A control scheme is proposed, in which liquid engine of constant thrust and impulse thruster are chosen to achieve hover task.
提出一种近月面定点悬停的控制方案，选用常推力液体发动机和脉冲式发动机实现悬停任务。
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.
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。
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