Effect of Yaw Angle on Flutter of Rectangular Plates at Low Supersonic Speeds

Abdukhakimov, F. A.; Vedeneev, Vasily

doi:10.2514/1.j061441

Cited by 4 publications

(1 citation statement)

References 21 publications

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“…16 of this reference). Recently, Shishaeva et al [51] has also studied the effect of external perturbations on nonlinear panel flutter at low supersonic speed. It is found that depending on the initial perturbation, different LCOs can be developed, which should be the same phenomenon that predicted by the reduced order model in our previous work [40].…”

Section: Effect Of the Initial Conditionmentioning

confidence: 99%

Numerical study on the nonlinear characteristics of shock induced two-dimensional panel flutter in inviscid flow

Zhou

Wang

et al. 2022

Preprint

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For an aeroelastic system of a two-dimensional elastic panel subjected to an impinging inviscid oblique shockwave, the nonlinear flutter characteristics are affected by many factors such as shock impingement location, cavity pressure and initial perturbation. The effects of the above factors on the variation of system bifurcation type and dynamic behaviors are investigated numerically. A low-fidelity computational method coupled with local piston theory and van Karman plate model, and a high-fidelity computational method coupled with Euler equations and finite element model are used for fluid-structure interaction simulations. Two sets of new findings are unveiled. First, either the variation of shock impingement location or cavity pressure can induce the aeroelastic system to transition between a subcritical bifurcation and a supercritical bifurcation. For some cases, the system bifurcation characteristics exhibit strong sensitivity to these two factors. Second, it is found that in addition to the limit cycle oscillation (LCO) in the form of a combination of the second and third structural modes, multiple stable LCOs due to the coupling of higher-order modes can be triggered by proper initial perturbations. These LCOs are attributed with high frequencies and some of them even have high amplitudes, which indicates the higher risk of structural fatigue failure.

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Section: Effect Of the Initial Conditionmentioning

confidence: 99%

Numerical study on the nonlinear characteristics of shock induced two-dimensional panel flutter in inviscid flow

Zhou

Wang

et al. 2022

Preprint

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Nonlinear axial-lateral coupled vibration of functionally graded-fiber reinforced composite laminated (FG-FRCL) beams subjected to aero-thermal loads

Alimoradzadeh,

Tornabene,

Dimitri

2024

International Journal of Non-Linear Mechanics

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Effects of Mass Attachments on Flutter Characteristics of Thin-Walled Panels

Wang

Tian

2022

Aerospace

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Mass attachments may exist in the design and use of an aircraft panel, such as sensor layout, internal wiring, surface icing, etc. These mass attachments can change the flutter characteristics of the panel in supersonic flight and have important impacts on structural safety. In order to investigate the flutter characteristics of the panel with mass attachments, an assumed mode method is proposed to deal with the changes in the modal properties of the panel structure. Combined with the first order piston theory and p-k method, the flutter velocities and flutter frequencies of the panel under different cases can be obtained in the frequency domain. Firstly, based on the large displacement with a small strain assumption proposed by von Kármán and the proposed assumed mode method, the structural dynamic model of a simply supported panel with mass attachments and artificial dampers is constructed. Then, modal aerodynamic forces of the simply supported panel can be obtained based on first-order piston theory. Finally, flutter equations are transformed into the frequency domain and solved by the p-k method. The results showed that the existence of mass attachments can significantly change the flutter velocities and flutter frequencies of the panel. However, the flutter characteristics of the panel can be enhanced or recovered through some appropriate damper configuration schemes. Calculating the flutter characteristics of thin-walled panels with mass attachments can more accurately simulate real situations during flight, and one can obtain a safer design scheme of thin-walled panels.

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Effect of Yaw Angle on Flutter of Rectangular Plates at Low Supersonic Speeds

Cited by 4 publications

References 21 publications

Numerical study on the nonlinear characteristics of shock induced two-dimensional panel flutter in inviscid flow

Numerical study on the nonlinear characteristics of shock induced two-dimensional panel flutter in inviscid flow

Nonlinear axial-lateral coupled vibration of functionally graded-fiber reinforced composite laminated (FG-FRCL) beams subjected to aero-thermal loads

Effects of Mass Attachments on Flutter Characteristics of Thin-Walled Panels

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