A helicopter auto-pilot or autonomous flight system can include an autorotation controller configured to adjust a desired trajectory based on a predicted time to ground impact value continuously calculated in response to a failure event. A multi-phase approach can be used in which the calculations for adjusting the desired trajectory depend on the time to ground impact value. In one case, the phases include steady state descent, flare, and touchdown. Flare descent can be fully automated by calculating the time needed to slow the helicopter before entering a landing phase and generating an altitude trajectory (along with control inputs for the helicopter) that will cause the vehicle to land at an appropriate time (the current time plus a prescribed time to impact).


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    Titel :

    HELICOPTER AUTOROTATION CONTROLLER


    Beteiligte:

    Erscheinungsdatum :

    2018-05-10


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    A Fuzzy Logic-Based Controller for Helicopter Autorotation

    Sunberg, Zachary / Rogers, Jonathan | AIAA | 2013


    A Fuzzy Logic-Based Controller for Helicopter Autorotation

    Sunberg, Z. / Rogers, J. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2013


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    Lee, Allan Y. / Bryson, Arthur E., Jr. / Hindson, William S. | NTRS | 1988


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    Abbeel, Pieter / Coates, Adam / Hunter, Timothy et al. | Tema Archiv | 2009