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Controllable Solid Propulsion Combustion and Acoustic Knowledge Base ImprovementsControllable solid propulsion systems have distinctive combustion and acoustic environments that require enhanced testing and analysis techniques to progress this new technology from development to production. In a hot gas valve actuating system, the movement of the pintle through the hot gas exhibits complex acoustic disturbances and flow characteristics that can amplify induced pressure loads that can damage or detonate the rocket motor. The geometry of a controllable solid propulsion gas chamber can set up unique unsteady flow which can feed acoustic oscillations patterns that require characterization. Research in this area aids in the understanding of how best to design, test, and analyze future controllable solid rocket motors using the lessons learned from past government programs as well as university research and testing. This survey paper will give the reader a better understanding of the potentially amplifying affects propagated by a controllable solid rocket motor system and the knowledge of the tools current available to address these acoustic disturbances in a preliminary design. Finally the paper will supply lessons learned from past experiences which will allow the reader to come away with understanding of what steps need to be taken when developing a controllable solid rocket propulsion system. The focus of this survey will be on testing and analysis work published by solid rocket programs and from combustion and acoustic books, conference papers, journal articles, and additionally from subject matter experts dealing currently with controllable solid rocket acoustic analysis.
Document ID
Document Type
Conference Paper
McCauley, Rachel
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Fischbach, Sean
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Fredrick, Robert
(Alabama Univ. Huntsville, AL, United States)
Date Acquired
August 26, 2013
Publication Date
April 30, 2012
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
Meeting Information
Meeting: 28th Rocket Nozzle Technology Subcommittee Meeting
Location: San Antonio, TX
Country: United States
Start Date: April 30, 2012
End Date: May 4, 2012
Sponsors: NASA Headquarters, Department of the Air Force, Department of the Army, Department of the Navy
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