Aeroelastic optimization of an aerobatic aircraft wing structure
Aeroelastic optimization of an aerobatic aircraft wing structure
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DOI：
10.1016/j.ast.2007.01.003
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发表时间：
2007-06
影响因子：
5.6
通讯作者：
Shijun Guo
中科院分区：
文献类型：
--
作者：
Shijun Guo
本文研究了某型飞机机翼结构的最小重量优化设计和气动弹性剪裁问题。首先，建立了原金属机翼和改进的复合材料翼盒结构的分析模型和有限元模型。为了验证数值模型，金属机翼盒的振动参数预测与实验结果进行了比较。还对不同尺寸金属和复合材料翼盒结构以及层合板铺层的应力预测结果进行了比较。其次，基于具有足够强度的最小重量复合材料翼盒模型，采用基于梯度的确定性优化方法，重点研究了翼盒的气动弹性剪裁。研究表明，通过优化机翼蒙皮和翼梁腹板层合板的纤维取向，复合材料翼盒的颤振速度可提高30%以上，且重量显著减轻。优化后的层合板进行了修整和增强，以满足制造和强度要求，颤振速度和较小的重量损失的妥协。
This paper aims at presenting an investigation into a minimum weight optimal design and aeroelastic tailoring of an aerobatic aircraft wing structure. Firstly, analytical and FE models were created for the original metallic wing and an improved composite wing box structures. In order to validate the numerical models, predicted vibration parameters of the metallic wing box were compared with the experimental results. Comparison was also made for the predicted stress results between the metallic and the composite wing box structures of different dimensions and laminate layups. Secondly, based on a minimum weight composite wing box model of adequate strength the investigation was focused on the aeroelastic tailoring of the wing box by employing the gradient-based deterministic optimization method. The study demonstrates that in addition to a significant weight saving, up to 30% increase of flutter speed for the composite wing box can be achieved by optimizing the fibre orientations of the wing skin and spar web laminates. The optimized laminates are trimmed and reinforced to meet the manufacture and strength requirements with little compromise of flutter speed and a minor weight penalty.