用固体火箭发动机中常用的瞬态平衡压强法对烟火剂式点火器内弹道性能进行了理论预示，并提出热损失系数的概念。
Instantaneous equilibrium pressure method is used in this paper to analysis the internal ballistics of pyrogen-type igniters. A concept of igniter heat loss coefficient is also presented.
因此对旋转固体火箭发动机尾部点火过程的数值模拟中，需要考虑点火器生成的高温粒子对点火过程的影响。
So the hot particles produced by the igniter should be considered in the numerical simulation of the ignition of the rotating RSM with the aft-end igniter.
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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