Table 5-9 – ASSUMPTIONS FOR THE APOLLO 11 DPS PROPELLANT BUDGET 1. Integrated average Isp = 301.9 ±3.54 seconds 2. LM separation weight = 33746. lb 3. Mixture ratio = 1.596 ±0.0108 4. Nominal ∆V = 6728.6 ±96 fps 5. Non-∆V consumables of 47.4 lb from separation to DOI and 106.1 lb from DOI to touchdown. ASCENT PROPULSION SYSTEM PROPELLANT BUDGET ASCENT PROPULSION SUBSYSTEM (APS) – Tables 5-10 and 5-11 present the ascent propellant budget for the current mission. Propellant loads are those actually on LM-5. Mission ∆V was coordinated with LAB in MPAD. The budget shown in table 5-10 accounts for an engine valve-pair malfunction, a PGNCS to AGS switchover, and a touchdown abort. There is a total propellant margin of 68 lb or about 6 seconds of burn time. Table 5-10 – APOLLO 11 APS PROPELLANT SUMMARY PROPELLANT PROPELLANT ITEM REQUIRED, LB REMAINING, LB Loaded a -- 5238.4 Trapped and unavailable 48.9 5189.5 Outage 17.5 5172.0 Available for ∆V -- 5172.0 Nominal Required for ∆V of 6072.5 fps 4965.8 206.2 Dispersions (-3 σ) 57.8 148.4 Contingencies Engine Valve-Pair Malfunction (∆MR=±.016) 19.6 128.8 PGNCS to AGS Switchover (40 fps) 23.8 105.0 Touchdown Abort (∆W=+99.9 lb, ∆∆V=-15fps) 36.8 68.2 Margin (6 seconds) -- 68.2 a Includes 2019.9 lb fuel and 3218.5 lb oxidizer this is loaded on the LM-5 spacecraft. Table 5-11 – ASSUMPTIONS FOR THE APOLLO 11 APS PROPELLANT BUDGET 1. Isp = 308.97 ±3.553 seconds 2. Mixture ratio = 1.602 ±0.0225 3. Nominal ∆V = 6072.5 ±33.5 fps 4. Ascent stage lift-of weight = 10873.6 lb 5 - 27