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COPY NO.

SNA-8-D-027(III) REV 2

NATIC) NAI AE RONAI.JIlCS AND SPACE ADMINISTRATION

CSM/LM SPACECRAFT

OPERATIONAL

DATA BO OK

VOLUME 1TI

MASS PROPERTIES

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REVISION 2

20 AUGU 3T 1969

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(NASA-TM-X-6896 81

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MANNED SPA(E('RAFT (ENTER

tt()US1 ()N, -I F.X A S

CSM/LM SPACECRAFT

BOOK. ¥OLUME 3: MASS

20 Auq. 1969 212 p

00/99

N73-7001_

Unclas

37210

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Summary of content (966 pages)

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I I COPY NO. SNA-8-D-027(III) REV 2 ".'.'.'.%'.'.'.'.'.:.: °°°o°°°°°o-o°°-o-o°o°oO NATIC) NAI AE RONAI.JIlCS AND SPACE ADMINISTRATION !!i!i!!iiii! o°o°°°°°°°°°O°°o°o°°°o, iii iCSM/LM i !iii!iiiiiiiii SPACECRAFT OPERATIONAL o°.o°°°°oo° ::::::::::::::::::::::: DATA BO OK ::::::::::::::::::::::: ::::::::::::::::::::::: o°o°°°°°,oo°°o°o°oOo°°° ,°°o°°°°,°°o°o°°°°°°OoO °..°°°°oo*°° • °°°°°o°°°°°°o°o°o°o°o°° °°°°oo°ooo° o°°°,oOo°oOo°°,°O°°oO°O o°°°°o°o°o°° .........
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I ":.:...:...:.......:..... °°°°°°°°°°°°°°%°°*°°°° °°°° .... .... °°°•°,° o°°°°•°°°°.°°°°°° COPY •°°° °°o o :.:::q.:.'.'.'.:.:::." -.-.-.-.:...-...::.._... SNA-8-D-027(III) °°°°•°°°°°°°-°°°°°°°°°° NATIONAl *°° ........ °°°°°,°•°,° °°°°°°°°°°°,°°°,°°°,,°° ,°°•°•°•°°•, °•°°°•°°°°° °°°°°°°°°°°°°°°°,°°°,°° I_10. AE RONAIJIlCS AND SPACE REV 2 ADMIN STRATION ° :.:.:.:.:.:.:.:.:.:.:.: °• ...... •°, °°°°°°°°°°°°,°°°°°°°°, °°°°°°° ,, ..... °°° .... ,°•° ...... .... °°°° °°,°• ° ° ° .....
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SNA-8-D-027 CSM/LM SPACECRAFT OPERATIONAL VGLIIME MASS PROP_TIES PREPARED DATA (III)REV 2 BOOK III DATA BOOK BY SYST_L$ OPERATIONS BRANCH SYSTEMS ENGINEERING DIVISION APOLLO SPACECRAFT PROGRAM OFFICE MANNED SPACECRAFT APPROVED BY SYSTemS GEGRGE APOLLO _INEE_ING DIVISION M.
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P RE FACE This document Data Book. In have been deleted. through 65, "C-Prime", cation bered of is the this this sequentially and Mass revision revision The except "D", second those "F". Missions"C", second revision amendments the the Mass "D", incorporates Book, revision Properties "C-Prime", released Data next of associated Amendments Properties with issue and Amendments with number i Mis_ions subsequent Revision "F" 2, (i.e.
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Amendment VOLUME MASS 1.0 Introduction 2.0 Configuration 3.0 Mass Properties 3.1 Mission G 3.2 Mission H1 3.3 Mission H2 3.4 Mission H3 3.5 Mission Jl CSH Reference 4°0 4.1 5.0 and PROPERTIES and SPS Tank SPS Density 4.2 RCS/ECS/EPS 4.3 CSM RCS 4.4 CM Loading LM Descent 5.2 LM Ascent 5.3 LM RCS 5.4 LM Descent 5.5 LM Ascent 5.
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i V" "V_ •" IrT ,_ ,. Z ILl 11 I.I I.:; 1: _ 1.
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1.0 i.i INTRODUCTION SCOPE The complete Spacecraft Operational consist of five separate volumes.
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r L L
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Amendment 10/30/69 TABLE I-I 72 SELECTED ABBREVIATIONS AND ACRONYMS ACT ACQ ALIGN ANG ASCT APS A/S ASSY Activation Acquisition Alignment Angle Ascent Ascent Propulsion Ascent Stage Assembly BIOINST Bioinstrumentation CAN:i CAM CK CIRC CSC COMPT CDR CM CMP CSM COMM CSI CWG CONT CLSRC Cannister Camera Check Circularization Close-Up Stereo Camera Compartment Commander Command Module Command Module Pilot ConTnand Service Module Communication Concentric Sequence Initiation Constant Wear Garment Container
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Anmndment 10130169 TABLE I-I (Continued) ICG IV In-FLight Coverall I ntra vehi cul ar JETT Jetti son LES LEV LV LH LEB LIQ LEC LM LOI LS LMP LUN Launch Escape System Launch Escape Vehicle Launch Vehicle Left Hand Left Hand Equipment Bay Liquid Lunar Equipment Conveyor Lunar Module Lunar Orbit Insertion Lunar Surface LM Pilot Lunar MC MECH MCC Main Chute Mechanism Midcourse Correction N/A Not OPS Oxygen Purge System PR P-GA PROC Pair Pressure Garment Assembly Procedure RAD RCS RELOC RESTR RT
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Amendment I0/30/69 TABLE I-I (Continued) SUBSYS SUMP SURF SYS RSS Subsystem Sump Tank Surface System Root Sum Square TEMP TBD TEl XFR TLI Temporary To Be Determined Transearth Insertion Tranfer Translunar Insertion TRANS TRANS/DOCK Transposi ti on Transposition and Docking UMB UPR UEB UCTA Umbil ical WT Waist Tether With Without w/ w/o 72 Upper Upper Equipment Bay Urine Collection Transfer i-4 Assembly SNA-8-D-O27(III)REV 2
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ililb ILl !1 :lJ 12 L E 12 I: ]_ E L' 1_ E E t IL
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'-_A_-d'lld_g"kd'kAdi'kA AA d"k \ " I r.
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2.0 This section locations craft and provides which may components docked relevant be and spacecraft useful the in for data presented are i. Apollo Vehicle 2. Saturn V Vehicle configuration describing relationship configuration Configuration CONFIGURATION the of Block II in Coordinate location coordinate CSM the drawings various systems spacecraft following of and and in categories space- the Lunar station launch Modules. and order: System.
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-- _ _ _o o_o J < o o _ _o _°°_ _ _u • ._0_ _ ....
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/ XL-- 400.8 XA_ 1484.2 -. /i_ 15°_ '_ X L -- 332.2 m X A s 10.55.715 ESCAPE / SUBSYSTEM 400.76 i_...o,,o,. ,.o.o i,iii, X A = 1133.5 (NO XC -- 133.5 COMMAND MODUI.E ABLATIVE) _ TO HEATSHIELD STRUCTURE -- 7" (REF V14-15-2) - -_ 33 ° 83.476 "_A_'/083.5 X A = 1000.00 SERVICE MODULE "" 83.5 ES = 162.0" ----e- j XA = 838.0 154.0" • / L XA = 833.
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STA 4240.792 I LES L STA 3890.055 STA 3841.182 X A = 1133.500 CM x A = 1000.000 STA 3756.555 SM t STA 3594.555 STA • DIA "_ • 3340. 045 260 IN. XA=583. _ t ..... 1 £ ,,.j Y-"I r'- DIA--.._ .A t.u. ] 490 XA = 502.000 e" s-,vB k---: ::.,t __J .... __ 1 STA 2746.500 GIMBAL SLA ____. STA 3258.555 STA 3222. 555 X A = 838.000 STA 2645.853 STA 2519.000 L._.b ,_ S°II \ STA 1760.000 GIMBAL STA 1664.000 STA 1564.000 STA 1541.
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e-4 i,-4 v 0 I I _0 I .< z Z 0 < l-- Z 0 l.u v U L_ I 0 _E I I,_ .iI U< i I 0 e_ _.uo L) LI- O_ 0 I Z,,, Z Z < I-.-L_.lm ¢_ ,..1 U< 11 11 1.[ IZ 1: E L L L I.
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+X A ÷X A 6. 750" ,0.94" X S = 320.97 X A = 958 3.125 VIEW ( @_PITCH AND 97 '_ YAW/ 1 . 83.OO'o' (*),,J'L._ I 10 = -Z A I VIEW 1 (TYP) i I. 2g" x •_----- 83.56" ------_ _REFERENCE _J LOCATIO +ZA LOOKING (IN Figure 2-5.
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_ 1818188 d#44_ _+ O ÷++÷ N _i_ " I U U i i i I ,-_ j ÷ 7 S o ÷++'_ _-+.f-++ o_ 7_ o_ o_ ZZ 7z _< m I \ C:::_:x ::-_ _ I -.
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NNZZ X X .j_.j oo_ v e_ , ,>_ ? XX_e4 ? I U _z_z ,--__> O"r .
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O x_ OO .,__z _X ,X.
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PROJECTION OF F IN -2.15 + XA 0.95 XA- YA PLANE +XA DEG / L A PROJECTION OF F IN GIMBALING CAPABILITY 8 = 4.5 DEG ENGINE PITCH _f'= -4.5 DEG ENGINE YAW + OF SPS ENGINE i; _ I "_ -_. XA _ YA •" ZA PLANE e=-4.5 "_,,] _ DEG +ZA "•// \ PROJECTION GIMBALING CAPABILITY _ IN PROJECTION XA - YA PLANE OF SPS ENGINE IN X A - Z A PLANE + OR - SIGN ACCORDING TO ENGINE GIMBAL _,+ _ =0.95 _/XA _'"_-'_,J,_"d'_ DEG SIGN CONVENTION XA DEG_ _" 8 = -2.
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;> UK e,',_ v r',- 4_ o I 0K_ _ 0 II ° UO I °_,,_ I 0.-x < a_ © < = z g 0 4 U u °_,,_ 0 U If<: × u o x < x L U I ¢,4 I ,_1 _.
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LM ADAPTER DEPLOYED ¢N -Z S-IVB _. LM °o°.°..°,°.°°°..°....°,.,.., ::::::::::::::::::::::::'::: :.:°:.:.:.:.:.:.:-:.:.:.:.:, .,......,.°.,-..,°..°,°...°, °:.:.:°_°:.:.:.:.:.: ,:-:.:.: :.:.:.:.:.:.:-:._ ¢.q C) I I _0 I X A = 1110.25 X E = 312.5 CSM z CSM/LM SEPARATE FROM S-IVB TRANSLATION SEPARATION :M ad -Z A i!iii!ii!ii_i_] iiii!iii!ililit -YE _ 0 60 ° ± 10o Z., iiiiii!iiii_iil +7 :!:!:i:i:i:i:il E ii_iii!i!_iiii_ _' !i!iiii_i!i_i:il .,,_. iiiiiiiii!ii!il ,_.
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FIGURE 2-10.
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LM ADAPTER DEPLOYED ...... -Z S-IVB XA 11 I0.2_, /× TRANSLATION CSM/LM SEPARATION SEPARATE FROM S-IVB -Z A !!i.i!i:iiiii!it !iiiii_iiiiiiiiil -YE LM _ 60 ° _ i0 o -'k'--- ,......... , ..-.......... i:i:!:i:i:i:i:i:i TARGET.__ iiiiiiiiii!iiilt ii!i!!iiiii¢_ iii!iiiiiii_!_i! , ::::::::::::::::i ":ili:Z:i:i::: ii.iiii i i!iii! fYA .-..... -.,., ./'L'X';'I , HIGH OAIN ANT SECTOR IV (SM_ i'i-.-b:_Cl -_Z A +YE ' ' ilil;iiii;i;i!)it "" I. -7 .t .: i.
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c-,,l ;> < v I- z O I iii O C',,I .< P/ iii X I I oo I O --- ill X / U < I_ I.- iii Z iii O iii O "' U > U ua iii iii v O ,,, " ,,, I.-I./'I >- ._ I.-- < I II Z iii > r,D Z ;.q iii z_<-,, 0 LLI X _ J_ Z O :_ O = z 2 -- .< N I---- "' U ._ m < Z,,, _ ,-] ..-I I m',l II C',,l iii N >- I z II X II "' X <-- -J I_ _-- < U ,v U ,..- QJ W I--- O z ILl ILl 1.[ E 1: E L L E E ]_ E L.
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I I XE _-4.6" , = 254.0 (TYP) J (TYP)/ i ! -Z E (REF)|CLUSTER "2_'N CLUSTER__ A_-__ 45_o (Typ) / +YE 4.6" (TYP) _CLUSTER 2-13. LM/RCS I LOCATION OF LM/RCS CLUSTERS LOOKING DOWN AT ASCENT STAGE IN LANDING POSITION +Z E THRUST CHAMBER LOCATIONS 2-14 ILl il I_ I.
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,_m_e,', dme.a.c.86 9/ZO/70 ZE A/S WATER (2) ±25.0 .13.7 D/S WATER (I) -43.2 -43.2 *54.O 0.0 DPS FUEL (2) DPS OXIDIZER 0.0 ('2) APS OXIDIZER (2) 0.0 +44.5 0.0 +44.5 +14.5 *44.5 _14.5 (I) RCS FUEL (2) RCS OXIDIZER *54.0 -71.3 APS FUEL (I) TANK YE RADIUS = 7.155 XA = 1110.25 X E = 312.5 H20 _[_ XE = 308.9 ----_ H20 X E = 295.45_ XE = 295.49 XE = 264.3 X E = 257.73 X E = 252.71 X E = 252.71 XE = 203.31 TANK RADIUS = 24.7 XE = 203.31 TANK RADIUS = 14.2 X E = 195.
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(GDA) Actuator Rotation Response Engine Commanded of Change Angular Extend - 60 Contract + 68 Vehicle Acceleration + Pitch Pitch Contract + !]Roll Extend )Roll PROJECTION OF DPS ENGINE F THRU SC c.g. +X E PITCH GDA ROLL GDA ... _. DPS ENGINE + PITCH PIVOT + ROLL + YE + ZE + XE +X E ENGINE PROJECTION ENGINE ROLL/ OF_'N _+YE + OR - SIGN ACCORDING SIGN CONVENTION Figure 2-15.
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XLv,XA,XE TO TRANSFORM: I) APOLLO TO LAUNCH VEHICLE XLV = XA + 2756.555 2) LUNAR MODULE TO LAUNCH VEHICLE XLV = X E + 3156.055 LM DOCKING INTERFACE X E : 312.5 XLV : 3468.555 LUNAR t 312.5 MODULE X E : 0.0 XLV = 3156.055 t 399.5 _-- Z E IN. APOLLO - ZA X A = 0.0 XLV = 2756.555 2756.555 SATURN V LAUNCH IN. VEHICLE ZLV XLV = 0.0 Figure 2-16.
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APOLLO TO TRANSFORM: 1) LAUNCH X A = 0.0 VEHICLE X A = 4578.805 TO APOLLO XLV -- 4578.805 - XLV 1110 25 IN. LM DOCKING INTERFACE CM DOCKING XA= 1110.25 INTERFACE +X A X E = 312.5 +X E XLV = 3468.555 312.5 LUNAR IN. MODULE ZE X E = 0.0 XLV = 3156. 055 Figure 2-17.
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AMendment 9/10/70 YE ZE A/S WATER (2) ±25.0 ±13.7 D/S WATER (2) ±43.2 +43.2 DPS FUEL (2) ,.54.0 0.0 DPS OXIDIZER APS FUEL (I) APS OXIDIZER (I) RCS FUEL (2) RCS OXIDIZER TANK :1=54.0 0.0 (2) (2) 86 -71.3 0.0 +44.5 0.0 :i:44.5 ±14.5 :t_,4.5 _14.5 RADIUS : 7.155 X A = 1110.25 X E = 312.5 H20 (_)_ XE = 308.9 __ H20 X E = 295.45 X E = 295.49 r XE = 264.3 • X E = 257.73 X E = 252.71 X E = 252.71 XE = 203,31 TANK RADIUS = 24.7 X E = 203.31 XE .= 200. XE = 197.
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Amendment 86 9110170 3.0 The mass diction SPACECRAFT property of launch data have been been organized presented of by MASS data specified loglcally according to basic individual and of spacecraft mass properties These data represent supplied perty data to NASA are at any the by mission time in composite by IJ Section 3.1 Mission G 2. Section 3.2 Mission H1 3. Section 3.3 Mission H2 4. Section 3.4 Mission H3 5. Section 3.
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Amendment llO 7/19/71 SUPPLEMENTARY General Comments Inertia to be data applied shall All initial propellant The (+) or is TO to dispersions (-) added be Tables are used 3.1-1 PROPERTIES through TABLES 3.1-8: +10%. as 30 deviation are following or MASS total the subtracted values. name from tanked. of the an item indicates preceding that the total. 3.1-i angles for SPS abort sequence are: Pitch = -0.524 3.
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PAGE 96
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PAGE 98
Amendment 111 7/22/71 XA COORDINATES CSM 112 TABLE LEV DETAIL (TILTED) MASS MASS The following Delta LES information motor down PCM PCM applies PROPERTIES HIGH ALTITUDE motor motor motor ABORT PROPERTIES to Tables 3.1-4 and 3.1-5. Z (Delta LES 3.1-4 = tilted angles includes range 0.3 deg. for Delta = Sigma = tilted confluence tilted X = point angels tilted confluence point L L L L deg. deg. 300 in. Y = 1222. 0. 011 in. Z = 0.282 in.
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PAGE 100
_D o• o• _ 0 0 _K 0 _ _ o• o• oe o• o• o• oe o• o _ _0 0 0 0 0 0 0 0 0 0 O O 0 0 0 0 0 0 0 0 0 0 0 O O 0 0 0 0 0 0 0 0 0 0 0 0 O O f;- I_I P-I 0 I_ 0 f"! 0 0 0 0 0 0 "_ _ P" P" 0 aO 0 /N 0 0 C: O (_ 0 0 a G _ C ,-4 NN ,))kLLQ. I (') .J _,1 )O I'," I,II I I I I ,0 4" ,,.t 4" J' 4' 0 .4" N 3: ,0 o_ ! Z.U _'_ 0 0_ ,,.5 _)un ,4" .
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o• • 0 e,i o• o• o• o• o• o• o• o• o• o• _.J: _. o• o• o• 0 Q * 0 0 0 0 0 O 0 0 0 0 0 0 Q 0 0 0 0 0 0 0 0 0 0 0 0 Q 0 0 o O_ 0 o 0 0 0 0 0 0 0 0 0 0 0 0 I I I I I | I I I I I I I I e • • • C "J!_ ,0 '_X _d Q. _'J _- ................ g_N I' *-e I N • (_ • 0 • 0 0 • _ 0 0 I I° 0 Ie 0 l° 0 Ie 0 0 tt Ie 0 Ie 0 Ie 0 0 ie ir ,( Z 0 0 _J --, _ = _ _. ,,,, _ . _ _, _ _ _. ,_ 4, 4,' 4.
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0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 • 0e 0• 0 • 0• 0 • 0• 0e 0• 0• 0• 0• 0• O! el 0 0 • 0 0 0 0 0 0 0 0 0 0 0 0 u' C Q • • • • • • • • • • • • • • • • • • • • • • • • .-_' 0 ¸ O_ 4" (_ ,4" _ (D I_ (3 0" ,-* ;/ 0_000000000000 _r,(! i" IL f_ P._ I_ ,._: d" .4 _0 ! I I I I co e_ r_ 0 0 0 0 0 I I _' _ I I I ! N-N ZO ..I ew Q_" :>0 0 _'_ . . 4" IZ *_L,I • • • , • .
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0 e-p.. D. 4-11_ X r--i_ Lr, In CJ ::) n,. x [=._ (_. N N A ,-.,I L_ tu J o,-.. 41 G,. 0 3 ¢g W -.p _ X O*. "_ r_+ LI_ fl+" N IP ,_I O'_ +" ',O _ _ r,.. ',-'1 _ v-I qD _" ,0 i_ _ P" .,.-I IP ...4 N +'" _ P" "F- _' "-" F- _w,, ._,t LA_ ,-._; v'),_ IL • • it _f_ (.- ._ U > .... ),.+ 0 I It-U 13. L, X "lC ¢1_ IF-- I,,0 It 1,3, ...._ "-_ ._+ e- 4-_ 0r- _J _ qO e- u'_ L.
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!i li lI IZ L 1£ L L E IZ la-' IL _ |_ li tL _ L L_ L
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IL'_I b,,l J,-->_LQ. Ib QJO'_ -J (_ P'a X U" n I-I,, c-. r.._ 0J O>" 'Y X Q. n &. II tiJ 2D .-/ a¢l (,'3 °e-. ]¢ _0 "* EZ* ll--12. r,"l ,act 4..J_J M I r%l ,_. ,o ipm u_ P.' _,,_' It,,-1.1."_" JILl,/ "T'_ o .41,,_ ,e,,41 _ °rep- N wP o I e.-_,.cl r¢l _J_ l,i., ./,. I.¢,1 UJ ,r" e,-°r- _),.. D m o B I,..rid _o,, w I,'- _J e K I,,,L/ .._ ,,l,,a _'u r0 ,,--"o CJ i_i eI,,- _/'J Z I-- U_ .,IL r-_ O e" ,,ka ,,a.I O ILl' 0 U") o_ _. 4.a J laJ U _ 3¢ •.
PAGE 106
Amendment 110 7/19/71 TABLE CSM (To be 112 used properties CONSUMABLES in 3.1-7 WEIGHT conjunction Table CHANGE with CSM Earth To Orbit Pre Consumable Trans/Dock sequential mass 3.1-2). EVENT From SUMMARY Weight Amount Change Remaining Total Usage (Pounds) (Pounds) (Pounds) SM-Hydrogen Tank Tank 1 & 2 3 -1.6 53.6 -1.6 -0.6 27.0 -0.6 -7.5 625.7 -7.5 -0.7 315.9 -0.7 +0.8 35.8 +6.0 36.
PAGE 107
Amendment 7/19/71 TABLE CSM 112 (To be used properties 3.1-7 CONSUMABLES (CONTINUED) WEIGHT in conjunction Table 3.1-2). with EVENT From Pre Post To D.O.I. D.O.I. Post Consumable D.O.I. CSM/LM SM-SPS Sep. 110 CHANGE CSM SUMMARY sequential mass Weight Amount Total Change _Pounds) Remaining (Pound#) Usage (Pounds) -i,561.4 12,617.7 -27,861.6 SM-Hydrogen Tank Tank 1 & 2 3 -4.0 -0.8 44.1 16.8 I & 2 3 -22.9 -13.5 534.6 219.6 -98.6 -97.0 -i14.7 +6.0 -3.8 998.9 30.0 -337.
PAGE 108
Amendment 110 7/19/71 TABLE CSM (To be 112 used properties 3.1-7 (CONTINUED) CONSUMABLES WEIGHT in conjunction Table CHANGE with CSM SUMMARY sequential Weight EVENT From Pre Post To Plane Change Plane Change Post Consumable Plane CSM/ASCT Change Dock mass 3.1-2). Change _Pounds) -1,133.8 SM-SPS Amount Total Remaining (Pounds) Usage _eounds_ 11,206.0 -29,273.3 SM-Hydrogen Tank Tank 1 & 2 3 -1.4 -0.3 31.1 13.9 -24.1 -13.7 1 & 2 3 -10.6 439.7 -193.5 -4.0 179.
PAGE 109
Amendment 110 7119171 TABLE 3.1-7 CSM 112 (To be used properties CONSUMABLES (CONCLUDED) WEIGHT in conjunction Table 3.1-2). with CHANGE CSM SUMMARY sequential Weight EVENT From Pre T.E.I. Post Post T.E.I. T.E.I. SM-SPS SM Jettison Amount Change (Pounds) Consumable To mass Total Remaining (Pognds) -9,366.8 Usage (Pounds) . 1,595.3 -38,884.0 SH-Hydrogen Tank Tank 1 & 2 3 -10.3 -2.9 12.0 9.0 -43.2 -18.6 1 & 2 3 -82.9 -49.2 293.5 96.0 -339.7 -220.6 -769.
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Amendment 110 7/19/71 TABLE LM-IO (To be used in conjunction with the 3.1-8 CONSUMABLES LM CHANGE sequential mass EVENT From To Earth Orbit Consumable CSM/LM Separation SUMMARY properties Weight Change (Pounds) Tabl e 3.1-_) Amount Remaining (Pounds) Total Usage (Pounds> D/S-Oxygen D/S-Water LM-RCS -1.0 -12.0 -5.0 92.8 396.0 600.4 -1.0 -12.0 -5.0 CSM/LM Separation Pre P.D.I. D/S-Oxygen D/S-Water LM-RCS -0.6 -23.0 -50.7 92.2 373.0 549.7 -1.6 -35.0 -55.
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Amendment 7/19/71 TABLE MISSION J-i 3.1-9 COMMAND (CONTINUED) MODULE SPACECRAFT AREA X STOWAGE VOLUME CENTROIDS 112 Y Z A1 i011.0 -21.0 2 i011.0 -22.0 1019.0 -22.0 8.0 3 1016.0 -24.0 28.0 4 1015.0 -7.0 28.0 5 1015.0 9.0 28.0 6 1017.0 26.0 28.0 7 i011.0 22.0 8 i011.0 21.0 -23.0 9 1013.0 0.0 16.0 A2 ISA -22.0 8.0 8.0 Top of A1 1017.0 -21.0 Top of A2 1019.0 -22.0 Top of A7 1019.0 22.0 8.0 Top of A8 1020.0 25.0 -8.0 Top of A9 1016.
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Amendment 1I0 7/19/71 TABLE MISSION J-i COMMAND The following stowage stowage volumes. with 3.
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Amendment 1 I0 7/19/71 TABLE MISSION J-i LUNAR 3.1-9.1 MODULE STOWAGE VOLUME CENTROIDS LM-10 DESCRIPTION X Y Z 280.0 263.5 -19.0 -20.6 13.5 14.9 240.5 270.3 265.9 -15.3 -15.0 -20.7 13.3 19.0 -6.0 LM Medical Pkg Boots & Purge Vlv-Upper Boots & Purge Vlv-Lower 257.4 257.5 265.9 273.7 281.0 273.7 -20.7 -20.0 -20.0 -20.4 -20.0 -20.0 -6.0 -18.0 -18.0 1.2 -8.5 -8.5 In-Flight 270.3 -15.0 19.0 260.0 280.0 221.8 278.5 250.0 272.6 288.0 250.0 262.4 272.0 300.0 -37.0 0.0 -I.0 -ii.0 11.
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Amendment 7/19/71 TABLE3.1-9.1 MISSION J-i LUNAR MODULE 110 (CONCLUDED) STOWAGE VOLUME CENTROIDS LM-IO AREA DESCRIPTION X Y Z 282.2 286.0 -21.0 17.8 66.6 66.6 270.3 238.0 238.4 0.0 38.0 38.6 52.8 49.8 46.0 F4 F5 COAS Earth Launch 16 MM Camera-DAC F6A,B,C FTA F7B ISA-Earth Launch 16 MM Camera Wedge Monocular FTC F7D F7E FTF 70 MM Camera Assy 70 MM Film Magazines (4) Neck Ring & LGC Adapters Camera Mount Brkt & Wrench 242.8 238.0 243.2 238.0 38.0 38.0 38.0 38.0 41.0 38.4 31.2 31.
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PAGE 205
TABLE CONSUMABLES LOADING 3. i-i0 REqUIKEMENTS MISSION SPS I D,es_ure tuel TOLERANCES PROPELLANT 70+_5 110±4 quantity Fue i 70±5 See 1_ _dout (%) Oxid i ze r Figure See 4.1-3 SPS Propellant Load (Ib) Loading Fuel 15704.0 78.6 15625.4 67.6 15557.8 ]Load 2Trapped Tanked 2Trapped 3Nomlnal Outside Tanks Inside Tanks Deliverable _Service Secondary Primary Fuel Fuel - Quads A, B, A, B, Primary and Secondary Figure 4.3-3.
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TABLE 3.1-i0 ConDand Module Pressure 900±50 and GOX Earth . Module Hydrogen Req. Per ,,,(pounds) Tank Hydrogen Tank Tank Tank 1 2 3 29.3 29.3 29.3 Oxygen Tank Tank Tank 1 2 3 330.1 330.1 330.1 Launch Weight 35.0 30.0 3.7 8Service Loading Water Loading Requirement Weight (ib) (pSIA) Waste Water6 Potable Water ? C M/GOX Amendment iI ' 7/2/i /7] (CONTINUED) 6.7 (ib) (Entry) and Oxygen Earth Launch Per Weight Tank (lb) Actual ' Rer Tank 27.6 27.6 27.6 27.3 316.6 316.
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i TABLE SPS Amendment 7/19/71 3.1-11 PROPELLANT LOAD CALCULATION FUEL 1. Enter Item 2. Use Fisures 4.1-3 pellant load for and 4.1-4 above quanClCy Nominal propellant (use temperature - 3. SPS Quantity C - Percent) 4. Cubic 5. Calculated 6. Adjustment due ?. Resulting item 5, actual less item SPS Oxidizer feet of Readout density density propellant density to SPS FUEL at from PSIA (Table to obtain readout, 3.1-12 (item Table PUGS zero adjust load i00.7 pro15,688.
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TABLE SPS F 3.1-13 PROPELLANT Amendment 1 I0 7/19/71 UNCERTAINTIES • ITEM LOADING Tank FUEL (ib) UNCERTAINTIES Volume Temperature Standpipe Gauge Height Propellant Density Batch (±2.0°F) Gauge (±0.
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Amendment 110 7/19/71 3.1-14 TABLE COMMAND MODULE RCS LOADING PARAMETERS AND CALCULATIONS This table will be completed when loading is accomplished. For Mission Planning, reference should be made to Section 4.2 for nominal load, loading tolerances, trapped and deliverable propellants. FUE_._L Tank A. Tank B. Liquid C. Total D. Initial Weight in Bleed Prior to Loading (Ib) E. F, Volume Final After Line @0.0 PSIA Volume (in 3) A + B (in 3) OXIDIZER Tank 1474.
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Amendment II0 7/19/71 TABLE 3.1-15 SERVICE MODULE RCSLOADING SUMMATION This table will be completed when loading is accomplished. should be made to Section 4.2, for nominal nominal deliverable propellants. ning, reference tolerances, and _uad A (Ib) quad Secondary Fuel Primary Fuel &h._ 69.0 Total Fuel Maximum Trapped 109.3 2.1 Nominal Deliverable 107.2 Total Oxidizer Maximum Trapped Nominal Deliverable 225.8 4.5 221.3 quad _0.7 '2.3 40.3 69.O Total Fuel Maximum Trapped 109.3 2.
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110 Amendment TABLE LM-IO CONSUMABLE LM-IO 7/19/71 3.1-16 LOADING APS REQUIREMENTS PROPELLANT Fu_l (ib) Propellant Trapped Load Outside Tanks 5.9 Tanked Inside Tanks Nominal Deliverable Propellant A. Final B. Propellant C. Nominal at loading Correction tank 0.09 = Correction 0.15 = off-load amount of propellant the indicated load. is ±0.5 (PSIG) pounds 60.3 50.3 69.0 70.25 2069.8 (ib) 2F. Measured (Item (Item (ib) 2G.
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Amendment TABLE 3.1-16(CONTINUED) LM-10 CONSUMABLE LM-IO LOADING DPS REQUIREMENTS PROPELLANT Fuel Propellant Load Trapped Outside Tanks Oxidizer 48.9 7510.3 Inside Nominal Deliverable Tanks 11975.0 ]0.5 23.5 7499.8 Outage TBD Propellant TBD The following table should be used to determine off-loaded from a full condition to arrive at the amount the indicated able tolerance ±0.5 AI. Final BI. Propellant CI. Nominal DI. Correction for tank .... I1951.
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TABLE LM-10 System A Fuel System A Oxidizer System System B Fuel B Oxidizer - 3.1-16 RCS PROPELLANT 42 ) Required Ullage Minimm _ 152.5 Requirement Maximum _ 164.5 208.2±1.9 107.4±0.9 267.0 152.5 279.0 164.5 208.2ZI.9 267.0 279.0 FUEL Load Trapped Tanked Outside Tanks Trapped Nominal in Tanks Deliverable LM-10 - tank #i (6) - APS - RCS - RCS tank 02 (6) tank tank #I #2 (6) (6) - DPS (SHe) - DPS (Ambient)(6) Nitrogen 416.4 15.8 400.6 4.2 200.6 8.0 392.
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I Amendment 110 7/19/71 TABLE 3.1-16.1 °F WATER LOADING DATA LM-IO TANKS DESCENT T ECS Po PFI* PFN PSIA PSIA PSIA ASCENT TANKS PF2 PFI PF2 PSIA PSIA PSIA 39,501 39,587 46,427 46,516 46,683 46,782 39,671 39,757 46,605 46,880 46,980 47,079 47,179 60 61 11,607 11,629 22,212 22,254 39,245 39,321 62 63 11,651.
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Amendment LOAD APS 1. , tank Fuel - Item K, 12. Density of temperature 13. Propellant volume item 2. (it 3) 14. (from Resulting 6. Off-load 7. Propellant (ib) required 8. Propellant load 1 i0. Iii. 112. full tank amount item Tablp load Oxidizer 2065.1 N/A N/A N/A N/A N/A N/A ] by 3.1-19) (Ib) 2065.1 (Ib) 3305.9 43.7 to fill RCS 64.5 manifolds i0.0 tank Density (Ib) - of Item 15.8 2011.4 and Propellant volume )(it K1 3.
PAGE 218
TABLE LM-10 PROPELLANT LM-10 Amendment 7119171 3.1-18 LOADING APS UNCERTAINTIES PROPELLANT Fuel Vent Line Tank Volume Volume (ib) Oxidizer +-0.2 -+0.3 +-0.8 +1.3 -+0.5 _+0.8 _+1.7 +_4.3 Density +-0.7 +-0.5 Weight Measurement _+0.5 +-0.5 iLoading Tolerance -+0.0 +0.0 -+4.3 -+7.7 +-0.2 +0.3 -+3.62 +-5.96 -+1.70 -+2.77 +-6.49 +-15.76 Density -+2.55 -+1.70 Weight Measurement +-0.5 -+0.5 iLoadlng Tolerance +-0.0 -+0.0 -+15.1 +-27.0 +-0.6 +-1.8 +-0.4 +-0.
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TABLE I_4-I0 APS (To Be PROEPLLANT Completed Amendment 1 10 7/19/71 3.1-19 LOADING by PARAMETERS KSC at Loading) Fuel Loading Pressure Loading Temperature - Fill Loading Temperature - Return Loading Temperature - Tank Number Total of Times Pounds Pounds - PSIA Weigh Tank Off-Loaded Off-Loaded Measured Fuel Measured Oxidizer Flow @ 25°C; Density Line Used _GP0718 F [GPI218 (Flow Meter Meter (Flow (Weigh Tank PSIA @ 14.7 3.]-]35 Fuel Oxidizer Not Tank @ 14.
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Amendment Il0 7/19/71 TABLE LM-10 DPS 3.1-19 (CONTINUED) PP4DPELLANT LOADING PARAMETERS Fuel Loading Pressure Loading Temperature - Fill Loading Temperature - Return Loading Temperature - Tank One - Degrees _#CQ3718 _GQ4218 Loading Temperature - Tank Two - _IGQ3719 -IGQ4219 Tank Used Number Total Pounds of - Times Pounds Weigh Off-Loaded Off-Loaded Fuel Density Measured Oxidizer Flow @ Density - 25"C; @ - Degrees Weigh Meter 4"C; Meter Tank 14.
PAGE 221
Amendment 7119/71 MISSION Table Table 3.1-20 3.1-21 presence the coordinates, SM/SPS burn. J-i MASS PROPERTY CSH-112/LH-10(docked) as a function of DATA II0 TABLES mass spacecraft properties, weight for in Apollo L.O.I. presents the CSM-112/I_4-10 coordinates, as a function D.O.I. SM/SPS burn. (docked) mass of spacecraft properties, weight for in Apollo the properties, for the in Apollo Circulartzatton coordinates, I SM/SPS coordinates, I SH/SPS Table 3.
PAGE 222
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9115171 SUPPLEMENTARY General DATA Comments Inertia to data APPLICABLE be applied dispersions Dispersions shall All initial propellant The (+) item Table or is (-) added be sign to TO to are used Tables MASS 3.2-1 PROPERTIES through TABLES 3.2-8: +10%. as 3o weights deviation are following or SEQUENTIAL total the subtracted values. name from tanked. of the an item preceding indicates that the total. 3.2-1 SM/SPS Yaw = Table gimbal 1.
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TABLE LM-II 3.2-3 (CONTINUED) CONTINGENCY To Be MASS PROPERTIES Supplied. 3.
PAGE 251
TABLE \ LRV FIRST 3.2-3.1 MASS PROPERTIES TRAVERSE To Be DEPARTURE Supplled. 3.
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Amendment 114 9/15/71 TABLE 3.2-3.1 LRV FIRST To MASS (CONTINUED) PROPERTIES TRAVERSE Be RETURN Supplied. 3.
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Amendment 114 9/15/71 TABLE 3.2-3.1 LRV SECOND MASS (CONTINUED) PROPERTIES TRAVERSE 'To Be DEPARTURE Supplied. 3.
PAGE 254
Amendment 9/15171 TABLE 3.2-3.1 LRV MASS 114 (CONTINUED) PROPERTIES SECOND TRAVERSE RETURN To Be Supplied.
PAGE 255
Amendment 9/15/71 TABLE 3.2-3.1 LRV MASS THIRD (CONTINUED) PROPERTIES TRAVERSE To Be 114 DEPARTURE Supplied. 3.
PAGE 256
Amendment 114 9is71 TABLE LRV 3.2-3.1 MASS THIRD (CONTINUED) PROPERTIES TRAVERSE To Be RETURN Supplied. 3.
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Amendment 9115171 TABLE HIGH ALTITUDE To be supplied 3.2-21 114 3.2-4 MASS PROPERTIES at a later date.
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Amendment 114 9115171 TABLE PAD To be ABORT 3.2-5 MASS supplied at PROPERTIES a later date. \ 3.2-22 SNA-8-D-027(III)REV 3 _ L 1_ EE L L.
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Amendment 114 9/15/71 TABLE SIVB U I/ L h I/ h L MASS 3.2-6 PROPERTIES s_-8-v-o27cI.
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Amendment 114 9/15/71 TABLE3.2-7 CSM (To be 113 used CONSUMABLES in properties WEIGHT conjunction Table with CHANGE CSM Earth To Orbit Pre Consumable Trans/Dock sequential mass 3.2-2). EVENT From SUMMARY Weight Amount Change Remaining (Pounds) _Pounds) Total Usage (Pounds) SM-Hydrogen Tank i & -1.6 53.6 -1.6 Tank 3 2 -0.6 27.0 -0.6 Tank 1 & 2 -7.5 625.7 -7.5 Tank 3 -0.7 315.9 -0.7 +4.8 39.8 +6.0 36.
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TABLE 3.2-7 CSM 113 CONSUMABLES (To be used properties WEIGHT in conjunction Table 3.2-2). with EVENT From Pre To D.O.I. Post D.O.I. Consumable Post D.O.I. CSM/LM Sep. Amendment 9/15/71 (CONTINUED) SM-SPS CHANGE 114 SUMMARY CSM sequential Weight Change (Pounds_ -1,561.4 mass Amount Remaining
PAGE 262
Amendment TABLE CSM (To be 113 used (CONTINUED) CONSUMABLES in properties 3.2-7 WEIGHT conjunction Table CHANGE with ?re ?out To Plane Change Plane Change Post Consumable Plane CSM/ASCT Change Dock SUMMARY sequential mass 3.2-2). EVENT From CSM 114 9/15/71 Weight Amount Change Remaining (Pounds) (Pounds) -1,133.8 SM-SPS 11,320.4 Total Usage (Pounds) -29,273.3 SM-Hydrogen Tank i Tank 3 & 2 -1.4 31.1 -24.1 -0.3 13.9 -13.7 -10.6 439.7 -193.5 -4.0 179.
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Amendment TABLE CSM (To be 113 used properties 3.2-7 CONSUMABLES in (CONCLUDED) WEIGHT conjunction Table with Pre Post To T.E.I. Consumable Post T.E.I. SM T.E.I. SM-SPS Jettison SUMMARY sequential mass 3.2-2). EVENT From CHANGE CSM 114 9/15/71 Weight Amount Change Remaining (Pounds_ {Pounds) -9,366.8 1,709.7 Total Usage (Pounds_ -38,884.0 SM-Hydrogen Tank I & 2 Tank 3 -10.3 12.0 -2.9 9.0 SM-Oxygen Tank i & 2 -82.9 293.5 -339.7 Tank 3 -49.2 96.0 -220.
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Amendment TABLE LM-II (To be used in conjunction CONSUMABLES with the LM CHANGE sequential EVENT From Consumable To Earth Orbit CSM/LM Pre CSM/LM Separation D/S-Oxygen P.D.I. Separation Pre LM P.D.I. D/S-Oxygen D/S-Water LM-RCS @ Touchdown 92.1 351.0 -1.7 -37.0 in A/S Pre @ Docking -i.0 -12.0 -5.0 -0.i -2.0 D/S-Oxygen D/S-Water A/S A/S 92.8 376.0 600.4 -55.7 LM-APS T.P.I. -i.0 -12.0 -5.0 Usage (Pounds) 549.7 in Post (Pounds) -50.
PAGE 265
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Amendment 9/15/71 TABLE MISSION 3.2-9 J-2 COMMAND (CONTINUED) MODULE SPACECRAFT STOWAGE VOLUME CENTROIDS 113 X Y Z i011.0 i011.0 1019.0 1016.0 1015.0 1015.0 1017.0 I011.0 I011.0 1013.0 -21.0 -22.0 -22.0 -24.0 -7.0 9.0 26.0 22.0 21.0 0.0 -22.0 8.0 8.0 28.0 28.0 28.0 28.0 8.0 -23.0 16.0 1017.0 1019.0 1019.0 1020.0 1016.0 1014.0 -21.0 -22.0 22.0 25.0 0.0 0.0 -22.0 8.0 8.0 -8.0 16.0 8.0 BI 2 3 4 5 6 8 i050.0 1039.0 i031.0 1031.0 1031.0 1031.0 1024.0 -27.0 -38.0 -28.0 -20.0 -8.0 13.0 -38.
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Amendment 114 9/15/71 TABLE MISSION The with J-2 following stowage 3.2-9 COMMAND stowage (CONCLUDED) MODULE locations STOWAGE have Signal Display unique CENTROID volume centroids not associated volumes. NOMENCLATURE G&N VOLUME Cond. LOCATION X Y Z LEB 1069.0 25.0 29.0 LEB 1060.0 26.0 32.0 Panel Keyboard Sleep Restraint Assy - Rt. Sleep Restraint Assy - Left Entry Locations Sleep Restraint ITLSA - IV - RH & Center Aft UEB 1018.0 23.0 -50.
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TABLE MISSION J-2 LUNAR MODULE Amendment 9/15/71 3.2-9.1 STOWAGE VOLUME 114 CENTROIDS LM-II AREA X AIA AIB AIC AID AIE AIF AIG AIH AIJ AlL AIK AIDA AIDB AlDC AlDD A2 A3 A5 A6 A7 A8 A9 AI0 All AI2 Al3 AI4 Al5 FIA FIB FIC FID FIE FIF FIG FIH FIJ FIK F2 F3 3.2-33 Y Z 280.0 263.5 240.5 270.3 265.9 257.4 257.5 265.9 273.7 281.0 273.7 -19.0 -20.6 -15.3 -15.0 -20.7 -20.7 -20.0 -20.0 -20.4 -20.0 -20.0 13.5 14.9 13.3 19.0 -6.0 -6.0 -18.0 -18.0 1.2 -8.5 -8.5 270.3 -15.0 19.0 260.0 280.0 221.
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114 Amendment 9/15/71 TABLE MISSION J-2 LUNAR 3.2-9.1 MODULE (CONCLUDED) STOWAGE VOLUME CENTROIDS LM-II AREA F4 F5 F6A,B,C F7A F7B FTC F7D F7E F7F F7G F7H F7J F7K F7L FFM F7N FTP F8 F9 FI0 3.2-34 X Y 282.2 286.0 270.3 238.0 238.4 242.8 238.0 243.2 238.0 227.9 237.7 231.5 222.6 231.8 225.7 238.0 241.0 221.0 219.9 221.0 -21.0 17.8 0.0 38.0 38.6 38.0 38.0 38.0 38.0 33.0 38.3 35.4 32.3 36.0 32.3 38.0 38.0 18.0 -1.3 -18.0 SNA-8-D-027 E E Z 66.6 66.6 52.8 49.8 46.0 41.0 38.4 31.2 31.6 31.8 45.
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PAGE 332
Amendment TABLE CONSUMABLES LOADING 3.2-10 REQUIREMENTS MISSION SPS Pressure Fuel 110±4 AND TOLERANCES J-2 PROPELLANT quantity Fuel Temperature (°F) Fuel Oxidizer (PS IA) Oxidizer 110±4 70±5 See 70±5 Readout (%) Oxidize r Figure 4.1-3 SPS Propellant Load (ib) Loading Fuel TLoad Outside 2Trapped 3Nominal Inside Tanks Deliverable Fuel Primary Fuel Primary and Figure 67.
PAGE 333
Amendment TABLE 3.2-10 (CONTINUED) MISSION Command Module Pressure Waste Water Potable J-2 Water Loading (PSIA) and GOX Earth Requirement Weight Actual (lb) 35.0 ? 30.0 CM/COX 900±50 3.7 8Service Loading Module Req. Per (Entry) 6.7 Hydrogen and Oxygen Earth Tank Launch Per (pounds) Tank Hydrogen Tank i 29.3 27.6 Tank 2 29.3 27.6 Tank 3 29.3 27.6 Oxygen Tank i 330.1 316.6 Tank 2 330 .i 316.6 Tank 3 330.1 316.
PAGE 334
TABLE Amendment 3.2-11 114 9/15171 MISSION SPS PROPELLANT J-2 LOAD CALCULATION FUEL i. Enter Item 2. Use load 3. SPS Figures for 4.1-3 above and at propellant ii0 PSIA (Table 3.2-12 5. Calculated density 6. Adjustment due 7. Resulting 5, of propellant SPS SPS Oxidizer Fuel from to PUGS actual less graph (item Table zero 6) propellant temperature below) (ib/ft 3) 2 divided 3.2-12 adjust propellant item obtain at loading - density Cubic to readout.
PAGE 335
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PAGE 336
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PAGE 337
TABLE MISSION SPS PROPELLANT UNCERTAINTIES FUEL Standpipe Gauge Density Batch (+2.0°F) Height Propellant Gauge (-+0.35% of Gaugeable) Measurement Density Loading (i) (I) Pressure OXIDIZER _ib) Volume Temperature 114 J-2 ITEM UNCERTAINTIES LOADING Tank Amendment 9115171 3.
PAGE 338
Amendment TABLE 3.2-14 MISSION CO_4AND This table will Planning, MODULE be LOADING completed reference tolerances, RCS should trapped and when be J-2 PARAMETERS loading made to deliverable is AND CALCULATIONS accomplished, Section 4.2 for For nominal Tank Tank B. Liquid C. Total D. E. F. Volume @0.0 Line A + Initial Volume B Weight to A Final Weight After Loading in Load Propellant H.
PAGE 339
Amendment TABLE 3.2-15 MISSION SERVICE This table Planning, will be reference tolerances, and quad Secondary completed should nominal A MODULE when be made deliverable RCS J-2 LOADING loading to SUMMATION is accomplished. Section 4.
PAGE 340
TABLE 3.2-16 MISSION LM-II CONSUMABLE LM-II Amendment 9115171 J-2 LOADING APS REQUIREMENTS PROPELLANT Fuel Propellant Load Trapped Outside Tanks Oxidizer Inside 5.9 Tanks Nominal Deliverable 8.3 APS 3217.4 i0.0 3189.7 TBD TBD Propellant following allowable TBD table off-loaded 27.7 1998.3 Outage Total (lh) 3225.7 2008.3 Trapped The (ib) 2014.
PAGE 341
Amendment TABLE 3.2-16 (CONTINUED) J-2 MISSION LM-II CONSUMABLE LM-II LOADING DPS REQUIREMENTS PROPELLANT Fuel Propellant Trapped Load Tanks 12035.8 48.9 27,3 Tanked 11986.9 74_8,7 Trapped Inside Nominal Deliverable Tanks 43.3 13,5 11943.6 7485.2 TBD TBD Outage Total Oxidizer (Ib) 7_26.0 Outside 114 9/15/71 DPS Propellant TBD The following table should be used to determine the amount off-loaded from a full condition to arrive at the indicated able tolerance for the AI.
PAGE 342
Amendment TABLE 3.2-16 MISSION LM-II System A Fuel System A Oxidizer System System B B Fuel Oxidizer - RCS J-2 PROPELLANT (2) Required Ullage Requirement Load (Ib) 5 107.4±0.9 Minimum 152.5 4 267.0 152.5 279.0 164.5 208.2±1.9 267.0 279.0 Load Trapped Tanked Outside Tanks Trapped Nominal in Tanks Deliverable LM-II 4.2 200.6 8.0 392.
PAGE 343
Amendment 9/15/71 TABLE LM-II ECS To 3.2-16.1 WATER Be 114 LOADING DATA Supplied. 3.
PAGE 344
Amendment TABLE 3.2-17 MISSION LM-II APS i. LOAD J-2 CALCULATION FUEL PROPELLANT Full tank - Item K, Table 3.2-16 Density of temperature off-load tables at loading and pressure (ib/ft 3) I 3. Propellant volume i 4. 2) (divide item OXIDIZER (ib) 12. item 114 9115/71 i by (ft 3) Measured density (from Table 3.2-19) (lblft3) * 5. Resulting full 6. Off-load amount 7. Propellant (ib) required 8. Propellant load DPS 9. Ii0. tank Density of 112.
PAGE 345
TABLE MISSION LM-II PROPELLANT LM-II Amendment 3.2-18 J-2 LOADING APS UNCERTAINTIES PROPELLANT Fuel Vent Line Tank Volume Volume Pressure Measurement Temperature Measured (+5 Measurement ±0.8 +-I.3 ±0.5 ±0.8 +-1.7 ±4.3 ±0.7 ±0.5 +-0.5 +-0.5 ±0.5 +-0.5 ±4.8 ±8.2 ±0.2 ±0.3 ±3.62 ±5.96 +-1.70 ±2.77 +-6.49 ±15.
PAGE 346
TABLE3.
PAGE 347
Amendment TABLE3.
PAGE 348
Amendment MISSION J-2 MASS PROPERTY DATA TABLES 114 9/15/71 Table 3.2-20 presents the CSM-ll3/LM-ll(docked) mass properties, in Apollo coordinates, as a function of spacecraft weight for L.O.I. SM/SPS burn. Table 3.2-21 presents the CSM-ll3/LM-ll(docked) mass properties, in Apollo courdinates, as a function of spacecraft weight for the D.O.I. SM/SPS burn. Table 3.2-22 presents the CSM-II3 mass properties, in Apollo coordinates, as a function of CSM weight for the Circularization I SM/SPS burn. Table 3.
PAGE 349
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PAGE 365
Amendment 1/14/7o SUPPLEMENTARY General Comments Inertia data be All propellant initial propellants in be are the LM tanks. propellants CSM The 30 weights docked SEQUENTIAL 3.3-1 through deviation are to be are are PROPERTIES TABLES 3.3-8: values. total in the tanked. low configuration. propellants MASS +10%.
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Amendment 79 3/30/70 THIS PAGE INTENTIONALLY LEFT BLANK 3.3-10.4 II II I: i: 1: E :L L L ]: E SNA-8-D027 :E L,' (III)REV 2 L..
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e.l 0000000000000000 • • • Z _ • • • • • • • o o o o o o o o o o o • • • • • • • • • • • O O a _c E_ -c.-_ • o o o e o 0 • • • o o o • • • v ? C _ O 0 0 0 0 0 0 0 0 0 0 0 I < ,=._ _ 0 o o 0 0 0 o 0 o o o 0 0 o 0 0 Co ,,j bu o _. =... = _. = _. = _. o _. o _. o _. _.
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e-I :> N Z =,== 0• 0• 0• 0• 0• 0• 0• O• O• 0• O• 0• O• .
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PAGE 387
Amendment 3130/70 TABLE CSM (To be used in 109 conjunction Consumables with the CSM 3.3-7 Weight Change sequential Summary mass properties Weight EVENT Consumable From Change (Pounds) To Earth Launch Pre Trans/Dock SM-Hydrogen SM-Oxygen CM-Potable H20 CM-Waste H20 Pre Trans/Dock Post Post Trans/Dock Pre Trans/Dock SPS Hybrid Post Pre SPS Post Hybrid H.C.C. Post Pre SPS Pre L.O.I. i L.O.I. Post Pre Post -159.8 L.O.I. Pre D.O.I. Post Post D.O.I. D.O.I.
PAGE 388
Amendment 3/30/70 , CSM _To be used in TABLE 109 conlunction 3.3-7 Consumables with the EVENT Change sequential Consumable From Post (Continued) Weight CSM To Circularization Pre Plane Change i SM-Hydrogen SM-Oxygen SM-RCS Pre Plane Post Change Plane CSM/ASCT 1 Change Post 1 Docking Plane CSM/ASCT Pre Change i Docking Plane Change 2 Plane Post Plane Change Change 2 Post 2 Pre Plane Change T.E.I. SM-SPS SM-Hydrogen Post Post T.E.I. SH T.E.I.
PAGE 389
Amendment 79 3130170 TABLE LM-7 _To be used in conjunction Consumables with the EVENT From LM 3.3-8 Change sequential Consumable To Earth Orbit CSM/LM Separation D/S-Oxygen Pre P.D.I. Pre LM P.D.I. @ Touchdown A/S Liftoff in Orbit A/S in A/S @ Orbit C.S.I. @ C.S.l. A/S @ Docking @ Docking A/S Jettison Remaining Usage (Pounds) (Pounds) (Pounds) -2.8 -5.0 599.6 -5.0 D/S-Oxygen D/S-Water -0.9 -23.6 44.3 211.6 -3.7 -38.4 LM-RCS -53.4 546.2 -58.
PAGE 390
Amendment 3/30/70 MISSION The reference of information intended "H-2" TRANSFERABLE EQUIPMENT table used with this transferable sources from which data for each to define the exact source of each correlated to each item in code number for each item Abbreviations in Co this G. O. "DATA" refers is designated "STOWAGE bi-weekly to to Stowage H. Operations all information, separate sources. LIST" refers for NASA by obtained requests the data the transferable listed. are as used.
PAGE 391
Amendment 3/30/70 TABLE MISSION H COMMAND MODULE S/C 3.3-9 STOWAGE 109 VOLUME CENTROIDS - iii AREA X Y Z A1 3 4 1012.0 1016.0 -22.0 -24.0 -26.0 28.0 1015.0 1015.0 1017.0 1012.0 1012.0 i011.0 1011.0 1013.0 i010.0 - 7.0 9.0 26.0 31.0 22.0 23.0 19.0 - 9.0 -22.0 28.0 28.0 28.0 7.0 -23.0 6.0 7.0 14.0 - 2.0 BI 2 3 4 5 6 7 8 1050.0 1039.0 1031.0 1031.0 1031.0 1031.0 1033.0 1024.0 -27.0 -38.0 -28.0 -20.0 - 8.0 13.0 27.0 -38.0 39.0 37.0 40.0 40.0 39.0 39.0 36.0 37.0 L2 3 1059.0 1048.0 -44.
PAGE 392
Amendment 70 10/10/69 TABLE The following stowage not associated with 3.3"9.1 locations stowage NO_ENCLATURE G&N Signal Display Cond. have Panel 25 0 26 0 UEB 1018.0 25 0 -47,9 UEB Right Aft Slee_ Food Restraint Container Assy - Left Aft Food Container Bags (In-flight Location) and Accessory (In-flight Location)- Helmet Stowage Bags Helmet (In-flight Location)Stowage and Accessory Bags and (In-flight L.H. -21 0 -49.9 1048.O -47 0 12.0 B1 1050.
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. Amendment 80 4/8/70 TABLE CONSUMABLES LOADING 3.3-10 REQUIREMENTS Mission SPS Pressure Fuel 11024 AND TOLERANCES H-2 Propellant Temperature _*F) Fuel Oxidizer _PSIA) Oxidizer 110t4 70t5 quant i ty Fuel 70_5 See Readout (%) Oxidizer Figure See 4.1-3 SPS Propellant Load Loadin_ Fuel (Ib) 2Trapped Tanked Outside 2Trapped 3Nominal Inside Tanks Deliverable Tanks _Service Secondary Primary Fuel Fuel Requirement Oxidizer 15704.0 78.6 15625.4 67.6 15557.
PAGE 432
Amendment 80 4/8/70 TABLE3.3-10 (Continued) Comand Module (P$1A) Potable I Water 7 CM/COX Waste Water 6 *As serviced, Water Weight Pressure lift-off; 8Service Module Req. Waste Water Hydrogen Per Oxygen 38.0 and Tank (Ib_ 36.0 Earth Requirement *30 ibs Actual Launch 6.7 (Entry) 18.0 ibs, Potable Water *ii ibs 31.4 ibs. Oxygen Earth (pounds) 29.3 330.I Hydrogen Weight 3.7 at Loading COX _ib_ Loading 900±50 predicted and Launch Per Tank 27.6 Weight (ib) 316.
PAGE 433
Amendment 3/30/70 TABLE 3.3-11 SPS Propellant Load Calculation OXIDIZER 1. Enter item sPa Quantity C - Percent) Readout at 110 Use F£guree 4.1-3 pellant load for 3. Nominal 4. Cubic 5. Calculated density 6. Adjustment due 7. Resulting actual propellant load Item 5, less item 6) (pounds) sPa Oxidizer and 4.1-4 above quantity propellant density temperature to obtaln readout. at - density feet of propellant to (Table 3.3-12 100.8 2.
PAGE 434
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¢'4 Cr_ A Ol _I Ol 1°1°1 _4 0 I I oO I 0 cU _ _ "_ O0 • .,-I 0 (/3 U _'_ I 0 _ U _ In I.., '_ I., ,-_ oO m m "_ _ _ I,.I N m • M I.I I-I _ 0 I,,I u, m 0 I!t _t.,-I Q_ ._..I ,i_ 4.J "_O 4.1 I _ -,,-I I _U ,,-t o • 0 m m m _U N q-4 m _J 0 _ 0 w-4 I c_ _._ 0 _-_ J -,-4 _I._ 0 c_ u_ I c_ ,-.1 0 0 4 m U_ 0 0 _ U m I.i al 0 C: I _._ .IJ _ 0 "0 I ,_I I ° '_ _ _'_ _ _.
PAGE 436
TABLE SPS 3.3-13 PROPELLANT Amendment 3130170 UNCERTAINTIES ITEM LOADING FUEL (ib) OXIDIZER ±24 _39 _18 ±46 ± 6 ±i0 ±54 ±86 ± 5 ± 5 I 0 0 ± 8 ±14 ± 63 ±107 UNCERTAINTIES Tank Volume Temperature Gauge Standpipe Height Propellant Density Batch (_2.0°F) Gauge (±0.
PAGE 437
Amendment 3130170 TABLE Command This table will Module be RCS completed Planning, reference tolerances, trapped 3.3-14 Loading when Parameters loading should be made and deliverable and Calculations is accomplished. to Section 4.2 propellants. for Tank Tank Volume @ 0.0 Line Volume B. Liquid C. Total D. Initial Weight in Bleed Prior to Loading (Ib) Weight Loading Propellant F° than Load Loading I. Specification Load @ 70_5"F L. Nominal Deliverable 1474.7 17.
PAGE 438
Amendment 3/30/70 TABLE SERVICE This nlns, table will reference tolerances, be completed when should be made to and quad nominal 2.1 1083 Trapped Deliverable Oxidizer 225.6 Total Maximum Nominal Total Maximum Nominal fuel* Maximum Nominal *Secondary +2.3 Trapped Deliverable Oxidizer 39.8 69.7 109.5 Maximum Nominal 2.1 i07t4 Trapped Deliverable Total Oxidizer Maximum Trapped 22_,5 4.5 Nominal 221,0 Total 2.
PAGE 439
Amendment 79 3/30/7o TABLE 3.3-16 Consuuunble LM-7 Loading LM- 7 APS ltequiraments Propeller Fuel Propellant Trapped Load Outside Trapped Inside Nominal Deliverable weigh Final B. Propellant C. Nominal D. Correction 26.4 1999.5 3194.1 TBD TBD TBD from tolerance should be used to determine the a full condition to arrive at for the calculeted off-load pressure overfill - Correction Measured 2G. Nominal Delta amount of propellant the indicated load. is _0.
PAGE 440
Amendment 3/3O/7O TABLE 3.3-16 (Continued) LM-7Conaumable Leaden LM-7 i lbmquirementa DPS Propellant Fuel Propellant Trapped Load Tanks Oxidizer 60,5 7048.5 Trapped Inside Tanks Nominal Deliverable 11290.4 21.7 62.7 7026,8 Outage 11227,7 TBD DPS Propellant Final tank B1. Propellant CI. Nominal DI. Correction pressure at overfill loading quantity for tank the amount of propellant the indicated load. The pounds par welsh tank.
PAGE 441
Amendment 80 418170 TABLE 3.3-16 I/4-7 - RCS Required Load _ib) 107.7'0.9 (Continued) Propellant Ullage M_n4_um IIi.0 5 (2) (3) *Actual Requirement (in _) _ Max_m,,_ _ 123.0 _ System System A A Fuel Oxidizer System B Fuel 208.8'1.9 I07.7*0.9 225.5 Iii.0 237.5 123.0 208.8 107.7 System B Oxidizer 208.8'1.9 225.5 237.5 208.8 Propellant FUEL 215.4 Load Trapped Tanked Outside Tanks Trapped Nominal in Tanks Deliverable LM-7 17.6 400.0 4.2 200.4 8.0 392.
PAGE 442
Amendment 3/30/70 TABLE LOAD i. 12. 13. 14. APS PROPELLANT Full tank - Item Density of temperature K, Table Propellant volume item 2. (ft 3) (from 5. Resulting full 6. Off-load amount 7. Propellant (ib) required Propellant load 8. DPS 9. ll0. Full tank Density Table load N/A N/A N/A N/A N/A N/A 1 by 3,3-19) (ib) 2071.1 3315.9 49.0 75.0 7,9 12.7 (ib) to fill RCS manifolds (Ib) - item K1 Table of off-load end Propellant 10 )(ft 112.
PAGE 443
An_.ndment 3/30/70 79 TABLE 3.3-18 LM-7 Propellant Loading Uncertainties LM-7 AP$ PROPELLANT Fue! (Ib) Vent llne Volume Tank Volume _0.3 zO.8 tl.3 PSIA) _0.5 tO.8 (ZI.5°F) ±1.7 z4.3 zO.7 zO.5 Measurement zO.5 zO.5 Tolerance ±0.0 ±OtO. ±4.4 ±7.7 Pressure Measurement Temperature Density tLoadlng Total Loading APS Mission Mixture _V, (±5 Measurement Measured 2Welght Oxidizer ±0.2 Uncertainty . I Uncertainties Ratlo !sp, (!b) Variatlon Vehicle Weight -34.
PAGE 444
TABLE LM-7 APS (To Pressure Loading Temperature -Flll Loading Temperature - Return Loading Temperature - Tank - Tank Used Number Total of Pounds by Weigh Off-Loaded Off-Loaded Measured Fuel at Measured Oxidizer Flow @_; Density _GP0718 FlGP1218 (Flow Meter @ @4°C; 14.7 @ Meter Not (Flow (Weigh Tank 14.7 64.0 66.6 69.1 66.8 69.3 68.0 3.3-62 68.
PAGE 445
79 Amendment 3130170 TABLE LM-7 I_S 3.3-19 (Continued) Propellant Loading Par_aeters Fuel - Oxidizer 68.3 Loading Pressure PSIA Loading Temperature - Fill Loading Temperature - Return Loading Temperature - Tank One Loading Temperature - Tank Two - Degrees Tank Used Line - _TT 58 F ITT258 Degrees Fuel Oxidizer 67.
PAGE 446
_nendment 74 1/14/70 MISSION H-2 MASS PROPERTY DATA TABLES Unless otherwise stated, the controlling vehicle propellants are in the end of their tanks and the passive vehlcle propellants are in the high end of their tanks. Table 3.3-20 presents CSM-109/LM-7 (docked) coordinates, as a function of Hybrid SM/SPS burn. Table 3.3-21 presents the coordinates, SM/SPS burn. CSM-109/LM-7 as a function Table 3.
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Amendment 3130170 LM-7 Table Ascent 3.3-30 Stage Lunar presents the three contingency cases. this table are presented Table 3.3-31 with each of Table 3.3-33 presents the LM-7 presents Lift-off LM-7 Contingencies Ascent Stage Mass Mass The detail equipment in Table 3.3-32. Properties Properties mass 79 properties for the for the CM re-entry mass properties associated Ascent Stage contingencies in Table 3.3-30. the detail equipment mass properties. 3.
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Amendment 1/22/71 SUPPLEHENTARY General DATA APPLICABLE Comments Inertia to data be applied dispersions TO SEQUENTIAL to Tables are +10%. MASK PROPERTIES 3.4-1 through 08 TABLES 3.4-8: m Table Dispersions shall All initial propellant The the (+) or (-) si_ followln8 the item is added to or subtracted used SM/SPS - simbal 1.315 3.4-7 and 3.4-4 and Delta Z deviation are total v_Jues. tonked. name of an item indicates from the preceding total.
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e_ N r | 1 • _x _ I ,I "_'., _ _ _ •_ _" _ _ _ ® _ _ _ _ _ _ _D _e_ (_d ,_ _ _ 4_ _ "_ _J _ 5- 0 • __i. _,°,_,®,'_ • • • • • °• _. _. "_ ° I _. _.
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i-i {/) o = a. • q -- K C _'. ,4' 17- #. c_N 1". _J i% • • • o • g o. •,_ x _ - ,_ m, _ L_ .el II - II II 13 L L L I-- L E 1_ ]_ II L: L,' L I._.
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Amendment 98 1/22/71 TABLE CSH (To be used in ii0 conjunction Consumables with the CSM 3.4-7 Weight Change sequential EVENT To From Earth Launch Consumable Pre Trans/Dock Trans/Dock Post Trans/Dock Post SM-Hydrogen Pre SPS Hybrid Post Pre SPS Hybrid L.O.I. Post L.O.I. Post Pre SPS Post CM-Potable +4.0 40.0 CM-Waste +0.8 18.8 -70.6 H20 Pre D.O.I. Post D.O.I. Post CSM/LM Separation Pre Circular- Circular- ization Post Circular- 724.3 -14.
PAGE 504
Amendment 1/22/71 TABLE (To be used 3.4-7 (CONTINUED) CSM 110 Consumables Weight Change Summary in conjunction with the CSM sequentlal mass properties EVENT From To Post CircularIzation Pre Pre Post Plane Post Plane CSM/ASCT Pre Change Docking Pre SM Jettison SM-SPS Docking DePloy Remaining (Pounds) -2.4 -25.1 -75.8 -1269.2 -4.9 -47.4 -135.2 -6.3 +7.8 +2.2 SM-Hydrogen SM-Oxy gen SM-RCS CM-Fec al CM-Food CM-LIOH T.E.I. SM-SPS Jettison CM @ M.C.
PAGE 505
Amendment 1/22/71 TABLE To be used in conjunction From Summary mass properties Consumable Weight Change (Pounds) D/S-Oxygen D/S-Water LM-RCS -1.1 -i 3.0 -5.0 To Earth Orbit CSM/LM CSM/LM Pre Separation P .D .I. D/S-Oxygen Separation Pre 3.4-8 LM-8 Consumables Change with the LM lequentlal EVENT P.D.I. LM @ Touchdown 98 -21.3 -55.5 D/S-Oxygen D/S-Water LM-I_S -0.i -I.I -97.0 3.4-2) Amount Remaining (Pounds) Total Usage (Pounds) 46.9 2 3 7.0 600.0 -I.
PAGE 506
r) p,-,i r_ I I I
PAGE 507
Amendment 1/22/71 98 TABLE 3.4-9 MISSION H COHHAND NODULE STOWAGE VOLLq4ZCENTROIDS S/C 109 - 111 x ! z 41 3 4 5 6 7 - NoC on S/C 110 8 10 - S/C 110 Only 11 - Not on S/C 110 12 13 1012.0 1016.0 1015.0 1015.0 1017.0 1012.0 1012.0 1011.0 1011.0 1013.0 1010.0 -22.0 -24.0 - 7.0 9.0 26.0 31.0 22.0 23.0 19.0 - 9.0 -22.0 -26.0 28.0 28.0 28.0 28.0 7.0 -23.0 6.0 7.0 14.0 - 2.0 al 2 3 4 5 6 7 8 1050.0 1039.0 1031.0 1031.0 1031.0 1031.0 1033.0 1024.0 -27.0 -38.0 -28.0 -20.0 - 8.0 13.0 27.0 -38.0 39.0 37.
PAGE 508
Amendment 1/22/71 TtbZe ,'he not followtn8 associated 8tovase vtth 3.4-9.Z locations have etovese volumes. NOHENCLATURE I Risht Left F_,rua,,, ltatch Container (unraL.er, R12 (Kn-fltlht Location) ,i,.Ime, Stowage and Accessory Ra_. ([n-flLeht Location)L.H. Helmel Stovsse and Accessory 8a8_ (Xn-£1L|ht Location)Cir. ilelmel Stovase and Accessory 8888 (lnofllsht Location) - R.H. Teumorary Stovese Ba8 - L.H. (In-flLsht LocatXon) Temporary StovaSe 888 -Ctr.
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PAGE 565
Amendment i00 1/28/71 TABLE command 3.4-10 Module Pressure Water Potable Water and Loading (PSIA) Waste (CONTINUED) GOX Earth Requirement Weisht (ib) 6 Water 7 CM/GOX 900±50 Module Loading and Requirement (ib) 33.0 36.0 31.4 6.7 Hydrogen Actual (ib) 18.0 3.7 8Service Launch Weisht (Entry) Oxygen Earth Launch Weight (pounds) (pounds) Actual (ib) Hydrogen Tank 1 29.3 27.6 27.2 Tank 2 29.3 27.6 27.2 Oxygen Tank i 330.i 316.6 316.9 Tank 2 330.
PAGE 566
Amendment 98 1/22/71 TABLE3.4-11 SPS PROPELLANT LOAD CALCULATIONS Fuel i. Enter SPS Item 2. Use Readout at Ii0 PSIA (Table Figures for 100.8 Nominal (use 4.1-3 above propellant Cubic 5. Calculated density 6. Adjustment due 7. Resulting SPS Oxidiser 5, of - 4. Item and to SPS FUEL Item to obtain 15688.0 density at density graph from PUGS (Item Table zero propellant 6) loading (ib/ft 2 divided 3.4-12 adjust load 25079.
PAGE 567
A wOw I I 0 IO aO I aO I el k_ k,* '_1 "O "GI r°° I,," III .G 01, I C i | | ¢ L_ k k_1_ k 14 I_1 _a 14 O .G &J k _.J 14 O I 6.1 .L ! ¢ 0 _c I '1"4 0 I' I 4. _ ¢ _2 I IPl I l 0 _ m w ,_ I I w crJ G w _." _ _,_ _ tU ! ,1.( I II II,_l C_lll ,v,I L' I.* m_mo _i_._ _t _ _ 22 2. _¢ _ _ i U U ]U _ L 1_, L L L U /_ _: U 1i 1I _ L_ L L.
PAGE 568
co o_, 4J t'M 4jr _. a=-_. 'I_ (.,,i _ (',,I A 0 4d I E o ! I < r,_ .u .,.g ._ ,b._ I.d ,'0 .,,.I _ ,-0 L_,.0 (U _.J ;_ "cI g 0 t.e "o I £ I _ I=, 0 .=4 QJ 4.J o d.g d._ d £ i £ I v ° 't tl I [._ M ,u c_m o _ W._l" ci III O | r,_o I:_ :lv_ 0-,-¢ , 4J ..,-4 ",'4 _ ,,. I '0 • _: 4) (B .,,,¢ _ 1,4 _.
PAGE 569
Amendment 98 1/22/71 TABLE SPS 3.4-13 PROPELLANT UNCERTAINTIES ITEM LOADING Volume Gauge Temperature Standpipe (Ib) ±24 ±39 Density Batch Gauge (±0.35% Measurement Density Loading (±2.0"F) ±18 ±46 +6 ±I0 ±54 ±86 ±5 ±5 ±0 +-0 Height Propellant of Gaugeable) (1) (I) Pressure +-8 (i) RSS RSS (1) Tolerance on Propellant of Plight Load TOTAL LOADING (1) Data will (2) Loading nomlnal, variables.
PAGE 570
Amendment 1/22/71 TABLE Command This table Planning, tolerances, Module will be reference trapped RCS Loading 3.4-14 Parameters completed when loading is should be made to Section and deliverable propellants. and Calculations accomplished. For Mission 4.2 for nominal load, loading FUEL Tank A. Tank B. Liquid C. Total D. Initial Weight in Bleed Prior to Loading (Ib) E. F. Volume Line @ 0.0 Volume Final After in Bleed (Ib) Weight Loading Load Propellant H. Loading I.
PAGE 571
Amendment 1/22/71 TABLE SERVICE This table will be ning, reference tolerances, and qtmd. Secondary couplecad should nomin_ a when Maxim,-. Nominal 108.0 Trapped Deliverable 225.3 4.5 Oxidizer Trapped Deliverable Secondary Primary 108._ Oxidizer Trapped Deliverable 39.8 70.1 10_.9 2.1 707.8 *2.3 Total Oxidizer Max£mum Trapped 225.2 4.5 Nominal 220.7 Deliverable t0.7 4.5 _.n S_RCS Propellant tl.4 Total Oxidiser tO. 7 4.5 21q .
PAGE 572
Amendment TABLE LM-8 Consumable 3.4-16 Loadin_ LM-8 APS Requirements Propellant Fuel Propellant Trapped Load (Ib) Tanks Inside Nominal Deliverable Tanks 1991.0 APS 3182.3 TBD Propellant TBD The following table should be used to to be off-loaded from a full condition allowable tolerance for the determine to arrive calculated the at amount of propellant the indicated load. off-load is _+0,5 pounds per tank. weigh A. Final B. Propellant C. Nominal D.
PAGE 573
TABLE LM-8 3.4-16 Consumable LM-8 Amendment 1/22/71 (Continued) Loadin_ DPS Requirements Propellant Fuel Propellant Trapped Load _ib) Oxidizer 7072.8 Outside Tanks 60.5 7037.7 Inside Tanks Nominal Deliverable 7Q0 11283.9 31,8 134.7 7,9 1 I149,2 Outage TBD Total DPS Propellant TBD Available TBD The following table should be used to determine the amount off-loaded from a full condition to arrive at the indicated tolerance for AI. Final BI. Propellant CI. Nominal DI.
PAGE 574
Amendment TABLE LM-8 L 3.4-16 - RCS (Continued) Propellant 42 ) Required Ullage Requirement Load Minimum _ (ib) 5 43 ) _ A Fuel 107.7±0.9 System A Oxidizer 208.8±1.9 225.5 237.5 ___SsSyStem B Fuel tem B Oxidizer 107.7±0.9 208.8±1.9 iii.0 225.5 123.0 237.5 FUEL Load Trapped Tanked Outside Tanks Trapped Nominal in Tanks Deliverable LM-8 - 417.6 17.6 400.0 4.2 200.4 8.0 392.0 & I 208.8 209.1 I 107.7128.0 208.8 258.
PAGE 575
Amendment TABLE LOAD APS I. 3.4-17 CALCULATION PROPELLANT Full tank - Item K, Table 3.4-15 (Ib) 12. Density of temperature off-load tables at loading and pressure (ib/ft 3) 13. Propellant volume item 34. 2. (divide density (ib/ft (from Resulting 6. Off-load 7. Propellant (lb) required Propellant load DPS 9. Oxidizer 3300.9 _ _ - - - - 2071.9 3300.9 57.0 70.0 7.9 12.7 2007.0 3218.2 7155.6 11432.4 7155.6 i1432.4 I by Table 3.4-19) 3) 5 8.
PAGE 576
Amendment TABLE LM-8 Propellant 3.4-18 Loadins LM-8 Uncertainties APS PROPELLANT Fuel Vent line Tank Volume Volume ±0.3 ±0.8 ±1.3 ±0.5 ±0.8 ±1.7 ±4.3 Density ±0.7 ±0.5 Measurement ±0.5 ±0.5 Tolerance ±0.0 ±0.0 ±4.4 ±7.7 ±0.2 ±0.3 ±3.4 ±5.6 PSIA) ±1.6 ±2.6 (l.5°F) ±6.1 ±14.8 ±2.4 ±i,6 Measurement ±o,_ ±0,_ Tolerance ±0.5 ±0.5 ±14.2 ±25,4 Measurement Temperature Measured 2Weight lLoading Total (±5 PSIA) Measurement Loading (±l.
PAGE 577
TABLE LM-8 APS (To Be Propellent Completed Amendment 1/22/71 3.4-19 Loading Parameters by KSC at Loading) Fuel 75.0 Loading Pressure Loading Temperature - Fill Loading Temperature - Return Loading Temperature - Tank Number Total of Times Pounds Pounds - PSIA Weigh Measured Fuel Measured Oxidizer Using Using Density Line Used Flow @ 25°C; Density @ [GP0718 F [GP1218 (Flow Weigh Meter Meter Tank (Weigh @ 14.7 4°C; @ PSIA 14.7 Fuel Oxidizer 68.
PAGE 578
TABLE 3.4-19 (Continued) 98 Amendment 1/22/71 LM-8 - DPS Propellant Loading Loading Pressure Loading Temperature - Loading Temperature - Return Loading Temperature - Tank One - Degrees Loading Temperature - Tank Two - Degrees Parameters PSIA Fill Line - ITT 58 FITT258 Degrees Fuel Oxldlzer Fuel Oxidizer 60.8 64.3 67.9 67.0 68.2 67.0 69.0 67.
PAGE 579
MISSION H-3 MASS PROPERTY DATA Amendment 1/22/71 TABLES Table 3.4-20 presents CSM-110/LM-8 (docked) coordinates, as a function of Hybrid SM/SPS burn. mass properties, spacecraft weight Table 3.4-21 presents CSM-IIO/LM-8 (docked) mass properties, coordinates, as a function of spacecraft weight SM/SPS burn. Table 3.4-22 presents the CSM-II0/LM-8 coordinates as a function D.O.I. SM/SPS burn. Table 3.4-23 presents the CSM-IIO as a function of CSM burn.
PAGE 580
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PAGE 581
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PAGE 592
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PAGE 593
Amendment 98 1/22/71 This page intentionally 3.4-113 left blank. SNA-8-D-027(III)P.
PAGE 594
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PAGE 595
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Amendment 96 12/18/70 This page intentionally left blank. 3.4-12.
PAGE 598
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PAGE 601
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PAGE 602
TABLE (To be used CSM Ii0 in conjunction Consumables Weight Change Summary with the CSM sequential mass properties EVENT From To Earth Launch Pre Consumable Trans/Dock Trans/Dock Post Trans/Dock Post Pre Trans/Dock SPS Hybrid post Pre Hybrid SPS Hybrid L.O.I. Post L.O.I. Post SPS Pre L.O.I. Post Pre Hybrid L.O.I. D.O.I. D.O.I. Post D.O.I. Post D.O.I. CSM/LM Separation Separation Pre Circularization Pre Circular- (Pounds) (Pounds) 54.7 -0.5 819.9 40.0 -11.
PAGE 603
TABLE 3.4-7 (To he used CSM ii0 in conjunction Amendment 12/4/70 (CONTINUED) Consumables Weight Change Summary with the CSM sequential mass properties Weight EVENT From To Post Circular- Pre Plane Change SM-Hydrogen ization Pre Plane Post Change Plane Change Post Plane CSM/ASCT Change Docking Docking Pre -2.& 33.8 -21.4 604.9 -226.4 SM-RCS -75.8 869.5 -472.9 SM-SPS -1269.5 12066.4 -28527.3 -4.9 28.9 -26.3 -47.4 -135.2 557.5 734.3 -273.8 -608.
PAGE 604
TABLE LM-8 (To be used in conjunction Consumables with the EVENT Amendment 12/4/70 3.4-8 Change LM sequential Consumable From To Earth Orbit CSM/LM CSM/LM Pre Separation D/S-Oxygen D/S-Water LM-RCS P.D.I. Summary mass properties Table Weight Amount Change Remaining (Pounds) (Pounds) -I.I -13,0 -5.0 D/S-Oxygen Separation D/S-Water LM-RCS . 3.4-2) Total Usage (Pounds) 46.9 237.0 600.6 -I.i -13,0 -5.0 -i.0 45.9 -2.1 -21.3 -55.5 215.7 545.1 -34.3 -60.5 Pre P.D.I.
PAGE 605
**._, C) ! ! i.
PAGE 606
Amendment 81 5/11/7o TABLE 3.4-9 MISSION H CO)_qAND MODULE STOWAGE VOLUME CENTROIDS S/C 109 - 111 A1 3 4 5 6 7 - Not on S/C 110 8 10 - S/C ii0 Only 11 - Not on S/C 110 12 13 1012.0 1016.0 1015.O 1015.O 1017.0 1012.O 1012.0 1011.0 1Oll.0 1013.0 I010.O -22.0 -24.0 - 7.0 9.0 26.0 31.0 22.0 23,0 19.0 - 9.0 -22.0 -26.0 28.0 28.0 28.0 28.0 7.0 -23.0 6.0 7.0 14.0 - 2.0 81 2 3 4 5 6 7 B 1050.0 1039.0 1031.0 1031.0 1031.O 1031.O 1033.0 1024.O -27.0 -38.0 -28.0 -20.0 - B.O 13.0 27.0 -38.0 39.0 37.0 40.
PAGE 607
Amendment 81 5/11170 Table _he not following associated 3.4-9.1 stowage locations have with storage volumes. unique volme L0ckzz0, G&N Signal Cond. Display Keyboard Sleep Restraint Sleep Restraint Food Container Food I_nntainer rec:al _cowage PEA C,_ntainer hatch F_Jrwai_ Panel Assy Amsy - Right Left Container Container Conrah_er, R12 (In-flight Location) tl,,lmet Stnwale and Accessory gag (In-flight Location)L.H. Helmet Stowage and Accessory Bag s (In-flight Location)Ctr.
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N _r I III II ,=_ || P_ Z ,v o O U o ! )= III I ? I t sr 4J i ] A ! o w _ L N _L Z II 0 ,Y _ [ z _J .**,**.
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N eoeeeeeeeeeoeeooeeoeeooooeeeeee _ N Cl 0_ O +i.=. IIIIIIIIIIII • 0_0000000000000000000000__ oooeooooeeooeooeeooeeeeoeeeeeeee ij + :0 ,.,J < • 00000000000000000000000000000000 eleeeeeeeeeeeeoeeeeoeeeeeeeeeeee ,,,0 q[ ..4 Z CO +o _ ZZ Z Z Z *e 7_ -I l-+,.el "q:l _l m°+++++++-+++++++-=+++++ ++ O l-P4 m ++ =, ,.e .i+ + 3 ++_+++ _+m++_++x+,+++ z 5,- Ol:: l.,.) gggggg_gg_z_ggg_g_g_$ggg_ggoooo_ 2 z Z 91 b> 4E k.,- eeeleleeee eeleeeeeeeeleeleeee r -,r- mmm+©mm u.
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r_ li _=_'"'"'"'"" '"''"' oeeeoeeeeeeoleooeeeeoeeeeoeeeooo _ d lttI_I_t_IIIIIIIII_IIIIIII*IBIBI ZZ Z Z Z Z Z i" ' 0 i _ _ lllllllllll|l _1 i_v_lm_l_ ZZZZZZZZZZZZZZZZZZZZZ_Z__Z _ _ *eooeeeeeeeeeeoooeeeeeeeeeeeee.
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IIIIIIIIIII I I I III |1 _0000000000000000000000000000 Ililllllllllll@lllllllllllllt O {3 IIIIIIIIII II I II + t1111 4: ..a 000000000000000_0_00000000000 M{i. 0 v 0 Z o vl kr_; p..._ A t_ • ++++ 9' " r_ z = 2 p_ z w 7. • Ileellleele+lll / I z _. _: z i,.- .d ra, 4, ,,.,,....,,,..+-.:z-+...-_+_:; +. _ <+ _<+.+ r_ 11 IIE E L. E EL E I: 1.
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f_ i Z _ J O _._ I _,. Illllll lr tlllllllllllil Z | N .J J ? ,1( b- Z = = u _ g Q. Z_ZZZZZ_Z_Z g _ uJ e_ 7. .¢ _ZZZE_EZZZE I -e uJ 0_ ,4 • P, _ S Z Z • m uo ).. I -r _ . z Q u_ Z Z _ _ Z G ( Q. m 11 !1 _ 1.: L. L: L L L E E E i: 1_ _ 1.: ': " L- IL.
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c_ I,- U Z M 0 N IIIIIIIIIIIIIIIII o IIIIIIIIIIII I eeooeeeooeoeoeoooooeaeeooeooeeoe I llllllll Ill .= .J 0 N .J & ? • ! r_j t_ o uiJ z 4J I.J Z z • Z ,( iJJ I-- eeeeeeoeeeeeeeeeeeeeeeee.eeeeeee 31: _ _ • X / -....
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li rq ¢_ t I # I I I I I • _®®®_®_ I _ / _ _ A ! I <'!. ,,4 "i I-i I > _0 2 I i o i, l! ILl ILl E L L E It L E i: L E L: 1; 1] E : ' _L. L.
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I A i.-4 t-4 +0000000_0_0000000000 I I I Z ll,_" Ig 0+++++++0 I + I I ++++++ * ,£, I t I U I CNNNNNNN_NNNNNNNNN NNNNNNNNNNNNNNNNNNNNN N N i oeeeleeeeleeeeeeleeee ,.t N .J II Z ¢I,, 3 _J Z N ,,.:, ,+ gD ,q[ _C .IJ Ill Z +l[ Z [-i U. _t' I II. b,Z Z Q w,i E_ o ZZ_ I I kM _ _-_- ,-,.+ ,9[ I=I _I Z O u_J ILl il _ _ 1: E 12 L K 1: E E U 1; E 1.: L, L L.
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P, )+ ! • II N O0000_O000000000_O000_m_OO0000 Illlllllttllllllllllll•llllllll I I I III IIIII I II Iilleeeeeeleteelleeelelleee•ell 000__0@____ i N 1.. "t" lleeOOilleellelllllilllllll*lll N .s0 ,,.+ N m: ._ w B+=..._ : 22:+o_-+oo+-+---+--+-+o,, _P, 0,. P,,l _ _,- < ...... N .&, ,.,.. E Z Z k- .+ I-N il • I_1 Z i.i +.u ,,_ T 1_ 31+ I--. ..... _'.-.+ ,._ < m _ ,,_+ _ _+ • !i lI I_ L: L E k L ._ ._ I.
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e_ ooloeooooooeoeeeoeeoooeoooeoooe ! Ill! Ill! I ! g ÷ u. u. .J )e,i Z uJ N ,( D. ,¢ U. N --I 4[ Z Illllillll IIIIIIIIIIIIIiIiiiIe - ____. _ - __...
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I m ,I I II1| 99299_ ! I | 0 N 99_992 • U I X _0OOO _NOOWI N_NNNN O OO_UU N .= u. N .J _.) 3_ZZZZ ¢L V,. 9 9 [-, (=_ w Q. Z 9[ L_ '1[ *-w I [ Z _J N ..J 2' - _;_ ¢ 000000 uJ t T _, :E _J _._ '_J b..
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0001_1',._,-00000 mllllml I I I I Ill _l_llmlmlml I I I I I _ N A I I I o.oo_._,-ooo oo 000_00000 I M NNNNNNNNNN eeoeeeeleo O' & ? I': | iz ill i 0 Q ,,,, "0 t-i +t Z + Z I-- 0 I,I,i. m _i I Z Lad l.kl 72 +T' ! ,,_I t- _Z • +++'++++ _ii +-i _"" =+, > +:,,,_ - ++ :+= ,_ ++.+ _.>,, ' :+ o + !1 II ],:' :L :1: E :L L L E t.
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Amendment 12/4/70 This page intentionally 3.4-64.14 92 left blank. SNA-8-D-027 (III) I_V 2 t.
PAGE 665
Amendment 88 1015170 TAIL[ ¢OUI_iL|8 i.O_Zl_ 3.4..2O I_UZlJDI_ 14Lnion 8PS Proeouro Fuel (PSZA) oxld;Loer 110t4 . H-3 Prooelllmt :u_re ('_) oxtdJ_ser Tempe Fvql 110*4 AND TOLI[LAll¢[8 70*$ toadout O_n Fuet 70'5 See FLjure Joe Load (Lb) ILiad 2Trapped Tanked Outside Tank8 2Trapped SMcnt2nal InaLde Tanka Deltvelsble Loedtnt rue1 kauir._menC Oxidtaer 15704.0 78.6 15625.4 67.6 15857.8 25092.0 123.7 24968.3 171.5 24796.
PAGE 666
TABLE Command 3.4-10 Module Pressure Water Loading (PSIA) Waste Potable (CONTINUED) and Amendment 1015170 GOX Launch Earth Requirement Wei6ht 88 (ib) Weight Water 6 Water 7 Actual (ib) 18.0 36.0 CM/GOX 900±50 3.7 8Service Loading Module 6.7 Hydrogen and Requirement Oxygen Earth (pounds) Hydrogen Tank Tank 1 2 29.3 29.3 Oxygen Tank Tank Tank 1 2 3 330.1 330.1 330.1 (Entry) Launch (pounds) Weight 27.6 27.6 316.6 316.6 198.
PAGE 667
Amendment 8B i01517o T_LE 8P$ PYaq)el1_t 3.4-II IMd Caleuletlon F_L J 1. Inter item SPS Quantity C - Betcent) 2. Use 718ures 4.1-3 peLXant Load for ' end 4.1-4 shove quantity 3. Ik)liinel propdllent (use tempersture - 4. Cubic S. Calculated demstty 6. Adjustment due 7. loeultiq item S, SPS Oxidizer feet of bedout st density density to (Table to obtain tJtdout, 3.4-12 pro- 2 divided (It_ Table PUGS sere 3.
PAGE 668
I i.I _° i ! A k-4 • II 0 ...,i _i,,_,,=t I O0 I I .ad I 0 II I _ li lliE II q,i IA Ill ql _l ll_i _ M U Q,A U ,_ 'U '_ I i,J I U I U _ U IC M I 0 U • U I i,i U I '! i Ill u _ W U _ _1_ II II ¢., rJ U il ,J N _ U _u u N 0 I M 0 14 lt_i |I|I: I _ ii" q II I _ lIU I_q II ,,..I li5 I II_i iI el II u N i+ U N U ,_ tI tIi tI _!
PAGE 669
00 _O CP .,4 I1, IO 1',41l,O O I I a" II,+ ,',1 g gll _ • n Ih,I ,,,I,q,,4P ,,I.I :l II all qls _C_ AI _ al ql QU b I.._ IL U "l_ ,,_ I0 I e'L I _ _ • t _ II a._ _ ta I am I N il U_ u U a. Ih L" k_ I Q,,,_ I,,,l , _¢ o OU n qJ II U IN al ,tl i.o N 0"_ U,_ U a,,..a..+ _ _1 ;gl _1 e.t,,u,._ 0 U _i:, II U.Ii I a8 k_ ii.u.i I I l_ U I qll _ 11 qll I'U m I,,O III • u _ D_ _ U N UU_ NIL. _11 __1 _ • N I i U M gl +i I "-' 0 II _ O I.
PAGE 670
Amendment 88 10/5/70 TAB;.E 3.4-13 SPS PROPELLANT UNCZETAINTIES ITEM FUEL LOADING UtlCERTAI_TIES Tank Volune Temperature Standpipe Propellant Density Batch Gauss (•2.0"F) Heliht GeuBe (tO.35Z Heesurement Density Loading of GeuBeable) (1) (1) (1) Pressure RSS (lb) OXIDIZE1 (lb) "24 t39 "18 t46 • 6 •10 ".54 "86 "0 "0 "94 t75 " 8 t14 s 130 ill3 L •172 TOTAL RSS Loading Specification (1) Tolerance on Propellent of F118ht Load (2) t16 Tesperature t24 +0.0 -46.
PAGE 671
Amendment 88 1015170 TABLE Com-lnd Module RCS LoadlnB Thto Cable wtll be 'comple:ed Planntn|, reference should tolerances, crepped end 3.4-14 Parameters when loedtnB is be made to Section deliverable end Calculations 8ccoupllshed. For Mieeion h.2 for nominal load, loadtn r_.__L OXIDIZZl Tank......_._B Tank A. Tank B. Liquid C. Tote1 k + B (In 3) £nltlal Prlor Welsht In Bleed co LoedinB (lb) E. Flnal After Weight Loadln8 F. Propellent Load (item then E WetBh Tank) G.
PAGE 672
Amendment 88 1015170 TABLE SERVICZ This table w_11 be nin|, reference tolerances, and q_d Secondary completed should noutnal Total when Total t2.3 Tote1 fuel Fuel SM/tCS Propellent tl.4 fuel t2.3 4.5 Trapped Deliverable D (lb) tO.7 2.1 Trapped Deliverable "2.3 Oxidiser Load Total 8.4 Trapped DellverabXe tO.7 2.t 4.5 )lmtt.momTrapped Mominal Deliverable %,5 Plan- loedin8 Oxidiser Maximum Nominal t2.3 Total KteeLon Secondary fuel Primary fuel Total rum1 2.
PAGE 673
TABLE LM-8 Consu--.ble Amendment 3.4-16 Loadln_ I/4-8 APS Requirements Propellant Fuel Load Propellant Trapped (Ib_ Tanks _ib_ 3218.1 5.9 Tanked 8.3 2000.8 Trapped Inside Nominal Tanks Deliverable 3209.8 I0.i 27.6 1990.7 Outase 3182.2 TBD Total APS Propellant allowable weigh TBD TED The following table should be used to to be off-loaded from a full condition The Oxidizer 2006.
PAGE 674
TABLE LM-8 3.4-16 Consumable Loadin 124-8 Amendment (Continued) DPS E Requirements Propellant Fuel Propellant Trapped Load (Ib) Oxidizer 7072.8 Outside Tanks 11341.9 60.5 7037.7 Inside Nominal Deliverable Tanks 11281.4 14.8 102.7 7022.9 Outage 11178.7 TBD Total DPS Propellant TBD Available TBD The following table should be used to determine the amount off-loaded from a full condition to arrive at the indicated tolerance AI. for Final Propellant C1. Nominal D1.
PAGE 675
Amendment TABLE 3.4-16 LH-8 System System System A Fuel A Oxidizer B Fuel System B Oxidizer - Required Load _Ib) 5 107.7±0.9 208.8±1.9 107.7±0.9 208.8±1.
PAGE 676
TABLE Anmndemnt 10/5/70 3.4-17 B8 LOAD CALCULATION APS 1. PROPELLANT Full tank - Fuel Item K, Table 12. Density of temperature off-load tables and pressure 13. Propellant item 2. volume 3) 341 (ft Measured (lb/ft at (Ib/ft (divide density loading 3) item (from Resulting full 6. Off-load amount 7. Propellant (ib) required 8. Propellant load 9. Full Table tank load 1 by 3.4-19) (lb) (lb) to fill RCS manifolds (lb) PRO_PLLANT tank - It--"em K1 Table 110.
PAGE 677
LM-8 Propellant Loading LM-8 APS Amendment 10/5/70 3.4-18 TABLE Uncertainties FRDPELLANT Fuel Vent llne Tank Volume Volume Pressure Measurement ±4.3 /0.7 ±0,5 Measurement ±0.5 ±0.5 Tolerance ±0.5 ±0.5 ±4.9 _8.2 Loadin 8 Mission Mixture _V, Uncertainty Isp, Variation Vehicle TBD Weight TBD Variation Propellant Usage Uncertainty Loading Uncertainty Due To Total For Mission Propellant Line Tank Volume Pressure Measurement PROPELLANT _3.4 -+5.6 ±1.6 -+2.
PAGE 678
Amendment TABLE LM-8 APS (To Be Propellant Completed 3.
PAGE 679
TABLE 3.
PAGE 680
MISSION Table 3.4-20 H-3 MASS PROPERTY presents CSM-II0/LM-8 (docked) coordinates, as a function of Hybrid SM/SPS DATA Amendment 10/5/70 TABLES mass propertieu, spacecraft weight iu Apollo for the mass properties, spacecraft weight in Apollo for L.O.I. burn. Table 3.4-21 presents CSM-II0/LM-8 (docked) coordinates, as a function of SM/SPS burn. Table 3.4-22 presents the CSM-II0/LM-8 coordinates as a function D.O.I. SM/SPS burn. Table 3.4-23 presents the as a function burn.
PAGE 681
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PAGE 683
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PAGE 684
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PAGE 686
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PAGE 688
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PAGE 689
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PAGE 690
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PAGE 691
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PAGE 692
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PAGE 693
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PAGE 694
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PAGE 695
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PAGE 696
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PAGE 697
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PAGE 698
PAGE 699
Amendment 94 12/10/70 SUPPLEMENTARY General Comments Inertia data DATA to be APPLICABLE applied dispersions Dispersions shall All propellant initial be The (+) or (-) sign item is added to or Table are used as weights following subtracted 3.5-7 and angles for Tables MASS 3.5-1 PROPERTIES through TABLES 3.5-8: +10%. 3o deviation are total values. tanked. the name of an item from the preceding indicates total. that the SPS abort sequence are: Pitch ffi-0.
PAGE 700
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PAGE 701
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PAGE 702
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PAGE 704
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PAGE 705
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PAGE 706
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PAGE 707
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PAGE 708
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PAGE 709
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PAGE 710
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PAGE 711
_aendmen 9110170 Tsble H4th A/tltude To be ac l_os Propertiaj J Later Dace 3.5-13 U 1/ I_ L L L L L L U L 86 3.
PAGE 712
Amendment 9/10/70 3.5-5 Table Pad To be Abort _s Supplled Prop@ztlu at a Later 3.
PAGE 713
Amendment 9/10/70 Table SIVB Sequential To be Mass 3.5-6 Properties Supplied at a (LV Coordinates) Later Date 3.
PAGE 714
Amendment 9/10/70 Table SIVB Sequential To Mass be 3.5-6 Properties Supplied at 3.
PAGE 715
Amendment 9 12/10/70 TABLE CSM 112 (To be used properties Constmables 3.5-7 Weight £n conjunction Table 3.5-2) Change with CSM sequential To Earth Orbit Pre Consumab Trans/Dock Amount Total Change Remaining Usage (Pounds) (Pounds)' (Pounds) le SM-Hydrogen SM-Oxygen CH-Potable H20 CM-Naste Pre Post Trans/Dock Post Trans/Dock Pre Trans/Dock S20 SM-RCS L.O,I. Post L.O.I. Post aM-Hydrogen SM-Oxygen SM-RCS L.O.I. Pre D.O.I. Post D.O.I. CSM/I.M Pre Post L.O.I.
PAGE 716
Amendment 9_ i2/lo/7o TABLE CSM 112 (To be used properties 3.5-7 Consumables (Continued) Weight in conjunction Table 3.5-2) with To Post Pre Circularlzation Change Pre Plane Change 1 Post Plane Change ] Post C::M/ASCT Plaue Change Plane i sequential Amount Total Remaining Usage Consumable _Pounds) _Pounds) (Pound_) SM-Hydrogen SM-Oxygen SM-RCS -13.2 -117.4 -168.4 -1236.8 SM-Hydrogen i Pre 13oc:king T.E.I. Post r.h.l. Pre Post T.E.I.
PAGE 717
Amendment TABLE LM-IO (To be used in conjunction Consumables with the LM Change sequential EVENT Earth To Orbit CSM/LM Pre Separation P.D.I. CSM/LM Pre LM Consumable Separation P.D.I. @ Touchdown D/S-Oxygen -5.0 D/S-Oxygen D/S-Water LM-RCS -3.0 -12.0 -51.0 88.0 348.0 550.5 -8.0 -32.0 -56.0 D/S-Oxygen -i.0 87.0 -9.0 -3.0 -i00.0 345.0 450.5 -35.0 -156.0 LM-RCS LM @ Lift-Off A/S in LM-APS AIS @ A/S @ T.P.I.
PAGE 718
xO t'J _C_ _,.
PAGE 719
Amendment 86 9110170 3.5-9 TABLE MISSION J-i COMMAND MODULE STOWAGE VOLUME CENTROIDS 112 sic AREA X Y Z AI 2 3 4 5 1012.0 1010.0 1016.0 1015.0 1015.0 -22.0 -23.0 -24.0 -7.0 9.0 -26.0 8.0 28.0 28.0 28.0 6 7 8 9 1017.0 i010.0 1012.0 1013.0 26.0 23.0 22.0 0.0 28.0 8.0 -23.0 16.0 B1 1050.0 -27.0 39.0 2 3 4 5 6 8 1039.0 1031.0 1031.0 I031.0 1031.0 1024.0 -38.0 -28.0 -20.0 -8.0 13.0 -38.0 37.0 40.0 40.0 39.0 39.0 37.0 L2 3 1059.0 1048.0 -44.0 -47.0 14.0 12.
PAGE 720
Amendment86 911o17o Table 3.5-9.1 The not followln alsociated I stOWale locations have with stowale volumes. NO .CLXTURE Container Forward Hatch Container Container. RI2 (In-flilht Location) Helmet Stowage and Accessory Bags (In-flight Location)L.H. Helmet Stowage and Accessory Bass (In-fllght Location)Cir. Helmet Stowage and Accessory Bags (In-flight Location) _ R.H. Teavorary Stowage Bag - L.H. (In-fllght Location) CO 2 Absorbers 6.8 6.8 Re_u.inder lb. lb. CO2 X 1069.0 1060.0 1018.0 1018.
PAGE 721
86 Amendment 9/10/70 TABLE MISSION J-i LUNAR MODULE 3.5-9.2 STOWAGE VOLUME CENTROIDS LM-IO X AIB AIC AIC AID AlE AIF AIG AIH AIK AlL A2 A3 A4 A5 AI0 All All AI2 AI3 FLA. FIB FIC FID FIE F1F FIG F5 F6 F6B F6C F7A F7B F7C F7D F7E F7F F7H F7J FTK ICG Assy PLSS LIOH Cart ECS LIOH Cart 262.8 240.5 240.5 270.3 265.9 257.4 257.5 265.9 281.0 273.7 260.0 280.0 244.1 224.3 250.0 263.6 261.2 272.0 300.0 244.5 235.5 242.5 242.8 237.9 235.5 228.0 286.0 270.3 270.3 270.3 238.0 238.0 238.0 238.0 238.0 238.
PAGE 722
Amendment86 9110170 TABLE MISSION J-i LUNAR 3.5-9.2 MODULE (Continued) STOWAGE VOLUME CENTROIDS LM-10 AREA F7L F7N F7P F8 F9 FIO X Y 236.0 238.0 238.0 221.0 219.7 221.0 36.0 38.0 38.0 18.0 0 -18.0 48.0 53.1 53.4 51.0 44.7 51.
PAGE 723
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PAGE 727
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PAGE 729
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PAGE 733
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PAGE 734
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PAGE 735
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~~PAGE 739~~
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~~PAGE 741~~
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~~PAGE 744~~
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~~PAGE 748~~
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~~PAGE 769~~
TABLE CONSUMABLES LOADING 3.5-10 REQUIREMENTS MISSION AND Amendment 86 9110170 TOLERANCES J-i SPS PROPELLANT Pressure Fuel (PSIA) Oxidizer 110±4 70+5 110±4 Readout (%) Oxidizer quantity Fuel Temperature (°F) Fuel Oxidizer 70.+_5 See See Figure 4.1-3 SPS Propellant Load Loading Fuel 15704.0 78.6 15625.4 67.6 15557.
~~PAGE 770~~
TABLE 3.5-10 Command (Continued) Module Pressure Water Amendment 9/10/70 and GOX Earth Loading Requirement Weight (ib) (PSIA) 900±50 3.7 8Service Loading Module 6.7 Hydrogen Req. Per (pounds) Tank Launch Weight 18.0 36.0 Waste Water6 Potable Water 7 CM/GOX 86 Actual (ib) (Entry) and Oxygen Earth Launch Weight Per Tank (ib) Hydrogen Tank Tank Tank 1 2 3 29.3 29.3 29.3 27.6 27.6 27.6 Oxygen Tank Tank Tank 1 2 3 330.1 330.1 330.1 316.6 316.6 316.
~~PAGE 771~~
Amendment TABLE SPS 3.5-11 PROPELLANT LOAD CALCULATIONS Fuel i. Enter SPS Item 2. Use Figures for Nominal (use 4.1-3 above propellant temperature feet 5. Calculated density 6. Adjustment due 7. Resulting 5, of - Cubic SPS Oxldlter and at Ii0 PSIA (Table Oxidizer 3.5-12 to SPS FLItL Item to obtain density at density graph from PUGS loading (Item Table zero propellant 6) propellant readout. propellant actual less 4.1-4 quantity 4.
~~PAGE 772~~
,I.I I! _0 <_ _8 W _ _". ''_lai i,b -! .!- 8. 0 A I O0 I I , U I I_ _._. I I I _ m_ m U _ I gI _ _ U - |;IU II U AL U O_ r_ 6 _ N Ne,_ U _ Ill U L_ II_ ,...++ -._t z _Tt N k III 0 III I,+ 0 I U U U U I U I U i I i q_ I,ii II I _ q'5 "_ _J q,4 fdd 4 I I n_ OIU I, I 0 1 .I II ( U U II,. _I, e, I_ L I U ,C L.. U I.I £ II.I , o_,,,_"4 7, +I" :'+""" • ,"q _ t'_ q dO _ _ _ _ ++|+: .oooo ._.
~~PAGE 773~~
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~~PAGE 774~~
Amendment 86 9110170 TABLE SPS 3.5-13 PItOPILL_ I/tICZlTJLINTIES ITEM LOADING Tank FUXL UtiCEitSAIttTIES Volume Tanparacure Standpipe Gauss Helaht Propellant Density Batch ('2.0oF) Gouje Meaeurtment Density hoadlnB of (tO.35X Oauaeable) (i) (I) Pressure (I) (lb) t24 t39 "18 it6 • 6 "10 "54 • 86 t 0 t 0 t9h .
~~PAGE 775~~
.amendment 86 9/10/70 TABLE 3.5-14 Com_tnd This table Plennln 8. tolerances, Module BC$ Losdln 8 Perameter8 will be 'completed when loadtn8 is reference should be made to SectLon trepped and deliverable propellantJ. and Calculationa accouplLshed. For HLsston 4.2 for nominal load, loedLn8 le_...._L Tank A. Tank B. Liquid C. Total A + B (in 3 ) Initial Prior to Ee Final After Wellht Loadtnj _e Propellan¢ Load (item than E Weilh Tank) De Volume @ 0.0 Line Volume Propellant H.
~~PAGE 776~~
Amendment 9110170 86 TABLE 3.5-15 SEIVlC Ir MODULE ICS This table v%11 be conpleted vhen hieS, reference should be made to tolerances, end nominal deliverable LOADING SUI_TZON loadln8 Ls accamplLshed. Section &.2, for holies1 propellants. Quad A (lb) Total Secondary fuel Prinary Fuel Total fuel J4aximum Trapped Nominal Deliverable t0.7 2.1 Trapped Deliverable Oxidizer Maximum Nominal *2.3 Trapped Deliverable Total 4. _ Primary _Totel t0.7 2.
~~PAGE 777~~
TABLE LM-10 CONSUMABLE LM-IO Amendment 3.5-16 LOADING APS REQUIRE_NTS PROPELLANT Fuel (lb) Propellant Load Trapped 2008.6 Outside Tanks Inside Nominal 27.6 1992.6 3189.9 Deliverable Outage APS TBD Propellant allowable tolerance Final B. Propellant C. Nominal D. Correction tank pressure overfill Fuel calculated the at off-load amount of propellant the indicated load. is ±0.5 pounds per Correction Fuel - 2F. Measured 2G.
~~PAGE 778~~
Amendment TABLE LM-IO 3.5-16 CONSUMABLE LM-IO LOADING DPS REQUIRE_NTS PROPELLANT Fuel Propellant Trapped Load Tanks Inside Nominal Deliverable Tanks 11997.5 40.9 19.2 7491.8 11956.6 TBD Propellant TBD The following table should be used to determine off-loaded from a full condition to arrive at the amount the indicated able ±0.5 tolerance for AI. Final BI. Propellant Cl. Nominal DI. Correction tank overfill Measured 2 G1.
~~PAGE 779~~
Amendment 3.5-16 TABLE LM-10 System System System A Oxidizer A Fuel B System B Oxidizer - Required Load (Ib) 5 107.7±0.9 208.8±1.9 RCS (Continued) PROPELLANT 152.5 267.0 Tanks Tanked in Tanks Deliverable LM-IO tank - APS - RCS - RCS DPS - DPS (Ambient)(6) - Ascent - Descent Nitrogen #i (6) tank #2 (6) tank #I (6) tank #2 (SHe) (6) - tank Water - Ascent COX Descent 401.4 4.2 200.9 8.0 393.4 ('F_ 70 70 (ib) 6.6 6.6 3050 3050 70 70 1.05 1.
~~PAGE 780~~
86 Amendment 9110170 TAllLI 3.5-17 LOAD CAL_TXOM Fuel 1. Full tank - Item 12. Denslty of temperature 13. Propellant Item 2. 14. Measured denslty (lb/fc 3) K, Table off-load tables at end preosuta (1hilt volume (f_3) (dlvtde (from 5. Rasulttns full 6. Off-load amount 7. Propellant (lb) requlred 8. Propellant lomd 9. pPS PROPELLANT Full tank - Item tank Table load to K1 Table voluDe 112. Measured density (lb/ft 3) Propellant RCS au.
~~PAGE 781~~
94 Amendment TABLE 124-10 PROPELLANT LM-10 12/lO/7O 3.5-18 LOADING APS UNCERTAINTIES PROPELLANT Fuel Vent Line Volume Tank Volume Pressure Measurement Temperature Measured Measurement ILoadlng Total Tolerance Loading Uncertainty Mission Mixture _V, (+-1.5°F) Density 2Welght APS (+-5 PSIA) Measurement Vent Line Tank Volume +-0.8 ±1.7 +-4.3 ±0.7 +-0.5 ±0.5 +-0.5 ±0.5 ±0.5 +-4.8 z8.2 TBD Due To Total Uncertainty For Mission TBD Measurement (±5 PSIA) ±2.
~~PAGE 782~~
Amendment 9110170 86 TABLE 3.5-19 LN-IO APS Propellant (To Be Completed LomUn8 Peremetors by DC at I_adins) Fue___I Losdin8 Pressure Losdin8 Tsmpersture - Fill Losdin8 Temperature - Return Losdlng Temperature - Tank Number Total of Pounds - PSIA Tt_ts Pounds Welih Neasured Fuel Density Heasured Oxidizer - Flow Density - Desroos Fuel Oxidlzmr _tTT 59 Fuel r il.
~~PAGE 783~~
Amendment 91101;'0 TABLK 3.5-19 Lid-10 DPS Propellant Loadin8 Pressure 86 (Continued) Loedln8 Parm_terz - PSIA 1 Line J_ 58 Fuel Fl_258.0xldlzer Loedi_ Te_erature - Ftll - _|rans Lo_in8 Temperature - _curn Loadin8 Temperature - Te_ _e - _8rmes F_3718 1_4218 - Te_ _o - F 1_3719 Fuel 1C,_4219 Oxidizer IT 59 r.
~~PAGE 784~~
Amendment 87 9115170 MISSION J-i MASS PROPERTY DATA TABLES Table 3.5-20 presents the coordinates, SM/SPS burn. CSM-112/LM-lO(docked) ms as 8 function of spacecraft Table 3.5-21 presents the CSM-112/LM-10 coordinates, as I functio_ D.O.I. SM/SPS burn. Table 3,5-22 presence the as a function burn. CSM-112 mama properties, of CSM weight for the in Apollo Circularization Table 3.5-23 presents the as a function burn.
~~PAGE 785~~
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~~PAGE 786~~
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~~PAGE 788~~
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~~PAGE 789~~
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~~PAGE 792~~
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~~PAGE 798~~
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4.0 The arate data presented REFERENCE in this centers-of-gravity sumables CSM CSM on-board consumables consumable property 4.1 4.2 mass loading data are for SPS Density PROPERTIES enable the each in must the following Mass Equations Consumables and obtain spacecraft and the the sepcon- CM performance. current Section 3.0. on-board The mass sections: Properties, Trapped Graphs, SPS Mass to and Properties, Propellants, Loading and Windows.
~~PAGE 806~~
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~~PAGE 807~~
r TABLE Table tanks. The 4.1-1 presents following units Height apply to Propellant Unstretched Tank Volume Stretched Moment of propellant PSIA, and oxidizer Inertia The YAand and are density ZA as Center the - Moment tank was of 90.
~~PAGE 808~~
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~~PAGE 822~~
_OOOQeOO0 > w Z v r_ o I 0 I 0o I < Z r_ _eoooeeoo _ _000o0o0o Oz _eoeeeooo 'o _J :_ Z 4..I i_ 0 ,el 7'- ,--4 o I j., L,U _ • • • o • e o o X C) _ooeooooo >_NNNNNNN _D Z 00000000 _0000000_ _OOOeOOOO £..
~~PAGE 823~~
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~~PAGE 824~~
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~~PAGE 825~~
~~_oeeoeeooeoeeeoeeoeoeeooooeeooeooeooee I-.4 ¢M 0 I I co I ,< Z OZ ,_eoooeoeeeeeeooooeoooeoeoooeeeeoooeo° o _._ z I J I lg J ,--t c_ o z _Z !1 ILl _ L: 1: 1..~~
~~PAGE 826~~
i-i h-i r_ o I I 00 I OZ "o °_ Z o u I-, v o CXl I n_ 0 _ _ c_oo oc o _ _ _ oo _ooo_ocoooooooo_o_oo_oooooooooOoooo _ oo oo 0oo oo c, o o _ o_ _ o oo o o c Oo _ooeooeeooeoOoeeeooeeeoeooeooeooeeeooo 11 11 i_ _ L 1-" L L I: L: IJ E L_ 1_ ii E : ' L L
~~PAGE 827~~
0_ __0_ Z i-,I 0,-I i-,,g o I I oo I _ooeoeeo _XO000000 "0 Z o,3 OZ .H 4J o L_ ,-4 I ,-4 Z Im I ,--4 ,-4 .1 _ooooeeo _oeeooeo o _ o _ oo c c_ _ _ooooooe ILl 1_ IJ [ 1; E IL: L E E ]J E L: l_ LT E L, L L _.
~~PAGE 828~~
TABLE TRAPPED SPS 4.1-2 MASS PROPERTIES Weight Pounds SERVICE - Trapped Outside Engine - XA YA ZA Tanks Fuel 29.6 846.9 6.6 0.4 - Oxidizer 47.4 843.0 -7.1 1.6 - Fuel 29.5 832.0 -48.0 -25.0 - Oxidizer 44.7 832.0 48.0 25.0 Line 19.5 829.0 -27.0 -24.0 31.6 829.0 27.0 24.0 202.3 836.0 4.5 3.7 Feedline Transfer - Fuel - Oxidizer Total Outside 2 Trapped in Tanks Tanks Retention Reservoir - Fuel 61.4 - Oxidizer Vapor - 97.5 6.
~~PAGE 829~~
TABLE4. i-3 SPSPropellant Density Equations (S/C 107 and Subsequent) Equations for calculating SPSfuel and oxidizer densities are given below. In order to calculate the density for fuel or oxidizer of a given load on a particular mission using the measureddensity furnished by KSC the following steps are necessary: A. Use the density appropriate at the will usually oxidizer. B. Use the density usually C. Subtract the KSC equation given be 14.
~~PAGE 830~~
1.00160 !_l',!'_i:_i,: !lilil _t!"? btl_- "T1-rt 1.00140 rttl-t-" "-tft OF LIVE =.ool2o tl'_ .I ........ ,. ,.** ::4,: PROPELLANTS [:;: ttl_ !='L: rt_ * !iii t_::' i ; ; ! * t _ t F._._ !ii!i i_i!i i!!!: :;:,. TN tttt' o l-(J 1.00100 t: ,. _!-t- -t LtV--' ii!i iiii::?isi iiiiii 'z_'_, " :t'A "-_ I'- _r : "r +'' ¢.) _- _i;t ! _.!:: .: 1.00060 i" !_; ::3__-_;_.-:._ I1: n o '_t: .-- L_ I * 1`._t ' !tt i it:t t* "÷'_ el -J- 1.00080 i'.
~~PAGE 831~~
1.00180 TI = 90"DE'G I='_ "1"2=70 DEG F T3 = 50 DEG F 1,00160 PROPERTIES OF LIVE PROPELLANTS TETROXIDE _ _ _. _ _ ii_ 1.00140 .+ 1.00120 :i (Z: 0 Itj _ ' ' i_7_+_ _ ! f4 . . tt t f!.t+lff-r 1.001 O0 >.. I-- _i :4443i4-; = q4: _ FJ477:_ .J +-++_.+ _-_+_ m I.iJ (Z: n .-_,44r .4.+-4-+-H.-_ 1.00080 i-4q4-14.k_- =E :_ 0 o 1.00060 _ _4Hi- _2 _t_tltt_'! 1.00040 ;-@ .... 1.00020 iil ¸ • ,+1 ÷°.. _ i _u_ -.-_ +-_4 H. l-t-t tll-i I.
~~PAGE 832~~
SERVICE MODULE SPS FUEL LOADING WINDOW FOR SM 107 AND SUBSEQUENT FUEL FOR ULLAGE LOADING PRESSURE OF 110±4 PSIA t- ;+__+__..+-. _' ,1- _ 1:!; ;1;;4 -;?{? ,, ZI- _ +_h _r:q ',_::;; _' .... +:t +-+++4-+_+_....... T_7_ ;4 He .-+: 10l _" :::: :i__xL'71_+"-_::_x _;tm:...... _:101 I .[ _.... ] 7:T; ii7{ .... -:rr ffr!_ : Lll0[ ....I ,+_%;_ ' 5723._ _})! -#-_-++ _l ' "2 _" _!:, ?tl_r m- tl If" !! x
~~PAGE 833~~
SERVICE MODULE SPS OXIDIZER LOADING WINDOW FOR SM 107 AND SUBSEQUENT OXIDIZER FOR if" ......... ULLAGE LOADING PRESSURE OF ii0_4 PSIA :;T; ..... ::: "if: :ii' .......+" cr]: !i!K ' !Mt -_- + )TT:_)F_ . . ?,+ __:t";;_: i+i! :_i,+4 _T: 11:: _i:ii :!? _ _41Ol.OH ?;fl '::! =_'2 r,
~~PAGE 834~~
~~U It/ l.~~
~~PAGE 835~~
~~I I ........... ' ! T- _ _ "" '1 "" V" •- TT r-, |_r M 0 •7 • r_ L'-'_ -,, L _,.~~
~~PAGE 836~~
~~PAGE 837~~
Amendment ii0 5/21/71 SNA-8-D-027(II) REV 2 Volume Subsystem II LM Data Performance Book Data - Crew/Equipment food per CREW / EQU I PMENT 4.2.2 Food Requirement Each man requires Sensory PLSS PLSS cc a (NASA DATA Condensate The of Condensate Transfer condensate. PLSS shall be PLSS to 135°F.
~~PAGE 838~~
SNA-8-D-027(II) REV Amendment 2 128 7/27/71 Volume Subsystem 4.'2.8 Data 4o9 Acquisition See Table Quad III tions Camera 3.10-2 and Stowase Temperature configurations (DAC) temperatures of pallet the its those Temperature of predictions individual Reference: tank for 135°F has a condensate has leading to psia 3.75 worst case 120°F, Figure Contract Prlmarv No. No.
~~PAGE 839~~
TABLE 4.2-1 (CONTINUED) (_oetor hklisht Pounde kll, wr-n,,Le Prtuuury fuel Iocndory Fu_l hidieer - Prioery I_Jol kclmdory o • Quid roe1 Oztdtnr C - PrL,_ry Voel |ocondory Foe L Oxidiser _ad U - Primary Fuel Second,try Fuel OxLdiler hltvereble Priury l_el Fuel OzLdLter Deliverable lroel Ozidt set" Oeltvereble 68.5t0.8 '964.| ZA (6) 4.2-3 O.O -68.5 $9'6"0'8 905.1 -9.0 !220.9t3.4 92b.9 8.0 68.5t0.8 91_.8 64.5 026.S 39.6'0.8 08S.1 68,0 -Ll,O 220.9*3.4 S2b.
~~PAGE 840~~
Amendment106 6/22/71 TABLE4.2-1 (CONTINUED) CSM112 ANDSUBSEQUENT MISCELLA_'EOUS CONSUMABLES CENTER CSMMISCELLANEOUS CONSUMABLESWEIGHT CM/RCS - HELIUM CMIECS Oxygen- Entry Potable Water (3) WasteWater (4) SM/RCS - Helium SM/SPS Helium- StorageBottles - Tanks(5) SM/Nitrogen OF G_VITY INCHES POUNDS XA YA ZA 1.0 ,1022.6 -3.1 25.8 (7) 1031.1 -26.9 -34.2 (7) (7) 1022.6 1022.6 -63.5 -19.7 -16.4 62.5 6.0 983.9 0.0 0.0 87.6 954.7 0.0 0.0 5.4 976.0 2.7 8.9 1.3 874.0 0.0 0.0 29.
~~PAGE 841~~
Amendment 86 9/10/70 Table CSM 112 and 4.2-1 Subsequent (Continued) Miscellaneous Consumables WEIGHT CENTER POUNDS CSM MISCELLANEOUS CM/RCS OF CONSUMABLES XA - HELIUM GRAVITY INCHES I ZA 25.8 1.0 1022.6 (7) 1031.1 -26.9 -34.2 (7) (7) 1022.6 -63.5 -16.4 1022.6 -19.7 62.5 6.0 983.9 0.0 0.0 87.6 954.7 0.0 0.0 5.4 976.0 2.7 8.9 1.3 874.0 0.0 0.0 29.3 974.6 37.0 29.3 859.4 -40.7 -46.0 41.2 29.3 892.9 -40.7 41.2 330.1 330.1 920.8 -20.9 26.9 330.
~~PAGE 842~~
~~Amendment 86 9/10/70 This page intentionally 4.2-4.~~
~~PAGE 843~~
~~Amendment 66 9/12/69 TABLE CSM This table - CONSUMABLE contains tolerances, temperatures 4.2-1 and/or and the LOADS AND consumable UNCERTAINTIES loads, uncertainties pressures.~~
~~PAGE 844~~
Amendment 66 9/12/69 Tab]t SERVICE MODULE - Nominal 4.2-1(Contlnued) (l)Center Load Weilht of Gravity Inches Rcs(2) Quad A - Loaded Prlmar_y - Fuel Secondary-Fuel Oxidizer Ouad B - Loaded Pri_uary - Fuel Secondary-Fuel Oxidizer Quad C - Loaded - Primary Fuel Secondary-Fuel Oxidizer Quad D - Loaded Primary - Fuel Secondary-Fuel Oxidizer Loaded Primary - Fuel Secondary-Fuel Oxidizer Loaded - Fuel -Oxidizer TOTAL LOADED Max. XA 964.8 y_ 8.0 ZA -68.5 40.3±0.8 985.
~~PAGE 845~~
k O_ C3 | I r_ O ....... I °.o°°°o.o,.,,°o,,°°.o°.,°°o°, I oo I t_ °.°,o°.,o.°,lO.,o°oo°o°°,.o°.o°,oo°. ,..°o.°,°°.,,°°.oo°o ..... oo. e_ 0 c 0 <.J u c qU _3 oh I o°...,.°,°°o,,o°°,o°°o,,o..°o,o.°.._ IX X I,. q- ,IJ oo°.oo.,.o.o,...°,,,.,...°..o.o. t',,4 • Z ..... .... ,.o,o.°°.o°,.,.°.0,°,,o,_,'°'° _ 5 ,..,°,,°.o,°.,,°°..,.o.,. _0 U U g _ ...... • .... NNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNN .................. _. ..........
~~PAGE 846~~
~~11 !1 E E L.~~
~~PAGE 847~~
~~I II I I IN 'llillli't-illlll/ptilli/li- lillill'lil'liilltilllilltiltllvtitm'llltmd 1!_ _ I"-_ T lr_ 1 __ _ _ I"" 'lr" l'w T_ 1_"I1 ! _- ,-- ,:- • • v- .~~
~~PAGE 848~~
~~PAGE 849~~
4.3 CM/RCS AND SM/RCS 4.3. i CM/RCS Table LOAD 4.3-1 is CALCULATION the CM/RCS by KSC for each mission. fuel and oxidizer loading F and 4.3.2 TABLES load AND LOADING calculation Figures windows 4.3-4 to be WINDOWS table to be completed and 4.3-5 are the CM/RCS used by KSC for Mission subsequent. SM/RCS Table 4.3-2 is the SM/RCS load summary table to be completed by KSC for each mission. Tables 4.3-3 through 4.
~~PAGE 850~~
TABLE 4.3-1 COMMAND MODULE RCS LOADING REQUIREMENTS, PARAMETERS AND CALCULATIONS Load Parameters and Fuel Tank A. Tank Volume AI. Liquid A2. Total B. Initial @ Line A + Final A1 Propellant B Tank A Tank B (in 3) (in 3) in in Bleed Bleed Load less Loading F. Specification G. Total Item Unit Prior Unit After by Item Weigh C Tank; (ib) Temperature (°F) Load @ 70 CM/RCS Propellant D above or Item Z5°F (Ib) Load from P below (ib) ±0.
~~PAGE 851~~
TABLE SERVICE MODULE RCS 4.3-2 PROPELLANT LOAD SUMMATION Actual: QUAD A (Pounds) Secondary Primary Fuel Fuel Total Total Oxidizer +2.3 Total Oxidizer +2.3 Total Oxidizer +2.3 Total Oxidizer +2.3 +0.7 QUAD B (Pounds) Secondary Primary Fuel Fuel +0.7 Total QUAD C (Pounds) Secondary Primary Fuel Fuel Total +0.7 QUA/) D (Pounds) Secondary Primary Fuel Fuel +0.7 Total Total Fuel SM/RCS Propellant Loaded (ib) Oxidizer +1.4 4.3-3 +4.
~~PAGE 852~~
TABLE SERVICE MODULE RCS LOADING 4.3-3 PARAMETERS AND CALCULATIONS Fuel Loading B. Tank BI. Liquid C. Tank D. E. to Final After *F. (in3/PSI) Bleed Bleed A. Tank Volume AI. Liquid B. Tank Stretch C. Tank Volume CI. Liquid D. Tank Unit Unit Load (ib) (Item D Nominal and 0.088 Oxidizer Tanks Volume of S/C Line (in 3) I. Volume of S/C Line (in 3) H. Bladder J. GSE I. Stabilized (PSIG) Pressure Secondary F.
~~PAGE 853~~
TABLE SERVICE T. Fuel MODULE Density equation (ib/in3); (i) Temperature PV below @ and LOADING AND CALCULATIONS - QUAD A T = for Combined Secondary Fuel Tanks Volume of GHE-GSE Line (in 3) V. Volume of S/C Line (in 3) W. GSE X. Bladder Y. Stabilized GHE Pressure (PSIG) Pressure (PSIG) Equilibrium Pressure Z. PARAMETERS solve where U. Line (Continued) P above Parameters Primary RCS 4.
~~PAGE 854~~
TABLE4.3-4 SERVICE MODULE RCSLOADING P_TERS ANDCALCULATIONS - QUAD B Fuel Oxidizer Secondary A. Loading B. Tank BI. Liquid C. Tank D. Initial Temperature Volume After of (in3/PSl) Bleed Loading Weight of A. Tank Volume AI. Liquid B. Tank Unit C. Tank Volume CI. Liquid D. Tank Resulting Item G. Load (ib) (Item D Nominal and (ib) Line (in 3) F. Volume of S/C Line (in 3) (in 3) G. GSE I. Volume of S/C Line (in 3) H. Bladder J. GSE I.
~~PAGE 855~~
TABLE SERVICE T. Fuel MODULE Density equation (ib/in3); (i) below Temperature PV @ P and T _qD CALCULATIONS - QUAD B = for Combined Second____ary Fue] Tanks Volume of GHE-GSE Line (in 3) V. Volume of S/C Line (in 3) W. GSE X. Bladder Y. Stabilized GHE Pressure (PSIG) Pressure (PSIG) Equilibrium Pressure Z. PARAMETERS solve where U. Line (Continued) LOADING above Parameters Primarv 4.
~~PAGE 856~~
TABLE4.3-5 SERVICE MODULE RCSLOADING PARA_TERS ANDCALCULATIONS - QUAD C Fuel Oxidizer Secondary A. Loading B. Tank BI. Liquid C. Tank D. Temperature Volume Initial Final of After (in3/PSl) Bleed Loading Weight Bleed A. Tank Volume AI. Liquid B. Tank Stretch C. Tank Volume CI. Liquid D. Tank Unit Unit Resulting Item Load (ib) (Item D Nominal ±5 ° F (Ib) (in 3) F. Volume of S/C Line (in 3) I. Volume of S/C Line (in 3) H. Bladder J. GSE I.
~~PAGE 857~~
TALBE4.3-5 (Continued) SERVICE MODULE RCSLOADING PARA>_TERS ANDCALCULATIONS - QUAD C T. Fuel Density (Ib/in3); solve equation (i) below where T = Temperature@P above PV Parameters for Combined Primar_ and Secondary, Fuel Tanks U. Volume of GHE-GSE Line (in 3) V. Volume of S/C Line (in 3) W. GSE X. Bladder Y. Stabilized Line Pressure (PSIG) Pressure (PSIG) Equilibrium Pressure Z. GHE (PSIG) Specification PV Temperature P Value above @ (ib) Maximum Minimum ZI.
~~PAGE 858~~
TABLE4.3- 6 SERVICE MODULE RCS LOADING PARAMETERS AND CALCULATIONS Fuel Loading B. Tank BI. Liquid C. Tank D. Initial Final After *F. of Bleed Unit Load (ib) AI. Liquid B. Tank Tank CI. Liquid D. Tank (Item Nominal ±5 ° F D PV less (Ib) Line (in 3) F. Volume of S/C Line (in 3) G. GSE Line (in 3) H. Bladder J. GSE I. Stabilized M. Primary Oo Equilibrium Q. Tank R. Liquid S.
~~PAGE 859~~
TABLE SERVICE T. Fuel MODULE Density equation FV RCS (Ib/in3); (i) Temperature below and LOADING AND CALCULATIONS - QUAD D T - for Combined Secondary Fuel Tanks Volume of GHE-GSE Line (in 3) V. Volume of S/C Line (in 3) W. GSE X. Bladder Y. Stabilized GHE Pressure (PSIG) Pressure (PSIG) Equilibrium Pressure Z. PARAMETERS solve where U. Line (Continued) @ P above Parameters Primary 4.
~~PAGE 860~~
240 230 220 cO Z v ,-I 210 .< 200 190 180 170 160 65 67 69 TEMPERATURE Figure (_F) CSM 104 AND SUBSEQUENT SECONDARY FUEL TANK ULLAGE VOLUME RANGE 4.3-1 4.3-12 !1 1_ E L E L L L SNA-8-D-O27(III)REV 1: E E 2 i_..
~~PAGE 861~~
!!! iiii _'_ t:: ii_i :I_! 73 ',_ _ iiii _. 72 .... _ +_I "" ._71,5 iii t_-_: .._I! '.il " 14..'41 .I:; 7i •, H;H,;:r li. ili 7O :::1....... !i_ Z ::: O ;',_ _._::_ _;'I ..... I I ;11 ,I Hi- : .. :_.i..,_i :.:;'._.*:I _'!:H'! !ii !!_ $i "" :i: 69 68.7 :i. •,,..,, .,: iii 121 'r_l _._'_ _ -4. ,-1 "T!.... _:'I 68 ::: ii:j !iij ii :_i: ; 67 .... :: ! .... .... Lli iii_':,'-_-::_ ...... 'T-i 7I "':1 ::_ :; i!!: :Z! 66 :_ :L!-:!] :ii, i'T ::T :_ ........
~~PAGE 862~~
_u+t: rttt _L !_4".', i]! 231 22). 230 J. II f-% C_ Z 229 4_ 0 4_ 228 n L_ _N 227 )--4 226 t,q )-4 ).-4 225 0 ::U 224 _'3 223 :2.. 222 F::" 7-i 221 :_ 64 65 66 67 68 OXIDIZER Figure 4.3-3 69 70 71 TEMPERATURE [l L; E l_ 73 74 75 76 (°F) SM RCS COMBINED PRIMARY-SECONDARY OXIDIZER TANK LOAD WINDOW 4.
~~PAGE 863~~
HH_4 :::::: !i!!}!!!_ [::[::i:: 12:Li;_i H__t_ t_ _ +.++++-1-4 150 E ii_iiii 4 Z 140 I*It_*I o U I:_ F I,-4 v i !!'!! 130 :l fl T- _P ,-.1 ,-.1 ::I 120 :_ :Aiii _i ,-I llO _"_ 4-14d-; +l_- 4: 100 4: _!'ttT!t _÷ 90 :;_ 80 --- ? i *l_'?t_r _J 7o FUEL LOAD: [!"!+ ,_4/,r_ !!T j- 'r 6o _ 4 MINIMUM _7_TF L_If 5o !! _t _t 40 ?Ttti_rl-t :_ 64 i!!!!!ii 66 68 70 FUEL TEMPERATURE Figure 4.
~~PAGE 864~~
360 350 340 I-% mD 330 Z "" -320 310 m_ 300 c_ 290 o 280 270 260 250 240 230 64 66 68 70 OXIDIZER Figure 4.3-5 CSM 104 OXIDIZER 72 TEMPERATURE 74 76 (OF) AND SUBSEQUENT CM RCS TANK ULLAGE VS TEMPERATURE 4.
~~PAGE 865~~
Amendment 105 6118171 TABLE COMMAND MODULE 4.3-7 112 RCS TANK VOLUMES Internal System Serial Gross Tank Equipment Number Volume I In 3 Volume_ Net in 3 Tank Volume_ 1 Fuel 100311537100 1490.003 15.3 1474.703 Oxidizer 100311545114 1804.744 17.8 1786.944 Fuel 100311537101 1486.982 15.3 1471.682 Oxidizer 100311545103 1808.798 17.8 1790.998 System in 3 2 4.
~~PAGE 866~~
Amendment 105 6/18/71 TABLE SERVICE MODULE 4.3-8 112 RCS TANK VOLUMES Internal S._s t_m Quad Serial Gross Tank Number Volume, Net Equipment in 3 Volume_ in 3 in 3 A Primary 100311521168 2862.193 19.1 2843.093 100311545116 1802.557 17.8 1784.757 Fuel_ Fuel 100311511167 2266.943 17.4 2249.543 100311537099 1476.143 15.3 1460.843 Oxidizer 100311521333 2861.264 19.1 2842.164 100311545110 !802.556 17.8 1784.756 100311511326 2259.267 17.4 2241.
~~PAGE 867~~
Amendment 105 6/18/71 TABLE COMMAND MODULE 4.3-9 113 RCS TANK VOLUMES Internal Serial Gross Tank Number Volume_ in 3 Equipment Volume_ Net in 3 Tank Volume_ in 3 Sys tern i Fuel 100311537115 1488.714 15.3 1473.414 Oxidizer 100311545115 1801.865 17.8 1784.065 Fuel 100311537116 1484.806 15.3 1469.506 Oxidizer 100311545118 1808.795 17.8 1790.995 System 2 4.
~~PAGE 868~~
Amendment 105 6/18/71 TABLE4.3-10 SERVICE MODULE 113 RCSTANKVOLUMES Internal System Quad Secondary Primary Secondary Secondary Primary Secondary Tank in 3 Equipment Volume_ Net in 3 Tank Volume 3 t in Oxidizer Oxidizer Fuel Fuel 100311521170 2857.098 19.1 2837.998 100311545125 1802.556 17.8 1784.756 100311511168 2267.924 17.4 2250.524 100311537129 1482.432 15.3 1467.132 100311521171 2862.193 19.1 2843.093 100311545101 1815.725 17.8 1797.925 100311511170 2272.138 17.
~~PAGE 869~~
Amendment 105 6/18/71 TABLE COMMAND MODULE 4.3-11 114 RCS TANK VOLUMES Internal Serial Number S_vstem System Gross Volume_ Tank in3 Equipment Net Vo!ume Volume, 100311537122 1503.864 15.3 1488.564 Oxidizer 100311545134 1801.085 17.8 1783.285 Fuel 100311537114 1461.808 15.3 1446.508 Oxidizer 100311545111 1799.807 17.8 1782.007 2 4.3-21 _ _ In 3 i Fuel System U I in 3 Tank _ L L L_ L L U SNA-8-D-027(III)REV U d U 3 L J,.
~~PAGE 870~~
Amendment 105 6/18/71 TABLE SERVICE MODULE 4.3-12 114 RCS TANK VOLUMES Internal S_.ystem Quad Secondary Primary Secondary Secondary Primary Secondary Number Volume_ in 3 Net Equipment Volume_ in 3 Tank Volume_ in 3 Oxidizer Oxidizer Fuel Fuel 100311521172 2862.193 19.1 2843.093 100311545104 1821.604 17.8 1803.804 100311511173 2266.191 17.4 2248.791 100311537128 1491.598 15.3 1476.298 Oxidizer Oxidizer 100311521330 2862.193 19.1 2843.093 100311545119 1800.
~~PAGE 871~~
~~m ql 0 _,. / ]_ -r_ o .L I,_ _ I_ I[ I,r I_' _.~~
~~PAGE 872~~
~~PAGE 873~~
~~I TO BE SUPPLIED. CM ABLATOR DATA L 4.~~
~~PAGE 874~~
~~PAGE 875~~
~~II II I II _y' 0 0 t.[ ILl !1 _ I.: L: E L v__ lrT _I.[ ll_. I[ I[ !( i _. 1[ I_ Z.. .L .I,,,. X,.,, .L ,L I. 1,_ L Z_ h L A. L L L{ I,,.~~
~~PAGE 876~~
~~PAGE 877~~
~~I II I II tl i,_,k_ A A AA dekd,,km di L,,,'t G_" L'-'_ _-,] C"_ L'-'_ .t[ I[ I( l{ I[ K 1. ILl lil i,[ I.: 1: ll: E L E Ii L,.~~
~~PAGE 878~~
~~PAGE 879~~
Amendment 86_ 9/lO/7O 5.0 The data separate craft in centers-of cons_ble LM section data data data are Descent and for enable affect must each be the the to provided to for those the in following sections: Fuel Properties 5 through LM 9 Table 5.1-2 LM 5 throuEh LM 9 Oxidizer Table 5.1-3 LM i0 and Subsequent DPS Fuel Table 5.1-4 LM i0 and Subsequent DPS Oxidizer 5.3 LM RCS 5.4 LM Descent Tank Tank Mass Mass Tank 8 Descent LM Table 5.
~~PAGE 880~~
~~t !1 !1 LI L E L L I: L ]_ L: L: Li Ii E i L.~~
~~PAGE 881~~
LUNAR MODULE DESCENT PROPELLANT MASS PROPERTIES NOTE: I. 2. 3. 4. Mass Properties are given for liquid in individual tanks. Moments of Inertia are about center of gravity of propellant in individual tanks, coordinates of which are given. Centers of Gravity in Y and Z directions are given at top of each page. The number of tanks of a particular kind is indicated by the last number on the first line of each page. 5.l-I II L L L L ]2 U I_ E SNA-8-D-027 l; II iI (I II) lz L, ILEV 2 ..
~~PAGE 882~~
\ rj ...................... j_ L_ oO oO ('-,4 C_ I _CD _un t cc I < z u3 .r.., °r- i, ,_" o,J LF) _'_ c;_ k_) II • ¢- II u_ .r- 1"-04 II tl ¢_ __ Ln k--'i _1 .l"- O0 I..ul i,. n_" II E _- U_I .._ • rO c-" ,,_- n."_ _C) II -I O 1,- ! ° I--I-- C I ,--0'9 °O0 I 0000000000000000000000000 eeee • I'-- _4 __0__ ILl -.1 ..-I ,'_UJ U.- CL O0 I .t- .--I •r-- (_ _. Itl _"- Ul It II II _'- "1- 0 "I1'I_.i.a II ¢" "P" U'I r.i_ E (i..) ILl lI 1; (.
~~PAGE 883~~
III c_j ......... > ______ OOOOOOOOO P_ 00 cO c_j ol 4.J Er-- I I o{3 I < Z _)-.. _° 1 ,-4 U9 ......... __E____o_o_o C"3 I pOOOOOOOOOOOOOOOOOOOOO OOOO Jg_CEMd_dJ_MMC_MdCdJj_C O" (J9 4-) i, I u'1 v I 0r-K. ..... _ ......... __ _NNNNNNNNNN_NNNNNNNN__ II U ILl [ L: h' L_ L L" L: h" E _ _ l.T 1E L _.
~~PAGE 884~~
:> *ee***e***e*eee*.eo*o*e* 000000000000000000000000 oO CO 0 I I CO i ,--I Z °_ °_0 _______0_ _ .................. _o_ II _ ",-- 1 +'_ f"_ Q# _ O II 0___0____0__ -I LLI 7" " I--- 0 m,_ __ I 0 000000000000000000000000 eee ! ,--- eooooe ee _--I L.I- --J 1-- e.r-- O0 I •r.- •_" _ 4-- I ¢_ \ II IJ _ v I _" 0 • ._ II _4D aJm -1- 0 II • 0.,- 4-_ II 0.} _ _"_ ._-- -_ i_j N -i _ U !1 I_ i_ L: E E L .___ E I_ ............
~~PAGE 885~~
o0 QO • il _J _U O I_r-- C_ P_ 0 I c_ I (Z) I .F-- Z 0e._"C _, • I,D II II =1 oP _-)'10 V_ l.IJ ol-- _-_ I._ "I .._ • _l t'- q_- n_" f,l-- _N 0 4. op LEE II 0 _U Od "-! u_ =1 O L_ I 0 L) V) L_ d.. un I.l.. -J __ °p. I eF.
~~PAGE 886~~
o4 > O0 O0 o4 0 I c_ I oO I < .,,,e,..,,o°°,.o,..o,*.,° ,-4 e.r- 1 1 ii ___00_00___0_ ooo***..****..**o.o**o... I_. o °e- ° q_" C_c_I d IX'; II II E _l II O0 U3 ::_ .r- ____0____ II = .r..- E .p _4-- eN b- 0 S.-E E U Ud ,% CD ***.***...****.°°°o°oo°°o "_ II _J tO I 0 L. X X I/) O4 bO _D r- 0000000000000000000000000 6d_M_MMC6Nd_dMJMMC6dd£_ m °e-. i CO (M . "1 O_ P'- _J °,'- Oh _ ¢/) _ u5 II • _r" ¢/1 UI {_IN ::l N i_- N-I V1 I ..o.o°.o..***.....
~~PAGE 887~~
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~~PAGE 888~~
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~~PAGE 889~~
¢0 O0 1 1 1 op 0 I oo I Z oeeeeoeeeoeeaeeeeeoeeoe*e °_ r"o_ N • f-- • L.I_ 0 OCX.I d_4 II II II t-- C_cn_ i..-i :::3.,--L¢ - ,.,o Z _- _ II '_',.C_ • C_ _I NO _ ° °'r. _ _'_. _,, Z 0 0 I _.- I x^ 0 0000000000000000000000000 e,oeoeoeoeooeeoDeeeee,ele 0 W N X 0 0" ¢._ °,I _:+; CO I •,- _ co P') co • •"_ .,=" O_ _ I c_ p=. II OOOO000OO0000OO0000000000 0000000000000000000000000 eoeeeeeeeeeeeoleoeeleeemo O00OO00000000000000OOOO00 II -I- (_ L II I _.1 _N +.
~~PAGE 890~~
~~Amendment 88 lo1517o This page intentionally left blank 5.~~
~~PAGE 891~~
~~Amendment 10/5/70 This page intentionally 5 .~~
~~PAGE 892~~
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~~PAGE 893~~
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~~PAGE 894~~
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~~PAGE 895~~
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~~PAGE 896~~
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~~PAGE 897~~
CO CM ¢i,i _o i--i r_ (,,q E3 A Z (/) e- 0 • _- _ "--;'tM uJ Z i.-i I--Z 0 v 6") i,i Fry i,i _ °_ r,o "_ ._ _ f,,,,, i,..,,_ E O ¢) nO 0 1 NO II 1 ',-,i _ II 1,- X 0 Q: • m e',,-" _ S P_ I k A Z 0" 4-) I, m N _nN •.._ _.__ v -.J ILl !/ ]J e- _ :L E L L E E lJ l: i_ |; I_ l_ i, IG , L L.
~~PAGE 898~~
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~~PAGE 899~~
e,) co 4-1 i= U.J hop,, 1.--, v E'_.. 000000000 ("4 O I ! ¢0 I .::f Z • C • ,.- Lt,,.% ::=, _=1 rj ..=,. o r..j . ._r'CO .1,I'_ CD IX_ ,-" • O r'..- (M i._9 II II (_ K. •"[ {a _ o_ f" m I.--W- -_'0_ _ l/1 L.I.I I,') I:: r-.. O_D 0 o vl.i. ! ¢_1 • I_ II (_ _..._ • "_ I ,"," "_O O(11 NO 040 4-_ _OOOOOO ul -.,i 1 "'-C,L (..._ I/1 u_ II ILl I n.." C_ N "_ X C' '7 d_dM_d_2_ &,,') ,.--. I--" Z 1.1.1 C:Y i,i If) r_ A (D" c¢) e- _" •" 4.-_ 4-I LII N I:r_N ::I _.
~~PAGE 900~~
~~I/ !] L IC L 1; L L E 1Z la Y L h IZ b L L~~
~~PAGE 901~~
~~III ':" • " • " "' _: I"_" I" at- atr- qlF" t "_ _;,.> z ,,-.) Ii 11 _ L L E k L t: I_ 1,'. E M li L. ,L.~~
~~PAGE 902~~
~~PAGE 903~~
Amendment 9/10/70 TABLE APS TANKED FUEL 5.2-1 MASS The following mass properties are range of tanked fuel quantity: X 86 PROPERTIES to be used over the entire - 228.0 inches - -71.3 inches - 0.0 inches - 0 slug-feet 2 - 0 slug-feet 2 - 0 slug-feet 2 - 0 slug-feet 2 - 0 slug-feet 2 - 0 slug-feet 2 cg Y cg Z cg I xx I YY I Zz I xy I xz I yz 5.2-1 tl lI E E L E IL L St_-8-D--027(ZZZ)REV I." L_ 12 IL L.
~~PAGE 904~~
Amendment 86 9/10/70 TABLE APS TANKED The following mass of tanked oxidizer X 5.2-2 OXIDIZER properties quantity: MASS are to PROPERTIES be used over E E L entire " 228.0 inches Ycg " 44.5 inches Zcg - 0.0 inches Ixx " 0 slug-feet 2 lyy " 0 slug-feet 2 I zz " 0 slug-feet 2 Ixy " 0 slug-feet 2 I xz " 0 slug-feet 2 ly z - 0 slug-feet 2 cg 5.
~~PAGE 905~~
LM ASCENT FUEL MASS PROPERTIES-70°F-I Y-CG = -71.3 (CONST) Z-CG = 0.0 RADIUS= 24.700 CYLINDRICAL DENSITY= 56.330 LBS/CU.FT. WEIGHT \ \ 1566.5 1556.6 1546.6 1536.6 1526.6 1516.7 1506,7 1496.7 1486.7 1476,7 1466,8 1456.8 1446.8 1436.8 1426.9 1416.9 1406.9 1396.9 1386.9 1377.0 1367.0 1357.0 1347.0 1337,1 1327.1 1317.1 1307.1 1297.1 1287.2 1277,2 1267,2 1257.2 1247.2 1237.3 1227.3 1217.3 1207.3 1197.4 1187.4 1177.4 1167.4 1157,4 1147.5 X-CG 223.4 223,3 223,3 223.2 223.1 223,0 222.9 222.8 222.7 222.7 222.
~~PAGE 906~~
LM ASCENT FUEL MASS PROPERTIES-70°F-I Y-CG = -71,3 (CONST) Z-CG = 0o0 RADIUS= 24.700 CYLINDRICAL DENSITY = 56.330 LBS/CU.FT. WEIGHT X-CG I137 1127 1117 1107 1097 I087 1077 1067 1057 I047 1037 1027 1017 1007 997 987 977 967 957 947 937 928 918 908 898 888 878 868 858 848 838 828 818 8O8 798 788 778 768 758 748 738 728 718 219.7 219.6 219.5 219.4 219.4 219.3 219.2 219.1 219.0 218.9 218,8 218.7 218.6 218.5 218.5 218.4 218.3 218.2 218,1 218,0 217.9 217.8 217.7 217.6 217,5 217.4 217.4 217.3 217.2 217.
~~PAGE 907~~
LM ASCENT FUEL MASS PROPERTIES-70°F-I TANK Y-CG = -7].3 (CONST) Z-CG : 0.0 (CONST) RADIUS= 24.700 CYLINDRICAL DENSITY= 56.330 LBS/CU.FT. WEIGHT X-CG 708.4 698.5 688.5 678.5 668.5 658.5 648 6 638 6 628 6 618 6 608 7 598 7 588 7 5787 568.7 558.8 548.8 538.8 528.8 518.9 508.9 498.9 488.9 478.9 469,0 459,0 449,0 439.0 429.1 419.1 409.1 399,1 389.1 479.2 369.2 359,2 349.2 339.3 329,3 319.3 309.3 299.3 289.4 215.7 215.6 215.5 215.4 215.3 215.2 215.1 215.0 214.9 214.8 214.7 214.6 214.5 214.4 214.3 214.2 214.
~~PAGE 908~~
LMASCENTFUELMASSPROPERTIES-70°F-I TANK Y-CG= -71.3 (CONST) Z-CG = 0.0 (CONST) RADIUS= 24.700 CYLINDRICAL DENSITY= 56.330 LBS/CU.FT. WEIGHT X-CG 279.4 269.4 259.4 249.4 239.5 229.5 219.5 209.5 199.6 189.6 179.6 169.6 159.6 149.7 139.7 129.7 I19.7 I09.8 99.8 89.8 79.8 69.8 59.9 49.9 39.9 29.9 20.0 lO.O SECTION = -0.0 WEIGHT= IXX(S-FT.SQ) 210.7 210.6 210.5 210.3 21 O. 2 210.0 209.8 209.7 209.5 209.4 209.2 209.0 208.8 208.7 208.5 208.3 208.1 207.9 207.6 207.4 207.2 206.9 206.6 206.3 206.0 205.6 205.2 204.
~~PAGE 909~~
LM ASCENT OXIDIZER Y-CG = +44.5 MASS PROPERTIES-70°F-I (CONST) Z-CG = 0,0 RADIUS= 24.700 CYLINDRICAL DENSITY= 90.050 LBS/CU.FT. (ULLAGE/VOL.OF WEIGHT 3172.9 3157,0 3141.2 3125.3 3109.4 3093.6 3077,7 3061.8 3046.0 3030.1 3014.3 2998.4 2982.6 2966.7 2950.8 2934.9 2919,1 2903.2 2887.3 2871.5 2855.6 2839.7 2823.9 2808.0 2792.2 2776.3 2760,4 2744.6 2728.7 2712.8 2697.0 2681.1 2665.2 2649.4 2633.5 2617.6 2601.8 2589.9 2570.0 2554.2 2538,3 2522,5 2506.6 LIQUID))x]O0= X-CG 227.2 227.1 227.0 226,9 226.8 226.
~~PAGE 910~~
LM ASCENT OXIDIZERMASSPROPERTIES-70°F -l TANK Y-CG = +44.5 (CONST) Z-CG = 0.0 (CONST) RADIUS = 24.700 CYLINDRICAL DENSITY= 90.050 LBS/CU.FT. WEIGHT X-CG 2490.7 2474.9 2459.0 2443.1 2427.3 2411.4 2395.5 2379.7 2363.8 2347.9 2332.1 2316.2 2300.4 2284.5 2268.6 2252.8 2236.9 2221.0 2205.2 2189.3 2173.4 2157.6 2141.7 2125.8 2110.O 2094.1 2078.2 2062.4 2046.5 2030.7 2014.8 1998.9 1983.1 1967.2 1951.3 1935.5 1919.6 1903.7 1887.9 1872.0 1856.1 1840.3 1824.4 223.4 223.3 223.2 223.1 223.0 222.9 222.8 222.8 222.
~~PAGE 911~~
LM ASCENT OXIDIZER MASS PROPERTIES-70°F-I Y-CG = +44.5 (CONST) Z-CG = 0.0 (CONST) TANK RADIUS= 24.700 CYLINDRICAL DENSITY= 90.050 LBS/CU.FT. WEI GHT= 3172.9 WEIGHT 1808,6 1792.7 1776,8 1761.0 1745.1 1729.2 1713.4 1697.5 1681.6 1665.8 1649.9 1634.0 1618.2 1602,3 1586.4 1570.6 1554.7 1538.9 1523.0 1507.1 1491.3 1475,4 1459.5 1443,7 1427,8 1411.9 1396.1 1380.2 1364.3 1348,5 1332.6 1316.8 1300.9 1285.0 1269,2 1253.3 1237,4 1221,6 1205.7 1189.8 1174.0 1158.1 1142.2 X-CG 219.7 219.6 219.5 219.4 219.3 219.
~~PAGE 912~~
LM ASCENT OXIDIZER Y-CG = +44.5 MASS PROPERTIES-70°F-I (CONST) TANK Z-CG = 0.0 (CONST) RADIUS= 24.700 CYLINDRICAL DENSITY= 90.050 LBS/CU.FT. WEIGHT X-CG I126.4 lllO.5 I094.7 I078.8 I062.9 I047.1 I031.2 I015.3 999.5 983.6 967.7 951.9 936.0 920.I 904.3 888.4 872.5 856.7 840.8 825.0 809.1 793.2 777 4 761 5 745 6 729 8 713 9 698 0 682.2 666.3 650.4 634.6 618.7 602.9 587.0 571.I 555.3 539.4 523.5 507.7 491.8 475.9 460.I 215 7 215 6 215 5 215 4 2]5 3 215 2 215 ] 215 0 214.9 214.8 214.7 2]4.6 214.4 214.
~~PAGE 913~~
LM ASCENT OXIDIZER MASS PROPERTIES-70°F-I Y-CG = +44.5 (CONST) Z-CG = 0.0 (CONST) RADIUS= 24.700 CYLINDRICAL DENSITY= 90.050 LBS/CU.FT. WEIGHT X-CG 444.2 428.3 412.5 396.6 380.7 364.9 349.0 333.2 317.3 301.4 285.6 269.7 253.8 238.0 222.1 206.2 190.4 174.5 156.6 142.8 126.9 lll.l 95.2 79.3 63.5 47.6 31.7 15.9 210.7 210.6 210.4 210.3 210.1 210.0 209.8 209.7 209.5 209.3 209.2 209.0 208.8 208.6 208.4 208.3 208.0 207.8 207.6 207.4 207.1 206.9 206.6 206.3 206.0 205.6 205.2 204.6 SECTION= TANK -0.
~~PAGE 914~~
~~ILl !1 ]5. L: L L L: L: ]_ E if L |; E E I I, L.~~
~~PAGE 915~~
~~I L:. .,..~~
~~PAGE 916~~
~~PAGE 917~~
LUNAR MODULE MASS RCS PROPELLANT PROPERTIES NOTE: I. 2. 3. 4. Mass Properties are given for liquid in individual tanks. Moments of Inertia are about center of gravity of propellant in individual tanks, coordinates of which are given. Centers of Gravity in Y and Z directions are given at top of each page. The number of tanks of a particular kind is indicated by the last number on the first line of each page. 5.
~~PAGE 918~~
LM RCS FUEL MASS PROPERTIES-70°F-2 Y-CG = + OR - 44.6 (CONST) Z-CG = + OR - RADIUS= 6.250 CYLINDRICAL DENSITY: 56.330 LBS/CU.FT. (ULLAGE/(VOL.OF TANKS SECITON= 18.650. LIQUID))xIO0= WEIGHT X-CG 103.7 103.2 102.7 102.1 101.6 I01.I 100.6 I00.I 99.6 99.0 98.5 98.0 97.5 97.0 96.4 95.9 95.4 94.9 94.4 93.8 93.3 92.8 92.3 91.8 91.3 90.7 90.2 89.7 89.2 88.7 88.1 87.6 87.1 86.6 86.1 85.6 85.0 84.5 84.0 83.5 83.0 82.4 81.9 279.3 279.2 279.2 279.1 279.0 279.0 278.9 278.8 278.8 278.7 278.7 278.6 278.5 278.
~~PAGE 919~~
LM RCS FUEL MASS PROPERTIES-70°F-2 TANKS Y-CG = + OR - 44.6 (CONST) Z-CG = + OR - 14.5 RADIUS= 6.250 CYLINDRICAL DENSITY: 56.330 LBS/CU.FT. WEIGHT 81.4 80.9 80.4 79.8 79.3 78.8 78.3 77.8 77.3 76.7 76.2 75.7 75.2 74.7 74.1 73.6 73.1 72.6 72.1 71.6 71.0 70.5 70.0 69.5 69.0 68.4 67.9 67.4 66.9 66.4 65.8 65.3 64.8 64.3 63.8 63.3 62.7 62.2 61.7 61.2 60.7 60.1 59.6 11 U I_ t; X-CG 276.5 276.4 276.4 276.3 276.2 276.2 276.1 276.0 276.0 275.9 275.9 275.8 275.7 275.7 275.6 275.5 275.5 275.4 275.3 275.3 275.2 275.
~~PAGE 920~~
LM RCS FUEL MASS PROPERTIES-70°F-2 TANKS Y-CG = + OR - 44.6 (CONST) Z-CG = + OR - 14.5 RADIUS= 6.250 CYLINDRICAL SECTION= DENSITY= 56.330 LBS/CU.FT. WEIGHT X-CG 59.1 58.6 58.1 57.6 57.0 56.5 56.0 55.5 55.0 54.4 53.9 53.4 52.9 52.4 51.8 51.3 50.8 50.3 49.8 49.3 48.7 48.2 47.7 47.2 46.7 46.1 45.6 45.1 44.6 44.1 43.6 43.0 42.5 42.0 41.5 41.0 40.4 39.9 39.4 38.9 38.4 37.9 37.3 273.7 273.6 273.6 273.5 273.4 273.4 273.3 273.2 273.2 273.1 273.0 273.0 272.9 272.8 272.8 272.7 272.6 272.6 272.5 272.5 272.4 272.
~~PAGE 921~~
LM RCS FUEL MASS PROPERTIES-70°F-2 TANKS Y-CG = + OR - 44.6 "(CONST) Z-CG = + OR - 14.5 RADIUS= 6.250 CYLINDRICAL DENSITY= 56.330 LBS/CU.FT. WEIGHT SECTION= 18.560. X-CG 36.8 36.3 35.8 35.3 34.7 34.2 33.7 33.2 32.7 32.1 31.6 31 .I 30.6 30.1 29.6 29.0 28.5 28.0 27.5 27.0 26.4 25.9 25.4 24.9 24.4 23.9 23.3 22.8 22.3 21.8 21.3 20.7 20.2 19.7 19.2 18.7 18.1 17.6 17.1 16.6 16.1 15.6 15.0 WEIGHT= 103.7 IXX(S-FT.SQ) 270.9 270.8 270.7 270.7 270.6 270.5 270.5 270.4 270.3 270.3 270.2 270.1 270.1 270.0 269.
~~PAGE 922~~
LM RCS FUEL MASS PROPERTIES-70°F-2 TANKS Y-CG = + OR - 44.6 (CONST) Z-CG = + OR - 14.5 RADIUS= 6.250 CYLINDRICAL DENSITY= 56.330 LBS/CU.FT. WEIGHT X-CG 14.5 14,0 13.5 13.0 12.4 11.9 11.4 10.9 I0.4 9.9 9.3 8.8 8.3 78 7.3 6.7 6.2 5,7 5.2 4.7 4.1 3.6 3.1 2.6 2.1 1.6 l.t] 0.5 267.9 267.8 267.7 267.7 267.6 267,5 267.4 267.3 267.3 267.2 267.1 267.0 266.7 266.8 266.7 266.6 266.5 266.4 266.3 266.2 266.1 266.0 265._ 265.7 265.5 265.4 265.2 264.9 SECTION = 18.650. WEIGHT= 103.7 IXX(S-FT.SQ) O.O C.O 0.0 0.0 0.
~~PAGE 923~~
LM RCS OXIDIZER MASS PROPERTIES,70°F-2 TANKS Y-CG = + OR - 44.6 (CONST) Z-CG = - OR + 14.5 RADIUS = 6.250 CYLINDRICAL DENSITY= 90.050 LBS/CU.FT. (ULLAGE/(VOL.OF LIQUID))xlO0= WEIGHT X-CG 203.4 202.4 201.4 200.3 199.3 198.3 197.3 196.3 195.3 194.2 193.2 192.2 191.2 190.2 189.2 188.1 187.1 186.1 185.1 184.1 183.1 182.0 181.0 180.0 179.0 178.0 177.0 175.9 174.9 173.9 172.9 171.9 170.9 169.8 168.8 167.8 166.8 165.8 164.8 163.7 162.7 161.7 160.7 275.7 275.6 275.5 275.4 275.3 275.3 275.2 275.1 275.0 274.
~~PAGE 924~~
LM RCS OXIDIZER Y-CG = + OR - RADIUS: DENSITY: 6.250 90.050 MASS PROPERTIES-70°F-2 44.6 (CONST) CYLINDRICAL Z-CG = - SECTION: TANKS OR + 25.260. 14.5 WEIGHT: 203.4 LBS/CU.FT. IXX (S-FT. SQ) IYY or WEIGHT X-CG 159.7 158.7 157.6 156.6 155.6 154.6 272.2 272.1 272.1 272.0 271.9 271.8 0.0 0.0 0.0 0.0 0.0 0.0 0.6 0.6 0.6 0.6 0.5 0.5 153.6 152.5 151.5 150.5 149.5 271.7 271.7 271.6 271.5 271.4 0.0 0.0 0.0 0.0 0.0 0.5 0.5 0.5 0.5 0.5 148.5 147.5 271.3 271.3 0.0 0.0 0.5 0.4 146.4 145.
~~PAGE 925~~
LM RCS OXIDIZER Y-CG = + OR - RADIUS = DENSITY= 6.250 90.050 MASS PROPERTIES-70°F-2 44.6 (CONST) CYLINDRICAL Z-CG TANKS = - SECTION: OR + 25.260. 14.5 WEIGHT = 203.4 LBS/CU.FT. WEIGHT X-CG IXX(S-FT.SQ) 115.9 114.9 113.9 112.9 111.9 110.9 109.8 108.8 268.8 268.7 268.6 268.5 268.5 268.4 268.3 268.2 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0o0 0. z O. 2 0.i 0.i 0.i 0.1 0.1 0.1 107.8 106.8 105.8 104.8 103.7 102.7 101.7 i00.7 99.7 268.1 268.1 268.0 267.9 267.8 267,7 267.7 267,6 267.5 0.0 0.0 0.0 0.
~~PAGE 926~~
LM RCS OXIDIZER Y-CG = + OR - RADIUS: DENSITY= MASS PROPERTIES-70°F-2 44.6 (CONST) 6.250 CYLINDRICAL 90.050 LBS/CU.FT. Z_CG = SECTION: TANKS OR + 14.5 25.260. IXX(S-FT.SQ) WEIGHT= 203.4 IYY or WEIGHT X-CG 72.2 71.2 265.3 265.3 0.0 0.0 0.0 0.0 70.2 69.2 68.1 67.1 66.1 65.1 64.1 63.1 62.0 61.0 60.0 59.0 58.0 57.0 55.9 54.9 53.9 52.9 51.9 50.8 49.8 48.8 47.8 46.8 45.8 265.2 265.1 265.0 264.9 264.8 264.8 264.7 264.6 264.5 264,4 264,4 264.3 264.2 264.1 264.0 264.0 263.9 263.8 263.7 263,6 263.
~~PAGE 927~~
LM RCS OXIDIZER MASS Y-CG = + OR - 44.6 RADIUS= DENSITY= PROPERTIES-70"F-2 (CONST) 6.250 CYLINDRICAL 90.050 LBS/CU.FT. TANKS Z-CG : - OR + 14.5 SECTION= 25.260. IXX(S-FT.SQ) WEIGHT= 203.4 IYY or WEIGHT X-CG 28.5 261.8 0.0 0.0 27.5 26.4 25.4 24.4 23.4 22.4 21.4 261.7 261.6 261.5 261.4 261.3 261.2 261.1 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 20.3 19.3 261.0 260.9 0.0 0.0 0.0 0.0 18.3 17.3 16.3 15.3 14.2 13.2 12.2 11.2 i0.2 260.8 260.7 260.6 260.5 260.4 260.3 260.
~~PAGE 928~~
~~U !1 i.I I.~~
~~PAGE 929~~
~~_ I.,/I t" t_ Z I--1 .11 11[- L L L -I] If _I] .II . 1[ II I[ I_ i .~~
~~PAGE 930~~
~~PAGE 931~~
Amendment 9/10/70 86 LUNAR MODULE DESCENT WATER MASS PROPERTIES NOTE : I. 2. 3. 4. Mass Properties are given for liquid in individual tanks. Moments of Inertia are about center of gravity of water in individual tanks, coordinates of which are given. Centers of Gravity in Y and Z directions are given at top of each page. The number of tanks of a particular kind is indicated by the last number on the first line of each page. 5.4-I 11 11 I.
~~PAGE 932~~
Amendment 9/10/70 TABLE 5,4-1 I 86 LM-8 DESCENT WATER MASS PROPERTIES-1 TANK Y-CG - -43,2 (CONST) Z-CG - -43.2 (CONST) RADIUS= 14.200 CYLINDRICAL SECTION= O.O WEIGHT= 323.8 DENSITY_ 62.400 LBS/CU.FT. (ULLAGE/VOL.OF LIQUID))xIO0: 33.757 WEIGHT X-CG IXX(S-FT.SQ) 323.8 322.2 320.6 _8.9 317.3 315.7 314.1 312.5 310.8 309.2 307.6 306.0 304.4 302.8 301.I 299.5 297.9 296.3 294.7 293.0 291.4 289.6 288.7 286.6 284.9 283.3 281.7 280.I 278.5 276.8 275.2 273.6 272.0 270.4 268.8 267.1 265.5 263.9 262.3 260.7 259.
~~PAGE 933~~
Amendment: 9/10/70 TABLE 5.4-I 86 (Continued) LM-8 DESCENT WATER MASS PROPERTIES-I TANK Y-CG--43.2 (CONST) Z-CG = -43.2 (CONST) RADIUS= ]4.200 CYLINDRICAL SECTION = O,O WEIGHT= 323.8 DENSITY= 62.400 LBS/CU,FT. WEIGHT X;CG 254.2 252.6 250.9 249.3 247.7 246.1 244.5 242.8 241.2 239.6 238.0 236.4 234.8 233.1 231.5 229.9 228.3 226.7 225.0 223.4 221.8 220.2 2]8.6 216.9 215.3 213.7 212.] 210.5 208.9 207.2 205.6 204.0 202.4 200.8 199.I 197.5 195.9 ]94.3 192.7 191.0 189.4 187.8 186.2 ]64.2 ]64.] 164. ] 164.
~~PAGE 934~~
86 Amendment TABLE5.4-I (Continued) 9110170 LM-8 DESCENT WATER MASSPROPERTIES-I TANK Y-CG= -43.2 (CONST)Z-CG- -43.2 (CONST) RADIUS= 14.200 CYLINDRICAL SECTION= 0.0 WEIGHT= 323.8 DENSITY= 62.400 LBS/CU.FT. WEIGHT X-CG 184.6 182.9 181.3 179.7 178.1 ]76.5 174.9 173.2 171.6 170.0 168.4 166.8 165.1 163.5 161.9 160.3 158.7 157.0 155.4 153.8 152.2 150.6 148.9 147.3 145.7 144.1 142.5 140.9 139.2 137.6 136.0 134.4 132.8 131.1 129.5 ]27.9 126.3 124.7 123.0 121.4 119.8 118.2 I16.6 IXX(S-FT. SQ) 162.5 162.
~~PAGE 935~~
Amendment TABLE 5.4-I 86 9/10170 (Continued) I LM-8 DESCENT WATER MASS PROPERTIES-I TANK Y-CG : -43.2 (CONST) Z-CG : -43.2 (CONST) RADIUS= 14.200 CYLINDRICAL SECTION: 0.0 DERSITY= 62.400 LBS/CU.FT. WEIGHT .X-CG I14.9 I13.3 Ill.7 llO.l I08.5 I06.9 I05.2 I03.6 102.0 I00.4 98.8 97.1 95.5 93.9 92.3 90.9 89.0 87.4 85.8 84.2 82.6 80.9 79.3 77.7 76.1 74 5 72 9 71 2 69 6 68 0 66 4 64 8 63 1 61 5 59 9 58 3 56 7 55 0 53 4 51.8 50.2 48.6 47.0 160.6 160.5 160.5 160.4 160.4 160.3 160.3 160.2 160.2 160.1 160.
~~PAGE 936~~
Amendment TABLE 5.4-! (Continued) 86 9/10/70 LM-8 DESCENT WATER MASS PROPERTIES-I TANK. Y-CG = -43.2 (CONST) Z-CG = -43.2 (CONST) RADIUS: 14.200 CYLINDRICAL SECTION = 0.0 DENSITY = 62.400 LBS/CU. FT. WEIGHT X-CG 45.3 43.7 42.1 40.5 38.9 37.2 35.6 34.0 32.4 30.8 29.l 27.5 25.9 24.3 22.7 21.0 19.4 17.8 16.2 14.6 13.0 II .3 9.7 8.1 6.5 4.9 3.2 l.6 158 l 158 l 158 0 157 9 157 8 157 8 157 7 157 6 157 5 157 4 157 .4 157 .3 157 .2 157 .I 157 .0 156 .9 156 .8 156 .7 156 .6 156 .5 156 .3 156 .2 156 .l 155 .
~~PAGE 937~~
Amendmenti01 2/16/71 LM RADIUS TANK NO. 14.2 1 SUBSEQUENT INCHES ,, -43.2 (CONSTANT) Z-CG ,, -43.2 (CONSTANT) OF 5.4-2 DESCENT STAGE DENSITY ¥-CC (ULLAGE/(VOLUME Weight Pounds 10 AND TABLE LIQUID)) X i00 TANK WATER = 62.4 NO. 2 ¥-CG Z-CG MASS LBS/CU. PROPERTIES FT. WEIGHT ., 43.2 (CONSTANT) - 43.2 (CONSTANT) - 323.8 POUNDS - 37.757 Tank-i X-CG Tank-2 X-CG Height Inches 333.0 166.0 142.9 19.542 323.8 165.8 142.7 19.080 322.2 165.8 142.7 19.000 320.
~~PAGE 938~~
Amendment 86 9/10/70 TABLE LM RADIUS • TANK = 14.2 NO. (ULLAGE/ I0 AND SUBSEQUENT INCHES 1 Y-CG Z-CG (VOLUME - -43.2 5.4-2 DESCENT (Continued) STAGE DENSITY (CONSTANT) TANK = -43.2 (CONSTANT) OF LIQUID)) X i00 = 37.757 WATER = 62.4 NO. MASS LBS/CU. PROPERTIES FT. WEIGHT 2 Y-CG = 43.2 (CONSTANT) Z-CG = 43.2 (CONSTANT) Weight Pounds Tank-i X-CG Tank-2 X-CG Height Inches 263.9 164.4 141.3 16.285 262.3 164.4 141.3 16.212 260.7 164.3 141.2 16.140 259.0 164.3 141.
~~PAGE 939~~
._aendment 86 9/10/70 TABLE 124 i0 AND RADIUS TANK NO. 14.2 INCHES 1 Y-CG Z-CG (ULLAGE/(VOLUME SUBSEQUENT DESCENT (Continued) STAGE DENSITY - -43.2 (CONSTANT) - -43.2" (CONSTANT) OF 5.4-2 LIQUID)) X i00 TANK WATER - 62.4 NO. MASS LBS/CU. PROPERTIES FT. WEIGHT 2 Y-CG - 43.2 (CONSTANT) Z-CG - 43.2 (CONSTANT) - 323.8 POUNDS - 37.757 Weight Pounds Tank-i X-CG Tank-2 X-CG 202.4 163.0 139.9 13.580 200.8 163.9 139.8 13.509 199.1 162.9 139.8 13.438 197.5 162.
~~PAGE 940~~
Amendment 86 9/10/70 TABLE LM RADIUS TANK - 14.2 NO. i0 AND SUBSEQUENT INCHES - -43.2 (CONSTANT) Z-CG - -43.2 (CONSTANT) OF DESCENT (Continued) STAGE DENSITY 1 Y-CG (ULLAGE/(VOLUME 5.4-2 LIQUID)) X 100 TANK WATER - 62.4 NO. MASS LBS/CU. PROPERTIES FT. WEIGHT 2 Y-CG - 43.2 (CONSTANT) Z-CG - 43.2 (CONSTANT) - 323.8 POUNDS - 37.757 Weight Pounds Tank-I X-CG Tank-2 X-CG Height Inches 144.1 161.4 138.3 10.977 142.5 140.9 161.4 138.3 10.902 138.2 10.827 139.
~~PAGE 941~~
Amendment 2/16/71 TABLE 5.4-2 I_ I0 AND SUBSEQUENT DESCENT (ConCLnued) STAGE WATER MASS PROPERTIES RADIUS - 14.2 INCHES DENSITY - 62.4 LBS/CU. FT. WEIGHT TANK NO. 1 Y-CG - -43.2 (CONSTANT) TANK NO. 2 Y-CG - 43.2 (CONSTANT) Z-CG - -43.2. (CONSTANT) Z-CG - 43.2 (CONSTANT) (ULLAGE/(VOLUME OF LIQUID)) X I00 m 37.757 Weight Pound____a Tank-1 X-C_._G 77.7 76.1 74.5 72.9 71.2 69.6 68.0 66.4 64.8 63.1 61.5 59.9 58.3 56.7 55.0 53.4 51.8 50.2 48.6 47.0 45.3 43.7 42.1 40.5 38.9 37.2 35.6 34.0 32.4 30.8 29.1 27.
~~PAGE 942~~
Amendment 86 9/10/70 TABLE LH 10 RADIUS TANK = 14,2 NO. INCHES - -43.2 (CONSTANT) Z-CG - -43.2 (CONSTANT) OF DESCENT (Continued) STAGE DENSITY 1 Y-CG (ULLAGE/(VOLUME Weight Pounds AND SUBSEQUENT 5.4-2 LIQUID)) X 100 TANK WATER = 62.4 NO. MASS LBS/CU. FT. WEIGHT 2 Y-CG - 43.2 (CONSTANT) Z-CG - 43.2 (CONSTANT) Tank-i X-CG Tank-2 X-CG 156.3 133 2 2.939 11.3 156.2 133 1 2.742 9.7 156.1 133 8.1 6.5 155.9 155.8 132 132 0 8 2.532 2.305 7 2.055 4.9 155.
~~PAGE 943~~
~~i ........ I L'_ z Vt .k.._ L T- 'v-- '_- v- V' _ . "11 _U -.l[_:. IS It l( l_ l_ ,L. .L J,- _ i,. L L _r t..~~
~~PAGE 944~~
~~PAGE 945~~
LUNAR MODULE ASCENT WATER MASS PROPERTIES NOTE: I. 2. 1 . Mass Properties are given for liquids in individual tanks. Moments of Inertia are about center of gravity of water in individual tanks, coordinates of which are given. Centers of Gravity in Y and Z directions are given at top of each page. The number of tanks of a particular kind is indicated number on the first line of each page. 5.5-I II IIJ I,[ E l:." 1,: L L L" l;.
~~PAGE 946~~
LM ASCENT WATER MASS PROPERTIES-2 TANKS Y-CG = + OR - 25.0 (CONST) Z-CG = + OR RADIUS=7.155 CYLINDRICAL DENSITY=62.400 LBS/CU.FT. (ULLAGE/(VOL. WEIGHT X-CG 41.2 41,0 40.8 40.6 40,4 40.2 40.0 39.8 39.6 39.3 39.1 38.9 38.7 38,5 36.3 38.1 37,9 37.7 37.5 37.3 37.1 36.9 36,7 36.5 36.3 36.0 35.8 35.6 35.4 35.2 35.0 34.8 34.6 34.4 34.2 34.0 33.8 33.6 33,4 33.2 33,0 32.8 32,5 300.3 300.3 300.3 300.3 300.3 300.2 300.2 300.2 300.2 300.2 300.1 300.1 300.1 300.1 300.1 300.1 300.0 300.0 300.0 300.0 300.0 299.9 299.
~~PAGE 947~~
LM ASCENT WATER MASS PROPERTIES-2 Y-CG = + OR RADIUS= DENSITY: 25.0 (CONST) 7.155 CYLINDRICAL 62.400 LBS/CU.FT. WEIGHT X-CG 32.3 32.1 31.9 31.7 31.5 31.3 31 .I 30.9 30.7 30.5 30.3 30.1 29.9 29.7 29.5 29,3 29.0 28.8 28.6 28.4 28.2 28.0 27.8 27.6 27.4 27.2 27.0 26.8 26.6 26.4 26.2 26.0 25.7 25.5 25.3 25.1 24.9 24.7 24.5 24.3 24.1 23.9 23,7 299.5 299.5 299.5 299.5 299,4 299.4 299.4 299.4 299.4 299.3 299.3 299.3 299.3 299.3 299.2 299.2 299.2 299.2 299.2 299,1 299.1 299.1 299.1 299.1 299.0 299.0 299.
~~PAGE 948~~
LM ASCENT WATER MASS PROPERTIES-2 Y-CG = + OR RADIUS= DENSITY= 25.0 (CONST) 7.155 CYLINDRICAL 62.400 LBS/CU.FT. WEIGHT X-CG 23.5 23.3 23.1 22.9 22.7 22.5 22.2 22.0 21.8 21.6 21.4 21.2 21.0 20.8 20.6 20.4 20.2 20.0 19.8 19.6 19.4 19.2 19.0 18.7 18.5 18.3 18.1 17.9 17.7 17.5 17.3 17.1 16.0 16.7 16.5 16.3 16.1 15.9 15.7 15.4 15.2 15.0 14.8 298.7 298.6 298.6 298.6 298.6 298.6 298.5 298.5 298.5 298.5 298.4 298.4 298.4 298.4 298.4 298.3 298.3 298.3 298.3 298 2 298 2 298 2 298 2 298 2 298 l 298 l 298.
~~PAGE 949~~
LM ASCENT WATER MASS PROPERTIES-2 Y-CG = + OR - 25.0 (CONST) RADIUS= 7.155 CYLINDRICAL DENSITY: 62.400 LBS/CU.FT. WEIGHT X-CG 14.6 14.4 14.2 14.0 13.8 13.6 13.4 13.2 13.0 12.8 12.6 12.4 12.2 II .9 II .7 I I. 5 II .3 II .l I0.9 I0.7 I0.5 I0.3 lO.l 9.9 9.7 9.5 9.3 9. l 8.9 8.7 8.4 8.2 8.0 7.8 7.6 7.4 7.2 7.0 6.8 6.6 6.4 6.2 6.0 297.7 297.7 297.6 297.6 297.6 297.6 297.5 297.5 297.5 297.5 297.4 297.4 297.4 297.4 297.3 297.3 297.3 297.3 297.2 297.2 297.2 297.2 297.1 297. l 297. l 297.0 297.0 297.0 297.
~~PAGE 950~~
LM ASCENT WATER MASS PROPERTIES-2 TANKS Y-CG = + OR - 25.0 (COrISl) Z-CC- = + OR - 13.7 RADIUS= 7.155 CYLINDRICAL SECTION= DENSITY= 62.400 LBS/CU.FT. WEIGHT X-CG 5.8 5.6 5.4 5.1 4.9 4.7 4.5 4.3 4.1 3.9 3.7 3.5 3.3 3.1 2.9 2.7 2.5 2.3 2.1 l .9 l .6 l .4 l .2 l .O 0.8 0.6 0.4 0.2 296.5 296.4 296.4 296.4 296.3 296.3 296.2 296.2 296.2 296.1 296.1 296.0 296.0 295.9 295.9 295.9 295.8 295.7 295.7 295.6 295.6 295.5 295.4 295.4 295.3 295.2 295.1 294.9 0.0 WEIGHT= IXX(S-FT.SQ.) 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.
~~PAGE 951~~
~~II Ill _ F "" II " IIII II '" I '" I II III r '-' 1_, 0 __0o-, o'_ _-_ [-_ L.~~
~~PAGE 952~~
~~PAGE 953~~
~~LUNAR MODULE AND TRAPPED AND MISCELLANEOUS 5.~~
~~PAGE 954~~
:> N_I r,- 0 u_ _ r,- 0 r-- 0 r-- 0 _ O_ 0 I I I I I I Z I Z W 0 ,..1 _-_ _-_ o,1 0 W _w I _D *0 _g 0 m m G ,,,,.4 qJ N N N III r_ o I N I N i-I ¢J "_ -_1 I I i-t _ "_ _ I I I.I I I M I I e_ ,,-t I= _1 '_ G 0 =1 _ 0 _ _ _J Q. u_ 0 _ 0 m m G r..3 ,-.i I ILl !1 1_ Z ]_ IL E L I: I: 1_ ]2 _ 1_ E E : 'l L..
~~PAGE 955~~
~~_4 v N "Q I 0 i-4 r_ E-i 1,4 0 _J I.i .I-I _J I CJ I 0 U Y m t_ I.i I U _J _J _J i-I ¢J 14 ,,-'4 "10 _ X 0 14 -i-I I:1 ,--1 I I t,l ,_ _J n_ el O _ J i-I _J I aO "_ ,i-I O .~~
~~PAGE 956~~
•"-t I I 0 I I cO I Q u'_ ,-,I ,-I Z k_ [._ 0 • . ° • ° ° 0 ¢I I-I u_ _=_ r_ 0 .4 ,,,-4 0 e_ ,,,,,I Iq ,-4 "_ I I ..M ,I=I N k_ I N N _J I r_ •,_ N 0 ,--1 I ,-_ _ _ t=. '_I _ N 0 I I I _ I .._ _ 0 r._ I I o I _-i N ._ "0 "_ _ r_ X 0 ,,4 ,--I ._ I e_ 0 I ._ .M e_ I •M il' !1 C_ I _1_ _l 0 _=* _J 0 -M ,--i ,-I _ 11 11 IL 1;. IL )L L _1 E 0 E _ E IJ _ H L" L _L. L.
~~PAGE 957~~
0 ,..4 ,-4 '4" +1 +_ ¢,,I ,4" 00 c:r_ ,.=4 • "0,-4 -- ¢',,I P,i ,-I" ,.-4 ,-4 • • o I I r_. 0 o "H • • • +1 4-1 • 0 _ +1 ...,,." +1 -,-, +1 • ',.3" I ii t= _ w %. • • • • • • ° • . I I +1 +I . • "o ,-I o •'o ¢:: o. 0 ,,M ,..-4 o .,.4 _ ,.-4 L"q "O + t-I _, ¢-I cn •,4 N -,4 ¢I o •,_ N 0 m u _J v ,.-4 I I _=_ _} t4 I l .Z3 +--4 _.j _:_ D.d ,-1 _ 0 ,_ ¢Jj_ ,-4 _ w w ",41_ I= ,,< .-4 t4 _ _ I_ 0 I.
~~PAGE 958~~
O r-r-- 0 0 4J,-r" I',. u'3 I L_ I 0 0 c; c; 0 0 0 cO 0 J "O,'- 0 7 U_ Ca- 0 ,.--t L3 0 L) ,-.I I Ul Ul If. I c_ _ N r_ 0 J ,--I [--_ ,--4 0 .,_ Z 0 I X I I .M ,--I .M D9 _J 0 0 -,.4 _J .IJ I/) F+ I I L) 5.
~~PAGE 959~~
• % Amendment TABLE LM-10 AND SUBSEQUENT 106 6/22/71 5.6-2 MISCELLANEOUS CONSUMABLES CENTER OF GRAVITY (Inches) ECS WEIGHT COOLANT: Ascent YE (Pounds) 32.1 - Primary 251.9 9.9 -2.4 - Redundant 3.3 251.0 9.9 -2.4 - Primary 1.7 163.5 25.0 38.0 - Redundant 0.0 Descent COX: Ascent Descent - Tank #i 2.4 266.1 - Tank #2 2.4 266.1 -15.1 -53.5 15 .I -53.5 - Tank #i 46.9 185.6 38.9 -53.5 - Tank #2 46.9 185.2 41.5 48.
~~PAGE 960~~
~~PAGE 961~~
5.
~~PAGE 962~~
~~-.I" ,-4 O _J r" o _g I I H o o O O o_ o m_ o UJ C_ o o .g d .g P-4 U O __) (.9 Ul I q) i o r_ O 1,1 Z .,-4 N O _J I M O I _ u .H O = _ 0 ?. I I _._ NASA _ MSC 5.~~
~~PAGE 963~~
TABLE LM Miscellaneous ECS Descent CENTER OF GRAVITY (Inches) Consumables WEIGHT (Pounds) COOLANT: Ascent 5.6-2 _ YE Zm 32.1 251.9 9.9 -2.4 - Redundant 3.3 251.0 9.9 -2.4 - Primary 1.7 163.5 25.0 38.0 - Redundant 0.0 - Primary GOX: Ascent - Tank #i 2.4 266.1 15.1 -53.5 - Tank #2 2.4 266.1 -15.1 -53.5 48.0 184.3 40.4 -40.4 Descent WATER: Ascent - Tank #i 42.5 300.4 25.0 13.7 - Tank #2 42.5 300.4 -25.0 -13.7 166.0 -43.2 -43.2 0.I 301.5 +25.0 13.
~~PAGE 964~~
~~ILl ILl IJ ;L: 1: E L L I: E E E L: l; I': E L L .~~
~~PAGE 965~~
0 .4.1 r--. = QO .io., 1_1 I-I > <.,, = '7 o., I O_ 0 0 O0 O_ I_O 0'_ _ o o -.7 _ ..4 .._ (",i I I _ I I _ (') I I ,-t I I 0 I 4_ "0 o_ ,.-] _ _,_.. <,'i I _i I 0 0 0 _ 0 _ 0 0 ..-, o o _ _ .4 ,_ .-, I CXl I _ _ u"i I <_ _ 0 I OJ ,--4 _> ¢li 0'3 ¢_ 0 u'3 • :_ -.I" .-I ¢_I ,-4 ql l=l I-i Qi i.-t -,,4 0 0 ¢j, I .4 [._ ,-] i:l < 0 0 5.
~~PAGE 966~~
~~U L L~~