Long, thin-walled, prismatic sections subject to bending moments suffer a nonlinearity in their bending response. Brazier (Late of the Royal Aircraft Establishment, Repts. and Memoranda No. 1081 (M 49), pp. 1-30) noted that such structures suffer crushing forces from the rotated (caused by curvature) compressible/tensile forces that arise as a result of bending. These forces reduce the second moment of area of the section and thus its ability to resist bending loads, leading to a nonlinear bending response. The importance of the Brazier effect lies in its contribution to other potential failure modes, namely local buckling and material failure as well as its effect on static and dynamic behavior caused by the nonlinearity of the bending response. In this paper a methodology is presented to provide analytical solutions to predict the nonlinear bending behavior of flapwise symmetric, thin airfoil sections exhibiting complex, especially curved, multibayed structures, and potentially variable composite material construction. The methodology is based on the separation of longitudinal and circumferential effects and the application of distributed loads to the cross section in order to recreate the Brazier crushing forces. To simplify the analysis, each bay's cross section is initially modeled as a series of straight elements of orthotropic material. Similar to Brazier's analysis, the approach is energy based and separates longitudinal and cross-sectional effects. A distributed crushing force is applied to the cross section. A NACA 0012 profile, divided into two bays through the mid chord, was used as an example to demonstrate the efficacy of the method. To test the validity of the analytical model, bending moment/deflection comparisons were carried out for the various sections using finite element models. The accuracy of the model was shown to be sufficient to give a good first indication of initial nonlinear response of the airfoil, for significantly less computational time than finite element analysis.


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    Titel :

    Brazier effect in multibay airfoil sections


    Weitere Titelangaben:

    Brazier-Effekt in Tragflächen mit dünnwandiger Wabenstruktur


    Beteiligte:

    Erschienen in:

    AIAA Journal ; 43 , 10 ; 2252-2258


    Erscheinungsdatum :

    2005


    Format / Umfang :

    7 Seiten, 11 Bilder, 6 Tabellen, 10 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch





    Brazier Effect in Multibay Airfoil Sections

    Luca Cecchini / Paul Weaver | AIAA | 2005


    The Brazier effect in multi-bay aerofoil sections

    Cecchini, Luca / Weaver, Paul | AIAA | 2004



    AIAA-2004-1522 The Brazier effect in multi-bay aerofoil sections

    Cecchini, L. / Weaver, P. | British Library Conference Proceedings | 2004