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.

&nbsp 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

The H-1 image came from this NASA graphic showing the specifications outlined in the table above.
The H-1 image came from this NASA graphic showing the specifications outlined in the table above.

[edit] Provenance

Image downloaded from NASA Marshall Spaceflight Center Image (MIX) Exchange server:

http://mix.msfc.nasa.gov/ABSTRACTS/MSFC-9801768.html

File history

Click on a date/time to view the file as it appeared at that time.

Date/TimeDimensionsUserComment
current02:57, 9 July 2004439×623 (40 KB)Ke4roh (Talk | contribs) (crop to just the engine)
01:27, 10 June 2004640×480 (95 KB)Reubenbarton (Talk | contribs) (H-1 Saturn I and Saturn IB rocket engine)

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