Journal ArticleDOI
Using Aeroelastic Modes for Nonlinear Panel Flutter at Arbitrary Supersonic Yawed Angle
Xinyun Guo,Chuh Mei +1 more
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TLDR
In this article, a thorough examination and understanding of the panel limit-cycle behavior leads to the use of aeroelastic modes for supersonic nonlinear panel flutter analysis.Abstract:
It is commonly accepted that six in vacuo natural modes are needed for converged, limit-cycle oscillations of isotropic rectangular plates exposed to supersonic flow at zero yaw angle to the principle panel length. For isotropic or orthotropic rectangular plates under an arbitrary nonzero yawed supersonic flow, then 36 or 6 x 6 natural modes are needed; for laminated anisotropic rectangular plates even at zero yaw angle, 36 or fewer natural modes are needed. To deal with such a large number of modes is computationally costly for flutter analysis, causing complexity and difficulty in designing controllers for flutter suppression. A thorough examination and understanding of the panel limit-cycle behavior leads to the use of aeroelastic modes for supersonic nonlinear panel flutter analysis. The system equations of motion are formulated first in structural node degrees of freedom. Aeroelastic modes are selected and determined, and the system equations is expressed in the aeroelastic modal coordinates. Limit-cycle amplitudes are then determined using numerical integration. Examples show that the number of modes could be greatly reduced by using aeroelastic modes. For determining limit-cycle oscillations of isotropic or anisotropic composite rectangular plates at zero or an arbitrary yawed flow angle, only two aeroelastic modes are needed; but six to seven aeroelastic modes are needed for designing controllers for flutter suppression.read more
Citations
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Journal ArticleDOI
A review of indirect/non-intrusive reduced order modeling of nonlinear geometric structures
TL;DR: In this article, a review of reduced order modeling techniques for geometrically nonlinear structures, more specifically those techniques that are applicable to structural models constructed using commercial finite element software, is presented.
Journal ArticleDOI
System identification-guided basis selection for reduced-order nonlinear response analysis
Stephen A. Rizzi,Adam Przekop +1 more
TL;DR: In this paper, the authors developed a reliable and rigorous procedure through which an efficient modal basis can be chosen, which is successfully applied to the analysis of a planar beam and a shallow arch over a wide range of nonlinear dynamic response regimes.
Journal ArticleDOI
Application of aeroelastic modes on nonlinear supersonic panel flutter at elevated temperatures
Xinyun Guo,Chuh Mei +1 more
TL;DR: In this article, the use of aeroelastic modes, instead of the traditional in vacuo natural modes, can reduce drastically the number of coupled nonlinear modal equations for the large amplitude nonlinear panel flutter analysis at an arbitrary yawed supersonic flow angle and elevated temperatures.
Journal ArticleDOI
Aeroelasticity of composite plates with curvilinear fibres in supersonic flow
Hamed Akhavan,Pedro Ribeiro +1 more
TL;DR: In this article, the aeroelastic (dynamic or static) instability of variable stiffness composite laminates (VSCLs) in the presence of supersonic airflow was investigated.
Journal ArticleDOI
Proper orthogonal decomposition method for analysis of nonlinear panel flutter with thermal effects in supersonic flow
TL;DR: In this paper, the proper orthogonal decomposition (POD) method for analysis of nonlinear panel flutter subjected to supersonic flow is presented, which can obtain accurate chaotic solutions, using fewer modes and less computational effort than the Galerkin mode approach; additionally, the POD method converges faster in the analysis of chaotic transients.
References
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Book
Fundamentals of Vibrations
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TL;DR: In this article, the Fourier series is used to measure the response of a single-degree-of-freedom system to initial and non-periodic oscillations, respectively.
Journal ArticleDOI
Panel flutter - A review of the aeroelastic stability of plates and shells
TL;DR: In this article, panel flutter theory applied to aeroelastic stability of flat unloaded plates and cylindrical shells is applied to the stability of aero-elastic vehicles.
Journal ArticleDOI
Plates and Shells
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