Nasa Washer Dryer Tm X 68968 Users Manual
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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
...,.
REVISION 2
20 AUGU 3T 1969
" !:,.":'..Tin
: _JY
(NASA-TM-X-6896 81
::::::::.:.:.:.:.: OPERATIONAL DATA
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MANNED SPA(E('RAFT (ENTER
tt()US1 ()N, -I F.X A S
I
CSM/LM SPACECRAFT
BOOK. ¥OLUME 3: MASS
20 Auq. 1969 212 p
00/99
N73-7001_
Unclas
37210
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COPY I_10.
SNA-8-D-027(III) REV 2
NATIONAl AE RONAIJIlCS AND SPACE ADMIN STRATION
CSM/LM SPACECRAFT
OPERATIONAL
DATA BOOK '1 I
VOLUME ITI
MASS PROPERTIES
, I
REVISION 2
20 AUGUST 1969 )
)
MANNEI) SPA(E(RA FT
tl()USI()N, IkXAS
(ENTER
II
U111 1: E L 1: L L L E L E _ l_ E l_ L L _ ;.
SNA-8-D-027 (III)REV 2
CSM/LM SPACECRAFT OPERATIONAL DATA BOOK
VGLIIME III
MASS PROP_TIES DATA BOOK
PREPARED BY
SYST_L$ OPERATIONS BRANCH
SYSTEMS ENGINEERING DIVISION
APOLLO SPACECRAFT PROGRAM OFFICE
MANNED SPACECRAFT
APPROVED BY
SYSTemS _INEE_ING DIVISION
GEGRGE M. LOW, MANAG_
APOLLO SPACE(_RAFT PROGRAM
ORFLIGHT_IONS lJ
P RE FACE
This document is the second revision issue of the Mass Properties
Data Book. In this revision Missions"C", "C-Prime", "D", and "F"
have been deleted. The second revision incorporates Amendments i
through 65, except those amendments associated with Mis_ions "C",
"C-Prime", "D", and "F". Amendments released subsequent to publi-
cation of this Mass Properties Data Book, Revision 2, will be num-
bered sequentially with the next revision number (i.e., 66 and on).
SNA-8-D-O27(III)REV 2
VOLUME IIl
MASS PROPERTIES DATA BOOK
1.0 Introduction
2.0 Configuration and Reference Station Locations
3.0 Mass Properties and Loading Data by Mission
3.1 Mission G
3.2 Mission H1
3.3 Mission H2
3.4 Mission H3
3.5 Mission Jl
4°0 CSH Reference Consumables Mass Properties Data
4.1
5.0
Amendment 86
9/lo/7o
SPS Tank Consumables Mass Properties, Trapped Propellants,
SPS Density Equations and Graphs, and SPS Loading Windows .
4.2 RCS/ECS/EPS Consumables Mass Properties
4.3
4.4 CM Ablator Data
LM Reference Consumables Mass Properties Data
I
CSM RCS Load Calculatlon Tables and Loading Windows
5.1 LM Descent Tank Mass Properties
5.2 LM Ascent Tank Mass Propartles
5.3 LM RCS Tank Mass Properties
5.4 LM Descent Water Tank Mass Properties
5.5 LM Ascent Water Tank Mass Properties
5.6 LM Trapped Consumables
Ii SNA-8-D-027 (III)REV 2
i
V" "V_ •" IrT
Z
ILl 11 I.I I.:; 1: _ 1.: L L" I; L,: EU 1_ li L-" k L ,_ ,.
1.0 INTRODUCTION
i.i SCOPE
The complete Spacecraft Operational Data Book for the manned missions will
consist of five separate volumes. These are defined as follows:
Volume I - CSM Data Book
Part I - Constraints and Performance
Part II - Launch Mission Rule Redlines
Volume II - LM Data Book
Part I - Constraints and Performance
Part II - Launch Mission Rule Redlines
Volume III - Mass Properties Data Book
Volume IV - EMU Data Book
Volume V - ALSEP Data Book
Volumes 1 and II present operational information on the capabilities and
limitations of the spacecraft. A brief discussion of the purpose and scope of
Volume III follows:
1.2 PURPOSE
The purpose of this document is to provide spacecraft mass properties data
per mission for use in the mission planning activities, trajectory documentation,
mission simulations, and to provide all necessary information and documentation
for consumable loading. The data contained herein represent the latest predictions
for the launch configuration mass properties and consumable loadings. Updates
to these data will be provided based on the actual weight and balance data for
each spacecraft. Mass properties data will be maintained and updated through the
actual consumables loading.
Section 2.0 presents relevant spacecraft configuration drawings and station
locations which may be useful in describing the location of various spacecraft
components and the relationship of coordinate systems in the launch and docked
configuration.
Section 3.0 presents mass properties and consumable loading data for each
mission. Included in this section are the predicted mass properties for the launch
configuration, the docked configuration, the normal entry, and for launch aborts.
Sections 4.0 and 5.0 contain consumables mass properties data and mission
independent consumable loading information for the CSM and LM, respectively.
In addition, CM ablator material data are provided in Section 4.0 to aid the user
in determining CM mass properties during reentry.
Amendments to this document will be made by page additions or replacements.
Data changed by an amendment will be denoted by an amendment date in the upper
right hand corner and avertical bar in the page margin to locate the change.
i-i SNA-8-D-027(III)REV 2
Lr
L
SELECTED
TABLE I-I
ABBREVIATIONS AND ACRONYMS
Amendment 72
10/30/69
ACT
ACQ
ALIGN
ANG
ASCT
APS
A/S
ASSY
BIOINST
Activation
Acquisition
Alignment
Angle
Ascent
Ascent Propulsion Subsystem
Ascent Stage
Assembly
Bioinstrumentation
CAN:i
CAM
CK
CIRC
CSC
COMPT
CDR
CM
CMP
CSM
COMM
CSI
CWG
CONT
CLSRC
DSEA
DECONTAM
DEPL
DSCT
DOI
DPS
D/S
DOCK
EOI
ELECT
ECU
EQUIP
EXCL
EXC
EXP
EV
FWD
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
Contingency Lunar Sample Return Container
Data Storage Electronic Assembly
Decontamination
Depletion
Descent
Descent Orbit Insertion
Descent Propulsion Subsystem
Descent Stage
Docking
Earth Orbit Insertion
Electrical
Environmental Control
Equipment
Exclude
Excursi on
Experiment
Extravehicul ar
Unit
Forward
HASS
INDIC
INFLT
Hasselblad
Indicator
In-Fl i ght
1-2 SNA-8-D-O27(III)REV 2
ILl 11 !.: L: L: EL L E L: E E _ l; E E L L ,_. ,.
Anmndment 72
10130169
ICG
IV
JETT
LES
LEV
LV
LH
LEB
LIQ
LEC
LM
LOI
LS
LMP
LUN
MC
MECH
MCC
N/A
OPS
PR
P-GA
PROC
RAD
RCS
RELOC
RESTR
RT
RH
RHEB
SRC
SCRS
SEP
SM
SLA
SPS
S/C
STG
STORE
STOW
TABLE I-I (Continued)
In-FLight Coverall Garment
I ntra vehi cul ar
Jetti son
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
Main Chute
Mechanism
Midcourse Correction
Not Available
Oxygen Purge System
Pair
Pressure Garment Assembly
Procedure
Radiation
Reaction Control System
Relocation
Restraint
Right
Right Hand
Right Hand Equipment Bay
Sample Return Container
Scissors
Separation
Service I.odule
Service Hodule LM Adapter
Service Propulsion System
Spacecraft
Stage
Storage Tank
Stowage
1-3 SNA-B-D-027(I II)REV 2
11 !1 1_ _ L l: L L L L: E E M l; E E L
TABLE I-I (Continued)
SUBSYS Subsystem
SUMP Sump Tank
SURF Surface
SYS System
RSS Root Sum Square
TEMP Temporary
TBD To Be Determined
TEl Transearth Insertion
XFR Tranfer
TLI Translunar Insertion
TRANS Transposi tion
TRANS/DOCK Transposition and Docking
UMB
UPR
UEB
UCTA
Umbil ical
Upper
Upper Equipment Bay
Urine Collection Transfer Assembly
WT
w/
w/o
Waist Tether
With
Without
Amendment 72
I0/30/69
i-4 SNA-8-D-O27(III)REV 2
ililb t
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2.0 CONFIGURATION
This section provides relevant spacecraft configuration drawings and station
locations which may be useful in describing the location of various space-
craft components and the relationship of coordinate systems in the launch
and docked configuration for Block II CSM spacecraft and Lunar Modules.
Configuration data are presented in the following categories and order:
i. Apollo Vehicle Coordinate System.
2. Saturn V Vehicle Outboard Profiles and Reference
Dimensions.
3. Apollo Spacecraft Reference Stations, Thrust Chamber
Locations, and CSM Consumables Tank Locations.
4. Lunar Module Reference Stations, Thrust Chamber Locations
and LM Consumables Tank Locations.
Consumables mass properties data for the CSM and LM may be found in Sections
4.0 and 5.0, respectively, of this volume. These consumables mass property
data must be compared to the onboard consumable loading data for each mis-
sion in Section 3.0 to determine the actual mission tanked consumables mass
properties.
2-1 SNA-8-D-027(III)REV 2
-- i
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X A = 1133.5 (NO ABLATIVE) - (REF V14-15-2) 83.476 "" 83.5
COMMAND TO HEATSHIELD -- - -_ 33 ° "_A_'/083.5
MODUI.E STRUCTURE 7"
X A = 1000.00 =
SERVICE
MODULE
XA = 838.0
SPACECRAFT
LM ADAPTER
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162.0"
----e- j 154.0" DIAMETER
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PLANE
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X A = 585 FLIGHT STIFFENER
ATTACHING
PLANE
260.0" DIAMETER
Figure 2-2. Apollo Spacecraft Reference Dimensions
2--'3
SNA-8-D-027(III)REV 2
STA 4240.792
STA 3890.055
STA 3841.182
STA 3756.555
STA 3594.555
STA 3340. 045
STA 3258.555
STA 3222. 555
STA 2746.500
GIMBAL STA 2645.853
STA 2519.000
STA 1760.000
GIMBAL STA 1664.000
STA 1564.000
STA 1541.000
NOTE:
NO ABLATIVE MATERIAL
DIMENSIONS INCLUDED
ON CM -._ I
STA 3890. 055--
STA 3841.182
STA 3756.555
STA 3594.555
SERVICE MODULE
I
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t
X A : 1133.500
XA = 1084.627
X A = 1000.000
X A =838.000
260 IN. DIA--.._
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X A = 1133.500
x A =1000.000
"_ X A = 838.000
XA=583. 490
XA = 502.000
AlL SEPARATION
FIELD SFLICE
2-4 SNA-8-D-027 (III)REV 2
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2-6 SNA-8-D-027(III)REV 2
HE L LLL
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GIMBALING
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YAW
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XA - YA PLANE
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Figure 2-9. SPS THRUST VECTOR ORIENTATION
2-10 SNA-8-D-027(III)REV 2
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XA = 1110.25
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-Z A
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Z.,
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LM OUTLINE
VIEW LOOKING FORWARD THROUGH CM APEX
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1110.25 XA = 312.5 X E
XA = 1422.75 - XE
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FIGURE 2-10. CSM/LM DOODLED CONFIGURATION REFERENCE DIMENSIONS
2-13 SNA-8-D-027(III)REV 3
LM ADAPTER
DEPLOYED
...... -Z S-IVB
X A 11 I0.2_,
/×
TRANSLATION CSM/LM
SEPARATION SEPARATE
FROM S-IVB
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X E
(TYP)
CLUSTER__
+YE !
i
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-Z E
(REF)|CLUSTER"2_'N
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/4.6" (TYP) I -YE
CLUSTER ,%
+Z E
_CLUSTER I
LOCATION OF LM/RCS CLUSTERS
LOOKING DOWN AT ASCENT STAGE
IN LANDING POSITION
Figure 2-13. LM/RCS THRUST CHAMBER LOCATIONS
2-14 SNA-8-D-027 (III)REV 2
ILl il I_ I.: 1_ _ IJ L EU_U_L{H_hhaL
,_m_e,',dme.a.c.86
9/ZO/70
YE ZE
A/S WATER (2)
D/S WATER (I)
DPS FUEL (2)
DPS OXIDIZER ('2)
APS FUEL (I)
APS OXIDIZER (I)
RCS FUEL (2)
RCS OXIDIZER (2)
±25.0
-43.2
*54.O
0.0
-71.3
+44.5
+44.5
*44.5
TANK RADIUS =7.155
.13.7
-43.2
0.0
*54.0
0.0
0.0
+14.5
_14.5
XE=295.45_
XE = 264.3
XE = 252.71
XE = 203.31
H20 _[_ XE =308.9 ----_ H20
TANK RADIUS =24.7
X E = 195.38-
XE= 125.08--
TANK RADIUS = 14.2
l'- XE =182.8_
XA = 1110.25
X E = 312.5
XE= 295.49
XE= 257.73
XE= 252.71
XE= 203.31
_X E = 200.00
_X E = 195.38
BX E = 125.08
(NoT TO SCALE)
Figure 2-14
LM-8 PROPELLANT TANK LOCATIONS IN LM (X=) COORDINATE SYSTEM
(See Figure 2-18 for LM-10 and Subsequent)
2-15 SNA-8-D-027(III)REV 2
II i] IJ IC ]/ L. ]/ L EK ]J ]£ L: 1i U l_ _ L L L
(GDA)
Actuator
Response
Extend
Contract
Contract
Extend
Rotation
of
Engine
- 60
+ 68
Commanded
Change Vehicle
Angular Acceleration
+
+
Pitch
Pitch
!]Roll
)Roll
+X E PROJECTION OF DPS
ENGINE F THRU SC c.g.
PITCH GDA ROLL GDA
... _. DPS ENGINE PIVOT
+ PITCH + ROLL
+ YE + ZE
+ X E +X E
ENGINE PROJECTION ENGINE PROJECTION
ROLL/OF_'N i PITCH/OF_',N
_+YE _ _ +Z E
+ OR - SIGN ACCORDING TO ENGINE GIMBAL ANGLE
SIGN CONVENTION
Figure 2-15. SIGN CONVENTION FOR DPS GIMBAL" ANGLE
2-16 SNA-8-D-027(III)REV 2
XLv,XA,XE
LM DOCKING INTERFACE
XE: 312.5
XLV : 3468.555
LUNAR MODULE
X E : 0.0
XLV = 3156.055
APOLLO
X A = 0.0
XLV = 2756.555
SATURN V LAUNCH VEHICLE
XLV = 0.0
t
312.5
t
399.5 IN.
2756.555 IN.
TO TRANSFORM:
I) APOLLO TO LAUNCH VEHICLE
XLV = XA + 2756.555
2) LUNAR MODULE TO LAUNCH VEHICLE
XLV = X E + 3156.055
_-- Z E
- ZA
ZLV
Figure 2-16. Launch Configuration Station Reference
2-17 SNA-8-D-027(III)REV 2
TO TRANSFORM:
1) LAUNCH VEHICLE TO APOLLO
XA = 4578.805 - XLV
LM DOCKING INTERFACE
X E = 312.5
XLV = 3468.555
312.5 IN.
LUNAR MODULE
XE = 0.0
XLV = 3156. 055
APOLLO
X A = 0.0
XLV -- 4578.805
1110 25 IN.
+X A
+X E
CM DOCKING INTERFACE
XA= 1110.25
Z E
Figure 2-17. Docked CSM/LM Station Reference
2-18 SNA-8-D-027(III)REV 2
L k
AMendment 86
9/10/70
A/S WATER (2)
D/S WATER (2)
DPS FUEL (2)
DPS OXIDIZER (2)
APS FUEL (I)
APS OXIDIZER (I)
RCS FUEL (2)
RCS OXIDIZER (2)
YE ZE
±25.0
±43.2
,.54.0
0.0
-71.3
+44.5
:i:44.5
:t_,4.5
±13.7
+43.2
0.0
:1=54.0
0.0
0.0
±14.5
_14.5
X E = 295.45
XE = 264.3
X E = 252.71
XE=203,31
X E =197.6
TANK RADIUS :7.155
X E -124.0
H20 (_)_ XE = 308.9 __ H20
r
TANK RADIUS = 24.7
-_XE=186.9
-TANK RADIUS -25.5
X A = 1110.25
XE = 312.5
XE = 295.49
•XE= 257.73
X E = 252.71
X E =203.31
XE .= 200. O0
X E = 197.6
XE-124.0
(NOT TO SCALE)
Figure 2-18
LM-10 AND SUBSEQUENT PROPELLANT TANK LOCATIONS IN LM (X E) COORDINATE SYSTEMS
2-19 SNA-8-D-027 (llI) REV 2
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3.0
Amendment 86
9110170
SPACECRAFT MASS PROPERTIES AND LOADING DATA BY MISSION
The mass property data specified in this section represent the best pre-
diction of launch configuration mass properties for each spacecraft. The
data have been organized loglcally by Apollo mission and the tables have
been organized according to basic mission profile. In addition, data are
presented by individual and composite spacecraft to reflect the variation
of centers-of-gravlty, moments of Inertla_ and products of inertia as a
function of spacecraft weight to enable the user to reasonably predict space-
craft mass properties at any time in the mission profile.
These data represent the composite results of the detailed mass properties
data supplied to NASA (MSC-ASPO) by the contractors. Spacecraft mass pro-
perty data are presented as follows:
1. 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 3.5 Mission J1 I
3-1 SNA-8-D-027 (Ill)REV 2
11 !1 IJ :L:" :L L L L E L; L_ E L,' 1_ I_ L: :'_
ILl ILl L: EEL: L L E1: L EL' |; E LL. It.
Amendment llO
7/19/71
SUPPLEMENTARY DATA APPLICABLE TO SEQUENTIAL MASS PROPERTIES TABLES
General Comments to be applied to Tables 3.1-1 through 3.1-8:
Inertia data dispersions are +10%.
Dispersions shall be used as 30 deviation values.
All initial propellant weights are total tanked.
The (+) or (-) sign following the name of an item indicates that the
item is added to or subtracted from the preceding total.
Table 3.1-i
SM/SPS gimbal angles for SPS abort sequence are: Pitch = -0.524
Yaw = 1.895
Table 3.1-2
L_I propellants are in high end of the tanks, (greatest X-c.g. station),
for all docked configuration where the CSM is the controlling vehicle.
The Mass Spectrometer and Gamma-Ray Spectrometer are shown deployed after
each SPS firing following D.O.I. For all other summations the M.S. and
G. R. Spectrometers are no____tdeployed. The following are the individual
mass properties for the M.S. and G.R. Spectrometers in Apollo Coordinates.
Weight X-Bar Y-Bar Z-Bar
(Ib) (in) (in) (in)
Gamma-Ray
Retracted 45._ 865.1 33.0 -57.0
Gamma-Ray 28.0 865.1 231.3 -312.4
Deployed 17.4 865.1 132.2 -184.7
Mass Spectrometer 47.4 863.1 55.8 -40.5
Retracted
Mass Spectrometer 27.4 863.1 341.7 -149.4
Deployed 20.0 863.1 198.8 -94.9
Tables 3.1-7 and 3.1-8
CSM and LM consumables changes are presented in Tables 3.1-7 and
3.1-8, respectively.
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SNA-8-D-027(III) REV 3
L. L
Amendment 111
7/22/71
XA COORDINATES TABLE 3.1-4
CSM 112 LEV DETAIL (TILTED) MASS PROPERTIES HIGH ALTITUDE ABORT
MASS PROPERTIES
The following information applies to Tables 3.1-4 and 3.1-5.
Delta Z
LES motor tilted angles
(Delta includes 0.3 deg. for
down range dispersions)
LES motor tilted confluence point
= O. 800 in.
Delta = 2.240 deg.
Sigma = 268.996 deg.
X = 1222. 300 in.
Y = 0. 011 in.
Z = 0.282 in.
PCM motor tilted angels Delta = 89.150 deg.
Sigma = 270.000 deg.
PCM motor tilted confluence point X = 1429.000 in.
Y = O. 134 in.
Z = 3.348 in.
3.1-44 SNA-8-D-027 (III) REV 3
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SNA-8-D-027(III)REV 3
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TABLE 3.1-7
CSM 112 CONSUMABLES WEIGHT CHANGE SUMMARY
(To be used in conjunction with CSM sequential mass
properties Table 3.1-2).
Amendment 110
7/19/71
From
EVENT
To Consumable
Earth Orbit Pre Trans/Dock
Weight Amount Total
Change Remaining Usage
(Pounds) (Pounds) (Pounds)
SM-Hydrogen
Tank 1 & 2 -1.6 53.6 -1.6
Tank 3-0.6 27.0 -0.6
SM-Oxygen
Tank I & 2-7.5 625.7 -7.5
Tank 3-0.7 315.9 -0.7
CM-Waste H20 +0.8 35.8
CM-Potable H20 +6.0 36.0
Pre Trans/Dock Post Trans/Dock SM-RCS -70.6 1,265.7 -70.6
Post Trans/Dock Pre L.O.I. SM-Hydrogen
Tank 1 & 2-4.7 48.9 -6.3
Tank 3 -9.3 17.7 -9.9
SM-Oxygen
Tank 1 & 2 -61.4 564.3 -68.9
Tank 3-81.5 234.4 -82.2
SM-RCS -110.2 1,155.5 -180.8
CM-Waste H20 +8.2 44.0
CM-LIOH +24.0 24.0
CM-Food -6.2 -6.2
Fecal +2.0 2.0
Pre L.O.I. Post L.O.I. SM-SPS -26,300.2 14,179.1 -26,300.2
Post L.O.I. Pre D.O.I. SM-Hydrogen
Tank i & 2-0.8 48.1 -7.1
Tank 3 -0.I 17.6 -i0.0
SM-Oxygen
Tank i & 2-6.8 557.5 -75.7
Tank 3 -1.3 233.1 -83.5
SM-RCS -41.9 1,113.6 -222.7
3.1-48 SNA-8-O-027(III) REV 3
TABLE 3.1-7 (CONTINUED)
CSM 112 CONSUMABLES WEIGHT CHANGE SUMMARY
(To be used in conjunction with CSM sequential mass
properties Table 3.1-2).
Amendment 110
7/19/71
EVENT
From To
Pre D.O.I. Post D.O.I.
Weight Amount Total
Change Remaining Usage
Consumable _Pounds) (Pound#) (Pounds)
SM-SPS -i,561.4 12,617.7 -27,861.6
Post D.O.I. CSM/LM Sep. SM-Hydrogen
Tank 1 & 2 -4.0 44.1
Tank 3 -0.8 16.8
SM-Oxygen
Tank I& 2 -22.9 534.6
Tank 3 -13.5 219.6
SM-RCS -i14.7 998.9
CM-LiOH +6.0 30.0
CM-Food -3.8
Fecal +3.0 5.0
-98.6
-97.0
-337.4
-10.0
CSM/LM Sep. Pre Circularization SM-Hydrogen
Tank 1 &2 -0.1 44.0
Tank 3 -0.i 16.7
SM-Oxygen
Tank 1 b 2 -0.7 533.9
Tank 3-2.3 217.3
-ii .2
-I0.9
SM-RCS -23.7 975.2 -361.I
Pre Circular- Post Circular-
izatlon Izatlon
SM-SPS -277.9 12,339.8 -28,139.5
Post Circular-
ization
Pre Plane Charge SM-Hydrogen
Tank 1& 2 -11.5 32.5
Tank 3 -2.5 14.2
SH-Oxygen
Tank 1 & 2 -83.6 450.3
Tank 3 -33.4 183.9
SH-RCS -112.0 863.2
Fecal +3.0 8.0
-182.9
-132.7
-473.1
3.1-49 SNA-8-D-027(III)REV 3
TABLE 3.1-7 (CONTINUED)
CSM 112 CONSUMABLES WEIGHT CHANGE SUMMARY
(To be used in conjunction with CSM sequential mass
properties Table 3.1-2).
Amendment 110
7/19/71
EVENT
From To Consumable
Pre Plane Change Post Plane Change SM-SPS
Weight Amount Total
Change Remaining Usage
_Pounds) (Pounds) _eounds_
-1,133.8 11,206.0 -29,273.3
Post Plane Change CSM/ASCT Dock SM-Hydrogen
Tank 1 & 2
Tank 3
SM-Oxygen
Tank 1 & 2
Tank 3
SM-RCS
CM-Food
CM-LiOH
CM-Fecal
-1.4 31.1 -24.1
-0.3 13.9 -13.7
-10.6 439.7 -193.5
-4.0 179.9 -136.7
-87.1 776.1 -560.2
-4.3 -14.3
+12.0 42.0
+3.1 ll.1
CSM/ASCT Dock Pre Orbit Shaping SM-Hydrogen
Tank 1 & 2 -8.4 22.7 -32.5
Tank 3 -1.9 12.0 -15.6
SM-Oxygen
Tank 1 & 2-60.5 379.2 -254.0
Tank 3 -33.0 146.9 -169.7
720.6
47.0
14.1
-615.7
SM-RCS -55,5
CM-LiOH +5.0
CM-Fecal +3.0
CM-Food -3.8 -18.1
Pre Orbit Shaping Post Orbit Shaping SM-SPS -243.9 10,962.1 -29,517.2
Post Orbit Shaping Pre T.E.I. SM-Hydrogen
Tank i & 2 -0.4 22.3 -32.9
Tank 3 -0.I ii.9 -15.7
SM-Oxygen
Tank 1 & 2-2.8 376.4 -256.8
Tank 3 -1.7 145.2 -171.4
SM-RCS -36.3 684.3 -652.0
3.1-50 SNA-B-D-OZ7(III) REV 3
TABLE3.1-7 (CONCLUDED)
CSM 112 CONSUMABLES WEIGHT CHANGE SUMMARY
(To be used in conjunction with CSM sequential mass
properties Table 3.1-2).
Amendment 110
7119171
From
EVENT
To Consumable
Pre T.E.I. Post T.E.I. SM-SPS
Weight Amount Total
Change Remaining Usage
(Pounds) (Pognds) . (Pounds)
-9,366.8 1,595.3 -38,884.0
Post T.E.I. SM Jettison SH-Hydrogen
Tank 1 & 2 -10.3 12.0 -43.2
Tank 3 -2.9 9.0 -18.6
SM-Oxygen
Tank 1&2 -82.9 293.5 -339.7
Tank 3 -49.2 96.0 -220.6
SM-RCS -117.8 566.5 -769.8
CM-LIOH +13.0 60.0
CM-Food -7.3 -25.4
CM-Fecal +4.6 18.7
SM Jettison CM @ Entry CM-RCS -11.6 233.4 -11.6
CM @ Entry CM @ M.C. Deploy CM-RCS -30.7 202.7 -42.3
CM @ M.C. Deploy CM @ Impact CM-RCS -202.7 0.0 -245.0
3.1-51 SNA-8-D-027(III) REV 3
IS II LL_ Ii L I/ L_ Lli Id L t_ li 1.I K ii L LL
TABLE 3.1-8
Amendment 110
7/19/71
LM-IO CONSUMABLES CHANGE SUMMARY
(To be used in conjunction with the LM sequential mass properties Tabl e 3.1-_)
Weight Amount
EVENT Change Remaining
From To Consumable (Pounds) (Pounds)
Earth Orbit CSM/LM Separation D/S-Oxygen -1.0 92.8
D/S-Water -12.0 396.0
LM-RCS -5.0 600.4
Total
Usage
(Pounds>
-1.0
-12.0
-5.0
CSM/LM Pre P.D.I. D/S-Oxygen -0.6 92.2 -1.6
Separation D/S-Water -23.0 373.0 -35.0
LM-RCS -50.7 549.7 -55.7
Pre P.D.I. LM @ Touchdown D/S-Oxygen -0.I 92.1 -1.7
D/S-Water -2.0 371.0 -37.0
LM-RCS -90.0 459.7 -145.7
LM-DPS -18,790.5 694.8 -18,790.5
LM @Touchdown A/S @Lift-Off LM-RCS -5.0 454.7 -150.7
A/S @ Lift-Off A/S in Orbit LM-APS -4,942.7 280.1 4,942.7
A/S in Orbit A/S Pre T.P.I. A/S-Water -8.0 77.0 -8.0
A/S-Oxygen -0.2 4.8 -0.2
LM-RCS -44.6 410.1 -195.3
A/S Pre T.P.I. A/S Post T.P.I. LM-APS -35.4 244.7 4,978.1
A/S Post T.P.I. A/S @ Docking A/S-Water -7.0 70.0 -15.0
A/S-Oxygen -0.3 4.3 -0.5
LM-RCS -70.3 339.8 -265.6
A/S @ Docking A/S Jettison A/S-Water -20.0 50.0 -35.0
3. ]-52 SNA-8-D-027(III)REV 3
t-. r,, .
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3.1-53 SNA-B-D-027(III)REV 3
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3.1-54 SNA-8-D-027(III) REV 3
k... I_ L
TABLE 3.1-9 (CONTINUED)
MISSION J-i COMMAND MODULE STOWAGE VOLUME CENTROIDS
SPACECRAFT 112
AREA X Y Z
A1 i011.0 -21.0 -22.0
2 i011.0 -22.0 8.0
A2 ISA 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
7i011.0 22.0 8.0
8 i011.0 21.0 -23.0
9 1013.0 0.0 16.0
Top of A1 1017.0 -21.0 -22.0
Top of A2 1019.0 -22.0 8.0
Top of A7 1019.0 22.0 8.0
Top of A8 1020.0 25.0 -8.0
Top of A9 1016.0 0.0 16.0
Between PGA & A9 1014.0 0.0 8.0
B1 1050.0 -27.0 39.0
2 1039.0 -38.0 37.0
3 1031.0 -28.0 40.0
4 1031.0 -20.0 40.0
5 1031.0 -8.0 39.0
6 1031.0 13.0 39.0
8 1024.0 -38.0 37.0
L2 1059.0 -44.0 14.0
3 1048.0 -47.0 12.0
RI 1072.0 26.0 21.0
2 1072.0 26.0 14.0
3 1072.0 26.0 9.0
4 1075.0 28.0 3.0
5 1059.0 44.0 15.0
6 1048.0 46.0 29.0
8 1052.0 46.0 12.0
ii 1038.0 47.0 26.0
13 1024.0 45.0 -26.0
Ul 1033.0 23.0 -50.0
2 1033.0 -23.0 -50.0
3 1033.0 -36.0 -44.0
4 1038.0 39.0 -43.0
L. H. Crew Station 1043.0 -24.5 -11.9
Cir. Crew Station 1043.0 0.0 -ii.9
R. H. Crew Station 1043.0 24.5 -11.9
Amendment
7/19/71
110
3.1-55 SNA-8-D-027(III)REV 3
TABLE 3.1-9 (CONCLUDED)
Amendment 1I0
7/19/71
MISSION J-i COMMAND MODULE STOWAGE VOLUME CENTROID
The following stowage locations have unique volume centroids not associated
with stowage volumes.
NOMEN CLATU RE LO CAT ION X Y Z
G&N Signal Cond. Panel LEB
Display Keyboard LEB
Sleep Restraint Assy - Rt. & Center Aft UEB
Sleep Restraint Assy - Left Aft UEB
Entry Locations
Sleep Restraint - RH & Center
ITLSA- IV (CMP)
Food Container
Food Container
Food Container
Fecal Stowage Container
PGA Container
Entry Location
Forward Hatch Container
Container, RI2
(In-flight Location)
Helmet Stowage & Accessory
Bags (In-flight Location) - LH
Helmet Stowage and Accessory
Bags (In-flight Location) - Ctr.
Helmet Stowage and Accessory
Bag (In-flight Location) - RH
CO2 Absorbers (2)
CO2 Absorbers (4)
CO2 Absorbers (4)
CO2 Absorbers (4)
CO2 Absorbers (4)
CO2 Absorbers (4)
CO2 Absorbers (4)
CO2 Absorbers (4)
First 8.0 ib CO2 Absorbed
Second 16.0 ib C02 Absorbed
Remainder CO2 Absorbed
1069.0 25.0 29.0
1060.0 26.0 32.0
1018.0 23.0 -50.0
1018.0 -23.0 -50.0
Top of Area A8 1020.0 25.0 -8.0
On RH & Ctr.
Sleep Restraint 1020.0 25.0 -22.0
L3 1048.0 -47.0 12.0
BI 1050.0 -27.0 39.0
A7 i011.0 22.0 8.0
RHEB 1039.0 47.0 12.0
On Aft Bulkhead 1015.0 0.0 -20.0
Under Ctr. Couch
Aft Bulkhead 1015.0 0.0 -6.0
Under LH Couch 1018.0 -24.5 -15.0
RH Girth Ring 1034.0 41.0 -21.0
U2 1033.0 -23.0 -50.0
BI 1050.0 -27.0 39.0
L3 1048.0 -47.0 12.0
In ECU 1031.0 -48.3 19.6
A3 1016.0 -24.0 28.0
A4 1015.0 -7.0 28.0
A5 1015.0 9.0 28.0
A6 1017.0 26.0 28.0
A9 1013.0 0.0 16.0
B5 1031.0 -8.0 39.0
B6 1031.0 13.0 39.0
Order of Loca-
tions Used in
Sequential Mass
Properties Tables
for CO2 Absorbed
B5 1031.0
(B6, A9) 1022.0
Composite Loca-
tion 1017.4
-8.0 39.0
6.5 27.5
-4.4 27 .i
3.1-56
L L L, L1
SNA-8-D-027 (III) REV 3
Lf_ L
AREA
AIA
AIB
AIC
AID
AlE
AIF
AIG
AIH
AIJ
AIL
AIK
AIDA
AIDB
AIDC
AIDD
A2
A3
A5
A6
A7
A8
A9
AIO
All
AI2
AI3
AI4
AI5
FIA
FIB
FIC
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FIF
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TABLE 3.1-9.1
Amendment 1 I0
7/19/71
MISSION J-i LUNAR MODULE STOWAGE VOLUME CENTROIDS
LM-10
DESCRIPTION X Y Z
Flight Data File
PLSS-Recharge Star
ICG, Elect. Harness
In-Flight ISA
OPS-Upper
OPS-Lower
Jett Bag (4) & CLSRC
PPK & Standard Flag
LM Medical Pkg
Boots & Purge Vlv-Upper
Boots & Purge Vlv-Lower
In-Flight ISA Items
DSEA
ISA-Aft Eng. Cover
BSLSS, ETB, PLSS Tool Carrier
Water Disp/Fire Ext.
ECS Umbilicals
Bungee Cord
LM Food Assy
ECS LIOH Can.-Eng. Cover
ECS LIOH, PLSS LIOH-190 Mod.
RCU (2)
Docking Drogue
500 MM Lens/70 MM Cam Assy
Bungee Cord
Feclal Wet Wipes
Lightweight Headset
Urine Recpt.
Tape & Utility Towel Check
CWG Elect. Harn.& Tiss. Disp.
Emesis, Urine Coll., Defec.
Hammocks & Towels
COAS Bulb & Filter
UCTA Clamp
Empty
Drogue-Abandon LM
COAS-Manned Pos.
280.0 -19.0 13.5
263.5 -20.6 14.9
240.5 -15.3 13.3
270.3 -15.0 19.0
265.9 -20.7 -6.0
257.4 -20.7 -6.0
257.5 -20.0 -18.0
265.9 -20.0 -18.0
273.7 -20.4 1.2
281.0 -20.0 -8.5
273.7 -20.0 -8.5
270.3 -15.0 19.0
260.0 -37.0 28.0
280.0 0.0 -i0.0
221.8 -I.0 29.5
278.5 -ii.0 23.0
250.0 11.5 31.0
272.6 14.8 17.3
288.0 0.0 -24.0
250.0 8.0 -11.8
262.4 19.8 4.2
272.0 0.0 -18.0
300.0 0.0 0.0
239.6 -5.5 -14.8
257.0 -30.0 27.5
244.5 -36.6 31.4
235.5 -35.5 38.5
242.5 -35.5 38.6
242.8 -35.4 44.7
237.9 -33.6 55.0
235.5 -37.6 46.6
228.0 -40.2 43.2
229.5 -35.5 39.0
229.5 -35.5 35.0
237.8 -37.8 31.5
218.5 -22.0 43.4
292.0 -21.0 38.6
3.1-57 SNA-8-D-O27(III)REV 3
TABLE3.1-9.1 (CONCLUDED)
MISSION J-i LUNAR MODULE STOWAGE VOLUME CENTROIDS
LM-IO
Amendment 110
7/19/71
AREA DESCRIPTION X Y Z
F4 COAS Earth Launch 282.2 -21.0 66.6
F5 16 MM Camera-DAC 286.0 17.8 66.6
F6A,B,C ISA-Earth Launch 270.3 0.0 52.8
FTA 16 MM Camera Wedge Brkt 238.0 38.0 49.8
F7B Monocular 238.4 38.6 46.0
FTC 70 MM Camera Assy 242.8 38.0 41.0
F7D 70 MM Film Magazines (4) 238.0 38.0 38.4
F7E Neck Ring & LGC Adapters 243.2 38.0 31.2
FTF Camera Mount Brkt & Wrench 238.0 38.0 31.6
FTG AOT Eyeguard & Filter 227.9 33.0 31.8
FTH 16 MM Cam Fuse Assy w/Bag 237.7 38.3 45.5
F7J Cont. Tiedn Webbing, Etc. 231.5 35.4 41.8
F7K Sample Scale 222.6 32.3 42.7
F7L 16 MM Film Magazines 231.8 36.0 47.3
F7M Empty 225.7 32.3 53.4
FTN LEC-Waist Tether Kit 238.0 38.0 53.1
F7P 70 MM Film Mags (3) 241.0 38.0 53.4
F8 LMP Helmet Bag 221.0 18.0 51.0
F9 PLSS-Floor 219.9 -1.3 44.5
FIO CDR Helmet Bag 221.0 -18.0 51.0
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TABLE 3. i-i0
CONSUMABLES LOADING REqUIKEMENTS AND TOLERANCES
Amendment 112
7/24/71
MISSION J-i
SPS PROPELLANT
I D,es_ure (PSIA)
tuel Oxidizer
110±4 110±4
Temperature (°F)
Fuel Oxidizer
70+_5 70±5
quantity 1_ _dout (%)
Fue i Oxid i ze r
See Figure See Figure
4.1-3 4.1-4
SPS Propellant Load (Ib)
]Load
2Trapped Outside Tanks
Tanked
2Trapped Inside Tanks
3Nomlnal Deliverable
Loading Requiremen, t
Fuel Oxidizer
25092.0
123.7
24968.3
171.5
24796.8
Fue I
15664.0
78.6
15585.4
67.6
15517.8
15704.0
78.6
15625.4
67.6
15557.8
Actual
Oxidizer
25035.6
123.7
24911.9
171.5
24740.4
_Service Module RCS Propellant
Secondary Fuel - Quads A, B, C, D - See Loading Window - Figure 4.3-1.
Primary Fuel - Quads A, B, C, D - See Loading Window - Figure 4.3-2.
Primary and Secondary Oxidizer - Quads A, B, C, D - See Loading Window -
Figure 4.3-3.
5Command Module RCS Propellant
Fuel - System A and B - See Loading Window - Figure 4.3-4.
Oxidizer - System A and B - See Loading Window - Figure 4.3-5.
9Helium and Nitrosen
Consumable
Helium - SPS Bottle_
Helium - Fuel Tanks
Helium - N20 hTanks
Helium - SM/RCS
Quads A
Quads B
Quads C
Quads D
Helium - CM/RCS
System A
System g
Nitrogen - SM
Primary
Secondary
Loadin_
Pressure
(PSIA)
3600
178
178
4150
4150
4150
4150
4150
4150
2500
2500
Te_
(°r)
70
70
70
70
70
70
70
70
70
85
85
Requl remen t
Weight
(Ib)
87.6
5.4
6.0
iJ
Actual
Earth Launch Pressure Temp
Weight (Ib)
87.6
6.0
1.0
1.3
(PSIA) (°F)
3590 87
181 74
181 72
4190 71
4200 72
4190 71
4220 72
4160 69
4110 65
2550 70
2550 70
3.1-121 SNA-8-D-027 (III) REV 3
!1 !1 I/ L l_ l: l/ L E H I,,: i Uli H E L L L L
TABLE 3.1-i0 (CONTINUED)
ConDand Module Water and GOX
Amendment iI '
7/2/i/7]
Waste Water6
Potable Water ?
C M/GOX
Pressure
(pSIA)
900±50
Loading Requirement
Weight (ib)
3.7
Earth Launch
Weight (ib)
35.0
30.0
. 6.7 (Entry)
8Service Module Hydrogen and Oxygen
Hydrogen
Tank 1
Tank 2
Tank 3
Oxygen
Tank 1
Tank 2
Tank 3
Loading Req. Per Tank
,,,(pounds)
29.3
29.3
29.3
330.1
330.1
330.1
Earth Launch Weight '
Per Tank (lb)
27.6
27.6
27.6
316.6
316.6
316.6
Actual
Rer Tank (ib)
27.3
25 .6
27.3
313.9
313.9
313.9
NOTES:
llndicated propellant load is based on nominal pressure and temperature
prior to actual loading. This number will be updated after loading
is accomplished.
2See Section 4.1 for explanation of trapped SPS propellant.
3See Table 3.1-13 for loading uncertainties.
4See Section 4.2 for SM/RCS loads and uncertainties to be used in His-
sion Planning. Actual SM/RCS loads and uncertainties will be published
in Table 3.1-15.
5See Section 4.2 for CM/RCS loads and uncertainties to be used in Mis-
sion Planning. Actual CM/RCS loads and uncertainties will be published
in Table 3.1-14.
6Launch Rule Redlines determine lift-off values.
7Launch Rule Redlines determine lift-off values.
8Launch Mission Rules will determine minimum lift-off quantities for
H2 and 02 .
9CSM helium and nitrogen should be loaded in accordance with loading
windows contained in CSM/LM Spacecraft Operational Data Book, Volume I,
Part 2, SNA-8-D-027(1) P2.
3. ]-] 22 SNA-8-D-027(III)REV 3
UII E E L: E L L E I; L; E h' U U /a
I
L6___
i
D
E
N
S
I
T
Y
LB/FT 3
TABLE 3.1-11
SPS PROPELLANT LOAD CALCULATION
FUEL
1. Enter SPS Quantity Readout at 110 PSIA (Table 3.1-12 100.8
Item C - Percent)
2. Use Fisures 4.1-3 and 4.1-4 to obtain pro-
pellant load for above quanClCy readout,
3. Nominal propellant density at loading temperature
(use temperature - density graph below) (ib/ft3) 56.46
4. Cubic feet of propellant (item 2 divided by item 3) 277.86
5. Calculated density from Table 3.1-12 item f (lb/ft 3) 56.37
6. Adjustment due to PUGS zero adjust (pounds)
?. Resulting actual propellant load (item 4 times
item 5, less item 6) (pounds)
15,688.0
15,664.0
SPS
Oxidizer
.[
,IIIT_
90. .
90. "_
90. •
-:L_2
T
90 .... --
90.°5el.
'-- --
89.9 _56.
_ tt_
ii
89.8 _56.
89.7: g6 -
+.. ,FH
SPS
FUEL
OXIDIZER[[
SPS Propellant Temperature/Density Graph
at 110+5 PSIA
Temperature Degrees F
Amendment llO
7/19/71
OXIDIZER
i00.7
25,042.0
89.97
278.33
89.94
25,035.6
3.1-123 SNA-8-D-027(III)REV 3
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3.1-125 SNA-8-D-O27(III)REV 3
ILl ILl JU _LLE L L ld L: i_ L; li _ EL,' L L ;.
TABLE 3.1-13
SPS PROPELLANT UNCERTAINTIES
Amendment 1 I0
7/19/71
F • ITEM FUEL OXIDIZER
LOADING UNCERTAINTIES
Tank Volume
Temperature Gauge (±2.0°F)
Standpipe Height
Propellant Gauge (±0.35% of Gaugeable)
Density Measurement (i)
Batch Density (I)
Loading Pressure (i)
TOTAL RSS
m, ,
Loading Specification (I) (2)
Tolerance on Propellant Temperature
of 7iiBht Load
TOTAL LOADING UNCERTAINITY
(ib)
±24
±18
±6
±54
+- 5
±0
±8
± 63
±123
i
±0
+0
0
_+123
(ib)
±39
±46
±i0
±86
± 5
± 0
±14
+_106
±0
+0
-0
NOTES : (i)
(2)
Data will be known after loading is accomplished.
Loading specification is an allowable tolerance about
nominal, this number is added to the loading uncertainity
variable.
3.1-126 SNA-8-D-O27(III)REV 3
LIE._
Amendment 110
7/19/71
TABLE 3.1-14
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 OXIDIZER
Tank A Tank BTank A Tank B
A. Tank Volume @0.0 PSIA (in 3) 1474.7 1471.7 1786.9 1791.0
B. Liquid Line Volume (In 3) 21.0 17.4 17.1 16.4
C. Total A + B (in 3) 1495.7 1489.1 1804.0 1807.4
D. Initial Weight in Bleed Unit
Prior to Loading (Ib) 149.0 103.8 195.O 115.2
E. Final Weight in Bleed Unit
After Loading (ib) 104.8 59.6 116.7 36._
44.2 78.3
F, Propellant Load (item D less
than E Weigh Tank) 44.2
G. Propellant Load by P.V. 44.2 44.3 77.6
7t_.3
7t_.4
H. Loading Temperature (°F)
72 72 69 69
I. Specification Propellant
Load @ 70±5°F (ib) 88.4 156.6
J. Total f24/RCS Propellant
Load from Item G above (ib) 88.5 156.0
13.3 23.1
K. Maximum Trapped Propellant (Ib)
L. Nominal Deliverable (ib) 75.2 132.9
3.1-127 SNA-8-D-027 (III) REV 3
Li--
TABLE3.1-15
SERVICEMODULERCSLOADINGSUMMATION
AmendmentII0
7/19/71
This table will be completed when loading is accomplished. For Mission Plan-
ning, reference should be made to Section 4.2, for nominal load, loading
tolerances, and nominal deliverable propellants.
_uad A (Ib) quad B (ib)
Secondary Fuel &h._ Secondary Fuel 40.3
Primary Fuel 69.0 Primary Fuel 69.O
Total Fuel 109.3 _0.7 Total Fuel 109.3 '0.7
Maximum Trapped 2.1 Maximum Trapped 2.1
Nominal Deliverable 107.2 Nominal Deliverable 1072
Total Oxidizer 225.8 '2.3 Total Oxidizer 224.0
Maximum Trapped 4.5 Maximum Trapped 4.5
Nominal Deliverable 221.3 Nominal Deliverable 219.5
"2.3
quad C(ib) quad D (ib)
Secondary Fuel 40.3 Secondary Fuel 40.3
Primary Fuel 69.4 Primary Fuel 6q.2
Total Fuel 109,7 *0.7 Total Fuel 109.5 *0.7
Maximum Trapped 2.1 Maximum Trapped 2.1
Nominal Deliverable 107.6 Nominal Deliverable 107,4
Total Oxidizer 224.6 *2.3 Total Oxidizer ._2.1&.I *2.3
Maximum Trapped 4,3 Maximum Trapped 4.5
Nominal Deliverable 220.1 Nominal Deliverable PIQ 6
Total SM/RCS Propellant Load (ib)
Total Fuel A_7.R ,1.4 Total Oxidizer _898.5 *4.6
Maximum Trapped 8.4 Maximum Trapped 18.0
Nominal Deliverable 429.4 Nominal Deliverable SSO.5
3.1-128 SNA-8-D-027(III)REV 3
TABLE 3.1-16
LM-IO CONSUMABLE LOADING REQUIREMENTS
LM-IO APS PROPELLANT
Fu_l (ib)
Propellant Load 2011.4
Trapped Outside Tanks 5.9
Tanked 2005.5
Trapped Inside Tanks i0.0
Nominal Deliverable 1995.5
Outage TBD
Total APS Propellant
Amendment 110
7/19/71
Oxidizer (Ib)
3225.6
8.3
3217.3
27.7
3189.6
TBD
TBD
The following table should be used to determine the amount of propellant
to be off-loaded from afull condition to arrive at the indicated load.
The allowable tolerance for the calculated off-load is ±0.5 pounds per
weigh tank.
A. Final tank pressure at overfill (PSIG)
B. Propellant loading temperature (°F)
C. Nominal overfill quantity (ib)
D. Correction for tank pressure (ib)
Fuel - 0.09 (Item A-40)
Oxidizer =0.15 (Item A-40)
IE. Correction for loading temperature (ib)
Fuel = 1.16 (Item B-65)
Oxidizer - -2.84 (Item B-65)
2F. Measured density (GM/CC)
2G. Nominal density (GM/CC)
H. Delta density (GM/CC) (Item F-G)
31. Correction for measured density
Fuel - 2300 (Item H)
Oxidizer - 2300 (Item H)
J. Propellant in GSE
K. Overfill quantity (C+D+E+I+J)
L. Target loading
M. Quantity required to fill KS manifolds
N. Quantity to be off-loaded (Item K-L-M)
60.3
69.0
2069.8
1.83
50.3
70.25
3315.6
i .55
-4,64 -14.91
0.8979 1.4819
0.8994 1.4824
-0.0015 -0.0005
-3.45 -I .15
1.6 4.8
2065.1 3305.9
2014.2 3225.7
i0.0 15.8
40.9 64.5
NOTES: q
ILoading temperature correction will always be negative.
2To calculate the nominal density solve the following equation where T =
temperature in °C of the measured density (usually 4°C for oxidizer and
25°C for fuel). This equation is valid for 14.7 PSIA. Therefore, the
measured density must also be at 14.7 PSIA.
Nominal fuel density =0.922904-0.0009377 (°C)
Nominal oxidizer density - 1.491539-0.0022832 (°C)
3Correction for measured density ,my be either positive or negative.
3.l-129 SNA-8-D-O27(III)REV 3
TABLE3.1-16(CONTINUED)
LM-10 CONSUMABLE LOADING REQUIREMENTS
LM-IO DPS PROPELLANT
Amendment 110
711g/71
Fuel (ib_ Oxidizer (ib)
Propellant Load 7537.6 12023.9
Trapped Outside Tanks 27.3 48.9
Tanked 7510.3 11975.0
Trapped Inside Tanks ]0.5 23.5 ....
Nominal Deliverable 7499.8 I1951.5
Outage TBD TBD
Total DPS Propellant TBD
IEI.
2FI.
2GI.
Nl.
311.
The following table should be used to determine the amount of propellant to be
off-loaded from a full condition to arrive at the indicated load. The allow-
able tolerance for the calculated off-load is ±0.5 pounds per weigh tank.
AI. Final tank pressure at overfill (PSIG) 47.4 54.0
BI. Propellant loading temperature (°F) 67.8 67.45
CI. Nominal overfill quantity (ib) 7606.6 12182.5
DI. Correction for tank pressure (ib) 2.44 7.56
Fuel =0.33 (Item A1 -40)
Oxidizer =0.54 (Item A1 -40)
Correction for loading temperature (lb) -i1.9 -25.73
Fuel =-4.25 (Item B1 -65)
Oxidizer = -10.5 (ltem B1 -65)
Measured density (GM/CC) 0.8979 1.4819
Nominal density (GM/CC) 0.8994 1.4824
Delta density (GM/CC) (Item Fl-ltem G1) -0.0015 -0.0005
Correction for measured density -12.6 -4.2
Fuel =8400 (Item H1)
Oxidizer =8400 (Item HI)
J1. Propellant in GSE 2.3 3.8
KI. Overfill quantity (Cl+Dl+El+ll+Jl) 7586.8 12163.9
L1. Target loading 7547.7 12___023.7
MI. Quantity required to fill RCS manifolds (APS only) xxxxxxx xxxxxxx
NI. Quantity to be off-loaded (Items KI-LI-MI) 39.1 140.2
NOTES:
ILoading temperature correction will always be negative.
2To calculate the nominal density solve the _ollowing equation where
T - temperature in °C of the measured density (usually 4°C for oxidizer
and 25°C for fuel). This equation is valid for 14.7 PSIA. Therefore,
the measured density must also be at 14.7 PSIA.
Nominal fuel density = 0.922904-0.0009377 (°C)
Nominal oxidizer density =1.491539-0.0022832 (°C)
3Correction for measured density may be either positive or negative.
3.1-130 SNA-8-D-027(III) REV 3
TABLE 3.1-16 (CONTINUED)
LM-10 - RCS PROPELLANT 42 )43 )
System A Fuel
System A Oxidizer
System B Fuel
System B Oxidizer
Required Ullage Requirement (in _)
Load (Ib) 5Minimm _ Maximum _
107.4±0.9 152.5 164.5
208.2±1.9 267.0 279.0
107.4±0.9 152.5 164.5
208.2ZI.9 267.0 279.0
FUEL OXIDIZER
Propellant Load 214.8 416.4
Trapped Outside Tanks I0.0 15.8
Tanked 204.8 400.6
Trapped in Tanks 4.2 8.0
Nominal Deliverable 200.6 392.6
_Act_ml _
Load (Ib)
107.4
208.2
107.4
208.2
Amendment 112
7/24/71
tActual_
Ullage (in 3)
172.0
267.0
151.0
255.8
LM-10 - Helium & Nitrogen
Consumable
Helium - APS tank #i (6)
-APS tank 02 (6)
- RCS tank #I (6)
- RCS tank #2 (6)
- DPS (SHe)
- DPS (Ambient)(6)
Nitrogen - Ascent
- Descent
- Descent
Nominal Loading Requirement Actual
Pressure 'Temp Weight Pressure Tamp
4PSIA) ("F) 41b) (PSIA) 4 "F)
3050 70 6.6 3142 68.9
3050 70 6.6 3137 69.1
..3050 70 1.05 3057 69.7
3050 70 1.05 3043 69.7
80+2 N/A 51.2
1600 70 1.1 1625 70.6
+0.1
0.6
Weight
(lb)
-0.6
LM-IO - Water &COX
Consumable
Ascent Water - tank #I
- tank #2
Descent Water - tank #I
-tank #2
Ascent COX - tank #i (6)
-tank #2 (6)
Descent GOX - tank #i (6)
-tank #2 (6)
Nominal Loading Requirement Actual
Pressure Weight Pressure Weight
(PSIA) (Ib) 4PSIA) 41b)
S/A (7) N/A 42.5
S/A (7) N/A 42.5
N/A (7) N/A 207.0
N/A (7) N/A 207.0
830 2.4 845 (71°F)
83o. 2.4 850 (71°F)
2700 46.9 2620 (72.1°F)
27oo 46.9 2620 (72.1"F)
NOTES:
lSee Table 3.1-17 for actual propellant load calculation.
2See Section 5.6 for explanation of trapped propellants.
3See Table 3.1-18 for loading uncertainties.
_PV ullage calculation should be 166.5+50 cubic inches for LM/RCS fuel and
280±50 cubic inches for LM/I_S oxidlz_r per tank.
5LM/RCS required load includes propellant required to fill RCS manifolds
to thruster valves. See Table 3.1-16. See Section 5.6 for trapped
propellants.
6The indicated items should be loaded in accordance with loading windows
contained in the CSM/LM Spacecraft Operational Data Book, Volume If,
Part 2, SNA-8-D-027PT2.
7LM-10 Descent Water shall be loaded to provide 408-0.0+10.0 pounds at
Earth Launch. LM-IO ascent water shall be loaded Co provide 85 pounds
at earth launch. Initial load will be determined by the prasure-
temperature relationships provided in Table 3.1-16.1.
3.1-131 SNA-8-D-O27(III)REV 3
I
Amendment 110
7/19/71
TABLE 3.1-16.1 ECS WATER LOADING DATA LM-IO
DESCENT TANKS ASCENT TANKS
T Po PFI* PFN PF2 PFI PF2
°F PSIA PSIA PSIA PSIA PSIA PSIA
60 11,607
61 11,629
62 11,651.
63 11,674
64 11,695
65 11,718
66 11,741
67 11,763
68 11,785
69 11,808
70 11,830
71 11,852
72 11,875
73 11,897
74 11,919
75 11,942
76 11,964
77 11,986
78 12,009
79 12,031
80 12,053
22,212 39,245 39,501
22,254 39,321 39,587
22,306 39,396 39,671
22,340 39,472 "' 39,757
22,383 39,547 39,842
22,425 39,623 39,929
22,469 39,698 40,014
22,511 39,774 40,102
22,553 39,849 40,188
22,597 39,924 40.275
22,639 40,000 40,363
22,681 40,075 40,451
22,725 40,151 40,540
22,767 40,226 40,628
22,S09 40,302 40,71S
22,S53 40,377 40,807
22,895 40,453 40,897
_2,937 40,528 40,987
22,982 40,604 41,079
23,024 40,679 41,170
23,066 40,755 41,262
46,427 46,683
46,516 46,782
46,605 46,880
46,695 46,980
46,784 47,079
46,873 47,179
46,963 47,279
4'7,052 47,380
47,141 47,480
47,231 47,582
47,320 47,683
47,409 47,785
47,499 47,888
47,588 47,990
47,677 48,093
47,767 48,197
47,855 48,299
47,945 48,404
48,035 48,510
48,124 48,615
48,213 48,720
NOTE: 1.
2.
Po - Initial Gas Pressure Setting
P}I - Pressure Required when Loading 'Killer" Solution.
PFN - Pressure Required for D/S N. Final Fill.
PF2 Pressure Required After Partial Drain and Refill.
NASA- MSC
Primary Reading of PFI using 0-60 psia Transducers verified by GF 4501 P.
* PFI -GF 4501 P + HEAD if GF 4501 P low, increase to required pressure.
D/S Tank #i HEAD - 2.502 PSI
D/S Tank #2 HEAD - 3.372 PSI
3. Po, PFI*, PFN, PF2, PFI values as shown above, may have a tolerance of
(+) one (i) PCM Bit as read on CRT.
MID 1 Bit
GF 4501 P .I psia
GF 4500 P .24 psia
GP 0500 P.24 psia
GF 4502 P .24 psta
GF 4503 P .24 psia
4. This table provides nominal descent loading of 212 lb/tank and ascent tank
loading of 42.5 lb/tank.
3.1-132
ENA-8-D-O27CTII)REV 3
11 !/ L E L L E L E U 12 L, LL
TI
&.
1.
12.
13.
14.
5.
, 6.
7.
8.
9.
1i0.
Iii.
112.
13.
14.
15.
Amendment 110
TABLE 3.1-17 7/19/71
LOAD CALCULATION
APS PROPELLANT Fuel Oxidizer
Full tank - Item K, Table 3.1-16 (ib) 2065.1
Density of off-load tables at loading
temperature and pressure (ib/ft 3) N/A N/A
Propellant volume (divide item ] by
item 2. (it 3) N/A N/A
Measured density (from Tablp 3.1-19)
(ib/ft 3) N/A N/A
Resulting full tank load (Ib) 2065.1 3305.9
Off-load amount (Ib) 43.7 64.5
Propellant required to fill RCS manifolds
(ib) i0.0 15.8
Propellant load (Ib) 2011.4 3225.6
DPS PROPELLANT
Full tank - Item K1 Table 3.1-16 7586.8 12163.9
Density of off-load tables at loading
temperature and pressure (ib/ft 3) N/A NIA
Propellant volume (divide Item 9by Item
i0 )(it 3) N/A N/A
Measured density (from Table 3.1-19)
(Ib/ft 3) N/A N/A
Resulting full tank load (ib) 7586.8 12163.9
Off-load amount (ib) 49.2 140.0
Propellant load (ib) 7537.6 12023.9
RCS PROPELLANT
P. V. Calculations Fuel Oxidizer
Tank A Tank B Tank A Tank B
NOTE:
A. GSE Volume (in 3)
B. Initial Ullage Pressure
(PSIG)
C. Initial GSE Pressure
(PSIC)
D. Final CSE - S/C Pressure
(PSIG)
E. Ullage Volume (in 3) -Solve
the following equation by
substituting the values in
the indicated steps.
(D-C) (A)
Ullage Volume -B-D
18.2 33.5 17.8 29.7
33.4 33.5 35.2 34.8
1.0 1.0 0.0 0.2
30.3 27.6 33.0 31.2
172.0 i___551.0 267______:.Q.255.8
IThese items will be completed only if a density sample is not
made prior to loading. If a density sample is made prior to
loading, then the items will be left blank.
*Initial APS & DPS Fuel Offload was based on a density of 0.8991
instead of 0.8979 gm/CC.
3.1-133 SNA-8-D-027(III)REV 3
TABLE 3.1-18
LM-10 PROPELLANT LOADING UNCERTAINTIES
LM-10 APS PROPELLANT
Vent Line Volume
Tank Volume
Pressure Measurement (+-5 PSIA)
Temperature Measurement (+_I.5°F)
Measured Density
Weight Measurement
iLoading Tolerance
Total Loading Uncertainity
Fuel (ib)
+-0.2
+-0.8
-+0.5
_+1.7
+-0.7
_+0.5
-+0.0
-+4.3
Amendment II0
7119171
Oxidizer (ib)
-+0.3
+1.3
_+0.8
+_4.3
+-0.5
+-0.5
+0.0
-+7.7
+0.3
+-5.96
-+2.77
+-15.76
-+1.70
-+0.5
-+0.0
+-27.0
LM-10 DPS PROPELLANT
Vent Line Volume
Tank Volume
Pressure Measurement (-+5 PSIA)
Temperature Measurement (I.5°F)
Measured Density
Weight Measurement
iLoadlng Tolerance
Total Loading Uncertainity
LM-10 RCS PROPELLANT
Loading Temperature
Ullage Calculation
Tank and Manifold Volume
Total
+-0.2
-+3.62
-+1.70
+-6.49
-+2.55
+-0.5
+-0.0
-+15.1
+-0.6 +-1.8
+-0.4 +-0.6
+-0.8 -+1.4
-+1.8 +-3.8
iThese will be known quantities after loading is accomplished.
3.1-134 SNA-8-D-027 (III) REV 3
TABLE 3.1-19
I_4-I0 APS PROEPLLANT LOADING PARAMETERS
(To Be Completed by KSC at Loading)
Loading Pressure - PSIA
_58 Fuel
Loading Temperature - Fill Line - Degrees F 258 Oxidizer
_ITT 59 Fuel
Loading Temperature - Return Line - Degrees t'[TT259 Oxidizer
_GP0718 Fuel
Loading Temperature - Tank - Degrees F [GPI218 Oxidizer
Amendment 110
7/19/71
Fuel Oxidizer
75.0 65.0
67.8 70.3
70.2 70.2
68.2 69.4
Number of Times Weigh Tank Used (Flow Meter Not Used) 1
Total Pounds Off-Loaded Using Neigh Tank (Flow Meter Not Used) 43.7
Pounds Off-Loaded Using Flow Meter (Weigh Tank Not Used) N/A
Measured Fuel Density @ 25°C; @ 14.7 PSIA GM/CC 0.8991
64.5
N/A
_ 1.4819
Measured Oxidizer Density @ 4eC; @ 14.7 PSIA GM/CC
3.]-]35 SNA-8-D-027(III)REV 3
TABLE 3.1-19 (CONTINUED)
LM-10 DPS PP4DPELLANT LOADING PARAMETERS
Loading Pressure - PSIA
ITT 58 Fuel
Loading Temperature - Fill Line - Degrees F ITT258 Oxidizer
_TT 59 Fuel
Loading Temperature - Return Line - Degrees FITT259 Oxidizer 68.2
_#CQ3718 Fuel
Loading Temperature - Tank One - Degrees _GQ4218 Oxidizer 68.2
_IGQ3719 Fuel
Loading Temperature - Tank Two - Degrees -IGQ4219 Oxidizer 68.6
Number of Times Weigh Tank Used (Flow Meter Not Used) 1
Total Pounds Off-Loaded Using Weigh Tank (Flow Meter Not Used) 49.2
Pounds Off-Loaded Using Flow Meter (Weigh Tank Not Used) N/A
Measured Fuel Density @ 25"C; @ 14.7 PSIA GM/CC
Measured Oxidizer Density @ 4"C; @ 14.7 PSIA GM/CC
Amendment Il0
7/19/71
Fuel Oxidizer
62.1 68.7
67.3 66.6
68.3
68.6
68.6
1
140.0
N/A
0.8991
1.4819
3.l-136 SNA-8-D-027(III)REV 3
I/
Amendment II0
7119/71
MISSION J-i MASS PROPERTY DATA TABLES
Table 3.1-20 presence the CSH-112/LH-10(docked) mass properties, in Apollo
coordinates, as a function of spacecraft weight for L.O.I.
SM/SPS burn.
Table 3.1-21 presents the CSM-112/I_4-10 (docked) mass properties, in Apollo
coordinates, as a function of spacecraft weight for the
D.O.I. SM/SPS burn.
Table 3.1-22 presents the CSM-112 mass properties, in Apollo coordinates,
as a function of CSMwetght for the Circulartzatton ISM/SPS
burn.
Table 3.1-23 presents the CSM-II2 mass properties, in Apollo coordinates,
as a function of CSM weight for the Plane Change ISH/SPS
burn.
Table 3.1-24 presents the CSM-II2 mass properties, in Apollo coordinates,
as a function of CaM weight for the T.E.I. SM/SPS burn.
Table 3.1-25 presents the LM-10maas properties, in LM coordinates, as a
function of I/4 weight for the P.D.I. DPS burn,
Table 3.1-26 presents the LM-10 ascent stage mass properties, in LM coordinates,
as a function of weight for the lunar liftoff APS burn.
Table 3.1-27 presence the LM-lOmass properties, in LM coordinates, as a
function of LM weight for the T.P.I. to docking LM/APS burn.
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9115171
SUPPLEMENTARY DATA APPLICABLE TO SEQUENTIAL MASS PROPERTIES TABLES
General Comments to be applied to Tables 3.2-1 through 3.2-8:
Inertia data dispersions are +10%.
Dispersions shall be used as 3o deviation values.
All initial propellant weights are total tanked.
The (+) or (-) sign following the name of an item indicates that the
item is added to or subtracted from the preceding total.
Table 3.2-1
SM/SPS gimbal angles for SPS abort sequence are: Pitch =-0.470
Yaw = 1.898
Table 3.2-2
LM propellants are in high end of the tanks, (greatest X-c.g. station),
for all docked configuration where the CSM is the controlling vehicle.
The Mass Spectrometer and Gamma-Ray Spectrometer are shown deployed after
each SPS firing following D.O.I. For all other summations the M.S. and
G.R. Spectrometers are no___/_tdeployed. The following are the individual
mass properties for the M.S. and G.R. Spectrometers in Apollo Coordinates.
Weight X-Bar Y-Bar Z-Bar
(ib) (in) (in) (in)
Gamma-Ray 45.4 865.1 33.0 -57.0
Retracted
Gamma-Ray 28.0 865.1 231.3 -312.4
Deployed 17.4 865.1 132.2 -184.7
Mass Spectrometer 47.4 863.1 55.8 -40.5
Retracted
Mass Spectrometer 27.4 863.1 341.7 -149.4
Deployed 20.0 863.1 198.8 -94.9
Tables 3.2-7 and 3.2-8
CSM and LM consumables changes are presented in Tables 3.2-7 and
3.2-8, respectively.
L:
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SNA-B-D-O27(III) REV 3
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SNA-8-D-0Z7(III) REV 3
3.2-13
TABLE 3.2-3 (CONTINUED)
LM-II CONTINGENCY MASS PROPERTIES
To Be Supplied.
3.2-14 SNA-B-D-O27(III)REV 3
E li E L 2 i- k_
\TABLE 3.2-3.1
LRV MASS PROPERTIES
FIRST TRAVERSE DEPARTURE
To Be Supplled.
3.2-15 SNA-8-D-027(III)REV 3
Amendment 114
9/15/71
TABLE 3.2-3.1 (CONTINUED)
LRV MASS PROPERTIES
FIRST TRAVERSE RETURN
To Be Supplied.
U L L E
3.2-16
E L I: E li
SNA-8-D-027 (III)REV 3
g 1i E L %
L£_
Amendment114
9/15/71
TABLE 3.2-3.1 (CONTINUED)
LRV MASS PROPERTIES
SECOND TRAVERSE DEPARTURE
'To Be Supplied.
II I/ I/ E L E L L
3.2-17
E E L _ K
SNA-8-D-027 (III)REV 3
EELLLi_
Amendment 114
9/15171
TABLE 3.2-3.1 (CONTINUED)
LRV MASS PROPERTIES
SECOND TRAVERSE RETURN
To Be Supplied.
L L E L I:
SNA-B-I)-O27(III)REV 3
1; E E_ ,_
Amendment 114
9/15/71
TABLE 3.2-3.1 (CONTINUED)
LRV MASS PROPERTIES
THIRD TRAVERSE DEPARTURE
To Be Supplied.
3.2-19 SNA-8-D-O27(III)REV 5
Amendment 114
9is71
TABLE 3.2-3.1 (CONTINUED)
LRV MASS PROPERTIES
THIRD TRAVERSE RETURN
To Be Supplied.
ILlEE Ii EL
3.2-20
LKE_E
SNA-8-D-027 (III)REV 3
,L_
Amendment 114
9115171
TABLE 3.2-4
HIGH ALTITUDE MASS PROPERTIES
To be supplied at a later date.
3.2-21 SNA-8-D-027 (III)REV 3
Amendment 114
9115171
TABLE 3.2-5
PAD ABORT MASS PROPERTIES
To be supplied at a later date.
\
3.2-22 SNA-8-D-027(III)REV 3
_ 1_ EE L L L. L
Amendment 114
9/15/71
TABLE 3.2-6
SIVB MASS PROPERTIES
UI/ L hI/ hL
s_-8-v-o27cI.)_ 3
H _ : L
TABLE3.2-7
Amendment114
9/15/71
CSM 113 CONSUMABLES WEIGHT CHANGE SUMMARY
(To be used in conjunction with CSM sequential mass
properties Table 3.2-2).
From
EVENT
To Consumable
Earth Orbit Pre Trans/Dock
Weight Amount Total
Change Remaining Usage
(Pounds) _Pounds) (Pounds)
SM-Hydrogen
Tank i & 2-1.6 53.6 -1.6
Tank 3 -0.6 27.0 -0.6
SM-Oxygen
Tank 1 & 2 -7.5 625.7 -7.5
Tank 3 -0.7 315.9 -0.7
CM-Waste H20 +4.8 39.8
CM-Potable H20 +6.0 36.0
Pre Trans/Dock Post Trans/Dock SM-RCS -70.6 1,271.8 -70.6
Post Trans/Dock Pre L.O.I. SM-Hydrogen
Tank i & 2-4.7 48.9 -6.3
Tank 3-9.3 17.7 -9.9
SM-Oxygen
Tank i & 2 -61.4 564.3 -68.9
Tank 3-81.5 234.4 -82.2
SM-RCS -110.2 1,161.6 -180.8
CM-Waste H20 +4.2 44.0
CM-LiOH +24.0 24.0
CM-Food -6.2 -6.2
Fecal +2.0 2.0
Pre L.O.I. Post L.O.I. SM-SPS -26,300.2 14,293.5 -26,300.2
Post L.O.I. Pre D.O.I. SM-Hydrogen
Tank 1 & 2 -0.8 48.1 -7.1
Tank 3 -0.i 17.6 -I0.0
SM-Oxygen
Tank i &2 -6.8 557.5 -75.7
Tank 3 -1.3 233.1 -83.5
SM-RCS -41.9 1,119.7 -222.7
3.2-24 SNA-8-D-027(III)REV 3
U l_ U E l_ E k L 15 15 U l: _ I; ii E L L L
TABLE 3.2-7 (CONTINUED)
Amendment 114
9/15/71
CSM 113 CONSUMABLES WEIGHT CHANGE SUMMARY
(To be used in conjunction with CSM sequential mass
properties Table 3.2-2).
From
EVENT
To Consumable
Pre D.O.I. Post D.O.I. SM-SPS
Weight Amount Total
Change Remaining Usage
(Pounds_ <Pounds_ <Pounds_
-1,561.4 12,732.1 -27,861.6
Post D.O.I. CSM/LM Sep. SM-Hydrogen
Tank i & 2
Tank 3
SM-Oxygen
Tank i&2
Tank 3
SM-RCS
CM-LiOH
CM-Food
Fecal
-4.0 44.1 -ii.i
-0.8 16.8 -10.8
-22.9 534.6 -98.6
-13.5 219.6 -97.0
-i14.7 1,005.0 -337.4
+6.0 30.0
-3.8 -10.0
+3.0 5.0
CSM/LM Sep. Pre Circular-
ization
SM-Hydrogen
Tank I & 2
Tank 3
SM-Oxygen
Tank i & 2
Tank 3
SM-RCS
-0.i 44.0 -II.2
-0.i 16.7 -i0.9
-0.7 533.9 -99.3
-2.3 217.3 -99.3
-23.7 981.3 -361.1
Pre Circular-
ization
Post Circular-
ization
SM-SPS -277.9 12,454.2 -28,139.5
Post Circular-
ization Pre Plane Change SM-Hydrogen
Tank i & 2
Tank 3
SM-Oxygen
Tank 1& 2
Tank 3
SM-RCS
Fecal
-11.5 32.5 -22.7
-2.5 14.2 -13.4
.83.6 450.3 -182.9
-33.4 183.9 -132.7
-112.0 869.3
+3.0 8.0 -473.1
3.2-25 SNA-8-D-027(III)REV 3
TABLE 3.2-7 (CONTINUED)
Amendment 114
9/15/71
CSM 113 CONSUMABLES WEIGHT CHANGE SUMMARY
(To be used in conjunction with CSM sequential mass
properties Table 3.2-2).
EVENT
From To Consumable
?re Plane Change Post Plane Change SM-SPS
Weight Amount Total
Change Remaining Usage
(Pounds) (Pounds) (Pounds)
-1,133.8 11,320.4 -29,273.3
?out Plane Change CSM/ASCT Dock SM-Hydrogen
Tank i & 2
Tank 3
SM-Oxygen
Tank I & 2
Tank 3
SM-RCS
CM-Food
CM-LiOH
(_-Fecal
-1.4 31.1 -24.1
-0.3 13.9 -13.7
-10.6 439.7 -193.5
-4.0 179.9 -136.7
-87.1 782.2 -560.2
-4.3 -14.3
+12.0 42.0
+3.1 Ii.i
CSM/ASCT Dock Pre Orbit Shaping SM-Hydrogen
Tank I & 2 -8.4 22.7 -32.5
Tank 3 -1.9 12.0 -15.6
SM-Oxygen
Tank i & 2 -60.5 379.2 -254.0
Tank 3 -33.0 146.9 -169.7
SM-RCS -55.5 726.7 -615.7
CM-LiOH +5.0 47.0
CM-Fecal +3.0 14.1
CM-Food -3.8 -18.1
?re Orbit Shaping Post Orbit Shaping SM-SPS -243.9 11,076.5 -29,517.2
Post Orbit Shap- Pre T. E.I. SM-Hydrogen
[ng Tank i & 2 -0.4 22.3 -32.9
Tank 3 -0.i 11.9 -15.7
SM-Oxygen
Tank 1 & 2 -2.8 376.4 -256.8
Tank 3 -1.7 145.2 -171.4
SM-RCS -36.3 690.4 -652.0
3.2-26 SNA-8-D-O27(III)REV 3
L-
TABLE 3.2-7 (CONCLUDED)
CSM 113 CONSUMABLES WEIGHT CHANGE SUMMARY
(To be used in conjunction with CSM sequential mass
properties Table 3.2-2).
Amendment 114
9/15/71
From
Pre T.E.I.
EVENT
To Consumable
Post T.E.I. SM-SPS
Weight Amount Total
Change Remaining Usage
(Pounds_ {Pounds) (Pounds_
-9,366.8 1,709.7 -38,884.0
Post T.E.I. SM Jettison SM-Hydrogen
Tank I & 2 -10.3 12.0
Tank 3 -2.9 9.0
SM-Oxygen
Tank i & 2-82.9 293.5
Tank 3 -49.2 96.0
SM-RCS -117.8 572.6
CM-LIOH +13.0 60.0
_4-Food -7.3
CM-Fecal +4.6 18.7
-339.7
-220.6
-769.8
-25.4
SM Jettison CM @ Entry CM-RCS -11.6 233.4 -11.6
CM @ Entry CM @ M.C. Deploy CM-RCS -30.7 202.7 -42.3
CM @ M.C. Deploy CM @ Impact CM-RCS -202.7 0.0 -245.0
3.2-27 SNA-8-D-O27(III)REV 3
TABLE 3.2-8
Amendment 114
9115171
LM-II CONSUMABLES CHANGE SUMMARY
(To be used in conjunction with the LM sequential mass properties Table 3.2-3)
From
EVENT
To
Weight Amount Total
Change Remaining Usage
Consumable (Pounds) (Pounds) (Pounds)
D/S-Oxygen -i.0 92.8 -i.0
D/S-Water -12.0 376.0 -12.0
LM-RCS -5.0 600.4 -5.0
Earth Orbit CSM/LM Separation
CSM/LM
Separation
Pre P.D.I. D/S-Oxygen -0.6 92.2 -1.6
D/S-Water -23.0 353.0 -35.0
LM-RCS -50.7 549.7 -55.7
Pre P.D.I. LM @ Touchdown D/S-Oxygen -0.i 92.1 -1.7
D/S-Water -2.0 351.0 -37.0
LM-RCS -90.0 459.7 -145.7
LM-DPS -18,790.5 695.1 -18,790.5
LM @ Touchdown A/S @ Lift-Off LM-RCS -5.0 454.7 -150.7
A/S @ Lift-Off A/S in Orbit LM-APS -4,942.7 283.0 4,942.7
A/S in Orbit A/S Pre T.P.I. A/S-Water -8.0 77.0 -8.0
A/S-Oxygen -0.2 4.6 -0.2
LM-RCS -44.6 410.1 -195.3
A/S Pre T.P.I. A/S Post T.P.I. LM-APS -35.4 247.6 4,978.1
A/S Post T.P.I. A/S @ Docking A/S-Water -7.0 70.0 -15.0
A/S-Oxygen -0.3 4.3 -0.5
LM-RCS -70.3 339.8 -265.6
A/S @ Docking A/S Jettison A/S-Water -20.0 50.0 -35.0
3.2-28 SNA-8-D-027(III)REV 3
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3.2-30 SNA-B-D-027(III)REV 3
ILl !1 1: L: L E E L E E E 12 l_ UE E " '
Li_ L
MISSION J-2
TABLE 3.2-9 (CONTINUED)
COMMAND MODULE STOWAGE VOLUME
SPACECRAFT 113
CENTROIDS
Amendment
9/15/71
114
AREA
AI
2
A2 ISA
3
4
5
6
7
8
9
Top of A1
Top of A2
Top of A7
Top of A8
Top of A9
Between PGA & A9
BI
2
3
4
5
6
8
L2
3
R1
2
3
4
5
6
8
ii
13
UI
2
3
4
L. H. Crew Station
Ctr. Crew Station
R. H. Crew Station
X Y Z
i011.0 -21.0 -22.0
i011.0 -22.0 8.0
1019.0 -22.0 8.0
1016.0 -24.0 28.0
1015.0 -7.0 28.0
1015.0 9.0 28.0
1017.0 26.0 28.0
I011.0 22.0 8.0
I011.0 21.0 -23.0
1013.0 0.0 16.0
1017.0 -21.0 -22.0
1019.0 -22.0 8.0
1019.0 22.0 8.0
1020.0 25.0 -8.0
1016.0 0.0 16.0
1014.0 0.0 8.0
i050.0 -27.0 39.0
1039.0 -38.0 37.0
i031.0 -28.0 40.0
1031.0 -20.0 40.0
1031.0 -8.0 39.0
1031.0 13.0 39.0
1024.0 -38.0 37.0
1059.0 -44.0 14.0
1048.0 -_7.0 12.0
1072.0 26.0 21.0
1072.0 26.0 14.0
1072.0 26.0 9.0
1075.0 28.0 3.0
1059.0 44.0 15.0
1048.0 46.0 29.0
1052.0 46.0 12.0
1038.0 47.0 26.0
1024.0 45.0 -26.0
1033.0 23.0 -50.0
1033.0 -23.0 -50.0
1033,0 -36.0 -44.0
1038.0 39.0 -43.0
1043.0 -24.5 -11.9
I043.0 0.0 -11.9
1043.0 24.5 -11.9
EELEkLE
SNA-8-D-027 (llI) REV 3
TABLE 3.2-9 (CONCLUDED)
Amendment 114
9/15/71
MISSION J-2 COMMAND MODULE STOWAGE VOLUME CENTROID
The following stowage locations have unique volume centroids not associated
with stowage volumes.
NOMENCLATURE LOCATION X Y Z
G&N Signal Cond. Panel LEB
Display Keyboard LEB
Sleep Restraint Assy - Rt. & Center Aft UEB
Sleep Restraint Assy - Left Aft UEB
Entry Locations
Sleep Restraint - RH & Center
ITLSA - IV (CMP)
Food Container
Food Container
Food Container
Fecal Stowage Container
PGA Container
Entry Location
Forward Hatch Container
Container, RI2
(In-flight Location)
Helmet Stowage & Accessory
Bags (In-fllght Location) - LH
Helmet Stowage and Accessory
Bags (In-flight Location) -Ctr.
Helmet Stowage and Accessory
Bag (In-flight Location) - RH
CO2 Absorbers (2)
C02 Absorbers (4)
C02 Absorbers (4)
CO2 Absorbers (4)
CO2 Absorbers (4)
C02 Absorbers (4)
C02 Absorbers (4)
CO2 Absorbers (4)
First 8.0 ib C02 Absorbed
Second 16.0 ib CO2 Absorbed
Remainder C02 Absorbed
1069.0 25.0 29.0
1060.0 26.0 32.0
1018.0 23.0 -50.0
1018.0 -23.0 -50.0
Top of Area A8 1020.0 25.0 -8.0
On RH &Ctr.
Sleep Restraint 1020.0 25.0 -22.0
L3 1048.0 -47.0 12.0
BI 1050.0 -27.0 39.0
A7 i011.0 22.0 8.0
RHEB 1039.0 47.0 12.0
On Aft Bulkhead 1015.0 0.0 -20.0
Under Ctr. Couch
Aft Bulkhead 1015.0 0.0 -6.0
Under LH Couch 1018.0 -24.5 -15.0
RH Girth Ring 1034.0 41.0 -21.0
U2 1033.0 -23.0 -50.0
BI 1050.0 -27.0 39.0
L3 1048.0 -47.0 12.0
In ECU 1031.0 -48.3 19.6
A3 1016.0 -24.0 28.0
A4 1015.0 -7.0 28.0
A.5 1015.0 9.0 28.0
A6 1017.0 26.0 28.0
A9 1013.0 0.0 16.0
B5 1031.0 -8.0 39.0
B6 1031.0 13.0 39.0
Order of Loca-
tions Used in
Sequential Mass
Properties Tables
for CO2 Absorbed
B5 1031.0
(B6, A9) 1022.0
Composite Loca-
tion 1017.4
-8.0 39.0
6.5 27.5
-4.4 27 .i
3.2-32 SNA-8-D-027 (III) REV 3
11 L E E L L L E E E1; E E L
AREA
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
MISSION J-2
TABLE 3.2-9.1
Amendment
9/15/71
LUNAR MODULE STOWAGE VOLUME CENTROIDS
LM-II
X Y Z
280.0 -19.0 13.5
263.5 -20.6 14.9
240.5 -15.3 13.3
270.3 -15.0 19.0
265.9 -20.7 -6.0
257.4 -20.7 -6.0
257.5 -20.0 -18.0
265.9 -20.0 -18.0
273.7 -20.4 1.2
281.0 -20.0 -8.5
273.7 -20.0 -8.5
270.3 -15.0 19.0
260.0 -37.0 28.0
280.0 0.0 -10.0
221.8 -i.0 29.5
278.5 -11.0 23.0
250.0 11.5 31.0
272.6 14.8 17.3
288.0 0.0 -24.0
250.0 8.0 -11.8
262.4 19.8 4.2
272.0 0.0 -18.0
300.0 0.0 0.0
239.6 -5.5 -14.8
257.0 -30.0 27.5
244.5 -36.6 31.4
235.5 -35.5 38.5
242.5 -35.5 38.6
242.8 -35.4 44.7
237.9 -33.6 55.0
235.5 -37.6 46.6
228.0 -40.2 43.2
229.5 -35.5 39.0
229.5 -35.5 35.0
237.8 -37.8 31.5
218.5 -22.0 43.4
292.0 -21.0 38.6
114
3.2-33 SNA-8-D-O27(III)REV 3
AREA
F4
F5
F6A,B,C
F7A
F7B
FTC
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F7E
F7F
F7G
F7H
F7J
F7K
F7L
FFM
F7N
FTP
F8
F9
FI0
MISSION J-2
TABLE 3.2-9.1 (CONCLUDED)
LUNAR MODULE STOWAGE VOLUME
LM-II
Amendment
9/15/71
CENTROIDS
X Y Z
282.2 -21.0 66.6
286.0 17.8 66.6
270.3 0.0 52.8
238.0 38.0 49.8
238.4 38.6 46.0
242.8 38.0 41.0
238.0 38.0 38.4
243.2 38.0 31.2
238.0 38.0 31.6
227.9 33.0 31.8
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222.6 32.3 42.7
231.8 36.0 47.3
225.7 32.3 53.4
238.0 38.0 53.1
241.0 38.0 53.4
221.0 18.0 51.0
219.9 -1.3 44.5
221.0 -18.0 51.0
114
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3.2-95 SNA-8-O-027(III) REV 3
TABLE 3.2-10
CONSUMABLES LOADING REQUIREMENTS AND TOLERANCES
MISSION J-2
SPS PROPELLANT
Amendment 114
9/15/71
Pressure (PS IA)
Fuel Oxidizer
Temperature (°F)
Fuel Oxidizer
110±4 110±4 70±5 70±5
quantity Readout (%)
Fuel Oxidize r
See Figure See Figure
4.1-3 4.1-4
SPS Propellant Load (ib)
TLoad
2Trapped Outside Tanks
Tanked
2Trapped Inside Tanks
3Nominal Deliverable
Loading Requirement
Fuel Oxidizer
15704.0 25092.0
78.6 123.7
15625.4 24968.3
67.6 171.5
15557.8 24796.8
Fuel
Actual
Oxidizer
4Servlce Module RCS Propellant
Secondary Fuel -Quads A, B, C, D - See Loading Window -Figure 4.3-1.
Primary Fuel - Quads A, B, C, D - See Loading Window - Figure 4.3-2.
Primary and Secondary Oxidizer - Quads A, B, C, D - See Loading Window -
Figure 4.3-3.
5Command Module RCS Propellant
Fuel - System A and B - See Loading Window - Figure 4.3-4.
Oxidizer - System A and B - See Loading Window - Figure 4.3-5.
9Helium and Nitrogen
Consumable
Helium - SPS Bottles
Helium - Fuel Tanks
Helium - N20 _ Tanks
Loadin 8
Pressure Temp
(°F)
70
70
70
Requirement
Weight
(ib)
Earth Launch
Weight (ib)
Helium- SM/RCS
Quads A
Quads B
Quads C
Quads D
Helium- CM/RCS
System A
Sys tern B
Nitrogen - SM
Primary
Secondary
(PSIA)
3600
178
178
4150
4150
4150
4150
70
70
70
70
70
70
85
85
87.6
5.4
6.0
1.0
87.6
6.0
1.0
4150
4_0
2500
2500 1.3
Actual
1.3
Pressure Temp
(PSIA) (°F)
3.2-96 SNA-8-D-027 (III) REV 3
|i ELehL-_ L
TABLE 3.2-10 (CONTINUED)
MISSION J-2
Command Module Water and GOX
Waste Water 6
Potable Water ?
CM/COX
Pressure
(PSIA)
900±50
Loading Requirement
Weight _ib)
3.7
Amendment 114
9/15/71
Earth Launch
Weight (lb)
35.0
30.0
6.7 (Entry)
Actual
8Service Module Hydrogen and Oxygen
Hydrogen
Tank i
Tank 2
Tank 3
Oxygen
Tank i
Tank 2
Tank 3
Loading Req. Per Tank
(pounds)
29.3
29.3
29.3
330.1
330 .i
330.1
Earth Launch Weight
Per Tank (ib)
27.6
27.6
27.6
316.6
316.6
316.6
Actual
Per Tank (Ib I
NOTES :
11ndicated propellant load is based on nominal pressure and temperature
prior to actual loading. This number will be updated after loading is
accomplished.
2See Section 4.1 for explanation of trapped SPS propellant.
3See Table 3.2-13 for loading uncertainties.
4See Section 4.2 for SM/RCS loads and uncertainties to be used in Mission
Planning. Actual SM/RCS loads and uncertainties will be published in
Table 3.2-15.
5See Section 4.2 for CM/RCS loads and uncertainties to be used in Mission
Planning. Actual CM/RCS loads and uncertainties will be published in
Table 3.2-14.
6Launch Rule Redlines determine lift-off values.
7Launch Rule Redlines determine lift-off values.
8Launch Mission Rules will determine minimum llft-off quantities for H 2
and 02 .
9CSM helium and nitrogen should be loaded in accordance with loading win-
dows contained in CSM/LM Spacecraft Operational Data Book, Volume I, Part
2, SNA-8-D-027(1) P2.
3.2-97 SNA-8-D-O27(III)REV 3
D
E
N
S
I
T
Y
B/FT 3
TABLE 3.2-11
MISSION J-2
SPS PROPELLANT LOAD CALCULATION
i. Enter SPS Quantity Readout at ii0 PSIA (Table 3.2-12
Item C - Percent)
2. Use Figures 4.1-3 and 4.1-4 to obtain propellant
load for above quantity readout.
3. Nominal propellant density at loading temperature
(use temperature - density graph below) (ib/ft 3)
4. Cubic feet of propellant (item 2 divided by item 3)
5. Calculated density from Table 3.2-12 item f (ib/ft 3)
6. Adjustment due to PUGS zero adjust (pounds)
7. Resulting actual propellant load (item 4 times
item 5, less item 6) (pounds)
SPS SPS
Oxidizer Fuel
3.2-98
Amendment 114
9/15171
FUEL OXI DI ZE R
_,_-! "-..I,_- .-_.
_"t_ '_r "_ ..
_!_ _ ,_-._._'_.:!--:
=4: .-; " ;:.;/-
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3.2-100 SNA-8-D-027(III)REV 3
Ii _ |i i_ L il L L ;_
TABLE 3.2-13
MISSION J-2
SPS PROPELLANT UNCERTAINTIES
Amendment 114
9115171
ITEM FUEL OXIDIZER
LOADING UNCERTAINTIES
Tank Volume
Temperature Gauge (+2.0°F)
Standpipe Height
Propellant Gauge (-+0.35% of Gaugeable)
Density Measurement (i)
Batch Density (I)
Loading Pressure (I)
_ib)
_+24
_+18
_+6
_+54
_+0
_+94
_+8
(lb)
_+39
±46
±i0
_+86
_+0
_+75
±14
RSS _+113 ±130
!
TOTAL RSS _+172
_+16 _+24
+0 +0
-46 -113
Loading Specification (I) (2)
Tolerance on Propellant Temperature
of Flisht Load
TOTAL LOADING UNCERTAINTY +212
-371
NOTES : (i) Data will be known after loading is accomplished.
(2) Loading specification is an allowable tolerance about
nominal, this number is added to the loading uncertainlty
variable.
3.2-101 "SRA-8-D-027(III)REV 3
II E E L E L L E E L I: L' E II E L L _ L
TABLE 3.2-14
MISSION J-2
Amendment 114
9/ls/71
CO_4AND 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.
FUEL OXIDIZER
Tank A Tank B Tank ATank B
A. Tank Volume @0.0 PSIA -(in3)
B. Liquid Line Volume (in 3)
C. Total A + B (in 3)
D. Initial Weight in Bleed Unit
Prior to Loading (lh)
E. Final Weight in Bleed Unit
After Loading (ib)
F. Propellant Load (item D less
than E Weigh Tank)
G. Propellant Load by .P.V.
H. Loading Temperature (°F)
I. Specification Propellant
Load @ 70±5*F (ib)
J. Total CM/RCS Propellant
Load from Item G above (Ib)
K. Maximum Trapped Propellant (ib)
L. Nominal Deliverable (ib)
3.2-102 SNA-8-D-027 (IIl) REV 3
II E E L: E L LL
I
TABLE 3.2-15
MISSION J-2
SERVICE MODULE RCS LOADING SUMMATION
Amendment 114
9/15/71
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, and nominal deliverable propellants.
quad A (ib) quad B (ib)
Secondary Fuel
Primary Fuel
Total Fuel
Maximum Trapped
Nominal Deliverable
Secondary Fuel
Primary Fuel
Total Fuel
Maximum Trapped
Nominal Deliverable
Total Oxidizer
Maximum Trapped
Nominal Deliverable
Total Oxidizer
Maximum Trapped
Nominal Deliverable
Ruad C (ib)
Secondary Fuel
Primary Fuel
Total Fuel
Maximum Trapped
Nominal Deliverable
Total Oxidizer
Maximum Trapped
Nominal Deliverable
quad D (ib)
Secondary Fuel
Primary Fuel
Total Fuel
Maximum Tr@pped
Nominal Deliverable
Total Oxidizer
Maximum Trapped
Nominal Deliverable
Total Fuel
Maximum Trapped
Nominal Deliverable
Total SM/RCS Propellant Load (Ib)
Total Oxidizer
Maximum Trapped
Nominal Deliverable
3.2-103 SNA-8-D-027(III)REV 3
TABLE 3.2-16 Amendment 114
9115171
MISSION J-2
LM-II CONSUMABLE LOADING REQUIREMENTS
LM-II APS PROPELLANT
Fuel (ib) Oxidizer (lh)
Propellant Load 2014.2 3225.7
Trapped Outside Tanks 5.9 8.3
Tanked 2008.3 3217.4
Trapped Inside Tanks i0.0 27.7
Nominal Deliverable 1998.3 3189.7
Outage TBD TBD
Total APS Propellant TBD
The following table should be used to determine the amount of propellant to
be off-loaded from a full condition to arrive at the indicated load. The
allowable tolerance for the calculated off-load is ±0.5 pounds per weigh
tank.
A. Final tank pressure at overfill (PSIG)
B. Propellant loading temperature (°F)
C. Nominal overfill quantity (ib)
D. Correction for tank pressure (ib)
Fuel = 0.09 (Item A-40)
Oxidizer - 0.15 (Item A-40)
IE. Correction for loading temperature (Ib)
Fuel - 1.16 (Item B-65)
Oxidizer =-2.84 (Item B-65)
2F. Measured density (GM/CC)
2G. Nominal density (GM/CC)
H. Delta density (GM/CC) (Item F-G)
3I. Correction for measured density
Fuel = 2300 (Item H)
Oxidizer = 2300 (Item H)
J. Propellant in GSE
K. Overfill quantity (C+D+E+I+J)
L. Target loading
M. Quantity required to fill RCS manifolds
N. Quantity to be off-loaded (Item K-L-M)
NOTES:
ILoading temperature correction will always be negative;
2To calculate the nominal density solve the following equation where T -
temperature in °C of the measured density (usually 4°C for oxidizer and
25°C for fuel). This equation is valid for 14.7 PSIA. Therefore, the
measured density must also be at 14.7 PSIA.
Nominal fuel density = 0.922904-0.0009377 ('C)
Nominal oxidizer density -1.491539-0.0022832 (°C)
3Correction for measured density may be either positive or negative.
3.2-104 SNA-8-D-O27(Ill)REV 3
E E L IL LL L L. L-' d li H, E
Propellant Load
Trapped Outside Tanks
Tanked
Trapped Inside Tanks
Nominal Deliverable
Outage
Total DPS Propellant
1El.
2 F1.
2GI.
HI.
3Ii.
TABLE 3.2-16 (CONTINUED)
MISSION J-2
LM-II CONSUMABLE LOADING REQUIREMENTS
LM-II DPS PROPELLANT
Amendment 114
9/15/71
Fuel (Ib)
7_26.0
27,3
74_8,7
13,5
7485.2
TBD
Oxidizer (lb)
12035.8
48.9
11986.9
43.3
11943.6
TBD
TBD
The following table should be used to determine the amount of propellant to be
off-loaded from a full condition to arrive at the indicated load. The allow-
able tolerance for the calculated off-load is ±0.5 pounds per weigh tank.
AI. Final tank pressure at overfill (PSIG)
BI. Propellant loading temperature (*F)
CI. Nominal overfill quantity (ib)
DI. Correction for tank pressure (Ib)
Fuel =0.33 (Item A1 -40)
Oxidizer =0.54 (Item A1 -40)
Correction for lording temperature (ib)
Fuel =4.25 (Item B1 -65)
Oxidizer --10.5 (Item B1 -65)
Measured density (GM/CC)
Nominal density (GM/CC)
Delta density (GM/CC) (Item F1 - Item GI)
Correction for measured density
Fuel -8400 (Item HI)
Oxidizer -8400 (Item HI)
Jl. Propellant in GSE
KI. Overfill quantity (CI+DI+EI+II+JI)
LI. Target loading
MI. Quantity required to fill RCS manifolds (APS only)
NI. Quantity to be off-loaded (Items KI-LI-MI)
NOTES:
ILoading temperature correction will always be negative.
2To calculate the nominal density solve the following equation where
T = temperature in *C of the measured density (usually 4"C for oxidizer
and 25"C for fuel). This equation is valid for 14.7 PSIA. Therefore,
the measured denisty must also be at 14.7 PSIA.
Nominal fuel density =0.922904-0.0009377 (*C)
Nominal oxidizer density - 1.491539-0.0022832 (*C)
3Correction for measured density may be either positive or negative.
3.2-105 SNA-8-D-027 (III) REV 3
TABLE 3.2-16 (CONTINUED)
MISSION J-2
LM-II - RCS PROPELLANT (2) (3)
System AFuel
System AOxidizer
System B Fuel
System B Oxidizer
Required Ullage Requirement (in _)
Load (Ib) 5 Minimum 4 Maximum 4
iActual5
Load (lb)
107.4±0.9 152.5 164.5
208.2±1.9 267.0 279.0
107.4±0.9 152.5 164.5
208.2±1.9 267.0 279.0
FUEL OXIDIZER
Propellant Load 214.8 416.4
Trapped Outside Tanks i0.0 15.8
Tanked 204.8 400.6
Trapped in Tanks 4.2 8.0
Nominal Deliverable 200.6 392.6
LM-II - Helium & NitroBen
Amendment 114
9/15/71
IActual 4
Ullage (In 3)
Consumable
Helium - APS tank #I (6)
- APS tank #2 (6)
- RCS tank #I (6)
RCS tank #2 (6)
- DPS (SHe)
-DPS (Ambient) (6)
Nitrogen - Ascent
- Descent
- Descent
Nominal Loadin_ Requirement
Pressure Temp Weight
(PSIA) (°F) (Ib)
3050 70 6.6
3050 70 6.6
3050 70 ]. 05
3050 70 1.05
80_2 N/A 51.2
1600 70 I.i
0.I
0.6
-0.6
Actual
Pressure Temp Weight
(PSIA) (°F) (ib)
LM-II - Water & GOX
Consumable
Ascent Water -tank #I
tank #2
Descent Water - tank #i
- tank #2
Ascent COX - tank #i (6)
- tank #2 (6)
Descent GOX - tank #i (6)
-tank #2 (6)
Nominal Loadin_ Requirement
Pressure Weight Pressure
(PSIA) (ib) (PSIA)
N/A (7) N/A
N/A (7) N/A
N/A (7) N/A
N/A (7) N/A
Actual
Weight
(Ib)
830 2.4
830 2.4
2700 48.0
2700 48.0
NOTES:
iSee Table 3.2-17 for actual propellant load calculation.
2See Section 5.6 for explanation of trapped propellants.
3See Table 3.2-18 for loading uncertainties.
4PV ullage calculation should be 166.5±50 cubic inches for LM/RCS fuel and
280±50 cubic inches for LM/RCS oxidizer per tank.
5LM/RCS required load includes propellant required to fill RCS manifolds
to thruster valves. See Table 3.2-16. See Section 5.6 for trapped
propellants.
6The indicated items should be loaded in accordance with loading windows
contained in the CSM/LM Spacecraft Operational Data Book_ Volume II,
Part 2, SNA-8-D-O27PT2.
7LM-II Descent Water shall be loaded to provide 388-0.0+I0.0 pounds at
Earth Launch. LM-II ascent water shall be loaded to provide 85 pounds
at earth launch. Initial load will be determined by the pressure-
temperature relationship provided in TABLE 3.2-16.1.
3.2-106 SNA-8-D-027 (Ill) REV 3
Amendment 114
9/15/71
TABLE 3.2-16.1
LM-II ECS WATER LOADING DATA
To Be Supplied.
3.2-107 SNA-8-D-027(III)REV 3
APS PROPELLANT
TABLE 3.2-17
MISSION J-2
LM-II LOAD CALCULATION
i. Full tank - Item K, Table 3.2-16 (ib)
12. Density of off-load tables at loading
temperature and pressure (ib/ft 3)
I3. Propellant volume (divide item i by
item 2) (ft 3)
i 4. Measured density (from Table 3.2-19)
(lblft3)
5. Resulting full tank load (ib)
*6. Off-load amount (ib)
7. Propellant required to fill RCS manifolds
(ib)
8. Propellant load (ib)
DPS PROPELLANT
9. Full tank - Item K1 Table 3.2-16
Ii0. Density of off-load tables at loading
temperature and pressure (ib/ft 3)
iii. Propellant volume (divide Item 9 by Item
i0) (ft 3 )
112. Measured density (from Table 3.2-19)
(iblft 3)
13. Resulting full tank load (ib)
14. Off-load amount (ib)
15. Propellant load (Ib)
RCS PROPELLANT
P. V. Calculations
Amendment 114
9115/71
FUEL OXIDIZER
A. GSE Volume (in 3 )
B. Initial Ullage Pressure
(PSIC)
C. Initial GSE Pressure
(PSIC)
D. Final GSE - S/C Pressure
(PSIG)
E. Ullage Volume (in 3) - Solve
the following equation by
substituting the values in
the indicated steps.
Ullage Volume = (D-C) (A)
B-D
NOTE :
Fuel Oxidizer
Tank A Tank BTank A Tank B
IThese items will be completed only if a density sample is not
made prior to loading. If a density sample is made prior to
loading, then the items will be left blank.
3.2-108
SNA-8-D-027 (III) REV 3
TABLE 3.2-18
MISSION J-2
LM-II PROPELLANT LOADING UNCERTAINTIES
Vent Line Volume
Tank Volume
Pressure Measurement (+5 PSIA)
Temperature Measurement (+-I.5°F)
Measured Density
Weight Measurement
ILoading Tolerances
Total Loading Uncertainlty
Vent Line Volume
Tank Volume
Pressure Measurement (+-5 PSIA)
Temperature Measurement (i. 5 °F)
Measured Density
Weight Measurement
1Loading Tolerance
Total Loading Uncertainity
Loading Temperature
Ullage Calculation
Tank and Manifold Volume
Total
Amendment 114
9/15/71
LM-II APS PROPELLANT
Fuel (ib) Oxidizer (ib)
±0.2 +-0.3
±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
LM-II DPS PROPELLANT
±0.2 ±0.3
±3.62 ±5.96
+-1.70 ±2.77
+-6.49 ±15.76
±2.55 ±1.70
±0.5 ±0.5
±0.5 +-0.5
±15.6 +-27.5
LM-II RCS PROPELLANT
±0.6 ±1.8
±0.4 ±0.6
±0.8 ±1.4
+-1.8 ±3.8
IThese will be known quantities after loading is accomplished.
3.2-109 SNA-8-D-027(III)REV 3
TABLE3.2-19
MISSIONJ-2
LM-II APSPROPELLANTLOADINGPARAMETERS
(To Be Completedby KSC at Loading)
Loading Pressur, - PSIA
i TT 58 Fuel
Loading Temperature - Fill Line - Degrees F I Tr258 Oxidizer
Loading Temperature - Return Line - Degrees F I TT 59 Fuel
I TT259 Oxidizer
Loading Temperature - Tank - Degrees F _ GP0718 Fuel
IGPI218 Oxidizer
Number of Times Weigh Tank Used (FIGw Meter Not Used)
Total Pounds Off-Loaded Using Weigh Tank (Flow Meter Not Used)
Pounds Off-Loaded Using Flow Meter (Weight Tank Not Used)
Measured Fuel Density @ 25°C; @ 14.7 PSIA GM/CC
Measured Oxidizer Density @ 4°C; 14.7 PSIA GM/CC
Amendment ] 14
9/15/71
Fuel Oxidizer
3.2-110 SNA-8-D-O27(III)REV 3
TABLE3.2-19 (CONTINUED)
MISSIONJ-2
LM-II DPSPROPELLANTLOADINGPARAMETERS
LoadingPressure - PSIA
ITT58 Fuel
Loading Temperature- Fill Line - DegreesF_TT258Oxidizer
ITr 59 Fuel
Loading Temperature- Return Line - DegreesF_TT259Oxidizer
_GQ3718Fuel
Loading Temperature- TankOne- DegreesF_GQ4218Oxidizer
LoadingTemperature- TankTwo- DegreesFIGQ3719Fuel
IGQ4219Oxidizer
Numberof TimesWeighTank Used (Flow Meter Not Used)
Total Pounds Off-Loaded Using Weight Tank (Flow Meter Not Used)
Pounds Off-Loaded Using Flow Meter (Weigh Tank Not Used)
Measured Fuel Density @ 25°C; @ 14.7 PSIA GM/CC
Measured Oxidizer Density @ 4°C; @ 14.7 PSIA GM/CC
Amendment 114
9/15/71
Fuel Oxidizer
3.2-111 SNA-8-D-027(III)REV 3
MISSION J-2 MASS PROPERTY DATA TABLES
Amendment 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 3.2-23 presents the CSM-II3 mass properties, in Apollo coordinates,
as a function of CSM weight for the Plane Change I SM/SPS
burn.
Table 3.2-24 presents the CSM-II3 mass properties, in Apollo coordinates
as a function of CSM weight for the T.E.I. SM/SPS burn.
Table 3.2-25 presents the LM-II mass properties, in LM coordinates, as a
function of LM weight for the P.D.I. DPS burn.
Table 3.2-26 presents the LM-ll ascent stage mass properties, in LM coordi-
nates, as a function of weight for the lunar liftoff APS burn.
Table 3.2-27 presents the LM-ll mass properties, in LM coordinates, as a
function of Lr'weight for the T.P.I. to docking LM/APS burn.
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Amendment 74
1/14/7o
SUPPLEMENTARY DATA APPLICABLE TO SEQUENTIAL MASS PROPERTIES TABLES
General Comments to be Applied to Tables 3.3-1 through 3.3-8:
Inertia data dispersions are +10%.
Dispersions shall be used as 30 deviation values.
All initial propellant weights are total tanked.
LM propellants are assumed to be in the low ends of their tanks except
when in the CSM/LM docked configuration. In the CSM/LM docked con-
figuration, LM propellants are assumed to be in the hlgh ends of their
tanks. CSM propellants are always assumed to be in the low ends of
their tanks.
The (+) or (-) sign following the name of an item indicates that the
item is added to or subtracted from the preceding total.
Table 3'3-i
SM/SPS glmbal angles for SPS abort sequence are: Pitch = -1.530 deg.
Yaw =1.315 deg.
Tables 3.3-7 and 3.3-8
CSM and 124 consumables changes are presented in Tables 3.3-7 and 3.3-8,
respectively.
Tables 3.3-4 and 3.3-5
Delta Z - 0.75 in.
LES motor tilted angles Delta = 2.124 deg.
Sigma =270.121 deg.
LES motor tilted confluence point X - 1222.379 in.
Y= 0.001 in.
Z-0.224 in.
PCMmotor tilted angles Delta = 89.324 deg.
Sigma = 270.676 deg.
PCM motor tilted confluence point X= 1428.970 in.
Y - 0.O18 in.
Z - 2. 662 in.
The docking probe and ring are Jettisoned at t=14.0 seconds in Table
3.3-4 and Table 3.3-5. Reference Memorandum EX24/8912-344B, dated
December 4, 1969.
Table 3.3-5 includes arapid depletion of CM/RCS oxidizer from t-0.0
to t=9.0 seconds and of CM/RCS fuel from t-5.0 to t=14.0 seconds.
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Amendment 79
3130/70
TABLE 3.3-7
CSM 109 Consumables Weight Change Summary
(To be used in conjunction with the CSM sequential mass properties Table 3.3-2_
EVENT
From To
Earth Launch Pre Trans/Dock
Weight Amount Total
Consumable Change Remaining Usage •
(Pounds) (Pounds) (Pounds_
SM-Hydrogen -i.i 54.1 -i.i
SM-Oxygen -13.0 620.2 -13.0
CM-Potable H20 +4.0 40.0
CM-Waste H20 +0.8 18.8
Pre Trans/Dock Post Trans/Dock SM-RCS -70.6 1,272.2 -70.6
Post Trans/Dock Pre SPS Hybrid SM-Hydrogen -5.0 4q.l -6.1
SM-Oxygen -59.7 560.5 -72.7
SM-RCS -82.1 1,190.1 -152.7
CM-Waste H20 +41.2 60.0
CM-LiOH +6.8
CM-Food -3.-8
Pre SPS Hybrid Post SPS Hybrid SM-SPS -159.8 40,406.8 -159._
Post SPS Hybrid Pre M.C.C.3 SM-Hydrogen -4.3 44.8 -i0.4
SM-Oxygen -40.6 519.9 -113.3
SM-RCS -12.0 1,178.1 -I_4.7
Pre H.C.C. Post _I.C.C SM-SPS -344.9 40,061.9 -504.7
Post H.C.C Pre L.O.I. i SM-Hydrogen -4.4 40.4 -14.8
SM-Oxygen -45.9 474.0 -15q.2
SM-RCS -30.1 1,148.0 -194.8
CM-Food -9.4 -13.2
CM-LIOH +6.8
Pre L.O.I. Post L.O.I. SM-SPS -23,510.5 16,551.4 24,015.2
Post L.O.I. Pre D.O.I. SM-Hydrogen -0.8 39.6 -15.6
SH-Oxygen -7.8 466.2 -167.0
SM-RCS -52.3 1,095.7 -247.1
Pre D.O.I. Post D.O.I. SM-SPS 1,537.3 15,014.1 -25,552.5
Post D.O.I. CSH/LH Separation SM-Hydrogen -3.3 36.3 -18.9
SM-Oxygen -32.8 433.4 -199.8
SM-RCS -73.7 1,022.0 320.8
CM-LIOH +5.0
CM-Food -3.8 -17.0
CSM/LM Separation Pre Circularization Hydrogen -0.3 36.0 -19.2
Oxygen -2.6 430.8 -202.4
SM-RCS -56.6 965.4 -377.4
Pre Circularizatlon Post Circularlzatlon SM-SPS -273.0 14,741.1 -25,825.5
SNA-8-D-027(III)REV 2
3.3-15
!1 !1 EEL E :i2 L L E U EEI_ EELL_;__
Amendment 79
3/30/70 ,
,TABLE 3.3-7 (Continued)
CSM 109 Consumables Weight Change Summary
_To be used in conlunction with the CSM sequential mass properties Table 3.3-2_
Weight Amount Total
EVENT Consumable Change Remaining Usage "
From To <Pounds) (Pounds_ (Pounds)
Post Circularization Pre Plane Change i SM-Hydrogen -2.6 33.4 -21.8
SM-Oxygen -24.4 406.4 -226.8
SM-RCS -73.4 892.0 -450.8
Pre Plane Change 1Post Plane Change iSM-SPS -679.1 14,062.0 -26,504.6
Post Plane Change 1 CSM/ASCT Docking SM-Hydrogen -5.4 28.0 -27.2
SM-Oxygen -51.4 355.0 -278.2
SM-RCS -158.9 733.1 -609.7
CM-Food -6.3 -23.3
CM-LIOH +7.8
CM-Fecal +2.2
CSM/ASCT Docking Pre Plane Change 2 SM-Hydrogen -2.3 25.7 -29.5
SM-Oxygen -22.2 332.8 -300.4
SM-RCS -39.8 693.3 -649.5
CM-LiOH +2.4
Pre Plane Change 2 Post Plane Change 2 SM-SPS -2,866.0 11,196.0 -29,370.6
Post Plane Change 2 Pre T.E.I. SM-Hydrogen -2.7 23.0 -32.2
SM-Oxygen -25.0 307.8 -325.4
SM-RCS -55.0 638.3 -704.5
CM-Fecal +i.I
CM-Food -3.8 -27.1
CM-LIOH +2.6
Pre T.E.I. Post T.E.I. SM-SPS 8,963.8 2,232.2 -38,334.4
Post T.E.I. SH Jettison SM-Hydrogen -13.2 9.8 -45.4
SM-Oxygen -126.2 181.6 -451.6
SM-RCS -206.9 431.4 -911.4
CM-LiOH +13.4
CH-Food -10.4 -37.5
CM-Fecal +3.3
r
SH Jettison C}! @ Entry CM-RCS -12.0 233.1 -12.0
CH @ Entry CH @ M.C. Deploy CM-RCS -31.7 201.4 -43.7
C:! @ M.C. Deploy CM @ Impact CH-RCS -201.4 0.0 -245.1
SNA-8-D-027(III)REV 2
3.3-16
Lb__
Amendment 79
3130170
TABLE 3.3-8
LM-7 Consumables Change Summary
_To be used in conjunction with the LM sequential mass properties Table 3-3.2
Weight Amount Total
EVENT Consumable Change Remaining Usage
From To (Pounds) (Pounds) (Pounds)
Earth Orbit CSM/LM Separation D/S-Oxygen -2.8 45.2 -2.8
D/S-Water -14.8 235.2 -14.8
LM-RCS -5.0 599.6 -5.0
CSM/LM Separation Pre P.D.I. D/S-Oxygen -0.9 44.3 -3.7
D/S-Water -23.6 211.6 -38.4
LM-RCS -53.4 546.2 -58.4
Pre P.D.I. LM @ Touchdown D/S-Oxygen -0.i 44.2 -3.8
D/S-Water -1.3 210.3 -39.7
LM-RCS -97.0 449.2 -155.4
LH-DPS -17,054.5 1,284.4 -17,054.5
LM @ Liftoff A/S in Orbit
A/S in Orbit A/S @ C.S.I.
LM-APS -4,902.4 326.6 -4,902.4
A/S-Water -15.6 69.4 -15.6
A/S-Oxygen -0.5 4.3 -0.5
LM-RCS -17.8 431.4 -173.2
56.5 -28.5
A/S @ C.S.l. A/S @ Docking A/S Water -12.9 3.7 -i.i
A/S Oxygen -0.6 309 8 -294.8
LM-RCS -121.6 "
A/S @ Docking A/S Jettison A/S-Water -12.4 44.1 -40.9
3.3-17
SNA-8-D-027(III)REV 2
Amendment 79
3/30/70
MISSION "H-2" TRANSFERABLE EQUIPMENT
The reference table used with this transferable equipment list is a-directory
of information sources from which data for each item were obtained. It is
intended to define the exact source of each portion of the data used. This
reference table is correlated to each item in the transferable equipment
list by a reference code number for each item listed.
Abbreviations used in this reference table are as follows:
Co G.
N. R.
S. L.
A. O. H.
Center of Gravity
North American Rockwell
Stowage List
Apollo Operations Handbook
"DATA" refers to all information, including nomenclature, except that which
is designated to separate sources.
"STOWAGE LIST" refers to the Apollo Stowage List for each mission prepared
bi-weekly for NASA by the Boeing Company.
"FLIGHT PLAN" refers to the Apollo Flight Plan prepared for each mission by
the Flight Planning Branch of NASA.
Data obtained from North American Rockwell and Boeing were obtained through
data requests and telephone communication.
REFERENCE USED IN COMPILING TRANSFERRED EQUIPMENT LIST
1 Data from S.L./C.G. from N. R.
2 Data from S.L./C.G. from Boeing Company
3 Data from S.L./C.G. estimated
4 Data from S.L./Weight Estimated/C.G. from N. R.
5 Data from S.L./C.G. from Mock-up
6 Data from S.L./Location from A.O.H./C.G. from N. R.
7 Data from S.L./C.G. Calculated from Drawing
8 Data for EVA from LM Lunar Surface Checklist
9 Data by Telecom. with Responsible MSC Apollo Division/Contractor
i0 Data from S.L./Weight and C.G. from Boeing Company
ii Data from Boeing Co./Location from Flight Plan
12 Data from S.L./Weight, Location and C.G. Estimated by TRW
13 Data from S.L./Location Estimated/C.G. from N. R.
14 Data from Flight Plan/C.G. from N. R.
15 Data from A. O. H/C.G. from N. R.
20 Data from LM Lunar Surface Checklist/S.L.
3.3-18
SNA-8-D-027(III)REV 2
!1 !1 1.: [ L E L L L ]: L'- E 1; I,: E: ' L.
MISSION H
TABLE 3.3-9
COMMAND MODULE STOWAGE
S/C 109 - iii
VOLUME
Amendment
3/30/70
CENTROIDS
79
AREA
A1
3
4
5
6
7 -
8
i0 -
ii -
12
13
BI
2
3
4
5
6
7
8
L2
3
R1
2
3
4
5
6
8
i0 -
i0-
ii
13
Ul
3
4
Not on S/C ii0
S/C ii0 Only
Not on S/C ii0
Forward
Aft
X Y Z
1012.0 -22.0 -26.0
1016.0 -24.0 28.0
1015.0 - 7.0 28.0
1015.0 9.0 28.0
1017.0 26.0 28.0
1012.0 31.0 7.0
1012.0 22.0 -23.0
i011.0 23.0 6.0
1011.0 19.0 7.0
1013.0 - 9.0 14.0
i010.0 -22.0 - 2.0
1050.0 -27.0 39.0
1039.0 -38.0 37.0
1031.0 -28.0 40.0
1031.0 -20.0 40.0
1031.0 - 8.0 39.0
1031.0 13.0 39.0
1033.0 27.0 36.0
1024.0 -38.0 37.0
1059.0 -44.0 14.0
1048.0 -47.0 12.0
1072.0 26.0 21.0
1072.0 26.0 14.0
1072.0 26.0 9.0
1075.0 28.0 3.0
1059.0 44.0 15.0
1048.0 46.0 29.0
1052.0 46.0 12.0
1053.0 47.0 5.0
1047.0 48.0 5.0
1038.0 47.0 26.0
1024.0 45.0 -26.0
1033.0 23.0 -50.0
1033.0 -36.0 -44.0
1038.0 39.0 -43.0
3.3-19
SNA-8-D-027(III)REV 2
Amendment 70
10/10/69
TABLE 3.3"9.1
The following stowage locations have unique volume centroids
not associated with stowage volumes.
NO_ENCLATURE LOCATION X Y
G&N Signal Cond. Panel
Display Keyboard
Sleep Restraint Assy - Right
Slee_ Restraint Assy - Left
Food Container
Food Container
Fecal Stowage Container
PCA Container
Forward Hatch Container
Container, RI2 (In-flight Location)
Helmet Stowage and Accessory
Bags (In-flight Location)- L.H.
Helmet Stowage and Accessory
Bags (In-flight Location)- Ctr.
Helmet Stowage and Accessory
Bags (In-flight Location) - R.H.
Temporary Stowage Bag - L.H.
(In-flight Location)
Temporary Stowage Bag - Ctr.
(In-flight Location)
Temporary Stowage Bag - R.H.
(In-flight Location)
CO_ Absorbers (2)
CO" Absorbers (4)
CO_ Absorbers (4)
CO_ Absorbers (2)
CO _ Absorbers (4)
CO_. Absorbers (4)
First 6.8 lb. CO^ Absorbed
Next 6.8 lb. COl Absorbed
Remainder CO 2 AbsOrbed
LEB 1069.0 25
LEB 1060.0 26
Aft UEB 1018.0 25
Aft UEB 1018.0 -21
L3 1048.O -47
B1 1050.0 -27
RHEB 1039.0 47
On Aft Bulkhead 1015.0 0
Under Center
Couch
Under L.H. Couch
R.H. Girth Ring
L.H. Girth Ring
LEB
R.H. Girth Ring
LEEB
LEB
RHEB
In ECU
A3
A4
A6
B5
B6
Composite Loca-
tion used in
Sequential Mass
Properties Tables
For CO 2 Absorbed.
B5
B6
Composite Loca-
tion
Z
029.0
0 32.0
0 -47,9
0 -49.9
0 12.0
0 39.0
0 12 .O
0 -19.9
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1036,5 40.0 -25.O
1036.5 -40,0 -25.0
1050.O -27.0 39.0
1036.5 40.0 -25.0
1039.0 -47.0 12.0
1050.0 -27.0 39.0
1039.0 47.0 12.0
1031.0 -48.3 19.6
1016.5 -23.9 27.5
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1016.9 26.2 27.5
1031.0 - 8.0 39.0
1031.0 13.0 39.0
1031.0 - 8.0 39.0
1031.0 13.0 39.O
1018.5 -14.3 26.1
3.3-20 SNA-8-D-027 (IIl) REV 2
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.Amendment 80
4/8/70
TABLE 3.3-10
CONSUMABLES LOADING REQUIREMENTS AND TOLERANCES
Mission H-2
SPS Propellant
Pressure _PSIA)
Fuel Oxidizer Temperature _*F)
Fuel Oxidizer Readout (%)
Oxidizer
quant ity
Fuel
11024 110t4 70t5 70_5 See Figure See Figure
4.1-3 4.1-4
SPS Propellant Load (Ib) Actual
iLoad
2Trapped Outside Tanks
Tanked
2Trapped Inside Tanks
3Nominal Deliverable
Loadin_ Requirement
Fuel Oxidizer
15704.0 25092.0
78.6 123.7
15625.4 24968.3
67.6 171.5
15557.8 24796.8
Fuel
15685.2
78.6
15606.6
67.6
15539.0
Oxidizer
25083.7
123.9
24960.0
171.5
24788.5
_Service Module RCS Propellant
Secondary Fuel - Quads A, B, C, D- See Loading Window - Figure 4.3-1.
Primary Fuel - Quads A, B, C, D-See Loading Window - Figure 4.3-2.
Primary and Secondary Oxidizer - Quads A, B, C, D - See Loading Window -
Figure 4.3-3.
5Co_nnand Module RCS Propellant
Fuel - System A and B - See Loading Window - Figure 4.3-4.
Oxidizer - System A and B - See Loading Window - Figure 4.3-5.
9Helium and Nitrogen
Consumable
Helium - SPS Bottles
Helium - Fuel Tanks
Helium -N20 _ Tanks
Helium - SM/RCS
Quad A
Quad B
Qued C
_ed V
Helium -_/lCS
System A
System B
Nitrogen - SM
Primary
Secondary
Pressure
(PSIA)
3600
178
178
4150
4150
4150
4150
4150
4150
2500
2500
Loadin S
Temp
('F)
70
70
70
70
70
70
70
70
70
85
85
Requirement
Weight
(lb)
87.6
5.4
6.0
1.0
1.3
Earth Launch
Weight (ib)
87.6
6.0
1.0
Actual
Pressure Temp
(PSIA) (°F)
3510
178
170
72
1.3
4350 86
4240 77
4210 73
4280 77
4140 65
4140 67
2510 71
2550 71
3.3-49 SNA-8-D-027(III)REV 2
Amendment80
4/8/70
TABLE3.3-10 (Continued)
Comand Module Water and COX
Pressure Loading Requirement Earth Launch Actual
(P$1A) Weight _ib_ Weight (Ib_
I Waste Water 6 18.0 *ii ibs
Potable Water 7 36.0 *30 ibs
CM/COX 900±50 3.7 6.7 (Entry)
*As serviced, predicted at lift-off; Waste Water 38.0 ibs, Potable Water 31.4 ibs.
8Service Module Hydrogen and Oxygen
Hydrogen
Oxygen
Loading Req. Per Tank
(pounds)
29.3
330.I
Earth Launch Weight
Per Tank (ib)
27.6
316.6
NOTES:
llndicated propellant load is based on nominal pressure and temperature
prior to actual loading. This number will be updated after loading
is accomplished.
2See Section 4.1 for explanation of trapped SPS propellant.
3See Table 3.3-13 for loading uncertainties.
_See Section 4.2 for SM/RCS loads and uncertainties to be used in Mis-
sion Planning. Actual SM/RCS loads and uncertainties will be published
in Table 3.3-15.
5See Section 4.2 for CM/RCS loads and uncertainties to be used in Mis-
sion Planning. Actual CM/RCS loads and uncertainties will be published
in Table 3.3-14.
6Launch Rule Redlines determine lift-off values.
7Launch Rule Redlines determine lift-off values.
8Launch Mission Rules will determine minimum lift-off quantities for
H 2 and 02.
gCSM helium and nitrogen should be loaded in accordance with loading
windows contained in CSM/LM Spacecraft Operational Data Book, Volume I,
Part 2, SNA-8-D-027(1) P2.
3.3-50 SNA-8-D-O27(III)REV 2
L
Amendment 79
3/30/70
D
E
N
S
I
T
Y
LB/F'T3
TABLE 3.3-11
SPS Propellant Load Calculation
1. Enter sPa Quantity Readout at 110 PSIA (Table 3.3-12
item C- Percent) 100.8
2. Use F£guree 4.1-3 and 4.1-4 to obtaln pro-
pellant load for above quantity readout. 15588.0 25092.0
3. Nominal propellant density at loading temperature
(use temperature -density graph below) (lb/fC3) 56.35
4. Cubic feet of propellant (item 2 divided by Item 3) 278.403
5. Calculated density from Table 3.3-12 Item f(Ib/fC 3) 56.34 90.41
6. Adjustment due to PUGS zero adjust (pounds) 0._..___0 0.0
7. Resulting actual propellant load (item 4times
Item 5, less item 6) (pounds) 15685.2 25083.7
sPa
Oxidizer
90.6
90.5
90.Z
90.
90.1
90. ]
90.0
89.9
89.8
89.7
SPS Propellant'Temperacure/Denelty Graph
at 110+5 PSIA
Temperature Degrees F
OXIDIZER
277.443
3.3-51 SNA-8-D-027 (Ill) IEV 2
E_
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TABLE 3.3-13
SPS PROPELLANT UNCERTAINTIES
Amendment 79
3130170
ITEM
LOADING UNCERTAINTIES
Tank Volume
Temperature Gauge (_2.0°F)
Standpipe Height
Propellant Gauge (±0.35% of Gaugeable)
Density Measurement (i)
Batch Density (I)
Loading Pressure (i)
RSS
TOTAL RSS
Loading Specification (I) (2)
Tolerance on Propellant Temperature
of Flight Load
FUEL
(ib)
±24
_18
± 6
±54
± 5
I 0
± 8
± 63
±124
OXIDIZER
(Ib)
_39
±46
±i0
±86
± 5
0
±14
J_
±107
_0 ±0
-+0 +0
TOTAL LOADING UNCERTAINTY ±124
MISSION UNCERTAINTIES
Mixture Ratio Variation
_V, I Vehicle Weight Variation
sp'
Propellant usage uncertainty due to
total loading uncertainty
TOTAL PROPELLANT UNCERTAINTY FOR
MISSION 8V
+ 65.5
-512.7
+422.2
-419.0
+ 75.9
-132.4
+434.0
-675.3
NOTES: (1)
(2)
Data will be known after loading is accomplished.
Loading specification is an allowable tolerance about
nominal, this number is added to the loading uncertainty
variables.
3.3 -54 SNA-B-D-027(III)REV 2
Amendment 79
3130170
TABLE 3.3-14
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.
A. Tank Volume @ 0.0 PSIA (in 3)
B. Liquid Line Volume (in 3)
C. Total A + B (in 3)
D. Initial Weight in Bleed Unit
Prior to Loading (Ib)
E°
F°
G,
H.
I.
J°
FUEL OXIDIZER
K°
L.
Tank ATank B Tank A
1472.8 1474.7 1789.2
21.0 17.4 17.1
1493.8 1492.1 1806.3
148.6 103.3 196.6
104.4 59.1 118.3
44.2 44.2 78.3
44.2 44.6 77.8
70.0 70_0 69.0
44.2 44.2 78.3
Tank B
1787.0
16.4
1803.4
116.7
38.4
78.3
78.5
69.0
78.3
Final Weight in Bleed Unit
After Loading (ib)
Propellant Load (item D less
than E Weigh Tank)
Propellant Load by P.V.
Loading Temperature ("F)
Specification Propellant
Load @70_5"F (Ib)
Total CM/RCS Propellant
Load from Item G above (ib) 88.8 156.3
23.1
133.2
Maximum Trapped Propellant (Ib) 13.3
Nominal Deliverable (Ib) 75.5
3.3-55 SNA-8-D-O27(III)REV 2
ILl 111 I_ L: L E E L L E1_ E_ |; E E L L _ L
Amendment 79
3/30/70
TABLE 3.3-15
SERVICE MODULE RCS LOADING SU_4ATION
This table will be completed when loading is accomplished. For Mission Plan-
nlns, reference should be made to Section 4.2, for nominal load, loading
tolerances, and nominal deliverable propellants.
quad A (ib) quad B(Ib)
Secondary fue_ 40,2 Secondary fuel* 39.8
Primary fuel 70.2 Primary Fuel 69.7
Total fuel 110.4 ±0.7 Total fuel 109.5 t0.7
Maximum Trapped 2.1 Maximum Trapped 2.1
Nominal Deliverable 1083 Nominal Deliverable i07t4
Total Oxidizer
Maximum Trapped
Nominal Deliverable
225.6 +2.3
A.5 Total Oxidizer 22_,5
Maximum Trapped 4.5
Nominal Deliverable 221,0
*2.3
Quad C(Ib)
Secondary fuel* 40.0
Primary fuel 7U.l
Total fuel 1101'0.7
Maximum Trapped 2.1
Nominal Deliverable 1080
Total Oxidizer 225.4 '2.3
Maximum Trapped ,4.5
Nominal Deliverable 220.9
quad D(lb_
Secondary fuel*= 3g.8
Primary fuel I0._
Total fuel Ii0,i
Maximum Trapped 2.1
Nominal Deliverable i08.0
226.2Total Oxidizer
Maximum Trapped 4.5
Nominal Deliverable 221.7
t0.7
*2.3
Total fuel
Maximum Trapped
Nominal Deliverable
Total SM/RCS Propellant Load (lb_
440,1 ±1.4 Total Oxidizer 902.7
R_4 Maximum Trapped IR__
431.7 Nominal Deliverable 884.7
14.6
*Secondary fuel load for all quads determined by P. V. calculations.
3.3-56 SNA-8-D-027(III)REV 2
II
Amendment 79
3/30/7o
TABLE 3.3-16
LM-7 Consuuunble Loading ltequiraments
LM- 7APS Propeller
Fuel _Ib_ Oxidizer _Ib 1
Propellant Load 2014.2 3228.2
Trapped Outside Tanks 5.6 7.8
Tanked 2008,6 3220.4
Trapped Inside Tanks 9.1 26.4
Nominal Deliverable 1999.5 3194.1
Outage TBD TBD
Total APS Propellant TBD
NOTES:
The following table should be used to determine the amount of propellant
to be off-loaded from a full condition to arrive at the indicated load.
The allowable tolerance for the calculeted off-load is _0.5 pounds per
weigh tank.
A. Final tank pressure at overfill (PSIG) 49.3 51.9
B. Propellant loading temperature (OF) 69.2 67.4
C. Nominal overfill quantity (Ib) 2074.1 3317,7
D. Correction for tank pressure (ib) 0,8 it8
Fuel - 0.09 (Item A-40)
Oxidizer -0.15 (Item A-40)
IE. Correction for loading temperature (Ib)
Fuel --1.16 (Item B-65i -4.9 -6.8
Oxidizer =-2.84 (Item B-65)
2F. Measured density (GM/CC) 0.8992 ]_4_I?
2G. Nominal density (GM/CC) 0,8994 1.4824
H. Delta density (GM/CC) (Item F-G) -0.0002 -0,0007
3I. Correction for measured density
Fuel =2300 (Item H) -0.5 -1.6
d Oxidizer - 2300 (Item N)
J. Propellant in GSE i_6 4.8
K. Overfill quantity (C+D+E+I+J) 2071ti 3315.9
L. Target loading 2014,4 __9228.2
H. Quantity required to fill RCS manifolds 7.9 12.7
N. Quantity to be off-loaded (Items K-L-M) 48.8 75.0
1Load::ng temperature correction will always be negative.
2To calculate the nominal density solve the followingoequation where T-
teomperature in °C of the measured density (usually 4C for oxidiser and
25 C for fuel). This equation is valid for 14.7 PSIA. Therefore, the
measured density must also be at 14.7 PSIA.
Nominal fuel density - 0.922904-0.0009377 ('C)
NoB,trial oxidizer demJity -1.491539-0.0022832 ('C)
3Correction for measured density amy be either positive or nelative.
3.3-57 SNA-8-D-O27(III)REV 2
lU ILl L: EE L E L" E L.' H E L' ' "
L. i_. L
TABLE 3.3-16 (Continued)
LM-7Conaumable Leaden ilbmquirementa
LM-7 DPS Propellant
Amendment 79
3/3O/7O
Fuel tlb) Oxidizer (lb_
Propellant Load 7083r6 11350,9
Trapped Outside Tanks 35.1 60,5
Tanked 7048.5 11290.4
Trapped Inside Tanks 21.7 62.7
Nominal Deliverable 7026,8 11227,7
Outage TBD TBD
Total DPS Propellant Available TBD
The following table should be used to determine the amount of propellant to be
off-loaded from a full condition to arrive at the indicated load. The allowable
tolerance for the calculated off-load is _0.5 pounds par welsh tank.
AI. Final tank pressure at overfill (PSIG) 41,8 53t6
B1. Propellant loading temperature ('F) 69.96 67,7
CI. Nominal overfill quantity (ib) 7159.1 i1462,3
DI. Correction for tank preseure (ib) 0,6 6. 9
Fuel =0.31 (Item AI-40)
Oxidizer -0.51 (Item AI-40)
Correction for loading temperature (lb) -19.8 -26.6
A Fuel - -4.0 (Item BI-65)
Oxidizer --9.85 (Item BI'65)
Measured density (GM/CC) 0.8992 ]_4R]7
Nominal density (GM/CC) 0.8994 1,4824
Delta density (GM/CC)(Item Fl-Item Gl) -0,0002 -0,0007
Correction for measured density -1.6 -5.5
Fuel = 7900 (Item Hl)
Oxidizer -7900 (Item HI)
Propellant in GSE 2.3 3.8
Overfill quantity (CI+DI+EI+II+JI) 7140.6 11440.9
Target loadlns 7083.7 11351.1
Quantity required to fill RCS mmnifolds (APS only) xxxx_x xxxxxx
Quantity to be off-loaded (Items KI-LI-MI) 56,8 89,8
IEI.
2F1.
2GI.
HI.
311.
Jl.
KI.
LI.
MI.
N1.
NOTES:
ILoading temperature correction will always be negative,
2To calculate the nominal density solve the followin8 equation where
T-temperature in "C of the measured density (usually &eC for oxidizer
and 25"C for fuel). Th£a equation is valid for 14.7 PSIA. Therefore.
the measured density must also be at 14.7 PSIA.
Nominal fuel density - 0.922904-0,0009377 (*C)
Nomlnal oxidizer denalty - 1.491539-0.0022832 (eC)
3Correction for measured density amy be either poeiCtva or n_lativa
3.3-58 SNA-8-D-027 (I II) REV 2
Ik.
TABLE 3.3-16 (Continued)
I/4-7 - RCS Propellant (2) (3)
System AFuel
System A Oxidizer
System B Fuel
System B Oxidizer
Required Ullage Requirement (in _)
Load _ib) 5 M_n4_um _ Max_m,,_ _
107.7'0.9 IIi.0 123.0
208.8'1.9 225.5 237.5
I07.7*0.9 Iii.0 123.0
208.8'1.9 225.5 237.5
FUEL OXIDIZER
Propellant Load 215.4 417.6
Trapped Outside Tanks 10.8 17.6
Tanked 204.6 400.0
Trapped in Tanks 4.2 8.0
Nominal Deliverable 200.4 392.0
Amendment 80
418170
*Actual _
Load (lb)
107,7
208.8
107.7
208.8
_Actual "
Ulla&e (In 3)
132.0
205.7
134.0
_lq_o
LM-7 - Helium & Nitrogen
Consumable
Helium - APS tank #1 (6)
-APS tank #2 (6)
-RCS tank #I (6)
-RCS tank #2 (6)
- DPS (SHe)
-DPS (Ambient)(6)
Nitrogen - Ascent
- Descent
Nominal LoadinS Requirement Actual
Pressure Temp Weight Pressure Temp
(PSIA) ('F) _ib) (PSIA) ('F)
3050 70" 6.6 3115 75.0
3050 70" 6.6 3203 76.4
3050 70o 1.05 3126 82.3
3050 70 ° 1.05 3099 81.1
80*2 N/A 48.5 __
1600 70 °I.I 1653 78.3
0.1 N/A N/A
0.6 N/A N/A
Weight
(lb)
LM-7-Water & GOX
Consumable
Ascent Water - tank #i
- tank #2
Descent Water
Ascent COX - tank #I (6)
-tank #2 (6)
Descent GOX (6)
Nominal Loadin_ Requirement Actual
Pressure Weight Pressure Weight
(PSIA) _Zb) (PSIA) (Zb)
N/A 42.5 N/A (99.6%) 42.3
N/A 42.5 N/A (99.2) 42.1
N/A (7) N/A (99.6) 264*
830 2.4 841 (720F) -
830 2.4 838 (72°F) -
2700 48.0 2776 (80°F) -
*As serviced, predicted at lift-off is 254 lb.
NOTES:
Isee Table 3.3-17 for actual propellant load calculation.
2See Section 5.6 for explanation of trapped propellants.
3See Table 3.3-18 for loading uncertainties.
"PV ullage calculation should be 125*50 cubic inches for LM/RCS fuel and
238.5'50 cubic inches for LM/RCS oxidizer per tank.
5LM/RCS required load includes propallant required to fill RCS manifolds
to isolation valves. See Table 3.3-16. See Section 5.6 for trapped
propellants.
6The indicated items should be loaded in accordance with loading windows
contained in the CSM/LM Spacecraft Operational Data Book, Volume II,
Part 2, SNA-8-D-027PT2.
7LM-7 Descent Water load at Earth Launch shall be 250 -0, +i0 pounds.
The initial load will be determined by samplinR reouirements.
3.3-59 SNA-8-D-O27(III)KEV 2
Amendment 79
3/30/70
TABLE 3.3-17
LOAD CALCULATION
APS PROPELLANT Fuel Oxldi_er
i. Full tank -Item K, Table 3.3-16 (Ib) 20"7_ 3315.9
12. Density of off-load tables at loading
temperature and pressure (lb/ft 3) N/A N/A
13. Propellant volume (divide item 1 by
item 2. (ft 3) N/A N/A
14. Measured density (from Table 3,3-19)
(ib/ft H) N/A N/A
5. Resulting full tank load (ib) 2071.1 3315.9
6. Off-load amount (ib) 49.0 75.0
7. Propellant required to fill RCS manifolds
(ib) 7,9 12.7
8. Propellant load (Ib) 2014.2 3228.2
DPS PROPELLANT
9. Full tank -item K1 Table 3.3-16 (Ib) 7140.6 11441.9
ll0. Density of off-load tables st loadin8
temperature end pressure (ib/ft 3) N/A N/A
iii. Propellant volume (divide Item 9 by Item
10 )(ft 3) N/A N/A
112. Measured density (from Table 3.3-19)
(Ib/ft 3) N/A N/A
13. Resulting full tank load (ib) 7140,6 11440.9
14. Off-load amount (ib) 57.0 90.0
15. Propellant load (ib) 7083.6
RCS PROPELLANT
P. V. Calculations Fue____l Oxidizer
Tank ATank BTank A Tank B
NOTE:
A. GSE Volume (In 3) 18.45 37.& 17.94 30.25
B. Initial lJlla_p Pr*-..ure
(PSIC) 33.7 33.a 34,9 34.6
C. Initial GSE Pre.sure
(PSlC) i.o o.5 o.o o.o
D, Final GSE - S/C Pressure
(PSIG) _ 26.2 32.1 30.4
E. Ullage Volume (in 3) -Solve _134 205 7219.01
the following equation by
substitutin8 the values in
the indicated step|.
(D-C) (A)
Ullase Volume - B-D
lTheae items will be completed only if 8 density 8ample Is not
made prior to loadin8. If 8 density nmple ia made prior to
loadin$, then the item- will be left blank.
NASA _ MSC
il 11 11 E li- L
3.3-60 SNA-8-D-O27(III)REV 2
LLLL_ L K L; L_ L_ Lk_ LL,. L
An_.ndment 79
3/30/70
Vent llne Volume
Tank Volume
Pressure Measurement (±5 PSIA)
Temperature Measurement (ZI.5°F)
Measured Density
2Welght Measurement
tLoadlng Tolerance
Total Loading Uncertainty
APS Mission Uncertainties
TABLE 3.3-18
LM-7 Propellant Loading Uncertainties
LM-7 AP$ PROPELLANT
Fue! (Ib)
±0.2
zO.8
_0.5
±1.7
zO.7
zO.5
±0.0
±4.4
Oxidizer (!b)
_0.3
tl.3
tO.8
z4.3
zO.5
zO.5
±OtO. .
±7.7
Mixture Ratlo Variatlon -34.6
_V, !sp, Vehicle Weight Variation -54.0
Propellant Usage Uncertainty Due To Total -9.7
Loading Uncertainty
Total Propellant Uncertainty ForMisslon _V -64.9
LM- 7 DPS PROPELLANT
Vent Line Volume ±0.2
Tank Volume ±3.4
Pressure Measurement (Z5 PSTA) _1.6
Temperature Measurement (1.5°F) Z6.1
Measured Density ±2.4
2Weight Measurement _0.5
1Loading Tolerance _OmO
Total Loading Uncertainty ±14.2
±0.3
Z5.6
Z2.6
Z14.8
±1.6
Z0.5
±0.0
±25.4
DPS Mission Uncertainties
Mixture Ratio Variation -115.7
_V, Isp, Vehicle Weight Variation -341.2
Propellant Usage Uncertainty Due to Total
Loading Uncertainty -29.3
Total Propellant Uncertainty For Mission AV -361.5
LM-7 RCS PROPELLANT
Loading Temperature ±0.6 ±1.8
Ullage Calculation ±0.4 ZO.6
Tank and Manifold Volume _0.8 ±1.4
Total ±1,8 Z3.8
1These will be known quantities after loading is accomplished.
21f weigh tank is used for off-loadlng, than weight measurement uncertainty
is _0.5 pounds per weigh tank. If flow meter is used for off-loadlng, then
weight measurement uncertainty is Z4.0Z of amount off-loaded.
I
lJ
3.3-61 SNA-8-D-027 (III)REV 2
L_ k_
TABLE 3.3-19
Amendment 79
3/30/70
LM-7 APS Propellant Loading Parameters
(To Be Completed by KSC at Loading)
Fuel Oxidizer
Loading Pressure -PSIA 64.0 66.6
G58 Fuel
Loading Temperature -Flll Llne- Degrees F 258 Oxidizer 69.1 66.8
_TT 59 Fuel
Loading Temperature - Return Llne- Degrees FITT259 Oxidizer 69.3 68.0
_GP0718 Fuel
Loading Temperature - Tank - Degrees FlGP1218 Oxidizer 68.2 67.7
Number of Times Weigh Tank Used (Flow Meter Not Used) i 1
Total Pounds Off-Loaded Using Weigh Tank (Flow Meter Not Used) 49.0 75.0
Pounds Off-Loaded Using Flow Meter (Weigh Tank Not Used) N/A N/A
Measured Fuel Density @_; @ 14.7 PSIA GM/CC 0.8992 -
Measured Oxidizer Density @4°C; @ 14.7 PSIA GM/CC 1.4817
3.3-62 SNA-8-D-O27(III)REV 2
Amendment 79
3130170
TABLE 3.3-19 (Continued)
LM-7 I_S Propellant Loading Par_aeters
Loading Pressure - PSIA
_TT 58 Fuel
Loading Temperature - Fill Line -Degrees F ITT258 Oxidizer
ITT 59 _el
Loading Temperature - Return Line - Degrees FITT259 Oxidizer
I_3718 Fuel
Loading Temperature -Tank One - Degrees F|C_4218 Oxidizer
_JGq3719 Fuel
Loading Temperature - Tank Two -Degrees -[GQ4219 Oxidizer
Number of Times Weigh Tank Used (Flow Meter NoC Used)
Total Pounds Off-Loaded Using Weigh Tank (Flow Meter NoC Used)
Pounds Off-Loaded Using Flow Meter (Weigh Tank Not Used)
Measured Fuel Density @ 25°C; 14.7 PSIA GM/CC
Measured Oxidizer Density @ 4°C; 14.7 PSIA GMICC
Fuel
69.7
1
57.0
NIA
0.8992
..__i_
Oxidizer
68.3
67.7
67.7
6_Z_78
67.4
1
90.0
N/A
1.4817
3.3-63 SNA-g-D-O27(III)KEV 2
UELELL-
_nendment 74
1/14/70
MISSION H-2 MASS PROPERTY DATA TABLES
Unless otherwise stated, the controlling vehicle propellants are in the low
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) mass properties, in Apollo
coordinates, as a function of spacecraft weight for the
Hybrid SM/SPS burn.
Table 3.3-21 presents the CSM-109/LM-7 (docked) mass properties, in Apollo
coordinates, as afunction of spacecraft weight for L.O.I.
SM/SPS burn.
Table 3.3-22 presents the CSM-109/LM-7 (docked) mass properties, in Apollo
coordinates as a function of spacecraft weight for the
D.O.I. SM/SPS burn.
Table 3.3-23 presents the CSM-I09 mass properties, in Apollo coordinates,
as a function of CSM weight for the Circularlzatlon I SM/SPS
burn.
Table 3.3-24 presents the CSM-I09 mass properties, in Apollo coordinates,
as a function of CSM weight for the Plane Change I SM/SPS
burn.
Table 3.3-25 presents the CSM-I09 mass properties, in Apollo coordinates,
as a function of CSM weight for the Plane Change II SM/SPS
burn.
Table 3.3-26 presents the CSM-I09 mass properties, in Apollo coordinates,
as a function of CSM weight for the T.E.I. SM/SPS burn.
Table 3.3-27 presents the LM-7 mass properties, in LM coordinates, as a
function of LMwelght for the P.D.I. DPS burn.
Table 3.3-28 presents the LM-7 ascent stage mass properties, in LM coordinates
as a function of weight for the lunar llftoff APS burn.
Table 3.3-29 presents the LM-7 mass properties, in LM coordinates, as a
function of LM weight for the C.S.I. to docking LM/RCS burn.
3.3-64 SNA-8-D-027(III)REV 2
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Amendment 79
3130170
LM-7 Ascent Stage Lunar Lift-off Contingencies Mass Properties
Table 3.3-30 presents the LM-7 Ascent Stage Mass Properties for the
three contingency cases. The detail equipment mass properties for
this table are presented in Table 3.3-32.
Table 3.3-31 presents the CM re-entry mass properties associated
with each of the LM-7 Ascent Stage contingencies in Table 3.3-30.
Table 3.3-33 presents the detail equipment mass properties.
3.3-81 SNA-8-D-027(III)REV 2
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Amendment 08
1/22/71
SUPPLEHENTARY DATA APPLICABLE TO SEQUENTIAL MASK PROPERTIES TABLES
General Comments to be applied to Tables 3.4-1 through 3.4-8:
Inertia data dispersions are +10%.
m
Dispersions shall be used as 3c deviation v_Jues.
All initial propellant weights are total tonked.
The (+) or (-) si_ followln8 the name of an item indicates that
the item is added to or subtracted from the preceding total.
Table 3.4-1
SM/SPS simbal angles for SPS abort sequence _re: Pitch - -1.417 deg.
Yaw - 1.315 des.
Table8 3.4-7 and 3.4-8
CSM and LM consumables changes are pre_ented in Tables 3.4-7 and
3.4-8, respectively.
Tables 3.4-4 and 3.4-5
Delta Z
LES motor tilted angles
(Delta includes 0.3 deE. for
down range dispersions)
LES motor tilted confluence point
PO_ motor tilted 8nsJ.ee
PCM motor tilted confluence point
- 0.85 in.
Delta = 2.260 des.
Sigma - 273.810 des.
X -1222.300 in.
Y=0.043 in.
Z=0.280 in.
Delta =89.i60 des.
Sigcua =270.000 des.
X=1429.000 in.
Y - 0.517 in.
Z - 3.320 in.
The docking probe and rlng are Jettisoned at t-14.0 seconds in Table 3.4-4
and Table 3.4-5.
I
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Amendment 98
1/22/71
TABLE 3.4-7
CSH ii0 Consumables Weight Change Summary
(To be used in conjunction with the CSM sequential mass properties Table 3.4-2)
EVENT
From To Consumable
Weight Amount Total
Change Remaining Usage
(Pounds) (Pounds) (Pounds)
Earth Launch Pre Trans/Dock SM-Hydrogen -0.5 54.7 -0.5
SM-Oxygen -11.4 819.9 -11.4
CM-Potable +4.0 40.0
CM-Waste +0.8 18.8
Pre Trans/Dock Post Trans/Dock SM-RCS -70.6 1270.0 -70.6
Post Trans/Dock Pre SPS Hybrid SM-Hydrogen -4.9 49.8 -5.4
SM-Oxygen -54.3 765.6 -65.7
SM-RCS -70.3 1199.7 -140.9
CM-Waste H20 +41.2 60.0
CM-LiOH +6.8 6.8
CM-Food -3.8 -3.8
Pre SPS Hybrid Post SPS Hybrid SM-SPS -724.3 39829.6 724.3
Post SPS Hybrid Pre L.O.I. SM-Hydrogen -9.4 40.4 -14.8
SM-Oxygen -93.9 671.7 -159.6
SM-RCS -65.5 1134.2 -206.4
CM-Food -9.4 -13.2
CM-LiOH +6.8 13.6
Pre L.O.I. Post L.O.I. SM-SPS -24777.8 15051.8 25502.1
Post L.O.I. Pre D.O.I. SM-Hydrogen -0.5 39.9 -15.3
SM-Oxygen -8.5 663.2 -168.1
SM-RCS -30.4 1103.8 -236.8
Pre D.O.I. Post D.O.I. SM-SPS -1470.8 13581.0 26972.9
Post D.O.I. CSM/LM Separation SM-Hydrogen -3.4 36.5 -18.7
SM-Oxygen -31.2 632.0 -199.3
SM-RCS -134.0 969.8 -370.8
CM-LIOH +5.0 18.6
CM-Food -3.8 -17.0
CSM/LM Separation Pre Circular- SM-Hydrogen -0.3 36.2 -19.0
ization SM-Oxy gen -2.0 630.0 -201.3
SM-RCS -26.3 943.5 -397.1
Pre Circular- Post Circular- SM-SPS -272.9 13308.1 27245.8
ization ization
3.4-21 SNA-8-D-O27(III)REV 2
Amendment 98
1/22/71
TABLE 3.4-7 (CONTINUED)
CSM 110 Consumables Weight Change Summary
(To be used in conjunction with the CSM sequentlal mass properties Table 3.4-2)
Weight Au_unt Total
EVENT Change Remaining Usage
From To Consumable (Pounds) (Pounds) (Pounds)
Post Circular- Pre Plane Change SM-Hydrogen -2.4 33.8 -21.4
Ization SM-Oxy gen -25.1 604.9 -226.4
SM-RCS -75.8 867.7 -472.9
Pre Plane Change Post Plane Change SM-SPS -1269.2 12038.9 28515.0
Post Plane Change CSM/ASCT Docking SM-Hydrogen -4.9 28.9 -26.3
SM-Oxygen -47.4 557.5 -273.8
SM-RCS -135.2 732.5 -608.1
CM- Food -6.3 -23.3
CM-LtOH +7.8 26.4
CM-Fe_al +2.2 2.2
CSM/ASCT Docking Pre T.E.I. SM-Hydrogen -1.1 27.8 -27.4
SM-Oxy gen -9.3 548.2 -283.1
SM-RCS -41.9 690.6 -650.0
CM-Fec al +I. 13.3
CM-Food -3.8 -27 .i
CM-LIOH +2.6 29.0
Pre T.E.I. Post T.E.I. SM-SPS -10059.4 1979.5 38574.4
Post T.E.I. SM Jettison SM-Hydrogen -11.8 16.0 -39.2
SM-Oxygen -127.3 420.9 -410.4
SM-RCS -179.9 510.7 -829.9
CM-LIOH +13.4 42.4
CM-Food - 10.4 - 37.5
CM-Fecal +3.3 6.6
SM Jettison CM @ Entry _-RCS -11.6 233.4 -11.6
CM @ Entry CM @ M.C. Deploy CM-RCS -30.7 202.7 -42.3
CM @ M.C. DePloy CM @ Impact CM-RCS -202.7 0.0 -245.0
3.4-22 SNA-8-D-027"_III) KEV 2
LI II ]_ L 1: 1:'. L L l_ h 1_ E E l_ E E L: LLE_
Amendment 98
1/22/71
TABLE 3.4-8
LM-8 Consumables Change Summary
To be used in conjunction with the LM lequentlal mass properties Table 3.4-2)
Weight Amount Total
EVENT Consumable Change Remaining Usage
From To (Pounds) (Pounds) (Pounds)
Earth Orbit CSM/LM Separation D/S-Oxygen -1.1 46.9 -1.1
D/S-Water -i 3.0 237.0 -13.0
LM-RCS -5.0 600.0 -5.0
CSM/LM Pre P .D .I. D/S-Oxygen -I.0 45.9 -2. i
Separation D/S-Water -21.3 215.7 -34.3
LM-I_ S -55.5 545. i -60.5
Pre P.D.I. LM @ Touchdown D/S-Oxygen -0.i 45.8 -2.2
D/S-Water -I.I 214.6 -35.4
LM-I_S -97.0 448.1 -157.5
LM-DPS 17,332.5 989.1 17,332.5
A/S @ Touchdown A/S at Lift-Off LM-RCS -5.0 443.1 -162.5
A/S @ Llft-Off A/S in Orbit LM-APS 4931.1 279.9 4931.1
A/S in Orbit Pre T.P.I. A/S-Water -5.0 80.0 -5.0
A/S-Oxygen -0.3 4.5 -0.3
LM- RCS -47.4 395.7 209.9
Pre T.P.I. Post T.P.I. LM-APS 56.9 223.0 4988.0
A/S @ Post T.P.I. A/S @Docking A/S-Water -3.8 76.2 -8.8
A/S-Oxygen -0.2 4.3 -0.5
LM-RC S 70.2 325.5 -280.1
A/S @ Docking A/S Jettison A/S-Water -8.2 68.0 -17.0
A/S-Oxygen -0.4 3.9 -0.9
NOTE :
Tanked LM RCS Propellant should be reduced by 0.3 ib
0.7 ib oxidizer.
fuel and
3.4-23 SNA-8-D-027(III) KEV 2
I
r)
p,-,i
r_
I
I
Amendment 98
1/22/71
TABLE 3.4-9
MISSION H COHHAND NODULE STOWAGE VOLLq4ZCENTROIDS
S/C 109 - 111
._Or
41
3
4
5
6
7
8
10
11
12
13
al
2
3
4
5
6
7
8
L2
3
I1
2
3
4
5
6
8
10
10
11
13
U1
3
4
- NoC on S/C 110
- S/C 110 Only
- Not on S/C 110
x ! z
1012.0 -22.0 -26.0
1016.0 -24.0 28.0
1015.0 - 7.0 28.0
1015.0 9.0 28.0
1017.0 26.0 28.0
1012.0 31.0 7.0
1012.0 22.0 -23.0
1011.0 23.0 6.0
1011.0 19.0 7.0
1013.0 -9.0 14.0
1010.0 -22.0 - 2.0
1050.0 -27.0 39.0
1039.0 -38.0 37.0
1031.0 -28.0 40.0
1031.0 -20.0 40.0
1031.0 - 8.0 39.0
1031.0 13.0 39.0
1033.0 27.0 36.0
1024.0 -38.0 37.0
1059.0 -44.0 14.0
1048.0 -47.0 12.0
1072.0 26.0 21.0
1072.0 26.0 14.0
1072.0 26.0 9.0
1075.0 28.0 3.0
1059.0 44.0 15.0
1048.0 46.0 29.0
1052.0 46.0 12.0
1053.0 47.0 5.0
1047.0 48.0 5.0
1038.0 47.0 26.0
102&.0 45.0 -26.0
1033.0 23.0 -50.0
1033.0 -36.0 -44.0
1038.0 39.0 -43.0
3.4-25 SNA-B-D--O27(III)REV 2
Amendment 98
1/22/71
TtbZe 3.4-9.Z
,'he followtn8 8tovase locations have unique voXume cemtroid8
not associated vtth etovese volumes.
I
NOHENCLATURE
G&N Siena1Cond. Panel
Display Keyboard
Sleep Restraint Assy -Risht
Sleep Restraint kssy - Left
Food ContaLner
Food (_ontetner
to(eL .rewaKe Container
PCA £_ntainer
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.
(Xn-tltsht Location)
Tempo_8c) StovaBe 888 - R.H.
(In. fltsht Location)
CO A_sorbers (2)
C_2 At_rbers (h)
CO_ Absorbers (&)
CO Absorbers (2)
CO_ Absorbers (h)
CO2Absorbers (6)
First 6.8 lb. CO2Absorbed
Next 6.8 lb. CO_ Absorbed
Reuminder CO2 Abe6rbed
LO TXO. A , Z
LH 1069.0 25.0
LE| 1060.0 26.0
Aft UF.JI 1020.0 25.0
Aft UE8 1018.0 -21.0
L3 1046.0 -47.0
81 1050.0 -27.0
IU/E8 1039.0 &7.O
O_ Aft |ulkheod 1011.0 0.0
Under Center
Couch
Under L.R. Couch 1018.0 -24.5
E.H. Girth Etn8 1036.5 40.0
L.H. Girth Rln8 1036.$ -40.0
LE8 1050.0 -27.0
R.H. Girth Rtn8 1036.5 &O.O
LHE8 1039.0 -47.0
LE| 1050.0 -27.0
tHE| 1039.0 47.0
In ECU 1031.0 -48.3
A3 IO16.O -2&.O
A& 1015.0 - 7.0
A6 1017.0 26.0
|S 1031.0 -6.0
16 1031.0 13.0
CosqJoeite Loce-
tLon used in
Sequential 14_s
Properties Tables
Yet CO2 Absorbed.
85 1031.0
16 1031.0
Composite Lots- IO18.$
tlon
Z
29.0 "
32.0
-22.0
-49.9
12.0
39.0
12.0
--I_ .0
-15.0
-25.0
-25.0
39.0
-25.0
12.0
39.0
12.0
19.6
28.0
28.0
28.0
39.0
39.0
-8.0 39.0
13.0 39.0
-14.3 26.1
3.4-26 lIilA-.8-D-O27(III)i_V 2
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TABLE 3.4-10 (CONTINUED)
command Module Water and GOX
Amendment i00
1/28/71
Waste Water 6
Potable Water 7
CM/GOX
Pressure
(PSIA)
900±50
Loading Requirement
Weisht (ib)
3.7
8Service Module Hydrogen and Oxygen
Earth Launch Actual
Weisht (ib) (ib)
18.0 33.0
36.0 31.4
6.7 (Entry)
Hydrogen
Tank 1
Tank 2
Oxygen
Tank i
Tank 2
Tank 3
Loading Requirement
(pounds)
Earth Launch Weight
(pounds)
29.3
29.3
330.i
330.1
330.1
27.6
27.6
316.6
316.6
198.1
Actual
(ib)
27.2
27.2
316.9
316.9
204.7
NOTES:
llndicated propellant load is based on nominal pressure and temperature
prior to actual loading. This number will be updated after loading
is accomplished.
2See Section 4.1 for explanation of trapped SPS propellant.
3See Table 3,4-13 for loading uncertainties.
4See Section 4.2 for SM/RCS loads and uncertainties to be used in Mis-
sion Planning. Actual SM/RCS loads and uncertainties will be published
in Table 3.4-15.
5See Section 4.2 for CM/RCS loads and uncertainties to be used in Mis-
sion Planning. Actual CM/RCS loads and uncertainties will be published
in Table 3.4-14.
6Launch Rule Redlines determine llft-off values.
7Launch Rule Redlines determine lift-off values.
8Launch Mission Rules will determine minimum lift-off quantities for
H 2 and 02.
9CSM helium and nitrogen should be loaded in accordance with loading
windows contained in CSM/LM Spacecraft Operational Data Book, Volume I,
Part 2, SNA-8-D-027(1) P2.
3.4-85
SNA-8-D-027(III)REV 2
TABLE3.4-11
SPS PROPELLANT LOAD CALCULATIONS
i. Enter SPS Quantity Readout at Ii0 PSIA (Table 3.4-12
Item C - Percent)
2. Use Figures 4.1-3 and 4.1-4 to obtain propellant
load for above quantity readout.
3. Nominal propellant density at loading temperature
(use temperature - density graph below) (ib/ft 3)
4. Cubic feet of propellant (Item 2 divided by Item 3)
5. Calculated density from Table 3.4-12 Item F (ib/ft 3)
6. Adjustment due to PUGS zero adjust (pounds)
7. Resulting actual propellant load (Item 4 times
Item 5, less Item 6) (pounds)
Amendment 98
1/22/71
Fuel Oxidizer
100.8 100.85
15688.0 25079.5
56.428 _46
278.017 276.485
56.454 90.279
15695.2 25061.0
SPS SPS
Oxidiser FUEL SPS Propellant Tempersture/Density Graph
at 110+5 PSIA
D
E
N
S
!
T
Y
LB/F'r 3
3.4-86
SNA-8-D-027 (III) REV 2
H L L L ;
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Amendment 98
1/22/71
TABLE 3.4-13
SPS PROPELLANT UNCERTAINTIES
ITEM
LOADING UNCERTAINTIES
Tank Volume
Temperature Gauge (±2.0"F)
Standpipe Height
Propellant Gauge (±0.35% of Gaugeable)
Density Measurement (1)
Batch Density (I)
Loading Pressure (i)
FUEL
(lh>
±24
±18
+6
±54
±5
±0
+-8
OXIDIZER
(Ib)
±39
±46
±I0
±86
±5
+-0
+-14
RSS ±63 ±107
TOTAL RSS ±124
±0
Loading Specification (1) (2)
Tolerance on Propellant Temperature
of Plight Load
+-0
±0 ±0
TOTAL LOADING UNCERTAINTY ±124
NOTES: (1) Data will be known after loadlng is accompllshed.
(2) Loading specification is an allowable tolerance about
nomlnal, this number is added to the loadlng uncertainty
variables.
3.4-89 SI_-8-D-027(III)REV 2
ILl II 1_ l_ L E LLLLla LL; li 1'. I_ L_ ,_ L ._.
Amendment 98
1/22/71
TABLE 3.4-14
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.
FUEL OXIDIZER
Tank k Tank B Tank ATank B
A. Tank Volume @0.0 PSIA (in 3) 1472.8 l_ 1/_ /._
B. Liquid Line Volume (in 3) 21.0 17.4 17.1 16.4
C. Total A+B(in 3) 1493.8 1491.9 1806.0 1803.9
D. Initial Weight in Bleed Unit
Prior to Loading (Ib) 150.0 104.7 _
E. Final Weight in Bleed Unit
After Loading (Ib) 105.8 60.5 119.8 39,7
F. Propellant Load (item D less
than EWeigh Tank) 44.2 _AK2- 7s_2 78.3
G. Propellant Load by P.V. ___ 44_5 78.6
H. Loading Temperature (=F) 70_0 7on ___ __X2.AI
I. Specification Propellant
Load @ 70e5"F (Ib) _._.9 -._.9 _.__±1.6 7A _±1.6
J. Total CM/RCS Propellant
Load from Item G above (lb) 88.8 156.7
23.1
133.6
K. Maximum Trapped Propellant (Ib) 13.3
L. Nominal Deliverable (Ib) 75.5
3.4-90 SNA-8-D-O27(III)KEV 2
i: i: li L,' L L_ L
Amendment 98
1/22/71
TABLE 3.4-15
SERVICE MODULE RCS LOADING SUI'94ATION
This table will be couplecad when loading is accomplished. For Mission Plan-
ning, reference should be made to Section 4.2, for nominal load, loading
tolerances, and nomin_ deliverable propellants.
qtmd. a (ib) Quid [ (Ib)
Secondary fuel
Primary fuel
Total fuel
Maxim,-. Trapped
Nominal Deliverable
40_3 Secondary fuel 39.8
69.8 Primary Fuel 70.1
11_,_ *0.7 Total fuel 10_.9
MaximuaTrapped 2.1
108.0 Nomlnal Deliverable 707.8
*0.7
Total Oxidizer
Maximum Trapped
Nominal Deliverable
225.3 *2.3 Total Oxidizer 225.2
4.5 Max£mum Trapped 4.5
Nominal Deliverable 220.7
t2.3
Quad C (Ib). _uad D(ib)
Secondary fuel
Primary fuel
Total fuel
Maximum Trapped
Nominal Deliverable
40.4 Secondary fuel
70.0 Primary fuel
ii0.4 t0.7 Total fuel
PlJxiuumTrappad
108._ Nominal Deliverable
aq,q
69.7
log. 7tO. 7
2,1
Total Oxidizer _'2.3
Maximum Trapped 4.5
Nominal Deliverable _.n
Total Oxidiser
Maximum Trapped
Nominal Deliverable
_2.3 4.5
21q .0
Total S_RCS Propellant Load (lb)
Total fuel _40.I
Maximum Trapped 8.4
Nominal Deliverable 4_1.7
tl.4 Total Oxidizer
HaximumTrapped
Nominal Deliverable
900.5 *4.6
18.0
3.4-91 SNA-8-D-O27(III)REV 2
TABLE 3.4-16
LM-8 Consumable Loadin_ Requirements
LM-8 APS Propellant
Amendment 98
1/22/71
Fuel (Ib) Oxidizer (Ib)
Propellant Load 2007.0 3218.2
Trapped Outside Tanks 5.9 8.3
Tanked 2001.1 _209.9
Trapped Inside Tanks 10.1 27.6
Nominal Deliverable 1991.0 3182.3
Outage TBD TBD
Total APS Propellant TBD
The following table should be used to determine the amount of propellant
to be off-loaded from a full condition to arrive at the indicated load.
The allowable tolerance for the calculated off-load is _+0,5 pounds per
weigh tank.
A. Final tank pressure at overfill (PSIG) 60.3
B. Propellant loading temperature (°F) 6_,05
C. Nominal overfill quantity (Ib) 2072t_
D. Correction for tank pressure (ib) 1.8
Fuel - 0.09 (Item A-40)
AOxidizer =0.15 (Item A-40)
IE. Correction for loading temperature (Ib) -4.7
Fuel =-1.16 (Item B-65)
AOxidizer =-2.84 (Item B-65)
2F. Measured density (GM/CC) 0.8998
2G. Nominal density (GM/CC) 0.8994
H. Delta density (GM/CC) (Item F-G) 0.0004
31. Correction for measured density +0.92
Fuel - 2300 (Item H)
Oxidizer = 2300 (Item H)
J. Propellant in GSE 1.6
K. Overfill quantity (C+D+E+I+J) 2071.9
L. Target loading 2006.7
M. Quantity required to fill RCS manifolds 7.9
N. Quantity to be off-loaded (Items K-L-M) 57.3
4_.3
68.4
1.4
-9.7
1.4812
-2.76
4,8
_300.9
3218.1
12.7
7Q.1
NOTES:
iLoading temperature correction will always be negative.
2To calculate the nominal density solve the following equation where T=
temperature in °C of the measured density (usually 4°C for oxidizer and
25"C for fuel). This equation is valid for 14,7 PSIA. Therefore, the
measured density must also be at 14.7 PSIA.
Nominal fuel density - 0.922904-0.0009377 ("C)
Nominal oxidizer density = 1.491539-0.0022832 (°C)
3Correction for measured density may be either positive or negative.
3.4-92 SNA-8-D-O27(III)REV 2
Amendment 98
TABLE 3.4-16 (Continued) 1/22/71
LM-8 Consumable Loadin_ Requirements
LM-8 DPS Propellant
Fuel _ib) Oxidizer _ib)
Propellant Load 7072.8 11344.4
Trapped Outside Tanks 35.1 60.5
Tanked 7037.7 11283.9
Trapped Inside Tanks 31,8 134.7
Nominal Deliverable 7Q0 7,9 1 I149,2
Outage TBD TBD
Total DPS Propellant Available TBD
The following table should be used to determine the amount of propellant to be
off-loaded from a full condition to arrive at the indicated load. The allowable
tolerance for the calculated off-load is_+O.5 pounds per weigh tank.
AI. Final tank pressure at overfill (PSIG) 46.1
BI. Propellant loading temperature (°F) 68.05
CI. Nominal overfill quantity (ib) 7160.4
DI. Correction for tank pressure (Ib) 1.9
A Fuel =0.31 (Item AI-40)
Oxidizer = 0.51 (Item AI-40)
IEI. Correction for loading temperature (ib) -12.2
AFuel --4.0 (Item BI-65)
AOxidizer =-9.85 (Item BI-65)
2FI. Measured density (GM/CC) 0.8998
2GI. Nominal density (GM/CC) 0.8994
HI. Delta density (GM/CC) (Item Fl-Item GI) .0004
3Ii. Correction for measured density 3.16
Fuel -7900 (Item HI)
Oxidizer -7900 (Item HI)
Jl. Propellant in GSE _2.3
KI. Overfill quantity (CI+DI+EI+II+JI) 7155.6
LI. Target loading 7072.8
MI. Quantity required to fill RCS manifolds
(APS only) xxxxxx
NI. Quantity to be off-loaded
(Items KI-LI-MI) 82.8
49.6
67.0
11452.9
4.9
-19,7
1.4812
1.4824
3.8
i14_,4
11341.9
XXXXXX
90.5
NOTES:
ILoading temperature correction will always be negative.
2To calculate the nominal density solve the following equation where
T=temperature in °C of the measured density (usually 4°C for oxidizer
and 25°C for fuel). This equation is valid for 14.7 PSIA. Therefore,
the measured density must also be at 14.7 PSIA.
Nominal fuel density =0.922904-0.0009377 (°C)
Nominal oxidizer density =1.491539-0.0022832 (°C)
3Correctlon for measured density may be either positive or negatlve.
3.4-93 SNA-8-D-027(III)REV 2
LSystem A Fuel
System A Oxidizer
___SsSyStem B Fuel
tem BOxidizer
TABLE 3.4-16 (Continued)
LM-8 - RCS Propellant 42 ) 43 )
Required
Load (ib) 5
107.7±0.9
208.8±1.9
107.7±0.9
208.8±1.9
Amendment iO0
1/28/71
Ullage Requirement _ r-_-_
Minimum _ Maxlmum 4 Load lbU11a e in s)
_ 107.7 135.0 I
225.5 237.5 208.8 209.1 I
iii.0 123.0 107.7128.0 1
225.5 237.5 208.8 258.3 i
FUEL OXIDIZER
Propellant Load 215.4 417.6
Trapped Outside Tanks 10.8 17.6
Tanked 204.6 400.0
Trapped in Tanks 4.2 8.0
Nominal Deliverable 200.4 392.0
LM-8 - Helium & Nitrogen
Consumable
Helium - APS tank #i (6)
- APS tank #2 (6)
- RCS tank #I (6)
- RCS tank #2 (6)
- DPS (SHe)
- DPS (Ambient) (6)
Nitrogen - Ascent
- Descent
Nominal Loadin$ Requirement Actual
Pressure Temp Weight Pressure Temp Weight
4PSIA) (°F) 41b) (PSIA) (°F) (]b)
3050 70 6.6 3130 72.9
3050 70 6.6 3122 72.9
3050 70 1.05 3016 70.5
3050 70 1.05 3030 70.6
80_+2 N/A 48.5
1600 70 i.] 1612 68.9
0.i
0.6
LM-8 - Water & GOX
Consumable
Ascent Water - tank #i
- tank #2
Descent Water
Ascent GOX - tank #I (6)
- tank #2 (6)
Descent GOX (6)
Nominal Loading geRuirement Actual
Pressure Weight Pressure Weight
(PSIA) 41b) (PSI_) 41b)
N/A 42.5 N/A 42.5
N/A 42.5 N/A 42.5
N/A (7) N/A 254.0
830 2.4 850@73°F 2.4
830 2.4 850@73°F 2.4
2365 42.0 2377@72°F 42.0
NOTFS:
]See Table 3.4-17 for actual propellant load calculation.
2See Section 5.6 for explanation of trapped propellants.
3See Table 3.4-18 for loading uncertainties.
4PV ullage calculation should be 125_+50 cubic inches for LM/RCS fuel and
23R.5±50 cubic inches for LM/RCS oxidizer per tank.
5LM/RCS required load includes propellant required to fill RCS manifolds
to isolation valves. See Table 3.4-16. See Section 5.6 for trapped
propellants.
6The indicated items should be loaded in accordance with loading windows
contained in the CSM/LM Spacecraft Operational Data Book, Volume II,
Part 2, SNA-8-D-O27PT2.
7LM-8 Descent Water shall be loaded to provide 250-0.0+i0.0 pounds
at Earth Launch. Initial load will be determined by sampling requirements.
NASA -- MSC 3.4-94 S_ -S-D-027 (III) P,EV 2
li U ME E L L L h L EL I/ L,'. " ""
L.. L_ z_
Amendment 98
TABLE 3.4-17 I122/71
LOAD CALCULATION
APS PROPELLANT Fuel Oxidizer
I. Full tank - Item K, Table 3.4-15 (Ib) 2071.9 3300.9
12. Density of off-load tables at loading _ _
temperature and pressure (ib/ft 3)
13. Propellant volume (divide item Iby
item 2. (ft 3) - -
34. Measured density (from Table 3.4-19)
(ib/ft 3) --
5Resulting full tank load (Ib) 2071.9 3300.9
6. Off-load amount (lb) 57.0 70.0
7. Propellant required to fill RCS manifolds
(lb) 7.9 12.7
8. Propellant load (Ib) 2007.0 3218.2
DPS PRORPLLANT
9. Full tank - Item K1 Table 3.4-16 (ib)
Ii0. Density of off-load tables at loading
temperature and pressure (Ib/ft 3)
111. Propellant volume (divide Item 9 by Item
lO) (ft 3 )
7155.6 11432.4
112. Measured density (from Table 3.4-19)
(lb/ft 3)
13. Resulting full tank load (Ib)
14. Off-load amount (ib)
15. Propellant load (Ib)
RCS PROPELLANT
P. V. Calculations
_. GSE Volume (in 3)
B. Initial Ullage Pressure
(PSIG)
C, Initial GSE Pressure
(PSIG)
D. Final GSE - S/C Pressure
(PSIG)
EUllaze Volume (in 3) -Solve
the following equation by
substituting the values in
the indicated steps.
Ullage Volume -(D-C) CA)
B-D
7155.6 i1432.4
83.0 88.0
7072.6 11344.4
Fuel Oxidizer
Tank A Tank B Tank A Tank B
18.01 36.7 17.0 28.09
34.0 32.3 35.25 34.45
0.0 1.8 0.0 0.8
30.0 25.5 32.6 31.15
135.0 128.0 209.1 258.3
NOTE. :iThese items wlll be completed only If a density sample is not
made prior to loading. If adensity sample is made prior to
loading, then the items will be left blank.
3.4-95 SNA-8-D-027(III)REV 2
!1 Ul; L l_ K kLLL L k1_ li 11 it L: k L L
TABLE 3.4-18 Amendment 98
1/22/71
LM-8 Propellant Loadins Uncertainties
LM-8 APS PROPELLANT
Vent line Volume
Tank Volume
Pressure Measurement (±5 PSIA)
Temperature Measurement (±l.5°F)
Measured Density
2Weight Measurement
lLoading Tolerance
Total Loading Uncertainty
Fuel (ib)
±0.2
±0.8
±0.5
±1.7
±0.7
±0.5
±0.0
±4.4
Oxidizer (ib)
±0.3
LM-8 DPS PROPELLANT
Vent Line Volume
Tank Volume
Pressure Measurement (±5 PSIA)
Temperature Measurement (l.5°F)
Measured Density
2Weight Measurement
ILoading Tolerance
Total Loading Uncertainty
±1.3
±0.8
±4.3
±0.5
±0.5
±0.0
±7.7
±0.2 ±0.3
±3.4 ±5.6
±1.6 ±2.6
±6.1 ±14.8
±2.4 ±i,6
±o,_ ±0,_
±0.5 ±0.5
±14.2 ±25,4
ZO.6 ±I.8
±0.4 ±0.6
zO.8 zl.4
Zl.8 ±3.8
Loading Temperature
Ullage Calculation
Tank and Manifold Volume
Total
LM-8 RCS PROPELLANT
IThese will be known quantities after loading is accompllshed.
21f weigh tank is used for off-loadlng, then weight measurement uncertainty
is ±0.5 pounds per weigh tank. If flow meter is used for off-loading, then
weight measuremnt uncertainty is ZA.0X of amount off-loadad.
3.4-96 SNA-8-D-027(III)REV 2
TABLE 3.4-19
LM-8 APS Propellent Loading Parameters
(To Be Completed by KSC at Loading)
Loading Pressure - PSIA
Fuel
75.0
G58 Fuel
Loading Temperature - Fill Line - Degrees F 258 Oxidizer 68.9
_ITT 59 Fuel
Loading Temperature - Return Line - Degrees F[TT259 Oxidizer 69.2
[GP0718 Fuel
Loading Temperature - Tank - Degrees F [GP1218 Oxidizer 69.4
Number of Times Weigh Tank Used (Flow Meter Not Used) 1
Total Pounds Off-Loaded Using Weigh Tank (Flow Meter Not Used) 57
Pounds Off-Loaded Using Flow Meter (Weigh Tank Not Used)
Measured Fuel Density @ 25°C; @ 14.7 PSIA GM/CC
Measured Oxidizer Density @ 4°C; @14.7 PSIA GM/CC
0.8998
Amendment 98
1/22/71
Oxidizer
64.0
67.9
68.9
68.6
1
70
1.4812
IJ
3.4-97 SNA-8-D-027(III)REV 2
L
TABLE 3.4-19 (Continued)
LM-8 DPS Propellant Loading Parameters
Amendment 98
1/22/71
Loading Pressure - PSIA
Fuel
60.8
Oxidizer
64.3
ITT 58 Fuel
Loading Temperature - Fill Line - Degrees FITT258 Oxldlzer 67.9 67.0
ITT 59 Fuel
Loading Temperature - Return Line - Degrees F[TT259 Oxidizer 68.2 67.0
_GQ3718 Fuel
Loading Temperature - Tank One -Degrees F |GQ4218 Oxidizer 69.0 67.0
Loading Temperature - Tank Two - Degrees F IGQ3719 Fuel
[GQ4219 Oxidizer _68.6 67.4
Number of Times Weigh Tank Used (Flow Meter Not Used) _.i____ i
Total Pounds Off-Loaded Using Weigh Tank (Flow Meter Not Used).._ 88.0
Pounds Off-Loaded Using Flow Meter (Weigh Tank Not Used)
Measured Fuel Density @ 25°C; 14.7 PSIA Qd/CC 0.8q98 -
Measured Oxidizer Density @ 4°C; 14.7 PSIA GM/CC
3.4-98 SNA-8-D-O27(III)REV 2
MISSION H-3 MASS PROPERTY DATA TABLES Amendment 98
1/22/71
Table 3.4-20 presents CSM-110/LM-8 (docked) mass properties, in Apollo
coordinates, as a function of spacecraft weight for the
Hybrid SM/SPS burn.
Table 3.4-21 presents CSM-IIO/LM-8 (docked) mass properties, in Apollo
coordinates, as a function of spacecraft weight for L.O.I.
SM/SPS burn.
Table 3.4-22 presents the CSM-II0/LM-8 (docked) mass properties, in Apollo
coordinates as a function of spacecraft weight for the
D.O.I. SM/SPS burn.
Table 3.4-23 presents the CSM-IIO mass properties, in Apollo coordinates,
as a function of CSM weight for the Circularization I SM/SPS
burn.
Table 3.4-24 presents the CSM-II0 mass properties, in Apollo coordinates,
as a function of CSM weight for the Plane Change I SM/SPS
burn.
Table 3.4-25 presents the CSM-IIO mass properties, in Apollo coordinates,
as a function of CSM weight for the T.E.I. SM/SPS burn.
Table 3.4-26 presents the LM-8 mass properties, in LM coordinates, as a
function of LM weight for the P.D.I. DPS burn.
Table 3.4-27 presents the LM-8 ascent stage mass properties, in LM coordinates
as a function of weight for the lunar lift-off APS burn.
Table 3.4-28 presents the LM-8 mass properties, in LM coordinates, as a
function of LM weight for the T.P.I. burn.
3.4-99 SNA-8-D-027(III)REV 2
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Amendment 98
1/22/71
This page intentionally left blank.
3.4-113 SNA-8-D-027(III)P.EV 2
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Amendment 96
12/18/70
This page intentionally left blank.
U E
3.4-12.2
L, LIi L L_ l_ LIi
SNA-8-D-027 (III) REV 2
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TABLE 3.4-7
Amendment 92
1214170
CSM Ii0 Consumables Weight Change Summary
(To be used in conjunction with the CSM sequential mass properties Table 3.4-2)
EVENT
From To Consumable
Weight Amount Total
Change Remaining Usage
(Pounds) (Pounds) (Pounds)
Earth Launch Pre Trans/Dock SM-Hydrogen -0.5 54.7 -0.5
SM-Oxygen -11.4 819.9 -11.4
CM-Potable +4.0 40.0
CM-Waste +0.8 18.8
Pre Trans/Dock Post Trans/Dock SM-RCS -70.6 1271.8 -70.6
Post Trans/Dock Pre SPS Hybrid SM-Hydrogen -4.9 49.8 -5.4
SM-Oxygen -54.3 765.6 -65.7
SM-RCS -70.3 1201.5 -140.9
CM-Waste H20 +41.2 60.0
CM-LiOH +6.8 6.8
CM-Food -3.8 -3.8
Pre SPS Hybrid Post SPS Hybrid SM-SPS -724.8 39868.9 -724.8
post SPS Hybrid Pre L.O.I. aM-Hydrogen -9.4 40.4 -14.8
SM-Oxygen -93.9 671.7 -159.6
SM-RCS -65.5 1136.0 -206.4
CM-Food -9.4 -13.2
CM-LiOH +6.8 13.6
Pre L.O.I. Post L.O.I. SM-SPS -24788.7 15080.2 -25513.5
Post L.O.I. Pre D.O.I. SM-Hydrogen -0.5 39.9 -15.3
SM-Oxygen -8.5 663.2 -168.1
SM-RCS -30.4 1105.6 -236.8
Pre D.O.I. Post D.O.I. SM-SPS -1471.4 13608.8 -26984.9
Post D.O.I. CSM/LM Separation SM-Hydrogen -3.4 36.5 -18.7
SM-Oxygen -31.2 632.0 -199.3
SM-RCS -134.0 971.6 -370.8
CM-LiOH +5.0 18.6
CM-Food -3.8 -17.0
CSM/LM Separation Pre Circular- SM-Hydrogen -0.3 36.2 -19.0
ization SM-Oxygen -2.0 630.0 -201.3
SM-RCS -26.3 945.3 -397.1
Pre Circular- Post Circular- SM-SPS -272.9 13335.9 -27257.8
ization ization
3.4-16 SNA-8-D-027 (IIl) REV 2
TABLE3.4-7 (CONTINUED)
Amendment 92
12/4/70
CSM ii0 Consumables Weight Change Summary
(To he used in conjunction with the CSM sequential mass properties Table 3.4-2)
Weight Amount Total
EVENT Change Remaining Usage
From To Consumable (Pounds) (Pounds) (Pounds)
Post Circular- Pre Plane Change SM-Hydrogen -2.& 33.8 -21.4
ization SM-Oxygen -25.1 604.9 -226.4
SM-RCS -75.8 869.5 -472.9
Pre Plane Change Post Plane Change SM-SPS -1269.5 12066.4 -28527.3
Post Plane Change CSM/ASCT Docking SM-Hydrogen -4.9 28.9 -26.3
SM-Oxygen -47.4 557.5 -273.8
SM-RCS -135.2 734.3 -608.1
CM-Food -6.3 -23.3
CM-LiOH +7.8 26.4
CM-Fecal +2.2 2.2
CSM/ASCT Docking Pre T.E.I. SM-Hydrogen -I.I 27.8 -27.4
SM-Oxygen -9.3 548.2 -283.1
SM-RCS -41.9 692.4 -650.0
CM-Fecal +i.i 3.3
CM-Food -3.8 -27.1
CM-LiOH +2.6 29.0
Pre T.E.I. Post T.E.I. SM-SPS -10061.0 2005.4 -38588.3
Post T.E.I. SM Jettison SM-Hydrogen -11.8 16.0 -39.2
SM-Oxygen -127.3 420.9 -410.4
SM-RCS -179.9 512.5 -829.9
CM-LiOH +13.4 42.4
CM-Food -10.4 -37.5
CM-Fecal +3.3 6.6
SM Jettison CM @ Entry CM-RCS -11.6 233.4 -11.6
CM @ Entry CM @ M.C. Deploy CM-RCS -30.7 202.7 -42.3
CM @ M.C. Deploy CM @ Impact CM-RCS -202.7 0.0 -245.0
3.4-17 SNA-8-D-027(III)REV 2
II II M M I: E h L E n l,: Eg E E E L l i 2
Amendment 92
TABLE 3.4-8 12/4/70
LM-8 Consumables Change Summary
(To be used in conjunction with the LM sequential mass properties Table 3.4-2)
Weight Amount Total
EVENT Consumable Change Remaining Usage
From To (Pounds) (Pounds) (Pounds)
Earth Orbit CSM/LM Separation D/S-Oxygen -I.I 46.9 -I.i
D/S-Water -13,0 237.0 -13,0
LM-RCS -5.0 600.6 -5.0
CSM/LM Pre P.D.I. D/S-Oxygen -i.0 45.9 -2.1
Separation D/S-Water -21.3 215.7 -34.3
LM-RCS .-55.5 545.1 -60.5
Pre P.D.I. LM @ Touchdown D/S-Oxygen -0.I 45.8 -2.2
D/S-Water -1.1 214.6 -35.4
LM-RCS -97.0 448.1 -157.5
LM-DPS -17,342.6 977.1 -17,342.6
A/5 @ Touchdown A/S at Lift-Off LM-RCS -5.0 443.1 -162.5
A/S @ Lift-Off A/S in Orbit LM-APS -4,927.8 282.8 -4,927.8
A/S in Orbit Pre T.P.I. A/S-Water -5.0 80.0 -5.0
A/S-Oxygen -0.3 4.5 -0.3
LM-RCS -47.4 395.7 209.9
Pre T.P.I. Post T.P.I. LM-APS -39.0 243.8 -4,966.8
A/S @ Post T.P.I. A/S @ Docking A/S-Water -3.8 76.2 -8.8
A/S-Oxygen -0.2 4.3 -0.5
LM-RCS 70.2 325.5 -280.1
A/S @ Docking A/S Jettison A/S-Water -8.2 68.0 -17.0
A/S-Oxygen -0.4 3.9 -0.9
3.4-18 SNA-B-D-027(III)REV 2
11 !1 I,: E E L L L L I: E 12 E1; t_ L: L L IL_
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Amendment 81
5/11/7o
TABLE 3.4-9
MISSION H CO)_qAND MODULE STOWAGE VOLUME CENTROIDS
S/C 109 -111
A1 1012.0 -22.0 -26.0
31016.0 -24.0 28.0
41015.O - 7.0 28.0
51015.O 9.0 28.0
61017.0 26.0 28.0
7-Not on S/C 110 1012.O 31.0 7.0
8 1012.0 22.0 -23.0
10 - S/C ii0 Only 1011.0 23,0 6.0
11 -Not on S/C 110 1Oll.0 19.0 7.0
12 1013.0 - 9.0 14.0
13 I010.O -22.0 -2.0
81 1050.0 -27.0 39.0
2 1039.0 -38.0 37.0
31031.0 -28.0 40.0
41031.0 -20.0 40.0
51031.O - B.O 39.0
6 1031.O 13.0 39.0
7 1033.0 27.0 36.0
B 1024.O -38.0 37.0
L2 1059.0 -44.0 14.O
31048.0 -47.0 12.O
RI 1072.O 26.0 21.0
2 1072.O 26.0 14.0
3 1072.0 26.0 9.0
4 1075.0 28.0 3.0
51059.0 44.0 15.O
61048.0 46.0 29.0
B 1052.0 46.0 12.0
10 - Forward 1053.0 47.0 5,0
I0 - Aft 1047.0 48.0 5,0
11 1038.O 47.0 26.0
13 1024.0 45.0 -26.0
U1 1033.0 23.0 -50.0
31033.0 -36.0 -44.0
41038.0 39.0 -43.0
3.4-20 SNA-B-D-027(III)REV 2
L_ &
E_
Amendment 81
5/11170
Table 3.4-9.1
_he following stowage locations have unique volme centroids
not associated with storage volumes.
G&N Signal Cond. Panel
Display Keyboard
Sleep Restraint Assy - Right
Sleep Restraint Amsy - Left
Food Container
Food I_nntainer
rec:al _cowage Container
PEA C,_ntainer
F_Jrwai_ hatch 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.
Helmex Stowage and Accessory
BaSs (In-flight Location) _ R.H.
Teemorary Storage Bag -L.H.
(In-flL8ht Location)
Temporary Stc_age Bag -Ctr.
(In-flight Location)
Tempo_'ax) Stowage Bag.- R.H.
(In. flight Location)
CO A_sorbers (?)
CO2 A_.'_rbers (4)
CO_ Absorbers (&)
CO Absorbers (2)
CO_ Absorbers (4)
CO2 Absorbers (4)
First 6.8 lb. __.CO,Absorbed
Next 6.8 lb. CO; Absorbed
Reminder CO2 Absgrbed
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Lg8 1069.0 25.0
Ln 1060.0 26.0
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Aft UE| 1018.0 -21.0
L3 1048.O -47.0
81 1050.0 -27.0
RI/EB 1039.0 47.0
On Aft Bulkhead IO15.0 0.0
Under Center
Couch
Under L.H. Couch 1018.0 -24.5
R.H. Girth Ring 1036.5 &0.0
L.H. Girth _in8 1036.5 -40.0
LEB 1050.0 -27.0
|.H. Girth Ring 1036.5 40.0
LHEB 1039.0 -47.0
LEB 1050.0 -27.0
t/4ZB 1039.0 47.0
In ECU IO31.O -48.3
A3 1016.O -24.0
A4 1011.0 - 7.0
A6 1017.0 26.0
|5 1031.0 - 8.0
B6 1031.0 13.0
Composite Loca-
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Amendment 92
12/4/70
This page intentionally left blank.
3.4-64.14 SNA-8-D-027 (III) I_V 2
t.
TAIL[ 3.4..2O
¢OUI_iL|8 i.O_Zl_ I_UZlJDI_ AND TOLI[LAll¢[8
14Lnion H-3
8PS Prooelllmt
Proeouro (PSZA) . Tempe :u_re ('_) O_n
Fuel oxld;Loer Fvql oxtdJ_ser Fuet
110t4 110*4 70*$ 70'5 See FLjure
4.1-3
Amendment 88
1015170
toadout (_)
Oxidiser
Joe FJaure
4.1-4
8P8 P¢opell_t Load (Lb)
ILiad
2Trapped Outside Tank8
Tanked
2Trapped InaLde Tanka
SMcnt2nal Deltvelsble
Loedtnt kauir._menC
rue1 Oxidtaer
15704.0
78.6
15625.4
67.6
15857.8
25092.0
123.7
24968.3
171.5
24796.8
Ac_wl
Fu*_ OxLdL.s,r
_Service Hodule ItS PropeZlant
Secondary Fue2 -quAJd8 A, |, C, D - See 1,oadLn8 Wlndov -rLaure 4.3ol.
P,*ury Fuel -Quids A, 8, C, D - See Lotdtn8 WLndov - fljure 4.3-2.
PrLlutry and Seccmdary OxLd/ser -QuAJd8 4, |, C, D - See Load/hi Wtndov -
F/aura 4.3-3.
sea.end Nodule ICS rropell_nc
Yue2 -Syotou Aand J -See LoadLn8 VLndov - Ftaure 4.3°4.
OxLdtzer - Syeton 4and J - See LoadLn8 ULndov - YLaure 4.3-5.
ConsLmable
9Hel_u8 and Nitrosan
Losdint leauirewnt
Praooufo
(PSIA)
3600
278
178
4150
4150
4150
6150
4150
41S0
2SO0
2500
Tmp WeLaht
('r) Clb)
70 87.6
70 5.4
70
70
7O 6.0
7O
7O
70 1.0
7O
88 1.3
85
|arch Launch
Velth¢ (lb_
87.6
6.0
1.0
1.)
Actusl
rrenure Teup
(PIIA) ('F)
HelLum - SPS llottla8
HAIL-- - Fuol Tsnk_
HelL_n - M20_ Tsakn
HelLum - |H/iLC8
_nd 8
QvU ¢
Qendn
NeLLn- O1/II_I
Syotmi A
Syste mi
NLtroEen - SH
PrL_ry
Secondary
3.4-65
SMA-8-D--027 (I 11 ) IU[V 2
TABLE 3.4-10 (CONTINUED)
Command Module Water and GOX
Amendment 88
1015170
Waste Water 6
Potable Water 7
CM/GOX
Pressure
(PSIA)
900±50
Loading Requirement
Wei6ht (ib)
3.7
8Service Module Hydrogen and Oxygen
Earth Launch
Weight (ib)
18.0
36.0
6.7 (Entry)
Actual
Loading Requirement
(pounds)
Hydrogen
Tank 1
Tank 2
Oxygen
Tank 1
Tank 2
Tank 3
29.3
29.3
330.1
330.1
330.1
Earth Launch Weight
(pounds)
27.6
27.6
316.6
316.6
198.1
NOTES:
llndicated propellant load is based on nominal pressure and temperature
prior to actual loading. This number will be updated after loading
is accomplished.
2See Section 4.1 for explanation of trapped SPS propellant.
3See Table 3,4_13 for loading uncertainties.
4See Section 4.2 for SM/RCS loads and uncertainties to be used in Mis-
sion Planning. Actual SM/RCS loads and uncertainties will be published
in Table 3.4-15.
5See Section 4.2 for CM/RCS loads and uncertainties to be used in Mis-
sion Planning. Actual CM/RCS loads and uncertainties will be published
in Table 3.4-14.
6Launch Rule Redlines determine lift-off values.
7Launch Rule Redllnes determine lift-off values.
8Launch Mission Rules will determine minimum llft-off quantities for
H 2 and 02.
9CSM helium and nitrogen should be loaded in accordance with loading
windows contained in CSM/LM Spacecraft Operational Data Book, Volume I,
Part 2, SNA-8-D-027(1) P2.
3.4-66 SNA-8-D-027(III)REV 2
11 !1 1: L :L: E L L E I: E L: U |; E E :" 'i_
T_LE 3.4-II
8P$ PYaq)el1_t IMd Caleuletlon
1. Inter SPS Quantity bedout st 110 PSIa (Table 3.4-12
item C - Betcent)
2. Use 718ures 4.1-3 'end 4.1-4 to obtain pro-
peLXant Load for shove quantity tJtdout,
3. Ik)liinel propdllent density st loedin8 _mnporsture
(use tempersture - density lrqh belov) (1b/fie)
4. Cubic feet of prel)ellent (It_ 2 divided by item 3)
S. Calculated demstty free Table 3.4-12 item f (lb/ft 3)
6. Adjustment due to PUGS sere adJult (pounds)
7. loeultiq actua_ propellant load (item 4times
item S, less item 6) (pounds)
F_L
J
m
w
m
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SPS SPS
Oxidizer FUEL SPS Propellent Temperature/Density Graph
st 110+5 PSZA
Amendment 8B
i01517o
90.4
13
E
N
S 90.
I
T
y 90.
LS/FT 3
90.:
90.0
8g.g
8g.8
89.7
Temperature Deerees Y
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Amendment 88
10/5/70
TAB;.E 3.4-13
SPS PROPELLANT UNCZETAINTIES
ITEM
LOADING UtlCERTAI_TIES
Tank Volune
Temperature Gauss (•2.0"F)
Standpipe Heliht
Propellant GeuBe (tO.35Z of GeuBeable)
Density Heesurement (1)
Batch Density (1)
Loading Pressure (1)
RSS
FUEL
(lb)
"24
"18
•6
".54
"0
"94
" 8
ill3
L
TOTAL RSS •172
Loading Specification (1) (2) t16 t24
Tolerance on Propellent Tesperature +0.0 +0.0
of F118ht Load -46.0 o113.0
m+212
TOTAL LOADING UNCERTAINTY _371
HISSION UNCERTAINTIES
Mixture its•is Variation
_V, Iap, Vehicle WsiBht Variation
Propellant USeBS uncertainty due to
total losdin8 uncertainty
OXIDIZE1
(lb)
t39
t46
•10
"86
"0
t75
t14
s130
TBD
TBD
TED
u,
TOTAL PROPELLAHT _dC_RTAINTY 1101
MISSION AV TED
NOTES: (1) Data will be knmm after loadin 8 is accompllshedu
(2) Losdin I specification is 8n allowable tolermsce about
nmminal, this number £s added to the load/hi uncertainty
variables.
3.4-70 St_-8-D-O27 (II1) ILEV 2
ILl II Id _ L l_ LLL I_ L'- E L,' 1_ L_ aL. L- L
Amendment 88
1015170
TABLE 3.4-14
Com-lnd Module RCS LoadlnB Parameters end Calculations
Thto Cable wtll be 'comple:ed when loedtnB is 8ccoupllshed. For Mieeion
Planntn|, reference should be made to Section h.2 for nominal load, loadtn i
tolerances, crepped end deliverable propellants.
r_.__L OXIDIZZl
A. Tank Volume @ 0.0 PSIA (ln 3)
B. Liquid Line Volume (ln 3)
C. Tote1 k+B(In 3)
Tank......_._B Tank ATankB
D, £nltlal Welsht In Bleed Unit
Prlor co LoedinB (lb)
E. Flnal Weight In Bleed Unit
After Loadln8 (lb)
F. Propellent Load (item D less
then E WetBh Tank)
G. Propellant Load by P.V.
H. Loadin8 Temperature (*F)
1. Specification Propel14m[
Loed @7OtS"Y (Ib)
J. Total CM/RCS Propellent
Load from Item G above (lb)
K. Haxlmum Trapped Propellant (lb)
L. Nominal Deliverable (lb)
3.4-71 SNA-8-D-O27 (l IX) KEY 2
II II lJ L L E Ii LI: I: I_ E E E H E L, L _ L
Amendment 88
1015170
TABLE 3.4-15
SERVICZ MODULE ICS LOADING SUMMATION
This table w_11 be completed when 1sadie| t0 eccouplished. For KteeLon Plan-
nin|, reference should be made to Section 4.2, for nominal load, loedin8
tolerances, and noutnal deliverable propellants.
q_d A(lb) Ousd | (lb)
Secondary fuel
Primary fuel
Total fuel t0.7
148xtmum Trapped 2.1
Nominal Deliverable
Secondary fuel
Primary Fuel
Tote1 fueX
VdmlJ,-,Trepped
N_lnel Deliverable
2.t
tO.7
Total Oxidizer
Maximum Trapped
Nominal Deliverable
t2.3 Total Oxidiser
Haxlmun Trapped
Nominal Deliverable
4.5
t2.3
_ad c (lb)
Secondary fuel
Primary fuel
Total fuel tO.7
Maximum Trapped 2.1
Nominal Deliverable
Total Oxidiser t2.3
Maximum Trapped %,5
Nominal DelivsrabXs
Quad D(lb)
Secondary fuel
Primary fuel
Total rum1
Maximum Trapped
Nominal Deliverable
Tote1 Oxidiser
)lmtt.momTrapped
Mominal Deliverable
tO.7
2.1
"2.3
4.5
Total fuel
Maximum Trapped
Nominal DellverabXe
Total SM/tCS Propellent Load Ilb)
tl.4 Total Oxidiser
8.4 _inumTrapped
Nominal Deliverable
ITS.0
t4.6
3.4-72 SNA-8-D-O27(III)REV 2
[I 11 IL; [1: E L LE1: EE L.' 1_ ii EL, L
TABLE 3.4-16
LM-8 Consu--.ble Loadln_ Requirements
I/4-8 APS Propellant
Amendment 91
11/25/70
Fuel (Ib_ Oxidizer _ib_
Propellant Load 2006.7 3218.1
Trapped Outside Tanks 5.9 8.3
Tanked 2000.8 3209.8
Trapped Inside Tanks I0.i 27.6
Nominal Deliverable 1990.7 3182.2
Outase TBD TBD
Total APS Propellant TED
The following table should be used to determine the amount of propellant
to be off-loaded from a full condition Co arrive at the indicated load.
The allowable tolerance for the calculated off-load is +0.5 pounds per
weigh tank.
A. Final tank pressure at overfill (PSIG)
B. Propellant loading temperature ("F)
C. Nominal overfill quantity (Ib) 2072.3
D. Correction for tank pressure (ib)
AFuel -0.09 (Item A-40)
Oxidizer =0.15 (Item A-40)
IE. Correction for loading temperature (ib)
Fuel =-1.16 (Item B-65)
Oxidizer - -2.84 (Item B-65)
2F. Measured density (GM/CC)
2G. Nominal density (GM/CC) 0.8994
H. Delta density (GM/CC) (Item F-G)
31. Correction for measured density
Fuel = 2300 (Item H)
Oxidizer = 2300 (Item H)
J. Propellant in GSE
K. Overfill quantity (C+D+E+I+J)
L. Target loading 2006.7
M. Quantity required to fill RCS manifolds
N. Quantity to be off-loaded (Items K-L-M)
NOTES:
_07.2
1._,82 l,
3218.1
ILoadlng temperature correction will always be negative.
2To calculate the nominal density solve the followlng equation where T-
temperature in °C of the measured density (usually 4°C for oxidizer and
25°C for fuel). This equation is valid for 14.7 PSIA. Therefore. the
measured density must also be at 14.7 PSIA.
Nominal fuel density = 0.922904-0.0009377 (*C)
Nominal oxidizer density - 1.491539-0.0022832 (°C)
3Correctlon for measured density may be either positive or negative.
3.4-73 SNA-8-D-027(III)REV 2
TABLE 3.4-16 (Continued)
LM-8 Consumable Loadin E Requirements
124-8 DPS Propellant
Fuel (Ib) Oxidizer (Ib)
Propellant Load 7072.8 11341.9
Trapped Outside Tanks 35.1 60.5
ranked 7037.7 11281.4
trapped Inside Tanks 14.8 102.7
Nominal Deliverable 7022.9 11178.7
Outage TBD TBD
Total DPS Propellant Available TBD
Amendment 91
11/25/70
The following table should be used to determine the amount of propellant to be
off-loaded from afull condition to arrive at the indicated load. The allowable
tolerance for the calculated off-load is_+0.5 pounds per weigh tank.
AI. Final tank pressure at overfill (PSIG)
BI. Propellant loading temperature (OF)
C1. Nominal overfill quantity (lb) 7160.4
D1. Correction for tank pressure (lb)
&Fuel = 0.31 (Item AI-40)
AOxidizer - 0.51 (Item AI-40)
IEI. Correction for loading temperature (ib)
&Fuel = -4.0 (Item BI-65)
A Oxidizer - -9.85 (Item BI-65)
2F1. Measured density (GM/CC)
2G1. Nominal density (GM/CC) 0.8994
N1. Delta density (GM/CC) (Item Fl-Item G1)
3II. Correction for measured density
A Fuel -7900 (Item HI)
AOxidizer - 7900 (Item HI)
Jl. Propellant in GSE
KI. Overfill quantity (CI+DI+EI+II+J1)
LI. Target loading 7072.8
MI. Quantity required to fill RCS manifolds
(APS only) xxxxxx
NIo Quantity to be off-loaded
(Items KI-L1-M1)
11452.9
1.4824
11341.9
XXXXXX
NOTES :
ILoadln8 temperature correction will always be nesatlve.
2To calculate the nominal density solve the following equation where
T-temperature in *C of the measured density (usually 4"C for oxidizer
and 25oC for fuel). This equation is valid for 14.7 PSIA. Therefore,
the measured density must also be at 14.7 PSIA.
Nominal fuel density - 0.922904-0.0009377 (°C)
Nominal oxidizer density - 1.491539-0.0022832 (°C)
3Correcclon for measured density may be either positive or negative.
3.4-74 SNA-8-D-027(III)REV 2
!1 !1 1: I: U 1.: L L I: I: L L L: L: L L
System AFuel
System A Oxidizer
System B Fuel
System B Oxidizer
TABLE 3.4-16 (Continued)
LH-8 - RCS Propellant (2) (3) .
Required Ullage Requirement (in _)
Load _Ib) 5Minimum _ Maximum _
107.7±0.9 111.0 123.0
208.8±1.9 225.5 237.5
107.7±0.9 111.0 123.0
208.8±1.9 225.5 237.5
iAciual_
Load (lb)
FUEl. OXIDIZER
Propellant Load 215.4 417.6
Trapped Outside Tanks 10.5 16.9
Tanked 204,9 400.7
Trapped in Tanks 4.2 8.0
Nominal Deliverable 200.7 392.7
LM-8 - Helium & Nitrogen
Amendment 88
1015170
IActual"
Ullage (in _)
Consumable
Helium - APS tank #I (6)
- APS tank #2 (6)
-RCS tank #I (6)
- RCS tank #2 (6)
- DPS (SHe)
- DPS (Ambient) (6)
Nitrogen - Ascent
- Descent
Nominal Loadin BRequirement
Pressure Temp Weight
(PSIA) ('F) (lb)
3050 70" 6.6
3050 70" 6.6
3050 70" 1.05
3050 70" 1.05
80¢2 N/A 48.5
1600 70" 1.1
0,1
0.6
Actual
Pressure Temv Weight
{PSIA) ('F) (lb)
LH-8 - Water & COX
Consumable
Ascent Water -tank #I
-tank #2
Descent Water
Ascent GOX - tank #I (6)
- tank #2 (6)
Descent GOX {6)
NOTES:
Nomlnal Loadln RRequirement Actual
Pressure Weight Pressure
(PSIA) (lb) (PSlA)
N/A 42.5 N/A
N/A 42.5 N/A
N/A (7) N/A
830 2.4
830 2.4
2700 48.0
ISee Table 3.4-17 for actual propellant load calculation.
2See Section 5.6 for explsnstlon of trapped propellants.
3See Table 3.4-18 for loading uncertslntles.
_PV ullage calculation should be 125_50 cubic inches for LM/RCS fuel and
23R,5±50 cubic inches for LH/RCS oxidizer per tank.
5LH/RCS required load includes propellant required to fill RCS mmifolds
to isolation valves. See Table 3.4-16. Sae Section 5.6 for trapped
propellants.
6The Indlceted items should be loaded in accordance with loading windows
contained in the CSM/LM Spacecraft Opcratlonal Data Book, Volume II,
Part 2, SNA-8-D-O27PT2.
7LM-8 Descant Water bhall be loaded to provide 250-0.0+10.0 pounds
at Earth Launch. Inltlal load will be determined by sampling requirements.
3.4-75 SNA_R_D_027 (III) REV 2
!1 !1 U E EU 12 L L: l: L; l: U Ek: L L,_ L
TABLE 3.4-17
LOAD CALCULATION
APS PROPELLANT
1. Full tank - Item K, Table 3.4-15 (lb)
12. Density of off-load tables at loading
temperature and pressure (Ib/ft 3)
13. Propellant volume (divide item 1 by
item 2. (ft 3)
341 Measured density (from Table 3.4-19)
(lb/ft 3)
5 Resulting full tank load (lb)
6. Off-load amount (lb)
7. Propellant required to fill RCS manifolds
(ib)
8. Propellant load (lb)
Fuel
Anmndemnt B8
10/5/70
Oxidizer
DPS PRO_PLLANT
9. Full tank - It--"emK1 Table 3.4-16 (Ib)
110. Density of off-load tables at loading
temperature and pressure (lb/ft 3)
Ill. Propellant volume (divide Item 9 by Item
lO)(ft 3)
112. Measured density (from Table 3.4-19)
(lb/ft 3)
13. Resulting full tank load (lb)
14. Off-load mnount (ib)
15. Propellant load (Ib)
RCS PROPELLANT
P. V. Calculations
A. GSE Volume (In 3)
B. Initial Ullage _ressure
(PSXC)
C. , Initial GSE Pressure
(PSIG)
D. Final GSE - S/C Pressure
(PSXC)
E UllaRe Volume (in 3) - Solve
the following equation by
substituting the values in
the indicated steps.
Ullage Volume .(D-C) (A_
B-D
Fue.__l Oxidizer
Tank ATank B Tank ATank B
NOTE,: IThese items will be completed only if a density sample is not
made prior to loading. If a density sample is made prior to
loading, then the items will be left blank.
3.4-76 SNA-8-D-027(III)REV 2
IIIIEIZEELL Z U U U LL
Amendment 88
TABLE 3.4-18 10/5/70
Vent llne Volume
Tank Volume
Pressure Measurement (Z5 PSIA)
Temperature Measurement (±l.5°F)
Measured Density
2Welsh± Measurement
ILoadlng Tolerance
Total Loadin 8 Uncertainty
LM-8 Propellant Loading Uncertainties
LM-8 APS FRDPELLANT
Fuel (Ib_
±0.2
±0.8
_0.5
±1.7
/0.7
±0.5
±0.5
±4.9
Oxldlzer (Ib_
±0.3
±1.3
±0,8
±4.3
±0,5
±0.5
±0.5
_8.2
AYS Mission Uncertainties
Mixture Ratio Variation
_V, Isp, Vehicle Weight Variation
Propellant Usage Uncertainty Due To Total
Loading Uncertainty
Total Propellant Uncertainty For Mission _V
TBD
TBD
TBD
TBD
LM-8 DPS PROPELLANT
Vent Line Volume "0.2
Tank Volume _3.4
Pressure Measurement (±5 PSIA) ±1.6
Temperature Measurement (I.5°F) _6.i
Measured Density !2.4
2WeiEht Measurement _0.5
lLoading Tolerance _0,5
Total Loading Uncertainty ±14._
-+0.3
-+5.6
-+2.6
±14,8
_._
-+Q._
±o._
_+25.9
DPS Mission Uncertainties
Mixture Ratio Variation
_V, Isp, Vehicle Weight Variation
Propellant Ussle Uncertainty Due to Total
Loading Uncertainty
Total Propellant Uncertainty For Mission _V
TBD
TBD
TBD
TBI)
L_-_ RC$ PRDPELLANT
Loading Temperature 10,2 tl.8
Ullage Calculation t0.4 t0.6
Tank and Manifold Volume t0.8 _1.4
Total tl.8 _3.8
IThese will be known quantttias after loading is accolpltehed.
21f weigh tank is used for off-load/n|, then wei|ht measurement uncertainty
Is ±0.5 pounds per weigh tank. If flow meter Is used for off-loadlng, then
weight measurement uncertainty is ±4.0Z of amount off-loaded.
3.4-77 SNA-8-D-O27(III)REV 2
U!1 _ I,:; ]_ UL L L: U I,,: Ei_ l_ I_ E:''
i.,. i_ i_. L
TABLE 3.4-19
LM-8 APS Propellant Loading Parameters
(To Be Completed by KSC at Loading)
Loading Pressure - PSIA
[TT 58 Fuel
Loading Temperature -Fill Line - Degrees F ITT258 Oxidizer
_TT 59 Fuel
Loading Temperature - Return Line - Degrees FITT259 Oxidizer
IGP0718 Fuel
Loading Temperature - Tank - Degrees F[GPI218 Oxidizer
Number of Times Weigh Tank Used (Flow Meter Not Used)
Total Pounds Off-Loaded Using Weigh Tank (Flow Meter Not Used)
Pounds Off-Loaded Using Flow Meter (Weigh Tank Not Used)
Measured Fuel Density @ °C; @ PSIA GM/CC
Measured Oxidizer Density @ °C; @ PSIA GM/CC
Fuel
Amendment 7_
31_)/_o
Oxidizer
3.4-78 SNA-8-D-O27(III)REV 2
11 11 EE l: EL" L :E I: E _: L' |; E I.: L LL-- IL
TABLE 3.4-19 (Continued)
LM_8 DPS Propellant Loading Parameters
Loading Pressure - PSIA
[Tr 58 Fuel
Loading Temperature -Fill Line - Degrees F|TT258 Oxidizer
[rr 59 _ex
Loading Temperature - Return Line - Degrees F ITT259 Oxidizer
_C1_3718 Fuel
Loading Temperature - Tank One - Degrees F i_4218 Oxidizer
Loading Temperature - Tank Two - Degrees F_GQ3719 Fuel
lgq4219 Oxidizer
Number of Times Weigh Tank Used (Flow _teCer Not Used)
Total Pounds Off-Loaded Using Weigh Tank (Flow Meter Not Used)
Pounds Off-Loaded Using Flow Meter (Weigh Tank Not Used)
Measured Fuel DenslCy @ _; PSIA GM/CC
Measured Oxidizer Density @"C; PSIA GM/CC
Amendment 78
3/9/70
Fuel Oxidizer
3.4-79 SNA-8-D-027(III)REV 2
U !1 UE 1: EELE E I,: Lg, 1_ 1_ L L L L L
MISSION H-3 MASS PROPERTY DATA TABLES Amendment H8
10/5/70
Table 3.4-20 presents CSM-II0/LM-8 (docked) mass propertieu, iu Apollo
coordinates, as a function of spacecraft weight for the
Hybrid SM/SPS burn.
Table 3.4-21 presents CSM-II0/LM-8 (docked) mass properties, in Apollo
coordinates, as a function of spacecraft weight for L.O.I.
SM/SPS burn.
Table 3.4-22 presents the CSM-II0/LM-8 (docked) mass properties, in Apollo
coordinates as a function of spacecraft weight for the
D.O.I. SM/SPS burn.
Table 3.4-23 presents the CSM-II0 mass properties, in Apollo coordinates,
as a function of CSM weight for the Circularlzatlon I Srl/SPS
burn.
Table 3.4-24 presents the CSM-II0 mass properties, in Apollo coordinates,
as a function of CSM weight for the Plane Change I SM/SPS
burn.
Table 3.4-25 presents the CSM-II0 mass properties, in Apollo coordinates,
as afunction of CSM weight for the T.E.I. SM/SPS burn.
Table 3.4-26 presents the LM-8 mass properties, in LM coordinates, as a
function of LM weight for the P.D.I. DPS burn.
Table 3.4-27 presents the LM-8 ascent stage mass properties, in LM coordinates
as a function of weight for the lunar lift-off APS burn.
Table 3.4-28 presents the LM-8 mass properties, in LM coordinates, as a
function of LM weight for the T.P.I. burn.
3.4-80 SNA-8-D-027(III)REV 2
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Amendment 94
12/10/70
SUPPLEMENTARY DATA APPLICABLE TO SEQUENTIAL MASS PROPERTIES TABLES
General Comments to be applied to Tables 3.5-1 through 3.5-8:
Inertia data dispersions are +10%.
Dispersions shall be used as 3o deviation values.
All initial propellant weights are total tanked.
The (+) or (-) sign following the name of an item indicates that the
item is added to or subtracted from the preceding total.
Table 3.5-1
SM/SPS glmbal angles for SPS abort sequence are: Pitch ffi-0.4104
Yaw = 1.895
Tables 3.5-7 and 3.5-8
CSM and LM consumables changes are presented in Tables 3.5-7 and
3.5-8, respectively.
Table 3.5-3
The mass Spectrometer and Gamma-Ray Spectrometer are shown deployed
after each SPS firing following D.O.I. For all other summations the
M.S. and G.R. Spectrometers are not deployed. The following are the
individual mass properties for the M.S. and G.R. Spectrometers in
Apollo Coordinates.
Weight X-Bar Y-Bar Z-Bar
(ib) (in) (in) (in)
Gamma-Ray 45.4 865.1 33.0 -57.0
Retracted
Gamma-Ray _28.0 865.1 231,3 -312.4
Deployed _17.4 865.1 132.2 -184.7
Mass Spectrometer 47.4 863.1 55.8 -40.5
Retracted
Mass Spectrometer _27.4 863.1 341.7 -149.4
Deployed _20.0 863.1 198.8 -94.9
3.5-1 SNA-8-D-O27(III)REV 2
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_aendmen t 86
9110170
Tsble 3.5-4
H4th A/tltude Abort l_os Propertiaj
To be $upplled ac J Later Dace
3.5-13 SNA-8-D-027(III)REV 2
U1/ I_ LLLL L LULL L: ii U _ _ L _
Amendment 86
9/10/70
Table 3.5-5
Pad Abort _s Prop@ztlu
To be Supplled at a Later Date
3.5-14 SNA-8-D-027(III)REV 2
I/ I/ LLE-E EL-- L_ L_ v•
|L 1L _ _ _ L L
Amendment 86
9/10/70
Table 3.5-6
SIVB Sequential Mass Properties (LV Coordinates)
To be Supplied at a Later Date
3.5-15 SNA-8-D-027(III)REV 2
I1 I1 I; ]L; L' h h L h h _ L" _ _ U U_, LL L
Amendment 86
9/10/70
Table 3.5-6 (Continued)
SIVB Sequential Mass Properties (Apollo Coordinates)
To be Supplied at a Later Date
3.5-16 SNA-8-D-027(III)REV 2
|i lI t_ L," kL_ L
Amendment 9
12/10/70
TABLE 3.5-7
CSM 112 Constmables Weight Change Summary
(To be used £n conjunction with CSM sequential mass
properties Table 3.5-2)
EVENT
From To Consumab le
Wefght Amount Total
Change Remaining Usage
(Pounds) (Pounds)' (Pounds)
Earth Orbit Pre Trans/Dock SM-Hydrogen -0.8 81.6 -0.8
SM-Oxygen -15.8 934.0 -15.8
CH-Potable H20 +4.0 40.0
CM-Naste S20 +0.8 18.8
Pre Trans/Dock Post Trans/Dock SM-RCS -70.6 1271.8 -70.6
Post Trans/Dock Pre L.O,I. aM-Hydrogen -15.5 66.1 -16.3
SM-Oxygen -155.6 778.4 -171.4
SM-RCS -85.5 1186.3 -]56.1
CM-Naste H20 +41.2 60.0
CN-LiOH +13.6 13.6
CM-Food -13.2 -13.2
Pre L.O.I. Post L.O.I. S]_-SPS -26684.3 13909.4 -26684.3
Post L.O.I. Pre D.O.I. SM-Hydrogen -0.8 65.3 -17.I
SM-Oxygen -7.4 771.0 -178.8
SM-RCS -44.7 1141.6 -200.8
Pre D.O.I. Post D.O.I. SM-SPS -573.8 13335.6 -27258.1
Post D.O.I. CSM/LM Separation SM-Hydrogan -3.4 61.9 -20.5
SM-Oxygan -35.9 735.1 -214.7
SM-RC$ -95.1 1046.5 -295.9
CN-LiOH 5.0 18.6
CM-Food -3.8 -17.0
CSM/I.M Separation Pre Circulartzation SH-Hydrosen -0.3 61.6 -20.8
SM-Oxygen -2.6 732.5 -217.3
SM-RCS -25.0 1021.5 -320.9
Pre Ctrcularization Post Ctrcularization SB-SPS -296.6 13039.0 -27554.7
3.5-17 SNA-8-D-027(III)REV 2
ItI il L_ L1_ El_ L L 1_ I,,. i; L; Ii II IL LL ± ;_
Amendment 9_
i2/lo/7o
TABLE 3.5-7 (Continued)
CSM 112 Consumables Weight Change Summary
(To be used in conjunction with CSM sequential mass
properties Table 3.5-2)
EVENT
From To
Post Pre Plane
Circularlzation Change i
Weight Amount Total
Change Remaining Usage
Consumable _Pounds) _Pounds) (Pound_)
SM-Hydrogen -13.2 48.4 -34.0
SM-Oxygen -117.4 615.1 -334.7
SM-RCS -168.4 853.1 -489 3
Pre Plane Post Plane SM-SPS -1236.8 11802.2 -28791.5
Change 1 Change ]
Post Plaue C::M/ASCT Docking SM-Hydrogen -1.7 46.7 -35.7
Change i SM-Oxygen -14.2 600.9 -348.)
SH-RCS -73.0 780.1 -562.5
CM-Food -6.3 -23.3
CM-LiOH +7.8 26.4
CM-Fecal +2.2 2.2
t_:_rL \SCT 13oc:king Pre r.h.l. SM-Hydrogen -I0.9 35.8 -_6.6
SM-Oxygen -i04.7 496.2 -453.b
SM-RCS -128.9 651.2 -691.2
CM-LIOH +5.0 31.4
CM-Fecal +i.I 3.3
CM-Food -3.8 -27.1
Pre T.E.I. Post T.E.I. SM-SPS -95_1.I 2661.1 -38332.6
Post T.E.I. SH Jettison SM-Hydrogen -14.9 20.9 -61.5
SM-Oxygen -168.9 327.3 -622.5
SM-RCS -71.8 579.4 -763.0
CM-LIOH +13.4 44.8
CM-Food -i0.4 -37.5
CM-Fecal +3.3 6.6
SM Jettison CM @ Entry CM-RCS -II.6 233.4 -Ii.6
CM @ Entry CM @ M.C. Deploy CM-RCS -30.7 202.7 -42.3
CM @ M.C. Deploy CM @ Impact CM-RCS -202.7 0.0 -245.0
3.5-18 SNA-8-D-027(III)REV 2
l/ !1 EE l_ E li L Ii 1_ I_ 1.' l_ li tl 12 i2 L
TABLE 3.5-8
Amendment 94
12110170
LM-IO Consumables Change Sun=aary
From
(To be used in conjunction with the
EVENT
To
LM sequential mass properties Table 3.5-2)
Weight Amount Total
Change Remaining Usage
Consumable _Pounds) (Pounds) (Pounds)
Earth Orbit CSM/LM Separation D/S-Oxygen -5.0 91.0 -5.0
D/S-Water -20.0 360.0 -20.0
LM-RCS -5.0 601.5 -5.0
CSM/LM Separation Pre P.D.I. D/S-Oxygen -3.0 88.0 -8.0
D/S-Water -12.0 348.0 -32.0
LM-RCS -51.0 550.5 -56.0
Pre P.D.I. LM @ Touchdown D/S-Oxygen -i.0 87.0 -9.0
D/S-Water -3.0 345.0 -35.0
LM-RCS -i00.0 450.5 -156.0
LM-DPS -18762.0 746.5 -18762.0
LM @Touchdown A/S @ Lift-Off LM-RCS -5.0 445.5 -161.0
LM @ Lift-Off A/S in Orbit LM-APS -4958.7 261.5 -4958.7
A/S in Orbit AIS @ T.P.I. A/S-Water -8.0 77.0 -8.0
A/S-Oxygen -0.4 4.4 -0.4
LM-RCS -20.0 425.5 -]81.0
AIs @ T.P.I. A/S @ Docking A/S Water -20.0 57.0 -28.0
A/S-Oxygen -I.0 3.4 -1.4
LM-RCS -80.0 345.5 -261.0
A/S @ Docking A/S Jettison A/S-Water -12.0 45.0 -40.0
\\
3.5-19 SNA-8-D-027(III)REV 2
xO
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Amendment 86
9110170
TABLE 3.5-9
MISSION J-i COMMAND MODULE STOWAGE VOLUME CENTROIDS
sic 112
AREA XY Z
AI 1012.0 -22.0 -26.0
2 1010.0 -23.0 8.0
31016.0 -24.0 28.0
41015.0 -7.0 28.0
51015.0 9.0 28.0
61017.0 26.0 28.0
7 i010.0 23.0 8.0
8 1012.0 22.0 -23.0
91013.0 0.0 16.0
B1 1050.0 -27.0 39.0
21039.0 -38.0 37.0
31031.0 -28.0 40.0
4 1031.0 -20.0 40.0
5 I031.0 -8.0 39.0
61031.0 13.0 39.0
81024.0 -38.0 37.0
L2 1059.0 -44.0 14.0
3 1048.0 -47.0 12.0
ILl 1072.0 26.0 21.0
21072.0 26.0 14.0
3 1072.0 26.0 9.0
41075.0 28.0 3.0
5 1059.0 44.0 15.0
61048.0 46.0 29.0
8 1052.0 46.0 12.0
11 1038.0 47.0 26.0
13 1024.0 45.0 -26.0
U1 1033.0 23.0 -50.0
21033.0 -23.0 -50.0
31033.0 -36.0 -44.0
41038.0 39.0 -43.0
3.5-21 SNA-8-D-027(III)REV 2
Amendment86
911o17o
Table 3.5-9.1
The followln I stOWale locations have unique volume centrolds
not alsociated with stowale volumes.
NO .CLXTURE OCXTIO" X
G&N Signal Cond. Panel
Display Keyboard
Sleep Restraint Assy -Right
Sleep Restraint Assy - Left
Food Container
Food Container
Fecal Stowage Container
PGA 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)
Temporary Stowage Bag -Ctr.
(In-fllght Location)
Temporary Stowage Bag.- R.H.
(In-flIsht Location)
CO Absorbers (2)
CO_ Absorbers (4)
CO2 Absorbers (4)
CO Absorbers (2)
CO_ Absorbers (4)
CO 2 Absorbers (4)
First 6.8 lb.
Next 6.8 lb.
Re_u.inder CO2
CO. Absorbed
CO_ Absorbed
AbsOrbed
LEB 1069.0 25.0 29.0
LEE 1060.0 26.0 32.0
Aft UEB 1018.0 25.0 -47.9
Aft UEB 1018.0 -21.0 -49.9
L3 1048.0 -47.0 12.0
B1 1050.0 -27.0 39.0
RHEB 1039.0 47.0 12.0
On Aft Bulkhead 1015.0 0.0 -19.9
Under Center
Couch
Under L.H. Couch 1018.0 -24.5 -15.0
R.H. Girth Ring 1036.5 40.0 -25.0
L.H. Girth Ring 1036.5 -40.0 -25.0
LEB 1050.0 -27.0 39.0
R.H. Girth Ring 1036.5 40.0 -25.0
LHEB 1039.0 -47.0 12.0
LEB 1050.0 -27.0 39.0
RHEB 1039.0 47.0 12.0
In £CU 1031.0 -48.3 19.6
A3 1016.0 -24.0 28.0
A4 1015.0 -7.0 28.0
A6 1017.0 26.0 28.0
B5 1031.0 - 8.0 39.0
86 1031.0 13.0 39.0
Composite Loca-
tion used in
Sequential Hum
Properties Tables
For 002 Absorbed.
85 1031.0 - 8.0 39.0
86 1031.0 13.0 39.0
CoIpostte LoGs- 1018.5 -14.3 26.1
tlon
II L L L L L
SM&-8-D-027 (IZI) IUtV 2
1... T
L
TABLE 3.5-9.2
MISSION J-i LUNAR MODULE STOWAGE VOLUME
LM-IO
CENTROIDS
Amendment
9/10/70
86
XY Z
AIB 262.8 -20.8 15.4
AIC ICG Assy 240.5 -15.3 13.3
AIC 240.5 -18.0 13.3
AID 270.3 -15.0 19.0
AlE 265.9 -20.7 -6.0
AIF 257.4 -20./ -6.0
AIG 257.5 -20.0 -18.0
AIH 265.9 -20.0 -18.0
AIK 281.0 -20.0 -8.5
AlL 273.7 -20.0 -8.5
A2 260.0 -37.0 28.0
A3 280.0 0 -i0.0
A4 244.1 -3.5 13.5
A5 224.3 -1.5 29.3
AI0 250.0 8.8 -11.8
All PLSS LIOH Cart 263.6 18.8 -2.4
All ECS LIOH Cart 261.2 20.7 5.9
AI2 272.0 0 -18.0
AI3 300.0 0 0
FLA. 244.5 -36.6 31.4
FIB 235.5 -35.5 38.5
FIC 242.5 -35.6 38.6
FID 242.8 -35.4 47.2
FIE 237.9 -33.6 55.0
F1F 235.5 -37.6 46.6
FIG 228.0 -40.2 43.2
F5 286.0 17.8 66.6
F6 270.3 0 52.8
F6B 270.3 0 52.8
F6C 270.3 0 52.8
F7A 238.0 38.0 49.8
F7B 238.0 38.0 49.8
F7C 238.0 38.0 41.0
F7D 238.0 38.0 38.4
F7E 238.0 38.0 32.7
F7F 238.0 38.0 31.6
F7H 238.0 38.0 45.5
F7J 238.0 38.0 39.2
FTK 238.0 38.0 42.7
3.5-23 SNA-8-D-027 (III) REV 2
Amendment86
9110170
MISSION
TABLE 3.5-9.2 (Continued)
J-i LUNAR MODULE STOWAGE VOLUME
LM-10
CENTROIDS
AREA X Y
F7L
F7N
F7P
F8
F9
FIO
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
51.0
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TABLE 3.5-10
CONSUMABLES LOADING REQUIREMENTS AND TOLERANCES
Amendment 86
9110170
MISSION J-i
SPS PROPELLANT
Pressure (PSIA) Temperature (°F)
Fuel Oxidizer Fuel Oxidizer
70+5 70.+_5
110±4 110±4
quantity
Fuel
See Figure
4.1-3
Readout (%)
Oxidizer
See Figure
4.;-4
SPS Propellant Load (ib)
ILoad
2Trapped Outside Tanks
Tanked
2Trapped Inside Tanks
3Nominal Deliverable
Loading Requirement
Fuel
15704.0
78.6
15625.4
67.6
15557.8
Oxidizer
25092.0
123.7
24968.3
171.5
24796.8
Fue i
Actual
Oxidizer
_Service Module RCS Propellant
Secondary Fuel - Quads A, B, C, D - See Loading Window - Figure 4.3-1.
Primary Fuel - Quads A, B, C, D - See Loading Window - Figure 4.3-2.
Primary and Secondary Oxidizer - Quads A, B, C, D - See Loading Window -
Figure 4.3-3.
5Command Module RCS Propellant
Fuel - System A and B - See Loading Window - Figure 4.3-4.
Oxidizer - System A and B - See Loading Window - Figure 4.3-5.
9Helium and Nitrogen
Con sumab le
Helium- SPS Bottles
Helium- Fuel Tanks
Helium- N20 _ Tanks
_elium- SM/RCS
Quads A
Quads B
Quads C
Quads D
Helium- CM/RCS
Sys ten A
Sys ten B
Nitrogen - SM
Primary
Secondary
Loadin_
Pressure Temp
(PSIA) (°F)
3600 70
178 70
178 70
4150 70
4150 70
4150 70
4150 70
4150 70
4150 70
2500 85
25O0 85
Re qui remen t
Weiaht
(Ib)
87.6
5.4
6.0
1.3
3.5-71
Actual
Earth Launch Pressure TeNp
(OF)
Weisht (ib)
87.6
6.0
1.0
1.3
(PSIA)
SNA-8-D-027 (III) REV 2
TABLE 3.5-10 (Continued)
Command Module Water and GOX
Amendment 86
9/10/70
Waste Water6
Potable Water 7
CM/GOX
Pressure
(PSIA)
900±50
Loading Requirement
Weight (ib)
3.7
Earth Launch
Weight (ib)
18.0
36.0
6.7 (Entry)
8Service Module Hydrogen and Oxygen
Hydrogen
Tank 1
Tank 2
Tank 3
Oxygen
Tank 1
Tank 2
Tank 3
Loading Req. Per Tank
(pounds)
Earth Launch Weight
29.3
29.3
29.3
330.1
330.1
330.1
Per Tank (ib)
27.6
27.6
27.6
316.6
316.6
316.6
Actual
NOTES:
llndicated propellant load is based on nominal pressure and temperature
prior to actual loading. This number will be updated after loading
is accomplished.
2See Section 4.1 for explanation of trapped SPS propellant.
3See Table 3.5-13 for loading uncertainties.
4See Section 4.2 for SM/RCS loads and uncertainties to be used in Mis-
sion Planning. Actual SM/RCS loads and uncertainties will be published
in Table 3.5-15.
5See Section 4.2 for CM/RCS loads and uncertainties to be used in Mis-
sion Planning. Actual CM/RCS loads and uncertainties will be published
in Table 3.5-14.
6Launch Rule Redlines determine lift-off values.
7Launch Rule Redlines determine lift-off values.
8Launch Mission Rules will determine minimum lift-off quantities for
H 2 and 02 .
9CSM helium and nitrogen should be loaded in accordance with loading
windows contained in CSM/LM Spacecraft Operational Data Book, Volume I,
Part 2, SNA-8-D-027(1) P2.
SNA-8-D-027(III)REV 2
3.5-72
TABLE 3.5-11
SPS PROPELLANT LOAD CALCULATIONS
i. Enter SPS Quantity Readout at Ii0 PSIA (Table 3.5-12
Item C - Percent)
2. Use Figures 4.1-3 and 4.1-4 to obtain propellant
load for above quantity readout.
3. Nominal propellant density at loading temperature
(use temperature - density graph below) (ib/ft 3)
4. Cubic feet of propellant (Item 2 divided by Item 3)
5. Calculated density from Table 3.5-12 Item F (Ib/ft 3)
6. Adjustment due to PUGS zero adjust (pounds)
7. Resulting actual propellant load (Item 4 times
Item 5, less Item 6) (pounds)
Amendment 86
9110170
Fuel Oxidizer
SPS SPS
Oxldlter FLItL SPS Propellsnt Teaqsersture/Denstty Grsph
8t 110+5 PSZA
n
E
N
S
I
T
y
I.I/r'F )
119.
temperature Dejroee F
3.5-73
SNA-8-D-027 (III) REV 2
,I.I
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Amendment 86
9110170
TABLE 3.5-13
SPS PItOPILL_ I/tICZlTJLINTIES
ITEM
LOADING UtiCEitSAIttTIES
Tank Volume
Tanparacure Gauss ('2.0oF)
Standpipe Helaht
Propellant Gouje (tO.35X of Oauaeable)
Density Meaeurtment (i)
Batch Density (I)
hoadlnB Pressure (I)
RSS
FUXL
(Ib)
t24
"18
• 6
"54
t 0
t9h
t8
t113
TOTAL RSS t172
Loadin$ Specification (1) (2)
Tolerance on Propellant Temperature
of Flight Load
TOTAL LOADING UNCERTAINTY
MISSION UNCERTAINTIES
Mixture Ratio Variation
iV. Iep, Vehicle Welehc Variation
Propellant usaee uncertainty due to
total loadin8 uncertainty
OXIDIZZl
(lb)
t39
it6
"10
• 86
t 0
.75
'14
'130
t16 t24
+0.0 +0.0
-46.0 -113.0 i
+212
-371
TBD
TBD
TBD
TOTAL PROPELLANT UNCERTAINTY FOI
MISSION AV TBD
NOTES: (1) Data viii be known after loadin8 is accolpliahed.
(2) Loedieql specification is an allovable tolerance about
nouinal, this number is added to the loadilqJ uncertainty
variables.
3.5-76 SNA-8-D-02 7 (III) REV 2
t_. t--
.amendment 86
9/10/70
TABLE 3.5-14
Com_tnd Module BC$ Losdln 8 Perameter8 and Calculationa
This table will be 'completed when loadtn8 is accouplLshed. For HLsston
Plennln 8. reference should be made to SectLon 4.2 for nominal load, loedLn8
tolerances, trepped and deliverable propellantJ.
le_...._L OXIDIZER
A. Tank Volume @0.0 PSIA (in 3)
B. Liquid Line Volume (in 3)
C. Total A+B(in 3 )
Tank A Tank BTank A Zank___.__S
De Initial Weilht In Bleed UnlC
Prior to Loed£n8 (lb)
Ee
_e
Final Wellht in Bleed Unit
After Loadtnj (lb)
Propellan¢ Load (item D lees
than EWeilh Tank)
G. Propellant Load by P.V.
H. Loadtn| Temperature ('F)
I. Specification Propellant
Load B70t$oF (lb)
J, Total Qq/lCS Propellant
Load from Item O above (lb)
K. Maximum Trapped Propellant (lb)
L. Nominal Deliverable (lb)
3.5-77 SNA-8-D-027 (Ill) EEV 2
ltl U I_ L L L lC L L LL LI LL L_ Ii 1_ t_ _ L ,_ ._.
Amendment 86
9110170
TABLE 3.5-15
SEIVlC Ir MODULE ICS LOADING SUI_TZON
This table v%11 be conpleted vhen loadln8 Ls accamplLshed. For NLaaLon Plan-
hieS, reference should be made to Section &.2, for holies1 load, lo_d£n 8
tolerances, end nominal deliverable propellants.
Quad A(lb) _uad J (Ib_
Secondary fuel
Primary fuel
Total fuel t0.7
Maxim,,- Trapped 2.1
Nominal Deliverable
Secondary fuel
Prinary Fuel
Total fuel
J4aximum Trapped
Nominal Deliverable
t0.7
2.1
Total Oxidizer
Maximum Trapped
Nominal Deliverable
Secondiry flreT--
Primary fuel
Totst-_uel .......
Maximum Trapped
No_ri_r_l DelTu_lrable
Total Oxidizer
MurlmuD Trapped--
Nominal Deliverable
Total fuel
Maxi_[mrTTIpped
Nominal Deliverable
*2.3 Total Oxidizer t2.3
4. _ Hmci_ua Trapped 4.5
Primary f@e_ ._d __ :-_-.__,_
_Totel fuel *0.7
_*_nom_nal Deliverable
•"'_'""_T
t2,3 Total OxldtzeTdL) _I.__2.3
(d;.) s_o_ _me;l mo_ bzoJ
Total SH/ltCS Propqt_4n_.o@_._l_.:.... _ b_qqr,.'_T _,_:xe_. ,Ji
,1.4 Total O,_,,li_.da.,,,v::,._,__;_._._L,,.. #
8.4--- lqsxlnum Trapped 18,0
Nomlnal Deliverable
3.5-78 SNA-8-D-027 (llI) REV 2
U 11 1_ _1_ LEL L l_ U_ _ l_ l_ _L_"
TABLE 3.5-16
LM-10 CONSUMABLE LOADING REQUIRE_NTS
LM-IO APS PROPELLANT
Amendment 94
12/10/70
Fuel (lb)
Propellant Load 2008.6
Trapped Outside Tanks 5.9
Tanked 2002.7
Trapped Inside Tanks i0.I
Nominal Deliverable 1992.6
Outage TBD
Total APS Propellant
Oxidizer (Ib_
3225.8
8.3
3217.5
27.6
3189.9
TBD
TBD
The following table should be used to determine the amount of propellant
to be off-loaded from a full condition to arrive at the indicated load.
The allowable tolerance for the calculated off-load is ±0.5 pounds per
weigh tank.
A. Final tank pressure at overfill (PSIG)
B. Propellant loading temperature (°F)
C. Nominal overfill quantity (Ib) TBD
D. Correction for tank pressure (ib)
Fuel - 0.09 (Item A-40)
Oxidizer =0.15 (Item A-40)
IE. Correction for loading temperature (Ib)
Fuel -1.16 (Item B-65)
Oxidizer --2.84 (Item B-65)
2F. Measured density (GM/CC)
2G. Nominal density (GM/CC) 0.8994
H. Delta density (GM/CC) (Item F-G)
3I. Correction for measured density
Fuel -2300 (Item H)
Oxidizer - 2300 (Item H)
J. Propellant in GSE
K. Overfill quantity (C+D+E+I÷J)
L. Target loading 2008.6
M. Quantity required to fill RCS manifolds i0.0
N. Quantity to be off-loaded (Item K-L-M)
TBD
1.4824
3225.8
15.8
NOTES:
iLoading temperature correction will always be negative.
2To calculate thenominal density solve the following equation where T -
temperature in °C of the measured density (usually 4"C for oxidizer and
25°C for fuel). This equation is valid for 14.7 PSIA. Therefore, the
measured density must also be at 14.7 PSIA.
Nominal fuel density =0.922904-0.0009377 (°C)
Nominal oxidizer density =1.491539-0.0022832 ('C)
3Correction for measured density mey be either positive or negative.
3.5-79 SNA-8-D-027(III)REV 2
TABLE 3.5-16 (Continued)
LM-IO CONSUMABLE LOADING REQUIRE_NTS
LM-IO DPS PROPELLANT
Amendment 94*
12/10/70
Fuel (lb)
Propellant Load 7538.7
Trapped Outside Tanks 27.7
Tanked 7511.0
Trapped Inside Tanks 19.2
Nominal Deliverable 7491.8
Outage TBD
Total DPS Propellant
IEI.
2FI.
2 G1.
HI.
BII.
Oxidizer (Ib)
12046.7
49.2
11997.5
40.9
11956.6
TBD
TBD
The following table should be used to determine the amount of propellant to be
off-loaded from a full condition to arrive at the indicated load. The allow-
able tolerance for the calculated off-load is ±0.5 pounds per weigh tank.
AI. Final tank pressure at overfill (PSIG)
BI. Propellant loading temperature (°F)
Cl. Nominal overfill quantity (ib) TBD TBD
DI. Correction for tank pressure (ib)
Fuel - TBD
Oxidizer = TBD
Correction for loading temperature (ib)
Fuel - TBD
Oxidizer - TBD
Measured density (GM/CC)
Nominal density (GM/CC) 0.8994 1.4824
Delta density (GM/CC) (Item Fl-ltem GI)
Correction for measured density
Fuel - TBD
Oxidizer - TBD
Jl. Propellant in GSE
KI. Overfill quantity (CI+DI+EI+II+JI)
LI. Target loading 753g.7
M/. Quantity required to fill RCS manifolds (APS only) xxxxxxx
NI. Quantity to be off-loaded (Items KI-LI-MI)
XXXXXXX
NOTES:
ILoading temperature correction will always be negative.
2To calculate the nominal density solve the following equation where
T-temperature in °C of the measured density (usually 4°C for oxidizer
and 25°C for fuel). This equation is valid for 14.7 PSIA. Therefore,
the measured density must also be at 14.7 PSIA.
Nominal fuel density =0.922904-0.0009377 (°C)
Nominal oxidizer density =1.491539-0.0022832 (°C)
3Correction for measured density may be either positive or negative.
3.5-80 SNA-8-D-O27(III)REV 2
t_
System AFuel
System A Oxidizer
System B Fuel
System B Oxidizer
TABLE 3.5-16 (Continued)
LM-10 - RCS PROPELLANT (2) (3)
Required Ullage Requirement (in _)
Load (Ib) 5Minimum 4 Maximum 4
107.7±0.9 152.5 164.5
208.8±1.9 267.0 279.0
107.7±0.9 152.5 164.5
208.8±1.9 267.0 279.0
Amendment 94
121_0/70
iActual4 i
Ullage (in 3)
FUEL OXIDIZER
Propellant Load 215.4 417.6
Trapped Outside Tanks 10.3 16.2
Tanked 205.1 401.4
Trapped in Tanks 4.2 8.0
Nominal Deliverable 200.9 393.4
LM-IO -Helium b Nitrogen
Consumable
Helium - APS tank #i (6)
-APS tank #2 (6)
- RCS tank #I (6)
-RCS tank #2 (6)
-DPS (SHe)
- DPS (Ambient)(6)
Nitrogen - Ascent
- Descent
Nominal Loading Requirement
Pressure ' Temp Weight
_PSIA_ ('F_ (ib)
3050 70 6.6
3050 70 6.6
3050 70 1.05
3050 70 1.05
80±2 N/A 48.5
1600 70 i.i
0.i
0.6
Actual
Pressure Temp Weight
(PSIA_ (°F) (ib)
LM-IO - Water bGOX
Consumable
Ascent Water -tank #I
- tank #2
Descent Water - tank #I
- tank #2
Ascent COX -tank #i (6)
-tank #2 (6)
Descent GOX - tank #i (6)
- tank #2 (6)
Nominal Loading Requirement Actual
Pressure Weight Pressure
(PSIA) (ib) (PSIA)
N/A 42.5 N/A
N/A 42.5 N/A
N/A (7) N/A
N/A (7) N/A
830 2.4
830 2.4
2700 48.0
2700 48.0
Weight
(lb)
NOTES:
iSee Table 3.5-17 for actual propellant load calculation.
2See Section 5.6 for explanation of trapped propellants.
3See Table 3.5-18 for loading uncertainties.
_PV ullage calculation should be 158.5±50 cubic inches for LM/RCS fuel and
273±50 cubic inches for LM/RCS oxidizer per tank.
5LM/RCS required load includes propellant required to fill RCS manifolds
to isolation valves. See Table 3.5-16. See Section 5.6 for trapped
propellants.
6The indicated items should be loaded in accordance with loading windows
contained in the CSM/LM Spacecraft Operational Data Book, Volume II,
Part 2, SNA-8-D-027PT2.
7LM-IO Descent Water shall be loaded to provide 365-0.O+10.0 pounds
at Earth Launch. Initial load will be determined by sampling requirements.
3.5-81 SNA-8-1)-027(III)REV 2
TAllLI 3.5-17
LOAD CAL_TXOM
1. Full tank - Item K, Table 3.5-16 (lb)
12. Denslty of off-load tables at loadlnl
temperature end preosuta (1hilt 3)
13. Propellant volume (dlvtde Item I by
Item 2. (f_3)
14. Measured denslty (from Table 3.5-19
(lb/fc 3)
5. Rasulttns full tank load (lb)
6. Off-load amount (lb)
7. Propellant requlred to f111 RCS au.nifolds
(lb)
8. Propellant lomd (lb)
pPS PROPELLANT
9. Full tank - Item K1 Table 3.5-16 (lb)
I10. Density of off-load tables st loadtn8
temperature and pressure (lb/ft l)
Ill. Propellant voluDe (divide Item 9by Ices
10 )(ft 3)
112. Measured density (from Table 3.5-19)
(lb/ft 3)
13. Resulting full tank load (Ib)
14. Off-load amount (lb)
15. Propellant load (Ib)
RcsPROFZLI_ST
P. V. Calculations
A. GSE Volume (In 3)
B. InitLel U1leSe Pressure
(PSIG)
C. Initial GSE Pressure
(PSIC)
D. Flnsl GSE - S/C Pressure
(PSZ¢)
E, Ullale Volume (in 3) - Solve
the follovin8 equation by
lubstttutin8 the valual in
the indicated steps.
Ullale Voluam - (D-C) (A)
I-O
NOTE:
Amendment 86
9110170
Fuel _ldlser .
Yuel Oxidizer
•_3.qnk_ tsu!_! _tsnk__ It_.._
1These _tewm will be completed only if a deem£ty smqple te emt
made prior to loadlnj. If 8 de_ity sample is m_le prior to
loadln8, then the items w111 be left blm.
3.5-82 SNA-S-D-O27 (IZl)UV 2
TABLE 3.5-18
124-10 PROPELLANT LOADING UNCERTAINTIES
LM-10 APS PROPELLANT
Vent Line Volume
Tank Volume
Pressure Measurement (+-5 PSIA)
Temperature Measurement (+-1.5°F)
Measured Density
2Welght Measurement
ILoadlng Tolerance
Total Loading Uncertainty
Amendment 94
12/lO/7O
Fuel (Ib) Oxidizer (Ib)
±0.2 +-0.3
+-0.8 +1.3
±0.5 +-0.8
±1.7 +-4.3
±0.7 +-0.5
±0.5 +-0.5
±0.5 ±0.5
+-4.8 z8.2
APS Mission Uncertainties
Mixture Ratio Variation
_V, Isp , Vehicle Weight Variation
Propellant Usage Uncertainty Due To Total
Loading Uncertainty
Total Propellant Uncertainty For Mission _V
TBD
TBD
TBD
TBD
LM-10 DPS PROPELLANT
Vent Line Volume
Tank Volume
Pressure Measurement (±5 PSIA)
Temperature Measurement (1.5°F)
Measured Density
2Welght Measurement
ILoading Tolerance
Total Loading Uncertainty
±0.2 ±0.3
±3.62 ±5.96
±1.70 ±2.77
±6.49 ±15.76
±2.55 ±1.70
±0.5 +-0.5
±0.5 +-0.5
±15.6 +-27.5
DPS Mission Uncertainties
Mixture Ratio Variation
dV, Isp , Vehicle Weight Variation
Propellant Usage Uncertainty Due To Total
Loading Uncertainty
Total Propellant Uncertainty For Mission AV
TBD
13D
TBD
TBD
_M-IO RCS PROPELLANT
Loading Temperature ±0.6 +-1.8
Ullage Calculation ±0.4 +-0.6
Tank and Manifold Volume ±0.8 +-1.4
Total +-1.8 +-3.8
IThese will be known quantities after loading is accomplished.
2If weigh tank is used for off-loadlng, then weight measurement uncertainty
_s ±0.5 pounds per wei&h Clmk. If flow meter le used for off-loadlng, then
weight measurement uncertainty is +-4'OZ of amount off-loaded.
3.5-83 SNA-8-D-O27(III)REV 2
TABLE 3.5-19
LN-IO APS Propellant LomUn8 Peremetors
(To Be Completed by DC at I_adins)
Losdin8 Pressure - PSIA
_58 Fuel
Losdin8 Tsmpersture - Fill Llsw - DeSreOe F 258 Oxidlzmr
_tTT 59 Fuel
Losdin8 Temperature -Return Line - Desroos ril.t259 Oxidiser
_1GP0718 Fuel
Losdlng Temperature - Tank - Desrees r_pl2x80zldlser
Number of Tt_ts Welih Tank Used (Flow Noter Hot Used)
Total Pounds Off-Losded Usin8 Welsh Tank (Flow Meter Hot Used)
Pounds Off-Loaded UsinS Flow Meter (Wetsh Tm_k Not Used)
Neasured Fuel Density @"C; @PSIA Q4/CC
Heasured Oxidizer Density @ eC; @ PSIA GN/C¢
Amendment 86
9110170
Fue___I Oxidizer
3.5-84 SNA-8-D.-027(tII)REV 2
I1 II E LL. LL L h h h
Amendment 86
91101;'0
TABLK 3.5-19 (Continued)
Lid-10 DPS Propellant Loedln8 Parm_terz
Loadin8 Pressure - PSIA
J_ 58 Fuel
Loedi_ Te_erature - Ftll Line - _|rans Fl_258.0xldlzer
IT 59 r.el
Lo_in8 Temperature -_curn Line - _8rmes FlTT259 Oxidiser
F_3718 _el
Loadin8 Temperature -Te_ _e -_8rmes 1_4218 _ldlzer
Loedin 8 Te_erature - Te_ _o -_sree8 F1_3719 Fuel
1C,_4219 Oxidizer
Number of Times Wetsh Tank Used (Flow _ter Not Used)
1
Total Pounds Off-Loaded Usln8 Wetsh Tank (Floe Meter Not Uzed)
Pounds Off-Loaded Uein8 Floe _Cer (Weish Tank NoC Used)
_asured Fuel Den81_ @"C; PS_ _/CC
Measured Oxidizer Density @"C; PSZA GN/CC
3.5-85 SNA-8-D-O27(III)REV 2
j_ L-
Amendment 87
9115170
MISSION J-i MASS PROPERTY DATA TABLES
Table 3.5-20 presents the CSM-112/LM-lO(docked) ms properties, in Apollo
coordinates, as 8 function of spacecraft weight for L.O.I.
SM/SPS burn.
Table 3.5-21 presents the CSM-112/LM-10 (docked) mass propercles, In Apollo
coordinates, as I functio_ of spacecraft welahC for the
D.O.I. SM/SPS burn.
Table 3,5-22 presence the CSM-112 mama properties, in Apollo coordinates,
as a function of CSM weight for the Circularization I SM/SPS
burn.
Table 3.5-23 presents the CSM-112 mass properties, in Apollo coordinates,
as afunction of CSM waisht for the Plane Change I SM/SPS
burn.
Table 3.5-24 presents the CSM-112 mass properties, in Apollo coordinates,
as a function of CSM wei6ht for the T.E.I. SN/SPS burn.
Table 3.5-25 presence the LM-10mas8 properties, in LM coordinates, as a
function of I/4 weiSht for the P.D.I. DPS burn.
Table 3.5-26 presents the LN-10iscent sCaBs mass properties, in I24 coordinates,
as a function, of weiiht for the lunar liftoff AFS burn.
Table 3.5-27 presents the L/f-10ums8 properties, in 124 coordinates, as a
function of LM lmisht for the T .P .I. to docking LM/RCS burn.
3.5-86 SNA-8-D-027 (III)P.EV 2
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The data presented in this section will enable the user to obtain the sep-
arate centers-of-gravity and moments-of-inertia for those spacecraft con-
sumables on-board that significantly affect overall CSM and CM performance.
CSM consumables mass property data must be compared to the current on-board
consumable loading data for each mission provided in Section 3.0. The mass
property data are presented in the following sections:
4.1 SPS Tank Consumables Mass Properties, Trapped Propellants,
SPS Density Equations and Graphs, and SPS Loading Windows.
4.2 RCS/ECS/EPS Consumables Mass Properties, and SM RCS Quad
Mass Properties
4.3 CSM RCS Load Calculation Tables and Loading Windows
4.4 CM Ablator Data
4-1 SNA-8-D-027(III)REV 2
11 lJ 1; :E l: E L L E L. L i: L' l; E E L, :_ L_ ,__
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TABLE 4.1-i
Table 4.1-1 presents the mass characteristics for the SM/SPS propellant
tanks.
The following units apply to the indicated headings:
Height of Propellant - Inches Mass of Propellant - Pounds
Tank Volume Unstretched - Ft3 Center of Mass - XA Coordinates - Inches
Tank Volume Stretched - Ft 3 Moment of Inertia (Iyy) - Slug-ft 2
Further, Moment of Inertia IZZ - Moment of Inertia Iyy; Moment of Inertia IXX-0.0
for all propellant weights; tank pressure used in calculating this table was
175±5 PSIA, propellant temperature was 70°F, density for fuel was 56.43 ib/ft 3,
and oxidizer density was 90.21 ib/ft 3.
The YAand ZA Center of Mass components for the individual tanks are constant
and are as follows:
YA (inches) ZA (inches)
Fuel Storage -14.8 -47.8
Fuel Sump -48.3 -6.6
Oxidizer Storage 14.8 47.8
Oxidizer Sump 48.3 6.6
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TABLE 4.1-2
TRAPPED SPS MASS PROPERTIES
SERVICE MODULE
i SPS - Trapped Outside Tanks
Engine - Fuel
- Oxidizer
Feedline - Fuel
- Oxidizer
Transfer Line - Fuel
- Oxidizer
Total Outside Tanks
2 Trapped in Tanks
Retention Reservoir - Fuel
- Oxidizer
Vapor - Fuel
- Oxidizer
Total Inside Tanks
Weight
Pounds
29.6
47.4
29.5
44.7
19.5
31.6
202.3
61.4
97.5
6.2
74.0
239.1
Center of Gravity
Inches
XA YA ZA
846.9 6.6 0.4
843.0 -7.1 1.6
832.0 -48.0 -25.0
832.0 48.0 25.0
829.0 -27.0 -24.0
829.0 27.0 24.0
836.0 4.5 3.7
i SPS propellant trapped outside tanks should be subtracted from the total
SPS propellant load for a particular mission to arrive at the tanked
SPS propellant. This tanked amount is then used in the preceeding
tables to arrive at the appropriate SPS propellant Mass Properties.
2 The total SPS propellant load for a particular mission less trapped
in tanks and outside tanks equals nominal deliverable SPS propellant.
4.1-22 SNA-8-D-027 (III)REV 2
L
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 appropriate equation below and calculate the fuel or oxidizer
density at the given pressure and temperature of the KSC sample. This
will usually be 14.7 PSIA and 25°C for fuel, and 14.7 PSIA and 4°C for
oxidizer.
B. Use the appropriate equation below and calculate the fuel or oxidizer
density at the final system pressure and temperature. This will
usually be 110±5 PSIA and 70±5°F.
C. Subtract the density obtained in step A from the measured density of
the KSC sample, and add this amount (may be either positive or
negative) to the density obtained from step B.
A-50 DENSITY EQUATION
PF _ [57"6095-0"058533(°C)](CF)
where: O F = A-50 density in Ib/ft 3
=C m Temperature in degrees centigrade
C F =Compressibility factor - obtain this number from the
pressure - compressibility graph on Figure 4.1-1 of
this section.
N204 DENSITY EQUATION
PO m [93.1048_0.14252(0C)](Co )
where: 00 =N20 _ density in ib/ft
°C = Temperature in degrees centigrade
CO =Compressibility factor - obtain this number from the
pressure - compressibility graph on Figure 4.1-2 of
this section.
4.1-23 SNA-8-D-027(III)REV 2
1.00160
1.00140
=.ool2o
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160 200 240
PRESSURE, PSIA
FIGURE 4.1-1 Aerozine-50 Compressibility Correction Factor
4.1-24 SNA-8-D-027 (IIl) REV 2
II II I,'K L I/ L L E I/ _ LL: 11 UL: _ ,..,__L
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FI GURE 4. i- 2
TI =90"DE'G I='_
"1"2=70 DEG F
T3 =50 DEG F
PROPERTIES OF LIVE PROPELLANTS _ _
TETROXIDE _. _ _ ii_
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PRESSURE, PSIA
i-.-_ +-_4 H.
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240
Nitrogen Tetroxide Compressibility Correction Factor
4.1-25 SNA-8-D-027 (III) REV 2
SERVICE MODULE SPS FUEL LOADING WINDOW FOR SM 107 AND SUBSEQUENT
FUEL
FOR ULLAGE LOADING PRESSURE OF 110±4 PSIA
-;?{?
10l _" ::::
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T._-'-;, _. ;i 2L _-i_
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Figure 4.1-3
PROPELLANTTEMPERATUREAT FLIGHT LOAD-
:@ti +
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4.1-26 SNA-8-D-O27(III)REV 2
EIS 1_ L id I_ I,: 1_ K-.
SERVICE MODULE SPS OXIDIZER LOADING WINDOW FOR SM 107 AND SUBSEQUENT
OXIDIZER
FOR ULLAGE LOADING PRESSURE OF ii0_4 PSIA
if" +
......... ?,+
_i:ii :!?
r, <!::::
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_,'+_ =: 25092 _1;: i
' -X-_-LV_I IF-:
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Figure 4.1-4
4.1-27 SNA-8-D-027 (III) REV 2
ILl II Id I: L. IL IL L IL E l_ 12 Y II Ii IL L, L ,_ ;_
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SNA-8-D-027(II) REV 2
Volume II LM Data Book
Subsystem Performance Data - Crew/Equipment
Amendment ii0
5/21/71
4.2.2
4.2.3
4.2.4
4.2.5
CREW /EQU I PMENT
Food Requirement
Each man requires 3200 calories of food per day.
Sensory Limits
Deleted (NASA DATA SOURCE)
PLSS Condensate Transfer Assembly
The PLSS Condensate Transfer Assembly accommodates a maximum of 5190
cc of liquid condensate. The maximum value of condensate fluid from
a single PLSS discharge shall be 4400 cc of which a maximum of 865
cc shall be liquid.
The PLSS Condensate Transfer Assembly operational temperature is 35°F
to 135°F. The relief valve cracking pressure is 2.1 to 2.9 psid.
The full open pressure is 3.8 psid.
The rate of flow of condensate from the PLSS to the PLSS Condensate
Transfer Assembly is from 0 cc/sec to i00 cc/sec. The maximum
flow rate for "all water" transfer is 25 cc/sec. The maximum flow
rate for all gas is i00 cc/sec.
Thermal Variations for the MESA
See appropriate S/C Appendix.
Thermal Variation of the Sample Return Containers after Removal
from the MESA (NASA DATA SOURCE)
See appropriate S/C Appendix.
4.2.6 Thermal Response of the Lunar Surface Color TV Camera (NASA DATA SOURCE)
See SODB Volume VII (GCTA) for TV Camera Operation and Performance data.
4.2.7 Crew Heat Storage and Temperature Tolerance Limits
Heat storage should be limited to _300 Btu. Above 300 Btu, the perfor-
mance of tasks of mental complexity or high physical demand is sharply
reduced. Below -300 Btu, shivering is continuous and very distracting
and likely to severely limit performance. Figure 4.2-1 indicates these
areas as the limited tolerance hot and cold zones. Between these zones
tolerance is not time limited.
Contract No. NAS 9-1100
Primary No. 664 G_ Aerospace Corporation
4.2-1
LED-540-54
II II 11 L 1i 11 12 12 1i l;i /d LL 1,_ II II i,1 k! __ L i.
SNA-8-D-027(II) REV 2
Volume II LM Data Book
Subsystem Performance Data-Crew/Equipment
Amendment 128
7/27/71
4.'2.8
4o9
Data Acquisition Camera (DAC) and Film Canisters Thermal Response
See Table 3.10-2 and appropriate spacecraft appendix.
Quad III Stowase Temperature Predictions
Temperature predictions were made for the LM-IO and LM-II pallet
configurations using the worst hot and cold case vehicle orienta-
tions allowable within the thermal design mission. The mission
timelines used are described in Figure 4.2-6. The temperature
profiles of each pallet are presented in Figures 4.2-2 through
4.2-5. It should be noted that the temperatures indicated are
average temperatures derived from a lumped one-node representation
of each pallet and its equipment. In reality, local equipment
temperatures could vary as much as 15°F from the predicted average
pallet temperature. The only difference between the two networks
used for the calculations is the thermal mass of each pallet.
Temperature responses for LM-12 pallet are expected to be less
severe than those of LM-I1 because of the increased pallet weights
for LM-12.
Temperature predictions for the actual mission profiles are contained
in the individual spacecraft appendices.
Reference: LMO 510-1765, LM-IO through LM-12 Quad III Stowage
Temperature Predictions for a two Pallet Flight
Configuration, dated ii January 1971.
4.'2.10 Waste Manasement System
The waste management system consists of a containerized waste
management tank in the descent stage, and urine receptacles and
transfer hoses in the cabin. An analysis has shown worst case
operating temperatures of the cabin items between 45°F and IO0°F,
well within the qualification test temperature range of 35°F to
135°F (see Figure 4.2-7). The containerized waste management tank
has a capacity of 5.0 _allons (40 ibs.) to accommodate urine and
PLSS condensate which are fed through a line from the cabin. The
tank has a primary vent valve which opens at 2.5 psia into a tube,
leading to the outside of the vehicle. A secondary valve opens
at 3.75 psia and empties into the quad IV bay. An analysis shows
worst case operating temperatures without heater use to be 40°F to
120°F, well within qualification test temperatures of 35°F to 160°F
(see Figure 4.2-8). Two 15-watt redundant heater systems are pro-
vided to heat inlet and outlet ports, and are planned for use shortly
before, after, and during container filling.
Contract No. NAS 9-1100
Prlmarv No. 664 Grumman Aerospace Corporation
4.2-1.1
LED-540-54
L7
1_
r
kll, wr-n,,Le
quad A -
Qued I -
o
• Quid C -
_ad U -
hltvereble
TABLE 4.2-1
(6)
Prtuuury fuel
Iocndory Fu_l
hidieer
Prioery I_Jol
kclmdory roe1
Oztdtnr
PrL,_ry Voel
|ocondory Foe L
Oxidiser
Primary Fuel
Second,try Fuel
OxLdiler
Priury l_el
Secondary Fuel
OzLdLter
Deliverable lroel
Ozidt set"
Tow! Oeltvereble (6)
(CONTINUED)
hklisht
Pounde
(_oetor of Grsvity
Inckoo
XA YA ZA
68.5t0.8 '964.| O.O -68.5
$9'6"0'8 905.1 -9.0 -69.0
!220.9t3.4 92b.9 8.0 -6|.5
68.5t0.8 91_.8 64.5 026.S
39.6'0.8 08S.1 68,0 -Ll,O
220.9*3.4 S2b.9 6_.5 -26.5
68.5t0.8 96_.8 -|.0 b|.S
39.6t0.8 905.1 7.0 60.0
220.9t3.4 926.9 -I.O 68.5
68.5t0.8 964.0 -6&.$ 26.5
39.6t0.8 gOS.L -60.0 11.0
220.9t3. 4926.9 -b4.5 2b.S
274.0tl.6 964.8 0.0 0.0
158"4t1"6 985.1 o.o o.o
883.6"6.8 92b.q 0.0 0.0
432.4_2.3 972.,) o.o o.o
883.6"6.8 92_.9 o.o o.o
3)b.0"7.2 942.L o.o o.o
4.2-3 SNA-8-D-027 (III) REV 3
TABLE4.2-1 (CONTINUED) Amendment106
6/22/71
CSM112 ANDSUBSEQUENTMISCELLA_'EOUSCONSUMABLES
CSMMISCELLANEOUSCONSUMABLES
CM/RCS- HELIUM
CMIECS
Oxygen- Entry
PotableWater (3)
WasteWater (4)
SM/RCS- Helium
SM/SPSHelium- StorageBottles
- Tanks(5)
SM/Nitrogen
SM/EPS/ECS
I
Oxygen- Hydrogen
H2 Tank 3
H2 Tank 2
H2 Tank 1
02 Tank I
02 Tank 2
02 Tank 3
Total - H2
- O
Total on B_ard
Unusable - H 2
H 2
H 2
O2
O 2
02
Unusable - H 2
- 0
Total Unusable
Usable - H 2
- H 2
- H 2
O2
O2
02
Usable - H 2
- 0
Total Usable
WEIGHT I
POUNDS
XA
1.0 ,1022.6
(7) 1031.1
(7) 1022.6
(7) 1022.6
6.0 983.9
87.6 954.7
5.4 976.0
1.3 874.0
29.3
29.3
29.3
330.1
330.1
330. i
87.9
990.3
1078.2
1.2
1.2
1.2
6.6
6.6
6.6
3.6
19.8
23.4
28.1
28.1
28.1
323.5
323.5
323.5
84.3
970.5
1054.8
_ominal Loading. For Liftoff values see
4.2-4
CENTER OF G_VITY
INCHES
974.6
859.4
892.9
920.8
920,8
938.0
909.0
926.6
925.1
974.6
859.4
892.9
920.8
920.8
938.0
909.0
926.6
923.8
974.6
859.4
892.9
920.8
920.8
938.0
909.0
926.6
925.1
YA ZA
-3.1 25.8
-26.9 -34.2
-63.5 -16.4
-19.7 62.5
0.0 0.0
0.0 0.0
2.7 8.9
0.0 0.0
37.0 -46.0
-40.7 41.2
-40.7 41.2
-20.9 26.9
-27.4 54.5
22.5 -30.0
-14.8 12.1
-8.6 17.1
-9.1 16.7
37.0 -46.0
-40.7 41.2
-40.7 41.2
-20.9 26.9
-27.4 54.5
22.5 -30.0
-14.8 12.1
-8.6 17.1
-9.6 16.4
37.0 -46.0
-40.7 41.2
-40.7 41.2
-20.9 26.9
-27.4 54.5
22.5 -30.0
-14.8 12.1
-8.6 17.1
-9.1 16.7
individual Mission Section.
SNA-8-D-027 (III) REV 3
li II l= i._ " "L. L
Table 4.2-1 (Continued)
CSM 112 and Subsequent Miscellaneous Consumables
Amendment 86
9/10/70
CSM MISCELLANEOUS CONSUMABLES
CM/RCS -HELIUM
CH/ECS
Oxygen -Entry
Potable Water (3)
Waste Water (4)
SM/RCS - Helium
WEIGHT CENTER OF GRAVITY
POUNDS INCHES
1.0
(7)
(7)
(7)
6.0
XA
1022.6
1031.1
1022.6
1022.6
983.9
-26.9
-63.5
-19.7
0.0
ZAI
25.8
-34.2
-16.4
62.5
0.0
SM/SPS Helium - Storage Bottles
SM/Nitrogen
SMIEPSIECS
-Tanks (5)
87.6
5.4
1.3
954.7
976.0
874.0
0.0
2.7
0.0
0.0
8.9
0.0
1
Oxygen -Hydrogen
0 2
0 2
0 2
Total - H 2
O
Total on Bo2ard
Unusable - H 2
H2
H2
02
02
02
Unusable - H2
- 0
Total Unusable
Usable - H 2
-H 2
H 2
02
02
02
Usable - H 2
-0
Total Usable
29.3
29.3
29.3
330.1
330.1
330.1
87.9
990.3
1078.2
1.2
1.2
1.2
6.6
6.6
6.6
3.6
19.8
23.4
28.1
28.1
28.1
323.5
323.5
323.5
84.3
970.5
1054.8
_ominal Loading. For Liftoff values see
974.6
859.4
892.9
920.8
920.8
938.0
909.0
926.6
925.1
974.6
859.4
892.9
920.8
920.8
938.0
909.0
926.6
923.8
974.6
859.4
892.9
920.8
920.8
938.0
909.0
926.6
925.1
37.0
-40.7
-40.7
-20.9
-27.4
22.5
-14.8
-8.6
-9.1
37.0
-40.7
-40.7
-20.9
-27.4
22.5
-14.8
-8.6
-9.6
37.0
-40.7
-40.7
-20.9
-27.4
22.5
-14.8
-8.6
-9.1
-46.0
41.2
41.2
26.9
54.5
-30.0
12.1
17.1
16.7
-46.0
41.2
41.2
26.9
54.5
-30.0
12.1
17.1
16.4
-46.0
41.2
41.2
26.9
54.5
-30.0
12.1
17.1
16.7
individual Mission Section.
4.2-4.1
SNA-8-D-027(III)REV 2
II I/ I: IJ I: ELL E E L L: L: Ii I.: " 'l_ _- L-- L
Amendment 86
9/10/70
This page intentionally left blank
4.2-4.2 SNA-8-D-027 (III) REV 2
Amendment 66
9/12/69
TABLE 4.2-1
CSM -CONSUMABLE LOADS AND UNCERTAINTIES
This table contains the consumable loads, associated
tolerances, and/or uncertainties aL nominal loading
temperatures and pressures.
COMMAND MODULE
Nominal Load
RCS (2)
Loaded System I - Fuel
System 1-Oxidizer
System 2 - Fuel
System 2 - Oxidizer
Loaded - Fuel
-Oxidizer
Total Loaded
Maximum Trapped
System 1 - Fuel
System I - Oxidizer
System 2 - Fuel
System 2 - Oxidizer
Trapped - Fuel
-Oxidizer
Total Trappea (Maximum)
Deliverable (6)
System 1-l'uel
System 1 - Oxidizer
System 2 -Fuel
System 2- Oxidizer
Deliverable - Fuel
- Oxidizer
Total Deliverable
WEIGHT
POUNDS
44.2:0.9
78.3*1.6
44.2*0.9
78.3tl.6
88.4'1.3
156.6:2.3
245.0:2.6
6.9
1i.7
6.4
11.4
13.3
23.1
36.4
37.3*0.9
66.6'1.6
37.8*0.9
66.9*1,6
75._1.3
133.5'2.3
20B.6t2.6
(1)CENTER OF GRAVITY
INCHES
XA YA ZA
1022.6 -38.7 52.8
1022.6 26.6 59.8
1022.6 -52.8 38,7
1022.6 2.3 65.5
1022,6 -45.8 45,8
1022.6 14,5 62.7
1022.6 -7.3 57.0
1022.6 -38.7 52,8
1022.6 26.6 59.8
1022.6 -52.8 38.7
1022.6 2.3 65,5
1022.6 -45.5 40.0
1022.6 14.b 62.6
1022.6 -7.3 56.5
I022.b -38.7 52.8
1022,6 26.6 59.8
1022.6 -52.8 38.7
1022.6 2.3 65.5
1022.6 -45.8 45.7
1022.0 14.4 62.7
1022.6 -7.3 56.5
!
4.2-I SNA-8-D-027 (III)REV 2
Tab]t 4.2-1(Contlnued)
SERVICE MODULE -Nominal Load
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. Trapped--Quad A -Primary Fuel
- Secondary Fuel
-Oxidizer
Quad B-Primary Fuel
- Secondary Fuel
-Oxidizer
Quad C -Primary Fuel
-Secondary Fuel
-Oxidizer
Quad D -Primary Fuel
Secondary Fuel
-Oxidizer
Trapped Primary Fuel
Secondary Fuel
Oxidizl, r
Fuel
Oxidizer
Trapped
TOTAL TRAPPED (P_XI_H)
Amendment 66
9/12/69
(l)Center of Gravity
Weilht Inches
Pounds XA y_ ZA
69.9±0.8 964.8 8.0 -68.5
40.3±0.8 985.1 -7.0 -69.0
225.4_3.4 926.9 8.0 -68.5
69.9±0.R 964.8 64.5 -26.5
40.3*0.8 985.1 68.0 -ll.O
225.4±3.4 926.9 64.5 -26.5
69.9±0,8 964.8 -8.0 68.5
40.3_0.8 985.1 7.0 69.0
225.4t3.4 926.9 -8.0 68.5
69.9*0.8 964.8 -64.5 26.5
40.3*0.8 985.1 -68.0 Ii.0
225.4.3.4 926.9 -64.5 26.5
279.6_1.6 964.8 0.0 0.o
161.2'1.6 985.1 0.0 0.0
901:6±6.8 926.9 0.0 0.0
440.8_2.3 972.9 0.0 0.0
901.6_6.8 926.9 0.0 0.0
L342.4_7.2 942.1 0.0 0.0
4.2-2
1.4
0.7
4.5
1.4
0.7
4.5
1.4
0.7
4.5
1.4
0.7
4.5
5.6
2.8
18.0
8.4
18.0
26.4
964.8 8.0 -68.5
985.1 -7.0 -69.0
926.9 8.0 -68.5
964.8 64.5 -26.5
985.1 68.0 -ii.0
926.9 64.5 -26.5
964.8 -8.0 68.5
985.1 7.0 h9.0
926.9 -8.0 08.5
964.8 -04.5 26.5
985.1 -68,0 II.0
920.9 -64.5 26.5
964.8 0.0 0.0
985.1 0.0 o.o
92(_.9 0.0 0.0
971.0 0,0 o.o
916,9 0.o o.o
940.9 0.0 0.0
SNA-8-D-027 (III) REV 2
IJ L: KL K LL K LLT = _, ' L.
U
O_
k
C3
|
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t_
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0
c
0
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q-
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IX
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q- t',,4
Z _
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....... °.o°°°o.o,.,,°o,,°°.o°.,°°o°,
°.°,o°.,o.°,lO.,o°oo°o°°,.o°.o°,oo°.
,..°o.°,°°.,,°°.oo°o ..... oo.
o°...,.°,°°o,,o°°,o°°o,,o..°o,o.°.._
oo°.oo.,.o.o,...°,,,.,...°..o.o. ....
•..... ,.o,o.°°.o°,.,.°.0,°,,o,_,'°'°
,..,°,,°.o,°.,,°°..,.o.,. ...... •....
NNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNN
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11 !1 E E L. 1: L- L L I: L E_ |; I_ E L L
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lr_ _ _ _ I"" 'lr" l'w T_ 1_"I1 14_1 _ !
_- ,-- ,:- • • v- .- I: !b"
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4.3 CM/RCS AND SM/RCS LOAD CALCULATION TABLES AND LOADING WINDOWS
4.3. i CM/RCS
Table 4.3-1 is the CM/RCS load calculation table to be completed
by KSC for each mission. Figures 4.3-4 and 4.3-5 are the CM/RCS
fuel and oxidizer loading windows to be used by KSC for Mission
F and subsequent.
4.3.2 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 4.3-6 are the load
calculation tables to be used by KSC to transmit to MSC the PV
parameters and calculations for each quad. All of these tables
are mission independent. Figures 4.3-1 through 4.3-3 are the
SM/RCS loading windows to be used by KSC for Mission F and sub-
sequent.
4.3.3 CSM/RCS Mass Calculations for Horizontal Tanks
The primary method for determining the amount of RCS propellant
loaded in the CSM horizontal tanks is by actual propellant weight
as determined by using the bleed unit scales. The weight as
determined by the bleed unit scales is verified by PV calculation
as outlined in Tables 4.3-1, and 4.3-3 through 4.3-6. If for
an individual tank the propellant weight as determined by the
bleed unit scales and the propellant weight as determined by the
PV calculation do not correlate, then KSC, ASPO, and the appro-
priate sub-system manager will Jointly determine which of the
above methods will be used.
4.3-1 SNA-8-D-027(III)REV 2
TABLE 4.3-1
COMMAND MODULE RCS LOADING REQUIREMENTS,
PARAMETERS AND CALCULATIONS
A. Tank Volume @ 0.0 PSIG (in 3)
AI. Liquid Line Volume (in 3)
A2. Total A + A1 (in 3)
B. Initial Weight in Bleed Unit Prior
to Loading (Ib)
C. Final Weight in Bleed Unit After
Loading (ib)
D. Propellant Load by Weigh Tank;
Item B less Item C (ib)
E. Loading Temperature (°F)
F. Specification Load @ 70 Z5°F (Ib)
G. Total CM/RCS Propellant Load from
Item D above or Item P below (ib)
Load Parameters and Calculations
Fuel Oxidizer
Tank A Tank B Tank A Tank B
±0.3 ±0.3
Ullage Calculation
GI. Density (ib/in3); solve the following
equation where T - Temperature in E
above and DF " fuel density; 0 o -
oxidizer density.
OF " 0.0329456 - (0.186979)(I0-4)(T)
Oo - 0.451591(I0-4)(II.8-T)+0.05475906
H. Specification Ullage @ E above; Maximum
Minimum
I. Tank Stretch Factor (in3/PSl)-
J. Volume of GHE-GSE Line (in 3)
K. Volume of S/C GHE Line (in 3)
L. GSE Line Pressure (PSIG)
M. Bladder Pressure (PSIG)
N. Stabilized Equilibrium Pressure (PSIG)
O. Ullage Volume (in3); solve the following
equation by substituting the values
contained in the above indicated steps.
Ullage Volume ffiJ _ - I (N +M+14.7) - K
P. Propellant load by P.V. (ib)
4.3-2 SNA-8-D-O27(III)REV 2
11 li U L 1: E L L L U U L L
TABLE 4.3-2
SERVICE MODULE RCS PROPELLANT LOAD SUMMATION
Actual:
QUAD A
(Pounds)
Secondary Fuel
Primary Fuel
Total +0.7
Total Oxidizer +2.3
Secondary Fuel
Primary Fuel
Total +0.7
QUAD B
(Pounds)
Total Oxidizer +2.3
Secondary Fuel
Primary Fuel
Total +0.7
QUAD C
(Pounds)
Total Oxidizer +2.3
Secondary Fuel
Primary Fuel
Total
Fuel +1.4
QUA/) D
(Pounds)
+0.7
Total Oxidizer
Total SM/RCS Propellant Loaded (ib)
Oxidizer
+2.3
+4.6
4.3-3 SNA-8-D-O27(III)REV 2
TABLE 4.3-3
SERVICE MODULE RCS LOADING PARAMETERS AND CALCULATIONS - QUAD A
Fuel
Sec£ndary Fuel
A. Loading Temperature (°F)
B. Tank Volume (in 3) @ 0.0 PSIG
BI. Liquid Line Volume (in 3)
C. Tank Stretch Factor (in3/PSI) 0.034
D. Initial Weight of Bleed Unit
Prior to Loading (ib)
E. Final Weight of Bleed Unit
After Loading (Ib)
Resulting Load (ib) (Item D less
Item E)
G. Specification Nominal Load
at 70 ±5 ° F (ib)
H. Volume of GHE-GSE Line (in 3)
I. Volume of S/C GHE Line (in 3)
J. GSE Line Pressure (PSIG)
K. Bladder Pressure (PSIG)
L. Stabilized Equilibrium
Pressure (PSIG)
M. Primary Liquid Close-Out
Pressure (PSIG)
N. Specification Ullage @ A Above
Maximum
Minimum
O. Ullage Volume (in3). Solve the
following equation by substituting
the values contained in the indi-
cated steps.
Ullage Volume = H (_)J - L _
(C + S)(L + K + 14.7) + S(M)- I
Primary Fuel
P. Loading Temperature (°F)
Q. Tank Volume (in 3) @ 0.0 PSIG
R. Liquid Line Volume (in 3)
S. Tank Stretch Factor (in3/PSI) 0.0652
*F.
Oxidizer
Secondary Oxidizer
A. Tank Volume (in 3) @ 0.0 PSIG
AI. Liquid Line Volume (in 3)
B. Tank Stretch Factor (in3/PSI)
Primary Oxidizer
C. Tank Volume (in 3) @ 0.0 PSIG
CI. Liquid Line Volume (in 3)
D. Tank Stretch Factor (in3/PSI)
0.045
0.088
PV Parameters for Combined
Primary and Secondary Oxidizer Tanks
E. Volume of GHE-GSE Line (in 3)
F. Volume of S/C GHE Line (in 3)
G. GSE Line Pressure (PSIG)
H. Bladder Pressure (PSIG)
I. Stabilized Equilibrium
Pressure (PSIG)
J. Loading Temperature (°F)
K. Oxidizer Density (ib/in3); solve
equation (4) below where T = Tempera-
ture @ J above
L. Specification Value @ Temperature J
above (ib) Maximum
Mimimum
M. PV Calculated Oxidizer Load (ib); solve
equation (5) and (6) below by sub-
stituting the values contained in the
above indicated steps where U =
Volume of tank gas (in 3) in both tanks
and He system, and F o = PV calculated
oxidizer load for both tanks
±2.3
N. Specification Nominal Value @ Tempera-
ture J above (ib)
(4) Oxidizer Density = 0.451591(10 -4 )
(11.8 - T) + 0.05475906
(5) U = E _ - (B+D)(I+H+I4.7)
(6) F o = K(A + C + A1 + C1 - U + F)
4.3-4 SNA-8-D-027 (I II) REV 2
L
*Z4.
TABLE 4.3-3 (Continued)
SERVICE MODULE RCS LOADING PARAMETERS AND CALCULATIONS - QUAD A
T. Fuel Density (ib/in3); solve
equation (i) below where T =
Temperature @ P above
PV Parameters for Combined
Primary and Secondary Fuel Tanks
U. Volume of GHE-GSE Line (in 3)
V. Volume of S/C GHE Line (in 3)
W. GSE Line Pressure (PSIG)
X. Bladder Pressure (PSIG)
Y. Stabilized Equilibrium
Pressure (PSIG)
Z. Specification PV Value @
Temperature P above (ib)
Maximum
Minimum
Z1. PV calculated fuel load (ib)
Solve equations (2) and (3) below
by substituting the values con-
tained in the above indicated
steps where UV = Volume or tanked
gas (in 3) in the primary tank and
F L = PV calculated fuel load.
Z2. Specification Nominal
value @ temperature H above (Ib)
Z3. Total fuel load (ib) ±0.7
(Item F plus Item ZI)
(i) Fuel density = 0.0329456 -
(0.186979)(i0-4)(T)
(w-Y)
(2) UV = U\y _ X - (C + S) (Y + X + 14.7)
F
k(3) FL = T (Q + R - U V + V + B + BI - T )
Secondary Fuel
Load by P.V. (ib)
* If secondary fuel load is determined by P.V. calculation, then in Equation Three
(3), substitute item Z4 for item F.
\
4.3-5 SNA-8-D-O27(III)REV 2
TABLE4.3-4
SERVICEMODULERCSLOADINGP_TERS ANDCALCULATIONS- QUADB
_F.
Fuel
Secondary Fuel
A. Loading Temperature (°F)
B. Tank Volume (in 3) @ 0.0 PSIG
BI. Liquid Line Volume (in 3)
C. Tank Stretch Factor (in3/PSl) 0.034
D. Initial Weight of Bleed Unit
Prior to Loading (Ib)
E. Final Weight of Bleed Unit
After Loading (Ib)
Resulting Load (ib) (Item D less
Item E)
G. Specification Nominal Load
at 70 ±5 °F (ib)
H. Volume of GHE-GSE Line (in 3)
I. Volume of S/C GHE Line (in 3)
J. GSE Line Pressure (PSIG)
K. Bladder Pressure (PSIG)
L. Stabilized Equilibrium
Pressure (PSIG)
M. Primary Liquid Close-Out
Pressure (PSIG)
N. Specification Ullage @ A Above
Maximum
Minimum
O. Ullage Volume (in3). Solve the
following equation by substituting
the values contained in the indi-
cated steps.
Ullage Volume = H (_-Z--K)J- L _
(C + s)(e + K + 14.7) + S(M)- I
Primary Fuel
P. Loading Temperature (°F)
Q. Tank Volume (in 3) @ 0.0 PSIG
•
R. Liquid Line Volume (in)
S. Tank Stretch Factor (in3/PSI) 0.0652
Oxidizer
Secondary Oxidizer
A. Tank Volume (in 3) @ 0.0 PSIG
AI. Liquid Line Volume (in 3)
B. Tank Stretch Factor (in3/PSl)
Primary Oxidizer
C. Tank Volume (in 3) @ 0.0 PSIG
CI. Liquid Line Volume (in 3)
D. Tank Stretch Factor (in3/PSl)
0.045
0.088
PV Parameters for Combined
Primary and Secondary Oxidizer Tanks
E. Volume of GHE-GSE Line (in 3)
F. Volume of S/C GHE Line (in 3)
G. GSE Line Pressure (PSIG)
H. Bladder Pressure (PSIG)
I. Stabilized Equilibrium
Pressure (PSIG)
J. Loading Temperature (°F)
K. Oxidizer Density (ib/in3); solve
equation (4) below where T = Tempera-
ture @ J above
L. Specification Value @ Temperature J
above (Ib) Maximum
Minimum
M. PV Calculated Oxidizer Load (Ib); solve
equation (5) and (6) below by sub-
stituting the values contained in the
above indicated steps where U =
Volume of tank gas (in 3) in both tanks
and He system, and Fo -- PV calculated
oxidizer load for both tanks
-+2.3
N. Specification Nor_inal Value @ Tempera-
ture J above (ib)
(4) Oxidizer Density = 0.451591(10 -4 )
(11.8 - T) + 0.05475906
(5) U = E _ - (B+D)(I+I{+I4.7)
(6) Fo = K(A + C + AI + CI - U + F)
4.3-6 SNA-8-D-027 (III) REV 2
H E L L
TABLE 4.3-4 (Continued)
SERVICE MODULE RCS LOADING PARAMETERS _qD CALCULATIONS - QUAD B
T. Fuel Density (ib/in3); solve
equation (i) below where T =
Temperature @ P above
PV Parameters for Combined
Primarv and Second____ary Fue] Tanks
U. Volume of GHE-GSE Line (in 3)
V. Volume of S/C GHE Line (in 3)
W. GSE Line Pressure (PSIG)
X. Bladder Pressure (PSIG)
Y. Stabilized Equilibrium
Pressure (PSIG)
Z. Specification PV Value @
Temperature P above (ib)
Maximum
Minimum
ZI. PV calculated fuel load (ib)
Solve equations (2) and (3) below
by substituting the values con-
tained in the above indicated
steps where U V = Volume or tanked
gas (in 3) in the primary tank and
F L = PV calculated fuel load.
Z2. Specification Nominal
value @ temperature H above (ib)
Z3. Total fuel load (Ib) ±0.7
(Item F plus Item ZI)
(i) Fuel density = 0.0329456 - ,
(0.186979)(I0-4)(T)
(w-y)
(2) Uv = U \y _ X - (C + S) (Y + X + 14.7)
F
*(3) Fe = T (Q + R - U v + V + B + B1 - ¥ )
*Z4. Secondary Fuel
Load by P.V. (ib)
*If secondary fuel load is determined by P.V. calculation, then in Equation Three
(3), substitute item Z4 for item F.
4.3-7 SNA-8-D-027(III)REV 2
TABLE4.3-5
SERVICEMODULERCSLOADINGPARA_TERSANDCALCULATIONS- QUADC
Fuel
Secondary Fuel
A. Loading Temperature (°F)
B. Tank Volume (in 3) @ 0.0 PSIG
BI. Liquid Line Volume (in 3)
C. Tank Stretch Factor (in3/PSl) 0.034
D. Initial Weight of Bleed Unit
Prior to Loading (ib)
E. Final Weight of Bleed Unit
After Loading (ib)
Resulting Load (ib) (Item D less
Item E)
i
G. Specification Nominal Load
at 70 ±5 ° F (Ib)
H. Volume of GHE-GSE Line (in 3)
I. Volume of S/C GHE Line (in 3)
J. GSE Line Pressure (PSIG)
K. Bladder Pressure (PSIG)
L. Stabilized Equilibrium
Pressure (PSIG)
M. Primary Liquid Close-Out
Pressure (PSIG)
N. Specification Ullage @ A Above
Maximum
Minimum
O. Ullage Volume (in3). Solve the
following equation by substituting
the values contained in the indi-
cated steps.
Ullage Volume = H _ -
(C + S)(L + K + 14.7) + S(M)- I
Primary Fuel
P. Loading Temperature (°F)
Q. Tank Volume (in 3) @ 0.0 PSIG
R. Liquid Line Volume (in 3)
S. Tank Stretch Factor (in3/PSl) 0.0652
*F.
Oxidizer
Secondary Oxidizer
A. Tank Volume (in 3) @ 0.0 PSIG
AI. Liquid Line Volume (in 3)
B. Tank Stretch Factor (in3/PSl)
Primary Oxidizer
C. Tank Volume (in 3) @ 0.0 PSIG
CI. Liquid Line Volume (in 3)
D. Tank Stretch Factor (in3/PSI)
0.045
0.088
PV Parameters for Combined
Primary and Secondary Oxidizer Tanks
E. VOlume of GHE-GSE Line (in 3)
F. Volume of S/C GHE Line (in 3)
G. GSE Line Pressure (PSIG)
H. Bladder Pressure (PSIG)
I. Stabilized Equilibrium
Pressure (PSIG)
J. Loading Temperature (°F)
K. Oxidizer Density (ib/in3); solve
equation (4) below where T = Tempera-
ture @ J above
L. Specification Value @ Temperature J
above (ib) Maximum
Minimum
M. PV Calculated Oxidizer Load (ib); solve
equation (5) and (6) below by sub-
stituting the values contained in the
above indicated steps where U =
Volume of tank gas (in 3) in both tanks
and He system, and Fo = PV calculated
oxidizer load for both tanks
±2.3
N. Specification Nominal Value @ Tempera-
ture J above (ib)
(4) Oxidizer Density = 0.451591(10 -4 )
(11.8 - T) + 0.05475906
(5) U = E _ - (B+D)(I+H+I4.7)
(6) Fo = K(A + C + AI + C1 - U + F)
4.3-8 SNA-8-D-027 (III) REV 2
11 11 L E E E L E E E L EEELLL
TALBE4.3-5 (Continued)
SERVICEMODULERCSLOADINGPARA>_TERSANDCALCULATIONS- QUADC
T. Fuel Density (Ib/in3); solve
equation (i) below whereT =
Temperature@P above
PVParameters for Combined
Primar_ and Secondary, Fuel Tanks
U. Volume of GHE-GSE Line (in 3)
V. Volume of S/C GHE Line (in 3)
W. GSE Line Pressure (PSIG)
X. Bladder Pressure (PSIG)
Y. Stabilized Equilibrium
Pressure (PSIG)
Z. Specification PV Value @
Temperature P above (ib)
Maximum
Minimum
ZI. PV calculated fuel load (Ib)
Solve equations (2) and (3) below
by substituting the values con-
tained in the above indicated
steps where UV = Volume or tanked
gas (in 3) in the primary tank and
F L = PV calculated fuel load.
Z2. Specification Nominal
value @ temperature H above (ib)
Z3. Total fuel load (Ib) ±0.7
(Item F plus Item ZI)
(i) Fuel density = 0.0329456 - .
(0.186979) (10 -4 ) (T)
(2) uv = u _ - (c + s) (Y + x + 14.7)
F
*(3) FL = T (Q + R - U V + V + B + BI - _ )
*Z4. Secondary Fuel
Load by P.V. (ib)
*If secondary fuel load is determined by P.V. calculation, then in Equation Three
(3), substitute item Z4 for item F.
4.3-9 SNA-8-D-O27(III)REV 2
TABLE4.3- 6
SERVICE MODULE RCS LOADING PARAMETERS AND CALCULATIONS - QUAD D
Fuel
Secondary Fuel
A. Loading Temperature (°F)
B. Tank Volume (in 3) @ 0.0 PSIG
BI. Liquid Line Volume (in 3)
C. Tank Stretch Factor (in3/PSl) 0.034
D. Initial Weight of Bleed Unit
Prior to Loading (ib)
E. Final Weight of Bleed Unit
After Loading (ib)
Resulting Load (ib) (Item D less
Item E)
i
G. Specification Nominal Load
at 70 ±5 ° F (Ib)
Volume of GHE-GSE Line (in 3)
Volume of S/C GHE Line (in 3)
GSE Line Pressure (PSIG)
Bladder Pressure (PSIG)
Stabilized Equilibrium
Pressure (PSIG)
Primary Liquid Close-Out
Pressure (PSIG)
Specification Ullage @ A Above
Maximum
Minimum
Ullage Volume (in3). Solve the
following equation by substituting
the values contained in the indi-
cated steps.
Ullage Volume = H (L---2---K)-J- L
(C + S)(L + K + 14.7) + S(M)- I
Primary Fuel
Loading Temperature (°F)
Tank Volume (in 3) @ 0.0 PSIG
Liquid Line Volume (in 3)
Tank Stretch Factor (in3/PSl) 0.0652
*F.
H,
I.
J.
K.
L.
M.
N.
Oo
Pe
Q.
R.
S.
Oxidizer
Secondary Oxidizer
A. Tank Volume (in 3) @ 0.0 PSIG
AI. Liquid Line Volume (in 3)
B. Tank Stretch Factor (in3/PSl)
Primary Oxidizer
C. Tank Volume (in 3) @ 0.0 PSIG
CI. Liquid Line Volume (in 3)
D. Tank Stretch Factor (in3/PSI)
0.045
0.088
PV Parameters for Combined
Primary and Secondary Oxidizer Tanks
E. Volume of GHE-GSE Line (in 3)
F. Volume of S/C GHE Line (in 3)
G. GSE Line Pressure (PSIG)
H. Bladder Pressure (PSIG)
I. Stabilized Equilibrium
Pressure (PSIG)
J. Loading Temperature (°F)
K. Oxidizer Density (ib/in3); solve
equation (4) below where T = Tempera-
ture @ J above
L. Specification Value @ Temperature J
above (ib) Maximum
Minimum
M. PV Calculated Oxidizer Load (ib); solve
equation (5) and (6) below by sub-
stituting the values contained in the
above indicated steps where U =
Volume of tank gas (in 3) in both tanks
and He system, and F o = PV calculated
oxidizer load for both tanks
±2.3
N. Specification Nominal Value @ Tempera-
ture J above (ib)
(4) Oxidizer Density = 0.451591(10 -4 )
(11.8 - T) + 0.05475906
(5) U = E _ - (B+D)(I+H+I4.7)
(6) Fo = K(A + C + AI + C1 - U + F)
4.3-10 SNA-8-D-027 (III)REV 2
HEhLL i_
TABLE 4.3-6 (Continued)
SERVICE MODULE RCS LOADING PARAMETERS AND CALCULATIONS - QUAD D
T. Fuel Density (Ib/in3); solve
equation (i) below where T -
Temperature @ P above
FV Parameters for Combined
Primary and Secondary Fuel Tanks
U. Volume of GHE-GSE Line (in 3)
V. Volume of S/C GHE Line (in 3)
W. GSE Line Pressure (PSIG)
X. Bladder Pressure (PSIG)
Y. Stabilized Equilibrium
Pressure (PSIG)
Z. Specification PV Value @
Temperature P above (Ib)
Maximum
Minimum
ZI. PV calculated fuel load (ib)
Solve equations (2) and (3) below
by substituting the values con-
tained in the above indicated
steps where U V =Volume or tanked
gas (in 3) in the primary tank and
FL = PV calculated fuel load.
Z2. Specification Nominal
value @ temperature H above (lb)
Z3. Total fuel load (ib) ±0.7
(Item F plus Item ZI)
(i) Fuel density = 0.0329456 - •
(0.186979)(I0-4)(T)
(2) U V = U _ - (C + S) (Y + X + 14.7)
F
_3) FL =T (O + R - Uv + V + B + B1 - ¥ )
Secondary Fuel
Load by P.V. (ib)
*Z4.
*If secondary fuel load is determined by P.V. calculation, then in
Equation Three (3), substitute item Z4 for item F.
4.3-11 SNA-8-D-027 (III)REV 2
L
cO
Z
v
,-I
.<
240
230
220
210
200
190
180
170
160
65 67 69
TEMPERATURE (_F)
Figure 4.3-1 CSM 104 AND SUBSEQUENT SECONDARY
FUEL TANK ULLAGE VOLUME RANGE
4.3-12 SNA-8-D-O27(III)REV 2
!1 1_ E L E L L L 1: E Ei_.. _L
Z
O
121
,-1
73
72
7i
7O
69
68
67
66
65
!!! iiii _'_
t:: ii_i :I_!
',_ _ iiii _.
.... +_I ""
_ ._71,5 iii
t_-_: .._I! '.il "
14..'41.I:;
•, H;H,;:r li. ili
::: :::1....... !i_
_._::_ I I ,I
;',_ _;'I ..... ;11 Hi-
: :_.i..,_i !ii $i
.. :.:;'._.*:I !!_ ""
_'!:H'! :i:
68.7 :i.
•,,..,, .,: iii
'r_l _._'_ _ -4.
"T!...._:'I
::: ii:j !iij ii:_i:
; .... ! ....
:: .... Lli
iii_':,'-_-::_ ......
'T-i 7I "':1 ::_
:; i!!: :Z!
:_ :L!-:!] :ii, i'T
::T
:_ ........ !ii
64 65 66 67 73
FUEL TEMPERATURE (OF)
Figure 4.3-2 SM RCS PRIMARY FUEL TANK LOAD WINDOW
4.3-13 SNA-8-D-027 (llI) REV 2
f-%
C_
Z
0
L_
)--4
t,q
)-4
).-4
0
231
230
229
228
227
226
225
224
223
_L
J.
II
4_
4_
n
::U
222
221 :_
64
_u+t:
rttt
!_4".', i]!
22).
_N
_'3
:2..
F::" 7-i
65 66 67 68 69 70 71 72 73
OXIDIZER TEMPERATURE (°F)
74 75 76
Figure 4.3-3
SM RCS COMBINED PRIMARY-SECONDARY
OXIDIZER TANK LOAD WINDOW
4.3-14 SNA-8-D-027(III)REV 2
I1 [l L; E l_ 12 L L E L: ]J :E E1_ H E ;a L_ L
Z
I,-4
v
,-.1
,-.1
,-I
t_
150 E
140 F
130 :l
fl
T-
_P
::I
120 :_
llO _"_
4:
100 4:
90 :;_
80 ---
7o
j-
6o _
5o !!
_t
_t
40 :_
64
HH_4
::::::
!i!!}!!!_
[::[::i::
12:Li;_i
H__t_
_ +.++++-1-4
ii_iiii
4I*It_*I
oUI:_
i !!'!!
:Aiii _i
4-14d-; +l_-
_!'ttT!t
_÷
?i *l_'?t_r
_J [!"!+
,_4/,r_!!T
'r _7_TF
4 L_If
?Ttti_rl-t
i!!!!!ii
66
FUEL LOAD:
MINIMUM
68 70 72
FUEL TEMPERATURE (°F)
Figure 4.3-4
CSM 104 AND SUBSEQUENT CM RCS
FUEL TANK ULLAGE VS TEMPERATURE
4.3-15 SNA-8-D-O27(III)REV 2
I-%
mD
Z
360
350
340
330
"" -320
310
m_
c_
o
300
290
280
270
260
250
240
230
64 66 68 70 72 74
OXIDIZER TEMPERATURE (OF)
76
Figure 4.3-5
CSM 104 AND SUBSEQUENT CM RCS
OXIDIZER TANK ULLAGE VS TEMPERATURE
4.3-16 SNA-8-D-027(III)REV 2
L
Amendment 105
6118171
TABLE 4.3-7
COMMAND MODULE 112 RCS TANK VOLUMES
System 1
Fuel
Oxidizer
System 2
Fuel
Oxidizer
Internal
Serial Gross Tank Equipment Net Tank
Number Volume I In 3 Volume_ in 3 Volume_ in 3
100311537100 1490.003 15.3 1474.703
100311545114 1804.744 17.8 1786.944
100311537101 1486.982 15.3 1471.682
100311545103 1808.798 17.8 1790.998
4.3-17 SNA-8-D-O27(III)REV 3
Amendment105
6/18/71
S._s t_m
Quad A
Primary Oxidizer
Secondary Oxidizer
Primary Fuel_
Secondary Fuel
TABLE 4.3-8
SERVICE MODULE 112 RCS TANK VOLUMES
Internal
Serial Gross Tank Equipment
Number Volume, in 3 Volume_ in 3
100311521168 2862.193 19.1
100311545116 1802.557 17.8
100311511167 2266.943 17.4
100311537099 1476.143 15.3
Net Tank
Volume_ in 3
2843.093
1784.757
2249.543
1460.843
Quad B
Primary Oxidizer
Secondary Oxidizer
Primary Fuel
Secondary Fuel
Quad C
Primary Oxidizer
Sec,,ndary f_xidizer
Primary Fuel
Secondary Fuel
Quad 11
Primary Oxidizer
Secondary Oxidizer
Primary Fuel
Secondary Fuel
100311521333 2861.264 19.1
100311545110 !802.556 17.8
100311511326 2259.267 17.4
100311537108 1482.432 15.3
100311521175 2866.460 19.1
100311545112 1805.330 17.8
100311511172 2272.138 17.4
100311537106 1491.598 15.3
100311521326 2862.193 19.1
100311545117 1803.507 17.8
1003115113]0 2270.980 17.4
100311537103 1489.144 15.3
2842.164
1784.756
2241.867
1467.132
2847.360
1787.530
2254.738
1476.298
2843.093
1785.707
2253.580
1473.844
4.3-18 SNA-B-D-027 (III)K}_v 3
U_LLLLLL L L L_ L L; ii _ I_ Li L. L_ [
Amendment 105
6/18/71
TABLE 4.3-9
COMMAND MODULE 113 RCS TANK VOLUMES
Sys tern i
Fuel
Oxidizer
Internal
Serial Gross Tank Equipment Net Tank
Number Volume_ in 3 Volume_ in 3 Volume_ in 3
100311537115 1488.714 15.3 1473.414
100311545115 1801.865 17.8 1784.065
System 2
Fuel 100311537116 1484.806 15.3 1469.506
Oxidizer 100311545118 1808.795 17.8 1790.995
4.3-19 SNA-8-D-027(III)REV 3
Amendment105
6/18/71
TABLE4.3-10
SERVICEMODULE113 RCSTANKVOLUMES
System
Quad A
Primary Oxidizer
Secondary Oxidizer
Primary Fuel
Secondary Fuel
Quad B
Primary Oxidizer
Secondary Oxidizer
Primary Fuel
Secondary Fuel
Quad C
Primary Oxidizer
Secondary Oxidizer
Primary Fuel
Secondary Fuel
Quad D
Primary Oxidizer
Secondary Oxidizer
Primary Fuel
Secondary Fuel
Internal
Serial Gross Tank Equipment Net Tank 3
Number Volume_ in 3 Volume_ in 3 Volume t in
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 17.4 2254.738
100311537105 1488.499 15.3 1473.199
100311521331 2861.677 19.1 2842.577
100311545100 1784.861 17.8 1767.061
100311511333 2269.657 17.4 2252.257
100311537102 1490.003 15.3 1474.703
4.3-20 SNA-8-D-027 (III) REV 3
Amendment105
6/18/71
TABLE 4.3-11
COMMAND MODULE 114 RCS TANK VOLUMES
S_vstem
System i
Fuel
Oxidizer
Internal
Serial Gross Tank Equipment
Number Volume_ in3 Vo!ume I in 3
100311537122 1503.864 15.3
100311545134 1801.085 17.8
Net Tank
Volume, In 3
1488.564
1783.285
System 2
Fuel
Oxidizer
100311537114 1461.808 15.3
100311545111 1799.807 17.8
1446.508
1782.007
4.3-21 SNA-8-D-027(III)REV 3
U___LLL_ L LUUdULJ,.
Amendment 105
6/18/71
TABLE 4.3-12
SERVICE MODULE 114 RCS TANK VOLUMES
S_.ystem
Quad A
Primary Oxidizer
Secondary Oxidizer
Primary Fuel
Secondary Fuel
Quad B
Primary Oxidizer
Secondary Oxidizer
Primary Fuel
Secondary Fuel
Quad C
Primary Oxidizer
Secondary Oxidizer
Primary Fuel
Secondary Fuel
Quad D
Primary Oxidizer
Secondary Oxidizer
Primary Fuel
Secondary Fuel
Internal
Serial Gross Tank Equipment
Number Volume_ in 3 Volume_ in 3
100311521172 2862.193 19.1
100311545104 1821.604 17.8
100311511173 2266.191 17.4
100311537128 1491.598 15.3
100311521330 2862.193 19.1
100311545119 1800.132 17.8
100311511328 2269.657 17.4
100311537107 1490.791 15.3
100311521173 2863.177 19.1
100311545127 1821.604 17.8
100311511175 2271.810 17.4
100311537112 1476.143 15.3
100311521332 2848.458 19.1
100311545123 1807.229 17.8
100311511331 2265.783 17.4
100311537109 1482.806 15.3
Net Tank
Volume_ in 3
2843.093
1803.804
2248.791
1476.298
2843.093
1782.332
2252.257
1475.491
2844.077
1803.804
2254.410
1460.843
2829.358
1789.429
2248.383
1467.506
4.3-22 SNA-8-D-O27(III)RF
NASA -- _.
II !1 I_ 1.' h Ii L L L1_ L _ gli LL. L
m
ql
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]_ -r_ I,_ _ I_ I[ I,rI_' I( i_ i_ i_ !
o
.L
v'
1,_ L
I
TO BE SUPPLIED.
CM ABLATOR DATA
L
4.4-1 SNA-8-D-O27(III)REV 2
II II I II
_y'0
0
v__lrT 1
t.[ _I.[ ll_. I[ I[ !( i _. 1[ I_ 1
.L .I,,,. X,.,, .L ,L I. 1,_ L Z_ h L A. Z..
ILl !1 _ I.: L: E L L L L{ I,,." E _ 1; E E LL ,__ ;_
I II I II
tl
i,_,k_ A A AA dekd,,kmdi
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Amendment 86_
9/lO/7O
5.0 LM REFERENCE CONSUMABLES MASS PROPERTIES DATA
The data presented in this section will enable the user to obtain the
separate centers-of gravity and moments-of-lnertla for those LM space-
craft consumables that slgnlficantly affect overall LMperformance. LM
consumables mass property data must be compared to the current on-board
The
cons_ble loading data for each mission provided in Section 3.0.
mass property data are presented in the following sections:
5.1 LM Descent Tank Mass Properties
Table 5.1-1 LM 5through LM 9 Fuel Mass Properties
Table 5.1-2 LM 5 throuEh LM 9 Oxidizer Mass Properties
Table 5.1-3 LM i0 and Subsequent DPS Fuel Mass Properties
Table 5.1-4 LM i0 and Subsequent DPS Oxidizer Mass Properties
5.2 LM Ascent Tank Mass Properties
5.3 LM RCS Tank Mass Properties
5.4 LM Descent Water Tank Mass Properties
Table 5.4-1 LM 8 Descent Water Tank Mass Properties
Table 5.4-2 I14 i0 and Subsequent Descent Water Tank Mass Properties
5.5 LM Ascent Water Tank Mass Properties
5.6 LM Trapped and Residual Propellants, and
Miscellaneous Consumables
I
5-1 SNA-8-D-027(III)REV 2
t
!1 !1 LI L E L L I: L ]_ L: L: Li Ii E L.
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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.
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Amendment 88
lo1517o
This page intentionally left blank
5. i-i0 SNA-8-D-O27(III)REV 2
!1 !1 IG E I; E LLLE I_ E L: ILL_
Amendment 88
10/5/70
This page intentionally left blank
5 .i-ii SNA-8-D-027(III)REV 2
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Amendment 86
9/10/70
TABLE 5.2-1
APS TANKED FUEL MASS PROPERTIES
The following mass properties are to be used over the entire
range of tanked fuel quantity:
Xcg
Ycg
Zcg
Ixx
IYY
IZz
Ixy
Ixz
Iyz
- 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
-0slug-feet 2
-0slug-feet 2
5.2-1 St_-8-D--027(ZZZ)REV 2
tl lI E E L E IL L I." L_ 12 IL L.' 1; EIL L, L L_ _L
Amendment 86
9/10/70
TABLE 5.2-2
APS TANKED OXIDIZER MASS PROPERTIES
The following mass properties are to be used over the entire range
of tanked oxidizer quantity:
X " 228.0 inches
cg
Ycg "44.5 inches
Zcg -0.0 inches
Ixx "0 slug-feet 2
lyy "0slug-feet 2
I"0 slug-feet 2
zz
Ixy "0slug-feet 2
I"0slug-feet 2
xz
ly z -0slug-feet 2
5.2-2 SNA-8-D-027(III)REV
_EELLELEEEEE E I_ E L L t
L
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LM ASCENT FUEL MASS PROPERTIES-70°F-I TANK
Y-CG = -71.3 (CONST) Z-CG = 0.0 (CONST)
RADIUS= 24.700 CYLINDRICAL SECTION= -0.0 WEIGHT=
DENSITY= 56.330 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ)
1995.6
IYY or
1566.5 223.4 4.4 3.3
1556.6 223,3 4.3 3.3
1546.6 223,3 3.3 3,2
1536.6 223.2 3.3 3.2
1526.6 223.1 4.2 3.2
1516.7 223,0 4.2 3.1
1506,7 222.9 4.2 3.1
1496.7 222.8 4.2 3.1
1486.7 222.7 4.1 3.0
1476,7 222.7 4.1 3.0
1466,8 222.6 4.1 3.0
1456.8 222.5 4.0 2.9
1446.8 222.4 4.0 2.9
1436.8 222.3 4.0 2.9
1426.9 222,2 3.9 2.8
1416.9 222.1 3.9 2.8
1406.9 222.0 3.9 2.8
1396.9 222.0 3.8 2.8
1386.9 221.9 3.8 2.7
1377.0 221,8 3.8 2.7
1367.0 221.7 3.8 2.7
1357.0 221,6 3.7 2.6
1347.0 221.5 3.7 2.6
1337,1 221.4 3.7 2.6
1327.1 221.4 3.6 2.5
1317.1 221.3 3.6 2,5
1307.1 221.2 3,6 2.5
1297.1 221,1 3,5 2,5
1287.2 221.0 3.5 2.4
1277,2 220.9 3,5 2.4
1267,2 220.8 3.4 2.4
1257.2 220.8 3.4 2.3
1247.2 220.7 3.4 2.3
1237.3 220.6 3,3 2.3
1227.3 220.5 3,3 2.2
1217.3 220.4 3.3 2.2
1207.3 220.3 3,2 2.2
1197.4 220.2 3.2 2.2
1187.4 220.1 3.2 2.1
1177.4 220.1 3.o 2.1
1167.4 220.0 3.1 2.1
1157,4 219.9 3,1 2.1
1147.5 219.8 3.0 2.0
IZZ(S-FT.SQ)
5.2-3 SNA-8-D-O27(III)REV 2
LM ASCENT FUEL MASS PROPERTIES-70°F-I TANK
Y-CG = -71,3 (CONST) Z-CG = 0o0 (CONST)
RADIUS= 24.700 CYLINDRICAL SECTION = -0.0 WEIGHT=
DENSITY = 56.330 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ)
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
.5 219.7 3.0
.5 219.6 3.0
.5 219.5 3.0
.6 219.4 2.9
.6 219.4 2.9
.6 219.3 2.9
.6 219.2 2.8
.6 219.1 2.8
.7 219.0 2.8
.7 218.9 2.7
.7 218,8 2.7
.7 218.7 2.7
.8 218.6 2.6
.8 218.5 2.6
.8 218.5 2.6
.8 218.4 2.5
.8 218.3 2.5
.9 218.2 2.5
.9 218,1 2.4
.9 218,0 2.4
.9 217.9 2.4
.0 217.8 2,3
.0 217.7 2.3
.0 217.6 2.3
.0 217,5 2.2
0 217.4 2.2
1 217.4 2.2
1 217.3 2.1
1 217.2 2,1
1 217.1 2.1
2 217.0 2.0
2 216.9 2.0
2 216.8 2.0
2 216.7 1.9
2 216.6 I .9
3 216.5 1.9
3 216.4 1.8
3 216.3 1.8
3 216.2 1.8
3 216.1 1.7
4 216.0 1.7
4 215.9 1.7
4 215.8 1,7
1995.6
LYY or IZZ(S-FT.SQ)
2.0
2,0
1 9
1 9
1 9
1 9
1 8
1 8
1 8
1 8
1 7
1 7
1 7
1 7
1 6
1 6
1 6
1 6
1 5
1 5
1 5
1 5
I 4
1 4
1 4
1 4
1 3
1 3
1 3
1 3
1 2
1 2
1 2
1 2
I 2
1 1
1 1
1 1
1 1
1 0
1 0
1 0
1 0
5.2-4 SNA-8-D-O27(III)REV 2
ILl 11 L L L E IZ L I: I: E I: 1; E E ,. ,_
LM ASCENT FUEL MASS PROPERTIES-70°F-I TANK
Y-CG =-7].3 (CONST) Z-CG :0.0 (CONST)
RADIUS= 24.700 CYLINDRICAL SECTION= -0.0 WEIGHT=
DENSITY= 56.330 LBS/CU.FT.
]995.6
WEIGHT X-CG IXX(S-FT.SQ) IYY or IZZ(S-FT.SQ)
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
214.1
213.9
213.8
213.7
213.6
213.5
213.4
213.3
213.2
213.0
212.9
212.8
212.7
212.6
212.4
212.3
212.2
212.1
212.0
211.8
211.7
211.6
211.4
211.3
211.2
211.0
210.9
l 6
l 6
l 6
l 5
l 5
l 5
l 4
I 4
l 4
l 3
l 3
] 3
l 3
l 2
l 2
l 2
l l
l l
l l
l.O
l.O
l.O
l.O
0.9
0.9
0.9
0.8
0.8
0.8
0.8
07
07
07
07
06
06
06
06
0.5
0.5
0.5
0.5
0.4
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
1.0
0.9
0.9
0.9
0.9
0.9
0.8
0.8
0.8
0.8
0.8
0.7
0.7
0.7
0.7
0.7
0.6
0.6
0.6
0.6
0.6
0.5
0.5
0.5
0.5
0.4
0.5
0.4
0.4
0.4
0.4
0.4
0.4
0.3
0.3
0.3
0.3
0.3
0.3
0.3
0.2
0.2
0.2
5.2-5 SNA-8-D-O27(III)REV 2
LMASCENTFUELMASSPROPERTIES-70°F-ITANK
Y-CG=-71.3 (CONST) Z-CG = 0.0 (CONST)
RADIUS= 24.700 CYLINDRICAL SECTION =-0.0 WEIGHT= 1995.6
DENSITY= 56.330 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ) IYY or OZZ(S-FT.SQ)
279.4 210.7
269.4 210.6
259.4 210.5
249.4 210.3
239.5 21O.2
229.5 210.0
219.5 209.8
209.5 209.7
199.6 209.5
189.6 209.4
179.6 209.2
169.6 209.0
159.6 208.8
149.7 208.7
139.7 208.5
129.7 208.3
I19.7 208.1
I09.8 207.9
99.8 207.6
89.8 207.4
79.8 207.2
69.8 206.9
59.9 206.6
49.9 206.3
39.9 206.0
29.9 205.6
20.0 205.2
lO.O 204.6
0.4
0.4
0.4
0.3
0.3
0.3
0.3
0.3
02
02
02
02
02
Ol
Ol
Ol
0.1
O.l
Ol
O0
O0
O0
O0
O0
0.0
0.0
0.0
0.0
0.2
0.2
0.2
0.2
0.2
O.l
O.l
O.l
O.l
O.l
O.l
O.l
O.l
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
0.0
5.2-6 SNA-8-D-O27(III)REV 2
ILl li IJ ;L; 1:. 12 L L E L: ]_ E L.' 1_ E E: ' L
LM ASCENT OXIDIZER MASS PROPERTIES-70°F-I
Y-CG = +44.5 (CONST) Z-CG = 0,0 (CONST)
RADIUS= 24.700 CYLINDRICAL SECTION= -0.0
DENSITY= 90.050 LBS/CU.FT.
(ULLAGE/VOL.OF LIQUID))x]O0= 3.672
TANK
WEIGHT= 31 72.9
WEIGHT X-CG IXX(S-FT.SQ) IYY or
3172.9 227.2 8.5
3157,0 227.1 8.5
3141.2 227.0 8.5
3125.3 226,9 8.4
3109.4 226.8 8.4
3093.6 226.7 8,4
3077,7 226.6 8.4
3061.8 226.6 8.3
3046.0 226,5 8.3
3030.1 226,4 8.3
3014.3 226,3 8.2
2998.4 226,2 8.2
2982.6 226.1 8.2
2966.7 226.0 8.2
2950.8 225.9 8.1
2934.9 225.8 8.1
2919,1 225.7 8.1
2903.2 225.6 8.0
2887.3 225.5 8,0
2871.5 225.5 7.9
2855.6 225.4 7.9
2839.7 225.3 7.9
2823.9 225.2 7,8
2808.0 225.1 7.8
2792.2 225.0 7.8
2776.3 224.9 7.7
2760,4 224,8 7.7
2744.6 224.7 7.6
2728.7 224.7 7.6
2712.8 224,6 7.6
2697.0 224.5 7.5
2681.1 224.4 7.5
2665.2 224.3 7,4
2649.4 224,2 7.4
2633.5 224.1 7.3
2617.6 224.0 7.3
2601.8 224.0 7.3
2589.9 223.9 7.2
2570.0 223,8 7,2
2554.2 223.7 7.1
2538,3 223.6 7.1
2522,5 223.5 7.0
2506.6 223.4 7.6
8.0
7.9
7,8
7.8
7.7
7.6
7,5
7,5
7.4
7.3
7.3
7.2
7.1
7.1
7.0
6.9
6.9
6,8
6,7
6.7
6.6
6.5
6.5
6.4
6.4
6.3
6.2
6.2
6.1
6.1
6.0
5.9
5.9
5.8
5.8
5.7
5.7
5.6
5.5
5.5
5.4
5.4
5.3
IZZ(S-FT.SQ)
5.2-7 SNA-8-D-O27(III)REV 2
LMASCENTOXIDIZERMASSPROPERTIES-70°F-l TANK
Y-CG=+44.5 (CONST) Z-CG = 0.0 (CONST)
RADIUS =24.700 CYLINDRICAL SECTION =-0.0 WEIGHT=
DENSITY= 90.050 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ)
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
222.7
222.6
222.5
222.4
222.3
222.2
222.2
222.1
222.0
221.9
221.8
221.7
221.6
221 6
221 5
221 4
221 3
221 2
221 l
221 0
221.0
220.9
220.8
220.7
220.6
220.5
220.4
220.3
220.3
220.2
220.I
220.0
219.9
219.8
219.7
7.0
6.9
6.9
6.8
6.8
6.7
6.7
6.6
6.6
6.5
6.5
6.4
6.4
6.3
6.3
6.2
6.2
6.1
6.1
6.0
6.0
5.9
5.9
5.8
5.8
5.7
5.7
5.6
5.6
5.5
5.5
5.4
5.4
5.3
5.3
5.2
5.2
5.1
5.1
5.0
5.0
4.9
4.9
3172.9
IYY or IZZ(S-FT.SQ)
5.3
5.2
5.2
5.1
5.1
5.0
5.0
4.9
4.9
4.8
4.7
4.7
4.6
4.6
4.5
4.5
4.4
4.4
4.3
4.3
4.3
4.2
4.2
4.1
4.1
4.0
4.0
3.9
3.9
3.8
3.8
3.7
3.7
3.6
3.6
3.6
3.5
3,5
3.4
3.4
3.3
3.3
3.2
5.2-8 SNA-8-D-O27(III)REV 2
L.. 3L-
LM ASCENT OXIDIZER MASS PROPERTIES-70°F-I
Y-CG = +44.5 (CONST) Z-CG = 0.0 (CONST)
RADIUS= 24.700 CYLINDRICAL SECTION= -0.0
DENSITY= 90.050 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ)
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
219.7
219.6
219.5
219.4
219.3
219.2
219.1
219.0
218.9
218.9
218.8
218.7
218 6
218 5
218 4
218 3
218 2
218 l
218 0
218 0
217 9
217 8
217 7
217 6
217.5
217.4
217.3
217.2
217.1
217o0
216.9
216.8
216.7
216.7
216.6
216.5
216.4
216.3
216.2
216.1
216.0
215.9
215.8
4.8
4.8
4.7
4.7
4.6
4.6
4.5
4.5
4.4
4.4
4.3
4.2
4.2
4.1
4,1
4.0
4.0
3.9
3.9
3.8
3.8
3.7
3.7
3.6
3.6
3.5
3.5
3.4
3.4
3.3
3.3
3.2
3.2
3.1
3.1
3.0
3.0
2.9
2.9
2.8
2.8
2.7
2.7
TANK
WEI GHT= 3172.9
IYY or IZZ(S-FT.SQ)
3.2
3.2
3.1
3.1
3.0
3.0
2.9
2.9
2.9
2.8
2.8
2.7
2.7
2.7
2.6
2.6
2.5
2.5
2.5
2.4
2.4
2.3
2.3
2.3
2.2
2.2
2.1
2,1
2.1
2,0
2.0
2.0
1.9
1.9
1.9
1 8
1 8
1 7
1 7
1 7
1 6
1 6
1 6
5.2-9 SNA-8-D-O27(III)REV 2
LM ASCENT OXIDIZER MASS PROPERTIES-70°F-I TANK
Y-CG =+44.5 (CONST) Z-CG = 0.0 (CONST)
RADIUS= 24.700 CYLINDRICAL SECTION= -0.0 WEIGHT= 3172.9
DENSITY= 90.050 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ)
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
214.3
214.2
214.1
214.0
213.9
213.8
2]3.7
213.6
213.5
213.4
213.2
213.1
213.0
212.9
212.8
2]2.7
212.5
212.4
212.3
212.2
212.1
211.9
211.8
211.7
211.5
211.4
211.3
2]I .l
211.0
210.9
2.6
2.6
2.5
2.5
2.4
2.4
2.3
2.3
2.2
2.2
2.1
2.1
2.0
2.0
1.9
].9
1.8
1.8
1.7
1.7
1.6
1.6
1.6
1.5
1.5
1.4
1.4
1 3
l 3
] 2
l 2
I 2
l l
l l
l 0
l 0
l 0
0.9
0.9
0.8
0.8
0.8
0.7
IYY or
1.5
1.5
1.5
1.4
1.4
1.4
1.3
1.3
1.3
1.3
1.2
1.2
1.2
l.l
l.l
l.l
l.O
l.O
l.O
l.O
0.9
0.9
0.9
0.8
0.8
0.8
0.8
0.7
0.7
0.7
0.7
0.6
0.6
0.6
0.6
0.5
0.5
0.5
0.5
0.4
0.4
0.4
0.4
IZZ(S-FT.SQ)
5.2-I0 SNA-8-D-O27(III)REV 2
L- L
LM ASCENT OXIDIZER MASS PROPERTIES-70°F-I TANK
Y-CG = +44.5 (CONST) Z-CG = 0.0 (CONST)
RADIUS= 24.700 CYLINDRICAL SECTION= -0.0 WEIGHT=
DENSITY= 90.050 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ)
444.2 210.7 0.7
428.3 210.6 0.6
412.5 210.4 0.6
396.6 210.3 0.6
380.7 210.1 0.5
364.9 210.0 0.5
349.0 209.8 0.5
333.2 209.7 0.4
317.3 209.5 0.4
301.4 209.3 0.4
285.6 209.2 0.3
269.7 209.0 0.3
253.8 208.8 0.3
238.0 208.6 0.2
222.1 208.4 0.2
206.2 208.3 0.2
190.4 208.0 0.2
174.5 207.8 O.l
156.6 207.6 O.l
142.8 207.4 O.l
126.9 207.1 O.l
lll.l 206.9 0.0
95.2 206.6 0.0
79.3 206.3 0.0
63.5 206.0 0.0
47.6 205.6 0.0
31.7 205.2 0.0
15.9 204.6 0.0
3172.9
IYY or IZZ(S-FT.SQ)
0.4
0.3
0.3
0.3
0.3
0.2
0.2
0.2
0.2
0.2
0.2
O.l
O.l
O.l
O.l
O.l
O.l
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.2-II SNA-8-D-O27(III)REV 2
ILl !1 ]5. L: LLL: L: ]_ Eif
L|; E EI, L.
I
I
L:.
.,..-
_K l
L'_
t_
L'-'
L'_
C_
LUNAR MODULE RCS PROPELLANT
MASS PROPERTIES
NOTE:
I. Mass Properties are given for liquid in individual tanks.
2. Moments of Inertia are about center of gravity of propellant
in individual tanks, coordinates of which are given.
3. Centers of Gravity in Y and Z directions are given at top of
each page.
4. The number of tanks of a particular kind is indicated
by the last number on the first line of each page.
5.3-I SNA-8-D-O27(III)REV 2
LM RCS FUEL MASS PROPERTIES-70°F-2 TANKS
Y-CG = + OR - 44.6 (CONST) Z-CG = + OR - 14.5
RADIUS= 6.250 CYLINDRICAL SECITON= 18.650. WEIGHT=
DENSITY: 56.330 LBS/CU.FT.
(ULLAGE/(VOL.OF LIQUID))xIO0= 4.093
WEIGHT X-CG IXX(S-FT.SQ)
103.7 279.3 0.0
103.2 279.2 0.0
102.7 279.2 0.0
102.1 279.1 0.0
101.6 279.0 0.0
I01.I 279.0 0.0
100.6 278.9 0.0
I00.I 278.8 0.0
99.6 278.8 0.0
99.0 278.7 0.0
98.5 278.7 0.0
98.0 278.6 0.0
97.5 278.5 0.0
97.0 278.5 0.0
96.4 278.4 0.0
95.9 278.3 O.O
95.4 278.3 0.0
94.9 278.2 0.0
94.4 278.1 0.0
93.8 278.1 O.O
93.3 278.0 O.O
92.8 277.9 0.0
92.3 277.9 0.0
91.8 277.8 0.0
91.3 277.7 O.O
90.7 277.7 0.0
90.2 277.6 0.0
89.7 277.5 O. 0
89.2 277.5 O.O
88.7 277.4 0.0
88.1 277.4 0.0
87.6 277.3 0.0
87.1 277.2 0.0
86.6 277.2 0.0
86.1 277.1 0.0
85.6 277.0 0.0
85.0 277.0 0.0
84.5 276.9 0.0
84.0 276.8 0.0
83.5 276.8 0.0
83.0 276.7 0.0
82.4 276.6 0.0
81.9 276.6 0.0
I03.7
IYY or IZZ(S-FT.SQ)
0.4
0.5
0.5
0.5
0.5
0.5
O5
O5
04
04
O3
04
04
04
0.4
0.4
0.4
0.4
0.4
0.4
0.4
0.4
0.4
0.3
0.3
0.3
0.3
0.3
0.3
0.3
0.3
0.3
0.3
0.3
0.3
0.3
0.3
0.2
0.2
0.2
0.2
0.2
0.2
5.3-2 SNA-8-D-O27(III)REV 2
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= 18.650, WEIGHT=
DENSITY: 56.330 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ)
81.4 276.5 0.0
80.9 276.4 0.0
80.4 276.4 0.0
79.8 276.3 0.0
79.3 276.2 0.0
78.8 276.2 0.0
78.3 276.1 0.0
77.8 276.0 0.0
77.3 276.0 0.0
76.7 275.9 0.0
76.2 275.9 0.0
75.7 275.8 0.0
75.2 275.7 0.0
74.7 275.7 0.0
74.1 275.6 0.0
73.6 275.5 0.0
73.1 275.5 0.0
72.6 275.4 0.0
72.1 275.3 0.0
71.6 275.3 0.0
71.0 275.2 0.0
70.5 275.1 0.0
70.0 275.1 0.0
69.5 275.0 0.0
69.0 274.9 0.0
68.4 274.9 0.0
67.9 274.8 0.0
67.4 274.7 0.0
66.9 274.7 0.0
66.4 274.6 0.0
65.8 274.5 0.0
65.3 274.5 0.0
64.8 274.4 0.0
64.3 274.4 0.0
63.8 274.3 0.0
63.3 274.2 0.0
62.7 274.2 0.0
62.2 274.1 0.0
61.7 274.0 0.0
61.2 274.0 0.0
60.7 273.9 0.0
60.1 273.8 0.0
59.6 273.8 0.0
103.7
IYY or IZZ(S-FT.SQ)
0.2
0.2
0.2
0.2
0.2
0.2
0.2
0.2
0.2
0.2
0.2
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.I
0.1
0.I
0.I
0.I
0.I
O.l
0.I
0.I
0.0
0.0_
0.0
0.0
0.0
5.3-3 SNA-8-D-O27(III)REV 2
11 U I_ t; 1.: I_ L E L." U. 1_ ELI L{ li 1_ L LLL
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= 18.650. WEIGHT = I03L7
DENSITY= 56.330 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ) IYY or IZZ(S-FT.SQ)
59.1 273.7 0.0
58.6 273.6 0.0
58.1 273.6 0.0
57.6 273.5 0.0
57.0 273.4 0.0
56.5 273.4 0.0
56.0 273.3 0.0
55.5 273.2 0.0
55.0 273.2 0.0
54.4 273.1 0.0
53.9 273.0 0.0
53.4 273.0 0.0
52.9 272.9 0.0
52.4 272.8 0.0
51.8 272.8 0.0
51.3 272.7 0.0
50.8 272.6 0.0
50.3 272.6 0.0
49.8 272.5 0.0
49.3 272.5 0.0
48.7 272.4 0.0
48.2 272.3 0.0
47.7 272.3 O.O
47.2 272.2 0.0
46.7 272.1 0.0
46.1 272.1 0.0
45.6 272.0 0.0
45.1 271.9 0.0
44.6 271.9 0.0
44.1 271.8 0.0
43.6 271.7 0.0
43.0 271.7 0.0
42.5 271.6 0.0
42.0 271.5 O.O
41.5 271.5 0.0
41.0 271.4 O.O
40.4 271.3 O.O
39.9 271.3 0.0
39.4 271.2 0.0
38.9 271 .l 0.0
38.4 271 .l 0.0
37.9 271 .O O.O
37.3 270.9 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
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
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
0.0
0.0
5.3-4 SNA-8-D-O27(III)REV 2
l/IlL[ 1;111/ L E11 b" E L.' EEL, L LtL
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= 18.560. WEIGHT= 103.7
DENSITY= 56.330 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ) IYY or
36.8 270.9 0.0 0.0
36.3 270.8 0.0 0.0
35.8 270.7 0.0 0.0
35.3 270.7 0.0 0.0
34.7 270.6 0.0 0.0
34.2 270.5 0.0 0.0
33.7 270.5 0.0 G.O
33.2 270.4 0.0 0.0
32.7 270.3 0.0 0.0
32.1 270.3 0.0 0.0
31.6 270.2 0.0 0.0
31 .I 270.1 0.0 (],.0
30.6 270.1 0.0 0.0
30.1 270.0 0.0 0.0
29.6 269.9 0.0 0.0
29.0 269.9 0.0 0.0
28.5 269.8 0.0 0.0
28.0 269.7 0.0 0.0
27.5 269.7 0.0 0.0
27.0 269.6 0.0 0.0
26.4 269.5 0.0 0.0
25.9 269.5 0.0 0.0
25.4 269.4 0.0 0.0
24.9 269.3 0.0 0.0
24.4 269.3 0.0 0.0
23.9 269.2 0.0 0.0
23.3 269.1 0.0 0.0
22.8 269.0 0.0 0.0
22.3 269.0 0.0 0.0
21.8 268.9 0.0 0.0
21.3 268.8 0.0 0.0
20.7 268.8 0.0 0.0
20.2 268.7 0.0 0.0
19.7 268.6 0.0 0.0
19.2 268.6 0.0 0.0
18.7 268.5 0.0 0.0
18.1 268.4 0.0 0.0
17.6 268.3 0.0 0.0
17.1 268.3 0.0 0.0
16.6 268.2 0.0 0.0
16.1 268.1 0.0 0.0
15.6 268.0 0.0 0.0
15.0 268.0 0.0 0.0
IZZ(S-FT.SQ)
5.3-5 SNA-&-D-O27(III)REV 2
ILl !1 I_ 1_ 1; ELE L" E UE L,' ]_ HE _ '
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 = 18.650. WEIGHT=
DENSITY= 56.330 LBS/CU.FT.
103.7
WEIGHT X-CG IXX(S-FT.SQ) IYY or IZZ(S-FT.SO)
O.O
C.O
0.0
0.0
0.0
0.0
0.0
0.0
0.0
O0
O0
O0
O0
O0
O0
O0
O0
O0
O0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
14.5 267.9
14,0 267.8
13.5 267.7
13.0 267.7
12.4 267.6
11.9 267,5
11.4 267.4
10.9 267.3
I0.4 267.3
9.9 267.2
9.3 267.1
8.8 267.0
8.3 266.7
78 266.8
7.3 266.7
6.7 266.6
6.2 266.5
5,7 266.4
5.2 266.3
4.7 266.2
4.1 266.1
3.6 266.0
3.1 265._
2.6 265.7
2.1 265.5
1.6 265.4
l.t] 265.2
0.5 264.9
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
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
5.3-6 SNA-8-D-O27(III)REV 2
ILl !1 t: [ L: 12 11 L :L: L: b." :L ,L. IL
LM RCS OXIDIZER MASS PROPERTIES,70°F-2 TANKS
Y-CG = + OR - 44.6 (CONST) Z-CG = - OR + 14.5
RADIUS = 6.250 CYLINDRICAL SECTION = 25.260. WEIGHT= 203.4
DENSITY= 90.050 LBS/CU.FT.
(ULLAGE/(VOL.OF LIQUID))xlO0= 5.621
WEIGHT X-CG IXX(S-FT.SQ)
203.4 275.7 0.0
202.4 275.6 0.0
201.4 275.5 0.0
200.3 275.4 0.0
199.3 275.3 0.0
198.3 275.3 0.0
197.3 275.2 0.0
196.3 275.1 0.0
195.3 275.0 0.0
194.2 274.9 0.0
193.2 274.9 0.0
192.2 274.8 0.0
191.2 274.7 0.0
190.2 274.6 0.0
189.2 274.5 0.0
188.1 274.5 0.0
187.1 274.4 0.0
186.1 274.3 0.0
185.1 274.2 0.0
184.1 274.1 0.0
183.1 274.1 0.0
182.0 274.0 0.0
181.0 273.9 0.0
180.0 273.8 0.0
179.0 273.7 0.0
178.0 273.7 0.0
177.0 273.6 0.0
175.9 273.5 0.0
174.9 273.4 0.0
173.9 273.3 0.0
172.9 273.3 0.0
171.9 273.2 0.0
170.9 273.1 0.0
169.8 273.0 0.0
168.8 272.9 0.0
167.8 272.9 0.0
166.8 272.8 0.0
165.8 272.7 0.0
164.8 272.6 0.0
163.7 272.5 0.0
162.7 272.5 0.0
161.7 272.4 0.0
160.7 272.3 0.0
IYY or IZZ(S-FT.SQ)
1.4
1.4
1.4
1.4
1.4
1.3
1.3
1.3
1.3
1.3
1.2
1.2
1.2
1.2.
1.2
1.21
1 .I;
I.I
I.I
1.I
1.0
l.O
1.0
1.0
I .0_
0.9
0.9
0.9
0.9
0.8
0.8
0.8
0.8
0.8
0.8
0.7
0.7
0.7
0.7
0.7
0.7
0.6
0.6
5.3-7 SNA-8-D-O27(III)REV 2
LM RCS OXIDIZER MASS PROPERTIES-70°F-2 TANKS
Y-CG = + OR - 44.6 (CONST) Z-CG = - OR + 14.5
RADIUS: 6.250 CYLINDRICAL SECTION: 25.260. WEIGHT:
DENSITY: 90.050 LBS/CU.FT.
WEIGHT X-CG IXX (S-FT. SQ)
203.4
IYY or IZZ(S-FT.SQ)
159.7 272.2 0.0 0.6
158.7 272.1 0.0 0.6
157.6 272.1 0.0 0.6
156.6 272.0 0.0 0.6
155.6 271.9 0.0 0.5
154.6 271.8 0.0 0.5
153.6 271.7 0.0 0.5
152.5 271.7 0.0 0.5
151.5 271.6 0.0 0.5
150.5 271.5 0.0 0.5
149.5 271.4 0.0 0.5
148.5 271.3 0.0 0.5
147.5 271.3 0.0 0.4
146.4 271.2 0.0 0.4
145.4 271.1 0.0 0.4
144.4 271.0 0.0 0.4
143.4 270.9 0.0 0.4
142.4 270.9 0.0 0.4
141.4 270.8 0.0 0.4
140.3 270.7 0.0 0.4
139.3 270.6 0.0 0.3
138.3 270.5 0.0 0.3
137.3 270.5 0.0 0.3
136.3 270.4 0.0 0.3
135.3 270.3 0.0 0.3
134.2 270.2 0.0 0.3
133.2 270.1 0.0 0.3
132.2 270.1 0.0 0.3
131.2 270.0 0.0 0.3
130.2 269,9 0.0 0.3
129.2 269.8 0.0 0.3
128.1 269.7 0.0 O. 2
127.1 269.7 0.0 0.2
126.1 269.6 0.0 0.2
125.1 269.5 0.0 0.2
124.1 269.4 0.0 0.2
123.1 269.3 0.0 0.2
122.0 269.3 0.0 0.2
121.0 269.2 0.0 0.2
120.0 269.1 0.0 0.2
119.0 269.0 0.0 O. 2
118.0 268.9 0.0 0.2
117.0 268.9 0.0 0.2
5.3-8 SNA-8-D-027(III)REV 2
L. i
L
LM RCS OXIDIZER MASS PROPERTIES-70°F-2 TANKS
Y-CG = + OR - 44.6 (CONST) Z-CG = - OR + 14.5
RADIUS = 6.250 CYLINDRICAL SECTION: 25.260. WEIGHT = 203.4
DENSITY= 90.050 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ) IYY or
115.9 268.8 0.0 0. z
114.9 268.7 0.0 O. 2
113.9 268.6 0.0 0.i
112.9 268.5 0.0 0.i
111.9 268.5 0.0 0.i
110.9 268.4 0.0 0.1
109.8 268.3 0.0 0.1
108.8 268.2 0o0 0.1
107.8 268.1 0.0 0.i
106.8 268.1 0.0 0.i
105.8 268.0 0.0 0.1
104.8 267.9 0.0 0.i
103.7 267.8 0.0 0.i
102.7 267,7 0.0 0.i
101.7 267.7 0.0 0.i
i00.7 267,6 0.0 O. i
99.7 267.5 0.0 0.i
98.6 267,4 0.0 0.i
97.6 267.3 0.0 0.1
96.6 267.3 0.0 0.1
95.6 267.2 0.0 0.i
94.6 267.1 0.0 0.i
93.6 267.0 0.0 0.1
92.5 266.9 0.0 0.0
91.5 266.9 0.0 0.0
90.5 266.8 0.0 0.0
89.5 266.7 0.0 0.0
88.5 266.6 0.0 0.0
87.5 266.5 0.0 0.0
86.4 266.5 0.0 0.0
85.4 266.4 0.0 0.0
84.4 266.3 0,0 0.0
83.4 266.2 0.0 0.0
82.4 266.1 0.0 0.0
81.4 266.1 0.0 0.0
80.3 266.0 0.0 0.0
79.3 265.9 0.0 0.0
78.3 265.8 0.0 0.0
77.3 265.7 0.0 0.0
76.3 265.7 0.0 0.0
75.3 265.6 0.0 0.0
74.2 265.5 0.0 0.0
73.2 265.4 0.0 0.0
IZZ (S-FT. SQ)
5.3-9 SNA-8-D-O27(III)REV 2
LM RCS OXIDIZER MASS PROPERTIES-70°F-2 TANKS
Y-CG = + OR - 44.6 (CONST) Z_CG = - OR + 14.5
RADIUS: 6.250 CYLINDRICAL SECTION: 25.260. WEIGHT=
DENSITY= 90.050 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ)
203.4
IYY or
72.2 265.3 0.0 0.0
71.2 265.3 0.0 0.0
70.2 265.2 0.0 0.0
69.2 265.1 0.0 O. 0
68.1 265.0 0.0 0.0
67.1 264.9 0.0 0.0
66.1 264.8 0.0 0.0
65.1 264.8 0.0 0.0
64.1 264.7 0.0 0.0
63.1 264.6 0.0 0,0
62.0 264.5 0.0 0,0
61.0 264,4 0.0 0.0
60.0 264,4 0.0 0.0
59.0 264.3 0.0 0.0
58.0 264.2 0.0 0.0
57.0 264.1 0,0 0.0
55.9 264.0 0.0 0.0
54.9 264.0 0.0 0.0
53.9 263.9 0.0 0.0
52.9 263.8 0.0 0.0
51.9 263.7 0.0 0,0
50.8 263,6 0.0 0.0
49.8 263.5 0.0 0.0
48.8 263.5 0.0 0.0
47.8 263.4 0.0 0.0
46.8 263.3 0.0 0.0
45.8 263.2 0.0 0.0
44.7 263.1 0.0 0.0
43.7 263.0 0.0 0.0
42.7 263.0 0.0 0.0
41.7 262.9 0.0 0.0
40.7 262.8 0.0 0.0
39.7 262.7 0.0 0.0
38.6 262.6 0.0 0.0
37.6 262.5 0.0 0.0
36.6 262.5 0.0 0.0
35.6 262.4 0.0 0.0
34.6 262.3 0.0 0.0
33.6 262.2 0.0 0.0
32.5 262.1 0.0 0.0
31.5 262.0 0.0 0.0
30.5 261.9 0.0 0.0
29.5 261.9 0.0 0.0
IZZ(S-FT.SQ)
5.3-10 SNA-8-D-027(III)REV 2
" _ ""h"
UEL, L L ..
LM RCS OXIDIZER MASS PROPERTIES-70"F-2 TANKS
Y-CG = + OR - 44.6 (CONST) Z-CG : - OR + 14.5
RADIUS= 6.250 CYLINDRICAL SECTION= 25.260. WEIGHT=
DENSITY= 90.050 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ)
203.4
IYY or
28.5 261.8 0.0 0.0
27.5 261.7 0.0 0.0
26.4 261.6 0.0 0.0
25.4 261.5 0.0 0.0
24.4 261.4 0.0 0.0
23.4 261.3 0.0 0.0
22.4 261.2 0.0 0.0
21.4 261.1 0.0 0.0
20.3 261.0 0.0 0.0
19.3 260.9 0.0 0.0
18.3 260.8 0.0 0.0
17.3 260.7 0.0 0.0
16.3 260.6 0.0 0.0
15.3 260.5 0.0 0.0
14.2 260.4 0.0 0.0
13.2 260.3 O. 0 0.0
12.2 260.2 0.0 0.0
11.2 260.1 0.0 0.0
i0.2 260.0 0.0 0.0
9.2 259.8 0.0 0.0
8.1 259.7 0.0 0.0
7.1 259.6 0.0 0.0
6.1 259.4 0.0 0.0
5.1 259.3 0.0 0.0
4.1 259.1 0.0 0.0
3.1 258.9 0.0 0.0
2.0 258.7 0.0 0.0
1.0 258.4 0.0 0.0
IZZ(S-FT.SQ)
5.3-ii SNA-8-D-027(III)REV 2
U!1 i.I I.:" :1: E :E L E L: :E E L,' |; I_ E_ __ _
_ I.,/I
t" t_
Z
I--1
i.I
.11 -I] If _I] .II . 1[ II I[ I_ 1_ tl
L11[-
L L
LUNAR MODULE DESCENT WATER
MASS PROPERTIES
Amendment 86
9/10/70
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 SNA-8-D-O27(III)REV 2
11 11 I.I E L E I/ L E I: Id I: M Ii li I_ L L ,_ L
TABLE 5,4-1
I 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=
DENSITY_ 62.400 LBS/CU.FT.
(ULLAGE/VOL.OF LIQUID))xIO0: 33.757
WEIGHT X-CG IXX(S-FT.SQ)
323.8 165.8 0.3
322.2 165.8 0,2
320.6 165.8 0,2
_8.9 165.7 0.2
317.3 165.7 0.2
315.7 165.6 0.2
314.1 165.6 0.2
312.5 165.6 0.2
310.8 165.5 0.2
309.2 165.5 0.2
307.6 165.4 0.2
306.0 165.4 0.2
304.4 165.4 O.2
302.8 165.3 0.2
301.I 165,3 0.2
299.5 165.3 0.2
297.9 165.2 0.2
296.3 165.2 0.2
294.7 165.1 0.2
293.0 165.1 0.2
291.4 165.1 0.2
289.6 165.0 0.2
288.7 165.0 0.2
286.6 165.0 0.2
284.9 164.9 0.2
283.3 164.9 0.2
281.7 164.8 0.2
280.I 164.8 0.2
278.5 164.8 0.2
276.8 164.7 0.2
275.2 164.7 0.2
273.6 164.6 0.2
272.0 164.6 0.2
270.4 164.6 0.2
268.8 164.5 0.2
267.1 164.5 0.2
265.5 164.5 0.2
263.9 164.4 0.2
262.3 164.4 0.2
260.7 164.3 0.2
259.0 164.3 0.2
257.4 164.3 0.2
255.8 164.2 0.2
323.8
IYY or
0.2
0.2
0,2
0,2
0.2
0.2
0.2
0.2
0,2
0.2
0.2
0.2
0.2
0,2
0.2
0.2
O.l
O.l
O.l
O.l
O.l
O.l
O.l
O.l
0.1
0.1
0.1
O.l
O.l
O.l
O.l
O.l
O.l
O.l
O.l
0.1
0.1
0.1
O.l
O.l
O.l
O.l
O.l
Amendment
9/10/70
IZZ(S-FT.SQ)
86
5.4-2 SNA-8-D-O27(III)REV 2
UII _L L EL L LLLLE U I! E L L L_ L
LM-8 DESCENT WATER MASS
Y-CG--43.2 (CONST) Z-CG
RADIUS= ]4.200 CYLINDRICAL
DENSITY= 62.400 LBS/CU,FT.
WEIGHT X;CG
TABLE 5.4-I (Continued)
PROPERTIES-I TANK
= -43.2 (CONST)
SECTION= O,O WEIGHT= 323.8
IXX(S-FTSQ)
254.2 ]64.2 0.2
252.6 ]64.] 0.2
250.9 164. ]O.2
249.3 164.l O.2
247.7 164.0 0.2
246.1 164.0 0.2
244.5 164.0 0.2
242.8 163.9 0.2
241.2 ]63.9 0.2
239.6 ]63.8 0.2
238.0 ]63.8 0.2
236.4 ]63.8 0.2
234.8 ]63.7 0.2_
233.1 163.7 0.2,
231.5 163.6 0.2_
229.9 163.6 0.2,
228.3 163.6 0.2,
226.7 163.5 O.l
225.0 163.5 O.l
223.4 163.4 O.l
221.8 163.4 O.l
220.2 163.4 0.]
2]8.6 163.3 O.l
216.9 163.3 0.]
215.3 ]63.2 0.]
213.7 ]63.2 0.]
212.] ]63.2 O.l
210.5 163.l O.l
208.9 163.1 O.l
207.2 ]63.0 O.l
205.6 163.0 O.l
204.0 163.0 O.l
202.4 162.9 0.]
200.8 ]62,9 0.]
199.I ]62.8 0.]
197.5 162.8 0.I
195.9 162.8 0.1
]94.3 162.7 0.]
192.7 162.7 0.1
191.0 162.6 O.l
189.4 162.6 O.l
187.8 162.6 O.l
186.2 162.5 O.l
Amendment: 86
9/10/70
IYY or IZZ(S-FT.SQ)
O.l
0.1
0.I
0.1
0.1
0.1
0.1
0.1
O.l
0.I
O.l
0.1
0.1
O.l
O.l
O.l
O.l
O.l
O.l
0.1
0.1
0.1
0.1
0.1
0.1
O.l
O.l
O.l
O.l
O.l
O.l
0.I
0.]
0.I
0.1
O.l
O.l
O.l
O.l
O.l
O.l
0.0
O.O
5.4-3 SNA-8-D-O27(III)REV 2
LM-8
Y-CG
RADIUS=
DENSITY=
WEIGHT
TABLE5.4-I (Continued)
DESCENTWATERMASSPROPERTIES-ITANK
= -43.2 (CONST)Z-CG- -43.2 (CONST)
14.200CYLINDRICALSECTION=0.0 WEIGHT=323.8
62.400 LBS/CU.FT.
Amendment
9110170
X-CG IXX(S-FT. SQ) IYY or IZZ(S-FT.SQ)
184.6 162.5 O.]
182.9 162.4 0.I
181.3 162.4 O.1
179.7 162.3 0.1
178.1 162.3 O.l
]76.5 162.3 O. 1
174.9 162.2 O.1
173.2 162.2 O.l
171.6 162.1 O.l
170.0 162.1 O.l
168.4 162.1 O.1
166.8 162.0 O.l
165.1 162.0 O.l
163.5 161.9 0.1
161.9 161.9 0.1
160.3 161.8 0.1
158.7 161.8 0.1
157.0 161.8 0.1
155.4 161.7 0.1
153.8 161.7 0.1
152.2 161.6 O.1
150.6 161.6 0.1
148.9 161.5 O.l
147.3 161.5 O.l
145.7 161.4 0.1
144.1 161.4 0.1
142.5 161.4 O.l
140.9 161.3 O.l
139.2 161.3 0.I
137.6 161.2 0.1
136.0 161.2 O.l
134.4 161 .l O.l
132.8 161.1 O.O
131.1 161.0 0.0
129.5 161.0 0.0
]27.9 160.9 0.0
126.3 160.9 0.0
124.7 160.9 0.0
123.0 160.8 0.0
121.4 160.8 0.0
119.8 160.7 0.0
118.2 160.7 O.O
I16.6 160.6 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
0.0
0.0
0.0
0.0
0.0
0.0
O.O
0.0
0.0
0.0
0.0
O.O
O.O
0.0
0.0
0.0
0.0
O.O
O.O
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
86
5.4-4 SNA-8-D-O27(III)REV 2
ILl It LLLL L 11 1i kLL__
I
TABLE 5.4-I (Continued)
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=
WEIGHT .X-CG IXX(S-FT.SQ)
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 0.0
160.5 0.0
160.5 0.0
160.4 0.0
160.4 0.0
160.3 0.0
160.3 0.0
160.2 0.0
160.2 0.0
160.1 0.0
160._ 0.0
160.0 0.0
160.0 0.0
159.9 0.0
159.9 0.0
159.8 O. 0
159.8 0.0
159.7 0.0
159.6 0.0
159.6 0.0
159.5 0.0
159.5 0.0
159.4 0.0
159.4 0.0
159.3 0.0
159.3 0.0
159.2 0.0
15911 0.0
159.I 0.0
159.0 0.0
159.0 0.0
158.9 0.0
158.8 0.0
158.8 O. 0
158.7 0.0
1S8.7 0.0
158.6 0.0
158.5 0.0
158.5 0.0
1$8.4 0.0
188.3 0.0
158.3 0.0
158.2 0.0
323.8
Amendment 86
9/10170
I
IYY or IZZ(S-FT.SQ.
0.0
0.0
0.0
O.C
0.0
0.(]
O.C
O.C
O.C
O.C
O.C
O.C
OC
OC
OC
OC
OC
OC
O.C
O.C
O.C
O.C
O.C
O.C
O.O
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
0.0
0.0
0.0
0.0
5.4-5 SNA-8-D-O27(III)REV 2
II II Ig if L. E If L E E I_ Ei_ l; I! E :' '
L,. L L L
LM-8 DESCENT WATER MASS
Y-CG = -43.2 (CONST) Z-CG
RADIUS: 14.200 CYLINDRICAL
DENSITY= 62.400 LBS/CU.FT.
WEIGHT X-CG
45.3 158
43.7 158
42.1 158
40.5 157
38.9 157
37.2 157
35.6 157
34.0 157
32.4 157
30.8 157
29.l 157
27.5 157
25.9 157
24.3 157
22.7 157
21.0 156
19.4 156
17.8 156
16.2 156
14.6 156
13.0 156
II .3 156
9.7 156
8.1 155
6.5 155
4.9 155
3.2 155
l.6 155
l
l
0
9
8
8
7
6
5
4
.4
.3
.2
.I
.0
.9
.8
.7
.6
.5
.3
.2
.l
.9
.8
.6
.4
.l
TABLE 5.4-!
PROPERTIES-I TANK.
= -43.2 (CONST)
SECTION = 0.0 • WEIGHT =
IXX(S-FT.SQ.)
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
O.O
0.0
0.0
O.O
0.0
0.0
O.O
O.O
O.O
0.0
O.O
0.0
0.0
0.0
(Continued)
323.8
IYY or
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
0.0
0.0
O.O
O.O
O.O
O.O
0.0
0.0
0.0
O.O
O.O
0.0
0.0
0.0
Amendment
9/10/70
IZZ(S-FT.SQ. )
86
5.4-6 SNA-8-D-027(I II)REV 2
IJ LI EL.EELEEEELi_
Amendmenti01
2/16/71
TABLE 5.4-2
LM 10 AND SUBSEQUENT DESCENT STAGE WATER MASS PROPERTIES
RADIUS - 14.2 INCHES DENSITY = 62.4 LBS/CU. FT. WEIGHT - 323.8 POUNDS
TANK NO. 1 ¥-CC ,, -43.2 (CONSTANT) TANK NO. 2¥-CG ., 43.2 (CONSTANT)
Z-CG ,, -43.2 (CONSTANT) Z-CG - 43.2 (CONSTANT)
(ULLAGE/(VOLUME OF LIQUID)) X i00 -37.757
Weight Tank-i Tank-2 Height
Pounds X-CG X-CG 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
320.6 165.8 142.7 18.921
318.9 165.7 142.6 18.841
317.3 165.7 142.6 18.762
315.7 165.6 142.5 18.683
314.1 165.6 142.5 18.605
312.5 165.6 142.5 18.527
310.8 165.5 142.4 18.449
309.2 165.5 I_2.4 18.371
307.6 165.4 142.3 18.294
806.0 165.4 I_2.3 18.217
304.4 165.4 142.3 18.140
302.8 165.3 I_2.2 18.064
301.1 165.3 142.2 17.987
299.5 165.3 142.2 17.911
297.9 165.2 142.1 17.835
296.3 165.2 142.1 17.760
294.7 165.1 142.0 17.684
293.0 165.1 142.0 17.609
291.4 165.1 142.0 17.534
289.8 165.0 141.9 17.459
288.2 165.0 141.9 17.385
286.6 165.0 141.9 17.310
284.9 164.9 141.8 17.236
283.3 164.9 141.8 17.162
281.7 164.8 141.7 17.088
280.1 164.8 141.7 17.014
278.5 164.8 141.7 16.941
276.8 164.7 141.6 16.867
275.2 164.7 141.6 16.794
273.6 164.6 141.5 16.721
272.0 164.6 141.5 16.648
270.4 164.6 141.5 16.575
268.8 164.5 141.4 16.502
267.1 164.5 141.4 16.430
265.5 164.5 141.4 16.357
5.4-7 SNA-8-D-027(III)REV 2
Amendment 86
9/10/70
TABLE 5.4-2 (Continued)
LM I0 AND SUBSEQUENT DESCENT STAGE WATER MASS PROPERTIES
RADIUS =14.2 INCHES DENSITY = 62.4 LBS/CU. FT. WEIGHT -323.8 POUNDS
•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 =37.757
Weight Tank-i Tank-2 Height
Pounds X-CG X-CG Inches
263.9
262.3
260.7
259.0
257.4
255.8
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
218.6
216.9
215.3
213.7
212.1
210.5
208.9
207.2
205.6
204.0
164.4 141.3 16.285
164.4 141.3 16.212
164.3 141.2 16.140
164.3 141.2 16.068
164.3 141.2 15.996
164.2 141.1 15.924
164.2 141.1 15.852
164.1 141.0 15.781
164.1 141.0 15.709
164.1 141.0 15.638
164.0 140.9 15.566
164.0 140.9 15.495
164.0 140.9 15.423
163.9 140.8 15.352
163.9 140.8 15.281
163.8 140.7 15.210
163.8 140.7 15.139
163.8 140.7 15.068
163.7 140.6 14.997
163.7 140.6 14.926
163.6 140.5 14.855
163.6 140.5 14.784
163.6 140.5 14.713
163.5 140.4 14.642
163.5 140.4 14.571
163.4 140.3 14.500
163.4 140.3 14.430
163.4 140.3 14.359
163.3 140.2 14.288
163.3 140.2 14.217
163.2 140.1 14.146
163.2 140.1 14.076
163.2 140.1 14.005
163.1 140.0 13.934
163.1 140.0 13.863
163.0 139.9 13.792
163.0 139.9 13.722
163.0 139.9 13.651
5.4-8 SNA-8-D-027(III)REV 2
._aendment 86
9/10/70
TABLE 5.4-2 (Continued)
124 i0 AND SUBSEQUENT DESCENT STAGE WATER MASS PROPERTIES
RADIUS - 14.2 INCHES DENSITY - 62.4 LBS/CU. FT. WEIGHT - 323.8 POUNDS
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 - 37.757
Weight Tank-i Tank-2 Height
Pounds X-CG X-CG Inches
202.4 163.0 139.9 13.580
200.8 163.9 139.8 13.509
199.1 162.9 139.8 13.438
197.5 162.8 139.7 13.367
195.9 162.8 139.7 13.296
194.3 162.8 139.7 13.225
192.7 162.7 139.6 13.154
191.0 162.7 139.6 13.082
189.4 162.6 139.5 13.011
187.8 162.6 139.5 12.940
186.2 162.5 139.4 12.869
184.6 162.5 139.4 12.797
182.9 162.4 139.3 12.726
181.3 162.4 139.3 12.654
179.7 162.3 139.2 12.582
178.1 162.3 139.2 12.511
176.5 162.3 139.2 12.439
174.9 162.2 139.1 12.367
173.2 162.2 139.1 12.295
171.6 162.1 139.0 12.223
170.0 162.1 139.0 12.150
168.4 162.1 159.0 12.078
166.8 162.0 138.9 12.006
165.1 162.0 138.9 11.933
163.5 161.9 138.8 11.860
161.9 161.9 138.8 11.788
160.3 161.8 138.7 11.715
158.7 161.8 138.7 11.642
157.0 161.8 138.7 11.568
155.4 161.7 138.6 11.495
153.8 161.7 138.6 11.421
152.2 161.6 138.5 11.348
150.6 161.6 138.5 11.274
148.9 161.5 138.4 11.200
147.3 161.5 138.4 11.126
145.7 161.4 138.3 11.051
5.4-9 SNA-8-D-027(IZI)REV 2
Amendment 86
9/10/70
TABLE 5.4-2 (Continued)
LM i0 AND SUBSEQUENT DESCENT STAGE WATER MASS PROPERTIES
RADIUS - 14.2 INCHES DENSITY -62.4 LBS/CU. FT. WEIGHT - 323.8 POUNDS
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 100 - 37.757
Weight Tank-I Tank-2 Height
Pounds X-CG X-CG Inches
144.1
142.5
140.9
139.2
137.6
136.0
134.4
132.8
131.1
129.5
127.9
126.3
124.7
123.0
121.4
119.8
118.2
116.6
114.9
113.3
111.7
110.1
108.5
106.9
105.2
103.6
102.0
100.4
98.8
97.1
95.5
93.9
92.3
90.7
89.0
87.4
85.8
84.2
82.6
80.9
79.3
161.4
161.4
161.3
161.3
161.2
161.2
161.1
161.1
161.0
161.0
160.9
160.9
160.9
160.8
160.8
160.7
160.7
160.6
160.6
160.5
160.5
160.4
160.4
160.3
160.3
160.2
160.2
160.1
160.1
160.0
160.0
159,9
1599
1598
159,8
159,7
159,6
159,6
159,5
159.5
159.4
138.3 10.977
138.3 10.902
138.2 10.827
138.2 10.752
138.1 10.677
138.1 10.601
138.0 10.526
138.0 10.450
137.9 10.373
137.9 10.297
137.8 10.220
137.8 10.143
137.8 10.066
137.7 9.989
137.7 9.911
137.6 9.833
137.6 9.755
137.5 9.676
137.5 9.597
137.4 9.518
137.4 9.438
137.3 9.358
137.3 9.278
137.2 9.198
137.2 9.117
137.1 8.035
137.1 8.953
137.0 8.871
137.0 8.789
136.9 8.706
136.9 8.622
136.8 8.538
136.8 8.454
136.7 8.369
136.7 8.284
136.6 8.198
136.5 8.111
136.5 8.024
136.4 7.937
136.4 7.849
136.3 7.760
5.4-10 SNA-8-D-O27(III)REV 2
U IZ '_.- L L
Amendment i01
2/16/71
TABLE 5.4-2 (ConCLnued)
I_ I0 AND SUBSEQUENT DESCENT STAGE WATER MASS PROPERTIES
RADIUS - 14.2 INCHES DENSITY - 62.4 LBS/CU. FT. WEIGHT - 323.8 POUNDS
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 Tank-1 Tank-2 Height
Pound____a X-C_._G X-CG Inches
77.7 159.4 136.3 7.670
76.1 159.3 136.2 7.580
74.5 159.3 136.2 7.489
72.9 159.2 136.1 7.398
71.2 159.1 136.0 7.306
69.6 159.1 136.0 7.213
68.0 159.0 135.9 7.119
66.4 159.0 135.9 7.024
64.8 158.9 135.8 6.929
63.1 158.8 135.7 6.832
61.5 158.8 135.7 6.735
59.9 158.7 135.6 6.637
58.3 158.7 135.6 6.538
56.7 158.6 135.5 6.437
55.0 158.5 135.4 6.336
53.4 158.5 135.4 6.233
51.8 158.4 135.3 6.129
50.2 158.3 135.2 6.024
48.6 158.3 135.2 5.917
47.0 158.2 135.1 5.809
45.3 158.1 135.0 5.700
43.7 158.1 135.0 5.589
42.1 158.0 134.9 5.476
40.5 157.9 134.8 5.361
38.9 157.8 134.7 5.245
37.2 157.8 134.7 5.126
35.6 157.7 134.6 5.005
34.0 157.6 134.5 4.882
32.4 157.5 134.4 4.757
30.8 157.4 134.3 4.628
29.1 157,4 134.3 4.497
27.5 157,3 134.2 4.363
25.9 157.2 134.1 4.225
24.3 157.1 134.0 4.083
22.7 157.0 133.9 3.937
21.0 156.9 133.8 3.787
19,4 156.8 133.7 3.631
17.8 156.7 133.6 3.469
16.2 156.6 133.5 3.301
14.6 156.5 133.4 3.124 I
5.4-11 SNA-8-1)-027(ZII)P,.EV 2
11 111 _ I_ 12 E 12 L L" E 1_ I: l.l 11 II lZ j_ L LE
Amendment 86
9/10/70
TABLE 5.4-2 (Continued)
LH 10 AND SUBSEQUENT DESCENT STAGE WATER MASS PROPERTIES
RADIUS = 14,2 INCHES DENSITY = 62.4 LBS/CU. FT. WEIGHT = 323.8 POUNDS
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 100 - 37.757
Weight Tank-i Tank-2 Height
Pounds X-CG X-CG Inches
13.0 156.3 133
11.3 156.2 133
9.7 156.1 133
8.1 155.9 132
6.5 155.8 132
4.9 155.6 132
3.2 155.4 132
1.6 155.1 132
2 2.939
12.742
02.532
82.305
7 2.055
5 1.774
3 1.442
0 1.015
5.4-12 SNA-8-D-027(III)REV 2
!1 !1 l,' [: l: E E LEEb: ]2 Lk_
........ I
i
L'_
z d
T- 'v-- '_- v- V'
."11 _U -.l[_:. IS It l( l_ l_ _ I
.k.._
Vt
L
_r
,L. t.. .L J,- _ i,. L L
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 by the last
number on the first line of each page.
5.5-I SNA-8-D-O27(III)REV 2
II IIJ I,[ E l:." 1,: L L L" l;. h" E E l_ I_ E L LL L
LM ASCENT WATER MASS PROPERTIES-2 TANKS
Y-CG = + OR - 25.0 (CONST) Z-CG =+ OR -
RADIUS=7.155 CYLINDRICAL SECTION= 0.0
DENSITY=62.400 LBS/CU.FT.
13.7 (CONST)
WEIGHT: 41.2
(ULLAGE/(VOL. OF LIQUID))xlO0: 34.481
WEIGHT X-CG IXX(S-FT.SQ.) IYY or IZZ(S-FT.SQ.)
41.2 300.3 0.0 0.0
41,0 300.3 0.0 0.0
40.8 300.3 0.0 0.0
40.6 300.3 O. 0 0.0
40,4 300.3 0.0 0.0
40.2 300.2 0.0 0.0
40.0 300.2 0.0 0.0
39.8 300.2 0.0 0.0
39.6 300.2 0.0 0.0
39.3 300.2 0.0 0,0
39.1 300.1 0.0 0.0
38.9 300.1 0.0 0.0
38.7 300.1 0.0 0.0
38,5 300.1 0.0 0.0
36.3 300.1 0.0 0.0
38.1 300.1 0.0 0.0
37,9 300.0 0.0 0.0
37.7 300.0 0.0 0,0
37.5 300.0 0.0 0.0
37.3 300.0 0.0 0.0
37.1 300.0 0.0 0.0
36.9 299.9 0.0 0.0
36,7 299.9 0.0 0.0
36.5 299.9 0.0 0.0
36.3 299.9 0.0 0.0
36.0 299.9 0.0 0.0
35.8 299.8 0.0 0.0
35.6 299.8 0.0 0.0
35.4 299.8 0.0 0.0
35.2 299.8 0.0 0.0
35.0 299.8 0.0 0.0
34.8 299,7 0.0 0.0
34.6 299.7 0.0 0,0
34.4 299.7 0.0 0.0
34.2 299.7 0,0 0.0
34.0 299.6 0.0 0.0
33.8 299.6 0.0 0.0
33.6 299.6 0.0 0.0
33,4 299.6 0.0 0.0
33.2 299.6 0.0 0.0
33,0 299.6 0.0 0.0
32.8 299.6 0,0 0.0
32,5 299.5 0.0 0.0
5.5-2 SNA-8-D-O27(III)REV 2
UL E L ' " '
LLL
LM ASCENT WATER MASS PROPERTIES-2 TANKS
Y-CG = + OR - 25.0 (CONST) Z-CG = + OR - 13.7 (CONST)
RADIUS= 7.155 CYLINDRICAL SECTION= 0.0 WEIGHT=
DENSITY: 62.400 LBS/CU.FT.
41.2
WEIGHT X-CG IXX(S-FT.SQ.)
32.3 299.5 0.0
32.1 299.5 0,0
31.9 299.5 0.0
31.7 299.5 0.0
31.5 299,4 0.0
31.3 299.4 0.0
31 .I 299.4 0.0
30.9 299.4 0.0
30.7 299.4 0o0
30.5 299.3 0.0
30.3 299.3 0.0
30.1 299.3 0.0
29.9 299.3 0.0
29.7 299.3 0.0
29.5 299.2 0.0
29,3 299.2 0.0
29.0 299.2 0.0
28.8 299.2 0.0
28.6 299.2 0.0
28.4 299,1 0.0
28.2 299.1 0.0
28.0 299.1 0.0
27.8 299.1 0.0
27.6 299.1 0.0
27.4 299.0 0.0
27.2 299.0 0.0
27.0 299.0 0.0
26.8 299.0 0.0
26.6 299.0 0.0
26.4 298.9 0.0
26.2 298.9 0.0
26.0 298.9 0.0
25.7 298.9 0.0
25.5 298.9 0.0
25.3 298.8 0.0
25.1 298.8 0.0
24.9 298.8 0.0
24.7 298.8 O. 0
24.5 298,8 O. 0
24.3 298.7 O. 0
24.1 298.7 O. 0
23.9 298.7 0.0
23,7 298.7 O. 0
IYY or IZZ(S-FT.SQ.)
O.O
O.O
0.0
O.O
0.0
O.O
0.0
0.0
O.O
O.O
O.O
O.O
0.0
0.0
0.0
0.0
O0
O0
O0
O0
O0
O0
O0
O0
O0
O0
O0
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
0.0
0.0
5.5-3 SNA-8-D-O27(III)REV 2
LM ASCENT WATER MASS PROPERTIES-2 TANKS
Y-CG = + OR - 25.0 (CONST) Z-CG = + OR - 13.7 (CONST)
RADIUS= 7.155 CYLINDRICAL SECTION= 0.0 WEIGHT:
DENSITY= 62.400 LBS/CU.FT.
WEIGHT X-CG IXX(S-FT.SQ.)
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. l
298. l
298.0
298.0
298.0
298.0
298.0
297.9
297.9
297.9
297.9
297.8
297.8
297.8
297.8
297.7
297.7
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
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
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
0.0
41.2
IYY or IZZ(S-FT.SQ.)
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
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
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
0.0
5.5-4 SNA-8-D-O27(III)REV 2
ILl ILl I.I I.; _ L E L E]2 E EU 1_ L_ E L ,_ ,_ ,L.
LM ASCENT WATER MASS PROPERTIES-2 TANKS
Y-CG = + OR - 25.0 (CONST) Z-CG = + OR - 13.7 (CONST)
RADIUS= 7.155 CYLINDRICAL SECTION= 0.0 WEIGHT=
DENSITY: 62.400 LBS/CU.FT.
41.2
WEIGHT X-CG IXX(S-FT.SQ.) IYY or
14.6 297.7
14.4 297.7
14.2 297.6
14.0 297.6
13.8 297.6
13.6 297.6
13.4 297.5
13.2 297.5
13.0 297.5
12.8 297.5
12.6 297.4
12.4 297.4
12.2 297.4
II .9 297.4
II .7 297.3
I I.5 297.3
II.3 297.3
II .l 297.3
I0.9 297.2
I0.7 297.2
I0.5 297.2
I0.3 297.2
lO.l 297.1
9.9 297. l
9.7 297. l
9.5 297.0
9.3 297.0
9.l 297.0
8.9 297.0
8.7 296.9
8.4 296.9
8.2 296.9
8.0 296.8
7.8 296.8
7.6 296.8
7.4 296.7
7.2 296.7
7.0 296.7
6.8 296.6
6.6 296.6
6.4 296.6
6.2 296.5
6.0 296.5
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
0.0
0.0
O.O
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
0.0
0.0
OO
O0
O0
O0
O0
O0
O0
O0
O0
0.0
IZZ(S-FT.SQ.)
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
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
0.0
0.0
0.0
0.0
O.O
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
O.O
5.5-5 SNA-8-D-O27(III)REV 2
ILl ILl 1.[ E 1: E IZ IL Z EEE L,' l J; Ii "ELL ,_ _
LM ASCENT WATER MASS PROPERTIES-2 TANKS
Y-CG = + OR - 25.0 (COrISl) Z-CC- = + OR - 13.7 (CONST)
RADIUS= 7.155 CYLINDRICAL SECTION= 0.0
DENSITY= 62.400 LBS/CU.FT.
WEIGHT= 41.2
WEIGHT X-CG IXX(S-FT.SQ.) IYY or IZZ (S-FT.SQ.)
5.8 296.5 0.0 0.0
5.6 296.4 0.0 0.0
5.4 296.4 0.0 0.0
5.1 296.4 0.0 0.0
4.9 296.3 0.0 0.0
4.7 296.3 0.0 0.0
4.5 296.2 0.0 0.0
4.3 296.2 0.0 0.0
4.1 296.2 0.0 0.0
3.9 296.1 0.0 O.O
3.7 296.1 0.0 0.0
3.5 296.0 0.0 0.0
3.3 296.0 0.0 0.0
3.1 295.9 0.0 0.0
2.9 295.9 0.0 0.0
2.7 295.9 0.0 0.0
2.5 295.8 0.0 0.0
2.3 295.7 0.0 0.0
2.1 295.7 0.0 0.0
l .9 295.6 0.0 0.0
l .6 295.6 0.0 0.0
l .4 295.5 O.O O.O
l .2 295.4 0.0 0.0
l .O 295.4 0.0 0.0
0.8 295.3 0.0 0.0
0.6 295.2 0.0 O.O
0.4 295.1 O.O O.O
0.2 294.9 0.0 0.0
5.5-6 SNA-8-D-O27(III)REV 2
i_ i_
II Ill II IIII II I I II III
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LUNAR MODULE TRAPPED AND RESIDUAL PROPELLANTS
AND MISCELLANEOUS CONSUMABLES
5.6-1 SNA-8-D-027(III)REV 2
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5.6-5 SNA-B-D-027 (III) REV 3
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5.6-6 SNA-8-D-027 (III)REV 3
NASA- MSC
• %
TABLE 5.6-2
Amendment 106
6/22/71
LM-10 AND SUBSEQUENT MISCELLANEOUS CONSUMABLES
ECS COOLANT:
Ascent -Primary
-Redundant
WEIGHT
(Pounds)
32.1
CENTER OF GRAVITY
(Inches)
YE
251.9 9.9 -2.4
3.3 251.0 9.9 -2.4
Descent - Primary
- Redundant
1.7
0.0
163.5 25.0 38.0
COX:
Ascent -Tank #i 2.4 266.1 15 .I -53.5
- Tank #2 2.4 266.1 -15.1 -53.5
Descent -Tank #i 46.9 185.6 38.9 -53.5
- Tank #2 46.9 185.2 41.5 48.2
WATER:
Ascent - Tank #i 42.5 300.4 25.0 13.7
- Tank #2 42.5 300.4 -25.0 -13.7
*Descent - Tank #I 166.0 -43.2 -43.2
- Tank #2 141.9 43.2 43.2
NITROGEN:
Ascent 0.i 301.5 +25.0 13.7
0.i 301.5 -25.0 -13.7
0.6 169.4 -43.2 -43.2
0.4 150.4 37.0 56.2
Descent
HELIUM:
APS - Tank #i 6.6 246.2 12.2 -48.6
-Tank #2 6.6 246.2 -12.2 -48.6
RCS -Tank #I 1.05 263.0 46.1 0.6
- Tank #2 1.05 263.0 -46.1 -0.6
DPS - (SHe) 51.2 148.3 47.2 -47.8
- (Ambient) i.i 175.8 59.2 -37.0
*See Mission Loading information in Section 3.0 for the required
Descent Water load for each mlssion.
I
5.6-7 SNA-8-D-O27(III)REV 3
NASA_MSC
lm la Ll _ L I' LJ L L L;; t'. L Li ill ___LL;_
5.6-5 SNA-8-D-027 (11I) REV 3
il 1_ L" L- IL IL L IL I_ _ IL _i Ii li la _ L__
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NASA _MSC 5.6-6 SNA-8-D-027 (III)REV 3
TABLE 5.6-2
LM Miscellaneous Consumables
ECS COOLANT:
Ascent -Primary
- Redundant
CENTER OF GRAVITY
(Inches)
WEIGHT
(Pounds) _ YE Zm
32.1 251.9 9.9 -2.4
3.3 251.0 9.9 -2.4
Descent - Primary 1.7 163.5 25.0 38.0
- Redundant 0.0
GOX:
Ascent - Tank #i 2.4 266.1 15.1 -53.5
- Tank #2 2.4 266.1 -15.1 -53.5
Descent 48.0 184.3 40.4 -40.4
WATER:
Ascent - Tank #i 42.5 300.4 25.0 13.7
- Tank #2 42.5 300.4 -25.0 -13.7
, Descent 166.0 -43.2 -43.2
NITROGEN:
Ascent 0.I 301.5 +25.0 13.7
0.i 301.5 -25.0 -13.7
Descent 0.6 169.4 -43.2 -43.2
HELIUM:
APS - Tank #i 6.6 246.2 12.2 -48.6
- Tank #2 6.6 246.2 -12.2 -48.6
RCS - Tank #i 1.05 263.0 46.1 0.6
- Tank #2 1.05 263.0 -46.1 -0.6
DPS -(SHe) 48.5 148.3 47.2 -47.8
- (Ambient) i.i 175.8 59.2 -37.0
*See Mission Loading information in Section 3.0 for the required
Descent Water load for each mission.
5.6-7 SNA-8-D-027(III)REV 2
ILl ILl IJ ;L: 1: E L L I: EEE L: l; I': ELL.4L
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5.6-4
SNA-8-D-027(III)REV 3
ULL
