Design of Robust Homing Missile Guidance Laws Based on Guaranteed Cost Control

摘要

The purpose of this paper is to design robust guidance laws of the missile to the maneuvering target based on guaranteed cost (GC) control. The robust stabilizing GC controller is designed in terms of linear matrix inequalities (LMIs), and the optimal guaranteed cost (OGC) controller is given. Simulations are implemented by digital control in several cases of maneuvering targets and launching sites, and then performances of proportional navigation (PN), GC and OGC are compared. Simulation results show the effectiveness of the proposed guidance laws.