Health monitoring of aerospace composite structures – Active and passive approach

Staszewski, Wiesław J.; Mahzan, Shahruddin; Traynor, Roger J.

doi:10.1016/j.compscitech.2008.09.034

Cited by 347 publications

(248 citation statements)

References 12 publications

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“…Many researchers agreed that impact damage is one of the most frequent damage encountered by aircraft structure (Diamanti & Soutis, 2010;Grondel et al, 2004;Haase, Thomson, Bishop, & Isambert, 2013;Staszewski et al, 2009) . A major concern is that some impact damages in composite materials do not provide visible evidence, therefore may not be detected during regular surface inspection.…”

Section: Common Damages In Aircraft Composite Structurementioning

confidence: 99%

“…Therefore, they are the starting point to reduction of the composites strength and degradation of its structural integrity (Grondel et al, 2004;Staszewski et al, 2009). Failure to detect damage before it expands and reach a critical size may lead to failure of the component.…”

Section: Common Damages In Aircraft Composite Structurementioning

confidence: 99%

“…In consequence, the detection of those damages as well as other flaws or defect is crucial. On the one hand to allow detection of the damaged area before it reaches a critical size, hence to ensure structure integrity and overall aircraft safety, on the other hand to provide sufficient time for action, such as by monitoring or preventing further growth of the damage (Staszewski et al, 2009). …”

Section: Common Damages In Aircraft Composite Structurementioning

confidence: 99%

“…Over the past 30 years composite materials have been increasingly used in aircraft structures (Diamanti & Soutis, 2010;Grondel, Assaad, Delebarre, & Moulin, 2004;Staszewski, Mahzan, & Traynor, 2009). Recent designed aircraft such as the Airbus A380 introduced in 2007 and the Boeing B787 introduced in 2011 have their structures made of 25% and 50% of composite materials respectively (Staszewski et al, 2009).…”

Section: Introductionmentioning

confidence: 99%

“…Recent designed aircraft such as the Airbus A380 introduced in 2007 and the Boeing B787 introduced in 2011 have their structures made of 25% and 50% of composite materials respectively (Staszewski et al, 2009). This growing interest for composite materials in aviation over aluminium alloys is mainly due to their excellent specific properties such as high stiffness and strength for weight ratio (especially in case of polymer matrix composite).…”

Section: Introductionmentioning

confidence: 99%

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Acousto-ultrasonic Structural Health Monitoring of aerospace composite materials

Grésil¹,

Muller²,

Soutis³

2015

Emerging Technologies in Non-Destructive Testing VI

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Piezoelectric transducers have a long history of applications in nondestructive evaluation (NDE) of material and structure integrity owing to their ability of transforming mechanical energy to electrical energy and vice versa. From an acoustic point of view, there is no difference between structural health monitoring (SHM) and conventional NDE since both rely on the same physics in the sense that in either case acoustic waves are generated and then detected. SHM was 'born' from the conjunction of several techniques and has a common basis with NDE. In fact, several NDE techniques can be converted into SHM techniques, by integrating sensors and actuators inside the monitored structure. For instance, traditional ultrasonic testing can be easily converted into an acousto-ultrasonic SHM system, using embedded or surface-mounted piezoelectric wafer active sensors (PWAS). These sensors should be affordable, lightweight, and unobtrusive such as to not impose cost and weight penalty on the structure and to not interfere with the structural strength and airworthiness. Other damage measuring methods based on large area measurements have been used in SHM development for verification and validation of damage and/or for understating the proposed SHM approach; however, they do not seem appropriate for permanent installation onto the monitored structure and will not be discussed under the heading of 'SHM sensors'. This paper presents and discusses an overview of ultrasonic SHM techniques for composite materials. After a brief introduction, it presents the PWAS-based SHM principle, which is followed by a discussion of the passive and active ultrasonic SHM techniques. The paper identifies advantages and disadvantages of these in-situ NDE methods and guidelines for future work on heterogeneous, anisotropic materials, like aerospace composite polymer.

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Section: Common Damages In Aircraft Composite Structurementioning

confidence: 99%

Section: Common Damages In Aircraft Composite Structurementioning

confidence: 99%

Section: Common Damages In Aircraft Composite Structurementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Acousto-ultrasonic Structural Health Monitoring of aerospace composite materials

Grésil¹,

Muller²,

Soutis³

2015

Emerging Technologies in Non-Destructive Testing VI

View full text Add to dashboard Cite

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Signal Processing for Structural Health Monitoring

Staszewski

Sohn

2010

Encyclopedia of Aerospace Engineering

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Recent years have shown a number of new structural health monitoring (SHM) technologies that have the potential for online damage detection in aircraft structures. Signal processing will become more critical in the implementation of these technologies because automated signal processing and data interpretation are the key for the success of online SHM. Signal processing can mainly address seven different problems related to SHM: measurements and data acquisition, data pre‐processing, signal feature analysis, pattern recognition and machine learning, reliability analysis, uncertainties, and data fusion. This chapter briefly discusses all seven problems. Finally, this chapter illustrates some signal‐processing examples relevant to damage detection in aircraft structure. Four different examples related to fatigue crack in aluminum specimens and impact damage detection in a composite specimen are presented.

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