关键词: 火箭冲压发动机;冲压进气燃烧室;流动分布;数值计算;发动机试验

Abstract: he purpose of this paper is to solve the specific problem of the combustion of boron in solid propellant ramrocket combustor. In this study, the reactingflow field in the combustor is described with two-dimension partial differential equations, k-ε two-equation model.SIMPLE method is adopted in the calculation. Asketch of a combustor with secondary air inlets is gaven and some experimental investigations have been done.The results show that higher combustion efficiency isachieved in the combustor with secondary air inlets than in normal combustor without them.

Key words: Rocket ramjet;Ram-air combustor;Flow distribution;Numerical computation;Engine test