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Saturn INT-21
Saturn V Skylab
Credit: NASA
Status: Study 1967. Payload: 115,900 kg (255,500 lb). Thrust: 33,737.90 kN (7,584,582 lbf). Gross mass: 2,916,080 kg (6,428,850 lb). Height: 80.00 m (262.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).
| Liftoff Mass - kg | S-IC - No. F-1 Motors | S-II - No. J-2 Motors | Payload - kg - 4.68 G limit |
| 2,209,000 | 4 | 3 | 76,000 |
| 2,209,000 | 4 | 4 | 84,000 |
| 2,209,000 | 4 | 5 | 89,000 |
| 2,762,000 | 5 | 3 | 101,000 |
| 2,762,000 | 5 | 4 | 112,000 |
| 2,762,000 | 5 | 5 | 116,000 |
LEO Payload: 115,900 kg (255,500 lb) to a 185 km orbit at 28.00 degrees. Flyaway Unit Cost 1985$: 681.500 million.
Stage Data - Saturn INT-21
- Stage 1. 1 x Saturn IC. Gross Mass: 2,286,217 kg (5,040,245 lb). Empty Mass: 135,218 kg (298,104 lb). Thrust (vac): 38,703.160 kN (8,700,816 lbf). Isp: 304 sec. Burn time: 161 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 42.06 m (137.99 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Out of Production.
- Stage 2. 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.
Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: F-1. Spacecraft: Space Station 1970. Stages: Saturn IC, Saturn II.
 | S-1C details Credit: © Mark Wade |
 | Saturn II stage Credit: © Mark Wade |
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