Comparison of damage resistance of CFRP lightweight panels

Found, M.S.; Lamb, J.R.; Moore, Philippa; JONES, M

doi:10.1016/s1359-835x(04)00149-6

Cited by 4 publications

(4 citation statements)

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“…It is worth noting that under the given loading cycles, a lower loading frequency would result in greater damage than a higher one [ 30 , 31 ]. Additionally, the applications of CFRPs for lightweight structures [ 32 , 33 , 34 ] are also notable. Chen et al [ 35 ] tested the mechanical performance and investigated the progressive failure characteristics of CFRP/aluminum joints for lightweight applications.…”

Section: Introductionmentioning

confidence: 99%

Micro-Scale Numerical Simulation of Fatigue Failure for CFRP Subjected to Multiple-Amplitude Cyclic Loadings Based on Entropy Damage Criterion

Deng,

Toda,

Sato

et al. 2023

Materials

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Fatigue failure of carbon fiber-reinforced plastics (CFRPs) under cyclic loadings has attracted the attention of researchers recently. In this study, the entropy-based failure criterion is proposed to investigate the fatigue lifetime of unidirectional CFRPs subjected to multiple-amplitude cyclic loadings. Due to the heterogeneity of CFRPs, a micro-finite element model considering matrix resin and fibers independently is developed, and the entropy-based damage criterion is implemented into a user-subroutine of Abaqus to model the progressive damage of matrix resin. The fatigue lifetime of CFRPs under typical loading sequences consisting of two stages, such as varying from low to high (L-H) or from high to low (H-L) loading sequence, is estimated with the proposed failure criterion. Numerical results show that the initial damage occurs near the area between two fibers, and a transverse crack propagates progressively under the cyclic loading. The difference in predicted lifetime to final failure in L-H and H-L stress levels is 6.3%. Thus, the effect of loading sequence on the fatigue lifetime can be revealed via the proposed entropy-based damage criterion. Comparisons with the conventional linear cumulative damage (LCD) and kinetic crack growth (KCG) theories are also conducted to demonstrate the validity of the proposed method. The entropy-based failure criterion is a promising method to predict the residual strength and fatigue lifetime of CFRP components.

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Section: Introductionmentioning

confidence: 99%

Micro-Scale Numerical Simulation of Fatigue Failure for CFRP Subjected to Multiple-Amplitude Cyclic Loadings Based on Entropy Damage Criterion

Deng,

Toda,

Sato

et al. 2023

Materials

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“…Various investigations have been conducted to quantify the severity of structure damage [25][26][27][28]. In this study, we propose a method of quantifying actual AE using the concept of 'damage index (DI) and appending it to the coordinate localized by waveform similarity between laser-simulated AE and actual AE Based on this method, the damage severity of the structure is mapped.…”

Section: Introductionmentioning

confidence: 99%

Laser-based structural training algorithm for AE localization and damage accumulation visualization in a composite wing skin with various sub-structures

Jung

Lee

2020

Smart Mater. Struct.

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Acoustic emission (AE) is a transient phenomenon in which an elastic wave propagates to a structure as a result of structure damage such as micro-cracks, internal-cracks, friction, fiber breakage and fiber matrix debonding in a structure. AE encompasses a lot of information related to the integrity of the structure. Particularly, AE is used to overcome the difficulties in detecting damages that are hard to detect, such as micro-cracks and internal cracks. Composite structures are widely used in high technology structures due to their high stiffness to weight ratio. However, the source localization in the composite structure has been difficult for years due to variables such as wave propagation direction and speed along the fiber direction. In this paper, we propose laser scan based structural training technique with a single AE sensor (lead zirconate titanate sensor) in a real composite wing skin with a spar and stringers. This technique compensates the difference in characteristics between actual AE and laser-induced elastic wave in the frequency domain using a structural training algorithm. Source localization was performed using cross-correlation based waveform similarity between actual AE and laser-simulated AE A pencil-lead break method, which is a standard method to mimic the AE induced by actual composite damage. The proposed laser scan based structural training technique derive 4.36 mm error distance in average in the actual composite wing skin structure with a spar and stringers. The flexibility of this technique for various amplitude of damaged signals, which induced cracks was verified by using various diameter of pencil-lead. To visualize the accumulated damage, the concept of damage index, which quantify AE is appended at localized point. Finally, we implemented the damage project system to intuitively identify the damage location in large wing skin structures.

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“…The use of composites is a growing reality in many industrial fields, from civil structures [1][2][3] to transport industry and especially in aeronautics components [4][5][6][7][8][9]. Some of their advantages are stiffness, ability to be tailored into complex shapes, strength, corrosion resistance, fatigue properties, and lightweight.…”

Section: Introductionmentioning

confidence: 99%

Cold Plasma Pretreatment of Carbon Fibre Composite Substrates to Improve Adhesive Bonding Performance

Mandolfino

Lertora

Gambaro

2014

Advances in Aerospace Engineering

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The purpose of the paper is to investigate the effects of low pressure plasma treatment on wettability of carbon fibre reinforced polymer samples and on shear properties of adhesive bonded joints based on these substrates. In particular, two plasma process parameters, exposure time and power input, were optimized, performing contact angle evaluation on lap-shear tests. The plasma treatment was also compared with a conventional mechanical abrasion and untreated and only degreased specimens. The experimental results show that choosing the optimal parameters is possible to improve the wettability of composite substrates and reduce the contact angle.

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Comparison of damage resistance of CFRP lightweight panels

Cited by 4 publications

References 0 publications

Micro-Scale Numerical Simulation of Fatigue Failure for CFRP Subjected to Multiple-Amplitude Cyclic Loadings Based on Entropy Damage Criterion

Micro-Scale Numerical Simulation of Fatigue Failure for CFRP Subjected to Multiple-Amplitude Cyclic Loadings Based on Entropy Damage Criterion

Laser-based structural training algorithm for AE localization and damage accumulation visualization in a composite wing skin with various sub-structures

Cold Plasma Pretreatment of Carbon Fibre Composite Substrates to Improve Adhesive Bonding Performance

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