REUSABLE BALLISTIC ENTRY STAGES SATURN V (S-IC AND SII) WEIGHT AND GEOMETRY TECHNOLOGY OBTAINED FROM W. HEINEMAN OF EW USED FOR STRUCTURE AND MISCELLANEOUS WEIGHT SCALING 20 PCT PROPELLANT TANK "BEEF UP" FOR WATER IMPACT AND REUSABILITY 20 PCT DRY WEIGHT CONTINGENCY ADDED ON BOTH STAGES PROPULSION SYSTEM WEIGHTS AND PERFORMANCE DATA FROM EP FOR ADVANCED ENGINES LOX/RP-1 AND LOX/CoHq PROPELLANT FOR BOOSTER STAGES J o L0X/LH2 propellant in second stage 950 PSF MAX Q CONSTRAINT (WHERE REQUIRED) 4 g MAXIMUM ACCELERATION LIMIT 1 AND 2 MILLION LB PAYLOAD VEHICLES (INCLUDING SHROUD) 50 FT PAYLOAD SHROUD DIAMETER DUE EAST LAUNCH FROM ETR INTO A 50 X 270 N.MI. INSERTION ORBIT ON-ORBIT AND RETRO PROPULSION SYSTEM AND PROPELLANT INCLUDED IN PAYLOAD BOOSTER F/W = 1.4; SECOND STAGE F/W =1.1 SATURN V LAUNCH VEHICLE AERODYNAMIC DATA FPR PROPELLANT CALCULATED BASED ON RESERVING 0.75% OF TOTAL IDEAL VELOCITY FIGURE VI—B—4—1.- PRELIMINARY HLLV SIZING GROUND RULES
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