HTPB复合固体推进剂率相关损伤机理分析与验证  

Analysis and Verification of Rate-Dependent Damage Mechanism of HTPB Composite Solid Propellant

作　　者：张亮 职世君[2] 申志彬[3] 虞跨海 ZHANG Liang;ZHI Shi-jun;SHEN Zhi-bin;YU Kua-hai(College of Architecture and Construction,Henan University of Science and Technology,Luoyang 471003,China;China Airborne Missile Academy,Luoyang 471000,China;College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]河南科技大学土木工程学院,河南洛阳471003 [2]中国空空导弹研究院,河南洛阳471000 [3]国防科技大学空天科学学院,湖南长沙410073

出　　处：《推进技术》2022年第10期431-439,共9页Journal of Propulsion Technology

基　　金：国家自然科学基金(11872372,11902348,11902350);国防科技基础加强计划(2019JCQZD178);河南省科技攻关(222102210298);河南省教育厅自然科学研究(22A130001)。

摘　　要：固体发动机在点火过程中常由于结构完整性问题而出现爆炸或性能曲线异常等问题,结合发动机在点火状态下推进剂的受载情况,亟待探索固体推进剂的率相关损伤机理。本文从HTPB复合固体推进剂在宽温和宽应变率下单向定速拉伸试验的力学响应特征入手,针对应力-应变曲线呈现的“双峰”、“脱湿”点前后移位等现象阐释了推进剂的率相关界面损伤特性,基于建立的推进剂细观有限元模型对推进剂的率相关损伤过程进行了仿真计算,通过提取有限元分析结果的损伤界面分析了推进剂的界面损伤机理,通过高速摄像试验的结果对损伤机理进行了验证。结果表明,推进剂的界面损伤过程具有很强的率相关性,“双峰”和“脱湿”点前后移位均与推进剂在不同应变率下拉伸时内部的损伤演化过程有关。通过对比推进剂在不同应变率下拉伸时断裂前的形貌,高应变率下AP颗粒析出数量较多,在一定程度上印证了本研究对推进剂损伤机理的阐释。The problems such as explosion or abnormal performance can happen due to structural integrity problems during ignition state of solid rocket motor(SRM). It is urgent to do the research on the rate-dependent damage mechanism of solid propellant when considering the loading condition of propellant during ignition state of SRM. The mechanical response characteristics of HTPB propellant at wide temperature range and different strain rates under uniaxial tensile test were investigated. The rate-dependent damage characteristics of the propellant were explained based on the phenomenon of "double peak" and "dewetting" point shifts on the stress-strain curve during the test. Then the rate-dependent damage process of propellant was analyzed based on the mesoscale finite element model of propellant,and the rate-dependent damage mechanism was analyzed by damage interface extraction according to results from finite element analysis(FEA). Finally,the damage mechanism was validated by results from high-speed photography experiment. The results show that the damage process of solid propellant has a strong rate dependence. The "double peak" and "dewetting" point shift are correlated to the internal damage evolution process of the propellant stretching at different strain rates. By comparing the morphology of propellant before fracture at different strain rates,more AP particles can be precipitated under high strain rate. It is a proof on the damage mechanism of propellant concluded in the study to a certain extent.

关 键 词：HTPB复合固体推进剂 损伤机理 应变率 率相关 脱湿 双峰 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]