Integrated guidance and control based on backstepping and input-to-state stability

This paper presents an approach of integrated guidance and control (IGC) design for interception of maneuvering targets (evaders). An IGC model with uncertainties in the pitch plane is formulated, and the IGC approach is developed via backstepping scheme. Theoretical analysis is shown that the design approach makes the line-of-sight (LOS) rate be input-to-state stable (ISS) with respect to target maneuvers and missile model uncertainties, and the stability of the missile dynamics can be guaranteed as well. The numerical simulation confirms the effectiveness of the proposed design approach.