Proprotor and cantilever wing aeroelastic behavior is applied to a gimballed rotor and a hingeless rotor to develop an analytical model for prediction of tilting proprotor aircraft dynamics. Particular attention is given to: the influence of coupled flap/lag bending modes; the influence of rotor blade torsion degrees of freedom on proprotor dynamics; and, to a constant coefficient approximation representing the dynamics in nonaxial flow through the rotor. The following are also examined: the number of blade bending and torsion modes required; the influence of the rotor aerodynamic model; the influence of the blade trim bending deflection; the importance of the rotor rotational speed degree of freedom; and the effect of the wing aerodynamic forces. The origin of the significant influence of the blade pitch motion on the proprotor dynamics is discussed. (Author)


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    Titel :

    Analytical Modeling Requirements for Tilting Proprotor Aircraft Dynamics


    Beteiligte:
    W. Johnson (Autor:in)

    Erscheinungsdatum :

    1975


    Format / Umfang :

    59 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch