Using differential spread laser infrared thermography to detect delamination and impact damage in CFRP

Wang, Qiang; Hu, Qiuping; Qiu, Jinxing; Pei, Cuixiang; Zhou, Hongbin

doi:10.1016/j.infrared.2020.103282

Cited by 16 publications

(4 citation statements)

References 19 publications

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“…Carbon fiber reinforced polymer/plastic (CFRP) composites are widely used in the aerospace industry due to their low weight and high strength properties -including both high strengthto-weight ratio and high stiffness-to-weight ratio. For example, in Bombardier Series C aircraft, CFRP composites account for 46% of the structure [1], while in the Airbus A350 and Boeing 787 it is more than 50% [2]. Despite the higher requirements for military aviation, CFRP composites are also used here on a regular basis.…”

Section: Introductionmentioning

confidence: 99%

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Selected Methods of Modifying the Surface Layer of a Carbon Composite

Kłonica,

Kubit,

Perłowski

et al. 2024

Adv. Sci. Technol. Res. J.

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This article presents the results of a comparative study on the modification of the surface layer of carbon composites. Fibre-reinforced polymer (FRP) composite materials are heterogeneous and anisotropic materials, characterised by high strength, low density, corrosion resistance along with ease of processing and moulding, and are increasingly replacing metal alloys. They are widely used in aviation, automotive and transport applications. One example of a modern composite is carbon fibre-reinforced polymer (CFRP). This study presents the influence of selected modifications of the surface layer of a CFRP composite on the values of free surface energy (SFE) and surface topography. The resulting SFE values were analysed together with the contribution of the polar SFE and dispersive SFE components. The article also presents the test results related to selected 3D surface roughness parameters and includes photographs of the test specimens after surface layer modification. The results were statistically processed in compliance with good research practice.

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Section: Introductionmentioning

confidence: 99%

“…Advances in Science and Technology Research Journal 2024, 18(1), 270-277 Table3. Surface topography with selected 3D surface roughness parameters…”

mentioning

confidence: 99%

Selected Methods of Modifying the Surface Layer of a Carbon Composite

Kłonica,

Kubit,

Perłowski

et al. 2024

Adv. Sci. Technol. Res. J.

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“…Το address this problem, algorithms have been used to represent the sparse and noise modeled as a mixture of Gaussian (MoG) distributions [ 21 ], on the stepped thermography approach [ 22 ] or have used the eddy current pulse-compression thermography (ECPuCT), combining the Barker code modulated eddy current excitation and pulse-compression technique [ 23 ]. IR, with laser thermal stimulation, has also been used to detect delaminations and impact damages in carbon fiber reinforced polymers (CFRPs) [ 24 , 25 ]. Impact damage produced at different impact energies has been successfully detected using eddy current pulsed thermography (ECPT) [ 26 ].…”

Section: Introductionmentioning

confidence: 99%

A Novel Infrared Thermography Sensing Approach for Rapid, Quantitative Assessment of Damage in Aircraft Composites

Farmaki

Exarchos

Tragazikis

et al. 2020

Sensors

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The current necessity of the scientific and industrial community, for reduction of aircraft maintenance cost and duration, prioritizes the need for development of innovative nondestructive techniques enabling fast and reliable defect detection on aircraft fuselage and wing skin parts. Herein, a new low-cost thermographic strategy, termed Pulsed Phase-Informed Lock-in Thermography, operating on the synergy of two independent, active infrared thermography techniques, is reported for the fast and quantitative assessment of superficial and subsurface damage in aircraft-grade composite materials. The two-step approach relies on the fast, initial qualitative assessment, by Pulsed Phase Thermography, of defect location and the identification of the optimal material-intrinsic frequency, over which lock-in thermography is subsequently applied for the quantification of the damage’s dilatational characteristics. A state-of-the-art ultra-compact infrared thermography module envisioned to form part of a fully-automated autonomous nondestructive testing inspection solution for aircraft was conceived, developed, and tested on aircraft-grade composite specimens with impact damages induced at variable energy levels and on a full-scale aircraft fuselage skin composite panel. The latter task was performed in semi-automated mode with the infrared thermography module mounted on the prototype autonomous vortex robot platform. The timescale requirement for a full assessment of damage(s) within the sensor’s field of view is of the order of 60 s which, in combination with the high precision of the methodology, unfolds unprecedented potential towards the reduction in duration and costs of tactical aircraft maintenance, optimization of efficiency and minimization of accidents.

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“…Low velocity impacts can often result in delaminations beneath the surface which are much larger than the area of the impact [ 6 , 7 , 8 ]. Several established Non Destructive Inspection (NDI) techniques are able to accurately indicate sub surface defects, broadly classified as Ultrasonic [ 9 , 10 , 11 ] and Infrared (IR) Thermography [ 12 , 13 , 14 ]. Whilst these techniques are proven and reliable, the component under inspection must be removed from a repair process to either be situated within a specialist testing unit (X-ray) or treated with couplant (ultrasonic) cleaner or powders to increase emissivity (IR) [ 15 ].…”

Section: Introductionmentioning

confidence: 99%

Composite Laminate Delamination Detection Using Transient Thermal Conduction Profiles and Machine Learning Based Data Analysis

Gillespie

Hamilton

Atkinson

et al. 2020

Sensors

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Delaminations within aerospace composites are of particular concern, presenting within composite laminate structures without visible surface indications. Transmission based thermography techniques using contact temperature sensors and surface mounted heat sources are able to detect reductions in thermal conductivity and in turn impact damage and large disbonds can be detected. However delaminations between Carbon Fibre Reinforced Polymer (CFRP) plies are not immediately discoverable using the technique. The use of transient thermal conduction profiles induced from zonal heating of a CFRP laminate to ascertain inter-laminate differences has been demonstrated and the paper builds on this method further by investigating the impact of inter laminate inclusions, in the form of delaminations, to the transient thermal conduction profile of multi-ply bi-axial CFRP laminates. Results demonstrate that as the distance between centre of the heat source and delamination increase, whilst maintaining the delamination within the heated area, the resultant transient thermal conduction profile is measurably different to that of a homogeneous region at the same distance. The method utilises a supervised Support Vector Classification (SVC) algorithm to detect delaminations using temperature data from either the edge of the defect or the centre during a 140 s ramped heating period to 80 °C. An F1 score in the classification of delaminations or no delamination at an overall accuracy of over 99% in both training and with test data separate from the training process has been achieved using data points effected by transient thermal conduction due to structural dissipation at 56.25 mm.

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Using differential spread laser infrared thermography to detect delamination and impact damage in CFRP

Cited by 16 publications

References 19 publications

Selected Methods of Modifying the Surface Layer of a Carbon Composite

Selected Methods of Modifying the Surface Layer of a Carbon Composite

A Novel Infrared Thermography Sensing Approach for Rapid, Quantitative Assessment of Damage in Aircraft Composites

Composite Laminate Delamination Detection Using Transient Thermal Conduction Profiles and Machine Learning Based Data Analysis

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