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|Title:||Étude numérique de linfluence de la vitesse dimpact sur la résistance des pales dhélicoptères à des impacts rasants||Authors:||Aubry, J
|Affiliations:||Department of Mechanical Engineering||Keywords:||Impact
Finite element modelling
|Issue Date:||2012||Part of:||Journal Matériaux & Techniques||Volume:||100||Issue:||6-7||Start page:||713||End page:||721||Conference:||Journées Nationales sur les Composites (17ème : 15-17 June 2011 : Poitiers, France)||Abstract:||
In aeronautics, passenger safety and reliability of structures are essential aspects. For the specific case of helicopters, blades are subjected to impact solicitations. Modelling these phenomena is still difficult and experimental tests often replace the prediction. This work will be focused on the experimental and numerical study of an oblique impact on the skin of the blade. It is equivalent in a first approach to an impact on a sandwich panel made up with a foam core and a thin woven composite skin. The objectives are to identify the mechanisms of damage in the skin for this kind of solicitation for various impact velocities. Thus, an F.E. explicit model has been developed. It relies on the development of a specific damageable element at the bundles scale. Numerical results obtained are correct compared to the experimental study and allow the identification of the damage mechanism of the woven skin.
|Appears in Collections:||Department of Mechanical Engineering|
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