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。 Aiming at the characteristics of the small rocket and the short range of the rocket, the design of the charge and nozzle of the engine is emphatically focused, and the design scheme of two kinds of charge parameters, single and three, is proposed. According to the different schemes, the fourth-order Runge-Kutta method is used to calculate the internal trajectory of the engine. By comparing the impulse, the design scheme of filling three drug columns is selected. Through the test, the engine chamber pressure, thrust was tested. The results show that the numerical results are in good agreement with the experimental data, and the engine design meets the technical requirements of the projectile rocket.