Two types of guidance systems 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 that the integrated two-loop autopilot-guidance law can manipulate the inner autopilot dynamics, resulting in the same performance as the integrated single-loop guidance law. The performance of the integrated two-loop autopilot-guidance diagram is shown to be highly dependent on the chosen autopilot block diagram.
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