Closed Loop Throttle Control of a Liquefying Fuel Hybrid Rocket Motor
نویسندگان
چکیده
The thrust produced by a hybrid rocket motor (HRM) can be controlled varying the oxidizer flow rate to combustion chamber. This feature is useful in shaping profiles and optimizing vehicle flight trajectory, but propellant throttling solid-fuel hybrids limited liquid component only, complicating control scheme potentially destabilizing motor. While ability remains subject of considerable interest, there has been little investigation motors that use high regression rate, liquefying fuels such as paraffin wax. article describes development implementation closed loop for laboratory-scale wax/nitrous oxide HRM using low-cost ball valve controlling hardware element. A model performance first developed from which proportional-integral-derivative (PID) controller constants are obtained through experimental testing. demonstrated hot fire tests tracks set-point value with feedback provided load cell. Upon reaching setpoint, throttled within ± 2.4% maximum Constant ramping demonstrated.
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ژورنال
عنوان ژورنال: Journal of Aerospace Technology and Management
سال: 2021
ISSN: ['2175-9146', '1984-9648']
DOI: https://doi.org/10.1590/jatm.v13.1206.2021