Integrated autopilot and guidance design for dual controlled missiles with terminal intercept angle constraint

Two types of integrated guidance systems that enable imposing a desired angle at impact are presented and compared. The guidance laws are designed for a dual controlled missile having both forward control and tail control. The first type is an integrated single-loop guidance law, where the coupling between flight control and guidance loops is taken into account in the derivation process. The second type is an integrated two-loop autopilot-guidance law. In this case, the autopilot loop is designed separately from the guidance one, but all the states are fed-back into the guidance loop. It is demonstrated, via the notion of Pareto front and sample runs, that the two integrated designs can achieve the same performance if a multi-input autopilot configuration is used in the integrated two-loop case.