An inertial stability and tracking control method for the nonlinear driving missile launcher

摘要

An inertial stability and tracking control method based on parameter identification is presented for the nonlinear driving missile launcher. Nonlinear driving structure of the missile launcher is analyzed, and the kinematic relationships and dynamical equations are described. Nonlinear driving part will be identified by the polynomials fitting function. Compared with the traditional inertial stability tracking control, the polynomials fitting function is applied to the inertial decoupling control, which will make the inertial stability control loop linear. The inverse of polynomials fitting function is added to the tracking feedback and feedforward controllers, which can satisfy the requirements of system stability and tracking performance. Finally the proposed method is applied to the mobile launch vehicle. Simulation and experimental results validate the effectiveness of the method.