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 6.82:1, 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. (Author)
Thrust Variation of a Gaseous Propellant Rocket Engine
1967
66 pages
Report
No indication
English
Rocket Engines & Motors , Combustion & Ignition , Controllable-thrust rocket motors , Gaseous rocket propellants , Fuel injection , Hydrogen , Oxygen , Throttling , Stability , Performance(Engineering) , Heat transfer , Design , Response , Nozzle area ratio , Instrumentation , Starting , Specific impulse , Manned spacecraft , Combustion , Thrust , Theses , Rocket motors(Gaseous propellant) , Apollo , Lem(Lunar excursion modules) , Low thrust
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