 | Saturn MLV 5-3
Credit - © Mark Wade
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Orbital launch vehicle. Year: 1967. 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. Manufacturer: Von Braun. LEO Payload: 171,990 kg (379,170 lb). to: 185 km Orbit. at: 28.00 degrees. Payload: 63,160 kg (139,240 lb). to a: Translunar trajectory. Liftoff Thrust: 69,317.100 kN (15,583,104 lbf). Total Mass: 4,699,860 kg (10,361,410 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 89.00 m (291.00 ft). Flyaway Unit Cost $: 97.440 million. in: 1985 unit dollars.
Stage Data - Saturn MLV-V-4(S)-B - Stage Number: 0. 4 x Stage: Titan UA1207 . Gross Mass: 319,330 kg (704,000 lb). Empty Mass: 51,230 kg (112,940 lb). Thrust (vac): 7,116.999 kN (1,599,965 lbf). Isp: 272 sec. Burn time: 120 sec. Isp(sl): 245 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 34.14 m (112.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1207.
- Stage Number: 1. 1 x Stage: Saturn MS-IC-1. Gross Mass: 2,694,703 kg (5,940,803 lb). Empty Mass: 169,719 kg (374,166 lb). Thrust (vac): 45,948.754 kN (10,329,691 lbf). Isp: 310 sec. Burn time: 158 sec. Isp(sl): 270 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 48.15 m (157.97 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1A. Status: Study 1967. Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse.
- Stage Number: 2. 1 x Stage: Saturn MS-II-1-J-2T-250K. Gross Mass: 521,447 kg (1,149,593 lb). Empty Mass: 49,877 kg (109,959 lb). Thrust (vac): 5,558.310 kN (1,249,558 lbf). Isp: 441 sec. Burn time: 348 sec. Isp(sl): 290 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 25.88 m (84.90 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2T-250K. Status: Study 1967. Basic Saturn II with 41 inch stretch of hydrogen tank, uprated J-2T 250k engines with 25% improvement in thrust and 16 second increase in specific impulse.
Bibliography and Further Reading - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. Accessed at: http://www.webcreations.com/ptm.
- Saturn V Improvement Study, Final report, NASA Contract NAS8-11359.
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