18Th European Conference on Composite Materials (ECCM-18)
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18th European Conference on Composite Materials (ECCM-18) Athens, Greece 25 - 28 June 2018 Volume 1 of 8 ISBN: 978-1-5108-9693-2 Printed from e-media with permission by: Curran Associates, Inc. 57 Morehouse Lane Red Hook, NY 12571 Some format issues inherent in the e-media version may also appear in this print version. Copyright© (2018) by Applied Mechanics Laboratory All rights reserved. Printed with permission by Curran Associates, Inc. (2020) For permission requests, please contact Applied Mechanics Laboratory at the address below. Applied Mechanics Laboratory Department of Mechanical and Aeronautical Engineering Engineering School, University of Patras Building 2 Patras University Campus Rio, Patras, 265 00, Greece http://www.aml.mech.upatras.gr/en/home/?lang=en Additional copies of this publication are available from: Curran Associates, Inc. 57 Morehouse Lane Red Hook, NY 12571 USA Phone: 845-758-0400 Fax: 845-758-2633 Email: [email protected] Web: www.proceedings.com 18th EUROPEAN CONFERENCE ON COMPOSITE MATERIALS ECCM18 Scientific Programme DAY 1 | Monday | June 25, 2018 08:00 Secretariat opens 08:25-08:50 Hall: Trianti Opening Ceremony 08:50-09:50 Hall: Trianti Plenary Lecture 1 Chair: T.-W. Chou Composite Materials – where we are and where to go Karl Schulte 09:50-10:35 Hall: Trianti Keynote Lecture 1 Chair: V. Kostopoulos Nanocarbon fabrics for energy storage in structural composites Juan Jose Vilatela 09:50-10:35 Hall: Mitropoulos Keynote Lecture 2 Chair: K. Schulte In-process Monitoring and Quality Assurance of Aerospace Composites Nobuo Takeda 10:35-11:00 Hall: Exhibition Area Coffee Break 11:00-13:00 Hall: Trianti 3.10 | Material and Structural Behavior – Simulation and Testing: Fracture and Damage – Lamina and Laminate Level Chairs: K. Kose, S. Pinho 3.10-01 Characterising Voids and Wrinkles in Curved Carbon Fibre Reinforced Polymer Parts using μ-CT and Optical Microscopy A. Ramesh, M. Battley, T. Allen (University of Auckland, New Zealand), C. Hickey (R&D and Design, New Zealand) Two techniques were developed to characterise defects in composites. The first method utilises µ-CT scans and determines geometric features of voids. The second method analyses micrographs to identify the edges of the plies within a laminate and characterises their wrinkle geometry. 3.10-02 Assessment of Failure Modes in Compression Loaded Laminates using Quasi In Situ Computerized Tomography Scans J. J. A. D’haen, S. Kerscher (BMW AG, Germany), M. May, S. Hiermaier (Fraunhofer Institute for High-Speed Dynamics, Germany) This research will investigate the failure evolution for a [45,-45,0]s stacking sequences using sequential computerized tomography scans. It is seen from results that the proposed methodology works well to investigate failure evolution. Furthermore, it is seen that the failure growth is repeatable for specimen with the same layup. 18th EUROPEAN CONFERENCE ON COMPOSITE MATERIALS Scientific Programme ECCM18 DAY 1 | Monday | June 25, 2018 3.10-03 Experimental Characterisation of Macro-Crack Propagation in 3D Woven Composites, Size Effect and Associated Damage Gradient Models V. Médeau (Université Paris Saclay & Safran Aircraft Engines & ISAE-SUPAERO, France), F. Laurin, J. Rannou, A. Hurmane (Université Paris Saclay, France), S. Mousillat (Safran Aircraft Engines, France), F. Lachaud (ISAE-SUPAERO, France) The critical energy release rate G_C was identified on 3D woven carbon/epoxy composites, using CT and SENB specimens. The analysis relied on multiple instrumen- tation methods to monitor the crack growth and compared several methods for the crack detection and G_C estimation in order to obtain a robust process. (Cntd) 3.10-04 Detection of Crack Initiation for Fracture Toughness Evaluation of Thermoset and Thermoplastic Fibre-Reinforced Materials M. G. R. Sause, M. Greisel, N. Schorer (University of Augsburg, Germany) We compare the mode I and mode II fracture toughness values from data reduction of ASTM D 5528 and ASTM D 7905 to results obtained by acoustic emission measurements and digital image correlation analysis. For brittle and ductile materials, the acoustic emission onset values act as most relevant values. 3.10-05 Mode I Intralaminar Fracture Toughness Of 2D Woven Carbon Fibre Reinforced Composites: Pre-Crack Tip Radius Sensitivity D. Dalli, G. Catalanotti, B. G. Falzon (Queen’s University Belfast, United Kingdom) An investigation of the pre-crack tip geometry sensitivity of Double Edge Notch Tension specimens used to determine the mode I intralaminar fracture toughness of 2D woven carbon fibre reinforced composites, using the size effect method 3.10-06 Experimental Verification of the Damage Model of Orthotropic Composite Materials under Multiaxial Loading P. A. Dodonov, N. N. Fedonyuk (The Krylov State Research Centre, Russia) This paper analyses test data for a layered polymeric composite material under combined loading. The tests were performed as per Arcan test principle. The materials tested in this study were based on glass- and carbon non crimp fabrics (NCF) with orthogonal fibers and vinyl-ether binder, (Cntd) 11:00-13:00 Hall: Mitropoulos 3.13 | Material and Structural Behavior – Simulation and Testing: Joining of Composites Chairs: Th. Loutas, A. Turon 3.13-01 Challenges of hybrid laminar flow control (HLFC) in aircraft design and manufacturing F. Martin de la Escalera, Y. Essa, M. Ángel Castello, U. Pillai (AERNNOVA Engineering Division SAU, Spain), A. Chiminelli, M. Lizaranzu (ITAINNOVA-Instituto Tecnológico de Aragón, Spain), P. Maimi (Universitat de Girona, Spain) The purpose of this paper is to describe barriers and efforts made in the design of an aircraft in terms of reducing pollution emission into the atmosphere throughout the structural optimization of the aircraft’s airfoils. In particular, the present work is focused on the design of a leading edge considering Hybrid Laminar Flow Control (HLFC) technology. The technological improvements of this topic are instilled through Clean Sky 2 platform. This will underpin inno- vative developments in the next generation of aircrafts; overcoming the risks and the technologies eventually to join the next market window to replace the current fleet. 3.13-02 On The Manufacturing and Testing of Dissimilar Adhesive Ti-CFRP Joints W. M. van den Brink, P. Nijhuis (NLR, Netherlands), Y. Essa, F. M. de la Escalera Cutillas (AERNNOVA, Spain) In this study, the manufacturing and testing of the coupons for the determination of the strain energy release rates during delamination crack growth in dissim- ilar (metal to composite) adhesive joints is investigated. It is part of the TicoAjo EU project and the results will be used for an application in aerospace (Cntd) 3.13-03 Surface Pretreatments on CFRP and Titanium for Manufacturing Adhesively Bonded Bi-Material Joints W. Wang, J. A. Poulis, S. Teixeira De Freitas, D. Zarouchas (Delft University of Technology, The Netherlands) Adhesive bonding is a highly desirable joining technique to join composites to metals. The surfaces of both composite and metal substrates have to be carefully treated before bonding them together, in order to avoid interface failure between the adherend’s surface and adhesive. (Cntd) 3.13-04 Hybrid Materials - Joining of Polymers and Metals D. Spancken, D. Laveuve (Fraunhofer LBF, Germany), J. Beck (Werkzeugbau S. Hofmann GmbH, Germany), N. Stötzner (We- ber Fibertech GmbH, Germany), K. van der Straeten (Fraunhofer ILT, Germany), A. Büter (Fraunhofer LBF, Germany), F. Henning (Fraunhofer ICT, Germany) The results of cyclic tests show little scatter indicating a stable and reproducible manufacturing process. The static and cyclic internal pressure tests of the test specimens show that the technology can be used for pressure tight applications. 3.13-05 On The Design and Analysis of Interlaminar Fracture Toughness Tests on Dissimilar Metal-Composite Adhesive Joints with Residual Thermal Stresses P. Tsokanas, T. Loutas, V. Kostopoulos (University of Patras, Greece), Y. Essa, F. M. de la Escalera (AERNNOVA Engineering Division SAU, Spain) DCB and ENF interlaminar fracture tests are designed and analysed for metal-composite adhesive joints with residual thermal stresses. The residual thermal stresses significantly affect the SERR and introduce ever-changing mode mixities during pure mode tests. 3.13-06 Analytical Model behavior for Bolted Metal-3D Woven Composite Joints W. El Masnaoui (Université de Toulouse & SAFRAN Aircraft Engines Villaroche, France), A. Daidie, F. Lachaud (Université de Tou- louse, France), C. Paleczny (SAFRAN Aircraft Engines Villaroche, France) This research work deals with development of a simplified beam model for 3D woven-metal bolted joints behavior. An analytical model called “bending beam model” applied to homogenous materials has been identified and investigated. Its adjustability to our application was confirmed through comparisons (Cntd) 18th EUROPEAN CONFERENCE ON COMPOSITE MATERIALS ECCM18 Scientific Programme DAY 1 | Monday | June 25, 2018 11:00-13:00 Hall: Skalkotas 2.08 | Materials Science: Graphene – Graphene-Based Composites Chair: C. Galiotis 2.08-01 Hybrid, Graphene-Reinforced Poly(Ether Ether Ketone) Nanocomposites D. G. Papageorgiou, M. Liu, Z. Li, I. A. Kinloch, R. J. Young (University of Manchester, United Kingdom) In this work, we investigate the viscoelastic properties and creep mitigation of poly(ether ether ketone) (PEEK) reinforced with graphene nanoplatelets (GNPs) and PEEK reinforced with a hybrid graphene and short glass (GFs) or