考虑弹头滚转姿态变化影响的防热层厚度优化  

Optimization on Heat-shield Thickness for Reentry Warhead Considering the Effect of Roll Attitude Change

作　　者：单继祥[1] 赵平[1] 何衍儒 杨鑫 SHAN Jixiang;ZHAO Ping;HE Yanru;YANG Xin(Institute of System Engineering,CAEP,Mianyang 621999,China)

机构地区：[1]中国工程物理研究院总体工程研究所,四川绵阳621999

出　　处：《弹道学报》2024年第1期10-17,共8页Journal of Ballistics

基　　金：中物院重大项目。

摘　　要：基于气动热/结构温度响应耦合计算方法,研究了弹头固定攻角再入条件下锥身典型子午面结构温度响应特性,以及滚转姿态变化时刻对各子午面结构温度响应的影响,建立了考虑弹头滚转姿态变化影响的防热层厚度优化方法,并基于该方法开展了弹头防热层厚度优化。最后,研究了滚转姿态变化次数对优化效果的影响。结果表明:在再入弹道前段进行滚转姿态变化可使外壁面气动加热量更为合理,有效降低弹体锥身壳体内壁面温升。当迎、背风面壳体内壁面最大温升约束为25 K时,与无滚转姿态变化状态下相比,滚转姿态变化设计可使防热层厚度减小0.725 mm,减小幅度为5.4%。通过与滚转姿态变化时刻的联合设计可有效降低锥身防热层厚度。与单次滚转姿态变化时相比,两次滚转姿态变化时防热层厚度减小量仅增大1.9%,增加滚转姿态变化次数对优化效果影响较小。The structure thermal response characteristics on typical meridian of the reentry warhead with fixed flying attack-angle and the effects of the roll attitude change time on the structure thermal response on typical meridian plane were studied by the coupling calculation method of the aerodynamic heating environment and structure thermal response.The heat-shield thickness optimization method considering the effect of roll attitude change times was built,and the heat-shield thickness of the warhead was optimized based on this optimization method.The effect of the body rolling numbers on the optimization results was researched.The results show that the aerodynamic heating on the shell surface is more reasonable,and the maximum temperature rise of the inner surface is effectively reduced by changing the roll attitude in the forepart of the flying trajectory.When the maximum temperature rise of the inner surface is 25 K,the thickness of heat-shield can be reduced by 0.725 mm(5.4%)compared with the condition without rolling movement.The heat-shield thickness can be effectively reduced by the joint optimization with the roll attitude change time.Compared with single rolling movement change,the decrease extent of heat-shield thickness increases by 1.9%considering twice rolling movement.The number of the rolling movement change has a small effect on optimization result.

关 键 词：气动热 再入攻角 滚转姿态变化 结构热响应 厚度优化 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]