The first flight test of an Hinfinity optimal controller was conducted on the Canadian National Research Council Bell 205 airborne simulator in the summer of 1997. The controller worked first time in flight, was stable and controllable, and achieved Level 2 handling qualities ratings. However, there still existed a large gap between the excellent performance obtained in simulation and the performance obtained in flight. Of particular concern was the model on which these initial designs were based, which was a simple six degree-of-freedom linear model that was known to exhibit significant levels of model uncertainty. This paper will describe the development of a higher fidelity simulation model and will report on the impact this model has had on further controller designs and flight tests. Initial findings suggest that the use of a higher order model (including rotor flapping dynamics and an inflow correction factor) in the design process has (i) improved the robustness properties of the controller and (ii) eliminated the need for predictor type filters in the feedback path. Further, compared with initial designs, there has been a certain degree of improvement in the aircraft response characteristics.


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    Title :

    Evaluating Hinfinity controllers on the NRC Bell 205 fly-by-wire helicopter


    Contributors:


    Publication date :

    1999


    Size :

    10 Seiten, 19 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Evaluating Hinfinity controllers on the NRC bell 205 fly-by-wire helicopter

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