微型固体脉冲推力器内弹道性能的实验研究

AN EXPERIMENTAL INVESTIGATION ON INTERNAL BALLISTIC PERFORMANCE OF A SOLID IMPULSIVE MICROTHRUSTER

关键词:  固体推进剂火箭发动机  脉动式火箭发动机  微型火箭发动机  内弹道性能

Key words:  Solid propellant rocket engine  Impulse rocket engine  Microrocket engine  Interior ballistic performance

摘要:

对高速动能导弹飞行姿态控制和弹道修正用的多管微型固体脉冲推力器的内弹道性能进行了试验研究。其中，以单管挂药式结构的试验为主，并以贴壁粘结式结构试验作为对比分析。试验结果表明，所设计的原理样机工作正常，可进行重复试验；单管挂药式结构的各项内弹道性能均满足指标，且数据重复性好。但由于挂药引起的燃烧后期的碎药损失和挂药段装药后期的低压燃烧，使挂药式结构的比冲效率较低。

Abstract:

An experimental investigation on internal ballistic performance of solid impulsivemicrothrusters has been conducted for the flight attitude control of a high velocity missile. Most ofthose experiments were per formed for a single thruster with suspended grain structure, and another ofthem with grain adhesive to chamber wall was made for comparison and analysis. The experimentalresults indicated that the designed prototype thruster operated normally, the technical requirements ofinternal ballistic performance for the suspended grain structure were met and the data repeatabilitywas excellent, but the specific impulse efficiency of that structure was lower because of grain brokenbits loss and low-pressure combustion loss near burnout period.