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Saturn MLV-V-4(S)-B
Part of Saturn V
Saturn MLV 5-3
Saturn MLV 5-3
Credit: © Mark Wade
American orbital launch vehicle. 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.

Status: Study 1967. Payload: 171,990 kg (379,170 lb). Thrust: 69,317.10 kN (15,583,104 lbf). Gross mass: 4,699,860 kg (10,361,410 lb). Height: 89.00 m (291.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

LEO Payload: 171,990 kg (379,170 lb) to a 185 km orbit at 28.00 degrees. Payload: 63,160 kg (139,240 lb) to a translunar trajectory. Flyaway Unit Cost 1985$: 97.440 million.

Stage Data - Saturn MLV-V-4(S)-B



Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: J-2T-250K, F-1A, F-1. Stages: Saturn MS-IC-1, Saturn MS-II-1-J-2T-250K, UA1207.

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