Control System Design Of Missile With Large Attack Angle Based On Trajectory Linearization

As the rising of comprehensive national strength and the strengthening of the ballistic missile defense system, it needs to be improved that the attack ability with high precision and the strong penetration of the ballistic missile. It has a high value to control the reentry maneuvering warhead on the large attack angle under hypersonic maneuver flight as it is an important embodiment of ballistic missile's penetration ability. It has large range of speed variation, wide airspace and complex flight environment, causing the flying environment parameters and aerodynamic parameters a wide range of nonlinear change, and serious couplings between the channels. As traditional small disturbance linearization method cannot complete control of the maneuvering warhead, it is imperative to find a suitable nonlinear control method. At first, it uses dynamic inversion control method to design the controller in this paper, then further trajectory linearization controller is designed on the basis of the dynamic inversion controller. Main work is as follows:First of all, according to the characteristics of the maneuvering warhead, after determine the geometric shape of maneuvering warhead, the three-channel six degrees of freedom is provided 12 state variable nonlinear mathematical model, on the basis of reference public literature published at home and abroad. It includes establishment of the dynamics equations and the aerodynamic model. We conducted the characteristic simulation experiment of the warhead, and the open-loop characteristics of maneuvering warhead and the coupling characteristics are analyzed, laying a good foundation for subsequent controller design.Secondly, the controller of dynamic inversion is designed based on the strongly nonlinear and coupling characteristics of maneuvering warhead. The dynamic inversion controller design are divided into inner loop controller and outer loop controller, after both inside and outside of the time-scale separation principle are used to get the system circuit of nonlinear affine model. According to the simulation results, the dynamic inverse controller can realize the maneuvering warhead attitude tracking instructions well, but it is poor in tracking with the maneuvering warhead attitude angle when the system has model error.Finally, aiming at the problems that the dynamic inversion control has, the trajectory linearization controller is designed under the condition of certain theoretical foundation knowledge. Overall, the trajectory linearization controller is also divided into the outer loop controller and the inner loop controller. But every part of the controller adds the linear time-varying controller design on the basis of the pseudo inverse controller where it is also an advantage of trajectory linearization compared with dynamic inversion method. The simulation result shows that the trajectory linearization method performs good attitude tracking orders, and has better robustness to parameter perturbations.