Title of article :
Predictive model to estimate the stress–strain curves of bulk metals using nanoindentation
Author/Authors :
Pelletier، نويسنده , , H.، نويسنده ,
Issue Information :
ماهنامه با شماره پیاپی سال 2006
Pages :
14
From page :
593
To page :
606
Abstract :
Many studies have shown that finite element modeling (FEM) can be used to fit experimental load–displacement data from nanoindentation tests. Most of the experimental data are obtained with sharp indenters. Compared to the spherical case, sharp tips do not directly allow the behavior of tested materials to be deduced because these produce a nominally-constant plastic strain impression. The aim of this work is to construct with FEM an equivalent stress–strain response of a material from a nanoindentation test, done with a pyramidal indenter. The procedure is based on two equations which link the parameters extracted from the experimental load–displacement curve with material parameters, such as Youngʹs modulus E, yield stress Y0 and tangent modulus ET. We have already tested successfully the relations on well-known pure metallic surfaces. However, the load–displacement curve obtained using conical or pyramidal indenters cannot uniquely determine the stress–strain relationship of the indented material. The non-uniqueness of the solution is due to the existence of a characteristic point (εc, σc); for a given elastic modulus, all bilinear stress–strain curves that exhibit the same true stress σc at the specific true strain εC lead to the same loading and unloading indentation curve. We show that the true strain εc is constant for all tested materials (Fe, Zn, Cu, Ni), with an average value of 4.7% for a conical indenter with a half-included angle θ=70.3°. The ratio σc/εc is directly related to the elastic modulus of the indented material and the tip geometry.
Keywords :
Nanoindentation , Finite element method , Elastic–plastic contact
Journal title :
Tribology International
Serial Year :
2006
Journal title :
Tribology International
Record number :
1425326
Link To Document :
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