AbstractThe current work is a contribution to the potential effect of the aft fuselage stiffness modifications on the flutter characteristics of a T-tail. The rear fuselage is simulated by beam elements, based on a fixed T-tail structure. Their stiffness ranges from 1×105  N-m2 to infinite. The present analyses and discussion predict that a combination of out-of-plane or in-plane bending and torsion of the fuselage, fin, and stabilizer affects modes, and critical flutter and divergence speeds and flutter mechanisms, when the fuselage stiffness continuously varies. With the distinct segmental stiffness of the simulated fuselage, the different flutter results are compared and investigated. This paper also points out that the increasing joint stiffness of the stabilizer and fin can benefit the flutter characteristics. The calculated and analyzed database should be available to use for the structural design of the empennage in engineering


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    T-Tail Flutter Analysis with Simulated Fuselage Stiffness


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2015




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 51.40 Werkstoffe für bestimmte Anwendungsgebiete / 55.60 Raumfahrttechnik
    Lokalklassifikation TIB:    770/7040




    Investigations Concerning the Coupled Wing-Fuselage-Tail Flutter Phenomenon

    W. J. MYKYTOW / T. E. NoLL / L. J. HUTTSELL et al. | AIAA | 1972


    AFFDL investigations concerning the coupled wing-fuselage-tail flutter phenomenon

    HUTTSELL, L. / MYKYTOW, W. / NOLL, T. et al. | AIAA | 1971


    Elevator-fuselage flutter

    Naylor, George A. | SLUB | 1938


    Fuselage stiffness

    Morris, J. | Engineering Index Backfile | 1936