The study upon bistable mechanism is a branch of the research on the Compliant Mechanism field, wich are structures that uses it s flexibility to perform a certain task. Bistable Mechanism s main feature is the high flexibitily wich involves large deflections, so that the desired motion is comparable to its size, needing to take into account the nonlinear force-deflection relationship. Through these large deflections, the mechanical structure is able to transit from one equilibrium state to the other, maintaining its position without the necessity to apply a constant force. The study of large deflection modeling on beams is fundamental since these elements are used in a wide variety of bistable mechanism designs, enabling the development of flexible structures that avoids the mechanical friction between adjacent elements, reducing the frame wear without losing its precision and reliability. All these features present on bistable mechanism are of interest to the aerospace industry. This work proposes to develop a structure with bistable properties, that can be applied on a UAV (Unmanned Aerial Vehicle). Through numerical analysis with Finite Element Method (FEM) different structural configurations will be compared in order to obtain an ideal configurantion for the problem.