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

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SM2A-03-SC01Z APOLLO OPERATIONS HANDBOOK 4.4.1.I ECS Radiator Inlet Temperature. PERFORY._NCE The ECS radiator inlet temperature (obtained from MSFN or the a_ciliary DC volts meter on panel 200) should be maintained at 75"F or warmer to prevent against radiator freezing. However, excessive water boiling will result if the radiators are directly exposed t6 the sun for prolonged periods. S/C orientations exposing the ECS radiator surface to solar incidence angles less than 45 degrees should not be maintained longer than 20 minutes per or_oit. Also, the S/C attitude should be constrained inertially or held fixed relative to the earth without roll for a period longer than one orbit, if the solar incidence to the radiator is less than 45 degrees. To prevent excessive water consumption (boiling) the S/C attitude must not be constrained in an inertial or earth-fixed orientation without roll for longer than 3 hours. CAUTION Extreme radiator sooting can be detected by a rapid depletion of the water supply and high radiator outlet temperature. • If the radiator outlet temperature averages above 53@F as a result of extreme sooting, high electrical loads, or poor radiator orientation, the water tanks _ill be depleted at a rate incompatible with the planned mission duration time. NOTE Observance of ECS radiator constraints will als0 ensure a satisfactory environment for EPS radiator operation. 4.4.1.2 S/M RCS Engine Temperatures. The S/M RCS engines are qualified to work within the range of 35" to 175"F, the propellant valve temperature limits. A red warning light on panel l0 will illuminate to indicate when the temperatures exceed this r_nge. Temperatures above 175°F are not expected, except temporarily (possible) during boost. Heaters that cycle automatically are provided on each quad to maintain temperatures above the lower limit. However, if one quad is continuously pointed away from the sun for longer than I0 hours, it is possible for the h0"F lower temperature limit (for the propellant) to be reached at the RCS tank outlet. NOTE S/C attitude should be monitored during extended periodz between RCS firings to ensure that safe temperatures awe maintained. S/C OPE_ATIOItAL CONS'fI_._INTS AND LI_,'rTATIONS Basic Date_'L_ I;_v L'_6.. . Revision Date m_ .L I i T as e ,
i I I I ' I . I : i i ' i ' i i I I I I I 1 r 4.4.1.3 4._ ,l.4 4 ,_.2 4.4,2, ] 4.4,2.2 SM2A-03-SC01 2 APOLLO OPERATIONS HANDBOOK PERFORMANCE BPS Propellant Feedllne Temperatures. SPS propellant feedllnes are normally maintained above h0"F by heaters and insulation. The MSFN should monitor SPS external line temperatures and advise the crew whenever temperatures drop below 50°F. If S/C attitude iS maintained so that the SPS is pointed away from the sun for an extended period and heater capacity is insufficient to maintain llne temperatures above h0"F, the S/C should be reoriented until acceptable SPS line temperatures are reached. Heat Shield Temperature. The heat shield ablator lower temperature limit of -150°F can be exceeded and cause surface cracking if the thin (-Z) portion of the ablator is pointed away from the sun for longer than 3 hours. Because of the moderate response time, it is unlikely that a critical cold condition would be approached during the mission. CAUTION If the heat shield ablator temperature is allowed to rise and remain above 200@F for any aggregate period longer than 2 hours, outgassing will result and cause a corresponding degradation to the ablator stress margin. OPERATIONAL LIMITATIONS. The available data in the subsequent paragraphs shows limitations imposed on the S/C and/or crew during ascent, descent or aborts, spaceflight, and entry. Acoustic and Vibration Effects. The crew will be exposed to acoustic and vibration effects during ascent (130 seconds), possible LES aborts (20 seconds), and entry (i00 seconds)_ Vibration effects will also be experlenced during hlgh-altltude aborts (SPS induced) and spaceflight SPS firings, (See figures 4-26 and 4-27.) Altimeter Error and C/M Base Pressure Effects. The altimeter (barometric pressure indicator) error resulting from veloclt_ pressures on the co_u-mand module (below iI_,000 feet) is shown in figure ' ._,_ C/M Llft/Dra_ Profile and Entry Effects. Charts showin_ the C/M li#t/drag profile iuid time histories for. normal.entrles _.e showu In figures i-2_ thr,A,_h l,.j[ ....... S/C OPERATIONAL CONSTRAIntS AND LIMITATIONS Basi_ Date .k2 N.'v..l_66 .-_Revtsion Date,.,- ........ -i-Pag_ .... !,=I,_..
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Apollo 204 Review Board Appendix C Section 2 - NASA's History ...

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