摘要
设计了一种适用于某微小型固体火箭发动机的点火器 ,对某微小型固体火箭发动机的点火特性进行了大量试验研究 ,引入了初始点火压强的概念 ,找出了影响点火延迟时间散布的主要规律 。
A kind of igniter has been designed for minute solid rocket motor. Many tests have been done to determine the ignition characteristics of minute solid rocket motor. A concept of initial ignition pressure has been introduced the principal principle which effected ignition delay time scatter has been found and determined the ignition scheme satisfying the demand for ignition performance of minute solid rocket motor determined.
出处
《国防科技大学学报》
EI
CAS
CSCD
2000年第5期23-25,共3页
Journal of National University of Defense Technology
基金
部委级重大科研项目资助
