提出了一种新的膏体推进剂脉冲火箭发动机设计方案及其再点火装置的设计与实现，建立了膏体推进剂在再点火装置中二维流动模型和传热模型，得到了发动机可靠点火时再点火装置温度、长度、通道直径和挤压压强间应满足的关系，以及发动机熄火应满足的条件，还进行了原理性热试车，成功实现了多脉冲工作。 A new design scheme of pulsed propellant rocket propellant and its re-ignition device design and implementation are put forward. The two-dimensional flow model and heat transfer model of the propellant in the re-igniting device are established, and the reliable ignition of the engine is obtained And then the ignition device temperature, length, diameter of the channel and the pressure to be met between the pressure, and the engine flameout conditions should be met, but also the principle of heat test, the successful implementation of the multi-pulse work.