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Saturn LCB-Lox/RP-1
Part of Saturn I Family
American orbital launch vehicle. 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 LOx/RFP-1 engine.

Status: Study 1967. Payload: 39,000 kg (85,000 lb). Thrust: 18,682.10 kN (4,199,903 lbf). Gross mass: 1,526,400 kg (3,365,100 lb). Height: 80.00 m (262.00 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-Lox/RP-1

  • Stage 1. 1 x Saturn LCB-Lox/RP-1. Gross Mass: 1,360,800 kg (3,000,000 lb). Empty Mass: 108,900 kg (240,000 lb). Thrust (vac): 20,306.600 kN (4,565,105 lbf). Isp: 275 sec. Burn time: 163 sec. Isp(sl): 253 sec. Diameter: 6.61 m (21.68 ft). Span: 9.26 m (30.38 ft). Length: 48.78 m (160.03 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: PF RP-1. 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 Lox/RFP-1 engine.
  • 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).



Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: PF RP-1. Stages: Saturn IVB (S-IB), Saturn LCB-Lox/RP-1 stage.

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