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Pulsed eddy current inspection of CF...

Horan, Peter Francis.

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Pulsed eddy current inspection of CF-188 inner wing spar.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Pulsed eddy current inspection of CF-188 inner wing spar./
作者:	Horan, Peter Francis.
面頁冊數:	158 p.
附註:	Source: Masters Abstracts International, Volume: 52-03.
Contained By:	Masters Abstracts International52-03(E).
標題:	Materials science. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=MR95043
ISBN:	9780494950432

Pulsed eddy current inspection of CF-188 inner wing spar.
Horan, Peter Francis.

Pulsed eddy current inspection of CF-188 inner wing spar. - 158 p.

Source: Masters Abstracts International, Volume: 52-03.

Thesis (M.A.Sc.)--Royal Military College of Canada (Canada), 2013.

Royal Canadian Air Force (RCAF) CF-188 Hornet aircraft engineering authorities have stated a requirement for a Non-Destructive Evaluation (NDE) technique to detect Stress Corrosion Cracking (SCC) in the inner wing spars without fastener or composite wing skin removal. Current radiographic inspections involve significant aircraft downtime, and Pulsed Eddy Current (PEC) inspection is proposed as a solution.

ISBN: 9780494950432Subjects--Topical Terms:

543314
Materials science.

Pulsed eddy current inspection of CF-188 inner wing spar.
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245 1 0 $a Pulsed eddy current inspection of CF-188 inner wing spar.
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500 $a Source: Masters Abstracts International, Volume: 52-03.
502 $a Thesis (M.A.Sc.)--Royal Military College of Canada (Canada), 2013.
520 $a Royal Canadian Air Force (RCAF) CF-188 Hornet aircraft engineering authorities have stated a requirement for a Non-Destructive Evaluation (NDE) technique to detect Stress Corrosion Cracking (SCC) in the inner wing spars without fastener or composite wing skin removal. Current radiographic inspections involve significant aircraft downtime, and Pulsed Eddy Current (PEC) inspection is proposed as a solution.
520 $a The aluminum inner wing spars of CF-188 Hornet aircraft may undergo stress corrosion cracking (SCC) along the spar between the fasteners that secure carbon-fiber/ epoxy composite skin to the wing. Inspection of the spar through the wing skin is required to avoid wing disassembly. The thickness of the wing skin varies between 8 and 20 mm (0.3 to 0.8 inch) and fasteners may be either titanium or ferrous. PEC generated by a probe centered over a fastener, demonstrates capability of detecting simulated cracks within spars with the wing skin present. Comparison of signals from separate sensors, mounted to either side of the excitation coil, is used to detect differences in induced eddy current fields, which arise in the presence of cracks. To overcome variability in PEC signal response due to variation in 1) skin thickness, 2) fastener material and size, and 3) centering over fasteners, a large calibration data set is acquired. Multi-dimensional scores from a Modified Principal Components Analysis (PCA) of the data are reduced to one dimension (1D) using a Discriminant Analysis method. Under inspection conditions, calibrated PCA scores combined with discriminant analysis permit rapid real time go/no-go PEC detection of cracks in CF-188 inner wing spar.
520 $a Probe designs using both pickup coils and Giant Magnetoresistive (GMR) sensors were tested on samples with the same ferrous and titanium fasteners found on the CF-188. Flaws were correctly detected at lift-offs of up to 21mm utilizing a variety of insulating skin materials simulating the carbon-fibre reinforced polymer wing skin of the CF-188. As well, preliminary field trials on aircraft with actual SCC showed success at identifying cracking in spars of unknown condition. This work demonstrates the capability for a field-implementable NDE technique with the potential to provide significant economic savings to the RCAF due to real-time identification of the presence of SCC at approximately five hours of inspection time per aircraft.
590 $a School code: 1103.
650 4 $a Materials science. $3 543314
650 4 $a Electromagnetics. $3 3173223
650 4 $a Aerospace engineering. $3 1002622
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710 2 $a Royal Military College of Canada (Canada). $b Chemical and Materials Engineering. $3 3184978
773 0 $t Masters Abstracts International $g 52-03(E).
790 $a 1103
791 $a M.A.Sc.
792 $a 2013
793 $a English
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