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This session focuses on particle emissions from combustion engines, including measurement methods and fuel effects. Presenter Leonidas D. Ntziachristos, Aristotle University Thessaloniki

“Spotlight on Design: Insight” features an in-depth look at the latest technology breakthroughs impacting mobility. Viewers are virtually taken to labs and research centers to learn how design engineers are enhancing product performance/reliability, reducing cost, improving quality, safety or environmental impact, and achieving regulatory compliance. Telematics, the convergence of telecommunications and informatics, uses electronic and computer technology built in to the vehicle to provide vehicle tracking, satellite navigation, wireless technology, and diagnostic information. In the episode “Diagnostics and Prognostics: Telematics Deep Dive” (8:09), an engineer from Delphi’s Telematics program discusses the advantages and challenges of telematics devices for the automotive industry, demonstrates the installation of an aftermarket telematics device, and shows how telematics can enhance diagnostics and preventative maintenance.

“Spotlight on Design” features video interviews and case study segments, focusing on the latest technology breakthroughs. Viewers are virtually taken to labs and research centers to learn how design engineers are enhancing product performance/reliability, reducing cost, improving quality, safety or environmental impact, and achieving regulatory compliance. In the episode “Composite Materials: Advanced Materials and Lightweighting” (30:20), Molded Fiber Glass Companies, known for its deep involvement in the creative development of the molded fiberglass process for the Corvette, demonstrates the manufacturing of sheet molded composite for fiberglass parts. Tanom Motors introduces the Tanom Invader, a blend between an automobile and a motorcycle made exclusively with composite materials. Finally, Euro-Composites demonstrates the manufacturing of honeycomb core material made out of aramid paper and phenolic resin used in aircraft structures.

At the end of 2006, two MTorres engineers visited the plant of Airbus UK in Filton receiving a new challenge: Find a more efficient way to manufacture Carbon Fiber Spars for the new A350 program. The range of possibilities were wide: manual infusion methods (RTM, RIM, RFI...), Automatic Taping & hot forming, or the new technology proposed, Fiberplacement or AFP. Two (2) options were considered: hot forming+ATL and AFP (both using prepeg technology.) The usage of a flat lay-up + hot forming technology was used in the only Airbus program that used carbon fiber for the wing manufacturing so far, the A400M. The expected greater complexity of A350 spar created doubts on the feasibility of using the above process, while the AFP technology, consisting of laying up directly on the final shape of the spar, also raised questions of technical feasibility, apart from the economic ?business case?, in case the productivity of the cell was not big enough. A ?Spar team?

A significant step is achieved on the flight control actuation system toward the more electrical aircraft through the Airbus A380, A400M and the A350 development phase ongoing. The A380/A400M/A350 features a mixed flight control actuation power source distribution, associating electrically powered actuators with conventional FlyByWire hydraulic servocontrols. In the scope of the preparation of the future Airbus Aircraft, this paper presents the perspectives of the use of the EMA technologies for the flight control systems in the more electrical aircraft highlighting the main technical challenges need to treat: jamming susceptibility, ?on board? maintenance reduction, Operational reliability increase, power electronics and power management optimization, and regarding the environmental constraints, the predicted performances; the benefits associated to the optimized utilization of on-board power sources.

Since 2006 Oak Ridge National Labs (ORNL) and the Pacific Northwest National Labs (PNNL) have conducted research of injection molded long glass fiber thermoplastic parts funded by U.S. DOE. At DOE's request, ACC's Plastics Division Automotive Team and USCAR formed a steering committee for the National Labs, whose purpose was to provide industry perspective, parts materials and guidance in processing. This ACC affiliation enabled the plastics industry to identify additional key research requirements necessary to the success of long glass fiber injection molded materials and their use in the real world. Through further cooperative agreements with Autodesk Moldflow and University of Illinois, a new process model to predict both fiber orientation distribution and fiber length distribution is now available. Mechanical property predictive tools were developed and Moldflow is integrating these models into their software.

The 11 papers in this technical paper collection focus on heat transfer and advances in thermal and fluid sciences. Topics covered include convection, conduction, radiation, porous media, phase change including boiling, condensation, melting and freezing, and more. The 11 papers in this technical paper collection focus on heat transfer and advances in thermal and fluid sciences. Topics covered include convection, conduction, radiation, porous media, phase change including boiling, condensation, melting and freezing, and more.

Abstract In this study, a multi-parameter analysis, using Taguchi method for design of experiments, has been conducted to investigate the optimum curing conditions for E-glass fabric/epoxy laminated composites. The independent variables in the L25 Taguchi orthogonal array were heating rate a, curing temperature TC and curing time tC, including five levels each. Tensile and 3-point bending tests were performed for each experiment number (run number) of the Taguchi L25. In this study, the significant factors for both tensile and flexural performance were temperature and time at 95% confidence level. Specifically, the tensile performance was affected almost equally by both curing temperature and time (32.71% and 35.89%, respectively). The flexural performance was mostly affected by curing temperature (44.02%) and secondarily by curing time (31.52%).

Abstract The paper presents a complete description of the design and manufacturing of a Carbon Fiber/epoxy mold with an embedded Carbon Fiber resistor heater, and the mold performances in terms of its surface temperature distribution and thermal deformations resulting from the heating. The mold was designed for manufacturing aileron skins from Vacuum Bag Only prepreg cured at 135°C. The glass transition temperature of the used resin-hardener system was about 175°C. To ensure homogenous temperature of the mold working surface in the course of curing, the Carbon Fiber heater was embedded in a layer of a highly heat-conductive cristobalite/epoxy composite, forming the core of the mold shell. Because the cristobalite/epoxy composite displayed much higher thermal expansion than CF/epoxy did, thermal stresses could arise due to this discrepancy in the course of heating.

The SAE Aerospace Information Report (AIR) is intended to be used as a process verification guide for evaluating implementation of key factors in bonded repair of fiber reinforced composite structure in a repair shop environment. The guide will be used in conjunction with a regulatory approved and substantiated repair, and is intended to promote consistency and reliability.

This guidebook will assist in the design and integration of composite commercial aircraft structures that exhibit improved durability, maintainability and repairability. For international use by composite aircraft component designers, this book identifies problems that have occurred with various composite components and provides potential problem-solving recommendations. Written primarily for composite design engineers, Design of Durable, Repairable, and Maintainable Aircraft Composites should also prove valuable to those in structural engineering, materials and processing, product support, advanced product development, systems engineering, technical services, and maintenance operations.

SAE CACRC has produced several standards, each representing the best-practice, recommended minimum training syllabus for the aforementioned target groups. The purpose of this document is to promote the use of these SAE standards, particularly for developing training programs for employee training, qualification in airlines and maintenance organizations, and as reference in regulatory guidance material. It summarizes, as a quick reference, the content of each training document and its relation to and interaction with other training documents. Thereby it allows users to select the appropriate training documents and syllabi to establish a comprehensive, sequential training program build-up customized to the specific needs of the aforementioned functions (see figure). This document does not intend to introduce new training content/syllabus.

To create Guidance on the essential information/data that is needed to correctly assess damage and document the damage. A guidance document is proposed as the initial step in which it is documented what essential information is required for a composite repair with the aim to reduce to number of back and forward communications, improve the documents to define damage such as mapping, damage descriptions, sketches, pictures. CACRC Procedures Task Group will be drafting the document.

Increased use of advanced composite structural materials on aircraft has resulted in the need to address the more demanding quality and non-destructive testing procedures. Accordingly, increased utilization of solid laminate composites is driving changes to airline NDT training requirements and greater emphasis on the application of accurate NDT methods. Modules, including an introduction to composite materials, composite NDI theory and practice, special cases and lessons learned, have been produced in addition to various hands-on NDT exercises. A set of proficiency specimens containing realistic composite structures and representative damage has been designed in order to reinforce teaching points of the course and “test” inspector’s proficiency. Extensive details of the course modules, hand-on exercises and the proficiency specimens are all presented in this report.

This document is intended to provide guidance towards setting up a composite repair workshop facility

Detail specification for T700S-12K-50C/#2511 Plain Weave Fabric

The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness.

The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness.

The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness. This is the base specification and it will have three slash/detail specs.

The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. These materials are designed specifically for vacuum bag autoclave cure. These materials are intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness. This is the base specification and it will have two slash/detail specs.