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Open AccessJournal ArticleDOI

Cross-sectional analysis of nonhomogeneous anisotropic active slender structures

Rafael Palacios, +1 more
- 01 Dec 2005 - 
- Vol. 43, Iss: 12, pp 2624-2638
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TLDR
In this article, a general formulation for the reduction of the three-dimensional problem of electrothermoelasticity in slender solids to an arbitrarily defined reference line is presented, which is based on a variationalasymptotic formulation, using the slenderness ratio as small parameter.
Abstract
A general formulation for the reduction of the three-dimensional problem of electrothermoelasticity in slender solids to an arbitrarily defined reference line is presented The dimensional reduction is based on a variationalasymptotic formulation, using the slenderness ratio as small parameter In the proposed scheme, the coupled linear electroelastic equations are solved at the cross-sectional level using the finite element method Furthermore, modal components of the displacement field are added to introduce arbitrary deformation shapes into the onedimensional analysis, and arbitrary electric modes are used to define applied electric fields at the cross section This results in a general definition of a coupled electroelastic stiffness, which can be used in virtually all composite and active beam formulations, as well as in the development of new low-order high-accuracy reduced models for active structures Finally, the formulation also yields recovery relations for the elastic and electric fields in the original three-dimensional solid, once the one-dimensional problem is solved The method has been implemented in a computer program (UM/VABS) and numerical results are presented for active anisotropic beam cross sections of simple geometries, which are shown to compare very well with three-dimensional finite element analysis

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Citations
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Applications of the unsteady vortex-lattice method in aircraft aeroelasticity and flight dynamics

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Structural and Aerodynamic Models in Nonlinear Flight Dynamics of Very Flexible Aircraft

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Computational Aeroelasticity Framework for Analyzing Flapping Wing Micro Air Vehicles

TL;DR: A computational framework for simulating structural models of varied fidelity and a Navier-Stokes solver, aimed at simulating flapping and flexible wings, and implications of fluid density on aerodynamic loading are explored.
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Strain-based geometrically nonlinear beam formulation for modeling very flexible aircraft

TL;DR: In this paper, a strain-based geometrically nonlinear beam formulation for structural and aero-elastic modeling and analysis of slender wings of very flexible aircraft is introduced, with beam extensional strain, twist, and bending curvatures defined as the independent degrees of freedom.
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Assessment of Wake-Tail Interference Effects on the Dynamics of Flexible Aircraft

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References
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Journal ArticleDOI

Modelling of Piezoelectric Actuator Dynamics for Active Structural Control

TL;DR: In this article, the effects of dynamic coupling between a structure and an electrical network through the piezoelectric effect are derived. But the authors focus on the case of a cantilevered beam with surface mounted piezoceramics and indirect voltage and current drive.
Proceedings ArticleDOI

Low-cost piezocomposite actuator for structural control applications

TL;DR: In this article, a planar composite piezoceramic actuator is presented, which uses interdigitated electrodes for poling and subsequent actuation of an internal layer of machined piezoelectric fibers.
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