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Saturn IB-A

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Saturn IB-A Credit: © Mark Wade

Status: Study 1965. Payload: 18,600 kg (41,000 lb). Thrust: 8,006.60 kN (1,799,955 lbf). Gross mass: 605,980 kg (1,335,950 lb). Height: 62.00 m (203.00 ft). Diameter: 6.61 m (21.68 ft). Apogee: 185 km (114 mi).

LEO Payload: 18,600 kg (41,000 lb) to a 185 km orbit at 28.00 degrees. Flyaway Unit Cost 1985$: 20.300 million.

Stage Data - Saturn IB-A

• Stage 1. 1 x Saturn S-IB-A. Gross Mass: 448,600 kg (988,900 lb). Empty Mass: 41,600 kg (91,700 lb). Thrust (vac): 9,045.600 kN (2,033,532 lbf). Isp: 296 sec. Burn time: 128 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-1c. Status: Study 1965. Comments: Douglas Studies, 1965: S-1B with 225 k lbf H-1's.

• Stage 2. 1 x Saturn IVB-A. Gross Mass: 118,800 kg (261,900 lb). Empty Mass: 12,900 kg (28,400 lb). Thrust (vac): 956.100 kN (214,940 lbf). Isp: 421 sec. Burn time: 450 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 17.80 m (58.30 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study 1965. Comments: Douglas Studies, 1965: S-IVB with 215k lbf J-1 (actual final model had 230k J-1).

• Stage 3. 1 x Centaur D/E. Gross Mass: 16,258 kg (35,842 lb). Empty Mass: 2,631 kg (5,800 lb). Thrust (vac): 131.222 kN (29,500 lbf). Isp: 444 sec. Burn time: 470 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.60 m (31.40 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-3. Status: Out of Production.