This paper presents a fatigue parameter identification analysis and response of a cracked helicopter blade in the hovering flight condition reinforced by GFRP fiber. The search for increasingly high performances in the field of the helicopters brings to the development of materials having higher rigidities and specific resistances. The use of the composite material offers a good aeroelastic Stability. On the basis of aerodynamic model, the use of the finite element method makes it possible to develop a three dimensional model of the blade and to establish dynamic equations of the movement. Numerical calculations of the model developed, prove that the Eigen frequencies of helicopter blade were decreased after cracking in the critical zone, and this reduce is nonlinear; however the stress increased with crack propagation. Therefore the modal parameter identification is an important factor for the detection of fatigue in aircraft structures.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Parameter Identification of Crack Growth in Helicopter Blade


    Contributors:
    Chellil, A. (author) / Nour, A. (author) / Lecheb, S. (author) / Chibani, M. (author) / Kebir, H. (author)


    Publication date :

    2013


    Size :

    4 Seiten




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Parameter Identification of Crack Growth in Helicopter Blade

    Chellil, A. ;Nour, A. ;Lecheb, S. | Trans Tech Publications | 2013


    Helicopter blade tips

    Lyothier, R. | NTRS | 1983


    Helicopter Blade Flutter

    N. D. Ham | NTIS | 1973


    Helicopter rotor blade

    WANG HUILING / CAI MENG / TIAN SHUQUAN et al. | European Patent Office | 2021

    Free access

    HELICOPTER ROTOR BLADE

    EREMIN MIKHAIL MIKHAJLOVICH / BORISOV EVGENIJ ALEKSANDROVICH | European Patent Office | 2018

    Free access