The present invention provides computer implemented methodology that permits the safe landing and recovery of rotorcraft following engine failure. With this invention successful autorotations may be performed from well within the unsafe operating area of the height-velocity profile of a helicopter by employing the fast and robust real-time trajectory optimization algorithm that commands control motion through an intuitive pilot display, or directly in the case of autonomous rotorcraft. The algorithm generates optimal trajectories and control commands via the direct-collocation optimization method, solved using a nonlinear programming problem solver. The control inputs computed are collective pitch and aircraft pitch, which are easily tracked and manipulated by the pilot or converted to control actuator commands for automated operation during autorotation in the case of an autonomous rotorcraft. The formulation of the optimal control problem has been carefully tailored so the solutions resemble those of an expert pilot, accounting for the performance limitations of the rotorcraft and safety concerns.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Autorotation flight control system


    Contributors:

    Publication date :

    2011-07-12


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English





    AUTOROTATION INITIATION SYSTEM

    LAPPOS NICHOLAS D / STRAUSS MICHAEL PETER | European Patent Office | 2016

    Free access



    Hybrid gyrodyne aircraft employing a managed autorotation flight control system

    VANDER MEY JAMES E | European Patent Office | 2018

    Free access