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Gross Mass: 1,270,100 kg.
Empty Mass: 95,300 kg. Thrust (vac): 1,924,600 kgf. Isp: 280 sec. Burn time: 168 sec. Propellants: N2O4/Alumizine Isp(sl): 260 sec. Diameter: 6.6 m. Span: 9.3 m. Length: 31.4 m. Country: USA. No Engines: 1. PF N204/Alumizine-1925k Status: Study 1967. Comments: 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, Ni-250 Hull.
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Last update 12 March 2001.
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© Mark Wade, 2001 .