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astronautix.com Saturn V-B


Family: Saturn V. Country: USA. Status: Study 1968.

MSFC study, 1968. Intriguing stage-and-a-half to orbit design using Saturn S-ID stage. The S-ID would be the same length and engines as the standard Saturn IC, but the four outer engines and their boost structure would be jettisoned once 70% of the propellant was consumed, as in the Atlas ICBM. This booster engine assembly would be recovered and reused. The center engine would be gimbaled and serve as a sustainer engine to put the rest of the vehicle and its 50,000 pound payload into orbit. At very minimal cost (36 months leadtime and $ 150 million) the United States could have attained a payload capability and level of reusability similar to that of the space shuttle.


Specifications

LEO Payload: 22,600 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 3,440,290 kgf. Total Mass: 2,313,320 kg. Core Diameter: 10.1 m. Total Length: 50.0 m.



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