Comparison of theory and experiment for nonlinear flutter of loaded plates

Dowell, Earl H.; Ventres, C. S.

doi:10.2514/3.6041

Cited by 94 publications

(7 citation statements)

References 11 publications

(19 reference statements)

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“…The transverse deflection of the panel is of the order of the panel thickness when it undergoes limit cycle oscillation in the fluttering zone, so linear analysis is inadequate. In order to account for the geometric nonlinearity, von Kármán large-plate theory is usually employed in nonlinear panel flutter problem, and it agrees well with experimental results [22] as shown in Fig. 1.2.…”

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confidence: 75%

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A Feedback Linearization Approach for Panel Flutter Suppression With Piezoelectric Actuation

Onawola

Sinha

2009

Volume 4: 7th International Conference on Multibody Systems, Nonlinear Dynamics, and Control, Parts A, B and C

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Panel flutter suppression by exact state transformations and feedback control using piezoelectric actuation is presented. A nonlinear control system is formulated for the nonlinear partial differential equation governing the dynamics of a simply supported rectangular panel with bonded piezoelectric layers based on the von Ka´rman large-deflection plate theory. Distributed piezoelectric actuators and sensors connected to processing networks are used as modal actuators and sensors to actively control panel vibrations. The control inputs are given by the electric fields required to drive the actuators based on piezoelectric actuation. Nonlinear feedback control laws are formulated through a transformation of the nonlinear system into an equivalent controllable linear system. The simulated results show that the resulting closed-loop system based on feedback linearized controllers effectively suppress panel flutter limit-cycle motions.

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confidence: 75%

“…22 Phase plot of the panel with feedback linearization controller, u , v , w = displacement field along −x , − y ,…”

mentioning

confidence: 99%

A Feedback Linearization Approach for Panel Flutter Suppression With Piezoelectric Actuation

Onawola

Sinha

2009

Volume 4: 7th International Conference on Multibody Systems, Nonlinear Dynamics, and Control, Parts A, B and C

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“…Three types of oscillations are found: a) coupledmode oscillation for M ≫ 1, b) single-mode oscillation for M ≈ 1, and c) single-mode, zero frequency oscillation (buckling) for M < 1.2. Ventres and Dowell [3] theoretically investigated the flutter behavior of clamped plates exposed to transverse pressure loading, or buckled by uniform thermal expansion, and compared the obtained results with existing experimental data. Singha and Mandal [4] studied supersonic panel flutter behavior of laminated composite plates and cylindrical panels.…”

mentioning

confidence: 94%

Effects of all-over part-through cracks on the aeroelastic characteristics of rectangular panels

AsadiGorgi

Dardel

Pashaei

2015

Applied Mathematical Modelling

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In this study, flutter, limit cycle oscillation, and different nonlinear oscillations analyses of rectangular panels with all-over part-through crack are presented. These analyses are carried out for panels in according to first order shear deformation or Mindlin plate theory. The effects of crack's depth and location on various aeroelastic characteristics of moderately thick rectangular panels are accurately studied. These analyses show that for much of crack's depths and locations, the amplitude of nonlinear vibrations are increased. But there are some crack's locations, for them panel has lower amplitude of vibrations with respect to its intact counterpart. With changing the location and depth of crack, the maximum limit cycle oscillation amplitude will be different from intact counterpart. Also cracked panel may exhibit complex oscillations, other than limit cycle oscillation of intact panel. From these analyses, it can be shown that crack has significant influence on flutter boundary, and amplitude of limit cycle oscillation. Nomenclatureܽ Panel chord-wise length ܷ elastic energy ܾ Panel span-wise length ‫,ݔ‬ ‫,ݕ‬ ‫ݖ‬ Coordinates ‫ܦ‬ Plate bending flexible ߫, ߟ, ‫ݓ‬ ഥ non-dimensional coordinates ‫ܧ‬ Panel module of elasticity ߛ Shear strains ‫ܪ‬ Panel thickness ߝ Tensile strain components ℎ Crack thickness ߢ Shear correction factor ݉, ݊ Number of modes shapes for chord-wise and span-wise direction ߣ ி Dimensionless flutter (critical) aerodynamic pressure ‫ܯ‬ Mass matrix ߩ, ߩ Panel and air densities ‫ܭ‬ Stiffness matrix ߥ Poisson's ratio ‫ܮܰ‬ Nonlinear matrix ߱ Dimensionless frequency ‫ܣ‬ cross-sectional area ߱ Dimensionless i'th transverse frequency ‫ܭ‬ Crack stiffness coefficient ߫ Chord wise dimensionless crack location

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“…Dowell [18] studied the non-linear curved panel flutter using non-linear von Kármán relations and quasi-steady aerodynamic loading. Dowell and Venters [19] compared theoretical and experimental non-linear flutter of loaded plates. Yang [20] investigated buckled plate flutter through the use of finite element method (FEM).…”

Section: Introductionmentioning

confidence: 99%

Time domain aero-thermo-elastic instability of two-dimensional non-linear curved panels with the effect of in-plane load considered

Moosazadeh

Mohammadi

2020

SN Appl. Sci.

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This study presents aero-thermo-elastic Instability of two-dimensional Non-linear Curved Panels. Aero-thermo-elasticity plays an important role in the design and optimization of supersonic aircrafts. Furthermore, the transient and nonlinear effects of the thermal and aerodynamic environment encompassing a curved surface cannot be ignored. Accordingly, a homogenous curved plate with a high length-to-width ratio and simply-supported boundary conditions is assumed. The effect of large deflection is included in the equations through von Kármán non-linear strain-displacement relations. The thermal load is assumed to be a steady-state temperature non-uniform distribution. Structural properties such as modulus of elasticity and thermal expansion coefficient are assumed to be temperature-dependent. The novelty is incorporating first-and third-order piston theory for the non-linear curved panel flutter analysis under the effects of inplane and thermal loads. Hamilton's principle is used and partial differential equations are derived. The semi-analytical weighted residual method for the nonlinear curved panel is utilized. The fourth-and fifth-order Runge-Kutta iterative method are deployed to obtain the non-linear aero-thermo-mechanical deflections. Non-linear frequency analysis of cambered panel with the combined effects of aerodynamics, thermal and in-plane loads is investigated for the first time. The increase in panel curvature leads to a complicated behavior in the non-linear structural frequency variations. With increasing in-plane compressive load, complicated oscillating behavior is observed. More critical instability boundary for cambered panel is detected through the use of third-order piston theory. In addition, with an increase in panel curvature from 0 to 3, the panel displacement increases and for higher camber ratio, it decreases. Keywords Panel flutter • In-plane load • Thermal effects • First-order piston theory • Third-order piston theory • 2D panel • Time domain

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Comparison of theory and experiment for nonlinear flutter of loaded plates

Cited by 94 publications

References 11 publications

A Feedback Linearization Approach for Panel Flutter Suppression With Piezoelectric Actuation

A Feedback Linearization Approach for Panel Flutter Suppression With Piezoelectric Actuation

Effects of all-over part-through cracks on the aeroelastic characteristics of rectangular panels

Time domain aero-thermo-elastic instability of two-dimensional non-linear curved panels with the effect of in-plane load considered

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