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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Contributors:

    Publication date :

    1961


    Size :

    22 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    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


    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



    ASSISTED COLLECTIVE PITCH CONTROL SYSTEM FOR A HELICOPTER ROTOR

    LAMANNA ROBERTO | European Patent Office | 2023

    Free access