This page no longer updated from 31 October 2001. Latest version can be found at 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.


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.


Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .