This work considers a metallic aeroelastic wingbox model seeded with runout blade stiffeners along the skins. Topology optimization is conducted within the shell webs of the stiffeners in order to add cutouts and holes for mass reduction. This optimization is done with a global–local approach in order to moderate the computational cost: aeroelastic loads are computed at the wing level, but the topology and sizing optimization are conducted at the panel level. Each panel is optimized separately under stress, buckling, and adjacency constraints; and it is periodically reassembled to update the trimmed aeroelastic loads. The resulting topology is baselined against a design with standard full-depth solid stiffener blades, and it is found to weigh 7.43% less.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Aeroelastic Wingbox Stiffener Topology Optimization


    Beteiligte:

    Erschienen in:

    Journal of Aircraft ; 55 , 3 ; 1244-1251


    Erscheinungsdatum :

    01.05.2018




    Medientyp :

    Aufsatz (Konferenz) , Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch