基于NSGA-Ⅱ的固体火箭发动机壳体不同开口比封头补强优化  

Reinforcement optimization for different opening ratios dome of SRM case based on the NSGA⁃Ⅱmethod

作　　者：张骞 刘浩 刘宏浩 牟星 吴世俊 丁文辉 张桂明 祖磊 ZHANG Qian;LIU Hao;LIU Honghao;MOU Xing;WU Shijun;DING Wenhui;ZHANG Guiming;ZU Lei(School of Mechanical Engineering,Hefei University of Technology,Hefei 230009,China;The Insitute of Xi'an Aerospace Solid Propulsion Technology,National Key Laboratory of Solid Rocket Propulsion,Xi’an 710025,China)

机构地区：[1]合肥工业大学机械工程学院,合肥230009 [2]西安航天动力技术研究所,固体推进全国重点实验室,西安710025

出　　处：《固体火箭技术》2024年第4期573-582,共10页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(12102115,52175133,52175311);中央高校基本科研业务费专项资金资助(JZ2023HGTB0214,JZ2023HGPB0289)。

摘　　要：封头补强工艺作为壳体封头承载能力提升的典型手段,其补强工艺参数对不同开口比壳体补强后应力水平、壳体质量的影响规律不明晰。为此,构建了?300 mm壳体分析模型,并结合径向基函数(RBF)神经网络分析方法拟合优化变量与优化目标间的映射关联,开展了补强角度、补强层数、补强区域对应力响应水平的影响规律研究。最后,基于非支配排序遗传算法(NSGA-Ⅱ)获得了最优开口比以及使壳体特性系数达到最大的最优补强参数。结果表明,优化后壳体的特性系数比未补强壳体提高16.28%,比未优化的编织布补强壳体提高6.53%。研究成果可以为不同开口比壳体补强工艺参数的选定提供理论依据。As a typical method for performance enhancement of the dome part,the reinforcements process with various parame⁃ters has little⁃known affect on the stress and mass of different opening ratios dome.Therefore,the analysis model of aϕ300 mm com⁃posite case was constructed.Combined with the radial basis function(RBF)neural network analysis method,the mapping relationship between the optimization variables and the optimization objectives was fitted,and the influence of the reinforcement angle,the num⁃ber of layers and the region of the case with different opening ratios on the stress level was studied.Finally,the optimal opening ratio and the optimal reinforcement parameters to maximize the case characteristic coefficient were obtained by means of the non⁃domina⁃ted sorting genetic algorithm(NSGA⁃Ⅱ).The results show that the characteristic coefficient of the optimized composite case is 16.28%higher than that of the unreinforced one and 6.53%higher than that of the unoptimized woven fabric reinforced one.The re⁃search results can provide a theoretical basis for the selection of process parameters for composite case reinforcement with different opening ratios.

关 键 词：固体火箭发动机 复合材料壳体 不同开口比 封头 补强优化 渐进损伤 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] TB332[一般工业技术—材料科学与工程]