In this analysis the retrorockets were used to terminate the final velocity of 150 fps (45.7 mps). The vehicles investigated all used a LOX/LH2 propellant second stage with high chamber pressure (Pc = 4000 psia) staged combustion cycle engines. Two booster classes were used. The first class used LOX/RP-1 propellant with high chamber pressure (Pc = 4000 psia) staged combustion cycle engines. The second booster class had LOX/propane for propellant and used lower chamber pressure (Pc = 3000 psia) gas generator cycle engines. The groundrules used for sizing the vehicles are summarized in figure VI-B-4-1. In addition to a 20 percent contingency that was added to the vehicle stage dry weights for uncertainty and vehicle weight growth, a 20 percent increase was added to the tank weights for slapdown loads and reusability considerations. The dry weight contingency on the booster stages was assumed to include the preignition and thrust buildup propellant of the second stages. Aerodynamic and propulsive data bases are presented in figures VI-B-4-2 through VI-B-4-4 respectively. Figures VI-B-4-5 through 22 present the major and detailed weight breakdowns for the launch system. Figure VI- B-4-23 outlines the payload changes expected for vehicles launched from 28.5 degrees and 7 degrees. Figure VI-B-4-24 outlines proposed future work for the SPS system. Questions concerning the results herein should be addressed to Mr. Gerald Launey and Mr. William Richards at extension 6258.
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