冲击载荷下NEPE高能固体推进剂响应特性分析及点火增长模型参数标定  

Response Characteristics Analysis and Parameters Calibration of Ignition and Growth Model of NEPE Propellants under Impact Load

作　　者：郭宗韬 许进升[1] 陈雄[1] 曹欣宇 庞嵩林 王金东 GUO Zong-tao;XU Jin-sheng;CHEN Xiong;CAO Xin-yu;PANG Song-lin;WANG Jin-dong(School of Mechanical Engineering,Key Laboratory of Special Engine Technology,Ministry of Education,Nanjing University of Science and Technology,Nanjing 210094,China;Jinxi Industries Group Co.,Ltd,Taiyuan 030027,China)

机构地区：[1]南京理工大学机械工程学院,特种动力技术教育部重点实验室,江苏南京210094 [2]晋西工业集团有限责任公司,山西太原030027

出　　处：《含能材料》2025年第2期165-177,共13页Chinese Journal of Energetic Materials

基　　金：中央高校基本科研业务费专项(30924010503)。

摘　　要：为保障固体火箭发动机在复杂战场环境下的安全应用,开展了冲击载荷作用下硝酸酯增塑的聚醚聚氨酯(NEPE)高能固体推进剂的响应特性研究,建立了一维拉格朗日锰铜压阻试验测试系统,使用锰铜传感器记录了冲击起爆过程中NEPE推进剂内部不同拉格朗日位置处前导冲击波的压力变化历史。通过冲击波波阵面前后动量守恒关系,获得了被测推进剂的未反应冲击绝热线,利用遗传算法得到了未反应NEPE推进剂状态方程参数。同时,设计并搭建了Φ50 mm的NEPE推进剂探针式圆筒试验测试平台,采用12根具有径向位移差的金属探针记录金属圆筒膨胀到不同位置的时间,获得了圆筒膨胀速度时间曲线。在此基础上提出了一种结合Gurney能量模型和遗传算法的考虑铝粉反应的爆轰产物JWL-Miller状态方程参数计算方法,得到了NEPE推进剂爆轰产物状态方程参数。最后,采用点火增长模型对不同拉格朗日位置处的压力曲线进行拟合。结果表明,未反应推进剂和爆轰产物状态方程参数曲线拟合相关性较高,获得的点火增长模型参数很好地模拟了NEPE推进剂冲击起爆试验结果,所获得的参数可以为冲击载荷作用下NEPE推进剂装药的固体火箭发动机安全性评价提供参考依据。In order to ensure the safe application of solid rocket motors in complex battlefield environments,it is necessary to conduct in‑depth research on the response characteristics of NEPE high‑energy solid propellants under impact loads.A one‑dimensional Lagrange test system was established to measure the pressure wave at different Lagrange location.The unreacted shock adiabatic curve of the measured propellant was obtained through the momentum conservation relationship before and after the shock wavefront,and the JWL EOS of the unreacted NEPE propellant were obtained by using a genetic algorithm.AΦ50 mm NEPE propellant probe‑type cylinder test platform was constructed and a 12‑channel probe with radial displacement difference was used to record the time of copper cylinder expansion to different probe positions and the time curve of cylinder ex‑pansion velocity was obtained.Based on the results of theΦ50 mm cylinder test,the JWL‑Miller EOS parameters of the detonation product of NEPE propellant was calibrated by Gurney model and genetic algorithm.Finally,the pressure curves at different Lagrange position were fitted with the ignition and growth model.The results show that the fitting correlation coefficients of JWL EOS parameter curves for unreacted propellant and detonation products are high enough and the obtained ignition and growth model parameters well simulate shock initiation experimental results and the obtained parameters can provide reference for the safety evaluation of solid rocket motors.

关 键 词：NEPE高能固体推进剂 冲击起爆 拉式试验 圆筒试验 点火增长模型 

分 类 号：TJ55[兵器科学与技术—军事化学与烟火技术] V435[航空宇航科学与技术—航空宇航推进理论与工程]