Abstract
Abstract In the present investigation an effort has been made to understand the thermal decomposition and burn rate characteristics of AP as oxidizer and PVC and HTPB as fuel binder in composite solid propellant. The burning rate study has been carried out at ambient and different pressures of 2.068Mpa, 4.760Mpa, 6.895Mpa. The mechanism of thermal decomposition of each composition have also been determined by NETZSCH simultaneous thermal analyser, comprising differential scanning calorimeter (DSC) and thermo-gravimetric analyser (TGA). An effort has been made to study the burn rate and decomposition of fuel binder and oxidizer in presence of Fe2O3 and also their overall impact on combustion of propellant.
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