Its ignition transient process plays an important role in determining whether a solid rocket motor can work normally.
星形是固体火箭发动机常用的装药形式，而其点火瞬时过程对发动机能否正常工作起着极为重要的作用。
This dissertation integrates theoretical analysis and numerical simulation method to investigate the ignition transient process of large aspect ratio solid rocket motors.
本文采用理论分析和数值仿真方法对大长径比固体火箭发动机点火瞬态过程进行了系统研究。
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