This page no longer updated from 31 October 2001. Latest version can be found at Saturn MLV-V-4(S)-B

Saturn MLV 5-3
Saturn MLV 5-3 -

Credit: © Mark Wade. 6,374 bytes. 164 x 923 pixels.

Family: Saturn V. Country: USA. Status: Study 1967.

Boeing study, 1967. Configuration of improved Saturn 5 with Titan UA1207 120 inch solid rocket boosters. Saturn IC stretched 336 inches with 6.0 million pounds propellant and 5 F-1 engines; Saturn II and Saturn IVB stages strengthened but not stretched. Empty mass of stages increased by 13.9% (S-IC), 8.6% (S-II) and 11.8% (S-IVB). Studied again by Boeing in 1967 as Saturn V-4(S)B.


LEO Payload: 171,990 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 63,160 kg. to a: Translunar trajectory. Liftoff Thrust: 7,068,380 kgf. Total Mass: 4,699,860 kg. Core Diameter: 10.1 m. Total Length: 89.0 m. Flyaway Unit Cost $: 97.44 million. in 1985 unit dollars.


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Last update 12 March 2001.
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