Delamination Propagation Study on Aircraft Composite Rib Subjected to Fatigue Loading

2020 ◽  
Vol 20 (4) ◽  
pp. 1351-1363
Author(s):  
V. Sivakumar ◽  
P. Gautham Barathwaj ◽  
M. Santosh Kumar ◽  
D. Srikar
Keyword(s):  
Fatigue Loading ◽  
Delamination Propagation

Damage Self-Diagnosis in Carbon Fiber-Reinforced Composites Under Fatigue Loading

2010 ◽  
Author(s):  
Yves Ngabonziza ◽  
Claudia Boldrini ◽  
Benjamin Liaw ◽  
Jackie Li ◽  
Feridun Delale
Keyword(s):  
Carbon Fiber ◽  
Fatigue Loading ◽  
Carbon Fiber Composites ◽  
Reinforced Composites ◽  
Resistance Change ◽  
Dcb Specimen ◽  
Interlaminar Crack ◽  
Carbon Fiber Reinforced Composites ◽  
Delamination Propagation ◽  
Probe Measurements

An experimental study was conducted to sense interlaminar delamination in carbon-fiber composites utilizing inherent material piezoresistivity. Damage detection was carried out using discrete electrodes mounted on a Double Cantilever Beam (DCB) specimen. The DCB composite specimens were tested for fatigue interlaminar fracture. The traditional two-point probe and four-point probe technique were employed to measure the through-thickness electrical resistance change. Optical marker method was also used to detect interlaminar crack growth. The results show that the two-point probe measurements did not capture effectively the delamination propagation while the four-point probe measurement showed a promising sensing capability in terms of delamination propagation.

Experimental investigation and phenomenological modeling of hygrothermal effect on tensile fatigue behavior of carbon/epoxy plain weave laminates

2018 ◽  
Vol 52 (27) ◽  
pp. 3803-3818 ◽  
Author(s):  
M Khay ◽  
AD Ngo ◽  
R Ganesan
Keyword(s):  
Fatigue Life ◽  
Composite Laminates ◽  
Fatigue Behavior ◽  
Tensile Load ◽  
Fatigue Loading ◽  
Stiffness Degradation ◽  
Plain Weave ◽  
Hygrothermal Effect ◽  
Tensile Fatigue ◽  
Delamination Propagation

The purpose of this paper is to study the hygrothermal effect on fatigue behavior of quasi-isotropic carbon/epoxy plain weave aerospace laminates containing artificial flaw under axial tension–tension loading. Dry and wet specimens were tested at tensile load-controlled cyclic loading with a stress ratio R = 0.1 and a load frequency of 7 Hz at room temperature (RT) and at 82℃ under different stress levels. Allowable stiffness change as a failure criterion was used to determine the delamination propagation onset threshold under cyclic tensile loading at each environmental condition. The delamination propagation onset was verified using the ultrasonic imaging (C-Scan) technique. The experimental results show that (1) fatigue life of CFRP specimens was more individually affected by moisture than by temperature and (2) combined moisture and temperature cause a drastic decrease in fatigue life. Finally, an investigation of the effect of hygrothermal conditions on stiffness degradation and damage of composite laminates subjected to tensile fatigue loading has been also carried. On the basis of the residual stiffness degradation, a damage variable was presented and phenomenological damage models were proposed by employing fatigue modulus and secant modulus concepts as measure of material damage.

Experimental Characterization of Monotonic and Fatigue Delamination of Novel Underfill Materials

2006 ◽  
Vol 128 (4) ◽  
pp. 405-411 ◽  
Author(s):  
Saketh Mahalingam ◽  
Kunal Goray ◽  
Sandeep Tonapi ◽  
Suresh K. Sitaraman
Keyword(s):  
Flip Chip ◽  
Fatigue Loading ◽  
Experimental Characterization ◽  
Material Interfaces ◽  
Interfacial Delamination ◽  
Mechanical Fatigue ◽  
Fine Pitch ◽  
Processing Steps ◽  
Delamination Propagation

No-flow underfill materials reduce assembly processing steps and can potentially be used in fine-pitch flip chip on organic board assemblies. Such no-flow underfills, when filled with nano-scale fillers, can significantly enhance the solder bump reliability, if the underfills do not prematurely delaminate or crack. Therefore, it is necessary to understand the risk of underfill delamination during assembly and during further thermal excursions. In this paper, the interface between silicon nitride (SiN) passivation and a nano-filled underfill (NFU) material is characterized under monotonic as well as thermo-mechanical fatigue loading, and fracture parameters have been obtained from such experimental characterization. The passivation-underfill interfacial delamination propagation under monotonic loading has been studied through a fixtureless residual stress induced decohesion (RSID) test. The propagation of interfacial delamination under thermo-mechanical fatigue loading has been studied using sandwiched assemblies and a model for delamination propagation has been developed. The characterization results obtained from this work can be used to assess the delamination propagation in flip-chip assemblies. Though the methods presented in this paper have been applied to nano-filled, no-flow underfill materials, their application is not limited to such materials or material interfaces.

Inhibition of RANKL-mediated bone remodeling decreases bone damage and improves strength in response to fatigue loading

2014 ◽  
Author(s):  
Nicolas Bonnet ◽  
Maude Gerbaix ◽  
Paul Kostenuik ◽  
Mike Ominsky ◽  
Serge Ferrari
Keyword(s):  
Bone Remodeling ◽  
Fatigue Loading ◽  
Bone Damage

Experimental analysis of thermal and damage evolutions of DCFC under static and fatigue loading

2016 ◽  
Vol 26 (2) ◽  
pp. 165-184 ◽  
Author(s):  
Jefri Bale ◽  
Emmanuel Valot ◽  
Martine Monin ◽  
Olivier Polit ◽  
Claude Bathias ◽  
...  
Keyword(s):  
Experimental Analysis ◽  
Fatigue Loading

scholarly journals Low-Cycle Fatigue Crack Initiation Simulation and Life Prediction of Powder Superalloy Considering Inclusion-Matrix Interface Debonding

Materials ◽  
2021 ◽  
Vol 14 (14) ◽  
pp. 4018
Author(s):  
Shuming Zhang ◽  
Yuanming Xu ◽  
Hao Fu ◽  
Yaowei Wen ◽  
Yibing Wang ◽  
...  
Keyword(s):  
Finite Element ◽  
Crack Initiation ◽  
Life Prediction ◽  
Damage Mechanics ◽  
Low Cycle Fatigue ◽  
Fatigue Crack Initiation ◽  
Fatigue Loading ◽  
Interface Debonding ◽  
Damage Evolution Equation ◽  
Finite Element Software

From the perspective of damage mechanics, the damage parameters were introduced as the characterizing quantity of the decrease in the mechanical properties of powder superalloy material FGH96 under fatigue loading. By deriving a damage evolution equation, a fatigue life prediction model of powder superalloy containing inclusions was constructed based on damage mechanics. The specimens containing elliptical subsurface inclusions and semielliptical surface inclusions were considered. The CONTA172 and TARGE169 elements of finite element software (ANSYS) were used to simulate the interfacial debonding between the inclusions and matrix, and the interface crack initiation life was calculated. Through finite element modeling, the stress field evolution during the interface debonding was traced by simulation. Finally, the effect of the position and shape size of inclusions on interface debonding was explored.

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