This study investigates the effects of single, double, and multi-protrusion on the performance of a hybrid rocket with two different ratio motors, mainly 12.5 and 18. Wax and gaseous oxygen were used as fuel and oxidizer, respectively. It has been observed from studies that the performance of a hybrid rocket is sensitive to the number of protrusions and their locations within the motor. Between the two motors, single protrusion was outperformed in the motor, whereas double and multi-protrusion were more effective in the motor. The highest improvement in regression rate was observed from the use of three protrusions (0.2, 0.5, and ) in both motors. The use of four protrusions (0.2, 0.4, 0.6, and ) was more significant in improving the regression rate with the motor than with the motor. Upon insertion of protrusion, combustion efficiency was enhanced in the motor and decreased in the motor. The motor was more stable in terms of the shift in oxidizer-to-fuel ratio than the motor. Studies on exhaust plume reveal that a large amount of unburned fuel comes out of the motor and remains as white smoke for all the protrusion cases tested with the motor.
Experimental Studies of Protrusion-Inserted Hybrid Rocket Motor with Varying Ratio
Journal of Spacecraft and Rockets ; 58 , 1 ; 134-147
2020-10-15
14 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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