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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.
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.
- Stage Number: 0. 1 x Saturn S-ID Booster Gross Mass: 67,100 kg. Empty Mass: 67,100 kg. Thrust (vac): 3,157,300 kgf. Isp: 304 sec. Burn time: 154 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 42.1 m. Propellants: Lox/Kerosene No Engines: 4. F-1
- Stage Number: 1. 1 x Saturn S-ID Sustainer Gross Mass: 2,219,100 kg. Empty Mass: 68,100 kg. Thrust (vac): 789,300 kgf. Isp: 304 sec. Burn time: 315 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 42.1 m. Propellants: Lox/Kerosene No Engines: 1. F-1
- 228 - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. HTML when accessed: http://www.webcreations.com/ptm
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Last update 12 March 2001.
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