Published 1999
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Numerical Analysis of Solid Rocket Motor Instabilities With AP Composite Propellants
Abstract
A non-steady model for the combustion of ammonium perchlorate composite propellants has been developed in order to be incorporated into a comprehensive gasdynamics model of solid rocket motor flow fields. The model including the heterogeneous combustion and turbulence mechanisms is applied to nonlinear combustion instability analyses. This paper describes the essential mechanisms and features of the model and discusses the methodology of non-steady calculations of the combustion instabilities of solid rocket motors.
Additional Information
©1999 by the authors. This work has been partially supported by the Caltech Multidisciplinary University Research Initiative under ONR Grant No. N00014-95-1-1338; Dr. Judah Goldwasser of the Office of Naval Research is Program Manager.Attached Files
Published - 391_Roh_TS_1999.pdf
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391_Roh_TS_1999.pdf
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Additional details
- Eprint ID
- 20898
- Resolver ID
- CaltechAUTHORS:20101118-132511549
- N00014-95-1-1338
- Caltech Multidisciplinary University Research Initiative
- Created
-
2010-11-18Created from EPrint's datestamp field
- Updated
-
2019-10-03Created from EPrint's last_modified field
- Caltech groups
- Guggenheim Jet Propulsion Center, GALCIT
- Series Name
- AIAA Papers
- Series Volume or Issue Number
- AIAA-99-2804
- Other Numbering System Name
- AIAA
- Other Numbering System Identifier
- 1999-2804