scholarly journals An Experimental Study of the Cyclic Compression after Impact Behavior of CFRP Composites

2021 ◽  
Vol 5 (11) ◽  
pp. 296
Author(s):  
Raffael Bogenfeld ◽  
Christopher Gorsky
Keyword(s):  
Composite Laminates ◽  
Composite Structures ◽  
Impact Behavior ◽  
Damage Growth ◽  
Compression Load ◽  
Kink Bands ◽  
Cyclic Compression ◽  
Compression After Impact ◽  
Ultimate Failure ◽  
Damage Tolerant

The behavior of impact damaged composite laminates under cyclic load is crucial to achieve a damage tolerant design of composite structures. A sufficient residual strength has to be ensured throughout the entire structural service life. In this study, a set of 27 impacted coupon specimens is subjected to quasi-static and cyclic compression load. After long intervals without detectable damage growth, the specimens fail through the sudden lateral propagation of delamination and fiber kink bands within few load cycles. Ultrasonic inspections were used to reveal the damage size after certain cycle intervals. Through continuous dent depth measurements during the cyclic tests, the evolution of the dent visibility was monitored. These measurements revealed a relaxation of the indentation of up to 90% before ultimate failure occurs. Due to the distinct relaxation and the short growth interval before ultimate failure, this study confirms the no-growth design approach as the preferred method to account for the damage tolerance of stiffened, compression-loaded composite laminates.

Failure Analysis of Laminated Composites under in-Plane Compressive Loading

2012 ◽  
Vol 476-478 ◽  
pp. 583-586
Author(s):  
Yin Huan Yang
Keyword(s):  
Failure Analysis ◽  
Composite Laminates ◽  
Composite Structures ◽  
Parametric Design ◽  
Laminated Composites ◽  
Progressive Failure ◽  
Compressive Loading ◽  
Laminated Composite ◽  
Progressive Failure Analysis ◽  
Ultimate Failure

Failure prediction of laminated composites is performed by progressive failure analysis method. A modified form of Hashin’s failure criterion by Shokrieh is used to detect the failure, where a sudden degradation model is proposed to reduce engineering material constants. The numerical analysis of composite laminates is implemented in ANSYS Parametric Design Language (APDL) with commercial finite element codes ANSYS. The method can predict the initiation and propagation of local damage and response of laminated composite structures from initial loading and ultimate failure. The model has been validated by comparing numerical results with existing experimental results. And then failure analysis specimen fabricated from M40J/Ag80 and investigation on influence of stacking sequences and fiber orientations under in-plane compressive loading have been performed by the proposed model.

Preliminary Review of Physically Based Methodologies for Predicting the Strength of Visibly Damaged Composite Laminates

2010 ◽  
Vol 654-656 ◽  
pp. 2587-2591 ◽  
Author(s):  
Alex Harman ◽  
Andrew Litchfield ◽  
Rodney Thomson
Keyword(s):  
Residual Strength ◽  
Composite Laminates ◽  
Composite Structures ◽  
Prediction Method ◽  
Cost Effective ◽  
Preliminary Review ◽  
Management Guidelines ◽  
Compression After Impact ◽  
Physically Based

Approaches to detect, assess, monitor and repair damage in critical aircraft components fabricated from composite materials are essential for safe and cost effective operation. In metallic aircraft structures, it is common to leave some fractures in situ for a prescribed period until it is convenient to repair, provided strict inspection and verification processes are in place. Under current military aircraft structural management guidelines, visible damage to critical composite components requires either immediate repair or replacement. Much has been learnt about the behaviour of damaged composite structures, but further investigation is required to develop validated residual strength and life prediction tools. A preliminary review of an early physically based, residual strength prediction method was conducted. The accuracy of this method for use in predicting the strength of composite following a complex damage was tested by comparing the results with compression-after-impact test data for a composite laminate representative of F/A 18 fracture critical structure.

Experimental Investigation of Notched CCF300/QY8911 Composite Laminates Subjected to Tension Load

2013 ◽  
Vol 787 ◽  
pp. 352-355
Author(s):  
Hui Min Fu ◽  
Xin Yang ◽  
Yong Bo Zhang ◽  
Zhi Hua Wang
Keyword(s):  
Experimental Study ◽  
Experimental Investigation ◽  
Composite Laminates ◽  
Damage Growth ◽  
Fiber Reinforced Composite ◽  
Pull Out ◽  
Reinforced Composite ◽  
Ultimate Failure ◽  
Hygrothermal Environment ◽  
Environment Condition

An experimental study was carried out to determine the notched tension characteristics of CCF300 fiber reinforced composite subjected to the normal and hygrothermal environment condition. In both conditions, the pull-out propagation was the ultimate failure mode of these specimens. The damage growth can be divided into four separate stages. In the hygrothermal environment condition, greater damage occurred, length of splitting increased and off axis plies were extensively pull-out from the adjacent plies.

Failure Predictions of Laminate under In-Plane Tensile Loading

2012 ◽  
Vol 450-451 ◽  
pp. 370-373
Author(s):  
Yin Huan Yang
Keyword(s):  
Failure Analysis ◽  
Composite Laminates ◽  
Composite Structures ◽  
Parametric Design ◽  
Progressive Failure ◽  
Laminated Composite ◽  
Progressive Failure Analysis ◽  
Proposed Model ◽  
Ultimate Failure ◽  
Failure Predictions

Failure analysis of laminates is performed by progressive failure analysis method. A modified form of Hashin’s failure criterion by Shokrieh is used to detect the failure, where a sudden degradation model is proposed to reduce engineering material constants. The numerical analysis of composite laminates is implemented in ANSYS Parametric Design Language (APDL) with commercial finite element codes ANSYS. The method can predict the initiation and propagation of local damage and response of laminated composite structures from initial loading and ultimate failure. The model has been validated by comparing numerical results with existing experimental results. And then failure analysis specimen fabricated from M40J/Ag80 and investigation on influence of stacking sequences and fiber orientations have been performed by the proposed model.

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