scholarly journals Post-buckling behavior estimation of composite panels of asymmetric structure with all-boundary rigid support with shear flows action

2021 ◽  
Vol 1027 ◽  
pp. 012020
Author(s):  
O Mitrofanov ◽  
M Osman
Keyword(s):  
Shear Flows ◽  
Asymmetric Structure ◽  
Composite Panels ◽  
Rigid Support ◽  
Buckling Behavior ◽  
Post Buckling

Designing of Thin Composite Panels with the Post-Buckling Behavior Considering Rigid Support and Loading with Shear Flows

2021 ◽  
Vol 887 ◽  
pp. 657-661
Author(s):  
O. Mitrofanov ◽  
O. Mazen
Keyword(s):  
Shear Flows ◽  
Solution Method ◽  
Linear Problem ◽  
Rigid Support ◽  
Optimal Parameters ◽  
Aircraft Structures ◽  
Buckling Behavior ◽  
Non Linear ◽  
Post Buckling ◽  
Support Conditions

Geometrically non-linear problem of orthotropic thin rectangular panel post-buckling behavior with shear is solved. Deflection function takes all-boundary rigid support conditions into account. Based on derived solution method of smooth panels design which can be used for aircraft structures rib and spar webs optimal parameters is suggested.

scholarly journals Post-buckling behavior estimation of rigidly supported cylindrical composite panels in case shear

2021 ◽  
Vol 2094 (4) ◽  
pp. 042078
Author(s):  
O V Mitrofanov ◽  
M Osman
Keyword(s):  
Linear Problem ◽  
Nonlinear Behavior ◽  
Cylindrical Panel ◽  
Geometrically Nonlinear ◽  
Rigid Support ◽  
Buckling Behavior ◽  
Nonlinear Stress ◽  
Cylindrical Panels ◽  
Post Buckling ◽  
Composite Cylindrical Panel

Abstract We present the solution of the geometrically nonlinear problem of the shear-critical behavior of a thin composite cylindrical panel of small curvature of orthotropic structure. The obtained solution considers the conditions of all-round rigid support. The expression for determining the membrane stresses arising in the supercritical state is given. When considering a linear problem, expressions for determining the critical shear flow are given. A method for determining the nonlinear stress-strain state in the overcritical state for a given thickness and stacking of an orthotropic panel is presented. The obtained solutions can be used in the design of load-bearing cylindrical panels, as well as in the analysis of geometrically nonlinear behavior of defects such as delaminations.

Post-buckling behavior of composite panels in the presence of unstable delaminations

2001 ◽  
Vol 51 (3) ◽  
pp. 301-309 ◽  
Author(s):  
P. Gaudenzi ◽  
P. Perugini ◽  
A. Riccio
Keyword(s):  
Composite Panels ◽  
Buckling Behavior ◽  
Post Buckling

Buckling Behavior of Tire Breaker Structure

1983 ◽  
Vol 11 (1) ◽  
pp. 3-19
Author(s):  
T. Akasaka ◽  
S. Yamazaki ◽  
K. Asano
Keyword(s):  
Elastic Foundation ◽  
Elastic Moduli ◽  
Wave Length ◽  
Bending Moment ◽  
Experimental Results ◽  
Automobile Tire ◽  
Buckling Behavior ◽  
Post Buckling ◽  
Steel Cord ◽  
Interlaminar Shear

Abstract The buckled wave length and the critical in-plane bending moment of laminated long composite strips of cord-reinforced rubber sheets on an elastic foundation is analyzed by Galerkin's method, with consideration of interlaminar shear deformation. An approximate formula for the wave length is given in terms of cord angle, elastic moduli of the constituent rubber and steel cord, and several structural dimensions. The calculated wave length for a 165SR13 automobile tire with steel breakers (belts) was very close to experimental results. An additional study was then conducted on the post-buckling behavior of a laminated biased composite beam on an elastic foundation. This beam is subjected to axial compression. The calculated relationship between the buckled wave rise and the compressive membrane force also agreed well with experimental results.

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