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Saturn V Skylab
Credit: NASA. 38,005 bytes. 631 x 477 pixels. |
Family: Saturn V. Country: USA. Status: Study 1967.
Saturn variant consisting of S-IC first stage and S-II second stage. This essentially flew once to launch Skylab in 1972, although the IU was located atop the Skylab space station (converted S-IVB stage) rather than atop the S-II as in the INT-21 design.
| 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 |
 | S-1C details Credit: © Mark Wade. 40,371 bytes. 510 x 391 pixels. |
SpecificationsLEO Payload: 115,900 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 3,440,310 kgf. Total Mass: 2,916,080 kg. Core Diameter: 10.1 m. Total Length: 80.0 m. Flyaway Unit Cost $: 681.50 million. in 1985 unit dollars.
- Stage Number: 1. 1 x Saturn IC Gross Mass: 2,286,217 kg. Empty Mass: 135,218 kg. Thrust (vac): 3,946,624 kgf. Isp: 304 sec. Burn time: 161 sec. Isp(sl): 265 sec. Diameter: 10.1 m. Span: 19.0 m. Length: 42.1 m. Propellants: Lox/Kerosene No Engines: 5. F-1
- Stage Number: 2. 1 x Saturn II Gross Mass: 490,778 kg. Empty Mass: 39,048 kg. Thrust (vac): 526,764 kgf. Isp: 421 sec. Burn time: 390 sec. Isp(sl): 200 sec. Diameter: 10.1 m. Span: 10.1 m. Length: 24.8 m. Propellants: Lox/LH2 No Engines: 5. J-2
Bibliography:- 228 - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. HTML when accessed: http://www.webcreations.com/ptm
- 233 - Alexander, George, Aviation Week and Space Technology, "Manned Flight Planning Gap Delays Saturn Development", 1966-08-08, page 60.
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Last update 12 March 2001.
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