Saturn MLV 5-3
Credit: © Mark Wade
American orbital launch vehicle. Boeing study, 1967. Configuration of improved Saturn 5 with Titan UA1207 120 inch solid rocket boosters. Saturn IC stretched 336 inches with 6.0 million pounds propellant and 5 F-1 engines; Saturn II and Saturn IVB stages strengthened but not stretched. Empty mass of stages increased by 13.9% (S-IC), 8.6% (S-II) and 11.8% (S-IVB). Studied again by Boeing in 1967 as Saturn V-4(S)B.
LEO Payload: 171,990 kg (379,170 lb) to a 185 km orbit at 28.00 degrees. Payload: 63,160 kg (139,240 lb) to a translunar trajectory in 1985 dollars. Flyaway Unit Cost $: 97.440 million.
Stage Data - Saturn MLV-V-4(S)-B
- Stage 0. 4 x Titan UA1207. Gross Mass: 319,330 kg (704,000 lb). Empty Mass: 51,230 kg (112,940 lb). Thrust (vac): 7,116.999 kN (1,599,965 lbf). Isp: 272 sec. Burn time: 120 sec. Isp(sl): 245 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 34.14 m (112.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1207. Status: In Production.
- Stage 1. 1 x Saturn MS-IC-1. Gross Mass: 2,694,703 kg (5,940,803 lb). Empty Mass: 169,719 kg (374,166 lb). Thrust (vac): 45,948.754 kN (10,329,691 lbf). Isp: 310 sec. Burn time: 158 sec. Isp(sl): 270 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 48.15 m (157.97 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1A. Status: Study NASA 1966. Comments: Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse.
- Stage 2. 1 x Saturn MS-II-1-J-2T-250K. Gross Mass: 521,447 kg (1,149,593 lb). Empty Mass: 49,877 kg (109,959 lb). Thrust (vac): 5,558.310 kN (1,249,558 lbf). Isp: 441 sec. Burn time: 348 sec. Isp(sl): 290 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 25.88 m (84.90 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2T-250K. Status: Study NASA 1966. Comments: Basic Saturn II with 41 inch stretch of hydrogen tank, uprated J-2T 250k engines with 25% improvement in thrust and 16 second increase in specific impulse.
Status: Study 1967.
More... - Chronology...
Gross mass: 4,699,860 kg (10,361,410 lb).
Payload: 171,990 kg (379,170 lb).
Height: 89.00 m (291.00 ft).
Diameter: 10.06 m (33.00 ft).
Thrust: 69,317.10 kN (15,583,104 lbf).
Apogee: 185 km (114 mi).
F-1 Rocketdyne Lox/Kerosene rocket engine. 7740.5 kN. Isp=304s. Largest liquid rocket engine ever developed and flown. Severe combustion stability problems were solved during development and it never failed in flight. First flight 1967. More...
F-1A Rocketdyne Lox/Kerosene rocket engine. 9189.6 kN. Study 1968. Designed for booster applications. Gas generator, pump-fed. Isp=310s. More...
J-2T-250K Rocketdyne lox/lh2 rocket engine. 1111.6 kN. Study 1967. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2. Isp=441s. More...
UA1207 CSD solid rocket engine. 7116.9 kN. Isp=272s. First flight 1989. More...
Saturn The Saturn launch vehicle was the penultimate expression of the Peenemuende Rocket Team's designs for manned exploration of the moon and Mars. Numerous designs and variants were studied, but in the end only three models - the Saturn I, IB, and V - were built in the 1960's, and then only used to support NASA's Apollo moon landing program. More...
Saturn V America's booster for the Apollo manned lunar landing. The design was frozen before a landing mode was selected; the Saturn V could be used for either Earth-Orbit-Rendezvous or Lunar-Orbit-Rendezvous methods. The vehicle ended up with the same payload capability as the 'too large' Nova. The basic diameter was dictated by the ceiling height at the Michoud factory selected for first stage manufacture. Despite the study of innumerable variants, production was ended after only 12 were built and America spent the next fifty years in a pointless slow-motion withdrawal from manned space exploration. More...
Associated Manufacturers and Agencies
Von Braun American manufacturer of rockets and spacecraft. Von Braun, USA. More...
Saturn MS-IC-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 2,694,703/169,719 kg. Thrust 45,948.75 kN. Vacuum specific impulse 310 seconds. Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse. More...
Saturn MS-II-1-J-2T-250K Lox/LH2 propellant rocket stage. Loaded/empty mass 521,447/49,877 kg. Thrust 5,558.31 kN. Vacuum specific impulse 441 seconds. Basic Saturn II with 41 inch stretch of hydrogen tank, uprated J-2T 250k engines with 25% improvement in thrust and 16 second increase in specific impulse. More...
Titan UA1207 Solid propellant rocket stage. Loaded/empty mass 319,330/51,230 kg. Thrust 7,117.00 kN. Vacuum specific impulse 272 seconds. More...
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