Finite element time domain - Modal formulation for nonlinear flutter of composite panels

Zhou, Ruhai; Xue, David Y.; Mei, Chuh

doi:10.2514/3.12250

Cited by 90 publications

(13 citation statements)

References 10 publications

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“…The potentiality of application of VSCL is large in lightweight structures, where vibrations can cause failure, instability, noise and life reduction due to fatigue. 112–115 Sub-section “ Vibration analysis ” reviews works on vibrations of VSCL. In Section “ Variable stiffness laminates with rectilinear fibres ”, a partial review is carried out on works where other means of varying the stiffness – not curvilinear fibres – are employed in fibre reinforced composites.…”

Section: Introductionmentioning

confidence: 99%

A review on the mechanical behaviour of curvilinear fibre composite laminated panels

Ribeiro

Akhavan

Teter

et al. 2013

Journal of Composite Materials

159

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A review on works that investigate the mechanical behaviour of variable stiffness composite laminated panels is carried out in this paper. The review mostly focuses on buckling, failure and vibrations in laminates reinforced by curvilinear fibres, although other issues related to variable stiffness laminates are also addressed. The peculiarities in the formulation of curvilinear fibre reinforced plates are briefly described. As an illustration, the natural frequencies of vibration of variable stiffness composite laminated plates with curvilinear fibres are computed by an h-version type finite element code and are compared with the ones calculated using another model, based on a Third-order Shear Deformation Theory. Areas of research to explore on variable stiffness composite laminates are suggested.

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Section: Introductionmentioning

confidence: 99%

A review on the mechanical behaviour of curvilinear fibre composite laminated panels

Ribeiro

Akhavan

Teter

et al. 2013

Journal of Composite Materials

159

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“…Fig. 6 also includes the result obtained for the same case by Zhou et al [23] but for a larger of dynamic pressure value. The present model simulation for = 800 provides an adequate match with Zhou et al [23], thereby ensuring appropriate time domain analyses features.…”

Section: Model Verificationmentioning

confidence: 82%

Nonlinear supersonic post-flutter motion of panels with adjacent bays and thermal effects

Guimarães

Sanches

Marques

2020

International Journal of Non-Linear Mechanics

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Aerospace vehicle structures in the supersonic regime flight have their outer skin subjected to unsteady aerodynamic and thermal loading, which may lead to aeroelastic instability. Typical aerospace structures are built as multiple adjacent panels, the so-called multi-bay configuration, but early efforts to predict the supersonic flutter were based on a single panel arrangement. This work evaluates the aeroelastic behavior of supersonic multi-bay fluttering panels under thermal effects, aiming to improve the understanding of adjacent panels interaction in the nonlinear regime. The aeroelastic model is established by using the first-order quasi-steady piston theory in conjunction with isotropic panel model using the von Kármán's assumptions to account for geometrical nonlinearities. The Newmark time-integration method is used to evaluate the resulting equations of motion. The Hopf bifurcation behavior that determines the flutter onset, thermo-buckling loading, phase portrait plots, and bifurcation diagrams for two adjacent panels are presented. The numerical results show the detrimental aspect of thermal loading in the aeroelastic behavior of fluttering panels, and the new findings corroborate with some recent studies that highlight the difference in the nonlinear flutter behavior between a single panel and multi-bay panels. Moreover, the existence of limit cycle oscillations amplitude jumps from a certain level of flow dynamic pressure is also observed. The multi-bay panels configuration also shows the anticipation of the buckled to the limit cycle oscillation solutions, when compared with a single panel analysis. Results indicate that simplified single bay panel assumptions can underestimate the post-flutter oscillations amplitudes of the adjacent bay. Such dynamic behavior may lead to a negative impact on aircraft structural design and fatigue life estimation.

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“…Bein et al [22] analyzed the hypersonic curved panel flutter in view of the effect of aerodynamic heating. Zhou [23] employed FEM for the frequency domain modeling of non-linear flutter in composite plates. Libresco [24,25] studied the vibration of geometrically-imperfect flat plate under thermal and mechanical loading as well as system frequency verses force in imperfect curved panels.…”

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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Finite element time domain - Modal formulation for nonlinear flutter of composite panels

Cited by 90 publications

References 10 publications

A review on the mechanical behaviour of curvilinear fibre composite laminated panels

A review on the mechanical behaviour of curvilinear fibre composite laminated panels

Nonlinear supersonic post-flutter motion of panels with adjacent bays and thermal effects

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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