 69
270 Channel Multiplexer
The 270 multiplexer was designed t o accrue data and channel
the data
via 270 lines to the data acquisition system. The multiplexer utilizes the
latest circuit configurations.
including integrated circuits. To develop
the multiplexer, the electromechanical
grated circuits with weldable
through the motherboard and
leads.
flexible
package was designed using inte
Interconnections were accomplished
printed circuit cabling. The
flight
housing was designed utilizing three configurations-almag sand casting,
aluminum sheet weldment and an aluminum dip brazed housing: of
latter was selected
for implementation. The multilayered circuit boards are
attached in an accordion
padding inserted
fashion with
flexcabling and with shock-resistant
into a cavity configuration. The module is currently des
ignated as backup
for t h e second ATM
for the
f i r s t ATM
flight and will maintain a prime status
flight upon completion of
RL # P4-008
AC DC
which the
prototype development.
Completion date:
6/68
Power Suoolu
An ac dc electronic
d c power t o t h e ATM
motor. The dc
power supply was designed and
platform modules and ac
portion of
the
power
supply
fabricated to
furnish
power t o t h e 4TM g y r o s p i n
is equipped with a
step-up
switching prereguIator. a dc-to-dc conuerter and a pulse regulator. The
2-25
�ACCEPTABLE S/N RATIO
The performance a t t a i n a b i l i t y of
brightness. as a function of
a star tracker, for a particular guide s t a r
the acceptable signal
J-26
to noise ratio.
�ac output
is equipped with a crystal-control led oscillator,
followed by a
binary countdown. The dc input uoltage is required to remain between 24 to
32 volts to maintain a dc
power output of
250 watts and 35 volts ac at
1600 Hz.
RL # 22-009
Completion aate:
Ground Support Electrical
Power Sustem
A power system is currently being designed t o
solar bus and or load bus and t o the electrical
forming ground checkout of
12 66
f u r n i s h power t o t h e ATM
support equipment when per
the ATM. The design e f f o r t
includes an overall
system analysis to establish design criteria, an evaluation of
s y s t e m s t o d e t e r m i n e t h e i r a d a p t a b i l i t y t o t h e ATM
comprehensive study of
paration of
existing
requirements, and a
each subsystem to provide details needed
for
pre
the preliminary design drawings. Fabrication drawings and pre
liminary early-order parts lists are also being prepared.
R L # 09-009
Completion date:
11 68
Hudrogen-Oxuaen Fuel Cell Resign and Test
Four
years of
detailed experience has
operation and test of
Hydrox
fuel
been obtained
in the design,
cells. Approximately 8000 hours of
ope
r a t i o n of 2-kilowatt A11 i s-ChaImers (AC) systems have been logged by d i v i
sion personnel
in the study and test of
developments have resulted
these power sources. Significant
from research conducted on single
sections on evaluation consoles developed and
OWS-4-4
fuel
cell
fabricated by this Division.
Completion date:
A continuing
effort
Sun Sensor and Star Tracker Computer Simulator
A computer simulator is currently being developed
of
the sun
sensor and
similar to that of
star tracker. The
simulator
internal electronics of
the
the data.
the direction and magnitude of
solver zero, and
tested when
flight:
function
i t gene
pulses, that are used
fine sun sensor and star tracker
purposes, gating, and shifting of
data of
performs a
the on-board digital computer during
rates an interrogate pulse, together with clock
the
for ground checkout
for timing
It also accepts serial
binary
the resolver rotation and the re-
presents them to the display panel. The simulator will
fabrication is completed.
RL # 13-001
Completion date:
2-27
in
Estimated 6 68
be
�2-28
�P a c h ac l i n g P e s i g n _ f o r t h e C h a r g e r B a t t e r y _ R e g u l a t o r M o d u l e ( C P R M )
Performed the packaging design and documentation of
t h e ATM C B R M . w h i c h
included engineering design, drafting, and checking. The packaging design
required compliance with the EnuironmentaI
Criteria for
ATM Components s p e c i f i c a t i o n . The purpose o f
prouide regulation, conuersion.
while
and storage of
solar-cell
t h e CBRM
is
to
power t o t h e ATM
in an earth orbit.
RL # 10-006
Completion date:
S-Band Helical
with a gain of
68
II
Arrau Antenna
Designed a S-band helical
of
Design and Dualif ication Test
array. The array consists of
a single helix,
8 db. mounted upon a common base p l a t e , adjacent t o an array
four helices. The array has a gain of
12 db. The dual
gain feature was
utilized to prouide hemispheric earth coverage from an altitude of
t o 2 3 . 0 0 0 s t a t u t e m i l e s . ,1 c o a x i a l
antenna radiator. A four helical
because of
antenna height
switch directs the rf
signal
8.000
to either
array was used for the high gain radiator
restrictions on the Saturn V Instrument Unit. A
laboratory
model
verified
the design dimensions.
A shop prototype was
fabricated
from design drawings. Qualif ication tests to flight certify
the
antenna were performed and the quaI i f i c a t i o n test report published.
RL # I 6 - 0 I 2
Completion date:
10/66
Power Control and Monitor Panel
A control
panel,
distribution of
for
monitoring and controlling the
ATM e l e c t r i c a l
support equipment power,
generation and
is currently
in the
preliminary stage of deuelopment. The subsystem w i l l
s i m u l a t e t h e ATM s o l a r
sources and control
Modules
(CBRM) during
also has override control
capabi I i t y for
the Charger-Battery-ReguIator
ground checkout. The control
panel
controlling the switch selector encoded assembly.
RL # 09-003
Completion date:
2/68
Solar Simulator
A solar
simulator,
gineered and designed
simulator
tube
mw cm- i n t e n s i t y
Celsius.
for
testing solar cell
for use
capable of
performance, has been en
i n t h e ATM q u a l i t y a s s u r a n c e program.
illuminating a 24- by 26-inch area,
has
The
a 100
capabiIity at any temperature setting between 100 and90°
RL # 10-022
Completion date:
) - 70
II
67
�radiated power.
2-30
�Portable Solar Reflectometer
A portable
solar reflectometer
for measuring reflective
property of
materials in space is currently under deueIopment. The instrument will make
measurements over a wave-length range of
bands.
Data obtained
from measurements
tape recorder, which is an integral
of
2500 A to 2.5 microns in eleuen
is to be recorded on a magnetic
part of
the reflectometer. The
the reflectometer is t o make refIectance measurements of
paint
purpose
samples
and or other materials which may be affected by the space environment.
PL - 16-027
Completion date:
8 68
Advanced Optical Communications Systems Research and Development
Research
perimental
in this area involves state-of-the-art theoretical
studies of
the eventual
cluded
visible and
development of
in this program are
infrared
and ex
laser systems, with an aim to
a deep-space laser communications
projects that involve
link.
In
laboratory photomixing
experiments. beam steering and alignment technique studies, the design and
testing of
signal
processing and information retrieval electronics,
laser
stability and control studies, and the development of transmitting optical
systems.
R L •• 0 1 - 0 0 1
Completion date:
This is a con
tinuing program.
Aavanced Optical Tracking Systems Research and Development
Under t h i s
program, research and development is being conducted on a
precision optical
tracker that utilizes a visible laser transmitter
for
monitoring the elevation and azimuth angles, angular rates, range, and
range rate of
a spacecraft during the critical
launch phase which occurs
immediately after l i f t o f f . Current activity in this program involves the
prototype development of
laser amplitude modulations, modulator drivers,
and diverse detection and demoduI ation eIectronics.
RL •• 0 1 - 0 0 2
Completion date:
4th Quarter/68
Gas Laser Research
This research and development program is directed
parameters of
gas
laser photomixing systems
at optimizing the
for potential use in tracking
and communication applications. Current program activities
involved in the measurement of
ment of
include projects
laser mode s t a b i l i t y , the prototype develop
scanning interferometers
for monitoring laser mode patterns, and
the experimental and theoretical research on the dependence of photomixing
on optical path length difference.
RL # 0 1 - 0 0 3
. •
r
Completion date: This is a con
tinuing program.
2-31
��Laser Atmospheric Propagation Studies
These studies
involve the experimental and theoretical
random phase variations in laser radiation during
research on the
Iong-distance atmospheric
propagation. Activities are oriented to the design and development of
laser system that is to be employed in the measurement of
ations of
an amp Iitude-moduIated
a
the phase vari
laser beam as i t traverses various atmo
spheric path lengths.
RL " 01-005
Completion date:
This is a con
tinuing program.
Optical Component Development
This RSD e f f o r t i s
organized to provide optical
systems-components
integration and correlation technology. The program consists of
an optical
systems design study that is being conducted in con j unction with an optical
components design and development activity (mirrors. lenses): which in turn
results
tical
in the integration of
the individual components
into complex op
s y s t e m s . /I c u r r e n t d e s i g n a n d d e v e I o p m e n t p r o j e c t i s t o d e s i g n l a r g e
f-number lenses with minimal
low-order Seidel abberations.
R L -- 0 1 - 0 0 4
Completion date:
This is a con
tinuing program.
Advanced Semiconductor Memoru Devices Research
Theoretical and experimental
research studies into the use of
a metal-
insulator- semi conductor (MIS) device, as a bistable active memory element,
were performed. The device utilizes the tunneling effect between the semi
conductor and the insulator to store trapped charges.
RL
H
01-009
Completion date:
This is a con
tinuing program.
Advanced Semiconductor Materials Research
Research studies involve state-of-the-art epitaxial
niques. Current
research includes development of
transistors, deposition of
growth of
and diffusion tech
deep diffusion
for power
silicon nitrides and oxides, and epitaxial
semiconductor materials.
RL - 01-006
Completion date:
This is a con
tinuing program.
2-33
�The Zeta angle uersus time plot depicts the angular change the solar vector makes
with its projection on t o the orbital
plane during a one year period. The high
frequency variations are caused by orbital
regression while the
I cycle per year - variation is caused by the earths
inclination of
degrees.
the orbital
journey about the sun. The
plane referenced to the equator
2-34
low frequency -
for this plot
is 28.5
�Non-linear Magnetics Memory Research and Deuelopment
This research effort is inuolued uiith state-of-the-art studies of
mag
netic t h i n - f i l m memory materials and deuice techniques. Areas researched
include magnetic material
properties, techniques of
deposition, and the
deuelopment of aduanced memory systems.
RL ' 01-008
Completion date:
This is a con
tinuing program.
2 - 35
����I I I . ORGANIZATION PROFILE
The Space Support Division i s an operating unit of
the Sperry Rand Corporation as illustrated in
figure
the Sperry Group of
I . The division was
founded in Huntsvi11e. Alabama in 1965 t o support the National
and Space Administration. George C. Marshall
trionics Laboratory,
sion is
in all
Aeronaut i cs
Space Flight Center. 4s-
technical disciplines. The Space Support Divi
fulfilling i t s mission by designing and producing, to the exacting
requirements of
the Astr ionics Laboratory. many complex systems in support
of the Apollo Telescope Mount. Orbital Workshop and Saturn/Apo11o programs.
The division is also
furnishing spacecraft reliability and test engineering
services to the Goddard Space Flight Center.
recently signed with the Army Corps of
cation of
In addition, a contract UKJS
Engineers that requires the appli
aerospace technology to the tactical
facilities of
the SENTINEL
Anti-ballistic Missile System.
From July 1966 through June
1968 the Space Support Division
engineering services to the Jet Propulsion Laboratory
furnished
for the design of
spacecraft and spacecraft systems.
FACILITIES AND STAFFING
The staff of
the Space Support Division is currently at the level of
employees. This staff
facilities of
840
includes 600 employees working in direct support in
the Marshall
Space Flight Center (MSFC) Astrionics Laboratory
in Huntsville, Alabama. There are 235 employees working in direct support
of
the Goddard Space Flight Center
portion of
in Greenbelt. Maryland. 4 substantial
our employees are housed in Space Support Division
Huntsville, Alabama, consisting of
facilities in
three buildings containing 53.000 square
feet of floor space. These facilities provide administrative, engineering.
Iaboratory, and prototype manufacturing areas.
T h e e n g i n e e r i n g a r e a i n c l u d e s a we1 1 - e q u i p p e d
perimental
laboratory in which ex
and prototype models are developed and tested.
A Sperry Rand Corporation computation
Support Division engineering
facility is located near the Space
facilities. 4 Univac 1108 computer is avail
able t o support simulation requirements. data reduction, and budget and
payment records.
3-1
�I
I
I
I
I
�SPERRY RAND CORPORATION
SPEP.RY RAND
RESEARCH CENTER
UN I VAC D I V I S I O N
SPERRY MARINE AND ELECTRONICS
DIVISION
SPERRY FLIGHT SYSTEMS
DIVISION
SPERRY SYSTEMS MANAGEMENT
D I V I S I ON
SPERRY MARINE SYSTEMS
DIVISION
SPERRY GYROSCOPE
DI V131 ON
REMINGTON. RAND
DIVISION
FORD INSTRUMENT
DIVISION
NEW HOLLAND GROUP
SPACE SUPPORT
DIVISION
SPERRY ELECTRONIC TUBE
DIVISION
SPERRY MICROWAVE
ELECTRONICS D I V I S I O N
INTERNATIONAL OPERATIONS
CHAPT S
!O-25-:960
SPERRY RAND CORPORATION
Figure 1
REMINGTON ELECTRIC SHAVER
DIVISION
��-6nrSFER*Y RAND
Figure 2 . Space Support Division
�mBsSSm
NHBRHBHH
BBhBHHI
�ENGINEERING
Approximately half
of
our engineering employees
Alabama are engaged in on-site support of
remainder of
of
located
in Huntsuille.
the Astr i on i cs Laboratory. The
the Engineering Department employees occury 23.SOD square
the Space Support Division
scientific employees
facility. This staff
responsible
feet
includes engineering and
for study, deuelopment. t e s t and docu
mentation work related to Space Support Diuision programs. In engineering
design department provides design and drafting
groups. The engineering staff
fifty masters
for development engineering
includes two doctorate degrees, approximately
degrees, over two hundred bachelor degrees and over one
hundred associate degrees.
PAST PERFORMANCE
Sperry Rand Space Support Division
a technical
performance rating of
management rating of
for the past three years has achieved
excellent or better, and a technical
superior on support services contracts.
COST REDUCTION AND CONTROL
Sperry Rand Space Support Division i s currently involved in an effective
cost reduction program (ORBIT)
in which all
employees are consistently
urged to participate. This program meets the cost reduction guidelines as
set
f o r t h b y b o t h DOD a n d NASA. T h e
program is coordinated by an assigned
individual and is guided by an established procedural manual which complies
with both government and corporative guidelines.
its
inception, a gross savings of
In the 2 1/2 years since
$1,170,134 has been reported. Through
F e b r u a r y 2 8 . I 0 6 8 . 53 8 s u g g e s t i o n s h a v e b e e n s u b m i t t e d r e p r e s e n t i n g a n
employee participation of 66%.
PROJECT MANAGEMENT
The Space Support Division has developed a project management point-ofview as
the result of
i t s three and a half
years experience in support of
aerospace agencies and has evolved an organization geared to the achieve
ment of
project goals on time, within budget, and within predetermined
performance spec i f icat ions. The management techniques deueloped cover the
planning, control, and supervision of
engineering and design resources and
include the whole range of
systems engineering, project control, configu
ration and data management
t e s t , and procurement. The result is the inte
gration of
the several
functional departments of
management system. Each contracted task
the division into a
is assigned to a
total
project manager
who assumes complete responsibility and accountabiIity t o divisional man
agement ana to t h e customer
for successful accomplishment of the program.
3-4
��SECTION IV
SUMMARY
SPACE SUPPORT
��IV.
SUMMARY
The qualifications, f a c i l i t i e s , and capabiI i t i e s of
Support Division may be summarized as
PersonneI
840 total
FaciI ities
S p e r r y R a n d S pa c e
follows:
- of which 40 percent are engineers.
S3.000 square feet of modern well
equipped fa
cilities.
Qua I i t y
Dedicated by pol icy and
practice to the highest
attainable level of quality control
with the cost
enced
in
aspects
complying
consistent
of the program. Experi
with
DOD and N1SA q u a l i t y
specifications.
Control s
A modern
UNIVAC
1108
computer
is utilized in
the management of man-hours schedules and cost
control.
Experience
Proven
for
success
the
Marshall
on support
Astrionics
services
Laboratory,
Space Flight Center;
Jet
contracts
George
C.
Propulsion
Laboratory and Goddard Space F l i g h t Center.
Security
Secret
facility
Contract
clearance
aamin istratiue
granted
services
by
Defense
region,
At
lanta, Georgia
Cost Savings
Gross savings of si,170,134 in 2 1/2 years with
66 percent employee participation.
Additional ly, through the corporate policy of
the Space Support Division can draw on a l l
nical
consuI t a t i o n . manpower,
or
synergistic operations
corporate resources when tech
equipment are needed.
4-1
���•EBIQN . DEVELOPMENT* STUDIES •
ENGINEERING
RANGE
SUPPORT
INSTRUMENTATION
AUTOMATIC
CHECKOUT
GUIDANCE AND
CONTROL SYSTEMS
TELEMETRY
-0"
ELECTRONIC POWER
CONFIGURATION
-$•
SYSTEMS
MANAGEMENT
FLIGHT DYNAMICS AND SIMULATION
ELECTRICAL AND ELECTRONIC SYSTEMS
SPACE AND SATELLITE
COMMUNICATIONS
NAVIGATION SYSTEM ANALYSIS
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RELIABILITY
ANALYSIS
FABRICATION
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Saturn V Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
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Saturn V Collection
Description
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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sdsp_skyl_000070
Title
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"Sperry Rand Earth Orbital Workshop Capabilities" Brochure.
Creator
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Sperry Rand (Corporation)
Date
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1969-02-01
Temporal Coverage
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1965-1970
Subject
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Sperry Rand (Corporation)
Skylab Program
Apollo applications program
Space habitats
Saturn launch vehicles
Apollo Telescope Mount
Huntsville (Ala.)
George C. Marshall Space Flight Center. Astrionics Laboratory
Sperry Rand (Corporation). Space Support Division
Type
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Brochures
Still Image
Source
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Saturn V Collection
Box 30, Folder 18
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/202/14406/sdsp_skyl_000071_001.pdf
feb0b60f503128e7cbf3488baba5a2c0
PDF Text
Text
����This handbook was prepared by MDAC-W Logistics
Engineering, Orbital Workshop Training, as a
reference document for Skylab/Orbital Workshop
Systems orientation and familiarization briefings.
Use of this document in whole or in part for
other than general information or training reference
is not authorized.
Questions concerning the contents of this handbook
may be directed to:
R. W. Peak
A3-751, Mail Station #7
Extension 5532
II
��TABLE OF CONTENTS
_Page
SECTION I
SECTION II
SECTION III
IHE SKYLAB
Configuration
^
Mission Description
2
Mission Objectives
3
Apollo Command and Service Module (CSM)
7
Payload Shroud (PS)
12
Apollo Telescope Mount (AIM)
17
Multiple Docking Adapter (MDA)
21
Airlock Module (AM)
29
Instrument Unit (IU)
37
Orbital Workshop (CMS)
41
ORBITAL WORKSHOP SYSTEMS
Crew Accommodations
51
Habitability Support
63
Experiment Accommodations
75
Stowage
108
Electrical
H6
Atmosphere Control
126
Refrigeration
133
Ihruster Attitude Control
138
Data Acquisition
144
Communication
147
APPENDICES
Skylab Nomenclature
157
References
163
iii
�.
�SKYLAB ORIENTATION
CONFIGURATION
The Skylab consists of the Apollo Telescope Mount (AIM), which is also referred
to as the Solar Astronomy Array, and the Orbital Assembly Module.
The Orbital
Assembly Module (OAM) consists of the Multiple Docking Adapter (MDA), the
Airlock Module (AM) including the Fixed Airlock Shroud (FAS), the Instrument
Unit (IU), and the Orbital Workshop (OWS).
The Instrument Unit is nomallv
considered as part of the launch vehicle, but because of its function in pre
paring the Sky lab, it is here considered as part of the Orbital Assemblv Module.
The Apollo Applications Caimand and Service Modules (CSM) are not considered
part of the Skvlab, but when docked with the Skylab, the entire cluster is
referred to as the Orbital Assembly (OA).
The launch configuration for the Skylab (SL-1) mission consists of the following
o
Saturn 1C Stage
o
Saturn II Stage
o
Skylab
o
Payload Shroud
The launch configuration for the SL-2, SL-3, and the SL-U missions consist of
the following:
o
Saturn IB Stage
o
Saturn SIV-B Stage
o
Instrument Unit
o
Spacecraft Lunar Module Adapter (SLA)
o
Ccmmand and Service Modules
o
Launch Escape Assembly (LEA)
1
�MISSION DESCRIPTION
The Skylab Program consists of three earth orbit missions:
SL-1/2
SL-3, and
SL-u, and extends over a period of about eight months.
SL-1/2 Mission
•he first mission, SL-1/2, consists of two launches approximately one day
apart.
This mission is 28 days in duration.
The SL-1 vehicle uses a Saturn V Launch Vehicle to place the Sky lab in
oroit about the earth at approximately 250 miles.
After insertion, the
S-II Stage is separated by retrorockets, and the Sky lab is pitched downward bv instrument unit command to the Thruster Attitude Control System
(.ACS).
As the Skylab passes through nose-down attitude, the pavload
shroud is jettisoned.
"When the Skylab achieves retrograde
attitude, the
instrument unit conmands the deployment of the Apollo Telescope Mount (AIM),
and the orientation of the Skylab to a solar inertial attitude using the
TACS.
The solar inertial attitude, with the Skylab axially aligned in the
orbital plane, and the ATM solar cannister pointing directly at the sun,
is the primary attitude for all Skvlab missions except for CSM docking and
earth resources passes.
Af -er soiar inertial attitude has been acquired, the instrument unit
cormands deployment of the ATM and OWS solar arrays, and the OWS meteoroid
shield.
The ATM Control Moment Gyros (CMG) are activated at this time.
-ne
chicle uses a Saturn IB Launch Vehicle to orbit the Apollo CSM
and the Skvlab crew.
The Skylab is oriented to a rendezvous/earth
resources attitude, in which the ATM solar cannister continuouslv points
to the earth, and the CSM docks at the MDA axial docking port.
The crew
then transfers to the Skylab and activates the OA systems for on-orbit
activities.
2
�SL-3 Mission
The second Skylab mission consists of one launch, using a Saturn IB Launch
Vehicle, approximately 80 days after the SI^2 launch. The CSM rendezvous
and docking is identical to SL-2. This mission has a planned duration of
56 days.
SL-4 Mission
The final mission, SL-4, uses a Saturn IB Launch Vehicle. The launch
occurs approximately 103 days after the SL-3 launch.
The duration of this
mission is also scheduled for 56 days.
MISSION OBJECTIVES
Mission objectives for the three Skylab missions are as follows:
0
Establish an experimental space station in orbit
o
Operate the OA as a habitable space structure for long duration
missions of 28 to 56 days.
o
Obtain data for evaluating OA performance.
o
Obtain data for evaluation of astronaut nobility and work
capability for intra- and extravehicular activities.
0
Extend the duration of manned spaceflight.
o
Obtain biomedical data for evaluating the effects of zero-g
missions of 28 to 56 days on crew members.
o
Determine the feasibility and advisability of manned zero-g space
flights with durations greater than 56 davs.
0
Perform inflight experiments.
o
Obtain solar astronomy and stellar astronomy data in several
wavelengths to continue and extend studies beyond the limits of
terrestrial observations.
3
�o
Obtain data for the evaluation of extended weightlessness on man.
o
Obtain data for the development of operational procedures for
extended manned orbital operation.
o
Obtain engineering and technological data for development of
advanced space vehicles and equipment.
4
��/Vic
OOOOLAS
COMP4/VV
ORBITAL WORKSHOP
SA-413
SKYLAB ORBITAL ASSEMBLY CONFIGURATION
POSITION 111
OWS
+Z OA
+X ATM
12-16-70
ATM
SOLAR
POSITION I
OWS
-Z OA
+Z ATM
PS
(FIXED
ows
GENERAL NOTES
1) THE MDA/AM/OWS AXES POLARITIES ARE
THE SAME AS THOSE SHOWN FOR THE OA.
2) THE OA Y AND Z AXES POLARITIES FOR
DYNAMIC BODY AXES ARE THE REVERSE OF
THOSE SHOWN.
31 AN OA IS THE DOCKED CONFIGURATION OR
A CSM AND A SWS.
A) A SWS IS THE OWS/AM/MDA/ATM/PS/IU.
+Y ATM
+X CSM
OWS SOLAR
ARRAY
+Y OA
�APOLLO APPLICATIONS COMMAND AND SERVICE MODULE
The Apollo Corrmand and Service Module, while not part of the Skylab, is con
sidered along with the other modules as part of the Orbital Assembly (OA) when
docked in orbit.
The Conmand Module is the control center of the Apollo spacecraft, and contains
necessary automatic and manual equipment to control and monitor the spacecraft
systems.
It also contains the required
of the three-man crew.
equipment for the safety and comfort
The module is an irregular-shaped primary structure
encompassed by three heat shields, forming a truncated conic structure.
The
CM consists of a forward compartment, a crew compartment, and an aft compart
ment for equipment stowage.
feet in diameter at the base.
The module is approximately 12 feet long and 13
The forward compartment surrounds the forward
access tunnel which interfaces the Skylab MDA, and most of the equipment
stored in the forward compartment is earth landing (recovery) system (ELS)
equipment.
The crew compartment or inner structure is a sealed cabin with
pressurization maintained by the Environmental Control System (ECS).
The
compartment, protected by a heat shield, contains controls and displays for
operation of the spacecraft and spacecraft systems, crew couches and restraint
harness assemblies, window, crew equipment such as food and water, waste
management, and survival provisions.
The aft area compartment is encompassed
by the aft portion of the crew compartment heat shield, aft heat shield, and
aft portion of the primary structure.
This compartment provides reaction
control engines, the impact attenuation structure, instrunentation, and storage
tanks for water, fuel, oxidizer (RCS), and gaseous helium
The service module is a cylindrical structure about 13 feet long and 13 feet
in diameter.
The Service Module (SM) contains service and reaction
propulsion systems including their respective
control
propeHants, descent battery
pack, fuel cells, for power generation (and contingency water production),
and storage tanks for oxygen and hydrogen.
Both the command and service modules have been modified from previous Apollo
configurations to better meet the mission requirements
7
of the Skylab series.
�The ccnnvand and service modules are attached to the launch vehicle via a
Spacecraft Lunar Module Adapter (SLA) which is empty except for a stabilizing
device which provides structural support to the outer skin of the adapter. The
adapter is a truncated oone structure.
8
�/VTCDO/V/VELL
_ _
APOLLO COMMAND MODULE (CM)
4STWO/V4(/r/CS
SA-682
EXTERIOR
CO/MP4/VV
•Y
C
'5
-v
• Z
TOWER ATTACHMENT
(4 PLACES)
FORWARD HEAT SHIELD
(APEX COVER)
PITCH ENGINES
FORWARO VIEWING
(RENDEZVOUS)
WINDOWS
CREW
COMPARTMENT
HEAT SHIELD
S10E WINDOW
(2 PLACES)
WINDOW
ROLL ENGINES
ITYP)
�/VTCOO/V/VtLL
oo^i4s
—
CO/VTP/l/VV
—
C
SA-6R1
MG E N E R A L A R R A N G E M E N T
DOCKING PROBE
FWD ACCESS TUNNEL
MAIN CHUTE
DROGUE CHUTE
FWD COMPT BULKHEAD
LES TOWER ATTACH POINT
RCS PITCH ENGINES
INSULATION
SPACE
MAIN DISPLAY CONSOLE
ABLATIVE
MATERIAL
RENDEZVOUS WINDOW
SIDE HATCH
SS HONEYCOMB
AL HONEYCOMB
RCS ROLL ENGINES
AFT COMPT
(UNDERNEATH)
AREA
RCS YAW ENGINES
RCS PITCH ENGINES
POTABLE WATER TANK
ECS STEAM VENT
RCS
ROLL ENGINES
�MCDO/VA/ELL
DOUGLAS
APOLLO SERVICE MODULE (SM)
ASTnO/VAUTtCS
SA~683
COtV1F»/\r>i\'
RAOIAL BEAM TRUSS
(6 PLACES)
HELIUM TANK
FUEL TANK
PRESSURE
SYSTEM
PANEL
TANK
OXlQiZER
SERVICE
PROPULSION
ENGINE
FUEL TANK
SPS ENGINE
EXPANSION NOZZLE
SECTORS TOR viE •
AND 4 ARE S!>DECR£E SECTORS
ANO SARE :>0EGREE SECTORS
AN0 6 ARE WOECREE SECTORS
��PAYLOAD SHPOUD (PS)
The payload shroud provides an aerodynamic envelope for the ATM, MCA, and part
of the AM during boost phase of the mission.
loads during pre launch, launch, and boost.
PS/FAS interface.
It also provides support for ATM
These loads are transmitted to the
After orbital insertion, during the retrograde maneuver,
die payload shroud is separated into four quarter segments and jettisoned.
The configuration of the PS is basically a double angle nose cone assembly
mounted on a 22 foot diameter cylindrical section 30 feet long.
The nose cap
and forward cone are approximately 15 feet long.
Mild Detonation Fuse (MDF) is used to separate the payload shroud into four
quarter segments at IU command, and inflate a bellows assembly which provides
separation and jettison force.
Primary material in the payload shroud is aluninum.
13
�/Vf COO/V/Vf n
SKYLAB
O/W-3900
5-26-70
•6 rwo/VA(/ncs
LAUNCH CONFIGURATION
NOSE CONE
PAYLOAD SHROUD
APOLLO
TELESCOPE MOUNT
MULTIPLE
DOCKING ADAPTER
AIRLOCK MODULE
INSTRUMENT UNIT
SATURN V
LAUNCH
VEHICLE
S-IC
STAGE
ORBITAL
WORKSHOP
SATURN V
INTERSTAGE
SATURN I I
���APOLLO TELESCOPE MOUNT (ATM)
The Apollo telescope mount consists of a rack, experiment cannister, solar
array, Control and Display (CSD) ccnsole, and various support subsystems.
ATM provides the OA with:
o
Attitude control via the Control Moment Gyro (CMG) subsystem
o
Electrical pcwer for the ATM experiments via the solar array
o
Sharing of OA electrical loads with the OWS solar array system and
The
1he AM batteries.
The ATM is launched in a stowed position forward of the MDA axial port (#5),
and is deployed after orbital insertion by a motorized deployment mechanism
at IU corrmand.
After the AIM is locked into place, the solar arrays are
deployed at a subsequent command frcm the IU.
ATM Rack
The ATM rack is an octagonal structure approximately 11 feet across and
12 feet high, with a 14 foot diameter solar shield at one end, and four
truss type structural member's extending from four of the eight sides.
The rack is open in the center to accommodate the experiment cannister
and has attachment points for the solar array and most of the ATM sub
system equipment on the exterior of its sides and one end.
It is mounted
to the ATM deployment assembly (AIM-DA).
Experiment Cannister
The experiment cannister is a cylinder approximately 7 feet in diameter,
10 feet in length, and closed at both ends except for experiment viewing
doors.
It has a cruciform spar inside, to provide for experiment mounting.
The cannister is attached to the rack
by means of a two-degree-of-freedom
gimbal and roll mechanism called the Experiment Pointing Control System
(EPCS) which allcws more accurate pointing control than the OA attitude
control provides.
Some subsystem equipment is mounted on the MDA end of
the cannister.
17
�Solar Array
The ATM solar array is the electrical pcwer source for the ATM.
The am.'
consists of four wings covered with solar cells, and the means to deploy
them cn-orbit.
The wings are attached to the experiment end of the rack
perpendicular to the long axis of the OA, and their span is approximately
100 feet.
The four wings comprise 1200 square feet of generating area,
and have an average pcwer capability of approximately 3500 watts.
ATM Control and Display Console (CSD)
The ATM CSD console is located in the MDA and provides the crew interface
with the ATM experiments, attitude control and ATM subsystems.
A water
cooling system which consists of a water reservoir, three pimp modules and
a heat exchanger, provides cooling to the CSD panel.
interfaces with an AM coolant system.
The heat exchanger
The water cooling system also
supports the Earth Resources Experiment Package (EREP) experiments.
ATM Deployment Assembly (ATM-DA)
The ATM-DA provides structural support for the ATM during launch and
deployment capabilities on-orbit.
It also provides mounting facilities
or rendezvous lighting and antennas for the earth resources experiment
package (EREP) and burst noise monitor experiments.
The ATM-EA consists
of upper and lower tubular truss assemblies, and a rotation
system. The
truss assemblies are attached to the FAS on the airlock module, and
provide support for the ATM.
The deployment is accomplished by means of
the rotation system which consists of springs, reels, cable, gear trains,
and motors.
The entire system is redundant in case of failure.
18
�ZVICOO/V/VELL
oouglas
ORBITAL WORKSHOP
/\s-moisjAur-ics
o/w-srose
8—12—70
APOLLO TELESCOPE MOUNT
ATM SOLAR ARRAY WING NO. 3
ATM SOLAR ARRAY
WING NO. 2
ATM SOLAR ARRAY
FILM RETRIEVAL DOOR
ATM SOLAR ARRAY WING NO. 1
CONTROL MOMENT GYRO
(3 PLACES)
��MULTIPLE DOCKING ADAPTER (MDA)
The MDA is basically a double walled pressure vessel of cylindrical configuration,
approxinately 17 feet in length, and 10 feet in diameter.
Ihe MDA provides the OA with the following:
o
TV/o docking interfaces (port 5 axial; and port 3, radial) for the CSM.
Port 3 provides physical interface only.
Cluster systems interface
capabilities are provided at port 5 to allow integration of the docked
CSM with the Sky lab.
o
Interface between the CSM and the rest of the cluster for transfer of
personnel, equipment, pcwer, and other electrical signals.
o
Internal storage and operation of hardware and experiments launched
in the MDA.
o
Control and display capabilities for the ATM and TACS.
o
Vent control for the AM/MDA.
o
Storage vaults for ATM cameras and film,
o
Thermal control of the MDA interior.
o
Crew svstems:
o
A viewing window with cover.
lighting, ccrrmunication, mobilitv aids and restraints,
MDA Configuration
The MDA consists of a conical forward bulkhead assembly with an axial
docking port, an upper cylindrical section with a radial docking port,
and a lcwer cylindrical section.
The MDA is structurally cantilevered
from the AM and is designed to withstand launch loads, docking loads, onorbit stabilization maneuvers, and internal pressure loads.
21
�rvi<: oo /v /v n L I_
DO(/f.l4S
/isrwo/v/ii/r/cs
CO/VIP/l/VV
ORBITAL WORKSHOP
SA-414
MDA EXTERNAL STRUCTURE
12-16-70
AXIAL DOCKING PORT
DOCKING TARGET
HANDRAILS
PROTON
SPECTROMETER
ELECTRICAL CORDAGE &
EQUIPMENT TUNNEL
IR SPECTROMETER
WINDOW
COVER
S-190
WINDOW
SIGNAL
CONDITIONER
POWER
DISTRIBUTION
BOX (2)
DOCKING
RADIAL
i— METEOROID SHIELD
& RADIATOR (MDACI
SUPER
INSULATION
PURGE
TUBING
BARREL
SHELL
10-BAND
MULTISPECTAL
SCANNER
OWS
TUNNEL
(REF)
�A single window with cover is located above the radial docking port.
The
MDA has external handrails, docking targets, cable tunnels, running lights,
and provisions for mounting the radiators,
meteoroid shield, proton spec
trometer, and Earth Resources Experiment Package (EREP).
Thermal Control System
The MDA employs double-walled construction, with standoffs and stiffeners
between the walls, and insulation mounted on the exterior of the inner wall
for passive thermal control.
The aft position of the MDA exterior is
shielded against meteoroids by a standoff radiator,
has a meteoroid shield.
and the forward portion
A multilayer High-Performance Insulation (KPI)
blanket is placed between the MDA pressure skin and the radiator/meteoroid
shields and extends into the docking ports.
The external surface thermal coating is white paint.
with a white zinc oxide paint with a low ratio
The radiator
is coated
of solar absorptivity to
surface emissivity to provide additional passive thermal control.
Active thermal control is provided by 16 strip heaters mounted at 45 degree
intervals around the interior wall.
Eight 40 watt heaters are located in
the aft section and eight 20 watt heaters in the forward section.
A 15
watt heater is located on each of the two docking ports.
Venting System
The MDA venting system provides the capability of venting the AM and MDA
during ascent and orbital storage.
It consists of two vent valves, an
overboard vent line, and vent plugs for sealing the vent valve ducts.
The
two vent valves are located on a vent valve panel in the forward section
of the MDA.
These valves are motor driven, and are remotely operated by
the Digital Command System (DCS).
23
�Crew Systems
Internal lighting is provided by eight 10-watt fluorescent lamps, four of
which are located in the dene, and four of which are in the cylindrical
section.
Three Speaker Intercom Assemblies (SIA) are provided in the MDA, one on
the dome above the MDA windew, one on the cylinder wall near Experiment
M512, and one on the cylinder aft wall, opposite the windew.
Crewman restraints and mobility aids include handrails, attach points for
tether devices, and an AIM Control and Display Panel (CSD)(which provides
operational control and monitoring of the AIM and TACS) work platform.
Docking Provisions
The MDA provides docking capabilities at two locations.
The primarv
docking location is the axial port, which is located at the forward end
of the MDA and centered in the dcme.
The radial port is located on the
forward portion of the cylindrical section opposite the deploved ATM.
Both docking ports have standard Apollo drogues, docking rings, and utilize
15-watt heaters, pressure hatches, and docking targets.
The axial docking
port, hewever, is the only one which has provisions for the transfer of
electrical pewer, caimunications, and conditioned air.
The drogue assembly is a conical structure with provisions for mounting
in the docking tunnel forward of the pressure hatch.
accept the docking probe en the CSM.
It is designed to
The drogue can be removed from
either end of the docking tunnel.
Docking Port Hatch
The docking port hatch is a circular machined member which is hinged on
one side and incorporates the following provisions:
o
A pressure equalization valve which can be operated from
either side.
24
�MCO°^ELL
OOUG14S
/XSTffOfY/XOTfCS
COM p/xrw
ORBITAL WORKSHOP
SA-416
MDA INTERNAL VIEW (LEFT SIDE)
12-16-70
ATM C&D FOOT
RESTRAINT PLATFORM
C 0 2 ABSORBER CONTAINER
ELECTRICAL UMBILICAL
VENT PANEL
ATM
ELECTRICAL
CONNECTORS
AXIAL
DOCKING
TUNNEL
ECS FLEX
DUCT ASSY
FILM VAULT
NO. 3
10 BAND MULTISPECTRAL SCANNER
IR SPECTROMETER
(EREP)
�mm
/VTCDO/V/VfLL
ORBITAL WORKSHOP
OOt/Ct4S
asthofs/AUTICH
MDA INTERNAL VIEW (RIGHT SIDE)
corvi pa/vy
FILM VAULT NO. 1
SA-417
12-16-70
SUB2A &
FILM VAULT NO. 4
M512/479
M479
CONTAINER
UTILITY OUTLET
M512 FOOT
RESTRAINTS
WINDOW
VAULT
NO. 2
�o
A differential pressure indicator on both sides of the hatch.
o
A latching handle on both sides of the hatch permitting opening
and closing from either side of the hatch.
o
Six, over center, positive locking, latching mechanisms.
Docking Aids
Docking aids are provided to facilitate final rendezvous maneuvers and
docking of the CSM to the Sky lab.
A set of docking lights located about the periphery of the dome area
provide visual orientation for rendezvous maneuvers.
controlled by DCS ccrmtand.
These lights are
A docking target, consisting of a circular
field and a standoff cross, illuninated by fluorescent paint and electro
luminescent disks, is provided for alignment of the probe and drogue
during docking.
27
��AIRLOCK MODULE (AM)
The Airlock Module (AM) is basically two double walled cylindrical pressure
vessels stacked together.
The overall length of the airlock module is approxi
mately 17 feet, the diameter of the large cylindrical section is about 10 feet,
and that of the smaller section is about 5 feet.
Included here is the Fixed Airlock Shroud (FAS) which interfaces the OWS, and
provides structural support for the MDA, AIM, and AM.
It is a cylinder,
approximately 22 feet in diameter, and 7 feet long.
The AM is situated between the MDA and OWS, and contains systems for environ
mental control, instrumentation, electrical power, communications, and operational
management for the OA.
It also provides a lock compartment, hatch, and support
systems for extravehicular activities (EVA).
Operational management is provided for OA systems by means of control and
display consoles (CSD), and a Digital Command System (DCS) for ground control
of Skylab systems.
The AM provides the OA with the following:
o
Conditioning, management, and distribution of electrical power for
the MDA, OWS, and CSM.
o
Management and control for paralleling the AM and ATM electrical
power systems.
o
Environmental control of the OA atmosphere.
o
Nitrogen storage and controls for the OA atmospheric supplies
(Nitrogen—N^, and Oxygen—0^).
o
Accumulation and conditioning of 0AM housekeeping, vehicle status,
and experiment data for real-time transmission to the Manned Spaceflight
Network (MSFN).
29
�Airlock Module
�o
Tape recording and storage of data for delayed transmission to the
MSB!.
o
OAM DCS link with the MSFN for system control frcm the ground.
o
Transmitters, receivers, and controls for the OAM data link with
the MSFN.
o
Transport equipment for traversing ATM film magazines frcm the EVA
hatch area to the AIM work stations.
o
Audio-visual alert system for OAM caution and warning indications.
o
Cluster intercommunications via the CSM for voice transmission to
the MSFN.
o
Hard copy message reception frcm the MSFN via teleprinter.
o
Life supporting oxygen, cooling, and communications for crew EVA.
o
Experiment installations and controls.
Equipment installation for systems performing listed functions is accomplished
by mounting modules on the AM tunnel and its trusses, and within the AM.
The lock compartment allows EVA without interrupting crew or systems operations
in the pressurized sections on either side of the lock.
Airlock Configuration
The AM consists of four major structural components, and the fixed airlock
shroud.
The major components are:
o
The Structural Transition Section (STS)
o
The tunnel assembly
o
The flexible tunnel extension
o
The airlock truss assemblies (4)
31
�The £M is attached to the MDA at the forward end of the STS, and to the OWS via
the flexible tunnel extension and the fixed airlock shroud. The truss assemblies
attach to the FAS at each axis.
Structural Transition Section (STS)
The STS provides structural transition from the 10 foot diameter MEA to the
5 foot diameter -AM tunnel assembly. The STS is a welded aluninun pressurized
cylinder approximately 46 inches long and 120 inches in diameter, of stressed
skin, semi-monocoque construction.
The STS bulkhead provides the transition from 120 inch diameter to 65 inch
diameter to mate with the tunnel assembly. The bulkhead, along with the tunnel
shear webs, provides shear continuity of the PM and redistributes loads to the
AM support truss assemblies.
Four double pane glass viewing ports are provided for visibility. Each window
is protected when not in use by an external movable cover assembly which is
actuated from inside the STS by the crew.
The covers serve to minimize meteoroid
impacts on the glass and heat losses from the cabin area.
AM Radiator Assembly
Tne AM radiator serves as a meteoroid shield for the MDA and STS in addition
to its primary function as a heat radiator to space.
The radiator consists of panels containing fluid paths which are supported three
inches outside the vehicle pressure skin. The coolant paths are connected to
the PM coolant loop. The radiator is constructed mostly of magnesiun alloy,
and extends virtually the entire length of the AM.
AM Tunnel Assembly
The tunnel assembly is a 65 inch diameter, 153 inch long cylinder of aluninun,
semi-monocoque construction. The tunnel is internally divided into three
sections bv two bulkheads equipped with hatches. These are the forward
compartment, the center or lock compartment, and the aft compartment.
32
�tVtC OO/V/VL'LL
AIRLOCK MODULE
OOUCI/1S
/I STFtOM/X
LJr/cs
SA -418A
INTERNAL VIEW LEFT SIDE
corvif/xrvv
ELECTRICAL PWR SYSTEM
INSTR. AND COMM.
UTILITY OUTLET NO. 1
ENVIRONMENTAL CONT.SYS.
EPS CAUTION &WARNIN
MOLLSIEVE 0 2 SUPPLY
LTG CAUTION & WARNING
MOLE. SI EVE A VENT VALVE
co
CO
CIRCUIT BREAKER (RIGHT
BUS DI ST. SCHEMATIC
PCG CONTROL SCHEMATIC
AFT COMPT VENT VALVE
AFT HATCH
CIRCUIT BREAKER (LEFT)
CIRCUIT BREAKER (CENTER)
FORWARD HATCH
�/V1CDO/V/VCLL
AIRLOCK MODULE
DOUG1.4S
4ST#?0/V4l/r/CS
SA -419A
INTERNAL VIEW RIGHT SIDE
corvif»j\rsiY
MOLE SI EVE VALVES AND
UTILITY OUTLET
O 2 /N 2 CONTROL SYSTEM
CONTROL PANEL
LCG SYS RESERVOIR
PR VLV
CONT PANEL
COOLANT FLOW CABIN
HEAT EXCHANGER VALVES
NO. 1 CONT PANa
EVA HATCH
COMPT CONT PANa
LOCK DEPRESS VLV
EVA NO. 2 CONTROL PANEL
COMPT CONT PANa
t
FWD
�Forward Compartment
The forward compartment mates to the STS and includes a cabin relief valve and
provisions for stowage containers, tape recorders, and miscellaneous equipment.
It is approximately 65 inches in diameter, and 31 inches in length.
Lock Ccmpartment
The center or lock ccmpartment is approximately 80 inches long, and includes a
Gemini type crew hatch for ingress/egress during EVA.
The lock ccmpartment is sealed frcm the rest of the Skylab during EVA by two
internal hatches.
These are circular machinings with radial stiffeners and
each has a dual pane windew which permits viewing the lock ccmpartment frcm
both forward and aft compartments.
Each hatch is equipped with a latching
mechanism which is actuated by rotating a handle.
The aft hatch can be detached
frcm its hinge by removing two quick release pins, and then be re-instailed at
the flexible tunnel extension to isolate the OWS frcm the rest of the Skylab
during "contingency mode" operations.
The EVA hatch is a titanium structure of conical section configuration like those
used in the Gemini missions.
The hatch is latched or unlatched by the rotation
of a handle on the interior of the hatch.
The EVA hatch is equipped with a dual pane viewing window which enables viewing
of the aft portion of the EVA quadrant.
Aft Ccmpartment
Hie aft compartment is approximately 42 inches long and provides a recessed
housing t o s u p p o r t 0/W t h e r m a l c o n t r o l system h e a t exchanger f a n s .
The a f t
ccmpartment also houses the controls for the (W1 Thermal Control System (TCS),
and the
recharge station which is associated with one of the experiments.
35
�Flexible Tunnel Extension Assembly (Bellows)
A metallic convolute flexible bellows approximately a foot long, and having an
internal diameter of about three and one-half feet, joins the AM to the OWS
forward dome.
The tunnel extension provides continuitv of the pressurized
passageway from the AM to the OWS.
It is attached to the AM and OWS prior to
launch and allcws relative deflection between the AM and OWS with minimum load
transfer.
A fiberglas laminate shield mounted inside the bellcws protects it
from damage during equipment and crew transfer through the bellows.
AM Support Truss Assemblies
Four truss assemblies are used to attach the AM to the FAS.
These are located
at ninety degree intervals around the AM, and are indexed to the reference axes.
The trusses are constructed of fusion welded aluminum tubes.
Machined fittings
are used at the attach points to the tunnel and FAS.
In addition to their primary function of attaching the AM to the FAS, and
strengthening the assembly, the truss assemblies support batterv modules (2),
and gaseous nitrogen (GN2) spheres (4).
Fixed Airlock Shroud
The Fixed Airlock Shroud (FAS) is a cylindrical structure approximately 7 feet
long and 22 feet in diameter.
It provides structural support for the ATM, AM,
MDA, and PS during the launch phase of the mission.
It also supports six
cylindrical gaseous oxygen (GO^) tanks and provides attachment points for two
discone antennas for OAM DCS and data canmunication. Five spherical GN? tanks
mounted in the FAS provide pressurdzation gas for the OWS water tanks, and
atmospheric supply.
36
�INSTRUMENT UNIT
The instrument unit is an unpressurized, cylindrical load-supporting structure
of honeycomb sandwich construction.
It is approximately 22 feet in diameter,
and 3 feet long, and it is located between the Fixed Airlock Shroud (FAS) and
•the OWS forward skirt.
The instrument unit is normally considered to be part of the launch vehicle,
but because of its location, and the role it plays in the orbital preparation
of the Skvlab, it is considered here as part of the OAM.
Mounted on the internal wall of the instrument unit are items of equipment
which comprise electrical and mechanical systems which guide, control, and
monitor vehicle performance from liftoff for approximately 7 hours.
Included
among these systems are guidance and control, measurement and telemetry,
tracking, IU command, and electrical systems.
The IU commands the following
orbital functions of the 0AM:
o
Skylab maneuver to retrograde following S-II separation,
o
Payload Shroud (PS) jettison during retrograde maneuver,
o
Apollo Telescope Mount (AIM) deployment,
o
Acquisition of solar inertial attitude,
o
OWS and AIM solar array deployment,
o
OWS meteoroid shield deployment,
o
ATM Control Moment Gyro (CMG) activation,
o
0AM systems activation,
o
0AM venting and pressurizing,
o
TACS command transfer to DCS.
After accomplishing the listed functions, the IU batteries expire, and the IU
has no further function during the Skylab mission.
37
��SA-502
1-11-71
ORBITAL WORKSHOP
/VfCDO/V/VCLL
DOUGLAS
INSTRUMENT UNIT
4STW0/V4iyncs
corvif/xrw
FLIGHT CONTROL COMPUTER
LAUNCH VEHICLE DATA ADAPTER
C-BAND ANTENNA
$
•VHFTLM
ANT
ACCESS DOOR
AZUSA ANTENNA
i / COMMAND
ANTENNA
HEAT EXCHANGERSUBLIMATOR
UMBILICAL
��ORBITAL WORKSHOP (OWS)
The OWS is a modified third stage of the Saturn V Launch Vehicle (SIV-B Stage).
The Liquid Hydrogen (LHj) fuel tank has been converted into crew living and
working quarters, and the Liquid Oxygen (LOj) oxidizer tank has been utilized
as a plenun area for waste matter.
The propulsion and propellant feed systems,
auxiliary propulsion system, and supporting hardware have been removed, and
certain structural modifications accomplished for the conversion.
The exterior of the CMS is fitted with a deployable meteoroid shield, a solar
power array system (SAS), a radiator
for the refrigeration system, two rings
of gaseous nitrogen (GN2) spheres for Hie thruster attitude control system, and
two thruster modules.
The meteoroid shield is deployed on-orbit and protects
the OWS against meteoroid penetrations.
The SAS wing assemblies are also
deployed on-orbit, and provide a source of electrical power to the 0AM.
The
refrigeration system radiator is mounted in a fixed position to the thrust
structure on the aft end of the OWS and is used to radiate heat absorbed by
the OWS refrigeration system.
The GN2 bottles store gas for use in the TACS
which maintains attitude control of the Skylab prior to CMG activation, and
supplements the CMG system after it has assumed primary control.
The OWS is divided into two major areas, the habitation area, and the waste
tank.
These areas are separated by the cannon bulkhead that separates the fuel
frcm the oxidizer portions of the SIV-B propellant tank.
During Hie Skylab mission, the crew will inhabit the living and working quarters
of the OWS, and perform many of the experiments required to meet Hie established
mission objectives.
The OWS provides the OA with the following:
o
OWS crew quarters in which the crew can live, and perform experiments
requisite to mission success.
o
Habitability support system, which includes the capabilities of food,
water, and waste management, personal hygiene, sleep accommodations,
and trash management.
41
��o
Stowage provisions for all equipment and consumables which are part
of the OWS.
o
Electrical power from the SAS, distribution, and control, and illumina
tion of both interior habitable areas, and exterior (running lights).
o
Atmosphere control of the OWS interior for pressure, ventilation, and
heating.
o
Refrigeration of food, water, and experimental samples.
o
Thruster attitude control of the cluster prior to activation of the
CMG system, and as backup to the C15G system.
o
Data acquisition for housekeeping, experiment data and vehicle/systerns
status, for telemetry and on-board display.
o
Corrmunications facilities among the various elements of the cluster,
television, telecommunications, and on-board caution and warning
indications.
o
A crew viewing window for observation and experiment support.
o
Scientific airlocks to support extravehicular experiment requirements.
o
On-board accommodations and support systems for experiment packages.
OWS Configuration
The Skylab OWS consists of a Saturn V SIV-B propellant tank assembly, forward
and aft skirts, thrust structure, and aft interstage.
The aft interstage
separates with the S-II stage, and is not considered to be part of the OWS
after launch.
Habitation Area
The habitation area is divided into the forward compartment, which is used
primarily as a storage and work area, and the crew quarters, which are the
living and operating areas for the crew on-orbit.
43
A third area, located between
��the crew quarters and the waste tank is used as a plenun for the ventilation
control system, and is accessible to the crew.
The forward compartment floor consists of an eight inch beam structure sand
wiched between triangular grid sections. The grid pattern is typical of that
used throughout "the OWS, and facilitates crew mobility.
The beam structure is
attached to the wall,and includes a large hexagonal opening in its center to
allow crew and equipment movement between the forward ocmpartment and the crew
quarters. TV;o smaller openings are provided in the floor above the sleep
compartment to allow emergency egress of the crew quarters.
The crew quarters floor is similar to the forward compartment floor but has an
aluriinum sheet on the underside, tcward the plenun area, and waste tank.
The
floor has three openings similar to those in the floor of the forward compart
ment.
The large opening provides access to the trash airlock, and the smaller
openings provide access to the plenum area.
The trash airlock is used for the
disposal of waste matter.
Forward Ccmpartment
Initial entry to the OWS from the AM is made through a hatch located at the
apex of the dcme in the forward compartment. The hatch is a reusable circular
machining curved to conform to the radius of the forward done.
It contains a
pressure equalization valve, and redundant check valves and operating handles
which are used to open the hatch from either side.
Ten water tanks are installed around the wall of the forward compartment.
tank has a capacity of approximately 50 gallons.
tanks are 25 stowage containers.
Each
Located just above the water
Stewed in these 25 containers are waste
management, personal hygiene, photographic, and maintenance equipment.
Various
stowage lockers and experiment equipment are also installed on the floor. The
two scientific airlocks are located in the wall of the forward compartment 180
degrees apart. These airlocks are used in the performance of various experiments
which involve exposure to space.
45
�Crew Quarters
The OWS crew quarters contain the sleep compartment, waste management compart
ment, wardroom, and experiment compartment.
These compartments provide areas
in which the crew can conduct their normal daily activities, as well as special
experiment tasks.
The sleep compartment furnishes sleeping and communication
equicment for each of the three crewmen.
The waste management compartment
provides toilet and personal hygiene facilities.
The wardroom provides storage
and preparation facilities for food, recreational facilities such as games and
television, communications, and a viewing window for observation and experimental
photography.
The wardroom also includes provisions for temporarv stowage of
trash.
Waste Tank
Ihe waste tank is the L02 portion of the SIV-B propellant tank assemblv from
which the propellant utilization probes, chilldcwn punps, and other support
hardware have been removed.
It is located irrmediately aft of the crew quarters
floor/plenum area, and shares the common bulkhead with the habitation area.
The trash airlock provides access to the waste tank from the crew quarters.
A
large mesh screen installed in the tank prevents trash from clogging the liquid
dump probe inlets and prevents trash and liquids from clogging or escaping
through the vent ducts.
Saturn V Skirts
Hie forward skirt is a cylindrical structure of the same diameter as the OWS
(approximately 22 feet), and approximately 10 feet in length.
It is located
between the Instrument Unit (IU) and the OWS habitation area wall.
Equicment mounted on the interior wall of Hie forward skirt is used during
launch and for telemetry throughout the mission.
Hie Solar Array System (SAS)
is attached to the forward skirt from which it hinges and deploys.
shield forward torsion arms are also supported by He forward skirt.
46
The metecroia
�/MCOO/V/VELL
DOUOL4f
——
CO*fP4/VK
CREW QUARTERS
COMPARTMENT
FWD DOMESCIENTIFIC
AIRLOCKS (2)
METEOROID
SHIELD
ORBITAL WORKSHOP
TANK ASSEMBLY, SKIRTS AND INTERSTAGE
FORWARD
SKIRT
REUSABLE
HATCH
HPI
FEED THRU (3)
VIEWING
WINDOW
INTERNAL
INSULATIONSAS
(RETRACTED)-
SIDE ACCESS PANEL
?2?72O
OWS REQUIREMENTS
STRUCTURE ASSEMBLY WILL WITHSTAND ALL
PRESSURE. PRIMARY BODY, THERMAL, AND
DYNAMIC LOADS
LEAKAGE (WHEN PRESSURIZED TO OWS
ENVIRONMENT PRESSURE): LESS THAN
5 LBS MASS PER DAY
METEOROID PROTECTIVE SHIELDING (INCLUDING
TANK STRUCTURE) TO BE EQUIVALENT OF 1.4? CM
OF 2024-T6 ALUMINUM
REUSABLE HATCH - 40" IN DIAMETER
AFT SKIRT
SIDE ACCESS PANEL - 35 X 52 INCHES
THRUST STRUCTURE
VIEWING WINDOW - APPROX 18" DIAM
25° 55' FROM POS III TOWARD POS II
AFT DOME
AFT INTERSTAGE
�The aft skirt is a cylindrical structure approximately 22 feet in diameter,
and approximately 7 feet long.
wall and the aft interstage.
It is located between the OWS habitation area
It supports the TACS thrusters and nrovides
support for the aft portion of the SAS, and the rear torsion arms of the
meteoroid shield.
Solar Array System (SAS)
Tne SAS consists of two wing assemblies which are attached to the OWS forward
skirt and deployed on-orbit out of beam fairings on opposite sides of the OWS.
Each wing assembly consists of:
o
Forward fairing assembly
o
Beam fairing assembly
o
Three wing section assemblies
o
SAS deployment system
Ihe wing assemblies are permanently attached to the forward skirt through the
forward fairing assembly.
The beam fairing assemblies are attached to the
forward fairing assemblies by machined hinge fittings.
The hinges are oriented
in such a way that the wing sections can be deployed in planes parallel to the
plane of the AIM experiment cannister.
The forward fairing assembly is a box
beam type structure which extends the length of the forward skirt, and houses
the deployment mechanism and hinge which interfaces the beam fairing.
Tne beam fairing is also basically a box beam structure which extends the
length of the OWS habitation area.
4 feet wide by 1 foot deep.
It is approximately 37 feet in length, and
The beam fairing houses the stowed SAS wing
sections during the launch phase of the mission.
Ihe wing assembly has three wing sections that are deployed out of the beam
fairing on-orbit.
Each wing section contains ten solar cell panels, a duimy
solar cell panel, a truss type panel, and two parallel stabilizing beans.
Ihe truss type panel is fastened to the beam fairing and to the dunny Danel.
The dunrnv panel is in turn fastened to the first of the ten active solar cell
panels.
All the panels are hinged together and folded accordion style into
the beam fairing until deployment.
Each panel is approximately 10 feet bv
2 feet, and is connected bv swivel fittings to the stabilizing beams.
48
�The parallel stabilizing beams each consist of seven truss type structures.
These beam sections contain the swivel fittings to which the solar cell panels
attach, and spring lock mechanisms which engage when the wing sections are
fullv deployed to hold the wing sections in that position.
The solar array system is capable of being oompletely deployed fran a stowed
position within 4 minutes.
Deployment of the SAS is automatic and completed
within the IU lifetime and prior to excessive discharging of the OAM batteries.
Primary control is from the IU programmer, with backup capabilitv fran the OAM
DCS.
The SAS is deployed in two stages which are initiated by Exploding Bridge-
Wire (EBW) firing units.
The first stage is the deployment of the beam fairing.
An interlock assures that the beam fairing is completely deployed before the
command is given to deploy the wing sections.
If the IU fails to deploy either
the beam fairing or the wing sections, the OAM DCS would be used to deplov the
SAS by ground conmand.
Meteoroid Shield
The meteoroid shield protects the CMS against penetration bv meteoroids during
a typical mission.
The shield is an aluninum sheet which encompasses the
exterior of the habitation area over the length of the cylindrical section of
the OWS.
It forms a cylinder that is concentric to the tank and when deployed
is spaced approximately 5 inches frcm the tank wall.
During ground handling
and launch the shield is held retracted against the tank wall.
The excess
shield material is retained in hinged panels which fold on themselves oermitting proper retraction to the smaller diameter.
The interior of the shield
is coated with teflon to allcw even distribution of preload forces around the
tank circunference.
The meteoroid shield is deployed on-orbit subsequent to SAS deolovment.
The
shield is deployed at IU conmand when the SAS has been fully deploved.
Ordnance trains initiated bv EBW firing units release tension straps, and
preload torsion arms complete the deployment.
Meteoroid shield boots of
preformed metal fingers close the forward and aft portions of the shield
after deployment.
49
�Thrust Structure
The OWS thrust structure is cone shaped, and mounted aft of the waste tank.
On Saturn flights, it is used to support the J-2 engine and to transmit engine
thrust to the fuel tank wall.
On the CWS, the thrust structure is used to
support the Thruster Attitude Control System (TACS) nitrogen spheres, the
pneunatic control sphere, the sphere meteoroid shield, and the refrigeration
system radiator.
The sphere meteoroid shield performs the same task as the
OWS meteoroid shield, protecting the TACS and pneunatic control spheres from
penetration by meteoroids can-orbit.
Refrigeration System Radiator
The refrigeration
system radiator is an irregular octagon shaped aluminun
structure attached to the OWS thrust structure at the engine mount.
The
radiator surface is slightly inclined from the CWS centerline to prevent the
sun's rays from striking the radiator surface while the Sky lab is in the solar
inertial attitude.
The surface is coated with zinc oxide.
The radiator contains cooling loops containing a refrigerant
room and food storage freezers, refrigerator,
and water chiller.
50
to cool the ward
urine freezer, urine chiller,
�ORBITAL WORKSHOP SYSTEMS
Ten major functional and structural systems are provided in the OWS vehicle to
establish a safe and habitable astronaut living area and facilitate planned
experimental operations while the OWS is on-ort>it.
o
Crew accommodations
o
Habitability support
o
Experiment accommodations
o
Stowage
o
Electrical
o
Atmosphere control
o
Refrigeration
o
Thruster attitude control
o
Data acquisition
o
Communication.
These systems are:
Crew Accommodations
The OWS crew accommodations system consists of equipment which:
o
Provides compartments for crew habitation and operational activites.
o
Aids crew mobility and restraint,
o
Supports crew safety.
Compartmentizaticn
Ihe crew quarters are divided into four compartments:
sleep compart
ment, waste management compartment, wardroom, and experiment compart
ment.
Access to each compartment is provided by openings to the experiment
compartment.
only.
A door is installed for the waste management compartment
A folded curtain is provided at the wardroom entrance.
The
curtain is constructed of aluminum coated mvlar, sandwiched between
two layers of Armalon fabric.
51
�~EU
DOl,CMS
ASTftO/V/XL/TiCS
corvif*/\tw
ORBITAL WORKSHOP
ORBITAL ASSEMBLY CREW STATION LOCATIONS
-
O/W-5278
4-14-70
©
FORWARD DOME
@
EXPERIMENT COMPARTMENT
@
FORWARD COMPARTMENT
©
SLEEP COMPARTMENT
©
WARD ROOM
©
WASTE MANAGEMENT COMPARTMENT
©
AFT COMPARTMENT
�/VfCOOIVWll
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ORBITAL WORKSHOP
O/W-7835
6-16-70
ASTrfO/V/XL/TICS
corvtpaMY
FORWARD COMPARTMENT
VENTILATION CONTROL
PQS II
VENTILATION CONTROL SYSTEM
DUCT 1
UTILITY
POS III
+Z
POS I
-Z
SPEAKER
INTERCOM
ASSEMBLY
UTILITY
OUTLETS
SAL
OUTLETS
SCIENTIFIC
AIRLOCK
OUTLETS
WC = WATER CONTAINER
�/VTCDO/ViVELL
ORBITAL WORKSHOP
001/GL4S
4STffOlV4yr/CS
CO/MP4/VK
CREW QUARTERS INSTALLATIONS
0/W-802D
5—26—70
SLEEP COMPARTMENT
WASTE MANAGEMENT COMPARTMENT
M131
CHAIR
WARDROOM
CONTROL
M131
STOWAGE
CONTAINER
M507
GRAVITY
SUBSTITUTE
WORK
BENCH
ROTATING
CHAIR
EXPERIMENT
COMPARTMENT
ELECTRICAL POWER
CONTROL CONSOLE
M171 GAS
ANALYZER
M171 HELMET STOWAGE
M092 LBNPO
m
�Fixed Astronaut Aids
Fixed astronaut aids consist of handrails, handholds, and the central
handrail.
The waste management ccmpartment ceiling handrail extends from the
doorway to the outboard wall of the ccmpartment.
The forward compart
ment handrails consist of a series of six handrails of various lengths
which extend vertically in the forward compartment, and a series of
three handrails which extend circunferentially around the floor of the
forward compartment about five feet from the floor.
The forward dome
handrails consist of a series of five handrails of various lengths
which extend circumferentially around the forward dome interior, and
a series of three segmented vertical handrails which extend frcm the
vicinity of the access hatch handrail, to the forward circumferential
wire cover above the water tank support structure.
The access handrail
consists of two circular segments which are concentric with the access
hatch.
The aft ccmpartment (plenum) handrail is a straight handrail
located on the aft side of the crew quarters floor.
The central
handrail is of irregular hexagonal cross-section, and extends from
the access hatch to the crew quarters ceiling.
It can be removed and
stowed during experimental operations in the forward compartment.
Portable Astronaut Aids
Portable astronaut aids consist of portable handholds, portable foot
restraints, portable pressure suit foot restraints, and detachable
tethers.
The portable astronaut aids attach to the standard triangular
grid pattern and can be used wherever open grid is available.
Crew Safety Provisions
Crew safety provisions include the meteoroid shield which is deploved
around the circumference of the OWS habitation area, fire protection
from three Apollo extinguishers, and utilization of stringent design
requirements regarding flammabilitv of materials used in the OWS, and
contamination control which is furnished by utilization of stringent
toxicity and outgassing requirements in the design of OWS equipment.
55
�rv?CDorv/vEi-L
oooct^s
4sr»OA//u;r/cs
CO/MP/l/VV
m.,-,.
M
ORBITAL WORKSHOP
_ _ _
«
ASTRONAUT AIDS
o/w-104
9—2—70
FWD DOME VERTICAL
HANDRAILS
CENTRAL HANDRAIL
ACCESS HATCH
CIRCULAR HANDRAIL
FWD DOME
CIRCUMFERENTIAL
HANDRAILS/HAND
HOLDS
MID FORWARD
COMPARTMENT
CIRCUMFERENTIAL
HANDRAILS
FWD COMPARTMENT
VERTICAL HANDRAILS
(3 PLACES IN LINE WITH
DOME HANDRAILS)
HEAD CEILING
HANDRAIL
�/VT CDO/V/VELI.
DOJ7GL4S
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ORBITAL WORKSHOP
ASTRONAUT AIDS
PORTABLE HANDHOLD
O/W-75
9-10-70
3
REF. 1B77067
��Orbital Maintenance Provisions
Orbital maintenance provisions consist of orbital spares, an orbital tool
kit, and an OWS repair kit.
The orbital spares list defines those items of replaceable equipment
deemed pertinent to orbital maintenance activities, such as switches,
lamps, filter elements, and seals.
The orbital tool kit contains common hand tools which will be useful to
the crew in the performance of orbital maintenance and spares replacement.
All tools are equipped with tether rings, and bits are furnished with
velcro patches so they may be applied to velcro pile during use.
The OWS repair kit is provided for the orbital repair of air ducts,
curtains, filters, and tank wall punctures.
59
�rvicoory/ryjELL
DOUGLAS
ASTf*OFSJAUT!CS
ORBITAL WORKSHOP
SA-290
12-2-70
MAINTENANCE
corvt f*AWY
REQUIREMENTS
TOOL KIT
SOCKETS. DRIVERS & RATCHETS
DRIVER HANDLES & ADAPTERS
TOOL TETHERS
LOOSE HAND TOOLS
REPAIR KIT
METEOROIO REPAIR EQUIPMENT
VELCRO (ON ORBIT APPLICATION
SCISSORS
SPARES
O'RING & SEALS
LIGHTS, FANS & FILTERS
COMM BOX'S
HEATERS
ELECTRONIC COMPONENTS
LIQUID DUMP PROBE
& HEATER
WATER DISPENSER & VALVE
�/VFCDO/V/VELL
DOI/G/.4S
Asrwo/v/iiyr/cs
CO/V*EVI/V v
ORBITAL WORKSHOP
REPAIR KIT
O/W-5836
10 - 14 " 70
WRIST TETHER
SCISSORS
MYSTIC TAPE
VELCRO STRIPS
(60 YDS PILE &
HOOK)
METEOROID
PATCHES
9 REQ'D
REF. 1B80508
��Habitability Support System
The Habitability Support System (HSS) consists of subsystems and equipment
which manage metabolic waste, and accommodate the crew for sustenance,
health, personal hygiene, and comfort.
The habitability support system includes:
o
Waste management subsystem
o
Water management subsystem
o
Food management subsystem
o
Personal hygiene subsystem
o
Sleep compartment equipment
o
Trash disposal subsystem
Waste Management Subsystem (WMS)
The waste management subsystem provides the equipment necessarv for
safe, effective and hygienic collection, processing, storage, return
and or disposal of feces, urine, and vcmitus waste products for three
OWS crewmen.
The UMS also provides for the collection and disposal
of debris and free water from the OWS atmosphere.
Waste product samples are processed for return by mass determination
and either freezing, or vacuum drying, and stored in special containers
for transfer to the command module at the end of the mission.
A portable vacuun cleaner is used to collect and retain particulate
matter and free water from any area within the OWS.
Water Management Subsystem
The OWS water management subsystem provides potable water to the OWS
crew quarters (WMC and wardroom) for consumption, personal hygiene,
and housekeeping.
The water management subsystem consists of water storage, distribution,
microbiological control, and dispensing equipment.
63
�ORBITAL WORKSHOP
ABILITY SUPPORT SY
HABITABILITY
SYSTEM
EQUIPMENT LOCATION
/VTCDO/WEtL
coivfpaniv
HT
SLEEP RESTRAINTS
PRIVACY PARTITION & CURTAINS
GENERAL PURPOSE TISSUE/UTILITY WIPE DISPENSER
STOWAGE LOCKERS & EQUIPMENT
TRASH CONTAINERS
SLEEP
COMPARTMENT
WASTE
MANAGEMENT
COMPARTMENT
WARD ROOM
• FECAL/URINE COLLECTION MODULES
• WASTE PROCESSOR
• URINE FREEZER
• COLLECTION BAG DISPENSERS
• STOWAGE LOCKERS & EQUIPMENT
• COLLECTION BAGS
• GENERAL PURPOSE TISSUE/UTILITY WIPE DISPENSER
• SPONGE SQUEEZER
• VACUUM CLEANER
• TRASH BAG CONTAINER
• TOWEL AND WASHCLOTH DRYING
• WMC WATER MODULE
• PERSONAL HYGIENE EQUIPMENT
• PROCESSED COLLECTION BAG CONTAINER
• TOWEL & WASH CLOTH DISPENSERS
• FOOD FREEZERS/REFRIGERATOR
• GALLEY
• FOOD PREPARATION TABLE
• FOOD MANAGEMENT RESTRAINTS
• FOOD TRAYS
• WATER CHILLER & HEATER
• WARD ROOM WATER MODULE
• GENERAL PURPOSE TISSUE/UTILITY WIPE DISPENSER
• TRASH BAG CONTAINER
• STOWAGE LOCKERS & EQUIPMENT
• WRITING DESK
�/WCOO/V/V£T£.JL
oouct-as
ASTftO/VAUTiCS
COSVf F»A/V V
ORBITAL WORKSHOP
WASTE MANAGEMENT SUBSYSTEM
SA-307
12-2-70
REQUIREMENTS
PROVIDE FOR COLLECTION, MASS
D E T E R M I N A T I O N , PROCESSING. A N D S T O R A G E
OF FECES A N D V O M I T
PROVIDE FOR COLLECTION, MASS AND/OR
S A M P L E D E T E R M I N A T I O N , DISPOSAL A N D / O R
PR O C E S S I N G , A N D S T O R A G E O F U R I N E
SAMPLES
WASTE
PROCESSORS
o
<-n
URINE DUMP
COMPARTMENT
P R E C L U D E M I X I N G A N D CROSS
C O N T A M I N A T I O N B E T W E E N CREW M E M B E R S
CONTROLS
AND
DISPLAYS
PROVIDE FOR TRANSFERRING OF
PROCESSED A N D I D E N T I F I E D SAMPLES
TO THE CM FOR RETURN TO EARTH FOR
ANALYSIS
URINE
FREEZER
FECAL BAG
DISPENSER
SPECIMEN
RETURN
PROVISIONS
CONTROLS & DISPLAYS
• WMC B L O W E R
• WASTE PROCESSORS
• DUMP HEATERS
PROVIDE FOR COLLECTION,
DEACTIVATION AND/OR PROCESSING,
S T O R A G E A N D / O R DISPOSAL O F D E B R I S
AND FREE WATER
FECAL/URINE
COLLECTOR
URINE VOLUME
DETERMINATION
URINE BA6
DIS P E NS E R
URINE
DUMP
SYSTEM
SYSTEM OPERATION
PROCESSOR
HEATER TEMP
POWER
AVERAGE
PEAK
A T M O S P H E R E LOSS
FECAL/URJNE COLLECTOR
3 URINE CHILLER DRAWERS
BLOWER MOTOR
AIR FLOW
POWER ( A V E )
140°F
30 WATTS
60 W A T T S
.33 L B / D A Y
1 1 .4 C F M
84 WATTS
�—
DOUGLAS
ASTffOISJAUTICS
ORBITAL WORKSHOP
HSS WASTE MANAGEMENT COMPARTMENT
n™
O/W-2183B I
8-28-70
corviF*Arv\r
VACUUM CLEANER LOCKER
SPECIMEN
MASS
MEASUREMENT
DEVICE
S
ECS VENT
WATER
MODULE
URINE BAG
HOLDING AREA
URINE BAG
DISPENSER
AND SAMPLE
TRAY ON-ORBIT
STORAGE
URINE FREEZER
URINE CHILLER
FECAL/URINE
COLLECTOR
STANDARD
STORAGE
LOCKER
�/WCOO/V/VELL
DOUGLAS
ASLffOfS/AUrtCS
COrvif*Afy/vr
ORBITAL W O R K S H O P
SA-296
12-2-70
WATER SYSTEM
REQUIREMENTS
6.000 LBS MAXIMUM
WATER WEIGHT
MEASUREMENT OF WATER
A M / O W S GAS
DRINKING
% OZ + 1X INCREMENTS
FOOD RECONSTITUTE
'A OZ (FROM 1 TO 6 OZ)
+ 1% INCREMENTS
INTERFACE —
WATER
TANKS (11) —
GAS PRESS
PANEL
PORTAILE
TANK LAUNCH
WARDROOM
LOCATION
TAILE —
• CHILLER
• HEATER
• DISPENSERS
WATER
PURIFICATION
EQUIPMENT
DRINK DISPENSERS (3)
40+5°F
FOOD RECONSTITUTION
DISPENSER (1)
40+5°F
FOOD RECONSTITUTION
DISPENSER (1)
150+5°F
PERSONAL HYGIENE
DISPENSER (1)
125+5°F
PORTABLE WATER TANK
28 LBS MINIMUM
IODINE USED AS BI0CI0E
2 TO 12 MG/L STORAGE
2 TO 6 MG/L CONSUMPTION
IODINE MONITORING
2 TO 18 MG/L
SYSTEM OPERATION
WASTE
MANAGEMENT
COMPARTMENT
• HEATER
• DISPENSERS
WATER TANKS (10)
600 LBS MINIMUM
FLEX METAL BELLOWS
GN 2 PRESSURE SYSTEM
35+2 PSIG
WATER HEATER VOLUME (2)
4.0 LBS NOMINAL
CONTROL
WATER CHILLER VOLUME
5.9 LBS NOMINAL
DISPLAY
WATER PRESSURE
35+f
• WRORM H20
PORTABLE TANK VOLUME
24 LBS WATER
PORTABLE TANK PRESSURE
11 TO 40 PSIG
IODINE STORAGE/INJECTION
1 2 + Kl
WATER SAMPLE/
STARCH REAGENT/
VISUAL COMPARISON
• CLOTH
SQUEEZER
D U M P PRESS M E T E R
• WRORM H20
DUMP HEATER CONTROL
• WMC H 2 0
D U M P PRESS M E T E R
• WMC H 2 0 OUMP
HEATER CONTROL
W A T E R OUMP L I N E S
(WASTE T A N K )
IOOINE MONITOR
5
PSIG
�Water is stored in ten stainless steel water tanks located around the
forward section of the forward compartment.
approximately 500 gallons.
Total storage capacity is
Each water tank has a stainless steel
bellows enclosed in the shell which is used to pressurize the contents
from a common manifold connected to all of the ten tanks, and an
agitator pimp which aids in the distribution of biocide throughout the
tank.
In addition to the ten tanks mounted in the forward compartment, the
CWS is equipped with a portable water tank of approximately 3 gallons
capacity.
Water conditioning and dispensing equipment is located in the wardroom
and in the waste management compartment.
The wardrccm eauipment con
sists of a water heater and a water chiller which condition the water
for reconstitution
of foods and drinking.
The waste management
equipment consists of a heater which conditions the water for body
cleansing and general housekeeping.
Appropriate dispensing equipment
is located in each of the two compartments for the controlled dispen
sation of water for these purposes.
Microbiological control of the OWS water supply begins with prelaunch
installation of processed water that meets stringent purity specifica
tions, and is continued on-orbit by periodic monitoring and addition
of iodine solution.
Food Management Subsystem
The CWS food management subsystem provides the equipment and supdies
required for storage, preparation, and consunption of the food supply
for three men for 140 days.
refrigerator,
Among this equipment are food freezers,
stowage containers, a galley, heaters, table, and
restraints.
One of the food freezers is located in the wardroom, and the other is
located in the forward compartment.
ments of 100 pounds capacity each.
68
They contain five freezer compart
�/MCDO/V/VELL
DOI/CL4S
ASTRO/V4(/r/CS
CO/VIP4/VV
FOOD FREEZERS (3)
ORBITAL WORKSHOP
FOOD MANAGEMENT SYSTEM
FOOD
STORAGE
CONTAINERS (11)
SA-304
12-2-70
REQUIREMENTS
11 FOOD STOWAGE CONTAINERS (CANNED)
2,200 LB
88 FT 3 (20 X 22 X 30 EACH)
OWS ENVIRONMENTAL PRESSURE
OWS ENVIRONMENTAL TEMP 40° - 80°F
FOOD CHILLER
o
•o
FOOD
FREEZERS (2)
FOOD TABLE
GALLEY
PROVISIONS
5 FOOD FREEZERS
(3) FORWARD COMPARTMENT, (2) WARD ROOM
23 DAY/EACH FREEZER
17 X 13 X 16.5
1.75 FT3 EACH/8.75 FT3 TOTAL
50.4 POUNDS EACH/252 POUNDS TOTAL
TEMPERATURE — 10 ± 10°F
OWS ENVIRONMENTAL PRESSURE
INTERNAL COOLANT LOOP
1 FOOD CHILLER
(1) WARDROOM
56 DAY CAPACITY
17 X 13 X 16.5
1.75 FT3 REQUIRED/54.4 LB
OWS ENVIRONMENTAL PRESSURE
45 + 0° - 12°F
GALLEY PROVISIONS
STORAGE FOR FOOD STORAGE OVERCANS
STORAGE FOR AVERAGE PACKAGES
STORAGE OF FOOD TRAYS
CAN OPENER, TRASH CONTAINER
FOOD TABLE
FOOD TRAYS - OPERATION & HEATING
FOOD MGMT RESTRAINTS
�ORBITAL WORKSHOP
UTILIZE FOOD PREPARATION TABLE,
FOOD MGT RESTRAINTS & FOOD HEATERS
/MCOO/V/VtLL
DOUGLAS
AfTirOA/4miC»
COMP4/VV
0/W-4280 A
4—^0—70
WINDOW
STANDARD
STORAGE LOCKERS
THIGH RESTRAINT
IXED
FOOT RESTRAINTS
REFRIGERATOR/
FREEZERS
�The food chiller, colocated with the wardroom freezer, stores 100 pounds
of refrigerated food and beverage.
The food stowage containers provide space for unrefrigerated food.
There are eleven of these stowage containers, which are located in the
forward compartment.
The galley provides for stowage of a seven day supply of food cannisters,
stowage for empty cannisters, a can opener, general purpose restraints,
food trays, covers, and utensils.
General purpose tissue-utilitv wipe
dispensers are also provided in the OWS galley.
The food table and restraints
provide the means for three crewmen to
simultaneously consume food in an efficient and comfortable manner.
The table also contains elements of the water management subsystem.
The table base contains the water heater, water chiller, water dispensers,
and personal dental hygiene equipment.
to a game table, or writing desk.
The table top is convertible
The,thigh restraints
are adjustable
for various sizes, and can be folded against the table base when not
in use.
Personal Hygiene Subsystem
The personal hygiene subsystem, in conjunction with the VMC water
equipment, provides for maintenance of skin health, personal cleanli
ness, and grooming, including total body cleansing, dental hygiene,
shaving, nail and hair clipping.
Included in the personal hygiene subsystem are towel and washcloth
dispensers, holders, general purpose tissue and utility wipe dispensers,
a mirror, a sponge/washcloth squeezer, and toothbrush stowage
containers.
Personal hygiene kits for each crewman are included as
government furnished equipment.
These kits contain hairbrush, nail
clippers, tooth brush, and such individually-used items of equipment.
71
�rvtCDOHHEi-LDOUGL/XH
/\STf*OrsJ/\VTiCS
ORBITAL WORKSHOP
PERSONAL HYGIENE EQUIPMENT
SA-288
12-2-70
COtvtF»/\r>j\r
TOWEL & WASH CLOTH DRYING
TISSUE/WIPE DISPENSER
TOWEL/WASH
CLOTH STORAGE
MIRROR
TISSUE/WIPE DISPENSER - 3 PLACES
WATER MODULE
TOWEL & WASH CLOTH DISPENSER
INDIVIDUAL
PERSONAL
HYGIENE
EQUIPMENT
--4
NJ
PERSONAL HYGIENE EQUIPMENT
INDIVIDUAL PERSONAL HYGIENE EQUIPMENT
GFE KITS—(15) 28 DAYKITS „
12 FT 3 EACH-TOTAL 1.80 FT 3
TOOTH BRUSH
STOWAGE - 3 PLACES
COMMON PERSONAL HYGIENE EQUIPMENT
TOWELS (120) 8. DISPENSER
WASH CLOTHS (840) & DISPENSER
TOOTH BRUSH STOWAGE CONTAINERS (3)
TOWEL & WASH CLOTH DRYING
EQUIPMENT (3 EACH)
SOAP (55 BARS) & SOAP DISPENSERS
MIRROR (1)
GENERAL PURPOSE TISSUES (4200)
8> WIPES (3500) AND DISPENSERS
WASH WATER BAGS (22)
HYGIENE WATER MODULE
�/VTCDO/V/VCLt.
DO«yGl4S
xisrwo/v/iur/cs
COfVIF»/\/VY
ORBITAL WORKSHOP
PERSONAL HYGIENE EQUIPMENT
O/W-9754-1
9-12-70
IRROR
TOWa AND WASH
CLOTH D I S P E N S E R
WATER
MODULE
CO
INDIVIDUAL
PERSONAL
HYGIENE KITS
GENERAL P U R P O S E
TISSUES
�/VtCOO/V/VCi.£.
DOUGLAS
SLEEP COMPARTMENT EQUIPMENT
A STF?OM/\CJTICS
SA-299A
5-19-71
COrV1F>/\MY
CREW PREFERENCE KIT
TRIANGLE SHOES
ONAL CURTAIN
LOCATION
LIGHT
BAFFEL
(3 PLACES)
STOWED POSITION
SLEEP RESTRAINT
(TYPICAL 3
CORNER
LOCKER
SLEEP
RESTRAINT
EQUIPMENT
TRASH CONTAINER
TRASH
CLOTHING STORAGE
PRIVACY PARTITION
PRIVACY CURTAINS
�Sleep Compartment Equipment
The sleep compartment equipment consists of crew sleep restraints,
a
privacy partition, and three privacy curtains.
Thirty sleep restraints
will be supplied for the entire mission, to
provide positive restraint of the crewmen during sleep.
One privacy
curtain is provided for each of the three individual sleep areas, to
provide visual separation and light control.
The privacy partition
separates two sleep areas in the sleep compartment, two lockers
separate the third..
The privacy partition provides
visual separation
and acts as a light barrier.
Trash Disposal Subsystem
The OWS trash disposal subsystem consists of the equipment and
supplies required
to manage the trash generated by three crewmen
during the 140 days of programmed mission duration.
This equipment
includes trash bags, a trash airlock and stowage provisions for trash
in the waste tank.
The trash bags are vented teflon containers of approximately cylindrical
configuration.
The trash bags are equipped with self closures which
seal the bags when full.
The trash airlock, located in the hexagonal opening in the center of
the crew quarters floor, provides for the expulsion of packaged trash
into the waste tank area for stowage.
It consists of a chamber,
inboard and outboard hatches, and a trash ejector which expels the
trash into the waste tank.
Experiment Accommodations
The OWS experiment accommodations include the necessary mounting,
electrical, gas, vacuim, and data collection requirements for the opera
tion of experiments which are installed and operated in the OWS.
experiments are divided into three categories:
75
The
�—
DOUGLAS
4STffO(V4l/nCS
coiMP4«r
ORBITAL WORKSHOP
SA-295
12-2-70
TRASH DISPOSAL SUBSYSTEM
REQUIREMENTS
GENERAL PURPOSE
TRASH BAG LOCATIONS*
FWD COMPARTMENT (1)
WARDROOM (1)
W. M. COMPARTMENT (1)
SLEEP COMPARTMENT (3)
EXPERIMENT (1)
DISPOSAL OF WET MATERIAL
DISPOSAL OF DRY MATERIAL
DISPOSAL FROM ORBITAL ASSY
DISPOSAL SHALL BE MADE
IN WASTE TANK
HABITABILITY AREA TO BE KEPT
FREE OF AGENTS THAT COULD
PROMOTE BACTERIAL GROWTH
AND UNDESIRABLE ODORS
TRASH BAG USAGE
(140 DAYS)
GENERAL PURPOSE BAG
SLEEP COMPARTMENT
WMC
WARDROOM
EXPERIMENT
FWD COMPARTMENT
MISC
URINE
TRASH AIRLOCK
TRASH DUMP AREA
CONTINGENCY
60
140
140
10
10
22
382
38
TOTAL
420
URINE TRASH BAG (WMC)
URINE POOLING
FOOD OVER CANS
SLEEP RESTRAINT
MISC
*RESUPPLY LOCATED NEAR EACH
USING LOCATION
CONTINGENCY
TOTAL
140
140
9
28
317
_32
349
�/VfCDO/V/VELL
ORBITAL WORKSHOP
DOUGLAS
ASTBOMAUTiCS
EXP. NO.
O/W-3974
6-7-71
EXPERIMENT PROVISIONS
CO/VlfA/VY
EXPERIMENT TITLE
M071
MINERAL BALANCE (HSS)
M073
BIOASSAY OF BODY FLUIDS (HSS)
M074
M092
EXP, NO,
EXPERIMENT TITLE
M509
ASTRONAUT MANEUVERING
EQUIPMENT
SPECIMEN MASS MEASUREMENT
SOW
UV STELLAR ASTRONOMY
INFLIGHT LOWER BODY
NEGATIVE PRESSURE
S020
UV/X-RAY SOLAR PHOTOGRAPHY
S063
UVAIRGLOW HORIZON PHOTOGRAPHY
M093
VECTORCARDIOGRAM
S073
GEGENSCHEIN/ZODIACAL LIGHT
M131
HUMAN VESTIBULAR FUNCTION
S149
PARTICLE COLLECTION
M133
SLEEP MONITORING
S183
UV PANORAMA
M151
TIME AND MOTION STUDY
T003
INFLIGHT AEROSOL ANALYSIS
M171
METABOLIC ACTIVITY
TOD
CREW/VEHICLE DISTURBANCE
M172
BODY MASS MEASUREMENT
T020
ESS
EXPERIMENT SUPPORT SYSTEM
FOOT CONTROLLED MANEUVERING
UNIT
T025
CORONAGRAPH CONTAMINATION
MEASUREMENT
T027
ATM CONTAMINATION MEASUREMENT
�MCDOMlVEU.
DOUG14S
4sr(?o»4iyrics
COMPANY
ORBITAL WORKSHOP
EXPERIMENT COMPARTMENT
o/w-5394
6-2-70
POS IV
CONTROL CONSOLE
SPEAKER INTERCOM
ASSEMBLY
UTILITY
OUTLETS
UTILITY OUTLETS
�o
Biomedical
o
Scientific
o
Technological and operational
Biomedical Experiments
The biomedical experiments to be performed in the OWS have a
general objective to determine the effects of extended weightlessness
and confinement in space on the three crewmen associated with each
mission.
Among these experiments are:
Experiment Support System (ESS)
The experiment support system is basically a console which contains
a power panel and an experiment control panel, and provides
support to several of the detailed biomedical experiments by
switching and distributing power, and providing control, display,
signal conditioning, and data management.
Inflight Lower Body Negative Pressure (LBNP) M092
The LBNP experiment reduces pressure to the lower portion of the
crewman's body to evaluate the cardiovascular deconditioning as
a function of time in a zero-g environment.
The device is basically
a tank into which the crewman is inserted to the waist, which has
an overboard vent system which can be controlled to reduce pressure
in the tank.
The crewman's temperature, blood pressure, leg volume,
and pulse are measured while the crewman is in the LBNP, and these
data are displayed on the ESS console and/or recorded for telemetrv.
Power is from the ESS console.
Vectorcardiogram (VCG) MO93
The vectorcardiogram experiment measures changes in the electrical
activity of the heart to determine the relationship of these
changes to prolonged exposure of the crew to weightless environment
79
�ORBITAL WORKSHOP
EXPERIMENT ACCOMMODATIONS CDR
EXPERIMENT SUPPORT SYSTEM (ESS)
"A7::::R
POWER
Ml 31
ROTATING CHAIR
CONTROL CONSOLE
DATA
M093
VCG
VEST
HARNESS
POWER
& DATA
0/W-7075A
9 8 70
M171
ERGOMETER
DATA
POWER
& DATA
MOTOR
BASE
BUS 1
POWER
POWER
& DATA
POWER (OWS)
DISTRIBUTION
PANEL
POWER
& DATA
M092:
LBNP
BLOOD PRESS. ASSEM
LEG VOLUME
PLETHYSMOGRAPHS
DATA
DATA
M171:
METABOLIC
ANALYZER
HI LEVEL
MULTIPLEXER
PCM
INTERFACE
BOX
�MCDO^/VELL
DOUGLAS
flSTPOMUT/CS
COMPANY
ORBITAL WORKSHOP
EXPERIMENT ACCOMMODATIONS CDR
EXPERIMENT - M092
INFLIGHT LOWER BODY NEGATIVE PRESSURE
O/W-7050
9-2-70
M171 EAR CANAL TEMPERATURE PROBE
(TEMPERATURE)
M093 VCG
BJA.
B. P. DATA
1
BUS 1
|Cj
^
LEG VOLUME
PLETHYSMOGRAPHS
ESS
(CONSOL
IDATED)
SERVICES
28 VOC POWER
LEG VOLUME DATA
l
r
l
LBNP DATA
POWER
I
. !
LBNPVACUUM
ows
BUS 2 |
SAFETY CUTOFF
SWITCH
r
i
1
AM DATA
SYSTEM
[
J
�DOI/GL4S
«rBov4ur,cS
co/vrp/i»v
ORBITAL WORKSHOP
SA-302
12-2-70
VACUUM S YST E M - EX P E RIM E N TS
METABOLIC ACTIVITY EXPERIMENT
REQUIREMENTS
PROVIDE VACUUM FOR
STARTING ION PUMP
VENT FOR GAS SAMPLE
OVERBOARD RELIEF FOR METHANE
(CALIBRATION GAS)
SYSTEM OPERATION
EXPERIMENT NO. M171
METABOLIC ACTIVITY
EXPERIMENT NO. M092
INFLIGHT LOWER BODY
NEGATIVE PRESSURE
VACUUM
VALVE
VENTED DIRECTLY
OVERBOARD
1 " VACUUM LINE WITH
ISOLATION VALVE
1 / 4 " METHANE RELIEF
LINE
INFLIGHT LOWER BODY NEGATIVE
PRESSURE
VACUUM LINE
METHANE VENT
LINE
REQUIREMENTS
PROVIDE VACUUM FOR
EXPERIMENT
VENT 0.141 POUNOS PER
MINUTE WITH INTERFACE
PRESSURE 2.8PSIA
SYSTEM OPERATION
VENTS DIRECTLY OVERBOARD
1 " VACUUM LINE WITH
ISOLATION VALVE
�MCDO/V/VfLL
DOUGLAS
ASTfrO/VAUTICS
COMPA/VV
ORBITAL WORKSHOP
EXPERIMENT ACCOMMODATIONS CDR
EXPERIMENT - M093
VECTORCARDIOGRAM
O.WS POWER
VOICE
DATA
SYSTEM
BEFORE
(RESTING)
DURING
(EXERCISE)
OPERATIONAL CONFIGURATION
AFTER
(RESTING) fl
O/W-7052
9-8-70
�and other stress conditions associated with spaceflight.
The
vectorcardiogram experiment is supported for pcwer, control, and
data management by the ESS console.
The ergcmeter frcm Experiment
M171 (metabolic activity) is used during the vectorcardiogram
experiment.
Experiment data will be recorded for telemetry, and/or
displayed on the VCG panel.
Human Vestibular Function M131
The human vestibular function experiment is conducted to determine
man's susceptibility to motion sickness, and his ability to adapt
to disorientation as a result of subgravity and other effects
which could be encountered during spaceflight.
The subject is seated in a rotating litter chair and required to
make verbal reports and perform head movements, to determine
symptoms and display judgment ability of spatial coordinates based
upon gravity receptor and visual clues.
Data is recorded and
telemetered, for both static and rotating cases.
The ESS provides
telemetry interface for this experiment, which has its cwn control
and display panel.
Sleep Monitoring M133
The sleep monitoring experiment is designed to evaluate sleep
quantity and quality by using automatic on-board analysis of the
Electro-Encephalographic (EEG), Electro-Oculographic (EOG) and head
movement activities of cne crewman subject.
It has been demonstrated that disrupted patterns of sleep are
associated with modified performance.
It has also been demonstrated
that changes in waveforms of brain activity are associated with the
transition frcm wakefulness to deep sleep.
Seven stages of sleep
activity have been defined, and individual requirements for each
stage have been established.
84
�/VtCOO/V/VELL
OOfCLAS
4STWOA/41/T/CS
corvtf/XMY
ORBITAL WORKSHOP
EXPERIMENT ACCOMMODATIONS CDR
EXPERIMENT - M131
HUMAN VESTIBULAR FUNCTION
O/W-7054
9-8-70
OTOLITH TEST GOGGLES
BITEBOARD
EMERGENCY
ST0PBITEBOARD
GOGGLE
CONTROL
°A°
CONSOLE
STORAGE
CO
Cn
EXPERIMENT
SUPPORT
SYSTEM
i
[CONTROLMNSOLE
DATA CABLE
1
FRONT
CONTROL FOR
BITEBOARD
VARYING
INTERNAL HORIZON
AM
DATA
POINTER AND SPHERE READOUT DEVICE
SYSTEM
CALIBRATED POINTER
ANGLE DISPLAY
DATA
POWER
'7
HEADSET
OBSERVER
SUBJECT
//
BASE AND DRIVE MOTOR
WITH N2 BOTTLE INSIDE COVER
COMM
SYSTEM
*
POINTER
MAGNETS
TOP VIEW
BOLTED TO CHAIR
ROTATING
LITTER CHAIR
SPHERE
HAND MAGNET
SPHERE HOLDER
(STRAP-ON)
�/Vf COO/V/VELL
DOI/GL4S
/\STf*OHI/\UTICS
CO/VIP/I/VV
ORBITAL WORKSHOP
EXPERIMENT - M171
METABOLIC COST OF INFLIGHT TASK
O/W-7056A
9-10-70
�/VfCOO/V/VELL
ORBITAL WORKSHOP
DOUGLAS
ASTRONAUTICS
EXPERIMENT M133
CON! RANT
SLEEP MONITORING
MINIATURE
CONNECTOR
VELCRO CLOSURE
ASSEMBLY
2
-
ACCELEROMETER/PREAMPLIFIER
Ml3
3 SLEEP MONITORING
CO
ELECTRODE STATUS
FRONT
CAPtl/B
'
TAPE RECORDER
SiejECT GAIN
ASSEMBLY
1 -
ELECTRODE SELECT
fii'.HI
EEG
LETT EEGv^^N.
CAP
ASSEMBLY
3
-
PANEL ASSEMBLE
�A cap assembly will be utilized to gain EEG and EOS data, and an
accelercmeter/preamplifier assembly mounted on the top of the cap
will obtain head movement data.
Changes in the frequency and amplitude of EEG waveforms, occurrence
of bursts of rapid eye movements (KEM's) associated with dreaming,
and head movement activity will be monitored and recorded on the
data tape recorders for subsequent transmission to the MSFN, to
provide investigators with essential information for planning the
work/sleep cycle for extended space missions.
Time and Motion Study M151
Experiment M151 will determine through analysis of film, the effective
ness with which crewmen perform inflight tasks compared with their
effectiveness in performing the same tasks during preflight zero-g
and neutral buoyancy training.
The GFE provided to accomplish this experiment includes 16mm Maurer
data acquisition cameras (DAC's), Skylab Universal camera mount,
high intensity photo lamps, power cable, auxiliary lenses, film
vault and film.
Tasks which will be filmed as part of the time and motion study will
include translation activities, the ingress and egress of confined
enclosures in the OWS, mounting and operation of the bicycle ergometer, operation of the SAL, donning and doffing of the pressure
garment assembly, periodic maintenance activities, food preparation,
oonsunption and measurement of residue,
related
and experimental activities
to M092, M509, T027, M171 and M074.
Metabolic Activity M171
The primary objective of the metabolic activity experiment is to
determine if man's metabolic effectiveness in doing mechanical work
is progressively altered by exposure to the space environment; and
to determine the metabolic cost of identical activities when man
is deprived of the benefits of earth gravity as canpared to the
88
�cost on earth.
Secondary objectives of the experiment are to
evaluate ground-based reduced gravity simulators, and to evaluate
the bicycle ergometer as an exerciser for long duration spaceflight
missions.
Elements of other experiments are used in conjunction
with the M171 equipment to measure the subject crewman's temperature,
vectorcardiogram, blood pressure, food consumption, and body mass.
The metabolic analyzer which forms part of the M171 equipment
determines oxygen consumption, carbon dioxide (CO,,) production,
and respiration volume during the experimental activity.
Data
related to this experiment will be recorded for telemetry, and the
activity will be photographed as part of another experiment (M151—
Time and Motion).
The ESS provides pcwer control, visual displays,
and telemetry interfaces for this experiment.
Mass Measurement (EMMD and SMMD) M07H and M172
TWo inertial pendulum measuring devices consisting of platforms
mounted on springs, with counting devices are furnished as means
of en-orbit mass determinations of waste and food samples, and crew
members' body masses in zero-g environment.
The sample/body is
placed on a platform, released, and the oscillations about an
equilibrium point are counted.
These oscillations can be related
to the mass of the object by calibration of the measurement devices.
These experiments are self contained except for power requirements.
Data is hand logged, and no telemetry is required.
Scientific Experiments
The scientific experiments to be performed in the OWS have a general
objective of providing researchers with multispectral photographic
data of stellar fields, micrometeoroid distribution data, contamination
data cn the induced atmosphere about the orbiting Skylab, and the
contamination on exposed optical elements.
These experiments consist of packages which are exposed to space via
the two scientific airlocks mounted in the wall of the OWS in the for
ward compartment.
Among the scientific experiments performed in the
OWS are the following:
89
�MCDO/V(VtLl
DOUC145
ASTRONAUTICS
COMPANY
ORBITAL WORKSHOP
EXPERIMENT - M172
BODY MASS MEASUREMENT DEVICE
O/W-7058A
5-20-70
ELECT. POWER
OPERATIONAL CONFIGURATION
READ OUT
§
mm
PERIOD SENSOR
�MCOO/V/VELL
DOUGLAS
ASTRONAUTICS
COMPANY
ORBITAL WORKSHOP
EXPERIMENT ACCOMMODATIONS CDR
EXPERIMENT - S019
UV STELLAR ASTRONOMY
O/W-7087A
9-2-70
SPECTROGRAPH ASSEMBLED TO THE
ARTICULATED MIRROR (IN SAL)
MIRROR SYSTEM EXTENDED
(EXTENDED)
SCIENTIFIC AIRLOCK (SAL)
TILT
(RETRACTED)
MIRROR SYSTEM
— ROTATION
OPTICAL CANISTER
FILM CANISTER
�Ultraviolet (UV) Stellar Astronany S019
This package consists basically of a spectrograph with a tele
scope sight, and an articulated mirror system with controls for
extension, retraction, tilt, and rotation of the mirror.
This
equipment will be used to photograph approximately 50 star fields
for studies of the UV line spectra and spectra energy distribu
tions of early type stars, and to obtain UV spectra for a nunber
of stars in the Milky Way.
X-Ray/UV Solar Photography SO20
This experiment also consists of a spectrograph camera, and a
sighting device, and will be used to photograph the sun during
quiescent and flare periods.
A flare notification device which
will signal crew members of solar flare activity will be provided.
The spectrograph camera will be mounted in the Sunside Scientific
Airlock (SAL).
During the performance of this experiment, the
vehicle must be held stationary, and no dumping will be accom
plished.
After the completion of this experiment, the film
cannister will be stored in the film vault.
Telemetrv of house
keeping data is required along with hand logging for this
experiment.
UV Airglcw Horizon Photography S063
This package consists of two cameras, and supporting equipment
which will be employed to photograph the earth's ozone layers,
and twilight airglcw at UV and visible wavelengths.
The ozone
layer photography will be accomplished during Earth Resources
Experiment Passes (EREP) when the sunside SAL will be pointing
at the earth.
For horizon airglcw photography, the vehicle will
be in the solar inertial attitude, and on the dark side of the
orbit.
Exposure data and time of performance will be voice
recorded for telemetry.
92
�/MCOO/V/VCLL
oouGias
c<
ORBITAL WORKSHOP
EXPERIMENT
ACCOMMODATIONS
RIMENT ACCOMMOD
EXPERIMENT - S020
D /W-708Q A
°™-°o
�Gegenschein/Zodiacal Light S073
This experiment utilizes the photometer system from Experiment
T027 (contamination measurement) and a film cannister, together
with one of the SAL's to measure the surface brightness and
polarization of the nightglcw over as large a portion of the
celestial sphere as possible at several wavelengths in the
visible light spectram, and to determine the extent and nature
of spacecraft corona while the vehicle is in sunlight.
Telemetry
requirements include photometer system data, housekeeping data,
and voice annotations.
Particle Collection S1U9
This experiment also utilizes portions of the T027 equipment,
together with a collection cassette which consists of two impact
plates which can be deployed at ground conmand or manually to
collect micrcmeteoroid particles in the vicinity of the earth.
The exposed cassettes will be returned in the conmand module.
Telemetry data cn cassette status and voice annotation of sig
nificant events is required for this experiment.
UV Panorama S183
The mirror system described for SO19 will be used for this
experiment together with a wide-angle spectrograph to obtain
luninosity distributions of selected star fields, improve the
classification of hot, young stars of up to 10th magnitude, and
provide a general survey of the sky in the UV range.
Three
analog data signals and voice ccnments are the data requirements
for this experiment.
Technological Experiments and Operational Experiments
The operational and technological experiments have a general objective
of obtaining data to further the development of advanced space
vehicles and equipment, and to aid in the development of operational
94
�ORBITAL WORKSHOP
EXPERIMENT - S149
PARTICLE COLLECTION
MCOO/V/VCLL
DOUGLAS
4STWOA/4l/r/CS
COMf*AMY
O/W-7093A
4-27-70
T027 EXTENSION ROD
9.5"
36.0"MAX
CONTROL PANEL
T027 CANISTER
>o
Cn
SCIENTIFIC AIRLOCK
INTERNAL OWS
ENVIRONMENT
EXTERNAL OWS
ENVIRONMENT
MOTOR/DRIVE
CASSETTE SUPPORT UNIT
EXTENSION
MECHANISM —
21.25"-
— DETECTOR CASSETTES
�/VfCDO/V/VELL
DOUGLAS
AST&O/VAUTICS
corviF>/\rv\r
ORBITAL WORKSHOP
EXPERIMENT ACCOMMODATIONS CDR
EXPERIMENT S 183 ULTRAVIOLET PANORAMA
FILM CARROUSEL
O/W-mim
�ORBITAL WORKSHOP
EXPERIMENT - S149
PARTICLE COLLECTION
CDO/V/Vflt
DOUGLAS
ASTftOMAUTtCS
CO/MP4/VV
O/W-7093A
4-27-70
T027 EXTENSION ROD
36.0"MAX
CONTROL PANEL
T027 CANISTER
o
Cn
SCIENTIFIC AIRLOCK
INTERNAL OWS
ENVIRONMENT
EXTERNAL OWS
ENVIRONMENT
EXTENSION
MECHANISM —
78" I——MOTOR/DRIVE
T
CASSETTE SUPPORT UNIT
DETECTOR CASSETTES
�ORBITAL WORKSHOP
JZZZL.
EXPERIMENT
ENT ACCOMMODATK
ACCOMMODATIONS CDR
EXPERIMENT S 183 ULTRAVIOLET PANORAMA
MCOO/V/VCtL
...
.... ^
— .- . ^ —*
m
m m
m.
9 —8 — 7 0
�/VtCDO/V/VtLL
DOl/CL4S
/ISTRO/VAl/riCS
CO/VIP/1/VV
ORBITAL WORKSHOP
EXPERIMENT • T003
INFLIGHT AEROSOL PARTICLE ANALYZER
O/W-7071A
4-27-70
�/Vf COO/V/Vfl_I_
DOUGLAS
ORBITAL WORKSHOP
EXPERIMENT ACCOMMODATIONS CDR
EXPERIMENT M509 AME
4STW0/V40F/CS
CO/VTP4A/V
HHMU
ASMU
£
CO
TRANSMITTER
INCLUDED
LSU TO AM
HAND CONTROLLER
DOWN POSITION
WHEN NOT IN USE
O/W-9364
9-18-70
�procedures for extended manned orbital operation.
Among the opera
tional and technological experiments planned for the OWS are the
following:
Astronaut Maneuvering Equipment (AME) M509
This experiment consists of two items of maneuvering equipment
which will be evaluated by crewmen in the forward compartment
of the OWS.
The Autcmamatically Stabilized Maneuvering Unit (ASMU) is a backmounted device that provides the astronaut with six-degree-offreedcm flight, utilizing compressed nitrogen gas thrusters in
conjunction with a control moment and rate gyro stabilizing
system.
The Hand Held Maneuvering Unit (HHMU) consists of a
hand held manifold with two tractor and one pusher thruster,
and is connected to the ASMU.
Inflight Aerosol Analysis TO03
This experiment consists of an aerosol analyzer (nephelcmeter)
which will be used to make concentration and size distribution
determinations at various locations throughout the OWS.
The
device is self-contained, battery-operated, and capable of either
hand-held or mounted operation.
The analyzer draws air samples into a chamber, and uses reflected
light from the sample to provide amplitude and time related pulses
that are counted and displayed for logging by the using crewmen.
The sample air is discharged through a filter and the particulate
matter is retained for return and postflight analysis.
Crew Vehicle Disturbance TO13
This package consists of equipment which will be utilized by
crewmen to determine the effects of various crew activities on
the dynamics of a manned spacecraft.
The equipment consists of
a limb motion sensor assembly, which will be worn by the crewman
99
�to measure his arm and leg motions, a force measuring system,
which consists of load cells, and load bearing platforms, and a
central data system which gathers the experimental data and trans
mits it to the airlock module data system for recording and
subsequent telemetering.
Photographic coverage, and recorded
voice comments are also required for this experiment.
Foot Controlled Maneuvering Unit TO 20
This experiment package consists of a gas propulsion device that
is straddled by a crewman and controlled by his foot movements.
The experiment is performed in the OWS forward compartment and
will provide data for use in determining the feasibility of the
FCMU concept for EVA, and the design of subsequent operational
systems of this type.
FCMU maneuvers will be photographed and voice comments will be
recorded for telemetry.
Coronagraph Contamination Measurements TO25
This experiment will be performed to determine the presence of
an induced particulate atmosphere surrounding the OA; to deter
mine changes in this atmosphere as a result of thruster pulsing,
waste dumps, and vehicle orientation; and to determine the nature
and extent of the solar F-corona viewed by the coronagraph.
The equipment for this experiment consists of a coronagraph
cannister which will be mounted in a scientific airlock, and an
extensible boom-mounted occulting disk assembly which will block
the solar disk.
Exposed film will be stored in film vaults and
returned in the command module.
Housekeeping data and recorded voice carments are required for
this experiment.
100
�NIC DON NELL
DOUGLAS
ASTRONAUTICS
C ONI RAN Y
O R B I T A L WORKSHOP
EXPERIMENT ACCOMMODATIONS CDR
EXPERIMENT - T020
FOOT CONTROLLED MANEUVERING UNIT
O/W-7082A
9-8-70
PRESSURE SUITED MODE
PRINCIPAL
FIELD OF
VIEW
BACK PACK
PROTECTIVE
BAR
LINE OF
SIGHT
SPLIT IMAGE
CAMERA
THRUST AXES
�/VTCDO/V/VELL
DOUGL/XS
ASTffO/VAUT/CS
corviF>/\r>iv
ORBITAL WORKSHOP
EXPERIMENT ACCOMMODATIONS CDR
EXPERIMENT - T025 CORONOGRAPH
CONTAMINATION MEASUREMENT
O/W-7098A
9-2-70
CAMERA LENS
MOUNT
OCCULTING
DISCS
SCIENTIFIC
AIRLOCK
o
CAMERA
-MAGAZINE
SOLAR POSITION
INDICATOR
BOOM
STANDOFFS
EXTERNAL
INTERNAL
CORONOGRAPH
CANISTER
�Contamination Measurement TO 2 7
This experiment will provide data to determine the effects of the
induced OA particulate atmosphere cm exposed optical elements such
as windows, lenses, mirrors, and diffraction gratings by exposing
a cannister containing various saitples (sample array system) to
space via a scientific airlock, and making photometric measure
ments of the particulate atmosphere.
Telemetry from the photometer system, the sample array system, and
voice comments, as well as logged data are required for this
experiment,
103
�/VTCOO/V/VELL
DOI/CL4S
4STffO/V4l/r/CS
CO/VIP4/VV
ORBITAL WORKSHOP
EXPERIMENT ACCOMMONATIONS CDR
EXPERIMENT - T027
ATM CONTAMINATION MEASUREMENT
O/W-7100A
9-2"70
EXTENSION ROD
MECHANICAL
CONTROL PANELMANUAL CONTROL PANEL
UNIQUE CONTROL
CANISTER
INTERNAL OWS
ENVIRONMENT
SCIENTIFIC AIRLOCK
AUTOMATIC PROGRAMMER
CONTROL PANEL
EXTERNAL OWS
ENVIRONMENT
CAMERA, PHOTOMETER
AND SUNSHIELDS
ELEVATION
MECHANISM
EXTENSION MECHANISM
�Scientific Airlock (SAL)
IWo government furnished scientific airlocks will be provided and
installed in "die forward compartment of the CMS.
One SAL will
be located facing sunward, and the other 180 degrees opposite
the first.
The two SAL will provide space exposure capabilities
for various experiment package components which are activated
and function in a space environment to achieve the experimental
objectives.
The SAL consists of a chamber, installed in the CWS wall, inner
and outer doors, vacuun/pressure gage, door control, and pressurization control.
SAL operating instructions are included on
decals mounted on each SAL faceplate.
105
�DOUGLAS
ORBITAL WORKSHOP
REVISED SCIENTIFIC AIRLOCK
O/W-7812
8 28-70
�MCOOMWELL
OOVOLM
/(•T)NMI4(/ncs
»r
ORBITAL WORKSHOP
SCIENTIFIC AIRLOCK INSTALLATION
0/W-5866A
8-12-70
TRUE ANGLE OF
THIS PLANE
SECTION A-A
�Stowage System
The OWS stowage system consists of provisions for the containment/restraint,
and accessibility of loose equipment within the OWS.
These provisions
consist of the following stowage system equipment:
o
Stowage lockers
o
Stowage cabinets
o
Containers
o
Miscellaneous provisions
o
Film Vault
o
Food chiller and freezers
Stowage lockers
Sixteen stowage lockers containing a total of 95 compartments are
located throughout the CWS. The lockers contain six stowage compart
ments which have approximate dimensions of 10 inches by 11 inches by
16 inches.
One locker in the forward compartment contains two compart
ments which are oversize, and have approximate dimensions of 10 inches
by 11 inches by 20 inches.
One locker in the waste management compart-
nent has only four compartments. The distribution of lockers and
compartments is as follows:
Lockers
Compartments
Forward compartment
2
13
Experiment compartment
1
6
Sleep compartment
3
18
Waste management compartment
2
10
Wardrocm
8
48
16
95
Totals
108
�SA-286A
5-19-71
/VfCDO/V/VELL
DOUGLAS
ASTRONAUTICS
STOWAGE SYSTEM
COM RAN V
WATER RING CONTAINERS (25)
INCLUDES ORBITAL SPARES
FOOD STOWAGE CONTAINERS (11)
FOOD FREEZERS (5)
FOOD CHILLER (1)8
STANDARD STOWAGE LOCKERS
(16 LOCKERS - 9 5 COMPARTMENTS)
CLUSTER TOOLS
STOWAGE COMPARTMENTS (12)
�MCOO/V/VELL
ORBITAL WORKSHOP
OOL/GL4S
/\STr*OIVAVTICS
STANDARD STOWAGE LOCKER
COMPA/VV
O/W-3759
4-2-70
a—
||:.^-|S—|
lr n
m -\
1
!
0
I
3. 3 ^ p
T
:
11.4"
CLEARANCE
BACK EACE OF DOOR
LOCKER COMPARTMENT INTERIOR
�The stowage lockers are of beaded aluminum construction with pianohinged and latched access doors.
The lockers are attached to the OWS
floor by means of a mounting pallet at the locker base and a pivotinp
linkage at the forward end of the locker.
The pallet and linkage
provide load restraint and stability.
The stowage compartments contain such items as 0^ mask, lights,
camera equipment, trash and waste collection bags, clothing, orbital
spares, tape recorders, medical supplies, personal hygiene equipment,
and crew personal preference items.
Stew age Cabinets
Five stowage cabinets are located throughout the OWS and contain a
total of 16 stcwage compartments of various sizes.
The stowage
cabinets are distributed in the OWS as follows:
Compartments
Cabinets
Compartments
Forward compartment
1
3
Wardroom
2
5
Waste management compartment
1
4
Sleep compartment
1
4
5
16
Total
The stcwage cabinets are constructed of sheet metal, and have pianohinged, latched access doors. Attachment provisions for the stcwage
cabinets are similar to those for the stcwage lockers.
Items stewed in the cabinet compartments include tool kit, repair kit
shoes, sleep restraints, entertainment kit, data file, vacuim cleaner
and waste collection bags.
Ill
�Containers
Stowage containers are loaded, prior to their installation in the CMS.
There are provisions for 25 containers forward of the water storage
tanks in the forward compartment.
Eleven food containers are provided
for the storage of dehydrated, intermediate moisture, and wet-pack
foods, and these are installed in the forward compartment.
Three
containers are provided for the storage and return of urine samples.
These are configured to fit the command module, and are located in
the forward compartment.
Miscellaneous Stowage Provisions
Miscellaneous stowage provisions consist of the mounting and restraint
hardware provisions for those items of equipment which are stowed
individually in the OWS, rather than in lockers or cabinets.
These
items include fire extinguishers, spare mole sieve, portable astronaut
aids, portable fans, and the IVA umbilicals.
These provisions are
mainly in the forward and experiment compartments.
Film Vault
The film vault provides the photographic film utilized to record
experimental data from the expected radiation environment in the OWS.
The 12 drawers of the vault will have different thicknesses of aluminin
for radiation protection.
The film vault will be bolted to the CMS
floor in the forward compartment.
Food Chiller and Freezers
The food chiller and freezers are provided for the storage of foods
which are perishable or frozen
The freezers are located in the for
ward compartment (3 compartments) and in the wardroom (2 compartments).
The chiller is the top compartment in the wardroom freezer assembly.
The freezer maintains a temperature of -10 +_ 10 degrees Fahrenheit, and
the chiller a temperature of 39 + 6 degrees Fahrenheit. These items
of equipment utilize heat rejection capabilities of the OWS refrigeration
svstem to achieve the required temperatures.
112
�/VICDO/V/VELL
DOUGLAS
O/W-8258
8-7-70
ORBITAL WORKSHOP
STOWAGE RING CONTAINER
ASTRONAUTICS
COMPANY
30" INSIDE
LATCH
�/VfCDO^Z/VELL
~
ORBITAL WORKSHOP
~
FORWARD COMPARTMENT ON-ORBIT STOWAGE
TBOMor/es
on**™
Q_77_7n
FOOD STOWAGE
CONTAINERS (11)
FOOD
FREZERS
PUMP ASSY
REFRIGERATION
SUBSYSTEM
(8 COMPARTMENTS)
�(VTCOO/V/VfLL
OOUGL4S
4STffO/V4Ur/CS
CO/VfPA/VV
ORBITAL WORKSHOP
SA-303
12-2-70
FILM VAULT
REQUIREMENTS
ALUMINUM CASTING 54 X 40 X 22
APPROX 3,000 LB
0.25 TO 3.40 IN RADIATION PROTECTION
FOUR VAULT COMPARTMENTS
FILM VAULT
REMOVABLE FILM DRAWERS (12)
TOTAL DRAWER AREA 270.0 IN2
APPROX
60,000 FT (APPROX) 16 MM
MOVIE FILM
27,000 (APPROX) FRAMES 70 MM
C A M E R A F I L M + M S C L SPECIAL F I L M
OWS A M B I E N T P R E S S U R E
45+15 RELATIVE HUMIDITY PASSIVE SALT PAD SYSTEM
�Electrical System
Hie electrical system provides the primary OWS electrical power source
and the distribution and control of IIJ/AM power and commands to OWS
equipment and experiments.
The OWS illunination system is also considered
as part of the electrical system.
IU/OWS PowerDistribution and Control
This system provides power and control of OWS functions interfacing
the Instrument Unit (IU).
These functions are as follows:
o
TACS control
o
Atmosphere control system
o
Refrigeration system
o
Solar array deployment
o
Meteoroid shield deployment
This system is peculiar to the launch phase of the mission, ascent,
and preliminary orbital phase, and has no function after IU power
depletion, approximately seven ana one-half hours after liftoff.
This system is electrically isolated from the At/CWS svstem.
AM/OWS Power Distribution and Control
The electrical power distribution and control svstem receives
control
and instrumentation power to support the OWS systems and experiments
via the airlock module.
Power is furnished at DCS command or bv
actuation of switches on either the STS instrumentation panel or the
OWS control and display panel.
The main power control and display
console in the OWS is located in the experiment compartment.
This
console contains all necessary switches, circuit breakers, and
indicators to alia-/ the crew to control electrical power throughout
the OWS.
There is no OWS crew interface with the instrumentation
power system.
116
�/VTCDO/V/VELL
DOUGL4S
/»STi?o/v4cyr/cs
CO/VTP4/VV
ORBITAL WORKSHOP
ELECTRICAL COMMAND SUBSYSTEM
SA-287
12-2-70
IU/0WS
INTERFACE
SWSEL
AM70WS
INTERFACE
PANEL 15
RELAY
OWS ELECTRICAL COMMAND SUBSYSTEM
MODULES
PANEL 17
REQUIREMENTS
FWD CONTR DIST
PANEL
MATRIX BLOCKS
PANEL 16
PROVIDE AUTOMATIC GROUND COMMAND
CAPABILITY FOR INITIAL 73 HOURS OF
MISSION FOR THE FOLLOWING SYSTEMS:
PANEL J
(1)
PRESSURE CONTROL
MATRIX
CZ)
THRUSTER ATTITUDE CONTROL
BLOCKS
(3)
SOLAR ARRAY DEPLOYMENT
(4)
METEOROID SHIELD DEPLOYMENT
(5)
REFRIGERATION
(6)
AM/ATM/MDA FUNCTIONS-INCLUDING
MAIN TUNNEL
CONTROL OF AM BUSSES. ATM
DEPLOYMENT. PAYLOAD SHROUD
JETTISON AND MOA VENT VALVE
CONTROL
PANEL 22
SYSTEM OPERATION
ORDER OF EVENTS IS DETERMINED BY THE SL-1
AFT UMBILICAL
PROGRAM FLIGHT SEQUENCE
SEQUENCE IS STORED IN A PREPROGRAMED IU
COMPUTER
OWS SWITCH SELECTOR DECODES COMMANDS
RECEIVED FROM IU
EACH SYSTEM AFFECTED RECEIVES COMMANDS
FROM THE OWS SWITCH SELECTOR
�ORBITAL WORKSHOP
ELECTRICAL POWER DISTRIBUTION SYSTEM
SA 306
AM/OWS INTERFACE
FEEDTHRU
REQUIREMENTS
PROVIDE 24-30 VDC TO OWS END ITEMS
PROTECT WIRING FROM DAMAGE AND FIRE
INTERNAL
PROVIDE CREW INTERFACE TO CONTROL AND
MONITOR POWER ALLOCATION
SYSTEM OPERATION
CO
EXTERNAL
RECEIVES 25.5 TO 30 VDC FROM AM
PROVIDES REDUNDANT BUSSES IN CONSOLE
SUPPLIES 24-30 VDC TO END ITEMS
MAIN
PROTECTS WIRING TO END ITEMS WITH CIRCUIT
BREAKERS
CAPABILITY OF 118 AMP LOADING
NOMINAL POWER USAGE AT 26 VDC IS 2200 WATTS
ELECTRICAL
CONTROL
CONSOLE
�Remote control panels for illumination, habitability support svstems,
and tape recorders are provided at convenient locations.
wiring is protected with circuit breakers.
All power
Seme of the design
characteristics of the distribution system are:
o
Two wire circuits are employed with a single point ground
which is isolated from the CWS structure ground.
o
Utility outlets with ccmmon receptacles are provided for
fans, lights, heaters, cameras, or experiments.
The
receptacles and connectors are designed to preclude arcing
when the crew mates or demates electrical equipment.
o
Internal OWS wiring is protected from physical damage, and
fire.
o
Procedural means of removing power from the OWS receptacles
is available.
o
Main power feeders are physically and electrically isolated
from each other.
o
Explosion-proof zero-g connectors, utilizing a bail handle
rather than twist-lock or screw engagement to facilitate
one handed operation are utilized on OWS equipment which
derives electrical power from the utilitv outlets.
Solar Array System (SAS)
The solar array system converts solar energy into direct current (DC)
electrical power and supplies it to the airlock module where it is
conditioned and distributed to the rest of the OA (OWS, MDA, AIM, DSM)
The SAS consists of two deployable wing assemblies externally mounted
cn the OWS, and their associated electronics, instrumentation, and
deployment equipment.
119
�MCOO^Vft/ElL
DOUGLAS
ASTftOHIAUTICS
CO/VIPA/VV
ORBITAL WORKSHOP
SASOO
12-2-70
GENERAL ILLUMINATION SYSTEM
REQUIREMENTS
GENERAL ILLUMINATION LIGHTS
SHALL PROVIDE THE FOLLOWING
AVERAGE ILLUMINATION LEVELS.
AREA
F00TCAN0LE
(MIN)
NASA SLEEP
COMPARTMENT
WARD ROOM
HEAD
WORK EXPERI
MENT COM
•cnoa »- A ma coarr
mt-r
PARTMENT
FORWARD
COMPARTMENT
DURING INITIAL ENTRY AND
EMERGENCY MODE THE LIGHTING
SYSTEM SHALL PROVIDE AN
AVERAGE ILLUMINATION OF 0.5
FOOT CANDLES (MIN) IN THE CREW
ani - i
QUARTERS AND FORWARD
COMPARTMENT.
SYSTEM OPERATION
42 SYLVANIA FLOODLIGHTS
(1869384) WITH 3 POSITION
(1*1-T
NCTlOa M CMC*IU«r<«
SWITCH, (OFF, LO, AND HI).
�/VfCDO/V/VELL
—
/ISRWO/V4(;R/CS
ORBITAL WORKSHOP
SA291
19 9 7N
ELECTRICAL CONTROLS AND DISPLAYS
SYSTEM OPERATION
PANEL-542
DATA RECORDERS FROM THE
FORWARD COMPARTMENT
PANEL-630
LIGHTS IN THE WMC AND
WARDROOM
PANEL-700
WATER SYSTEM AND WINDOW
HEATER IN WARDROOM
PANEL-800
WATER, URINE, AND FAN IN
WMC
OUTLETS -402, -521,-531,-541,
-601, -631, -603
CREW CONVENIENCE,
PORTABLE, LIGHTS, FANS,
CAMERAS AND VACUUM
CLEANER
OUTLETS -518, -544,
EXPERIMENTS UTILIZING
THE SAL'S
�/VtCT DO/V\£tl
ORBITAL WORKSHOP
SA-306
SOLAR ARRAY SYSTEM-STRUCTURE
12270
D O U G L / X S
4ST#?0'V4Ur/CS
CO/VfP/»/VV
BEAM
FAIRING
ASSEMBLY
FORWARD
FAIRING
ASSEMBLY
PANEL
v
A
\
-V
MODULE-
\
1
ro
>o
\
/
/
STOWED
WING SECTION
/
FULLY DEPLOYED IN 4 MINUTES
DEPLOYED PANELS FACE DIRECTION OF POS I
\
A
SAS REQUIREMENTS
FORWARD
SKIRT
(
y
'
NO CONTAMINATION OF PANELS BY
EXPLOSIVE DEVICES
'
-
OUTPUT OF 11,200 WATTS AT FAIRING INTERFACE
\
AT:
A
\
X
/
PARTIALLY
FULLY
DEPLOYED
DEPLOYED
•- WING —- — WING
SECTION
SECTION
S-IVB
HABITATION
AREA
AFT SKIRT
a.
130°F
b.
c.
INTENSITY OF 140 NM/CM 2
BEGINNING O F MISSION
OPERATING TEMPERATURE OF -85° TO +212°F
WITHSTAND VIBRATION AND SHOCK LOADS
OF DOCKING OPERATIONS AND SWS MANEUVERS
�During the Sky lab orbital mission, when the OA is maintained in a solar
inertial attitude, the SAS active faces point toward the sun.
Each of the wing assemblies consist of:
o
Fairing assemblies which house the wings and their actuating
mechanisms during the launch and ascent phases of the mission.
o
Three wing sections which contain the solar cells and are
stored within the fairing assembly.
o
Mechanical and ordnance systems for SAS orbital deployment.
o
Stabilizing beams which restrain the wing sections in the
deployed position.
Electrical support equipment for the solar array system consists of
the following:
o
Cabling frcm the SAS modules to the SAS power unit located
in the OWS forward skirt.
o
The SAS power unit which contains isolation and bussing
devices, and GSE connectors.
o
The SAS instrumentation signal conditioning unit in the CWS
forward skirt.
o
Cabling from the SAS pcwer unit to the /W.
o
Fairing release and SAS deployment electronics.
The solar array wing sections are made up of 240 modules (120 per
wing), divided into eight electrically isolated pcwer groups of 30
parallel-connected cells each.
This arrangement minimizes power
output differences among "the groups as a result of expected shadowing
conditions.
123
�ORBITAL WORKSHOP
sazss
SOLAR ARRAY SYSTEM-ELECTRICAL
12270
/MCOO/V/VELL
DOUGLAS
ASTnOnJAUTICS
CO/VfP4/VV
NUMBERING TYPICAL
SECTION
WING 2
POWER UNIT
(PANEL 15)-
WING 1
POWER UNIT
(PANEL 6)
POSITION III
POSITION II
POSITION IV
MODULE
POWER
CABLES
PANEL
WING 2
NOTES:
1. (616) SOLAR CELLS MAKE UP A MODULE
2. (4) MODULES MAKE UP A PANEL
3. (10) PANELS MAKE UP A WING SECTION
4. (3) WING SECTIONS PLUS BEAM FAIRING
MAKE UP A WING
WING 1
FAIRINGS
�The solar array is deployed at IU command by means of preloaded
mechanical energy storage systems which are released by initiation of
redundant EBW firing unit/EBW/CDF ordnance trains.
Ground command
backup is provided via the DCS should "the IU fail to command the
deployment.
After the wings' beam fairing assemblies are deployed,
the solar panel wing sections are released
and driven into extension,
where they are locked by means of devices in the stabilizing beams.
The deployed SAS provides approximately 10,000 watts of electrical
power for operation of OA systems, and recharging of /W batteries,
which provide OA pcwer during the night side of the orbit.
125
�Atmosphere Control System (ACS)
The CMS atmosphere control system provides for habitation area and waste
tank pressurization prior to launch and pressure control during boost phase-,
remote pressurization and venting of the OWS on-orbit; active and passive
control of atmospheric temperatures within human comfort limits; and
controlled atmospheric circulation.
Pressure Control System (PCS)
The pressure control function of the ACS provides for prelaunch
pressurization and inflight venting control for the habitation area
and waste tank. The habitation area pressure control capability
includes the use of two sets of valves: a pair of pneumatically
operated valves which are used for orbital blcwdcwn immediately
after orbital insertion; and a set of solenoid valves utilized for
venting the habitation area for storage. Both sets of valves exhaust
into ducts which terminate in orifice plates so oriented as to render
the venting non-propulsive.
The waste tank has similar pneumatic vent valves, and both the
habitation area and waste tank pneumatic valves include pressure
relieving functions.
The pressurization of the habitation system after orbital insertion
is accomplished by an airlock-controlled system. The habitation area
is pressurized and maintained at 5.0 psia total pressure (3.7 psia 0^
partial pressure, and 1.3 psia Nj partial pressure) throughout the
manned portions of the mission. This pressurization is accomplished
after the launch pressure has been blown-down. This pressure is
required to provide structural integrity during launch loads. The
waste tank is also pressurized to avoid high differential pressure
across the common propellant tank bulkhead which separates the
habitation area from the waste tank.
126
�MCOOfWiVElLi.
rX>UGL.X\S
iSTHo^4(;rics
COMP/l/VV
SA-294A
5-19-71
ACTIVE THERMAL CONTROL
AIRLOCK DUCT
VENTILATION
DUCT (3)
MIXING
CHAMBER
WMC VENTILATION
FAN CLUSTER (3)
KJ
0"
RADIANT HEATER (8)
GROUND CONDITIONING
BLOWER AND HEAT
EXCHANGER
DIFFUSER (12)
DUCT HEATER (3)
TEMP
CONTROL
SENSORS
CONTROL AND
DISPLAY PANEL
�.5ICDO/V(Vtlt
OOUGL4S
«r»OMuric«
COMP4*V
PRESSURIZATION AND PRESSURE
CONTROL SYSTEM
CHECK VALVES
III
VENT
SEALING
DEVICES
SA-284A
5-19-71
QUAD REDUNDANT
SOLENOID VENT
VALVES
HABITATION AREA
VENT SYSTEM
GROUND PURGE &
PRESSURIZATION
UMBILICAL
PNEUMATIC
CONTROL
SYSTEM
WASTE TANK
VENT SYSTEM
�A pneumatic system consisting of a GN2 sphere containing aporoximatelv
five cubic feet of nitrogen at 750 psia, and an actuation control
module containing solenoid valves, is utilized in the operation of
the OWS pneunatic vent valves.
Thermal Control System (_TCS)_
The OWS thermal control system is designed to meet the OWS thermal
requirements from ground-hold conditions through orbital activation,
habitation, and storage.
During ground-hold, and orbital storage,
the OWS is thermally conditioned to satisfy the temperature require
ments of the food and film stored in the OWS.
During orbital activa
tion and habitation, the OWS must be conditioned to within astronaut
entry limits (activation), and "shirtsleeve" environment (habitation).
The ground thermal control portion of the svstem employs OWS heat
exchangers 'which are serviced with a mixture of water and ethvlene
glycol and circulation fans along with ground thermal conditioning
units (TCU).
The orbital thermal control portion consists of active
and passive provisions for maintaining orbital thermal requirements.
Cabin gas temperature is maintained by heat exchangers located in the
airlock module, as well as convective heaters mounted in the ventila
tion ducts.
Passive thermal control provisions include optical
property control of exterior and interior surfaces, and application
of insulating material on the insides of habitation area pressure
walls.
Ventilation Control System (VCS)
The ventilation control svstam transports revitalized air which has
been purified and dehumidified from the airlock module and mixes it
with the CWS atmosphere, and circulates the mixture "throughout the
habitable area.
The system also provides for particulate and odor
filtration of the waste management air.
129
�ORBITAL WORKSHOP
VCS/TCS SCHEMATIC
RZZZR
RECIRC.
FAN CLUST
FROM AM
•
VCS
RECIRC
FAN
VCS
RECIRC.
FAN
VCS
RECIRC.
FAN
VCS
RECIRC.
FAN
TCS
• CONVECT
HEATER
B E$>A
VCS
RECIRC.
FAN CLUST.
VCS FILTER
& MIXING
CHAMBER
E
TCS
CONVECT.
HEATER
gg>.A
I
CONTROL
CONSOLE
|
8-25-70
RECIRC.
A
FAN CLUST.
VCS
AIR
DIFFUSER
VCS
AID
DIFFUSER
CONVECT
HEATER
WARD
ROOM
VCS
AIR
DIFFUSER
VIEWA-A
VCS RECIRCULATION
FAN CLUSTER
VCSPORTABLE
FAN
AIRLOCK
CONTROL
TCS
RADIANT
HEATERS
VRS
VCS
EXHAUST MUFFLER RECIRC
SCREEN
FAN
VCS
FILTER &
ODOR
ABSORB
CAN
WASTE MGT
CO MPT
VCS
INLET
SCREEN
VCS
AIR
DIFFUSER
�/VfCDO/V/VELL
ORBITAL WORKSHOP
DOUC14S
ASTWO/VA^r/CS
VENTILATION
CO/VfP4<VV
MIXING CHAMBER
MIXING
CHAMBER
SCREEN
4 FAN CLUSTER
WITH SOUND
SUPPRESSION
HEATER
O/W-3961
8-5-70
CARRY-IN DUCT FROM AM SYSTEM
12 DIA. DUCT ARMALON
WMC
VENTILATION
UNIT
DUCT DIFFUSER
ADJUSTABLE
DIFFUSERS -
�Revitalized atmosphere is brought frcm the AM to the cfcme of the OWS
via a duct, which is fed into a mixing chamber (plenun) located in
the forward compartment cn the OWS dome.
Three OWS ventilation ducts
are routed frcm the mixing chamber to the plenun chamber between the
crew quarters and the waste tank.
clusters mounted in each duct.
The ventilation is produced by fan
The crew quarters floor is equipped
with adjustable diffusers which allow the ducted air to circulate
through the crew quarters and back to the forward compartment, thence
to the airlock module for revitalization.
Each ventilation duct contains four Apollo post landing ventilation
CPLV) fans, mounted in a baffled cluster assembly.
A filter/odor
removal cannister is mounted on the forward compartment floor, and
contains activated charcoal filters to remove odors and particles
suspended in the atmosphere.
A portable fan complement is included
in the OWS consisting of three of the PLV fans mounted in central
fixtures which can be located anywhere cn the OWS grid, on handrails,
or the central fireman's pole, and can be connected to utility outlets
for electrical power.
132
�flfi
Refrigeration System
The Refrigeration System (RS) provides cooling and freezing capabilities
for food, potable water, and urine samples in the OWS.
Redundant cooling
loops are provided, one for the normal operational requirements, and one
backup system in case of primary system failure.
Each system utilizes liquid refrigerant which is circulated through Hie
temperature-controlled storage units absorbing heat.
The coolant is then
routed either to a ground cooling heat exchanger, while the OWS is in a
ground hold status, or to the OWS external radiator,
or, during phases of
the mission where the radiator cannot provide sufficient heat rejection,
to a thermal capacitor.
Recirculation
Four positive displacement gear pimps are utilized in each refrigerant
loop for circulating the Coolanol-15 refrigerant.
The pimping and
thermal control assemblies contain approximately 80 percent of the
potential leak paths for the refrigerant aboard the CWS.
To minimize
the possibility of inboard coolant leakage, the pimping and chiller
thermal control assemblies are combined in a pressure tight container
which is vented directly to the waste tank and overboard, in the event
of leakage.
A hand shutoff valve is provided for cm-orbit access to
these assemblies.
The pimps are automatically shut off during launch
to prevent exceeding the radiator
working pressure, and are sequenced
on at IU command following S-II separation.
The pimps are also shut
off manually prior to exceeding their guaranteed life cycle of 2,200
hours.
Controls and Displays
The refrigeration system is provided with the following major electrical
components for control and display of its operation:
133
�/VICDO/V/VtLL
DOI/GI /*S
/\&Tf*OrS//\VTICS
i/vv
corvif*/
ORBITAL WORKSHOP
SA-277
12-2-70
REFRIGERATION SYSTEM
REQUIREMENTS
FOOD
STORAGE
FREEZERS
1
PUMPING UNIT
COLD PLATE
FOOD
CHILLER
WARDROOM
FREEZEFG
TANK WALL
PENETRATION
TANK WALL
PENETRATION
— URINE FREEZER
URINE CHILLER
WARDROOM
TABLE
CONTROLS & DISPLAYS
• CIRCUIT BREAKER
PANEL - 611
• CONTROL AND
DISPLAY PANEL - 617
PROVIDES SWITCHES,
NETECROiD LIGHTS
FOR RS
WATER
CHILLER
THERMAL
CAPACITOR
FROZEN FOOD
CHILLERS
CHILLED WATER
FROZEN URINE
CHILLED URINE
-20° TO +0°F
+33° TO +45° F
+33° TO +45°F
-2.5°F MAX
+59°F MAX
SYSTEM OPERATION
-14°F
THERMAL CAPACITOR
-50° TO +10°F
RADIATOR TEMP CYCLE
PUMPS
.0365 CFM
VOLUMETRIC FLOW
55 PSID
PRESSURE DROP
50 WATTS
PUMP POWER
1,680 BTU/HR
RADIATOR CAPACITY
PUMP OPERATING LIFE 2250 HRS EA
EARTH RESOURCES CAPABILITY
2 PASSES PER 6 ORBITS
4 PASSES PER 16 ORBITS
MAX OPERATING PRESSURE 140 PSIA
TO GSE
(DESIGN)
COOLANT VOLUME PER LOOP 1016 IN. 3
RADIATOR
THERMAL
CONTROL
-GROUND HEAT EXCHANGER
RADIATOR
�/VtCDO/V/VtLI.
/1STWO/V41/FICS
CO/VfP/1/VK
ORBITAL WORKSHOP
:RIGERATION SUBSYS1
REFRIGERATION
SUBSYSTEM
EQUIPMENT LOCATION
2SST
(7)
PUMPING ASSEMBLY, REFRIGERATION SUBSYSTEM
(7)
THERMAL CONTROL ASSY, CHILLER, REFRIGERATION SUBSYSTEM
(T) CONTAINER - STORAGE, FOOD
(4) FREEZER, FOOD STORAGE
(?) FREEZER, WARDROOM
(?) RADIATOR ASSEMBLY
TEMP CONTROL VALVE
(ROUTES TO TUNNEL)
(?) URINE CHILLER
(?) URINE FREEZER
CONTROL PANEL
INSULATION
THERMAL CAPACITOR
GC HEAT EXCHANGER
VALVE
(ROUTES TO UMBILICAL)
RADIATOR)
�o
IWo coolant pump inverters
o
TWo control logic units
o
IWo radiator
o
Two regenerator heater controllers
o
One display and control panel (part of pcwer console)
o
Instrumentation and control sensors
bypass valves
7S
The coolant punp inverters convert the 28 VDC electrical power to -8-r5~
VFMS to drive the punp.
the punps, radiator
loops.
The control logic units provide operation of
bypass valves, and regenerator heaters for the two
System parameters requiring display are also derived from the
control logic units.
Radiator bypass valve controllers are provided
in each coolant loop to control refrigerant bypass from the radiator
to the thermal capacitor when abnormal radiator
sensed.
Flow throughout the radiator
temperatures are sensed.
temperatures are
is restored when normal radiator
Electrical heater blankets are provided in
each loop to maintain the temperature of the refrigerant in each loop
within a selected control range.
These regenerator heaters have their
own controllers which are operated by the control logic units to
provide on-off power to the heaters.
The RS control and display panel
is part of the electrical control and display console located in the
experiment compartment and provides for crew mcnitoring and manual
system control.
>
136
�/XST&O/VAUTtCS
corvif/x/vv
ORBITAL WORKSHOP
VACUUM SYSTEMS
WARD ROOM & REFRIGERATION SYSTEM
ESS
REFRIGERATION PUMP
ENCLOSURE
REQUIREMENT
VENTS REFRIGERATION
PUMP ENCLOSURE
IN EVENT OF
COOLANT LEAKAGE
WARDROOM
C&O PANEL
NO. 700
• WATER DUMP
PRESSURE
0-2 PSIA
DUMP HEATER
ON - LIGHT
(REMOTE
INDICATION
ON C&DPANEL
NO. 617)
REFRIGERATION
SUBSYSTEM
PUMPING ASSEMBLY
ENCLOSURE
SYSTEM OPERATION
VENTS INTO WASTE
TANK
1/4" LINE WITH ISOLATION
-REFRIGERATION PUMP
CLOSURE VACUUM
VALVE
VALVE
WARDROOM WATER DUMP
REQUIREMENTS
EVACUATE WATER LINES
FOR SYSTEM ACTIVATION
AND FOR STORAGE
WATER DUMP
VACUUM VALVE
SYSTEM OPERATION
1/4" LINE WITH ISOLATION
VALVE
HEATED PROBE FOR
DUMP INTO WASTE
TANK
LINE DISCONNECTED
WHEN NOT IN USE
�Thruster Attitude Control System (TACS)
The Thruster Attitude Control System consists of 22 GN^ spheres manifolded
together on the OWS thrust structure, two thruster modules, and control
valves and plimbing to operate the system.
The TACS provides primary OA
attitude control following separation of the S-II, until the ATM control
moment gyros are brought up to operating speed.
The TACS can be controlled
by the IU, or the DCS, and operates on caimand during "the following mission
phases and conditions:
o
During CMG spinup the TACS is the primary OA attitude control
system.
The IU provides control of the TACS for approximately
the first 7.5 hours of the mission, and then transfers control
to the Digital Corrmand System (DCS).
o
Whenever the TACS deadband is exoeeded, or the CMG momentun build
up is excessive.
o
Whenever "TACS ONLY" mode of OA control is selected by the crew.
o
In the event of a CMG failure.
TACS thrusters are pulsed gas nozzles which provide approximately 20 to
50 pounds of thrust each.
They are located on the aft skirt of the OWS
in two clusters of three nozzles each.
Propellant Supply/Distribution
The Gaseous Nitrogen (GN^) propellant is stored in 22 spheres which
have a volune of 4.5 cubic feet each, at 3100 +_ 100 psia, and
distributed via a common manifold connecting the thruster modules.
The propellant supply and distribution system is ccmpletely brazed
to avoid gas leakage.
Meteoroid shielding is included to prevent penetration of the spheres
or pressure lines by meteoroid particles, and to provide passive
thermal protection.
The spheres are fabricated of Titaniun, and
are the same as currently used on "the S-IV-B stage.
Two filters are
used in the propellant supply/distribution system, and these are
brazed into the lines to the thruster modules.
138
�/VtCDO/V/VELL
OOi/GL/lS
/\STf*OrV/%UTiCS
corvif/xrvv
O R B I T A L WORKSHOP
THRUSTER ATTITUDE CONTROL SYSTEM
SA-292
12-2-70
RELAY
CONTROL
PLANES
FAM
REQUIREMENTS
PROVIDE PRIMARY ATTITUDE
CONTROL THRU CMG SPIN-UP
PROVIDE BACKUP & SUPPLEMENTAL
ATTITUDE CONTROL FOR CMG
DESATURATION, FOR MANEUVERS
& DOCKING TRANSIENTS
HARNESSES
SYSTEM OPERATION
MANIFOLD
THRUSTER
MODULE
(TYPICAL
2 PLACES)
TWENTY TWO
4.5 FT3 SPHERES
3100 ± 100 PSI
GASEOUS NITROGEN PROPELLANT
BLOW-DOWN SYSTEM
TWO MODULES - THREE THRUSTERS EACH
QUAD REDUNDANT VALVES - EACH THRUSTER
ALL BRAZED SYSTEM
�TO °rrr
RZZZT
ORBITAL WORKSHOP
TACS-SYSTEM CONFIGURATION
0/W-3982B
8 25 70
POWER & CONTROL
METEOROID
SHIELD
SUPPLY
THRUSTERS
& CONTROL
VALVES
�/V7COO/V/V£TILI_
DOUGL4S
/tSTftOK/AUTiCS
CO/VfP/l/VV
TACS SPHERES AND METEOROID
SHIELD INSTALLATION
22 GN
O/W-5730
9-11-70
METEOROID
SHIELD IN
8 SEGMENTS
STORAGE SPHERES
1 PNEUMATIC SPHERE
DOUBLE WALL
ALUMINUM ALLOY
�Thruster Control
Propellant is supplied to each of the six nozzles in the two thruster
modules by quad redundant solenoid control valves.
A control switching
assembly provides for valve actuation cn corrmand from either the IU,
or DCS.
The Control Switching Assembly (CSA) is located in the OWS
forward skirt, and provides isolation from other on-board electrical
and electronic systems to minimize detrimental influence of these
systems on the reliability of the TACS.
Thrusters
Six stainless steel nozzles, with their associated control valve
packages, are mounted in two thruster modules of three thrusters each.
The modules are located 180 degrees from each other on the OWS aft
skirt, and provide 20 to 50 pounds of thrust fran each nozzle.
The
nozzles point directly out and 90 degrees to either side of a plane
dividing the OWS longitudinally.
142
�/vico
ORBITAL WORKSHOP
001/GL4S
4STROMl/T(CS
COMPAIVV
TACS-AFT SKIRT-EXTERNAL VIEW
O/W-3986
9—2—70
THERMAL SHIELD
PITCH
THRUSTER
IMPINGEMENT
SHIELD
STA. 212.500
STA. 228.000
ROLL & YAW
THRUSTERS
POSITION I
STA. 211.250
�, O/
ysg-c^
/s
'•
Data Acquisition System (DAS)
The CWS data acquisition system provides for the collection of experimental,
housekeeping, crew and OWS systems status data for transmission to the
ground.
The OWS data acquisition system is divided into telemetry, on-board
display, and manual data sections.
Telemetry
CWS telemetry consists of transducers, signal conditioning modules,
and transducer power supplies, as well as high and low-level multi
plexers.
A Remote Automatic Calibration System (RACS) is provided
for ground checkout of the OWS telemetry system.
The transducers convert physical phenomena into electrical signals
that are routed to signal conditioners or multiplexers.
Transducer
power is derived from the airlock module, as is power for the multi
plexers.
The control signals, which are sent to the multiplexers
for gating are also from the airlock module.
The transmitters,
receivers, and controls for the data link with the Manned Space
flight Network (MSFN) are located in the airlock module, and it is
to these items of equipment that the various data gathered in the
CWS are routed.
Multiplexers accept analog and bilevel signals for a total of 450
channels of data.
The Remote Automatic Calibration System (RACS)
is designed to allow ground checkout of the OWS signal conditioning
modules by supplying stimuli to the electronics which results in
0, 20, or 80 percent of full scale output, for the selected channel.
No provisions exist for inflight calibration.
144
�/VtCDO/V/VELL
DOUGLAS
4Srwo/V4i;r/cs
CO/VIP4/VV
CHAN.DECODERS
& SIG. COND. MOD.
ORBITAL WORKSHOP
DATA ACQUISITION SUBSYSTEM
MULTIPLEXER
SIGNAL COND.
REQUIREMENTS
SIGNAL COND.
GEMINI TYPE MULTIPLEXERS
LOW LEVEL (7 REQ'D)
HIGH LEVEL (5 REQ'D)
FWD
SKIRT
WIRE
RUNS
<-n
MAIN
TUNNEL
INSTRUMENTATION
FEED THRU AND
HARNESS
SIGNAL CONDITIONING MODULES
TEMPERATURE BRIDGES
5 VDC EXCITATION MODULES (9 REQ'D)
DC AMPLIFIERS
DISPLAY PANEL
TAPE RECORDER
CONTROL
TRANSDUCERS
DISPLAY
PANELS
THERMAL CONDITIONING MULTIPLEXERS
HEATERS
THERMOSTATS
CONTROLS
DISPLAY
CONSOLE
FWD COM
PARTMENT
REMOTE TAPE
RECORDER
CONTROL
SIGNAL COND.
SA-289
12-2-70
SIGNAL COND.
REMOTE CALIBRATION
CENTRAL DECODER (1 REQ'D)
CHANNEL DECODERS (15 REQ'D)
SYSTEM OPERATION
LOW LEVEL MULTIPLEXERS
SAMPLE RATE 1.25 SPS, 0.416 SPS
INPUT 0-20 MVDC, OUTPUT 0-5 VDC
HIGH LEVEL MULTIPLEXERS
SAMPLE RATE • 1.25 SPS (ANALOG),
10 SPS (BI-LEVEL, BI-LEVEL PULSE)
INPUT - BI-LEVEL < 5 VDC OFF,
>15 VDC ON
�On-Board Display
The OWS data acquisition system includes on-board displays which
provide crew members with selected system status and caution and
warning information.
These data are displayed to the crew cn various
panels and consoles located in the forward compartment, experiment
compartment, wardroom, and waste management compartment.
The OWS
on-board instrumentation for meters and annunciators located in
these panels is separate from that used for telemetry.
Manual Data
In addition to the data gathered automatically by Electronics, there
is a requirement for additional data which can be met only by crew
action.
The manual data section of "the OWS data acquisition system
provides for the gathering of these data.
Log books, and use of
recorders, television, and photography equipment furnished with
experiment and other systems constitute the manual data gathering
activities which meet the additional data requirement.
146
�Coirnunication System
The OWS ccmmunication system consists of the teleccrmunicatioris subsystem,
the intercommunications subsystem, the caution and warning subsystem, and
television.
o
The corrmunication system provides the following capabilities:
Interface with the OA audio system providing the OWS with a
direct voice link with the MSFN.
(Voice communication is via
the CSM.)
o
Interface the astronauts with the airlock module telemetry
system for biomedical data transmission to the MSFN.
o
In te rcommunicaticn provisions throughout the orbital assembly.
o
Provision of a video link from the OWS to the CSM for television
transmissions originating in the OWS.
Telecommunication Subsystem;
The telecommunication subsystem is an extension of the cluster
communications system provided by the Speaker Intercom Assemblies (SIA)
located throughout the OWS.
Ihe CSM S-band communications system
provides the voice link with the MSFN.
Intercaimunicaticn Subsystem
The CWS interoonmunicaticn subsystem comprises 10 Speaker Intercom
Assemblies (SIA) and their associated wiring, and provides dual channel
oormunications.
Ihe dual channel capability allows simultaneous
transmission of voice and/or biomedical data from two astronauts to
the MSFN.
Conversation can be carried on via headsets, or the
speaker/microphone at any SIA.
The SIA are located aboard the OWS as follows:
147
�TO°RRR
~
/ISTROIVAUDCS
ORBITAL WORKSHOP
_
COMMUNICATION SYSTEM
AM/OWS INTERFACE
SA297
12-2-70
REQUIREMENTS
PROVIDE ASTRONAUT COMMUNICATIONS WITHIN
CLUSTER
PROVIDE COMMUNICATIONS BETWEEN FLIGHT
CREW AND GROUND CONTROL
TV OUTLET
UTILIZE DUAL CHANNEL SYSTEM
PROVIDE DATA INTERFACE FOR BIO-MED
FUNCTIONS
CONTROL &
DISPLAYS
CIRCUIT
BREAKERS FOR
TV
PROVIDE AUDIO DEVICE FOR CAUTION AND
WARNING TONES
PROVIDE ACCOMMODATIONS FOR TV CAMERA
SYSTEM OPERATION
CREWMANS COMMUNICATIONS UMBILICAL MAY
BE CONNECTED TO CHANNEL A OR B
TV OUTLET
OUTLET
PUSH-TO-TALK OR PUSH-TO-TRANSMIT IS
SELECTED
VOICE TAPE RECORDER MAY BE SELECTED
SPEAKER
INTERCOM
ASSY
(TYPOF 10)
443A1
DISPLAY ON SPEAKER INTERCOM ASSEMBLY
INFORMS ASTRONAUT OF VOICE RECORDER
OPERATION
BIO-MED DATA IS AVAILABLE THROUGH THE
CCU CABLE
TV CAMERA CAN BE OPERATED IN CREW
QUARTERS OR IN FORWARD COMPARTMENT
�/VfCDO/V/VELL
ORBITAL WORKSHOP
DOUGLAS
AsmorsjAUTics
O/W-4347
5-26-70
COMMUNICATION
COMfANY
MDA
AM
OWS
MODULE
SELECT
i TELEVISION
REALTIME VOICE
TAPE
RECORDER
NO. 1
M 509AT013/T020
'DATA & CLOCK
DCS
RECORDER
LOGIC
$>
INTERCOM
MUNICATION
SYSTEM
INTERCOM
MUNICATION
SYSTEM
TAPE
RECORDER
NO. 2
VOICE
TAPE
RECORDER
NO. 3
SF3 DATA
SF2 DATA
VOICE 1
PSF DATA
VOICE 2
TRANSMITTER
2 WATT
230.4 MHz
OWS
DATA
AM
DATA
SYSTEM
REAL
TIME
DATA
DCS
MODULATION
SELECT
LOGIC
TRANSMITTER
2 WATT
246J MHz
TRANSMITTER
10 WATT
235.0 MHz
0ISC0NE
& WHIP
ANTENNA
SYSTEM
CSM
TO CSM
S BAND
XMTR
�——
ORBITAL WORKSHOP
INTERCOMMUNICATIONS STATIONS
DOUGLAS
4srwo/v/i(;rics
COHP4/VV
FORWARD COMPARTMENT
nMM,75B
O/W-1375B
w°
INSTR
FEEDTHRU
TV STATION
TV STATION
INTERCOMM
JUNCTION
SIA
KLAXON
SI A
SPEAKER INTERCOMM ASSEMBLY
�\
/VfCDO/V/VELL
ORBITAL WORKSHOP
DOUGLAS
ASTffOKIAUTICS
CO/Vlf/X/S/V
Cn
SPEAKER INTERCOM ASSEMBLY
O/W-1151A
9-9-70
HEADSETRESTRAINT
CLIPS
TO CREWMAN
COMMUNICATIONS
UMBILICAL (CCU)
�QUANTITY
SIA LOCATION
Sleep conpartment
3
Waste management compartment
1
Experiment conpartment
2
Forward conpartment
3
Wardroom
1
Total
10
The Crew Ccmmunication Unbilicals (CCU) interface with the SIA,
allowing crew communication capabilities while suited for IVA.
The master alarm light, as well as cauticn and warning tones are
provided for by the SIA.
Cauticn and Warning Subsystem
The caution and warning subsystem provides for the alerting of crew
men to impending or existing conditions that are hazardous to crew
safety or completion of missicn requirements.
The OWS cauticn and
warning subsystem is an extension of Hie AM Cauticn and Warning
System (CWS), and consists of the repeater CMS control and display
panel, alarm devices (Klaxons and SIA), and associated wiring.
The repeater control and display panel provides the annunciators
for emergency, cauticn, and warning parameters with redundant panel
lamps.
Red lamps are provided for emergency and warning indications,
and yellow lamps for caution indications.
mainly of fire, or rapid pressure fall.
Emergencies consist
Warnings indicate lew bus
power or crew alert, and cauticn indicaticns include lew cluster
pressure.
Malfunction indicators are included on the panel to shew
the cause of the malfunction which caused the alarm.
These indicators
remain lighted even when the alarm light and tone has been reset.
audible tones indicating emergency, warning, or cauticn conditions
are routed to the SIA and crew headsets while in the "ON" mode of
operation.
A "crew alert" groind axrmand will override "off" or
"sleep" modes.
152
The
�rvi <:oo/v/vitll
OOUGL4S
/\&Tf*Orv/\VT$CS
co'vir*/\/\jy
EMERGENCY
ALARMS
FWO COMPT
CONTROL
O R B I T A L WORKSHOP
CAUTION AND WARNING SYSTEM
AM/OWS INTERFACE
FEEDTHRU
CAUTION AND WARNING SIGNALS TO AM
CONTROL
EMERGENCY SIGNALS TO AM
PNLS
FWD COMPT
FIRE SENSORS
(3)
FIRE DETECTION SYSTEM
MASTER RESET
SYSTEM OPERATION
CAUTION, WARNING AND EMERGENCY
REMOTE
PARAMETERS MONITORED IN OWS
OWS C&D
WARD ROOM
FIRE SENSORS
SLEEP &
WASTE MGMT
WARD ROOM
CONTROL PNL
CONTROL PNLS
FIRE SENSORS
PARAMETERS ARE ROUTED TO AM
AM LOGIC RECOGNIZES ALARM CONDITIONS
AM TRANSMITS CAUTION, WARNING AND
EMERGENCY INDICATIONS TO OWS
AUDIO AND VISUAL DISPLAYS INDICATE
CAUTION, WARNING AND EMERGENCY
CONDITIONS
EMERGENCY INDICATORS ARE EXTINGUISHED
SLEEP
COMPT
FIRE
SENSORS
REDUNDANT SYSTEM
EMERGENCY ALARM
EXP COMPT
EXP COMPT
REQUIREMENTS
CONTROL AND DISPLAY PANEL
PNLS
tn
to
SA-293
12-270
WHEN CONDITION IS CORRECTED
MASTER RESET TURNS OFF ALL CAUTION AND
WASTE MGMT
WARNING INDICATORS
FIRE SENSOR
FIRE DETECTION SYSTEM UTILIZES
INDIVIDUAL CONTROL PANELS
�ORBITAL WORKSHOP
/VfCOO/V/VELL
OOOGL4S
O/W-7363
8-23-70
CAUTION AND WARNING SYSTEM
/\STf?€>A//%UTiCS
corw F*/\rw
AM
CSM
OWS
AM DISPLAY
WARNING
TONE
Ln
i
it±
T/M
T/M
JL
CSM DISPLAY
& ELECTRONICS
AM CONTROL
ELECTRONICS
r—
CSM
SENSORS
REMOTE
OWS CONTROL
& DISPLAY
C&W TONES TO
COMMUNICATION
SYSTEM
1
I
1
i
ATM
SENSORS
j
MDA
SENSORS
OWS
SENSORS
J
AM
SENSORS
—1
EMERGENCY
ALARM
i
1
I
i
1
1
i
EMERGENCY
ALARM
�Television
The television subsystem is an extension of the cluster television
system for coverage of crew activities, equipment operation, and
experimental activity in the OWS.
The OWS television provisions
allow the operation of an /'polio color television camera and monitor
unit.
Mounting and power provisions are included in the OWS as well
as provisions for routing "the coaxial cable which interfaces with
the CSM video system for S-band transmission to the MSFN.
155
�SKYLAB NOMENCLATURE
ACS
-
Atmosphere control system
AM
-
Airlock module
AME
-
Astronaut maneuvering equipment
APCS
ASMU
-
-
Attitude and pointing control system
Automatically stabilized maneuvering unit
AIM
-
bicmed
-
Biomedical
BL
-
Bilevel
BLP
-
Bilevel pulse
EMMD
-
Body mass measurement device
ecu
-
Apollo telescope mount
Crewman ccnmunications imbilical
CSD
-
Control and display
CDF
-
Confined detonating fuse
CM
-
Command module
-
Control moment gyros
CMG
Cemm
-
CSM
-
Command and service mcxlule
dc
-
Direct current
DCS
-
Digital command system
-
Exploding bridge wire
ECS
-
Environmental control system
EPS
-
Electrical power system
-
Earth resources
EREP
-
Earth resources experiment package
ESS
-
Experiment support system
-
Extravehicular activity
FAS
-
Fixed airlock shroud
FCMU
-
Foot controlled maneuvering unit
-
Frequency modulation
EBW
ER
EVA
FM
GN2
Corrmunication
-
Gaseous nitrogen
-
Gaseous oxygen
hpi
-
High performance insulation
HSS
-
Habitabilitv support system
GO2
156
�Hz
- Hertz
icon
- Intercom
IOP
- In orbit plane
IU
- Instrument unit
IVA
- Intra vehicular activity
KSC
- Kennedy Space Center
LBNP
- Lower body negative pressure
LiOH
- Lithium hydroxide
LV
- Launch vehicle
LVDC
- Launch vehicle digital computer
MDA
- Multiple docking adapter
MDF
- Mild detonating fuse
mHz
- Mega-Hertz
mol
- Molecular
MSC
- Manned Spacecraft Center
MSFC
- George C. Marshall Space Flight Center
MSIN
- Manned spaceflight network
N2
- Nitrogen
NASA
- National Aeronautics and Space Administration
NI-CD
- Nickel-cadniun
NPV
- Non-propulsive vent
02
- Oxygen
OA
- Orbital assembly (CSM/0AM/A1M)-(CSM/SWS)(CSM/ATM/MDA/AM/0WS)
OAM
- Orbital assembly module (0WS/AM/M£A)
OWS
- Orbital workshop
PCM
- Pulse code modulation
PCS
- Pressure control system
PS
- Payload shroud
psia
- Pounds per square inch absolute
ptt
- Press to transmit
RS
- Refrigeration system
SAL
- Scientific airlock
SAS
- Solar array system
SIA
- Speaker intercom assembly
S-IVB
- Saturn IVB "stage"
Skylab
- To be used svncnymously with "SWS"
157
�SL
-
Skylab (program designation)
SLr-1
-
Skylab (mission designation)
SL-I
-
Skylab (ATM/MDA/AM/CWS) (Spacecraft designation)
SLA
-
Spacecraft launch adapter
-
Specimen mass measurement device
-
Structural transition section
SWS
-
Saturn workship (ATM/MDA/AM/CWS) = (ATM/OAM)
TACS
-
Thruster attitude control system
TCS
-
Thermal control system
tlm
-
Telemetry
TV
-
Television
VCG
-
Vectrocardiogram
VCS
-
Ventilation control system
vdc
-
Volts direct current
-
Waste management compartment
-
Waste management system
-
Transducer
SMMD
STS
VMC
VMS
xducer
xfer
_
Transfer
158
�REFERENCES
For more detailed information concerning the Skylab
Mission, Skylab and Orbital Workshop Systems, the
reader is referred to the following docunents:
1.
Mission Requirements, Skylab Missions SL-1,
SL-2, SL-3, and SL-4.
I-MRD-001B
National Aeronautics and Space Adninistration
June 30, 1970.
2.
Skylab Operations Handbook (MDA/AM/OWS)
MDC E0097 Volumes I and II
McDonnell Douglas Astronautics Company East
November 23, 1970.
3.
Orbital Workshop Design Data Handbook EAC 56694B
McDonnell Douglas Astronautics Company West
August 1, 1970.
159
����
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Charles Mauldin Collection
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
sdsp_skyl_000071
Title
A name given to the resource
"Skylab Systems Handbook."
Creator
An entity primarily responsible for making the resource
McDonnell Douglas Astronautics Company
Temporal Coverage
Temporal characteristics of the resource.
1970-1979
Subject
The topic of the resource
McDonnell Douglas Astronautics Company
Skylab Program
Apollo Telescope Mount
Multiple docking adapters
Airlock modules
Space habitats
Saturn launch vehicles
Skylab 1
Skylab 2
Skylab 3
Skylab 4
Experimentation
Human factors in engineering design
Life support systems
Onboard equipment
Provisioning
Extravehicular mobility units
Film Vault
Earth Resources Program
Type
The nature or genre of the resource
Technical Manuals
Text
Source
A related resource from which the described resource is derived
Charles Mauldin Collection
Box 5, Folder 1
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
A language of the resource
en
Rights
Information about rights held in and over the resource
This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/203/14407/sdsp_skyl_000072_001.pdf
85959cbac50c01a2d4a7596b518dac69
PDF Text
Text
�����������������������������������������������������������������������������������������������������
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
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Paul Todd Collection
Identifier
An unambiguous reference to the resource within a given context
Paul Todd Collection
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
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sdsp_skyl_000072
Title
A name given to the resource
"Skylab Experiments Volume 1 Physical Science, Solar Astronomy Information for Teachers."
Description
An account of the resource
This is a workbook for science teachers to create lesson plans around.
Creator
An entity primarily responsible for making the resource
United States. National Aeronautics and Space Administration
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-05-01
Temporal Coverage
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1970-1979
Subject
The topic of the resource
United States. National Aeronautics and Space Administration. Education Programs Division
University of Colorado
Skylab Program
Science—Study and teaching
Earth Resources Program
Experimentation
Apollo Telescope Mount
Multiple docking adapters
Airlock modules
Space habitats
Extravehicular mobility units
Type
The nature or genre of the resource
Workbooks
Text
Source
A related resource from which the described resource is derived
Paul Todd Collection
Box 4, Folder 77
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
A language of the resource
en
Rights
Information about rights held in and over the resource
This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/20/14408/001.pdf
921170356ee20a1b14bfbade0ab86710
PDF Text
Text
��ST/iTSSaST 07 WORK
HAU/MVCBUST ACQJIVrriES - AIM
SCOPE
TMs^rvtccsMit of \Jovk. cjicoBroaasGs the oan/niaeMne effort reoulretl
to optimize tho crew role cod the eysteas deslsn for the Apoilo
Telescope Mouat (AT^!) erpcriaeat*
OBJECrmS
The objectives of the progrsia eret
1.
To Id TiciCy the tcoho re®ilred to actuate, coir;i-ol and ncnitor
the
to rct.rl<Tve data casosttea ty EWl, end to ctov tlia
cassettes aboard the AEl carri<ir.
2.
To define cud cstabUsh apeclfiCGtlcns for the cquipE jiifc requited
to support the crov dJtrlng EKA trcnslatlcai, do^.a retrieval.
haadllDg and etovn^e.
3.
To cpp3y huran casiaeerins criteria thru design outroort of those
systems interfacing the orbital crew mcaibor.
forj3lbimy of lr.tv.m p^rforannco on those tashs
Identified ly caalj'Gia (inciud'jjs sittulatica) a£ crew variables
and ccostralnts, equiprent UitViatloas, and alnsica roquircmsnfcs.
5.
,
To devadop a tradning program, Inclv.dlr-g coursti outlines, ^-quipmont
description, personnel requirfiicnto, end fanllJ.ty utUlEaiion,
to lEjiltBEnt indoctrinatlca of the crew to the ATIl,
ASSUiPnOilS
The follo»7lns esovurotious will be included emong thoca to be used
in the performance of this prosrom.
1*
The Apollo Elcch II suit shall be ;rtili2ed by the sstrcsmts.
2.
Attitude stabilization, pointing and control el"'all be ccadr^rted
by the nstrona'jtCc) within the AEi carrier.
3*
The carrier configuration end flight profile shall be ccnoistcirb
with the curitiatiy dsolgnated /-AP ccafiguratlozxs.
�2
IV
ERa'.RAIl OUTUES
1«
2.
GeDcral
a.
Ka::irniax utlllT:t;tion vill l)is made of reaultn clrtaijiod from
the G&*ainl and Apollo proc^ans.
b.
l^axlrai:! use shall
-S hardware coiEpimeata and syeteans
which oro either availnblo cosomQrciaUy or have teen developed
uudior other rclr.tod prograias.
c.
The Ernsn Fac<:ors Ehciuorr.his Section shall fi-volop
a de
tailed progmu plan catega.'lsinc th? effort into a logical
sequence cf outicireted tatla. Enoh task will ocntain obJ-.ctlvos, the Kcpected proiuet, allocated maa-hci;ro, relaticn to
crthax' tasks, data rcxjuired from Gv-vamment scwraen; the plan
shall also provida for mihistone event rcvicvs.
d.
CoaveJitlonal equlpiC'^ait, procedures, end tcehniyica \;j.ll be
xrfcilizs.d ^dtenovcr possible-.'
Crew/System Jtitecration
a.
The Eumon Feotcrs Enginccivlng Section shall idorttify critical
system paramstci-s for both the ASIA and its carrie?.'. Such
factors as pointing and
Reciu'aciejj, motating character
istics, tarcct nocuisition modes, cnvircnmiintal lijaitaticns,
aoaitcring rccruirements, data rotrievol roouiremrnts (removal
and/or rsTJlaceaoat, frequ:>ncy, inasscs), aoceoslbDity and
interfaces will bo evaluntod for ccspatibmty with too htann
opci'atcr.
b.
Those system rcguireincats which constitute a eonstraiat
directly or indirectly on na interfacing system and which affect
odrc-x'soly ths crew pcxrfommco will be identified, l/hcre
possible Eltemato systems or procedures will bs x*econmcnd.cd
which will clloviate the constx'aint or improve system cffcctivoncas«
c.
Identification will bo csdo of the varlcblns and constraints
imposed ly
crew mcaber plxis
caadldiite crew support
(IVA end EVA) equipaient, cixd incorporate this data into the
task analyses and new equipment design specif1cations.
d.
All equlisEont with '.dilch tlxe crew will intorfaco ">>•^7) be
analyzed and the opdratlixg and stowage rc^xlramsnts determined.
This equirnx-at will include.
'
�3
1)
2)
3)
i;)
5)
6)
7)
0)
«
fSTA dioplay and ccatrol egjilpBent
Gu-lflcnce and aaylgatlcn equipmant
AE' data cassottas
Datii hinadllng cq^alp22?nt (tools)
D:j,ta atov.'aso crraj-prir^nt
Li'Zo ciipport equlprant
AlalocJca and nccossorlsa (hctch^a ond Ccmtro:^)
Crav Bto.'billaeticc and traiislr.tion oquipiBunt (IVA artd eva)
e. A dstallcd task aiS'Jyais iacludlng tinellns shall be conducted
baosa on the follovins najor actlvitiea:
1)
2)
3)
h)
5)
6)
T)
TciTcefc aeqtilsltion,
otabiiization and control,
Beta recording,
Data rctrio%'al,
Data Dtowego,
E-q.u.'.pnint assembly,
Crs-7 Qovcment to and frcaa the A2M work area*
The enalyois shall bo updated basod on simulation results.
f« Dwsicn opscifleatians will bs created for spnciol crf;w
eqiJ-prc it and tools rcauirlng dovclopm-uat and vhnro rcoircsory
modifi&itions will be rcec^snondcd for existing cduiui^at.
AppUcablo hiwan englaeariag criteria wlU bo ro^crorced for
boca now design and modifications.
3. Design Si^port
%
The principles of hunian factors cnginoerlng shall be applied to
all related AKI eq^iisncnt to ensure the efficient inte^tioi of
men into the design of the system.
a. The EPS Inpirts shall con^l,y with system ena^sls regvli^ments
as well as other appropriate inputs. Standard ^iS?'C-£TD-267
shall bo the basic jvcfereace doctnnsnt for the human €nginegring design features.
b. Euirnn factors cri.teria end reccmmendatlons shall be fpplli.a to
system and subsystem prelimiliary Ijycuts and related dratrings.
The approval of Isyout drawings by the IF3 group shall verify
that ths configuration end arrangamant of cqaipffo-'nt satisfy
Esn/equipmcat perfomnnce rcguiremcnts, and that the design
ccc^ilies with applicable criteria specified in Standcrd
JBPC-STD-267.
S
�c. OsTrJi fnotora prJ.r^.ir--C3 rud proccdu-vcs cboll "be GxroHcxI,
dVLTlac detail dc alfpa, -fco cquiinisnt di-avrlns3; sucli a;i pan<;l
Inycuts, vorlaipccc I'v'oui^s, eon'trols, crew ciiuipTn-n-t oad
•.•thcT dravinso <;japlofcirvs cqiii-prnDH-fc tiaccaBory for operation
"by tho ABl caiTicr crow.
d.
nFB parsccmel sliall pjarfciclpi:to In dcalca rovicvo to enuvxe
ccnalderatioa oi' crev oporationa and crew/eqjiiipra&nt intjractlons.
SimtlAtioa
a. Upon ccoiplotion of tho pxaHnicary task orolcrsls, e. airulatloa
plzin vlll te vrittea and iiapl€n:ca:tod coverins the follcvdnc
factors:
1)
2)
Critical task? to he siaulcted,
?.2c:ar:-adcd a-.'le zf sl=;latlcn - aicohanical, SC-135, Itrt
task, etc.,
3) Sketches of noakeps required,
k) Facilities required,
5) SiEulatloa schedule,
h.
The E-rrnn Factcrs Fa.-l2-~Sccticn skall write the .ietailed
test prccedureo and suhnlt iioakup deslea xecpiirecents for
the approved tasks to tie ajjprppriate doslGu s^^cups,
c, 1F2 personnel ohrOl monitor the operation of all almlstitai
tenting end participate in the dcelga evtOxvitions conducted
on ccn^ncnt mockups which interface the Jaaaon ope rator,
d.
Prccc3ural changes end time iseasurcnients prodv.ccd oy sjarolrtion
testing flhc.ll he incorporated into the detailed taok cna'^'sis,
RcciBCzumdcd design changca rssidtlng from aiusulatioa rnd/OT
lacckup drsloi evaluation shall be submitted by the Hunim Factors
Eagineering Section to the appropriate design groups.
Training
a. The ATM task roqulrcs^rrts shall he evaluated and chose ckiU
IsvcOa required to fulfill the oihital functions shall he
presented.
h.
Prcm the detailed task analysis, H?3 porscmei sha^ldmtify
those tasks vhsre training is neccssa^ end ^ dc^. of
training xequirad to ensure their desired perfonrance,
c.
The Euman Factors Englnoerins Section shr^
training support personnel b? special-ty, traininc level «nd
certiflcaticQ.
�d. Training eqjilpncat and fanilitica shall be Iclentifici
quantity, configuration, ntate of developEien-fc, location
(if cxiatinc), and need date.
e*
^
A trnlniDG pr Cfac outlintj shall be developed. This will
include:
f:ilGli-t crew.
^ w <)•
rfJla ••cla3s:-u9a ir.";U:ri^il and equipacnt.
3) TraiDc?^s.>
it)
f
p^racnnol and expcrlacnt
c. ntrootcns.
'4
"'
Cvurse cutllnoa, frcquenc;' and duraticn, as vc.iJL as cquipasnt
descriptions, iacludina sJffitchca, will be pro/ided with the
traininc plan.
ESPECTED rCBtJLiTS
The fs-Uc^rlnc docuacntctitn will l>e submitted
Saelneerins Section:
the ffurnnri Factors
1. A listing f the syr^tems and/or prtcedures rolatad to ATi >4iich
ara incoirpatiblo with bunaa p>.arfQraanoe crltej.*ia bti!? ov&r i^ch
the contractor has no direct ccntr.1.
2,
Related mission ccnstx'aints, A3S-I and corxder design constx'alnts,
pers.nal equipment ccnstralats, and crew inrpi,i{ed constraints.
^3*
A detailed task zinalysls and tiffiejlne conrncncing with th?
pitspamtlon for iZA torcet cc<iuisition and cndinc with tha
stLwace of the data cassettes within the AIM carrier ofter the
final m.
Design specificoticns f^r bcTth newly develvped crow sxQ^io-rt
equipment end m. difIcatlon tt. existix^g e^ilxKoent.
5<
The simulnticn plan and detal.Icd simulation results, concluslLns
and recoBEcendatl ns*
6.
Desl{pi cvaluatl n inputs ux related AT:-! subsystems requiring
crew/equipment Interactions.
7*
A training plan including course descripticn, material end
eqpipBient requirements, skill levels and fcciU'ty rcccasnondstions.
8,
A training irplementatlon plan containing a sched'alo of overall
training events propcssd for .M!-!.
9. An outline and content description of an A33i flight crev training
and familiarization manual.
��ATM FnOBI.TO AREAS
1«
The general cost of EVA in ezcpendsblcSi crew
end crew fotigiio. (See attnchceats 1
2).
hours, oafoty,
2*
The iJBpact of EVA whore vehicle configurations Involve crew
traaafers by EVA. (See attachaent »,
3*
Other EVA consideratlono.
h.
The baeic everlond of the crew In reopect to nian hours nvailtible
for expcrlrerts vorcus the can hours required by preaent experi-.;:ent dcfinitiona. On 211/2^ this chows 502 aaa hours
avnilablo veraua 859 cian hours required. (Seo attachoem; 5).
5»
Tho problea of dovolopinj and getting iraplcnentcd into
exporinont dcaigno. basic principles of huaan factor cngineaj*ing
and nlooioD oporation rcqu\rc-cnte. Thio io an cxtrc^caly tineGcnaitivo function. (Sea attGchoent 6 for a TOJV prolir-inary
cot of the types of dntn that cuot get factored into the
exporicent and carrior oquipnent designs).
(See nttocfaj^ent 4).
6. Stabilization and Control requlrecents for ATM are the ooafc
otringont ever attoapted in canned space fli^t. Consldorable
study and cinulntion above that already ur.dertakon is probably
required. (Soe attachncat 7 for eooe of the basic iteoo re
quiring work in this area).
7«
The I/EH io en extremely poor vehicle for extended habitation.
Much huson factor effort nust be expended to provide reasonablo
comfort to the crow. (See attaehnent 8 for oone considerations
on this item. Also, refer to the section on crew habitabillty
in attauhoent 5)*
8.
See attacbxcent 9 for other AiOl Kan/^nchine Considerations.
�/o
�o
0
EVA CREW TIAU COST
.
vy
CO
32
u CLOSE 12
5
REEVA
«
U2
u
lUTCH
O
fj CH.^RGE S
o
w S
2
and
o
u
BPLSS
REPRES- O
D O CO ^a
and
SURIZE
kJ
STOW
u u
CABIN "a
STA®B'ir;
b. -O
k
3
u
ec«
2s ce
•••; ...'-v8
&
u
u
H
Q
0*
5
§
2
cu
O
b
Q
b.
I','-"'
CO
CO
ASIRCr^AUT
f .
CO
R EST
(2 lir)
CO
< CO
•i.V
CO
3VA.'
As-rn(>"""
HAUr
CO
CO
CO
CO
h:,'
-
9
•i.'i
''
A';--' 0
*'. 'I •
a™A /Ws}»
^
'"•"-l'
'• • " •"
.TiMS.. -(mlnutos)
8
.1.
so
X
60
X
70
X
80
90
K' •l-. Slv
"-y-.
^rr ;.:
£•'1--•'• •- "'-H
• • •'
*•• '•• *
r- .*» •
'>
K
. •A
•
J- r ••"•>'-"*':•
'• .'•f'-
,
CO
SVA
-_yS•.•:-••.
»V ' • -
i.. •-•:- .?:.v'';-.--.I
..•••• „ •. -t-
o
:
bV.'
J.
100
TOTAL aiANHOvHS,® 0* .(3 X Period of Actual EVA)
Attnchm^nt
I
�o
O'
•.» .2J ' ...• • .•
».
:j:
o
,:.;1;;-."V•.'-•»-> --'•
..~ >
'•
-. •
OTHER EVA COSTS t
fr •• • > •
CONSUMABLES per EVA
:r • ••
ft-n
*-» i-
'1-^
^ •<
t—;• f^...
•;»
w:J.'. --jy
lb
Oxygen
Cabin Loss
7.0+
Consumed by
Astronauts (PLSS)
3.0+
Umbilical
6 IbAr
Water
I • • -.• •-.
»=,•
f-.-'. •'
14.66
LiOH (Contaminant
Control Cartridge)
Fuel (Stabll^e and
Station Keeping)
7.2
?
SAFETY FACTORS
Raciiation Exposure
Meteoroid Exposure
Astromut Fatigue
Lo^v Systciii Safety
.-V
-.rv '- • -•"• ••-•
ADDITIONAL REQUIREMENTS
Wt (lb)
PLSS
Protective
Oarments
64
Thermal
50
Meleorok1 15
Safety Tethers
10
EVA Astronaut
Maneuvering System 10-140
PLSS Replaceables
Battery
Contaminant
Control Cartridge
Rescue Kit (est)
TOTAL
Vr
rVol (ft^) Quantity
3
2
.5
1
2
2
f,
.5
2
f- .
2
f"
>>«-
<1-9
^'
I
»--
t_ -
V-
5
.05
1 per 4
EVA 'S
t
3,6
10
.04
.5
167-297 6.6-15.8
1 per EVA
1
i-r-: . -
S'-.T
��'xHE g/A CO?g.TPTTm PPnarr^f
Pcyhapo tho aoot olsiificeat diffeiwfo
AV
tionc lo a >oquirci=ent for rcEr.lsr comaytinn- toVork
conflfpiraDr. MnoUcr and tho Altorrjtc /;a ccnfi-ajTc-tion S.^r.5^. i
clic-.;a that ••.•hllo EVA caa bo RC'-canlioh"^
ia'iv-H-t' i
i^^iperinent ha.9
l".bcrion3 to the crc-^. Ar.v clo^ig^
f-fficalt £«:cl
nhould bo cnrofullo- aea3y=c;d and tho con;cqSSca
PCrtcdlo EVA
tho cafety foctoro and worlclcada Ir.volvod, every offo^ ^
^
nxniniro tho qi-mtlty of m'o required.,
o^^^ort ebould bo ca(\o to
D..
«to oori in tho l.:li/Ai;.. Ho oo-ola flea no' rtc-ro-rhir^f^^f
=0
tfor.trbsp, cater the AL, ccciiro th-t
j
^ the S-Iva
veuld then AopTczav.^zo the AL and opcts fcha'^A^St°r
Eo
tfceeo aetlvltlcn tho r.otro"-auJ- ^,0 v,,,
Wij.le .10 t-ao doing
thocu-h a oiailnr cot of ooUi-ltioVin
^
prepared, tho firet aotrone.ut would then
a '
ucro
cuter the LEd and hook up ore of tho Dtsr£^va Iv^
^'^5
Ea would then traacfor hlo Icrg urb^i^oal to
K5?oilicalc to hio cuit.
hock it up a-d diaooraoofc the .4ord:"j^fiMaeal
^^^roraut who would
thou travoroe back to tho AL v.hile tho
aatroraAtt would
froa tho open hatch of tho Ii:i. Follcsr'-'^
procrecs
ecouro tho LEj hatch, rcprcc-er'-e S^rVv
S®
as'crouaut would
by the Chart, nfto? ah.a 5o
the bSi:
^oo'sin^^SiSr&
for short tora taslaj. Eowovo- the PLSS
vould bo loncer. It is alco based ou^o dcvfi«n-.'^^^
^^5
althoush tho tisa
icfJiJuS'coSfbe
^tnntit. Of on,,. oon.«i .^rS; =-.t'rnSSt51S'?::o1^°Snnn.
requeued. Due to'^voMclo^coSwrftiS^S^"^'^^'^^ ® sindlar EVA would bo
r. desxrablo and the P15S vouid S S ?
®''^ rnbiUcal would be
fiE •-ration woald be porhaaa 10-35
^
probably ccnoiotius o* haadholde and riii
Addittcnally, r. t^alkt.'sy,
scroGo tho entire lorgth of tho coi^±s^lo^
developed
of E/Ariri-iU
So
P-!>teo
ri:;o Oithor tho Dr. MuoH^or
« EOtivity is, orflcr to
Ito root ohviof.s Kthed of aoins So iT^o j™ ".nfisoraiiono orootloal.
nu tho noceocax^ natch rcouii-c^onto"^,
^^ZlZ
Attachc;cat ^5
�/ .
O
•
DEN OO6232 (11-62)
ZVA
9
FOB SHIFT-CHANGEAUELLER COHFIGCRATION
Hlnixnim
Time Costs
Activity
Don and Check Out Suit
"
•4
filter and Secure
long DnbiUcal
AL, Connect
^2 Costs
20
10
Depressurize AL
3.5 lbs
Open EVA Hatch
Traverse to IM
filter m. Switch to IM Umbilical
Monitor #3 Traverse to AL
Secure IM Hatch
ID
'
5
12 lbs (DmbiUcal
System loss)
ID
2.
Repressurize IM
15
Doff Suit and Stow
15
91 Dlnutea
6.9 lbs
22A lbs
Developfflent Requirements:
.
•
»
.
150 foot DmbiUcal
"Clothesline" Traverse Rig
IM Hatches for Multiple Usage
External Lighting
CHART #1
^
�o
0 ^ t66232,t1I-6Z,)
CREW SCHSMJLE
EXPERIMENTATIOH
1
1 WATCH NAP
EVA
n
SLEEP
SLEEP
0
2
^
SLEEP
EVA
X
6
8 1 0 1 2
X
X
X
1d
WATCH
EXPERIMnfTATION
WATCH
±
L
•4
tVA 1
KAP
SLEEP
X
X
X
1 ' » I 6 I 8 2 O
2 2
2 ^
X
2 6
2 8
3 0
J
3 2
3 4 J 6
Mueller Configuration and Alternative 1 (3'* hour cycle) - l8 Hour Exporinental Shift
tXPERIMQITATION
2
SI.EEP
ATCH
E
SLEEP
^ATCH
EXPERIHENTATIOM
SLEEP
ATCH
L
X
X
X
X
0
2
4
6
8 l 0 1 2
X
X
I
I OPEN
ATCfl
WATCH^^SLEEP
OPE» jEXPER.
X
X
X
WATCH
X
1 i f l 6 l 8 2 0
2 2
2 %
Alternative 2 (24 Hour Cycle) - 6-8 Hour Ibcperiaental Shift
CHART #2
I
�THE EVA COK^UTina PSDBLEH
Pogo Z
Md eiDlInr activitico. In fnjperiod the iiidivldiu 1 vdU ebtiiln
Zh bouro of nlccp altho.n^ It would not be diatributcd 1
^-hour baoio. ^ala cycle rey vcxy veil rot bo practical from a lloT
^
®®'® ccaaideratioa cucfc as this ci;ot
*?
coafigurstiono r-ractical.
The cocond
of Clwrfc ^<2 soroly indlontos that la th® rblrt-oieoro
^ Altcr^to ilZ ccnfiguratioa, it is -pooaible to wori a ;iorBal
o-hour day; 8-hour olcop cyclo.
f^wbaj.
Chart #3 providoa a r^r-aiy of opsrational differonccs botynoa the
throo confasxiraticno for a 7-dry mission^ In ordor to nal-:o tho KncLler
c^isuratiou and the Altorretc #1 corpotitivop tboy aro both barod on an
Ib-hoi^ cxporincav vork cchcdulo as coapai-od to on B-hour work cchedulo
for Altcmsio s^Z. Bf.ocd on tbia prsstce,- there ia no scrioua pa-ralty in
t^e available for or-pcnrscnts between vaiilona config-jratioaa. Howctrer.
thoro io a rajor difforccco ia tho aurbcr of EVA»3 aiid pr« est^isation
cjclco required by the Altercate ij^ and tho othor two coalinuratlono..- If
tho work schedule is changed to a 12-hour oicperli^sat duty cycle the iju-lbcr of
EVA s Involved in the first t-wo configurations changos frca 18 to 28, and tha
aur.oGr of prooourizatioa cyclca chrPees from 10 to 15. At tho onso tino. the
amount of cino availrJjlo for experijcsnts crops to about SG hours. Althou^
tno txne available for AIH crpericoato io not greatly different for
Altaraato ^Z,
I
Another feature choaii on tho eurcaaxy chart Is the feet that tho tins
required for the crcv to rcatcfsblo into the CSH for ccGrgoncy abort is
conoidcrobly loca for tho Alternate ^ corfigyrstioa. llhowieo, tho chart
chouo an.orrdcp of ranking due to tho hazard of ETA. Bccavso of the fTcat
ni^hor of EM'S required for tho first tuo ccnfigurations, there io a conoxdorablo spread b-t--.:r.a the number ono rating of Alternate j^S and the
oocond and third ratings of tho other configurations. Another factor in
this rating io the fact that the EVA at the cad of the work shift id.ll bo
ficccoplich.-d by an. astronaut who nay already be hi^ly faticuod cud aoro
prono to accidents.
Ono pln.co on tho chart ropresento tho relative crow vorklcad for
Mcccbl^g the basic configuration. Tho configunitica i?2 would be acconplicsc-d by a relative norcal Apollo dockljag maneuver. In both the Dr. Mueller
wd Alternate #1 relatively complicated eijace erection techniqueo would bo
involved. Horo again there is a wide spread between tho #1 rating and tho
comparative evaluation of the second and third ratings.
In GuiEmary, from a crow operation point of view, thore ia a caior
bailee ia favor of Alternate ^ coafigurutionc Between tho Dr. tfuoUor
Alternate j^^l there is little choice. It would appear
that the ccmautxug problem is easier for the Dr. Mueller coafisuraticn- but
the probloa of tho original structural build-up would be somewhat co«»'
difficult.
Attachment #3
���OTHBR 17//. CO?:SI03?JVTXOIiS
nVA cyclea and ducatloa
To Reduce crcu workload to realistic level
Insure conpatiblllcy with support equipment, I.e., life support
ayatCD, caneuverins unit, A.L. hatch seal
Reduce o.xygen required
By Opclmltlng E?A procedures
Eliniinatlng tasks not demandlns direct Vii,twiqTi input
Siaq>lifylng required EVA tasks for mlnicaun crew e:;erticn
Insurins cocpatlble hardware design, i.e., cascecce fartoncrs,
iiandJ.es, tethers, controls
Insuring optimum equipment Location for crev aecesstbllity
Determine 5T7A support hardware requirements
Including SLatilisatlon hardware
IhuiGuvering oquipiscnt
IUvrnlnaticn requireircnCs
«
Data cnsoette/crnw tethering harduare
Data cassette protective equipmnnt
Casratte attachment/detanhmcnt Cools
Airlock hatch actuation toolc
Sy Idoncifylng ajohility, dexterity, and visual acuity requirements
for ea<:h task
Simulating critical tasks to develop optlmua procedure and establish
support requirements
Analysing available support hardware far application and coEpatibillty
Identifying AIM interfaces for crew tciherlng
Dctcrtiinlag ATM data cassette envlrorjiintal lltaitations.
�cj-vj-.z/oycCem
By ••
durlog EVA
«
E\-nluatln3 AT^l/carrier attitude stability oodoo
Analyzing crew cquipcoafc failure wodeo
Coternininc eonpliancc of AXH eyptora with applicable hiaaan enalncarinc
critcfAa and avallablo Gcmini/Apollo data
Siiaulatioa of critical casks to insure reaccnablc notabolic loads
EctrbXiehins safety procedures to be undertaken in the event of an
ejr.crgeacy
Datrcnnlning ACS conotrainto on crewoan
Insure crew/nisslon cosapatibility during EVA
By Scheduling EVA for maximum operation during orbital light side
Schcdiilias EVA during orbital perioda poesecsing mininun hazard,
i.e., HKteorold shower activity. South Atlantic anomaly, solar
radiation
Scheduling EVA during periodu of minimum mieaioa operation
��AHAixsis OP csm camusmTnyss
MlSSICai 2U/212
SEP 14 196S
�TABTJS OP CCKTEiTrS
BTTHOljirCSIOn
Mission OETECTIVIS
MISSION FUGEP PROFILE & 0PERAa?I(M3
EXPI21B5ZNP OPERATIOnS
EVA E^UZE-IK® REQUIBESIEnrS
CARRIER RECa-WEimATIOES
CGRCLGSIonS 3s RECaM>-IBil!A!riOK3
�Sunxiry
The anolysij of missico objectives, flicht profiles, spacecraft
operations, cxpci-lmcait considerations end opcratioQS, and, carrier
coapai-iscos for Liisoicn 211/212 is presented with ccnclus'lons and
reca-asendntlons cs related to crcv c^naldoratioas end optratioas.
The C3M/nc:'l/ATM offers crew advcntac«33 not available vrt,tMn the CSM/
LEl/AlIl confic:tu*ation. All ezipcrimeats con bo cccomplislicd with a
reduction in the quantity but not the quality of desired infoxniaticci.
The mission will bo trying and difficult for even the niO£;t MgMy
motivotcd astronauts.
Introduction
The jiurposG of this study is to 03Cf;rtaln, in preliidnary form, the
operational constraints end potential problems associated with crew
participation during the mission. Fnctox-s considered aro mission oV
jectivo, flight profiles, spacecraft opei*atlcns, experimnnta cparatlona
and carrier considoratlcai. Conclusions and rccaumendatians are included
for xiso by technical personnel.
There ore many factors that can have an Influence on crev ciperaticaia
during orbital or lunar missions. Some are very real, and can be evaluated,
Willie many are qvdto nebulous and are a function of an individual crev
member on a specific flight. Many in tliis category can only bs ovoluated
at this time by Intuition and opinion, with little or no firm facts to
substantiate the conclusion. Many of the opinionated iti^ms nust await
actual Apollo flight experience before real answers are available.
Therefore, this study will be revised and upgraded as more and
better information becomes available.
Basic crcv considerations must be evaluated for two categories,
i.e., Intra-Vchiculor Activities including all spacecraft operations,
hcusekceping, personal hygiene, and s:q>cTlniant operations; Extra-Vehicular
activities. Including all preparations for external spacecraft cad experi
ment operations, crew and cargo transfer, c:cternal maintenance and re
pairs, and emergency operations including astronaut rescue and retrieval.
The crew represents the most fleoible system contained In the space
craft. It has a demonstrated capability of rapidly adjusting to the
situation without severely effecting adjacent systems. Dual or triple
redundancy Is incorporated depending upon the number of astronauts
present. Adaptation to limited and restricted operating envircnmcnts
has been rei>eatedly accCTplished with selected personnel in test flights
for years. Eowcver, flights have been a relatively short duration limited
to a few hours, or a fov days, in the cost extreme cases. Since the main
objective of AAP Is the extcmsicn of luanned space flight function, eveiy
effort must be exerted to increase tba ccanfort end working conditioas of
the astronaut.
�MISSION 0EJECT3VES
crct; consideratiors
�4
r
Mtjjton O'o.lcc&lx'a
The objective of Mission 211/212, as specified by HASA. is ns
follows;
'
1. Conduct solnr astranotry observations using
es^erlmezrt sensors.
ircunted
2. Store cnrrler-AT2I in orbit for subsequent rcndc-avdo and
reuse (see tUssion 213 - Lamch CSM into rendezvous orbit,
coplnaor 'rfith carrier ATM from Mission 211/212),
*3. Conduct rendezvous oxparimc-nts totveca CSM and corricy
Vehicle for lunar rendezvous problem analysis early In
flight program.
Observation and zacnoureoent of extended duration space fUrJrt
effects on crew mnmbors,
*5. Conduct synoptic weather and mapping photogi^by cjcperlmeat
using CSM as espsrliuent carrier.
C
» Objectives not supplied by HASA.
��A,
Mission 211/212 - MISSION PROFILB AKALYSIS
o A
doecriptlon for 211/212 as deocribed In C-2-2n/212-2
9 «i>"3t 1906, forna the basis for theao ccmmeats as to obe relAtlve
dcslmbillty of various possible miaslon profiles for Fllclits 211/212.
TABLB I
msslcn DeaerlPtloaa - 212 Firaf. launch
Method I
212-LIi;i (ATM)-Dlr. inj. 200 n.ol. circular
211-03.1-Dlr» inJ. 120 n.mi, phuslnrt orbit
2L1-.CSM dock •.d.th 212 UM
Ccnduot all e.^ei'icont8 In 200 a.mi. circular orbit
Ccamonts; All ej:poi1m^ts vou-lcl be conducted at 200 n.ml. Altitude
LF/
^eter tb^ doslrGd. It may be neccssa.'y to separate
LKi ^ 0^.1 durirs ATM experiment so that more than one exneria-at
can be ccnaucted simultaascaisly. This method is rated #4 for crew
ccnsideratlcn.
Method II
212-LE-I (ATM)-Dlr. InJ. 200 n.ml. circular
2^-CoM (RQck)-Dlr. inj. 120 n.ml. circular phasing orhit
211-Conduct mapping expcrriments
2L1-Transfcr, rendezvous and doci with 212 lEM at 200 n.ml.
Conduct AI2.I experiments
Commits; This launch and orhitnl coquence is rated #2 and pcnnlts
E^lmum utilisation of ths manned vt?hlclc at both the 120 n.mi, end
200 n.mi. orbits. Furthermore, If the LE-l must be separated frcm
the CSM during the ATM cacpariinc.it, separation time fmd distance can
be ^^mum (5 miles or less), This is required in the event the LE-I
tt^t be abandoned or cn oi-bit short is required. It should bo rcalizea
V Ii.
^snnod LE.J, when separated frca the OSM, brs no orbital
rendezvous end crow transfer mist be acccmpUshed by ^,he CM prior to aborting the orbit. Therefore, a ciinned
f
c
i
r
^
d e s i r a b l e c c n f l g u r a t i o n e n d s h o u l d
oc avoided. In the event this eonflguraticn is rcqvirod, the LEI
crew is placed in a very hi^ risk situation.
�I-tethod III
212-LE:I (A'.v:-L)-Dir.inJ. 200 n.ML. ci.rculQr
2L1-CSM (nr.elO-Dir. inj. 100 x 200 a.mi.
211-CuM i;i-2n3no30 rjid. dock to rack
211-COM (Rr.ck)-P,cadozvou3 witk 222 7JSd la 200 n.ml. clrculer orbit
2n-CSM imdcc]: rack
211-CSM deck to 212 LS-l cad troasfor two (2) crewmca
211-CSM vadock 2:2-LS-l
211-CSM dock to rock
211-CSM (Rcck)-Ti*an3fer to 120 n.ni. circulor
CcEduct roappins o:qx»rlEent3
211-CEl (Rr^k)-Tj.'ca3fer ead readozvous with 212 LEM
212-Ln-l crow (IT/A) i*cGovcr rack data
2U-CS-I undcxk rack
211-CSII dock to 212 LEM
Cczmcnts; SMa cequcacc Is nnich too con5)licated cad places oa uaac-cessory risk oa the 2-naa crc-w o? the LEI at 200 aoini. cad the CM
at 120 aoml. This ssquencs is highly laiticceptable for crew ocfety
la the event of a LK-l failure or orbi\>al abort.
^tcthcd IV
212-LE-: (AIM and MarFplns)-Dir.iBj. to 120 a.mi. circular
211-CSM-Dir.iaJ. 120 x 200 n.mi. phising orbit
211-Circularize, rendezvous and dock with 212 LSI At 120 a.mi.
Conduct all experimcats
CSM/ISI transfer to 200 n.mi. for LSI (AE^) storage
«
Corx^nts; This, method required lamcccssajy orbital changes by the
manned vehicle, Sxiggest 211 CSI-I direct inject into 120 a.mi.
phasing orbit with lE-I.
Mochod V
212-LE'I (AS!d)-Dir. InJ. to 200 n.mi, circular
211-CSM (Eack)-Dir. Inj. to 100 x 200 n.mi. phrLq^-ng orbit
211-C^ transpose and dock to rack
211-CS!'! (Kack)-Readezvous with 212 LES'l in 200 n.ml. circular csrbit
Transfer tvro (2) crewmen ty E7A from 211 CSM to 212 LEd
Conduct ATM and mapping eaperimants
211-Cad undock rack dock to LEd
Ccmrasnts; This method requires transfer of the craw by E/A and
undcoking frca the rack by ths CM prior to dockdng with the LEd,
Again, it veold appear that more time than is accessary would be
spent ly the two cre^mien in the LEd with soparatlcm from the CSId,
Not a desirable cocdition.
�Mothcd VI
(ATTO-Dlr. inj. 200 n.ffi. circular
Sll-cni (Rcclcj-Dlr, InJ, 100 x 200 n.iai,
2ll-CG:i-TrQnspo3e and dccic to r:ick
2.U-CS-I rfadcrA-ouj with 212 LE-i zi 200 n.ol.
Trsjiafcr two (2) ercwxa to LE-1 hy EVA
an-CS-i (EccJ;)-Tr3n3fcr to 120 n.ai. circular
Conduct uapiplnc c-^ipavliccnt
"^o.^OO n.El. ond roadezvoua with 212 LEt-l
LTL-I crew recover data (Fv'A) frca rack
211-CSM undcck froa rack
211-CS:-I dock to 212 LEM
reecnreiy of tho two cwowtoii
4
5
I
n.ai., CSM at 120 n.mi. Tb:
method is not accejftable for safety reasons.
Hlssloa PoaerlT^tlons - 211 First
l-Icthod I
^ n.nO., itolns orbit
(A!Ei'I)-Dir. laj, 200 n.mi, circular orbit
n.mi. and rendezvous with 212 LSI
211-CSII-Dock with 212 LEI
Conduct aU ci^crimcnts In 200 n.mi. circular orbit
This sequence is acceptable for crew safety. However,
tac 200 n.mi. mapplns orbit is not desirable when 120 n.nl. Is
preferred. This method is rated #3.
Mothcd II
^ ri.Toi. circular phasing orbit
)^®*)-Ccnduct mapping and weather crocrimeirts
oH**^
n.mi. circular orbit
211-CSIl-Transfor, rendezvous and dock with 212 LBI at 200 n.mi.
Conount AIM esporlments
Co^cnts: Tills seqv.eace is profcrrod from crew consideration and
^lers better utllizatim of e<^imezit than Method n - Table I.
This seijuence Is rated
from crew considemticn.
�J'f.thccl III
(Krj?ls)-Dir, Inj. 100 x SOO n*i!il* pbsslng crbll;
ail-CSM-Tmnflpo?3 oad dock to ztick
212-IiEJ (A'iM)-Dlr, inj. 200 n»ai« circular orbit
CU-CS!I-Uadcck r3ck
211-CS:!-Dcck to 2J5 LTSI and transfer two (2) crovcsa to LHI and
conduct /.Ti'l c:ncriacnt5
m-CSM-Undcck 212 ISI
211-C3t-'-Dock to rack
211-CSM (Rr-clO-Tronsfcr to 120 n.ml. clrcxOor orbit
211-CSM-(Rr.cl:)-Conduct rcairpins experiments
211-CGI-!-(Rack)-Triia3fer and rendezvous 222 LSI
212-LE.I Crcv-Rccovc-r rack data by EVA ,
211-CS-I-Undock rack
211-CSM-Dock to 222 LEM
Cp^f.nto;_ Tills ssthod Is too cccipllcated end prefventa rapid racoveiy
of the u^l crew by the COM, i.e., lEl at 200 n.ml. (SM at 120 n.ml.
Totally unacccptablo for crow safety.
Mathod IV
211-CSI-Dlr, inj. 120 x 200 n.ml. phasing orbit
212-LEI (AEI and Mapplag)-Dir. InJ. to 120 n.ml. circular orbit
21l-C3:l-ClrculGrlr.e, rendezvous and dock with 212 lE-C at 120 n.ml.
Conduct all e^crlments
CSM-Lni transfer to 200 n.ml, circular oiblt for lEJ! storage
Co^T^onts: This scQjionce requires •unnccessaiy orbit changes
the
in order to rendezvous with the LDd, I.e., Cai 120 x 200 n.ml.
LC-I 120 n.ml. This method Is more ccmpllcated than necessaxy.
2'Icthod V
211-CSM {Rack)-Dlr. InJ. to 100 x 200 n.ml. phasing orbit
212-IiIiM (ATM)-Dlr. InJ. 2C0 n.ml. circular orbit
211-CSI-Tran3po3C and dock to i*ack
211-C3M (Rcck)-F.eadGSVou3 with 212 LE-I in 200 n.ml. orbit
Transfer two (2) crewxea by E/A from CSM to LBl
Conduct AIM and mapping, and weather experlicents
211-CSK-ltodcck rack and dock to lEi
CwEnents; Thin method requires jT/A transfer cf the crew from (^I
to LSI, and undocMng from rack prior to docking with LS^. Appears
to be unnccesseiy, conc'lic&'tc'd and time ccaisumlng If abort cf the
L51 Is required. Sot a desirable sequence.
�VI
SU-Cfw'I (R?.cl£)-Diy» InJ* 3.00 x 200
phcolng orbll;
211-cr.l-Tro\ij3po3C» JiTKi do::!: to rack
212-U2I (ATi')-B1j*« IdJ. 200 n.iai, circulcs* orl>lt
211-C52! (Pv';rl:)-Rond02Vc-ao with 21S LEI at 200 n.iai. orbit
(2) crcv.7.:.n to 212 LF^l by EVA and start A214 c::pcriacirto
211«CS!-I (Raok)-Tran3for to 120 a,ml. circular orbit
211-CS:i fRrok)-CcvnaE.ct mipplns csxpo-rlmcnto
2U.-CSM (Racl:)-Traasi'er to 200 a>mi<i cad readezrvouo with 212 LSI
Lri crcv recover data from rack by EVA
23J.-CS'-Unclcck froia rack
211-CS:i-Dock to 212 LSI
Cc-rr-ents; Totally unacceptable due to co.':c)l£Xity and orbital
rci-m-aticai of manned LE-I cad CSM, i.e., LM at 200 n.mi,, CSM at
120 n.mi* Dot a deolrablo candltlcax.
caicLUBicn
Table 1
Method I
Method n
Method III
Jlethod 17
Method 7
Method VI
i?2
Dot aceeptablo
Requires otra
corbital cbt-i^es
Rcquirco EWI and
cornpllcatee
emergency
Dot acceptable
TeCblo II
#3
^1
Dot c.ccaptable
Rcauires extra
orbiial chc'eges
Pequirca EVA nr^d
coaplicatos
emergency
Dcrc acceptable
Table I lists tha 212 launch first folloircd "by 211 (manned). Table
II lists 211 launch first foUowad by 212 (unmatmed). At this tino, uo
cen state tiiat It is preferable to oeccroplish all rendezvous vith immnimsd
vehicles having a passive rathc-r than sn active role. TfcGrefoi*a, the
unmenncd 232 should be placed in orbit prior to launch of the mannad 211
80 tnat all Dnnojvcring is porfonncd end ccntrolled by the crevr vchi-clo
(during its poxfcrcd phase). This is preferable frcm safety and pfcyclological reasons in that the crev is actually initiating and temlnaticg all
povnred maneuvers and can tal:o abort action in tha event of a coHicion.
Furthermore, the pilot has the plysiologlcal advcntaga of asoui'ing thTt
he has ccn^plete control of the powered vehicle and con utilize his Judgment
OS rcq\ilred. Therefore, ^AlsrQ the choice c::i3ts. It is always preferable
�to plsce tho unEaonGd vehicle In or-bit prior to the Inunrh of the n enned
vehicle? or In ths event the arjsiiGd veMclo is la orbit, to pla-- tl s
^ f
.-nd P3rmit the tnsnn^d vgMcIo to
Inltloto o povr3rca phase to accorTOlish the rcndcsvoia. 3aocd ou theea
^yr^.1^3, the first choice frcni sn operational poii;
u
Mctaod II of Table II as described belov:
^
circular phealns orbit
mapplr^ and weather expcriiaerrfcs
200 n.jnl. circular orbit
? I
' rendezvous and dosk with 212 LBl at 200 n.ml.
Conduct Ani ej^ierlaents
B,
OEERATIOHAI, MJIHEUVER RTIQUIRGIEnS (mssion 211/212)
r.f
^ forcGolna elLosIcci profile, tha folloid.33 is an analvsls
nancavera rcov_lred to perform the mLsslL ^iSS
recard to ®^sriiSwat ccaisldezatlonad
FnrOK; 21-1
1.
Assinna velocity tilnmins and ffisncmvcrins
is performed by S-r/B until
separa-.ion. SMa includes orientation for tknspositiS Ld dcS^.
2.
Tra^positlon and dwhins (starl;
+X axis fcn.'oid and opprcximtely
in the trajcotciy plane, +Z axla vp) ~ hO minutes.
^
a.
b«
c.
d.
e#
f.
g.
3«
Add 2 FPS forvrard velocity to CSIi,
Perform I80® pitch maneuver.
Roll - 63°.
Subtract 2 FPS forward velocity#
For final docking, assume 15 mlnimtm pulse cyolaa of
ECS control axes.
Eotate mated I'chlcle 180° (place +X axis forward).
Jottlsoa S-IVB using 3-IVB ECS.
During the rack experiments operational phase of the mission at 120
n.mi., the following manemrcrs are performed m a
basis:
a,
EttJ alignment cnce per day. (X axis unchanged, rotate +Z axis to
+30" above horizon, maintain fine mode stability 20 minutes).
�b. Uavleationcl clchtlnsa tvico poi» day, (X axis tnichoagccl, rotate
+2 axis to local vortical mil por.ntcd toward aarl-h. Maintain
fine node stability for 36 ninutco).
c. Anoaiae the str-i-t up and stoi>plni» of alx barbecue nsncnvoro x>^r
doy. Asauae c 90® yav or pitcli i-oallGav.rnt frcai nonral fll^
oUgnneat to the bai-bocuo at.<\\ile which orients the Y-Z plane
tei^ard the sun (+20®), EstnbUsh a roU rate of 1 to 2,5 revo
lutions per hcur obouc the }: axio. Aseur-.e driiil.iig mode oneo roll
rate is obtained. On stoppjns, i-etum vehicle to original attitude.
In preparing for the orbit chrnge, Uie *Z axis is fonrr.rd end appradLantcly parallel to the local horizcrrijal. Ihe -Z axis la down and
epproxteateiy parrllcl to local vertical. Obtain required ^ V
using SM idln CTiglne,
luring orbit
a.
b.
c.
transfer perform the following;
One
aligon-.c-at (Ssc 3a).
One navlGotlcnal sighting (See 3b).
One midcourse corrtjction: Assuaj correction of 10 fps.
Cli'cularlze orbit using main ffll engine. Adjust X axis about 10® In
pitch.
Brcrp RACX.
Rendezvous with Plight 212. Use Qi-HCS for following maneuvers:
a. Adjust velocity total of 60 ^>8.
,20 fps In fine incremants),
b.
Lateral translation of 3 miles»
c.
Vertical translation of 10 miles,
(tO fps in coarse Incr^nents,
d. Assume 30 mlnlsnna inpulsc Qrcles of each ccotrol axis.
On a daily basis, the following maneuvers are reipjircd.
(Same as item 3).
If the I^/AIii is undecked fcr experiment purposes:
a. Plight 211 will be tho target vehicle for subsequent dockings.
Assume fine mode stability in normal flight attitude for 20
minutes for each docking.
�n
b.
FHchfc 2U vlU ettttlon k.^op oa Flisht 212, i.e.,
a
poaiticn abowi 1/2 rile below aoS vlthin 1 to 3 itiles aft.
(Contiji«.o i*cciiilrer;c'-ts of Item 9 \^iilc 8ta{;ioBl::cplng), Poi»
caeb imdocldas, subtract 2 fps oca then eajust tc achieve
station position.
H.
At cccroleticn of fUcbt, rotate corablnad vehicle so +X axis Is forward
and slow CSM (Plljj-it 211) h fps rjid translate down 1/2 mile to «-chlovo
aeiorotlCBi from ths LH-I (Pll^^t 212).
12.
Dui'ins the 8 hours prior to rc-entiy, cool tho fonara heat sliKld by
rotating the -X axis tovrard tl«: sun.
13»
For C-I/SM oepiration, the +X axis is rotated (50-70® above tho dJ.rEotloa
fllj^t end in the trajectory plane. The +2 axis la oriented to upward
local vertical.
l^^.
Entry starts vd,th the -X axis In the trajectory plans and rotatr'd
epproxifxrtcly 26® carthvoitl frcm local horizontal cad with the +Z
axis polnv-r-d awuy from earth.
Bote; Winlmum RCS propellant at start of ro-rartiy will be
pounds.
Fllrht 212
1,
Assume velocity trlDralng ond manf-urerlns is performocl ty S-rs?B vntU
separation. This includes oricnrtatlcn for transposition end dorldng,
2,
K tho tS'I remains docked there will be no maaeuvarlnj requirements
(the.CSl of PUcht 211 will cOso provide maneuvcrinc for CKG unloading),
3»
If LSI pperatcs undcclied:
a.
b.
c.
d.
Assume one dally H-OJ aligcment (See 3a),
Assume one dally navlgatlcml sighting (See 3b),
There will be no barbecue requirement,
For rcdccldag the LS-I will be the active vehicle,
1) Assume lateral translatica of one mile, vertical of cna mile,
and longitudinal of three miles,
2) For final docklag, assume 15 minimum pulse ^cles of each
control axis.
�c.
coTcifSKus concE-2ii;G Tins op^iy.iL'ioi'jLt. aspects (f Mirsica 2.u/2i2
Thl-s mioslon provides oovoral opblffial miosica proflloa, A rccomicndcd
profile haa' been Given la paa-asraph. A. Bualc mission nnacnvcrs arc all
slnilrj to Apollo reaulrcccato end will cnitall no nriW trainitiG cr cqvijsne-at
revisions. IMs is on cltcimatc AAP missicn and the inlsoion as descirlbad,
will ce-pler.-c-nt the dcvolopmeat of tlie basic Apollo miDGlon. The possible
separation of the LS-I for csctendcd ptjrlod'j of c:^srlmont operations Is
undesirable and will bo discussed lai^sr in this report.
�o
GF^9!\SI0k5
CREi-f cc3sm:niv?TfiTia
C
�t
E^cpj'rjlracat Oporotloni
sade:
c
Prior "to Mloslcm 211/212 analysis, tba Tollovin^ naansiptioas vare
a.
A CSII/Rack (211) in a 320 n«mi. circular orbit for a total of
13
"b.
The l^Jth day sprint vlth the C3M trenoferrinG to a 200
ond rendezvouainfl and docldos vlth the carrier (232).
c.
Tho carrier (212) injected directly into a 200 n.mi. circular
orbit after the launching of 211,
d.
The carrier spends 13 dtya in a 200 a.al. orhit.
e.
The 28th chiy spent in CoM-caxTier separation and CM re-cntrj'
maneuvers.
f.
Six mcnlxours of <-:q)ci'iinental time avallahle on the first day of
the 211/212 mission,
orbit
g« EiGht hours/day/mau are available for (3q)ei*i3neat3 (24 manhoura per
day).
h.
The one astronaut in the CSM durij^ CSM-ccrrier eeparaticn, viU
not be c:^ctcd to perform €:;^er3Jiionts,
Tho preceding asaumptlons indicate thnt thcsre arc 294 coxhocra free
for experiment time during Flight 211 (low orbit) and 208 ircnhcura arailable
for carrier (based on 2 men) exqjcrlmjatatlon. This totals 502 nrnhcu's,
A thorough onolyaio of the candidate cxpcric:.nt3 reveals a icivuireacat
for 659 manhovcrs, including such expcriaeixt-rolatcd tasha as alicamciifej
spocecraf-v attitude holds, un3toirf.ag and setting up cq.uipmi3it, EVA prepara
tion, etc. It is obvlcvs that all these cxpcrim-ints cannot bo operated for
the desired time because of the deficit of available time (859 desired
cj^ierincnt time mirma 502 available eapcriment time = -357 manhours).
T>i^ 055 cjgjcrimfnt times can bo brolan doun as follous in Tablx: I.
V '
3^
�TcbXo
I
All 3 crcwaen
ncc(io<l
^Zwo erevmm
ncsded
One croua^n
needed
1^50 maniainutee - 13th day
616 maaairnrtca - daily
lot - 13th day
26 inamiiinc^ico - let, 7i;h
& 13th dey
c:onminutcs - dally,
15th - 27t;i day
600 Kfamlnutes - l^th &
l£tb day
232 manmimrtcs - 17th •
25th day
367* - dally, 1st - 13th
day
180' - and - 8th day
720 manminutcs - l6th day
900 maninlnutea - 27th day
170' - 3rd - 13th
903' - dally, 15th - 27th
d;^
10» - 17th - 25th cUy
120« - 15fch, 17th, 19th,
21st, aSrcl day
60' - 28th day
Inr-'jrnueh do -three
are avollahlc for & wpviTmiiT^ ctf 88O moainlaiites
oa eny givtrn dry ( of -fiiGht 211 ), there appears to he no nausucl prohli^a
in performing
"of the oMperlircaifcii retpiirlnc three men. The ;jc?.vy ragjxlremcnto for all three ei-cvnrca on the 13th, l6th and 27th d-iys of the mission
sharply cmtoil odditional c:qjer3.ma.itatlon on those drys- Ihc remainins
tlir^ allocation oa thc^so three doys for the rcmainlns c-Aiv nzoabera io as
follo-.ra, Txra msn available for a rmxlimrfl of 520 Daniuinutos.
Eurins carrier operation vhcre only tvo men are c/arllable for
c:q)srir.cnto, it Is estimated that there vlU be
rrrsainutes available
for two men and 200 nianteo available for one man. K can be seen that
the 139ft manmlaute, doll-/ (l5th - 271;h day) requircmcato for two moa,
cannot be net. Iloroover, the daily refi-iairciasnts of one
for 903' per
day (15th - 27th day) cannot be satisfied.
It should be pointed out that e:q3criiK-nt3 l-Wll, 14022 and KQfjis have
no In-flicht requircnonts. 14005 and MOO7 were combined for purposes of
ecir tine study. ^-012 uas ccmbincd, in part, with MOI7. I-K>19 is also
coribincd with iK)12. The FvA rcqulromcnts of S005 and SOOS were combined.
rVA rcqulrcaBoats for S016, SOI7, S018, SOI9, S020, S052, S053, S05f^, end
S056 were also combined.
A total (rf 16 E7A's, requiring 97«2 uanhours were prescaitly required.
Experiment SOI8 takes 5^
the manhcurs for EVA'a related to micrcmcteoroid
collections. All these EVA hours Includa tbs pre and pcst-Fv'A eetivities
OS well as the actual EVA tine; The longest period of ZJA outside the
spacecraft is three hours.
�(D
rExpcr^nto SOO5
SOO6 vill bo flown on mebfc ru end wlU
rcoulrs a I50 inlnufco EVA
on oatronrcafc apendlcc 30 r'inu;:c3 ouiside
tl^ c>rXt collcctlcs film ccnnlstois frcaa tbo raclc. liuc activity
It ntjccaoniY to ccrry ono F13^3 for the EVA irorloir end 01,0 PISS for the
Gtcndhy in tba cvoat It is nccosaaiy for him to rcscuo tho LVA wor:ser«
There is ccricus donbt if the C/l-l can ctow tvo Pl-SS's, It mDy be aecesofuy vo pi'ovldc tlie stcndty an 'mbllicea., hooked into the C/il ECS
lone cn^h to allow reccuc oporationo. Another desirable cpnrc-'a la
to do the basic EVA by means of en unfblllcoa, Foi* EVA emcursioas
tho
carrier, it is ooomred that two PTSS's vrlU bo ovailable and that the
carrier will have sufficient rcauprOy cranaoditlcs,
Tho f
EVA wherein all the iVE-I cJtperimsnt packecos ore to be
rcti'iovcd (27th inissloa day) should not bo undertaken until the CSi
has docked with the carrier, thus utllialns a full crew of throe aitroC&tluO«
The followin£5 ei^crimcnts inrpose the greatest time diaipoT^/^c m tha
Apollo crewEon:
C
M012
^M020
^005
esSOOo
-
50h
270
180
170
Honnlnv.tca
I'uuminutcs
Kcnminutcs
ilanicinutes
per
por
per
per
toy
cry
day
doy
-
drys
deya
dnys
dcys
2-13
2-13
2-8
2-12
)
)
j
)
Plight
•*3018 - 270 I-iGnainutes per dry - days 15-27 (EVA) )
**3019 - 538 Manmimttes per dry - days 15-27
)
•*3053 - 193 Mauminutco per day - drys 15-27
)
SSA • iyi
!f^
15-27
«S05t> . 5i5 I-ianntnutes per day - days 15-27
)
)
Fllg^rt 212
«
An additional factor which has a serious Impact on tho accctnpllohEsat
of euoporirairts is the night and daytime experiment pperating requircaGnte.
The e:^p^i-3;nt3 above, marked with
can be done in deyllf^ only; •those
marked '
con bo perfoimed only during the nl^rttime,
A glance at the estsbiishad misoion timeline shora 90 manmlnutGS
oU-CTtted of exercise time. Inasmuch as M012 requires e:'"ercising m the
ergcmater, these allocated 90 manminvtes could be u-cillscd for performance
of exportnant M012. Moreover, the set up time required for M012 is 60 '
menralnutes per day. If the ergometor can be left in an asscsiblcd poaition,
this would save en additional hour of tixoc.
1!
�c
Ccn-t'rcJ. Ccnc.Tvnlon3 anfl Rogccxicndatlcma
A typical" dry of lUsaioQ 211 ^ras timalined in texina of e:spei*lmontcl oporaticna and frm thlo tlmvline tho foUoulns conclofliona and
roc cfor,gndntiona ware evolved;
X,
Periods of Watch xost be uf-ilizcd to occonrnlich the c:;porijacat8.
Tho duration of »,'atch poric^ vhoroin tho crcCT.an can he e.wsy
froa bio watch otation nrst ba ercbcndcd fra-a 15 to 20 minutes.#
Otherwise, experiments reqtdrics I7 and 18 mimite continuous
ciperatlano will have to be re-evoluated.
2.
Astronauts miat give up po-tlans of ttelr sleep, nsps, nci-ocaial
lygiciic and lunch hours in order to schedule the ej^jerlments.
3. Dally o::poplmcnt participaclOTi by crowmon will bo as follows;
Pilot
ITavigator
Engineer
- 319 minutes
- 395 minvites
- 36I minutes
h.
Eu^arlmznts requiring 30 continuous minutes of saqjeriment craoj.T'.tlon
can be pcrforiKsd only during an astronaut's standly porlof.." Ihis
means teat c:y crpcrimant i-cqulrine 30 successive minutes can bo
pcrfor.r-^d only once per day per men \-nlcso it is all right to
repeat the some eciperircnt within a men's 3 hour ctendTy period,
Experimarcters should tiy to arr£mge c:<i!crlJn3nfco so that thmr can
be porfonsed in 35-20 minute inororarrts.
5.
Eccauso of the great demand on crowmen's tlma, it will be naccscniy
to set up appoi-atus for cxpcrimairt "X" end do pert of that expcri* mantj while this apparatus is still set up, it will be ncccsoexy
to se-t up apparatus for cuorerlzrent T" and then perform sera of
that csq^oriciim.t., A complete caa3ysis of space problans need to be
undcrtahca in connection with the csperimant timelines. (In other
words, available craw time alone docs not give ics a realletic
picture of \diat can be cpkimaUy nccccrolishcd within the C/li,)
The value of simulation cannot be over-stressed.
6.
Though the mlssion-sssigned experiments can be performod curing
Plight 211 within the allocated tirus, the C/H will be a busy end
crowdad laboratory. The aaditlon of e PCH to cany soas of the
exp^icontal apparcrtus would significantly r3.Ueve this ccngestlon
problem while saving a sizeable amount cxf time. The inclvalco of
a EC2i on Flight 211 vcu3^ allow the crgjcrimcntnl aK?sratuc to he
Initially set up and then left in an assembJad position. If
experimsrrt apparatus for Ho. llOOk, WQ^, K012, MOlB and 1220
could remain assembled, the nstrcmauts would face a more realistic
time schedule.
c
# 15 mimite watch period \33 rcccnnsnclod by I'Tcrtin CoBsajay m "Cre^Qperaticas Eequiremonta" dated 10 Aiypist 1965.
�7*
It l3 Intcrcotins to nots tiuit once tb© typical mission tl^rollne
of events \ms ccnplctcd for FUx^lvb 211, there uerc a Diais!rm of
3^ hours for tbn three crcsnren por dcy on aa iiidlvichtal bnais.
lOnly one icna free) Tliis cucsenta that O3>orim;ntcr3 should
look very closely at the car^Erincnto to detonnino vcys la which
e:-7/orlnents could bo cccdac-bcd by ctio person, rather than on a
pair (subJcct-ezptriiKater) basis.
^ «, Jf«allx-d etperlmc-nt cpei-aticns data for mssion 211/212 con be found
la Table I. The fcUoulns cocxeats ^ply to the Indlviaual espca-lmeate
^dilch present problems:
1.
KOOl^ - This e^erimeat req.i^lre3 17 mlnube time Inorcccnts. HeccaECiia 17 minut-e avcy«fr(x>vorlc ollot.'ancc diurlnc astronaut's >ntch
periods.
2.
M012 - Thouch the annVsts have requested this experiment to be
repeated three times a dry, it is reccmmonded tjrvt it bo done
only tvice a dsy. Tho oajj' moans of scheduling it three times a
Stbla ^0 ^1^
appuxatus scb up permnnontl;' - cn improbabllllgr
3.
M020 - Bequlrcacnts for this 30 miaxite caroerimenfc incividr- its
®:c^tica tvrlcc per day on all astrcaau-ts. It io recoscrnded that
it bo per*Oi-flcd only once per day. Otherwise, it inroosea serious
schcouling proolems.
4.
SOI8 - At tliis tine, this c:^parimsut reqj^ircs one 135' IVA per day
fw the orientation of nicrccetcorlte detector plates for a total
of twlve days. Reccmmand that:
' a.
Tho number of FJA's be halved, or
b.
Means of rcmctcly reorienting the plates be devised, cr
c.
Detector plates be positioned so that visual inspection con
be made from within the LEI, thus possibly cUninatlng the
need for 12 EVA's.
5*
SOI9 - Ccnpletely imreallstic rcquircnont for cons-taat sur/oillsnce
ly on astrcaisut during all dark-sldo orbits. Reccanncnd tbjtthls
tine demand bo reduced by 75^, Or develop an automatic device
capable of meeting <u^>erlnieDt objectives.
6.
SO55 - Requires two cstroaD.trts for a tottil of ^h6 minutes a d^.
Reeenmead ttot this rsojiirciaent bo halved.
1,
SO56 - Ells ei^^orlmcnt requires 320 hours of Plight 212 time,
Incliiding spacecraft orientation. On a 12 day flight, this means
ten hoars a dcy are to bo devoted to this one e:q>cilmsnt. Reccsmsead
that the exporlmaafc be seriously analyzed to determine if it is
worth this Each time. Reduce caqoerimeat time by at least 75^,
�.
/
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MISSION 211/212
O A 4*
B Q O
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I0 D U
SXPERIHEICT
ln»rilght HionocardlogrsD
Blo-Aeeaye Body Flulda
Calcium Balance Study
In-Flight Sleep Analysis
Human Otolith l^inction
Cytogenie Study
Bcercise Ergometer
nioraclc Blood Flow
Vector Cardiogram
Hetabolic Bate Keasurement
Pulmonary Function
Red Blood Cell Survival
Microbiological Assay
Antl-Q riastic Qarment
In-Flight Nephelometer
Space Suits + Lunar Exp. Hardware
Synoptic Terrain Photography
Synoptic Weather Photography
Trapped Particles Assyatetry
X-Eay Astronocgr
Hicrometeorite Collection
OV Stellar Astronocy
0"/ X-tey Solar Photography
Apollo Telescope Mount
White Light Coronagrapb
High Resnlutlon Photography of
Solar Ataoaphere
X-Ray Teleacope {21V215/216)
Ultraviolet Spectrometer
Intensity of Solar Flares
gpectroheliogrephy in the EDV
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��For o;-:p2rlnu-nt3
S005
Is ncodcd (In C/JI-Fllchfc 211);
MOO6, tho following !27A e<iuipacrrt
lunar SpiaCQ Suit Aaseabl^ (3)
C'A
(2)
LCA
(2)
era
(1*2)
•PISS ( 2 ) and spores
Al-dJ (i) and spares
Aim P^iol Sijpport
20' Tcthor (2)
EVA Visor (2)
)
Boaed on
)
iVDay Mission
"^If only ono PLSS can "be sto"/ad in the C/M, the standby crowaon
will need a twenty foot nmbillcal (hoohed into tho spacocraft
ECS) to perform roooue nisoions if necescesy. It may also bo
possible to substitute 75 foot itabilicolc for the PLSS'o.
For experlcants SOI6 and SOI8, all the following EVA equlpoent vcwld
bo transferred Into tho carrier (Fliglat 212):
TI-IA
(2)
LCA
(2)
*C\'!Q
(11*)
FLS3 ( 2 ) and spares
A^^J (1) and spai*cs
Al'U j\xGl Sunport
20' Tethers (2)
EVA Visors (2)
*31och U Pressure Suits (2)
•Portable Light
)•
)
)
)
)
)
)
)
)
)
Based ^
ll*-Day Missieu
*19 additional C^vG's will be needed to "bo carried into orbit by
the carrier. (2) Block II suits also to be carried by carrier.
It should be noted that a handJiold system must be developed for
crcwrnn stability at tho work locations. Morec/cr, if an AJS3 is not used,
a handhold ^stcm will have to be developed for crewman transfer.
�o
CRsw con3r:rPMV.eio:3
CARRIER Ri:CO:.::-u-ro\TICTiS
�Crev Ccnslflgratlcais - Mlsaica gl?./glS
Tho cdcctlon of Q carric:.' tajod aololy c© crow con$idcra'lilons lo
on cs^ircaaly dlfflcwll; •took. For c.-ftng>la, -fcha aMUly to iBa5.ntaln on
otation for a pariod of two vcate ii tha Gcelnl has bean dcaonotratcd In
a ain^jle flight by highly motivated astronavrts.
this particular ease,
tba accccmliohmant was a chaUcngo of e slncolar feat rathor than a
routine occurrence. Tho tread today is to incrccae the vorKLoad ccd tho
nisslca duration scvei*al fold in a spacecraft that is so/crly restricted
end limited for a I'f-doy mission. Wo mart accept the rojulto of tto
Gcsninl end tho initial threo nnn Apollo mlsslona as islnliim E;trada"da for
crcv/ habltabillty and ccaaforb and attcagJt to iarprove thcsa standards for
tho AAP missions.
Habitability
Environmental paramcrSors are not a consldsration for carrier tradeoff
studios in tbat the cabin atniospherci idH be maintained at 5 + .2 p^i
normal, 3^
cmnrgcney end prior to BVA egi^ss, 100^ orygonV relative
humidity from hO to
cabin toapc;rature 75 + 5*^ aad <5ebln dicoldc not
to excc^ 5 millimeters of morcuzy for nOTngil operation end 7*6 mn. Eg
maximum*
Crew Comfort
The LEi and AIEl rcpri>3cat3 a total iMressurizcd volnr:c of 8o0
with
a vorldng space of 122 ft-^ for two ni'ai* Weiste disposal end storage, food
and sleeping facilities are ninlmiaa end sized for o 2J<-~hcur mission with a
reserve tlmj of 2k hours. Eor-iaii crew operation requires suited astronauts
that may'or may not be prossurisod. Fccal collection with two cuit-id cramcn
in tho LE'i would be very difficult. The ECM on the other bond, vlth
356 ft3 of pressurized volume with sepasrate waste focilisies, offers more
privacy for waste collection. The cppoz'tunity to brcalc the routine ccn
be tc3;en advantage of by utllizins the movements and tasks esscclated
%7lth the food storage end preparation areas. In addition, the necessity
for the astronauts to move around within the U".! is vciy liralting* TIis
actual operation of the vehicle is acccngjlishcd from tho craw statlcais,
Tho RCM could be designed to parciit mora moVGmmit of tho crow which is
certalniy dcsixablG on missions of 2U hours or longer.
The ability to r-aaovc the pressure suit for shirtsleeve cperatlon
oiid for personal lyglene, is highly desirable for all Apollo Applications
flights. Equipment and space for shaving and cleansing chcuid bo provided
for dally use. The IE>I can be modified to provide this capcbillty for
a two-man crow. Pressxxre suit opieratlcao, including EVA, will require
suit storage, and ability for crew to inspect, clean, and diy each suit
53
�prior to storcoo end use. iluy siilt<:d opf^rafcion vill require both oxiw
moT-jbcra to be la prereviro otdta so
tho dressing ond denning of the
salt, rcaovol and drj'ins, will probnbiy ;-ciiuirQ the utlli-Eatioa of all
avallablo free prcssurited apace. I;o other taalts, ecporimcats, or pro
cedures nofually will ba ecconqjllohcid imivll the suits nr« stored.
Internal arrnngoiLcnto, Includirg proturberancos or £:harp edges, must
be ccOTr.tlblo with tl-jy ncveatsnts oact aotlcoa rcqplrcd for two astroaeirts
to adequately accomplish all cperatioas regplred with th.'> auits,
ModlfIcatlcma ore required for alsoJ.ons that require separation a£
the U::-! from the Ccrmend Modulo for periods in excess of Sh hou.i-s, A
seven day rcnnned Lul separated from the Ccancmd Module wz^.th a t\ro-ir2n
crow, requires fccal collection and ston^go# vxine collection and storage/
dump. It is rcccavrcnded that (sclnting food storcge end juaparatica bo
cnlnrced to include a preparation a:v^. Perocjial hygiene f^ilitics
should be modified to Include provisicms for body and dojital clcannlng
and shr.vlcg. Shirtsleeve should be normal operating modt;. Chnnge of
clothing cvoiy other day, or threo changos for the seven day mlooioa
are minimal roquircncnto.
The LEI has ao^ provision for sleeplTig other than napping on stations
during the normal 2h hcnu' mission, hhca awry from the OoTsend Module
during a basic Apollo mission, tbo nrsw is crrpcctcd to
falrlv
BCtlve for the 2ij. hcji.u' period. no-«T.vor, on a ssven dry nlGcion with
the existing ci-ew station restraints, napping on statlcn-c cannot be ex
pected to suffice for sleeping faci:'J,tle9. Provlslcas for uninterrupted
sleep for a miainrun of seven hours for each crew member la^at bs provided.
Similarly, this feature mast bn retained in its existing form In the
EC31, or suitable facilities provided.
The Conmnnd Module aoncally provides the
crow caaforfc reqoiremonts including a "gallsy" for food pi'sparation, and separated waste col
lection and storage facilities. It would appear ot this time that the IttM
cculd have at least the same capabilily as tho CM. In fact, depending upon
the •Ission, the available facilltlGs could be euqpondcd to provide additional
crew comfort.
Craw Safety
The separation of the experiment carrier. I.e., either the lEI and AIM
or the ECIl and ZiE-I from the Command Module, represents an extremely high
risk sitv.atlcsa In that the ability to abort from orbit is delayed until the
crcv is aboard the Ccmmssd Module.
�6)
Ths ability to ecrcso froa the Lr:i tlira;3h tho batchss In tho eiroat two
mm ore conaif.tia^ eiqiorliucats, la (UiTicult end tiying ^indnr noriLtJl coadltlocs. Es-jreoncy cgi-cos of two {Vitroniuto Siid trcnsfc:.' to"
to the
^ preferred to roadozToaoing end docldLng, providing
the Cli is ^-oondicg iry, Sio ECJI eoiUpped VTlth the airloc"':, cpprrers to
offer M crislcr egress than thrcn-ii the tmmol aystoB on the Ul-l, Tm
airlcc.: can ccccr--aodato only one astroaa-rt at a time; ho-^evcr, the opening
dimensions aro considerably Inrger end more accocioodatln'j to the evltod
ootroaaut. Escrgcacy egrcoe should bo quicker and less
to tho
astronaut.
ability to provide assistance to a dlstreasad astronaut
dm-ins
or crcv transfer appeni-a to bo easier and milcker fToa the
RC4 airlock in preference to tho LEi hatches.
Retrieval of tho disabled astrcnaut through the airlock probably can
bo ccc^Uoh^d with less difficulty and capenditure of energy than through
the hatch on tho IS.I derivatives.
"
Conclusions
n».ri I-S
.
conilr:^n.-Qtion for tho noraiaL 2h hour mloslon,
and tho abinty wO incorporate addicloc-al crov hnbitabillty, confoit, and
s^c.y rccalrod ^or a seven dry misolon, a revised LG-I cnn be dcsifncd to
^ccmplish the i^sslon. On the cthrr hand, the fcatur-es alrerdy available
w
Module, nodlficd end cxpsndcd in the ECM, ccabined vith the
3
an ^rlock, certainly pi-ovldes a safer, more hnbltabillty and
coaiforfceblo configuration for a two-man crew on a seven day mission.
«
Carrier Chice - Ist, ECU;
2nd, LEI
�c^cmrasj™ E^>?.fimy?ron3
CRBtf CCE3IPKRATI033
�V
4
Connliislono cind Reenwwi/;^^3^.^^ons
mont ccjnaidoStioaa^ Sa°cSrl2'coS^°^ spscccrcft operations, cxpcri~
Prccnt^ OS relate to
^
LE!/Aa:i configuration.'^
CS^VJ^CM/Aril or with the CSt-1/
cecoii^lisbed i,^tlUn the mlosiok
Pi^oscntly defined ccnaot be
times and rcpoatabiHt^ ^
opezatlng
the niosloa could preuce voluaWo
oxporlmcnts,
me^s,^^Quantlty of o::perlmental-dntf^f- ^.^^-1-
inrtopoildait
f
^riSSS™-
ssi? LT? —-s
ssSi~'/•~
\.
presents a vc^
siSiS^'^rthQ^ caiTlc-r for seven d^ys
event of nn emei^eS^ Invoi^rn^^^i^S^ abL^
^
^•psnmcnt comer roust soai-hw tiansSr
^ crewa=fl,.ln the
Cororond Modulo before ro-entuy Prcccd^Ss^aJ'SliSrS''''^
^
alccpiyat'S^^vS^^'
iJito tho LHM and are asaiKscd part of the ROI.
«incorporated
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O
s-?
��CRE'.v C:":V.T*Oi^S IJD l'-3b"IE^TS
'KE^lMJNAir
•1 A-VjTJiiT if-6
Approwed
(i. A» fiotUji,'
/
f^r9M Operas .ons, AAP
�CKD/ (iPBoATJO^;? R£.;"^^;7^S^-TS
YAHLE Oi CON" :nTS
Human Factor SoqulrciBcrta
Cperational Scqutreraeffis
Astronaut Training
Crow Equijauent Data
�a.
Miacion AS-2C'jA, fjC-012 Cpacf?raft Oijorauioa Ri es
b»
Aosusip fc '*.oin,3«
c.
Espcriaent Tallot Opp'-a^Aonal Conat.-.ilnt, fi5-3/?!AA;
d.
NASA Jftttort P0H/0]3VL~l3« datfd j5 L -Tairjajry .19£;6»
e.
NAA tntercal latter, 692-80't ^50-66-')17, dated 2 Fob;.'uai7 L^6,
t.
NAA internal Jitter, 692-3cA-050-66-020. dated
g.
Design Reference Kxetnotic LE7)~M0-l2., QAEC, dated 50 C.tober 196'».
h.
Apollo E.;i.a.ncioa Syeteaa - LC-5 Phass- D Fxae.1 Se,,or:-.. Vol. 3V,
dated S
1965«
i.
Apollo S-;t£-ns3on Systems - LSI Hiasfj B Final Remrt. Vol, TTI,
dated 8 Deccrrber 1965«
J.
Desj-gn CritorJa and Reference Data Jfcindbook for Uv>ar- Stpleration
Systeasf Vol- II, NASA, li'ir.tsvllle.
k,
Systea A'^alysis Sxtnmary, Part II, Na\ SID-65-15;1>-.2, dated
29 Dcoeaber 1955,
KOTS:
HAA«
!C101
Febi-Uery 1966.
bliore appropriate, the l«iutf'- de »igcatiwi of tb© souree reference
is placed by the psi'agraph nuBflsev",
�r
X.O
HUMAN FACTOR PS^UIR>^-?}TS
1.1
Scop**
Theco requ-trnraents applj to cqui.pfj»cit and warl: p.i.n^o which dlrcctlj
affect the flight cre< durtn^ Intr?veh1ruJ-ar Ar tivUJos (IVA) and
Extravehicular A:5tlvit5ea (BIX),
1-.2
Purpopo
The primary purpose is to eptabldoo spcclficacionc for the equlpsenv
ouppLiftr and AAP design and tticsios plaanlng g"o"o.t, Tu is an ohjoc
bivB to tnaintai-T. st.nndordizer-i.on with the cr.le .ir.g Apoiio svotem
hardware,
1-3 General Reqti^"roT.anta
1,3Ipplementatlon
iBplcaeu^at-ioA will be ucrorplichod through decdgn roviowcioterfac© docuocrtation, oni -confiyirtttion copvrol.
l,3-»2
f-
_Equ'prerit. Slandqrdtz^At'on
EquipRonl coaf'.guraticn ehojld be sini:ar to certstieg Apollo
flight eqalpmcnt BO thti ere.- will require minlinal special
trainingc
1«3®3
Equtp«>ent. Deslgrstioa
/
'
Bquipe-ent will be named for case of Idnitif-iration by the
.crow rather than no confom with sciectt.o.r custom or
academic precision.
1,3>^ Exceptiop-s to Specific Regvirrpcnta
Exception to specific requlcements will be made by reference
to the general requJrci'.ente,
la3»3 Supplenonte to Sreclflc Beg ji rcmentg
Vhen a des5gn requirement is not spccif.cdc typical Upoan
2hglneeriag practicfs will no followed, Tho following
docunentB are recogrlzed as authoritative in coating good
Euman Eogineering dfoigas
a, KtL-ifn>-13036 Zk April 1962» (rriL-STD identification
Marking of U.n,- FP.'.tn , P.roperly.
G
b. KT]>STD»^3A 1.
c, HII-SIi>-803A-2 (US/if)j 1 Dcrcenhcr .I96'i; Rirt 2.
d. HIL-£1».12B, 18 Kay 1959^ (AhbrcvJal ionc for use oi.
drawings and technical type j.yb Ucnfcion.n).
(£>•?-
�NPC-^CO~lj 18
RTid ^{SC S-ofp" wont i^l, :?ev . B,
26 April 196i», (Ap')Llo Con^Jsun-Jlo" iiir-imi).
MC-999-00'J7. 15 Septcraijer 1952. KAA, (Grrcr.il CpcclfiCQUoHtiaan ahcincering Seelgo nrltexlo fo;* Sfooecraft Syst©a3),.
�'•
•
•*
Ami PtfYSlU/iL PJKTGii HPXfJ^ !.-^?4r:r."".'^
- ''•1 P^ro-il Cr-.'-ti-.a
3jyi» Crr^ir'a
Cj)
Tfie 6£bo cf -be cr^wrar ahalJ. be wdfhii: the tpj'jjc froi
5» to
pc?)i-.'aMon ac ^iven bei.ov.-
y^GTRONAin' STZE Clfr'fI::n'A
Mcnonreracnte*
IIS.TGUT Fn02l FLCOR
Stn,ure
LVo Holghtj Standing
t.cr.-it-ale
Crcrch
Foot Length
Foot Braodth
bpper Anu Langth
Forparo-IIand Icagrh
Hand Lnngih
Cheat Braadth
Wa.'-St Bri adth
Hip Breadth
Wrlot Brcodt-h
Forc-nro to Grip Lcngih
FuQciional Reach
Eibow VJrioc teagth
B"ihev;-Raot Height
66,30—70.9'3
62,1/V.6?.O5
56,'? —6'4.„25
30.31--33.79
lO.C:-11.25
5,70- i?..52
11.85—15-59
17.i?—20.39
7.2:— 7..83
n.3-'—12 80
10.53--12.'?8
12.7':--:'A.33
2,2?-. 2.'I8
13.1 >-1'? .56
29a:-.5J^,.hi?
10.8 j—11,96
7.51—iiooa
69.25
59.19
32,92
10.-56
h.07
•5.57
.'8.'t9
7-'?7
12-33
12.36
13.88
2 <35
-?3-67
31 ;i2
8,99
DEFras
Ccc-ot Depth
Waiet Depth
Bj-^cok Depth
8.3?—•
7.M«— 9,92
8,«»2-^aD,55
8,95
9-2?
SEATTD nEASBREHENTS
^
Sitting Height
£?© Height^ Sitting
Head Height
Kr'ee Height
E2bow«EUbow
K'^ce-K&co
Shoulder Breadth
Rip Breadth
Buttock-Knee Length
35,00—37,67
29,21—33.5'»
83—5.6?
20,r .—22-83
16,97-~20;20
13,31^-15^51
17 51 ••-I9.IK)
15^30
22.03—25.63
?6.il
Jl. 36
5,29
21,8.5
13,90
lV,8S
18-91
;iij-58
23.9-9
�'"A •• ' c?r"r • i-)
Kccijiureae'i le*
HEAP
lOEgth
Bro-vcii-.h
Cli^unforcnce
8.35
5.71— 6.1'f
aa.Ofi—25.70
7.^3
r>.26
22.7A
55.3f»—'!l-53
28,8f.—3i?.''0
36.2(>'~38..'f6
21,0^^—2^
15..2>-18.07
13-.9'' -.16.77
.Qif
l2.0'/.-.i5„27
30.7f^-ll.8l
6,5"-.- 7.52
9.13
12.00-13.5<»
-I'f,5'.'--16„06
J3.5^
5U93
CIKGUMFiSEHCE
Choal:
Wnis"
H^.p
Opppr Th '.gh
ij>wor Thjgh
Calf
Arvkic
Bictpa (Flexed)
Foitaro
Wl-l3t
KatJd
WaisI; Front
Haf.et Back
=,0
vilie
1'>,1j6
.).o8
15,10
IL,39
7,03
8.7/
y,i.S3
isj<5
LlfIiV3
%
Vertex to Seat
*A1X ficasureacnta
>.8a-59,oi
37„7i»
ia Inches
Dloplr»y and Coatrol IcnM'.lon
(J)
Control pot^ets and £i.iop".ays shall be so located An
respect to tho cre*<?can''o restrained oponttiag oto'-Jon
that they are wltWn the noriial reach dint-ance of a 5tt
to 95'^ percentile Pnn, This fucctioral ans rca'-b dietaacp \a defined 5p tho foliowlcs tahle,
PfiOoX Xnyorte should be constrained betveea tiere Units
but noiT'.illy clo.^er to •:iat defined by the 5a percrntile
cret7r:.->:^. All controls will bo adapteblo to efricicoi.
opora^'ofl Jjj eifjor c)i»r»s of preecr.tro of esilt, PraleiKlnary Ita-tJi-- Cfper^aertol tiata indicntos n tKsxinuro forvard
rea-?fc of a 5>2 pereentiJo cian in a epnce cruit Is lens than
17,0 inrhfis.
(of
�nsiGHT A30VE
SF^T IW
-_jNCHEs_
mmi
0
15
30
'if.
et)
V5
90
105
u>c
17.^!
23.9
2?..6
29-3
23.9
2S.3
25-1
20.3
IC.5
23.5
23.0
30.0
30.0
29.3
2S.9
21, :t
19^2
25.8
28,S
30.8
3U1
30,0
2G,9
22.2
19.2
25.3
29,1
30.7
31.2
29„i
25.7
ZO.k
21.0
26.5
29.5
31a
31.5
30.5
29.0
24,5
16,8
21.0
27.0
ro .0
32.0
32,5
31.5
29.0
25.>5
18,0
22 „0
28,0
53-0
" • T
22.0
27,5
50.5
2if.5
29.6
>a,i
Zk,S
Sib I-'arrr>zt.! !•» (Tr,)
«6
0
6
12
18
24
30
56
42
48
•
.
17,0
19-4
21.3
21,6
20a
17.4
12,7
*
21.5
22.9
23.4
22,0
18,7
13.2
25-5
25.4
24.9
25,7
20.2
13»6
16-0
22.4
24. 9
26.0
26,4
26 >4
22.4
36.0
17.9
25»3
27,0
28a
28.0
27,4
23c9
19a
SOjbPorcflnfclle fin.)
.
%
23,5
25.8
26,0
25.2
25o0
.19,0
iao3
3.7.5
23.0
26,0
27.0
27,5
26,9
24.5
19.5
13.5
•19,0
24.5
27,5
29..0
29,5
28.4
25.5
22,0
15,0
20.0
26-0
28,5
30.1
30.5
29-5
27,0
23>0
16,0
33,0
32.2
30-.0
26.5
19o5
•
r
19,5
22.5
24,0
24.5
25,6
21,0
17.0
11,0
0
^6
0
6
12
18
24
50
56
42
48
32.4
30=0
26.0
19,0
PnrccntlTe (In.)
S
0
6
12
18
24
30
>5
^•2
48
22.7
25.1
26.6
26.3
25.9
24.5
20.8
.35,4
21.6
27.2
28.7
28,7
28-1
25.7
25.5
3i;..3
?.l„2
Z2A
25.5
28,7
29..8
.30.1
29.4
28.1
24,6
18.3
27-3
29.7
31.2
31..L
50,6
28.1
24,5
..8.2
2? 5
2B,6
3\a
32 5
53.0
31-9
29.5
26,5
20.>
34.0.
33.3
31a
27,5
"
30,3
33,.2
5'»<6
35.0
3U,-'i
32.0
29-0
21-9
25.5
30.5
33,5.
35.0
5s,:i
54.6
52.7
29,7
24.^<f.
35.1
25.2
>0.5
33,5
5sa
y,,e
>5,2
55.1
>0,0
�PrcL'r-.ry
i j 1 tv
Th- eq.j*i)0.;nt «. f I !)» il'- j)gnycJ
pr^•8a•i^^ ctfit
The fflt-Ml-i.iy
e-^V.ecvjvliof
jjiy ea-'Apollo
do-a not pi-OJid;? fM'fldof
The raflge of raovonnnt
ar.d fr gure 2-1.,
v.-^ i-ju.a'v. *i;,;, ,b-
pr«s«ntnd
of
-i : Fiiiinri- H-l.
nir,r.k.'l',
pjoTomeji
in «nic!<iar'.scd
a6i.)
In all asco.
In Table
RRiDTREMENTS ^'OR THE mrE^™Y flODT
>.OVmE?iTo IfiTRAVERICUIjlK AW) £.XTRA\ vfllCULAR VDH. AT 3,7 PSIQ
A«
NSIK M0311.TTY
Flex-:on
'forward-! ackwsrd )
'
<^0
Flexlca (loft-r.Vgh-)
^
Rotation (AbdU'-tion)
B,
SHOHLDER 1KBT1.TTT
Adduntlen
^3
Adbuctlon
225
Lateral - Medial
jjO
FlpjdorEKlencion
Dcwn-up
lateral Rotation
55
Medial Ro'-ation
C,
1
ELBOW KC«rLTTT
Fjexion - Ettenoion
D.
J55
FOREARM K0BTLTT7
Supination
(pairs up)
150
Prooation (pains down)
E.
75
WRIST KOBILiry
Flexion (Adduction)
Sxtoaaion
Flexion
(Ai)d'ict:ion)
(Barkward)
Extenoio.n (Forward)
55
• .
35
50
(x>1
�scvf mohilit:
OF J50VEMEHTS
( fN Dro«EES)
HOV&iEJ'TrS
'J?RUKK •• TORSO KOSfiLTTV
Trunk
Torso
Torso
Torso
a»
Rota^'Jon CAdbuci: lon^Ad^luction '
Flexion (Ini-.oral " Modlai)
Flexion (For^'iard'^
Flexion (Bs'^kward)
HIP MCETITTY
Adbuftlon ;leg s^' cai.^l)
Addnction (knea beat)
AbducMon (knos beat)
Rotation ^SitUjig)
lateral
Rotation (Sitting)
Hadial
F.loxioti
Extonoion
H,
'O
30
35
30
30
V3
35
KHEE kOBTLITY
Flexion (striadlng)
Rotov/'on (oedial)
Ro^,?.-..lra (lateral)
Flexion (kneeling)
J.
.
70
50
80
25
120
55
35
160
AFKL'-; riOSTLTTY
Etctenelon
F'jexioD
Abduction
Adduction
kO
50
y)
�•
SPACE SUIT ASSEMBLY MOBJUTV
PRESSUSlzeO. TO , ^ FOlO '
�Any f.rca rrjqulrius any iBinlrul.-.ttion ?rd/or
r<>adou^.
of an InatruTcnt by a crew racbor vrl l.,i bo provided with
poi«l' vrt n-aos of crew restraint that will cctirol both
trojie-(atlonal nnd r;>ratl9nal Biovrmenrla^o2.2
R* t,rr :tr.in<^ Drvji-oo
Rt.r.tminloj; devleeo will be provided at 2WA work areao aod
Jn Qro.vo ro.-juJring -.-row troasDntioBal no/enwii. Acceptab\
dcvie cf 1nr bide•
""
developed EVCT haoclholdbe added)..
(Ujegraa to
b.
Velcro Pads - Conditions to be oidcd.
c«
P/indHolda •• Gritert i to be added.
d.
P;l.j,3n " Pr<»l 1 CI 1 naiy ••?artin data indl-rato that rigid
ral)T ut.lH;'.»d for longitudinal tracslatlooal
should have .i re^rtaiigulvr crossosection 7/8"
wide X l-l/'J * deep and be olovated 3" above
tao .•Jd^accut yvrfare.
e.
Tc-'hors •• Conditioa.i to be added.
S
1«4«3
AeseroibiV ty
fi-ncl
Openings - (P-reU'iinary Ke.r'.in Data)
Ihe else of any op'jnlPg reiuli-lng the mut'»d sntronaut to
rrnoh in wi.th oo^ bnnd ipint be nt le-^rt >>'/-•' «;
v<t>'
ivi handa« at Iflinl BY/^ high x 25" v>Mo, art! if visual
viewing is neces isry, t'li opooing w.sv b t 8" wide x 11" big'
for one am and 23" wldo x tl" high for -mo atns. SJoce the
suited aoti-onsut h.-s li ;;le feel rapsbil'.ty, vis»iBl capobll.ti;,
will gansraHy be required at any accoGO panel- All edgoa f h
projoctlona near the op-riing must be rc-'-ided eo ao not to
puncture the ^a'te cuit l.-4»3»2
Typo of Dcorn or Ponela
A door OP ]«asel optnirg outwnrd should hive a a. ilhcd for
8eeur.ing ir the open po'iltlon. Lnvmrd opecing coors oust
not trap the 3m 03 sfvii ....ocft during rr-at-ival.. Freo v.ypo
panels rauet be provided rfith
a positive 'Jraao of s^-owase
adjacent to the area and located so ec not to intefere wlVii
srboequent work activity.
lclf.3,3
E/A Pntch Sizes
(To be added)*
�Is'j.-'to1 G .•';•• t", 1 1
w
linttc which nun! hf tfio% «t1 rJjcll he 'rrovlded wUh lift poAnxe
In T.ine v/itli thf crntci of rarr,, Tiie wricht of the ujj.lt "
chslL be ffarkfd
on the •'Jiit and tho ccntor of nana shall tr
Ador,;.-;fied if it it. noi coinddent uith tho goffietrlcel
cpn-T. lioto ,-ba7.l bf hnajoned to poinit Ttr,joval and r-- •
ri:->i; wi'lh one hoi''d ur-df i- .TJmJ.tod vl;jibiUty coodiUons. i
aboli aJJdo into pooifci C'U and be concfcrwotod no that nliyr. •
mem is icpoasib le, Ur ;to chall slide ovt of position to • •
Um tc and rhall be ret rved froffl til'.* sujijoriiafj panel or
b.y .1 ranof- in tho dirt ftioa of reanval at the ritop. Dnl.
fhil., be prca'ided vdth ritanda or rR.-.ls J'or moc »/hrai out opond or aclc. The uui i will have no piojoctioBOc coble/; r
other tr.onrfcprap-ces whj th Ts--3\ b© v.'afivcd whl.l& the unit x-j.
belli
Thr. syeten "ufil; Tot present j:!jorp <«!ss.o or protrud.?
boyord lh<? surface of t ho panel or rack whoa tho unit is ro'.
in xhe operating positi c r .
l.kA^2
U n i f G<iyv>r6
ly •?"""*?" "•
«> 'owe ':hcy «. b,
or
r^oveo Kithout iootrurUon or tool.-, out oSall be p-ovlded
With a method of Btor&yt .
C
f'iont! f 'rrj*ipt>
To p-evont confkcten, f c-nponenta to be removed rhould be
rd.or rcdod or othrruder oLiirly IdatiHfied d.tff>reatly
f en the c«!|icnent:? usee as repliice;.:cnft"..
Sau pmpnt S:-ae /-nd W e ' y h t
Hsximum s.\se for novoable cqu'i'saent is »fci.! t--.jr.i
Bf.sjn
O r b i t a l TVA
Oibiiral EVA
Lutar TVA
I?jnar SVA
Voif^ht
(TO BE ADDS3)
Fasteners
Grnc--ai
Mount .ing faateTfTft ahal ? rrquirr r.o too)o and shall be op^^n-V tb either batid. When a fastener io net see^ircd, th-io Bacu.l.d be obviars on JrspcTEion^ Fasteners to be latchcJ •ualatobod ditrior S!k sb<'.fld not require an opcn.-i.ooo rpac-- v
xorcce De/fl ^yr.cv faolv ccs art uufatiefar.rory siace ihey cquirc rluward and rotaiJcnol Tir®'S/-TTtj srrh'''oh cioo'; b<> r^nct,.? i
ccthcrao
'
O
l-^o5®2
Fr.e-c.nor Pfrriorj
T- 1
�O
1-5
TI.U'filtlATTO'.The estcnwl r-blonr Ught co^di. Ic-ns f >r the AAP ttlaaicA
«vll vorr frota
apnroxi«atoly rcro ro 12.2^0 foot t.vndi ,5, Secauao of the colllmted'notrrof thd Tishtv excfine contxa^n between Urec.f.ty ngl-.tort -traae end iboea 1ciLauov 07<]Rt be exfjcotcdo
1.5 =1
- Cn^lndlns aroaa .jc^aaslble oy EfA la
u>
whuh data recovery. «qulp,w;H c'lmgea, adjiiccrawCc, etc.. are
com cnplatod)
a.
AabionJ lllumtna>.ion 'ox-els .i al.l arsao requlrins ary visual
re.oronce by the aatronaut sHtll be adjucmb?./! wlthta the ran:r<
of 25 to 50 focn -.tQad Leo,
b.
'.•.'here cabin windous are prov ..ted the jnrontRl bt-ightaess ratio
eball be nontrollnble to ra* vos ?paB than lOrl.
c.
Light sources shall be of a 'li.ffuso type.
d.
All inrifcotora and panel are,..e ehnll have nn form nmbieat
1j gbt coveragu.
©..
L'ghc Gonrces ehaU bs e^ran,;-.d so thoc che vieidjig acglo
of the vicaial worlc ar^ja is n-.t equal to the onglo of indidence
f.roa the oouroft»
C
la5"2
<j)
•>
Work StcT-lcn tHuaufTvitlon
Tho general requirements for the mumlnation of wrk stations ai-e;
a.
'
le5»3
(j)
O
No light aoureoB visible to 'he operator ( i v noraal worlting
pooltioas)o
b.
Anti.-gl^re coatod iae'^nnjent <-over8..
c.
Bulb rcplacoiBoni. froo the fr-jit of diisp1.!iy ptjielf no apocJai
tools r.5quired»
dn
Sharply defined irmatllnolD :ed narkings ret'U-ible vhen vlevcd
at any angle up to 60^? froo noraal of the display panel,
Brirhtncse L9re.ls ard Ad1 <str!enf.<i
Bo
For map and obnrt reading: n diffuse scitrce. oontinnouoly
adjustable to produce a hrig'-.tness level of 15 to 50 foot
latrborlSo
bo
For inetrunent. jiantls;
foofc'-levber^.B, whether
Co
Controls: allowance of nd.Ji>*_-;-caat "for saparene ponel light eoM.T-a
to achieve apparent squa.i b.r-.ghtnesc.
do
£VA work areas:
brig . .peso level adji-jtable froi*. 0 to 200
.J.rated from external or iotcmal oo?irce/:
(To bo added)
7^
�!• I'lk'h(r.ep»
?.ii
vcH
f frrr
tc< within:
a.,
5sl
b/'lVA.'n ti,-
h.
7^1 belwcf" the
'• '
• >«< ,n.'«
r, io» Jhould h, control
j ;..ri3o«lat(^ :r..r>-»vr,.-;^hss.
.i/id i - jfliti'sr ini-tr-Jiiola..
c. 20;1 befw?ei5 Ihe '.it-jk jrct stj.. reraotei our:';jceit,
do '»0:1 befwseu a
o-ui-® .i, :! the oui'Viife adjaceat "io Ifc.
�c
1-.6
(J)
C07.0R CODTKCJ
'• .-houlj bo c.oiiip{it5*>;i.c ^llh U^/AdoIIo
The appUcuble Tablon i-l acd 2-2 docuj.iin:-.ed in LlN "
5'iO-OOU of Z/WA, .»s changed c.t 6/3/64. are ohown
in the foUowing tables:
Ml..cd/,rds.
COLOR CODCNO (C0> PONIJWl'S)
Ttf|TC
Tau
30227
Internal Kovoblo Stnicturr
(balch.s, access panela)
Ito Brown
5o:-.'to
Brown
20099
•live Gray
35189
31'Je Gray
351S9
Gray
35189
Restraint Straps
Restraint Structure
Kcstraint Upholstry
PLSS (Pa^lqvock)
Harness Straps PLSS
o
Fed. Std
Wal3a. Coiling^ Internal Stnict'ire
Floor. Steps, Wori S'^rlac*
c
Color
«bi te
37875
*bi te
37875
Cabling, Dixts, Internal
oajse as Background
Controlss Emergency
OpEi!g*~yellov»
<• Black Striped
25553
27058
Docking Ring I^nnel
naite
27673
Glare Shield
'J iack
37058
Hand Grips
Tellow
25793
Hand end Foot LoTcrs, Knobs»
Control H-^jidlea- Son Illiua.
Push But fcono
Lt- Gray
Handles* Assist latch
Jatin Chrome
HCPR
Hardware* Instrunent Penel
-ray
36a31
Inotru'ioct, Indicator Hezole
Old Casct;
Gray
56231
Instrument and Indicator Faces
btitft or Black
37375-57058
�1.-6
"c-'Jrri.'irED
Color
Panola
y^l- S?d, 50^
'J .-ay
^231
tottering;
Wsite
37375
Sw.-.tch, Icvera, Toggle
Hatln Chroao
Koae
TeloB'opc and IMU
It-- Grcea
Z'iklO
COLOS COHiXSNlIfTS (SYSTE3I?)
xtrm
Color
Crow PJCTleions
-t,.. Bll'rt
Fed- Sl.d,
CosiRu n ir a t i ona
1J;«. Gray
26132
EPS (Elocti*lcnl Pousr Syaton)
Orange
ZZZk6
N & 0 (Navigation 8t Guldarce)
Lc„ Gracn
Operat to.'ial TflGtniiDontatio'i
iJlne Green
25195
S & C (£ ch?.lization & Control)
'ellow
23793
Ecpert::c".t Hardware
-?<'
�CptiBua panel ev.rfaco srenn r.houid be
unj displays.,
ur.-H\
for prloiity 3vbtj*s!.ea contrelj
With that enctpt^on, roD-.-N)lR ehculd bo
1)
£aoo of Operation
2)
Gequenee of Opera'ior.
3)
Fr'rqueacy of Operntion
k)
CoatroVOlsplay Rclatirn^'jin.-^
3)
Minimal Hnnd/lJiro Excuri'io-:
AecaLed for:
Autonotie flyatoms
with functlooa critical to crev safety shall have audibl
and vicaal warning sigcals ajid n-mwil o 'lrridea..
Controls shall bo decigued to prevent;
1)
Ircdverfcont Opera'-lon
2)
CrewTnaa Tojuz^
3)
Dofrage to Syaieci
All controls other than r.u..nd<rd
Apollo
tcu.ipmen«
strata freedom from control --eve-ssl er<-sre and
nl'all be tested to d&TO
alia I t neot the system
precisioa requlr.-mer.ts with no more tha i one overahcot error and rwo unde^
shoot errorsg
l'7-l
Gor'-rnl IbOcr. "or Controls
(k)
The direciio" of norextat of the -control will ho corsJstert with tb
aovemcnt of rho conirjlied objec: or moving rortion of di^play^
Controls Bust be easily idc-ntifi.Viie by both^visinl scC 'actile ten
Because vleual cues are pr^inary^ iowovort the control arr.rklngc are*
ni?ot important coding method for ooaf:;^ol id^rtifioahioa..
%
All
eoDi.rGi.s will iiave two types of Inforoation Xaeatod px-oxinate r
the control —• idsntiflcaf-loa of the control funrl ion and raethod
control operat'on, vh-re r-«quirpl>
Crebioed hmd
two controls on concentric shaft i for g'-ocs >.nd flco 'nlj'.i
be naod only when cjiace limMati )>s prohibit
controls and accidental oovcmant
hazardous cor/i.iUon.
of
coTf-^iV,
s'^
the use of ludlvidoal
>r the controls will xot create a
When manual ixrfoxmanco rcqalrem:3ts are ouch t'm.t the rcni!;rollod
object can be adjusted in a lioi ted number of dis-rrete stops, dncea
controls will be uood..
When hlg'i-precirjlon iikTiu'pl ectflngc arc- rc
quired over a wide 'range, assitirc-tationel cor.fc'-ols should he ueade
All controls will be distributed so that no ^n©
burdened.
ll»Bb will be over
All controls will be ieBigned, ori.cntcd. and located so
that they ore in acoottlsE:? .-iti. lonrol vrork habit patLoruo,
cusiomaiy reactions
and hvnuo reflexes.
It is des-.rable to recog
nise the goneralised oovrcss of human error in t-he orer-vtioo of
controls in order thi
rh*
.-say prKciurlo then..
for human error exlats in the foJ.lowiag ercamplrs:
The potential
�a
Sim.l larity of control csvlcfiii, cauclng tl.R wi^ong coatrol to bt
octiintrd borauflf. of ro\ftiMiijj; Lt vritli oi>t,}.hor,
b.
locatio*^ of controls t„o eaoc.ly rojsthcr 'r.nsln? ».nad»arteat
operation of adjno^ot '-ontro:.. and iatoxf'x'ii.p; with eaco of
. operation^
c.
Improper aequonrj.i.ij, :n«o ofj.Jiatment, one orerly complicated
adjuatmenta mutiny a',oUtkes .a coatro.1 cperotlon-
d. l«ng oBd involved prorodupes dlffieuit tc oomnit ko oonoiy,
Xa7t2
o.
Operation of cont^^3la in a d;v'cctlon conlp.ix^ to normal novcme
of the operator (}wrt.\cu\apl> tnibject to human error during tJof otresR or enerr;.3icy),
f.
location of coatrolfl .u mich positions that t]ie oporator can
bruch or kcock againol theu, i;au3ing inrirJvcrleat opemtionp
g«
Arrangf r.ient of I ho ln:;t >'ii'3oa* panel 1n is'ch s. v/ay that It is
.Impoosible or very dirficult c reach for one control vihilo
operating another^
Gcnc'a'l S-sfsini.';!'^ rri- .»p^r»
<k)
Bcoanoo of the confjnc^l q- n.-^ ern .tad tho djf Crl v.-l, v of controlled
Bovcmenr by the astronauts, in 2eix> g>'aviJ;y -•a-.'lrcjw»ni., safeguards
iTiot be adhered to in tho d^nign -tf control? ixnd In/out of tho
console bo prc-lude toadvcr net. (..ctuaiion .of coniroiso Recooaee
Will be used for toggle ewitchos ^f it aprraro thau the rontrol
olght bo acTn^aiod ir-advertcntly, Guarde-l'p«oljhnt';oas. toggle ewitrh ...
^or levcT-lock-t.ypa tv,Uoh.-3 are •.•.^:^ulred for'iVncticns that are
^irreversible.. They wl 11 nnv.; re' ->n3 installation depending the po
tion, or> tho .main disp^uiy coraoXe ,)rovlously etlpulakedl,..7-3
(k)
Toggle r.s-Jtr.hf^a
Toggle or lever^typr j.-it hc.u ma.- be two^ or «-hr{-«-peollicn, tab
handle,, or lei[er-lork "-.anile an 1 isotrentary cr Da;.rt3inirg in thai,
switching action- Total ..hrow d .itaneoc of iogglo .aad J.;ve--lo'ri£
switchc.9 should be
f 8 dcgree.'i. The force r.'cit'red to change
poGitien should be ^jO-IOO ouiiccg
Ad axial pill of 'fO • 30 oJUJces
is rccoamended to release the lev.jr-lork switch f.-om a iorked pos-ltior:.
Tho m.iaicaiin allov/eb.le spscing be^'^een log'jle switches grouped in
hori.noDtai rows sliouid be oc« in i on centers- Vlien xi.vtd in locaticaa
whore the baodle could po-'e n -ta /icd to «:r«v r'crb ^rs or be subje-icfd
to inadvertent actuavicn, tho sw..t;ch should be sc-aireccssod and pro
vided i.lth barrier guacdl -u rbo 'i in Figur? l-J..
distanctbocyocn barrier guards .?h-'uid ro- be Rorc than or,.. Jjvch. t>ierg:-a:-y
s'/itchea or switches whose iiuidv<srteDt actuation would create a
hazardoua condition rn.ist iiave a '.evor-lcrk handle or be pro»;ectcd by
a guardc
nl
�RECESSED liVERLOCK TOGGLE
Figure 1-5 Toggle SwitchcB
- 112
STD 65-1534-2
�-ogg-/^-sw.Mch 0]ie.-atioii is varS-icol iv
foBltloa jalrB sS=oa<i b. ,„ ac=<
7^
*
-DOrfh _ .
rgi»ARY
BACKUP
gj,
Oif
eit?':.
Ctoi;;
tl.b xc L'bv,ins brtbari ,
TMOK'•A^^s
DJSAcm'm
_ D.-.i'ipy
dwoi.auinr
Brc£s;»3B
/ijjo
JiT'LvrC
Where a thlni position Jr added for OPi;, v;-e-oiild h« in «•»,«
center position orrept. .tore thjr «ouW
perforonnco.. In „h:r,. mrr OFF .tonM be In the litSr!'^Sunn.
l.-7oA
(k)
Rotary Switrhc/
notary swi^ohoe (with not oore \hon
-
12
floior-rohi.
^ * •. •
\
^oJeM'" ''"If "•
"«»« l-*~ *li roia^^LThen
I - ..ctpblc pocLtlonc Pbou.Xd be detnited. Eioh swJ tch ohould
oy a detent cao, to hc»d the .rliva.ins nhaft ia ZToAZ
nd.vldual ^Jtch positicne., A itop will be i>rovXC.TTl "he
^cnee of the actuatir,5 rkaft's cotation exooot. in oases reouirinr
Joa-degree rotation,
,
.
-""juA-riniT .
^csTj switch throw distc-ir.:a bttwaca poait.loaR chould be 30 dee'with a torquo required to change positions of .12 - 100 inch-ouacee
of ^sitiona will be sjch that rleclcwJao ooveoent ie
on , ascecdijig order", "incroaasd perforuiance", etc.
I«7n5
(k)
Rheostots
l^ea the th^gtat 3.^ ncw.d rro^r. U« knob side, the maxi'M resir;.
tnnce should be in the OFP diroc Uoo ^c^t-h d4--r<-a«Jr,. jvr.tw.n-- ™ dire.-t!.oa„ The ront-ol should .royatr, throui:a so a:^„.
of 300 oegrers plus or mj.nun 5 d j^raes, A B:«p..n-}tion OFF positio .
.B recommended to opaf the rhoos:ar. rircuit and should occur j stas the contact passes beyond the i<a5;in!nm ropj.Btanse polntb
Depending on the ^st;allation rejuired. al;. -heoststa should
to the rotary Knob nesign as shc#o in Fxgure V4.
1j7o6 ^nmhwheels .• PotentioKaterH
(k.)
contact nm should rotate throy.-h an arof 300 degrees plus or ai.-us ID degro^rs.
Tf the poteatiora^ter is to be mo-Mtsd riush on th-s control ranel
bf the tl„,nb»bb,l bh,uld
�RANGSS
A
8
C
0
E
F
G
H
MINIMUM -MAXIMUM
2. i2r.
I.W
a687 - a 812
asoo -0.678
0.31? - a 437
a 43? - 0.56?
ao»3 - a 156
a093 - a 156
1.08 - 1.20
ROTARY KNOBS AND RHEOSTATS
ri^ur-i 1-5
Thumbwheel and Rotar/-Knob Switches
- 113 Sir
�c
Tho r'.arTclfjrd r trhb" ..i-:n
0. '/;0
jrch-?« nad
•'onill iijiiaatud,
< •';
J>r i
75 owucfte thnsusToul tl.? dw>r«sejoi5 v-n-.^pf.
i'AS/iMv. toTi Si'-u-hry Sjy hM (i(.-jr:Kji
rti
or iiorl/.onhelly oa
ons-inc'j ccr,tcT.-„
^^c.-js i>-e to bs n'ourvcd fJus^h wj in the
r^-Dcl nnd bavr- a mljtlr-in
sf C, 125 '"nrh. S-;•^-~lte(l p»sh.
b'iilontt Rhould iooorpcrotrr gvard » (P'y.fa j
:.o p-.n-^nt Inadvart'
ijctuatson
. h o rolor of tho ilJuTin-i «cJ pufiiiattro sirf^cc. I'-pc^v.^of; on
opplieatlon. wJLbo ^viaw .a
yolLow. ni, or
jn
nccordar.cs wlh eho-11
;v on H::.C-2505A. Vhen sot OluMira^^ed,
».he
'on facti or ca.-> ::ovf!T
bA o ilcrcp^ruUr white with
n 1:7 r-r gr^a^ ar '-an'-fasl r.nf jo !face to i««gcnd> and ir^e of tint,
'.pon viaua-L 3r3pectloOB
C
1,7.8
(k)
^i';y'jlt Breeker
CJi'^uit breaker dori.gi should coifonn to dst.-.ilc of Fir;aro i~6.
Circuit broekerH! gMieralJ;' iii-s o.f the pop-on: rolco.oa. puah-co^
rc5et-.type. Circuit V.ros ,r-n uiW be nordnf-nUns
ho.-jilng thf? krob in the r -s«t jsoiiMon wjli rot oferi-tdt? (>.&
r rcui ^-^brcak-tng fur-t ion .
The -rri.ppod r.ooditioa of h- p'oi • .jer-t.yp- .--iicu-.? breaker la i.r.d.vc3''•d.
by a white bcrJ whicr. is . nltiLina of f, ••.5/-..inc:h w.'de. The
b.renk'jr body aid head vili b*' h? -Ir, r',-t.d«r.- |r ,^...,,.,-,.1 .,i,r.v
*•
Ii.T.itod to tbf to? .-vJcfaca of »;/ • virru'^t e-- ake,^ s
roqn'r«d to re?i?1 a ph'vg.T- t.Tpe Aircjit bre..ker •rill i«>t exceed
'2 pounds, and the forc-e rcqj-.rr» ic '-rip a c i nniLt brenker Battiei i
u'ii.1 tiofc excefl 3 p->'.;cdBThe mioiaoiB a7.i'-vatle spare between rirrujt. trealjers g"cjuped tc.
horizontal rows wl.li. bo 0- 8 ?.B!}x on center s.nd hhe dio*'oj>f-p.a
bo'wfon rows a miri-j.; of o;:p
o
31
�o
rr* ;a
^•nG» <
A
XLUV. O'-v
'j:iO
UG/ii :
• 9.tir,
P
ttov • • •
-A. 875
r.Oi;
•K
•*A<T'- .
-KANOr. Ml>l
A
0
" ON'.'*'
A - i'<..\.'iv.,
.'J'0.«7
• 17$
- 0.8A3
r». ••
- 0.156
c
0
E
PUS E'JTTON SWITCH
G
RANOCS
A
B
c
0
MINIMUM • M/
0.W - 1.967
1.975 - 1. OCO
0.943 • 0.4t«
0.3IB - a 711
va•.
-
>-v.
O'
3 ISHBUTTON :OVE! GUARD (TY»:C4
FigjUrs 1-5
1." • - /-?>>•*•» '•
Pu^button Sv'itches
�KANGCS
MINIMUM-MAXIMUM
A
t
a37S
0.«J7
a093
0. 156
0.167
0.250
0.37S
a AS?
a 281.
asAS
a
375
u. ISA
lo® — a J/3
a «s »i - a
0 . 5593
93
« ».A
I «t
a
730 _ I.OOt
c
0
t
ff
O
o
H
o
—
—
RESn CONDITION
->
—
—
fJ
Nw*
—
TRIPPED CONDITION
r
Figure 1-6 Circuit Breaker
- 116 -
SIC
�In tt? dosign of a n y Uco thr.i ,!..-olv=£ op^mvor.-^ o- K,r
ccn3-6' y r ^ i i o a t i i s th^r a ^ t h c d b y i-H.vch . t - r M n e n i \ u r r > " ^ 5 v i o n w i l l
а.
Display irfomif:i,.a wiU be limited to the desree of accuracy actoall^
-dovstandablo.
Identified eo aa U, ot.-/i«te undue
5
•"•
E.-=.p=d.»,, to
.
б.
lDfomat...on will be prceenttcd in ouih a manner tbot any frilnre or
apparent
7-
All displays will be prorerly illuair^tel-• c-'V- --•>
fureti-^r..
"'
.. .
••
lobol ^Keters
<k)
Tho opooir.tc,viion of aet.ro, InolodJog polutor loMtlon. oovomoot
display scale,, and penersl frrm factor character-,ties, v-iii nrn^-.
to tse fcl.is-/ir.2 'y.-*23 (r-^-rec '.•? a-;! !•£)•
" '
1 8-2
(k)
O
lo
Single boriaontal moytng pol;ttar displayed
2o
Single vertical moving iKJint.jx- displays.
3e
Dual vertical ffioviag
*»«
Fc-u* vertical ajoving pointer diepiays.
5®
Single circular diGplays.
6«
Dual circular dleplayT-
pointer displays.
Meter Scale.
linear ocaTes ara gene.rally prei-r^d., Idien accuracy r^-ouiranentn
exceed there that can be at^alnM usi^tg a Uncnr .cSc SSS!
"f
e-pa=clcd to acquire the -Drdcd accuracv,
rc;pi;'rc(', to b? f>r.'-ri;v,7,j trc.'i -i .-.(ij-j
. -^
,
--•
�i.
EL. n
JL
DUAL VERTICAL
MOVING POINTERS
SINGLE VERTICAL
MOVING POINTER
FOUR VERTICAL
MOVING POINTERS
Figure 1-7
Vertical Meters
- I2r. -
sr:
�%
DUAL CIRCULAR
MOVING POINTER
i
figure 1-8 Circular Meters
- 12" -
€ ( •
'••o
�rRANOrS
MINIMUM - MAXIMUM
.300
. .500
.187
.391
.093
A
»
c
0
..362
.562
.250
.343
.156
-
:C7
DRUM INDICATORS
RANOCS
A
t
C
MINIMUM - MAXIMUM
.718
.425
.093
.
-
.?«'
.856
.156
DISC INDICATOR
Figure
Electromechanical Event Indicators
'O- 1?.7 SID A'>-lS34-2
�1>8 3
(k)
D'np'i/'-- rcrr' 1 J A.Tnf>j?frt.'!n
'
—
>.ncr'.c <.t:aM.3 y rv»sdwto. d.gi'j l or Oa.nlos. nhonlC b« Doni^Uy-ea
to read i n vr of »a* Mi-a !t«ihlo f.Uild t, 'olupw or walgh):
as rer>prJ. V'r.;?'-Q.l eoalc indlcnt.or (Tiaup" for r-'bsyatea condltiou
raeti.l toring ::ho. *<1 bw orrorged
by aycteni fyj Jtloii ihon by
displ-'jyod iv-.rn'i-jterv Chen by alpl.iibftt.Vc or Dusiftflc scc^itisnces 5c
deoccaJJng o-dftr of fT>bgro«i.M. i'.n- typlr-oi ri„td syctctns, chc profcrrccl ord.-^r of dtspl/iy sf rongoutjitf rtadicg froci left to right O'r
ffoo top to boiioo la pi.lol. Hxes Is cs follnvcJ
In
Gyafon fua- lion:
Preo.Ttr 1
fOel., oxjilizor
"a
2a
^
D.6p,.ay;d r^rAmetors:
Plov., toiip'ratovo# prresnre, >ii.'antlty» TQlcot aaperes#
3®
Alphabetic or ounoric rfquenco;
S.Tst.e-3 A •
Syvjten B
or
TcnU 1.
1<>8.4
(k)
T&jik 2
DJcpVv pointsr Location nod NoT/nrnt
Jbo pnlJitcr In vertica I single-'p< tnter diepL-iye fclll bo located to
the right of t.he scale. Jointer 'loveinent- io na up direction indicaVea inrreasfch values®
Tho pointer i a horizontal oinglc- oipter dl.nl'iyf c- <; ?. I
above the ijcale (there isay be .lo/:U.taate exccptloJisJa f^'inter neve
went to the right indl'-at?y itirri't.eed valueu.. lbs {rd..lvidvial
peictcre on dunl-pclater •.ndl'-etors .'ihonld he lor.ifed oi'thoard of
thalr rosp^•cttve scales (Ue., b--:el, po.'nler 1; icftle J., scale 2,
pointer 2, berol). Pointer (aover-ient upward Indicates Iniroased
values..
The individual pointers on four»i)ointer lndicctor.3 will be ao ohow'^
in Flg'jrc 1-7 flrC,, bezel- poin^^er 1, scale I, piintor 2, pointer _•
pointer k, bezel)®
The pointers In dual elrc-jlar io' lcetors shovild pVvot about the
extrsaiitics of the horizoat?. I ex s- The lef- cfvxle cocuicrcea at nl.i
i33=degr«''c point from the -.op cc-n er point end oonclMdee countercloclcvise o t t h e ^5* degree p»iiit
The right scale co-itrcncea a t the
225''dGgroo poln' froa the top cc:\i.ftr point aad ronclude? clockwln
at the 315'dflgree point.. Pointers for both circular arc vori'lcei
dial fares should be close to the dial fr.ue and c^ale to reduce
�parai-Vix to a o»Piou4.
for c.cpro7«d
tieisee, tha
pointer h^^ad wi.ll be triar.|i«Ur m d the a i d s t of the pointer
shaft, where required, vdU ha parallel (n.g'.reo 1-7 actl 1-8),
1.8-.5
(k)
DlnclS"? Mni-kinera .
,
When oporationnlly useful., eolorel renije tear!' in.'is wet be used
on vortical, borlaontal, and circular diopla:,-3 to Indieat.o
operating ranges, "Kiree oporatiog rooge marl-rtngo arc recommendod
to indicate the following oouditionsj
1,
Nora.al
2,
Marginal
1
Prohibited or limit mark
3-
"" I
Rargo Pirkireo ehould be 0. 05-loch mde and extend to the Umite
of tlK; uiuile factor reprcscrted, Range mrkings vail bo imposed
over Lbe scale index tnirklnga to enhance reRdnbllity and visual
cue rcGTion.ce, Idmit ra-ixkaar: should be 0, 07'ln«ii wide end equal
la Icngih to the loag graduation of the scale in qvestioa,
Diraplaj* cover face© will ba coated wj.th an artiroflectlvs trans
parent materials
l.-8a6
(k)
Alpiinr.'-V'erlc Roadouls
"
A.lphanuncric readouts should be ocmposod of dcctroluMaescent
eoven-line characters that have :>ie following deaign details:
Slant-
- 14-2/2 degrees + 1/2 degree tc the right frw» the vcr.
Height
- 0. 500 Jnoh + 0, t>05 inch
Width
•
- 0. 375 Inch i; 0, <>>5 inch
Stroke Width - 0, 625 inch • 0, «>15 inch
Spacing boiwecn nxwEorala - 0, IXy) inch ^ 0, C05 Inch DimlBsuiB
Iraeasyrcd at the bace of the num-jml
1.8.7
(k)
Elc t'-oirechanical Eo-eat. Trdlcaioca
Blectronschanlcal event indicators are rocomtiandod for use when
highly reliable go^no-go '!or two•oogition) iiTdicaoion^ o.r®
r e q u i r e d a n d when e l e c t r i c a l p o w e r n v a l l j i b i l i t y i s o e v c r l y v e strtcted. These Indicators are recommended for use as go-no-go
(opcrational/nonoperatloa.il! s{e .2s iad:'cator6 oni for vwo-positio'*
positioning Indlcatorn, e.g. , no'^'mal-naxia-.ia and norrr.al-rtfiii.lawa
poGitious,
1.8.8
(k)
Two-Pos'ltion Dmia Xrd.lcators
"
™ "•
Two-position, electroncchanlcal dnia indicators will be need for
status "indicators
1-8), The Mark (gray) poaitien of th?
�drtia vrtll i-jTor
tr« ^•^ane^^Te-J
l e in or oi>Rrt«tJo'ial node or o r o t inhibited i i o n oneratic*?.
rho baohcr poiw
(n'U rmnie b 1 : . . / . n i v.1alr) position o," tio rirvrii iadlcntocs Kill
Infer tint .!;c 'r.. •no-led pyatesc «>aiint lo i.ihibilsdl frto operation
or
'in l:olflrnc05 -03<iLtirr.,
•
A pair of
»•:. ^etr^e-hvclcci.l dru.t iai'.cators t.'ill be
uoed ao por.i >. . •>> i- icdieatore for eomo jsycteit <iericea« Ono will
Indicate th .if:;
ir.d c-3;d.itur. yt-sitjonB of the dt9vlce.
second will i i i -ifi: : he r.omal std eiimtmiBi vasitlon of the dcvicoTbo pair of dr n ii.d -cotorB will t e referenced
to a switoh pooitiori
The dleplay face of th.* two-poottlon event Inilcoloro ohould ba
Pcrtongular vi.-h a dleplay sine 3o Joss-?han D, 187 by Go 2Cl Inob
ard iho lon^ nxla nourted horlzot1,nll,y„
Z'i<-< I-c^icch-nioal f:fatiJo t-d^cntorc tj/rinlly t i l l be localod above
the nfjnooiatcd r o r t r o l cwAtohoa^
Rleetrooechsnlcal position
in.'l.;eatr.rn vfii: be located with r.-'ference to aw.tcb positions1<&«9
(k)
D.-f.r Irvl.''".TO"*.
Eiectrononhana'al dJaf event i a d l ' a t o r s eay be uoed t o diaply cbacges
onalofrora to a speceiu device poni^on, "nieec indicators are used In
ttucoaatic
syct/ns and.are rot dii'ic-tly asaociated vdth a ev;xt.oh
opcrationa Th'y iT'xy t o Ufied for riystcm devlrr operational position
BxatU3'.
ir-d'. ;otor will tlispljiy the poaJ' J a of the i^sterj devic.from ore exlrc-iTie la the other wains a rotatablo biack pointer. Thorc
should be two black indices on a white baclfgrovnd to indicate the
extreraecs (?'ig-jre .1-8)'The display face of the electronfohanlcal di'.c e»cat ir.dl-:afcoro val
be c.lrcular bavin,;.- a dtsp'sy dioircter no lees than O. 625 Inches.
Tha Indices ffiy-ct be f j ted lisving a leegth of 0.. CIO and wldrh of
O- 093 inches. Tho winter Aengvh ahould be 0- M ',m ':,c
0 . 093 inch. 'Tlie pointer opncinc from an index uhould be no sreatf than 0 . 016 inch 'Fisiire .1—S)»
1-8.10
Alarn S y s t n
Any e>:porJ.rcent that has any oper.-jr.ins characteristic which can pro
duce a ti'se-critical liasardous c<«iditioa requirin.g laasdiate corrective
action will ba desagned with an i.ntcrfaoe Ine-trunantataor output ccapatible vd-th the CH Master Aiazwi Systca.
(Additional crlteriii to be addnd)
1,8.11
VaJldation Tas^irq
Kooslandard or intoerated displays which coobine related Inforaatlcn
in a single display uni t , s h a l l be subjected t o huiraQ cngiv.eezliig
t e s t s to dcterraine the effect of the lategrEcion on pyst era perfojTBaDce.
Units which produce pcrfo:-nani'r equal to or batter thsn
single purpose indicators are flccsptable.
�_FHY.-JIOlonTCAl
i T,T|i^mCW3
i-O'L Cr«>w Ont-Ta' Icn.-il ry.-:; . -.jij |,» Rygu^romcit./i
(See Table
i;
(1)
tor H.i'Vnrj)
Food
Pood quar.lity vill bp based <>a on Hndivjcual calorie intake of
3000K caloi -OB par tnon p«r d-if^ Cnc-ron dayo' food rrqoirca
179 cu. Irpbos nforcd volumo at 3.3 ponacs vfelslit.
2.
(i>
Wnter
Water con)?-.itipc-or. .3 .10 folL-Jwai"
2,.6
ili-iiikf.Qjj aod food proparation
5.0 Ai/c:-.c dry,, ^aolcatioa and hygiene
3»
ConotnTil" '-.'par C'ln^ente
Each crew r.crbcr .-sr^ulrca a jjsw co-irtan'; i.ear garsent, (C^Q)
r.'cry two dnyn., .Nuober of milte >-'iTU>r^d
fnvr^cr of crow)
X ' o | 2 ) where r -n m i z s t o n deration i n days. Wliare p. . 3 an
odd nvcibp" 'ice the ne:ct afBal.ler p«»iri>er,^
•13 cu. ft- and
pounda par auife,
Stored volua® ie
Pc^sopol HvffioPo
(To be added)
*5'
EVA Opcrat-orval ror^nnptiofi
a.
(h)
One PiSS UOH ar.-^dgo )»Qr wofgs; dlisena-lon
* IV*,
weight ^i->3 ^h}. Store 5 Lntera:illy,
rf3.T,?»ii-r «.•- i«
s t o r e d exte ?*nn l l y .
b»
(h)
The PUiS lie: 3 'K rechnrgerililo battery that nrist be recbarccci for 10 hours per uaago. Allow '1 ysagen per
battery- Dimcnrdon 3^* x VyA" x 6H", weight 3 ibs.,
store Jnternaliy,
c.
A full PISS oxygea c»iarge J.a
pounds.
tion Will average
pounds per hour,
Csyg-'O rtononpu-
d.
(1)
During iWA the standby D'A acfronaut wil?. cperete frcw th-^
sMlt loop of the tCS, requiring operation of the suit loop
fan at '52 watts ?ri* hoc • powar romrjoption!
e.
An additioDfll Constant Wnar Gament. (CV.^) iflll be included
for each €re\-.3-n on ^iVA :»r EVA afsndby duty. (ThJa is in
addition to the callout of pai^agraph 1-,2.5,1 (5^.
�C?.Zv! OL'IvRATTON.H C0tvSiJM.*i3I.E Kf-vUIIiSHENTS
Wir,
C-^wi'ioclv f'j
f
1
ECKMARi)
V<» l'>mo
Pcyer
Ci'.. Xn.
Watts
. . . .
Ar
i
I'er Msn Per Dcy
Is
Food
2a
Water
3o
Oaggen
2
Va
CoQstanl' V/^ar Garrao,;iL
(
2-3
r.'9
7.6
2-a
.
\
1
>
(based on i ovoij? other day*)
4
(" )
Perooruel Iiyj^lene -• chowiji,3
5'
gu.t tooth ijieanera
M
C - )
deodorant t
OtCa
6~
<
•^
Bo
Per Kan Per IT/A
•
1»
PLSS LIOH cartridge
2a
Battery
a,
after Uut ueage
< - )
•
».
0
Constant Wear GnnaQnt
Oxygen "'per hour)
5e
fio
Ecohargfl a.fter Jisaga
bo fioplnce
3o
*
Coolicg Water
1.9"2
1J9
225
0..25
.1.83
Crnw Wor?fcc' Ppcf^nrnioB
1#
i
tJjitrented bloi.ogiral waatij eh.,11 not be allc-wed to bccoaa free
residue in spnco.
.J
�2,
(i)
yao'c Vaslo Production
Vol,
.1,
3
Orino
3^2
Feces
0-3
Water Vnpo.r
5-3
Carbon Dioxide
2.3
There are additioDsl oinor-itcos of hyM-^a -.fci-.l;® that can be
ignored frois a weight staadpoitit att total jn'odeetion for a
i-isan crew for 30 doye is cbovt 1,25 pouod:?- Iheoe ilffluo
i-ic.\ydo flavusr hairv naiJs,. n-j rrocrcani&'Jn, aliiia cells,
a'"id mucins,
1,9-3
Radinti qp LIti;', rntlooo
(To bo added)
r":
�FiTJiT or-:-:\'AT:rGi:AL
2.-01
Thopo requirerannwj cl«?faaa i-);o.';e
«>ud oanotrBlats that
•ffpcl the
m ..ri.oic'i op'^ratloiia of A/a',
2«02
gnrpog-i
T}ie priiicry r .vpoa" -f. i.o d. fice tlnr.^ rrqulr«:r>flata r-ncl rr\t-7rla
6.lth«»r pocuJp.-ii- to A/J" ->1' def?)icd by tho Anollo wlosion cor/ljuratlon tha.t five nc-'.-onary for nlaslon pli=,r.aiQg or l^ffect cquxpneat
doaign,
Tt 13 nn obrif.tivs to e>aint«:«ji the saria functioeai in-flighffilsalon
p'-occiwresv t c-hnlquoa, and planning ti ar. oharactari ae the
atacdsrd Apollo i-i}.6a5c:>
�2 - 1 cr;^rf ArsiGT>7;:-:.vT.: ••
nun stati<m>T7
j
Crew Arr.'i.
It ic findelpo^ .jQ that aXl <• ri^y wt-niboi-a \.lll recelvo a d'^grce of
trA.';nlni;
porro^ ts total later^hangcabi llty of crow dutJos on
en oa<>r;tnry hcoiis, 'fhs onlsr of priori iy of crow ntiliaotiott in:
a*
^kliatonarJCc of flight eafo^y
h*
Condvict of hasio
c.
Exploi-arion of natural phonoaeoa
d«
S;;hedulod pi?c:sureaents oBd eboervatioBe of natural pehnoneaa
e.
Repair. •^ali.braUoo and codifloation of olssJon-epcclflo
cqu-lpcient..
oporations
For the p-.r^cacn of rrov s'e.U^T. salei':tlou„ tvaicing plans, arid
nora?al oloB*.en planning, the following ground rul9.-5 ehall apply:
a»
• "^c eoomnd asiron^ut viil nflrrFo'ti all major spacacraft taar.'iuvars froa the left haad poaiiloa of cither the CM or
LS-lj He will also be the bacioip navigalor on the CM.
responsible for Q}\ naYlgatler. a-^d cperailcTi of
the CH Iccluding docking khea the XifJl io sinarated.
E-n'recr -• Is pr5.raarily re.'iponslhl? for all experloent
act-irltieo pins backnp operation and rarigatioa of the LEH,
Aaoi (Tr"fnt l^'-iorlttes - The follo'dnc tab i o lioi B acslgnaeat
priorities for the rorlo-.in crew meai'ei's. For purpoees of
mission plaanlng no noroul oasLgacfflento will bo oatie where the
crew n^tnher .Is listed as type 'in In t-hr va<" of CK 'v^,. ,»>;•»
pcrlceni-s the ccr-snnder I3 lifted as bdh typo j5 and
- *ypo >
for repel (.••.!ve axpariB cnfcs or 'hoso otnou^ly requiring all
or«u cecibsr.s such as most bio-oed» r.od type ^ for highly speoisl'
typo of experluieata ewh as a 'clescciw prigrara,
,
Crrw
Hersber
CoaaiaTider
lani-'ch 1
CM or OK Dochcd to VO'. or
J
iXri
&
I
Experintn*- Carrier Operatioi'B
J
Orerniic^e
Recovery i^larc 'ivers "^Javi'^Vica' h;^erire^t6»"^'.accu» erb liavT'
t
J i t
1
i 1
1
j
1
•i
Navigator
2
1
2
1
2
Syecen Efegr.
3
1
^
h
1
'
2
c
'
1 2
Q
-
�priisc fi-r'.poti8; bJ li ty
a-ileP
i=>iU tmjjiina and capabiUty
a-
SocoQdery F.ecpoPclblll»-y - fjill tralulns
5>
Operating CepaoiLlty
-• S'jftl.c-venc. vr-aiuta^ to dfCQnabratf;
capability o£ Bor.iial oporation
Boorgency Capobil!.^
- Tj»do'2';riaQVioi> aad Xlaitcd praetice-
Duty StnnlonB
(To ba added)
C
«
r-apabiUty
�6,
AL\ri>f zh bo*.' 'r between hVA'a fo;' <Tur-h crevmaii,
7«
Maxur.,i!a
hours c.
o'Jtslds Hno for owo .^A operation Is thr^e
8-. Provlslosa w 31 be sisde to penult Ev'A d»4ring darkBeHa,,
2.2<.5
t»nd
'a'e^Con.ytrainfcs
Jiard s'j-'.; 3!A oo ."urcr ourfe-ce vl H be 'Limltec to aix contlsuous
hours per daj.,
(This reiju-.r-;r a .^'ISS char^ge)
;.:>r
�n i l
t h r ' f c .'ir-t r.-tri.;i ; •
l i f y r.:
An
y'or
• ;
iVA
?'!-
• i •
r
i
v.->(111 j : j ;
;-r' v.-th
ti*
.i-f
t h e atar'jb.^-
•••
';,
kjjuo**"
>N'
cosimunitfatiena
.».J
.linllons of
. r virau
iticinr*
j,"3ivT«
rhe
nur >
f;ht L\A
£.11 fliK?:*.
ci« '-rev
tjtlitl :5stl«:«3UL
i y efaal".
..ivifr or « ' c h l c l i » .
iOi bcv
'-a •.in>l,o.or/
;>• r ; . . e . - r , • ;
^' -ndby
T/J: nnd
rrv
• •
. . n - . - n v v o i , ' ? • t . . .i o r i
fi'.u
blinij epotp are
the
>
"
ii't
be oroHab''
^•inH
.11'
i - f l , , mo
lo
be'WttaR
w1 'J. hnvs
TnlroaanJ
entetua
vthiclea
tvo-wey
h-y
v o i r e r o v e - - , •'
'•
.-rc-"
^j-atrcysnr'
jon:
'.n roqutrcd e c
lollowst
3-
AIJ
C i f! b u r n ; ;
bo
Once p,>- oj'h'.'
ni' v.,I
lavr
" ban .J-hou.v inioi ' a'l6>
Deorblfc
T/Mt
voice, radar;
i e required aa
a*
Xaoucii,.
t>«
Major Si'S burr^^
t o •iRci
Cf
Aoy
cn : • • . .rin;j c - ' v a r - t j e
f o l ':••••
i"oLT.ir»wi
oijj3if:tri,nt
n
it-nft ctnl mJK
'
atH'u'orial •
cos.plf'tloit
Jtars'j'jvor'
i»airo two
;»f b j m
(i5X«'ej;».if.a
roOwOi:'- p r i o r
Jg doorb?.t
sijneitwc-r)
�G:--'-: r-i.
ON Er.'snr-jii' Ort:..ArMi<s
}
1,
llvtl-r.- 'n I.! j U.r.itlon of the cr<-"v lor n-dumjancy TPtiootcrlng tiod r?i.il»irp.
stotJo coi-rro'.ion.T/otor-tiono ol «>;perJrt:a*«G viil tc sjp««d»
?.
Gxpcrijn.^n'; (*atn oet-up, pr«- or i*03t«« nJjbrarion asi ooRratlon Mill bp
0'n-bo!*i\i rcjitrollcd sad will &ot roqu-xe ory groind upllnit euoporh
sapabl\j. Ci-spo
3-
Tao
rcrrd , dunp or ."oGufi p reqii
wiV. be h crsM roBponeibili'y
aod will not requiro c.ny ground upliiJ: controls
4c
It ie clsr lr-;blc not to hare
"• PoUviiien oi'rtng major Jliglit
ffipneu 'ero — iaunch- tra'isiLatinn and iloi
, 'sa^oi* Sj^^S burns, deotbit,
lun*r '-.adinij md aooenc^ .md rc--onti:'
If roqu- rc.d., il will not.
utili:;.' moro tlian or>e cx-nw m/t.bcr pef'ornliig Troi^i lis rtf^xhr duty
otat jo.i.
5,
Ibcpor-;:,! >;it .int.lri»lc8 xfil'. be co'rplo--i at Jr-ast togUt hours prior to
dso.'bit ond ao notrd in a'jotion ?..
•
�2,5
riTOfis T-T-'B T.if?2-,5-i
Gefe'-al "»ro-;ad Puiilfrg
Tho question of u prcpe.r worc/re^t dniy r y d e in b
cpinloitat.rd
variable.,
A fjj>aL ocovox- will not maalt x.\ a.L'. probablbty until
after ccvaral .long period Arollo UlgSits have bees r.osipleUd.
In th
oioartlr.fi, a re.-jsonable rye l.e rrast be nelf.-ctad to p.^nnit inUi^ion
analysis of celfvrtcd erperlR^nt granp.ngs- TIds ejr J.r will be used to
anuljzo the bnslr arceptai'"! vt ty .of vrrious ex-jerimer.t groupings with
tho ucderstijiidius tlmt whore i t beoocxja a .litn ! lug factor, a specif --r
aoalysir. of altoraaSo GOlutlo«i3 will be madd- The cyclo eelected
t
based on the foilowing geDcral pre^'soss
4
1«
One rreura.-iii -.iill always be awake rjid in rtiBrge of roiGoion
lai:r/.;rity, i„e.M v.'stch duty.
2«
The woi-iyrest cyc.le will be orUnted to itnlutain a nornal
Uving i-coitine phased to coSn;idc with thu eastern U.S.
t.imc zone,
3»
i:,arh astronaut ul.ll have one sl?ep period of approximatej,y
serec houro augjneated, wlien p;soltlft( by >• rap of not moro than
one hour..
h..
Persem?l Triaha - cr.tirg hygLsne, exei-t-iae v/iil not be rigidly
sch-duL'^dt and fo.r olsc.U'r p.>j-»nl;.'g p»'rpo.«.es ii^e allocatiODS
for 'Ae.fe tasks will be ts^de by duty poriol.
5.
Koutice
micG'oa
and for
will be
1
^
.
6.
ml.':.3ica houflelc^ejiing :?.sks - stot .a checkc, LiOH changcsc
log raa:lr.t.enaj)or,
will ?!ot b€ rigidly rchodulsd,
mis«non plrfoning f'urpor.os lima al'.c<atlonB for these ta. . •
rsiy-c i by duty perJ.id-
For prellBlaaiy AAP misft'on aiulysis i t wall ba asnu'^cd tSxat
elgbl C8) hours p*>r day per
or o tot-.-l of ?i» a-r.bourj» per
day in aeailable for experitpeu actfvity.
2 * 5 S t a n d a r d ".U'rnjeft Cr-uw Duty Cycle -ind Ttnig Avtr-ilaliLe
la
Three^iwn operation with C.S o - GH docked <6 other vehicle.
•20
24
D8
'v/T«--h
Glean
katch
Ocea
1
1 V.'ei r.h
1
Oncn
1 ;,'al:<h
Sleip
i
Si
e
.12
1,6-
1
;
Wa!;ch
1
Or
.Iv'atvh
•All tinea ere Eastern Standard Tines and the s t a r t of f i r s t d e e p period may be
established for any given niseion f?*on i600 t o 20C0.
.
�^' Crev Tlac
for gHtKiriT-ont Cirjoi-attooo
(See sections
and 1»3»5 iof derivation of tioec)
;jiii;;i>cr of Crev
Avpi.loble
jSpcn Tin ?
3
a
UikO « ikskO
2
8
?:X0 - 8:'fO
1
8
2:^-0
f nuiiours Avali&ble
.for Z^poclmfoto
2>.:30 - 2S:00 (hrs.)
2*
Thrc-'ngn Operation • one In (2M« TKO in uraocl-.gd II5H
a>
Pvtj Cycle
8
T^na:
Doy/Niglit
(x) XXX
XXX
XXX
LE« n
XXX
Tx\
:oa
i
U3i HZ
'••/atrh
CM
Ik
rxx
18
16
xxx
xxx
20
XXX
XXX
>
i
1
V/p.tch na?' »>p#vn DUvv
Watc'i end On'-r, l'u«y
This duty cyolc ia based «a the folioving araolsoa:
•
1) Kln-itaizlDj the tiipo aH.! three creii' 'fiC-'jero are asleep,
simiiltaiseously. Ta tJ-.ls crisc- It le only for about
2 boura since ibc lac: ho»r of tbif sloop period la
actually invdlvcc In personnel hy&iene and eating.
2) Kininieirg the niTJibcr of day u<-rlcdc »'jdc un.-ivnlLih)*for opers>::ions dc? to the LB4 rrsy bei-ug asleop. In
this cas" only ore even day psrio'^ is lost.
3) This cycle Is based ai a 2-hour oibib- period for gro;utd
scheduling purposes. Rjc actual cycle should be adjMsved
to the tru-» orbit period tha*. vi.!! be closer to 1,9 hours
for 'lO-tsile and 2.1 hi»urs for S-nile l»nor orbitn. 'PhiH
will result Ir. ;u.-nor variations to the tine allotraeats
available.
2.5.5
Zk
Vatfh end Cofai D'*l v
Cleeo
Sloen
12
3U
Watch Duty Period
2.5.3'1 Three lLm Operation vith 0" or CM JJoc"ifcd^co_0^ior V shlc le
One crowr:aa vlU. be awake and oa vatch duty osslgcment at al':
times. Durin-j these porlcda he v,lll be rsspensibir for the
EMintentince of spacf'Crafo syGccr.S; roxauuicatioue. position
and flight records or logs, and geaci-al operational actli'iti-
—1
f
I
�Ta CHPo of rnei-fjcncy ?•© -illL f fcrt
-wpilrle CowmadariEach cjcw (r'.'ti'.»er wt II v-'or^i two four-hour wa^ch duty aasSgnaicPta per d.ty,
•>• cdt3tpl,y i'oliov.ng tbn sl«ep cycl#
cod tiiQ ,'n':;';d.UteTy n.-ccosin,'^ t?i3 olifop cycla^ During each
four-hoor vfTfi'b the roliotjojj aclirit.'.f.p 'jill ba perforseds
1.
SJxteca (i6) n'cut.oq cut of every hour will he upcd for
vehicle :sor ;.torJ
loi: •V2"*ntoaanc.».
Q.
Stfl-up cbe-^k of ZfG hovvly (6 win.) recharge batter.'
ae required.
b.
Statue ch-^rk of ECS hourly (1 mln.).
e.
Vo«ce oontnct vitt MSfS every 2 houru or once per
orbit (5 atn.).
d.
Pi)r,^e fuel ct lle - al.i.ernate 3^ ard ©2 purgea every
5o5 hor.re
(j.2
nie.),
$
e.
Si^-SCS eteluc check prsfcrftbi/ ulthln T/h range of
HSFh every b houti' (3 mio.).
f. Status check-of SES evsiy ^ haws (2 tnlo.).
g.
nritery check evsiy 7 hcurs (1 Bin.).
h.
S ii'^s check of CK-BCS in unpreseurLzed state every
'2 Isoiu's (I ntn.)
I,
Alternate replacing the CK Id5H filter eloasata ever
12 hoMrs (5 ain,).
J,
Staiun chock of ryro batteri.es every
k*
Data aoBip to 11577 oa eocft
(2 nxii- rj-aw tloci.
Zh
hours (1 oia
na
2.
Twcrty-i'l.t i
.otn' teo fo,i. i-anco of poaiticm
logs and bneir is'sc-icJ. rccrric,
; i-iboh crevoan wii.
be expected to Raintsin cifficlert eppcecrair. pasdtioo
ortenraf.-'on to be able to in\t.l«t! «d>o'-t pj-o-rlures at
aoy tlae.,
3"
Twenty (20) aisiites for eating (gancrally enacka)
during each wstob^ llils is ao arerage valiio that will
be wprki'd on nn "as «*^'ai-Lable" baaio ly the crsu.
Fifteen (15) MJ JI - tec .or exei'clse. This provides oni>half hour of cxerrlce during watch doty wliich will be
added to one-half hour additional duriitg the open d»ity
period. Tills
• I cc- ^-orlced on e.n "ae available" basi-e
by the crew,flo
exert iso will be perfomed oa the da;,
that a crevsan EKhea an £t;tra Vehicalsr operaiioa.
«
�5.
6.
Tv/s»Dtj < 2 0 ) ffllPi:'.-op
J*">r
a i ' o i a p i ? v n l u e t o frs
t h e ttSt.roiuiuJ
,
in^d c;i nu "hu
^bchty
jKir \ M l c h
^ 8 o i o 1 n a t n.7
»*xp:!rioi''ni.nl
the rptPro?-y
hysrt«nt>.
TbAs i n an
rfquiiod" baale by
: o u v a l l o b l o foT- 3 e r o n d o . r y
'ilicnc fliouifl prsmarlly f a l l into
of nanlfujuf; ii; b<o-iied experiments or
i f l l t - i a t j i i j ; an<J/o)* a e j . >;or:n.'* ' • o c k j . U c o n t r o i l o c l e x p o r t . ciPAte,.
Gcnpp.all;-
it-e :n'j -o t h a n ; 5 m.l.nntec
e o n t l r i i c ^ ' M con-^ r-i r a .
o'-« .'.i
mental du-,..«o should l e
c^a^•c!-•a.
DurJivt
frc.r: the eonKr-odi-r's
f.
or.'.-
ported on oxperl**
A' : c d i t i e d
f o r the vatr^h d u ^
: h e i f a t c h d>i : y e r e w / ; s B w i l l o p e r a t e
'IJa)
' •
7»
Thin
c n v r ; j e'v^r<>D
(
•>.>
tjr'- t o a o n a e p i ^ n e d p e r w i t c h
\rx
i ; geeevolly ) o
o r additional e::jjei-ltioPt
2.50»2
:-or rovljiatAonnl fjjcea
T h r c - l i a e O p « i r a t ^ o •• o n r cian
I4
i a Cll,
iwo DCD
In Lat
'4'alrh Dfof Op3 l/ot in CM
a»
The ciagl? iituj i i
Add'.n: onally,
of
b,
t h e CI-! v i i l p a r f o T i n n l . l t h e f u c c t - i <
in ntti ionc
cal.icd ou'.
2..50-!. CD and 2,5.3.1 (2),
h e w i l l c h e c k i i w i t h t h o I S i o n a niJji: r v ?
ouce per hour ( 1 ci5.n.)»
Tbr ouo-h^l.f
O J ) >ioi:r •• i r i n s i i R t p l y p r i o r t o a n d lencirdi.? "c't
foUovrtr.g tbo olr'-p poi-iod wiJl t o utfliaed to
aco'icrilated
s.
•
d.
ooctionn .?»5.3ol
< .\) and 2.5»3'>l (2)
accoapLiRhod due
'O '?e,.nl«flp period.
that ware not
T h o s e prJ.iT'Erj- vo'Sch f u a c t i o n e w i l l a r e r a g e a b o u t
Th.c
r<'.v<iAain[; c o t . t r i t j o a
eectioii
notel In sactljuo 2-5-3.1
v m I I h-i l i s t e d u n d e r O p o n D u t y
2x3'^*
^ a t c h ^ Pti'-.; 0 3 o f ':Vo n-;n
1/ '.ig^
*•
'-very
C
) n i n u t e o on*
of
hour Hill, be iiard for
vehlolo aonltoriri^ and salntorancei
^
chec): r,f
ppg hourly
(6
sin
),
batteTdco, an roqutrsd, if capcbllity
t.
I. .
^fO
cinutoo per hour.
Ihrc'-ij;!! 2 . 5 "> 1
..."
pe.rfoi-3 t '
and Bainter-fineo functions of
recharge
e*ists,
»
O
2)
5)
S t i t u i c>*eck
'f
0:^5 h o u r l y ( I t a i o . ) ,
V o i c e c o n t a c t w i t l i CK a o i a - l n u a o f c n c c h c u r l ?
O fflin.)
Voice centaol
with
y.STii
per oriTit (5 niji,).
every
two hours o r onct
�5^
i'
j
Og
6)
2-.5.'*
'-f.abl'i - ait.fr-nnlB Hg
.
(12 n^C,),
rep.\fl-'n ..f'M I. 01: niter elflttonto evory
'5 »jn^).
ho'irs
Open t>L;ty Pt rir^r
2 . 5 . 4 T h r e r > ! : » a O r - - i v r ^ j a n W t U i T M r.•• C M Poe'tcd no tm
Durlnr ari.y S'uUoiir perlcS
K V H will bAve O'A© contlruoar
oaf'T duly Il^rlod. D;:;-jrr.* thio period cortjjin houe'?ke3pir,7 r.:'^
nuai te p.;f i\-.r-scd hut the ren-eind^r of t';tl5c" ie tan> lible for
cr.'r-. r.t acti'/ltj «»rd rc-quJrcd
Pav^fjatlon.'il fAxca or .9pTf;aor.v.ft. jaiineivaro. Tho foliowing
act:'.Ham ore iurludti jurieg thi.i psrlod:
1.
"fciko ^.'ip (i hour), rhic ot-a bo eoho-Julyd by tho crew o
"as cvoUabic" baoio
r.nji be eUsipatod oi.crxionally
2.
3»
OOP hot Baol (I 5our;. 'fbio le aohedu.lcd for one }>• v
pli^'W cotae tvae fir rolavation or recreation.
oxorriS'"; fox* I/? hosW' I'.xie vfou.ld riortnftlly bo
broken Into tbra" 'n- C'-O) Hiaout-e parl.cic nnd cr.a be
niuiJp.-xcoi cep jiona lly. J'O exercise in i t-nuirfd on vba
day a ore-.msin piirforu? rn cxtrn rehicular operation#
Perform waste e.llmlrntioa and body oloooins (1 hour)#
5c
'
k
2c5»^t.2
'ITjo rcBiining tlfle i s avaUrsble for other activities
to. o hours) .
a.
Flight optmtloa; - r-oe section.3.0 for required fit;!.'
openitloa f»inctl>33-
b.
Bcfpriaent
Three-Man 0:><-ratlon - on r In
- to be dete/KinfJ»
two in tBI.
(To be added)#
2»5e5
Sleop Period
2«5->5«-l
Three-»Man Oppratloa V.i1h TH or CH Docked •*<> L3i
The sleep p«rl-od for escn nen will be eif;ht (8) hours. It
anticipated that about eu^cn (?) bouro of this lice will be
o f f e c t l v c e.'.n";-. Tt • r» -.-fria^ t l c e w i l l b-? ntlV;.'':.! t c p r a pait tin £.l^>p
ca risixj, cl-v-ninr cp clxe
ar.al1on, parf.vrraing pcrsuciicl irrglone, and earing b.ranktasl ,
T5ic iQ'Uviduals eigh.rh hour of deep will bo in the fora of a
nap during the opea «!uty period, (Sao 1,5.5.1.1),
/ O 2,
�J
- One in CH. T^ Q
Th- flc-p IVnr.i fry.' eacfc ooc uiU be 6c-7fn (7) hour3, n •
a n t i c l r . » t ' : d tf., -. M?oct si:- ("S) heuro of t h i s t l a e i f i l l b e
efro-rtiv.?
Tljp roirinijis tiino rfili he uttliiod to pr.-.
paro t h e alu'p otj^tuo aoc. o n riftios, cloanlng up the oloep
BtatioQ. pevic-mJn^ F-eroci-nel K yfj I ousc. nncl sating brcakfosr.
Depe..<jlng oil tl;s iength OJ' chis type vC operatiun a tuip of
ono to two h;. -rs dwratlot ehOKld bo o^;hc€tulod durJac tho opc^
poricd-
\v.
10^
�o^f:i?ATicNAL coNoTRAiNT.;
2<6^1
Kii;src;«
c
Tjiipch O.-'c"n". Io;:« to Liftoff
1, Inunrh cuUoff time io IfjCO hours Iccal t^me b^<-.PUoe of recovery
(a) rcqulrcQcntg..
2« Ho cxpcrjnent activity w^Xt r-s-iuire crcv tariicipatlon itore tfacJi
(b) 90 minutes, or loss than I nluite prior, tc .dftoff.
3» lixpnrlijient uotivit-lea during "fie coi'Dtdowj* are iimitRd to those
(b) that can bo perforned by the ayoteme ensinacr from his counh
pooltlon.
266'.2
Pone Vi'iT'ch and Sa-rth Crbit
1« J'roa Liftoff to confirmation of orbit experlraeat activity is
(b) u-ndruirablo.. It required, it should bo Itinitud to lha capabllliy
of the .vycitoaa on^lnocr from hLs couch poeition.
2B A ctntun check of all systems wil-l bo pei*foni'.ei after insertion,
(g) Aosume ^5 minutea with all
BoiabArs occupied except as oote<'.
above,
3' Eftttcrj-ca will bo recharged after .tj-'oertiru, Hcniml span is
(a) 100 oln-'tes but crew loading :,a 2 nlautcs for jyeteca engineer,
4, There shall be a mloim'jra of o!ij orbit piicr to S--IVB/CSM
(a) tioparatlon.
5, The S-IVB G&C and PCS shall b*? uaed for all aaJieuvers prior to
(c) S^r/B/CSM Eoparation.
I?iU fine alignment vill be required once per day for normal
<c) epaccrraft raquirenents f20 ns.-mte),
7o IJTO alipanent requ'res hiving the '•X axis cj-.; i-•*'i- r?, '.1
(c) local horizontal^ pointed in -Ho direction of flight and aalntnliuvH
within + JO' of the plane of • le orbit. The
axis nict re-ajr. r
least yj'* above the local hor ioo,
8, During near earth orbit cperav.ioas navigational sl^tiago will i>'
(b) token 00 loss than twice per day (3^ urinates per set of three
sightings).
9B Oribral navigational eightlnga require having the •••X axis in thn
(c) dlrectioa of flight anl the +;• axis n-var iocal vertical and pointed
toward earthB
2.6,3
Transluugr Tn.jectloa
1, The S-TV3 provides G?;C and thi^ust for the vraaslurar Icjsction.
(c) The -j-X cxls is for-i.-arc rnJ approxiPiatcly parallel to local horisoatalft The *-3 axis la down aad appro^J-o-etcly pajvillcl to Jocol
vortical.
�&
2
<b)
5.
(g)
battcrjca 20 niratea
Prejvrtmlioii
crev
tlrae
l l o down,
arlor to d « r b i t bum (20 siautoe)
for tranalumir icjcctic®
incbidee eyotsas
IHU c o n r o e a n d f i n e a L i g a a ' . n t
chcc'rr.
— ^2 mljiut-es iOTOiv . -
a l l crew acKboro»
2,oJt
Trpr-.npoc-lllon npd Docjfln^ 1,
(c)
2.
<c)
The
i a tho active vohicle diirinj tmniposition and docking*
Tl}r S—IVB l a l a
The
f.-l'VB o c p n P s M o n
tranrpeoition noaeuver ol«rla with
within + JO" of
tho trajectory
pleucs
the
3*
(g)
r o l l i a order to s-.llgn
+X a x i s f o r w a r d a n d
*2. ^xla
frofT t h e S - J V B t h o CSM p o r f o m j a + 1 8 0 "
a --63°
'
tfaa a t t i t u d e IiaLd n o d e -
-Jp.
After eeparation
p'tch maneuver follovicd by
for docking,
Tioo for tranepoottlon anif decking including preparation,
jettison
o f SIA<. a n d p e r f o n v a n c e o f b a r v l d o c k i n g p r o c e d u r e o i s 4 0 m i n u t e s
Inrolving a l l crcwucn.
4.
(g)
2-6«5
Time f o r S-IVB ceparation
including preparatoiy
procedures i s
5 minutes.
T r n n s l H c y . r Co.-5j^
1(c)
2»
(d)
Tno coast period iacluiofi o mariruQ of nine nrdcourse Rovigaticr .
c i g h t i n g a , f o u r THU a i i g n m o n t n a n d t h r o o d c i t n V c o r r e c t i o n s .
Passjye Hiermnl Control (ITC) io required during cooct
except a s Jnternipted by
i'TC t h e Cf-H
mte of
'
\ axis.
the
j'equircmonts of
y-Z phase l e pointed toward
This
Periods of
nor
ratio
ITC o j u r a t i o n e r e I t i l ^ - - ?
contlnucie
f o r a long a t t l t i - d e hold t i n e , t.hs
PTl*.
the 7 aud
••cf
The "nile-oi'''thUaE."
iratlo of
For ehort attitude hold tlnco (l';6e
roll to hold ic
than 15 minutes), tkf
i s 7 to 1«
Attttndff
Eold
5 oin*
Hequlrcd Roll Tine
55
15 laln.
X'.75 h o u r n
30 min.
2.5
3 hrs (esx.)
3.
i t s initial oi*lontation,
if s,pp:-oviBatoly ^20" about
must bo follovcd by 15 hc-sre of
i s that
the
rollLog cictioa ^-onbines with vehicle residual d r i f t
ra'-fto causing the X a r i a ro pi'^cees about
5 to lo
Duri.-.
tho tnm (•20") end a r o l
I t o 2*5 rovolvi Jons ]v?r hour I s coteMlshcd about
precession creating rocotiooe
Z cscs.
periods
itrfo 1 abo-^e.
hoars
15 hrs.
Tine period for navigBtiocal ei^^tiugs i s 36 Bin.
InyolTss one c m .
(g)
10^
�P®rio^> Tor oid-courc? rcrr^^tion involvt>« oil thx-fy crewmea,
includeo ri^noutfcr C/K to dooirM atUhide^ syatea en-up acd
(g)
checkout, firixij; of aj-uv.'> for tillnpc, SPS firing, rci-ifl'-etiou
of doUa V cl'tnlapd (requ'rce contact vUh Wr-FtO^ poot ilrina
eyoteia checkn, 25 oUa.
j"
5
vg)
2.6 6
TXtno poriod for an TKU ocanfle oUgnriCit. £c:ji)onco is IL nlnutos,
6 min'itcs additiorjil for fine .lUEftmrnt, oad ? wlnutos for a finn
allgninont cneck.
lAxnur Or'olf Tn>;"vtJ on
1.
(c)
2o
(g)
The X axis is
appro^rlnvjtoljr pn-allcl to
with -X forrfnrd.
Y cr Z axes.
th? limar local borizorr
'
Ho reotriction ia placed on the direction of •
TiiBO for lunar orbit inj&cticn Jjiclndcc sy-^teoi chorlca.
lOT eoar,
ollgnaeatp IMU fine alignnant. manouver C/H to decirjA alignfflent^
eet-«p lOI navigation pamneters, ullage firing, SFC firing, poo-:
fire syetea checka - 1 hr. 5 oin.
2. 6^7
I.uner Orh: t
1.
Co)
Orbital aav5gr.~iorj.al. iiighcliign wil.l bo requ.ii^d durJ.og rbo first,
two orbits for orbit coaC: nnatlon..
CSM aititudc will fc?
with the
During thin period the general
cad +Z
-X
cxsa jwlateci below the
local horJronfcal plane and the X ax-ls will .'io wlth.iu 6'J® of tha
orbit p.i-.no;.
C
2,
(c)
A Blnlojum of thros cib'tal car
gotio-al s'.ghtlnge (iitiliaiiig IHO
alignment of 'lO a.-lni-tea) will he x*ca«.tred daily.
See itea
ebove for atl.ttUfic3%
3.
Proper ECS oporatioa in Invar >>rbtt la dejj.rndent upon the orien*
(d)
tioo of a plane which b.is'jcts
(c)
and which p^.rnlloi the X ttxia.
.he
CSK
withjn 25" of th:i swbpoir-r po^it
dxrertloa of
i.-.a-
rr .
Devl.a'-.ior froa thia require-
ortilts every two days.
IKIJ aligaiaoiit ."cccasita«ea pli-.eliig the
(c)
i.h.f.e plr.r.? a-;iet; rtmi-
< the r.str.t at vMc!i t-.c
iise intersects the .lun.ar (rjrj".»<-e).
Bent Is aIloj:;ed a n-uciM'.'ni of
+Z/'"f and -Z/+T quadranta
The edge of
vX ax.ia in the general
and wiiatcinirg it witnln
6o*
of the oihit
planelihe -fX axis susfc ^etEa^n at least 35® BJ»cve the IcK^al
hori-zontal.
5,
(g)
Tlae fox in;-tl-al rotry ici o LfJi-fiq'iaLiac CSM c:\d .lor?: prcpsure.;
roQove and etow CH preaeure aid thonsal fcatchear
puTforvi CM
eyotpm checks? diecoaaar t and blow probe and c-4*o.^e, cheek for
Lffl pressure equal!tat loo. op-ri LBl hatch,
tranafer unbiU.cnl
O
6.
<s)
Time for initial
ro
trsnsfer tc
155'. - It. tiiin.
rh-rkc.it
activate and chocjcout •jo-oiunica-'
tlona, control aed v.-^tning sysven, power ayatca, SXiSj ARS,
fanB.^ transfer of PISS and other eei:..'.i:nca! to LEr!?
suit
transfer serond
oan, d-:^ploy landing g?ar, checkout propuliUon r^ystcae? coarss and
fine allgmjcnt of liEM TIPJ. set wp rarisation ia L£K, close up I~;
-- 2
hro, -17 .?5n.
jOfe
�2n6.8 lii'/nv Trrnnfor and Uindtug
lo Tho 1 hour pr.'.or to I£K e^^pnration frao tlin CM, all three CTv^
(«) cc-j;hor3 will be totally' occupied w.Ub
Ration nnd other
ispaceoraft xreparatory aetivitias,
Z . -Kroa lEM cop^ratron to ton-hdo-n, ao o.rperi.montQ will bo porforC' '
Ch) oithoT on-bcard LEM or CM,
•
3# "^he two LEN trrt'vnflQ will have "•erapi.ritfd a ulcep cycle no store thcc
<b) 6 hours prior to start of litoar trr.anfpr.
2..6,9 Lio.ar Surface
1. After landlns,. prallol.nary LSM cecxirtng and checlrout tiote Is 15 eiu.
(g)
2.. Preparation tim? for initial Ivr-ar egress •• -^x^^llne .r>rface,
(g) photograffti, review exploration plans ia light of actual conditions,
check out ond don suits and PLT-S equ^poent., check out cconunlos*
tions, get ocicntlflc oqulpmenl ready - 1 )jr,. 8 oin<c)
Duoo lEH preosuro - 5 oin,
U, Erf.t Lai, get scientific equipaent and 3ow.»r to gro'ind, oliBb dc.'o
(g) loddcT to lunar surface, chock nobility cum iru"fnce coaditions
12 Din.
5. Conduct external inspection of LEW - 5 dn.
(r)
6. Erect and align lunar surface S-band dish aotonna - 20 Bin.
^b-)
7. Climb ladder, transfer equlpfflcit into LW, enter Lra • 2 sin,
(g) 50 sec,
S
8. Repressuzdso LE31 - l8 nin. 50 <ee. (eirgie oysten)
(g)
1 Bin. 20 £«, (both'eyctcr.6)
9. No biological waste shall be disposed on the lunar sarfsce withou
(g) sterilization,
•
10, The LBi is designed so that it con bo left unoccupied with the
(g) cabin unpreaeurlzed on the lurar aorfnce. Etqic-rlment design
should conform, or posnlble eil'ects be properly defined*
#
11, Figure
shows tkf- c-xim* disteaeo for E/A froa the I£K
as a function of the duration cf the EI ertiwily, TlJo ig based
on the amount of oxyger. available to provida purging of ^he SI
ffJit in case of pressure stiit rcvitalizatlon syeteBi failure.
10-1
�2.6,10
T.i;inr
1
r:-.-?
ZVOU8
f-rc.-^jror:.-'. fo-^ J.^-^ach -
L t r -
I
=
xE.
2.
(b)
Tl-.ore uj.li be r.o exi>9rici.iat activity dvwin? L5J1 iunor return,
doekir-s, ="d period throu..^ trausearth a.iiJftCfc:;.on..
JJ.
(g)
Tft't I.TI vfl be "enof.derni the neiive dni^kJn^ "ncaber on th®
roMiru fcr.irtzroua.
.9
2f6«l.l
Trencrifi'-tb T^jrcttoa
1.
(c)
2-
(c)
(c)
k,
(b)
C
5,
(g)
>2i.6vl2
1-
FolloHiPg TI'U alignTBept the +:i lucla in dJ.r<ictod approx^natoly
pnr.illel to rhe local bor-',zont;al prior to jr-Untiog transearth
in.ief.ticr .
Hocharge b:i>-tQrir-3 20 oiontea prior to dooiblt burn • 20 ain.
Prcperat ion iinte for traeooanJi injectioa
3 hrso pr'or to engine ignltlo.
xrill
take approrltcatoJj
-gnd TH/SM $*n^3rn_t loa
98 Trnr'.oluner Coaut '2,6r5'*l)
2e
<c)
Saoe as Tv;jnaluri.nr Coaat ''2.6.''-2)
5..
(c)
Tn addition to tho .-TC ratiulrc.sants of Iterei 2 aboTe, It ia
necoasary to provide pre- re'er.-;ry coolirg j!or the for,<ard heat
3l!i9ld> Tliio is acccaplifihcd by keeping the -X axis cumM
sun-.T-aT^J i/itn,ln ^o lioitg specified for PTf*.
4.
(a, b 8f c)
*
IflU allgr.r.er'j; io tJie aftnc as Innar orbit (2.6-7),
Trrrn'-trth Co<^n
(b & c)
(a
LSTH Jattlrcn orruro prior to
oll^^ncDt ejkI la acooupllahod
With tbf -X axis in the dircctLon of riJgbl. msd Uie *Z arts
pointed tovmrdo the liiv'nr f.urfvjc.
tt
No e.-nJoriccntnl or .•3peri,n.l ope-.-atlooil activity rcoulring crrw
attenticn e.-mll be echcJulcd during the final
hours of the
Ti'arcear'h Coast period dug to the cr.ltioality of «ct«blJ.shlng
a cafe on'-ry corridor, liiui-pueat etownge
bo rooplotGd
during this period.
5.
c)
For CM/EM e rnr^^-e.tioe tho »X s.tis is rotated 60-70® nbovo the
dlrectloo of flight and ti the trs.Jectory plane. The +Z axis
baa s 'zcii.-.iTs prnjcctlcr. ra
np-wr.rd l?c-^l Tartl'r.l.
6.
(a)
The zy^'"-- s-:-arE':i,:: a-i ;;re-sf:7y s.aiavTer r-j>t ce r: ::a-ci
Its less thxn 5 clautas prior to reaeliiSr; ^O.CCO fee' entry
altitude.
i
ICS.
�7. ferforr iPS statu© clieck prior fo CH/SM c^pcratioo (6 mln.) and
.n) © Bain bus status checlt eftar separation nr.d prior to ro-eatrr
(5 nlQ,).
•
8. Check pyro br.ttcriss prior to C.V5M esparstlon (1 ailoO,
(a)
9« Disconnect fuot colla froo CM bnoses orlor to CH/5H aaparatioa
(o) (Icda.),
•
10. Porforra oTatuo check of ClVSCS tvo houro prior to CM/CM aeaaratlo .
(a) (1 Din.),
'
U, Preheat C^/RCS wigine vaivns 10-15 atnutes, to be corjplcte 10 ola'.tca
(n) prior to ri-I/JSi saparaticn-.
2.6 15
Rg'-ertry nrri Piecoy.^ry
1-
CM landing shall be planc^-d no earlier thsn one hour prior to
(A) Eunriae, or later than three bo'.'ra prior to ouacet*
2. The longitude of entry for both the CH and .Ti ojuat bo such that
(a) the GM doon not endanaer any lend raaaes.,
5* Sitry stares vlth the —X axis In the trajectory p32me aod rotatr-'
(c) appro::lnvite3y 26* earTh>fard from local horizontal and vd-th the
*Z nsia pointed avay from earth.
A,
(fi)
E^orin'-dta or data roturned In the CH. mu^t eorvivo a aaxiBua
of two dayo aftor landing.
%
((A
�2.7
op.•^ATTO^?/.L
2 ^ 7 1 gns
1.
(a)
i n vattcr.,;
•'^.^.-•,?(».- J-.o
;<.on." '. C?yr. - ra l"v«
Tne ndiator inifti; toapL>^i-ntnrc r-ua^; ba i*A*3tr.ia:i r.bov® 75®F fo
prevont frcftriiia and b-jl^v
"F to prevoni bnlHua- 1'h«
- folL- ving .nr® operational ••ni?.^of-thuB'a" ron-itrolata. Where
expor. riai raquiremcata roquir-a rioUition .>r these rules, &
d^tai.V-i vhffirmal balnnoe onaljats ohoald ba ci-.ie.
•*
2.7,2
2®7»3
b(a)
The apa-'.-ecraft attltvde ahould not be .-'cr.Btralned In an
ir-crtlai or earth relftive orientation fc-r longer than
3 h-'-G ..
C,
(a)
Eleetrieal loads of loss tlias l68o»l65K3'vatto require periodic
oxpoctira of the radietor to tho sun to picvent freezing,
Routiaa Ovi-Tn tlon.?! Coaatrglnts
SPG prc.p ;llant O'lsi be rsintniiied clove 'tO®F, Alihongh no fixed
rule if poGjiiblo, attitude bo:d? grc^t-er t-uir 3 hours in curatior
without uoLrc incidence on the £»•! aft end should be avoided,
bhoro cxpcrlrtent cctlvitJes exrresd this tiue, ti theroal aaaljalr
should be conducted to check propellant tc«porr.tari?6,
PCS fSM) routine Opcrattooal roGgt;-g.intq
1,.
(a)
2»7«'f'
Tha radiator ourfoc'j'nliould not be ercporad to ao^ar radlatlc.
Incidenrro angles of
for mora thar 20 clautss por orbit
cn vhe n-emge to p.i-event boiling, Jln-:inuB expocurc of theo<'
rnslao tor any one tine ifj one orbit,
Service Pre'M! J'l i c.:t Syin c-n
1.
(a)
C
a,
(a)
/'ny f pe quad of the ECS (SM) ihall not b® pclnted towards deep
cpace for prrlode exceeding 6* "jO hours.
S—IVB Po^itj.re ^'eratipoul^CquKV-raiuj-g
i,
(a)
'Hie S^TVB propellmt tar.k« oatv be veutod parittdlcally, probably
about evnry 'i boors on aa avenig®.
2(a)
The S-1V3 ofabie pJatfora in tha lb has a ::».dd!.e gimbnl restrlfttion of +45® about the X^dxis vehicle yaw at luunch, roll la.
flight.
2.7.5 Ouidence end Jfevigatioo Syntem RovHoe Opftiational Con^t.'rslnta
1.
(a)
O
The S-lb'S stable platform in ii.e 10 has a slddie glsfiai
rectrlctiVon of ^5® about the X-ex<a vehicle ji-w at lauochs
roll in flight,*'
�2 8
Rr,^UIRg!ir.'iTg
2.8.1
1. SPS propolLs^t chctll b* kiiatainod above lift c^rnbutloa
(a) Inatabl'Llt/ iovoi during any d<orbit ironeu^rr,
(OX
Yoot
Iba.).
2 . Contiuuo':a iii'G abort capability will be ea'At-ntalacd.
(o)
3. Tbo nicaloa rhall be aborted a® eoon aa i>038lblc after
(a)- wnoontroliacl lo^3 of cabin prec^urizaltca.
U- SK-KCS dcorbit capability chnll be provided during ary? portica
(a) of near-earth orbital flight.
5« In-fl.''-ght contingency octious eb&ll b© initiated prircarily by
Cg) oanual Rcr-an utilesn cfflorgsncy corditlon rc-iuirestcata ars cuch
that c!.anual opo ation Is incoaelsteat with crew oafety.
C
-
��r-
ATH Sfcr.MHzr.tior ai>:I Ccjcvn1
T ..— . •» t>i.«»-or-«v ^*^..4—-,—^-^-
ui:;hia Coicr>'nc<&8 of huspa cr.pablllty
By Anolyzina crow cfipability to acquire target within 10 oinutea
\j
Dotcrainios crew inputo for autcaiatic operation of the ATM
^
Evaluating ooquencc for cxperlnent cctamanda (tsaxiraum 100 ccxsands)
Selecting control toodeo coopatible with operator capabilitioa
Analysing available ATM target and status presentetioa har(h7are
Selecting diaplsQ' and control coabinotlon which places least demand
on operator skill and endurance
Insuric^ that AiM
to opGrstcr input
2.
c
end LE2I ASS prc'ide near synchronous respcnse
D-Jtucwitie training requlreL^nts to ensuire ma-y<tmrm crew proflciencv t^ith
selected /AM display ajid ccntrol hardware
By Specifying critical tacke required for perfomeace of A'-AI alsoion
Providing course and briefing outlines for crew fcsdUerizatioa
and training
InawiiiS direct ccrrolction between trainer and opcracionoi equipircnt
•T
h
�ATM
1.
r'Mtabll.'.(:y_rnd "roCj.\e
Evaiuat*
haoiualtiiity
By Analysing ovorall usabla volutn.; Avnllabillty
Insuring ATI! peeullcr and crev fiupport equipasnt ecaplles vltb buisaa
enginacring and fllghc snfcty criCaria
Inruring adequacy of Illumination for A1^! display and cnntrol eystems
Entabliahing vrorb cycle conipecible with overall mission requlrcnonts
and Gcailni/Apollo data
2.
Evaluate carrier profile for coirpatibllity vitb ATM oysteas
By Chacking ATM retrievable (EVA) cassette alze against hatch sizec
Evaluating data ensootte maaseo to eisure crew translation capability
Confirroing compatibility between cascettes and carrier otowago provisions
C
Evaluating ATM DJC for cdB^liance with human engineering work station
criteria
Confirming volume allocation and stot-age configuration for special
EVA gear, i.e., maneuvering system, tools, lights, life support
f
O
�Am u:^7^^Ac^^y::a co??57p};p,^Txo^ls
n.^onj'.vof^jr.tfl Fvow ATd
1V\
Ground chsckout of ATH
OrbJ.tnl checkout of All-I
Sonceeraft poAntlnE end trncking prior and durlns experiment
Crev notion reotri.ctlons during tracking
Ara poiutlag end trucking design and techniques
ATH enperlircnft Goqucnclng and control
Tarseto of opportunity (in-flight noprosrninalng)
ATH ocbltcl reactivation (potential rainfccnancc)
Control/dicpley coinpatibllity with LEH/AXM C£-.D
Orbital/baSC-H cosaounicationn and flig^C planning
C
^
f,
E7A
ti'."/, film data retrieval (esasette management)
r^'A crew equipment fcr frequent Bv'A'b (mod^s)
Cr.--.- locc.-nction and tcthsring (hardware)
Cv£!.* rr:tabolAc load (vork cchedulc)
IllualnaCion duriaag EVA
Crew corpartceut pre- during and post- KVA procedures
Crcv; corrpartiMnt EVA coinpacibillty (b&tchcs, O2 supply)
A'.il rc^tctiration and rafurhishmcnt (fcatterlea, Ci-';G'8, etc.)
Crev force aiui morsant impacts on iVlM Instsllation design
Special tools and test equipment.
�
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Saturn V Collection
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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sdsp_skyl_000073
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"Human Factor: ATM/Skylab."
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The "Skylab" in the title was a later addition. This is a summary of the human factor aspects of the Apollo Applications space habitat.
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Martin Marietta Corporation
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1966-09-21
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1965-1970
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Martin Marietta Corporation
Skylab Program
Apollo applications program
Human factors in engineering design
Apollo Telescope Mount
Onboard equipment
Extravehicular mobility units
Life support systems
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Text
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Saturn V Collection
Box 19, Folder 9
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
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en
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Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
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https://digitalprojects.uah.edu/files/original/21/14409/001.pdf
57c118af0b27289322b6f8f251bd3c0e
PDF Text
Text
NASA Contractor Report 3942
Human Performance Issues Arising
From Manned Space Station Missions
William K. Douglas
CONTRACT NAS2-11725
OCTOBER 1986
fVJASA
��SK (.58
NASA Contractor Report 3942
Human Performance Issues Arising
From Manned Space Station Missions
William K. Douglas
McDonnell Douglas Astronautics Company
Huntington Beach, California
Prepared for
Ames Research Center
under Contract NAS2-11723
fUASA
National Aeronautics
and Space Administration
Scientific and Technical
Information Branch
1986
��CONTENTS
SUMMARY
INTRODUCTION
METHOD
MECHANICS
SAFEGUARDING CONFIDENTIALITY
GENERAL FINDINGS
ANSWERS TO PREPARED QUESTIONS
SPONTANEOUS COMMENTS
APPENDIX A
APPENDIX B
��SUMMARY
Ten former NASA astronauts were Interviewed t o provide Information f o r use
In planning f u t u r e space f l i g h t missions.
Although no s t a t i s t i c a l analysis of
t h e material was performed, t h e responses do provide Insight Into numerous
aspects of space f l i g h t . Including psychological aspects, t r a i n i n g , command
s t r u c t u r e , health and comfort, physical aspects, and many o t h e r s .
The
responses by t h e Astronauts t o t h e questions a r e presented together with
coRTients by t h e researcher, himself a physician with long experience with the
space program.
Additionally, spontaneous matters t h a t came up 1n t h e
questioning periods a r e reported upon together with t h e r e s e a r c h e r ' s comments
on t h e s e a s w e l l .
The r e s u l t s , which maintain the s t r i c t c o n f i d e n t i a l i t y of
the Individual respondents, contribute t o t h e basic Information required by
those planning f u t u r e missions In space.
INTRODUCTION
This I s a report of information obtained during t h e course of separate
Interviews with ten former NASA astronauts t h a t took place during t h e f i r s t
half of 1984.
The purpose of t h e Interviews was t o e l i c i t Information t h a t
had not been previously reported and t h a t might open leads f o r f r u i t f u l
research endeavors applicable t o the United S t a t e s Space Station program.
There a r e many reasons why t h i s Information might not have been reported.
I t might have been forgotten during the Astronaut's p o s t - f l i g h t debriefing, o r
he might not have f e l t t h a t i t was Important a t t h a t time.
There may have
been personal reasons why he did not care t o mention some Items.
Some
material may have developed in h i s mind as a r e s u l t of r e f l e c t i o n s since h i s
f l i g h t and of h i s observations of f l i g h t a c t i v i t y t h a t have occurred since h i s
own mission.
Every e f f o r t has been made t o safeguard t h e c o n f i d e n t i a l i t y of t h e
inquiry, a s described in t h e section on c o n f i d e n t i a l i t y .
1
�METHOD
A 11st of fifty-one questions (Appendix A) was formulated by the
Investigator.
Published documents, discussions with NASA personnel, and the
Investigator's own personal knowledge of space f l i g h t human factors entered
Into the formulation of the questions.
Some changes were made In the l i s t of
questions as Insights were gained during the course of the Interviews.
The original thought was that each subject would be asked each question on
the l i s t , but I t soon became apparent that t h i s approach would not be the best
way t o proceed.
Some of the questions clearly referred t o specific programs.
Project ApoUo for example, and would be of l i t t l e use in Interviewing a
person whose experience was restricted t o an e a r l i e r program.
Further, I t was
seen that s t r i c t adherence t o the l i s t of questions would result In s t i l t e d ,
stereotyped replies - the questions became boring rather than stimulating.
After the f i r s t two o r three Interviews, I t was decided t o use the questions
only t o stimulate discussion.
Although some questions were given t o a l l ten
contacts, some were only given t o one or two. with each question being
presented t o an average of 6.2 contacts.
This I s somewhat misleading because
In certain Instances questions would stimulate answers t o l a t e r questions, and
the responses were combined.
(See Question 4)
Ames Research Center provided the Investigator with a l e t t e r of
Introduction (Appendix B), which described the program and I t s goals, and
which reviewed the background of the Investigator. The l e t t e r gave absolute
assurance that the Information given would be safeguarded In such a manner
that no statement could be attributed e i t h e r t o an Individual o r t o his
specific f l i g h t .
The contacts were each paid a consultant's fee of $50.00 per hour.
I t was originally Intended for Mr. Donald K. Slayton t o be present a t each
Interview so as t o take advantage of his background, training, and knowledge
of manned space f l i g h t operations.
I t proved nearly Impossible t o coordinate
the schedules of the Investigator, of Mr. Slayton, and of the contacts.
2
�without delaying the progress of the project to an unacceptable degree; Hr.
Slayton, therefore, was present during only two of the interviews.
The first interviews were with people known personally to the investigator
or to Hr. Slayton (or both).
These individuals made suggestions for
subsequent interviews.
MECHANICS
The contacts were first called by telephone and the purpose of the study
was explained to them.
If they consented to being interviewed (and some
declined because of their busy schedules), an appointment was made, and a copy
of the letter of introduction was mailed to them in sufficient time to allow
them to review it before the interview.
Because of the preconceived opinion of the investigator that the presence
of a tape recorder would be inhibitory to the free flow of information, the
original plan specifically excluded the taping of the interviews.
When the
first individual was contacted, and when it was explained to him that a tape
recorder would not be used, he said he felt the taking of handwritten notes
would be distracting to him.
interview.
He then asked that a recorder be used in his
When subsequent contacts were made, each person was given his
option of using a tape recorder or not.
reluctance to being taped.
None expressed even the slightest
One even asked for a copy of the tape for his
children.
In all cases the investigator traveled to the community where the contact
lived.
The interviews took place in the contact's office on three occasions,
in his home on three occasions, and in the investigator's hotel room on four
occasions.
The environment was very informal.
used only to stimulate discussion.
question was selected and asked.
As stated earlier, the questions were
When the conversation lagged, another
This usually resulted in a great deal more
spontaneous conversation.
3
�SAFEGUARDING CONFIDENTIALITY
Each contact was assured at the time of the initial telephone conversation
that anything he said would not be traceable to him or to his flight.
The
letter of Introduction contained these same assurances, and they were repeated
in the investigator's letter that forwarded the NASA letter of Introduction.
Finally, the subject was given the same assurances orally at the time of the
Interview.
It was apparent that most of them appreciated the assurances of
confidentiality and were probably more open In their discussions as a result
of those assurances.
After each Interview the tapes (12 In all) were brought back to the
Investigator's residence, where they have remained stored In a safe location.
They are identified only with a numerical code number.
does not appear on the cassette label.
material verbatim In most Instances.
The contact's name
The Investigator transcribed the
Paraphrasing was rarely used and then
only when It became necessary to clarify syntax that was peculiar to the oral
Interview situation.
There are a few portions of the tape that have not been
transcribed because they referred to the personal social relationships of the
contact and the Investigator.
The Investigator transcribed a11 the recorded material on an Apple He
personal computer In his home, using the Apple Writer II word processing
program.
No secretarial assistance was used In either transcribing the taped
material or In the preparation of this report.
tapes of these Interviews.
No other person has heard the
To facilitate preparation of this report, the
transcribed Interviews were printed on 104 single-spaced sheets.
than the Investigator has seen these typed pages.
No one other
When not In use. they are
kept In a combination-locked safe In the Investigator's office.
Each transcription Is saved on a magnetic disc, and duplicate discs have
been made and stored separately.
4
�GENERAL FINDINGS
The subjects were, without exception, extremely cooperative.
towards the investigator or the project was expressed.
No animosity
The investigator could
detect no evidence of conscious withholding of information.
A broad range of experienced people were interviewed, including persons
who had flown on all NASA programs, with the exception of the Space Shuttle.
Interviews were conducted with crew members from Mercury, Gemini, Apollo, and
Stcylab.
The Apollo contacts included men who had participated in the
Earth-orbiting phase of the project, and in the lunar landing phase.
One of
these latter contacts landed on the moon and another was a Command Module
Pilot who remained in lunar orbit alone during a lunar landing mission.
No meaningful statistical evaluation can be made for several reasons:
1.
The list of questions was not rigidly adhered to.
All subjects were
not asked all questions.
2.
Answers to questions were subjective in nature.
3.
Many spontaneous questions generated by the subject's comments evolved
on the spot.
interviews.
Some of these were not really applicable to subsequent
On the other hand, some of these spontaneously generated
questions were asked at subsequent interviews, but no effort was made to
contact earlier subjects to ask them to answer the newly generated questions.
4.
Only ten people were interviewed.
In this report the questions will be stated, and in cases where the
question was presented to several individuals, an evaluation of the replies
will be attempted.
Spontaneous statements of importance and answers to spontaneously
generated questions are included at the end of the answers to the list of
fifty-one questions.
NOTE:
After the answers to each question, there is a section labeled
"COMMENTS'.
This section contains the investigator's own subjective remarks
5
�and evaluation of the statements made by the contacts.
A COMMENTS section
w111 be found after each spontaneous comnent as well as after the answers to
the prepared questions.
ANSWERS TO PREPARED QUESTIONS
1.
Opinion of the Crew Health Stabilization Program.
Surprisingly, only 2 of 9 who were asked this question were opposed to the
program.
All stated either spontaneously (5) or upon questioning (2) that
they thought It was helpful In keeping the crews Insulated from annoying
contacts.
•1 thought 1t was kind of fun.
It kept the world away from us."
•It allows the crews to concentrate on what It Is they have to think
about.
flight.
They are not being pulled In a number of directions just before the
It allows them to focus on the task and the training ahead."
CoiMents;
Inasmuch as the Crew Health Stabilization Program is no longer
practiced with as much rigidity as It was In the early Apollo flights, 1t
might be wise to develop some policy for providing a similar degree of privacy
and seclusion for future missions.
2.
Thoughts on Space Station maintenance activities.
NOTE:
Because of the similarity of responses to this question and Question 4
regarding tools, the responses to both questions have been cond>1ned here.
This question was presented to all the contacts.
Two had no comments on
the subject.
One man said that multipurpose tools were Important.
Inclusion of files, wrenches, and other common tools.
Swiss Army knife was especially valuable.
tape with the adhesive on both sides.
He urged the
He stated that his
He also suggested providing sticky
This would be useful In restraining
small parts to the workbench surface when making repairs.
6
�One man commented that the Apo11o tool kit was very good.
Another urged that maintenance should be kept simple - at the 'black box'
level.
One respondent thought that neutral buoyancy training was good practice
for maintenance, but another stated that it was misleading at best.
He urged
that any procedures developed in a neutral buoyancy tank be checked out in the
zero-g aircraft before being adopted for use in space flight.
Only one person mentioned the importance of foot restraints.
One recommendation was to project maintenance instructions, and even
diagrams, on the inside of the helmet visor in the manner of a Head-Up Display
(HUD).
A quotation from one of the contacts might prove interesting:
•You design things for routine maintenance done there by people with tools
in order to keep the system simple, and with simplicity you gain reliability.
You get the reliability through that route rather than through redundancy and
automation."
Comments:
The most significant response to this question is contained in the'
last quotation.
The recent remarkable successes in satellite recovery
operations add emphasis to the quotation.
Future satellites and future Space
Station equipment should be developed with the plan in mind that crew members
are capable of performing routine bench-level maintenance.
3.
Alarm Systems.
This question was presented to seven contacts.
Two of them mentioned that
they noticed a decrease in the loudness of sounds somewhat proportional to the
reduction of pressure in the helmet.
experience.
Another denied that he had had that
Other comnents included the reconmendation that the volume of the
alarm be proportional to the severity of the situation; that for critical
7
�energencles t h e r e should be simultaneous visual and a u d i b l e alarms; and t h a t
audible alarms should be a "warble t o n e ' a s i s used by some European police
cars.
Two individuals mentioned t h e g r e a t importance of e l i m i n a t i n g f a l s e
alarms. One suggested t h a t a study of t h e c h a r a c t e r i s t i c s of f a l s e alarms
might reveal a "signature" f o r f a l s e alarms.
This s i g n a t u r e could be
Incorporated i n t o a computer, and alarms could be evaluated a g a i n s t t h e s e
signatures before being sounded.
Comments:
The suggestion t o i n v e s t i g a t e t h e " s i g n a t u r e s ' of f a l s e alarms
might be worthy of f u r t h e r i n v e s t i g a t i o n .
4.
Tools f o r o n - o r b i t r e p a i r and maintenance.
Inasmuch a s t h i s was covered adequately in Question 2 , r e l a t i n g t o
maintenance a c t i v i t i e s , t h e answers t o t h i s question have been combined with
those obtained i n response t o Question 2 .
Comments;
5.
None.
Food and meals.
Of t h e ten persons Interviewed, one had no cormnent; t h r e e suggested t h a t
meals be s elected from a menu i n - f l i g h t ; and f i v e advised t h a t a l l individuals
e a t t h e same thing a t each meal with no s e l e c t i o n .
Hention was made by these
individuals t h a t t h e m i l i t a r y chow l i n e had much t o reconmend i t . One of the
f i v e suggested t h a t snack Items be provided f o r f r e e s e l e c t i o n from a pantry,
but he s t i l l did not recommend t h a t t h e r e be Item s e l e c t i o n f o r t h e main meals.
One person said he f e l t a menu determined ahead of time by crew interviews
was of l i t t l e value because people lose some of t h e i r a b i l i t y t o t a s t e when in
zero-g.
He a t t r i b u t e d t h i s t o loss of convection c u r r e n t s carrying aromatics
i n t o t h e nose.
He s a i d t h i s could be helped by providing strong condiments -
pepper i n o i l s o l u t i o n , hot mustard, and s o f o r t h .
6
�One contact suggested the Investigation of foil-packaged foods that are
marketed under the brand name of RETORT FOODS.
These are not freeze dried,
and may be eaten hot or cold.
One contact urged that more attention be paid to the nutritional aspects
of the diet.
He distinguished between those aspects of food preparation that
are conventionally performed by a dietician and those performed by a
nutritionist.
He suggested NASA pay more attention to the latter aspects of
menu and diet selection.
Comments;
Those who advocated the military chow-line approach have probably
not seen today's chow line.
In present-day military dining halls, there is a
remarkably broad selection of items available.
One of the contacts suggested
that each crew member be asked about his dislikes rather than his likes.
disliked foods would not be provided in his menu.
The
This seems like a
reasonable approach.
6.
Trash disposal.
This question did not stimulate much discussion in the early interviews so
was eliminated later on.
Two subjects suggested that trash be pyrolized -
convert trash to energy.
Two others who were asked had no comment.
Five were
not asked.
Comments;
7.
None.
Clothing design.
The overwhelming opinion was for a two-piece garment with lots of pockets
(seven out of nine, with two "No Comments").
The advantage of being able to
shed the upper garment for comfort in warm areas was comnented on twice.
All
agreed that many pockets were a necessity, but pocket closure should be with
Velcro rather than with buttons, which could catch on things.
Two unusual
comments included the suggestion that a "dress" uniform be provided for
special occasions- this for morale purposes.
colors and styles was important for morale.
9
Another was that a variety of
One individual stated the need
�for strict dress-code enforcenient as an aid to maintaining discipline.
One
subject stated he had had some experience with polypropylene outdoor clothing
and thought it might be worthwhile investigating.
He said it was quite
comfortable, but brought up the question of its fire resistance.
One suggested a different garment for wear during exercise periods.
One man suggested that two-piece uniforms have some means of fastening the
shirt/jacket to the waist of the trousers to prevent uncomfortable gapping at
that point.
He suggested Velcro.
There was a need expressed for a place to carry an emergency checklist at
all times.
Free choice of underwear was suggested.
One man suggested that slippers be provided for off-duty wear.
Coweents:
As might be expected, there was a wide range of suggestions
regarding clothing.
When some of the more extreme suggestions are eliminated
one reaches the conclusion that the basic in-flight uniform should be a
two-piece garment with many pockets.
The suggestion for the provision of a
place to keep an emergency checklist available at all times is a good one.
B.
Personal hygiene equipment.
Three contacts had no comments, and three were not asked.
The remainder
had comments that did not fit any pattern:
One wanted to use an electric toothbrush and an electric razor.
Another
preferred manual toothbrushes and a blade razor.
One man said that all on board should use whatever turned out to be
'issue' equipment.
He also mentioned that he would insist on daily shaving as
he felt it to be good for mental discipline.
mental set.
10
He felt it establishes a good
�Although not r e a l l y classed a s personal hygiene equipment, one man
commented t h a t showers were important but he f e l t a sponge bath might do a s
well.
Comments;
One might question t h e a d v i s a b i l i t y of providing e l e c t r i c razors,
what with t h e p o s s i b i l i t y of producing "whisker dust" In t h e v i c i n i t y of t h e
face of t h e u s e r .
Since e l e c t r i c razors seem t o be more p r a c t i c a l i n the
Space S t a t i o n environment, i t might be worthwhile t o conduct s t u d i e s on t h e
Shuttle t o determine whether o r not whisker dust r e a l l y i s formed in the
v i c i n i t y of t h e external nares in a zero-g environment.
One might a l s o
perform animal s t u d i e s t o determine whether o r not dust produced from t h a t
animal's own guard h a i r s produced any lung pathology when inhaled on a d a i l y
basis f o r extended periods of time.
9.
Aids t o t r a n s f e r of massive o b j e c t s .
The question was asked of only four people, and two of them had no
comments.
One person s a i d , "Put a loop of rope around i t and snub i t down."
Another suggested t h e use of a "Brooklyn c l o t h e s l i n e " .
loop of rope strung between two p u l l e y s .
l i n e with c l i p s .
This i s a continuous
Objects could be attached t o the
On t h e other hand, another contact mentioned, in response t o
a d i f f e r e n t question, t h a t he had t r i e d such a device in t h e Weightless
Environment Training F a c i l i t y (WETF) and found i t worked very well, but when
he t r i e d i t in t h e zero-g a i r c r a f t i t became tangled t o such an extent as t o
prove u s e l e s s .
Comments:
10.
None.
I d e n t i f i c a t i o n of "Up" and "Down".
Because of t h e s pecial i n t e r e s t of t h i s question, a g r e a t deal of time was
spent on i t .
Of t h e t e n subjects questioned, nine were very d e f i n i t e in
s t a t i n g t h a t t h e r e was no need t o t a k e any p a r t i c u l a r pains t o i d e n t i f y up and
down.
Several commented t h a t down was always where t h e i r f e e t were.
There
appeared t o be no d i f f e r e n c e between t h e answers from individuals who had
flown in confined spacecraft and answers from those who had flown in spacious
11
�vehicles.
One Individual said he himself was not bothered by the lack of up
and down, but stated he f e l t I t would be wise t o ensure t h a t everything In a
given volume have the same orientation.
One contact related that one of his colleagues had spent "hours and hours'
In the simulator, then went Into f l i g h t and became 111 even before he had
gotten out of the s eat . The point of t h i s observation I s t h a t t h i s person had
excellent up and down references but became 111 anyway.
In response t o a direct question, one man said t h a t even seeing his
colleagues In an orientation different from his own did not disturb him.
Two men conmented that the use of a simulator may drive the configuration
of the Space Station, a t least In areas where simulator training 1s
extensive.
The simulator will have t o be constructed with an up and down
orientation because I t I s used In a one-g f i e l d .
The Space Station area must
match the simulator for training If I t I s t o serve any purpose.
The following quotations are presented:
(1)
'Before I came Into the space program I tended t o have a great amount
of familiarity with mathematical techniques of rotation and translation of
axes systems...! tended t o look a t something and j u s t figure t h a t I had a
rotated coordinate system.
(In space) I ' d look out a t the Earth, and I ' d
recognize the Earth had I t s own set of Earth-centered coordinates.
The
spacecraft had I t s space-centered coordinates. Whenever I saw the two In the
same field of view 1 just automatically thought of the spacecraft as being
oriented t o the Earth, but more Importantly, I had my own body-centered
coordinates, and the Input, If somebody allows them t o , can be of those
things. . . . I f you operate 1n egocentric coordinates "down" will be towards
your f e e t .
I t makes no difference whether you're going over the Earth upside
down o r diving under I t , or any of those things, If you really look a t I t as
your world Is where you are, and everything else I s oriented around you."
(2)
One contact said he thought I t fun t o look a t the world upside down.
"Trying t o force a one-gravity mode of operation Into zero-gravity I s a
mistake.
I t defeats a l l of the freedom which you a r e given."
12
�(3)
When he would go from one compartment t o another, one person s a i d ,
•There would be moments of d i s o r i e n t a t i o n and you would kind of f l i p your body
around and you'd pick t h e work s t a t i o n you were going t o work a t , and then a s
soon as you got your body flipped around t o where you were within about 45
degrees of t h a t work s t a t i o n ' s local v e r t i c a l then everything clicked in and
you were comfortable."
(4)
" I think t h a t maybe i f you s t a r t i d e n t i f y i n g up and down you may be
reminding people of t h i n g s they should be f o r g e t t i n g . "
" I think we adapt e a s i l y t o most any environment, but I j u s t d o n ' t think
there i s a g r e a t deal t o be gained by t r y i n g t o force people t o think as they
do here on Earth when they a r e , i n f a c t , in space."
Comments:
If t h e opinions of t h i s small sample of people a r e f e l t t o be
s i g n i f i c a n t one must conclude t h a t special e f f o r t s t o i d e n t i f y "up" and "down"
in Space Station will not pay l a r g e dividends.
The comment t o maintain a
constant local v e r t i c a l i n each module seems worthwhile following, i f i t i s
a r c h i t e c t u r a l l y f e a s i b l e and charges no penalty from a design standpoint.
On t h e other hand, none of t h e ten subjects interviewed admitted t o having
experienced any degree of nausea.
If none of t h e ten contacts became i l l , and
i f approximately 40X of S h u t t l e crew members become i l l , we a r e drawn t o four
possibilities:
(1)
The sample i s s o small t h a t chance alone resulted in my interviewing
only those individuals who did not become i l l .
(2)
There really i s some difference between those interviewed and Shuttle
crew members.
(3)
flight.
The persons interviewed did not admit t h a t they become i l l i n
From t h e obvious s i n c e r i t y and d i r e c t n e s s of t h e s e ten contacts, I am
convinced t h a t none of them became i l l .
This, I must admit, i s a very
subjective assessment, but i t i s my conviction t h a t they were a l l t r u t h f u l and
f o r t h r i g h t in t h e i r answers t o my questions.
This opinion i s substantiated by
t h e f a c t t h a t one individual did admit t h a t he would have become i l l had he
not paced h i s o n - o r b i t a c t i v i t y f o r t h e f i r s t t h r e e o r four days.
This
person's conments a r e found in t h e SPONTANEOUS COMHENTS s e c t i o n , which follows.
13
�(4)
The flight environment of these ten contacts was different from the
Shuttle environment.
I suspect that the reason for the observed difference 1n distribution of
nausea In this group Is a combination of (1) and (4).
11.
Use of vented gases for attitude control.
This was only asked of four contacts.
One remarked that vented gases had
been used as an expediency to control tumbling In Gemini V.
Another had no
coment regarding the use of gases for attitude control, but he did suggest
that they be used to run turbines for power.
One said he did not think It such a good Idea - use control moment gyros
Instead.
Comments:
12.
None.
Importance of private cwnnunlcatlons.
This question was asked of all ten Individuals.
Responses varied from,
'Hot all that Important' to 'Absolutelyl'
Host of the respondents thought a private line was Important for personal
connunlcatlon with families, but of equal Importance was Its use In
operational control of the flight.
One subject gave an example of a situation
In which Instructions had to be paraphrased to keep them from being heard by
the press.
The paraphrased Instruction was misinterpreted to be a Joke and
was not followed.
The example cannot be further Identified or described here
as it would reveal the source, but suffice It to say that the well-being of a
crew member was Jeopardized by this misunderstanding.
One contact said, 'The Administrator [NASA] doesn't have a microphone In
his office with the world listening Into everything he says.
astronauts have the same privilege?'
14
Why can't
�Another s a i d , 'They ( t h e press) have no more r i g h t in your bedroom on
o r b i t than they have in your bedroom on Earth.
They a r e not allowed t o go t o
your doctor and find out how you a r e and what you a r e doing (on Earth so they
d o n ' t have t h a t r i g h t i n s p a c e ) .
Coffinents:
I d o n ' t c a r e who's paying t h e b i l l . "
The respondents' r e p l i e s t o t h i s question were based more on t h e i r
feelings of p r i v i l e g e r a t h e r than on t h e a c t u a l need f o r and u t i l i t y of a
private communications l i n k .
They admitted t h e importance of the r i g h t t o
speak p r i v a t e l y t o t h e i r f a m i l i e s , but they did not seem too concerned with
the beneficial e f f e c t such communications would have on mission
accomplishment.
The comment regarding the u t i l i t y of a p r i v a t e link t o
discuss purely operational matters was s i g n i f i c a n t .
I would l i k e t o point out t h a t during s t r e s s f u l t r a i n i n g exercises during
the Mercury program I had many opportunities t o use t h e private l i n e and found
i t t o be of g r e a t b e n e f i t in assessing the s t a t u s of t h e t r a i n e e .
The
t r a i n e e s more than once made statements a s t o t h e i r physical s t a t u s t o me on
t h e p r i v a t e l i n e t h a t they would not make on t h e open loop.
As an individual,
and not a s t h e i n v e s t i g a t o r i n t h i s study. I would strongly recommend t h a t an
absolutely p r i v a t e communications l i n k be provided.
The "Earth end" of t h e
link would be under t h e control of t h e crew member.
That i s , t h e crew member
would decide who he would t a l k p r i v a t e l y t o , h i s family, t h e f l i g h t
c o n t r o l l e r , t h e physician, o r anyone e l s e .
One of t h e contacts in t h i s
investigation even mentioned t h a t a person spending many weeks o r months in a
Space S t a t i o n might wish t o speak p r i v a t e l y t o h i s broker!
13.
Use of portable f a n s .
Five contacts were asked t h i s question, and none of t h e f i v e ventured an
opinion.
Comments:
14.
The question was not presented t o t h e o t h e r f i v e .
None.
Opinions regarding t r a n s l a t i o n a l a i d s , control/switch p r o t e c t i v e devices,
o r i e n t a t i o n cues, and p r o t e c t i v e gear f o r personal wear.
15
�Five of t h e ten contacts were not asked any p a r t of t h i s q u e s t i o n . Of the
f i v e remaining, only p a r t s were asked, o r only p a r t s were answered.
Four subjects expressed s a t i s f a c t i o n with t h e coninon "wicket-type" switch
guards.
One person s a i d he could not v i s u a l i z e r o l l r a t e s of such a magnitude as
t o require personal p r o t e c t i v e equipment such a s headgear.
He a l s o said
rounded corners and o t h e r methods should be used t o p r o t e c t a person moving
about in t h e cabin.
be required.
Comments;
15.
One o t h e r person s a i d he did not b e l i e v e headgear would
None.
Opinions regarding t h e a i r l o c k on Skylab.
This question was presented t o only t h r e e people, and only one of them had
an opinion.
He s t a t e d , "There should always be a s a f e haven one can g e t t o .
The racetrack design I s good. To have a s a f e haven in each module I s too
c o s t l y , I t takes up t o o much room."
Cocmaents:
16.
None.
Ideas regarding crew q u a r t e r s .
This was addressed by nine out of t h e ten Interviewed.
f e e l t h a t p r i v a t e crew q u a r t e r s were necessary.
very Spartan conditions.
Only two did not
One of t h e s e two advocated
He commented t h a t we c a n ' t a f f o r d t o build a Space
S t a t i o n t o accormodate anybody and everybody.
We must s e l e c t crews t h a t can
t o l e r a t e Spartan l i v i n g conditions f o r ninety days.
they can hang up anywhere."
"Olve them a sleeping bag
The o t h e r one of t h e s e two s a i d he compared a
ninety-day Space S t a t i o n t o u r with an overseas m i l i t a r y t o u r o r a camping
trip.
He s a i d , " I d o n ' t t h i n k you need t o have a p r i v a t e room and a l l t h a t as
long a s you have a place t o s l e e p . "
16
�One of t h e remaining seven who commented s a i d he saw two c o n f l i c t i n g
requirements, one was t h e need f o r q u i e t and privacy, and t h e o t h e r was t h e
need t o be near t h e work s t a t i o n t o respond t o emergencies.
He suggested t h a t
NASA explore t h e p o s s i b i l i t y of providing a "sea cabin" f o r one o r more crew
members.
He a l s o f e l t t h a t any alarms sounded In t h e crew q u a r t e r s should be
p r i o r i t i z e d - perhaps only a " B a t t l e S t a t i o n s ! " type of alarm.
One contact with Skylab experience said he thought t h e crew quarters
should be a t l e a s t twice t h e s i z e of t h e Skylab q u a r t e r s .
He a l s o advised
t h a t they not be located near t h e exercise area t o diminish t h e noise l e v e l s .
One person commented t h a t t h e Apollo s l e e p r e s t r a i n t s were adequate, and
one commented t h a t t h e Skylab s l e e p r e s t r a i n t s were good.
With t h e exception of t h e two "Spartans", everyone believed p r i v a t e ,
individual, comfortable q u a r t e r s should be provided.
Comments:
There seems t o be no question but t h a t p r i v a t e crew quarters should
be provided.
These should be a s large a s I s practicably possible.
It Is
evident t h a t t h e e a r l y Space S t a t i o n w i l l not be large enough t o provide
commodious q u a r t e r s , but I t seems t h a t , given t h e a l t e r n a t i v e s , privacy I s
more t o be desired than volume.
17.
Medical t r a i n i n g f o r crew members.
This question was presented t o e i g h t of t h e ten c o n t a c t s .
The most common
response was t h a t e i t h e r a f l i g h t surgeon be on each crew, o r t h a t two of t h e
crew members should be t r a i n e d t o t h e level of paramedics. One respondent said
he believed a l l crew members should have extensive t r a i n i n g 1n physiology so
t h a t they would b e t t e r understand medical o r physiological problems t h a t arose
In themselves o r In o t h e r s . He a l s o f e l t t h e r e should be a f l i g h t surgeon on
board f o r long-term exposures.
Another f e l t t h a t every crew member should
have t h e equivalent of paramedic t r a i n i n g , and t h a t a physician was not
necessary unless he was dual t r a i n e d - a s a payload s p e c i a l i s t f o r example.
One o t h e r contact suggested t h a t i f a physician were assigned he should be
17
�dual t r a i n e d .
Another contact reconnended t h a t NASA. 1n t h e i r s e l e c t i o n
program f o r mission s p e c i a l i s t s . Include s u f f i c i e n t physicians a s t o provide
one f o r each Space S t a t i o n crew.
Comments:
C l e a r l y , a minimum of two people on each crew must have some
competency 1n providing medical c a r e .
other can take care of him.
If one of t h e s e two becomes 111, the
A good compromise would be f o r one of t h e crew
members t o be a dual-trained ( a s a payload s p e c i a l i s t ) physician and t h e other
a s a dual-trained person with medical t r a i n i n g e q u i v a l e n t t o t h a t of a
paramedic.
18.
Need f o r group dynamics t r a i n i n g .
Group dynamics t r a i n i n g was b r i e f l y described a s a psychological technique
which helps people t o work together and t o give each o t h e r mutual support and
tolerance.
This question was presented t o nine c o n t a c t s .
Only two f e l t no t r a i n i n g
was required, and one f e l t I t should be given only If a problem a r o s e .
stated he had heard t h e Russians had had a problem.
One
One commented a s follows:
*I think t h a t I t ' s going t o be Increasingly important t h a t they have a t
l e a s t some amount of t h i s [group dynamics t r a i n i n g ] because you would l i k e t o
have a preconditioned a t t i t u d e of how t h e y ' r e supposed t o work t o g e t h e r .
You
d o n ' t want t o have some highly motivated mission s c i e n t i s t back t h e r e [ I n the
space lab o r an analogous p a r t of a Space S t a t i o n ] who d o e s n ' t understand
where t h a t p r i o r i t y I n t e r f a c e s with t h e s e o t h e r p r i o r i t i e s . "
Another commented t h a t he f e l t f u t u r e crews, who would not have a s much
I n t e r a c t i v e t r a i n i n g a s those of today, should be required t o function In some
s o r t of environment together before they launch.
He suggested t h a t Survival
School might be useful f o r t h a t purpose.
One contact was e s p e c i a l l y concerned In regard t o t h i s m a t t e r .
His
coenents took up more than a page of single-spaced t y p e s c r i p t , and Included
t h e following statements:
16
�' I think t h a t [ t h e lack of p s y c h i a t r i c o r psychological support] i s one of
the shortcomings of NASA over t h e y e a r s , and I d o n ' t know i f they've solved
t h a t problem yet today, and t h a t i s t h a t t h e r e i s no a c t i v e program having t o
do with t h e behavioral sciences t h a t helps e i t h e r t h e astronauts in dealing
with one another o r t h e a s t r o n a u t s and t h e i r families dealing with t h e
situation."
' I think i t i s unfortunate t h a t astronauts have never been given any kind
of opportunity f o r behavioral science understanding.
There has been such a
stigma associated with psychologic o r p s y c h i a t r i c therapy t h a t everyone stays
away from i t l i k e i t i s some kind of poison."
' I though i t was j u s t r e a l l y too bad t h a t t h e r e was not some s o r t of a
program in NASA t o help i n some s o r t of an upbeat way - t o give them access t o
these people - give them some t r a i n i n g on techniques of dealing with t h e s e
problems.
The problems a r e t h e r e ! "
Another c o n t a c t ' s comments f i l l e d t h r e e single-spaced t y p e s c r i p t pages,
but were mostly personal experiences with h i s f r i e n d s , and cannot be reported
here because of t h e p o s s i b i l i t y of revealing t h e source.
He l e f t no doubt in
t h i s i n t e r v i e w e r ' s mind t h a t he was strongly i n favor of professional
psychological support f o r t h e crews and f o r t h e i r f a m i l i e s .
Comments:
19.
See comments t o Question 1 9 .
Should f a m i l i e s have s i m i l a r psychological support?
This question was posed t o e i g h t of t h e t e n c o n t a c t s .
One had no comment,
two said i t need not be provided, and one s a i d i t should be provided only on a
voluntary b a s i s If t h e family member f e l t t h e need and asked f o r i t .
The r e s t
f e l t i t should be provided In some degree o r another.
A commonly expressed suggestion was t o keep t h e f a m i l i e s very well
informed about a l l a s p e c t s of t h e program, and t o g e t them involved with
whatever i s going on.
One man s a i d , "The more you involve t h e wives i n t o t h e
19
�operation, t h e more support you g e t from them.
Keep them Informed and give
them l i n e s of conmunlcatlon t o , f o r example. Mission Control Center." He also
s a i d , ' I know when I was t h e r e [assigned t o NASA], t h e wives and t h e families
were r e a l l y I s o l a t e d .
They were r e a l l y pushed back In a c o r n e r .
I s , t h a t kind of treatment was I n f e c t i o u s .
The program t r e a t e d t h e wife t h a t
way, and p r e t t y soon we s t a r t e d t r e a t i n g our wives t h e same way.
really tragic."
The problem
" I know I t cost a l o t of guys t h e i r m a r r i a g e . "
I t was
He continued
by saying. 'You c a n ' t t r e a t people l i k e numbers, and t h a t ' s what NASA d i d .
t h e wives were unhappy, w e l l , t h a t ' s t o o bad!
If
'Think of a l l t h i s Important
work t h a t your husband I s doing and go home and s h u t u p ! '
I t d i d n ' t work."
On the other hand, another contact s t a t e d , "The t h i n g s t h a t d o n ' t k i l l you
make you s t r o n g e r .
I , f r a n k l y , think t h e experience was a p o s i t i v e experience
f o r my w i f e . "
He was not one of those In favor of a formal program f o r t h e f a m i l i e s .
Comments:
Because Question 18 and Question 19 a r e s o c l o s e l y r e l a t e d ,
comments t o both of them w i l l be presented h e r e .
For some reason t h e r e seemed
t o be more enthusiasm expressed f o r providing some s o r t of psychological
support f o r t h e crew members than f o r providing s i m i l a r support f o r t h e
families.
I had expected t h e reverse would prove t h e c a s e .
I t would seem
Important t o ensure t h a t f u t u r e Space S t a t i o n crews have t h e opportunity t o
work very c l o s e l y together in s i t u a t i o n s t h a t w i l l r e q u i r e mutual support.
Although I t might be d i f f i c u l t t o j u s t i f y giving survival t r a i n i n g t o Space
Station crews, t h a t s o r t of s o c i a l I n t e r a c t i o n would probably pay large
dividends when t h e crew occupy t h e Space S t a t i o n .
I t might a l s o be of benefit
f o r NASA t o Introduce a c e r t a i n amount of psychological t r a i n i n g I n t o t h e
program.
The contacts, f o r the most p a r t , were not concerned about providing
psychological support f o r t h e f a m i l i e s .
However, t h o s e who were In favor of
such support were very p o s i t i v e In t h e i r s t a t e m e n t s .
My personal f e e l i n g s in
t h i s regard, and many of t h e s e f e e l i n g s have been generated by t h e very strong
�and sincere statements expressed by two of t h e c o n t a c t s , a r e t h a t NASA has
been remiss In not Including t h e f a m i l i e s a s p a r t of t h e program. I t seems
that more d e t a i l e d b r i e f i n g s might be given t h e wives so t h a t they would have
a better Idea of of what t h e i r husbands a r e doing.
This action might not
Improve the effectiveness of t h e husbands, but nevertheless should be provided
if only f o r humanitarian reasons.
The question of r e l i g i o u s b e l i e f s was never presented a s a formal
question, but I t did come up spontaneously In t h e discussions with most of t h e
contacts.
From t h e i r expressions of belief and f a i t h 1 t I s my conclusion t h a t
a resident chaplain a t JSC would be of g r e a t value t o t h e program.
20.
Crew I n t e r a c t i v e t r a i n i n g In a one~g simulator.
Because of t h e many very strong polarized f e e l i n g s brought out by t h e
questions on group dynamics t r a i n i n g (Questions 19 and 20), I t was f e l t t h a t
t h i s question should be eliminated.
misinterpreted i t .
I t was asked of only one contact and he
His answer r e l a t e d t o command s t r u c t u r e of a Space Station
crew, and will be included with t h e answers t o Question 45.
Comments:
21.
None.
Problem of ambient nois e.
Here I s another question t h a t was, f o r a l l I n t e n t s and purposes,
eliminated. The contacts a c t u a l l y answered I t when speaking of t h e need f o r
quiet In p r i v a t e q u a r t e r s .
The question was posed t o t h r e e I n d i v i d u a l s .
One Implied In h i s answer
t h a t noise was not a big problem - one g e t s used t o I t .
On t h e o t h e r hand,
unanticipated noises o r motions of t h e s p a c e c r a f t a r e very d i s t r a c t i n g .
The
third said t h a t on h i s f l i g h t , crew member noise prevented sound sleeping In
shifts.
Comitents:
None.
21
�22.
Wardroom, e n t e r t a i n m e n t , e x t e r n a l v i e w i n g , and E a r t h p o s i t i o n .
All t e n c o n t a c t s a g r e e d t h a t a wardroom was I m p o r t a n t .
There was near-unanimous o p i n i o n t h a t p e r s o n a l l y s e l e c t e d books and music
t a p e s were I m p o r t a n t t h i n g s t o t a k e a l o n g .
Other suggestions Included the
p r o v i s i o n of movies on VCR t a p e s , and one I n d i v i d u a l s u g g e s t e d t h a t books,
movies, and o t h e r forms of a u d i o - v i s u a l e n t e r t a i n m e n t c o u l d be p u t on l a s e r
video d i s c s .
Hany I n d i v i d u a l s commented on t h e f a c t t h a t r e a l - t i m e coimerclal
news progratming and e n t e r t a i n m e n t shows c o u l d be u p - l i n k e d w i t h l i t t l e
difficulty.
Only one person had no s t r o n g o p i n i o n on t h e need f o r windows, b u t even he
s a i d t h e y were h i g h l y d e s i r a b l e , b u t n o t o f prime I m p o r t a n c e .
One person
s a i d , 'Nobody e v e r g e t s enough t i m e l o o k i n g o u t o f w i n d o w s . '
Another s a i d ,
'They should make s u r e t h a t t h e r e a r e a s many windows a s p o s s i b l e . '
He
suggested one be p u t n e a r t h e e x e r c i s e d e v i c e s o one c o u l d l o o k o u t w h i l e
exercising.
One man s a i d t h e windows a r e e x t r e m e l y 1nQ)ortant from a
recreational as well an Inspirational standpoint.
p o r t s and t i m e t o u s e t h e m . '
spacecraft the better.
He s a i d , 'You need viewing
One of t h e c o n t a c t s s a i d , ' T h e more windows In a
One of t h e most e n j o y a b l e t h i n g s you have t o do up
t h e r e 1 s t o look o u t t h e window.
I n f a c t , even a b u b b l e window might be n i c e . *
One of t h e more a r t i c u l a t e c o n t a c t s s a i d :
' I , f o r o n e , am t o t a l l y convinced t h a t t h e magic of s p a c e and t h e v a l u e of
being t h e r e I n v o l v e s being a b l e t o s e e w h a t ' s o u t t h e r e . . . I t 1 s from t h e human
s t a n d p o i n t t h a t I t h i n k you need l o t s of viewing p o r t s .
Important.
I d o n ' t c a r e I f 1 t does c o s t more money.
I t h i n k t h a t ' s very
The r e t u r n I n keeping
p e o p l e ' s I n t e r e s t , and t h e m o t i v a t i o n and a l l t h a t s o r t o f t h i n g , t o d o more
and more, and t o g o f u r t h e r , 1 s v e r y d r a m a t i c a l l y enhanced by b e i n g a b l e t o
see.'
Comments:
The most c o n s i s t e n t answer t o a n y of t h e f i f t y - o n e q u e s t i o n s was
t h e s t r o n g p o s i t i v e e x p r e s s i o n of a need f o r a wardroom w i t h some s o r t of
entertainment equipment.
Individual preferences.
The s u g g e s t i o n s f o r t h i s equipment c l e a r l y followed
Of equal unanimity was t h e e x p r e s s e d need f o r many
22
�and large windows.
This has such g r e a t importance t h a t i t would appear
important t o consider t h e p o s s i b i l i t y of providing bubble windows, a s was
suggested by one of t h e c o n t a c t s .
23.
Body waste c o l l e c t i o n and d i s p o s a l .
Six contacts were asked t h i s question.
Two had no ccHwnents, and two said
they f e l t t h a t t h e Skylab system was adequate, although they did not l i k e t h e
idea of bagging t h e f e c e s .
One man said even t h e Apollo system was a l l r i g h t
in s p i t e of t h e need t o bag t h e f e c e s .
The t h i r d comment related only t o
urine collection and t h a t person said he f e l t t h e ordinary a i r c r a f t , r e l i e f
tube was adequate.
Although he d id not say s o , i t was c l e a r t h a t he meant
such a device would have t o be adapted t o t h e zero-g environment.
Comments:
24.
None.
Personal c l e a n l i n e s s .
Since t h i s question had a l s o been addressed in Question 8 , Personal
Hygiene Equipment, i t was presented t o only f o u r of t h e c o n t a c t s .
Two of them
had no comment; one recommended t h e use of a spring-driven razor; and another,
who uses a blade r a z o r , s a i d he f e l t frequent o r d a i l y shaving was good f o r
crew d i s c i p l i n e .
Conments:
25.
This was t h e second contact t o make t h a t comment.
This was considered in t h e comments t o Question 8 .
Exercise.
This question was asked of nine c o n t a c t s .
important.
All agreed t h a t exercise was
One s a i d he f e l t e x e r c i s e and good food were t h e two most
in^ortant things t o provide f o r long-duration space f l i g h t .
Two others said
they f e l t e x e r c i s e was important from a psychological and morale standpoint a s
well as from a physical well-being point of view.
Five people recommended t h a t both a bicycle ergometer and a treadmill be
provided.
One mentioned only a treadmill and one mentioned only a bicycle.
a
�Two people mentioned that it Is also necessary to exercise the upper torso
and arms.
One of these recoimiended spring or bungee devices for this
purpose.
Another thought a Nautilus-type of exercise device should be
provided.
One person said he thought the Cxergenle was a very useful device, but
another stated that he tried to use it on his flight and found that the nylon
ropes heated from the friction of use and stretched, making the device useless.
Another person said he believed there is a need for something that will
provide structural stress to the skeletal system, but he had no ideas on how
to do that.
Only two people suggested a duration for the exercise period.
One
suggested ninety minutes and the other sixty minutes.
Coniwents;
The need for exercise was strongly supported by all.
It Is my
understanding that investigations into the types of exercise equipment needed
are being conducted.
I can only urge that these Investigations be continued
both on the ground and In flight.
2b.
How to manage books and manuals.
This question was presented to only four of the ten contacts.
One stated
he preferred books, but could learn to live with Information presented on
CRTs.
One contact had no comments, and the other two said that they did not
think that everything had to be In data banks.
Some material can best be
presented in book form, and other material can be stored In data banks for
retrieval when needed.
The feeling seemed to be that recreational material was best presented In
book form, but technical material (with the exception of emergency checklists)
could be stored In data banks.
Cowaents:
None.
24
�27.
Han/machine interface.
This question was put to five of the ten contacts.
One suggested that color be used more in the design of the Space Station,
and one said color was not a11 that important.
One had no comment.
One man suggested that NASA employ what he called "functional artists" to
help in designing the interior of the Space Station.
He stated that the
wardroom should be of a "relaxing* color and the flight deck should be of an
"alerting" color.
One individual urged caution in accepting the use of digital displays.
He
said:
"Digital offers various advantages in terms of accuracy, precision when
you need precision, but the human being is an integrator, he doesn't take
snapshots, and there is a lot of information and intelligence lost when you're
looking at a digital display."
Comments:
The science of architecture is advancing at a great pace.
NASA
would be well advised to use the services of this discipline in establishing
interior design criteria for the Space Station.
I was impressed by the warning about digital displays.
From a purely
personal standpoint I find it easier to integrate analog informational
displays than I do digital displays, but this may be purely cultural.
An
interesting area for investigation would be to assess whether people get more
or less information from one display than the other.
Unquestionably, it is
easier and quicker to read, for example, the exact time from a digital
display, but does one find it also easier to tell how many minutes have
elapsed since a given event or how much time remains before a given action
must be taken. I am sure similar analyses could be made of altimeters, and
other displays of changing quantifiable information.
25
�2B.
Three s h i f t s o r one?
This question was asked of s i x people.
One had no connient.
Only one of
t h e remaining f i v e f e l t t h a t a l l crew members should be allowed t o s l e e p a t
t h e same time.
times.
They f e l t t h a t someone should be awake and on watch a t a l l
One man s a i d t h a t t h e crews should be a b l e t o work longer than
eight-hour s h i f t s .
He s a i d , 'You're not t h e r e on a v a c a t i o n , even f o r three
months.'
One contact s t a t e d t h a t timelines should be f l e x i b l e enough t o accomnodate
t h e mission, and t h e crew members should be i n d o c t r i n a t e d in t h e occasional
need f o r working on t h e i r off-duty time.
For exati^le, an Earth resources task
night require t h a t t h e Earth resources s p e c i a l i s t t a k e photos a t a p a r t i c u l a r
time on a p a r t i c u l a r o r b i t , and t h a t might occur during h i s o f f - d u t y time.
This question a l s o asked t h e contact t o comment on whether e x e r c i s e should
be an off-duty endeavor o r a duty-time a c t i v i t y .
obtained.
Only t h r e e answers were
One man said exercise should be done during o f f - d u t y hours.
The
second said t h e question was i r r e l e v a n t because one i s never ' o f f d u t y ' In
space.
The t h i r d said he thought half of t h e e x e r c i s e should be done during
on-duty time and half of i t when off d u t y .
Comments:
As was t h e case i n most of t h e s e q u e s t i o n s , t h e r e was no r eal
unanimity of opinion unless i t was t h a t someone should be awake a t a l l times.
This seems t o be a most reasonable and l o g i c a l p o s i t i o n .
29.
Importance of real-time TV.
Here i s another example of a question t h a t was covered f a i r l y well i n an
e a r l i e r question.
See Question 22. which addresses wardroom accommodations.
This question (29) was asked of only t h r e e persons.
One had no comment:
one thought i t was very important; and t h e o t h e r did not b e l i e v e i t t o be of
g r e a t importance.
Comments:
None.
�30.
Who should s e l e c t t h e crews?
All but t h r e e of t h e contacts were asked t h i s question and, a s one might
expect, t h e r e was a wide range of opinion i n t h i s regard.
person a r e summarized in t h e following paragraphs.
(1)
A crew s e l e c t i o n committee has v i r t u e .
made by one person.
The r e p l i e s of each
No r e a l p a t t e r n emerged.
The s e l e c t i o n should not be
Perhaps t h e Captain should be s e l e c t e d f i r s t .
He would
then s e l e c t a second person; t h e two of them would s e l e c t t h e t h i r d ; and s o on
until a l l crew members had been chosen.
(2)
Overall Management should make t h e s e l e c t i o n .
The Commander should
not have s o l e s e l e c t i o n a u t h o r i t y , but he should have veto powers.
The peer
review concept has v i r t u e i n t h a t i t i d e n t i f i e s t h e unpopular individuals.
(3)
The crew should be s e l e c t e d by Management - they have more
information a v a i l a b l e t o them than does anyone e l s e .
i s a useful t o o l .
The peer review process
Management needs an input from t h e crew Commander.
This
contact believed t h a t a small group of crews should be selected and flown
frequently.
This saves expensive t r a i n i n g time over t h e o t h e r a l t e r n a t i v e ,
which i s t o have a l a r g e pool of candidates from which crews a r e selected t o
fly less fre q uently.
(4)
Believes a nucleus of crew members should be s e l e c t e d .
These people
fly frequently and t r a i n t h e i r own replacements ( t h e r i g h t - s e a t man eventually
moves i n t o a l e f t - s e a t assignment).
Whatever system i s used, i t should be
well understood by a l l t h e candidates.
Each should know what the s e l e c t i o n
c r i t e r i a a r e , and how t h e process o p e r a t e s .
(5)
Mentioned t h a t he l i k e d t h e way Slayton handled t h e s e l e c t i o n
process, but believes t h e s e l e c t i o n pool i s much too l a r g e .
(6)
Also mentioned t h a t he liked t h e way Slayton did h i s job i n t h e p a s t .
(7)
NASA management should s e l e c t t h e operational crew.
authority should s e l e c t t h e t e c h n i c a l crew.
Some o t h e r
The combined group should work
together f o r a period of time, and t h e Commander should be a b l e t o e x e r c i s e
veto power over members of both groups i f he f e l t an individual would not f i t
in.
Conments:
I am i n c l i n e d t o go along with respondent Number 3 .
Number 7 made e s s e n t i a l l y t h e same comments.
27
Respondent
My disagreement with Number 3 i s
�only i n regard t o t h e concept of peer review.
I an s u r e i t does point out the
unpopular i n d i v i d u a l s , a s s t a t e d by c o n t a c t Number 2 , but a t what expense?
I
am s u r e t h e unpopular individual i s already known by Management by t h e time
they g e t around t o s e l e c t i n g t h e crews.
One i s i n c l i n e d t o ask how important
i s popularity anyway?
31.
Does EVA require t h e 'buddy system"?
Only four people were asked t h i s question.
One had no conntent, and the
other t h r e e said they believed i t was necessary.
One of them s a i d he thought
the buddy might be a f u l l y s u i t e d a s t r o n a u t who remained i n s i d e t h e s t a t i o n ,
but was ready t o go outside a t a moment's n o t i c e .
None said they though t h e buddy system was unnecessary.
Comments:
32.
None.
How can t h e EVA s u i t be in^troved?
This question was asked of seven people.
Again, t h e comments were not
c o n s i s t e n t , and r e f l e c t t h e i n d i v i d u a l ' s personal views.
There i s a l s o some
overlap in t h e answers with t h e answers t o some of t h e o t h e r q u e s t i o n s .
(1)
For prolonged EVA t h e astronaut should be provided with a 'motorman's
f r i e n d * , a d i a p e r , water, but no food.
(2)
For missions t h a t w i l l require EVA soon a f t e r a t t a i n i n g o r b i t , t h e
EVA crewman should be s elected from a pool of i n d i v i d u a l s who, by t h e i r past
experience in o r b i t , have shown t o be r e s i s t a n t t o space motion s i c k n e s s .
Nevertheless, vomitus containment apparatus should be provided ' j u s t in case.*
(3)
Consider using honey water a s a source of energy and f l u i d .
glove needs improvement s o a s t o provide b e t t e r t a c t i l e s e n s a t i o n .
The
A wire saw
(Gigli saw) should be taken along on every EVA f o r emergency u s e .
(4)
Mentions b e t t e r gloves with improved t a c t i l e s e n s a t i o n .
(5) Suggests t h a t t h e problem of f i n g e r t i p i n j u r y could be solved by
c l o s e r trimming of t h e f i n g e r n a i l s .
(6)
Recommends t h e hard, r i g i d , high-pressure ( 8 p s i ) s u i t .
(7)
One man had no comments.
28
�Cownents:
The suggestion t o use honey water a s a source of nourishment and of
fluids c e r t a i n l y deserves i n v e s t i g a t i o n .
Methods f o r c o l l e c t i n g urine and
feces (a diaper should be adequate f o r emergencies) a r e e s s e n t i a l , and I
believe t h a t some s o r t of vomitus containment device i s a l s o e s s e n t i a l .
People s t i l l become i l l , even on t h e s u r f a c e of t h e Earth in a one-g f i e l d ,
^
and there i s no reason t o suspect t h i n g s w i l l d i f f e r i n space.
^
problem comes up with t h e food s t o r a g e equipment, t h e r e might well be some
gastroenteric I l l n e s s e s developing.
In f a c t , i f a
F i n a l l y , i t seems logical t o develop a
suit t h a t provides a t l e a s t 8 - p s i p r e s s u r e , more If f e a s i b l e .
The advantages
to such a garment a r e t o o well known t o warrant elaboration in t h i s r e p o r t .
33.
EVA r e s t r a i n t s , t e t h e r s , hand holds, l i g h t s , e t c .
After receiving t h r e e "no comments" i n a row, t h i s question was
eliminated.
I t was asked of f o u r c o n t a c t s and only one had any comments.
His
are as follows:
"There i s a need f o r a s m a l l , multipurpose t o o l k i t with interchangeable
end-effectors.
Small l i g h t s on t h e f i n g e r t i p s a s were used in the Mercury
program a r e extremely u s e f u l .
These can be d i r e c t e d b e t t e r than a
helmet-mounted l i g h t . "
Comments;
effective.
34.
The use of f i n g e r t i p l i g h t s on t h e Mercury s u i t was most
This might be i n v e s t i g a t e d again f o r t h e Space S t a t i o n s u i t .
Suggestions regarding mortuary a f f a i r s .
This question was posed t o f o u r of t h e persons interviewed.
Two s t a t e d
that the sensible t h i n g t o do would be some form of o n - o r b i t d i s p o s a l .
said, in some s e r i o u s n e s s , "Shoot me i n t o t h e Sun!"
(One
He was aware of t h e
high-energy c o s t of doing t h i s , s o t h e r e was some l e v i t y i n t h e remark t o o . )
6ut they a l s o recognize t h a t t h i s would not be acceptable in today' s s o c i e t y .
I
^
One of t h e contacts s a i d t h e problem should be addressed and solved before
we go t o Space S t a t i o n , but he had no i d e a s .
The f o u r t h person agreed with
the necessity t o bring t h e body back i n a condition s u i t a b l e f o r an
open-casket f u n e r a l , but he had no ideas on how t h i s could be accon4)lished.
29
�Conroents;
One approach t o mortuary ser vices might be t o c o n s u l t with various
museums of natural h i s t o r y .
One of t h e modern methods of taxidermy i s t o
place the animal In a l i f e - l i k e pose and f r e e z e I t in t h a t p o s i t i o n .
A vacuum
i s then drawn on t h e container, and t h e animal i s c o n p l e t e l y d e s i c c a t e d . The
desiccated specimen i s then placed in a sealed c a s e .
This technique could be
adapted t o t h e Space S t a t i o n as a method of preserving t h e body of a deceased
crew member u n t i l a r e l i e f vessel makes c o n t a c t .
35.
Foot r e s t r a i n t s a t t h e work s t a t i o n .
This question was given t o four s u b j e c t s .
Three had no comments, and one
s t a t e d t h e t r i a n g u l a r shoes used in Skylab worked f i n e .
Topics explored in t h i s question were a l s o addressed i n Questions 33 and
36.
Comments:
36.
None.
Locomotion a i d s .
Only two s u b j e c t s were asked t h i s question.
One had no comments, and the
other s a i d , 'Only what i s needed f o r f a c i l i t y and s a f e t y .
The best locomotion
i s j u s t t o head out and across!*
Co—mnts:
37.
None.
Body r e s t r a i n t s f o r t a s k s requiring extreme s t e a d i n e s s .
This question was presented t o only t h r e e s u b j e c t s .
Two f e l t i t t o be no
problem, and one s t a t e d t h a t perhaps a r i g i d arm could be i n s t a l l e d a t t h e
work s t a t i o n .
This could be swung out from a stowed p o s i t i o n and used t o
clamp t h e a s t r o n a u t i n t o p o s i t i o n .
Comments:
None.
30
�38.
Thoughts on a r t i f i c i a l g r a v i t y .
This topic was discussed with nine c o n t a c t s .
make.
Two had no connients t o
One s t a t e d c a t e g o r i c a l l y t h a t he thought t h e r e i s a d i s t i n c t medical
need for a r t i f i c i a l g r a v i t y .
Three were of t h e opinion t h a t a r t i f i c i a l
gravity should not be considered unless an overwhelming physiological need
developed.
One expressed t h e opinion t h a t when t h e time comes when we can
build very-long-term-exposure f a c i l i t i e s , a r t i f i c i a l g r a v i t y should be
provided because t h e time expended in e x e r c i s e (he estimated one t o one and a
half hours a day.) a r e nonproductive hours which could be put t o b e t t e r use i f
a r t i f i c i a l g r a v i t y were provided.
No respondent f e l t a r t i f i c i a l g r a v i t y i s required f o r psychological
reasons.
One was very s t r o n g l y opposed t o i t .
Our conversation went a s follows:
'Another thing - I wouldn't worry about a r t i f i c i a l g r a v i t y .
i s considering a r t i f i c i a l g r a v i t y any more.
I hope nobody
I t h i n k t h a t ' s a waste of time.
And you destroy many of t h e advantages you gain by being weightless.
Particularly f o r those people who may have a g r a v i t a t i o n a l handicap.
don't have a g r a v i t a t i o n a l handicap in space.
They
They ought t o be permitted t o
participate a s f u l l - f l e d g e d workers and crew members i n space.
0.
There i s some consideration being given t o t h e so-called t e t h e r
system, which w i l l provide a r t i f i c i a l g r a v i t y .
A.
Well, I ' l l t e l l you - I t h i n k t h a t ' s a waste of money, a waste of
manpower and i n t e l l e c t s t o even worry about i t .
have a good reason t o do i t .
F i f t y years from now you may
I d o n ' t t h i n k you have a good reason now.
Certainly calcium loss i s not a j u s t i f i c a t i o n , i n my o p i n i o n . "
One person f e l t t h a t t h e r e was a need f o r an a r t i f i c i a l g r a v i t y area in
the Space S t a t i o n , but he had no ideas a s t o how t h i s could be accomplished.
He said:
31
�•There are some good benefits from zero-g, but I would hope that in the
Space Station there would be some area or some volume of the Space Station
that would have artificial gravity. I don't know whether it should be the
gravity of Earth or the gravity of the moon, but some light gravity field
would prevent the deterioration, the decondltioning, of the cardiovascular
system, and also the sickness that comes Initially with exposure to the
weightless environment.'
Comments:
I am in agreement with the contact who stated that the provision of
artificial gravity negates one of the more Important reasons for being there.
Of course, it Is self-evident that If an overwhelming medical or physiological
need arises for artificial gravity. It must be provided, but lacking that, I
can see no justification for It.
The concept that the provision of artificial
gravity would eliminate the need for exercise and thus be an economically
justifiable approach warrants study.
The economics of this question Is beyond
my area of knowledge, so I do not feel competent to coiment one way or another
on the suggestion.
39.
What about autonomy?
This question was presented to eight contacts, and all but one had very
definite opinions on the subject.
Four contacts stated that they believed the
Space Station Commander should be the final authority.
ground should perform strategic planning only,
Four felt that the
other comaents included one
that the Control Center should be used only for their more extensive
resources.
Two others stated that Hisslon Control Center should be used for
routine data analysis only, and this because 1t was more economical to do this
kind of Information processing on the ground than in the Space Station.
Another connent was that the Control Center should be informative, not
protective, and finally, one person commented that the Control Center should
be absolutely honest with the flight crew; no information should be withheld
from the crew using the Justification that they were being protected by this
action. This respondent also said that the crew must be open and honest with
the ground as well.
32
�Conments;
All of t h e contacts were i n c l i n e d towards more autonomy f o r the
Space Station, and l e s s r e l i a n c e on t h e ground.
logical and a p p r o p r i a t e .
This trend seems t o be most
I concur with t h e conment t h a t t h e g r e a t e r
analytical resources on t h e ground should be used in preference t o i n - f l i g h t
analysis.
40.
U t i l i t y of a miniature helmet-mounted TV camera.
This question was presented t o only two c o n t a c t s .
useful, but only f o r c e r t a i n (unspecified) t a s k s .
One said i t might be
The o t h e r contact had no
connents t o make on t h e s u b j e c t .
Conntents:
41.
None.
What about an expendable launch vehicle rescue c a p a b i l i t y .
The question was put t o f i v e people, of which one had no comment.
Only
one person was e n t h u s i a s t i c about t h e concept and he s a i d :
"I d o n ' t s e e why n o t .
I t would be expensive, but i t would be only a
one-time expense. Once you got t h e t h i n g ready t o go, t h e expense of recycling
i t would not be t h a t g r e a t .
You could even go with a s o l i d .
have t o be reserviced a s o f t e n .
I t would not
Over a period of years t h e r e ' s going t o be
some times when i t j u s t might be needed, and i t would c e r t a i n l y pay f o r
itself.'
One said he would r a t h e r put t h e emphasis on more on-board r e l i a b i l i t y .
Another said he would r a t h e r use t h o s e resources t o expand t h e o r b l t e r f l e e t
so as t o provide a quick-rescue c a p a b i l i t y .
One individual said he would
rather have t h e escape c a p a b i l i t y b u i l t i n t o t h e Space S t a t i o n i t s e l f .
Comments:
42.
None.
How can man-on-board reduce redundancy?
This question was presented t o only f o u r c o n t a c t s .
that they had no comments.
33
Three of them said
�One s t a t e d he did not want t o g e t Involved 1n a lengthy discussion of the
question, but did want t o venture h i s opinion t h a t we a r e s t i l l designing too
much redundancy I n t o experiments because t h e s c i e n t i s t s r e f u s e t o accept t h a t
man can make up f o r i t .
Cowwents;
The comments following Question 2 point out t h e u t i l i t a r i a n value
of man on t h e scene.
Again, we should design equipment f o r r e p a i r and
maintenance on o r b i t r a t h e r than provide layer s of redundancy.
A3.
Ideas f o r design of a safe haven.
This question was put t o seven people.
Two of them had no comments.
One
s t a t e d t h a t he did not think we needed more than two s a f e havens on t h e Space
S t a t i o n ; another man said he thought every module should be I s o l a t a b l e ; and a
t h i r d suggested designing t h e s a f e haven s o t h a t t h e occupants could continue
t o be productive.
He f e l t t h i s was e s s e n t i a l t o t h e i r morale.
One contact s t a t e d , " I would put my e f f o r t s I n t o Introducing realism t o
t h e public."
When asked t o explain t h e statement he s a i d t h a t we must prepare
the public t o accept the f a c t t h a t we're going t o lose a s p a c e c r a f t sometime.
pomnents:
The suggestion t o provide means f o r crews t o remain productive as a
morale booster In t h e s a f e haven I s one t h a t deserves some thought.
44.
Philosophy f o r EVA use.
Of t h e f i v e people who were presented with t h i s q u e s t i o n , one had no
comment; two f e l t t h a t I t should be used r o u t i n e l y ; one s a i d I t should be used
when c o s t e f f e c t i v e ; and one s t a t e d only, " I am s u r e i t would be u s e f u l . "
Conmmnts:
45.
None.
On-board command s t r u c t u r e .
This question probably stimulated a s much discussion a s any of t h e 51.
was presented t o a l l ten c o n t a c t s .
Six of them unequivocally recomaended a
strong Commander with a c l e a r and d i s t i n c t chain of conmend.
p o s i t i v e voice In t h i s group was one who s a i d :
34
The most
It
�•The Commander 1s the boss—just like 1n a military vehicle [or] In polar
exploration trips.
He's the boss.
varied opinions on things.
He can appoint deputies.
He's a real strong individual.
'This is the way it's donel [Strikes table for emphasis.].
He can ask for
He's going to say,
We're not even
going to question it.'"
A considerably milder comment was made by another contact who said that a
clear chain of command was needed but, "...you don't need a man beating his
chest."
The nearly opposite view was expressed by a contact who said:
"Yog know the stereotype of Marine Drill Instructor - you don't need those
kinds of abilities up there - you need people with a broad perspective; people
who are interested in enough different things outside their own area of
expertise. I think that would be especially apropos of the Commander of the
mission."
He went on to say, "When you go to autonomy in space and you have
your scientists up there [there are going to be conflicts which the Commander
will have to solve].
You have to be able to compromise, and accommodate all
those kinds of things.
The Commander will have to be real diplomat."
Another contact recommended a strong authoritative Commander, but he has
to be the kind of person who knows how to lead, and "...just to give an order
is not the best way to lead."
But, he said, there also has to be a strong
connand structure.
One man who stated there must be a chain of command suggested that there
night possibly be a Commander for each shift with interaction between them.
He said that the Commander should be not be resistant or blind to suggestion
and inputs from the rest of the crew.
When asked if he would recommend a
military hierarchial system, he replied that he would prefer a NASA
hierarchial system, which he said is not as rigid as the military system.
Another contact also recommended a dual command system, but constructed
around different lines.
He suggested a military Commander and a scientific
35
�conmander.
The military Conroander would be in ultimate charge, but as long as
things are going well, he would delegate command to the chief scientist.
He
agreed tha,t this might be somewhat analogous to the relationship that exists
between the Captain of a carrier and his Air Sroup Commander.
The contact
stated that the ultimate responsibility must be assigned to one person.
said, 'You cannot have a voting situation up there."
NOTE:
He
The term "Hilltary Commander" as used above was not meant by the
speaker to imply that he advocated the Space Station be conuianded by a DOD
representative.
Conments:
He used it as a figure of speech.
Most of the respondents focused on the role that the Conmander must
play, and how he must act in exercising that role.
One contact really caught
the significant part of the question and stated that even more important than
the Commander's actions was the need for a strong comaand structure.
It has
been my observation that some Military Commanders get the job done by virtue
of the fact that their subordinates are afraid of them; others because they
are respected:and others because they are idolized.
Regardless of the
Commander's attitude, the job always gets done unless the conmand structure
breaks down.
Even the autocratic Commander gets the job done unless he
attempts to dissolve the command structure.
When he does that, the
organization falls apart and the mission is a failure.
46.
How Hi-Fi should the Space Station simulator be?
This question was given to five people.
Only one recownended that the
simulator have as much fidelity as possible recognizing the limits imposed by
gravity.
Two men felt that a complete simulator, a duplicate Space Station, was not
needed.
Part-task and modular simulation should be adequate.
These were
thought to be especially valuable devices for problem solving.
one man suggested that the Space Station control room should be fairly
well simulated, but the other functions of a Space Station need not be
36
�duplicated on the ground.
He suggested a minimum ground training period and
conpletion of training In the Space Station itself under the supervision of
the crew.
He presupposed that only part of the crew, perhaps two out of ten,
would be replaced at any one time.
One man had no comments.
Conments:
The suggestion that part-task and modular simulations should be
adequate seems to be a reasonable approach.
The concept of training after
arriving on station is an interesting one and might be an area for
investigation.
49.
Accommodating diverse groups of people.
Seven people were asked this question.
Two people expressed disapproval
of the concept of taking the "man on the street".
Both of these contacts felt
that, in the foreseeable future, we would be taking selected people.
One
mentioned that we would select them first for their skills, second for their
motivation, and third for their physical and mental health.
mentioned construction workers.
One contact
He thought we would ask for volunteers from
the population of construction workers, then we would select the most skilled
and the most fit.
Three contacts mentioned their opposition to the practice of applying
arbitary age limits.
They felt that the results of a physical examination
should determine a person's fitness to fly, not his age.
One mentioned a Dr.
Vincent in Houston who has a program that is an excellent predictor of mental
acuity.
The respondent thought some of the airlines were using Or. Vincent's
technique.
One stated that we could markedly relax our physical requirements because
there are no stresses in space.
Another felt that most of the problems will be societal, and the Commander
will have to deal with them.
37
�Another suggestion was t h a t planning f o r medical c a r e f a c i l i t i e s must take
Into consideration t h a t crew members of t h e f u t u r e may n o t be 1n t h e b e s t of
health o r of optimum age.
Comments;
I was pleased t o hear one of t h e contacts s t a t e t h a t we could
markedly relax our physical requirements because t h e r e a r e no s t r e s s e s In
space.
I do not know. In any g r e a t d e t a i l , what physical l i m i t a t i o n s NASA
places on s e l e c t e e s f o r space f l i g h t , but senators and school t e a c h e r s a r e now
being considered.
From a purely s c i e n t i f i c standpoint 1 t seems reasonable t o
f l y a group of "average" people t o see whether they perform any d i f f e r e n t l y
than the highly selected and superbly f i t persons we have flown In t h e p a s t .
There was r e a l l y no reason f o r s e l e c t i n g t h e cream of t h e crop a f t e r Mercury
and Gemini.
Both of those e a r l y missions had t h e unknown p o s s i b i l i t y of
requiring t h e a b i l i t y t o s u s t a i n hIgh-Q reentry followed by a survival
experience l a s t i n g several days a t sea o r on t h e d e s e r t .
e x t r a o r d i n a r i l y f i t human specimen was required.
Obviously an
We might be surprised t o
find out t h a t the average person who I s accustomed t o a more sedentary l i f e
might even perform I n t e l l e c t u a l t a s k s In space a t l e a s t a s well a s t h e more
f i t person does.
I have not followed up on t h e suggestion t h a t Or. Vincent In Houston be
contacted because of h i s a b i l i t y t o p r e d i c t mental a c u i t y s e p a r a t e from age.
50.
Thoughts regarding s a f e t y hazards.
This question was presented t o nine c o n t a c t s .
nothing t o c o n t r i b u t e .
One said t h e only thing he could t h i n k of was a k i t t o
s e a l meteorold punctures.
redundancy a s p o s s i b l e .
Three s t a t e d t h a t they had
Another suggested only t h a t we build In a s much
One person said t h a t a s i d e from t h e pure vacuum of
space, living In t h e Space Station I s no d i f f e r e n t , from a s a f e t y point of
view, than l i v i n g on Earth.
The hazards a r e t h e same and you p r o t e c t against
them with s t r u c t u r a l design. You c a n ' t p r o t e c t a g a i n s t a l l e v e n t u a l i t i e s .
f e l t compartmentallzatlon w i l l solve many problems.
38
He
�Another person made t h e s e f i v e p o i n t s :
1.
Follow e s t a b l i s h e d p r o c e d u r e s .
2.
Have two c u e s t o a p r o b l e m , i . e . , a u d i o and v i s u a l warnings i n
case one o r t h e o t h e r i s m i s s e d .
3.
Eliminate single-point failures.
He s a i d NASA has done a v e ry
?oo(l job of doing t h a t .
4.
When a f a i l u r e d o e s o c c u r , f a l l back t o a s a f e p o s i t i o n
iimediately, and examine t h e f a i l u r e .
5.
Use e x t r a o r d i n a r i l y w e l l - t r a i n e d p e o p l e i n p o s i t i o n s of p r i n c i p a l
responsibility.
One respondent urged t h a t NASA d o c a r e f u l f a i l u r e mode a n a l y s e s , and where
they discover h a z a r d s t h a t t h e crew w i l l have t o l i v e w i t h , t h e n make s u r e t h e
crew i s well t r a i n e d , o r e v e n o v e r t r a i n e d t o d e a l w i t h t h e m .
One of t h e most l e n g t h y and t h o u g h t f u l comments was:
'The hazardous s i t u a t i o n i s a c o m p l i c a t e d one i n which you a r e n o t q u i t e
sure what t o d o .
The s i m p l e r t h e s i t u a t i o n , t h e l e s s d a n g e r t h e r e i s of
screwing i t up.
I t h i n k t h e most i m p o r t a n t t h i n g from t h a t s t a n d p o i n t i n
Space S t a t i o n i s t o c l e a r l y i d e n t i f y and c o l o r - c o d e a l l t h e v a r i o u s p i e c e s of
equipment a t d i f f e r e n t l e v e l s of h a z a r d .
The most s e r i o u s b e i n g r e d , t h e n e x t
yellow, then maybe y e l l o w - a n d - b l a c k s t r i p e s .
now.
B a s i c a l l y l i k e t h e m i l i t a r y does
Mark 'NO STEP' and 'HAND HOLD', and s o f o r t h .
A c o n c e r t e d e f f o r t should
be made t o s e e t h a t we d o n ' t g e t s h a r p c o r n e r s and t h a t s o r t of t h i n g .
"The dangers a r e g o i n g t o be i n t h e p r e s s u r e s u i t p e o p l e w e a r .
With a l o t
of people up t h e r e working around t h e r e i s g o i n g t o be a s u i t p u n c t u r e , o r
swneone i s n o t g o i n g t o p u t t h e w r i s t s e a l on p r o p e r l y and a g l o v e w i l l pop
off.
Those a r e t h e k i n d s of problems we a r e g o i n g t o h a v e .
We a r e n o t going
to have any problems i n s i d e . "
Cowitents:
Of a l l t h e r e s p o n d e n t s , I c o n c u r most c l o s e l y w i t h t h e i n d i v i d u a l
who made t h e f i v e p o i n t s .
They s h o u l d be remembered and p r a c t i c e d by a l l who
have any r o l e i n s a f e t y d e s i g n o r p r a c t i c e s - and t h a t i n c l u d e s n e a r l y
everyone.
39
�51.
Suggestions which would help maintain crew h e a l t h .
This question was asked of nine c o n t a c t s .
t o make.
Two s t a t e d they had no comments
Proper n u t r i t i o n o r d i e t was mentioned by t h r e e people, a s was
proper e x e r c i s e .
Recognition t h a t people have t h e same psychological needs In
space as on Earth was mentioned frequently.
One c o n t a c t urged t h a t t h e time
l i n e be structured t o provide time f o r q u i e t r e f l e c t i o n and contemplation.
The b e n e f i t In crew member contributions t o t h e mission w i l l outweigh any cost
In time.
Another said t h a t we must choose s e n s i t i v e . I n t e l l i g e n t people t o
serve on Space S t a t i o n .
You d o n ' t need t h e "machonnan", and b r u t e - f o r c e kind
of people - they should be kept o u t .
One man s t a t e d , "Try t o make I t a s much l i k e a normal c i v i l i a n l i f e a s
possible, recognizing t h a t we're going t o have a connand s t r u c t u r e , and by
t h a t I mean If a guy wants t o have a g l a s s of wine with dinner o r a s h o t of
brandy a f t e r , he ought t o be e n t i t l e d t o do s o .
I t ' s home!"
He's not f l y i n g an a i r l i n e r -
One other man had mentioned t h a t he thought moderate consumption of
alcohol was probably b e n e f i c i a l .
Another man, who I am s u r e would have agreed
with the comments above regarding wine with t h e meals and brandy a f t e r ,
nevertheless warned against what he perceived a s t h e c u r r e n t s o c i a l acceptance
of overindulgence by m i l i t a r y p i l o t s .
s a f e flying t h e next day.
He f e l t t h a t behavior was hazardous t o
The mental health aspects of t h e Space S t a t i o n were considered by another
contact.
He s a i d , "He should allow a routine-enough work c y c l e and approach
t o Space S t a t i o n operations so t h a t If someone does g e t s1ck they can go take
a day off and r e s t .
L e t ' s ease off on t h e work load.
L e t ' s l e t the
astronomers have some time t o j u s t s i t t h e r e and look through t h e telescopes.
Hhat's wrong with t h a t ?
g r e a t Ideas anyway."
Coweents:
T h a t ' s where a l l t h e g r e a t astronomers got a l l t h e i r
Here a g a i n , I was pleased t o s e e t h e emphasis on f a c t o r s
Influ e n c i n g m e n t a l h e a l t h .
If one lesson should have been learned from a l l of
40
�our space f l i g h t p r o j e c t s , i t i s t h a t we must guard a g a i n s t overloading the
crew metrtier.
I was most impressed by t h e l a s t comment recorded, " L e t ' s ease
off on the work load.
L e t ' s l e t t h e t h e astronomers have some time t o j u s t
sit there and look through t h e t e l e s c o p e s .
What's wrong with t h a t ?
That's
where a l l the g r e a t astronomers g o t a l l t h e i r g r e a t ideas anyway."
I can only applaud t h a t a d v i c e .
SPONTANEOUS COMMENTS
As stated in t h e s e c t i o n e n t i t l e d METHOD, t h e 51 questions were a c t u a l l y
used only t o s t i m u l a t e d i s c u s s i o n .
Although a g r e a t many comments were
received in response t o t h o s e q u e s t i o n s , t h e r e were some additional statements
•ade either spontaneously o r a s a r e s u l t of thoughts stimulated by t h e
questions.
Some of t h e s e spontaneous statements a r e presented in t h i s s e c t i o n .
1. I t had been several y e a r s , and even decades, since some of t h e contacts
had flown.
One of them opened t h e interview with t h i s statement:
" I t i s i n t e r e s t i n g your coming around doing t h i s .
I commented t o [ h i s
wife] t h i s morning t h a t t h i s i s t h e f i r s t time anybody has asked my opinion
about anything s i n c e t h e day I l e f t NASA.
And, consequently, i t i s of a l o t
less value than i t might have been a year a f t e r I l e f t NASA."
Conments:
In l i g h t of t h e remark made by one c o n t a c t t h a t h i s remarks might
have had more value had he been contacted a year a f t e r leaving t h e program
rather than several years l a t e r might suggest t h a t NASA give consideration t o
establishing a procedure whereby a l l former a s t r o n a u t s would be interviewed a
year or two a f t e r they leave t h e program.
1 f e e l confident t h a t individuals
who are no longer competing f o r a f l i g h t p o s i t i o n , o r who a r e no longer hoping
for advancement i n , o r rewards from, t h e system might well be a very valuable
source of information.
Among t h e t e n people I interviewed, 1 f e l t t h a t some
of there were so long out of t h e program a s t o be of l i t t l e value t o t h i s
project.
On t h e o t h e r hand, some who were more r e c e n t menders of NASA had
•any good conments which t h e y probably would not have made had they been
corepeting f o r f l i g h t assignment.
41
�2.
One stated that he feU gymnastics might be a good training procedure,
particularly use of the trampoline, in combatting space motion sickness.
Cowwents;
3.
None.
In view of the fact that EVA astronauts do not appear to use their legs
very much, one contact was asked his opinion regarding a suit without separate
legs. He replied;
•Some of the EVA tasks would require that you anchor your feet somehow,
because that's the way you apply the torque.
If. of course, you have some
umbilical 'belly-button' kind of thing with which you attach yourself rigidly
through your center of gravity, then you could obviously use your arms pretty
well without a foot restraint.
I would kind of think that having your legs
separate would give you much better torque and muscle control."
In response to the same question another contact said•But If you're thinking In terms of a Space Station where you're going to
have to do some manual work with your arms, and you look at the situation
Where you put In a torque motion. I don't know how you would counteract that
without having your feet somehow [stabilized],
speaking of construction work
1n space he said. "It Is In that kind of a mode where I would envision that
you might want [to use your legs].'
Comments:
4.
None.
When speaking of training, one contact mentioned what he called an
advocacy position In training,
it Is sitting down ahead of time and asking
what^one will do If a certain event takes place.
He said:
•Within certain limitations you could take the advocacy role ahead of
time.
It's a 'brain-washing', and I know that's a bad word, but you train to
the point where, when you get there, the actual case Is a piece of cake.
many times It doesn't have to be a hands-on kind of training.
And
You can sit In
a room and discuss what we're going to do If this happens and why do that
one.
But you gotta go through that exercise.
42
It's a very Important part of
�getting ready t o go."
The contact then gave two examples from h i s f l i g h t
where f a m i l i a r i t y with the system and procedures saved t h e mission.
Cofiments;
The remarks regarding "advocacy" t r a i n i n g were i n t e r e s t i n g t o me.
The mental exercise of s i t t i n g q u i e t l y alone o r with o n e ' s colleagues and
contemplating possible events and how t o cope with them I s probably an
excellent way t o t r a i n f o r foreseeable e v e n t u a l i t i e s .
Perhaps such t r a i n i n g
methods could be encouraged.
5.
At the close of h i s interview, one contact offered t h e following
independent thought:
"One of t h e t h i n g s I d o n ' t think we're doing t o o w e l l . . . i s designing
things l i k e t h e Space S t a t i o n , taking advantage of t h e r eal and unique
environment.
Using t h e d e l t a temperature and t h e d e l t a pressure a s driving
forces t o some degree in equipment design.
We're s t i l l designing things f o r
here t h a t we then make a l l s o r t s of special precautions t o operate up t h e r e
instead of designing them t o r e a l l y optimize the environment they have t o be
in.
I think when t h a t happens we w i l l have problems t e s t i n g i t down here, but
i t w i n [work b e t t e r up t h e r e . ] "
When asked f o r examples he said t h a t he had
none a t t h e moment.
Comments:
6.
None.
Another contact i n explaining why he thought he did not g e t motion
sickness i n f l i g h t s a i d :
"We would go up and do parabolas in t h e T-38 where we could do between 15
and 23 r o l l s on a given parabola.
with each r o l l .
We put our head i n d i f f e r e n t o r i e n t a t i o n s
I ' d do t h a t maybe twice, and a l l of a sudden t h e sweat would
break out—you'd s i t t h e r e with t h e world going around and you'd t r y t o f l y
s t r a i g h t and level f o r f i v e minutes u n t i l you could g e t t h e world back
together again, then you'd go a t i t a g a i n .
[before t h e f l i g h t ] .
I did t h a t down a t t h e Cape
I got t o where i t r e a l l y took something t o g e t me s i c k .
I d o n ' t know whether i t was t h a t conditioning t h a t helped o r whether i t was
t h a t I was j u s t more n a t u r a l l y r e s i s t a n t than some.
43
You can do t h e same thing
�in a swlnwing pool.
nystagmus.*
You can get some pretty high rates—until you get severe
He continued t o cowaent that performing r o l l s In a zero-g parabola and
holding the head in different positions a t the same time was the most
efficient way of producing nystagmus that he knows.
He got t o the point where
he could make the world 'twitch* in any direction depending upon how he held
his head during the r o l l .
£ommsntsj_
NASA might give some thought t o investigating t h e training routine
described by the contact who stated he and his partner executed 15 t o 23 rolls
while in a zero-g parabola, with t h e i r heads in a d i f f e r e n t orientation for
each parabola.
I am astounded a t the piloting s k i l l which t h i s maneuver
requires, but if i t can be done I t might be of value i n anti-motion sickness
training.
I know that aerobatics have been attempted t o t r a i n against motion
sickness, largely without benefit, but t h i s i s the f i r s t I have heard of
stimulating the semicircular canals while in zero-g.
7.
One contact was asked for his ideas regarding the changing crews.
He said
that i t might be necessary t o bring up one o r two s p e c i a l i s t s for short
periods t o perform specific tasks, but he f e l t i t was important t o change the
e n t i r e basic crew a t the same time t o maintain a cohesive u n i t .
Comments:
8.
None.
Another Interesting concluding remark was:
"There i s one other thing I always make a pitch on. and t h a t i s that they
do not realize that people in space f l i g h t o r in zero-gravity condition are no
different than down here.
You have zero gravity and a b e t t e r view, but other
than that you are dealing with the same person and the same working
environment and they can do exactly the same thing they can do down here.
If
a person i s exceptionally good as an observer o r working out something
analytically, or if he i s good a t doing any kind of a detailed task (for
example, a photo interpreter), you can put him up there where he i s looking a t
44
�the real thing.
He can do just as good a Job up there as down here.
no reason for not using a person's intellect fully.
There is
So far, the way space
flights have been constructed, they want to dictate everything by checklist
and take away your ability to think.
Coninents;
9.
See comments following Statement 9.
Another man expressed the same thoughts in this way:
"My big 'soap box' effort is the thing about let's not forget who we are
and what our needs are as people, and carry those things with us.
Let's not
lull ourselves into thinking that this is such a special environment that all
the rules change and everything is different, and that people will give up
this and give up that In order to be up there.
They will do it for a ten-day
mission, but they won't do it for ninety days."
He went on to say, "One of the problems we ran into on our mission was
that we forgot to think about those things, and we got ourselves caught up in
a workaday thing where we were working fourteen to sixteen hours a day, and
working strictly following a carrot - following a very precise agenda every
day.
Halfway through the mission we began to get inefficient and made
mistakes.
Me finally recognized our problem and did something about it, and
came out at the end of the mission in good shape.
We finished everything we
were supposed to do and got it all right."
Comments: I commend the two remarks regarding utilization of people for their
capabilities and their human abilities to NASA for serious consideration. I
agree with both comments.
If we are to put people in space we must take
advantage of their capabilities and their "humanness", whatever that is.
He
should recognize the tendency to overschedule and actively correct for that
tendency.
10.
One contact believes that the absence of low-frequency electromagnetic
radiation in space might have some physiological consequences.
this radiation is commonly referred to as Schumann resonance.
this subject he said:
45
He said that
Speaking to
�•W1th1n the Ionosphere-Earth surface cavity there is, I think, about an
8-H2
to 32-Hz oscillating field with a series of peaks in that field that is
generated by lightning storms on Earth, but the net result of all that
electromagnetic activity is that we're exposed from conception to death to
this oscillating field, and there is some evidence that if you play with that
field here on Earth, particularly by superimposing a 5-Hz, 4-Hz, or 3-Hz field
on what is already there (and it is very difficult to isolate the individual
from it unless you go underground) and you get some neurological problems.
It
does affect people, and it is probably related to what happens to you when you
get a relatively low-frequency strobe light flashing at you.
A lot of people
feel very very uncomfortable neurologically when that happens.
course, it's absent.
In space, of
Once you get above the ionosphere that field is absent,
and there is some concern among physicists who have a background in
neurophysiology that there might be an instantaneous effect contributing to
the Space Adaptation Syndrome, but they are more concerned about what the
long-term effect may be if the brain actually uses that frquency on occasion
or continuously to reset it's own timing signals in it's central processor.
So, 1 would FLAG that as an unknown."
This contact was also concerned about "intermittent sleep."
could cause difficulty from the standpoint of loss of REH sleep.
sleep is different from simple insomnia.
He felt it
Intermittent
Intermittent sleep is that situation
where a person wakes up and goes back to sleep several times during a sleep
period.
It should cause no problem over short periods, but if continued for
two months or so it might.
It has been noticed in sleep labs on the Earth,
but the contact was of the opinion that it occurs more frequently in space
flight than it does on the Earth.
Comments; I cannot connent on the role of low-frequency electromagnetic
radiation in space and its physiological consequences and I am unaware of
"Schumann Resonance", but I do want to underline this individual's connent as
a possible route of inquiry, which NASA might investigate.
I also am unable
to comment on this same contacts remarks regarding "Intermittent Sleep".
46
�11. One man mentioned t h a t he f e l t h i s mind worked b e t t e r i n space.
When
asked t o elaborate on t h a t s u b j e c t he s a i d :
' . . . i t might be j u s t t h a t you a r e doing i t f o r r eal r a t h e r than in
practice.
The f a c t t h a t you're i n 100X oxygen environment - t h a t should allow
you t o perform a l i t t l e b e t t e r .
I think i n a place of reduced g r a v i t y , t h a t
could have a contributing f a c t o r t o o .
including mental.
Cownent;
12.
[There was a ] changed response p a t t e r n ,
That i s p a r t i c u l a r l y t r u e in the weightless s i t u a t i o n . "
None.
One contact mentioned t h a t i t took him four t o f i v e days t o g e t adjusted
to the zero-g environment.
He s a i d t h a t he knew t h a t i f he moved about
Quickly he would become s i c k , s o he moved very slowly and very d e l i b e r a t e l y
until he became accustomed t o t h e environment.
He a l s o mentioned t h a t upon h i s return t o Earth he had " v e r t i g o " .
as if t h e bed was i n c l i n e d about 30 degrees head down.
for about a week.
He f e l t
This sensation lasted
He mentions t h a t he was unable t o c l e a r h i s e a r s during
parachute descent a t t h e end of h i s mission and wonders i f t h a t did not
contribute t o h i s f e e l i n g s of " v e r t i g o " .
He believes i t would have been
interesting t o go through v e s t i b u l a r t e s t i n g during t h a t period, but o t h e r
matters seemed t o occupy t h e time of t h e physicians.
Comments:
The contact who said i t took him four t o f i v e days t o g e t adjusted
t o the zero-g environment was t h e only one of t h e group t h a t admitted t o even
the l e a s t t r o u b l e .
I found i t i n t e r e s t i n g t h a t he experienced a head-down
sensation a f t e r return t o Earth.
I would have expected him t o experience a
head-down sensation in f l i g h t due t o migration of f l u i d t o t h e head and a
head-up sensation upon return t o Earth.
13.
Several s u b j e c t s mentioned d i f f i c u l t y sleeping i n f l i g h t .
The consensus
seemed t o be t h a t f r e e - f l o a t i n g s l e e p was not comfortable o r r e s t f u l .
One man
mentioned t h a t i n o r d e r t o g e t a comfortable n i g h t ' s s l e e p , t h e head and hands
have t o be r e s t r a i n e d t o prevent them from moving about i n random fashion.
47
�Coimients; I believe this last remark regarding the unsatisfactory nature of
unrestrained or free-floating sleep has been made before, so It requires no
further Investigation, but should be kept In mind when sleep restraints In the
Space Station crew quarters are being designed.
48
�APPENDIX A
1.
Flight Crew Health Stabilization Program;
Discuss in context of SS vs Skylab, Apollo, and STS.
Worthwhile?
Retain?
Eliminate?
Modify?
2.
Do you have any thoughts on facilitating SS maintenance activities of the
crew?
3.
Discuss alarm systems:
False alarms.
Lights.
Horns.
Voice.
Tactile.
4.
Any thoughts as to tools for on-orbit repair and maintenance?
Including "work bench", location, equipment, etc.
5.
What about food and meals?
A11 eat same foods on same days?
Individually selected menu?
Suggested changes/improvements.
6.
Any suggestions regarding trash disposal?
49
�7.
Any thoughts on clothing design?
One piece c o v e r a l l s v s . pants and s h i r t ?
Pocket l o c a t i o n , design, closure?
Off-duty and on-duty.
Any d i f f e r e n c e ?
Special clothing f o r e x e r c i s e ?
What kind of sleepwear would you choose?
Any personal Items of c l o t h i n g f o r you?
8.
Suggestions a s t o personal hygiene equipment.
9.
Aids t o t r a n s f e r of massive o b j e c t s .
1 0 . Skylab crews found t h a t they o r i e n t e d t o t h e f l o o r In small compartments,
but t r a n s l a t e d h e a d - f i r s t in large compartments.
Does t h i s Influence your
thinking In regard t o I d e n t i f i c a t i o n of "up" and "down"?
Would visual
o r i e n t a t i o n cues a s t o "up" o r "down" be helpful o r harmful?
[At l e a s t one Skylab crew member reported t h a t he always o r i e n t e d down
towards h i s f e e t . ]
n . What about using vented gases f o r a t t i t u d e c o n t r o l , o r what about using
opposing vents t o cancel any e f f e c t from venting?
1 2 . What I s the Importance of p r i v a t e coniminlcatlons with o p e r a t i o n s s t a f f ,
medical s t a f f , f r i e n d s , and r e l a t i v e s ?
1 3 . Some Skylab crew members reported t h a t p o r t a b l e f ans were of l i t t l e use
f o r crew comfort, but were useful f o r equipment c o o l i n g .
Others reported that
they a r e u s e f u l , e s p e c i a l l y t o cool a person during and a f t e r e x e r c i s e .
I s your opinion?
1 4 . Oo you have any Ideas concerning:
Translation a i d s ?
Control/switch p r o t e c t i v e devices?
Orientation cues?
Protective devices f o r personal wear (helmets, g l o v e s , e t c . )
50
What
�15. Skylab crew's coimients about the airlock Included such remarks as:
It was too small for two crewmen.
Insufficient stowage volume. "Like a rat's nest during EVA.'
Lack of foot restraints.
Poor location;
-Between Multiple Docking Adapter and Orbital Workshop.
-In mainstream of traffic.
-Failure of any one of three hatches would be cause for mission
abort or even catastrophic situation (EVA crewman being trapped
outside).
OUESTIOMS: Here any of these problems present on STS?
What suggestions have you for Space Station?
16. Any Ideas about the Individual crew quarters?
Location.
General arrangement:
(1) Size (Skylab nominal was 28 In. x 38 In. x 78 In.).
(2) Restraints.
(3) Stowage.
Noise.
Lighting.
Temperature.
Ventilation.
What kind of sleep restraint?
Should washing and toilet facilities be Included?
-Cofflode?
-Urinal?
-Both?
What about shift occupancy?
Communications?
Warning signals?
51
�17. How much medical training should crew members have?
Equivalent to CNT?
More?
Less?
18. Oo you believe crew members should engage in 'group dynamics* training
before being assigned to SS?
Should one CH be trained in this discipline?
19. Should families be given similar psychological training and support?
20. What about crew interaction training in a one-g simulator?
21. How much of a problem is ambient noise?
22. Wardroom:
What suggestions for entertainment?
Will external viewing be of great importance from a recreational
standpoint?
Is It Important that the Earth appear "down"?
23. Discuss body waste collection and disposal.
24. Personal cleanliness.
Shaving.
Haircuts.
Showers.
25. Exercise.
What kind?
26. How best to manage books and manuals.
Should everything be in data banks with CRT display?
27. Han/machine interfaces.
Brightness.
Shape, color, texture.
52
�28. Three shifts or one (or two)?
All sleep at the same time?
How long a work day?
Eight hours?
Hore?
Less?
Should work time Include one to two hours of exercise, or should all
exercise be performed In off-duty time?
29. How Important would be real-time TV, Including network news?
30. l>/ho should select the crew?
What Input should crew members have In regard to crew composition?
31. Does EVA require "buddy system" or can one person do It alone with
monitoring from the Inside?
32. How can the EVA suit be Improved?
Urine collection.
Fecal collection.
Provision for food and water.
Vomiting.
33. EVA
Restraints and tethers.
Hand and foot holds.
Lighting.
Helmet mounted?
Tools.
34. With a twenty-one-day rescue time at worst, do you have any suggestions
regarding mortuary services?
35. What about foot restraints at the work station?
Locking grid and shoe.
Stirrups.
Clangs.
Velcro.
Other.
53
�36. Loconotlon aids.
Lines, slldewlres.
Distributed handles.
Other.
37. What about body restraints for tasks requiring extreme steadiness?
3B. Any thoughts on artificial gravity?
Need.
Methods.
Rotating SS.
Tether.
Continuous or Intermittent?
39. What about autonomy?
Is "control" by NCC a pain, or Is It reassuring?
40. Would a miniature helmet-mounted TV to record EVA activities be useful?
41. What about an ELV rescue capability?
capsules.
For example, a Titan with reentry
42. How can man-on-board reduce redundancy?
43. Any Ideas for design of a safe haven for two to three weeks' occupancy?
44. What about EVA?
Use only for contingency?
Use for contingency and major tasks only?
Design for and use routinely?
45. On-board command structure:
Strong, authoritative Comnander with clear chain of command?
Participative management?
Coenlttee decision making?
54
�46. How H1-F1 should the SS simulator be?
47. Is the orbiter overdesigned for safety?
Can safety requirements be relaxed for SS?
Any examples?
48. Any suggestions as to docking techniques or aids?
Proximity operations.
Approach corridors.
Plume impingement considerations.
Others.
49. In the future many diverse groups of people will have to participate in
Space Station activities.
For many of these people—scientists, construction
workers, and so forth—there will be no arbitrary age limit.
Can you think of any investigations that should be performed now, either
to select those persons or to accommodate them in flight?
50. Do you have any thoughts as regards safety hazards?
51. Do you have any suggestions as to measures that would help maintain crew
health?
55
��National Aeronautics and
Space Administration
APPENDIX B
Ames Research Center
Moffett Field. California 94035
rUASA
aeiirioAdnai: LMA:239-2
Dear Space Missioa Participant:
The purpose of this letter is to introduce Dr« William K« Douglas and a
project that he is conducting under the sponsorship of NASA's Anes
Research Center.
The Ames Man-Vehicle Systems Research Division under its Space Human Fac
tors Office is in the process of planning research that will help to as
sure high levels of crew effectiveness on future space missions, including
NASA's proposed space station. Several expected differences between the
space station and previous missions suggest that such research is warrant
ed. Such differences include more heterogeneity of crew members in back
ground and experience, broader variety of work requirements (including
more EVA), larger crews, and longer durations.
To accommodate some of these changes, plans and designs are being
developed for configurations of the total station, individual modules, and
work stations, as well as for habitability Issues and operational pro
cedures.
In many cases the appropriate design or plan for promoting and
maintaining effective crew performance under the changing conditions is
unknown. Numerous cases involving new designs for work stations and habi
tats have been documented, in which serious performance problems have ar
isen because of either the lack of human factors information or the
failure to incorporate available information.
The Division has been active for several years in research to support the
aviation community in developing methods for avoiding such errors in
design, and operations. One of the more valuable sources of Information
that has directed our research activities has been the Aviation Safety Re
porting System (ASRS), which we direct (through a contract, under the
sponsorship of the FAA).
The system solicits voluntary comments and
recommendations from pilots and air traffic controllers that concern any
procedural problems encountered in the aviation system, and how these
might be corrected. The reports are completely deidentified to insure
anonymity of the reporter.
Publication of the obtained information is
generally in the form of a report that synthesises Individual comments and
recommendations related to some particular Issue.
Information such as that generated by the ASRS has proven of value, not
only by indicating problems that require research for their solution, but
by Indicating when research is unnecessary, either because Information is
available to effect a solution, research is already in progress, or the
57
�problem Is not amenable to research. When research has been prescribed,
the value of Its product has been enhanced significantly by the direction
received from such information.
The project being conducted by Dr. Douglas Is consistent with the intent
and spirit of the ASRS. We are convinced that the experience of partici
pants in previous space missions can form the basis for cogent recommenda
tions for design, operations, and appropriate research relevant to future
space missions, similarly to our experience in aviation.
Therefore, we
have asked Dr. Douglas to solicit thoughts regarding apace station design
and operational requirements. The information obtained will be used to
help us (and others) supply guidelines to designers, and to discover
inadequacies in available knowledge that Indicate a need for further
research.
Dr. Douglas has contacted you as part of that process.
Dr. Douglas was
the first flight surgeon for the Mercury astronauts. We sought his assis
tance in this project because of his reputation for sensitivity, objec
tivity, general knowledge of and appreciation for the human in space mis
sions, and his acquaintance with many members of the astronaut corps.
We are requesting your participation because of our sincere interest in
helping to assure a high level of effectiveness for future manned space
missions. Dr. Douglas' approach will be informal.
He will ask you a
series of questions designed to focus your consideration of design and
operational Issues, which we judge are important to the success of future
missions.
In your answers to the questions we are asking you to project
from your experience to the expected conditions on a space station.
We are not interested in documenting or reporting problems, either person
al or general, from past missions. Rather, we are asking for your judg
ment of where impediments to task performance, motivation, morale, etc.
could arise; what changes in design and operations would you recommend,
based on your experience and expected mission differences.
Dr. Douglas will be assisted on the project by Mr. Donald K. (Deke) Slayton, whom you may know personally. Mr. Slayton's experience and knowledge
should be of great assistance to Dr. Douglas in interpreting and syn
thesizing the information, and producing a useful report.
Please be assured, should you elect to participate, that the information
obtained by Dr. Douglas will be completely deidentified from you as the
source. Not only will your individual anonymity be assured with respect
to specific information that you volunteer, but the identity of those per
sons interviewed will not be revealed by Dr. Douglas or Mr. Slayton.
58
��1 fttcori No.
NASA CR-3942
4. Titlf and SuMiM
2. Geynwuwi HICHDH NO.
Human Performance Issues Arising From Manned Space
Station Missions
J
Autttorlll
3. Reopant't Cralog No.
& Report Dite
October 1986
e. Performing Orgeniotlon Code
8. Perfornung Or^izabon Report No.
William K. Douglas
9. ^lormina Orfonitation Nama and Addras
McDonnell Douglas Astronautics Company
3301 Bolsa Avenue
Huntington Beach, CA 92647
17 Soomortnf A^ncy Nama and Addra«
National Aeronautics and Space Administration
Washington, DC 20546
MDC H1363
10. Work Unit No.
11. Contract or Grant No.
NAS2-11723
13. Type of Report and Period Ceiwad
14. Sporaoring Agency Coda
FLS
IS Supplamantary Nolat
The author was the flight surgeon for the original Mercury Seven Astronauts.
Point of Contact: Trleve A. Tanner, MS239-2
(415)694-5185
Ames Research Center. Moffett Field. CA 94035 FTS464-5185
IS Aeanoei
Ten former NASA astonauts were Interviewed using a set of 51 questions
developed to encourage the contacts to discuss any thoughts, opinions, con
clusions, or suggestions which might have evolved since they left the astronaut
program.
Strict confidentiality was maintained. The reader will not be able to
attribute any recorded remark to an individual person or to a particular mis
sion.
At least one astronaut from each of the NASA manned space flight programs,
excluding the Space Transportation System (Shuttle), was Interviewed. The
report records the answers to the questions asked, spontaneous comments, and
the Investigator's oim personal evaluations of the material obtained. No
statistical analysis of the material was attempted.
The professional opinions of these ten experienced astronauts will be
of value to persons concerned with the design and operation of mannoH space
craft and manned space stations.
17 Key Warm ISunxtad by AutbarNIl
l& OtiMutMn StPMiweW
Crew health, maintenance, alarms, food,
Unclassified - Unlimited
clothing, personal hygiene, "up and
down" identification, private communi
Subject Category 54
cations, psychological support, crew
selection, group dynamics, crew quartet s
19 Secieity OmuI.|o(itM'•pert)
20. Sacurilv Otmri.lef tN* page)
21. No. of Pagn
22
Unclassified
Unclassified
62
'Forseleby the Nst>onii T*hriieel Infemriitttn Semee.Spnflgfield, Virgmi* 22161
.
A04
^
NASA'LANGLEY, 1986
��National Aeronautics and
Space Administration
Code NIT-4
BULK RATE
POSTAGE & FEES PAID
NASA
Permit No. G-27
Washington, D.C.
20546-0001
0*hcrat Business
Penalty toi Pftfjie Use. S300
rwvsA
M-sCT^ AcxrB •
njS>lMA^IkK.
If Undelfvcrablc (SBCCiun 156
MtnuBl) Do Not Return
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
sdsp_skyl_000074
Title
A name given to the resource
"Human Performance Issues Arising From Manned Space Station Missions."
Description
An account of the resource
This is a series of interviews with various anonymous astronauts from various programs including Skylab, focused on the future of manned spaceflight.
Creator
An entity primarily responsible for making the resource
Douglas, William K.
Date
A point or period of time associated with an event in the lifecycle of the resource
1986-10-01
Temporal Coverage
Temporal characteristics of the resource.
1980-1990
Subject
The topic of the resource
McDonnell Douglas Corporation
United States. National Aeronautics and Space Administration
Skylab Program
Human factors in engineering design
Neutral buoyancy simulation
Provisioning
Airlock modules
Extravehicular mobility units
Experimentation
Type
The nature or genre of the resource
Interviews
Text
Source
A related resource from which the described resource is derived
Skylab Collection
Box 16, Folder 2
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
A language of the resource
en
Rights
Information about rights held in and over the resource
This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14410/sdsp_skyl_000075_Combined.jpg
81268b29427400f96e13138a211af7a0
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
sdsp_skyl_000075
Title
A name given to the resource
Skylab Blueprint "119700."
Description
An account of the resource
This blueprint depicts a working space for the Skylab habitat, and includes work stations, and storage systems. This blueprint also depicts the water storage system for the Skylab habitat.
Creator
An entity primarily responsible for making the resource
United States. National Aeronautics and Space Administration
Temporal Coverage
Temporal characteristics of the resource.
1970-1979
Subject
The topic of the resource
Skylab Program
Human factors in engineering design
Provisioning
Experimentation
Film Vault
Life support systems
Airlock modules
Type
The nature or genre of the resource
Reprographic Copies
Still Image
Source
A related resource from which the described resource is derived
Skylab Collection
Box 22, Folder 34
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
A language of the resource
en
Rights
Information about rights held in and over the resource
This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14411/sdsp_skyl_000076_001.pdf
9e342fbc4bbc5654e9c49bef4997154e
PDF Text
Text
Sc.-/
•
I
SKYLAB MISSION COMMENTARY 5/14/73 CST 12:47 GET 17:00 MC10/1
PAO
Mark. Standing by now for confirmation of
ATM deployment. We're 17 minutes 35 seconds. The deployment
motors of the Apollo telescope mount now running. This deploy
ment sequence in toto takes about 4 minutes. Deployment
being activated by two Apollo telescope mount motors which
are presently running. We're 18 minutes 20 seconds now
ground elapsed time. The booster now being maneuvered to a
solar inertial attitude. We're at 19 minutes 10 seconds
ground elapsed time. Mark 20 minutes ground elapsed time.
We should be less than a minute away now from deployment.
Mark 20 minutes 12 seconds ground elapsed time. Our data
displays, Mission Control, now show the ATM has deployed and
locked. The Apollo telescope mount has been deployed and
securely latched. The 24,500 pound ATM reaching out now at
a 90»sdegree angle from the orbital workshop. We're at
20 minutes 35 seconds. We've had confirmation. We have data
here in Mission Control that the ATM has deployed and latched.
Mark 20 minutes 50 seconds. The next event to occur will be
the deployment of the four wings of the telescope mount solar
array system. We're standing by now for that deployment. Mark,
we're at 21 minutes 40 seconds ground elapsed time. Prelim
inary tracking data shows an orbit for the orbital workshop
of 237 nautical miles by 236.3 nautical miles near circular.
We repeat 237 nautical miles by 236.3 nautical miles. We're
at 24 minutes 30 seconds now ground elapsed time. Continuing
with the solar inertial maneuver, reports booster. Twentyfive minutes ground elapsed time. We've got 1 minute until
loss of signal with Madrid. Mark, we're 25 minutes 45 seconds.
The deployment motors have been turned on. The solar array
system wings on the Apollo telescope mount are now extended.
Standing by, continuing to monitor.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 CST 12:57 GET 27:00 MC11/1
Mark we're at 26 minutes 30 seconds under
acquisition now by an ARIA aircraft following loss of signal
with Madrid. Okay, all four Apollo telescope mount solar
array wings *re out and securely locked. Mark we're 27 min
utes 20 seconds now ground elapsed time. The Apollo telescope
mount has been deployed and securely latched. The solar array
system for the telescope mount, the four wings, has been deployed
and securely locked. The next thing we should be seeing in
Mission Control - We'll be receiving telemetry data from the tele
scope mount and this should occur within the next several
minutes. We are presently receiving data through an ARIA
aircraft beyond Madrid tracking station. Mark 28 minutes
10 seconds. We now show an orbit of 237.1 nautical miles
by 236.6 nautical miles for the orbital workshop. Mark
29 minutes 20 seconds. We've had some dropout in data from
the ARIA aircraft, presently showing static displays in Mission
Control. The procedures officer here working to get locked
up on the data at this time. We're at 29 minutes 40 seconds
ground elapsed time. We repeat that the Apollo telescope
mount has been deployed. The solar array system from the
telescope mount also deployed at this time. The next deployto °ocur will be the solar array system for the workshop.
?S ground elapsed time. We presently show an
K „ ^ *
nautical miles by 236.8 nautical miles for
the orbital workshop now in its first revolution. Mark
34 minutes 20 seconds ground elapsed time. Flight Director
Don Puddy speaking to his flight control team in mission
control saying everything looks good up to this point. We're
standing by now for definite indication through ARIA aircraft
WP'JiCniS ^ telemetry data from the Apollo telescope mount.
We re now at 34 minutes 40 seconds ground elapsed time.
Continuing to monitor. This is Skylab Control, Houston.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 CST 13;07 GET 36:00 MC-12/1
PAO
This is Skylab Control, Houston, at
36 minutes ground elapsed time, still standing by for a
definite indication of receipt of telemetry from the Apollo
telescope mount. Following this we will see the deployment
of the meteoroid shields and the deployment of the solar array
system wings aboard the workshop. Thus far, we've seen the
successful activation of the Apollo telescope mount as well as
the solar array system for that mount. We're at 36 minutes
35 seconds, continuing to monitor. This is Skylab Control,
Houston.
PAO
This is Skylab Control, Houston; 41 minutes
ground elapsed time. We presently show an orbit of 236.2
nautical miles by 237 nautical miles. We are some 12 minutes
26 seconds away now from acquisition Carnarvon at which
time we should be able to verify telemetry being received
from the Apollo telescope mount. This is Skylab Control,
Houston, at 41 minutes 35 seconds ground elapsed time.
END OF TAPE
SKYLAB MISSION COMMENTARY 5/14/73 CST 13:24 GET 53:00 MC13/1
PAO
Skylab Control, Houston, at 53 minutes
ground elapsed time. We're less than a minute away now from
acquisition by Carnarvon tracking. We'll keep the line open.
Stand by, continue to monitor. A quick status check in Mission
Control by a Flight Director, Don Puddy, led him to say every
thing looks "super good" so far. We presently show an orbit
based on increased tracking data of 236.5 nautical miles by
236.2 nautical miles. Standing by continuing to monitor. This
is Skylab Control, Houston. We are now acquiring data through
Carnarvon. Booster reports the vehicle is now in solar
inertial attitude. We are now receiving telemetry data from
the Apollo telescope mount. The Environmental Officer reports
the data receiving looks good. The habitation area vent valves
have been closed as scheduled. We're now at 55 minutes
ground elapsed time. This is Skylab Control, Houston.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 CST 13:29 GET 58:00 MC14/1
PAO
Skylab Control, Houston, at 59 minutes ground
elapsed time. We have no confirmation yet on the deployment
of the airlock solar array system. We'll stand by and con
tinue to monitor at 59 minutes ground elapsed time. This
is Skylab Control, Houston. Skylab Control, Houston, at 1 hour
4 minutes ground elapsed time. We're less than a minute
away now from acquisition by Honeysuckle. This
ke j*
very short acquisition time, some 1 minute 11 seconds. Follow
ing Honeysuckle, the next station to receive data will be
Texas, and that would be 30 minutes 30 seconds from this time.
We're now at 1 hour 4 minutes ground elapsed time. Continuing
to monitor, this is Skylab Control, Houston. We have acqui
sition through Honeysuckle at this time. We're 1 hour 5 min
utes ground elapsed time. Skylab Control, Houston, at
1 hour 7 minutes ground elapsed time we've passed out of
station contact with Honeysuckle at this time. The next sta
tion to acquire will be Texas at 27 minutes 42 seconds from
this time. We've still received, through data, no definite
indication on the airlock solar array system deployment;
however, this pass, as well as Carnarvon, was through dark
ness and the Sun will be the first definite way of giving
an indication as to whether or not the airlock module solar
array system has been deployed. We would expect to take a
good hard look at this through our first stateside pass.
We're now at 1 hour 7 minutes ground elapsed time. This is
Skylab Control, Houston.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 14:05 CST 1:34 GET MC15/1
PAO
This is Skylab Control, Houston, at 1 hour
34 minutes ground elapsed time. Less than a minute away now
from acquisition by Texas, We show an orbit of 237,1 nautical
miles by 236.2 nautical miles. To quickly recount what we've
seen during this first revolution of the workshop orbit. The
payload shroud jettisoned on schedule. The ATM Apollo telescope
mount has deployed. The solar array system for the ATM
has also deployed. We have no indication yet on the deploy
ment of the two solar array wings attached to the workshop.
We will look at this - at display data for about 10 minutes
under sunlight on this stateside pass to endeavor to confirm
or not confirm that deployment. Given a nonconfirmation, of
course, backup commanding could be necessary from the Control
Center. We're at 1 hour 35 minutes ground elapsed time. This
is Skylab Control, Houston.
PAO
Skylab Control, Houston, 1 hour 38 minutes
ground elapsed time. Flight Director, Don Puddy, talking to
the Booster System Engineer here in Mission Control. We have
no indication of deployment of the workshop solar array system wings.
No indication of deployment of those wings. The Booster
now going through some backup command procedures. We've also
had an indication of partial deployment of the meteoroid shield.
We're at 1 hour 39 minutes ground elapsed time, continuing
to monitor. This is Skylab Control, Houston.
PAO
Skylab Control, Houston. Now 1 hour
40 minutes ground elapsed time. The orbital workshop now
on it's first stateside pass since launch and insertion
into orbit. We are presently looking at the orbital workshop
solar array system. No indication at this time of deployment.
The Booster Systems Engineer here in Mission Control going
through backup procedures to issue a command for deployment.
Standing by, continuing to monitor. This is Skylab Control,
Houston.
PAO
Skylab Control, Houston, now 1 hour 46 minutes
ground elapsed time. Continuing to monitor on this first
stateside pass, the orbital workshop. Again, we repeat the
orbital workshop solar array system wings have not deployed.
Command procedures are being followed presently on the ground
by the Booster Systems Engineer. Standing by, continuing
to monitor. This is Skylab Control, Houston.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 C5T 14:20 GET 1:48 MC16/1
PAO
Skylab Control, Houston, now 1 hour 53 minutes
ground elapsed time. Receiving good data now through New
foundland. Booster at this time issuing commands to the
workshop. To repeat what we said earlier, the orbital workshop
solar array system wings have not yet deployed. Standing by,
continuing to monitor. This is Skylab Control, Houston. Skylab Control, Houston, 1 hour 57 minutes ground elapsed time.
We now have acquisition with Madrid. Standing by, continuing
to monitor. This is Skylab Control, Houston.
END OF TAPE
SKYLAB MISSION COMMENTARY 5/14/73 CST 14:35 GET 2:03 MC17/1
PAO
Skylab Control, Houston, at 2 hours 7 minutes
ground elapsed time. We've passed out of acquisition with
Madrid tracking. The commanding by the booster systems
engineer was verified. The commands did get in; however,
we still have no indication of deployment of the orbital
workshop solar array system wings. It is known, of course,
that the commands did get in. At the present time, however,
with the Apollo telescope mount solar array system deployed
successfully, we do have a power system to support the vehicle.
We're now at 2 hours 8 minutes ground elapsed time and this
is Skylab Control, Houston.
END OF TAPE
SKYLAB MISSION COMMENTARY 5/14/73 CST 15:12 GET 2:41 MC18/1
This is Skylab Control. Two hours 41 minutes
ground elapsed time in the mission of Skylab 1. Skylab space
station now in orbit, coming up on the Honeysuckle, Australia,
tracking station. Still some doubt in the minds of Flight
Controllers here in Mission Control as to whether the main
solar panels on the workshop have indeed deployed. They
have had no confirmation on the ground from telemetry that
this is the case; the solar panels on the telescope mount
have deployed normally. Also, the micrometeoroid shield
around the workshop has partially deployed. The large wings
of three sections of solar panels on each wing, one on each
side of the workshop, generate anywhere from 51 to 125 volts
depending on the Sun angle at the time. This power goes
through chargers which in turn keeps storage batteries in
the workshop built up to supply power throughout the mission,
half of each orbit approximately is in darkness when no
power can be generated by the solar panels. The two solar
panel wings are deployed out to the side of the workshop,
and each panel on the wings operates similar to a scissors
action. It's spring loaded to extend the panels. We should
be getting data now through Honeysuckle. We'll stand by for
comments to the Flight Director from the Flight Controllers
who are concerned with the workshop electrical power system,
and relay this information as it - No change reported in the
solar panel wing status.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 15:27 CST 2:56 GET MC19/1
PAO
This is Skylab Control. Three minutes
2 hour - Three hours 2 minutes ground elapsed time, and
the mission of Skylab 1. Skylab space station now being
tracked by the Hawaii tracking station. Waiting for the
systems engineers to report the space station status back
to the Flight Director as the data comes in.
PAO
It appears that a plan will be formulated
later on in the day and this evening by which the existing
available power coming into the Skyiab workshop will be
conserved to the greatest extent, on the assumption that
we may not be able to get the main solar panels deployed,
we'll continue to standby the remainder of the Hawaii pass,
which is a fairly low elevation angle. Coming up in a few
moments to Goldstone, in approximately 5-1/2 minutes for a
fairly lengthy stateside pass over the tracking stations in
the contintental United States. At 3 hours 5 minutes ground
elapsed time, this is Skylab Control.
END OF TAPE
SKYLAB MISSION COMMENTARY 5/14/73 15:41 CST 03:10 GET MC20/1
This is Skylab Control, 3 hours 10 minutes,
ground elapsed time. Acquisition of signal over Goldstone
Tracking Station for the second stateside pass after launch.
We'll stand by here as the data comes in for any further
developments in the situation in which the main solar panels
on the workshop apparently have not deployed.
PA0
END OF TAPE
SKYLAB MISSION COMMENTARY 4/14/73 15:56 CST 3:24 GET MC-21/1
PAO
This is Skylab Control. Three hours 31 min
utes, ground elapsed time. Skylab space station presently
crossing over the combined coverage of Canary Island track
ing station and Madrid, Spain, tracking station. Flight Controllers,
here, continuing to assess the possible effects on the
mission on the apparent nondeployment of the large solar
panels on the workshop. As the afternoon and evening
wears on, there likely will be some considerable amount
of sorting out as to what course should be taken to get
the most out of the mission. As these facts develop, as
the plans are worked out, they will be relayed on over the
circuit at 3 hours 32 minutes, ground elapsed time, with
some 5 minutes and a half remaining over Madrid. And,
standing by; this is Skylab Control.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 15:00 CST 16:10 GET 3:39 MC22/1
PAO
This is Skylab Control, 3 hours 42 minutes,
ground elapsed time. Skylab space station now over the hill
from the Canary Island tracking station. Thirty-four minutes
away from being acquired again by the Honeysuckle, Australia,
tracking station. No further resolution at this time on the
solar pnel deployment problem, which likely will affect the
course of the mission. As the planning develops, on how to
best manage the mission for the maximum return, we'll bring
these details to you on this circuit. And, at 3 hours 40 minutes,
ground elapsed time, on the mission of Skylab 1, this is
Skylab Control.
END OF TAPE
SKYLAB MISSION COMMENTARY 5/14/73 16:42 CST 4:11 GET MC-23/1
PA0
This is Skylab Control. Four hours 14 min
utes ground elapsed time - the Skylab space station mission.
Here in the Control Center, the problems associated with
the failure of the Saturn workshop solar panels to deploy
are being discussed, at some length, by management and flight
controllers. Preliminary telemetry indications are that
there could have been a malfunction with one solar array
beam fairing and the meteroid shield, which could have led
to such anomalies. These malfunctions are indicated
to have occurred 1 minute and 3 seconds after lift-off,
based on postlaunch examination of telemetry.
The Planned 28-day mission is not possible with«„4. ^PA?
out deployment of the workshop main solar panels. Project
° lcl^ls arf considering an alternate mission using the
command service module power system to augment the limited
power supply provided by the Apollo telescope mount solar
panels aboard the workshop, through a system of managing
the two power sources for the optimum usage. An announce
ment will be made as soon as these decisions have been
reached. The decision on such an alternate mission is
expected to be had by about 9:00 p.m. eastern daylight time,
at which time a news conference will be held at the Cape,
exPected that Skylab Program Director, Bill
cu
chnieder, will take part. We're starting to get data, now,
through the Honeysuckle, Australia tracking station. This
is a rather low elevation angle pass of little over
4 degrees, or approximately - I stand corrected, 86 degrees,
the max elevation on this particular pass, almost directly
overhead, at Honeysuckle. Almost 9 minutes remaining in
this pass across Honeysuckle station. We'll stand by on
Skylab Control circuit for the Honeysuckle, followed by
Hawaii, and the next stateside pass. At 4 hours 18 minutes
ground elapsed time, this is Skylab Control.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 15:00 CST 16:57 GET 4:26 MC24/1
PAO
This is Skylab Control at 4 hours 28 minutes
ground elapsed time, as the Skylab workshop heads across the
south-central Pacific toward the Hawaii tracking station
coming up in about 8 minutes over that station. To reiterate
what was stated before about the current situation in the
Skylab-1 mission, preliminary telemetry playback indications
are there could have been a malfunction with one solar array
beam fairing. That is the cover that is - that houses the solar
array beam before it swings outward from the workshop itself.
And the meteroid shield, which could have led to the subsequent
anomalies that have been witnessed this afternoon. And, namely,
the failure of the large solar panels to properly deploy.
The malfunction was measured to have taken place 1 minute and
3 seconds after lift-off, based on examination of the telemetry
records and tapes played back post-launch. Now, the current
posture in the mission is as follows: the planned 28-day
mission is not possible without full deployment of the solar
panels on the workshop. At the same time, all the other work
shop systems and deployment sequences are fully nominal. Pro
ject officials are considering an alternate mission, using the
power supply aboard the command service module to augment, or
supply additional power to the workshop, through managing of
the various electrical buses aboard. The ATM solar panels are
deployed, and are generating power. This power supply, tied
with that brought up by the command module when it docks
with the workshop, would supply power for a reduced mission.
However, an announcement will be made as soon as a decision
on how the mission will be managed. This decision on alternate
mission is expected by about 9 o'clock Eastern Daylight Time.
Our news conference at Kennedy Space Center newsroom, with
Skylab Program Director, Bill Schneider, will take place at
this time. Five minutes out from Hawaii, and at 4 hours 32
minutes, ground elapsed time. This is Skylab Control.
END OF TAPE
SKYLAB MISSION COMMENTARY 5/14/73 17:12 CST 04:41 GET MC25/1
PAO
This is Skylab Control, 4 Hours 48 minutes,
ground elapsed time. Skylab space station now being tracked
by the Goldstone tracking station in the Mohave Desert,
California. No apparent change in the mission status at
this time. The large solar panels on the workshop still
undeployed. And among the considerations to be looked at
later in the evening by the Mission Director and other
members of management on the Skylab team, will be whether
or not to launch Skylab 2 on schedule tommorow, or to delay
the manned mission until some later time, after a new flight
plan for a shortened mission can be formulated and designed.
At 4 hours 49 minutes, this is Skylab Control.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 17:45 CST 05:14 GET MC26/1
PAO
This is Skylab Control, 5 hours 14 minutes,
ground elapsed time, in the mission of the Skylab space
station, presently over the Canary Island tracking station.
Some 3 minutes remaining until loss of signal, crossing
over into Ascension Island tracking station coverage. At
5 hours and 9 minutes, ground elapsed time, it was reported
that the Skylab workshop has settled down into solar inertial
attitude, that is, that the Apollo telescope mount portion
points at the Sun continuosly. To recap again the current
posture in this mission, it appears that a malfuntion
in one of the fairings covering the solar arrays on Saturn
workshop may have malfunctioned at about a minute and 3 seconds
after lift-off. Playback of the telemetry data has shown
that there was an apparent malfunction of this fairing, also,
the meteoroid shield malfunctioned at the same time. As
it stands now, the planned 28-day mission for Skylab 2,
still scheduled for launch tomorrow, at this time,
would not be possible for the full 28 days without deploy
ment of the workshop solar panels. Skylab program officials
are looking at all of the alternate missions that would be
feasible and possible to conduct. The main guiding factor
would be the amount of electrical power available from the
fully deployed, and presently generating Apollo telescope
mount solar panels, put together with the power available
from the command service module, when it docks with the
cluster. The decision on whether to continue with a some
what abbreviated mission tomorrow on schedule, or whether a
delay is necessary to regroup, will be made later in the
evening. Decisions on alternate missions, on an abbreviated
mission, is expected around 9:00 eastern daylight time. A
news conference with Skylab Program Manager, Bill Schneider,
is expected to take place at 9:00 o'clock eastern time at the
Kennedy Space Center newsroom. That is currently the status
in the mission of Skylab 1, the Skylab space station. And
at 5 hours 18 minutes, ground elapsed time, this is
Skylab Control.
END OF TAPE
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
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sdsp_skyl_000076
Title
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"Skylab Mission Commentary 5/14/73 1:10 CST 18:04 GET 5:32 MC27/1" - "Skylab Mission Commentary 5/15/73 1:20 CST MC38/1."
Description
An account of the resource
This mission commentary depicts the initial discovery of Skylab 1's Orbital Workshop Solar arrays not deploying as intended.
Creator
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United States. National Aeronautics and Space Administration
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-05-14
Temporal Coverage
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1970-1979
Subject
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John F. Kennedy Space Center
Skylab Program
Skylab 1
Apollo Telescope Mount
Type
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Transcripts
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Skylab Collection
Box 17, Folder 1
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14412/sdsp_skyl_000077_001.pdf
2d5a9acc6123c5f762d4a089ebb60f0e
PDF Text
Text
<=5*- I
SKYLAB MISSION COMMENTARY 5/14/73 1:10 CST 18:04 GET 5:32 MC27/1
PAO
This is Skylab Control at 5 hours 32 minutes,
ground elapsed time, in the mission of Skylab 1, currently over
the southern tip of the African continent. There's been a
change in the expected time of the press conference with Skylab Program Director, Bill Schneider, Cape Kennedy newsroom.
It will now be no earlier than 10 p.m. eastern daylight time,
instead of the earlier predicted 9 p.m. That is a 1 hour delay
in the press conference with Skylab Program Director, Bill
Schneider, at Kennedy Space Center newsroom. At 5:33, ground
elapsed time, this is Skylab Control.
END OF TAPE
SKYLAB MISSION COMMENTARY 5/14/73 18:45 CST 6:15 GET MC28/1
PAO
This is Skylab Control, 6 hours 15 min
utes into the mission of Skylab 1. A little over a minute, now,
until acquisition at the Hawaii tracking station. A matter of
interest on this pass on Hawaii will be some attitude ex
cursions that were noticed just as we left Honeysuckle
station, where the vehicle apparently drifted off inertial solar inertial attitude. As we come across Hawaii, the
gyros aboard the spacecraft and the spacecraft attitude
will be examined closely by telemetry to see if the vehicle
has returned to the desired attitude, or whether it's still
drifting. To repeat again an earlier announcement, the
press conference with Skylab Program Director, Bill
Schneider at Kennedy Space Center newsroom has been
delayed to no earlier than 10:00 p.m. eastern daylight time.
That would be 9:00 p.m. central. We'll stand by here as the
Skylab workshop attitude problem is sorted out during
this Hawaii pass and the subsequent stateside pass. At
6:16 ground elapsed time, this is Skylab Control.
PAO
This is Skylab Control. The guidance con
troller here in the control room has confirmed that the
vehicle has returned to solar inertial attitude. However,
there are some apparent problems in some of the gyros which
control the spacecraft attitude. Flight controllers are
continuing to sort out these problems at this time. Some
2 minutes remaining until we have loss of signal at Hawaii,
9 minutes out of Goldstone for a stateside pass on
this fourth revolution of the Skylab space station. At
6:19 and standing by, this is Skylab Control.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 20:15 CST 7:45 GET MC29/1
PAO
This is Skylab Control, 7 hours, 44 minutes
ground elapsed time. Skylab orbital workshop presently over
the Guam tracking station, with some 5 minutes remaining during
this pass over the Western Pacific. Skylab Program Director
Bill Schneider has issued the following statement. "The launch
of Skylab 2, the manned launch, has been recycled for 5 days
to Sunday, May 20, because of the incidents which occurred
during the Skylab 1 deployment. The recycling will permit
further evaluation of alternative flight plans to maximize
scientific returns from the Skylab mission." Program Director
Bill Schneider will hold a press conference at 9 p.m. central
daylight time at Kennedy Space Center newsroom. At the Houston
end, the Flight Director, who has been on the flight director
console during most of the day, Don Puddy, will take part in
the small briefing room in the building 1 news center at Johnson
Space Center. To repeat the statement issued by Skylab Program
Director Bill Schneider: "The launch of Skylab 2
has been recycled for 5 days, to Sunday, May 20, because of
the incidents which occurred during Skylab 1 deployment. This
will permit further evaluation of alternative flight plans to
maximize scientific returns from the Skylab mission." Some
45 minutes away from the press conference, 9 p.m. central,
10 p.m. eastern daylight time, with participants at Houston
and Kennedy Space Center. We understand that the prime crew
of Skylab 2, will return to Houston tomorrow. At 7 hours 47
minutes, ground elapsed time, this is Skylab Control.
END OF TAPE
SKYLAB MISSION COMMENTARY 5/14/73 20:47 CST 08:15 GET MC30/1
PAO
This is Skylab Control, 8 hours
15 minutes, ground elapsed time, in the Skylab 1 mission.
Skylab orbital workshop presently over the Texas tracking
station, nearing the end of the fifth Earth orbit. Re
minder to newsmen, both at Kennedy Space Center and Houston,
some 15 minutes away from a press conference, which will have
participants at both ends, Houston-Cape line. Skylab
Program Director Bill Schneider will be at Kennedy Space
Center; Flight Director Don Puddy and Gene Kranz, who's
chief of the Johnson Space Center Flight Control division
will take part in Houston. The oncoming Flight Director,
Milt Windier, went around the room, talking to the flight controllers
and asking them to examine ways to get the most out of
a reduced power situation for the modified mission, which
will be resumed on the delayed launch of Skylab 2. To
repeat the earlier statement by Skylab Program Director
Bill Schneider, "The launch of Skylab 2 has been
recycled for 5 days to Sunday, May 20, because of the
incidents which occurred during Skylab 1 deployment. This
will permit further evaluation of alternative flight plans to
maximize scientific return from the Skylab mission." The prime crew
for Skylab 2 will return to Houston, Tuesday morning. Thirteen
minutes until the press conference starts and at 8 hours
18 minutes, ground elapsed time, this is Skylab Control.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 23:00 CST MC31/1
PAO
This is Skylab Control. Ten hours
30 minutes ground elapsed time. The mission of Skylab 1
presently off the southern tip of the African continent and
the island of Madagascar. At the beginning of the seventh
earth orbit or revolution, which ever term you prefer.
The cabin pressurization sequence, which had been underway, has
been terminated for the time being to allow some thermal
responses to balance out. We have no estimate yet as to
when the pressurization will be resumed. But at the time the
sequence was stopped over the Vanguard tracking ship which
is hove to off the southeast coast of South America, the
pressure was at 1.9 pounds in the habitable area of the Skylab
space station. We're some 51 minutes out now from the next
station which will be Goldstone. The next two REVs, there
will be only Hawaii and Vanguard which will track the space
craft. Flight director Milt Windier is having numerous
conversations with the individual flight controllers and
sorting out how best to manage the resources available. Still
tracking the gyro problems in the ATM guidance system. And
at 10 hours 32 minutes ground elapsed time this is Skylab
Control.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/14/73 2350CST MC32/1
PAO
This is Skylab Control at 11 hours 20 min
utes. During the last few minutes here in Mission Control,
Flight Director Milton Windier has accepted a recommendation
from the Marshall Space Flight Center to make an attitude
change in the Skylab workshop. This change will, in effect,
change the attitude or the angle at which the Sun is shining
on the side of the workshop. Now what we're finding is that
as a result of the loss of the micrometeorite shield or panels,
the thermal characteristics of the workshop now are different
than had been planned. Normally, with those micrometeorite
shields in place, they are coated with a coating that reflects
sunlight. The workshop itself is not coated with the same
reflective materials. Consequently, the amount of solar energy
absorbed is higher and we're watching an increase in the
temperature. There is no concern in that temperature increase
at the present time, but in order to keep it from going beyond
acceptable limits, the workshop will be placed in an attitude
that directs the Sun more toward the end of the vehicle, the
end at which the command module would be docked once the
rendezvous and docking is accomplished. At the present time,
the workshop is in an attitude with the Sun shining directly
on the solar panels of the ATM, the Apollo telescope mount,
this also places the Sun shining directly on the side of the
workshop. The plan is to pitch up about 90 degrees, again
placing the Sun more toward the end of the multiple docking
adapter, to stay in this attitude for one revolution and then
to pitch back 45 degrees in a compromise attitude which con
tinues to reduce the amount of solar energy absorbed by the
workshop, but also places the solar panels in more of an
opportune position to provide the electrical current necessary
for operating the vehicle and reducing any unnecessary drain
on the batteries. This maneuver is going to be performed over
Goldstone. We're about 15 seconds now from regaining radio
contact with the workshop over the Goldstone tracking station.
It will take about 13 minutes maneuvering with the attitude
control system to place the vehicle in the desired attitude.
We're standing by for confirmation that the attitude change
has begun. We expect that to begin momentarily. This is
Skylab Control, we have a relatively low elevation pass over
Goldstone; we're waiting for a good solid telemetry lockup
before the command is initiated to begin that attitude change.
We're getting solid data now and we're getting a recommendation
to go ahead and attempt to command the attitude change. We
have about 1-1/2 minute of acquisition remaining at Goldstone.
Once this command is initiated, the 13 minute maneuver is an
automatic maneuver. This is Skylab Control, we've had loss of
signal through Goldstone without getting the command initiated
to make that attitude change. We did not get the solid data
from the ATM that we thought we needed to initiate that maneuver,
and we'll take a look at the situation over Vanguard, how
ever, scheduled to acquire there in about 17 minutes. And
we'll attempt to get the necessary data lockon and get
the command initiated at that point. This is Skylab
Control at 11 hours 31 minutes.
END OF TAPE
�SKYLAB I MISSION COMMENTARY 5/15/73 CST 00:15 GET 135:05:15 MC-33/1
PAO
This is Skylab Control at 11 hours
45 minutes. Now, we have reacquired the workshop over the
tracking station at Vanguard. And, we're standing by to
confirm we've got good data. Valid data will allow flight
controllers here in Mission Control to send the proper
command to initiate an attitude change maneuver. This maneuver
again will be - it's about a 13 minute maneuver using the
thruster attitude control system on the workshop. Pitching
up 90 degrees, this will change the angle at which the Sun
is striking the side of the workshop, an attempt to control
the temperatures in the vehicle. We do now have confirmation
that we've got attitude data, and that the attitude looks good
on the orbital workshop.
PAO
We've got a confirmation now of good
solid lockup on the data.
PAO
This is Skylab Control. We again have
intermittent data and Flight Director Milton Windier has
elected to hold the maneuver until we've got solid data.
We have about 6 minutes remaining in this pass over the
tracking ship Vanguard.
PAO
This is Skylab Control. We have a
little less than 1 minute of acquisition time remaining over
Vanguard. And, we have not at this point resumed solid
enough data lock to go ahead with the commanded maneuver
change for the workshop. And we will be reacquiring in
about an hour at Hawaii. During this pass over Vanguard,
the instrumentation communications engineer has been going
through a number of troubleshooting procedures to determine
the nature of the data problem, to tie it down to either an
onboard or a ground station problem, and to determine
the proper workaround, as they say. And we now show that
we've had loss of signal at Vanguard, we're predicting
acquisition at Hawaii in 58 minutes 26 seconds. This is
Skylab Control at 11 hours 55 minutes.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/15/73 01:26 CST 12:56 GET MC34/1
PAO
This is Skylab Control at 12 hours
56 minutes. We have now acquired the orbital workshop on
its eighth revolution over the Hawaii tracking station.
We have good solid data and we've commanded the start of
the maneuver which will change the spacecraft attitude the workshop attitude for improved thermal control. And
that maneuver is scheduled to require about 13 minutes.
We have a report that it is progressing smoothly at this
time. And we have about 4 minutes 45 seconds of acquisition
remaining at Hawaii. We will be reacquiring at Vanguard
about 21 minutes after we lose contact in Hawaii. The
attitude control change, the attitude change that is
being made at this time, is to place the Sun more end - on
to the spacecraft. The normal attitude has the ATM, the
Apollo telescope mount, solar panels pointed directly at
the Sun. This also has the Sun shining directly on the
side of the orbital workshop. Without the micrometeoroid
panels, which have a thermal coating on them to reflect
solar heat - solar energy, we're finding some increases
in temperature within the workshop. As a means of getting
an assessment of this temperature increase and controlling
it, the attitude change is being made. The plan is to
leave the spacecraft in the pitched up attitude, pitching
up 90 degrees from the present attitude, leaving it in this
position for 1 revolution; then pitching back to an atti
tude midway between the initial attitude and the pitched
up attitude and holding it there for one revolution, and
then returning to the normal attitude with the ATM solar
panels again pointed directly at the Sun. This maneuver
is being accomplished with the thruster attitude control
system, controlled by the ATM.
pAO
This is Skylab Control. We've lost
radio contact now with the spacecraft as it passes over
the horizon from the Hawaiian tracking station. And we'll
be reacquiring in about 20 minutes over the tracking ship
Vanguard in the south Atlantic off the coast of South
America. Over Hawaii we had good solid data. We commanded
the orbital workshop to begin an automatic attitude change.
That maneuver was progressing smoothly as we lost radio
contact. It will go to completion. The total maneuver
is scheduled to take about 13 minutes, and we'll be able
to confirm the new attitude over Vanguard. At the present
time, our plan is to discontinue commentary operations
following the Vanguard pass. The Houston News Center is
scheduled to reopen at 6 a.m., at which time commentary
operations will be resumed. This is Skylab Control at
13 hours 4 minutes.
END OF TAPE
�SKYLAB I MISSION COMMENTARY 5/15/73 CST 02:20 GET 13:32 MC-35/1
PAO
This is Skylab Control. The orbital
workshop now is starting its 9th revolution of the Earth.
And, we've just completed a 9 minute pass over the tracking
ship Vanguard. During that pass we received solid telemetry
data from the spacecraft, and verified that the vehicle had
maneuvered to the desired attitude, pitching up 90 degrees
from the normal attitude at which the ATM solar panels
are pointed directly at the Sun. The new attitude has the
multiple docking adapter end of the vehicle pointing at the
Sun. The ATM solar panels are parallel to the Sun's rays
and receiving little or no solar energy. During this period
of time, the vehicle is being powered from stored battery
power. We plan to stay in this attitude for 1 revolution,
allowing the temperatures to drop on the orbital workshop.
These temperatures running higher that normal, due to the
apparent loss of the meteoroid panels, which in addition to
protecting against meteoroid impacts, also have an effect on
the way in which the vehicle absorbs and radiates thermal
energy from the Sun. And we're seeing, consequently, an
increase in temperatures. Engineers here in the Control
Center and in the Marshall Space Flight Center are interested
in watching the temperature curve as the temperatures come
back down to determine the total amount of thermal energy
absorbed by the workshop. During this period of time,
the pressurization of the orbital workshop has been terminated;
we're holding at 2 pounds internal pressure. And once
we've gotten a better indication of what the total thermal
energy absorbed by the workshop is, we'll continue that
pressurization up to the desired 5 pounds per square inch.
The plan again, is to hold at the current attitude for
1 revolution and then to pitch up to an intermediate atti
tude where we're about 45 degrees pitched up instead of the
current 90 degrees. At a 45 degree angle, it'll be a compro
mise attitude with some solar energy being supplied striking
the solar panels, and a portion of the energy, still supply
electrical energy still supplied by the batteries, staying
in this attitude for 1 revolution before returning to the
normal attitude with the ATM solar panels pointing directly
at the Sun. At this time we will terminate commentary
operations. The Houston News Center will also be closing
at this time. We will be reopening at 6 AM. This is
Skylab Control at 13 hours 36 minutes.
END OF TAPE
�SKYLAB I MISSION COMMENTARY 5/15/73 CST 06:53 GET 18:23 MC-36/1
PAO
This is Skylab Control. Eighteen hours,
23 minutes since Skylab 1 lift-off. Skylab attitude control has
just been shifted to the control moment gyros. Skylab now over
the Vanguard tracking ship on the 12th revolution of the
Earth. Prior to this time, attitude control has been provided
by the thruster attitude control system, the RACS. The
control moment gyros are fully spun up now, and just a few
minutes ago, additive control was transferred to the gyros.
Temperatures on structural members in the orbital workshop continue
to run near or slightly in excess of 100 degrees. The
orbital cluster was taken out of the solar inertial attitude
for two revolutions during the night to allow readings from
several temperature sensors which had gone off the scale.
This temperature data is being used by the Marshall Space
Flight Center in a thermal model in an attempt to determine
how serious the problem is and to develop a plan to manage
the thermal profile. Skylab, now, is back in a solar inertial
attitude. The ATM telescope is unpowered at the present time,
and the cluster pressure is holding at 1.9 pounds per square
inch - decision having been made that there is no reason
at this time to go to the full 5-PSI pressure. At 18 hours
25 minutes, ground elapsed time, this is Skylab Control.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/15/73 7:35 CST 19:05 GET MC37/1
PAO
This is Skylab Control at 19 hours
4 minutes since Skylab 1 lift-off. Flight director
Neil Hutchinson, who has been leading the overnight shift
of flight controllers monitoring the Skylab workshop,
will hold a status briefing in the small briefing room
at the Johnson Space Center News Center at 8:15 a.m. central
daylight time; 8:15 a.m. central daylight time, briefing
by Neil Hutchinson, flight director on the overnight shift.
We've been informed that the Skylab 2 crew plans to leave the
Kennedy Space Center at 9 a.m. central daylight time for
their return to Houston. This is Skylab Control.
END OF TAPE
�SKYLAB MISSION COMMENTARY 5/15/73 1:20 CST MC38/1
PAO
This is the Skylab News Center at KSC.
The engineering investigation of the inflight anomaly for
Skylab and the effect on subsequent mission activities
continues at the Marshall Spaceflight Center in Huntsville,
Alabama. No new information has been uncovered which
reveals the cause of the failure of the micrometeoroid
shield during launch and the apparent subsequent fouling
of the workshop solar array. The data continues to be
analyzed by the engineering team. The data is somewhat
incomplete in real time, since some of the events occurred
between station passes and the tape telemetry data must be
dumped at a ground station, processed and then analyzed.
The analysis of the thermal and electrical systems effects
continues on an intensive basis. The ATM solar arrays
continue to work properly and there is no significant change
in the status of the workshop solar panels. They are still
in a partially extended position with no new estimate of
the extent of their deployment. The thermal condition of
the spacecraft is more troublesome than had been anticipated
last evening. The meteoroid shield, in addition to providing
a protection against small punctures, was painted in such
a manner to provide a temperature balance in the spacecraft
on the external skin. The two effects have been found to
have contradictory mission requirements; that is to maximize
the electrical power available, it's desired to point the
solar arrays at the Sun constantly; however, this is the
cause, this causes the skin of the now unprotected OWS to
heat up excessively. Engineering evaluation and computer
analysis is currently under way to find an optimum combina
tion of solar oriented and nonsolar oriented orbit. The
flight support team at JSC and MFSC, that's Johnson Space
Center and the Marshall Space Flight Center, are continuing
in their tasks of trying to develop an optimum flight plan
for Skylab 2. Obviously the experiment activity which will
be possible depends upon the resolution of the electrical
and thermal questions. These resolutions are expected prior
to the launch of Skylab 2 now scheduled for Sunday, May 20,
1973, at approximately 11 a.m. eastern daylight time.
Preparations at the Kennedy Space Center are proceeding
accordingly. By Saturday afternoon a full understanding
of the technical situation will be available and an assess
ment of the mission impact will be made. The decision to
launch or not to launch will be made at that time. Skylab
Program Director, William Schneider, will be available at
the Kennedy Space Center auditorium for a brief news con
ference at 3 p.m. eastern daylight time today, that's a little
over a half an hour from now. The Skylab Program Director,
William Schneider will be available for a brief news
conference at the News Center at KSC today.
END OF TAPE
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
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sdsp_skyl_000077
Title
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"Skylab Mission Commentary 5/14/73 1:10 CST 18:04 GET 5:32 MC27/1" - "Skylab Mission Commentary 5/15/73 1:20 CST MC38/1."
Description
An account of the resource
This mission commentary depicts NASA's attempts to alleviate some of the temperature issues caused by the broken micrometeoroid shield on Skylab 1.
Creator
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United States. National Aeronautics and Space Administration
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-05-14
Temporal Coverage
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1970-1979
Subject
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John F. Kennedy Space Center
Skylab Program
Skylab 1
Apollo Telescope Mount
Multiple docking adapters
Manned Spacecraft Center (U.S.)
George C. Marshall Space Flight Center
Type
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Transcripts
Text
Source
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Skylab Collection
Box 17, Folder 1
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
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en
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14413/sdsp_skyl_000078_001.pdf
761f456bfafd9abffa9d0b4f8a0e7c0f
PDF Text
Text
SL II MC 1/1
Time: 6:32 a.m. CDT, T-01:25:00 GET
5/25/73
L
PAO
This is Skylab Launch Control T minus
1 hour 25 minutes and counting. Just completed at the T minus
1 hour and 30 minute mark were a simulated first motion signal
test. During this test the simulated signal indicating first
motion is sent to the Eastern Test Range and also to the
Mission Control Center in Houston. During the actual lift-off
this first motion signal starts the countdown clock in the
plus time at those two areas. Recently completed were checks
of the emergency detection system. This is a system that is
designed to sense and react to any emergency situation resulting
from a launch vehicle malfunction during the early portion of
the powered flight. During most of the first stage flight the
EDS, as it's called, provides the capability for automatically
aborting the mission. The auto abort system is turned on at
lift-off and disabled by the crew about 2 minutes into the flight.
The system senses such things as loss of thrust in first stage
engines or excessive rates in pitch or yaw. The test takes
about 30 minutes, it's conducted with the spacecraft commander,
Pete Conrad, and the launch vehicle people here in the firing
room. During the test, simulated emergency conditions are sent
to the vehicle and lights in the spacecraft light indicating
what the nature of the emergency is. We have one more hold
planned in the countdown, that's at the T minus 15 minute
mark. Nominally that will be for 2 minutes duration. AT that
time the clock will be updated to correspond with the orbiting
Skylab overhead. The close out crew at the white room area
is securing now for their cabin purge and leak checks. Every
thing continues to move along smoothly there. Now for a status
report from the Mission Control we go to Houston.
PAO
This is Skylab Control at Houston at
minus 1 hour 24 minutes and continuing with the count. In the
Mission Control Center two teams of flight controllers now on
station at their consoles proceeding toward the launch of
Skylab 2. The crimson team of flight controllers headed by
Flight Director Don Puddy managing the orbital workshop systems,
and the purple team headed by Flight Director Phil Shaffer,
which will be in control for the manned launch and rendezvous
phase of the flight. The Saturn workshop is presently in an
orbit of 239 nautical miles by 234 nautical miles. An average
workshop cabin temperature now reading 120 degrees. At the
time of ignition, the workshop will have passed directly
overhead and should be approximately 780 nautical miles downrange at the time of ignition. Flights Dynamics advises that
Skylab 2 will be launched with an azimuth of 47.58 degrees.
CAECQM^for our launch will be Astronaut Dick Truly.... We're at
1 hour 23 minutes, continuing with the count at Mission Control
Houston, this is Skylab Control.
END OF TAPE
�SL-II MC2/1
Time: 07:02 a.m. CDT, T-00:55:00 GET
5/25/73
PAO
This is Skylab Launch Control we're at
T minus 55 minutes and counting. T minus 55 and counting in
the first manned mission in the Skylab program. The closeout
crew at the pad is now clearing the pad area. Before leavinq,
the pad leader confirmed that the white room area had been com
pletely secured, all loose equipment removed and stowed and
the tool and supply cabinet secured. There is an environ
mental control hood which attaches between the white room
area and the spacecraft. That's also now been secured. He
reported back that the white room now ready for swing arm
retract. This will happen at the T minus 45 minute mark in
the countdown and actually the swing arm will come back to
what is called the 12 degree position. This is the standby
or park position. And it will remain there until the final
minutes in the launch. At T minus 5 minutes it will swing
back to the fully retracted position. Also underway at this
time the superintendent of range operations calling in to
Bill Schick the Test Supervisor indicating that the launch
danger area has been declared clear for a launch. In the
spacecraft itself pilot of the mission, Paul Weitz been working
with ground controllers on spacecraft communications fre
quency and power readouts. Weitz selected as an astronaut in
1966 was a member of the astronaut support crew for Apollo 12.
That Apollo 12 mission also commanded by Pete Conrad. Weitz
^ \,degree tn aeronautical engineering. He's a Commander
in the Navy with approximately 4000 hours of flying time.
Our weather at this time is generally cloudy in the launch
area, however, some of that cloud is expected to dissipate
during the next hour. For launch time the weather men are
predicting broken clouds. These will be in several layers.
5 5uPSv.°
upper layers expected to be about 15,000 feet
and the base of the lower layer is about 6,000 feet. Winds
at launch time are expected to be approximately 10 knots from
the southwest and the temperature about 78 degrees Fahrenheit.
Closeout crew now cleared the area. T minus 53 minutes
40 seconds and counting this is Kennedy Launch Control.
END OF TAPE
�SL-II MC3/1
Time: 07:13 a.m. CDT, T-00:45:00 GET
5/25/73
PAO
This is Skylab Launch Control; we're at
T minus 45 minutes and counting. We'll expect the swing arm
to be retracted shortly. Mark there comes the swing arm,
moving back to the park position; this is a 12 degree
park position, approximately 10 to 15 feet from the vehicle.
It will remain there now until approximately 5 minutes in the
countdown, and at that time it will be moved back to the full
retract position. Also underway at this time are interroga
tions of the C-band beacons. These are two beacons aboard the
instrument unit of the vehicle. During this test these are
simply checked, the beacons are checked to insure that they
are being tracked and will be tracked during the powered phase
of flight. During powered flight the beacons give position
data as well as speed and acceleration. Now that the swing
arm has come back, the launch escape system atop the command
module will be armed. Stoney, Astronaut Bob Crippen, will
position the mobile launcher elevators at the 320-foot level
in what is called the egress mode. The - Bob Crippen is the
Astronaut communicator name that is called, he is called
Stoney, will be in the Launch Control Center. Crippen was
also a member of the crew which entered the altitude chamber
for the Medical Experiments Altitude Test, 56-day test run in
Houston last July. A short time from now we expect the
science pilot, Joseph Kerwin. We'll begin arming the service
module reaction control system. To do this, he actually opens
valves and allows the hypergolic fuels to flow down through
the lines down to the engines. The countdown has proceeded
very smoothly this morning. Now at T minus 43 minutes 4 sec
onds and counting, this is Kennedy Launch Control.
END OF TAPE
�SL-II MC4/1
Time: 07:30 a.m. CDT, T-00:27:00 GET
5/25/73
PAO
This is Skylab Launch Control. T-27
minutes 59 seconds and counting. Preflight command system
tests for the mission control center in Houston have just
been completed. Also just completed at this time was a final
level adjustment of RPl, the fuel used in the first stage.
RP1 is actually loaded prior to the countdown demonstration
test and replenished last night before cryogenic loading.
This level adjustment made here during the final hour of the
count is necessary to take into account temperature and
humidity and to assure us a full flight load. Cryogenic
loading of course, also completed earlier this morning
and topping continues. The astronaut crew completing their
preflight check list in the command module at this time. Now
we'll switch to Houston for a status from the Mission Control
Center.
PAO
This is Skylab Control Houston at
-27 minutes and counting. Flight director Don Puddy of the
workshop team is going around the Horn with his team in the
mission control center for a GO/NO GO for Skylab launch
based on orbital workshop data. Given a GO at this time
for the launch of Skylab II. The workshop is now passed out
of range of the Honeysuckle tracking station. The next
station to acquire will be Texas on this the 156 revolution.
Meanwhile the Shaffer team of flight controllers has been
given a GO for the start of the terminal count which
is now in progress. The displays of mission control center
in Houston now selected for the launch of Skylab II. At
-26 minutes and continuing with the count, this is Skylab
Control Houston.
SL II MC 5/1
Time: 7:36 a.m. CDT, T-00:21:59 GET
5/25/73
pAO
This is Skylab Launch Control passing
the T minus 22 minute mark in the countdown for the first
manned mission in Skylab. Science Pilot Joseph Kerwin at
this time reading out temperatures, pressures, and quantities
in the service module reaction control system quadrant. Cryo
genic fuels aboard the launch vehicle continue to be topped.
We have one more hold as we aim toward our 9:00 a.m. lift-off.
That's a nominally 2 minute hold and we're coming to the T minus
15 minute mark. Our countdown continuing to go smoothly at
this time, T minus 21 minutes 30 seconds and counting, this
is Kennedy Launch Control.
END OF TAPE
�SL-H
MC6/1
Time: 07:42 a.m. CDT, T-15 min GET
5/25/73
PAO
This is Skylab Launch Control we're now
at the 15 minute mark in the count, T minus 15 minutes and
holding this is a planned hold period nominally for 2 minutes.
It's a final clock adjustment to assure lift-off at the
proper time in conjunction with the orbiting Skylab overhead.
Interrogation of radar beacon number 1 has just been com
pleted. When we come out of this hold at the T minus 15 min
ute mark the spacecraft will go to full internal power.
Actually the fuel cells have been supporting the spacecraft
at this time but they have also had a backup of ground support
power. In the command module the crew completing their checks
They actually on their display panels have some 24 instru
ments, 566 switches, 40 event indicators and over 70 lights.
Inside the command module they have approximately 70 cubic
feet per man. This is a little larger. A little more room
than one would have in a compact car. Once they get into
Skylab, however, that will change considerably. They will
actually have about 59 times the volume in Skylab that they
have to work in in the command module. At this time Stony,
the astronaut communicator Bob Crippen here in the Launch
Control Center, the Launch Operations Manager, Paul Donnelly
and the Spacecraft Test Conductor, Bob Reed have switched to
the astro launch circuit for communications checks. This is
the circuit which will be used by the astronaut crew and these
members at launch time. When he came aboard this morning
Astronaut Pete Conrad commented that he hoped the launch team
planned to blow the clouds away by 9 a.m. The clouds, in fact
are breaking up somewhat at this time. Bob Reed, the Space
craft Test Conductor, indicated that if the clouds weren't all
blown away he was sure that they would do it as they lifted
off. We're preparing to pick up the countdown now. Mark
T minus 15 minutes and counting. This is Kennedy Launch
Control.
SL-II MC7/1
Time: 7:47 a.m. CDT, T-00:10 GET
5/25/73
crew now making some quick voice
Cryogenic topping continues.
Swing arm number 9 in the standby position. It will be moved
back to the full retract at T-5 minutes. Now T-10 minutes
42 seconds and counting. This is Kennedy Launch Control.
PA0
qw?niVn
The
their
END OF TAPE
aj
;troccT circuit-
�SL-II MC8/1
Time: 7:49 a.m. CDT, T-9 min GET
5/25/73
PA0
This is Skylab Launch Control crew finish
ing up now in their checks on communications. Launch Oper
ations Manager Paul Donnelly wishing the crew good luck,
God's speed and good sailing. Now T minus 9 minutes 47 seconds
and counting this is Kennedy Launch Control.
SL-II MC9/1
Time: 7:54 a.m. CDT, T-7 min GET
5/25/73
PAO
This is Skylab Launch Control we're passing
the 6 minute mark in the countdown now. Various personnel now
reporting in to the spacecraft test supervisor Bill Schick that
they are ready and GO for launch. Bob Reed the spacecraft
test conductor has indicated that the spacecraft is GO. Launch
operations manager Paul Donnelly reports GO and the director
of launch operations Walter Kapryan also has reported GO for
a launch. Final computer programs are now being run to
place the launch vehicle in a launch mode. In the space
craft the final action to be taken there will be at the
T minus 4 minute mark. Paul Weitz will turn on the spacecraft
batteries and at T minus 45 seconds, the last action to be taken
by the crew will be taken by Pete Conrad when he makes a final
guidance alinement. We're coming up now to the 5 minute mark.
At that time the swing arm, swing arm number 9 will come back
to the full retrack position. Actually for the Saturn-IB
there are only 5 swing arms. The number 9 designation comes
from the earlier launches using this same mobile launcher,
using the Saturn-V. Swing arm now coming back to the full
retrack position. It will remain in that full retrack position now for the rest of the countdown. At T minus 3 minutes
and 7 seconds the count will go on the automatic sequencer
and will be carried out automatically from that time on. Now
at T minus 4 minus 39 seconds and counting this is Kennedy
Launch Control.
END OF TAPE
�SL-II MC-10/1
Time; 7;57 a.m. CDT, T-3 min GET
5/25/73
PAO
This is Skylab Launch Control. The
launch sequence has started. We're now on the automatic
sequencer, and the countdown will be run now by that automatic
sequencer. The number of functions are carried out by the
sequencer, and they must be carried out in the proper order,
or they would be automatically shut down. Also, at the same
time, the launch crew here in the firing room will continue
to monitor their various readout temperatures, checking the
gages for pressures and rates. They could override the
sequencer if necessary. At the T-3 minute and 6 second
mark, the automatic sequencer terminated the liquid oxygen
and liquid hydrogen replenishing. These cryogenic fuels
have been being replenished since fueling was actually
completed early this morning. After this termination the
fuel tanks will be pressurized. Actually pressurization has
now started. The second stage liquid oxygen tank has now been
pressurized, and the first stage fuel tank also has been
pressurized. Now passing the 2 minute mark in the countdown.
The vents closing and the pressurization is taking place on the
2 stages of the Saturn IV. At the T-l minute 15 second
mark, Paul Weitz will trip two switches in the command module,
placing the spacecraft batteries on line. These batteries
will give added support to the fuel cells and also act
as a backup to the fuel cells. Fuel cells also on line at
this time. T-l minute 30 seconds and counting. Our count
down continues to go smoothly. Also during the automatic
sequence we'll switch to internal power. We've been carrying
the power from a ground source up to this point to save on
the flight batteries. At T-50 seconds in the count, we'll
switch to internal power and stay on internal power for
the remainder of the count. We are approaching the 1 minute
mark in our countdown. MARK T—
END OF TAPE
�SL-II MC-11/1
Time 08:01 a.m. CDT, T-l min GET
5/25/73
PAO
Countdown MARK; T-l min., 1 minute and
counting in the launch of the first manned mission in Skylab.
T-50 seconds, T minus 50 seconds, and cb76g. And we are
now going to internal power, all stages switching to internal
power, stages now and fuel tanks pressurized. Approaching
the 30-second mark in countdown. At 30 seconds water will
begin spraying on the deck of the mobile launcher. T minus
30 seconds, and the countdown continuing to go smoothly. The
Skylab, itself, orbiting some 780 nautical miles northeast
of KSC, at this time. T-17 seconds and counting, T-15. At
T-3.1 second we'll expect the engine sequence to start on the
vehicle. T-7, 6, 5, 4, 3, engine sequence start, 2, 1, 0. We
have launch commit and we have lift-off. The clock is running
and Skylab has cleared the tower.
SC
Tower and Houston, Skylab II, we fix
anything, we've got a pitch and a roll program.
PAO
Houston is now controlling.
cc
The thrust is going all engines.
SC
Boy, is that a smooth ride.
PAo
Twenty five seconds pitch and roll program
started. Skylab now maneuvering to its proper flight path
attitude. MARK 35 seconds, 1 nautical mile in altitude.
Given a green by-range safety. MARK 45 seconds, cabin pres
sure relieving, adjusting now from sea level to a space
environment. MARK 50 seconds, 2 nautical miles in altitude.
SC
And roll is complete, Houston.
CC
Roger. Standby for mode-1 BRAVO. MARK,
1 BRAFG
SC
Roger. Propellant ... as RCS ...
CC
Roger.
PAO
MARK, 1 minute 8 seconds roll program
completed
CC
Skylab, Houston, you're feet wet.
SC
Roger, feet wet.
PAO
That call out from Capcom Dick Truly,
says Skylab, now, capable of water landing. One minute,
20 seconds, passing through the period of maximum aerodynamic
pressure on the vehicle. One minute 25 seconds, 8 nautical
miles in altitude. MARK, 1 minute 35 seconds pass through
MAX Q, Skylab still flying steady on all 8 engines.
SC
JEDS (garble) engine, launch vehicle rates
are all off.
...
CC
Roger, stand by for mode 1 Charlie. MARK,
your 1 mode, Charlie.
SC
1 Charlie.
�SL-II MC-11/2
Time: 08:01 a.m. CDT, T-l min GET
5/25/73
PAO
The status check in mission control by
Flight Director Phil Shaffer, a GO no GO for staging. Given
a GO, for staging.
CC
You're GO for staging, you're looking
good.
PAO
MARK, 2 minutes, 6 seconds, 21 nautical
miles in altitude, 20 nautical miles downrange, velocity now
reading, 5947 feet per second. Coming up now on staging and
shutdown.
PAO
Center engine shutdown. Seven outboards
out.
SC
All right, I've got an S-IVB light
Houston, and a nice staging.
CC
Roger, that.
PAO
MARK, 2 minutes, 35 seconds, staging on
schedule. Conrad, Weitz, Kerwin, now riding on a good second
stage engine. Coming up now a luanch escape tower jettisons.
SC
4-B.
SC
Tower jet on time.
CC
Roger, tower jettison, you're mode 2.
PAO
MARK, 3 minutes, 2 seconds, 47 nautical
miles in altitude. The launch escape tower now ejected,
reports Conrad, his crew safety roll no longer required.
Three minutes 12 seconds, 50 nautical miles in altitude, 84 naut
ical miles downrange. Velocity now reading 8200 feet per
second.
PAO
3 minutes, 25 seconds, the first stage in
launch escape tower both falling away now, headed for their
own splash downs. Meanwhile, Conrad, Weitz, Kerwin, now at
58 nautical miles. The Skylab continuing to climb, moving out
well beyond the Earth's armosphere.
SC
Okay. Houston, the computer looks good
here.
CC
Roger, we concur, CMC's go.
PAO
3 minutes 58 seconds, 66 nautical miles
in altitude, 140 nautical miles downrange.
CC
Houston, looking good, GO at 4 minutes.
SC
And we're GO, here, Houston.
PAO
MARK, 4 minutes, 15 seconds, now at
71 nautical miles in altitude, 167 nautical miles downrange,
Skylab's onboard performance continues smooth. Onboard
reading show, Conrad, Weitz, Kerwin with their computer in
program 11, the earth orbit insertion program, ticking off
their own altitude velocity. Velocity now reading, 9852 feet
per second. MARK, 4 minutes 40 seconds, 77 nautical miles in
altitude, at 199 nautical miles downrange. Flight Director
Phil Shaffer pulsing his flight team, looking good.
�SL-II MC-11/3
Time: 08:01 a.m. CDT, T-l minute GET
5/25/73
CC
Skylab, Houston. You're GO in five
minutes, set your trajectories right on the nominal.
SC
And, we're go here, Houston, looks good
in here.
CC
Roger.
PAO
MARK, 5 minutes, 10 seconds, 82 nautical
miles in altitude, 244 nautical miles downrange. A trajectory
data in mission control looking good. Skylab now threading
the eye of the desired flight path orbit. We're at 5 minutes,
22 seconds, 11,326 feet per second, now traveling Skylab.
PAO
MARK, 5 minutes 35 seconds. Skylab now
85 nautical miles in altitude. Skylab*s climb for altitude
now essentially complete, moving out now for downrange dis
tance. Conrad, Weitz, Kerwin, now flying almost parallel to
the Atlantic below in a heads down position. We show a downrange distance of 312 nautical miles.
CC
Skylab, Houston, you can GO at 6 minutes.
SC
Roger, we're GO up here.
CC
Roger.
PAO
MARK, 6 minutes, 10 seconds, that GO
given by Capcom Dick Truly. Responding spacecraft commander
Pete Conrad. We now show Skylab at 88 nautical miles in
altitude, 362 nautical miles downrange.
SC
(Garble), Houston. Standby to GIMBAL
motors at 7.
CC
Roger.
PAO
MARK, 6 minutes 45 seconds, Skylab
velocity building up now, now reading 14,538 feet per second.
Conrad, Weitz, Kerwin, traveling almost parallel to the
east coast of the United States, the most northerly powered
flight in the space for astronauts, thus far.
CC
Skylab, Houston. We're go at 7 minutes.
SC
Okay, Houston, 4 good Gimbal motors, then
we're GO at 7.
CC
Roger, copy.
PAO
MARK, 7 minutes 25 seconds, 89 nautical
miles in altitude, 522 nautical miles downrange now for
Skylab, velocity now reading 16,709 feet per second.
SC
Hey, do we just have - We just have
PU shift, Houston?
CC
Roger, we concur and you're GO at 8 minutes.
SC
Okay.
PAO
MARK, 8 minutes 10 seconds, a good
propellant and utilization shift, says Booster Engineer, giving
a change in fuel oxidizer ratio of - for more efficient engine
performance in space. We show 87 nautical miles in altitude,
665 nautical miles downrange. Velocity now reads 19,605 feet
per second.
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
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sdsp_skyl_000078
Title
A name given to the resource
"SL II MC 1/1 Time: 6:32 a.m. CDT, T-01:25:00 GET 5/25/73" - "SL-II MC-11/3 Time: 08:01 A.M. CDT, T-1 minute Get 5/25/73."
Description
An account of the resource
This mission commentary depicts the Skylab 1 launch.
Creator
An entity primarily responsible for making the resource
United States. National Aeronautics and Space Administration
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-05-25
Temporal Coverage
Temporal characteristics of the resource.
1970-1979
Subject
The topic of the resource
John F. Kennedy Space Center
Skylab Program
Skylab 2
Saturn launch vehicles
Type
The nature or genre of the resource
Transcripts
Text
Source
A related resource from which the described resource is derived
Skylab Collection
Box 17, Folder 2
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
A language of the resource
en
Rights
Information about rights held in and over the resource
This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
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SL-II MC-60/1
Time: 22:50 CDT 14:50 GET
5/25/73
This is Skylab Control at 14 hours
PA0
50 minutes ground elapsed time. About a minute 50 seconds
until acquisition at the Vanguard tracking ship, which is
stationed off the southeast <~oast of South America. And
hopefully we will have a positive statement from the crew
that they have been successful in docking after the |-as^
procedure that they went through. Failing that, it looks
like they go through a standoff maneuver for the evening,
and regroup tomorrow for further docking attempts. We 11
wait and see what happens here over Vanguard. The Vanguard
pass will last almost 8 minutes and the next station after
Vanguard will be Vanguard again, an hour and 38 minutes
from now. We'll stand by for the first call from sPac®~
craft communicator to the crew of Skylab II. We ve had
AOS.
Skylab Houston through the Vanguard.
cc
How do you read?
CDR
We got a hard dock out of it.
CC
Way to go.
pA0
Considerable applause here on the re
port of hard docking.
... we got a tunnel integrity
CDR
check in the work right now.
CC
Hey, way to go. Good show.
CDR
You can tell sim sup that we really
would sure like to get some ... out of this thing
after a while.
CC
You can bet your life I will Pete.
CDR
We're starting our quiescent switch
configuration with the notes that you gave me some where
back day before yesterday it seems like.
CC
Stand by for one on the quiescent
check please, Pete.
CC
CDR Houston. We've got 6 minutes left
in this pass. We do have about an hour and a half a whole
rev before we get Vanguard back again. I do have just a
few short notes that might help you go through the check
list for the post docking this evening. Over.
CDR
Fire away.
CC
Okay, the first of course is get
through the post docking work. And I'm not sure what of
this you've done on the SEVA checklist on page L/Delta.
Then go through the helmets gloves and PGA docking and
stowage and that is on pages L/l-13, L/l-14 and 15 in the
SEVA section.
CDR
Okay.
�SL-II MC-60/2
Time: 22:50 CDT 14:50 GET
5/25/73
CC
Okay, following that Pete, go through
the presleep activity on SEVA section page L/Foxtrot. And
we want to add one additional step in the presleep activity.
We need to replace system Alfa LIOH canister, it's in
Alfa 4 and stow the used canister back in Alfa 4. Over.
CDR
Okay. System A is the top system, right?
CC
That's affirmative Pete.
CDR
Okay, look we've had our problems
and you've had your problems so we'll probably press on
to get this thing completely configured according to the
checklist that you gave us. We have eaten dinner, so
whenever we get this thing done, we'll get to bed and
press on first thing in the morning. I would, because of
the docking like to go ahead, if we've got a good tunnel
and verify all latches. It sounded to me like we got at
least 10. But I would like to verify them and then we'll
put the hatch back in and go to bed. Do you concur with
it?
CC
Stand by one.
CC
Okay, you tell them you got anything
else other than that you want to do tonight? Well he does
that as far as the list.
CC
CDR Houston. On your question, we do
concur that if you have a good hatch integrity check to
verify the docking latches. Also one thing we want to be
sure to catch is a fuel cell reactants valves to unlatch
in a normal. And be advised that we will be going back
to CMG control on the SWS. We expect you may get a little
bit of movement out of it but we want to get out of TACS
only.
CDR
Okay sir it is all yours.
CC
Roger that.
CC
Skylab Houston.
CDR
Go ahead Houston.
CC
Okay, Pete. One thing in the checklist
that we were going to read you and just never had time and
got in a hassle. During the quiescent panel check on panel
201, we do not want to inhibit items 9 Alfa Charlie and
Delta. Over.
CDR
Do not inhibit 9 Alfa Charlie and
Delta.
9^
That's right Pete. And where we're
looking at our time line, we expect bed time will be some
where around 18 hours or a little bit sooner and we think
that ought to give us plenty of time to call you on this
next Vanguard pass next time around, which is about an
hour and a half from now, and if you don't have any objec—
�SL-II MC-60/3
Time: 22:50 CDT 14:50 GET
5/25/73
tions we're going to call you at that pass and that will
probably be the last AOS today.
C°R
Yes sir, we'll see how much we can
get done in the next hour and a half.
CC
Okay real fine. We're about 30 sec
onds from LOS now and we'll see you at Vanguard next time
around.
CDR
Okay, sure glad we practiced those
procedures on that probe.
CC
Yes sir, looking good.
pAO
This is Skylab Control at 15 hours
ground elapsed time. We've had loss of signal out of the
Vanguard tracking station. It's unlikely we will continue
to pick up communications through the ARIA aircraft out
east of Vanguard. The attempt at docking, hard docking
was indeed successful. The crew believes that 10 of the
12 main latches did fire. They're proceeding with the
tunnel pressure integrity check and going through their
presleep checklist. There will be one more call in an hour
and 30 minutes from now over Vanguard again. Then the crew
will go to bed, and proceed with the days work tomorrow.
Or going into the workshop and deploying the parasol thermal
shield. At 15 hours 2 minutes ground elapsed time, this
is Skylab Control.
END OF TAPE
SL-II MC-61/1
Time: 23:27 CDT
5/25/73
15:26 GET
PAO
This is Skylab Control 15 hours 26
minutes ground elapse time in the Skylab 2 mission. The
Skylab space station, with a successfully docked Command
Service Module is presently over the Arabian Peninsula, and
an hour and 3 minutes out of Vanguard for the final com
munications of the evening, which will consist primarily
of a status report on the presleep checklist and the final
goodnight of the evening. In 10 <->r 15 minutes, a press
conference will be held in the Johnson Space Center news
room, small briefino room. Participants being, Mr. Bill
Schneider, Skylab Program Director, NASA headquarters.
The two Manned Space Flight Center Skylab Program Manaaers,
Kenny Kleinknecht from Johnson Space Center, and Leland
Belew from Marshall Space Flight Center. They should be
arriving within the next 10 minutes, and at 15:27 ground
elapsed time, this is Skylab Control.
END OF TAPE
�SL-II MC-62/1
Time: 00:27 a.m. CDT, 16:27 GET
5/26/73
PAO
This is Skylab Control at 5 hours 27
minutes 54 seconds Greenwich mean time. We can hear the horn
buzzing in Mission Control to announce acquisition of signal
coming up in a little under 2 minutes. We'll have acquisition
of signal at Vanguard. This period of pass is approximately
10 minutes and 17 seconds, and after that there will be another
opportunity at Ascension at approximately 3 minutes later.
At this time it appears that we'll not use that opportunity,
that they'll allow the crew to go to sleep immediately after
the Vanguard pass. That's still open however, at this time.
Among the instructions we passed up - in this coming pass by
the CAP COM are instructions to reset the clock that they're
using now - the G.E.T. or ground elapsed time clock which will
be reading 17:00 hours on the next even hour. They will reset
that clock to read 06:00 Greenwich mean time and from now on the
mission will be conducted on Greenwich mean time. They also
will give instructions to the crew to go to sleep within the
next hour before 17:00 GET or 6 o'clock Greenwich mean time
and their wake-up will be left open. They can wake up when
ever they like. At any case they expect to wake up no earlier
than 9 a.m. central daylight time. There will not be a wakeup call given from the ground if present plans are continued.
There are two reset maneuvers being scheduled during the night and
the crew will be informed about this. The first reset maneuver
may take place right immediately after the Vanguard pass at
Ascension. That still is - has not been computed completely
and they're going to try and compute that in time and let the
crew know what - the exact details that reset maneuver will
be. We're going to have acquisition of signal very shortly
and you can listen in for the - - This is Skylab Control.
CC
Skylab, Houston. We're AOS over Van
guard for the next 11 minutes.
PAO
We have AOS.
CC
10 minutes for the next 10 minutes.
CC
Skylab, Houston. We're AOS over Van
guard for the next 9 minutes. How do you read?
PAO
We're trying to acquire the CSM on voice.
CC
Skylab, Houston. We're AOS over Van
guard for the next 8 minutes. Over.
CC
Skylab, Houston over Vanguard for the
next 7 minutes. How do you read? Over.
CDR
CC
Roger, Pete. You were a little bit
garbled there. For your information I've got a few messages
for you I'd like to give if you can copy.
PLT
Okay, Houston.
CC
Roger. Fine job today, Pete. Number 1
�SL-1I MC-62/2
Time: 00:27 a.m. CDT. 16:27 GET
5/26/73
I guess - PLT
Okay, this is Paul, ready to copy.
CC
Number one, I guess we'd like to get
over for G.m.t. so your checklist tomorrow will give you some
good AOS times. We'd like you to set 17:00 GET, or BET rather,
to set time at 06:00 G.m.t.
CC
Did you copy, Paul?
CC
Skylab, Houston. How do you read?
CC
Skylab, Houston. How do you read?
PLT
Loud and clear now.
CC
Okey doke, we lost you there for awhile.
Did you get the time set at 17:00 BET time will be 06:00 G.m.t.?
PLT
No, we didn't get any of your messages
at all. Bob. As soon as you said you had messages for us, you
quit.
CC
Okay. Let's try it again. We would like
to give you - set your timer so you can go back to G.m.t. and
at 17:00 elapsed time the time will be 06:00 G.m.t.
PLT
Okay.
CC
Okey dokey. And we would also like if
you got time meal status for day 1.
CC
Okay. We would also like to insure that
VHF A and B are OFF before going to sleep.
PLT
Okay, we had them OFF and then I noticed
that I had a barber pole in a power amplifier. And I'm still
not sure what games that those guys can play with it down there
so we left B DUPLEX UP just to make sure he wouldn't be able
to get ahold of it. That's why it's ON now.
CC
Okay. Okay, we're taking care of that.
You can turn VHF A and B OFF.
CDR
Okay, Bob, and for your information the
CDR ate everything.
CC
All right. Okey doke, Roger.
PLT
The PLT dipped the first spoonful of
his asparagus was half wood, so I only ate about one-third
of it, mostly the non-woody part.
CC
Rog.
PLT
The SPT said he ate everything. I'm going
to have eaten everything else. Bob.
CC
Okay, very good. Thank you, Paul.
CDR
Okay. We have the LiOH canister changed
out. We've done the quiescent switch checklist. We got a
couple of questions for you. What mode would you like to leave
the computer in - you want to leave it in POO and ACCEPT? And
while you're answering that one - let me - we had one on whether
we're supposed to use this max power down. Do you want that
or not?
�•
I.
SL-II MC-62/3
Time: 00:27 a.m. CDT, 16:27 GET
5/26/73
V
CC
Stand by 1. We do want the computer
left in POO and ACCEPT.
CDR
Okay, the computer's in POO and ACCEPT and on the max power down we've stopped most of that, but
there are a couple of things that we have not done. Like, do
you want the E/P spectrometer off?
CC
Okay, Pete. They really didn't want
you to do the max power down, but ...*5
PLT
RCS q uad Bravo temperature
indicates off=scale high, associated CAUTION. At first we
didn't know if it was real or not. We ... 2 - turned
those heaters off on Bravo and I assume that it's safe to
turn them back on again.
CC
Rog. I didn't get the which C&W you
had there, Paul.
PLT
RCS quad Bravo.
CC
Rog.
PLT
And the reason we got - the reason
we got it was for temperature - that it was high at the time
and now it's off=scale high.
CC
Rog. Copy.
CC
We would like to - PLT
Go ahead.
CC
Okay. We had not planned to give you
a call over the ground station, however there's several mes
sages here that we probably ought to talk about. So we are
about a minute and one half to LOS and we'll have you again
at Ascension and at 16:43. I'll go ahead and hit you with
a couple of things here. They would like you to back out of
that MAX POWER DOWN if you could and just have the quiescent
POWER DOWN.
PLT
Okay. I think we can sort that out.
CC
Okay dokey.
PLT
Yeah, also, I got a popped circuit
breaker I want to talk about next time on panel 5. It's last
one in the second row, UTILITY. We're R/L station MAIN A.
CC
Rog. I understand that one's popped.
CDR
Well, we reset it but that's the one
that feeds the backup way that we got docked and we think it
probably popped when we docked.
CC
Okay, but it did reset okay. Is that
correct?
PLT
Yeah.
CC
Can you tell us whether you used A or
B system for docking?
CDR
Bravo.
CC
Rog. Copy, Bravo.
CDR
The bottom one in the panel I believe.
�<7
(
SL-II MC-62/4
Time: 00:27 a.m. CDT, 16:27 GET
5/26/73
CC
Rog. Okay, we're just about to go LOS
here. By the way wake-up tomorrow is going to be open-ended.
You give us a call.
MS
Yea.
CDR
Okay, that's good because look we got about
another hour at least in here. Man, this place looks like
somebody blew through here with a tornado.
CC
I think you guys earned a good night's
sleep.
CDR
We'll be around for at least another
hour and a half I think.
CC
Rog. We were going to end up doing
a CMG reset at the next station pass and that's going to move
the vehicle around a little bit.
CDR
Well we notice ... up here a
little bit.
CC
Okay, you have got a slight maneuver
going on now, but that's not a reset. We're trying to get back
PAO
We have LOS. We've have our next
axquisition of signal in about 2 minutes and 17 seconds and
the crew will be again given further information about maneuvers
We'll be on for about 2 minutes.
END OF TAPE
�c .. t
SL-II MC-63/1
Time: 00:43 CDT 16:43 GET
5/25/73
we have acquisition of telemetry data
and we expect acquisition any moment now.
we are AOS over Acsension for the iu
cc
minutes for the next 10 minutes.
Okay, we are backing out of this low
PLT
cc
POWV
Rog, understand. And I guess you got
your flight plan there with you and it did have exceptions
listed on the quiescent time line. That s in your
9
checklist.
_ _ tQO but he also had the max power
down and I wasn't sure which one you wanted, so I went into
that and we'll be out in a minute.
CC
Roger, understand.
Rog, the exceptions are listed in SEVA
cQ
L-E.
CDR
Right.
CC
And we are going to be starting the
CMG reset routine very soon, and it's going to cause the
vehicle to move around, oh a good little bit. This one is
going to be kind of small, it can't be large. For your in
formation, we are probably going to have to do an^her one
of these tonight before you wake up. We ve been having to
do them about every 4 to 8 hours.
CDR
Okay.
cc
And Skylab, we would like you to select
secondary package heaters on quad Bravo.
CDR
Okay, everything works.
PLT
Well we've got the package heater and
we've got the quad heater. Do you want them both to go
to 2 and secondary as appropriate?
cc
Pete, that was a little bit garbled
on did you understand it on quad Bravo. We wanted the pack
age heaters to secondary.
CDR
Okay, the package heaters to secondary.
CC
Rog•
„
PLT
Okay except thats what's confusing. Crip.
We got two sets of heaters. One for the package and one for
the quad.
cc
Rog. It is the package.
PLT
Well the backup one for the package
is two and the backup one for the quad is second. So you
want the package heater to 2 and the quad heater left in
primary. Is that right?
CC
That is affirmative.
CDR
Okay, and by going to the caution
warning, it was a package indication that was tripping it.
CC
Rog, understand.
�SL-II MC-63/2
Times 00:43 CDT 16:43 RET
5/25/73
CDR
Say, Crip, we did have to dump urine once
today, which I believe we reported. The time that we
did it all three crew members other wise we have collected
all the rest of it onboard.
CC
Roger, copy.
CC
Skylab Houston. We still have about
6 minutes left in this pass. The next pass is
going to be over Guam at 17:27 elapsed time and that will
06:27. I guess our intent now is not to give you a call
there.
CDR
Okay.
CC
Skylab Houston. I guess tomorrow
morning, what you can do is on your activation checklist
pick out a site to give us a call when you're awake and
want to go to work.
CDR
Okay.
CC
Skylab Houston. We're 1 minute to
LOS over Ascension and we'll see you manana. That pass
over Guam, in case you need us is at 06:27 GMT.
CDR
06:27, Okay, thank you.
PAO
This is Skylab Control. We have loss
of signal now at Ascension. The spacecraft is now passing
to the northeast over Africa on rev 167. Our next chance
for signal will be, as the Capcom indicated, in about 33 min
utes and 40 seconds from now at Guam. And we expect to
have no communications from the spacecraft at that time
unless the crew has something they would like to say to
the ground. They did indicate at Vanguard that they did not
expect to be asleep by 1:00 a.m. central daylight time as
they were to been instructed to go to sleep. They may be
up a little later, you may hear from them at Guam. We're
not quite certain about that. They are expecting to go to
bed as soon as possible and will get up probably get up no
earlier than 9:00 a.m. central daylight time tomorrow.
They will not be awakened from the ground. They will give
a call to the ground from their headsets whenever they are
ready to get up and go to work. This is about an hour and
a half, the 9:00 a.m. mininum sleep time will make it about
an hour and a half later than the flight plan that was set
up premission. That's to give them time to get plenty of
rest after a very hard day. This is Skylab Control at 5 hours
54 minutes and 50 seconds Greenwich mean time.
END OF TAPE
�SL-II MC 64/1
Times 01:25 CDT 17:25 GET
5/25/73
PAO
This is Skylab Control. We again have
the horn sounding in Mission Control, 2 minutes coming up
for opportunity for acquisition of signal at Guam. The
space station at this time is on its 167th revolution on
a decending node, passing over Japan. And we're about
1-1/2 minutes from acquisition of signal. This acquisition
of signal may not actually indicate any sort of discussion
between the crew and ground. We don't know one way or the
other whether the crew will still be awake. We will, how
ever, be getting telemetry data. And we may hear something
from the crew, since they indicated they may not yet be
asleep. We have 1 minute and 20 seconds to acquisition of
signal.
PAO
Skylab Control. We have 55 seconds to
acquisition of signal. The crew is now operating on
Greenwich mean time. They have reset their clocks at 1700
hours ground elapsed time to the Greenwich mean time 600
hours. They are now going to be getting all times in
Greenwich mean time. At 06:26:49 Greenwich mean time, we
have 38 seconds to acquisition of signal.
PAO
We have telemetry acquisition of signal.
And we should have voice acquisition of signal shortly.
PAO
AOS.
MCC
Guam tech. Comm Tech, Houston, take net
one for a voice check.
MCC
Guam, Comm Tech
MCC
Roger.
PAO
We have indications that the crew is
attempting MCC
Guam station, do you read. Over.
CDR
Affirmative Guam, loud and clear.
MCC
We have a communications problem between
the tracking station and the network, and we'll be back
with you as soon as we reestablish.
CC
Skylab, Houston. How do you read.
CDR
Loud and Clear.
CC
Okay. Read you loud and clear.
CDR
Hey, we finished clorinating the water.
P.J. Weitz is sliding into his sleeping bag, along with
Pete Conrad and Joe Kerwin. We're just about to bed out.
CC
Very good. Anything else we can do for
you tonight?
CDR
No. We did have a question. We have
turned the potable water tank on not for any other reason
than it was down to 25 percent. We figure we might as well
fill it up.
CC
Rog.
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
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Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
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Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
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sdsp_skyl_000079
Title
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"SL-II MC-60/1 Time: 22:50 CDT 14:50 GET 5/25/73" - "SL-II MC 64/1 Time: 01:25 CDT 17:25 GET 5/25/73."
Description
An account of the resource
This mission commentary depicts Skylab 2 docking with Skylab 1. This mission commentary also depicts the Skylab 2 crew beginning work on resolving the solar panel and micrometeoroid shield problems.
Creator
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United States. National Aeronautics and Space Administration
Date
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1973-05-25
Temporal Coverage
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1970-1979
Subject
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John F. Kennedy Space Center
Skylab Program
Skylab 1
Skylab 2
Multiple docking adapters
Conrad, Charles, Jr.
Weitz, Paul J.
Kerwin, Joseph P.
Manned Spacecraft Center (U.S.)
George C. Marshall Space Flight Center
Belew, Leland F.
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Transcripts
Text
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Skylab Collection
Box 17, Folder 2
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
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en
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Relation
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Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14415/sdsp_skyl_000080_001.pdf
a79cfc62836231bf52638ee59853db4f
PDF Text
Text
SL-U MC-64/2 'Ufa
Time: 01:25 CDT717:25 GET
5/26/73
. CC
For your information, we got about
6 minutes left on this pass.
CDR
in to that day 2 activation
tomorrow, as soon as we get up and eat.
CC
Okay, no need to rush.
cc
While I got you here, we talked about
that reset routine. I don't know whether that bugged you
all. The motion, it could get up into as much as 3/10 of
a degree per second if we - on some of them, we have seen
those kind of things.
CDR
Yeah. Is it maneuvering right now?
^
i don't beleive so.
CDR
Okay, well, we got the window shades up,
so we don t know what you guys are doing.
, CC
Very good. And Pete, that potable tank
and that valve is okay like you got it.
CDR
Okay.
CC
Skylab, Houston. If you need us for
any reason tonight, if you'd give us a VERB 99, we'll
have AOS.
CDR
Okay.
CC
Skylab, Houston. We're 1 minute til
LOS and we 11 see you manana.
Nighty-Nite.
CDR
Nighty-Nite honey.
CDR
Hey Crip, you still with us.
CC
Affirm.
C R
Hey, I just wanted to impress on every
body how - how black or burnt looking that gold foil was
getting on the sunny side of the vehicle. I suspect that's
the reason your temperature is going up. That mylar's S**just deteriorating or whatever that gold stuff is.
CC
.
Roger. I think they got that impression
today during the fire up.
CDR
Okay.
CC
Let's hope the parasol takes care of it.
C R
Yeah. Now that we're docked, I'm not
sure how we get undocked.
CC
We'll work on that.
PA?
,„
. We have lost the signal at Guam and the
crew should be going to sleep very shortly now. They will
wake up at their will in the morning. Probably sometime
after 9:00 a.m. central daylight time. During the evening
a reset maneuver will be preformed to reset the control
moment gyros, beside that it should be a rather quite/w-T^
evening. Systems are being monitered. Temperatures kee^
to be at very acceptable levels. The suit coolant loop,
which has given some concern earlier in the last few days
P
P
�SL-II MC-64/3
Time: 01:25 CDT 17:25 GET
5/25/73
has now risen to 36.8 degrees. Very mild temperature. Very
well above freezing, and very well above the safe range
that had been indicated earlier, and the temperatures seem to
be about the same level that they were earlier in the workshop
habitation area. So, we don't expect to hear anything more
from the crew tonight. We will have a Skylab reports on
the hour from now on, and in the event of any sort of
status change, we will come on. This is Skylab Control at
6 hours 39 minutes Greenwich mean time.
END OF TAPE
SL-II MC-65/1
Time: 03:00 CDT 19:00 GET
5/25/73
PAO
This is Skylab Control at 8 hours
and 2 seconds Greenwich mean time. At the present time,
the Skylab space station is in its 168th revolution. The
command module is completing its 12th revolution. They
are properly docked. The period of revolution is 1 Ijour
33 minutes 13.5 seconds. The low point in the orbit 235.2
nautical miles. The high point 239.7 nautical miles. That's
a variation from approximately 270 statute miles to 275
statute miles. Speed at this time 25,087.8 feet per sec
ond, approximately 17,100 miles per hour. Biomedical officer
informs us that we will have no information on the time the
crew went to sleep tonight because none of the crew members
are wearing the^operational biomedical system, the OBS which
records heart rate and related data. It allows us to deter
mine whether or not they have gone to sleep. At the present
time the command module is a very comfortable 70.6 degrees.
And it's pressurized to 4.9 pounds per square inch. This
is Skylab Control at 8 hours 1 minute and 17 seconds Green
wich mean time.
END OF TAPE
�SL-II MC-66/1
Time: 04iOO_ a.m.
5/26/73
CDT»
20:00 GET
This is Skylab Control at 9 hours Green
PA0
wich mean time. At the present time the Flight Controller,
Milt Windier, and his team of flight controllers are
f
a slight attitude adjustment to take place
Greenwich mean time, that's a little less thanan 1
now at Honeysuckle tracking station. That will be iater i
rev 170. We are at this point - I take that back - that
on rev 169 . We are at this point early in rev 169, .just be
ginning our pass over the Equator and we're headedto the north
east - headed for the Canary Island tracking statioi„!!?«» o
have acquisition of signal there in a little over 4
There have been no new problems arising in the mission a
everything looks successful. We expect the crew tobeawakening
y
at approximately 9 o'clock, but they will not be al**ted.
will wake up on their own - at their own time and
their awakening to us and we'll be waiting for ^sometime
after 9:00 a.m. central daylight time. This is Skylab
at 1 minute and 8 seconds after the hour.
END OF TAPE
�SL-II MC-67/1
Time: 05:00 CDT 21:00 GET
5/26/73
This is Skylab Control at 10 hours
L
Greenwich mean time. At the present time repressurization
of the orbital workshop area is preceeding on schedule
towards a completion about 12:49 Greenwich mean time. 2
hours and 50 minutes from now. Making the station ready for
habitation before the crew wakes up sometime after 1400
Greenwich mean time. At this time the pressure indicator
in that area are reading about 3.9 pounds per square inch.
There are expected - The crew's expected to enter the
workshop about 1600 Greenwich mean time, depending on crew
wakeup. That's assuming they wake up after about 8 hours
of sleep. Power usage during the final depressurization
e orbibal workshop has been relatively high and
SYFlight Director Milton Windier has reduced the pitch of
the space station to bring more direct sunlight on the ATM
solar panels, thus increasing the charge levels of the
seventeen batteries still operating aboard Skylab. ^Charger
ttery_regu1ator module number 15, which ceased operations
earlier in the mission continues to show no amperage and is
a stuck relay that cannot be repaired by the
' . hl? inactive CBRM will cost an estimated 150 to
200 watts in power generation. Battery charge is relatively
low, as electronic equipment is being operated to provide
heat needed to warm oxygen as it is released into the
rhl°p J? prevent coolant temperatures from dropping.
of P^tchup to 45 degrees, which began about
5 minn^pB
M«h i
i
charge batteries, which should be at
b<Tfor® the crew begins activation later today.
•iwLilll
^ W3Jer coolant lo°P tbat connects the suit
8ys!:em iavf been rising Steadily after a very
angle of about 25 degress up was used during the
temner^in9 nighJ:* ^fc,the Present time the SUS coolant inlet
f! reads 1
degrees Fahrenheit, far above the
J lhat caused concern for several days this past
weex. Estimated temperature in the food storage area is
12J de9rees and may be expected to rise 1 to 2
e"ters*
As a result of the lower
p
pitch angle now being used to charge the ATM batteries. At
the present time there have been no additional problems
arising at the Skylab Mission Control Center. A^d we expect
Mnfnn9w-°5iShlft 3t 7:00 this mornin9 as Flight Director
o
i!r gOGS °ff and Fli3ht Director Neil Hutchinson
Mission Control Houston at 10
hours 2 min, J18 X%S!5«
hours 2 minutes and 40 seconds, Greenwich mean time.
PA0
END OF TAPE
�SL-II MC-68/1
Time: 06:00 a.m. CDT, 22:00 GET
5/26/73
PAO
This is Skylab Control at 11 hours
Greenwich mean time. At the present time all systems are
still operating properly on the Skylab workshop and in the
command module. The temperature right now in the cabin of
the command module is 69.3 degrees and the pressure level in
there is 4.95. We have continued to pressurize the orbital
workshop. It is now past the 4 pound per square inch level,
and will rise to 5 pounds per square inch in plenty of time
for a crew wakeup and they're having no problems with any of
those systems so far. The TACS consumable status right now
is that we have 54.5 percent of the total amount of TACS gas
originally carried still in the tank. Considerable amount
of TACS gas was used last night but there still remains approx
imately 30 percent more than is required for all experiments
and maneuvers throughout an eight month period. This is about
8 percent at this time - about 8 percent more than was
expected in the flight plan so that there's a - there's
fortunately a very large pad in this area so that we have
plenty of TACS gas remaining. But there was quite a lot
used last night during the maneuver. This is Skylab Control
at 11 hours 1 minute and 16 seconds Greenwich mean time.
SL-II MC-69/1
Time: 07»00 a.m. CDT, 00:23:00 GET
5/26/73
PAO
Skylab Control, Houston, at 1200 hours
Greenwich mean time. The Skylab orbital assembly now traveling
in an orbit of 239 nautical miles by 235 nautical miles, presently
passing over the southeast portion of the Pacific Ocean. The
next tracking station to acquire will be Texas, some 7 minutes
from this time. The Skylab crew aboard the command module
are still in their rest period. Wake-up time is presently
somewhat open-handed; however, it should be around 9 o'clock
central daylight time, or 1400 hours G.m.t. Also, the assign
ment of the Mission Control Center is being handled in much
the same way. Flight Director Milt Windier's team is still
on duty. However, it is expected that they will be replaced
by the Neil Hutchinson team shortly. At 1200 hours G.m.t.,
this is Skylab Control, Houston.
END OF TAPE
�SL-II MC70/1
Time: 08:00 a.m. CDT, 1:00:00:00 GET
5/26/73
PAO
Skylab Control, Houston, at 1300 hours
Greenwich mean time. The Skylab orbital assembly presently in
an orbit of 239 nautical miles by 235 nautical miles. Pres
ently passing over the Indian Ocean on the 171st revolution
for the Saturn workshop. Meanwhile, in Mission Control, the
Neil Hutchinson team is beginning to arrive on the scene.
Their team color is silver. Presently, discussions are cen
tering on the activation checklist,»*?hich represents the pro
cedures that the crew aboard Skylab will follow for entry
into the workshop today. We're at 1300 hours 1 minute Green
wich mean time. This is Skylab Control, Houston.
SL-II MC-71/1
Time: 09:00 a.m. CDT, 1:00:60 GET
5/26/73
PAO
Skylab Control, Houston, at 1400 hours
GMT. Skylab is presently in an orbit of 239 nautical miles
by 235 nautical miles and under acquisition, at this time,
by Newfoundland Tracking. The next station to acquire will
be Madrid, in approximately 3 minutes. Meanwhile, in the
Mission Control Center, Flight Director Neil Hutchinson
continuing to go around the room consulting with his flight
control team on the very detailed activation checklist,
which the Skylab Crew will follow when they enter the work
shop for parasol deployment later on today. Presently, no
plans are laid on for a detailed analysis of the probe by
the crew after it's removed for entry into the multiple docking
adapter. And also, at this time, there is still no definite
indication as to when Conrad, Weitz, and Kerwin will wake up
to start their work day. We're at 14 hours 1 minute GMT;
this is Skylab Control, Houston.
END OF TAPE
�SL-II MC-72/1
Time: 09:05 a.m. CDT, 01:01:04 GET
5/26/73
cc
SC
cc
g°°dS
C
Skylab, Houston. Good morning.
Hi there.
How is it going this morning? You guys rest
Yeah, we slept pretty good. We're just "
we really just got up just a few seconds ago, and we 11 try and put
(cut out) and get with it.
CC
Okay.
,,
,
what friendly words did you all think
sc
about over the night?
,
Spacecraft Commander, Pete Conrad,
PA0
talking with CAP COM, Henry Hartsfield, here in the)Mission
Control Center. Per an agreement, which was reached last night
when the VERB 99 flashed up in the DSKY, the crew was saying
they were ready to talk. We see VERB 99 now on the command
module computer display.
, „
.. . ,ro a-rsmniSkylab Control, Houston. We have
approxi
PA0
mately 5 minutes remaining on this Madrid pass; the next station
to acquire will be Honeysuckle, and that's about 42 minutes from
this time.
sc
Hey, Henry, where are we?
You're over Madrid now.
CC
SC
We thank you.
That was Paul Weitz chiming in to the
PA0
conversation, asking for location - cc
Four more minutes on this pass,
sc
You got any big changes for us, or are
we qoing to crap off on day 2 the way we got it figured?
Yeah, Pete, we're working on it now.
cc
What we want to do is get together a package for you; try to
have it either at Honeysuckle or stateside before we get going
here. And we got a few changes for the activation checklist,
and we're also going to have some questions for you on probe
removal. We'd like to check a few things, before we puH that
thing out, to help us in the troubleshooting. And the main
is, we want to just kind of relax here a bit and get organized
start off on the right foot.
.
sc
Okay, very good. I was thinking about
that probe, too. You know we did lose a little nut, but if
you got another one of those around anywhere in the spacecrart,
we could always rob it.
CC
Roger; copy.
About a minute away now from loss ot PA0
Cc
About 1 minute to LOS; we'll be picking
you up at Honeysuckle at 00:50:00.
SC
Right. Honeysuckle at 00:50:00.
Skylab Control, Houston; 14 hours 12 min
PA0
utes G.m.t. We've had loss of signal with Madrid. Next sta
tion to acquire is Honeysuckle in approximately 37 minutes.
END OF TAPE
�SL-II MC-73/1
Time: 09:48 a.m. CDT, 1:01:48 GET
5/26/73
PAO
Skylab Control, Houston, at 14 hours
48 minutes Greenwich mean time. About a minute away now,from
acquisition with Honeysuckle. This will be a very short pass,
approximately 1 minute and 55 seconds in duration. We may or
may not start passing to the crew the checklist change items
for the activation. It will be a crew option. We'll stand
by and monitor.
CC
Skylab, Houston. ... Honeysuckle for a
minute and a half.
SC
We can't tell us much then, can you?
CC
No, Pete, but I'll tell you what we've got
here. We've got all the checklist changes put together in a
little package. There's about 11 of them that should bring
the activation checklist up to date. Rusty's working on the
questions on the probe. And if you like, we'll hold that
off to stateside. We're also planning a private conference
before Madrid, which will be coming up at 00:40:00.
SC
Okay. Whose the private with?
CC
Okay. It'll be with the surgeon.
SC
All righty.
SC
If you could go ahead, maybe - Yeah, let me get an activation checklist of my dumps while I
have just finished breakfast, and I'll copy some of this.
CC
Okay. And the computer's yours, too.
SC
Okay. How about battery A, has that got a
good enough charge on it, yet?
CC
Okay. We want to let it continue to charge.
And ah - We've only got about 15 seconds left here (static)
at Goldstone, which is coming up at 00:18:00.
CC
I'll repeat. Goldstone at 00:18:00.
SC
Okay. Roger.
PAO
Skylab Control, Houston, at 14 hours
52 minutes GMT. We've just had loss of signal with Honeysuckle.
The next station to acquire over the States will be Goldstone,
aDDroximatelv 26 minutes from this time.
SL-II MC74/1
Time: 10:02 a.m. CDT, 1:02:02 GET
5/26/73
PAO
Skylab Control Houston, at 15 hours
2 minutes Greenwich mean time. The private conversation
referred to by CAP COM Henry Hartsfield during the up coming
Madrid pass is the routinely scheduled surgeon crew conversation
set up on a daily basis. A medical bulletin will be released
later. We're at 15 hours 3 minutes Gmt. This is Skylab
Control, Houston.
END OF TAPE
�SL-II MC75/1
Time: 10:17 a.m. CDT, 1:02:17 GET
5/26/73
PAO
Skylab Control, Houston at 15 hours 17
minutes Greenwich mean time, approximately one minute away
now from acquisition through Goldstone. The Skylab workshop
presently in a orbit of 238.9 nautical miles by 235.1. Dur
ing the stateside pass we expect checklist changes.
PAO
Standing by now for Henry Hartsfield's
call up to the crew.
CC
Skylab Houston stateside for about
11 1/2 minutes.
SC
Okay we're ready to copy. We've got the
activation checklist open. Be advised that we've pressurized
the tunnel and we had very little leakage on it last night,
maybe a tenth of a psi. So we got a good tunnel and we're
standing by for your word.
CC
Roger. Copy. The first item is on
page A-3, that's a little time line we put in the front of
the checklist.
SC
Up there that's mission day 2. Go ahead.
CC
Okay there is just a typo there on the
M168 relocation. It gives you page 2-12; that really should
be page 2-121.
SC
Okay, whose column is that in?
CC
SPT column.
SC
Yeah, and it should be 2 dash what?
CC
2-121.
SC
Okay. We got it.
CC
Okay the next one is on page A-5.
SC
Go ahead.
CC
And the CDR column all the way at the
bottom of the page the quiescent configuration - we just want
to write a little note there Pete to the effect that do not
configure panel 275 until all battery charging is complete.
SC
Understand.
CC
Okay. The next one is on page A-10.
SC
Go ahead.
CC
Okay step 6. The TV input station 320
should be 133. The same thing applies to step 7 that should
be panel 133. Okay after step 10 we want to add a step 10-A
that says VTR power switch on.
SC
Okay.
CC
And step 12, second line, that panel 320
should be 133. And in addition after VTR standby we want to
add VTR power switch OFF.
SC
We've got it.
CC
Okay next one is on A-13.
SC
Go ahead.
CC
Okay. The first two lines up there should
be changed to read connect CWG electrical harness to CCA.
�SL-II MC75/2
Time: 10:17 a.m. CDT, 1:02:17 GET
5/26/73
SC
Okay.
CC
Okay. A-15. On the stowage location
for 16 millimeter cassette takeup it should be VOX 524 instead
of 527.
SC
Okay. Got that one.
CC
Okay now if you'll jump over in activa
tion checklist to page 2-18 SC
All right go ahead, E MEMORY DUMP?
CC
Roger. After the E MEMORY DUMP there
we want a note to the effect that after guidance has given a
GO on the E MEMORY DUMP, perform P06, program 06, CMC POWER
DOWN and that's on page 2-78.
SC
Okay.
CC
Okay the next one is on page 2-29.
SC
Go ahead.
CC
Okay we want to delete the last line of
step 2 which reads panel 311 pressure equalization valve
OPEN, we want to leave it CLOSED.
SC
Okay.
CC
Okay. The next one is on page 2-42;
these are the changes to your ATM panel configuration, com
mand changes, SC
Okay, go ahead.
CC
Okay about halfway down the lefthand
side where it says mode talkback solar inertial it should be
CMG.
SC
Roger.
CC
Okay, righthand side status word 2, counter
1 indicator should be 0353.
SC
Okay.
CC
Status word 4, counter 2 should read
1000.
SC
You cut out Hank. What was the (garble)
switch.
CC
Okay, 1000. Did you copy?
SC
No. Say the checks both once again. Hank.
CC
One thousand, 1000.
Okay.
SC
Okay on the rate gyro monitor Y should be
CC
3/1.
SC
Okay.
CC
Okay the next one is on page 2-43, right
under the last item that we've got pinned in there about the
hold for 25 seconds, we want to add EVA AUTO DOOR SWITCH to
STORAGE.
SC
Okay.
CC
Okay the next one is on page 2-50.
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
Dublin Core
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sdsp_skyl_000080
Title
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"SL-II MC-64/2 Time: 01:25 CDT 17:25 GET 5/25/73" - "SL-II MC 75/2 Time: 10:17 a.m. CDT 1:02:17 GET 5/26/73."
Description
An account of the resource
This mission commentary depicts the improving temperature conditions on Skylab 1 following the Skylab 2 crew's efforts to resolve the temperature problems.
Creator
An entity primarily responsible for making the resource
United States. National Aeronautics and Space Administration
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-05-25
Temporal Coverage
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1970-1979
Subject
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John F. Kennedy Space Center
Skylab Program
Skylab 1
Skylab 2
Multiple docking adapters
Conrad, Charles, Jr.
Weitz, Paul J.
Kerwin, Joseph P.
Manned Spacecraft Center (U.S.)
Type
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Transcripts
Text
Source
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Skylab Collection
Box 17, Folder 2
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14416/sdsp_skyl_000081_001.pdf
90b884b987ee485819987850895398eb
PDF Text
Text
SL-II MC75/3 "~79/3
Time: 10:17 a.m. CDT, 1:02:17 GET
5/26/73
o>i -k
SC
Break, break. What have you got for us
on the probe. I'm scared we're going to get all this stuff
in and not get the probe stuff where we can get in there.
CC
Okay we've only got a couple items, Pete,
and then Rusty has got some words for you on the probes.
SC
Okay.
CC
Okay on page 2-50 we don't want you to
close the hatch channel. We'd like for that to read Don
CHARCOAL MASS and then just place the hatch over the opening.
SC
Okay.
CC
And the last one is on page 2-60. On
the circuit breaker configuration, panel 614, on the righthand
side on duct 3 fans we want to keep all those open - the four
duct 3 fan circuit breakers, we'll only use 8 fans.
SC
That's affirm.
CC
Okay and Rusty has got some words for you
on the probe.
CC
Okay Skylab we've got 3-1/2 minutes here
left in the pass for your information and let me tell you what
we want on the probe. There is a general caution note - I
don't know who is going to do it - but when you collapse the
probe for removal be aware of the fact that it may come com
pletely free of the drogue right at that time.
SC
Okay we are guessing that it will.
CC
Right. That's what we're guessing also.
Okay when you get up in there Pete what we're interested in
finding out is what is the clocking of the center shaft latch
on the aft end of the probe relative to the CSM axes. If you what we're recognizing is pressing on with a normal probe
removal checklist but before you do anything look at the flats
on the center shaft and give us your orientation. And a good
reference, by the way, is systems checklist page 2-10, gives
you a look at the back end of that whole probe and you can
reference the flats to that.
SC
Okay. Now you don't want us to put the
pyro cover back on with all the handles, huh?
CC
Pete, we don't want it to go back on
permanently at this time but if that helps to determine the
orientation go ahead and do it, then take it off and then go
through the rest of the probe collapsing and removal.
Okay.
SC
Okay now CC
Rusty, the picture I'm looking at has the
SC
cover on and I'm not sure I know what flats you're talking
about?
Okay, Paul, the shaft - it's a circular
CC
shaft with a flat on each side and what we're recommending
�SL-II MC75/4
Timei 10:17 a.m. CDT, 1:02:17 GET
5/26/73
in a way is if you can draw a perpendicular through those
flats and then give us the clocking of that line with respect
to the command module or that diagram on 2-10, either one.
SC
All right.
CC
Okay. Now the only other things we want,
when you vent the probe, is when you press the button to bleed
the nitrogen out keep watching that shaft and let us know if
it rotates. There is a possibility that it may rotate 30 to
40 degrees. We don't think it will but we would like to know
if it does.
SC
Unfortunately we vented it last night.
CC
You vented the probe itself or the tunnel?
SC
No we checked the docking latched, by
the way it made all 12 of them and in the process of doing
that we went ahead and bled the probe. And I have the feeling
that you're right. Joe said the probe was quite free in there
after he bled it and I have the feeling that the whole probe
is just loose in there and we do not have any capture latches.
CC
Roger. If you did then all we can get
from you is the clocking of the shaft before you - Okay we're
going to have LOS in about 15 seconds. We'll pick it up
GARBLE in about 1 minute.
CC
Skylab Houston how do you read?
END OF TAPE
�SL-II MC-76/1
Times 10:30 a.m. CDT, 1:02:30 GET
5/26/73
CC
Skylab, Houston.
SC
Go ahead.
CC
Okay, we got about 5-1/2 more minutes
now through Bermuda, and for your info, the med conference
over Madrid has been scrubbed.
SC
Okay, we're all healthy. And let's
hear from Rusty some more on that probe. We didn't catch
your last remark.
CC
Okay.
CC
All right. It sounds as though, since
you've already vented the probe, that the thing we're
looking for is the clocking on the center shaft, and other
than that - and the caution about the probe being free, you're
to press on with a normal probe removal as per the activation
checklist.
SC
All right. And what's your opinion on
if we had to undock? How we'd go about doing it? Do you
think we could get the capture latches to cock?
CC
Okay, we're thinking about that, Pete,
and we have a considerably longer procedure on verification
of the probe capability, that will come later in the mission
that'll answer that question specifically. One further comment
on the probe removal, and that is: In your judgment you'll
have to look at the back end of the probe, and if you feel
that it's going to be safer removing it with the pyro cover
back on, that is avoiding sharp edges, feel free to do so and
let us know.
SC
Okay. Stand by for the clocking. Pete's
looking at it.
CC
Roger.
SC
Houston, Skylab.
CC
Go ahead.
SC
Okay, the line perpendicular to the
flatch on that rod is rotated 15 degrees counterclockwise
from the plus-Z axis as we view it. Or from the Z-axis, I
should say.
CC
Okay, understand. If you stand by just 15 degrees counterclockwise from the Z-axis, and that's
counterclockwise looking up at the probe from down in
the command module?
SC
That is correct.
SC
(garble) talking about the removal (garble)
CC
Roger. It has systems 2-10. Let me just
verify. In other words, you're saying that the - that that line
is essentially over the ratchet handle. By the extension of
the line you just talked about, it's over the ratchet handle.
SC
That's right (garble).
�SL-II MC-76/2
Time: 10:30 a.m. CDT, 1:02:30 GET
5/26/73
CC
Okay, fine. Thank you. We have it, and
go ahead and proceed with the removal then.
SC
Okay, but that now. Rusty, is the line
perpendicular to the flat.
CC
Roger; we understand. That's the
line perpendicular to the flat. Thank you.
PAO
Skylab Control, Houston. We've been
listening to Backup Commander Rusty Schweickart chat with
the crew about the probe. Presently sitting at the CAP COM'
console - CC
Skylab, Houston. We're about 40 seconds
from LOS. We'll pick you up over Madrid at 40.
SC
Return at 40.
SC
Did you read comm check on that one?
CC
Roger. We heard Houston's comm check;
we read you loud and clear, thank you.
CC
Copy.
END OF TAPE
�SL-II MC-77/1
Time: 10:39 a.m. CDT, 1:02:39 GET
5/26/73
CC
Skylab, Houston, through Madrid for
7 minutes.
SC
Okay. We've got the probe out and the
capture latches were not engaged.
CC
Roger. Understand.
PAO
That's CAP COM Henry Hartsfield speaking
to the crew aboard Skylab on this Madrid acquisition, Paul
Weitz responding to that call.
SC
Okay, Houston. Here's a data plate for
you, 2 capture latches are out and one capture latch is
stuck in.
CC
Roger. Copy.
SC
Hey, Houston.
CC
Go ahead.
SC
Another data plate on that probe. It
turned out that that one was squashed and the little ear,
when I kicked it, it came up. It looks, to me, like 2 of
them had captured and this one, for what ever re- you can
tell better on the ground than I can. It would not come up
and allow the little lever to trip and lock it. It looked
like something was out of sequence with the trigger on that latch.
CC
Roger. Copy.
SC
Now. We've got all three capture latches
latched and if I push on the end of the probe, it will re
lease all three capture latches, they'll all fold and then
pull them all down. Now let's push that up. Now let it
go, they should all lock.
SC
All down?
Yeah. Two of them are up and the third
one is stuck down and I can't answer for you, why, and so
is the little center button stuck down.
CC
Pete, let me make sure I understand you.
You went through your little sequence there, at one point
you had all three capture latches out and you then tripped
it again, and they went in and one of them stayed in and
the button is - on the end of the probe is also staying
depressed.
SC
With me Rusty?
CC
Pete, do you read?
SC
Yeah, go ahead.
CC
Yes. Did you read my summary there?
Did it agree with what had happened?
SC
No, I didn't read your summary, let me
give it to you again. When we took the probe out, 2 latches
were out and they were out, but appar - (loss of comm) Push the plunger in the end of the probe - SC
Capture latch released.
�SL-II MC-77/2
Time: 10:39 a.m. CDT, 1:02:39 GET
5/26/73
SC
Capture catch released, but left side
button, it sticks in now; and the one latch, capture latch
stays flush and the other two pop up.
cc
Okay, Pete. At one point you mentioned
also, that the one that was flush, popped out when you kicked
the trigger on it, is that correct?
SC
Well, that's what I thought, but that s
what's not doing it now.
SC
Yes it is, too.
SC
I take that back, it is. Paul just did
it and it came up.
CC
Okay. I'll tell you what, we're going
to digest all that, Pete, and the boys in the backroom will
be working and we'll probably come back to you at some
later point. I suggest just going ahead with the time line.
CC
And one further question. What's the
status of the pyro cover? Did you put it on, or do you
still have it off?
SC
It's off.
CC
Okay, fine. We'll assume it'll stay off,
then and you're going to let us know where you stow it
temporarily?
SC
Yeah. We'll put the pyro cover in with
the probe in the bag.
CC
Okay, thanks.
CC
Skylab, Houston. We're about 40 seconds
from LOS. We'll pick you up again at Honeysuckle at 2.5.
SC
Okay.
PAO
Skylab Control, Houston, at 15 hours
52 minutes Greenwich mean time, our next station to acquire
will be Honeysuckle. We're out of range, now with Madrid
and that will be approximately 34 minutes from this time.
This is Skylab Control, Houston.
END OF TAPE
�SL-II MC-78/1
Times 11;04 a.m. CDT, 01:03:04 GET
5/26/73
PAO
Skylab Control, Houston; 16 hours 4 minutes
Greenwich mean time. During our Madrid pass, we had a momentary
communications dropout. However, we have recovered the tape,
and we'll play that tape for you now.
cc
Yes. Did you read my summary there; did
it agree with what had happened?
SC
No, I didn't read your summary. Let me
give it to you again. When we took the probe out, two latches
were out. Add they were out, but apparently not locked. One
was flush. Okay. Now, if we push the plunger in the end of
the probe - SC
Capture latch release - SC
- - capture latch release left side, but it
sticks in now, and the one latch, capture latch, stays flush,
and the other two pop up.
PAO
Skylab Control, Houston. That completes
our tape playback.
END OF TAPE
�SL-II MC-79/1
Timei 11:24 a.m. CDT, 01:03:24 GET
5/26/73
PAO
Skylab Control, Houston, at 16 hours 25 min
utes Greenwich mean time, less than a minute away now from
acquisition with Honeysuckle. The Skylab presently in an
orbit of 239 nautical miles by 235 nautical miles. We will
stand by to pick up conversation at that time when CAP COM,
Henry Hartsfield, calls up the crew of Skylab.
CC
Skylab, Houston, to Honeysuckle for about
9 minutes.
CC
Skylab, Houston, to Honeysuckle for 9 minutes.
SC
Roger, Houston. And be advised we had a
MAIN A undexvolt, which sucked the voltage down to about 25 volts,
and it turns out to be a heater cycle, as best we can determine
it. We must have had all the heaters on at one time. If you
^ can look at your low bed rate, if you'd add that on, maybe
you can come up with a better scheme for configuring these
heaters for us. We just spent 10 minutes sorting that one out.
CC
Roger.
SC
And we've got about 5 minutes to go on the
TDI sampling. We've gotten out sample and we're waiting the
15 minutes.
CC
Roger; copy. And we got a couple of things
for you too. It looks like we missed a couple of checklist
changes here that we should have gotten.
SC
Okay, hold it, and let me bring you up.
We've got the secondary glycol evap dried out and the primary
evap is on its way. Would you like E-memory dumped?
CC
Stand by.
CC
While we get set down here, we're - just
for your information, we're going to do a CMG reset at 16:33 at
about 6 minutes from now. Maximum excursion, we expect, is about
35 degrees in roll and 5 degrees each in pitch and yaw.
SC
Okay. Go ahead with your checklist changes.
CC
Okay, on page A-9, we had a comment earlier
about whether you want to close the latch handle, the hatch
handle, and that same comment applies there. On panel 312, we
just want that to read to close the hatch.
SC
Okay, just close the hatch; don't lock it,
is what you're saying.
CC
We don't - well, we had you closing in
the hatch handle then laying the hatch over on the dogs. We
didn't want to do that, we just want to strick that out so it
just says close the hatch.
SC
Oh, okay.
CC
But don't lock the hatch. And we're ready
for the E-memory dump any time.
CC
And the only other checklist change we
got for you is on page 2-51.
�SL-II MC-79/2
Time: 11:24 a.m. CDT, 01:03:24 GET
5/26/73
•t
SC
Who's it for?
CC
That's for the PLT.
SC
Ready.
,
CC
Okay, there on panel 390 in the aft lock
activation, we want to turn heat exchanger pans 1 ON. And
the reason we're doing that, Paul, is we want to stir up the
air there prior to getting a sniff sample there.
SC
The E-MOD's coming at you.
CC
Roger.
SC
Okay, JOB, you want the number 1 fan,
or do you want them all on?
CC
Just the number 1.
SC
Okay. And we chose - like you to look
at how we got that great big load on MAIN A because, as we remember
at it, it just sort of kinda of took care of itself there. We
were turning heaters on and off. But whatever heater cycle^
it was on, or maybe you'll see something on the data, but I 11 tell
you, we had one big load on that bus for a minute.
CC
Roger. We'll take a look at it.
CC
And, for info, our attitude plan is, after
we do the CMG reset here at Honeysuckle - at Hawaii, we're going
to command a small pitch maneuver to get a little more power
in preparation for activation.
CC
Roger.
SC
And, Pete, we got one more probe question
for you here in trying to psyche this one out^
SC
Go ahead.
CC
Okay. If the probe is not bagged yet,
if you'll look, minus X along the probe and using the strut
with the yellow end on it as a 12 o'clock reference, I wonder
if you could give us the clocking of the capture latch which
is sticking in.
SC
Hey, Rusty, on page 2-11 is the one you
can't see on that picture.
CC
Okay, I've got it. And let me ask you
another question. Jlave you rotated the head of the probe?
Or do you think it's the same as it was for docking attempts?
SC
We haven't touched that, and I'm sure it's
the same. It's just the way we took it out of there.
Okay. Fine. So that's - looking in the
CC
I
was
saying
that's something like 7 or 8 o'clock.
direction,
I
don't
know. It's in the bag now.
SC
Okay,
fine.
We've got it. Thank you.
CC
(Garble),
Houston.
SC
Go ahead.
CC
Okay,
we passed the TDI monitor check
SC
It's
pure white. Nothing that we could
with flying colors,
see at all.
�SL-II MC-79/3
Time: 11:24 a.m. CDT, 01:03:24 GET
5/26/73
CC
Roger; copy. That's good news.
SC
And we're on our way to the MDA. I wish
I had a poloroid picture to send down to you guys from the
inside of this command module with three suits, all that gear,
a drogue, a probe, and a hatch, Joe, Paul, and Pete.
CC
Roger. I'd like to see that myself.
SC
It's unbelievable.
CC
Okay, the CMG maneuver is coming up and
we got the E-memory dump; you're cleared to do the power down
now.
SC
Okay, going to P06.
SL-II MC-80/1
Time: 11:35 a.m. CDT, 1:03:35 GET
5/26/73
Cc
And, Pete, if you have the docking
index angles available, we'd like to get those.
SC
It's minus 1.5.
CC
Roger; copy. Minus 1.5.
cc
Skylab, Houston. We're about 15 seconds
from LOS. Looking good going over the hill. We'll see you
at Hawaii at 45.
., ,
gC
Okay, we've done the E—Mode. The (garble)
is deactive and (garble) proceed the MDA hatch opened.
CC
Roger; copy.
, t
5C
Paul just went in, and he said it s
very cold in there with the (garble).
CC
50 in there, I think.
SC
Yeah, boy, and it looks great. He just turned
on the lights.
Skylab Control, Houston, at 16 hours
PA0
35 minutes ground elapsed time. We've just had loss of sig
nal with Honeysuckle. Hawaii will be the next station to
acquire. We heard the rather lengthy discussion over Honey
suckle with the crew aboard Skylab, Pete Conrad reporting the
TDI sample tube completely white. At that point they proceeded to open the hatch to the multiple docking adapter. You
heard the remarks that it was quite cold in there, in the order
of 50 degrees. The lights in the multiple docking adapter
apparently working. The main A undervolt, referred to as in
the command service module, Conrad speculating that possibly
a configuration of all the heaters on at once could have
caused this. This data will be looked at on the ground.
Meanwhile, as we approach Hawaii, a maneuver is planned to
pitch the vehicle down 11 degrees to an attitude of 36 degrees,
and this providing for a better electrical power system, which
will be utilized in the course of the activation today. This
pitch-down maneuver has been computed by the EGIL flight controller
in the Mission Control Center, and the command will be given
by the ASCO console. We're at 16 hours 37 minutes Greenwich
mean time, and this is Skylab Control, Houston.
END OF TAPE
�
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Title
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Skylab Collection
Date
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1973-1979
Relation
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https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
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Skylab Collection
Description
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Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
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sdsp_skyl_000081
Title
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"SL-II MC75/3 Time: 10:17 a.m. CDT, 1:02:17 GET 5/26/73" - "SL-II MC-79/3 Time: 11:24 a.m. CDT 1:03:24 GET 5/26/73."
Description
An account of the resource
This mission commentary depicts the Skylab 2 crew working to secure the fastening between the Skylab 2 command module and the Skylab 1 habitat. This mission commentary also depicts the Skylab II crew working on the life support systems.
Creator
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United States. National Aeronautics and Space Administration
Date
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1973-05-25
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1970-1979
Subject
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John F. Kennedy Space Center
Skylab Program
Skylab 1
Skylab 2
Conrad, Charles, Jr.
Weitz, Paul J.
Kerwin, Joseph P.
Multiple docking adapters
Type
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Transcripts
Text
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Skylab Collection
Box 17, Folder 2
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
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Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14417/sdsp_skyl_000082_001.pdf
78339f6efea95b8bb290079da53b97b9
PDF Text
Text
SL-II MC-81/1
Times 11:44 a.m. CDT, 1:03:44 GET
5/26/73
PAO
Skylab Control Houston, at 16 hours
45 minutes Greenwich mean time apporaching acquisition now
with Hawaii. As we last saw the Skylab vehicle over Honey
suckle the multiple docking adapter hatch was just being opened
and the pilot Paul Weitz was proceeding inside as the activation
of the orbital workshop was at it's very beginning. Standing
by now for acquisition.
CC
Skylab, Houston to Hawaii for 9-1/2 minutes.
SC
Okay Houston, we're in the MDA and
we're pretty busy. I'm working on (garble) and we're jumping
around a little bit to try and clean up the command module
because we got so much stuff in it. So we're moving the
probe and drogue at this place. Be advised that nobody has
had any trouble so far in the MDA. And be advised to tell
the doctors that we did not in fact try our motion sickness pills
this morning because none of us felt like we needed them.
CC
Roger, copy.
SC
Also we've got a window shade dump.
And the command module is really beginning to pick up water
on the inside of it I noticed. Our side hatch has got quite
a bit of moisture on it and so do our windows. Just generally
picking up moisture all over. But now that we've got this
MDA dry air I think maybe that will help a little bit.
CC
Roger, copy.
CC
Skylab, Houston. The pitch maneuver's
in work, should be about 11 degrees.
SC
Okay, we're going to (garble) this
up up here so you guys can maneuver away to your hearts content.
SC
So far we've collected one screw, one
nut, and one piece of red thread floating around in the
MDA otherwise it's clean as a whistle. It's very nice.
CC
Roger, copy.
PAO
That's commander Pete Conrad reporting
on the status of the multiple docking adapter inside.
PAO
Sky lab Control Houston, the Skyled)
crew now inside the multiple docking adapter as the activation
process has started.
CC
Skylab, Houston, whenever it's con
venient we'd like to get a reading on the CL seunple.
SC
Okay, Houston, it was about 5 parts
per million.
CC
Roger, copy.
PAO
Very little conversation with the
crew at this time. Apparently preoccupied and busy as - as
they start through their checklist.
CC
Skylab, Houston, we're about 15 seconds
from LOS. We'll be picking you up at Goldstone at 57.
�SL-II MC-81/2
Time: 11:44 a.m. CDT, 1:03:44 GET
5.26.73
SC
Okay Houston, the MDA Doc is in
the command module and the suit circuit is deactivated.
CC
Copy.
PAO
Skylab Control Houston, we've had loss
of signal with Hawaii. We should be picking up Goldstone
in approximately 2 minutes.
SL-II MC-82/1
Time: 11:55 a.m. CDT, 1:03:55 GET
5/26/73
CC
Skylab, Houston. Stateside for 5 minutes.
PAO
Skylab Control, Houston, standing by
now for acquisition there with Goldstone. The five parts
per million CO referred to in that test is well within acceptable
limits.
SC
Roger, Houston, and we may be off the
air here. We're going through umbilical connect crap and so
forth.
CC
Roger.
PAO
Skylab Control, Houston, at 17 hours
2 minutes Greenwich mean time. A very little conversation
with the crew as they're continuing through the checklist as
the activation inside the multiple docking adapter continues.
END OF TAPE
�SL-II MC-83/1
Time: 12:06 p.m. CDT, 1:04:06 GET
5/26/73
PAO
Skylab Control, Houston. We've just
had loss of signal. Our next station to acquire will be
Newfoundland.
PAO
As the activation of multiple docking
adapter proceeds. Commander Pete Conrad presumably is
spending much of his time inside the command and service
module, squaring things away at that point, while Kerwin
and Weitz, we would expect, are mainly preoccupied with the
MTA activities. We're at 17 hours 7 minutes ground Greenwich mean time. This is Skylab Control, Houston.
CC
Skylab, Houston through Bermuda for
7-% minutes.
SC
Okay, Houston. We're hooking up umbilical
for SPS PT configuration check's been made; those guys are
pressing on.
CC
Roger, Copy.
PAO
That was Commander Pete Conrad responding
from the command module, stating that Kerwin and Weitz are
pressing on.
PAO
Henry Hartsfield, our CAP COM, here in
Mission Control.
PAO
Skylab Control, Houston, at 17 hours
13 minutes Greenwich mean time. About 2 minutes 45 seconds
remaining on this pass over Bermuda. The activation of
multiple docking adapter continuing with Kerwin and Weitz
working inside, and meanwhile. Commander Pete Conrad remain
ing in the command and service module. We'll stand by and
continue to monitor the conversation that takes place during
this pass.
CC
Skylab, Houston, we're about 1 minute to
LOS. Be seeing you at Canaries at 17.
SC
Roger, Houston.
CC
Okay, no need to acknowledge. And for
your info, we're playing back the data, now on the main A
undervolt. We don't think it's a big problem at this point,
but we are working on a plan. We'll have them for you later
this morning and we may want to change some switches and
bus setups in the command module.
SC
Yeah, that's what we finally concluded that it wasn't just sure we got too many heaters or some - PAO
Skylab Control, Houston. We've had loss
of signal with Bermuda. The next station to acquire is
Canary in less than one minute. We'll stand by and continue
to monitor. Meanwhile, the crew aboard Skylab continuing
to press on through the activation, Weitz and Kerwin, presently
in the multiple docking adapter; Pete Conrad communicating
with the ground through the command and service module. It
appears at this point, the Skylab Crew very much on their
time line for the activation.
END OF TAPE
�SL-II MC84/1
Time: 12:17 p.m. CDT, 1:04:17 GET
5/26/73
PAO
It appears at this point the Skylab
crew very much on their time line for activation.
CC
Skylab Houston through Canaries for
about 15 minutes.
SC
Okay, Houston.
PAO
Skylab Control, Houston, at 17 hours
23 minutes Greenwich mean time. Almost no conversation with
the crew during this pass. The crew most preoccupied at this
point as they go through their checklist for activation.
PAO
Skylab Control, Houston. The EGIL flight
controller reports, looking at his data that the caution warn
ing system is working in good shape aboard the MDA. Very little
conversation over the flight director's loop at this point,
controllers monitoring their consoles, watching data as it
appears.
SC
Hello.
CC
Hello.
CC
Skylab, Houston, you called?
PAO
We heard the callup from Pete Conrad to
conjecture here. He was CC
Did you call?
PAO
The conjecture here that he was trying
to reach Weitz and Kerwin via the comm loop in the workshop.
SC
Say Houston, Paul wanted me to tell you
he's got a primary coolant temp low. Is that to be expected?
CC
Standby 1. Roger that's expected. Temps
are running real low down there in the MDA.
SC
Okay the other thing is I've gone all
the way through the complete hookup and includes panel 230
CSMs with (garble). It actually got in a barber pole and none
of our SIA's need to talk to one another down there.
CC
Roger, we copy. During one of those
checkouts we heard someone say hello, hello there on the trans
mitter, I guess.
SC
That was me, Jim, sitting on VOX 98.
That doesn't count.
CC
Okay.
CC
Houston.
SC
Go ahead.
CC
Those SIAs aren't going to work until
you get down to the page 233 there for the PLT where he puts
the 8 audiocircuits in; closes those.
SC
Okay.
PAO
The SIA is the intercom system aboard
the workshop.
SC
We figured it was some place here.
�SL-II MC84/2
Time: 12:17 p.m. CDT, 1:04:17 GET
5/26/73
SC
Hey, Brad, SPT is about to start ATM
panel Y activation.
CC
Roger, and I assume that all the items
previous to that have been accomplished.
SC
That's affirmative.
PAO
That report from Skylab that the Science
Pilot, Joe Kerwin getting ready to start the Apollo telescope
mount activation, moving well along now into the time line.
We presently show a Greenwich mean time of 17 hours 32 min
utes. And 1 minute 45 seconds until loss of signal with
Ascension.
CC
Skylab Houston we're about a minute and
a half from LOS. Next contact is Carnarvon at 01 and at
Carnarvon we plan to uplink a test message to the teleprinter
and when you get that you can take a look at it and tell us if
it looks all right and then we'll be all set to send the pads
and the rest of the uplinks.
SC
Okay.
SL-II MC-85/1
Time: 12:33 p.m. CDT, 1:04:33 GET
5/26/73
SC
How do you read from the MDA, Houston?
CC
Okay, we're reading you, Paul. There's
a little squeal in the background. Looks like you're getting
some feedback from SIAs there.
SC
Yeah. That was one of them. Okay.
CC
Hey, you sounded real good then.
SC
Roger. We're getting there.
SC
PLT's on page 2-35.
CC
Roger, copy.
SC
The CDR's finishing up primary GLY ADAPT
DRYOUT, and I'll (garble) where the glycol circ reads (garble),
CC
Roger. Copy.
PAO
We just heard from Pilot Paul Weitz,
speaking through the intercom aboard the workshop.
SC
Houston, Skylab.
CC
Go ahead.
SC
Never mind, we'll catch you later.
CC
Okay. Well, I've got a few seconds to
LOS.
PAO
Skylab Control, Houston, at 17 hours
34 minutes Greenwich mean time. We've just had loss of
signal on this Ascension pass. The next station to acquire
will be Carnarvon, and at that time, from the Mission Control
Center, we will do an initial checkout of the teleprinter
system aboard Skylab. This is Skylab Control, Houston.
END OF TAPE
�SL-II MC86/1
Time: 12:59 p.m. CDT, 1:04:59 GET
5/26/73
PAO
Skylab Control, Houston, at 1800 hours
Greenwich mean time. We're standing by now for acquisition
of signal over Carnarvon. We presently show the workshop in
an orbit of 240.5 nautical miles by 234.2 nautical miles.
During this Carnarvon pass we should have the initial check
out of the teleprinter aboard the workshop. We'll standby
now and continue to monitor any conversations as they develop.
CC
Skylab Houston through Carnarvon and
Honeysuckle for about 10 minutes.
SC
Roger, Houston. How do you read?
CC
Roger, read you loud and clear.
SC
GARBLE okay the CDR has completed the
command module configuration through CM02 systems config and
I just completed the caution and warning checkout on the
GARBLE except for 392. And we're waiting right
now to go into the lock and the OWS; we're configuring for
that.
CC
Roger and we do have things we'd like
for you to set up in the command module. Are you up there
now?
SC
Yeah, but what do you want set up in the
command module?
CC
Okay we've looked at this heater prob
lem; we think you've already powered down enough things that
you're probably not going to get that undervolt again. However,
we would like to go ahead and reconfigure the heaters. We
were going to do it tonight anyhow but we'll go ahead and do
it and then we'll be doubly sure that we probably won't get
another undervolt, if you want to do that now.
SC
Okay, if you'll wait 2 seconds I'll take
you down into the command module and you can tell me what to
do.
CC
And Skylab for information we're going to
command the fill valves closed according to flight plan.
SC
Okay and I'm down in the command module
now. Could you tell me what you want done?
CC
Okay, panel 226; circuit breaker 02 fiftywatt heaters Main A, tow; MAIN A OPEN.
SC
Was that two breakers?
CC
That is tank 2, MAIN A.
SC
Are you with us Houston?
CC
Okay, we're in a hole right now between
Carnarvon and Honeysuckle. How do you read?
SC
You're right it was 251 OPEN, right,
MAIN A?
CC
Positive, tank 2 MAIN A OPEN. On 50 watt.
SC
That's done.
�SL-II MC86/2
Time: 12:59 p.m. CDT, 1:04:59 GET
5/26/73
CC
Okay on panel 2.
SC
Yeah.
CC
Okay our H2 heaters, one, OFF. 02 heaters.
one, OFF. And H2 fans, one, OFF and H2 fans, two, OFF.
CC
Skylab how do you read me?
SC
(static) are you going to (GARBLE) us
1? Hello, hello.
CC
Skylab Houston we're in a key hole now.
If you'll hang on a second or two.
SC
GARBLE.
CC
Okay, I think we're pretty good now, how
about you?
CC
Okay. On panel 2 that was H2 heaters, one;
02 heaters, one OFF. That was two switches.
SC
Okay, H2 heater, one, and 02 heater, one.
are OFF.
CC
Okay and H2 fans 1 and 2, OFF.
CC
CDR did you copy that last on the H2 fans?
SC
Where'd you disappear to that time?
CC
I don't know. Did you get the H2 fans
OFF?
SC
I got the H2 fans OFF, yeah.
CC
Okay. That's it.
SC
Houston, SPT.
CC
Go ahead.
SC
Okay on the panel activation I suppose
you know, but I want to be reassured that we have a power
system alert light, a bat charger alert light, the battery
and charger lights on CBRN 15 are ON and the - our charger the bat charge bat volts"-and reg volts talkbacks are all
barberpoled. Does that jive with the power problems that
you've got?
cc
That's affirmative. That all jives, Joe.
We've lost that CBRM.
sc
Okay and I did not connect the CBRM an
tenna because my assumption is we aren't going to use the I don't mean CBRN or FNRBM, the noise burst monitor. Now
I'm ready to do the DAS test if you are.
cc
Okay standby the DAS test. We agree
with the other things you said.
sc
Glad you can understand them.
CC
SPT, Houston.
CC
SPT, Houston.
sc
(Static) (Garble).
cc
SPT, Houston. I'm reading you broken.
We would like for you to go ahead and configure for the
GARBLE. We are not going to use it. We'll correct that but
we would like to get it connected up.
�SL-II MC86/3
Time: 12:59 p.m. CDT, 1:04:59 GET
5/26/73
SC
Oh. Houston are you there?
CC
Roger. How do you read?
SC
Okay. Do you want the EP spec on or off
on the panel 16?
CC
Roger. We want it on - ON.
CC
SPT, Houston.
SC
Houston.
CC
Joe we'd like to make one last attempt
on that CBRN number 15. We'd like you to hit the ALL/ON switch.
SC
You bet. Okay we did it Hank and the
lights are out at the moment.
CC
Hey, looks like me may have it back.
SC
Whoopee.
CC
We'll know when we get some sunlight.
SC
That'll be soon, right?
CC
We've got about 3 minutes to go. And
we're about 10 seconds from LOS. We'll be seeing you at
Hawaii at 23 and we plan to dump the data recorder there.
SC
Okay.
CC
And your teleprinter message should be
up there now.
SC
We'll take a look.
PAO
Skylab Control Houston at 18 hours
12 minutes Greenwich mean time. The next station we'll acquire
will be Hawaii in approximately 11-1/2 minutes. The later
portion of that pass over Honeysuckle that was Joe Kerwin the
Science Pilot who was speaking with Hank Hartsfield while he
was at the Apollo telescope mount control and display panel,
going through the activation process there. Eighteen hours,
13 minutes Greenwich mean time this is Skylab Control Houston.
END OF TAPE
�SL-II MC-87/1
Time: 1:22 p.m. CDT, 1:05:22 GET
5/26/73
CC
Houston through Hawaii for 9 minutes.
SC
Roger, Houston. Paul's down turning
on the fans in the OWS at this time. Joe is monitoring him
(garble) further word for you on that in just a minute. I
can see Paul is on his way back up now.
CC
Roger; copy.
PAO
Hank Hartsfield talking to Skylab
through Hawaii.
SC
Your teleprinter message came through.
It's kind of faded at the end. I hope they come through better
than that.
CC
Do you mean that all the message
wasn't there, or it just printed rather weakly at the end?
SC
It printed rather weakly at the
end.
SC
Okay, Paul is out. He's closing the
(garble) lock hatch at this time.
CC
Copy.
PAO
Skylab Control, Houston. That's Paul
Weitz who's taken off the airlock module aft hatch. Entered
the orbital workshop and appears to have activated the fans.
CC
Skylab, Houston. For information we're
going to have to do another CMG reset here. Be coming up
in a couple of minutes.
SC
Okay, Houston. What's the problem?
We've had two ACS^malfs here in the last couple of minutes.
CC
~ Well, the CMGs are saturated now (garble).
SC
Okay, all right. Are you ready for
the DAS test yet?
CC
Roger.
SC
Okay, here comes a (garble).
CC
Skylab, Houston. We just want him to
TACS on the control mode.
SC
Did you do that?
CC
Negative, I think it went out
20 degrees in attitude to cause it, and we'd like for you
to stay off the DAS while we command the system.
SC
Roger.
CC
Skylab, Houston. We're about 1 minute
from LOS. Goldstone coming up at 35.
SC
Roger. Do you still want us to stay
off the DAS?
CC
Okay, you can clear the caution on
your ACS malf, and we'll be standing by for Goldstone for
the DAS checks.
SC
Okay.
PAO
Skylab Control, Houston. We're about
a minute and a half away now from acquisition by Goldstone.
END OF TAPE
�SL-II MC-88/1
|Time: 1:34 p.m. CDT, 01:05:34 GET
w5/26/73
CC
Skylab, Houston through Goldstone for 6 minutes
SC
Hello.
SC
Hello, Houston, we hear you.
CC
Okay. Read you loud and clear.
SC
Hey, Houston; PLT.
CC
PLT, go ahead.
SC
Okay, on our very quick inspection, the
OWS appears to be in good shape. It feels a little bit warm,
as you might expect. From the 3 or to 5 minutes I spent in
there, I would say, subjectively, it's about - it's a dry
heat, I guess. It feels like 90 to a 100 degrees in the
desert. Hank, I could feel heat radiating from all around
me, but in the short time I was in there, I never felt un
comfortable. I had the soft shoes and the gloves on, and
nothing I touched even felt hot to me.
CC
Roger; copy.
PA0
It's Paul Weitz giving his first - cc
SPT, are you ready for those DAS tests?
SC
That's affirmative.
sc
Okay, I'm going to give you 10,000.
Please acknowledge.
cc
SPT, you got a GO on the first one.
SC
Okay, here comes 20,000.
cc
And, Paul, did you notice the duct flows
when you turned the fans on downstairs?
SC
If you want numbers, I didn't notice
numbers. They came up to what I expected to be normal.
cc
Okay; copy. And you have a GO on the
second one, Joe.
sc
Okay, and did I get this fuse thing going?
Turned on eight fans down there.
SC
You did want only eight fans turned on
for this, right?
cc
And, SPT, you got a GO on the third one.
We wanted all twelve fans, but that's okay.
SC
All right.
PA0
We heard Paul Weitz's first assessment of
the workshop.
CC
SPT, you got a GO on number 1.
CC
SPT, GO on number 2.
PA0
Meanwhile, Science Pilot, Joe Kerwin, making
an initial checkout of the ATM digital computer.
CC
j,
A GO on number 3.
cc
JwpjV
And you have a GO on number 4. All look good.
SC >• 1
Okay, thank you. And, Hank, it looks as
if CPRs 15 came off the line again. Is that right?
CC
Roger; we concur. I think we still got
:roubles with it.
SC
Okay.
�
Dublin Core
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Title
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Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
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Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
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sdsp_skyl_000082
Title
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"SL-II MC-81/1 Time: 11:44 a.m. CDT, 1:03:44 GET 5/26/73" - "SL-II MC-88/1 Time: 1:34 p.m. CDT 1:05:34 GET 5/26/73."
Description
An account of the resource
This mission commentary depicts the Skylab 2 crew trying to resolve a low temperature problem in the scientific airlock. The commentary also depicts the Astronaut assessment of the Orbital Workshop high temperature problems.
Creator
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United States. National Aeronautics and Space Administration
Date
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1973-05-26
Temporal Coverage
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1970-1979
Subject
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John F. Kennedy Space Center
Skylab Program
Skylab 1
Skylab 2
Conrad, Charles, Jr.
Weitz, Paul J.
Kerwin, Joseph P.
Multiple docking adapters
Apollo Telescope Mount
Life support systems
Space habitats
Type
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Transcripts
Text
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Skylab Collection
Box 17, Folder 2
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
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Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14418/sdsp_skyl_000083_001.pdf
12a36424c49c562a45c2a669ddf70905
PDF Text
Text
SL-II MC-88/2
Time: 1:34 p.m. CDT, 01:05:34 GET
5/26/73
SC
And by the way, Houston, this is SPT. I
take it you didn't have any changes for me on page 2-38 for
addition.
CC
That's affirmative; no changes there. And
if you want to clear that BATT VOLTS light, I guess you can
turn the charger and reg off - SC
Okay.
CC
- - and number 15 there.
SC
Okay, (garble).
CC
And, Joe, while you're there, do you have
any other talkbacks on the fire system that look like they
might be out of kilter?
SC
CDR says the fire detection system checked
out 40.
CC
Roger; copy.
CC
Skylab, Houston. We're about 10 seconds
from LOS; we'll pick you up again over Bermuda at 45.
END OF TAPE
�SL-II MC-89/1
Time: 13:45 p.m. CDT, 1:05:45 GET
5/26/73
CC
Skylab, Houston, through Mila for
10-1/2 minutes.
sc
Gosh Houston, we're just (garble)
your checklist here.
Cc
I didn't copy that last. Would you
say again?
,
,
SC
By gosh, we're just logging along
on the checklist here and we're gonna (garble) TDI sampling
in the OWS area after awhile.
CC
Roger, copy and for - Joe if you
are still at the ATM console, we would like for you to stay
off the DAS. We're gonna - we think the reason that our
momentum is building up is we're a little bit out of plane
so we're gonna command a Z rotation.
SC
Okay, you got it.
PAO
This would be a pitch down of some
6 degrees; this maneuver coming up. ASCO will be the flight
controller putting in the command.
PAO
Skylab Control, Houston, at 18 hours
and 48 minutes Greenwich mean time. We heard from commander
Pete Conrad reporting that they're moving well along on the
time line. Paul Weitz has been inside the workshop. He
gave a very good description of the temperature inside.
CC
Skylab to the CDR.
SC
Houston, SPT.
CC
Go SPT.
Spt
Roger, I'm not sure if it's okay for
me to go ahead with pages 2-42 and 2-43 or not with what
you guys are doing.
CC
Stand by.
CC
Okay Joe, the DAS is yours and also
we got a little message for the CDR.
SC
Go ahead and I'll relay.
CC
Okay, we goofed up a while ago and
didn't beat the quiscent checklist against our power
down on the panel 226, so next time Pete goes up there we d
like for him to go to 226 and turn 02 heater number 2, 100
watt, close the main B circuit breaker.
SC
Okay.
PAO
That last comment refers to the heater
configuration aboard the command and service module.
sc
Okay, Houston that was 100 watt 02 heater
2 MAIN B. Right?
CC
That is affirmative.
SC
It's on.
CC
Thank you sir.
Skylab, Houston, we're about 1 minute
cc
from LOS. We'll be picking up Ascension at 02.
�SL-II MC-89/2
Time: 13:45 p.m. CDT, 1:05:45 GET
5/26/73
Skylab Control Houston, we've had
loss of signal with Bermuda. Ascension will be acquired
by Skylab in approximately 6 minutes. We're now at 18 hours
56 minutes Greenwich mean time, this is Skylab Control Houston.
SL-II MC90/1
Time: 1:58 p.m. CDT, 1:05:58 GET
5/26/73
PA0
. PA0
Skylab Control, Houston, at 19 hours and
I minute Greenwich mean time, less than a minute away now
from acquisition through Ascension. This should be a long
pass over the Ascension station, somewhere in excess of
10 minutes.
cc
Skylab, Houston through Ascension for
II minutes.
sc
Roger, Houston; SPT. Over.
cc
Roger. Go ahead.
sc
Okay. In rolling the canister to unlock
the GSE nitrogen purge fitting, the initial roll postion was
minus 1440 instead of 1350 per the checklist. I thought about
it and went ahead and did the procedure? and it appeared to
work very well. I then deployed the scan spec mirror to the
unlock position per the red line checklist. And looked at
the DAS counter 2 scan spec mirror position; it read 6901,
|
f which is garbage. I just thought I'd pass that along for
evaluation and reassurance.
cc
Roger. Copy.
sc
I think it's because I don't have the
experiment powered up yet.
cc
That is affirmative. That's the reason,
Joe.
sc
Okay, and I'm about to sample TDI through
y
the aft hatch.
cc
Roger. Copy.
PA0
Joe Kerwin reporting he's getting ready
to sample the TDI through the aft airlock module hatch.
.cc
Skylab, Houston. Ww're going to be starting
a pitch maneuver here shortly to get you 6 degrees more
into the Sun for power, and we'd like you to stay clear of
the DAS.
cc
Skylab, Houston. Did you copy, reference
the DAS?
sc
No. Say again.
cc
Roger. We're going to be commanding a
maneuver in pitch, and we'd like to keep the DAS free.
sc
Okay, it is. Joe is in sampling the
workshop air right now.
cc
Roger. Copy.
sc
CDR is taking out the launch pins for
• the film vault, and the PLT is in the midst of his - getting
ready for water separator (garble) wetting.
CC
Roger. Copy.
CC
Skylab, Houston. The DAS is yours.
SC
GARBLE.
PA0
Skylab Control, Houston; 19 hours 7 minutes
Greenwich mean time. Science Pilot Joe Kerwin has been into
�fcL-II MC90/2
Rme: 1:58 p.m. CDT, 1:05:58 GET
5/26/73
the workshop taking samples. The crew moving well along in
compliance with their time lines at this point.
END OF TAPE
SL-II MC-91/1
Time: 2:00 p.m. CDT, 01:06:10 GET
5/26/73
CC
Skylab, Houston.
CC
Skylab, Houston.
CC
Skylab, Houston. (static) and set it at
19:21. It's just past 19:21 and it looks like you're GO for
(static).
CC
Skylab, Houston.
PAO
Skylab Control, Houston. We've just gone
out of acquisition range with Ascension. The next station to
acquire will be Carnarvon, some 22 minutes from this time.
The last message passed by Henry Hartsfield, which may or
may not have been heard by the crew, was a request to command
reset for a roll maneuver. Since we have been experiencing
some drift in attitudes, and to do this via the control
moment gyros versus the attitude thrusters would be highly
desirable from the mission point-of-view. We're at 19 hours
14 minutes Greenwich mean time, this is Skylab Control,
Houston.
END OF TAPE
SL-II MC-92/1
Time: 2:26 p.m. CDT, 01:06:26 GET
5/26/73
PAO
Skylab Control, Houston, at 19 hours 26 min
utes Greenwich mean time, and 2:25 p.m. central daylight time.
One point of clarification, when Paul Weitz first entered the
orbital workshop, he was wearing a mask and was observed by
Science Pilot, Joe Kerwin, during this time, through the hatch
while he, too, was wearing a mask. The TDI CO sampling, which
was done following this, took place through the aft airlock
module hatch with no crewmember inside the orbital workshop.
This is Skylab Control, Houston.
END OF TAPE
�SL-II MC-93/1
Time: 2:34 p.m. CDT, 01:06:34 GET
5/26/73
PAO
This is Skylab Control at 19:34 Greenwich
mean time, 30 seconds out from the Carnarvon, Australia, Track
ing Station. A pass that will last about 10 minutes and
40 seconds. A short hop across West Irian and to the Guam
tracking coverage. We should have acquisition at this time;
we'll stand by for CAP COM's call.
SC
Skylab, Houston through Carnarvon for
10 minutes.
CC
Skylab, Houston. Do you have anything to
report on the TDI sniff?
SC
It's cooking. It's time (garble), Houston,
and so far it doesn't look like anything, but we'll let it
run its full (garble).
CC
Roger; copy. And for the SPT, we just
dug out some info and learned that the canister was launched
with a roll of 14 30. So the reading he got was right on the
money.
SC
Okay. He's nodding his head, and if you're
looking at the data, you may have just seen a note to (garble)
the command module. We activated the water system again so
that we could get some chow.
CC
Roger; copy. And to help our pyro situation,
I guess we'd like to get the OWS entry lights turned off there
in the aft lock here while we're eating lunch - after you com
plete the sniff.
SC
Okay, we'll get that as soon as we're done
testing for TDI. I though I turned them off when I came
out. Hank.
CC
Okay, you may have. Yeah, he did.
SC
If you think I'm not power conscious here,
I thought I'd thought about it, and you guys caught me. And I
have something else for you on the corner space tank dump system.
(Garble) heaters when you're ready to listen.
CC
Okay, go ahead.
SC
Turn to procedure on page - wait until I
find the page.
CC
And we'd like for you to keep clear of the
DAS for the next few minutes.
SC
I'm within 3 feet of it. That won't
hurt it, will it?
CC
That'll be safe enough.
SC
On page 119, Henry, he's preping for this You ready to listen to me? You were talking about some
thing else to somebody else.
CC
Go ahead.
SC
Okay. Anyway, apparently, on our corner
space tank, it appears that the secondary vent heater did not
work. I turned it on, and the light came on, and I came back
�•
SL-II MC-93/2
Time: 2:34 p.m. CDT, 01:06:34 GET
5/26/73
and checked it about 20 minutes later. The temperature was
reading zero. I cycled the circuit breaker. The light went
out and came back on. I went to primary, and afterwhile its
temperature came right on up. So I went ahead and did that
dump, using the primary system. You might think about it and
see what other readings you have on the ground, if any, and
1
let us know.
CC
Roger; we copy.
Su .
•
Also, I don't know, but I turned that heater
off about 10 minutes ago, after having dumped through it, and the
temperature is still pegged high, in excess of 150.
cc
Roger; we copy.
Sky lab, the DAS is yours.
^.
Skylab, Houston. For info, we're going to
be sending up via teleprint, hopefully prior to the stateside
pass, some mod's to the parasol deployment checklist; so you'll
have time to browse them over before you have to do it.
sc
Okay.
CC
Skylab, Houston. One minute to LOS; Guam
at 49.
sc
Okay. Stand by for the TDI results.
CC
Okay.
S(- ,
TD1 level's okay. There's no discernable
change in color.
cc
Roger; copy. That's good news.
,fc
Smells kind of funny in there, though.
Smells like hot metal for some reason.
cc
Roger.
sc
Or it's from this vent on.
^
Smell anything like butterscotch pudding?
. PA0 ,
This is Skylab Control. We've had loss
of signal through the Carnarvon, Australia, Tracking Station.
About 2-1/2 minutes to Guam. We'll leave this circuit up for
that small jump across to the Guam station. At 19:46 Zulu
and standing by, this is Skylab Control.
END OF TAPE
�SL-II MC94/1
Time: 2:47 p.m. CDT, 1:06:47 GET
5/26/73
CC
Skylab, Houston through Guam for
9 minutes.
SC
Roger, Houston.
SC
Roger. We'll have some (garble) results
for you in a couple or 3 minutes.
CC
Okay. Standing by.
SC
Hello, Houston.
CC
Roger. Go ahead.
SC
Okay. No detectable CO, according to
our tester in the workshop.
CC
Roger. Copy.
SC
We're going to close the hatch again
and eagerly awaiting your GO for entry.
CC
Roger.
SC
You want me to turn on those other
three spare, other four fans, Hank, or just let her run on
eight.
CC
Stand by 1.
9C
Okay, Paul. We'd like to just leave
it like it is now, and you can turn out the lights and go
on about your business.
sc
Okay. That's complete; the lights are
out, and Joe's securing the airlock aft hatch, right
now.
SC
And we're going to leave the airlock
forward hatch open. (Consider the airlock is - the walk
compartment of the airlock is usable and livable.
CC
Roger. We concur.
sc
Hey, Henry. I've got one more question
for the ECS guys.
CC
Okay. Go ahead.
SC
Okay. I don't want to waste going
through one of these water separator plate wetting deals. The
dewpoint right now is 36 degrees. Is it going to do me
any good to wet the plates now and put them in?
CC
Stand by 1.
SC
Okay.
END OF TAPE
�SL-II MC-95/1
Time: 2:55 p.m. CDT, 1:06:55 GET
5/26/73
CC
Standby one.
SC
Okay.
CC
Skylab, Houston. For Paul - well we'll
go ahead and delay doing that right now. Looks like it's
going to be quite awhile before we need the things. If it turns
out that we do need them, it looks like the SPT may have
some free time later to say it.
sc
Yeah, okay. That's just a rather
lengthy procedure and I didn't want to waste time doing it
twice, that's all Hank.
CC
Okay, and we got about 1 minute to
LOS so we'll be coming up at Goldstone at 14.
SC
Roger.
sc
(garble) around here. Hey, something
else for them to think about is since we got a late start
we got about 2 hours and 45 minutes left to go in the bake out
of bed 1. You ought to ask Vick what they want to do about
bake out of bed 2.
CC
Roger, copy.
SC
..
Well, why don't we do it tonight or put it
off until tomorrow morning on that one?
PA0
This is Skylab Control. 19:59 Greenwich
mean time. Loss of signal out of the Guam station. 14 minutes
and a half until acquisition at Goldstone station in the
Mojave Desert in California and a fairly lengthy stateside pass
through most of the stations. During this just completed
pass over Guam, Paul Weitz reported that there has been no
change in the TDI level in the workshop. The sensor still
came out white. He did comment that it smells like hot
metal. OWS pressure holding now at 5.1 pounds. Weitz also
reported that there's no detectable carbon monoxide in the
workshop. And as they prepare for their lunch meal the
crew will close off the workshop but consider the airlock
module as a habitable area for the time being until activation
of the workshop itself is complete. Currently the Skylab
cluster is in an orbit measuring 235.1 nautical miles at
Perigee, and 239.2 nautical miles at Apogee. Orbital
period 1 hour 33 minutes and 22 seconds. At 20:01 Greenwich
mean time, this is Skylab Control.
END OF TAPE
�SL-II MC-96/1
Times 15:13 p.m. CDT, 1:07:13 GET
5/26/73
PA0
This is Skylab Control; 20:13 Greenwich
mean time, which translates out to 3:13 central daylight time;
44 seconds now from a good solid state-side pass. We've got
a LOS, now.
cc
That's affirmative. It looks like
you ought to be coming right up, or near, Seattle.
sc
Okay. Mr. Weitz just recognized the
world?
sc
Oh yeah. And we'd like you to pass
along to the Principal Investigator of ah - sc
Pardon me, (chuckle) to Don Lind, that
his experiment is in super shape.
CC
Roger; copy.
sc
We can see it out the window.
cc
Skylab, Houston (garble) you notice
any lights changing down on your CBRMs. We're managing
5 and 6. Because of the attitude, we're having trouble
getting the batteries charged. So, we're just kinda switching
them around. So, that would explain any lights that you see
on those 2.
SC
Roger, Houston.
sc
Say, Houston, you with us?
CC
That's affirmative.
sc
_
We're getting ready to eat lunch. Waiting
for your GO to go on into the workshop and it's my - contamination
goes on any one of these 4 STS windows. They are just as clean
as a whistle. They're as clean windows as I've ever seen in a
spacecraft.
CC
Roger; copy.
cc
CDR, Houston. You're GO for entering
OWS and the modifications of procedure should be coming up
SC
Okay. We're going to go eat. It's
kinda hard to get away from the windows, especially for the
new boys.
CC
Roger.
SC
The Pacific Northwest is really some
thing. Right now, we're over what appears to be a fairly
major weather system with pretty good overcast clouds in the
Montana, Dakotas region.
CC
Roger; copy.
CC
And for info, we're also going to be
doing another CMG reset at 2:08, a nominal (garble).
SC
Roger. We'll wait for all the clang,
bang and the bells to ring.
SC
Also, Hank, not having spent any great time
at 237 nautical miles, why we passed some familiar landmarks like
NAS Whimpy and a couple of other airfields. And we can see
those runways pretty good. So, hopefully we'll do pretty
�
Dublin Core
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Title
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Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
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Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
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sdsp_skyl_000083
Title
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"SL-II MC-88/2 Time: 1:34 p.m. CDT, 1:05:34 GET 5/26/73" - "SL-II MC-96/1 Time: 15:13 p.m. CDT 1:07:13 GET 5/26/73."
Description
An account of the resource
This mission commentary primarily depicts the Skylab 2 crew carrying out maintenance on the life support systems. This mission commentary also depicts the Skylab 2 crew operating the Apollo Telescope Mount.
Creator
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United States. National Aeronautics and Space Administration
Date
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1973-05-26
Temporal Coverage
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1970-1979
Subject
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John F. Kennedy Space Center
Skylab Program
Skylab 1
Skylab 2
Conrad, Charles, Jr.
Weitz, Paul J.
Kerwin, Joseph P.
Provisioning
Airlock modules
Life support systems
Space habitats
Type
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Transcripts
Text
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Skylab Collection
Box 17, Folder 2
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14419/sdsp_skyl_000084_001.pdf
799b8f661fc73f3bf0aa9a78a578260b
PDF Text
Text
SL-II MC-97/1 —10?
Time: 3:23 p.m. CDT, 1:07:23 GET
5/26/73
sc
Pete, tell them about the one operation;
it wasn't any easier.
Sc
Yes, the doctor wanted me to remind
you, though, that the one operation that has not changed in
the history of manned space flight was just performed by
a CDR, and, as usual, its backup (garble) it takes approxi
mately 1 (garble).
CC
(Laughter) Roger; copy.
SC
(garble) and we just passed Florida, as
I'm sure you know. And that we were able to make out - the
(garble) Cape and from there we could all (garble) could not
actually see the buildings. Do you see the cleared area around
the VAB? Do you see the (garble) way out to the pads, both
pads, and also make out quite distinctly the (garble).
CC
Wow, must be pretty down there today.
SC
It looks like they get some super
big boomers in Miami, and that's just right to the Cape, too.
CC
Roger. In fact, one of them must have
got us, because we are having a little trouble with our command
lines. That teleprinter message on the procedure change
may be a little late getting up to you. However, there
are no changes, at least up to step 5.
SC
Okay, good enough. Gosh, something's
coming in now.
CC
Okay, the step 5 was in the parasol
deployment.
SC
That looks like black magic - that stuff
coming out of that teleprinter.
CC
Skylab, Houston. For info, we'll be
dumping the data recorded over Bermuda, which is just a
couple of minutes from now.
SC
Okay, and as I remember, the cue cards
for the (garble) deployment are in the back of the rendezvous
book. Is that right?
CC
Stand by.
CC
That's a correct location. Back of the
rendezvous book.
SC
Okay, thank you.
SC
Hey, Hank, you with us?
CC
Roger.
SC
Okay, I rewound the video tape recorder.
It took about 3 minutes and 20 seconds for it to rewind. That s
all configured for you.
CC
Roger, thank you.
CC
Skylab, Houston. Teleprinter load
should be up to you now, and you look those over. If you
got any comments, you can give them back to us. We got about
1 minute left on this pass.
�V
SL-II MC-97/2
Time: 3:23 p.m. CDT, 1:07:23 GET
5/26/73
SC
Okay, Houston, I've got them in hand,
and the teleprinter does a very nice job, except it's awfully
faint.
. .
.
SC
We don't know whether it s this particular
paper or whether that's the way it's going to be the
rest of the time. (garble) difficult to read.
CC
You can read it all, can't you, Pete?
SC
I think so. Hank.
SC
Okay, we're just short of LOS. And
our next contact is going to be Carnarvon at 13, which
is a long time from now, and we'll be dumping the recorder
there again.
.
SC
Okay, hopefully we'll have had lunch
by then, and we'll work these changes while we're doing lunch.
CC
Okay.
PAO
This is Skylab Control. We've had
loss of signal apparently. The station is in the eastern
test range. Next station Carnarvon in 39 minutes. During
the just completed stateside pass, the commander reported
that he could see runways on airfields across the northern
United States. And commented that, hopefully, we'll do pretty
well with EREP, referring to the earth resources experiment
package, which does multispectral scanning and photography
of Earth features. He also commented that the mobility in
zero-g, going back and forth along the multiple docking adapter
and airlock to the CSM and performing their activation chores,
he commented that the mobility is super. Coming across Florida
they reported seeing features at Kennedy Space Center, the
cleared area around the vehicle assembly building. Conrad
also brought up the fact that the Skylab windows were as
clean as any he'd ever seen in any spacecraft. And looking
up toward the telescope mount truss, he mentioned that the
that Don Lend's experiment was in super shape. This refers to
,,-nr-un Astronaut Don Lend, who is also a co-investigator on experiment
t y I number S23Q. magnetospheric particle composition experiment.
jtf'yirf.His co-investigator is Dr. Johannes Guiss of the University of
/perne in Switzerland. The detector is mounted on the ATM strut, with
cuff over it. And the detectors will be brought in during
'the EVA in which the ATM film canisters are retrieved.
QT Crew presently is having a lunch meal, and they should be well
into preparations for deploying the parasol during the next
M stateside pass, which is still another hour and 15 minutes
away, when we come across Goldstone. Next station to
acquire will be Carnarvon in 36 minutes, followed by Guam,
with a slight gap between the two stations. At 20:36
Greenwich mean time, 3:36 central time, this is Skylab Control.
END OF TAPE
�SL-II MC-97/2
Time: 3:23 p.m. CDT, 1:07:23 GET
5/26/73
SC
Okay, Houston, I've got them in hand,
and the teleprinter does a very nice job, except it's awfully
faint.
SC
We don't know whether it's this particular
paper or whether that's the way it's going to be the
rest of the time. (garble) difficult to read.
CC
You can read it all, can't you, Pete?
SC
I think so, Hank.
SC
Okay, we're just short of LOS. And
our next contact is going to be Carnarvon at 13, which
is a long time from now, and we'll be dumping the recorder
there again.
SC
Okay, hopefully we'll have had lunch
by then, and we'll work these changes while we're doing lunch.
CC
Okay.
PAO
This is Skylab Control. We've had
loss of signal apparently. The station is in the eastern
test range. Next station Carnarvon in 39 minutes. During
the just completed stateside pass, the commander reported
that he could see runways on airfields across the northern
United States. And commented that, hopefully, we'll do pretty
well with EREP, referring to the earth resources experiment
package, which does multispectral scanning and photography
of Earth features. He also commented that the mobility in
zero-g, going back and forth along the multiple docking adapter
and airlock to the CSM and performing their activation chores,
he commented that the mobility is super. Coming across Florida
they reported seeing features at Kennedy Space Center, the
cleared area around the vehicle assembly building. Conrad
also brought up the fact that the Skylab windows were as
clean as any he'd ever seen in any spacecraft. And looking
up toward the telescope mount truss, he mentioned that the that Don Lend's experiment was in super shape. This refers to
Astronaut Don Lend, who is also a co-investigator on experiment
number S230, magnetospheric particle composition experiment.
His co-investigator is Dr. Johannes Guiss of the University of
Berne in Switzerland. The detector is mounted on the ATM strut, with
a cuff over it. And the detectors will be brought in during
the EVA in which the ATM film canisters are retrieved.
Crew presently is having a lunch meal, and they should be well
into preparations for deploying the parasol during the next
stateside pass, which is still another hour and 15 minutes
away, when we come across Goldstone. Next station to
acquire will be Carnarvon in 36 minutes, followed by Guam,
with a slight gap between the two stations. At 20:36
Greenwich mean time, 3:36 central time, this is Skylab Control.
END OF TAPE
�SL-II MC98/1
Time: 16:12 p.m. CDT, 1:08:12 GET
5/26/73
PAO
This is Skylab Control; 21 hours 12 min
utes Greenwich mean time. We have acquisition at Carnarvon.
This Carnarvon pass lasts almost 10 minutes. Flight Direc
tor Neil Hutchinson has been going over the procedures for
deploying the parasol device to understand in his mind,
how the thing works, how the rods are attached one at a time
and pushed out with retainer knobs attached.
CC
Carnarvon for 7 minutes and we'll be dump
ing the recorder.
SC
Roger. Okay. The CDR's headed into the
workshop right now with duals ahead trying to (garble).
CC
Roger; copy. And the next guy through
the airlock there we'd like to get him to turn OWS heat
exchange fans number one off. We don't need that anymore
and we'll conserve a little power.
CC
Skylab, Houston. Did you have any ques
tions on the mods we sent up by teleprinter?
SC
I just finished incorporating them in
the cue card, Hank. We haven't really had the time to go
over and review them. We'll do that later.
CC
Okay. And ah - For the SPT there, he's
to set up the TV. We'd like to give you some words on order
of priority. The number 1 priority is, that he be able to
observe the deployment. If the TV camera's going to inter
fere with his observation, then eyeballs come first.
SC
Roger. This morning is the first time
I had an inkling you guys wanted to see this and I just
haven't thought about it, yet.
CC
Okay. It's called out there on our page
A-4 in the time line.
SC
Yeah, which I saw this morning for the
first time.
SC
Say, Hank. There's one whale of a lot
of stuff in that command module. And we'll see if we can
get it out.
CC
Okay.
SC
Because in order to neaten it up to leave
room for three guys, among other things, we had to dismantle
the TV and restow it. In order to get it out, we are going to
have to move a whole lot of other stuff.
SC
We'll try to do it, but we're not promising
anything, is what I'm saying, I guess.
CC
Okay. That's good, but before you try it,
take a look out the window and see if you think you're still
going to be able to see if the TV camera is installed.
SC
Ahhh yeah, well, oh I see your side yeah.
CC
Well, the number 1 priority is being able to
see it with your eyballs, and if the camera interferes we
don't want the camera.
�SL-II MC98/2
Time: 16:12 p.m. CDT, 1:08:12 GET
5/26/73
you cannot see out that window with the TV
camera in there.
,
i tried that yesterday and I coudn t see
sc
and I didn't get any TV by trying to do both.
CC
Okay; copy.
,a ,..
i guess, if it's feasible, what we^d like
cc
to do is have you eyeball the deployment and after it's de
ployed give us a TV picture of it.
SC
Understand you.
Skylab, Houston. We're about 30 seconds
cc
from LOS. We'll be coming up on Guam at 27.
SC
Roger, Houston.
.
This is Skylab Control; 21:22 Greenwich
PA0
mean time, in a gap now between Ca:rnarvon 'Track*"9
and the Guam Island Tracking Station in the western Pacific.
Some discussion over Carnarvon on deployment of the parasol
through the solar scientific airlock. It was mentioned that
TV would be desirable through the command module window as
the parasol is extended up above the workshop wall. However,
the eyeball observation was prime. TV would be nice, but
not to let it interfere with Kerwin's visual observation of
the parasol. However, it was mentioned that after it was
successfully deployed, it would be highly desirable to have
a television picture. The parasol that is being carried was
the brain-child of Jack Kinzler, who is Chief*°VidwIre fo?
Services Division at Johnson Space Center. The hardware for
the parasol, all of the telescoping tubing up, and all or
the deployment mechanism adapted to the TO-27 canister we
all built in the Tex Services Machine Shop. The parasol
canopy was also constructed here at Johnson Space
During all of the testing and modification period, the test
teams worked around the clock. Most of the testing was ..
headed up by Don Arabian. The poles wort, rather Uke oollapa
able tent poles, in that they-re aiuminuopolesortubinq o
descending diameters to telescope inside each other with
sc
—ZSiHlrMIS & Hrur-
Environment Test Division, building 32. ^"^"^.^rigqers
all the care of a parachutte. In fact, parachutte riggers
did most of the actual packing_and folding down to a packag
iiAnnnnh fro fit into the 8 by 8 inch square canister, which
is^some 53 inches long inside.
teflon sleeves, then sheets
of Teflon on the 4 sides of the canister
END OF TAPE
�SL-II MC99/1
Time: 4:25 p.m. CDT, 1:08:25 GET
5/26/73
_ which is some 53 inches long inside.
PA0
Teflon sleeves, thin sheets of Teflon on the four sf^es
the canister, will aid in allowing the canopy to slide outward.
The Teflon will act as a lubricant. We're less than a minute
away now from Guam station. We'll leave the circuit up for
the Guam pass. And we're 25 minutes out of Goldstone. This
is Skylab Control standing by.
Skylab, Houston through Guam for 8 ramcc
Sc
Roger, Houston. This is the SPT. (garble)
The other two guys are in the workshop getting ready for
parasol deployment.
cc
Roger; copy. And, for your information,
we'll be switching the mission timer from B to A according
to the Flight Plan.
CC
Skylab for the SPT.
SC
Go ahead.
cc
Okay. Are you up in the STS or ATM panel
now?
SC
I'm moving now, but I can get there
(GARBLE.)
,
^ ^
.
Cc
You're picking up a lot of feeabacK
through the SIAs, Joe. I'm having trouble reading you l0UdScqUGal*
I know. I had my hands full of (garble).
iftfl had to use the wrong VOX. Go ahead.
.
v
oh, okay. Sometime when you get a break
cc
there, we'd like for you to take a look at the Calfax
fasteners on the teleprinter print cartridge and see if
they are tied. J don't know whether that's - I can't imagine
tnem not being tiea, but it's one thing we couldn't check.
sc
Standby. They're all tied. Hank.
CC
Okay, thank you.
CC
Skylab, Houston. For info, we're initializing
a shutdown.
SC
Roger.
CC
Skylab, Houston. The DAS is yours.
CC
Skylab, Houston. For information, we're
commanding a (garble).
SC
Roger.
CC
Skylab, Houston. We're about 15 seconds
from LOS. Goldstone at 51.
PAO
This is Skylab Control, 21:35 Greenwich
mean time. And we have gone out of range over the hill from
the Guam Island tracking station; 15 minutes now until
Goldstone in California. Crew at this time making preparations
for attaching the canister containing the Skylab parasol to
�SL-II MC99/2
Time: 4:25 p.m. CDT, 1:08:25 GET
5/26/73
the solar airlock (scientific airlock), a rather tedious job
of extending the parasol, attaching one section of rod at a
time to the central core rod, the main shaft of the parasol.
This main shaft is actually part of the hardware for the T027
experiment, and the parasol four diagonal ribs and central
hub were simply attached to the existing experiment hardware.
The outer ends of the telescoping ribs are attached by screws
to the inner plate, end plate, of the canister, and as the
canopy is fully extended by successive attachments of rods,
much like going down in a hole with drill stem in an oil well,
the four screws will be released at the end plate, allowing
the ends of the rods to pass on out through the canister
past the wall of the workshop and rotate 90 degrees into the
four corners, taking the folded parasol canopy with it. At
21:37, up again at Goldstone in 13 minutes, this is Skylab
Control.
END OF TAPE
�•
L-II MC-100/1
ime: 16:48 p.m. CDT, 1:08:48 GET
5/26/73
PAO
This is Skylab Control. 21:48 Greenwich
mean time, 4:48 Central daylight time. Acquisition at
Goldstone in 2 minutes 25 seconds. Crew still at this time
making preparations for deploying the Skylab parasol. They
first have to move a water tank from the floor of the
workshop up to it's permanent resting place lashed down up in
the - near the dome. During this stateside pass the final
discussion of the changes in the deployment procedure for
the parasol will be carried out. Just one more stateside
pass after this one. And then we are pretty much on the
back side of the orbit which takes us through the Hawaii
station and Vanguard for several REVs before we start coming
back on the main part of the network. Less than a minute
now to Goldstone. We'll standby for the initial call from
the spacecraft communicator Hank Hartsfield. Standing by
at 21:50 Greenwich time, this is Skylab Control.
CC
Skylab, Houston to Goldstone and
stateside for 15 minutes.
SC
Roger Houston. We have had what we
consider to be 3 false alarms from BUS 1 fire detector in
the center sleep compartment. And in all(garble) instances,
^fcthey were transient, lasting less than two seconds. However,
^Rhe first time it does give you a start. And for right now
we got Bus 1 powered off on that detector.
CC
Okay. Would you say again the location?
SC
The detector in the center sleep
compartment. Sleep compartment number 2.
SC
Roger, copy.
SC
Work is progressing. We've relocated
the (garble) holding tank, and that went like a piece of
cake, just like two thousand and in one. We've done the tripod
move. We got the foil off the SAL. It is in good condition
we're in a process of moving the T027 down now, while Joe
hunts for the (garble) bags.
CC
Roger, copy.
CC
Skylab, Houston. Paul, we're having to
manage this momentum and do maneuvers here pretty often as you
know and we feel that we can't afford to have a maneuver
while you're pushing this thing out. Now you can work
all the way up to step 22A, but we'd kind of like to a
feel for, later on in the pass here. We got about 12 more
minutes. About when are you going to get to that so we can
manage the momentum?
SC
Okay, Hank. Paul heard that and tells
me that they don't have a field yet for what they are going
to be at that - We'll let you know.
�SL-II MC-100/2
Time: 16:48 p.m. CDT, 1:08:48 GET
5/26/73
okay, I just wanted to make you
cc
aware. I knew you wouldn't know at this point. But as you
start working along maybe you can get an idea about when
it will be.
You bet.
SC
.
.,
Skylab, Houston. We'd like to verify
cc
that - that you have read the procedure and don't have any
questions about it because we're starting to come up on the
time of day when we don't have many station contacts. In fact,
after we dJrop out stateside here, we'll pick you up at Vanguard
in about 20 minutes and that's the last pass before Goldstone.
Okay, I'll pass that word to the
sc
workshop Hank. How many minutes left on this pass?
Okay, we got 10 minutes here.
cc
SC
Okay.
END OF TAPE
�•
-II MC-101/1
me: 4:56 p.m. CDT, 01:08:56 GET
5/26/73
CC
Skylab, Houston. For information, we'll
be commanding the spectrometer on the CSM; no action required.
SC
How do you read, Houston?
CC
Roger; I'm reading you loud and clear, Pete.
SC
Okay, I got you on the speaker box (garble).
1 got one of my hot gloves back on again. The speaker box is
about 130. We're taking the tape off the box and we're taking
our time right now, and if we have any questions on the pro
cedures, we will wait to ask you.
CC
Roger; copy.
SC
It occurs to me, the question I had was
why did you want to reverse the sleeves on the SAL tripod?
CC
Say again, please?
SC
On the SAL tripod, why did you reverse the
speed on it? You know, I just couldn't figure out why (garble).
CC
That's the screws that - the way the thing
is mounted there for launch, Pete, you know, you turn those
around, as part of activation.
CC
SPT, Houston.
SC
He's down in the workshop.
CC
Okay. SPT, just give us a call when you're
ee for a minute.
•
SC
Can I relay you. Hank?
CC
Negative. I just got a little pass we want
him to perform here sometime when he's free, and I need to read
it to him whenever he's got a chance to listen.
SC
Okay.
CC
Skylab, Houston. For information, no action
required, we're going to do another nominal H-cage in about
2 minutes.
SC
Okay.
CC
Skylab, Houston. Is one of the guys
near the ATM console?
SC
No, we're all in the OWS.
CC
Okay. We're just trying to verify here.
We saw a change of status on the CBRM's. We're managing 5 and 6,
Now, we're about a minute from LOS now. We'll be picking you
up at Vanguard at 17.
SC
Okay.
CC
And the reset are the nominal H-cage should
be starting now.
SC
How many minutes until sunset?
CC
Okay, sunset's coming up in 13 minutes.
SC
Sure gets hot down here on the stateside
pass, and the other thing is when that TACS goes off, it sounds
_like somebody's beating on the bottom of the lab with a hammer.
CC
Roger.
PAO
This is Skylab Control at 22:06 Greenwich
mean time, 5:06 central daylight. Ten minutes to Vanguard
Tracking Station. Apparently we have had loss of signal
through Mila, a tracking station near Kennedy Space Center
�•
L-II MC—101/2
ime: 4:56 p.m. CDT, 01:08:56 GET
5/26/73
in Florida. Pete Conrad commented that during this last pass,
that moving the water tank from the floor of the workshop up
onto the wall, was a "piece of cake". And just a few moments
ago, he said that any time the TACS system, or thruster attitude
control system fired, it sounds like someone pounding on the
workshop with a hammer. We'll bring the line up again at
Vanguard in about 9 minutes. At 22:07 Greenwich mean time,
this is Skylab Control.
END OF TAPE
�
Dublin Core
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Title
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Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
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https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
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Skylab Collection
Description
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Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
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sdsp_skyl_000084
Title
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"SL-II MC-97/1 Time: 3:23 p.m. CDT, 1:07:23 GET 5/26/73" - "SL-II MC-101/2 Time: 4:56 p.m. CDT 1:08:56 GET 5/26/73."
Description
An account of the resource
This mission commentary primarily depicts the Skylab 2 crew discussing the deployment of the parasol for the alleviation of temperature pressures. The Skylab 2 crew is also depicted making the preparations for the deployment of the solar parasol.
Creator
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United States. National Aeronautics and Space Administration
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-05-26
Temporal Coverage
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1970-1979
Subject
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John F. Kennedy Space Center
Skylab Program
Skylab 1
Skylab 2
Conrad, Charles, Jr.
Weitz, Paul J.
Kerwin, Joseph P.
Earth Resources Program
Apollo Telescope Mount
Airlock modules
Space habitats
Type
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Transcripts
Text
Source
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Skylab Collection
Box 17, Folder 2
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14420/sdsp_skyl_000085_001.pdf
196f4182d8491230da02868e42c5d280
PDF Text
Text
/
ime: 17:15 p.m. CDT, 1:09:15 GET
L-II MC102/1
/26/73
PAO
This is Skylab Control, 22:15 Greenwich
mean time. Little over a minute out from the Vanguard Tracking
Ship for the first pass over that tracking vessel this
evening. Three successive - four successive passes, 177
178, 179. After Vanguard, it's long dry spell until we hit
the States again now; almost a complete revolution. We
should have a status report from the crew during the Vanguard
pass on how the work in preparing the Skylab parasol is
proceeding. We'll stand by for spacecraft communicator
Hank Hartsfield's first call. 22:16 Greenwich mean time,
standing by, this is Skylab Control.
CDR
Houston, you read?
CC
Roger, read you loud and clear. We're
through Vanguard for about 8 minutes.
CDR
Okay, Houston. Damn it. Between
steps 6 and 7 you didn't verify bottom. Teflon flaps is
innermost and top is out. And unfortunately, the forward
flaps run vertically. Now, do you mean the flaps that are
inside, the two vertical running flaps? There are 4 flaps
there. If you hadn't sent us the change, we'd understood it.
CC
Okay. The way that's suppose to be, is
he bottom flaps should be folded upwards, then the two side
laps folded across, and then the last flap on top should
•
be folded down.
CDR
Okay. That means we have to refold it.
Do you understand that?
CC
Right. The purpose of that, Pete, is
to keep the SAL door, when it pushes in and down from pulling
that flap down.
CDR
Okay. I'm not arguing with you, I'm
telling you we have to change it. Is that what you expected
us to have to do, change it?
CC
Negative, we did not expect that.
CDR
Because it's not packed that way.
You want us to hold while you verify or do you want us to
change it? I understand what you're talking about.
CC
We want it changed, Pete. We want it
so that the SAL door will not drag the flap down. So, that
top flap has to be on the outside folded down.
CDR
Top flap folded down. You will have.
CC
That's the thing we uncovered last
night, Pete, when we were working in the trainer. The - When
they packed it, we didn't know about that problem with the
SAL door.
CDR
Yeah, I understand that, I just wanted
you to understand that we were going to have to rearrange those
�^^,-11 MCI02/2
^R.me: 17:15 p.m. CDT, 1:09:15 GET
5/26/73
flaps because it was not packed the way you described it
to start with.
CC
Okay. We did that in the trainer. That's
easy to do.
CDR
Okay.
CC
Skylab, Houston. For your info on the
maneuver, we're doing a pitch maneuver now to pick up the
power situation. We shouldn't have to do that again while
we're deploying. Our next nominal H-cage is going to have
to be done at 23:39 over Texas, which is on the next contact
after Vanguard. So, the only constraint we have on you is
that we cannot be maneuvering while you're doing steps 33 to
35 and that is when you actually deploy the parasol. So,
if you reach that point in the checklist and it looks like
it's getting close to the time we're going to have to do that
reset, we're going to have to hold up until we get it completed.
CDR
We understand that. But we need your
steps at the time, so we can write it down. It was 34 and
35 and when are we over Texas?
CC
Okay. Over Texas at 23:39, that's when
we have to do a re - nominal H-cage. And the steps were
, 34, and 35. That's when you do the last little push to
5loy the parasol.
•
CDR
Okay.
CC
Skylab, Houston. We're about 20 seconds
to LOS. We'll be picking you up at Goldstone at 28. And ah we show you coming up close to termination of bed-1 bake-out,
we want to delay bed 2.
CDR
Say again about bed-1 bake-out. Hank.
CC
Roger. According to our time, it's
just about through and we want to delay number 2.
CDR
Okay.
PAO
This is Skylab Control. We've had
loss of signal from tracking ship Vanguard. The Skylab
cluster now over the South Atlantic an hour and 2 minutes
out of Goldstone; almost a complete rev before the next
station pass. We're proceeding quite well on preparing the
Skylab parasol for deployment. The Teflon flaps, which are
the ends, actually, of long sheets of Teflon on the four
sides of the canister, are being repacked so that the upper
flap is downward to avoid any binding with the opening of the
airlock - scientific airlock door; a fairly minor operation.
It was checked out in a trainer last night and found to be
the best way to avoid any possible difficulties. At 22:26
Greenwich mean time, up again in 1 hour and 1 minute,
this is Skylab Control.
OF TAPE
\
�SL-II MC-103/1
Time: 18:18 p.m. CDT, 1:10:18 GET
5/26/73
PAO
This is Skylab Control, 23:18 Greenwich
mean time. Slightly over 9 minutes to acquisition on the final
stateside pass of the day. Pickup at Goldstone and just sliced
through the western edge of the Texas circle. Flight controll
ers here in the control room are taking advantage of this long
LOS period to drag out brown-bags and go down to the snack
bar and other places in the building and in general, stretch
their legs. After Goldstone and Texas we have about 3 or 4
successive passes at the lower end of the descending node,
passing through the Vanguard tracking ship acquisition range.
Orbit continuing to precess westward during this time of the
day off the range coming back on to it in the early morning.
During the upcoming stateside pass we should get a fairly good
estimate or evaluation by the crew on how they stand with the
deployment of the Skylab parasol. At least verbal descriptions
and if they've found the time to take the effort to unstow the
television camera, hopefully a picture. Up again in 7-1/2
minutes with Goldstone acquisition. At 23:20 Greenwich mean
this is Skylab Control.
END OF TAPE
�SL-II MC-104/1
Time: 18:26 CDT 1:10:26 GET
5/26/73
This is Skylab Control 23 hours 26 min
utes Greenwich mean time, slightly over a minute until
acquisition through Goldstone and a small slice of the
Texas station. Flight Director Neil Hutchinson went on
the flight director loop and asked everyone to settle
down after this long LOS period,;sit down and settle down.
Everyone anticipating and hoping for a successful Skylab
parasol deployment, either completed or near completion.
They will leave the air-to-ground line up to catch the
first call as we have acquisition of signal. At 23:27 stand
ing by, this is Skylab Control.
CC
Skylab, Houston through Goldstone for
12-1/2 minutes.
CDR
Hello, Houston.
CC
Hello there.
CDR
(garble) Be advised we have invented we have - - We are getting a little coolant break. It's
pretty warm down there. So we are progressing slow but
sure and everything so far is working.
cc
Okay Pete. We had a little dropout
there, some noise. Could you tell us what step you're on?
CDR
We're about to put rod Delta on.
CC
Roger, copy.
CRR
Okay, we had no trouble venting it down.
It vented in about 4 minutes and it held zero for 10 minutes
without any outgassing. Going at it very smoothly and,
so far, the rod extension has gone very easily. And as I
say, we're just taking a little heat break.
CC
Hey, that's a good lick.
CDR
And Paul has terminated mol sieve IB
bake-out. Now we noticed that the dewpoint has gotten up
to 44 and we want to know whether you want us to go ahead
a little later in the day or (garble)
CDR
Hello, Houston. Are you there?
CC
Roger.
CDR
You're breaking up. Hank. Did you
copy my last about the mol sieve?
cc
Roger, understand you are terminating
the bed-1 bake-out.
CDR
That's right. Also, did you get in on
the onboard dewpoint?
cc
Roger, we copy 44. Is that correct?
CDR
That's affirmative. If you want us to
do it later on, just let us know and we'll do it. Now I
have something else on a PP C02. We've got three active sensors
and they are all reading differently. Just for your infor
mation - PAO
END OF TAPE
�SL-II MC-105/1
Times 18:32 CDT 01:10:32 GET
5/26/73
PLT
this is how we'll do it.
CDR
Now, I got something else on the PCC 02.
We've got three active sensors, and they are all reading
differently, just for your information. Sieve B IN is read
ing 2 millimeters, Seive A is reading 3, and surprisingly
well,not so surprisingly because , since it's been doing it
but Seive A-OUT is reading about 4-1/2.
CC
Roger, we copy, and we have telemetry
on those.
CDR
Okay. Also, How about, just for onboard
information, confirming or correcting our report indication
that showed that our Panel 225 the 120 psi 02 regulator
is regulating to 140, also, let me look a minute, the N2
is regulating to about 165.
CC
Okay. Those figures agree with what we
got down here, Paul, and they're acceptable.
PLT
Okay. So everythings working right that way
but those are the right numbers.
PLT
Okay, Henry, Now, let me verify about
this parasol extension stuff.
CC
Okay. Go ahead.
PLT
We can do everything except Step-33,34,
and 35 while you're maneuvering the vehicle. Is that right?
CC
Stand by 1 minute.
CC
Skylab, Houston, we're coming up at
in about 5 minutes, with the nominal H- case, and we would like
for you not to do any more extensions until after maneuver
is complete. Once that maneuver is complete, you're clear
to press on through the deployment. The thing we don't we
don't want to do is be deploying while - when the maneuver
is going on and thrust is firing.
CDR
Okay, I thought that might be the case,
which wasn't clear before. When's that maneuver going to
be over. You know?
CC
Stand by. I'll get an answer on that.
CDR
Okay. Either a time, or another AOS.
Just so we know when we can pick up.
CC
Okay. We are about 6 more minutes on
this pass, and then we'll be picking up Vanguard at 54.
CDR
You cut out, Henry. All I got was 4.
Say again.
CC
Okay. We have about 6 more minutes on
this pass, and then we'll pick you up at Vanguard at 54.
CDR
Okay. When can we continue the mission.
You want to wait until we pick up at Vanguard? You give
us the GO then?
CC
s tand by.
�SL-II MC-105/2
Time: 18:32 CDT 01:10:32 GET
5/26/73
cc
Skylab Houston. You're clear to proceed
with the deployment at 23:45.
CDR
23:45, Okay.
t
QQ
we're getting a good picture down
^"cDR
Okay. That's TV specialist Dr. Kerwin.
Paul he - would you look at the picture of the right
window, in the foreground you see the see the MDA, that
white painted, (garble) behind that is ATM the strutwork, and
mostly the@rest of it is dirt. I don't think is this picture
you can see the - the thing deployed yet. If you like I 11
take it to the left hand window now, and give you a hand held
shot of it. And tell me, what are your - what are TV
opportunities? Do you have any over Vanguard?
CC
That's negative. And we got about 4
minutes left, and if you could give us that other window,
we'd appreciate it.
CDR
(Garbled)
CDR
Okay, Henry - Let me - You did say we
could resume deployment at 23:45?
CC
That is affirmative.
CDR
Okay.
CC
And Joe, before we lose you, we would
like to get the TV on tne BTR, in any event.
SPT
Okay, I'll turn it on, and you guys
can start it anytime you want. How's that?
CC
We're going to have to have you start
it, because we probably won't be in a station contact when
they get it deployed.
SPT
Oh. Okay. You wanted - You wanted to
get it on the BTR, the deployment itself.
CC
That is affirmative.
SPT
Oh. All right.
PAO
Kerwin has moved the camera over to the
left Command Module rendezvous window looking up through the
telescope mount truss, back toward the area where the parasol
should be poking up through the scientific airlock. You can
see the bottom of the — see the bottom of the telescope mount.
SPT
Okay Henry, you're looking at a hand
held view out of the left window, with the monitor between
my knee and unfortunately, I don't think you can see the
orange sail material, which is right in the center line of
that ATM strut - (garble), because I have to move my head
to the very right hand side of the window to see it, and I
can't get the TV camera in over there. There isn't room.
CC
I guess we're having trouble seeing it.
�s^-ll MC-105/3
Time: 18:32 CDT 01:10,32 GET
GET
5/26/73
SPT
If I try to move it to the right, the
body of the camera's too long, and I can't hack it.
CC
Skylab, we're about 45 seconds from LOS.
Vanguard at 54.
PAO
This is Skylab Control. We've had loss
of signal as the cluster passed out the southern edge of
the Texas acquisition circle. Slightly over 12 minutes
until acquisition at tracking ship Vanguard, which will
be almost straight over head at a 86 degree elevation angle.
90 Degrees being straight up, obviously. Total pass time
of 7 minutes and 20 seconds. The crew had attached sev
eral of the extension rods and had it partially deployed
through the airlock scientific, scientific airlock, and on
the television picture from the lefthand window, the still
folded canapy could be seen at the apex of the truss frame
of the telescope mount. Any subsequent television will be
loaded on the on-board vidio tape recorder, in as much as
there are no more stations with live capability until
tomorrow. We'll return with this circuit in 11 minutes
with the Vanguard pass. After Vanguard, it will be about
an hour and 8 minute gap again until Hawaii. At 23:43
Greenwich mean time, this is Skylab Control.
END OF TAPE
�SL-II MC-106/1
Timei 18:52 p.m. CDT, 1:10:52 GET
5/26/73
This is Skylab Control, 23 hours 52
minutes Greenwich mean time. A minute and a half out of track
ing ship Vanguard at the start of revolution number 177 for
the orbital workshop. We should continue to hear a proqress
report on deployment of the Skylab parasol. After Vanguard
there will be another long break of an excess of an hour be
fore we come up on Hawaii, stand by now for the resumption
of communications from the crew of Skylab and the ground.
_ , .;rc .
Skylab, Houston through Vanguard for
7-1/2 minutes.
™
^ ,
Roger, Houston. The parasol is I think
completely deployed. I m just going down to check on it.
cc
Roger.
PLT
It's not completely extended, it's
not deployed.
cc
Roger.
„.
Correction, we're about to extend rod
Echo, rod Echo.
cc
Okay.
Roger, copy rod Echo.
PLT
Hey, Henry?
cc
Go ahead.
PL"L
Okay. According the the procedures
e
e
et
E
a£d'nu5h *iT «-S!
°Ut' ifc reads like we put F and G together
I juat want you'to^garble)1"** 'h""'5 * h™1"5" <9arble> °n L"
CDR
we used
to lork «-w 01i*y'*X "4"* OUr <9arble> " the one
ised
we used to lock the 4 rods. (Garble) And to release the springs
PLT
Houston, we're not reading you. We're
g
»
9
move up to the ^ a"d talk to you.
0kay' we've been having a little trouble
withCLn„,rH
u
® We got good conun now? How do you read?
..
Lond and clear. What's the storv with
the stripe on F? The procedures don't say anything about it.
Okay, step 27 tells you about rod F.
rr
Af
put F on and 26 yon "ove it
out- to
fn the markU and
wer you
J
out
then
clamp it.
PA0
pf^E
Okay, 1 got you. I read that over.
the two marks on E are only about
^ow
w
an inch and one half apart. That's right, huh?
*• *.
. That's affirmative, and when you get
Sd^SdJ "irTlSekiJS ShSUlK bG thG P°int Where the telescope
8econd P°int you
Sould be il i iKfi??
k WhenJ°u reach
should be in a vicinity where all of them should be locked.
pLT
Okay.
if you have any doubts we want to
push it further until you have no doubts that all the
�SL-II MC-106/2
Time: 18:52 p.m. CDT, 1:10:52 GET
5/26/73
telescope and rods are locked.
PLT
Okay. (Garble)
PLT
How important is TV Hank? It's dark
outside now, you want to wait for light?
CC
Negative. We want to get it out.
CC
Skylab, Houston. We would like for
you to get a visual verification on the deployment. Whether
we get TV or not is not important. We want you to have a visual
on it though.
PLT
No chance of a visual, Paul, until we
go into sunrise.
PLT
When did that start. Hank? We're at
the first mark on E now. How far can we progress before deal
ing?
CC
Okay, you can progress all the way up
to step 32. That's when you start the final deployment.
PLT
Okay.
CC
Thirty-two is releasing the brake.
Go up to 32. We have about 26 minutes to sunrise.
CC
And we're one minute from LOS. Our next
contact is Hawaii at 03.
PAO
This is Skylab Control. Apparently
we have had loss of signal through Vanguard with the Skylab
cluster. Not too much farther to go now in the extension rod
attachment to bring the Skylab parasol out to the full exten
sion point where the 4 ribs will fly upward and outward to
90 degrees to the center pole. However, they express a desire
to wait until spacecraft sunrise before doing this. And sun
rise for them will be in 23 minutes. However, the Skylab will
not be over any ground station for another hour. Hawaii in
59 minutes at 00:03 Greenwich mean time. This is Skylab Control.
END OF TAPE
SL-II MC-107
Time: 19:32 CDT 1:11:32 GET
5/26/73
PAO
This is Skylab Control 0032 Greenwich
mean time. Skylab space station just crossing the island
of Ceylon on over into the Bay of Bengal on revolution
number 178. Fifty-two minutes remaining until the space
craft sunset. And it is hoped that the Skylab parasol de
ployment will be accomplished during this day side pass.
We're still a half hour out of Hawaii. It's fairly quiet
in the Control Room here. People are taking a , again
taking this long LOS break as an opportunity for meals,
getting a cup of coffee. We'll bring up the circuit again
at acquisition Hawaii in 28 minutes. And at 0033 Greenwich
mean time, this is Skylab Control.
END OF TAPE
�SL-II MC-108/1
Times 19:53 p.m. CDT, 1:11:53 GET
5/26/73
PAo
This is Skylab Control, 00:53 Greenwich
mean time. Skylab space station and command service module,
known as the Skylab cluster, now nearing the three-quarter-way
point of revolution 178, crossing just south of the Aleutian
Island chain, some 8 minutes and 50 seconds out of acquisition
at Hawaii. A group of about 30 people just came into the
viewing room here in the control center. This group is made
up of people from the Johnson Space Center Technical Services
Division, Crew System Division, and other elements of the
NASA center, plus people from the support contractor organiza
tions who were involved in design, fabrication, and testing
of the Skylab parasol. They've come in to see the final hear the final report of deployment, hopefully, which will
be over Hawaii and most probably over Vanguard a few moments
later. We'll be up again in 7 minutes at 00:55 Greenwich mean
time. This is Skylab Control.
END OF TAPE
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
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sdsp_skyl_000085
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"Time: 17:15 p.m. CDT, 1:09:15 GET SL-II MC102/1 5/26/73" - "SL-II MC-108/1 Time: 19:53 p.m. CDT 1:11:53 GET 5/26/73."
Description
An account of the resource
This mission commentary primarily depicts the Skylab 2 crew unpacking and assembling the solar parasol. The Skylab 2 crew is also depicted deploying the solar parasol.
Creator
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United States. National Aeronautics and Space Administration
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-05-26
Temporal Coverage
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1970-1979
Subject
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John F. Kennedy Space Center
Skylab Program
Skylab 1
Skylab 2
Conrad, Charles, Jr.
Weitz, Paul J.
Kerwin, Joseph P.
Life support systems
Experimentation
Apollo Telescope Mount
Multiple docking adapters
Manned Spacecraft Center (U.S.)
Type
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Transcripts
Text
Source
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Skylab Collection
Box 17, Folder 2
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14421/sdsp_skyl_000086_001.pdf
9a6cd0a710be5508951eed7f38f44bd6
PDF Text
Text
SL-II MC-109/1
Time: 20:02 CDT 1:12:02 GET
5/26/73
This is Skylab Control 1 hour and 1 min
ute ground elap - I mean Greenwich mean time. We have
had data acquisition through Hawaii tracking station. We 11
stand by for resumption of air-to-grwnd MUHiwtion^
This pass is only 5-1/2 minutes long. This is Skylab Con
pA0
tr0lCCtandin9 by*
Skylab, Houston to Hawaii for 5 minutes.
PLt
Roger, Houston. Stand by one, we're
trying to get the PB on the VTR and Pete will have a chat
Wlth c°U*
C
Skylab, Houston. We've got about 4 min
utes left on this pass. Can you give us a report?
CDR
Be right with you, Houston.
Okay, Houston. We had a clean deploy
CDR
ment as far as rods clearing and e^ryhthing, but it s not
laid out the way it's supposed to be. And we ve gotpic
tures of it on the VTR for you. Now right at the moment,
we've operated voided the rod in and out a couple of inches
short stroke-wise rapidly, which has improved the deploy
ment. But the problem seems to be that the folds in
material have taken too much of a set. And it is more
fully deployed in the front across the upper skirts. But,
there are two folds emanating from the set, 3 folds emanating from the center deployment plate; one to each side an
one towards the base skirt. So, in effeet,we 1have a trap
ezoid which is the smallest dimension toward the base of
the vehicle. Now, that's as far as we We gone. We:re
open for suggestions. I have the feeling that if we pulled
it all the way in close to the vehicle that it would touch
in the back and along the sides. It might possibly "SlP
the folds out of the material and if we did push her back
out again and gently oscillate it in and out, as we have in
the past, which seems to improve it. But, I think we ve
gotten about as much out of it as we're going to get. My
guess is we've only got about 12 to 14 feet at the
back end with perhaps 18 to 20 at the front end. And
don't even know the dimensions of the sail.
cc
Okay the dimensions are supposed to
be 22 by 24, Pete.
CDR
Well, it's possible that we ve got it
completely backwards and we could turn it 180 degrees. That
would - which way do you want - which dimension do you want
the 24?
cc
Twenty-four is the length of it, l i
feet should be the width.
CDR
Okay. Then it is in fact a square.
I mean a rectangle.
CC
Yes.
�SL-II MC-109/2
Time: 20:02 CDT 1:12:02 RET
5/26/73
CDR
Is that right, Houston, it's a rectangle?
CC
Roger, it's rectangular and the center,
of it - the hub is off center on the rectangle. There's
to be the poles that are pointed back toward the ATM should
be the ones that have a length without fabric on them.
CDR
That's the way it is.
CC
That's the way it should be.
CDR
If you are able to dump our TV we, I
think, give you a pretty good TV of it. It just does look
to me like the end aft toward the aft skirt has got three wrin
kles. One coming between the aft skirt line and one on each
side running along you know running outboard to the side.
And that it's pinched the fabric, you know. It's taken a
permanent set. And the front end, which has the strings on
it, that's pretty well deployed.
CC
Okay, we're about 15 seconds from LOS.
We'll think about it and we'll talk to you at Vanguard.
We hope to have a plan then. Vanguard is coming up at 30.
CDR
Three zero, Roger.
CC
Skylab, Houston. If you can still read,
we'd like to terminate that Bat A charge and get Bat B to
charging. And also, if anybody is free, we'd like to start
them on the water flight servicing.
CDR
Okay, we were just going to ask you
that.
PAO
This is Skylab Control. We've had loss
of signal through the Hawaii tracking station. Coming up
on Vanguard in 21 minutes. There was considerable applause
in the viewing room from the people who are involved in
designing, fabricating, testing the parasol when it was re
ported that it had deployed with a few wrinkles in the after
end of it - end pointing - facing toward the telescope
mount. Meanwhile, here on the ground, discussion is underway
on how would be the best way to try to shake the wrinkles
out. And, hopefully, over Vanguard, some word will be passed
up to the crew on how would be the best way to correct the
problems and get the full 22 by 24 foot dimensions out
of the parasol for the optimum solar shading. We'll come
back up at Vanguard in 20 minutes. At 01:10 Greenwich mean
time, this is Skylab Control.
END OF TAPE
�SL-II MC-110/1
Time: 20:21 CDT 01:02:21
5/26/73
This is Skvlab Control 01 hours 21
BBSWT
orouos scattered around the room, on how the beat wayto
shake loosethe folds in the canopy. The main consensus
seems t^be to pull it down fairly close » the workshop^
sHSS&Sss
HrSsr
•.Kn fshrfr
And we'll be coming up on the reset in ure
6-1/^nute. for the^
Vanguard pass at 01:23 Greenwich mean time. This is
y
Control.
END OF TAPE
ln
�SL-II MC-111/1
Times 20:28 p.m. CDT, 1:12:28 GET
5/26/73
This is Skylab Control 01 hours 28
PA0
minutes Greenwich mean time. About a minute and 56 seconds
out from Vanguard tracking ship nearing the end of revolution
178 for the workshop. After Vanguard, we again have a long
gap of about an hour before Hawaii. Hawaii pass will be almost
due overhead, 81 degrees elevation, maximum elevation. And
we expect another status report from the crew on the retraction
operation of withdrawing the center support rod, taking off
the rods as they bring it in. Forty-five seconds to acquisition.
However, occasionally we get acquisition ahead of the clock
time. So, at this time we'll bring up the circuit for the Vanguard
pass, which has a duration of 10 minutes and 2 seconds. Skylab
Control standing by.
CC
Skylab, Houston through Vanguard for
9 minutes.
CDR
Go ahead.
CC
Roger. First off, we'd like to get Joe
to tell us what he saw out the window. We would like to know
if the rods are approximately in the same plane.
SPT
Well, we don't think so, Houston. We
can see the ends of all the rods.
It's completely free of
anything and there's nothing hanging it up.
SPT
And if you want to know what it looked
when it deployed I can see the thing stickin up, bunched in
the middle, billowed a little bit at the top and at the bottom,
and when they deployed it, all four legs came up. The front legs,
that is, the forward ones closest to the command module, came
up smartly. It looks as if they actually went over center a
little bit, then bounced back. The back ones did not come up,
it looked like, all the way - didn't come to 90 degrees.
They went slowly and they just kind of drifted to a stop.
CC
Okay. What kind of an angle do you think
they made with the plane of the first two rods?
SPT
It's your guess, but I guess 30 degrees,
something like that.
CC
Okay, we would like for the CDR and the
PLT to go back in the workshop and pull her in and we'd like
for you to pull as many rods in at one whack. Undo the rod
break and bring in about three at a time and them remove them
and we want you to complete the procedures down to step 43 so
you've done a full retraction and got the rod A configuration
proper. And we're going to be doing a nominal H-cage at the
end of this pass and we want to get it in close.
SPT
It worked.
CC
Skylab, Houston. We'll give the time
for that reset so that you can be sure and have the rod brake
on when we start it.
�SL-II MC-111/2
Time: 20:28 p.m. CDT, 1:12:28 GET
5/26/73
r£T
Skylab, Houston the time for the reset
is 01:36. That will be the time for the nominal H-cage. 01:3
and we'll warn you again at - close to that time.
CDR
Understand 01:36. That's two minutes
from now, but we'll hustle.
i re_
CC
Roger, and once we get theparasolre
We.re
tracted, we do not plan to do anything mojr® with
. We re
going to take a look at it, and we think we've got almost a full
deployment and pulling in will do the rest for us.
cdt
I understand.
And for the CDR, we're not too concerned
cc
about getting it all the way down before the reset. The main
thing we want is that you do have the rod brake on when
reset starts or the nominal H-cage starts.
Skylab, Houston we're going to give you
cc
a little more time here. We're going to delay that reset to
40.
CDR
Okay. 40.
_
SPT
Okay, we're pulling it in Houston. Be
advised the rods we're pulling in are quite cool and feel very
nice to the touch.
CC
Roger, copy.
SPT, Houston. Did the CDR, PLT take
CC
a rest between the Hawaii and Vanguard?
CC
SPT, Houston.
SPT
Go ahead.
cc
Roger, we'd like to know if the CDR,
PLT took a rest between Hawaii and Vanguard?
5PT
They took a break, Houston.
CC
Roger, copy.
SPT
Okay, Houston, we got it in.
cc
Okay. I understand you got a full re
traction and you've followed - completed the checklist through
at least 42.
spt
I didn't say that. We're presently
double checking that. We got it all the way into the mark
on rod Alpha and «£ rod brake clamp thing tightened down.
cc
Roger, sounds good. We re going to
start the reset - the nominal H-cage immediately. Now, for the
rest of the evening, we'd like for you guys to go back and if
you haven't eaten already, eat, and we're going to try to get
on with the nominal flight plan.
spt
Okay, good enough. ^Also rod B is gathering
frost as it lays here in the fiery workshop
cc
And we'd like to insure that you do
�SL-II MC-lll/3
Time: 20:28 p.m. CDT, 1:12:28 GET
5/26/73
complete step 41 there, Paul. We'd like to make sure we get
the push rod knob A on there and the set screw in.
PLT
That didn't work. Hank. It's a little
tough getting these two sections separated. We'll get on that
as soon as we can.
CC
Okay.
CC
Okay, we're almost LOS now, we'll be
picking you up over at Hawaii at 37.
PLT
Okay.
PAO
This is Skylab Control. We've had loss
of signal through the Vanguard tracking ship. With a successful
retraction and clamping of the center pole of the Skylab parasol.
The brake set prior to the time the commands were sent to
reset the control moment gyros using the thrusters on the orbital
workshop. Still 18 minutes remaining of nightside pass. It
will likely take a couple of dayside passes before a trend is
observed of reduced temperatures - temperatures coming down.
Acquisition directly over the Hawaii station in 55 minutes.
At 01 hours 41 minutes Greenwich mean time, this is Skylab
Control.
END OF TAPE
�SL-II MC-112/1
Times 20:58 CDT, 1:12:58 GET
5/26/73
PAO
This is Skylab Control. 01 hours 58 min
utes Greenwich mean time, 38 minutes away from Hawaii.
Skylab cluster crossing the east African coast in the straights
between the Island of Madagascar and the continent of Africa.
Here in the Mission Control Center there's a great deal of
confidence that the recently deployed Skylab parasol will
have a good effect on the internal temperatures of the Skylab
workshop. Johnson Space Center Technical Services Division
Chief Jack Kindsler just spoke to the group of people in his
division and other elements of the center and support contrac
tors in the viewing room, and expressed the belief that as
the parasol gets warmed up by the Sun during the next couple
of dayside passes, the wrinkles in the after end of the canopy
which apparently were set by the cold soak during the early
part of the deployment will indeed flatten out. And that the
parasol will provide the designed effect of lowering the
temperatures, and acting as a parasol in name and indeed for
the Skylab workshop. 37 minutes to Hawaii. At 02:00 hours
Greenwich mean time, this is Skylab Control.
END OF TAPE
SL-II MC-113/1
Time: 21:19 CDT 1:13:19 GET
5/26/73
PAO
This is Skylab Control 2 hours 19 min
utes Greenwich mean time. Skylab cluster now over north
central China, midway through the 179th workshop revolution.
Seventeen minutes out of Hawaii. Thirty-eight minutes re
maining in the current dayside pass. And flight controllers
will be observing the workshop temperatures during the next
couple dayside passes to see if there is a trend of
temperature reduction in the workshop structure and in
the atmosphere. It will probably take at least 2 revolu
tions for the temperatures to begin a downward trend.
And hopefully through the night, the workshop will be in
a comfortable temperature, by the start of tomorrow's crew
workday. People here in the Control Center are well sat
isfied with the deployment of the Skylab parasol. And
as the inventor of the parasol mentioned in his pep talk
to the people in the viewing room who had built and tested
the device, he felt that the wrinkles seen in the after
end were a result of cold soak and that as the Sun warmed
up the canopy, the wrinkles would flatten out.> We're
looking now at a handover from Flight Director Neil Hutch
inson to Milt Windier at about 10:15 central time. And
anticipating a press conference shortly there after, per
haps 10:30 p.m. central. Participants will be William C.
Schneider, Director of Skylab Program NASA Headquarters,
Flight Director Neil Hutchinson, and Jack Kinsler who is
Chief of the Technical Service Division Johnson Space Cen
ter, the man who's brainchild the parasol was. Fifteen min
utes out of Hawaii, at 02:22 Greenwich mean time, this is
Skylab Control.
END OF TAPE
�SL-II MC-114/1
Time: 21:36 CDT 01:13:36 GET
5/26/73
PAO
This is Skylab Control 2 hours 36 minutes
Greenwich mean time. We have acquisition now, even though
the clock says we're some 15 seconds away, through the
Hawaii station. Almost directly over the Hawaii station.
81 degrees elevation angle maximum. We'll see how the solar
sunshade or Skylab parasol is working as we read temperatures
on this pass. See if they're coming down.
SC
See you over Hawaii for 10 minutes.
CC
Okay, we got a lot of things we want to
talk about on this pass. I guess I'll get on with it. First
off we're planning a medical conference at Vanguard, which
is about 03:04. That will be the next station contact
after this one. The next item is that we have a requirement
that one of you wear the OBS tonight, since we don't have
any (garble) in the Command Module, and depending upon the
CSM fan, we're recommending the SPT.
CDR
Okay.
CC
And for the SPT, we'd like to get his
opinion on - we can only - we can't dump all of the VTR
tape to get that pictures back of the parasol, and we'd
like to know whether it would be better to lop off the
first part or the last part. In other words, about where
in there was the pictures of the deployed parasol?
SPT
Hank, if you might get the pictures of
the actual deployment at the beginning, and the pictures
most actually representative of the configuration in which
we ditched it down are at the end, and you can take your
choice.
CC
Okay, thank you.
SPT
Hey, Hank.
CC
Go ahead.
SPT
I got to apologize profusely, but I
inadvertently opened the circuit breakers to the amp hour
integrator number 8, and it's reset to zero onboard.
CC
Roger. Copy.
CC
And our maneuver plan is here, we're
going to take a look at the temperatures, and we think
they're coming down. We're prepared to command a solar
inertial here over Hawaii. Just let you know, and we're
also prepared to back that up at Vanguard as a last choice.
SPT
You say you think they're coming down
or if they're coming down.
CC
Well we're looking at them now to see
what they look like.
SPT
We just finished weighing all the mol sieve
heat exchanges. What do you do with them? Just stand by
until tomorrow.
�SL II MC-114/2
Time: 21:36 CDT 01:13:36
5/26/73
CC
Okay, while we're getting an answer on
that, we'd like to know how far you got in the - your
checks, have you done the quiescent panel yet?
CDR
Yeah. I rated panel 351, which we're
leaving UP so that we can have water. I was gonna do 352,
382, and 378, 79, 76, 399, 377, 600, 602, 601,603, 604 and
side hatch tunnel hatch, and that's it. The rest of it's
done. BAT B is being charged. I just did an 02 purge.
CC
Okay, what we're getting at, Pete, we we're wondering how you feel about trying to get the VCS
dump in tonight, and get some circulation going.
CDR
Boy, you bet, we can do that.
CDR
Hey, if you think those temps are coming
down, and that will help any, that's no strain. We're in
good shape up here.
CC
Okay, then, in that case, we'd like fot
you to do Step 1 & 2 on Page 2-62, and following that, on
Panel 390, I'd like to get all four OWS heat exchanger
fans on. Just place all four of them to'on'. And tomorrows
flight plan, of course, we'll delete that part of it ahd
do Steps 3 & 4.
CDR
You say you wanted the OWS heat exchanger
fans on or off?
CC
On. O N. After you install the duc|f
according to Steps 1 & 2 on Page 2-62, Panel 390 in the
lock there, we want to get all four heat exchanger fans on.
CDR
Will do. How did the temps look?
CC
Okay, it looks like to us the temps are
coming down, so we're going to put the solar inertial in
WORK.
CDR
Very good. Very good.
CC
Okay, and another thing, Pete, we're
looking at two flight plans tomorrow. We - We're just
taking a tentative look at a flight plan that doesn't
consider anything in the workshop. And we have the other
alternative is going as planned with a what we launched
with. Now, we'll try to get - We'd like to get your opinion
on this, how you feel about working in the workshop tomorrow.
CDR
Well Buck, if you bring those temperatures
down any at all, I'm guessing, but, we spent the better
part of 2 or 3 hours down there, and everytime we'd get
hot, we'd come up and take a rest. Now, if the temperatures
are coming down, and they've come down at - I don't know Maybe Paul's got a different idea, but/I'd say it was
at least 120 in there today, but you carrwork in thfere.
It's dry*j We didn't get any problems with heat, whenever we
just got too hot, we'd come up and cool off for awhile and
�SL-n MC-114/3
Time: 21:36 CDT 01:13:36 GET
5/26/73
cool off and go back to work, so
.th®y
riband*'
I would like to stick with our original flight plan,
\
go start activating it down there.
we'll
CC
Okay, our best estimate, Pete, is we 11
be below 100 degrees in there by tomorrow morning•
CDR
Well, what do you think it was in there
today?
Skar^elH think we're pretty well
calibrated. You bring it down 20. We
^£9 ^o ® ri
any bicycles or anything, but we can get down there and^at
least start configuring things, and we U ]
p
as best we can. If we cannot, we can come out. As far
the temps are coming down. I think that s gre .
like to press for the normal flight pi®". V
...
CC
Okay, I guess we will concur with that
then. We uplinked you a contingency on dock procedure
regard to the probe! By Poking them together you^robably
aot now
That is just a get me home thing. Tomorrow we
hope to have a better analysis of the probe for you.
PLT
Okay', HenJy! when we put on the yCs ducts
and we turn on the OWS heat exchangers, what do we do
S2 vent fan. r>o you want to unplug the vent and go ahead
and fire up that fan, or leave it like it
rr
Stand by just 1.
^ _
That's the A - that's the A-N duct fan.
pLT
Roger. I understand. Let me get an
CC
answer on that right quick.
Roger. We'd like to proceed with un
capping that duct, -day!ettingotthteifanigoing.sEvA
Do
we have time ^^over ^with^now?
right now in this pass. I guess we'd like to delay those.
PLT
HowYabout if I record them on Channel A
for now and you can listen to them, and if we get a
chance. I'll give them to you, and otherwise, they
on tape, and you can listen and see if you got any
further questions.
up to you with that.
jUst getting ready tocome
That's real good. Press on with that.
x was
CcT
Skylab, Houston.
solar inertial now.
You're on your way to
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
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Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
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sdsp_skyl_000086
Title
A name given to the resource
"SL-II MC-109/1 Time: 20:02 CDT 1:12:02 GET 5/26/73"-"SL-II MC-114/3 Time: 21:36 CDT 01:13:36 GET 5/26/73."
Description
An account of the resource
This mission commentary primarily depicts the Skylab 2 crew finishing their work on the solar parasol. This mission commentary also depicts the discussion between the Skylab 2 crew and ground control about the permanent move to habitation in the Orbital Workshop.
Creator
An entity primarily responsible for making the resource
United States. National Aeronautics and Space Administration
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-05-26
Temporal Coverage
Temporal characteristics of the resource.
1970-1979
Subject
The topic of the resource
John F. Kennedy Space Center
Skylab Program
Skylab 1
Skylab 2
Conrad, Charles, Jr.
Weitz, Paul J.
Kerwin, Joseph P.
Onboard equipment
Experimentation
Life support systems
Type
The nature or genre of the resource
Transcripts
Text
Source
A related resource from which the described resource is derived
Skylab Collection
Box 17, Folder 3
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
A language of the resource
en
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Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
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https://digitalprojects.uah.edu/files/original/21/14422/sdsp_skyl_000087_001.pdf
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SL-II MC-114/4
Time: 21:36 CDT 01:13:36 GET
5/26/73
We^re about 30 seconds from LOS, Skylab.
We'll be coming up on Vanguard, as I said, at -it'll be
about 09 now, and we'd like to say, you guys did a tre
mendous job down there. We've got everybody smiling here,
now th.t we've got ££P.r.sol out. ^^those
that I'm awful sorry about that breaker. Ithnrtjd it
(garbled) in that heat exchanger break, but I 311st flipped
it up with my toe.
...
CC
And if you still read us, we d like to
get that (garble) system activated.
Roger, you got a page number for that. Hank?
CDR
SC
Okay, that's page 2-137.
This is Skylab Control. The Skylab
pA0
cluster has gone over the hill from Hawaii tracking station.
It is now just north of the equator in the Central Pacific.
Twenty minutes to Vanguard. The trend in temperatures as
shown on the numerous different measurement points through
out the workshop is definitely downward. And as mentioned
by spacecraft communicator Jack Hartsfield, it s likely
that the workshop atmospheric temperatures will be below
100 degrees Fahrenheit by tomorrow morning. They re now
around 120 to 125. We're still estimating around 10:30
for the change of shift press conference in the Johnson
Space Center news room. Participants again. Skylab
Program Director, William C. Schneider. Flight Director
Neil Hutchinson, and Jack Kinzler, Chief of the Johnson
Space Center Technical Services Division, who will discuss
his invention. Eighteen minutes to Vanguard where th®re
will be a medical consultation on a private loop. And at
2 hours 50 minutes Greenwich mean time, this is Skylab
Control.
END OF TAPE
�SL-II MC-115/1
Time: 22:07 CDT 1:14:07 GET
5/26/73
nan
This is Skylab Control 3 hours 6 min
J®
utes Greenwich mean time, a minute
crossing
from the tracking ship V7":/ky?n ^ across over
the western coast of SouthJ*® „d in the next
the horizon from the tracking sh p
.^ed to the spaceP
few moments. The command will
n solar inertial atticraft through the Vanguard to g
still in darkness,
tude even though we are, at this time, still
24 minutes away from the SP®C®C" .
before the next trackVanguard, it will be more than an hour before tn
en
ing station, Hawaii.
About an hour and 2^inut
Hank
LOS, Vanguard and AOS, Hawaii. We will stana ay
Hartsfield-s first «Uto thejrew.^
^you
another 4-1/2 »>in"tes.y>
for
well
just had another one^ "^J^havl^single talkback in the
,?We're; no;solar inertia!^
ATO
SW
"
is going on.
^we,ye
dQne ig
the hec*
ma„euver
K-r-k tn an attitude that should be approximately solar
r-n*i
We're in ATT HOLD, we're not in the solar
aboutpthe status ""J";it^^Qf
they^ave been
SPT
rate |yr° drift?
c
eUVe^TJOe*
failure
that
.
Okay, I'm going to INHIBIT it then,
0kay,
that saturation is due to man-
Well okay. It wasn't that ^d earlier
in the maneuver but I still believe you. And what is your
ground figure for TACS percent (garble)?
~.™nt
CC
The last figure I saw was 51 percent.
In fact, we're showing 51.6 percent now, Joe. 0**Y'.
got a couple of other items for you. We "c^esdthat
you leave all the hatches open tonight. No need to ciose
them up. And we'd also like to inform you that there will
�SL-II MC-115/2
Times 22:07 CDT 1:14:07 GET
5/26/73
not be a trim burn tomorrow. We only have 5 foot per sec
ond capability and we're going to try to use it at th
optimum tim .
okay, no trim burn. We will leave the
hatches open tonight. One to 5 feet per second above.
QQ
That's above the SMRCS red line.
SPT
Okay.
CC
SPT Houston. We'd like you to select
1 and 3 in the Y AXIS. And you may get another failure
alert there until we can get the drift correction in.
gpT
Okay, you don't want me to do any DAS
work, iust select it on the panel, right?
we'd like you to select it through the
cc
DAS.
SPT
Oh, Okay.
Skylab, Houston. As soon as you grt tne^
cc
gyros configured, we'd like you to do a nominal H-cage. We re
about 20 seconds from LOS. We hope you guys get a good
night's rest, and we'll see you in the morning.
SPT
Gyros and then a nominal H—cage, Okay.
Cc
And Skylab, if you get a chance, we'd
like you to put the evening status report on channel A.
PAO
This is Skylab Control. We have ap
parently had loss of signal through the Vanguard tracking
station. One hour and 37 seconds until Hawaii acquisition.
A very low elevation angle pass, only 2 and a quarter min
utes long. And then Vanguard an hour and 28 minutes from
now. By then the crew will likely be in the sleep period.
Some difficulties experienced with the Y-axis rate gyro,
which the flight controllers here in the Control Center
feel confident they will be able to sort out and go into
solar inertial rev later than intended. They had planned to
command solar inertial attitude during this Vanguard pass,
but it's been delayed 1 rev until the rate gyro problem
is sorted out. At 3 hours 19 minutes Greenwich mean time,
this is Skylab Control.
END OF TAPE
�SL-II MC-116/1
Times 23:32 CDT 1:15:32 GET
5/26/73
PAO
This is Skylab Control at 4 hours 32
minutes Greenwich mean time. We're going to play for you
now the record-recording of the air-to-ground during the
Hawaii pass. As it turns out, the flight director indicated
that he needed some additional conversation with the crew
at Hawaii. And the crew is still in the process of wrapping
up before going to bed and they will be again contacted
now at Vanguard and possibly even as late as Ascension. So
we are now going to play the Hawaii track and we'll have
another acquisition or signal coming up in a little under
15 minutes. This is Skylab Control and here is the air-toground.
CC
Skylab, Houston. We're AOS over Hawaii
for the next 2 minutes. How do you read?
CC
Skylab, Houston. We're AOS over Hawaii
for about the next 3 minutes. How do you read?
CDR
Read you loud and clear. How me?
CC
Okay, same here. Sorry to bother you
but we've got a short pass, a couple of important items I'd
like to get up to you. We're going to be turning on your
airlock module primary coolant loop. And that's going to
give you a pri cool flow caution or warning loop.
CDR
Okay. We're in the process of dumping
the condensate plate as soon as we brought the thing on
condensate tank filled to the top with water.
e're working
that problem right now.
CC
Roger, understand it filled with water.
Okay, we would like on panel 203 for you to take the mol sieve B
fan power to secondary.
PLT
It's in secondary, Houston.
CC
Roger, thank you. We know you have
been having some problems still with the APCS and we're going
to be trying to work those out for you a little bit later.
So, just don't worry about them right now. We're trying
to get back to solar inertial and didn't. We'll be trying - CC
Rog. We said that we should be close
to solar inertial attitude. We're not solar inertial mode,
we'll be working that ourselves.
PLT
Well, you're not even very close. You
don't have (garble) Do you know where to go?
CC
Probably not.
CDR
Well I'm looking out the window and
it looks as if you need plus rotation about Y and a plus about
X. And I'm not sure of the magnitude, but about 10 degrees or more
CC
I'm sorry, I couldn't copy there. Did
you say we were about 10 degrees off?
PLT
We are more than 10 degrees off. It's
hard to estimate, but it's a plus Y and a plus X rotation.
�SL-II MC-116/2
Time: 23:32 CDT 1:15:32 GET
5/26/73
We are not going to touch it this time. We're going to let you
guys fool with it. We'd like to get in solar inertial once so
we'd know what it looked like and if we get off we can get our
selves back on.
CC
Okay, we'll try to work that.
CC
Okay, we've got a pass probably in
about oh. Vanguard coming up. We'll be trying to work that
then at around 4:46.
SPT
Okay, what is the temperatures doing
in the workshop there?
CC
I'll try to get a report for you on
that. Meanwhile, we'd like to find out if you did put the
SEVA report on channel A or B. We're dumping A right now.
We didn't see it there last dump.
SPT
We haven't gotten to the evening reports.
It is still about the middle of the afternoon for us. Pete
and Paul are working pretty hard on the condensate system
They're dleaning up the command module and stuff like that.
CC
Okay understand. We just want to
make sure you did know that we were recording channel A.
And you will be putting the medical status report on channel
A for us later. Is that correct?
SPT
Yes, and we're going to have a couple
of large (garble) I think because we have enough other problems
coming up. We're going to stick with it. We are in good shape
andwe've had our private medical talk. And we don't have any
thing to report.
CC
Roger. I think all we are interested
in there is the food and, you know, whether you took any
drugs or not and that kind of stuff.
SPT
We are eating like hogs and drinking
lots of water.
CC
Very good.
SPT
- this evening status report and we'll get
as much of this to you as we can.
CC
Roger Joe, understand.
If you could also
put down, we would like sort of a relative amount of time
spent between the airlock module MDA and the workshop today.
I guess they're kind of interested in what kind of tempera
tures you were experiencing. You can put that on channel A.
SPT
My off the cuff answer (garble) they can
apparently get thatby looking at my biomed tonight.
CC
Okay, they were kind of interested in
that for the other guys too though Joe. Okay, the skin tents
have dropped about 70 degrees. We're going to have LOS
here in about 1 minute. We're going to be over Vanguard
at 4:46. We were kind of hoping that you guys were going
to bed. Do you want us to give a call there or not?
�SL-II MC-116/3
Time: 23:32 CDT 1:15:32 GET
5/26/73
SPT
yes
cc
You'want us to give you a call at
Vanguard understand.
CCT
AndSI*guess I must have got somebody
there. We would like to verify that you did get the
phant trunk installed between the OWS and the
III
?"s™fs£yiab Control. We have a
note now from Dr. Willard Hawkins on the medical jjreifing
earlier. This is a private conversationbetween «edical
officers to assess the status of
* H re is the
to prescribe drugs or anything of that so .
information given to us by Dr. Haw!JJ'i
the first 2 days
remained in good physical condition during the first 2 aay
as zras-
»«- 4 hours 38 minutes and 8 seconds.
END OF TAPE
cintrol
�SL-II MC-117/1
Time: 23:47 CDT, 1:15:47 GET
5/27/73
CC
Skylab, Houston. How do you read?
CDR
Loud and clear (garble).
CC
Okay. We're a little bit garbled. I'd
like to talk about maneuvering here a little bit if I could,
to Joe.
SC
(Garble)
CC
Roger. We are prepared to put a maneuver
to try to reacquire solar inertial and there's some confusion
on our part about whether we should go plus or minus Y. We
understood you to say plus Y awhile ago. We think it's minus.
Will you confirm that?
SPT
Okay, let's talk about it. Maybe I'm
getting it wrong. It would appear to take - to require a pitch
above the Y axis. I was going to say toward the CSM, if that
makes any sense to you. As I stand facing the CSM and look
up the Z-axis, the Sun is forward of the zenith. It's in other words, it's between the plus-Z axis and the plus-X
axis.
CC
Okay, that's a plus-Y. That - we got
up there on the top of the MDA - we got the plus-Y axis indicated
and that still sounds like a plus-Y rotation to us.
SPT
Well, I thought it was. What have you
got for X?
CC
Okay, about plus 15 degrees.
SPT
That sounds right.
CC
Let's go back and review that again.
You say the Sun is between the CSM and the ATM?
SPT
Yes. That's right.
CC
That's a negative-Y rotation.
CC
You're right, you're right. Okay, it is
a plus-Y rotation.
SPT
Nyaaa nyaaa.
CC
Okay. Okay, what we're going to do is
put in a plus-Y rotation of 40 degrees and a plus-X rotation of
15 degrees. We got a maneuver time on it of 15 minutes. If we
don't hack it this time we'll probably suggest turning it over
to you. And before you would ever try to do it, you would need
to - before you ever select solar inertial mode, you need to
make sure that you put in a command to initialize your strapdowns because they're way off right now.
SPT
Understand.
CC
And for Pete or Paul, I guess maybe we'd
like to ask a question. Is there any reason that duct 1 flow
would be down now. We've got a substantial drop in it.
SPT
(Garble) MDA. Oh, duct 1. No, not that I
know of. I can go check it if you want.
SPT
Talking about duct 1 in the workshop,
right?
�SL-II MC-117/2
Time: 23:47 CDT, 1:15:47 GET
5/27/73
CC
That's affirm.
SPT
We didn't do anything. I'll go check it.
SPT
If you're ready, let me give you
a status of our ECS, all right?
CC
Okeydoke, go ahead.
SPT
Okay, we presently are running both
condensing heat exchangers A, and mol sieve A and B. We just
finished a condensate dump into the waste tank. We have two
ducts. Ducts 1 and 2 were running in the workshop. We got
the airlock module duct fan on HIGH with all the mol sieve
air going to the workshop through that diverter valve. We've
got the MDA fans on low, the CSM fans on low, and the three AM
circ fans we just turned on about 5 minutes ago on LOW.
CC
Okay, we copy. We got all four fans
running in ducts 1 and 2. Is that affirm?
SPT
Hell I turned them on. I'll go check.
CC
Okay.
SPT
You still want to leave just ducts 1 and 2,
leave 3 off, right?
CC
That's affirm.
SPT
Okay. You say duct 2 is the low one?
CC
Negative. Duct 1.
SPT
Okay.
CC
Joe. We have initiated a new one now.
And it might be - if you got time, it might be wise to take
a look out and see. Looks like we're going the right direction.
SPT
Roger.
cc
And CDR, Houston. If you got a chance,
I guess maybe we'd like to get an idea about how much longer
you guys are planning on working.
CDR
I'm trying to make dinner. I don't think
we're going to work very much longer. I would like to go to
bed, but everytime we do, something comes up. Duct 1 for
600 plus; CSM.
cc
Roger, understand. Duct 1 600 plus; CSM.
CDR
Duct 2 (garble) 550 and duct 3 (garble)
75; CSM.
CC
Roger, copy.
CDR
And, Crip, as soon as we get into sun
shine, I'll give you a hack on the maneuver. I guess it'll
be gone by then.
CC
Roger. Also be advised that we're
starting to get a lot of feedback out of those SIAs. If you
might could do a little adjustment. I don't know whether it's
ringing there or not.
CDR
Yeah, it is.
CDR
Hey, Crip, how much temperature skid
drop are you getting. Does it really look like that the
shield's working?
�SL-II MC-117/3
Times 23:47 CDT, 1:15:47 GET
5/27/73
CC
That's affirm. It looks like it's really
coming down. Did you hear my last call back when we were - at
Guam I gave you a call that we'd dropped 70 degrees.
CC
That's skin temp. I'll probably get a
hack for you - what the workshop temperature inside - what we
think it is. Okay, the next pass is going to be coming up at
Ascension at 05:00. And would you like us just to forget that call?
CDR
No, we're eating. We're trying to get
to bed. I think that everybody shouldn't worry too much if
we slipped a day, around here a little bit. Let us sleep in in
the morning. (Garble) We're hanging in there. We've had a lot
of (garble) come up today. You know - kind of held us back.
CC
Rog, Pete. I'm getting an awful lot
of feedback there still. We're going to have LOS in about 1
minute. We will give you a call at Ascension and I understand
that your recommendation is you'd like to sleep in tomorrow.
CC
And we concur.
CC
And we would like to make sure that we
have the VTR MAIN POWER switch left on because we want to
dump it and take a look at that dump - parasol deployment parasol, rather.
CDR
Okay, Crip, and how's that on the
squeal now? That should be a little bit better. We've com
pleted everything today, but with all the rest of the little
master alarms and the few things that came up, we're running a
little behind. We'll sleep in. We'll press on with the day 4
just like it is in the book and hopefully we can catch up. You
know, somewhere along in there and then we'll screw our day back
around to the right time.
CC
Rog, Pete. You're doing a fantastic job.
(garble) sleep in.
CDR
and besides that (garble) completed
(garble).
PAO
This is Skylab Control. We have loss of
signal at Vanguard. The spacecraft is now traveling over the
ocean on rev 181. We'll have acquisition of signal again at
Ascension in about 3 minutes. During the conversation, one of
the important points that was brought up is the pitch maneuver
that has now been commanded at Vanguard. There was some question in
the minds of flight controllers as to whether the crew had
indicated that the craft was pitched up in their opinion or
pitched down. And there was a question here whether they
should do a 40 degree maneuver in one direction or the other.
They did clarify that. The indication is that the crew - from
the crew that there was a pitch up and we are pitched up 40
degrees, so we are now in the process of pitching down and
we're also doing a roll of 15 degrees. And hope that we can
get the spacecraft properly in solar inertial mode. They are
not absolutely certain that 15 degrees is the right number, but
�SL-II MC-117/4
Time: 23:47 CDT, 1:15:47 GET
5/27/73
it gives them a fairly wide range of latitude. They know that
it's something a little over 10 and 15 should get them well
within range and they have a range of about 9 degrees. They
also indicated that there are figures here on - from telemetry
data was that we had a 75 cubic feet per minute air flow through
duct 1 in the orbital workshop. However, visual inspection
there indicated that that indicator was not reading properly.
And we have a 600 cubic feet per minute reading which is a proper
reading for that duct with four fans operating. Some of the
noise you may have noticed earlier was feedback from a speaker
intercomm and they did clarify that. They reduced the sound
levels there and we got good clear voice after that. No figures
yet on what the temperatures are inside the orbital workshop.
It's about 70 degrees reduction in temperature on the outside
of the workshop, but the inside of the workshop still has it's
temperatures now leveling out, all at off-scale high. As you
know before we had a lot of temperatures that were below 120
degrees because of their location, but once you have air flowing
that 120 degree level is now pretty well spread throughout the
workshop with the exception of a couple of temperature scales.
Crew is presently eating and trying to get ready for bed. They
have now been given an okay to sleep in in the morning.
There will be no wakeup call given, and they may be asleep
promptly after this Ascension pass which is now 50 seconds away.
This again puts them a little bit behind the Flight Plan, but
they hope to catch up in the next couple of days. This won't
be a problem now that they have the major task fulfilled. This
is Skylab Control. We'll be staying live now. In 36 seconds you
should hear acquisition of signal at Ascension. The Ascension
pass is about a 9-minute and 48-second pass. And that's now just
27 seconds away. They should be finalizing because after that
we have a period of over 40 minutes before we have acquisition
of signal again at Guam. And during that period we would
expect them to have gone to sleep. This is Skylab Control.
CC
Skylab, Houston. We're AOS over Ascen
sion for the next 10 minutes.
CDR
Rog. Have you all found the Sun yet?
CC
We're waiting for you to tell us.
CDR
Did you get my (garble) on the first
Skylab record?
CC
Negative. You faded out there. Which
of the - CDR
CDR is faded from a dredge airlock completing
a complete 360 going through the OWS dome hatch without touching
anything and not contacting till in the middle of the airlock.
That's as far as we've made it so far. In our world breaking record
attempt to go for the dredge airlock through locker AA the command
�
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Title
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Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
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https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
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Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
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sdsp_skyl_000087
Title
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"SL-II MC-114/4 Time: 21:36 CDT 01:13:36 GET 5/26/73" - "SL-II MC-117/4 Time: 23:47 CDT, 1:15:47 GET 5/27/73."
Description
An account of the resource
This mission commentary primarily depicts the Skylab 2 crew transitioning to permanent habitation in the Skylab 1 Orbital Workshop from the Skylab 2 Command module.
Creator
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United States. National Aeronautics and Space Administration
Date
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1973-05-26
Temporal Coverage
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1970-1979
Subject
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John F. Kennedy Space Center
Skylab Program
Skylab 1
Skylab 2
Conrad, Charles, Jr.
Weitz, Paul J.
Kerwin, Joseph P.
Life support systems
Onboard equipment
Airlock modules
Type
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Transcripts
Text
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Skylab Collection
Box 17, Folder 3
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
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en
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Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14423/sdsp_skyl_000088_001.pdf
41d6fc18270880a639e6b89dc3b3c397
PDF Text
Text
SL-II MC-616/1
Time:
2 0 : 4 1 CDT, 1 4 : 0 1 : 4 1 GMT
6/6/73
This i s Skylab Control, Greenwich mean
time 1 hour 41 minutes. As t h e Skylab s p a c e s t a t i o n completes
i t ' s 337th revolution as i t nears the Vanguard tracking station.
We e x p e c t CapCom Hank H a r t s f i e l d t o r e a d up t h e e v e n i n g news
to the crew as the Skylab space station will s t a r t i t s 338th
revolution.
CC
Skylab, Houston through Vanguard for 11 min
utes.
PLT
Hi there.
CC
And s o you d o n ' t get confused we goofed
up and sent you page 1 of the flight plan twice.
PLT
Say again what you did?
c c
Okay, we sent page 1 of the flight plan
twice.
c c
(Garble) Belay that.
We d i d n ' t s e n d i t t w i c e
we just put i t i n the wrong order.
PLT
You're forgiven.
PLT
Okay, Houston, i f you want a status report
on where we are, we're about to open the hatch.
We f i g u r e d
t o h a v e t h e EVA w r a p p e d up i n a b o u t an h o u r and a h a l f .
CC
A few people got up on that one.
PLT
(Laughter)
MCC
I'm glad I stayed awake.
PLT
No. seriously, we are a t the place on page
3 on t h e cue c a r d where i t s a y s OBM's a n d LCG k n o t t i n g ,
s o we're going t o p r e t t y much wind i t up there.
We're going
to smoke through the rest of i t and see i f there's any l i t t l e
details we could catch up on.
And go through t h e EVA p l a n
one more time and eat our ice cream and strawberries.
MCC
Sounds like preflight.
PLT
Hey, Rusty, I can't find that (garble).
I remember seeing i t that has the S082 dope on i t .
Is there
anything else of interest on that one?
MCC
Stand by.
S CHWEICKART
Yes, PJ, i t does have some other things on
it.
Stand by just 1.
PLT
Okay.
CDR
You know me, Rusty.
I like to get things
done early and not work late.
CDR
I t ' s like the night before Christmas up
here.
The suits are hung by the fireplace with their LSU's in
place just waiting to go.
MCC
Okay, Skylab.
I ' l l tell you what.
It's
not too long a message, but i t does have some other things
on i t t h a t deal with the prep and what we think w e ' l l do here
i s retransmit i t to you here over Ascension which i s coming
up in about 15 minutes.
PA0
�SL-II MC-616/2
Time:
2 0 : 4 1 CDT,
6/6/73
1 4 : 0 1 : 4 1 GMT
CDR
What's the message numbers, Rusty?
SCHWEICKART
I t ' s 1316 Alfa and aside from what we
already talked up, Pete, most of i t deals with Post and I
think the only thing in (garble) is getting the right film
magazine out of 141 there.
CDR
And I got i t (garble) and i t ' s ready to go.
END OF TAPE
�SL-II MC-617/1
Time:
2 0 : 4 7 CDT, 1 4 : 0 1 : 4 7 GMT
6/6/73
cc
Skylab, Houston, we need
c l e a n e d up o n t h e ATM p a n e l .
CDR
Shoot.
CC
Okay, we need t o get t h e H-alfa
camera OFF, and close the doors on H a l f a 1 and 2 , and the
S056 d o o r CLOSED, and MPC INHIBIT.
CDR
Okay, I was seeing how many of those you'd
pick up.
You did pretty good.
CC
And - CDR
I think we've got a bat charge light.
CC
The star trackers kicked off again and
we're getting some angles for you now.
We n e e d t o r e a c q u i r e .
CDR
How come I have a b a t charge l i g h t ,
Houston?
CC
Okay, s t a r t r a c k e r a n g l e s a r e OUTER
1500, INNER i s 0035.
And t h e b a t c h a r g e l i g h t o n CBRM 1 3 i s
no sweat; we just had the heaters on during the dark period
the re.
CDR
Hey, how come the heaters on the
night s i d e made the bat charge l i g h t come on then?
CC
I ' l l get an answer.
CDR
(garble)
CC
Okay, what happened there was the
heaters were on during the day l i g h t so the bat didn't get
completely charged.
CDR
Okay.
How much of a sweat i s i t ,
f o r power tomorrow on EVA?
CDR
Or to put i t another way, I ' d like a
briefing.
I don't want to be hanging half way out the hatch
and have PJ s t a r t t a l k i n g about b a t t e r y c h a r g e r s and PCG and
this that and the other thing without understanding whats going
B
on.
Okay?
CC
Okay.
The EVA power down we s e n t you
up there - the things we're going t o command o f f , t o t a l 1106
w a t t s and we c a l c u l a t e f o r the EVA, y o u ' l l need 1012 w a t t s
and t h a t i n c l u d e s the VTR which w e ' r e s c r u b b i n g , s o we
think we've got a real good margin.
CDR
Okay.
I won't scrub the VTR, you
f
know.
You'd be surprised how much you can see from the i n s i d e .
And I t h i n k w e ' l l put t h e camera up here and PJ can r e a l l y give
you a good shot of Joe standing out there because t h a t ' s the
wide open from t h i s STS window.
CC
Okay, we - t h a t ' s a good idea, we got
t h e - t h e VTR s c h e d u l e i n t h a t 1012 w a t t s and w e ' r e about
LOS now, P e t e .
Vanguard will be coming up in - correction
Ascension coming up in 56 and that w i l l be your med conference.
CDR
Okay, see you later.
*f
END OF TAPE
k U A . l l
�SL-II MC-618/1
Time:
2 0 : 5 5 CDT, 1 4 : 0 1 : 5 5 GMT
6/6/73
PAO
This i s Skylab Control, Greenwich mean time
one hour 55 minutes.
On t h e p r e v i o u s p a s s a c r o s s Vanguard
tracking station Science Pilot Kerwin jokingly told the ground
we're about ready t o open the hatch and we should have the
EVA o v e r i n about an hour and a h a l f .
His comments were
a d d r e s s e d t o t h e f a c t t h a t t h e crew i s t h a t w e l l a h e a d on t h e EVA
preparations for tomorrow morning.
When t h a t remark came
down from Skylab space s t a t i o n , s e v e r a l of the f l i g h t c o n t r o l
lers here in the Mission Control Center stood up and looked
around quite surprised.
Commander Conrad mentioned that they
were ready with their equipment for tomorrow morning.
He
said the LSU's are by the fireplace ready to go.
The LSU
i s the Life Support Umbilical which i s a 60-foot long umbilical
cord that the crew - through which the crew will receive their
oxygen and water supply for their liquid cooled garment that
they wear underneath their Apollo-type pressure suits for the
EVA.
We now a r e e n t e r i n g t h e A s c e n s i o n t r a c k i n g s t a t i o n ,
during which time Skylab Flight Surgeon, Dr. Charles Ross
will have the evening medical conference with the crew.
At
Greenwich mean time one hour 56 minutes, t h i s i s Skylab Control.
CC
Skylab, Houston.
We've got about 15 min
utes left.
SPT
Fifteen minutes?
CC
Roger, we're picking up Canary and Madrid
here contiguous.
SPT
Woo woo.
Okay, l e t ' s hear the l a t e show.
CC
Hey, I could give you a l i t t l e run down
on t h e power h e r e you asked about j u s t b e f o r e LOS a w h i l e ago.
The actions you're taking there are essentially cutting a l l
t h e f a n s o f f and g e t a l l t h e l i g h t s i n OWS, g e t t i n g t h e
w a r d r o o m w a t e r h e a t e r s o f f a n d t h e ATM C&D c o o l a n t l o o p o f f a n d
o n e o f t h e ( g a r b l e ) i s POWER DOWN, a n d t h a t t o t a l s o u t a b o u t
415 watts.
Now, j u s t p r i o r t o t h e EVA what w e ' r e going t o
d o i s command OFF t h e ATM e x p e r i m e n t p o w e r a n d g e t r e g s
three and 15 off which are not outputting anyhow, get your
bat h e a t e r ' s o f f , power down experiment Pointing and the
r e a l b i g g y t h e r e i s s w i t c h t h e ATM - t h e r m a l c o n t r o l s y s t e m
over to survival which saves us 466 watts.
And a l l t h i s comes
up to 1100.
And then t h e t h i n g s t h a t a r e required f o r your
EVA - a l l y o u r l i g h t s , SUS pumps, t a p e r e c o r d e r , and c o n
v e r t e r , t h e primary c o o l a n t l o o p , and LSU power comes o u t
t o about 887 and t h e n VTR i s a n o t h e r 125 f o r a t o t a l of 1 , 0 1 2 .
SPT
Okay, we noticed that l i t t l e note not t o
use the food heaters for lunch tomorrow.
I ' l l have you know
that we've only been using the food heaters for one food
each day and that's the evening frozen the meal.
CC
Roger, copy.
�SL-II MC-618/2
Time:
2 0 : 5 5 CDT, 1 4 : 0 1 : 5 5 GMT
6/6/73
SPT
Now, Henry, l e t me make s u r e t h a t t h e way
we're figuring on going tomorrow.
And I d o n ' t know what happened
to that message I told Rusty I'm missing.
We're going to basically
work from three books/pieces of paper.
One of them
b e i n g t h e EVA c u e c a r d s , a n o t h e r b e i n g t h e EVA c h e c k l i s t , and
t h e t h i r d b e i n g t h a t EVA p r o c e d u r e t h a t was s e n t up h e r e t o d a y
and yesterday - part of i t was in that stuff yesterday.
So
I assume that everything you're talking about i s included in
either checklist changes, cue card changes, or in that procedure,
is that right?
CC
That's affirmative.
SPT
And I remember s e e i n g t h a t message, Rusty
and I don't know how i t was thrown out of (garble).
CDR
Hey, by the way, what are you planner types
planning for the day after tomorrow so that we could get this space
craft put back in the right shape.
Don't forget we got tools
and you know a l l that other Mickey Mouse s a i l s are hanging
around and man, there's junk a l l over everywhere, so i t ' s
n o t j u s t t h e r e g u l a r EVA p o s t - o p e r a t i o n .
Copy that?
CC
Roger, we've got people looking at that,
Pete, and they're - we hope t o have a plan.
CDR
Okay, i t i s definitely going to take
us - I think we ought t o have a 12-man hour three hour each no e x c u s e me - n i n e manhour t h r e e h o u r e a c h p e r i o d i n a d d i t i o n
t o t h e normal p o s t EVA OPS t o p u t t h i s s p a c e c r a f t back i n shape
because we've done torn i t apart for the last two days.
CC
Roger, we concur.
END OF TAPE
�SL-II MC-619/1
Time:
2 1 : 0 4 CDT, 1 4 : 0 2 : 0 4 GMT
6/6/73
MCC
Henry?
^C
Hey, CDR o r t r o o p s up t h e r e .
We'd
like to say just a word about the lighting related to the power
here.
If you get out there, especially i f Joe gets up around
the discone antenna i n the evening there when i t s dark, and
decides he does not need the docking lights, PJ could pull
the breakers.
There are two breakers, they knock out the two
d i f f e r e n t l i g h t s t h a t apply t o t h a t a r e a , and we could
save power and would appreciate i t i f you don't need
those lights, Joe, to let PJ turn them off.
P L T
Are the breakers labeled what, docking
light?
MCC
Stand by, I ' l l get the specific
label on the panel for you.
PLT
1 got
another question while you're
doing that.
Remember, you said something about a reconfiguration
of the STS panel tonight.
I see that tomorrow night, but I don't
see anything to do tonight yet.
, MCC
Okay, we got that one.
The circuit
breakers for the docking light are on panel (garble).
PLT
Hello, Houston, you s t i l l there?
MCC
Roger.
PLT
Maybe I'm confused,
I have here a
message for (garble) I got a message number for you.
1414,
now i s t h a t t o be performed tonight or tomorrow night?
MCC
Roger, that has to be done prior to
t h e EVA.
That's the one I was talking about earlier, that i f
you could do, i t ' s a real short one, you might do i t tonight.
r - i a v.
^ » okay*
You c a n ' t ask me tomorrows
Flight Plan, and I thought - I locked in right away on
presleep plan tomorrow night. (Laughter)
MCC
Paul, the - we have two ways t o turn
off the docking lights - there's a switch on 207 which turns them
We g 0 t
t h e c i r c u l t breakers which turn off
u 7c
u' °r °n
half the lights
each of them.
And I ' l l t e l l you r i g h t now which
one turns off which lights.
. SPT
you in a minute.
H e
'8 en route
t o t h e MDA,
Rusty, he'll call
,
. . PL*
docking light switch
are the breakers, on
MCC
Okay, Rusty, I see the switch, the
above the caution warning.
Where
what panel?
202.
PLT
Okay, which one?
, 1 4 MCJ4 t
Okay» i t ? s next t o the bottom row and i t ' s
docking lights 1 and 2.
P J T
,
down, whatever i t
0h
is.
» yeah, okay.
I'm doing that power
The three configurations now, Hank.
�SL-II MC-619/2
Time:
2 1 : 0 4 CDT, 1 4 : 0 2 : 0 4 GMT
6/6/73
CC
Roger.
Copy.
PLT
O k a y , t h a t m a d e t h e AM b a t t e r i e s
6 and 7 s t a r t discharging (garble)
c c
Roger, we're going to take those
off the line tonight to keep them up.
PLT
Okay.
END OF TAPE
two BATS
�SL-II MC-620/1
Time:
2 1 : 1 0 CDT 1 4 : 0 2 : 1 0 GMT
6/6/73
CC
Skylab, Houston.
To f i l l you i n a
l i t t l e more on the power thing, the reason that we're doing
t h i s REG a d j u s t t o n i g h t i s - t h e p l a n i s t h a t i f we g e t i n t o
a bind and have to do the pitchup to 45 degrees for thermal
reasons, that to handle the loads we're gonna bring the
AM BATS o n t h e l i n e , a n d s o w e ' r e a l l s e t u p t o d o t h a t
and command i t from the ground.
PLT
Okay.
S CHWEICKART
And Skylab, Houston h e r e , we - and a s
I mentioned earlier had not thought about the view out the
STS w i n d o w a n d i f y o u c a n g e t a TV v i e w o u t t h e r e , t h a t
would be appreciated.
We c a n p i c k u p t h e r e a l - t i m e o v e r
the s t a t e s , which w i l l be shortly after sunrise, and w e ' l l
g i v e y o u a GO f o r u s e o f a VTR i f y o u w a n t t o t r y t h a t a l s o .
CDR
I have thought of physically putting
the camera there, Rusty, but there's nothing behind
your head, and you can see the whole dipole antenna
to the base, below the base, and the A-Frame, a l l through
t h a t w i n d o w , and I ' l l t h i n k y o u ' l l h a v e e x c e l l e n t TV o f J o e .
Mcc
Yeah, I think that would be a - very
educational here, and I think everyone would look forward to
seeing i t , i f it's no sweat.
CDR
Okay, I went back up t o look at
the s a i l again.
There i s no doubt about i t that the
orange i s beginning to fade.
I would say that i t ' s a nice
orangy-frost-gold now, i f that i s a good description.
And
I think I can get the TV up there t o where I can show you
about a 6 inch strip about 3 inches wide of i t .
In full
zoom, you might think about what that would do for color
resolution.
And we can work that one l a t e r .
^cc
Okay, fine.
It just so happens I
have i n my very hand a t t h e moment a couple o f samples o f
the sail material here, which have been exposed to various
thermal c y c l i n g , and l e t me ask you, with your d e s c r i p t i o n
if you might take a gander at the stationary end of the
LBNP f o r c o l o r c o m p a r i s o n w i t h what y o u j u s t d e s c r i b e d t o
me .
don't know.
I t ' s s t i l l much more
oranger than that, Rusty.
That's a flat gold and this has
s t i l l got a lot of orange l e f t in i t , but i t ' s - i t looks
faded.
That's what i t looks like.
CDR
1
**CC
Okay, fine, well i t ' s between two of
them that we got here i n our hands right now.
So that does
give us some hack on i t , thanks.
. CDR
Okay, give us a l i t t l e more advance
warning i f we're going to do a s a i l deployment, w i l l you?
MCC
1
kee
P frying to get
some, but I'm not
�SL-II MC-620/2
Time: 21:10 CDT 14:02:10 GMT
6/6/73
having much luck.
Skylab, Houston.
We're about 30 seconds
from LOS.
Be c o m i n g u p o n G u a m a t 4 0 , a n d I d o h a v e s o m e n e w s
if you've got time to listen to it there, if not we'll do
it in the morning.
PAO
This is Skylab Control.
Greenwich
mean time 2 hours and 15 minutes. The previous several
passes had Commander Conrad, Science Pilot Kerwin, and
Pilot Paul Weitz discussing preparations for tomorrow's
EVA.
Commander Conrad passed to the ground a suggestion
that they use the TV camera tomorrow by placing it at one
of the windows in the STS, the structural transition section,
which is between the airlock module and the MDA, the multiple
docking adaptor.
There are four windows, 8 by 12 inches, oval
windows spaced 90 degrees apart, on the outside of the STS.
Commander Conrad said that by placing the camera in one of
those windows, they might get a good picture of Science
Pilot Joe Kerwin as he passes out the equipment for the EVA.
At G r e e n w i c h m e a n t i m e 2 h o u r s a n d 1 7 m i n u t e s , t h i s i s
Skylab Control, with next acquisition at - over the Guam
Island tracking station in 23 minutes.
cc
END OF TAPE
�SL-II MC-621/1
Time:
2 1 : 3 8 CDT, 1 4 : 0 2 : 3 8 GMT
6/6/73
PAO
This i s Skylab Control, Greenwich mean
time two hours 38 minutes.
We w i l l h a v e a c q u i s i t i o n o f t h e
Skylab space s t a t i o n over the Guam I s l a n d tracking s t a t i o n
momentarily.
We'll hold the line up for conversations.
Probably
the last conversation with the crew tonight before they get
t h e good-night c a l l from Cap Com Hank H a r t s f i e l d .
CC
Skylab, Houston through Guam f o r 1 0 minutes.
PLT
Hi.
CC
PLT?
PLT
Yeah?
CC
Yeah, h e y , PJ l e t me t e l l you a b o u t one
thing here t h a t ' s come in l a t e and just a warning f o r tomorrow.
If you've got message 1326 around which i s the second part
of t h e EVA p r o c e d u r e s t h a t i s the p o r t i o n where y o u ' r e changing
out the S082-A film?
P L T
Well, we just happen to be there, talking
i t over.
Let me - t h e s e message numbers d o n ' t r e a l l y do a n y t h i n g f o r
us, Rusty.
We d o n ' t f i l e them by message number.
We g o t t a
have a subject.
Yeah, I see how I missed that other card I
missed the - well anyway I made what I thought was most of
the changes and threw that other message away.
I missed changing
the stowage compartment number though.
CC
Okay, well the one I'm talking about now,
t h e n , P a u l i s g e n e r a l message EVA a d d i t i o n a l .
PLT
I'm looking at i t Rusty, go ahead.
SCHWEICKART
Okay.
Down t h e r e where - a f t e r t h e magazine
i s a l l replaced and you're up at panel 130 doing the film
checks there, the verifications?
PLT
Yeah.
SCHWEICKART
Okay, we found out l a t e here, unfortunately,
t h a t t h e r e may be a r e l a y r a c e l o g i c problem which means t h a t
when you - okay you go down about three l i n e s there and y o u ' r e s t e p
and i t s a y s main power s w i t c h ON?
pCT
I'm looking, wait a minute.
SCHWEICKART
Okay, i t ' s right after i t says EV-3 and
y o u r e s e t t h e f i l m c o u n t e r a n d t h e n i t s a y s XUV SPECT MAIN
POWER s w i t c h ON a n d t h e n i t t a l k s a b o u t t h e p o w e r d o o r s .
P L T
Yeah, okay I got i t .
(Garble) are you
getting to handling these things?
You know, I got a 16-foot
message here and I'm trying to read from i t .
I t ' s hard to
find things sometimes.
But I've found that place, go ahead.
SCHWEICKART
Okay, the problem here i s that the door
i s open - the outer door i s open when you s t a r t this thing
a n d i f y o u j u s t t u r n t h e m a i n p o w e r ON t h e n t h e r e - i t ' s p o s
sible that the logic race will be such that you will not get
a film decrement even though everything i s okay.
And t h e way
t o f i x t h a t up i s j u s t before main power switch ON, go ahead
�SL-II MC-621/2
Time:
2 1 : 3 8 CDT, 1 4 : 0 2 : 3 8 GMT
6/6/73
and put the power door switch OFF and wait i o r tne doors t o
close.
In other words, wait about 20 seconds and then go
r i g h t a h e a d w i t h t h e m a i n p o w e r s w i t c h ON e t c e t e r a .
PLT
You're saying then that the power door's
power to the doors i s independen t of on the main power switch
position?
SCHWEICHKART
Yeah, the main power position will affect boi
doors, both the outer door, the thermal shield door and the inner
door.
If you have the main power switch OFF t h e i n n e r
door
will remain closed but the thermal shield door will s t i l l open
a n d c l o s e when y o u h i t t h e POWER DOOR s w i t c h .
PLT
Okay, so just ahead of main power
switch
ON y o u w a n t me t o s a y p o w e r d o o r s O F F .
SCHWEICKART
Right and then wait 20 seconds and then
press on with i t just as written.
PLT
Okay.
SCHWE1CKART
And I hope - I ' d l i k e t o promise you t h a t
t
that s the l a s t change on anything we got here.
And l e t me
try that just before we go t o bed here.
PLT
Okay.
Skylab, Houston.
I've got a few news items
Are you too busy to listen or rather wait?
PLT
No, take them up.
okay,
t n v,<
/
/
I ' l l s t a r t off by saying on this day
1Q
in history, 1944 we landed i n Normandy.
President Nixon's
made several new appointments t h i s week.
Former Defense Secre
t a r y , Melvin Laird has been made p r e s i d e n t i a l counselor f o r
domestic affairs.
Laird said that he will form close ties with
the heads of a l l the federal departments and agencies with
members of Congress and with the President.
He w i l l have cab
inet s t a t u s and w i l l be a member of the National Security
Counsel.
General Alexander Hague w i l l r e t i r e from the Army to
become Nixon s assistant in charge of the White House s t a f f .
Hague, as you recall, waas former assistant t o Henry Kissinger
and has been acting as the White House Chief of Staff about
one month.
Kansas City Police Chief, C.M. Kelley i s expected
to become permanent Director of the FBI.
Kelley's been in
his present job since 61 and i s considered an innovator of
new police methods and techniques.
Kelley was an FBI agent
for more than 20 years.
Ronald Zeigler, White House - CC
here.
END OF TAPE
�SL-II MC-622/1
Time: 21:46 COT, 14:02:46 GMT
6/6/73
CC
Kelly has been in his present job
since '61 and is considered an innovator of new police methods
and techniques. Kelly was an FBI agent for more than 20 years.
Ronald Zeigler, White House Press Secretary will become a
presidential assistant for communications in addition to keeping
his present duties.
MCC
Okay, President Nixon will be near the
Cape Kennedy area Friday when he delivers a commencement
address at Florida Technological University.
The new school
was founded in 1968 and will be graduating about 700 students.
Vice President Spiro Agnew spoke to U.S. Governors at the National
Governer's Conference Wednesday at Stateline, Nevada.
Agnew
told the audience that he is " available for consultation,
available for counseling."
MCC
In Paris, Henry Kissinger resumed secret
talks with Lee Due Tho, solithuro member from Hanoi. The two
representatives are seeking ways to halt continued violations
of the cease-fire in Viet Nam.
Congress was told by Deputy
Defense Secretary, William Clements that the Pentagon will
not order any more F-lll fighter bombers when the current
production run ends late next year. The Air Force will have
543 of the aircraft by that time.
MCC
The Senate Watergate hearings continue
to be televised during the daytime hours. Wednesday's hearings
featured Hugh Sloan, Jr., former Republican Campaign Treasurer.
Sloan discussed the intricate business of receiving and handling
huge sums of money during the election campaign.
He also
expressed his concern that the committee to re-elect the President
might be involved in the Watergate affair, but said he was
ignored by other officials.
A bill has passed the House of
Representatives to raise the minimum wage from a $1.60 an hour
to $2.20 an hour next year.
They will also extend coverage
to six million more American workers, including household
domestic workers. The bill now goes to the Senate.
CC
I guess my wife's going to get a raise.
CC
Wet weather in the mid-west caused by this
Spring's heavy flooding has delayed Spring crop planting.
Farmers and federal agricultural officials can't agree however,
whether delay will mean higher prices for consumers.
Bridgette
Bardot announced that she will retire from film making. "I
have had enough" she was quoted as saying. Some baseball
scores from yesterday, National League - Philadelphia 4,
Houston nothing. Dodgers 10, Chicago 1, Montreal 7, Atlanta
6, San Francisco 3, Pittsburg 2, Cinncinatti 6, New York 5,
Saint Louis 5 and San Diego 3. In the American League the
scores were 7 to 4, 9 to 2, 8 to 6, 5 to 4, and 5 to 2.
PLT
(Garble) report.
SCHWEICKART
Good night Henry.
�SL-1I
MC-622/2
Time:
21:46 CDT, 14:02:46 GMT
6/6/73
CC
SCHWEICKART
PLT
CDR
cc
Goodnight Rusty.
Goodnight, Henry.
Good day you all.
Thank you, we appreciated that.
Skylab, Houston we're about 30 seconds
from LOS.
We'll see you in the morning.
Okay, Hank you might make sure you give
us a holler (garble) we're up by 11:00.
What are the State s
passes (garble)?
Have you got them?
Y o u s a y y o u w a n t a w a k e - u p c a l l i n trie
CDR
morning^ Pete.
well, if you got one around" give us a holler
Real good.
We appreciate the good (garble) even though we have
been needling you.
We'll give (garble)
And we just need to - one last message here
cc
we need to INHIBIT the MOMENTUM DUMP on the next rev.
We messed
, .
This is Skylab Control, Greenwich mean
time two hours 51 minutes.
The crew has closed out their
14th day in space as the Skylab space station passed over the
Guam tracking island - tracking station on rev 338.
The crew
closed out the night by getting the daily news report from
Astronaut Rusty Schweickart and Hank Hartsfield.
The daily
medical bulletin from Dr. Charles Ross, Skylab Flight Surgeon
is as follows:
"The Skylab crew is in good physical condition
for tomorrow's EVA.
The Science Pilot mentioned his complete
lack of symptoms while conducting vigorous head movements during
the Ml31 protocol and the fact that none of the crew has ever
experienced any motion sickness.
The crew's day tomorrow
begins at 6:00 a.m. Houston time.
The EVA preparations will
run for about 3-1/2 to 4 hours.
EVA hatch opening is scheduled
for 10:37 a.m. central daylight time.
A four-hour EVA is
planned to accomplish five - four different activities:
de
ployment of the orbital workshop solar array panel, pin
ning back the S054 door in the Apollo telescope mount and
changing out the S082 film magazine.
The crew will be wearing
Apollo-type suits during the extravehicular activity.
The
crew will be attached to the vehicle by means of a 60-foot
long tether in which lines are provided to carry w 3 er, electri
cal power and oxygen.
During the EVA, Dr. Kerwm, an£.Commander Conrad will be hard-suited while inside the vehicle
in a pressurized portion of the vehicle, Pilot P a u l Weitz
will be soft-suited. He will not be wearing helmet or gloves
during this exercise.
He'll be in the pressurized portion
of what is referred to as the structural transition section,
a portion
between the multiple docking adapter and the air
lock module.
Pilot Weitz will monitor systems inside the STS,
ud
K
the (garble)
PA0
i
�SL-II MC-622/3
Time:
21:46 CDT, 14:02:46 GMT
6/6/73
and will also read Out procedures to the other two crew mem
bers as they perform the EVA. It's a possibility that the
TV camera will be put up at one of the windows of the STS.
There are four 8 by 12 inch oval windows spaced 90 degrees
apart on the outside of the structural transisition section,
and it's possible to get - possible they may get a picture
of Science Pilot Kerwin exiting the spacecraft. For early
space-watchers in the Houston area, tomorrow morning at
5:39 a.m., Skylab space station will pass on a westerly,
west to north path over Houston.
It will be visible for four
minutes and 14 seconds at an elevation of 15 degrees. At
Greenwich mean time two hours and 55 minutes, this is Skylab
Control.
END OF TAPE
�SL-II MC-623/1
Time:
2 2 : 0 5 CDT 1 4 : 0 3 : 0 5 GMT
6/6/73
A0
This i s Skylab Control, Greenwich
mean time 3 hours 5 minutes as the spacecraft i s on i t ' s
338th revolution of the Earth going over the South Pacific.
The crew h a s b e e n b i d good n i g h t f o r t h e e v e n i n g by CAPCOM
Hank Hartsfield and Astronaut Rusty Schweickart.
The crew will
arise at 6 a.m. Houston time, Central Daylight time to
begin a big day of extravehicular activities.
At 3 hours
6 minutes Greenwich mean time t h i s concludes the reports
from the mission control center.
The next report will be
Thursday morning at 6 a.m. Central Daylight time.
This is
Skylab Control, Greenwich mean time 3 hours, 6 minutes.
p
END OF TAPE
�SL-II MC-624 / 1
Time:
06:07 CDT,
6/7/73
1 4 : 1 1 : 0 1 GMT
PAO
This i s Skylab Control at 11 hours 1 minute
Greenwich mean time.
We're standing by for acquisition at of Skylab at the Honeysuckle Creek station in Australia.
Ex
pect to wake up the crew at that time, i f they're not already
awake.
Vehicle status has not changed over night.
CBRMs 3
and 15 are s t i l l offline and number 17 s t i l l has a degraded
output 4 to 4-1/2 amps below what's expected.
There was no
TACS g a s usage o v e r n i g h t .
We'll stand by for the wakeup c a l l .
CC
Good morning, Skylab.
This i s Houston.
We
got you at Honeysuckle for 5 minutes.
SC
Go ahead, Houston.
CC
Hi there.
CC
Skylab, Houston.
We're starting our morning
chores on commanding.
We're going back to s o l a r i n e r t i a mode
and closing fine sensor doors.
SC
How d i d t h e i n e r t i a go l a s t n i g h t ?
(Garble).
CC
Sorry, Joe.
Didn't copy the question.
SC
I ' l l c a t c h y o u l a t e r , I ' m a t a b a d VOX.
CC
Okay, w e ' r e about 1 minute from LOS h e r e .
We're going to see you at Hawaii at 11:23.
PAO
This i s Skylab Control; 11 hours and 9 minutes
Greenwich mean time.
We've had loss of signal at Honeysuckle.
The Hawaii station w i l l acquire i n about 13-1/2 minutes.
Entire
day today will be devoted to the extravehicular activity and
preparations for that activity and cleanup after the activity.
EVA d e s i g n e d t o f r e e t h e s o l a r a r r a y w i n g i n a n a t t e m p t t o improve
the electrical power situation on Skylab.
Two Apollo t e l e s c o p e
mount a c t i v i t i e s may be performed l a t e r t h i s evening by Joe
Kerwin, the science pilot, and Paul Weitz, the pilot.
However,
other than that and a short break for housekeeping tasks, the
entire day will be devoted to the extravehicular activity.
At
11 hours 10 minutes Greenwich mean time, this i s Skylab Control.
END OF TAPE
�SL-II MC625/1
rime:
0 6 : 2 2 CDT, 1 4 : 1 1 : 2 2 GMT
> / 7 / 73
PAO
This i s Skylab Control at 11 hours 22
minutes Greenwich mean time.
Skylab about to be acquired
at the Hawaii Station.
Now on i t s 343rd r e v o l u t i o n of t h e
Earth.
We'll stand by for acquisition at Hawaii.
CC
Hi there, Skylab; Houston.
We g o t y o u
at Hawaii for 7 minutes.
SC
Okay.
SC
I say, Houston, how did the momentum go
last night?
We d i d n o t i n h i b i t .
We f o u n d a s t a r i n s t e a d t h a t
looked l i k e we had a good Nz; so I'm i n t e r e s t e d in how things
came out.
CC
Joe, that work you did on the startracker
fixed us up r e a l f i n e , and we had no problems with momentum
throughout the evening.
SC
Okay.
SC
Say, Dick, there was a general message
sent up during the night or morning sometime, and one of them
w a s o n t h e MOL SIEVE.
CC
Roger.
SC
The answer i s yes.
CC
Okay, thank you much.
SC
And you might p a s s on t o t h e ECS guys t h a t
I inadvertently turned that thing off yesterday, and that's what
brought to mind the whole business about checking out the
primary timer.
We n e e d a l l k i n d s o f w o r d o n w h a t ' s s u p p o s e d
to happen when you i n i t i a l l y activate a timer.
Well, I got
to playing with the secondary one yesterday, in the course
o f p u t t i n g i t b a c k o n , a n d t h e s e c o n d a r y t i m e r o n MOL SIEVE A
worked like we always thought i t would work.
That i s , regardless
o f BED p o s i t i o n , a s s o o n a s you t u r n on t h a t t i m e r , i t i m m e d i a t e l y
vents A to adsorb and B to desorb.
CC
Roger; copy.
SC
And we heard they weren't supposed t o work
like that, but that one does.
Even i f i t ' s already there,
i t ' l l send a squirt of nitrogen through there and just
dump i t r i g h t away.
But i t works l i k e we thought i t didn't
anymore.
CC
Hey, Paul, are you i n secondary now?
SC
That's affirm.
CC
Okay.
CC
Well, PLT, t h a t ' s a l l kind of interesting.
The EGIL says that i t can happen the way you described.
It will
not - He thinks though i t w i l l not n e c e s s a r i l y happen t h a t way
everytime.
So possibly i t ' s been just coincidence so far.
At any r a t e , we are going to schedule a - a good timer checkout
when we get to i t .
SC
Okay.
Darn i t , l e t ' s say t h a t my d a t a , o r
�SL-II MC625/2
Time:
0 6 : 2 2 CDT, 1 4 : 1 1 : 2 2 GMT
6/7/73
what I ' m b a s i n g my remark o n i s t h e f a c t t h a t I t u r n e d t h e
MOL SIEVE - I i n a d v e r t e n t l y t u r n e d i t o f f , t u r n e d i t b a c k o n ,
and heard i t dump the gas but not cycle.
You know you can
hear - that thing gives you a big sigh i n your face when i t
cycles, and I didn't hear i t do t h a t .
So I opened up the
cover and looked, and A was in adsorb, B was in desorb
And
I thought I said, "Well, I wonder i f I'm double stroking that
bed?
So I ' l l hit i t one time and see i f i t cycles."
So I
turned the timer off, back on, and gave i t a shot of air and
dumped i t , and n o t h i n g happened t o t h e BED i n d i c a t o r s .
They
stayed where they were.
So I watched i t , thinking about what
EGIL i s going t o s a y , f o r a minute o r two, and then I turned
a n d b a c k o n , and
o
the same thing happened.
I t gave i t
h
h
C
f
n
l
t
r
8
e
n
d
u
m
e
d
i
b
they were °
°
°
'
P
, and t h e BEDS s t a y e d where
c c
C
,
.
T ^
e
co"Lt°=; . t l "
S C
END OF TAPE
3
r
n
Roger; understand.
Skylab, Houston.
We're about
8 1 0 h a v e a s h ° "
Roger, Dick.
30 seconds
r°u at
�SL-II MC626/1
Time:
06:31 CDT,
6/7/73
1 4 : 1 1 : 3 1 GMT
CC
Hello again, Skylab.
This i s Houston, and
we've got you for about the next 8 minutes.
SC
Roger.
CC
Skylab, Houston.
We're going to have a
short break, and we'll see you a t Bermuda.
SC
Roger, Richard.
END OF TAPE
�SL-II MC-627/1
Time:
0 6 : 4 2 CDT, 1 4 : 1 1 : 4 2 GMT
6/7/73
CC
Hello again, Skylab.
We're a t Bermuda
for the next 6 minutes.
SC
Okay, Houston.
CC
Skylab, Houston.
We're one minute t o LOS.
We're going to see you at the Canary Islands at 11:53.
SC
Roger, Dick.
PAO
This i s Skylab Control; 11 hours 51 minutes
Greenwich mean time.
We've had loss of signal at Bermuda.
There was no air-ground conversation during this pass over
t h e U n i t e d S t a t e s , o t h e r t h a n t h e u s u a l a m e n i t i e s a t AOS and
LOS.
We'll pick up Skylab at the Canary Island Station in
about a minute and a half.
We'll continue to stand by for
that pass.
END OF TAPE
�SL-II MC-628/1
Time:
0 6 : 5 2 CDT, 1 4 : 1 1 : 5 2 GMT
6/7/73
CC
Skylab, Houston.
W e ' r e AOS a t Canary
for 10 minutes.
SC
Roger, Dick.
And we j u s t passed over
an area that's almost like Meteorology for Naval Aviators textbook
pictures of developing cyclonic depressions.
They got a tropical
depression out here about oh a couple of 100 miles behind us now?
CC
Let me c h e c k w i t h t h e w e a t h e r man, P a u l .
CC
Skylab, Houston.
There i s a very large
low pressure center that you just passed over and i t ' s about
a 43 degrees north.
So i t can hardly be a tropical depression,
but i t i s - i t i s a large low area.
And t h a t ' s probably
what you saw.
SC
Yeah.
I t ' s loud and clear out there.
CC
Skylab, Houston.
We're about 1 minute
from LOS a t C a n a r i e s .
You guys are s t i l l on a long descending
pass down the African Continent.
And we're going t o see you
at Honeysuckle at 12:38.
SC
Roger, Dick.
^
T
h
i
s i s S k y l a b C o n t r o l a t 1 2 h o u r s 4 m i n u t e s
Greenwich mean time.
Skylab has passed out of range of the
Canary Station now.
At acquisition of the spacecraft a t Canaries,
the Pilot Paul Weitz reported sighting what he thought was a
classic textbook developing cyclonic depression just shortly
b e f o r e AOS.
Checked with the weather man; showed that there
is a large low pressure center in that area 42 degrees north.
:ie d e s c r i b e d i t , however, a s a p l a i n o l d s t o r m , n o t h i n g too
fancy.
We'll next acquire Skylab at the Honeysuckle Creek,
Australia, Station in 33 minutes.
I t ' s about 1 minute after
the crew i s scheduled to begin preparations for the upcoming
extravehicular Activity.
Those preparations scheduled to
begin at 15 hours, 37 minutes Greenwich mean time, or 7:37
I beg your pardon, those are scheduled to begin at 12:40
Greenwich mean time, or 7:40 central daylight time.
Hatch
opening i s scheduled at 15 hours, 37 minutes Greenwich mean
time or 10:37 central daylight time.
At 12 hours 6 minutes
this i s Skylab Control.
END OF TAPE
�SL-II MC629/1
Time:
0 7 : 3 7 CDT, 1 4 : 1 2 : 3 7 GMT
6/7/73
i s i s Skylab Control 12 hours 37 minutes
Greenwich mean time.
We're about 1/2 minute away from acqui
sition at Honeysuckle.
EVA p r e p a r a t i o n i s s c h e d u l e d t o s t a r t
12 hours 40 minutes.
The maroon team has taken over in the
Mission Operations Control Room.
Flight Director is Milton
Windier.
CAP COM A s t r o n a u t Bob C r i p p e n a n d t h e b a c k u p c r e w
Commander A s t r o n a u t R u s s e l l S c h w e i c k a r t i s a t t h e CAP COM c o n
sole also.
We'll stand by for the Honeysuckle pass.
c c
Good morning, Skylab.
We've got you
over Honeysuckle for about 8-1/2 minutes.
s c
Roger, Houston.
I'm ready to go ahead
w i t h ATM C&D p a n e l c o n f i g u r a t i o n p r o c e d u r e , o k a y ?
CC
Stan d by.
s c
An<* a n o t h e r t h i n g ,
I want you to verify
on the checklist on page 1.2-3 in the right hand corner that
w a s X e d o u t b e f o r e - d o y o u w a n t me t o c l o s e t h e OWS p a n e l 2
valve or not?
CC
Getting a reading on that, Paul.
Hold on.
SC
Okay.
CC
Okay, that's an affirmative PJ.
SC
On which one?
On t h e N2 v a l v e ?
CC
Yes s i r , affirmative on the N2.
What
was the other one?
SC
I'm ready to do
" p r e p s " w i t h ATM C&D
panel configuration soon as you guys say i t ' s okay.
CC
Okay.
Y o u ' v e g o t a GO o n t h a t , P a u l .
SC
You're easy to get along with this
morning.
Thank you.
SC
Houston, CDR.
CC
Go ahead.
SC
Oh my God, i s t h i s Rusty?
CC
That's affirmative.
SC
You better give us - what's the e a r l i e s t
time we can s t a r t
Rusty ?
CC
Okay, you've got a sunset a t right around
14:10.
Hold on, I ' l l get the exact time.
S C ,
Okay.
I'm not sure that w e ' l l make that
but there s - we're - try to (garble) things and just kinda
how f a s t i t goes, otherwise w e ' l l cool i t t o the r i g h t time.
CC
, „
Okay, we understand.
And we're s o r t of
PA0
T h
Prok»f
L 6 t me
8 l v e
here,
fPeettee." O
k a y , t h e p"
r i"
o r• s u n s e t t i m e i s a b o u t 1 4 : 0 3 .
A n d P e t e
f o r positive
...
,CC
ID purposes we'd
like just a word of confirmation that you'll be playing the
role of EV1 end that Dr. Kerwln win b e p l a y l n g P t h /,°L'of
SC
Say again Rusty.
I was top side.
�SL-II MC629/2
Time:
0 7 : 3 7 CDT, 1 4 : 1 2 : 3 7 GMT
6/7/73
CC
Roger.
Since we don't have any red
stripes around the arm we're just interested in being positive
that the player for EV1 w i l l be the commander and that the
p l a y e r f o r EV2 w i l l be t h e SPT.
Is that correct?
SC
That's Charlie.
CC
Charlie Pete Conrad.
SC
Okay, l e t me t e l l you where we a r e .
I'm
doing the visors right now which i s out of step and we're right
a t " s t r i p off the clothes, put on the biomed LCG's GO."
CC
Okay, we're right with you on our check
list here, thank you.
PAO
This i s Skylab Control.
Pete Conrad
reporting that he i s at this time coating the helmet visors
with anti-fog compound and he and Joe Kerwin are preparing to
put on the biomedical sensors and the liquid cooled garment.
To c l a r i f y conversation between Conrad and Rusty Schweickart,
a few minutes ago there i s a possibility the crew will be
ready and will open the hatch one sunset early.
There is a
possibility that hatch opening time w i l l be moved up to 14
hours 3 minutes Greenwich mean time o r 9:03 c e n t r a l daylight
time.
The regular hatch opening time i s scheduled for 15:30.
CC
Go ahead.
SC
Okay, I just want to double check, verify
Houston on S054.
I can go ahead and turn the main power
switch OFF, the door w i l l stay open, right?
CC
That's affirmative.
SC
Okay.
PAO
Skylab Control.
We're s t i l l holding
w i t h t h e F l i g h t Plan time f o r h a t c h opening of 1 5 : 3 7 Gmt o r
10:37 central daylight time, with the possibility of a hatch
opening a t 1 4 : 0 3 Gmt o r 9 : 0 3 c e n t r a l d a y l i g h t time.
CC
Okay, Skylab we've got about 30 seconds
l e f t here at Honeysuckle; going to pick up Hawaii at 58.
SC
Say again, Rusty.
CC
Right, we've got about 10 seconds here
and we're going to pick you up a t Hawaii a t 58.
SC
See you then.
PAO
This i s Skylab Control at 12 hours 48
minutes Greenwich mean time.
We've had loss of signal at
Honeysuckle on the 344th revolution.
Hawaii will acquire in
about 10-1/2 minutes.
Crew i s i n t h e i r EVA p r e p a r a t i o n s a t
this time.
Pete Conrad reporting he was coating the visors
with the anti-fog compound.
He and Joe Kerwin ready to don
the biomedical sensors and the liquid cooled garments.
Regu
l a r hatch open time f o r t h i s EVA, 15 hours 37 minutes Gmt.
That will be at sunset with the possibility that if the crew
s t a y s ahead o f t h e time l i n e on t h e EVA p r e p a r a t i o n s and i s
�SL-II MC629/3
Time:
0 7 : 3 7 CDT, 1 4 : 1 2 : 3 7 GMT
6/7/73
ready t o go 1 revolution e a r l y o r 1 sunset early we would pe
mit them to open the hatch at 14 hours 3 minutes Greenwich
mean time.
Four h o u r s s c h e d u l e d f o r t h i s EVA.
At 12 hours
49 minutes this i s Skylab Control.
END OF TAPE
�SL-II MC-630/1
Time:
0 7 : 5 7 CDT, 1 4 : 1 2 : 5 7 GMT
6/7/73
PA0
T h l s i s Skylab Control; 12 hours 57 minutes
Greenwich mean time.
We're less than a minute away from
acquisition a t Hawaii; w e ' l l stand by for that pass.
CC
Okay, Skylab.
We g o t y o u a g a i n a t H a w a i i
for about 10 minutes.
SC
Okay.
CC
Okay, Paul.
You might want t o expect the
PRIMARY COOLANT FLOW CAUTION AND WARNING h e r e .
EGIL's going
to be powering down the primary system.
I beg your pardon,
t h e y 1 1 b e p o w e r i n g i t u p , w h i c h w i l l g i v e y o u a C&W t h e r e
on PRIMARY COOLANT FLOW.
SC
Okay.
C
C
A
n d a l s o , PJ, f o r you up i n your area,
,
we r e going t o be doing some commanding here.
Specifically
we r e g o i n g t o e n a b l e AUTO RESET, and w e ' d l i k e you t o s t a y '
c l e a r o f the DAS.
I don't think you have any operations there,
but we d l e t you know t h a t .
SC
Okay.
CC
PLT, give a c a l l when you got a second.
SC
Calling Rusty.
Y
eah» okay" enc/
We g o t a n i n d i c a t i o n h e r e , P J ,
J
the S054 main power and thermal power are s t i l l on
Is
that the case up there?
We're looking at page 1.2-3, where
i t calls for them both to be off.
Yeah, and I finished that (garble).
L e t me g.
All right?
c c
Okay.
Appreciate i t .
SC
No, both the switches are i n the OFF position
CC
Okay, stand by just 1.
CC
okay, we may have a p u l s e r problem t h e r e o r
It hhe m b o ?t h! ' «t. o OnNi ', a nw d t h e n bd o lt ihk eb a cy ko u O tFoF ad g a1i 8n . g o a h e a d a n d c c l e
S c
Okay.
Task complete.
CC
okay>
Paul,
Stand by on that.
It looks
l i k e we may have a problem with the switch; w e ' l l get back
with you.
S C
double check.
r »I
°
Right.
I'm going in the workshop.
Okay, PLT.
We're going to go ahead and
command i t from the ground here and see whether that gives
us positive indication at a l l .
SC
Go ahead.
S C
CC
END OF TAPE
y
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
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sdsp_skyl_000088
Title
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"SL-II MC-616/1 Time: 20:41 CDT, 14:01:41 GMT 6/6/73" - "SL-II MC-630/1 Time: 07:57 CDT, 14:12:57 GMT 6/7/73."
Description
An account of the resource
This mission commentary primarily depicts the Skylab 2 crew working on, and maintaining the Apollo Telescope Mount systems.
Creator
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United States. National Aeronautics and Space Administration
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-06-06
Temporal Coverage
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1970-1979
Subject
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John F. Kennedy Space Center
Skylab Program
Skylab 1
Skylab 2
Conrad, Charles, Jr.
Weitz, Paul J.
Kerwin, Joseph P.
Extravehicular mobility units
Apollo Telescope Mount
Life support systems
Onboard equipment
Human factors in engineering design
Experimentation
Type
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Transcripts
Text
Source
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Skylab Collection
Box 17, Folder 5
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
https://digitalprojects.uah.edu/files/original/21/14424/sdsp_skyl_000089_001.pdf
76eb82b41ba91712aae583b04194ed95
PDF Text
Text
SL-III MC-1/1
Time: 05:01 CDT 09:10:01 GMT
7/28/73
LCC
This is Skylab launch control. T minus
1 hour 7 minutes and counting toward lift off in the second
manned mission in Skylab. At this time checks are underway on
the radar beacon aboard the space vehicle. There are two
of these beacons actually located in the instrument unit of
the Saturn IB. They're used in conjunction with ground
radars to track the velocity position and the acceleration
vehicle during the power phase of flight.
Up at the
320 foot level at the pad launch complex 39, the close out
crew are making their final preparations. They are taking
down some connector panels which connect the white room to
the space craft and sealing off the boost protective cover
hatch, which has now been pulled closed. We're continuing to
aim for a lift off time of 7:10:50, that is 10 minutes
50 seconds after 7:00 a.m. eastern daylight time this
rooming.
Now T minus 1 hour 6 minutes and countinq, this
is Kennedy Launch Control.
END OF TAPE
SL-III MC—2/1
Time: 05:10 CDT 09:10:11 GMT
7/28/73
LCC
This is Skylab Launch Control. T minus
56 minutes 58 seconds and counting.
Just completed
was a very critical power transfer test. During this test
the power is transferred from the ground source, which has
been being used up to this point to conserve on the flight
batteries. Transfer to those flight batteries to ensure that
all systems are operating during and after that transfer.
Transfer was made, the various elements of the launch team
reported in that systems continued operating correctly. We
switch back then to the ground source and we'll stay on that
ground source down to a T minus 50 second mark in the
countdown at which time we'll switch finally to the flight
batteries and stay on the flight batteries from that point on.
Coming up in the countdown are checks of the digital rain
safety receivers aboard the space vehicle. These receivers
are part of what's called the secure arrange safety systems
aboard the Skylab. A range safety officer could send a destruct
signal to the rockets if it became erratic or straight off
course. He would do this by initiating the emergency cut off,
and if necessary, the propellant dispersion command. The
systems are located on each stage of the Saturn IB. The
two receivers in each stage and they receive the signal from
the range safety officer, and then send them through the
proper channels to perform the propellant dispersion. These
actions of course will be taken only if the vehicle were so
erratic that it endangered land areas, and also only after
the crew has been advised and has used one of the escape
options that is open to them. Countdown proceeding smoothly
now in the final hour. T minus 55 minutes 23 seconds and
counting, this is Kennedy Launch Control.
END OF TAPE
�SL III MC3/1
Times 05:23 CDT 09:10:23 GMT
7/28/73
LCC
This is Skylab Launch Control, T-minus 45
minutes and counting. Chief Staff Supervisor, Bill Schick
advises that the swing arm, swing arm number 9, with the
environmental chamber will be coming back, it's coming back
now to the 12 degree or park position. Schick advises also
this and other aspects of the count continue to go well.
All on time or actually running somewhat ahead of schedule.
The environmental chamber at the end of swing arm 9, will
remain at the park position here. This is about 10 to 12
feet from the spacecraft. It could be quickly moved back
to the spacecraft in an emergency. Swing arm number 9 is
somewhat of a misnomer, the facilities here at complex 39
were designed for the larger Saturn V vehicle, 365-foot
tall. Specially designed 127-foot pedestal adapts the
smaller Saturn IB so that it does use the same upper swing
arm. Actually this is the fifth of the five swing arms used
for the Saturn IB, but it does continue to carry that
swing arm 9 designator, which it gained back in the Saturn V
program. Once the swingarm is moved back, launch escape
system is armed. That's the small rocket tower that can
be seen perched on top of the command module. That system
could be used by the astronauts in an emergency to pull the
command module free of the space vehicle. It would lift
it up in an arcing path, high enough so that the parachutes
could deploy and it could come down for a normal landing.
That launch escape system, interestingly enough, develops
a 147,000 pounds of thrust, that's about twice that
developed by the Mercury Redstone rocket, which launched
our first two astronauts into suborbital space. However
that's a rather short duration burn of 3.2 minutes for the
launch escape system. The escape system itself is 33 feet
long, weighs about 8,000 pounds. Now, T minus 42 minutes
57 seconds and counting. This is Kennedy Launch Control.
END OF TAPE
SL-III MC-4/1
Time: 05:00 CDT 9:10:00 GMT
7/28/73
LCC
This is Skylab Launch Control. T minus
34 minutes 59 seconds and counting. The closeout crew, which
left the pad area just a short time ago, has now cleared that
area. And the test supervisor. Chuck Henchel has announced
that the KSC area is now cleared for launch. Range safety
command receiver checks now have been completed and also the
replenishing of the liquid oxygen and liquid hydrogen is
continuing. Liquid oxygen and liquid hydrogen, the cryogenic
fuels for the Saturn IB, were loaded earlier this morning.
Actually completed loading at about the T minus 4 hour mark
in the countdown. These are continuing to be replenished
down through the countdown until we get into the terminal
sequencer; the replenishing is then stopped.
£t is necessary
to replenish these because there is some bci
ff that takes
place. T minus 34 minutes 11 seconds and co ~.r.g, this is
Kennedy Launch Control.
END OF TAPE
�SL-III MC 5/1
Time: 05:45 CDT, 09:10:45 GET
7/28/73
LCC
This is Skylab Launch Control, we are
T minus 23 minutes 48 seconds and counting toward the lift off
of the second manned mission in the Skylab program. Count
continuing to go smoothly here at Launch Complex 39. Preflight
command checks with the Mission Control Center in Houston
have just been completed. These are the checks of the systems
which are used to remotely command various functions in the
vehicle. Checkout of radar beacon number 1 has been
completed. Checkout of radar beacon number 2 underway as
all continues to go well. Science pilot Owen Garriott at
this time is completing some checks of the service module
reaction control system. He's armed that system which in
a sense means that he has opened valves allowing the hypergolic
fuels to flow down to the engine area. Hypergolic fuels are
ones that ignite on contact. In this case, for the service
module reaction control system, these fuels are monomethyl
hydrazine and nitrogen tetrocide. The system has been
pressurized, Garriott is now reading off the different
temperatures and pressures and the fuel quantities. Hypergolic
fuels are actually loaded aboard the service module well
before the countdown began. Service module reaction control
system provides stabalization and control of the spacecraft
during Earth orbit and docking. It can also be used for minor
course changes or the backup system for deorbiting the
spacecraft. We're continuing to look for 7:10 lift-off.
Actually to be more accurate 07:10:50, 50 seconds after
07:10. We have a window which extends to 07:19:27, that's
a.m. eastern daylight time. Weather continues to look good.
The sun is about to come here at Kennedy Space Center, it's
coming up through some cloud cover, we expect some of that
to blow off and at lift-off time, approximately 22 minutes
from now, we'll be looking for some scattered clouds, surface
winds at 6 knots, temperature is approximately 76 degrees
farenheit, and a visibility of about 8 miles. There is a
possibility of some ground fog but 8 miles visibility should
be good in most areas. T minus 21 minutes 44 seconds and
counting, this is Kennedy Launch Control.
END OF TAPE
�SL-III MC 6/1
Times 05:53 CDT 09:10:53 GMT
7/28/73
MCC
This is Skylab Launch Control. T minus
15 minutes and we're in a planned brief hold at this time.
This is actually a clock adjustment hold. It's to insured
that we are lifting off at the proper time to get us in the
best trajectory toward the orbiting laboratory. We'll resume
our countdown at 6:55:50 seconds. That's 6:55 am and 50
seconds. Chief Test Supervisor Bill Schick just reported to us
before going into the hold that all systems are in good shapem the
countdown has been running very smoothly. As we lift off at
7:50 this morning the orbiting Skylab will be some 300 nautical
miles South of Newfoundland. Predicted lift-off time 7:10:50
at this time. The orbiting lab of course was launched back on
May 14. Flight controllers out at Houston report that all
systems aboard there are in good shape and ready for the
second crew to move in and set up housekeeping. That crew
aboard the command service module this morning eager to get
there. When the count resumes at the T minus 15 minutes mark the
?Launch operations manager Paul Donnelley here in the firing room
he has the abort advisory responsibility up to the point when
the space vehicle clears the tower. He'll make some communi
cation checks with the astronauts on the special astro launch
circuit. This is a circuit on which the spacecraft test
conductor, the astronaut communicator Bob Crippen here in the
firing room and Donnelly use with the astronauts during the final
4 minutes of launch. This is essentially to isolate them from
any other discussions which might be going on in the operational
intercom system here in the firing room which link together
the various members of the launch team. Also as the count resumes
spacecraft will be going to full internal power. Up to this
point it has been powered by the fuel cells aboard the space
craft but also it has had a ground source fed to it as a backup.
We're about to resume the count.
MARK. T minus 15 minutes and counting now. Preparations under
way at this time now to chill the systems in the second stage which
will be receiving the very cold liquid hydrogen after first
stage burnout and as the second stage ignites. T minus 14 minutes
45 seconds and counting. This is Kenneday Launch Control.
END OF TAPE
�SL-III MC-7/1
Time: 06:01 CDT 01:11:01 GMT
7/28/73
LCC
This is Skylab Launch Control. T minus
8 minutes 59 seconds and counting. Bean, Garriott and Lousma
are now finishing up their checks inside the spacecraft.
Final launch vehicle checks also being made now before going
on the automatic sequencer. There is not an ignition switch
or button for the Saturn launches either the Saturn 5 or the
Saturn IB. An automatic sequencer takes over the count at
T minus 3 minutes and 7 seconds. And that sequencer then
initiates all action from that time, including the ignition.
There are some 91 cameras out at the pad that will cover the
action at ignition detailing the sequence of events for engineers
to study after the launch. A number of visitors here at
Kennedy Space Center have jammed the entire space center.
35000 guests have taken all available space on the space
center and this does not include thousands of people who are
lining the highways nearby. T minus 8 minutes 8 seconds and
counting. This is Kennedy Launch Control.
END OF TAPE
SL-III MC-8/1
Time: 06:04 CDT 01:11:04 GMT
7/28/73
LCC
This is Skylab Launch Control passing
the 6 minute mark in the countdown. T minus 5 minutes 57 sec
onds and counting. At this time various elements of the
Skylab team reporting in to the test supervisor with their
go or no go status. This team includes the mission controllers
in Houston. The Program Director who is watching from
here at Kennedy Space Center for this launch. The Air Force
Eastern test range who will perform tracking during the powered
phase of the flight, and of course the launch team here in
the firing room, all reporting in at this time. Houston
flight just reported in that they are go for the start of
the automatic sequencer. The Program Director William Schneider
also reports we're go for launch. Swing arm number 9, that's
the access arm that reaches across the launch tower to the
spacecraft, will be swinging back to the full retract position
just a few moments from now. Up to this point it's been in
a park position for about the last 40 minutes in a stand by
park position about 10 to 15 feet from the spacecraft. T minus
5 minutes. And sswing arm number 9 coming back now. It will swing
back 180 degrees, and a fully park position beside the launch
tower and it will remain there now through launch. Safety and
test support now reporting to the test supervisor Chuck Henschel
that we are go for launch. The range also says we are go for
launch. Launch Operations Manager, Paul Donnelly has given his go
and Walter Kapryan, Director of Launch Operations gives us a go
for launch. T minus 4 minutes 32 seconds and counting, this
is Kennedy Launch Control.
END OF TAPE
�SL-III MC 9/1
Time: 06:06 CDT 01:11:06 GMT
7/28/73
LCC
This is Skylab Launch Control. T minus
3 yes, 3 minutes 30 seconds and continuing to count. Launch
Vehicle Test Conductor Norm Carlson has reported to the
Test Supervisor that the launch vehicle is cleared for launch.
Essentially what he is saying is the launch vehicle is ready
to go on the automatic sequencer. The automatic sequencer
comes into play at T minus 3 minutes 7 seconds in the count
down.
Launch sequence has started now we passed the three
minutes 7 seconds mark and we're on the automatic sequencer.
Liquid oxygen and liquid hydrogen have been being replenished
up to this point. That replenish now will be terminated, the
vents will be closed and the fuel tanks will be pressurized.
This replenish has been necessary since these are cryogenic
or extremely cold fuels which do boil off. They were fueled.
Fueling was completely about 5 hours before launch and it's
necessary to continue to replenish them on down through the
final portion of the countdown. Various elements of the
launch team now reporting in. All coming in on a go condition.
T minus 2 minutes 20 seconds and continuing to count. Here
in the firing room we are having what's called operational
silence. The men have reported in that they're go. There
will be no further reporting in now except when they see a
problem. If they saw a problem they could report in. Could
request an override to this automatic sequencer and stop
the count. Bob Crippen the Astronaut Communicator here in the
firing room is reporting the countdown clock times to the
crew. Chuck Henschel the test supervisor reporting - END OF TAPE
�SL-III MC-10/1
Time: 06:08 CST 09:11:08 GMT
7/28/73
LCC
- - supervisor reporting the countdown
clock times here to the firing room team. Paul Downey, the
Launch Operations Manager just called up to the crew, said
the launch team wishes you good luck, and Godspeed. T
minus 1 minute 36 seconds and counting. A large status
board here in the firing room shows the status of the various
systems and also shows the action being taken by the automatic
sequencer. The instrument unit ready light now is on. The
emergency dectection system ready light is on. Launch sequence
start light of course came on at the T minus 3 minute 7 second
mark in the countdown. Pressurization of the tanks now showing
up now on our status board. ^S.IVB LOX tank now pressurized.
SIB fuel tank pressurized as we approach the 1 minute mark
in the countdown. MARK. T minus 1 minute, T minus 1 minute
and counting. In the spacecraft, Garriot and Lousma have
essentially completed their check out, and their - astronauts
Bean, Garriot and Lousma, they are ready to become the second
manned crew to man the orbiting Skylaboratory. T minus
42 seconds. Spacecraft commander now has made the final
guidance alignment. That's the final action to be taken
by the crew onboard the spacecraft until after the launch.
T minus 30 seconds. T minus 30 seconds and counting. The ^ight
first stage engines will ignite at 3.1 seconds in our count
down. They will be held down while thrust is built up until
the zero mark at which time we'll get liftoff. We'll be
looking for liftoff right at the T zero mark. We passed
the 15 second mark in the count. T minus 10, 9, 8, 7, 6,
5, 4, 3, 2. We have ignition sequence start. All ignitions all ignitions are running, all engines running. We have a
liftoff. And the second manned crew has cleared the tower.
CDR
Roll and pitch program, Houston.
CC
Roger, roll and pitch, Skylab. And thrust
looks good on all engines.
PAO
A1 Bean reports. Al Bean reports the
automatic maneuver that puts Skylab on the proper course.
Altitude 0.7 of a mile. Velocity 1432 feet per second.
36 seconds.
CDR
It's got a pretty noise to it right now.
CC
Roger that. You're looking real good.
PAO
Fifty seconds. 2-1/2 miles high.
1700 feet per second.
CDR
Comm down.
CC
Roger. Stand by for Mode 1 Bravo.
CDR
Roll arc (garble).
CC
Mode 1 Bravo.
CC
Roger.
CDR
Propellant DUMP is RCS command.
�SL-III MC-10/2
Time: 06:08 CDT 09:11:08 GMT
7/28/73
CC
Roger.
PLT
I get a great feeling of motion up here,
Dick. I really feel like it's moving out.
CC
Roger, PLT. And Skylab, Houston, you're
feet wet.
CDR
Understand.
PAO
One minute 30 seconds, 10 miles high now,
5 miles down range. Velocity 3280 feet per second. Thrust
still looking good. Trajectory looking good.
CDR
EDB engine out and LV rates off.
CC
Stand by for Mode 1 Charlie capability.
MARK. 1 Charlie.
Understand.
CDR
Skylab, Houston. Go for staging.
CC
Roger. GO here.
CDR
Twenty-two miles high, 19 miles down range.
PAO
Velocity 5800 feet per second. Standing by for staging.
CDR
Inboards. Outboards. Staging.
Roger.
CC
Good staging. Ignition on the SIVB stage.
PAO
Roger. We're watching the thrust come up now.
CC
Skylab, Houston. Thrust looks good on SIVB.
CDR
That's good news.
Two minutes 45 seconds. Altitude 41-1/2
PAO
miles. Velocity 7695 feet per second. Down range 60 miles
now.
Roger. Tower jettison, you're mode 2.—
CC
CDR
Guidance initiate.
Roger. Everything is looking real good.
CC
you're GO in 3 minutes.
CDR
It's nice and bright up here in the Sun.
CC
Roger.
PAO
Three minutes 15 seconds. Altitude 55 miles,
down range 90 miles, velocity 8889 feet per second. Thrust
still good on the second stage.
PLT
Okay, Dick, the cabin pressure is locked up
real good here. You should have seen that tower go.
CC
Roger. Understand.
CDR
And we're GO at 4 minutes —
CC
Roger, Skylab. We concur, you're GO
in 4.
PAO
Everything is still looking good. Skylab
now 142 miles down range. Altitude 70 miles, velocity
9135 feet per second.
PLT
Hey, we'd like to try that lift-off again.
That was great there Dick.
�SL-III MC-10/3
Time: 06:08 CDT 09:11:08 GMT
7/28/73
CC
My turn next.
PAO
That's a report there from Jack Lousma.
Four minutes 40 seconds down range now, 197 nautical miles
altitude 80 miles, velocity 10027 feet per second. Skylab
has achieved 34 percent of the velocity needed for orbit.
CC
There you GO at j^A looking real great.
PAO
Five minutes 35 seconds. Down range
283 nautical miles now, 88 miles high, 11687 feet per second.
PLT
Go at 6.
-^CC
Roger, CDR. Go at 6.
PAO
Skylab has 47 percent of the velocity needed
for orbit now. 12796 feet per second. Down range 354 nautical
miles. Altitude 91-1/2.
PLT
We're right on time.
CC
Roger. Omni Charlie. Thank you, sir.
PLT
I want to keep old Ed down there happy.
CC
He's happy.
CDR
Okay, we just put on the gimbal motors,
Houston.
CC
Roger, CDR.
CC
Skylab, Houston. We see 4 good gimbal
motors, good trims. You're go at 7 minutes, looking real good.
CDR
Roger.
PAO
Seven minutes 10 seconds now. Down range
473 nautical miles, velocity 15380 feet per second, altitude
92 nautical miles. Seven minutes 40 seconds. Skylab now
has 65 percent of the velocity needed for orbit.
CDR
PU shift, Houston. We're go at 8.
CC
Roger, PU shift. And we concur, you're go
at 8 minutes.
PAO
Propellant utilization shift. The mixture
ratio for the propellant has changed now to provide a better
propellant feed at altitude. Eight minutes 16 seconds.
Skylab now 648 nautical miles down range. Altitude 89 nautical
miles. Velocity 19172 feet per second. 75 percent of the
velocity needed for orbit now achieved.
CDR
We're go at 9, Houston.
CC
Roger, CDR, go at 9 minutes.
\PAO
Flight Director Phil Shaffer taking a
status for the Eurasian gate.
CDR
- - in the CMF.
CC
Roger.
PAO
He advises the range safety officer that
Skylab is go at the gate. Passing that gate will permit Skylab
to fly over portions of the land masses of Europe and Asia.
CC
CDR, Houston. We're predicting a guidance
�SL-III MC-10/4 *"
Time: 06:08 CDT 09:11:08 GMT
7/28/73
CC
cutoff at 9 plus 53.
CDR
Roger, 9 plus 53.
CC
Stand by for mode 3 Alfa capability.
MARK. Mode 3 Alfa.
CDR
Roger, 3 Alfa.
CC
Stand by for mode 4 capability. MARK,
mode 4.
CDR
Roger, mode 4.
PAO
Skylab could now get into orbit if it
had to abort, using the service propulsion system. At 9 min
utes 50 seconds.
V- CDR
125, 709. 122.2 by 83.2, we look good.
CC
Sounds real great.
PLT
You sure know it when it quits.
CC
Roger.
PAO
That was an onboard readout of the orbit,
122.2 nautical miles by 82.2 anutical miles. We'll confirm
the orbit with tracking in a little bit.
\
CC
Skylab, Houston. We've confirmed your orbit
•^and you're GO for orbit. Looks good.
CDR
Okay, tell the guys at KSC thanks. It
was a nice, nice job.
CC
Roger, Al.
PAO
And .the heaviest command and service module
ever to be launched is now in orbit, 13410 pounds^
CC
Hold separation sequence. We're aboift 45 sec
onds from LOS in Bermuda. We're going to drop out for about a
minute and a half, and I'll give you a call at ARIA.
CDR
Okay.
END OF TAPE
SL-III
MC 11/1
Time: 06:22 CST, 09:11:22 GET
7/28/73
PAO
The first Skylab command and service
module held a weight record before this, that weight was
13,383 pounds. We're standing by for communications through
a tracking aircraft.
CC
Skylab, Houston, through ARIA. How
do you read?
CDR
Read you pretty good, Dick. Everything's
going along all right.
CC
Roger. I hear a little bit of static
on the line but I heard fairly reasonably. We're standing by.
CDR
Okay.
CDR
And we're standing by for (garble), Houston.
CC
Roger.
SPEAKER Out stretchers are too long. As we move by
rapidly, it looks almost like we're above some strated layer at
5000 feet or something like that. They are really moving
out.
CC
Roger.
PAO
This is Skylab control at 16 minutes
ground elapsed time. Communication is very bad through the
aircraft. Skylab will be acquired by the Madrid tracking
station in about 3-1/2 minutes.
END OF TAPE
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Skylab Collection
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-1979
Relation
A related resource
https://libguides.uah.edu/ld.php?content_id=10578214<br /><br /><a href="http://libarchstor.uah.edu:8081/repositories/2/resources/80">View the Skylab Collection finding aid on ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Skylab Collection
Description
An account of the resource
Skylab was the first space station operated by NASA; it was launched without a crew on May 14, 1973. Skylab had three manned missions: Skylab 2, launched May 25, 1973, lasting 28 days, Skylab 3, launched July 28, 1973, lasting 60 days, and Skylab 4, launched November 16, 1973, lasting 84 days. Crews on Skylab conducted a variety of experiments during their missions, including experiments in human physiology, circadian rhythms, solar physics and astronomy, and material sciences. Important earth resources studies were conducting including studies on geology, hurricanes, and land and vegetation patterns.
Two of the more important components for conducting research on Skylab were the Apollo Telescope Mount (ATM) and the Earth Resources Experiment Package (EREP). The ATM was a multi-spectral solar observatory, and NASA’s first full-scale manned astronomical observatory in space. The ATM yielded a significant number of images and provided useful data for understanding our sun. The EREP provided thousands of images of the Earth’s surface in visible, infrared, and microwave spectral regions.
Skylab remained in orbit, unoccupied after the Skylab 4 mission, until July 11, 1973, when the space station reentered Earth’s atmosphere.
References:
https://en.wikipedia.org/wiki/Skylab#Manned_missions
https://www.nasa.gov/missions/shuttle/f_skylab1.html
https://history.nasa.gov/SP-402/ch4.htm
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
sdsp_skyl_000089
Title
A name given to the resource
"SL-III MC-1/1 Time: 05:01 CDT 09:10 GMT 7/28/73" - "SL-III MC-10/4 Time:06:08 CDT 09:11:08 GMT 7/8/73."
Description
An account of the resource
This mission commentary describes the Skylab 3 launch.
Creator
An entity primarily responsible for making the resource
United States. National Aeronautics and Space Administration
Date
A point or period of time associated with an event in the lifecycle of the resource
1973-07-28
Temporal Coverage
Temporal characteristics of the resource.
1970-1979
Subject
The topic of the resource
Merritt Island (Fla.)
John F. Kennedy Space Center
Skylab Program
Skylab 3
Lousma, Jack R.
Bean, Alan L.
Garriott, Owen K.
Saturn launch vehicles
Onboard equipment
Type
The nature or genre of the resource
Transcripts
Text
Source
A related resource from which the described resource is derived
Skylab Collection
Box 17, Folder 6
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
A language of the resource
en
Rights
Information about rights held in and over the resource
This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary