Morphing or a shape adaptable structure can be described as a structural system whose shape and structural characteristics can be changed in order to satisfy the operational characteristics alteration. A main type of morphing structures is so-called the bi-stable structures. The interest in bi-stable structures comes from their ability that these structures can have two different stable equilibrium configurations to define a discrete set of stable shapes. The geometrical changes occur with no need to continuously consume power, and mechanical hinges to preserve the structure in each stable shape. It is well known that in the asymmetric composite laminate bi-stability occurs due to residual stresses resulting from differences in coefficients of thermal expansion, and elastic properties in each lamina within the laminate. Consequently when these structures are subjected to a thermal load, one can observe out of plane large deflection and cylindrical configurations that contradict with the classical lamination theory prediction. In this research, the thermal response and stability characteristics of a bi-stable composite plate with different asymmetric composition are considered. Attention was focused on the temperature dependency of laminate mechanical properties, especially on the thermal expansion coefficients of the composite graphite-epoxy plate and the effect of including resin layers on the stability characteristics of the laminate. To this end, Hyer's theory was used to study the relationship between temperature and curvature of asymmetric cured graphite-epoxy laminates in the temperature range. The strain fields were approximated and then used in the expression for the total potential energy, based on the Rayleigh-Ritz technique. The set of the obtained equations were solved by a specifically-written MATLAB program in order to predict the curvatures variation versus temperature. Optical microscopy was used to characterize the laminate composition. The effect of temperature dependency of laminate mechanical properties, resin layers and lay up thickness variations were also investigated by Hyer's theory. The results obtained from the theory were compared with the finite element simulations implemented in ABAQUS software and experimental results and a good correlation was obtained. In order to study the stability characteristics of asymmetric laminates a nonlinear finite element methodology using ABAQUS software was developed to predict the critical loads that responsible for snap-through and snap-back behaviors. The effects of the mentioned factors such as including resin layers and temperature dependency of laminate mechanical properties on the critical loads were also investigated. The results obtained from the finite element simulations were compared with experimental results and a good agreement was obtained. The current research also explores the potential for implementing bi-stable structures for Uninhabited Aerial Vehicle (UAV) wing configuration. To this end, the stability characteristics of a bi-stable tapered composite panel were studied in the ABAQUS software. The morphing of NACA 23012 airfoil flappers with bi-stable structures was also studied. The flappers were modeled by graphite-epoxy asymmetric laminates in the ABAQUS software and the magnitude of loads required to actuate the airfoil section between the stable shapes was evaluated. Keywords: Bi-stable structure, Graphite-epoxy plate, Finite element method, Snap behavior, Morphing airfoil, Thermal response