Encyclopedia Astronautica
Saturn LCB-SR


Solid propellant rocket stage. Loaded/empty mass 1,678,300/136,100 kg. Thrust 27,034.90 kN. Vacuum specific impulse 263 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, Solid Propellant

Status: Study 1967.
Gross mass: 1,678,300 kg (3,700,000 lb).
Unfuelled mass: 136,100 kg (300,000 lb).
Height: 38.11 m (125.03 ft).
Diameter: 6.61 m (21.68 ft).
Span: 9.26 m (30.38 ft).
Thrust: 27,034.90 kN (6,077,687 lbf).
Specific impulse: 263 s.
Specific impulse sea level: 238 s.
Burn time: 144 s.

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Associated Countries
Associated Engines
  • AJ-260X Aerojet solid rocket engine. 35,390.7 kN. Study 1967. Full length version of 260 inch motor tested in 1960's. Proposed for use in various Saturn and Nova configurations. Isp=263s. More...

Associated Launch Vehicles
  • Saturn LCB-SR 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, 260 inch solid motor, full length. More...

Associated Propellants
  • Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...

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