RESEARCH ON COMBUSTION OF SOLID PROPELLANTS
Final rept. 20 Apr 1965-31 Aug 1968
UNITED TECHNOLOGY CENTER SUNNYVALE CA RESEARCH AND ADVANCED TECHNOLOGY DEPT
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A study was made to relate theoretically predicted and experimentally observed pressure-coupled combustion instability behavior of solid propellants. Using a generalized theoretical model which incorporates both surface and gas phase combustion effects, the linear and nonlinear higher pressure amplitude region has been characterized by a group of combustion parameters. Concurrent experimental studies were directed toward investigating 1 the effects of coating the solid oxidizer crystals, 2 the chemical and physical nature of the propellant binder, catalysts, and crosslinking agents on the acoustic admittance, 3 nonlinear response properties, and 4 propellant burning rate. The data show that small changes in propellant formulations can have a significant effect on the derived parameters characterizing the surface and, therefore, on relative contributions of these reactions to the acoustical response properties.
- Solid Rocket Propellants