Morphing wings have a significant impact of aircraft performance in different flight phases. The outer surface of the leading edge is subjected to large deflections leading to large stresses when considering standard materials and structures. The initial requirement of the morphing is that the additional weight of the structure, i.e. kinematic mechanism, should not prevail the benefits of the effect to the aerodynamic performance of the wing. Thus, integrating of metamaterial structures with functionally graded characteristics is beneficial to control bending and axial stiffness while fulfilling the weight limitations. In this work, the leading edge is divided into two regions – outer surface made from functionally graded metamaterials, connected to the kinematic mechanism by joints. The mechanism is consisted of stiff rods connected with joins so that motion has one degree of freedom that is constricted by the actuator. The rods are connected to the outer surface in the mounting points. Deformation and stresses of the leading edge model are computed by the finite element method with finite strain Timoshenko beam theory with the apparent mechanical variables obtained by FEM calculations of the compound outer surface model, where metamaterial with generally non-linear properties is coated with flexible skin, where the effect of the boundaries and boundary conditions is also investigated. The required position of the airfoil and static pressures are obtained by aero-elastic optimization. The parameters of the metamaterial geometry and the kinematic mechanism layout is determined by using the neural network regression.