变弯度机翼参数化气动弹性建模与颤振特性分析

doi:10.7527/S1000-6893.2022.27346

Abstract

Abstract:

The mass，stiffness，and damping characteristics of the morphing aircraft structure will change significantly during the morphing process to lead to incredible complexity of the aeroelastic effect. Efficient and accurate prediction of the flutter boundary is one of the challenging problems in the structural dynamics design of morphing aircraft. Existing nonparametric aeroelastic modeling methods can only analyze the flutter of a single morphing configuration，and repeated modeling is required for flutter calculation of morphing configuration，which may incur low computational efficiency and result in flutter boundary loss. This paper proposes a new parametric aeroelastic modeling for efficient flutter analysis of a wing with a continuously variable trailing edge. Based on the proposed aeroelastic modeling method，systematic analysis of parameter-varying flutter characteristics of a variable camber wing is investigated. To verify the accuracy of the parametric modeling method in parameter-varying flutter prediction，numerical calculation and comparative study were carried out in terms of parameter-varying modal characteristics， aerodynamic calculation and flutter prediction of variable camber wing. The simulation results indicate that the method proposed can efficiently and accurately predict parameter-varying flutter characteristics of morphing wing in the whole parameter space.

Key words: dynamics, morphing wing, aeroelasticity, vibration, flutter

CLC Number:

V215.3

Shijie YU, Xinghua ZHOU, Rui HUANG. Parametric aeroelastic modeling and flutter characteristic analysis of variable camber wing[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(8): 227346.

Figures/Tables 24

Fig. 1

Fig. 2

Table 1

Fig. 3

Fig. 4

Fig. 5

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Fig. 7

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Fig. 9

Fig. 10

Table 2

Fig. 11

Table 3

Parameters of wing segments

参数	数值
来流速度/（m·s^-1）	15
翼展/m	0.3
转轴距离	-1.0
$ω$ /（rad·s^-1）	45
空气密度/（kg·ms^-3）	1.225
半弦长/m	0.1
$a m a x$ /（°）	10

Table 3

Fig. 12

Fig. 13

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Fig. 15

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部位	弹性模量/GPa	厚度/mm	密度/（g·cm^-3）
蒙皮	71.7	1	2.8
翼梁、翼肋	71.7	1，2	2.0
柔性引导面	7	0.5	1.2

θ/（°）	1阶	2阶	3阶	4阶	5阶	6阶
0	1.000	1.000	1.000	1.000	1.000	1.000
5	1.000	0.997	0.999	1.000	1.000	0.998
10	1.000	0.999	1.000	1.000	1.000	0.996
15	1.000	1.000	1.000	1.000	1.000	1.000
20	1.000	1.000	1.000	1.000	1.000	0.999
25	1.000	1.000	1.000	1.000	1.000	0.999
30	1.000	1.000	1.000	1.000	1.000	1.000

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Parametric aeroelastic modeling and flutter characteristic analysis of variable camber wing

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