Helicopter rotor blades are made of fiber-reinforced composite materials that are prone to matrix cracking. Matrix cracking precedes more serious damage mechanisms such as delamination and fiber breakage and is therefore a useful indicator of structural health. In the present study, the effect or matrix cracking on composite blade stiffness and deflections is investigated. A stiff in-plane rotor blade with a rectangular box and two-cell airfoil section with [0 / +/-45 / 90]% family of laminates is considered. It is observed that the stiffness decreases rapidly in initial phase of matrix cracking and then becomes saturated. Study of the behavior of composite rotor blade from matrix cracking in single, two and complete lamina group show a bending stiffness loss of 6-12 percent and a torsion stiffness loss or 25-30 percent at the point where matrix cracking saturates, and more severe forms of damage such as debonding/delamination and fiber breakage begin.


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    Title :

    Modeling multi-layer matrix cracking in thin walled composite rotor blades


    Additional title:

    Mathematisches Modellierung von Matrixrissen in Flügelblättern aus dünnwandigen Verbundstoffen


    Contributors:

    Published in:

    Publication date :

    2005


    Size :

    13 Seiten, 10 Bilder, 2 Tabellen, 45 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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