Combustion Surface Calculation Method of Solid Rocket Propellant Based on Parameterized Volume Boolean Operation

Abstract In order to solve the problem of long time consuming and low efficiency in solving complex combustion surface solid rocket propellant, a calculation method based on parameterized volume Boolean operation was proposed. After model propellant created by using 3D modeling software, burning used perform difference between obtained growth entity entity. Through Sensitivity Analysis function, variation range value set, so as obtain face under different thickness. this paper, star shaped charge column is selected calculate surface, feasibility verified. This provides basis for subsequent calculation.