Variations of flutter mechanism of a span-morphing wing involving rigid-body motions

Huang, Chao; Yang, Chao; Wu, Zhigang; Tang, Changhong

doi:10.1016/j.cja.2017.12.014

Cited by 15 publications

(10 citation statements)

References 17 publications

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“…Huang et al [42] presented an aeroelastic formulation with the inclusion of rigid-body motion and a flutter analysis. Quasi-static modeling was used to develop an aeroelastic equation for a span morphing wing, involving the rigid-body motion by combining unsteady strip aerodynamic theory with Euler-Bernoulli beam theory.…”

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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“…In the model, the linear part was constructed by a linear reduction model, and the nonlinear part was identified by a neural network model. Huang et al 187 analyzed the flutter mechanisms of a morphing wing, and the influences of some parameters on the variations of flutter mechanisms were studied. Schewe and Mai 188 conducted flutter experiments on the flexible wing model, and obtained stability diagrams and LCO amplitudes in the transonic range of 0.84 < M a < 0.89 and six attack angles from 1.46° to 2.7°.…”

Section: Research Status Of Aeroelastic Analysismentioning

confidence: 99%

Aeroelastic analysis and flutter control of wings and panels: A review

Chai

Gao

Ankay

et al. 2021

Int Journal of Mech Sys Dyn

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Flutter is a self-excited vibration under the interaction of the inertial force, aerodynamic force, and elastic force of the structure. After the flutter occurs, the aircraft structures will exhibit limit cycle oscillation, which will cause catastrophic accidents or fatigue damage to the structures. Therefore, it is of great theoretical and practical significance to study the aeroelastic characteristics and flutter control for improving the aeroelastic stability of aircraft structures. This paper reviews the recent advances in aeroelastic analysis and flutter control of wings and panel structures. The mechanism of aeroelastic flutter of wings and panels is presented. The research methods of aeroelastic flutter for different structures developed in recent years are briefly summarized. Various control strategies including the linear and nonlinear control algorithms as well as the active flutter control results of wings and panels are presented. Finally, the paper ends with conclusions, which highlight challenges of the development in aeroelastic analysis and flutter control, and provide a brief outlook on the future investigations. This study aims to present a comprehensive understanding of aeroelastic analysis and flutter control. It can also provide guidance on the design of new wings and panel structures for improving their aeroelastic stability.

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“…In the present study, a so-called '3211' signal developed by Cowan et al 19 is utilized as the input of the CFD solve due to its broad frequency spectra. Then the least squares method is adopted to fit the time history of the output of the CFD solver, i.e., f a , to carry out the unknown coefficient matrices in equation (5).…”

Section: Aerodynamic Rom and Flutter Equationmentioning

confidence: 99%

“…In recent years, many efforts have been made to assess the aeroelastic stability for different types of morphing concepts. The flutter mechanism of a span-morphing wing was analysed by Huang et al, 5 revealing the rigid-body modes especially pitch motion of the aircraft have a significant effect on flutter characteristics. The flutter and divergence characteristics of a large civil aircraft with morphing winglets and adaptive flap tabs were systemically examined to assess the robustness and safety of adoption in the real structure.…”

Section: Introductionmentioning

confidence: 99%

Transonic flutter characteristics of an airfoil with morphing devices

Guo

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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An investigation into transonic flutter characteristic of an airfoil conceived with the morphing leading and trailing edges has been carried out. Computational fluid dynamics (CFD) is used to calculate the unsteady aerodynamic force in transonic flow. An aerodynamic reduced order model (ROM) based on autoregressive model with exogenous input (ARX) is used in the numerical simulation. The flutter solution is determined by eigenvalue analysis at specific Mach number. The approach is validated by comparing the transonic flutter characteristics of the Isogai wing with relevant literatures before applied to a morphing airfoil. The study reveals that by employing the morphing trailing edge, the shock wave forms and shifts to the trailing edge at a lower Mach number, and aerodynamic force stabilization happens earlier. Meanwhile, the minimum flutter speed increases and transonic dip occurs at a lower Mach number. It is also noted that leading edge morphing has negligible effect on the appearance of the shock wave and transonic flutter. The mechanism of improving the transonic flutter characteristics by morphing technology is discussed by correlating shock wave location on airfoil surface, unsteady aerodynamics with flutter solution.

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Variations of flutter mechanism of a span-morphing wing involving rigid-body motions

Cited by 15 publications

References 17 publications

Recent developments in the aeroelasticity of morphing aircraft

Recent developments in the aeroelasticity of morphing aircraft

Aeroelastic analysis and flutter control of wings and panels: A review

Transonic flutter characteristics of an airfoil with morphing devices

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