Nonlinear flutter of composite panels under yawed supersonic flow using finite elements

Abdel-Motaglay, K.; Chen, R.; Mei, C.

doi:10.2514/3.14284

Cited by 2 publications

(3 citation statements)

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“…The nonlinear finite element formulation, introduced by Mei [1], was the basis on which Dixon and Mei [2], Xue and Mei [3] and Abdel-Motagaly et al [4] built their finite element models to analyse the flutter boundary, the limit cycle and the thermal problems, with the extension to random loading and SMA embedding studied by Zhong [5].…”

Section: Introductionmentioning

confidence: 99%

“…They studied the effect of the temperature elevation on the critical dynamic pressure as well as the buckling temperature variation under different dynamic pressure conditions. Abdel-Motagaly et al [4] studied the effect of flow direction on the panelflutter behaviour using first-order shear deformation theory for laminated composite panels.…”

Section: Introductionmentioning

confidence: 99%

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Thermal post-buckling and aeroelastic behaviour of shape memory alloy reinforced plates

Tawfik

Mei

2002

Smart Mater. Struct.

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A novel concept is proposed: the use of shape memory alloy (SMA) to reduce panel thermal deflection and flutter responses. SMA has a unique ability to recover large pre-strains completely when the alloy is heated above the austenite finish temperature Af. The transformation austenite start temperature As for nitinol can be anywhere between -60 °F (-50 °C) and +340 °F (+170 °C) by varying the nickel content. During the recovery process, a large tensile recovery stress occurs if the SMA is restrained. The shape memory effect phenomenon is attributed to a change in crystal structure known as a reversible austenite to martensite phase transformation. This solid-solid phase transformation also gives a large increase in Young's modulus and yield stress. In this paper, a panel subject to the combined aerodynamic and thermal loading is investigated. A nonlinear finite element model based on the von Karman strain-displacement relation is utilized to study the effectiveness of an SMA-embedded panel on the flutter boundary, critical buckling temperature, post-buckling deflection and free vibration. The study is performed on an isotropic panel with embedded SMA. The aerodynamic model is based on the first-order quasi-steady piston theory. The dynamic pressure effect on the buckling and post-buckling behaviour of the panel is investigated by introducing the aerodynamic stiffness term, which changes the critical buckling temperature. Panels with SMA embedded in either the longer or shorter direction and either fully or partially embedded are investigated for post-buckling behaviour. Similarly, the influence of temperature elevation on the flutter boundary and vibration frequencies is investigated.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Thermal post-buckling and aeroelastic behaviour of shape memory alloy reinforced plates

Tawfik

Mei

2002

Smart Mater. Struct.

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“…In the analysis of nonlinear panel flutter response, the mode truncation technique is used to reduce the order of panel flutter model [3,4]. These studies show that 36 in vacuo natural modes (NMS) are needed for converged, limit-cycle oscillations (LCOs) of isotropic or laminated anisotropic rectangular panels.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Aeroelastic Panel Flutter Based on Proper Orthogonal Decomposition

Jian

Yang

2013

AMM

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It is commonly accepted that 36 in vacuo natural modes (NMS) are needed for converged, limit-cycle oscillations (LCOs) of isotropic or laminated anisotropic rectangular panels in supersonic air flow. It’s computationally costly for nonlinear aeroelastic panel response using such a large number of modes, and it also causes complexity and difficultly in designing controllers for panel flutter suppression. Based on Hamilton principle, the aeroelastic finite element motion equations of the 3-D panel are established by using the von Karman large deflection theory, first-order piston theory aerodynamics, the proper orthogonal decomposition (POD) method are adopted to construct a reduced order model of the panel, then the reduced panel flutter equations are solved in time domain using a numerical integration method. Comparing with the LCOs calculated by using 36NMS, the results obtained by using the reduced order model based on POD method (POD/ROM) show a good agreement.

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Nonlinear flutter of composite panels under yawed supersonic flow using finite elements

Cited by 2 publications

References 0 publications

Thermal post-buckling and aeroelastic behaviour of shape memory alloy reinforced plates

Thermal post-buckling and aeroelastic behaviour of shape memory alloy reinforced plates

Nonlinear Aeroelastic Panel Flutter Based on Proper Orthogonal Decomposition

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