Aeroservoelastic tailoring for lateral control enhancement

The purpose of this paper is to illustrate the application of an automated optimization approach to the integrated structural and control design of an aircraft wing and its control surface. The performance index or cost function for optimization is the aileron hinge moment required to sustain a specified terminal roll rate at a chosen design speed at which aeroelastic effects are significant. The design variables used for aileron hinge-moment minimization are the aileron flap-to-chord ratio; the location of the aileron with respect to the roll axis; and the orientations of three advanced composite plies comprising 60% of the wing structure. In addition to presenting the results of the optimization process itself, the study examines the effects of aileron location and advanced composite ply orientation on the terminal roll rate and aileron hinge moment. Optimization is seen to involve a compromise between a laminated structure/aileron combination that is effective in creating large rolling moments and one that minimizes the damping-in-roll. These two requirements are in conflict; the optimization driver must locate a compromise design point by moving the control surface and changing its size while also creating a suitable structural design.