| 面内线性变化载荷作用复合材料层合板的振动与屈曲优化 |
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| 引用本文： | 孙士平,曾庆龙,胡政.面内线性变化载荷作用复合材料层合板的振动与屈曲优化[J].复合材料学报,2016,33(12):2860-2868. |
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| 作者姓名： | 孙士平 曾庆龙 胡政 |
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| 作者单位： | 南昌航空大学 航空制造工程学院, 南昌 330063 |
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| 基金项目： | 国家自然科学基金(11362017)，博士后科学基金(20110491693) |
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| 摘 要： | 采用广义微分求积(GDQ)法开展了不同边界条件下承受面内线性变化载荷作用复合材料层合板振动与屈曲的分析与优化。针对GDQ法求解面内线性变化载荷工况复合材料层合板屈曲问题存在计算振荡、不收敛现象,提出载荷扰动策略实现了GDQ法对复合材料层合板屈曲问题的稳定高效求解。基于基础圆频率和临界屈曲载荷系数的归一化指标,分析了铺层角度对复合材料层合板综合性能的影响,并结合直接搜索模拟退火算法开展了复合材料层合板的铺层顺序优化。结果表明:铺层角度变化对屈曲性能的影响明显强于频率特性;面内线性变化载荷中,以弯曲载荷作用下复合材料层合板的优化综合性能受边界条件变化的影响最小,而优化铺层角度受边界条件变化的影响最大。研究结果为复杂载荷作用下复合材料层合板的设计提供了参考。
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| 关 键 词： | 复合材料层合板 广义微分求积法 面内线性变化载荷 优化设计 屈曲 |
| 收稿时间： | 2015-12-09 |
Optimization of vibration and buckling for composite laminate under linearly varying in-plane loads |
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| SUN Shiping,ZENG Qinglong,HU Zheng.Optimization of vibration and buckling for composite laminate under linearly varying in-plane loads[J].Acta Materiae Compositae Sinica,2016,33(12):2860-2868. |
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| Authors: | SUN Shiping ZENG Qinglong HU Zheng |
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| Affiliation: | School of Aeronautical Manufacturing Engineering, Nanchang Hangkong University, Nanchang 330063, China |
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| Abstract: | Generalized differential quadrature (GDQ) method was used to analyze and optimize the vibration and buckling of composite laminate under different boundary conditions and linearly varying in-plane loads. Since GDQ method led to calculation oscillation and non-convergence for the case of buckling for composite laminate under linearly varying in-plane loads, load perturbation strategy was developed to achieve the stable and efficient computation of buckling for composite laminate by GDQ method. Influence of ply angle on the comprehensive performance of composite laminate was analyzed base on the normalized index of fundamental circle frequency and critical buckling load coefficient, while the stacking sequence of composite laminate was optimized by using the direction search simulated annealing algorithm. The results show that ply angle variation has greater effect on buckling performance than frequency. Boundary condition is the least one to affect the optimal comprehensive performance of composite laminate under the bending load in the family of linearly varying in-plane loads, on the contrary, the most dominant factor to affect the optimal ply angle. The study provides a reference for the design of composite laminate under complex loading. |
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| Keywords: | composite laminate generalized differential quadrature method linearly varying in-plane loads optimal design buckling |
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