Research on a H∞ sliding mode algorithm of integrated control and guidance

A new approach about design for supersonic anti-ship missiles guidance laws (GLs) was proposed in this study. Firstly, the normal form of the fourth order state equation for integrated guidance and control loop about the yaw plane was formulated considering target uncertainties and control loop dynamics. Next the proposed GLs adopts the sliding mode control approach with adaptation for known bound of uncertainties based on the fuzzy-neural-network-approximator (FNNA) and H _infin tracking performance index function, which can be employed to approximate the unknown nonlinear function of system. We provide the stability analyses and demonstrate the effectiveness of our scheme. Finally, the simulation results were presented to show the validity of the proposed method.