Wing Structural Optimization

A set of tools for wing structural optimization in Matlab. This code was orginally developed for the SAE Aerodesign Brasil competition at the UFMG's Aerodesign Team (Uai, Sô! Fly!).

TODO

• Refactor the code to be more modular.
• Full documentation corverge.

Improvements

• Implement others beam cross-sections.
• Implement foil geometric torsion.
• Implement wing sweep.
• Implement foil aerodynamic torsion.
• Implement composite ply analysis.

Next Version

• Migration to Python.
• Migration to OpenMDAO.

Methodology

This approach utilizes the basic elastic equations to evaluate structural stress under a set of specified load conditions.

• Descritize the wing foil and spar cross-section in N sections given a full defined wing and spar geometry.
• Interpolate wing foil section and spar cross-section geometry given the a set of M concetrated loads along the span.
• Evaluate cross-section properties.
• Calculates the M internal loads along the span.
• Evaluate the maximum stress in each cross-section.
• Find the critical stress value acting on the spar.

References

• Greco, M. - Resistência dos Materiais: Uma Abordagem Sintética
• Megson, T.H.G. - Aircraft Structures for Engineering Students
• Airframe and Equipment Engineering Report No. 45, AD-A955 270, 1955
• Mathworks Matlab Optimization Docs