THRUST VARIATION OF A GASEOUS PROPELLANT ROCKET ENGINE
AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING
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The purpose of this thesis was to investigate the performance of a variable thrust rocket engine incorporating a variable area injector. The injector was designed, constructed, and assembled on an existing thrust chamber which was lengthened and provided with water cooling. Gaseous hydrogen and oxygen were used as propellants. The thrust was varied over a continuous range from 11 to 75 pounds, resulting in a throttling ratio of 6.821, while the specific impulse remained nearly constant. The transient response of the engine was fast, smooth, and accurate, and no indication of combustion instability was observed during the investigation.
- Combustion and Ignition
- Rocket Engines