Structural optimization of flexible aircraft considering aileron efficiency based on experimental aerodynamic forces

Wing's structural optimization of a flexible aircraft was conducted to solve aileron reversal problem utilizing a genetic algorithm. The aileron efficiencies and rates of roll of the aircraft were calculated using nonlinear experimental aerodynamic forces. The emphasis research was wing's structural optimization to a serious flight state which contained the aileron reversal problem. The variations of aileron efficiency and angular velocity of rolling with dynamic pressures were investigated separately based on the aircraft structure before and after the optimization. The flutter characteristics of the aircraft before and after the structural optimization were contrasted. The optimizations to different flight states and a synthesized optimization considering constraints of three different flight states were developed. The affection of angle of attack to the optimization was analyzed. The results show the aileron reversal can be solved using structural optimization in the detailed design phase of the aircraft, and the optimization has no negative effect on the flutter characteristics of the aircraft.