Abstract
The short period longitudinal mode of an F4-E aircraft with additional horizontal canards is unstable in subsonic flight and unsufficiently damped at supersonic speed. The control system has to provide acceptable pole locations according to military specifications for flying qualities. A fixed gain controller is designed, such that the pole region requirements are met in four typical flight conditions simultaneously. For robustness of pole region requirements with respect to one or two sensor failures it turns out, that it is advantageous not to use accelerometers. A controller with three paralleled gyros and dynamic output feedback is designed. The design is performed by a novel parameter space design method.
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