|
Orbital launch vehicle. Year: 1968. Family: Saturn V. Country: USA. Status: Study 1968. Boeing study, 1968. 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. This vehicle would place Nerva nuclear third stage into low earth orbit, where five such stages would be assembled together with the spacecraft for a manned Mars expedition. Manufacturer: Von Braun. LEO Payload: 248,663 kg (548,208 lb). to: 486 km Orbit. at: 28.00 degrees. Payload: 160,000 kg (350,000 lb). to a: Translunar trajectory. Liftoff Thrust: 72,338.400 kN (16,262,319 lbf). Total Mass: 6,439,300 kg (14,196,200 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 153.00 m (501.00 ft). Flyaway Unit Cost $: 174.000 million. in: 1985 unit dollars.
Stage Data - Saturn V-25(S)U - Stage Number: 0. 4 x Stage: UA 156 inch. Gross Mass: 544,311 kg (1,200,000 lb). Empty Mass: 37,195 kg (82,000 lb). Thrust (vac): 8,924.482 kN (2,006,303 lbf). Isp: 263 sec. Burn time: 157 sec. Isp(sl): 238 sec. Diameter: 3.96 m (12.99 ft). Span: 3.96 m (12.99 ft). Length: 34.00 m (111.00 ft). Propellants: Solid. No Engines: 1. Engine: UA-156. Status: Study 1968.
- Stage Number: 1. 1 x Stage: Saturn MS-IC-25(S). Gross Mass: 3,223,800 kg (7,107,200 lb). Empty Mass: 211,900 kg (467,100 lb). Thrust (vac): 45,925.500 kN (10,324,463 lbf). Isp: 304 sec. Burn time: 192 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 54.70 m (179.40 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1A. Status: Study 1968. S-IC with 41.5 foot stretch, 6,640,0000 lbs propellant, uprated F-1 engines.
- Stage Number: 2. 1 x Stage: Saturn MS-II-4(S)B. Gross Mass: 494,100 kg (1,089,300 lb). Empty Mass: 42,300 kg (93,200 lb). Thrust (vac): 5,169.000 kN (1,162,037 lbf). Isp: 421 sec. Burn time: 355 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 24.84 m (81.49 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2. Status: Study 1968. Standard S-II but with structural strength increased from 86% to 502% depending on station, resulting in 8.6% increase in empty weight.
- Stage Number: 3. 1 x Stage: Saturn S-N V-25(S)U. Gross Mass: 245,760 kg (541,800 lb). Empty Mass: 71,190 kg (156,940 lb). Thrust (vac): 889.325 kN (199,928 lbf). Isp: 825 sec. Burn time: 1,500 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 48.17 m (158.03 ft). Propellants: Nuclear/LH2. No Engines: 1. Engine: Nerva. Status: Study 1968. Version of Nerva studied by Boeing for manned Mars expedition.
Bibliography and Further Reading - 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.
|