基于复合材料弹性周期结构和预应力蒙皮的变弦长机翼

doi:10.7527/S1000-6893.2024.30966

Abstract

Abstract:

A variable chord wing based on composite material elastic periodic structure and flexible skin is designed using NACA0014 profile. According to the requirement of structure stiffness， the concept of pre-morphing is introduced. The non-mechanical high variable chord length is realized， while ensuring the structure strength and stiffness. The disadvantages of heavy weight and complex drive of traditional morphing mechanism are avoided. A finite element model of the wing is built， and the maximum chord morphing amplitude is given based on static strength analysis. An aerodynamic analysis model of the wing is established， and the aerodynamic performance of the wing is calculated at different morphing states. The pre-morphing analysis is done according to stiffness requirement in the normal direction. The strength， stiffness and stability of the morphing wing structure are checked in the heavy load case and economical cruise case. The initial damage mode and ultimate load factor of the wing structure are predicted through overload calculation. The normal mode analysis and transient analysis of the morphing wing are completed， and the basic dynamic performance is given. It is shown that the variable chord wing based on symmetrical double ripple elastic periodic structure has simple structure and activation mechanism. During chord morphing， the streamline and smooth wing surface are maintained， and the strength， stiffness and stability of the morphing wing meet the design requirements. The maximum stretch amplitude of the elastic periodic structure is 140 mm， which is 58.33% of the initial chord length of periodic structure and 23.33% of the initial wing chord length. The maximum safety angle of attack and the optimum angle of attack of the initial and maximum morphing states of the wing is 12° and 8°， respectively. The lift of the maximum morphing state is higher than that of the initial states by 22.89%. The stiffness issue in Y direction is satisfied through the pre-stressed silicon rubber skin with the pre-chord-morphing of 16 mm. The initial damage of the periodic structure occurs when the aerodynamic load increases up to 1.96 times of the static strength heavy load， and the damage mode is fiber tensile failure. The first and second order normal modes of the maximum morphing state are vertical and horizontal bending， respectively. The displacement kinetic convergence of the morphing wing occurs in 2 s when gust load is encountered during level flight.

Key words: composite material, elasticity, periodic structure, pre-stressed skin, morphing, wing

CLC Number:

V224

Feng LIU, Sen YANG, Zhenpeng WEI. Variable chord wing based on composite material elastic periodic structure and pre-stressed skin[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(7): 230966.

Figures/Tables 28

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Table 9

Modal frequency of the wing

阶次	1	2	3	4	5	6
频率/Hz（ $Δ L$ =16 mm）	5.165	8.221	16.247	20.980	25.346	27.523
频率/Hz（ $Δ L$ =140 mm）	56.682	68.587	92.370	113.23	125.79	139.89

Table 9

Fig.18

Fig.19

References 20

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参数	数值
波纹宽度/mm	10
波纹厚度/mm	0.72
翼肋从左至右第1个波纹高度/mm	27
翼肋从右至左第1个波纹高度/mm	11

参数	数值	参数	数值
纵向弹性模量/MPa	38 360	纵向抗拉强度/MPa	450
横向弹性模量/MPa	38 360	纵向抗压强度/MPa	550
泊松比	0.26	横向抗拉强度/MPa	450
1-2面内剪切模量/MPa	4 140	横向抗压强度/MPa	550
1-3面内剪切模量/MPa	4 140	纵向剪切强度/MPa	45
2-3面内剪切模量/MPa	1 312	横向剪切强度/MPa	45

参数	数值	参数	数值
纵向弹性模量/MPa	62 400	纵向抗拉强度/MPa	655
横向弹性模量/MPa	62 400	纵向抗压强度/MPa	621
泊松比	0.33	横向抗拉强度/MPa	655
1-2面内剪切模量/MPa	3 140	横向抗压强度/MPa	621
1-3面内剪切模量/MPa	3 140	纵向剪切强度/MPa	128
2-3面内剪切模量/MPa	1 312	横向剪切强度/MPa	128

部件名称	铺设角度
前/后缘翼肋	［0°/45°］_s
主梁	［0°/45°/0°/45°］_s
后梁	［0°/45°/0°/45°］_s
固定/刚性段蒙皮	［0°/45°］
弹性周期结构翼肋波纹结构	［0°/45°/0°］_s
弹性周期结构局部加强构件	［0°/45°/0°/45°］_s

工况	损伤模式	损伤值	载荷倍数
工况1	纤维拉伸损伤	1.000	1.96
工况2	纤维拉伸损伤	1.000	1.56

Variable chord wing based on composite material elastic periodic structure and pre-stressed skin

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Figures/Tables 28

References 20

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阶次	1	2	3	4	5	6
特征值（预变体）	2.041	2.047	-2.090	-2.097	2.113	2.119
特征值（工况1）	9.371	9.373	-9.383	9.417	9.427	-9.432
特征值（工况2）	7.352	7.354	7.355	7.359	-7.361	-7.362

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