The subject of the paper is to show an optimal aircraft's structure analysis made by students of UACJ using diverse software's such as MATLAB, SolidWorks, Ansys to model and calculate shear force, bending moment, moment of inertia, and all structure loads. The analysis includes wing's structure, fuselage's structure divided by three section, nose, central fuselage and tail, as well as tail assembly. Data in this research show methodologies and tools applied to accomplish the final design.