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CATALOG O

F 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 ARE

DIGITAL TECHNOLOGY AT THE HEART

OF FUTURE CHALLENGES

The 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 patented

enabling technologies applicable to

numerous fields of application.

– An ‘innovation federator’: our

research engineers design and provide

comprehensive solutions consistent

and optimized for the needs of our

partners.

– 20 R&D platforms with the latest

equipment, 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]

www-list.cea.frCONTACT

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


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.

BALASUBRAM

ANIAM

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 TEJEDO

R Alvaro

ABSTRACT

Alvaro ESPADA TEJEDOR - AIRBUS

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com

e &

Intr

oduc

tion

P

LEN

AR

Y S

ESS

ION

S

9h00

- 9h

45 :

Alv

aro

Esp

ada

Teje

do

r -

Air

bu

s N

DE

Chal

leng

es a

t Airb

us

9h

45 -

10h3

0 : S

eth

Kes

sler

- M

etis

Des

ign

Co

rp

Stru

ctur

al H

ealth

Mon

itorin

g : T

akin

g yo

ur N

DT

syst

em a

long

for t

he ri

de

10h

30

- 1

0h

50

- C

off

ee

Bre

ak

TEC

HN

ICA

L P

RO

GR

AM

SES

SIO

NS

WE.

1.A

.W

E.1.

B.

WE.

1.C

TOP

ICS

Ad

van

ces

in N

DT

Met

ho

ds

ISt

ruct

ura

l Hea

lth

Mo

nit

ori

ng

IM

od

ellin

g &

Sim

ula

tio

n I

10h5

0-11

h10

WE.

1.A.

1

Mill

imet

er w

aves

Rad

ar :

A w

ay to

see

thro

ugh

the

airp

lane

cov

erin

g ?

Ad

rien

Ch

op

ard

- L

abo

rato

ire

IMS

- U

MR

52

18 C

NR

S,

Un

iver

sité

Bo

rdea

ux

WE.

1.B.

1D

amag

e Q

uant

ifica

tion

in A

lum

iniu

m-C

FRP

Com

posi

te

Stru

ctur

es u

sing

Gui

ded

Wav

e W

aven

umbe

r Map

ping

Ye

vgen

iya

Lug

ovt

sova

(BA

M, B

erlin

)

WE.

1.C.

1

A M

acro

-ele

men

t str

ateg

y de

dica

ted

to th

e tr

ansi

ent m

odel

-lin

g of

the

ultr

ason

ic te

stin

g in

car

bon

rein

forc

ed c

ompo

site

la

min

ates

: Effi

cien

t inc

orpo

ratio

n of

loca

l fibe

r orie

ntat

ion,

vi

sco-

elas

tic b

ehav

ior a

nd th

in in

term

edia

te la

yers

Ed

ou

ard

Dem

ald

ent

(CEA

LIS

T)

11h1

0-11

h30

WE.

1.A.

2

Stan

dard

izat

ion,

Influ

ence

s, P

ossi

bilit

ies

and

Risk

s of

U

V LE

D T

echn

olog

y to

Flu

ores

cent

Mag

netic

Par

ticle

In

spec

tion

(MPI

) and

Pen

etra

nt In

spec

tion

(FPI

) M

arc

Bre

it (S

ecu

-Ch

ek G

mb

H)

WE.

1.B.

2M

achi

ne le

arni

ng b

ased

tem

pera

ture

com

pens

atio

n fo

r G

uide

d W

ave

Imag

ing

in S

truc

tura

l Hea

lth M

onito

ring

Flo

rian

Le

Bo

urd

ais

(CEA

-Lis

t)

WE.

1.C.

2

Inve

stig

atio

ns o

f the

Pot

entia

l of U

ltras

onic

Gui

ded

Wav

es

Test

ing

for F

law

Det

ectio

n in

Rep

rese

ntat

ive

Aero

spac

e St

ruct

ures

usi

ng C

IVA

Fatm

a S

ella

mi (

Tech

nic

al U

niv

ersi

ty o

f M

un

ich

)

11h3

0-11

h50

WE.

1.A.

3N

ew m

etho

d fo

r the

eva

luat

ion

of t

he S

mal

l Refl

ecto

rs in

th

e U

ltras

onic

Insp

ectio

n of

the

Forg

ing

Tita

nium

Allo

y Te

od

or

Tran

ca (D

iac

Ser

vici

i srl

)

WE.

1.B.

3

Hyb

rid S

truc

tura

l Hea

lth M

onito

ring

on c

ompo

site

pla

tes

with

em

bedd

ed a

nd s

econ

dary

bon

ded

Fibe

r Bra

gg

Gra

tings

arr

ays

and

piez

oele

ctric

pat

ches

E.

Mo

nac

o (U

niv

of

Nap

oli)

WE.

1.C.

3Im

prov

ing

Ultr

ason

ic In

spec

tion

of T

aper

ed C

FRP

Stru

c-tu

res

Usi

ng C

loud

Bas

ed F

EA S

imul

atio

n Je

ff D

ob

son

(On

Sca

le)

11h5

0-12

h10

WE.

1.A.

4St

udy

of th

e da

mag

e ev

alua

tion

met

hod

usin

g th

e fr

eque

ncy

chan

ge in

the

tens

ile te

st o

f the

CFR

P H

irak

u K

awas

aki (

IIC

IHI J

apan

)

WE.

1.B.

4Im

prov

ing

Lam

b w

ave

dete

ctio

n fo

r SH

M u

sing

a d

edi-

cate

d LW

DS

elec

tron

ics

Gla

dys

Jau

ssau

d -

Ced

rat

Tech

no

log

ies

WE.

1.C.

4

Ultr

ason

ic N

DT

and

num

eric

al s

imul

atio

n of

adh

esiv

ely

bond

ed a

lum

iniu

m to

CFR

P m

ater

ials

D

amir

a S

mag

ulo

va (U

ltra

sou

nd

Res

earc

h In

stit

ute

of

Kau

nas

Un

iver

sity

of

Tech

no

log

y)


Wed

nes

day

, No

vem

ber

13

th, 2

019

12h1

0-12

h30

WE.

1.A.

5

Con

tact

less

Ter

aher

tz P

aint

Thi

ckne

ss M

easu

rem

ents

: sp

ecifi

city

of a

eron

autic

s in

dust

ry

Ad

rien

Ch

op

ard

- L

abo

rato

ire

IMS

- U

MR

52

18 C

NR

S,

Un

iver

sité

Bo

rdea

ux

WE.

1.B.

5Th

erm

al a

gein

g ev

alua

tion

of c

ompo

site

pla

tes

thro

ugh

elec

trom

echa

nica

l im

peda

nce

P

ierr

e M

arec

hal

- U

niv

ersi

ty o

f Le

Hav

re

WE.

1.C.

5Im

plic

it-ex

plic

it sc

hem

e fo

r the

ela

stod

ynam

ic w

ave

equa

tion

in p

late

s H

ajer

Met

hen

ni (

DIS

C, C

EA-L

IST)

12h3

0 - 1

4h00

- Lu

nch-

Buffe

t

SES

SIO

NS

WE.

2.A

.W

E.2

.B.

WE.

2.C

TOP

ICS

Ad

van

ces

in N

DT

Met

ho

ds

IISt

ruct

ura

l Hea

lth

Mo

nit

ori

ng

I (c

on

t.)

Mo

del

ling

& S

imu

lati

on

II

14h0

0-14

h20

WE.

2.A.

1H

alf-S

pace

ND

T/N

DE

thro

ugh

Mul

ti-Fr

eque

ncy

Bay

e-si

an C

ompr

essi

ve S

ensi

ng

Mar

co S

alu

cci (

ELED

IA R

esea

rch

Cen

ter)

WE.

2.B.

1

Str

ain

and

dam

age

sens

ing

by C

NT

mod

ified

adh

esiv

e fil

ms

and

fiber

opt

ic d

istr

ibut

ed s

ensi

ng .

Com

paris

on o

f pe

rfor

man

ces

in a

dou

ble

lap

bond

ed jo

int

Alf

red

o G

uem

es (U

PM

)

WE.

2.C.

1

Para

met

ric s

tudy

by

sim

ulat

ion

of a

ther

mog

raph

y co

ntro

l by

indu

ctio

n he

atin

g. A

pplic

atio

n to

the

dete

ctio

n an

d ch

arac

teriz

atio

n of

cra

cks.

O

livie

r G

hib

aud

o (S

afra

n T

ech

)

14h2

0-14

h40

WE.

2.A.

2

Endo

scop

ic S

patia

l Pha

se S

hift

Shea

rogr

aphy

With

The

In

terf

eros

kop

For T

urbi

ne B

lade

Fla

w In

spec

tion

M.E

ng

. Ch

rist

op

her

Pet

ry (U

niv

ersi

ty o

f A

pp

lied

Sci

ence

s Tr

ier)

WE.

2.B.

2

Inte

rpre

ting

resu

lts o

f ND

T/SH

M m

etho

ds b

ased

on

elas

tic g

uide

d w

aves

in c

ompo

site

pla

te-li

ke s

truc

ture

s by

a s

emi-a

naly

tic m

odal

sim

ulat

ion

tool

Jo

rdan

Bar

ras

(CEA

Lis

t)

WE.

2.C.

2Se

mi-a

naly

tical

mod

elin

g of

edd

y cu

rren

t ins

pect

ion

for

anis

otro

pic

mat

eria

l pre

sent

ing

roug

h in

terf

aces

H

ou

ssem

Ch

ebb

i (C

EA L

ist)

14h4

0-15

h00

WE.

2.A.

3N

eutr

on a

nd s

ynch

rotr

on X

-ray

mea

sure

men

ts: u

niqu

e to

ols

in th

e no

n-de

stru

ctiv

e to

olbo

x C

aro

line

Bo

ud

ou

(ILL

)

STU

DE

NT

CH

ALL

EN

GE

I

Te

am 1

WE.

2.C.

3

Redu

cing

ND

T Eff

ort b

y Co

uple

d M

onito

ring

and

Sim

ula-

tion

of L

iqui

d Co

mpo

site

Mol

ding

Pro

cess

es

Nic

o L

ieb

ers

(Ger

man

Aer

osp

ace

Cen

ter,

Inst

itu

te o

f

Co

mp

osi

te S

tru

ctu

res

and

Ad

apti

ve S

yste

ms

)

15h0

0-15

h20

WE.

2.A.

4N

on-d

estr

uctiv

e qu

ality

eva

luat

ion

of a

dditi

vely

-man

u-fa

ctur

ed c

ompo

nent

s S

am Y

ang

(CS

IRO

)Te

am 2

WE.

2.C.

4

The

use

of fr

ee-s

pace

mic

row

ave

non-

dest

ruct

ive

tech

-ni

ques

: sim

ulat

ion

of d

amag

e de

tect

ion

in c

arbo

n fib

re

rein

forc

ed c

ompo

site

s.

Dan

iela

Mu

nal

li (T

he

Un

iver

sity

of

No

ttin

gh

am)

15h2

0-15

h40

Team

3W

E.2.

C.5

Non

-Des

truc

tive

Com

pone

nt In

spec

tion

and

Num

eric

al

Sim

ulat

ion:

App

licat

ions

to A

dditi

ve M

anuf

actu

ring

Dav

id H

arm

an (S

yno

psy

s)

15h4

0 - 1

6h10

- Co

ffee

Brea

k

SES

SIO

NS

WE.

3.A

.W

E.3

.C

TOP

ICS

ND

T M

eth

od

s -

Mag

net

ics

& E

dd

y C

urr

ent

STU

DEN

T C

HA

LLEN

GE

IIN

DT

Des

ign

& P

rod

uct

ion

Inte

gra

tio

n

16h1

0-16

h30

WE.

3.A.

1M

icro

-mag

netic

non

-des

truc

tive

test

ing

on e

xtre

me

cond

ition

age

d sa

mpl

es.

Ben

jam

in D

uch

arn

e (L

GEF

, IN

SA

Lyo

n)

Team

4W

E.3.

C.1

Loca

l Aco

ustic

Res

onan

ce S

pect

rosc

opy:

An

Esca

latio

n Ap

proa

ch fo

r effi

cien

t ND

T of

fibe

r rei

nfor

ced

com

posi

tes

Ph

ilip

p J

atzl

au (T

ech

nic

al U

niv

ersi

ty o

f M

un

ich

)

16h3

0-16

h50

WE.

3.A.

2

Dev

elop

men

t of P

orta

ble

Wire

less

Non

-Des

truc

tive

Cra

ck Id

entifi

catio

n M

etho

d by

Usi

ng G

MR

Sens

or A

rray

fo

r Ove

rhea

d Cr

ane

Brid

ges

Aru

n K

um

ar Y

adav

(AG

H U

niv

ersi

ty o

f S

cien

ce &

Tech

no

log

y)

Team

5W

E.3.

C.2

3D X

-ray

Insp

ectio

n Sy

stem

for H

elic

opte

r Rot

or B

lade

s M

ich

ael K

rum

m (R

ayS

can

Tec

hn

olo

gie

s G

mb

H)


Wed

nes

day

, No

vem

ber

13

th, 2

019

16h5

0-17

h10

WE.

3.A.

3

Sizi

ng m

etho

d of

cra

ck le

ngth

on

carb

on s

teel

s fo

r edd

y cu

rren

t tes

ting

usin

g tr

ansm

itter

-rec

eive

r pro

be

Sh

uru

i Zh

ang

- In

stit

ute

of

Flu

id S

cien

ce, T

oh

oku

Un

iver

sity

Team

6W

E.3.

C.3

Mill

imet

er-s

ized

non

-con

tact

ultr

asou

nd p

robe

bas

ed o

n fib

er-c

oupl

ed la

ser e

xcita

tion

and

dete

ctio

n W

olf

gan

g R

oh

rin

ger

- X

AR

ION

Las

er A

cou

stic

s

17h1

0-17

h30

WE.

3.A.

4M

R se

nsor

s ar

rays

for e

ddy

curr

ent t

estin

g N

. Ser

gee

va-C

ho

llet

(CEA

Lis

t)Te

am 7

WE.

3.C.

4

Effici

ent i

mpl

emen

tatio

n of

cor

rela

tion-

base

d til

t filte

r for

im

agin

g of

CRF

P pl

y w

avin

ess

usin

g la

ser u

ltras

ound

Lu

kasz

Am

bro

zin

ski (

AG

H U

niv

ersi

ty o

f S

cien

ce a

nd

Tech

no

log

y, K

rako

w, P

ola

nd

)

17h3

0-17

h50

Team

8W

E.3.

C.5

Non

dest

ruct

ive

eval

uatio

n of

ther

mal

bar

rier c

oatin

g th

ickn

ess

degr

adat

ion

usin

g in

frar

ed th

erm

ogra

phy

and

tera

hert

z-td

s im

agin

g S

reed

har

Un

nik

rish

nak

uru

p (C

ente

r fo

r n

on

-des

tru

ctiv

e

eval

uat

ion

, IIT

Mad

ras,

Ch

enn

ai, I

nd

ia)

End

of

the

tech

nic

al p

rog

ram

me

& d

epar

ture

to

th

e C

EA L

ist

STU

DE

NTS

CH

ALL

EN

GE

A no

velty

this

yea

r will

be

a st

uden

t cha

lleng

e, w

here

mai

nly

post

grad

uate

stu

dent

s w

ill h

ave

to d

etec

t hid

den

flaw

s in

com

posi

te s

ampl

es in

clud

ing

to p

rese

nt a

con

cept

on

how

to g

et th

ose

dam

ages

mon

i-to

red

in th

e se

nse

of s

truc

tura

l hea

lth m

onito

ring

(SH

M),

all b

eing

insp

ired

by d

amag

e to

lera

nt d

esig

n.

8 te

ams

of 4

mem

bers

of s

tude

nts

from

Bel

gium

, Den

mar

k, G

erm

any,

Lith

uani

a, P

olan

d, S

pain

and

the

Fran

ce/U

K w

ill p

rese

nt th

eir s

olut

ions

of d

etec

ting

on c

ompo

site

s (C

OTE

SA)

durin

g a

spec

ial s

essi

on w

ith a

rew

ardi

ng a

t the

Con

fere

nce

Din

ner.

The

stud

y ca

se g

ives

five

diff

eren

t int

erna

l def

ects

in th

e sa

mpl

e w

hose

min

imum

siz

e is

3 m

m x

3 m

m. O

ne d

efec

t is

loca

ted

in th

e bo

ndin

g ar

ea o

f the

T-b

ar to

the

spec

imen

.Th

e ch

alle

nge

is h

igh

! Eac

h te

am w

ill b

e ev

alua

ted

on 3

mai

n cr

iteria

: de

tect

abili

ty o

f the

def

ects

, app

roac

h of

thei

r wor

ks a

nd th

e pr

esen

tatio

n on

nov

embe

r at t

he 11

th N

DT

in

Aero

spac

e.

Pa

rtic

ipa

nts

will b

e w

elc

om

ed

in

CE

A L

ist

for

an

exclu

siv

e v

isit

of

the

la

bs, fo

llo

we

d b

y a

co

ck

tail d

inn

er.

SO

CIA

L E

VE

NT

18h

00

-G

rou

p 1

: Dep

artu

re D

epar

ture

Gro

up

1 t

o C

EA L

ist

for

the

ND

T La

bs

Vis

it

18h

00

- G

rou

p 2

: ND

T in

Aer

osp

ace

Co

nfe

ren

ce C

ente

r : R

efre

shm

ent

& E

xhib

itio

n

18h

45

- D

epar

ture

Gro

up

2 t

o C

EA L

ist

19h

00

-21h

30

- C

EA L

ist:

Co

ckta

il D

inn

er

21h

30

- S

hu

ttle

s tr

ansf

ers

bac

k to

;

- th

e S

ymp

osi

um

, Cam

pan

ile

- N

ovo

tel S

acla

y

- &

Mer

cure

Mas

sy T

GV


Thu

rsd

ay N

ove

mb

er 1

4th

, 20

19

8h00

- D

epar

ture

of t

he S

huttl

es fr

om N

ovot

el S

acla

y &

Mer

cure

Mas

sy T

GV

to S

acla

y, N

DT

Aero

spac

e 20

19 S

ympo

sium

.

8h15

- O

peni

ng o

f the

Sym

posi

um, W

elco

me

Coffe

e an

d ex

hibi

tion

8h30

- 10

h00

- PLE

NAR

Y SE

SSIO

N

8h30

- 9h

15 :

Ellio

tt C

ram

er -

NA

SA

Lan

gle

y N

DE

Chal

leng

es a

t NAS

A

9h15

- 10

h00

: Pr

Kri

shn

an B

alas

ub

ram

ania

n -

ITT

Mad

ras

Ultr

ason

ic a

nd T

herm

al T

echn

ique

s fr

om C

ND

E@IIT

M fo

r Aer

ospa

ce A

pplic

atio

ns

10h

00

- 1

0h

30

- C

off

ee B

reak

SES

SIO

NS

THU

.1.A

.TH

U.1

.B.

THU

.1.C

TOP

ICS

ND

T M

eth

od

s -

Fro

m M

icro

wav

e to

Ther

mo

gra

ph

ySt

ruct

ura

l Hea

lth

Mo

nit

ori

ng

IID

ata

pro

cess

ing

& S

tati

stic

al m

eth

od

s I

10h3

0-10

h50

THU

.1.A.

1

Sizi

ng th

e w

idth

of t

ilted

cra

cks

usin

g la

ser s

pot

lock

-in th

erm

ogra

phy

Ara

ntz

a M

end

ioro

z (E

scu

ela

de

Ing

enie

ria

de

Bilb

ao)

THU

.1.B.

1

A to

olbo

x co

ncep

t to

confi

gure

a s

hm s

olut

ion

on

agei

ng a

ircra

ft st

ruct

ures

bas

ed o

n ac

oust

ic a

nd th

erm

al

met

hods

R

aman

an, S

rid

aran

Ven

kat

(Saa

rlan

d U

niv

ersi

ty)

THU

.1.C.

1In

nova

tive

Lear

ning

-by-

Exam

ples

App

roac

hes

for R

eal-

Tim

e N

DT/

ND

E of

Com

plex

Str

uctu

res

Mar

co S

alu

cci (

ELED

IA R

esea

rch

Cen

ter)

10h5

0-11

h10

THU

.1.A.

2Ra

dom

e In

spec

tion

with

Ter

aher

tz W

aves

Jo

ach

im J

on

usc

hei

t (F

rau

nh

ofe

r IT

WM

, Kai

sers

-

lau

tern

, Ger

man

y)

THU

.1.B.

2St

ruct

ural

hea

lth m

onito

ring

syst

em fo

r moi

stur

e in

gres

s de

tect

ion

in s

andw

ich

com

posi

te s

truc

ture

s S

evili

a S

un

etch

iieva

(KU

Leu

ven

)

THU

.1.C.

2O

ptio

ns to

und

erta

ke th

e AI

dig

ital t

rans

form

atio

n jo

urne

y fo

r ND

T in

Aer

ospa

ce

Pet

er C

ho

w (F

ujit

su)

11h1

0-11

h30

THU

.1.A.

3

Sing

le-s

hot p

ulse

d te

rahe

rtz

non-

dest

ruct

ive

eva-

luat

ion

syst

ems

for i

n-lin

e pr

oduc

tion

cont

rol a

nd

auto

mat

ed in

spec

tion

Uli

Sch

mid

ham

mer

(Ter

ato

nic

s)

THU

.1.B.

3W

irele

ss s

yste

m fo

r str

uctu

ral h

ealth

mon

itorin

g w

ith

Gui

ded

Ultr

ason

ic W

aves

: Det

ectio

n of

def

ects

M

arw

en A

ou

ini

(In

stit

ut

de

So

ud

ure

)

THU

.1.C.

3M

icro

wav

e N

DT/

ND

E th

roug

h a

Prob

abili

stic

Com

pres

sive

Se

nsin

g M

etho

d M

arco

Sal

ucc

i (EL

EDIA

Res

earc

h C

ente

r)

11h3

0-11

h50

THU

.1.B.

4

Dam

age

asse

ssm

ent o

f com

posi

te s

truc

ture

s us

ing

elec

trom

echa

nica

l im

peda

nce

met

hod

Wie

slaw

Ost

ach

ow

icz

(Po

lish

Aca

dem

y o

f S

cien

ces,

Inst

itu

te o

f Fl

uid

–Fl

ow

Mac

hin

ery,

Po

lan

d)

THU

.1.C.

4Effi

cien

t TR-

MU

SIC

dam

age

dete

ctio

n in

com

posi

tes

with

a

limite

d nu

mbe

r of s

enso

rs

Vas

ileio

s D

imo

po

ulo

s (D

MM

S L

ab)

11h5

0-12

h10

THU

.1.A.

53d

Sur

face

Top

ogra

phy

Mea

sure

men

t Usi

ng E

las-

tom

eric

Con

tact

Th

ierr

y M

ante

l (G

elS

igh

t In

c.)

THU

.1.B.

5

Vibr

atio

n he

alth

crit

erio

n ba

sed

on th

e co

mbi

natio

n of

ben

ding

and

tors

iona

l mod

es to

mon

itor t

he h

ealth

st

atus

of s

afet

y-cr

itica

l com

posi

te s

truc

ture

s O

livie

r P

on

te F

elg

uei

ras

(Min

es P

aris

tech

)

THU

.1.C.

5N

DT

4.0

: App

licat

ion

of In

dust

ry 4

.0 in

ND

T an

d im

pact

on

aero

spac

e co

mpa

nies

P

hili

pp

e M

eyn

ard

(Vis

ico

nsu

lt)

12h1

0-12

h30

THU

.1.A.

6Fl

ying

Lin

e Ac

tive

IR T

herm

ogra

phy

appl

ied

to th

e in

spec

tion

of e

nviro

nmen

tal b

arrie

r coa

tings

Lu

do

vic

Gav

erin

a (O

ner

a)

THU

.1.B.

6

Stru

ctur

al h

ealth

mon

itorin

g fr

amew

ork

base

d on

pro

ba-

bilit

y m

odel

ing

unde

r tim

e-va

ryin

g co

nditi

ons

Fan

g F

ang

(Nan

jing

Un

iver

sity

of

Aer

on

auti

cs a

nd

Ast

ron

auti

cs)

THU

.1.C.

6

Dee

p Le

arni

ng fr

amew

orks

for w

ave

prop

agat

ion-

base

d da

mag

e de

tect

ion

in 1D

-wav

egui

des

Mah

ind

ra R

aute

la (D

epar

tmen

t o

f A

ero

spac

e En

gin

ee-

rin

g, I

nd

ian

Inst

itu

te o

f S

cien

ce, B

ang

alo

re, I

nd

ia)


Thu

rsd

ay, N

ove

mb

er 1

4th

, 20

19

12h

30

- 1

4h

00

- L

un

ch-B

uff

et

SES

SIO

NS

THU

.2.A

.TH

U.2

.B.

THU

.2.C

TOP

ICS

ND

T M

eth

od

s- P

has

ed A

rray

IN

DT

& S

HM

Rel

iab

ility

ass

essm

ent

Dat

a p

roce

ssin

g &

Co

mp

ute

d T

om

og

rap

hy

14h0

0-14

h20

THU

.2.A

.1Ap

plic

atio

n of

TFM

imag

ing

for e

nhan

ced

ND

T in

Ae

rosp

ace

Hu

ber

t V

oill

aum

e (E

dd

yfi T

ech

no

log

ies)

THU

.2.B

.1

Mod

el A

ssis

ted

Prob

abili

ty o

f Det

ectio

n in

Str

uctu

ral

Hea

lth M

onito

ring

appl

ied

to im

pact

ed c

ompo

site

st

ruct

ures

O

livie

r M

esn

il (C

EA-L

ist)

THU

.2.C

.1Co

mpu

ted

Radi

ogra

phy

for H

igh

Reso

lutio

n Im

agin

g Ap

plic

atio

ns o

f Airc

raft

Stru

ctur

es

Mu

zib

ur

Kh

an (N

atio

nal

Res

earc

h C

ou

nci

l Can

ada)

14h2

0-14

h40

THU

.2.A

.2M

ulti-

elem

ent u

ltras

onic

eva

luat

ion

of s

catte

ring

solid

s by

refle

ctio

n m

atrix

ana

lysi

s

Céc

ile B

rütt

(Saf

ran

Tec

h, I

nst

itu

t La

ng

evin

)

THU

.2.B

.2D

igita

l Tw

in a

ppro

ach

for c

ritic

al e

ngin

e co

mpo

nent

s us

ing

PCRT

Th

om

as K

öh

ler

(Vib

ran

t G

mb

H)

THU

.2.C

.2

A ne

w b

i-im

agin

g N

DT

syst

em fo

r sim

ulta

neou

s re

cove

ry

of a

ttenu

atio

n an

d el

ectr

onic

den

sity

map

s C

écili

a Ta

rpau

Lab

ora

toir

e d

e P

hys

iqu

e Th

éori

qu

e et

Mo

dél

isat

ion

(LP

TM)

14h4

0-15

h00

THU

.2.B

.3

Effec

t of O

xide

Indu

ced

Mic

rost

ruct

ure

Deg

rada

tion

in

Aero

-Eng

ine

Com

pone

nts

on P

OD

of N

DT

Tech

niqu

es

Vam

si K

rish

na R

enta

la (S

cho

ol o

f Eng

inee

ring

Sci

ence

s

and

Tec

hno

log

y, U

nive

rsit

y o

f Hyd

erab

ad, I

ndia

)

THU

.2.C

.3X-

ray

scat

ter r

emov

al fo

r art

ifact

free

CT

imag

ing

Jen

s H

anse

n (C

arl Z

eiss

IMT

Gm

bH

)

15h0

0-15

h20

THU

.2.A

.4

Ensu

ring

com

plet

e in

tegr

ity o

f aer

onau

tic c

ompo

-si

te p

arts

than

ks to

a fu

lly a

utom

ated

non

-des

truc

-tiv

e in

spec

tion

solu

tion

and

proc

ess

An

gél

iqu

e R

aud

e (T

esti

a)

THU

.2.B

.4In

tegr

atio

n of

exp

erim

enta

l dat

a in

Mod

el A

ssis

ted

Prob

abili

ty O

f Det

ectio

n co

mpu

tatio

ns

Ch

rist

op

he

Reb

ou

d (C

EA)

THU

.2.C

.4Co

mpu

ted

Tom

ogra

phy

in N

DT

and

Met

rolo

gy fo

r Add

i-tiv

ely

Man

ufac

ture

d Ae

rosp

ace

Com

pone

nts

Do

min

ik M

arti

nse

n (Y

xlo

n In

tern

atio

nal

Gm

bH

)

15h2

0-15

h40

THU

.2.A

.5Fl

exib

le w

edge

pha

sed

arra

y tr

ansd

ucer

s fo

r ins

-pe

ctin

g va

riabl

e-ge

omet

ry o

r com

plex

com

pone

nts

Ph

ilip

pe

Du

mas

- Im

aso

nic

THU

.2.B

.5

Iden

tifica

tion

of K

ey P

erfo

rman

ce In

dica

tors

for S

HM

in

Stru

ctur

es o

f Inc

reas

ing

Com

plex

ity B

ased

on

Artifi

cial

N

eura

l Net

wor

ks

Aad

hik

Aso

kku

mar

(Dre

sden

Inte

rnat

ion

al U

niv

ersi

ty

(DIU

), D

resd

en/G

erm

any)

THU

.2.C

.5

Com

pute

d To

mog

raph

y an

d D

igita

l Rad

iogr

aphy

for

Addi

tive

Man

ufac

turin

g pr

oces

s Q

ualit

y As

sura

nce

and

para

met

ers

defin

ition

C

arlo

s G

alle

gu

illo

s (F

AD

A-C

ATE

C)

15h

40

- 1

6h

10 -

Co

ffee

Bre

ak

SES

SIO

NS

THU

.3.A

.TH

U.3

.B.

THU

.3.C

TOP

ICS

ND

T M

eth

od

s- A

dva

nce

d U

ltra

son

ics

Co

mp

on

ents

Dat

a p

roce

ssin

g &

Sta

tist

ical

met

ho

ds

II

16h1

0-16

h30

THU

.3.A

.1

Imag

ing

of im

pact

dam

age

in s

titch

ed c

arbo

n-fib

er

rein

forc

ed p

last

ic c

ompo

site

s us

ing

lase

r ultr

ason

ic

tech

niqu

e J.

Mro

wka

(AG

H U

niv

ersi

ty o

f S

cien

ce a

nd

Tec

h-

no

log

y)

THU

.3.B

.1X-

ray

digi

tal r

adio

logy

to in

fer w

eldi

ng d

efec

ts d

epth

Em

man

uel

Sir

yab

e (S

afra

n H

elic

op

ter

Eng

ines

)TH

U.3

.C.1

Auto

mat

ic a

naly

sis

of u

ltras

onic

dat

a fo

r lar

ge a

nd c

om-

plex

CFR

P ai

rcra

ft co

mpo

nent

s Ju

lien

Wal

ter

(Cen

tre

tech

no

log

iqu

e en

aér

osp

atia

l,

Can

ada)

16h3

0-16

h50

THU

.3.A

.2Ev

alua

tion

of m

etal

lic b

onde

d pl

ates

with

non

linea

r ul

tras

ound

and

com

paris

on w

ith d

estr

uctiv

e te

stin

g R

ibay

Gu

illem

ette

(CEA

, Lis

t)

THU

.3.B

.2

Elec

trom

agne

tic p

ulse

-indu

ced

acou

stic

test

ing

and

its

appl

icat

ion

to th

e no

n-de

stru

ctiv

e ev

alua

tion

of a

dhe-

sive

bon

ding

bet

wee

n ca

rbon

fibe

r com

posi

te a

nd m

etal

To

shiy

uki

Tak

agi

(To

ho

ku U

niv

ersi

ty)

THU

.3.C

.2D

evel

opm

ent o

f ded

icat

ed c

lass

ifica

tion

tool

s fo

r the

aut

o-m

ated

dia

gnos

tic fr

om n

on-d

estr

uctiv

e te

stin

g da

ta

Ro

ber

to M

iore

lli (C

EA L

ist)


We

lco

me

in t

he

Va

ux

le C

ern

ay

Ab

be

y.

Loca

ted

in t

he

Ch

evr

eu

se v

alle

y in

th

e R

am

bo

uill

et

sta

te-

ow

ne

d f

ore

st, i

s a

n e

nch

an

ted

pla

ce. F

ou

nd

ed

in 1

118

by

a g

rou

p o

f m

on

ks f

rom

Sa

vig

ny

Ab

be

y (i

n M

an

che

) th

e

Va

ux-

de

-Ce

rna

y A

bb

ey

en

joys

mo

re t

ha

n e

igh

t ce

ntu

rie

s

of

his

tory

.

CO

NFE

RE

NC

E D

INN

ER

18h

30

- S

hu

ttle

s tr

ansf

ers

to V

aux

le C

ern

ay

19h

15 -

22

h3

0 -

Gal

a D

inn

er a

t th

e A

bb

aye

of

Vau

x le

Cer

nay

22

h3

0 -

Sh

utt

les

tran

sfer

s b

ack

to;

- th

e S

ymp

osi

um

at

Cen

tral

eSu

pél

ec

- N

ovo

tel S

acla

y

- &

Mer

cure

Mas

sy T

GV

Thu

rsd

ay, N

ove

mb

er 1

4th

, 20

19

16h5

0-17

h10

THU

.3.A

.3

Non

-con

tact

det

ectio

n of

dis

bond

s in

adh

esiv

ely

bond

ed m

etal

lic p

late

s us

ing

lase

r-ex

cite

d ze

ro

grou

p ve

loci

ty L

amb

mod

es

Luka

sz A

mb

rozi

nsk

i (A

GH

Un

iver

sity

of

Sci

ence

and

Tec

hn

olo

gy

in K

rakó

w)

THU

.3.B

.3Su

rfac

e ch

arac

teriz

atio

n us

ing

mul

ti-or

ient

atio

n lig

ht

tech

niqu

e C

lém

ent

Sko

pin

ski (

Fram

ato

me

Inte

rco

ntr

ôle

)

THU

.3.C

.3D

efec

t siz

ing

in g

uide

d w

ave

imag

ing

usin

g a

conv

olut

io-

nal n

eura

l net

wor

k R

ob

erto

Mio

relli

(CEA

-Lis

t)

17h1

0-17

h30

THU

.3.A

.4N

onco

ntac

t las

er-b

ased

ultr

ason

ic d

etec

tion

of

dyna

mic

str

ess

mod

ulat

ed c

rack

s P

eilo

ng

Yu

an (K

ath

olie

ke U

niv

ersi

teit

Leu

ven

)

THU

.3.B

.4Ed

dy-C

urre

nt P

ulse

d Th

erm

ogra

phy

for t

he D

etec

tion

of

Impa

ct D

amag

e on

CFR

P A

bd

ou

laye

Ba

(Nan

tes

Un

iver

sity

)

THU

.3.C

.4

ND

T of

Wel

ds U

sing

Hig

h Sp

eed

Dat

a Co

llect

ion

and

an

Artifi

cial

Neu

ral N

etw

ork

Real

-Tim

e Pr

oces

sing

Sys

tem

D

urin

g th

e W

eldi

ng O

pera

tion

Jera

ld E

. Jo

nes

(En

erg

ynTe

ch, I

nc.

)

17h3

0-17

h50

THU

.3.A

.5

Inno

vativ

e U

ltras

onic

Non

dest

ruct

ive

Test

ing

Tech

-ni

que

for B

ondi

ng Q

ualit

y Ev

alua

tion

B

eng

isu

Yilm

az (U

ltra

sou

nd

Res

earc

h In

stit

ute

,

Kau

nas

Un

iver

sity

of

Tech

no

log

y)

THU

.3.C

.5

On

The

Impr

ovem

ent o

f Hei

ght I

ndic

atio

n M

easu

rem

ent

in W

elds

A

bd

En

no

ur

Bo

uze

nad

(In

stit

ut

de

So

ud

ure

/ L

abo

rato

ire

d’A

cou

stiq

ue

de

l’Un

iver

sité

du

Man

s)

End

of

the

tech

nic

al p

rog

ram

me

- sn

cak

in t

he

exh

ibit

ion

are

a &

dep

artu

res

of

the

shu

ttle

s fo

r th

e C

on

fere

nce

Din

ner


Frid

ay,

No

vem

be

r 15

th, 2

019

8h00

- D

epar

ture

of t

he S

huttl

es fr

om N

ovot

el S

acla

y &

Mer

cure

Mas

sy T

GV

to S

acla

y, N

DT

Aero

spac

e 20

19 S

ympo

sium

.

8h30

- 9h

15 -

PLE

NA

RY

SE

SS

ION

8h

30 -

9h15

: Jo

hn

Ald

rin

- C

om

pu

tati

on

al T

oo

ls

Appl

icat

ions

of M

odel

ing

in A

eros

pace

ND

T: P

ast,

Pres

ent a

nd F

utur

e

9h

15 -

9h

30

- C

off

ee

Bre

ak

SES

SIO

NS

FRI.1

.A.

FRI.1

.B.

FRI.1

.C

TOP

ICS

ND

T M

eth

od

s- M

ob

ile N

DT

Co

mp

on

ents

- C

om

po

site

sM

ater

ials

Ch

arac

teri

sati

on

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 us

ing

2D a

nd 3

D c

ompu

ter v

isio

n H

am

di B

en

Ab

da

llah

(IM

T M

ine

s A

lbi/

Inst

itu

t C

lém

en

t

Ad

er

(IC

A)

FRI.1

.B.1

Adva

nced

ther

mog

raph

ic N

DT

appl

ied

on c

ompo

site

airc

raft

com

pone

nts

Da

nie

l Ch

au

vea

u (

Inst

itu

t d

e S

ou

du

re In

du

stri

e)

FRI.1

.C.1

In S

itu T

herm

ogra

phic

Insp

ectio

n of

Aut

omat

ed

Fibe

r Pla

cem

ent a

t NAS

A La

ngle

y Re

sear

ch C

ente

r

E

liza

be

th D

. Gre

go

ry, P

h.D

. NA

SA

La

ng

ley

Re

sea

rch

Ce

nte

r

9h50

-10h

10FR

I.1.A

.2Ac

cura

te &

Fle

xibl

e So

lutio

n fo

r Non

Des

truc

tive

Test

ing

in A

eros

pace

Indu

stry

Usi

ng R

obot

ised

Sys

tem

M

r Th

om

as

Gra

mb

erg

er

(Fill

Ge

sells

cha

ft m

.b.H

)

FRI.1

.C.2

Mul

ti-fu

nctio

nal p

hase

d ar

ray

ultr

ason

ic im

agin

g: 4

mod

es fo

r be

tter a

naly

sis

Ch

oo

n-S

u P

ark

, Ko

rea

Re

sea

rch

Inst

itu

te o

f S

tan

da

rds

an

d S

cie

nce

, Re

pu

blic

of

Ko

rea

10h1

0-10

h30

FRI.1

.A.3

Ultr

asou

nd N

on D

estr

uctiv

e Te

stin

g of

Sta

ge 8

-10

Spoo

ls

On

Win

g B

ria

n P

rad

ale

t (A

ir F

ran

ce In

du

stri

es

KLM

En

gin

ee

-

rin

g a

nd

Ma

inte

na

nce

)

FRI.1

.B.3

Com

paris

on o

f Adv

ance

d Po

st-P

roce

ssin

g Te

chni

ques

for

Flas

h Th

erm

ogra

phy

for R

apid

ND

T of

CFR

P Ai

rcra

ft Co

mpo

-ne

nt: A

Cas

e St

udy

Ga

éta

n P

oe

lma

n (

Me

cha

nic

s o

f M

ate

ria

ls a

nd

Str

uct

ure

s

(UG

en

t-M

MS

)

FRI.1

.C.3

Use

of m

icro

focu

s X-

ray

syst

em a

nd p

ulse

ther

mog

raph

y to

m

easu

re p

oros

ity c

onte

nt in

to a

eros

pace

com

posi

te p

arts

P

ierr

e S

erv

ais

(N

DT

serv

ice

co

mp

osi

te t

est

ing

, Be

lgiu

m)

10h

30

- 1

0h

45

- C

off

ee B

reak

SES

SIO

NS

FRI.

2.A

.FR

I.2

.B.

FRI.

2.C

TOP

ICS

ND

T M

eth

od

s- P

has

ed A

rray

IIC

om

po

nen

ts -

Co

mp

osi

tes

Mat

eria

ls C

har

acte

risa

tio

n

10h4

5-11

h05

FRI.2

.A.1

Hig

h-Pe

rfor

man

ce U

ltras

onic

Tra

nsdu

cers

bas

ed o

n PM

N-P

T Si

ngle

Cry

stal

s fo

r ND

T of

aer

ospa

ce m

ater

ials

Th

om

as

He

rzo

g (

Fra

un

ho

fer

Inst

itu

te f

or

Ce

ram

ic

Tech

no

log

ies

an

d S

yste

ms

IKTS

)

FRI.2

.B.1

Elec

trom

agne

tic n

onde

stru

ctiv

e in

spec

tion

of fi

ber m

isal

ign-

men

t in

CFRP

with

dire

ctio

nal e

ddy

curr

ent

Hir

oyu

ki K

osu

keg

aw

a (

Inst

itu

te o

f Fl

uid

Sci

en

ce, T

oh

oku

Un

ive

rsit

y)

FRI.2

.C.1

Cont

ribut

ion

of u

ltras

onic

ND

T to

the

asse

ssm

ent o

f the

eff

ect o

f out

-of-p

lane

wav

ines

s de

fect

s on

the

mec

hani

cal

stre

ngth

of t

herm

opla

stic

com

posi

te m

ater

ials

C

am

ille

Tro

ttie

r (O

ne

ra)


IND

US

TRIA

L V

ISIT

S

Pa

rtic

ipa

nts

will

ha

ve t

he

ch

oic

e b

etw

ee

n 4

ind

ust

ria

l sit

es

to v

isit

. Ea

ch v

isit

s w

ill la

st b

etw

ee

n 2

hO

O &

2h

30

. Sh

utt

les

tra

nsf

ers

are

org

an

ize

d, a

nd

will

dro

p t

he

pa

rtic

ipa

nts

off

on

th

e w

ay

ba

ck a

t O

rly

Air

po

rt, w

ith

a s

top

at

Ce

ntr

ale

Su

pé

lec.

At

the

Air

po

rt o

f O

rly,

pa

rtic

ipa

nts

ca

n fi

nd

diff

ere

nt

op

tio

ns

for

the

ir t

rave

l co

nn

exio

ns:

• A

ir F

ran

ce B

us

shu

ttle

s to

Ro

issy

Ch

arl

es

de

Ga

ulle

air

po

rt

• P

ub

lic t

ran

spo

rt: O

rly

Va

l, R

ER

• Ta

xi.

On

ce r

eg

iste

red

, yo

u w

ill r

ece

ive

by

em

ail

the

re

gis

tra

tio

n li

nk

for

the

vis

it o

f yo

ur

cho

ice

.

Ple

ase

, co

nsi

de

r th

e t

ime

tab

les

wit

h a

pp

rox

arr

iva

l ho

urs

fo

r yo

ur

flig

hts

bo

oki

ng

.

Frid

ay, N

ove

mb

er 1

5th

, 20

19

11h0

5-11

h25

FRI.2

.A.2

Adva

nced

DD

F fo

r ins

pect

ion

of th

ick

Alum

iniu

m a

nd

Tita

nium

mat

eria

ls

Xa

vie

r H

arr

ich

(S

oco

ma

te In

tern

ati

on

al)

FRI.2

.B.2

Ultr

asou

nd d

efec

t det

ectio

n in

thic

k co

mpo

site

s w

ith o

ut-o

f-pl

ane

wav

enes

s C

ui F

an

gse

n (

Inst

itu

te o

f H

igh

Pe

rfo

rma

nce

Co

mp

uti

ng

,

A*S

TAR

, Sin

ga

po

re)

FRI.2

.C.2

Non

-Des

truc

tive

Mag

netic

Tes

ting

of th

e Ph

ysic

al a

nd M

echa

-ni

cal P

rope

rtie

s of

Mis

sion

-Crit

ical

Mou

ntin

g Co

mpo

nent

s in

Av

iatio

n Te

chno

logy

S

erg

ey

G. S

an

do

mir

ski (

Join

t In

stit

ute

of

Me

cha

nic

al

En

gin

ee

rin

g o

f th

e N

AS

of

Be

laru

s, M

insk

, Be

laru

s)

11h2

5-11

h45

FRI.2

.A.3

Dyn

amic

trac

king

of p

hase

d-ar

ray

prob

e an

d 3D

C-s

can

reco

nstr

uctio

n fo

r in-

serv

ice

insp

ectio

n of

CFR

P ai

rcra

fts

com

pone

nts

Ale

xan

dre

Be

au

sole

il (C

en

tre

te

chn

olo

giq

ue

en

aé

rosp

ati

ale

)

FRI.2

.B.3

Ad-h

oc s

olut

ions

for u

ltras

onic

insp

ectio

n of

radi

i in

clos

ed

com

posi

te s

truc

ture

s S

erg

io G

on

zále

z (C

ATE

C-A

dva

nce

d C

en

ter

for

Ae

rosp

ace

Tech

no

log

ies)

FRI.2

.C.3

Mat

eria

ls F

atig

ue C

hara

cter

izat

ion

thro

ugh

Feat

ure

Extr

ac-

tion

from

The

rmog

raph

ic Im

ages

A

lexa

nd

r Lo

zak

(Sa

arl

an

d U

niv

ers

ity,

Sa

arb

rück

en

/Ge

r-

ma

ny)

11h4

5-12

h05

FRI.2

.A.4

Insp

ectio

n of

Com

posi

te L

amin

ate

Mat

eria

l usi

ng A

dap -

tive

Focu

sing

Tec

hnol

ogy

Eti

en

ne

Gro

nd

in (

Oly

mp

us)

FRI.2

.B.4

Full

wav

e fie

ld s

igna

l pro

cess

ing

tech

niqu

es fo

r ND

T of

CFR

P ai

rcra

ft pa

nel:

A c

ase

stud

y Jo

ost

Se

ge

rs (

Me

cha

nic

s o

f M

ate

ria

ls a

nd

Str

uct

ure

s

(UG

en

t-M

MS

), G

he

nt

Un

ive

rsit

y)

FRI.2

.C.4

Mic

ro-m

agne

tic n

on-d

estr

uctiv

e te

stin

g: a

eros

pace

bea

ring

appl

icat

ion

Be

nja

min

Du

cha

rne

(LG

EF)

12h0

5-12

h25

FRI.2

.A.5

Mod

elin

g an

d In

spec

tion

Chal

leng

es fo

r Eva

luat

ion

of

Com

posi

te M

ater

ials

and

Str

uctu

res

De

bo

rah

Ho

pki

ns,

Be

rcli

FRI.2

.B.5

Lase

r-ge

nera

ted

shoc

k w

aves

for N

DE

: app

licat

ion

to s

truc

-tu

ral b

ondi

ng a

nd d

elam

inat

ion

of c

ompo

site

mat

eria

ls

Ma

thie

u D

uco

uss

o (

Sa

fra

n G

rou

p)

FRI.2

.C.5

Ultr

ason

ic g

uide

d w

aves

as

a to

ol fo

r the

eva

luat

ion

of e

ffec-

tive

elas

tic m

odul

i of l

amin

ate

com

posi

te m

ater

ials

A

rte

m E

rem

in (

Inst

itu

te f

or

Ma

the

ma

tics

, Me

cha

nic

s a

nd

Info

rma

tics

, Ku

ba

n S

tate

Un

ive

rsit

y, K

rasn

od

ar,

Ru

ssia

)

End

of

the

Sym

po

siu

m p

rog

ram

me

and

dep

artu

res

for

ind

ust

rial

vis

its


SA

FRA

N A

IRC

RA

FT E

NG

INE

S

ST Q

UEN

TIN

EN

YVE

LIN

ES

12h3

0 Sh

uttle

dep

artu

re w

ith L

unch

on

Boar

d

13h3

0 - 1

5h30

Vis

it of

the

site

17h

30

ap

pro

x. a

rriv

al a

t O

rly

Air

po

rt

AIR

FR

AN

CE

En

gin

e P

art

Re

pa

ir C

en

ter

ELAN

COU

RT

12h3

0 Sh

uttle

dep

artu

re w

ith L

unch

on

Boar

d

13h3

0 - 1

5h30

Vis

it of

the

site

17h

30

ap

pro

x. a

rriv

al a

t O

rly

Air

po

rt

AR

IAN

E G

RO

UP

LES

MU

REAU

X

12h3

0 Sh

uttle

dep

artu

re w

ith lu

nch

on B

oard

14h0

0 - 1

6h00

Vis

it of

the

site

18h

30

ap

pro

x. a

rriv

al a

t O

rly

Air

po

rt

SY

NC

HR

OTR

ON

SO

LEIL

PARI

S-SA

CLAY

12h1

5 Lu

nch-

snac

k at

Cen

tral

eSup

élec

13h1

5 Sh

uttle

dep

artu

re

13h3

0 - 1

5h30

Vis

its o

f the

site

17h

00

ap

pro

x. a

rriv

al a

t O

rly

Air

po

rt

Frid

ay, N

ove

mb

er 1

5th

, 20

19

29

ABSTRACTS

WEDNESDAY 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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ABSTRACTS

THURSDAY 14TH


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.

KEYWORDS

3d 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.

KEYWORDS

SHM | 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.

KEYWORDS

Structural 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.

KEYWORDS

Composite 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

ABSTRACTS

A 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.

KEYWORDS

NDT/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.

KEYWORDS

Microwave 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.

KEYWORDS

X-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.

KEYWORDS

Ultrasonic 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.

KEYWORDS

Electromagnetic 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 IMPACT

DAMAGE 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.

KEYWORDS

SHM | 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.

KEYWORDS

PAUT | 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.

KEYWORDS

NDT | 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

KEYWORDS

Composite | 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.

KEYWORDS

Composites | 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.

KEYWORDS

Ultrasonics | 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.

KEYWORDS

Ultrasonics | 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).

KEYWORDS

Composite 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.

KEYWORDS

Out-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).

KEYWORDS

Composites | 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.

KEYWORDS

Ultrasonic 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.

KEYWORDS

Thermography | 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.

KEYWORDS

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

135

PRESENTING

AUTHORS

November 13 to 15, 2019136

PRESENTING AUTHORS

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 Fang

FRI.2.B.2 Fangsen Cui

THU.2.C.5 Galleguillos Carlos

THU.1.A.6 Gaverina Ludovic

WE.2.C.1 Ghibaudo Olivier

FRI.2.C.5 Glushkov Evgeny

FRI.2.B.3 Gonzalez Sergio

FRI.1.A.2 Gramberger Thomas

FRI.1.C.1 Gregory Elizabeth D.

FRI.2.A.4 Grondin Etienne

WE.2.B.1 Guemes Alfredo

THU.3.A.2 Guillemette Ribay

WE.2.C.5 Harman David

FRI.2.A.2 Harrich Xavier

THU.2.C.3 Hansen Jens

FRI.2.A.1 Herzog Thomas

FRI.2.A.5 Hopkins Deborah

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A TO H

November 13 to 15, 2019137

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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EXHIBITION

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