Status: Study 1965. Payload: 22,000 kg (48,000 lb). Thrust: 7,295.10 kN (1,640,004 lbf). Gross mass: 610,110 kg (1,345,060 lb). Height: 62.00 m (203.00 ft). Diameter: 6.61 m (21.68 ft). Apogee: 185 km (114 mi).

LEO Payload: 22,000 kg (48,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 5,590 kg (12,320 lb) to a translunar trajectory. Flyaway Unit Cost 1985$: 63.800 million.

Stage Data - Saturn IB-CE

• 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 Saturn IVB (S-IB). Gross Mass: 118,800 kg (261,900 lb). Empty Mass: 12,900 kg (28,400 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 475 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: Out of Production. Comments: Saturn IB version of S-IVB stage. Due to lower payload, 300 kg saving in structure compared to Saturn V version. Due to deletion of restart requirement, 700 kg saving in propulsion system (primarily reduction in helium for restart).

• 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.