Composite material selection for aircraft structures based on experimental and numerical evaluation of mechanical properties

In this paper determination of mechanical properties composite material using experimental and numerical approach is presented. The a laminate obtained in the experiment are used for verification numerically values, as well estimation load-carrying capacities engine cover light aircraft. Composite specimens, consisting epoxy matrix glass fibers with orientation angles 0º, 450, 900, have been made according to standards, were investigated tensile three-point bending tests. strength, elasticity modulus, strain, force at failure evaluated then compared values simulations aim verifying FE model prediction structural laminates. Good agreement provides solid foundation further improvements model.