Abstract
An analytical formulation is developed to model the radiation due to aluminum/alumina particles in order to investigate the effects of the radiative heat feedback on low frequency combustion instability in hybrid rockets using aluminized propellants. A quasi-steady aluminum combustion model is considered, with a delay that accounts for the adjustment of radiating particle clouds to the changes in the regression rate. A linearized treatment shows that low frequency combustion instability can be driven by the coupling of the thermal transient in the solid fuel grain and the radiation heat feedback related to the distributed combustion of aluminum particles.
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