|
Gross Mass: 1,270,100 kg (2,800,000 lb). Empty Mass: 95,300 kg (210,100 lb). Thrust (vac): 18,873.800 kN (4,242,999 lbf). Isp: 280 sec. Burn time: 168 sec. Propellants: N2O4/Alumizine. Isp(sl): 260 sec. Diameter: 6.61 m (21.68 ft). Span: 9.26 m (30.38 ft). Length: 31.40 m (103.00 ft). Country: USA. No Engines: 1. Engine: PF N204/Alumizine-1925k. 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, Ni-250 Hull
Used on Launch Vehicles:
|