High-Speed Measurements of Multiple Species and Temperature in Composite Solid Propellant Flames

Solid propellant combustion models have been developed for decades in order to eliminate the time, cost, and lack of safety involved with empirical testing. Critical to the accuracy of these models is an understanding of flame structure, which requires measurements at small spatial and temporal scales beyond what conventional capabilities can provide. Laser diagnostic techniques, such as planar laser-induced fluorescence (PLIF) and laser-absorption provide the opportunity to make novel observations of composite solid propellant flame structure. These observations include a more detailed understanding of chemical kinetics governing the flame, which is currently still significantly incomplete. As current models of composite solid propellants have moved beyond what has been experimentally observed, these diagnostic techniques can provide the required measurements for validation. The goal of this project is to expand the understanding of flame structure and chemistry of composite solid rocket propellants via planar laser-induced fluorescence of multiple species and infrared laser-absorption at high-speed. This work will begin with studying a basic propellant of ammonium perchlorate (AP) in a hydroxyl terminated polybutadiene (HTPB) binder. This composite propellant has been a major subject of modelling efforts and is of interest to NASA for next generation boosters. Upon validation of this diagnostic approach, it can then be applied to novel solid propellants with lower toxicity, higher performance, and lower sensitivity.

The goal of this project is to expand the understanding of flame structure and chemistry of composite solid rocket propellants via planar laser-induced fluorescence of multiple species and infrared laser-absorption at high-speed. This composite propellant has been a major subject of modelling efforts and is of interest to NASA for next generation boosters. Upon validation of this diagnostic approach, it can then be applied to novel solid propellants with lower toxicity, higher performance, and lower sensitivity.

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