Design of wing mechanism with variable camber based on cross-spring flexural pivots

doi:10.3785/j.issn.1008-973X.2022.03.003

Journal of ZheJiang University (Engineering Science)

2022, Vol. 56

Issue (3): 444-451, 509 DOI: 10.3785/j.issn.1008-973X.2022.03.003

Design of wing mechanism with variable camber based on cross-spring flexural pivots

Jun-heng XU1,2(

),Xiao-jun YANG1,*(

),Bing LI1

1. School of Mechanical Engineering and Automation, Harbin Institute of Technology Shenzhen Graduate School, Shenzhen 518000, China
2. Shanghai Institute of Aerospace System Engineering, Shanghai 201108, China

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Abstract

In order to design airfoil mechanism with continuous variable camber, a morphing wing structure and modeling analysis was proposed by using flexible trailing edge mechanism and rigid connecting rod driving mechanism. The wing mechanism was based on cross-spring flexural pivots. The theoretical mechanics model of the flexible trailing edge mechanism was established by using chained beam constraint model, and the relationship between the force and deformation of the mechanism was also obtained. Then, compared the theoretical mechanics model with finite element model. On the basis of the mechanical model, In order to improve the aerodynamic characteristics of the wing mechanism, NSGA-II multi-objective genetic algorithm was used to optimize the dimension parameters of the mechanism. After optimization, the lift-drag ratio of the morphing wing in cruise stage is increased by 1.09%, and the lift coefficient in takeoff stage is increased by 2.54%. The deformation precision and deformation range of the airfoil mechanism were tested by experiments.

Key words： variable camber wing flexible mechanism chained beam constraint model multi-objective optimization aerodynamic performance

Received: 21 April 2021 Published: 29 March 2022

CLC:

V 224

Fund: 深圳市国际合作研究资助项目（GJHZ20170313113529978）

Corresponding Authors: Xiao-jun YANG E-mail: xujunheng0704@163.com;yangxiaojun@hit.edu.cn

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Cite this article:

Jun-heng XU,Xiao-jun YANG,Bing LI. Design of wing mechanism with variable camber based on cross-spring flexural pivots. Journal of ZheJiang University (Engineering Science), 2022, 56(3): 444-451, 509.

URL:

https://www.zjujournals.com/eng/10.3785/j.issn.1008-973X.2022.03.003 OR https://www.zjujournals.com/eng/Y2022/V56/I3/444

基于交叉簧片式铰链的变弯度机翼机构设计

为了研究机翼弦向连续变弯度的设计问题，提出由柔性后缘机构与刚性连杆驱动机构组成的机翼变弯度设计方案以及建模分析方法. 基于交叉簧片式柔性铰链设计机翼机构构型. 采用链式梁约束建模方法，建立柔性后缘机构的理论力学模型，得到其受力和变形的关系，并利用有限元仿真对理论力学模型进行验证. 在力学模型的基础上，采用NSGA-II多目标遗传算法优化机翼机构的相关尺寸参数，提升机翼的气动特性. 经优化，机翼巡航阶段的升阻比提升1.09%，起降阶段的升力系数提高2.54%. 经实验验证了设计的变弯度机翼机构变弯度的精度和变弯度的范围.

关键词： 变弯度机翼, 柔性机构, 链式梁约束建模方法, 多目标优化, 气动性能

Fig.1 Schematic diagram of wing layout

Fig.2 Overall schematic diagram of variable camber wing

Fig.3 Flexible trailing edge and sub element of wing

Fig.4 Driving mechanism model diagram

Fig.5 Parameter definition of flexible trailing edge sub element

Fig.6 Stress diagram of flexible trailing edge

Fig.7 Diagram of force and deformation of sub unit

Tab.1 Shape and geometric parameters of flexible trailing edge sub element

Fig.8 Comparison of results when flexible trailing edge subjected to bending moment

Fig.9 Comparison of results when flexible trailing edge subjected to longitudinal load

Fig.10 Flow chart of optimization algorithm

Fig.11 Schematic diagram of optimization results

Fig.12 Airfoil diagram at optimized design point

Tab.2 Optimization design variable results

Fig.13 Driving mechanism diagram

Fig.14 Wing trailing edge trajectory

Fig.15 Parameter definition of flexible trailing edge sub element

Fig.16 Experimental results of deformation accuracy

Fig.17 Deformation range experimental results


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