PW-R01 was a proof-of-concept hybrid rocket thruster prototype. A 50% H2O2 solution was used as the oxidizer and a PLA (polylactic acid) propellant with a helical geometry was used as the fuel.
Due to insufficient decomposition of the oxidizer, a proper ignition was not achieved, and sustained combustion did not occur. I considered the testing a failure and focused development efforts on a new model with an additional oxidizer decomposition stage.
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