RESPONSE OF A BURNING PROPELLANT SURFACE TO EROSIVE TRANSIENTS
Quarterly rept. no. 6, 1 Apr-30 Jun 1967
STANFORD RESEARCH INST MENLO PARK CA
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The report covers the research progress on combustion instability characteristics of solid propellants accomplished under Contract AF 49638- 1665, during the period 1 April through 30 June 1967. During this quarter the analytical model of transient solid propellant combustion has been modified to account for a decrease in gas-phase heat release whenever there is an increase in surface-coupled heat release, and vice versa. The computer analysis has been changed to reflect this modification. Correlation of the numerically predicted behavior with the experimental results obtained previously from traveling wave studies will allow the determination of those factors that are most influential in determining the burning rate response to sudden pressure changes. Experimental studies of the detailed structure of the flame zone, using fiber optics in conjunction with high-speed photography, have shown that both ammonium perchlorate crystals and aluminum particles may ignite at or near the surface, providing further support for the concept of surface-coupled heat release.
- Combustion and Ignition
- Solid Rocket Propellants