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Saturn A-2
| Field | Value | ||
|---|---|---|---|
| name | Saturn A-2 | ||
| country-origin | United States | ||
| function | Uncrewed launch vehicle | ||
| manufacturer | Von Braun | ||
| height | 62 m | ||
| alt-height | 203.00 ft | ||
| diameter | 6.52 m | ||
| alt-diameter | 21.39 ft | ||
| mass | 524,484 kg | ||
| stages | 3 (all used on various vehicles, now retired) | ||
| status | Never flown | ||
| sites | N/A | ||
| stage1name | S-IB | ||
| stage1engines | 8 × Rocketdyne H-1 | ||
| stage1thrust | 1,600,000 lbf | ||
| stage1time | 150 seconds | ||
| stage1fuel | RP-1/LOX | ||
| stage2name | Jupiter Cluster | ||
| stage2engines | 4 x Rocketdyne LR79 | ||
| stage2thrust | 3,034.285 kN | ||
| stage2time | 172 seconds | ||
| stage2fuel | RP-1/LOX | ||
| stage3name | Centaur C | ||
| stage3engines | 2 RL-10A-1 | ||
| stage3thrust | 133 kN | ||
| stage3time | 430 seconds | ||
| stage3fuel | LH2 | ||
| image | [[File:Saturn C, 1959.jpg | 100px]] | LEO-payload=10,000 kg |
|country-origin = United States |alt-height = 203.00 ft |alt-diameter = 21.39 ft Studied with the Saturn A-1 in 1959, the Saturn A-2 was deemed more powerful than the Saturn I rocket, consisting of a S-IB first stage, which actually flew on the Saturn IB, a second stage which contains four S-3 engines that flew on the Jupiter IRBM and a Centaur high-energy liquid-fueled third stage.
References
- Koelle, Heinz Hermann, Handbook of Astronautical Engineering, McGraw-Hill, New York, 1961.
- Bilstein, Roger E, Stages to Saturn, US Government Printing Office, 1980. .
References
- Bilstein, Roger E.. (1996). "Stages to Saturn: a technological history of the Apollo/Saturn launch vehicles". National Aeronautics and Space Administration, NASA History Office : For sale by the U.S. G.P.O., Supt. of Docs.
- "Saturn A-2".
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