高能固体发动机冲击安全性试验及数值研究  

Experimental and Numerical Research on Impact Safety of High Energy Solid Engine

作　　者：刘凯[1] 张宏亮[2] 韩明[2] 刘长猛[1] 王宇[1] 

机构地区：[1]中国航天科技集团公司四院41所,西安710025 [2]中国人民解放军驻航天科工二院210所军事代表室,西安710065

出　　处：《战术导弹技术》2017年第6期50-56,共7页Tactical Missile Technology

基　　金：国家自然科学基金(10972063)

摘　　要：为了对高能固体火箭发动机进行冲击安全性研究,开展了Ф200 mm和Ф480 mm高能发动机火箭撬径向冲击试验,获得了高能发动机在不同撞击速度情况下的推进剂反应特征,确定了发动机冲击反应临界区域。应用实验所确定的固体推进剂爆轰反应速率方程,建立了高能固体发动机撞击靶板的爆炸数值计算模型,确定了不同几何尺寸下发动机装药爆燃的撞击速度阈值范围。结果表明,Ф480 mm高能发动机比Ф200 mm发动机点火延迟时间短,且起爆阈值更低。In order to study the impact safety of high energy solid rocket motor,Ф 200 mm and Ф480 mm high-energy engine rocket pry radial impact test were carried out. The propellant reaction characteristics of the high-energy engine at different impact speeds were obtained and the critical area of the engine impact response was determined. The numerical simulation model of the impact of the high speed solid engine impact target is established by using the experiment of the solid propellant detonation reaction rate equation,and the range of the impact velocity of the engine charge detonation under different geometric dimensions is determined. The results show that Ф480 mm high-energy engine is shorter than the ignition delay time of Ф200 mm engine,and the ignition threshold is lower.

关 键 词：高能固体火箭发动机 安全性 火箭撬 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]