This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
 |
S-1C details
Credit: © Mark Wade. 40,371 bytes. 510 x 391 pixels. |
Family: Saturn V. Country: USA. Status: Study 1967.
Saturn variant consisting of S-IC first stage and S-IVB second stage. Consideration was given to deleting one or more of the F-1 engines in the first stage.
| Liftoff Mass - kg | S-IC - No.
F-1 Motors | Payload - kg - 4.68 G limit | Payload - kg - 6.0 G limit |
| 1,107,000 | 2 | 36,000 | 27,000 |
| 1,655,000 | 3 | 78,000 | 47,000 |
| 2,209,000 | 4 | 132,000 | 63,000 |
| 2,299,000 | 5 | 133,000 | 72,000 |
SpecificationsLEO Payload: 60,000 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 3,440,310 kgf. Total Mass: 2,478,120 kg. Core Diameter: 10.1 m. Total Length: 72.0 m. Flyaway Unit Cost $: 391.50 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: 3. 1 x Saturn IVB (S-V) Gross Mass: 119,900 kg. Empty Mass: 13,300 kg. Thrust (vac): 105,200 kgf. Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.6 m. Span: 6.6 m. Length: 17.8 m. Propellants: Lox/LH2 No Engines: 1. 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.
Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .