Image:H-1 rocket engine.jpg
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The H-1 rocket engine stands 8.8 feet (268 cm) high and 4.9 feet (149 cm) wide. It was used for the Saturn I and Saturn IB rocket systems.
  | Vehicle Effectivity | |
---|---|---|
SA-201 through SA-205 | SA-206 and subsequent | |
Thrust (sea level) | 200,000 lb (890 kN) | 205,000 lb (912 kN) |
Thrust duration | 155 sec | 155 sec |
Specific impulse (lb-sec/lb) | 260.5 min | 261.0 min |
Engine weight dry (inboard) | 1,830 lb (830 kg) | 2,200 lb (998 kg) |
Engine weight dry (outboard) | 2,100 lb (953 kg) | 2,100 lb (953 kg) |
Engine weight burnout | 2,200 lb (998 kg) | 2,200 lb (998 kg) |
Exit-to-throat area ratio | 8:1 | 8:1 |
Propellants | LOX & RP-1 | LOX & RP-1 |
Mixture ratio | 2.23±2% | 2.23±2% |
- Contractor: NAA/Rocketdyne
- Vehicle application: Saturn IB/S-IB stage (eight engines)
[edit] See also
[edit] Provenance
Image downloaded from NASA Marshall Spaceflight Center Image (MIX) Exchange server:
http://mix.msfc.nasa.gov/ABSTRACTS/MSFC-9801768.html
This file is in the public domain because it was created by NASA. NASA copyright policy states that "NASA material is not protected by copyright unless noted". (NASA copyright policy page or JPL Image Use Policy)
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Date/Time | Dimensions | User | Comment | |
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current | 02:57, 9 July 2004 | 439×623 (40 KB) | Ke4roh (Talk | contribs) | (crop to just the engine) |
01:27, 10 June 2004 | 640×480 (95 KB) | Reubenbarton (Talk | contribs) | (H-1 Saturn I and Saturn IB rocket engine) |
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