Non-destructive evaluation (NDE) of aerospace composites: structural health monitoring of aerospace structures using guided wave ultrasonics

Veidt, Martin; Liew, Chin Kian

doi:10.1533/9780857093554.3.449

Cited by 9 publications

(7 citation statements)

References 119 publications

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“…The Table 3 shows that none of the measured samples was invalidated by the failed measurement during the tests, since all tests were performed successfully. Within the graphical course of measurements, the results were slightly different, and the samples (11)(12)(13)(14)(15) showed a parabolic course of loading against strain. Figure 14 shows the graphical course of the tensile test of sample "1-130-2" (Figure 14 In terms of recording the interruption of the RFID tag signal by the recording antenna, the samples showed no change.…”

Section: Measurements Using Samples With Rfid Tags: Type Nomentioning

confidence: 93%

“…The aerospace industry has always been the leader in the development of structural health monitoring (SHM) systems, which are key technologies to ensuring the structural integrity of future aircraft structures. There are many types of NDT methods used in the aircraft maintenance sector, but not all are suited for SHM applications due to integration and cost difficulties [15].…”

Section: The Role and Types Of Non-destructive Testingmentioning

confidence: 99%

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Internal Damage Detection of Composite Structures Using Passive RFID Tag Antenna Deformation Method: Basic Research

Pecho

Hrúz

Novák

et al. 2021

Sensors

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This manuscript deals with the detection of internal cracks and defects in aeronautical fibreglass structures. In technical practice, it is problematic to accurately determine the service life or MTBF (Mean Time Between Failure) of composite materials by the methods used in metallic materials. The problem is mainly the inhomogeneous and anisotropic structure of composites, possibly due to the differences in the macrostructure during production, production processes, etc. Diagnostic methods for detecting internal cracks and damage are slightly different, and in practice, it is more difficult to detect defects using non-destructive testing (NDT). The article deals with the use of Radio frequency identification (RFID) technology integrated in the fibreglass laminates of aircraft structures to detect internal defects based on deformation behaviour of passive RFID tag antenna. The experiments proved the potential of using RFID technology in fibreglass composite laminates when using tensile tests applied on specimens with different structural properties. Therefore, the implementation of passive RFID tags into fibreglass composite structures presents the possibilities of detecting internal cracks and structural health monitoring. The result and conclusion of the basic research is determination of the application conditions for our proposed technology in practice. Moreover, the basic research provides recommendations for the applied research in terms of the use in real composite airframe structures.

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Section: Measurements Using Samples With Rfid Tags: Type Nomentioning

confidence: 93%

Section: The Role and Types Of Non-destructive Testingmentioning

confidence: 99%

Internal Damage Detection of Composite Structures Using Passive RFID Tag Antenna Deformation Method: Basic Research

Pecho

Hrúz

Novák

et al. 2021

Sensors

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show abstract

“…Different type of integrated sensors exists, while most commonly piezoelectric and fibre Bragg grating are used. Sensor integration can introduce additional resin-rich regions in the laminate or the sources of crack initiation around the corners of the piezoelectric sensor, therefore the shape and integration design has to be considered carefully taking into account overall strength of the host structure (Veidt and Liew 2012). Fibre Bragg grating sensors are lightweight and designed to be integrated into the composite structures.…”

Section: Guided Wave Excitation and Mode Selectionmentioning

confidence: 99%

“…Fibre Bragg grating sensors are lightweight and designed to be integrated into the composite structures. Such sensors do not require wiring, are cheap, durable and do not change the strength of the host structure (Veidt and Liew 2012;Majumder et al 2008). Non-contact inspection methods like air-coupled or laser ultrasonics provide an ability to adjust to the complex surface of the structure.…”

Section: Guided Wave Excitation and Mode Selectionmentioning

confidence: 99%

Ultrasonic Methods

Samaitis

Jasiūnienė

Paćko

et al. 2021

Structural Health Monitoring Damage Detection Systems for Aerospace

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Ultrasonic inspection is a well recognized technique for non-destructive testing of aircraft components. It provides both local highly sensitive inspection in the vicinity of the sensor and long-range structural assessment by means of guided waves. In general, the properties of ultrasonic waves like velocity, attenuation and propagation characteristics such as reflection, transmission and scattering depend on composition and structural integrity of the material. Hence, ultrasonic inspection is commonly used as a primary tool for active inspection of aircraft components such as engine covers, wing skins and fuselages with the aim to detect, localise and describe delaminations, voids, fibre breakage and ply waviness. This chapter mainly focuses on long range guided wave structural health monitoring, as aircraft components require rapid evaluation of large components preferably in real time without the necessity for grouding of an aircraft. In few upcoming chapters advantages and shortcommings of bulk wave and guided wave ultrasonic inspection is presented, fundamentals of guided wave propagation and damage detection are reviewed, the reliability of guided wave SHM is discussed and some recent examples of guided wave applications to SHM of aerospace components are given.

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“…Guided ultrasonic wave, with stress distributed through the thickness of the material, can propagate along the thin and large components of one-dimensional structures with little loss in energy. It offers the potential to achieve the required permanent structural integrity monitoring [1,2]. It is difficult to control the excitation and reception of selected guided wave modes.…”

Section: Introductionmentioning

confidence: 99%

A novel method to analysis strong dispersive overlapping lamb-wave signatures

Li¹,

Liu²,

Lin³

2017

J. vibroeng.

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Dispersive propagation and overlapping wave modes are two main obstacles for guided Lamb wave SHM applications. In an effort to overcome such obstacles, a new signal-processing technique taking advantage order tracking based on dispersion relation, is developed. In this approach, by referencing the wave number-frequency function of specified mode, the operations of resampling and interpolating are performed on the frequency-spectral series of raw signal. The orders referenced to wave number-frequency are calculated, according to which the individual wave-packet is identified and its corresponding propagating distance is estimated. In the order domain, the overlapping modes are readily separated by Gabor expansion on the frequency-spectral series of raw signal. Numerical and FEM simulations on strongly dispersive and multimode overlapping guided waves were carried out to evaluate the performance of the proposed approach. The results demonstrated that the proposed approach is effective in dispersion analysis, mode differentiation and overlapped wave-packets separation. techniques were applied including Wiener pulse shaping filter, two-sided Wiener filter, weighted least squares filter, Mendel's minimum variance deconvolution algorithm, Oldenburg's frequency domain deconvolution algorithm and L1-norm deconvolution [11,12]. Since the deconvolution methods were very sensitive to noises, they generally could be inapplicable if strong noise were present in the sensor signal. Furthermore, even with high time resolution, the method of pinpointing wave-packet arrival time maybe loses its effectiveness. That is because Lamb waves are inherently dispersive, i.e., different frequency components propagate at different speeds in a wave-packet, which cause wave-packets to spread out in space and time when they propagate through a structure so as to make the concept of arrival time ill-defined in time domain. To obtain well-defined onset-time of echoes, Chirplets based dispersion curve were employed to extract the onset-time of that single mode from multimode dispersive wave signal [13,14]. However, in the case of coherent interferences (false reflection) in the waveform, the Chirplet method may produce misleading results. To eliminate interference of false reflections, Ajay et al. [15] adopted an algorithm based on correlation analysis and matching pursuit method to estimate onset-time of echoes. But this method still has a deficiency in that the wave propagation model and baseline signal must be known.In an effort to overcome the difficulty of wave-packet identification caused by strong dispersion, researchers developed some signal-processing techniques to compensate for the dispersive nature of Lamb waves in long-range inspections. The time reversal technique and its improved methods [16][17][18][19] are used to achieve temporal recompression of Lamb waves under broadband signal excitation. Warped frequency transform [20] upwarps the dispersive signal, and then wraps TF points of the STFT of the signal to obtain a dispersion-m...

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Non-destructive evaluation (NDE) of aerospace composites: structural health monitoring of aerospace structures using guided wave ultrasonics

Cited by 9 publications

References 119 publications

Internal Damage Detection of Composite Structures Using Passive RFID Tag Antenna Deformation Method: Basic Research

Internal Damage Detection of Composite Structures Using Passive RFID Tag Antenna Deformation Method: Basic Research

Ultrasonic Methods

A novel method to analysis strong dispersive overlapping lamb-wave signatures

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