This page no longer updated from 31 October 2001. Latest version can be found at Saturn V-3B

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

Boeing study, 1967. Variation on MSFC 1965 study Saturn MLV-V-3 but with toroidal engines. Saturn IC stretched 240 inches with 5.6 million pounds propellant (but only 4.99 million pounds usable without solid rocket boosters) and 5 F-1A engines; S-II stretched 186 inches with 1.29 million lbs propellant and 5 J-2T-400 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2T-400 engine.


LEO Payload: 166,600 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 72,800 kg. to a: Translunar trajectory. Liftoff Thrust: 4,082,310 kgf. Total Mass: 3,741,120 kg. Core Diameter: 10.1 m. Total Length: 121.0 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 .