This page no longer updated from 31 October 2001. Latest version can be found at Saturn V-25(S)U

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

Boeing study, 1968. 4 156 inch solid propellant boosters; Saturn IC stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; S-II standard length with 5 J-2 engines. This vehicle would place Nerva nuclear third stage into low earth orbit, where five such stages would be assembled together with the spacecraft for a manned Mars expedition.


LEO Payload: 248,663 kg. to: 486 km Orbit. at: 28.0 degrees. Payload: 160,000 kg. to a: Translunar trajectory. Liftoff Thrust: 7,376,460 kgf. Total Mass: 6,439,300 kg. Core Diameter: 10.1 m. Total Length: 153.0 m. Flyaway Unit Cost $: 174.00 million. in 1985 unit dollars.


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Last update 12 March 2001.
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