Nasa Washer Dryer Tm X 68968 Users Manual
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SNA-8-D-027
CSM/LM
SPACECRAFT
OPERATIONAL
VGLIIME
MASS
PROP_TIES
PREPARED
DATA
(III)REV
2
BOOK
III
DATA
BOOK
BY
SYST_L$
OPERATIONS
BRANCH
SYSTEMS
ENGINEERING
DIVISION
APOLLO
SPACECRAFT
PROGRAM
OFFICE
MANNED
SPACECRAFT
APPROVED
BY
SYSTemS
GEGRGE
APOLLO
_INEE_ING
DIVISION
M. LOW, MANAG_
SPACE(_RAFT
PROGRAM
ORFLIGHT_IONS
lJ
P RE FACE
This
document
Data
Book.
In
have
been
deleted.
through
65,
"C-Prime",
cation
bered
of
is
the
this
this
sequentially
and
Mass
revision
revision
The
except
"D",
second
those
"F".
Missions"C",
second
revision
amendments
the
the
Mass
"D",
incorporates
Book,
revision
Properties
"C-Prime",
released
Data
next
of
associated
Amendments
Properties
with
issue
and
Amendments
with
number
i
Mis_ions
subsequent
Revision
"F"
2,
(i.e.,
to
will
66
"C",
publibe
and
numon).
SNA-8-D-O27(III)REV
2
Amendment
VOLUME
MASS
1.0
Introduction
2.0
Configuration
3.0
Mass
Properties
3.1
Mission
G
3.2
Mission
H1
3.3
Mission
H2
3.4
Mission
H3
3.5
Mission
Jl
CSH
Reference
4°0
4.1
5.0
and
PROPERTIES
and
SPS
Tank
SPS
Density
4.2
RCS/ECS/EPS
4.3
CSM RCS
4.4
CM
Loading
LM Descent
5.2
LM Ascent
5.3
LM RCS
5.4
LM
Descent
5.5
LM
Ascent
5.6
LM Trapped
Locations
Data
Mission
Mass
Consumables
Mass
Equations
Data
Properties,
Graphs,
Mass
Calculatlon
Trapped
and
SPS
Propellants,
Loading
Windows
.
Properties
Tables
and
Loading
Windows
Data
Tank
Tank
Tank
by
Properties
and
Consumables
Consumables
5.1
Station
Consumables
Ablator
BOOK
I
Load
LM Reference
DATA
Reference
86
9/lo/7o
IIl
Mass
Water
Water
Mass
Mass
Mass
Properties
Data
Properties
Propartles
Properties
Tank
Tank
Mass
Mass
Properties
Properties
Consumables
Ii
SNA-8-D-027
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2
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1.0
i.i
INTRODUCTION
SCOPE
The complete
Spacecraft
Operational
consist
of five separate
volumes.
These
Volume
I - CSM
Data
Part
Part
Volume
Data
I - Constraints
Part
II - Launch
III
Volume
IV - EMU
Volume
V - ALSEP
Volumes
- Mass
1 and
Performance
Rule Redlines
Data
Data
and
Performance
Mission
Properties
II
of the
follows:
will
Book
Part
Volume
missions
Book
I - Constraints
and
II - Launch
Mission
II - LM
limitations
Volume
III
Data Book
for the manned
are defined
as follows:
Data
Rule
Redlines
Book
Book
Book
present
operational
spacecraft.
information
A brief
discussion
on
of
the
the
capabilities
purpose
and
and
scope
of
PURPOSE
1.2
The purpose
of
per mission
for use
mission
simulations,
for
for
consumable
the launch
to
these
data
this document
is to provide
spacecraft
mass properties
data
in the mission
planning
activities,
trajectory
documentation,
and to provide
all necessary
information
and documentation
loading.
The
configuration
will
each spacecraft.
actual
consumables
be
data
mass
provided
contained
properties
based
Mass properties
loading.
on
data
the
will
herein
represent
and consumable
actual
be
weight
maintained
the latest
predictions
loadings.
Updates
and
balance
data
and
updated
through
Section
2.0 presents
relevant
spacecraft
configuration
locations
which
may be useful
in describing
the location
of
components
and
configuration.
the
relationship
of
coordinate
systems
in
drawings
various
the
launch
for
the
and station
spacecraft
and
docked
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,
Sections
independent
In addition,
in
right
4.0
docked
and
consumable
CM ablator
determining
Data
the
CM
mass
5.0
configuration,
contain
the
consumables
loading
information
material
data are
properties
during
normal
mass
for the
provided
entry,
properties
and
for
data
launch
and
aborts.
mission
CSM and LM, respectively.
in Section
4.0 to aid the
user
reentry.
Amendments
to this document
will be made by page additions
or replacements.
changed
by an amendment
will be denoted
by an amendment
date
in the upper
hand
corner
and
a vertical
bar
in the
i-i
page
margin
to
locate
the
change.
SNA-8-D-027(III)REV
2
r
L
L
Amendment
10/30/69
TABLE I-I
72
SELECTED ABBREVIATIONS AND ACRONYMS
ACT
ACQ
ALIGN
ANG
ASCT
APS
A/S
ASSY
Activation
Acquisition
Alignment
Angle
Ascent
Ascent Propulsion
Ascent Stage
Assembly
BIOINST
Bioinstrumentation
CAN:i
CAM
CK
CIRC
CSC
COMPT
CDR
CM
CMP
CSM
COMM
CSI
CWG
CONT
CLSRC
Cannister
Camera
Check
Circularization
Close-Up
Stereo
Camera
Compartment
Commander
Command Module
Command Module Pilot
ConTnand Service
Module
Communication
Concentric
Sequence Initiation
Constant
Wear Garment
Container
Contingency
Lunar Sample Return
DSEA
DECONTAM
DEPL
DSCT
DOI
DPS
D/S
DOCK
Data Storage Electronic Assembly
Decontamination
Depletion
Descent
Descent Orbit
Insertion
Descent Propulsion Subsystem
Descent Stage
Docking
EOI
ELECT
ECU
EQUIP
EXCL
EXC
EXP
EV
Earth Orbit Insertion
Electrical
Environmental Control Unit
Equipment
Exclude
Excursi on
Experiment
Extravehicul
ar
FWD
Forward
HASS
Hasselblad
INDIC
INFLT
Indicator
In-Fl i ght
Subsystem
1-2
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SNA-8-D-O27(III)REV
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Anmndment
10130169
TABLE I-I
(Continued)
ICG
IV
In-FLight
Coverall
I ntra vehi cul ar
JETT
Jetti son
LES
LEV
LV
LH
LEB
LIQ
LEC
LM
LOI
LS
LMP
LUN
Launch Escape System
Launch Escape Vehicle
Launch Vehicle
Left Hand
Left Hand Equipment Bay
Liquid
Lunar Equipment Conveyor
Lunar Module
Lunar Orbit Insertion
Lunar Surface
LM Pilot
Lunar
MC
MECH
MCC
Main Chute
Mechanism
Midcourse
Correction
N/A
Not
OPS
Oxygen Purge System
PR
P-GA
PROC
Pair
Pressure Garment Assembly
Procedure
RAD
RCS
RELOC
RESTR
RT
RH
RHEB
Radiation
Reaction Control System
Relocation
Restraint
Right
Right Hand
Right Hand Equipment Bay
SRC
SCRS
SEP
SM
SLA
SPS
S/C
STG
STORE
STOW
Sample Return Container
Scissors
Separation
Service I.odule
Service Hodule LM Adapter
Service Propulsion System
Spacecraft
Stage
Storage Tank
Stowage
Garment
Available
1-3
11 !1
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SNA-B-D-027(I II)REV 2
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Amendment
I0/30/69
TABLE
I-I (Continued)
SUBSYS
SUMP
SURF
SYS
RSS
Subsystem
Sump Tank
Surface
System
Root Sum Square
TEMP
TBD
TEl
XFR
TLI
Temporary
To Be Determined
Transearth Insertion
Tranfer
Translunar Insertion
TRANS
TRANS/DOCK
Transposi ti on
Transposition
and Docking
UMB
UPR
UEB
UCTA
Umbil ical
WT
Waist Tether
With
Without
w/
w/o
72
Upper
Upper Equipment Bay
Urine Collection Transfer
i-4
Assembly
SNA-8-D-O27(III)REV
2
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2.0
This
section
locations
craft
and
provides
which
may
components
docked
relevant
be
and
spacecraft
useful
the
in
for
data
presented
are
i.
Apollo
Vehicle
2.
Saturn
V Vehicle
configuration
describing
relationship
configuration
Configuration
CONFIGURATION
the
of
Block
II
in
Coordinate
location
coordinate
CSM
the
drawings
various
systems
spacecraft
following
of
and
and
in
categories
space-
the
Lunar
station
launch
Modules.
and
order:
System.
Outboard
Profiles
and
Reference
Dimensions.
3.
Apollo
Spacecraft
Locations,
4.
Lunar
and
Consumables
4.0
and
data
must
sion
in
and
Module
Reference
CSM
Stations,
Consumables
Reference
Tank
Stations,
LM
Consumables
Tank
Locations.
mass
properties
data
for
5.0,
be
Section
respectively,
compared
3.0
of
to
to
the
this
the
the
Thrust
CSM
Chamber
and
LM
These
consumable
actual
Chamber
Locations.
volume.
onboard
determine
Thrust
may
Locations
be
consumables
loading
mission
data
tanked
found
in
mass
for
Sections
property
each
consumables
mismass
properties.
2-1
SNA-8-D-027(III)REV
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Figure
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Apollo
DIAMETER
Spacecraft
Reference
Dimensions
2--'3
SNA-8-D-027(III)REV
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STA 4240.792
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Figure
2-3. Saturn
AlL
FIELD SFLICE
V/Apollo
Configuration
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Amendment
86
9110170
3.0
The
mass
diction
SPACECRAFT
property
of launch
data
have
been
been
organized
presented
of
by
MASS
data
specified
loglcally
according
to basic
individual
and
of spacecraft
mass
properties
These
data
represent
supplied
perty
data
to NASA
are
at any
the
by
mission
time
in
composite
by
IJ
Section
3.1
Mission
G
2.
Section
3.2
Mission
H1
3.
Section
3.3
Mission
H2
4.
Section
3.4
Mission
H3
5.
Section
3.5
Mission
J1
L
L
each
mission
and
and
pre-
spacecraft.
the
reflect
products
of
The
tables
have
data
are
the variation
inertia
to reasonably
the mission
the
the best
In addition,
to
user
of
BY MISSION
as a
predict
space-
profile.
the
detailed
contractors.
mass
properties
Spacecraft
mass
pro-
as follows:
1.
:L:" :L
for
spacecraft
the
DATA
represent
profile.
results
I
3-1
11 !1
Apollo
to enable
(MSC-ASPO)
presented
section
of Inertla_
weight
LOADING
properties
composite
moments
AND
this
mass
organized
craft
data
in
configuration
centers-of-gravlty,
function
PROPERTIES
L
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SNA-8-D-027
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Amendment llO
7/19/71
SUPPLEMENTARY
General
Comments
Inertia
to be
data
applied
shall
All
initial
propellant
The
(+)
or
is
TO
to
dispersions
(-)
added
be
Tables
are
used
3.1-1
PROPERTIES
through
TABLES
3.1-8:
+10%.
as
30
deviation
are
following
or
MASS
total
the
subtracted
values.
name
from
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of
the
an
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indicates
preceding
that
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total.
3.1-i
angles
for
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abort
sequence
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=
-0.524
3.1-2
L_I propellants
are
for
all
configuration
The
Mass
each
docked
R.
mass
in
Spectrometer
SPS
G.
firing
and
following
Spectrometers
properties
high
for
end
of
the
where
the
Gamma-Ray
For
are
no____t
deployed.
the
M.S.
and
tanks,
CSM
all
the
G.R.
shown
Y-Bar
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in
865.1
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28.0
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231.3
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863.1
341.7
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198.8
-94.9
3.1-7
CSM
and
3.1-8,
and
LM
33.0
and
the
Apollo
M.S.
individual
Coordinates.
-57.0
3.1-8
consumables
changes
are
presented
in
Tables
3.1-7
and
respectively.
3.l-I
1i
after
the
(in)
45._
Spectrometer
vehicle.
Z-Bar
(in)
Gamma-Ray
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deployed
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Spectrometers
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X-c.g.
controlling
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other
The
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(greatest
is
Spectrometer
D.O.I.
Weight
Tables
SEQUENTIAL
weights
sign
to
SM/SPS
gimbal
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Table
APPLICABLE
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item
Table
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111
7/22/71
XA
COORDINATES
CSM
112
TABLE
LEV
DETAIL
(TILTED)
MASS
MASS
The
following
Delta
LES
information
motor
down
PCM
PCM
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PROPERTIES
HIGH
ALTITUDE
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motor
motor
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3.1-4
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Amendment
110
7/19/71
TABLE
CSM
(To
be
112
used
properties
CONSUMABLES
in
3.1-7
WEIGHT
conjunction
Table
CHANGE
with
CSM
Earth
To
Orbit
Pre
Consumable
Trans/Dock
sequential
mass
3.1-2).
EVENT
From
SUMMARY
Weight
Amount
Change
Remaining
Total
Usage
(Pounds)
(Pounds)
(Pounds)
SM-Hydrogen
Tank
Tank
1 &
2
3
-1.6
53.6
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27.0
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625.7
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315.9
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35.8
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36.0
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Tank
I &
Tank
3
CM-Waste
H20
CM-Potable
Pre
Post
Trans/Dock
Trans/Dock
Post
Pre
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L.O.I.
2
H20
SM-RCS
-70.6
1,265.7
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SM-Hydrogen
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1
Tank
3
&
2
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48.9
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17.7
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564.3
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234.4
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Tank
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2
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L.O.I.
D.O.I.
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3.1-48
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1,113.6
SNA-8-O-027(III)
-222.7
REV
3
Amendment
7/19/71
TABLE
CSM
112
(To be used
properties
3.1-7
CONSUMABLES
(CONTINUED)
WEIGHT
in conjunction
Table 3.1-2).
with
EVENT
From
Pre
Post
To
D.O.I.
D.O.I.
Post
Consumable
D.O.I.
CSM/LM
SM-SPS
Sep.
110
CHANGE
CSM
SUMMARY
sequential
mass
Weight
Amount
Total
Change
_Pounds)
Remaining
(Pound#)
Usage
(Pounds)
-i,561.4
12,617.7
-27,861.6
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Tank
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1 & 2
3
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44.1
16.8
I & 2
3
-22.9
-13.5
534.6
219.6
-98.6
-97.0
-i14.7
+6.0
-3.8
998.9
30.0
-337.4
+3.0
5.0
1 & 2
3
-0.1
-0.i
44.0
16.7
1 b 2
3
-0.7
-2.3
533.9
217.3
-23.7
975.2
SM-Oxygen
Tank
Tank
SM-RCS
CM-LiOH
CM-Food
Fecal
CSM/LM
Sep.
Pre
Circularization
-10.0
SM-Hydrogen
Tank
Tank
-ii .2
-I0.9
SM-Oxygen
Tank
Tank
SM-RCS
Pre Circularizatlon
Post CircularIzatlon
SM-SPS
Post
Circularization
Pre
SM-Hydrogen
Plane
Charge
Tank
Tank
-277.9
12,339.8
-361.I
-28,139.5
1 & 2
3
-11.5
-2.5
32.5
14.2
1 & 2
3
-83.6
-33.4
450.3
183.9
-182.9
-132.7
-112.0
+3.0
863.2
8.0
-473.1
SH-Oxygen
Tank
Tank
SH-RCS
Fecal
3.1-49
SNA-8-D-027(III)REV 3
Amendment
110
7/19/71
TABLE
CSM
(To be
112
used
properties
3.1-7
(CONTINUED)
CONSUMABLES
WEIGHT
in conjunction
Table
CHANGE
with
CSM
SUMMARY
sequential
Weight
EVENT
From
Pre
Post
To
Plane
Change
Plane
Change
Post
Consumable
Plane
CSM/ASCT
Change
Dock
mass
3.1-2).
Change
_Pounds)
-1,133.8
SM-SPS
Amount
Total
Remaining
(Pounds)
Usage
_eounds_
11,206.0
-29,273.3
SM-Hydrogen
Tank
Tank
1 & 2
3
-1.4
-0.3
31.1
13.9
-24.1
-13.7
1 & 2
3
-10.6
439.7
-193.5
-4.0
179.9
-136.7
-87.1
-4.3
+12.0
+3.1
776.1
-560.2
-14.3
1 & 2
3
-8.4
-1.9
22.7
12.0
-32.5
-15.6
1 & 2
3
-60.5
-33.0
379.2
146.9
-254.0
-169.7
-55,5
720.6
47.0
14.1
-615.7
SM-Oxygen
Tank
Tank
SM-RCS
CM-Food
CM-LiOH
CM-Fecal
CSM/ASCT
Dock
Pre
Orbit
Shaping
42.0
ll.1
SM-Hydrogen
Tank
Tank
SM-Oxygen
Tank
Tank
SM-RCS
CM-LiOH
CM-Fecal
CM-Food
Pre
Post
Orbit
Orbit
Shaping
Shaping
Post
Pre
Orbit
T.E.I.
Shaping
+5.0
+3.0
-3.8
SM-SPS
-243.9
-18.1
10,962.1
-29,517.2
SM-Hydrogen
Tank
Tank
i & 2
3
-0.4
-0.I
22.3
ii.9
-32.9
-15.7
Tank
1 & 2
Tank
3
-2.8
376.4
-256.8
-1.7
145.2
-171.4
-36.3
684.3
-652.0
SM-Oxygen
SM-RCS
3.1-50
SNA-B-D-OZ7(III)
REV 3
Amendment
110
7119171
TABLE
3.1-7
CSM
112
(To be used
properties
CONSUMABLES
(CONCLUDED)
WEIGHT
in conjunction
Table 3.1-2).
with
CHANGE
CSM
SUMMARY
sequential
Weight
EVENT
From
Pre
T.E.I.
Post
Post
T.E.I.
T.E.I.
SM-SPS
SM Jettison
Amount
Change
(Pounds)
Consumable
To
mass
Total
Remaining
(Pognds)
-9,366.8
Usage
(Pounds)
.
1,595.3
-38,884.0
SH-Hydrogen
Tank
Tank
1 & 2
3
-10.3
-2.9
12.0
9.0
-43.2
-18.6
1 & 2
3
-82.9
-49.2
293.5
96.0
-339.7
-220.6
-769.8
SM-Oxygen
Tank
Tank
SM-RCS
SM Jettison
CM
@ Entry
CM @ Entry
CM
@ M.C.
CM
@ Impact
CM @ M.C.
Deploy
Deploy
-117.8
566.5
CM-LIOH
CM-Food
CM-Fecal
+13.0
-7.3
+4.6
60.0
18.7
CM-RCS
-11.6
233.4
-11.6
CM-RCS
-30.7
202.7
-42.3
CM-RCS
-202.7
0.0
-245.0
-25.4
3.1-51
IS
II
L
L_
Ii
L
I/
L_
L
li
SNA-8-D-027(III)
Id
L
t_
li
1.I
K
ii
REV
L
3
L
L
Amendment 110
7/19/71
TABLE
LM-IO
(To be used
in conjunction
with
the
3.1-8
CONSUMABLES
LM
CHANGE
sequential
mass
EVENT
From
To
Earth
Orbit
Consumable
CSM/LM
Separation
SUMMARY
properties
Weight
Change
(Pounds)
Tabl e 3.1-_)
Amount
Remaining
(Pounds)
Total
Usage
(Pounds>
D/S-Oxygen
D/S-Water
LM-RCS
-1.0
-12.0
-5.0
92.8
396.0
600.4
-1.0
-12.0
-5.0
CSM/LM
Separation
Pre
P.D.I.
D/S-Oxygen
D/S-Water
LM-RCS
-0.6
-23.0
-50.7
92.2
373.0
549.7
-1.6
-35.0
-55.7
Pre
LM @ Touchdown
D/S-Oxygen
D/S-Water
LM-RCS
-0.I
-2.0
-90.0
92.1
371.0
459.7
-1.7
-37.0
-145.7
P.D.I.
LM-DPS
LM
-18,790.5
-18,790.5
@ Touchdown
A/S
@ Lift-Off
LM-RCS
A/S
@ Lift-Off
A/S
in Orbit
LM-APS
A/S
in Orbit
A/S
Pre
A/S-Water
-8.0
77.0
-8.0
A/S-Oxygen
LM-RCS
-0.2
-44.6
4.8
410.1
-0.2
-195.3
LM-APS
-35.4
244.7
A/S
Pre
T.P.I.
A/S
Post
A/S
@ Docking
T.P.I.
T.P.I.
T.P.I.
-5.0
694.8
-4,942.7
454.7
-150.7
280.1
4,942.7
A/S
Post
A/S
@ Docking
A/S-Water
A/S-Oxygen
LM-RCS
-7.0
-0.3
-70.3
70.0
4.3
339.8
-15.0
-0.5
-265.6
A/S
Jettison
A/S-Water
-20.0
50.0
-35.0
3. ]-52
4,978.1
SNA-8-D-027(III)REV 3
t-. r,, .
CP
3.1-53
U
!1
1_ ld
L:
E
L
L
E
Li I_ IL _
SNA-B-D-027(III)REV 3
li l! K
L.
L
L
L
C',d
Ec'J
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I/_&lJ
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0
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o
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s
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-JZ
u_e,
I°
'T
z
0
3.1-54
SNA-8-D-027(III) REV 3
k...
I_
L
Amendment
7/19/71
TABLE
MISSION
J-i
3.1-9
COMMAND
(CONTINUED)
MODULE
SPACECRAFT
AREA
X
STOWAGE
VOLUME
CENTROIDS
112
Y
Z
A1
i011.0
-21.0
2
i011.0
-22.0
1019.0
-22.0
8.0
3
1016.0
-24.0
28.0
4
1015.0
-7.0
28.0
5
1015.0
9.0
28.0
6
1017.0
26.0
28.0
7
i011.0
22.0
8
i011.0
21.0
-23.0
9
1013.0
0.0
16.0
A2
ISA
-22.0
8.0
8.0
Top
of
A1
1017.0
-21.0
Top
of
A2
1019.0
-22.0
Top
of
A7
1019.0
22.0
8.0
Top
of
A8
1020.0
25.0
-8.0
Top
of
A9
1016.0
0.0
16.0
1014.0
0.0
8.0
Between
PGA
& A9
-22.0
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
L.
H.
Cir.
R.
Crew
Crew
H.
Crew
Station
Station
Station
110
1043.0
39.0
-24.5
-43.0
-11.9
1043.0
0.0
-ii.9
1043.0
24.5
-11.9
3.1-55
SNA-8-D-027(III)REV
3
Amendment 1I0
7/19/71
TABLE
MISSION
J-i
COMMAND
The following
stowage
stowage
volumes.
with
3.1-9
(CONCLUDED)
MODULE
locations
STOWAGE
have
NOMEN CLATU RE
Food
Food
Food
& Center
Entry
Location
Forward
Hatch
Container
Container,
RI2
(In-flight
Location)
Helmet
Stowage
& Accessory
Bags (In-flight
Location)
Helmet
Stowage
and Accessory
Bags (In-flight
Location)
Helmet
Stowage
and Accessory
Bag (In-flight
Location)
CO2 Absorbers
(2)
CO2 Absorbers
(4)
CO2
CO2
CO2
CO2
CO2
CO2
Absorbers
Absorbers
Absorbers
Absorbers
Absorbers
Absorbers
-
centroids
not
associated
X
Y
Z
1069.0
1060.0
1018.0
1018.0
25.0
26.0
23.0
-23.0
29.0
32.0
-50.0
-50.0
Top of Area A8
On RH & Ctr.
1020.0
25.0
-8.0
Sleep Restraint
L3
1020.0
1048.0
25.0
-47.0
-22.0
12.0
1050.0
i011.0
-27.0
22.0
39.0
8.0
RHEB
On Aft Bulkhead
Under Ctr. Couch
Aft Bulkhead
Under LH Couch
1039.0
1015.0
47.0
0.0
12.0
-20.0
1015.0
1018.0
0.0
-24.5
-6.0
-15.0
RH
1034.0
41.0
-21.0
BI
A7
Container
CENTROID
volume
LEB
LEB
Aft UEB
Aft UEB
Container
Container
Container
Fecal
Stowage
PGA Container
unique
LO CAT ION
G&N Signal
Cond. Panel
Display
Keyboard
Sleep
Restraint
Assy - Rt. & Center
Sleep
Restraint
Assy - Left
Entry
Locations
Sleep Restraint
- RH
ITLSAIV (CMP)
VOLUME
Girth
Ring
- LH
U2
1033.0
-23.0
-50.0
-
BI
1050.0
-27.0
39.0
L3
ECU
A3
A4
A5
A6
A9
1048.0
1031.0
1016.0
1015.0
1015.0
1017.0
1013.0
-47.0
-48.3
-24.0
-7.0
9.0
26.0
0.0
12.0
19.6
28.0
28.0
28.0
28.0
16.0
1031.0
1031.0
-8.0
13.0
39.0
39.0
1022.0
-8.0
6.5
39.0
27.5
1017.4
-4.4
27 .i
Ctr.
RH
In
(4)
(4)
(4)
(4)
(4)
(4)
B5
B6
Order of Locations Used in
Sequential
Mass
Properties
Tables
for CO2 Absorbed
B5
1031.0
First
8.0 ib CO2 Absorbed
Second
16.0 ib C02 Absorbed
Remainder
CO2 Absorbed
(B6, A9)
Composite
tion
3.1-56
L
L
Loca-
SNA-8-D-027
L,
L1
(III) REV
3
L
f_
L
Amendment
1 I0
7/19/71
TABLE
MISSION
J-i
LUNAR
3.1-9.1
MODULE
STOWAGE
VOLUME
CENTROIDS
LM-10
DESCRIPTION
X
Y
Z
280.0
263.5
-19.0
-20.6
13.5
14.9
240.5
270.3
265.9
-15.3
-15.0
-20.7
13.3
19.0
-6.0
LM Medical
Pkg
Boots & Purge Vlv-Upper
Boots & Purge Vlv-Lower
257.4
257.5
265.9
273.7
281.0
273.7
-20.7
-20.0
-20.0
-20.4
-20.0
-20.0
-6.0
-18.0
-18.0
1.2
-8.5
-8.5
In-Flight
270.3
-15.0
19.0
260.0
280.0
221.8
278.5
250.0
272.6
288.0
250.0
262.4
272.0
300.0
-37.0
0.0
-I.0
-ii.0
11.5
14.8
0.0
8.0
19.8
0.0
0.0
28.0
-i0.0
29.5
23.0
31.0
17.3
-24.0
-11.8
4.2
-18.0
0.0
239.6
257.0
244.5
235.5
242.5
242.8
237.9
235.5
228.0
-5.5
-30.0
-36.6
-35.5
-35.5
-35.4
-33.6
-37.6
-40.2
-14.8
27.5
31.4
38.5
38.6
44.7
55.0
46.6
43.2
229.5
229.5
237.8
218.5
292.0
-35.5
-35.5
-37.8
-22.0
-21.0
39.0
35.0
31.5
43.4
38.6
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
FID
FIE
FIF
FIG
FIH
Flight
Data File
PLSS-Recharge
Star
ICG, Elect.
Harness
In-Flight
ISA
OPS-Upper
OPS-Lower
FIJ
FIK
F2
F3
UCTA Clamp
Empty
Drogue-Abandon
LM
COAS-Manned
Pos.
Jett Bag (4) & CLSRC
PPK & Standard
Flag
ISA
Items
DSEA
ISA-Aft
Eng. Cover
BSLSS,
ETB, PLSS Tool
Water Disp/Fire
Ext.
ECS Umbilicals
Carrier
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
3.1-57
SNA-8-D-O27(III)REV
3
Amendment
7/19/71
TABLE3.1-9.1
MISSION
J-i
LUNAR
MODULE
110
(CONCLUDED)
STOWAGE
VOLUME
CENTROIDS
LM-IO
AREA
DESCRIPTION
X
Y
Z
282.2
286.0
-21.0
17.8
66.6
66.6
270.3
238.0
238.4
0.0
38.0
38.6
52.8
49.8
46.0
F4
F5
COAS Earth Launch
16 MM Camera-DAC
F6A,B,C
FTA
F7B
ISA-Earth
Launch
16 MM Camera
Wedge
Monocular
FTC
F7D
F7E
FTF
70 MM Camera
Assy
70 MM Film Magazines
(4)
Neck Ring & LGC Adapters
Camera
Mount Brkt & Wrench
242.8
238.0
243.2
238.0
38.0
38.0
38.0
38.0
41.0
38.4
31.2
31.6
FTG
FTH
F7J
F7K
F7L
F7M
FTN
AOT Eyeguard
& Filter
16 MM Cam Fuse Assy w/Bag
Cont. Tiedn Webbing,
Etc.
Sample
Scale
16 MM Film Magazines
Empty
LEC-Waist
Tether
Kit
227.9
237.7
231.5
222.6
231.8
225.7
238.0
33.0
38.3
35.4
32.3
36.0
32.3
38.0
31.8
45.5
41.8
42.7
47.3
53.4
53.1
F7P
F8
F9
70 MM Film
LMP Helmet
PLSS-Floor
Mags
Bag
241.0
221.0
219.9
38.0
18.0
-1.3
53.4
51.0
44.5
FIO
CDR
Bag
221.0
-18.0
51.0
Helmet
Brkt
(3)
3.]-58
SNA-8-D-027(III)REV
3
3.l-59
SNA-8-D-027
(III)
REV
3
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MSC
L_
L_
L!
L
LL
LL
U
J_
1_
/1
11
t._
_
L_
f-
L
TABLE
CONSUMABLES
LOADING
3. i-i0
REqUIKEMENTS
MISSION
SPS
I
D,es_ure
tuel
TOLERANCES
PROPELLANT
70+_5
110±4
quantity
Fue i
70±5
See
1_ _dout
(%)
Oxid i ze r
Figure
See
4.1-3
SPS
Propellant
Load
(Ib)
Loading
Fuel
15704.0
78.6
15625.4
67.6
15557.8
]Load
2Trapped
Tanked
2Trapped
3Nomlnal
Outside
Tanks
Inside Tanks
Deliverable
_Service
Secondary
Primary
Fuel
Fuel
- Quads
A, B,
A, B,
Primary
and Secondary
Figure
4.3-3.
Fuel
- System
Oxidizer
A and
- System
Pressure
Quads
A
Quads
B
Quads
C
Quads
D
Helium
- CM/RCS
4150
4150
4150
4150
70
70
70
70
System
A
System
g
Nitrogen
- SM
Primary
Secondary
4150
4150
2500
2500
Helium
Helium
- N20 h Tanks
- SM/RCS
Window
Window
A, B,
!1
I/
L
l_ l:
l/
L
- Figure
- Figure
C, D - See
Window
- Figure
Window
4.3-1.
4.3-2.
Loading
Window
-
4.3-4.
- Figure
4.3-5.
Nitrosen
Requl remen t
Weight
(Ib)
87.6
Actual
Earth Launch
Weight
(Ib)
87.6
Pressure
(PSIA)
3590
181
181
5.4
Temp
(°F)
87
74
72
6.0
4190
4200
4190
4220
71
72
71
72
70
70
1.0
4160
4110
69
65
85
85
1.3
2550
70
2550
70
6.0
iJ
SNA-8-D-027
3.1-121
!1
171.5
24740.4
Propellant
Loading
and
(°r)
70
70
70
- SPS Bottle_
- Fuel Tanks
Loading
Loadin_
Te_
(PSIA)
3600
178
178
Helium
Helium
RCS
Loading
Loading
- Quads
B - See
9Helium
Consumable
C, D - See
Module
A and
Oxidizer
25035.6
123.7
24911.9
RCS Propellant
C, D - See
B - See
4.1-4
Fue I
15664.0
78.6
15585.4
67.6
15517.8
24968.3
171.5
24796.8
Oxidizer
5Command
Figure
Actual
Requiremen, t
Oxidizer
25092.0
123.7
Module
- Quads
112
J-i
Temperature
(°F)
Fuel
Oxidizer
(PSIA)
Oxidizer
110±4
AND
Amendment
7/24/71
E
H
I,,:
i
U
li
H
E
(III) REV
L
L
3
L
L
TABLE
3.1-i0
ConDand
Module
Pressure
900±50
and
GOX
Earth
.
Module
Hydrogen
Req.
Per
,,,(pounds)
Tank
Hydrogen
Tank
Tank
Tank
1
2
3
29.3
29.3
29.3
Oxygen
Tank
Tank
Tank
1
2
3
330.1
330.1
330.1
Launch
Weight
35.0
30.0
3.7
8Service
Loading
Water
Loading
Requirement
Weight
(ib)
(pSIA)
Waste Water6
Potable
Water ?
C M/GOX
Amendment
iI '
7/2/i /7]
(CONTINUED)
6.7
(ib)
(Entry)
and Oxygen
Earth
Launch
Per
Weight
Tank
(lb)
Actual
'
Rer
Tank
27.6
27.6
27.6
27.3
316.6
316.6
316.6
313.9
313.9
(ib)
25 .6
27.3
313.9
NOTES:
llndicated
propellant
load
prior to actual
loading.
is accomplished.
2See
Section
3See
Table
4See
Section
4.1
for
3.1-13
4.2
explanation
for
for
loading
SM/RCS
sion Planning.
Actual
in Table
3.1-15.
5See
Section
4.2
for
is based on nominal
pressure
This number
will be updated
loads
CM/RCS
trapped
SPS
loads
CM/RCS
and
loads
and
loads
uncertainties
and
uncertainties
uncertainties
and
uncertainties
6Launch
Rule
Redlines
determine
lift-off
values.
7Launch
Rule
Redlines
determine
lift-off
values.
8Launch
Mission
H 2 and
Rules
will
propellant.
uncertainties.
SM/RCS
sion Planning.
Actual
in Table 3.1-14.
of
and temperature
after loading
determine
minimum
lift-off
to
be
used
will
to be
used
will
in His-
be published
be
quantities
in Mispublished
for
02 .
9CSM helium
and nitrogen
should be loaded
in accordance
with loading
windows
contained
in CSM/LM
Spacecraft
Operational
Data Book, Volume
Part 2, SNA-8-D-027(1)
P2.
3. ]-] 22
U
II E
E
L: E
L
L
E
I,
SNA-8-D-027(III)REV
I; L; E
h' U
U
3
I
/a
L
6___
i
TABLE
SPS
Amendment
7/19/71
3.1-11
PROPELLANT
LOAD
CALCULATION
FUEL
1.
Enter
Item
2.
Use Fisures
4.1-3
pellant
load
for
and
4.1-4
above
quanClCy
Nominal
propellant
(use
temperature
-
3.
SPS Quantity
C - Percent)
4.
Cubic
5.
Calculated
6.
Adjustment
due
?.
Resulting
item
5,
actual
less
item
SPS
Oxidizer
feet
of
Readout
density
density
propellant
density
to
SPS
FUEL
at
from
PSIA
(Table
to obtain
readout,
3.1-12
(item
Table
PUGS zero
adjust
load
i00.7
pro15,688.0
2 divided
3.1-12
OXIDIZER
100.8
at
loading
temperature
graph
below)
(ib/ft3)
propellant
6) (pounds)
SPS
110
by
item
89.97
56.46
item
f
25,042.0
3)
(lb/ft
3)
278.33
277.86
89.94
56.37
(pounds)
(item
4
times
15,664.0
Propellant
Temperature/Density
at 110+5 PSIA
25,035.6
Graph
.[
,IIIT_
OXIDIZER[[
D
E
N
S
I
T
Y
90.
.
90.
"_
90.
•
-:L_2
T
90 ....
--
LB/FT 3
90.°5el.
'-- --
89.9
_56.
_
tt_
ii
89.8
_56.
89.7: g6 +.. ,FH
Temperature
llO
Degrees
3.1-123
F
SNA-8-D-027(III)REV
3
O
4-)
°°.
r,_
OJo'_
E_
e- t,,,
aJ
E
4J
,-4
s
0
_
m
O
m
0
'_,_
I
.-_
I
O
04)
aJ
_
.,-i
4...
I._o
H
Q_
"_
.-4
_)-_
_0
_U
m
0
I
I
S
0
m
I
I
0
_0
s
_
t_
I
_
_._
_>
._
_-,4
m
S
4.1
_
U
_
U
!
_o._
._ ._ o _
4J
e,m _
RI
o
W
G
_
Ca
0
O0
_J
¢-,
o
e.'
eN
NO
NO
0
C
iJ
G
o
0
c,'I
00"(0<0<
o
¢',.I
r-i
I
r_
0
O
_
o
O
O
_
I
G
•
O
I.I
•,.4
Z
D,
oi
_b.41
_o
_
O
O
_
_U
m ,,_
I
_4
QJI
GI
_
_., o,.,
El
O
_
O
_'
(.J
M
O
8
,,,.I
0
O
,--I
N
o_,
_-
_._
0
8
0
_
u_
O
I
I
,._,_"
I
I.I
o
_
m
,.-4
m
_
m
,
_1_
G
I
nl
_U
"c_
e_
._
t_ o
_
• J
'.i-i
O)
I
I.,i
:>r+
C3.. _
_
I'_ "e'*
"a
_
l.'l
r_
Oa .,.'_
I..i
I
m_u
3.1-124
_
"_
O.I C
O0 O0
+0"_
,I..I 09
crm
SNA-8-D-027
_
,._
(III) REV
3
,
I
0
e-p..
4Jr_
E,-c-f_
E
co
_11 _
,J
•
0
I.i
_l
0
I
0
0
13.
_
CO
I
.®
13,.,1-
_,_o
El
.,-_ _3
I
•
0
>
I=,--I
_; "_
0
_
m
N
_
_3 .M
0
_
m
m
4-1
0
>-,:_
m
Nu
Z
0
¢j
¢xl
,.4
I
P4
;I 1:1
,-1
c14
_J
I
t_l
I
_
_
0
0
l.l
>
0
I
I
¢1
u_ m
v) I_
aJ
:3
I
"
_
_-_
"_
_
_-_ _
_I ¢-_
I,.i
3.1-125
ILl
ILl
JU
_
L
L
E
L
L
ld
L:
i_
_l
0
_.,
i_.
SNA-8-D-O27(III)REV
L;
li
_
E
L,' L
L
3
;.
TABLE
SPS
F
3.1-13
PROPELLANT
Amendment
1 I0
7/19/71
UNCERTAINTIES
•
ITEM
LOADING
Tank
FUEL
(ib)
UNCERTAINTIES
Volume
Temperature
Standpipe
Gauge
Height
Propellant
Density
Batch
(±2.0°F)
Gauge
(±0.35%
Measurement
Density
Loading
of Gaugeable)
(i)
(I)
Pressure
(i)
±39
±18
±46
± 6
±i0
±54
±86
+- 5
± 5
± 0
±
± 8
±14
RSS
m,
Loading
NOTES :
+_106
i
(I)
on Propellant
of 7iiBht
TOTAL
0
±123
,
Specification
Tolerance
(ib)
±24
± 63
TOTAL
OXIDIZER
±0
(2)
Temperature
+0
(i)
Data
(2)
Loading
nominal,
variable.
_+123
UNCERTAINITY
will
+0
-0
0
Load
LOADING
± 0
be known
after
specification
this
loading
is accomplished.
is an allowable
number
is added
3.1-126
to the
tolerance
loading
about
uncertainity
SNA-8-D-O27(III)REV
3
L
IE._
Amendment
110
7/19/71
3.1-14
TABLE
COMMAND
MODULE
RCS
LOADING
PARAMETERS
AND
CALCULATIONS
This table will be completed
when loading
is accomplished.
For Mission
Planning,
reference
should be made to Section
4.2 for nominal
load, loading
tolerances,
trapped
and deliverable
propellants.
FUE_._L
Tank
A.
Tank
B.
Liquid
C.
Total
D.
Initial
Weight
in Bleed
Prior to Loading
(Ib)
E.
F,
Volume
Final
After
Line
@0.0
PSIA
Volume
(in 3)
A + B (in 3)
OXIDIZER
Tank
1474.7
(In 3)
Weight
in Bleed
Loading
(ib)
A
B
1471.7
Tank
A
Tank
1786.9
B
1791.0
21.0
17.4
17.1
16.4
1495.7
1489.1
1804.0
1807.4
149.0
103.8
195.O
115.2
104.8
59.6
116.7
36._
44.2
44.2
78.3
7t_.3
44.2
44.3
77.6
Unit
Unit
Propellant
Load (item
than
E Weigh Tank)
D less
7t_.4
G.
Propellant
H.
Loading
Load
by P.V.
Temperature
(°F)
72
72
I.
J.
Specification
Load @ 70±5°F
Propellant
(ib)
Total f24/RCS Propellant
Load from Item G above
K.
Maximum
Trapped
L.
Nominal
Deliverable
88.4
(ib)
Propellant
(Ib)
(ib)
3.1-127
69
69
156.6
88.5
156.0
13.3
23.1
75.2
132.9
SNA-8-D-027
(III) REV
3
L
i--
Amendment
II0
7/19/71
TABLE
3.1-15
SERVICE
MODULE
RCSLOADING
SUMMATION
This table will be completed
when loading
is accomplished.
should
be made to Section
4.2, for nominal
nominal
deliverable
propellants.
ning, reference
tolerances,
and
_uad
A
(Ib)
quad
Secondary
Fuel
Primary
Fuel
&h._
69.0
Total Fuel
Maximum
Trapped
109.3
2.1
Nominal
Deliverable
107.2
Total Oxidizer
Maximum
Trapped
Nominal
Deliverable
225.8
4.5
221.3
quad
_0.7
'2.3
40.3
69.O
Total Fuel
Maximum
Trapped
109.3
2.1
Nominal
1072
Deliverable
Total Oxidizer
Maximum
Trapped
Nominal
Deliverable
quad
40.3
69.4
109,7
2.1
Nominal
107.6
Deliverable
Total Oxidizer
Maximum
Trapped
224.6
4,3
Nominal
220.1
Deliverable
Total
Total Fuel
Maximum
Trapped
Nominal
Deliverable
*0.7
*2.3
A_7.R
8.4
429.4
Nominal
107,4
Deliverable
Total Oxidizer
Maximum
Trapped
Deliverable
Load
"2.3
._2.1&.I
4.5
PIQ
*0.7
*2.3
6
(ib)
Total Oxidizer
Maximum
Trapped
Nominal
Deliverable
3.1-128
'0.7
D (ib)
40.3
6q.2
109.5
2.1
Propellant
,1.4
224.0
4.5
219.5
Secondary
Fuel
Primary
Fuel
Total
Fuel
Maximum
Trapped
Nominal
SM/RCS
B (ib)
Secondary
Fuel
Primary
Fuel
C (ib)
Secondary
Fuel
Primary
Fuel
Total Fuel
Maximum
Trapped
For Mission
Planload, loading
_898.5
18.0
SSO.5
*4.6
SNA-8-D-027(III)REV
3
110
Amendment
TABLE
LM-IO
CONSUMABLE
LM-IO
7/19/71
3.1-16
LOADING
APS
REQUIREMENTS
PROPELLANT
Fu_l (ib)
Propellant
Trapped
Load
Outside
Tanks
5.9
Tanked
Inside
Tanks
Nominal
Deliverable
Propellant
A.
Final
B.
Propellant
C.
Nominal
at
loading
Correction
tank
0.09
=
Correction
0.15
=
off-load
amount
of propellant
the indicated
load.
is
±0.5
(PSIG)
pounds
60.3
50.3
69.0
70.25
2069.8
(ib)
2F.
Measured
(Item
(Item
(ib)
2G.
Nominal
Delta
A-40)
temperature
(ib)
Correction
Fuel
(Item
for
-
2300
Oxidizer
-
0.8979
(GM/CC)
(GM/CC)
1.4819
0.8994
(Item
measured
(Item
-14.91
B-65)
(GM/CC)
density
density
i .55
B-65)
- -2.84
density
3315.6
1.83
-4,64
Oxidizer
per
A-40)
loading
1.16
the
at
(°F)
pressure
(Item
for
calculated
overfill
quantity
for
-
the
temperature
overfill
Fuel
for
pressure
Oxidizer
31.
TBD
TBD
tolerance
tank
Fuel
H.
3189.6
TBD
APS
The
allowable
weigh
tank.
IE.
27.7
1995.5
The following
table
should
be used
to determine
to be off-loaded
from
a full condition
to arrive
D.
3217.3
i0.0
Outage
F-G)
1.4824
-0.0015
-0.0005
density
H)
-3.45
J.
Propellant
K.
Overfill
in
2300
(Item
Target
M.
Quantity
required
N.
Quantity
to be
-I .15
H)
GSE
1.6
quantity
L.
(C+D+E+I+J)
loading
to
fill
off-loaded
KS
manifolds
(Item
K-L-M)
4.8
2065.1
3305.9
2014.2
3225.7
i0.0
15.8
40.9
64.5
NOTES:
q
ILoading
temperature
2To calculate
temperature
25°C
for
measured
Nominal
Nominal
3Correction
correction
the nominal
in °C of the
fuel).
density
This
must
will
density
measured
equation
also
be
always
measured
density
be
negative.
solve
the following
equation
where
density
(usually
4°C
for oxidizer
is valid
for
at 14.7
PSIA.
fuel density
= 0.922904-0.0009377
oxidizer
density
- 1.491539-0.0022832
for
(Ib)
8.3
2005.5
Trapped
Total
Oxidizer
3225.6
2011.4
,my
be
3.l-129
14.7
PSIA.
Therefore,
T =
and
the
(°C)
either
(°C)
positive
or
negative.
SNA-8-D-O27(III)REV
3
Amendment
TABLE
3.1-16(CONTINUED)
LM-10
CONSUMABLE
LM-IO
LOADING
DPS
REQUIREMENTS
PROPELLANT
Fuel
Propellant
Load
Trapped
Outside
Tanks
Oxidizer
48.9
7510.3
Inside
Nominal
Deliverable
Tanks
11975.0
]0.5
23.5
7499.8
Outage
TBD
Propellant
TBD
The
following
table
should
be used
to determine
off-loaded
from
a full condition
to arrive
at
the amount
the indicated
able
tolerance
±0.5
AI.
Final
BI.
Propellant
CI.
Nominal
DI.
Correction
for
tank
....
I1951.5
TBD
DPS
(ib)
12023.9
27.3
Tanked
Total
(ib_
7537.6
Trapped
110
711g/71
the
calculated
pressure
at
loading
overfill
overfill
tank
is
pounds
per
(PSIG)
temperature
quantity
for
off-load
of propellant
load.
The
tank.
47.4
(°F)
54.0
67.8
(ib)
pressure
weigh
67.45
7606.6
(ib)
to be
allow-
12182.5
2.44
7.56
Fuel
= 0.33
(Item
A1 -40)
Oxidizer
= 0.54
(Item
A1 -40)
IEI.
Correction
for
loading
temperature
Fuel = -4.25
(Item
B1
Oxidizer
= -10.5
(ltem
2FI.
Measured
2GI.
Nominal
Nl.
311.
Delta
density
(GM/CC)
density
density
Correction
Fuel
(GM/CC)
(GM/CC)
for
=
8400
Oxidizer
=
(Item
measured
(Item
8400
in
(lb)
Propellant
KI.
Overfill
L1.
Target
MI.
Quantity
required
NI.
Quantity
to be
ILoading
temperature
Fl-ltem
G1)
-25.73
0.8979
1.4819
0.8994
1.4824
-0.0015
-0.0005
density
-12.6
HI)
GSE
quantity
-4.2
H1)
(Item
J1.
-i1.9
-65)
B1 -65)
2.3
(Cl+Dl+El+ll+Jl)
loading
to
fill
RCS
off-loaded
manifolds
(Items
(APS
only)
3.8
7586.8
12163.9
7547.7
12___023.7
xxxxxxx
KI-LI-MI)
xxxxxxx
39.1
140.2
NOTES:
2To
calculate
the
correction
nominal
T - temperature
in
and 25°C
for fuel).
the
measured
always
solve
must
density
= 0.922904-0.0009377
fuel
Nominal
oxidizer
for
the
°C of the measured
This equation
is
density
Nominal
3Correction
will
density
density
measured
also
be
at
be
may
3.1-130
equation
density
(usually
4°C
valid
for 14.7 PSIA.
14.7
be
where
for oxidizer
Therefore,
PSIA.
(°C)
= 1.491539-0.0022832
density
negative.
_ollowing
either
(°C)
positive
or
negative.
SNA-8-D-027(III)
REV
3
TABLE
LM-10
System
A Fuel
System
A Oxidizer
System
System
B Fuel
B Oxidizer
-
3.1-16
RCS
PROPELLANT
42 )
Required
Ullage
Minimm
_
152.5
Requirement
Maximum _
164.5
208.2±1.9
107.4±0.9
267.0
152.5
279.0
164.5
208.2ZI.9
267.0
279.0
FUEL
Load
Trapped
Tanked
Outside
Tanks
Trapped
Nominal
in Tanks
Deliverable
LM-10
-
tank
#i
(6)
- APS
- RCS
- RCS
tank
02
(6)
tank
tank
#I
#2
(6)
(6)
- DPS
(SHe)
- DPS
(Ambient)(6)
Nitrogen
416.4
15.8
400.6
4.2
200.6
8.0
392.6
Ascent
..3050
Descent
3057
3043
69.7
69.7
1625
70.6
80+2
1600
N/A
70
1.1
-0.6
&
- tank
- tank
- tank
#i
(6)
-
#2
(6)
GOX
tank
tank
#i
(6)
-
tank
#2
(6)
Pressure
Weight
(Ib)
(7)
4PSIA)
N/A
41b)
42.5
(7)
(7)
N/A
N/A
42.5
207.0
N/A
(7)
N/A
207.0
830
83o.
2.4
2.4
845
850
(71°F)
(71°F)
46.9
46.9
2620
2620
S/A
N/A
-
Actual
Requirement
Weight
(PSIA)
S/A
#I
#2
(lb)
COX
Loading
Nominal
Pressure
Weight
51.2
Descent
COX
Descent
1.05
1.05
-
Water
Ascent
70
70
- Water
Tamp
4 "F)
68.9
69.1
3050
#I
#2
Actual
Pressure
(PSIA)
3142
3137
+0.1
0.6
tank
tank
151.0
255.8
41b)
6.6
6.6
Ascent
Descent
-
2700
27oo
(72.1°F)
(72.1"F)
NOTES:
lSee
2See
Table
Section
3.1-17
5.6
3See
Table
3.1-18
for
actual
for explanation
for
_PV ullage
calculation
280±50
cubic
inches
contained
Part
7LM-10
2,
Earth
at
items
in
the
should
earth
temperature
launch.
ascent
Initial
relationships
be
loaded
Spacecraft
shall
LM-IO
calculation.
propellants.
uncertainties.
be
loaded
provided
in
accordance
Operational
water
load
cubic
inches
per
tank.
to
be
be
in
LM/RCS
3.1-131
loading
Book,
Volume
408-0.0+10.0
loaded
determined
Table
with
Data
provide
shall
will
for
fuel
and
required
to
fill
RCS manifolds
See Section
5.6
for trapped
includes
propellant
See Table
3.1-16.
CSM/LM
SNA-8-D-027PT2.
Descent
Water
Launch.
load
trapped
should
be 166.5+50
for LM/I_S
oxidlz_r
5LM/RCS
required
load
to thruster
valves.
propellants.
6The
indicated
propellant
of
loading
3)
172.0
267.0
("F)
70
70
-
Water
(in
Ullage
107.4
208.2
Loading
Requirement
' Temp
Weight
4PSIA)
3050
3050
Consumable
tActual_
& Nitrogen
Helium
LM-IO
_
Load
(Ib)
107.4
208.2
OXIDIZER
I0.0
204.8
Pressure
- APS
_Act_ml
(in _)
214.8
Nominal
Consumable
112
43 )
Load
(Ib) 5
107.4±0.9
Propellant
Helium
Amendment
7/24/71
(CONTINUED)
pounds
Co
provide
by
the
85
windows
If,
at
pounds
prasure-
3.1-16.1.
SNA-8-D-O27(III)REV
3
I
Amendment
110
7/19/71
TABLE
3.1-16.1
°F
WATER
LOADING
DATA
LM-IO
TANKS
DESCENT
T
ECS
Po
PFI*
PFN
PSIA
PSIA
PSIA
ASCENT
TANKS
PF2
PFI
PF2
PSIA
PSIA
PSIA
39,501
39,587
46,427
46,516
46,683
46,782
39,671
39,757
46,605
46,880
46,980
47,079
47,179
60
61
11,607
11,629
22,212
22,254
39,245
39,321
62
63
11,651.
11,674
22,306
22,340
39,396
39,472
64
65
11,695
11,718
22,383
22,425
39,547
39,623
39,842
39,929
46,695
46,784
46,873
66
67
11,741
11,763
22,469
22,511
39,698
39,774
40,014
40,102
46,963
4'7,052
47,279
47,380
68
11,785
22,553
39,849
40,188
47,141
47,480
69
70
11,808
11,830
22,597
22,639
39,924
40,000
40.275
40,363
47,231
47,320
47,582
47,683
"'
71
11,852
22,681
40,075
40,451
47,409
47,785
72
73
74
11,875
11,897
11,919
22,725
22,767
22,S09
40,151
40,226
40,302
40,540
40,628
40,71S
47,499
47,588
47,888
47,990
75
76
11,942
11,964
22,S53
22,895
40,377
40,453
40,807
40,897
47,677
47,767
48,093
48,197
77
11,986
_2,937
40,528
40,987
78
79
12,009
12,031
22,982
23,024
40,604
40,679
41,079
41,170
47,855
47,945
48,035
48,299
48,404
48,510
48,124
48,615
80
12,053
23,066
40,755
41,262
48,213
48,720
NOTE:
1.
Po
-
P}I
PFN
PF2
- Pressure
- Pressure
Pressure
Initial
Gas
Pressure
Required
Required
Required
Setting
when
Loading
'Killer"
Solution.
for D/S N. Final
Fill.
After
Partial
Drain
and Refill.
2.
Primary
Reading
of PFI
using
0-60
psia Transducers
* PFI
- GF 4501
P + HEAD
if GF 4501
P low,
increase
D/S Tank
#i HEAD
- 2.502
PSI
D/S Tank
#2 HEAD
- 3.372
PSI
verified
by
to required
3.
Po,
PFI*,
may
have
(+)
one
212
lb/tank
PFN,
(i)
PF2,
PCM
PFI
Bit
as
values
read
on
as
This
above,
P
P
P
.I
.24
.24
psia
psia
psia
GF
4502
P
.24
psta
GF
4503
P
.24
psia
table
provides
of
42.5
tolerance
of
1 Bit
GF 4501
GF 4500
GP 0500
loading
a
CRT.
MID
4.
shown
GF 4501
P.
pressure.
nominal
descent
loading
of
and
ascent
tank
lb/tank.
3.1-132
ENA-8-D-O27CTII)REV
NASA-
11
!/
3
MSC
L
E
L
L
E
L
E
U
12 L, L
TI
L
&.
Amendment
LOAD
APS
1.
,
tank
Fuel
- Item
K,
12.
Density
of
temperature
13.
Propellant
volume
item
2. (it 3)
14.
(from
Resulting
6.
Off-load
7.
Propellant
(ib)
required
8.
Propellant
load
1 i0.
Iii.
112.
full
tank
amount
item
Tablp
load
Oxidizer
2065.1
N/A
N/A
N/A
N/A
N/A
N/A
] by
3.1-19)
(Ib)
2065.1
(Ib)
3305.9
43.7
to
fill
RCS
64.5
manifolds
i0.0
tank
Density
(Ib)
-
of
Item
15.8
2011.4
and
Propellant
volume
)(it
K1
3.1-16
tables
pressure
3225.6
at
13.
Resulting
14.
Off-load
15.
Propellant
full
(from
3)
Item
tank
amount
load
Table
load
12163.9
loading
(ib/ft
(divide
7586.8
9
by
N/A
NIA
N/A
N/A
N/A
N/A
7586.8
12163.9
Item
3)
Measured
density
(Ib/ft 3)
RCS
Table
off-load
temperature
P.
(ib)
PROPELLANT
Full
i0
3.1-16
(divide
Measured
density
(ib/ft 3)
DPS
Table
off-load
tables
at loading
and
pressure
(ib/ft 3)
5.
9.
CALCULATION
PROPELLANT
Full
110
7/19/71
3.1-17
TABLE
3.1-19)
(ib)
(ib)
49.2
(ib)
7537.6
140.0
12023.9
PROPELLANT
V.
Calculations
Fuel
Tank A Tank
A.
GSE
Volume
(in
B.
Initial
(PSIG)
Ullage
C.
Initial
(PSIC)
GSE
D.
Final
(PSIG)
E.
Ullage
CSE
NOTE:
18.2
33.5
17.8
29.7
33.4
33.5
35.2
34.8
1.0
1.0
0.0
0.2
33.0
31.2
Pressure
-
S/C
Pressure
30.3
Volume
IThese
Volume
items
made
prior
loading,
*Initial
instead
APS
Solve
equation
the
values
by
in
will
to
then
of
(in 3) -
steps.
(D-C)
indicated
Ullage
B
Pressure
the following
substituting
the
3)
Oxidizer
Tank A
Tank
B
& DPS
i___551.0
267______:.Q.
255.8
(A)
B-D
be
completed
loading.
the
items
0.8979
27.6
172.0
Fuel
If
a
will
only
if
density
be left
Offload
was
a
density
sample
blank.
based
is
on
a
sample
made
is
prior
density
not
to
of
0.8991
gm/CC.
3.1-133
SNA-8-D-027(III)REV
3
TABLE
LM-10
PROPELLANT
LM-10
Amendment
7119171
3.1-18
LOADING
APS
UNCERTAINTIES
PROPELLANT
Fuel
Vent
Line
Tank
Volume
Volume
(ib)
Oxidizer
+-0.2
-+0.3
+-0.8
+1.3
-+0.5
_+0.8
_+1.7
+_4.3
Density
+-0.7
+-0.5
Weight
Measurement
_+0.5
+-0.5
iLoading
Tolerance
-+0.0
+0.0
-+4.3
-+7.7
+-0.2
+0.3
-+3.62
+-5.96
-+1.70
-+2.77
+-6.49
+-15.76
Density
-+2.55
-+1.70
Weight
Measurement
+-0.5
-+0.5
iLoadlng
Tolerance
+-0.0
-+0.0
-+15.1
+-27.0
+-0.6
+-1.8
+-0.4
+-0.6
+-0.8
-+1.4
-+1.8
+-3.8
Pressure
Measurement
Temperature
Measured
Total
(+-5 PSIA)
Measurement
Loading
(+_I.5°F)
Uncertainity
LM-10
Vent
Line
Tank
Volume
Measurement
Temperature
Measured
Total
(I.5°F)
Uncertainity
LM-10
Ullage
Tank
RCS
PROPELLANT
Temperature
Calculation
and
Manifold
Volume
Total
iThese
will
be known
quantities
(ib)
PROPELLANT
(-+5 PSIA)
Measurement
Loading
Loading
DPS
Volume
Pressure
II0
after
loading
3.1-134
is accomplished.
SNA-8-D-027
(III) REV
3
TABLE
I_4-I0
APS
(To
Be
PROEPLLANT
Completed
Amendment 1 10
7/19/71
3.1-19
LOADING
by
PARAMETERS
KSC at
Loading)
Fuel
Loading
Pressure
Loading
Temperature
- Fill
Loading
Temperature
- Return
Loading
Temperature
- Tank
Number
Total
of Times
Pounds
Pounds
- PSIA
Weigh
Tank
Off-Loaded
Off-Loaded
Measured
Fuel
Measured
Oxidizer
Flow
@ 25°C;
Density
Line
Used
_GP0718
F [GPI218
(Flow
Meter
Meter
(Flow
(Weigh
Tank
PSIA
@ 14.7
3.]-]35
Fuel
Oxidizer
Not
Tank
@ 14.7
Fuel
Oxidizer
_ITT 59 Fuel
t'[TT259 Oxidizer
- Degrees
Neigh
@ 4eC;
F _58258
- Degrees
- Degrees
Using
Using
Density
Line
Used)
Meter
Not
GM/CC
PSIA
Oxidizer
75.0
65.0
67.8
70.3
70.2
70.2
68.2
69.4
1
Not
Used)
Used)
43.7
64.5
N/A
N/A
0.8991
GM/CC
_
SNA-8-D-027(III)REV
1.4819
3
Amendment Il0
7/19/71
TABLE
LM-10
DPS
3.1-19
(CONTINUED)
PP4DPELLANT
LOADING
PARAMETERS
Fuel
Loading
Pressure
Loading
Temperature
-
Fill
Loading
Temperature
-
Return
Loading
Temperature
-
Tank
One
- Degrees
_#CQ3718
_GQ4218
Loading
Temperature
-
Tank
Two
-
_IGQ3719
-IGQ4219
Tank
Used
Number
Total
Pounds
of
-
Times
Pounds
Weigh
Off-Loaded
Off-Loaded
Fuel
Density
Measured
Oxidizer
Flow
@
Density
-
25"C;
@
-
Degrees
Weigh
Meter
4"C;
Meter
Tank
14.7
Not
(Flow
(Weigh
Tank
PSIA
@ 14.7
3.l-136
I/
68.7
67.3
66.6
68.2
68.3
Fuel
Oxidizer
68.2
68.6
Fuel
Oxidizer
68.6
68.6
1
1
49.2
140.0
Fuel
Oxidizer
_TT 59
FITT259
Degrees
(Flow
@
ITT 58
F ITT258
Degrees
Line
Using
Using
Measured
62.1
PSIA
Line
PSIA
Oxidizer
Fuel
Oxidizer
Used)
Meter
Not
GM/CC
Not
Used)
Used)
N/A
N/A
0.8991
1.4819
GM/CC
SNA-8-D-027(III)REV
3
Amendment
7119/71
MISSION
Table
Table
3.1-20
3.1-21
presence
the
coordinates,
SM/SPS
burn.
J-i
MASS
PROPERTY
CSH-112/LH-10(docked)
as a function
of
DATA
II0
TABLES
mass
spacecraft
properties,
weight
for
in Apollo
L.O.I.
presents
the
CSM-112/I_4-10
coordinates,
as a function
D.O.I.
SM/SPS burn.
(docked)
mass
of spacecraft
properties,
weight
for
in Apollo
the
properties,
for
the
in Apollo
Circulartzatton
coordinates,
I SM/SPS
coordinates,
I SH/SPS
Table
3.1-22
presents
the
as a function
burn.
CSM-112
mass
of CSMwetght
Table
3.1-23
presents
the
as a function
burn.
CSM-II2
of CSM
mass
weight
properties,
for
the
in Apollo
Plane
Change
Table
3.1-24
presents
the
CSM-II2
as a function
of CaM
mass
weight
properties,
for the
in Apollo
coordinates,
T.E.I.
SM/SPS burn.
Table
3.1-25
presents
function
the
of
LM-10maas
I/4 weight
properties,
for
the
Table
3.1-26
presents
the
as a function
LM-10 ascent
of weight
Table
3.1-27
presence
function
LM-lOmass
LM weight
the
of
in
P.D.I.
LM coordinates,
DPS burn,
stage
mass
properties,
for
the
lunar
liftoff
properties,
for
the
T.P.I.
3.1-137
as
a
in LM coordinates,
APS burn.
in LM coordinates,
as a
to docking
LM/APS burn.
SNA_B_D-027
(lll) REV
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SUPPLEMENTARY
General
DATA
Comments
Inertia
to
data
APPLICABLE
be
applied
dispersions
Dispersions
shall
All
initial
propellant
The
(+)
item
Table
or
is
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added
be
sign
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used
Tables
MASS
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as
3o
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deviation
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name
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abort
sequence
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3.2-2
LM
propellants
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all
The
Mass
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docked
in
Spectrometer
each
SPS
G.R.
mass
Spectrometers
properties
high
end
configuration
firing
and
following
for
of
D.O.I.
X-Bar
(in)
Gamma-Ray
Retracted
45.4
865.1
Gamma-Ray
28.0
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17.4
Mass
Spectrometer
Retracted
Mass
Spectrometer
Deployed
CSM
and
3.2-8,
and
LM
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the
all
other
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Z-Bar
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865.1
231.3
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132.2
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47.4
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863.1
341.7
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198.8
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TABLE
LM-II
3.2-3
(CONTINUED)
CONTINGENCY
To
Be
MASS
PROPERTIES
Supplied.
3.2-14
SNA-B-D-O27(III)REV
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TABLE
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LRV
FIRST
3.2-3.1
MASS
PROPERTIES
TRAVERSE
To
Be
DEPARTURE
Supplled.
3.2-15
SNA-8-D-027(III)REV
3
Amendment
114
9/15/71
TABLE
3.2-3.1
LRV
FIRST
To
MASS
(CONTINUED)
PROPERTIES
TRAVERSE
Be
RETURN
Supplied.
3.2-16
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E
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Amendment
114
9/15/71
TABLE
3.2-3.1
LRV
SECOND
MASS
(CONTINUED)
PROPERTIES
TRAVERSE
'To Be
DEPARTURE
Supplied.
3.2-17
II I/ I/ E
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Amendment
9/15171
TABLE
3.2-3.1
LRV MASS
114
(CONTINUED)
PROPERTIES
SECOND TRAVERSE
RETURN
To Be Supplied.
SNA-B-I)-O27(III)REV
L
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3
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Amendment
9/15/71
TABLE
3.2-3.1
LRV MASS
THIRD
(CONTINUED)
PROPERTIES
TRAVERSE
To Be
114
DEPARTURE
Supplied.
3.2-19
SNA-8-D-O27(III)REV
5
Amendment
114
9is71
TABLE
LRV
3.2-3.1
MASS
THIRD
(CONTINUED)
PROPERTIES
TRAVERSE
To
Be
RETURN
Supplied.
3.2-20
ILlE
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SNA-8-D-027
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(III)REV
3
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Amendment
9115171
TABLE
HIGH
ALTITUDE
To be supplied
3.2-21
114
3.2-4
MASS
PROPERTIES
at a later
date.
SNA-8-D-027
(III)REV
3
Amendment
114
9115171
TABLE
PAD
To
be
ABORT
3.2-5
MASS
supplied
at
PROPERTIES
a later
date.
\
3.2-22
SNA-8-D-027(III)REV
3
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1_ EE
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L.
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114
9/15/71
TABLE
SIVB
U
I/
L
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I/ h
L
MASS
3.2-6
PROPERTIES
s_-8-v-o27cI.)_ 3
H _ :
L
Amendment
114
9/15/71
TABLE3.2-7
CSM
(To
be
113
used
CONSUMABLES
in
properties
WEIGHT
conjunction
Table
with
CHANGE
CSM
Earth
To
Orbit
Pre
Consumable
Trans/Dock
sequential
mass
3.2-2).
EVENT
From
SUMMARY
Weight
Amount
Change
Remaining
(Pounds)
_Pounds)
Total
Usage
(Pounds)
SM-Hydrogen
Tank
i &
-1.6
53.6
-1.6
Tank
3
2
-0.6
27.0
-0.6
Tank
1 & 2
-7.5
625.7
-7.5
Tank
3
-0.7
315.9
-0.7
+4.8
39.8
+6.0
36.0
SM-Oxygen
CM-Waste
H20
CM-Potable
Pre
Post
Trans/Dock
Post
Trans/Dock
Pre
Trans/Dock
H20
SM-RCS
L.O.I.
-70.6
1,271.8
-70.6
SM-Hydrogen
Tank
i &
Tank
3
2
-4.7
48.9
-6.3
-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
CM-Waste
CM-LiOH
Pre
Post
L.O.I.
Post
L.O.I.
Pre
L.O.I.
H20
+4.2
+24.0
CM-Food
-6.2
Fecal
+2.0
SM-SPS
D.O.I.
-26,300.2
1,161.6
-180.8
44.0
24.0
-6.2
2.0
14,293.5
-26,300.2
SM-Hydrogen
Tank
1 & 2
-0.8
48.1
-7.1
Tank
3
-0.i
17.6
-I0.0
-6.8
557.5
-75.7
-1.3
233.1
-83.5
SM-Oxygen
Tank
i &
Tank
3
2
SM-RCS
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3.2-24
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TABLE 3.2-7
CSM 113 CONSUMABLES
(To be used
properties
WEIGHT
in conjunction
Table 3.2-2).
with
EVENT
From
Pre
To
D.O.I.
Post D.O.I.
Consumable
Post
D.O.I.
CSM/LM
Sep.
Amendment
9/15/71
(CONTINUED)
SM-SPS
CHANGE
114
SUMMARY
CSM sequential
Weight
Change
(Pounds_
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mass
Amount
Remaining
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Amendment
9/15/71
TABLE
MISSION
3.2-9
J-2 COMMAND
(CONTINUED)
MODULE
SPACECRAFT
STOWAGE
VOLUME
CENTROIDS
113
X
Y
Z
i011.0
i011.0
1019.0
1016.0
1015.0
1015.0
1017.0
I011.0
I011.0
1013.0
-21.0
-22.0
-22.0
-24.0
-7.0
9.0
26.0
22.0
21.0
0.0
-22.0
8.0
8.0
28.0
28.0
28.0
28.0
8.0
-23.0
16.0
1017.0
1019.0
1019.0
1020.0
1016.0
1014.0
-21.0
-22.0
22.0
25.0
0.0
0.0
-22.0
8.0
8.0
-8.0
16.0
8.0
BI
2
3
4
5
6
8
i050.0
1039.0
i031.0
1031.0
1031.0
1031.0
1024.0
-27.0
-38.0
-28.0
-20.0
-8.0
13.0
-38.0
39.0
37.0
40.0
40.0
39.0
39.0
37.0
L2
3
1059.0
1048.0
-44.0
-_7.0
14.0
12.0
R1
2
3
4
5
6
8
ii
13
1072.0
1072.0
1072.0
1075.0
1059.0
1048.0
1052.0
1038.0
1024.0
26.0
26.0
26.0
28.0
44.0
46.0
46.0
47.0
45.0
21.0
14.0
9.0
3.0
15.0
29.0
12.0
26.0
-26.0
UI
2
3
4
1033.0
1033.0
1033,0
1038.0
23.0
-23.0
-36.0
39.0
-50.0
-50.0
-44.0
-43.0
L. H. Crew Station
Ctr. Crew Station
R. H. Crew Station
1043.0
I043.0
1043.0
-24.5
0.0
24.5
-11.9
-11.9
-11.9
AREA
AI
2
A2 ISA
3
4
5
6
7
8
9
Top of
Top of
Top of
Top of
Top of
Between
A1
A2
A7
A8
A9
PGA
& A9
SNA-8-D-027
E
E
L
E
k
L
E
114
(llI) REV
3
Amendment
114
9/15/71
TABLE
MISSION
The
with
J-2
following
stowage
3.2-9
COMMAND
stowage
(CONCLUDED)
MODULE
locations
STOWAGE
have
Signal
Display
unique
CENTROID
volume
centroids
not
associated
volumes.
NOMENCLATURE
G&N
VOLUME
Cond.
LOCATION
X
Y
Z
LEB
1069.0
25.0
29.0
LEB
1060.0
26.0
32.0
Panel
Keyboard
Sleep
Restraint
Assy
-
Rt.
Sleep
Restraint
Assy
-
Left
Entry
Locations
Sleep
Restraint
ITLSA
- IV
- RH
& Center
Aft
UEB
1018.0
23.0
-50.0
Aft
UEB
1018.0
-23.0
-50.0
1020.0
25.0
-8.0
Top
& Center
of
On
(CMP)
Area
RH
Sleep
A8
&Ctr.
Food
Container
L3
1020.0
1048.0
25.0
-47.0
-22.0
12.0
Food
Container
BI
1050.0
-27.0
39.0
Food
Container
A7
i011.0
22.0
8.0
RHEB
1039.0
47.0
12.0
1015.0
0.0
-20.0
Fecal
Stowage
PGA
Container
Container
On
Restraint
Aft
Bulkhead
Under
Aft
Entry
Location
Forward
Hatch
Container
Container,
Stowage
Bags
and
Stowage
Bag
RH
Location)
Couch
1018.0
-24.5
0.0
-15.0
-6.0
Ring
1034.0
41.0
-21.0
-50.0
Girth
Location)
and
(In-flight
LH
U2
1033.0
-23.0
-Ctr.
BI
1050.0
-27.0
39.0
L3
1048.0
-47.0
12.0
1031.0
-48.3
19.6
-
Accessory
(In-flight
Helmet
1015.0
LH
& Accessory
(In-fllght
Helmet
Bulkhead
Under
Location)
Stowage
Bags
Couch
RI2
(In-flight
Helmet
Ctr.
Accessory
Location)
- RH
In
ECU
CO2
Absorbers
(2)
C02
Absorbers
(4)
A3
1016.0
-24.0
28.0
1015.0
-7.0
28.0
C02
Absorbers
(4)
A4
CO2
Absorbers
(4)
A.5
1015.0
9.0
28.0
CO2
Absorbers
(4)
A6
1017.0
26.0
28.0
C02
Absorbers
(4)
A9
1013.0
0.0
16.0
C02
Absorbers
(4)
B5
1031.0
-8.0
39.0
CO2
Absorbers
(4)
B6
1031.0
13.0
39.0
1031.0
-8.0
39.0
1022.0
6.5
27.5
1017.4
-4.4
Order
of
Loca-
tions
Used
Sequential
Mass
Properties
for
First
8.0
Second
Remainder
ib
16.0
C02
ib
C02
Tables
Absorbed
B5
Absorbed
CO2
CO2
in
Absorbed
(B6,
Absorbed
A9)
Composite
tion
Loca-
3.2-32
11
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SNA-8-D-027
L
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27 .i
(III)
REV
1;
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3
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TABLE
MISSION
J-2
LUNAR
MODULE
Amendment
9/15/71
3.2-9.1
STOWAGE
VOLUME
114
CENTROIDS
LM-II
AREA
X
AIA
AIB
AIC
AID
AIE
AIF
AIG
AIH
AIJ
AlL
AIK
AIDA
AIDB
AlDC
AlDD
A2
A3
A5
A6
A7
A8
A9
AI0
All
AI2
Al3
AI4
Al5
FIA
FIB
FIC
FID
FIE
FIF
FIG
FIH
FIJ
FIK
F2
F3
3.2-33
Y
Z
280.0
263.5
240.5
270.3
265.9
257.4
257.5
265.9
273.7
281.0
273.7
-19.0
-20.6
-15.3
-15.0
-20.7
-20.7
-20.0
-20.0
-20.4
-20.0
-20.0
13.5
14.9
13.3
19.0
-6.0
-6.0
-18.0
-18.0
1.2
-8.5
-8.5
270.3
-15.0
19.0
260.0
280.0
221.8
278.5
250.0
272.6
288.0
250.0
262.4
272.0
300.0
239.6
257.0
244.5
235.5
242.5
242.8
237.9
235.5
228.0
229.5
229.5
237.8
218.5
292.0
-37.0
0.0
-i.0
-11.0
11.5
14.8
0.0
8.0
19.8
0.0
0.0
-5.5
-30.0
-36.6
-35.5
-35.5
-35.4
-33.6
-37.6
-40.2
-35.5
-35.5
-37.8
-22.0
-21.0
28.0
-10.0
29.5
23.0
31.0
17.3
-24.0
-11.8
4.2
-18.0
0.0
-14.8
27.5
31.4
38.5
38.6
44.7
55.0
46.6
43.2
39.0
35.0
31.5
43.4
38.6
SNA-8-D-O27(III)REV
3
114
Amendment
9/15/71
TABLE
MISSION
J-2 LUNAR
3.2-9.1
MODULE
(CONCLUDED)
STOWAGE
VOLUME
CENTROIDS
LM-II
AREA
F4
F5
F6A,B,C
F7A
F7B
FTC
F7D
F7E
F7F
F7G
F7H
F7J
F7K
F7L
FFM
F7N
FTP
F8
F9
FI0
3.2-34
X
Y
282.2
286.0
270.3
238.0
238.4
242.8
238.0
243.2
238.0
227.9
237.7
231.5
222.6
231.8
225.7
238.0
241.0
221.0
219.9
221.0
-21.0
17.8
0.0
38.0
38.6
38.0
38.0
38.0
38.0
33.0
38.3
35.4
32.3
36.0
32.3
38.0
38.0
18.0
-1.3
-18.0
SNA-8-D-027
E
E
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66.6
66.6
52.8
49.8
46.0
41.0
38.4
31.2
31.6
31.8
45.5
41.8
42.7
47.3
53.4
53.1
53.4
51.0
44.5
51.0
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SNA-8-O-027(III)
REV 3
Amendment
TABLE
CONSUMABLES
LOADING
3.2-10
REQUIREMENTS
MISSION
SPS
Pressure
Fuel
110±4
AND
TOLERANCES
J-2
PROPELLANT
quantity
Fuel
Temperature
(°F)
Fuel
Oxidizer
(PS IA)
Oxidizer
110±4
70±5
See
70±5
Readout
(%)
Oxidize
r
Figure
4.1-3
SPS
Propellant
Load
(ib)
Loading
Fuel
TLoad
Outside
2Trapped
3Nominal
Inside
Tanks
Deliverable
Fuel
Primary
Fuel
Primary
and
Figure
67.6
- Quads
Module
A,
D -
A,
Secondary
B,
B,
C,
C,
D -
Oxidizer
See
See
- Quads
-
System
A and
- System
B - See
A and
Module
Loading
B - See
Propellant
Loading
Loading
A,
B,
Loadin
Consumable
Pressure
(PSIA)
- SPS
Bottles
Temp
(°F)
3600
70
70
Helium
-
Tanks
178
Helium
Helium-
- N20 _ Tanks
SM/RCS
178
70
Fuel
Window
Window
C,
- Figure
- Figure
D - See
Loading
4.3-1.
4.3-2.
Window
-
A
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70
Quads
B
4150
70
C
4150
70
4150
70
4150
70
4_0
70
2500
85
2500
85
System
A
Sys tern B
Nitrogen
- SM
Primary
Secondary
and
Propellant
- Figure
Window
4.3-4.
- Figure
4.3-5.
Nitrogen
8 Requirement
Weight
(ib)
87.6
Actual
Earth
Launch
Weight
(ib)
Pressure
(PSIA)
Temp
(°F)
87.6
5.4
Quads
Quads
D
HeliumCM/RCS
RCS
Window
Loading
9Helium
Quads
RCS
4.3-3.
Oxidizer
Helium
171.5
24796.8
4Servlce
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Fuel
24968.3
15557.8
- Quads
Oxidizer
Fuel
123.7
15625.4
Secondary
Figure
4.1-4
25092.0
78.6
Tanks
See
Actual
Requirement
Oxidizer
15704.0
2Trapped
Tanked
114
9/15/71
6.0
6.0
1.0
1.0
1.3
1.3
3.2-96
SNA-8-D-027
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3.2-10
(CONTINUED)
MISSION
Command
Module
Pressure
Waste
Water
Potable
J-2
Water
Loading
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and
GOX
Earth
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Weight
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?
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3.7
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6.7
Hydrogen
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Earth
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Per
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i
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27.6
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27.6
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316.6
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330.1
316.6
NOTES
Launch
Weight
_ib)
6
Water
114
9/15/71
Actual
Weight
(ib)
Per
Tank
:
11ndicated
prior
propellant
to
actual
load
is based
loading.
This
on
number
nominal
pressure
will
updated
be
and
after
temperature
loading
is
accomplished.
2See
Section
3See
Table
4See
Section
4.1
3.2-13
Planning.
Table
5See
for
explanation
for
4.2
for
Actual
loading
SM/RCS
SM/RCS
of
trapped
SPS
uncertainties.
loads
loads
and
and
uncertainties
uncertainties
4.2
for
Planning.
Actual
Table
3.2-14.
CM/RCS
CM/RCS
loads
loads
and
and
uncertainties
uncertainties
6Launch
Rule
Redlines
determine
lift-off
values.
7Launch
Rule
Redlines
determine
lift-off
values.
8Launch
Mission
be
used
in
Mission
published
in
Rules
will
determine
minimum
to be
will
llft-off
be
used
in
Mission
published
quantities
in
for
H2
02 .
9CSM
helium
dows
2,
to be
will
3.2-15.
Section
and
propellant.
and
contained
SNA-8-D-027(1)
nitrogen
in
CSM/LM
should
be
Spacecraft
loaded
in
accordance
Operational
Data
with
Book,
loading
Volume
winI,
Part
P2.
3.2-97
SNA-8-D-O27(III)REV
3
(Ib I
TABLE
Amendment
3.2-11
114
9/15171
MISSION
SPS
PROPELLANT
J-2
LOAD
CALCULATION
FUEL
i.
Enter
Item
2.
Use
load
3.
SPS
Figures
for
4.1-3
above
and
at
propellant
ii0
PSIA
(Table
3.2-12
5.
Calculated
density
6.
Adjustment
due
7.
Resulting
5,
of propellant
SPS
SPS
Oxidizer
Fuel
from
to PUGS
actual
less
graph
(item
Table
zero
6)
propellant
temperature
below)
(ib/ft 3)
2 divided
3.2-12
adjust
propellant
item
obtain
at loading
- density
Cubic
to
readout.
density
temperature
feet
4.1-4
quantity
4.
item
Readout
C - Percent)
Nominal
(use
Quantity
OXI DI ZE R
load
by
item
item
3)
f (ib/ft 3)
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SNA-8-D-027(III)REV
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TABLE
MISSION
SPS PROPELLANT
UNCERTAINTIES
FUEL
Standpipe
Gauge
Density
Batch
(+2.0°F)
Height
Propellant
Gauge
(-+0.35% of Gaugeable)
Measurement
Density
Loading
(i)
(I)
Pressure
OXIDIZER
_ib)
Volume
Temperature
114
J-2
ITEM
UNCERTAINTIES
LOADING
Tank
Amendment
9115171
3.2-13
(I)
RSS
(lb)
_+24
_+39
_+18
±46
_+6
±i0
_+54
_+86
_+0
_+0
_+94
_+75
_+8
±14
_+113
±130
!
TOTAL
Loading
RSS
Specification
Tolerance
on Propellant
of Flisht
TOTAL
NOTES :
_+172
_+16
(I) (2)
Temperature
+0
-46
Load
LOADING
UNCERTAINTY
(i)
Data will
be known
(2)
Loading specification
nominal,
this number
variable.
E
L
E
L
L
E
E
+0
-113
+212
-371
after
loading
is accomplished.
is an allowable
tolerance about
is added to the loading uncertainlty
3.2-101
II E
_+24
L
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Amendment
TABLE
3.2-14
MISSION
CO_4AND
This
table
will
Planning,
MODULE
be
LOADING
completed
reference
tolerances,
RCS
should
trapped
and
when
be
J-2
PARAMETERS
loading
made
to
deliverable
is
AND
CALCULATIONS
accomplished,
Section
4.2
for
For
nominal
Tank
Tank
B.
Liquid
C.
Total
D.
E.
F.
Volume
@0.0
Line
A +
Initial
Volume
B
Weight
to
A
Final
Weight
After
Loading
in
Load
Propellant
H.
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A
Tank
B
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Bleed
Unit
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Bleed
Unit
(item
Load
I.
Specification
Load
@ 70±5*F
J.
Total
Load
by
Temperature
D
less
.P.V.
(°F)
Propellant
(ib)
CM/RCS
Propellant
from
Item G above
K.
Maximum
Trapped
L.
Nominal
Deliverable
(Ib)
Propellant
(ib)
(ib)
3.2-102
I
B
Tank)
G.
E
Tank
(ib)
E Weigh
II E
OXIDIZER
(in 3)
in
Loading
Propellant
loading
(in 3)
Prior
than
PSIA
Mission
load,
propellants.
FUEL
A.
114
9/ls/71
L: E
L
L
SNA-8-D-027
(IIl) REV
3
L
Amendment
TABLE
3.2-15
MISSION
SERVICE
This
table
Planning,
will
be
reference
tolerances,
and
quad
Secondary
completed
should
nominal
A
MODULE
when
be
made
deliverable
RCS
J-2
LOADING
loading
to
SUMMATION
is
accomplished.
Section
4.2,
Fuel
Secondary
Maximum
Nominal
Trapped
Deliverable
Oxidizer
Total
Trapped
Deliverable
Oxidizer
Maximum
Nominal
Trapped
Deliverable
quad
Fuel
Secondary
Primary
Fuel
Total
Fuel
Maximum
Nominal
Maximum
Nominal
Trapped
Deliverable
Oxidizer
Total
Trapped
Deliverable
Maximum
Nominal
Total
Total
Maximum
Nominal
Fuel
Trapped
Deliverable
SM/RCS
Propellant
Total
Maximum
Nominal
3.2-103
D
(ib)
Fuel
Primary
Fuel
Total
Fuel
Maximum
Nominal
loading
Trapped
Deliverable
Ruad C (ib)
Total
Mission
load,
Fuel
Maximum
Nominal
Secondary
For
nominal
quad B (ib)
(ib)
Primary
Fuel
Total
Fuel
Maximum
Nominal
for
propellants.
Primary
Fuel
Total
Fuel
Total
114
9/15/71
Tr@pped
Deliverable
Oxidizer
Trapped
Deliverable
Load
(Ib)
Oxidizer
Trapped
Deliverable
SNA-8-D-027(III)REV
3
TABLE
3.2-16
MISSION
LM-II
CONSUMABLE
LM-II
Amendment
9115171
J-2
LOADING
APS
REQUIREMENTS
PROPELLANT
Fuel
Propellant
Load
Trapped
Outside
Tanks
Oxidizer
Inside
5.9
Tanks
Nominal
Deliverable
8.3
APS
3217.4
i0.0
3189.7
TBD
TBD
Propellant
following
allowable
TBD
table
off-loaded
27.7
1998.3
Outage
Total
(lh)
3225.7
2008.3
Trapped
The
(ib)
2014.2
Tanked
be
114
should
from
a
tolerance
be
full
for
used
to
condition
the
determine
to
calculated
the
arrive
at
off-load
amount
the
is
of
propellant
indicated
±0.5
pounds
load.
to
The
per
weigh
where
T
tank.
A.
Final
B.
Propellant
tank
C.
Nominal
D.
Correction
0.09
Oxidizer
-
Correction
-
1.16
Oxidizer
=
2G.
Nominal
H.
3I.
tank
0.15
(Item
temperature
2300
Oxidizer
=
(Ib)
B-65)
(Item
(GM/CC)
=
A-40)
B-65)
(GM/CC)
for
Fuel
(ib)
(GM/CC)
density
Correction
(Item
-2.84
density
(ib)
A-40)
loading
density
Delta
(PSIG)
(°F)
pressure
(Item
for
Fuel
Measured
quantity
for
=
overfill
temperature
overfill
2F.
at
loading
Fuel
IE.
pressure
(Item
2300
in
(Item
measured
J.
Propellant
K.
Overfill
L.
Target
M.
Quantity
required
N.
Quantity
to
F-G)
density
H)
(Item
H)
GSE
quantity
(C+D+E+I+J)
loading
be
to
fill
off-loaded
RCS
manifolds
(Item
K-L-M)
NOTES:
ILoading
2To
temperature
calculate
the
temperature
25°C
for
measured
in
nominal
°C
of
will
density
the
fuel).
This
equation
must
also
fuel
Nominal
oxidizer
density
for
=
be
always
solve
measured
density
Nominal
3Correction
correction
the
density
is
at
valid
14.7
measured
-
following
for
14.7
may
be
equation
4°C
PSIA.
E
L
IL
L
L
L
oxidizer
Therefore,
-
and
the
('C)
either
(°C)
positive
3.2-104
E
for
PSIA.
1.491539-0.0022832
density
negative;
(usually
0.922904-0.0009377
density
be
L.
or
negative.
SNA-8-D-O27(Ill)REV
L-' d
li
H,
3
E
Amendment
TABLE
3.2-16
(CONTINUED)
J-2
MISSION
LM-II
CONSUMABLE
LM-II
LOADING
DPS
REQUIREMENTS
PROPELLANT
Fuel
Propellant
Trapped
Load
Tanks
12035.8
48.9
27,3
Tanked
11986.9
74_8,7
Trapped
Inside
Nominal
Deliverable
Tanks
43.3
13,5
11943.6
7485.2
TBD
TBD
Outage
Total
Oxidizer
(Ib)
7_26.0
Outside
114
9/15/71
DPS Propellant
TBD
The following
table should be used to determine
the amount
off-loaded
from a full condition
to arrive at the indicated
able
tolerance
for the
AI.
Final
BI.
Propellant
CI.
Nominal
DI.
Correction
tank
calculated
pressure
at overfill
loading
overfill
for
off-load
temperature
quantity
tank
is ±0.5
pounds
of propellant
to be
load.
The allowper
weigh
tank.
(PSIG)
(*F)
(ib)
pressure
(Ib)
Fuel = 0.33 (Item A1 -40)
Oxidizer
= 0.54 (Item A1 -40)
1El.
Correction
for lording
temperature
(ib)
Fuel = 4.25 (Item B1 -65)
Oxidizer
- -10.5 (Item B1 -65)
2 F1.
Measured
2 GI.
Nominal
HI.
3Ii.
Delta
density
density
density
Correction
(GM/CC)
(GM/CC)
(GM/CC)
(Item
for measured
F1 - Item
GI)
density
Fuel - 8400 (Item HI)
Oxidizer
- 8400 (Item
Jl.
Propellant
KI.
Overfill
LI.
Target
MI.
Quantity
required
NI.
Quantity
to be off-loaded
HI)
in GSE
quantity
(CI+DI+EI+II+JI)
loading
to fill
RCS manifolds
(Items
(APS
only)
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
Nominal
oxidizer
3Correction
density
= 0.922904-0.0009377
density
for measured
(*C)
- 1.491539-0.0022832
density
may be either
3.2-105
(*C)
positive
or negative.
SNA-8-D-027
(III)
REV
3
(lb)
Amendment
TABLE
3.2-16
MISSION
LM-II
System
A
Fuel
System
A Oxidizer
System
System
B
B
Fuel
Oxidizer
-
RCS
J-2
PROPELLANT
(2)
Required
Ullage
Requirement
Load
(Ib) 5
107.4±0.9
Minimum
152.5
4
267.0
152.5
279.0
164.5
208.2±1.9
267.0
279.0
Load
Trapped
Tanked
Outside
Tanks
Trapped
Nominal
in Tanks
Deliverable
LM-II
4.2
200.6
8.0
392.6
- APS
- APS
tank
tank
#I
#2
(6)
(6)
-
RCS
RCS
tank
tank
#I
#2
(6)
(6)
3050
3050
-
DPS
DPS
(SHe)
(Ambient)
-
Ascent
Descent
-
Descent
Descent
Water
COX
Descent
70
70
]. 05
1.05
(ib)
Loadin_
Pressure
Weight
(ib)
(7)
(PSIA)
N/A
(Ib)
N/A
N/A
(7)
(7)
N/A
N/A
#2
N/A
(7)
N/A
2.4
tank
#i
(6)
830
tank
#2
(6)
830
2.4
2700
2700
48.0
48.0
tank
tank
Actual
Requirement
Weight
(PSIA)
N/A
#I
tank
& GOX
-
Weight
(°F)
I.i
0.I
-
GOX
Temp
(PSIA)
51.2
70
- Water
tank
#2
tank
#i
-
(Ib)
6.6
6.6
Pressure
0.6
-0.6
tank
-
(°F)
70
70
N/A
Nominal
Pressure
-
#i
#2
(6)
(6)
NOTES:
iSee
2See
Table
3.2-17
Section
5.6
3See
4PV
Table
ullage
280±50
5LM/RCS
3.2-18
for actual
propellant
load
calculation.
for explanation
of trapped
propellants.
for
to thruster
valves.
propellants.
6The
indicated
items
Part
7LM-II
loading
calculation
uncertainties.
should
be
cubic
inches
for LM/RCS
required
load
includes
contained
in
the
See
be
166.5±50
oxidizer
propellant
Table
should
CSM/LM
2, SNA-8-D-O27PT2.
Descent
Water
shall
3.2-16.
loaded
Spacecraft
be
relationship
in
to
in
inches
to
Section
provide
3.2-106
fill
with
Data
Book_
388-0.0+I0.0
be loaded
determined
TABLE
for
5.6
accordance
Operational
loaded
provided
cubic
per
tank.
required
See
Earth
Launch.
LM-II
ascent
water
shall
at earth
launch.
Initial
load will
be
temperature
(In 3)
Actual
Loadin_
Requirement
Temp
Weight
1600
Consumable
Water
4
Ullage
(lb)
& NitroBen
80_2
(6)
LM-II
Ascent
15.8
400.6
(PSIA)
3050
3050
Nitrogen
Ascent
416.4
i0.0
204.8
Nominal
Pressure
Consumable
Load
OXIDIZER
214.8
- Helium
IActual
iActual5
(in _)
Maximum
4
164.5
FUEL
Helium
(3)
208.2±1.9
107.4±0.9
Propellant
114
9/15/71
(CONTINUED)
to
by
LM/RCS
RCS
for
fuel
and
manifolds
trapped
loading
windows
Volume
II,
pounds
at
provide
85 pounds
the pressure-
3.2-16.1.
SNA-8-D-027
(Ill) REV
3
Amendment
9/15/71
TABLE
LM-II
ECS
To
3.2-16.1
WATER
Be
114
LOADING
DATA
Supplied.
3.2-107
SNA-8-D-027(III)REV
3
Amendment
TABLE
3.2-17
MISSION
LM-II
APS
i.
LOAD
J-2
CALCULATION
FUEL
PROPELLANT
Full
tank
-
Item
K,
Table
3.2-16
Density
of
temperature
off-load
tables
at loading
and
pressure
(ib/ft 3)
I 3.
Propellant
volume
i 4.
2)
(divide
item
OXIDIZER
(ib)
12.
item
114
9115/71
i by
(ft 3)
Measured
density
(from
Table
3.2-19)
(lblft3)
*
5.
Resulting
full
6.
Off-load
amount
7.
Propellant
(ib)
required
8.
Propellant
load
DPS
9.
Ii0.
tank
Density
of
112.
fill
RCS
manifolds
Item
K1
Table
and
3.2-16
tables
pressure
at
loading
(ib/ft
(divide
Item
3)
9 by
Item
(ft 3 )
(iblft
density
(from
Table
3.2-19)
3)
13.
Resulting
14.
Off-load
15.
Propellant
RCS
(ib)
(ib)
volume
Measured
P.
to
off-load
Propellant
i0)
load
(ib)
PROPELLANT
Full
temperature
iii.
tank
full
tank
amount
load
(ib)
(ib)
load
(Ib)
PROPELLANT
V.
Calculations
Fuel
Tank
A.
GSE
Volume
B.
Initial
(PSIC)
Ullage
C.
Initial
GSE
Oxidizer
A
Tank
B
Tank
A
Tank
B
(in 3 )
Pressure
Pressure
(PSIC)
D.
Final
GSE
-
S/C
Pressure
(PSIG)
E.
Ullage
the
Volume
substituting
the
NOTE
:
(in 3) -
following
Solve
equation
the
indicated
by
values
in
steps.
Ullage
Volume
=
IThese
items
will
made
prior
to
loading,
then
(D-C)
(A)
B-D
be
completed
loading.
the
items
only
If a density
will
be left
if
a
density
sample
blank.
sample
is made
is
prior
not
to
3.2-108
SNA-8-D-027
(III) REV
3
TABLE
MISSION
LM-II
PROPELLANT
LM-II
Amendment
3.2-18
J-2
LOADING
APS
UNCERTAINTIES
PROPELLANT
Fuel
Vent
Line
Tank
Volume
Volume
Pressure
Measurement
Temperature
Measured
(+5
Measurement
±0.8
+-I.3
±0.5
±0.8
+-1.7
±4.3
±0.7
±0.5
+-0.5
+-0.5
±0.5
+-0.5
±4.8
±8.2
±0.2
±0.3
±3.62
±5.96
+-1.70
±2.77
+-6.49
±15.76
Measurement
ILoading
Tolerances
Total
Loading
Uncertainlty
LM-II
Vent
Line
Tank
Volume
DPS
Measurement
Temperature
Measured
(+-5 PSIA)
Measurement
(i. 5 °F)
Density
±2.55
±1.70
Weight
Measurement
±0.5
±0.5
1 Loading
Tolerance
±0.5
+-0.5
±15.6
+-27.5
Total
Loading
Uncertainity
LM-II
Loading
Ullage
Tank
RCS
PROPELLANT
Temperature
Calculation
and
Manifold
Volume
Total
IThese
will
be
known
quantities
after
(ib)
PROPELLANT
Volume
Pressure
Oxidizer
+-0.3
PSIA)
(+-I.5°F)
(ib)
±0.2
Density
Weight
114
9/15/71
loading
3.2-109
is
±0.6
±1.8
±0.4
±0.6
±0.8
±1.4
+-1.8
±3.8
accomplished.
SNA-8-D-027(III)REV
3
TABLE3.2-19
MISSION
J-2
] 14
Amendment
9/15/71
LM-II APSPROPELLANT
LOADING
PARAMETERS
(To Be Completedby KSC at Loading)
Fuel
Loading
Pressur,
Loading
Temperature
-
Fill
Loading
Temperature
-
Return
Loading
Temperature
- Tank
Number
Total
Pounds
of
- PSIA
Times
Pounds
Oxidizer
Weigh
Tank
Off-Loaded
Off-Loaded
Measured
Fuel
Measured
Oxidizer
@
Density
- Degrees
- Degrees
Used
Flow
25°C;
i TT 58
F I Tr258
- Degrees
Line
Using
Using
Density
Line
Weigh
Meter
Tank
Meter
(Weight
@ 14.7
@ 4°C;
F I TT 59
I TT259
F _ GP0718
I GPI218
(FIGw
14.7
PSIA
PSIA
3.2-110
Fuel
Oxidizer
Not
(Flow
Tank
Fuel
Oxidizer
Fuel
Oxidizer
Used)
Meter
Not
Not
Used)
Used)
GM/CC
GM/CC
SNA-8-D-O27(III)REV
3
Amendment
TABLE3.2-19 (CONTINUED)
114
9/15/71
MISSION
J-2
LM-II DPSPROPELLANT
LOADING
PARAMETERS
Fuel
Oxidizer
Loading Pressure - PSIA
Loading Temperature- Fill
ITT58 Fuel
Line - DegreesF _TT258Oxidizer
ITr 59 Fuel
Loading Temperature- Return Line - DegreesF _TT259
Oxidizer
_GQ3718
Fuel
Loading Temperature- TankOne- DegreesF _GQ4218
Oxidizer
Loading Temperature- Tank Two- DegreesFIGQ3719
IGQ4219F
Ouel
xidizer
Numberof TimesWeighTank
Total
Pounds
Pounds
Off-Loaded
Off-Loaded
Measured
Fuel
Measured
Oxidizer
Using
Using
Density
Used
Flow
@ 25°C;
Density
(Flow
Weight
Meter
Tank
(Weigh
@ 14.7
@ 4°C;
Meter
@
Used)
(Flow
Meter
Tank
PSIA
14.7
Not
Not
Not
Used)
Used)
GM/CC
PSIA
3.2-111
GM/CC
SNA-8-D-027(III)REV
3
Amendment
MISSION J-2 MASS PROPERTY DATA TABLES
114
9/15/71
Table 3.2-20 presents the CSM-ll3/LM-ll(docked) mass properties, in Apollo
coordinates, as a function of spacecraft weight for L.O.I.
SM/SPS burn.
Table 3.2-21 presents the CSM-ll3/LM-ll(docked) mass properties, in Apollo
courdinates, as a function of spacecraft weight for the D.O.I.
SM/SPS burn.
Table 3.2-22 presents the CSM-II3 mass properties, in Apollo coordinates,
as a function of CSM weight for the Circularization I SM/SPS
burn.
Table 3.2-23 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 coordinates, 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.
3.2-112
SNA-8-D-027(I II)REV 3
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Amendment
1/14/7o
SUPPLEMENTARY
General
Comments
Inertia
data
be
All
propellant
initial
propellants
in
be
are
the
LM
tanks.
propellants
CSM
The
30
weights
docked
SEQUENTIAL
3.3-1
through
deviation
are
to
be
are
are
PROPERTIES
TABLES
3.3-8:
values.
total
in
the
tanked.
low
configuration.
propellants
MASS
+10%.
as
assumed
CSM/LM
TO
Tables
are
used
figuration,
their
to
dispersions
shall
when
APPLICABLE
Applied
Dispersions
LM
assumed
always
to
assumed
ends
In
the
be
in
to
of
their
CSM/LM
the
be
in
tanks
except
docked
hlgh
con-
ends
the
low
of
their
ends
of
that
the
tanks.
(+)
item
Table
to
DATA
or
is
(-)
sign
added
to
or
following
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subtracted
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from
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the
an
item
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preceding
total.
3'3-i
SM/SPS
Yaw
Tables
=
glmbal
1.315
3.3-7
CSM
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and
angles
for
SPS
abort
sequence
are:
Pitch
= -1.530
deg.
deg.
3.3-8
124 consumables
changes
are
presented
in
Tables
3.3-7
and
3.3-8,
respectively.
Tables
3.3-4
Delta
LES
and
Z
-
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LES
tilted
motor
tilted
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PCM
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motor
The
and
December
to
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3.3-4
Table
3.3-5
3.3-5
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3.3-5.
Delta
=
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=
X -
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angles
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Table
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2.124
270.121
1222.379
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deg.
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deg.
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=
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deg.
X =
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point
Reference
0.75
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in.
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0.O18
in.
Z -
2. 662
in.
at
Memorandum
t=14.0
seconds
EX24/8912-344B,
in
Table
dated
1969.
includes
seconds
and
a rapid
of
CM/RCS
depletion
fuel
of
from
3.3-1
CM/RCS
t-5.0
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TABLE
CSM
(To
be
used
in
109
conjunction
Consumables
with
the
CSM
3.3-7
Weight
Change
sequential
Summary
mass
properties
Weight
EVENT
Consumable
From
Change
(Pounds)
To
Earth
Launch
Pre
Trans/Dock
SM-Hydrogen
SM-Oxygen
CM-Potable
H20
CM-Waste
H20
Pre
Trans/Dock
Post
Post
Trans/Dock
Pre
Trans/Dock
SPS
Hybrid
Post
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SPS
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Post
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SPS
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L.O.I.
i
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Pre
Post
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L.O.I.
Pre
D.O.I.
Post
Post
D.O.I.
D.O.I.
CSH/LH
Separation
Separation
Pre
Circularizatlon
Post
Circularlzatlon
1,190.1
-152.7
60.0
40,406.8
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44.8
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-113.3
SM-RCS
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1,178.1
-I_4.7
SM-SPS
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40,061.9
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40.4
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474.0
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16,551.4
24,015.2
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39.6
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466.2
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1,095.7
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Hydrogen
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SM-RCS
Pre
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519.9
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560.5
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40.0
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Post
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54.1
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CM-Food
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620.2
SM-Hydrogen
SM-Oxygen
H20
3.3-2_
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CM-LiOH
SPS
Table
Amount
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SM-RCS
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79
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36.3
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433.4
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320.8
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36.0
430.8
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965.4
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SM-SPS
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14,741.1
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,
CSM
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TABLE
109
conlunction
3.3-7
Consumables
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EVENT
Change
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1
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2
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Post
T.E.I.
SH
T.E.I.
SM-SPS
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IX
Ix
L
li
L_
L
.
Amendment
80
4/8/70
TABLE
CONSUMABLES
LOADING
3.3-10
REQUIREMENTS
Mission
SPS
Pressure
Fuel
11024
AND
TOLERANCES
H-2
Propellant
Temperature
_*F)
Fuel
Oxidizer
_PSIA)
Oxidizer
110t4
70t5
quant i ty
Fuel
70_5
See
Readout
(%)
Oxidizer
Figure
See
4.1-3
SPS
Propellant
Load
Loadin_
Fuel
(Ib)
2Trapped
Tanked
Outside
2Trapped
3Nominal
Inside Tanks
Deliverable
Tanks
_Service
Secondary
Primary
Fuel
Fuel
Requirement
Oxidizer
15704.0
78.6
15625.4
67.6
15557.8
iLoad
- Quads
- Quads
A, B, C, D - See
Oxidizer
- System
Oxidizer
A and
- System
B - See
A and
Loading
B - See
9Helium
Consumable
Pressure
and
RCS
Window
24788.5
Window
- Figure
- Figure
B, C, D - See
Loading
4.3-1.
4.3-2.
Window
-
Propellant
Window
- Figure
Window
4.3-4.
- Figure
4.3-5.
Nitrogen
Loadin S Requirement
Temp
Weight
(PSIA)
('F)
(lb)
87.6
Helium Helium Helium Helium Quad
Quad
Qued
SPS Bottles
Fuel Tanks
N20 _ Tanks
SM/RCS
A
B
C
3600
178
178
70
70
70
4150
4150
4150
70
70
70
_ed
Helium
-
V
_/lCS
4150
70
4150
4150
70
70
1.0
2500
2500
85
85
1.3
System A
System B
Nitrogen
- SM
Primary
Secondary
25083.7
123.9
24960.0
171.5
78.6
15606.6
67.6
15539.0
Loading
A,
Loading
Oxidizer
15685.2
Propellant
Loading
- Quads
5Co_nnand Module
Fuel
RCS
A, B, C, D - See
Primary
and Secondary
Figure 4.3-3.
Actual
Fuel
25092.0
123.7
24968.3
171.5
24796.8
Module
Figure
4.1-4
Actual
Earth
Launch
Weight
87.6
3.3-49
Temp
(°F)
3510
178
170
72
4350
4240
86
77
4210
4280
73
77
1.0
4140
4140
65
67
1.3
2510
71
2550
71
5.4
6.0
(ib)
Pressure
(PSIA)
6.0
SNA-8-D-027(III)REV
2
Amendment
80
4/8/70
TABLE3.3-10 (Continued)
Comand
Module
(P$1A)
Potable
I
Water 7
CM/COX
Waste
Water 6
*As serviced,
Water
Weight
Pressure
lift-off;
8Service
Module
Req.
Waste
Water
Hydrogen
Per
Oxygen
38.0
and
Tank
(Ib_
36.0
Earth
Requirement
*30 ibs
Actual
Launch
6.7 (Entry)
18.0
ibs, Potable
Water
*ii ibs
31.4 ibs.
Oxygen
Earth
(pounds)
29.3
330.I
Hydrogen
Weight
3.7
at
Loading
COX
_ib_
Loading
900±50
predicted
and
Launch
Per
Tank
27.6
Weight
(ib)
316.6
NOTES:
llndicated
propellant
prior
to actual
is accomplished.
2See
Section
3See
Table
_See
Section
4.1
for
3.3-13
4.2
load
loading.
loading
SM/RCS
sion Planning.
Actual
in Table
3.3-15.
5See
Section
4.2
for
nominal
of
will
trapped
pressure
be updated
SPS
loads
and
loads
loads
CM/RCS
and
loads
uncertainties
uncertainties
and
uncertainties
Rule
Redlines
determine
lift-off
values.
7Launch
Rule
Redlines
determine
lift-off
values.
8Launch
Mission
Rules
will
temperature
loading
propellant.
and uncertainties
6Launch
H 2 and
and
after
uncertainties.
SM/RCS
CM/RCS
sion Planning.
Actual
in Table
3.3-14.
on
number
explanation
for
for
is based
This
determine
minimum
lift-off
to be
used
will
to be
will
be
used
be
quantities
in Mispublished
in Mispublished
for
02.
gCSM helium
and nitrogen
should
be loaded
in accordance
with loading
windows
contained
in CSM/LM
Spacecraft
Operational
Data Book,
Volume
Part
2, SNA-8-D-027(1)
I,
P2.
3.3-50
SNA-8-D-O27(III)REV
2
L
Amendment
3/30/70
TABLE
3.3-11
SPS Propellant
Load
Calculation
OXIDIZER
1.
Enter
item
sPa Quantity
C - Percent)
Readout
at
110
Use F£guree
4.1-3
pellant
load
for
3.
Nominal
4.
Cubic
5.
Calculated
density
6.
Adjustment
due
7.
Resulting
actual
propellant
load
Item 5, less item 6) (pounds)
sPa
Oxidizer
and
4.1-4
above
quantity
propellant
density
temperature
to obtaln
readout.
at
- density
feet of propellant
to
(Table
3.3-12
100.8
2.
(use
PSIA
loading
graph
(item
from Table
PUGS zero
pro15588.0
below)
(lb/fC3)
2 divided
3.3-12
adjust
25092.0
temperature
Item
56.35
by Item
278.403
f (Ib/fC 3)
(pounds)
(item
3)
56.34
0._..___0
277.443
90.41
0.0
4 times
15685.2
SPS Propellant'Temperacure/Denelty
at 110+5
PSIA
25083.7
Graph
90.6
90.5
D
E
N
S
I
T
Y
90.Z
90.
90.1
LB/F'T3
90. ]
90.0
89.9
89.8
89.7
Temperature
3.3-51
Degrees
F
SNA-8-D-027 (Ill) IEV
2
79
E_
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W
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L
,_. L
TABLE
SPS
3.3-13
PROPELLANT
Amendment
3130170
UNCERTAINTIES
ITEM
LOADING
FUEL
(ib)
OXIDIZER
±24
_39
_18
±46
± 6
±i0
±54
±86
± 5
± 5
I 0
0
± 8
±14
± 63
±107
UNCERTAINTIES
Tank
Volume
Temperature
Gauge
Standpipe
Height
Propellant
Density
Batch
(_2.0°F)
Gauge
(±0.35%
Measurement
Density
Loading
of
Gaugeable)
(i)
(I)
Pressure
(i)
79
(Ib)
J_
RSS
TOTAL
Loading
±124
RSS
Specification
(I)
Tolerance
on Propellant
of Flight
Load
TOTAL
MISSION
±0
-+0
+0
Temperature
UNCERTAINTY
I
Ratio
±124
sp'
+ 65.5
-512.7
Variation
Vehicle
Weight
Variation
Propellant
usage uncertainty
total loading
uncertainty
TOTAL PROPELLANT
MISSION
8V
NOTES:
_0
UNCERTAINTIES
Mixture
_V,
LOADING
(2)
(1)
(2)
Data
UNCERTAINTY
will
Loading
due
be known
to
+ 75.9
-132.4
FOR
+434.0
-675.3
after
specification
nominal,
this
variables.
+422.2
-419.0
number
is
is
3.3 -54
loading
is
an allowable
added
to the
accomplished.
tolerance
loading
about
uncertainty
SNA-B-D-027(III)REV
2
Amendment
3130170
TABLE
Command
This
table
will
Module
be
RCS
completed
Planning,
reference
tolerances,
trapped
3.3-14
Loading
when
Parameters
loading
should
be made
and deliverable
and
Calculations
is accomplished.
to Section
4.2
propellants.
for
Tank
Tank
Volume
@ 0.0
Line
Volume
B.
Liquid
C.
Total
D.
Initial
Weight
in Bleed
Prior
to Loading
(Ib)
Weight
Loading
Propellant
F°
than
Load
Loading
I.
Specification
Load @ 70_5"F
L.
Nominal
Deliverable
1474.7
17.4
L: L
E
Tank
B
1789.2
1787.0
17.1
16.4
1803.4
148.6
103.3
196.6
116.7
104.4
59.1
118.3
38.4
44.2
44.2
78.3
78.3
44.2
44.6
77.8
78.5
70.0
70_0
69.0
69.0
44.2
44.2
78.3
78.3
Unit
("F)
88.8
(ib)
Propellant
E
A
1806.3
(Ib)
(Ib)
156.3
13.3
23.1
75.5
133.2
3.3-55
ILl 111 I_
Tank
1492.1
Propellant
(Ib)
Trapped
B
1493.8
by P.V.
Maximum
Tank
D less
Total CM/RCS
Propellant
Load from Item G above
K°
loading
Unit
(item
Temperature
Mission
load,
OXIDIZER
21.0
Tank)
H.
J°
1472.8
(in 3)
in Bleed
(ib)
Load
E Weigh
Propellant
G,
(in 3)
A + B (in 3)
Final
After
E°
PSIA
A
For
nominal
FUEL
A.
79
L
L
E
SNA-8-D-O27(III)REV
1_ E
_
|;
E
2
E
L
L
_
L
Amendment
3/30/70
TABLE
SERVICE
This
nlns,
table
will
reference
tolerances,
be completed
when
should
be made
to
and
quad
nominal
2.1
1083
Trapped
Deliverable
Oxidizer
225.6
Total
Maximum
Nominal
Total
Maximum
Nominal
fuel*
Maximum
Nominal
*Secondary
+2.3
Trapped
Deliverable
Oxidizer
39.8
69.7
109.5
Maximum
Nominal
2.1
i07t4
Trapped
Deliverable
Total Oxidizer
Maximum
Trapped
22_,5
4.5
Nominal
221,0
Total
2.1
1080
Maximum
Nominal
fuel
Deliverable
for
all
quads
Plan-
Propellant
±1.4
by
P.
*2.3
4.5
221.7
(lb_
Total Oxidizer
Maximum
Trapped
Nominal
Deliverable
determined
t0.7
2.1
i08.0
226.2
Trapped
Deliverable
Load
*2.3
3g.8
I0._
Ii0,i
Trapped
Deliverable
Oxidizer
Total
t0.7
D (lb_
fuel
Maximum
Nominal
SM/RCS
440,1
R_4
431.7
Trapped
Deliverable
load
'2.3
4.5
220.9
3.3-56
II
Secondary
fuel*
Primary
Fuel
Total
fuel
1101'0.7
225.4
,
Mission
loading
Secondary
fuel*=
Primary
fuel
7U.l
fuel
fuel
±0.7
40.0
fuel
For
load,
B (Ib)
quad
Total
Total
is accomplished.
4.2,
for
nominal
C (Ib)
Trapped
Deliverable
SU_4ATION
propellants.
A.5
Trapped
Deliverable
Quad
Primary
LOADING
quad
Maximum
Nominal
Secondary
RCS
A (ib)
40,2
70.2
110.4
Maximum
Nominal
3.3-15
loading
Section
deliverable
Secondary
fue_
Primary
fuel
Total
fuel
Total
MODULE
79
V.
902.7
IR__
884.7
14.6
calculations.
SNA-8-D-027(III)REV
2
Amendment
79
3/30/7o
TABLE
3.3-16
Consuuunble
LM-7
Loading
LM- 7 APS
ltequiraments
Propeller
Fuel
Propellant
Trapped
Load
Outside
Trapped
Inside
Nominal
Deliverable
weigh
Final
B.
Propellant
C.
Nominal
D.
Correction
26.4
1999.5
3194.1
TBD
TBD
TBD
from
tolerance
should
be used
to determine
the
a full
condition
to
arrive
at
for
the
calculeted
off-load
pressure
overfill
-
Correction
Measured
2G.
Nominal
Delta
amount
of
propellant
the
indicated
load.
is
_0.5
pounds
per
Fuel
=
2074.1
3317,7
0,8
it8
-4.9
-6.8
A-40)
(Ib)
B-65i
(Item
B-65)
0.8992
]_4_I?
0,8994
1.4824
-0.0002
-0,0007
-0.5
-1.6
(GM/CC)
(GM/CC)
-
67.4
(GM/CC)
(Item
measured
2300
Oxidizer
51.9
69.2
(ib)
temperature
(Item
density
for
49.3
A-40)
= -2.84
density
(Ib)
(Item
loading
density
Correction
d
(Item
for
(OF)
pressure
0.15
- -1.16
Oxidizer
2F.
tank
- 0.09
(PSIG)
temperature
quantity
for
Fuel
at overfill
loading
Oxidizer
3I.
3220.4
9.1
table
tank
Fuel
H.
2008,6
1
tank.
A.
IE.
7.8
Propellant
The
following
to
be off-loaded
The allowable
_Ib
5.6
Tanks
Outage
APS
Oxidizer
3228.2
Tanks
Tanked
Total
_Ib_
2014.2
(Item
2300
J.
Propellant
K.
Overfill
L.
Target
H.
Quantity
required
N.
Quantity
to
F-G)
density
H)
(Item
N)
in GSE
quantity
(C+D+E+I+J)
loading
be
4.8
i_6
to
fill
RCS
2071ti
3315.9
2014,4
__9228.2
manifolds
off-loaded
(Items
K-L-M)
correction
will
7.9
12.7
48.8
75.0
NOTES:
1Load::ng
2To
temperature
calculate
the
in
fuel).
of
This
measured
density
must
Nominal
fuel
NoB,trial
oxidizer
3Correction
for
°C
nominal
teomperature
25 C for
density
solve
the
measured
equation
is
also
density
demJity
measured
be
at
always
the
density
valid
14.7
followingoequation
amy
L: E
E
L
E
L"
Tand
the
('C)
be
('C)
either
positive
3.3-57
lU ILl
where
4 C for
oxidiser
PSIA.
Therefore,
PSIA.
1.491539-0.0022832
density
negative.
(usually
for
14.7
0.922904-0.0009377
-
be
or
nelative.
SNA-8-D-O27(III)REV
E
L.'
H E
2
L'
L.
'
i_.
"
L
Amendment
3/3O/7O
TABLE
3.3-16
(Continued)
LM-7Conaumable
Leaden
LM-7
i
lbmquirementa
DPS Propellant
Fuel
Propellant
Trapped
Load
Tanks
Oxidizer
60,5
7048.5
Trapped
Inside
Tanks
Nominal
Deliverable
11290.4
21.7
62.7
7026,8
Outage
11227,7
TBD
DPS Propellant
Final
tank
B1.
Propellant
CI.
Nominal
DI.
Correction
pressure
at overfill
loading
quantity
for
tank
the
amount
of propellant
the
indicated
load.
The
pounds
par welsh
tank.
(PSIG)
temperature
overfill
TBD
TBD
Available
The following
table
should
be used
to determine
off-loaded
from
a full
condition
to arrive
at
tolerance
for
the
calculated
off-load
is _0.5
AI.
(lb_
11350,9
35.1
Tanked
Total
tlb)
7083r6
Outside
79
41,8
('F)
(ib)
preseure
to be
allowable
53t6
69.96
67,7
7159.1
i1462,3
(ib)
0,6
6. 9
Fuel
= 0.31 (Item AI-40)
Oxidizer
- 0.51 (Item AI-40)
IEI.
Correction
for
loading
temperature
(lb)
-19.8
-26.6
A Fuel - -4.0 (Item BI-65)
Oxidizer
- -9.85
(Item BI'65)
2F1.
Measured
density
2GI.
Nominal
density
HI.
311.
Delta
density
Correction
Fl-Item
measured
Propellant
KI.
Overfill
LI.
Target
MI.
Quantity
required
N1.
Quantity
to
ILoading
temperature
Gl)
density
7900 (Item Hl)
- 7900
(Item
Jl.
(CI+DI+EI+II+JI)
loadlns
be
to
fill
RCS
off-loaded
1,4824
-0,0002
-0,0007
-1.6
-5.5
2.3
3.8
HI)
in GSE
quantity
]_4R]7
0.8994
(GM/CC)(Item
for
Fuel =
Oxidizer
0.8992
(GM/CC)
(GM/CC)
mmnifolds
(Items
(APS
7140.6
11440.9
7083.7
11351.1
only)
xxxx_x
KI-LI-MI)
xxxxxx
56,8
89,8
NOTES:
2To calculate
T-temperature
and
25"C for
the measured
will
always
be
negative,
the nominal
density
solve
the
followin8
in "C of
the
measured
density
(usually
fuel).
Th£a
equation
is valid
for
14.7
density
must
also
be at
14.7 PSIA.
density
Nominal
fuel
Nomlnal
oxidizer
3Correction
correction
for
-
0.922904-0,0009377
denalty
measured
(*C)
- 1.491539-0.0022832
density
amy
be either
3.3-58
equation
where
&eC for
oxidizer
PSIA.
Therefore.
(eC)
poeiCtva
or
n_lativa
SNA-8-D-027
(I II) REV
2
Ik.
Amendment
80
418170
TABLE
3.3-16
I/4-7 - RCS
Required
Load
_ib)
107.7'0.9
(Continued)
Propellant
Ullage
M_n4_um
IIi.0
5
(2)
(3)
*Actual
Requirement
(in _)
_
Max_m,,_
_
123.0
_
System
System
A
A
Fuel
Oxidizer
System
B
Fuel
208.8'1.9
I07.7*0.9
225.5
Iii.0
237.5
123.0
208.8
107.7
System
B
Oxidizer
208.8'1.9
225.5
237.5
208.8
Propellant
FUEL
215.4
Load
Trapped
Tanked
Outside
Tanks
Trapped
Nominal
in Tanks
Deliverable
LM-7
17.6
400.0
4.2
200.4
8.0
392.0
LoadinS
Pressure
*As
Pressure
Temp
#1
(6)
- APS
tank
#2
(6)
3050
70"
6.6
3203
76.4
- RCS tank
- RCS tank
- DPS
(SHe)
#I
#2
(6)
(6)
3050
3050
80*2
70o
70 °
N/A
1.05
1.05
48.5
3126
3099
_
82.3
81.1
_
1600
70 °
I.I
1653
78.3
0.1
0.6
N/A
N/A
N/A
N/A
DPS
(Ambient)(6)
('F)
70"
_ib)
6.6
- Ascent
- Descent
&
Water
-
tank
tank
-
tank
tank
#I
#2
GOX
serviced,
NOTES:
Isee
Table
238.5'50
5LM/RCS
6The
indicated
The
Descent
initial
Actual
Weight
_Zb)
42.5
Pressure
Weight
(PSIA)
(Zb)
N/A
(99.6%)
42.3
2.4
841
(720F)
-
830
2.4
838
(72°F)
-
(6)
2700
2776
(80°F)
-
at
lift-off
for
actual
inches
load
Water
load
254
See
load
3.3-16.
loaded
Spacecraft
load
will
be
at
Earth
42.1
264*
calculation.
of
trapped
propellants.
uncertainties.
be 125*50
cubic
inches
be
should
(99.2)
(99.6)
lb.
propellant
Table
N/A
N/A
48.0
for
LM/RCS
oxidizer
includes
propallant
valves.
items
is
explanation
loading
should
contained
in the
CSM/LM
Part
2, SNA-8-D-027PT2.
7LM-7
Requirement
830
5.6
for
3.3-18
for
calculation
to
isolation
propellants.
(lb)
(6)
(6)
3.3-17
cubic
required
Weight
42.5
(7)
predicted
2See
Section
3See Table
"PV ullage
('F)
75.0
N/A
N/A
Water
COX
Loadin_
Pressure
(PSIA)
N/A
#i
#2
(PSIA)
3115
GOX
Nominal
Descent
Actual
Weight
tank
Consumable
Ascent
Requirement
Temp
LM-7-Water
Descent
134.0
_lq_o
- APS
-
Ascent
205.7
(PSIA)
3050
Nitrogen
(In 3)
132.0
& Nitrogen
Nominal
Helium
Ulla&e
OXIDIZER
417.6
10.8
204.6
- Helium
Consumable
_Actual "
(lb)
Load
107,7
See
in
Section
Launch
3.3-59
by
shall
samplinR
with
Data
be
250
LM/RCS
fill
5.6
accordance
Operational
determined
for
per
tank.
required
to
RCS
for
fuel
manifolds
trapped
loading
Book,
-0,
and
windows
Volume
+i0
II,
pounds.
reouirements.
SNA-8-D-O27(III)KEV
2
Amendment
3/30/70
TABLE
LOAD
i.
12.
13.
14.
APS PROPELLANT
Full tank - Item
Density
of
temperature
K, Table
Propellant
volume
item
2.
(ft 3)
(from
5.
Resulting
full
6.
Off-load
amount
7.
Propellant
(ib)
required
Propellant
load
8.
DPS
9.
ll0.
Full
tank
Density
Table
load
N/A
N/A
N/A
N/A
N/A
N/A
1 by
3,3-19)
(ib)
2071.1
3315.9
49.0
75.0
7,9
12.7
(ib)
to fill
RCS
manifolds
(Ib)
- item
K1 Table
of off-load
end
Propellant
10 )(ft
112.
loading
3)
item
Oxldi_er
3315.9
Fuel
20"7_
(Ib)
2014.2
3228.2
7140.6
11441.9
PROPELLANT
temperature
iii.
tank
CALCULATION
at
(lb/ft
(divide
Measured
density
(ib/ft H)
3.3-17
3.3-16
off-load
tables
and pressure
79
st
tables
pressure
volume
3.3-16
loadin8
(ib/ft
(divide
(Ib)
3)
Item
3)
Measured
density
(from
Table
N/A
N/A
N/A
N/A
9 by Item
3.3-19)
(Ib/ft 3)
N/A
13.
Resulting
full
tank
14.
Off-load
amount
15.
Propellant
load
load
(ib)
N/A
7140,6
(ib)
57.0
(ib)
7083.6
11440.9
90.0
RCS PROPELLANT
Fue____l
Tank A Tank
P. V. Calculations
A.
GSE
Volume
B.
Initial
(In 3)
(PSlC)
Final
- S/C
NOTE:
lTheae
33.a
34,9
_
(in 3) - Solve
equation
by
the
values
in
step|.
(D-C)
(A)
Volume B-D
items
made prior
loadin$,
NASA _
33.7
will
to
then
o.5
11
34.6
o.o
be
_
completed
loadin8.
the item-
26.2
o.o
32.1
134
only
If 8 density
will
be left
if
8
205
density
nmple
blank.
30.4
7
219.01
8ample
ia made
Is
prior
not
to
MSC
3.3-60
il
30.25
Pressure
Ullage Volume
the following
substitutin8
the
indicated
Ullase
17.94
i.o
GSE
(PSIG)
E.
37.&
GSE Pre.sure
Initial
D,
18.45
B
lJlla_p Pr*-..ure
(PSIC)
C.
Oxidizer
Tank A
Tank
B
11
E
li-
L
L
L
L
L_
L
SNA-8-D-O27(III)REV
K
L;
L_
L_
L
2
k_
L
L,.
L
An_.ndment
3/30/70
79
TABLE 3.3-18
LM-7 Propellant
Loading
Uncertainties
LM-7 AP$ PROPELLANT
Fue! (Ib)
Vent
llne
Volume
Tank
Volume
_0.3
zO.8
tl.3
PSIA)
_0.5
tO.8
(ZI.5°F)
±1.7
z4.3
zO.7
zO.5
Measurement
zO.5
zO.5
Tolerance
±0.0
±OtO.
±4.4
±7.7
Pressure
Measurement
Temperature
Density
tLoadlng
Total
Loading
APS Mission
Mixture
_V,
(±5
Measurement
Measured
2Welght
Oxidizer
±0.2
Uncertainty
.
I
Uncertainties
Ratlo
!sp,
(!b)
Variatlon
Vehicle
Weight
-34.6
Variation
-54.0
Propellant
Usage Uncertainty
Loading
Uncertainty
Due To Total
Total
ForMisslon
Propellant
Uncertainty
-9.7
_V
-64.9
LM- 7 DPS PROPELLANT
Vent Line
Tank
Volume
Volume
Pressure
Measurement
(Z5 PSTA)
±0.2
±0.3
±3.4
Z5.6
_1.6
Z2.6
Z6.1
Z14.8
Density
±2.4
±1.6
2Weight
Measurement
_0.5
Z0.5
1Loading
Tolerance
Temperature
Measured
Total
Loading
DPS Mission
Mixture
_V,
Measurement
(1.5°F)
Uncertainty
Ratio
Variation
Isp, Vehicle
Weight
-341.2
Variation
Total
For Mission
Propellant
Total
-29.3
Uncertainty
LM-7
AV
-361.5
RCS PROPELLANT
Temperature
Ullage Calculation
and
Manifold
Volume
Total
1These
will
±14.2
-115.7
Due to
Tank
±0.0
±25.4
Uncertainties
Propellant
Usage Uncertainty
Loading Uncertainty
Loading
_OmO
be
known
quantities
after
loading
is
±0.6
±1.8
±0.4
ZO.6
_0.8
±1.4
±1,8
Z3.8
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.
3.3-61
lJ
SNA-8-D-027 (III)REV
2
L_
k_
TABLE
LM-7
APS
(To
Pressure
Loading
Temperature
-Flll
Loading
Temperature
-
Return
Loading
Temperature
-
Tank
-
Tank
Used
Number
Total
of
Pounds
by
Weigh
Off-Loaded
Off-Loaded
Measured
Fuel
at
Measured
Oxidizer
Flow
@_;
Density
_GP0718
FlGP1218
(Flow
Meter
@
@4°C;
14.7
@
Meter
Not
(Flow
(Weigh
Tank
14.7
64.0
66.6
69.1
66.8
69.3
68.0
3.3-62
68.2
Used)
Meter
Not
GM/CC
PSIA
Fuel
Oxidizer
Fuel
Oxidizer
Tank
PSIA
Fuel
Oxidizer
_TT 59
FITT259
Degrees
Degrees
Weigh
Oxidizer
Loading)
F G58 258
Degrees
Llne-
Using
Using
Density
Llne-
Fuel
Parameters
KSC
- PSIA
Times
Pounds
Loading
Completed
Loading
79
3.3-19
Propellant
Be
Amendment
3/30/70
Not
Used)
Used)
67.7
i
1
49.0
75.0
N/A
N/A
0.8992
GM/CC
1.4817
SNA-8-D-O27(III)REV
2
79
Amendment
3130170
TABLE
LM-7
I_S
3.3-19
(Continued)
Propellant
Loading
Par_aeters
Fuel
-
Oxidizer
68.3
Loading
Pressure
PSIA
Loading
Temperature
-
Fill
Loading
Temperature
-
Return
Loading
Temperature
-
Tank
One
Loading
Temperature
-
Tank
Two - Degrees
Tank
Used
Line
-
_TT 58
F ITT258
Degrees
Fuel
Oxidizer
67.7
ITT 59 _el
Number
Total
of
Times
Pounds
Pounds
Weigh
Off-Loaded
Off-Loaded
Using
Using
Measured
Fuel Density
Measured
Oxidizer
Line
Degrees
Degrees
(Flow
Meter
@ 25°C;
@
-
Weigh
Flow
Density
-
4°C;
Tank
PSIA
14.7
3.3-63
U
E
L
E
L
Oxidizer
I_3718
F|C_4218
Fuel
Oxidizer
_JGq3719
-[GQ4219
Fuel
Oxidizer
Meter
(Weigh
14.7
F ITT259
NoC Used)
(Flow
Tank
Meter
Not
GM/CC
PSIA
GMICC
NoC Used)
Used)
67.7
6_Z_7
8
69.7
67.4
1
1
57.0
90.0
NIA
N/A
0.8992
1.4817
..__i_
SNA-g-D-O27(III)KEV
2
L-
_nendment
74
1/14/70
MISSION
H-2
MASS
PROPERTY
DATA
TABLES
Unless
otherwise
stated,
the controlling
vehicle
propellants
are in the
end of their
tanks and the passive
vehlcle
propellants
are in the high
end of their
tanks.
Table
3.3-20
presents
CSM-109/LM-7
(docked)
coordinates,
as a function
of
Hybrid
SM/SPS
burn.
Table
3.3-21
presents
the
coordinates,
SM/SPS
burn.
CSM-109/LM-7
as a function
Table
3.3-22
presents
CSM-109/LM-7
the
(docked)
mass
of spacecraft
(docked)
coordinates
as a function
D.O.I.
SM/SPS
burn.
of
mass
spacecraft
in Apollo
for the
properties,
weight
for
properties,
weight
for
in Apollo
L.O.I.
in Apollo
the
Table
3.3-23
presents
the
as a function
burn.
CSM-I09
of CSM
mass properties,
in Apollo
coordinates,
weight
for the Circularlzatlon
I SM/SPS
Table
3.3-24
presents
the
as a function
burn.
CSM-I09
of CSM
mass properties,
in Apollo
coordinates,
weight
for the Plane Change
I SM/SPS
Table
3.3-25
presents
the
as a function
burn.
CSM-I09
of CSM
mass properties,
in Apollo
coordinates,
weight
for the Plane Change
II SM/SPS
Table
3.3-26
presents
the
as a function
CSM-I09
of CSM
mass properties,
in Apollo
coordinates,
weight
for the T.E.I.
SM/SPS
burn.
Table
3.3-27
presents
function
the
of
Table
3.3-28
presents
the
as a function
Table
3.3-29
presents
function
LM-7 mass
LMwelght
properties,
for the
LM-7 ascent
of weight
in
P.D.I.
LM coordinates,
DPS burn.
as
a
stage mass properties,
in LM coordinates
for the lunar llftoff
APS burn.
the LM-7 mass properties,
in LM coordinates,
as a
of LM weight
for the C.S.I.
to docking
LM/RCS
burn.
3.3-64
11
mass properties,
spacecraft
weight
low
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2
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LM-7
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Ascent
3.3-30
Stage
Lunar
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Table
3.3-31
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Properties
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mass
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1/22/71
SUPPLEHENTARY
General
DATA APPLICABLE
Comments
Inertia
to
data
be
applied
dispersions
TO SEQUENTIAL
to
Tables
are
+10%.
MASK PROPERTIES
3.4-1
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08
TABLES
3.4-8:
m
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changes
Pitch
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down
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Table8
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-
UNCERTAINTIES
Tank
OXIDIZER
FUEL
la
L
L;
li
1'.
I_
2
L_
,_
L
._.
Amendment
1/22/71
TABLE
Command
This
table
Planning,
tolerances,
Module
will
be
reference
trapped
RCS Loading
3.4-14
Parameters
completed
when
loading
is
should
be made
to Section
and deliverable
propellants.
and
Calculations
accomplished.
For Mission
4.2
for nominal
load,
loading
FUEL
Tank
A.
Tank
B.
Liquid
C.
Total
D.
Initial Weight
in Bleed
Prior to Loading
(Ib)
E.
F.
Volume
Line
@ 0.0
Volume
Final
After
in Bleed
(Ib)
Weight
Loading
Load
Propellant
H.
Loading
I.
Specification
Load @ 70e5"F
by
Temperature
Nominal
Deliverable
Tank
l_
A
1/_
Tank
B
/._
17.4
17.1
1493.8
1491.9
1806.0
16.4
1803.9
150.0
104.7
105.8
60.5
_
119.8
39,7
D less
44.2
___
P.V.
_AK2-
7on
_._.9
-._.9
(Ib)
(Ib)
3.4-90
7s_2
44_5
70_0
(lb)
Propellant
L.
B
Unit
CM/RCS Propellant
from Item
G above
Trapped
Tank
Unit
Propellant
(Ib)
Maximum
OXIDIZER
21.0
(=F)
K.
k
1472.8
(in 3)
Propellant
Load (item
than E Weigh Tank)
Total
Load
(in 3)
A + B (in 3)
G.
J.
PSIA
98
78.3
78.6
___
__X2.AI
_.__±1.6
88.8
156.7
13.3
23.1
75.5
133.6
SNA-8-D-O27(III)KEV
i:
i:
li
7A _±1.6
2
L,' L
L_
L
Amendment
1/22/71
TABLE
SERVICE
This
table
will
be
ning,
reference
tolerances,
and
qtmd.
Secondary
couplecad
should
nomin_
a
when
Maxim,-.
Nominal
108.0
Trapped
Deliverable
225.3
4.5
Oxidizer
Trapped
Deliverable
Secondary
Primary
108._
Oxidizer
Trapped
Deliverable
39.8
70.1
10_.9
2.1
707.8
*2.3
Total
Oxidizer
Max£mum Trapped
225.2
4.5
Nominal
220.7
Deliverable
t0.7
4.5
_.n
S_RCS
Propellant
tl.4
Total
Oxidiser
tO. 7
4.5
21q .0
(lb)
Oxidizer
HaximumTrapped
Nominal
Deliverable
3.4-91
69.7
log. 7
2,1
_2.3
Trapped
Deliverable
Load
t2.3
aq,q
fuel
PlJxiuumTrappad
Nominal
Deliverable
Maximum
Nominal
*0.7
D (ib)
Primary
fuel
Total
fuel
Total
_40.I
8.4
4_1.7
(Ib)
fuel
Fuel
Secondary
Plan-
loading
Total
fuel
MaximuaTrapped
Nomlnal
Deliverable
_'2.3
Total
Total fuel
Maximum
Trapped
Nominal
Deliverable
[
Mission
load,
*0.7
40.4
Maximum
Nominal
Trapped
Deliverable
For
nominal
_uad
70.0
ii0.4
Maximum
Nominal
for
C (Ib).
Secondary
fuel
Primary
fuel
Total
fuel
Total
accomplished.
Section
4.2,
propellants.
40_3
69.8
fuel
Quad
is
SUI'94ATION
Quid
11_,_
Maximum
Nominal
loading
(ib)
Primary
fuel
Total
fuel
Total
3.4-15
MODULE RCS LOADING
be made
to
deliverable
98
900.5
18.0
SNA-8-D-O27(III)REV
*4.6
2
Amendment
TABLE
LM-8
Consumable
3.4-16
Loadin_
LM-8
APS
Requirements
Propellant
Fuel
Propellant
Trapped
Load
(Ib)
Tanks
Inside
Nominal
Deliverable
Tanks
1991.0
APS
3182.3
TBD
Propellant
TBD
The
following
table
should
be used
to
to be off-loaded
from
a full condition
allowable
tolerance
for
the
determine
to arrive
calculated
the
at
amount
of propellant
the indicated
load.
off-load
is _+0,5
pounds
per
tank.
weigh
A.
Final
B.
Propellant
C.
Nominal
D.
Correction
tank
pressure
-
0.09
=
Fuel
Measured
2G.
Nominal
tank
=
(Item
= -2.84
Delta
Fuel
-
(Ib)
2300
J.
Propellant
in
K.
Overfill
L.
Target
M.
Quantity
required
N.
Quantity
to be
-9.7
-4.7
B-65)
(Item
(Item
=
1.4
A-40)
B-65)
1.4812
0.8998
0.8994
(Item
measured
2300
Oxidizer
68.4
1.8
temperature
(GM/CC)
for
6_,05
2072t_
(GM/CC)
density
Correction
4_.3
(ib)
(GM/CC)
density
60.3
A-40)
(Item
density
(Ib)
(Item
loading
-1.16
(PSIG)
(°F)
pressure
0.15
for
Oxidizer
2F.
quantity
for
Oxidizer
overfill
temperature
overfill
Correction
A
at
loading
Fuel
A
H.
27.6
TBD
Total
31.
8.3
_209.9
10.1
Outage
IE.
3218.2
2001.1
Trapped
(Ib)
5.9
Tanked
The
Oxidizer
2007.0
Outside
98
1/22/71
F-G)
0.0004
density
-2.76
+0.92
H)
(Item
H)
GSE
4,8
1.6
quantity
(C+D+E+I+J)
_300.9
2071.9
loading
3218.1
2006.7
to
fill
off-loaded
RCS
(Items
12.7
7.9
manifolds
K-L-M)
7Q.1
57.3
NOTES:
iLoading
2To
temperature
calculate
the
temperature
in
25"C
for fuel).
measured
Nominal
Nominal
3Correction
density
°C
correction
nominal
will
density
always
solve
the
negative.
following
equation
of the measured
density
(usually
4°C
This
equation
is valid
for 14,7
PSIA.
must
also
be
at
14.7
measured
density
may
where
for oxidizer
Therefore,
T=
and
the
PSIA.
fuel density
- 0.922904-0.0009377
oxidizer
density
= 1.491539-0.0022832
for
be
be
3.4-92
("C)
either
(°C)
positive
or
negative.
SNA-8-D-O27(III)REV
2
TABLE
LM-8
3.4-16
Consumable
LM-8
Amendment
1/22/71
(Continued)
Loadin_
DPS
Requirements
Propellant
Fuel
Propellant
Trapped
Load
_ib)
Oxidizer
7072.8
Outside
Tanks
60.5
7037.7
Inside
Tanks
Nominal
Deliverable
7Q0
11283.9
31,8
134.7
7,9
1 I149,2
Outage
TBD
Total
DPS
Propellant
TBD
Available
TBD
The
following
table
should
be used
to determine
the amount
off-loaded
from a full
condition
to arrive
at the indicated
tolerance
for
AI.
Final
BI.
Propellant
CI.
Nominal
DI.
Correction
A
the
tank
calculated
pressure
Fuel
for
A
Fuel
A
Oxidizer
2FI.
Measured
2GI.
Nominal
HI.
3Ii.
Delta
(Item
Correction
Oxidizer
-
Jl.
Propellant
KI.
Overfill
LI.
Target
MI.
Quantity
(APS
in
(Ib)
(Item
(ib)
(Item
Fl-Item
-19,7
0.8998
1.4812
0.8994
1.4824
GI)
density
.0004
3.16
HI)
(Item
HI)
_
(CI+DI+EI+II+JI)
to
fill
Quantity
(Items
to be off-loaded
KI-LI-MI)
ILoading
temperature
RCS
2.3
3.8
7155.6
loading
required
only)
-12.2
BI-65)
GSE
quantity
4.9
AI-40)
(Item
measured
7900
11452.9
1.9
(GM/CC)
for
7900
67.0
68.05
temperature
(GM/CC)
-
49.6
7160.4
(GM/CC)
density
density
tank.
BI-65)
-9.85
density
Fuel
NI.
=
(Item
loading
- -4.0
weigh
to be
allowable
AI-40)
= 0.51
for
per
of propellant
load.
The
46.1
(°F)
(ib)
pressure
(Item
pounds
(PSIG)
temperature
tank
is_+O.5
overfill
quantity
= 0.31
Correction
off-load
at
loading
overfill
Oxidizer
IEI.
_ib)
11344.4
35.1
Tanked
Trapped
98
i14_,4
7072.8
11341.9
xxxxxx
XXXXXX
manifolds
82.8
90.5
NOTES:
2To
calculate
the
T=temperature
in
and
the
25°C
for
measured
nominal
°C of
will
density
the
always
solve
measured
following
(usually
density
= 0.922904-0.0009377
Nominal
oxidizer
for
density
measured
=
is valid
for
at 14.7
PSIA.
3.4-93
may
be
14.7
equation
4°C
PSIA.
for
where
oxidizer
Therefore,
(°C)
1.491539-0.0022832
density
negative.
the
This
must
fuel
equation
also be
be
density
fuel).
density
Nominal
3Correctlon
correction
either
(°C)
positive
or
negatlve.
SNA-8-D-027(III)REV
2
Amendment
TABLE
LM-8
L
3.4-16
- RCS
(Continued)
Propellant
42 )
Required
Ullage
Requirement
Load
Minimum
_
(ib) 5
43 )
_
A
Fuel
107.7±0.9
System
A
Oxidizer
208.8±1.9
225.5
237.5
___SsSyStem
B
Fuel
tem
B
Oxidizer
107.7±0.9
208.8±1.9
iii.0
225.5
123.0
237.5
FUEL
Load
Trapped
Tanked
Outside
Tanks
Trapped
Nominal
in Tanks
Deliverable
LM-8
-
417.6
17.6
400.0
4.2
200.4
8.0
392.0
&
I
208.8
209.1
I
107.7128.0
208.8
258.3
1
i
Nitrogen
Loadin$
Actual
Requirement
Weight
Pressure
Temp
Weight
(°F)
70
41b)
6.6
(PSIA)
3130
(°F)
72.9
(]b)
72.9
APS
tank
#i
(6)
- APS
tank
#2
(6)
3050
70
6.6
3122
-
RCS
tank
#I
(6)
3050
70
1.05
3016
70.5
-
RCS
tank
#2
(6)
3050
70
1.05
3030
70.6
1612
68.9
80_+2
- DPS
(SHe)
- DPS
(Ambient)
N/A
1600
(6)
48.5
70
i.]
0.i
- Ascent
- Descent
0.6
- Water
& GOX
Nominal
Loading
Consumable
Water
Descent
-
tank
#i
-
tank
#2
Descent
geRuirement
Actual
Pressure
Weight
Pressure
Weight
(PSIA)
N/A
41b)
42.5
(PSI_)
N/A
41b)
42.5
42.5
N/A
Water
GOX
in s)
Temp
LM-8
Ascent
e
135.0
Pressure
4PSIA)
3050
Nitrogen
Ascent
lbU11a
Load
107.7
OXIDIZER
10.8
204.6
Nominal
Helium
4
215.4
- Helium
Consumable
r-_-_
Maxlmum
_
System
Propellant
iO0
1/28/71
N/A
42.5
N/A
(7)
N/A
254.0
-
tank
#I
(6)
-
tank
#2
(6)
830
830
2.4
2.4
850@73°F
850@73°F
2.4
2.4
(6)
2365
42.0
2377@72°F
42.0
GOX
NOTFS:
]See
Table
2See
Section
3See
4PV
3.4-17
Table
actual
cubic
for
of
loading
load
for
be
See
items
should
125_+50
LM/RCS
includes
valves.
load
trapped
calculation.
propellants.
uncertainties.
should
inches
required
isolation
propellant
explanation
calculation
23R.5±50
to
for
3.4-18
ullage
5LM/RCS
for
5.6
cubic
oxidizer
per
propellant
Table
inches
required
3.4-16.
See
for
LM/RCS
fuel
and
tank.
to
Section
fill
5.6
RCS
for
manifolds
trapped
propellants.
6The
indicated
contained
Part
7LM-8
at
NASA
li
--
U
2,
in
CSM/LM
be
Water
Launch.
shall
Initial
be
in
accordance
Operational
loaded
load
will
to
be
provide
E
with
Data
loading
Book,
windows
Volume
E
L
L
L
250-0.0+i0.0
determined
3.4-94
MSC
M
loaded
Spacecraft
II,
SNA-8-D-O27PT2.
Descent
Earth
the
by
S_
h
L
pounds
sampling
-S-D-027
EL
requirements.
(III) P,EV
I/
2
L,'.
"
L..
"
L_
"z_
Amendment
TABLE
LOAD
APS
I.
3.4-17
CALCULATION
PROPELLANT
Full
tank
- Item
K,
Table
3.4-15
(Ib)
12.
Density
of
temperature
off-load
tables
at loading
and
pressure
(ib/ft 3)
13.
Propellant
volume
item
34.
2.
(divide
density
(ib/ft
(from
Resulting
6.
Off-load
7.
Propellant
(lb)
required
Propellant
load
DPS
9.
Oxidizer
3300.9
_
_
-
-
-
-
2071.9
3300.9
57.0
70.0
7.9
12.7
2007.0
3218.2
7155.6
11432.4
7155.6
i1432.4
I by
Table
3.4-19)
3)
5
8.
item
Fuel
2071.9
(ft 3)
Measured
full
tank
amount
load
(Ib)
(lb)
to
fill
98
I122/71
RCS
manifolds
(Ib)
PRORPLLANT
Full
tank
-
Item
K1
Table
3.4-16
(ib)
Ii0.
Density
of
temperature
off-load
tables
at loading
and pressure
(Ib/ft 3)
111.
Propellant
volume
(divide
Item
9 by
Item
lO) (ft 3 )
112.
Measured
(lb/ft
3)
density
13.
Resulting
full
14.
Off-load
15.
Propellant
RCS
P.
(from
tank
amount
load
Table
load
3.4-19)
(Ib)
(ib)
83.0
(Ib)
7072.6
Fuel
Calculations
_.
GSE
B.
Initial
(PSIG)
Ullage
Initial
GSE
C,
Volume
(in 3)
D.
Final
GSE
-
S/C
NOTE. :
(in 3) equation
substituting
the indicated
the values
steps.
iThese
Volume
items
-
wlll
made
prior
to
loading,
then
L
l_
K
k
L
Tank
A
Tank
18.01
36.7
17.0
28.09
34.0
32.3
35.25
34.45
0.0
1.8
0.0
0.8
Solve
by
30.0
25.5
32.6
135.0
128.0
209.1
B
(D-C)
CA)
B-D
be
completed
loading.
the items
L
31.15
258.3
in
only
If
If a density
will
be left
a density
sample
blank.
L
L
is
sample
made
is
prior
SNA-8-D-027(III)REV
3.4-95
l;
B
Pressure
Ullaze
Volume
the following
Ullage
Oxidizer
Tank
Pressure
(PSIG)
E
A
Pressure
(PSIG)
U
11344.4
PROPELLANT
V.
Tank
!1
88.0
k
1_
li
11
it
not
to
2
L:
k
L
L
Amendment
TABLE
LM-8
Propellant
3.4-18
Loadins
LM-8
Uncertainties
APS PROPELLANT
Fuel
Vent
line
Tank
Volume
Volume
±0.3
±0.8
±1.3
±0.5
±0.8
±1.7
±4.3
Density
±0.7
±0.5
Measurement
±0.5
±0.5
Tolerance
±0.0
±0.0
±4.4
±7.7
±0.2
±0.3
±3.4
±5.6
PSIA)
±1.6
±2.6
(l.5°F)
±6.1
±14.8
±2.4
±i,6
Measurement
±o,_
±0,_
Tolerance
±0.5
±0.5
±14.2
±25,4
Measurement
Temperature
Measured
2Weight
lLoading
Total
(±5 PSIA)
Measurement
Loading
(±l.5°F)
Uncertainty
LM-8
Vent
Line
Tank
Volume
Measurement
Temperature
Measured
(±5
Measurement
Loading
Uncertainty
LM-8
Loading
Ullage
Tank
RCS
PROPELLANT
Temperature
Calculation
and
Manifold
Volume
Total
IThese
21f
will
weigh
is
±0.5
weight
be
tank
pounds
measuremnt
known
is
quantities
used
per
for
after
loading
off-loadlng,
weigh
tank.
uncertainty
If
is
(ib)
PROPELLANT
Density
ILoading
Total
DPS
Volume
Pressure
2Weight
Oxidizer
(ib)
±0.2
Pressure
98
1/22/71
then
flow
ZA.0X
3.4-96
is
weight
meter
is
of amount
ZO.6
±I.8
±0.4
±0.6
zO.8
zl.4
Zl.8
±3.8
accompllshed.
measurement
used
for
off-loadad.
uncertainty
off-loading,
then
SNA-8-D-027(III)REV
2
TABLE
LM-8
APS
(To Be
Propellent
Completed
Amendment
1/22/71
3.4-19
Loading
Parameters
by KSC at
Loading)
Fuel
75.0
Loading
Pressure
Loading
Temperature
- Fill
Loading
Temperature
- Return
Loading
Temperature
- Tank
Number
Total
of
Times
Pounds
Pounds
- PSIA
Weigh
Measured
Fuel
Measured
Oxidizer
Using
Using
Density
Line
Used
Flow
@ 25°C;
Density
@
[GP0718
F [GP1218
(Flow
Weigh
Meter
Meter
Tank
(Weigh
@
14.7
4°C;
@
PSIA
14.7
Fuel
Oxidizer
68.9
_ITT 59 Fuel
F[TT259
Oxidizer
- Degrees
3.4-97
IJ
F G58258
- Degrees
- Degrees
Tank
Off-Loaded
Off-Loaded
Line
98
Fuel
Oxidizer
Not
(Flow
Tank
Used)
Meter
Not
GM/CC
PSIA
Not
Used)
Oxidizer
64.0
67.9
69.2
68.9
69.4
68.6
1
1
57
70
Used)
0.8998
1.4812
GM/CC
SNA-8-D-027(III)REV
2
L
TABLE
3.4-19
(Continued)
98
Amendment
1/22/71
LM-8
-
DPS Propellant
Loading
Loading
Pressure
Loading
Temperature
-
Loading
Temperature
- Return
Loading
Temperature
- Tank
One
- Degrees
Loading
Temperature
- Tank
Two
- Degrees
Parameters
PSIA
Fill
Line
-
ITT 58
FITT258
Degrees
Fuel
Oxldlzer
Fuel
Oxidizer
60.8
64.3
67.9
67.0
68.2
67.0
69.0
67.0
ITT 59 Fuel
Number
Total
of
Times
Pounds
Pounds
Weigh
Tank
Off-Loaded
Off-Loaded
Measured
Fuel
Measured
Oxidizer
Used
Using
Using
Density
Line
@
Density
(Flow
Weigh
Flow
Meter
25°C;
@
- Degrees
14.7
4°C;
F[TT259
_GQ3718
F |GQ4218
Fuel
Oxidizer
F IGQ3719
[GQ4219
Fuel
Oxidizer
Meter
Not
Tank
(Flow
(Weigh
Tank
PSIA
Qd/CC
14.7
3.4-98
Oxidizer
PSIA
Used)
Meter
Not
_68.6
67.4
_.i____
Not
Used).._
i
88.0
Used)
0.8q98
-
GM/CC
SNA-8-D-O27(III)REV
2
MISSION
H-3
MASS
PROPERTY
DATA
Amendment
1/22/71
TABLES
Table
3.4-20
presents
CSM-110/LM-8
(docked)
coordinates,
as a function
of
Hybrid
SM/SPS burn.
mass
properties,
spacecraft
weight
Table
3.4-21
presents
CSM-IIO/LM-8
(docked) mass properties,
coordinates,
as a function
of spacecraft
weight
SM/SPS burn.
Table
3.4-22
presents
the CSM-II0/LM-8
coordinates
as a function
D.O.I. SM/SPS burn.
Table
3.4-23
presents
the CSM-IIO
as a function
of CSM
burn.
mass properties,
in Apollo
coordinates,
weight
for the Circularization
I SM/SPS
Table
3.4-24
presents
the CSM-II0
as a function
of CSM
burn.
mass properties,
in Apollo
coordinates,
weight
for the Plane Change
I SM/SPS
Table
3.4-25
presents
the CSM-IIO
as a function
of CSM
mass properties,
in Apollo
coordinates,
weight
for the T.E.I.
SM/SPS burn.
Table
3.4-26
presents
function
Table
3.4-27
presents
the LM-8 ascent
stage mass properties,
as a function
of weight
for the lunar lift-off
Table
3.4-28
presents
function
(docked) mass
of spacecraft
in Apollo
for the
in Apollo
for L.O.I.
properties,
weight
for
the LM-8 mass properties,
in LM coordinates,
of LM weight
for the P.D.I. DPS burn.
as a
in LM coordinates
APS burn.
the LM-8 mass properties,
in LM coordinates,
of LM weight
for the T.P.I. burn.
3.4-99
in Apollo
the
as a
SNA-8-D-027(III)REV
2
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L.
Amendment
98
1/22/71
This
page
intentionally
3.4-113
left
blank.
SNA-8-D-027(III)P.EV
2
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96
12/18/70
This
page
intentionally
left
blank.
3.4-12.2
U
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TABLE
(To be
used
CSM Ii0
in conjunction
Consumables
Weight
Change
Summary
with the CSM sequential
mass properties
EVENT
From
To
Earth
Launch
Pre
Consumable
Trans/Dock
Trans/Dock
Post
Trans/Dock
Post
Pre
Trans/Dock
SPS
Hybrid
post
Pre
Hybrid
SPS
Hybrid
L.O.I.
Post
L.O.I.
Post
SPS
Pre
L.O.I.
Post
Pre
Hybrid
L.O.I.
D.O.I.
D.O.I.
Post
D.O.I.
Post
D.O.I.
CSM/LM
Separation
Separation
Pre Circularization
Pre
Circular-
(Pounds)
(Pounds)
54.7
-0.5
819.9
40.0
-11.4
+0.8
18.8
SM-RCS
-70.6
SM-Hydrogen
H20
SM-SPS
1271.8
-70.6
-4.9
49.8
-5.4
-54.3
-70.3
765.6
1201.5
-65.7
-140.9
+41.2
+6.8
-3.8
60.0
6.8
-724.8
-3.8
39868.9
-724.8
aM-Hydrogen
SM-Oxygen
-9.4
-93.9
40.4
671.7
-14.8
-159.6
SM-RCS
CM-Food
CM-LiOH
-65.5
-9.4
+6.8
1136.0
-206.4
-13.2
SM-SPS
SM-Hydrogen
SM-Oxygen
SM-SPS
SM-Hydrogen
SM-Oxygen
SM-RCS
CM-LiOH
CM-Food
CSM/LM
(Pounds)
Total
Usage
-0.5
SM-RCS
Pre
Amount
Remaining
-11.4
+4.0
CM-Waste
CM-LiOH
CM-Food
SPS
Weight
Change
3.4-2)
SM-Oxygen
CM-Potable
SM-Oxygen
SM-RCS
Pre
Table
92
SM-Hydrogen
CM-Waste
Pre
Amendment
1214170
3.4-7
SM-Hydrogen
ization
SM-Oxygen
SM-RCS
Post Circularization
SM-SPS
3.4-16
-24788.7
13.6
15080.2
-0.5
-8.5
39.9
663.2
-30.4
-1471.4
-25513.5
-15.3
-168.1
1105.6
-236.8
13608.8
-26984.9
-3.4
36.5
-18.7
-31.2
-134.0
+5.0
-3.8
632.0
971.6
18.6
-199.3
-370.8
-17.0
-0.3
36.2
-19.0
-2.0
-26.3
630.0
945.3
-201.3
-397.1
-272.9
13335.9
-27257.8
SNA-8-D-027
(IIl) REV
2
TABLE
3.4-7
(To
he used
CSM ii0
in conjunction
Amendment
12/4/70
(CONTINUED)
Consumables
Weight
Change
Summary
with the CSM sequential
mass properties
Weight
EVENT
From
To
Post
Circular-
Pre
Plane
Change
SM-Hydrogen
ization
Pre
Plane
Post
Change
Plane
Change
Post
Plane
CSM/ASCT
Change
Docking
Docking
Pre
-2.&
33.8
-21.4
604.9
-226.4
SM-RCS
-75.8
869.5
-472.9
SM-SPS
-1269.5
12066.4
-28527.3
-4.9
28.9
-26.3
-47.4
-135.2
557.5
734.3
-273.8
-608.1
CM-Food
CM-LiOH
CM-Fecal
-6.3
+7.8
+2.2
26.4
2.2
SM-Hydrogen
-I.I
27.8
-27.4
-9.3
-41.9
+i.i
548.2
692.4
3.3
-283.1
-650.0
-3.8
+2.6
29.0
SM-Oxygen
SM-RCS
CM-Fecal
CM-Food
CM-LiOH
Pre
T.E.I.
Post
Post
T.E.I.
T.E.I.
SM-SPS
SM Jettison
SM
Jettison
CM
@ Entry
CM
@ Entry
CM
@ M.C.
CM
@ M.C.
CM
@ Impact
Deploy
Deploy
M
I: E
h
L
E
-23.3
-27.1
-10061.0
2005.4
-38588.3
SM-Hydrogen
SM-Oxygen
-11.8
-127.3
16.0
420.9
-39.2
-410.4
SM-RCS
CM-LiOH
CM-Food
CM-Fecal
-179.9
+13.4
-10.4
+3.3
512.5
42.4
-829.9
CM-RCS
-11.6
233.4
-11.6
CM-RCS
-30.7
202.7
-42.3
CM-RCS
-202.7
0.0
-245.0
3.4-17
II II M
Usage
(Pounds)
-25.1
SM-Hydrogen
T.E.I.
Total
Remaining
(Pounds)
SM-Oxygen
SM-Oxygen
SM-RCS
CSM/ASCT
3.4-2)
Amount
Change
(Pounds)
Consumable
Table
92
n
l,: E
-37.5
6.6
SNA-8-D-027(III)REV
g
E
E
E
2
L
l
i
2
TABLE
LM-8
(To
be
used
in
conjunction
Consumables
with
the
EVENT
Amendment
12/4/70
3.4-8
Change
LM sequential
Consumable
From
To
Earth
Orbit
CSM/LM
CSM/LM
Pre
Separation
D/S-Oxygen
D/S-Water
LM-RCS
P.D.I.
Summary
mass
properties
Table
Weight
Amount
Change
Remaining
(Pounds)
(Pounds)
-I.I
-13,0
-5.0
D/S-Oxygen
Separation
D/S-Water
LM-RCS
.
3.4-2)
Total
Usage
(Pounds)
46.9
237.0
600.6
-I.i
-13,0
-5.0
-i.0
45.9
-2.1
-21.3
-55.5
215.7
545.1
-34.3
-60.5
Pre
P.D.I.
LM
A/5
@ Touchdown
A/S
at
A/S
@ Lift-Off
A/S
in Orbit
LM-APS
A/S
in Orbit
Pre
T.P.I.
A/S-Water
-5.0
80.0
A/S-Oxygen
-0.3
4.5
-0.3
209.9
Pre
T.P.I.
A/S
@ Post
A/S
T.P.I.
@ Docking
@ Touchdown
Lift-Off
Post
T.P.I.
A/S
@ Docking
A/S
D/S-Oxygen
D/S-Water
LM-RCS
LM-DPS
-0.I
-1.1
-97.0
-17,342.6
LM-RCS
Jettison
-5.0
-4,927.8
I,:
E
E
L
L
L
45.8
214.6
448.1
977.1
-2.2
-35.4
-157.5
-17,342.6
443.1
-162.5
282.8
-4,927.8
-5.0
LM-RCS
-47.4
395.7
LM-APS
-39.0
243.8
A/S-Water
A/S-Oxygen
-3.8
-0.2
76.2
4.3
LM-RCS
70.2
A/S-Water
-8.2
68.0
-17.0
A/S-Oxygen
-0.4
3.9
-0.9
3.4-18
11 !1
L
-4,966.8
-8.8
-0.5
325.5
-280.1
SNA-B-D-027(III)REV
I:
92
E
12 E
1;
t_
L:
2
L
L
IL_
**._,
C)
!
!
i.-4
I
fIG
L
Amendment
81
5/11/7o
TABLE 3.4-9
MISSION
H CO)_qAND MODULE
STOWAGE
VOLUME
CENTROIDS
S/C 109 - 111
A1
3
4
5
6
7 - Not on S/C 110
8
10 - S/C ii0 Only
11 - Not on S/C 110
12
13
1012.0
1016.0
1015.O
1015.O
1017.0
1012.O
1012.0
1011.0
1Oll.0
1013.0
I010.O
-22.0
-24.0
- 7.0
9.0
26.0
31.0
22.0
23,0
19.0
- 9.0
-22.0
-26.0
28.0
28.0
28.0
28.0
7.0
-23.0
6.0
7.0
14.0
- 2.0
81
2
3
4
5
6
7
B
1050.0
1039.0
1031.0
1031.0
1031.O
1031.O
1033.0
1024.O
-27.0
-38.0
-28.0
-20.0
- B.O
13.0
27.0
-38.0
39.0
37.0
40.0
40.0
39.0
39.0
36.0
37.0
L2
3
1059.0
1048.0
-44.0
-47.0
14.O
12.O
RI
2
3
4
5
6
B
10 - Forward
I0 - Aft
11
13
1072.O
1072.O
1072.0
1075.0
1059.0
1048.0
1052.0
1053.0
1047.0
1038.O
1024.0
26.0
26.0
26.0
28.0
44.0
46.0
46.0
47.0
48.0
47.0
45.0
21.0
14.0
9.0
3.0
15.O
29.0
12.0
5,0
5,0
26.0
-26.0
U1
3
4
1033.0
1033.0
1038.0
23.0
-36.0
39.0
-50.0
-44.0
-43.0
3.4-20
SNA-B-D-027(III)REV
2
&
L_
E_
Amendment
81
5/11170
Table
_he
not
following
associated
3.4-9.1
stowage locations
have
with
storage
volumes.
unique
volme
L0ckzz0,
G&N Signal
Cond.
Display
Keyboard
Sleep Restraint
Sleep
Restraint
Food Container
Food I_nntainer
rec:al
_cowage
PEA C,_ntainer
hatch
F_Jrwai_
Panel
Assy Amsy -
Right
Left
Container
Container
Conrah_er,
R12 (In-flight
Location)
tl,,lmet
Stnwale
and Accessory
gag
(In-flight
Location)L.H.
Helmet
Stowage
and Accessory
Bag s (In-flight
Location)Ctr.
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.(In. flight
Location)
CO A_sorbers
(?)
CO2 A_.'_rbers
(4)
CO_ Absorbers
CO Absorbers
CO_ Absorbers
(&)
(2)
(4)
CO2 Absorbers
(4)
6.8
Next
6.8
Reminder
lb.
!
%
1069.0
1060.0
1018.0
1018.0
1048.O
1050.0
1039.0
IO15.0
25.0
26.0
25.0
-21.0
-47.0
-27.0
47.0
0.0
29.0
32.0
-47.9
-49.9
12.0
39.0
12.0
-19.9
Under L.H.
R.H.
Girth
Couch
Ring
1018.0
1036.5
-24.5
&0.0
-15.0
-25.0
L.H.
_in8
1036.5
-40.0
-25.0
1050.0
-27.0
39.0
Girth
LEB
Girth
|.H.
Ring
40.0
1036.5
U
U
L
L
1039.0
-47.0
12.0
LEB
1050.0
-27.0
39.0
t/4ZB
In ECU
A3
A4
A6
|5
B6
Composite
Location
used in
Sequent/81
H_s
Proportion
Tables
1039.0
IO31.O
1016.O
1011.0
1017.0
1031.0
1031.0
47.0
-48.3
-24.0
- 7.0
26.0
- 8.0
13.0
12.0
19.6
28.0
28.0
28.0
39.0
39.0
1031.0
1031.0
1018.5
-
39.0
39.0
26.1
R.H.
__.CO,Absorbed
(02
Absorbed.
15
!16
Composite
t/on
lb.
CO; Absorbed
CO2 Absgrbed
L
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LHEB
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8.0
13.0
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81
RI/EB
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Couch
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4.1-3
8P8 P¢opell_t
(_)
Oxidiser
-
ULndov
Ftaure
4.3°4.
- YLaure
4.3-5.
Nitrosan
Losdint
leauirewnt
Praooufo
(PSIA)
Tmp
('r)
WeLaht
Clb)
3600
278
178
70
70
70
4150
4150
4150
6150
70
7O
7O
7O
6.0
6.0
4150
41S0
70
7O
1.0
1.0
2SO0
2500
88
85
1.3
1.)
87.6
|arch
Velth¢
Launch
(lb_
Actusl
rrenure
Teup
(PIIA)
('F)
87.6
5.4
SMA-8-D--027
3.4-65
(I 11 ) IU[V 2
TABLE
Command
3.4-10
Module
Pressure
Water
Loading
(PSIA)
Waste
Potable
(CONTINUED)
and
Amendment
1015170
GOX
Launch
Earth
Requirement
Wei6ht
88
(ib)
Weight
Water 6
Water 7
Actual
(ib)
18.0
36.0
CM/GOX
900±50
3.7
8Service
Loading
Module
6.7
Hydrogen
and
Requirement
Oxygen
Earth
(pounds)
Hydrogen
Tank
Tank
1
2
29.3
29.3
Oxygen
Tank
Tank
Tank
1
2
3
330.1
330.1
330.1
(Entry)
Launch
(pounds)
Weight
27.6
27.6
316.6
316.6
198.1
NOTES:
llndicated
propellant
load
prior
to actual
loading.
is accomplished.
2See
Section
3See
Table
4See
Section
4.1
for
3,4_13
4.2
explanation
for
for
loading
SM/RCS
sion Planning.
Actual
in Table
3.4-15.
5See
Section
4.2
sion Planning.
in Table
3.4-14.
for
is based on nominal
This number
will be
loads
CM/RCS
trapped
SPS
and
loads
loads
CM/RCS
and
and
uncertainties
loads
and
determine
lift-off
values.
7Launch
Rule
Redllnes
determine
lift-off
values.
8Launch
Mission
H 2 and
9CSM
minimum
to be
llft-off
be published
used
will
in Mis-
be
quantities
in Mispublished
for
02.
helium
and
nitrogen
should
windows
contained
in CSM/LM
Part 2, SNA-8-D-027(1)
P2.
be
loaded
Spacecraft
in
accordance
Operational
3.4-66
11 !1
used
will
uncertainties
Redlines
determine
to be
uncertainties
Rule
will
propellant.
uncertainties
6Launch
Rules
and temperature
after loading
uncertainties.
SM/RCS
Actual
of
pressure
updated
1:
L
:L: E
L
L
E
with
Data
loading
Book,
Volume
I,
SNA-8-D-027(III)REV
I:
E
L: U
|;
E
E
2
:"
'
i_
Amendment
8B
i01517o
T_LE
8P$
PYaq)el1_t
3.4-II
IMd
Caleuletlon
F_L
J
1.
Inter
item
SPS Quantity
C - Betcent)
2.
Use 718ures
4.1-3
peLXant
Load for
' end
4.1-4
shove
quantity
3.
Ik)liinel
propdllent
(use
tempersture
-
4.
Cubic
S.
Calculated
demstty
6.
Adjustment
due
7.
loeultiq
item
S,
SPS
Oxidizer
feet
of
bedout
st
density
density
to
(Table
to obtain
tJtdout,
3.4-12
pro-
2 divided
(It_
Table
PUGS sere
3.4-12
adJult
actua_
propellant
load
less
item
6) (pounds)
SPS
FUEL
PSIa
st loedin8
_mnporsture
lrqh
belov)
(1b/fie)
prel)ellent
free
110
SPS Propellent
st
by
item
f
m
item 3)
(lb/ft
w
3)
m
(pounds)
(item
I
4 times
Temperature/Density
110+5 PSZA
Graph
90.4
13
E
N
S
I
T
y
90.
90.
LS/FT 3
90.:
90.0
8g.g
8g.8
89.7
Temperature
Deerees
Y
.t.4-67
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Amendment
94
12/10/70
SUPPLEMENTARY
General
Comments
Inertia
data
DATA
to be
APPLICABLE
applied
dispersions
Dispersions
shall
All
propellant
initial
be
The (+) or (-) sign
item is added to or
Table
are
used
as
weights
following
subtracted
3.5-7
and
angles
for
Tables
MASS
3.5-1
PROPERTIES
through
TABLES
3.5-8:
+10%.
3o
deviation
are
total
values.
tanked.
the name of an item
from the preceding
indicates
total.
that
the
SPS
abort
sequence
are:
Pitch
ffi-0.4104
3.5-8
CSM and LM consumables
3.5-8,
respectively.
Table
to
SEQUENTIAL
3.5-1
SM/SPS
glmbal
Yaw = 1.895
Tables
TO
changes
are
presented
in Tables
3.5-7
and
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
(ib)
X-Bar
(in)
Y-Bar
(in)
Gamma-Ray
Retracted
45.4
865.1
33.0
-57.0
Gamma-Ray
Deployed
_28.0
_17.4
865.1
865.1
231,3
132.2
-312.4
-184.7
Mass Spectrometer
Retracted
47.4
863.1
55.8
-40.5
Mass Spectrometer
Deployed
_27.4
_20.0
863.1
863.1
341.7
198.8
-149.4
-94.9
3.5-1
Z-Bar
(in)
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SNA-8-D-027(III)REV
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9/10/70
3.5-5
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3.5-14
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SNA-8-D-027(III)REV
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9/10/70
Table
SIVB
Sequential
To
be
Mass
3.5-6
Properties
Supplied
at
a
(LV Coordinates)
Later
Date
3.5-15
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9/10/70
Table
SIVB
Sequential
To
Mass
be
3.5-6
Properties
Supplied
at
3.5-16
86
(Continued)
(Apollo
a Later
Coordinates)
Date
SNA-8-D-027(III)REV
|i
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L_
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Amendment
9
12/10/70
TABLE
CSM 112
(To be used
properties
Constmables
3.5-7
Weight
£n conjunction
Table
3.5-2)
Change
with
CSM sequential
To
Earth
Orbit
Pre
Consumab
Trans/Dock
Amount
Total
Change
Remaining
Usage
(Pounds)
(Pounds)'
(Pounds)
le
SM-Hydrogen
SM-Oxygen
CH-Potable
H20
CM-Naste
Pre
Post
Trans/Dock
Post
Trans/Dock
Pre
Trans/Dock
S20
SM-RCS
L.O,I.
Post
L.O.I.
Post
aM-Hydrogen
SM-Oxygen
SM-RCS
L.O.I.
Pre
D.O.I.
Post
D.O.I.
CSM/I.M
Pre
Post
L.O.I.
Separation
Pre
SM-SPS
Separation
Ctrcularization
Post
Ctrcularization
40.0
+0.8
18.8
-15.5
-155.6
-85.5
66.1
778.4
1186.3
+41.2
+13.6
-13.2
60.0
13.6
L_
L
1_
E
l_
L
-16.3
-171.4
-]56.1
-26684.3
65.3
771.0
1141.6
13335.6
-3.4
-35.9
-95.1
-17.I
-178.8
-200.8
-27258.1
61.9
735.1
1046.5
-20.5
-214.7
-295.9
CN-LiOH
CM-Food
5.0
-3.8
SH-Hydrosen
-0.3
61.6
-20.8
-2.6
-25.0
732.5
1021.5
-217.3
-320.9
-296.6
SB-SPS
L
-70.6
-13.2
13909.4
1_
I,,.
18.6
-17.0
13039.0
3.5-17
ItI il
-0.8
-15.8
1271.8
-573.8
SM-Oxygen
SM-RCS
Pre
+4.0
-0.8
-7.4
-44.7
SM-Hydrogan
SM-Oxygan
SM-RC$
Circulartzation
81.6
934.0
-26684.3
SM-Hydrogen
SM-Oxygen
SM-RCS
D.O.I.
CSM/LM
H20
S]_-SPS
D.O.I.
-0.8
-15.8
-70.6
CM-Naste
CN-LiOH
CM-Food
Pre
mass
Wefght
EVENT
From
Summary
-27554.7
SNA-8-D-027(III)REV
i;
L;
Ii
II
IL
L
2
L
±
;_
Amendment
9_
i2/lo/7o
TABLE
CSM
112
(To be used
properties
3.5-7
Consumables
(Continued)
Weight
in conjunction
Table
3.5-2)
with
To
Post
Pre
Circularlzation
Change
Pre Plane
Change
1
Post Plane
Change
]
Post
C::M/ASCT
Plaue
Change
Plane
i
sequential
Amount
Total
Remaining
Usage
Consumable
_Pounds)
_Pounds)
(Pound_)
SM-Hydrogen
SM-Oxygen
SM-RCS
-13.2
-117.4
-168.4
-1236.8
SM-Hydrogen
i
Pre
13oc:king
T.E.I.
Post
r.h.l.
Pre
Post
T.E.I.
CM
@ Entry
CM
@ Entry
CM
@ M.C.
46.7
-35.7
-348.)
SH-RCS
CM-Food
CM-LiOH
-73.0
-6.3
+7.8
780.1
-562.5
-23.3
+2.2
2.2
CM
@ M.C.
Deploy
CM @ Impact
26.4
-I0.9
35.8
-_6.6
SM-Oxygen
-i04.7
496.2
-453.b
SM-RCS
CM-LIOH
-128.9
+5.0
651.2
31.4
-691.2
CM-Fecal
+i.I
3.3
CM-Food
-3.8
-27.1
-95_1.I
SM-Hydrogen
Deploy
2661.1
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E
E
l_
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li
L
-38332.6
-14.9
20.9
-61.5
-168.9
-71.8
+13.4
327.3
579.4
44.8
-622.5
-763.0
CM-Food
CM-Fecal
-i0.4
+3.3
6.6
CM-RCS
-II.6
233.4
-Ii.6
CM-RCS
-30.7
202.7
-42.3
CM-RCS
-202.7
0.0
-245.0
-37.5
3.5-18
l/
-28791.5
600.9
SM-Oxygen
SM-RCS
CM-LIOH
SM Jettison
11802.2
-1.7
SM-SPS
SH Jettison
-34.0
-334.7
-489
3
-14.2
SM-Hydrogen
T.E.I.
48.4
615.1
853.1
SM-Oxygen
CM-Fecal
t_:_rL \SCT
mass
Change
SM-SPS
Docking
CSM
Summary
Weight
EVENT
From
Change
Ii
1_
SNA-8-D-027(III)REV
I_
1.'
l_
li
tl
2
12
i2
L
Amendment
TABLE
LM-IO
(To
be
used
in
conjunction
Consumables
with
the
LM
Change
sequential
EVENT
Earth
To
Orbit
CSM/LM
Pre
Separation
P.D.I.
CSM/LM
Pre
LM
Consumable
Separation
P.D.I.
@ Touchdown
D/S-Oxygen
-5.0
D/S-Oxygen
D/S-Water
LM-RCS
-3.0
-12.0
-51.0
88.0
348.0
550.5
-8.0
-32.0
-56.0
D/S-Oxygen
-i.0
87.0
-9.0
-3.0
-i00.0
345.0
450.5
-35.0
-156.0
LM-RCS
LM
@ Lift-Off
A/S
in
LM-APS
AIS
@
A/S
@
T.P.I.
@ Docking
A/S
A/S
@ Docking
Jettison
(Pounds)
-20.0
-5.0
@ Lift-Off
AIs
Usage
(Pounds)
91.0
A/S
T.P.I.
Total
Remaining
360.0
601.5
@ Touchdown
Orbit
3.5-2)
-5.0
LM
Orbit
_Pounds)
Table
Amount
-20.0
-5.0
LM-DPS
in
mass
properties
Weight
D/S-Water
LM-RCS
D/S-Water
LM-RCS
A/S
Sun=aary
Change
From
94
12110170
3.5-8
A/S-Water
-18762.0
-5.0
-4958.7
746.5
-18762.0
445.5
-161.0
261.5
-4958.7
-8.0
77.0
-8.0
A/S-Oxygen
LM-RCS
-0.4
-20.0
4.4
425.5
-0.4
-]81.0
A/S
-28.0
-20.0
57.0
A/S-Oxygen
LM-RCS
Water
-I.0
-80.0
3.4
345.5
-1.4
-261.0
A/S-Water
-12.0
45.0
-40.0
\
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3.5-19
SNA-8-D-027(III)REV
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Amendment
86
9110170
3.5-9
TABLE
MISSION
J-i
COMMAND
MODULE
STOWAGE
VOLUME
CENTROIDS
112
sic
AREA
X
Y
Z
AI
2
3
4
5
1012.0
1010.0
1016.0
1015.0
1015.0
-22.0
-23.0
-24.0
-7.0
9.0
-26.0
8.0
28.0
28.0
28.0
6
7
8
9
1017.0
i010.0
1012.0
1013.0
26.0
23.0
22.0
0.0
28.0
8.0
-23.0
16.0
B1
1050.0
-27.0
39.0
2
3
4
5
6
8
1039.0
1031.0
1031.0
I031.0
1031.0
1024.0
-38.0
-28.0
-20.0
-8.0
13.0
-38.0
37.0
40.0
40.0
39.0
39.0
37.0
L2
3
1059.0
1048.0
-44.0
-47.0
14.0
12.0
ILl
2
3
4
5
6
8
11
13
1072.0
1072.0
1072.0
1075.0
1059.0
1048.0
1052.0
1038.0
1024.0
26.0
26.0
26.0
28.0
44.0
46.0
46.0
47.0
45.0
21.0
14.0
9.0
3.0
15.0
29.0
12.0
26.0
-26.0
U1
1033.0
23.0
-50.0
2
3
4
1033.0
1033.0
1038.0
-23.0
-36.0
39.0
-50.0
-44.0
-43.0
3.5-21
SNA-8-D-027(III)REV
2
Amendment86
911o17o
Table 3.5-9.1
The
not
followln
alsociated
I
stOWale
locations
have
with
stowale
volumes.
NO .CLXTURE
Container
Forward
Hatch
Container
Container.
RI2
(In-flilht
Location)
Helmet Stowage and Accessory
Bags (In-flight
Location)L.H.
Helmet Stowage and Accessory
Bass
(In-fllght
Location)Cir.
Helmet Stowage and Accessory
Bags (In-flight
Location)
_ R.H.
Teavorary
Stowage
Bag - L.H.
(In-fllght
Location)
CO 2 Absorbers
6.8
6.8
Re_u.inder
lb.
lb.
CO2
X
1069.0
1060.0
1018.0
1018.0
1048.0
1050.0
1039.0
1015.0
25.0
26.0
25.0
-21.0
-47.0
-27.0
47.0
0.0
29.0
32.0
-47.9
-49.9
12.0
39.0
12.0
-19.9
Under L.H.
R.H. Girth
Couch
Ring
1018.0
1036.5
-24.5
40.0
-15.0
-25.0
L.H.
Ring
1036.5
-40.0
-25.0
1050.0
-27.0
Girth
LEB
40.0
-25.0
LHEB
1039.0
-47.0
12.0
LEB
1050.0
-27.0
39.0
RHEB
In £CU
A3
A4
A6
B5
86
Composite
Location
used
in
Sequential
Hum
Properties
Tables
1039.0
1031.0
1016.0
1015.0
1017.0
1031.0
1031.0
47.0
-48.3
-24.0
- 7.0
26.0
- 8.0
13.0
12.0
19.6
28.0
28.0
28.0
39.0
39.0
1031.0
1031.0
1018.5
- 8.0
13.0
-14.3
39.0
39.0
26.1
Ring
R.H.
(4)
CO. Absorbed
CO_ Absorbed
AbsOrbed
002
85
86
CoIpostte
tlon
Absorbed.
LoGs-
SM&-8-D-027
II
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39.0
1036.5
R.H. Girth
For
First
Next
centrolds
LEB
LEE
Aft UEB
Aft UEB
L3
B1
RHEB
On Aft Bulkhead
Under
Center
Couch
Temporary
Stowage
Bag -Ctr.
(In-fllght
Location)
Temporary
Stowage
Bag.(In-flIsht
Location)
CO Absorbers
(2)
CO_ Absorbers
(4)
CO2 Absorbers
(4)
CO Absorbers
(2)
CO_ Absorbers
(4)
volume
OCXTIO"
G&N Signal Cond. Panel
Display Keyboard
Sleep Restraint Assy - Right
Sleep
Restraint
Assy
- Left
Food Container
Food Container
Fecal
Stowage
PGA Container
unique
L
L
(IZI)
IUtV 2
1...
T
L
86
Amendment
9/10/70
TABLE
MISSION
J-i
LUNAR
MODULE
3.5-9.2
STOWAGE
VOLUME
CENTROIDS
LM-IO
X
AIB
AIC
AIC
AID
AlE
AIF
AIG
AIH
AIK
AlL
A2
A3
A4
A5
AI0
All
All
AI2
AI3
FLA.
FIB
FIC
FID
FIE
F1F
FIG
F5
F6
F6B
F6C
F7A
F7B
F7C
F7D
F7E
F7F
F7H
F7J
FTK
ICG
Assy
PLSS LIOH Cart
ECS LIOH Cart
262.8
240.5
240.5
270.3
265.9
257.4
257.5
265.9
281.0
273.7
260.0
280.0
244.1
224.3
250.0
263.6
261.2
272.0
300.0
244.5
235.5
242.5
242.8
237.9
235.5
228.0
286.0
270.3
270.3
270.3
238.0
238.0
238.0
238.0
238.0
238.0
238.0
238.0
238.0
Y
-20.8
-15.3
-18.0
-15.0
-20.7
-20./
-20.0
-20.0
-20.0
-20.0
-37.0
0
-3.5
-1.5
8.8
18.8
20.7
0
0
-36.6
-35.5
-35.6
-35.4
-33.6
-37.6
-40.2
17.8
0
0
0
38.0
38.0
38.0
38.0
38.0
38.0
38.0
38.0
38.0
Z
15.4
13.3
13.3
19.0
-6.0
-6.0
-18.0
-18.0
-8.5
-8.5
28.0
-i0.0
13.5
29.3
-11.8
-2.4
5.9
-18.0
0
31.4
38.5
38.6
47.2
55.0
46.6
43.2
66.6
52.8
52.8
52.8
49.8
49.8
41.0
38.4
32.7
31.6
45.5
39.2
42.7
3.5-23
SNA-8-D-027
(III) REV
2
Amendment86
9110170
TABLE
MISSION
J-i
LUNAR
3.5-9.2
MODULE
(Continued)
STOWAGE
VOLUME
CENTROIDS
LM-10
AREA
F7L
F7N
F7P
F8
F9
FIO
X
Y
236.0
238.0
238.0
221.0
219.7
221.0
36.0
38.0
38.0
18.0
0
-18.0
48.0
53.1
53.4
51.0
44.7
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The
arate
data
presented
REFERENCE
in
this
centers-of-gravity
sumables
CSM
CSM
on-board
consumables
consumable
property
4.1
4.2
mass
loading
data
are
for
SPS
Density
PROPERTIES
enable
the
each
in
must
the
following
Mass
Equations
Consumables
and
obtain
spacecraft
and
the
the
sepcon-
CM performance.
current
Section
3.0.
on-board
The
mass
sections:
Properties,
Trapped
Graphs,
SPS
Mass
to
and
Properties,
Propellants,
Loading
and
Windows.
SM RCS
Quad
Properties
4.3
CSM
4.4
CM Ablator
1; :E l:
to
in
RCS
Load
Calculation
Tables
and
Loading
E
Windows
Data
4-1
11 lJ
CSM
compared
provided
DATA
those
overall
be
mission
user
for
affect
data
Consumables
RCS/ECS/EPS
MASS
moments-of-inertia
property
presented
Tank
will
significantly
data
SPS
Mass
section
and
that
CONSUMABLE
L
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TABLE
Table
tanks.
The
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presents
following
units
Height
apply
to
Propellant
Unstretched
Tank
Volume
Stretched
Moment
of
propellant
PSIA,
and
oxidizer
Inertia
The
YAand
and
are
density
ZA
as
Center
the
- Moment
tank
was
of
90.21
Mass
was
ib/ft
SM/SPS
of
Propellant
Center
of
Mass
Moment
of
Inertia
of
pressure
temperature
the
propellant
headings:
Mass
- Ft3
IZZ
for
indicated
- Ft 3
weights;
propellant
characteristics
- Inches
Volume
all
175±5
mass
Tank
Further,
for
of
the
4.1-i
Inertia
used
70°F,
in
- Pounds
- XA
Coordinates
(Iyy)
Iyy;
Moment
calculating
density
for
fuel
-
- Slug-ft
of
Inertia
this
table
was
56.43
Inches
2
IXX-0.0
was
ib/ft
3.
components
for
the
individual
tanks
are
constant
follows:
YA
(inches)
ZA
(inches)
Fuel
Storage
-14.8
-47.8
Fuel
Sump
-48.3
-6.6
Oxidizer
Storage
14.8
47.8
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48.3
6.6
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TABLE
TRAPPED
SPS
4.1-2
MASS
PROPERTIES
Weight
Pounds
SERVICE
- Trapped
Outside
Engine
-
XA
YA
ZA
Tanks
Fuel
29.6
846.9
6.6
0.4
- Oxidizer
47.4
843.0
-7.1
1.6
- Fuel
29.5
832.0
-48.0
-25.0
- Oxidizer
44.7
832.0
48.0
25.0
Line
19.5
829.0
-27.0
-24.0
31.6
829.0
27.0
24.0
202.3
836.0
4.5
3.7
Feedline
Transfer
- Fuel
- Oxidizer
Total
Outside
2 Trapped
in
Tanks
Tanks
Retention
Reservoir
-
Fuel
61.4
- Oxidizer
Vapor
-
97.5
6.2
Fuel
- Oxidizer
Total
Inside
239.1
propellant
trapped
SPS
propellant
load
SPS
propellant.
tables
to
total
tanks
and
outside
for
This
arrive
SPS
74.0
Tanks
i SPS
in
of Gravity
Inches
MODULE
i SPS
2 The
Center
at
amount
appropriate
propellant
outside
should
a particular
tanked
the
tanks
tanks
load
for
equals
be
mission
is
then
SPS
4.1-22
to
arrive
used
in
propellant
a particular
nominal
subtracted
mission
deliverable
at
the
Mass
from
the
the
total
tanked
preceeding
Properties.
less
SPS
trapped
propellant.
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
density
appropriate
at
the
will
usually
oxidizer.
B.
Use
the
density
usually
C.
Subtract
the
KSC
equation
given
be
14.7
appropriate
at
be
the
25°C
for
fuel,
below
and
calculate
and
equation
density
to
the
and
_
where:
calculate
PSIA
obtained
add
this
density
temperature
in
and
step
amount
obtained
A-50
PF
and
and
the final
system
pressure
110±5
PSIA
and 70±5°F.
sample,
negative)
below
pressure
A
(may
from
DENSITY
O F = A-50
m
density
Temperature
in
in
N204
where:
fuel
the
KSC
14.7
the
from
the
be
either
step
or
fuel
and
or
This
measured
oxidizer
sample.
PSIA
temperature.
This
4°C
for
oxidizer
will
density
positive
of
or
B.
EQUATION
Ib/ft
3
degrees
centigrade
C F = Compressibility
factor
- obtain
pressure
- compressibility
graph
this
section.
m
and
the
[57"6095-0"058533(°C)](CF)
=C
PO
of
DENSITY
[93.1048_0.14252(0C)](Co
00
= N20 _ density
°C
= Temperature
CO =
this number
from
on Figure
4.1-1
the
of
this number
from
on Figure
4.1-2
the
of
EQUATION
)
in
in
ib/ft
degrees
centigrade
Compressibility
factor
- obtain
pressure
- compressibility
graph
this
section.
4.1-23
SNA-8-D-027(III)REV
2
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Factor
SNA-8-D-027
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4.1-24
II
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120
PRESSURE,
FIGURE
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1.00140
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1.00120
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I.iJ
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1.00040
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iil
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80
IPO
PRESSURE,
FI GURE
a
4. i- 2
Nitrogen
Tetroxide
160
240
PSIA
Compressibility
4.1-25
200
Correction
SNA-8-D-027
Factor
(III)
REV
2
SERVICE
MODULE
SPS
FUEL
LOADING
WINDOW
FOR
SM
107
AND
SUBSEQUENT
FUEL
FOR
ULLAGE
LOADING
PRESSURE
OF
110±4
PSIA
t-
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Figure
4.1-4
4.1-27
ILl
II
Id
I:
L.
IL
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L
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SNA-8-D-027
l_
12 Y
II
Ii
IL
(III) REV
L,
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2
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Amendment
ii0
5/21/71
SNA-8-D-027(II)
REV
2
Volume
Subsystem
II
LM
Data
Performance
Book
Data
- Crew/Equipment
food
per
CREW / EQU I PMENT
4.2.2
Food
Requirement
Each
man
requires
Sensory
PLSS
PLSS
cc
a
(NASA
DATA
Condensate
The
of
Condensate
Transfer
condensate.
PLSS
shall
be
PLSS
to
135°F.
discharge
Condensate
The
full
open
The
rate
of
The
for
shall
Transfer
relief
valve
pressure
is
flow
all
Thermal
See
of
See
of
of
Volume
VII
Crew
Heat
Heat
storage
mance
S/C
Response
SODB
of
reduced.
Contract
No.
Primary
No.
NAS
of
be
cc
which
4400
Storage
3.8
of
condensate
of
5190
fluid
a maximum
of
Below
is
not
operational
pressure
from
of
865
temperature
is
2.1
to
2.9
is
35°F
psid.
psid.
from
the
0 cc/sec
transfer
to
is
PLSS
to
the
i00 cc/sec.
25 cc/sec.
PLSS
Condensate
The maximum
The maximum
flow
cc/sec.
the
the
MESA
Sample
DATA
Return
Containers
after
Removal
SOURCE)
Appendix.
the
Lunar
(GCTA)
and
should
tasks
Assembly
cracking
for
TV
Temperature
be
limited
mental
-300
Surface
Btu,
time
Color
Camera
_300
Camera
Operation
Tolerance
to
TV
(NASA
DATA
and
Performance
300
Btu,
SOURCE)
data.
Limits
Btu.
Above
complexity
or
high
physical
shivering
is
continuous
and likely
to severely
limit
areas
as the limited
tolerance
tolerance
a maximum
value
Appendix.
(NASA
appropriate
See
4.2.7
S/C
MESA
Thermal
i00
for
Variation
the
accommodates
maximum
condensate
is
appropriate
from
4.2.6
gas
Variations
Thermal
Assembly
The
liquid.
The
rate
4.2.5
day.
Assembly
Transfer
Assembly
is from
flow
rate
for "all
water"
4.2.4
of
SOURCE)
Transfer
liquid
single
cc
calories
Limits
Deleted
4.2.3
3200
demand
and
performance.
Figure
hot and cold
zones.
very
the
is
perforsharply
distracting
4.2-1
indicates
Between
these
these
zones
limited.
LED-540-54
9-1100
G_
664
Aerospace
Corporation
4.2-1
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
Amendment
2
128
7/27/71
Volume
Subsystem
4.'2.8
Data
4o9
Acquisition
See
Table
Quad
III
tions
Camera
3.10-2
and
Stowase
Temperature
configurations
(DAC)
temperatures
of
pallet
the
its
those
Temperature
of
predictions
individual
Reference:
tank
for
135°F
has a
condensate
has
leading
to
psia
3.75
worst
case
120°F,
Figure
Contract
Prlmarv
No.
No.
NAS
664
one-node
representation
local
from
the
between
the
equipment
predicted
the two
actual
increased
mission
average
networks
pallet
profiles
LM-12
Quad
weights
are
III
for a two Pallet
January
1971.
of
stage,
contained
Stowage
Flight
An
the
a containerized
and
analysis
cabin
test
urine
has
items
are
vent
of
empties
within
4.2-8).
fed
through
valve
which
the
the
qualification
15-watt
without
test
45°F
range
at
from
2.5
bay.
and
of
the
psia
IO0°F,
35°F
to
heater
heater
inlet
and outlet
ports,
and are
and during
container
filling.
9-1100
into
of
to
be
35°F
systems
planned
The
a
tube,
opens
analysis
use
tank
and
cabin.
valve
An
temperatures
redundant
case
waste
management
accommodate
urine
line
IV
and
worst
A secondary
quad
temperatures
Two
a
vehicle.
into
shown
between
opens
waste
receptacles
temperature
4.2-7).
The containerized
5.0 _allons
(40 ibs.)
to
operating
vided
to heat
before,
after,
of
outside
and
well
of
consists
descent
cabin.
which
the
mission
temperature
4.2-2
through
indicated
are
reality,
through
qualification
a primary
at
The
The
appendices.
LM-IO
the
the
(see Figure
capacity
of
tank
(see
in
the
PLSS
lumped
Predictions
dated
ii
temperatures
within
a
In
the
system
in
hoses
operating
well
from
mission.
4.2-6.
pallet
orienta-
System
management
transfer
Response
appendix.
in Figures
temperatures
because
510-1765,
Manasement
waste
Thermal
is the thermal
mass
of each
pallet.
LM-12
pallet
are expected
to be less
LM-I1
Temperature
Configuration,
The
design
Figure
equipment.
spacecraft
LMO
management
in
vary
as much
as 15°F
The only
difference
severe
than
for LM-12.
Waste
Canisters
spacecraft
thermal
derived
and
used
for the calculations
Temperature
responses
for
4.'2.10
Film
Predictions
described
temperatures
could
pallet
temperature.
the
Book
pallet
are presented
be noted
that
the
average
in
and
appropriate
within
are
of each
It should
each
Data
Data-Crew/Equipment
predictions
were
made
for the LM-IO
and LM-II
using
the worst
hot and cold
case vehicle
used
profiles
4.2-5.
LM
Temperature
allowable
timelines
II
Performance
for
shows
40°F
to
to
160°F
are
pro-
use
shortly
LED-540-54
Grumman
Aerospace
Corporation
4.2-1.1
L
7
1_
r
TABLE
4.2-1
(CONTINUED)
(_oetor
hklisht
Pounde
kll,
wr-n,,Le
Prtuuury
fuel
Iocndory
Fu_l
hidieer
- Prioery
I_Jol
kclmdory
o
•
Quid
roe1
Oztdtnr
C - PrL,_ry
Voel
|ocondory
Foe L
Oxidiser
_ad
U - Primary
Fuel
Second,try
Fuel
OxLdiler
hltvereble
Priury
l_el
Fuel
OzLdLter
Deliverable
lroel
Ozidt set"
Oeltvereble
68.5t0.8
'964.|
ZA
(6)
4.2-3
O.O
-68.5
$9'6"0'8
905.1
-9.0
!220.9t3.4
92b.9
8.0
68.5t0.8
91_.8
64.5
026.S
39.6'0.8
08S.1
68,0
-Ll,O
220.9*3.4
S2b.9
6_.5
-26.5
68.5t0.8
96_.8
-|.0
-69.0
-6|.5
b|.S
39.6t0.8
905.1
7.0
60.0
220.9t3.4
926.9
-I.O
68.5
68.5t0.8
964.0
-6&.$
26.5
39.6t0.8
gOS.L
-60.0
11.0
926.9
-b4.5
2b.S
220.9t3.
Secondary
Tow!
YA
(6)
quad A -
Qued I
XA
of Grsvity
Inckoo
4
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
SNA-8-D-027
(III)
REV
3
Amendment106
6/22/71
TABLE4.2-1 (CONTINUED)
CSM112 ANDSUBSEQUENT
MISCELLA_'EOUS
CONSUMABLES
CENTER
CSMMISCELLANEOUS
CONSUMABLESWEIGHT
CM/RCS
- HELIUM
CMIECS
Oxygen- Entry
Potable Water (3)
WasteWater (4)
SM/RCS
- Helium
SM/SPS
Helium- StorageBottles
- Tanks(5)
SM/Nitrogen
OF
G_VITY
INCHES
POUNDS
XA
YA
ZA
1.0
,1022.6
-3.1
25.8
(7)
1031.1
-26.9
-34.2
(7)
(7)
1022.6
1022.6
-63.5
-19.7
-16.4
62.5
6.0
983.9
0.0
0.0
87.6
954.7
0.0
0.0
5.4
976.0
2.7
8.9
1.3
874.0
0.0
0.0
29.3
974.6
37.0
-46.0
29.3
859.4
892.9
-40.7
-40.7
41.2
41.2
I
SM/EPS/ECS
I
Oxygen- Hydrogen
H2 Tank 3
H2 Tank 2
H2 Tank 1
02 Tank I
02 Tank 2
02 Tank 3
29.3
330.1
Total -- H
O2
Total on B_ard
Unusable
920.8
-20.9
26.9
330.1
330. i
920,8
938.0
-27.4
22.5
54.5
-30.0
87.9
909.0
-14.8
12.1
990.3
926.6
1078.2
925.1
-8.6
-9.1
17.1
16.7
- H2
H2
H2
O2
O2
02
Usable
- H2
- H
2
- H2
O2
O2
02
Usable
Total
_ominal
- H2
- 0
Usable
Loading.
For
Liftoff
974.6
1.2
1.2
859.4
892.9
37.0
-40.7
-40.7
-46.0
41.2
41.2
6.6
6.6
6.6
920.8
920.8
-20.9
-27.4
26.9
54.5
938.0
22.5
-30.0
3.6
909.0
-14.8
12.1
19.8
926.6
-8.6
17.1
23.4
923.8
-9.6
16.4
28.1
974.6
37.0
-46.0
28.1
859.4
-40.7
41.2
28.1
323.5
323.5
892.9
920.8
920.8
-40.7
-20.9
-27.4
41.2
26.9
54.5
323.5
938.0
22.5
-30.0
84.3
909.0
970.5
1054.8
926.6
-14.8
-8.6
12.1
17.1
925.1
-9.1
16.7
individual
Mission
Unusable
Total
- H2
- 0
Unusable
1.2
values
see
Section.
4.2-4
SNA-8-D-027
li
II
(III)
l=
REV
3
i._
L.
"
"
L
Amendment
86
9/10/70
Table
CSM
112
and
4.2-1
Subsequent
(Continued)
Miscellaneous
Consumables
WEIGHT
CENTER
POUNDS
CSM
MISCELLANEOUS
CM/RCS
OF
CONSUMABLES
XA
- HELIUM
GRAVITY
INCHES
I
ZA
25.8
1.0
1022.6
(7)
1031.1
-26.9
-34.2
(7)
(7)
1022.6
-63.5
-16.4
1022.6
-19.7
62.5
6.0
983.9
0.0
0.0
87.6
954.7
0.0
0.0
5.4
976.0
2.7
8.9
1.3
874.0
0.0
0.0
29.3
974.6
37.0
29.3
859.4
-40.7
-46.0
41.2
29.3
892.9
-40.7
41.2
330.1
330.1
920.8
-20.9
26.9
330.1
920.8
938.0
-27.4
22.5
-30.0
CH/ECS
Oxygen
Potable
Waste
- Entry
Water
Water
SM/RCS
- Helium
SM/SPS
Helium
(3)
(4)
- Storage
- Tanks
Bottles
(5)
SM/Nitrogen
SMIEPSIECS
1
Oxygen
- Hydrogen
02
02
02
Total
Total
on
Unusable
H2
O
Bo2ard
87.9
909.0
-14.8
990.3
926.6
-8.6
12.1
17.1
1078.2
925.1
-9.1
16.7
37.0
-40.7
-40.7
-46.0
1.2
- H2
H2
6.6
6.6
6.6
938.0
22.5
54.5
-30.0
02
909.0
-14.8
12.1
926.6
-8.6
17.1
23.4
923.8
-9.6
16.4
28.1
974.6
28.1
859.4
-40.7
41.2
28.1
323.5
323.5
892.9
920.8
-40.7
-20.9
-27.4
41.2
26.9
- H2
Usable
Total
_ominal
84.3
- H2
- 0
Usable
Loading.
920.8
938.0
323.5
02
970.5
1054.8
For
values
Liftoff
41.2
26.9
3.6
- H 2
02
-20.9
-27.4
19.8
- H2
- 0
Unusable
H2
02
41.2
892.9
920.8
920.8
Unusable
Usable
974.6
859.4
1.2
1.2
H2
02
02
Total
54.5
see
37.0
22.5
909.0
926.6
-14.8
-8.6
925.1
-9.1
individual
Mission
-46.0
54.5
-30.0
12.1
17.1
16.7
Section.
4.2-4.1
SNA-8-D-027(III)REV
II I/ I: IJ I: E
L
L
E
E
L
L: L:
Ii I.: l_
"
2
'
_-
L--
L
Amendment
86
9/10/70
This
page
intentionally
4.2-4.2
left
blank
SNA-8-D-027
(III) REV
2
Amendment
66
9/12/69
TABLE
CSM
This
table
- CONSUMABLE
contains
tolerances,
temperatures
4.2-1
and/or
and
the
LOADS
AND
consumable
UNCERTAINTIES
loads,
uncertainties
pressures.
aL
WEIGHT
nominal
associated
loading
(1)CENTER
POUNDS
XA
COMMAND
MODULE
Nominal
Load
RCS
System
I
-
System
1
- Oxidizer
System
2
-
System
2
- Oxidizer
Loaded
Total
Fuel
Fuel
-
Fuel
-
Oxidizer
Loaded
Maximum
Trapped
System
1
-
System
I
- Oxidizer
System
System
2
2
- Fuel
- Oxidizer
Trapped
Fuel
YA
ZA
Trappea
44.2:0.9
78.3*1.6
1022.6
1022.6
26.6
59.8
44.2*0.9
78.3tl.6
1022.6
-52.8
38,7
88.4'1.3
1022,6
(Maximum)
1022.6
-38.7
2.3
-45.8
14,5
52.8
65.5
45,8
156.6:2.3
1022.6
245.0:2.6
1022.6
-7.3
57.0
1022.6
-38.7
52,8
6.4
1022.6
1022.6
26.6
-52.8
59.8
38.7
11.4
1022.6
2.3
65,5
13.3
1022.6
23.1
1022.6
36.4
1022.6
-7.3
37.3*0.9
I022.b
-38.7
52.8
66.6'1.6
1022,6
1022.6
26.6
-52.8
59.8
38.7
1022.6
2.3
65.5
6.9
1i.7
- Fuel
- Oxidizer
Deliverable
System
-45.5
14.b
62.7
40.0
62.6
56.5
(6)
1
-
System
System
1
2
- Oxidizer
- Fuel
System
2
- Oxidizer
Deliverable
Total
GRAVITY
(2)
Loaded
Total
OF
INCHES
l'uel
-
Fuel
-
Oxidizer
37.8*0.9
66.9*1,6
75._1.3
133.5'2.3
20B.6t2.6
Deliverable
4.2-I
1022.6
1022.0
1022.6
SNA-8-D-027
-45.8
14.4
-7.3
(III)REV
45.7
62.7
56.5
2
!
Amendment
66
9/12/69
Tab]t
SERVICE
MODULE
- Nominal
4.2-1(Contlnued)
(l)Center
Load
Weilht
of Gravity
Inches
Rcs(2)
Quad
A - Loaded
Prlmar_y
- Fuel
Secondary-Fuel
Oxidizer
Ouad
B -
Loaded
Pri_uary
-
Fuel
Secondary-Fuel
Oxidizer
Quad
C -
Loaded
-
Primary
Fuel
Secondary-Fuel
Oxidizer
Quad
D -
Loaded
Primary
-
Fuel
Secondary-Fuel
Oxidizer
Loaded
Primary
- Fuel
Secondary-Fuel
Oxidizer
Loaded
- Fuel
-Oxidizer
TOTAL LOADED
Max.
XA
964.8
y_
8.0
ZA
-68.5
40.3±0.8
985.1
-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
7.0
69.0
40.3_0.8
985.1
225.4t3.4
926.9
-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
901:6±6.8
985.1
0.0
0.0
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
942.1
0.0
0.0
Fuel
1.4
964.8
8.0
-68.5
- Secondary
Fuel
0.7
985.1
-7.0
-69.0
4.5
926.9
8.0
-68.5
Oxidizer
Primary
Fuel
1.4
- Secondary
Fuel
0.7
B -
-26.5
-ii.0
926.9
64.5
-26.5
Fuel
1.4
964.8
-8.0
68.5
- Secondary
Fuel
0.7
985.1
7.0
h9.0
4.5
926.9
Fuel
1.4
964.8
-04.5
26.5
Fuel
0.7
985.1
-68,0
II.0
920.9
-64.5
26.5
Oxidizer
D - Primary
Secondary
4.5
- Oxidizer
Primary
Trapped
Secondary
Fuel
Fuel
Trapped
Oxidizer
(P_XI_H)
0.0
0.0
2.8
985.1
0.0
o.o
92(_.9
0.0
0.0
971.0
0,0
o.o
18.0
916,9
0.o
o.o
26.4
940.9
0.0
0.0
4.2-2
IJ
L:
K
L
K
L
L
08.5
964.8
8.4
Fuel
-8.0
5.6
18.0
Oxidizl, r
TRAPPED
64.5
68.0
C - Primary
-
TOTAL
964.8
985.1
4.5
- Oxidizer
Quad
68.5
964.8
A - Primary
-
Quad
-8.0
69.9*0.8
L342.4_7.2
Trapped--Quad
Quad
Pounds
69.9±0.8
SNA-8-D-027
K
L
L
T =
(III) REV
2
_, '
L.
k
O_
C3
|
I
r_
O
.......
I
°.o°°°o.o,.,,°o,,°°.o°.,°°o°,
I
oo
I
t_
°.°,o°.,o.°,lO.,o°oo°o°°,.o°.o°,oo°.
,..°o.°,°°.,,°°.oo°o
.....
oo.
e_
0
c
0
<.J
u
c
qU
_3
oh
I
o°...,.°,°°o,,o°°,o°°o,,o..°o,o.°.._
IX
X
I,.
q-
,IJ
oo°.oo.,.o.o,...°,,,.,...°..o.o.
t',,4
•
Z
.....
....
,.o,o.°°.o°,.,.°.0,°,,o,_,'°'°
_
5
,..,°,,°.o,°.,,°°..,.o.,.
_0
U
U
g
_
......
•
....
NNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNNN
..................
_. ..........
_¢;_;_;_;
11 !1 E
E
L. 1: L- L
L
I:
L
E
_
|;
I_ E
L
L
I
II
I
I
IN
'llillli't-illlll/ptilli/li- lillill'lil'liilltilllilltiltllvtitm'llltmd
1!_ _
I"-_
T
lr_
1
__
_
_
I""
'lr"
l'w
T_
1_"I1
!
_-
,--
,:-
•
•
v-
.-
I:
!b"
14 _
C
z
•
4.3
CM/RCS
AND
SM/RCS
4.3. i
CM/RCS
Table
LOAD
4.3-1
is
CALCULATION
the
CM/RCS
by KSC for each mission.
fuel and oxidizer
loading
F and
4.3.2
TABLES
load
AND
LOADING
calculation
Figures
windows
4.3-4
to be
WINDOWS
table
to be
completed
and 4.3-5 are the CM/RCS
used by KSC for Mission
subsequent.
SM/RCS
Table 4.3-2 is the SM/RCS
load summary
table to be completed
by KSC for each mission.
Tables
4.3-3
through
4.3-6 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.
SM/RCS
loading
windows
Figures
to be used
4.3-1 through
4.3-3 are the
by KSC for Mission
F and sub-
sequent.
4.3.3
CSM/RCS
Mass
Calculations
for
Horizontal
The primary
method
for determining
loaded
in the CSM horizontal
tanks
Tanks
the amount
of RCS propellant
is by actual
propellant
weight
as determined
by using the bleed unit scales.
determined
by the bleed unit scales
is verified
as outlined
in Tables
4.3-1,
and 4.3-3 through
The weight
as
by PV calculation
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 appropriate
sub-system
manager
will
above methods
will be used.
4.3-1
Jointly
determine
which
of
SNA-8-D-027(III)REV
the
2
TABLE
4.3-1
COMMAND MODULE RCS LOADING
REQUIREMENTS,
PARAMETERS
AND CALCULATIONS
Load
Parameters
and
Fuel
Tank
A.
Tank
Volume
AI.
Liquid
A2.
Total
B.
Initial
@
Line
A +
Final
A1
Propellant
B
Tank
A
Tank
B
(in 3)
(in 3)
in
in
Bleed
Bleed
Load
less
Loading
F.
Specification
G.
Total
Item
Unit
Prior
Unit
After
by
Item
Weigh
C
Tank;
(ib)
Temperature
(°F)
Load
@
70
CM/RCS
Propellant
D above
or Item
Z5°F
(Ib)
Load
from
P below
(ib)
±0.3
Ullage
Density
(ib/in3);
equation
solve
where
the
0.0329456
-
density;
Calculation
in
E
0o -
OF
"
Oo
- 0.451591(I0-4)(II.8-T)+0.05475906
Specification
±0.3
following
T - Temperature
above
and DF " fuel
oxidizer
density.
H.
B
(ib)
E.
GI.
Tank
(Ib)
Weight
Item
Oxidizer
(in 3)
Weight
Loading
D.
PSIG
Volume
to Loading
C.
0.0
A
Calculations
(0.186979)(I0-4)(T)
Ullage
@
Maximum
E above;
Minimum
I.
Tank
Stretch
J.
Volume
of
GHE-GSE
Line
(in 3)
K.
Volume
of
S/C
Line
(in 3)
L.
GSE
M.
Bladder
N.
Stabilized
O.
Ullage
Line
(PSIG)
Equilibrium
Volume
(in3);
by
Pressure
solve
substituting
in
Volume
Propellant
(in3/PSl)-
(PSIG)
Pressure
contained
P.
GHE
Pressure
equation
Ullage
Factor
the
above
ffiJ
load
_
by
P.V.
(PSIG)
the
the
following
values
indicated
-
I (N
steps.
+ M +
14.7)
- K
(ib)
SNA-8-D-O27(III)REV
4.3-2
11 li
U
L
1: E
L
L
L
U
U
2
L
L
TABLE
SERVICE
MODULE
RCS
4.3-2
PROPELLANT
LOAD
SUMMATION
Actual:
QUAD A
(Pounds)
Secondary
Primary
Fuel
Fuel
Total
Total
Oxidizer
+2.3
Total
Oxidizer
+2.3
Total
Oxidizer
+2.3
Total
Oxidizer
+2.3
+0.7
QUAD B
(Pounds)
Secondary
Primary
Fuel
Fuel
+0.7
Total
QUAD C
(Pounds)
Secondary
Primary
Fuel
Fuel
Total
+0.7
QUA/) D
(Pounds)
Secondary
Primary
Fuel
Fuel
+0.7
Total
Total
Fuel
SM/RCS
Propellant
Loaded
(ib)
Oxidizer
+1.4
4.3-3
+4.6
SNA-8-D-O27(III)REV
2
TABLE
SERVICE
MODULE
RCS
LOADING
4.3-3
PARAMETERS
AND
CALCULATIONS
Fuel
Loading
B.
Tank
BI.
Liquid
C.
Tank
D.
E.
to
Final
After
*F.
(in3/PSI)
Bleed
Bleed
A.
Tank
Volume
AI.
Liquid
B.
Tank
Stretch
C.
Tank
Volume
CI.
Liquid
D.
Tank
Unit
Unit
Load
(ib)
(Item
D
Nominal
and
0.088
Oxidizer
Tanks
Volume
of
S/C
Line
(in 3)
I.
Volume
of
S/C
Line
(in 3)
H.
Bladder
J.
GSE
I.
Stabilized
(PSIG)
Pressure
Secondary
F.
GSE
Pressure
Combined
Load
(ib)
GHE
for
(in 3)
G.
Line
Pressure
(PSIG)
Pressure
J.
Loading
K.
Oxidizer
(PSIG)
Equilibrium
Pressure
(PSIG)
GHE
(PSIG)
Temperature
(°F)
Equilibrium
Pressure
(PSIG)
Liquid
Pressure
N.
(in3/PSI)
Line
(in 3)
Primary
Factor
GHE-GSE
Line
M.
(in 3)
of
GHE-GSE
Stabilized
PSIG
Volume
of
L.
0.045
E.
Volume
Bladder
@ 0.0
Volume
Parameters
H.
K.
(in3/PSI)
Oxidizer
(in 3)
Stretch
Primary
±5 ° F
Line
(in 3)
Factor
Line
PSIG
less
E)
70
0.0
(Ib)
Specification
at
@
Volume
Primary
PV
Resulting
Oxidizer
(in 3)
Line
0.034
(ib)
of
Loading
Item
G.
of
Loading
Weight
PSIG
(in 3)
Factor
Weight
Prior
@ 0.0
Volume
Stretch
Initial
(°F)
(in 3)
Line
Secondary
Fuel
Temperature
Volume
A
Oxidizer
Sec£ndary
A.
- QUAD
Density
(ib/in3);
equation
(4) below
ture @ J above
Close-Out
solve
where
T =
Tempera-
(PSIG)
Specification
Ullage
@ A
L.
Above
Specification
above
Value
(ib)
@
Temperature
J
Maximum
Maximum
Mimimum
Minimum
O.
Ullage
Volume
following
the values
(in3).
Solve
M.
the
PV
Calculated
equation
equation
by substituting
contained
in the indi-
stituting
above
cated
steps.
Ullage
= H (_)J
-
L
S)(L
K +
and
the
of
tank
gas
and
for
(ib);
below
by
where
(in 3)
Fo =
both
in
U
in
solve
sub-
contained
steps
and He system,
oxidizer
load
_
Load
(6)
values
indicated
Volume
Volume
Oxidizer
(5)
the
=
both
tanks
PV calculated
tanks
±2.3
(C
+
Primary
P.
Loading
Q.
Tank
R.
Liquid
S.
Tank
Temperature
Volume
Line
Stretch
(in 3)
Volume
Factor
+
14.7)
+
S(M)-
I
N.
Fuel
(°F)
@ 0.0
Specification
ture J above
(4)
PSIG
Oxidizer
(11.8
Nominal
(ib)
Value
Density
- T)
=
@ Tempera-
0.451591(10
-4 )
+ 0.05475906
(in 3)
(in3/PSI)
(5)
U = E
_
(6)
F o = K(A
-
(B+D)(I+H+I4.7)
0.0652
4.3-4
+ C +
A1
+
SNA-8-D-027
C1
-
U +
F)
(I II) REV
2
L
TABLE
SERVICE
T.
Fuel
MODULE
Density
equation
(ib/in3);
(i)
Temperature
PV
below
@
and
LOADING
AND
CALCULATIONS
- QUAD
A
T =
for
Combined
Secondary
Fuel
Tanks
Volume
of
GHE-GSE
Line
(in 3)
V.
Volume
of
S/C
Line
(in 3)
W.
GSE
X.
Bladder
Y.
Stabilized
GHE
Pressure
(PSIG)
Pressure
(PSIG)
Equilibrium
Pressure
Z.
PARAMETERS
solve
where
U.
Line
(Continued)
P above
Parameters
Primary
RCS
4.3-3
(PSIG)
Specification
PV
Temperature
Value
P above
@
(ib)
Maximum
Minimum
Z1.
PV
calculated
Solve
fuel
equations
by substituting
tained
in the
Z2.
below
load.
Total
calculated
@
fuel
Nominal
temperature
fuel
load
F plus
Fuel
density
(2)
UV =
U (w-Y)
\y
_ X
FL
= T
Secondary
Load
by
H above
(Ib)
(ib)
Item
(i)
k(3)
=
(Q + R
±0.7
ZI)
0.0329456
(0.186979)(i0-4)(T)
-
(C
+
- UV +
S)
(Y
V +
B +
+
X +
BI
F
- T
)
substitute
(ib)
fuel
load
item
Z4
is
determined
for
item
by
P.V.
calculation,
then
in
Equation
Three
F.
4.3-5
\
14.7)
Fuel
P.V.
secondary
(3),
(3)
values
conindicated
F L = PV
(Item
* If
the
above
or tanked
tank and
value
*Z4.
(ib)
and
steps
where
U V = Volume
gas
(in 3) in the primary
Specification
Z3.
load
(2)
SNA-8-D-O27(III)REV
2
TABLE4.3-4
SERVICE
MODULE
RCSLOADING
P_TERS ANDCALCULATIONS
- QUAD
B
Fuel
Oxidizer
Secondary
A.
Loading
B.
Tank
BI.
Liquid
C.
Tank
D.
Initial
Temperature
Volume
After
of
(in3/PSl)
Bleed
Loading
Weight
of
A.
Tank
Volume
AI.
Liquid
B.
Tank
Unit
C.
Tank
Volume
CI.
Liquid
D.
Tank
Resulting
Item
G.
Load
(ib)
(Item
D
Nominal
and
(ib)
Line
(in 3)
F.
Volume
of
S/C
Line
(in 3)
(in 3)
G.
GSE
I.
Volume
of
S/C
Line
(in 3)
H.
Bladder
J.
GSE
I.
Stabilized
(PSIG)
Line
Stabilized
Pressure
Equilibrium
(PSIG)
Primary
Liquid
Close-Out
Pressure
(PSIG)
N.
Specification
Pressure
Ullage
J.
Loading
Equilibrium
(PSIG)
K.
Oxidizer
Density
equation
ture
@ J
@ A
L.
Above
Specification
(in3).
Solve
M.
the
PV
equation
by substituting
contained
in the indi-
= H (_-Z--K)J
- L
(C +
s)(e
Primary
+
K +
14.7)
+
S(M)-
Tank
R.
Liquid
S.
Tank
(in 3)
the
Load
(6)
values
indicated
of tank
(Ib);
below
by
contained
steps
where
gas (in 3) in
and
for
solve
subin
U =
both
the
tanks
F o -- PV calculated
both
tanks
-+2.3
N.
Specification
Nor_inal
J above
Value
@ Tempera-
(ib)
(°F)
(4)
Volume
J
I
Fuel
Temperature
and
and He system,
oxidizer
load
_
ture
Q.
= Tempera-
@ Temperature
Oxidizer
(5)
stituting
above
Volume
Volume
Loading
T
Maximum
Calculated
equation
steps.
P.
solve
where
Minimum
Volume
Ullage
(ib/in3);
Value
(Ib)
Minimum
cated
(°F)
(4) below
above
Maximum
following
the values
(PSIG)
Temperature
above
Ullage
(PSIG)
(PSIG)
M.
O.
GHE
Pressure
Pressure
Pressure
Tanks
GHE-GSE
Line
Pressure
Combined
Oxidizer
of
GHE-GSE
GHE
for
Secondary
Volume
of
L.
0.088
E.
Volume
Bladder
(in3/PSl)
Load
H.
K.
PSIG
(in 3)
Factor
Parameters
Primary
±5 ° F
Line
0.0
less
E)
70
@
Volume
Stretch
0.045
(Ib)
Specification
at
(in3/PSl)
Oxidizer
(in 3)
Line
PSIG
(in 3)
Factor
Primary
Unit
@ 0.0
Volume
Stretch
PV
_F.
Oxidizer
(in 3)
Line
0.034
(Ib)
Bleed
Loading
PSIG
(in 3)
Factor
Weight
to
Final
@ 0.0
Volume
Stretch
Secondary
(°F)
(in 3)
Line
Prior
E.
Fuel
@
0.0
PSIG
Oxidizer
Density
(11.8
-
(5)
U = E
_
(6)
Fo
T)
+
= 0.451591(10
-4 )
0.05475906
•
Line
Stretch
Volume
Factor
(in)
(in3/PSI)
-
(B+D)(I+I{+I4.7)
0.0652
4.3-6
= K(A
+
C + AI
+
CI
SNA-8-D-027
- U +
(III)
H
E
REV
F)
2
L
L
TABLE
SERVICE
T.
Fuel
MODULE
Density
equation
(ib/in3);
(i)
below
Temperature
PV
@ P
and
T
_qD
CALCULATIONS
-
QUAD
B
=
for
Combined
Second____ary Fue]
Tanks
Volume
of
GHE-GSE
Line
(in 3)
V.
Volume
of
S/C
Line
(in 3)
W.
GSE
X.
Bladder
Y.
Stabilized
GHE
Pressure
(PSIG)
Pressure
(PSIG)
Equilibrium
Pressure
Z.
PARAMETERS
solve
where
U.
Line
(Continued)
LOADING
above
Parameters
Primarv
4.3-4
RCS
(PSIG)
Specification
PV
Temperature
P
Value
@
above
(ib)
Maximum
Minimum
ZI.
PV
calculated
Solve
Z2.
by substituting
tained
in the
the
above
below
FL =
load.
PV
calculated
@
F
(i)
Fuel
(2)
Uv
*(3)
Fe
Nominal
load
plus
=
=
by
secondary
substitute
H above
(Q
+
±0.7
ZI)
= 0.0329456
,
(0.186979)(I0-4)(T)
(w-y)
U \y
_ X
T
(ib)
(Ib)
Item
density
Secondary
Load
fuel
temperature
fuel
(Item
(3),
(3)
values
conindicated
or tanked
tank
and
Total
*Z4.
(ib)
and
steps
where
U V = Volume
gas
(in 3) in the primary
Specification
Z3.
load
(2)
value
*If
fuel
equations
R
-
(C
Uv
+
+
S)
(Y
V +
B +
+
X +
B1
-
14.7)
F
¥
)
Fuel
P.V.
fuel
(ib)
load
item
Z4
is
determined
for
item
by
P.V.
calculation,
then
in
Equation
Three
F.
4.3-7
SNA-8-D-027(III)REV
2
TABLE4.3-5
SERVICE
MODULE
RCSLOADING
PARA_TERS
ANDCALCULATIONS
- QUAD
C
Fuel
Oxidizer
Secondary
A.
Loading
B.
Tank
BI.
Liquid
C.
Tank
D.
Temperature
Volume
Initial
Final
of
After
(in3/PSl)
Bleed
Loading
Weight
Bleed
A.
Tank
Volume
AI.
Liquid
B.
Tank
Stretch
C.
Tank
Volume
CI.
Liquid
D.
Tank
Unit
Unit
Resulting
Item
Load
(ib)
(Item
D
Nominal
±5 ° F
(Ib)
(in 3)
F.
Volume
of
S/C
Line
(in 3)
I.
Volume
of
S/C
Line
(in 3)
H.
Bladder
J.
GSE
I.
Stabilized
(PSIG)
Line
Pressure
(PSIG)
Equilibrium
(PSIG)
(PSIG)
J.
Loading
Temperature
(PSIG)
K.
Oxidizer
(°F)
Density
equation
Liquid
Pressure
Close-Out
ture
(4)
(ib/in3);
solve
below
where
T =
Tempera-
Value
@ Temperature
@ J above
(PSIG)
L.
N.
(PSIG)
Equilibrium
Pressure
Primary
GHE
Pressure
Pressure
M.
Tanks
Line
GSE
Pressure
Oxidizer
GHE-GSE
G.
Pressure
Combined
of
(in 3)
GHE
for
Secondary
VOlume
Line
Stabilized
0.088
E.
GHE-GSE
L.
(in3/PSI)
Load
of
Bladder
PSIG
(in 3)
Factor
and
Volume
K.
@ 0.0
Volume
Parameters
H.
Line
0.045
less
E)
70
(in3/PSl)
Oxidizer
(in 3)
Stretch
Primary
Specification
at
(in 3)
Factor
Line
PSIG
(ib)
i
G.
@ 0.0
Volume
Primary
PV
*F.
Oxidizer
(in 3)
Line
0.034
(ib)
of
Loading
PSIG
(in 3)
Factor
Weight
to
@ 0.0
Volume
Stretch
Secondary
(°F)
(in 3)
Line
Prior
E.
Fuel
Specification
Ullage
@ A
Above
Specification
above
(ib)
J
Maximum
Maximum
Minimum
Minimum
O.
Ullage
Volume
(in3).
Solve
M.
the
PV
Calculated
equation
following
the values
equation
by substituting
contained
in the indi-
stituting
above
cated
steps.
Ullage
= H
_
S)(L
+ K +
and
the
of
tank
gas
and
for
(ib);
below
by
where
(in 3)
in
U
in
solve
sub-
contained
steps
and He system,
oxidizer
load
-
Load
(6)
values
indicated
Volume
Volume
Oxidizer
(5)
the
=
both
tanks
F o = PV calculated
both
tanks
±2.3
(C +
Primary
P.
Loading
Q.
Tank
R.
Liquid
S.
Tank
Line
(in 3)
Volume
Stretch
+
S(M)-
I
N.
Fuel
Temperature
Volume
14.7)
Factor
(°F)
@ 0.0
Specification
ture J above
(4)
Oxidizer
PSIG
(11.8
L
E
Value
Density
- T)
+
=
@ Tempera-
0.451591(10
-4 )
0.05475906
(in 3)
(in3/PSl)
(5)
U
= E
E
E
_
(6)
F o = K(A
-
(B+D)(I+H+I4.7)
0.0652
4.3-8
11 11
Nominal
(ib)
L
E
+
C +
AI
+
SNA-8-D-027
E
E
L
E
E
C1
- U +
(III)
E
F)
REV
L
2
L
L
TALBE4.3-5 (Continued)
SERVICE
MODULE
RCSLOADING
PARA>_TERS
ANDCALCULATIONS
- QUAD
C
T.
Fuel Density (Ib/in3); solve
equation (i) below where T =
Temperature@P above
PV Parameters
for Combined
Primar_
and
Secondary,
Fuel
Tanks
U.
Volume
of
GHE-GSE
Line
(in 3)
V.
Volume
of
S/C
Line
(in 3)
W.
GSE
X.
Bladder
Y.
Stabilized
Line
Pressure
(PSIG)
Pressure
(PSIG)
Equilibrium
Pressure
Z.
GHE
(PSIG)
Specification
PV
Temperature
P
Value
above
@
(ib)
Maximum
Minimum
ZI.
PV
calculated
Solve
by
substituting
tained
Z2.
fuel
equations
in
the
above
(3)
below
con-
indicated
load.
PV
calculated
@
Total
(i)
*(3)
fuel
Nominal
load
F plus
Fuel
FL =
by
H
(ib)
±0.7
ZI)
=
0.0329456
(0.186979)
_
T
above
(Ib)
Item
density
Secondary
Load
fuel
temperature
(2) uv = u
.
(10 -4 ) (T)
- (c + s) (Y + x + 14.7)
(Q + R
- UV +
V +
B +
BI
F
- _
by
P.V.
)
Fuel
P.V.
secondary
(3),
values
FL =
(Item
*If
the
or tanked
tank
and
value
*Z4.
(Ib)
and
steps
where
U V = Volume
gas (in 3) in the primary
Specification
Z3.
load
(2)
substitute
fuel
(ib)
load
item
is
Z4
determined
for
item
calculation,
then
in
Equation
Three
F.
4.3-9
SNA-8-D-O27(III)REV
2
TABLE4.3- 6
SERVICE
MODULE
RCS
LOADING
PARAMETERS
AND
CALCULATIONS
Fuel
Loading
B.
Tank
BI.
Liquid
C.
Tank
D.
Initial
Final
After
*F.
of
Bleed
Unit
Load
(ib)
AI.
Liquid
B.
Tank
Tank
CI.
Liquid
D.
Tank
(Item
Nominal
±5 ° F
D
PV
less
(Ib)
Line
(in 3)
F.
Volume
of
S/C
Line
(in 3)
G.
GSE
Line
(in 3)
H.
Bladder
J.
GSE
I.
Stabilized
M.
Primary
Oo
Equilibrium
Q.
Tank
R.
Liquid
S.
Tank
Oxidizer
(PSIG)
Pressure
(PSIG)
Equilibrium
(PSIG)
Temperature
Density
@ A
(ib/in3);
L.
Above
Specification
above
(ib)
(in3).
Solve
by
M.
the
PV
Calculated
equation
substituting
in the indi-
stituting
and
the
steps.
above
Volume
Volume
and He system,
oxidizer
load
= H (L---2---K)-J
- L
+
S)(L
Temperature
+
K +
14.7)
+
S(M)-
Line
Stretch
(in 3)
Volume
Factor
= Tempera-
Temperature
Load
(6)
values
indicated
of tank
T
(ib);
below
by
solve
sub-
contained
steps
where
gas
(in 3) in
and
for
J
in
U =
both
tanks
±2.3
N.
Fuel
the
F o = PV calculated
both
tanks
I
Specification
ture J above
Nominal
(ib)
Value
@ Tempera-
(°F)
(4)
Volume
@
Oxidizer
(5)
solve
where
Value
Minimum
equation
contained
(°F)
equation
(4) below
ture
@ J above
Minimum
Primary
Loading
Pressure
Maximum
(C
Pe
K.
GHE
Maximum
Volume
Ullage
Loading
Close-Out
Ullage
following
the values
cated
J.
(PSIG)
Specification
Ullage
(PSIG)
Liquid
Line
Pressure
(PSIG)
Pressure
N.
(PSIG)
Pressure
Tanks
GHE-GSE
S/C
Pressure
Combined
Oxidizer
of
of
GHE
for
Secondary
Volume
Volume
Pressure
0.088
E.
I.
Stabilized
(in3/PSI)
Load
(in 3)
L.
PSIG
(in 3)
Factor
and
Line
Bladder
@ 0.0
Parameters
GHE-GSE
K.
0.045
Oxidizer
Volume
Stretch
of
Line
(in3/PSl)
(in 3)
Line
PSIG
(in 3)
Factor
Volume
Volume
H,
@ 0.0
Volume
Stretch
C.
E)
70
Oxidizer
(in 3)
Line
Primary
Specification
at
Volume
(ib)
i
G.
Tank
Primary
Unit
Bleed
A.
0.034
(ib)
of
Loading
Resulting
Item
(in3/PSl)
Loading
Weight
PSIG
(in 3)
Factor
Weight
to
@ 0.0
Volume
Stretch
Secondary
(°F)
(in 3)
Line
Prior
E.
Fuel
Temperature
Volume
D
Oxidizer
Secondary
A.
- QUAD
@ 0.0
PSIG
Oxidizer
Density
(11.8
-
(5)
U = E
_
(6)
Fo
T)
+
= 0.451591(10
-4 )
0.05475906
(in 3)
(in3/PSl)
0.0652
4.3-10
= K(A
+ C +
(B+D)(I+H+I4.7)
AI
+
C1
SNA-8-D-027
H
- U +
F)
(III)REV
E
h
2
L
L
i_
TABLE
SERVICE
T.
Fuel
MODULE
Density
equation
FV
RCS
(Ib/in3);
(i)
Temperature
below
and
LOADING
AND
CALCULATIONS
- QUAD
D
T -
for
Combined
Secondary
Fuel
Tanks
Volume
of
GHE-GSE
Line
(in 3)
V.
Volume
of
S/C
Line
(in 3)
W.
GSE
X.
Bladder
Y.
Stabilized
GHE
Pressure
(PSIG)
Pressure
(PSIG)
Equilibrium
Pressure
Z.
PARAMETERS
solve
where
U.
Line
(Continued)
@ P above
Parameters
Primary
4.3-6
(PSIG)
Specification
PV
Temperature
Value
P above
@
(Ib)
Maximum
Minimum
ZI.
PV
calculated
Solve
fuel
equations
by substituting
tained
in the
Z2.
Z3.
load
(2)
the
above
and
(ib)
(3)
below
values
conindicated
steps where
U V = Volume
gas (in 3) in the primary
or tanked
tank and
F L = PV
load.
calculated
fuel
Specification
Nominal
value
@ temperature
Total
fuel
(Item
load
F plus
(i)
Fuel
(2)
UV = U
(ib)
Item
density
H above
(lb)
±0.7
ZI)
= 0.0329456
•
(0.186979)(I0-4)(T)
_
-
(C + S)
(Y + X +
14.7)
F
_3) FL = T (O + R - Uv + V + B + B1 - ¥ )
*Z4.
Secondary
Load
*If
by
secondary
Equation
Three
Fuel
P.V.
(ib)
fuel
load
(3),
is
determined
substitute
item
4.3-11
by
Z4
P.V.
for
calculation,
item
then
in
F.
SNA-8-D-027
(III)REV
2
L
240
230
220
cO
Z
v
,-I
210
.<
200
190
180
170
160
65
67
69
TEMPERATURE
Figure
(_F)
CSM 104 AND SUBSEQUENT
SECONDARY
FUEL TANK ULLAGE
VOLUME
RANGE
4.3-1
4.3-12
!1 1_ E
L
E
L
L
L
SNA-8-D-O27(III)REV
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65
64
65
66
67
73
FUEL
Figure
4.3-2
SM
RCS
TEMPERATURE
PRIMARY
FUEL
4.3-13
(OF)
TANK
LOAD
WINDOW
SNA-8-D-027
(llI) REV
2
_u+t:
rttt
_L
!_4".', i]!
231
22).
230
J.
II
f-%
C_
Z
229
4_
0
4_
228
n
L_
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227
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226
t,q
)-4
).-4
225
0
::U
224
_'3
223
:2..
222
F::" 7-i
221
:_
64
65
66
67
68
OXIDIZER
Figure
4.3-3
69
70
71
TEMPERATURE
[l
L; E
l_
73
74
75
76
(°F)
SM RCS COMBINED
PRIMARY-SECONDARY
OXIDIZER
TANK LOAD WINDOW
4.3-14
I1
72
12 L
L
E
L: ]J
SNA-8-D-027(III)REV
:E E
1_ H
E
2
;a
L_
L
HH_4
::::::
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150
E
ii_iiii
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140
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130
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fl
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100
4:
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:;_
80
---
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7o
FUEL LOAD:
[!"!+
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j-
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6o _
4
MINIMUM
_7_TF
L_If
5o !!
_t
_t
40
?Ttti_rl-t
:_
64
i!!!!!ii
66
68
70
FUEL TEMPERATURE
Figure
4.3-4
72
(°F)
CSM 104 AND SUBSEQUENT CM RCS
FUEL TANK ULLAGE VS TEMPERATURE
4.3-15
SNA-8-D-O27(III)REV
2
360
350
340
I-%
mD
330
Z
""
-320
310
m_
300
c_
290
o
280
270
260
250
240
230
64
66
68
70
OXIDIZER
Figure
4.3-5
CSM 104
OXIDIZER
72
TEMPERATURE
74
76
(OF)
AND SUBSEQUENT
CM RCS
TANK ULLAGE
VS TEMPERATURE
4.3-16
SNA-8-D-027(III)REV
2
L
Amendment
105
6118171
TABLE
COMMAND
MODULE
4.3-7
112
RCS
TANK
VOLUMES
Internal
System
Serial
Gross
Tank
Equipment
Number
Volume
I In 3
Volume_
Net
in 3
Tank
Volume_
1
Fuel
100311537100
1490.003
15.3
1474.703
Oxidizer
100311545114
1804.744
17.8
1786.944
Fuel
100311537101
1486.982
15.3
1471.682
Oxidizer
100311545103
1808.798
17.8
1790.998
System
in 3
2
4.3-17
SNA-8-D-O27(III)REV
3
Amendment
105
6/18/71
TABLE
SERVICE
MODULE
4.3-8
112
RCS
TANK
VOLUMES
Internal
S._s
t_m
Quad
Serial
Gross
Tank
Number
Volume,
Net
Equipment
in 3
Volume_
in 3
in 3
A
Primary
100311521168
2862.193
19.1
2843.093
100311545116
1802.557
17.8
1784.757
Fuel_
Fuel
100311511167
2266.943
17.4
2249.543
100311537099
1476.143
15.3
1460.843
Oxidizer
100311521333
2861.264
19.1
2842.164
100311545110
!802.556
17.8
1784.756
100311511326
2259.267
17.4
2241.867
100311537108
1482.432
15.3
1467.132
100311521175
2866.460
19.1
2847.360
100311545112
1805.330
17.8
1787.530
100311511172
2272.138
17.4
2254.738
100311537106
1491.598
15.3
1476.298
100311521326
2862.193
19.1
2843.093
100311545117
1803.507
17.8
1785.707
1003115113]0
2270.980
17.4
2253.580
100311537103
1489.144
15.3
1473.844
Oxidizer
Secondary
Oxidizer
Primary
Secondary
Quad
B
Primary
Secondary
Oxidizer
Primary
Fuel
Secondary
Quad
Fuel
C
Primary
Oxidizer
Sec,,ndary
Primary
f_xidizer
Fuel
Secondary
Quad
Fuel
11
Primary
Oxidizer
Secondary
Primary
Oxidizer
Fuel
Secondary
Fuel
4.3-18
U
Tank
Volume_
_
L
L
L
L
L
L
L
L
SNA-B-D-027
L_
L
L;
ii
_
(III)K}_v
I_
Li
3
L.
L_
[
Amendment
105
6/18/71
TABLE
COMMAND
MODULE
4.3-9
113
RCS
TANK
VOLUMES
Internal
Serial
Gross
Tank
Number
Volume_
in 3
Equipment
Volume_
Net
in 3
Tank
Volume_
in 3
Sys tern i
Fuel
100311537115
1488.714
15.3
1473.414
Oxidizer
100311545115
1801.865
17.8
1784.065
Fuel
100311537116
1484.806
15.3
1469.506
Oxidizer
100311545118
1808.795
17.8
1790.995
System
2
4.3-19
SNA-8-D-027(III)REV
3
Amendment
105
6/18/71
TABLE4.3-10
SERVICE
MODULE
113 RCSTANKVOLUMES
Internal
System
Quad
Secondary
Primary
Secondary
Secondary
Primary
Secondary
Tank
in 3
Equipment
Volume_
Net
in 3
Tank
Volume
3
t in
Oxidizer
Oxidizer
Fuel
Fuel
100311521170
2857.098
19.1
2837.998
100311545125
1802.556
17.8
1784.756
100311511168
2267.924
17.4
2250.524
100311537129
1482.432
15.3
1467.132
100311521171
2862.193
19.1
2843.093
100311545101
1815.725
17.8
1797.925
100311511170
2272.138
17.4
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
Oxidizer
Oxidizer
Fuel
Fuel
C
Primary
Secondary
Primary
Secondary
Quad
Volume_
B
Primary
Quad
Gross
Number
A
Primary
Quad
Serial
Oxidizer
Oxidizer
Fuel
Fuel
D
Primary
Secondary
Primary
Secondary
Oxidizer
Oxidizer
Fuel
Fuel
4.3-20
SNA-8-D-027
(III) REV
3
Amendment
105
6/18/71
TABLE
COMMAND
MODULE
4.3-11
114
RCS
TANK
VOLUMES
Internal
Serial
Number
S_vstem
System
Gross
Volume_
Tank
in3
Equipment
Net
Vo!ume
Volume,
100311537122
1503.864
15.3
1488.564
Oxidizer
100311545134
1801.085
17.8
1783.285
Fuel
100311537114
1461.808
15.3
1446.508
Oxidizer
100311545111
1799.807
17.8
1782.007
2
4.3-21
_
_
In 3
i
Fuel
System
U
I in 3
Tank
_
L
L
L_
L
L
U
SNA-8-D-027(III)REV
U
d
U
3
L
J,.
Amendment
105
6/18/71
TABLE
SERVICE
MODULE
4.3-12
114
RCS
TANK
VOLUMES
Internal
S_.ystem
Quad
Secondary
Primary
Secondary
Secondary
Primary
Secondary
Number
Volume_
in 3
Net
Equipment
Volume_
in 3
Tank
Volume_
in 3
Oxidizer
Oxidizer
Fuel
Fuel
100311521172
2862.193
19.1
2843.093
100311545104
1821.604
17.8
1803.804
100311511173
2266.191
17.4
2248.791
100311537128
1491.598
15.3
1476.298
Oxidizer
Oxidizer
100311521330
2862.193
19.1
2843.093
100311545119
1800.132
17.8
1782.332
Fuel
Fuel
100311511328
2269.657
17.4
100311537107
1490.791
15.3
2252.257
1475.491
100311521173
2863.177
19.1
2844.077
100311545127
1821.604
17.8
1803.804
100311511175
2271.810
17.4
2254.410
100311537112
1476.143
15.3
1460.843
100311521332
2848.458
19.1
2829.358
100311545123
1807.229
17.8
1789.429
100311511331
2265.783
17.4
2248.383
100311537109
1482.806
15.3
1467.506
C
Primary
Secondary
Primary
Secondary
Quad
Tank
B
Primary
Quad
Gross
A
Primary
Quad
Serial
Oxidizer
Oxidizer
Fuel
Fuel
D
Primary
Secondary
Primary
Secondary
Oxidizer
Oxidizer
Fuel
Fuel
4.3-22
SNA-8-D-O27(III)RF
NASA
II
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1.'
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BE
SUPPLIED.
CM ABLATOR
DATA
L
4.4-1
SNA-8-D-O27(III)REV
2
II
II
I
II
_y'
0
0
t.[
ILl !1
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L:
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Amendment
86_
9/lO/7O
5.0
The
data
separate
craft
in
centers-of
cons_ble
LM
section
data
data
data
are
Descent
and
for
enable
affect
must
each
be
the
the
to
provided
to
for
those
the
in
following
sections:
Fuel
Properties
5
through
LM
9
Table
5.1-2
LM
5 throuEh
LM
9 Oxidizer
Table
5.1-3
LM
i0
and
Subsequent
DPS
Fuel
Table
5.1-4
LM
i0
and
Subsequent
DPS
Oxidizer
5.3
LM
RCS
5.4
LM
Descent
Tank
Tank
Mass
Mass
Tank
8 Descent
LM
Table
5.4-2
I14 i0
Ascent
5.6
LM Trapped
Miscellaneous
Water
and
LM
on-board
3.0.
The
Mass
Mass
Properties
Mass
Properties
Mass
Properties
Properties
Water
5.4-1
LM
space-
Properties
Table
5.5
the
Properties
LM
Ascent
LM
current
Section
5.1-1
LM
obtain
LMperformance.
Table
5.2
DATA
user
overall
compared
mission
in
Mass
PROPERTIES
moments-of-lnertla
presented
Tank
MASS
will
slgnlficantly
property
loading
property
this
that
mass
CONSUMABLES
gravity
consumables
5.1
REFERENCE
presented
consumables
mass
LM
and
Tank
Mass
Properties
Water
Tank
Subsequent
Mass
Residual
Consumables
Mass
Descent
I
Properties
Water
Tank
Mass
Properties
Properties
Propellants,
5-1
and
SNA-8-D-027(III)REV
2
t
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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.
5.l-I
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9/10/70
TABLE
APS
TANKED
FUEL
5.2-1
MASS
The following
mass properties
are
range of tanked fuel quantity:
X
86
PROPERTIES
to be
used
over
the entire
-
228.0
inches
-
-71.3
inches
-
0.0
inches
-
0
slug-feet 2
-
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slug-feet 2
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slug-feet 2
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Amendment
86
9/10/70
TABLE
APS
TANKED
The following
mass
of tanked
oxidizer
X
5.2-2
OXIDIZER
properties
quantity:
MASS
are
to
PROPERTIES
be
used
over
E
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entire
"
228.0
inches
Ycg
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44.5
inches
Zcg
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0.0
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5.2-2
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LM ASCENT FUEL MASS PROPERTIES-70°F-I
Y-CG = -71.3
(CONST) Z-CG = 0.0
RADIUS= 24.700
CYLINDRICAL
DENSITY= 56.330
LBS/CU.FT.
WEIGHT
\
\
1566.5
1556.6
1546.6
1536.6
1526.6
1516.7
1506,7
1496.7
1486.7
1476,7
1466,8
1456.8
1446.8
1436.8
1426.9
1416.9
1406.9
1396.9
1386.9
1377.0
1367.0
1357.0
1347.0
1337,1
1327.1
1317.1
1307.1
1297.1
1287.2
1277,2
1267,2
1257.2
1247.2
1237.3
1227.3
1217.3
1207.3
1197.4
1187.4
1177.4
1167.4
1157,4
1147.5
X-CG
223.4
223,3
223,3
223.2
223.1
223,0
222.9
222.8
222.7
222.7
222.6
222.5
222.4
222.3
222,2
222.1
222.0
222.0
221.9
221,8
221.7
221,6
221.5
221.4
221.4
221.3
221.2
221,1
221.0
220.9
220.8
220.8
220.7
220.6
220.5
220.4
220.3
220.2
220.1
220.1
220.0
219.9
219.8
TANK
(CONST)
SECTION=
-0.0
WEIGHT= 1995.6
IXX(S-FT.SQ)
4.4
4.3
3.3
3.3
4.2
4.2
4.2
4.2
4.1
4.1
4.1
4.0
4.0
4.0
3.9
3.9
3.9
3.8
3.8
3.8
3.8
3.7
3.7
3.7
3.6
3.6
3,6
3,5
3.5
3,5
3.4
3.4
3.4
3,3
3,3
3.3
3,2
3.2
3.2
3.o
3.1
3,1
3.0
5.2-3
IYY or
IZZ(S-FT.SQ)
3.3
3.3
3,2
3.2
3.2
3.1
3.1
3.1
3.0
3.0
3.0
2.9
2.9
2.9
2.8
2.8
2.8
2.8
2.7
2.7
2.7
2.6
2.6
2.6
2.5
2,5
2.5
2,5
2.4
2.4
2.4
2.3
2.3
2.3
2.2
2.2
2.2
2.2
2.1
2.1
2.1
2.1
2.0
SNA-8-D-O27(III)REV
2
LM ASCENT FUEL MASS PROPERTIES-70°F-I
Y-CG = -71,3
(CONST)
Z-CG = 0o0
RADIUS= 24.700 CYLINDRICAL
DENSITY = 56.330 LBS/CU.FT.
WEIGHT
X-CG
I137
1127
1117
1107
1097
I087
1077
1067
1057
I047
1037
1027
1017
1007
997
987
977
967
957
947
937
928
918
908
898
888
878
868
858
848
838
828
818
8O8
798
788
778
768
758
748
738
728
718
219.7
219.6
219.5
219.4
219.4
219.3
219.2
219.1
219.0
218.9
218,8
218.7
218.6
218.5
218.5
218.4
218.3
218.2
218,1
218,0
217.9
217.8
217.7
217.6
217,5
217.4
217.4
217.3
217.2
217.1
217.0
216.9
216.8
216.7
216.6
216.5
216.4
216.3
216.2
216.1
216.0
215.9
215.8
.5
.5
.5
.6
.6
.6
.6
.6
.7
.7
.7
.7
.8
.8
.8
.8
.8
.9
.9
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0
1
1
1
1
2
2
2
2
2
3
3
3
3
3
4
4
4
TANK
(CONST)
SECTION = -0.0
WEIGHT= 1995.6
L
L
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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
3.0
3.0
3.0
2.9
2.9
2.9
2.8
2.8
2.8
2.7
2.7
2.7
2.6
2.6
2.6
2.5
2.5
2.5
2.4
2.4
2.4
2,3
2.3
2.3
2.2
2.2
2.2
2.1
2,1
2.1
2.0
2.0
2.0
1.9
I .9
1.9
1.8
1.8
1.8
1.7
1.7
1.7
1,7
5.2-4
ILl 11 L
LYY or
IXX(S-FT.SQ)
SNA-8-D-O27(III)REV
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2
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LM ASCENT FUEL MASS PROPERTIES-70°F-I
TANK
Y-CG = -7].3 (CONST) Z-CG : 0.0 (CONST)
RADIUS= 24.700 CYLINDRICAL
DENSITY= 56.330 LBS/CU.FT.
WEIGHT
X-CG
708.4
698.5
688.5
678.5
668.5
658.5
648 6
638 6
628 6
618 6
608 7
598 7
588 7
5787
568.7
558.8
548.8
538.8
528.8
518.9
508.9
498.9
488.9
478.9
469,0
459,0
449,0
439.0
429.1
419.1
409.1
399,1
389.1
479.2
369.2
359,2
349.2
339.3
329,3
319.3
309.3
299.3
289.4
215.7
215.6
215.5
215.4
215.3
215.2
215.1
215.0
214.9
214.8
214.7
214.6
214.5
214.4
214.3
214.2
214.1
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
SECTION=
-0.0 WEIGHT=
IXX(S-FT.SQ)
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
5.2-5
]995.6
IYY or IZZ(S-FT.SQ)
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
SNA-8-D-O27(III)REV
2
LMASCENTFUELMASSPROPERTIES-70°F-I
TANK
Y-CG= -71.3 (CONST) Z-CG = 0.0 (CONST)
RADIUS= 24.700 CYLINDRICAL
DENSITY= 56.330 LBS/CU.FT.
WEIGHT
X-CG
279.4
269.4
259.4
249.4
239.5
229.5
219.5
209.5
199.6
189.6
179.6
169.6
159.6
149.7
139.7
129.7
I19.7
I09.8
99.8
89.8
79.8
69.8
59.9
49.9
39.9
29.9
20.0
lO.O
SECTION = -0.0
WEIGHT=
IXX(S-FT.SQ)
210.7
210.6
210.5
210.3
21 O. 2
210.0
209.8
209.7
209.5
209.4
209.2
209.0
208.8
208.7
208.5
208.3
208.1
207.9
207.6
207.4
207.2
206.9
206.6
206.3
206.0
205.6
205.2
204.6
IJ
;L; 1:. 12 L
L
E
L: ]_
IYY or OZZ(S-FT.SQ)
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
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
5.2-6
ILl li
1995.6
SNA-8-D-O27(III)REV
E
L.' 1_ E
E
:
2
'
L
LM ASCENT OXIDIZER
Y-CG = +44.5
MASS PROPERTIES-70°F-I
(CONST)
Z-CG = 0,0
RADIUS= 24.700
CYLINDRICAL
DENSITY= 90.050
LBS/CU.FT.
(ULLAGE/VOL.OF
WEIGHT
3172.9
3157,0
3141.2
3125.3
3109.4
3093.6
3077,7
3061.8
3046.0
3030.1
3014.3
2998.4
2982.6
2966.7
2950.8
2934.9
2919,1
2903.2
2887.3
2871.5
2855.6
2839.7
2823.9
2808.0
2792.2
2776.3
2760,4
2744.6
2728.7
2712.8
2697.0
2681.1
2665.2
2649.4
2633.5
2617.6
2601.8
2589.9
2570.0
2554.2
2538,3
2522,5
2506.6
LIQUID))x]O0=
X-CG
227.2
227.1
227.0
226,9
226.8
226.7
226.6
226.6
226,5
226,4
226,3
226,2
226.1
226.0
225.9
225.8
225.7
225.6
225.5
225.5
225.4
225.3
225.2
225.1
225.0
224.9
224,8
224.7
224.7
224,6
224.5
224.4
224.3
224,2
224.1
224.0
224.0
223.9
223,8
223.7
223.6
223.5
223.4
TANK
(CONST)
SECTION= -0.0
WEIGHT=
31 72.9
3.672
IXX(S-FT.SQ)
8.5
8.5
8.5
8.4
8.4
8,4
8.4
8.3
8.3
8.3
8.2
8.2
8.2
8.2
8.1
8.1
8.1
8.0
8,0
7.9
7.9
7.9
7,8
7.8
7.8
7.7
7.7
7.6
7.6
7.6
7.5
7.5
7,4
7.4
7.3
7.3
7.3
7.2
7,2
7.1
7.1
7.0
7.6
5.2-7
IYY or
IZZ(S-FT.SQ)
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
SNA-8-D-O27(III)REV
2
LM ASCENT
OXIDIZERMASSPROPERTIES-70°F
-l TANK
Y-CG = +44.5 (CONST) Z-CG = 0.0 (CONST)
RADIUS = 24.700 CYLINDRICAL
DENSITY= 90.050 LBS/CU.FT.
WEIGHT
X-CG
2490.7
2474.9
2459.0
2443.1
2427.3
2411.4
2395.5
2379.7
2363.8
2347.9
2332.1
2316.2
2300.4
2284.5
2268.6
2252.8
2236.9
2221.0
2205.2
2189.3
2173.4
2157.6
2141.7
2125.8
2110.O
2094.1
2078.2
2062.4
2046.5
2030.7
2014.8
1998.9
1983.1
1967.2
1951.3
1935.5
1919.6
1903.7
1887.9
1872.0
1856.1
1840.3
1824.4
223.4
223.3
223.2
223.1
223.0
222.9
222.8
222.8
222.7
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
SECTION = -0.0 WEIGHT=
IXX(S-FT.SQ)
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
5.2-8
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
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)
TANK
RADIUS= 24.700
CYLINDRICAL
DENSITY= 90.050
LBS/CU.FT.
WEI GHT= 3172.9
WEIGHT
1808,6
1792.7
1776,8
1761.0
1745.1
1729.2
1713.4
1697.5
1681.6
1665.8
1649.9
1634.0
1618.2
1602,3
1586.4
1570.6
1554.7
1538.9
1523.0
1507.1
1491.3
1475,4
1459.5
1443,7
1427,8
1411.9
1396.1
1380.2
1364.3
1348,5
1332.6
1316.8
1300.9
1285.0
1269,2
1253.3
1237,4
1221,6
1205.7
1189.8
1174.0
1158.1
1142.2
X-CG
219.7
219.6
219.5
219.4
219.3
219.2
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
SECTION= -0.0
IXX(S-FT.SQ)
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
5.2-9
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
SNA-8-D-O27(III)REV
2
LM ASCENT
OXIDIZER
Y-CG = +44.5
MASS PROPERTIES-70°F-I
(CONST)
TANK
Z-CG = 0.0 (CONST)
RADIUS= 24.700 CYLINDRICAL
DENSITY= 90.050 LBS/CU.FT.
WEIGHT
X-CG
I126.4
lllO.5
I094.7
I078.8
I062.9
I047.1
I031.2
I015.3
999.5
983.6
967.7
951.9
936.0
920.I
904.3
888.4
872.5
856.7
840.8
825.0
809.1
793.2
777 4
761 5
745 6
729 8
713 9
698 0
682.2
666.3
650.4
634.6
618.7
602.9
587.0
571.I
555.3
539.4
523.5
507.7
491.8
475.9
460.I
215 7
215 6
215 5
215 4
2]5 3
215 2
215 ]
215 0
214.9
214.8
214.7
2]4.6
214.4
214.3
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
SECTION=
-0.0 WEIGHT=
IXX(S-FT.SQ)
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
5.2-I0
3172.9
IYY or IZZ(S-FT.SQ)
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
SNA-8-D-O27(III)REV
2
L-
L
LM ASCENT OXIDIZER MASS PROPERTIES-70°F-I
Y-CG = +44.5 (CONST) Z-CG = 0.0 (CONST)
RADIUS= 24.700 CYLINDRICAL
DENSITY= 90.050 LBS/CU.FT.
WEIGHT
X-CG
444.2
428.3
412.5
396.6
380.7
364.9
349.0
333.2
317.3
301.4
285.6
269.7
253.8
238.0
222.1
206.2
190.4
174.5
156.6
142.8
126.9
lll.l
95.2
79.3
63.5
47.6
31.7
15.9
210.7
210.6
210.4
210.3
210.1
210.0
209.8
209.7
209.5
209.3
209.2
209.0
208.8
208.6
208.4
208.3
208.0
207.8
207.6
207.4
207.1
206.9
206.6
206.3
206.0
205.6
205.2
204.6
SECTION=
TANK
-0.0 WEIGHT=
IXX(S-FT.SQ)
0.7
0.6
0.6
0.6
0.5
0.5
0.5
0.4
0.4
0.4
0.3
0.3
0.3
0.2
0.2
0.2
0.2
O.l
O.l
O.l
O.l
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.2-II
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
SNA-8-D-O27(III)REV
2
ILl !1
]5. L: L
L
L: L: ]_
E
if
L
|;
E
E
I
I,
L.
I
L:.
.,..-
_
K
L'_
t_
L'-'
L'_
C_
l
LUNAR MODULE
MASS
RCS PROPELLANT
PROPERTIES
NOTE:
I.
2.
3.
4.
Mass Properties are given for liquid in individual tanks.
Moments of Inertia are about center of gravity of propellant
in individual tanks, coordinates of which are given.
Centers of Gravity in Y and Z directions are given at top of
each page.
The number of tanks of a particular kind is indicated
by the last number on the first line of each page.
5.3-I
SNA-8-D-O27(III)REV
2
LM RCS FUEL MASS PROPERTIES-70°F-2
Y-CG = + OR -
44.6
(CONST) Z-CG = + OR -
RADIUS= 6.250 CYLINDRICAL
DENSITY: 56.330
LBS/CU.FT.
(ULLAGE/(VOL.OF
TANKS
SECITON= 18.650.
LIQUID))xIO0=
WEIGHT
X-CG
103.7
103.2
102.7
102.1
101.6
I01.I
100.6
I00.I
99.6
99.0
98.5
98.0
97.5
97.0
96.4
95.9
95.4
94.9
94.4
93.8
93.3
92.8
92.3
91.8
91.3
90.7
90.2
89.7
89.2
88.7
88.1
87.6
87.1
86.6
86.1
85.6
85.0
84.5
84.0
83.5
83.0
82.4
81.9
279.3
279.2
279.2
279.1
279.0
279.0
278.9
278.8
278.8
278.7
278.7
278.6
278.5
278.5
278.4
278.3
278.3
278.2
278.1
278.1
278.0
277.9
277.9
277.8
277.7
277.7
277.6
277.5
277.5
277.4
277.4
277.3
277.2
277.2
277.1
277.0
277.0
276.9
276.8
276.8
276.7
276.6
276.6
14.5
WEIGHT= I03.7
4.093
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
0.0
O.O
0.0
0.0
0.0
O.O
O.O
0.0
0.0
0.0
O.O
0.0
0.0
O. 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
5.3-2
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
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
DENSITY: 56.330
LBS/CU.FT.
WEIGHT
81.4
80.9
80.4
79.8
79.3
78.8
78.3
77.8
77.3
76.7
76.2
75.7
75.2
74.7
74.1
73.6
73.1
72.6
72.1
71.6
71.0
70.5
70.0
69.5
69.0
68.4
67.9
67.4
66.9
66.4
65.8
65.3
64.8
64.3
63.8
63.3
62.7
62.2
61.7
61.2
60.7
60.1
59.6
11 U
I_ t;
X-CG
276.5
276.4
276.4
276.3
276.2
276.2
276.1
276.0
276.0
275.9
275.9
275.8
275.7
275.7
275.6
275.5
275.5
275.4
275.3
275.3
275.2
275.1
275.1
275.0
274.9
274.9
274.8
274.7
274.7
274.6
274.5
274.5
274.4
274.4
274.3
274.2
274.2
274.1
274.0
274.0
273.9
273.8
273.8
1.: I_ L
E
SECTION=
18.650,
WEIGHT= 103.7
IYY or
IXX(S-FT.SQ)
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
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
L." U. 1_ E
LI L{ li
1_ L
L
2
L
L
LM RCS FUEL MASS PROPERTIES-70°F-2
TANKS
Y-CG = + OR - 44.6 (CONST) Z-CG = + OR - 14.5
RADIUS= 6.250 CYLINDRICAL SECTION=
DENSITY= 56.330 LBS/CU.FT.
WEIGHT
X-CG
59.1
58.6
58.1
57.6
57.0
56.5
56.0
55.5
55.0
54.4
53.9
53.4
52.9
52.4
51.8
51.3
50.8
50.3
49.8
49.3
48.7
48.2
47.7
47.2
46.7
46.1
45.6
45.1
44.6
44.1
43.6
43.0
42.5
42.0
41.5
41.0
40.4
39.9
39.4
38.9
38.4
37.9
37.3
273.7
273.6
273.6
273.5
273.4
273.4
273.3
273.2
273.2
273.1
273.0
273.0
272.9
272.8
272.8
272.7
272.6
272.6
272.5
272.5
272.4
272.3
272.3
272.2
272.1
272.1
272.0
271.9
271.9
271.8
271.7
271.7
271.6
271.5
271.5
271.4
271.3
271.3
271.2
271 .l
271 .l
271 .O
270.9
18.650.
WEIGHT
IXX(S-FT.SQ)
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
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
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
O.O
0.0
O.O
O.O
0.0
0.0
0.0
0.0
O.O
0.0
5.3-4
l/IlL[
1;111/
L
E
11 b" E
= I03L7
SNA-8-D-O27(III)REV
L.'
E
E
L,
2
L
L
tL
LM RCS FUEL MASS PROPERTIES-70°F-2
TANKS
Y-CG = + OR - 44.6 "(CONST) Z-CG = + OR - 14.5
RADIUS= 6.250 CYLINDRICAL
DENSITY= 56.330
LBS/CU.FT.
WEIGHT
SECTION= 18.560.
X-CG
36.8
36.3
35.8
35.3
34.7
34.2
33.7
33.2
32.7
32.1
31.6
31 .I
30.6
30.1
29.6
29.0
28.5
28.0
27.5
27.0
26.4
25.9
25.4
24.9
24.4
23.9
23.3
22.8
22.3
21.8
21.3
20.7
20.2
19.7
19.2
18.7
18.1
17.6
17.1
16.6
16.1
15.6
15.0
WEIGHT= 103.7
IXX(S-FT.SQ)
270.9
270.8
270.7
270.7
270.6
270.5
270.5
270.4
270.3
270.3
270.2
270.1
270.1
270.0
269.9
269.9
269.8
269.7
269.7
269.6
269.5
269.5
269.4
269.3
269.3
269.2
269.1
269.0
269.0
268.9
268.8
268.8
268.7
268.6
268.6
268.5
268.4
268.3
268.3
268.2
268.1
268.0
268.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
I_
1_ 1;
E
L
E
L" E
U
E
IZZ(S-FT.SQ)
0.0
0.0
0.0
0.0
0.0
0.0
G.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
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.3-5
ILl !1
IYY or
SNA-&-D-O27(III)REV
L,' ]_
H E
_
'
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
DENSITY= 56.330 LBS/CU.FT.
WEIGHT
X-CG
14.5
14,0
13.5
13.0
12.4
11.9
11.4
10.9
I0.4
9.9
9.3
8.8
8.3
78
7.3
6.7
6.2
5,7
5.2
4.7
4.1
3.6
3.1
2.6
2.1
1.6
l.t]
0.5
267.9
267.8
267.7
267.7
267.6
267,5
267.4
267.3
267.3
267.2
267.1
267.0
266.7
266.8
266.7
266.6
266.5
266.4
266.3
266.2
266.1
266.0
265._
265.7
265.5
265.4
265.2
264.9
SECTION = 18.650.
WEIGHT= 103.7
IXX(S-FT.SQ)
O.O
C.O
0.0
0.0
0.0
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
5.3-6
ILl !1
t:
[
L: 12 11 L
:L: L: b." :L
IYY or IZZ(S-FT.SO)
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0,0
0.0
0.0
0,0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
SNA-8-D-O27(III)REV
2
,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
DENSITY= 90.050
LBS/CU.FT.
(ULLAGE/(VOL.OF
LIQUID))xlO0=
WEIGHT
X-CG
203.4
202.4
201.4
200.3
199.3
198.3
197.3
196.3
195.3
194.2
193.2
192.2
191.2
190.2
189.2
188.1
187.1
186.1
185.1
184.1
183.1
182.0
181.0
180.0
179.0
178.0
177.0
175.9
174.9
173.9
172.9
171.9
170.9
169.8
168.8
167.8
166.8
165.8
164.8
163.7
162.7
161.7
160.7
275.7
275.6
275.5
275.4
275.3
275.3
275.2
275.1
275.0
274.9
274.9
274.8
274.7
274.6
274.5
274.5
274.4
274.3
274.2
274.1
274.1
274.0
273.9
273.8
273.7
273.7
273.6
273.5
273.4
273.3
273.3
273.2
273.1
273.0
272.9
272.9
272.8
272.7
272.6
272.5
272.5
272.4
272.3
SECTION = 25.260.
WEIGHT= 203.4
5.621
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
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.3-7
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
SNA-8-D-O27(III)REV
2
LM RCS OXIDIZER
Y-CG
= + OR -
RADIUS:
DENSITY:
6.250
90.050
MASS PROPERTIES-70°F-2
44.6
(CONST)
CYLINDRICAL
Z-CG
= -
SECTION:
TANKS
OR +
25.260.
14.5
WEIGHT:
203.4
LBS/CU.FT.
IXX (S-FT. SQ)
IYY
or
WEIGHT
X-CG
159.7
158.7
157.6
156.6
155.6
154.6
272.2
272.1
272.1
272.0
271.9
271.8
0.0
0.0
0.0
0.0
0.0
0.0
0.6
0.6
0.6
0.6
0.5
0.5
153.6
152.5
151.5
150.5
149.5
271.7
271.7
271.6
271.5
271.4
0.0
0.0
0.0
0.0
0.0
0.5
0.5
0.5
0.5
0.5
148.5
147.5
271.3
271.3
0.0
0.0
0.5
0.4
146.4
145.4
144.4
143.4
142.4
141.4
140.3
139.3
138.3
137.3
136.3
135.3
134.2
133.2
132.2
131.2
130.2
129.2
128.1
127.1
126.1
125.1
124.1
123.1
122.0
121.0
120.0
271.2
271.1
271.0
270.9
270.9
270.8
270.7
270.6
270.5
270.5
270.4
270.3
270.2
270.1
270.1
270.0
269,9
269.8
269.7
269.7
269.6
269.5
269.4
269.3
269.3
269.2
269.1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
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
O. 2
0.2
0.2
0.2
0.2
0.2
0.2
0.2
0.2
119.0
118.0
117.0
269.0
268.9
268.9
0.0
0.0
0.0
O. 2
0.2
0.2
5.3-8
IZZ(S-FT.SQ)
SNA-8-D-027(III)REV
2
i
L.
L
LM RCS OXIDIZER
Y-CG
= + OR -
RADIUS =
DENSITY=
6.250
90.050
MASS PROPERTIES-70°F-2
44.6
(CONST)
CYLINDRICAL
Z-CG
TANKS
= -
SECTION:
OR +
25.260.
14.5
WEIGHT =
203.4
LBS/CU.FT.
WEIGHT
X-CG
IXX(S-FT.SQ)
115.9
114.9
113.9
112.9
111.9
110.9
109.8
108.8
268.8
268.7
268.6
268.5
268.5
268.4
268.3
268.2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0o0
0. z
O. 2
0.i
0.i
0.i
0.1
0.1
0.1
107.8
106.8
105.8
104.8
103.7
102.7
101.7
i00.7
99.7
268.1
268.1
268.0
267.9
267.8
267,7
267.7
267,6
267.5
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.i
0.i
0.1
0.i
0.i
0.i
0.i
O. i
0.i
98.6
97.6
96.6
95.6
94.6
93.6
92.5
91.5
90.5
89.5
88.5
87.5
86.4
85.4
84.4
83.4
82.4
81.4
80.3
267,4
267.3
267.3
267.2
267.1
267.0
266.9
266.9
266.8
266.7
266.6
266.5
266.5
266.4
266.3
266.2
266.1
266.1
266.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0,0
0.0
0.0
0.0
0.0
0.i
0.1
0.1
0.i
0.i
0.1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
79.3
78.3
77.3
76.3
75.3
74.2
73.2
265.9
265.8
265.7
265.7
265.6
265.5
265.4
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
5.3-9
IYY
or
IZZ (S-FT. SQ)
SNA-8-D-O27(III)REV
2
LM RCS OXIDIZER
Y-CG
= + OR -
RADIUS:
DENSITY=
MASS PROPERTIES-70°F-2
44.6
(CONST)
6.250 CYLINDRICAL
90.050
LBS/CU.FT.
Z_CG = SECTION:
TANKS
OR + 14.5
25.260.
IXX(S-FT.SQ)
WEIGHT=
203.4
IYY
or
WEIGHT
X-CG
72.2
71.2
265.3
265.3
0.0
0.0
0.0
0.0
70.2
69.2
68.1
67.1
66.1
65.1
64.1
63.1
62.0
61.0
60.0
59.0
58.0
57.0
55.9
54.9
53.9
52.9
51.9
50.8
49.8
48.8
47.8
46.8
45.8
265.2
265.1
265.0
264.9
264.8
264.8
264.7
264.6
264.5
264,4
264,4
264.3
264.2
264.1
264.0
264.0
263.9
263.8
263.7
263,6
263.5
263.5
263.4
263.3
263.2
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0,0
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. 0
0.0
0.0
0.0
0.0
0.0
0,0
0,0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0,0
0.0
0.0
0.0
0.0
0.0
0.0
44.7
43.7
42.7
263.1
263.0
263.0
0.0
0.0
0.0
0.0
0.0
0.0
41.7
40.7
39.7
38.6
37.6
36.6
35.6
34.6
33.6
32.5
31.5
30.5
29.5
262.9
262.8
262.7
262.6
262.5
262.5
262.4
262.3
262.2
262.1
262.0
261.9
261.9
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
5.3-10
IZZ(S-FT.SQ)
SNA-8-D-027(III)REV
U
E
2
L, L
"
_
L
"
..
"h"
LM RCS OXIDIZER
MASS
Y-CG = + OR - 44.6
RADIUS=
DENSITY=
PROPERTIES-70"F-2
(CONST)
6.250 CYLINDRICAL
90.050
LBS/CU.FT.
TANKS
Z-CG : - OR + 14.5
SECTION=
25.260.
IXX(S-FT.SQ)
WEIGHT=
203.4
IYY
or
WEIGHT
X-CG
28.5
261.8
0.0
0.0
27.5
26.4
25.4
24.4
23.4
22.4
21.4
261.7
261.6
261.5
261.4
261.3
261.2
261.1
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
20.3
19.3
261.0
260.9
0.0
0.0
0.0
0.0
18.3
17.3
16.3
15.3
14.2
13.2
12.2
11.2
i0.2
260.8
260.7
260.6
260.5
260.4
260.3
260.2
260.1
260.0
0.0
0.0
0.0
0.0
0.0
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
9.2
8.1
259.8
259.7
0.0
0.0
0.0
0.0
7.1
6.1
5.1
4.1
3.1
2.0
1.0
259.6
259.4
259.3
259.1
258.9
258.7
258.4
0.0
0.0
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-ii
IZZ(S-FT.SQ)
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
.11
11[-
L
L
L
-I]
If
_I] .II
. 1[
II
I[
I_
i .
I
1_
tl
Amendment
9/10/70
86
LUNAR MODULE DESCENT WATER
MASS PROPERTIES
NOTE :
I.
2.
3.
4.
Mass Properties are given for liquid in individual tanks.
Moments of Inertia are about center of gravity of water in
individual tanks, coordinates of which are given.
Centers of Gravity in Y and Z directions are given at top of
each page.
The number of tanks of a particular kind is indicated by
the last number on the first line of each page.
5.4-I
11 11 I.I
E
L
E
I/ L
E
I:
SNA-8-D-O27(III)REV
Id
I:
M
Ii
li
I_
2
L
L
,_
L
Amendment
9/10/70
TABLE 5,4-1
I
86
LM-8 DESCENT WATER MASS PROPERTIES-1 TANK
Y-CG - -43,2 (CONST) Z-CG - -43.2
(CONST)
RADIUS= 14.200 CYLINDRICAL SECTION= O.O WEIGHT= 323.8
DENSITY_ 62.400 LBS/CU.FT.
(ULLAGE/VOL.OF LIQUID))xIO0:
33.757
WEIGHT
X-CG
IXX(S-FT.SQ)
323.8
322.2
320.6
_8.9
317.3
315.7
314.1
312.5
310.8
309.2
307.6
306.0
304.4
302.8
301.I
299.5
297.9
296.3
294.7
293.0
291.4
289.6
288.7
286.6
284.9
283.3
281.7
280.I
278.5
276.8
275.2
273.6
272.0
270.4
268.8
267.1
265.5
263.9
262.3
260.7
259.0
257.4
255.8
165.8
165.8
165.8
165.7
165.7
165.6
165.6
165.6
165.5
165.5
165.4
165.4
165.4
165.3
165,3
165.3
165.2
165.2
165.1
165.1
165.1
165.0
165.0
165.0
164.9
164.9
164.8
164.8
164.8
164.7
164.7
164.6
164.6
164.6
164.5
164.5
164.5
164.4
164.4
164.3
164.3
164.3
164.2
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
0.2
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
0.3
0,2
0,2
0.2
0.2
0.2
0.2
0.2
0.2
0.2
0.2
0.2
O.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
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
5.4-2
U
II
_
L
L
E
L
L
L
L
SNA-8-D-O27(III)REV
L
L
E
U
I! E
2
L
L
L_
L
Amendment:
9/10/70
TABLE
5.4-I
86
(Continued)
LM-8 DESCENT WATER MASS PROPERTIES-I TANK
Y-CG--43.2
(CONST) Z-CG = -43.2 (CONST)
RADIUS= ]4.200 CYLINDRICAL SECTION = O,O WEIGHT= 323.8
DENSITY= 62.400 LBS/CU,FT.
WEIGHT
X;CG
254.2
252.6
250.9
249.3
247.7
246.1
244.5
242.8
241.2
239.6
238.0
236.4
234.8
233.1
231.5
229.9
228.3
226.7
225.0
223.4
221.8
220.2
2]8.6
216.9
215.3
213.7
212.]
210.5
208.9
207.2
205.6
204.0
202.4
200.8
199.I
197.5
195.9
]94.3
192.7
191.0
189.4
187.8
186.2
]64.2
]64.]
164. ]
164.l
164.0
164.0
164.0
163.9
]63.9
]63.8
]63.8
]63.8
]63.7
163.7
163.6
163.6
163.6
163.5
163.5
163.4
163.4
163.4
163.3
163.3
]63.2
]63.2
]63.2
163.l
163.1
]63.0
163.0
163.0
162.9
]62,9
]62.8
162.8
162.8
162.7
162.7
162.6
162.6
162.6
162.5
IXX(S-FTSQ)
0.2
0.2
O.2
O.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
0.]
O.l
0.]
0.]
0.]
O.l
O.l
O.l
O.l
O.l
O.l
0.]
0.]
0.]
0.I
0.1
0.]
0.1
O.l
O.l
O.l
O.l
5.4-3
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
SNA-8-D-O27(III)REV
2
86
Amendment
TABLE5.4-I
(Continued)
9110170
LM-8 DESCENT
WATER
MASSPROPERTIES-I
TANK
Y-CG= -43.2 (CONST)Z-CG- -43.2 (CONST)
RADIUS=
14.200 CYLINDRICAL
SECTION=
0.0 WEIGHT=
323.8
DENSITY=
62.400 LBS/CU.FT.
WEIGHT
X-CG
184.6
182.9
181.3
179.7
178.1
]76.5
174.9
173.2
171.6
170.0
168.4
166.8
165.1
163.5
161.9
160.3
158.7
157.0
155.4
153.8
152.2
150.6
148.9
147.3
145.7
144.1
142.5
140.9
139.2
137.6
136.0
134.4
132.8
131.1
129.5
]27.9
126.3
124.7
123.0
121.4
119.8
118.2
I16.6
IXX(S-FT. SQ)
162.5
162.4
162.4
162.3
162.3
162.3
162.2
162.2
162.1
162.1
162.1
162.0
162.0
161.9
161.9
161.8
161.8
161.8
161.7
161.7
161.6
161.6
161.5
161.5
161.4
161.4
161.4
161.3
161.3
161.2
161.2
161 .l
161.1
161.0
161.0
160.9
160.9
160.9
160.8
160.8
160.7
160.7
160.6
O. ]
0. I
O. 1
0.1
O.l
O. 1
O. 1
O.l
O.l
O.l
O. 1
O.l
O.l
0.1
0.1
0.1
0.1
0.1
0.1
0.1
O. 1
0.1
O.l
O.l
0.1
0.1
O.l
O.l
0.I
0.1
O.l
O.l
O.O
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
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
5.4-4
ILl It
L
L
L
L
L
11
IYY or IZZ(S-FT.SQ)
1i k
SNA-8-D-O27(III)REV
2
L
I
L__
Amendment
TABLE
5.4-I
86
9/10170
(Continued)
I
LM-8 DESCENT WATER MASS PROPERTIES-I TANK
Y-CG : -43.2 (CONST) Z-CG : -43.2 (CONST)
RADIUS= 14.200 CYLINDRICAL SECTION: 0.0
DERSITY= 62.400 LBS/CU.FT.
WEIGHT
.X-CG
I14.9
I13.3
Ill.7
llO.l
I08.5
I06.9
I05.2
I03.6
102.0
I00.4
98.8
97.1
95.5
93.9
92.3
90.9
89.0
87.4
85.8
84.2
82.6
80.9
79.3
77.7
76.1
74 5
72 9
71 2
69 6
68 0
66 4
64 8
63 1
61 5
59 9
58 3
56 7
55 0
53 4
51.8
50.2
48.6
47.0
160.6
160.5
160.5
160.4
160.4
160.3
160.3
160.2
160.2
160.1
160._
160.0
160.0
159.9
159.9
159.8
159.8
159.7
159.6
159.6
159.5
159.5
159.4
159.4
159.3
159.3
159.2
15911
159.I
159.0
159.0
158.9
158.8
158.8
158.7
1S8.7
158.6
158.5
158.5
1 $8.4
188.3
158.3
158.2
If L
E
323.8
IYY or IZZ(S-FT.SQ.
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
0.0
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
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
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
II II Ig if L. E
WEIGHT=
E
I_ E
SNA-8-D-O27(III)REV
i_ l; I! E
:' '
L
L,.
L
2
L
Amendment
TABLE
5.4-!
(Continued)
86
9/10/70
LM-8 DESCENT WATER MASS PROPERTIES-I TANK.
Y-CG = -43.2 (CONST) Z-CG = -43.2 (CONST)
RADIUS: 14.200 CYLINDRICAL SECTION = 0.0
DENSITY = 62.400 LBS/CU. FT.
WEIGHT
X-CG
45.3
43.7
42.1
40.5
38.9
37.2
35.6
34.0
32.4
30.8
29.l
27.5
25.9
24.3
22.7
21.0
19.4
17.8
16.2
14.6
13.0
II .3
9.7
8.1
6.5
4.9
3.2
l.6
158 l
158 l
158 0
157 9
157 8
157 8
157 7
157 6
157 5
157 4
157 .4
157 .3
157 .2
157 .I
157 .0
156 .9
156 .8
156 .7
156 .6
156 .5
156 .3
156 .2
156 .l
155 .9
155 .8
155 .6
155 .4
155 .l
• WEIGHT =
IYY or IZZ(S-FT.SQ. )
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
0.0
0.0
0.0
0.0
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
5.4-6
IJ LI
E
L. E
E
L
E
E
323.8
SNA-8-D-027(I II)REV 2
E
E
L
i_
Amendmenti01
2/16/71
LM
RADIUS
TANK
NO.
14.2
1
SUBSEQUENT
INCHES
,,
-43.2
(CONSTANT)
Z-CG
,, -43.2
(CONSTANT)
OF
5.4-2
DESCENT
STAGE
DENSITY
¥-CC
(ULLAGE/(VOLUME
Weight
Pounds
10 AND
TABLE
LIQUID))
X i00
TANK
WATER
= 62.4
NO.
2 ¥-CG
Z-CG
MASS
LBS/CU.
PROPERTIES
FT.
WEIGHT
.,
43.2
(CONSTANT)
-
43.2
(CONSTANT)
-
323.8
POUNDS
- 37.757
Tank-i
X-CG
Tank-2
X-CG
Height
Inches
333.0
166.0
142.9
19.542
323.8
165.8
142.7
19.080
322.2
165.8
142.7
19.000
320.6
165.8
142.7
18.921
318.9
317.3
165.7
165.7
142.6
142.6
18.841
18.762
315.7
165.6
142.5
18.683
314.1
165.6
142.5
18.605
312.5
310.8
165.6
165.5
142.5
142.4
18.527
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
302.8
165.4
165.3
142.3
I_2.2
18.140
18.064
301.1
165.3
142.2
17.987
299.5
297.9
165.3
165.2
142.2
142.1
17.911
17.835
296.3
294.7
293.0
165.2
165.1
165.1
142.1
142.0
142.0
17.760
17.684
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
281.7
164.9
164.8
141.8
141.7
17.162
17.088
280.1
278.5
164.8
164.8
141.7
141.7
17.014
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
268.8
164.6
164.5
141.5
141.4
16.575
16.502
267.1
265.5
164.5
164.5
141.4
141.4
16.430
16.357
5.4-7
SNA-8-D-027(III)REV
2
Amendment
86
9/10/70
TABLE
LM
RADIUS
• TANK
= 14.2
NO.
(ULLAGE/
I0
AND
SUBSEQUENT
INCHES
1 Y-CG
Z-CG
(VOLUME
- -43.2
5.4-2
DESCENT
(Continued)
STAGE
DENSITY
(CONSTANT)
TANK
= -43.2
(CONSTANT)
OF LIQUID))
X i00
= 37.757
WATER
= 62.4
NO.
MASS
LBS/CU.
PROPERTIES
FT.
WEIGHT
2 Y-CG
= 43.2
(CONSTANT)
Z-CG
= 43.2
(CONSTANT)
Weight
Pounds
Tank-i
X-CG
Tank-2
X-CG
Height
Inches
263.9
164.4
141.3
16.285
262.3
164.4
141.3
16.212
260.7
164.3
141.2
16.140
259.0
164.3
141.2
16.068
257.4
164.3
141.2
15.996
255.8
254.2
164.2
164.2
141.1
141.1
15.924
15.852
252.6
164.1
141.0
15.781
250.9
249.3
164.1
164.1
141.0
141.0
15.709
15.638
247
246
7
1
164.0
140.9
15.566
244
242
5
8
164.0
164.0
140.9
140.9
15.495
15.423
163.9
140.8
15.352
241
2
163.9
140.8
15.281
239
6
238
236
0
4
163.8
163.8
140.7
140.7
15.210
15.139
234
233
8
1
163.8
163.7
140.7
140.6
15.068
14.997
163.7
140.6
14.926
163.6
163.6
140.5
140.5
14.855
14.784
231,5
229.9
228.3
226.7
225.0
223.4
163.6
140.5
14.713
163.5
163.5
140.4
140.4
14.642
14.571
163.4
140.3
14.500
221.8
163.4
140.3
14.430
220.2
218.6
163.4
163.3
140.3
140.2
14.359
14.288
216.9
163.3
140.2
14.217
215.3
163.2
163.2
140.1
140.1
14.146
14.076
213.7
212.1
163.2
140.1
14.005
210.5
163.1
140.0
13.934
208.9
163.1
140.0
13.863
207.2
163.0
163.0
139.9
139.9
13.792
13.722
163.0
139.9
13.651
205.6
204.0
5.4-8
- 323.8
SNA-8-D-027(III)REV
POUNDS
2
._aendment
86
9/10/70
TABLE
124 i0 AND
RADIUS
TANK
NO.
14.2
INCHES
1 Y-CG
Z-CG
(ULLAGE/(VOLUME
SUBSEQUENT
DESCENT
(Continued)
STAGE
DENSITY
- -43.2
(CONSTANT)
- -43.2"
(CONSTANT)
OF
5.4-2
LIQUID))
X
i00
TANK
WATER
- 62.4
NO.
MASS
LBS/CU.
PROPERTIES
FT.
WEIGHT
2 Y-CG
- 43.2
(CONSTANT)
Z-CG
- 43.2
(CONSTANT)
-
323.8
POUNDS
- 37.757
Weight
Pounds
Tank-i
X-CG
Tank-2
X-CG
202.4
163.0
139.9
13.580
200.8
163.9
139.8
13.509
199.1
162.9
139.8
13.438
197.5
162.8
139.7
13.367
195.9
194.3
162.8
162.8
139.7
139.7
13.296
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
186.2
162.6
162.5
139.5
139.4
12.940
12.869
184.6
182.9
162.5
162.4
139.4
139.3
12.797
12.726
181.3
179.7
162.4
162.3
139.3
139.2
12.654
12.582
178.1
162.3
139.2
12.511
176.5
174.9
162.3
162.2
139.2
139.1
12.439
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
166.8
162.1
162.0
159.0
138.9
12.078
12.006
165.1
163.5
162.0
161.9
138.9
138.8
11.933
11.860
161.9
161.9
138.8
11.788
160.3
158.7
161.8
161.8
138.7
138.7
11.715
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
150.6
161.6
161.6
138.5
138.5
11.348
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
Height
Inches
SNA-8-D-027(IZI)REV
2
Amendment
86
9/10/70
TABLE
LM
RADIUS
TANK
- 14.2
NO.
i0
AND
SUBSEQUENT
INCHES
- -43.2
(CONSTANT)
Z-CG
- -43.2
(CONSTANT)
OF
DESCENT
(Continued)
STAGE
DENSITY
1 Y-CG
(ULLAGE/(VOLUME
5.4-2
LIQUID))
X 100
TANK
WATER
- 62.4
NO.
MASS
LBS/CU.
PROPERTIES
FT.
WEIGHT
2 Y-CG
- 43.2
(CONSTANT)
Z-CG
- 43.2
(CONSTANT)
-
323.8
POUNDS
- 37.757
Weight
Pounds
Tank-I
X-CG
Tank-2
X-CG
Height
Inches
144.1
161.4
138.3
10.977
142.5
140.9
161.4
138.3
10.902
138.2
10.827
139.2
161.3
161.3
138.2
10.752
137.6
161.2
136.0
134.4
161.2
161.1
138.1
138.1
10.677
10.601
138.0
10.526
132.8
161.1
138.0
10.450
131.1
129.5
161.0
161.0
127.9
160.9
137.9
137.9
137.8
10.373
10.297
10.220
126.3
124.7
160.9
160.9
137.8
10.143
137.8
10.066
123.0
160.8
121.4
119.8
160.8
160.7
137.7
137.7
9.989
9.911
137.6
9.833
118.2
116.6
160.7
160.6
137.6
137.5
9.755
9.676
114.9
160.6
113.3
111.7
110.1
160.5
160.5
137.5
137.4
9.597
9.518
160.4
137.4
137.3
9.438
9.358
108.5
160.4
137.3
9.278
106.9
137.2
9.198
105.2
160.3
160.3
137.2
9.117
103.6
102.0
160.2
160.2
137.1
137.1
8.035
8.953
100.4
160.1
137.0
8.871
98.8
97.1
160.1
137.0
136.9
8.789
8.706
136.9
8.622
8.538
8.454
95.5
160.0
160.0
93.9
159,9
92.3
1599
136.8
136.8
90.7
1598
136.7
8.369
89.0
159,8
136.7
8.284
87.4
85.8
84.2
159,7
159,6
159,6
136.6
136.5
136.5
8.198
8.111
8.024
82.6
159,5
80.9
79.3
159.5
159.4
136.4
136.4
7.937
7.849
136.3
7.760
5.4-10
SNA-8-D-O27(III)REV
U
IZ
2
_'.-
L
L
Amendment
2/16/71
TABLE 5.4-2
I_ I0 AND SUBSEQUENT
DESCENT
(ConCLnued)
STAGE WATER MASS PROPERTIES
RADIUS
- 14.2 INCHES
DENSITY - 62.4 LBS/CU. FT. WEIGHT
TANK NO. 1 Y-CG - -43.2 (CONSTANT)
TANK NO. 2 Y-CG - 43.2 (CONSTANT)
Z-CG - -43.2. (CONSTANT)
Z-CG - 43.2 (CONSTANT)
(ULLAGE/(VOLUME OF LIQUID)) X I00 m 37.757
Weight
Pound____a
Tank-1
X-C_._G
77.7
76.1
74.5
72.9
71.2
69.6
68.0
66.4
64.8
63.1
61.5
59.9
58.3
56.7
55.0
53.4
51.8
50.2
48.6
47.0
45.3
43.7
42.1
40.5
38.9
37.2
35.6
34.0
32.4
30.8
29.1
27.5
25.9
24.3
22.7
21.0
19,4
17.8
16.2
14.6
159.4
159.3
159.3
159.2
159.1
159.1
159.0
159.0
158.9
158.8
158.8
158.7
158.7
158.6
158.5
158.5
158.4
158.3
158.3
158.2
158.1
158.1
158.0
157.9
157.8
157.8
157.7
157.6
157.5
157.4
157,4
157,3
157.2
157.1
157.0
156.9
156.8
156.7
156.6
156.5
Tank-2
X-CG
I_
12 E
12 L
L"
136.3
136.2
136.2
136.1
136.0
136.0
135.9
135.9
135.8
135.7
135.7
135.6
135.6
135.5
135.4
135.4
135.3
135.2
135.2
135.1
135.0
135.0
134.9
134.8
134.7
134.7
134.6
134.5
134.4
134.3
134.3
134.2
134.1
134.0
133.9
133.8
133.7
133.6
133.5
133.4
E
1_ I:
- 323.8 POUNDS
Height
Inches
7.670
7.580
7.489
7.398
7.306
7.213
7.119
7.024
6.929
6.832
6.735
6.637
6.538
6.437
6.336
6.233
6.129
6.024
5.917
5.809
5.700
5.589
5.476
5.361
5.245
5.126
5.005
4.882
4.757
4.628
4.497
4.363
4.225
4.083
3.937
3.787
3.631
3.469
3.301
3.124
I
SNA-8-1)-027(ZII)P,.EV
5.4-11
11 111 _
i01
l.l
11 II
lZ
j_
L
L
2
E
Amendment
86
9/10/70
TABLE
LH 10
RADIUS
TANK
= 14,2
NO.
INCHES
- -43.2
(CONSTANT)
Z-CG
- -43.2
(CONSTANT)
OF
DESCENT
(Continued)
STAGE
DENSITY
1 Y-CG
(ULLAGE/(VOLUME
Weight
Pounds
AND SUBSEQUENT
5.4-2
LIQUID))
X 100
TANK
WATER
= 62.4
NO.
MASS
LBS/CU.
FT.
WEIGHT
2 Y-CG
- 43.2
(CONSTANT)
Z-CG
- 43.2
(CONSTANT)
Tank-i
X-CG
Tank-2
X-CG
156.3
133
2
2.939
11.3
156.2
133
1
2.742
9.7
156.1
133
8.1
6.5
155.9
155.8
132
132
0
8
2.532
2.305
7
2.055
4.9
155.6
132
5
1.774
3.2
155.4
132
3
1.442
1.6
155.1
132
0
1.015
l,' [: l: E
E
L
POUNDS
Height
Inches
13.0
!1
= 323.8
- 37.757
5.4-12
!1
PROPERTIES
E
E
SNA-8-D-027(III)REV
b:
]2
2
L
k_
i
........
I
L'_
z
Vt
.k.._
L
T-
'v--
'_-
v-
V'
_
. "11 _U
-.l[_:.
IS
It
l(
l_
l_
,L.
.L
J,-
_
i,.
L
L
_r
t..
d
I
LUNAR MODULE ASCENT WATER
MASS PROPERTIES
NOTE:
I.
2.
1
.
Mass Properties are given for liquids in individual tanks.
Moments of Inertia are about center of gravity of water in individual
tanks, coordinates of which are given.
Centers of Gravity in Y and Z directions are given at top of each
page.
The number of tanks of a particular kind is indicated
number on the first line of each page.
5.5-I
II
IIJ I,[ E
l:." 1,: L
L
L" l;.
h"
by the last
SNA-8-D-O27(III)REV
E
E
l_
I_ E
L
2
L
L
L
LM ASCENT WATER MASS PROPERTIES-2 TANKS
Y-CG = + OR - 25.0 (CONST) Z-CG = + OR RADIUS=7.155
CYLINDRICAL
DENSITY=62.400
LBS/CU.FT.
(ULLAGE/(VOL.
WEIGHT
X-CG
41.2
41,0
40.8
40.6
40,4
40.2
40.0
39.8
39.6
39.3
39.1
38.9
38.7
38,5
36.3
38.1
37,9
37.7
37.5
37.3
37.1
36.9
36,7
36.5
36.3
36.0
35.8
35.6
35.4
35.2
35.0
34.8
34.6
34.4
34.2
34.0
33.8
33.6
33,4
33.2
33,0
32.8
32,5
300.3
300.3
300.3
300.3
300.3
300.2
300.2
300.2
300.2
300.2
300.1
300.1
300.1
300.1
300.1
300.1
300.0
300.0
300.0
300.0
300.0
299.9
299.9
299.9
299.9
299.9
299.8
299.8
299.8
299.8
299.8
299,7
299.7
299.7
299.7
299.6
299.6
299.6
299.6
299.6
299.6
299.6
299.5
(CONST)
WEIGHT:
SECTION = 0.0
OF LIQUID))xlO0:
13.7
41.2
34.481
IXX(S-FT.SQ.)
IYY or
0.0
0.0
0.0
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
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0,0
0.0
0.0
0.0
0.0
0.0
0.0
0,0
0.0
5.5-2
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
SNA-8-D-O27(III)REV
U
LE
L
2
'
L
"
L
'
L
LM ASCENT WATER MASS PROPERTIES-2
Y-CG = + OR RADIUS=
DENSITY:
25.0
(CONST)
7.155 CYLINDRICAL
62.400
LBS/CU.FT.
WEIGHT
X-CG
32.3
32.1
31.9
31.7
31.5
31.3
31 .I
30.9
30.7
30.5
30.3
30.1
29.9
29.7
29.5
29,3
29.0
28.8
28.6
28.4
28.2
28.0
27.8
27.6
27.4
27.2
27.0
26.8
26.6
26.4
26.2
26.0
25.7
25.5
25.3
25.1
24.9
24.7
24.5
24.3
24.1
23.9
23,7
299.5
299.5
299.5
299.5
299,4
299.4
299.4
299.4
299.4
299.3
299.3
299.3
299.3
299.3
299.2
299.2
299.2
299.2
299.2
299,1
299.1
299.1
299.1
299.1
299.0
299.0
299.0
299.0
299.0
298.9
298.9
298.9
298.9
298.9
298.8
298.8
298.8
298.8
298,8
298.7
298.7
298.7
298.7
TANKS
Z-CG = + OR SECTION=
0.0
13.7
WEIGHT=
IXX(S-FT.SQ.)
0.0
0,0
0.0
0.0
0.0
0.0
0.0
0.0
0o0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
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. 0
O. 0
O. 0
O. 0
0.0
O. 0
5.5-3
(CONST)
41.2
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
SNA-8-D-O27(III)REV
2
LM ASCENT WATER MASS PROPERTIES-2
Y-CG = + OR RADIUS=
DENSITY=
25.0
(CONST)
7.155 CYLINDRICAL
62.400 LBS/CU.FT.
WEIGHT
X-CG
23.5
23.3
23.1
22.9
22.7
22.5
22.2
22.0
21.8
21.6
21.4
21.2
21.0
20.8
20.6
20.4
20.2
20.0
19.8
19.6
19.4
19.2
19.0
18.7
18.5
18.3
18.1
17.9
17.7
17.5
17.3
17.1
16.0
16.7
16.5
16.3
16.1
15.9
15.7
15.4
15.2
15.0
14.8
298.7
298.6
298.6
298.6
298.6
298.6
298.5
298.5
298.5
298.5
298.4
298.4
298.4
298.4
298.4
298.3
298.3
298.3
298.3
298 2
298 2
298 2
298 2
298 2
298 l
298 l
298. 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
TANKS
Z-CG = + OR SECTION=
13.7
0.0
(CONST)
WEIGHT:
IYY or IZZ(S-FT.SQ.)
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
0.0
0.0
0.0
0.0
0.0
0.0
0,0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0,0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
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
ILl ILl I.I I.; _
L
E
L
E
]2 E
41.2
SNA-8-D-O27(III)REV
E
U
1_ L_ E
L
2
,_ ,_ ,L.
LM ASCENT WATER MASS PROPERTIES-2
Y-CG = + OR -
25.0
(CONST)
RADIUS= 7.155 CYLINDRICAL
DENSITY: 62.400
LBS/CU.FT.
WEIGHT
X-CG
14.6
14.4
14.2
14.0
13.8
13.6
13.4
13.2
13.0
12.8
12.6
12.4
12.2
II .9
II .7
I I. 5
II .3
II .l
I0.9
I0.7
I0.5
I0.3
lO.l
9.9
9.7
9.5
9.3
9. l
8.9
8.7
8.4
8.2
8.0
7.8
7.6
7.4
7.2
7.0
6.8
6.6
6.4
6.2
6.0
297.7
297.7
297.6
297.6
297.6
297.6
297.5
297.5
297.5
297.5
297.4
297.4
297.4
297.4
297.3
297.3
297.3
297.3
297.2
297.2
297.2
297.2
297.1
297. l
297. l
297.0
297.0
297.0
297.0
296.9
296.9
296.9
296.8
296.8
296.8
296.7
296.7
296.7
296.6
296.6
296.6
296.5
296.5
TANKS
Z-CG = + OR SECTION= 0.0
1:
E
IZ IL Z
(CONST)
WEIGHT=
IXX(S-FT.SQ.)
41.2
IYY or
E
E
E
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
0.0
0.0
0.0
0.0
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
5.5-5
ILl ILl 1.[ E
13.7
SNA-8-D-O27(III)REV
L,' l J; Ii
"E
L
L
2
,_
_
LM ASCENT WATER MASS PROPERTIES-2 TANKS
Y-CG = + OR - 25.0 (COrISl) Z-CC- = + OR - 13.7
RADIUS= 7.155 CYLINDRICAL SECTION=
DENSITY= 62.400 LBS/CU.FT.
WEIGHT
X-CG
5.8
5.6
5.4
5.1
4.9
4.7
4.5
4.3
4.1
3.9
3.7
3.5
3.3
3.1
2.9
2.7
2.5
2.3
2.1
l .9
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0.8
0.6
0.4
0.2
296.5
296.4
296.4
296.4
296.3
296.3
296.2
296.2
296.2
296.1
296.1
296.0
296.0
295.9
295.9
295.9
295.8
295.7
295.7
295.6
295.6
295.5
295.4
295.4
295.3
295.2
295.1
294.9
0.0
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0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
0.0
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0.0
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5.5-6
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0.0
0.0
0.0
0.0
0.0
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0.0
0.0
0.0
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O.O
0.0
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TABLE
LM-10
AND
SUBSEQUENT
106
6/22/71
5.6-2
MISCELLANEOUS
CONSUMABLES
CENTER
OF
GRAVITY
(Inches)
ECS
WEIGHT
COOLANT:
Ascent
YE
(Pounds)
32.1
- Primary
251.9
9.9
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9.9
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1.7
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load
information
in Section
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3
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SNA-8-D-027
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3
TABLE
LM
Miscellaneous
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CENTER
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(Inches)
Consumables
WEIGHT
(Pounds)
COOLANT:
Ascent
5.6-2
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YE
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6.6
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48.5
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Loading
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load
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in Section
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5.6-7
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SNA-8-D-027(III)REV
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