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

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