Buckling and postbuckling behavior of shell type structures under thermo mechanical loads

Abstract

The thermomechanical buckling and postbuckling behavior of layered composite shell type structure are considered with the finite element method (FEM) under the combination of temperature load and applied mechanical loads. To account for through-thickness shear deformation effects, the thermal elastic, Higher-Order Shear deformation Theory (HOST) is used in this study. The refined higher order theories, that takes into account the effect of transverse normal deformation, is used to develop discrete finite element models for the thermal buckling analysis of composite laminates. Attention in this study is focused on analyzing the temperature effects on buckling and postbuckling behavior of thin shell structural components. Special attention in this paper is focused on studying of values of the hole in curved panel on thermal buckling behavior and consequently to expend and upgrade previously conducted investigation. Using FEM, a broader observation of the critical temperature of loss of stability depending on the size of the hole was conducted. The presented numerical results based on HOST can be used as versatile and accurate method for buckling and postbuckling analyzes of thin-walled laminated plates under thermo-mechanical loads.

Computational Fluid Dynamics and Strength Analysis of Composite UAV Wing

“…For structural analysis of sandwich and thin-walled composite wing Finite Element Method (FEM) was used [9, 11-14, 19, 25, 26]. These results, later on, are compared with the own experimental test results [10,15,23,27,28]. After the numerical stress analysis of the UAV composite structure, usually, experimental tests are undertaken.…”