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。
The results present thrust, specific impulse and thrust efficiency of the thruster under various environmental pressures, as well as impulse density distribution on the exit plane.
计算结果给出了不同环境压强下推力器的推力、比冲、推进效率和出口平面冲量密度分布。
Microwave Plasma Thruster (MPT) is a new type of electro-thermal thruster, which has widely applied prospect because of its high specific impulse, long lifetime, low plume contaminant and so on.
微波等离子推力器（MPT）是一种新型的电热型推力器，它具有比冲高、寿命长、羽流污染小等优点，具有广阔的应用前景。
Ignition start-up model of impulse micro-thruster is established, considering two phase flow and impact heat transfer of particle on the surface of propellant.
建立了微型脉冲推力器点火启动模型，模型中考虑了两相流动和颗粒对推进剂表面的冲击传热。
Ignition start-up model of impulse micro-thruster is established, considering two phase flow and impact heat transfer of particle on the surface of propellant.
建立了微型脉冲推力器点火启动模型，模型中考虑了两相流动和颗粒对推进剂表面的冲击传热。
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