低温点火条件下发动机装药结构完整性分析及验证  

Structural Integrity Analysis and Experiment of Motor Grain under Low Temperature Ignition

作　　者：李晔鑫 职世君[1,2] 王虎干 肖志平[1] Li Yexin;Zhi Shijun;Wang Hugan;Xiao Zhiping(China Airborne Missile Academy,Luoyang 471009,China;Aviation Key Laboratory of Science and Technology on Airborne Guided Weapons,Luoyang 471009,China)

机构地区：[1]中国空空导弹研究院,河南洛阳471009 [2]航空制导武器航空科技重点实验室,河南洛阳471009

出　　处：《航空兵器》2021年第4期82-87,共6页Aero Weaponry

摘　　要：为评估某固体发动机装药低温点火条件下安全系数,开展了发动机装药结构完整性仿真和试验研究。基于三维线粘弹性模型,通过有限元软件分析了某发动机装药在低温和内压载荷下的结构完整性。利用快速建压试验系统模拟了低温下发动机点火升压过程,获得装药体积变形和最大主应变。对比仿真和试验结果,完成了相应条件下的泊松比反演。结合推进剂低温快慢组合拉伸试验,得到推进剂在模拟低温点火条件下的最大延伸率,从而获取发动机药柱在低温点火条件下的安全系数。In order to evaluate the security coefficient of certain solid rocket motor(SRM)grain under low temperature ignition,the simulation and test of SRM grain structural integrity are carried out.Based on the three-dimensional linear viscoelastic model,the structural integrity of the SRM grain under low temperature and internal pressure is analyzed by finite element software.The rapid pressure building test system is used to simulate the engine ignition boost process under low temperature,and the volume deformation and maximum principal strain of the grain are obtained.The Poisson’s ratio inversion under the corresponding conditions is completed by comparing the simulation and experimental results.The maximum elongation of the propellant under simulated low-temperature ignition is obtained by combining the low temperature fast-slow tensile test,and then the security coefficient of motor grain under low-temperature ignition is obtained.

关 键 词：低温点火 结构完整性 泊松比 松弛模量 体积变形 装药 推进剂 固体火箭发动机 

分 类 号：TJ763[兵器科学与技术—武器系统与运用工程] V43[航空宇航科学与技术—航空宇航推进理论与工程]