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 Steel Hull.

LEO Payload: 39,000 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 2,136,460 kgf. Total Mass: 1,707,800 kg. Core Diameter: 6.6 m. Total Length: 65.0 m.

• Stage Number: 1. 1 x Saturn LCB-Alumizine-140 Gross Mass: 1,542,200 kg. Empty Mass: 154,200 kg. Thrust (vac): 2,300,800 kgf. Isp: 280 sec. Burn time: 166 sec. Isp(sl): 260 sec. Diameter: 6.6 m. Span: 9.3 m. Length: 36.3 m. Propellants: N2O4/Alumizine No Engines: 1. PF N204/Alumizine-2300k

• Stage Number: 2. 1 x Saturn IVB (S-IB) Gross Mass: 118,800 kg. Empty Mass: 12,900 kg. Thrust (vac): 105,200 kgf. Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 17.8 m. Propellants: Lox/LH2 No Engines: 1. J-2

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