Investigations on the flutter properties of supersonic panels with different boundary conditions

Song, Zhiguang; Li, Fengming

doi:10.1007/s40435-013-0038-5

Cited by 46 publications

(7 citation statements)

References 22 publications

(19 reference statements)

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Section: Numerical Methods and Resultsmentioning

confidence: 99%

“…The location of maximum vibration amplitude is in good agreement with the results by Dowell 11 and other literatures. 35,36 CFD/CSD method Before beginning to investigate mathematical basis of the reason why the location of maximum vibration amplitude always locates at 0.75 of panel length, it is important to ''double check'' this conclusion which was found by many scholars. 11,35,36 The purpose of this section is to verify the pattern by using existing methods.…”

Section: A Nonlinear Panel Modelmentioning

confidence: 99%

“…Thus, even though a different numerical method is adopted, the pattern of the location of maximum vibration amplitude is in good agreement with the results by Dowell 11 or existing literatures. 35,36 Linear panel model Due to the assumption that the relationship between the load and the deflection is nearly linear, the linear panel model is unable to simulate limit cycle oscillation. However, within the framework of linear panel model, there is a critical dynamic pressure.…”

Section: A Nonlinear Panel Modelmentioning

confidence: 99%

“…Contrary to previous work with simple supported boundary conditions, in engineer practice, the boundary condition of the panel may be non-classical due to the deviation of assembly process, friction and gasket creep. 35 Song and Li 36 compared the calculation results of panel flutter with classical and elastic boundary conditions. The results indicated that the assumed model was not suitable for panel flutter with elastic boundary conditions.…”

Section: Introductionmentioning

confidence: 99%

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Analysis on location of maximum vibration amplitude in panel flutter

Meng

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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When the panel is under limit cycle oscillation, the location of maximum vibration amplitude always locates at 0.75 of panel length under different dynamic pressure. However, this conclusion is drawn from engineer practice without further investigations on its theoretical basis. Thus, the current study focuses on the theoretical and mathematical basis of this problem. The pattern of the location of maximum amplitude is verified at first by using three numerical methods. Then, based on the law of energy conservation, the displacement function of linear panel oscillation is derived for theoretical investigation. The linear panel consists of two structural modes. Theoretical analysis shows that, under critical dynamic pressure, the generalized displacement responses of two structural modes have opposite phase, the same vibration amplitude and the same vibration frequency. As a result, the superposition of displacement function of two structural modes, which is the displacement function of panel, leads to the occurrence of maximum vibration amplitude at 0.7 of panel length. With more structural modes considered, the location of maximum moves to 0.75 of panel length.

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Section: Numerical Methods and Resultsmentioning

confidence: 99%

Section: A Nonlinear Panel Modelmentioning

confidence: 99%

Section: A Nonlinear Panel Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Analysis on location of maximum vibration amplitude in panel flutter

Meng

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Dowell [6] [7] gave a typical investigation on nonlinear panel flutter of 2D and three dimensional (3D) isotropic and simply-supported panels. Impact on 3D panel flutter properties of different boundary conditions (SSSS, SCSC and SFSF) were investigated using the assumed mode method and finite element method in 2014 [8]. Yufeng Xing gave the overall assessment of closed-form solution methods for free vibrations of rectangular thin plate [9] With the increase of the flight speed of modern aircrafts, the Mach number can reach more than five Mach.…”

Section: Introductionmentioning

confidence: 99%

Analytical Solution for Thermal Flutter of Laminates in Supersonic Speeds

Dai¹,

Sun²

2020

JAMP

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As a basic component of engineering fields such as aeronautics, astronautics and shipbuilding, panel structure has been widely used in engineering and scientific research. It is of great theoretical and practical significance to study the vibration of panels. The panel flutter problem has caused widely concerned by researchers at home and abroad during to the emergence of high-speed aircrafts. With regard to the eigenvalue problem of rectangular panels, it is generally believed that it is difficult to obtain a closed form eigen solution in the case of an adjacent boundaries clamped-supported or a free boundary that cannot be decoupled. Aiming at the problem, this paper studies the two-dimensional symmetric orthogonal laminated plate structure in the hypersonic flow in the thermal environment, and combines the first-order piston aerodynamic theory to study a high-precision separation variable method. Through this method, analytical solution to the closed form of the thermal flutter problem of rectangular panels can be obtained under any homogeneous boundary conditions.

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