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

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_M2A-03-SC012
APOLLO OPERATIONS HANDBOOK
PERFORMkNCE
_ith an e!ectricul current level of ::bout 55 :_mps By
rolling or tumbling the S/C, to allo_, for periodic exposure
of the radiators to the sun, the inlet temperature can be
70°F _ith an electrical current level of about 50 :imps
before the space r_6iators start to freeze.
RCS AND SPS THRUSTING DATA.
RCS TRANSLATION CONTROL.
0
Spacecraft translation is possible at any time after S-IVB
separation and prior to the time when S/M-C/M separation occurs.
Translation maneuvers are provided through the S/M RCS engines
andare normally initiated manually b_ the translation control
T-handle in the ±X, Y, and Z axes, or by the DIRECT ULLAGE switch
in the +X axis. The translation control (manipulated in the
counterclock_.:ise position to the abort detent for about 2.5
seconds) also providez for CSM/S-IVB separation. "While the
control is in the abort detent position, the CSM attitude is not
controlled. Upon.confirmati6n of physical separation, the translation
control is moved to the.÷X position and the SCS initiates
attitude control to a mazim_m deadband o£ 5 degrees.. (R.,fer to
section 2 for systems operation.)
NOTE Each S/M RCS engine nominally develops i00 pounds
of thrust. If four engines are ignited (as in u iX
translation), the S/C v;ill accelerate _t 0.4 to 0.8
ft/sec2, depending on the S/C v_eight ',ridcontrol mode.
(0nly two engines are ignited for ±Y and ±Z translations.)
The minimtur, RCS impulse duration, assuming _verage human-
response, is on the order of 200 milliseconds. The maximum
translation duration is a function of the uvailzble
propellant.
RCS ROTATION C@_TROL.
Automatic or manual rotational control of the S/C is pro-
vided in both the G&_; and the SCS control modes. (Refer to
section 2 for systems operation.)
NOTE TLe S/C can !rye a ma: