变刚度复材板壳结构优化及热环境下的屈曲
收稿日期: 2025-06-26
修回日期: 2025-07-28
录用日期: 2025-09-03
网络出版日期: 2025-09-10
基金资助
国家自然科学基金(12472202);强度与结构完整性全国重点实验室开放基金(LSSIKFJJ202403014)
Structure optimization of variable-stiffness composite shells and buckling in thermal environments
Received date: 2025-06-26
Revised date: 2025-07-28
Accepted date: 2025-09-03
Online published: 2025-09-10
Supported by
National Natural Science Foundation of China(12472202);Open Project Program of National Key Laboratory of Strength and Structural Integrity(LSSIKFJJ202403014)
变刚度（VS）复合材料的刚度和强度性能具有较强的可定制性，因此在航空航天结构中具有较大的应用潜力。VS薄壁结构在热环境下的失稳问题不可忽视，研究了在不同温度环境下直线铺层及可制造的最优曲线铺层层合板和圆柱壳结构的热屈曲性能及其缺陷敏感度。首先，利用变保真度Kriging代理模型优化算法求解得到考虑最小曲率半径的最优铺层角度。其次，通过热环境下的静力分析及考虑初始缺陷的非线性屈曲分析研究了VS层合板和圆柱壳的热屈曲问题，同时对直线铺层和曲线铺层层合板与VS圆柱壳的缺陷敏感度进行了比较。结果表明，优化后的VS结构的线性屈曲载荷均大于直线铺层层合板。热应力会导致VS层合板的失稳总载荷下降，而对常规直线铺层层合板的影响较小；对于VS圆柱壳结构，在热应力作用下，其屈曲总载荷有一定提升；温度对层合板的缺陷敏感度影响较小，但会使圆柱壳结构的抗压缺陷敏感度增加。
关键词： 变刚度（VS）复合材料; 变保真度Kriging代理模型; 纤维角度优化; 热屈曲; 几何缺陷敏感度
孙瑀珩 , 郭玉杰 , 肖世杰 , 崔慧文 , 延浩 , 魏小辉 . 变刚度复材板壳结构优化及热环境下的屈曲[J]. 航空学报, 2026 , 47(6) : 232473 -232473 . DOI: 10.7527/S1000-6893.2025.32473
Variable-Stiffness （VS） composites have gained significant attention due to their tunable stiffness and strength properties. The instability issues of VS thin-walled structures in thermal environments cannot be ignored. The thermal buckling performance and geometric imperfection sensitivity of laminated plate and cylindrical shell structures with straight layups and manufacturable optimal curved fiber layups under different thermal environments are investigated. First， the optimal layup angles considering the minimum radius of curvature are obtained using an optimization algorithm based on a variable-fidelity Kriging surrogate model. Second， the thermal buckling problems of VS laminated plates and cylindrical shells are studied through static analysis and nonlinear buckling analysis considering thermal environments and initial imperfections. Comparisons are conducted between straight and curved fiber layup laminated plates and VS cylindrical shell considering their imperfection sensitivities. The results show that the linear buckling loads of the optimized VS structures are all greater than those of the straight layup laminated plates. Thermal stress leads to a reduction in the total instability load of VS laminated plates， while having a smaller impact on conventional straight layup laminated plates； for VS cylindrical shell structures， the total buckling load value increases slightly under thermal stress. Temperature has a minor effect on the imperfection sensitivity of laminated plates， while for cylindrical shell structures， temperature increases their compressive imperfection sensitivity.
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