某型固体火箭发动机不稳定燃烧仿真分析与试验  

Simulation analysis and experiment on discontinuous combustion of a solid rocket motor

作　　者：李娟[1] 王占利[1] 王栋[1] 李鹏飞 王牧昕 LI Juan;WANG Zhanli;WANG Dong;LI Pengfei;WANG Muxin(210 Institute,The Sixth Academy of China Aerospace Science ＆ Industry Corp.Xi＇an 710065, China)

机构地区：[1]中国航天科工集团公司六院210所,西安710065

出　　处：《固体火箭技术》2018年第2期151-155,共5页Journal of Solid Rocket Technology

摘　　要：针对某型大长径比固体火箭发动机研制过程中,发动机地面试验出现不稳定燃烧的现象,结合声腔频率分析方法和地面试验过程中增加脉冲触发,对其产生不稳定燃烧的频率范围进行了分析,通过优化发动机型腔结构改变发动机固有声腔频率,消除了不稳定燃烧现象,优化后的发动机通过地面试验增加脉冲触发进行验证。结果表明,所采用的声腔频率分析方法、优化改进措施及脉冲触发验证方法有效。In the developed process of solid rocket motor,there always exists discontinuous combustion phenomenon during its ground triggering test.The frequency range of discontinuous combustion was analyzed by acoustic frequency analysis method and increase of pulse trigger in the process of ground triggering test.Discontinuous combustion phenomenon was estimated by optimizing the cavity structure of the motor aiming to change the natural acoustic frequency. The optimized motor was verified by increasing the pulse triggering in the ground test.The results show that the acoustic frequency analysis,optimization improvement and pulse triggering verification methods are effective.

关 键 词：固体火箭发动机 不稳定燃烧 脉冲触发 声腔频率 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]