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
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.
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.
Fig.2Overall schematic diagram of variable camber wing
Fig.3Flexible trailing edge and sub element of wing
Fig.4Driving mechanism model diagram
Fig.5Parameter definition of flexible trailing edge sub element
Fig.6Stress diagram of flexible trailing edge
Fig.7Diagram of force and deformation of sub unit
子单元编号
L/mm
T/mm
W/mm
λ
α/（°）
1
55.43
3.000
15
0.127
30
2
44.34
2.400
15
0.127
30
3
35.47
1.920
15
0.127
30
4
28.38
1.536
15
0.127
30
Tab.1Shape and geometric parameters of flexible trailing edge sub element
Fig.8Comparison of results when flexible trailing edge subjected to bending moment
Fig.9Comparison of results when flexible trailing edge subjected to longitudinal load
Fig.10Flow chart of optimization algorithm
Fig.11Schematic diagram of optimization results
Fig.12Airfoil diagram at optimized design point
飞行阶段
θ1/(°)
θ2/(°)
θ3/(°)
θ4/(°)
Fx/N
Fy/N
状态1）不考虑气动力 状态1）考虑气动力 状态2）不考虑气动力 状态2）考虑气动力
2.3
1.2
2.0
3.8
0
5.8
2.0
1.6
2.5
2.8
?198
46.0
4.6
2.5
4.0
7.5
0
12.0
4.6
2.6
4.0
9.2
?58
26.0
Tab.2Optimization design variable results
Fig.13Driving mechanism diagram
Fig.14Wing trailing edge trajectory
Fig.15Parameter definition of flexible trailing edge sub element
Fig.16Experimental results of deformation accuracy
Fig.17Deformation range experimental results
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