A series of examples illustrates the application and results of the method previously given for improving the conditioning of the primary redundancies. The transformation matrix giving locally orthogonal redundancies for the parent station is used also to generate the primary self-equilibrating stress systems for sections with different (but related) geometry and varying ring stiffness. A double-cell cross-section is also treated and a brief investigation shows that the general methods developed for establishing primary redundancies in the fuselage can be usefully and economically applied to certain kinds of wing structure. Preparatory to a detailed discussion of cut-outs and modifications in the fuselage structure, the necessary general theory is collected and summarized.


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    Title :

    The Analysis of Fuselages of Arbitrary Cross-section and Taper


    Subtitle :

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


    Contributors:
    Argyris, J.H. (author) / Kelsey, S. (author)


    Publication date :

    1961-03-01


    Size :

    13 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English



    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


    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 | 1959