This study applies the crack growth resistance curve (R-curve) method to predict the residual strength of a composite fuselage panel with discrete source damage. The R-curve is constructed from the energy release rates computed from cracked tensile plate test specimens at their failure loads. To predict the residual strength of a curved fuselage panel with discrete source damage using the R-curve method, G-curves of the energy release rate of the damaged fuselage panel need to be established. These G-curves are generated for various fuselage pressures over a range of crack lengths. Since this study found that the membrane stiffening effect could significantly reduce the energy release rate at the crack tip of a pressurized fuselage, geometrically nonlinear behavior was considered in the calculations. The residual strength of the damaged fuselage panel was determined by comparing the energy release rates with the 'allowable-like' R-curve. The correlation between the crack growth predictions and the damage progression results obtained from experiments is very good. Therefore, the R-curve method has the potential to be a practical engineering method for predicting the residual strength of damaged fuselage panels.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Residual strength prediction of damaged composite fuselage panel with R-curve method


    Contributors:

    Published in:

    Publication date :

    2006


    Size :

    9 Seiten, 15 Bilder, 1 Tabelle, 22 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    RESIDUAL STRENGTH PREDICTION OF IMPACT DAMAGED

    Yap, J. / Rodney S, R. / Hachenberg, D. et al. | British Library Conference Proceedings | 2004


    Residual Strength Prediction of Fuselage Structures with Multiple Site Damage

    Chen, C.-S. / Wawrzynek, P. A. / Ingraffea, A. R. et al. | British Library Conference Proceedings | 1999


    The repair of damaged fuselage members

    Ofenstein, C.L. | Engineering Index Backfile | 1928


    Bulging Factors for Predicting Residual Strength of Fuselage Panels

    Bukuckas, J. G. / Nguyen, P. V. / Bigelow, C. A. et al. | British Library Conference Proceedings | 1997


    Residual Strength of Fuselage Panels with Wide Spread Fatigue Damage

    Park, J. H. / Singh, R. / Pyo, C. R. et al. | British Library Conference Proceedings | 1993