A semi-analytical approach for the non-linear large deflection analysis of laminated rectangular plates under general out-of-plane loading

2008 ◽  
Vol 43 (4) ◽  
pp. 328-340 ◽  
Author(s):  
I. Shufrin ◽  
O. Rabinovitch ◽  
M. Eisenberger
Keyword(s):  
Analytical Approach ◽  
Large Deflection ◽  
Rectangular Plates ◽  
Non Linear ◽  
Out Of Plane ◽  
Deflection Analysis

Application of large-deflection theory to normally loaded rectangular plates with clamped edges

1970 ◽  
Vol 5 (2) ◽  
pp. 140-144 ◽  
Author(s):  
A Scholes
Keyword(s):  
Large Deflection ◽  
Rectangular Plates ◽  
Simply Supported ◽  
Aspect Ratios ◽  
Non Linear ◽  
Deflection Theory ◽  
Large Deflection Theory ◽  
Clamped Edges ◽  
Clamped Edge ◽  
Good Agreement

A previous paper (1)∗described an analysis for plates that made use of non-linear large-deflection theory. The results of the analysis were compared with measurements of deflections and stresses in simply supported rectangular plates. In this paper the analysis has been used to calculate the stresses and deflections for clamped-edge plates and these have been compared with measurements made on plates of various aspect ratios. Good agreement has been obtained for the maximum values of these stresses and deflections. These maximum values have been plotted in such a form as to be easily usable by the designer of pressure-loaded clamped-edge rectangular plates.

Large deflection of plates and beams obeying non-linear stress—strain laws

1974 ◽  
Vol 9 (3) ◽  
pp. 178-184 ◽  
Author(s):  
K R Rushton ◽  
P M Hook
Keyword(s):  
Finite Difference ◽  
Large Deflection ◽  
Experimental Results ◽  
Large Deflections ◽  
Rectangular Plates ◽  
Dynamic Relaxation ◽  
Stress Strain ◽  
Finite Difference Technique ◽  
Non Linear ◽  
Alternative Solutions

The large deflections of rectangular plates and beams obeying a non-linear stress-strain law are examined. Solutions are obtained by use of dynamic relaxation, a numerical finite-difference technique. Comparisons are made with alternative solutions and experimental results. The effects of varying parameters in the non-linear expressions are considered.

BUCKLING OF COMPOSITE PLATES WITH ARBITRARY BOUNDARY CONDITIONS BY A SEMI-ANALYTICAL APPROACH

2012 ◽  
Vol 12 (05) ◽  
pp. 1250033 ◽  
Author(s):  
EUGENIO RUOCCO ◽  
VINCENZO MINUTOLO
Keyword(s):  
Analytical Approach ◽  
Composite Plates ◽  
Analytical Form ◽  
Biaxial Compression ◽  
Rectangular Plates ◽  
Arbitrary Boundary ◽  
Buckling Loads ◽  
Plate Buckling ◽  
Out Of Plane ◽  
Plane Displacement

A semi-analytical approach for the buckling analysis of symmetrically laminated rectangular plates under arbitrary constrains is presented. In the proposed method, the out-of-plane displacement field is assumed to be of a multiplicative form containing two vectors of functions, one being prescribed and the other to be determined, depend on separate variables. As a consequence, one may solve the equilibrium equation analytically, and obtain exact buckling loads for the biaxial compression and different boundary constrains. Several cases of plate buckling under different load combinations are studied, in order to demonstrate the applicability of the proposed approach. The results obtained are compared with the existing ones, where available in analytical form, and approximate results obtained by other numerical methods.

Bending of normally loaded simply supported rectangular plates in the large-deflection range

1969 ◽  
Vol 4 (3) ◽  
pp. 190-198 ◽  
Author(s):  
A Scholes ◽  
E L Bernstein
Keyword(s):  
Linear Equations ◽  
Rectangular Plates ◽  
Algebraic Equations ◽  
Simply Supported ◽  
Aspect Ratios ◽  
Linear Algebraic Equations ◽  
Non Linear ◽  
Out Of Plane ◽  
Linear Differential ◽  
Good Agreement

Means of solving the non-linear differential equations of plate bending are revieweed and a method based on minimizing the corresponding energy integral is selected as offering most advantages. The energy intergral can be approximated either by using finite-difference approximatons or by assuming a form of displacement variation. Two sets of non-linear algebraic equations (in the in-plane and out-of-plane deflections) are thus formed and, by substitution alternately in each set, the resulting linear equations are solved. Results for simply supported rectangular plates have been worked out in some detail; these are compared with tests made on plates of various aspect ratios. Good agreement on maximum values of stress and deflection was obtained.

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