Longitudinal Channel Controller Design Of The Target Missile Aircraft

Target missile is used to simulate the dynamics of physical targets to be attacked, and is an important technical indicator equipment in performance test for the development, shaping, batch inspection, testing of weapon system. As a simulation dummy missile, the target missile control system design methods and design is consistent with real missile. The main difficulties of the target missile controller design are the complex motion model and the existence of a large number of uncertain factors,This paper discussed the control system design of a subsonic cruise dummy missile, focusing on its longitudinal channel controller design. The system model was established using MATLAB. The control requirements and their implementation methods for engineering were analyzed, and a controller design based on the traditional PID was proposed. The design of fuzzy PID controller was adopt to take the shifts of system parameters into account. In order to improve the robustbility of the system, a controller was designed based on H∞methods.The process parameters or model structure often changes with time and work environment because of noise and load disturbance. This demonstrated that the PID parameters setting are not depended on the mathematical model and must be able to be adjusted online to meet the requirements of real-time control. Therefore, a classical PID controller combined with a fuzzy controller was employed to adjust the PID parameters on-line. The simulation results showed that the fuzzy controller made the PID controller more effective and adaptive.As the cruise missile in flight, the altitude, speed and other flight environment parameters are time-variant, which make the missile dynamics also time-variance. So the projectile parameters are time-varying that linear controller can not meet the general system requirements. In order to get a small linear perturbation model for short-cycle missile campaign, a simplified missile body longitudinal channel model was build which used the angle of attack as state variables in contrast to traditional control methods. The H∞robust control theory combined with the appropriate sensitivity function was applied to design the missile longitudinal channel H∞controller.Simulation results showed that the designed H∞controller was robust to the parameter perturbation of the system, with dynamic performance, and less significant jitter. The effect of the controller design was verified in practical project by flight test evaluation under the condition of the absence of altitude sensor. The aircraft altitude control was implemented by tracking the pitch angle and the result precision is comparative. The methods used in this thesis can be referred by similar aircraft controller design.