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Saturn MLV-V-1A

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Status: Study 1965. Payload: 145,000 kg (319,000 lb). Thrust: 40,485.10 kN (9,101,413 lbf). Gross mass: 3,648,700 kg (8,044,000 lb). Height: 121.00 m (396.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

LEO Payload: 145,000 kg (319,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 54,400 kg (119,900 lb) to a translunar trajectory.

Stage Data - Saturn MLV-V-1A

• Stage 1. 1 x Saturn MS-IC-1A. Gross Mass: 2,694,700 kg (5,940,700 lb). Empty Mass: 160,600 kg (354,000 lb). Thrust (vac): 46,443.300 kN (10,440,869 lbf). Isp: 304 sec. Burn time: 160 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 48.16 m (158.00 ft). Propellants: Lox/Kerosene. No Engines: 6. Engine: F-1. Status: Study 1966. Comments: Basic Saturn IC stretched 240 inches with 6 F-1 engines.

• Stage 2. 1 x Saturn MS-II-1A. Gross Mass: 600,800 kg (1,324,500 lb). Empty Mass: 60,000 kg (132,000 lb). Thrust (vac): 6,380.941 kN (1,434,493 lbf). Isp: 421 sec. Burn time: 345 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 29.59 m (97.08 ft). Propellants: Lox/LH2. No Engines: 7. Engine: J-2. Status: Study NASA 1966. Comments: Basic Saturn II with 187 inch stretch of propellant tanks, 1.2 million pound propellant capacity, and 7 J-2 engines.

• Stage 3. 1 x Saturn MS-IVB-1A. Gross Mass: 179,200 kg (395,000 lb). Empty Mass: 20,400 kg (44,900 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 625 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 22.82 m (74.86 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study Boeing 1967. Comments: S-IVB with 16.5 foot stretch, 350,000 pounds propellant, standard J-2 engine.