Work In Progress: This is Rocket Science: Development and Testing of a Hybrid Rocket Motor in a Rocket Propulsion Course

This paper describes a unique design and laboratory experience that was incorporated into an introductory rocket propulsion course. Specifically, each student team designed, built and tested a 7 lb_f thrust hybrid rocket motor. The thrust chambers were fabricated from aluminum and the nozzles were fabricated from graphite. Solid fuel grains consisting of HTPB and HTPB/Al were produced by each team. Each rocket was tested on a thrust stand that enabled the measurement of instantaneous oxygen mass flow rate, chamber pressure (P_c) and thrust. With these data, each team was able to measure specific impulse (I_sp), characteristic exhaust velocity (C*) and thrust coefficient (C_F) and compare these measurements to their theoretical models, which predicted instantaneous O/F, C*, P_c , and thrust. This design experience, which can be easily and inexpensively replicated at other institutions, was universally evaluated by students as a major highlight in their education to date and multiple students have expressed an interest in a career in aerospace engineering as a result