Saturn S-IC-TLB

American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb payload to LEO): S-IC Technology Liquid Booster: 260 inch liquid booster with 2 x F-1 engines, recoverable/reusable

LEO Payload: 39,000 kg (85,000 lb) to a 185 km orbit at 28.00 degrees.

Stage Data - Saturn S-IC-TLB

• Stage 1. 1 x Saturn S-IC-TLB. Gross Mass: 952,500 kg (2,099,900 lb). Empty Mass: 68,000 kg (149,000 lb). Thrust (vac): 15,532.700 kN (3,491,890 lbf). Isp: 304 sec. Burn time: 167 sec. Isp(sl): 265 sec. Diameter: 6.61 m (21.68 ft). Span: 10.58 m (34.71 ft). Length: 36.36 m (119.29 ft). Propellants: Lox/Kerosene. No Engines: 2. Engine: F-1. Status: Study 1967. Comments: Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb payload to LEO): S-IC Technology Liquid Booster: 260 inch liquid booster with 2 x F-1 engines, recoverable/reusable.

• 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).