Intelligent Guidance And Control Of Vertical Launching Antiaircraft Missiles

Vertical launching anti-aircraft missile is an important part of the equipment system of the modern anti-air combat. With the worsening of the battlefield environment and update of the aerial attack weapons, it is necessary to improve the tactical performance of the anti-aircraft missile in order to cope with this challenge. Applying the vertical launching technique of anti-aircraft missile, the launching arm of the missile launch vehicle is expected to reach the vertical position rapidly and steadily. In the initial phase of the emission, the attitude angles of missile need to change fleetly.Meanwhile, designing an efficient stable automatic pilot and guidance control law against the high maneuverable object with strong disturbance are required to substantially raise the performance of anti-aircraft missile. In such case, the demand of future anti-air battlefield can be satisifed. Therefore,this work investigates the key technique of the vertical launching anti-aircraft missile. The main works of the thesis are as follows.Firstly, the control of erecting device of the vertical launching anti-aircraft missile is investigated.With the established model, the parameters of this device are selected optimally. To estimate modeling uncertainties and unknown external disturbances, the radial basis function(RBF) neural network based disturbance observer is developed for the system.Considering the high order of the erecting device system model, the backstepping method is utilized to design the controller. Simulation results are presented to demonstrate the effectiveness of the designed control scheme.Secondly, the attitude transfer control of the vertical launching anti-aircraft missile in initial turning stage is studied. The attitude angles are described by the quaternion to deal with the singular points in system model. Then, the active disturbance rejection control(ADRC) method is employed to improve the robustness of system and eliminate the effect caused by the modeling errors.Simulation results show that the good dynamic performance and strong robustness are obtained under the designed controller for the attitude motion.Following, the attitude controller of the vertical launching anti-aircraft missile in steady flight is designed. Afterwards, the skit-to-turn(BTT) automatic pilots are designed in fast loop, slow loop and overload loop respectively by using the ADRC method. Simulation results show that the good dynamic and tracking performance are obtained under the designed automatic pilots.Finally, the guidance law of the vertical launching anti-aircraft missile is studied. The guidance law of the sliding mode variable structure is designed by the zero sight angle speed method. The extended state observer is designed according to the observable error and target maneuver. Then, the parameters of guidance law are adjusted online by establishing the fuzzy logic of the fuzzy control rules. To attack the ultra high-velocity target, the head pursuit is introduced and is combined with the guidance law of the sliding mode in variable structure. The guidance laws in three periods of the prior interception are both considered for the vertical launching control system. Simulation results show that missile could attack target with small miss-distance under the designed guidance law.