Maneuver Trim Optimization Techniques for Active Aeroelastic Wings

A new method for performing trim optimization of Active Aeroelastic Wing (AAW) technology is presented. The method is based on posing the trim problem as a linear program and solving it with the simplex method. Trim optimization is then integrated with the structural design process in a sequential manner, such that new optimal deflections of the control surfaces are computed for every structural design iteration. The use of the simplex method for trim optimization allowed the elimination of non- physical constraints that had to be imposed when a gradient-based method was used. This resulted in significantly better objectives for the trim optimization. The sequential AAW design process was demonstrated on a lightweight fighter type aircraft performing symmetric and antisymmetric maneuvers at subsonic and supersonic speeds. The concurrent trim and structural optimization resulted in a significantly lighter structure compared to a structure designed with conventional control technology and to a structure employing AAW technology with fixed control surface deflections.