Research On Design Method Of Small Precision Guided Ammunition Controller

This paper relies on the demand for small precision guided missile control technology,and focuses on the time domain,frequency domain performance and parameter design methods of overload autopilot with different structures,and provides theoretical basis for the development of corresponding guided missiles in our country.This paper takes the axisymmetric aerodynamic layout of the guided missiles as the research object,establishes the mathematical model of the linearized missile control system for the design of overload autopilot,and uses the state space and transfer function to characterize the missile system.The influence of normal layout and canard layout on transfer function is also analyzed.The structure of the traditional two-loop overload autopilot is analyzed.The parameters of the overload autopilot are solved by the time domain method and the frequency domain method respectively.The performance of the system is analyzed through simulation.Among them,the parameter design method of two-loop overload autopilot based on amplitude and phase margin is deduced,and the algorithm steps are given.At the same time,the best design results are applied to two aerodynamic layouts to analyze the influence of aerodynamic layout on the autopilot system.The structure of the traditional three-loop overload autopilot is analyzed.The three-loop structural parameters are solved by using the pole configuration method and the amplitude-phase margin method respectively.The time-frequency characteristics and robustness of the three-loop driver under different design results are compared and analyzed.And then explain the impact of structural parameters on the overall performance.Using model reference adaptive control(MRAC)theory,a model reference adaptive autopilot for missile-guidance was designed.The model reference adaptive control method based on Lyapunov theory is introduced,and two different adaptive structures are proposed.Because the damping loop is closest to the projectile,the uncertainty and interference are more,so the model references the adaptive structure to control the damping loop.The time-domain performance of traditional two-loop overload autopilot and model reference adaptive autopilot were compared,and the influence of parameters is illustrated.An improved method of model reference adaptive control method—L1 adaptive control method—is further studied and applied to overload autopilot.The structure of L1 adaptive controller is introduced and the design method is given.Through simulation,the robust performance of the designed L1 adaptive autopilot was explained by the aerodynamic parameter bias,and the performances of the two loops,the three loops,the model reference adaptive,and the L1 adaptive autopilot were compared and analyzed.Finally,the influence of system parameters of L1 adaptive autopilot on system performance is analyzed.