The flexibility matrices for the unassembled structural elements are discussed and a more concise form developed appropriate to the fuselage structure. A general method is given for obtaining self-equilibrating flange load and shear flow systems in a single-cell fuselage, the primary redundancies being defined by a simple transformation matrix. The particular matrix based on the orthogonal stress systems for a circular section is especially convenient. A slight extension of the equations leads also to alternative statically equivalent stress systems in the cover.


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    Titel :

    The Analysis of Fuselages of Arbitrary Cross-section and Taper


    Untertitel :

    A DSIR Sponsored Research Programme on the Development and Application of the Matrix Force Method and the Digital Computer


    Beteiligte:
    Argyris, J.H. (Autor:in) / Kelsey, S. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1959-05-01


    Format / Umfang :

    11 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    The Analysis of Fuselages of Arbitrary Cross-section and Taper

    Argyris, J.H. / Kelsey, S. | Emerald Group Publishing | 1959


    The Analysis of Fuselages of Arbitrary Cross-section and Taper

    Argyris, J.H. / Kelsey, S. | Emerald Group Publishing | 1961


    The Analysis of Fuselages of Arbitrary Cross-section and Taper

    Argyris, J.H. / Kelsey, S. | Emerald Group Publishing | 1961


    The Analysis of Fuselages of Arbitrary Cross-section and Taper

    Argyris, J.H. / Kelsey, S. | Emerald Group Publishing | 1959


    The Analysis of Fuselages of Arbitrary Cross-section and Taper

    Argyris, J.H. / Kelsey, S. | Emerald Group Publishing | 1959