Tensile and Compression Strength Prediction in Laminated Composites by Using Discrete Damage Modeling

2015 ◽  
Author(s):  
Endel V. Iarve ◽  
Kevin H. Hoos ◽  
Michael Braginsky ◽  
Eric Zhou ◽  
David Mollenhauer
Keyword(s):  
Compression Strength ◽  
Laminated Composites ◽  
Strength Prediction ◽  
Damage Modeling ◽  
Discrete Damage Modeling

Static strength prediction in laminated composites by using discrete damage modeling

2016 ◽  
Vol 51 (10) ◽  
pp. 1473-1492 ◽  
Author(s):  
Kevin Hoos ◽  
Endel V Iarve ◽  
Michael Braginsky ◽  
Eric Zhou ◽  
David H Mollenhauer
Keyword(s):  
Compressive Strength ◽  
Input Data ◽  
Damage Mechanics ◽  
Laminated Composites ◽  
Matrix Cracking ◽  
Damage Modeling ◽  
Fiber Failure ◽  
Failure Patterns ◽  
Open Hole ◽  
Discrete Damage Modeling

Discrete Damage Modeling of complex local failure patterns in laminated composites including matrix cracking, delamination, and fiber failure was performed. Discrete Damage Modeling uses the Regularized eXtended Finite Element Method for the simulation of matrix cracking at initially unknown locations and directions independent of the mesh orientation. Cohesive interface model is used both for Mesh Independent Cracking as well as delamination propagation. The fiber failure mode is modeled by two different methods in tension and compression. Tensile failure is predicted by Critical Failure Volume criterion, which takes into account volumetric scaling of tensile strength. Compression fiber failure is simulated with a single parameter continuum damage mechanics model with non-compressibility condition in the failed region. Ply level characterization input data were used for prediction of notched and unnotched laminate strength. All input data required for model application is directly measured by ASTM tests except tensile fiber scaling parameter and compression fiber failure fracture toughness, which were taken from literature sources. The model contains no internal calibration parameters. Tensile and compressive strength of unnotched and open hole composite laminates IM7/977-3 has been predicted and compared with experimental data. Three different layups, [0/45/90/−45]2S, [30/60/90/−60/−30]2S, and the [60/0/−60]3S, were modeled and tested and showed good agreement with experiment in the case of tensile loading, whereas the compressive strength was generally under predicted for unnotched laminates and overpredicted for open hole laminates.

Strength Prediction in Open Hole Composite Laminates by Using Discrete Damage Modeling

AIAA Journal ◽  
2013 ◽  
Vol 51 (4) ◽  
pp. 936-945 ◽  
Author(s):  
Michael J. Swindeman ◽  
Endel V. Iarve ◽  
Robert A. Brockman ◽  
David H. Mollenhauer ◽  
Stephen R. Hallett
Keyword(s):  
Composite Laminates ◽  
Strength Prediction ◽  
Damage Modeling ◽  
Open Hole ◽  
Discrete Damage Modeling

Progressive failure simulation in laminated composites under fatigue loading by using discrete damage modeling

2016 ◽  
Vol 51 (15) ◽  
pp. 2143-2161 ◽  
Author(s):  
Endel V Iarve ◽  
Kevin Hoos ◽  
Michael Braginsky ◽  
Eric Zhou ◽  
David H Mollenhauer
Keyword(s):  
Laminated Composites ◽  
Progressive Failure ◽  
Fatigue Loading ◽  
Matrix Cracking ◽  
Zone Model ◽  
Damage Modeling ◽  
Fiber Failure ◽  
Material History ◽  
Discrete Damage Modeling ◽  
History Variable

The discrete damage modeling method is extended for progressive failure analysis in laminated composites under fatigue loading. Discrete damage modeling uses the regularized extended finite element method for the simulation of matrix cracking at initially unknown locations and directions independent of the mesh orientation. A material history variable in each integration point is introduced and updated after each loading increment, corresponding to certain load amplitude and number of cycles. The accumulation of the material history variable is governed by Palmgren-Miner’s rule. Cohesive zones associated with mesh-independent cracks are inserted when the material history parameter reaches the value of 1. Cohesive zone model consistently describing crack initiation and propagation under fatigue loading without any assumption of initial crack size is proposed. The fatigue properties required for matrix failure prediction include shear and tensile S-N curves as well as Mode I and II Paris law parameters. Tensile fiber failure is assumed unaffected by fatigue. All input data required for model application are directly measured by ASTM tests except tensile fiber scaling parameter and compression fiber failure fracture toughness, which were taken from literature sources. The model contains no internal calibration parameters. Fatigue damage extent, stiffness degradation and residual tensile and compressive strength of IM7/977-3 laminates have been evaluated. Three different layups, [0/45/90/-45]2S, [30/60/90/-60/-30]2S and [60/0/-60]3S, were modeled and tested. The predictions captured most experimental trends and showed good agreement with X-ray CT damage assessment; however, significant further work is required to develop reliable methodology for quantitative composite durability prediction.

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.

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