Abstract The stress-strain state of thin-walled aircraft structures such as a wing or fuselage made of composite materials is determined based on the beam theory. The laminated skin is orthotropic. The solution was obtained without using the centroidal principal section axes and subdividing the problem in shear and torsion. A calculation variant with skin discretization along the section contour was studied.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Analysis of thin-walled stiffened rods using the beam theory


    Beteiligte:
    Shataev, V. G. (Autor:in) / Shataev, P. A. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2011-03-01


    Format / Umfang :

    7 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Aerothermoelastic Analysis and Optimization of Stiffened Thin-Walled Structures

    Halim, Lenard J. / Sahu, Sejal / Kennedy, Graeme et al. | AIAA | 2022


    Thin-walled rods with semiopened profiles

    Kobelev, V. | Tema Archiv | 2013


    Thin-Walled Rods with Semi-opened Profiles

    Kobelev, Vladimir | Springer Verlag | 2021


    Computationally Efficient Analysis and Optimization of Stiffened Thin-Walled Panels in Shear

    Awie Viljoen / Andries Visser / Albert Groenwold | AIAA | 2005