179
20
8239
-
https://digitalprojects.uah.edu/files/original/20/10660/propdeveprobassowithlargliqurock_040207114707.pdf
d984b42a968e80fbc708c86e6527176b
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Saturn V Collection
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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
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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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propdeveprobassowithlargliqurock_040207114707.pdf
spc_stnv_000628
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"Propulsion development problems associated with large liquid rockets."
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NASA TM X-53075.
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NASA technical memorandum, Propulsion and Mechanism Branch. Propulsion and Vehicle Engineering Division, Research and Development Operations.
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McCool, A. A.
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1968-08-12
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1960-1969
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Saturn project
Saturn stages
Spacecraft propulsion
Space vehicles
Liquid propellant rocket engines
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Text
Memorandums
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Saturn V Collection
Box 9, Folder 24
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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en
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spc_stnv_000625_000649
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http://libarchstor.uah.edu:8081/repositories/2/archival_objects/16850
-
https://digitalprojects.uah.edu/files/original/123/8027/r04a14-25.pdf
9219b9414a3993c6b007101218fd9e07
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Series 04, Subseries A: Huntsville History
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Series 04, Subseries A: Huntsville History
Still Image
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r04a14-25
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Frances Cabaniss Roberts Collection
Series 4, Subseries A, Box 14, Folder 25
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Title
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Rocket City, USA Booklet by McCormick and Record, 1953
Description
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Huntsville Tours
Relation
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r04a-210924
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McCormick, John
Record, James, 1918-
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1953
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1950-1959
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Advertising
Alabama–History–Huntsville, Madison County
Brochures
“Rocket City USA”
Tourism
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Pamphlets
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en
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-
https://digitalprojects.uah.edu/files/original/4/4131/spc_nick_000089_000090.pdf
f21cbe0effc22525b122d58861a7a9ac
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Col. John C. Nickerson, Jr. Papers
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spc_nick_000089_000090
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Letter to Robert K. Bell from Douglas H. McDonald.
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McDonald expresses interest in John C. Nickerson's case to Bell in this letter. He explains that he heard about the case from a friend, Ralph Wiltsie, who served under Colonel Nickerson during World War II. McDonald writes that Wiltsie is under the impression that the counsel will want to call him as a trial witness.
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McDonald, Douglas H.
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1957-04-30
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1950-1959
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Courts-martial and courts of inquiry--United States
Defense information, Classified
Intermediate-range ballistic missiles
Jupiter missile
Leaks (Disclosure of information)
Huntsville (Ala.)
Madison County (Ala.)
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Correspondence
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Col. John C. Nickerson, Jr. Papers
Box 1, Series 1, Folder 1
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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en
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spc_nick_2021_03
-
https://digitalprojects.uah.edu/files/original/4/4138/spc_nick_000099_000099.pdf
f49b6bdbc7e669d91f4f13c130082030
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Col. John C. Nickerson, Jr. Papers
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spc_nick_000099_000099
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Letter from Douglas H. McDonald to Robert K. Bell.
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In response to Bell's May 8th letter, McDonald informs Bell that Mr. Wiltsie will proceed as instructed regarding the reponse to the inquiry. He also expresses that he and his wife are excited to have Bell and his wife visit them.
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McDonald, Douglas H.
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1957-05-16
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1950-1959
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Courts-martial and courts of inquiry--United States
Defense information, Classified
Intermediate-range ballistic missiles
Jupiter missile
Leaks (Disclosure of information)
Huntsville (Ala.)
Madison County (Ala.)
Princeton (Ind.)
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Correspondence
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Col. John C. Nickerson, Jr. Papers
Box 1, Series 1, Folder 2
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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en
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spc_nick_2021_03
-
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
DOlIGtdS
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
/isrffO/v4(;ncs
CO/MP4/VV
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
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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/20/10728/nextstopthemoon_030209161111.pdf
eaccb02b26cb183f28376a9f936c4b85
Dublin Core
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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>
Identifier
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Saturn V Collection
Description
An account of the resource
<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>
Dublin Core
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Identifier
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Nextstopthemoon.pdf
spc_stnv_000552
Title
A name given to the resource
"Next stop : the moon."
Description
An account of the resource
Release describing the launch of the Apollo 11.
Creator
An entity primarily responsible for making the resource
McDonnell Douglas Corporation
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Saturn project
Apollo project
Liquid propellant rockets
Saturn S-4B stage
Type
The nature or genre of the resource
Text
Press Releases
Source
A related resource from which the described resource is derived
Saturn V Collection
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
spc_stnv_000550_000574
-
https://digitalprojects.uah.edu/files/original/20/10764/Moonbounphot_040709153207.pdf
e40fb1120c59885794f3a4d06be25c8a
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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Saturn V Collection
Relation
A related resource
<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>
Identifier
An unambiguous reference to the resource within a given context
Saturn V Collection
Description
An account of the resource
<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>
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
Moonboundphot.pdf
spc_stnv_000514
Title
A name given to the resource
"Moon-bound"
Description
An account of the resource
Press release describing a photograph of a lunar module.
Creator
An entity primarily responsible for making the resource
McDonnell Douglas Corporation
Date
A point or period of time associated with an event in the lifecycle of the resource
1967-11-26
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Saturn project
Apollo project
Apollo 11 flight
Saturn S-4B stage
Type
The nature or genre of the resource
Text
Press Releases
Source
A related resource from which the described resource is derived
Saturn V Collection
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
spc_stnv_000500_000524
-
https://digitalprojects.uah.edu/files/original/20/10842/Mcdodougsivb_092910153345.pdf
2c09d0ebd4b83bbff037aa4dfd31e60b
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
Saturn V Collection
Relation
A related resource
<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>
Identifier
An unambiguous reference to the resource within a given context
Saturn V Collection
Description
An account of the resource
<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>
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
Mcdodougsivb_092910153345.pdf
spc_stnv_000443
Title
A name given to the resource
"McDonnell Douglas S-IVB rocket for NASA's Saturn launch vehicle."
Description
An account of the resource
Press release detailing how a rocket is the top stage of both the Saturn IB and Saturn V launch vehicles.
Creator
An entity primarily responsible for making the resource
McDonnell Douglas Corporation
Date
A point or period of time associated with an event in the lifecycle of the resource
1967-07-01
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Saturn project
Saturn launch vehicles
Type
The nature or genre of the resource
Text
Press Releases
Source
A related resource from which the described resource is derived
Saturn V Collection
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
spc_stnv_000425_000449
-
https://digitalprojects.uah.edu/files/original/199/14368/sdsp_skyl_000021.jpg
54908bb9b88db9b70cb78e530e479316
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
Richard Heckman 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_000021
Title
A name given to the resource
Skylab Sticker, Realistic Depiction.
Creator
An entity primarily responsible for making the resource
McDonnell Douglas Corporation
Temporal Coverage
Temporal characteristics of the resource.
1970-1979
Subject
The topic of the resource
Skylab Program
Skylab 1
Space habitats
Type
The nature or genre of the resource
Stickers
Still Image
Source
A related resource from which the described resource is derived
Richard Heckman Collection
Box 2, Folder 8
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/75/1546/spc_spac_000281_000282.pdf
626c960eaea0b6644a71ce0a0dd0b738
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
Space City Collection
Title
A name given to the resource
Space City Collection
Description
An account of the resource
Space City was to be an outer space theme park fantasy based in Huntsville; it was to capitalize on space's growing popularity as putting man on the moon became closer and closer to reality. The park's construction began in January 1964.
Though a popular idea with the residents, the park ran into various difficulties and was never opened to the public or even fully completed. Construction was abandoned, and the land was put up for auction on October 17, 1967.
Relation
A related resource
<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/166">View the Space City Collection finding aid on ArchivesSpace</a>
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
spc_spac_000281_000282
Title
A name given to the resource
Flier advertising the "Half Scale 1910 Tin Lizzie Model T-10-Torpedo" and "The Buckboard Model 60" model cars.
Description
An account of the resource
This flier advertises the Tin Lizzie and Buckboard scale replica motored cars. It provides images, descriptions, and specifications for both vehicles.
Creator
An entity primarily responsible for making the resource
McDonough Power Equipment, Inc.
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Amusement rides
Motor vehicles
Type
The nature or genre of the resource
Advertisements
Fliers (Printed matter)
Still Image
Text
Source
A related resource from which the described resource is derived
Space City Collection
Box 3
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
spc_spac_2020_02
Provenance
A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource.
This collection was generously loaned for digitization by Dustin Shannon. The collection is digital only.
-
https://digitalprojects.uah.edu/files/original/75/1560/spc_spac_000305.pdf
cdf979123a3738d89b3729006cc2a7fa
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
Space City Collection
Title
A name given to the resource
Space City Collection
Description
An account of the resource
Space City was to be an outer space theme park fantasy based in Huntsville; it was to capitalize on space's growing popularity as putting man on the moon became closer and closer to reality. The park's construction began in January 1964.
Though a popular idea with the residents, the park ran into various difficulties and was never opened to the public or even fully completed. Construction was abandoned, and the land was put up for auction on October 17, 1967.
Relation
A related resource
<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/166">View the Space City Collection finding aid on ArchivesSpace</a>
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
spc_spac_000305
Title
A name given to the resource
McFadden "Ride Price List."
Description
An account of the resource
The list provides prices for different models of rides, including, but not limited to, "Bubble Bounce," "Dodgem," and "River Queen."
Creator
An entity primarily responsible for making the resource
McFadden, Richard B.
Date
A point or period of time associated with an event in the lifecycle of the resource
11/1/1960
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Amusement parks--Planning
Amusement rides
Type
The nature or genre of the resource
Price lists
Text
Source
A related resource from which the described resource is derived
Space City Collection
Box 3
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
spc_spac_2020_02
Provenance
A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource.
This collection was generously loaned for digitization by Dustin Shannon. The collection is digital only.
-
https://digitalprojects.uah.edu/files/original/75/1562/spc_spac_000310_000311.pdf
9bcc0a1423efc730d95f32c90210773d
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
Space City Collection
Title
A name given to the resource
Space City Collection
Description
An account of the resource
Space City was to be an outer space theme park fantasy based in Huntsville; it was to capitalize on space's growing popularity as putting man on the moon became closer and closer to reality. The park's construction began in January 1964.
Though a popular idea with the residents, the park ran into various difficulties and was never opened to the public or even fully completed. Construction was abandoned, and the land was put up for auction on October 17, 1967.
Relation
A related resource
<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/166">View the Space City Collection finding aid on ArchivesSpace</a>
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
spc_spac_000310_000311
Title
A name given to the resource
"Water Scamp."
Description
An account of the resource
This flier has an illustration of the Water Scamp, a diagram of the layout of its use in a pool, and its specifications.
Creator
An entity primarily responsible for making the resource
McFadden, Richard B.
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Amusement rides
Type
The nature or genre of the resource
Advertisements
Fliers (Printed matter)
Still Image
Text
Source
A related resource from which the described resource is derived
Space City Collection
Box 3
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
spc_spac_2020_02
Provenance
A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource.
This collection was generously loaned for digitization by Dustin Shannon. The collection is digital only.
-
https://digitalprojects.uah.edu/files/original/75/1571/spc_spac_000344_000345.pdf
87a8299ef88e7d9453d844ddd63cf4cc
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
Space City Collection
Title
A name given to the resource
Space City Collection
Description
An account of the resource
Space City was to be an outer space theme park fantasy based in Huntsville; it was to capitalize on space's growing popularity as putting man on the moon became closer and closer to reality. The park's construction began in January 1964.
Though a popular idea with the residents, the park ran into various difficulties and was never opened to the public or even fully completed. Construction was abandoned, and the land was put up for auction on October 17, 1967.
Relation
A related resource
<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/166">View the Space City Collection finding aid on ArchivesSpace</a>
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
spc_spac_000344_000345
Title
A name given to the resource
"Bubble Bounce."
Description
An account of the resource
This flier has a description, specifications, photographs, and an illustration of the Bubble Bounce ride.
Creator
An entity primarily responsible for making the resource
McFadden, Richard B.
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Amusement rides
Type
The nature or genre of the resource
Advertisements
Fliers (Printed matter)
Still Image
Text
Source
A related resource from which the described resource is derived
Space City Collection
Box 3
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
spc_spac_2020_02
Provenance
A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource.
This collection was generously loaned for digitization by Dustin Shannon. The collection is digital only.
-
https://digitalprojects.uah.edu/files/original/75/1572/spc_spac_000346_000347.pdf
7c8074cc539d78d004167d1615bfc5a9
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
Space City Collection
Title
A name given to the resource
Space City Collection
Description
An account of the resource
Space City was to be an outer space theme park fantasy based in Huntsville; it was to capitalize on space's growing popularity as putting man on the moon became closer and closer to reality. The park's construction began in January 1964.
Though a popular idea with the residents, the park ran into various difficulties and was never opened to the public or even fully completed. Construction was abandoned, and the land was put up for auction on October 17, 1967.
Relation
A related resource
<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/166">View the Space City Collection finding aid on ArchivesSpace</a>
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
spc_spac_000346_000347
Title
A name given to the resource
"Litter Bug" vacuum cleaner.
Description
An account of the resource
This flier describes the Litter Bug outdoor vacuum cleaner and its three models.
Creator
An entity primarily responsible for making the resource
McFadden, Richard B.
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Amusement rides
Type
The nature or genre of the resource
Advertisements
Fliers (Printed matter)
Still Image
Text
Source
A related resource from which the described resource is derived
Space City Collection
Box 3
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
spc_spac_2020_02
Provenance
A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource.
This collection was generously loaned for digitization by Dustin Shannon. The collection is digital only.
-
https://digitalprojects.uah.edu/files/original/75/1573/spc_spac_000348_000349.pdf
394f79a4bb993427435d8e4f2fdda20d
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
Space City Collection
Title
A name given to the resource
Space City Collection
Description
An account of the resource
Space City was to be an outer space theme park fantasy based in Huntsville; it was to capitalize on space's growing popularity as putting man on the moon became closer and closer to reality. The park's construction began in January 1964.
Though a popular idea with the residents, the park ran into various difficulties and was never opened to the public or even fully completed. Construction was abandoned, and the land was put up for auction on October 17, 1967.
Relation
A related resource
<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/166">View the Space City Collection finding aid on ArchivesSpace</a>
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
spc_spac_000348_000349
Title
A name given to the resource
"River Queen."
Description
An account of the resource
The flier has illustrations of the "Customer Operated Boat Ride" and its possible tracks as well as ride specifications.
Creator
An entity primarily responsible for making the resource
McFadden, Richard B.
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Amusement rides
Boats and boating
Type
The nature or genre of the resource
Advertisements
Fliers (Printed matter)
Still Image
Text
Source
A related resource from which the described resource is derived
Space City Collection
Box 3
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
spc_spac_2020_02
Provenance
A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource.
This collection was generously loaned for digitization by Dustin Shannon. The collection is digital only.
-
https://digitalprojects.uah.edu/files/original/20/10881/Liqurockprop.pdf
e3f281597e2f36cab928ab28ae6f845e
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
Saturn V Collection
Relation
A related resource
<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>
Identifier
An unambiguous reference to the resource within a given context
Saturn V Collection
Description
An account of the resource
<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>
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
Liqurockprop.pdf DIVIDED INTO TWO FILES
spc_stnv_000407
Title
A name given to the resource
"Liquid Rocket Propellant Compatibility Testing."
Description
An account of the resource
Material-propellant compatibility as related to liquid rocket propulsion system design criteria is discussed and applicable test methods to derive usable design data are presented. Test methods, with emphasis on metallic materials, are discussed and the shortcomings of a number of these test methods are pointed out. These tests include static immersion tests, stress-corrosion tests, flow tests, impact tests, and tests to determine the effect of cracks and notches in metals on compatibility. A general outline for the evaluation of metallic and nonmetallic materials with respect to propellant compatibility is presented.
Creator
An entity primarily responsible for making the resource
McFarlen, William T.
Date
A point or period of time associated with an event in the lifecycle of the resource
1967-06-28
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Saturn project
Liquid propellant rockets--Testing
Liquid propellant rockets
Type
The nature or genre of the resource
Text
Essays
Source
A related resource from which the described resource is derived
Saturn V Collection
Box 23, Folder 13
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
spc_stnv_000400_000424
Is Referenced By
A related resource that references, cites, or otherwise points to the described resource.
<a href="http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17703"> View this item in ArchivesSpace. </a>
-
https://digitalprojects.uah.edu/files/original/33/4724/loc_gold_000356_000357.pdf
1913ee951ecf281bd6cbd53ac92475b8
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
Goldsmith-Schiffman Collection
Identifier
An unambiguous reference to the resource within a given context
Goldsmith-Schiffman Collection
Description
An account of the resource
<p>"My ancestors were all German Jewish immigrants, members of four families who settled in Huntsville, Alabama before and following the Civil War. The Bernstein, Herstein and Schiffman families arrived during the 1850s, and Oscar Goldsmith arrived in 1879. Subsequent generations united these four families in marriage. Members of the extended family have figured in every phase of the history of Huntsville, both economically and socially; from the agrarian years of the nineteenth century through Huntsville’s growth after World War II, to becoming known as Rocket City USA; and socially, from the time of institutionalized slavery before the Civil War to segregation followed by the civil rights era."</p>
<p>-<a href="https://www.myjewishlearning.com/southern-and-jewish/highlighting-the-history-of-huntsvilles-jewish-community/">Margaret Anne Goldsmith in an interview with My Jewish Learning</a></p>
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
loc_gold_000356_000357
Title
A name given to the resource
Financial statement for Pacolet Manufacturing Company.
Description
An account of the resource
Detailed condensed financial statement for Pacolet Manufacturing Company located in Spartanburg, South Carolina.
Creator
An entity primarily responsible for making the resource
McIver, R. S.
Date
A point or period of time associated with an event in the lifecycle of the resource
1914-04-01
Temporal Coverage
Temporal characteristics of the resource.
1910-1919
Subject
The topic of the resource
Accounting
Business
Financial statements
Greenville (S.C.)
Spartanburg (S.C.)
Type
The nature or genre of the resource
Financial statements
Text
Source
A related resource from which the described resource is derived
I. Schiffman and Company
Box 99, Folder Dallas MGF. Co.
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
loc_gold_2021_02
-
https://digitalprojects.uah.edu/files/original/33/4685/loc_gold_000253_000257.pdf
43de0038eb30c0674e2c68baab275920
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
Goldsmith-Schiffman Collection
Identifier
An unambiguous reference to the resource within a given context
Goldsmith-Schiffman Collection
Description
An account of the resource
<p>"My ancestors were all German Jewish immigrants, members of four families who settled in Huntsville, Alabama before and following the Civil War. The Bernstein, Herstein and Schiffman families arrived during the 1850s, and Oscar Goldsmith arrived in 1879. Subsequent generations united these four families in marriage. Members of the extended family have figured in every phase of the history of Huntsville, both economically and socially; from the agrarian years of the nineteenth century through Huntsville’s growth after World War II, to becoming known as Rocket City USA; and socially, from the time of institutionalized slavery before the Civil War to segregation followed by the civil rights era."</p>
<p>-<a href="https://www.myjewishlearning.com/southern-and-jewish/highlighting-the-history-of-huntsvilles-jewish-community/">Margaret Anne Goldsmith in an interview with My Jewish Learning</a></p>
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
loc_gold_000253_000257
Title
A name given to the resource
Handwritten letters from R. D. McKinney to S. Schiffman.
Description
An account of the resource
In these letters, R. D. McKinney tells S. Schiffman that he will have to take all McKinney's stocks as his landlord has taken all his cotton stock to pay his rent before McKinney could pay S. Schiffman. In the second letter, McKinney asks S. Schiffman to send him two dollars to finish paying off the cotton pickers. The final letter is a request for meat and coffee on credit.
Creator
An entity primarily responsible for making the resource
McKinney, R. D.
Date
A point or period of time associated with an event in the lifecycle of the resource
1898-12-31
1899
Temporal Coverage
Temporal characteristics of the resource.
1890-1899
Subject
The topic of the resource
Cotton manufacture--United States
Rent--United States
Selling--Cotton
Huntsville (Ala.)
Madison County (Ala.)
Type
The nature or genre of the resource
Correspondence
Text
Source
A related resource from which the described resource is derived
I. Schiffman and Company
Box 95, Folder 1899
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
loc_gold_2021_02
-
https://digitalprojects.uah.edu/files/original/33/4749/loc_gold_000451_000451.pdf
543a34ff031d773a15123cab20791273
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
Goldsmith-Schiffman Collection
Identifier
An unambiguous reference to the resource within a given context
Goldsmith-Schiffman Collection
Description
An account of the resource
<p>"My ancestors were all German Jewish immigrants, members of four families who settled in Huntsville, Alabama before and following the Civil War. The Bernstein, Herstein and Schiffman families arrived during the 1850s, and Oscar Goldsmith arrived in 1879. Subsequent generations united these four families in marriage. Members of the extended family have figured in every phase of the history of Huntsville, both economically and socially; from the agrarian years of the nineteenth century through Huntsville’s growth after World War II, to becoming known as Rocket City USA; and socially, from the time of institutionalized slavery before the Civil War to segregation followed by the civil rights era."</p>
<p>-<a href="https://www.myjewishlearning.com/southern-and-jewish/highlighting-the-history-of-huntsvilles-jewish-community/">Margaret Anne Goldsmith in an interview with My Jewish Learning</a></p>
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
loc_gold_000451_000451
Title
A name given to the resource
Receipt from $85.32 for S. Schiffman & Co. from R. D. McKinney.
Description
An account of the resource
Receipt from $85.32 for S. Schiffman & Co. from R. D. McKinney.
Creator
An entity primarily responsible for making the resource
McKinney, R. D.
Date
A point or period of time associated with an event in the lifecycle of the resource
1899-06-01
Temporal Coverage
Temporal characteristics of the resource.
1890-1899
Subject
The topic of the resource
Business
Payment
Purchasing
Huntsville (Ala.)
Madison County (Ala.)
Type
The nature or genre of the resource
Receipts (financial records)
Text
Source
A related resource from which the described resource is derived
I. Schiffman and Company
Box 27, Folder 1910
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, 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
loc_gold_2021_02
-
https://digitalprojects.uah.edu/files/original/123/8231/r04a04-08.pdf
45ee0c0d97643d26454dbfe318bef009
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
Series 04, Subseries A: Huntsville History
Title
A name given to the resource
Series 04, Subseries A: Huntsville History
Still Image
A static visual representation. Examples include paintings, drawings, graphic designs, plans and maps. Recommended best practice is to assign the type Text to images of textual materials.
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
r04a04-08
Source
A related resource from which the described resource is derived
Frances Cabaniss Roberts Collection
Series 4, Subseries A, Box 4, Folder 8
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Title
A name given to the resource
McLaughlin, G. C. - copy
Relation
A related resource
r04a-210924
Creator
An entity primarily responsible for making the resource
McLaughlin, G. C.
Date
A point or period of time associated with an event in the lifecycle of the resource
1984-07-25
Temporal Coverage
Temporal characteristics of the resource.
1980-1989
Subject
The topic of the resource
Alabama–History–Madison County
Citizen lawsuits
Huntsville (Ala.)
McLaughlin, G. C.
Murder
Type
The nature or genre of the resource
Forms (Documents)
Photographs
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.