Encyclopedia Astronautica
Saturn LCB-Lox/RP-1


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 pyld to LEO): Low Cost Booster, Single Pressure-fed Lox/RFP-1 engine.

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 pyld 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 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).

Status: Study 1967.
Gross mass: 1,526,400 kg (3,365,100 lb).
Payload: 39,000 kg (85,000 lb).
Height: 80.00 m (262.00 ft).
Diameter: 6.61 m (21.68 ft).
Thrust: 18,682.10 kN (4,199,903 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • PF RP-1 Notional Lox/Kerosene rocket engine. 20,306 kN. Study 1967. Isp=275s. Used on Saturn LCB-Lox/RP-1 launch vehicle. More...

See also
  • Saturn The Saturn launch vehicle was the penultimate expression of the Peenemuende Rocket Team's designs for manned exploration of the moon and Mars. Numerous designs and variants were studied, but in the end only three models - the Saturn I, IB, and V - were built in the 1960's, and then only used to support NASA's Apollo moon landing program. More...
  • Saturn I Von Braun launch vehicle known as 'Cluster's Last Stand' - 8 Redstone tanks around a Jupiter tank core,powered by eight Jupiter engines. Originally intended as the launch vehicle for Apollo manned circumlunar flights. However it was developed so early, no payloads were available for it. More...

Associated Manufacturers and Agencies
  • Von Braun American manufacturer of rockets and spacecraft. Von Braun, USA. More...

Associated Stages
  • Saturn IVB (S-IB) Lox/LH2 propellant rocket stage. Loaded/empty mass 118,800/12,900 kg. Thrust 1,031.60 kN. Vacuum specific impulse 421 seconds. Saturn IB version of S-IVB stage. Due to lower payload 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). More...
  • Saturn LCB-Lox/RP-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,360,800/108,900 kg. Thrust 20,306.60 kN. Vacuum specific impulse 275 seconds. 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 Lox/RFP-1 engine More...

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