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Saturn MLV-V-4(S)-A
Part of Saturn V Family
Saturn V 120
Saturn V 120" SRB
Saturn V 120 inch strapons
Credit: © Mark Wade
American orbital launch vehicle. MSFC study, 1965. 4 Titan UA1205 solid rocket boosters; Saturn IC stretched 337 inches with 6.0 million pounds propellant and 5 F-1 engines; S-II with 970,000 pounds propellant and 5 J-2 engines; S-IVB strengthened but with standard 230,000 lbs propellant, 1 J-2 engine.

Status: Study 1965. Payload: 160,880 kg (354,670 lb). Thrust: 54,920.00 kN (12,346,500 lbf). Gross mass: 4,615,440 kg (10,175,300 lb). Height: 113.00 m (370.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

LEO Payload: 160,880 kg (354,670 lb) to a 185 km orbit at 28.00 degrees. Payload: 57,500 kg (126,700 lb) to a translunar trajectory. Flyaway Unit Cost 1985$: 71.920 million.

Stage Data - Saturn MLV-V-4(S)-A

  • Stage 0. 4 x Titan UA1205. Gross Mass: 226,233 kg (498,758 lb). Empty Mass: 33,798 kg (74,511 lb). Thrust (vac): 5,849.411 kN (1,315,000 lbf). Isp: 263 sec. Burn time: 115 sec. Isp(sl): 238 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 25.91 m (85.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1205. Status: Out of Production.
  • Stage 1. 1 x Saturn MS-IC-4(S)B. Gross Mass: 2,875,500 kg (6,339,300 lb). Empty Mass: 154,000 kg (339,000 lb). Thrust (vac): 38,717.600 kN (8,704,063 lbf). Isp: 304 sec. Burn time: 206 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 50.58 m (165.94 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Study Boeing 1967. Comments: S-IC with 336 inch stretch, 6,000,0000 lbs propellant, structural strength increased from 56% to 65% depending on station, resulting in 13.9% increase in empty weight.
  • Stage 2. 1 x Saturn MS-II-1. Gross Mass: 521,447 kg (1,149,593 lb). Empty Mass: 49,877 kg (109,959 lb). Thrust (vac): 5,165.790 kN (1,161,316 lbf). Isp: 425 sec. Burn time: 361 sec. Isp(sl): 306 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-2. Status: Study NASA 1966. Comments: Basic Saturn II with 41 inch stretch of hydrogen tank.
  • Stage 3. 1 x Saturn MS-IVB-1. Gross Mass: 120,500 kg (265,600 lb). Empty Mass: 13,900 kg (30,600 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 18.08 m (59.31 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study 1965. Comments: Marshall studies, 1965: S-IVB structurally strengthened to handle larger payloads, otherwise unchanged.



Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: F-1. Stages: Saturn MS-II-1, Saturn MS-IVB-1, Saturn MS-IC-4(S)B, UA1205.

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