Debonding monitoring of a composite repair patch using small-diameter FBG sensors

2004 ◽  
Author(s):  
Shin-ichi Takeda ◽  
Takeharu Yamamoto ◽  
Yoji Okabe ◽  
Nobuo Takeda
Keyword(s):  
Small Diameter ◽  
Composite Repair ◽  
Repair Patch ◽  
Fbg Sensors

scholarly journals Health monitoring of a bonded repair patch using small-diameter FBG sensors

2003 ◽  
Vol 2003.9 (0) ◽  
pp. 181-182
Author(s):  
T. Yamamoto ◽  
S. Takeda ◽  
Y. Okabe ◽  
N. Takeda
Keyword(s):  
Health Monitoring ◽  
Small Diameter ◽  
Repair Patch ◽  
Bonded Repair ◽  
Fbg Sensors

Debonding monitoring of composite repair patches using embedded small-diameter FBG sensors

2007 ◽  
Vol 16 (3) ◽  
pp. 763-770 ◽  
Author(s):  
S Takeda ◽  
T Yamamoto ◽  
Y Okabe ◽  
N Takeda
Keyword(s):  
Small Diameter ◽  
Composite Repair ◽  
Fbg Sensors

Application of small-diameter FBG sensors for detection of damages in composites

2001 ◽  
Author(s):  
Yoji Okabe ◽  
Tadahito Mizutani ◽  
Shigeki Yashiro ◽  
Nobuo Takeda
Keyword(s):  
Small Diameter ◽  
Fbg Sensors

scholarly journals Strain Measurement on Cracks Using Fiber Bragg Gratings for Use in Aircraft Composite Skin Repairs

Aerospace ◽  
2020 ◽  
Vol 7 (9) ◽  
pp. 138
Author(s):  
Aris A. Ikiades
Keyword(s):  
Spectral Characteristics ◽  
Fiber Bragg Gratings ◽  
Bragg Gratings ◽  
Stress Fields ◽  
Composite Repair ◽  
Local Stresses ◽  
Fbg Sensors ◽  
Critical Components ◽  
Co Doped

Fiber Bragg grating (FBG) sensors have been widely used for measurements of strain and temperature in a host of different applications, including aerospace in composite wings, fuselage structures, and other critical components. Here, we report on a method to measure highly localized intense stress fields, generated at the initialization point of a crack, or crack-tip, using Fiber Bragg Gratings (FBG) inscribed in highly photosensitive hydrogenated germanium and boron co-doped fiber. From the spectral characteristics of short and long FBGs, bonded on a test aluminum coupon with a crack, which simulated damaged skins of an aircraft, the local stresses near the cracks were measured and assessed. As a case study, bespoke composite repair patches were designed and bonded on a coupon, incorporating a number of gratings to monitor the stress distribution with applied force in the composite patch, near the crack.

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