Honeycomb sandwich panels are used in aerospace structures for their high stiffness-to-mass ratio. Reducing structural mass is critical in aircraft and spacecraft development due to its direct impact on payload capacity and operational costs. Typically, hexagonal honeycombs manufactured by cold expansion of periodically bonded strips of metal or foils of other materials are used for sandwich construction. With rapid development in additive manufacturing, other core shapes with higher specific stiffness can now be considered as an alternative. The authors of this paper had previously evaluated triangular cores to have higher or comparable specific moduli as compared with other two-dimensional core shapes. Further, the panels constructed using triangular cores had higher stiffness than traditional hexagonal core panels. To consider practical use of the triangular cores, elastic-plastic structural analysis is performed to evaluate the strength and failure of sandwich panel construction. Load bearing capacity of triangular core panels under three-point bending, in-plane compressive loading, and transverse shear loading is evaluated using finite element software ABAQUS/Explicit. The comparison made between triangular core and hexagonal core sandwich panels having the same cell size and relative density showed that triangular cores outperform hexagonal cores for applications where in-plane loading is dominant, whereas, in terms of transverse shear and out-of-plane loading, triangular core panels tend to fail at lower loads and lower deflections.


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    Titel :

    Failure of Hexagonal and Triangular Honeycomb Core Sandwich Panels


    Beteiligte:

    Erschienen in:

    AIAA Journal ; 58 , 11 ; 4923-4940


    Erscheinungsdatum :

    2020-09-24


    Format / Umfang :

    18 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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