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Saturn LCB-Alumizine-140

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Status: Study 1967. Payload: 39,000 kg (85,000 lb). Thrust: 20,951.50 kN (4,710,085 lbf). Gross mass: 1,707,800 kg (3,765,000 lb). Height: 65.00 m (213.00 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-140

• Stage 1. 1 x Saturn LCB-Alumizine-140. 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. 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). Propellants: N2O4/Alumizine. No Engines: 1. Engine: PF N204/Alumizine-2300k. 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, HY-140 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).