Adaptive integrated guidance and control with actuator failures based on backstepping and input-to-state stability

A fault-tolerant integrated guidance and control law is proposed based on backstepping and input-to-state stability in the presence of actuator failures, target maneuvers and unknown bounded model uncertainties. An adaptive law is designed to estimate the unknown parameter with respect to the actuation effectiveness components. Theoretical analysis is shown that the line-of-sight (LOS) rate is input-to-state stable (ISS), and the stability of the missile dynamics can be guaranteed as well. The numerical simulation results confirm the effectiveness of the fault-tolerant IGC law.