Coordinated-Turn Control Law Design And Optimize Of B737

The latitude movement of aircraft has strong coupling and poor stability, and takes on strong nonlinear. And also the coupling will bring bad influence to flight control. Coordinated-turn control is one of the latitude control research interests. This thesis adapts traditional PID control, linear-quadratic optimal tracking and robust optimal control to study the design of Boeing 737-800 coordinated-turn law designing.First, aircraft's motion equations are established by the coordinate transformation. Base on linearization method of min-disturbance principle, do linearization disposal to aircraft motion equation. Identify the unknown parameters in the space motion equations from QAR flight data by using evolutionary strategy.Then, adopt traditional PID control method to design coordinated-turn control law. Set up mathematic model of control object; analyze the force situation during coordinated-turn; design the control law and also make simulation. And the experimental result demonstrates after adjusting parameters the control law work effective.Because the integrity of parameters and the accuracy of identification couldn't insure effectively, so couldn't set up accurate mathematic model. In the practically control process, the method of parameter tuning is tedious and requires the designers' experience, PID controller always has not good adjustment and performance. To the trait of aircraft latitude flight control, utilize linear-quadratic optimal tracking control method and robust optimal control method to design Boeing 737-800 coordinated-turn law independently, simulation results show the designed control laws base on two methods have merits and demerits and basically meet the control demands.