Impact damage detection of curved stiffened composite panels by using wavy embedded small-diameter optical fibers

2002 ◽  
Author(s):  
Hiroaki Tsutsui ◽  
Akio Kawamata ◽  
Junichi Kimoto ◽  
Tomio Sanda ◽  
Nobuo Takeda
Keyword(s):  
Damage Detection ◽  
Optical Fibers ◽  
Impact Damage ◽  
Small Diameter ◽  
Composite Panels ◽  
Stiffened Composite Panels

Detection of impact damage of stiffened composite panels using embedded small-diameter optical fibers

2004 ◽  
Vol 13 (6) ◽  
pp. 1284-1290 ◽  
Author(s):  
Hiroaki Tsutsui ◽  
Akio Kawamata ◽  
Tomio Sanda ◽  
Nobuo Takeda
Keyword(s):  
Optical Fibers ◽  
Impact Damage ◽  
Small Diameter ◽  
Composite Panels ◽  
Stiffened Composite Panels

scholarly journals Prediction of the Compresion-After-Impact Strength of Thin-Skin Stiffened Composite Panels

2000 ◽  
Vol 9 (4) ◽  
pp. 096369350000900 ◽  
Author(s):  
Y. Zhuk ◽  
C. Soutis ◽  
I. Guz
Keyword(s):  
Impact Damage ◽  
Low Velocity Impact ◽  
Composite Panels ◽  
Low Velocity ◽  
Damage Initiation ◽  
Mechanics Model ◽  
Stiffened Composite Panels ◽  
Open Hole ◽  
Thin Skin ◽  
The Impact

The compressive response of thin-skin stiffened composite panels with low velocity impact damage is examined. The finite element method together with the Soutis-Fleck fracture mechanics model is used to predict damage initiation in the form of fibre microbuckling in the 0° plies, propagation and final failure; in the model the impact damage is replaced with an equivalent circular or elliptical open hole. Theoretical results are compared to experimental data and found in good agreement.

scholarly journals Remote inspection system for impact damage in large composite structure

2015 ◽  
Vol 471 (2173) ◽  
pp. 20140631 ◽  
Author(s):  
C. H. Zhong ◽  
A. J. Croxford ◽  
P. D. Wilcox
Keyword(s):  
Damage Detection ◽  
Impact Damage ◽  
Electromagnetic Coupling ◽  
Random Noise ◽  
Inspection System ◽  
High Signal ◽  
Single Shot ◽  
Composite Panels ◽  
Large Area ◽  
Baseline Subtraction

A significant opportunity for reducing the weight of composite aircraft is through the development of an economically efficient method to detect barely visible or invisible impact damage sustained in service. In this paper, a structurally integrated, inert, wireless system for rapid, large-area impact damage detection in composite is demonstrated. Large-area inspection from single sensors using ultrasonic-guided waves is achieved with a baseline-subtraction technique. The wireless interface uses electromagnetic coupling between coils in the embedded sensor and inspection wand. Compact encapsulated sensor units are built and successfully embedded into composite panels at manufacture. Chirp-based excitation is used to enable single-shot measurements with high signal-to-random-noise ratio to be obtained. Signal processing to compensate for variability in inspection wand alignment is developed and shown to be necessary to obtain adequate baseline subtraction performance for damage detection. Results from sensors embedded in both glass fibre and carbon fibre-reinforced composite panels are presented. Successful detection of a 10 J impact damage in the former is demonstrated at a range of 125 mm. Quantitative extrapolation of this result suggests that the same level of impact damage would be detectable at a range of up to 1000 mm with an inspection wand alignment tolerance of 4 mm.

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