101
20
8239
-
https://digitalprojects.uah.edu/files/original/76/3920/Loc_burw-686.pdf
2cc930e0119d73e5533d781ff54ea720
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
Burwell Family Collection
Title
A name given to the resource
Burwell Family Collection
Relation
A related resource
<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/145" target="_blank" rel="noreferrer noopener">View the Burwell Family Collection finding aid in ArchivesSpace</a>
Description
An account of the resource
<a href="http://libarchstor2.uah.edu/digitalcollections/items/show/3332" target="_blank" rel="noreferrer noopener">View Edwin D. Burwell's World War II service timeline, 1943-1944</a>
<a href="http://libarchstor2.uah.edu/digitalcollections/items/show/3333" target="_blank" rel="noreferrer noopener">View Edwin D. Burwell's World War II service timeline, 1944-1945</a>
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.
Materials donated and digitized by Dudley Burwell
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_burw_000686
Title
A name given to the resource
American Tank San Piedro.
Description
An account of the resource
Photograph number 465. This photograph shows a flipped tank in San Pietro, Italy. The title for this image was found in Major Edwin D. Burwell Jr.'s list of photographs.
Date
A point or period of time associated with an event in the lifecycle of the resource
1944
Temporal Coverage
Temporal characteristics of the resource.
1940-1949
Subject
The topic of the resource
Tanks (Military science)
World War, 1939-1945--Campaigns--Italy
San Pietro Infine (Italy)
Type
The nature or genre of the resource
Photographs
Still Image
Source
A related resource from which the described resource is derived
Burwell Family 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
loc_burw_2021_03B
Creator
An entity primarily responsible for making the resource
Burwell, Edwin D. III [Burwell, Edwin D., Jr.]
-
https://digitalprojects.uah.edu/files/original/8/14230/loc_hbhc_American_Triple-Coated_Enameled_Ware.pdf
a0d022ad11129aeb8b0e1388cee55c9d
PDF Text
Text
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Harrison Brothers Hardware Collection
Relation
A related resource
<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/65" target="_blank" rel="noreferrer noopener">View the Harrison Brothers Hardware Collection finding aid in ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Harrison Brothers Hardware Collection
Description
An account of the resource
Originally establishing a tobacco shop on Jefferson Street in 1879, brothers James B. and Daniel T. Harrison moved their shop to their current location in Huntsville’s Southside Square in 1897. After the building was damaged by a fire in 1901, the brothers rebuilt and expanded their store, reopening as Harrison Brothers Hardware in 1902. After James’ death in 1908, Daniel T. and Robert Harrison, their younger brother, ran the store. In 1940, Daniel T. Harrison passed away leaving Robert the sole owner of the store. In the 1950s, Robert’s sons, Daniel F. and John Harrison, took over the store. In 1952, Robert Harrison passed away. In 1981, Daniel F. Harrison passed away leaving John Harrison as the sole owner of the store. The Historic Huntsville Foundation purchased the store in 1984, after the store closed due to John’s death in 1983. As one of the first major projects of the Historic Huntsville Foundation, the store was reopened in October of 1984 and is staffed by several volunteers. The Historic Huntsville Foundation currently continues the operation of Harrison Brothers Hardware in Huntsville, making it Alabama’s oldest operating hardware store.
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_hbhc_American_Triple-Coated_Enameled_Ware
Title
A name given to the resource
American Triple-Coated Enameled Ware advertisement.
Description
An account of the resource
This is an image of a Harrison Brothers advertisement for a "100-Piece Assortment of American Triple-Coated Enameled Ware". The advertisement also states "Quality Highest Standard" and features images of several enameled ware products such as pans, dippers, coffee pots, and tea pots. Each of the items included in the 100-piece assortment is listed and priced below the image. The description at the bottom of the page lists the freight charge for the purchase and describes the high quality of the "American Ware".
Creator
An entity primarily responsible for making the resource
Harrison Brothers Hardware (Huntsville, Ala.)
Temporal Coverage
Temporal characteristics of the resource.
1900-1909
Subject
The topic of the resource
Harrison Brothers Hardware (Huntsville, Ala.)
Advertising
Enameled ware
Huntsville (Ala.)
Madison County (Ala.)
Type
The nature or genre of the resource
Leaflets
Still Image
Source
A related resource from which the described resource is derived
Harrison Brothers Hardware Collection
Box 16
Folder 2
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
HBH_Merchants_and_Mill_Workers_RCEU_2023
-
https://digitalprojects.uah.edu/files/original/204/14646/The_Incident_1892.pdf
96ba3eb02bf4d24509dd2b6a85c1db02
PDF Text
Text
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
HON 399 Research in London
Title
A name given to the resource
HON 399 Research in London
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
An Incident at the London County Banquet
Description
An account of the resource
This is a page from a scrapbook with three pieces of a newspaper or magazine depicting the London County Banquet and an incident that occured with Frank Shorland.
Creator
An entity primarily responsible for making the resource
Cycling
Date
A point or period of time associated with an event in the lifecycle of the resource
1892-12-17
Subject
The topic of the resource
Cycling
Source
A related resource from which the described resource is derived
University of Warwick, Modern Records Center, National Cycle Archive
Is Part Of
A related resource in which the described resource is physically or logically included.
"Herne Hill Velodrome and the Cuca Cocoa Challenge Cup", by Colby Winters, HON 399 Research in London, Spring 2024"
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.
-
https://digitalprojects.uah.edu/files/original/39/538/spc_mraz_019_045.pdf
6481a274b8c14f5e9bf70581a3c92d8a
PDF Text
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13eruf:
Dierer AhnenpaO i(t begulachlel oon ller Reichsflelle fur !iippenforfchung
im 11eichsminiflerium bes Jnnern unb oon oielen Dienflftellen bee 115DAp.
3u111 Dienflgebraud1 empfohlen. fr ifl nur fi.ir Deutrmbliitige beflimmt.
mifdilinge unb frembroffige erholten Eintrogungen in bieran Ahnenpo�
bei ben !itonbHiimtern n i di I begloubigt.
3entrnloerlag ller n5DAp., frnn3 Eher nnchf. 6. m. b. fi., munch en
�Die gefamte Bilbungs- unb Er3iehungsarbeit bes
oolhifd1en Staates muB ihre Aronung bacin finben,
ba0 fie ben naffefinn unb bas Raff egefLihl inftinl.t
unb oer�anbesmiiBig in �et3 unb Gehirn bet ihr
anoertrauten 1ugenb hineinbrennt. Es foll lwin Anabe
unb lwin mabdwn bie Schute oerlaffen, ohne 3ur
le�tcn Ethenntnis uber bie notll)enbigheit unb bas
LOefen bet Blutreinheit gcfuhrt Ll)Otbtrn 3u fein!
Darn it Ll)lt'D 'Die Oornusfe�ung gefd,affcn fUr
bie Erhaltung bet raffenmiiBigen Grun'Dlagen un
feres Oolhstums unb 'Durd, fie wieberum 'Die Sid1e
rung 'Der Oorbebingungen fLir 'Die fpo.tern lrnlturelle
lDeitimrntwid�lung I
2
Stoolsburger hann nur rein, wer Oolhsgenoffe
ifl. Oolhsgenoffe hann nur rein, wer beutrchen
Blutes ifl, ohne Rudl[ichlnahme aufAonfer[ion!
Rein lube hann baher Oolhsgenoffe rein!
(Programm ber n5DAp. punhl 4)
�er Ahnenpa� r�ellt eine Urhunbe im 5inne bes Gerc9es bar;
es tft baher bet re111er Erftellung auf peinlirhfte Genauigheit ber
gemad1ten Angaben unb auf bie unbebingte Rid1tigheit ber nieber
gelegten Ahnenreihen 3ll arhten. Audi errpart fid1 ber PaOinhaber
burd1 forgfi:iltige unb rid1tige Rufftellung Rrbeit, Jeit unb unniitige
Roften, ba bei ber amtlirhen Uberprufung fehler unb Jrrtumer im
eingereirhten RhnenpaO be(timrnt 3utage treten werben. Es fdieue
baher nien_ianb bie geringfugigen Roften fur bie Rnfd1affung bes
unentbehrltd1en Batgebers 0011 Dr. jur. Graf oon 5d1werin ,,Die
Erfte llung bes Rhnenpaffes", ber ausfuhrlid1ere unb erfrhiipfenbere
_
Rnle1tungen geben hann, als bies bei bem hier befchri:inhlen pta9
miiglirh ift.
�ie rorgfi:iltig ausgef[illten Oortlruche nr.1-63, wcld1e auf ben
5etten 8-39 enthalten finb, rowie tiie Ergi:in3ungen auf ben 5eitim
40 rnit �7, erre9en fur b_en Jwech ties beutfrhbllitigen Rbftammungs
_
nad1wetfes antlerwetttge beglaubigte Llrhuntlenabrd1ri�en. 5ie
muffen nber ei113eln burd1 ben 3ufti:inbigen 5tantlesbcamten otler
Rird1enbud1fuhrer beglaubigt untl gcftempelt werben.Der RhnenpaO
n� u0 �er � bet_reffenb_en Beam ten eingeranbt wertlen mit bem Erfurhcn,
btc Btd1!tghe1t tier e1113elnen fur biefen Beamten 3uftonbigen Eintra
gungen 3u uberpriifen unb gegebenen falles Rnberungen unb Hid1tig
ftellungen oor3unehmen unb bann tlie orbnungsmciOig erftellten
Rngaben mit feiner Unterfchrift 3u beglaubigen unb mit bem Dienft
ftempel 3u oerfehen. Jm fnlle einer Birhligftellung finb bie LDorte:
A_uf �rur�b oorgelegt�r �rhuntlen ...3u ftreirhen. Erfolgt jeborh
llte Eu1mrhung ber Emtrage unler Beifugung oon Urhunben (was
bef or:bers empfehlenswert ift, ba in biefem falle bie Bcglaubigung
0011 1ebc111 5tanbesamt burrhgefuhrt werben liann), fo 1oirtl ber
oorher erwi:ihnte Juf09: Rt1f Grunb oorgelegter Llrhunben ...
?eibehalten, unb tiie Beglaubigung erfolgt auf Grunb bee Oorlage
1ener Dohumente.fur t)en erfteren fall, wenn alf o bie Einfenlnmg
o�ne Dohumente erfolgt, ftnb bie Rngaben mit wcid1em Bleifti�
wi:ihrenb im le�tmrn falle tlie Rusfullung mit
ein3ufdmiben,
_
Tmte uor3unehrnen irt. Die Eintri:ige follen ben Haum ber Oorbrudie
3
�11nd1 rTioglimheit nusfiillen, wo 'Dies nid,t tier fall irt. mLiffen bie
leeren Stellen tiurm Strime nusgefiillt wertlen, Ulll fo.trd1lid1en untl
u11bered1tigte11 fpo.tercn Jufii9e11 oor3ubeugen. Ebenf o in be( tier
Beglnubigung an l;nntl eines bereits oorliegentien bcglnubtgten
Ahnenpnffes 3u oerfnhren.
An Gebiihren wertien It. n111 tlid1 e11 1 Erinn IO Reid1 spfe1111ig fiir
jetie ei113elne Beglnubigung erhoben. bei Jehn otier rnehr glcid1 _
3eitige11 Beglnubigungen nicht mehr nls I Reid1 s111nrh, fowe1t rtd1
tltefe nuf tiie Ahnen llr. I- 31 be3iehe11. Ab llr. 32 (LlrnrurgroO
eltern) mun jetiorh LOietier fiir jetie Beglnubigung RITI.-, IO be3nh_lt
wertien. Oorausre9u11g if! bei tiierer Gebiihrenbered111u_ng, tinn ti�e
Angnben rid1 tig untl rnit Tinte gefd,rieben rtnti uni) tlte Beglnub L
_
gung an l;nntl uorgelegter Llrhunl)en erfolgt. Wertien tlagegen tl�e
Eintrngungen oom Stnnbesbeamten uorgenommen, fo betrngen_ tne
Gebi.ihren fiir jetie Beurhunllung, wie fur llie Ausrtellung euier
Originalurhunlle Bin.-,60.Die gennue ferttegung nller anfallenticn
Gebiihren, tiie bei l)er Bemiihung um llen nrifdien Abftnmmu�gs
nnmweis entrtehen honnen, erfolgte mit tien Erlnffen ties Re1d1 s
i1111 enmi1 1irtm u. 26.1.1935 - IB 22/236 II, o. 4.3.1935 1B 3/29, u. 10. I0.1935 - lB 3/305 unti o.5. 4. 1931 - JB 3/403.
nach wt!lcht!n Richtlinit!n wirb bit! Ahnt!ntaft!I t!r[tt!llt?
Die Ahnentafel foll tien llad1 weis tier l)eutfd1e11 otier artoer
wnnl)ten Abnnmmung einer benimmten Perfon erbring1m. Sie geht
l)aher 0011 tier an erfter (unterfter) Stelle ftehenl)en Perfon ('Dern
Ahnentro.ger) nus uni) erftrecht fid1 'Dann iiber 'Die Heihe tier Ahnen
fdrnft 0011 Gefd1led1t 3u Gefd1 ledit, fomit llen Wcg l)es Blutes nuf
weifenti, llas fid1 tiurd1 'Den (auf ller lahrhuntlerte bis nuf ben
ji.ingflen llnd,hornmen tibertragen hat.fiiernus ergib� fi_d1 f ci1 011, tinn
es fid1 bei tier Aufflellung ller Ahnentnfcl nur um letbhd1 e, nlfo um
Blutsahnen hantieln hann. unti l)an 'Daher Alloptio- ol)er 5ticfdtern
ohne weiteres aus3ufmeillen haben.Bei tier Aufftellung ift llarnuf 3u
ndi ten, llaO alle Al111en an rid1tiger Stelle einget:ngen werllen.Da�
wirtl erreicht tiurd1 cine rtnnuolle Jo.hlung, llie bet llr. I, l)em Ahnen
tro.ger, beginnt uni) fid, mit 2 fur 'Den Oater, 3 fur_ tiie mutter,
..
4 untl 5 fiir !lie Gronettern oiiterlid1er-, 6 Ullll t fur tile Gronettern
mi.itterlidmfeits uff. aufbaut.
Bei biefer Be3ifferung erhalten llie Ausgangsperfonen ungenmtet
ihres Gefd1 led1ts ftets !lie Jiffer 1, im weiteren Oerlauf !lie 111 6.1111-
4
lid1e11 Ahnen immer gera!le, llie weiblid1e 11 Ahnen ungera!le Jiffern.
fern er fei barnuf hingewiefen, ban !lie Eltern immer llie !loppelte
Jiffer ihrer Rinller aufweifen; hat !ler Sohn nlfo beifpielsweife bie
Jiffer 4. fo lro.gt !ler Oater bie Juhl 8, tiie fllutter 8 +I= 9. 11am
lliefer formel geht !lie Aufflellung llurd1 alle Gefci1 led1 terfolge11 hin
burch, f O tian man fid1 l)urd, bie Be3ifferung rehr leid,t nuci, in Ulll
fnngreimen Ahnenreihen 3ured1 tftn!le11 un!l einen beftirnmten Ahn mit
(eid1tigheit hernusfud1 en ha1111 . Die en!lgiiltige faffung !lee Ahnen
tafel, !lie je nad1 Um tang oiel Jeit unb Arbeit erforl)ern hann, follte
nur auf Grunl) einwanbfreier Ermittelungen uni) beglaubigter Llr
hunllen uorgenommen wertien. lint 111011 erft feine Ahnentafel in
tier oorerwo.hnten einwnn!lfreien, 0011 Llrhunben untermauerten
Art ernellt, fo finll !lie Llnterlagen fiic 'Den Ahnenpan, !ler eine
wertoolle. fiir nlle Jwerne unti Behorben gultige Llrhun!le bnrftellt,
ohne weiteres gegeben, unll llie Beglnubigung r1ont auf lieinerlei
l;in!lerniffe.
Uber hur3 otier lung wirti bee Ahnenpnn ein PRimtnusweis
c
fur jetien l)eulf i1en Oollisgenoffen wer!len, unb es ift bann 3weifel
los oorteilhaft, bereits Jnhnber tiiefer Llrhunbe 3u fein; aud1 erfpart
es !len mit Arbeit uberho.uften Amlsftellen mnndie !lliihe, wenn
jel)er 0011 fid1 aus fid, !liefer, Ausweis befdrnfft, !ler ihn als ooll
wertigen Oolhsgenoffen im 5inne ties Punhtes 4 bes Programms
ller llSDAp. he11113eid111et.
fur !lie Aufnahme in !lie llSDAp. wir!l !ler beutrrnbllitige Ab
fta111 mungsnad1Lueis bis min!leftens 3u111 lahre 1800 geforllert. Es
hann baher bei fr(ih hciratenben Geld1lediterfolge11 !ler fall ein
treten, ban 3um oollgiiltigen llamweis in ei113elnen Gnien nod, eine
weitcre Geld1 lrdltertolge benotigt wir!l, um l)as Stid1 jahr 1800 JU
iiberbrLirnen.fur biefen fall finll 3ur Erg6.n3ung llie unnumerierten
Oor!lrurhe auf 5eite 40 mil 47 oorgefehen, tlie aud1 fiir llie weitere
Erforfdiung bes llamensftnmmbaumes, b. h. ller oo.terlidi en (inie,
oerwenllet wecllen honnen. Die llumerierung ift hierbei felbn
!lurd1 3ufiihren.
Der Ahnenpnn ha1111 fur Angehorige bei!ler Gefd1lemter aufge
ftellt werl)en, gilt aber immer nur fiir e i n e Perfon, im Gegenfag
3um ,, Ahnenbuch !ler !leutfdien f nmilie'', llas als pr6.ci1tiges familien
bolmment Auf3eid111unge11 fiir !lie gefamte familie aufnehmen hann
un!l fomit gleid1 Jeitig 'Den Abflnmmu11gsnnd1 weis fur Ehemann
unl) -frau uni) !leren Rin!ler erbringt.
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ge�orben am
............
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t
................ ]
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geboren am .. -9. J-/f.......(.f..!l__.J.. in �m?7.1��h:.��
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.
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Behenntnis: .....?.'!...A.t:1-:M.... Tauflag :..f: ,;-�...... /���.
e
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6
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�
b. Pfarramt: .
.
.
!auf-Reg.-llr.
Beurh. b. 5ta
in���-
beurh. b. Stanbesamt - Pfarraml �.p, Reg.-llr...............
fiir ntb•nPthtnbtn
Eintrog ifl G,gloublgung
nic!,t •rforbtrlicl,.
"''fh'r��,., .��········ ·· ;�1
t-?-t........
L,-H.5:...
f...£....��:!:_-?._. in �r?.".�q:�,t,���U.�.....
ge�orben am ....
beurh. b. 5tanbesamt- Pfarramt�4..4.1.(�eg.-11r...........
fiir n,b,nPeh,nben
Eintrag lP B,gloubigung
ni<ht trforborllcl,.
4/5
Beru[: ��-44.� ..... ······;
ehennlnis:
.l.
unb ller ..... ....f-,t:;1_�.....
!Jl'£/./!.4.-!.:.... . . ..
/J.�./'.tP r.. . . .
geborene .'..
er[olgte am
. .. . .... ·�··
Bellenntnis: 7?............,........ ..
in...5a.,t.t.4_��.At.....
beurh. b."'hnh,a1Mt
p[arram�c.-&�t,;?!.7 Reg.-llr... ..........
(mutter oon 2)
5
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(mutter oon '.J)
d.f:.�.fY.?..... ...... .............................
geboren am ...
in
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unb bee (11 )'-.....�
Behenntnis: ..
?....
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6eb.-Reg.-11r. ......... ........
b. p[arramt:�a,��..?Z?<f�
!au[-Reg.-llr. .. .... .
genorben am ....... ................... .. . in ..........................................
.
beurh. b. 5tanbesamt - Pfarramt ............................. Reg.-llr........
GroPeltern oiihrlich
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31',J:..(',t._<!_..f_.. in ?J&�!!Y((e-t.�
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Belienntms .. ........................................ !au[tag
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Beurh. b. 5tanbesamt: ...................·-··········· Geb.-Reg.-llr...................
b. Pfarraml: ...�4.1.4.........
file n,b,nftrh,nbtn
€mtrag ijl B•glaubigung
nidit ,rfori)rrhch.
......
tauf-Reg.-llr.J.Mf.. ..
genorben am .................................. in .........................................
beurh. b. 5tanbesamt- Pfarramt .......................... Reg.-llr . ..........
6rohltern miitterlich
fur ntb,np,h,nbon
finlrag ijl B,gto.ubigung
nic!,t tr(ocb,rlic!,,
II
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··-·
Beurh. b. 5tanbesamt:
b. Pfarramt�4.44�-t.?IU:
geflorben am
/4....
Geb.-Reg.-nr.
in
Geburtsname:
Docnamen: .. .
geboren am
�a�a..n,;n
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Tauf-Reg.-nr... \- A
geftorben am
beurh. b. Stnnbesnml - Dfarraml
in
Reg.-nr.
in
:
0
Reg.-nr.
bcurh. b. 5tanl)esnmt - Dfarramt
6eburtsname:
fiic neb,nn,h,nb,n
Einlrag 1n B,gloubigung
nicht ,cforborluh.
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·
·
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unb ller (23) -r....;>;>a:.n,?.L./!.kl od. IJcAc'c!-'7
nls Tochter bes (22)
ff.,,n.L{� ·····
·
Geb.-Reg.-nr.
ge(torben am
(ITiutter oon 5)
�
v i
� J!-t1 f/.
Beurh. b. 5tanbcsamt:
12
file n,b,nn,h,nb,n
Eintrag ,n 8,9laubi9un9
nid,I erfacbtclich.
./Jt�/..4.. 7.?.d. �.,(-!'!.�.
'7! /&2.M
Tauflag: J. !:!ff /�,?_!':_
urlb ber (19) � (I"
Behennlnis:
b. Dfnrramt: Ja.LL.6�.n.z/2rnuf-Reg.-nr.
Reg.-nr. ·········-
beurh. b. 5tanbesamt- Dfarramt
(ITiuttor uon 4)
'5"
Touf-Rcg.-nr.
Geb.-Reg.-nr.
Beurh. b. 51anbesamt:
Behennlnis: -?.'7
./eaLA
r::ftag: /��-/'.
Geb.-Reg.-nr........ ........
Beurh. b. 5tanbesamt:
b. Pfarramt: ....5a.L..z �.LC4 Tauf-Reg.-nr.
n
fU.r ntbrn�thtnbtn
ifl Brglaulllgung
ni<hl •rforb,ctich.
Ei.ntrog
UrgroPaltern
geflorben am
beurh. b. 5tanllesamt - Pfnrramt
oiiterlich
/.,P/J
�(
in
Heg.-nr.
fUr ntbtnflrh,nben
Eintrog ill Btgloubigw,g
nlchl ,rfocbtctlch.
13
�(Dater oon 6)
�
12
4./
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familiennarm: ..
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als Sohn ll s (24� ��;,!?� �e>d,�n.,n
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.
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unll ller ( 29 )
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b
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urh. b. 5tanllesnmt - Pfarramt.............................. lleg.-llr........... .
fUr neben(hhenben
Eintrag iA 8e9toubi9un9
nidit ,rfocbertich.
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lleurh. b. 5tnnllesnmt: ...... .............. ........ 6e b.-Reg.-11r. ....... .. ...
.. in ..... . ............... ..................
.........................................
als 5ohn lles (28) ...... ... ....
e e
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14 /
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ge{torben am .............. .
beurl;. b. 5tanllesnmt- Pfarrnmt ........
lleg.-llr.............
filr nl"benftehenben
Eintrag iA Begtoubigung
nicht erforberlich.
I 12/13
Die Ehefdiliepung bu
.... .>..A<���.'4?e.t-?.?7· .....��.�.......... �.
:7':'...
Beruf:
B ehenntnis: ...
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unb ller .........
e
erfolgte am ....
?;£..-:(/.:.�( in .��/q_..q.17.,.
beurh. b. Stu11bcsa11<+-
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13
15 /
(mutter oon 1)
6eburtsname: ..............
Oornamen: .............
geboren an1
als Iochter
Behenntnis: ...
b
. Pfarramt:
6eb.-Reg.-llr. .........
.in ........................... ..
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14
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�dCJJ"'/a. e1.erauf-Re9.-llr. .........
geftorben am .................
b
tleuril. b. 5
17..-?:?.n. q_. ............ ;�............................
.3. 17, ✓c/'/t.G m. ..........................................
"7�e.L.A .
bes (30) .. .. �,1.g�----�.,,n..�.
/ -..... ................
............
unll ber ( 31)
Beurh. b. 5tanllesamt: ....... ............ ........
�A�. . . . . . . . . . .. . . . . . . . .
fur nebenAehenben
Eintrog i� Segloubigung
nicht erfocberlich.
UrgroPeltern
J.. .tt....
geftor ben am ...................... .......... in ........... ............... ...............
beurh. b. 5tan�esnmt - Pfarramt
miitterlidt
....... Reg.-llr...........
fUr n�benflehcmben
Eintcog Be9toubigun9
nicht rrforbedidi .
,n
15
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(Oater uon S)
·········· ........... . .. .............
familienname:
Oornamen:
in ...
als Sohn bes (32)
..
,:
9
l
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U"IIC
...
.. .
........ ..
Behenntnis:
..
Reg.-nr.
bcurl1. b. Stanbesaml - p farramt
i5]'
·"
fur n,b,nft,h,nb,n
E1nlrag ift Btglaubigung
nicht erforbetlich.
in
gcflorbcn am
i�
a: �
Beurh. b. Stanbesamt:
6eb.-Reg.-nr.
b. Pfarramt:
Tauf-Reg.-nr.
geflorben am
fiic neb,n(l,h,nbtn
Eintrog ijl Btglaub,gun�
nuht trforbtrll<h.
in
Reg.-llr.
beurh. b. Stanbesamt - Pfarramt
1 18119
Behenntnis:
Beruf:
Behenntnis: .....
Beruf:
unb ber
unb bcr
crfolgte am
in
erfolgte am
I
(ITiutter uon S)
in
Reg.-llc.
beuch. b. Stanbesamt - pfacramt
Reg.-llr....
bcurh. b. Stanbesamt - Pfarraml
Behenntnis:
geborene
Behenntnis:
geborcne
19
(mutter uon 9)
17
6eburtsname:
6eburlsname: ......
Oomamen:
Oomamen:
·".,
... .... in
9
als Toditer bes (34)
Bchenntnis:
6eb.-Reg.-llr.
b. Pforramt:
Tauf-Reg.-llr.
beurh. b. !itanbesaml - Pfarramt
in
als Tomtee bes (38)
Behennlnis:
Tauftag:
Beurh. b. Stanbesamt:
geflorben am
gebocen am
unb ber (39)
unb ber (35) ... .. .
16
.. Tauftag:
I 16/17
Die Ehermlie�ung bes
geboren am
in
geboren am
QC
.: 3
Tauf-Reg.-nr.
Oornamen:
unb bee (37)
;'!:�
6eb.-Reg.-nr.
Beurh. b. Stanbesamt:
fnmilienname:
]5
"'"'&
Tauftag:
18
(Oater oon 9)
nls Sohn bes (36) . •... .... ... ....
...;
Behcnntnis:
b. Pfarramt:
j
§
................. 5-eE.. -6�
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...
,:
...
unb bee r 33 i
[ 1
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..
.......
geboren am
16
in
Rcg.-llr.
'fW' nrb,n(lthrnbrn
Einlrag ift 8,glaubigung
mdll tr(orbtclidl.
Tauftag:
6eurh. b. Stanbesamt: ... .... .... ... ... .
6eb.-Reg.-llr.
b. Pfarraml:
Tauf-Reg.-llr.
geflocben am
beurh. b. !itanbesamt - Pfacramt
oiitorlich (1)
in
Reg.-nr.
TUC nrb,n(tthtnbtn
(inlrag ijl B,gtoub19ung
n,dlt •rforbtrlid!.
11
�20
(Doter Don 10)
fomiliennome:
fomiliennome:.
Oornamen:
Oornamen:
geboren am.
geboren am
........ .... . ...... in .... ................ .................. ..
unb ber (45)
unb ber(41)
:J
...... Tauftag:
Behenntnis: ..
6eb.-Reg.-nr.
Beurh. b. 5tanbesamt:
I
b. Pfarramt: .................. .................. ..... Tauf-Reg.-nr. .
fUr neben�ehenbtn
fu,trag in Begloubigung
nit:hl tcforberlich.
.. ............. in
Reg.-nr. .
beurh. b. 5tanbesomt - Pforramt
erfolgte am
6eb.-Reg.-nr.
b. Pfarromt:
Tauf-Reg.-nr.
in
Reg.-nr. ..........
\
... Behenntnis:
unb ber
geborene
.. ........ ........... Behenntnis: .................... ... .
.... .......... in ...
·""'
Reg.-nr.
21
Geburtsnome:
�]
E •�
.
�!
f�
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.0 •
Oomamen:
geboren am ... . ...... ..................... .. in ............. .....................
1,
,
.................... .. ,
...........
erfolgte am
.. Behenntnis:
...... in
beurh. b. Stanbesomt - Pfarramt .
Reg.-nr............
23
(ffiutter con 11)
Geburtsnome:
Oornomen:
in
geboren om
als Tochter bes (46)
alsTochter !)es (42) .. ... ... .............. ........ .................... ........
unb ber (47)
·······••··•·····"·""""""
Behenntnis:....
... .......... Tauftag: .......... .... ..
........ ... Tauftog: .. ..... .... .... ......
Beurh. b. 5tanbesomt: ....... ... ....... .
6eb.-Reg.-llr.
Beurh. b. 5tonbesamt:
Geb.-Reg.-nr.
b. Pfarramt:
Tauf-Reg.-nr.
b. Pforramt:
Touf-Reg.-llr...........
geflorben am ......
beurh. b. 5tonbesamt - Pforramt
18
fur ntbenn,h,nben
finlrog ijl B,gloubigung
nidll erforbtrfoh.
22/23
Beruf:
(mutter uon 10)
Behenntnis:.
Beurh. b. 5tanbesomt:
Die Ehef<hlie�ung be1
.......... .... ...... ..... Behenntnis:.
beurh. b. 5tanbesamt - Pfarramt
unbber (43).
Tauftog:
beurh. b. 5tanbesomt - pfarramt.
unb ber
geborene
Behenntnis:
geflorben am
I 20121
Beruf: .
in.
als 5ohn bes (44)
als 5ohn bes (40)
geflorben om ..
22
(Oater Don 11)
in
Reg.-nr.
liir nebrnflehtnb,n
fint,09 ijl Begloubigung
ntcht erforbtrlich.
Ur-Urgro�eltern
111
geflorben om
beurh. b. 5tonbesamt - Pforromt
oiiterlirh
(2)
in
Reg.-nr. ...
fur nebenn,h,nben
Einlrog ijl Beglaubigung
ni<ht ,rjorbe<li<h
19
�24
(Oater oon 12)
familiennan,e: ............... ...................... ...................... .
fnmilienname:...................... ....................................................................
�a
Oornamen: ..................
Oornnmen:.......................
in ............ ..................
geboren am..................................
26
(Oater uan 1:J)
geboren am ..................... .
in ..........................................
als Sohn bes (48) .. ..................... . .....................................
nls Sohn bes ( 52) .................................................................. .
unlJ ber (49) .. -.
unlJber(53) ...............
13el1enntnis: .... ................................... Tauftag: ...................................
Behenntnis:...... .
Beurh. b. 5tanbesnmt: .. ...................•........ 6eb.-Reg.-nr. .......•.......
Beur�. b. 5tnnlJesamt:................................. 6eb.-11eg.-nr...
b. Pfnrraml: . ............................................... Tauf-Reg.-nr. ..........
geflorben am
............................... . in . ............................
Reg.-nr............ .
beurh. b. 51anlJesaml- Pfarraml
b. Pfarramt: .
fi.ir neben(tthenben
Eintcng i� B,glnubigung
nldlt erfori)erlich.
24/25
Die Ehefchlie�ung be11
........ Tauftng: . ................................
Tauf-Reg.-nr. .
geflorben nm ............. ..................... in
beurh. b. Stnnbesaml - Pfnrromt
I 26121
Die Ehefdllie�ung bes
13eruf:. .................. .... ........ ......... .. Belienntnis: ............... .
Bemf: ............................................. Behenntnis:
unb ?Jee . .......... ...............•.. -----------·················· ...................................
unb ber . ............
geborene ................................... ....... Behenntnis: ...
geborene .......
erfolgte om ....................... ........ in . .. ........ . .....
erfolgte nm ......
beurh. b. 5lanlJesnmt - Pfarraml.. .... ................... . Reg.. nr.
beurli. b. Stnnbesoml - Pforrnmt .
I
(mutter oan 12)
Reg.-nr............
25
"'
. .. ...... ,. Behennlnis:....
in .
Reg.-nr.
27
(mutter oan 13)
0
0
G�buctsname: .. ..................... ............................
6eburtsname: ..
Oornomen: .................... .
Oornamen: ....... .
·"
geboren nm. ........................ ........ ... in ............. .................................. !l
,0
geboren om .
. ................. .. in ........
als Tod1ter bes (50)
als Tod1IH bes ( 54)
unlJ ller (51} , . ......... ....................
unll ller (55) .................
Behenntnis: .......................... ....... Tauftog:
Behenntnis: .... ....................... .......... Tauflag:
Beurk. b. 5tanllesamt:...................... ........ 6eb.-Reg.-nr. .
geflocben nm .....
.. in ..
beurk. b. 5tanllesnmt- Pfncramt....
20
Beur�. b. 5tanbesaml:....... ......................... 6eb.-11eg.-nr. ........... .....
Tauf-Reg.-nr.........
b. Pfarromt: .....
fiir nebenflehtoben
Eintcag i/l 8,gtnubigung
nidit ('l"forberlidl.
11eg.-nr........... .
b. Pfarromt: ....
fiir ncbcnjlehenb('n
Eintrag l� BeglaLtbigung
nicht erforbedich.
Ur-Urgralleltern
geflorbcn om ...
Tauf-Reg.-nr. .
......... in ................. ......................... .
beurh, b. 5tonllesamt - Pfacramt .................... .
mlitterlich (1)
Reg.-nr.....
fiic neben�ehenben
Eintrng i� o,glouuigung
nidit ,c/ocb,rlidi.
21
�.,1 ::::::,,
28
(Oater oon 14)
familiennamc:......
familiennnme:
§
,5
Oornamen: . ... ...................
Oornomen : .... ................. .
geboren nm ...........
in ....
goboren nm.
als Sohn bes (5 6)
als Sohn bes ( 60) .
unb ber (S1)
unl> ber (61)
Behenntnis: ..
30
(Doter uon 15)
0
0
in.
Behenntnis: ................... ...
. .. ..... Tauftng: .......
Tauftog: ......... .....
Bcurh. b. 5tonl>esnmt: ..
6eb. .Rcg.-Or. ...
Beurh. b. 5tanl>esnmt:
6eb.-Reg .. llr.
b. Pfarram t:
Touf-Reg.-Or ..
b. Pfarramt: ... ....
Tauf-Reg .• nr. ..
geflorben am .
. in .
beurh. b. 5tanbesamt- Pfnrrnmt.
Reg.-Or.....
1
Die fhefchlie�ung bee
Bemf:.........
Hir neben�eh"nben
Eintrog ill 8egloubigung
nidit "rfor!lerlich.
beurh. b. 5tanl>esamt- Pfarrnmt .
Behenntnis:...........................
lleruf:..... ............... ....... ... .
Behenntnis: ....
unb l>er ............ ................
geborene ...................................... .......... Behenntnis : ...
... Behenntnis:.
erfolgle om
beurh. b. 5tnnbesnmt - Pfarrnmt ........................
Reg..lJr.
in
beurh. b. 5tnnbesamt - Pfnrrnmt.
29
(ffiuttu oon 14)
Reg.-llr......
31
(ITiutter oon 15)
6eburtsname: .......
6eburtsname: .............. ..
Oornnmen:.........
Oornnmen:
geboren om ..... .......... .... ...
. in ......................
nls '[od1ter bes (58)..
ols Iod1ler bes ( 62).
unb l>er (59) ..
unb ber ( 63) ......................
Behenntnis:
Reg.• n,......... ..
Touftng:.
... in .....
llehennlnis:........................................ Inuftng :.................. ......... ......... .
Beurh. b. 5tnnbesnmt:.
6eb.• Reg..Jlr.
Beurh. b. 5tanbesamt:..................................
6eb .• Rcg.• nr. ..........
b. Pfnrrnmt:
Touf-Heg.• nr.
b. Pfnrromt: ........... ................ .
Tauf.Reg.-nr ..................
geflorben nm .....................
beurh. b. 5tnnl>esamt- Pfnrrnmt .
22
fiir nebtnneheri�en
Einlcog ifl O"glaubigung
nicht Hforberlich.
30/31
erfolgte om....... . ...................... in
geboren om ........
in..
28129
unl> ber
geborcne.
geflorben am..
in ....... .................................
....... Heg.-nr. ......
filr nebenf'tehenben
Eintro9 i� Be9loubigung
nicht ecfortlerlif:h.
Ur-Urgro�eltern
geflorbcn am .... .............................. in............................................
beurh. b. 5tanbesamt- Pfarramt.. ......
miitterlich (2}
Reg.-Or.......
fi1r nebtnnehtnben
Eintrng ifl Bt'glaubigung
ntcht rrforb"ctich.
23
\
�I
(Oater uon 16)
32
34
(Oater uon 11)
fnmilienname:.
famitienname:................... .
""
Oornamen: ...
Oornamen: .......................... ................ ...............
geboren am ..................... .......... ..... in ... .............
geboren am ....... ... .
als Sohn bes (64 ) ......
als Sohn bes ( 6S J . .
13ehennlnis: ..
. ... Tau flag: .............. ....... .
13eurh. b. 5tnnbesamt: ..
Geb.-Reg.-llr.
b. Pfarramt:
Iauf-Reg.-llr.
geflorben am ..
J
·�
unb ber ( 65)
t:
9
�
Jii.r neb,mf1ehenben
Eintrog 8,gloubigung
nicht ,rfocbeclich.
;n
beurh. b. 5tanbesaml - Pfarraml ............................. Reg.-llr ...
lforuf : .... .
erfolgte am ................ .
in ......................................... ......
beurh. b. 5tanbesnml - Pfarrnml
geborene ...
.. .
.
.
� ... . .............. ...... .
Reg.-llr...
1
Ji.ir nrbenftehenben
Eintrog
6egloubigung
nicht erforberlith.
;n
34/35
............................ Behennlnis:....................... .
33
Geburtsname: .................... ........................................... ............. .
Oornamen: ........
als Torhter bes (66)
�
Q
Q
,g
"'cl
I
I
t t
ii
...•� -6
...�
• C
.s "E
•
I,;) iii:
·g
I{�·.... i
9
1!
cc �
-6
unb ber(67)
Tauftag: ............... ....................
6eb,-Reg.-llr •...........
b. Pfarramt: ........................................... Tauf-Reg.-llr . ..................
geflorben am ................................. .in ............... .
beurh. b. 5tanbesnml- Pfarramt.... ......................... Reg.-llr ..........
Reg.-llr.
beurh. b. 5tanbe!inml - Pfarramt
,0
....... in ..........................................
............................... Behennlnis :... .......................
erfolgte am ............................... in ........................................
Reg.-llr..........
(mutter uon 16)
24
.
unb ber ....
13el1enntnis: ..........................
Beurh. b. 5tanbesamt:
6eb.-t1eg.-llr.
Die Ehefd1Ue�ung be,
..... 13ehenntnis:
geborene ....................
Behenntnis: ............................ .
13eurh. b. 5tanbesamt: ........ ................ ...
beurh. b. 5tanbesamt- Pfarramt.
unb ber .
geboren am
......... Iauftag:
13ehennlnis: ..............
ge florben am . .
1 3 2;33
13eruf:.
unb ber ( 69) ........
b. Pfarramt: . ............... ........., ............... Tauf-Reg.-llr. ...................
.... ..... in..
Die Ehefchlie8ung bu
.. . in ...........................................
,0 C
35
( mutter uon 11)
l
6eburtsnnme: .. ..................... .. .............. , ................................. .
�
als Tod1ter bes (10 ).... ...................................................... .
Oornnmen: ........ .......................................................................................
geboren nm ............. ...................... . in .......................................... .
unb ber ( 7l ) ...................................................................
13ehenntnis: ..... ............................. Tau flag; ..................... ..
-6=i
Beurh. b. 5tanbesaml: .....................
6cb.-Reg.-Jlr.. .
A.!:
b. Pfarraml: ...
Tauf-Reg.-llr .................
-� a,
fU.r nebenflrhtnben
fintrog i� 8egloubigung
nic!,t ,rfocbeclicl,.
Ur-Ur-Urgro8eltern
geflorben am ..........
. ........... in ..........
belirh. b. 5tanbcsaml - Pfarrnmt .......................... Reg.-llr•..
uiiterllch (I)
fUr nt"benflflhenben
Eintrog i� Begloubigung
nichl ec'focberlich.
25
�36
(Oater uon 18)
familienname:
......... ..
..........
1
.. ........... .. ,.
Dornamen:
...................
geboren am
in ... ...... ......................
a(s 5ohn bes ( 72)
. . ..
... .. ..
t
9
t_j
"
�
9
..
�.: t
.:!§
,,g'-f 9
-6"'
6eb.•Reg.-nr.
cc ::
5]'
Tauf-Reg.-nr . .
ge�orben am ........ .
in
beurh. b. 5tanbesamt - Pfarramt
!i
;; i;
§ -6
"'�
Reg .• nr. ........
(Oater oon 19)
familienname: ............. ..
Dorn amen: .. .. .....
.... ..... ..... ··········
I
�
.;;
i"
Tllc n,benl'tthrnb,n
Einlrag Brglaubigw,g
n1d,l •rforb,dcd,.
0
:g
in
als 5ohn bes (?6)
,, .....................
9
g'j
s1
'°'"a.
"w
•-"
"'c
:[
t
9
t �
irE.
.,,• -6"
.�.,,"
,0 •
.§ �
"'ii<
:=:�
wC
Beurh. b. 5tanllesamt:.
b. Pfarramt: .
Tau f-Reg.-r r.
C
:§
i
t
�,, 9
Tauftag:
I��
=-;s]'
in
Reg.-nr. . .........
beurh. b. 5tanl>esamt - Pfarramt
�
"'
... ...
6eb.. Reg .. nr...
ge�orben am
Q
Q
�
geboren am
llellennlnis: ...
"'
]"'
..
I 38/39
1 36/37
Die Ehefchlie�ung be•
38
unl> l>er (17)
,o C
... Tauftag;
b. Pfarramt:
ij
�l
.... 1
"w
Beurll. b. 5tanbesamt:
1
1i
·"
,0
unb ber f13 )
Behennlnis:
�
a:
-�
"'
file ntbrn�thtnben
fintrng ill Beglnubigung
nicht erfocberlich.
································· - ················ ······················"'····················
Beruf;
Beruf · .............................................. Behenntnis :.......................
Bellenntnis:........ . . .. .......••. .
unb bH
unb bee ........................... ................ ..
geborene .......... .......................
erfolgte am
geborene . ............. ................
Bellenntnis:. ....... ....... .. ..
erfolgte am ..................................... in .................................... ...........
. ....... in
beurh. b. 51anbesamt- Pfarramt ..........
I
6eburtsname: ..... .
37
Reg.-nr ...........
beurh. b. 5tanbesamt - Dfarramt ..
Reg.-nr..... ....
(ffiutter oon 18)
"'
Q
D
Oornamen :.......... .
geboren am
als !ochler bes ( i'4)
in
als !ochter bes (78)
unl> ber (15) ..... .. . ................
unll lier (19)
... Tauftag;
Behenntnis:
Iauftag:
lleurll. b. 5tanbesamt: ......... ................... 6eb.-Reg.-nr.
Beurh. b. 5tanllesamt:
6eb.-Reg.-nr.
b. Pfarraml: .... ............. ..
b. Pfarramt:
Tauf-Reg.-nr......
Tauf-Reg.-nr.
ge�orben am ................................ ... in ..................
beurl1. b. 5tanbesamt - Pfarramt................
76
39
6eburtsname: ...................
geboren am.....
. ........... .............. in
l
(mutter uon 19)
Oornamen: ... . .................................................... ......... ..... ..
Bellenntnis : .....
llellenntnis: .............. ... ....
Reg.. nr.
fiit n,b,n"•hrnb,n
Einlrag iJl Beglaubigw,g
nid,t rrforbrrlich.
Ur-Ur-Urgro�eltern
gc�orben am
beurh. b. 5tanbesamt- Pfarramt
uiiterlich (2)
in
Reg.-nr.
fiit n,b,np,h,nbtn
Einlcag ij\ Begloubigw,g
nuht ecfo,btrluh.
77
�40
(Oater oon 20)
I
(Datu oon 21)
familienname:
familienname: .............................................................. ..
Oornamen:
Oornamen:
geboren am
in
......... ................
.. in
geboren am ... .. .. ....... .............
nls Sohn bes(84) ....... .............. . ... ........ -·
unbl>er(Sl)
unb lier (85)
............... ... - •·
13eurh. b. 5tnnbesamt:
6eb.-Reg.-Or ...................
13eurlt. b. 5tanbesaml:....................
6eb.-Reg.-Or................ ..
b. Pfarramt:.
Tauf-Reg.-Or . .
b. Pfarramt: .......
Tauf-Reg.-Or. .. .. .. ...
geflorben am
in
beurh. b. 5tanbesamt - Pfarraml
Reg.-nr. ..........
fUr ntbrnllfhrnbtn
Einlrog ii\ Brglaubigung
nidll rcforbrclich.
1 40141
Die EhefchlieOung be•
Behennlnis:
................................... . .... ···········•·
Behenntnis:
13eruf: ..
unb ber
geborene
Beltenntnis:
erfolgte am
.. 13ehenntnis:
geborene
in
in .... .. ... ....
erfolgte am
beurh. b. 5tanbesaml - Pfarramt
beurh. b. 5tan1>esaml - Pfarraml
Reg.-Or. ............
41
(mutter oon 20)
Reg.-Or.
43
(ffiuthr oon 21)
6eburtsname:
6eburtsname:
Oornamen: ...:......
Oornamen:
in
.0
C
e
\0
als tochter bes (86)
unb ber (83)
unb bet (87)
... tauftag:
13ehenntnis: ...
·�
in
geboten am . .. .
a!s tod1ter bes(82)
Behennlnis:
1 42143
Die EhefchlieOung be•
unb ber
geboren am
Reg.-Or.
beurh. b. 5tanbesamt - Pfarraml
········•""''''''''
fiir nrbrnfhhtnbtn
Eiotrag i/t Brglaubigung
nidll rrforbrrlidl.
in
geflorben nm
········-··
Beruf:
.... Tauftag: ...
Beurlt. b. 5tanl>esamt:.
6eb.-Reg.-Or.
13eur11. b. 5tanbesamt:
6eb.-Reg.-Or ..............••
b. Pfarramt:
fouf-Reg.-Or.
b. Pfarraml:
Tauf-Reg.-Or. ...........
geflorben am .................
beurh. b. 5tanbesamt - Pfarramt
21
'
· ······ ······· ·····" ... ·············
l3ekenntnis: ..................................... tauftag:
Tauftng:
•··•· ······
. ... .... ........ ...................
als 5ohn bes(80)
13ekenntnis: .... ..
42
in .................... . ....................
.............. Reg.-Or.
'fUr ntbrnflrh,nbtn
Eiolrog ii\ Brglaubig:Jng
n1<hl rrfor�rrlich.
Ur-Ur-UrgtoOeltetn
geflorben am ....................... .
beurh. b. 5tanllesaml - Pfatraml
oiitctlich (3)
in
Reg.-Or.
fur nrbtnnehrnb,n
Eintrag •� Orgloubigung
ni.lhl uforbc-rlidl.
29
�44
(Doter uon 22)
familiennnme: ......................
familicnnamc:
Dorn amen:
Oornamcn:
geboren am
als !iohn bes (92)
al5 !iohn bes (SS I
unl> l>cr (93)
unll ber (89)
Behenntnis: .................. ............... Tauftag: .
... Iauftag:.....
Beurh. b. !ilanbesnmt:
Geb.-Reg.. nr. ............
b. Pfarramt: ...
Iauf-Rcg.-llr. ...... .
geflorben nm
............. ........... ..... .. in .........................
beurh. b. !itnnlle5nmt - p fnrrarnt ............. . .....
Bcruf:
Rcg.-llr ... .......
I
fut ntbtr,n,hrnb,n
Eintroy ijl B,gtou�igw,g
nid1t Hforberlii:h,
erfolgte am
Beurh. b. !itanllesamt: ............... .
6eb.-Reg.-flr.
b. Pfarramt: ...............
Tauf-Reg.-llr.
beurh. b. !itanbesnmt - Pf arramt..
Reg.-nr.......... .
I 4&/47
unl> l>er
erfolgte am.....
........... ... . ......... in .. ...................."........
I
Gcburt5name:
geboren am
9
Oornamen:
alsTorhter llcs (94)
unl> l>cr (91)
unll ber (95)
Behennlnis:
Tauftag: . ...
in
geboren am
als Iod1ler bes (90 )
Behenntnis:
47
6eburtsname: ....
-e
'9
in
lleg ..nr.............
(mutter oon 23)
45
"a
Oornamen:
in
beurll. b. 5tanbesamt - Pfarramt
Reg.-llr.........
(mutter uon 22)
... Behennlnis:
geborene
............. . .. .... .......... Behenntnis: .... .................
beurh. b. !itanbe5amt - Pfarramt
.... Tauftng:
Beurh. b. !ilnnbcsnmt: ...... .. .. ....
Geb.-Rcg.-llr.
Beurh. b. !ilanbcsamt:
Geb.-Reg.•llr ...................
b. Pfarromt:
Tauf-Reg.• nr.
b. Pfarramt :
Tauf-Reg.-llr.
1
gcflorben am.................................. in
beurh. b. !itanllcsamt - Pfarramt.. ............
30
file ntb•nn,h,nbtn
Eint,ag ill Btgloubigung
nicht ,rfo,b,rllch.
l3ehenntnis:
Beruf:.
l3chenntnis :...................... .
a,
"
"'
in
geflorben am
44,45
unb l>er
geborene
in
geboren am
in
Behenntnis:
46
(Doter oon 23)
Reg.-llr.
fUc neben�thtnb,n
Eintrag i[l 8l'9laubi9Lm9
nicht ,rforbecthh.
Ur-Ur-UrgroBeltern
ge�orben am ...
beurh. b. !itanl>esaml - Ptarramt .
oiiterlich (4)
in ................... .
Beg.-llr........... .
liit nebtnn,h,nbtn
E!nlrog ijl B,gloublgung
nicht «forbocl!ch.
31
�48
(Oater uon 24)
50
(Oater oon 25)
familienna1m: ......... .
familienname:......
Oornamen :.. .....................
in ............ .
geboren am ................... .
als Sohn bes ( 96)
Dom amen: ..
"a
geboren am ...................................... in ...-....
"§
als Sohn bes ( I O:J)
unll ller ( 91 J
unllller(IOI) ...
Behennlnis: .............
.............. Iauftag :............. .................... .
13ehenntnis: .............
...... Tauflag:
13eurh. b. Stanbesamt: ............... .
Geb.-fleg.-llr. ... ............
Beuth. b. 5tanbesumt:
6eb.-11cg.-llr.
b. Pfarramt: ................................
Tauf-Reg.-llr.... .
b. Pfatramt: ..
Tauf-Reg.-llr. ..
.................... ............. in
Rcg.-llr............
beurh. b. Stanbesamt - Pfarramt
filr ni?benflehenben
Eintcog in Begloubigung
nlcht erfocbedid'I.
I 48/49
Die Ehafchlia�ung Iles
bcuth. b. 5tanllesamt - Pfarramt ...
Bmif:
unll ller .....
unb ber .
geborene .....
......................... Behennlnis:...........................
erfolgte am
........•.......... in........................................................
beurh. b. Stanbesarnt - Pfarramt... ............... .
............................. Behenntnis:.
Belw111tnis: .................
erfolgte am .................................... in
beurh. b. 5tanbesamt - Pfarramt ...
49
Rcg.-llr.............
51
(mutter oon 25)
Geburtsname: .. .....................................
Geburtsname:
Oornamen: ......... ...........
Oornamen: ..
in . .......................................
geboren am
1 50151
geborenc ...................
Reg.-llr.
(mutter uon 24)
Reg.-llr .......
Die Ehefchlie�ung Iles
Beruf:.................... ...... .................. Bel,ennlnis:...........................
"a
geboren am ...................... .
als Tod1ter bes ( 98)
als Tod1tcr bes ( 102) ....
unll bcr ( 99 ) ......................... .......................................
unll ber ( 103)
13ehenntnis:
Bel;enntnis: .........
............... Iauftag: ..................
in..
·9
. ............. Iauftag:.
Beuth. b. 5tanbesamt:
Geb.-Reg.-llr. ..... .........
Geurh. b. Stanbesamt: .
Geb.-Reg.-llr. ..
b. Pfatramt:
Iauf-Reg.-llr. ........ ..
b. Pforramt: ....... ..................•.
Tauf-Beg.-llr. ..... .
ge[torben am .. .............................. in
beurh. b. 5tanllesaml - Pfarraml
Reg.-llr ...... .
fUt nebenftehenb1m
Eintrog 8,gloubigung
nidlt erfod)Hlich.
tn
geflorben am ... .......... ......................... in
'fUr nebenfhhenb,m
Einlcog i/l Begloubigung
nicht er/orb"lich.
Ur-Ur-Urgro�eltern
gefro rben am .....
beurh. b. Stanbesamt - Pfarramt ..
miitterlich (I)
in ............
Reg.-llr.
fUr neben�ehenben
Eintrog 8egloubigung
nicht erforberlich,
tn
33
�52
(Oater uon 26)
familienname: . ...............
faniiliennnme: ..
0ocnamen: ........
0ornamen: ......
�
d
geboren am .
............... in ............... ... . .....................
geboren am ..................
54
(Oater uon 21)
. in ...... .
als Sohn l>es (10:J.)
nls Sohn bes ( I 03)
unl> ber (105) .. ....... .
unl> ber ( 109)
Behennlnis :.. .................................... Tauftag: ................... .
Behenntnis: .......... ........................ Tauftag: .............. .....................
Geb.-Reg.-nr .................
Beurh. b. 5tanl>esamt: ........
Geb.-Beg.-llr................ .
Tauf-Reg.-nr. . ...............
b. j)farramt: ..............
Iauf-Reg.-llr . ....... .......
Beurh. b. 5tanl>esamt: ..........................
b. j)farramt: .... ..
in
geflorben am .......... .....
Reg.. nr ............
beurh. b. 5tanl>esamt- j)farramt
I 52/53
Die EhefchlieRung bu
fiir nl'brnjlthenben
finlrag in Btglaubigung
ni<hl "forbtrli<h.
geflorben am ................................... in ........................... ............
beurh. b. 5tanl>esamt - j)farramt
Beruf: ...
geborene ..........
Behenntnis : ...... ....................
erfolgte am . ...
...... . .. in ..................... .......................... .
beurh. b. 5tanl>esamt - j)facramt . ........................ 11eg.-nr.
. Behenntnis : ....
geborene ...
·""'
53
(ffiutter uon 26)
erfolgte am
0ornamen:...
0omamen: ......
geboren am
.... in
als Iochter bes (106) _ .......... .....................
als Tod,ter bes ( 110)
unl> ber ( I 07)
unl> ber ( I 11)
Behenntnis: ....
. . .............. Iauftag: ...................
Beurh. b. 5tanbesamt: ..
b. j)farrnml:
geflorben am ..........
beurh. b. 5tnnl>esnmt- j)facrnmt. ..
..... i:1 .....
55
Geb.-Beg.-nr.
Tnuf-Reg.-llr........
b. j)fnrrnmt: .....................
Tauf-Reg.-llr.
Reg.-llr.
Ur-Ur-Urgropeltern
geflorben am ..........
. ...... in .. .
beurh. b. 5tanl>esamt- j)farramt..
miltterlich (2)
0
D
..... .. .. Tauftag:
Geb.-Reg.-nr. ..... ..............
JUr nebrn[tehenben
finltog in 8egloubi9ung
ni<hl "fotbrrli<h.
"'
. . ....... in . ..................
lleudi. b. 5tanbesamt:
in ..
·""'"'
Reg.-llr.
( Tiutter uon 21)
Geburtsname:
geboren am..
.. llehenntnis :.
beurh. b. 5tanbesnmt - j)farramt .. ........... .
Geburtsname:
34
I 54/55
'fi.ir nebenftehen�en
Einlrog in Begloubigung
nldtl ecforbuli<h.
unl> ber .
unl> ber .......... ..
l3ehennlnis: .....
Reg.-llr ..
Die EhefchlieRung Iles
Behenntnis: ...
Beruf: .............................
i
11eg.-llr.
fut n,b,nnehenben
Eint,09 iR Beglaubigung
ni"11 ecforbetli<h.
35
�56
(Oater oon 28)
familienname:... ...................................
familienname:
Oornamen: ...................... .
Oornamen:...
geboren am .
geboren am .
.......... in
als 5ohn l>es ( 112)......... . .. ........... .
nls 5ohn bes ( 116)
unl> ber ( 113).
unl> ber ( I It)
Behenntnis:.
58
(Oater oon 29)
.................. in......
Behenntnis:... . ............................. Tauftng:.
Tauftag:
6eb.-Reg.-nr.................
Beurh. b. 5tanl>esamt:
6eb.-Reg.-llr. .............
Beurh. b. 5tanbesamt:.... ........................ .
b. Pfarramt: ................ .
Tauf-Reg.-llr...... ...........
b. Pfarramt: .. ............................................. Tauf-Reg.-llr . .
genorben am .
filr nebenflehenben
Einlrag ij\ 8egtoubigung
nicht erforbeclich.
........ ... in
beurh. b. 5tanbesamt - Pfarraml
Reg.-llr.
genorben am ...
beurli. b. 5tanbesamt - Pfarramt... ................. .... . Reg.-llr.............
13eruf:.. ........................................... Behenntnis:.
Beruf= .·-····
unl) l>er ...
unl) ber ...
erfolgte am ...............
erfo!gte am .. ................................. in ..................... ............. .
in ....................
(mutter oon 28)
beurh. b. Stanbesamt - Pfarramt.............................. Reg.-llr....
Reg.-llr...
T
I
(ITiutter oon 29)
51
6eburtsname: .....
6eburtsname:
Oornamen:.........
Oornamen:..
geboren am .......
geboren am..
... in ....... .
il
in...................................
13ehenntnis:...
13eurh. b. 5tanbesamt:.
6eb.-Reg.-llr.
Beurh. b. 5tnnbesamt:. .
6eb.-Reg.-llr.
b. Pfarramt:.
Tauf-Reg.-llr..
b. Pfarramt:
Tauf-Reg.-llr. .
36
0
D
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Behenntnis: .............................. ... Tauftag: ...
beurh. b. 5tanl)esamt - Dfarramt
�
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unb l>er ( 119)
15) ......
genorben am .. .....
59
als Tochter bes ( 118)
alsTochtcr bes (I 14).
unb l>er(l
.. 13ehenntnis:
geborene ....... ........................................ 13ehenntnis: .................
Behenntnis:
beurh. b. 5tanbesamt - Dfarramt......................
fUr nebennehenben
Elntrog i� Beglnubigung
nitht erforb,clith.
1 sst59
I 56/57
Die Ehef chlie�ung l>e1
geborene ..
............ in .....................
in .
Reg.-llr.......... .
fii.c nebenflrhimben
Eintrog lft Beglaubigung
nidit erfortlerli<h.
Ur-Ur-UrgroPeltern
. ............ Tauftng: ....... ..........
genorben am ...... ............................ ... in ........................... ...................
beurh. b. Stanbesamt - Pfarramt ...
........ ...... lleg.-llr.
fiic neben�ehenb .J
Eintrag i� Begtaubigung
nicht rrfocb,clich.
miitterlich ['.l)
'J1
"
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(Onter oon 30)
60
familienname: . ............................ ..................... .
familiennnme: .......... .
Oornamen:
Oornamen: .....
geboren am ......................... . ........ in
in
geboren am ...
als Sohn bes ( 124)
als 5ohn bes ( 120).
unb ber ( 125) ...
unb ber(l21) ..... .
Bekenntnis: ......................
........... ..... Tauftag:................ .
Behennlnis: ........
Beurk. b. 5tanbesaml: ................... ........�
Geb.-Reg.-nr. ..................
b. Pfarraml: .......................... ................ tauf-Reg.-nr . ....
geflorben am...........
.. in
Reg.-nr .. ...
beurh. b. 51anbesaml - Pfarramt
fur neb,n�ehen�,n
fintra9 i� Be9taubigung
riidit erfoc�,rlid,.
......... in ...
beurh. b. 5tanbesaml - Pfarramt
lleg.-llr..........
fUr nebenf?ehenben
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nlcht erforbertich.
I 621u
Behennlnis: ................
....... Behennlnis : ................
................... in
Heg.-llr. ... .... .
63
(ffiutter oon 31)
61
6eburtsname : . ...................
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Oornamen:.....
geboren am
in .. ........
unb ber (123) ....... .... .
Behennlnis:........................... ........ Tauftag:
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b. Pfarramt: .. .......
Tauf-Reg.-nr. .
................. in
beurk. b. 5tanbesaml - Pfarromt .... .. ......... ......... Reg.-llr...
. i.1
als Tochter bes ( 126) ...
als Tochter bes ( 122).....
38
geflorben am . ..........
beurh. b. 5tanbesamt - Pfarramt......
Reg.-nr....
(ffiutter oon 30)
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b. Pfarramt:
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. ... ...... .............. Behennlnis:
beurh. b. 5tanbesnmt - Pfarramt....... .
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unb ber . ................................
unb ber .
geborene ...
Beurh. b. 5tanbesaml: ........ .....................
Beruf: .... .......
Behenntnis :.....
Beruf:
.. Tauftag: ...
Die EhefchliePung bet
1 60/61
Die EhefchliePung be•
erfolgle am
62
(Oater oon 31)
unb ber ( 127) ................... ..
. ................
Behennlnis: . ......................... .
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geflorben am ...................
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in .
beurh. b. 5tanbesamt - Pfarramt .................
mlitterlidi (4)
lleg.-llr..
fUr neb"n�ehl'nben
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nidlt et'focberlidi.
39
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(Oater uon ........... )
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I
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i:1.
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40
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.. Reg.-llr..........
fut neben(bhenben
Einlrag in Beglaubigung
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41
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42
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unb bee( . . ) ...... .... ...........
Tauftag:
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in
Oorbrudle fur Er9iin1un9en ff, Stile 5)
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)
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44
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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
William A. Mrazek Collection
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 is digital only. This collection was generously lent to UAH for digitization by Ursula Mrazek Vann.
Identifier
An unambiguous reference to the resource within a given context
William A. Mrazek Collection
Description
An account of the resource
William Anthony Mrazek “(October 20, 1911 to February 8, 1992)” received his education at Deutsche Technische Hochschule, Brünn, Germany, graduating with an engineering diploma in 1935 (Wade, Lundquist). Mrazek worked at Peenemünde from 1941 to 1945 as a loads engineer (Lundquist, Wade). He worked with Wernher von Braun at Peenemünde. <br /><br />Mrazek was brought to America through Operation Paperclip and arrived at Fort Bliss on April 8, 1946 (Wade, Lundquist). In 1950, Mrazek moved to Huntsville, Alabama, and worked for the U.S. Army’s rocket programs until 1960.<br /><br />By 1960, Mrazek became Director, Structures and Mechanics Division at the George C. Marshall Space Flight Center, and by February 1969, he became the Assistant Director for Engineering for Industrial Operations (Wade, Lundquist). Mrazek later served as the “Chief Engineer for all Saturn development and fabrication work, reporting to the Saturn V Project Manager,” from “1965 to 1970” (Lundquist).<br /><br />Mrazek retired from the Marshall Space Flight Center in 1973 (Lundquist).<br /><br />Works Cited<br /><br />Lundquist, Charles. "Transplanted Rocket Pioneers," 2015.<br /><br />Wade, Mark. "Mrazek, Willi." <em>Encyclopedia Astronautica</em>, http://www.astronautix.com/m/mrazek.html.
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Identifier
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spc_mraz_019_045
Title
A name given to the resource
Ancestor pass issued to Berta Mrazek.
Description
An account of the resource
The document identifies Berta Mrazek's family lineage, including parents, grandparents, great grandparents, and 2nd-great grandparents. The <i>Ahnenpass</i> was a standard booklet issued to German citizens in order to prove their ancestry in the Third Reich.
Creator
An entity primarily responsible for making the resource
Mrazek, Berta Richter
Date
A point or period of time associated with an event in the lifecycle of the resource
1942-08-21
Temporal Coverage
Temporal characteristics of the resource.
1940-1949
Subject
The topic of the resource
Mrazek, Berta Richter
Germany--Genealogy
Type
The nature or genre of the resource
Family trees
Text
Source
A related resource from which the described resource is derived
William A. Mrazek Collection
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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 is digital only.
Language
A language of the resource
de
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
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spc_mraz_2019_03
-
https://digitalprojects.uah.edu/files/original/8/14238/loc_hbhc_Ancor_Oak_Stove.pdf
812a32b2724879e27e98ba54d178a192
PDF Text
Text
THE OAK ANCHOR.
FOR
SOFT OR
HARD
COAL. COKE. OR
WOOD.
Air Tight.
List Price
Height to
Circumference
Code
Full Nickel
List Price
Diameter
Collar
Weight
Pipe Collar
Word
$18 50
$20 00
12 in.
38
in.
141 lbs.
19
in.
Lift.
22 50
24 00
14 in.
40J4 in.
180 lbs.
19
in.
I.igan.
29
25
27 50
18 in.
44
in.
245 lbs.
22V in.
Lictor.
32 50
34 25
18 in.
47J4 in.
287 lbs.
22 V in.
Libral.
Self Feeder, for Hard Coal, extra add to list No. 611. $2.25; 616, $2.75; 618. $3.25.
Leash.
When Full Nickel is wanted.
Leaven.
A first-class air tight construction in Oak Stoves, carefully fitted and mounted: heavy steel plate body : beauti
ful rococo ornamentation, unusually well proportioned and symmetrical lines. Extra deep fire pot to protect steel
plate from discoloration by fire, constructed with heavy ribs on inner side, a most effective Hot Blast holding
coal away from fire pot, making it more durable and less liable to crack while admitting an abundant supoiv of air
for perfect combustion, also has triple safe joint ground into ash box. no leak. Large double feed door with Alaska
turn key and splendid mica illumination with smokeless device. Air Tight Ash Box: Ash Door and Draft
Slide ground and fitted to prevent leakage of air this means control, any desired degree of heat and conseouently. economy. Keeps fire twelve to twenty-four hours. Draw center grate, works on ball bear
ings, shakes from outside with alight effort, no duet, easy and cleanly: ha largo surface, hence perfect
combustion, is readily removed through ash pit door. Lsrge ash pan. Swing off urn top. boiler hole below. The
new style Foot Rail with attached Skirting or Screen, deflects heat to the floor, but does not become tarnished ; also
prevents sight of fire bowl when discolored.
Nickeled Parts: Drntop.top ring, both panels in feed door, round foot rail, with attached Skirting, drafl
slide, grate shaker, knobs and turn keys, nickel Bnd bronze urn. Full nickel finish has in addition to above parts
four feet and skirting base, nickel plated.
78
No.
612
614
616
618
�SMOKE AND GAS
CONSUMING DEVICE
AS APPLIED TO THE
"OAK ANCHOR,"
ILLUSTRATED ON OPPOSITE PAGE.
To llio left is represented a side Re
flector and at the bottom a Bell Re
flector as tbev appear before being
placed in stove.
Above the Reflectors are shown
in the position occupied in the
"Oak Anchor" ready to ignite
and consume soot, smoke and
gases when heated.
THE OAK ANCHOR SMOKE CONSUMER.
Air Tight, for Soft or Hard Coal, Coke or Wood.
No.
1)12
614
616
618
List Price
List Price
Fuli Nickel
Diameter
§23 50
§25 00
12 in.
28 50
30 00
14 in.
34 50
36 25
16 in.
40 50
42 25
18 in.
When full nickel is wanted.
Height to
Collar
38 in.
40}£ in.
44
in.
47t£ in.
Weight
163 lbs.
208 lbs.
279 lbs.
329 lbs.
Circumf.
Pipe Col.
19 in.
19
in.
22^ in.
22% in.
Code Word
Likol.
Lilok.
Lipol.
Lil'os.
Lentven.
We have secured from Messrs. Oblinger & Beatty, patentees and owners, license to manufacture this
marvelous invention, and are now prepared to otter the exclusive sale of this stove to live, wide-awake,
pushing dealers. No such chance will appear again in a life-time. Mankind has looked forward for years'
confident that some genius would invent a simple device for consuming the valuable gases and smoke
given off by our present imperfect methods of burning soft coal. The Hot Blast Tube, the Hot Blast Rings.
Air -lets, etc. have all been tried, but they consume only a small fraction of the gases and smoke, and no
device that permits open combustion, as these do, will ever realize reasonable expectations of the vast economy
to be achieved. Two things have been shown to be absolutely essential by the thousands of devices and
years of experiments: 1st, The gases and smoke must be confined, otherwise they will escape up the chim
ney unburned. 2d, Great heat is necessary, applied direct to the gases and smoke above the fire itself.
All appliances that have contained these essential and successful requirements have been so compli
cated and costly as to preclude their common use. All really great inventions are SIMPLE, and as
an evidence of the great simplicity of this invention no directions are necessary beyond turning the
damper i handle toward the front) when starting fire, (this gives direct draft same as if the smoke consumer
was not in the stove) in ten or fifteen minutes, reverse the damper the Bell Reflectors will then have become
hot, and the reversal of the damper will force all of the gases and smoke into the hollow red hot bell,
suspended over the fire, and then between it and the outer bell, tbe opening between the two being 'f-., of an
inch, all of the soot, gases and smoke will be consumed instantly. The roar of the gases can be heard
while burning and their combustion can be seen through the small damper in pipe collar, but best of all,
their perfect combustion, can be felt in the great heat given oil and the small amount of coal consumed.
After the Bell Reflectors are once heated the burning gases will keep tliern hot, so that a slow fire may be
kept. The black coal smoke turns white like steam as it comes from the chimney immediately after the
damper has been turned and the reflectors are hot, and as they become highly heated the white smoke Grad
ually disappears, and after the gases are all burned the coal will be found coked and will burn to light ashes
without clinkers.
Lose no time, apply immediately and get the best seller in stoves ever put forward in this centurv.
79
�
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Title
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Harrison Brothers Hardware Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/65" target="_blank" rel="noreferrer noopener">View the Harrison Brothers Hardware Collection finding aid in ArchivesSpace</a>
Identifier
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Harrison Brothers Hardware Collection
Description
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Originally establishing a tobacco shop on Jefferson Street in 1879, brothers James B. and Daniel T. Harrison moved their shop to their current location in Huntsville’s Southside Square in 1897. After the building was damaged by a fire in 1901, the brothers rebuilt and expanded their store, reopening as Harrison Brothers Hardware in 1902. After James’ death in 1908, Daniel T. and Robert Harrison, their younger brother, ran the store. In 1940, Daniel T. Harrison passed away leaving Robert the sole owner of the store. In the 1950s, Robert’s sons, Daniel F. and John Harrison, took over the store. In 1952, Robert Harrison passed away. In 1981, Daniel F. Harrison passed away leaving John Harrison as the sole owner of the store. The Historic Huntsville Foundation purchased the store in 1984, after the store closed due to John’s death in 1983. As one of the first major projects of the Historic Huntsville Foundation, the store was reopened in October of 1984 and is staffed by several volunteers. The Historic Huntsville Foundation currently continues the operation of Harrison Brothers Hardware in Huntsville, making it Alabama’s oldest operating hardware store.
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Identifier
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loc_hbhc_Ancor_Oak_Stove
Title
A name given to the resource
Anchor Stove and Range Co. stove catalog, 1904.
Description
An account of the resource
These images are from Anchor Stove and Range Company catalog and price list volume no. 39, August 1904. The item pictured on the first page is The Oak Anchor stove and price descriptions and product details are written in the text below the image and the second page.
Creator
An entity primarily responsible for making the resource
Anchor Stove and Range Co.
Date
A point or period of time associated with an event in the lifecycle of the resource
1904
Temporal Coverage
Temporal characteristics of the resource.
1900-1909
Subject
The topic of the resource
Anchor Stove and Range Company
Catalogs
Type
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Books
Still Image
Source
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Harrison Brothers Hardware Collection
Box 45
Folder 4
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
HBH_Merchants_and_Mill_Workers_RCEU_2023
-
https://digitalprojects.uah.edu/files/original/124/8387/r04b06-01.pdf
95c1f85c4268a7a3d33a91004c9bbddc
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Identifier
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Series 04, Subseries B: Madison County History
Title
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Series 04, Subseries B: Madison County History
Still Image
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r04b06-01
Source
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Series 4, Subseries B, Box 6, Folder 1
Title
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Anderson, George T. Diary - copy
Relation
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r04b-210924
-
https://digitalprojects.uah.edu/files/original/109/7409/r01c05-01.pdf
000d16e46ca80c94c351369a9348b1b7
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Series 01, Subseries C: Cabaniss Personal Correspondence
Title
A name given to the resource
Series 01, Subseries C: Cabaniss Personal Correspondence
Description
An account of the resource
Subseries C, Cabaniss Personal Correspondence (CPC), consists of correspondence from letters from friends, relatives, and their children. Most of the family correspondence involves these children and families of S. D. Cabaniss, and his brothers and sisters who appeared to have been enormous burdens in these difficult years. These papers are sorted "to whom," "from whom," and then chronologically.
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.
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r01c05-01
Title
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Anderson, John C. to Cabaniss, Fanny (Fannie), 1904
Relation
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r01c-210910
Source
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Frances C. Roberts Collection, Series 1, Subseries C, Box 5, Folder 1, University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
-
https://digitalprojects.uah.edu/files/original/109/7310/r01c07-08.pdf
9c852610943364cb38ed6c05903d5082
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Series 01, Subseries C: Cabaniss Personal Correspondence
Title
A name given to the resource
Series 01, Subseries C: Cabaniss Personal Correspondence
Description
An account of the resource
Subseries C, Cabaniss Personal Correspondence (CPC), consists of correspondence from letters from friends, relatives, and their children. Most of the family correspondence involves these children and families of S. D. Cabaniss, and his brothers and sisters who appeared to have been enormous burdens in these difficult years. These papers are sorted "to whom," "from whom," and then chronologically.
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.
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Identifier
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r01c07-08
Title
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Anderson, Mary to Cabaniss, Septimus Douglass, Sr., 1884
Relation
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r01c-210910
Source
A related resource from which the described resource is derived
Frances C. Roberts Collection, Series 1, Subseries C, Box 7, Folder 8, University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
-
https://digitalprojects.uah.edu/files/original/109/7149/r01c11-18.pdf
b5c7ef72d3440663c02fc04f49b9984d
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Identifier
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Series 01, Subseries C: Cabaniss Personal Correspondence
Title
A name given to the resource
Series 01, Subseries C: Cabaniss Personal Correspondence
Description
An account of the resource
Subseries C, Cabaniss Personal Correspondence (CPC), consists of correspondence from letters from friends, relatives, and their children. Most of the family correspondence involves these children and families of S. D. Cabaniss, and his brothers and sisters who appeared to have been enormous burdens in these difficult years. These papers are sorted "to whom," "from whom," and then chronologically.
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
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Identifier
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r01c11-18
Title
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Anderson, S. Dudley to Cabaniss, Virginia (Shepherd), 1890
Relation
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r01c-210910
Source
A related resource from which the described resource is derived
Frances C. Roberts Collection, Series 1, Subseries C, Box 11, Folder 18, University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
-
https://digitalprojects.uah.edu/files/original/104/5396/img_01237.pdf
de5a0d349fb3490b3a21ceb492f9ff60
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Title
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Southpaw Postcard Collection
Identifier
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Southpaw Postcard Collection
Description
An account of the resource
George (Buzz) & Peg Heeschen have allowed us to include their collection of about 500 Huntsville and Madison County postcards, including scenes of buildings, streets, homes, Big Spring, Monte Sano, Marshall Space Flight Center and many others.
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img_01237;img_01238
Title
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Anna Knight Elementary School, Oakwood College
Coverage
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Oakwood University
Description
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Back: Oakwood College. Huntsville, Alabama. Cunningham Hall, Women's Dormitory (1947)
Type
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Postcards
Subject
The topic of the resource
Schools (Huntsville, Ala.)
Huntsville (Ala.)
Madison County (Ala.)
Publisher
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Scenic South Card Co., Bessemer, Ala.
Source
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From the postcard collection of George and Peg Heeschen, The Southpaw, Huntsville, Alabama
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 is digital only.
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections may have 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
postcard_import-210603
Language
A language of the resource
en
Spatial Coverage
Spatial characteristics of the resource.
34.752793,-86.655985
Date
A point or period of time associated with an event in the lifecycle of the resource
1947
Temporal Coverage
Temporal characteristics of the resource.
1940-1949
-
https://digitalprojects.uah.edu/files/original/123/7992/r04a16-19.pdf
99a78df73cc03a8e94af31a90282add9
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Identifier
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Series 04, Subseries A: Huntsville History
Title
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Series 04, Subseries A: Huntsville History
Still Image
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Identifier
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r04a16-19
Source
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Frances Cabaniss Roberts Collection
Series 4, Subseries A, Box 16, Folder 19
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Title
A name given to the resource
Annie Merts Center Dedication, 1981
Description
An account of the resource
City Schools
Relation
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r04a-210924
Date
A point or period of time associated with an event in the lifecycle of the resource
1981-05-10
Temporal Coverage
Temporal characteristics of the resource.
1980-1989
Subject
The topic of the resource
Alabama–History–Huntsville, Madison County
Building dedications
Merts, Annie C.
Programs
Type
The nature or genre of the resource
Leaflets
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.
-
https://digitalprojects.uah.edu/files/original/204/14587/Bigger_Crossed_Out_Annotated_Page_of_Otia_Imperialia.jpg
a2a06789d60f3c2ec63105dc706762d8
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HON 399 Research in London
Title
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HON 399 Research in London
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Title
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Annotated Page of Otia Imperialia
Description
An account of the resource
Annotated pages of a 14th century Italian manuscript of the Otia Imperialia by Gervase of Tilbury. Past owners of the manuscript have crossed out sections and included their own notes in the margins in Latin.
Creator
An entity primarily responsible for making the resource
Waugh, Caroline
Gervase, of Tilbury, approximately 1160-approximately 1211
Date
A point or period of time associated with an event in the lifecycle of the resource
c. 1350-1400
Subject
The topic of the resource
Manuscripts
Source
A related resource from which the described resource is derived
Oxford Bodleian library, Special Collection, MS Canon. Misc. 53
Is Part Of
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“Marvels, Folklore, and the Otia Imperialia by Gervase of Tilbury,” by Caroline Waugh, HON 399 Research in London, Spring 2024
Language
A language of the resource
Latin
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
HON 399
Honors College
Student Projects
Study Abroad
-
https://digitalprojects.uah.edu/files/original/207/14685/Birmingham_Post_Herald_1996_06_11_25.jpg
9bbb311e476e5a9e3791411facca494d
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Title
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RCEU Faith Based AIDS Responses in 1980s and 1990s Alabama
Creator
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Morgon Newquist
Dublin Core
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Identifier
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Birmingham_Post_Herald_1996_06_11_25
Title
A name given to the resource
Announcement in the Birmingham Post-Herald about Meal Deliveries
Description
An account of the resource
Clipping of a scan of the Birmingham Post-Herald from 1996 announcing that the AIDs Task Force of Alabama, the Birmingham AIDS Outreach and the Community Kitchens would work together to provide meals for HIV positive individuals who needed help with meal preparation.
Creator
An entity primarily responsible for making the resource
Birmingham Post-Herald
Publisher
An entity responsible for making the resource available
Birmingham post-herald
Date
A point or period of time associated with an event in the lifecycle of the resource
1996-06-11
Temporal Coverage
Temporal characteristics of the resource.
1990-1999
Spatial Coverage
Spatial characteristics of the resource.
Alabama
Birmingham (Ala.)
Subject
The topic of the resource
AIDS (Disease)
AIDS (Disease) and mass media
AIDS (Disease) in mass media
AIDS (Disease)--History
HIV-positive persons--Care
Type
The nature or genre of the resource
Newspapers
Clippings
Source
A related resource from which the described resource is derived
Birmingham Post-Herald, Newspapers.com, Ancestry.com (LLC), Alabama Media Group
https://www.newspapers.com/image/795948828/
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.
-
https://digitalprojects.uah.edu/files/original/109/7320/r01c06-36.pdf
3492ef8fc7bc365132cdff3e07f60893
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Identifier
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Series 01, Subseries C: Cabaniss Personal Correspondence
Title
A name given to the resource
Series 01, Subseries C: Cabaniss Personal Correspondence
Description
An account of the resource
Subseries C, Cabaniss Personal Correspondence (CPC), consists of correspondence from letters from friends, relatives, and their children. Most of the family correspondence involves these children and families of S. D. Cabaniss, and his brothers and sisters who appeared to have been enormous burdens in these difficult years. These papers are sorted "to whom," "from whom," and then chronologically.
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.
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r01c06-36
Title
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Announcements of Death & Mementos, 1903
Relation
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r01c-210910
Language
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en
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Source
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Frances C. Roberts Collection, Series 1, Subseries C, Box 6, Folder 36, University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
-
https://digitalprojects.uah.edu/files/original/120/7888/r02h03-00-003.pdf
df12cb64ef00e56bf676f2583a6be591
Dublin Core
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Series 02, Subseries H: Mementos, photos, and cards
Title
A name given to the resource
Series 02, Subseries H: Mementos, photos, and cards
Dublin Core
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Identifier
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r02h03-00-003
Title
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Ánnus Mirabilis, Yearbook, Livingston, AL, 1932
Source
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Frances Cabaniss Roberts Collection
Series 2, Subseries H, Box 3, Item 3
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
A language of the resource
en
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
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r02h-210915
Date
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1932
Temporal Coverage
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1930-1939
Subject
The topic of the resource
High School Yearbooks
Livingston High School
Mementos
Photographs
Type
The nature or genre of the resource
Yearbooks
-
https://digitalprojects.uah.edu/files/original/76/3924/Loc_burw-690.pdf
a37edcb919603ee38511b467124f83cd
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Identifier
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Burwell Family Collection
Title
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Burwell Family Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/145" target="_blank" rel="noreferrer noopener">View the Burwell Family Collection finding aid in ArchivesSpace</a>
Description
An account of the resource
<a href="http://libarchstor2.uah.edu/digitalcollections/items/show/3332" target="_blank" rel="noreferrer noopener">View Edwin D. Burwell's World War II service timeline, 1943-1944</a>
<a href="http://libarchstor2.uah.edu/digitalcollections/items/show/3333" target="_blank" rel="noreferrer noopener">View Edwin D. Burwell's World War II service timeline, 1944-1945</a>
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.
Materials donated and digitized by Dudley Burwell
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Identifier
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loc_burw_000690
Title
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Another tank (San Piedro).
Description
An account of the resource
Photograph number 469. This photograph shows a tank on an incline in San Pietro, Italy. The title for this image was found in Major Edwin D. Burwell Jr.'s list of photographs.
Date
A point or period of time associated with an event in the lifecycle of the resource
1944
Temporal Coverage
Temporal characteristics of the resource.
1940-1949
Subject
The topic of the resource
Tanks (Military science)
World War, 1939-1945--Campaigns--Italy
San Pietro Infine (Italy)
Type
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Photographs
Still Image
Source
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Burwell Family 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
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loc_burw_2021_03B
Creator
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Burwell, Edwin D. III [Burwell, Edwin D., Jr.]
-
https://digitalprojects.uah.edu/files/original/110/7579/r02a06-00-012.pdf
33d4e485d51815ac8bda973257fd9b08
Dublin Core
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Identifier
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Series 02, Subseries A: Frances Roberts' Early Years and Teaching Career
Title
A name given to the resource
Series 02, Subseries A: Frances Roberts' Early Years and Teaching Career
Description
An account of the resource
These papers include material about the family history of Dr. Roberts, her early education, and college, teaching career at Huntsville High School and UAH. Also there are a few notes for her M. A. "An Experiment in Emancipation of Slaves by an Alabama Planter," 1940. (The majority of this material is at the Hoole Library, Tuscaloosa, UA.) Notes for the Dissertation "Background and Formative Period in the Great Bend and Madison County," 1956, are included here also. There is also a great deal of miscellaneous personal correspondence that is sorted only by decade.
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
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Identifier
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r02a06-00-012
Title
A name given to the resource
Answer Guide for Understand Civics to Accompany Civics for Alabama Schools
Relation
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r02a-210915
Creator
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Florida. State Department of Education
Date
A point or period of time associated with an event in the lifecycle of the resource
1962
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Americanisms
Communism
Education
History
Type
The nature or genre of the resource
Pamphlets
Source
A related resource from which the described resource is derived
Series 2, Subseries A, Box 6, Item 12
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Frances C. Roberts Collection
Language
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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.
-
https://digitalprojects.uah.edu/files/original/126/8673/r04d02-10.pdf
4c808c595a9ecf077d15d6d133e55984
Dublin Core
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Identifier
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Series 04, Subseries D: Committees and Organizations, State and Local
Title
A name given to the resource
Series 04, Subseries D: Committees and Organizations, State and Local
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.
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Identifier
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r04d02-10
Source
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Series 4, Subseries D, Box 2, Folder 10
Title
A name given to the resource
Antiquarian Society Materials
Relation
A related resource
r04d-211008
-
https://digitalprojects.uah.edu/files/original/40/749/uah_uahp_000194_web.pdf
cfa4f37264ba3fd73f06ab2a4c9fdd4a
PDF Text
Text
�
Dublin Core
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Title
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UAH Photograph Collection
Identifier
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UAH Photograph Collection
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uah_uahp_000194
Title
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Antique car parked at the entrance to the Noojin House.
Description
An account of the resource
Located at 3300 Holmes Ave. in Huntsville, the home was donated to UAH by F. Kenneth Noojin in 1983. UAH sold the home in 2001.
Creator
An entity primarily responsible for making the resource
University of Alabama in Huntsville
Temporal Coverage
Temporal characteristics of the resource.
1980-1989
Subject
The topic of the resource
College buildings
University of Alabama in Huntsville
Huntsville (Ala.)
Madison County (Ala.)
Type
The nature or genre of the resource
Photographs
Still Image
Source
A related resource from which the described resource is derived
UAH Photograph 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
uah_photos_2019_05
-
https://digitalprojects.uah.edu/files/original/20/1155/spc_stnv_000071.pdf
b1640a68a7f1bcbf1b664bdfa25ace14
PDF Text
Text
.
J
I k
@
NATIONALAERONAUTICS AND SPACE ADM*lSTRATlON
TELS
WASHINGTON,D .C. 20546
WO 2-4155
W 0 3-6925
FOR RELEASE: ~ D I A T E
m y 7, 1969
RELEASE NO:
69-68
PROJECT:&pow
19
SATURN !-llSTORY DOCUMENT
University of Alabama Research lnstitcrk
History of Science G. Technology G ~ w
------- - - - DOC.NO.
Date
S
*S
------a-
GB#ERALWSE--------------------------------------------1-7
WSSIOM oBJgc~s-----------------------------------------~-lo
A ~ U X ) 10 ~~~~~---------------------------------------11-1
HISSIOBi CPWAJECTORY AND MHBWER DESCRImION----------------14
Launch Evenes-------------------------------------------15
m r s l o n E;vants---------------------------------------------l6-18
m t h ]Pa**
Opblt-------------------------------------19
Wan8l-r
Injection-------------------------------------19
Tranarposition, Daoklng and $;leetion----------------------
19
'pransl-r
Coaet-----------------------------------------2Q
L m r Orbst Im%erti~n------------------------------------20
Lunar Parking Orbit L W-Autive Rendezvous---------------20-22
K
I
Transearth Injecti~n------------------------------~-------22
wasearth Caa~t----------------------------------------22
mtrg mding--------------------------------------------22
O~~TIQ~S--------------------------------------APOLLO 10 A L ~ A T MIISJSIOH~--------------------------------~~-~~
E
ABORT MoDES------------------------------------------------29
Deep Smae Abort@---------------------------------------- 29-31
APOLLO 10 a0/#0-80 DBCISIOM POImS------------------------ 32
O m R D mf;EfISIOM----------------;.----c-------------------APOLm 10 PBQmQRAPHIC TASKS------------------------------3
MHAR DESCRIPTION------------------------------------------35
pol lo Lunar mdiw ~ites-------------------------------36-37
COMMAND M D SBFtVICE MODULE STIPFICTURE, SYS'PElrtS---------------38-39
Y
CSH Systees---------------------------------------.----.39-41
S~UCSTTL;ZES,
UEIG~----------------------------~~
Ascent St;age--------------------------------------------
L W HOW
~
I)escent Stwe-------------------------------------.----.
m w Module System------------------------------------A448
�Conteats Continued
SAmRH W U W C R VEHICLE DESCRIPTIOM & OPERATIO&----------- 4 9
pipst Stage--------------------------------------------49
Second Stage--------------------------------------..----49-50
Stags---------------------------------------------50-51
nt Unit-----------------------------------------Ina
51-52
on----------------------------------------------Pro
52-53
Munch Vehicle Instrumentation and Communication---------53
Restapt-------------------------------------------S54 -55
APOEW 10 CRW-----------------------------------------------56
L i f e Support Equipment
Space Suits--------------------56-57
-
Heala---------------------------------------------------2;-62
Personal mgiene----------------------------------------$upviva& aeap--------------------------------------------63-64
Biomedical Lnflight lulsnitoring---------------------------a
Regt-Wopk Cgcles------------------------------------------&
waAnbg--.-----------------------------------------------65-66
Crew B&~gratphres-----~------------------------~---------67-72
&BI.uNcHQPEWONS-r,---------------------------73
Prelamch Preparakions----------------------------------73-75
u u H c R @omem39------------------------------------------76
a h i e l e Assembly m%ld$ng-------------------------------77-78
h m e h Control Center-----------------------------------78-79
Mob$le Launchep-------------------------------------------79-80
ABOLLX)
T~~nsporker------------..---------------------------------80-81
Cpawlemaye-----------------------------------------------8l
Mobile Service Stmewre---------------------------------81-82
Water mbwe System--------------------------------------82
m n e k and Deflector--------------------------------82-83
Pad areas------------------------------------------------83-w
Mfasfsn control Centep---------------------------.--------84-85
~~1aw"
WC~WORK---------------------------------~~-~$
p
ations ~etwork------------------------------8$-89
teps----------------------------------------
89-90
Ships-----------------------------------------90-91
Xnrstrumentrttion Aircraft (ARIA)-------------91
0110 lo-----------------------------92
ye----------------------------------93
Is---------------------------------9 -95
luraJor Apollo/Saturn V Cont~actors-----------------------2-97
98 102
APOLLO GLOS
----,-,i,---------------------AI?
ACRO
A
m mBRNmTxONS---------------------------103-l&
CO
SIOW
~s----------------------------.------------105 106
-
-
�LI
Y
N A T I O N A L AERONAUTICS
AND
WASHINGTON,D
SPACE ADMINISTRATION
.C. 20546
TELS'
W O 2-4 155
W 0 3-6925,
FOR' RE1
R E ~ S ENO:
69-68
APOLU) 10: MANt S NEAREST LUNAR APPROACH
Two Apollo 10 astronauts w i l l descend to within eight
nautical miles of the Moonls surface, the closest man has
ever been to another c e l e s t i a l body.
A dress rehearsal for the first manned lunar landing,
Apallo 10 is scheduled for launch Mag 18 at 12:49 p.m. EMP
f r o m the National Aeranautfca and Space Adlainistration's
Kennedy Space Center, Fla.
!?he eight-day, lunar orbit mission will mark the first
time the complete Apollo spacecraft has operated around the
Moon and the second manned flight for the lunar module.
Pollowlng c l o s e l y the time line and traJectory t o be
flown on Apollo 11, Apollo 10 w i l l Include an eight;-houp
eequence o f lunar module (W)undocked a c t i v i t i e s during which
the c o m d e r and Ijl p i l o t w i l l descend t o within eight nautical
milea o f the lunar surface and later rejoin the colllmajld/aervice
module (CSM) I n a 60-nautioal-mlle circular orbit.
�MOON AT EARTH LANDING
TRANSEARTH
INJECTION
ENTRY & LANDING
TRANSPOSITION
LUNAR ORBIT INSERTION
MOON AT EARTH LAUNCH
APOLLO LUNAR MISSION
�A l l a s p e c t s of Apollo 10 w i l l d u p l i c a t e conditions of
t h e l u n a r landing mission as c l o s e l y as p o ~ ~ i b l e - - S u angles
n
a t Apollo S i t e 2, t h e out-and-back flight path t o t h e Moon,
and the time l i n e of mission events,
Apollo 10 d i f f e r s from
Apollo 11 i n t h a t no landing w i l l be m d e on t h e Moon's surf ace,
Apollo 10 is designed t o provide a d d i t i o n a l operational
experience f o r t h e crew; space vehicle; and mission-support
f a c i l i t i e s during a simulated lunar landing mission.
Among
d e s i r e d data p o i n t s t o be gained by Apollo 10 a r e 3.44 systems
operations a t lunar d i s t a n c e s a s well as o v e r a l l mission
o p e r a t i o n a l experience.
The
was s u c c e s s f u l l y checked
-
out i n Earth o r b i t i n Apollo go i n c l u d i w a rendezvous sequence
simulating l u n a r o r b i t rendezvous.
Space navigation experience around t h e Moon is another
b e n e f i t t o be gained from f l y l n g a r e h e a r s a l mission before
making a l u n a r landing,
More knowledge of t h e l u n a r p o t e n t i a l ,
o r g r a v i t a t i o n a l e f f e c t will provide a d d i t i o n a l refinement of
Manned Space F l i g h t Metwork tracking techniques, and broad
landmark t r a c k i n g w i l l b o l s t e r t h l s knowledge,
�-
Analysis of l a s t Becemberls Apollo 8 l u n a r o r b i t mission
t r a c k i n g has aided refinement of t r a c k i n g and navigation techniques and Apollo 10 should reduce e r r o r margins s t i l l f u r t h e r .
Apollo 10 crewmen a r e Commander Thomas P. S t a f f o r d ,
Command Moudle P i l o t John W e Young and Lunar Module P i l o t
Eugene A. Cernan.
The mission w i l l be t h e t h i r d apace f l i g h t
f o r S t a f f o r d (Gemini 6 and 9 ) and Young ( ~ e m i n i3 and l o ) , and
t h e second f o r Cernan ( ~ e m i n i9 ) .
t h e Apollo 7 backup crew.
The three were recycled from
The Apollo 10 backup crew i a Com-
mander L. Gordon Cooper, Command Moudle P i l o t Donn F. E i s e l e
and Lunar Module P i l o t Edgar D, Mitchell.
S t a f f o r d i s an A i r Force Colonel; Young and Cernan are
Navy Commanders.
If necessary, t h e backup crew can be s u b s t i t u t e d f o r
t h e prime crew up t o about two weeks p r i o r t o a n Apollo launch.
During t h i s period, t h e f l i g h t hardware and software, ground
hardware and software, f l i g h t crew and ground crews work as an
i n t e g r a t e d team t o perform ground simulations and o t h e r tests
It i s necessary t h a t t h e f l i g h t crew
of t h e upcoming mission.
t h a t w i l l conduct t h e mission t a k e p a r t i n t h e s e a c t i v i t i e s ,
which a r e not repeated f o r t h e b e n e f i t of t h e backup crew.
To
v
do s o would add an a d d i t i o n a l c o s t l y two-week perlod t o t h e prelaunch schedule, which, f o r a l u n a r mission, would r e q u i r e
rescheduling f o r t h e next l u n a r window.
�-4-
The Apollo 10 rendezvous w i l l be t h e f i f t h space
rendezvous i n which S t a f f o r d has taken part--Gemini
7/6 and
t h e w o r l d ' s first rendezvous, and t h r e e t y p e s of rendezvous with
t h e augmented t a r g e t docking a d a p t e r i n Gemini 9 ,
The Apollo 10 mission time l i n e can be d e s c r i b e d as
a combination of Apollo 8 and Apollo 9 i n t h a t i t w i l l be a
l u n a r o r b i t mission w i t h a CSM-LM rendezvous,
Apollo 8 was a
l u n a r o r b i t mission with t h e command/service module only, while
Apollo 9 w a s an E a r t h o r b i t a l mission w i t h the complete Apollo
s p a c e c r a f t and included a LW-active rendezvous w i t h t h e CSM.
Apollo 10, a f t e r l i f t o f f from Launch Complex 39B, w i l l
begin t h e three-day voyage t o t h e Moon about two and a h a l f
hours a f t e r t h e s p a c e c r a f t is i n s e r t e d i n t o a 100-nautical
mile c i r c u l a r E a r t h parking o r b i t .
The Saturn V launch v e h i c l e
t h i r d s t a g e w i l l r e s t a r t t o i n j e c t Apollo LO i n t o a t r a n s l u n a r
t r a j e c t o r y as t h e v e h i c l e p a s s e s over A u s t r a l i a mid-way through
t h e second r e v o l u t i o n of t h e Earth.
The "go" f o r t r a n s l u n a r i n j e c t i o n w i l l f o l l o w a complete
checkout of t h e s p a c e c r a f t ' s r e a d i n e s s t o be committed f o r i n jection.
About a n hour a f t e r t r a n s l u n a r i n 3 e c t i o n (TLI), t h e
command/service module w i l l s e p a r a t e from t h e Saturn t h i r d
stage, t u r n around qnd dock with t h e l u n a r module n e s t e d i n
t h e s p a c e c r a f t IlvI a d a p t e r .
Spring-loaded l u n a r module holddowns
w i l l be r e l e a s e d t o e j e c t t h e docked s p a c e c r a f t from t h e a d a p t e r .
�-5-
Later, l e f t o v e r liquid p r o p e l l a n t i n t h e Saturn t h i r d
s t a g e w i l l be vented through the engine b e l l t o p l a c e t h e s t a g e
i n t o a " s l i n g s h o t " t r a j e c t o r y t o miss t h e Moon and go i n t o
solar orbit,
During the t r a n s l u n a r c o a s t , Apollo 10 w i l l be i n t h e
so-called passive thermal c o n t r o l made i n whlch t h e spacec r a f t r o t a t e s slowly about one of i t s axes t o s t a b i l i z e thermal
response t o s o l a r h e a t i n g ,
Four midcourse c o r r e c t i o n maneuvers
a r e p o s s i b l e during t r a n s l u n a r c o a s t and w i l l be planned i n
real time t o a d J u s t t h e t r a j e c t o r y ,
Apallo 10 w i l l first be I n s e r t e d i n t o a 60-by-170-nautical
mile e l l i p t i c a l l u n a r o r b i t , which two r e v o l u t i o n s later w i l l
be circularized t o
60 n a u t i c a l miles,
Both l u n a r o r b i t I n s e r -
t i o n burns (MI) w i l l be made when Apollo 10 Is behind t h e Moon
out of " s i g h t " of Manned Space F l i g h t Network s t a t i o n s ,
S t a f f o r d and Cernan w i l l man t h e U4 f o r systems checkout
and p r e p a r a t i o n s f o r a n eight-and-a-half
hour sequence t h a t
duplicates--except f o r an a c t u a l landing--the maneuvers planned
f o r Apollo 11.
The LM twice w i l l sweep within 50,000 f e e t of
Apollo Landing S i t e 2, one of t h e prime t a r g e t s f o r t h e Apollo
11 landing.
�-6Maximum s e p a r a t i o n between t h e IM and the CSM during
the rendezvous sequence w i l l be about 350 miles and w i l l
provide an extensive checkout of t h e LPlI rendezvous r a d a r as
well as of t h e backup VHF ranging device aboard t h e CSM, flown
f o r t h e first t i n e on Apollo LO.
When the LM ascent stage has docked w i t h t h e CSW and
the two crewmen have t r a n s f e r r e d back t o t h e CSM, t h e LM w i l l
be j e t t i s o n e d f o r a ground command ascent engine burn t o prop e l l a n t depletion which w i l l place the IN ascent s t a g e i n t o
solar oribt.
The crew of Apollo 10 w i l l spend t h e remainder of t h e
time i n lunar o r i b t conducting lunar navigational t a s k s and
photographing Apollo landing sites t h a t a r e within camera range
of Apollo 10's ground track.
The t r a n s e a r t h i n j e c t i o n burn w i l l be made behind the
Moon after 61.5 hours i n l u n a r o r b i t .
During t h e %-hour
t r a n s e a r t h coast, Apollo 10 again w i l l c o n t r o l s o l a r heat
loads by using t h e passive thermal c o n t r o l "barbecue" technique.
Three t r a n s e a r t h midcourse c o r r e c t i o n s are possible
and w i l l be planned i n r e a l time t o a d j u s t the Earth e n t r y
corridor.
�-7-
Apollo 10 w i l l e n t e r the E a r t h ' s atmosphere (400,000 f e e t )
a t 191 hours 51 minutes a f t e r launch a t 36,310 feet-per-second,
Command module touchdown w i l l be 1,285 n a u t i c a l miles down-
range from e n t r y a t 15 degrees 7 minutes South l a t i t u d e by
165 degrees West longitude a t a n elapsed time of 192 hours
5 minutes.
The touchdown point i s about 345 n a u t i c a l a i l e s
e a s t of Pago Pago, Tutuila, i n American Samoa.
(END OF GENERAL RELEASE; BACKGROUND IPIFORMATION FOLLOWS)
�APOLLO 10
lunch aB/dTrans Lunar njection
Astronauts Board' Apollo
Trans Lunar Injection
S a t u r n Staging
Papollo S a t u r n Separation
�P O L L O 10
Trans L u ~ . a rF
Apollo Midcourse Maneuver
Astronauts a t Command Module S t a r b n s
�APOLLO 10
Trans Lundr F
Final Course Adjustment
Navigational Check
�APOLFO 10
Lunar Oroita
Lunar Orbit Insertion
Television Braadcast
9
I
Lunw Landmark Tracking
Transfer to Lunar Module
�APOLLO 10
Descent Orbit Insertion
Lunar LBscent and Ren-dezvous
Lunar Mceduie! %tag"sng
LM
Ascent Engine Firing to Depletion
Lunar Landmark Tracking
�APOLLO 10
Trans - ~ a r t h njection and F
Trans Earth Injection
ApsBlas Midcourse Maneu ler
Navigational Check
Final Reentry Preparations
�Earth Reentry and Recovery
-
Command-Service Module
Separation
Command Module R e e n t r y
Splashdown
Recovery
�MISSION Ol3JECTIVES
Although Apollo 10 w i l l pass no c l o a e r than e i g h t
n a u t i c a l miles from t h e l u n a r ~ u r f a c e , a l l o t h e r a s p e c t s
of t h e mission w i l l be similar t o the f k r s t l u n a r landing
mission, Apollo 11, now scheduled f o r July.
The t r a j e c t o r y , time l i n e and maneuvers follow t h e
l u n a r landing p r o f l l e . After rendezvous i s completed, t h e
Apollo 1 0 t i m e l i n e w i l l d e v i a t e from Apollo 11 i n t h a t
Apollo 1 0 w i l l spend a n e x t r a day i n l u n a r o r b i t ,
Additional LP4 o p e r a t i o n i n e i t h e r E a r t h o r b i t o r l u n a r
o r b i t w i l l provide a d d i t i o n a l experience and confidence with
t h e IM systems, i n c l u d i n g v a r i o u s c o n t r o l modes of t h e Ul
primary/abort guidance systems, as w e l l as further assessment
of crew time l i n e s .
The mission w i l l a l s o t e s t t h e Apollo rendezvous radar
a t maximum range (approximately 350 miles vs. 100 miles during
Apollo 9). Apollo 10 w i l l mark t h e first space f l i g h t t e s t
of t h e
s t e e r a b l e S-band antenna and of t h e
landing radar,
The LM landing radar has undergone numeroue t e s t s i n Earth environment, but t h i s mission w i l l provide a n opportunity t o
check t h e l u n a r s u r f a c e r e f l e c t i v i t y c h a r a c t e r i s t i c s with t h e
landing r a d a r ,
Some 800 seconds of landing r a d a r a l t i t u d e a e a s u r i n g
data w i l l be gathered as the IIvI makes two sweeps eight nautical
miles above Apollo Landing S i t e 2.
!Ehis mission w i l l a l s o provide t h e first opportunity t o
check t h e very high frequency (VHP) ranging device aboard t h e
CSM which s e r v e s as a backup t o t h e LM rendezvous r a d a r ,
The Apollo 10 mission p r o f i l e provides f u e l and o t h e r consumable reserves i n t h e rsrl. t h a t are g r e a t e r t h a n those planned
f o r t h e first LM t o land on t h e Moon. The l u n a r landing mission
i s t h e "design mission" f o r t h e Apollo s p a c e c r a f t , and such a
mission has smaller although adequate margins of r e s e r v e consumable~.
From l i f t o f f through descent o r b i t i n s e r t i o n , Apollo 10
f o l l o w s c l o s e l y t h e t r a j e c t o r y and time l i n e t h a t w i l l be flown
i n t h e landing miss4on. Following t h e eight-mile pericynthion,
t h e p r o f i l e c l o s e l y simulates t h e c o n d i t i o n s o f l u n a r o r b i t
rendezvous af t a r a landing.
�The May 18 launch d a t e w i l l produce l i g h t i n g conditions
on Apollo S i t e 2 similar t o those t h a t w i l l be present f o r t h e
landing mission. A t t h e low i n c l i n a t i o n t o be flown on Apollos
10 and 11
about 1,2 degrees r e l a t i v e t o the lunar equator-Apollo landing S i t e 3 can be photographed and o p t i c a l l y tracked
by t h e crew of Agollo 10 i n addition t o t h e p ~ i m eS i t e 2.
--
S i t e 1 waa photographed by Apollo 8 i n last December's
lunar o r b i t mission and, together with t h e two s i t e s t o be
covered i n Apollo 10, photographic, tracking and s i t e a l t i t u d e
data on three s i t e s w i l l be in hand.
Among the Apollo 10 obJectlves i s the gathering of
a d d i t i o n a l Manned Space F l i g h t Network (MSFN) tracking data
on vehicles i n lunslr alpbit. While MSFN experience i n tracking
Apollo 8 w i l l benefit Apollo 10, t h e r e a r e s t i l l some uncert a i n t i e s , For example, t h e r e is s t i l l some lack of knowledge
as t o what t h e exact lunar p o t e n t i a l o r g r a v i t y f i e l d i s and
how it a f f e o t s an orbiting, spacecraft.
I n tracking Apollo 8, downtrack, o r o r b i t a l timing e r r o r s
projected ahead two revolutions were 30,000 f e e t , and o r b i t a l
radtus measurements r e l a t i v e t o t h e center of t h e Moon were
off 5,500 f e e t . MSFN tracking can produce accurate position
and velocity information i n r e a l time while a spacecraft i s
" i n view" from t h e Earth and not occulGed by the Moon, but
landing and rendezvous operations w i l l require accurate pred i c t i o n s of p e s i t i o n and velocity several revolutions i n advance
of t h e e v m t ,
The lunar p o t e n t i a l apparently a f f e c t s an o r b i t i n g
spacecraft d i f f e r e n t l y depending upon o r b i t a l i n c l i n a t i o n
and a l t i t u d e . Apollo 10 w i l l be flown on t h e same i n c l i n a t i o n
t o the lunar equator a s the landing mission and w i l l provide
iflormation f o r refining prediction techniques.
Apollo 8 p o s t f l i g h t a n a l y s i s has produced modifications
t o tracking a& position prediction techniques which should reduce downtrack e r r o r s t o 3,000 feet and a l t i t u d e e r r o r s t o
l,lC00 f e e t . Apollo 10 w i l l allow mission planners t o p e r f e c t
techniques developed as a r e s u l t of Apollo 8 tracking a n a l y s i s ,
Other space navigation benefits from Apollo 10 w i l l ha
gained from combinin$ onboard spacecraft lunar landmark tracking data with ISSFN tracking and from evaluating present lunar
landing site maps a t close v i s u a l and camera ranges.
�Additionally, LEI descent and ascent engine burns will
be monitored by HSFN stations for developing useful techniques
for tracking powered Pllgbt in future miaslons.
�APOLLO 10 COUNTDOWN
The clock for t h e Apollo 10 countdown w i l l start a t T-28
hours, with a six--hour built-in-hold planned a t T-9 hours, p r i o r
t o launch v e h i c l e p r o p e l l a n t loading.
The countdown i s preceded by a pre-count operation t h a t
begins some 4 days before launch. During t h i s e r i o d t h e t a s k s
include mechanical buildup of both t h e comandAervice module
and Uvl, f u e l c e l l a c t i v a t i o n and s e r v i c i n g and loading of t h e
super c r i t i c a l helium aboard t h e LM descent stage. A 5% hour
built-in-hold i s scheduled between t h e end of t h e pre-count and
start of t h e f i n a l countdown.
Pollowing are same of t h e h i g h l i g h t s of t h e f i n a l count:
T-28 h r s
.
O f f l c i a l countdown starts
T-27 h r s . 30 mins.
I n s t a l l launch v e h i c l e f l i g h t b a t t e r i e s
( t o 23 h r s . 30 mins.)
LM stowage and cabin closeout ( t o 15 firs.)
T-21 hrs.
Top off LM super c r i t i c a l helium ( t o
19 hrs )
.
Launch v e h i c l e range s a f e t y checks
15 hrs .)
(to
T-11 hrs. 30 mlns.
I n s t a l l launch v e h i c l e d e s t r u c t devices
( t o 10 hrs. 45 mins,)
~ommand/service module pre-ingress
operations
T-10 h r s .
S t a r t mobile s e r v i c e s t r u c t u r e move t o
park s i t e
T-9 hrs
.
S t a r t s i x hour built-in-hold
T-9 h r s . counting
Clear b l a s t a r e a f o r p r o p e l l a n t loading
T-8 hrs. 30 mins.
Astronaut backup crew t o s p a c e c r a f t f o r
prelaunch checks
T-8 ~ P S *15 mins.
Launch Vehicle p r o p e l l a n t loading, t h r e e
s t a g e s ( l i q u i d oxygen i n first stage)
l i q u i d oxygen and l i q u i d hydrogen i n
second, t h i r d stages.
Continues t h r u T-3 hrs. 38 mins.
�T-5 h r s ,
F l i g h t crew alerted
T-4 hrs. 45 mins ,
Medical examination
T-4 hrs, 15 mins.
Breakfast
T-3 hrs, 45 mins.
Don space s u i t s
T-3 h r s , 30 mins*
Depart Manned Spacecraft Operations Buildi n g for LC-39 v i a crew transfer van
T-3 hrs. 14 m i n s .
Arrive a t LC-39
T-3 hrs. 10 a n s .
Enter Elevator t o spacecraft l e v e l
T-2 hrs. b mins.
Start f l l g h t crew ingress
T-1 h r .
55 mins.
Mission Control Center-Houston/spacecraft
cornmad checks
T-1 hr. 50 mins,
Abort advisory system checks
T-1hr, 46 mins.
Space vehicle Ebergency Detection System
T-43 mins.
Retrack Apollo access arm t o standby
p o s i t i o n (12 degrees)
T-42 mins,
Ann launch escape system
T-40 mins,
Final launch v e h i c l e range safety checks
(to 35 mins, )
T-30 mins,
Launch v e h l c l e power t r a n s f e r test
( ~ m tiest
)
LM switch over t o internal power
T-20 mins.
Shutdown U
l o p e r a t i o n a l instrumentation
T-15 mins,
Spacecraft t o i n t e r n a l power
T-6 rnins.
Space v e h i c l e f i n a l s t a t u s checks
to
T-10 rnlns.
T-5 mins. 30
set,
Am d e s t r u c t system
T-5 mins.
Apollo access arm fully retracted
T-3 mins. 10 sec,
I n i t i a t e f i r i n g command (automatic sequencer)
T-50 see.
Launch v e h i c l e t r a n a f e r to i n t e r n a l power
�T-8.9
see.
Ignition sequence start
A l l engines running
Liftoff
*Note:
Some ckianges i n the above countdown are possible as a
r e s u l t of experience gained i n the Countdown Demonstration
T e s t (C9M') which occurs about 10 days before launch.
�lUCSSION TRAJECPORY AND BUUEWER DESCRIPTION
Q
Note; Information presented herein is based upon a
May 1 launch and is subject t o change p r i o r ta the mission
or i n real time during the mission t o meet changing conditions,)
Iaunch
Apollo 10 vdll be launched fran Kennedy Space Center Launch
Complex 39B on a launch azimuth that can vary from 7 2 degrees to
108 degrees, depending upon the t3me of day of launch, The
azimuth changes with time of day t o perfnit a fuel-optimum injection
frm Earth paI?king o r b i t i n t o a free-return circumlunar trajectory,
O t h e r factors influencing thelaunch windows are a daylight launch
and proper Sun angles on lunar landing sites.
The planned Apollo 10 launch date of Hay 18 w i l l c a l l f o r
l i f t o f f a t 12:49 p.m. Efi on a launch azimuth of 72 degrees,
Insertion i n t o a 100-nautical-=mile
circular Earth parking o r b i t
w i l l occur at 11 mlrmtes 53 seconds ground elapsed frun launch
(GET), and t h e resultant o r b i t will be,inclZnd 32.5 degrees to
the Earth's equator.
�FLIGHT PROFILE
TRANSEARTH lNJECTlON BURN
CSM/LM SEPARATION
LM PI-IASING BURN
EARTH PARKING ORBIT
CSM60N.MI.
S-IVB RESTART
CSM 60
DURING 2ND
OR 3RD ORBIT
CM SPLASHDOWN
& RECOVERY
S-IVB 2ND BURN CUTOFF
TRANSLUNAR INJECTiON
-IVB RESIDUAL
/
S/C
SEPAR~TION',
TRANSPOSITION,
DOCKING & EJECTION
(SLINGSHOT)
60 N.M.
LUNAR OF
.
LUNAR ORBlT
ClRCUlARIZATION
�SPACE VEHICLE LAUNCH EVENTS/WEIGH!?'S
Hrs.
00
00
00
00
00
00
00
00
00
00
00
00
00
i!
0
3
CC
I
00
00
00
00
Time
Min.
00 (-)08.9
00
00
12
00
21
01
92
32
02
02
.
Altitude
Sec.
15
40
41
42
11
03
03
03
07
09
09
09
16
21
39
14
15
18
11
11
43
53
:
Event
:
Ignition
F i r s t Motion
T i l t Initiation
Maximum Dynamic Pressure
Center Engine Cutoff
Outboard Engines Cutoff
S-IC/S-II Separation
S-I1 I g n i t i o n
S-11 A f t I n t e r s t a g e J e t t i s o n
LES J e t t i s o n
I n i t i a t e IGM
S-I1 Center Engine Cutoff
S-I1 Outboard Engines Cutoff
S-II/S-IVB
Separation
S-IVB I g n i t i o n
S-IVB F i r s t Cutoff
Parking O r b i t I n s e r t i o n
Naut
~ e l o c l t y 'deight
: Pounds
M i . : Knots
0 .OO
0 .033
0.12
7
24
35
36
37
49
51
53
97
102
102
102
103
103
0
"0
*3
1554
3888
5324
5343
5335
5581
5642
5701
10977
13427
13434
13434
15135
15139
6,499,016
6,412,918
.
I
)
985
2,43;,
1,842,997
1,465,702
1,465,123
-..
.
I
,
644,128
471,494
364,429
364,343
295,153
295,008
*First two v e l o c i t i e s are space f i x e d ,
Others are inertial v e l o c i t i e s . Vehicle
on launch pad has i n e r t i a l v e l o c i t y of 408.5 meters p e r second (793.7 knots).
The above figures a r e based on a launch azimuth of 72 degrees.
a l l g h t l y f o r o t h e r azimuths.
Figures w i l l vary
�Apollo 10 l i e s i a n Events
Event
-
Qmund Elapsed Time
hr8:rIn: 8eC
Date 6c lima
v
Purpose and (Resultant Orbit)
Insertion into 100 nm c i r o u l a r
EM.
Insertion
Injection i n t o free-return
translunar traJectory with
60 arn pericynthion.
CSH separatio?:, docking
?Iard-mating
Ejection from SLA
Separates CSM-LbI Prom S-IVB/
SLA.
SPS evasive maneuver
Frovides separation p r i o r t o
f-IVE propellant dump and
slingshotn mBnBuver.
6 lidcourse
2
correction No. 1
' ,Midcourse correction
No. 2
TJd +9 hrs.
%
+24 I
&a.
Ridcourse cormction No. 3
LC1 -22 h r s ,
Mldcour~ecorrection No. 4
LO1 -5 hre.
Of
CSM and LSI.
* These
midcourse corrections
have a nomlnal velocity change
of 0 fps, but w i l l be c a l culated in r e a l time t o eorr e c t 'PLIT: dispersions. LQCC-3
w i l l have a plane change
component t o achieve desired
lunar o r b i t Inclination.
Lunar Orbit Insertion No. 1
I n s e r t s Apollo 10 i n t o 60x170
nm e l l i p t i c a l lunar o r b i t .
huuw Orbit InsertSon No. 2
Circularizes lunar parking
o r b i t t o 60 nm.
CSlrI-IX undoaklng; separation
Establishes equiperiod o r b i t
f o r 2 nm separation
(mini~ootball).
Descent o r b i t insertion (DPB)
Lower LH pericynthion t o eight
nm (8x60).
(SM RCS)
,
g
I
�Xvent
-
Date
& The
Purpose and (Resultant Orbit1
7Enr)
DPS phasing bum
Raises JN apocynthlon to
194 nm, allows OSM t o ass
a d overt*
(8x197.
AP8 Insertion gum
Siaulates I . ascent I n t o
lunar o r b i t a f t e r landing
(8~43.6).
LH RCS concentria sequenae
ini:late (CSI) burit
Raises M pericynthion t o
46.2 nm, adjusts o r b i t a l
shape f o r rendeevms sequence
(42. w46.2)
Radially dowmard bum adJusts IA t o constant 15 nm
below CSH.
1l1 RCS conatant d e l t a height
(om)burn
6 L1I RCS terminal phase
7 (WI) h r n
Initiate
.
I1I thTYLsts along l i a a - O f -
s&ht t o w a r d CSM, mldoourse
and braking manepvors, a s
neoessam.
m0-W
~ b s f e back
r
to E)SM (about
107 om).
APS burn ta depletion
Poaigrade APS depletion bum
near I# perloynthion i g j e c t s
X.#l asoent s t q e into heliooentrla orbit.
Transearth injection (%I)
SP8 bum
~ n j e a t sCSM into Slf-hour
transearth t r a j e a t a q .
I
5
�Ground
Elapsed Tiae
hmr:mlm: see
Bate h Tirw,
(EBT)
Midcourse correction Ilo. 5
!fSI
+15 hrs.
5/24
5: 09 gas
Midoaur~ecorrrrution XQ. 6
m e -~15 ~hrs.
5/25
5: 39 pas
Xidcourse oorreotion Ha. 7
&try
5/26
5: 39 w
WS?!
reparation
Entry Interface (400,680 feet)
- 3 ~lrs.
Parpose and (lle~)ulbntOrbit)
--
* Tmwearth mLdoourse
earrootloma w i l l be omin real tlma for
entry oomidor contwl
and for adjusting landing
poiat to avoid recover~r
area foul weather.
Reentry condition.
got4
Command module enters
BartR(a aenaible ataosphere a t 36,310 fps.
an ding: 1,285 na domrsly.
iFo1p entry, 15 degree8
seven airmtas South
latitude x 165 degrees
West longitude.
�The crew f o r t h e first t i m e w i l l have a backup t o launch
v e h i c l e guidance d u r i n g powered f l i g h t , If t h e S a t u r n i n s t r u ment u n i t i n e r t i a l platform f a i l s , t h e crew can switch guidance
t o the command module computer f o r f i r s t - s t a g e powered f l i g h t
automatic c o n t r o l . Second and t h i r d stage backup guidance i s
through manual takeover i n which command module hand c o n t r o l l e r
i n p u t s a r e f e d through t h e command module computer t o t h e Saturn
instrument u n i t ,
Apollo 10 w i l l remain i n E a r t h parking o r b i t f o r one-andone-half r e v o l u t i o n s a f t e r i n s e r t i o n and w i l l hold a l o c a l
h o r i z o n t a l a t t i t u d e d u r i n g t h e e n t i r e period. The crew w i l l
p e r f o m s p a c e c r a f t s stems checks i n p r e p a r a t i o n f o r t h e t r a n s l u n a r i n j e c t i o n (TLI burn. The f i n a l "go" f o r the TLI burn
w i l l be given t o t h e crew through t h e Carnarvon, A u s t r a l i a ,
Manned Space F l i g h t Network s t a t i o n ,
3
Midway through t h e second r e v o l u t i o n i n Earth parking
o r b i t , t h e S-IVB t h i r d - s t a g e engine w i l l r e i g n i t e a t two hours
33 minuees 26 seconds Ground Elapsed Time (GET) over f i u s t r a l i a
t o i n j e c t Apollo 1 0 toward t h e Moon, The v e l o c i t y w i l l i n c r e a s e
f p s ) t o 35,651 f p s a t TLI c u t o f f
from 25,593 feet-per-second
a v e l o c i t y i n c r e a s e of 1O,O5 f p s , The TLI burn w i l l p l a c e t h e
s p a c e c r a f t on a f r e e - r e t u r n circumlunar t r a j e c t o r y f rorn which
midcourse c o r r e c t i o n s could be made with t h e SM r e a c t i o n
c o n t r o l system t h r u s t e r . Splashdown f o r a f r e e - r e t u r n t r a j e c t o r y
would be a t 6:37 porn4 EDT May 24 a t 24.9 degrees South l a t i t u d e
by 84,3 degrees E a s t l o n g i t u d e a f t e r a f l i g h t time of 149 hours
and 49 minutes,
--
Q
Transposition, Docking and E j e c t i o n (TM)
A t about t h r e e hours a f t e r l i f t o f f and 25 minutes a f t e r
t h e TLI burn, t h e Apollo 1 0 crew w i l l s e p a r a t e t h e command/
s e r v i c e module from t h e s p a c e c r a f t l u n a r module a d a p t e r (SLA),
thmst o u t away from t h e S-IVB, t u r n around and move back i n
f o r docking w i t h t h e l u n a r module. Docking should t a k e place
a t about t h r e e hours and t e n minutes GET, and a f t e r t h e crew
c o n f i m s a l l docking l a t c h e s s o l i d l y engaged, they w i l l connect
t h e CSM-to-W u m b i l i c a l s and p r e s s u r i z e t h e LM with t h e command
module surge tank. A t about 4:09 GET, docked s p a c e c r a f t w i l l
be e j e c t e d from t h e s p a c e c r a f t LM a d a p t e r by s p r i n g d e v i c e s a t
the four
landing g e a r " k n e e H a t t a c h p o i n t s , The e j e c t i o n
springs w i l l i m p a r t abput one fps v e l o c i t t o t h e s p a c e c r a f t .
A 19.7 f p s s e r v i c e propulsion system (SPS e v a s i v e maneuver
i n plane a t 4:29 GET w i l l s e p a r a t e t h e s p a c e c r a f t t o a s a f e
d i s t a n c e f o r t h e S-IVB " s l i n g s h o t " maneuver i n which r e s i d u a l
l i q u i d p r o p e l l a n t s w i l l be dumped through t h e 3-2 engine b e l l t o
propel t h e s t a g e i n t o a t r a j e c t o r y passing behind t h e Moon's
t r a i l i n g edge and on i n t o s o l a r o r b i t .
T
�SPACE VEHICLE EARTH PARKING ORBIT CONFIGURATION
(SATURN V THIRD STAGE AND INSTRUMENT UNIT, APOLLO SPACECRAFT)
�0
10
LUNAR ORB I T INSERTION
LUNAR ORB I T
20
80
30
40
50
60
70
90
100
TRANSEARTH 'INJECTION
110
120
130
140
150
LAUNCH
160
170
180
193
200
SPLASHDOWN
GROUND ELAPSED TlME (HOURS)
SPACECRAFT ALTITUDE VS. T l M E
�':
25
VELOCITY3
(MPH x 10
10
36
24
VELOC ITY
(FTISEC)
(lo3,
,
5
0
0
0
40
80
120
160
200
TRANSLUNAR VELOCITY PROFILE
240
�POST TLI TIMELINE
T L I + 2 0 SEC
-:ORBIT RATE
T L I + 2 5 MlN SC
INITIAL SEPARATION
(1 F P S )
T L I t 2 7 MIN
NULL SEPARATION
RATE AND PITCH
TO DOCKING
ATTITUDE
LM WITHDRAWAL
-20 FPS
�T r a n s l u n a r Csast
Up t o f o u r midcourse c o r r e c t i o n burns a r e planned
d u r i n g t h e t r a n s l u n a r c o a s t phase, depending upon the accuracy
of t h e t r a j e c t o r y r e s u l t i n g from the TLI maneuver. If required;
the midcourse c o r r e c f i o n burns are planned a t TLI +g hours,
TLI +24 hours, l u n a r o r b i t i n s e r t i o n (LOI) -22 hours and LOX
-5 hours.
During c o a s t p e r i o d s between midcourse c o r r e c t i o n s , t h e
s p a c e c r a f t w i l l be i n t h e p a s s i v e thermal c o n t r o l (PTC) o r
"barbecue" mode i n which t h e s p a c e c r a f t w i l l r o t a t e s l o w l y about
one a x i s t o s t a b i l i z e s p a c e c r a f t thermal r e s p o n s e s p a c s t o t h e
continuous s o l a r exposure.
Midcourse c o r r e c t i o n s 1 and 2 w l l l n o t normally be made
u n l e s s the p r e d i c t e d Mission Control Center 3 v e l o c i t y change
i s g r e a t e r t h a n 25 feet-per-second.
Lunar O r b i t I n s e r t i o n (WI)
The f i r s t of two l u n a r o r b i t i n s e r t i o n burns w i l l be
made a t 75:45:43 GET a t a n a l t i t u d e of 89 lllg above t h e Moon,
LOI-1 w i l l have a nominal r e t r o g r a d e v e l o c i t y change of 2,974
f p s and w i l l i n s e r t Apollo 10 i n t o a 60x170-nm e l l i p t i c a l
l u n a r o r b i t . LOI-2 two o r b i t s l a t e r a t 80:10:45 GET w i l l c3.r-
c u l a r i z e t h e o r b i t t o 60 nm. The burn w i l l be 138.5 f p s r e t r o grade. Both LO1 maneuvers w i l l be w i t h t h e SPS engine n e a r
p e r i c y n t h i o n when t h e s p a c e c r a f t i s behind t h e Moon and o u t
of c o n t a c t w i t h MSPN s t a t i o n s .
Lunar Parking O r b i t (LPO) and IN-Active Rendezvous
Apollo 1 0 w i l l remain i n l u n a r o r b i t about 61.5 hours,
and I n a d d i t i o n t o t h e LEP d e s c e n t t o eight n a u t i c a l m i l e s
above t h e l u n a r s u r f a c e and subsequent rendezvous w i t h t h e
CSM, e x t e n s i v e l u n a r landnark tracking t a s k s w i l l be performed
by t h e crew,
Following a r e s t period a f t e r t h e l u n a r o r b i t c i r c u l a r i z a t i o n , t h e LH w i l l be manned by t h e command and l u n a r module
p i l o t and p r e p a r a t i o n s begun f o r undocking a t 98:10 GET. Some
25 minutes of s t a t i o n keeping and CSM i n s p e c t i o n of the IM will
be followed by a 2.5 f p s r a d i a l l y downward SM RCS maneuver, plati n g t h e I24 and CSM i n e q u i e r i o d o r b i t s w i t h a maximum s e p a r a t i o n
A t t h e midpoint of t h e m i n i f o o t b a l l ,
of two m i l e s ( m i n i f o p t b a l l
the
descent propulsion system (DPs) w i l l be f i r e d r e t r o g r a d e
71 f p s a t 99:34 GET f o r t h e descent o r b i t i n s e r t i o n (DOI) t o
lower LM p e r i c y n t h i o n t o e i g h t miles. The DPS engine w i l l be
f i r e d a t 10 p e r c e n t t h r o t t l e s e t t i n g f o r 1 5 seconds and a t 40
p e r c e n t f o r 13 seconds,
7.
�LUNAR ORBIT INSERTION
101- 1
LO1 - 2
I
EARTH
EARTH
�LUNAR ORBIT ACTIVITIES
LM A C T I V E
RENDEZVOUS
LM C ; O
AND
LANDMARK
S
RN
31
I
SEP PHAS
STRl P
PHOTO
1 AND 2
T g . 0.
33
I
h)
0
d
4
LANDMARK
TRACKING
I
I
TEI
STRIP
PHOTO
3
�24.5 DEG PlTCH DOWN
FROM LOCAL HORIZONTAL
OVER LANDMARK
2 DEG PITCH DOWN
FROM LOCAL HORIZONTAL
BEGIN 0.3 DEGPEC PITCH
DOWN AT A05
'a
PITCH DOWN 47 DEG FROM
AT, = 296 SEC
-
a T 2 40 SEC
AT3 = 25 SEC
A Tq =
25 SEC
AOS TO LOS = 3 MIN TOTAL
I
C S M / L M TYPICAL L A N D M A R K T R A C K I N G PROFILE
�APOLLO 10 RENDEZVOUS SEQUENCE
�COMPARISON OF F A N D G LM OPERATIONS PHASE
RENDEZVOUS
MANEUVERS
UNDOCKING
ilNG
I
I
\
SEPARATION
F
UNDOCKING
G
RENDEZVOUS
DOCKING
INSER
LM
LIFTOFF
RENDEZVOUS
MANEUVERS
k
8
�@lLM (DO1 DESCENT ORB IT INSERTION MANEUVER
I
MSFN
AOS
MSFN
LOS
SURFACE DARKNESS
SC DARKNESS
Ib
0
'?
T
+
k/ -,
\ (DO11
' ~ ~ ~ ~ FAND
+ ~BEHIND
'.
:TSEPARATION
~ I R E C T I Ok+
N
OF MOTION I\
I MOTION OF
~
o
~
"PL1.8 N. MI.
/
t
EARTH
LM RELATIVE TO CSM
MOON
CSM/LM SEPARATION MANEUVER
�LUNAR MODULE DESCENT ORBIT INSERTION
@ LM
DESCENT ORB I T INSERTION
(DO1 MANUEVER,
RETROGRADE,
DP,~S
TO
d
C1
0
I
200 N. MI.
I
-a
LM BELOW
A N D AHEAD
1
- 1-
LM BELOW
-a
(PHASING)
LANDING SITE
54 000 FT.
\
ABOVE
LANDING SITE RAD IUS
MOON
�ORBIT RATE (0.05 DEG/sEC PITCH DOWN) FROM -400 to 200 FROM PERlCYTHlON
O€iSERW
CANDING
SITE
(PHOTOGRAPIO
CHECKOUT LANDING
O8SERVE LUNAR
YAW RIGHT180 DEG AND plrcn up
NEAR LUNAR SURFACE ACTIVITY
MANEUVER 10 RIASlNG
BURNATTITUDE
�A s t h e W passes over Apollo landing S i t e 2, t h e IN
landing radar w i l l be t e s t e d i n t h e a l t i t u d e mode but not i n
descent r a t e , About 10 minutes a f t e r t h e pass over S i t e 2,
t h e 195 f p s DPS phasing burn a t 100:46 GET w i l l boost t h e IM
i n t o an 8x194-nm o r b i t t o allow the CSM t o overtake and pass
t h e M , The phasing burn i s posigrade and t h e DPS engine is
f i r e d a t 10 per cent t h r o t t l e f o r 26 seconds and f u l l t h r o t t l e
f o r 17 seconds, The phasing burn places t h e LM i n a l'dwellll
o r b i t which allows t h e CSN t o overtake and pass t h e LPI s o that
a t t h e second LM passes over S i t e 2, t h e I24 w i l l t r a i l t h e CSM
by 27 nm and w i l l be i n a proper p o s i t i o n f o r t h e i n s e r t i o n maneuver simulating ascent from t h e l u n a r surface a f t e r a landing
mission,
P r i o r t o t h e 207-fps M ascent engine retrograde i n s e r t i o n
burn, the Ilvl descent s t a g e w i l l be j e t t i s o n e d and an evasive
maneuver perfo~medby t h e ascent stage t o prevent recontact.
The i n s e r t i o n burn w i l l be made a t 102:43 CIET and w i l l lower
LM apocynthion t o 44.9 nra s o t h a t t h e LM i s 14.7 nin below and
148 rn behind t h e CSM a t t h e time of t h e concentric sequence
i n i t i a t e (CSI) burn.
Following IM radar tracking of t h e CSM and onboard
computation of t h e CSI maneuver, a 50.5 f p s IM RCS posigrade
burn w i l l be made a t a nominal time of 103:33 GET a t apocynthion and all l ~ g s u l ti n a 44.9~44.3-nm fM o r b i t , The IEI RCS
w i l l draw from t h e LM ascent propulsion system (BPS) propellant
tanks through t h e interconnect valves.
A 3.4 f p s r a d i a l l y downward U
l RCS constant d e l t a height
(cDH) maneuver a t 104:31 GET w i l l place t h e W on a c o e l l i p t i c
o r b i t 15 nm below that of t h e CSM and w i l l set up conditions
f o r t h e terminal phase i n i t i a t e (TPI) burn 38 minutes l a t e r ,
The T P I maneuver w i l l be made when t h e CSM i s a t a 26,6degree e l e v a t i o n angle above t h e M a s l o c a l h o r i z o n t a l following
continuing r a d a r tracking of t h e CSM and onboard computations
for t h e maneuver. Nominally, t h e T P I burn w i l l be a 24.6-fps
LM RCS burn along t h e l i n e of s i g h t toward t h e CSM a t 105:09 GET.
Midcourse c o r r e c t i o n and braking maneuvers w i l l place the XM and
CSM i n a rendezvous and station-keeping p o s i t i o n , and docking
should take place a t 106:20 GET t o complete a eight-and-a-half
hour sequence of undocked a c t i v i t i e s .
After t h e commander and lunar. module p i l o t have
t r a n s f e r r e d i n t o t h e CSM, the IM.w i l l be j e t t i s o n e d and t h e
CSM w i l l maneuver 2 fps r a d i a l l y upward t o move above and
behind the IN a t the t i m e of the W a s c e n t propulsion system
burn t o propellant d e p l e t i o n a t 108:39 GET.
�LUNAR MODULE PHASING MANEUVER
I N. MI.
I
MOON
U\A PHAS ING MANEUVER
DPS- FULL THROTTLE
LANDING
S ITE
�LUNAR MODULE INSERTION MANEUVER
MSFN
I
147
270
N.MI. N. MI.
I
n
I
\
15 N. MI.--/
I
(CSI)
I
MSFN
AOS
I
I
(RETROGRADE, APS)
\
\
.-4
I
--I 51
.
I
MOON
N.
;O
*L MI.
/
@ LM INSERTION MANEUVER
INSERTION
�LUNAR MODULE
CONCENTRIC SEQUENCE INITIATION MANEUVER
@cs I MANEUVER
,/-0>.
..
/
\ 4 ; . - 4 15
- N.
MI.
'\
MSFN
LOS /
I
/
1
I
147 N. MI.
\
(CSI)
\\
'15 N.MI~,&, ( T P(CDH)
I)
AOSt
MOON
I
/
,/
�LUNAR MODULE CONSTANT
DIFFERENTIAL HEIGHT AND TERMINAL PHASE MANEUVERS
RENDEZVOUS AND
@ T P I MANEUVER
(MIDPOINT OF DARKNESS)
LM RCS
8
cj
(0
I
BRAKING
I
-45
75 N. MI.
30 N. M I .
1
I
I
MINI
\
1\\,
15 N MI
\26.b0
TPI
LOOK ANGLE TO CSM
36 MIN
CDH
I-@
CDH MANEUVER
�The burn w i l l be ground-coamanded,
An estiwated 3,837-Pps
posigrade v e l o c i t y w i l l be imparted by t h e APS d e p l e t i o n burn
near Uf pericynthion t o place t h e IN a s c e n t s t a g e i n a h e l l o centric orbit,
h a d d i t i o n a l 29 hours w i l l be spent i n l u n a r o r b i t
before t r a n s e a r t h i n j e c t i o n while t h e crew conducts l u n a r
landmark t r a c k i n g t a s k s and makes photographs of Apollo landing sites.
TransearBh I n j e c t i o n (TEI)
The 54-hour r e t u r n t r i p t o Earth begins a t 137:20 GET
when the SPS engine i s f i r e d 3622.5 fps posigrade f o r the TEI
burn, L i k e LOI-1 and LOI-2, t h e T E I burn w i l l be made when t h e
s p a c e c r a f t i s behind the Moon and out of touch w i t h MSFN s t a t i o n s .
Transearth Coast
Three c o r r i d o r - c o n t r o l t r a n s e a r t h midcourse c o r r e c t i o n
b u m s w i l l be made i f needed: MCC-5 a t TEI +35 hours, MCC-6
a t entry interface (EI=400,000 f e e t ) -15 hours and a t E I -3 hours,
Entry, Laodine
Apollo 10 w i l l encounter t h e E a r t h ' s atmosphere (400,000
f e e t ) a t 191:50 GET a t a v e l o c i t y of 36,310 f p s and w i l l land
some 1,285 nm downrange from t h e e n t r y - i n t e r f a c e p o i n t using
the s p a c e c r a f t ' s l i f t i n g c h a r a c t e r i s t i c s t o reach t h e landing
p o i n t . Touchdown w i l l be a t l92:O5 GET a t 15 degrees 7 minutes
South l a t i t u d e by 165 degrees West longitude.
�EARTH ENTRY
ENTRY RANGE CAPABILITY
*
NOMINAL ENTRY RANGE
-
1200 TO 2500 N. MI.
- 1 2 8 5 N.
MI.
SHORT RANGE SELECTED FOR NOMINAL MISSION BECAUSE:
e RANGE FROM ENTRY TO lANDlNG CAN B E SAME FOR
PRIMARY AND BACKUP CONTROL MOPES
PRIMARY MODE EASIER TO MONITOR WITH SHORT RANGE
WEATHER AVOIDANCE, WITHIN ONE DAY PRIOR TO ENTRY, I S
ACHIEVED USING ENTRY RANGING CAPABILITY TO 2500 N. MI.
UP TO ONE DAY PRIOR TO ENTRY USE PROPULSION SYSTEM
TO CHANGE LANDING POINT
r:
E'
t
�VELOCITY AT ENTRY INTERFACE
36.5 x l o 3
LAUNCH W INDOW CLOSED
VELOC l TY
4
2I
LAUNCH WI NDOW OPEN
(FPS
18
20
24
L A U N C H D A T E (MAY)
23
25
�GEODETIC ALTITUDE VERSUS RANGE TO GO
400
NOTE: T I M E T I C K E D E V E R Y 1/2 MLN
FROM E N T R Y INTERFACE
ENTER S-BAND BLACKOUT
320
240
A3
8
88
h)
0
8
ALTITUDE
(1000 FT)
160
E*XIT S-BAND BLACKOUT
DROGUE PARACHUTE DEPLOYMENT
80
MAIN PARACHUTE DEPLOYMEN
TOUCHDOWN.
0
1400
1200
1000
800
600
400
200
R A N G E TO SPLASHDOWN, (Nautical Miles)
0
�DROGUE
CHUTES
PILOT CHUTES
CHUTE
SPLASH DOWN VELOCITIES:
3 CHUTES
2 CHUTES
- 31 FT/SEC
- 36 FT/ SEC
- _
- - --
AFTER TOUCHDOWM
--
--
- -
--
-
-
-
E A R T H RE-ENTRY AND LANDING
�ACTIVITY D A Y
1
REST PERIODS
DATE/DAY'
ED7
LUNAR REVOLUTION N O .
1
GET
0
1
8
12
12
6
16
20
24
28
6
24
32
36
40
12
44
-
I
Q
18
52
56
60
I
MAY 21 -WEDNESDAY
24
6
64
12:so
68
1
4 LO1 D A Y
I
MAY 20 -TUESDAY
I8
I
3
2
MAY I 9 MONDAY
24
IS
4
- -
-
MAY
SUNDAY
I8
12 48
APOLLO 10
SUMMARY FLIGHT PLAN
n
18-50
74
I
2
76
78
6
- THURSDAY
I
I
1MO
18
6
3
4
5
6
7
8
9
10
11
12
13
14
IS
16
17
18
80
82
84
86
88
w
92
94
96
$0
IW
102
IM
106
la,
110
19
112
20
I14
12254
21
116
:8
i
22
23
24
118
~ z o 122
a? 26
I 4
1%
M A Y 24
24
v
28
128
130
29
132
I
7 TEl D A Y
I
MAY 23 -FRIDAY
24
- -
I
I
MAY 22
24
-
:6
5 DO1 DAY
-
M
134
31
136
I
SATURDAY
1250
b
1
8
I8
MAY 25
24
6
- SUNDAY
12
I
9
18
10
MAY 26 -MONDAY
24
6
12.52
32
138
YO
I42
144
148
152
156
160
164
168
172
176
180
I84
I@
192
LM MANEUVER DATA
81. 15.6 SEC
AV: 24.6 FPS
NO ULLAGE
LM
(SNOOPY)
(CHARLIE BROWN)
C S M MANEUVER D A T A
1-5
�RECOVERY OPERATIONS
The primary recovery l i n e f o r Apollo 10 i s i n t h e mtdP a c i f i c a l o n g t h e 175th West meridian of longitude above 15
degrees North l a t i t u d e , and jogging t o 165 degrees West
l o n g i t u d e below t h e Equator. The h e l i c o p t e r c a r r i e r USS
P r i n c e t o n , Apollo 10 prime recovery v e s s e l , w3 11 be s t a t i o n e d
n e a r t h e end-of-mission aiming p o i n t .
Splashdown f o r a f u l l - d u r a t i o n l u n a r o r b i t mission launched
on time May 18 w i l l be a t 5 d e g r e e s 8 minutes South by 165
degrees West a t a ground e l a p s e d time o f 192 hours 5 minutes.
The l a t i t u d e o f splashdown depends upon t h e time of t h e
t r a n s e a r t h i n j e c t i o n burn and t h e d e c l i n a t i o n o f t h e Moon a t
t h e t i m e o f t h e burn. A s p a c e c r a f t r e t u r n i n g from a l u n a r
f l i g h t w i l l e n t e r E a r t h ' s atmosphere and s p l a s h down a t a p o i n t
on E a r t h d i r e c t l y o p p o s i t e t h e Moon.
T h i s p o i n t , c a l l e d t h e a n t i p o d e , i s a p r o j e c t i o n of a l i n e
from t h e c e n t e r o f t h e Moon through t h e c e n t e r o f t h e Earth t o
t h e s u r f a c e o p p o s i t e t h e Moon. The mid-Pacific recovery l i n e
r o t a t e s through t h e a n t i p o d e once each 24 hours, and t h e t r a n s E a r t h i n j e c t i o n burn w i l l be t a r g e t e d f o r splashdown along t h e
p r i m s y recovery l i n e .
Other planned recovery l i n e s f o r a deep-space mission a r e
t h e E a s t P a c i f i c l i n e extending roughly p a r a l l e l t o t h e c o a s t l i n e s o f North and South America; t h e A t l a n t i c Ocean l i n e running a l o n g t h e 3 0 t h West meridian i n t h e n o r t h e r n hemisphere
and a l o n g t h e 2 5 t h West meridian I n t h e s o u t h e r n hemisphere;
t h e I n d i a n Ocean l i n e a l o n g t h e 6 5 t h E a s t meridian; and t h e
West P a c i f i c l i n e along t h e 150th East meridian i n t h e n o r t h e r n
hemisphere and jogglng t o t h e 170th E a s t meridian i n t h e
s o u t h e r n hemisphere.
Secondary landing areas f o r a p o s s i b l e Earth o r b i t a l
a l t e r n a t e mission have been e s t a b l i s h e d i n two zones--one i n
t h e P a c i f i c and one i n t h e A t l a n t i c .
Launch a b o r t landing areas extend downrange 3,400 n a u t i c a l
m i l e s from Kennedy Space C e n t e r , fanwise 50 n a u t i c a l m i l e s above
and below t h e l i m i t s o f t h e v a s i a b l e launch azimuth ( 7 2 degrees 107 d e g r e e s ) . Ships on s t a t i o n i n t h e launch a b o r t a r e a w i l l
be t h e d e s t r o y e r USS Rich, t h e i n s e r t i o n t r a c k i n g s h i p USNS
Vanguard and t h e a t t a c k t r a n s p o r t USS C h i l t o n .
I n a d d i t i o n t o t h e primary recovery v e s s e l steaming up and
down t h e mid-Pacific recovery l i n e and s u r f a c e v e s s e l s on t h e
A t l a n t i c Ocean recovery l i n e and i n t h e launch a b o r t a r e a , 14
HC-130 a i r c r a f t w i l l be on standby a t seven s t a g i n g bases around
t h e Earth: Guam, Pago Pago, American Samoa; H a w a i i , Bermuda;
L a j e s , Azores; Ascension I s l a n d ; M a u r i t i u s and t h e Panama Canal
Zone.
�Apollo 10 recovery operations w i l l be d i r e c t e d from t h e
Recovery Operations Control Room i n t h e Mission Control
Center and w i l l be supported by t h e A t l a n t i c Recovery Control
Center, Worfolk, Va., and t h e P a c i f i c Recovery Control Center,
Kunla, H a w a i i .
The Apollo 10 crew w i l l be flown from t h e primary r e covery v e s s e l t o t h e Manned Spacecraft Center a f t e r recovery.
The s p a c e c r a f t w i l l r e c e i v e a preliminary examination, s a f i n g
and power-down aboard t h e Princeton p r i o r t o offloading a t
Ford I s l a n d , H a w a i i , where t h e s p a c e c r a f t w i l l undergo a more
complete d e a c t i v a t i o n . It i s a n t i c i p a t e d t h a t t h e s p a c e c r a f t
w i l l be flown from Ford I s l a n d t o Long Beach, C a l i f . , within
72 hours, and then trucked t o the North American Rockwell
Space Division p l a n t i n Downey, Calif., f o r p o s t f l i g h t a n a l y s i s .
�APOLLO 10 ALTmNATE MISSIONS
Five a l t e r n a t e mission p l a n s have been prepared f o r t h e
Apollo 10, each depending upon when i n t h e mission time l i n e
it becomes necessary t o switch t o the a l t e r n a t e , Testing of
t h e lunar module and a m - a c t i v e rendezvous i n E a r t h o r b i t
a r e p r e f e r r e d over a CSM-only flyby mission. When it is
impossible t o r e t u r n t o a low Earth o r b i t with rendezvous,
a h i g h - e l l i p s e LM t e s t i s p r e f e r r e d over a low Earth o r b i t
test.
Where p o s s i b l e , Apollo 10 a l t e . r n a t e missions follow the
l w r o r b i t mission time l i n e and have a d u r a t i o n of about 10
days.
Apollo 10 a l t e r n a t e missions a r e summarized as follows:
A l t e r n a t e 1: Early shutdown of S-IVB during TLI with
r e s u l t i n g apogee l e s s than 25,000 n a u t i c a l miles, o r f a i l u r e
of S-IVB t o i n s e r t s p a c e c r a f t i n t o Earth parking o r b i t and
subsequent SPS contingency o r b i t i n s e r t i o n (COI), and in both
cases no LM e x t r a c t i o n possible. A l t e r n a t e maneuvers would
inc lude :
'
*
SPS phasing burn t o o b t a i n ground coverage of simulated
*
*
Simulated L O 1 burn t o a 100x400 nm Earth o r b i t .
lunar o r b i t i n s e r t i o n .
Midcourse c o r r e c t i o n s t o modify o r b i t t o 90x240 nm
end-of-mission e l l i p s e and t o complete SPS lunar mission duty
cycle during remainder of ten-day mission.
A l t e r n a t e 2: S-IW3 f a i l s during TLI burn and r e s u l t i n g
apogee i s between 25,000 and 40,000 n a u t i c a l m i l e s ; no LM
e x t r a c t i o n . Maneuver sequence would be:
* SPS phasing burn t o o b t a i n ground coverage of simulated
lunar o r b i t insertion.
*
*
Simulated LO1 burn t o a semi-synchronous Earth o r b i t .
SPS phasing maneuver t o place a l a t e r perigee over o r
opposite d e s i r e d recovery zone.
* SPS maneuver t o place CSM i n semi-synchronous o r b i t with
a 12-hour period.
* Deorbit d i r e c t l y from semi-synchronous o r b i t into Pacific
recovery a r e a (ten-day mission).
�Alternate
No
burn o r
d
u l l y extracted,
:
but
TLI
T L I apogee less than 4,000
mi
success
*
*
*
*
Simulated LO1 burn to lOOxk.lO-nm o r b i t ,
+
IN-active rendezvous,
Simulated descent o r b i t inserstion (DOI) maneuver with IN,
Simulated
powered descent i n i t i a t i o n (PDI) maneuver.
Two SPS burns to c i r c u l a r i z e CSM orbit; t o 3-50 run.
* Ground-commanded LM a s c e n t p r o p u l s i o n system (APs) b u r n
t o d e p l e t i o n under abort guidance system (AGS) control, similar
t o APS d e p l e t i o n burn i n Apo1l.o 9.
* Additional SPS burns t o place CSM in 90x2@-nm end-ofmission e l l i p s e and t o complete SPS l u n a r mission duty cycle
during remainder of ten-day mission,
�A l t e r n a t e 4: E a r l y S-IVB TLI c u t o f f w i t h r e s u l t i n g
apogee g r e a t e r than 4,000 nrn b u t l e s s than 10,000 nm, and
c a p a b i l i t y of SPS and LM d e s c e n t propulsion system t o g e t h e r
t o r e t u r n CSM-LW t o low E a r t h o r b i t without compromising
CSM1s a b i l i t y t o r e s c u e LM.
* SPS phasing burn t o obtain ground coverage of simulated
lunar o r b i t insertion.
* F i r s t docked DPS burn out-of-plane s i m u l a t e s d e s c e n t
orbit insertion.
*
*
*
Second docked DPS burn s i m u l a t e s power d e s c e n t i n i t i a t i o n .
*
SPS burns tc c i r c u l a r i z e CSM o r b i t a t 150
+
LM-active rendezvous.
SPS simulated L O 1 burn.
Phaslng maneuver t o o b t a i n ground coverage o f simulated
powered d e s c e n t i n i t i a t i o n .
ma.
* Ground-commanded
a s c e n t propulsion system burn t o
d e p l e t i o n under a b o r t guidance system (AGS) c o n t r o l , s i m i l a r t o
APS d e p l e t i o n burn i n Apollo 9 ,
*
A d d i t i o n a l S P S burns t o p l a c e CSM i n 90x240 nm end-ofmission e l l i p s e and t o complete SPS l u n a r mission d u t y c y c l e
d u r i n g remainder o f ten-day mission.
A l t e r n a t e 5: SPS and DPS j o i n t l y cannot p l a c e CSM-LM i n
low Earth o r b i t without compromising a b i l i t y o f CSM t o rescue
LPI i n a rendezvous sequence, and SPS f u e l q u a n t i t y is too low
f o r a CSM-LM circumlunar mission.
* SPS phasing burn t o o b t a i n ground coverage of simulated
lunar o r b i t insertion.
*
orbit.
Simulated l u n a r o r b i t i n s e r t i o n i n t o semisynchronous
* SPS p h a s i n g burn t o o b t a i n ground coverage o f simulated
power d e s c e n t i n i t i a t i o n .
*
First docked DPS burn o u t o f plane s i m u l a t e s d e s c e n t
o r b i t insertion.
* Second docked DPS burn s i m u l a t e s power d e s c e n t i n i t i a t i o n
and is d i r e c t e d o u t of plane.
�* SPS phasing burn t o place a l a t e r perigee over or
opposite desired recovery zone.
*
SPS maneuver to place CSM-LM insemi-synchronous orbit
with a 12-hour period,
* around-commanded LM ascent propulsion system burn t o
depletion under abort guidance system control; poslgrade a t
apogee.
* Additional midcourse corrections along a lunar mission
time line and d i r e c t entry from high ellipse,
�ABORT MODES
The Apollo 10 rni&lon can b e a b o r t e d at any time during
t h e launch phase o r terminated during l a t e r phases a f t e r a
successful insertion i n t o Earth o r b i t .
Abort modes can b e summarized as follows:
Launch phase
-
--
Mode I
h u n c h escape (LEs) tower p r o p e l s command module
away from launch v e h i c l e . This mode i s i n e f f e c t from about
T-45 minutes when LES i s armed u n t i l L E S ' j e t t i s o n a$ 3:07 GET
and command module l a n d i n g p o i n t C ~ J I range from the Launch
Complex 39B area t o 520 nm (600 sm, 964 km) downrange,
Mode 11
- Begins
when LES i s jetti'soned and r u n s u n t i l
the SPS can be used t o i n s e r t t h e CSM i n t o a s a f e E a r t h o r b i t
( 9 : 2 2 GET) o r u n t i l l a n d i n g p o i n t s t h r e a t e n t h e A f r i c a n c o a s t ,
Mode I1 r e q u i r e s manual s e p a r a t i o n , e n t r y o r i e n t a t i o n and f u l l l i f t e n t r y w i t h landing between 400 and 3,200 nm (461-3,560 s m ,
741-5,931 km) downrange.
-
Begins when f u l l - l i f t landing p o i n t reaches 3,200
Mode 111
nm (3,560 sm, 5,931 km) and extends through E a r t h o r b i t a l i n s e r t i o n ,
The CSM would s e p a r a t e fram t h e launch v e h i c l e , and I f necessary,
an SPS r e t r o g r a d e burn would b e made, and t h e command module wol~ld
be flown h a l f - l i f t t o e n t r y and landing a t approximately 3,350
nm (3,852 sm, 6,197 km) downrange.
-
Mode I V and Apogee Kick
Begins a f t e r t h e p o i n t t h e SPS could
b e used t o i n s e r t t h e CSM i n t o a n Earth p a r k i n g o r b i t
from about
9:22 GE2.
The SPS burn i n t o o r b i t would b e made two minutes a f t e r
--
s e p a r a t i o n from t h e S-IVB and t h e mission would continue as an
Earth o r b i t a l t e r n a t e . Mode I V i s p r e f e r r e d over Mode 111. A
v a r i a t i o n of Mode I V i s t h e apogee k i c k i n which t h e SPS would
be ignited a t f i r s t apogee t o r a i s e p e r i g e e f o r a safe o r b i t .
Beep Space Aborts
Translunar I n j e c t i o n Phase
--
Aborts during t h e t r a n s l u n a r i n j e c t i o n phase are only a
remote p o s s i b i l i t y , but if an a b o r t became necessary d u r i n g t h e
TLI maneuver, a n SPS r e t r o g r a d e burn could be made t o produce
s p a c e c r a f e e n t r y , T h i s mode of a b o r t would be used o n l y i n t h e
event of a n extreme emergency t h a t a f f e c t e d crew s a f e t y , The
s p a c e c r a f t landing p o i n t would vary with launch azimuth and l e n g t h
of t h e TLI burn, Another TLI a b o r t s i t u a t i o n would be used if a
malfunction cropped up a f t e r i n j e c t i o n . A r e t r o g r a d e SPS burn
a t about 90 minutes a f t e r TLI s h u t o f f would allow t a r g e t i n g t o
land on t h e A t l a n t i c Ocean recovery l i n e ,
�Translunar Coast phase
--
Aborts a r i s i n g during t h e three-day t r a n s l u n a r c o a s t phase
would be similar i n n a t u r e t o t h e 90-minute TLI a b o r t . Aborts
from deep space b r i n g i n t o t h e p l a y t h e Moon's a n t i p o d e ( l i n e
p r o j e c t e d from Moon's c e n t e r through E a r t h ' s c e n t e r t o o p p o s i t e
f a c e ) and t h e e f f e c t of t h e E a r t h ' s r o t a t i o n upon t h e geographlcal
l o c a t i o n of t h e antipode. Abort times would be s e l e c t e d f o r landi n g when t h e a n t i p o d e c r o s s e s 1650 West l o n g i t u d e , The a n t i p o d e
c r o s s e s t h e mid-pacific recovery l i n e once each 24 hours, and i f
a t i m e - c r i t i c a l s i t u a t i o n f o r c e s an a b o r t e a r l i e r t h a n t h e s e l e c t e d
f i x e d a b o r t times, l a n d i n g s would be t a r g e t e d f o r t h e A t l a n t i c
Ocean, E a s t P a c i f i c , West P a c i f i c o r I n d i a n Ocean recovery l i n e s
i n t h a t o r d e r of preference. When t h e s p a c e c r a f t e n t e r s t h e Moon's
sphere of i n f l u e n c e , a circumlunar a b o r t becomes faster t h a n an
a t t e m p t t o r e t u r n d i r e c t l y t o Earth.
Lunar Orbit I n s e r t i o n phase
--
E a r l y SPS shutdowns during t h e l u n a r o r b i t i n s e r t i o n burn (MI)
a r e covered by t h r e e modes i n t h e Apollo 10 mission. A 1 1 t h r e e
modes would r e s u l t i n t h e CM l a n d i n g a t t h e E a r t h l a t i t u d e of t h e
Moon a n t i p o d e a t t h e time t h e a b o r t was performedt
Mode I would be a I24 DPS posigrade burn i n t o an Earth-return
t r a j e c t o r y about two hours ( a t next p e r i c y n t h i o n ) after an LO1
shutdown during t h e f i r s t two minutes of t h e LO1 burn.
%ode IT, f o r SPS shutdown between two and t h r e e minutes a f t e r
i g n i t i o n , would use t h e LM DPS engine t o a d j u s t t h e o r b i t t o a
s a f e , non-lunar impact t r a j e c t o r y followed by a second DPS posigrade
burn a t next p e r i c y n t h i o n t a r g e t e d f o r t h e mid-Pacific recovery
line.
Mode 111, from t h r e e minutes a f t e r LO1 i g n i t i o n u n t i l normal
c u t o f f , would a l l o w t h e s p a c e c r a f t t o c o a s t through one o r two
l u n a r o r b i t s b e f o r e doing a DPS posigrade burn a t p e r i c y n t h i o n
t a r g e t e d f o r t h e mid-pacific recovery l i n e .
Lunar O r b i t Phase
--
If d u r i n g l u n a r p a r k i n g o r b i t i t became necessary t o a b o r t ,
the t r a n s e a r t h i n j e c t i o n (TEI) burn would be made early and
would t a r g e t s p a c e c r a f t landing t o t h e mid-Pacific recovery l i n e .
T r a n s e a r t h I n j e c t i o n phase
--
m r l y shutdown of t h e T E I burn between i g n i t i o n and two m i n u t e s would cause a Mode I11 a b o r t and a SPS posigrade TEI burn
would be made a t a l a t e r p e r i c y n t h i o n . Cutoffs a f t e r two minutes
TEI burn t i m e would c a l l f o r a Mode I a b o r t - - - r e s t a r t of SPS as
soon as p o s s i b l e f o r E a r t h - r e t u r n t r a j e c t o r y , Both modes produce
mid-Pacific recovery l i n e l a n d i n g s n e a r t h e l a t i t u d e of t h e a n t i pode a t t h e time of t h e TEI burn.
�Transearth Coast phase
--
Adjustments of the landing point are possible during the
transearth coast through burns with the SPS or the service
module RCS thrusters, but in general, these are covered in
the discussion of transearth midcourse corrections. No abort
burns will be made later than 24 hours prior to e n t r y to avoid
effects upon GM entry velocity and flight path angle.
�A P O U o 10 GO/NO-GO DECISION POINTS
Like Apollo 8, Apollo 10 will be flown on a step-by-step
commit point or go/no-go basis in which the decisions will be
made prior to each major maneuver whether to continue che misston
or to switch 'to one of the possible alternate missions. The
go/no-go decisions will be made by the flight control teams in
Mission Control Center.
~o/no-go decisions will be made prior to the following events:
*
*
*
*
*
*
*
*
+
Launch phase go/no-go at 10 min. GEP for orbit insertion
Translunar injection
Transposition, docking and LM extraction
Each translunar midcourse correction burn
Lunar orbit insertion burns Nos. 1 and 2
Crew intravehicular transfer to M
CSM-LM undocking and separation
Hendezvous sequence
I&! Ascent Propulsion system burn to depletion
*
Transearth injection burn (no-go would delay TEI one or
more revolutions to allow maneuver preparations to be
completed. )
*
Each transearth midcourse correction burn
�ONBOAHD TELEVISION
On Apol i~
ill,
onboard v i d e o will o r i g i n a t e f r o m t h e CM;
Plans c a l l f o r both b l a c k
tliere w i l l b e no 'CV camera i n t h e LM.
arid white arld c o l o r ;
V t o b e carried.
Tkze b l a c k and white camera i s a 4.5 pound RCA camera equipped
w i t h a 60-degree field of v i e w wide angle and lOOmm nine-degree
i ' i e l d of' v i e w t,elephoto lens, attached to a 12-foot power/video
cable. It produces a black-and-white 227 TV l i n e s i g n a l scanned
a t 13 frames a second. Madrid, Goldstone and Honeysuckle C r e e k
all w i l l Lave equipment t o make s t i l l photographs o f t h e slow
s c a n s i g n a l and t o convert t h e s i g n a l t o commercial TV format.
The color TV camera i s a 12-pound Westinghouse camera w i t h a
zoom lens f o r close-up o r wide a n g l e use and a three-inch monitor
which can be mounted on t h e camera o r i n t h e CM.
It produces a
s t a n d a r d 525-line, 30-frame-per-second s i g n a l i n c o l o r by u s e of
a r o t a t i n g color, wheel. The s i g n a l can be viewed i n b l a c k and
white. Only MSC, r e c e i v i n g t h e s i g n a l through Goldstone, w i l l
have equipment to colorLze t h e s i g n a l .
T e n t a t i v e plannlng i s t o use the c o l o r camera predominately,
reverting t o t h e lack and white camera if t h e r e i s difficulty with
t h e c o l o r system b u t r e q u i r i n g a t l e a s t one b l a c k and white t r a n s mission t o Honeysuckle Creek. The f o l l o w i n g i s a p r e l i m i n a r y
p l a n f o r TV p a s s e s based on a 12:49 May 18 launch:
GET
-
DATE/EDT
EVENT
T r a n s p)Io s i t i o n & dock
Madrid
Goldstone
Transl u n a r c o a s t
Goldstone
Goldst one
Translunar coast
Pre-LOI-1
Qoldstone/Madrld
Post LOI-2
Goldstone
Post undock; formation
Goldstone
APS Burn t o Depletion Goldstone
Landmark Tracking
Goldstone
Post -TEI
Honeysuckle*
Transearth coast
Goldstone
Transearth coast
Goldstone
*Transmission from RCA b l a c k and white camera.
t o be from c o l o r camera.
A l l o t h e r s planned
�APOLW) 10 PHOTOGRAPHIC TASKS
S t i l l a n d motion p i c t u r e s w i l l be made of most s p a c e c r a f t
maneuvers as well as of t h e lunar s u r f a c e and of crew a c t i v i t i e s
i n t h e ApolLrs 10 cabin.
The t r a n s p o s i t i o n , docking and lunar module e j e c t ion
maneuver will b e t h e f i r s t major event t o b e photographed. In
lunar orbit, t h e IN-active rendezvous sequence w i l l be photographed from both the command and t h e l u n a r module.
During t h e period between t h e LN DPS phasing burn and t h e
APS i n s e r t i o n burn, t h e commander and lunar module p i l o t w i l l
make still photos of t h e l u n a r ground t r a c k and of landing S i t e
2 from t h e eight-mile low p o i n t of t h e M 1 s f l i g h t path.
After rendezvous i s complete and t h e LM APS d e p l e t i o n burn
h a s been photographed, the crew w i l l make s t e r e o s t r i p s t i l l
phot,ographs of t n e l u n a r s u r f a c e and i n d i v i d u a l frames of t a r g e t s
of opportunity. Using t h e navigation sextant" o p t i c s a s a
camera lens system, lunar s u r f a c e features and landmarks will be
recorded on motion p i c t u r e f i l m . Additionally, t h e camerathrougi-1-sextarli. system will photograph star-horizon and star-landmark c m b i n a ; i o n s a s they a r e superimposed i n v i s u a l navigation
signtirgs.
The A p o i i u iO przotography plan c a l l s f o r motion p i c t u r e s
o f crew a c t i v i t i e s srlch as i n t r a v e h i c u l a r t r a n s f e r through t h e
CSN-LV docking t u n n e l and of o t h e r crew a c t i v i t i e s such as
prcssdre s u i S donning.
Long-dfstance E a r t r i and lunar t e r r a i n photographs w i l l be
s h o S w i t h tne ? O w . still cameras.
Camera eq:liprnent carried on Apollo 10 c o n s i s t s of two 7Omm
Hasselbiad s t i l l cameras, each fitted with 80mm f/2.8 t o f/22
Zeiss P l a n a r lenses, a 250m t e l e p h o t o l e n s stowed aboard t h e
connand xodule, and a s s o c i a t e d e q ~ i p m e n tsuch as f i l t e r s , r i n g s i g h t , spotmeter and a n i n t e r v a l m e t e r f o r s t e r e o s t r i p hot0 raphy.
One iIaseeltlad w i l l b e stowed i n t h e IN and returned t o he C M
a f t e r rendezvo~ls. Easselblad s h u t t e r speeds range from one second
t o 1/503 s e c ,
e s
For cotion p l c t u r e s , two Maurer data a c q u i s i t i o n cameras
(one i n the CSM, one i n t n e 3.24) with v a r i a b l e frame speed
selection .dl1 be ~ s e d . . Motion p i c t u r e camera a c c e s s o r i e s
Incflde bayonet-mount l e n s e s of 75, 18, and 5m focal length,
a r i s h t - a n g l e mirror, a c m a n d module boresignt bracket, a
power c a j l e , and an a d a p t e r f o shooting
~
through t h e s e x t a n t .
Apollo 10 f i b . stowage i n c l u d e s s i x '7Omrn Hasselblad
magazines---two e x t e r i o r c o l o r r e v e r s a l and f o u r f i n e - g r a i n
black and white; and 12 140-foot 16mm maoazbes of motion
p i c t u r e film---eight e x t e r i o r c o l o r and Pour interior color--f o r a t o l a 1 1630 feet.
�LUNAR DESCRIPTION
T e r r a i n - Mountainous a n d c r a t e r - p i t t e d , t h e former
r i s i n g thousands of feet and t h e l a t t e r ranging from a few
i n c h e s t o 180 m i l e s i n diameter. The c r a t e r s a r e thought
to be formed by t h e impact of m e t e o r i t e s . The s u r f a c e i s
covered with a l a y e r of fine-grained m a t e r l a l resembling
s i l t o r sand, a s w e l l a s small rocks and boulders.
Environment - No air, no wind, and no moisture. The
temperature ranges from 243 degrees i n t h e two-week lunar
day t o 279 degrees below zero i n t h e two-week l u n a r a i g h t .
Gravity i s one-sixth t h a t of Earth. Micrometeoroids p e l t t h e
Moon ( t h e r e i s no atmosphere t o burn them up). Radiation
might p r e s e n t a problem during per3 ods of unusual s o l a r a c t i v i t y .
-
Dark Side
The dark o r hidden s i d e of the Moon no longer
i s a complete mystery. It was f i r s t photogre~phed by a Russian
c r a f t and s i n c e then has been photographed many times, p a r t i c u l a r l y by NASAJs Lunar O r b i t e r s p a c e c r a f t and Apollo 8.
-
Ori in
There i s s t i l l no agreement among s c i e n t i s t s
on t h -IT
e o r g i n of t h e Moon. The t h r e e t h e o r i e s : (1) t h e Moon
once w a s p a r t of E a r t h and s p l i t o f f i n t o i t s own o r b i t , ( 2 )
i t evolved as a s e p a r a t e body a t t h e same time a s E a r t h , and
(3) i t formed elsewhere i n space and wandered u n t i l i t was
captured by E a r t h ' s g r a v i t a t i o n a l f i e l d .
Physical F a c t s
Mameter
2,160 miles (about
that of Earth)
Circumference
6,790 miles (about
Distance from E a r t h
238,857 m i l e s (mean; 221,463 minimum
t o 252,710 maximum)
Surface temperature
+243O~(sun a t z e n i t h ) - 2 7 9 ' ~ ( n i g h t )
Surface g r a v i t y
1/6 t h a t of E a r t h
Mass
1/100th ghat of E a r t h
Volume
1/50th t h a t of E a r t h
Lunar day and n i g h t
1 4 E a r t h days each
Mean v e l o c i t y i n o r b i t
2,287 m i l e s p e r hour
Escape v e l o c i t y
1.48 m i l e s p e r second
&
t h a t of Earth)
Month ( p e r i o d of r o t a t i o n
27 days, 7 hours, 43 minutes
around E a r t h )
�Apollo Lunar Landing S i t e s
P o s s i b l e l a n d i n g s i t e s f o r t h e Apollo l u n a r module have
been under study by NASA's Apollo S i t e S e l e c t i o n Board f o r more
than two years. T h i r t y s i t e s o r i g i n a l l y were considered. These
have been narrowed down t o f o u r f o r t h e f i r s t l u n a r landing.
( S i t e 1 c u r r e n t l y not considered f o r f i r s t landing.)
S e l e c t i o n o f t h e f i n a l f i v e s i t e s was based on high r e s o l u t i o n
photographs by Lunar O r b i t e r s p a c e c r a f t , p l u s close-up photos
and s u r f a c e d a t a provided by t h e Surveyor s p a c e c r a f t which s o f t
landed on t h e Moon.
-
The o r i i n a l sites a r e l o c a t e d on t h e v i s i b l e s i d e of t h e
Moon w i t h i n 5 degrees e a s t and west of t h e Moon's c e n t e r and
5 degrees n o r t h and s o u t h of i t s equator.
!$
The f i n a l s i t e choices were based on t h e s e f a c t o r s :
*Smoothness ( r e l a t i v e l y few c r a t e r s a n d b o u l d e r s )
"Approach (no l a r g e hills, h i g h c l i f f s , o r deep c r a t e r s
t h a t could cause i n c o r r e c t a l t i t u d e s i g n a l s t o t h e l u n a r
module l a n d i n g r a d a r )
"Propellant requirements ( s e l e c t e d s i t e s r e q u i r e t h e least
expenditure of s p a c e c r a f t p r o p e l l a n t s )
*Recycle ( s e l e c t e d s i t e s allow e f f e c t i v e launch p r e p a r a t i o n
r e c y c l i n g i f t h e Apollo Saturn V countdown i s delayed)
"Free r e t u r n ( s i t e s a r e w i t h i n reach of t h e s p a c e c r a f t
luanched on a f r e e r e t u r n t r a n s l u n a r t r a j e c t o r y )
--
"Slope ( t h e r e i s l i t t l e s l o p e
l e s s t h a n 2 degrees i n
t h e approach p a t h and landing a r e a )
�The F l v e Landing S i t e s P i n a l l y Selected Are:
Designations
-
Center Coordinates
l a t i t u d e 2' 37' 54" North
longitude 34 01' 31" East
S i t e 1 is l o c a t e d on t h e e a s t c e n t r a l p a r t
of t h e Moon i n s o u t h e a s t e r n Mare Tranq u i l l i t a t i s . The s i t e i s approximately 62
m i l e s (100 k i l o m e t e r s ) east of t h e rlm of
C r a t e r Maskelyne,
Site 2
l a t i t u d e 0' 43l $" North
longitude 23' 38' 51" East
S i t e 2 i s located on t h e e a s t c e n t r a l p a r t
of t h e Moon in southwestern Mar Tranq u i l l i t a t i s , The s i t e i s approximately
62 m i l e s (100 k i l o m e t e r s ) e a s t o f t h e r h
of Crater Sabine and approximately 118
m i l e s (190 k i l o m e t e r s ) southwest of t h e
C r a t e r Maskelyne.
Site 3
l a t i t u d e o0 22' 27'' North
longitude lo 20' 42" West
S i t e 3 i s l o c a t e d n e a r t h e c e n t e r of the
v i s i b l e f a c e of t h e Moon i n t h e southwestern
p a r t of Sinus Medii. The s i t e i s approximately
25 m i l e s (40 k i l o m e t e r s ) west of t h e c e n t e r
or' the face and 21 m i l e s (50 kilometers)
southwest of t h e C r a t e r Bruce,
Site 4
l a t i t u d e 3 O 28' 34" South
longitude 36 41' 53" West
S i t e 4 i s l o c a t e d on the west c e n t r a l p a r t
of t h e Moon i n s o u t h e a s t e r n Oceanus
Procellanun. The s i t e i s approximately 149
m i l e s (240 k i l o m e t e r s ) south of t h e r i m of
C r a t e r Encke and 136 m i l e s (220 k i l o m e t e r s )
e a s t of t h e r i m of C r a t e r Flamsteed,
Site 5
l a t i t u d e lo 461 19" North
longitude 41' 50' 20" West
S i t e 5 i s l o c a t e d on t h e w e s t c e n t r a l p a r t
of t h e v i s i b l e f a c e in southeastern Oceanus
Procellanun, The s i t e i s approximately 130
m i l e s (210 k i l o m e t e r s ) s o u t h s e s t of t h e rim
of C r a t e r Kepler and 118 m i l e s (190 kilometers)
n o r t h n o r t h e a s t of t h e r i m of Crater Flamsteed,
�APOLLO LUNAR LANDING S I T E S
�COMMAND AND SERVICE MOUDLE STRUCTURE, SYSTEMS
The Apollo s p a c e c r a f t for t h e Apollo 10 mission i s comprised
o f Command Module 106, S e r v i c e Module 106, Lunar Module 4, a
s p a c e c r a f t - l u n a r module a d a p t e r (SLA) and a launch escape system,
The SLA s e r v e s as a m a t i n g s t r u c t u r e between t h e instrument u n i t
a t o p t h e S-IVB s t a g e of t h e S a t u r n V launch v e M c l e and as a
housing f o r t h e l u n a r mcdule.
--
Launch Escape System (LES)
P r o p e l s command module t o
s a f e t y i n a n a b o r t e d launch, It i s made up of an open-frame
tower s t r u c t u r e , mounted t o t h e command module by f o u r f r a n g i b l e
b o l t s , and three s o l i d - p r o p e l l a n t rocket motors: a 147,000 poundt h r u s t launch escape system motor, a 2,400-pound-thrust p i t c h
c o n t r o l motor, and a 31,500-pound-thrust tower j e t t i s o n motor.
Two canard vanes n e a r t h e t o p deploy t o t u r n t h e command module
aerodynamically t o an a t t i t u d e w i t h t h e h e a t - s h i e l d forward.
Attached t o t h e base of t h e launch escape tuwer i s a boost prot e c t i v e c o v e r composed of g l a s s , c l o t h , and honeycomb, t h a t
p r o t e c t s t h e command module from r o c k e t exhaust g a s e s from t h e
main and t h e j e t t i s o n motors, The system I s 33 f e e t t a l l , f o u r
P e e t i n diameter a t t h e base, and weighs 8,848 pounds.
Command Module (CM) S t r u c t u r e -- The basic s t r u c t u r e of' t h e
command module i s a pressure v e s s e l encased i n h e a t s h i e l d s ,
cone-shaped 11 f e e t 5 i n c h e s high, base diameter of 1 2 feet-10
inches, and launch weight 12,27'7 pounds.
The command module c o n s i s t s o f t h e forward compartment
which c o n t a i n s two r e a c t i o n c o n t r o l engines and components of
t h e Earth l a n d i n g system; t h e crew compartment o r i n n e r p r e s s u r e
v e s s e l c o n t a i n i n g crew accomodatlons, c o n t r o l s and d i s p l a y s , and
s p a c e c r a f t systems; and t h e a f t compartment housing t e n r e a c t i o n
c o n t r o l engines and p r o p e l l a n t tankage. The crew compartment
c o n t a i n s 210 c u b i c f e e t o f h a b i t a b l e volume.
Heat-shields around the t h r e e compartments are made of
brazed s t a n l e s s steel honeycomb w i t h an o u t e r l a y e r of phenolic
epoxy resin as an a b l a t i v e material, S h i e l d thickness, varying
according t o hea% l o a d s , ranges from 0.7 inch at the apex t o
2.7 Inches a t the a f t end,
The s p a c e c r a f t inner s t r u c t u r e i s of sheet-aluminum honeycomb bonded sandwhich ranging i n t h i c k n e s s from 0.25 i n c h t h i c k
a t fo*ard a c c e s s t u n n e l t o 1.5 inches t u c k a t base.
CSM 106 and LM-4 are equipped w i t h the probe-and-drogue
docking hardware. The probe assembly i s a f o l d i n g coupling and
Impact a t t e n t u a t i n g d e v i c e mounted on the CM t u n n e l t h a t mates
w i t h a c o n i c a l drogue mounted on t h e Lfvl docking t u n n e l . After
t h e docking latches are dogged down f o l l o w i n g a docking maneuver,
both t h e probe and drogue a s s e m b l i e s are removed from the v e h i c l e
t u n n e l s and stowed t o a l l o w free crew t r a n s f e r between the CSM
a n d LM.
�APOLLO SPACECRAFT
�EARTH LANDING SUBSYSTEM
DOCKING M E C H A N I S M
STABILIZATION
EARTH LANDING
ENVIRONMENTAL
( I N BOOST COVER)
ROLL E N G I N E S
WI*DOW
( 2 PLACES1
ENGINES
COMMAND MODULE
FLY AWAY UMBILICAL
SERVICE MODULE
SECTOR I V
O X I G I N TANKS 1 I O R O G I N
T A N K S L I P S FUEL C I L L S
CENTER SECTION
S I R V I C I PROPUlSlON
SISTEM n f L l u M T A N K S
>
�LUNAR MODULE
COMMAND MODULE
DROGUE ASSEMBLY
DOCKING RING
\
PROBE ASSEMBLY
\
LATCH ASSEMBLIES
APOLLO DOCKING MECHANISMS
�--
S e r v i c e Module (SM) S t r u c t u r e
The s e r v i c e module f s a
c y l i n d e r 12 feet 10 i n c h e s f n d i a m e t e r by 24 feet 7 I n c h e s U g h ,
F o r the Apollo 10 m i s s i o n , it w 5 l l weigh, 51,371 pounds a t launch.
Aluminum honeycomb p a n e l s one i n c h t h i c k form the o u t e r skin, and
m i l l e d aluminum r a d i a l beams separate the i n t e r i o r InCo s i x
s e c t i o n s c o n t a i n i n g s e r v i c e propulsion system and r e a e t f o n c o n t r o l
f u e l - o x i d i z e r tankage, f u e l c e l l s , c r y o g e n i c oxygen and hydrogen,
and onboard conszunables.
--
S p a c e c r a f t -LM Adapter (sLA) S t r u c t u r e
The spacecrat't LM
a d a p t e r 1s a t r u n c a t e d cone 28 f e e t l o n g t a p e r i n g from 200 i n c h e s
d i a m e t e r a t the base t o 154 i n c h e s a t t h e forward end a t t h e
s e r v i c e module m a t i n g l i n e . Aluminum honeycomb 1.75 i n c h e s t h i c k
i s the s t r e s s e d - s k i n s t r u c t u r e f o r the s p a c e c r a f t adapter. The
SLA weighs 4,000 pounds.
CSM Systems
--e
--
Guidance, Navigation and C o n t r o l S s t e m D N C S )
Measures
caland c o n t r o l s s p a c e c r a f t p o s i t i o n , att t u d e anmelocity,
c u l a t e s t r a d e c t o r y , c o n t r o l s s p a c e c r a f t p r o p u l si on s y s t e m t h r u s t
v e c t o r , and d i s p l a y s a b o r t data. The g u i d a n c e s y s t e m c o n s i s t s a:'
three subsystems: I n e r t i a l , made up of' a n inertial measurement
u n i t and a s s o c i a t e d power and data components; computer which
p r o c e s s e s i n f o r m a t i o n t o o r from ocher components; and o p t i c s ,
i n c l u d i n g s c a n n i n g t e l e s c o p e and sext3mt f o r celesl3al and/or
landmark s p a c e c r a f t n a v i g a t i o n . CSM 106 and subsequent modules
a r e equipped with a VHF r a n g i n g d e v i c e a s a backup t o the LM
rendezvous r a d a r .
S t a b i l i z a t i o n and C o n t r o l System (SCS) -- C o n t r o l s spacec r a f t r o t a t i o n , t r a n s l a t i o n , and t h r u s t v e c t o r a n d p r o v i d e s
d i s p l a y s f o r c r e w - i n i t i a t e d maneuvers; backs up tihe guidance
system. It has t h r e e subsystems: a t t i t u d e r e f e r e n c e , a t t l t u d e
c o n t r o l , and t h r u s t v e c t o r c o n t r o l ,
--
Provides t h r u s t f o r l a r g e
S e r v i c e P r o p u l s i o n System ( S P S )
s p a c e c r a f t v e l o c i t y changes t h r o u g n a gimbal-mounted 20,500pound-thrust h y p e r g o l i c e n g i n e u s i n g a n i t r o g e n t e t r i o x i d e o x i d i z e r
and a 50-Fj0 m i x t u r e o f unsymmetrl c a l dimethyl h y d r a z i n e and
h y d r a z i n e f u e l . Tankage o f t h i s s y s t e m i s i n zhe s e r v i c e module.
The system responds t o a u t o m a t i c f l r i n g commands from the guida n c e and n a v i g a t i o n system o r t o manual commands from t h e crew.
The e n g i n e p r o v i d e s a c o n s t a n t t h r u s t rate. The s t a b i l i z a t i o n and
c o n t r o l system g i m b a l s the e n g i n e t o f i r e t h r o u g h t h e s p a c e c r a f t
c e n t e r of g r a v i t y .
--
The command module and t h e
R e a c t i o n C o n t r o l System (RCS)
s e r v i c e module e a c h has i t s own independent system. The SM RCS
has f o u r i d e n t i c a l RCS "quads mounted around t h e SM 90 d e g r e e s
apart. Each quad has f o u r 100 p o u n d - t h r u s t e n g i n e s , two f u e l and
two o x i d i z e r t a n k s and a helium p r e s s u r i z a t i o n sphere. The SM RCS
p r o v i d e s redundant s p a c e c r a f t a t t i t u d e c o n t r o l t h r o u g h c r o s s - c o u p l i n g
l o g i c i n p u t s from the s t a b i l i z a t i o n and g u i d a n c e systems.
�Small v e l o c i t y change maneuvers can a l s o be made w i t h the
SM RCS. The CM RCS c o n s i s t s o f two independent s i x - e n g i n e sub-
systems o f s i x 93 pound-thrust e n g i n e s each. Both subsystems
are a c t i v a t e d a f t e r CM s e p a r a t i o n from t h e SM: one is used f o r
s p a c e c r a f t a t t i t u d e c o n t r o l d u r i n g e n t r y . The o t h e r s e r v e s i n
s t a n d b y as a backup. P r o p e l l a n t s for b o t h CM and SM RC$ are
monomethyl h y d r a z i n e f u e l and n i t r o g e n t e t r o x i d e o x i d i z e r with
helium p r e s s u r i z a t i o n . These p r o p e l l a n t s are h y p e r g o l i c , i . e . ,
t h e y burn s p o n t a n e o u s l y when combined w i t h o u t an i g n l t e r .
--
E l e c t r i c a l Power System (EPS)
C o n s i s t s o f t h r e e , 31c e l l Bacon-type hydrogen-oxygen f u e l c e l l power p l a n t s i n t h e
s e r v i c e module which supply 2 8 - v o l t DC power, t h r e e 28-volt DC
z i n c - s i l v e r o x i d e main s t o r a g e b a t t e r i e s i n t h e command module
lower equipment bay, and three 115-200-volt 400 h e r t z t h r e e phase AC i n v e r t e r s powered by t h e main 2 8 - v o l t DC bus. The
i n v e r t e r s are a l s o l o c a t e d i n t h e lower equipment bay, Cryogenic
hydrogen and oxygen react i n the f u e l c e l l s t a c k s t o provide
e l e c t r i c a l power, p o t a b l e water, and h e a t . The command module
main b a t t e r i e s can be switched t o f i r e p y r o t e c h n i c s i n an
emergency. A b a t t e r y c h a r g e r r e s t o r e s s e l e c t e d batteries t o
f u l l s t r e n g t h as r e q u i r e d w i t h power from t h e f u e l c e l l s .
--
Environmental C o n t r o l System (Ecs)
Controls spacecraft
atmosphere, p r e s s u r e , and t e m p e r a t u r e and manages water. In
a d d i t i o n t o r e g u l a t i n g c a b i n and s u i t gas p r e s s u r e , t e m p e r a t u r e
and humidity, t h e system removes carbon d i o x i d e , o d o r s and
p a r t i c l e s , and v e n t i l a t e s t h e c a b i n a f t e r l a n d i n g . I t c o l l e c t s
and s t o r e s f u e l c e l l p o t a b l e water f o r crew use, s u p p l i e s water
t o t h e g l y c o l e v a p o r a t o r s f o r c o o l i n g , and dwnps s u r p l u s w a t e r
overboard t h r o u g h the u r i n e dump v a l v e . P r o p e r o p e r a t i n g tempe r a t u r e of e l e c t r o n i c s and e l e c t r i c a l equipment i s m a i n t a i n e d
by t h i s system t h r o u g h t h e u s e of t h e c a b i n h e a t exchangers, t h e
s p a c e r a d i a t o r s , and t h e f l y c o l e v a p o r a t o r s .
Telecommunications System -- P r o v i d e s v o i c e , t e l e v i s i o n t e l e metry, and command d a t a and t r a c k i n g and r a n g i n g between t h e spacec r a f t and E a r t h , between t h e command module and t h e l u n a r module
and between t h e s p a c e c r a f t and t h e e x t r a v e h i c u l a r a s t r o n a u t . It
a l s o p r o v i d e s intercommunications between a s t r o n a u t s . The t e l e c o m u n i c a t i o n s system c o n s i s t s o f p u l s e code modulated t e l e m e t r y
f a r r e l a y i n g t o Manned Space P l i g h t Network s t a t i o n s d a t a on
s p a c e c r a f t systems and crew c o n d i t i o n , VHP/AM voice, and u n i f i e d
S-Band t r a c k i n g t r a n s p o n d e r , a i r - t o - g r o u n d v o i c e communications,
onboard t e l e v i s i o n , and a VHF' recovery beacon. Network s t a t i o n s
can t r a n s m i t t o t h e s p a c e c r a f t s u c h i t e m s as u p d a t e s t o t h e
Apollo guidance computer and c e n t r a l t i m i n g equipment, and r e a l time commands f o r c e r t a i n onboard f u n c t i o n s .
�S-band inflight antenna-
7
LM docking light
SPACECRAFT AXIS A N D ANTENNA LOCATIONS
�Two scimitar VHF omni antennas on SM--I
(180deg. apart)
axis
Rendezvous radar
SPACECRAFT AXIS A N D ANTENNA LOCATIONS
�The high-gain s t e e r a b l e S-Band antenna c o n s i s t s o f four,
31-inch-diameter p a r a b o l i c d i s h e s mounted on a f o l d i n g boom a t
the a f t end of t h e s e r v i c e module. Nested a l o n g s i d e t h e s e r v i c e
p r o p u l s i o n system engine nozzle u n t i l deployment, t h e antenna
swings out a t r i g h t a n g l e s t o t h e s p a c e c r a f t l o n g i t u d i n a l a x i s ,
w i t h t h e boom p o i n t i n g 52 degrees below t h e heads-up h o r i z o n t a l ,
S i g n a l s from t h e ground s t a t i o n s can be t r a c k e d e i t h e r automati c a l l y o r manually with t h e a n t e n n a ' s g i m b a l l i n g system. Normal
S-Band voice and uplink,downlink communications w i l l be handled
by t h e omni and high-gain antennas.
--
S e q u e n t i a l System
I n t e r f a c e s w i t h o t h e r s p a c e c r a f t systems
and subsystems t o i n i e i a t e time c r i t i c a l f u n c t i o n s d u r i n g launch,
docking maneuvers, s u b - o r b i t a l a b o r t s , and e n t r y p o r t i o n s of a mission. The system a l s o c o n t r o l s r o u t i n e s p a c e c r a f t sequencing
such as s e r v i c e module s e p a r a t i o n and deployment of t h e E a r t h
landing system.
--
Detects and d i s p l a y s t o
the c
d i t i o n s , such as e x c e s s i v e
p i t c h o r r o l l r a t e s o r two engines out, and a u t o m a t i c a l l y o r
manually s h u t s down t h e b o o s t e r and a c t i v a t e s t h e launch escape
system; f'unctions u n t i l t h e s p a c e c r a f t i s i n o r b i t ,
--
)
Includes t h e drogue and main
s t - l a n d i n g recovery a i d s . I n a
parac
normal e n t r y descent, t h e command module forward h e a t s h i e l d
i s j e t t i s o n e d a t 24,000 f e e t , p e r m i t t i n g m o r t a r deployment of
two r e e f e d 16.5-foot diameter drogue p a r a c h u t e s f o r o r i e n t i n g
and d e c e l e r a t i n g t h e s p a c e c r a f t , After d i s r e e f and drogue r e l e a s e , t h r e e p i l o t mortar deployed c h u t e s p u l l o u t t h e t h r e e
main 83.3-foot diameter p a r a c h u t e s with two-stage r e e f i n g t o
provide g r a d u a l i n f l a t i o n i n t h r e e s t e p s , Two main p a r a c h u t e s
out of t h r e e can provide a s a f e landing.
Recovery a i d s i n c l u d e t h e u p r i g h t i n g system, swimmer i n t e r phone connections, s e a dye marker, f l a s h i n g beacon, VHF recovery
beacon, and VHF t r a n s c e i v e r , The u p r i g h t i n g system c o n s i s t s of
t h r e e compressor-inflated bags t o u p r i g h t t h e s p a c e c r a f t if i t
should land i n t h e water apex down ( s t a b l e I1 p o s i t i o n ) .
--
Monitors s p a c e c r a f t systems f o r
o~t-o
a l e r t s crew by v i s u a l and a u d i b l e
alarms s o t h a t c r e m e n may trouble-shoot t h e problem.
--
Controls and Displays
Provide r e a d o u t s and c o n t r o l f u n c t i o n s
of a l l o t h e r s p a c e c r a f t systems i n t h e command and s e r v i c e modules,
A l l c o n t r o l s a r e designed t o be operated by crewmen i n p r e s s u r i z e d
s u i t s . Displays a r e grouped by system and l o c a t e d according t o t h e
frequency t h e crew r e f e r s t o them.
�WNAR MODULE STRUCTURESy WEIGHT
The lunar module is a two-stage v e h i c l e designed f o r
space o p e r a t i o n s near and on t h e Moon, The W is incapable
of r e e n t e r i n g the atmosphere. The lunar module s t a n d s 22
f e e t 11 inches high and is 31 f e e t wide (diagonally a c r o s s
landing g e a r ) ,
Joined by four explosive b o l t s and umbilicals, t h e asc e n t and descent s t a g e s of t h e LM operate as a u n i t u n t i l
s t a g i n g , when the a s c e n t s t a g e f u n c t i o n s as a s i n g l e spacec r a f t f o r rendezvous and docking with t h e CSM.
Ascent Stage
Three main s e c t i o n s make up t h e a s c e n t stage: t h e crew
compartment, midsection, and a f t equipment bay. Only t h e
crew compartment and midsection a r e p r e s s u r i z e d (4.8 psig;
337.4 gm/sq cm) as p a r t o f t h e LM cabin; a l l o t h e r s e c t i o n s
of t h e LM a r e unpressurized, The cabin volume is 235 cubic
f e e t ( 6 . 7 cubic m e t e r s ) . The a s c e n t s t a g e measures 12 f e e t
4 inches high by 14 f e e t 1 inch i n diameter.
S t r u c t u r a l l y , t h e a s c e n t s t a g e has s i x s u b s t r u c t u r a l
areas: crew compartment, midsection, a f t equipment bay, t h r u s t
chamber assembly c l u s t e r supports, antenna supports and thermal
and microme teoroid s h i e l d .
The c y l i n d r i c a l crew compartment i s a semimonocoque
s t r u c t u r e o f machined longerons and fusion-welded aluminum s h e e t
and i s 92 inches (2.35 m ) i n diameter and 42 inches (1.07 m)
deep, Two f l i g h t s t a t i o n s a r e equipped with c o n t r o l and d i s play panels, a r m r e s t s , body r e s t r a i n t s , landing aids, two f r o n t
windows, an overhead docking window, and a n alignment o p t i c a l
telescope In t h e c e n t e r between t h e two f l i g h t s t a t i o n s , The
h a b i t a b l e volume i s 160 cubic feet.
Two t r i a n g u l a r f r o n t windows and t h e 32-inch (0.81 rn)
square inward-opening forward h a t c h are i n t h e crew compartment
f r o n t face.
External s t r u c t u r a l beams support t h e crew compartment
and serve t o support t h e lower i n t e r s t a g e mounts a t t h e i r
lower ends, R i n g - s t i f fened semimonocoque c o n s t r u c t i o n i s employed i n the midsection, w i t h chem-milled aluminum skin over
fusion-welded longerons and s t i f f e n e r s , Fore -and-aft beams
a c r o s s t h e t o p of t h e midsection j o i n with those running a c r o s s
t h e t o p of t h e cabin t o take a l l a s c e n t s t a g e stress loads and,
i n e f f e c t , i s o l a t e t h e cabin from stresses,
�DOCKING
LUNAR SURFACE SENSING PROBE (4)
APOLLO LUNAR MODULE
�VHF ANTENNA(2)
TRANSFER TUNNEL AND HATCH
ALIGNMENT OPTICAL TELESC
OCKING TARGET RECESS
GASEOUS OXYGEN TANK (2)
RENDEZVOUS
RADAR ANTENNA
AFT EQUIPMENT BAY
REPLACEABLE ELECTRONIC ASSEMBLY
FUEL TANK (REACTION CONTROL)
IQUlD OXYGEN TANK
ASCENT ENGINE COVER
S-BAND INFLIGHT ANTENNA
Q)
HELIUM TANK @)
HELIUM TANK
(REACTION CONTROL)
REACTION CONTROL
ASSEMBLY (4 PLACES)
OXIDIZER TANK
(REACTION CONTROL)
INGRESS/EGRESSHATCH
CREW COMPARTMEN
WATER TANKQ)
APOLLO LUNAR MODULE
-
ASCENT STAGE
�LM CABIN INTERIOR, LEFT HALF
�LM CABIN INTERIOR, RIGHT HALF
�The a s c e n t s t a g e engine compartment i s formed by two
beams running a c r o s s t h e lower midsection deck and mated
t o t h e f o r e and a f t bulkheads. Systems located i n t h e
midsection include t h e LM guidance computer, t h e power and
servo assembly, a s c e n t engine propellant tanks, RCS prop e l l a n t tanks, t h e environmental c o n t r o l system, and t h e
waste management section.
A tunnel r i n g a t o p t h e a s c e n t s t a g e meshes with t h e
command module l a t c h assemblies. During docking, t h e r i n g
and clamps a r e aligned by t h e LM drogue and the CSM probe,
The docking tunnel extends downward i n t o t h e midsection
The tunnel is 32 Inches (0.81 cm) i n diameter and is used f o r crew t r a n s f e r between t h e CSM and LFnl by
crewmen. The upper hatch on t h e inboard end of' t h e docking
tunnel hinges downward and cannot be opened with t h e
pressurized and undocked.
16 inches (40 cm).
A thermal and micrometeoroid s h i e l d of multiple l a y e r s
of mylar and a s i n g l e thickness of t h i n aluminum s k i n encases
t h e e n t i r e ascent s t a g e s t r u c t u r e .
Descent Stage
The descent s t a g e c o n s i s t s of a cruciform load-carrying
s t r u c t u r e of two p a i r s of p a r a l l e l beams, upper and lower decks,
and enclosure bulkheads -- a l l of conventional skin-and-stringer
aluminum a l l o y construction. The c e n t e r compartment houses
the descent engine, and descent propellant tanks a r e housed
i n the four square bays around the engine. The descent stage
measures 10 f e e t 7 inches high by 14 f e e t 1 inch i n diameter.
Pour-legged t r u s s o u t r i g g e r s mounted on the ends of each
p a i r of beams serve a s SLA a t t a c h points and a s "knees" f o r the
landing g e a r main s t r u t s .
Triangular bays between t h e main beams a r e enclosed i n t o
quadrants housing such components a s t h e ECS water tank, helium
tanks, descent engine c o n t r o l assembly of t h e guidance, navig a t i o n and c o n t r o l subsystem, ECS gaseous oxygen tank, and
b a t t e r i e s f o r the e l e c t r i c a l power system. Like the ascent
stage, t h e descent s t a g e is encased i n the mylar and aluminum
a l l o y thermal and micrometeoroid shLeld.
The I;M e x t e r n a l platform, o r "porch", is mounted on the
forward o u t r i g g e r j u s t below t h e forward hatch. A ladder extends down t h e forward landing gear s t r u t from t h e porch f o r
crew lunar s u r f a c e operations.
��I n a r e t r a c t e d p o s i t i o n u n t l . 1 a f t e r t h e crew mans t h e
LM, t h e landing g e a r struts a r e e x p l o s i v e l y extended and
provide l u n a r s u r f a c e landing impact a t t e n u a t l o n
W 4 e ma i n
s t r u t s a r e f i l l e d with c r u s h a b l e aluminum honeycomb f o r
absorbing compression l o a d s . Footpads 37 inches ( 0 . 9 5 m) I n
diameter a t t h e end o f each landing g e a r provide v e h i c l e
" f l o a t a t i o n " on t h e l u n a r s u r f a c e ,
.
Each pad i s f i t t e d with a l u n a r - a u ~ f a c e s e n s i n g probe
which s i g n a l s t h e crew t o s h u t down t h e d e s c e n t engine upon
contact with the lunar surface.
LM-11 flown on t h e Apollo 10 mission w i l l have a launch
weight o f 30,849 pounds. The weight breakdown is as follows:
Ascent s t a g e , d r y
4,781 l b s .
Descent s t a g e , d r y
4,703 l b s .
RCS propel l a n t s
DPS propel l a n t s
612 ~ b s .
18,134 l b s .
APS p r o p e l l a n t s
Lunar Module Systems
E l e c t r i c a l Power System -- The LM DC electrical system
masts of s i x s i l v e r z i n c primary b a t t e r i e s -- f o u r i n the
d e s c e n t s t a g e and two i n t h e a s c e n t s t a g e , each w i t h i t s own
e l e c t r i c a l c o n t r o l assembly (ECA)
Power f e e d e r s from a l l
primary b a t t e r i e s pass through c i r c u i t b r e a k e r s t o e n e r g i z e
t h e LM DC buses, from which 28-volt DC power i d distributed
through c i r c u i t b r e a k e r s t o a l l LM systems. A? power
(117v 400Hz) i s s u p p l i e d by two i n v e r t e r s , e l t h e r o f which can
supply s p a c e c r a f t AC load needs t o t h e AC buses.
.
Environmental Control System -- C o n s i s t s c f t h e atmosphere
r e v i t a l i z a t i o n s e e t l o n , oxygen supply
n
- - and cabin pressure c f ~trcl
s e c t i o n , water management,-heat t r a n s p o r t s e c t i o n , and o u t i e t s
f o r oxy en and water s e r v i c i n g o f t h e F o r t a b i e L i f e Support,
Sys tem TPLSS).
�Components of t h e atmosphere r e v i t a l i z a t i o n s e c t i o n are
the s u i t c i r c u i t assembly which c o o l s and v e n t i l a t e s t h e
pressure garments, reduces carbon d i o x i d e l e v e l s , removes
o d c r s , noxious g a s e s and e x c e s s i v e moisture; t h e c a b i n rec l r c u l a t J o n assembly which v e n t i l a t e s and c o n t r o l s c a b i n
atmosphere temperatures; and t h e steam f l e x d u c t which v e n t s
t o space steam from t h e s u i t c i r c u i t water e v a p o r a t o r .
The oxygen supply and cabin p r e s s u r e s e c t i o n s u p p l i e s
gaseous axygen t c t h e atmosphere r e v i t a l i z a t i o n s e c t i o n f o r
maintaining s u i t and c a b i n p r e s s u r e . The d e s c e n t s t a g e
oxygen supply provides d e s c e n t f l i g h t phase and l u n a r s t a y
oxygen needs, and t h e a s c e n t s t a g e oxygen supply provides
oxygen needs f o r t h e a s c e n t and rendezvous f l i g h t phase.
Water f o r d r i n k i n g , cooling, f i r e f i g h t i n g , food p r e p a r a t i o n , and r e f i l l i n g t h e PLSS c o o l i n g water s e r v i c i n g
tank i s s u p p l i e d by t h e water management s e c t i o n . The water
i s contained i n t h r e e n i t r o g e n - p r e s s u r i z e d bladder-type tanks,
one o f 367-pound c a p a c i t y i n t h e d e s c e n t s t a g e and two of
147.5-pound c a p a c l t y i n t h e a s c e n t s t a g e .
The heat t r a n s p o r t s e c t i o n h a s primary and secondary
water-glycol s o l u t i o n c o o l a n t loops. The primary c o o l a n t
l o o p c i r c u l a t e s water-glycol f o r temperature c o n t r o l o f cabin
cnd s u i t c l r c u i t oxygen and f o r thermal c o n t r o l of b a t t e r i e s
and electronic components mounted on cold p l a t e s and r a i l s .
If' the primary loop becomes i n o p e r a t i v e , t h e secondary loop
c i r c u l a t e s c o o l a n t through t h e r a i l s and c o l d p l a t e s only.
E u i t c i r c u i t c ~ o l i n gd u r i n g secondary c o o l a n t loop o p e r a t i o n
?s provided by the s u i t loop water b o i l e r . Waste h e a t from
b o t h l o o p s is v e n t e d overboard by water e v a p o r a t i o n o r subllrnators.
Zomunlcation System -- Two S-band t r a n s m i t t e r - r e c e i v e r s ,
two VHF t r a n s m i t t e r - r e c e i v e r s , a s i g n a l processing assembly,
and a s s o c t a t e d s p a c e c r a f t antenna make up t h e LM communications
system. The system t r a n s m i t s and r e c e i v e s v o i c e , t r a c k i n g
and ranglng d a t a , and t r a n s m i t s t e l e m e t r y d a t a on 281 measurements and TV s i g n a l s t o t h e ground. Voice communications between t h e TLM and ground s t a t i o n s i s by S-band, and between t h e
LN and CSM voice i s on VHF.
�Real-time commands t o t h e l u n a r module are r e c e i v e d and
encoded by t h e d i g i t a l u p l i n k assembly--a black box t i e d i n
t o the S-band r e c e i v e r . The d i g i t a l u p l i n k assembly w i l l be
used on Apollo 10 t o arm and f i r e thg a s c e n t propulsion
system f o r the unmanned APS d e p l e t i o n burn following f i n a l
docking and LM j e t t i s o n . LM-4 w i l l b e t h e l a s t s p a c e c r a f t t o
be f i t t e d with equipment f o r a c c e p t i n g r e a l - t i m e commands from
t h e ground.
The d a t a s t o r a g e e l e c t r o n i c s assembly (DSEA) i s a f o u r channel voice r e c o r d e r with timing s i g n a l s w i t h a 10-hour
recording c a p a c i t y which w i l l be brought back i n t o t h e CSM
for r e t u r n t o Earth. DSEA r e c o r d i n g s cannot be "dumped" t o
ground s t a t i o n s .
rsJI antennas a r e one 26-inch diameter p a r a b o l i c S-band
s t e e r a b l e antenna, two S-band i n f l i g h t antennas and two VHF
I n f l i g h t antennas.
Guidance, Navigation and Control System -- Comprised o f
six s e c t i o n s :
idance and n a v i g a t l o n s e c t i o n (PGNS),
a b o r t guidance
radar section, control electronics
s e c t i o n (CES), and o r b i t a l r a t e d r i v e e l e c t r o n i c s f'or Apollo
and LM (ORDEAL).
* The PGNS i s a n i n e r t i a l system a i d e d by t h e alignment
o p t i c a l t e l e s c o p e , a n i n e r t i a l measurement u n i t , and t h e r e n dezvous and landing r a d a r s . The system provides i n e r t i a l
r e f e r e n c e d a t a f o r computations, produces i n e r t fa1 alignment
r e f e r e n c e by feeding o p t i c a l s i g h t i n g data i n t o the LM guidance
computer, d i s p l a y s p o s i t i o n and v e l o c i t y d a t a , computes TA-CSM
rendezvous d a t a from r a d a r i n p u t s , c o n t r o l s a t t i t u d e and t h r u s t
t o maintain d e s i r e d LM t r a j e c t o r y , and c o n t r o l s d e s c e n t engine
t h r o t t l i n g and gimbaling.
* The AGS i s an independent backup s y s t e m f o r t h e PGNS,
having i t s own i n e r t i a l s e n s o r and computer.
*. The r a d a r s e c t i o n i s made up of t h e rendezvous radar
which provldes CSM range and range r a t e , and l i n e - o f - s i g h t
a n g l e s f o r maneuver computation t o t h e LM guidance computer;
t h e landing r a d a r which provide a l t i t u d e and v e l o c i t y data t o t h e
TSJI guidance computer during l u n a r l a n d i n
The rendezvous radar
has an o p e r a t i n g range from 80 f e e t t o 4 6 n a u t i c a l miles.
The range t r a n s f e r tone assembly, u t i l i z i n g VKF e l e c t r o n i c s ,
i s a p a s s i v e responder t o t h e CSM VHF ranging device and i s a
backup t o the rendezvous r a d a r .
d
�+
217e CES c o n t r o l s I24 a t t i t u d e and t r a n s l a t i o n about a l l
axes. I t a l s o c o n t r o l s by PGNS command t h e automatic o p e r a t i o n
of t h e a s c e n t and d e s c e n t engines., and t h e r e a c t i o n c o n t r o l
t h r u s t e r s . Manual a t t j t u d e c o n t r o l l e r and t h r u s t - t r a n s l a t i o n
controller commands are a l s o handled by t h e CES.
* ORDEAL, d i s p l a y s on t h e f l i g h t d i r e c t o r a t t i t u d e i n d i c a t o r , is t h e computed l o c a l v e r t i c a l i n t h e p i t c h a x i s
during circular, Earth o r lunar o r b i t s .
Reaction C o n t r o l System -- The LM has f o u r RCS engine
c l u s t e r s o f four 100-pound (45.8 kg) t h r u s t engines each which
use helium-pressurized hypergollc p r o p e l l a n t s . The o x l d l z e r
1s n i t r o g e n t e t r o x i d e , f u e l i s Aerozlne 50 ( 5 0 / 5 0 blend of
hydrazine and unsymmetrical dimethyl h y d r a z i n e ) . P r o p e l l a n t
plumblng, valves and p r e s s u r i z i n g components are i n two
p a r a l l e 1, independent s y s terns, each f e e d i n g h a l f the e n g i n e s
i n each c l u s t e r . E i t h e r system is capable o f m a i n t a i n l n g
a t t i t u d e a l o n e , b u t if one supp3.y system f a i l s , a p r o p e l l a n t
c r o s s f e e d a l l o w s one system t o s u p p l y a l l 16 engines,
A d d i t i o n a l l y , i n t e r c o n n e c t valves permit t h e RCS system t o
draw from a s c e n t engine p r o p e l l a n t t a n k s .
The engine c l u s t e r s a r e mounted on o u t r i g g e r s 90 degrees
a p a r t on t h e a s c e n t s t a g e .
The RCS provides s m a l l s t a b i l i z i n g Impulses d u r i n g a s c e n t
and d e s c e n t burns, c o n t r o l s LM a t t i t u d e d u r i n g maneuvers, and
produces t h r u s t f o r s e p a r a t i o n , and ascent/deseent engine tank
u l l a g e . The system may be o p e r a t e d i n e i t h e r t h e p u l s e o r
s t e a d y - s t a t e modes.
Descent Propulsion System -- Maximum r a t e d t h r u s t o f t h e
d e s c e n t engine i s g,tjq(O pounds (4,380.9 kg) and is t h r o t t l e a b l e
between 1,050 pounds (476.7 kg) and 6,300 pounds (2,860.2 kg).
The engine can be gi-nbaled s i x degrees i n any d i r e c t i o n f o r
o f f s e t c e n t e r of g r a v i t y trimming. P r o p e l l a n t s are heliumpressurized Aerozine 50 and n i t r o g e n t e t r o x i d e .
--
The 3,500-pound (1,589 kg)
Ascent Propulsion System
t h r u s t a s c e n t engine i s n o t gimbaled and performs a t f u l l
t h r u s t . The engine remains dormant u n t i l a f t e r t h e a s c e n t
s t a g e s e p a r a t e s f r o & t h e d e s c e n t s t a g e . P r o p e l l a n t s are the
same as are burned by the RCS engines and t h e d e s c e n t engine.
Caution and Warning, C o n t r o l s and Displays -- These two
systems have t h e same f u n c t i o n aboard t h e lunar module as t h e y
do aboard t h e command module.
(see CSM systems s e c t i o n . )
�Tracking and Docking Lights -- A flashing tracking l i g h t
(once per second, 20 milliseconds duration) on t h e front face
of the lunar module i s an a i d f o r contingency CSM-active
rendezvous IH rescue. V i s i b i l i t y ranges from 400 n a u t i c a l
miles through the CSM sextant t o 130 miles with the naked eye.
Five docking l i g h t s analagous t o a i r c r a f t running l i g h t s a r e
mounted on the IN f o r CSM-active rendezvous: two forward
yellow l i g h t s , a f t white light, p o r t red l i g h t and starboard
green l i g h t . All docking l i g h t s have about a 1,000-foot
visibility.
�SATURN V LAUNCH VEHICLE DESCRIPTION AND OPERATION
The S a t - ~ r nV, 363 feet t a l l with the Apollo s p a c e c r a f t
i n place, g e n e r a t e s enough t h r u s t t o place a 125-ton payload
i n t o a lO5-nm c i r c u l a r o r b i t of t h e Earth, It can boost
about 50 t o n s t o l u n a r o r b i t . The t h r u s t of t h e t h r e e prop u l s i v e s t a g e s range Prom almost 7.6 m i l l i o n pounds f o r t h e
booster t o 230,000 pounds f o r t h e t h i r d s t a g e a t operating
a l t i t u d e , Including t h e instrument u n i t , t h e launch v e h i c l e
without t h e s p a c e c r a f t is 281 feet t a l l ,
F i r s t Stage
The first s t a g e (s-IC) w a s developed j o i n t l y by t h e
National Aeronauties and Space Administration's Marshall
Space p l i g h t Center, Huntsville, A l a . and t h e Roeing Co.
The Marshall Center assembled f o u r S-IC stages: a
s t r u c t u r a l test model, a s t a t i c test version, and t h e first
two f l i g h t stages. Subsequent f l i g h t s t a g e s are assembled
by Boeing a t t h e Michoud Assembly F a c i l i t y , New Orleans,
The S-IC s t a g e destined f o r t h e Apollo 10 mission w a s t h e
second f l i g h t booster s t a t i c t e s t e d a t t h e NASA-Mississippi
Test F a c i l i t y . The f i r s t S-IC test a t MTF w a s on May 11,
1967, and t h e t e s t of t h e second S-IC t h e r e -- t h e booster
f o r Apollo 10 -- was completed Aug. 9, 1967. E a r l i e r f l i g h t
s t a g e s were s t a t i c f i r e d a t t h e Marshall Center.
The S-IC s t a g e boosts t h e space v e h i c l e t o a n a l t i t u d e
of 35.8 nm a t 50 nm downrange and i n c r e a s e s t h e v e h i c l e ' s
v e l o c i t y t o 5,343 knots i n 2 minutes 40 seconds of powered
flight.
It then s e p a r a t e s and f a l l s i n t o t h e A t l a n t i c Ocean
about 351 nm downrange (30 degrees North l a t i t u d e and 74 degrees
West longitude) about nine minutes a f t e r l i f t o f f .
Normal propellant flow rate t o t h e f i v e F-1 engines i s
Four of t h e engines a r e mounted
on a r i n g , each 90 degrees from i t s neighbor, These f o u r
are gimballed t o c o n t r o l t h e r o c k e t ' s d i r e c t i o n of P l i g h t .
The f i f t h engine i s mounted r i g i d l y i n t h e center.
29,522 pounds p e r second.
Seccnd Stage
The second stage (S-11), l i k e the t h i r d stage, u s e s
high performance 3-2 engines t h a t burn l i q u i d oxygen and
l i q u i d hydrogen. The s t a g e ' s purpose is t o provide s t a g e
boost n e a r l y t o Earth o r b i t ,
�SATURN V LAUNCH VEHICLE
5,031,023 LBS. FUELED
294,200 LBS .DRY
/ LM \
PROPE LLANTS
l NSTRUMENT
LIQUID OXYGEN (3,258,280
LBS.)
RP-I (KEROSENE) (1,417,334 LBS .)
(S- IVB
.
1,074,590 isS FUELED
84,367 LBS. DRY
tf
/ SECOND STAGE
PROPELLANTS
LIQUID OXYGEN (829,114
LBS .)
LIQUID HYDROGEN
.
261,836 LBS FUELED
ST STAGE
(S-IC)
PROPE LLANTS
LIQUID OXYGEN (190,785
LBS .)
LlQUlD HYDROGEN
(43,452 LBS .)
NOTE: WEIGHTS AND MEASURES GIVEN ABOVE ARE FOR THE
N O M I N A L VEHICLE CONFIGURATION FOR APOLLO 10. THE
FIGURES M A Y VARY SLIGHTLY DUE TO CHANGES BEFORE
LAUNCH TO MEET C H A N G I N G CONDITIONS.
�A t outboard engine cutoff, the S-I1 separates and,
following a b a l l i s t i c t r a j e c t o r y , plunges i n t o t h e Atlantic
mean abmat 2,400 nm downrange from Kennedy Space Center (31
degrees ~ o p t hl a t i t u d e and 34 degrees west longitude) about
20 minutes a f t e r l i f t o f f ,
Five J-2 enaines power t h e S-11, The o u t e r four engines
a r e equally spaced on a 17.5-foot diameter c i r c l e . These
four engines may be glmbaled through a plus o r mlnus sevendegree square p a t t e r n f o r t h r u s t vector control. A s on t h e
first stage, t h e c e n t e r engine (number 5) i s mounted on the
s t a g e c e n t e r l i n e and is f i x e d i n position,
The S - I 1 c a r r i e s t h e rocket t o an a l t i t u d e of about
101,6 nm and a distance of some 888 nm downrange, Before
burnout, t h e vehicle w l l l be moving a t a speed of 13,427
knots, The outer 5-2 engines w i l l burn 6 minutes 32 seconds
during t h i s powered phase, but t h e c e n t e r engine w i l l be c u t
off a t 4 minutes 59 seconds of burn tine,
The Space Division of North American Rockwell Corp,
builds t h e S-I1 a t Seal Beach, Calif, The c y l i n d r i c a l vehicle
i s made up of t h e forward s k i r t t o which t h e t h i r d s t a g e
attaches, t h e l i q u i d hydrogen tar&, the l i q u i d oxygen tank
(separated from t h e hydrogen tank by a common bulkhead), t h e
t h r u s t s t r u c t u r e on which t h e engines a r e mounted and an i n t e r stage s e c t i o n t o which t h e first stage attaches. The common
bulkhead between t h e two tanks i s heavily insulated.
The S-I1 f o r Apollo 10 was s t a t i c t e s t e d by North American
Rockwell a t the NASA-Nississippi Test F a c i l i t y on Aug. 9, 1968,
This stage was shipped t o the t e s t s i t e v i a t h e Panama Canal
f o r the t e s t f i r i n g ,
Third Stage
The Ehird stage (s-M3) was developed by t h e McDonnell
Douglas Astronautics Co, a t Huntington Beach, C a l i f , A t
Sacramento, Calif., t h e stage passed a s t a t i c f i r i n g t e s t on
O e t , 9, 1967 a s p a r t of the preparation f o r t h e Apollo 10
mission. The stage was flown d i r e c t l y t o t h e NASA-Kennedy
Space Center,
Measuring 58 f e e t 4 inches long and 21 feet 8 inches i n
diameter, t h e S - N B weighs 25,750 pounds Qry, A t first i g n i t i o n ,
i t weighs 261,836 pounds, The i n t e r s t a g e s e c t i o n weighs an
a d d i t i o n a l 8,081 pounds, The s t a g e 1s 5-2 engine burns l i q u i d
oxygen and l i q u i d hydrogen,
�The s t a g e provides propulsion t w l c e during t h e Apollo
10 mission, The first burn occurs
e d i a t e l g after separat%on from the S-XI, It w i l l last long enough (156 seconds)
to Znsert t h e v e h i c l e and s p a c r c r a f t i n t o a c i r c u l a r W r t h
parking o r b i t a t about 52 degrees West longitude and 32 degrees
North l a t i t u d e ,
The second bum, which begins a t 2 hours 33 minutes 25
seconds after l i f t o f f ( f o r first opportunity t r a n s l u n a r inj e c t i o n ) o r 4 hours 2 minutes 5 seconds ( f o r second TLI opport u n i t y ) , w i l l plaee t h e stage, instrument u n i t , and spacecraft
i n t o t r a n s l u n a r t r a J e c t o r y . "The burn w i l l continue u n t i l
proper "nI end conditions are m e t ,
The f u e l tanks contain 4?,452 pounds of l i q u i d hydrogen
and 190,785 pounds of IiquLd oxygen a t first i g n i t i o n , totalling
234,237 pounds of propellants, I n s u l a t i o n between t h e two
tanks i s necessary because t h e l i q u i d oxygen, a t about 293
degrees below zero I?, is warm enough, r e l a t i v e l y , t o heat t h e
l i q u i d hydrogen, a t 423 degrees below zero F, r a p i d l y and cause
i t t o t u r n I n t o gas.
Instrument Unit
The instrument u n i t (IN) i s a cylinder t h r e e f e e t high
and 21 f e e t 8 inches i n diameter, It weighs 4,254 pounds and
contains t h e guidance, navigation, and c o n t r o l equipment which
w i l l s t e e r t h e vehicle through its Earth o r b i t s and i n t o t h e
f i n a l t r a n s l u n a r i n j e c t i o n maneuver,
The IU a l s o contains telemetry, communieations, tracking,
and crew s a f e t y systems, along with i t s own supporting e l e c t r i c a l
power and environmental c o n t r o l systems,
Components making up the "brain" of t h e Saturn V are
mounted on cooling panels fastened t o t h e i n s i d e surface of
t h e instrument u n i t skin, The "cold p l a t e s " a r e p a r t of a
system t h a t removes heat by c i r c u l a t i n g cooled fluid through
a heat exchanger t h a t evaporates water from a separate s u p p l y
i n t o t h e vacuum of space.
The six maJor systems of the instrument u n i t a r e
s t r u c t u r a l , thermal control, guidance and control, measuring
and telemetry, r a d i o frequency, and e l e c t r i c a l .
The instrument u n i t provides navigation, guidance,
and c o n t r o l of t h e vehicle; measurement of vehicle performance
and environment; data transmission with ground s t a t i o n s ; radio
tracking of t h e vehicle; checkout and monitoring of vehicle
functions; i n i t i a t i o n of stage functional sequencing; detection
f o emergency s i t u a t i o n s ; generation and network d i s t r i b u t i o n of
e l e c t r i c power system operation; and p r e f l i g h t checkout and
launch and f l i g h t operations.
�A path-adaptive guidance scheme i s used i n t h e Saturn
A programmed t r a j e c t o r y i s used i n t h e
V instrument u n i t .
i n i t i a l launch phase with guidance beginning only a f t e r t h e
v e h i c l e h a s l e f t t h e atmosphere. This i s t o prevent movements
t h a t might cause t h e v e h i c l e t o break a p a r t while a t t e m p t i n g
t o compensate f o r winds, J e t streams, and g u s t s encountered
i n t h e atmosphere.
If such a i r c u r r e n t s d i s p l a c e t h e v e h i c l e from t h e
optimum t r a j e c t o r y i n climb, t h e v e h i c l e d e r i v e s a new traJ e c t o r y . C a l c u l a t i o n s are made about once each second througho u t t h e f l i g h t . The launch v e h i c l e d i g i t a l computer and
d a t a a d a p t e r perform t h e n a v i g a t i o n and guidance computations.
--
The ST-124M i n e r t i a l platform
t h e h e a r t of t h e navigat i o n , guidance and c o n t r o l system -- provides space-fixed
r e f e r e n c e c o o r d i n a t e s and measures a c c e l e r a t i o n a l o n g t h e t h r e e
mutually perpendicular a x e s of t h e c o o r d i n a t e system.
I n t e r n a t i o n a l Buuiness Machines Corp., i s prime c o n t r a c t o r
f o r t h e instrument u n i t and i s t h e s u p p l i e r of t h e guidance
s i g n a l processor and guidance computer. Major s u p p l i e r s of
instrument u n i t components a r e : E l e c t r o n i c Communications,
Inc., c o n t r o l computer; Bendix Corp., ST-124M i n e r t i a l platform;
and IBM Federal Systems Division, launch v e h i c l e d i g i t a l comp u t e r and launch v e h i c l e data a d a p t e r .
Propulsion
The 4 1 r o c k e t engines of t h e S a t u r n V have t h r u s t
r a t i n g s ranging from 72 pounds t o more t h a n 1.5 m i l l i o n pounds.
Some e w i n e s burn l i q u i d p r o p e l l a n t s , o t h e r s use s o l i d s .
The f i v e F-1 engines i n t h e f i r s t s t a g e burn RP-1
(kerosene) and l i q u i d oxygen. Fngfnes i n t h e f i r s t s t a g e
develop approximately 1,536,197 pounds of t h r u s t each a t l i f t o f f , b u i l d i n g up t o 1,822,987 pounds b e f o r e c u t o f f . The
c l u s t e r of f i v e engines g i v e s t h e first s t a g e a t h r u s t range
from 7,680,982 m i l l i o n pounds a t l i f t o f f t o 9,114,934 pounds
just b e f o r e c e n t e r engine c u t o f f
.
The F-1 engine w e i ~ h salmost 10 t o n s , i s more t h a n 18
f e e t h i a h and has a n o z z l e - e x i t diameter of n e a r l y 14 f e e t .
The F-1 undergoes s t a t i c t e s t i n g f o r a n average 650 seconds
i n q u a l i f y i n g f o r t h e 160-second run d u r i n g t h e S a t u r n V f i r s t
s t a g e b o o s t e r phase. The engine consumes almost t h r e e t o n s of
p r o p e l l a n t s p e r second.
�The first stage of t h e Saturn V f o r t h i s mission h a s
e i g h t other rocket motors, These are t h e s o l i d - f u e l r e t r o rockets which w i l l slow and separate t h e s t a g e from t h e second
stage, Each rocket produces a t h r u s t of 87,900 pounds f o r 0.6
second.
The main propulsion f o r t h e seaend stage i s a c l u s t e r
of f i v e 3-2 engines burning l i q u i d hydrogen and l i q u i d oxygen,
Each engine develops a mean t h r u s t of more than 205,000 pounds
a t 5,0:1 mixture r a t i o ( v a r i a b l e from 184,000 t o 230,000 i n
pbases of f l i g h t ) , giving t h e stage a t o t a l mean t h r u s t of
more than a m i l l i o n pounds.
Designed t o operate i n t h e hard vacuum of space, t h e
3,500-pound 5-2 i s mere e f f i c i e n t than t h e F-1 because it
burns t h e high-energy f u e l hydrogen. F-1 and 5-2 engines
are produced by t h e Rocketdyne Division of North American
Roekwell Corp
.
The second s t a g e has f o u r 21,000-pound-thrust s o l i d
f u e l rocket engines. These a r e t h e u l l a g e rockets mounted
on t h e S-IC/S-11 i n t e r s t a g e section, These rockets f i r e t o
s e t t l e l i q u i d propellant i n t h e bottom of the main tanks and
help a t t a i n a "clearn" separation from t h e first stage, they
remain with t h e I n t e r s t a g e when it drops away a t second plane
separation. Four retrorockets are located I n t h e S-IVB a f t
i n t e r s t a g e (which never separates from the S-11) t o separate
t h e S-I1 f r m the S-IVB p r i o r t o S-TVB i g n i t i o n .
Eleven rocket engines perform various functions on t h e
t h i r d stage. A s i n g l e 5-2 provides t h e main propulsive
force; t h e r e a r e two J e t t i s o n a b l e main u l l a g e rockets and e i g h t
smaller engines i n t h e two a u x i l i a r y propulsion system modules.
Launch Vehicle Instrumentation and Comrnunloation
A t o t a l of 2,342 measurements w i l l be taken I n f l i t on
t h e Saturn V launch vehicle: 672 on the first stage, 9 6 on
'?f
the second stage, 386 o n t h e t h i r d stage, and 298 on t h e i n s t r u ment u n i t .
The Saturn V has 16 telemetry systems: six on t h e first
stage, s i x on t h e second stage, one on the t h i r d stage and
t h r e e on the instmment u n i t . A C-band system and command
system are a l s o on t h e instrument u n i t , Each powered stage
has a range s a f e t y system a s on previous f l i g h t s ,
�S-IVB R e s t a r t
The t h i r d s t a g e of t h e Saturn V rocket f o r t h e Apollo 10
mission w i l l burn t w i c e i n apace, The second b u m places t h e
spacecraft on t h e t r a n s l u n a r t r a j e c t o r y , =Thefirst opportunity
f o r t h i s burn is a t 2 hours 33 minutes and 25 seconds after
JLauach,, The second opportunity f o r TLI begins a t 4 hours 2
minutes and 5 seconds after l i f t o f f ,
The primary p r e s s u r i z a t i o n system of the propellant
tanks f o r t h e 5-nr13 restart uses a helium heater, I n t h i s
sytem, nine helium storage spheres i n t h e l i q u i d hydrogen
tank contain gaseous helium charged t o about 3,000 p s i , This
h e f h m is passed through t h e h e a t e r wh%chh e a t s and expands
t h e gas before it e n t e r s t h e propellant tanks, The h e a t e r
operates on hydrogen and oxygen gas from t h e main propellant
tanks,
The backup system c o n s i s t s of f i v e ambient helium
spheres mounted on t h e s t a g e t h r u s t s t r u c t u r e . This system,
controlled by t h e f u e l repressurization c o n t r o l module, can
repressurize %he tanks i n case t h e primary system fails, !Phe
r e s t a r t w i l l use t h e primary system. If t h a t system fails, t h e
backup system w i l l be used.
The t h i r d stage f o r Apollo 10 w i l l not be Ignited f o r a
t h i r d burn a s on Apollo 9, Following spacecraft separation
i n t r a n s l u n a r t r a j e c t o r y , the s t a g e w i l l undergo the normal
5-2 engine chilldown sequence, stopping j u s t short of r e i g n i t i o n ,
On Apollo 10 t h e r e i s no requirement f o r a t h i r d burn, and
t h e r e w i l l not be s u f f i c i e n t propellants aboard, most of t h e
f u e l s having been expended during the tranalunar i n j e c t i o n maneuver,
Differences i n Apollo 9 and Apollo 10 Launch vehicles
Two modifications r e s u l t i n g from problems encountered
during the second Saturn V f l i g h t were incorporated and proven
successful an t h e t h i r d and f o u r t h Saturn V missions. The new
helium prevalve c a v i t y pressurization system w i l l again be
flown on the first (s-IC) stage of Apollo 10, New augmented
spark I g n i t e r l i n e s which f l e w on t h e engines of t h e two upper
s t a g e s of Apollo 8 and 9 w i l l again be used on Apollo 10,
�The major first s t a g e (s-IC) d i f f e r e n c e s between
Apollo 9 and 10 a r e :
1.
pounds,
Dry weight was reduced from 295,600 t o 294,200
2. Weight a t ground i g n i t i o n increased from 5,026,200
t o 5,031,023 pounds.
3.
Instrumentation measurements were increased from
666 t o 672.
S-I1 s t a g e changes a r e :
1. Nominal vacuum t h r u s t f o r 5-2 engines i n c r e a s e
w i l l change maximum s t a g e t h r u s t from 1,150,000 t o 1,168,694
pounds.
2. The approximate empty weight of t h e S-I1 has been
reduced from 84,600 t o 84,367 pounds. The S-IC/S-11 i n t e r stage weight was reduced from 11,664 t o 8,890 pounds.
3. Approximate s t a g e g r o s s l i f t o f f weight was increased
from 1,069,114 t o 1,074,590 pounds.
4.
to 986.
975
Instrumentation measurements increased i ~ m
Major d i f f e r e n c e s on t h e S-IVB s t a g e of Apollo 9 and
10 a r e :
S - N B dry s t a g e weight increased from 25,300 t o
T h i s does n o t include t h e 8,084-pound i n t e r stage section.
1.
25,750 pounds.
2.
S-NB
8r o s s
s t a g e weight a t l i f t o f f increased from
259,337 t o 261, 36 pounds.
3. Instrumentation measurements were increased from
296 t o 386.
�APOLLO 10 CREW
L i f e Support muipment
- Space S u i t s
Apollo 10 crewmen w i l l wear two versions of t h e Apollo
space s u i t : an i n t r a v e h i c u l a r p r e s s u r e garment assembly
worn by t h e command module p i l o t and t h e e x t r a v e h i c u l a r press u r e garment assembly worn by the commander and the lunar
module p i l o t , Both versions a r e b a s i c a l l y i d e n t i c a l except
t h a t t h e e x t r a v e h i c u l a r version has an i n t e g r a l thermal/
meteoroid garment over the b a s i c s u i t .
From the s k i n o u t , the b a s i c pressure garment c o n s i s t s
of a nomex comfort l a y e r , a neoprene-coated nylon pressure
bladder and a nylon r e s t r a i n t l a y e r , The o u t e r l a y e r s of t h e
i n t r a v e h i c u l a r s u i t a r e , from t h e inside o u t , nomex and two
l a y e r s of Tef lon-coated Beta c l o t h . The e x t r a v e h i c u l a r i n t e g r a l thermal/meteoroid cover c o n s i s t s o f a l i n e r o f two l a y e r s
of neoprene-coated nylon, seven l a y e r s o f ~ e t a / K a p t o nspacer
laminate, and an o u t e r l a y e r o f Teflon-coated Beta f a b r i c .
The e x t r a v e h i c u l a r s u i t , t o g e t h e r with a l i q u i d cooling
garment, p o r t a b l e l i f e support system (PLsS), oxygen purge
system, e x t r a v e h i c u l a r v i s o r assembly and o t h e r components
make up t h e e x t r a v e h i c u l a r m o b i l i t y u n i t (EMU). The EMD provides an e x t r a v e h i c u l a r crewman with l i f e support f o r a , f o u r hour mission o u t s i d e t h e l u n a r module without r e p l e n i s h i n g
expendables. EPlIZ t o t a l weight i s 183 pounds. The i n t r a vehicular suit weighs 35.6 pounds.
Liquid cooling garment--A k n i t t e d nylon-spandex garment
w i t h a network of p l a s t i c tubing through which cooling watelr
from the PLSS i s c i r c u l a t e d . It i s worn next t o the s k i n and
r e p l a c e s t h e constant wear-garment during EVA only.
Portable l i f e support system--A backpack supplying oxygen
a t 3.9 p s i and cooling water t o t h e l i q u i d cooling garment.
Return oxygen i s cleansed o f s o l i d and gas contaminants by a
l i t h i u m hydroxide canister. The PLSS i n c l u d e s communications
and telemetry equipment, d i s p l a y s and c o n t r o l s , and a main
power supply. The PLSS i s covered by a thermal i n s u l a t i o n
Jacket. (one stowed i n LM).
Oxygen purge sys tern--Mounted a t o p t h e PLSS, the oxygen
purge system provides a contingency 30-minute supply of
gaseous oxygen i n two two-pound b o t t l e s p r e s s u r i z e d t o 5,880
p s i a . The system may a l s o be worn s e p a r a t e l y on the f r o n t of
t h e pressure garment assembly t o r s o , It serves as a mount f o r
t h e VHF antenna f o r the PLSS. (Two stowed i n LM)
.
��HOLD DOWN STRAP
ACCESS FLAP
L U V Y lAPt
SHOULDER
DISCONNECT \
CONNECTOR COVER
CHEST COVER
SUNG LASSES
+--SHELL
-+iNSUlATION
+-LINER
PENLIGHT POCKET
TYPICAL CROSS SECTION
LM RESTRAINT
BELT ASSEMBLY
LITY POCKET
SLlDE FASTENER
DATA LIST POCKET
WRIST CLAMP
ASSIST STRAP
URINE TRANSFER
CONNECTOR AND
BIOMEDICAL INJECTION
P
!
LOOP TAPE
L U U P IAPE
ACTIVE
DOSIMETER
POCKET
ENTRANCE
SLIDE FASTENER
FLAP
a ------I/,
'\I
,
L
ASSISTS
SCISSORS POCKET
CHECKLIST POCKET
�-56~-
BACKPACK SUPPORT STRAPS
OXYGEN PURGE SYST
CKPACK CONTROL BOX
SYSTEM ACTUATOR
PENLIGHT POCKET
CONNECTOR COVER
COMMUNICATION,
VENT1 LATI ON, AND
LIQUI D COOLING
PURGE SYSTEM
LM RESTRA lNT R ING
INTEGRATED THERMAL
METEOR0 I D GARMENT
UR INE TRANSFER CONNECTOR,
DOS IMETER ACCESS FLAP AND
DONN I NG LANYARD POCKET
UTILITY POCKET
�Extravehicular v i s o r assembly--A polycarbonate s h e l l and
two v i s o r s with thermal c o n t r o l and o p t i c a l coatings on them,
The EVA v i s o r i s attached over t h e pressure helmet t o provide
impact, micrometeoroid, thermal and l i g h t protection t o t h e
EVA crewman.
Extravehicular gloves--Built of an o u t e r s h e l l of
Chromel-R f a b r i c and thermal i n s u l a t i o n t o provide protect i o n when handling extremely hot and cold o b j e c t s , he f i n g e r
t i p s a r e made of s i l i c o n e rubber t o provide the crewman more
sensitivity.
A one -piece cons tan%-wear garment, similar t o " long
johns", is worn as an undergarment f o r the space suit in i n t r a vehicular operations and f o r the i n f l i g h t coveralls. The
garment 5s porous-knit cotton with a waist-to-neck zipper f o r
doming. Biomedical harness a t t a c h points are provided.
During periods out of the space s u i t s , crewmen w i l l wear
two-piece Teflon f a b r i c i n f l i g h t c o v e r a l l s f o r warmth and f o r
pocket stowage of personal items.
Communications c a r r i e r s ( " ~ n o o p yh a t s " ) with redundant
microphones and earphones a r e worn w i t h the pressure helmet;
a lightweight headset i s worn with the i n f l i g h t coveralls,
Meals
The Apollo 10 crew has a wide Pange of food items from
which t o s e l e c t t h e i r d a i l y mission space menu, More than
60 items comprise the food s e l e c t i o n l i s t of freeze-dried
rehydratable foods. I n addition, one "wet pack" meal-per-man
per-day w i l l be stowed f o r a t o t a l of 27. These meals, cons i s t i n g of foil-wrapped beef and potatoes, ham and potatoes
and turkey chunks and gravy, a r e s i m i l a r t o the Christmas
meals c a r r i e d aboard Apollo 8 and can be eaten with a spoon.
Water f o r drinking and rehydrating food is obtained from
three sources i n the command module
a dispenser f o r drinking
water and two water spigots a t the food preparation s t a t i o n ,
one supplying water a t about 155 degrees F., the other a t about
55 degrees F, The potable water dispenser s q u i r t s water continuously as long a s the t r i g g e r i s held down, and the food
preparation s p i g o t s dispense water i n one-ounce increments.
--
�Command module potable water i s supplied from s e r v i c e
module f u e l ce 11 byproduct water, Three one - p i n t " p i c n i c
Jugs", o r p l a s t i c bags, w i l l be stowed aboard Apollo 10 f o r
drinking water, Each crewman once a day w i l l f i l l a bag
with water and then s p i n it up t o s e p a r a t e t h e suspended
hydrogen gas from t h e water so t h a t he w i l l have hydrogenl e s s water t o d r i n k t h e following day. The suspended hydrogen
i n t h e f u e l c e l l byproduct water has caused i n t e s t i n a l d i e comfort t o crewmen i n previous Apollo missions.
A continuous-feed hand water dispenser similar t o t h e one
i n the command module i s used aboard the l u n a r module f o r
cold-water rehydration of food packets stowed aboard t h e M.
A f t e r water has been i n j e c t e d i n t o a food bag, it is
kneaded f o r about t h r e e minutes, TZle bag neck i s then c u t
o f f and t h e food squeezed i n t o t h e crewman's mouth. A f t e r a
meal, germicide p i l l s attached t o t h e o u t s i d e of the. food bags
a r e placed i n the bags t o prevent fermentation and gas formation.
The bags a r e then r o l l e d and stowed i n waste d i s p o s a l compartments,
The day-by-day, meal-by-meal Apollo 10 menu f o r each crewman f o r both t h e command module and the l u n a r module i s
l i s t e d on t h e following pages.
�MEAL
Day 2, 6, 1 0
Day I*, 5, 9
A
Peaches
Bacon Squares (8)
Cinn Tstd Bread Cubes (4)
Grapefruit Drink
Orange Drink
F r u i t Cocktail
Sugar Coated Corn Flakes
Bacon Squares (8)
Grapefruit Drink
Grape Drink
B
Salmon Salad
Chicken & Rice**
Sugar Cookie Cubes (4)
Cocoa
Grape Punch
P o t a t o Soup
Chicken & Vegetables
Tuna Salad
Pineapple Fruitcake (4)
Orange Drink
S
(D
I
Day 3, 7, 11
Peaches
Bacon Squares (8)
Strawberry Cubes (4)
Cocoa
Orange Drink
Cream of Chicken Soup
(Turkey & Gravy Wet Pack)
Butterscotch Pudding
Brownies ( 4 )
G r a p e f r u i t Drink
-
F r u i t Cocktail
Sausage P a t t i e s
Bacon Squares (8)
Cocoa
Grape Drink
P o t a t o Soup
Pork & Scalloped P o t a t o a
Applesauce
Orange Drink
&
\O
I
C
-
(Beef & Potatoes
Wet pack)
Cheese Cracker Cubes (4)
Chocolate Pudding
Grange-Grapefruit Drink
*Day 1 c o n s i s t s of Meal C only
**Nev spoon-bowl package
Spaghetti & Meat Sauce**
(Ham & Potatoes Wet pack)
Banana Pudding
Pineapple-Grapefruit Drink
-
Pea Soup
Beef StewY*
Chicken Salad
Chocolate Cubes (4)
Grape Punch
Shrimp Cocktail
Chicken Stew**
Turkey B i t e s (4)
Date Fruitcake ( 4 )
Orange-Grapefruit Drink
�APOLLO 10 (YOUNG)
MEAL
Day l*,5 , 9
Day 2, 6, 10
A
Peaches
Bacon Squares (8)
Cinn Tstd Bread Cubes ( 4 )
Grapefruit' Drink
Orange Drink
F r u i t Cocktail
Sugar Coated Corn Flakes
Brownies ( 4 )
Grapefruit Drink
Grape Drink
B
Salmon Salad
Chicken & Rice**
Sugar Cookie Cubes (4)
Cocoa
Grape Punch
Potato Soup
Tuna Salad
Chicken & Vegetables
Pineapple Fruitcake ( 4 )
Pineapple-Grapefruit Drink
'3
CD
I
C
-
(Beef & Potatoes
Wet pack)
Cheese Cracker Cubes ( 4 )
Chocolate Pudding
Orange-Grapefruit Drink
*T)sy 1 c o n s i s t s o f Meal C: only
**Nev spoon-Sow1 psckage
S p a g h e t t i & Meat SauceY*
(Ham & P o t a t o e s Wet pack)
Banana Pudding
Grange Drink
-
Day 3, 7, 11
Peaches
Bacon Squares (8)
Strawberry Cubes ( 4 )
Cocoa
Orange Drink
Cream of Chicken Soup
(Turkey & Gravy - Wet Pack)
Butterscotch Pudding
Grapefruit Drink
Beef StewY*
Chicken Salad
Corn Chowder
Chocolate Cubes ( 4 )
Grape Punch
F r u i t Cocktail
Sausage P a t t i e s
Bacon Squares (8)
Cocoa
Grape Drink
Pea Soup
Pork & Scalloped P c t s t o e s
Applesauce
Orange D r i n k
Shrimp Cocktail
Chicken Stew**
Turkey Bites ( 4 )
Date Fruitcake (4)
Orange-Grapef r u i t Drink
�MEAL
Uay l * , 5, 9
Day 2, 6, 1 0
A
Peaches
Bacon Squares (8)
Cinn T s t d Bread Cubes (4)
Orange Drink
Orange-Pineapple Drink
F r u i t Cocktail
Sugar Coated Corn F l a k e s
Bacon Squares (8)
Orange Drink
Grape Drink
B
Salmon S a l a d
Chicken & Rice**
Sugar Cookie Cubes ( 4 )
Cocoa
Grape Punch
P o t a t o Soup
Tuna Salad
Chicken & Vegetables
Brownies (4)
Orange-Grapefruit Drink
Day 3, 7, 11
Peaches
Bacon Squares (8)
Strawberry Cubes ( 4 )
Cocoa
Orange Drink
Cream of Chicken Soup
(Turkey & Gravy
Wet pack)
Cinn T s t d Bread Cubes ( L )
B u t t e r s c o t c h Pudding
Pineapple-Grapefrui t Drink
-
Day 4, 8
F m i t Cocktail
Sausage P a t t i e s
Bacon Squares (8)
Cocoa
Grape Drink
P o t a t o Soup
Pork & Scalloped P o t a t o e s
Applesauce
Orange Drink
Y
I
ui
I-'
I
C
Cream of Chicken Soup
Wet pack)
(Beef & P o t a t o e s
Cheese Cracker Cubes ( 4 )
F r u i t Cocktail
Orange-Grapefruit Drink
-
*Day 1 c o n s i s t s of Meal C only
**New spoor-'mwl package
S p a g h e t t i & Meat Sauce**
(Ham & P o t a t o e s
Wet pack)
Banana Pudding
Orange Drink
-
Pea Soup
Chicken S a l a d
Beef Stew**
Grape Punch
Shrimp C o c k t a i l
Chicken Stew**
Turkey B i t e s (6)
Chocolate Cubes (6)
Orange-Grapefruit Drink
�-62-
APOLLX) 10 ZM MENU
Meal A
F m it Cocktail
Bacon Squares ( 8 )
Brownies ( 4 )
Orange Drink
Grape Punch
Meal I3
Beef and Vegetables
Pineapple F r u i t c a k e (4)
Orange-Grapefruit Drink
Grape Punch
Meal C
Cream o f Chicken Soup
Beef Hash
Strawberry Cubes (4)
Pineapple-Grapefruit
."I
Drink
2 man-days only
L meals p e r overwrap
Red and Blue Velcro
�Personal Hygiene
Crew personal hygiene equipment aboard Apollo 10 i n cludes body c l e a n l i n e s s items, t h e waste management system
and one medical k i t .
Packaged with t h e food a r e a toothbrush and a two-ounce
tube of t o o t h p a s t e f o r each crewman. Each man-meal package
contains a 3.5-by-four-Inch
wet-wipe cleansing towel.
Additionally, t h r e e packages of 12-by-12-Inch dry towels ape
stowed beneath t h e command module p i l o t ' s couch. Each package
c o n t a i n s seven towels. Also stowed under t h e command module
p i l o t ' s couch a r e seven t i s s u e d i s p e n s e r s containing 53 t h r e e p l y t i s s u e s each.
S o l i d body wastes are c o l l e c t e d i n Gemini-type p l a s t i c
d e f e c a t i o n bags which contain a germicide t o prevent b a c t e r i a
and gas formation. The bags a r e sealed a f t e r use and stowed
i n empty food c o n t a i n e r s f o r p o s t - f l i g h t a n a l y s i s .
Urine c o l l e c t i o n devices a r e provided f o r use while
wearing e i t h e r the pressure s u i t o r the f n f l i g h t c o v e r a l l s .
The u r i n e i s dumped overboard through t h e s p a c e c r a f t u r i n e
dump valve i n the CM and s t o r e d i n t h e LM.
The 5 x 5 ~ 8 - i n c hmedical accessory k i t i s stowed i n a cornpartment on t h e s p a c e c r a f t r i g h t s i d e w a l l beside t h e lunar
module p i l o t couch. The medical k i t c o n t a i n s t h r e e motion
sickness i n j e c t o r s , t h r e e pain suppression i n J e c t o r s , one twoounce b o t t l e f i r s t a i d ointment, two one-ounce b o t t l e eye
drops, t h r e e n a s a l sprays, two compress bandages, 12 adhesive
bandages, one o r a l thermometer and two s p a r e crew biomedical
harnesses. P i l l s i n t h e medical k i t a r e 60 a n t i b i o t i c , 12
nausea, 12 s t i m u l a n t , 18 pain k i l l e r , 60 decongestant, 24
d i a r r h e a , 72 a s p i r i n and 2 1 sleeping. Additionally, a small
medical k i t containing four stimulant, e i g h t d i a r r h e a , two
s l e e p i n g and four pain k i l l e r p i l l s , 12 a s p i r i n , one b o t t l e eye
drops and two compress bandages i s stowed i n t h e lunar module
f l i g h t d a t a f i l e compartment.
Survival Gear
The s u r v l v a l k i t i s stowed i n two rucksacks in the r i g h t hand forward equipment bay above t h e lunar module p i l o t .
Contents of rucksack No. 1 are: two combination s u r v i v a l
l i g h t s , one d e s a l t e r k i t , t h r e e p a i r sunglasses, one r a d i o
beacon, one spare r a d i o beacon b a t t e r y and s p a c e c r a f t connector
cable, one k n i f e i n sheath, t h r e e water c o n t a i n e r s and two cont a i n e r s of Sun l o t i o n .
��Rucksack No. 2: one three-man l i f e raft with CO
i n f l a t e r , one sea anchor, two s e a dye markers, t h r e e unbonnets, one mooring lanyard, t h r e e manllnes, and two a t t a c h
brackets.
5
The s u r v i v a l k i t is designed t o provide a 48-hour
postlanding (water o r land) s u r v i v a l c a p a b i l i t y f o r t h r e e
crewmen between 40 degrees North and South l a t i t u d e s .
Biomedical I n f l i g h t Monitorin4
The Apollo 10 crew biomedical telemetry d a t a received
by the Manned Space F l i g h t Network w i l l be relayed f o r Instantaneous d i s p l a y a t Mission Control Center where h e a r t
r a t e and breathing r a t e d a t a w i l l be displayed on the f l i g h t
surgeon's console. Heart r a t e and r e s p i r a t i o n rate average,
range and d e v i a t i o n a r e computed and displayed on d i g i t a l TV
screens.
I n a d d i t i o n , t h e instantaneous h e a r t r a t e , real-time and
delayed EXG and r e s p i r a t i o n a r e recorded on s t r i p c h a r t s f o r
each man.
Biomedical telemetry w i l l be simultaneous from a l l crewmen while i n the CSM, but s e l e c t a b l e by a manual onboard
switch i n the LM.
Biomedical data observed by t h e f l i g h t surgeon and
h i s team i n the L i f e Support Systems S t a f f Support Room w i l l
be c o r r e l a t e d wlth s p a c e c r a f t and space s u i t environmental
data displays.
Blood pressures a r e no longer telemetered as they were
i n the Mercury and Gemini programs. Oral temperature, however, can be measured onboard f o r d i a g n o s t i c purposes and
voiced down by the crew In case o f i n f l i g h t i l l n e s s .
Rest-Work Cycles
A l l t h r e e Apollo 10 crewmen w i l l s l e e p simultaneously
during r e s t periods. The average mission day w i l l c o n s i s t of
16 hours of work and e i g h t hours of r e s t . Two crewmen normally
w i l l s l e e p i n t h e s l e e p s t a t i o n s ( s l e e p i n g bags) under t h e
couches, w i t h t h e t h i r d man i n the couch. During r e s t periods,
one crewman w i l l wear h i s communications headset.
The only exception t o t h i s s l e e p i n g arrangement w i l l be
during the r e s t period on lunar o r b i t i n s e r t i o n day, when two
crewmen w i l l s l e e p i n the couches s i n c e the docking probe and
drogue assemblies w i l l be stowed i n one o f t h e s l e e p s t a t i o n s .
When poss'ible, a l l t h r e e crewmen w i l l e a t together i n onehour e a t p e r i o d s during which o t h e r a c t i v i t i e s w i l l be held t o
a minimum.
�The crewmen of Apollo 10 have spenlt; more than f i v e hours
of forrnal crew t r a i n i n g f o r each hour of t h e l u n a r - o r b i t
missiont s e i g h t -day d u r a t i o n . Almost 1,000 hours of t r a i n i n g
were i n the Apollo 10 crew t r a i n i n g s y l l a b u s over and above
t h e normal p r e p a r a t i o n s f o r the mission--technical b r i e f i n g s
and reviews, p i l o t meetings and study.
The Apollo 10 crewmen also took p a r t i n s p a c e c r a f t manuf a c t u r i n g checkouts a t the Nosrth American Rockwell p l a n t i n
Downey , C a l i f . , a t Orumman A i r c r a f t Engineering Gorp,, Bethpaga,
N.Y., and i n prelaunch t e s t i n g a t NASA Kennedy Space Center.
Taking p a r t i n f a c t o r y and launch a r e a t e s t i n g has provided t h e
crew with thorough o p e r a t i o n a l knowledge of the complex vehicle.
Highlights of s p e c i a l i z e d ApoPlo 10 crew t r a i n i n g t o p i c s
are:
* Detailed s e r i e s of b r i e f i n g s on s p a c e c r a f t systems,
operation and modifications.
* Saturn launch vehicle b r i e f i n g s on countdown, range
s a f e t y , f l i g h t dynamics, f a i l u r e modes and a b o r t conditions.
The launch vehicle b r i e f i n g s were updated p e r l o d e a l l y .
* Apollo ouidance and Navigation system b r i e f i n g s a t the
Massachusetts I n s t i t u t e of Technology I n s t
e n t a t i o n Laboratory.
* B r i e f i n g s and continuous t r a i n i n g on mission photographic o b j e c t i v e s and use of camera equipment.
* Extensive p i l o t p a r t i c i p a t i o n i n reviews of a l l f l i g h t
procedures f o r normal as well as emergency s i t u a t i o n s .
* Stowage reviews and p r a c t i c e i n t r a i n i n g s e s s i o n s i n
t h e s p a c e c r a f t , mockups and command module simulators allowed
t h e crewmen t o evaluate s p a c e c r a f t stowage of crew-associated
equipment.
* More than 300 hours of t r a i n i n g p e r man i n command module
and lunar module simulators a t NSC and KSC, including cloeedloop simulations with f l i g h t c o n t r o l l e r s i n t h e Mission Control
Center. Other Apollo simulators a t various l o c a t i o n s were
used e x t e n s i v e l y f o r s p e c i a l i z e d crew t r a i n i n g .
* Entry c o r r i d o r d e c e l e r a t i o n p r o f i l e s a t lunar-return
conditions i n t h e MSC F l i g h t Acceleration F a c i l i t y manned
centrifuge,
�* Zero-g a i r c r a f t f l i g h t s using command module and lunar
module mockups f o r EVA and pressure s u i t doffing/donning
p r a c t i c e and t r a i n i n g .
* Underwater zero-g t r a i n i n g i n the MSC Water Immersion
F a c i l i t y using spacecraft mockups t o f a m i l i a r i z e f u r t h e r crew
with a l l a s p e c t s of CSM-LM docking tunnel i n t r a v e h i c u l a r
t r a n s f e r and GVA i n pressurized s u i t s .
* Water e g r e s s t r a i n i n g conducted i n indoor tanks a s
well as i n t h e Gulf of Mexico included uprighting from the
Stable I1 p a a i t i o n (apex downj t o the S t a b l e I p o s i t i o n
(apex up), egress onto r a f t s and h e l i c o p t e r pickup.
* Launch pad egress t r a i n i n g from mockups and from the
a c t u a l s p a c e c r a f t on the launch pad f o r possible emergencies
such as f i r e , contaminants and power f a i l u r e s .
+ The t r a i n i n g covered use of Apollo s p a c e c r a f t f i r e
suppress ion equipment i n t h e cockpit.
*
Planetarium reviews a t Morehead Planetarium, Chapel
and a t G r i f f i t h Planetarium, Los Angeles, Calif.,
of t h e c e l e s t i a l sphere with s p e c i a l emphasis on the 37
navigational s t a r s used by t h e Apollo guidance computer.
H i l l , N.C.,
�Crew Biographies
NAME:
Thomas P. S t a f f o r d ( c o l o n e l , USAF) Apollo 10 commander
NASA Astronaut
BIRTHPLACE AND DATE: Born September 17, 1930, i n Weatherford,
Okla., where h i s mother, Mrs. Mary E l l e n S t a f f o r d , now
resides.
PHYSICAL DESCRIPTION: Black h a i r , blue eyes; height:
weight: 175 pounds.
6 feet;
EDUCATION: Qraudated from Weatherford High School, Weatherford,
Okla.; received a Bachelor of Science degree from the
United S t a t e s Naval Academy i n 1952; r e c i p i e n t of an
Honorary Doctorate of Science from Oklahoma C i t y U n i v e r s i t y
i n 1967.
MARITAL STATUS:
Married t o t h e former Faye L. Shoemaker of
Weatherford, Okla. H e r p a r e n t s , M r . and Mrs. E a r l e R.
Shoemaker, r e s i d e i n Thomas, Okla.
CHILDREN:
Dionne, July 2, 1954; Karin, Aug. 28, 1957.
H i s hobbies include handball, weight l i f t i n g
and swimming.
OTHER ACTIVITIES:
ORGANIZATIONS:
Pilots.
Member of t h e S o c i e t y o f Experimental Test
SPECIAL HONORS: Awarded two NASA Exceptional Service Medals
and t h e A i r Force Astronaut Wings; t h e Distinguished
Flying Cross; the A I A A A s t r o n a u t i c s Award; and co-rec i p i e n t of t h e 1966 Harmon I n t e r n a t i o n a l Aviation Trophy.
EXPERIENCE: Staffo.rd, an A i r Force c o l o n e l , was colnmissioned i n
i n t h e United S t a t e s A i r Force upon graduation from
Annapolis. Following h i s f l i g h t t r a i n i n g , he flew f i g h t e r
i n t e r c e p t o r a i r c r a f t i n t h e United S t a t e s and Germany
and l a t e r a t t e n d e d t h e USAF m p e r i m e n t a l F l i g h t T e s t
School a t Edwards A i r Force Base, C a l i f .
H e served as Chief of t h e Performance Branch a t t h e USAP
Aerospace Research P i l o t School a t Edwards and was res p o n s i b l e f o r t h e s u p e r v i s i o n and a d m i n i s t r a t i o n o f t h e
f l y i n g curriculum f o r s t u d e n t test p i l o t s . H e was also
an i n s t r u c t o r i n f l i g h t test t r a i n i n g and s p e c i a l i z e d
academic s u b j e c t s - - e s t a b l i s h i n g b a s i c textbooks and
d i r e c t i n g t h e w r l t i n g o f f l i g h t t e s t manuals f o r use by
t h e s t a f f and s t u d e n t s . He i s co-author o f t h e P i l o t ' s
Handbook for Performance F l i g h t T e s t i n g and t h e Asrodynamics Handbook f o r Performance F l i g h t Testing,
-
�H e has accumulated over 5,000 hours f l y i n g t b e , of
which over 4,000 hours are i n jet a i r c r a f t .
Colonel S t a f f o r d was s e l e c t e d as an
a s t r o n a u t by NASA i n September 1962. H e has s i n c e
served as backup p i l o t f o r the Gemini 3 f l i g h t .
CURRENT ASSIGNMENT:
On Dec. 15, 1965, he and command p i l o t Walter M. S c h i r r a
were launched i n t o space on the history-making Qemini 6
mission and subsequently p a r t i c i p a t e d i n the f i r s t
s u c c e s s f u l rendezvous of two manned maneuverable spacec r a f t by joining the a l r e a d y o r b i t i n Gemini 7 crew.
Gemini 6 returned t o Earth on k c . 1 , 1965, a f t e r 25
hours 51 minutes and 24 seconds of f l i g h t .
ti
He made h i s second f l i g h t as command p i l o t o f t h e Gemini
9 mission. During t h i s 3-day f l i g h t which began on
June 3, 1966, the s p a c e c r a f t a t t a i n e d a c i r c u l a r o r b i t of
161 s t a t u t e m i l e s ; t h e crew performed t h r e e d i f f e r e n t
types of rendezvous with the previously launched Augmented
Target Docking Adapter; and p i l o t Eugene Cernan logged
two hours and t e n minutes o u t s i d e t h e s p a c e c r a f t i n
e x t r a v e h i c u l a r a c t i v i t y . The f l i g h t ended a f t e r 72 hours
and 20 minutes with a p e r f e c t r e e n t r y and recovery as
Gemini 9 landed within 0.4 naukical m i l e s of t h e des i g n a t e d t a r g e t point and 13 miles from the prlme recovery
s h i p , USS WASP.
�NAm:
John W. Young(Commander, USN)
pilot
NASA Astronaut
Apollo 10 conrmand module
BIRTHPLACE AND DATE: Born i n San Francisco, C a l i f . , on Sept.
24, 1930. H i s parents, M r . and Mrs. W i l l i a m 8 . Young,
r e s i d e i n Orlando, Fla.
PHYSICAL DESCRIPTION: Brown h a i r ; green eyes; height:
9 inches; weight: 165 pounds.
5 feet
.
Qraudated from Orlando High School, Orlando, Fla ;
received a Bachelor o f Science degree i n Aeronautical
Engineering from the Georgia I n s t i t u t e of Technology i n
1952*
EIXJCATION:
MARITAL STAWS: Married t o the former Barbara V. White of
Savannah, Ga, Her parents, M r . and Mrs. Robert A . White,
r e s i d e i n Jacksonville, Fla.
CHILDREN:
Sandy, Apr. 30, 1957; John, Jan. 17, 1959.
OTHER ACTIVITIES:
H i s hobbles a r e bicycle r i d i n g and handball.
ORGAMIZATIONS: Member of the American I n s t i t u t e of Aeronautics
and Astronautics and the Society of Experimental Test
Pilots.
SPECIAL HONORS: Awarded two NASA Exceptional Service Medals,
t h e Navy Astronaut Wings, and three Distinguished Flying
Crosses.
EXPWIENCE: Upon graduation from Georgia Tech, Young entered
t h e U,S, Navy i n 1952 and holds t h e rank of commander.
He was a t e s t p i l o t a t t h e Naval A i r Test Center from 1959
t o 1962. Test p r o j e c t s included evaluations of t h e F8D
and F4B f i g h t e r weapons systems. I n 1962, he set world
time-to-climb records t o 3,000 and 25,000-meter a l t i t u d e s
i n the F4B. P r i o r to h i s assignment t o NASA he was
k i n t e n a n c e O f f i c e r of All-Weather -Fighter Squadron 143
a t t h e Naval A i r S t a t i o n , M i r a m a r , C a l i f .
H e has logged more than 4,500 hours f l y i n g time, including
more than 3,900 hours i n j e t a i r c r a f t .
�CURRENT ASSIGNMENT: Commander Poumze; was s e l e c t e d as an a s t r o naut by NASA in September 1962.
H e served as p i l o t on t h e first manned G e m i n i f l i g h t - - a
3 - o r b i t mission, launched on March 23, 1965, during which
t h e crew accomplished t h e first manned s p a c e c r a f t o r b i t a l
t r a j e c t o r y modifications and l i f t i n g r e e n t r y , and f l i g h t
t e s t e d all systems i n G e m i n i 3. After t h f a assignment, he
was backup p i l o t f o r Gemini 6.
18, 1966, Young occupied t h e co&d
p i l o t seat
f o r t h e Gemini 10 mission and, with Michael C o l l i n s as
p i l o t , e f f e c t e d a successf'ul rendezvous and docking with
t h e Agena target vehicle. men, they i g n i t e d t h e large
Agena main engine t o propel t h e docked combination t o
a record a l t i t u d e of approximately 475 miles above t h e
Earth--the first manned operation o f a large r o c k e t
engine i n space. They later performed a completely
o p t i c a l rendezvous (without r a d a r ) on a second passive
Agena. A f t e r t h e rendezvous, while Young f l e w formation
on t h e passive Agena, C o l l i n s performed e x t r a v e h i c u l a r
a c t i v i t y t o it and recovered a micrometeorite d e t e c t i o n
experiment, accomplfahing an In-space r e t r i e v a l of t h e
d e t e c t o r t h a t had been o r b i t i n g the Earth f o r t h r e e months.
On July
The f l i g h t was concluded a f t e r 3 days and 44 revolutions-during which Gemini 10 t r a v e l e d a t o t a l d i s t a n c e of 1,275,
091 s t a t u t e miles. Splashdown occurred in the West A t l a n t i c ,
529 s t a t u t e miles e a s t of' Cape Kennedy, where Gemini 10
landed 2.6 miles from the USS GUADAUANBL w i t h i n eye and
camera range of t h e prime recovery v e s s e l .
�NAME:
Eugene A. Cernan (Commander, USN)
pilot
NASA Astronaut
Apollo 10 lunar module
BIRTHPLACE AND DATE: Born i n Chicago, Ill,, on March 14, 1934,
H i s mother, H r s . Andrew a. Cernan, r e s i d e s i n Bellwood,
Ill.
Brown h a i r ; blue eyes; height:
170 pounds.
PHYSICAL DESCRIPTION:
weight:
6 feet;
EDJCATION: araduated from Proviso Township High School i n
Maywood, Ill.; received a Bachelor of Science degree i n
E l e c t r i c a l Engineering from Purdue University and a Master
of Science degree i n Aeronautical Engineering from t h e
U.S. Naval Postgraduate School.
MARITAL STATUS: Married t o t h e former Barbara J . Atchley of
Houston, Tex.
CHILDREN:
Teresa Dawn, March 4 , 1963.
OTHER ACTIVITIES: H i s hobbies include gardening and a l l s p o r t s
activities.
ORQANIZATIONS: Member of Tau Beta P i , n a t i o n a l engineering s o c i e t y ;
Sigma X i , n a t i o n a l science research s o c i e t y ; and Phi Gamma
Delta, n a t i o n a l s o c i a l f r a t e r n i t y .
SPECIAL HONORS:
Awarded t h e NASA Exceptional Service Medal; t h e
Navy Astronaut Wings; and t h e Distinguished Flying Cross.
EXPERIENCE: Cernan, a United S t a t e s Navy commander, received h i s
commission through t h e Navy ROTC program a t Purdue. He
entered f l i g h t t r a i n i n g upon h i s graduation.
P r i o r t o a t t e n d i n g the Naval Postgraduate School, he was
assigned t o Attack Squadrons 126 and 113 a t t h e Miramar,
C a l i f . , Naval A i r S t a t i o n ,
H e has logged more than 3,000 hours flying time with more
than 2,810 hours i n jet a i r c r a f t .
CURRENT ASSIGNMENT: Commander Cernan was one of t h e t h i r d group
of a s t r o n a u t s s e l e c t e d by NASA i n October 1963.
�He occupied t h e p i l o t seat alongside Command Pilo"u0m
S t a f f o r d on t h e Gemini 9 mission. During t h i s 3-day
f l i g h t which began on June 3, 1966, t h e s p a c e c r a f t a t t a i n e d
a c i r c u l a r o r b i t o f 161 s t a t u t e miles; t h e crew used t h r e e
d i f f e r e n t techniques t o e f f e c t rendezvous with t h e previous ly launched Augmented Target Docking Aaap t e r ; and
Cernan logged two hours and t e n minutes o u t s i d e t h e spacec r a f t i n e x t r a v e h i c u l a r a c t i v i t y , The f l i g h t ended a f t e r
72 hours and 20 minutes with a p e r f e c t r e e n t r y and recovery as Gemini g landed within 1* miles of t h e prime
recovery s h i p USS WASP and 3/8 of a mile from t h e predetermined t a r g e t p o i n t .
He has s i n c e served as backup p i l o t f o r Gemini 12.
�APOLLO LAUNCH OPERATIONS
NASA's John F, Kennedy Space Center performs p r e f l i g h t
checkout, t e s t , and launch of t h e Apollo 10 space v e h i c l e , A
government-industry team of about 550 w i l l conduct t h e f i n a l
countdown from F i r i n g Room 3 of t h e Munch Control Center (LCC).
The f i r i n g room team i s backed up by more t h a n 5,000
persons who a r e d i r e c t l y involved i n launch o p e r a t i o n s a t KSC
from t h e time t h e v e h i c l e and s p a c e c r a f t s t a g e s a r r i v e a t t h e
c e n t e r u n t i l t h e launch i s completed,
--
I n i t i a l checkout of t h e Apollo s p a c e c r a f t i b conducted i n
work s t a n d s and i n t h e a l t i t u d e chrunbers i n t h e Manned Spacec r a f t Operations Building (MSOB) a t Kennew Space Center. A f t e r
completion of checkout t h e r e , t h e a s s a b l e d s p a c e c r a f t I s taken
t o t h e v e h i c l e Assembly Building (vAB) and mated with t h e launch
vehicle.
There t h e f i r s t i n t e g r a t e d s p a c e c r a f t and launch
v e h i c l e tests a r e conducted, The assembled space v e h i c l e i s
then r o l l e d o u t 60 t h e luanch pad f o r f i n a l p r e p a r a t i o n s and
countdown t o launch,
I n mid-October 1968, P l i g h t hardware f o r Apollo 10 began
a r r i v i n g a t Kennedy Space Center, j u s t as Apollo 7 was being
launched from Complex 34 on Cape Kennedy and as Apollo 8 and
Apollo 9 were undergoing checkout a t lCennedy Space Center.
The l u n a r module was t h e f i ~ s pt i e c e of' .&pollo 10 f l i g h t
hardware t o a r r i v e a t KSC, The two s t a g e s e r e moved i n t o t h e
a l t i t u d e chamber i n t h e Manned S p a c e c r a f t Operations Building
(MSOB) a f t e r a n i n i t i a l m c e i v i n g i n s p e c t i o n i n October, I n
t h e chamber &he I$I underwent systems tests and both unmanned
and manned chamber runs, During t h e s e runs t h e chamber a i r was
pumped out t o s i m u l a t e t h e vacuum of space a t a l t i t u d e s i n excesa
of 200,000 f e e t , There t h e s p a c e c r a f t systems and t h e a s t r o n a u t s g
l i f e support systems were t e s t e d ,
While t h e 1C4\11 was undergoLng p r e p a r a t i o n f o r i t s manned
a l t i t u d e chamber runs, t h e Apollo 10 command/service module
a r r i v e d a t KSC and a f t e r r e c e i v i n g i n s p e c t i o n , it, too, was
placed i n a n a l t i t u d e chamber i n t h e MSOB f o r systems t e s t s
and unmanned and manned chamber runs, The prime and back-up
crews p a r t i c i p a t e d i n t h e chamber r u n s on both t h e LM and t h e
CSM ,
I n January, t h e I24 and CSM were removed from t h e chambers.
A f t e r i n s t a l l i n g t h e landing g e a r on t h e LM and t h e SPS engine
nozzle on t h e CSM, t h e LM was encapsulated i n t h e s p a c e c r a f t
W a d a p t e r (SLA) and t h e CSM was mated t o t h e SLA. On February
6, t h e assembled s p a c e c r a f t was moved t o t h e VAB where i t was
mated t o t h e launch v e h i c l e ,
�The launch vehicle flight hardware began a r r i v i n g a t KSC
i n late November, and by t h e end of December t h e t h r e e stages
and t h e instrument unit were erected on t h e mobile launcher
i n high bay 2, This was the first time high bay 2, on t h e
west s i d e of t h e VAB, had been used f o r assembling a Saturn V,
Tests were conducted on Individual systems on each of t h e s t a g e s
and on t h e o v e r a l l launch vehicle before the spacecraft was
erected a t o p t h e vehicle,
After spacecraft erection, t h e spacecraft and launch vehicle
were e l e c t r i c a l l y mated and t h e first o v e r a l l test (plugs-in)
of t h e space vehicle was conducted, I n accordance with t h e
philosophy of a c c m p l i s h i n g as much of t h e checkout as possible
i n t h e VAB, t h e o v e r a l l test was conducted before t h e space
vehicle was moved t o t h e launch pad.
The plugs-in test v e r i f i e d the compatibility of the space
vehicle systems, ground support equipment, and o f f - s i t e support
f a c i l i t i e s by demonstrating t h e a b i l i t y of t h e systems t o proceed
through a simulated countdown, launch, and f l i g h t . During t h e
simulated f l i g h t portion of t h e test, t h e systems were required t o
respond t o both emergency and normal f l i g h t conditions,
The move t o Pad B from t h e VAB on March 11 occurred while
t h e Apollo 9 c i r c l e d t h e Earth i n t h e first manned test of t h e
lunar module.
Apollo LO w i l l mark the first launch a t Pad B on complex 39.
The first two unmanned Saturn V launches and t h e manned Apollo 8
and 9 launches took place at Pad A. It a l s o marked t h e f i r s t time
t h a t t h e t r a n s p o r t e r maneuvered around t h e VAB carrying a f u l l
load from high bay 2 on t h e 5-mile t r i p t o the launch pad,
The s t a c e vehicle F l i g h t Readiness Test was conducted i n e a r l y
April. Both t h e prime and backup crews p a r t i c i p a t e i n portions of
t h e FFtT, which is a f i n a l o v e r a l l t e s t of t h e space vehicle systems
and gmund support equipment when a l l systems are a s near as
possible t o a launch configuration,
After hypergolic f u e l s were loaded aboard the spsce vehicle,
and t h e launch vehicle first s t a g e f u e l (RP-1) was brought aboard,
t h e f i n a l major test of the space vehicle began. T h i s w a s the
countdown demonstration test ( c D ~ ) , a d r e s s r-?hearsal f o r the f i n a l
countdown t o launch, The CDM! f o r Apollo 10 was divided into a
"wet" and a "dryf' portion.
D u r i n g t h e first, o r "wet" portion, t h e
e n t i r e countdown, including propellant loading, rlas c a r r i e d out
down t o T-8.9 seconds, The astronaut crews did not p a r t i c i p a t e i n
t h e w e t CDm. A t t h e completion of the wet CDEP, t h e cryogenic
�.
p r o p e l l a n t s ( l i q u i d oxygen and liquid hydrogen) were off-loaded,
and t h e f i n a l p o r t i o n of t h e countdown was re-run, t h i s time
s i m u l a t i n g t h e f u e l i n g and w i t h t h e prime a s t r o n a u t crew p a r t i c i p a t i n g as t h e y will on launch day.
By t h e time Apollo 10 was e n t e r i n g t h e f i n a l phase of Its
checkout procedure a t Complex 39B, crews had a l r e a d y s t a r t e d t h e
checkout of Apollo 11 and Apollo 12. The Apollo 11 s p a c e c r a f t
completed a l t i t u d e chamber t e s t i n g and was mated t o t h e launch
v e h i c l e i n tne VAR i n mid-April a s t h e Apollo 12 CSM and LM
begari checkout i n t h e a l t i t u d e chambers.
Because of t h e complexity involved i n t h e checkout of t h e
363-foot-tall (110.6 meters) Apollo/Saturn V configuration, t h e
launch teams make use of e x t e n s i v e automation in t h e i r checkout.
Automation i s one of t h e major d i f f e r e n c e s i n checkout used on
Apollo compared t o t h e procedures used i n t h e Mercury and Gemini
programs.
Computers, data d i s p l a y equipment, and d i g i t a l d a t a techniques are used throughout t h e automatic checkout f r o m t h e time
t h e launch v e h i c l e i s e r e c t e d i n t h e VAB through l i f t o f f , A
s i m i l a r , but s e p a r a t e computer o p e r a t i o n c a l l e d ACE ( ~ c c e p t a n c e
Checkout Equipment) i s used t o v e r i f y t h e f l i g h t r e a d i n e s s of
t h e s p a c e c r a f t . Spacecraft checkout i s c o n t r o l l e d from s e p a r a t e
rooms i n t h e Manned Spacecraft Operations Building.
'
�LAUNCH C O M P U X 39
Launch Complex 39 f a c i l i t i e s a t t h e Kennedy Space Center
were planned and b u i l t s p e c i f i c a l l y f o r t h e Apollo S a t u r n V
program, t h e s p a c e v e h i c l e t h a t will be u s e d t o c a r r y a s t r o n a u t s
t o t h e Moon.
Complex 39 i n t r o d u c e d t h e m o b i l e concept of l a u n c h operat,ions,
a d e p a r t u r e from t h e f i x e d l a u n c h pad t e c h n i q u e s u s e d p r e v i o u s l y
a t Cape Kennedy and o t h e r l a u n c h s i t e s . S i n c e t h e e a r l y 1950's
when t h e first b a l l i s t i c misslles were launched, t h e f i x e d l a u n c h
concept had been used on NASA m i s s i o n s , T h i s method c a l l e d f o r
assembly, checkout and l a u n c h of a rocket a t one s i t e o m t h e l a u n c h
pad. I n a d d i t i o n t o t y i n g up t h e pad, t h i s method a l s o o f t e n l e f t
t h e flight equipment exposed t o t h e o u t s i d e i n f l u e n c e s of t h e
weather f o r extended p e r i o d s .
Using t h e mobile concept, t h e s p a c e v e h i c l e i s t h o r o u g h l y
checked i n a n e n c l o s e d b u i l d i n g b e f o r e i t i s moved t o the launch
pad f o r f i n a l p r e p a r a t i o n s . T h i s a f f o r d s g r e a t e r p r o t e c t i o n , a
more s y s t e m a t i c checkout p r o c e s s u s i r g computer t e c h n i q u e s and
a h i g h l a u n c h r a t e f o r t h e f u t u r e , s i n c e t h e pad time i s minimal.
S a t u r n V s t a g e s are s h i p p e d t o t h e Kennedy Space C e n t e r b y
ocean-going v e s s e l s and s p e c i a l l y d e s i g n e d a i r c r a f t , s u c h as the
Guppy, Apollo s p a c e c r a f t modules a r e t r a n s p o r t e d by a i r . The
s p a c e c r a f t components a r e f i r s t t a k e n t o t h e Manned Spacecraft
O p e r a t i o n s B u i l d i n g f o r p r e l i m i n a r y checkout, The S a t u r n V
s t a g e s are b r o u g h t immediately t o t h e V e h i c l e Assembly B u i l d i n g
a f t e r a r r i v a l a t t h e nearby t u r n i n g b a s i n .
Apollo 10 i s t h e f i r s t v e h i c l e t o be launched from Pad
B, Complex 39.
"11 p r e v i o u s S a t u r n V v e h i c l e s were launched
Pad A a t Complex 39, The h i s t o r i c first l a u n c h of t h e S a t u r n
V, d e s i g n a t e d Apollo 4 , took p l a c e Nov. 9, 1967 a f t e r a p e r f e c t
countdown and on-time l i f t o f f a t 7 a.m. EST. The second S a t u r n
V mission--Apollo 6--was conducted last A p r i l 4, The t h i r d
S a t u r n V m i s s i o n , Apollo 8 , was conducted last Dec. 21-27.
Apollo 9 was March 3-13, 1969.
The major components of Complex 39 i n c l u d e : (1) t h e
V e h i c l e Assembly B u i l d i n (VAB) where t h e A p o l l o 1 0 w a s
assembled and p r e p a r e d ; 2 ) t h e Launch C o n t r o l C e n t e r , where
t h e launch team c o n d u c t s t h o p r e l i m i n a r y checkout and f i n a l
countdown; ( 3 ) t h e mobile l a u n c h e r , upon which t h e Apollo 10
was e r e c t e d f o r checkout and from where i t w i l l be launched;
( 4 ) t h e mobile s e r v i c e s t r u c t u r e , which p r o v i d e s e x t e r n a l access
t o t h e s p a c e v e h i c l e a t t h e pad; ( 5 ) t h e t r a n s p o r t e r , which
a r r r i e s t h e s p a c e v e h i c l e and mobile l a u n c h e r , as w e l l as t h e
mobile s e r v i c e s t r u c t u r e t o t h e pad; ( 6 ) t h e crawlerway over
which t h e s p a c e v e h i c l e t r a v e l s from t h e VAB t o t h e l a u n c h pad;
and ( 7 ) t h e l a u n c h pad i t s e l f t ,
'T
�Vehicle Assembly build in^
The Vehicle Assembly Building i s t h e h e a r t of Launch Complex
39. Covering e i g h t a c r e s , i t i s where t h e 363-foot-tall space
v e h i c l e i s assembled and t e s t e d .
The VAB c o n t a i n s 129,482,000 cubic f e e t of space,
It i s
716 f e e t long, and 518 f e e t wide and it covers 343,500 square
f e e t of f l o o r space.
The foundat i o n of t h e VAB rests on 4,225 s t e e l p i l i n g s ,
each 16 inches i n diameter, d r i v e n from 150 t o 170 f e e t t o bedrock. If placed end t o end, t h e s e p i l i n g s would extend a d i s t a n c e
of 123 miles. The s k e l e t a l s t r u c t u r e of t h e b u i l d i n g c o n t a i n s
approximately 60,000 t o n s of s t r u c t u r a l s t e e l . The e x t e r i o r i s
covered by more t h a n a m i l l i o n square f e e t of i n s u l a t e d aluminum
siding,
The b u i l d i n g i s divided i n t o a h i g h bay a r e a 525 f e e t high
and a low bay area 210 f e e t high, with both a r e a s s e r v i c e d by a
t r a n s f e r a i s l e f o r movement of v e h i c l e s t a g e s .
The low bay work a r e a , approximately 442 f e e t wide and 274
f e e t long, c o n t a i n s e i g h t s t a g e - p r e p a r a t i o n and checkout c e l l s .
These c e l l s a r e equipped with systems t o s i m u l a t e s t a g e i n t e r f a c e
and o p e r a t i o n with o t h e r s t a g e s and t h e instrument u n i t of t h e
S a t u r n V launch v e h i c l e .
A f t e r t h e Apollo 10 launch v e h i c l e upper s t a g e s a r r i v e d a t
t h e Kennedy Space Center, t h e y were moved t o t h e low bay of t h e
VAB.
Here, t h e second and t h i r d s t a g e s underwent acceptance and
checkout t e s t i n g p r i o r t o mating w i t h t h e S-IC f i r s t s t a g e a t o p
mobile launcher 3 i n t h e high bay a r e a .
The high bay provides f a c i l i t i e s f o r assembly and c h e c k o ~ t
of both t h e launch v e h i c l e and s p a c e c r a f t . It c o n t a i n s f o u r
s e p a r a t e bays f o r v e r t i c a l assembly and checkout. A t p r e s e n t ,
t h r e e bays a r e equipped, and t h e f o u r t h w i l l be r e s e r v e d f o r
p o s s i b l e changes i n v e h i c l e c o n f i g u r a t i o n .
--
--
Work platforms
some as high a s t h r e e - s t o r y b u i l d i n g s
in
t h e high bays provide a c c e s s by surrounding t h e v e h i c l e a t varying
l e v e l s . Each high bay has f i v e platforms, Each platform c o n s i s t s
of two b i - p a r t i n g s e c t i o n s t h a t move i n from opposite s i d e s and
mate, providing a 360-degree a c c e s s t o t h e s e c t i o n of t h e space
v e h i c l e being checked.
A 10,000-ton-capacity a i r c o n d i t i o n i n g system, s u f f i c i e n t
t o cool about 3,000 homes, h e l p s t o c o n t r o l t h e environment within
t h e e n t i r e o f f i c e , l a b o r a t o r y , and workshop complex l o c a t e d i n s i d e
t h e low bay a r e a of t h e VAB. A i r c o n d i t i o n i n g i s a l s o fed t o
i n d i v i d u a l platform l e v e l s l o c a t e d around t h e v e h i c l e .
�There a r e 141. l i f t i n g devices i n t h e VAB, ranging from onet o n h o i s t s t o two 250-ton h i g h - l i f t brrdge cranes.
The mobile launchers, c a r r i e d by t r a n s p o r t e r v e h i c l e s , move
i n and out of t h e VAB through f o u r doors i n t h e high bay a r e a , one
i n each of t h e bays, Each door i s shaped l i k e an i n v e r t e d T. They
a r e 152 f e e t wide and 114 f e e t high a t t h e base, narrowing t o 76
f e e t i n w i d t h . T o t a l door h e i g h t i s 456 f e e t ,
The Lower s e c t i o n of each door i s of t h e a i r c r a f t hangar t y p e
t h a t s l i d e s h o r i z o n t a l l y on t r a c k s . Above t h i s a r e seven t e l e s c o p i n g v e r t i c a l l i f t p a n e l s s t a c k e d one above t h e o t h e r , each 50 f e e t
high and d r i v e n by a n i n d i v i d u a l motor, ]Each p a n e l s l i d e s over
t h e next t o c r e a t e a n opening l a r g e enough t o p e n n i t passage of
t h e mobile launcher,
Munch Control Center
Adjacent t o t h e VAB i s t h e h u n c h Control Center (LcC). This
four-story s t r u c t u r e i s a r a d i c a l d e p a r t u r e from t h e dame-shaped
blockhouses a t o t h e r launch s i t e s ,
The e l e c t r o n i c " b r a i n " of Launch Complex 39, t h e LCC was used
f o r checkout and t e s t o p e r a t i o n s while Apollo 10 was being assembled
i n s i d e t h e VAB. The LCC c o n t a i n s d i s p l a y , monitoring, and c o n t r o l
equipment used f o r both checkout and launch o p e r a t i o n s .
The b u i l d i n g has t e l e m e t e r checkout s ' t a t i o n s on i t s second
f l o o r , and f o u r f i r i n g rooms, one f o r each high bay of t h e VAB,
on i t s t h i r d f l o o r , Three f i r i n g rooms conta%n i d e n t i c a l s e t s of
c o n t r o l and monitoring equipment, s o t h a t launch of a v e h i c l e and
checkout of o t h e r s t a k e p l a c e simultaneously, A ground computer
f a c i l i t y i s a s s o c i a t e d with each f i r i n g room,
The high speed computer d a t a l i n k i s p r o ided between t h e LCC
and t h e mobile launcher f o r checkout of t h e 1 unch v e h i c l e . This
l i n k can be connected t o t h e mobile launcher t e i t h e r t h e VAB
o r a t t h e pad,
I
The t h r e e equipped f i r i n g rooms have some 450 consoles which
c o n t a i n c o n t r o l s and d i s p l a y s r e q u i r e d f o r the1 checkout process.
The d i g i t a l d a t a l i n k s connecting taith t h e high b a y areas of t h e
VAB and t h e launch pads car-ry v a s t amounts of data r e q u i r e d during
checkout and launch,
I
I.
There a r e 15 d i s p l a y systems i n each LCC i r i n g room, with
each system capable of providing d i g i t a l infornlation i n s t a n t a n e ously,
�S i x t y t e l e v i s i o n cameras a r e p o s i t i o n e d around t h e Apollo/
S a t u r n V t r a n s m i t t i n g p i c t u r e s on 10 modulated channels. The LCC
f i r i n g room a l s o c o n t a i n s 112 o p e r a t i o n a l intercommunication
channels used by t h e cpews i n t h e checkout and launch countdown.
Mobile Launcher
The mobile l a u n c h e r i s a t r a n s p o r t a b l e launch base and
u m b i l i c a l tower f o r t h e space v e h i c l e . Three mobile launchers a r e
used a t Complex 39.
The launcher base i s a two-story s t e e l s t r u c t u r e , 25 f e e t h i g h ,
160 f e e t long, and 135 f e e t wide. It i s p o s i t i o n e d on s i x s t e e l
p e d e s t a l s 22 f e e t high when i n t h e VAB o r a t t h e launch pad, A t
t h e launch pad, i n a d d i t i o n t o t h e s i x s t e e l p e d e s t a l s , f o u r extend a b l e columns a l s o are used t o s t i f f e n t h e mobile launcher a g a i n s t
rebound l o a d s , i f t h e S a t u r n engines c u t o f f ,
The u m b i l i c a l tower, extending 398 f e e t above t h e launch p l a t form, i s mounted on one end of t h e launcher base. A hammerhead
c r a n e a t t h e t o p h a s a hook h e i g h t of 376 f e e t above t h e deck with
a t r a v e r s e r a d i u s of 85 f e e t from t h e c e n t e r of t h e tower.
The 12-million-pound mobile launcher s t a n d s 445 f e e t high
when r e s t i n g on its p e d e s t a l s , The base, covering about h a l f an
a c r e , i s a compartmented s t r u c t u r e b u i l t of 25-foot s t e e l g i r d e r s ,
The launch v e h i c l e s i t s over a 45-foot-square opening which
a l l o w s an o u t l e t f o r engine exhausts i n t o t h e launch pad t r e n c h
c o n t a i n i n g a flame d e f l e c t o r . T h i s opening i s l i n e d w i t h a r e p l a c e a b l e s t e e l b l a s t s h i ~ l d ,independent of t h e s t r u c t u r e , and
i s cooled by a water c u r t a i n i n i t i a t e d two seconds a f t e r l i f t o f f .
There a r e n i n e h y d r a u l i c a l l y - o p e r a t e d s e r v l c e arms on t h e
u m b i l i c a l tower, These s e r v i c e arms s u p p o r t l i n e s f o r t h e v e h i c l e
u m b i l i c a l systems and provide a c c e s s f o r personnel t o t h e s t a g e s
as well as t h e a s t r o n a u t crew t o t h e s p a c e c r a f t .
On Apollo 10, one of t h e s e r v i c e arms i s r e t r a c t e d e a r l y i n
t h e count. The Apollo s p a c e c r a f t a c c e s s arm i s p a r t i a l l y r e t r a c t e d a t T-43 minutes, A t h i r d s e r v i c e am i s r e l e a s e d a t T-30
seconds, and a f o u r t h a t about T-16.5 seconds, The remaining
f i v e arms a r e s e t t o swing back a t v e h i c l e f i r s t motion a f t e r T-0.
The s e r v i c e arms a r e equipped w i t h a backup r e t r a c t i o n system
i n c a s e t h e primary mode f a i l s .
�The Apollo a c c e s s arm ( s e r v i c e arm g ) , l o c a t e d a t t h e 320f o o t l e v e l above t h e l a u n c h e r base, provides a c c e s s t o t h e spacec r a f t c a b i n f o r t h e c l o s e o u t team and a s t r o n a u t crews, The f l i g h t
crew w i l l board t h e s p a c e c r a f t s t a r t i n g about T-2 hours, 40 minutes
i n t h e count, The a c c e s s a m w i l l be moved t o a parked position,
12 degrees from t h e s p a c e c r a f t , a t about T-43 minutes, T h i s i s a
d i s t a n c e of about t h r e e f e e t , whish p e r m i t s a r a p i d r e c o n n e c t i o n
of t h e arm t o t h e s p a c e c r a f t i n t h e event of a n emergency condition.
The arm i s f u l l y r e t r a c t e d a t t h e T-5 mlnute mark i n t h e count,
The Apollo 10 v e h i c l e i s secured t o t h e mobile l a u n c h e r by
f o u r combination s u p p o r t and hold-down arms mounted on t h e launcher
deck. The hold-down ams are c a s t i n one p i e c e , about 6 x 9 feet
a t t h e b a s e and 10 f e e t t a l l , weighing more t h a n 20 t o n s . Damper
s t r u t s s e c u r e t h e v e h i c l e n e a r i t s top.
A f t e r t h e engines i g n i t e , the arms hold Apollo LO f o r about
s i x seconds u n t i l t h e engines build u p t o 95 p e r c e n t t h r u s t and
o t h e r monitored systems i n d i c a t e they a r e f u n c t i o n i n g p r o p e r l y .
The arms r e l e a s e on r e c e i p t of a launch commit s i g n a l a t t h e z e r o
mark i n t h e count. B u t t h e v e h i c l e i s prevented from a c c e l e r a t i n g
t o o r a p i d l y by c o n t r o l l e d r e l e a s e mechanisms.
Transporter
The six-million-pound t r a n s p o r t e r s , t h e l a r g e s t t r a c k e d vehi c l e s known, move mobile l a u n c h e r s i n t o t h e VAB and mobile launchers
w i t h assembled Apollo space v e h i c l e s t o t h e launch pad.
They also
a r e used t o t r a n s f e r t h e mobile s e r v i c e s t r u c t u r e t o and from t h e
launch pads. Two t r a n s p o r t e r s are i n u s e a t Complex 39,
The TYansporter i s 131 f e e t long and 114 f e e t wide. The
v e h i c l e moves on f o u r double-tracked c r a w l e r s , each 10 feet high
and 40 f e e t long, Each shoe on t h e c r a w l e r t r a c k i s seven f e e t six
i n c h e s i n l e n g t h and weighs about a ton.
S i x t e e n t r a c t i o n motors powered by f o u r 1,000-kilowatt gene r a t o r s , which i n t u r n a r e d r i v e n by two 2,750-ho~sepower d i e s e l
engines, p r o v i d e t h e motive power f o r t h e t r a n s p o r t e r . Two 750k w g e n e r a t o r s , d r i v e n by two 1,065-horsepower d i e s e l engines,
power t h e jacking, s t e e r i n g , l i g h t i n g , v e n t i l a t i n g and e l e c t r o n i c
systems.
Maximum speed of t h e t r a n s p o r t e r is about one-mile-per-hour
loaded and about two-miles-per-hour unloaded, A five-mile t r i p
t o Pad I3 with a mobile launcher, made a t l e s s t h a n maximum speed,
t a k e s approximately 10-12 hours,
�The t r a n s p o r t e r has a l e v e l i n g system designed t o keep t h e
t o p of t h e space v e h i c l e v e r t i c a l within plus-or-minus 10 minutes
of a r c
about t h e dimensions of a basketball.
--
This system a l s o provides l e v e l i n g operations required t o
n e g o t i a t e t h e f i v e percent ramp which l e a d s t o t h e launch pad and
keeps t h e load l e v e l when it i s r a i s e d and lowered on p e d e s t a l s
both a t t h e pad and within t h e VAB.
The o v e r a l l
level t o the top
transportation.
b a l l diamond (90
height of t h e t r a n s p o r t e r i s 20 f e e t from ground
deck on which t h e mobile launcher i s mated f o r
The deck is f l a t and about t h e s i z e of a baseby 90 f e e t ) ,
Two operator c o n t r o l cabs, one a t each end of t h e c h a s s i s
located diagonally opposite each other, provide t o t a l l y enclosed
s t a t i o n s f r a m which a l l operating and c o n t r o l functions a r e
coordinated.
Crawlerway
The t r a n s p o r t e r moves on a roadway 131 f e e t wide, divided
by a median s t r i p . This i s almost a s broad a s an eight-lane
turnpike and i s designed t o accommodate a combined weight of about
18 m i l l i o n pounds.
The roadway i s b u i l t i n t h r e e l a y e r s with an average depth
of seven f e e t . The roadway base l a y e r i s two-and-one-half f e e t
of hydraulic f i l l compacted t o 95 percent density. The next l a y e r
c o n s i s t s of t h r e e f e e t of crushed rock packed t o maximum density,
followed by a l a y e r of one f o o t of s e l e c t e d hydraulic fill. The
bed I s topped and s e a l e d w i t h an a s p h a l t prime coat.
On top of t h e t h r e e l a y e r s i s a cover of r i v e r rock, e i g h t
inches deep on t h e curves and s i x inches deep on t h e straightway,
This l a y e r reduces the f r i c t i o n during s t e e r i n g and helps
d i s t r i b u t e the load on the t r a n s p o r t e r bearings.
Mobile Service S t r u c t u r e
A 402-foot-tall,
9.8-million-pound tower i s used t o s e r v i c e
t h e Apollo launch vehicle and spacecraft a t t h e pad. The 40-story
s t e e l - t r u s s e d tower, c a l l e d a mobile s e r v i c e s t r u c t u r e , provides
360-degree platform access t o t h e Saturn launch vehicle and t h e
Apollo s p a c e c r a f t
.
--
The s e r v i c e s t r u c t u r e has f i v e platforms
two self-propelled
Two e l e v a t o r s carry personnel and
equipment between work platforms. The platforms can open and c l o s e
around t h e 363-foot space vehicle,
and t h r e e fixed, but movable.
�A f t e r dep<:*sitingt h e mobile launcher wLth i t s space
vehicle on t h e pad, the t r 8 a n s p o r t e r r e t u r n s t o a parking
a r e a about 13,000 f e e t from pad B. There i t p i c k s up the
mobile s e r v i c e s t r u c t u r e and moves it t o t h e launch pad.
A t t h e pad, t h e huge tower i s lowered and secured t o f o u r
mount mechanisms.
The t o p t h r e e work platforms are l o c a t e d i n f i x e d
p o s i t i o n s which s e r v e t h e Apollo s p a c e c r a f t , The two lower
movable platforms s e r v e t h e S a t u r n V.
The mobile s e r v i c e s t r u c t u r e remains i n p o s i t i o n u n t i l
about T-11 hours when it i s removed from i t s mounts and r e turned t o t h e parkinff area.
Water Deluge System
4 water deluge system w i l l provide a m i l l i o n g a l l o n s
of i n d u s t r i a l water f o r c o o l i m and f i r e prevention d u r i n g
launch of Apollo 10. Once t h e s e r v i c e anns a r e r e t r a c t e d a t
l i f t o f f , a s p r a y system w i l l come on t o c o o l t h e s e arms from
t h e h e a t of t h e f i v e S a t u r n F-1 engines d u r i n g l i f t o f f .
On t h e deck of t h e mobile launcher are 29 water nozzles.
This deck deluge w i l l s t a r t immediately a f t e r l i f t o f f and w i l l
pour a c r o s s t h e f a c e of t h e launcher f o r 30 seconds a t t h e r a t e
of 50,000 gallons-per-minute,
a f t e r 30 seconds, t h e flow w i l l
be reduced t o 20,000 gallons-per-minute,
Positioned on both s i d e s of t h e flame t r e n c h a r e a
s e r i e s of nozzles which w i l l begin pouring water at 8,000
gallons-per-minute, 10 secorcl s before l i f t o f f . This water
w i l l be d i r e c t e d over t h e flame d e f l e c t o r .
Other f l u s h mounted nozzles, p o s i t i o n e d around t h e pad,
w i l l wash away any f l u i d s p i l l a s a p r o t e c t i o n a g a i n s t f i r e
hazards.
Water spray systems a l s o a r e a v a i l a b l e along t h e
e g r e s s r o u t e t h a t t h e a s t r o n a u t s and c l o s e o u t crews would
follow i n c a s e a n emergency evacuation w a s required.
Flame Trench and D e f l e c t o r
The flame t r e n c h i s 58 f e e t wide and approximately s i x
f e e t above mean s e a l e v e l a t t h e base. The h e i g h t of t h e
t r e n c h and d e f l e c t o r i s approximately 42 f e e t .
�The Tiam-.d e f l e c t o r weighs about 1.3 m i l l i o n pounds and
i s s t o r e d o u t s i d e t h e flame t r e n c h on rails. Wehn i t i s moved
beneath the launcher, i t i s raised h y d r a u l i c a l l y i n t o p o s i t i o n ,
The d e f l e c t o r i s covered w i t h a four-and-one-half-inch t h i c k ness of r e f r a c t o r y c o n c r e t e c o n s i s t i n g of a v o l c a n i c a s h
aggregate and a calcuim aluminate binder. The heat and b l a s t
of t h e engines a r e expected t o wear about t h r e e - q u a r t e r s of a n
i n c h from t h i s r e f r a c t o r y s u r f a c e d u r i n g t h e Apollo l o launch.
pad Areas
Both Pad A and Pad B of -hunch Complex 39 are roughly
octagonal I n shape and cover about one f o u r t h of a square
mile of t e r r a i n .
The c e n t e r of t h e pad i s a hardstand c o n s t r u c t e d of
heavily reinforced concrete. I n addition t o supporting t h e
weight of t h e mobile launcher and t h e Apollo S a t u r n V v e h i c l e ,
it a l s o must support t h e 9.8-million-pound mobile s e r v i c e
s t r u c t u r e and 6-million-pound t r a n s p o r t e r , a l l a t t h e same
time. The t o p of t h e pad s t a n d s some 48 f e e t above s e a l e v e l ,
Saturn V p r o p e l l a n t s -- l i q u i d oxygen, l i q u i d hydrogen
and RP-1
are s t o r e d n e a r t h e pad perimeter.
--
S t a i n l e s a s t e e l , vacuum-jacketed p i p e s c a r r y t h e l i q u i d
oxygen (LOX) and l i q u i d hydrogen from t h e s t o r a g e t a n k s t o
t h e pad, up t h e mobile launcher, and f i n a l l y i n t o t h e launch
v e h i c l e p r o p e l l a n t tanks.
LOX i s supplied from a 900,000-gallon s t o r a g e t a n k .
c e n t r i f u g a l pump w i t h a d i s c h a r g e p r e s s u r e of 320 poundsper-square-inchpumps LOX t o t h e v e h i c l e a t flow rates as high
as 10,000-gallons-per-minute.
A
Liquid hydrogen, u s e d i n t h e second and t h i r d s t a g e s ,
i s s t o r e d i n an 850,000-gallon tank, and i s s e n t through
1,500 f e e t of 10-inch, vacuum-Jacketed i n v a r pipe. A vapori z i n g h e a t exchanger p r e s s u r i z e s t h e s t o r a g e tank t o 60 p s i
f o r a 10,000 gallons-per-munute flow r a t e ,
The RP-1 f u e l , a high grade of kerosene i s s t o r e d i n
t h r e e tanks--each with a c a p a c i t y of 86,000 g a l l o n s . It i s
pumped a t a r a t e of 2,000 gallons-per-minute a t 175 p s i g ,
The Complex 39 pneumatic system i n c l u d e s a convertercompressor f a c i l i t y , a pad high-pressure gas s t o r a g e b a t t e t y ,
a high-pressure s t o r a g e b a t t e r y i n t h e VAB, low and high-press u r e , cross-country supply l i n e s , h i ~ h - p r e s s u r e hydrogen s t o r a g e
and conversion equipment, and pad d i s t r i b u t i o n pipinp, t o pneumatic c o n t r o l panels, The v a r i o u s purging systems r e q u i r e 187,000
pounds of l i q u i d n i t r o g e n and 21,000 g a l l o n s of helium,
�Pad B is v i r t u a l l y a twin of Pad A , The $op sf Pad B
i s 5 f e e t h i g h e r i n e l e v a t i o n above mean sea l e v e l than Pad
A t o provide b e t t e ~dratnage of t h e general area p tus b e t t e r
drainage from h o P d i n ~and burn ponds.
The e l e c t r i c a l s u b s t a t i o n f o r Pad B is l o c a t e d undern e a t h t h e w e s t s l o p e of t h e p a d whereas t h e corresponding
s u b s t a t i o n f o r Pad A i s i n t h e open approximately 150 f e e t
from t h e lower edge of t h e west s l o p s of t h e pad, The pad
B d e s i g n change was made t o harden t h e s u b s t a t i o n a g a l n s t tfre
launch environment. The only o t h e r major d i f f e r e n c e i s i n
t h e l o c a t i o n of t h e i n d u s t r i a l / f i r e / p o t a b l e water valve p i t .
A t Pad A, i t ' s on t h e west s i d e of t h e Pad and a t Pad B i t ' s
on t h e east s i d e of t h e pad. The d i f f e r e n c e r e s t s i n t h e r o u t ing of water l i n e s a l o n g s i d e t h e crawlerway.
Basic c o n s t r u c t i o n work on Pad B began on Dec, 7, 1964,
and t h e f a c i l i b y was accepted by t h e government on August 22,
1966. The intemrening period h a s been s p e n t i n equipping t h e
pad and b r i n g i n g it up t o launch r e a d i n e s s ,
Mission Control Center
The Hission Control Center a t t h e Manned Spacecraft
Center, Houston, i s t h e f o c a l p o i n t f o r Apollo flight c o n t r o l
a c t i v i t i e s . 'Pbe c e n t e r r e c e i v e s t r a c k i n g and t e l e m e t r y d a t a
from the Manned Space F l i g h t Network, p r o c e s s e s t h i s d a t a
through t h e Mission Control Center Real-Time Computer Complex,
and d i s p l a y s t h i s d a t a t o t h e f l i g h t c o n t r o l l e r s and e n g i n e e r s
i n t h e Mission Operations Control Room and staff support rooms.
The Manned Space F l i g h t Network t r a c k i n g and d a t a
acqufaftfon s t a t i o n s link t h e f l i g h t controllers a t t h e center
t o the spacecraft,
For Apollo 10 a l l network s t a t i o n s w i l l be remote s i t e s ,
t h a t is, without f l i g h t c o n t r o l teams, A l l u p l i n k commands and
voice c o m n i c a t i o n s w i l l o r i g i n a t e from Houston, and t e l e m e t r y
d a t a w i l l be s e n t back t o Houston a t high speed r a t e s (2,400
b i t s - p e r - s e c o n d ) , on two s e p a r a t e d a t a l i n e s . They can be
e % t h e r r e a l time o r playback information.
S i g n a l flow f o r voice c i r c u i t s between Houston and
t h e remote s i t e s i s v i a commercial c a r r i e r , u s u a l l y s a t e l l i t e ,
wherever p o s s i b l e u s i n g leased l i n e s which a r e part of t h e NASA
n i c a t i o n s Network.
Comands a r e s e n t from Houston t o NASA's Goddard Space
F l i g h t Center, Greenbelt, Md., on l i n e s which l i n k computers
a t t h e two p o i n t s . The Goddard communication computers prov i d e automatic switching f a c i l i t i e s and speed b u f f e r i n g f o r t h e
command d a t a , Data a r e t r a n s f e r r e d from Goddard t o remote s i t e s
on high speed (2,400 bits-per-second) l i n e s . Command loads a l s o
can be s e n t by t e l e t y p e from Houston t o the remote sites a t 100
wor8-s-per-minute . Again, Goddard computers provide s t o r a g e and
switching f u n c t i o n s .
-more-
�Telemetry data at the remote site are received by
the RF receivers, processed by the pulse aede modulation
ground stations, and transferred to the 642B remote-site
telemetry computer for storage. Depending on the format
selected by the telemetry controller at Houston, the 642B
willsend the desired format through a 2010 data trans
mission unit which provides parallel to serial conversion,
and drives a 2,400 bit-per-second mode.
The data mode converts the digital serial data to
phase-shifted keyed tones which are fed to the high speed
data lines of the comunications network.
Tracking data are sent from the sites in a low
speed (100 words) teletype format and a 240-bit block high
speed (2,400 bits) format. Data rates are one sample-6
seconds for teletype and 10 samples (frames) per second for
high speed data.
All high-speed data, whether tracking or telemetry,
which originate at a remote site are sent to cfoddard on highspeed lines. Goddard reformats the data when necessary and
sends them to Houston in 600-bit blocks at a 40,800 bits-persecond rate. Of the 600-bit block, 480 bits are reserved for
data, the other 120 bits for address, sync, intercomputer instructions, and polynominal error encoding.
All wideband 40,800 bits-per-second data originating at
Houston are converted to high speed (2,400 bits-per-second)
data at Goddard before being transferred to the designated
remote site.
�MANNED SPACE FLIGHT NETWORK
The Manned Space F l i g h t Network (MSFN) w i l l support
the complete Apollo s p a c e c r a f t , o p e r a t i n g a t l u m r d i s t a n c e ,
f o r t h e first t i m e i n Apollo 10, The network had i t s i n i t i a l
s e r v i c e w i t h l u n a r d i s t a n c e s i n Apollo 8 last December, b u t
that flfght d i d n o t c a r r y t h e l u n a r module.
For Apollo 10, the MSPN will employ a'? ground s t a t i o n s
( i n c l u d i r t ~thtSee wing, or backup, s i t e s ) , f s ~ i rinstrumented
shLps, and s i x to e i g h b instrumented aiseraft, t o track spacecraft position and furnish a large volume of e o m u n i c a t i o n s ,
t e l e v i s i o n arad telemetry servfces,
Essentially, t h e e n t i r e network I s d e s i ~ n e dt o provide
r e l i a b l e and continuous c o m u n i c ~ t i o n sw i t h t h e a s t r o n a u t s ,
launch v e h i c l e and s p a c e c r a f t from l i f t o f f through l u n a r o r b i t
t o splashdown. It w i l l keep ground c o n t r o l l e r s i n c l o s e cont a c t with t h e s p a c e c r ~ f tand a s t r o n a u t s a t a l l times, except
f o r approximately 45 minutes when Apollo 1 0 w i l l be behind
t h e Moon d u r i n g each l u n a r o r b i t =nd t h e time between s t a t i o n s
w h i l e i n Earth o r b i t ,
As tke space v e h i c l e l i f t s o f f from Kennedy Space Center,
t h e t r a c k i n g s t a t i o n s w i l l be watchine; it. A s t h e S a t u r n ascends,
v o i c e and d a t a w i l l be i n s t a n t a n e o u s l y t r a n s m i t t e d t o Mission
.
Control Center (MCC) i n Houston. Data w i l l be run through
computers a t MCC f o r v i s u a l d i s p l a y t o f l i g h t c o n t r o l l e r s .
Depending on t h e launch azimuth, a s t r i n g of 30-footdiameter antennas around t h e Earth w i l l keep t a b s on Apollo 10
and t r a n s m i t information back t o Houston: beginning with t h e
s t a t i o n a t Merritt I s l a n d , F l a , ; thence Grand Bahama I s l a n d ,
Bermuda; t h e t r a c k i n g s h i p Vanguard; Canary I s l a n d ; Carnarvon,
Australia; Hawaii, t r a c k i n g s h i p Redstone, Guaymas, Mexico;
and Corpus Christi, T e x .
To i n j e c t Apollo 1 0 i n t o t r a n s l u n a r t r a j e c t o r y WCC w i l l
send a s i g n a l through one of t h e land s t a t i o n s o r one of t h e
Apollo s h i p s i n t h e P a c i f i c . A s t h e s p a c e c r a f t head f o r t h e
Moon, t h e engine burn w i l l be monitored by t h e s h i p s and a n Apollo
Range I n s t r u m e n t a t i o n A i r c r a f t ( A R I A ) , The A R I A p r o v i d e s a
r e l a y f o r t h e a s t r o n a u t s 1 v o i c e s and d a t a communication w i t h
Houston.
As t h e s p a c e c r a f t moves away from Earth, t h e s m a l l e r
30-foot diameter antennas communicate first w i t h t h e spacec r a f t . A t a s p a c e c r a f t a l t i t u d e of 10,000 miles the t r a c k i n g
f u n c t i o n goes t o t h e more powerful 85-foot antennas. These
a r e l o c a t e d n e a r Madrid, Spain; Goldstone, C a l i f . ; and Canberra, Australia.
�A R C T I C OCEAN
1 0 1 W C I C I f I C OCfAU
I N D I A N OCEAN
M A N N E D SPACE FLIGHT TRACKING NETWORK
�The 85-foot a n t e n n a s are spaced a t approximately 120degree i n t e r v a l s around U r t h $0 at least one antenna has thp
Moon in view a t glla times. As &he & r t h revolveg from we@C f;o
east, one s t a t i o n hands over c o n t r o l t o t h e next s t a t i o n a@ i t
moves i n t o view of Che s p a c e c r a f t . I n this way, cont$nuous
d a t a and communication flow 1s maintained.
Data are c o n s t a n t l y r e l a y a d back through t h e huge
antennas and t r a n s m i t t e d v i a t h e NASA Communications Network
(NASCOM)
a h a l f m i l l i o n milea of land and underseas c a b l e s
and r a d i o c i r c u i t s , i n c l u d i n g t h o s e t h m ugh communications
s a t e l l i t e s , t o MCC, T h i s information i s f e d i n t o computers
f o r v i s u a l d i s p l a y i n Missidn Control. For example, a d i s p l a y
would show t h e exact p o s i t i o n of t h e s p a c e c r a f t on a l a r g e map.
Returning data could i n d i c a t e a drop i n power o r some o t h e r
d i f f i c u l t y which would r e s u l t i n a red l i g h t going on t o a l e r t
a f l i g h t controller t o corrective action.
Returning data flowing t o t h e Earth s t a t i o n s g i v e t h e
necessary information f o r commanding mid-course maneuvers t o
keep t h e Apollo 1 0 i n a proper t r a j e c t o r y f o r o r b i t i n g , t h e
Moon, While t h e f l i g h t i s i n t h e v i c i n i t y of t h e Moon, t h e s e
data i n d i c a t e t h e amount of r e t r o g r a d e burn necessary f o r t h e
s e r v i c e module engine t o p l a c e t h e s p a c e c r a f t u n i t s i n l u n a r
orbit.
Once t h e l u n a r module s e p a r a t e s from t h e command module/
s e r v i c e module and goes i n t o a s e p a r a t e l u n a r o r b i t , t h e MSFN
w i l l be r e q u i r e d t o keep t r a c k of both c r a f t and provide cont i n u o u s two-way communicatlons and t e l e m e t r y between them and
t h e Earth, The prime antenna a t each of t h e t h r e e MSFN deep
space t r a c k i n g s t a t i o n s w i l l handle one c r a f t while t h e wing
o r back-up antenna a t each of t h e s e s t a t i o n s w i l l handle t h e
o t h e r c r a f t d u r i n g each pass.
Continuous t r a c k i n g and a c q u i s i t i o n of d a t a between
Earth and t h e Apollo s p a c e c r a f t w i l l provide support f o r t h e
Apollo rendezvous and docking maneuvers. T h i s information a l s o
w i l l be used t o determine t h e time and d u r a t i o n of t h e s e r v i c e
module propulsion engine burn r e q u i r e d t o place t h e command
s e r v i c e module i n t o a p r e c i s e t r a j e c t o r y f o r reenterkng t h
E a r t h ' s atmosphere a t t h e planned l o c a t i o n . A s t h e s p a c e c r a f t
moves toward E a r t h a t about 25,000 miles-per-hour, i t must ree n t e r a t t h e proper angle.
l
Data coming t o t h e v a r i o u s t r a c k i n g s t a t i o n s and s N p s
a r e f e d i n t o t h e computers a t MCC. From computer c a l c u l a t i o n s . ,
t h e P l i g h t c o n t r o l l e r s w i l l provide t h e r e t u r n i n g s p a c e c r a f t
with t h e necessary information t o m k e a n a c c u r a t e r e e n t r y .
Appropriate MSFN s t a t i o n s , i n c l u d i n g t r a c k i n g s h i p s and a irc r a f t p o s i t i o n e d i n t h e P a c i f i c f o r t h i s event a r e on hand t o
provide support d u r i n g r e e n t r y . An A R I A a i r c r a f t w i l l r e l a y
a s t r o n a u t voice communications t o MCC and Qntennas on r e e n t r y
s h i p s w i l l follow the s p a c e c r a f t .
�During t h e journey t o t h e Moon and back, t e l e v i s i o n w i l l
be received from t h e s p a c e c r a f t a t t h e t h r e e 85-foot antennas
around the world, i n Spain, C a l i f o r n i a , and A u s t r a l i a , Scan
c o n v e r t e r s permit imediat e t r a n s m i s s i o n of c o m e r c i a 1 q u a l i t y
t e l e v i s i o n v i a NASCOM t o Mission Control where I t w i l l be rel e a s e d t o TV networks.
NASA Communications Network
The NASA Communications Network (NASCOM) c o n s i s t s of
s e v e r a l systems of d i v e r s e l y r o u t e d communications channels
l e a s e d on communications satellites, common c a r r i e r systems
and high frequency r a d i o f a c i l i t i e s where necessary t o provide the access links,
The system c o n s i s t s of both narrow and wide-band
channels, and some TV channels, Included a r e a v a r i e t of
t e l e g r a p h , voice, and d a t a systems ( d i g i t a l and analog7 with
s e v e r a l d i g i t a l data rates. Wide-band systems do not extend
overseas. A l t e r n a t e r o u t e s o r redundancy provide added r e l i a bility,
A primary switching c e n t e r and i n t e r m e d i a t e switching
and c o n t r o l p o i n t s provide c e n t r a l i z e d f a c i l i t y and t e c h n i c a l
c o n t r o l , and switching o p e r a t i o n s under d i r e c t NASA c o n t r o l .
The primary switching c e n t e r i s a t t h e Goddard Space F l i g h t
Center, Greenbelt, Md. I n t e r m e d i a t e switching c e n t e r s a r e
l o c a t e d a t Canberra, Madrid, London, Honolulu, Guam, and Kennedy
Space Center.
F o r Apollo 10, t h e Kennedy Space Center i s connected
d i r e c t l y t o t h e Mission Control Center, Houston v i a t h e Apollo
Launch Data System and t o t h e Marshall Space F l i g h t Center,
H u n t s v i l l e , Ala., by a Launch Information Exchange F a c i l i t y . Both of t h e s e systems a r e p a r t of NASCOM, They c o n s i s t of
d a t a g a t h e r i n g and t r a n s m i s s i o n f a c i l i t i e s designed t o handle
launch d a t a e x c l u s i v e l y ,
A f t e r launch, a l l network t r a c k i n g and t e l e m e t r y d a t a hubs
a t QSFC f o r t r a n s m i s s i o n t o MCC Houton v i a two 50,000 b i t s - p e r second c i r c u i t s used f o r redundancy and i n c a s t of data overflow.
Two I n t e l s a t communications s a t e l l i t e s w i l l be used f o r
Apollo 10. The A t l a n t i c s a t e l l i t e w i l l s e r v i c e t h e Ascension
I s l a n d u n i f i e d S-band (USB) s t a t i o n , t h e A t l a n t i c Ocean s h i p
and t h e Canary I s l a n d s s i t e . These s t a t i o n s w i l l be able t o
t r a n s m i t through t h e s a t e 1l i t e v i a t h e Comsat -operated ground
s t a t i o n a t Etam W.Va.
�A R C T I C OCEAN
A R C T I C OCEAN
I N D I A N OCEAN
SOUTH P A C I F I C OCEAN
NASA COMMUNICATIONS NETWORK
�The second Apollo I n t e l s a t communications s a t e l l i t e
over t h e mid-Pacific w i l l s e r v i c e t h e Carnarvon, A u s t r a l i a
USB s i t e and t h e P a c i f i c Ocean ships. A l l t h e s e s t a t i o n s
w i l l b e able t o transmit simultaneously through t h e s a t e l l i t e
t o Houston v i a Brewster F l a t , Wash,, and t h e Goddard Space
F l i g h t Center, Greenbelt, Md.
Network Computers
A t fraction-of-a-second i n t e r v a l s , t h e network's
d i g i t a l data processing systems, with NASA's Manned s p a c e c r a f t
.
Center a s t h e f o c a l p o i n t , " t a l k " t o each o t h e r o r t o t h e
spacecraft
High-speed computers a t t h e remote s i t e ( t r a e k i n g ships included) i s s u e commands o r "up-link" d a t a on auch
matters
as c o n t r o l of cabin p r e s s u r e , o r b i t a l p i d a n c e commands,
o r I t go-no-go" i n d i c a t i o n s t o perform c e r t a i n f u n c t i o n s ,
When information o r i g i n a t e s from Houston, t h e computers
rere? t o t h e i r pre-programmed information f o r v a l i d i t y before
transmitting t h e required d a t a t o t h e s p a c e c r a f t ,
Such "up-link" Information i s comminicated by ultrahigh-frequency r a d i o about 1,200 bits-per-second,
Communication
between remote ground s i t e s , v i a high-speed communications l i n k s ,
occurs a t about t h e same rate. Houston reads lnf'omation from
t h e s e ground s t i e s aG 2,400 bits-per-second, as well a s from
remote sites a t 100 words-per-minute.
The computer systems perform many o t h e r functions, i n cluding:
.
.
.
Assuring t h e q u a l i t y of t h e transmission l i n e s by
c o n t i n u a l l y e x e r c i s i n g d a t a paths.
Verifying accuracy of t h e messages by r e p e t i t i v e
operations,
Constantly updating t h e f l i g h t status.
For "down l i n k " data, sensors b u i l t i n t o t h e s p a c e c r a f t
c o n t i n u a l l y sample cabin temperature, pressure, physical i n f o r mation on t h e a s t r o n a u t s such as h e a r t b e a t and r e s p i r a t i o n ,
among o t h e r items, These d a t a a r e t r a n s m i t t e d t o t h e ground
s t a t i o n s a t 51,2 k i l o b i t s (12,800 binary d i g i t s pe r-second.
A t MCC t h e computers:
.
Detect and s e l e c t changes o r d e v i a t i o n s , compare with
t h e i r s t o r e d programs, and i n d i c a t e t h e problem a r e a s
o r pertinent data t o t h e f l i g h t controllers.
�,
Provide d i s p l a y s t o mission personnel,
.
Assemble output d a t a i n proper formats,
, Log d a t a on magnetic t a p e f o r r e p l a y f o r t h e f l i g h t
control-lers.
.
Keep t i m e ,
The A ~ o l l oS h i ~ s
The mission w i l l be supported by f o u r Apollo instrumentat i o n s h i p s o p e r a t i n g a s i n t e g r a l s t a t i o n s of t h e Manned Space
F l i g h t Network (MSFN) t o provide coverage i n areas beyond
t h e range of land s t a t i o n s ,
The s h i p s , Vanguard, Redstone, Mercury, and H u n t s v i l l e ,
. w i l l perform t r a c k i n g , t e l e m e t r y , and communication f u n c t i o n s
f o r t h e launch phase, Earth o r b i t i n s e r t i o n , t r a n s l u n a r l n j e c t i o n and r e e n t r y a t t h e end of t h e mission,
Vanguard w i l l be s t a t i o n e d about 1,030 m i l e s s o u t h e a s t
of Bermuda (25 d e g r e e s N, 49 d e g r e e s W ) t o bridge t h e BermudaAntigua gap during E a r t h o r b i t i n s e r t i o n . Vanguard a l s o f u n c t i o n s
as p a r t of t h e A t l a n t i c recovery f l e e t i n t h e event of a launch
phase c o n t i w e n c y , The Redstone, a t 14 degrees S , 145.5 degrees
E; Mercury, 32 degrees S, 131 d e g r e e s E; and H u n t s v i l l e , 1'7 dee ~ s b i l estations beg r e e s S, 174 degrees W, provide a % r i a n ~ ; lof
tween t h e MSFN stations at Carrnarvsn and Hawaii f s eoveTage
~
of
t h e burn i n t e r v a l f o r t r a n s l u n a r inJeetion.
I n the event t n e
launch d a t a slips from May 18, the ships w $ l L a i l move g e n e r a l l y
northeastward t o cover the changing flight window patterns.
Redstone and H u n t s v i l l e w i l l be r e p o s i t i o n e d along t h e
r e e n t r y c o r r i d o r f o r t r a c k i n g , t e l e m e t r y , and communicatfons
f u n c t i o n s during r e e n t r y and landing. They w i l l t r a c k Apollo
from about 1,000 m i l e s away through comrnunicat i o n s blackout
when t h e s p a c e c r a f t w i l l drop below t h e h o r i z o n and w i l l be
picked up by t h e A R I A a i r c r a f t ,
The Apollo s h i p s were develop-d j o i n t l y by NASA and t h e
Department of Defense, The DOD oy;(::rates t h e s h i p s - - i n support
of Apollo and o t h e r NASA and DOD missions on a non-interference
basis w i t h Apollo requirements,
Management of t h e Apollo s h i p s i s t h e r e s p o n s i b i l i t y
of t h e Commander, A i r Force Western T e s t Range (AFWTR), W e
M i l i t a r y Sea T l a n s p o r t S e r v i c e provides t h e m a r i t i m e crews and
t h e F e d e r a l E l e c t r i c Corp,, I n t e r n a t i o n a l Telephone and Telegraph, under c o n t r a c t t o AFWTR, provides t h e t e c h n i c a l i n s t r u mentation crews.
�The t e c h n i c a l crews o p e r a t e i n accordance w i t h j o i n t
NASA/DOD s t a n d a r d s and s p e c i f i c a t i o n s which a r e compatible
w i t h MSFN o p e r a t i o n a l procedures.
Apollo Range I n s t r u m e n t a t i o n Aircraft (ARIA)
The Apollo Range I n s t r u m e n t s t i o n A i r c r a f t w i l l s u p p o r t
t h e mission by f i l l i n g gaps i n both land and s h i p s t a t i o n
coverage where important and s i g n i f i c a n t coverage requirements
exist.
During Apollo 10, t h e A R I A w i l l be used p r i m a r i l y t o
fill coverage gaps of t h e ?and and s h i p s t a t i o n s i n t h e I n d i a n
Ocean and i n t h e P a c i f i c between A u s t r a l i a and Hawaii during
t h e t r a n s l u n a r i n j e c t i o n i n t e r v a l , P r i o r t o and d u r i n g t h e
burn, t h e A R I A r e c o r d t e l e m e t r y data from Apollo provide a
r e a l - t i m e v o i c e communication between t h e a s t r o n a u t s and t h e
f l i g h t d i r e c t o r a t Houston.
E i g h t a i r c r a f t w i l l p a r t l c i p a t e i n this mission, o p e r a t i n g
from P a c i f i c , A u s t r a l i a n and I n d i a n Ocean a i r F i e l d s i n
p o s i t i o n s under t h e orbital t r a c k of the s p a c e c r a f t and b o o s t e r .
The a i r c r a f t . l i k e t h e t r a c k i n g s h i p s , w i l l be redeployed i n a
northeastward d i r e c t i o n i n t h e e v e n t of launch day s l i p s .
F o r r e e n t r y , t h e A R I A w i l l be redeployed t o t h e l a n d i n g
area t o c o n t i n u e communications between Apollo and Mission
Control and provide p o s i t i o n i n f o r m a t i o n on t h e s p a c e c r a f t
a f t e r t h e blackout phase of r e e n t r y has passed.
The t o t a l A R I A f l e e t f o r Apollo m i s s i o n s c o n s i s t of
e i g h t EC-135A ( ~ o e i n g707) j e t s equipped s p e c i f i c a l l y t o
meet mission needs, Seven-foot p a r a b o l i c a n t e n n a s have been
i n s t a l l e d i n t h e nose s e c t i o n of t h e p l a n e s g i v i n g them a
l a r g e , bulbous look.
The a i r c r a f t , as w e l l a s f l i g h t and i n s t r u m e n t a t i o n
crews, are provided by t h e A i r Force and t h e y a r e equipped
through j o i n t A i r Force-NASA c o n t r a c t a c t i o n . A R I A o p e r a t e
in Apollo m i s s l o n s i n accordance w i t h MSFN procedures.
�Ship Positions f o r Apollo 10
-- 49
degrees W
131 degrees E
145.5 degrees E
172.5 degrees E
Insertion Ship
I n j e c t i o n Ship
I n j e c t i o n Ship
I n j e c t i o n Ship
Reentry Suppore
Reentry Skip (Hw)
25 degrees N
32 degrees S
14 degrees S
20 degrees S
17 degrees
S - 174 degrees W
I n s e r t i o n Ship
I n j e c t i o n Ship
I n j e c t i o n Ship
Injection ship
Reentry Support
Reentry Ship (HTV)
25
32
14
13
N
S
S
S
I n s e r t i o n Ship (VAN
I n j e c t i o n Ship
I n j e c t i o n Ship
I n j e c t i o n Ship
Reentry Support
Reentry Ship (HTV)
25 degrees W
I n s e r t i o n Ship
I n j e c t i o n Ship
I n j e c t i o n Ship
I n j e c t i o n Ship
Reentry Support
Reentry Ship (HTV)
25 degrees N
Released
3 degrees S
9 degrees M
I n s e r t i o n Ship
I n j e c t i o n Ship
I n j e c t i o n Ship (RED
Indection Ship (RED)
Reentrg Support
Reentry Ship (HTV)
25 degrees N
Released
0.5 degrees N
16 degrees N
degrees
degrees
degrees
degrees
-
- 49
degrees W
131 degrees E
-- 145.5
degrees E
174 degrees E
-
-
8 degrees S
173 degrees W
-
49 degrees W
Released
7.5 degrees S 156 degrees E
1 degree I4
177.5 degrees E
-
-
- 172 degrees W
10 degrees N
-
- 49 degrees W
-175.5
158 degrees E
d e ~ r e e sE
15.5 degrees N
22 degrees N
-
173 degrees
w
- 49 degrees W
- 161 degrees E
- 174 degrees E
- 173 degrees W
�APOLLO PROGRAM MANAGENEW
The Apollo Program, t h e United S t a t e s ' e f f o r t t o land
men on t h e Moon and r e t u r n them s a f e l y t o Earth before 1970,
i s t h e r e s p o n s i b i l i t y of the O f f i c e of Manned Space F l i g h t
(OWSF), National Aeronautics and Space Administration, Washington, D.C.
D r . George E. Mueller i s Associlate Administrator
f o r Manned Space F l i g h t .
NASA Manned Spacecraft Center (MSC), Houston, is r e sponsible f o r development of t h e Apollo s p a c e c r a f t , f l i g h t
crew t r a i n i n g and f l i g h t c o n t r o l . Dr. Robert R . Q i l r u t h i s
Center D i r e c t o r .
NASA Marshall Space F l i g h t Center (MSFC), H u n t s v i l l e , A l a . ,
i s responsible f o r development o f the Saturn launch vehicles,
D r . Wernher von Braun is Center D i r e c t o r .
NASA John F. Kennedy Space Center (KSC), F l a . , i s r e sponsible f o r ~ p o l l o / ~ a t u r launch
n
o p e r a t i o n s . D r . Kurt H.
Debus i s Center D i r e c t o r .
NASA Goddard Space F l i g h t Center (GSFC), Greenbelt, Md. ,
manages t h e Manned Space F l i g h t Network under the d i r e c t i o n
of the NASA Office of Tracking and Data Acquisition (OTDA).
Gerald M. Truszynski i s Associate Administrator f o r Tracking
and Data Acquisition. D r . John F. Clark i s Director of GSFC,
Apollo/Saturn O f f i c i a l s
NASA HEADQUARTERS
L t . Gen. Sam C, P h i l l i p s , (USAF)
Apollo Program D i r e c t o r , OMSF
George H. Hage
Apo 110 Program Deputy Director,
Mission D i r e c t o r , OMSF
Cnester M. Lee
A s s i s t a n t Mission D i r e c t o r , OMSF
:ol.
A s s i s t a n t Mission Director, OMSF
Thomas H. McMullen (USAF)
Maj. Gen. James W. Humphreys, J r .
Director o f Space Medicine, OMSF
Norman Pozinsky
Director, Network Support Implementation Div. , OTDA
�Manned Spacecraft Center
George M. Low
MBnager, Apollo Spacecraft
Program
Kenneth S . Kleinknecht
Manager, Command and Service
Modules
B r i g . Gen, C. H. Bolender (USAF)
Manager, Lunar Module
Donald K. Slayton
Director of F l i g h t Crew Operations
Chrf stopher C, Kraft , Jr.
Director of' F l i g h t Operations
Glynn S. Lunney
F l i g h t Director
Milton L. Windler
F l i g h t Director
M. P. Frank
F l i g h t Director
Gerald G r i f f i n
F l i g h t Director
Charles A. Berry
Director of Medical Research
and Operations
Marshall Space F l i g h t Center
Ma3. Gen. Ednn;md P. OtConnor
Director of I n d u s t r i a l Operations
D r . F. A. Speer
Director o f Mission Operations
Lee 33. James
Manager, Saturn V . Program Off i c e
William D. Brown
Manager, Engine Program Office
Kennedy Space Center
Miles Ross
Deputy Director, Center Operations
Rocco A. Petrone
Director, Launch Operations
Raymond L. Clark
Director, Technisal Support
Rear Adm. Roderick 0. Middleton
(USN)
Manager, Apollo Program Office
Walter 3, Kapryan
Deputy Director, Launch Operations
D r . Hans F. Gruene
Director, Launch Vehicle Operations
John 3 . Williams
Director, Spacecraft Operations
�Paul C, DDnnelly
Launch Operations Manager
Goddard Space Flight Center
Assistant Mrector POP Manned
Space Flight Tracking
-
Henry F. Thompson
Deputy Assistant Director f o r
Manned Space Flight Support
H. W i l l i a m Wood
Chief, Manned Flight Operations
Tecwyn Roberts
Chief, Manned F l i g h t Engineering
Div.
Div.
Department of Defense
Maj. Gen. Vincent Q . Huston, (USAP) DOD Manager of Planned Space
Flight Support Operations
Maj. Gen. David M. Jones, (US-)
Deputy DOD m g e r of Manned
Space Flight Support Operations, Commander of USAF
Eastern Test Range
Rear A m , F. E. Bakutis, (USW)
Commander of Combined Task Force
130, Pacific Recovery Area
Rear Adm. P. S. PLcManus, (USN)
Commander of Combined Task Force
140, Atlantic Recovery Area
Col, Royce G. Olson, (USAF)
Director of DOD Manned Space
Flight Office
Brig. Gen. Allison C. Brooks,
Commander Aerospace Rescue and
Recovery Service
(USAP)
�Pllajor Apollo/Satucn V Contractors
Contractor
Item
Bellco~pn
Washington, D, C.
Apollo Systems Engineering
The Boeing Co.
Washington, D. C,
Technical I n t e g r a t i o n and
Evaluation
General E l e e t r i c -Apollo
Support Dept,,
Dagtona Beach, Bla,
Apollo Checkout, and Quality and
Reliability
North American Rockwell Corp.
Space D i v e , Downey, Callf.
Command and S e w i c e Modules
Grumman A i r c r a f t Engineering
Corp, , Bethpage, N. I.
Lunar Module
Massachusetts I n s t i t u t e of
Technology, Cambridge, Mass.
Guidance h Navigation
(Technical Management)
General Motors Corp., AC
Electronics Div., Milwaukee, W i s .
Guidance & Navigation
(~anufacturing)
TRW Systems Inc.
Trajectory Analysis
Redondo Beach, C a l i f .
Avco Corp., Space Systems
D i v . , L o w e l l , Mass,
H e a t Shield Ablative Material
North American Rockwell Corp,
Rocketdyne D i v .
Canoga Park, Calif.
3-2 Engines, F-1 Engines
The Boeing Co.
Mew Orleans
F i r s t Stage (SIC) of Saturn V
Launch Vehicles, Saturn V
Systems Engineering and Integration, Ground Support Equipment
North American Rockwell Corp,
Space Div,
Seal Beach, Calif.
Development and Production of
S a t u r n V Second Stage (s-11)
McDonnell Douglas Astronautics
Co.
Huntington Beach, Callf.
Development and Production of
Saturn V . Third Stage (s-IVB)
�International Business Machines
Federal Systems Div,
Huntsville, Ala.
Instrument Unit
Bendix Corp.
Navigation and Control Div.
Teterboro, N . 3 .
Guidance Components for Instrument Unit (Includin
Stabilized
Federal Electric Corp.
Communications and Instrumentation Support, KSC
Bendix Field Engineering Corp.
Launch Operations/Complex
Support, KSC
Catalytic-Don
Facilities Engineering and
Modifications, KSC
Hamilton Standard Division
United Aircraft Corp.
Windsor Locks, Conn.
Portable Life Support System;
LM ECS
IiC Industries
Dover, Del.
Space Suits
Radio Corp. of America
Van Nuys, Calif.
llOA Computer
Sanders Associates
ACashua, N . H .
Uperat iona1 Display Systerns
Brown Engineering
Huntsville, Ala.
Discrete Controls
Reynolds, Smith and Hill
Jacksonville, Fla.
Engineering Desfgn of Moblle
Launchers
Ingalls Iron Works
Birmingham, Ala.
Mobile Launchers (ML)
(structural work)
Srnith/Ernst (foint Venture)
Tampa, Fla.
Washington, D, C.
Electrical Mechanical Portion
Power Shovel, Inc.
Marion, Ohio
Transporter
Hayes International
Birmingham, Ala
Mobile Launcher Service Arms
.
- Saturn Checkout
Saturn
of E4Ls
�APOLLO GLOSSARY
Ablating Materials--Special heat-dissipating materials on the
surface of a spacecraft that vaporize during veentry.
Abort--The unscheduled ternination of a mission prior to its
completion,
Accelerometer--An instrument to sense accelerative forces and
convert them into corresponding electrical quantities
usually for controlling, measuring, indicating or recording
purposes.
Adapter Skirt--A flange or extension of a stage or section that
provides a ready meaner of fitting another stage or section
to It.
Antipode--Point on surface of planet exactly 180 degrees opposite
from reciprocal point on a line projected through center of
body. In Apollo usage, antipode refers to a line from the
center of the Moon through the center of the Earth and projected to the Earth surface on the opposite side. The antipode crasses the mid-Pacific recovery line along the 165th
meridian of longitude once each 24 hours.
Apocynthion--Point at which object In luna orbit is farthest
from the lunar surface
object having been launched from
body other than Moon. (
, Romm goddess of Moon)
--
Apogee--The point at which a Moon or artificial satellite in its
orbit is farthest from -rth.
Apolune--Point at which object launched from the Moon into lunar
orbit is farthest from lunar surface, e,g.: ascent stage
of lunar module after staging into lunar orbit fillowing
lunar landing
.
Attitude--The position of an aerospace vehicle as detemined by
the inclination of its axes to some frme of reference;
for Apollo, an Inertial, space-fixed reference is used.
Burnout--The point when combustion ceases in a rocket engine.
Canard--A short, stubby wing-like element affixed to the launch
escape tower to provide CM blunt end forward aerodpamic
capture durlng an abort.
Celestial Guidance--me guidance of a vehicle by reference to
celestial bodies.
�C e l e s t i a l Mechanics--The science t h a t d e a l s primarily with t h e
e f f e c t of force as an agent i n determining the o r b i t a l
p a t h s of c e l e s t i a l bodies.
Cislunar--Adjective r e f e r r i n g t o space between Earth and t h e Moon,
o r between Earth and Moon18 o r b i t .
Closed Loop--Automatic c o n t r o l u n i t s 1l.nked t o g e t h e r w i t h a
process t o form an endless chain,
Deboost--A retrograde maneuver which lowers either perigee o r
apogee of an o r b i t i n g s p a c e c r a f t , Not t o be confused with
deorbit.
&elination--Angular measurement of a body above o r below c e l e s t i a l
equator, measured n o r t h o r south along t h e body's hour
c i r c l e . Corresponds t o Earth surface l a t i t u d e .
Delta V--Velocity change.
D i g i t a l Computer--A computer i n which q u a n t i t i e s a r e represented
numerically and which can be used t o solve complex problems,
Down-Link--The part o f a communication system t h a t r e c e i v e s , proc e s s e s and d i s p l a y s d a t a from a s p a c e c r a f t .
E n t r y Corridor--The f i n a l f l i g h t path of the s p a c e c r a f t before
and during Earth r e e n t r y .
Ephemeris--Orbital measurements (apogee, perigee, i n c l i n a t i o n ,
period, e t c . ) of one c e l e s t i a l body i n r e l a t i o n t o another
a t given times. I n s p a c e f l i g h t , t h e o r b i t a l measurements
of a s p a c e c r a f t r e l a t i v e t o the c e l e s t i a l body about which
it orbited.
Escape Velocity--The speed a body must a t t a i n t o overcome a
g r a v i t a t i o n a l f i e l d , such as t h a t of Earth; t h e v e l o c i t y
of escape a t the E a r t h ' s s u r f a c e i s 36,700 feet-per-second,
Explosive Bolts--Bolts destroyed o r severed by a surrounding
explosive charge which can be a c t i v a t e d by an e l e c t r i c a l
impulse,
Fairing--A piece, p a r t o r s t r u c t u r e having a smooth, streaml i n e d o u t l i n e , used t o cover a nonstreamlined o b j e c t o r t o
smooth a junction.
P l i g h t Control System--A system t h a t s e r v e s t o maintain a t t i t u d e
s t a b i l i t y and c o n t r o l during f l i g h t ,
�Fuel Cell--An electrochemical generator i n which t h e chemical
energy from t h e reaction of oxygen and a fuel La converted d i r e c t l y i n t o e l e c t r i c i t y .
e x e r t e d upon an o b j e c t by gravity o r by
r e a c t i o n t o a c c e l e r a t i o n o r d e c e l e r a t i o n , as In a change
o f d i r e c t i o n : one g is t h e measure o f f o r c e required t o
a c c e l e r a t e a body a t t h e rate of 32.16 feet-per-second.
g o r g Force--Force
on a
Gimbaled Motor--A rocket motor mounted on gimbal; 1.e.:
contrivance having two mutually perpendicular axes o f rot a t i o n , so as t o o b t a i n p i t c h i n g and yawing c o r r e c t i o n moments.
Guidance System--A system which measures and e v a l u a t e s f l i g h t
information, c o r r e l a t e s t h i s with t a r g e t d a t a , converts
t h e r e s u l t i n t o t h e conditions necessary t o achieve t h e
d e s i r e d f l i g h t path, and communicates t h i s d a t a i n t h e form
of commands t o t h e f l i g h t c o n t r o l system.
Heliocentric--Sun-centered
Sun a t i t s c e n t e r .
o r b i t o r o t h e r a c t i v i t y which h a s the
I n e r t i a l , Guidance --Guidance by means o f t h e measurement and
i n t e g r a t i o n of a c c e l e r a t i o n from on board t h e s p a c e c r a f t .
A s o p h i s t i c a t e d automatic navigation system using gyroscopic devices, accelerameters e t c . , for high-speed v e h i c l e s .
It absorbs and i n t e r p r e t s such d a t a a s speed, p o s i t i o n , e t c . ,
and automatically a d j u s t s t h e vehicle t o a pre-determined
f l i g h t path. E s s e n t i a l l y , i t knows where i t ' s going and
where it i s by knowing where i t came from and how i t g o t
t h e r e . It does n o t give out any r a d i o frequency s i g n a l ao
i t cannot be detected by r a d a r o r jammed.
Injection--The process of boosting a s p a c e c r a f t i n t o a calculated trajectory.
Insertion--The process o f boosting a s p a c e c r a f t i n t o an o r b i t
around the Earth o r o t h e r c e l e s t i a l bodies.
Multiplexing--The siaiultaneous transmission of two o r more s i g n a l s within a s i n g l e channel. The t h r e e b a s i c methods
of multiplexing involve t h e s e p a r a t i o n of s i g n a l s by time
d i v i s i o n , frequency d i v i s i o n and phase d i v i s i o n .
O p t i c a l Navigation--hlavlgation by s i g h t , as opposed t o i n e r t i a l
methods, using stars o r o t h e r v i s i b l e o b j e c t s as reference.
Oxidizer--In a rocket p r o p e l l a n t , a substance such as l i q u i d
oxygen o r n i t r o g e n t e t r o x i d e which supports combustion of
the mel.
�Penumbra--Semi-dark portion of a shadow in which light is partly
cut off, e .g. : surface of Moon or Earth away from Sun where
the disc of the Sun is only partly obscured,
Pericynthion--Point nearest Moon of object In lunar orbit--object
having been launched fron body other than Moon.
Perigee--Point at which a Moon or an artificial satellite I n its
orbit is closest to the Earth.
Perilune--The point at which a satellite ( e , g . : a spacecraft) in
its orbit is closest to the Moon. Differs from pericynthion
in that the orbit is Moon-originated.
Pitch--The movement of a space vehicle about an axis (Y) that is
perpendfcular to its longitudinal axis.
Reentry--The return of a spacecraft that reenters the atmosphere
after flight above it.
Retrorocket--A rocket that gives thrust in a direction opposite
to the direction of the object's motion.
-
Right Ascension -Angu lar measurement of a body eastward alon the
celestial equator Prom the vernal equinox (0 degrees RAY to
the hour circle of the body. Correaponds roughly to Earth
surface longitude, except as expressed in hrs:min:sec instead
of 180 degrees west and east from 0 degrees (24 hours-360
degrees)
.
Roll--The movements of a space vehicle about its longitudinal
(x) axis.
S-Band--A radio-frequency band of 1,550 to 5,200 megahertz.
Selenographic--Adjective relating to physical geography of Moon.
Specifically, positions on lunar surface as measured in
latitude from lunar equator and in longitude from a
reference lunar meridian.
Selenocentric--Adjective referring to orbit having Moon as center.
(~elene,Or. Moon)
Sidereal--Adjective relating to measurement of time, position
or angle in relation to the celestial sphere and the vernal
equinox.
State vector--Ground-generated spacecraft position, velocity and
timing information uplinked to the spacecraft computer for
crew use as a navigational reference.
�Telemetering-A system for taking measurements within an aerospace vehicle in flight and transmitting them by radio to
a ground station.
Terminator--Separation line between lighted and dark portions
of celestial body which is not self luminous.
Ullage--me volme in a closed tank or container that is not
occupied by the stored liquid; the ratio of this volume
to the total volume of the tank; also an acceleration to
force propellants into the engine pump intake lines before
ignition.
Umbra--Darkest part of a shadow in which light is completely
absent, e-g.: surface of Moon or Earth away from Sun where
the disc of the Sun l a completely obscured.
Update pad--Information on spacecraft attitudes, thrust values,
event times, navigational data, etc., voiced up to the crew
in standard formats according to the purpose, e.g,: maneuver
update, navigation check, landmark tracking, entry update,
etc.
Up-Link Data--Information fed by radio signal from the ground to
a spacecraft
.
Yaw--An l a r displacement of a space vehicle about its vertical
( zraxis .
�APOLLO ACRONYMS AND AIEIBREVIATIONS
(Note: This l i s t makes no attempt t o inelude a l l Apollo
program acronyms and abbreviations, but s e v e r a l are l i s t e d
t h a t w i l l be encountered frequently i n the Apsllo 10 mission.
Where pronounced a s words i n a i r - t o -ground transmissions,
acronyms a r e phonetically shown i n parentheses. Otherwise,
abbreviations a r e sounded out by l e t t e r . )
AGCS
(At3gs )
Apogee kick
AK
APS
Abort Guidance System ( W )
(APP~)
Aacent Propulsion System (LM)
Awtiliaqy Propulsion System (S-IVB s t a g e )
(Be-WZ)
Body mounted a t t i t u d e gyro
CBSf
Constant delta height
CMC
Cornand Module Computer
COI
Contingency o r b i t i n s e r t i o n
CRS
Concentric rendezvous sequence
CSI
Concentric sequence i n i t i a t e
DAP
(~PP)
Digital autopilot
DEDA
( Dee -da )
Data Entry and Display Assembly
(MIAQS)
DFI
Development f l i g h t instrumentation
DO1
Descent o r b i t i n s e r t i o n
DPS
( Dips
Descent propulsion system
DSKY
( isk key )
Display and keyboard
EPO
Earth Parking O r b i t
FDA1
Flight director attitude i n d i c a t o r
FIllI
(Fith)
F i r e In the hole (LM ascent a b o r t
staeing)
Fixed t h r o t t l e point
High-gain antenna
I n e r t i a l measurement u n i t
�APOLLO ACRONYMS AND ABBREYIATIONS
(Note: T h i s l i s t makes no attempt t o include a l l Apollo
program acronyms and abbreviations, but s e v e r a l a r e l i s t e d
t h a t w i l l be encountered frequently i n the Apollo 10 mission.
Where pronounced a8 words i n air-to-ground transmissions,
acronyms a r e phonetically shown irP parentheses. Otherwise,
abbreviations a r e sounded out by l e t t e r )
.
Abort Guidance System ( W )
Apogee kick
APS
B31AQ
A ~ c e n tPropulsion System (IN)
Auxiliary Propulsion Sy~rtem(s-IVB atage)
(Bee--)
Body mounted a t t i t u d e gyro
Constaikt d e l t a height
CMC
Cormnand Module Computer
Contbgency o r b i t i n s e r t i o n
CRS
Concentric rendezvous sequence
CSI
Concentric sequence i n i t i a t e
DAP
Digital autopilot
DEDA
Data Entry and Display Assembly
(LM AM)
DFI
1)evelopment f l i g h t instrumentation
Descent o r b i t i n s e r t i o n
DPS
Descent propulsion system
DSKY
Display and keyboard
EPO
Earth Parking O r b i t
Flight director attitude indicator
FITH
F i r e in the hole (LM ascent abort
staging
PPP
Fixed t h r o t t l e point
High-gain antenna
I n e r t i a l measurement u n i t
�IRIO
I n e r t i a l ra%e i n t e g r a t i n g gyro
LO1
Lunar o r b i t f n s s r t i o n
LPO
Lunar p a r k i w o r b i t
MCC
Misaion Control Center
MC&W
Master caution and warning
MSI
Moon sphere of influence
MTVC
Manual t h r u s t vector c o n t r o l
NCC
Combined c o r r e c t i v e maneuver
NSR
C o e l l i p t i c a l maneuver
PIPA
( f ippa)
Pulse i n t e g r a t i ~pendulous
accelerometer
PLSS
(~lisro)
Portable l i f e support system
Passive the
PTC
mas
(Pugs)
Propellant u t i l i z a t i o n and gaging
systern
REFSWT
( ~ esmat)
f
Reference t o s t a b l e member matrix
RHC
Rotation h m d c o n t r o l l e r
R E
Real-time a s
SCS
S t a b i l i z a t i o n m d c o n t r o l system
SLA
Spacecraft LM adapter
SPS
Service p r o ~ l s i o nsystem
TEI
Transearth I n j e c t i o n
THC
Thrust hand c o n t r o l l e r
TLI
Translunar InJection
TPF
Terminal phase f i n a l i z a t i o n
TPI
Terminal phase I n i t i a t e
TVC
Thrust vector c o n t r o l
d
�CONVERSION FACTORS
Multiply
2
To Obtain
feet
0,3048
meters
Distance :
feet
kilometers
feet
kilometers
statute miles
statute miles
kilometers
nautical miles
kilometers
nautical miles
statute miles
statute miles
nautical miles
statute mile
yards
feet/sec
meters/sec
Velocity:
feet/sec
statute mph
statute miles/hr
nautical miles/hr
statute miles/hr
1.609
km/hr
nautical miles/hr
(knots)
1.852
km/hr
statute miles/hr
Liquid measure, werkht :
gallons
liters
liters
gallons
pounds
kilograms
kilograms
pounds
- more -
�Multiply
8
To Obtain
cubic f e e t
0.02832
cubic meters
pounds/sq i n c h
70.31
grarns/sq cm
Volume :
Pressure :
�
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
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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
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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spc_stnv_000071
Title
A name given to the resource
Apollo 10 press kit.
Description
An account of the resource
The press kit includes documentation on the Command and Service Module, Lunar Module, Saturn V launch vehicle, astronauts, and mission descriptions. Release No. 69-68.
Creator
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United States. National Aeronautics and Space Administration
Date
A point or period of time associated with an event in the lifecycle of the resource
1969-05-07
Temporal Coverage
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1960-1969
Subject
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Project Apollo (U.S.)
Space flight to the moon
Saturn launch vehicles
Saturn Project (U.S.)
Type
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Press kits
Text
Source
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Saturn V Collection
Box 31, Folder 30
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
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en
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
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spc_stnv_000051_000074