This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
 |
| Saturn IB-INT-27 - Credit: © Mark Wade. 1,472 bytes. 74 x 386 pixels. |
|
Family: Saturn I. Country: USA. Status: Study 1965.
UA study, 1965. Saturn variant using various combinations of 156 inch rocket motors as first and second stages, with S-IVB upper stage.
| | | | |
| Number of Strapon Motors | 4 | 3 | 2 | 2 |
| Number of Core Stage Motors | 1 | 1 | 1 | 0 |
| Payload with 4 Segment Motors | 79,000 | 68,000 | 54,000 | 36,000 |
| Payload with 3 Segment Motors | 70,000 | 59,000 | 45,000 | 29,000 |
| Payload with 2 Segment Motors | 57,000 | 47,000 | 36,000 | 24,000 |
| Payload with 1 Segment Motors | 45,000 | 39,000 | 27,000 | 18,000 |
SpecificationsLEO Payload: 40,000 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 6,711,060 kgf. Total Mass: 3,068,800 kg. Core Diameter: 6.6 m. Total Length: 67.0 m. Flyaway Unit Cost $: 200.00 million. in 1985 unit dollars.
- Stage Number: 1. 4 x UA 156 inch 4 Segment Gross Mass: 725,500 kg. Empty Mass: 49,250 kg. Thrust (vac): 1,854,000 kgf. Isp: 263 sec. Burn time: 94 sec. Isp(sl): 238 sec. Diameter: 4.0 m. Span: 4.0 m. Length: 38.0 m. Propellants: Solid No Engines: 1. UA-156
- Stage Number: 2. 1 x Saturn IVB (S-IB) Gross Mass: 118,800 kg. Empty Mass: 12,900 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
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 .