Detection of Impact Damage on PVA-ECC Beam Using Infrared Thermography

Wu, Jianchao; Xu, Changhang; Qi, Baoxin; Hernandez, Francisco C. Robles

doi:10.3390/app8050839

Cited by 12 publications

(13 citation statements)

References 56 publications

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“…Various nondestructive testing (NDT) techniques have been developed for damage detection in composite structures, including thermography [6], eddy currents [7], and ultrasonic C-scans [8].…”

Section: Introductionmentioning

confidence: 99%

Multimode Guided Wave Detection for Various Composite Damage Types

et al. 2020

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This paper presents a new methodology for detecting various types of composite damage, such as delamination and impact damage, through the application of multimode guided waves. The basic idea is that various wave modes have different interactions with various types of composite damage. Using this method, selective excitations of pure-mode guided waves were achieved using adjustable angle beam transducers (ABTs). The tuning angles of various wave modes were calculated using Snell’s law applied to the theoretical dispersion curves of composite plates. Pitch–catch experiments were conducted on a 2-mm quasi-isotropic carbon fiber-reinforced polymer (CFRP) composite plate to validate the excitations of pure fundamental symmetric mode (S0) and shear horizontal mode (SH0). The generated pure S0 mode and SH0 mode were used to detect and separate the simulated delamination and actual impact damage. It was observed that S0 mode was only sensitive to the impact damage, while SH0 mode was sensitive to both simulated delamination and impact damage. The use of pure S0 and SH0 modes allowed for damage separation. In addition, the proposed method was applied to a 3-mm-thick quasi-isotropic CFRP composite plate using multimode guided wave detection to distinguish between delamination and impact damage. The experimental results demonstrated that the proposed method has a good capability to detect and separate various damage types in composite structures.

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Section: Introductionmentioning

confidence: 99%

Multimode Guided Wave Detection for Various Composite Damage Types

et al. 2020

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“…Impact damage produced at different impact energies has been successfully detected using eddy current pulsed thermography (ECPT) [26]. There are several studies dealing with detection of impact damage with lock-in thermography (LT) and also the reconstruction of the evolution of impact damage in-depth [27][28][29][30]. Benchmarking of thermographic results is commonly based on ultrasonic C-scan techniques [31].…”

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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“…For the locating of the impact source in the panel, some scholars have carried out research based on a variety of methods [22][23][24][25][26][27][28][29][30][31], such as the polyvinylidene fluoride (PVDF) thin film method, fiber grating method, acoustic emission method and so on.…”

Section: Introductionmentioning

confidence: 99%

Impact Location on a Fan-Ring Shaped High-Stiffened Panel Using Adaptive Energy Compensation Threshold Filtering Method

Wang

Rui

et al. 2019

Applied Sciences

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The increase in the number of space debris is a serious threat to the safe operation of in-orbit spacecraft. The propagation law of the impact signal in the stiffened panel of the spacecraft’s sealed bulkhead is very complicated, and there is less research on the impact source location in the high-stiffened panel. In this paper, an adaptive energy compensation threshold filtering (AECTF) method based on acoustic emission is proposed, which can realize large-scale, fast and accurate locating of the impact source on the stiffened panel with less resource consumption. The influence law of the stiffeners on the lamb wave is analyzed by finite element simulation, and the Lamb wave energy factor curve is obtained. The correctness of the simulation is verified by the locating experiment on the impact point. The results show that the proposed AECTF method has better adaptability and can correctly locate the impact points in complicated locations. By selecting the appropriate frequency band to filter the signal, the locating accuracy and stability can be improved. When the frequency band is 100–200 kHz, the locating result is optimal, the average absolute error is 7.0 mm, the average relative error is 0.86%, and the error standard deviation is 3.5 mm. This study will generate fresh insight into the impact location technology of high-stiffened panel and provide a reference for the in-orbit spacecraft health monitoring system.

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Detection of Impact Damage on PVA-ECC Beam Using Infrared Thermography

Cited by 12 publications

References 56 publications

Multimode Guided Wave Detection for Various Composite Damage Types

Multimode Guided Wave Detection for Various Composite Damage Types

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

Impact Location on a Fan-Ring Shaped High-Stiffened Panel Using Adaptive Energy Compensation Threshold Filtering Method

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