Composite corrugated structures for morphing wing skin applications

Thill, C.; Etches, Julie A; Bond, Ian P; Potter, Kevin D; Weaver, Paul M.

doi:10.1088/0964-1726/19/12/124009

Cited by 153 publications

(114 citation statements)

References 17 publications

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“…Corrugated structures have been used in morphing structures (Thill et al, 2008(Thill et al, , 2010Shaw 2015) as well. Yokozeki et al (2014) and Takahashi et al (2016) developed a morphing wing with leading edge and trailing edge made of corrugated structures.…”

Section: Conceptsmentioning

confidence: 99%

Design and mechanical testing of a variable stiffness morphing trailing edge flap

Azarpeyvand²

2017

Journal of Intelligent Material Systems and Structures

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Morphing structures that are both light-weight and conformal to the aerofoil are currently being considered as promising candidates for the next generation of aircraft high-lift systems. Utilizing spatially variable stiffness materials in morphing structures leads to a possible reduction in the actuation energy requirement and also enables geometric control over the deformed shape of the morphing structure, resulting in enhanced aerodynamic and aeroacoustic performance. In this study, a design optimization methodology has been developed to identify the required material stiffness variations of a morphing structure for target optimal deformed shapes. In the optimization scheme, a layer-wise sandwich beam model is used to predict the structural behaviour of the flap with a specific material stiffness variation. Two-dimensional fluid/structure static aeroelastic interaction analysis is performed in the design optimization. Finite element analysis and mechanical tests were also carried out for a chosen optimization result to study the actuation requirements and the capability of control over the deformed shape of the morphing trailing edge. Numerical and experimental results confirm the feasibility of the proposed optimization methodology for identifying the required stiffness variation in the core and also ways of using rapid prototyped honeycomb core to realize the honeycomb core stiffness variations are discussed.

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Section: Conceptsmentioning

confidence: 99%

Design and mechanical testing of a variable stiffness morphing trailing edge flap

Azarpeyvand²

2017

Journal of Intelligent Material Systems and Structures

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“…Recent advancements in additive manufacturing and 4D printing [1,2] facilitate the fabrication of these structures with wide-ranging architectures and geometries. Such progress renders plates and shells, including sandwich and reinforced structures, particularly attractive for many applications in lightweight construction, aerospace and automotive engineering, naval architecture and marine engineering, nanotechnology, biomedical engineering and sports equipment, e.g [3][4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Asymptotic homogenization for modeling of wingbox structures

Hadjiloizi

2018

2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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The asymptotic homogenization technique has been used to analyze a wing box structure consisting of trapezoidally arranged reinforcements encased within thin rectangular plates. Ignoring stress concentration effects at the region of the overlap between the various components, the wingbox structure can be analyzed by handling each constituent independently from each other. To this end, a simpler structure was first considered which was made up of a base plate and a single stiffener web; the results were then extrapolated to those of the wingbox structure via superposition by adding in the contributions of each constituent of the overall unit cell. The work culminated in closed-form expressions for the effective in-plane elastic coefficients of the wingbox. This result demonstrates the attractiveness of the methodology in that it can be used in engineering analysis and design to customize the architecture of a thin-walled reinforced composite by changing some material or geometrical parameters of interest. Such parameters could be the material of the base plate, the spatial arrangement of the reinforcements, the relative sizes of the different constituents.

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“…stiff direction) coincide with chord direction and span direction of the wing, respectively. Several researches on morphing structures using corrugated structures follow recently [19][20][21][22]. It is expected that this structural concept is useful for realizing the variable camber airfoil or the conformal trailing edge control surface [23].…”

Section: Introductionmentioning

confidence: 99%