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Non-Local Analysis of Forming Limits of Ductile Material Considering Void growth

Journal of Materials Science & Technology 2003年第4期19卷 294-299页

作者： Youngsuk Kim School of Mechanical Engineering Kyungpook National University702-701DaeguSouth Korea

The current study performed a finite element analysis of the strain localization behavior of a voided ductile material using a non-local plasticity formulation in which the yield strength depends on both an equivalent plastic strain measurement (hardening parameter) and Laplacian equivalent. The introduction of gradient terms to the yield function was found to play an important role in simulating the strain localization behavior of the voided ductile material. The effect of the mesh size and characteristic length on the strain localization were also investigated. An FEM simulation based on the proposed non-local plasticity revealed that the load-strain curves of the voided ductile material subjected to plane strain tension converged to one curve, regardless of the mesh size. In addition, the results using non-local plasticity also exhibited that the dependence of the deformation behavior of the material on the mesh size was much less sensitive than that with classical local plasticity and could be successfully eliminated through the introduction of a large value for the characteristic length.

关键词： Non-local Characteristic length Vbid damage growth Gradient-dependent plasticity Forming limit Strain localization

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ON RESIDUAL COMPRESSIVE STRENGTH PREDICTION OF COMPOSITE SANDWICH PANELS AFTER LOW-VELOCITY IMPACT damage

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Acta Mechanica Solida Sinica 2006年第1期19卷 9-17页

作者： Xie Zonghong Anthony J. Vizzini Tang Qingru College of Astronautics Northwestern Polytechnical University Xi＇an 710072 China Department of Aerospace Engineering Mississippi State University MS 39762 USA Aviation Engineering Institute Civil Aviation Flight University of China Guanghan 618307 China

This paper introduces a nonlinear finite element analysis on damage propagation behavior of composite sandwich panels under in-plane uniaxial quasi-static compression after a low velocity impact. The major damage modes due to the impact, including the residual indentation on the impacted facesheet, the initially crushed core under the impacted area, and the delamination are incorporated into the model. A consequential core crushing mechanism is incorporated into the analysis by using an element deactivation technique. damage propagation behavior, which corresponds to those observed in sandwich compression after impact （SCAI） tests, has been successfully captured in the numerical simulation. The critical far field stress corresponding to the onset of damage propagation at specified critical locations near the damage zone are captured successfully. They show a good correlation with experimental data. These values can be used to effectively predict the residual compressive strength of low-velocity impact damaged composite sandwich panels.

关键词： sandwich structures impact delamination damage growth honeycomb core finite element method

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