Saturn MLV-V-1/J-2T/250K

American orbital launch vehicle. 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.

at: 28.00 degrees.

Stage Data - Saturn MLV-V-1/J-2T/250K

• Stage 1. 1 x 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 NASA 1966. Comments: Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse.

• Stage 2. 1 x 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 NASA 1966. Comments: 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.