Theoretical analysis, considering unsteady effects, shows that response to collective pitch while in descending flight is largely dependent upon rapidity of control application; experimental tests confirm results. Translation from Technique et Science Aeronautiques n 3 May-June 1959 p 177-83.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

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


    Weitere Titelangaben:

    NASA -- Tech Translation


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


    Erscheinungsdatum :

    1961


    Format / Umfang :

    20 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    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