Abstract
A hydrogen-oxygen torch igniter was developed and utilized to study its effects on a solid acrylonitrile butadiene styrene thermoplastic (ABS)-gaseous oxygen (GOx) hybrid rocket motor. The effects thereof are not presently found in literature. An increase of the hydrogen mass flow rate, at constant GOx mass flow rate, led to an increase in the average linear regression rate and a decrease in characteristic ignition time for fuel-lean and stoichiometric hydrogen-oxygen flames. Additionally, extending the duration of hydrogen flow from 10% to 50% of the total burn time led to an increase in the regression rate. Results suggest that the hydrogen-oxygen torch igniter can be used as a reliable starter with reignition capabilities and also for regression rate and ignition delay enhancement that targets the rate-limiting step, pyrolysis, for hybrid rocket combustion at stoichiometric and fuel-lean operating conditions of the torch igniter.
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