Quantitative experimental measurements of matrix cracking and delamination using acoustic emission

Scholey, Jonathan J.; Wilcox, Paul D.; Wisnom, Michael R; Friswell, Michael I.

doi:10.1016/j.compositesa.2010.01.008

Cited by 91 publications

(52 citation statements)

References 17 publications

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“…However, in high damping composites materials such as glass fiber resin polymer, higher frequency components may experience greater attenuation rates than the lower frequency components, which may lead to inaccurate information especially in the study of failure characterization. For instance, consider the case of matrix cracking in composite plates which was found to be dominated by the extensional mode (Scholey et al, 2010). If AE transducers are not placed at the appropriate distance from the source, the strength of the extensional waves might be attenuated and lost along their way to the sensors, thus losing the information.…”

Section: Introductionmentioning

confidence: 99%

“…Moreover, there is a significant challenge for a reliable AE based SHM system for composite structures due to the anisotropic nature of the materials. Much research has been undertaken to create more reliable quantitative AE for the SHM of composite structures (Scholey et al, 2010;Scholey et al, 2009). A recent study proved modal acoustic emission (MAE) to be the preferred method for source location detection and failure characterization.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

An Investigation of Acoustic Emission Signal Attenuation for Monitoring of Progressive Failure in Fiberglass Reinforced Composite Laminates

Hafizi¹,

Epaarachchi²,

Lau³

2013

Int J Automot Mech Eng

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Glass fiber reinforced polymer (GFRP) laminates have a high damping characteristic which can retard ultra-high frequency guided wave signals from propagating along the plate. Owing to this, the identification of an effective area for sensor location is essential. Appropriate signal processing, including wavelet analysis was done, in order to observe the details of an acoustic emission (AE) signal which was emitted at a distance from it source. This study reveals that it is necessary to consider the near field and far field effects of AE signal attenuation, in particular, to determine a composite's micro failure characterization. Consequently, this attenuation behavior was used to develop the non-velocity based source mapping to monitor the progressive failure in composite laminates. This paper details the outcomes of the signal energy attenuation method with an improved algorithm for progressive failure monitoring in fiberglass reinforced composite laminates and the 'effective length' for better AE detection.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

An Investigation of Acoustic Emission Signal Attenuation for Monitoring of Progressive Failure in Fiberglass Reinforced Composite Laminates

Hafizi¹,

Epaarachchi²,

Lau³

2013

Int J Automot Mech Eng

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“…On the second loading, it is not recorded acoustic emission before reaching the previous load at 6 g which checks Kaiser effect [13][14][15][16][17][18][19][20] 614-page 10 (Fig. 19); in other words, no damage is detected before the limit load 6 g.…”

Section: Results and Analysis Of The Testmentioning

confidence: 99%

Complex wing spar design in carbon fiber reinforced composite for a light aerobatic aircraft

Fleuret

Andreani

Lainé

et al. 2016

Mechanics & Industry

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-The challenge concerns the realization of the lightest composite wing for E-FAN prototype 1.0 aircraft. This wing must be dismantled and must support critical loads for aerobatics. The bonding conception between the composites parts must transfer the high loads. This article presents a methodology to design a multi-materials structure with a complex geometry of varying thickness. So, the mechanical behavior must be known for the structure, as well as their weaknesses which can involve the rupture. For that, numerical simulations are elaborated in taken into account the constraints inherent in the manufacturing processes and DGAC's requirements (Direction Générale de l'Aviation Civile, French Authorities for Civil Aviation). The predictive character of these models is realized by numerical and experimental results correlations in order to optimize the numerical model accuracy. Indeed, the complete spar's sizing is validated by static rupture tests. This last point requires the building of a special testing equipment which is able to generate a load compared to the one applied in flight. Moreover, the testing metrology is used to quantify the accuracy level of models. Wing spar, central spar and central/wing bonding are qualified by DGAC for flight.

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“…Ciampa and Meo [25] proposed a new algorithm for the AE localization and flexural group velocity determination in anisotropic structures. Hill et al [26], Scholey et al [27], and Gutkin et al [28] explored the failure mechanisms including the matrix cracking and delamination of composite laminates by AE. Furthermore, Czigány [29] proved it possible to correlate the AE features such as the number of events, the amplitude, and energy to the physical properties of composites.…”

Section: Introductionmentioning

confidence: 99%

A Study on the Intralaminar Damage and Interlaminar Delamination of Carbon Fiber Composite Laminates Under Three-Point Bending Using Acoustic Emission

Liu

Yang

Wang

et al. 2014

J Fail. Anal. and Preven.

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The complicated failure mechanisms are always distinct features of composite materials which largely affect the stiffness and strength as well as the structural integrity. Yet, until now there are still no mature methods based on various test approaches for accurately predicting the failure mechanisms and damage evolution behaviors of composite structures by considering the effects of loads, environments, and material defects. This research designs and prepares the [0°1 6 //0°1 6 ], [30°1 6 // 30°1 6 ], and [15°/À15°] 3s //[15°/À15°] 3s carbon fiber composite specimens with initial interlaminar cracks, and performs the single-leg and over-leg three-point bending mechanical experiments and acoustic emission (AE) tests of composite specimens under 70°C temperature. The effects of the layup patterns, the loading conditions, and the initial interlaminar crack length on the intralaminar damage and interlaminar delamination behaviors of composite laminates are comparatively studied by analyzing the response process of the AE characteristic parameters including the amplitude, energy, and counting. The AE analysis provides theoretical and technique support for further elucidating the complicated failure mechanisms and their interactions of carbon fiber composite laminates.Keywords Carbon fiber composite laminates Á Intralaminar damage and interlaminar delamination Á Acoustic emission (AE) test Á Single-leg three-point bending (SLB) and over-leg three-point bending (OLB)

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Quantitative experimental measurements of matrix cracking and delamination using acoustic emission

Cited by 91 publications

References 17 publications

An Investigation of Acoustic Emission Signal Attenuation for Monitoring of Progressive Failure in Fiberglass Reinforced Composite Laminates

An Investigation of Acoustic Emission Signal Attenuation for Monitoring of Progressive Failure in Fiberglass Reinforced Composite Laminates

Complex wing spar design in carbon fiber reinforced composite for a light aerobatic aircraft

A Study on the Intralaminar Damage and Interlaminar Delamination of Carbon Fiber Composite Laminates Under Three-Point Bending Using Acoustic Emission

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