Wing weight optimization model restrictions based on aeroelastic sensibility studies

The wings structural design of an aircraft involves the interaction of various technologies. Nowadays an integrated project must result in a compromise solution based on the final objective of the aircraft, i.e. it should optimize performance, aerodynamic characteristics, weight, flexibility, flight qualities or dynamic behavior, among others. Usually the objective of an aircraft in its preliminary design phase is to reduce the weight to the maximum, knowing that it will always increase during the projects development and will influence many technologies. Therefore a mass optimization model is necessary during the wings structural design. In parallel it should be considered that preliminary aeroelastic sensibility studies are important, due to the fact that these have an impact to the wings optimal stiffness. The objective of the work presented here is to demonstrate the importance of an integrated study of a mass optimization model including restrictions originated from aeroelastic studies. A method for applying the stiffness restrictions will be presented resulting in a practical example.