Autopilot Control Parameter Gain Scheduling Method Design

This thesis emphatically discussed how to design missile’s control loop----autopilot.On the condition of linearization of missile model by means of minor parameter method,longitudinal control loop adopts control structure of three-loop with pseudo-angle of attack feedback,rotation control loop adopts control structure of PD.They all take advantage of adaptive control design idea based on gain scheduling to select and design the parameter.Autopilot of longitudinal control loop takes advantage of the looping method to design from inner loop to outer loop,principal design index is frequency domain index,as the aiding methods are root locus method, time domain index and autopilot’s open loop frequency at actuator are checked up to ensure the rapidity and stability of autopilot. When designing from outer loop to inner loop with the method of undetermined coefficients, the index of outer loop and control parameter are connected,appropriate index of outer loop are selected,check out the index which is the inner loop performance and range of control parameter, as the aiding index is the obligatory target of inner loop to complete the design of autopilot. To complete the design of control parameter of rotation loop,rotation control loop takes frequency domain index ae the main design index,while pole-zero separation principle is applied.Then,the design result of autopilot of three control loops is used to complete6DOF trajectory simulation and similarities and differences between the two design methods is also introduced.In view of autopilot’s difficulties in the practical application,such as filtering,lever arm correction,shock of flight attitude and so on,this thesis puts forward how such problems happen and how to solve them,and further points out the optimization direction of autopilot.