Panel flutter analysis using high precision shear flexible element
TL;DR: In this article, a finite element formulation with use of a two-noded shear flexible element with four degrees of freedom (DOF) node is adopted to study the effects of shear deformation and rotary inertia on two-dimensional panel flutter.
About: This article is published in Journal of Sound and Vibration.The article was published on 1991-01-08. It has received 1 citations till now. The article focuses on the topics: Flutter & Rotary inertia.
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TL;DR: In this paper, the chaotic and limit-cycle oscillations of an isotropic plate are obtained based on direct integration of the discretized equation of motion, and the plate is modeled using the von Karman theory and the geometrical nonlinearities are separated in a nonlinear term of the first kind which manifests especially in the prebuckling and buckling regimes, and a non linear term of a second kind which is responsible for the postbuckling behavior.
Abstract: Higher order elements were first design for linear problems where, in certain situations, they present advantages over the lower order elements. A method to efficiently extend their use to geometrical nonlinear problems as panel flutter and postbuckling behavior is presented. The chaotic and limit-cycle oscillations of an isotropic plate are obtained based on direct integration of the discretized equation of motion. The plate is modeled using the von Karman theory and the geometrical nonlinearities are separated in a nonlinear term of the first kind which manifests especially in the prebuckling and buckling regimes, and a nonlinear term of the second kind which is responsible for the postbuckling behavior. A fifth order, fully compatible element has been used to model thin plates while the inplane loads where introduced through a membrane element. The aerodynamics was modeled using the first order 'piston theory’. The method introduces the concept of a deteriorated form of the second geometric matrix which is equivalent to neglecting higher order terms in the strain energy of the plate. This allows for a drastic reduction in the computational effort with no observable loss of accuracy. Well established results in the literature are used to validate the method.
3 citations
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...[4] studied two-dimensional panels using an element having four degrees of freedom per node which also takes into consideration shear effects....
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01 Jan 1975TL;DR: In this article, aeroelasticite was used to construct an instationnaire for the structure reference record created on 2005-11-18, modified on 2016-08-08.
Abstract: Keywords: aeroelasticite ; instationnaire ; structures Reference Record created on 2005-11-18, modified on 2016-08-08
640 citations
TL;DR: In this paper, a penalty type argument is used to degenerate thick elements to thin elements, and various approximations of the shear related energy terms act as different types of constraints.
Abstract: The Timoshenko beam element is studied in an investigation of shear locking in the development of C(0) continuous elements using shear-flexible or penalty function type formulations. A penalty type argument is used to degenerate thick elements to thin elements, and the various approximations of the shear related energy terms act as different types of constraints. Depending on the formulation, two types of constraints may emerge, which are classified as true or spurious. Formulations that ensure only true constraints in the extreme penalty limit cases display superior performance in the thick element situation. The argument is extended to a shallow curved Timoshenko beam, and another mechanism, inplane locking, arises if all energy terms corresponding to the membrane energy are exactly integrated.
231 citations
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01 Jan 1949
205 citations
TL;DR: In this paper, the aerodynamic forces are represented by finite elements, that is, directly in terms of the generalized displace-ments used as unknowns, resulting in an increased flexibility and generality in the structural configurations that can be treated.
Abstract: INTRODUCTION The finite element method is a powerful tool to solve static and dynamic problems of structural analysis. Its application to flutter analysis can be envisaged in two ways. It can be used to obtain a more accurate modal shape of complex structures which in turn are introduced in traditional methods. The approach followed here is different, and consists in representing the non-stationary aerodynamic forces also by finite elements, that is, directly in terms of the generalized displace- ments used as unknowns. The resulting advantage is an increased flexibility and generality in the structural configurations that can be treated. The aerodynamic forces are evaluated using the linearized piston theory and follows the line first presented by Olson.' It is extended
101 citations
86 citations