Status: Study 1965. Payload: 43,034 kg (94,873 lb). Thrust: 32,027.10 kN (7,199,979 lbf). Gross mass: 1,818,800 kg (4,009,700 lb). Height: 58.00 m (190.00 ft). Diameter: 6.61 m (21.68 ft). Apogee: 185 km (114 mi).

LEO Payload: 43,034 kg (94,873 lb) to a 185 km orbit at 28.00 degrees. Flyaway Unit Cost 1985$: 111.650 million.

Stage Data - Saturn INT-05A

• Stage 1. 1 x 260 inch solid FL. Gross Mass: 1,648,355 kg (3,634,000 lb). Empty Mass: 156,126 kg (344,198 lb). Thrust (vac): 35,391.395 kN (7,956,302 lbf). Isp: 263 sec. Burn time: 114 sec. Isp(sl): 238 sec. Diameter: 6.60 m (21.60 ft). Span: 6.60 m (21.60 ft). Length: 30.48 m (99.99 ft). Propellants: Solid. No Engines: 1. Engine: AJ-260X. Status: Study 1968. Comments: 260 inch solid booster - full length. These would have been the flight configuration motors, replacing the Saturn V first stage or being used as booster motors in various Uprated Saturn and Nova configurations.

• 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).