H-1 (rocket engine): Meaning (information, definition, explanation, facts)

The H-1 engine is a 200,000 lbf (890 kN) thrust LOX/RP-1 engine, used alone in the first stages of some Thor - Delta rockets and the Jupiter rocket. It is derived from the Navaho missile, and was simplified and improved for S-IB use. It is used in clusters on all S-IB rocket stages. Later it would be uprated to 205,000 lbf (912 kN) of thrust. The H-1 preceded the F-1 engine, which was used on the Saturn V rocket.

Specifications

  Vehicle Effectivity
SA-201 through SA-205 SA-206 and subsequent
Thrust (sea level) 200,000 lbf (890 kN) 205,000 lbf (912 kN)
Thrust duration 155 s 155 s
Specific impulse 260.5 lbf.min/lb (153 kNs/kg) 261.0 lbf.min/lb (154 kNs/kg) 261.0 lbf.min/lb (154 kNs/kg)
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%
Fuel flow rate 2092 USgal/min (132 L/s)  
Oxidizer flow rate 3330 USgal/min (210 L/s)  
Nominal chamber pressure 633 psia (4.4 MPa)  
  • Contractor: NAA/Rocketdyne
  • Vehicle Application: Saturn I / S-IB 1st stage - 8-engines
  • Vehicle Application: Saturn IB / S-IB 1st stage - 8-engines
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