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Here you can download the papers of the ECCM17 separately. They are sorted by their presentation ID.
"INNOVATIVE AIRCRAFT POLYMER MATRIX COMPOSITES (IAPMC)" PROJECT IN SIP- SM4I JAPAN - INTELLIGENT PROCESS MONITORING AND QUALITY ASSESSMENT OF CFRP STRUCTURES
Nobuo Takeda (University of Tokyo) Shu Minakuchi (University of Tokyo) Akira Hamamoto (University of Tokyo)
The main purpose of this project is to develop high-rate production aircraft PMC products and quality assurance technology for next-generation CFRP aircraft structures, including Low-cost Autoclave and OoA CFRP, and Theromoplastic CFRP.
COMPOSITE FATIGUE DAMAGE EVOLUTION USING DISCRETE DAMAGE MODELING
Endel Iarve (University of Texas Arlington) Kevin Hoos (University of Dayton) Michael Braginsky (University of Texas Arlington) Eric Zhou (University of Dayton) David Mollenhauer (Air Force Research Laboratory)
Discrete Damage Modeling was used to simulate IM7/977-3 [30/60/90/-60/-30]2s laminate under cyclic loading.
ALIGNED CARBON NANOTUBE WEBS IN AEROSPACE CARBON FIBRE REINFORCED POLYMER COMPOSITES FOR ANTI-ICING/DE-ICING APPLICATIONS
Yao Xudan (Queen's University Belfast) Brian Falzon (Queen's University Belfast) Stephen Hawkins (Queen's University Belfast)
This paper reports on an initial investigation into the use of carbon nanotube (CNT) webs incorporated at an interface of a carbon fibre composite laminate to increase thermal conductivity for energy efficient anti-icing/de-icing applications.
A MULTIPHYSIC APPROACH TO PREDICT THE DEGRADATION OF A COMPOSITE MATERIAL DUE TO CURRENT INJECTION
Jean Rivenc (Airbus Group) Richard Perraud (Airbus Group Innovations) Gilles Peres (Airbus Group Innovations) Thierry Zink (Airbus SAS) David Andissac (Airbus SAS) Richard Mills (Airbus Operations) Jacques Cinquin (Airbus Group Innovations)
An study is performed in order to analyse the degradation of a composite material when a short-circuit current flows in the structure. A multiphysics model is developed in order to predict the shape and the depth of the degradation.
INNOVATIVE TOOL AND PROCESS CONCEPT FOR DRILLING CFRP/TITANIUM STACK MATERIAL
Marco Schneider (Fraunhofer IPA) Andreas Gebhardt (Fraunhofer IPA) Philipp Esch (Fraunhofer IPA)
An innovative tooling concept for drilling lightweight stack material is developed and presented. The counter drilling concept achieves higher tool performance and quality output.
DEVELOPMENT OF CARBON FIBER REINFORCED PLASTIC FITTINGS TO ATTACH RODS IN CENTRAL WING BOX OF AIRBUS AIRCRAFT
Jerome Terrazzoni (Airbus Operations) Jean-Brice Rousset (Airbus Operations) Florent Fauchery (SKF Aerospace) Jean-Michel Buchin ()
Carbon fiber reinforced plastic fitting is developed by SKF Aerospace using unfolding concept (patented) for use in Airbus A350 eXtra Wide Body aircraft for weight saving purpose. Specimens are tested to check compliance with requirements.
FATIGUE SUBSTANTIATION AND DAMAGE TOLERANCE EVALUATION OF FIBER COMPOSITE H145 COMPONENTS
Max Wedekind (Airbus Helicopters) Christeline Salmon (Airbus Helicopters) Elif Ahci (Airbus Helicopters)
The new EASA rules for helicopter certification, §27/29.571 and 573 respectively, require a flaw tolerant fatigue substantiation. Within this paper the flaw tolerant safe life substantiation is shown for different composite components.
FORMING THE FUTURE: STRUCTURAL APPLICATIONS FOR FIBRE REINFORCED THERMOPLASTICS IN NEXT GENERATION AIRFRAMES
Robert Jarczyk (Premium Aerotec GmbH) Lukas Meis (Premium Aerotec GmbH) Tim Neitzel (Premium Aerotec GmbH) Klaus Edelmann (Premium Aerotec GmbH) Angelos Miaris (Premium AEROTEC GmbH)
Premium AEROTEC has developed from scratch a process for the production of complex detailed parts reinforced with unidirectional thermoplastic tapes. The developed process meets all requirements concerning production stability and part quality.
FULL SCALE STATIC TEST OF A LIGHTWEIGHT COMPOSITE STRUCTURE
Barbara Goller (Intales GmbH) Manfred Gratt (Intales GmbH) Federico Simonelli (FACC Aerostructures)
A full scale static test of a lightweight composite structure is described, where all steps of load calibration, test preparation and monitoring are discussed. Also methods for assessing the data and comparison with the FE-model are presented.
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