Gliding descent in autorotation is a maneuver used by helicopter pilots in case of engine failure. The landing of a helicopter in autorotation is formulated as a nonlinear optimal control problem. The OH-58A helicopter was used. Helicopter vertical and horizontal velocities, vertical and horizontal displacement, and the rotor angle speed were modeled. An empirical approximation for the induced veloctiy in the vortex-ring state were provided. The cost function of the optimal control problem is a weighted sum of the squared horizontal and vertical components of the helicopter velocity at touchdown. Optimal trajectories are calculated for entry conditions well within the horizontal-vertical restriction curve, with the helicopter initially in hover or forwared flight. The resultant two-point boundary value problem with path equality constraints was successfully solved using the Sequential Gradient Restoration Technique.


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    Titel :

    Optimal Landing of a Helicopter in Autorotation


    Beteiligte:
    A. Y. N. Lee (Autor:in)

    Erscheinungsdatum :

    1985


    Format / Umfang :

    322 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Optimal landing of a helicopter in autorotation

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


    Optimal landing of a helicopter in autorotation

    LEE, ALLAN Y. / BRYSON, ARTHUR E. / HINDSON, WILLIAM S. | AIAA | 1988


    Optimal landing of a helicopter in autorotation

    LEE, A. / BRYSON, JR., A. / HINDSON, W. | AIAA | 1986


    Optimal landing of a helicopter in autorotation

    Lee, A. Y. / Bryson, A. E., Jr. / Hindson, W. S. | NTRS | 1986