H-1 rocket engine diagram image.jpg
NASA
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H 1 rocket engine diagram image, H-1 (rocket engine)
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H 1 rocket engine diagram image, The H-1 rocket engine


 &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)
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H1ロケットエンジン図
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H1ロケットエンジン図。H1ロケットエンジンとH1ロケットエンジンの実効性SA-201からSA-205、およびそれに続く推力。20万lb。 推力155 sec。 比推力260.5 min。 エンジン重量2,200 lb。
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rocket base sea-rocket space rocket rocket thrust stage lox rocket propulsion rocket-propelled