Design of three-dimensional missile guidance law via tunable nonlinear H∞ control with saturation constraint

The three-dimensional missile guidance law with saturating actuator is proposed for the pursuit of an unpredictably manoeuvring target. The proposed guidance law achieves a satisfactorily robust performance without having to solve a complicated nonlinear Hamilton-Jacobi partial differential inequality and without relying on Takagi-Sugeno linear fuzzy models. In the proposed guidance scheme, the nonlinear part of the relative motion equations between the missile and target is first cancelled. Then, a tunable state feedback guidance law is designed to eliminate the effect of external disturbance. The conditions of tunable parameters are also proved to achieve the desired goal. The proposed guidance law can achieve reduced interception time than others, yet it is considerably simpler. An example is proposed to confirm it