固体火箭发动机易损性试验研究  

Experimental Study of the Solid Rocket Motor Vulnerability

作　　者：李瑞锋 党永战[1] 李宏岩[1] 王中[1] Li Rui-feng;Dang Yong-zhan;Li Hong-yan;Wang Zhong(Xi′an Modern Chemistry Research Institute,Xi′an,710065)

机构地区：[1]西安近代化学研究所

出　　处：《导弹与航天运载技术》2019年第5期53-58,共6页Missiles and Space Vehicles

摘　　要：为了研究某固体火箭发动机的易损性,提出了适用于发动机的3项易损性试验方案和响应类型判定方法。根据试验方案搭建了试验系统,开展了固体火箭发动机快速烤燃、慢速烤燃、子弹撞击3项易损性试验。通过对试验现象的分析,依据响应类型判定方法得出发动机对于各项试验的响应类型,得到发动机易损性结论。结果表明:易损性试验方案合理可行,对固体火箭发动机以及不敏感弹药的易损性评估具有一定的参考和借鉴意义。In order to study the vulnerability of the solid rocket motor, three vulnerability experimental programs and response type judgment rules suitable for the solid motor are proposed. Test system is set up according to the experimental program, three vulnerability evaluation tests as fast cook-off test、slow cook-off test and bullet impact test are carried out. Based on the analysis of experimental phenomena and the judgment rules, the response type of each test is obtained,the vulnerability evaluation experimental conclusion is reached, the rationality and feasibility of the evaluation experimental program is also verified, which have reference value to the vulnerability evaluation of the full-size solid rocket motor and insensitive munitions in the future.

关 键 词：固体火箭发动机 易损性 快速烤燃 慢速烤燃 子弹撞击 

分 类 号：TJ76[兵器科学与技术—武器系统与运用工程]