Design Method And Simulation Of Gust Load Alleviation Control System For Civil Airplane

Civil airplane is often disturbed by gust when it cruises. Gust gives the airplane additional load, which increases the dynamic structure load of the airplane. What’s more, fatigue failure happens on the airplane more easily, making life period of the airplane decrease. Also the passengers’riding comfort quality and the burden of steering of the pilot are influenced. This paper points out that the influences on the airplane, passengers and crew members can be restrained by applying gust alleviation system with active control technology. This paper uses the maneuver flaps to restrain the airplane’s additional normal overload given by the gust. And elevator is necessary to balance the pitching moment caused by the deflection of maneuver flaps. Finally, two actuators balance the force and moment caused by the gust. Namely, gust load is restrained effectively. This paper firstly alleviates the gust load with the method of the combination of the decoupling and proportion feedback. However, the integral effect of alleviation is not ideal. Then optimal state controller is used to restrain the gust load. A feedback controller is designed by minimizing the index of property (namely index arrives to an optimal value). Compared to the decoupling method, the result is improved greatly. Finally, this paper uses the robust control method to restrain the gust load. Robust control method is on the basis of the Linear Matrix Inequality, which gets an ideal integral alleviation effect.