大柔性机翼几何非线性结构降阶模型与气动弹性分析

doi:10.7527/S1000-6893.2024.30569

Abstract

Abstract:

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.

Key words: geometric nonlinearity, reduced-order model, aeroelasticity, nonlinear flutter, large flexible aircraft

CLC Number:

V211.47

Chao AN, Rui ZHAO, Changchuan XIE, Chao YANG. Reduced-order modeling and aeroelastic analysis of geometrically nonlinear structures of large flexible wings[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(S1): 730569.

Figures/Tables 28

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References 24

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参数	数值	参数	数值
展长/mm	1 000	弹性轴位置	50%弦线位置
质量/kg	0.613	弹性模量/GPa	219
弦长/mm	100	梁截面	35 mm×1.5 mm矩形

阶数	模态频率/Hz	地面试验频率/Hz	模态振型
1	1.179	1.18	垂直一弯
2	7.724	7.81	垂直二弯
3	22.19	22.35	垂直三弯
4	22.95	23.07	一阶扭转
5	27.47	27.63	水平一弯

工况参数	位移幅值/mm
工况参数	基于结构降阶模型	基于有限元方法	线性方法
风速10 m/s+阵风频率3 Hz	19.2	18.9	18.0
风速10 m/s+阵风频率4 Hz	11.3	11.2	9.8
风速12 m/s+阵风频率3 Hz	25.1	24.7	23.3
风速12 m/s+阵风频率4 Hz	13.0	13.2	11.0
风速14 m/s+阵风频率3 Hz	33.1	32.0	29.6
风速14 m/s+阵风频率4 Hz	17.2	16.8	13.9

工况参数	位移幅值/mm
工况参数	基于结构降阶模型	基于有限元方法	线性方法
风速10 m/s+阵风频率3 Hz	19.8	19.5	18.3
风速10 m/s+阵风频率4 Hz	10.1	10.0	8.9
风速12 m/s+阵风频率3 Hz	23.9	22.6	21.0
风速12 m/s+阵风频率4 Hz	15.2	14.7	13.4
风速14 m/s+阵风频率3 Hz	32.1	33.0	27.3
风速14 m/s+阵风频率4 Hz	16.6	15.9	13.6

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Reduced-order modeling and aeroelastic analysis of geometrically nonlinear structures of large flexible wings

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