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Model: 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. Propellants: N2O4/UDMH. 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). Country: USA. No Engines: 1. Motor: PF N204/UDMH-2912k. Status: Study 1967. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, HY-140 Hull Model: Saturn LCB-Alumizine-250. Gross Mass: 1,270,100 kg (2,800,000 lb). Empty Mass: 95,300 kg (210,100 lb). Thrust (vac): 18,873.800 kN (4,242,999 lbf). Isp: 280 sec. Burn time: 168 sec. Propellants: N2O4/Alumizine. Isp(sl): 260 sec. Diameter: 6.61 m (21.68 ft). Span: 9.26 m (30.38 ft). Length: 31.40 m (103.00 ft). Country: USA. No Engines: 1. Motor: PF N204/Alumizine-1925k. Status: Study 1967. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/Alumizine Propellant engine, Ni-250 Hull Model: Saturn LCB-Alumizine-140. Gross Mass: 1,542,200 kg (3,399,900 lb). Empty Mass: 154,200 kg (339,900 lb). Thrust (vac): 22,563.100 kN (5,072,387 lbf). Isp: 280 sec. Burn time: 166 sec. Propellants: N2O4/Alumizine. Isp(sl): 260 sec. Diameter: 6.61 m (21.68 ft). Span: 9.26 m (30.38 ft). Length: 36.28 m (119.02 ft). Country: USA. No Engines: 1. Motor: PF N204/Alumizine-2300k. Status: Study 1967. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/Alumizine Propellant engine, HY-140 Hull Model: Saturn LCB-Storable-250. Gross Mass: 1,451,500 kg (3,200,000 lb). Empty Mass: 108,900 kg (240,000 lb). Thrust (vac): 21,232.300 kN (4,773,211 lbf). Isp: 267 sec. Burn time: 163 sec. Propellants: N2O4/UDMH. Isp(sl): 245 sec. Diameter: 6.61 m (21.68 ft). Span: 9.26 m (30.38 ft). Length: 40.70 m (133.50 ft). Country: USA. No Engines: 1. Motor: PF N204/UDMH-2165k. Status: Study 1967. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, Ni-250 Hull Model: Saturn LCB-Lox/RP-1. Gross Mass: 1,360,800 kg (3,000,000 lb). Empty Mass: 108,900 kg (240,000 lb). Thrust (vac): 20,306.600 kN (4,565,105 lbf). Isp: 275 sec. Burn time: 163 sec. Propellants: Lox/Kerosene. Isp(sl): 253 sec. Diameter: 6.61 m (21.68 ft). Span: 9.26 m (30.38 ft). Length: 48.78 m (160.03 ft). Country: USA. No Engines: 1. Motor: PF RP-1. Status: Study 1967. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed Lox/RFP-1 engine Model: Saturn PFL. Gross Mass: 2,057,400 kg (4,535,700 lb). Empty Mass: 205,400 kg (452,800 lb). Thrust (vac): 28,553.000 kN (6,418,969 lbf). Isp: 267 sec. Burn time: 167 sec. Propellants: N2O4/UDMH. Isp(sl): 245 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 33.57 m (110.13 ft). Country: USA. No Engines: 1. Motor: PF N204/UDMH-2912k. Status: Study 1969. NASA, Saturn Alternative Booster Studies, 1969 (trade study of 120, 156, 260 inch solid, and Storable liquid boosters for S-IVB. Reached opposite conclusion from Boeing study, that Pressure Fed Liquid Booster would be 6.5% more expensive than solid). Pre Used on Launch Vehicles: Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2008 except where otherwise noted. |