CATALOG OF ABSTRACTS 11th International Symposium on NDT … · 2019-11-28 · plenary session 7:45...

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CATALOG OF ABSTRACTS

11th International Symposium on NDT in Aerospace

PARIS SACLAY NOVEMBER 13th TO 15th, 2019

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November 13 to 15, 20193

EDITO

On behalf of the organizing committee, it is my great pleasure and honor to welcome you at Paris Saclay for the 11th International Symposium on NDT in Aerospace. The scientific program, thanks to the NDT scientists from all over the world, coming to present their latest work is really exciting with more than 120 conferences from 30 different countries, along with five exciting keynote lectures given by recognized experts of the field. Numerous companies will attend the exhibition presenting innovative NDT technologies.

Moreover, leading aerospace companies and research organizations have accepted to open their facilities offering the opportunity of outstanding visits on Friday. We are grateful to all these actors for making these three days what we hope will be a stimulating and memorable experience. We also hope you will enjoy the scientific environment offered by Paris Saclay, first innovation center in France, bringing together in the same area higher education institutions, research organizations and technology companies. The symposium takes place in the premises of University Paris-Saclay and CEA LIST invites you to a friendly welcome cocktail in CEA NDT Laboratories. Thank you for your attendance and contribution to the success of the 11th NDT in Aerospace International Symposium.

Pierre Calmon - Chairman of the 11th International Symposiumon NDT in Aerospace

VENUE .................................................................................................................3

PROGRAMME GLOBAL....................................................................................4 à 8

KEYNOTE SPEAKERS.....................................................................................9 à 14

PROGRAMME..............................................................................................16 à 25

ABSTRACTS..............................................................................................27 à 139

PRESENTING AUTHORS............................................................................141 à 143

EXHIBITION..............................................................................................144 à 146

SOMMAIRE

LIST INSTITUTE, SMART DIGITAL SYSTEMS

WHO WE AREDIGITAL TECHNOLOGY AT THE HEARTOF FUTURE CHALLENGESThe LIST, a CEA Tech institute, implements technological research dedicated to smart digital systems. Labelled Carnot, the LIST contributes to the competitiveness of companies of all sizes and sectors via technological innovation.

Data intelligence | Embedded systems design | Cybersecurity | Software & systems engineering | Non destructive testing | Collaborative robotics | Virtual reality | Nuclear instrumentation for energy | DOSEO Radiotherapy & imaging | ...

1.Factory of the future2. Artificial intelligence

3. Cyber physical systems4. Innovative control & process5. Innovative instrumentation

6. Digital health

1. Cultivating scientificand technological excellence

2. Creating industrial value3. Inspiring innovation ecosystems

4. Opening to international partnership

20 technology platforms

OUR DIFFERENTIATING ASSETS– A protected portfolio of patentedenabling technologies applicable tonumerous fields of application.

– An ‘innovation federator’: ourresearch engineers design and providecomprehensive solutions consistentand optimized for the needs of ourpartners.

– 20 R&D platforms with the latestequipment, led by high-level experts,capitalising on our knowledge.

Institut List, CEA SACLAY Nano-INNOV PC142 | F-91191 Gif-sur-Yvette Cedex

+ 33 1 69 08 05 14 | [email protected]

OUR SITES @PARIS-SACLAY NANO-INNOV | DIGITEO SACLAY | DOSEO | CEA SACLAY

80%of budget from

external resources

300publications/year

140active licences

514portfolio patents

22startups created

since 2001

850people

130including PhD students and post-doc positions

200industrial partners

40Joint R&D

programmes and labs

6 themes

4 pillars


VENUE

Paris-Saclay place of the NDT in Aerospace 2019, brings together around a world-class academic pole, with higher education institutions, research organizations and technology small and medium companies. This scientific concentration makes the Paris-Saclay cluster, one of the most important innovation centers in the world.

Centrale Supelec – Eiffel Building 8-10, rue Joliot Curie, 91190 Gif sur Yvette

http://www.centralesupelec.fr/en

You are welcome in the premises of CentraleSupélec, Higher Education and Research Institution, member of the University Paris-Saclay.

WELCOME IN PARIS-SACLAY

Christian Boller Saarland University, GermanyMatthias Buderath Airbus, Germany

Pierre Calmon CEA List, FranceFu-Kuo Chang Stanford University, USA

Younho Cho Pusan National University, South KoreaEsmeralda Cuevas Tecnatom, Spain

Nicolas Dominguez Airbus, FranceZheng Fan Nanyang Technological University, Singapore

Gary Georgeson Boeing, USAChristian Große TU München, Germany

Srinivasan Gopalakrishnan Indian Institute of Science, IndiaAlfredo Güemes Polytechnic University of Madrid, Spain

Henning Heuer Fraunhofer IKTS, GermanyFrédéric Jenson Safran Tech, France

Johann Kastner FH Oberösterreich, AustriaWieslaw Ostachowicz Polish Academy of Sciences, Poland

William Prosser NASA, USAMatthias Purschke DGZfP, Germany

Xinlin (Peter) Qing Xiamen University, ChinaLei Qiu Nanjing University of Aeronautics and Astronautics, China

Robert Smith University of Bristol, UKZhonquing Su Hong Kong Polytechnic University, Hong Kong

GuiYun Tian Newcastle University, UKShenfang Yuan Nanjing University of Aeronautics

and Astronautics, ChinaZhenggan Zhou Beihang University, China

Pierre Calmon CEA List, France, (Chairman)Christian Boller Saarland University, Germany, (Co-chair)David Barnoncel Ariane Group, FranceBastien Chapuis CEA List, FranceNicolas Dominguez Airbus, FranceFlorence Giraud COFREND, FranceFrédéric Jenson Safran Tech, FranceJean Marie Morvan Dassault Aviation, FranceChristophe Parsis, Afenda FrANDTBMichael Stamm Brussels Airlines/KU Leuven, Belgium (Student Challenge)

ORGANISING COMMITTEESCIENTIFIC COMMITTEE


PROGRAMME GLOBAL

WEDNESDAY, 13 NOVEMBER, 2019

Departure of the Shuttles from Novotel Paris-Saclay & from Mercure Massy TGV to Saclay, NDT Aerospace 2019 Symposium

Opening of the Symposium, Welcome Coffee and Exhibition

OPENNING CEREMONY

PLENARY SESSIONS

7:45 - 8:00

8:15

8:45

9:00

10:30

10:50

12:30

14:00

15:40

16:10

18:00

18:00

18:45

19:00

21:30

Coffee Break

WE.1.AADVANCES IN NDT

METHODS I

WE.1.BSTRUCTURAL HEALTH

MONITORING I

WE.1.CMODELLING & SIMULATION I

WE.3.ANDT METHODS

MAGNETICS & EDDY CURRENT

STUDENTS CHALLENGE II

WE.3.CNDT DESIGN & PRODUCTION INTEGRATION

Lunch Buffet

Coffee Break

Group 1: Departure to CEA List for Labs Visit

Group 2: NDT in Aerospace Conference Center : Refreshment & Exhibition

Departure Group 2 to CEA List

CEA List: Cocktail Dinner

Shuttles departure back to the Symposium at Campanile, Novotel Saclay and Mercure Massy TGV

WE.2.AADVANCES IN NDT

METHODS II

WE.2.BSTRUCTURAL HEALTH

MONITORING I

STUDENTS CHALLENGE I

WE.2.CMODELLING & SIMULATION II


THURSDAY, 14 NOVEMBER, 2019


Opening of the Symposium, Welcome Coffee and exhibition

PLENARY SESSIONS

7:45 -8:00

8:15

8:30

10:00

10:30

12:30

14:00

15:40

16:10

18:00

18:30

19:15

22:30

Coffee Break

THU.1.ANDT METHODS - FROM

MICROWAVE TO THERMOGRAPHY

THU.1.BSTRUCTURAL HEALTH

MONITORING II

THU.1.CDATA PROCESSING &

STATISTICAL METHODS I

THU.2.ANDT METHODS - PHASED ARRAY I

THU.2.BNDT & SHM RELIABILITY

ASSESSMENT

THU.2.CDATA PROCESSING

& COMPUTED TOMOGRAPHY

THU.3.ANDT METHODS

ADVANCED ULTRASONICS

THU.3.BCOMPONENTS

THU.3.CDATA PROCESSING &

STATISTICAL METHODS II

Lunch Buffet

Coffee Break

NDT in Aerospace Center: Refreshment & Exhibition

Shuttles transfers to Vaux le Cernay

Gala Dinner at the Abbaye of Vaux le Cernay

Shuttles transfers back to the Symposium at Campanile, Novotel Saclay, & Mercure Massy TGV


FRIDAY, 15 NOVEMBER, 2019


Opening of the Symposium, Welcome Coffee and exhibition

PLENARY SESSION

7:45 -8:00

8:15

8:30

09:15

09:30

10:30

10:45

12:30

Coffee Break

FRI.1.ANDT METHODS

MOBILE NDT

FRI.1.BCOMPONENTS -

COMPOSITES

FRI.1.CMATERIALS

CHARACTERISATION

FRI.2.ANDT METHODS - PHASED ARRAY II

FRI.2.BCOMPONENTS -

COMPOSITES

FRI.2.CMATERIALS

CHARACTERISATION

INDUSTRIAL VISITS (DETAIL OF THE TOURS)

Coffee Buffet

Shuttles Departure for Industrial Visits

AIR FRANCE Engine Part Repair Center

12h30: Shuttle departure with Lunch on Board 13h30-15h30/16h: Visit of the site 17h30/18h: Approx. Arrival at orly Airport

ARIANE GROUP

12h30: Shuttle departure with Lunch on Board 14h-16h/16h30: Visit of the site 18h30/19h: Approx. Arrival at orly Airport

SAFRAN Aircraft Engines

12h30: Shuttle departure with Lunch on Board 13h30-15h30/16h: Visit of the site 17h30/18h: Approx. Arrival at orly Airport

SYNCHROTRON SOLEIL

12h15: Lunch-snack at CentraleSupélec

13h15: Shuttle departure 13h30-15h30/16h: Visits of the site 17h/17h30: Approx. Arrival at Orly Airport

13504_visuel insertion 100x200.indd 1 02/04/2019 10:37


STUDENTS CHALLENGE

•Falk Stelzmann (COTESA – Germany), •Nicolas Dominguez (Airbus – France), •Krishnan Balasubramaniam (IIT Madras-India), •Fang Fang (Nanjing University of Aeronautics and Astronautics).

Conferences and symposia are mainly events where senior people in a respective field meet. A group being relatively underrepresented is the next generation that will give those events sustainability, hence the students we educate today will be the drivers of those events tomorrow. This is why the student challenge has been considered within the frame of the NDT in Aerospace Symposium and why it is run this year for the very first time. Apply – invent – present! Under this motto this year’s student challenge is to be run. Eight student teams from different European countries will compete in front of an international jury. The goal is to show NDT skills on and to possibly develop an inspection concept for a special CFRP sample that was specifically designed and artificially ‘contaminated’ for this challenge by the aerospace CFRP component supplier COTESA in Germany. Eight of those ‘artificially contaminated’ samples were manufactured by COTESA and delivered to each of the teams around 6 months prior to the symposium. The teams had to identify each of the five hidden and - for the teams - unknown ‘contaminations’ in the sample and have been asked to develop inspection concepts and possibly new inspection ideas. Next to the clarity and correctness of the defect detection, aspects of applicability, cost factors and presentation skills will be judged at a special Student Challenge session. (day 1; 14h40-17h50). We encourage everybody to join, discover, discuss and compare the different approaches and results of the respective teams. The organizers, the jury and the teams are looking forward to this special feature of the symposium that may bring in ideas completely out of the box worth to be considered and discussed with a next generation that needs to mingle with the seniors in the field in view of its future development and career.

THE JURY

THE TEAMS•TEAM 1: Hena Bata Nkirda1 | Koh, Myungjun1 | Labanie, MHD. Fateh1 | Yuan, Mingchun1 1. Dresden International University

•TEAM 2: Jakub Spytek1 | Patrycja Pyzik1 | Jakub Mrówka1 | Łukasz Pieczonka1 | Łukasz Ambroziński1 1. AGH University of Science and Technology in Kraków

•TEAM 3: Junzhen Zhu1 | Abdoulaye Laye Ba2 | Qiuji Yi1 | Adi Marindra1 | Gui Yun Tian1 | Gerard Berthiau2 | Huu Kien Bui 1 1.School of Engineering, Newcastle University / 2.Institute of Research in Electrical Energy of Nantes-Atlantique

•TEAM 4: Bilal Ali Qadri1 | Artur Movsessian2 | Callum Roberts2 | 1.Aalborg Universitet Esbjerg / 2.University of Strathclyde

•TEAM 5: Mastan Raja Papanaboina1 | Smagulova Damira1 | Bengisu Yilmaz1

1.Kazimieras barsauskas ultrasoundresearch institute, Lithuania

•TEAM 6: Guillermo Azuara1 | María Luisa Rapún2 | Eduardo Barrera1 | Rodrigo Alonso2 1.Instrumentation and Applied Acoustics Research Group, Universidad Politécnica de Madrid, Spain / 2. E.T.S.I. Aeronáutica y del Espacio, Universidad Politécnica de Madrid, Spain

•TEAM 7: Gaétan Poelman1,2 and Joost Segers1 | Mathias Kersemans1 | Saeid Hedayatrasa1,2 | Erik Verboven1 Wim Van Paepegem1 1. Mechanics of Materials and Structures (UGent- MMS), Department of Materials, Textiles and Chemical Engineering (MaTCh), Ghent University, Belgium / 2.SIM Program M3 DETECT-IV, Belgium

•TEAM 8: Oliver Maurer1 | Vincent Glößner1 | Sascha-Dirk Power1 | Lea Herrmann1

1.Saarland University, Department of Material Science and Engineering, Germany

Michael Stamm Brussels Airlines/KU Leuven, Belgium

Christian Boller Saarland University, Germany, (Co-chair of the 11th Symposium)

11

KEYNOTE SPEAKERS


TITLE : APPLICATIONS OF MODELING IN AEROSPACE NDT: PAST, PRESENT AND FUTURE

ABSTRACTSThe main objective of the talk is to highlight the value of NDT modeling, through past and recent aerospace applications. As well, ‘The Ten Laws of NDT Modeling’ will be introduced, encouraging certain best-practices and emphasizing the experiences of the author over the past two decades.

Modeling and simulation tools have been shown to support the NDT engineer to better understand the physics of complex inspection problems and provide significant benefits at several stages of NDT technique development. An overview of past and current NDT modeling and simulation tools is summarized with an emphasis on ultrasonic and eddy current testing. Several case studies are presented demonstrating the application of simulations to improve NDE design. As model accuracy has improved over the years, it is now feasible to integrate numerical models as part of an iterative inverse method scheme for sizing cracks dimensions using eddy current techniques. Recent results on eddy current characterization of discontinuities in propulsion components using model-based inversion are introduced. Best-practices on the topics of model-assisted probability of detection (MAPOD) evaluation and training machine learning (ML) models with limited experimental data are discussed. Lastly, models can provide additional value during the transition of an NDT technique and be especially helpful in the training of inspectors. Throughout the talk, opportunities for the broader use of models in the future will be emphasized.

Dr. John C. Aldrin obtained his Ph.D. in Theoretical and Applied Mechanics from Northwestern University in 2001 under Prof. Jan Achenbach. Since 2001, he has been working as the principal of Computational Tools, specializing in NDE modeling and simulation, data analysis, inverse methods, and reliability assessment. Contracts have included a Visiting Scientist position with the Air Force Research Laboratory leading research on computational method in NDE, automated data analysis (ADA) software development services for SAIC and TRI/Austin, and participation in the NASA Engineering and Safety Center (NESC) Nondestructive Evaluation (NDE) Technical Discipline Team (TDT). Dr. Aldrin has co-authored over 170 journal, conference and book publications in the field of nondestructive testing and is a Fellow of the American Society of Nondestructive Testing (ASNT).

ALDRIN John C.

ABSTRACT

John C. ALDRIN - Computational Tool


TITLE: ULTRASONIC AND THERMAL TECHNIQUES FROM CNDE@IITM FOR AEROSPACE APPLICATIONS

ABSTRACTSNDT methods are currently employed in the quality assurance during the manufacturing and for in-service inspection of aerospace components and structures. Most of these techniques are focused on the detection, sizing, and characterisation of flaws such as cracks, at pre-determined critical locations, that lead to fractures and hence failures in the component. Advanced NDE methods are being developed by the Centre for NDE at the Indian Institute of Technology Madras (CNDE@IITM) that may potentially influence the fabrication, inspection, safety, costing, and maintainability of the aerospace components and its fleets in the military as well as the commercial sector. Some of the techniques that will be discussed here includes: (a) Use of ultrasonic guided waves for the improved inspection of complex structures and components including hidden areas, (b) Structural health monitoring of components and structures using attached and embedded sensor networks, (c) Use of new and novel active thermography techniques for thermal barrier coatings on engine components, and (d) Waveguide sensors for process condition measurements. Using the methods discussed here, the operator now has the opportunity to take vital decisions such as component integrity and propose necessary repair/replacement or estimate the remaining life of the component.

Prof. Krishnan Balasubramaniam : Chair Professor in Mechanical Engineering, Head of Centre for Nondestructive Evaluation (CNDE), Indian Institute of Technology Madras

Prof. Krishnan Balasubramanian is currently the Dean for Industrial Consultancy and Sponsored Research at the Indian Institute of Technology Madras. He also serves as a Chair Professor in the Department of Mechanical Engineering, and also serves as the Head of the Centre for Nondestructive Evaluation which he founded in 2001. His research focus is in the field of Non-destructive evaluation, Smart Inspection and Structural Health Monitoring, with applications in the fields of maintenance, quality assurance, manufacturing and design.

BALASUBRAMANIAM Krishnan

ABSTRACT

Pr. Krishnan BALASUBRAMANIAM - Indian Institute of Technology Madras


TITLE: CURRENT AND FUTURE NEEDS AND RESEARCH FOR COMPOSITE MATERIALS NDE AT NASA

ABSTRACTSThe use of composite materials continues to increase in the aerospace community due to the potential benefits of reduced weight, increased strength, and manufacturability. The ability to characterize damage in carbon fiber reinforced polymer composite components is required to facilitate damage progression models capable of yielding accurate remaining life predictions. As these composite structures become larger and more complex, nondestructive evaluation (NDE) techniques capable of quantifying and fully characterizing the material state are needed to enable damage progression models capable of yielding accurate remaining life predictions. This paper will present an overview of current NASA inspection challenges for both aircraft and spacecraft as well as some NDE needs unique to NASA. Further, ongoing NDE research activities at NASA for quantitative characterization of aerospace composites along with a discussion of future directions in NDE research will be presented.

Mr. Cramer has been the the Head of the Nondestructive Evaluation Sciences Branch in the Research Directorate at NASA Langley Research Center since January 2011. In his current assignment, Mr. Cramer provides strategic leadership and technical guidance for a team of 25 researchers in the development of novel nondestructive evaluation (NDE) techniques in support of the NASA missions in space operations, exploration and aeronautics. Mr. Cramer has over 30 years experience in NDE research, development and deployment, including the development of advanced inspection methods for aerospace applications, transitioning basic research to inspections used on NASA aircraft, spacecraft and other space structures. Mr. Cramer holds 14 U.S. patents on various inventions, including NASA’s Ultrasonic Wire Crimp Inspection Technology, winner of the 2009 NASA Government Invention of the Year Award. He is a recipient of numerous awards throughout his career including a NASA’s Exceptional Engineering Achievement Medal, the NASA Space Flight Awareness Award (Silver Snoopy) and an Outstanding Leadership Medal. During his career, Mr. Cramer has authored more than 85 conference and journal publications. Mr. Cramer hold a B.S. in Physics from Indiana University of Pennsylvania and an M.S. in Applied Science from the College of William and Mary.

CRAMER K. Elliott

ABSTRACT

Elliott K. CRAMER - NASA Langley Research Center


TITLE: STRUCTURAL HEALTH MONITORING: TAKING YOUR NDT SYSTEM ALONG FOR THE RIDE

ABSTRACTSDamage tolerant design for aircraft traditionally requires periodic tear-down and manual NDT by trained inspectors at fixed flight-hour intervals to determine if flaws have grown to a detectable size. These intervals are set to minimize risk, and ensure multiple NDT opportunities to detect a flaw before it could achieve a critical size. While this approach is extremely safe, its conservatism can be quite costly to the life-cycle costs of the aircraft due to the inspection process and associated time out of service for preventative maintenance. For several decades, researchers have been investigating structural health monitoring (SHM) systems as a cost-effective compliment to manual NDT, leading to condition based maintenance (CBM) where targeted manual inspection would be triggered “as needed” based on frequent automated inspections rather than on a fixed schedule. While SHM sensors, hardware and algorithms have matured sufficiently to be taken seriously in the past few years, several roadblocks still remain before these systems can be introduced into military or commercial service. This presentation will highlight the key factors that need to be addressed before an SHM system can be fielded. First, since the SHM system is permanently installed within the aircraft, hardware and sensors much meet environmental and electrical airworthiness standards. Second, since sensors generally need to be intimately bonded to the structure being inspected, mechanical loading and durability requirements must be met. Finally, the detection performance of the SHM system must able to be quantified not only at the time of installation, but throughout its design life. While testing for the first two items are relatively straightforward, SHM system detection sensitivity assessment could prove to be quite challenging. NDT typically uses statistical metrics like probability of detection (PoD) to express the detection capabilities, however traditional approaches for measuring PoD are impractical for SHM due to fact that their sensors are permanently bonded thus many sensors must be used once then “wasted” to achieve statistical significance. Alternative proposed approaches to establishing statistical equiveillance to PoD for SHM will be described. Finally, an overview of the activities of the SAE International Steering Committee on Structural Health Monitoring (AISC-SHM) will be provided.

Dr. Kessler is president and CEO of Metis Design Corporation, a recognized international leader in the field of structural health monitoring (SHM). He received his Bachelors, Masters and Ph.D. in Aerospace Engineers from the Massachusetts Institute of Technology (MIT) with a focus on composite material design, modeling and inspection. In 1998, he received the MIT Admiral Luis De Florez Award for ingenuity in design, a Draper Laboratory Fellowship in 1999 was awarded the American Society for Composites Ph.D. Research Scholarship in 2001. Dr. Kessler has authored chapters in 3 textbooks and co-authored more than 70 technical publication, including best paper awards in 2002 from the American Society for Composites, in 2009 from the Prognostics & Health Management Society, and in 2011 from the International Workshop on Structural Health Monitoring. He holds 18 patents with a dozen more pending, and periodically guest lectures for advanced graduate courses in the Aerospace Department at MIT. From 2015-17 Dr. Kessler served as the Chair of the Aerospace Industry Steering Committee on SHM, and continues to actively participate in that committee to help formulate guidance and regulation for SHM. In 2019 he received the «Most Practical SHM Solution» award voted by a panel of Aerospace industry experts.

KESSLER Seth

ABSTRACT

Dr. Seth S. KESSLER - Metis Design Corporation


TITLE: NDE CHALLENGES AT AIRBUS

ABSTRACTSThe aerospace industry is one of the engines of the global economy. The need of commercial aircrafts, satellites and helicopters, to name some, has a direct impact in the Non-Destructive Testing (NDT). Other sectors, such as the medical, nuclear or piping, rely as well on non-destructive techniques, from ‘day 1’ to end of life of the structures/systems. The aerospace sector is not different: the NDT has been one of the key enablers. NDT (also known as NDI or NDE) is probably unknown for the majority of the global popula-tion. However, when we name “SAFETY”, we talk about NDT. When we refer to “SAVING LIVES”, we talk about NDT. We, the NDT community, understand the high impact that our work has in the society. This understanding implies responsibility, accuracy and knowledge. Definitely, for us, “failure is not an option”. Since the first applications in the aerospace sector, and in many cases due to incidents, the Authorities have been more and more requesting inspections. Methods such as visual in-spection, eddy currents, ultrasonics, to name some of them, have been further customized for the aerospace needs. And it has been in the last 40 years when the equipment and appli-cations have evolved to the level of what we have nowadays. However the demands in the aerospace sector are increasing, and the current NDT ecosystem is not ready to answer to them. Faster, more-efficient and same-reliability are not enough. Additionally, the aerospace industry, including the operators and Authorities, are showing their concerns about the knowledge and experience that will leave after the experienced NDT personnel retires. Those 40 years of development have been possible with the engagement of many NDT fellows. Is the new wave of NDT inspectors and engineers ready to take over? New competences are required, and the transition will be fast.

Airbus, as well other actors in the NDT world, is working on automation, digitalization and connectivity. These three factors, when combined, bring a new set of tools that will form the next chapter of NDT. An overview of the needs and developments will be presented.

Looking into the (near) future, the society is demanding more options to travel around the world, either within a city, or between continents, with environmentally friendly aircrafts. Air-bus is committed to exceed the needs and requirements by using new materials, designs and manufacturing processes. The development of new concepts goes hand in hand with the development of the next generation of NDT equipment, and the NDT personnel.

We, the global NDT Community, have great challenges in front of us to demonstrate again that NDT is a key enabler.

Alvaro Espada is leading the Non-Destructive Testing Engineering department at Airbus, covering the end-to-end NDT process, from R&T up to In-Service aircraft inspection requirements. He started in the NDT world in 2001, with the inspection automation of A380 large composite parts in production, and went on with the NDT requirements for the A350. Alvaro is a curious engineer: Technology, automation and space are his passions. He graduated from Industrial Engineering School in Madrid (UPM-ETSII) and from École Supérieure d’Électricité (Supélec) focusing on Systems Automation. Till today Alvaro has not been able to break out of the NDT Community. And so he is very proud of it.

ESPADA TEJEDOR Alvaro

ABSTRACT

Alvaro ESPADA TEJEDOR - AIRBUS

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irbus

9h45

- 10

h30

: Set

h Ke

ssle

r - M

etis

Desig

n Co

rp

Stru

ctur

al He

alth

Mon

itorin

g : T

akin

g yo

ur N

DT sy

stem

alon

g fo

r the

ride

10h3

0 - 1

0h50

- Co

ffee

Brea

k

TECH

NICA

L PRO

GRAM

SESS

IONS

WE.1

.A.

WE.1

.B.

WE.1

.CTO

PICS

Adva

nces

in N

DT M

etho

ds I

Stru

ctur

al H

ealth

Mon

itorin

g I

Mod

ellin

g &

Sim

ulat

ion

I

10h5

0-11h

10W

E.1.A

.1

Milli

met

er w

aves

Rad

ar :

A wa

y to

see

thro

ugh

the

airpl

ane

cove

ring

? Ad

rien

Chop

ard

- Lab

orat

oire

IMS-

UM

R 52

18 C

NRS,

Un

ivers

ité B

orde

aux

WE.1

.B.1

Dam

age

Quan

tifica

tion

in A

lum

iniu

m-C

FRP

Com

posit

e St

ruct

ures

usin

g Gu

ided

Wav

e W

aven

umbe

r Map

ping

Ye

vgen

iya Lu

govt

sova

(BAM

, Ber

lin)

WE.1

.C.1

A M

acro

-elem

ent s

trate

gy d

edica

ted

to th

e tra

nsien

t mod

el-lin

g of

the u

ltras

onic

testi

ng in

carb

on re

infor

ced

com

posit

e lam

inate

s : Effi

cient

inco

rpor

ation

of lo

cal fi

ber o

rient

ation

, vis

co-e

lastic

beh

avior

and

thin

inter

med

iate l

ayer

s Ed

ouar

d De

mal

dent

(CEA

LIST

)

11h10

-11h3

0W

E.1.A

.2

Stan

dard

izatio

n, In

fluen

ces,

Poss

ibilit

ies a

nd R

isks o

f UV

LED

Tech

nolo

gy to

Fluo

resc

ent M

agne

tic P

artic

le

Insp

ectio

n (M

PI) a

nd P

enet

rant

Insp

ectio

n (F

PI)

Mar

c Bre

it (S

ecu-

Chek

Gm

bH)

WE.1

.B.2

Mac

hine

lear

ning

bas

ed te

mpe

ratu

re co

mpe

nsat

ion

for

Guid

ed W

ave

Imag

ing

in S

truct

ural

Healt

h M

onito

ring

Flor

ian

Le B

ourd

ais (

CEA-

List)

WE.1

.C.2

Inve

stiga

tions

of t

he P

oten

tial o

f Ultr

ason

ic Gu

ided

Wav

es

Testi

ng fo

r Flaw

Det

ectio

n in

Rep

rese

ntat

ive A

eros

pace

St

ruct

ures

usin

g CI

VA

Fatm

a Se

llam

i (Te

chni

cal U

nive

rsity

of M

unich

)

11h30

-11h5

0W

E.1.A

.3Ne

w m

etho

d for

the e

valua

tion

of th

e Sm

all Re

flecto

rs in

the U

ltras

onic

Inspe

ction

of th

e For

ging T

itaniu

m A

lloy

Teod

or Tr

anca

(Dia

c Ser

vicii s

rl)

W

E.1.B

.3

Hybr

id S

truct

ural

Healt

h M

onito

ring

on co

mpo

site

plat

es

with

em

bedd

ed an

d se

cond

ary b

onde

d Fib

er B

ragg

Gr

atin

gs ar

rays

and

piez

oele

ctric

pat

ches

E.

Mon

aco

(Uni

v of N

apol

i)

WE.1

.C.3

Impr

ovin

g Ul

traso

nic I

nspe

ctio

n of

Tape

red

CFRP

Stru

c -tu

res U

sing

Clou

d Ba

sed

FEA

Sim

ulat

ion

Jeff

Dobs

on (O

nSca

le)

11h50

-12h1

0W

E.1.A

.4St

udy o

f the

dam

age

evalu

atio

n m

etho

d us

ing

the

frequ

ency

chan

ge in

the

tens

ile te

st of

the

CFRP

Hi

raku

Kaw

asak

i (IIC

IHI J

apan

)W

E.1.B

.4Im

prov

ing

Lam

b wa

ve d

etec

tion

for S

HM u

sing

a ded

i-ca

ted

LWDS

ele

ctro

nics

Gl

adys

Jaus

saud

- Ce

drat

Tech

nolo

gies

WE.1

.C.4

Ultra

soni

c NDT

and

num

erica

l sim

ulat

ion

of ad

hesiv

ely

bond

ed al

umin

ium

to C

FRP

mat

erial

s Da

mira

Sm

agul

ova

(Ultr

asou

nd R

esea

rch

Inst

itute

of

Kaun

as U

nive

rsity

of T

echn

olog

y)


Wed

nesd

ay, N

ovem

ber 1

3th,

201

9

12h1

0-12

h30

WE.1

.A.5

Cont

act l

ess T

erah

ertz

Pain

t Thi

ckne

ss M

easu

rem

ents

: sp

ecific

ity o

f aer

onau

tics i

ndus

try

Adrie

n Ch

opar

d - L

abor

atoi

re IM

S- U

MR

5218

CNR

S,

Unive

rsité

Bor

deau

x

WE.1

.B.5

Ther

mal

agei

ng e

valu

atio

n of

com

posit

e pl

ates

thro

ugh

elec

trom

echa

nica

l impe

danc

e

Pier

re M

arec

hal -

Uni

vers

ity o

f Le

Havr

eW

E.1.C

.5Im

plici

t-exp

licit

sche

me

for t

he e

lasto

dyna

mic

wave

eq

uatio

n in

plat

es

Haje

r Met

henn

i (DI

SC, C

EA-L

IST)

12h3

0 - 1

4h00

- Lu

nch-

Buffe

t

SESS

IONS

WE.

2.A.

WE.

2.B.

WE.

2.C

TOPI

CSAd

vanc

es in

NDT

Met

hods

IISt

ruct

ural

Hea

lth M

onito

ring

I (co

nt.)

Mod

ellin

g &

Sim

ulat

ion

II

14h0

0-14

h20

WE.

2.A.1

Half-

Spac

e ND

T/ND

E th

roug

h M

ulti-

Freq

uenc

y Ba

ye-

sian

Com

pres

sive

Sens

ing

Mar

co S

aluc

ci (E

LEDI

A Re

sear

ch C

ente

r)W

E.2.

B.1

Stra

in an

d da

mag

e se

nsin

g by

CNT

mod

ified

adhe

sive

films a

nd fi

ber o

ptic

distr

ibut

ed se

nsin

g . C

ompa

rison

of

perfo

rman

ces i

n a d

oubl

e lap

bon

ded

join

t Al

fredo

Gue

mes

(UPM

)

WE.

2.C.

1

Para

met

ric st

udy b

y sim

ulat

ion

of a

ther

mog

raph

y con

trol

by in

duct

ion

heat

ing.

App

licat

ion

to th

e de

tect

ion

and

char

acte

rizat

ion

of cr

acks

. Ol

ivier

Ghi

baud

o (S

afra

n Te

ch)

14h2

0-14

h40

WE.

2.A.

2

Endo

scop

ic Sp

atial

Pha

se S

hift

Shea

rogr

aphy

With

The

Inte

rfero

skop

For T

urbi

ne B

lade

Flaw

Insp

ectio

n M

.Eng

. Chr

istop

her P

etry

(Uni

vers

ity o

f App

lied

Scie

nces

Trie

r)

WE.

2.B.

2

Inte

rpre

ting

resu

lts o

f NDT

/SHM

met

hods

bas

ed o

n el

astic

gui

ded

wave

s in

com

posit

e pl

ate-

like

struc

ture

s by

a se

mi-a

nalyt

ic m

odal

simul

atio

n to

ol

Jord

an B

arra

s (CE

A Lis

t)

WE.

2.C.

2Se

mi-a

nalyt

ical m

odel

ing

of e

ddy c

urre

nt in

spec

tion

for

aniso

tropi

c mat

erial

pre

sent

ing

roug

h in

terfa

ces

Hous

sem

Che

bbi (

CEA

List)

14h4

0-15

h00

WE.

2.A.

3Ne

utro

n an

d sy

nchr

otro

n X-

ray m

easu

rem

ents:

uni

que

tool

s in

the

non-

destr

uctiv

e to

olbo

x Ca

rolin

e Bo

udou

(ILL

)

STUD

ENT

CHAL

LENG

E I

Te

am 1

WE.

2.C.

3

Redu

cing

NDT E

ffort

by C

oupl

ed M

onito

ring

and

Sim

ula -

tion

of Li

quid

Com

posit

e M

oldi

ng P

roce

sses

Ni

co Li

eber

s (Ge

rman

Aer

ospa

ce C

ente

r, In

stitu

te o

f Co

mpo

site

Stru

ctur

es a

nd A

dapt

ive S

yste

ms )

15h0

0-15

h20

WE.

2.A.

4No

n-de

struc

tive

quali

ty e

valu

atio

n of

addi

tivel

y-m

anu-

fact

ured

com

pone

nts

Sam

Yang

(CSI

RO)

Team

2W

E.2.

C.4

The

use

of fr

ee-sp

ace

micr

owav

e no

n-de

struc

tive

tech

-ni

ques

: sim

ulat

ion

of d

amag

e de

tect

ion

in ca

rbon

fibr

e re

info

rced

com

posit

es.

Dani

ela

Mun

alli (

The

Unive

rsity

of N

ottin

gham

)

15h2

0-15

h40

Team

3W

E.2.

C.5

Non-

Destr

uctiv

e Co

mpo

nent

Insp

ectio

n an

d Nu

mer

ical

Sim

ulat

ion:

App

licat

ions

to A

dditi

ve M

anuf

actu

ring

David

Har

man

(Syn

opsy

s)

15h4

0 - 1

6h10

- Co

ffee

Brea

k

SESS

IONS

WE.

3.A.

WE.

3.C

TOPI

CSND

T M

etho

ds -

Mag

netic

s & E

ddy C

urre

ntST

UDEN

T CH

ALLE

NGE

IIND

T De

sign

& Pr

oduc

tion

Inte

grat

ion

16h1

0-16

h30

WE.

3.A.1

Micr

o-m

agne

tic n

on-d

estru

ctive

testi

ng o

n ex

trem

e co

nditi

on ag

ed sa

mpl

es.

Benj

amin

Duc

harn

e (LG

EF, I

NSA

Lyon

)Te

am 4

WE.

3.C.

1Lo

cal A

cous

tic R

eson

ance

Spe

ctro

scop

y: An

Esc

alatio

n Ap

proa

ch fo

r effi

cient

NDT

of fi

ber r

einf

orce

d co

mpo

sites

Ph

ilipp

Jatz

lau

(Tech

nica

l Uni

vers

ity o

f Mun

ich)

16h3

0-16

h50

WE.

3.A.

2

Deve

lopm

ent o

f Por

tabl

e W

irele

ss N

on-D

estru

ctive

Cr

ack I

dent

ificat

ion

Met

hod

by U

sing

GMR

Sens

or A

rray

for O

verh

ead

Cran

e Br

idge

s Ar

un K

umar

Yada

v (AG

H Un

ivers

ity o

f Scie

nce

& Te

chno

logy

)

Team

5W

E.3.

C.2

3D X

-ray I

nspe

ctio

n Sy

stem

for H

elico

pter

Rot

or B

lades

M

ichae

l Kru

mm

(Ray

Scan

Tech

nolo

gies

Gm

bH)


Wed

nesd

ay, N

ovem

ber 1

3th,

201

9

16h5

0-17

h10

WE.

3.A.

3

Sizin

g m

etho

d of

crac

k len

gth

on ca

rbon

stee

ls fo

r edd

y cu

rrent

testi

ng u

sing

trans

mitt

er-re

ceive

r pro

be

Shur

ui Z

hang

- In

stitu

te o

f Flu

id S

cienc

e, To

hoku

Un

ivers

ityTe

am 6

WE.

3.C.

3M

illim

eter

-size

d no

n-co

ntac

t ultr

asou

nd p

robe

bas

ed o

n fib

er-c

oupl

ed la

ser e

xcita

tion

and

dete

ctio

n W

olfg

ang

Rohr

inge

r - X

ARIO

N La

ser A

cous

tics

17h1

0-17

h30

WE.

3.A.

4M

R se

nsor

s arra

ys fo

r edd

y cur

rent

testi

ng

N. S

erge

eva-

Chol

let (

CEA

List)

Team

7W

E.3.

C.4

Efficie

nt im

plem

enta

tion

of co

rrelat

ion-

base

d til

t filte

r for

im

agin

g of

CRF

P pl

y wav

ines

s usin

g las

er u

ltras

ound

Lu

kasz

Am

broz

insk

i (AG

H Un

ivers

ity o

f Scie

nce

and

Tech

nolo

gy, K

rako

w, P

olan

d)

17h3

0-17

h50

Team

8W

E.3.

C.5

Nond

estru

ctive

eva

luat

ion

of th

erm

al ba

rrier

coat

ing

thick

ness

deg

rada

tion

usin

g in

frare

d th

erm

ogra

phy a

nd

tera

hertz

-tds i

mag

ing

Sree

dhar

Unn

ikris

hnak

urup

(Cen

ter f

or n

on-d

estru

ctive

ev

alua

tion,

IIT

Mad

ras,

Chen

nai,

Indi

a)

End

of th

e te

chni

cal p

rogr

amm

e &

depa

rture

to th

e CE

A Lis

t

STUD

ENTS

CHA

LLEN

GEA

nove

lty th

is ye

ar w

ill be

a stu

dent

chall

enge

, whe

re m

ainly

postg

radu

ate

stude

nts w

ill ha

ve to

det

ect h

idde

n fla

ws in

com

posit

e sa

mpl

es in

cludi

ng to

pre

sent

a co

ncep

t on

how

to g

et th

ose

dam

ages

mon

i-to

red

in th

e se

nse

of st

ruct

ural

healt

h m

onito

ring

(SHM

), all

bei

ng in

spire

d by

dam

age

tole

rant

des

ign.

8 te

ams o

f 4 m

embe

rs o

f stu

dent

s fro

m B

elgi

um, D

enm

ark,

Germ

any,

Lithu

ania,

Pol

and,

Spa

in an

d th

e Fr

ance

/UK

will p

rese

nt th

eir s

olut

ions

of d

etec

ting

on co

mpo

sites

(COT

ESA)

du

ring

a spe

cial s

essio

n wi

th a

rewa

rdin

g at

the

Conf

eren

ce D

inne

r.

The

study

case

give

s five

diff

eren

t int

erna

l def

ects

in th

e sa

mpl

e wh

ose

min

imum

size

is 3

mm

x 3

mm

. One

def

ect i

s loc

ated

in th

e bo

ndin

g ar

ea o

f the

T-ba

r to

the

spec

imen

.Th

e ch

allen

ge is

hig

h ! E

ach

team

will

be e

valu

ated

on

3 m

ain cr

iteria

: det

ecta

bilit

y of t

he d

efec

ts, ap

proa

ch o

f the

ir wo

rks a

nd th

e pr

esen

tatio

n on

nov

embe

r at t

he 11

th N

DT in

Ae

rosp

ace.

Part

icip

ants

will

be

wel

com

ed in

CEA

Lis

t for

an

excl

usiv

e vi

sit o

f the

labs

, fol

low

ed b

y a

cock

tail

dinn

er.

SOCI

AL E

VENT

18h0

0 -G

roup

1: D

epar

ture

Dep

artu

re G

roup

1 to

CEA

List

for t

he N

DT La

bs V

isit

18h0

0 - G

roup

2: N

DT in

Aer

ospa

ce C

onfe

renc

e Ce

nter

: Ref

resh

men

t & E

xhib

ition

18h4

5 - D

epar

ture

Gro

up 2

to C

EA Li

st

19h0

0-21

h30-

CEA

List

: Coc

ktai

l Din

ner

21h3

0 - S

huttl

es tr

ansf

ers b

ack

to;

- the

Sym

posiu

m, C

ampa

nile

- N

ovot

el S

acla

y - &

Mer

cure

Mas

sy TG

V


Thur

sday

Nov

embe

r 14

th, 2

019

8h00

- D

epar

ture

of t

he S

huttl

es fr

om N

ovot

el S

aclay

& M

ercu

re M

assy

TGV

to S

aclay

, NDT

Aer

ospa

ce 2

019

Sym

posiu

m.

8h15

- Op

enin

g of

the

Sym

posiu

m, W

elco

me

Coffe

e an

d ex

hibi

tion

8h30

- 10

h00

- PLE

NARY

SES

SION

8h

30 -

9h15

: Ellio

tt Cr

amer

- NA

SA La

ngle

y ND

E Ch

allen

ges a

t NAS

A

9h15

- 10

h00

: Pr K

rishn

an B

alas

ubra

man

ian

- ITT

Mad

ras

Ultra

soni

c and

Ther

mal

Tech

niqu

es fr

om C

NDE@

IITM

for A

eros

pace

App

licat

ions

10h0

0 - 1

0h30

- Co

ffee

Brea

k

SESS

IONS

THU.

1.A.

THU.

1.B.

THU.

1.C

TOPI

CSND

T M

etho

ds -

From

Micr

owav

e to

Th

erm

ogra

phy

Stru

ctur

al H

ealth

Mon

itorin

g II

Data

pro

cess

ing

& St

atist

ical m

etho

ds I

10h3

0-10

h50

THU.

1.A.1

Sizin

g th

e wi

dth

of ti

lted

crac

ks u

sing

laser

spot

lo

ck-in

ther

mog

raph

y Ar

antz

a M

endi

oroz

(Esc

uela

de

Inge

nier

ia d

e Bi

lbao

)

THU.

1.B.1

A to

olbo

x con

cept

to co

nfigu

re a

shm

solu

tion

on

agei

ng ai

rcra

ft str

uctu

res b

ased

on

acou

stic a

nd th

erm

al m

etho

ds

Ram

anan

, Srid

aran

Ven

kat (

Saar

land

Uni

vers

ity)

THU.

1.C.1

Inno

vativ

e Le

arni

ng-b

y-Ex

ampl

es A

ppro

ache

s for

Rea

l-Tim

e ND

T/ND

E of

Com

plex

Stru

ctur

es

Mar

co S

aluc

ci (E

LEDI

A Re

sear

ch C

ente

r)

10h5

0-11h

10TH

U.1.A

.2Ra

dom

e In

spec

tion

with

Tera

hertz

Wav

es

Joac

him

Jonu

sche

it (F

raun

hofe

r ITW

M, K

aise

rs-

laut

ern,

Ger

man

y)TH

U.1.B

.2St

ruct

ural

healt

h m

onito

ring

syste

m fo

r moi

sture

ingr

ess

dete

ctio

n in

sand

wich

com

posit

e str

uctu

res

Sevil

ia S

unet

chiie

va (K

U Le

uven

)TH

U.1.C

.2Op

tions

to u

nder

take

the

AI d

igita

l tra

nsfo

rmat

ion

jour

ney

for N

DT in

Aer

ospa

ce

Pete

r Cho

w (F

ujits

u)

11h10

-11h3

0TH

U.1.A

.3

Sing

le-sh

ot p

ulse

d te

rahe

rtz n

on-d

estru

ctive

eva

-lu

atio

n sy

stem

s for

in-li

ne p

rodu

ctio

n co

ntro

l and

au

tom

ated

insp

ectio

n Ul

i Sch

mid

ham

mer

(Ter

aton

ics)

THU.

1.B.3

Wire

less

syste

m fo

r stru

ctur

al he

alth

mon

itorin

g wi

th

Guid

ed U

ltras

onic

Wav

es: D

etec

tion

of d

efec

ts M

arwe

n Ao

uini

(In

stitu

t de

Soud

ure)

THU.

1.C.3

Micr

owav

e ND

T/ND

E th

roug

h a P

roba

bilis

tic C

ompr

essiv

e Se

nsin

g M

etho

d M

arco

Sal

ucci

(ELE

DIA

Rese

arch

Cen

ter)

11h30

-11h5

0TH

U.1.B

.4

Dam

age

asse

ssm

ent o

f com

posit

e str

uctu

res u

sing

elec

trom

echa

nica

l impe

danc

e m

etho

d W

iesla

w Os

tach

owicz

(Pol

ish A

cade

my o

f Scie

nces

, In

stitu

te o

f Flu

id–F

low

Mac

hine

ry, P

olan

d)

THU.

1.C.4

Efficie

nt TR

-MUS

IC d

amag

e de

tect

ion

in co

mpo

sites

with

a lim

ited

num

ber o

f sen

sors

Va

silei

os D

imop

oulo

s (DM

MS

Lab)

11h50

-12h1

0TH

U.1.A

.53d

Sur

face

Topo

grap

hy M

easu

rem

ent U

sing

Elas-

tom

eric

Cont

act

Thie

rry M

ante

l (Ge

lSig

ht In

c.)TH

U.1.B

.5

Vibr

atio

n he

alth

crite

rion

base

d on

the

com

bina

tion

of b

endi

ng an

d to

rsio

nal m

odes

to m

onito

r the

hea

lth

statu

s of s

afet

y-cr

itica

l com

posit

e str

uctu

res

Olivi

er P

onte

Fel

guei

ras (

Min

es P

arist

ech)

THU.

1.C.5

NDT 4

.0 : A

pplic

atio

n of

Indu

stry 4

.0 in

NDT

and

impa

ct o

n ae

rosp

ace

com

pani

es

Philip

pe M

eyna

rd (V

isico

nsul

t)

12h1

0-12

h30

THU.

1.A.6

Flyin

g Lin

e Ac

tive

IR Th

erm

ogra

phy a

pplie

d to

the

insp

ectio

n of

env

ironm

enta

l bar

rier c

oatin

gs

Ludo

vic G

aver

ina

(One

ra)

THU.

1.B.6

Stru

ctur

al he

alth

mon

itorin

g fra

mew

ork b

ased

on

prob

a -bi

lity m

odel

ing

unde

r tim

e-va

ryin

g co

nditi

ons

Fang

Fan

g (N

anjin

g Un

ivers

ity o

f Aer

onau

tics a

nd

Astro

naut

ics)

THU.

1.C.6

Deep

Lear

ning

fram

ewor

ks fo

r wav

e pr

opag

atio

n-ba

sed

dam

age

dete

ctio

n in

1D-w

aveg

uide

s M

ahin

dra

Raut

ela

(Dep

artm

ent o

f Aer

ospa

ce E

ngin

ee-

ring,

Indi

an In

stitu

te o

f Scie

nce,

Ban

galo

re, I

ndia

)


Thur

sday

, Nov

embe

r 14t

h, 2

019

12h3

0 - 1

4h00

- Lu

nch-

Buffe

t

SESS

IONS

THU.

2.A.

THU.

2.B.

THU.

2.C

TOPI

CSND

T M

etho

ds- P

hase

d Ar

ray I

NDT

& SH

M R

elia

bilit

y ass

essm

ent

Data

pro

cess

ing

& Co

mpu

ted

Tom

ogra

phy

14h0

0-14

h20

THU.

2.A.1

Appl

icatio

n of

TFM

imag

ing

for e

nhan

ced

NDT i

n Ae

rosp

ace

Hub

ert V

oilla

ume

(Edd

yfi Te

chno

logi

es)

THU.

2.B.1

Mod

el A

ssist

ed P

roba

bilit

y of D

etec

tion

in S

truct

ural

Healt

h M

onito

ring

appl

ied

to im

pact

ed co

mpo

site

struc

ture

s Ol

ivier

Mes

nil (

CEA-

List)

THU.

2.C.

1Co

mpu

ted

Radi

ogra

phy f

or H

igh

Reso

lutio

n Im

agin

g Ap

plica

tions

of A

ircra

ft St

ruct

ures

M

uzib

ur K

han

(Nat

iona

l Res

earc

h Co

uncil

Can

ada)

14h2

0-14

h40

THU.

2.A.

2M

ulti-

elem

ent u

ltras

onic

evalu

atio

n of

scat

terin

g so

lids b

y refl

ectio

n m

atrix

analy

sis

Cécil

e Br

ütt (

Safra

n Te

ch, I

nstit

ut La

ngev

in)

THU.

2.B.

2Di

gita

l Twi

n ap

proa

ch fo

r crit

ical e

ngin

e co

mpo

nent

s us

ing

PCRT

Th

omas

Köh

ler (

Vibr

ant G

mbH

)TH

U.2.

C.2

A ne

w bi

-imag

ing

NDT s

yste

m fo

r sim

ulta

neou

s rec

over

y of

atte

nuat

ion

and

elec

troni

c den

sity m

aps

Cécil

ia Ta

rpau

Labo

rato

ire d

e Ph

ysiq

ue T

héor

ique

et

Mod

élisa

tion

(LPT

M)

14h4

0-15

h00

THU.

2.B.

3

Effec

t of O

xide I

nduc

ed M

icros

tructu

re D

egra

datio

n in

Aero

-Eng

ine C

ompo

nent

s on P

OD o

f NDT

Tech

nique

s Va

msi

Krish

na R

enta

la (S

choo

l of E

ngin

eerin

g Sc

ienc

es

and

Tech

nolo

gy, U

nive

rsity

of H

yder

abad

, Indi

a)

THU.

2.C.

3X-

ray s

catte

r rem

oval

for a

rtifa

ct fr

ee C

T im

agin

g Je

ns H

anse

n (C

arl Z

eiss

IMT

GmbH

)

15h0

0-15

h20

THU.

2.A.

4

Ensu

ring

com

plet

e in

tegr

ity o

f aer

onau

tic co

mpo

-sit

e pa

rts th

anks

to a

fully

auto

mat

ed n

on-d

estru

c-tiv

e in

spec

tion

solu

tion

and

proc

ess

Angé

lique

Rau

de (T

estia

)

THU.

2.B.

4In

tegr

atio

n of

expe

rimen

tal d

ata i

n M

odel

Ass

isted

Pr

obab

ility O

f Det

ectio

n co

mpu

tatio

ns

Chris

toph

e Re

boud

(CEA

)TH

U.2.

C.4

Com

pute

d To

mog

raph

y in

NDT a

nd M

etro

logy

for A

ddi-

tivel

y Man

ufac

ture

d Ae

rosp

ace

Com

pone

nts

Dom

inik

Mar

tinse

n (Y

xlon

Inte

rnat

iona

l Gm

bH)

15h2

0-15

h40

THU.

2.A.

5Fle

xible

wed

ge p

hase

d ar

ray t

rans

duce

rs fo

r ins

-pe

ctin

g va

riabl

e-ge

omet

ry o

r com

plex

com

pone

nts

Philip

pe D

umas

- Im

ason

icTH

U.2.

B.5

Iden

tifica

tion

of K

ey P

erfo

rman

ce In

dica

tors

for S

HM in

St

ruct

ures

of I

ncre

asin

g Co

mpl

exity

Bas

ed o

n Ar

tificia

l Ne

ural

Netw

orks

Aa

dhik

Aso

kkum

ar (D

resd

en In

tern

atio

nal U

nive

rsity

(D

IU),

Dres

den/

Germ

any)

THU.

2.C.

5

Com

pute

d To

mog

raph

y and

Dig

ital R

adio

grap

hy fo

r Ad

ditiv

e M

anuf

actu

ring

proc

ess Q

ualit

y Ass

uran

ce an

d pa

ram

eter

s defi

nitio

n Ca

rlos G

alle

guillo

s (FA

DA-C

ATEC

)

15h4

0 - 1

6h10

- Co

ffee

Brea

k

SESS

IONS

THU.

3.A.

THU.

3.B.

THU.

3.C

TOPI

CSND

T M

etho

ds- A

dvan

ced

Ultra

soni

csCo

mpo

nent

sDa

ta p

roce

ssin

g &

Stat

istica

l met

hods

II

16h1

0-16

h30

THU.

3.A.1

Imag

ing

of im

pact

dam

age

in st

itche

d ca

rbon

-fibe

r re

info

rced

plas

tic co

mpo

sites

usin

g las

er u

ltras

onic

tech

niqu

e J.

Mro

wka

(AGH

Uni

vers

ity o

f Scie

nce

and

Tech

-no

logy

)

THU.

3.B.1

X-ra

y dig

ital r

adio

logy

to in

fer w

eldi

ng d

efec

ts de

pth

Emm

anue

l Siry

abe

(Saf

ran

Helic

opte

r Eng

ines

)TH

U.3.

C.1

Auto

mat

ic an

alysis

of u

ltras

onic

data

for l

arge

and

com

-pl

ex C

FRP

aircr

aft c

ompo

nent

s Ju

lien

Wal

ter (

Cent

re te

chno

logi

que

en a

éros

patia

l, Ca

nada

)

16h3

0-16

h50

THU.

3.A.

2Ev

aluat

ion

of m

etall

ic bo

nded

plat

es w

ith n

onlin

ear

ultra

soun

d an

d co

mpa

rison

with

des

truct

ive te

sting

Ri

bay G

uille

met

te (C

EA, L

ist)

THU.

3.B.

2

Elect

rom

agne

tic p

ulse

-indu

ced

acou

stic t

estin

g an

d its

ap

plica

tion

to th

e no

n-de

struc

tive

evalu

atio

n of

adhe

-siv

e bo

ndin

g be

twee

n ca

rbon

fibe

r com

posit

e an

d m

etal

Tosh

iyuki

Taka

gi (

Toho

ku U

nive

rsity

)

THU.

3.C.

2De

velo

pmen

t of d

edica

ted

class

ificat

ion

tool

s for

the

auto

-m

ated

diag

nosti

c fro

m n

on-d

estru

ctive

testi

ng d

ata

Robe

rto M

iore

lli (C

EA Li

st)


Wel

com

e in

the

Vaux

le C

erna

y Abb

ey.

Loca

ted

in th

e Ch

evre

use

valle

y in

the

Ram

boui

llet s

tate

-ow

ned

fore

st, i

s an

ench

ante

d pl

ace.

Fou

nded

in 11

18 b

y a

grou

p of

mon

ks fr

om S

avig

ny A

bbey

(in

Man

che)

the

Vaux

-de-

Cern

ay A

bbey

enj

oys m

ore

than

eig

ht ce

ntur

ies

of h

istor

y.

CONF

EREN

CE D

INNE

R18

h30

- Shu

ttles

tran

sfer

s to

Vaux

le C

erna

y

19h1

5 - 2

2h30

- Ga

la D

inne

r at t

he A

bbay

e of

Vau

x le

Cern

ay

22h3

0 - S

huttl

es tr

ansf

ers b

ack

to;

- the

Sym

posiu

m a

t Cen

trale

Supé

lec

- Nov

otel

Sac

lay

- & M

ercu

re M

assy

TGV

Thur

sday

, Nov

embe

r 14t

h, 2

019

16h5

0-17

h10

THU.

3.A.

3

Non-

cont

act d

etec

tion

of d

isbon

ds in

adhe

sivel

y bo

nded

met

allic

plat

es u

sing

laser

-exc

ited

zero

gr

oup

velo

city L

amb

mod

es

Luka

sz A

mbr

ozin

ski (

AGH

Unive

rsity

of S

cienc

e an

d Te

chno

logy

in K

rakó

w)

THU.

3.B.

3Su

rface

char

acte

rizat

ion

usin

g m

ulti-

orie

ntat

ion

light

te

chni

que

Clém

ent S

kopi

nski

(Fra

mat

ome

Inte

rcon

trôle

)TH

U.3.

C.3

Defe

ct si

zing

in g

uide

d wa

ve im

agin

g us

ing

a con

volu

tio-

nal n

eura

l net

work

Ro

berto

Mio

relli

(CEA

-List

)

17h1

0-17

h30

THU.

3.A.

4No

ncon

tact

lase

r-bas

ed u

ltras

onic

dete

ctio

n of

dy

nam

ic str

ess m

odul

ated

crac

ks

Peilo

ng Y

uan

(Kat

holie

ke U

nive

rsite

it Le

uven

)TH

U.3.

B.4

Eddy

-Cur

rent

Pul

sed

Ther

mog

raph

y for

the

Dete

ctio

n of

Im

pact

Dam

age

on C

FRP

Abdo

ulay

e Ba

(Nan

tes U

nive

rsity

)TH

U.3.

C.4

NDT o

f Wel

ds U

sing

High

Spe

ed D

ata C

olle

ctio

n an

d an

Ar

tificia

l Neu

ral N

etwo

rk R

eal-T

ime

Proc

essin

g Sy

stem

Du

ring

the

Wel

ding

Ope

ratio

n Je

rald

E. J

ones

(Ene

rgyn

Tech

, Inc

.)

17h3

0-17

h50

THU.

3.A.

5

Inno

vativ

e Ul

traso

nic N

onde

struc

tive

Testi

ng Te

ch-

niqu

e fo

r Bon

ding

Qua

lity E

valu

atio

n

Beng

isu Y

ilmaz

(Ultr

asou

nd R

esea

rch

Inst

itute

, Ka

unas

Uni

vers

ity o

f Tec

hnol

ogy)

THU.

3.C.

5

On Th

e Im

prov

emen

t of H

eigh

t Ind

icatio

n M

easu

rem

ent

in W

elds

Ab

d En

nour

Bou

zena

d (In

stitu

t de

Soud

ure

/ Lab

orat

oire

d’

Acou

stiq

ue d

e l’U

nive

rsité

du

Man

s)

End

of th

e te

chni

cal p

rogr

amm

e - s

ncak

in th

e ex

hibi

tion

area

& d

epar

ture

s of t

he sh

uttle

s for

the

Conf

eren

ce D

inne

r


Frid

ay, N

ovem

ber 1

5th,

201

9

8h00

- De

partu

re o

f the

Shu

ttles

from

Nov

otel

Sac

lay &

Mer

cure

Mas

sy TG

V to

Sac

lay, N

DT A

eros

pace

201

9 Sy

mpo

sium

.

8h30

- 9h

15 -

PLEN

ARY

SESS

ION

8h30

- 9h

15 : J

ohn

Aldr

in -

Com

puta

tiona

l Too

ls

Appl

icatio

ns o

f Mod

elin

g in

Aer

ospa

ce N

DT: P

ast,

Pres

ent a

nd Fu

ture

9h15

- 9h

30 -

Coffe

e Br

eak

SESS

IONS

FRI.1

.A.

FRI.1

.B.

FRI.1

.C

TOPI

CSND

T M

etho

ds- M

obile

NDT

Com

pone

nts -

Com

posit

esM

ater

ials

Char

acte

risat

ion

9h30

-9h5

0FR

I.1.A

.1

Auto

mat

ic In

spec

tion

of A

eron

autic

al M

echa

nica

l Ass

em-

blie

s usin

g 2D

and

3D co

mpu

ter v

ision

Ha

mdi

Ben

Abd

alla

h (IM

T M

ines

Alb

i/Ins

titut

Clé

men

t Ad

er (I

CA)

FRI.1

.B.1

Adva

nced

ther

mog

raph

ic ND

T app

lied

on co

mpo

site

aircr

aft

com

pone

nts

Dani

el C

hauv

eau

(Inst

itut d

e So

udur

e In

dust

rie)

FRI.1

.C.1

In S

itu Th

erm

ogra

phic

Insp

ectio

n of

Aut

omat

ed

Fiber

Plac

emen

t at N

ASA

Lang

ley R

esea

rch

Cent

er

El

izabe

th D

. Gre

gory

, Ph.

D. N

ASA

Lang

ley R

esea

rch

Cent

er

9h50

-10h1

0FR

I.1.A

.2Ac

cura

te &

Flex

ible

Sol

utio

n fo

r Non

Des

truct

ive Te

sting

in

Aer

ospa

ce In

dustr

y Usin

g Ro

botis

ed S

yste

m

Mr T

hom

as G

ram

berg

er (F

ill G

esel

lscha

ft m

.b.H

)FR

I.1.C

.2

Mul

ti-fu

nctio

nal p

hase

d ar

ray u

ltras

onic

imag

ing:

4 m

odes

for

bette

r ana

lysis

Choo

n-Su

Par

k, K

orea

Res

earc

h In

stitu

te o

f Sta

ndar

ds

and

Scie

nce,

Rep

ublic

of K

orea

10h1

0-10

h30

FRI.1

.A.3

Ultra

soun

d No

n De

struc

tive

Testi

ng o

f Sta

ge 8

-10 S

pool

s On

Win

g Br

ian

Prad

alet

(Air

Fran

ce In

dust

ries K

LM E

ngin

ee-

ring

and

Mai

nten

ance

)

FRI.1

.B.3

Com

paris

on o

f Adv

ance

d Po

st-Pr

oces

sing

Tech

niqu

es fo

r Fla

sh Th

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SAF-AP METIERS DU CND 2019-210x297-GB-V3.indd 1 14/10/2019 10:18

29

ABSTRACTSWEDNESDAY 13TH


WE.1.A.1

Presenting author : Adrien Chopard - Laboratoire IMS,UMR 5218 CNRS, Université Bordeaux

Co-Authors : Q.Cassar2 | A.Susset1 | P.Fauché1 | J.Bou Sleiman1 | JB.Perraud2 | JP.Guillet2 | P. Mounaix2 1. Rd Vision / 2. Laboratoire IMS- UMR 5218 CNRS, Université Bordeaux.

MILLIMETER WAVES RADAR : A WAY TO SEE THROUGH THE AIRPLANE COVERING?

ABSTRACTS The usability of pulsed broadband terahertz radiation for the inspection of polymer materials from the aeronautics industry is investigated, with the goal of developing a mobile Frequency modulated continuous wave system that operates in reflection geometry. Frequency-modulated continuous-wave (FMCW) technique was originally investigated in radar for locating a distant object by means of a reflected radio wave. Contrarily to the continuous wave systems, FMCW has the possibility to provide information on the time delay. By modulating the frequency, the concept of the technique is equivalent to putting a unique «time stamp» on the emitted wave at every instant. First, the frequency is modulated with a triangle waveform by using a voltage-controlled oscillator (VCO), which varies the frequency between a maximum and a minimum value while changing the voltage. Then, the emitted signal is frequency-multiplied and amplified to reach the working frequency. This signal is considered as a reference signal and is emitted by a horn antenna. After being transmitted or reflected by the sample, the signal is detected and mixed with the reference signal using a multiplexer . The mixing produces a beat signal at a frequency fb, which is directly proportional to the time delay τ. This signal contains amplitude and phase information.

A wide range of samples based on glass and reinforced plastics with various types of geometry is examined using an imaging system; the results are evaluated in frequency domain at 100GHz and 300GHz. The conductivity of carbon fibers prevents penetration of the respective samples but also allows analysis of coatings from the reflected THz pulses. Glass fiber composites are, in principle, transparent for millimeter wave radiation, but commonly with significant absorption for wavelengths >1 THz. Depending on depth, matrix material, and size, defects like foreign material, object or moisture contamination can be visualized through a covering structure of aeronautics. If a defect is not too deep in the sample, its location and its shape can be correctly identified from the delay between partial reflections at the surface and the defect itself.

Acknowledgement: The authors thank Nouvelle Région d’Aquitaine and BPI France for Athermo project funding

KEYWORDS MMW Radar | Imaging | Defect localization |


WE.1.A.2

Presenting author : Marc Breit - Secu-Chek GmbH

STANDARDIZATION, INFLUENCES, POSSIBILITIES AND RISKS OF UV LED TECHNOLOGY TO FLUORESCENT MAGNETIC PARTICLE INSPECTION (MPI) AND PENETRANT INSPECTION (FPI)

ABSTRACTS UV LED Technology is about to completely substitute discharge bulb-based UV-Sources like Mercury Vapour Lamps.

The endless design possibilities of LED Technology are both a blessing and curse. A blessing because it allows to allows to build UV Sources that can make the inspection easier, better and faster than ever before and a curse because the technology itself is not, as the bulb-based UV-A sources, secure by design and it needs high efforts to achieve at least similar process security and performance with UV LED Technology.

The wide range of very different lamps and the missed characterisation challenge responsible and users.

All the possibilities and their influences to this security-critical process also challenge the standardization.

The presentation will outline the process-relevant characteristics of UV sources, the possibilities the technology offers to Fluorescent Penetrant Inspection (FPI) Magnetic Particle Inspection (MPI) and how standardization is about to handle to describe the issues of LED based UV Sources that didn’t exist in the previous used technology.

KEYWORDS UV LED lamps | Fluorescent Penetrant Inspection | Magnetic Particle Inspection | Fluorescent Inspection |


WE.1.A.3

Presenting author : Teodor Tranca - Diac Servicii srl

Co-Authors : Teodor Tranca1 | Luliana Radu2

1. Diac Servicii srl / 2. ZIROM-SA

NEW METHOD FOR THE EVALUATION OF THE SMALL REFLECTORS IN THE ULTRASONIC INSPECTION OF THE FORGING TITANIUM ALLOY

ABSTRACTS Titanium’s accelerating usage in global markets is attributable to its distinctive combination of physical and metallurgical properties. The key to best utilizing titanium is to exploit these characteristics, especially as they complement one another in a given application, rather than to just directly substitute titanium for another metal. The current essay highlights some of the most important aspects concerning the industrial use of Titanium and its alloys. Starting with those regarding its properties, continuing with some technological processes involved in developing those materials and ending with the issues regarding recycling processes, titanium challenges scientists and engineers as well because of its remarkable properties that allow special applications in various human activities.

Commercial Ti-6Al-4V forgings are widely used in the rotating components of aircraft engines. The failure of such parts can be quite catastrophic because of the large amount of kinetic energy. To ensure the safety and longer lifetime of these critical parts working in the hostile environments of high temperature and high stress, the need to detect smaller defects becomes more and more important. Ultrasonic inspection is one of the non-destructive evaluation (NDE) methods widely used by the titanium forgings manufacturers because of its capability to penetrate to the interior of a component. Over the last decades sizing methods were established like DGS (Distance Gain Size) or DAC (Distance Amplitude Correction) for defects smaller than the beam profile. Those methods utilize the echo amplitude and provide results which are proportional to the defect area.

With the progress of material technology and ultrasonic inspection the need to detect and size smaller defects is growing. Therefore, both for flat bottom holes and disc shaped reflectors the usability for small defects needs to be checked.

KEYWORDS Simulation Program | Grain Noise | Small Defect |


WE.1.A.4

Presenting author : Hiraku Kawasaki - IIC IHI Japan

STUDY OF THE DAMAGE EVALUATION METHOD USING THE FREQUENCY CHANGE IN THE TENSILE TEST OF THE CFRP

ABSTRACTS We have been studying the damage evaluation method during the tensile test of CFRP (Carbon Fiber Reinforced Plastic) materials by AE (Acoustic Emission) method.

We reported previously that there are some possibilities to detect a sign of delamination occurred by the variation of F.C.O.G (Frequency Center Of Gravity) concentrated part of AE waves during the tensile test of CFRP materials by AE method.

In this study, we confirmed that if the material is soundness, the concentrated part of F.C.O.G of AE wave will be risen with increasing the load stress. On the other hand, it was also confirmed that the concentrated part of F. C. O. G was decreased when damage has occurred.

In this time, we investigate the AE signals generated by CFRP damage from tensile test of test pieces by only the carbon fiber and the ultrasonic propagation test during the tensile test. As a result, we were able to extract only the frequency of AE generated by damage of the carbon fiber from the AE signal generated during tensile test.

KEYWORDS Acoustic Emission | Frequency Center Of Gravity | Tesile Test | Carbon Fiber Reinforced Plastics |


WE.1.A.5

Presenting author : Adrien Chopard - Laboratoire IMS,UMR 5218 CNRS, Université Bordeaux

Co-Authors : Q.Cassar2 | A.Susset1 | P.Fauché1 | J.Bou Sleiman1 | JB.Perraud2 | JP.Guillet2 | P. Mounaix2 1. Rd Vision / 2. Laboratoire IMS- UMR 5218 CNRS, Université Bordeaux.

CONTACTLESS TERAHERTZ PAINT THICKNESS MEASUREMENTS : SPECIFICITY OF AERONAUTICS INDUSTRY

ABSTRACTS The thickness of paint films is one of the most critical quality parameters in the aeronautics paint process. Numerous measurement techniques exist for quantifying coated film thickness but many are unsuited to deployment in industrial environments or non metallis subtrate. With the advent of robust, turnkey systems in recent years, time-resolved terahertz pulsed sensing has matured sufficiently to find application in providing quantitative analysis of physical properties to a range of industries, including semiconductor package inspection and non-destructive testing of larger scale composites

For many applications, layer thickness determination can be accomplished using a simple time-of-flight approach, whereby the thickness of individual layers can be estimated from the successive reflections from front and back interfaces of each layer[3]. This may be applicable to thick paint layers where the interface reflections are well separated, as in marine paint systems [4], but modern paint systems such as aeronautics painting are comprised of many thin paint layers, making accurate identification of individual interface reflections difficult.

Terahertz time-domain spectroscopy is a specifically appropriated technique to analyze layered structure composition and geometry and dimension. Inverse electromagnetic problems are commonly performed to extract, from a recorded reflection THz-signal, the distinctive layer dielectric properties and thicknesses. However, main origins and formation routes of the signal are left unassessed while it could be of great value to deepen, to enlarge and to optimize stratified material THz-probing possibilities, control and understanding. In this work, an iterative algorithm implements a connected propagation tree where each node denotes a subsequent pulse subdivision. For each interface, nodes are pre-filled with the respective dielectric interface transmitted and reflected power coefficients. Descendant pulses are thus individually monitored and their carried proportion of the incident power remains at any time accessible. By constraining the algorithm to a given number of internal subdivisions, the original signal is recovered and the power contribution of each optical path is assessable. On the basis of this knowledge, the transfer function to be calculated within inverse electromagnetic problems can be simplified to enhance algorithm convergence speed. For instance, convergence speed-up would benefit the automation thickness chain control in industry. The algorithm robustness is demonstrated through the reconstruction of a THz-signal from a micro-metric layered structure used in aeronautics. The power proportions of different optical paths contributing to each part of the signal were explored. The algorithm allowed to reduce by about 99\% the number of calculated pulses compared to a standard stratified model.

Acknowledgement: The authors thank Nouvelle Région d’Aquitaine and BPI France for Athermo project funding

KEYWORDS Terahertz | Thickness evaluation | Contactless| Painting


WE.1.B.1

Presenting author : Yevgeniya Lugovtsova - BAM, Berlin

Co-Authors : Yevgeniya Lugovtsova1 | Olivier Mesnil2 | Jens Prager1 | Christian Boller3

1. BAM, Berlin / 2. CEA List, Saclay / 3. University of Saarland, Saarbrücken

DAMAGE QUANTIFICATION IN ALUMINIUM-CFRP COMPOSITE STRUCTURES USING GUIDED WAVE WAVENUMBER MAPPING

ABSTRACTS The use of composite materials is associated not only with the advantages of weight reduction and improved structural performance but also with the risk of barely visible impacts or manufacturing damages. One of the promising techniques for the detection and characterisation of such damages is based on ultrasonic guided wave propagation and analysis. However, the multimodal nature and dispersive behaviour of these waves make their analysis difficult. Various signal processing techniques have been proposed for easier interpretation of guided wave signals and extraction of the necessary information about the damage. One of them is the wavenumber mapping which consists of creating a cartography of the wavenumber of a propagating mode over an inspected area, using a dense wavefield acquisition measured for example with a scanning laser Doppler vibrometer. This technique allows both the quantification of the in-plane size and the depth of damage, for example, impact-induced delamination in composite laminates.

In this contribution, this imaging technique is applied to delaminated aluminium-CFRP composite structures which correspond to composite-overwrapped pressure vessels used for storing gases in aerospace and automotive industries. At first, the numerical investigations for the simple delamination positioned at different depth across the thickness are presented. Next, the analysis of experimental data obtained from the measurements of guided waves propagating in an aluminium-CFRP composite plate with impact-induced damage is performed. The output of the imaging is a three-dimensional representation of the delamination induced by the impact. Good agreement between the numerical and experimental residual thickness map can be found.

KEYWORDS Wavefiel Analysis | Damage Assessment | Imapact damage


WE.1.B.2

Presenting author : Florian Le Bourdais - CEA List

Co-Authors : Florian Le Bourdais1 | Olivier Mesnil1 | Christophe Reboud1 | Oscar d’Almeida2

1. CEA List / 2. Safran Tech

MACHINE LEARNING BASED TEMPERATURE COMPENSATION FOR GUIDED WAVE IMAGING IN STRUCTURAL HEALTH MONITORING

ABSTRACTS In Guided Wave (GW) Structural Health Monitoring (SHM), a baseline, i.e a set of measurements taken on the inspected structure in a pristine state, is often required to separate the contributions of the defect(s) from the other propagating wavepackets. Due to the sensitivity of GWs to Environmental and Operational Conditions (OEC), most GW-SHM techniques are limited in terms of range of applicability.

More specifically, the inspection of the unknown state must be conducted under the same EOCs as the ones of the pristine state. Besides measuring baselines on the structure under all the EOCs of interest, which is prohibitively expensive, a potential solution is to compensate the EOC effects on the measured signals. Several solutions in the literature, such as Baseline Signal Stretch and Dynamic Time Warping, have been proposed to solve this problem, but are somewhat limited in terms of amplitude of compensation or range of application.

In this paper, a model-based machine learning procedure to compensate the measured signals in an unknown state and known EOCs is presented. The compensation model is trained on experimental data acquired at various temperatures on a structure representative of the one of interest. In other words, an experiment under various EOC must be conducted on a simplified version of the structure with at least two transducers. Material and transducers of the simplified experiment must be identical to the ones of the real structure, but the actual geometry might differ. The compensated signals are then used to conduct guided wave imaging, allowing immediate defect detection and localization. Results are shown for both aluminum and composite panels.

KEYWORDS SHM | Environmental effect compensation | Guided Wave Imaging |


WE.1.B.3

Presenting author : E. Monaco - Univ of Napoli «Federico II» Napoli - Italy - Dept. Industrial Engineering

Co-Authors : E. Monaco1 | V. Memmolo1 | N. D Boffa1 | F. Ricci1 1. Univ of Napoli «Federico II» Napoli - Italy - Dept. Industrial Engineering

HYBRID STRUCTURAL HEALTH MONITORING ON COMPOSITE PLATES WITH EMBEDDED AND SECONDARY BONDED FIBER BRAGG GRATINGS ARRAYS AND PIEZOELECTRIC PATCHES

ABSTRACTS Secondary bonded or embedded sensors are usually adopted in Structural Health Monitoring of composite aerospace structures. Each type of sensor has advantages and drawbacks when used separately although their proper integrated combination may improve the overall performance of a SHM system.

The aim of the present work is to evaluate the feasibility of an efficient hybrid SHM system based on elastic wave propagation. The structure is sensorized with both piezoelectric patches (PZT) able to generate and receive strain waves and Fiber Bragg Gratings (FBG) working as receivers only. A dedicated software implementing acquisition strategies and data analysis allows to the SHM system to sense and locate low velocity impacts (in this mode both PZTs and FBGs work as receivers in a passive way) and to localize eventual impact damages at their early stage with few sensors: in this active mode PZTs work as sources and receivers, FBGs as receivers only.

Many studies have been carried out by the scientific community to show SHM applications with a variety of bonded sensors integrated in to the structure. FBG sensors are among the most promising ones due to their lightweight, small dimensions, EMI immunity and good resistance to chemical environments. Generally, FBGs are used as static sensors for temperature and strain measurements but in the SHM system proposed herein the acquisition from FBGs are managed through a 4-channel acoustic emission sensor interrogator developed by Redondo Optics Inc. with a sampling rate slightly higher than 1MHz per channel. Ultrasonic pitch-catch technique has been used to perform the impact detection and hybrid guided wave (GuW) propagation. The technique has been applied to two CFRP panels. In the first one a FBGs network was embedded between the composite layers during the manufacturing process, performed by Automatic Fiber Placement with Liquid Resin Infusion. The second one was exploited for GuW propagation and impact detection tests, using a secondary bonded PZT-FBG network of sensors and FBG arrays. A dedicated software in LABVIEW environment has been developed starting from the source code provided by the interrogator producer. The preliminary tests on the FBG’s sensitivity and on the impact detection confirmed the capability of the FBG technology for this specific application, evidencing a good accuracy in the signals time delay measurements for both passive event detection and active guided waves propagation methodologies implementation.

The proposed hybrid SHM system has been successfully applied to the two different panels, achieving good results in both low velocity impact tests and guided wave propagation experiments. The signals acquired through the FBG sensors are compared with those gathered from PZTs, demonstrating a very satisfactory matching.

As a conclusion this paper demonstrated the feasibility of the set-up of the array of FBGs sensors in terms of hardware and software, matching the needed signal acquisition accuracy and parameters for both passive and active SHM. Some results will be presented for aircraft wings skin panels.


WE.1.B.4

Presenting author : Gladys Jaussaud - Cedrat Technologies

Co-Authors : G. Jaussaud1 | J. Rebufa1 | M. Fournier1 | F. Claeyssen1 | M. Logeais1 | N. Bencheikh1 | M. Rébillat1 | M. Guskov1 | 1. Cedrat Technologies

IMPROVING LAMB WAVE DETECTION FOR SHM USING A DEDICATED LWDS ELECTRONICS

ABSTRACTS Ultrasonic waves generated by piezo-electric patches offer an efficient way to perform Structural Health Monitoring (SHM). Permanently attached sensor arrays are interesting for on-demand interrogation of the structure in order to localize defects (pits), or follow defects progression (cracks). In this paper, improvements of the piezo-electronic system efficiency and robustness are proposed as required in H2020 REMAP project.

SHM based on Lamb wave detection needs a dedicated electronic system enable to emit and detect Lamb waves. That is ensured by the Lamb Wave Detection System (LWDS), an electronic device developed by Cedrat Technologies. This module can drive a lot of piezo sensor (up to 36), and allows to work either in pitch-catch mode (each sensor is in emission or in detection) or pulse-echo mode (the same sensor can be in emission and in reception using a commutation time). This feature can drastically improve detection time, and defect localization.

The integration of the sensors is another very influent feature for Lamb wave detection. That has been improved by focusing on the coupling efficiency between the piezo patch and Lamb wave propagation. Coupling dispersion curves, FEM modelling, and experimental testing have been investigated to define sensors and integration process favorable to Lamb wave detection.

[1] E. Balmes, M. Guskov, and J.-P Bianchi, « Validation and verification of FE models of piezo based SHM systems, », ISMA International Conference on Noise and Vibration Engineering, Sep. 2016

[2] M. Rébillat, R. Hajrya, and N. Mechbal, « Nonlinear structural damage detection based on cascade of Hammerstein models, » Mechanical Systems and Signal Processing, vol. 48, no. 1, pp. 247-259, Oct. 2014.

KEYWORDS Structural Health Monitoring | Aircraft maintenance | Condition-based Maintenance (CBM) | Non Destructive Testing (NDT) | Lamb wave detection |


WE.1.B.5

Presenting author : Pierre Maréchal - LOMC, UMR 6294 CNRS, University of Le Havre

Co-Authors : Hugues Duflo1

1. LOMC, UMR 6294 CNRS, University of Le Havre

THERMAL AGEING EVALUATION OF COMPOSITE PLATES THROUGH ELECTROMECHANICAL IMPEDANCE

ABSTRACTS Electromechanical impedance monitoring is investigated to quantify changes in physical and mechanical properties during the ageing of composite plates. In this context, an experimental measurement protocol is proposed, on the basis of a broadband 1 MHz center frequency piezoelectric transducer. After a preliminary characterization of the parameters of the transducer itself, the acoustical impedance of the front medium is deduced. More particularly, the acoustical properties such as longitudinal wave velocity and attenuation are identified in the studied composite carbon/epoxy plates. From the electrical measurement results in the MHz frequency range, the acoustical impedance of the plate is plotted in the complex plane, showing characteristic signatures corresponding to the actually monitored composite plate.

The ageing is quantified, showing the effectiveness of this non-destructive evaluation method. First, the acoustical parameters of an carbon/epoxy composite plate are modeled in order to study their sensitivity. During the ageing, those acoustical properties are known to evolve significantly, i.e. a decrease of the wave velocity and an increase of the attenuation, which can both be related to the increase of the porosity level in the plate.

Secondly, these acoustical properties are evaluated on a set of samples which were submitted to a range of ageing duration from 500 to 5000 h performed at a thermostated temperature of 180°C. The feasibility of the evaluation of the ageing is demonstrated, and the precision of this measurement is discussed both in terms of temperature dependency and reproducibility.

KEYWORDS Piezoelectric transducer | Thermal ageing | Carbon/epoxy composite | Electromechanical impedance


WE.1.C.1

Presenting author : Edouart Demaldent - CEA List

Co-Authors : Edouard Demaldent1 | Alexandre Imperiale1 | Nicolas Leymarie1 | 1. CEA List

A MACRO-ELEMENT STRATEGY DEDICATED TO THE TRANSIENT MODELLING OF THE ULTRASONIC TESTING IN CARBON REINFORCED COMPOSITE LAMINATES : EFFICIENT INCORPORATION OF LOCAL

FIBER ORIENTATION, VISCO-ELASTIC BEHAVIOR AND THIN INTERMEDIATE LAYERS

ABSTRACTS Modelling high-frequency wave propagation phenomena in anisotropic laminated materials such as carbon fiber reinforced composite structures is a major asset in numerous advanced industrial fields, such as for NdT in aerospace. Traditional homogenization procedures of each single ply (from 100 to 500 µm) lead to stratified isotropic transverse material properties whose anisotropic orientations depend on both the position of the layer in the stacking and the geometric deformation of the specimen (e.g. from a flat to a curved media). Both resin viscosity and multiple diffractions at the fiber scale attenuate the ultrasonic beam while intermediate epoxy layers (whose thickness is about 10 to 25 µm) reproduce the structural noise that arises around specific cutting frequencies of the bulk wave.

Providing numerical solution to these problems requires complex and time-consuming calculation procedures in 3D, sometimes even hardly parameterized with a generic finite element software. It results in a drastic limitation of the computational performance, thus making it difficult to access any parametric study based on modelling. For a few years now, CEA LIST proposes a transient numerical computation strategy based upon a specific block-structured domain decomposition approach, denoted as the macro-element (or macro-mesh) strategy. In the context of curved composite laminates, this solution exploits both the continuity of the curvature as well as the regularity of the stacking to lighten the simulation with an efficient on-the-fly reconstruction of the local fiber orientation [QNDE 18, ARTICLE].

This communication will first recall this strategy and then focus on recent advances in the consideration of visco-elasticity and structural noise phenomena. Concerning the visco-elasticity, after recapping the attenuation behaviours of standard models (Kelvin-Voigt, Maxwell and Zener), we will propose a simple calibration procedure and analyze relevant time discretization strategies for each model, leading to efficient explicit numerical schemes. Concerning the structural noise, we will propose to incorporate the effect of epoxy layers using spring-mass transmission conditions between plies, adequately embedded in the macro-mesh strategy.

KEYWORDS Composite laminates | Ultrasonic testing | Finite element transient modelling |


WE.1.C.2

Presenting author : Fatma Sellami - Technical University of Munich, Institute of Aircraft Design and Bauhaus Luftfahrt e.V.

Co-Authors : Fatma Sellami1 | Prof. Mirko Hornung1

1. Technical University of Munich, Institute of Aircraft Design and Bauhaus Luftfahrt e.V.

INVESTIGATIONS OF THE POTENTIAL OF ULTRASONIC GUIDED WAVES TESTING FOR FLAW DETECTION IN REPRESENTATIVE AEROSPACE STRUCTURES USING CIVA.

ABSTRACTS In Non-Destructive Evaluation and Structural Health Monitoring, simulations tools are needed to model energy-damage interactions. Aircraft structures such as wing skins are natural waveguides that allow energy propagation. The latter property can be used to apply the Guided Waves Testing method to analyze the interactions of ultrasonic waves with different defects geometries, assess material losses and adhesion problems. Using CIVA SP3 Guided Waves Testing Module we generate inspection procedures for the following sample problems: fuselage wall thinning and corrosion which provokes small thickness changes, debonding of lap-splice joints, hidden defects in multilayered-aircraft structures, ice detection, and coating delamination inspections, integrity of stringers, spars and load-carrying paths’ parts susceptible to high stresses and fatigue cracks.

Within the simulation platform, CIVA, the Semi-Analytical Finite Element method which relies on modal decomposition is applied for the wave propagation analysis and reciprocity relations are used to compute the elastic wave scattering coefficients. Mode computations, beam computations, inspection simulations and, parametric studies are performed to monitor the designed simplified aircraft components. The fuselage wall thinning case is addressed by assessing the frequency thickness dependence that can be demonstrated by analyzing the frequency content of the signal and the dispersion curves. In the case of lap splice joints and multi-layered structures, we analyze the in- and out- of planes modes that compose the guided waves and monitor energy leaks by varying the transducer parameters. Other theoretical investigations focus on enhancement methods based on time-reversal invariance with the aim of optimally focusing on a defect, resolving the problem of the dispersive character of guided waves, the coexistence of multiple modes at high frequencies and thus improving sensors readings reliability. The time-reversed iteration approach is used to precisely focus elastic waves in time and space in complex mediums by time-reversing and retransmitting echoes until the amplitude signal remains unchanged and a compact time-domain signal from an original multi-mode waveguide is obtained.

Forward and inverse simulation approaches are investigated and additionally Acousto-Ultrasonics’ experiments are performed for defect detections (cracks and shrinkage cavities) in Dornier 328 Al2024 stringers and in the upper part of the Telescope Spectrograph Assembly Support Box of the Sentinel-4 instrument.

KEYWORDS Aircraft component inspections | Guided Waves Simulations | Time-reversal Techniques |


WE.1.C.3

Presenting author : Jeff Dobson - OnScale

IMPROVING ULTRASONIC INSPECTION OF TAPERED CFRP STRUCTURES USING CLOUD BASED FEA SIMULATION

ABSTRACTS The ultrasonic inspection of tapered Carbon Fiber Reinforced Polymer (CFRP) structures is challenging due to their internal ply layer structure often leading to high levels of refraction of the incident beam. This work demonstrates how time domain finite element analysis modelling can be utilized to evaluate and optimize the inspection of these components. Traditionally, fully numerical simulation has been too computationally expensive for many modelling scenarios. However, when deployed on cloud computing, 1,000s of simulations can be executed in parallel to enable parametric studies and full ultrasonic scans to be completed in economical timeframes. The value of modelling to aid the understanding of ultrasonic inspections of CFRP components is demonstrated through ultrasonic B-scan simulations of tapered structures.

Model geometries are constructed directly from ply layup specifications, simplifying the generation of complex 3D structures. Each generated model considers the entire composite geometry, including the thin resin layers and variations of out-of-plane ply orientations. 2D Simulations were executed in parallel, allowing a B-scan inspection of over 100 individual measurements to be constructed in under 10 minutes. The inspection performance for varying tapered component geometries is evaluated, along with investigating the ability to detect defects, such as delamination’s. Additional simulations were performed to highlight the capability of simulation to optimize inspection techniques for these challenging structures.

KEYWORDS Numerical Simulation | Modelling | Ultrasonic Inspection | Composite Materials | Finite Element Analysis |


WE.1.C.4

Presenting author : Damira Smagulova - Ultrasound Research Institute of Kaunas University of Technology

ULTRASONICS NDT AND NUMERICAL SIMULATION OF ADHESIVELY BONDED ALUMINIUM TO CFRP MATERIALS

ABSTRACTS The use of bonded aluminium alloy to carbon fiber reinforced plastics (CFRP) has become very popular, particularly in aviation and automotive industries due to increased mechanical performance, high fatigue strength, better damage tolerant and structure lightweight in order to increase reliability, save energy consumption and reduces pollutant emission. A junction between two dissimilar materials is the weakest part of the structure. Delaminations are common defects in adhesively bonded materials which affect the integrity of the entire structure. However, detection of delaminations is a challenging task because of different properties of dissimilar materials and possible complex geometry of the object. The objective of this investigation is delamination detection using ultrasonic non-destructive methods and numerical study of probability of defect detection (POD).

Numerical simulation was performed to examine the object using various ultrasonic inspection methods and get the expected behavior of ultrasonic wave and results. POD estimation was done from the both sides, one is metal and other is composite. The adhesively bonded aluminium to CFRP was inspected experimentally using immersion and contact pulse echo techniques. Transducer frequencies were selected based on wavelength of the signal in different materials, their thickness, velocity, propagation distance, attenuation characteristics and expecting defects. A-scans and spectrum of received signals of different frequency transducers were analysed. Multiple reflections from not defected and defected bonding zones, transmission and reflections coefficients were studied and estimated. Post-processing of the data collected from the inspection was performed in order to increase the quality of defect imaging and it’s distinguishing on ultrasonic scans.

Results of inspections from both metal and composite sides were compared. As a result phased array and focused transducers of 10 to 15 MHz were used for the investigation as well as CIVA software was used for numerical simulations. The percent of energy reflected from defected bonding zone is greater only by 1% of the energy reflected from not defected bonding zone. All delaminations were detected in immersion and contact method with a different probability. After post-processing increased image quality of ultrasonic scans was achieved and more suitable technique configuration was determined.


WE.1.C.5

Presenting author : Hajer Methenni - CEA-List

Co-Authors : Hajer Methenni1 | Sonia Fliss2 | Alexandre Imperiale1 | Sébastien Imperiale3

1. CEA List / 2. POEMS - CNRS-INRIA-ENSTA Paristech, Université Paris-Saclay / 3. INRIA — LMS (École polytechnique-CNRS)

IMPLICIT-EXPLICIT SCHEME FOR THE ELASTODYNAMIC WAVE EQUATION IN PLATES

ABSTRACTS The objective of our work is to provide an efficient simulation tool for the propagation of elastic waves generated by piezoelectric sensors in thin stratified plates or shells, in the context of Structural Health Monitoring (SHM). This method of Non-Destructive Testing (NDT), aiming at monitoring in-situ and periodically a structure, is increasingly present in many industrial fields, particularly in the aeronautics sector. Efficient simulation tools will be therefore increasingly needed for the transient simulations of elastic wave propagation. Such simulations can be used to improve the interpretations of the reception signals, to calibrate optimal control configuration or as building blocks of imaging processes.

Natural discretization procedures, for instance, based on low-order finite elements and explicit schemes can be really costly especially because of the relative small thickness of the plate. Based on high-Order spectral finite elements, we propose an efficient time discretization that treats explicitly the propagative phenomena in the in-plane direction and implicitly the phenomena occurring through the thickness. In our algorithm, the time step can be chosen independently of the discretization parameters along the thickness (this specific point is the bottleneck of explicit methods). The price to pay is to solve at each iteration a linear system which is decoupled into several small linear systems (that can be solved efficiently in parallel) for each interpolation point on the in-plane surface of the plate.

We will present numerical results showing the efficiency and accuracy of our approach on realistic applications. Finally we will discuss the potential extension of our method to plates with smoothly varying thickness or shells with small curvature.

KEYWORDS Structural Health Monitoring | Elastodynamics | Finite element method | Time discretization |


WE.2.A.1

Presenting author : Marco Salucci - ELEDIA Research Center

Co-Authors : Marco Salucci1 | Alessandro Polo1 | Lorenzo Poli1 | Andrea Massa1,2

1. ELEDIA Research Center, Trento, Italy / 2. ELEDIA Research Center, Gif-sur-Yvette, France

HALF-SPACE NDT/NDE THROUGH MULTI-FREQUENCY BAYESIAN COMPRESSIVE SENSING

ABSTRACTS Microwave radiation can be successfully exploited to perform contactless inspection of dielectric structures for NDT/NDE purposes. As a matter of fact, microwave imaging (MI) approaches can retrieve both qualitative (i.e., number, location, and shape) and quantitative (i.e., material composition) information on unknown targets embedded inside an inaccessible domain by means of low-cost, portable, and safe (i.e., non-ionizing) equipment, representing a valid alternative to well-established technologies such as ultrasound (UT) and eddy current testing (ECT). However, solving the arising inverse scattering (IS) problem is a challenging task, requiring the development of suitable contre-mesure to paramount issues such as ill-posedness and non-linearity.

It is worth observing that typical NDT/NDE probing scenarios are characterized by strongly aspect-limited measurement setups (being often mathematically modelled as half-space configurations), allowing to collect a limited amount of non-redundant data on the imaged domain. To overcome such a lack of information, wide-band electromagnetic sources can be effectively exploited to enable the exploitation of multi-frequency (MF) data and yield regularized solutions thanks to the arising frequency diversity. Moreover, additional a-priori information on the solution can be enforced once the type/class of targets is known (e.g., cracks, delaminations, rust, ...). Indeed, sparseness-promoting approaches formulated within the compressed sensing (CS) paradigm proved to yield stable solutions of the IS problem once a suitable expansion basis is selected to represent the unknowns with few non-null coefficients. Within this context, Bayesian CS (BCS) approaches recently emerged as a computationally efficient solution strategy not requiring the compliance of the restricted isometry property (RIP) of the involved kernel/measurement operator.

Accordingly, this work presents a novel MI methodology to perform NDT/NDE inspections of dielectric materials based on the effective integration of a BCS solution strategy and a MF scheme. Thanks to the BCS, sparseness priors are effectively exploited to regularize the IS problem, which is formulated within the contrast source inversion (CSI) framework to avoid the use of linear approximations (e.g., Born) and enable the reconstruction of non-weak scatterers. Moreover, the existing correlation among several spectral components of the collected wide-band data is efficiently and effectively exploited thanks to a multi-task (MT-BCS) inversion approach. Numerical experiments are presented to validate the potentialities as well as the current limitations of the proposed approach.

KEYWORDS NDT/NDE | Bayesian Compressive Sensing (BCS) | Inverse Scattering | Multi-Frequency |


WE.2.A.2

Presenting author : M.Eng. Christopher Petry - University of Applied Sciences Trier

Co-Authors : M.Eng. Christopher Petry1 | Prof. Dr. Michael Schuth1 1. University of Applied Sciences Trier

ENDOSCOPIC SPATIAL PHASE SHIFT SHEAROGRAPHY WITH THE INTERFEROSKOP FOR TURBINE BLADE FLAW INSPECTION

ABSTRACTS Shearography has already established for NDT applications in the field of aerospace. Compared to thermogra-phy, which is commonly used in this area, the material-independent working shearography offers several ad-vantages, such as for testing impact damage, delamination, crack, void, and undulation in composites. Howev-er, the major disadvantage of shearography is its susceptibility to failure in the presence of vibrations and envi-ronmental disturbances. In the OGKB laboratory of the University of Applied Sciences in Trier, the method is now being stabilized in a way that allows it to be used in raw industrial applications for the first time. The basis for this is the method of spatial phase shifting (SPS) according to the carrier frequency method, which, thanks to the further developed camera technology, firstly delivers representable results.

The implementation of this method is presented in the patented measuring device Interferoskop 5.1, which combines shearography with endoscopy for difficult to access areas. The Interferoskop consists of a housing, which contains the camera and the optical setup. The housing is designed for hand-held inspection and can be equipped with different endoscope tips. The laser illumination as well as the object monitoring is performed through the endoscope. The aim of this development project is to create a measuring device for the testing of turbines by spyholes, thus a high time and cost effort by disassembling the turbines can be avoided.

The implemented spatial phase shift method allows deformation measurements to be made in the video clock of the camera, which enormously increases process stability and at the same time permits dynamic component excitations. The Interferoskops performance for NDT is demonstrated by the inspection of defective turbine blades. Hereby, simply the cooling behaviour of the turbine blades can be used as active object excitation for the flaw check, while no additional excitation system is required. The new optical miniature design in 3D print construction enables maximum light efficiency and full shear-sensitivity adjustment while maintaining optimal result quality. In addition, the optical setup can be extended by a simple modification for holographic defor-mation measurement. Furthermore, first tests were made in hand-held operation of this micrometre accurate measuring method.

KEYWORDS Shearography | Turbine blade inspection | Endoscopy | Interferoskop | Spatial phase shift |


WE.2.A.3

Presenting author : Caroline Boudou - Institut Laue-Langevin

Co-Authors : Caroline Boudou1 | Ennio Capria2 | Duncan Atkins1 | Veijo Honkimaki2 | Elodie Boller2 | Sandra Cabeza1

| Thilo Pirlng1

1. Institut Laue-Langevin / 2. ESRF

NEUTRON AND SYNCHROTRON X-RAY MEASUREMENTS: UNIQUE TOOLS IN THE NON-DESTRUCTIVE TOOLBOX

ABSTRACTS Neutron and X-ray beams provide unique, powerful and non-destructive access into the heart of materials and components, over length scales ranging from the centimetre to the atom. The Institut Laue-Langevin ILL – Europe’s leading neutron source - and the ESRF – Europe’s leading synchrotron light source, combine 80 experimental stations providing neutron and X-ray beams with exceptional properties to overcome the limitations of standard laboratory characterisation techniques. Regarding challenges in the aeronautic and space sectors, we will detail some advantages obtained by synchrotron and neutron beams in stress mapping and computed tomography.

The ESRF’s high-energy synchrotron X-rays can map efficiently the strain and stress at the surface and up to several hundreds of microns below to give depth profiling with high spatial resolution. Neutrons give access to the full stress tensor from 60µm below the surface up to the interior of the component (e.g. 30 cm in Al, 6 to 7 cm in Ti, Ni or steel). Both techniques are able to measure in real time and non-destructively the stress distribution during mechanical loading, or during heating/cooling processes. A current exciting development is the investigation of residual stress build-up during additive manufacturing. Here, we will show examples of measurements taken from aircraft and satellite components. Note that a combination of neutron and X-ray datasets can be offered by the institutes.

With regards to computed tomography, synchrotron X-rays and neutrons provide complementary information. Synchrotron X-rays provide remarkable insights into materials up to the nanoscale with a resolution as high as 30 nm. At the microscale, synchrotron X-rays enable vastly more accurate (eg. with phase contrast imaging and lower beam hardening effect) and faster data collection than lab equipment – 2D radiography can be performed at MHz rate for monitoring rapid phenomena and 3D CT can be done at ~Hz speed. With these capabilities, it is possible to monitor dynamic processes in real time (e.g. crack propagation, exploding fuse or bed fusion in additive manufacturing). Neutron tomography makes use of the specific properties of thermal neutrons to penetrate deeply a large majority of materials (e.g. most metals) whilst being highly sensitive to other elements, notably hydrogen and lithium, enabling the imaging of water, polymers or explosive charges embedded in metallic structures, without metal induced image artefacts neither radiation damage.

We will conclude our presentation by briefly showing how further neutron and synchrotron X-rays techniques can address issues in composites, electrical components and radiation

KEYWORDS Stress and strain | Tomography | In-operando and in-situ | Advanced techniques |


WE.2.A.4

Presenting author : Sam Yang - CSIRO

Co-Authors : Sam Yang1 | Clement Chu1 | Tony Murphy1 | Leon Prentice1

1. CSIRO

NON-DESTRUCTIVE QUALITY EVALUATION OF ADDITIVELY-MANUFACTURED COMPONENTS

ABSTRACTS Additive metal manufacturing (AM) offers distinctive advantages over conventional subtractive manufacturing processes such as machining from metal castings. AM is capable of producing complex high-performance components with shapes that are practically impossible to achieve with conventional processes. The design flexibility offered by AM is particularly important for high-value applications such as aerospace, where the performance-to-weight ratio is critical. AM components require little or no additional machining or other processing steps. This reduces both the manufacturing cost and environmental impact through reduced wastage. However, due to the specific conditions of the AM process, AM components often have microscopic structural defects such as porosity that are difficult to detect non-destructively with current off-the-shelf technology. Microscopic structural defects affect the fit-for-purpose performance of the components. These defects typically manifest as microscopic porosity distributions. Available non-destructive testing (NDT) technologies have major shortcomings. For instance, the BET (Brunauer-Emmett-Teller) analysis is unable to determine the location of defects, and the conventional X-ray CT (computed tomography) imaging analysis cannot resolve the microscopic porosity defects in macro-sized parts, due to limitations in resolving the multiple length scales.

In the last ten years, CSIRO has developed a data-constrained modelling technology. Together with quantitative X-ray CT, it allows the resolution of fine defects in AM metal components. This has been demonstrated using test samples and synchrotron-based X-ray CT imaging. The technology is being further developed NDT of with macro-sized AM metal components using industrial X-ray CT facilities.

KEYWORDS

Addtive-Manufacturing | Am | Non-Destructive Quality Evaluation | Data-Constrained Modelling | Dcm |


WE.2.B.1

Presenting author : Alfredo Guemes - UPM

Co-Authors : Alfredo Guemes1 | Angel Renato Pozo1 | Xoan Xose Fernandez2 | Maria Sanchez2 | Alejandro Ureña2 | Antonio Fernandez1 | 1. UPM / 2. URJC

STRAIN AND DAMAGE SENSING BY CNT MODIFIED ADHESIVE FILMS AND FIBER OPTIC DISTRIBUTED SENSING . COMPARISON OF PERFORMANCES IN A DOUBLE LAP BONDED JOIN

ABSTRACTS Bonded joints show a complex stress field, with large strain gradients, difficult to acquire experimentally, which would be very useful to validate numerical models; normally DIC is used for it. Two experimental techniques are proposed at this paper, and their feasibility and performances are compared. The properties of CNT doped adhesive films are well known for uniform strain field; by plotting conductive patterns on the adhesive film, the responses at the high and low shear strain regions are obtained, giving a much better insight on the changes in electrical conductivity under complex strain field.

An optical fibre embedded into the adhesive film, aligned to the loads, experience the strong strain gradients that are predicted by the models. Experimental results are compared to the numerical predictions given by Volkorsen model. The double lap joint is selected to avoid the bending moments caused by load misalignments, with strong out-of-plane displacements that frequently mask strains caused by the pure shear loads. With the double lap, the symmetry of loads simplify the response, only the shear stresses are present, with a minor component of peeling stresses at the discontinuities, Strain measurements were done at several load levels and at two different temperatures, to validate the temperature compensation algorithms.

Partial damage are then be inflicted at the adhesive joint, and the ability of the two techniques to detect early damages is quantified. It has been reported previously that partial damages cause very slight changes at the strain field, and consequently they would be undetected by an strain measurement technique. Nevertheless, we have found experimental evidence of changes in the electrical response in case of partial debonding, and even in case of improperly treated surfaces. More tests are on progress, and results will be reported.

KEYWORDS Bonded joints | Fiber optic | Nanocomposites | Strain Sensing | SHM |


WE.2.B.2

Presenting author : Jordan Barras - CEA List

Co-Authors : Jordan Barras1 | Alain Lhémery1

1. CEA List

INTERPRETING RESULTS OF NDT/SHM METHODS BASED ON ELASTIC GUIDED WAVES IN COMPOSITE PLATE-LIKE STRUCTURES BY A SEMI-ANALYTIC MODAL SIMULATION TOOL

ABSTRACTS Elastic guided waves (GW) are valuably used for NDT/SHM of metallic or composite plate-like structures. They allow fast scanning of large parts for the detection of all kinds of inner or surface defects and flaws. However, their complex behaviour is quite challenging as far as solving the inverse problem of defect characterization from a set of measured signals is concerned. Their modal nature and dispersion properties lead to strong variations of signal time-history all along the wavepaths, even more since reflections (at boundaries with possible mode conversion) occur between a source and a receiver. Furthermore, transducers diffraction effects add some complexity to the formation of GW field. Consequently, designing optimal NDT/SHM configurations for a given part, accurately interpreting measured signals, make it necessary to grasp the various phenomena that arise. Simulation obviously constitutes an efficient and quantitative way of doing it.

Here, results obtained by means of a newly developed model are presented, to demonstrate how the understanding of complex waveforms typically measured in NDT/SHM experiments is greatly simplified as soon as the modal nature of the various wavepackets can be exhibited and understood.

The presentation briefly reviews the semi-analytic model developed, which accounts for multiple-reflections at boundaries of arbitrary shape and transducer diffraction effects. Then, predictions of typical complex wavefields in realistic configurations are shown. They are first computed by means of a time-dependent in-house finite element code. Then, they are fully explained thanks to the modal interpretation gained in reproducing them by means of the semi-analytic model.

KEYWORDS Guided waves | Simulation | Composite | SHM |


WE.2.C.1

Presenting author : Olivier Ghibaudo - Safran Tech

Co-Authors : Olivier Ghibaudo1 | Fabrice Foucher2 | Anouar Kalai2 | Thierry Le Pollès1 | Frédéric Jenson1 | 1. Safran Tech / 2. Extende

PARAMETRIC STUDY BY SIMULATION OF A THERMOGRAPHY CONTROL BY INDUCTION HEATING. APPLICATION TO THE DETECTION AND CHARACTERIZATION OF CRACKS.

ABSTRACTS In the last few years, induction thermography has been identified as a non-destructive testing method for detecting and characterizing surface cracks in metals. The sample to be inspected is heated with a short induced electrical current pulse, and the infrared camera records the temperature distribution and transient temporal behavior at the surface during and after the heating pulse. In this work, 3D Finite element simulations, performed with the software FLUX®, were carried out to investigate how the contrast depends on parameters such as excitation frequency, pulse duration, material parameters, crack depth and length.

To compare the simulations with the experimental results, the modeled inductor is a realistic U-ferritic yoke surmounted by a copper winding. The two block samples involve two materials massively used in aeronautics: the first one is paramagnetic (nickel based superalloy INCONEL 718), the second one is ferromagnetic (low carbon steel 16CND13), which implies very different skin depths.

The simulations take into account the non-linearity of the sample magnetic permeabilities, which makes it possible to calculate finely the total impedance of the inductor. For a current imposed excitation through the inductor, this allows to normalize the observations with respect to the active and reactive power consumed by the inductor.

From the temperature distributions at each time step, the analysis of the differential thermal contrast between a defect situation and a defect-free situation, emphasizes the detectability of the defect as a function of the introduced parametric variations. The thermal extractions provided are used firstly to find the optimal excitation parameters (frequency of the induced currents, heating duration) which maximizes the thermal contrast, and on the other hand to define a methodology for sizing defects according to their lengths and depths. The optimum contrast calculated on the phase of the Fourier Transform (Pulse Phase Thermography PPT) provides credible but sensitive information related to the excitation parameters and the geometric parameters of the defects. In the final paper, two methods of analysis will be compared: the PPT and the wavelet pulsed phased thermography.

KEYWORDS Non Destructive Testing | Non Destructive Evaluation | Simulation | Thermography | Induction Heating |


WE.2.C.2

Presenting author : Houssem Chebbi - CEA List

Co-Authors : Houssem Chebbi1 | Denis Prémel1 1. CEA List

SEMI-ANALYTICAL MODELING OF EDDY CURRENT INSPECTION FOR ANISOTROPIC MATERIAL PRESENTING ROUGH INTERFACES

ABSTRACTS Within our department for NDT in the CEA LIST institute, this PhD work is a part of the European project NDTonAir (H2020 Marie Sklodowski-Curie European Training Network) which adresses several issues of NDT in the aeronautic field involving different methods of NDT based on several testing technics as ultrasonic waves, electromagnetic waves or infrared thermography.

As part of the project, we are interested in the interaction of a composite material with an eddy current sensor. The goal is to develop a robust, fast and accurate numerical model based on a semi-analytic approach to optimize ECNDT methods for this type of material. This model will be implemented in the commercial platform CIVA developed by CEA LIST.

The first part of this work was published in the previous proceedings of the 10th international symposium of NDT in aerospace held in Dresden. Here we propose the second part in which we deal with the fast computation of a quasi-static fields induced by a 3D eddy current probe in a stratified and homogenized anisotropic material with a local 2D5/3D perturbation in the geometry representing a kind of delamination in the material.

Subsequently, the original part of the thesis lies in taking into account local deformations of the geometry by applying an original approach called Curvilinear Coordinates Method or CCM which consists in considering a change of coordinates to fit the deformation of the interface and in solving the covariant form of Maxwell’s equations in a new transformed coordinates system using a modal approach.

Hence, the complex stratified structure is transformed into a plane structure in the new coordinate system in which the boundary conditions are described in an analytical way. Therefore, no mesh is necessary to maintain local variations of the fields in the structure.

Finally, the validation of the model yields in comparing FE data to simulated data provided by the numerical model. Further details and more results will be presented in the full paper.

KEYWORDS Semi-analytic model | CCM | Anisotropy | Modal approach |


WE.2.C.3

Presenting author : Nico Liebers (German Aerospace Center, Institute of Composite Structures and Adaptive Systems)

Co-Authors : Nico Liebers1 | Dominic Bertling1 1. German Aerospace Center, Institute of Composite Structures and Adaptive Systems

REDUCING NDT EFFORT BY COUPLED MONITORING AND SIMULATION OF LIQUID COMPOSITE MOLDING PROCESSES

ABSTRACTS Liquid Composite Molding (LCM) is a manufacturing technique which could reduce material and process costs in comparison to the widely used prepreg processes. The raw materials are less expensive and easier to store. Also relatively high layup rates of dry fiber textiles can be achieved. But LCM requires more sophisticated process design due to their sensitivity to deviations in the raw materials or process setup. For example a larger gap around the fiber preform can lead to trapped gas in the middle of the part. Such gas inclusions can lead to porosity or even larger dry spots and thus an unusable part.

At the DLR Institute of Composite Structures and Adaptive Systems adapted and low cost ultrasonic sensors for LCM monitoring were developed. The sensors do not require direct contact to the part and therefore do not affect the part surface or mold. Due to enhanced signal analysis not only the flowfront arrival can be detected, but also its flow speed. Further the moments of wetting of the mold surface and the infiltration through the part thickness can be distinguished. The sensor system is also able to perform cure monitoring including the detection of gelation and vitrification points.

These sensor inputs are coupled with a fast flow simulation where the model parameters are adapted to match the measurement by a sophisticated optimization algorithm. The most important model parameters are the permeability and gap sizes. By adapting the simulation the pointwise monitoring results are transformed into a two-dimensional representation of the flowfront and enables the prediction of its further course. The results are used to detect gas inclusions and areas of high porosity. If in a LCM process none of these defects are detected the NDT process could be omitted. In the case of detected defects only these areas would have to be tested potentially.

KEYWORDS Liquid Composite Molding | | NDT reduction | Process Simulation | Ultrasonic Process Monitoring |


WE.2.C.4

Presenting author : Daniela Munalli - The University of Nottingham

Co-Authors : Daniela Munalli1 | Georgios Dimitrakis1 | Stephen Greedy1 | Dimitrios Chronopoulos1 1. The University of Nottingham

THE USE OF FREE-SPACE MICROWAVE NON-DESTRUCTIVE TECHNIQUES: SIMULATION OF DAMAGE DETECTION IN CARBON FIBRE REINFORCED COMPOSITES.

ABSTRACTS Microwave non-destructive testing (MNDT) methods represent an effective solution in detecting defects within composite structures with relatively low electrical conductivity. They offer the advantage to overcome the problems of traditional NDT techniques such as coupling, danger coming from ionizing radiation, limited depth of operation, large wavelengths, time consuming post processing. Near-field microwave and millimetre non-invasive inspections have been successfully used for detecting defects such as disbond and delamination in complex structures. In dielectric materials, they can be used for dielectric properties characterization, degree of porosity evaluation, degree of ageing, anisotropy, dielectric mixture constituents determination, state of cure. When it comes to the analysis of carbon fibre reinforced polymers (CFRPs), the use of these non-destructive techniques is restricted by the composite relatively high conductivity of about 104 S/m. In this paper, the investigation of a free-space microwave method for non-destructive testing of unidirectional CFRPs has been carried out by means of a pair of standard gain horn antennas, covering a frequency range from 26.5 GHz to 40 GHz. With the simulations, experimental results related to the presence/severity of the analysed defects are linked to the variations of the measured scattering parameters Sij. The approach is based on the comparison between the electromagnetic signal reflected and transmitted through a healthy sheet material under test, when a radio frequency (RF) wave is incident on it, and the one reflected and transmitted by a damaged sheet. The eventual presence of the defect is revealed by measuring the mismatch between the two transmitted waveforms. The performance of this radio wave technique is investigated in relation to surface defects and also in relation to those types of defects that are less detectable with this method, such as delaminations, cavities and inclusions. The simulations make use of the finite integration technique (FIT) and the finite element method (FEM).

KEYWORDS Microwaves | Electromagnetic simulation | Damage | Non-destructive testing |


WE.2.C.5

Presenting author : David Harman - Synopsys

Co-Authors : David Harman1 | Paul W. Badding2 | Steve Pilz3 | Lin Cheng4 | Albert To4 | Nate DeRoo5 | Nick Brinkhoff5 | Philippe Young1 | Timothy Williams1 | Ross Cotton1 | Kerim Genc1

1. Simpleware product group, Synopsys, Inc. / 2. Technology and Advanced Pursuits Group Moog Incorporated / 3. Ansys, Inc. / 4. University of Pittsburgh / 5. NSI

NON-DESTRUCTIVE COMPONENT INSPECTION AND NUMERICAL SIMULATION: APPLICATIONS TO ADDITIVE MANUFACTURING

ABSTRACTS Additive manufacturing (AM) gives aerospace part manufactures advantages in terms of flexibility when designing components. In addition, AM methods help with traditional challenges such as prototyping or testing multiple design iterations, as well as for optimizing structures with lattices for weight-saving. However, it can be difficult to quantify defects in AM parts, for example during the printing stage. Non-destructive inspection and numerical simulation methods have therefore been developed to reduce uncertainty by comparing as-designed CAD models to models generated from as-manufactured parts scanned using computed tomography (CT).

Synopsys, ANSYS, and North Star Imaging collaborated on a workflow for going from a 3D CT scan of an AM part to a Finite Element (FE) simulation. In this presentation we will discuss the key steps in this process, from scanning of a part through to image segmentation and processing in Synopsys Simpleware™ software. We will show how surface deviation tools in Simpleware software allowed for comparison of the CAD and scanned model to identify and inspect defects.

The presentation will also look at how FE simulation in ANSYS software made it possible to evaluate how the CAD and CT-based models perform under specific conditions. To understand the results and the success of this workflow, we will give an example of its use by Moog, Inc., for designing an impulse pressure manifold. This workflow involves inspection of residual problems from the AM process, and how the CT to simulation method identified unforeseen defects and enabled Moog to assess the usability of an AM-produced part.

The overall goal of this presentation is to consider the benefits of an integrated workflow for CT-based inspection and simulation of AM parts, with broader applications to traditional manufacturing and design challenges. We will also discuss the value of this method for aerospace companies in terms of reducing the risk of design uncertainty and manufacturing errors, as well as potential future developments in using these techniques.

KEYWORDS Computed tomography | Numerical simulation | Additive manufacturing |


WE.3.A.1

Presenting author : Benjamin Ducharne INSA Lyon

Co-Authors : Bhaawan Gupta1 | Benjamin Ducharne1 | Tetsuya Uchimoto2 | Gael Sebald3

1. LGEF, INSA Lyon / 2. IFS, Tohoku University / 3. ELyTMaX, Tohoku University

MICRO-MAGNETIC NON-DESTRUCTIVE TESTING ON EXTREME CONDITION AGED SAMPLES.

ABSTRACTS Creep phenomenon is an important feature to assess in extreme condition applications, although the correlations with microstructure and magnetic behavior remain unclear. Conventional Eddy current testing has been extensively used for the ferromagnetic materials characterization but when it comes to creep damage detection, it becomes difficult to distinguish between the changes caused by the actual creep damage and from the signals generated by other sources like cracks, surface roughness, hardness, etc...

In this work, 12%Cr-Mo-W-V creep test samples are investigated using three electromagnetic inspection techniques. Magnetic parameters based on the results are then evaluated in comparison to the microstructure. Additionally, a modified Jiles-Atherton model has been used to numerically reproduce experimental results from Magnetic Incremental Permeability (MIP), Magnetic Barkhausen Noise (MBN) and standard B(H) measurements. All the three techniques exhibit different responses in understanding creep and the modeling parameters derived from the adapted Jiles-Atherton model parameters are then correlated to the microstructure information. Some suitable parameters are then shortlisted according to the application technique. Coupling between the stress and magnetic field is the main and important feature of the ferromagnetic materials consisting of various small magnetic domains in its microstructure [1][2].

Magnetic Incremental Permeability (MIP) is used to investigate samples as it is highly sensitive to stress. On the other hand, Magnetic Barkhausen Noise being sensitive to the mechanical changes in the materials is also used to analyze the samples in addition to standard B(H) curve measurements. Finally, ferromagnetic hysteresis models such as dry friction quasi-static model [3], Preisach model [4], Jiles-Atherton model [5], which are based on magnetic induction B versus applied magnetic field strength H, are implemented to get the simulated data based on experiments. The objectives of these simulations are to improve magnetic signatures interpretations in co-relation to microstructure.

References

[1] Schull P.J, New York. Marcel Dekker, Inc., 2002.

[2] B. Ducharne and al., IEEE Trans. on. Mag, vol. 99, pp. 1-6, 2018.

[3] B. Ducharne and al., J. of Phys. D: Applied Physics, vol. 40, Iss. 2, pp. 551-555, 2007.

[4] B. Zhang and al., IEEE Trans. on. Mag, vol. 54 iss. 3, 2017.

[5] B. Zhang and al., IEEE Trans. on. Mag, iss. 99, 2018.

KEYWORDS Micromagnetism | Magnetic incremental permeability | Non destructive testing | Barkhausen noise |


WE.3.A.2

Presenting author : Arun Kumar Yadav - AGH University of Science & Technology

Co-Authors : Arun Kumar Yadav1 | Janusz Szpytko1

1. AGH University of Science & Technology

DEVELOPMENT OF PORTABLE WIRELESS NON-DESTRUCTIVE CRACK IDENTIFICATION METHOD BY USING GMR SENSOR ARRAY FOR OVERHEAD CRANE BRIDGES

ABSTRACTS Structural Health monitoring of overhead cranes bridges by the traditional inspection system with wired and bulky instrumental technologies face many challenges during the harsh environment and under working condition. This paper proposes a portable wireless and efficient NDT method using the GMR sensor array technique for the identification of fatigue cracks in the bridges of travelling overhead cranes. In order to enhance the efficiency of overhead cranes by minimizing the inspection time, a portable wireless robot combined with GMR (Giant Magnetoresitivity ) sensor and NDT technique is presented. This novel solution offers mobility, high accuracy and low power consumption. For the detection of cracks and defects in overhead crane bridge eight GMR (Giant Magneto Resistive) sensors of NVE (AA006-02) placed linearly on a PCB board with equal distance. Two magnetic wheel of neodymium N42 located on both side of the GMR sensor array to magnetize the steel surface for accurate defect reorganization. Unlike MPI (Magnetic Particle Inspection) where a global magnetization require for further inspection, this automated detection system only magnetize the surface area under the vicinity of GMR sensor array. The instrumentation circuit including eight high speed multiplexer, Operational amplifier, and one 8 bit analog to digital converter. A PIC 877A microcontroller and raspberry pie was used to perform local data storage, data processing and controlling. This presented testing solution is quick and offers a step towards automated testing of overhead crane bridges. However it improves the work efficiency and can meet the serious challenges within the inspection of overhead crane bridges.

KEYWORDS GMR | Sensor Array | Non- destructive testing | Overhead crane bridges | Crack Inspection |


WE.3.A.3

Presenting author : Shurui Zhang - Institute of Fluid Science, Tohoku University

Co-Authors : Shurui Zhang1 | Sho Takeda1 | Tetsuya Uchimoto1 | Toshiyuki Takagi1 | Mitsuo Hashimoto1

1. Institute of Fluid Science, Tohoku University

SIZING METHOD OF CRACK LENGTH ON CARBON STEELS FOR EDDY CURRENT TESTING USING TRANSMITTER-RECEIVER PROBE

ABSTRACTS Transmitter-reciver(TR) probe is one of the most common eddy current testing (ECT) probe used for crack detection. The previous study showed that due to the existence of magnetic flux leakage (MFL) in carbon steels, the amplitude of ECT signal can be influenced by the scanning angle of the TR probe. In addition, the MFL works effectively on crack estimation because the effect of MFL makes the signal more sensitive to be detected. Quantitative measurement of the size of the crack is important for evaluating the extent of the damage to the structure and for timely repair. In the previous research, the 12dB down method was proposed for length sizing. Nevertheless, the evaluation of the crack size is not precise especially when the length of crack is shorter than the distance between transmitter and receiver coils, because the 12dB down method only roughly assumes the crack length by obtained ECT signals. In this study, to improve the precision of the crack sizing especially for short cracks, ECT signals were processed by using two functions: Gaussian function and unary quadratic function, and the relationship between ECT signal and crack length was investigated. The ECT signals were Gaussian fitted, and the relationship between the variance of the obtained Gaussian function and the crack length was calculated as the unary quadratic function. To investigate the difference of the precision of the length estimation due to the shape and the length of the cracks, two types of cracks, rectangular and elliptical, with different lengths were prepared on the carbon steel plate. In addition, the angle of TR probe was set to 0° and 90° in order to investigate the effect of the MFL on ECT signal. The precision of new signal processing method is evaluated by comparing the estimated length and the measured length of cracks. As a result, it is clarified that the new signal processing method can estimate the crack length more precisely than the previous 12dB down method especially for the short cracks. The errors between the measured and the estimated lengths of the elliptical cracks were smaller than that of the rectangular cracks because of the signals obtained from the rectangular cracks were too complicated to be fitted on Gaussian curve. Moreover, the error when the scanning angle is 90° is smaller than that of 0°.

KEYWORDS Eddy Current Testing | Transmitter/receiver probe | Crack length sizing | Gaussian fitting | Unary quadratic function |


WE.3.A.4

Presenting author : N. Sergeeva-Chollet - CEA List

Co-Authors : N. Sergeeva-Chollet1 | C. Fermon² | A. Solignac² | M.Pannetier-Lecoeur² 1. CEA List | 2. SPEC CEA |

MR SENSORS ARRAYS FOR EDDY CURRENT TESTING

ABSTRACTS Eddy Current (EC) Technique is a powerful method for detection of surface notches and of buried flaws during inspection of metallic parts. This technique is used for inspection of aerospace components. Classical winding coils are the most commonly used EC sensors. Nevertheless, when the size of flaws decreases or the defect is rather buried deep inside the material, traditional winding coil probes turn out to reach their limits. For this reason, other technologies are investigated to improve this technique.

Magnetoresistive sensors present the advantages of flat frequency response and dimensions at the micron size. These sensors are hence very attractive for the detection of buried defects that require low frequencies because of skin depth effect. Also, they are suitable for small surface defects due to high spatial resolution because of their manufacturing down to µm without losing their field sensitivity. In addition, several magnetic field components can be simultaneously detected for a better analysis of defects.

We will present last advances of MR based probes containing arrays of GMR- (giant magneto resistance) and TMR-elements (tunnel magneto resistance) with comparison of experimental datas and simulations on Aluminium and Titanium mock-ups.

We will discuss the input brought by the development of ASIC components for compact probes and paths to develop probes adapted to complex geometries.

KEYWORDS MR sensors | Eddy current |


WE.3.C.1

Presenting author : Philipp Jatzlau - Technical University of Munich

Co-Authors : Philipp Jatzlau1 | Christian U. Grosse1 1. Technical University of Munich

LOCAL ACOUSTIC RESONANCE SPECTROSCOPY: AN ESCALATION APPROACH FOR EFFICIENT NDT OF FIBER REINFORCED COMPOSITES

ABSTRACTS Local acoustic resonance spectroscopy (LARS) is a non-destructive technique suitable for fast defect detection in large planar parts, especially in fiber composite structures. Applied in the acoustic frequency spectrum LARS is closely related to the coin tap test. In recent years, several applications in mechanical engineering have been established. These include the inspection of GFRP rotor blades as well as defect detection in CFRP parts in the automotive and aeronautic sectors. LARS is suitable for fast and therefore inexpensive measurements, also because it can be automated easily. For this, an automated tapping device for usage with a small industrial robot is developed in a student project. The objective of this system is to be able to scan plates of a maximum area of approx. 1m² using a roving impulse hammer and a capacitive microphone. Alongside experimental data, numerical simulation of the impulse response within the part is particularly useful to optimize the configuration on both the transmitting and receiving side for early identification of possible disturbances. After being detected by LARS, potential defect locations can then be more closely inspected by more complex non-destructive or destructive methods such as ultrasound. The general goal of this escalation approach is to reduce overall inspection effort.


WE.3.C.2

Presenting author : Michael Krumm - RayScan Technologies GmbH

Co-Authors : Michael Krumm1 | Volker Hämmerle1 | Héctor Cárdenez1 | Michael Fix1 | Christoph Sauerwein1 1. RayScan Technologies GmbH

3D X-RAY INSPECTION SYSTEM FOR HELICOPTER ROTOR BLADES

ABSTRACTS Modern-style helicopter rotor blades have a complex structure consisting of lightweight materials, such as fiber-reinforced plastics, foams or honeycomb structures, and metallic components such as titanium, aluminum or steel. Selection, combination and arrangement of the individual materials and structural elements are optimized to ensure the desired behavior for the respective rotor blade areas.

The quality assurance of such complex components requires a complete representation of the total component volume in order to detect pores, defects, delaminations, cracks and other discontinuities and to verify the inner structure. A detailed analysis showed that 3D X-ray techniques are best suited for this purpose.

The system presented here, was developed for the following purpose: complete horizontal, fully automatic handling and complete three-dimensional testing of helicopter rotor blades with up to 11 m length and 600 mm width and with up to 400 kg mass. Further, generation of 3D volume sectional images from partially incomplete data sets in different quality levels as well as processing and management of terabytes of memory. As part of the development, a novel measurement strategy for acquiring 3D information based on the successful RoboTom technique has been introduced, combined with an exact manipulation system and a compact radiation protection cabin.

This paper presents the developed system and the typical measurement results.

KEYWORDS X-ray | 3D Computed Tomography | Helicopter | NDT | Rotor blades |


WE.3.C.3

Presenting author : Wolfgang Rohringer - Xarion Laser Acoustics

Co-Authors : Balthasar Fischer1 | Wolfgang Haase2 | Thomas Gramberger2 | Nils Panzer1 1. Xarion Laser Acoustics | 2. Fill GmbH

MILLIMETER-SIZED NON-CONTACT ULTRASOUND PROBE BASED ON FIBER-COUPLED LASER EXCITATION AND DETECTION

ABSTRACTS For the ultrasonic inspection of confined spaces, a small probe head is desirable. We present a novel fully integrated laser-acoustic inspection head of 7mm by 7mm footprint: the device combines two miniaturized optical interferometers for acoustic signal detection. These two Fabry-Pérot interferometers are arranged in a 90 degree fashion in respect to each other, so that butt joints and corners can be accurately inspected. The ultrasound signal is generated by a short laser pulse, which is also delivered via an optical fiber, hence also being accessible to confined spaces. Both signal generation and signal detection are not requiring physical contact to the workpiece and do not require a coupling liquid.

This novel laser ultrasound testing head can be mounted on a robot in a through-transmission and a single-sided echo configuration, and enable a fully automated inspection. The design of the device is presented, results of scans obtained from CFRP sandwich structures are discussed. The performance and the design are compared to a classical liquid-coupled ultrasound inspection setup, the so-called squirter method. It is found that with comparable sensitivity at 1MHz, the laser-based head is much smaller than the squirter head; on the other hand, the dry inspection using the laser requires additional safety measures such as eye protection. However, a strongly diverging laser beam design leads to a beam expansion to a degree that the laser is eye-safe from a distance of 2m, which is a typical distance of a robot safety fence, which can easily be equipped with a laser interlock. In this scenario, no laser safety googles or additional protective measures are required for the operator.

KEYWORDS Ultrasound | Laser | NDT | Optical Microphone | CRFP |


WE.3.C.4

Presenting author : Lukasz Ambrozinski - AGH University of Science and Technology,Krakow, Poland

EFFICIENT IMPLEMENTATION OF CORRELATION-BASED TILT FILTER FOR IMAGING OF CRFP PLY WAVINESS USING LASER ULTRASOUND

ABSTRACTS Ply waviness that may arise during the manufacturing of carbon-fiber reinforced plastics (CFRP) is extremely dangerous, dramatically reducing the designed performance of a composite structure. Wrinkles belong to the most difficult defects to detect and characterize since they do not produce large echoes like other flaws. Laser ultrasound (LU) provides sub-ply imaging resolution permitting visualization of CFRP details in a non-contact manner. Therefore, the technique seems feasible for wrinkles detection. It appears, however, that the quality of LU images can be reduced from low signal to noise ratio (SNR) obtained at points with low light reflectivity. A standard procedure to improve SNR is repeating the measurements and averaging the resulting signals. In the case of LU operating at high pulse repetition rate, however, this approach may lead to heat accumulation and can damage the inspected surface. As a possible solution, the scanning can be performed at full repetition rate over a relatively dense grid of sensing points and the adjacent signals can be averaged within a weighting spatial window. In the presence of wrinkles however, the signals are shifted; a simple addition of non-aligned waveforms reduces the signal amplitude and removes information about the structure. As a solution, a correlation-based tilt-filter can be used. The method investigates local time-shifts between the signals and performs averaging along ply orientation. Since the technique is based on short-time cross-correlation, processing of large sets of data in the time domain can be challenging. Therefore, an efficient implementation of the technique in the frequency domain is presented in this paper. Replacing numerically expensive time-domain procedures with multiplication in the frequency domain leads to an efficient algorithm for visualization and quantification of wrinkles severity.

KEYWORDS CFRP | Tilt filter | Laser ultrasound | Wrinkles |


WE.3.C.5

Presenting author : Sreedhar Unnikrishnakurup - Center for non-destructive evaluation, IIT Madras, Chennai, India

Co-Authors : Sreedhar Unnikrishnakurup1 | Bala Pesala1 | Krishnan Balasubramaniam1 1. Center for non-destructive evaluation, IIT Madras, Chennai, India

NONDESTRUCTIVE EVALUATION OF THERMAL BARRIER COATING THICKNESS DEGRADATION USING INFRARED THERMOGRAPHY AND TERAHERTZ-TDS IMAGING

ABSTRACTS Being hot gas path components, the super alloy flaps and spacers of the gas turbine engine are coated with ceramic Thermal barrier coatings to withstand the high temperatures. During prolonged exposure at high service temperatures, the microstructure of the ceramic layer changes and it undergoes sintering. This can lead to an increase in its thermal conductivity during service. Such increase in the conductivity is undesirable because it would reduce the ability of the ceramic coating to provide the required thermal insulation to the underlying substrate.

During service the coatings degrade because of erosion by hot gas and also by localised wear due to rubbing of flaps with spacers. It is necessary to assess the condition of the coatings as a function of service life through suitable non-destructive means. Pulse phase thermography and THz-TDS techniques are used to evaluate the degree of degradation of the TBC top coat thickness. Infrared thermography has the advantage of fast inspection of a large area. In this work, we used a numerical simulation aided calibration and development of a regression model to quantitatively analyse the thickness degradation in TBC system undergone variable time of thermal exposure. These measurements were later verified using well detailed THz-TDS imaging.

Experimental results of both technique indicate that these two techniques are feasible for the evaluation of thickness degradation in TBC system.

KEYWORDS TBC | Pulse phase thermography | THz | Thickness degradation |

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THU.1.A.1

Presenting author : Arantza Mendioroz - Departamento de Física Aplicada I, Escuela de Ingeniería de Bilbao, Universidad del País Vasco UPV/EHU

Co-Authors : Jorge González1 | Javier Rodriguez-Aseguinolaza2 | Arantza Mendioroz2 | Agustín Salazar2

1. Department of Applied Physics, CINVESTAV Unidad Mérida / 2.Departamento de Física Aplicada I, Escuela de Ingeniería de Bilbao, Universidad del País Vasco UPV/EHU

SIZING THE WIDTH OF TILTED CRACKS USING LASER SPOT LOCK-IN THERMOGRAPHY

ABSTRACTS Laser spot thermography has been successfully applied to characterize the width of narrow (down to 0.5 micron) vertical cracks in both, modulated and pulsed regimes. In addition to the experimental thermographic procedure, the accurate quantification of the properties of the crack involves the calculation of the surface temperature distribution. The solution of this heat diffusion problem can only be accomplished analytically in the case of infinite vertical cracks. For more realistic situations, i.e., when the crack is finite, is tilted, or is not flat, etc., numerical approaches are needed.

In this work, we address the characterization of infinite tilted cracks using laser spot lock-in thermography. Continuous finite element models (FEM) have been widely implemented to solve the heat diffusion problem in cracked specimens. These models propose separate domains for the sound material and the crack, which is treated as a volume filled with air. As a consequence, the system is discretized by using conforming meshes that match at the interfaces between the bulk and the crack, leading to continuous temperature distributions in both domains. Even if these methods provide appropriate solutions, they present important shortcomings such as the treatment of narrow cracks, which involves extremely fine meshes leading to very poor computational efficiency.

To overcome this difficulty, we have developed a new numerical approach based of discontinuous Galerking finite elements modelling (DG-FEM) which is much more efficient to deal with narrow cracks (below 10 micron). The use of DG-FEM enables non-continuous solutions of the thermal diffusion equations over the crack, which is modeled as a single interface characterized by a thermal resistance (Rth) value. The procedure we propose to evaluate this thermal resistance lies in fitting the experimental surface temperature profile perpendicular to the crack, through the center of the laser spot, to the theoretical model. Once determined, this thermal resistance can be related to an air gap width (L) through the thermal conductivity of air (Kair) by Rth = L / Kair.

In order to validate the methodology, we have performed laser spot lock-in thermography experiments on stainless steel (AISI-304) samples containing infinite artificial slanted cracks of different widths at pre-selected angles (30, 45 and 60 degrees) with the sample surface. The experimental temperature amplitude profiles were introduced as input data on the developed inversion algorithm. The results confirm the success of the proposed methodology, combining DG-FEM and laser spot lock-in thermography, in characterizing the width of tilted cracks.

KEYWORDS Infrared thermography | Crack characterization | Tilted cracks |


THU.1.A.2

Presenting author : Joachim Jonuscheit - Fraunhofer ITWM, Kaiserslautern, Germany

RADOME INSPECTION WITH TERAHERTZ WAVES

ABSTRACTS We present a terahertz imaging system for aircraft radome inspection based on a two-frequency FMCW radar working at center frequencies of 100 and 150 GHz and with 40 and60 GHz bandwidth, respectively. The imaging sensor combines two all-electronic multiplier chains at the respective frequencies and is integrated in the production environment of radomes built of glass fiber-reinforced composite structures. While images acquired at the two distinct working frequencies can yield different information of possible structural defects, at the same time, a data fusion algorithm is applied combining the signals of both terahertz sensors for enhanced depth resolution by a total FMCW bandwidth of 100 GHz.

I. INTRODUCTION

Fiber-reinforced plastic (FRP) composite structures are widely used in mechanical construction where a combination of light weight, high structural integrity, and – in the case of aircraft radomes – transparency for radio and microwave frequencies is required. Such composite structures commonly consist of multiple functional layers of various materials, e.g., aramide and glass fiber material. Since the structures are built layer by layer, an inline production quality control is desirable to detect possible delaminations, structural imperfections and other defects already during manufacturing. Defect detection is furthermore desired in in-field inspection of complete radome structures during maintenance procedures. Frequency-modulated continuous-wave (FMCW) terahertz imaging systems have shown to present an excellent combination of spatial and depth resolution for typical defect sizes while providing large penetration depths in the respective materials [1,2].

In this contribution we demonstrate a two-frequency FMCW imaging system which was integrated in an aircraft radome production environment [3]. We show first measurements of a test radome structure as well as images of flat FRP panels with embedded artificial defects as well as real radomes.

REFERENCES [1] I. Amenabar, F. Lopez, and A. Mendikute, Journal of Infrared, Millimeter, and Terahertz Waves, vol. 34, no. 2, p. 152, 2013.

[2] E. Cristofani et al., Optical Engineering, vol. 53, no. 3, p. 031211, 2014.

[3] F. Friederich et al., “Terahertz Radome Inspection,” Photonics, vol. 5, no. 1, p. 1, 2018.

KEYWORDS NDT | Radome | Terahertz | Millimeterwave | Production |


THU.1.A.3

Presenting author : Uli Schmidhammer - Teratonics

Co-Authors : Xavier Neiers1 | Marco Cavallari1 | 1. Teratonics

SINGLE-SHOT PULSED TERAHERTZ NON-DESTRUCTIVE EVALUATION SYSTEMS FOR IN-LINE PRODUCTION CONTROL AND AUTOMATED INSPECTION

ABSTRACTS The regulated reduction of greenhouse gas emissions is accelerating the adoption of increasingly lightweight innovative materials - such as composites, plastics and coatings - in the transportation industries. New means of Non-Destructive Testing and Evaluation (NDT&E) are needed to meet the quality and safety requirements for these materials during production and maintenance operations. Supported by the «Industry 4.0», a production integrated NDT&E is often needed during the manufacturing process itself (as opposed to a control of the finished product) in order to minimise the waste of time, raw materials and energy. These new controls require stability, operational simplicity, speed, depth of analysis and characterization of internal defects. These needs are not all met by current methods (X-rays, ultrasound, optical methods...). Teratonics satisfies these industrial requirements by providing non-destructive, fast, non-contact and non-ionizing control solutions based on a breakthrough single-shot terahertz (THz) pulse technology invented initially at the University Paris Sud / CNRS, Paris Saclay. By reducing the acquisition time by more than 10,000,000 times compared to the commercial state of the art, our technology opens up a major field of application for THz radiation analysis. Thanks to its unparalleled speed and stability, our solution can be used as a production integrated NDT&E system for in-line inspection. It can also be used as a mobile NDT&E equipment for maintenance operations. It can perform dimensional control (including thicknesses with micrometric precision), and defect sizing and imaging on the surface and inside products. For example, in composite tapes, it is possible to control the fiber / resin ratio and the spatial homogeneity. During the placement of the tapes, the orientation and the contact of the tapes can be checked. When producing composites by RTM or pultrusion, typical defects that can be detected are fiber misalignment/waviness, fiber density variations, bubbles, inclusions, or delamination. In glued products, our technology allows to characterize the distribution and the thickness of the bead of glue and to reveal bubbles or inclusions. It can also be used to detect weld defects, thickness variations or bubbles in welded plastics or composites. Finally, our technology can control thicknesses of single or multi-layer coatings with accuracies of the order of a few microns on both metal and plastic / composite surfaces. Our presentation will present the major results obtained to date and will suggest future directions, both on the NDT system design and on the data analytics.

KEYWORDS Terahertz NDT&E method | Defect sizing and imaging | Mobile NDT&E for maintenance | Production integrated NDT&E | Dimensional control |


THU.1.A.5

Presenting author : Thierry Mantel - GelSight Inc.

Co-Authors : Thierry Mantel1 | Micah K. Johnson1 1. GelSight Inc.

3D SURFACE TOPOGRAPHY MEASUREMENT USING ELASTOMERIC CONTACT

ABSTRACTS GelSight is a 3D surface imaging technology based on an elastomeric sensor that enables high-resolution surface metrology and compliant tactile sensing. Using controlled illumination and advanced computer vision techniques, GelSight can transform multiple 2D images into a detailed 3D surface within seconds.

A painted membrane on the gel closely conforms with any surface it touches. Then multiple images of the surface with different lighting conditions are taken in a very short time from a single high-resolution digital camera. A 3D reconstruction algorithm generates a height map allowing precise measurement of surface shapes regardless of the optical properties of the material.

Based on these concepts, GelSight, Inc. has developed a portable high-resolution 3D measurement system that can quantify surface geometry down to one micrometer on any rigid material, including metals, composites, plastics, glass, fabric, and leather. The system can be taken to the factory floor or in a maintenance facility for in-situ measurements on aerospace components.

Working with researchers in the aerospace industry, GelSight, Inc. has developed streamlined algorithms of interest to the NDT community, including automatic measurement of the deepest point of a scratch, hole diameter and circularity, and fastener flushness. The GelSight Mobile system also has basic measurements such as gap widths, offsets, Z height profiles, radius of curvature and roughness. The system provides detailed digital information that can easily be integrated in advanced manufacturing organizations or in advanced on-line maintenance management services. For more advanced applications, the system can export data under formats readable by commercial analysis and metrology software.

GelSight systems are currently deployed in various industries such as aerospace, automotive, energy and many others.

KEYWORDS3d scanner | surface topography | tactile sensing |


THU.1.A.6

Presenting author : Ludovic Gaverina - ONERA

Co-Authors : Ludovic Gaverina1 | Thibault Archer1 | Bruno Passilly1 | Camille Trottier1 | Jean-Michel Roche1 1. ONERA

FLYING LINE ACTIVE IR THERMOGRAPHY APPLIED TO THE INSPECTION OF ENVIRONMENTAL BARRIER COATINGS

ABSTRACTS In the aerospace industry, Environmental barrier coated (EBC) ceramic matrix composites (CMCs) are considered as an attractive option for use in turbine engines. When the system is subjected to thermal gradients, through-thickness cracks can appear. It is therefore crucial to investigate damage evolutions of the EBC. Twenty years ago, Krapez et al. proposed the “flying spot technique” based on a constant displacement of the laser spot to detect cracks in steel. Later, the Pulsed Flying Spot (P.F.S) was developed to obtain in-plane thermal diffusivity fields on heterogeneous and anisotropic materials. Though the laser spot is a very interesting approach due to its known analytical solution, it has a lower scanning rate than the line scan method. For this reason, the flying line method has been proposed instead to detect cracks in EBCs. Recently, ONERA has developed and improved two laser based setup: (i) one to perform thermal fatigue test and create a cracking network on the EBCs and (ii) a second one dedicated to the non-destructive inspection of the EBCs by the flying spot method.

The present paper is based on experimental tests carried out on a coated woven SiC/SiC CMC. First, advanced post-processing methods are developed and applied to the thermal sequences acquired by flying line thermography, in order to improve the detection of the cracks. Then, damage localization characterization approaches are introduced and discussed. Finally, conclusions and perspectives are addressed.

KEYWORDS Flying-Line | Environmental Barrier Coated (Ebc) | Ceramic Matrix Composites (Cmcs) | Non-Destructive Testing | Cracks |


THU.1.B.1

Presenting author : Ramanan, Sridaran Venkat - Saarland University

Co-Authors : Ramanan, Sridaran Venkat1 | Christian Boller1 1. Saarland University

A TOOLBOX CONCEPT TO CONFIGURE A SHM SOLUTION ON AGEING AIRCRAFT STRUCTURES BASED ON ACOUSTIC AND THERMAL METHODS

ABSTRACTS One of the challenging issues in aerospace industries is to configure a SHM solution for ageing aircraft structures. This is because of the lack of information regarding the current state of the material properties and the higher likelihood of damage to occur. Principally, when classical NDT actuators/sensors are embedded onto/into structures to perform real-time monitoring of tolerable damages, an SHM-solution is principally obtained. However, in reality this is not that much easy to be realised since most of the NDT techniques are off-line methods meaning they are human based and not implicitly ready for automation. Classical ultrasonic NDT methods like phased array ultrasonics have undergone technological innovations in terms of data acquisition and data representation through the development of Sampling Phased Array (SPA) and Reverse Phase Matching (RPM) methods. These methods have advantages in determining in-situ material properties and result in a comparatively higher probability of damage detection. Unlike the classical ultrasonic methods, where transducers can be virtually moved to any location on a structure, guided waves (GW) based sensing and actuation in SHM is fixed to a ‘static’ actuator/sensor network. In order to detect damages considered to be tolerable efficiently the optimal positions of actua-tors/sensor need to be identified in advance. To identify those optimal positions numerical simulation is indispensable, allowing something to be generated called differential imaging, that identifies where damage related sensor signals are to be recorded best. Laser Doppler Vibrometry (LDV) has proven to be another efficient tool for monitoring in the recent years often to be used as a means for validation. In addition to this, linear/nonlinear vibrational acoustics combined with thermography have shown a large potential in identifying particu-lar types of damage where the response has been monitoring representative frequencies based on Local Damage Resonance (LDR). When such LDR frequencies are used to excite the ultrasonic actuators, the signal received from the sensors will be sensitive to the given damage to which the LDR frequency refers.

This paper will present how a ‘toolbox’ has to be configured such that approaches used in classical NDT including SPA, RPM and LDR along with numerical simulations can be applied to design SHM system solutions for monitoring isotropic and anisotropic structural parts.

KEYWORDSSHM | Guided waves | Numerical simulation | Vibrational analysis | Phased array ultrasonics |


THU.1.B.2

Presenting author : Sevilia Sunetchiieva - KU Leuven

Co-Authors : Sevilia Sunetchiieva1 | Helge Pfeiffer1 | Martine Wevers1 1. KU Leuven

STRUCTURAL HEALTH MONITORING SYSTEM FOR MOISTURE INGRESS DETECTION IN SANDWICH COMPOSITE STRUCTURES

ABSTRACTS Aircraft innovation includes increasing the performance of air structures by utilizing new materials in order to be more durable and lighter. The percentage composite usage in recent airplane designs has reached more than 50% by weight which goes hand in hand with a reduction of fuel consumption. At the same time, the Maintenance, Repair and Overhaul (MRO) requirements for composites are very different from those applied to metals which lead to new NDT procedures, including a still pending lack of trained staff and certification issues.

Honeycomb sandwich materials are widely used in aircraft structures. Some of them are taking an important role in the flight control process, like rudders, elevators, and winglets which in a long run need to be appropriately maintained. Despite the thickness of the core including the metal meshes, sandwich composites are still relatively light and have a relatively high flexural strength. The most common purpose of manufacturing sandwich structures is to obtain the greatest stiffness at minimum total density (average). However, the water ingress problem is very common for these structures with even further risk of corrosion if the core is made of aluminum honeycomb and/or adhesive bond (node and skin-to-core) degradation. Moreover, structural damage (node bond failure) could appear due to repeated freeze-thaw cycles of trapped standing water (in liquid or vapor state) in the structure during normal flight operations.

Here, we aim to monitor the water ingression by percolation threshold sensors integrated into monolithic and sandwich composite structures, addressing the difficulties of the sandwich composite manufacturing process, e.g. high pressure and temperature, its quality and data acquisition. The percolation threshold sensor is based on the collapse of a conductive particles network in a randomized lattice structure. The presented SHM system finally is validated on a lab scale and it is robust to environmental changes and sensitive to moisture ingression.

Part of the research leading to these results has received funding from the European Community’s Seventh Framework Programme [FP7/2007-2013] under grant agreement n°212912 and the “NDTonAIR” project (Training Network in Non-Destructive Testing and Structural Health Monitoring of Aircraft structures) under the action: H2020-MSCA-ITN-2016- GRANT 722134.

KEYWORDS Structural Health Monitoring | Moisture ingress | Sandwich composites | Integrated percolation sensor |


THU.1.B.3

Presenting author : Marwen Aouini - Institut de Soudure

Co-Authors : Marwen Aouini1 | Morgan Ferrari1 | Slah N. Yaacoubi1 | Cedric Pradalier2 1. Institut de Soudure / 2. Unité Mixte Internationale 2958

WIRELESS SYSTEM FOR STRUCTURAL HEALTH MONITORING WITH GUIDED ULTRASONIC WAVES: DETECTION OF DEFECTS

ABSTRACTS In this paper, a miniaturized, low-power wireless system was developed to provide structural health monitoring (SHM) of a metal structure based on Ultrasonic Guided Waves (UGW) technique. This non-destructive technique has an excellent long-range diagnostic capability and it is effective for detecting material losses, cracks and structural fatigue damages. The developed system makes it possible to send the collected short-range and long-range data to a processing center. It plays both the role of an actuator to excite a piezoelectric patch with UGW as well as the role of a sensor that can detect and remotely send the waves responses through emails and/or via an FTP server. In order to control the energy autonomy of the system, the deep sleep mode was used. In this mode, a microcontroller that has an internal clock was used. This clock allows the system to wake up at a predetermined time interval to send and receive the waves using only one single module and then transmit the data remotely. After the data transmission, it goes into deep sleep mode. To validate and verify the effectiveness of the proposed approach, tests were carried out on two types of databases collected using different artificial damages. In the first database, damages were created by removing the material. While in the second case, damages were simulated by adding magnets on the surface of the structure. The choice of this method of the damage creation by magnets was justified using a simulation study. A graphical interface has been developed for the visualization and the automatic detection of damage by using statistical features sensitive to the presence of damages and setting a detection threshold. This threshold is calculated based on the statistical distribution of the damage indices. The experimental results show that the statistical index that we have proposed is efficient.

KEYWORDSStructural health monitoring (SHM) | Ultrasonic guided wave (UGW) | Miniaturized and low power wireless system | Artificial damages | Statistical characteristics |


THU.1.B.4

Presenting author : Wiesław Ostachowicz - Polish Academy of Sciences, Institute of Fluid–Flow Machinery, Gdansk, Poland

Co-Authors : Tomasz Wandowski1 | Paweł Malinowski | Wiesław Ostachowicz1 | Bartosz Puchowski2 1. Polish Academy of Sciences, Institute of Fluid–Flow Machinery, Fiszera 14 St., 80–231, Gdansk, Poland / 2. CreeYacht, Platynowa 16, 84-123 Rekowo Gorne, Poland

DAMAGE ASSESSMENT OF COMPOSITE STRUCTURES USING ELECTROMECHANICAL IMPEDANCE METHOD

ABSTRACTS In this paper results of application of electromechanical impedance (EMI) method for damage assessment in composite materials were presented. Object of investigation was a glass fibre reinforced polymer (GFRP) sandwich structure with honeycomb core, stiffeners and bonded joints. The EMI method is takes advantage electrical parameters of a piezoelectric transducer that is either bonded on the structure or embedded inside it. Due to electromechanical coupling of the transducer with the structure, mechanical resonances of structure can be seen in spectra of electrical characteristic of the piezoelectric transducer.

Authors investigated the problem of damage assessment using EMI method under the influence of varying temperature. The studies were focused on the composite materials. Authors investigated both the influence of changing temperature and the influence of damage on resistance spectra gathered at the transducer. Results showed that temperature compensation is needed for the purpose of damage detection. Authors proposed temperature compensation algorithm based on signal correlation. Composite materials especially with sandwich structure are characterised by large material damping which could be a problem in the field of damage assessment. Due to the fact of large damping, the damage sensitive area for EMI method could be strongly reduced. This problem was also investigated in the conducted research.

KEYWORDS Electromechanical impedance | Composites | Damage assessment |


THU.1.B.5

Presenting author : Olivier Ponte Felgueiras - MINES Paristech, PSL University, Centre des Matériaux (CMAT), CNRS UMP 7633, EVRY, France

Co-Authors : Olivier Ponte Felgueiras1 | Jacques Renard1 1. MINES Paristech, PSL University, Centre des Matériaux (CMAT), CNRS UMP 7633, EVRY, France

VIBRATION HEALTH CRITERION BASED ON THE COMBINATION OF BENDING AND TORSIONAL MODES TO MONITOR THE HEALTH STATUS OF SAFETY-CRITICAL COMPOSITE STRUCTURES

ABSTRACTS Despite high interest in composite materials (mechanical performance and mass reduction), their application in the transport industry is still limited: suspension, wheels, steering connection elements (axle fronts and postpones, direction and hanging devices,…). In order to ensure the reliability of these safety-critical parts, it is essential to dimension them properly in the design phase, validate correctly the prototypes and, especially, to be able to diagnose their health status throughout their lifetime. Nowadays, multiple methods are available, but measuring equipment which their use is often expensive, with long acquisition and postprocessing times, and often requiring immobilizing the vehicle or extracting parts of its structure. It is therefore desirable to develop a non-intrusive measurement method allowing the assessment of material degradation, from the mesoscopic to the structural scale (cracking, delamination, …), without the need to disassemble the structure.

Using the principles of experimental modal analysis, we aim at establishing a clear link between the evolution of certain modal parameters and the damage observed under tensile loading. In order to do this, the load is applied via a piezoelectric actuator, the response of the system is measured by a 3D vibrometer laser and the damage identification is carried out along a section of the specimen using a motorized optical microscope. The tensile modal basis is characterized for several stages of loading and damage. We propose a vibration criterion, using a combination of bending and torsional modes. The idea consists, firstly, of introducing specific damage, controlled by the orientation of composite plies in the specimen, and then allowing it to appear in a natural way (for instance originating at a porosity). This experimental vibration health criterion is then compared to its digital counterpart in order to validate its relevance.

KEYWORDSComposite materials | Health monitoring | Modal parameters (Dumping factor - Modal shape - Resonance frequency) | Bending and torsional modes | Cracking - Delamination |


THU.1.B.6

Presenting author : Fang Fang, Nanjiung University of Aeronautics and Astronautics, China

Co-Authors : Fang Fang1 | Lei Qiu1 | Shenfang Yuan1 | Yuanqiang Ren1

1. Nanjiung University of Aeronautics and Astronautics

DAMAGE MONITORING FRAMEWORK BASED ON PROBABILITY MODELING UNDER VARYING STRUCTURAL BOUNDARY CONDITIONS

ABSTRACTSA key challenge for the practical application of aircraft structural health monitoring (SHM) is to realize reliable damage monitoring under time-varying conditions. To deal with this challenge, a SHM framework based on probability modeling is proposed to provide a modular architecture with high generalization capability. In this framework, double probability models combining short term and long term SHM information are updated dynamically and an improved probability modelling method is proposed to construct models in a stable, adaptive and efficient way. Finally, the probability similarity of models is measured to realize normalized and reliable damage detection under time-varying conditions. The framework applied with the guided wave-based SHM technology is validated by the hole-edge cracks monitoring of an aircraft wing spar and the cracks are monitored reliably under varying structural boundary conditions.

KEYWORDS Structural Health Monitoring | Time-varying condition | Probability modeling | Dynamic update| Guided Wave | Aircraft structures |


THU.1.C.1

Presenting author : Marco Salucci - ELEDIA Research Center, University of Trento, Italy & ELEDIA Research Center Gif-sur-Yvette, France

Co-Authors : Marco Salucci1² | Paolo Rocca2 | Nicola Anselmi2 | Andrea Massa1,2

1. ELEDIA Research Center Gif-sur-Yvette, France 2. ELEDIA Research Center, University of Trento), Italy

INNOVATIVE LEARNING-BY-EXAMPLES APPROACHES FOR REAL-TIME NDT/NDE OF COMPLEX STRUCTURES

ABSTRACTS Non-destructive testing and evaluation (NDT&E) is aimed at non-invasively evaluating the structural integrity of complex structures and guarantee human safety in many civil and industrial (e.g., aerospace and nuclear) applications. Within this context, probing the structure under test (SUT) through electromagnetic (EM) fields and processing the resulting «signature» measured over an external observation domain allows one to retrieve preliminary diagnoses before proceeding with ad-hoc (often invasive) repairing/substitution actions. Typical NDT&E analyses can be subdivided into a sequence of inter-connected tasks aimed at progressively infer the SUT status. More in detail, the first task is aimed at detecting the presence of one or multiple defects with respect to a (a-priori known) healthy scenario. Then, a second task is devoted to estimate qualitative information such as the number and the position of the detected targets, while a third step is aimed at retrieving a guess of their shape and size. Finally, depending on the targeted application, a fourth task is the estimation of quantitative information (i.e., material composition) on the imaged defects.

Although fast and accurate EM forward solvers have been recently introduced, many state-of-the-art imaging approaches are not suitable for applications where an immediate feedback is required because of their iterative nature and the resulting very high computational load. On the other hand, learning-by-examples (LBE) strategies recently attracted particular attention since they can yield accurate and robust diagnoses with real-time capabilities. LBE methods are based on the generation of a training database of input/output pairs to build a computationally fast surrogate model of the (unknown) inverse operator relating measurements and SUT status. More in detail, such a process can be seen as a three-step procedure aimed at (a) reducing the dimensionality of the input/data space by identifying a reduced set of features carrying the largest information on the predicted output (i.e., the SUT descriptors), (b) collecting the lowest possible number of I/O training samples able to accurately model the underlying physical phenomena, and (c) train a machine learning (ML) algorithm with good generalization capabilities in order to effectively process previously unseen data during the on-line test phase. Accordingly, this work is aimed at providing an overview of the most recent advances on LBE techniques as applied to NDT&E scenarios, highlighting their current limitations and challenges as well as envisaging future trends including their natural evolution within the ever-growing deep learning framework.

KEYWORDSNDT/NDE | Learning-by-Examples (LBE) | Real-Time Inversion | Deep Learning |


THU.1.C.2

Presenting author : Peter Chow - Fujitsu

OPTIONS TO UNDERTAKE THE AI DIGITAL TRANSFORMATION JOURNEY FOR NDT IN AEROSPACE

ABSTRACTS Artificial intelligence (AI) in machine learning (ML) and deep learning (DL) technologies are making a colossal change in all areas of our lives, societies and businesses. Compared to previous generation of AI the main factor is no coding for every situations, just sufficient data to train the system to the needed accuracy level. This is a huge efficiency in scalability and cost. Also, previous out-of-scope applications such as non-destructive testing and evaluation (NDT&E) like ultrasound and similar methods for automated inspection and structural health monitoring (SHM) are now realisable. Combining with advanced image process technology for defect sizing assessment, the automated quality assurance process provides same high consistency across plants anywhere in the world.

This AI digital transformation undertaking is no simple task for any organisations. In the manufacturing NDT&E space some of the technical challenges are:

• Lack of expertise and skill personnel

• In a good production process the lack of data (e.g. defects) and the fabrication method frequently protected

• Further R&D or production insertion suitable

On the organisation side some of the reasons for undertaking that need to face are:

• Business need e.g. measurable benefits from AI digital transformation and why now

• Consequences of not undertaking e.g. delay taking actions

• Strategic fit e.g. enabling consistency across both within and across facilities

• Fit with programme plan e.g. digitalisation and/or Industry 4.0 roadmap

To leverage this technology to support NDT&E and SHM, what are the options today for companies? In this presentation we will present some of the options, “Continue As-Is”, “Develop In-House”, “Strategic University Collaborations”, and “Strategic Alliance with AI service providers” to help organisations thinking or already undertaking the AI journey.

KEYWORDS NDT&E | Artificial Intelligence | Automated Evaluation | Digital Transformation |


THU.1.C.3

Presenting author : Marco Salucci- ELEDIA Research Center, University of Trento, Italy

Co-Authors : Lorenzo Poli1 | Marco Salucci12 | Giacomo Oliveri12 | Andrea Massa12 | 1. ELEDIA Research Center, University of Trento,Italy 2. ELEDIA Research Center, Gif-sur-Yvette, France

MICROWAVE NDT/NDE THROUGH A PROBABILISTIC COMPRESSIVE SENSING METHOD

ABSTRACTS During the last years, microwave imaging techniques have emerged in the framework of non-destructive testing and evaluation (NDT/NDE) as an effective alternative to well-known methods such as X-rays or eddy current testing (ECT). Such methods afford several advantages, among which (i) the use of low-power/non-ionizing electromagnetic waves, (ii) the possibility to avoid a direct contact of the sources with the material under test, and (iii) the strong penetrability of microwaves into dielectric materials. Moreover, they can be exploited in several applicative framework ranging from structural health monitoring to biomedical diagnosis.

In this framework, this paper presents a novel method devoted to the retrieval of unknown defects or anomalies embedded within physically inaccessible dielectric media by processing the measured scattered radiation. Towards this goal, the Born approximation is applied to linearize the inverse scattering problem at hand, the total field within the undamaged structure being assumed almost equal to that in presence of the defects. Moreover, in order to counteract the strong ill-posedness and ill-conditioning issues, the proposed method properly combines prior information available on (i) the host media to be investigated and on (ii) the sparsity of the defect/anomaly (namely, physical sparsity or with respect to a suitable set of basis functions), by using a differential compressive sensing (CS) approach enabling an efficient retrieval of a few number of non-zero coefficients modelling the unknown solution. Finally, the inversion is formulated in a multi-task Bayesian compressive sensing (MT-BCS) framework and a fast Relevance Vector Machine (RVM) is used to reconstruct the unknown defects by taking into account the inter-relationship between the linear systems arising from multiple (sequential) illuminations/measurements of the host specimen. Both numerical and experimental results are presented in order to assess the effectiveness of the proposed methodology.

KEYWORDSMicrowave imaging | Bayesian Compressive Sensing (BCS) | NDT/NDE | Relevance Vector Machine (RVM) |


THU.1.C.4

Presenting author : Vasileios Dimopoulos - KU Leuven, Department of Mechanical Engineering, Belgium

Co-Authors : Vasileios Dimopoulos1 | Philip Becht1 | Dennis Janssens1 | Elke Deckers1 | Wim Desmet1

1. KU Leuven, Department of Mechanical Engineering,Belgium

EFFICIENT TR-MUSIC DAMAGE DETECTION IN COMPOSITES WITH A LIMITED NUMBER OF SENSORS

ABSTRACTS Time Reversal Multiple Signal Classification (TR-MUSIC) has been shown to successfully localize extended defects in complex media. To this end, an extended degradation is approximated through a set of independent and effective scatterers. These effective contributions dictate the minimum number of sensors and excitations needed for adequate measurements and precise classification.

More specifically, in the algorithm’s first step the obtained scattered field is analyzed into a signal and a noise space. In the second step the signal space information is used to highlight steering vectors focusing on the defect’s position. Overall, localization’s quality becomes proportional to the accuracy of the space separation which in turn depends on the number of sensors and scatterers existing in the system. However, in many real-life applications the latter is unknown. Therefore, it becomes problematic to identify and design sensing arrays a priori.

In this paper, for an extended degradation, we use a limited number of sensors to identify the scatterer’s position. Although it is common to use large arrays, here we prove through a monitoring network of reduced dimensions, we are able to obtain characteristic information for the defect. Over this process, the ideal signal space is approximated with only a limited number of observations. In addition, these approximations are later on enhanced by increasing data’s dimensionality. In practice, we prove that one may use a single sensor accompanied with multiple excitations and still be able to achieve accuracy analogous to the ideal network. Furthermore, due to reciprocity, this relationship may be inverted. The proposed approach has been evaluated with a sensing array of reduced dimensions performing damage localization on degraded composite structures. To demonstrate the algorithm’s robustness, information from only the vibro-acoustic range is exploited enabling for fast and inexpensive detection for subwavelength defects.

KEYWORDS Non-Destructive Testing & Evaluation | Time Reversal Multiple Signal Classification | Sensor Reduction | Composite Materials | Mid Frequency Range |


THU.1.C.5

Presenting author : Philippe Meynard - Visiconsult

Co-Authors : Philippe Meynard1 | Lennart Schulenburg1 1. Visiconsult

NDT 4.0 : APPLICATION OF INDUSTRY 4.0 IN NDT AND IMPACT ON AEROSPACE COMPANIES

ABSTRACTS Industries are living today a change called Industry 4.0. After the version 3.0 based on the electronics, computers and automation, this new evolution is now oriented with cloud, connected devices, Internet of things and networks. Actually, on aerospace companies, the need is to maintain a high-quality production despite higher volume, less time for control. Industry 4.0 could be an opportunity to match this new challenge.

In this paper, we present a description about NDT 4.0 and examples of this new concept on aerospace companies. NDT 4.0 is the declination of industry 4.0 dedicated to the NDT world. It gives new tendencies, key points for this market linked to Industry 4.0 with a description of the cycle (Autonomous robot; simulation; system integration; Internet of things; Cybersecurity; Cloud computing; Additive manufacturing; augmented reality and big data)

We will give examples of applications and customized systems applied with the NDT 4.0 philosophy. We will mention new challenges and developments using x-ray technologies.

KEYWORDSX-ray and Computed Tomography | NDT 4.0 | Automatized systems | Simulation | Automatic defect recognition (ADR) |


THU.1.C.6

Presenting author : Mahindra Rautela - Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India

Co-Authors : Mahindra Rautela1 | S. Gopalakrishnan1 1. Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India

DEEP LEARNING FRAMEWORKS FOR WAVE PROPAGATION-BASED DAMAGE DETECTION IN 1D-WAVEGUIDES

ABSTRACTS Deep Learning methodologies are said to mimic the brain cognition capabilities and are revolutionizing across various engineering domains. Wave propagation-based damage detection methodology is one of the preferred candidates for online health monitoring systems. In this paper, we have used deep learning models to detect cracks in 1D-waveguides using axial waves. A discontinuity in the waveguide in the form of a crack introduces prior reflections and these signatures are utilized to classify them. In this work, different cracks are introduced with varying crack lengths across different locations. High-frequency tone-burst signals are used to excite the waveguide and their time-domain representations are converted into the frequency domain. Spectral finite element formulations are used to model the cracks in the frequency domain. The solution is converted back into the time-domain and is used to form the feature space (inputs) for deep learning frameworks. We have used classification based supervised deep learning models: Dense Neural Networks (DNNs), 1D-Convolutional Neural Networks (1D-CNNs), Recurrent Neural Networks (RNNs) and Long Short-Term Memory (LSTMs) to detect damage in the waveguide. Alternatively, time-frequency analysis in the form of wavelet transform is also employed to train 2D-CNNs for damage detection. The proposed models are implemented in Python using TensorFlow APIs and the models are trained to learn decision boundary mappings from the feature space to the target space. New signatures are fed into the trained models to detect damages autonomously in real-time without resorting to time-taking pre-processing step and expert’s analysis. Metrics like accuracy, binary cross-entropy loss and training time per epoch are used to compare the performance of these frameworks. Their ability to learn and generalize over the phenomenon of damage detection is also discussed.

KEYWORDS

Deep learning | Wave Propagation | 1D-Waveguides | Spectral FEM | Damage Detection | DNNs| CNNs | RNNs | LSTMs |


THU.2.A.1

Presenting author : Hubert Voillaume - Eddyfi Technologies

Co-Authors : Hubert Voillaume1 | Olivier Roy1 | Frédéric Reverdy1 1. Eddyfi Technologies

APPLICATION OF TFM IMAGING FOR ENHANCED NDT IN AEROSPACE

ABSTRACTS Although ultrasonic phased array is now widely used for aerospace NDT, a new imaging technique called Total Focusing Method (TFM) is bringing new performances with high definition, realistic images. TFM imaging is now available with real time capabilities on rugged UT instruments, and the number of successful applications is growing. Several applications have been demonstrated for aerospace NDT showing advantages in terms of easy to setup, quality, analysis and reliability.

In this paper, we will compare PAUT and TFM and discuss how the improved images of TFM give practical advantages over other phased array techniques. Application cases of weld testing on Aluminium and Titanium assemblies, commonly used in aerospace industry, are presented. ATFM, an adaptive version of the imaging technique, is applied to inspect irregularly shaped components produced by the weld bead. Other application cases are presented regarding productivity of base steel for aerospace; how to increase coverage and quality of inspection in production stage.

KEYWORDSUltrasonic testing | PAUT | FMC/TFM | ATFM | Weld testing |


THU.2.A.2

Presenting author : Cécile BRÜTT - Safran Tech, Institut Langevin

Co-Authors : Cécile BRÜTT12 | Benoit GERARDIN1 | Alexandre AUBRY2 | Arnaud DERODE2 | Claire PRADA2 1. Safran Tech / 2. Institut Langevin

MULTI-ELEMENT ULTRASONIC EVALUATION OF SCATTERING SOLIDS BY REFLECTION MATRIX ANALYSIS

ABSTRACTS Multiple scattering due to strong heterogeneities of the microstructure make ultrasonic testing of forged metal alloys often difficult. Indeed, ultrasound imaging is based on the assumption that the RF signals come from single scattered waves only, so that there is a one-to-one correspondence between depth and time. Multiple scattering breaks this equivalence; as a consequence, the echo of a defect is harder to distinguish from structural noise. Thus, an estimation of the proportion of single versus multiple scattering would be a valuable indicator to assess the quality of ultrasonic inspection.

In this work, we present several estimators of the single-to-multiple scattering ratio, obtained by analyzing the scattering reflection matrix. Data were either numerically simulated, or acquired by actual ultrasonic measurements on samples of interest (TA6V and Ti17 titanium alloys billets, 3 MHz linear probe of 128 transducers). The dataset consists in a Full Matrix Capture, which contains all combinations of A-scans with one probe element firing an ultrasonic wave and all elements receiving the backscattered echoes.

Two estimators are compared. The first one, introduced by Aubry and Derode (PRL, 2009) and rearranged by Baelde & al. (Ultrasonics, 2018) consists in projecting the data matrix onto a theoretical subspace of single scattering. More than just estimating the single scattering proportion by taking the norm of the projection on the subspace basis, this method also enables to isolate single scattering information. The second method, built by Badon & al. (Sci. Adv., 2016), projects the data matrix in a focused basis to extract the local scattering parameters. In this basis, single scattering appears on the main diagonal of the matrix, whereas multiple scattering results in non-diagonal elements.

The results show that in the studied titanium alloys, the single scattering proportion can be as low as 20%: multiple scattering is not negligible and strongly affects the backscattered signals. This conclusion is discussed in relation to the scattering parameters such as the diffusion constant and the scattering mean-free path.

KEYWORDS Ultrasound array imaging | Matrix approach | Multiple scattering |


THU.2.A.4

Presenting author : Angélique Raude - Testia

Co-Authors : Angélique Raude1 | Guillaume Ithurralde1 | Francisco Carrasco1 | 1. Testia

ENSURING COMPLETE INTEGRITY OF AERONAUTIC COMPOSITE PARTS THANKS TO A FULLY AUTOMATED NON-DESTRUCTIVE INSPECTION SOLUTION AND PROCESS

ABSTRACTS Composite materials have widely been developed and used in the Aeronautic industry over the years, thanks to their unique combination of high strength, light weight and durability ensuring an excellent strength to weight ratio compare to other types of material. They can be manufactured in various shapes, forms and compositions, including glass or carbon fibre, fibre-reinforced matrix systems or any combination of any of these. This naturally explain why almost all airplanes incorporate some kind of composite materials in their design. And in some cases, they can account for up to 50 to 70 percent of a complete airplane structure. It is therefore critical to inspect such materials / component to ensure their complete integrity at a manufacturing stage to look for known flaws such as: porosity, delamination, lack of bonding, foreign objects, etc.

The non-destructive inspection of composite components can be challenging due their varying nature and shapes and tedious depending on the chosen technique. The most common technique used is ultrasonic testing. Although this technique is very beneficial, it has some downsides such as: human dependencies, slow manual process, and the area under investigation is limited by the transducer active area. This has now been addressed by the development of a complete automated solution improving both inspection efficiency and reliability.

This paper describes the studies carried out to establish dedicated inspection methods based on conventional and phased array ultrasonic testing, the development of a tailored and fully automated acquisition solution and the creation of a masked analysis process, as well as their deployment. Those tools aim to simplify and speed-up the part integrity diagnosis.

KEYWORDS Ultrasound |Composite | Automation | Processing | Aerospace |


THU.2.A.5

Presenting author : Philippe Dumas - Imasonic

Co-Authors : Philippe Dumas1 | Germain Braillard1 | Arnaud Member1 | Laurent Fournier1 | Stephane Oster1 1. Imasonic

FLEXIBLE WEDGE PHASED ARRAY TRANSDUCERS FOR INSPECTING VARIABLE-GEOMETRY OR COMPLEX COMPONENTS

ABSTRACTS The transmission of ultrasound from the transducer into the inspected component is a determining factor in the performance of ultrasound inspections. Various coupling solutions exist to ensure this transmission. The most frequently used are:

• Immersion of the component in water tank: This coupling presents the best acoustic performance (low attenuation, coupling homogeneity, no intermediate interface). However, the inspected parts need to be fully immersed and thus complex control systems are required.

• Coupling by direct contact with a liquid couplant, or via a rigid wedge or a delay line with liquid couplant at the interfaces: This coupling requires simpler control systems for the inspection, but the homogeneity of the couplant film and attenuation in the wedges deteriorate the signal. The geometry of the inspected part can make the coupling more difficult to setup, particularly if the surface is complex or varies from one point to another. The problem becomes critical when the dimensions of the transducer are large in comparison with the local curvature of the interface. The use of transducers that are flexible, or that are fitted with a flexible wedge, improves the quality of the coupling for components with complex or variable geometry, and in some cases, makes it possible to do certain inspections that currently have no solution.

This article presents the recent developments and results obtained in the context of transducers with flexible wedges, in particular:

• Design options;

• Flexible membranes development;

• Mechanical interfaces development for multi-element transducers;

• Mechanical supports development for manual or automated use;

• Acoustic performance tests;

• Wear resistance tests.

These studies have demonstrated the contribution of flexible wedge transducers to various applications, with acoustic performances similar to that of immersion and easy implementation comparable to standard contact inspections, while remaining compatible with an industrial use. The detailed results will be presented, as well as the possibilities for the future developments of transducers with flexible wedges.


THU.2.B.1

Presenting author : Olivier Mesnil - CEA-List

Co-Authors : Olivier Mesnil1 | Pierre Calmon1 | Bastien Chapuis1 | Roberto Miorelli1 | Xavier Artusi1 | Christophe Reboud1 | Oscar d’Almeida2 1. CEA List / 2. Safran Tech

MODEL ASSISTED PROBABILITY OF DETECTION IN STRUCTURAL HEALTH MONITORING APPLIED TO IMPACTED COMPOSITE STRUCTURES

ABSTRACTS In Guided Wave Structural Health Monitoring (GW-SHM), reliability and performance demonstration is one of the main challenge to overcome to ensure industry adoption. However, the cost of computing a Probability of Detection (POD) from experimental data is much higher in SHM than in NDE due to the permanent integration of sensors. In addition, SHM presents specificities (such as the dependency on environmental and operational conditions, the durability of sensors overt time, the need for complex algorithms in post-processing) which makes especially relevant the use of simulation in the reliability assessment process. A methodology of performance demonstration based on numerical tools and dedicated to GW-SHM is therefore required.

This work proposes the application of the Model Assisted POD (MAPOD) approach on the case of a guided wave imaging technique, which consists of creating an image representing the health of the inspected structure using a sparse grid of ultrasonic transducers. The use of simulation allows studying the response of the system for a large set of possible configurations, accounting for the variability of defect morphology, of transducer performances or environmental conditions. In order to compute the POD for the range of input parameters of interest, a meta-model of the configuration is built from the forward model of the CIVA software.

The illustrative use-case is an aerospace composite panel instrumented by piezoelectric transducers and the studied defect is an impact-like delamination of various size, position and morphology. A dedicated detection criterion is developed for the application and the false alarm rate is studied with Receiving Operating Curves.

KEYWORDS MAPOD | SHM | Guided wave imaging |


THU.2.B.2

Presenting author : Thomas Köhler - Vibrant GmbH

Co-Authors : Thomas Köhler1 | Leanne Jauriqui2 | 1. Vibrant GmbH / 2. Vibrant Corporation

DIGITAL TWIN APPROACH FOR CRITICAL ENGINE COMPONENTS USING PCRT

ABSTRACTS This paper describes ways to apply Process Compensated Resonance Testing (PCRT) to critical engine components to improve quality and to reduce risk using a Digital Twin and Birth Certificate approach.

Over the last few years there have been several high-profile engine blade failures, putting a spotlight on risk management for these critical components.

Current inspections can cover many of these risks, but some conditions are more readily addressed with traditional methods than others. Historically, some of these risks have been handled with destructive “sampling” evaluations or other process control approaches, because there is insufficient linkage to the actual fitness of the component at the time of inspection.

Where visual inspections are perfectly suited judging the appearance of a component, structural information is required to understand the development of a critical part in its life cycle. Component failures are usually caused by abnormal behaviour of an individual component compared to the predicted model. Digital Twin approaches can be used to manage the lifecycle of critical components by generating models of the component. Birth and Life Cycle Certificates using resonant data provide structural information of the real-world component.

PCRT creates birth certificate data using the resonant fingerprint of a component. This fingerprint is unique but follows the variation of the underlying production process. Hence, PCRT fingerprint data is a perfect source to select components based on a Digital Twin model approach. As components age under the stress of the engine operation, the change in the fingerprint data provides a valuable source of identifying components that change in an unusual or unexpected fashion compared to the Digital Twin model. Combining this information with inflight data as well as visual inspection criteria opens new opportunities to reduce risk of critical components and improve safety.

KEYWORDS Digital Twin| Birth Certificate | Big Data | Modelling | Risk Reduction


THU.2.B.3

Presenting author : Vamsi Krishna Rentala - School of Engineering Sciences and Technology, University of Hyderabad, India

Co-Authors : Vamsi Krishna Rentala1 | Phani Mylavarapu2 | Atul Kumar2 | Jai Prakash Gautam1 | B.V.N.Shiva2 | K.Gopinath2 | T.Jayakumar2 | Vikas Kumar2 | 1. School of Engineering Sciences and Technology, University of Hyderabad, India / 2. Defence Metallurgical Research Laboratory, Hyderabad, India

EFFECT OF OXIDE INDUCED MICROSTRUCTURE DEGRADATION IN AERO-ENGINE COMPONENTS ON POD OF NDT TECHNIQUES

ABSTRACTS Successful implementation of damage tolerant (DT) methodology for aero-engines requires estimation of reliability of various NDT techniques. Probability of Detection (POD), being a standard metric for measuring the NDT reliability, is usually established with the help of a large number of service expired aero-engine components containing several fatigue cracks. However, EDM notches or starter cracks generated at room temperature conditions are considered for POD studies in the absence of service expired components with defects. This methodology may or may not consider the effect of crack morphology and the service induced microstructural changes present in a service exposed component. Therefore, considering the POD value generated using such EDM based starter defects for estimating NDT reliability can be unrealistic in nature. For example, eddy current technique is dependent on electrical conductivity of material which is in-turn dependent on oxide induced microstructural degradation and crack morphology. Hence, it is essential to understand the relation between POD of NDT technique and oxide induced microstructure degradation. It is also understood that PODs not all NDT techniques are affected by microstructural variations. Therefore, in the current study, an attempt has been made to understand the effect of service induced oxide cracks in aero-engine components on POD studies. Accordingly, samples with representative geometric stress concentration factor of a typical bolt hole in a turbine disc were prepared from an aero-engine turbine disc. These samples were subjected to high temperature (650oC ~ typical engine service temperatures) fatigue testing with a stress ratio (R) of 0.1 and constant number of fatigue cycles using Gleeble test system. Natural fatigue cracks generated in these samples under laboratory conditions were inspected using fluorescent penetrant and eddy current inspection techniques. This paper discusses the variability associated in the POD or a90/95(flaw detection with 90 % probability and 95 % confidence) values with respect to the oxide induced microstructure degradation. A comparison will be drawn between the POD curves generated using high temperature and room temperature tested samples to understand the effect of oxidation.

KEYWORDS Damage tolerance methodology | oxidation | NDT response variation | POD |


THU.2.B.4

Presenting author : Christophe Reboud - CEA List

Co-Authors : Christophe Reboud1 | Houssam AlRachid1 | Guillaume Damblin1 | Xavier Artusi1 | 1. CEA List

INTEGRATION OF EXPERIMENTAL DATA IN MODEL ASSISTED PROBABILITY OF DETECTION COMPUTATIONS

ABSTRACTS Probability of detection (POD) is a recognized performance indicator of non-destructive methods in various industrial fields, like Aeronautics or Energy. It consists in calculating the probability to detect a flaw in a specimen according to a characteristic parameter, usually linked to its size. To access this curve experimentally, one needs to establish a design of experiment (DoE) covering a certain range of random effects that may affect the specimen.

To be pertinent, this DoE typically involves a quite large number of mock-ups and repeated inspections with different operators, which makes the complete process costly and time consuming. In recent years, the use of simulation has emerged to improve the calculation of PoD curves. This is known as Model-assisted Probability of Detection (MaPoD). The advantages of simulation is its competiveness in terms of cost and speed with respect to experimental approach, as well as its ability to investigate wider ranges of parameters (either characteristic or uncertain) and to produce large datasets that are statistically representative. The main problem with MaPoD in general is its arbitrary description of uncertainty, which has of course a great impact on the calculated POD and relies currently mainly on experts judgments. While some laws of these parameters are well characterized and easily accessible (for example in datasheets), others are more difficult to quantify (human factors). In this work, we propose to enhance and evaluate performance of a Bayesian Inversion implementation to infer the laws of uncertain parameters based on integration of information coming from real experiments.

This methodology is evaluated on two use cases. The first one is purely numeric and allows us to access the limit of the method in terms of precision and data requirement to converge to the solution. The second one is experimental and consists in an inspection with an ultrasonic sensor of a planar specimen affected by calibrated defects. We monitor in real time the sensor position parameters (that are uncertain parameters in the context of a manual inspection) thanks to an optical tracking tool. With this system, we have access to the true distribution of uncertain parameters and we can validate the approach experimentally.

KEYWORDS Probability of Detection | Uncertainty Quantification | Bayesian Inversion | Ultrasound |


THU.2.B.5

Presenting author : Aadhik Asokkumar - Dresden International University (DIU), Dresden/Germany

Co-Authors : Aadhik Asokkumar1 | Ramanan Sridaran Venkat2 | Christian Boller2 1. Dresden International University (DIU), Dresden, Germany / 2. Saarland University, Saarbrücken, Germany

IDENTIFICATION OF KEY PERFORMANCE INDICATORS FOR SHM IN STRUCTURES OF INCREASING COMPLEXITY BASED ON ARTIFICIAL NEURAL NETWORKS

ABSTRACTS Lamb wave based technology being one of the advanced approaches in the field of ultrasonics, is being widely considered to perform Structural Health Monitoring (SHM) in damage tolerant aeronautical structures. Damage tolerance is a concept in which damage up to a tolerable size is allowed to exist in structural components before those components will have to be repaired. To get such damages detected reliably, an automated inspection process based on SHM technology is considerable. However, it is important to know at what features such SHM technology needs to look at such that the appropriate key performance indicators (KPI) can be well identified. Such an identification may be best done through numerical simulation which is the purpose of the paper being proposed here. Referring to guided ultrasonic waves and here specifically to Lamb waves different modes being sensitive to the tolerable damages defined have to be identified such as the S0 mode for through thickness cracks and possibly others for further types of damage.

To optimize the quality of the Lamb wave modes generated in the first place, two actuators have been placed opposite to each other on the top and the bottom of the plate like structure considered. Changes in the plate geometry such as thickness have been detected through a mode conversion and the dispersive effect of the mode considered i.e. the S0 mode. In this paper the approach on how to determine the input features for an artificial neural network (ANN) will be described on a numerical basis as well as the resulting KPIs obtained through the ANN. At first, the concept is explained using a plate with five holes from which cracks emanate and will be finally explained for a riveted patched repair such as widely used in aeronautical structures.

KEYWORDS Lamb waves | Artificial Neural Networks | Structural Health Monitoring | Damage tolerant design | Key Performance Indicators |


THU.2.C.1

Presenting author : Muzibur Khan - National Research Council Canada

Co-Authors : Muzibur Khan1 | Trent Gillis1 | Mike Brothers1 1. National Research Council Canada

COMPUTED RADIOGRAPHY FOR HIGH RESOLUTION IMAGING APPLICATIONS OF AIRCRAFT STRUCTURES

ABSTRACTS Industrial radiography provides high throughput in non-destructive inspection particularly for aircraft structural components and therefore an important tool for aircraft maintenance. Film-based radiography requires consumables (films, toxic chemicals and proper disposal of chemical waste), darkroom facility and manual processing which is not only time consuming, but also requires more radiation exposure than digital systems. The industrial radiography community is making an intense effort to replace the conventional film technique with digital technologies such as digital radiography and computed radiography (CR). The CR technology uses a reusable phosphor imaging plate instead of a film, and therefore allows faster/easier digital image acquisition. Moreover, CR has advantage over conventional film as wider dynamic range, higher sensitive to radiation, requires lower radiation dose and shorter exposure times.

CR imaging performance for general applications such as water ingress, composite honeycomb structures, and foreign object damage in aircraft structures is similar to that of film radiography. However, CR imaging for high resolution requirement applications such detecting fatigue cracks or weld defects is much more challenging; making it difficult to match the detection limit obtain by film. Performance assessment of the CR technology is required to determine if it can effectively provide equal or better performance than the existing film-based technology for high resolution applications, and to provide satisfactory and repeatable inspection results

This paper highlights the CR performance metrics, lessons learned and key issues faced while performing experimental validation of CR imaging for detecting fatigue cracks in aircraft structural components. CR system quality parameters such as spatial resolution, contrast sensitivity, contrast-to-noise ratio (CNR), signal-to-noise ratio (SNR), equivalent penetrameter sensitivity (EPS) as well as other system hardware integrity features were evaluated as part of an assessment of CR suitability for aerospace applications.

KEYWORDS Non Destructive Testing | Computed Radiography | Industrial Radiography | Inspection Qualification |


THU.2.C.2

Presenting author : Cécilia Tarpau - Equipes de Traitement de l’Information et Systèmes (ETIS) / Laboratoire de Physique Théorique et Modélisation (LPTM) / Laboratoire de Mathématiques de Versailles (LMV), France

Co-Authors : Cécilia Tarpau1 | Javier Cebeiro2 | Mai K. Nguyen-Verger1

1. Equipes de Traitement de l’Information et Systèmes (ETIS) / Laboratoire de Physique Théorique et Modélisation (LPTM) / Laboratoire de Mathématiques de Versailles (LMV), France 2. Centro de Matematica Aplicada (CEDEMA) A NEW BI-IMAGING NDT SYSTEM FOR SIMULTANEOUS RECOVERY OF ATTENUATION AND ELECTRONIC

DENSITY MAPS

ABSTRACTS Computed Tomography (CT) is a widely used imaging technique for non-destructive testing and evaluation (NDTE) in industry. CT modalities exploit only primary radiation, which is un-deviated but attenuated radiation going through matter. However, in the energy range of X and gamma rays used in NDTE, Compton effect is an important physical phenomenon which should be taken into account. Compton Scattering Tomography (CST) is precisely the imaging technique, which not only accounts for the Compton effect but uses it to image material electronic density. Compton scattering tomography is appropriate for metal objects and yields higher contrast images as compared to computed tomography.

This paper proposes the concept of a CST scanner, which is formed by a source and several detectors placed on a circular ring. When the detectors are set to register the energy of primary photons, the system works as Fan-Beam Computed Tomography (FBCT) scanner. But if the detectors are set to register the energy of scattered photons, the system operates as Compton Scattering Tomography scanner. Thus such a device, which provides both attenuation map (by the fan-beam tomography mode) and electronic density (by the Compton scatter tomography mode) of an object, is called a bi-imaging tomographic system. Both information from primary and scattered rays is then wisely exploited.

The mathematical modelling of this system makes use of a Radon transform on circular arcs, a generalization of the classical Radon transform (on straight lines).

Numerical simulations are carried out in order to show the theoretical feasibility of the proposed system.

KEYWORDS Fan-Beam Computed Tomography (FBCT) | Compton Scattering Tomography | Bi-imaging | Electronic density | Attenuation map |


THU.2.C.3

Presenting author : Jens Hansen - Carl Zeiss IMT GmbH

Co-Authors : Martin Krenkel1 | Peter Katuch1 | Marco Erler1 | Stratis Tzoumas1 | Christoph Kuhn1 1. Carl Zeiss IMT GmbH

X-RAY SCATTER REMOVAL FOR ARTIFACT FREE CT IMAGING

ABSTRACTS In the past decades, industrial computed tomography (CT) has become a powerful tool for the nondestructive, three-dimensional (3D) examination of intricate parts and their inner structures. In particular the possibility to inspect parts for inner defects allows a much better understanding of manufacturing processes and thus paves the way for systematic tuning of process parameters, for example in the field of additive manufacturing of aerospace components. However, the necessary x-ray energies to allow inspection of high density materials required in these applications come with the drawback that the interaction probability of scattering processes become more likely, which poses a limit to the resulting 3D image quality. Scattered radiation leads to a non-linear image formation resulting in image artifacts like streaking or cupping. In the worst case, these artifacts may limit defect recognition possibilities due to a mix of the actual defect signal and scattered radiation or it may inhibit further evaluation of the measured data as the resulting 3D image quality is not sufficient for, e.g., a high quality surface determination.

In this paper we present a method to compensate for scattered radiation artifacts. Using a newly developed workflow to determine the scattered radiation, scatter artifacts can be dramatically reduced to a level, where further evaluation of the data becomes possible with state-of-the-art algorithms. The method intrinsically corrects for all kinds of scatter problems that may occur in a CT system including scattering inside the object. We will demonstrate the approach for the inspection of turbine blades and large aluminum castings. We will show that using this method an image quality can be achieved, which is otherwise only available using fan-beam tomography with line detectors. In comparison to line detector based fan-beam CT we show the great potential of time reduction to allow high quality scans in minutes instead of hours.

KEYWORDS X-Ray | Computed Tomography | Artifact Correction | Scatter Removal |


THU.2.C.4

Presenting author : Dominik Martinsen - YXLON International GmbH

Co-Authors : Dominik Martinsen1 | Patrick De Soete1 1. YXLON International GmbH

COMPUTED TOMOGRAPHY IN NDT AND METROLOGY FOR ADDITIVELY MANUFACTURED AEROSPACE COMPONENTS

ABSTRACTS Additive Manufacturing (AM) is becoming an increasingly important production technique also for safety critical aerospace parts. Often these parts are very complex and require new methods of testing to assure their structural health and integrity. Furthermore it is often important to verify certain wall thicknesses or for example the inner diameter of a turbine blade’s cooling channel.

The Computed Tomography (CT) allows both detecting the mentioned anomalies and carrying out dimensional measurements. Since the CT data represent the full 3D volume of the parts, the analysis covers not only the outer surface, but the complete part including the inner structures. However, due to the many different scan parameters it is often difficult to define he right inspection parameters.

At first a sophisticated method will be presented that helps the operator to determine the optimum parameter set, which suits the part material(s) and geometry, the required test specification as well as the side conditions of the available X-ray system.

Secondly, we will describe how to adjust the inspection strategies in order to adapt to the very specific requirements of the aircraft industry. Since DR standards as the ASTM E 2737 are still missing their equivalent for CT inspection, we will present a method that helps to determine both qualitatively and quantitatively the inspection quality of the CT scans.

KEYWORDS Computed Tomography (CT) | Metrology | NDT | Additive Manufacturing (AM) |


THU.2.C.5

Presenting author : Carlos Galleguillos - FADA-CATEC

Co-Authors : Carlos Galleguillos1 | Antonio Periñan1 | Javier Santaolaya1 | Sergio González1 | Fernando Lasagni1 1. FADA-CATEC

COMPUTED TOMOGRAPHY AND DIGITAL RADIOGRAPHY FOR ADDITIVE MANUFACTURING PROCESS QUALITY ASSURANCE AND PARAMETERS DEFINITION

ABSTRACTS The demand of metallic parts produced by Additive Manufacturing (AM) is continuously growing in aerospace industry. X-Ray Computed Tomography (CT) has been stablished as preferable Non Destructive Testing (NDT) method for validating flight components. This technique shows as the most reliable solution for the inspection of complex geometries (e.g. topology optimized parts, lattice structures, etc.) for both the analysis of dimensional accuracy and verifying the internal condition of the fuse material and its indications/defects (voids, cracks, lack of fusion, inclusions, etc.).

On the other hand, validation of flight components by Computed Tomography use to be performed in the final stage of the manufacturing route which involve different sub-processes such as part extraction of the building plate, heat treatments, interface machining, surface post-processing, etc. In this context, Non-destructive testing based on Digital Radiography just after part fabrication could help to detect not acceptable indications in an early stage, avoiding costs related with post processing in a not valid component.

This work presents results of detection of non-acceptable indications on an early stage of the manufacturing route using industrial radiography. Tests are performed in both, control samples and components with different geometries. Even more, inspection results of samples with induced defects (typical from metal additive manufacturing processes) are presented for helping in the evaluation of the indications Also, CT results are studied as input of the process regarding raw material inclusions analysis, settings of the manufacturing parameters, development of controlled porosity and dimensional deviation analysis related with thermal shrinking during the manufacturing stage.

KEYWORDS Computed Tomography, | Aerospace | Additive Manufacturing | Digital Radiography |


THU.3.A.1

Presenting author : J. Mrowka - AGH University of Science and Technology

Co-Authors : J. Mrowka1 | K. Dziedziech1 | F. Aymerich2 | L. Pieczonka1 | L. Ambrozinski1 1. AGH University of Science and Technology / 2. Università di Cagliari

IMAGING OF IMPACT DAMAGE IN STITCHED CARBON-FIBER REINFORCED PLASTIC COMPOSITES USING LASER ULTRASONIC TECHNIQUE

ABSTRACTS Composite materials become increasingly common in a wide range aerospace structures. In these applications carbon-fiber renforced plastics (CFRP) offer numerous advantages over metals due to their flexibility in design and superior stiffness to mass ratio. The main disadvantage of these materials, however, is their sensitivity to incur impact damage, which may be difficult to detect. Their resistance to damage can be, however, improved by stitching the fabric in the manufacturing process with high-strength fibrous yarns such as Kevlar, polyethylene or glass fibers. The stitches increase interlaminar shear strength and reduce delamination progression. The stitching causes, however, additional issues for non-destructive evaluation, particularly for ultrasonic methods. Because of the difference in wave velocity between the stitching fibers and the surrounding material, the phase-distorted wave front is obtained. The reflected wave is integrated within the transducer aperture and reduces signal amplitude.

Laser ultrasound (LUS)offers ultra-wideband of generated signals and allows for sub-ply imaging resolution. Moreover, it features very small footprint area of both the ransmitter and the receiver not achievable for other ultrasonic techniqes. In some cases LUS can nearly reach the imaging quality of the X-ray computed tomography. In this paper, we utilize the superior properties of LUS for imaging of Kevlar stitched CFRPs using laser ultrasound technique. In the experiment the diameter of the pulsed laser spot was approx. 1 mm and point-like receiver of diameter approx. 10 um was used. Both laser beams were aligned to perform a non-contact pulse-echo scanning of the samples. Two sets of samples impacted with various energy levels were investigated and damage severity was compared. For comparison, the X-ray images were used as a reference data.

KEYWORDS CFRP | Stitching | Non-contact | LUS |


THU.3.A.2

Presenting author : Ribay Guillemette - CEA List

Co-Authors : Ribay Guillemette1 | Jumel Julien2 | Zabbal Paul1 1. CEA List / 2. Univ. Bordeaux, CNRS, Bordeaux INP, Arts et métiers Paris Tech, I2M

EVALUATION OF METALLIC BONDED PLATES WITH NONLINEAR ULTRASOUND AND COMPARISON WITH DESTRUCTIVE TESTING

ABSTRACTS In the last decades, the use of structural adhesion has increased. It is indeed able to replace traditional bonded techniques such as rivets or bolts, and reduces the global weight of the structure, which is of great interest in the aeronautic industry. In addition, it allows the assembly of mixed or composite materials with better stress repartition. However, to be used for structural joining and critical application, reliable non-destructive testing techniques are compulsory for evident safety reasons, be it after fabrication or during the whole life of the structure.

While linear ultrasound is known to detect easily decohesion or voids in a structure, its use for bond strength inspection is less straightforward. Constraining hypothesis have to be made to retrieve the bond strength [1]. However, in some cases, the effect of such bond degradation on ultrasound is the same as the effect of geometrical fluctuations of the structure (eg thickness of various layers)[2]. Another approach relies on the nonlinear signature of a bond defect inspected by high amplitude ultrasound [3], generated with a chaotic cavity transducer [4]. In the present paper, this method is applied to the inspection of various metallic bonded plates (titanium or aluminum) with several bond defects. The defects were introduced by degradation of the surface preparation process (introduction of PTFE spray, or finger prints). Combined with the pulse inversion technique, high amplitude plane waves were sent in the structure, leading to harmonic components observed in the defect region. Mechanical destructive tests were performed and display a good agreement with nondestructive tests.

References:

1. E. Siryabe, M.Rénier, A. Meziane, J.Galy & M. Castaings. (2017). Apparent anisotropy of adhesive bonds with weak adhesion and non-destructive evaluation of interfacial properties. Ultrasonics, 79, 34-51.

2. P. Zabbal, these de doctorat, November 2018

3. P. Zabbal, Nonlinear ultrasound for nondestructive evaluation of adhesive joints, QNDE 2018

4. O. Bou Matar, O., Li, Y. F., & K. Van Den Abeele, (2009). On the use of a chaotic cavity transducer in nonlinear elastic imaging. Applied physics letters, 95(14), 141913.

KEYWORDS Nonlinear Ultrasound | Bonded joint |

November 13 to 15, 2019100

THU.3.A.3

Presenting author : Lukasz Ambrozinski - AGH University of Science and Technology in Kraków

Co-Authors : Jakub Spytek1 | Aleksandra Ziaja1 | Kajetan Dziedziech1 | Jakub Mrówka1 | Łukasz Pieczonka1 | Łukasz Ambroziński 1. AGH University of Science and Technology in Kraków

NON-CONTACT DETECTION OF DISBONDS IN ADHESIVELY BONDED METALLIC PLATES USING LASER-EXCITED ZERO GROUP VELOCITY LAMB MODES

ABSTRACTS The multi-layered composite components are broadly used in advanced engineering structures, especially in the aerospace industry. Adhesively bonded plates are one of the more interesting types of structures due to their high strength to weight ratio and inherent vibroacoustic damping properties. Unfortunately, they are also prone to delamination defects occurring during the manufacturing process or during the service period. One of the more effective ultrasonic solutions developed for investigating the quality of bonding in such structures is the Zero Group Velocity (ZGV) spectroscopy. The ZGV modes are the specific form of Lamb waves, which become trapped near the excitation region and do not propagate, which results in a local resonance at the frequency characteristic to a given plate. It has been demonstrated, that the frequency of the ZGV mode is very sensitive to the changes of the plate thickness and material properties. This phenomenon is also observed in multi-layered plates, in which even the slight deterioration of the bonding layer may lead to noticeable shift in the local ZGV frequency.

Here, we present a non-contact scanning system for non-destructive inspection of multi-layered aluminium plates based on the ZGV frequency measurement. The setup comprises two laser sources – the excitation diode pulse laser and the measuring laser interferometer, which are spatially superimposed on the same spot. The resulting broadband excitation coupled with high-precision measurement allows the detection of the ZGV frequencies in the megahertz range. The investigated sample is placed on the automated XY translation stage to enable fast scanning of the inspected surface. Analysis of the local frequency spectrum for each measurement point results in a two dimensional image revealing defects. Detailed theoretical analysis of the ZGV frequencies allows for precise identification of the delaminated interfaces.

KEYWORDS ZGV | NDT | LUS |

November 13 to 15, 2019101

THU.3.A.4

Presenting author : Peilong Yuan - Katholieke Universiteit Leuven

Co-Authors : Peilong Yuan1 | Lisha Huo1 | Tommaso Seresini1 | Yang Liu1 | Sevilia Sunetchiieva1 | Helge Pfeiffer1 | Martine Wever1 | Christ Glorieux1 | 1. Katholieke Universiteit Leuven

NONCONTACT LASER-BASED ULTRASONIC DETECTION OF DYNAMIC STRESS MODULATED CRACKS

ABSTRACTS Laser ultrasonic generation and detection of guided acoustic waves is an attractive non-contact technique for non-destructive testing, which exploits the sensitivity of the wave propagation to the presence of defects that act as scattering heterogeneities. Remote inspection by laser ultrasonic is an important asset, especially when the object of interest is in rotational or translational motion. This study presented exploits the variability of the interaction of a crack defect with probing waves, which results from dynamical stress opening and closing the crack, and can be detected by the accompanying modulation of the detected reflected, transmitted and mode converted waves.

The proposed NDT concept is illustrated on a component undergoing cyclic stress during a fatigue treatment. Laser pulses are used to photoacoustically generate wave packets at a high repetition rate. Detection is done by laser Doppler vibrometry. The correlation between the envelope, arrival time, spectrum and other detected wave characteristics at different instants of the dynamic load cycles on one hand, and the state of the growing crack, on the other hand, are analyzed. The results demonstrate the potential of laser-based ultrasonic inspection for simple and rapid detection of fatigue cracks open and closed under dynamic stress.

KEYWORDS Laser-based ultrasonic | Open and closed cracks | Non-destructive testing method | Dynamic load |

November 13 to 15, 2019102

THU.3.A.5

Presenting author : Bengisu Yilmaz – Ultrasound Research Institute, Kaunas University of Technology

INNOVATIVE ULTRASONIC NONDESTRUCTIVE TESTING TECHNIQUE FOR BONDING QUALITY EVALUATION

ABSTRACTS In the aerospace industry, high-performance engineering materials such as aluminium and composites are widely used. In order to maintain the advantages of these materials and to preserve the flexibility in design and maintenance, the choice of joining technology plays an important role. Among different joining techniques, adhesive bonding is one of the most suitable candidates with homogenous load distribution, the ability to join dissimilar materials and high performance to weight ratio. Due to lack of knowledge in the quality control of adhesive bonding with non-destructive testing, they are only allowed to be used in secondary load carrier structures. The state of the art non-destructive testing techniques such as ultrasonic inspection is able to identify debonding at the interface, delamination, and some inclusions.

Even though defect identification in adhesive joints has been studied broadly, the reliability in the NDT of adhesive bonding remains questionable due to variations during manufacturing and consolidation. Such contaminations may lead to a dramatic decrease in quality, and in some cases to weak bond. This study offers a new methodology with a conventional immersion ultrasonic testing system in order to evaluate bonding quality. In this study two different substrate containing weak bonds have manufactured with release agent contamination: aluminium – epoxy – aluminium and carbon fibre reinforced epoxy -epoxy-carbon fibre reinforced epoxy.

The study investigates the shear wave propagation through weak and perfect adhesive bonds and compares them quantitatively according to received ultrasonic signal shape and amplitude. The study emphasizes new parameters related to behind weak bonds with innovative NDT methodology in immersion testing. During tests, the transmitter sensor stays stable while the sample is rotated and the receiver transducer moves along the direction of propagation respectively. On contrary to classical pulse-echo ultrasonic investigations where only interface condition is evaluated, the received signals contain the information from the whole bonding zone. The quantitative analysis of the weak bond for both aluminium and composite adhesive joints have been reported.

November 13 to 15, 2019103

THU.3.B.1

Presenting author : Emmanuel Siryabe - Safran Helicopter Engines

Co-Authors : Emmanuel Siryabe1 | Etienne Juliac1 | André Barthe1 | Cyrille Ferdinand1 1. Safran Helicopter Engines

X-RAY DIGITAL RADIOLOGY TO INFER WELDING DEFECTS DEPTH

ABSTRACTS X-ray digital radiology is increasingly used in aerospace industries and medical applications because of their numerous advantages such as the non-use of consumables and chemicals products, the capability to storing information via digital media, the reduction of time of control, etc. Today, the use of X-ray digital radiology give news needs and challenges for industrials. In this paper, X- ray digital radiology is used to infer welding defects such as depth of collapse or undercut, in welded assemblies, by measuring the grey level difference. Two batches of representatives samples are tested according to different composition: the first one is HA188 and the second HA230. Comparing depths of collapse measured by X-ray technique with those obtained by laser profilometer and micrographics cuts, we observe a good agreement, in the range of 30 - 250 µm. This results demonstrate the capability of X-ray non-destructive technique to estimate the “depth of collapse” in representative samples. Further investigations will be applied on real parts and results will be presented in a new paper.

KEYWORDS X-Ray digital radiology | Welded assemblies | Depth of collapse |

November 13 to 15, 2019104

THU.3.B.2

Presenting author : Toshiyuki Takagi - Institute of Fluid Science, Tohoku University, and ELyTMaX Université de Lyon

Co-Authors : Toshiyuki Takagi1,2 | Hongjun Sun1 | Hiroyuki Kosukegawa1 | Mitsuo Hashimoto1

1. Institute of Fluid Science, Tohoku University / 2. ELyTMaX UMI 3757 CNRS-Université de Lyon- Tohoku University, International Joint Unit

ELECTROMAGNETIC PULSE-INDUCED ACOUSTIC TESTING AND ITS APPLICATION TO THE NON-DESTRUCTIVE EVALUATION OF ADHESIVE BONDING BETWEEN CARBON FIBER COMPOSITE AND

METAL

ABSTRACTS Composite materials are used in aerospace industries to replace metals and to reduce the structural weight. Some new aircraft, such as Boeing 787 and Airbus A350, use composite materials in more than half of their structures. However, it is evident that composite materials cannot wholly replace metals under the current condition. Therefore, the adhesive bonding between metal and composite material is adopted as one of the methods that satisfy the above demands. However, with the increase in usage time, debonding phenomena may occur at the bonding part. Non-destructive testing for the inspection of metal/composite adhesive bonding is required to ensure the safety of the structure. The authors propose the electromagnetic pulse-induced acoustic testing (EPAT) method for non-destructive testing of adhesive bonding between metals and composite materials.

In this paper, we introduce the principle of EPAT. A pulsed magnetic field (from the driving coil) excites metal material and generates an acoustic sound, and defects in adhesive joints are inspected by measuring and analyzing the acoustic signal obtained from composite materials side. Acoustic emission (AE) sensors measure the acoustic sound. Because the debonding brings changes in vibration propagation time and frequency, the presence and location of the debonding can be determined by analyzing the received acoustic signals at various locations. Two adhesive bonding specimens of metal and carbon fiber reinforced plastics (one with debonding and one without debonding) are used in EPAT experiments. Two sets of received signals are compared. Also, a finite element simulation is used to elucidate the mechanism of the method.

KEYWORDSElectromagnetic pulse-induced acoustic testing | Carbon fiber composite | Acoustic sound | Non-Destructive Testing | Adhesive bonding |

November 13 to 15, 2019105

THU.3.B.3

Presenting author : Clément Skopinski - Framatome Intercontrôle

Co-Authors : Clément Skopinski1 | Matthieu Taglione1 | 1. Framatome Intercontrôle

SURFACE CHARACTERIZATION USING MULTI-ORIENTATION LIGHT TECHNIQUE

ABSTRACTS Framatome Intercontrôle has developed a solution that improves visual inspections, in terms of inspection duration and/or indications characterization. This presentation will focus on the Helios technology, which uses multiple light orientations to determine the reflectance equation at any point of the surface.

The analysis of the reflectance coefficients allows to apply quantitative detection criteria and then objectively discriminate surface indications as scratches, cracks, porosities, rugosity, ...

A 3D mapping of the surface indications is also possible with a data processing of the reflectance map of the surface that allows to size the indications in the 3 x-Y-Z directions. This technology is scalable and could be apply to small scale and large scale parts.

In this presentation, the technology will be presented illustrated with different experimental results on different applications.

KEYWORDS Visual Testing | Quality | Helios | Lightning |

November 13 to 15, 2019106

THU.3.B.4

Presenting author : Abdoulaye Ba - Nantes University

Co-Authors : Abdoulaye Ba1, Huu-Kien Bui1, Gérard Berthiau1, Qiuji Yi2, Junzhen Zhu², Gui Yun Tian2

1. Institute of Research in Electrical Energy of Nantes-Atlantiques (IREENA), University of Nantes 2. School of Engineering, Newcastle University

EDDY-CURRENT PULSED THERMOGRAPHY FOR THE DETECTION OF IMPACTDAMAGE ON CFRP

ABSTRACTS Carbon Fiber Reinforced Polymer (CFRP) materials are widely used in aerospace due to their low weight and high strength. Non-destructive Testing (NDT) Techniques become a necessity with increasing use of CFRP materials. Induction Thermography is a new NDT technique that can be exploited as a promising fast and global control. However, the detection of typical flaws in carbon composites such as delamination, fibers rupture and impact damages need to be further investigated in order to optimize the technique. Optimization can be done in the test configuration level and by the use an appropriate image processing technique. In this paper Eddy Current Pulse Compression Thermography (ECPuCT) is used to detect impact damages on CFRP materials. The Principal Component Analysis (PCA) based image processing technique is used to detect and visualize impact damage area from transient thermal images. Flaw detection results using experimental measures will be shown and discussed.

November 13 to 15, 2019107

THU.3.C.2

Presenting author : Roberto Miorelli - CEA List

Co-Authors : Damien Segur1 | Xavier Artusi1 | Pierre Calmon1 | Silvère Barut2 | 1. CEA List / 2. Airbus

DEVELOPMENT OF DEDICATED CLASSIFICATION TOOLS FOR THE AUTOMATED DIAGNOSTIC FROM NON-DESTRUCTIVE TESTING DATA

ABSTRACTS An important problematic in the field of non-destructive testing is the management of large datasets of inspection data and their efficient exploitation to monitor the life of various structures and components. A collaboration between CEA LIST and Airbus has led to the development of dedicated classification algorithms. The application case proposed by Airbus was addressed in the context of the CORAC [1] project INNOFAB. Airbus group collects, with its software NDTKIT [2], data coming from inspections of airfoil stiffeners made of composite material. These experimental databases contain quantitative indicators extracted from ultrasonic testing signals and a set of tags affected to the measurement by technical experts, in particular the category of damage. The volume of inspection of those structures is typically 60 per year, each one being equipped with 18 stiffeners. An unsupervised classifier has been designed and trained to attribute to input data a class of damage among a set of four classes (layer porosity, volume porosity, gap between tows and irrelevant indications). Specific treatments applied to the database, like dimensionality reduction and handling of over/under-representation of classes will be described, as well as results obtained in terms of performance on experimental datasets. In terms of perspectives, this work demonstrates the potential of learning by example techniques to assist the experts and provide automated diagnostic.

KEYWORDS Classification | Database | Dimension Reduction | Machine learning |

November 13 to 15, 2019108

THU.3.C.3

Presenting author : Roberto Miorelli - CEA List

Co-Authors : Roberto Miorelli1 | Clément Fischer1 | Andrii Kulakovskyi12 | Olivier Mesnil1 | Bastien Chapuis1 | Oscar d’Almeida2 | Alain Lhémery1 1. CEA-List / 2. Safran Tech

DEFECT SIZING IN GUIDED WAVE IMAGING USING A CONVOLUTIONAL NEURAL NETWORK

ABSTRACTS In Guided Wave (GW) Structural Health Monitoring (SHM), a sparse array of ultrasonic sensors, usually piezoelectric transducers, are permanently integrated on the inspected structure to periodically investigate its health. Among the set of post-processing techniques to analyze such measurements, Guided Wave Imaging (GWI) is a promising approach as it allows immediate defect detection and localization. With a large number of sensors and tomographic algorithms, GWI can provide quantitative information on the defect size. However, with a limited number of sensors, inversion of the defect size from the imaging algorithm is a non-linear problem depending on many parameters, including the defect size and position, the frequency of inspection and the positions of the sensors.

In this work, a deep learning strategy is implemented to invert the size of defects based on GWI with a sparse array of transducers. A database of guided wave images is first built with the simulation software CIVA for various defect positions and sizes. The database is then used to train a Convolutional Neural Network (CNN) to learn an inversion model. A CNN is a type of neural network relying on successive convolution-like operations applied to images, and is usually used in classification problems. The constructed model is then used to invert the size of defects on experimental images.

This methodology is applied on an aluminum panel with a circular through-hole of various positions and diameters, due to the simplicity of creating such experimental samples. Successful inversion of experimental defects is conducted with the numerically trained model. The defect size is inverted with an accuracy of the order of the millimeter for defect in the range of 5 to 15 mm with an inspection frequency at 40 kHz.

KEYWORDSSHM | Guided wave imaging | Inversion | Neural networks |

November 13 to 15, 2019109

THU.3.C.5

Presenting author : Abd Ennour Bouzenad - Institut de Soudure / Laboratoire d’Acoustique de l’Université du Mans

Co-Authors : Abd Ennour Bouzenad12 | Slah Yaacoubi1 | Sylvie Bittendiebel1 | Bruno Grzeskowiak1 | Mourad Bentahar2 | Silvio Montresor2

1. Institut de Soudure / 2. Laboratoire d’Acoustique de l’Université du Mans

ON THE IMPROVEMENT OF HEIGHT INDICATION MEASUREMENT IN WELDS

ABSTRACTS Phased Array Ultrasonic Testing (PAUT) is one of the most mature Non-Destructive Testing (NDT) imaging techniques in industrial activities. As all ultrasonic-based techniques, one of its main advantages over other NDT imaging techniques lies on its detection capability deep within materials. However, PAUT is subjected to beam spreading phenomenon within materials under test, which introduces an overestimation of the height and length of an indication during the sizing operation. In some applications, such as fatigue tests, this overestimation can severely impact the conclusion of a study. In this contribution, a two-step algorithm is proposed in order to automatically measure the indication height in weld-beads. This is performed by considering sectorial scanning images (S-Scan) and applying a correction method to get closer to the existing height. The first step includes the measurement of beam spread in PAUT data collected on a calibration block in the same environmental conditions and using the same probe, wedge and acquisition chain. The second step aims at detecting an indication and measuring its height. The indication’s height is then corrected by considering the beam spread of the different focal laws and the indication depth as well. To validate the present algorithm, two PAUT databases collected on carbon steel welded samples containing several types of real and artificial welding defects were used to quantify the sizing error in correlation with the type of defects. In addition, the comparison is also performed between the proposed algorithm height sizing and the human interpretation of conventional phased array ultrasonic images.

KEYWORDSPAUT | Automation | Height size | Beam spread | Weld-beads |

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November 13 to 15, 2019112

FRI.1.A.1

Presenting author : Hamdi Ben Abdallah - IMT Mines Albi/Institut Clément Ader (ICA) + DIOTA

Co-Authors : Hamdi Ben Abdallah123 | Jean-José Orteu12 | Igor Jovancevic3 | Benoît Dolives3 | Ludovic Brèthes3 1. IMT Mines Albi / 2. Institut Clément Ader (ICA) / 3. DIOTA

AUTOMATIC INSPECTION OF AERONAUTICAL MECHANICAL ASSEMBLIES USING 2D AND 3D COMPUTER VISION

ABSTRACTS Quality control is of key importance in the aerospace industry.

This paper deals with the automatic inspection of mechanical aeronautical assemblies. For that purpose, we have developed a computer-vision-based system made of a robot equipped with several 2D cameras and a 3D scanner.

The 3D CAD model of the mechanical assembly is available. It is used as a reference and it describes the assembly as it should be. The objective is to verify that the mechanical assembly conforms with the CAD model.

Several types of inspection are required.

For instance, we must check that the needed elements of the assembly are present, and that they have been mounted in the correct position. For this kind of inspection we use the 2D cameras and we have developed inspection solutions based on 2D image analysis.

We have found that some types of inspection cannot be performed by using only 2D image analysis. A typical example of such types is the interference between elements. It requires to check if two flexible elements (e.g. cables, harnesses) or a flexible and a rigid element (e.g. pipe, support) are at a safe distance from each other. For this type of situations, we use the 3D data provided by the 3D scanner and we have developed inspection solutions based on 3D point cloud analysis.

We have also developed a method to compute the best viewpoints for the sensor held by the robot, in order that an optimal view of each component to be inspected can be obtained. The view-point selection is performed off-line (before the on-line inspection) and it exploits the CAD model of the mechanical assembly.

The proposed automatic robotized computer-vision-based inspection system has been validated in the context of industrial applications.

KEYWORDS Robotized Inspection | Manufacturing | Maintenance | Cad Model | 2D Images And 3D Point Clouds |

November 13 to 15, 2019113

FRI.1.A.2

Presenting author : Mr Thomas Gramberger - Fill Gesellschaft m.b.H

Co-Authors : Mr Thomas Gramberger1 | Mr Wolfgang Haase1 | Mr Yash Khandhia2 1. Fill Gesellschaft m.b.H / 2. Applied Computing & Engineering Ltd

ACCURATE & FLEXIBLE SOLUTION FOR NON DESTRUCTIVE TESTING IN AEROSPACE INDUSTRY USING ROBOTISED SYSTEM

ABSTRACTS An ever increasing demand for reducing cost of air travel, rising cost of fuel & environmental constraints has driven the need to further reduce weight of aircrafts & improve performance. Carbon Fibre Composite offers an effective high strength low weight solution. The challenge in using carbon fibre composite for aircraft structures is to ensure that there are no manufacturing defects in the material. Unlike aluminium, composite parts do not “dint” or bend when damaged & detecting defects, especially internal to surfaces become difficult. NDT methods of which several are available become an essential approach.

Each method has specific benefits and disadvantages. Today Ultrasonic testing (UT) methods are becoming more popular since they are flexible and relatively easy to implement in production environments. Any selected inspection system needs to be accurate and fast thereby ruling out the use of manually operated scanning devices for large parts. Traditionally, in aerospace industry use of linear kinematics machines was a standard approach for UT systems for Through Transmission or Pulse Echo inspection due to achievable accuracy of positioning required for true inspection paths. Particularly for Through Transmission (TTU) using a Squirter high positional accuracy is necessary to be compliant with stringent inspection specifications.

Robot based systems are an attractive alternative as accuracy enhancements in robot kinematics allow them to have the same or even better path accuracy. The challenge however is that although repeatability of standard robotics solutions is excellent the dynamic positional accuracy along a path is not perfect & is only achievable with reduced inspection speed & low data acquisition rates based on the position feedback. Additionally, standard robots need to be protected against water splashes particularly in Squirter Through Transmission technique. Also, programming the robots and ensuring collision free motion through the large number of points is an impossible task using the conventional teach pendant programming methods. An automated approach for programming the system for inspection of all complex aircraft parts including double curvature surfaces e.g. Nose cones and nacelles are essential for successful implementation of a robotised solution.

This paper will present a comprehensive and operational NDT solution for aerospace industry with an integral off-line programming system which is based on standard Stäubli TX200L robots controlled by industry standard Numerical Controller SIEMENS Sinumerik 840D and secondary encoders to achieve high precision on complex scan paths while ensuring a high inspection speed.

KEYWORDSNDT | Off-line programming | UT | Through Transmission | Robot |

November 13 to 15, 2019114

FRI.1.A.3

Presenting author : Brian Pradalet - Air France Industries KLM Engineering and Maintenance

ULTRASOUND NON DESTRUCTIVE TESTING OF STAGE 8-10 SPOOLS ON WING

ABSTRACTS For 2 years now, Air France Industries KLM Engineering & Maintenance has been carrying out ultrasound non-destructive testing on Stage 8-10 Spools. This is a core part of GE90-9 engines and is a component of the High-Pressure Compressor module. The ultrasound inspections carried out in our hangars or on site for our customers means we can identify any signs of cracks that can lead to the loss of the engine in the event of part failure. The operation is extremely delicate and one of the most difficult to perform.

The On-Wing method consists in using an ultrasound probe directly on the wing-mounted engine and significantly cuts TAT. To carry out an ultrasound inspection, the HPC module must be accessible. The access space is very limited and calls for precise movements.

This operation requires a degree of dexterity: the technician must be able to place the probe in direct contact with the Stage 8-10 Spool through a borescope hole using a facing camera. In addition, once the probe has been positioned, the inspectors must make sure that the camera probe does not interfere with the Stage 8 compressor blades during the engine core rotation. By manually moving the accessory case, the engine can be rotated to carry out this type of inspection.

The probe is very sensitive and fragile and must be handled with extreme care during insertion. Technician are like men with the gold fingers, their expertise ensures high-quality procedures. Inspection of the Stage 8 Web guarantees the detection of any signs likely to emerge in this critical area of the part. Any results outside the OEM’s acceptance criteria will require engine removal for shop inspection and possible repairs.

The skills of AFI KLM E&M technicians and their specifications are vital when carrying out ultrasound non-destructive testing. That expertise requires regular updating and refresher training in the use of the tools and the technical actions. The initial training is delivered by General Electric.

With the on wing method, innovation process could rise, such as have a more performant probe, more reliable and resistant.

Those projects demonstrate AFI KLM E&M wants to consolidate its footprint on Non Destructive Testing

KEYWORDS Ultrasound, Engine, On wing, Probe, Maintenance, GE90-9

November 13 to 15, 2019115

FRI.1.B.1

Presenting author : Daniel Chauveau – Institut de Soudure Industrie

Co-Authors : J.Raynal1 | M.Ruppel1 | D.Chauveau1 | M.Hubert2 1. Institut de Soudure Industrie / 2. P.E.I

ADVANCED THERMOGRAPHIC NDT APPLIED ON COMPOSITE AIRCRAFT COMPONENTS

ABSTRACTS An advanced robotised thermographic NDT solution, usable as an alternative to ultrasonic squirter systems, is described.

The main innovations are based on:

• the analysis and processing of the thermal signal from each pixel of a thermal image. As a matter of fact, the thermal signal resulting of the thermal wave diffusion through the component is mathematically processed and treated using multiple derivatives. The final signal is then compared to the original signal obtained on a reference part in order to detect defects such as delamination, inclusion, void, porosity.

• the automation and integration in a fully robotic cell allowing industrial production control with consistency and reliable NDT analysis.

The system is designed to be able to perform daily inspection of flying aircraft parts with higher rate and lower costs compared to UT squirter devices. So the inspection rate is now suitable with the production rate. One of the main advantage of thermography is no coupling medium is necessary. There is no longer need of water in the shop and then to dry the parts.

Benefits, performance and limitations of the robotised technique are presented and discussed

KEYWORDSComposite | NDT | aircraft | thermography |

November 13 to 15, 2019116

FRI.1.B.3

Presenting author : Gaétan Poelman - Mechanics of Materials and Structures (UGent-MMS)

Co-Authors : Gaétan Poelman1 | Saeid Hedayatrasa1 | Joost Segers1 | Wim Van Paepegem1 | Mathias Kersemans1

1. Mechanics of Materials and Structures (UGent-MMS)

COMPARISON OF ADVANCED POST-PROCESSING TECHNIQUES FOR FLASH THERMOGRAPHY FOR RAPID NDT OF CFRP AIRCRAFT COMPONENT: A CASE STUDY

ABSTRACTS Over the last few decades, composite materials such as carbon fiber reinforced polymers (CFRP) have become widely used due to their high specific stiffness and strength in comparison to traditional metals. At present, they are being implemented for critical components in multiple industrial sectors (e.g. automotive, aerospace, …). However, due to their layered structure, they are prone to internal damage features introduced during manufacturing or during operation, which may deteriorate their mechanical performance. Hence, in order to ensure their structural integrity, these materials need to be inspected non-destructively.

Flash thermography, which is a specific type of optical infrared thermography, is a nondestructive testing method that can be adopted to evaluate a material’s internal structure. In this technique, a component’s surface temperature is rapidly elevated by means of an intense optical flash (5 ms at 6 kJ). Subsequently, a high-end infrared camera is used to record the cooling down regime of the sample’s surface. Internal defects cause heat to be built up above them, making them detectable as localized anomalies in the surface’s temperature profile. Considering that CFRPs have an anisotropic thermal diffusivity and the fact that thermal waves are strongly damped, appropriate post-processing techniques are indispensable for the detection of deeper defects.

In this study, flash thermography is applied to a stiffened CFRP aircraft panel (vertical tail of an Airbus A320) with several real production defects. The performance and computational effort of various classical post-processing approaches (e.g. Pulsed phase thermography, Principal component thermography) as well as several more recent post-processing techniques (e.g. partial least-squares thermography, gapped smoothing thermography) is investigated and evaluated with respect to improving the defects’ detectability.

Acknowledgments

The authors acknowledge both the Research Foundation Flanders (FWO grants 12T5418N and 1148018N) and the SBO project DETECT-IV (Grant no. 160455), which fits in the SIM research program MacroModelMat (M3) coordinated by Siemens (Siemens PLM software, Belgium) and funded by SIM (Strategic Initiative Materials in Flanders) and VLAIO (Flemish government agency Flanders Innovation & Entrepreneurship). The authors express their gratitude towards SABCA for supplying material for this research.

KEYWORDSComposites | NDT | Flash thermography | Post-processing techniques |

November 13 to 15, 2019117

FRI.1.C.1

Presenting author : Elizabeth D. Gregory, Ph.D. NASA Langley Research Center

Co-Authors : Elizabeth D. Gregory1 | Peter D. Juarez1

1. NASA Langley Research Center

IN SITU THERMOGRAPHIC INSPECTION OF AUTOMATED FIBER PLACEMENT AT NASA LANGLEY RESEARCH CENTER

ABSTRACTS Automated fiber placement (AFP) can be used to fabricate complex structure with highly tailorable properties but it can also introduce critical manufacturing flaws that are difficult to detect. Inspection of parts comprises a significant amount of the overall manufacturing time for AFP and is often done manually, by human visual inspection. The In Situ Thermographic Inspection System (ISTIS) developed at NASA Langley Research Center aims to reduce the time needed to inspect these parts. ISTIS uses an algorithmic, data-rich process for detection and can assess the quality of cohesion between plies beyond the ability of human visual inspection.

ISTIS consists of a thermal camera and a customizable mini PC mounted on the AFP head with image acquisition triggered by the AFP system at known, discrete spatial increments. The ISTIS system has been used to create three-dimensional data sets of the thermal signal of each ply. ISTIS has been used by multiple projects at NASA Langley to observe flaws that would not have been detectable by visual inspection.

ISTIS has proven to be a useful tool for process development in addition to part inspection by providing unique information about substrate heating. ISTIS has been able to detect ply debonding resulting from the steering geometry of subsequent plies. ISTIS has been able to illustrate heating variability due to AFP head position during fabrication of a complex geometry part. The NASA Langley team is also planning to expand the amount of data that will be collected and the type of automatic analysis that will occur at the time of collection incorporating machine learning for flaw classification. This presentation will also discuss upcoming improvements to the system and data analysis algorithm.

November 13 to 15, 2019118

FRI.1.C.2

Presenting author : Choon-Su Park, Korea Research Institute of Standards and Science, Republic of Korea

MULTI-FUNCTIONAL PHASED ARRAY ULTRASONIC IMAGING: 4 MODES FOR BETTER ANALYSIS

ABSTRACTS Phased array ultrasound testing (PAUT) is able to visualize defects inside structures. As industry develops, various structural components are made of many kinds of materials, and they need appropriate frequencies corresponding materials for non-destructive PAUT. Conventional PAUT, however, generally needs an array transducer that has a single resonant frequency. In addition, nonlinear PAUT with high resolution [C. Park et al., NDT&E Int., 2016] has been newly proposed to look for hidden defects from linear PAUT. These recent trends lead us to develop multi-functional phased array ultrasonic testing (M-PAUT), which provides two linear images and two nonlinear images. The M-PAUT needs an inter-leaved array transducer composed of two different resonant frequencies intervening each other. Two linear phased array images are able to be from each resonant frequency array, and two nonlinear phased array images are higher-harmonic image and sub-harmonic image by corresponding transmitting-receiving combination. The 4 images with an array transducer must be able to delineate more information on the status of structures. The multi-functional phased array imaging scheme is introduced, and computer simulations have assured that the proposed method successfully shows two linear phased array images compatible with conventional PAUT image. In the end, some experiments clearly demonstrate that the system for M-PAUT works well for linear phased array images as well as non-linear phased array images.

November 13 to 15, 2019119

FRI.1.C.3

Presenting author : Pierre Servais - NDT service composite testing), Belgium

Co-Authors : Pierre Servais1 | Ezio Gandin2 | Christophe Greffe3 1. NDT service composite testing, Belgium / 2. Polymers and Composites, Solvay, Belgium / 3. Manufacturer Digital Xray system), Belgium

USE OF MICROFOCUS X-RAY SYSTEM AND PULSE THERMOGRAPHY TO MEASURE POROSITY CONTENT INTO AEROSPACE COMPOSITE PARTS

ABSTRACTS A major problem for aerospace composite parts is to size and measure the porosity content. Ultrasonic is being used since many years but relies on the backwall echo amplitude to determine the porosity content of the defect. As production parts have now more and more complex geometries with internal ribs and locally high curvature, it is here proposed to use the latest state-of-the-art X-ray system using high resolution Flat Panel combined with a microfocus X-ray tube.

This new digital technique is more and more portable and wireless and can be combined with robots to be able to X-ray zones in less than 20 seconds for each area (25x30 cm). Future artificial intelligence will recombine the different Xray images to provide a full mapping of the part and assess directly the porosity percentage.

New design of Inspection Reference Panel for porosities are now used to build up a first correlation between the ADU graylevel of different porous zones using CNR as given by ASTM.

Porosity is usually very difficult to measure for chamfer zone or joggle or curved areas for the historic Ultrasonic Testing method but digital Xray is a very good way to visualize and analyze the porous areas based on quantitative measurement of radiographic attenuation which was not possible for the old Silver Film technique.

This paper will study different artificial and natural porous zones inspected by Ultrasonics and compared to digital X-ray (RT) and pulse thermography (IRT). A combination of both digital methods (RT and IRT) will be presented as a future alternative to Ultrasonics as X-ray is sensitive to any defect perpendicular to plies orientation and Thermography is sensitive to any air gap parallel to the plies. Combining both images (RT and IRT) will be a very clever way to inspect composite parts, it is very fast and digital and without any water consumption like ultrasonics and it permits to push further the NDT Data Fusion algorithms used in Artificial Intelligence.

KEYWORDS Composite Testing | Digital Radiography | Thermography | Porosity Evaluation |

November 13 to 15, 2019120

FRI.2.A.1

Presenting author : Thomas Herzog - Fraunhofer Institute for Ceramic Technologies and Systems IKTS

Co-Authors : Thomas Herzog1 | Susan Walter1 | Sang-Goo Lee2 | Jeong-Ho Lee2 | Frank Schu2 Schubert1 | Henning Heuer1

1. Fraunhofer Institute for Ceramic Technologies and Systems IKTS / 2. Ibule Photonics Co., Ltd

HIGH-PERFORMANCE ULTRASONIC TRANSDUCERS BASED ON PMN-PT SINGLE CRYSTALS FOR NDT OF AEROSPACE MATERIALS

ABSTRACTS Ultrasonic transducers for NDE applications are commonly based on Lead Zirconate Titanate or PZT, an inorganic compound and ceramic perovskite material. Until now the advantages of PMN-PT are used in medical applications, but are not implemented in NDE. For applications with low signal amplitudes, high electronic noise and small transducer elements, the perfor-mance of ultrasonic probes can be significantly enhanced by using Lead Magnesium Niobate-Lead Titanate (PMN-PT) instead of PZT. This single-crystal material offers significantly better piezo parameters and leads to a higher sensitivity and larger bandwidth. There is a better depth resolution possible with this transducers as practical tests have shown. Similar to PZT it can also be fabricated in 1-3 piezo-composite technology. In a cooperation between Fraunho-fer IKTS and Ibule Photonics, PMN-PT ultrasonic transducers are developed and optimized. The performance of phased array probes and single element transducers was measured by a so called PCUS® pro electronic front end from Fraunhofer and compared with equivalent PZT-based probes. As a result various single element and phased array transducers with im-proved performances are available for NDT of typical aerospace materials and applications.

KEYWORDSUltrasonics | Transducers | PMN-PT | Single Crystals |

November 13 to 15, 2019121

FRI.2.A.2

Presenting Author : Xavier Harrich - Socomate International

ADVANCED DDF FOR INSPECTION OF THICK ALUMINIUM AND TITANIUM MATERIALS

ABSTRACTS Abstract. FAAST is a UT Phased Array system especially designed to meet with the high productivity inspection needs, thanks to its outstanding capability at replacing multiple conventional Phased Array systems working in parallel.

The FAAST technology has the capability to transmit multiple sound beams, multi-oriented and/or multi-focused in one single shot using standard 1D or 2D phased array probes. More features are integrated into the instrument, such the possibility to shot at different frequencies within the same shot. Furthermore, it allows to work in full parallel or by using several active apertures on the same probe. Hereafter is a list of applications where the FAAST technology brings added value within the Aircraft industry:

Using FAAST for special alloy and titanium turbine disc inspection complying with Multi-zone testing procedures aiming at the detection of down to Ø0.4mm FBH at 2.5mm up to 140mm depth from the surface. Multi-zone testing procedure requests Multi-focused and/or Multi-oriented beams generation within a single spray throughout a 2D matrix probe, reducing thus considerably the inspection time per turbine disc.

Using FAAST in Aircraft Industry for aluminium plate has been performed using the multiple focused aiming at the detection of Ø0.8mm FBH from 2mm up to 160mm depth from the surface using a single 1D linear 128 elements phased array probe with a width of 120mm. As the FAAST allows to generate all focusing delay laws in one single shot, the scanning speed can reach up to 700mm/s while the performances answer the Aircraft standards in terms of SNR.

Using FAAST in Bars application has been performed using the multiple angles to detect Ø0.8mm FBH and longitudinal notch. By using a curved phased array probe, the FAAST generates the 0° and ±45° angles in one single shot allowing thus an increase of speed of 60.

KEYWORDS Phased Array | Turbine discs | Plates | Billets | UT inspection |

November 13 to 15, 2019122

FRI.2.A.3

Presenting author : Alexandre Beausoleil - Centre technologique en aérospatiale

Co-Authors : Alexandre Beausoleil 1 | Julien Walter 1 | Frédéric Morrow2 | Alexandre Charlebois2 | Dominic Giguère2

1. Centre technologique en aérospatiale / 2. Zetec

DYNAMIC TRACKING OF PHASED-ARRAY PROBE AND 3D C-SCAN RECONSTRUCTION FOR IN-SERVICE INSPECTION OF CFRP AIRCRAFTS COMPONENTS

ABSTRACTS Ultrasonic testing is the preferred method to perform in-service inspection of CFRP aerospace parts. Obtaining C-scan images is highly desirable in order to increase the probability of detection, to improve the results traceability or to provide guidance for repairs. Different phased-array solutions exist to obtain C-scans during in-service manual inspections, but they require mechanical encoders or scanners which bring limitations: limited inspection surface, restrictions to the operator movement, problems adapting the scanner to curves and complex geometries that can be found on an aircraft.

An improved inspection technique is proposed using a portable phased-array UT instrument coupled to a dynamic tracking system. Using markers, a stereoscopic camera collects the real-time 3D position of a phased-array probe. A software application was developed to perform real-time transformation of the 3D coordinates measured by the tracking system into 2D “scan-index” coordinates required by the UT instrument. C-scans can thus be generated as the probe moves along the inspected surface. As the link between the probe’s path and the C-scan axes is determined dynamically, the skew angle of the probe can also be calculated.

If the probe moves in a direction normal to the surface, the acquisition is interrupted until the inspector puts the probe back on the surface. This allows to resume an inspection and to scan discontinuous surfaces. Moreover, a reference tool can be used to allow a displacement of the camera. As the inspection resumes, no discontinuity is observed on the C-scan. In addition, for every pixel of the C-scan, the probe’s 3D position is recorded to allow for a post-treatment 3D reconstruction of the inspected part. The first step is to create a mesh of the surface based on valid probe positions. Then, for each valid position, a C-scan pixel cell is associated to the face of a 3D surface voxel so that the C-scan is locally stretched or compressed to fit the part’s surface.

The technique was tested on reference CFRP specimens including artificial defects as well as real aerospace components. The accuracy of the defects positioning, and sizing and the overall performance of the technique are discussed.

KEYWORDSUltrasonics | In-service inspection | CFRP | Dynamic tracking | 3D imaging |

November 13 to 15, 2019123

FRI.2.A.4

Presenting author : Etienne Grondin - Olympus

INSPECTION OF COMPOSITE LAMINATE MATERIAL USING ADAPTIVE FOCUSING TECHNOLOGY

ABSTRACTS For the past several years, the aviation industry has seen important growth due, in part, to an increased presence of low-cost carriers and regional airlines which has changed the business dynamics by introducing new low-cost business models. As a result of this growth, production rates for new airplanes have increased and new aircraft programs are being launched. Consequently, aviation component manufacturers are facing new challenges including a rise in production rates, a high probability of detection (POD) due to the critical nature of the parts being manufactured, lack of skilled operators, and parts with increasingly complex geometry. Ultrasonic phased array (PA) instruments have evolved, enabling the implementation of advanced acquisition strategies. The introduction of these acquisition strategies helps manufacturers address the inspection challenges they are facing. The evolution of electronic components enables advanced acquisition strategies, such as adaptive focusing, to be implemented. Adaptive focusing simplifies the inspection of variable radiuses, variable opening angle and twisted components and will also compensate for probe misalignment by using innovative signal-processing algorithms. This paper presents an overview of the adaptive focusing technology with the goal of helping NDT integrators and composite material manufacturers to address the challenges they are facing in terms of system performance, production output, and quality control.

KEYWORDS Adaptive Focusing | | NDT integrators | Phased Array Instruments |

November 13 to 15, 2019124

FRI.2.A.5

Presenting author : Deborah Hopkins - Bercli

Co-Authors : Michel Brassard1 / 1. TD NDE

MODELING AND INSPECTION CHALLENGES FOR EVALUATION OF COMPOSITE MATERIALS AND STRUCTURES

ABSTRACTS The challenges in inspecting and modeling composites are significant, and it is often the case that both experiments and modeling are necessary to design and optimize inspections. Whereas laboratory and field experiments have long been the standard for validating models, the complexity and heterogeneity of composite materials makes it extremely difficult to replicate test specimens and experimental conditions as is necessary to achieve comparable results and statistically valid results. Similarly, it is extremely difficult to capture the complexity and material variability of composites in numerical models. Previous results, including successful implementation of composite-inspection systems, have demonstrated the ability to meet aerospace requirements for both in-line and off-line applications [1-3]. Ongoing work and research by others [4] promise to further advance ultrasonic-inspection methodologies. In spite of these advances and the success of existing industrial implementations, significant challenges remain, particularly for polymer-matrix composites with multiple layers and complex geometry. The approach taken for the work reported here is to use modeling (CIVA 16 with and without Surface Adaptive Ultrasound [SAUL]) in conjunction with laboratory experiments to identify and characterize the variability for specific cases. The laboratory experiments were performed using both flat and curved linear arrays, as well as a matrix phased array, for a variety of composite aerospace parts and a specially designed test specimen. Among the specimen variables studied were thickness, shape, and for curved specimens, the effect of changes in the radius of curvature across the part. For the SAUL measurements, variables included the number of active elements used for each shot. All of these variables are shown to be important for the design of probes and optimization of inspection strategies for both in-line and off-line inspection of composite structures

1. D. Hopkins, M. Datuin, M. Brassard, “Challenges and solutions for ultrasonic phased-array inspection of polymer-matrix composites at production rates,” Proc. 45th Annual Rev. of Prog. in QNDE, (2018).

2. M. Brassard, D. Hopkins, J. N. Noiret, “Integration of robotics and surface-adaptive phased-array ultrasound for fully automated inspection of complex composite parts,” JEC Composites Magazine, 83, (2013).

3. S. Mahaut, O. Roy, S. Chatillon, P. Calmon, “Modeling and application of phased array techniques dedicated to complex geometry inspection,” Proc. 39th Annual Rev. of Prog. in QNDE, (2012).

4. E. Carcreff, G. Dao and D. Braconnier, “Fast total focusing method for ultrasonic imaging,” QNDE, (2016).

KEYWORDSComposite inspection | Phased array | Ultrasonics |

November 13 to 15, 2019125

FRI.2.B.1

Presenting author : Hiroyuki Kosukegawa - Institute of Fluid Science, Tohoku University

Co-Authors : Hiroyuki Kosukegawa1 | Yuta Kiso2 | Mitsuo Hashimoto1 | Toshiyuki Takagi3 1. Institute of Fluid Science, Tohoku University / 2. Graduate School of Engineering, Tohoku University / 3. ELyTMaX UMI 3757 CNRS

ELECTROMAGNETIC NONDESTRUCTIVE INSPECTION OF FIBER MISALIGNMENT IN CFRP WITH DIRECTIONAL EDDY CURRENT

ABSTRACTS Carbon fiber reinforced plastics (CFRPs) have been increasingly employed for structural materials in aircraft these days. However, the development of nondestructive testing (NDT) technique for CFRPs is still not sufficient. In particular, “fiber waviness” and “misorientation” are representative defects which largely affect mechanical properties of the product and cannot be inspected by conventional NDT technique. We introduce electromagnetic nondestructive technique with directional eddy current to inspect and evaluate these fiber misalignment defects. Because directional eddy current is highly sensitive to the direction of carbon fiber, eddy current testing (ECT) using directional eddy current can efficiently evaluate fiber misalignment by comparing with conventional isotropic eddy current.

In this paper, we adopt three types of eddy current probes: (i) circular driving (CirD), (ii) symmetrical driving (SymD), (iii) uniform driving (UniD). CirD probe is a conventional type and generates isotropic magnetic flux. SymD probe generates directional and sharp eddy current near the center of the probe. UniD generates directional but widely uniform magnetic flux.

The detectability of fiber waviness and misorientation are evaluated with three probes above. CirD probe shows fairly good performance on both misalignment defects. SymD probe exhibits high performance on the evaluation of fiber waviness but poor ability on misorientation. UniD probe shows the highest performance on both fiber waviness and misorientation. UniD probe can detect fiber waviness with a waviness angle of more than 2º. The lowest misorientation angle which UniD probe can detect is less than 3º. These capacities of UniD probe is effective to assess the quality in mechanical properties of the CFRP products. We conclude that ECT with directional eddy current can be a powerful technique to evaluate fiber misalignment and useful for quality assurance of CFRP products.

KEYWORDS Eddy current testing | Misorientation | Fiber waviness | CFRP | Misalignment |

November 13 to 15, 2019126

FRI.2.B.2

Presenting author : Cui Fangsen - Institute of High Performance Computing, A*STAR, Singapore

Co-Authors : Liu Menglong1 | Cui Fangsen1

1. Institute of High Performance Computing, A*STAR, Singapore

ULTRASOUND DEFECT DETECTION IN THICK COMPOSITES WITH OUT-OF-PLANE WAVENESS

ABSTRACTS Thick composites (usually thickness > 10 mm) are increasingly applied in aerospace engineering and prone to out-of-plane waviness in the manufacturing process. Besides the drastic decrease of compressive strength due to out-of-plane waviness, local resin rich regions may also exist in the composite, both perplexing the ultrasound propagation therein. In this study, a multi-frequency ultrasound-based method is proposed to characterize both waviness and delamination. Numerical modeling with frequency sweeping is conducted first, to quantitatively analyze influence of waviness and local resin rich region on ultrasound propagation in pulse-echo mode. It is found that at the resonance frequency corresponding to single composite ply, ultrasound B-scan built from signal phase can well characterize the waviness. And ultrasound with a lower frequency, compared with the ply resonance frequency, enables more energy to penetrate the local resin rich region and propagates with minor wave vector deviation through the wavy region. Then, a two-step composite characterization method is proposed. In the first step, ultrasound with frequency corresponding to the ply resonance is used to characterize waviness, and in the second step, ultrasound with a lower frequency is generated to detect delamination within wavy composite based on reflected wave signal. With this method, defects can be detected in the coexistence of waviness and local resin rich region. Finally, experimental validation work is performed, showing the method is promising in detecting defects.

KEYWORDSOut-of-plane waviness | Delamination | Ultrasound defect detection | Thick composite |

November 13 to 15, 2019127

FRI.2.B.3

Presenting author : Sergio Gonzalez - CATEC-Advanced Center for Aerospace Technologies

Co-Authors : Sergio Gonzalez1 | Álvaro Herrera1 | Fernando Lasagni1 1. CATEC-Advanced Center for Aerospace Technologies

AD-HOC SOLUTIONS FOR ULTRASONIC INSPECTION OF RADII IN CLOSED COMPOSITE STRUCTURES

ABSTRACTS Nowadays, the ultrasonic inspection (UT) is the most common Non Destructive method (NDT) largely applied in the aerospace industry due to its accuracy, reliability and the degree of industrialization. Although UT is widely developed, new manufacturing processes and part concepts are continuously pushing the technology for new improvements and applications. This is the case of the geometries resulting from novel composites manufacturing methods, such as Resin Transfer Moulding (RTM) or Liquid Resin Infusion (LRI). The last allows the fabrication of complex parts with internal stiffeners and closed geometries in one shoot, reducing assembly time but also limiting the accessibility for NDT inspections.

In this sense, one of the critical issues in the aeronautic sector is the improvement of radii inspection capabilities. The requirement of the aeronautic industry of guaranteeing the quality of the primary composite structures implies the inspection of the whole component through certified technologies. This constraint, together with the lack of technological solutions for the inspection of regions with limited accessibility is blocking the industrial implementation of optimized manufacturing processes.

The present work describes the design and development of adaptive hardware solutions for the inspection of internal radii in composite structures. The final positioning tool has been obtained as result of an iterative design process and manufactured through additive manufacturing technology (Powder Bed Laser Fusion, formerly SLS-Selective Laser Sintering) using polyamide. This device was validated for inspection of inner radii of five outboard boxes, belonging to the winglet structure of a Green Regional Aircraft prototype (Clean Sky 2 programme). The inspections under real operational environment demonstrated the validity of the devices, enabling a certified inspection in the whole radii length and reducing the lead time of the process.

KEYWORDS Ultrasonic Testing | Radii Inspection | Composite Structures |

November 13 to 15, 2019128

FRI.2.B.4

Presenting author : Joost Segers - Mechanics of Materials and Structures (UGent-MMS), Ghent University

Co-Authors : Joost Segers1 | Saeid Hedayatrasa1 | Erik Verboven1 | Gaétan Poelman1 | Wim Van Paepegem1 | Mathias Kersemans1 1. Mechanics of Materials and Structures (UGent-MMS), Ghent University

FULL WAVE FIELD SIGNAL PROCESSING TECHNIQUES FOR NDT OF CFRP AIRCRAFT PANEL: A CASE STUDY

ABSTRACTS Composite materials (e.g. carbon fiber reinforced polymer CFRP) are increasingly used for critical components in several industrial sectors (e.g. aerospace, automotive,…). A major challenge is the detection of internal damages in these composites which may have occurred during manufacturing or during operational life.

One possibility for damage detection in thin-walled composite structures is to analyze the elastic wave characteristics measured on the surface. Many different wave actuation and sensing configurations are possible combined with advanced data processing methods. In this study, a single piezoelectric actuator is used for excitation combined with a 3D scanning laser Doppler vibrometer to measure the resulting full wave field.

Depending on the frequency of excitation, different approaches are used. At relatively low frequencies, i.e. 5 to 100 kHz, damages can be localized by searching for local defect resonances (LDR). In this case, the full field steady-state vibration is analyzed in the frequency domain. At higher frequencies, i.e. 100 to 300 kHz, wave propagation analysis is conducted in time domain to search for defect-wave interactions e.g. wave amplification, wave scattering, change in local wave number, …

In this study, the applicability of full wave field signal processing techniques for the detection of production defects in a CFRP aircraft panel with stringers (A320 tail spar) is investigated. Multiple data processing strategies (e.g. automated LDR detection and acoustic wave number spectroscopy) are used and the damage identification and localization performance is critically compared and evaluated.

Acknowledgments:

Joost Segers is a PhD fellow of the Research Foundation-Flanders (FWO, Grant no. 1148018N). The authors further acknowledge FWO (through grants 12T5418N) and the SBO project DETECT-IV (Grant no. 160455), which fits in the SIM research program MacroModelMat (M3) coordinated by Siemens (Siemens PLM software, Belgium) and funded by SIM (Strategic Initiative Materials in Flanders) and VLAIO (Flemish government agency Flanders Innovation & Entrepreneurship).

KEYWORDSComposites | Non-destructive testing (NDT) | 3D scanning laser Doppler vibrometer | Guided waves | Local Defect Resonance (LDR)

November 13 to 15, 2019129

FRI.2.B.5

Presenting author : Mathieu Ducousso - Safran Group

Co-Authors : Marine Scius Bertrand1 | Romain Ecault2 | Tomas Bergara3 | Laurent Videau1 | Laurent Berthe4 | Nicolas Cuvillier5

1. CEA DAM / 2. Airbus Operation S.A.S / 3. Rescoll / 4. Laboratoire Procédés et Ingénieries en Mécanique et Matériaux, CNRS, Arts et Métiers Paris Tech / 5. Safran Tech

LASER-GENERATED SHOCK WAVES FOR NDE : APPLICATION TO STRUCTURAL BONDING AND DELAMINATION OF COMPOSITE MATERIALS

ABSTRACTS We propose in this study to use intense acoustic shock waves to evaluate mechanical strength of structural bondings or to create delamination in monolithic composite materials. Such last application is dedicated to the creation of delaminated reference samples for NDE procedure and to allow validation of SHM procedure.

The shock waves were generated using ns-scale intense laser pulses in the GW/cm2 intensity range. Such illumination creates a plasma expansion from the sample surface and, thanks to reaction principles, an intense stress, in the GPa order, propagates into the bulk of the material. The sample surface is protected from laser and plasma radiation using an aluminum tape. After back face reflection, phase change occurs, and the compressive shock wave becomes a release shock wave. Such release wave can be used to create a local tension, high enough to evaluate mechanical strength of a structural bonding[1] or to delaminate a composite material[2]. A symmetrical laser shock approach on the structure of interest with controlled time delay between laser pulses can be used to localize the maximal tensile strength anywhere in the structure. First numerical and experimental works are presented here.

Bondings are structural epoxy bonds of different mechanical strength between a TA6V4 titanium alloy and a 3D woven carbon/epoxy composite material. composite materials are CFRP of thicknesses from 1.8 to 6 mm. Results demonstrate the high potential of laser-generated shock waves for NDE.

References

[1] M. Ducousso, S. Bardy, Y. Rouchausse, T. Bergara, F. Jenson, L. Berthe, L. Videau, N. Cuvillier, Quantitative evaluation of the mechanical strength of titanium/composite bonding using laser-generated shock waves, Appl. Phys. Lett., 112, 2018, 111904

[2] M. Ghrib, L. Berthe, N. Mechbal, M. Rébillat, M. Guskov, R. Ecault, N. Bedreddine, Generation of controlled delaminations in composites using symmetrical laser shock configuration, Composite Structures, 171, 2017, 286

KEYWORDS Shock waves | Composite | Delamination | Structural bonding | Laser |

November 13 to 15, 2019130

FRI.2.C.1

Presenting author : Camille Trottier - Onera

Co-Authors : Camille Trottier1 | Jean-Michel Roche1 | Bruno Passilly1 | Patrick Lapeyronnie1 | Achraf Ben Fekih1 1. Onera

CONTRIBUTION OF ULTRASONIC NDT TO THE ASSESSMENT OF THE EFFECT OF OUT-OF-PLANE WAVINESS DEFECTS ON THE MECHANICAL STRENGTH OF THERMOPLASTIC COMPOSITE MATERIALS

ABSTRACTS In the aerospace industry, mass reduction has been an important economic and environmental issue for many years. The replacement of metallic materials by composite materials for mechanically stressed structural parts is a real technological challenge. In the aeronautic industry, the need for increased production rates and reduced costs led to the introduction of thermoplastic resins (TP) which can be used to develop complex-shaped structures. However, the shaping of TP prepregs can create severe damage such as fiber breakage, disorientation of the layer, in plane or out-of-plane waviness. The consolidation step of the manufacturing process can also generate defects such as dry or resin-rich areas and high porosity rate in intra- or inter-layer areas. The optimal use of such complex composite structures requires both non-destructive and mechanical testing to detect and characterize these defects. The aim of the present paper is to closely link ultrasonic NDT measurements to the effect of defects on the structural mechanical integrity.

In this study, various defect manufacturing techniques are used to generate calibrated out-of-plane waviness defects in carbon-fiber reinforced TP composite plates. All manufactured plates are inspected and characterized by NDT: first, ultrasonic testing to precisely locate and size the defects; then, laser vibrometry to measure the mechanical modulus. The accuracy of those NDT measurements is then validated by comparisons with optical microscopy observations. Finally, compression tests are carried out on several specimens with and without defects so that the non-destructive characterizations can be linked to the loss of mechanical properties induced by out-of-plane waviness.

KEYWORDSUltrasonic Ndt | Thermoplastic Composite | Out-Of-Plane Waviness Defects | Laser Vibrometry |

November 13 to 15, 2019131

FRI.2.C.2

Presenting author : Sergey G. Sandomirski - Joint Institute of Mechanical Engineering of the NAS of Belarus

NON-DESTRUCTIVE MAGNETIC TESTING OF THE PHYSICAL AND MECHANICAL PROPERTIES OF MISSION-CRITICAL MOUNTING COMPONENTS IN AVIATION TECHNOLOGY

ABSTRACTS Mounting products with mission-critical functions (bolts, studs, rods) used in aviation technology are subject to increased strength, hardness, and wear resistance requirements. They are made of medium carbon steels alloyed with chromium, manganese, or silicium (steel 37Cr4, 41Cr4, 46Cr2, 42CrMo4, and others). The balance between the strength and plastic properties of the products is achieved by the choice of the mode of their heat treatment - quenching and subsequent medium or high temperature tempering. Possible deviations in the chemical composition of the material of the products and the modes of their heat treatment from the prescribed ones lead to unacceptable deviations of the properties of the products. This requires monitoring all products.

The physical basis of magnetic structural analysis lies in the fact that mechanical and magnetic properties of steels are sensitive to the structural transformations occurring in them during thermal treatments. It has been proven that the coercive force Нc and the remanent magnetization Мr of many steels are related to their structure. When controlling mass batches of products, the best results in reliability and productivity are achieved by magnetization of products when they fall through a coil with direct current and measurement of the remanent magnetic flux Fd in the product. In this case, Fd in products is not proportional to Mr, but to Hc of the material of the products.

A characteristic feature of alloyed steels with a carbon content greater than 0.3%, including steels 37Cr4, 41Cr4, 46Cr2, 42CrMo4 and others, is a non-monotonic change in Hc with an increase in the tempering temperature Tt of products. Therefore, magnetic quality control of products from such steels requires a specific process. To test the tempering mode of such products, we have proposed to expose the magnetized products to a graded influence of a demagnetizing field with intensity Нp, before measuring Fd.

The developed method allows us to choose the value of Hp, at which the optimum sensitivity to changes in Tt is achieved while monitoring products of specific sizes. In this report we show that such testing is based on the sensitivity of Fd in the product after its reverse magnetization in the field Hp to the remanent magnetization of the material Mr. We also report the technical means ensuring application of the developed methodology in industrial settings with a control output of up to 2 products per second. Examples of application of the method for controlling the hardness of small bolts made of steel 42CrMo4, intended for use in aircraft construction, are given.

KEYWORDS Mounting Components | Non-Destructive Testing | Mechanical Properties | Heat Treatment | Medium Carbon Steels |

November 13 to 15, 2019132

FRI.2.C.3

Presenting author : Alexandr Lozak - Saarland University

Co-Authors : Christian Boller1 / 1. Saarland University, Saarbrücken/Germany)

MATERIALS FATIGUE CHARACTERIZATION THROUGH FEATURE EXTRACTION FROM THERMOGRAPHIC IMAGES

ABSTRACTS Developments in digital image recording and processing as well as the increased sensitivity of sensing systems has opened a variety of opportunities within the scope of NDT and structural assessment. One of those opportunities is the recording of thermographic images during fatigue tests. When done appropriately thermographic topographies can be obtained that can provide a variety of relationships between, temperature and stresses applied, plastic deformation zones developing, damage to accumulate, cracks to emerge and possibly much more. Traditionally a single fatigue test is considered as a single data point result. However, this may not be required for a thermographic image since it shows the temperature generated within the specimen as a result of fatigue loading assuming all other external thermal influences to be excluded. If a specimen’s loading condition is known then the thermal information recorded could be well correlated. This virtually allows this thermal information to be segmented leading to more than a single data point to be retrieved from the experiment. In the paper to be presented thermal images of “most indicative” zones will be shown first in terms of their topography and its respective change. Such changes can be clear damage indicators i.e. cracks. However, are there possibly more damage related indicators to retrieve including possibly a statistic of some material’s intrinsic properties? How does such a statistic change in case smaller segments on the specimen surface are considered for evaluation? Some thought will be also spent on how to retrieve the information from a single un-notched specimen first before moving to a special five segment mainly un-notched specimen in a second step. This comparison will be based on different feature extraction, signal and image processing, and classification techniques to be applied It will be shown how much the thermographic image can be sectioned such that the information retrieved is still representative when compared to analyzing the complete un-notched specimen. Feature extraction and image processing techniques in terms of smoothening, noise elimination and outlier determination will be addressed as well as related statistics, feature maps, dynamic representation and behavior of features all in relation to material properties. Machine learning algorithms, deep learning or neural networks are further prospective aspects addressed.

KEYWORDSThermography | Fatigue test | Image processing | Feature extraction |

November 13 to 15, 2019133

FRI.2.C.4

Presenting author : Benjamin Ducharne - LGEF

Co-Authors : Benjamin Ducharne1 | Bhaawan Gupta1 | Yoann Hebrard2 | Jean-Baptiste Coudert2

1. LGEF / 2. SKF Aerospace

MICRO-MAGNETIC NON-DESTRUCTIVE TESTING: AEROSPACE BEARING APPLICATION

ABSTRACTS The quality standards improvement in the aerospace field have revealed a real industrial need for precise and systematic control of the produced and manufactured steels. Different techniques for the control of the manufactured products quality already exist, the so-called “non-destructive testing and evaluation (NDT&E) techniques”. The objective is to evaluate both internal and external states of the tested samples without affecting their integrities. The need for NDT is becoming more prominent. Its evolution is linked to the increasing complexity of the new industrial products geometries and to the instrumentation and computer science improvements. This evolution is also related to the evolution of society preoccupation.

In the aerospace bearing industry, the nondestructive testing techniques based on the “local magnetic signature” constitutes a real alternative to the classic NDT methods like the traditional chemical baths which reveal defects in the form of nuances of gray spots (precipitated carbon) and which are generally quite difficult to interpret. The micro-magnetic methods are nonpolluting methods, they consist in controlling the structural modifications of a test sample under high magnetic field excitation [1]-[4]. Using local dedicated magnetic sensors, we can establish a precise cartography of the controlled structure and the treated parts. In SKF Company, France, Barkhausen noise is by instance used since many years now. It is particularly efficient for the control of contact zones between the rolling and the set elements of the bearings.

The current industrial uses of the Barkhausen’s noise in particular and of the micro-magnetic NDT&E methods in a general way are very empirical; operators set thresholds of rejection using experimental results but no accurate models are available to refine these thresholds and to improve the phenomena understanding. The purpose of our work is to develop local accurate models of the coupled mechanical/magnetic and of the microstructure to improve the understanding of the material behavior [5]. This will help to refine and generalize the use of the micromagnetic signature control as a method for nondestructive testing.

[1] B. Gupta & al., J. of Mag. and Mag. Mat., vol. 486, pp. 165250, 2019.

[2] B. Gupta & al., NDT & E Int., vol. 104, pp. 42-50, 2019.

[3] B. Ducharne & al., IEEE Trans. on. Mag, vol. 99, pp. 1-6, 2018.

[4] B. Ducharne & al., J. of Mag. And Mag. Mat., pp. 231-238, 2017.

[5] T. Matsumoto & al., AIP Advance, vol. 9, Iss. 3, 2019.

KEYWORDS Micromagnetism | Hysteresis model | Non-destructive testing |

November 13 to 15, 2019134

FRI.2.C.5

Presenting author : Artem Eremin - Institute for Mathematics, Mechanics and Informatics, Kuban State University, Krasnodar, Russia

Co-Authors : Evgeny Glushkov1 | Natalia Glushkova1 | Artem Eremin1 | Rolf Lammering2 1. Institute for Mathematics, Mechanics and Informatics, Kuban State University, Krasnodar, Russia / 2. Institute of Mechanics, Helmut-Schmidt-University, Hamburg, Germany

ULTRASONIC GUIDED WAVES AS A TOOL FOR THE EVALUATION OF EFFECTIVE ELASTIC MODULI OF LAMINATE COMPOSITE MATERIALS

ABSTRACTS Non-destructive assessment of the effective elastic properties of laminate composite structures is motivated by various practical needs such as the demand for reliable input data for numerical simulation and design, control of material degradation during structure operation, etc. While propagating over a thin-walled structure, elastic guided waves (GWs) carry information about its material properties, i.e., elastic moduli, density, thickness, and lamination scheme. This provides a basis for the development of appropriate assessment strategies for ultrasonic NDT and SHM systems, especially in view of the achievements in non-contact and in-situ approaches for the GW excitation and sensing using laser and piezoelectric emitters and receivers.

This approach has been implemented for the evaluation of effective parameters of laminate carbon fiber-reinforced plastic (CFRP) composites fabricated from identical unidirectional plies. The developed method is based on the use of the Green matrix of the multilayered anisotropic structure under study in the Fourier transform domain. The effective elastic moduli and, if required, the thickness and density of each sublayer are obtained via the minimization of certain goal functions that specify the discrepancies between the measured and calculated GW characteristics and/or the polar sets of Green’s functions. Previously, we investigated the sensitivity of dispersion properties of fundamental and high-order GWs for various propagation directions to the variation of certain elastic constants in the sublayer stiffness matrix for different typical lamination schemes.

As a goal function, we tested two approaches: the sum of deviations between the calculated and measured group velocities, and the inverted Green’s matrix elements, which must be zero at the poles yielding GWs. The practical implementation of the developed method is discussed and illustrated by examples of effective material property restoration for several unidirectional, cross-ply and quasi-isotropic CFRP samples. In the experiments, GWs are excited by surface-attached piezoelectric wafer active sensors (PWAS) and acquired with a non-contact scanning laser vibrometer or other PWASs arranged in a distributed sensor network. The results obtained are validated against destructive tensile tests as well as by comparing the simulated and measured transient signals carried by excited GWs.

KEYWORDSElastic guided waves | Laminate composite materials | Effective elastic properties | Material characterization

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SESSION AUTHORWE.3.C.4 Ambrozinski LukaszTHU.1.B.3 Aouini MarwenTHU.2.B.5 Asokkumar AadhikTHU.3.B.4 Ba AbdoulayeWE.2.B.2 Barras JordanFRI.2.A.3 Beausoleil AlexandreFRI.1.A.1 Ben Abdallah HamdiWE.2.A.3 Boudou CarolineTHU.3.C.5 Bouzenad AbdEnnourWE.1.A.2 Breit MarcTHU.2.A.2 Brütt CécileFRI.1.B.1 Chauveau DanielWE.2.C.2 Chebbi HoussemWE.1.A.1 Chopard AdrienWE.1.A.5 Chopard AdrienTHU.1.C.2 Chow PeterWE.1.C.1 Demaldent EdouardTHU.1.C.4 Dimopoulos VasileiosWE.1.C.3 Dobson JeffFRI.2.C.4 Ducharne BenjaminWE.3.A.1 Ducharne Benjamin

SESSION AUTHOR FRI.2.B.5 Ducousso Mathieu THU.2.A.5 Dumas Philippe THU.1.B.6 Fang FangFRI.2.B.2 Fangsen CuiTHU.2.C.5 Galleguillos CarlosTHU.1.A.6 Gaverina LudovicWE.2.C.1 Ghibaudo OlivierFRI.2.C.5 Glushkov EvgenyFRI.2.B.3 Gonzalez SergioFRI.1.A.2 Gramberger ThomasFRI.1.C.1 Gregory Elizabeth D.FRI.2.A.4 Grondin EtienneWE.2.B.1 Guemes AlfredoTHU.3.A.2 Guillemette RibayWE.2.C.5 Harman DavidFRI.2.A.2 Harrich XavierTHU.2.C.3 Hansen JensFRI.2.A.1 Herzog ThomasFRI.2.A.5 Hopkins Deborah

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SESSION AUTHORTHU.1.C.6 Rautela MahindraTHU.2.B.4 Reboud Christophe WE.3.C.3 Rohringer WolfgangTHU.1.C.1 Salucci MarcoTHU.1.C.3 Salucci MarcoWE.2.A.1 Salucci MarcoFRI.2.C.2 Sandomirski Sergey G.THU.1.A.3 Schmidhammer UliFRI.2.B.4 Segers JoostWE.1.C.2 Sellami FatmaWE.3.A.4 Sergeeva-Chollet N.FRI.1.C.3 Servais PierreTHU.3.B.1 Siryabe EmmanuelTHU.3.B.3 Skopinski ClémentWE.1.C.4 Smagulova DamiraTHU.3.A.3 Spytek JakubTHU.1.B.1 Sridaran Venkat Ramanan,THU.1.B.2 Sunetchiieva SeviliaTHU.3.B.2 Takagi ToshiyukiFRI.1.B.2 Tardif XavierTHU.2.C.2 Tarpau CéciliaWE.1.A.3 Tranca TeodorFRI.2.C.1 Trottier CamilleWE.3.C.5 Unnikrishnakurup SreedharTHU.2.A.1 Voillaume HubertTHU.3.C.1 Walter JulienTHU.1.B.4 Wandowski TomaszWE.3.A.2 Yadav Arun KumarWE.2.A.4 Yang SamTHU.3.A.5 Yilmaz BengisuTHU.3.A.4 Yuan PeilongWE.3.A.3 Zhang Shurui

SESSION AUTHORWE.3.C.1 Jatzlau PhilippWE.1.B.4 Jaussaud GladysTHU.1.A.2 Jonuscheit JoachimWE.1.A.4 Kawasaki HirakuTHU.2.C.1 Khan MuziburTHU.2.B.2 Köhler ThomasFRI.2.B.1 Kosukegawa HiroyukiTHU.2.B.3 Krishna Rentala VamsiWE.3.C.2 Krumm MichaelWE.1.B.2 Le Bourdais Florian WE.2.C.3 Liebers NicoFRI.2.C.3 Lozak AlexandreWE.1.B.1 Lugovtsova YevgeniyaTHU.1.A.5 Mantel ThierryWE.1.B.5 Marechal PierreTHU.2.C.4 Martinsen DominikTHU.1.A.1 Mendioroz Arantza THU.2.B.1 Mesnil OlivierWE.1.C.5 Methenni HajerTHU.1.C.5 Meynard PhilippeTHU.3.C.3 Miorelli RobertoTHU.3.C.2 Miorelli RobertoWE.1.B.3 Monaco ErnestoTHU.3.A.1 Mrowka JakWE.2.C.4 Munalli DanielaFRI.1.C.2 Park Choon-SuWE.2.A.2 Petry M.Eng. ChristopherFRI.1.B.3 Poelman GaétanTHU.1.B.5 Ponte Felgueiras OlivierFRI.1.A.3 Pradalet BrianTHU.2.A.4 Raude Angélique

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CATALOG OF ABSTRACTS 11th International Symposium on NDT … · 2019-11-28 · plenary session 7:45...

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