Lateral Acceleration Control Design of a Non-Linear Homing Missile

Abstract

This paper presents the lateral acceleration control design of non-linear missile model using the multiple single objective Pareto sampling method. The LTI controller design for the uncertain plants is carried out by minimising gain-phase margin and tracking frequency domain based performance objectives. The Pareto optimal solutions (corresponding to a given set of weight vectors) are obtained. The selected solution, as illustration, is analysed. The gain-scheduling controller is obtained by the interpolation of zeros, poles and gains, where the smooth deterministic transtion rule is implemented using the TS fuzzy model. The non-linear simulation results show that the selected interpolated controller is a robust tracking controller for all perturbation vertices.