Aeroelastic optimization design of composite wing for large aircraft with panel stiffness matching
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摘要:
针对大型飞机复合材料机翼，发展了一种考虑壁板刚度匹配的气动弹性优化设计方法。基于敏度算法，以结构质量最小化为目标，以壁板刚度匹配、颤振速度、翼尖变形、设计许用值、工艺性等为约束，在严重载荷状态下设计复合材料机翼结构，研究不同壁板刚度匹配要求对于优化设计结果的影响，并与传统优化设计结果进行比较。结果表明：考虑壁板刚度匹配需要付出一定的结构质量，但对局部稳定性设计、损伤容限设计和大型复合材料壁板制造有利；壁板刚度匹配设计范围对于优化设计结果影响显著，需要根据设计和制造要求合理确定；压缩设计许用值是影响复合材料机翼气动弹性优化设计的关键约束。
Abstract:A method of aeroelastic optimization design with consideration of panel stiffness matching was developed for the composite wing of large aircraft. The optimization was performed based on the sensitivity algorithm, and the objective was to minimize the structural mass subject to the constraints of panel stiffness matching, flutter speed, deformation at wingtip, design allowable and manufacturability. The composite wings were designed in the case of critical load conditions. The influences of various panel stiffness matching requirements on optimal design results were studied and they were compared with the conventional optimal design results. The results indicate that the structural weight will increase with consideration of panel stiffness matching. However, it has an advantage in local buckling design, damage tolerance design and manufacturing of large composite panel. The optimal design results can be significantly affected by the design ranges of panel stiffness matching, so these design ranges should be properly determined according to the requirements of design and manufacturing. The design allowable of compression is a crucial constraint of the aeroelastic optimization design for composite wing.
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Key words:
- composite wing /
- panel stiffness matching /
- aeroelasticity /
- flutter /
- structural optimization
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图 3 复合材料机翼在严重载荷下的变形
Figure 3. Deformations of composite wings under critical load conditions
图 4 复合材料机翼上蒙皮压缩应变(Case1)
Figure 4. Compression strain of up skin for composite wing (Case1)
图 6 复合材料机翼下蒙皮屈曲稳定性分布
Figure 6. Buckling stability distribution of lower skin for composite wing
表 1 复合材料机翼优化结果在严重载荷下的变形
Table 1. Deformations of optimal results for composite wings under critical load conditions
刚度比约束 翼尖相对变形/% 翼尖扭角/(°) Case1 Case2 Case1 Case2 不考虑刚度比 9.07 -3.08 1.42 0.98 km∈[0.25, 0.5] 8.28 -2.82 1.33 0.90 km∈[0.5, 0.75] 8.66 -2.94 1.19 0.89 km∈[0.75, 1.0] 8.80 -2.98 1.25 0.92 
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表 2 复合材料机翼颤振速度
Table 2. Flutter speed of composite wings
刚度比约束 颤振速度/(m·s-1) 不考虑刚度比 407.8 km∈[0.25, 0.5] 423.1 km∈[0.5, 0.75] 407.4 km∈[0.75, 1.0] 406.9
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