scholarly journals Active Health Monitoring of Thick Composite Structures by Embedded and Surface-Mounted Piezo Diagnostic Layer

Sensors ◽  
2020 ◽  
Vol 20 (12) ◽  
pp. 3410
Author(s):  
Tianyi Feng ◽  
Dimitrios Bekas ◽  
M. H. Ferri Aliabadi
Keyword(s):  
Composite Structures ◽  
Guided Waves ◽  
Impact Damage ◽  
Effective Means ◽  
Laser Doppler Vibrometer ◽  
Mechanical Impedance ◽  
Bonding Process ◽  
Ultrasonic Guided Waves ◽  
Impedance Technique ◽  
The Relationship

An effective approach for an embedded piezo diagnostic layer into thick composite material is presented. The effectiveness of the approach is assessed in comparison to the surface-mounted layer. The proposed manufacturing alleviates difficulties associated with trimming edges of composites when embedding wires. The Electro-Mechanical Impedance technique is used to access the integrity of the piezoelectric sensors bonding process. Comparisons of ultrasonic guided waves are made between embedded and surface-mounted diagnostic layers and their penetration through and across the thickness of the composites. Temperature influences with the range from −40 °C up to 80 °C on embedded and surface-mounted guided waves are investigated. An investigation is carried out into the relationship between amplitude and time-of-flight with temperature at different excitation frequencies. The temperature has significant but different effects on amplitude and phase-shift of guided waves for the embedded layer compared to the surface-mounted layer. A Laser Doppler Vibrometer is used to identify the blue tack and impact damage. Both embedded and surface-mounted layers are shown to be an effective means of generating detectable wave scatter from damage.

scholarly journals Effect of Multi-Impact on QIQH Carbon/Epoxy Composite Laminate

Proceedings ◽  
2018 ◽  
Vol 2 (8) ◽  
pp. 511
Author(s):  
Adadé Seyth Ezéckiel Amouzou ◽  
Olivier Sicot ◽  
Ameur Chettah ◽  
Shahram Aivazzadeh
Keyword(s):  
Composite Structures ◽  
Epoxy Composite ◽  
Impact Damage ◽  
Ultrasonic Control ◽  
Impact Tests ◽  
Post Impact ◽  
Testing Techniques ◽  
Force Time ◽  
The Relationship ◽  
Force Displacement

This work is motivated by increasingly used of composite structures under severe loading conditions. During their use, these materials are often subjected to impact as for example, in the aeronautical field the fall of hailstone on structure composites. In fact, the low energy traditional impact tests don’t allow to see the evolution of the damage and don’t permit also to compare the best tolerance to impact between different stratifications. The multi-impact tests made it possible to find a solution to this problem. In this work, multi-impact tests are performed on three carbon/epoxy stratifications. The final goal is to predict the durability of the composite structures during impact loading for their design. This study brings to light the response of multi-impact tests through force-time and force-displacement curves obtained experimentally. On the other hand, a parameter D has introduced following the experimental results. This made it possible to rank the three stratifications from their tolerance to multi-impact tests. To evaluate the post impact damage, ultrasonic testing techniques are used. The results allow to find the relationship between the damaged surface obtained by the ultrasonic control and the parameter D and to rank the three laminates configurations.

scholarly journals Non-Destructive Inspection of Impact Damage in Composite Aircraft Panels by Ultrasonic Guided Waves and Statistical Processing

Materials ◽  
2017 ◽  
Vol 10 (6) ◽  
pp. 616 ◽  
Author(s):  
Margherita Capriotti ◽  
Hyungsuk E. Kim ◽  
Francesco Lanza di Scalea ◽  
Hyonny Kim
Keyword(s):  
Guided Waves ◽  
Impact Damage ◽  
Statistical Processing ◽  
Ultrasonic Guided Waves ◽  
Non Destructive ◽  
Aircraft Panels

NDE of composite structures using ultrasonic guided waves

2013 ◽  
Author(s):  
Ajit Mal ◽  
Fabrizio Ricci ◽  
Himadri Samajder ◽  
Harsh Baid
Keyword(s):  
Composite Structures ◽  
Guided Waves ◽  
Ultrasonic Guided Waves

Health monitoring of smart composite structures using ultrasonic guided waves

2000 ◽  
Author(s):  
Thomas Monnier ◽  
Philippe Guy ◽  
Yves Jayet ◽  
Jean-Claude Baboux ◽  
Michelle Salvia
Keyword(s):  
Health Monitoring ◽  
Composite Structures ◽  
Guided Waves ◽  
Ultrasonic Guided Waves ◽  
Smart Composite ◽  
Smart Composite Structures

scholarly journals Experimental and Numerical Analysis of Multiple Low-Velocity Impact Damages in a Glass Fibered Composite Structure

Materials ◽  
2021 ◽  
Vol 14 (23) ◽  
pp. 7268
Author(s):  
Kaleeswaran Balasubramaniam ◽  
Dominika Ziaja ◽  
Michał Jurek ◽  
Piotr Fiborek ◽  
Paweł Malinowski
Keyword(s):  
Composite Structure ◽  
Thermal Loading ◽  
Guided Waves ◽  
Short Pulse ◽  
Impact Damage ◽  
Thermal Strain ◽  
Laser Doppler Vibrometer ◽  
Image Correlation ◽  
Low Velocity Impact ◽  
Low Velocity

Glass fiber-reinforced polymer structures (GFRPS) are widely used in civil and mechanical fields due to their light weight and corrosion resistance. However, these structures are prone to damage with very-low-energy impacts. The reliability of such structures is of prime importance before their installation and usage. This study aimed to identify, visualize, localize, and verify multiple barely visible impact damage (BVID) in a GFRPS using a combination of guided waves (GW)-based online structural health monitoring (SHM) and thermal strain-based nondestructive testing (NDT) approaches. Global NDT techniques like the use of a laser Doppler vibrometer (LDV) and digital image correlation (DIC) were used in the experimental analysis. The effectiveness of the experimental LDV-GW process was also checked numerically with the spectral element method (SEM). A threshold-based baseline free SHM approach to effectively localize the damages was proposed along with quick DIC verification of composite structure with thermal loading based on short-pulse heating as an excitation source. This study analyzed combined experimental- and numerical-based SHM-NDT methods in characterizing the multiple BVIDs located in a GFRPS.

Advanced debonding detection technique for aerospace composite structures

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Assunta Sorrentino ◽  
Fulvio Romano ◽  
Angelo De Fenza
Keyword(s):  
High Frequency ◽  
Composite Structures ◽  
Guided Waves ◽  
Plastic Material ◽  
Impact Damage ◽  
Small Scale ◽  
Content Type ◽  
Stiffened Panels ◽  
Reinforced Plastic ◽  
Debonding Detection

Purpose The purpose of this paper is to introduce a methodology aimed to detect debonding induced by low impacts energies in typical aeronautical structures. The methodology is based on high frequency sensors/actuators system simulation and the application of elliptical triangulation (ET) and probability ellipse (PE) methods as damage detector. Numerical and experimental results on small-scale stiffened panels made of carbon fiber-reinforced plastic material are discussed. Design/methodology/approach The damage detection methodology is based on high frequency sensors/actuators piezoceramics system enabling the ET and the PE methods. The approach is based on ultrasonic guided waves propagation measurement and simulation within the structure and perturbations induced by debonding or impact damage that affect the signal characteristics. Findings The work is focused on debonding detection via test and simulations and calculation of damage indexes (DIs). The ET and PE methodologies have demonstrated the link between the DIs and debonding enabling the identification of position and growth of the damage. Originality/value The debonding between two structural elements caused in manufacturing or in-service is very difficult to detect, especially when the components are in low accessibility areas. This criticality, together with the uncertainty of long-term adhesive performance and the inability to continuously assess the debonding condition, induces the aircrafts’ manufacturers to pursuit ultraconservative design approach, with in turn an increment in final weight of these parts. The aim of this research’s activity is to demonstrate the effectiveness of the proposed methodology and the robustness of the structural health monitoring system to detect debonding in a typical aeronautical structural joint.

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