Abstract: An integrated design methodology considering the simultaneous optimization of structure and trim is developed for the active aeroelastic wing(AAW), based on the genetic algorithm. This method is applied to the design of fighter configuration employing AAW technology. The optimization design for the wing of fighter aircraft is conducted in multiple maneuver conditions of level-flight with roll. The objective is to minimize the structural mass subjected to the constraints of deflections of control surfaces, hinge moments, aerodynamic loads acting on wing root and critical flutter speed. A comparison between the new method and traditional method which utilizes a single control surface, is also presented. The results demonstrate that AAW technology takes the full advantages of structural flexibility by the coordinated deflections of multiple control surfaces, and has significant merits in improving maneuverability and reducing structural mass.