限制的化学火箭发动机。
固体火箭发动机的点火是一个十分复杂的物理化学过程，包括三个阶段：点火延迟、火焰传播和燃烧室气体充填。
The ignition of the solid rocket motor (SRM) is a very complex physical and chemistry process, which is composed of three component phases: ignition delay, flame spreading and chamber filling.
建立了任意斜交曲线坐标系下液体火箭发动机(LRE)内部工作过程的气液两相湍流化学反应流模型。
Two-phase turbulent reacting flow model of the internal operating processes in Liquid Rocket Engine (LRE) is set up in non-orthogonal curvilinear coordinates.
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。
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。
Orbit maneuver hydrogen-oxygen thruster based on gas dynamic resonance igniter is a novel chemical propulsion technology especially prospective in space station application.
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