针对固体火箭发动机难以实现推力调节和能量控制,限制导弹射程和滞空时间的问题,采用隔舱式脉冲发动机设计,提出了一种可行的三脉冲的发动机结构方案,详细介绍了发动机总体方案及工作过程,完成了硬质隔板选材与结构设计,通过原理样机对隔板方案进行了单项试验考核,最终成功实现了发动机的三级脉冲工作。 In view of the difficulty of the thrust control and the energy control of the solid rocket motor and the limitation of the missile range and the lag time, a feasible three-pulse engine structure scheme is proposed by using the bayonet pulse engine design. The overall scheme and work of the engine are introduced in detail Process, completed the selection of rigid separator material and structural design, through the prototype of the prototype test program to conduct a single test assessment, the final success of the engine to achieve the three pulse.