Encyclopedia Astronautica
Saturn LCB-Alumizine-140


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 N2O4/Alumizine Propellant engine, HY-140 Steel Hull.

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 pyld 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 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: 1,707,800 kg (3,765,000 lb).
Payload: 39,000 kg (85,000 lb).
Height: 65.00 m (213.00 ft).
Diameter: 6.61 m (21.68 ft).
Thrust: 20,951.50 kN (4,710,085 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • PF N204/Alumizine-2300k Notional N2O4/Alumizine rocket engine. 22,562 kN. Study 1967. Isp=280s. Used on Saturn LCB-Alumizine-140 launch vehicle. More...

See also
  • 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...
  • 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...

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-Alumizine-140 N2O4/Alumizine propellant rocket stage. Loaded/empty mass 1,542,200/154,200 kg. Thrust 22,563.10 kN. Vacuum specific impulse 280 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 N2O4/Alumizine Propellant engine, HY-140 Hull More...

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