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

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SMZA- 03-SC012 APOLLO OPERATIONS HANDBOOK PERFORMANCE S/M RCS PROPELLANT REQUIRED FOR UUGE SPACECRAFf WEIGHT (19 S/M RCS PROPELUNT REQUIRED FOR +X TRANSLATION T Y VlUL MMDB INFORMATION NOTE: Cuwos I, 2, and 3 hpnmt am ongfnr eonflgmtlon as abow. Figure L-17, S/M RCS Propellant Consumption for SPS Propellant Settling and Tx~anslation Maneuvers COBSUMABLE REQUIRmENTS 7 , .' .. ~~~i~ ~~t~ .. . 1-66 Revision Date - Page 11-24 ,--.
SM2A-03-SCO12 APOLLO OPERATIONS HANDBOOK PERFORMANCE Attitude Hold Following SPS Burn. S/M RCS propellant consumption required for attitude hold in three axes, immediately following an SPS burn and extending over a 10-minute period after the SPS burn, is presented in the upper chart of figure 4-18, his curve includes the total RCS requirement and should not be added to the results obtained from figure 4-14. However, after the end of the 10-minute slosh damping period, the rates in the lower chart of figure 4-14 should be used. ) For attitude holds delayed after the termina- tion of an SPS burn, both charts in figure 4-18 are used for adjusting BCS propellant consumption rates. j.1 .2 .2 C/M RCS PROPELWT CONSWTION DATA. Propellant consumables utilized by the 12 C/M RCS engines provide thrust for three-axes rotational and attitude control of the C/M (after an abort or during normal entry). The oxidizer/ fie1 ratio (by veight) for each of the four roll engines is 2.1t0.09 :1 at a propellant consumption rate of 0.345 lb/sec. The oxidizer/fuel ratio (by weight) for each of the eight remaining engines is 2.0+0.09:1 at a propellant consumption rate of 0.342 lb/sec. Any remaining propellant, including the helium used as a pressurant, is ejected prior to C/M touchdown (for all mission modes). Nominal values for the individual C/M RCS consumables (usable tank capacity of 225 pounds) are as follows : Weight per Tank Storage Filled Usable Consumables Tank (lb) (lb) Nitrogen tetroxide 2 89.2 75.0 (~~04 ) (oxidizer ) Monomethylhydrazine (MMH) (fuel) Helium (~e) 2 0.52 0.52 ( pressurant ) - Delivery Rate. to Engine 0.228 lb/sec (oxidizer/fuel ratio -of 2:l) I 0.234 Ib/sec (oxidizer/fuel ratio of 2.1:l) 0.114 lb/sec (oxidizer/fuel ratio of 2:l) 0.111 lb/sec (oxidizer/fuel 1 ratio of 2.1:l) rl C3NSUMABLE REQUIREMENTS Basic Date l2 NOv 1g66 Revision Date - - - Page 4-25 ,
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Apollo 204 Review Board Appendix C Section 2 - NASA's History ...

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