Nonlinear Dynamics of Prestressed Panels in Low Supersonic Turbulent Flow

Alder, Marko

doi:10.2514/1.j054783

Cited by 18 publications

(4 citation statements)

References 30 publications

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“…The main purpose of flutter bound analysis is to determine the critical conditions of panel flutter. On this basis, the influences of structural parameters, 93 temperature distributions, 94 in‐plane stresses, 95,96 and boundary conditions 97 on the flutter bounds of panels were analyzed, and the influences of various factors on the flutter bounds were summarized. Structural parameters mainly involve deformation theory, thickness, aspect ratio and fiber orientations of composite structures, and so on.…”

Section: Contents and Methods Of Aeroelastic Analysismentioning

confidence: 99%

“…The main purpose of flutter bound analysis is to determine the critical conditions of panel flutter. On this basis, the influences of structural parameters, 93 temperature distributions, 94 in-plane stresses, 95,96 and boundary conditions 97 The influence of the temperature caused by aerodynamic heating should be considered in the supersonic flutter, which can more truly reflect the aeroelastic behaviors of supersonic aircraft structures. 101 The existence of thermal load will cause the structure to flutter under lower aerodynamic pressure or produce more severe LCO under the same aerodynamic pressure.…”

Section: Prediction Of Structural Flutter Boundsmentioning

confidence: 99%

See 1 more Smart Citation

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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Section: Contents and Methods Of Aeroelastic Analysismentioning

confidence: 99%

“…The main purpose of flutter bound analysis is to determine the critical conditions of panel flutter. On this basis, the influences of structural parameters, 93 temperature distributions, 94 in-plane stresses, 95,96 and boundary conditions 97 The influence of the temperature caused by aerodynamic heating should be considered in the supersonic flutter, which can more truly reflect the aeroelastic behaviors of supersonic aircraft structures. 101 The existence of thermal load will cause the structure to flutter under lower aerodynamic pressure or produce more severe LCO under the same aerodynamic pressure.…”

Section: Prediction Of Structural Flutter Boundsmentioning

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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“…This classical panel flutter problem has been studied in the 1950-1970s in numerous papers, where linear piston theory was employed for modeling high-speed supersonic flow [6][7][8][9][10][11]. The interest in this problem was renewed in the 2000s, when several aeroelastic solvers based on full Euler or Reynolds-averaged Navier-Stokes equations were developed by different groups and showed their capability of solving the panel flutter problem at transonic and low supersonic speed in linear [12,13] and nonlinear [5,[14][15][16][17][18][19][20][21] formulations.…”

Section: Introductionmentioning

confidence: 99%

“…Note that single mode flutter, which is caused by negative aerodynamic damping dominating in this range of speeds, can be significantly affected by the boundary layer over the panel surface (unlike coupled-mode flutter at high supersonic speeds). Although zero-gradient boundary layers reduce the flutter region in the parameter space [15,16,18,19,[22][23][24][25], boundary layers over concave walls can be essentially destabilizing [26,27]. In this paper, the boundary layer is neglected for simplicity, and only inviscid fluidstructure interaction mechanism is studied.…”

Section: Introductionmentioning

confidence: 99%

Transonic Panel Flutter in Accelerating or Decelerating Flow Conditions

Shishaeva¹,

Vedeneev²,

Aksenov³

et al. 2018

AIAA Journal

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Nonlinear panel flutter oscillations at transonic and low supersonic flow speed demonstrate rich panel dynamics, which includes bifurcations of the limit cycle, coexisting of different limit cycles, and nonperiodic oscillations. Passing through the range of transonic Mach numbers to supersonic cruise speed should be sufficiently fast to avoid significant fatigue damage. In this study, the sequence of bifurcations of limit cycles when the flow speed is continuously increasing or decreasing is analyzed. The evolution of limit-cycle oscillations is carefully studied. It is shown that the most dangerous oscillation regimes, high-frequency periodic or nonperiodic oscillations, are suppressed if the flow acceleration is sufficiently fast. However, first-mode limit cycle and limit cycle involving internal 1:2 resonance are not affected by the flow acceleration, such that lower accumulation of the fatigue damage in fast accelerating flow is possible only because of fewer cycles of oscillations, but not because of the decrease of the limit-cycle amplitude.

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