A review of modelling and analysis of morphing wings

The technological advances, mainly in the development of new materials, recovered the interest in the application of morphing wings in aircraft. Due to the potential of replacing conventional control surfaces by morphing surfaces, the present work presents the modeling of aerodynamics, dynamics and control design of an aircraft with morphing wings. The morphing concept is given by changing the camber of the trailing edge along the wingspan. For aerodynamics modeling, it was adopted unsteady strip theory and, for dynamics modeling, it was used rigid body mechanics, considering the displacement of the center of mass and the time-varying inertia tensor. Finally, control design is performed using Exponential Mapping Controller (EMC) method. The results showed that, for the adopted variable geometry configuration, the influence of the center of mass displacement and the inertia variation on the aircraft behavior were insignificant, whereas the influences of the unsteady aerodynamics were significant. Consideration of the unsteady aerodynamic effects increases the magnitude of the aircraft movements, necessitating a greater control action.

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“…For the profile change, [6] presents two distinctions for variations in arching, leading edge variation and trailing edge variation.…”

Section: 3384/ecp19162002mentioning

confidence: 99%

Modeling, Simulation and Control of an Aircraft with Morphing Wing

Luz

Schinestzki

Souza

et al. 2019

Proceedings of the 10th Aerospace Technology Congress, October 8-9, 2019, Stockholm, Sweden

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“…2 Also, the noise of fixed wings can be suppressed largely if continuous skins are covered on the slats and flaps. 3 Many research studies have been carried out to analyze the aerodynamic characteristics of morphing wings. Burnazzi and Radespiel evaluated the aerodynamics of flexible droop noses, which can reduce the Coanda flap blowing power and increase the attack angle of maximum lift coefficient (Cl).…”

Section: Introductionmentioning

confidence: 99%

Design of compliant mechanism-based variable camber morphing wing with nonlinear large deformation

Zhang

et al. 2019

International Journal of Advanced Robotic Systems

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The morphing wing with large deformation can benefit its flight performance a lot in different conditions. In this study, a variable camber morphing wing with compliant leading and trailing edges is designed by large-displacement compliant mechanisms. The compliant mechanisms are carried out by a hyperelastic structure topology optimization, based on a nonlinear meshless method. A laminated leading-edge skin is designed to fit the curvature changing phenomenon of the leading edge during deformation. A morphing wing demonstrator was manufactured to testify its deformation capability. Comparing to other variable camber morphing wings, the proposal can realize larger deflection of leading and trailing edges. The designed morphing wing shows great improvement in aerodynamic performance and enough strength to resist aerodynamic and structural loadings.

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“…Their aim was not to provide an alternative to a discrete control surface but to morph the entire camber of the aerofoil. Even more recently, the same technology was used to optimise the aerodynamics by changing the wing geometry for the different flight phases [18].…”

Section: Introductionmentioning

confidence: 99%

High-Bandwidth Morphing Actuator for Aeroelastic Model Control

2019

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The design and testing of a high-bandwidth continuous actuator for aeronauticalapplications is presented hereinafter. The actuator has a dual goal of controlling both the aeroelasticbehaviour and the flight mechanics of the model in which it is installed. In order to achieve theseaims, the actuation bandwidth of the active aerofoil, as well as its static camber variation, have to besufficiently high. The camber morph is achieved by using tailored piezoelectric patches in a sandwichconfiguration with a linear trailing edge slider to allow the necessary compliance. The morphingactuator is designed for a NACA 0018 aerofoil with a chord of 300mmand a span of 40 mm. Static anddynamic experimental tests are carried out on a prototype, and a camber variation control techniqueis implemented. It is proved that the actuator bandwidth is up to 25 Hz and the equivalent maximumdeflection is 15 degrees. This solution is shown to be a viable light-weight alternative to theconventional brushless/servo-motor approach currently used in aeroelastic models.

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A review of modelling and analysis of morphing wings

Cited by 228 publications

References 127 publications

Modeling, Simulation and Control of an Aircraft with Morphing Wing

Modeling, Simulation and Control of an Aircraft with Morphing Wing

Design of compliant mechanism-based variable camber morphing wing with nonlinear large deformation

High-Bandwidth Morphing Actuator for Aeroelastic Model Control

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