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

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9550-10-C-0023
Agency Tracking Number: F08A-010-0200
Amount: $399,928.00
Phase: Phase II
Program: STTR
Solicitation Topic Code: AF08-T010
Solicitation Number: 2008.A
Solicitation Year: 2008
Award Year: 2010
Award Start Date (Proposal Award Date): 2009-12-23
Award End Date (Contract End Date): 2011-12-23
Small Business Information
P.O. Box 131460
Ann Arbor, MI 48113-1460
United States
DUNS: 610511334
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: Yes
Principal Investigator
 Dean Massey
 Senior Engineer
 (734) 786-1434
Business Contact
 Jonathan Zagel
Title: Business Manager
Phone: (734) 786-1434
Research Institution
 Pennsylvania State University
 Sven B Ph.D.
213N Hammond Building
University Park, PA 16802-
United States

 (814) 863-1526
 Nonprofit College or University

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.

* Information listed above is at the time of submission. *

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