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IntroductionComposite materials are attracting growing interest from many industry sectors, and their use is becoming widespread. This enthusiasm can be explained by their geometric structure designed to impart properties that their elementary constituents do not have individually, and allow them to fulfill many technical functions and achieve new levels of performance. The coupling between composites and metals gives rise to a range of so-called high-tech materials that can fulfill several tasks than traditional composites can't do include bolted joints. These materials can be tailored to suit a wide variety of applications by varying the fiber/ resin system, the alloy type and thickness, stacking sequence, fiber orientation, surface pretreatment technique, etc. They are used specially for advanced aerospace structural.Much research has been conducted to better understand the mechanical responses of these materials to applied loads [1][2][3][4]. However, little has been reported in the open literature on the composite plates buckling due to temperature changes. Biswa [5] solved thermal problems involving buckling of orthotropic plates. Similar problems for anti-symmetric and symmetric plates were resolved by Tauchert and Huang [6]. A more general formulation was proposed by Chen and Chen [7].Many analytical studies have been performed on analyzing the behavior of functionally graded hybrid plates under different types of loading, such as: [8][9][10][11].In this paper, we are interested by the deformation of these plates due at change of temperature. The equilibrium equations are obtained and used to calculate the thermal elastic buckling critical loads for a rectangular thin plate. To derive these equations, nonlinear relationships deformation-displacement was used. To introduce the transverse shear, U and V displacement components are approximated with expressions of high order.

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