Using MATLAB, a simplified uniform wing was analyzed. The wing was subjected to one-dimensional aerodynamics loads and in-flight maneuvering loads. The skin of the wing was analyzed as composite material for stiffness properties.

 

By inputting stringer properties and skin panel properties, various analyses regarding wing cross-sectional properties, margin of safety at given stress states, and wing displacements will be executed. Given fiber and matrix properties, laminate ply design, and applied stresses, the laminate stiffness properties and margin of safety was analyzed.

 

From this programming project, it can be seen that the forces acting upon the wing largely affect the manner in which the wing functions. By inputting the various loads produced from lift, drag, and weight, the margin of safety can be calculated. Subsequently, the margin of safety can further be used to design aerospace structure properties. By adjusting the section properties of the wing, a greater of margin of safety can be produced.

 

From this programming project, it can be seen that the forces acting upon the wing largely affect the manner in which the wing functions. By inputting the various loads produced from lift, drag, and weight, the margin of safety can be calculated. Subsequently, the margin of safety can further be used to design aerospace structure properties.By adjusting the section properties of the wing, the MATLAB code allowed for design of the structure and produced a greater of margin of safety.