In the recent years, morphing or shape-adaptive structures increasingly being considered as a solution for better performance of aircraft. These structures change their shape and operating characteristics as a response to changes in the environmental and load conditions. Current designs used in morphing structures consist of complex assemblies of rigid bodies hinged to the main structure and several actuators. To improve morphing structures, bi-stable composite structures could provide an interesting alternative to traditional designs, thanks to their high strength to weight ratio and multiple equilibrium configurations that can be maintained without the need for continuous energy supply. In this regard many studies have been done on the static and dynamic response of bi-stable composite structures. However, hygrothermal variability with environmental conditions, low stiffness, low snap-through load, and restrictive configurations of bi-stable composite laminates limit their application. To address some of these limitations, bi-stable hybrid composite laminates are proposed as a suitable alternative for the conventional bi-stable composite structures. According to the above explanations, in the first part of this thesis, the static and dynamic responses of bi-stable hybrid composite laminates (BHCLs) with an inner isotropic metal layer [0 n /Metal/90 n ] T are scrutinized analytically and experimentally, and their behavior are compared to bi-stable pure composite laminates (BPCLs) including [0 n /90 n ] T . In the analytical method, the nonlinear static equations are extracted using the principle of minimizing the total potential energy and the Rayleigh-Ritz method. The stable configurations, out of plane displacement and static snap through load are investigated. The results show that adding an inner metal layer to BPCLs has the potential to increase the curvature and static load carrying capability up to two and five times, respectively when compared to a BPCLs with the same thickness. The analytical method are developed based on Hamilton’s principle to extract the nonlinear differential dynamic equations and investigate the natural frequency and dynamic response under base excitation. In order to validate the analytical results, several BPCLs and BHCLs are fabricated and further experimental analysis are performed to characterize the major curvatures, out of plane displacement, snap-through load, damping viscous ratio, the first natural frequency and corresponding mode shape, dynamic response under base excitation, and critical base excitation that causes the snapping between the two different stable shapes. In another part of the thesis, a new category of BHCLs that contains multiple metal strips in the middle layer are introduced. The laminates are simulated using finite element analysis. The effect of the number, width, thickness, and mechanical properties (thermal expansion coefficient and Young's modulus) of the metal strips on the static characteristics of the laminate are numerically investigated in ABAQUS and experimentally validated. The results show that the new category of BHCLs will give designers the more flexibility to tune the parameters for a desired application. Fabrication of several BHCLs with metal strips in the middle layer is another innovation of this thesis. Keywords : Bi-stable hybrid composite laminate, thermal and mechanical loading, vibration response, static response, Hamilton principle, finite element methods.