Characterizing the dynamic behavior of novel energetic materials for space propulsion.

Period of Performance: 08/15/2008 - 05/15/2009


Phase 1 STTR

Recipient Firm

Electrodynamic Applications, Inc.
P.O. Box 131460
Ann Arbor, MI 48105
Principal Investigator
Firm POC

Research Institution

Pennsylvania State University
110 Technology Center Building
University Park, PA 16802
Institution POC


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.