Optimization of an Aeroservoelastic Wing with Distributed Multiple Control Surfaces

This paper considers the aeroelastic optimization of a subsonic transport wing box under a variety of static and dynamic aeroelastic constraints. Three types of design variables are used: structural variables (skin thickness, stiffener details), the quasi-steady deflection scheduling of a series of control surfaces distributed along the trailing edge for maneuver load alleviation and trim attainment, and the design details of a linear quadratic regulator controller (for flutter suppression), which commands oscillatory hinge moments into those same control surfaces. Optimization problems are solved where a closed-loop flutter constraint is forced to satisfy the required flight margin, and mass reduction benefits are realized by relaxing the open-loop flutter requirements.