大型飞机机翼典型盒段后屈曲分析与验证

Analysis and Verification for Post-buckling of Large Aircraft Typical Wing-box

大型飞机机翼盒段结构静强度问题复杂,开展典型盒段稳定性研究,对机翼结构优化设计和降低研制成本具有重要意义。由于材料非线性和结构几何缺陷,对机翼典型盒段进行了后屈曲仿真分析,并通过破坏试验进行对比验证。结果表明,机翼典型盒段后屈曲仿真分析的失稳载荷和承载能力与试验值误差在5%以内,预测的破坏模式与试验结果相似,可为大型飞机机翼结构稳定性设计提供参考。

The static strength of the aircraft wing-box structure is complex, so it is of great significance to study the stability of typical box structure for optimizing wing structure and reducing development cost. According to the material nonlinearity and geometric defects, the post-buckling simulation analysis of the typical wing-box is carried out, and the comparison and verification are carried out through the failure test. The results show the error of the post-buckling load and load-carrying capacity of the typical wing-box is within 5% of the experimental value, and the predicted failure mode is similar to the experimental result, which can provide a reference for the structural stability design of large aircraft wings.