SARISTU Newsletter
04/12/2013
Issue: 04
Work Progress &
Achievements
2
Mid-Term Review
Meeting
15
SARISTU Around the Globe
16
SARISTU in Academia
& Science
17
SARISTU in Upcoming
Events
25
SARISTU Partners 26
In this Issue:
“...addressing aircraft weight
and operational cost reductions,
as well as an improvement in
the flight profile specific
aerodynamic performance”
Editorial
Dear Reader,
SARISTU has completed its first two years out of the four year project
duration. While the key objectives for the first year of the project fo-
cused around the initiation of the individual working groups, process-
es, process refinement and, above all, the collation and development
of the required specifications and initiating the first test series and
top level design requirements, the second year of the project fo-
cused on very different activities. The key activities during this period
can best be grouped into two major categories. In particular, with
respect to the wing integration, the majority of the work conducted
focused on design activities, both non-specific and specific, the con-
duct of specific demonstrator design activities as well as the launch
and conduct of the individual scenarios test campaigns. In addition,
individual scenarios even had to perform the design, manufacturing
and implementation of a pilot manufacturing line for the integration
of Carbon Nanotubes into prepreg material. On the other hand, and
in particular in regards to the fuselage integration, progress on the
application scenarios physical integration test campaigns was at the
forefront.
As such, overall progress is fully meeting expectations as is perhaps
best be highlighted by the 77 Scientific and other publications al-
ready made by the consortium partners within the first half of the
project.
Piet-Christof Woelcken
Project Coordinator
AIRBUS Operations GMBH
Start Date 2011-09-01
Duration 48 months
Number of partners 64
Project Cost 50.95 M EURO
Project Funding 32.43 M EURO
URL www.saristu.eu
Page 2
Of particular importance during the second year of
the project was the progression on the specific de-
sign of the wing integration demonstrator to be
“flown” in TsAGI’s T-104 wind tunnel in 2015. Re-
quiring a significant coordination between the Inte-
gration Scenario and the feeder Application Sce-
nario’s (addressing the morphing components on
the leading edge, trailing edge and winglet trailing
edge as well as the Structural Health Monitoring
Scenarios), the SARISTU consortium has achieved
the near completion of the detailed design of this
major test piece.
Furthermore, of particular importance was the
sufficient maturity of the design to initiate the part
manufacture right at the start of the third year of
the project. This achievement would not have been
possible without the individual Application Scenari-
os’ excellent progress. In particular, progress was
performed in narrowing down the different bird
strike solutions for the leading edge spar by simu-
lation. Moreover, the manufacture of two out of
the four planned dummy structures for system in-
tegration trials for the trailing edge was also per-
formed. Additionally, the system safety and robust-
ness assessment for the wingtip active trailing edge
was also performed. Similarly, initial test cam-
paigns resulted in the refinement of fibre optic
tapes for easy and rapid integration and algorithm
maturation for acoustic damage detection.
On the fuselage integration, the test campaigns for
acoustic damage detection and assessment are
progressing fast with a range of manufacturing
concerns already addressed satisfactorily. In addi-
tion, simulations indicating the key parameters of
importance during multi-site damage events have
been performed. The associated test results have
led to a down selection of suitable solutions for
damage indicating surfaces. Also, the manufactur-
ing trials have been completed for co-bonded me-
tallic strips for low cost Electrical Structure Net-
work integration. Finally, the initial test campaign
for different Carbon Nanotube integration routes
has been completed.
Page 2
Conformal Morphing Application Scenario 1 : Enhanced Adaptive Droop Nose
Page 2 Page 3
Conformal Morphing Application Scenario 1 : Enhanced Adaptive Droop Nose
The goal of AS01 is a three dimensional, large scale
and enhanced morphing wing leading edge that
allows for integration in the morphing wing of In-
tegration Scenario 12 (IS12). The focus in the sec-
ond year of the project was on the finalization of
the pre-design and the detailed design of the lead-
ing edge part for the wind tunnel demonstrator.
In particular, during the second year of the project,
the pre- and detailed design was focused on the
three relevant test campaigns for the enhanced
adaptive leading edge, planned in AS01/IS12
(Wind Tunnel Test (IS12), Structural Ground test
(AS01), and Bird Strike Test (AS01)). All tests were
performed using the outboard segment of the
SARISTU wing.
It is worth mentioning that all three test sections
should be arranged so that one tooling for manu-
facturing of the subsequent test structure could be
used for manufacturing of the leading edge skin.
The pre-design/design included mainly the itera-
tive process of finite element analysis and the 3D
CAD design of skin and kinematical mechanism.
A major outcome during the second year of the
project was the experimental results for Single
Discipline (Glass Fiber Prepreg HexPly913), and
Combined Disciplines (LSP-Tests, Coating Tests,
Bending Tests, and Manufacturing Tests). Finally,
another important outcome was the definition of
instrumentation and test program for wind tunnel
and ground test.
Conformal Morphing Application Scenario 2 : Adaptive Structural Tailoring of a Trailing Edge
Page 4
Conformal Morphing Application Scenario 3 : Wingtip Morphing Trailing Edge
The adaptive trailing edge device (ATE) is aimed at
maximizing wing aerodynamic performance in
cruise condition with the ultimate goal of a 3% re-
duction in fuel consumption. L/D ratio is the refer-
enced parameter to catch the performance varia-
tions, kept to its optimal value while weight and
angle of attack vary. Because span-wise variations
can be also attained, design weight decrease
through Root Bending Moment reduction could be
also evaluated. The focus during the second year
of the project was on the finalization of the Adap-
tive trailing Edge design including the structural
layout, the actuation system, the morphing skin,
the sensor system and the control system.
Numerical methods combined with rational design
criteria have been implemented to assess the pre-
liminary sizing of the ATE primary structure. A mul-
ti-disciplinary approach was adopted to efficiently
match design specification while assuring: i)
smooth rigid-body kinematic of the mechanisms
enabling the structural morphing, ii) the absence
of any failure at ultimate load condition, and iii)
preliminary estimate of the flutter clearance for
the coupled system composed by the A/C wing
and the actuated trailing edge device. A detailed
layout of ATE was finally drawn on the base of pre-
liminary sizing outcomes.
Conformal Morphing Application Scenario 3 : Wingtip Morphing Trailing Edge
In AS03, a winglet with an active trailing edge
(WATE) is developed. Winglets are intended to im-
prove the aircraft’s efficiency aerodynamically but
simultaneously they introduce significant loads to
the outer wing structure. AS03 focuses on the de-
velopment of a full scale demonstrator with the
additional objective of a certifiable WATE design
according to the EASA CS 25 certification require-
ments for large aeroplanes.
Based on a failure hazard assessment,
failure scenarios were investigated and their se-
verities classified. Relevant failure conditions were
investigated by fault tree analysis (in order to com-
pute probabilities of failure occurrence and obtain
design guidelines for the WATE). Main results from
this analysis were that a 5-hinge concept is re-
quired as well as the computation of factors of
safety are required for the computation of ulti-
mate loads for relevant load cases, e.g., continua-
tion of flight with hinge failure.
Page 5
Structural Health Monitoring (SHM) Application Scenario 4 : Fibre optic (FO) based Monitoring System
Page 6
Structural Health Monitoring (SHM) Application Scenario 5 : Wing damage detection employing guided waves technique
The strain monitoring of structural parts of an air-
craft is a task leading to significant opportunities. A
good real-time understanding of the structure dur-
ing flight could contribute to the reduction of drag
losses during flight, decrease in aircraft inspection
times and, at a later stage, improvement of the
safety margins used in the design process. This can
be achieved by monitoring the strains at specific
areas of the aircraft during flight. The objectives of
AS04 are the design, optimisation and implementa-
tion of a strain monitoring system, based on a net-
work of fibre optic sensors. These sensors will be
integrated into the structural parts during the man-
ufacturing phase.
During the second year of the project partners in-
volved in AS04 kept on working on the processes to
be used for the manufacturing of the selected
structural parts with an integrated FO monitoring
system. In addition, the application scenario defi-
nition was completed and a preliminary sensor net-
work was identified. The identified sensor network
was capable of performing the respective monitor-
ing task of each application scheme. Fur-
thermore, the first algorithm was developed
for the damage detection target while the second
one for the shape identification. Also, a preliminary
analysis was conducted regarding strain data man-
agement and data filtering, storage and position
identification of the FBG measurements. In regards
to the strain monitoring task, the required FE anal-
ysis of all monitored parts has recently started in
order to produce the necessary data for PCA and
for the rest of the developed algorithms. Finally,
the manufacturing and test campaigns started and
the following were achieved:
Completion of the ribbon tape development,
Identification of the primary and alternative
connector to be used with the ribbon,
Identification of integration methods of rib-
bon tape to the structure, and
Proof of the repair ability of such a monitor-
ing system in coupon scale.
Structural Health Monitoring (SHM) Application Scenario 5 : Wing damage detection employing guided waves technique
The application scenario AS05 combines state-of-
the-art numerical and experimental approaches
aimed at the simulation and experimental valida-
tion of guided ultrasonic wave propagation and
analysis in wing’s CFRP structural components. The
final target of AS05 is design, manufacturing and
implementation of a composite wing damage de-
tection system which will be based on guided ul-
trasonic wave measurements techniques. This
wing damage detection system will be able to de-
tect Barely Visible Damages (BVID) and Visible
Damages (VID) on reinforced skin of a composite
wing. The damage detection system is expected to
reduce drastically the inspection time of the se-
lected part if compared to available NDT. The ex-
pected benefits include reduction of life cycle
costs related to maintenance and inspections,
through reduced maintenance time and/or inspec-
tion intervals.
During the 2nd year of the project the main activi-
ties carried out which have been finalised include
impact calibration campaign, damage analysis and
sensors selection. Finally, within the second period
much effort and time have been spent on flat pan-
els in order to achieve the damage typology and
dimensions.
Page 7
Structural Health Monitoring (SHM) Application Scenario 6 : Impact assessment using integrated ultrasonic sensors
Within this application scenario, AU (Acousto Ul-
trasonic) damage assessment approach for Door
Surrounding Structures will be verified in order to
achieve operational cost reduction (up to 2%) for
CFRP fuselage. The operational costs shall be re-
duced by reduction of aircraft downtime, by faster
damage assessment after visual indication, and a
simplified inspection process.
Within the second year of the project,
significant progress has been made regard-
ing the cobonding process, the sensor network
connection, and the damage detection. Main work
during this period was dedicated to the mechani-
cal testing. While, one of the significant findings
during this period was that the use of PZT / guided
waves based technique for damage detection on a
real-life structure using simple SHM algorithms is
possible and very promising.
Page 8
Structural Health Monitoring (SHM) Application Scenario 7 : Multi-side damage assessment of CFRP structures
Structural Health Monitoring (SHM) Application Scenario 7 : Multi-side damage assessment of CFRP structures
Page 9
The main objective of AS07 is to develop a predic-
tion method for multi side impact events. During
the 2nd year of the project, one of the main activi-
ties was the design and manufacturing of the
adaptor for the impact fixture. Also, the optimiza-
tion design of the SAI (Shear After Impact) test fix-
ture was performed. Moreover, an additional pan-
el impact fixture and a design of anti-buckling sup-
ports for the curved stiffened panels were includ-
ed.
The FE models of coupons and curved stiffened
panel for impact and CAI (Compression After
Impact) study have been developed:
i) to carry out trial impacts on coupons (to select
impact critical scenarios), and
ii) to design curved stiffened panels.
In addition, a non disturbance concept has been
developed and a POD (Probability Of Detection)
and durability on coupons levels have been evalu-
ated by the Airbus Operations GmbH and the Uni-
versity of Stuttgart (UNIST). Also, UNIST has devel-
oped a laser drilling process for industrial applica-
tion. Finally, significant progress has been per-
formed on: the prediction damage method, the
campaign of test, as well as the damage detection
approach.
Structural Health Monitoring (SHM) Application Scenario 8: Sensitive coating for impact detection
Page 10
Multifunctional Materials Application Scenario 9 : Enhancement of primary structure robustness by improved
damage tolerance
The objective in AS08 is to ease impact detection
on composite structures by improving the BVID
threshold. This would be one feature that may en-
able a further optimization of aircraft design by
reducing the structure thickness margin and there-
by save weight.
During the 2nd year of the project, chemical com-
patibility between the revealing agents and the
matrix compounds has really been a problem.
Clearcoat proved to be adjustable in terms of im-
pact marking capabilities with a thickness around
50μm, and the compatibility with piezochromic
pigments has been demonstrated. Sol-gel matrix
seems more adapted to UAVR mesoporous nano-
containers containing Umbelliferon and its lay-
er can be very thin (<20μm).
Currently, in terms of sensors:
Piezochromic pigments phase threshold has
been modified to obtain low pressure and
high pressure particles.
Mesoporous nanocontainers with umbellifer-
on have the advantage to be stable in time
and temperature, and be small in size
(~0.1μm). The impact revelation will be un-
der UV light only.
Microcapsules resistance and size have been
improved to cope with the requirements. At
the current stage of the project, it is not pos-
sible to identify the best solution in terms of
impact revelation yet; the next 6 months will
be determinant and challenging.
Within the AS09 scenarios, partners are develop-
ing and investigating means by which the damage
tolerance of carbon fibre reinforced polymer
(CFRPs) can be improved. The goal is to see an im-
provement in damage tolerance which in turn can
produce a reduction in weight at the aircraft struc-
ture level. In addition, the aim of AS09 is to take
nanotechnology to a higher Technology Readiness
Level (TRL) within CFRP’s used for Aerospace.
The technologies investigated within AS09 have
shown a marked improvement in mechanical
properties compared to the reference material
values. Overall, it can be concluded that alt-
hough there are still possible improvements to be
made, the AS09 test campaign has been proven
successful. It is worth mentioning that for most of
the developments, a significant reduction in dam-
age area after a 30J impact could be witnessed
compared to the baseline material. The only ex-
ception to this was the process of spray-infusion
studied by EADS IWG. Further investigations are
needed to better understand the results achieved
from the spray infusion technology. The reductions
in damage area were translated to real world im-
provements in compression after impact proper-
ties.
Multifunctional Materials Application Scenario 9 : Enhancement of primary structure robustness by improved
damage tolerance
Page 11
Page 12
Integration Scenarios Integration Scenario 12 : Wing Assembly, Integration & Testing
Within the AS10, the goal is to take forward to
higher maturity level various technologies and
methods that realise measureable improvements
in CFRP electrical conductivity and weight reduc-
tions. In addition, AS10 will validate the manufac-
turability of panel sized structures using nanorein-
forced resins and the ability to integrate these in
major assemblies, improving damage tolerance
and supporting low level ESN functionalities. Out
of plane electrical conductivity improvements are
expected to reduce the installation cost of the
Electrical Structure Network by up to 15%.
During the 2nd year of the project, specifications
based on representative fuselage section have
been fixed. The carrier material for the
MWCNTs have been identified and MWCNT con-
tent and inclusion process have been optimised to
produce a more conductive thermoplastic.
In addition, laminates with improved Z-
conductivity and initial models for lightning strike
effects on MWCNT doped CFRP have been pro-
duced and correlated with published literature.
The design for metallic strips has been fixed, while
electrical, mechanical and thermal simulations
have been conducted for strips with good results.
Multifunctional Materials Application Scenario 10 : Improvement of the electrical isotropy of composite
structures
Integration Scenarios Integration Scenario 12 : Wing Assembly, Integration & Testing
Page 13
The objective of IS12 is completion of the wing de-
monstrator design. The demonstrator is aimed at
ground test and low velocity WT tests. It is worth
mentioning that SHM and shape monitoring and
control system will be also installed. The Wing De-
monstrator is a typical aerostructure obtained
through the assembly of several major items. Each
of these major items is a sub-assembly supposed
to feed the above one. For this reason, the main
assembly has been structured just like a typical
product structure organized by levels, from the
bottom to the top. There’s a Main wing Box (WB),
made up by spars, ribs, angles/brackets, skins and
closure ribs (root & tip). Attaching to this, we find
major items like Leading Edge (L/E), Trailing edge
(T/E), WingLet, and interface with Wing Tunnel
test rig, as well as Ground test strong-back.
During the 2nd year of the project, the Value pa-
rameters have been defined and have been linked
to the definition of benefit of morphing solutions
vs. conventional solution and validation foreseen
method. High level description of relevant risks
have been performed and have been linked to ver-
ification / validation foreseen method and guessed
technical risk level. A risk analysis dedicated to
lower level process has been started, defining the
associated risk level and associated risk reduction
action for the critical project sub tasks. The 3D op-
timization of wing morphing airfoil design consid-
ering all concepts at wing level is in progress. At
the same time, the multi field structural stick ele-
ments have been implemented. Finally, the test
for aero-elastic analysis has been completed.
Integration Scenarios Integration Scenario 13 (IS 13) : Fuselage Assembly, Integration & Testing
Page 14
Integration Scenario 13 (IS13) takes the most
promising technologies from Application Scenarios
04, 06, 07, 08, 09 and 10 and clusters them for in-
tegration into generic fuselage demonstrators.
As activities only officially began in month 22, IS13
has, so far, produced limited results. Within the
last 12 months, the key coupon level test cam-
paigns have yielded further data for use in prelimi-
nary benefit analysis. These data cover both
Technology performance (e.g., material improve-
ments due to carbon nanotube (CNT) inclusions),
as well as the effect on process times (e.g., the in-
clusion of sensor networks). In addition, the
testing, together with further consultation with
experts, has highlighted areas requiring further
investigation. Finally, modelling and technical
drawing preparation for the stiffened lower panel
started in M22 according to the reference geome-
tries defined.
Page 15
The SARISTU Consortium conducted successfully
the SARISTU Mid-Term Review Meeting on the
24th, 25th and 26th of September 2013 at the Uni-
versity of Naples Federico II in Naples, Italy. The
meeting was chaired by the Project Coordinator,
Piet Wölcken, with the support of the Project
Management Office and participants from all part-
ners.
The meeting began with the welcome speech of
the Project Coordinator and a presentation on the
overall status. During the 1st day afternoon ses-
sion the dissemination activities performed within
the second year of the project were presented, as
well as the status and progress of the Integration
Scenario 12 (Wing Assembly, Integration and
Testing) and Integration Scenario 13 (Fuselage As-
sembly, Integration and Testing). The second day
began with the progress and status of all Applica-
tion Scenarios and was completed with a feedback
session from the EU-Project Officer and the Asses-
sors. On the third day individual technical Scenario
Workshops were performed in order to define the
next steps and discuss a detailed planning for the
upcoming months.
During the three day meeting, the very positive
progress performed within all Scenarios was pre-
sented and first demonstrator containing SARISTU
research results was exposed. The highlights in-
clude the positive and creative ambiance of the
meeting and the great participation and extremely
high level of involvement of all SARISTU partners.
In addition, participants were extremely encour-
aged by the constructive discussions and the posi-
tive outcomes of the meeting. Overall, SARISTU
activities are in their majority very well on track
with most of the objectives being successfully
achieved. Most importantly, SARISTU’s external
Assessors as well as the project’s EU Officer ex-
pressed their satisfaction with the progress and
very high scientific quality presented.
Page 16
From the beginning of the project, 77 SARISTU
related dissemination activities have been
performed, 39 of which were performed dur-
ing the last six months. In this period, SARISTU
related information was published in 2 Jour-
nals and 16 Conferences and Workshops. In
addition, SARISTU related information was
published in websites, master theses, and
partners’ newsletters.
S A R I S T U Around the
Globe
Τhe dissemination actions performed so far
have resulted in an increased awareness of
the SARISTU project in the European Aero-
nautical Industry, the European Scientific
Community and Academia, as well as in the
European general public. At least 11,000
“SARISTU followers” have received at least once an electronic notification of the SARISTU project and
on average 2,600 unique website visits (almost 70% loyal-returning visitors) and 11,000 page views are
performed per year.
It is estimated that several thousands of engi-
neers and scientists throughout Europe are
aware of the project and of its main objectives,
achievements and news, having received at least
once a printed or electronic notification of
SARISTU.
in Academia & Science
S A R I S T U
This work deals with the design of the actuation
mechanism transmitting the motion from the
actuator to the rib segment in order to realise the
target optimal shape.
MasterThesis
on
Multi-Site Damage Assessment of CFRP
Panels – A Validated Finite Element Analysis
Supervised by Tulug Pince (ALTRAN)
and
conducted by Julian Guehrs (ALTRAN)
MasterThesis
on
Actuation System for a Morphing Trailing
Edge Device
Conducted by Domenico Flauto
University of Palermo
Supervised by Ignazio Dimino
CIRA
This work aims to contribute to the optimal
integration of SHM systems by determining the
influence of CFRP impact damage variations on the
residual strength, placing special emphasis on
delamination
L. Maio, E. Monaco, F. Ricci & L. Lecce
University of Naples Federico II
participated in the
17th International Conference on Composite
Structures (ICCS17)
held in Porto, Portugal
on the 17th of June 2013
and made a presentation entitled
“Ultrasonic Wave propagation in composite
laminates by numerical simulation”
Mihail Lilov
Fraunhofer LBF
participated in the
10th International Conference on Damage
Assessment of Structures
held in Dublin, Ireland
between 8th and 10th on July 2013
and made a presentation entitled
“Experimental Investigation on Improving
Electromechanical Impedance based Damage
Detection by Temperature Compensation”
Page 17
Page 18
A. Perelli, L. De Marchi and Marzani from the University
of Bologna & S. Freear from the University of Leeds
participated in the 9th International Workshop on Structural
Health Monitoring held in Stanford, California, USA between
the 10th and 12th of September 2013 and made a presentation
entitled “Compressive Sensing for Damage Detection in
Composite Aircraft Wings”
& Science
S A R I S T U
L. De Marchi , A. Perelli, N. Testoni, A.
Marzani, D. Brunelli & L. Benini
University of Bologna
participated in the
9th International Workshop
on Structural Health Monitoring
held in Stanford, California, USA between the
10th and 12th of September 2013
and made a presentation entitled
“A small, light and low-power passive node
sensor for SHM of composite panels”
V. Cokonaj, A. Alcaide, J.P. Solano, G.
Aranguren, P. M. Monje, E. Barrera,
M. Ruiz & R. Meléndez
AERNNOVA Engineering Solutions Iberica S.A.
participated in the 9th International Workshop
on Structural Health Monitoring
held in Stanford, California, USA between the
10th and 12th of September 2013
and made a presentation entitled
“Verification tests of integrated Phased Array
transducer - PhA III”
V. Cokonaj, A. Alcaide, G. Aranguren, P. M. Monje,
E. Barrera M. Ruiz & R. Meléndez
AERNNOVA Engineering Solutions Iberica S.A.
participated in the 9th International Workshop on Structural
Health Monitoring held in Stanford, California, USA between the
10th and 12th of September 2013 and made a presentation
entitled “Structural health monitoring during assembly of
aerospace structures”
Page 19
E. Barrera, M. Ruiz, R. Meléndez, N. Fernández,
V. Cokonaj, G. Aranguren & P. M. Monje
AERNNOVA Engineering Solutions Iberica S.A.
participated in the 9th International Workshop on Structural
Health Monitoring held in Stanford, California, USA between
the 10th and 12th of September 2013 and made a presentation
entitled “Multiple PAMELA SHM™ system for automated SHM
control during fatigue tests of aircraft structures”
& Science
S A R I S T U
Z. Sharif Khodaei (ICL), M. H. Aliabadi (ICL),
A. Apicella (Alenia) &
U. Heckenberger (EADS-D)
participated in the 9th International Workshop
on Structural Health Monitoring
held in Stanford, California, USA between the
10th and 12th of September 2013
and made a presentation entitled
“Structural Health Monitoring of Composite
Wing Box”
M. Bach (EADS D), N. Dobmann (EADS D),
B. Eckstein (EADS D), M. Moix Bonet (DLR) &
C. Stolz (EADS D)
participated in the 9th International Workshop
on Structural Health Monitoring
held in Stanford, California, USA between the
10th and 12th of September 2013
and made a presentation entitled
“Reliability of co-bonded piezoelectric sensors
on CFRP structures”
Julián Sierra-Pérez & Alfredo Güemes
Universidad Politecnica de Madrid
participated in the 9th International Workshop on Structural
Health Monitoring held in Stanford, California, USA between the
10th and 12th of September 2013 and made a presentation
entitled “Damage detection at an aluminum beam from discrete
and continuous strain measurements”
Page 20
Marco Magnifico, Rosario Pecora, Francesco Amoroso
& Leonardo Lecce
University of Naples Federico II
participated in the 6th ECCOMAS Thematic Conference
on Smart Structures and Materials – SMART 2013 held
in Torino, Italy between the 24th and 26th of June 2013
and made a presentation entitled “Trade-off flutter
analysis of a morphing wing trailing edge”
& Science
S A R I S T U
I. Dimino, M. Schüller, A. Gratias
& D. Flauto
Centro Italiano Ricerche Aerospaziali SCPA
participated in the 6th ECCOMAS Thematic Conference
on Smart Structures and Materials – SMART 2013 held
in Torino, Italy between the 24th and 26th of June
2013 and made a presentation entitled “Adaptive
G. Diodati, A. Concilio
Centro Italiano Ricerche Aerospaziali
SCPA
participated in the
6th ECCOMAS Thematic Conference
on Smart Structures and Materials –
SMART 2013 held in Torino, Italy
between the 24th and 26th of June
2013 and made a presentation
entitled “Actuation system
requirements for morphing wing TE”
P. Michaelides
NASTECH SRL – Novel Aerospace Technologies
participated in the 6th ECCOMAS Thematic Conference
on Smart Structures and Materials – SMART 2013 held
in Torino, Italy between the 24th and 26th of June 2013
and made a presentation entitled “Development of
guided wave pitch-catch mode based structural health
monitoring system for aerospace structures simulation
study”
Alessandro De Gaspari & Sergio Ricci
Politecnico di Milano
participated in the 6th ECCOMAS
Thematic Conference on Smart
Structures and Materials – SMART
2013 held in Torino, Italy between
the 24th and 26th of June 2013 and
made a presentation entitled “A
Parametric Framework for the Design
of Morphing Wings”
Paulina Latko, Rafał Kozera
& Anna Boczkowska
Technology Partners Foundation
C. Heinen (EADS IW-D), A. Wildschek (EADS
IW-D) & M. Herring (EADS IW-UK)
participated in the
International Forum for Aeroelasticity and
Structural Dynamics
held in Bristol, UK
between the 24th and 27th of June 2013
and made a presentation entitled
“Design of a Winglet Control Device for Active
Load Alleviation”
Paulina Latko, Rafał Kozera
& Anna Boczkowska
Technology Partners Foundation
participated in the
Third International Symposium “Frontiers in
Polymer Science
held in Sitges, Spain
between the 21st and 23rd of May 2013
and made a presentation entitled
“Polymer based Nanocomposites for
Aerospace Industry”
Paulina Latko, Rafał Kozera
& Anna Boczkowska
Technology Partners Foundation
participated in the
Austrian – Slovenian Polymer Meeting BLED
held in Bled, Slovenia
between the 3rd and 5th of April 2013
and made a presentation entitled
“Polymer based Nanocomposites for
Aerospace Industry”
participated in the
29th International Conference of the Polymer
Processing Society
held in Nuremberg, Germany
between the 15th and 19th of July 2013
and made a presentation entitled
“Manufacturing and characterisation of ther-
moplastic nanocomposite fibers with carbon
nanotubes”
& Science
S A R I S T U
Page 21
participated in the 10th International Confer-
ence on Damage Assessment of Structures
(DAMAS 2013) held in Dublin, Ireland be-
tween the 8th and 10th of July 2013 and
made a presentation entitled “Extension of
Lamb Waves Defect Location Techniques to
the case of Low Power Excitation by Com-
pressing Chirped Interrogating Pulses”
L. De Marchi, N. Testoni, A. Perelli
& A. Marzani
University of Bologna A. Perelli, C. Caione, L. De Marchi, D.
Brunelli, A. Marzani & L. Benini
University of Bologna
participated in the SPIE International
Conference on Smart Structures held at
San Diego, California, United States between
the 10th and 14th of March 2013 and made a
presentation entitled
“Design of a Low-Power Structural Monitoring
System to Locate Impacts based on Dispersion
Compensation”
S. Delrue, K. Van Den Abeele
KU Leuven
participated in the
2013 International Congress on Ultrasonics
held in Singapore
between the 2nd and 5th of May 2013
and made a presentation entitled
“Simulations of Nonlinear Air-Coupled
Emission (NACE)”
J. Pattinson and M. Herring (EADS Innovation
Works – UK)
participated in the International Forum for
Aeroelasticity and Structural Dynamics
held in Bristol, UK
between the 24th and 27th of June 2013
and made a presentation entitled
“High Fidelity Simulation of Novel Loads
Control Devices”
& Science
S A R I S T U
Page 22
A. De Gaspari & S. Ricci
Politecnico di Milano
participated in the 2013 AIDAA Conference of
the Italian Association of Aeronautics XXI
Conference held at
Naples, Italy between the 9th and 12th of
September 2013 and made a presentation
entitled “Active Camber Morphing Wings
Based on Compliant Structures”
Z. Sharif Khodaei, O. Bacarreza & M.H.
Aliabadi
ICL
participated in the
12th International Conference on Fracture
and Damage Mechanics
held in Alghero, Sardinia, Italy
between the 17th and 19th of September
2013 and made a presentation entitled
“Lamb-wave Based Technique for Multi-site
Damage Detection”
V. Blanco-Gutierrez, A. Demourgues
& M. Gaudon
CNRS
published a scientific paper entitled
“Sub-micrometric β-CoMoO4 rods: optical
and piezochromic properties”
at the Dalton Transactions Journal of the
Royal Society of Chemistry
The study has been carried
out considering five Co-
molybdate samples with
different size and morphology
Z. M. Moix‐Bonet (DLR), B. Eckstein (EADS-D)
& P. Wierach (DLR)
participated in the
International Symposium on Piezocomposite
Applications (ISPA 2013)
held in Dresden, Germany
between the 19th and 20th of September
2013 and made a presentation entitled
“SHM Integration in Aircraft Structures:
Challenges and Outcomes”
& Science
S A R I S T U
Page 23
T. Siebel & M. Lilov
Fraunhofer LBF
N. Testoni, L. De Marchi, and A. Marzani
University of Bologna
participated in the
3rd International EASN Association Workshop
on Aerostructures
held in Milan, Italy
between the 9th and 11th of October 2013
and made a presentation entitled
“Detection of delamination in composite
plates via acoustic full-field guided waves
detection and wavenumber filtering”
published a scientific paper
entitled “Detection of delamina-
tion in composite plates via acous-
tic full-field guided waves detec-
tion and wavenumber filtering”
at the Key Engineering Materials Vols. 569-
570 (2013), pp. 1132-1139.
& Science
S A R I S T U
Page 24
in Upcoming Events
S A R I S T U
Page 25
Partners S A R I S T U
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SARISTU
www.saristu.eu
ject and to follow its progress, you can visit
Coordinated By:
Website: www.airbus.com
For further information about the pro-
the SARISTU website at:
DISCLAIMER
The research leading to these results has
gratefully received funding from the European Union
Seventh Framework Programme (FP7 / 2007—2013) under Grant
Agreement N° 284562.
Every effort has been made to ensure complete and accurate information concern-
ing the articles in this newsletter. However, the authors and members of
the consortium cannot be held legally responsible for any mistakes in
printing or faulty instructions. The authors and consortium members
reserve the right not to be responsible for the topicality,
correctness, completeness or quality of the infor-
mation provided.
Designed and created by EASN-TIS in conjunction with
AIRBUS & ALTRAN
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