Replacing the helicopter rotor swashplate and blade pitch control system with on-blade elevon control surfaces for primary flight control may significantly reduce weight and drag to improve mission performance. Simplified analyses are used to examine the basic aeroelastic characteristics of such rotor blades, including pitch and flap dynamic response, elevon reversal, and elevon control effectiveness. The profile power penalty associated with deflections of elevon control surfaces buried within the blade planform is also evaluated. Results suggest that with aeroelastic design for pitch frequencies in the neighborhood of 2/rev, reasonable elevon control effectiveness may be achieved and that, together with collective pitch indexing, the aerodynamic profile power penalty of on-blade control surface deflections may be minimized.


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    Titel :

    Aeroelastic Considerations For Rotorcraft Primary Control with On-Blade Elevons


    Beteiligte:

    Kongress:

    American Helicopter Society 57th Annual Forum and Technology Display ; 2001 ; Washington, DC, United States


    Erscheinungsdatum :

    2001-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    AEROELASTIC CONSIDERATIONS FOR ROTORCRAFT PRIMARY CONTROL WITH ON-BLADE ELEVONS

    Ormiston, R. A. / American Helicopter Society | British Library Conference Proceedings | 2001



    Rotorcraft aeroelastic stability

    Ormiston, Robert A. / Warmbrodt, William G. / Hodges, Dewey H. et al. | NTRS | 1988


    Rotorcraft Aeroelastic Stability

    R. A. Ormiston / W. G. Warmbrodt / D. H. Hodges et al. | NTIS | 1988


    Aeroelastic Analysis for Rotorcraft

    Johnson, W. | NTRS | 1982