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Orbital launch vehicle. Year: 1965. Family: Saturn V. Country: USA. Status: Study 1965. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Variant of MLV-V-1 with toroidal J-2T-250K engines replacing standard J-2 engines in upper stages. Manufacturer: Von Braun. at: 28.00 degrees. Liftoff Thrust: 40,019.900 kN (8,996,831 lbf). Total Mass: 3,216,150 kg (7,090,390 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 89.00 m (291.00 ft).
Stage Data - Saturn MLV-V-1/J-2T/250K - 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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