Boeing study, 1968. Four core vehicles from Saturn V-25(S) study lashed together to obtain million-pound payload using existing hardware. First stage consisted of 4 Saturn IC's stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; second stage 4 Saturn II standard length stages with 5 J-2 engines

LEO Payload: 527,600 kg. to: 486 km Orbit. at: 28.0 degrees. Liftoff Thrust: 16,329,230 kgf. Total Mass: 15,504,720 kg. Core Diameter: 10.1 m. Total Length: 95.0 m.

• Stage Number: 1. 4 x Saturn MS-IC-25(S) Gross Mass: 3,223,800 kg. Empty Mass: 211,900 kg. Thrust (vac): 4,683,100 kgf. Isp: 304 sec. Burn time: 192 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 54.7 m. Propellants: Lox/Kerosene No Engines: 5. F-1A

• Stage Number: 2. 4 x Saturn MS-II-4(S)B Gross Mass: 494,100 kg. Empty Mass: 42,300 kg. Thrust (vac): 527,100 kgf. Isp: 421 sec. Burn time: 355 sec. Isp(sl): 200 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 24.8 m. Propellants: Lox/LH2 No Engines: 5. 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