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Analysing some solid rocket double-base propellant ignition cases using the thermal theory
Dragan Lemiæ
The thermal theory of solid rocket propellant ignition based on the exothermic chemical reaction in the solid phase subsurface layer was analysed. Time-dependent equations controlling the process (the conservation of energy and components) were numerically solved, aiming at defining the temperature and concentration distribution in the solid phase. The calculated values of the characteristic parameters are in reasonable agreement with a large amount of experimental data from the references. Although the influence of the gas-phase reactions during the double-base rocket propellant ignition is obvious, the prospects of using the ignition theory while investigating the DB propellant ignition under certain conditions was demonstrated.
Key
words: solid rocket propellant,
double-base propellant, ignition, combustion.
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