Numerical Method of Propulsion Concept: Partially Cut Multiaperture Stick Propellant

Abstract The partially cut Multiaperture stick propellant is a new concept charging structure. In this paper, in order to accurately obtain the change and development process of two-phase flow field different stages whole interior ballistic propulsion system, coupled calculation model computational established, which converts Euler-Lagrange method Euler-Euler method. Firstly, at initial stage ignition, used describe field. During period, gas phase based on Euler coordinates, while solid Lagrangian coordinates. After projectile starts, fractured into granular propellant. converted by using mapping Finally, comparing calculated results with experimental results, maximum pressure error only 0.54%, verifies accuracy effectiveness coupling It effectively captures distribution physical parameters combustion chamber, providing research for concept. Based method, system obtained, no obvious shock waves expansion are seen, indicating that charge scheme can improve launch safety.