In this paper, Semiloof shell finite element formulation has been extended to thermal stress analysis of laminated plates and shells. The accuracy of the formulation has been verified using sample problems available in the literature. Thermal stresses in cross-ply and angle-ply laminated plates and shells subjected to thermal gradients across the thickness are presented for different boundary conditions, taking into account the temperature dependence of the material properties. The behaviour of laminates under thermal load is found to be different from that under mechanical loads in certain respects. © 1988.

R. Kari Thangaratnam

- Palaninathan

J. Ramachandran

IIT Madras is a public technical and research university located in Chennai, Tamil Nadu. Founded in 1959, it is recognised as an Institute of National Importance.

IIT Madras has been ranked as the top engineering institute in India for four years in a row by the National Institutional Ranking Framework of the MHRD

It currently offers undergraduate, postgraduate and research degrees across 16 disciplines in Engineering, Sciences, Humanities and Management. About 596 faculty belonging to science and engineering departments and centres of the Institute are engaged in teaching, research and industrial consultancy.

IIT Madras

Thermal stress analysis of laminated composite plates and shells

Computers and Structures

The linear buckling analysis of laminated composite cylindrical and conical shells under thermal load using the finite element method is reported here. Critical temperatures are presented for various cases of cross-ply and angle-ply laminated shells. The effects of radius/thickness ratio, number of layers, ratio of coefficients of thermal expansion, and the angle of fiber orientation have been studied. The results indicate that the buckling behavior of laminated shell under thermal load is different from that of mechanically loaded shell with respect to the angle of fiber orientation. © 1990 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

AIAA Journal

Thermal buckling of laminated composite shells

Buckling analysis of composite laminates for critical temperatures under thermal loads is reported here. The formulation is based on linear theory and the finite element method using semiloof elements. The governing equation for critical temperature corresponding to the bifurcation budding is obtained by equating the second variation of total potential energy to zero. The validation checks on the program are carried out using results on homogeneous isotropic plates available in the literature. Results are presented for: 1. (1) cross-ply and angle-ply laminations with symmetry and antisymmetry stacking, 2. (2) simply supported, clamped and combination of boundary conditions, 3. (3) different aspect ratios, 4. (4) various moduli ratios, 5. (5) uniform and linearly varying temperature across thickness, 6. (6) varying ratios of coefficients of linear thermal expansion, and 7. (7) varying number of layers for given laminate thickness. Certain conclusions have been drawn based on these results. © 1989.

Thermal buckling of composite laminated plates

A simple C0 isoparametric finite element formulation based on a higher-order displacement model for the analysis of symmetric and unsymmetric, composite, and sandwich laminates subjected to a thermal gradient across the thickness is presented. The displacement model accounts for the nonlinear distribution of in-plane displacement components through the plate thickness, and the theory requires no shear correction coefficients. The nine-noded quadratic Lagrangian two-dimensional element is used with five and nine degrees of freedom per node. The accuracy of the formulation is verified by analyzing sample problems available in literature. Numerical results are presented in nondimensional form for symmetric, antisymmetric, and cross-ply laminates, both thick and thin. © 1994 Taylor &amp; Francis Group, LLC.

Journal of Thermal Stresses

Finite element thermal stress analysis of composite laminates using a higher-order theory

Thermal stresses are induced in general due to nonuniform temperature distribution or due to the boundary restriction. Most of the work reported so far deals with either plates with edges clamped in plane of the plate or plates with stress free edges. While studying buckling or post-buckling problems, one should ideally analyse the plates with mixed in-plane boundary conditions. Hence, in the present analysis, thermal stress analysis of skew plates with mixed in-plane boundary conditions using finite element approach is attempted. In addition, the effect of in-plane boundary conditions on the thermal stresses is also discussed. © 1985.

Journal	Computers and Structures
ISSN	00457949
Open Access	No