Integrated Guidance and Control for Homing Missiles with Terminal Angular Constraint in Three Dimension Space

A three dimension integrated guidance and control (3D-IGC) system for homing missiles with terminal angle constraint is designed. Firstly, a nonlinear mathematical model of the homing missile is established. In order to deal with the problem of multiple states regulation of such a nonlinear system, an adaptive multiple sliding surface control methodology is deduced. The frame of 3D-IGC law is accomplished by associating with the backstepping method. The digital simulation results verify that the proposed control law can both satisfy the accuracy of target interception and the constrained conditions of terminal angular. Moreover, it shows strong robustness against parameter uncertainties.