Abstract
A pilot-induced oscillation is a type of instability caused by dynamic couplingbetween the pilot and the aircraft. Linear system analysis reveals that the pilot/aircraft system is unstable during the oscillation event. However, nonlinearities in the feedback system can limit the response variables so that a sustained, constant amplitude limit cycle results. A method is presented to analyze the limit cycle behavior of pilot/aircraft systems as a means of understanding pilot-inducedoscillations and their causes. A new computationaltechnique is considered and a new methodof testing limit cycle stability is presented. An analysisof the YF-12 pilot-inducedoscillation characteristics is used to demonstrate the method.
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