Integrated guidance and control design of missile with terminal impact angle constraint

The problem of integrated guidance and control for missiles against maneuvering target was studied in this paper. Integrated guidance and control model of pitch plane was established on a roll stable missile. The target maneuver was considered as unknown bounded uncertainty. An adaptive integrated guidance and control law was designed by adopting sliding mode control to deal with the uncertainty. The adaptability and robustness were achieved by choosing zero effort miss as the sliding mode surface. The simulation result demonstrates that the integrated guidance and control system can meet the accuracy requirement of hitting the maneuvering target with terminal impact angle constraint.