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 Steel Hull.

Manufacturer: Von Braun. LEO Payload: 39,000 kg (85,000 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 17,525.800 kN (3,939,957 lbf). Total Mass: 1,435,700 kg (3,165,100 lb). Core Diameter: 6.61 m (21.68 ft). Total Length: 59.00 m (193.00 ft).

• Stage Number: 1. 1 x Stage: 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. 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). Propellants: N2O4/Alumizine. No Engines: 1. Engine: 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

• Stage Number: 2. 1 x Stage: 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. Saturn IB version of S-IVB stage. Due to lower payload 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).

• Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. Accessed at: http://www.webcreations.com/ptm.