ofpowder AP has ~n detennined and it is observed that °p(ROwder) > Op(pellel), which clearly suggests that of is influencqi by tl1e surface tempcrature sensitive parameter (aT slaT o)p and hence by the surfacdsubsurface microstructure. In powder burning, the buoyal1t lifting of the particles into the gas phase occurs, whic~constitutes the so-called 'free board region' (FER) extending just above the b"ue I surface. Consequenl to the decomposition of AP particles in FER, the condensed phase heat release gets curtailed and Op(pow.der) becomes larger. A general relationship for Op in tenns of density and surface temperature is suggested,
T HE initial temperature of a solid propellant influences the burning rate and affects the performance of a rocket motor. A review of the literature reveals that a very thin zone beneath the burning surface is conceived to be effectively heated and important. However, this is not fully recognized in the quantitative prediction of the effect of temperature on the burning rate. Therefore, studies emphasizing the role of condensed and gas phase processes in different solid propellants are presented in this review so that there is some basis for unifying theories for predicting the effect of temperature on burning rate and other related properties like extinction, radiation effect, and deflagration pressure limit.
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