A helicopter flight control system is designed to incorporate variable rotor speed while handling torque limits and other constraints. The vertical axis controller uses a fixed non-linear mapping to find the combination of collective pitch and rotor speed to optimize performance in level flight, climbing/descending flight, and steady turns. In this scheme, the controller is open-loop, making it an inexpensive and reliable solution. The mapping is designed to produce a desired power level for a given pilot input. Thus the mapping can take into account the performance limits associated with the vertical axis such as power limits, torque limits, and maximum rate of descent. A model following controller is implemented for the pitch, roll, and yaw axes. The control system is demonstrated using the GENHEL simulation of a UH-60A helicopter.


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    Title :

    Helicopter flight control with variable rotor speed and torque limiting


    Additional title:

    Hubschrauber-Flugregelung mit variabler Rotordrehzahl und Drehmomentbegrenzung


    Contributors:
    Guo, Wei (author) / Horn, Joseph F. (author)

    Published in:

    Publication date :

    2009


    Size :

    11 Seiten, 21 Bilder, 21 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Helicopter Flight Control with Variable Rotor Speed and Torque Limiting

    Guo, W. / Horn, J. / AHS International | British Library Conference Proceedings | 2009


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