变形翼可调泊松比柔性蒙皮力学特性分析

doi:10.7527/S1000-6893.2022.27748

Abstract

Abstract:

To satisfy the requirements of in-plane large deformation and out-of-plane high bearing capacity for flexible skin imposed by the morphing wing of aerospace vehicle in realizing continuous variable span-wise bend， span-wise torsion， and sweep， we propose a hybrid metastructure skin structure with tunable Poisson’s ratio. This structure consists of a hybrid metastructure composed of a concave hexagon and a quadrangular star cell， with a flexible surface bonded on both sides. Based on the theory of beam buckling， the theoretical model of the relative elastic modulus in x and y directions and Poisson’s ratio in the xy plane of the hybrid metastructure cell is established. The accuracy of the theoretical model is verified by the relative errors of the theoretical and simulation results which is not greater than 10%. The effects of cell geometry parameters on the relative elastic modulus and Poisson’s ratio in the xy plane are studied. The results show that the thickness of the cell wall exhibits the largest effect on both， followed by the length of the horizontal cell wall， while the inner angle of the quadrangular star has the least effect on both. The in-plane deformation capacity of the metastructure is studied. The comparative analysis of the specific stiffness of four different metastructures shows that the new hybrid metastructure has more advantages in the specific stiffness within a certain range of cell angles. The results provide a theoretical basis for the application of morphing wing skin of high-speed aircraft.

Key words: aerospace vehicle, morphing wing, flexible skin, metastructure, Poisson's ratio

CLC Number:

V250.3

Songcheng JIANG, Hui YANG, Yan WANG, Hong XIAO, Yongbin LIU, Chuanyang LI. Analysis of mechanical characteristics of flexible skin with tunable Poisson's ratio for morphing wing[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(13): 227748-227748.

Figures/Tables 19

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Table 1

Comparison between theoretical results and simulation results

θ₁/（°）	相对弹性模量E_y /E_s			泊松比 $ν y x$			相对弹性模量E_x /E_s
θ₁/（°）	理论值	仿真值	E_r/%	理论值	仿真值	E_r/%	理论值	仿真值	E_r/%
6	0.015 65	0.015 36	-1.909	-1.304 7	-1.436 2	9.150	0.001 15	0.001 08	-6.643
8	0.011 32	0.010 98	-3.094	-1.229 0	-1.332 0	7.735	0.001 16	0.001 09	-6.248
10	0.008 41	0.008 10	-3.786	-1.098 3	-1.178 9	6.836	0.001 16	0.001 10	-5.891
20	0.002 91	0.002 84	-2.329	-0.550 5	-0.561 4	1.934	0.001 28	0.001 23	-4.336
30	0.001 61	0.001 60	-0.860	-0.261 5	-0.262 3	0.309	0.001 57	0.001 52	-3.52
40	0.001 21	0.001 23	1.299	-0.090 1	-0.091 6	1.638	0.002 19	0.002 11	-3.690
50	0.001 20	0.001 23	2.254	0.020 2	0.021 2	5.135	0.003 60	0.003 42	-5.137
60	0.001 62	0.001 68	3.584	0.087 3	0.087 2	-0.172	0.007 39	0.006 82	-8.318

Table 1

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Analysis of mechanical characteristics of flexible skin with tunable Poisson's ratio for morphing wing

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