固体火箭发动机不点火自毁爆炸危险性研究  

Study on the non-ignition self-destruction explosion hazard of SRM

作　　者：殷雅侠[1] 刘平[1] 谷乃古[1] 

机构地区：[1]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2004年第2期111-113,共3页Journal of Solid Rocket Technology

摘　　要：根据中能固体火箭发动机的自毁爆炸特点及发动机自毁模拟试验的结果,结合过去固体火箭发动机的研制经验,提出了中能固体发动机不点火自毁爆炸危险性的计算方法,并对三级火箭固体火箭发动机不点火自毁时的爆炸TNT当量、碎片飞散距离和冲击波超压安全距离进行了计算和分析,为导弹自毁爆炸危险性分析提供了参考。Based on the self-destruction explosion characteristics and self-destruction simulation test results of a medium energy solid rocket motor(SRM), with the reference of the development experience of SRM, the non-ignition self-destruction explosion hazard calculating method for medium energy SRM was put forward. This method was used for calculation and analysis of the explosion TNT equivalent value, the fragment flying distance and the safe distance of blast wave overpressure when a three-stage SRM was destructed because of the ignition failure. The results provide a reference to the self-destruction explosion hazard analysis of missile.

关 键 词：固体火箭发动机 不点火自毁 爆炸危险性 线形爆炸器 联合自毁 柱形爆炸器 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]