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Saturn MLV-V-3

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Saurn MLV 5-3 Saturn MLV 5-3 Credit: © Mark Wade

Status: Study 1965. Payload: 160,400 kg (353,600 lb). Thrust: 40,019.90 kN (8,996,831 lbf). Gross mass: 3,664,570 kg (8,078,990 lb). Height: 121.00 m (396.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

LEO Payload: 160,400 kg (353,600 lb) to a 185 km orbit at 28.00 degrees. Payload: 65,800 kg (145,000 lb) to a translunar trajectory.

Stage Data - Saturn MLV-V-3

• 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-2. Gross Mass: 600,788 kg (1,324,510 lb). Empty Mass: 59,844 kg (131,933 lb). Thrust (vac): 7,003.477 kN (1,574,444 lbf). Isp: 451 sec. Burn time: 324 sec. Isp(sl): 280 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: 5. Engine: HG-3. Status: Study NASA 1966. Comments: Basic Saturn II with 187 inch stretch of propellant tanks and high chamber pressure SSME-type engines with 65% increase in thrust and 26 second improvement in specific impulse.

• Stage 3. 1 x Saturn MS-IVB-2. Gross Mass: 176,600 kg (389,300 lb). Empty Mass: 17,800 kg (39,200 lb). Thrust (vac): 1,401.300 kN (315,025 lbf). Isp: 447 sec. Burn time: 489 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 23.12 m (75.85 ft). Propellants: Lox/LH2. No Engines: 1. Engine: HG-3. Status: Study 1965. Comments: Douglas Studies, 1965: S-IVB with 315 k high pressure 3000 psia engine, 350,000 pounds propellant.