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4th International Conference “Supply on the wings“

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1<BR>NOVEMBER 03 - 05, 2009<BR>EXHIBITION CENTER<BR>FRANKFURT / MAIN, GERMANY<BR>Conference Manual<BR>4th International Conference „Supply on the wings“<BR>Aerospace - Innovation through international cooperation<BR>in conjunction with the International Aerospace Supply Fair<BR>AIRTEC 2009<BR>Keynotes by Airbus, Boeing, Embraer<BR>Alenia, Voith Engineering Ser vices,<BR>German Aerospace Center/DLR<BR>2<BR>CONTENT<BR>Welcome addresses<BR>D. Schnabel and R. Degenhardt.............04<BR>Committee...........................................05<BR>Conference Programme.........................06<BR>Abstracts.............................................09<BR>3<BR>Together with the Chairmen of the conference<BR>and the Scientific and Technical Advisory<BR>Board we cordially invite you to attend the<BR>4th International Conference “Supply on the<BR>wings” held in conjunction with the International<BR>Aerospace Supply Fair AIRTEC. This year<BR>the conference has grown again, it is held in<BR>four parallel sessions, very international, with<BR>speakers from 19 nations.<BR>The conference provides excellent opportunities<BR>to learn about new trends and technologies<BR>and to exchange information, opinions<BR>and ideas and to discuss important issues<BR>facing the aerospace industry. Networking is<BR>key to any convention. Besides the technical<BR>sessions there will be time for communication<BR>with speakers, delegates and exhibitors<BR>during the lunch and coffee breaks as well as<BR>during the evening conference reception.<BR>The keynote speakers this year will be from<BR>German Aerospace Center/DLR, Airbus, Boeing,<BR>Embraer, Alenia and CeBeNetwork.<BR>We wish all attendees new insights and inspiring<BR>discussions at a successful conference.<BR>4th International Conference “Supply on the wings“<BR>Aerospace - Innovation through international cooperation<BR>INVITATION TO ATTEND<BR>Diana Schnabel<BR>Exhibition Management<BR>AIRTEC 2009<BR>CEO / President<BR>airtec GmbH &amp; Co. KG<BR>Volker Schulze<BR>Exhibition Management<BR>AIRTEC 2009<BR>Managing Director<BR>airtec GmbH &amp; Co. KG<BR>4<BR>Despite the financial crisis, the aerospace industry<BR>develops very fast and affects strongly<BR>the OEMs and suppliers. Changing markets<BR>are on the one hand a challenge but on<BR>the other hand a chance for the aerospace<BR>industry. Intensive networking across different<BR>sectors and technologies is therefore more important<BR>than before. Under this year’s motto<BR>“Aerospace – Innovation through international<BR>cooperation” the 4th International Conference<BR>“Supply on the wings”, which is taking place<BR>November 3 - 5, 2009 in Frankfurt / Germany<BR>as part of the AIRTEC fair, brings together<BR>renowned experts from industry and academia<BR>of various field of the aerospace industry.<BR>The topics addressed in the conference will<BR>cover all aspects of current and future aerospace<BR>products. Although the conference<BR>considers all relevant aerospace topics, the<BR>main focus this year is on the process chain<BR>for composites and metals. The head topics<BR>of the sessions are:<BR>- Composite structures<BR>- Metallic structures<BR>- Improved simulation (for composites and<BR>metallics)<BR>- Non-destructive inspection and<BR>Structural-Health-Monitoring<BR>- Engines<BR>- Systems and components<BR>- Aerospace supply chain<BR>- Life Cycle Support<BR>New<BR>- Whole aircraft design<BR>- International co-operation<BR>- Young academics<BR>- Forum Simulation (application oriented)<BR>The high-lights of the conference are the<BR>invited keynote presentations from high level<BR>speakers from German Aerospace Center<BR>(DLR), Airbus, Boeing, Embraer, Alenia and<BR>CeBeNetwork. In total the conference programme<BR>combines 86 presentations from 19<BR>countries of 5 different continents. This underlines<BR>the year’s conference motto “Aerospace<BR>– Innovation through international cooperation”.<BR>The conference is an ideal meeting place<BR>for professionals from the area of development,<BR>engineering, project management,<BR>business administration, production, manufacturing,<BR>procurement and related fields.<BR>I wish all attendees successful and inspiring<BR>days and a pleasant stay in Frankfurt.<BR>Prof. Dr.-Ing. Richard Degenhardt<BR>Scientific Chairman of the Conference<BR>German Aerospace Center (DLR) and<BR>Private University of Applied Sciences<BR>G&ouml;ttingen (PFH)<BR>5<BR>International Scientific and Technical Advisory Board<BR>Chairman<BR>Prof. Richard Degenhardt, PFH G&ouml;ttingen and DLR Braunschweig, D<BR>Vice-Chairman<BR>Dr. Trevor Young, University Of Limerick, IRL<BR>Academia<BR>Prof. Giacomo Frulla, Polytechnic University of Turin, I<BR>Prof. Harald Funke, Aachen University of Applied Sciences, D<BR>Prof. Ulrich Gabbert, Otto-von-Guericke University Magdeburg, D<BR>Prof. Alfredo Güemes, Polytechnic University of Madrid, E<BR>Prof. Wolfgang Hintze, Hamburg University of Technology, D<BR>Prof. Giulio Romeo, Polytechnic University of Turin, I<BR>Prof. Alois Schlarb, University of Kaiserslautern, D<BR>Prof. Murray Scott, CRC-ACS Melbourne, AUS<BR>Prof. Janusz Narkiewicz, Warsaw University of Technology, PL<BR>Prof. Romana Eva Sliwa, Rzeszów University of Technology, PL<BR>Prof. Bernd Steckemetz, University of Applied Sciences Bremen, D<BR>Prof. Gerhard Ziegmann, Clausthal University of Technology, D<BR>Industry<BR>Dr. Rainer Rauh, Airbus Deutschland GmbH, D<BR>Dr. Gregorio Kawiecki, Boeing, E<BR>Dr. Douglas McCarville, Boeing, USA<BR>Mr. Sam Wilson, Bombardier, UK<BR>Dr. Jens Henkner, EADS, EFW, Elbe Flugzeugwerke GmbH, D<BR>Mr. Fabio Soares, Embraer, BR<BR>Dr. Leslie Cohen, Hitco, USA<BR>Mrs. Gila Ghilai, Israel Aerospace Industries, IL<BR>Mr. Olaf Lenk, Rolls-Royce, D<BR>Dr. Lars Herbeck, Voith Materials, D<BR>6<BR>First Day: 3rd November 2009 4th Int. Conference “Supply on the Wings”, 3 – 5 November 2009, Frankfurt<BR>08:30 Check-in and morning coffee<BR>09:45 V. Schulze (Airtec) / Prof. R. Degenhardt (DLR, PFH)<BR>Welcome<BR>Keynote lectures Chair: Dr Leslie Cohen (Hitco)<BR>10:15 Prof. J. Szodruch (DLR, DGLR)<BR>Challenges beyond the Vision 2020<BR>10:45 Mr John M. Griffith (Boeing)<BR>Bridging the Gulf Between Development and Transition<BR>11:15 Dr Jocelyn Gaudin (Airbus France)<BR>MAAXIMUS: A major lever for aircraft structure innovation<BR>11:45 Lunch break<BR>Session A1a Composite Structures<BR>Chair: I. Dikici (Turkish Aerospace Industries), Prof. A. Güemes (Polytecnic University of Madrid)<BR>Session A1b Metallic structures<BR>Chair: Prof. B. Surowska (Lublin University of Technology), Dr L. J. Ruiz-Aparicio (ATI Allegheny Ludlum)<BR>Invited Speaker Invited Speaker<BR>A. Engleder, W. Koletzko (Eurocopter Germany)<BR>Current Helicopter Composite Applications and its way ahead – with a short look back to the beginnings<BR>13:20 Dr L. J. Ruiz-Aparicio, A. DeNoi, J. V. Mantione, R. Wendel, J. Smith, Dr T. D. Bayha (ATI Allegheny Ludlum)<BR>Development of ATI 425&reg; Titanium Alloy Sheet, Strip and Foil<BR>Prof. A. Güemes (Polytecnic University of Madrid)<BR>Fibre optics distributed sensing: Status and perspectives<BR>13:40 Dr J. Adamus, Dr P. Lacki (Czestochowa University of Technology)<BR>The most important aspects of sheet-titanium forming<BR>Dr M. Heneczkowski , Prof.H.Galina, Dr M. Oleksy (Rzeszow University of Technology)<BR>Fire resistant epoxy composites<BR>14:00 U. Speetzen, L. Castellano (Makino GmbH)<BR>The New Economic Feasibility of Titanium Machining<BR>Mr R. M&ouml;ller (Flow Europe GmbH)<BR>Machining of Composites with Abrasive Waterjets<BR>14:20 Dr T. Balawender, Prof. R. E. Sliwa (Rzeszow University of Technology)<BR>A new concept of rivet proposed to use in aeronautical constructions<BR>Dr M. Potoczek, Prof. R. Sliwa (Rzeszow University of Technology)<BR>Metal-ceramic interpenetrating composites obtained by metal infiltration into gelcast alumina foams<BR>14:40 W. Beck, W. G. Jung, S. Arends (FormTech GmbH)<BR>Forming of Titanium Alloys<BR>Dr P. Müller-Hummel (MAPAL Dr Kress KG)<BR>New Economic Solutions for Drilling and Milling of CFRP and Low Force Drilling of CFRP/Titanium Stacks for Aeronautic Applications<BR>15:00 F. Wildenberg (CMW)<BR>On site machining (on an airport) of wings and fuselage of a twin jet with HEXAPODE CMW 380<BR>Coffee break 15:20 Coffee break<BR>Session A2a Life Cycle Support / NDT and SHM<BR>Chair: Prof. J. Narkiewicz (Warsaw University of Technology)<BR>Session A2b Simulation forum<BR>Chair: Mr Yvan Radovcic (Samtech)<BR>B. Neuner (AMETEK Programmable Power), M. van den Bergh (CNS Inc. – Poway)<BR>Modern aircraft power system testing<BR>16:00 Dr M. Hortmann<BR>Simulation Driven Product Development with ANSYS Workbench<BR>Dr M. Ehrmann (Dürr Systems GmbH)<BR>Process planning and assembly structures in aircraft environments<BR>16:20 S. Peck (VISTAGY, Inc.)<BR>Enhancing the Composites Design-to-Manufacturing Process with FiberSIM(R) 2009<BR>S. Vrignon, B. Pouilleau (euroscript International S.A.)<BR>ILS as seen by an Army: The national French Air Force Library or the first Open Source based S1000D solution<BR>16:40 M. Kürten, P. Block (CGTech Deutschland GmbH)<BR>VERICUT Composite Programming &amp; Simulation<BR>M. M&auml;useler (GfU Gesellschaft für Unternehmenslogistik mbH)<BR>Requirements Engineering supports Life Cycle Management<BR>17:00 A. Walter (aicas Allerton Interworks Computer Automated Systems)<BR>Java for Safety Critical Applications<BR>M. Cacciola, A. Gasparics, G. Megal, D. Pellicanò, F.C. Morabito<BR>Model for Eddy Current testing of CFRPs<BR>17:20 T. Baudach, Dr. S. Kleiner (engineering methods AG)<BR>Knowledge Based Engineering using CATIA V5 for High Lift Device Design at Airbus<BR>Dr P. Weinhold, Dr T. Schü&szlig;ler (Innowep GmbH)<BR>Mobile Measuring and Documentation of Visual Impression and Surface Topography<BR>17:40 Dr A. Mete (MSC Software GmbH)<BR>State of the art of composites material simulation<BR>Conference reception 18:00 Conference reception<BR>7<BR>Second Day: 4rd November 2009 4th Int. Conference “Supply on the Wings”, 3 – 5 November 2009, Frankfurt<BR>08:30 Check-in and morning coffee<BR>Keynote lectures Chair: Albrecht Pfaff (MSC.Software GmbH )<BR>09:00 Mr G. Avalle, L. Fossati, V. Sapienza (Alenia Aeronautica): Effects of the corrosion on the structural fatigue life and their management in the in-service ageing aircraft<BR>09:30 Mr Marco Cecchini, Alexandre C. de Moura, Fabio R. Soares da Cunha (Embraer): Embraer at a glance, engineering tools for aircraft simulation<BR>10:00 Coffee break<BR>Session B1a Composite Structures<BR>Chair: Dr Leslie Cohen (Hitco)<BR>Session B1b Improved simulation<BR>Chair: Albrecht Pfaff (MSC.Software GmbH )<BR>Invited Speaker Invited Speaker<BR>Dr C. Hühne, T. Str&ouml;hlein (DLR)<BR>Door surround structures for next generation aeroplanes<BR>10:45 F. Soares (Embraer), M Lopes de Oliveira e Souza (INPE)<BR>Simulation of aircraft structures using non-linear analysis techniques<BR>L. Cevolini (CRP Technology)<BR>Cold Duct Fan<BR>11:05 F. Rogin, F. Soares, G. Abumeri, Dr. F. Abdi (Alpha Star, Embraer), K. Nikbin (Imperial College)<BR>Robust Design of Composite Wing Structure, a combined durability and reliability approach<BR>Mr D. McCarville (Boeing)<BR>Historic Study of Automated Material Placement Equipment<BR>11:25 Prof. G.Frulla , Ing. E.Cestino (Politecnico di Torino)<BR>Preliminary design of aeroelastic experimental slender wing model<BR>Lunch Break 11:45 Lunch Break<BR>Session B2a Composite Structures<BR>Chair: Gila Ghilai (IAI), Prof. R. E. Sliwa (Rzeszow University of Technology)<BR>Session B2b Systems and components<BR>Chair: Prof. J. Narkiewicz (Warsaw University of Technology), Dr. S. Frohriep (Leggett &amp; Platt Automotive Europe)<BR>Dr K. Jansen (Thomas GmbH + Co. Technik + Innovation KG)<BR>Production of springs with Radius-Pultrusion – a new manufacturing process for a core element of aircraft technology<BR>13:20 M. Fumey (Thales)<BR>Architecture Modelling for IMA platform<BR>S. Peck (VISTAGY, Inc.)<BR>VISTAGY‘s AeroSuite(tm) for Composite Aircraft Assemblies: The Complete Solution<BR>13:40 G. Romanski (Verocel GmbH)<BR>Avionic Systems Integration through the use of IMA platforms<BR>I. Dikici (Turkish Aerospace Industries Inc.)<BR>Composite bone structure with embedded block<BR>14:00 H. Jonas, T. Gumpinger, C. Blees, Prof. D. Krause (Hamburg University of Technology)<BR>Innovation Design of a Gallery Product Platform by applying a new Modularisation Method<BR>G. Ghilai, Dr A. Green (IAI)<BR>Development of Aircraft Flight Control Surfaces - An Evolutionary Process<BR>14:20 Prof. M. K. Knyazyev (National Aerospace University “KhAI”)<BR>Optimisation of Pressure Fields with Multi-Electrode Discharge Blocks at Electro-hydraulic Forming of Aircraft Components<BR>A. Zammit, Prof. J. Bayandor, M. Garg, F. Abdi (RMIT, Alpha STAR)<BR>Impact damage resistance and compression-after-impact strength of sandwich composites with graphite-epoxy facesheets and nomex honeycomb cores (RMIT, Alpha STAR)<BR>14:40 Dr. S. Frohriep, J. P. Petzel (Leggett &amp; Platt Automotive Europe)<BR>Improving Aircraft Passenger Seating Comfort by Comfort Elements and Seat Design<BR>P. Kruecken (Trevira GmbH)<BR>Trevira CS – Functional Textiles for Aircraft Interiors<BR>15:00 W. Luber (EADS-M)<BR>Aeroservoelastic Design and Certification of a Combat Aircraft<BR>Coffee break 15:20 Coffee break<BR>Session B3a Improved simulation<BR>Chair: Fabio Soares (Embraer)<BR>Session B3b Engines<BR>Chair: Prof. H. Funke (FH Aachen)<BR>Prof. M. Oberguggenberger (University of Innsbruck)<BR>Simulation tools for assessing the reliability and robustness of shell structures<BR>16:00 Prof. A. Boguslawski, Dr. A. Tyliszczak (Czestochowa University of Technology)<BR>CFD modeling of combustion and ignition processes in aeroengine combustion chamber<BR>G. Malherbe, Y. Radovcic, D. Granville, M. Balzano (SAMTECH, Airbus)<BR>C&AElig;SAM CAE centric Application Framework Application to AIRBUS Stress Analysis Tool<BR>16:20 G. Ripper, Dr M. Mücke (Steigerwald Strahltechnik GmbH)<BR>Electron beam welding – actual applications in the aerospace industry<BR>Prof. M. Zasuwa, Prof. J. Narkiewicz (Warsaw University of Technology)<BR>Simulation Research Center for Mobile Platforms<BR>16:40 Dr W. Pieper, Dr J. Gerster (Vacuumschmelze GmbH &amp; Co. KG)<BR>High temperature properties and aging effects of soft magnetic 49%Co - 49%Fe - 2%V based alloys with high saturation and high strength for aircraft generators<BR>F. Klunker, S. Aranda, Prof. G. Ziegmann (TU Claustal)<BR>Flow and Cure Simulation for the Production of Large and Thick Walled Composite Structures<BR>17:00 G. Reich, A. DeWeze, Dr A. Oppert (Turbine Airfoil Coating and Repair GmbH)<BR>First Class Refurbishment for Gasturbine Components<BR>R. A. Gibbon (Frazer-Nash Consultancy Limited)<BR>Coupled Eulerian-Lagrangian analysis to predict impact damage to fluid-filled composite structures<BR>17:20 Dr N. Volbers, Dr W. Pieper (Vacuumschmelze GmbH &amp; Co. KG)<BR>Soft Magnetic Cobalt Iron Lamination Stacks for High-Performance Generators and Motors<BR>17:40 Prof. G. Romeo, Prof. F. Borello (Politecnico di Torino)<BR>ENFICA-FC: Design, Realisation and Flight Test of New All Electric Propulsion Aircraft powered by Fuel Cells<BR>AIRTEC Exhibition Night 18:00 AIRTEC Exhibition Night<BR>8<BR>Third Day: 5rd November 2009 4th Int. Conference “Supply on the Wings”, 3 – 5 November 2009, Frankfurt<BR>08:30 Check-in and morning coffee<BR>Keynote lectures Chair: Prof. R. E. Sliwa (Rzeszow University of Technology)<BR>09:00 Dr Frank Arnold (Voith Engineering Services GmbH)<BR>The Engineering Supply Chain - Chances and Risks<BR>Session C1a Aerospace supply chain<BR>Chair: Dr Trevor Young (University of Limerick)<BR>Session C1b Composite Structures<BR>Chair: Prof. G. Frulla (Politecnico di Torino)<BR>Invited Speaker Invited Speaker<BR>N. Clement, H. Gusterhuber (Konecranes Lifting Systems GmbH)<BR>Advanced Handling Solutions for Aircraft Parts<BR>09:40 Prof. B. Surowska, Prof. J. Warmiński, Dr H. Dębski (Lublin University of Technology)<BR>Some aspects of design and use of smart composite structure<BR>U. M&ouml;llmann (Dürr Systems GmbH)<BR>Improving Aircraft Production - MES tool for optimization of production lines<BR>10:00 Dr M. Lange (Premium Aerotec GmbH)<BR>High Performance Cutting of Aluminium and Titanium Parts for Aircrafts<BR>Dr K. Kandadi, Dr D.Bailey, V. Perera (University of Bolton)<BR>Providing visibility to supplier rationalisation through a tiering structure<BR>10:20 D. Herzog, P. Jaeschke, H. Haferkamp, C. Peters, H. Purol, A. Herrmann (LZH, FIBRE)<BR>Laser joining of fibre reinforced composites<BR>Coffee Break 10:40 Coffee Break<BR>Session C2a Aerospace supply chain<BR>Chair: Dr Trevor Young (University of Limerick)<BR>Session C2b International co-operation /Young academics<BR>Chair: Prof. A. Boguslawski (Czestochowa University of Technology)<BR>Invited Speaker Invited Speaker<BR>M. Huber, Dr M. Rübartsch (P3 Ingenieurgesellschaft)<BR>Supply Chain Excellence with SCOR<BR>11:30 Prof. R. E. Sliwa (Rzeszow University of Technology)<BR>System of Aerospace Education in Aviation Valley<BR>C. Buske, Dr A. Knospe (Plasmatreat GmbH )<BR>Openair-Plasma – Cleaning, activation and coating of modern aircraft materials<BR>11:50 F. Passarinho, L. Sim&otilde;es (CEIIA-CE)<BR>CEIIA-CE and AgustaWestland RDE Partnership – Cross Experiences between the automotive and aeronautical<BR>industries - Case Study: Composites Design of the Future Lynx Cockpit Door<BR>Prof. S. Markovich<BR>The technology of high-speed burnless deep grinding for parts from hard-to-machine materials<BR>12:10 T. Geissinger (P3 Digital Services GmbH)<BR>Advantages of excelling knowledge organisations in international aerospace cooperation<BR>D. Clarke (University of Bolton)<BR>UK Aerospace supply chain process improvement: the implementation of SC21<BR>12:30 C. Siegmund, Prof. B Steckemetz (University of Applied Sciences Bremen)<BR>Joint Aerospace Education Initiative<BR>Lunch break 12:50 Lunch break<BR>Session C3a Systems and components / Whole aircraft design<BR>Chair: J. G&ouml;pfert (ID-Consult GmbH)<BR>Session C3b Composite Structures<BR>Chair: Dr. Douglas A. McCarville (Boeing)<BR>Invited Speaker Invited Speaker<BR>Dr T. Dittrich, Dr C. Menachem, Dr H. Yamin, A. Daniel, Dr D. Shapira (Tadiran Batteries GmbH)<BR>Tadiran introduces cost-effective, high power military grade lithium battery<BR>14:00 D. Hartung (DLR)<BR>Experimenteal and numerical analysis of interlaminar material properties of carbon fibre composites<BR>Dr J. G&ouml;pfert (ID-Consult GmbH)<BR>Using the competence of system suppliers in concept competition - Example Airbus A350<BR>14:20 F. Kruse, Prof. T. Gries (RWTH Aachen)<BR>Non-crimped fabrics: Production, Tendency of Development and there potentials for aircraft structures<BR>Dr R. Lernbeiss (TU Wien/Austrian Airlines), Prof. H. Ecker (TU Wien), Prof. M. Pl&ouml;chl (TU Wien)<BR>Simulation of touch-down and roll phase using advanced aircraft frame and landing gear models<BR>14:40<BR>End of conference 15:00 End of conference<BR>9<BR>DAY 1 – 3rd November 2009<BR>KEYNOTES<BR>Chair: Dr Lesli Cohen (Hitco)<BR>Title: Challenges beyond the Vision 2020<BR>Author: Prof. J. Szodruch<BR>DLR, DGLR<BR>Time: November 3, 2009 10:15 am<BR>Room: Frequenz 1<BR>Title: Bridging the Gulf Between Development and Transition<BR>Author: Mr John M. Griffith<BR>Boeing<BR>Time: November 3, 2009 10:45 am<BR>Room: Frequenz 1<BR>Title: MAAXIMUS: A major lever for aircraft structure innovation<BR>Author: Dr Jocelyn Gaudin<BR>Airbus France<BR>Time: November 3, 2009 11:15 am<BR>Room: Frequenz 1<BR>SESSION A1A COMPOSITE STRUCTURES<BR>Chair: I. Dikici (Turkish Aerospace Industries),<BR>Prof. A. Güemes (Polytecnic University of Madrid)<BR>Title: Current Helicopter Composite Applications and its way ahead – with a short look back to<BR>the beginnings<BR>Authors: A. Engleder, W. Koletzko<BR>Eurocopter Germany<BR>Time: November 3, 2009 1:20 pm<BR>Room: Lumen<BR>Today, the helicopter is an indispensable part of our daily life. We aren’t even aware that a large number of<BR>institutions and organizations deploy this highly flexible, vertical take-off and landing aircraft for the benefit of<BR>people living in our country. The German Automobile Organization (ADAC) and other institutions use the helicopter<BR>to get to the site of an accident or incident fast and provide first aid. They are the “Yellow Angels” or the<BR>“Rescuers from the Air”. This widespread use of the helicopter owes a great deal to the use of advanced fibre<BR>composite materials, which have significantly reduced the weight of the helicopter and enhanced its capability.<BR>Fibre composites are being used in aviation for a very long time now. The outstanding characteristics of fibre<BR>composites have been used in the German aerospace industry for the past 50 years. EUROCOPTER Deutschland,<BR>formerly the helicopter division of Messerschmitt-B&ouml;lkow-Blohm, consistently applied the advantages of<BR>fibreglass reinforced composites for the rotor blades of the helicopter BO 105. The virtually unlimited lifetime of<BR>these rotor blades also influenced the development of the bearing less main rotor of the EC 135.<BR>In the beginning fibre composites have mainly been used for components not subject to significant stress, such<BR>as fairings, doors and horizontal stabilizers. Intensified use of fibre composites in other industrial sectors has<BR>also led to falling prices for fibres and resins, which has in turn led to an expansion of use. Eurocopter established<BR>the necessary expertise in the area of airframe structures e.g. by developing an entire BK117 airframe<BR>from fibre composites. This research project contributed to the breakthrough of fibre composites in the Tiger<BR>and NH90 programmes. Actual research projects are focused on the development of cost-effective production<BR>methods, in order to further enhance the use in civil helicopter construction.<BR>Prof. J. Szodruch<BR>John M. Griffith<BR>Dr Jocelyn Gaudin<BR>10<BR>The specifications for helicopter airframes and blades can be derived from customers’ requirements: high payload,<BR>low maintenance expenditure, resistance to corrosion, and high level of safety combined with maximum<BR>comfort. The advantages obtained by using fibre composites are clearly evident. Highly integrated assemblies<BR>or individual components can be designed and manufactured with specifications optimized to match requirements<BR>and minimum weight. Todays prepreg technology may reach in some areas its limits with regard to<BR>producibility and production costs. Hence new production processes and more automated manufacturing has<BR>to be developed. The following paper gives an overview of the latest improvements.<BR>Title: Fibre optics distributed sensing: Status and perspectives<BR>Authors: Prof. A. Güemes<BR>Polytecnic University of Madrid<BR>Time: November 3, 2009 1:40 pm<BR>Room: Lumen<BR>Getting the strains all along the optical fiber, with adequate spatial resolution and strain accuracy, open new<BR>possibilities for structural tests and for structural health monitoring. Formerly, only point sensors, as strain gages<BR>or FBGs, were available, and information on the response to loads was restricted to those points onto which<BR>the sensors were bonded. Unless some sensor was located near to the damage initiation point, details about<BR>the failure initiation and growth were lost. With a distributed system the information is given as an array of<BR>data with the position in the optical fibre and the strain or temperature data at this point.<BR>In this paper the physical principles underlying the different techniques for distributed sensing are discussed,<BR>a classification is done based on the backscattered wavelength; this is important to understand its possibilities<BR>and performances. The definition of performance for distributed sensors is more difficult than for traditional<BR>point sensors, since the performance depends on a combination of related measurement parameters. For example,<BR>accuracy depends on the spatial resolution, acquisition time, distance range or cumulated loss prior to<BR>measurement location.<BR>The field of applications of this new technology is very wide; Results of the structural tests of a 40 mts long<BR>wind turbine blade, detecting the location and load of onset of buckling, and the results of the delamination<BR>detection in a composite plate, are presented as examples.<BR>Title: An Experimental Investigation into Frictional Effects in Bolted Joints<BR>Authors: M. Oswald, W. Stanley, C. McCarthy<BR>University of Limerick<BR>Time: November 3, 2009 2:00 pm<BR>Room: Lumen<BR>Bolted joints form critical elements in composite aircraft structures and their design is heavily influenced by<BR>friction acting at the interface between the joined members. In fully torqued joints, most of the load is transferred<BR>through friction at this interface, with only a small percentage being transferred by contact between<BR>the bolt and laminate. This is the most desirable situation, therefore to take full advantage of this phenomenon<BR>designers need a full understanding of the coefficient of friction (COF) at this interface. The static and dynamic<BR>COF at the interface in joints can vary over time due to wear, for example. Hence, this paper sets out to experimentally<BR>measure the COF between bolted composite laminates and between bolted composite laminates and<BR>aluminium. In this study, a versatile friction testing rig was designed and commissioned. This rig was mounted<BR>on a universal testing frame and the normal force (which was monitored by a loadcell) was applied through<BR>hydraulic jacks. The material under examination was a carbon fibre/epoxy resin composite (HTA/6376) in a<BR>quasi-isotropic configuration and aircraft grade aluminium (T2024). Both these materials are used extensively in<BR>the aerospace industry. The baseline COF of these materials was determined using Herzian contact through the<BR>use of a cylindrically shaped specimen. Several adaptations were incorporated into the rig to closely simulate<BR>actual bolted joint conditions (e.g. the use of washers and countersunk bolts). An extensive test series was conducted<BR>to quantify the COF that exists between the laps for various bolt pre-loads (i.e. increasing levels of bolt<BR>torque). Tests were also conducted to investigate if protruding head bolts, countersunk head bolts, and washers<BR>had any effect on the COF at the shear plane of the joint.<BR>11<BR>Title: Machining of Composites with Abrasive Waterjets<BR>Authors: Mr R. M&ouml;ller<BR>Flow Europe GmbH<BR>Time: November 3, 2009 2:20 pm<BR>Room: Lumen<BR>It is widely known that composite materials offer significant strength-toweight advantages over metals. These advantages<BR>couldn’t be more evident than as seen in the increasing use of composite materials on commercial and<BR>military aircraft. Where airframes were traditionally constructed of metal, structures such as the fuselage, wings,<BR>and the empennage (vertical and horizontal stabilizers), are now made of composite materials.<BR>The Boeing 787, for instance, with delivery beginning in 2008 will be 50% composite structure by weight. In<BR>comparison, the 777, which entered service just over ten years ago, is only 10% composite structure by weight.<BR>AIRBUS, with it’s A350XWB, is considering an all composite fuselage and wing. The military’s F-22 Rapture<BR>aircraft contains approximately 60% composite structure.<BR>With the increased use of composite materials on primary aircraft structures comes the greater need for technological<BR>improvements in the production of those structures. The obvious factors driving this need includes: 1)<BR>Consistent high product quality due to the potential for imminent catastrophic aircraft failure if a structure fails inflight;<BR>2) Lower processing and materials cost since the $/LB cost of composite structures compared to structures<BR>made from conventional metals (such as aluminum) have historically prevented the use of composites on aircraft;<BR>3) Shorter processing times in light of forecasted order and build rates of new aircraft.<BR>Abrasive waterjet (AWJ) cutting is one technology enabling the realization of all three of the above factors, provides<BR>several advantages over conventional cutting methods, and is the preferred method for cutting composite<BR>structures.<BR>Abrasive Waterjet (AWJ) Technology<BR>When water is pressurized up to 60,000 pounds (or more) per square inch (psi) and forced through a tiny<BR>opening, it can cut a variety of soft materials including food, paper and baby diapers, rubber and foam. When<BR>small amounts of abrasive particles, such as garnet, are mixed into the jet stream, the resulting „abrasive waterjet“<BR>can cut virtually any hard material such as metal, composites, stone and glass. …<BR>Title: Metal-ceramic interpenetrating composites obtained by metal infiltration into<BR>gelcast alumina foams<BR>Authors: Dr M. Potoczek, Prof. R.Sliwa<BR>Rzeszow University of Technology<BR>Time: November 3, 2009 2:40 pm<BR>Room: Lumen<BR>Looking for strong and light materials to adopt as elements of aeronautical construction, the composite based<BR>on foams infiltrated by light metals have been analysed. In order to obtain the porous alumina material a new<BR>method of manufacturing of porous ceramics known as “gelcasting of foams” was applied. The gelcast alumina<BR>foams were used as preforms for AlCu5 alloy infiltration by pressure technique. The results of apparent density,<BR>percentage of theoretical density, open and total porosity of alumina foams are presented. SEM observations of<BR>alumina foams are the base for looking for the best solution for manufacturing such kind of composite material.<BR>The alumina foams were typically composed of approximately spherical cells interconnected by circular windows.<BR>Spherical pores were associated with well-densified polycrystalline struts The presence of well-densified<BR>struts is the main microstructure difference between the gel-casting technique and another method of manufacturing<BR>of highly porous ceramics, known as a replication process. One of the drawbacks of the replication process<BR>is the tendency to leave hollow struts, causing lowering of the mechanical properties. …<BR>12<BR>Title: New Economic Solutions for Drilling and Milling of CFRP and Low Force Drilling of<BR>CFRP/Titanium Stacks for Aeronautic Applications<BR>Authors: Dr P. Müller-Hummel<BR>MAPAL Dr. Kress KG<BR>Time: November 3, 2009 3:00 pm<BR>Room: Lumen<BR>This article characterises the special features of milling and drilling of CFRP and develops aspects for new tool<BR>geometries for milling CFRP/titanium. Simplified theoretic models will show how CFRP should be machined and<BR>what has to be observed with regard to new developments. Low axial forces are main characteristics of the<BR>drilling tool optimised in this way, which makes it especially suited for being used in drilling feed units.<BR>SESSION A1B METALLIC STRUCTURES<BR>Chair: Prof. B. Surowska (Lublin University of Technology),<BR>Dr L. J. Ruiz-Aparicio (ATI Allegheny Ludlum)<BR>Title: Development of ATI 425&reg; Titanium Alloy Sheet, Strip and Foil<BR>Authors: Dr L. J. Ruiz-Aparicio, A. DeNoi, J. V. Mantione, R. Wendel, J. Smith, Dr T. D. Bayha<BR>ATI Allegheny Ludlum<BR>Time: November 3, 2009 1:20 pm<BR>Room: Candela<BR>ATI 425&reg; alloy titanium, with its high strength, cold formability and lower-temperature super-plastic formability,<BR>has emerged as an innovative, high-potential alternative to 6-4 titanium, today’s workhorse alloy.<BR>ATI is pursuing a corporate-wide technical project to add sheet, strip and foil, in individual lengths, to the<BR>company’s current ingot, billet, plate and bar product offerings. In addition, sheet and strip in continuous coils<BR>are being developed.<BR>These continuous product forms have never been available in alloy titanium mill products. Continuous coils<BR>will provide titanium sheet and strip consumers a productive, cost- saving alternative to current products. Coil<BR>products are similar to what has been available in aluminum and steels.<BR>With its good corrosion resistance, ATI 425&reg; titanium possesses a unique combination of properties that allows<BR>it to be considered for a wide variety of applications where design challenges include weight reduction or an<BR>alternative to steel, aluminum, composites or other titanium and titanium alloys. Market sectors for ATI 425&reg;<BR>titanium range from aerospace, defense and commercial vehicles to recreational equipment.<BR>This paper will provide an update of process development as well as review the production capabilities that<BR>are expected to provide tighter-gauge tolerances and flatness for ATI 425&reg; titanium alloy over today’s titanium<BR>alloy sheet and strip.<BR>Title: The most important aspects of sheet-titanium forming<BR>Authors: Dr J. Adamus, Dr P. Lacki<BR>Czestochowa University of Technology<BR>Time: November 3, 2009 1:40 pm<BR>Room: Candela<BR>In the paper sheet-metal forming process as the essential part of modern industry, which allows for production<BR>of the near net-shape drawn-parts, will be discussed. Although deep-drawing steel sheets still play the leading<BR>13<BR>role in sheet metal forming the other materials like aluminium, magnesium and titanium alloys are shaped more<BR>and more often. The main aim of the application of the light alloys is a decrease in construction weight. Titanium<BR>and its alloys seem to be the noteworthy materials because of unique set of properties such as: low specific<BR>gravity, high strength and good corrosion resistance. Unfortunately, using these materials entails a necessity of<BR>solving new technological problems.<BR>Generally, titanium alloys are rather difficult to process. Poor drawability of most titanium alloys arising from<BR>their tendency to strain hardening at lower temperatures can be improved by working at higher temperatures.<BR>Additionally, forming at elevated temperatures decreases spring-back and improves dimensional accuracy of<BR>the drawn-parts. Unfortunately, such processing must be carried out under special conditions in order to avoid<BR>diffusion of oxygen, nitrogen, and hydrogen into the titanium what affects its brittleness.<BR>Galling and pick-up of titanium on the die pose another problem in sheet-metal forming processes. The galling<BR>tendency of titanium is greater than that of typical deep drawing sheets. This necessitates close attention to lubrication<BR>in each forming operation where titanium is in moving contact with metal dies or other forming equipment.<BR>The „build-ups” phenomenon can be limited or even completely eliminated by the application of proper<BR>technological lubricants and antiadhesive coatings on the tools. In the paper some possibilities of limitation the<BR>unfavourable tribological properties of titanium in sheet-metal forming process will be given.<BR>Moreover some test results for CP2 and Ti6Al4V titanium alloy will be given. The numerical simulation results of<BR>the stamping process of the titanium cylindrical cup will be presented. A special attention will be paid to the effect<BR>of such parameters as: friction, tool geometry and holding down force on the strain and stress distribution.<BR>The simulation results will be compared with the experimental ones. The numerical simulation will be carried<BR>out with the ADINA System based on the finite element methods (MES).<BR>Title: The New Economic Feasibility of Titanium Machining<BR>Authors: U. Speetzen, L. Castellano<BR>Makino GmbH<BR>Time: November 3, 2009 2:00 pm<BR>Room: Candela<BR>With the aim of creating intelligent lightweight structures, modern aircraft manufacturing has become focused<BR>on continuously updating its construction materials. Due to the rapid growth of composites as a structural<BR>material, the number of Titanium structural parts in aircraft construction has also increased. The reason for<BR>combining titanium and carbon fiber lies in the low electro-chemical difference between the two materials, in<BR>comparison to the combination of aluminium and carbon fiber.<BR>Moreover, titanium alloys are regarded among the most preferred construction materials due to their light<BR>weight as well as their high tensile strength characteristics. When compared to other materials, titanium also<BR>demands completely different tool and machine characteristics due to the high cutting load, torque and the<BR>extreme temperatures that are created at the cutting edge. The economical feasibility of titanium machining<BR>can only be achieved through a holistic view of the complete process chain. Thanks to years of experience in<BR>titanium and aluminium structural parts machining, MAKINO has created a new family of machines specifically<BR>designed for the machining of titanium.<BR>The challenge: roughing and finishing Titanium structural parts on a 5 axis machine.<BR>This challenge however is not new. Indeed, 5 axis simultaneous machining for finishing operations is already<BR>commonly used and there are many machines which can perform high demanding roughings in 3-axis movements.<BR>Therefore, MAKINO brought the challenge one step further.<BR>The new concept: improving the efficiency of the cutting process by performing not only finishing operations<BR>but also highly demanding roughing operations with simultaneous 5-axis machining. This approach demands<BR>new levels of performance from both the machine and cutting-tool.<BR>The solution: a compact horizontal machining centre featuring a revolutionary spindle head which allows not<BR>only simultaneous 5-axis cutting but also utilizes high pressure / volume coolant directly through the spindle.<BR>14<BR>The application: utilization of innovative tooling technology and process strategies.<BR>The result: four times more productivity than conventional machining, not only with regards to machining times<BR>but also to the final cost of produced parts.<BR>Title: A new concept of rivet proposed to use in aeronautical constructions<BR>Authors: Dr T. Balawender, Prof. R. E. Sliwa<BR>Rzeszow University of Technology<BR>Time: November 3, 2009 2:20 pm<BR>Room: Candela<BR>The new rivet construction has been analysed and proposed to apply for aeronautical use. The rivet is made<BR>up of two parts. Each part consists of head and shank but one shank is in form of a pin and another is in form<BR>of a sleeve. Closing up of rivet consist in joining of these two rivet parts. Joining is the consequence of plastic<BR>deformation of constituent rivet shanks. No rivet head plastic forming is performed during clenching process,<BR>so it can be accurately controlled by displacement of dies. When the rivets are compressed, the diameter of<BR>the pin shank grows and forces the deformation of the second rivet shank (sleeve) until the rivet hole is completely<BR>filled. Because the pin deformation leads to barrel-shaped resulting from non-homogeneous deformation ,<BR>the initial outer shape of the sleeve is in the form of concave cylinder; inner shape of sleeve is matched to the<BR>pin cylindrical shape. At the end of compressing process this concave shape is straighten to cylindrical hole<BR>shape but because of pin barrelling the inner shape of sleeve becomes concave. This concave curvature of pin<BR>–sleeve shank surface gives the effect of the rivet shut.<BR>The results of the first step of new rivet investigations have been realised. Two different materials (aluminium<BR>and copper) were used for constituent rivets. The obtained results of good connection investigated under different<BR>conditions have been presented.<BR>Title: Forming of Titanium Alloys<BR>Authors: W. Beck, W. G. Jung, S. Arends<BR>FormTech GmbH, Weyhe, Germany<BR>Time: November 3, 2009 2:40 pm<BR>Room: Candela<BR>Titanium alloys are badly desired for aircraft from the stress calculation and weight saving point of view. Titanium<BR>alloys exhibit an extraordinary favourable combination of low specific weight, high strength and corrosion<BR>resistance. But, at ambient temperature, it is difficult to form titanium to the complex curved geometries of aircraft<BR>components. The achievable strain at room temperature is rather limited, springback is unpredictable and<BR>after trimming parts often change shape.<BR>There are few titanium parts designed and built from sheet metal for current structures due to the described difficulties<BR>and high cost per kg. Scrap reduction and careful handling of materials&acute; resources has sense and will<BR>get a much bigger item with the increasing number of composite fuselages. Further, unlike aluminum titanium<BR>inherently resists corrosion . This paper describes an option for reducing the cost of titanium parts and therein<BR>increasing its use on future aircraft. Forming titanium is simpler at elevated temperatures than at room temperature.<BR>Complex shapes can be formed if the material is raised to temperatures approaching 900°C .<BR>At such temperatures some titanium alloys will strain up to some hundred percent without degrading structural<BR>properties. In this condition, the titanium is pliable, shows high ductility and forms with such a low flow stress<BR>that it is possible to form with gas pressure. After de-moulding and cooling, parts don&acute;t exhibit residual stresses<BR>and trimming doesn&acute;t change part contour. Tooling for such applications can be relatively simple. For the gas<BR>pressure forming process, the tools just need a shaped cavity bottom die half and a flat closure top die half.<BR>Gas pressure forming of titanium sheets is competitive when compared to machining components from thicker<BR>15<BR>plate material. Formed parts can be designed thinner and weigh less than comparable machined parts due to<BR>the practical limitation of not being able to machine down to thickness less than 2,5mm. Another advantage of<BR>forming is minimal scrap.<BR>Whereas machining scrap ratios of more than 90% are typical, formed parts seldom have scrap ratios exceeding<BR>30%. Gas pressure forming can typically be cost justified as production quantities increase and there are<BR>more parts over which to amortize tooling costs. Weight and cost balance compared against the accumulated<BR>parts quantity count show an early break-even point. FormTech is a leader in titanium forming with gas pressure<BR>at elevated temperature. In this paper an overview of the process is presented from a production point of<BR>view and many different shapes are discussed as a way of illustrating a wide range of possible future applications.<BR>Title: On site machining (on an airport) of wings and fuselage of a twin jet with<BR>HEXAPODE CMW 380<BR>Authors: F. Wildenberg<BR>CMW<BR>Time: November 3, 2009 3:00 pm<BR>Room: Candela<BR>• CMW has developed (with research centers and university) a new technology to make 5 axes High Speed<BR>Machining on very large parts:<BR>HEXAPODE CMW 380.<BR>• It is very similar to the human machine:<BR>o The support is the arm and wrist: a serial machine without rigidity like any milling machine<BR>o The hand is a parallel kinematic machine with high rigidity<BR>o The hand correct the positioning errors of the wrist<BR>o It works on a sequential way: successive mesh machining<BR>o They are no measuring system into the machine<BR>o They are 2 external measuring technology: eyes (laser tracker), internal ear ( electronic level)<BR>• One application which was not initially anticipated is the on-site machining<BR>• The first use was made for aircraft industry.<BR>• Now CMW is discovering that they are a lot of other uses of this new technology<BR>• How it started:<BR>o The problem:<BR>The customer is a company specialized in maintenance of twin jet aircraft<BR>A twin jet had a leakage problem of fuel at the junction between the wings and the fuselage.<BR>So they disassemble the wings and fuselage and discover a lot of corrosion. During the manual grinding of the<BR>corrosion they created a lot of hollow small surfaces. This was going to induce more leakage. So it was necessary<BR>to make a full machining of the surfaces. The wings were on a trolley and the fuselage was on fixed jack.<BR>So it was impossible to move the fuselage.<BR>o The answer:<BR>CMW came and made the on-site machining of the wings and fuselage with HEXAPODE CMW 380<BR>It was necessary to make High Speed Machining (HSM)<BR>-First to induce very low forces on the wings and fuselage since their support had no rigidity<BR>-Second to achieve very low residual stresses. So the aircraft will have a longer life expectancy<BR>-Third to get a very good surface finishing<BR>-Forth to be able to machine very thin extra thickness in some places<BR>It was necessary to make automatic correction in 6 directions (3 positions and 3 angles) due to the initial<BR>positioning errors of the machine. This is automatically done with the use of external measuring systems. 2 different<BR>technologies can be used. One with touching probe and one with a laser tracker. It is the only machine<BR>around the world working in that way<BR>The technology of HEXAPODE CMW 380 make all that possible.<BR>16<BR>• A new application will arise soon with the maintenance of frames made of composite especially on very<BR>large parts.<BR>o To make repair it will be necessary to start with making a clean machining around the destructed<BR>zone.<BR>o With HSM, orbital drilling, and the use of tools with a small diameter it will avoid the delaminating<BR>problem.<BR>o It could happen everywhere. So it is necessary to make on site machining<BR>o HEXAPODE CMW 380 will again be perfectly suited for solving this soon arising problem<BR>SESSION A2A Life Cycle Support / NDT and SHM<BR>Chair: Prof. J. Narkiewicz (Warsaw University of Technology)<BR>Title: Modern aircraft power system testing<BR>Authors: B. Neuner (AMETEK Programmable Power),<BR>M. van den Bergh (CNS Inc. – Poway)<BR>Time: November 3, 2009 4:00 pm<BR>Room: Lumen<BR>The Airbus A380 and Boeing B787 projects required technological advancements in many areas, including<BR>the onboard electrical power distribution network. Innovations were required not only from Boeing and Airbus<BR>engineering but also from suppliers of avionics, flight controls, landing gear, cabin electronics etc. The decision<BR>to replace many hydraulics by electric motor driven systems in the A380 and B787, and changing from a fixed<BR>400 Hz AC to a wide frequency 360 800 Hz AC power system added more challenges. The plethora of electrical<BR>and electronic apparatus all have to co-exist in a compatible manner, without disturbing each other or<BR>the aircraft power distribution network. Thus the power distribution network complexity increased substantially,<BR>and changes affect the 115 and 230 VAC three phase as well as the 28 VDC buses. This article provides some<BR>insight into power system EMC testing, in accordance with standards such as DO-160, ABD0100.1.8 (Airbus),<BR>and the 787B3 (Boeing) standards. In addition, the newer ABD0100.1.8.1B for the Airbus A350 project, and<BR>the AMD-24 for the A-400M Aircraft will be mentioned briefly. …<BR>Title: Process planning and assembly structures in aircraft environments<BR>Authors: Dr M. Ehrmann<BR>Dürr Systems GmbH<BR>Time: November 3, 2009 4:20 pm<BR>Room: Lumen<BR>The Dürr Group is a supplier of plant and equipment that commands leading global market positions in its<BR>areas of activity. Business with the automotive industry accounts a major part of its sales. Dürr also supplies innovative<BR>manufacturing and environmental technologies for the aircraft, mechanical engineering, chemical and<BR>pharmaceutical industries. In the aircraft environment we identity various challenges our customer (international<BR>operating aircraft manufactures) are faced with.<BR>Increase o • f productivity<BR>• Reducing throughput time<BR>• Stable and reliable manufacturing processes<BR>• Weight reduction<BR>• Increase Efficiency of components<BR>• Flexibility and customer orientation<BR>Based on these challenges, trends towards lean production principles can be seen. Especially flow production<BR>is implemented in various facilities. Nevertheless, processes are investigated by their automation potentials.<BR>17<BR>In addition, the use of modern materials like CFRP in combination with increasing part dimensions is pushed<BR>forward.<BR>All this has a high impact on organization, processes, equipment, conveyor systems, handling and information<BR>flow. In order to ensure a holistic set up of this changing framework, a systematic planning approach is suggested.<BR>This approach is characterized by specific, well defined phases, considering the specific requirements of<BR>the CFRP materials. …<BR>Title: ILS as seen by an Army : The national French Air Force Library or the<BR>first Open Source based S1000D solution<BR>Authors: S. Vrignon<BR>euroscript International S.A.<BR>Time: November 3, 2009 4:40 pm<BR>Room: Lumen<BR>For the French Air Force as for any army in the world, the documentation of their assets e.g. land vehicules,<BR>ships and of course aircraft, must be updated and distributed during the whole life product cycle. In the mean<BR>time not only the French government had clearly indicated its willingness to promote open source technologies<BR>where applicable but also had contracted for A400M and RAFALE. The DoD budget is also under strong pressure.<BR>The French Air Force relies on 300 people to ensure the update, the review, the approval and the publishing of<BR>more than 21,000 documents to 30,000 readers each having of course its own rights.<BR>So it was stated that the means and the goals were no longer aligned. S1000D adoption was a straight forward<BR>decision. The change management was a central and global consideration :<BR>• Data conversion<BR>• A single platform for un-structured and structured documents<BR>• New processes<BR>• New tool : XML under S1000D authoring and management<BR>• New means of dissemination<BR>So the open source based solution became the best option and we will explain why it remains the best for any<BR>army in the world. Armies are transitioning to a new management model that affects all their means including<BR>the documentation. We’ll explore this in our presentation.<BR>Title: Requirements Engineering supports Life Cycle Management<BR>Authors: M. M&auml;useler<BR>GfU Gesellschaft für Unternehmenslogistik mbH<BR>Time: November 3, 2009 5:00 pm<BR>Room: Lumen<BR>Various functions of a company use product data during the life cycle. First, the product will be invented or<BR>developed. Partially, complete systems or parts will be subcontracted. Suppliers must be selected and deliverables<BR>must be tested and integrated. After the entry into service components will be changed, redesigned,<BR>varied or used for new developments. Product manager has to monitor the impact of changes in all phases of<BR>the life cycle. The higher the complexity of the product the higher the effort he has to spend to fulfill this task.<BR>Forgotten requirements from connected processes, functions or products cost more money the later they will be<BR>identified. Requirements Engineering (RE) is the method to save costs by identifying these impacts immediately<BR>in all phases of the life cycle.<BR>Prerequisite is the capturing of all requirements as objects with an unique identifier and additional information from<BR>the beginning. The benefits are manifold. First all requirements will be identified quicker than reading a continuous<BR>text. Beside this the clearness of the specification will increase. Further on each requirement could be addressed in<BR>communication precisly with e.g. stakeholders for requirement validation, potential suppliers or test departements.<BR>18<BR>The exceeding of a certain amount of requirements in a single collection is attended by a loss of its clearness.<BR>Requirements should be allocated into several subcollections. A cascade of collections arise. Each collection<BR>remains manageable. To keep the overview links will be established between the collections on requirement<BR>level. If one requirement changes all linked requirements will be identified automatically. It could be checked<BR>easily, if these requirements are impacted of the change.<BR>Capturing requirements in a solution neutral way has various advantages over the life cycle. The solution isn’t<BR>fixed; every feasible solution could be checked. Beyond that potential suppliers could offer new approaches,<BR>technologies, processes that were unknown yet. In the case of asking for fixed solutions, innovations will be<BR>blocked.<BR>Another advantage of the solution neutral capturing is the high rate of reuse of requirements. Products of one<BR>family varies in several dimensions and parameters. But by checking the differences in detail, commonly up to<BR>90% are the same. Best for specifications, that are solution neutral. The authors needn’t start from scratch, but<BR>could start from 90 %, which implies enormous time and cost savings.<BR>But what about the rest of 10% difference between both products? If all requirements were linked even these<BR>requirements at all levels could be identified instantly. The consequences of changes will be displayed and<BR>remain manageable. The exact amount of requirements will be checked against the changes. No dissipation of<BR>ressources is the consequence.<BR>Linking of requirements is the key for high reaction time on changing markets. Market requirements will be followed<BR>through the collection cascade down to part level. All related risks and opportunities could be identified<BR>instantly. Even in the case of fluctuation of employees the product knowledge is implemented in the specification.<BR>If every requirement has additional information brain drain has less impacts.<BR>Finally the optimum can be reached, if the product manager looks beyond RE and integrates other useful methods<BR>in the life cycle management as functional analysis, target costing or logstics-orientated product development.<BR>Title: Model for Eddy Current testing of CFRPs<BR>Authors: M. Cacciola, A. Gasparics, G. Megal, D. Pellicanò, F.C. Morabito<BR>Time: November 3, 2009 5:20 pm<BR>Room: Lumen<BR>In order to improve manufacturing quality and ensure public safety, components and structures are commonly<BR>inspected for early detection of defects or faults which may reduce their structural integrity. Non Destructive<BR>Testing (NDT) techniques present the advantage of leaving the specimens undamaged after inspection. Within<BR>this framework, Eddy Current Testing (ECT) of composite materials is of importance in many domains of industry:<BR>energy production (nuclear plants), transportation (aeronautic), workpiece manufacturing, and so forth.<BR>This technique, based on the investigation of magnetic flux of exciting coils placed close to the specimen under<BR>analysis, is used to detect and characterize possible flaws or anomalies in specimens.<BR>In contrary to the traditional targets of the ECT investigations, the carbon fibre reinforced plastic materials<BR>(CFRPs) has non isotropic and non continuous but patterned spatial distribution of the conductivity due to the<BR>composite structure. Therefore, the study as well as the modelling of the interaction between the composite<BR>materials and the electromagnetic field requires novel approach.<BR>The method of approach depends on the objectives of the investigation. Typical testing configurations may consist<BR>of ferrite core coil probes, placed above a planar (or at least locally planar) composite specimen and operating<BR>at frequency depending on the problem (typically between a few Hz to a few MHz). The aim of ferrite<BR>core is to focus the magnetic flux into the certain area of the specimen, in order to increase the probe sensitivity<BR>to the defect. For each application, the coil model, as well as, the operating frequencies are set according to<BR>the task. This paper proposes an application of a novel electromagnetic computational method for the problem<BR>of ferrite core based ECT probe can be used for inspecting of composite materials.<BR>For our purpose a Finite Element Method (FEM) based software has been exploited in order to optimise the<BR>19<BR>sensor effect and the drop-in suppression, the operating parameters of the frequency and field strength and for<BR>geometrical and physical modeling. In order to simulate the response of a probe to the presence of defects, it<BR>is necessary to study how a probe excites the specimen to be tested, considering its electrical anisotropy. Usually,<BR>the goal is the optimisation of probe and the assessment of such perturbation as lift-off and tilting.<BR>In the investigated situation, the probe is placed above and parallel to a composite block. It is made of a Eprofiled<BR>ferrite core, excited by a coaxial coil. We verify the distortion of EC’s flux lines caused by the presence<BR>of defect and the magnetic field’s density. In our FEM, since we use A-ψ formulation, just the z-component of<BR>magnetic potential A is non null. This paper presents the details and numerical results of our study.<BR>Title: Mobile Measuring and Documentation of Visual Impression and Surface Topography<BR>Authors: Dr P. Weinhold, Dr T. Schü&szlig;ler<BR>Innowep GmbH<BR>Time: November 3, 2009 5:40 pm<BR>Room: Lumen<BR>So far, the visual impression and the micro topography of a lacquer surface could only be measured with highly<BR>sophisticated scientific instruments used in laboratories, such as auto-focus testing devices for topography.<BR>To achieve this, samples had to be removed from the aeroplane for laboratory measurements. Furthermore, up<BR>to now there are no mobile methods or devices available. Methods and devices are needed that generate key<BR>figures in order to quantify results in an objective and reproducible way. The technology has to be capable<BR>of determining the visual impression and surface topography at the same time. The measured data must be<BR>processed in a suitable way to assess the performance of the lacquer coating.<BR>A new mobile measuring technology for documentation of the visual impression of a surface and its topography<BR>has been developed and validated. The topography as well as the visual impression is measured by a<BR>mobile unit under reproducible conditions. The data is recorded, stored and evaluated by a documentation<BR>and analysis software. Thus it is possible to measure the quality of the lacquer surface of an aeroplane wing<BR>directly on the plane without the need to remove the parts.<BR>SESSION A2B SIMULATION FORUM<BR>Chair: Mr Yvan Radovcic (Samtech)<BR>Title: Simulation Driven Product Development with ANSYS Workbench<BR>Authors: Dr M. Hortmann<BR>Time: November 3, 2009 4:00 pm<BR>Room: Candela<BR>Title: Enhancing the Composites Design-to-Manufacturing Process with FiberSIM(R) 2009<BR>Authors: S. Peck<BR>VISTAGY, Inc.<BR>Time: November 3, 2009 4:20 pm<BR>Room: Candela<BR>The FiberSIM(R) CEE (Composite Engineering Environment) software is fully integrated into all major CAD<BR>systems and is based on VISTAGY‘s EnCapta technology that allows the storage of specific-engineering data<BR>(at the feature level) right within the CAD part. In this demo of FiberSIM, you will see how the software helps<BR>companies clearly identify and mitigate risks associated with the design and manufacture of composite parts<BR>by virtually creating a „window“ onto the manufacturing floor. The software also increases part quality by<BR>20<BR>providing greater control over design intent and ensures that all parts are manufactured with the prescribed<BR>physical properties intended. In addition, you will see how FiberSIM also bridges the gap between analysis,<BR>design, and manufacturing by creating all the necessary data used by each group within the CAD model.<BR>Title: VERICUT Composite Programming &amp; Simulation<BR>Authors: M. Kürten, P. Block<BR>CGTech Deutschland GmbH<BR>Time: November 3, 2009 4:40 pm<BR>Room: Candela<BR>Von CGTech wurde mit der VERICUT Composite Software eine neue, maschinenunabh&auml;ngige Softwareentwicklung<BR>für die Programmierung und Simulation automatisierter CNC-gesteuerter Faserverbund- und Faserablegemaschinen<BR>vorgestellt. Sie besteht aus zwei Einzelanwendungen: VERICUT Composite Programming (VCP) und<BR>VERICUT Composite Simulation (VCS).<BR>VCP liest die Informationen über CAD-Oberfl&auml;chen und Lagen konturen und fügt Material hinzu, um damit die<BR>Lagen entsprechend den benutzerspezifischen Herstellungsstandards und -vorgaben zu erfüllen. Die Ablegebahnen<BR>sind miteinander verknüpft und bilden bestimmte Ablege folgen. Sie werden als CNC-Progra me für<BR>die automatisierte Ablegemaschine ausgegeben.<BR>VCS liest CAD-Modelle und CNC-Programme, entweder von VCP oder anderen Anwendungen für die Erzeugung<BR>von Ablegebahnen für Verbundwerkstoffe und simuliert die Abfolge der NCProgramme auf einer virtuellen<BR>Maschine. Das Material wird über CNC-Programmanweisungen in einer virtuellen CNC-Simulationsumgebung<BR>auf die Ablegeform aufgebracht. Das simulierte Material, das auf die Form aufgebracht wurde, kann<BR>gemessen und untersucht werden (z.B. auf Material st&auml;rke, Luftspalt oder &Uuml;berlappung), um sicherzugehen,<BR>dass das Programm die Herstellungsstandards und -vorgaben einh&auml;lt. Ein Bericht mit den Simulationsergebnissen<BR>und statistischen Daten l&auml;sst sich automatisch erstellen.<BR>„Es besteht ein klarer Bedarf an Programmiersoftware, die von einem in der Branche anerkannten Softwarehersteller<BR>im Rahmen einer Standard-Software regelm&auml;&szlig;ig aktualisiert und gepflegt wird“, so Peter Vogeli von Electroimpact.<BR>„Die Auslieferung von Maschinen durch kompetente Werkzeugmaschinenanbieter zusammen mit der<BR>Auslieferung von Programmiersystemen durch kompetente Softwareanbieter spiegelt die Praxis in der technisch<BR>ausgereiften Zerspanungsbranche wider.In dieser Branche versuchen die Werkzeugmaschinenanbieter inzwischen<BR>nicht mehr, mit weitaus kompetenteren Programmierfirmen zu konkurrieren.“<BR>Die VERICUT Composite Programming&amp; Simulation Software wurde unabh&auml;ngig von jeder speziellen CNCFaser-<BR>legemaschine (Fiberplacement Maschine) konzipiert, genauso wie eine moderne CAD/CAM-Anwendung<BR>auch verschiedene CNC-Maschinen unterstützt. „Wenn ein Werkzeugmaschinenhersteller auch die Software<BR>zur Programmierung seiner Maschinen entwickelt, ist die Software h&auml;ufig auf die Technologie der Maschine<BR>beschr&auml;nkt“, sagt Bill Hasen jaeger, Leiter für Produktmarketing bei CGTech. „Wenn die Software getrennt von<BR>der Maschine entwickelt und in einer Vielzahl von Anwendungen eingesetzt wird, so erweitert sich sowohl die<BR>Soft ware selbst als auch die zugrunde liegende Technologie. Die Metall bearbeitungs industrie hat dasselbe<BR>mit der Weiter entwicklung bei CAD/CAM erlebt.“<BR>Seit mehr als 20 Jahren verbessert CGTech st&auml;ndig seine VERICUTSoftware für die Metallzerspanung, aber<BR>erst im Jahre 2004 stieg CGTech voll in die Welt der Faserverbundwerkstoffe ein, nachdem Boeing (seit 1989<BR>Kunde bei CGTech) das Unternehmen bat, ein Simulationsprogramm für die AFPMaschine zur Her stellung der<BR>787 zu entwickeln. Dieses Projekt wurde im Jahre 2005 auf die Entwicklung einer Programmierl&ouml;sung für AFPMaschinen<BR>erweitert.<BR>21<BR>Title: Java for Safety Critical Applications<BR>Authors: A. Walter<BR>aicas Allerton Interworks Computer Automated Systems<BR>Time: November 3, 2009 5:00 pm<BR>Room: Candela<BR>Up until now, the preferred language for developing safety critical applications has been Ada, but this is<BR>beginning to change. The number of developers willing to program in Ada is diminishing, while the complexity<BR>of applications is increasing. Where as C and C++ are poor alternatives to Ada, realtime Java specifications<BR>have benefited from strong cross fertilisation from the Ada community, giving realtime Java much of the Ada for<BR>developing safety critical systems.<BR>Though strongly related to standard Java technology such as J2SE and J2EE, realtime Java is really a different<BR>beast. The differences are subtle, so as to benefit from a common language base; but essential. realtime Java<BR>sets itself apart by having much stronger threading semantics and a means of avoiding timing anomalies due<BR>garbage collection, ideally while maintaining the reference consistency automatic object deallocation ensures.<BR>In the past, reference consistency was maintained by disallowing or severely limiting dynamic memory management.<BR>This approach works well for state machine like tasks, but not for more complex applications. The<BR>up and coming Safety Critical Java standard (JSR 302) provides some more flexibility than currently tolerated<BR>by providing a stack like approach to memory allocation and deallocation. This will enable the Java language<BR>to be used at the highest criticality levels in the near term, but does not address increasing complexity well.<BR>In the long run and for applications into the medium criticality today, where complexity is already challenging,<BR>realtime garbage collection offers a more practical solution. Garbage collection relieves the application developer<BR>of reference inconsistency concerns, such as dangling pointers and memory leaks, since these can be<BR>guaranteed by the Java runtime environment. A deterministic, realtime garbage collector can also ensure that it<BR>does not interfere with application meeting timing deadlines.<BR>New work on object oriented technology in SG-5 of the SC 205 / WG 71 Plenary to update the DO-178 standards,<BR>will make certification of Java technology, including the use of virtual machine technology and garbage<BR>collection, easier. In the past, these technologies where up to the discretion of individual certification experts,<BR>who often have only minimal understanding of OO Technology. New standards will provide both stronger<BR>guidelines and rationale for how certification should conducted.<BR>This talk outlines the important Java standards, such as the realtime Specification for Java (JSR 1 and JSR 282)<BR>and Safety Critical Java (JSR 302), as well as proposed changes from SG-5 for object oriented technology.<BR>New garbage collection technology will also be covered. This should give the attendee a good background in<BR>the state-of-the-art of realtime Java Technology and safety certification.<BR>Title: Knowledge Based Engineering using CATIA V5 for High Lift Device Design at Airbus<BR>Authors: T. Baudach, Dr S. Kleiner<BR>engineering methods AG<BR>Time: November 3, 2009 5:20 pm<BR>Room: Candela<BR>In the High Lift Device Design domain Knowledge Based Engineering (KBE) for aero, structure, kinematic and<BR>system design has been decided as a core element in lean engineering at Airbus. Hence, knowledge based<BR>engineering and process chains supported by Template Based Design using CATIA V5 as well as the integration<BR>of calculation and simulation in early design stages were introduced. The following article describes the<BR>usage of KBE based on an example for High Lift Device structure design at Airbus, Germany.<BR>During the concept phase of High Lift Devices different design alternatives and variants come up and need to<BR>be validated concerning requirements regarding weight, loads and static issues, manufacturing, costs, etc. 3D<BR>CAD models of devices are designed and analysed using CATIA V5 in order to meet the demands in early<BR>stages. The structure of high lift devices contains multiple but similar elements such as ribs, spars and stringers<BR>22<BR>which are used as stiffeners. These stiffeners are represented by concept models based on wireframe elements<BR>in CATIA V5 in early design stages. Based on an overall wireframe model simple solid elements were set up in<BR>order to construct the device and perform digital mock-up (DMU, e.g. clash and assembly analysis) and weight<BR>management analysis based on a 3D solid model.<BR>The integration of knowledge capabilities in CAD systems allows capturing, sharing and re-using of design rationale<BR>and engineering know how. KBE has led to massive progress in efficient CAD design and allows an easy<BR>way to modify features and models, re-use and adapt CAD models for design changes, create product variants<BR>and families. High level templates automatically adapt themselves to new design contexts. This full morphing<BR>concept reduces design time and costs to levels not previously met in the industry. In order to automate the<BR>High Lift Design process and reduce repetitive manual tasks the solutions CADSTRUCTURAS for device design<BR>(CAD Structure Assistant) was implemented based on KBE technologies.<BR>At Airbus design templates for ribs, spars, stringers etc. and KBE tools have been provided for the design of<BR>high lift devices. Functions of CATIA V5 Knowledgeware such as document templates, power copies and user<BR>defined features allow designers and engineers to embed knowledge into the structure design and leverage<BR>them to reduce errors and automate design for maximum productivity. The appliance of these templates and<BR>KBE features is supported by an assistant software system which manages the template catalogues und guides<BR>the user through the design process. Hence, CADSTRUCTURAS offers design templates with embedded knowledge,<BR>which encapsulate geometry and design know-how for maximum re-use of high lift device elements. After<BR>that, the assistant software creates interactively intelligent features, parts and assemblies in order to ensure<BR>design compliance with established standards by capturing, managing and sharing corporate knowledge in<BR>rule bases and leverage it across the enterprise.<BR>KBE and CAD result in automated goal driven designs. It accelerates more design alternatives, exploration and<BR>optimization of high lift devices and its structure elements for better design in less time through the interactive<BR>capture of optimization intent, such as cost, weight and material. In addition KBE and CAD ensure design consistency<BR>and quality with rule-based design validation according to standards and best practices. At the end,<BR>the benefits for Airbus using CADSTRUSTURAS besides using CADAERAS for aero design (CAD Aero Assistant)<BR>and CADKINAS for kinematic design (CAD Kinematic Assistant) are reduced costs, higher quality and shorter<BR>design cycle time.<BR>Title: State of the art of composites material simulation<BR>Authors: Dr A. Mete<BR>MSC Software GmbH<BR>Time: November 3, 2009 5:40 pm<BR>Room: Candela<BR>Study of Progressive damage, Fracture, Delamination of composite structures and a methodology to share Native<BR>Geometry and LayUp data between CAD and CAE will be described. The objective of this paper is to show<BR>the advanced composite FEM simulation capability based on innovative tools available with the MSC Software<BR>technology. SimXpert the fully integrated multidiscipline simulation environment is able to manage the Simulation<BR>Process of the advanced composite analysis technologies. Two progressive failure analysis available in MD<BR>Nastran, the MSC‘s multidiscipline solver (MD), to ensure the highest levels of accuracy on composite structures.<BR>Predict the failure of laminated composite structures during critical damage events from local damage such<BR>as matrix cracks, fiber breakage, fibermatrix debonds, and delaminations under normal operating conditions<BR>which may contribute to their failure. The ability to predict the initiation and growth of such damage is essential<BR>for predicting the performance of composite structures and developing reliable, safe designs which exploit the<BR>advantages offered by composite materials. With this approach is possible to ‘track’ the failure modes in detail<BR>for every load step till the final failure of the composite structures.<BR>MD Nastran Composite Simulation Methods includes:<BR>• PFA (Progressive Failure Analysis): Progressive failure analysis predicts the damage initiation, growth,<BR>and final failure of 2D and 3D composite laminated. Available for ‘classic’ failure criteria like Hill, Tsai-Wu<BR>Hoffman and for new available failure criteria like Puck and Hashin, Hashin-tape, Hashin-fabric as well.<BR>23<BR>• Adv. PFA (Progressive Failure Analysis): Micromechanical’s material library, evaluation and damage<BR>evolution is fully integrated in MD Nastran. Based on Micromechanical properties (Fiber and Matrix) MD<BR>Nastran and the available Micromechanical Failure Criteria evaluate the structural and material response<BR>including degradation of material properties due to initiation and growth of damage. Is possible analyze<BR>not only traditional 2-D tape and fabric laminate layups, but also 3-D weaves and braids. Over 20 Micro<BR>Mechanical Failure Criteria available with MD Nastran Adv. PFA analysis including failure mechanisms in<BR>honeycomb composite structures such as Wrinkling, Crimping and Dimpling.<BR>• Cohesive Element: The cohesive element formulation, available in MD Nastran, can be used to simulate<BR>delamination phenomena. It is an energetic method that determines delamination initiation and<BR>propagation. Used by special interface elements with different cohesive material models based on<BR>different energy laws depending from the matrix characteristics. Available for 2D and 3D FEM model.<BR>• VCCT (Virtual Crack Closure Techniques): The VCCT is the fracture mechanics approach for studying<BR>delamination and crack initiation and growth. Available in MD Nastran it is used for calculating the<BR>energy release rate of single or multiple cracks. The results will be obtained for each crack separately.<BR>Each crack consists of a crack tip grid for shells and a crack front for solids.<BR>• Breaking glued contact: A powerful tool to evaluate delamination based on a stress criteria. Release<BR>glued contact when a stress criterion is satisfied.<BR>• SimXpert: SimXpert the fully integrated multidiscipline simulation environment, integrated with MSC‘s<BR>advanced multidiscipline (MD) solver technologies, is able to manage the Simulation Process of all the<BR>advanced composite analysis available with these technologies including the Micromechanics approach<BR>based on Alpha Star Genoa material library. SimXpert is a very new interface concept with a direct user<BR>interface and a template builder interface. MD Nastran is fully addressed thru the new preprocessor<BR>SimXpert.<BR>• SimXpert FiberSim integration: MSC SimXpert and Vistagy FiberSIM interconnection is a link between the<BR>CAD draping and FEM analysis in respect to composite part conception phases. The first level based on<BR>‘first’ layup is used for pre sizing and optimization. The second level including draping directions and<BR>thickness variations is used for part validation and certification. SimXpert and FiberSIM offer a native<BR>geometry access to leading commercial CAD systems: CATIA V5, NX and Pro/ENGINEER.<BR>DAY 2 – 4th November 2009<BR>KEYNOTES<BR>Chair: Albrecht Pfaff (MSC.Software GmbH)<BR>Title: Effects of the corrosion on the structural fatigue life and their<BR>management in the in-service ageing aircraft<BR>Author: Mr G. Avalle, L. Fossati, V. Sapienza<BR>Alenia Aeronautica<BR>Time: November 4, 2009 9:00 am<BR>Room: Frequenz 1<BR>The prevention of corrosion is one of the main factors to be taking into account in the Design phase of A/C<BR>structures.<BR>In the military A/C, designed and developed in the early years ’70, the corrosion prevention methodologies<BR>were widely applied by the using of appropriate materials, protective treatments and sealant which were the<BR>“status of art” at that time.<BR>Nevertheless, due to gradually ageing of the Aircraft fleets and also considering the changes in the operational<BR>requirements, the different environmental conditions and the material and protective selection in the design<BR>phase, the arising of corrosion phenomena are inevitable and leads to detrimental effects on aircraft efficiency<BR>and on the related maintenance costs.<BR>Gianni Avalle<BR>24<BR>In case of corrosion, the local stress increase due to thickness reduction and the effects related to the stress<BR>concentration in consequence of the geometry alterations may have implication on fatigue life of the structural<BR>component.<BR>Therefore, in order to maintain the adequate structural safety level, appropriate measures have to be applied in<BR>the management of the corrosion issue on the In-Service aircraft.<BR>Purpose of this paper, is to present for a case of corrosion, a methodology approach based on theoretical<BR>analysis and test to estimate fatigue penalties due to corrosion on an airframe primary component.<BR>Title: Embraer at a glance, engineering tools for aircraft simulation<BR>Author: Mr Marco Cecchini, Alexandre C. de Moura, Fabio R. Soares da Cunha<BR>Embraer<BR>Time: November 4, 2009 9:30 am<BR>Room: Frequenz 1<BR>Embraer was created after Word War II from a strategic national aircraft manufacturing project. As a large<BR>aeronautical company, Embraer has products in three major markets: commercial jets, business jets, and defense.<BR>It is well known that one of the aeronautical industry fundamentals is high technology, and engineering<BR>tools for aircraft simulation play an important role to guarantee the application of cutting edge technology on<BR>product development process. Aeronautical industry uses a large variety of engineering tools to assist product<BR>development such as virtual reality, knowledge based engineering, digital mock-up and manufacturing, structural<BR>analysis, fluid dynamics, systems engineering, and multidisciplinary design optimization. Training and certification<BR>of people are also key points for the success of the company. The development of new technologies<BR>helps to promote continuous enhancement of current engineering processes. In this scenario, data management<BR>is a matter of special attention, and actual processes shall be captured from people’s minds and properly managed.<BR>This work presents challenges of managing and promoting engineering tools on a large aeronautical<BR>company.<BR>SESSION B1A COMPOSITE STRUCTURES<BR>Chair: Chair: Dr Lesli Cohen (Hitco)<BR>Title: Door surround structures for next generation aeroplanes<BR>Authors: Dr C. Hühne, T. Str&ouml;hlein<BR>DLR<BR>Time: November 4, 2009 10:45 am<BR>Room: Lumen<BR>Due to the continuous increase of fuel prices and a hard contention, there is a high demand for more efficient<BR>aircrafts. At the same time, passengers demand for more comfort, better entertainment and anytime communication<BR>while the authorities raise the safety requirements. All that conflictive demands can only be fulfilled<BR>by combining most advanced engine technology with best aerodynamic shape and high efficient light weight<BR>structures.<BR>The demand for light structural weight can best be reached by applying advanced materials like CFRP with<BR>a high specific strength. This is also the reason while the contingent of CFRP has steadily be increased since<BR>the last 30 years to an actual maximum of ~50% for the coming mid and long range planes B787 and A350<BR>XWB. While cost efficient highly automated CFRP processes are already available for most standard parts<BR>like for the tail planes, fuselage, wing skins, stringers, frames, the floor grid and some other parts, the highly<BR>loaded door surround structure is still planned as differential metal parts as no processes and designs are<BR>available. That means high costs as due to corrosion and fatigue reasons, expensive titanium alloys have to<BR>25<BR>be used. Since different projects the DLR Institute Composite Structures and Adaptive Systems is analysing<BR>and developing door surround structures for the use in civil aircrafts. The requirement list is thereby increasing<BR>permanently.<BR>For ensuring the safety of the CFRP door surround structure, in one of the first concepts, the load carrying skin<BR>and frames are rerouted to the inside, giving space for an additional ultra lightweight sandwich impact absorber<BR>structure. This concept is highly optimised in respect to in-service costs, but needs further production cost reduction.<BR>In order to reduce this, a production analysis of all available CFRP processes and designs showed that<BR>instead of a single process a combination of several technologies would lead to a global optimum. To achieve<BR>the highest benefit of each technology, the DLR has combined the Prepreg with the textile technology with skin<BR>and surround structure in one integral one-shot part.<BR>Due to the demand for faster development time and ramp up time, the DLR has developed new concepts for<BR>door surround structures, where the analysis as well as detailed and mould design can proceed mostly parallel.<BR>The logical result of that assumption is, that the door surround structure as well as the moulds should be designed<BR>up-side-down. In case of a later change of the skin thickness or geometry, only a relatively cheap caul<BR>plate must be adapted.<BR>In actual researches the tolerance management is in focus. For solving the tolerance problem at the interface<BR>to the skin, a compromise of integral and differential design gives the best overall solution: Most of the main<BR>frame, secondary frame, intercostals, sill part and longitudinal beam can be manufactured in a one shot solution,<BR>while simple L-profile connectors will be manufactured and assembled separately.<BR>Title: Cold Duct Fan<BR>Authors: L. Cevolini<BR>CRP Technology<BR>Time: November 4, 2009 11:05 am<BR>Room: Lumen<BR>Among the most significant case studies, developed together with our partners, the “Mini Fan”<BR>described in this document is one of my favourite one, as we tried to choose the most suitable<BR>technology and material to push forward for this project.<BR>We could in fact try to manufacture it with several different technologies, such as CNC machining<BR>or through casting with special metal alloys, or even laser sintering of simple PA12 or PA12 glass<BR>filled (we cooperate in fact also with some companies in France that have PA12 and have tested it<BR>for the mini-fan too), but at the end it has been really clear that WINDFORM&reg; XT was the best<BR>choice. Let’s see why.<BR>We can think about a little fan, whose engine power is given by an electric device, instead of 2/4<BR>strokes engine. By extrapolation, we could even call it small mono stage compressor even if in this<BR>case the static pressure increase is very low (no precise data to be released).<BR>Now, without the classic parameters (due to confidentiality), such as efficiency or level of reaction,<BR>which permit to characterize quality of a turboshaft engine, we will try to explain the advantages of<BR>this project analyzing the data provided by our partner: …<BR>Title: Historic Study of Automated Material Placement Equipment<BR>Authors: Mr D. McCarville<BR>Boeing<BR>Time: November 4, 2009 11:25 am<BR>Room: Lumen<BR>As the commercial aircraft industry attempts to improve airplane fuel efficiency, large airframe components like<BR>wing skins and fuselage barrels are shifting from aluminum to composites. As a result, there is an increased<BR>26<BR>demand for automated material placement (AMP) equipment capable of making large and small highly sculptured<BR>parts. Existing texts and scholarly articles concerning AMP equipment are typically limited in scope to<BR>basic machine functionality and/or vendor specific innovations. Few studies have attempted to create a historic<BR>understanding of how this branch of machinery evolved to its current state. For the current study, various sources<BR>(i.e., scholarly text, trade journals, and patent databases) were examined in order to create the following<BR>historic information: (a) comprehensive equipment definitions, (b) equipment breakdown categorizations, (c)<BR>family trees, and (d) evolutionary timelines covering the past 50 years. The purpose of this study is to provide<BR>foundational information on AMP equipment evolution and future capabilities at a time of economical and<BR>technological change within the commercial aerospace industry.<BR>SESSION B1B IMPROVED SIMULATION<BR>Chair: Albrecht Pfaff (MSC.Software GmbH )<BR>Title: Simulation of aircraft structures using non-linear analysis techniques<BR>Authors: F. Soares (Embraer),<BR>M Lopes de Oliveira e Souza (INPE)<BR>Time: November 4, 2009 10:45 am<BR>Room: Candela<BR>Nonlinear analysis expands engineering capacity to simulate physical problems of structures. The complexity<BR>of new systems requires the usage of more sophisticated simulation techniques to enhance certification process.<BR>Aeronautical structures shall be reliable to comply with certification standards, and they shall be optimized to<BR>fulfill performance requirements. This work explores industry applications and how nonlinear analysis techniques<BR>have been employed on a day-to-day basis of structural analysis. Challenges to improve engineering<BR>simulation are also presented based on industry experience. The focus of this work is the investigation of progressive<BR>failure of composite structures. It is well known that composite materials degradation analysis based<BR>on macromechanical or micromechanical approach plays an important role on progressive failure prediction.<BR>Tailoring geometric instability of reinforced panels such as buckling, postbuckling, mode-jumping and snapthrough<BR>is also important to determine the ultimate load of aircraft structures. This work shows how advanced<BR>finite element tools for certification purpose applied on engineering process have been used to assist engineers<BR>on progressive failure analysis.<BR>Title: Robust Design of Composite Wing Structure, a combined durability and<BR>reliability approach<BR>Authors: F. Rogin, F. Soares, G. Abumeri, Dr F. Abdi (Alpha Star, Embraer),<BR>K. Nikbin (Imperial College)<BR>Time: November 4, 2009 11:05 am<BR>Room: Candela<BR>This paper describes a computational simulation approach devised to perform Robust design of composite<BR>structures that is not sensitive to certain type of failure such as delamination growth. The computational<BR>approach maximizes the durability and damage tolerance (D&amp;DT), and reliability in presence of material ,<BR>fabrication and geometric uncertainties. This computer-based life prediction methodology combines composite<BR>mechanics with finite element analysis, damage and fracture tracking capability, probabilistic analysis, and<BR>robust design optimization algorithm to maximize reliability for given operating condition. NASA Advanced<BR>composite semi wing span structure developed by Boeing (McDonnell Douglas Aerospace Company)<BR>was successfully proof load tested at NASA Langley. The wing stub box is representative of a section of a<BR>commercial transport aircraft wing. The wing structure for Durability and Damage Tolerance was evaluated<BR>first with finite element based multi-scale progressive failure analysis to determine failure modes, locations and<BR>fracture load. The prediction results were then validated against the Langley test data. Next robust design<BR>optimization is used to maximize the wing structural durability without loss in reliability. The applied computa27<BR>tional process ensures that certain type of failure modes, such as delamination progression, are contained to<BR>reduce risk to the structure. The design enhancement is achieved by tailoring the shape of the wing skin/stiffeners<BR>ratio such as height, width, and the skin thicknesses to absorb the energy that induces delamination. The<BR>application of coupled optimization-probabilistic approach to wing platform shows that the structural reliability<BR>and durability can be simultaneously improved with little or no weight penalty.<BR>Title: Preliminary design of aeroelastic experimental slender wing model<BR>Authors: Prof. G.Frulla , Ing. E.Cestino<BR>Politecnico di Torino<BR>Time: November 4, 2009 11:25 am<BR>Room: Candela<BR>Innovative Aircraft designs, such as very long endurance UAVs have necessitated advances in the methods<BR>of computational aeroelasticity. Analyses procedures for conventional aeroelastic phenomena, such as wing<BR>flutter, also need to be revisited for very flexible aircrafts. In general, the sensitivity of the flutter characteristics<BR>of the aircraft to the reference geometry can be quite important, even for relatively small deformations.<BR>The process chain of the aeroelastic flutter analysis should always include an experimental test phase. A wind<BR>tunnel test model, will provide the opportunity to modify and calibrate theoretical models showing the effect of<BR>theoretical approximation and their limits, introducing a discussion about the necessary model modifications<BR>and future investigations.<BR>An experimental aeroelastic slender wing model may be designed using a dynamically scaled model. By<BR>expressing the aeroelastic equations of motion in non-dimensional form, it is possible to relate the behaviour of<BR>the small scale models to that of full-scale wing in flight.<BR>All the physical parameters which have been determined to be significant for flutter response should be appropriately<BR>scaled. These will include elastic and inertia properties, geometric properties and dynamic pressure.<BR>In the case of an advanced very flexible wing configuration, stability studies need to be performed about the<BR>trimmed aircraft configuration, which will be different for each flight condition. In addition to that, geometrically<BR>nonlinear structural effects imply both the presence of significant in- and out-of-plane wing bending displacements,<BR>even though the first ones are usually negligible with linear structural models. The investigation of the<BR>correct structural behaviour of such kind of configurations force the designer to increase the number of test<BR>parameters to deal with. A parametric study will be performed in order to establish an extensive database<BR>useful for identification of driven dimensionless parameters. Starting from the parametric analysis a successive<BR>experimental test model will be preliminary designed following the definition of simplified structural models<BR>used for initial evaluation, (like balsa wing models) to evolve towards more complex cases set up.<BR>SESSION B2A COMPOSITE STRUCTURES<BR>Chair: Gila Ghilai (IAI),<BR>Prof. R. E. Sliwa (Rzeszow University of Technology)<BR>Title: Production of springs with Radius-Pultrusion – a new manufacturing process for<BR>a core element of aircraft technology<BR>Authors: Dr K. Jansen<BR>Thomas GmbH + Co. Technik + Innovation KG<BR>Time: November 4, 2009 1:20 pm<BR>Room: Lumen<BR>It is well known that substituting steel by fibre reinforced material in screw spring applications means potential<BR>weight savings between 30% and 50%. Until now a major drawback was the lack of a suitable continuous<BR>and cost effective production process. The classic process for the manufacturing of fibre reinforced profiles, the<BR>28<BR>pultrusion, only allows the production of straight or slightly bended profiles but no kind of bow or screw. By<BR>inverting this standard process the Radius-Pultrusion™ now allows the production of massive and hollow bows<BR>and screws with nearly unlimited small radii. Thus in the near future the advantages of fibre reinforced material<BR>will be available for nearly all kinds of screw springs.<BR>Title: VISTAGY‘s AeroSuite(tm) for Composite Aircraft Assemblies: The Complete Solution<BR>Authors: S. Peck<BR>VISTAGY, Inc.<BR>Time: November 4, 2009 1:40 pm<BR>Room: Lumen<BR>All trends indicate that composite aerostructures are continually getting more complex. This is due in large part<BR>to the fact that aircraft assemblies have huge volumes of highly interdependent design information. Creating<BR>the initial designs and making subsequent changes to these complex aerostructures is both time-consuming and<BR>error-prone.<BR>In this session you will learn how a tightly integrated suite of software and services for aerostructure development<BR>greatly increases the design and manufacturing efficiency as well as the quality of today‘s complex<BR>composite aircraft assemblies.<BR>The presentation will take a close look at the AeroSuite(tm) software product from VISTAGY illustrated with a<BR>composite skin and substructure assembly taken through an end to end development process. Beginning with<BR>initial thickness requirements the composite skin will be developed including sizing through a closed loop<BR>between composite design and structural analysis, detailed ply definitions and the creation of the final solid.<BR>Transitioning into assembly definition, we will present how all joints, fasteners, and hole requirements can be<BR>captured. Design requirements such as edge distances and countersink limits in the skin will be verified and<BR>producibility checks of the composite part and assembly will be reviewed to ensure manufacturability. The as<BR>purchased condition of supply for details will be generated as well as the intermediate states of the assembly.<BR>The presentation will also feature the automated generation of an AS9102 quality plan that is required for the<BR>First Article Inspection buy-off.<BR>The new generation of all composites airplane requires new design and manufacturing processes and the<BR>AeroSuite(tm) from VISTAGY is what is needed to support an efficient, reliable and faster development process<BR>for building successfully complex modern aerostructures.<BR>Title: Composite bone structure with embedded block<BR>Authors: I. Dikici<BR>Turkish Aerospace Industries Inc.<BR>Time: November 4, 2009 2:00 pm<BR>Room: Lumen<BR>The concept is a bone structure concept as shown in Figure-2 that provides assembly of two parts by opening<BR>threads into metal embedded block (15) installed parallel to composite layer direction (14) during manufacturing<BR>lay-up operation. The “T-cross section” and “L-cross section” cleats as shown in Figure-1, which are used<BR>in composite structures, are eliminated by using this way of connections ease and weight gain is targeted<BR>at the product assembly phase. It was observed that the invention is able to withstand extremely high loads<BR>when compared to parameters determined in the shear force in the direction of resin in composite structures<BR>with fibers. In manual/automatic laying production technique in autoclave curing process, the resin flow and<BR>precision tolerances are taken under control with the new vacuum bagging design, which is realized during the<BR>production of the invention. The concept is especially an alternative to omit the radii effect of composite, which<BR>comes mostly from the uncontrolled lay-up process of composite plies, especially at composite L and T cross<BR>section folding regions.<BR>The concept is targeted to be used in the industries where the assembly connection are primarily targeted to<BR>carry high loads such as aeronautics, space, automotive, marine, furniture and construction sectors, followed<BR>29<BR>by other sectors in which composite design and manufacturing are realized.<BR>This concept is used at ALCAS (EU 6th Framework Program managed by AIRBUSUK) project for the design and<BR>the manufacturing of LWB (Lateral Wing Box) Rib-09 (which is 2.3 m long and 0.5 m in max. width) as shown<BR>in Figure-3. The delivery of the rib was in February 2009 to AIRBUS-UK by TAI. And the assembly concept at<BR>the 30 LWB level is being developed by AIRBUS-UK.<BR>Title: Development of Aircraft Flight Control Surfaces - An Evolutionary Process<BR>Authors: G. Ghilai, Dr A. Green<BR>IAI<BR>Time: November 4, 2009 2:20 pm<BR>Room: Lumen<BR>Historically, many of the earliest applications of composites to aircraft were for flight control surfaces: ailerons,<BR>flaps, elevators and rudders. The weight saving possible with composites is particularly important for these<BR>components. Also, they are removable and replaceable parts for which application of new technologies are<BR>more easily accepted.<BR>IAI applied composite structure to the ailerons of the Astra aircraft about 30 Years ago. Prior to this, these structures<BR>were mechanically fastened sheet metal assemblies or bonded full depth honeycomb metal structures.<BR>The Astra ailerons used pre-cured composite skins and spars, metal fittings and non metallic full depth honeycomb,<BR>structurally bonded (fig. 1). Later developments used one shot co cured structures with integral spar and<BR>leading edges (fig. 2).<BR>Trends in the aircraft industry are in the direction of eliminating honeycomb structures, primarily due to problems<BR>of moisture ingress and water accumulation, even in undamaged structures. Accordingly, when it was decided<BR>to develop a composite rudder for a new IAI aircraft, various non-honeycomb options were considered.<BR>The first option was for integrally stiffened covers cured integrally with front and rear spars, with final assembly<BR>incorporating separately manufactured ribs using mechanical fastening. This concept was complicated to<BR>manufacture and expensive.<BR>A single curing process for all spar structure was then considered, with much better productivity. However this<BR>concept was shown to be too heavy in design and stress analysis studies.<BR>The concept eventually adopted was for an integral one shot cure combined rib and spar torsion box with a<BR>separate front spar attached mechanically. Experience at IAI with a similar structure had proved the efficiency<BR>of such a structure, but had shown that cost efficiency was limited by the prepeg/autoclave technology used.<BR>Accordingly for the new component, RTM manufacturing technology was adopted.<BR>Design evolution, manufacturing process development and structural testing will be described in detail in the<BR>full paper.<BR>Title: Impact damage resistance and compression-after-impact strength of sandwich<BR>composites with graphite-epoxy facesheets and nomex honeycomb cores<BR>(RMIT, Alpha STAR)<BR>Authors: A. Zammit, Prof. J. Bayandor, M. Garg, F. Abdi<BR>RMIT, Alpha STAR<BR>Time: November 4, 2009 2:40 pm<BR>Room: Lumen<BR>Physically motivated and empirically validated finite element models are developed for characterizing the<BR>impact damage resistance and compression-after-impact (CAI) residual strength of sandwich composites com30<BR>prised of woven-fabric graphite-epoxy facesheets and Nomex honeycomb cores. A hierarchical micromechanically<BR>based failure technique is employed to predict local composite failure initiation and damage progression/<BR>growth in both facesheets and core. Numerical estimates of impact damage development, obtained using<BR>GENOA/ LS-DYNA, are compared to experimental results for flat sandwich composite specimens subjected<BR>to drop weight normal impact with spherical steel impactors. Here a combination of ultrasonic C-scan images,<BR>visual inspections, and destructive sectioning measurements from the literature are used to assess impact damage.<BR>Impact damage estimates obtained from dynamic impact simulations are used to establish initial conditions<BR>in material and geometric nonlinear GENOA/ ABAQUS finite models aimed at predicting CAI residual<BR>strength; the effect of adhesive (interfacial) failure on damage resistance and CAI strength is also addressed.<BR>Numerical predictions for impact damage resistance, damage progression, and CAI strength are obtained for<BR>a variety of sandwich composite lay-up configurations and over a range of impact velocities and energies,<BR>impactor diameters, and support boundary conditions. Finite element estimates for facesheet surface strains<BR>correlate well with strain gage measurements, as well with strain measurement obtained using the ARAMIS<BR>optical imaging system. Moreover, numerical estimates of CAI residual strength are consistent with experimental<BR>observations.<BR>Title: Trevira CS – Functional Textiles for Aircraft Interiors<BR>Authors: P. Kruecken<BR>Trevira GmbH<BR>Time: November 4, 2009 3:00 pm<BR>Room: Lumen<BR>Perfectly equipped on board<BR>Trevira CS fabrics have many advantages over fabrics made of natural fibres, not only because of their flame<BR>retardant properties but also due to their colour brilliance, low-crease, dimensional stability and anti-abrasion<BR>qualities, not to mention their breathability. The possibility of washing Trevira CS instead of expensive drycleaning<BR>required by alternative products reduces costs significantly. Trevira CS fabrics also offer the potential<BR>for weight reduction compared to other commonly used materials.<BR>Trevira CS Bioactive fabrics are an excellent choice for improving hygiene in aircrafts. Aircraft seats are used<BR>intensively and by many people all over the world. Therefore, it may be reassuring for passengers to know that<BR>every effort has been taken to limit the growth of bacteria in the upholstery. Trevira CS Bioactive fabrics have a<BR>permanent antimicrobial effect preventing odour formation and growth of bacteria in the upholstery. In addition,<BR>they are also flame retardant.<BR>Trevira CS and Trevira CS Bioactive fabrics satisfy the relevant and important international aviation fire protection<BR>standards. The complete range of permanently flame retardant fibres and filaments gives the designers of<BR>aircraft interior fabrics unlimited scope for new patterns, designs and colours. The flame retardant and antimicrobial<BR>modification are built into the Trevira Polyester molecule and are maintained throughout the entire<BR>lifetime of the fabric.<BR>The Trevira fibres and filament yarns are produced in accordance with the highest standards on sustainable<BR>production.<BR>SESSION B2B SYSTEMS AND COMPONENTS<BR>Chair: Prof. J. Narkiewicz (Warsaw University of Technology),<BR>Dr S. Frohriep (Leggett &amp; Platt Automotive Europe)<BR>Title: Architecture Modelling for IMA platform<BR>Authors: M. Fumey<BR>Thales<BR>31<BR>Time: November 4, 2009 1:20 pm<BR>Room: Candela<BR>Title: Avionic Systems Integration through the use of IMA platforms<BR>Authors: G. Romanski<BR>Verocel GmbH<BR>Time: November 4, 2009 1:40 pm<BR>Room: Candela<BR>The extraordinary advances in computer power, memory sizes and Input/Output bandwidth have stimulated<BR>the evolution of Integrated Modular Avionics (IMA) platforms which can support many aircraft functions. These<BR>functions run as applications in one of many virtual target computers provided by the platform. The applications<BR>must co-operate and co-exist even if they are developed by competing suppliers. It is the platform<BR>supplier’s responsibility to provide a development and verification environment such that applications can be<BR>developed and verified independently and then integrated. The integration mechanisms must guarantee that<BR>the verification evidence developed by the application supplier can be carried forward to the system certification<BR>process.<BR>The IMA Platform supplier may use an ARINC-653 type platform, a Virtual-OS platform, Distributed Interconnected<BR>elements, or a Multiple Independent Layer Security (MILS) platform. These may be implemented on<BR>single processors, dual-core or multi-core systems with various communication topologies. Whichever technologies<BR>are used, the underlying safety concerns persist. Fault isolation, error management, I/O, use of shared<BR>resources, including processing power and memory must all be robustly partitioned and controlled. This integration<BR>must be flexible but also trusted.<BR>Integration through IMA platforms provides great benefits, but only if a contract model between application<BR>developers and system integrators can be established and enforced. If a software application satisfies its interfacing<BR>obligations as specified in the integration contract, then it can be treated as a component which can be<BR>reused on different aircraft.<BR>IMA platforms provide an opportunity to increase the number and quality of aircraft level functions to improve<BR>safety and flying experience.<BR>Title: Innovative Design of a Galley Product Platform by applying a new<BR>Modularisation Method<BR>Authors: H. Jonas, T. Gumpinger, C. Blees, Prof. D. Krause<BR>Hamburg University of Technology<BR>Time: November 4, 2009 2:00 pm<BR>Room: Candela<BR>For the airline passenger the factors price, time schedule and service are most important. In terms of service,<BR>the cabin interior design becomes more and more important for realising airline-individual cabin interior- and<BR>catering concepts. The aircraft galley is an important factor for new concepts to ensure and improve the quality<BR>of service for the passenger. In this context, the requirements of the galley design shifted. Besides airworthiness<BR>and a load capable design the customer’s satisfaction is driven by further aspects. The airlines ask for customised<BR>galleys, which are configurable in terms of operating equipment, product design and functionality. Prior<BR>excitement factors such as reliability, lightweight design and design for maintenance became basic requirements<BR>nowadays.<BR>Especially in the market segment of VIP-Cabins, an individual design of the galleys is focus of the engineering<BR>design process. Nearly every VIP-galley is a unique product, which mostly is an adaption design based on<BR>an existing products. Due to the individual design demands, often the customer brings own design ideas or<BR>features into the product.<BR>32<BR>The above described individual product designs, as well from the airline- as from the VIP-market, lead to a<BR>high internal complexity for the galley manufacturer. Independently from the vertical range of manufacturing,<BR>a large number of different design principles, detail design solutions and single parts lead to likely confusing<BR>development and production processes. Additionally the quality assurance process is made more difficult.<BR>The project1 “FlexGalley” contains the conceptual design of a new, modularised aircraft galley platform. Using<BR>a new Modularisation Method developed by the Institute PKT, the galley design consists of different component<BR>modules, which both provide a standardised platform structure and configurable hat units. The customer can<BR>choose of several pre-configured module alternatives for assembling an individual galley product. The overall<BR>compatibility allows a combination of the galley modules, which allows implementing the demanded design<BR>features and functionalities more easily. Using the modular concept, still it is needed to provide a lightweightoptimised<BR>design. In this context, the principle of Integration of Functions applied inside of the modules offers<BR>benefits.<BR>The modular product structure transforms the external variety, which is offered to the customer, to a much lower<BR>internal variety by using few standardised modules. In this context, Lead User Innovations can directly be used<BR>for expanding or adapting the product portfolio of the company. Issue of the paper is a detailed description of<BR>the modular “FlexGalley” product design, as well as the platform definition and technical realisation aspects.<BR>Title: Optimisation of Pressure Fields with Multi-Electrode Discharge Blocks at<BR>Electro-hydraulic Forming of Aircraft Components<BR>Authors: Prof. M. K. Knyazyev<BR>National Aerospace University “KhAI”<BR>Time: November 4, 2009 2:20 pm<BR>Room: Candela<BR>Along with strong advantages equipment for electrohydraulic forming (EHF) has two significant limitations:<BR>relatively low intensity of impulse pressures (as compared with explosive forming) and low controllability of<BR>pressure fields generated by spark filaments (channels) in discharge chamber.<BR>Multi-electrode discharge block (MDB) is a successful attempt to overcome these limitations. MDB is an assembly<BR>of a large number of electrode pairs with reflecting and directing elements combined into one solid unit<BR>with small distances between electrodes. Principle advantages are the capability to generate pressure fields<BR>of high intensity, higher accuracy of pressure distribution, energy savings, and also capability to operate with<BR>small number of high-voltage capacitors. Though the highest efficiency is obtained when each electrode pair is<BR>equipped with its own capacitor’s bank, the practical tests showed that the most of sheet components could be<BR>formed at high efficiency with number of discharge circuits equal to 60-70 % number of electrode pairs.<BR>High pressure intensity is assured not only high density of energy per area unit, but also by non-linear effects of<BR>compressive waves interaction. Higher controllability of pressure fields is insured by discharges at those electrodes,<BR>which are necessary for certain configuration. Electrodes are connected with special switches in order to<BR>provide proper diagram of loading (impulse pressure field).<BR>Vast experimental investigations allowed obtaining rich results for development of approximation relationships<BR>and simulation of pressure loading fields at any arbitrary configuration of connected (working) electrodes.<BR>Measurements were carried out with multi-point membrane pressure gauges (MMPG). Deformation of metallic<BR>membrane in each point (hole) is proportional to the pressure intensity applied to the membrane.<BR>Calculations with simulation program and experimental forming tests confirmed high efficiency of MDB in<BR>application for typical aircraft sheet components of middle and large sizes. Now the researches are conducted<BR>for further MDB improvements, modifications to combine advantages of both traditional hard punch-and-die<BR>and electrohydraulic impulse forming for deep drawing processes, punching of small-diameter holes and perforations,<BR>as well as for improvements of simulation computer program.<BR>33<BR>Title: Improving Aircraft Passenger Seating Comfort by Comfort Elements and Seat Design<BR>Authors: Dr S. Frohriep, J. P. Petzel<BR>Leggett &amp; Platt Automotive Europe<BR>Time: November 4, 2009 2:40 pm<BR>Room: Candela<BR>Passengers in airline seats are restricted to a narrow space and limited in their possible sitting positions. Thus,<BR>they are in a static situation with potential health risks. Passengers now used to adjustability options in personal<BR>vehicles and home furnishing are less and less willing to accept static aircraft seating with a pre-determined<BR>contour that fits only a margin of its users, a trend that is called “amenity transfer”.<BR>To improve passenger comfort and health, contour changes of seats should be enabled, possibly with motile<BR>elements to enhance dynamic sitting. This paper will present electro-mechanical and pneumatic solutions for<BR>seat contour adjustment. Muscle relaxation, pain relief and increased blood circulation are established physiological<BR>effects of motile seat elements especially relevant for long durations of immobile positions. Passively<BR>moving the contact area between occupant and seat has positive effects for persons with back problems, and<BR>it entails positive effects for healthy individuals in improving well-being.<BR>Concerning microclimate, a material make-up that supports air flow and humidity transport away from the<BR>occupant is to be offered. Due to an open surface, higher transmissibility and moisture transport, fiber offers<BR>a better climate in the contact area between seat and occupant. The immediate contact feel offers comfort<BR>in warm and cold climate, especially important for aircraft use with changing climatic conditions before and<BR>during the flight. A new fiber shaping technology will be introduced that features the possibility to shape the<BR>3D contour of fiber pads. An additional advantage, especially for aircraft industry, is the approximately 40%<BR>weight saving of contoured fiber pads compared to foam.<BR>At Leggett &amp; Platt, computer tools are employed to assess seating comfort with occupants constituting the complex<BR>interface. Research results are continuously incorporated into the process of seat comfort element design.<BR>“Measurable comfort” has been implemented in defined procedures of product development. This process is<BR>applicable to automotive applications for which it has mainly been developed and aircraft seating comfort.<BR>Title: Aeroservoelastic Design and Certification of a Combat Aircraft<BR>Authors: W. Luber<BR>EADS-M<BR>Time: November 4, 2009 3:00 pm<BR>Room: Candela<BR>The aim of the aeroservoelastic flight control system design for an advanced military weapon system is mainly<BR>to avoid interaction between structure and flight control system.<BR>The design strategy of the advanced flight control system development is important through the integrated<BR>design optimization process, which includes besides the modeling of the coupled system of the flight dynamics,<BR>also the structural dynamics, the actuators of the control surfaces and the sensors as well as the effects of the<BR>digital flight control systems.<BR>Results from structural mode coupling investigations from Eurofighter Aircraft are presented. Analytical and<BR>experimental methods to avoid structural mode coupling on ground and during flight are described. Especially<BR>the design of structural notch filters to minimize interaction between structure and flight control system is outlined<BR>using a mathematical model of the elastic aircraft. The paper explains design procedures, design and clearance<BR>requirements, test procedures and the correlation between mathematical model predictions and structural<BR>coupling tests as well as the aeroservoelatic model update using on ground and in flight structural coupling test<BR>results.<BR>34<BR>SESSION B3A IMPROVED SIMULATION<BR>Chair: Fabio Soares (Embraer)<BR>Title: Simulation tools for assessing the reliability and robustness of shell structures<BR>Authors: Prof. M. Oberguggenberger<BR>University of Innsbruck<BR>Time: November 4, 2009 4:00 pm<BR>Room: Lumen<BR>This presentation addresses the longstanding question of assessing the reliability and safety of design of shell<BR>structures. As a rule, computational costs of computing e.g. the buckling behavior of complex shell structures as<BR>arising in aerospace applications are extremely high. We argue that the most useful approach consists in sampling<BR>based sensitivity analysis. In the past years, we developed a pool of Monte Carlo methods for sensitivity<BR>analysis. The methods are based on artificial random variations of the decisive input and shape parameters<BR>and a statistical evaluation of the effects on the outputs.<BR>Relatively small sample sizes suffice for the required accuracy of the statistical indicators. Nevertheless, the<BR>issue of accelerating the computations remains an important one. We are currently engaged in a large research<BR>project that aims at improving computational efficiency and widening the scope of the stochastic models<BR>for the parameter variations. This research project ACOSTA (Advanced Concept for Structure Analysis of large<BR>light weight structures) is carried out jointly with Intales GmbH Engineering Solutions and two departments at<BR>the University of Innsbruck (Mathematics, Civil Engineering), supported by the Austrian Research Promotion<BR>Agency. The project focuses on the buckling behavior of the frontskirt of the ARIANE 5 launcher under various<BR>loading and flight scenarios, and the development of new and faster numerical algorithms.<BR>We report about two major new developments in sensitivity analysis. The first one concerns the combination<BR>of Monte Carlo simulation methods with iterative solvers. We succeeded to show that it is possible to save a<BR>significant amount of computing time by performing a load incremental procedure with an initial set of input<BR>parameters and starting the random variations at a later time, when a larger percentage of the ultimate load is<BR>reached. Our experiments showed that this approach does not disturb the accuracy of the statistical indicators.<BR>We also gained understanding of how and when the random variations should be entered in the iterations.<BR>The second development is about incorporating correlation in the sensitivity analysis. On the one hand, an a<BR>posteriori correlation analysis of output variables and their sensitivities allows searching for the most important<BR>indicators of failure. On the other hand, existing correlations of input parameters can be modelled by copulas;<BR>spatial random variations of parameters across the structures can be modelled by random fields. We extended<BR>our computer codes to include both methods (copulas, random fields). This admits the introduction of further<BR>indicators and thus a more complete sensitivity analysis.<BR>We believe that our methods contribute to progress in the area of simulation, focusing especially on robustness,<BR>safety and improvement of design.<BR>Title: C&AElig;SAM CAE centric Application Framework Application to<BR>AIRBUS Stress Analysis Tool<BR>Authors: G. Malherbe, Y. Radovcic, D. Granville, M. Balzano<BR>SAMTECH, Airbus<BR>Time: November 4, 2009 4:20 pm<BR>Room: Lumen<BR>Aeronautical industry is currently facing high industrial challenges: cycle reduction, high simulation fidelity<BR>(composites challenge…), find a new way of working in a world wide organization, cost reduction, improvement<BR>of aircraft Simulation Lifecycle Management.<BR>35<BR>To answer these challenges in Aircraft Structural Analysis, SAMTECH developed C&AElig;SAM (an acronym for<BR>„Computer Aided Engineering by SAMTECH“), a CAE centric open Application Framework. C&AElig;SAM allows<BR>the customization and the management of the whole aircraft engineering process, involving any commercial<BR>software and in-house skill tools. This environment manages the Product Lifecycle at the simulation level and the<BR>Knowledge Based Engineering (KBE) by encapsulating the customer skills and knowledge into Analysis Processes<BR>and Analysis Methods that ensure the reusability and sharing of knowledge in the context of the Extended<BR>Enterprise. C&AElig;SAM can also be linked to the customer Simulation Data Management system and lastly, thanks<BR>to its graphical interface, data sharing is provided within and across CAE analysis disciplines.<BR>The analyst experts of the company can autonomously build and document their own simulation processes,<BR>involving commercial software, in-house codes, but also re-engineered algorithms with the CAESAM development<BR>toolkit. This includes any kind of simulation, from simple analytic formulas to complex Finite Element<BR>models, for whom advanced capabilities (pre- and post- processing, exchange...) are provided.<BR>Application- The CAE centric application framework CAESAM developed by SAMTECH was chosen by<BR>Airbus for its new harmonised trans-national Structure Analysis environment ISAMI. The main objectives of<BR>ISAMI (which stands for „Improved Structure Analysis Multidisciplinary Integration“) are to rationalize processes,<BR>methods and tools, and to have one common environment for structure analysis disciplines at an Extended<BR>Enterprise level. ISAMI integrates the AIRBUS aircraft structure analyses in one single CAE framework where all<BR>the computation processes, methods, software tools and data are fully embedded.<BR>Since July 2008, this new platform ISAMI is deployed at an Extended Enterprise level and will be used by<BR>AIRBUS for the composite and metallic structural sizing of the A350 XWB to secure the sizing by fully validated/<BR>efficient processes methods and tools, with also advanced capabilities (like NASTRAN or SAMCEF Finite<BR>Element models…) when needed.<BR>Title: Simulation Research Center for Mobile Platforms<BR>Authors: Prof. M. Zasuwa, Prof. J. Narkiewicz<BR>Warsaw University of Technology<BR>Time: November 4, 2009 4:40 pm<BR>Room: Lumen<BR>The paper presents the Simulation Research Center (SRC) that is under development at the Department of Automation<BR>and Aeronautical Systems (DAAS), Institute of Aeronautics and Applied Mechanics (IAAM), Warsaw<BR>University of Technology (WUT).<BR>The objective of the Centre is to provide support for design and development of several mobile platforms by<BR>operating several innovative, reconfigurable simulators. The moving platforms are: UGV robot supporting various<BR>operations for security and anti-disaster operations, helicopter simulator as training device class for flight<BR>and navigation procedures and the platform for fixed-wing aircraft basic instrument training.<BR>The novelty of the approach in the Centre development is the high level of reconfigurability, which allows to<BR>implement simulation models of other, various mobile platforms.<BR>The reconfiguration level is important for simulating operations of very different mobile platforms, which may<BR>operate in ground and air in various environment conditions and scenarios. The software has an open, modular<BR>architecture allowing for the modification, extension and enrichment. Due to their flexibility the simulators<BR>may be used to verify the design of mobile platforms (at the design process and after), and they may be used<BR>for training of the operators both of robots, helicopters and fixed-wings as well as for the validation of the<BR>system elements.<BR>In the paper the requirements, architecture and usability of the simulators are described,<BR>showing the novelty of the solution (both in hardware and software).<BR>36<BR>Title: Flow and Cure Simulation for the Production of Large and<BR>Thick Walled Composite Structures<BR>Authors: F. Klunker, S. Aranda, Prof. G. Ziegmann<BR>TU Claustal<BR>Time: November 4, 2009 5:00 pm<BR>Room: Lumen<BR>Fibre reinforced polymer composites offer desirable properties for the design of lightweight structures and<BR>thus are becoming more and more the materials of choice in the aircraft and aerospace industry. The further<BR>reduction of costs while maintaining the quality is a major challenge to be faced in the production of this kind<BR>of composite parts. A well accepted technology for the manufacturing of structural and semi-structural components<BR>is Liquid Composite Moulding. The production costs reduction in these technologies requires the optimisation<BR>of the impregnation and curing phases. Simulation is a valuable tool for the reduction of the whole cycle<BR>and in consequence, for the rise of the maximum affordable production rate. Especially in the case of complex<BR>geometries, large structures with high permeable media and sandwich panels with core inserts, the flow behaves<BR>in a very complex manner. Flow simulation allows the prediction of the flow front advancement, the total<BR>filling time and the exerted forces within the cavity during impregnation. The evolution of the curing system can<BR>be predicted as well, so different curing cycles can be tested virtually before bringing them into production.<BR>This tool is able to support engineers during design of the manufacture process in order to avoid critical heat<BR>concentration regions during exothermal curing, especially in the case of thick walled parts.<BR>Productive process simulation is based on effective modelling and accurate material models. In this presentation<BR>a method for characterising the permeability of reinforcements with high permeable layer is explained, and<BR>how it can be applied in flow simulation for the design of complex structures is presented as well. An approach<BR>for the management of cure temperatures by means of curing simulation is proposed for the optimisation of the<BR>curing phase of thick components.<BR>Title: Coupled Eulerian-Lagrangian analysis to predict impact damage to<BR>fluid-filled composite structures<BR>Authors: R. A. Gibbon<BR>Frazer-Nash Consultancy Limited<BR>Time: November 4, 2009 5:20 pm<BR>Room: Lumen<BR>Numerical finite element methods are increasingly used to simulate the impact behaviour and subsequent damage<BR>of composite materials.<BR>Within the aerospace industry composites are being specified for a growing number of components to take<BR>advantage of the potential for weight saving that they can offer. However unlike conventional metallic materials,<BR>the complex failure mechanisms of composite structures mean the consequences of an impact event can be<BR>diverse.<BR>A number of aerospace applications of composites result in a fluid-filled composite structure. Damage caused<BR>by an impact event onto these structures is not necessarily limited to the impact site but can also extend to other<BR>areas of the structure as a result of pressure waves in the fluid.<BR>This paper presents the results of an investigation into damage of fluid-filled composite structures using coupled<BR>Eulerian-Lagrangian analysis. The impact is modelled analytically in ABAQUS, and the results compared to<BR>those obtained experimentally.<BR>The work provides an extremely useful insight into how modern numerical simulation methods can be used to<BR>predict damage inflicted upon composite components during impact events encountered during service.<BR>37<BR>SESSION B3B ENGINES<BR>Chair: Prof. H. Funke (FH Aachen)<BR>Title: CFD modeling of combustion and ignition processes in aeroengine<BR>combustion chamber<BR>Authors: Prof. A. Boguslawski, Dr. A. Tyliszczak<BR>Czestochowa University of Technology<BR>Time: November 4, 2009 4:00 pm<BR>Room: Candela<BR>A common view in academic and industrial research centers working on the combustion optimization in<BR>aeroengines is that the real breakthrough in the development of a new design of aeroengine, with significantly<BR>reduced emissions of greenhouse gases, requires advanced modelling of turbulent flow and turbulence/<BR>combustion interaction in combustion chamber. Commonly used in industrial design RANS methods are limited<BR>to steady combustion processes while in the case of non-premixed combustion unsteady large scale structures<BR>are responsible for fuel and oxidizer mixing and as a consequence combustion efficiency. The limitations of the<BR>RANS methodology are well known after the decades of use in industrial applications. Unsteady flame behaviour<BR>and flame stability are especially important in the case of new low emission combustion chambers based<BR>on lean fuel combustion technology. The unsteady and ignition processes are of major importance due to<BR>safety reasons as the altitude relight and light across characteristics are mandatory for a new design of combustion<BR>chamber. A natural choice for efficient modelling of mixing and non-premixed combustion is Large<BR>Eddy Simulation (LES) method according which large scale flow structures controlling mixing of fuel and<BR>oxidizer are resolved directly on the basis of filtered Navier-Stokes equations and small scale structures, much<BR>more isotropic, are modelled with the use of subgrid model. LES approach in industrial applications, much<BR>more feasible for nowadays computers than DNS (Direct Numerical Simulation), still requires very fine meshes,<BR>CPU-time and computer storage capacity so a careful mesh design and quality testing for well validated LES<BR>predictions are required. LES, extensively used for simulations of academic testcases, in industrial design is still<BR>considered as a new tool and particular attention is necessary for validation in the case of complex geometry<BR>industrial flows. Within the lecture some examples of LES predictions quality will be illustrated using academic<BR>test cases of round free jet in isothermal and heated conditions. Then some examples concerning flow predictions<BR>in real aeroengine combustion chamber geometry with strong swirling will be presented and comparisons<BR>between RANS modelling, k-ε and second moment closure, and LES on coarse and sufficiently refined mesh<BR>will be analysed. Within the analysis the results obtained with commercial and academic codes will be taken<BR>into account. Finally the method of Eulerian stochastic fields for turbulence/combustion interaction will be<BR>discussed with examples of ignition modelling in one and three-sector combustor. Some examples on a laboratory<BR>test cases of altitude relight at low pressure simulated with the Eulerian stochastic fields and validated with<BR>experimental data will be discussed.<BR>Title: Electron beam welding– actual applications in the aerospace industry<BR>Authors: G. Ripper, Dr M. Mücke<BR>Steigerwald Strahltechnik GmbH<BR>Time: November 4, 2009 4:20 pm<BR>Room: Candela<BR>Shortage of resources and reduction of pollutant emission on the one hand, increased passenger safety and<BR>comfort standards on the other hand demands new constructions. New concepts has forced designers to use<BR>light-weight material and to redesign turbines in respect of higher efficiencies.<BR>In order to achieve the higher production volumes demanded by the aerospace industry; high welding speeds<BR>with constant quality and low operating costs are absolute requirements. Consequently, production engineers<BR>demand alternative technologies to manufacture the complex components and to satisfy the new requirements.<BR>Typical aircraft components for EB welding will be presented together with tailored processing machines for<BR>these applications. To facilitate the machine operator’s work, tools are developed so that operators can weld<BR>repeatable in shorter times.<BR>38<BR>One important item is the recognition of the welding line. Classical it is done by using a binocular system and<BR>a manual or automatic off line teach in procedure. After teaching the welding line, the programme will be checked<BR>by CNC and can be started. The weld seam and the surrounding area are monitored and recorded with<BR>a CCD camera with a high dynamic range.<BR>With the new technology EBO JUMP the welding line is detected automatically in the area ahead of the<BR>welding seam during the welding. An additional advantage of EBO JUMP is the implemented optoelectronic<BR>viewing system with high depth of sharpness and variable magnification for alignment and positioning of the<BR>work piece and the starting point before the weld starts.<BR>To use all these advantages with already existing machines and not only for new delivered ones, the unit is<BR>developed in that way, that it is capable of being integrated also in existing machines.<BR>Title: High temperature properties and aging effects of soft magnetic<BR>49%Co - 49%Fe - 2%V based alloys with high saturation and<BR>high strength for aircraft generators<BR>Authors: Dr W. Pieper, Dr J. Gerster<BR>Vacuumschmelze GmbH &amp; Co. KG<BR>Time: November 4, 2009 4:40 pm<BR>Room:<BR>For an increasing number of generator and motor applications there are strength requirements to the soft<BR>magnetic material caused by a high rotational speed. Thus additional elements were added to the standard<BR>2-Vanadium-Permendur composition 49%Co - 49%Fe - 2%V acting as inhibitors to grain growth in the annealing<BR>process of the material therefore increasing material strength at moderate ambient temperatures.<BR>The alloys are also potential candidates for high temperature applications due to their high Curie temperature<BR>of 950°C. Earlier reported were limitations of the alloys because of limited phase stability at elevated temperatures.<BR>Yet the kinetics of the process and effects on magnetic and mechanical properties were not clear. In<BR>the following magnetic and mechanical properties of 49%Co - 49%Fe - 2%V high strength alloys with Nb, Ta<BR>and Zr additions at temperatures up to 500°C and long time effects like magnetic aging and high temperature<BR>creep on a timescale &gt;1000h are reported.<BR>Title: First Class Refurbishment for Gasturbine Components<BR>Authors: G. Reich , A. DeWeze, Dr A. Oppert<BR>Turbine Airfoil Coating and Repair GmbH<BR>Time: November 4, 2009 5:00 pm<BR>Room: Candela<BR>Title: Soft Magnetic Cobalt Iron Lamination Stacks for High-Performance Generators<BR>and Motors<BR>Authors: Dr N. Volbers, Dr W. Pieper<BR>Vacuumschmelze GmbH &amp; Co. KG<BR>Time: November 4, 2009 5:20 pm<BR>Room: Candela<BR>Soft magnetic cobalt-iron alloys with 49% Co, 49% Fe and 2% V are commonly used materials for high performance<BR>generators and motors due to their high saturation. As a result of a B2-type ordered structure below<BR>730°C the material has a limited ductility in the final annealed state. To realize high performance electromagnetic<BR>systems these characteristics have to be taken into account.<BR>In a thoroughly optimized production process (VACSTACK&reg;) lamination stacks with extremely high stacking<BR>factors of 98% for 0.1mm laminations have been achieved with optimized magnetic and loss performance. The<BR>excellent core loss of the material in comparison to standard SiFe electrical steel is pointed out.<BR>39<BR>Title: ENFICA-FC: Design, Realisation and Flight Test of New All Electric Propulsion<BR>Aircraft powered by Fuel Cells<BR>Authors: Prof. G. Romeo, Prof. F. Borello<BR>Politecnico di Torino<BR>Time: November 4, 2009 5:40 pm<BR>Room: Candela<BR>DAY 3 – 5th November 2009<BR>KEYNOTES<BR>Chair: Prof. R. E. Sliwa (Rzeszow University of Technology)<BR>Title: The Engineering Supply Chain - Chances and Risks<BR>Author: Dr Frank Arnold<BR>Voith Engineering Services GmbH<BR>Time: November 5, 2009 9:00 am<BR>Room: Frequenz 1<BR>The aerospace engineering services are manifold. They vary from initialization of engineer capacities for OEM<BR>to suppliers executing whole work packages. Accordingly, OEM’s as well as suppliers are facing specific and<BR>different challenges. The projects have to be thoroughly specified and evaluated by the OEM’s concerning<BR>time, volume and integrability. The suppliers on the other hand have to meet the requirements of feasibility and<BR>economic viability. Therefore, so called 1st tier supplier are preferentially consulted when dealing with largescale<BR>and strategically important tasks. These 1st tier suppliers are able to meet the above mentioned demands.<BR>Furthermore, they have the duty to integrate further suppliers – so called 2nd and 3rd tier suppliers – into their<BR>supply chain.<BR>Hence, for both the engineering suppliers and the OEM’s, chances as well as risks are arising from this engineering<BR>supply chain. My key-note lecture will present as well as question both effects.<BR>SESSION C1A AEROSPACE SUPPLY CHAIN<BR>Chair: Chair: Dr Trevor Young (University of Limerick)<BR>Title: Advanced Handling Solutions for Aircraft Parts<BR>Authors: N. Clement, H. Gusterhuber<BR>Konecranes Lifting Systems GmbH<BR>Time: November 5, 2009 9:40 am<BR>Room: Lumen<BR>Title: Improving Aircraft Production - MES tool for optimization of production lines<BR>Authors: U. M&ouml;llmann<BR>Dürr Systems GmbH<BR>Time: November 5, 2009 10:00 am<BR>Room: Lumen<BR>The need for higher efficiency and reduction of costs forces all companies to reduce interfaces within the pro-<BR>Dr Frank Arnold<BR>40<BR>duction and organize the data stream for the benefit of the whole production. A MES (Manufac-turing Execution<BR>System) supports this approach in collecting information from the equipment on the shop-floor and data<BR>from the plant administration systems (orders, supply etc.) and rendering custom-ized evaluations and status<BR>information. A tailored MES helps identifying bottlenecks and streamlines the operation on the shop-floor level.<BR>With even increasing capacities the trouble-free management of production lines is an important step to keep<BR>track with international markets. Experiences from other high-volume industries (e.g. automo-tive) are rendering<BR>a basis for development of MES for aerospace and aircraft industries.<BR>Title: Providing visibility to supplier rationalisation through a tiering structure<BR>Authors: Dr K. Kandadi, Dr D.Bailey, V. Perera<BR>University of Bolton<BR>Time: November 5, 2009 10:20 am<BR>Room: Lumen<BR>Purpose<BR>Supplier rationalisation is a well advocated concept in the discipline of supply chain management (SCM)<BR>(Cousins,1999). Supplier rationalisation utilising the tiering approach reduces the number of suppliers that an<BR>organisation deals with directly but does not necessarily reduce the total number of suppliers in the supply<BR>chain (SC) (Ogden &amp; Carter, 2008). Consequently managing supplier relationships also becomes an important<BR>issue.<BR>In the SCs of industry sectors where the end product is technologically complex and advanced, this process of<BR>rationalisation can be difficult due to multifaceted SC tiering structures. In the face of economic, geo-political<BR>and technological issues, the Original Equipment Manufacturers (OEMs) in the North West of England aerospace<BR>sector sent a strong message to the industry calling for SC restructuring. The non-existence of an effective<BR>supplier tiering structure has lead to difficulties in supplier rationalisation efforts. This paper aims to propose<BR>a tiering structure that will help SC rationalisation through collaborative relationships.<BR>Research approach<BR>A survey was conducted involving 30 aerospace companies in the target region to identify supplier capabilities,<BR>supplier tiers and relationships between various tiers. A comprehensive survey questionnaire comprising indepth<BR>qualitative and quantitative questions was used to identify gaps in the existing structure and recommend<BR>a new pragmatic tiering structure. The sample covered approximately 50 per cent of the aerospace industry in<BR>the region in terms of turnover and number of employees (excluding the OEMs).<BR>Findings and originality<BR>A supplier tiering structure will be presented based on each company’s core capabilities. The proposed tiering<BR>structure will be useful for all the stakeholders (OEMs, policy makers, funding bodies and suppliers) of the<BR>aerospace industry. It will give a pragmatic view to identify the region’s strengths and weaknesses and help<BR>determine joint strategy development by these stakeholders. It will, also, be used by OEMs to identify suppliers<BR>with the required capabilities and as a guide in a supplier rationalisation exercise. This will add to the theory<BR>of tiering based approach to supplier rationalisation where there is a dearth of research.<BR>Practical impact<BR>The development of the tiering structure will help the industry in its supplier rationalisation exercise. It will also<BR>help the industry to understand the issues and challenges for supplier collaboration between various tiers. As<BR>the tiering structure is based on the capabilities of companies, it will help to identify capability gaps and assist<BR>in the subsequent understanding of the competitiveness of the region and help direct future improvements.<BR>41<BR>SESSION C1B COMPOSITE STRUCTURES<BR>Chair: Prof. G.Frulla (Politecnico di Torino)<BR>Title: Some aspects of design and use of smart composite structure<BR>Authors: Prof. B. Surowska, Prof. J. Warminski, Dr H. Debski<BR>Lublin University of Technology<BR>Time: November 5, 2009 9:40 am<BR>Room: Candela<BR>Smart structures are important because of their: relevance to hazard mitigation, structural vibration control,<BR>structural health monitoring, transportation engineering, thermal control and energy saving. Smart materials or<BR>structures have embedded sensors to monitor their own state as well as environmental stimuli. They have the<BR>ability to perform both sensing and actuating functions which sense a change in the environment and responds<BR>by altering one or more of its property coefficients. It is possible to realize the passive or active constructions.<BR>In passive construction (intrinsically-smart) the symmetry and balance of the composite filament plies controls<BR>the elastic deformation response to loading of the composite structure. Intrinsically smart structural composites<BR>can perform functions such as: sensing strain, stress, damage or temperature, thermoelectric energy generation,<BR>EMI shielding, electric current rectification, vibration reduction. They have been attained in polymer-matrix<BR>composites with continuous carbon, polymer, or glass fibers. Continuous carbon fiber epoxy-matrix composites<BR>provide temperature sensing by acting as thermistors and thermocouples. Self-monitoring of damage (whether<BR>due to stress or temperature, under static or dynamic conditions) has been achieved as the electrical resistance<BR>of the composite changes with damage. Self-monitoring of strain (reversible) has been achieved in carbon fiber<BR>epoxy matrix composites without the use of embedded or attached sensors, as the electrical resistance of the<BR>composite in the through-thickness or longitudinal direction changes reversibly with longitudinal strain because<BR>of alterations in the degree of fiber alignment.<BR>The design of glass fiber epoxy matrix composite with embedded sensors and carbon fiber epoxy matrix composite<BR>without sensors for self-monitoring of strain are presented as the first step of smart structure production.<BR>…<BR>Title: High Performance Cutting of Aluminium and Titanium Parts for Aircrafts<BR>Authors: Dr M. Lange<BR>Premium Aerotec GmbH<BR>Time: November 5, 2009 10:00 am<BR>Room: Candela<BR>Machined parts made from plate material, forgings or castings are widely spread in all aircrafts especially as<BR>structural components. High performance cutting processes lead to a high level of flexibility and efficiency needed<BR>due to the highly competitive market. As a first tier supplier of Airbus the Premium Aerotec GmbH delivers<BR>more than 3 million machined parts per year for further assembling.<BR>One particularly demanding activity conducted at the Varel parts manufacturing facil-ity is the 5-axis highperformance<BR>cutting of milled aluminium integral components. In this high-performance environment, fuselage<BR>frames measuring up to seven metres in length are milled in aluminium. As part of the same manufacturing<BR>network, the Premium AEROTEC plant in Augsburg is equipped with equally sophisticated high-performance<BR>milling machines, used for instance to produce titanium components for the central fuselage section of the Eurofighter.<BR>The Varel plant manufactures ma-chined parts (air intake shells and ducts) for the Eurofighter.<BR>Most of the machined parts are typically made from aluminium wrought alloys with a good machinability behaviour.<BR>High end machines can run carbide tools at very high rotational speeds and feeds. Linear driven axis<BR>and direct drives are used to enable these HPC-processes also for small complex components. In the large part<BR>manufac-turing a so called tripod technology at the support of the spindle allows for a simulta-neously highly<BR>dynamic 5-axis machining. For complex rotational parts like trunnions etc. turning milling machine tools are<BR>42<BR>used for a complete machining of these parts on only one machine tool.<BR>The A350 and the composite materials lead to an increasing trend of titanium com-ponents due to a better<BR>corrosion and mechanical compatibility to composites in comparison to aluminium. The Varel plant machined<BR>the first titanium door frames measuring a length up to 4.2m. As raw material Varel uses hand forgings until the<BR>ramp up of the A350 production when die forgings are planned as raw material. Due to the difficult machining<BR>behaviour of titanium in comparison to aluminium the tita-nium door frame machining is a huge challenge. The<BR>pockets can be milled with solid carbide tools at high material removal rates.<BR>Title: Laser joining of fibre reinforced composites<BR>Authors: D. Herzog, P. Jaeschke, H. Haferkamp, C. Peters, H. Purol, A. Herrmann<BR>LZH, FIBRE<BR>Time: November 5, 2009 10:20 am<BR>Room: Candela<BR>Thermoplastic matrix composites are of rising interest due to their superior producability and formability. One<BR>major advantage over epoxy based composites is their weldability. Therefore, it is necessary to make use of<BR>this advantage through application of flexible, reliable welding processes with a high automation potential that<BR>can fulfill the requirements of future high volume productions.<BR>Laser transmission welding is an industrially established joining method for unreinforced polymers. It was first<BR>presented as a potential joining technology involving continuous fibre composites by the authors in /1/, where<BR>high performance polymers such as polyphenylene sulfide (PPS) have been welded to an absorbing joining<BR>partner with a carbon fibre reinforcement. It has been shown that the absorption of the laser radiation takes<BR>place within the carbon fibres and heat conduction leads to the desired joining zone between the materials in<BR>an overlap position.<BR>In this paper, the behaviour of carbon fibre composites as laser absorbing joining partners is further studied.<BR>For detection of the heat distribution during laser irradiation of a carbon fibre composite in dependence of<BR>the relative position, a pyrometer is used. The temperature signal allows for identification of the position of the<BR>laser on the composite with respect to the fibre orientation. In a second step, a closed loop control can be realized,<BR>adapting the laser power and homogenizing the weld seam in the otherwise inhomogenous, anisotropic<BR>material. Using this technology, a method is presented to weld carbon fibre composites to carbon fibre composites,<BR>using a third, laser transparent joining partner for the connection.<BR>SESSION C2A AEROSPACE SUPPLY CHAIN<BR>Chair: Dr Trevor Young (University of Limerick)<BR>Title: Supply Chain Excellence with SCOR<BR>Authors: M. Huber, Dr M. Rübartsch<BR>P3 Ingenieurgesellschaft<BR>Time: November 5, 2009 11:30 am<BR>Room: Lumen<BR>This abstract provides a principal description of the Supply Chain Operations Reference (SCOR) model and an<BR>overview how to achieve based on this methodology Supply Chain Excellence.<BR>Main Topic of SCOR: A Process Framework<BR>- Process frameworks deliver the well-known concepts of business process reengineering, benchmarking, and<BR>best practices into a cross-functional framework<BR>- Standard processes (Plan, Source, Make, Deliver, Return, Enable), standard metrics (Perfect Delivery, Cash<BR>43<BR>Cycle Time, Supply-Chain Cost …), standard practices (EDI, CPFR, Cross-Training …) and pre-defined relationships<BR>between processes metrics and practices.<BR>How SCOR impacts a company<BR>When we solve business problems – which is what SCOR is all about – there are generally three main techniques:<BR>1. One is to look at business processes, business activities in detail, mapping them, and seeing ‘if they make<BR>sense’, when we measure them to see if they are working the right way.<BR>2. Second is to compare our company to others, at all levels and benchmarking measures by selecting the<BR>basis for competition and ensure we are better than competitive performance.<BR>3. Lastly, when we need to look at practices for solving process performance problems, SCOR provides a quick<BR>basis for analysis to ensure we’re starting out at least even with competitors.<BR>Main issues still existing<BR>- Business process re-engineering initiatives are not linked to reference models and develop their own and<BR>isolated environment.<BR>- Industry Best Practise and Benchmarking Information are hard to link to the own business.<BR>- Process analyses are based often on company internal experts. What they know well can be analysed in<BR>detail - what they don’t know remains in a black box.<BR>How can we use the SCOR model<BR>- The five distinct management processes link together (the chain in supply-chain) seamlessly from supplier to<BR>customer – end-to-end.<BR>- Standard language and standard nomenclature accelerates process understanding and definition.<BR>- Depicts relationship between Supply Chain Partners, Suppliers and Customers.<BR>- Incorporates industry best practices and metrics. …<BR>Title: Openair-Plasma – Cleaning, activation and coating of modern aircraft materials<BR>Authors: C. Buske, Dr A. Knospe<BR>Plasmatreat GmbH<BR>Time: November 5, 2009 11:50 am<BR>Room: Lumen<BR>Nowadays, the highest demands are imposed on surfaces intended to reflect superior quality. From the semiconductor<BR>industry through to the aircraft industry, surfaces ideally matched to the application in question are<BR>needed so that production can proceed in systematic practical fashion without waste. Thus, plastics must be<BR>activated prior to bonding and metals freed of oily contaminants; metal surfaces susceptible to corrosion, especially<BR>in the aircraft sector, must be protected against environmental effects.<BR>Pre-treatment methods used for these purposes include the cleaning of surfaces with solvents, fluorination and<BR>chlorination of plastics, corona or low-pressure plasma processes and mechanical treatments. These methods,<BR>however, are to varying degrees not capable of in-line integration, do not always yield reproducible results or<BR>pollute the environment.<BR>An atmospheric-pressure plasma system capable of in-line integration in numerous applications is presented.<BR>This is based on plasma jets (Openair&reg;-Plasma) which can powerfully activate plastic and metal surfaces. The<BR>effects of the plasma have been demonstrated by ESCA studies and practical bonding trials amongst others on<BR>carbon composites. Measurements over time of surface tension have shown that, depending on the material,<BR>the surface effects achieved have good long-term durability. Furthermore, the possibility of plasma polymerisation<BR>is examined. Chemical additives are mixed with the plasma and these are then deposited on the surface<BR>in question. In this way metal surfaces can be provided with coatings which inhibit corrosion and aid bonding.<BR>It has been shown by salt spray tests that the layers deposited, in particular on aluminium, have a very high<BR>anticorrosion effect. The system is already being successfully employed in the sealing of aluminium engine<BR>housings.<BR>44<BR>On account of its wide range of potential applications Openair&reg;-Plasma technology is numbered among the<BR>key technologies in surface treatment. It is already used today in practically all fields of industry to activate and<BR>clean surfaces in order to improve the adhesion of glues and paints and to achieve better long-term durability.<BR>Title: The technology of high-speed burnless deep grinding for parts from<BR>hard-to-machine materials<BR>Authors: Prof. S. Markovich<BR>Time: November 5, 2009 12:10 pm<BR>Room: Lumen<BR>Now the most progressive method of grinding of parts from hard-to-machine materials is a high-speed deep<BR>grinding. But this technique requires very expensive powerful high-speed special machine tools, expensive<BR>high porous abrasive wheels and cutting emulsion containing surface-active substances. In addition, for today<BR>there exists no solution to grinding burns problems for parts from hard-to-machine materials with formation of<BR>compression residual stresses in a surface layer with deep grinding.<BR>The offered technology is implemented with the special planetary-grinding head installed on a spindle of a<BR>grinding machine. Thus usual grinding wheels and cutting emulsion are used. Provision of the fullest proceeding<BR>of adsorption-plasticizer effect (APE) in the contact zone results in sharp decrease of cutting forces and contact<BR>temperatures in the cutting zone. It excludes burns formation and provides formation of compression residual<BR>stresses in a surface layer of a workpiece resulting in substantial increase of the part life.<BR>The method allows to raise productivity of machining by 2-5 times and decreases consumption of cutting emulsion<BR>by 5-9 times.<BR>The authors have developed the theory for round and flat planetary grinding and the technology of deep grinding.<BR>Criterion conditions of APE proceeding for round and flat deep grinding were developed. On this basis<BR>the technique and technology of deep grindings of flat, profilecomposite and cylindrical details from hard-tomachine<BR>materials were created (compressor and turbine blade foot, cranked and camshafts, shafts and rollers<BR>of units, etc.).<BR>Now the researches are conducted for improvements of simulation computer program and creation of special<BR>maintenance-free planetary-grinding heads.<BR>Title: UK Aerospace supply chain process improvement: the implementation of SC21<BR>Authors: D. Clarke<BR>University of Bolton<BR>Time: November 5, 2009 12:30 pm<BR>Room: Lumen<BR>Purpose<BR>‘Twenty first century supply chains’ (SC21) is an aerospace &amp; defence industry led improvement programme aimed<BR>at increasing the competitiveness of the UK aerospace and defence industry. The purpose of this research<BR>was threefold: first to understand the adoption rate of SC21, second to discover the attitudes of suppliers when<BR>collaborating with different levels of the supply chain to improve the delivery and quality performance, and<BR>thirdly to provide feedback to the Society of British Aerospace Companies (SBAC) on the progress of programme.<BR>Research approach<BR>This is an empirical investigation into the attitudes of suppliers on supply chain management and supply chain<BR>process improvement. Questionnaires were personally given to 22 ‘A class’ suppliers of an aerospace original<BR>equipment manufacturer (OEM), and a further 22 questionnaires were also distributed to other aerospace<BR>45<BR>suppliers through an SBAC regional meeting. The data was analysed quantitatively. This was a cross sectional<BR>survey and the personal distribution ensured very high response rates, giving increased reliability and validity<BR>to the data collected.<BR>Findings and Originality<BR>All the respondents understand what a supply chain is and there is good understanding of what SC21 is in<BR>terms of performance improvement. However, adoption of SC21 is slow, with just over half having signed up to<BR>it. The suppliers are struggling to implement it, and they require more ongoing support. They do however view<BR>supply chain improvement as a priority, and do expect some benefits to result. The originality of this research<BR>lies in the fact that it gives a ‘snap-shot’ of the status of the project from a dyadic viewpoint. A previous survey<BR>in September 2008 by SBAC was of limited use due to the poor response rates from the suppliers.<BR>Research impact<BR>The research impacts are that it adds to the body of knowledge on the propensity of firms to adopt industry<BR>body sponsored improvement projects. It will give feedback to SBAC on the design of future questionnaires in<BR>order to improve response rates.<BR>It will also serve as a test bed for the author to develop questionnaires and structured interviews with the same<BR>group of suppliers as part of a wider research programme focusing on the influence that organsational behaviour<BR>has on the performance of supply chains.<BR>Practical impact<BR>The practical impacts of this research are that SBAC will have a measure of the adoption rate and attitudes<BR>towards the implementation of SC21. A ‘tool-bag’ of suggested improvements to the promotion, content, and<BR>nature of SC21 will be given to SBAC, which will enable wider participation and faster accreditation to the<BR>SC21 standard within the aerospace supply chain.<BR>It also gives the OEM an insight into the attitudes that their suppliers have to supply chain issues and process<BR>improvement and with assistance from the OEM, will allow a more bespoke approach to be taken to supplier<BR>development and improvement.<BR>SESSION C2B INTERNATIONAL CO-OPERATION /YOUNG ACADEMICS<BR>Chair: Prof. A. Boguslawski (Czestochowa University of Technology)<BR>Title: System of Aerospace Education in Aviation Valley<BR>Authors: Prof. R. E. Sliwa<BR>Rzeszow University of Technology<BR>Time: November 5, 2009 11:30 am<BR>Room: Candela<BR>Title: CEIIA-CE and AgustaWestland RDE Partnership – Cross Experiences between<BR>the automotive and aeronautical industries - Case Study:<BR>Composites Design of the Future Lynx Cockpit Door<BR>Authors: F. Passarinho, L. Sim&otilde;es<BR>CEIIA-CE<BR>Time: November 5, 2009 11:50 am<BR>Room: Candela<BR>CEIIA and AgustaWestland(AW) started in the end of 2008 a Research, Design and Engineering (RDE) Partnership,<BR>creating a multidisciplinary Aeronautical Engineering Platform in Portugal.<BR>In the frame work of its offset agreements with the Portuguese government, the Anglo-Italian helicopter company turned<BR>its commitments into an opportunity of developing engineering activities, as well as broaden its base of suppliers.<BR>46<BR>CEIIA-CE is an engineering centre of competence with expertise in product development and in the production<BR>of components and prototypes through advanced manufacturing processes, created to support Portuguese companies<BR>operating in the automotive and aeronautical industries.<BR>Agusta Westland selected CEIIA-CE due to its extensive background experience in product-design for the automotive<BR>industry, both in niche and mass-production applications.<BR>As a pilot project, the assigned task was to research for new materials suitable for aeronautical components,<BR>and demonstrate its potential in a new design for the Future Lynx’s cockpit door.<BR>By relieving it from the constraint of having to use certified materials, AW requested CEIIA-CE to use this project<BR>both for the assessment of alternative materials, and to demonstrate its design capabilities for aeronautical<BR>components.<BR>Title: Advantages of excelling knowledge organisations in international<BR>aerospace cooperation<BR>Authors: T. Geissinger<BR>P3 Digital Services GmbH<BR>Time: November 5, 2009 12:10 pm<BR>Room: Candela<BR>An excelling knowledge organisation – what does this mean? Know-how creates advantages; knowledge organizations<BR>create an impulse for innovation, generate and facilitate the introduction of new technologies.<BR>Which advantages do result for customers?<BR>Knowledge organizations relate to all areas of a company, range from risk management for new projects to<BR>the aspect of knowledge transfer, e.g. in the course of employee attrition or management changes. Knowledge<BR>balance sheets are being used as controlling tools. An established knowledge balance sheet specifically relates<BR>to the following three aspects:<BR>1. The human capital characterizing competences, skills and motivation of employees<BR>2. The organizational capital comprising all organizational aspects and processes that make a company efficient<BR>and innovative.<BR>3. The relational capital of an organisation defined by all relations to external sources (e.g. suppliers, customers,<BR>etc…)<BR>This paper deals in particular with the benefits of a process-driven approach of knowledge organizations when<BR>establishing international cooperation and supply chains. Building international cooperation always goes along<BR>with reorganisation, creating a focus on core competences as a result of outsourcing and expectations of new<BR>innovation. How do you establish such an organisation? There are numerous methods and tools, which support<BR>the constitution of a knowledge organisation: e-learning and coaching, creativity methods e.g. Brainstorming,<BR>Balanced Scorecard and knowledge structures, e.g. Mind Mapping.<BR>The paper will give an insight into<BR>1. the definition of knowledge organizations,<BR>2. the latest methods and tools<BR>3. resulting benefits for customers, employees and hence the company itself<BR>4. the advantages in international cooperation based on today’s expectations in the<BR>aerospace industry<BR>Title: Joint Aerospace Education Initiative<BR>Authors: C. Siegmund, Prof. B Steckemetz<BR>University of Applied Sciences Bremen<BR>Time: November 5, 2009 12:30 pm<BR>Room: Candela<BR>47<BR>Hochschule Bremen, the University of Applied Sciences in Bremen, has started the Aerospace Education Initiative<BR>in the end of 2006. The Ministry of Education and Science in Bremen has officially accepted this initiative<BR>within its high school education profile in Bremen. The team consists of two high schools and Hochschule Bremen<BR>providing the sponsorship for the cooperation with the high schools. The high schools have been chosen<BR>within a competition by taking into regard their effort in the subjects Physics, Mathematics, English and Economy.<BR>In the last three years of high school education the high school students will be educated in these subjects<BR>taking examples and practical case studies of Aerospace Engineering into account. One day in the week is<BR>the project day held at Hochschule Bremen, providing staff people, laboratories and lecture rooms for the high<BR>school students. Furthermore the initiative includes activities for teaching the teachers of the high schools, study<BR>tours, presentations and visits of aerospace companies.<BR>In the final constellation established in Summer 2009 three classes with twenty five high school students per<BR>class are supported in every of the two partner high schools. The initiative puts emphasis on interesting projects<BR>about satellites, rockets, sail plane events and others. The high school students shall be made familiar with demanding<BR>technical and economical topics. Amazement, fun and last but not least success in solving problems<BR>in the area of Aerospace Engineering both by high school teachers and high school students have first priority<BR>of the initiative. It shall at least result in a later decision of the high school students for technical professions and<BR>study programs.<BR>The Aerospace Education Initiative has been awarded by “Deutsche Telekom Stiftung” as a “Junior-Ingenieur-<BR>Academie” of this institution. Furthermore the initiative has been awarded by “Robert Bosch Stiftung” within<BR>the “NaT-Working- Preis” in 2007. The „Stifterverband für die Deutsche Wissenschaft“ supports this activity<BR>by its award „ReformStudiengang Fachhochschule“ for the study program „Aviation Systems Engineering and<BR>Management“ (ILST) of Hochschule Bremen.<BR>SESSION C3A SYSTEMS AND COMPONENTS / WHOLE AIRCRAFT DESIGN<BR>Chair: J. G&ouml;pfert (ID-Consult GmbH)<BR>Title: Tadiran introduces cost-effective, high power military grade lithium battery<BR>Authors: Dr T. Dittrich, Dr C. Menachem, Dr H. Yamin, A. Daniel, Dr D. Shapira<BR>Tadiran Batteries GmbH<BR>Time: November 5, 2009 2:00 pm<BR>Room: Lumen<BR>Tadiran Lithium-Metaloxide cells of type TLM are now available in a Military Grade. They feature an open<BR>circuit voltage of 4V, with a discharge capacity of 500 mAh (20 mA to 2.8V at RT), capable of handling 5A<BR>continuous pulses and 15A maximum high current pulses. These batteries are constructed with a carbon-based<BR>anode, multi metal oxide cathode, organic electrolyte, and shut-down separator for enhanced safety. TLM<BR>Military Grade batteries also feature low self-discharge and a wide operating temperature range of –40°C<BR>to +85°C. These batteries comply with MIL-STD 810G specs for vibration, shock, temperature shock, salt fog,<BR>altitude, acceleration (50,000 gn) and spinning (30,000 rpm) and conform to UL 1642 and IEC 60086-4<BR>standards for crush, impact, nail penetration, heat, over-charge and short circuit, and can be shipped as nonhazardous<BR>goods. Product advantages include:<BR>SMALL, LIGHTWEIGHT, HIGH POWER<BR>4.0 V open circuit voltage, 500 mAh capacity<BR>SAFE DESIGN<BR>Hermetically sealed (glass-to-metal), can be shipped as non-hazardous goods<BR>LOW SELF-DISCHARGE<BR>enables long storage life<BR>48<BR>HIGH SURVIVABILIY<BR>withstands 50,000 gn acceleration and 30,000 rpm spinning<BR>WIDER OPERATING TEMPERATURE<BR>–40°C to +85°C<BR>END-OF-LIFE INDICATION<BR>can be programmed to alert before fully discharged<BR>COTS TECHNOLOGY<BR>far less expensive than reserve/thermal batteries<BR>TLM Military Grade batteries meet the demanding requirements of single use applications such as avionics,<BR>navigation systems, ordinance fuses, missile systems, telemetry, electronic warfare systems, GPS tracking and<BR>emergency/safety devices, shipboard and oceanographic devices. These batteries come in a variety of cylindrical<BR>configurations and can easily be assembled into custom battery packs to meet virtually any requirement.<BR>Apart from the TLM series, Tadiran lithium thionyl chloride primary cells and Pulses Plus™ batteries for high<BR>current pulse applications will shortly be mentioned.<BR>Title: Using the competence of system suppliers in concept competition -<BR>Example Airbus A350<BR>Authors: Dr J. G&ouml;pfert<BR>ID-Consult GmbH<BR>Time: November 5, 2009 2:20 pm<BR>Room: Lumen<BR>Um die Komplexit&auml;t der Produktentwicklung und der logistischen Prozesse zu reduzieren, arbeiten die Flugzeughersteller<BR>zunehmend mit Systemlieferanten zusammen, die gr&ouml;&szlig;ere Entwicklungsumf&auml;nge übernehmen.<BR>Dazu müssen sie schon in der Konzeptphase in den Entwicklungsprozess eingebunden werden. Lange vor dem<BR>ersten Zeichenstrich visualisiert Airbus die unterschiedlichen Konzepte seiner Entwicklungspartner mit Hilfe der<BR>Metus-Methode von ID-Consult. …<BR>Title: Simulation of touch-down and roll phase using advanced aircraft frame<BR>and landing gear models<BR>Authors: Dr R. Lernbeiss (TU Wien/Austrian Airlines),<BR>Prof. H. Ecker, Prof. M.Pl&ouml;chl (TU Wien)<BR>Time: November 5, 2009 2:40 pm<BR>Room: Lumen<BR>Landing gear dynamics are investigated with an MBS-based model of an Airbus A320 upon landing and<BR>during subsequent roll-out with application of brakes achieved by an automatic braking system in conjunction<BR>with an anti skid system. All structural compo-nents of the air-frame are considered flexible including the<BR>landing gear with elastic properties of its structure. Aerodynamic loads are applied to generate lift and drag<BR>acting on the regarding surfaces of the elastic air-frame corresponding to the conditions in flight and roll-out<BR>during the whole simulation. Controlling the flight-path is achieved by a simulated flight control system which is<BR>capable of generating bank and yaw angles as needed to account for crosswind conditions. Also the vertical<BR>speed is controlled during approach, flare and upon touch-down. Landings are simulated with different values<BR>of the landing mass and the centre of gravity of the aircraft. The influence of flight parameters and the landing<BR>weight on the dynamic behaviour of the landing gear is investigated. Special attention is given to landing gear<BR>oscillations like gear-walk and shimmy vibra-tions. Modelling issues are also considered by comparing landing<BR>gear vibrations for dif-ferent models with increasing number of elastic elements included in the airframe.<BR>49<BR>The modular product structure transforms the external variety, which is offered to the customer, to a much lower<BR>internal variety by using few standardised modules. In this context, Lead User Innovations can directly be used<BR>for expanding or adapting the product portfolio of the company. Issue of the paper is a detailed description of<BR>the modular “FlexGalley” product design, as well as the platform definition and technical realisation aspects.<BR>SESSION C3B COMPOSITE STRUCTURES<BR>Chair: Dr. Douglas A. McCarville (Boeing)<BR>Title: Experimenteal and numerical analysis of interlaminar material properties of<BR>carbon fibre composites<BR>Authors: Dr D. Hartung<BR>DLR<BR>Time: November 5, 2009 2:00 pm<BR>Room: Candela<BR>Introduction<BR>Composite are not only used in advanced structures in the aerospace industry, they become more and more<BR>practically be used in classical engineering applications for example the automotive or mechanical industry.<BR>As commonly known composite are particular interesting for lightweight structures because of their advantageous<BR>weight to stiffness and weight to strength ratios. Carbon fibre composites provide highest strength and<BR>stiffness in fibre direction. Despite of these advantageous material properties in fibre directions, the application<BR>of composites is mostly restricted due to relative low material properties perpendicular to that direction. Also<BR>for quasistatic load conditions, the material and failure behaviour of composites is a complex phenomenon, it<BR>dependents on local microscopic damages by low-level load conditions. The load drop of load-displacement<BR>curves correspondent to ultimate material strengths, which are generally higher, compared to damage initiation<BR>limits.<BR>The interlaminar failure between adjacent plies is a common problem of fibre composites especially for thickwalled<BR>structural regions with load introductions. Despite the advantageous strength in fibre direction, the design<BR>and geometry of most structural components are characterised by these interlaminar failure phenomenon.<BR>The interlaminar failure limits are low, compared to the failure limit in fibre direction. The load carrying capability<BR>of thick-walled structures are mainly characterised of the interlaminar material strengths. In order to analyse<BR>the load carrying capability of lightweight structures with critical interlaminare stresses, one have to know the<BR>interlaminar material properties. Furthermore, adequate material and damage models are required. A precise<BR>failure analyse requires the prediction of the damage initiation and particularly the description of a representative<BR>damage evolution function. …<BR>Title: Fire resistant epoxy composites<BR>Authors: Dr M. Heneczkowski , Prof.H.Galina, Dr M. Oleksy<BR>Rzeszow University of Technology<BR>Time: November 5, 2009 2:20 pm<BR>Room: Candela<BR>Epoxy resins and other thermoset matrices are used for fabrication of aircraft composite structures reinforced<BR>with glass, carbon, boron and/or aramides fibres. Growing number of published reports and patents demonstrate<BR>increasing interest in environment friendly flame retardants for these materials. Phosphorus-containing<BR>compounds incorporated into epoxy resins network as comonomers and/or crosslinking agents are more and<BR>more often used to improve the flame resistance of polymer based composites.<BR>Some attention attracted recently also quaternary ammonium salts (QAS) modified montmorillonite clays (organoclays)<BR>that serve as nanoparticles improving mechanical, thermal and fire resistant properties of thermoset<BR>50<BR>matrices. It was found that the best effect of organoclays addition is observed when exfoliated structure of composite<BR>is obtained.<BR>In our investigation we used natural bentonites S and SN (purified and enriched in montmorillonite, produced<BR>by ZGM “Zebiec” – Poland) modified with benzyl-alkyl- dimethylammonium chloride. Composites of epoxy<BR>resin (Epidian 6, liquid bisphenol A resin produced by “Organika-Sarzyna”, Poland) and 0.5, 1.0, 3.0 and<BR>5.0 wt% of organoclay cured with triethylenetetramine were obtained. Fire resistance of composites specimens<BR>were tested according to UL94 HV standard. It was found that fire resistance of prepared specimens depended<BR>on homogenization temperature and organoclay dispersion in the composite precursor mixture …<BR>Title: Non-crimped fabrics: Production, Tendency of Development and there potentials<BR>for aircraft structures<BR>Authors: F. Kruse, Prof. T. Gries<BR>RWTH Aachen<BR>Time: November 5, 2009 2:40 pm<BR>Room: Candela<BR>A longheaded focus of research at the Institute for Textile Techniques of the RWTH Aachen (ITA) is the development<BR>of efficient automated production technologies for shell structures made of fibre composite materials.<BR>In this process dry textile semi-finished products such as multiaxial layers, fabrics or braids are joined to a nearnetshape<BR>textile structure by stitching or binders. These so called preforms are then impregnated in one shot.<BR>An example for the industrial application of this production technology is the pressure bulkhead of the Airbus<BR>A 380.<BR>Especially for shell structures multiaxial, non-crimped fabrics (NCFs) are gaining importance as the semi-finished<BR>product to start from. These NCFs contain up to seven layers which can be produced with orientations up<BR>to +/-20° to the direction of production. 0°-layers can be supplied additionally, but only as the last layer on the<BR>topside of the NCFs. The single layers are fixed by knitting and therefore form an easy to handle, plain structure<BR>of any desired length.<BR>By the use of NCF a highly lessened time is needed for the production of large components such as the wingshells<BR>or sparwebs can be expected. Instead of a multitude of unidirectional prepreg-layers which need to be<BR>laid singulary and slowly by a tape laying machine, the layup now consists of only a few multiaxial NCFs with<BR>the desired layer-setup.<BR>Beside of all advanteges, the production of NCFs is actually restricted to a constant arealweight and constant<BR>width. Thus, an aim of the current research program DFG Researchgroup 860 at the ITA, is to develop the<BR>machines in a way that NCFs with several local reinforcements can be produced continually. This is done by<BR>an innovative supply modul, which cuts preproduced NCFs or UD-Layer to the desired length and feeds them<BR>on the basis layers.<BR>On second focus of the currend research at the ITA is the warpknitting-unit. As a result to the undulation of the<BR>warpknitting-stitches, the ultimate (compression-) strenght in the plain of the laminate usually lower than those of<BR>prepregs. On the other hand, the stitches have a positive effect in cases of impact-loads. Hence the goal was,<BR>to change the knitting-type, the stiching-length and the tension of the knitting yarn continuously while production.<BR>To fulfill this mission, a newly electromechanical driven an computer controlled guidebar was developed<BR>instead of the common mechanical cams-disks. This new guidebar drive can also be used, to change the drapability<BR>of the produced NCF locally.<BR>The oral presentation will close with an outlook on futher developing goals like production of near-netshape<BR>NCFs to reduce the waste of expensive high performance fibres.<BR>51<BR>LEVEL VIA LEVEL C<BR>SEE YOU AGAIN AT AIRTEC 2010<BR>November 02 - 04, 2010<BR>4th International Conference „Supply on the wings“<BR>Aerospace - Innovation through international cooperation<BR>in conjunction with the International Aerospace Supply Fair<BR>AIRTEC 2009<BR>Room Frequenz 1<BR>Entrance (P11)<BR>Room Lumen<BR>Room Candela<BR>Entrance (P11)<BR>

super_xxx 发表于 2010-10-29 15:18:10

于当今航空业大环境中保持竞争力 PPT

:victory:&nbsp;

bocome 发表于 2011-7-31 06:33:48

4th International Conference “Supply on the wings“
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