Thermal buckling analysis of laminated composite shell panel embedded with shape memory alloy fibre under TD and TID

Abstract

Laminated composite shell panels are increasingly used in aeronautical, marine and mechanical industries as well as in other fields of modern technology because of its advance mechanical properties. It is well known that the composites have high strength to weight ratio and stiffness to weight ratio as compared to any conventional materials like concrete, metal, and wood. As the uses of the composites in different industries have increased which leads to their analysis through mathematical, experimental and/or simulation based model for accurate design and subsequent manufacturing.The mathematical model is developed based on higher order shear deformation theory (HSDT) to count the exact flexure of the laminate. The buckling behaviour is evaluated based on the Green-Lagrange strain-displacement equations for in-plane strains to account the large deflections under uniform temperature loading. The nonlinear material behaviour of shape memory alloy is introduced through a marching technique. The responses are obtained using variational principle in conjunction with suitable isoparametric finite element modelling based on the MATLAB code. In addition to that, a simulation model is also being developed in ANSYS environment using ANSYS parametric design language code for laminated composites curved panel and the corresponding responses are compared with those available literatures. The effects of layup sequence, thickness ratio, ply angle, support conditions and temperature dependence material properties on thermal buckling load is obtained and discussed.