Comprehensive Load Alleviation Control And Simulation For A High Flexible Aircraft

Nowadays, the technology of the high-altitude, long endurance unmanned air vehicles(UAV) has become the research focus for the scientists in the aeroelastic field. It's crucial to make the nonlinear aeroelastic research of the high-aspect ratio wing because that the wing of such aircraft has the characteristics of a larger aspect ratio and a bigger static deformation. Especially in the mission of flight, to get the gust response of wing and control the gust response when the aircraft is going through the gust cannot be ignored anymore.In this paper, a finite element dynamic model of the structure is established considering the geometric nonlinearity of the high-aspect ratio wing on the NASTRAN platform. And then make nonlinear aeroelasticity balancing research of the high-aspect ratio wing on the basis of the aerodynamic model of the Double Lattice Method. Then the linearized modes can be getted at the state of the balancing. Comparing with the original linear modes, we can make out the effects of the geometric nonlinear factors on the modal.And then we can get the flutter analysis and gust response analysis with the original linear modes and the linearized modes to make out the contribution to the flutter analysis results and gust response analysis results.At last, a state-space equation has established of the wing with a control surface through the rational function approximation method. In addition, the Modal Predictive Control method is established to control the gust response. It turned out that the geometric nonlinearity makes the modes of the wing changed, and then its flutter point reduced, the gust response more true and accurate. Also the control system can reduce the gust response efficiently.