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Gross Mass: 1,542,200 kg (3,399,900 lb). Empty Mass: 154,200 kg (339,900 lb). Thrust (vac): 22,563.100 kN (5,072,387 lbf). Isp: 280 sec. Burn time: 166 sec. Propellants: N2O4/Alumizine. Isp(sl): 260 sec. Diameter: 6.61 m (21.68 ft). Span: 9.26 m (30.38 ft). Length: 36.28 m (119.02 ft). Country: USA. No Engines: 1. Engine: PF N204/Alumizine-2300k. Status: Study 1967. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/Alumizine Propellant engine, HY-140 Hull
Used on Launch Vehicles:
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