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!).
- Refactor the code to be more modular.
- Full documentation corverge.
- Implement others beam cross-sections.
- Implement foil geometric torsion.
- Implement wing sweep.
- Implement foil aerodynamic torsion.
- Implement composite ply analysis.
- Migration to Python.
- Migration to OpenMDAO.
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.
- 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