Geometrically nonlinear static FE-simulation of multilayered magneto-electro-elastic composite structures

2015 ◽  
Vol 127 ◽  
pp. 120-131 ◽  
Author(s):  
M.N. Rao ◽  
R. Schmidt ◽  
K.-U. Schröder
Keyword(s):  
Composite Structures ◽  
Fe Simulation ◽  
Geometrically Nonlinear ◽  
Elastic Composite ◽  
Nonlinear Static

Dynamic Buckling of Shallow Spherical Shells

1973 ◽  
Vol 40 (2) ◽  
pp. 411-416 ◽  
Author(s):  
R. E. Ball ◽  
J. A. Burt
Keyword(s):  
Computer Program ◽  
Dynamic Analysis ◽  
Digital Computer ◽  
Large Range ◽  
Dynamic Buckling ◽  
Geometrically Nonlinear ◽  
Shells Of Revolution ◽  
Spherical Shells ◽  
Static And Dynamic Analysis ◽  
Nonlinear Static

The dynamic behavior of clamped shallow spherical shells subjected to axisymmetric and nearly axisymmetric step-pressure loads is examined using a digital computer program for the geometrically nonlinear static and dynamic analysis of arbitrarily loaded shells of revolution. A criterion for dynamic buckling under the nearly axisymmetric load is proposed and critical buckling pressures are determined for a large range of shell sizes.

Geometrically exact vortex lattice and panel methods in static aeroelasticity of very flexible wing

2019 ◽  
Vol 234 (3) ◽  
pp. 742-759
Author(s):  
Lan Yang ◽  
Changchuan Xie ◽  
Chao Yang
Keyword(s):  
Large Deformation ◽  
Vortex Lattice ◽  
Panel Method ◽  
Theoretical Research ◽  
Full Potential ◽  
Geometrically Nonlinear ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Aeroelastic Analysis ◽  
Nonlinear Static

Geometrically exact vortex lattice method and panel method are presented in this paper to deal with aerodynamic load computation for geometrically nonlinear static aeroelastic problems. They are combined with geometrically nonlinear finite element method through surface spline interpolation in the loosely-coupled iteration. From the perspective of theoretical research, both vortex lattice method and panel method are based on the full potential equation and able to model the deflection and twist of the wing, while vortex lattice method is based on the thin airfoil theory, and panel method is suitable for thick wings. Although the potential flow equation is linear, the introduction of geometrically exact boundary conditions makes it significantly different from the linear aeroelastic analysis. The numerical results of a high aspect ratio wing are provided to declare the influence of large deformation on nonlinear static aeroelastic computation compared with linear analysis. Aeroelastic analyses based on geometrically exact vortex lattice method and panel method are also compared with the results of computational fluid dynamics/computational structural dynamics coupling method and the wind tunnel test data. The nonlinear static aeroelastic analysis agrees with the measurement even in considerably large deformation situations.

Physically and Geometrically Nonlinear Static Problems for Thin-Walled Multiply Connected Shells

2003 ◽  
Vol 39 (6) ◽  
pp. 679-687 ◽  
Author(s):  
Aleksandr Nikolaevich Guz ◽  
E. A. Storozhuk ◽  
Ivan Chernyshenko
Keyword(s):  
Geometrically Nonlinear ◽  
Multiply Connected ◽  
Nonlinear Static ◽  
Thin Walled

Application of Groebner Basis Methodology to Nonlinear Static Cable Analysis

2013 ◽  
Vol 135 (4) ◽  
Author(s):  
Y. Jane Liu ◽  
George R. Buchanan ◽  
John Peddieson
Keyword(s):  
Nonlinear Analysis ◽  
Analytical Solutions ◽  
Geometrically Nonlinear ◽  
Large Deflections ◽  
Groebner Basis ◽  
Governing Equations ◽  
Geometrically Nonlinear Analysis ◽  
Exact Analytical Solutions ◽  
Highly Nonlinear ◽  
Nonlinear Static

The governing equations for large deflections of cables have a highly nonlinear and coupled nature, which precludes exact analytical solutions except in a few simplified cases. The present study demonstrates the utility of Groebner Basis methodology in facilitating the construction of approximate analytical and semianalytical Galerkin solutions in the geometrically nonlinear analysis of cable statics.

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