A Phantom Paired Element Based Discrete Crack Network (DCN) Toolkit for Residual Strength Prediction of Laminated Composites

2015 ◽  
Author(s):  
Eugene Fang ◽  
Xiaodong Cui ◽  
Tingting Zhang ◽  
Xiaohu Liu ◽  
Jim Lua
Keyword(s):  
Residual Strength ◽  
Laminated Composites ◽  
Strength Prediction ◽  
Crack Network ◽  
Discrete Crack

A discrete crack network toolkit for Abaqus for damage and residual strength prediction of laminated composites

2016 ◽  
Vol 51 (10) ◽  
pp. 1355-1378 ◽  
Author(s):  
Xiaodong Cui ◽  
Eugene Fang ◽  
Jim Lua
Keyword(s):  
Air Force ◽  
Residual Strength ◽  
Laminated Composites ◽  
Matrix Crack ◽  
Matrix Cracking ◽  
Fiber Direction ◽  
Crack Network ◽  
Matrix Cracks ◽  
Damage Progression ◽  
Discrete Crack

The main objective of this article is to exploit a phantom paired element based discrete crack network toolkit for predicting the damage progression and residual strength of laminated composites without and with a hole under tension and compression. Both intra-ply matrix cracking and inter-ply delamination are considered under a co-simulation framework in the discrete crack network toolkit. A mesh-independent kinematic description of discrete matrix cracks is accomplished via user-defined phantom paired solid elements to capture the initiation and evolution of fiber orientation dependent matrix cracking. In-ply matrix crack initiation is realized by inserting a crack along the fiber direction when a matrix driven failure criterion is satisfied and a cohesive injection along the matrix crack interface is applied to account for energy dissipation during matrix crack opening. The delamination failure mode is characterized by applying Abaqus’ cohesive interaction at ply interfaces. The non-linear shear behavior is introduced by employing a power law based curve-fit model and the fiber failure is described using a continuum damage mechanics based model. Both the blind and recalibrated predictions are performed for specimens of three different layups under the Air Force Tech Scout 1 program. The predicted damage progression and the load displacement curves are compared with the testing results provided by the Air Force Research Laboratory.

A continuum damage and discrete crack-based approach for fatigue response and residual strength prediction of notched laminated composites

2017 ◽  
Vol 51 (15) ◽  
pp. 2203-2225 ◽  
Author(s):  
Eugene Fang ◽  
Xiaodong Cui ◽  
Jim Lua
Keyword(s):  
Fatigue Damage ◽  
Air Force ◽  
Residual Strength ◽  
Damage Mechanics ◽  
Finite Thickness ◽  
Strength Prediction ◽  
Continuum Damage ◽  
Failure Initiation ◽  
Damage Characterization ◽  
Discrete Crack

This paper presents a combined continuum damage and discrete crack (CDDC) modelling approach for fatigue damage characterization and post-fatigue residual strength prediction of laminated composite components with a hole. In order to capture both the fatigue cycle-driven material degradation and discrete damage-induced stress concentration and redistribution, an overlapped element approach is developed based on a combined user-defined material (UMAT) and user-defined element (UEL). An Abaqus element coupled with UMAT for fatigue damage characterization is used to detect the location of failure initiation, while the discrete crack network-based (DCN) UEL is applied to insert a crack without remeshing. The intensified stress field induced by the newly inserted matrix crack is used for the evaluation of failure initiation and stiffness degradation. The UMAT for the fatigue analysis has incorporated the stress-cycle ( S-N) curves for the damage evolution characterization associated with matrix and fiber based on the tested S-N curves for plies at their different orientations. A continuum damage mechanics (CDM) approach is used for the fatigue-driven delamination initiation and propagation by insertion of a finite thickness interface layer at each ply interface. Both the blind and recalibrated predictions are performed for specimens of three different layups under the Air Force Tech Scout 1 program. The predicted fatigue failure progression and the stiffness against cycle curves are compared with the test data provided by the Air Force Research Lab (AFRL). In addition, post-fatigue residual strength predictions are performed for these notched specimens under tension and compression.

scholarly journals Research on Residual Strength Prediction Model of Corroded Pipeline Based on Improved PSO-BP

2021 ◽  
Vol 687 (1) ◽  
pp. 012007
Author(s):  
Li Tingke ◽  
Peng Yuanchun ◽  
Li Jiadi ◽  
Dulin ◽  
Lian Xingqin
Keyword(s):  
Prediction Model ◽  
Residual Strength ◽  
Strength Prediction ◽  
Improved Pso

Strength Prediction of Laminated Composites upon Independent Constituent Properties

2015 ◽  
Vol 665 ◽  
pp. 153-156
Author(s):  
Zheng Ming Huang ◽  
Li Min Xin
Keyword(s):  
Ultimate Strength ◽  
Input Data ◽  
Laminated Composites ◽  
Laminated Composite ◽  
Failure Detection ◽  
Strength Prediction ◽  
Internal Stresses ◽  
Matrix Properties

To predict ultimate strength of a laminated composite subjected to any load only using its constituent fiber and matrix properties measured independently, three challenging problems must be resolved with high success. First, internal stresses in the fiber and matrix must be accurately determined. Second, efficient failure detection for laminae and laminate upon the internal stresses must be achieved. Last but not the least, input data for the in-situ strengths of the constituents must be defined correctly from their original counterparts, as the former, different from the latter, are immeasurable. This presentation briefly summarizes our work on the targeted subject. All of the three issues have been systematically addressed with reasonable success.

Residual strength prediction of damaged composite fuselage panel with R-curve method

2006 ◽  
Vol 66 (14) ◽  
pp. 2557-2565 ◽  
Author(s):  
John T. Wang ◽  
Clarence C. Poe ◽  
Damodar R. Ambur ◽  
David W. Sleight
Keyword(s):  
Residual Strength ◽  
Strength Prediction ◽  
Curve Method
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