Abstract
In this paper the μ-synthesis multivariable control design method is applied to the F-117A to meet stability, performance, and disturbance rejection requirements. Using structured singular value (μ) synthesis allows for the direct optimization of robust performance. Performance specifications are weighted transfer functions that express the magnitude and frequency content of external disturbances, pilot commands, atmospheric gusts, and sensor noise. Maximum allowable limits are set for the magnitude and frequency content of generalized tracking errors, actuator activity, handling and ride qualities. Performance specifications and the model set definition are incorporated within a single interconnection structure upon which existing design algorithms can operate.
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