This paper describes a strategy for predicting internal damage in a laminated composite structure, when subjected to low-velocity impact. The aim was to obtain a better understanding of and cure for the notorious reduction in strength of aircraft compression panels when they suffered barely visible impact damage (BVID). A finite element model is presented which incorporates the non-linear behaviour due to gross deformation, interlaminar delamination and in-plane fibre and matrix failure. The strategy is validated by impact tests for a wide range of carbon/epoxy composite structures ranging from small stiff plates to realistic aircraft compression panels. It is demonstrated that the finite element model is capable of predicting impact damage in laminated composite structures and thus could be used as a design tool.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Impact damage in composite aircraft structures - experimental testing and numerical simulation


    Contributors:
    Zhang, X. (author)


    Publication date :

    1998


    Size :

    15 Seiten, 15 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English






    Ground vehicle blunt impact damage formation to composite aircraft structures

    Kim, Hyonny / DeFrancisci, Gabriela K. / Chen, Zhi M. | Tema Archive | 2014


    Numerical simulation of composite structures under impact

    Kermanidis, T. / Labeas, G. / Apostolopoulos, C. et al. | Tema Archive | 1998


    Evaluation of Impact Damage in Composite Structures Using Ultrasonic Testing

    Wronkowicz-Katunin Angelika / Dragan Krzysztof | DOAJ | 2018

    Free access