提出了一种带有中间喷管的新型双脉冲固体火箭发动机技术方案，设计了一台结构参数可调的试验发动机；
A new type of dual-pulse solid rocket motor concept with an intermediate nozzle is presented and a test motor with changeable structural parameters was designed.
最后将算例的计算结果与常规液体火箭发动机及固体火箭发动机的相关参数作了对比，脉冲爆震发动机具有更优越的整体性能，因此，有必要对它进行更进一步的研究。
When calculations are compared with the performance parameters of solid engine and liquid engine, it is concluded that PDE has very superior performance. It is necessary to continue research on PDE.
最后将算例的计算结果与常规液体火箭发动机及固体火箭发动机的相关参数作了对比，脉冲爆震发动机具有更优越的整体性能，因此，有必要对它进行更进一步的研究。
When calculations are compared with the performance parameters of solid engine and liquid engine, it is concluded that PDE has very superior performance. It is necessary to continue research on PDE.
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