Minimum-sensors Flight Control System Research On Unmanned Aircraft

As great benefits are got from the applications of UAV (unmanned air vehicle), especially the applications in military, more and more attentions are paid to the development of UAV in the world. UAV is not safety without flight control system. The thesis studies the minimum-sensors control system. The output Linear Quadratic (LQ) theory is adapted to enhance the efficiency of designing.Firstly, the mathematical model is built. Taking CK1G as object, the motion of UAV is expressed in 12 first-order, coupled ordinary differential equations (ODEs), which is six-degrees-of-freedom (6-DOF) rigid model. Then the model is trimmed and linearizated.In follow, the thesis describes the LQ theory, which is the design method of control law. The LQ theory and arithmetic is described detailed. The LQ is adapted to the flight control law design such as the Normal Acceleration control system.Two kinds of cases are studied: the vertical gyroscope and GPS are equipped; the angle velocity gyroscope and GPS are equipped. The minimum-sensors control system is studied separately for the cases. The LQ is applied in the control law design.Lastly, the controller gains are verified at each design equilibrium point and nonlinear model of CK1G to guarantees stability for actual flight conditions near the equilibrium point.Minimum-sensors control is verified practical in the engineering by intensive simulation.