To develop light, reliable, sanitary space station maneuverable orbital transfer thruster, the novel gas dynamic resonance ignition method was applied.
为研究轻型、可靠、环保的空间站机动变轨发动机，在氢氧液体火箭发动机头部设计中引入了新型气动谐振点火技术。
Orbit maneuver hydrogen-oxygen thruster based on gas dynamic resonance igniter is a novel chemical propulsion technology especially prospective in space station application.
结合气动谐振点火器进行头部设计的氢氧变轨火箭发动机是一项新颖化学火箭推进技术，尤其适于空间站应用。
This paper described the primary analysis of a new model helicopter ground resonance in taking off and landing by employed classical spatial dynamic model.
对某新型直升机垂直起落状态“地面共振”初步分析，采用经典的空间动力模型进行计算。
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