Next-generation magnetic flowmeter for characterizing the dynamic behavior of novel energetic materials for space propulsion

The objective of this program is to build upon many decades of experience with magnetic flowmeters to develop a next-generation system to measure the burning surface admittance of high-energy-density solid propellants at high frequencies and pressures. Using the results of research on solid propellant rocket motor combustion instability from the past fifty years, one can directly measure the acoustic admittance of the atomization/vaporization/mixing/combustion processes associated with liquid propellant rocket engine injection. Such a measurement would provide a quantitative value for the acoustic sources or sinks caused by these processes. This would enable an a priori prediction of the combustion stability for a particular liquid rocket engine design, something that has not been possible to date. BENEFIT: If successful, this research will provide a commercially available apparatus that would be able to characterize the dynamic behavior of a wide number of high-energy-density propellants. This would provide faster prototyping, and allow for more mass and fuel efficient design of rocket engines in general. This diagnostic technology would obviously be very attractive to any commercial market working in solid and liquid rocket design in both military and commercial applications.