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Saturn V-25(S)U
Part of Saturn V
American orbital launch vehicle. 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.

Status: Study 1968. Payload: 248,663 kg (548,208 lb). Thrust: 72,338.40 kN (16,262,319 lbf). Gross mass: 6,439,300 kg (14,196,200 lb). Height: 153.00 m (501.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 486 km (301 mi).

LEO Payload: 248,663 kg (548,208 lb) to a 486 km orbit at 28.00 degrees. Payload: 160,000 kg (350,000 lb) to a translunar trajectory. Flyaway Unit Cost 1985$: 174.000 million.

Stage Data - Saturn V-25(S)U



Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: F-1A, Nerva-1. Stages: Saturn MS-IC-25(S), Saturn MS-II-4(S)B, Saturn S-N V-25(S)U, UA-156.


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