A theoretical analysis, considering unsteady effects, shows that the response to collective pitch while in descending flight is largely dependent upon the rapidity of control application. Experimental tests confirm the theoretical results.


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    Titel :

    Response of a Helicopter Rotor to an Increase in Collective Pitch for the Case of Vertical Flight


    Beteiligte:
    J. Redont (Autor:in) / J. Valensi (Autor:in) / J. Soulez-Lariviere (Autor:in)

    Erscheinungsdatum :

    1961


    Format / Umfang :

    22 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Response of helicopter rotor to increase in collective pitch for case of vertical flight

    Rebont, J. / Valensi, J. / Soulez-Lariviere, J. | Engineering Index Backfile | 1961


    Response of a helicopter rotor to an increase in collective pitch for the case of vertical flight

    Rebont, Jean / Valensi, Jacques / Soulez-Larivière, Jean | TIBKAT | 1961



    ASSISTED COLLECTIVE PITCH CONTROL SYSTEM FOR A HELICOPTER ROTOR

    LAMANNA ROBERTO | Europäisches Patentamt | 2023

    Freier Zugriff

    Response of rotor lift to increase in collective pitch in case of descending flight, regime of rotor being near autorotation

    Rebont, J. / Soulez-Lariviere, J. / Valensi, J. | Engineering Index Backfile | 1960