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A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z Saturn V-ELV Part of Saturn V American orbital launch vehicle. NASA study, 1966. No-height-limitation stretched Saturn with Titan UA1207 motors for thrust augmentation.
Status: Study 1966. Payload: 200,000 kg (440,000 lb). Thrust: 59,392.70 kN (13,352,010 lbf). Gross mass: 5,172,820 kg (11,404,110 lb). Height: 124.00 m (406.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).
LEO Payload: 200,000 kg (440,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 67,000 kg (147,000 lb) to a translunar trajectory. Flyaway Unit Cost 1985$: 97.440 million.
Stage Data - Saturn V-ELV
- 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-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-1A. Gross Mass: 600,800 kg (1,324,500 lb). Empty Mass: 60,000 kg (132,000 lb). Thrust (vac): 6,380.941 kN (1,434,493 lbf). Isp: 421 sec. Burn time: 345 sec. Isp(sl): 200 sec. Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft). Length: 29.59 m (97.08 ft). Propellants: Lox/LH2. No Engines: 7. Engine: J-2. Status: Study NASA 1966. Comments: Basic Saturn II with 187 inch stretch of propellant tanks, 1.2 million pound propellant capacity, and 7 J-2 engines.
- Stage 3. 1 x Saturn MS-IVB-1A. Gross Mass: 179,200 kg (395,000 lb). Empty Mass: 20,400 kg (44,900 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 625 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 22.82 m (74.86 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study Boeing 1967. Comments: S-IVB with 16.5 foot stretch, 350,000 pounds propellant, standard J-2 engine.
Family: orbital launch vehicle. People: von Braun. Country: USA. Stages: Saturn MS-IC-4(S)B, Saturn MS-II-1A, Saturn MS-IVB-1A, UA1207. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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