A morphing leading edge, based on the compliant mechanism, is a novel concept which can improve the aerodynamic performance of aircraft for different missions. This can obviously reduce the weight and enhance the aircraft’s fuel efficiency. A simultaneous optimization of topology and fiber orientations for a composite leading edge has been achieved in the paper. It mainly included two steps. Initially, the lamination parameters and density were taken as design variables to determinate the fiber angles and topology, respectively. The least squares between the actual and desired displacements at key points were set as the objective function. Under the volume constraints, the combined optimization model of the leading edge was built to simultaneously obtain the optimal lamination parameters and topology shape. Then the optimal fiber angles were matched with the optimal lamination parameters by transforming the nonlinear equations to the least squares optimization. The physical model of the composite leading edge and experiments for it were manufactured and designed. The morphing capability of the composite’s compliant leading edge was investigated through simulation and experiments.
VasistaSTongLYWongKC.Realization of morphing wings a multidisciplinary challenge. J Aircraft2012;
49: 11–28.
2.
RudenkoAHannigAMonnerHPet al.
Extremely deformable morphing leading edge: optimization, design and structural testing. J Intel Mat Syst Str2018;
29: 764–773.
3.
BeniniEMagriniA.Aerodynamic optimization of a morphing leading edge airfoil with a constant arc length parameterization. J Aerosp Eng2018;
31: 04017093-1.
4.
TakahashiHYokozekiTHiranoY.Development of variable camber wing with morphing leading and trailing sections using corrugated structures. J Intel Mat Syst Str2016;
27: 2824–2836.
5.
WissaACalogeroJWereleyNet al.
Analytical model and stability analysis of the leading edge spar of a passively morphing ornithopter wing. Bioinspir Biomim2015;
10: 065003.
6.
JhaAKKudvaJN. Morphing aircraft concepts, classifications, and challenges. In: Smart structures and materials 2004: industrial and commercial applications of smart structures technologies, California, USA, 2004.
7.
SunRChenGChenZet al.
Multidisciplinary design optimization of adaptive wing leading edge. Sci China Technol Sci2013;
56: 1790–1797.
8.
SoflaAYNMeguidSATanKTet al.
Shape morphing of aircraft wing status and challenges. Mater Design2010;
31: 1284–1292.
9.
OhsakiMTsudaSWatanabeH.Optimization of retractable structures utilizing bistable compliant mechanism. Eng Struct2013;
56: 910–918.
10.
CulpepperMLAndersonG.Design of a low-cost nano-manipulator which utilizes a monolithic, spatial compliant mechanism. Precis Eng2004;
28: 469–482.
11.
LuharukaRHeskethPJ.Design of fully compliant, in-plane rotary, bistable micromechanisms for MEMS applications. Sensor Actuat A-Phys2007;
134: 231–238.
12.
HuangXLiYZhouSet al.
Topology optimization of compliant mechanisms with desired structural stiffness. Eng Struct2014;
79: 13–21.
13.
KotaS. System for varying a surface contour. U.S. Patent Nos. 5971328 and 6491262.
14.
KotaSHetrickJOsbornRet al. Design and application of compliant mechanisms for morphing aircraft structures. In: Smart structures and materials 2003: industrial and commercial applications of smart structures technologies, California, USA, 2003.
15.
LuKKotaS.Design of compliant mechanisms for morphing structural shapes. J Intel Mat Syst Str2003;
14: 379–391.
16.
LuKKotaS.An effective method of synthesizing compliant adaptive structures using load path representation. J Intel Mat Syst Str2005;
16: 307–317.
17.
LuKKotaS.Topology and dimensional synthesis of compliant mechanisms using discrete optimization. J Mech Des2006;
128: 1080–1091.
18.
HetrickJOsbornRKotaSet al. Flight testing of mission adaptive compliant wing. In: The 48th structural dynamics and materials conference, Honolulu Hawaii, USA, 2007.
19.
PoduguPAnanthasureshGK.Topology optimization-based design of a compliant aircraft wing for morphing leading and trailing edges. Am Soc Mech Eng2012;
21: 732–738.
20.
YinLAnanthasureshGK.Topology optimization of compliant mechanisms with multiple materials using a peak function material interpolation scheme. Struct Multidiscip O2001;
23: 49–62.
21.
LiDZhangXGuanYet al. Topology optimization of compliant mechanisms with anisotropic composite materials. In: IEEE mechatronics and automation conference. Xi'an, China, 2010.
22.
TongXGeWZhangY.Topology optimization of compliant mechanisms with curvilinear fiber path laminated composites. P I Mech Eng C-J Mec2016;
230: 3101–3110.
23.
TongXGeWSunCet al.
Topology optimization of compliant adaptive wing leading edge with composite materials. Chin J Aeronaut2014;
27: 1488–1494.
24.
SellittoARiccioARussoAet al.
Compressive behaviour of a damaged omega stiffened panel: damage detection and numerical analysis. Compos Struct2019;
209: 300–316.
25.
LoughlanJ.The buckling of composite stiffened box sections subjected to compression and bending. Compos Struct1996;
35: 101–116.
26.
RiccioADamianoMRaimondoAet al.
A fast numerical procedure for the simulation of inter-laminar damage growth in stiffened composite panels. Compos Struct2016;
145: 203–216.
27.
DegenhardtR.Stability of composite stringer-stiffened panels in book stability and vibrations of thin-walled composite structures.
Cambridge:
Woodhead Publishing, 2017.
28.
WangY.Mechanics and structural design of composite materials.
Shanghai:
East China University of Science and Technology Press, 2012.
29.
IJsselmuidenSTAbdallaMMGürdalZ.Optimization of variable stiffness panels for maximum buckling load using lamination parameters. AIAA J2010;
48: 134–143.
30.
SetoodehSAbdallaMMGurdalZ.Design of variable–stiffness laminates using lamination parameters. Compos Part B-Eng2006;
37: 301–309.
31.
TongXGeWGaoXet al. Optimization of combining fiber orientation and topology for constant-stiffness composite laminated plates. J Optim Theory Appl. DOI: 10.1007/s10957-018-1433-z.
