TABLE 5-5 – ASSUMPTIONS FOR THE APOLLO 11 SPS PROPELLANT BUDGET 1. There is a non-propulsive propellant loss of 14.4 lb for each engine start. LM rescue assumed three engine starts. 2. A mission fl exibility ?V of 900 fps has been included in the SPS budget to provide the capability to perform a worst case LM rescue, or to handle several other contingencies (such as loss of PGNCS), or to perform a quicker earth return. 3. Spacecraft weight: CM 12 280.0 lb SM 10 551.3 lb SLA Ring 98.0 lb Tanked SPS 40 600.7 lb LM (unmanned) 33 278.3 lb Total 96 808.3 lb 4. Lunar Orbit Activity Total weight transfer (CSM to LM) = 436.7 lb Total weight transfer (LM to CSM) = 284.0 lb 5. SM RCS, EPS and ECS weight losses: Mission Period Incremental Weight Loss, lb EL to TLMC 151.8 TLMC to LOI-1 327.1 LOI-1 to LOI-2 32.0 LOI-2 to LOPC 146.5 LOPC to TEI 216.1 6. SM RCS usage (above nominal rendezvous requirement) for LM rescue was 216 lb. 5 - 21