Saturn LCB-Storable-140

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): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, HY-140 Steel Hull.

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

Stage Data - Saturn LCB-Storable-140

• Stage 1. 1 x Saturn LCB-Storable-140. Gross Mass: 1,995,800 kg (4,399,900 lb). Empty Mass: 199,600 kg (440,000 lb). Thrust (vac): 28,553.000 kN (6,418,969 lbf). Isp: 267 sec. Burn time: 162 sec. Isp(sl): 245 sec. Diameter: 6.61 m (21.68 ft). Span: 9.26 m (30.38 ft). Length: 57.16 m (187.53 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: PF N204/UDMH-2912k. 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): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, HY-140 Hull.

• 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).