Visualization of Delaminations in Composite Structures Using a Baseline-Free, Sparse Array Imaging Technique Based on Nonlinear Lamb Wave Propagation

Tabatabaeipour, Morteza; Hettler, Jan; Delrue, Steven; Abeele, Koen Van Den

doi:10.3813/aaa.919128

Cited by 19 publications

(19 citation statements)

References 29 publications

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“…The result of the experiment showed that damage detection and localization is possible with the RAPID algorithm. Since the correlation coefficient is sensitive to frequency changes or flight time variations 25 and SAPS focus on amplitude changes, the fusion combining multiple indicators could be considered. However, some limitations still exist for the basic RAPID-Algorithm due to peak intensity at the intersection points.…”

Section: Resultsmentioning

confidence: 99%

Structural health monitoring of an adhesively bonded CFRP aircraft fuselage by ultrasonic Lamb Waves

Weiland

Hesser

Xiong

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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The aviation industry faces the challenge of offering aircraft that are lighter, more economical, and safer. One of the solutions is to increase the use of composites. For these materials, adhesive bonding has proven to be the appropriate joining technology. To check these adhesive joints, costly and time-consuming maintenance measures are carried out. An intelligent Structural Health Monitoring (SHM) system can extend these intervals and allow the use of a predictive maintenance system. This paper describes the method of Ultrasonic Lamb Waves for monitoring a adhesively bonded Carbon Fiber Reinforced Polymer (CFRP) aircraft fuselage. Prior to this, the production of a segment of a fuselage and the characterization of the materials (CFRP and adhesive) is shown. Afterwards the method of Ultrasonic Lamb Waves with the use of piezoelectric transducers and signal processing based on the Reconstruction Algorithm for Probabilistic Inspection of Damage (RAPID) algorithm are explained. At the end, the experimental evaluation of an undamaged and a damaged fuselage structure is done. The results have shown the possibility of RAPID algorithm for damage detection on adhesive. An outlook on future work is given.

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Section: Resultsmentioning

confidence: 99%

Structural health monitoring of an adhesively bonded CFRP aircraft fuselage by ultrasonic Lamb Waves

Weiland

Hesser

Xiong

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The damaged index selected is the Subtraction Scaling Method (SSM) [23], which normalizes the compared signals and calculates the area between them (Figure 10) through integration, in the analyzed time section nT of the signal (7).…”

Section: Imaging Algorithmmentioning

confidence: 99%

“…An alternative to the traditional procedure of damage detection (i.e., baseline vs. damaged) is the evaluation comparing two tests in the damaged state conditions (baseline-free), but varying some conditions of the excitation (amplitude of the excitation signal [23], multi-frequency tests [24], etc.). However, since this methodology is based on the appearance of nonlinearities in the structure response (e.g., non-uniform signal's envelope distribution variation, appearance of higher-order harmonics or changes in phase velocity), the possible inherent nonlinearities of the composite material make the application of this method not suitable to all geometries (e.g., the geometry generates itself nonlinearities in the guided waves).…”

Section: Introductionmentioning

confidence: 99%

Influence and Compensation of Temperature Effects for Damage Detection and Localization in Aerospace Composites

Azuara

Barrera

2020

Sensors

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Structural Health Monitoring (SHM) of Carbon Fiber Reinforced Polymers (CFRP) has become, recently, in a promising methodology for the field of Non-Destructive Inspection (NDI), specially based on Ultrasonic Guided Waves (UGW), particularly Lamb waves using Piezoelectric Transducers (PZT). However, the Environmental and Operational Conditions (EOC) perform an important role on the physical characteristics of the waves, mainly the temperature. Some of these effects are phase shifting, amplitude changes and time of flight (ToF) variations. In this paper, a compensation method for evaluating and compensating the effects of the temperature is carried out, performing a data-driven methodology to calculate the features from a dataset of typical temperature values obtained from a thermoset matrix pristine plate, with a transducer network attached. In addition, the methodology is tested on the same sample after an impact damage is carried out on it, using RAPID (Reconstruction Algorithm for Probabilistic Inspection of Damage) and its geometrical variant (RAPID-G) to calculate the location of the damage.

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“…One way for identifying the Lamb wave modes that are propagating in the sample is by using 2D FFT. 34 2D FFT graphs are obtained by measuring the wave signal along a straight line as shown in Figure 4. In Figure 4, 64 signals are measured along a straight line on the left side of the hole for calculating the 2D FFT.…”

Section: Finite Element Modelmentioning

confidence: 99%

Investigation of the scattering of Lamb waves from a generalized circular cavity by using Poisson/Mindlin plate theories and numerical simulation

Sedaghati

Honarvar

Tabatabaeipour

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part C:

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A mathematical model for the scattering of a symmetric [Formula: see text] Lamb wave mode from a circular cavity in an isotropic plate is developed that can handle both symmetric and asymmetric single- and double-sided blind holes. The theoretical formulation is based on Mindlin and Poisson plate theories. A finite element model is also utilized to extract the scattering patterns of Lamb waves from various cases of a generalized circular cavity. Two-dimensional FFT analysis is used to determine the transmitted and reflected Lamb wave modes when the incident wave interacts with either symmetric (through-hole and double-sided blind hole) or asymmetric (blind hole and double-sided blind hole) cavities. Results indicate that the remaining thickness of a cavity zone and the type of a cavity are two key parameters in the scattering pattern. For asymmetric cavities, the shape of the scattering pattern of the mode-converted [Formula: see text] mode does not vary significantly. However, the amplitude of the scattering pattern shows noticeable changes in the out-of-plane component of the displacement. Results obtained from the proposed theory and finite element model are in good agreement with previously published data.

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Visualization of Delaminations in Composite Structures Using a Baseline-Free, Sparse Array Imaging Technique Based on Nonlinear Lamb Wave Propagation

Cited by 19 publications

References 29 publications

Structural health monitoring of an adhesively bonded CFRP aircraft fuselage by ultrasonic Lamb Waves

Structural health monitoring of an adhesively bonded CFRP aircraft fuselage by ultrasonic Lamb Waves

Influence and Compensation of Temperature Effects for Damage Detection and Localization in Aerospace Composites

Investigation of the scattering of Lamb waves from a generalized circular cavity by using Poisson/Mindlin plate theories and numerical simulation

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