Geometrically nonlinear static aeroelastic analysis of composite morphing wing with corrugated structures

Tsushima, Natsuki; Yokozeki, Tomohiro; Su, Weihua; Arizono, Hitoshi

doi:10.1016/j.ast.2019.03.025

Cited by 61 publications

(12 citation statements)

References 18 publications

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“…Moreover, the flight speed could be increased by 83.4% whilst maintaining sufficient roll control. Tsushima et al [125] conducted a static nonlinear aeroelastic study on a composite morphing wing with a corrugated structure to achieve camber morphing. They developed an aeroelastic framework consisting of FEM for structural modeling and the UVLM for aerodynamic predictions.…”

Section: Aeroelastic Stabilitymentioning

confidence: 99%

Recent developments in the aeroelasticity of morphing aircraft

Ajaj

Parancheerivilakkathil

Amoozgar

et al. 2021

Progress in Aerospace Sciences

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Section: Aeroelastic Stabilitymentioning

confidence: 99%

Recent developments in the aeroelasticity of morphing aircraft

Ajaj

Parancheerivilakkathil

Amoozgar

et al. 2021

Progress in Aerospace Sciences

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“…The performance of generating lift force by a morphing flap was improved compared with one of conventional flap although the influence of nonlinear aerodynamic forces could not be considered in the potential solver. Tsushima et al developed an integrated aeroelastic analysis framework for dynamic analysis of morphing wing with corrugated structures (Tsushima et al, 2019b). The framework integrated the corotational shell finite element approach to consider geometrical nonlinearity, which was coupled with the unsteady vortex lattice method.…”

Section: Experiments and Numerical Analysis Of Morphing Aircraftmentioning

confidence: 99%

Recent researches on morphing aircraft technologies in Japan and other countries

Tsushima

Tamayama

2019

Mechanical Engineering Reviews

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Morphing aircraft technology has recently gained attention of many research groups by its potential for aircraft performance improvement and economic flight. Although the performance of conventional control surfaces is usually compromised in off-design flight conditions, the morphing technique may achieve optimal flight performance in various operations by to adaptively altering the wing shape during flight. This paper aims to provide a comprehensive review on morphing aircraft/wing technology, including morphing mechanisms or structures, skins, and actuation techniques as element technologies. Moreover, experimental and numerical studies on morphing technologies applying those elemental technologies are also introduced. Recent research on these technologies are particularly focused on in this paper with comparisons between developments in Japan and other countries. Although a number of experimental and numerical studies have been conducted by various research groups, there are still various challenges to overcome in individual elemental technologies for a whole morphing aircraft or wing systems. This review helps for researchers working in the field related to morphing aircraft technology to sort out current developments for morphing aircraft.

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“…Such tools are also applicable to the aeroelastic analysis of helicopter rotor blades and wind turbines. Recent research works related to aeroelastic analysis were conducted by Amoozgar et al [5], Vazhayil Thomas et al [6], Rajpal et al [7], Tsushima et al [8], Rong et al [9], Sommerwerk et al [10] and Qin et al [11]. It is with these developments in mind that the present work was undertaken.…”

Section: Introductionmentioning

confidence: 95%

On a Novel Approximate Solution to the Inhomogeneous Euler–Bernoulli Equation with an Application to Aeroelastics

Fleischmann

Könözsy

2021

Aerospace

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This paper focuses on the development of an explicit finite difference numerical method for approximating the solution of the inhomogeneous fourth-order Euler–Bernoulli beam bending equation with velocity-dependent damping and second moment of area, mass and elastic modulus distribution varying with distance along the beam. We verify the method by comparing its predictions with an exact analytical solution of the homogeneous equation, we use the generalised Richardson extrapolation to show that the method is grid convergent and we extend the application of the Lax–Richtmyer stability criteria to higher-order schemes to ensure that it is numerically stable. Finally, we present three sets of computational experiments. The first set simulates the behaviour of the un-loaded beam and is validated against the analytic solution. The second set simulates the time-dependent dynamic behaviour of a damped beam of varying stiffness and mass distributions under arbitrary externally applied loading in an aeroelastic analysis setting by approximating the inhomogeneous equation using the finite difference method derived here. We compare the third set of simulations of the steady-state deflection with the results of static beam bending experiments conducted at Cranfield University. Overall, we developed an accurate, stable and convergent numerical framework for solving the inhomogeneous Euler–Bernoulli equation over a wide range of boundary conditions. Aircraft manufacturers are starting to consider configurations with increased wing aspect ratios and reduced structural weight which lead to more slender and flexible designs. Aeroelastic analysis now plays a central role in the design process. Efficient computational tools for the prediction of the deformation of wings under external loads are in demand and this has motivated the work carried out in this paper.

show abstract

Geometrically nonlinear static aeroelastic analysis of composite morphing wing with corrugated structures

Cited by 61 publications

References 18 publications

Recent developments in the aeroelasticity of morphing aircraft

Recent developments in the aeroelasticity of morphing aircraft

Recent researches on morphing aircraft technologies in Japan and other countries

On a Novel Approximate Solution to the Inhomogeneous Euler–Bernoulli Equation with an Application to Aeroelastics

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