user manual

TABLE 3.2-16 (CONTINUED)
MISSION J-2
LM-II - RCS PROPELLANT (2) (3)
System A Fuel
System A Oxidizer
System B Fuel
System B Oxidizer
Required Ullage Requirement (in _)
Load (Ib) 5 Minimum 4 Maximum 4
iActual5
Load (lb)
107.4±0.9 152.5 164.5
208.2±1.9 267.0 279.0
107.4±0.9 152.5 164.5
208.2±1.9 267.0 279.0
FUEL OXIDIZER
Propellant Load 214.8 416.4
Trapped Outside Tanks i0.0 15.8
Tanked 204.8 400.6
Trapped in Tanks 4.2 8.0
Nominal Deliverable 200.6 392.6
LM-II - Helium & NitroBen
Amendment 114
9/15/71
IActual 4
Ullage (In 3)
Consumable
Helium - APS tank #I (6)
- APS tank #2 (6)
- RCS tank #I (6)
RCS tank #2 (6)
- DPS (SHe)
- DPS (Ambient) (6)
Nitrogen - Ascent
- Descent
- Descent
Nominal Loadin_ Requirement
Pressure Temp Weight
(PSIA) (°F) (Ib)
3050 70 6.6
3050 70 6.6
3050 70 ]. 05
3050 70 1.05
80_2 N/A 51.2
1600 70 I.i
0.I
0.6
-0.6
Actual
Pressure Temp Weight
(PSIA) (°F) (ib)
LM-II - Water & GOX
Consumable
Ascent Water - tank #I
tank #2
Descent Water - tank #i
- tank #2
Ascent COX - tank #i (6)
- tank #2 (6)
Descent GOX - tank #i (6)
- tank #2 (6)
Nominal Loadin_ Requirement
Pressure Weight Pressure
(PSIA) (ib) (PSIA)
N/A (7) N/A
N/A (7) N/A
N/A (7) N/A
N/A (7) N/A
Actual
Weight
(Ib)
830 2.4
830 2.4
2700 48.0
2700 48.0
NOTES:
iSee Table 3.2-17 for actual propellant load calculation.
2See Section 5.6 for explanation of trapped propellants.
3See Table 3.2-18 for loading uncertainties.
4PV ullage calculation should be 166.5±50 cubic inches for LM/RCS fuel and
280±50 cubic inches for LM/RCS oxidizer per tank.
5LM/RCS required load includes propellant required to fill RCS manifolds
to thruster valves. See Table 3.2-16. See Section 5.6 for trapped
propellants.
6The indicated items should be loaded in accordance with loading windows
contained in the CSM/LM Spacecraft Operational Data Book_ Volume II,
Part 2, SNA-8-D-O27PT2.
7LM-II Descent Water shall be loaded to provide 388-0.0+I0.0 pounds at
Earth Launch. LM-II ascent water shall be loaded to provide 85 pounds
at earth launch. Initial load will be determined by the pressure-
temperature relationship provided in TABLE 3.2-16.1.
3.2-106
SNA-8-D-027 (Ill) REV 3