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在给定全复合材料机翼结构几何外形尺寸条件下,以最高载荷/质量比(P/W)为目标,提出了一种复合材料机翼铺层优化设计与分析方法。主要进行了三方面优化工作:铺层厚度优化、铺层比例优化以及铺层顺序优化。首先,在初始结构方案的基础上,利用有限元分析软件ANSYS对复合材料层合板进行结构优化,得到了复合材料层合板铺层厚度与铺层比例。然后,插值拟合生成结构性能(即P/W)在设计区域的空间分布曲面,量化材料分布对结构性能的影响,得到了最佳材料分配比例,为分析复合材料铺层提供了新方法。最后,根据已经得到的铺层厚度和铺层比例方案,运用遗传算法对铺层顺序进行优化,得到最优铺层方案。根据最终优化的铺层设计方案,加工制造机翼样件并完成了试验验证。数值模拟结果与试验结果非常吻合,其中,破坏载荷的相对误差为-1.91%,结构刚度的相对误差为1.10%。与初始设计相比,载荷/质量比提高了70.23%(忽略翼梢小翼),证明本文优化工作的合理性与有效性。
Aiming at the maximum load / mass ratio (P / W), a composite wing optimization design and analysis method is proposed given the geometrical dimensions of all-composite wing structure. Mainly carried out three aspects of optimization work: optimization of ply thickness, ply ratio optimization and ply order optimization. First of all, based on the initial structure scheme, the structural optimization of the composite laminates was carried out by using the finite element analysis software ANSYS, and the composite laminates thickness and lay-up ratio were obtained. Then, interpolation fitting results in the spatial distribution of the structural properties (P / W) in the design area, and the effect of the material distribution on the structure performance is quantified. The optimal material distribution ratio is obtained, which provides a new method for analyzing the composite material ply. Finally, according to the obtained ply thickness and ply ratio scheme, genetic algorithm is used to optimize ply sequence to get the optimal ply scheme. According to the final optimization of the ply design, processing and manufacturing wing prototype and completed the test verification. The numerical simulation results are in good agreement with the experimental results. The relative error of failure load is -1.91% and the relative error of structural stiffness is 1.10%. Compared with the original design, the load / mass ratio increased by 70.23% (ignoring wingtips), which proves the rationality and effectiveness of the optimization work in this paper.