Performance of Additively Manufactured Fuels for Hybrid Rockets

Hybrid rocket engine (HRE) performance is dependent on fuel/oxidizer selection and fuel grain geometry. A literature review was performed to identify key trends findings related the application of additive manufacturing (AM) systems for HREs. The effects complex combustion port geometries, embedded structures, end-burning systems, along with use metallic additives, turbulators, diaphragms, gel-like fuels, powdered liquid liquifying fuels their impact regression rates, efficiencies, and/or mechanical strength are thoroughly documented here. In general, AM HRE can be implemented increase rates efficiency, tailor designs. Chemical equilibrium analysis computations were completed characterize theoretical HTPB common (ABS, PLA, PC, PMMA, Nylon 6, a UV-based fuel) oxidizers (LOX N2O). exhibit similar as commonly used fuel, proper yield improved design metrics. Development approaches have significantly expanded trade space should enable competitive HREs future propulsion missions.