In this paper, the analysis of fatigue crack propagation on the folding beams mounted on the rear fuselage of a helicopter is performed under complex flight and folding load spectra; a preliminary cumulative damage fatigue analysis is used to select the zone of the structure where cracking is most likely to occur. A damage tolerance analysis is then carried out in the selected zone using an FEM-based approach in conjunction with a Three-Dimensional (3D) automatic crack propagation algorithm developed by the authors. The submodelling technique is used to obtain accurate results in the assessment area with a limited increase in the amount of time required for calculations. The numerical approach is validated by the experimental results of full-scale fatigue tests on the rear fuselage of the helicopter.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    3D fatigue crack propagation analysis of a helicopter component


    Additional title:

    Dreidimensionale Ermüdungsrissausbreitungsanalyse einer Hubschrauberkomponente


    Contributors:


    Publication date :

    2007


    Size :

    17 Seiten, 14 Bilder, 4 Tabellen, 21 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Life prediction of helicopter planetary carrier plate fatigue crack propagation

    Fan, Lei / Wang, Shaoping / Zhang, Chao et al. | British Library Online Contents | 2016



    Analysis of fatigue crack propagation

    Liu, H. W. | TIBKAT | 1972


    Fatigue Crack Propagation

    Alderliesten, René | Springer Verlag | 2017