IGNITION RESPONSE OF SOLID PROPELLANTS TO RADIATION AND CONDUCTION
STANFORD RESEARCH INST MENLO PARK CA
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Experimental measurements were carried out on the ignition response of solid propellants to radiative and to conductive heat transfer. The propellants were composed of ammonium perchlorate and different organic binders. The experimental results were interpreted in terms of a model involving exothermic chemical reaction in the condensed phase of the propellant. The heat release rates in the surface-coupled reactions were measured independently. Such a model adequately fitted the ignition process associated with a thermal runaway in the condensed phase. A comparison of the ignition data demonstrated different response of the propellants to the mode of ignition. The importance of these results to rocket motor tests is discussed.
- Solid Rocket Propellants