关键词: 固体推进剂火箭发动机;装药结构;流场模拟;数值模拟

Abstract: In this paper, MacCormack’s time-dependent explicit scheme is used to solveaxisymmetric mienal flow fields of the solid propellant rocket motor. The governing equations arecompressible full Navier-Stokes equations. In the calculation, the Boundary-Fitted-Coordinate systemis applied to transform a physic plane into calculation plane, the governing equations in calculationplane are obtained. A kind of arc-hyperbolic-sine function is utilized to construct the partialconcentrated grids, so that the region in which the physical variables have greater gradient will havemore grids than elsewhere. A turbulent model based on the Baldwin-Lomax algebraic scheme isemployed toget the coefficient of turbulent viscosity. The parameters on boundary of flow field aredetermined by characteristic line method on a reference plane and physic boundary conditions. Thenumerical results indicate that the numerical method employed here is effective. When concentratedmass is injected into the chamber, the pressure at the chamber head raises, which also depends oninjection mass ratio and jet position and the outlet direction of slot.

Key words: Solid propellant rocket engine;Charge structure;Flow field simulation;Numerical Simulation