大跨度抛索火箭发动机总体设计与计算

针对抛索火箭质量小、射程近的特点，重点对发动机的装药、喷管进行了设计，提出单根药柱和三根药柱两种装药参数设计方案。针对不同方案，采用四阶龙格．库塔法对发动机的内弹道进行了计算，通过冲量对比，选用装填三根药柱的设计方案。通过试验，对发动机的膛压、推力进行了测试。结果表明，数值计算结果与试验数据较为一致，发动机设计方案满足抛索火箭的技术指标要求。

Design and Calculation of Large-span Throwing Solid Rocket Engine

The charge and nozzle of solid rocket motor used to rocket throwing system are designed based on its features of low mass and short range. The charge parameters design of single grain and three grains are proposed, and the internal ballistic calculation of solid rocket motor are carried out by fourth-order Runge-Kutta method. The design of three grains is selected by contrast of impulse. The chamber pressure and thrust of the solid rocket motor are obtained by experiment. The results show that the numerical re- sults are consistent with the experimental data, and the design of engine fulfill the technical requirements of rocket throwing system.