At high angles-of-attack (AOA) flow separations can produce non-linear and time varying aerodynamic loads, which cannot be predicted with great certainty. Such loads make control system development extremely difficult. A control system has thus been developed which can accomplish on-line reduction of the a-priori uncertainties pertaining to the effective control of the aircraft. The self-organising control system was developed to suppress unacceptable pitch-up tendencies of an aircraft at high AOA, without the use of AOA measurement. The final control system demonstrated good performance for a variety of inputs although performance was not as good in turbulence.


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    Title :

    Self-Organizing Control System for Non-Linear Aircraft Dynamics


    Contributors:
    C. Evans (author)

    Publication date :

    1985


    Size :

    12 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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