关键词: 液固混合火箭发动机;火箭冲压发动机;加力燃烧室;流动分布;二相流

Abstract: For computation of the flow field established in the chamber of solid liquid rocket ramjet,the block implicit algorithm was used to solve the Navier Stokes equations for gas.The separated flow model and continuum formulation model were used to characterize the flow and vaporization of droplets.For droplet flow,a special approach was tried to represent the law of mass conservation and the size changing of the droplets.It was demonstrated that the solution was rapidly convergent and the numerical results were qualitatively correct.

Key words: Lithergol rocket engine;Rocket ramjet;Afterburner;Flow distribution;Two phase flow