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Saturn A-2

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Saturn A-2 Credit: © Mark Wade

Status: Study 1959. Payload: 10,000 kg (22,000 lb). Thrust: 7,295.10 kN (1,640,004 lbf). Gross mass: 702,960 kg (1,549,760 lb). Height: 62.00 m (203.00 ft). Diameter: 6.52 m (21.39 ft). Apogee: 185 km (114 mi).

LEO Payload: 10,000 kg (22,000 lb) to a 185 km orbit at 38.00 degrees. Payload: 2,000 kg (4,400 lb) to a translunar trajectory. Flyaway Unit Cost 1985$: 63.800 million.

Stage Data - Saturn A-2

• Stage 1. 1 x Saturn IB. Gross Mass: 448,648 kg (989,099 lb). Empty Mass: 41,594 kg (91,699 lb). Thrust (vac): 8,241.763 kN (1,852,822 lbf). Isp: 296 sec. Burn time: 155 sec. Isp(sl): 262 sec. Diameter: 6.52 m (21.39 ft). Span: 6.52 m (21.39 ft). Length: 24.48 m (80.31 ft). Propellants: Lox/Kerosene. No Engines: 8. Engine: H-1b. Status: Out of Production.

• Stage 2. 1 x Jupiter Cluster. Gross Mass: 226,716 kg (499,823 lb). Empty Mass: 27,205 kg (59,976 lb). Thrust (vac): 3,034.285 kN (682,134 lbf). Isp: 282 sec. Burn time: 172 sec. Isp(sl): 248 sec. Diameter: 5.34 m (17.51 ft). Span: 5.34 m (17.51 ft). Length: 18.28 m (59.97 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: S-3. Status: Study 1959. Comments: Masses estimated (cluster of four Jupiter IRBM stages).

• Stage 3. 1 x Centaur C. Gross Mass: 15,600 kg (34,300 lb). Empty Mass: 1,996 kg (4,400 lb). Thrust (vac): 133.448 kN (30,000 lbf). Isp: 425 sec. Burn time: 430 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.14 m (29.98 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-1. Status: Out of Production.

Photo Gallery

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Saturn A-1 to C-5 Credit: © Mark Wade

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