Apollo 204 Review Board Appendix C Section 2 - NASA's History ...

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SM2A-03-SCO12
APOLLO OPERATIONS HANDBOOK
PERFORMANCE
the individual S/M RCS consumables (maximum usable tank capacity
of 790 pounds) are as follows:
Weight
per Tank , Delivery
Maximum Rate to
Storage Filled Usable Engine
Consumables Tank (lb) (lb) (lb/sec )
Nitrogen tetroxide (N2Q4) 4 138.1 131.7 0.241
(oxidizer)
50% unsymmetrical 4 69.7 65.8 0.119
diamethylhydrazine and
50% hydrazine (UDMH/
N ~ H ~ (fuel) )
Helium (~e) (pressurant ) 4 0.52 0.52 N /A
Manual Attitude Control Maneuvers
S/M RCS propellant consumption rates for manual attitude
control maneuvers (proportional and direct control) are presented
in figure 4-13. Assumptions applicable to the curves shown in
figure 4-13 ' are as follows :
The dynamic disturbances accounted for are SPS propellant
slosh, the earth orbit aerodynamics and gravity gradient,
ECS steam venting, and rotating EPS.and ECS equipment.
s A nominal maneuver of 5.020.5 degrees per axis,
This data may be ratioed to account for different maneuver
axigles. The propellant consumption must be decreased by
10 percent for a 30-degree maneuver and increased by
20 percent for a 100-degree maneuver.
The manual single-axis maneuver propellant consumption is
the same as the single-axis maneuver in paragraph 4.2.1.2.
Automatic Attitude Control Maneuvers and Attitude Hold,
SIM RCS propellant consumption rates for G&N control
maneuvers (attitude control and attitude hold), versus S/C
CONSW@tE REQUIRPiENTS
Basic Date l2 NLO1' L36-6 ,Revirion Date,-,