Acoustic detection of invisible damage in aircraft composite panels

Dickinson, L P; Fletcher, Neville H.

doi:10.1016/j.apacoust.2007.12.012

Cited by 27 publications

(16 citation statements)

References 9 publications

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“…Low energy impacts can cause a complex net of matrix cracking and delaminations inside a composite, which can decrease its strength and durability. The danger of such damage is that in most cases they are invisible on the surface and cannot be detected during visual inspections of the structure, hence they are often called Barely Visible Impact Damage (BVID) [1][2][3][4][5].…”

Section: Introductionmentioning

confidence: 99%

“…The experimental verification of this technique was performed on the composite laminated plate with low-velocity impact damage. Dickinson and Fletcher [2] studied the ability of detection and localization of BVID in an aircraft sandwich panel using this technique. The obtained results by the authors indicate a great accuracy in detection and localization of a damage.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Damage identification in aircraft composite structures: A case study using various non-destructive testing techniques

Katunin

Dragan

Dziendzikowski

2015

Composite Structures

280

116

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Damage identification in aircraft composite structures: A case study using various non-destructive testing techniques

Katunin

Dragan

Dziendzikowski

2015

Composite Structures

280

116

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“…The method makes it possible to track the progression of inward cracks. The accuracy depends on the transducer frequency and the minor crack size can be estimated by using Equation 3 [12][13][14][15] .…”

Section: Introductionmentioning

confidence: 99%

Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling

Shiino¹,

Faria²,

Botelho³

et al. 2012

Mat. Res.

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In recent years, structural composites manufactured by carbon fiber/epoxy laminates have been employed in large scale in aircraft industries. These structures require high strength under severe temperature changes of -56° until 80 °C. Regarding this scenario, the aim of this research was to reproduce thermal stress in the laminate plate developed by temperature changes and tracking possible cumulative damages on the laminate using ultrasonic C-scan inspection. The evaluation was based on attenuation signals and the C-scan map of the composite plate. The carbon fiber/epoxy plain weave laminate underwent temperatures of -60° to 80 °C, kept during 10 minutes and repeated for 1000, 2000, 3000 and 4000 times. After 1000 cycles, the specimens were inspected by C-scanning. A few changes in the laminate were observed using the inspection methodology only in specimens cycled 3000 times, or so. According to the found results, the used temperature range did not present enough conditions to cumulative damage in this type of laminate, which is in agreement with the macro -and micromechanical theory.

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“…As a matter of fact, the sensitivity at a given frequency is related to flaw size, but is not directly proportional in the sense that even though a given frequency detects a certain flaw size, this does not imply that this same frequency will detect another larger flaw. This observation leads to the hypothesis that a single frequency technique is not an optimal approach for detecting multiple size flaws within a given structure [2]. An inspection technique with multiple frequencies would appear to be beneficial.…”

Section: Introductionmentioning

confidence: 96%