Original file (15 MB)

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

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

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

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.

Structural Health Monitoring (SHM) Application Scenario 4 : Fibre optic (FO) based Monitoring System

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.

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.

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

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

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

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

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

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.

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.

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


“Experimental Investigation on Improving

Electromechanical Impedance based Damage

Detection by Temperature Compensation”

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


“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





“Verification tests of integrated Phased Array

transducer - PhA III”

V. Cokonaj, A. Alcaide, G. Aranguren, P. M. Monje,

E. Barrera M. Ruiz & R. Meléndez



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”

E. Barrera, M. Ruiz, R. Meléndez, N. Fernández,

V. Cokonaj, G. Aranguren & P. M. Monje



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)






“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)






“Reliability of co-bonded piezoelectric sensors

on CFRP structures”

Julián Sierra-Pérez & Alfredo Güemes

Universidad Politecnica de Madrid


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”

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



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



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


“Design of a Winglet Control Device for Active

Load Alleviation”


& Anna Boczkowska


participated in the

Third International Symposium “Frontiers in

Polymer Science

held in Sitges, Spain

between the 21st and 23rd of May 2013


“Polymer based Nanocomposites for

Aerospace Industry”


& Anna Boczkowska


participated in the

Austrian – Slovenian Polymer Meeting BLED

held in Bled, Slovenia

between the 3rd and 5th of April 2013


“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


“Manufacturing and characterisation of ther-

moplastic nanocomposite fibers with carbon

nanotubes”

& Science

S A R I S T U

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


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


“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


“High Fidelity Simulation of Novel Loads

Control Devices”

& Science

S A R I S T U

http://spie.org/x12228.xml

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

T. Siebel & M. Lilov

Fraunhofer LBF

N. Testoni, L. De Marchi, and A. Marzani


participated in the

3rd International EASN Association Workshop

on Aerostructures

held in Milan, Italy

between the 9th and 11th of October 2013


“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

in Upcoming Events

S A R I S T U

Partners S A R I S T U

Page 24

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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