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These advanced checks have resulted in development of many new diagnostic monitors, of varying types, and a whole new internal software infrastructure to handle tracking, reporting, and self-verification of OBD related items. Due to this amplified complexity and the consequences surrounding a shortfall in meeting regulatory requirements, efficient and thorough validation of the OBD system in the powertrain control software is critical. Hardware-in-the-Loop (HIL) simulation provides the environment in which the needed efficiency and thoroughness for validating the OBD system can be achieved. A HIL simulation environment consisting of engine, aftertreatment, and basic vehicle models can be employed, providing the ability for software developers, calibration engineers, OBD experts, and test engineers to examine and validate both facets of OBD software: diagnostic monitors and diagnostic infrastructure (i.e., fault memory management).

Optical fiber has begun replacing copper in avionic networks. So far, however, it has been mainly restricted to non-critical applications (video transmission to the flight deck, IFE?). In order to take advantage of the high-bandwidth, low weight, no EMI properties of optical fibers in all data transmission networks, it will be necessary to improve the testing. One part of the puzzle, which is still missing, is the self-test button: the possibility to check the network and detect potential failures before they occur. The typical testing tool of a technician involved in optical fiber cables is the ?light source ? optical power meter? pair. With this tool, one can measure the insertion loss of the fiber link. A second important parameter, the return loss at each optical connector, is not analysed. In addition, this is only a global measurement, which does not allow the detection of possible weak points.

Edgewater Computer Systems Inc. product RTEdge Platform 1.2 is a software toolset supporting proof based engineering, implementation and deployment of software components, built using the RTEdge AADL Microkernel modeling subset. This is a small subset of the AADL component model and execution semantics, covering threads and thread-groups communicating solely through asynchronous event ports and through explicitly shared data ports. Threads behavior is expressed as state machines and dispatch run time semantics is encoded in a Run-time Executive, enforcing pre-emptive priority dispatch based on statically assigned event priorities, with ceiling priority protocol access to shared data. This simple AADL microkernel semantic core can support all dispatch policies, communication and synchronization mechanisms of a fully fledged AADL run time environment, permitting the systematic use of the RTEdge static analysis tools for AADL compliant software components.

The use of Engine Health Management (EHM) systems has been growing steadily in both the civilian and the military aerospace sectors. Barring a few notable exceptions (such as certain temperature and thrust margin monitoring) regulatory authorities around the world have not required these systems to be certified in any way. This is changing rapidly. New airframes and engines are increasingly being designed with the assumption that EHM will be an integral part of the way customers will operate these assets. This leads to a need for better guidelines on how such systems should be certified. The SAE E-32 committee on Propulsion System Health Monitoring is leading an industry-wide effort to develop a set of guidelines for certifying EHM systems.

By introducing the concept of a separation between graphics and logic, interpreted run time architecture, and defined communication protocol, the ARINC 661 standard has addressed many of the concerns that aircraft manufacturers face when creating cockpit avionics displays. However, before kicking off a project based on the standard, it is important to understand all aspects of the standard, as well as the benefits and occasional drawbacks of developing with ARINC 661 in mind. This white paper will first provide an overview of ARINC 661 to clarify its concepts and how these relate to the development process. The paper will also describe the benefits of using a distributed development approach, and will outline practical, real world considerations for implementing an ARINC 661-based solution. Finally, readers will learn how commercial tools can be used to simplify the creation of displays following the standard to speed development and reduce costs.

This article characterizes the special features of drilling of CFRP/Titanium and -Aluminium stacks. Simplified theoretic models will show how CFRP/Titanium stacks should be machined without scratches and burn marks contacting carbon. Low axial forces and smart chip removal technology are the main characteristics of the drilling tool technology, optimized to reach H8 quality in one shot operation. Presenter Peter Mueller-Hummel, Cutting Tools Inc.

Many manufacturing companies want to apply AFP technology to complex high-curvature part shapes. As new AFP machine technologies are developed to specifically apply material over complex shapes, new and innovative NC programming approaches are needed to successfully, reliably, and accurately apply material with good consolidation, while meeting the fiber direction and coverage requirements. A big issue with AFP is the production rate vs. part complexity. Most complex shapes can be created with a single .125? wide strip (tow) of material. But the production time would be impractically long. So machine builders create 6, 8, 16, even 32 tow AFP heads, and use the widest tow possible for the highest laydown rates. But then wide compaction rollers on these systems have difficulty consolidating material over curved surfaces, and the minimum steering radius of wider tows challenge the software?s ability to meet the layup requirements.

In recent years, all major microprocessor manufacturers are transitioning towards the deploymenet of multiple processing cores on every chip. These multi-core architectures represent the industry consensus regarding the most effective utilization of available silicon resources to satisfy growing demands for processing and memory capacities. Porting off-the-shelf software capabilities to multi-core architectures often requires significant changes to data structures and algorithms. When developing new software capabilities specifically for deployment on SMP architectures, software engineers are required to address specific multi-core programming issues, and in the ideal, must do so in ways that are generic to many different multi-core target platforms. This talk provides an overview of the special considerations that must be addressed by software engineers targeting multi-core platforms and describes how the Java language facilitates solutions to these special challenges.

PRESENTATION ABSTRACT (ROI Approval BOE021811-122) REVIEW OF UPDATED AEROSPACE RECOMMENDED PRACTICES ARP5061A, Guidelines for Testing and Support of Aerospace, Fiber Optic, Inter-Connect Systems RATIONALE: A single source document to capture current best practices, methods, test equipment, and materials that support fiber optic interconnect systems including high-density applications deployed in Aerospace platforms. SCOPE: This presentation will describe how the ARP5061 document provides the maintainer unique guidelines for optical performance testing of short haul fiber optic inter-connect systems used in aerospace vehicles. The focus of this document is to establish common pre and post installation test methods, equipment, materials, and troubleshooting methodologies. QUALIFICATIONS AND TRAINING STANDARDS: The repair and maintenance of a fiber optic system should ONLY BE PERFORMED by qualified personnel.

TAUPE is a collaborative research project co-funded by the European Commission in the framework of the Seventh Framework Programme (FP7). It addresses the aeronautic sector and is composed of 17 partners from 6 European countries. The project lasts 3,5 years (September 2008 ? February 2012), is led by Safran Engineering Services (Labinal, SAFRAN Group) and has a budget of 5.5M?. The project aims to simplify the electrical architecture of aircraft and to reduce the length and mass of cabling by introducing PLC (PowerLine Communication) or PoD (Power over Data) technologies inside the aircraft. Both technologies essentially aim to supply power and data over the same cable.

Presented by: Dan Ott Web Industries Director, Business Development, Advanced Composites Market With the growth of Fiber Placement technology as a preferred automation technology in aerospace manufacturing and the rapid growth of new production line installations, it is crucial to provide material in a form which meets all necessary specifications and supports the optimum productivity available from this major capital investment made by the producer of the parts. Achieving these goals happnes when the part designer, AFP machine builder, and the slit tape producer design the best process and format which provides smooth, efficient and rapid delivery of the prepreg slit tape to the Fiber Placement laydown head. Tape size (width), slit width tolerance, spool shape and size, density of prepreg on the spool, spool change-over and handling processes all play a factor in productivity, and creating (or inhibiting) the best ROI on a full-scale AFP production line.

The Java language is now the most popular programming language for the creation of new software capabilities. Its popularity has resulted in signficant economies of scale, with Java adopted as the primary language of instructional within many university curriculums, an abundance of reusable Java software components and Java software development tools available both from commercial suppliers and as open source technology, a large pool of competent Java developers from which to recruit staff, and a general willingness by senior staff software engineers to invest the effort required to learn this new programming language and technology. This talk describes the special approaches recommended for the use of Java in safety-critical deployments. The talk surveys the current state of the draft JSR-302 Safety Critical Java Specification and describes related experiences with commercially available technologies based on the constraints of early JSR-302 design discussions.

: Fiber Placement equipment has historically been very large and very expensive. Therefore, the AFP process has been mostly exclusive to the larger aerospace companies of the world. In order to achieve more widespread use of the AFP process, a wider variety of machine configurations must be offered and cost of the equipment must be decreased. Commercially available, articulated robotic arms have been identified as an attractive, low cost option for AFP machine platforms. However, incorporating AFP material delivery technology with robotic arms has many challenges. These challenges relate to both hardware and software issues. This presentation will address the technical challenges of using robots as a machine platform for the AFP process and review the current status of this composites lamination equipment technology. Presenter Frederic Challois, Coriolis Composites

All Semi Vendors do have multi core CPUs in their portfolio and adding new devices every day. This is the only possibility to grow performance and fulfill Moore's law. Multi core offers a wide variety of possibilities to reduce hardware complexity, reduce power consumption, shrink board space, expand functionality and performance. On the other hand the software complexity goes up and this directly affects the ability to achieve a certified system. The main trend as of today and in the future is the rising number of cores in a single chip and the increasing functionality of the software. As this trend does not stop at safety critical systems, the System/Solution Architects have to question themselves how to guarantee data integrity, robustness, robust portioning, avoid multi point of failures and race conditions. This presentation will highlight ideas, do's and don'ts for those who will design a safety critical multi Core system today or in the near future.

Probabilistic methods are used in calculating composite part design factors for, and are intended to conservatively compensate for worst case impact to composite parts used on space and aerospace vehicles. The current method to investigate impact damage of composite parts is visual based upon observation of an indentation. A more reliable and accurate determinant of impact damage is to measure impact energy. RF impact sensors can be used to gather data to establish an impact damage benchmark for deterministic design criteria that will reduce material applied to composite parts to compensate for uncertainties resulting from observed impact damage. Once the benchmark has been established, RF impact sensors will be applied to composite parts throughout their life-cycle to alert and identify the location of impact damage that exceeds the maximum established benchmark for impact.

With the increase of functions in the next generation of aircrafts, it has become very important to address reconfigurability. The bottom line is that space and weight available for critical computers in an aircraft remain mostly unchanged. These new functions imply more computation power and so more redundant elements for safety. CPU power has been increased but the latest evolution with the new multi-core CPU's introduces additional difficulties in terms of certification. IMA first generation was the first answer to address some of these problems by enabling the concentration of several certified critical functions in the same physical computer. However, up to now, such implementations were very static and did not scale very well with the increase of functions need for the next generation aircraft. That?s why the avionics industry is looking for improvement of existing solutions and must work on what would be the next generation of IMA (IMA-NG).

With the growing use of carbon fiber composite structure in Aircraft Manufacturing, the challenge of drilling carbon fiber stacked with Titanium has become a focus point. Due to the abrasive nature of the carbon fiber (CF), cutting tool life is relatively short when drilling carbon fiber stalked with Titanium. A common drill wear indicator is exit burr formation in the Titanium. As drilling tools wear due to the abrasive nature of the CF, the exit burr in the in the Titanium increases. This study seeks to understand the factors that lead to tool wear and exit burr formation. A correlation may be made relating drilling thrust forces with exit burr formation. Different cutting tools geometries and materials are studied using a high speed camera to attempt to understand the factors influencing exit burr formation. Findings are optimized and tested. Decreasing exit burr in the drilling of CF and Titanium may increase tool life thereby reducing tool costs to airframe manufacturers.

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.