Encyclopedia Astronautica
Saturn LCB-Alumizine-250


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, Ni-250 Steel Hull.

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

More... - Chronology...


Associated Countries
Associated Engines
  • PF N204/Alumizine-1925k Notional N2O4/Alumizine rocket engine. 18,873 kN. Study 1967. Isp=280s. Used on Saturn LCB-Alumizine-250 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 LCB-Alumizine-250 N2O4/Alumizine propellant rocket stage. Loaded/empty mass 1,270,100/95,300 kg. Thrust 18,873.80 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, Ni-250 Hull More...
  • 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...

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