Saturn V 156" SRB - Saturn V 156 inch strapons Credit: © Mark Wade. 6,714 bytes. 154 x 1002 pixels.

Boeing study, 1967. 4 156 inch solid propellant boosters; Saturn IC stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; S-II standard length with 5 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine.

LEO Payload: 223,500 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 85,600 kg. to a: Translunar trajectory. Liftoff Thrust: 7,376,460 kgf. Total Mass: 6,342,540 kg. Core Diameter: 10.1 m. Total Length: 123.0 m. Flyaway Unit Cost $: 174.00 million. in 1985 unit dollars.

• Stage Number: 0. 4 x UA 156 inch Gross Mass: 544,311 kg. Empty Mass: 37,195 kg. Thrust (vac): 910,044 kgf. Isp: 263 sec. Burn time: 157 sec. Isp(sl): 238 sec. Diameter: 4.0 m. Span: 4.0 m. Length: 34.0 m. Propellants: Solid No Engines: 1. UA-156

• Stage Number: 1. 1 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. 1 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

• Stage Number: 3. 1 x Saturn MS-IVB-1A Gross Mass: 179,200 kg. Empty Mass: 20,400 kg. Thrust (vac): 105,200 kgf. Isp: 421 sec. Burn time: 625 sec. Isp(sl): 200 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 22.8 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