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Saturn 2SL/120" SRB
Saturn 2SL 120 inch strapons
Credit: © Mark Wade North American study, 1966. Saturn variant with Titan UA1205 or 1207 motors as boosters, Saturn II stage as core, and Saturn IVB upper stage. Various combinations of numbers of strap-ons, propellant loading of the two core stages, and sea-level versus altitude ignition were studied.
Status: Study 1966. Payload: 66,590 kg (146,800 lb). Thrust: 25,642.10 kN (5,764,573 lbf). Gross mass: 1,966,810 kg (4,336,070 lb). Height: 51.00 m (167.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).
Liftoff Mass - kg Strapon Motor Type Number of Strapons S-II Propellant - kg S-IVB Propellant - kg Payload - kg 1,132,000 Titan UA1204 4 215,400 80,300 21,300 1,132,000 Titan UA1204 4 215,400 78,500 23,100 1,030,400 Titan UA1207 2 254,000 80,700 27,400 1,132,400 Titan UA1207 2 349,200 79,800 35,400 1,083,000 Titan UA1205 2 431,600 77,400 40,500 1,570,500 Titan UA1205 4 440,400 74,400 51,700 1,895,200 Titan UA1207 4 446,700 75,700 66,400 1,476,200 Titan UA1205 4 446,700 No S-IVB 39,000 1,779,600 Titan UA1207 4 446,700 No S-IVB 44,000
LEO Payload: 66,590 kg (146,800 lb) to a 185 km orbit at 28.00 degrees. Flyaway Unit Cost 1985$: 387.440 million.
Stage Data - Saturn INT-18
- 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 II. Gross Mass: 490,778 kg (1,081,980 lb). Empty Mass: 39,048 kg (86,086 lb). Thrust (vac): 5,165.790 kN (1,161,316 lbf). Isp: 421 sec. Burn time: 390 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: Out of Production.
- Stage 2. 1 x Saturn IVB (S-IB). Gross Mass: 118,800 kg (261,900 lb). Empty Mass: 12,900 kg (28,400 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: 17.80 m (58.30 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Out of Production. Comments: Saturn IB version of S-IVB stage. Due to lower payload, 300 kg saving in structure compared to Saturn V version. Due to deletion of restart requirement, 700 kg saving in propulsion system (primarily reduction in helium for restart).
Family: orbital launch vehicle. People: von Braun. Country: USA. Stages: Saturn II, Saturn IVB (S-IB), UA1207. Photo Gallery Saturn MLV 2-120-7
Credit: © Mark Wade Saturn 2-120-5
Credit: © Mark Wade Saturn 2-120-4
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