Apollo 11 Flight Plan, Final - July 1, 1969 Page 311 (311 of 353)

5 - 19 TABLE 5-3 CM RCS Propellant Summary Item Propellant required, lb. Propellant remaining, lb. Loaded -- 245.0 Trapped 36.4 208.6 Available for -- 208.6 mission planning Nominal usage 39.3 169.3 Nominal remaining -- 169.3

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5 - 19 TABLE 5-3 CM RCS Propellant Summary Item Propellant required, lb. Propellant remaining, lb. Loaded -- 245.0 Trapped 36.4 208.6 Available for -- 208.6 mission planning Nominal usage 39.3 169.3 Nominal remaining -- 169.3

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5 - 18 Usable SM RCS propellant remaining, lb 20 200 180 160 140 120 100 80 60 40 100 0 20 40 60 80 305 240 200 160 40 80 120 0 Onboard gaging, percent Ground elapsed time, hr Figure 5-5 SM RCS propellant profi le - quad D 280 Quad D

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SERVICE PROPULSION SYSTEM SERVICE PROPULSION SYSTEM (SPS). – The budget presented in table 5-4 is for a July 16 launch, 72 degree launch azimuth, fi rst opportunity injection, 59.5 hour lunar parking orbit, and fast earth return. The assumptions used in preparing this budget are presented in table 5-5. ∆V requirements were coordinated with LMAB in MPAD. It should be noted that the mission fl exibility allowance of 900 fps has been used in addition to the fast return. In real time however, it is highly likely that a slower earth return would be performed in the mission fl exibiblity ∆V had already been used (e.g., for LM rescue). Table 5-4 shows 3906 lbs of propellant remaining nominally and a total propellant margin (accounting both for the fl exibility ∆V and the fast return) of 1268 lb. Table 5-4 – APOLLO 11 SPS PROPELLANT SUMMARY PROPELLANT PROPELLANT ITEM REQUIRED, LB REMAINING, LB Loaded a -- 40803.0 Trapped and unavailable 441.4 40361.6 Outage 59.5 40302.1 Unbalance meter 100.0 40202.1 Available for ∆V -- 40202.1 Required for ∆V TLMC (120 fps)b 1166.4 39035.7 LOI-1 (2924 fps, 5 min. 59 sec.) 23862.4 15173.3 LOI-2 (157.8 fps, 16.4 sec.) 1115.4 14057.9 LOPC (16.6 fps, .9 sec.) 73.8 13984.1 TEI (3292.7 fps, 149 sec.) 10077.8 3906.3 Nominal remaining -- 3906.3 Mission fl exibility (900 fps) 2212.4 1693.9 Dispersions (-3 σ) 426.0 1267.9 Propellant margin -- 1267.9 a 15712.0 lb of fuel and 25091.0 lb of oxidizer this is loaded on CSM-107. b Includes 19.7 fps for evasive maneuver. 5 - 20

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Page 21Section I - General click to expand contents

Page 45Section II - Update Forms click to expand contents

Page 101Section III - Detailed Timeline click to expand contents

Page 1153. Translunar Coast Activities click to expand contents

Page 1734. Lunar Orbit Activities click to expand contents

Page 267Section IV - Detailed Test Objectives click to expand contents

Page 289Section V - Consumables click to expand contents

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