Integrated guidance and control for dual-control missiles against ground fixed targets

A scheme of integrated guidance and control (IGC) is proposed for missiles steered by both canard and tail controls against ground fixed targets. The attack angle and pitch rate commands are generated by a guidance law that makes the missile hit the target accurately with a desired terminal attitude angle. Then an IGC law is designed based on generalized small-gain theorem to enforce the commands, and it can be shown that the law enables to maintain stability and performance of the overall system. The numerical simulation confirms the effectiveness of the proposed design approach.