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Saturn LCB-Alumizine-250

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Status: Study 1967. Payload: 39,000 kg (85,000 lb). Thrust: 17,525.80 kN (3,939,957 lbf). Gross mass: 1,435,700 kg (3,165,100 lb). Height: 59.00 m (193.00 ft). Diameter: 6.61 m (21.68 ft). Apogee: 185 km (114 mi).

LEO Payload: 39,000 kg (85,000 lb) to a 185 km orbit at 28.00 degrees.

Stage Data - Saturn LCB-Alumizine-250

• Stage 1. 1 x Saturn LCB-Alumizine-250. 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. 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). Propellants: N2O4/Alumizine. No Engines: 1. Engine: 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 payload to LEO): Low Cost Booster, Single Pressure-fed N2O4/Alumizine Propellant engine, Ni-250 Hull.

• Stage 2. 1 x Saturn IVB (S-IB). Gross Mass: 118,800 kg (261,900 lb). Empty Mass: 12,900 kg (28,400 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 17.80 m (58.30 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Out of Production. Comments: Saturn IB version of S-IVB stage. Due to lower payload, 300 kg saving in structure compared to Saturn V version. Due to deletion of restart requirement, 700 kg saving in propulsion system (primarily reduction in helium for restart).