大柔性机翼几何非线性结构降阶模型与气动弹性分析
收稿日期: 2024-04-22
修回日期: 2024-05-14
录用日期: 2024-06-24
网络出版日期: 2024-06-25
基金资助
中国科学技术协会青年人才托举工程(YESS20230417);北京市科学技术协会青年人才托举工程(BYESS2023345)
Reduced-order modeling and aeroelastic analysis of geometrically nonlinear structures of large flexible wings
Received date: 2024-04-22
Revised date: 2024-05-14
Accepted date: 2024-06-24
Online published: 2024-06-25
Supported by
Young Elite Scientists Sponsorship Program by CAST(YESS20230417);Young Elite Scientists Sponsorship Program by BAST(BYESS2023345)
几何非线性气动弹性问题是大柔性飞行器设计中的关键问题，准确的大变形结构建模是几何非线性气动弹性分析的基础。相比非线性有限元方法，降阶模型具有阶次低、求解快的优势，但传统的结构模态建模方法并不适用于非线性结构。针对大柔性飞行器机翼，以结构模态作为基底建立非线性结构降阶模型，利用“非侵入式”方式求解非线性刚度系数，补充残量基函数提高结构变形计算精度，计算结果与非线性有限元方法对比具有很好的一致性。结合曲面涡格法建立几何非线性气动弹性分析框架，进行几何非线性静气动弹性变形、颤振及阵风响应分析。结果表明，几何非线性因素对于大柔性机翼气动弹性特性具有重要影响，基于非线性结构降阶模型建立的气动弹性分析方法能够兼顾分析精度、计算效率及复杂模型适用性。
安朝 , 赵睿 , 谢长川 , 杨超 . 大柔性机翼几何非线性结构降阶模型与气动弹性分析[J]. 航空学报, 2024 , 45(S1) : 730569 -730569 . DOI: 10.7527/S1000-6893.2024.30569
Geometrically nonlinear aeroelastic problems are key issues in the design of large flexible aircrafts， and accurate modeling of large deformation structures is the basis for geometrically nonlinear aeroelastic analysis. Compared with the nonlinear finite element method， the reduced order model has the advantages of low order and fast solution， but the traditional structural modal modeling method is not applicable to nonlinear structures. For a large flexible aircraft wing， a nonlinear structural reduced-order model is established with the linear structural mode as the base. Nonlinear stiffness coefficients are solved in a “non-intrusive” way， and residual basis functions are supplemented to improve the accuracy of structural deformation calculation. The calculation results are in good agreement with the results of the nonlinear finite element method. A geometrically nonlinear aeroelastic analysis framework is established by using the non-planar vortex lattice method， and the geometrically nonlinear static aeroelastic deformation， flutter and gust response are analyzed. The results show that the geometric nonlinear factors have an important influence on the design of large flexible wings， and the aeroelastic analysis method based on the nonlinear structural reduced-order model can take into account the analysis accuracy， computational efficiency， and applicability of complex models.
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