In this paper results of numerical analysis of the ground resonance are shown. This analysis is performed making use of the complete model of the one-main rotor helicopter. This model is adopted from flight mechanics. For the basic analysis it is assumed that the helicopter fuselage is a rigid body and the main rotor consists of four rigid blades. Each blade performs motions about its horizontal flapping hinge and vertical lagging hinge. The tail rotor is treated as a hingeless and weightless source of thrust, which equilibrates the drag moment and ensures directional control of the helicopter. For analysis of the ground resonance phenomenon, forces and moments produced by the landing gear are taken into account – their rigidity and damping are included into consideration.


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    Titel :

    Effect of free play in rotor blades hinges on the non-linear ground resonance of a helicopter


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2002-12-01


    Format / Umfang :

    9 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





    Helicopter rotor-blades

    Engineering Index Backfile | 1955


    Free-wakw calculation of helicopter rotor blades

    Liu, X. / Shen, X. / Xue, Z. | British Library Online Contents | 1996


    Ground resonance of a helicopter with inter-connected blades

    Sela, N.M. / Rosen, A. | Tema Archiv | 1991


    Aeroelastic Analysis of Helicopter Rotor Blades

    Landmann, Björn / Wagner, Siegfried | AIAA | 2004