WorldWideScience

Sample records for avionics

  1. Avionics and Software Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The goal of the AES Avionics and Software (A&S) project is to develop a reference avionics and software architecture that is based on standards and that can be...

  2. Flight Avionics Hardware Roadmap

    Science.gov (United States)

    Hodson, Robert; McCabe, Mary; Paulick, Paul; Ruffner, Tim; Some, Rafi; Chen, Yuan; Vitalpur, Sharada; Hughes, Mark; Ling, Kuok; Redifer, Matt; hide

    2013-01-01

    As part of NASA's Avionics Steering Committee's stated goal to advance the avionics discipline ahead of program and project needs, the committee initiated a multi-Center technology roadmapping activity to create a comprehensive avionics roadmap. The roadmap is intended to strategically guide avionics technology development to effectively meet future NASA missions needs. The scope of the roadmap aligns with the twelve avionics elements defined in the ASC charter, but is subdivided into the following five areas: Foundational Technology (including devices and components), Command and Data Handling, Spaceflight Instrumentation, Communication and Tracking, and Human Interfaces.

  3. Avionics systems integration technology

    Science.gov (United States)

    Stech, George; Williams, James R.

    1988-01-01

    A very dramatic and continuing explosion in digital electronics technology has been taking place in the last decade. The prudent and timely application of this technology will provide Army aviation the capability to prevail against a numerically superior enemy threat. The Army and NASA have exploited this technology explosion in the development and application of avionics systems integration technology for new and future aviation systems. A few selected Army avionics integration technology base efforts are discussed. Also discussed is the Avionics Integration Research Laboratory (AIRLAB) that NASA has established at Langley for research into the integration and validation of avionics systems, and evaluation of advanced technology in a total systems context.

  4. Avionics Architecture for Exploration

    Data.gov (United States)

    National Aeronautics and Space Administration — The goal of the AES Avionics Architectures for Exploration (AAE) project is to develop a reference architecture that is based on standards and that can be scaled and...

  5. Avionics Architecture for Exploration Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The Avionics Architectures for Exploration Project team will develop a system level environment and architecture that will accommodate equipment from multiple...

  6. Software for Avionics.

    Science.gov (United States)

    1983-01-01

    Dr. T. G. Swann Marconi Avionics Ltd., Elstree Way, Borehamwood, Herts. WD6 lRX SUMMARY A myth is a traditional fiction that reveals a greater truth...myths. 1. INTRODUCTIORN A myth is a traditional fiction that reveals a greater truth. Once, long ago, a powerful king wished to buy a toy. He described...ressources machine, fiabilit6, sympt6mes visibles et mesurables oO le logiciel eat consid6rC corume une boite noire ;ayant 6t6 intensivement 6tudi~es elles

  7. Avionics Design for Reliability

    Science.gov (United States)

    1976-03-01

    from having higher than essential reliability : some avionic failures will be catastrophic , some only critical, some of marginal importance. In every...vironnernent climatiques et mdcaniques proches des conditi-Ins rA- silos d’utilisation. Lee essais offectuds mont comparabios & cciii d~crita dana is...liquide mtcanlques et climatiques Varations CCTU O-01A .. esures a3riv rapides de 5 par 51 5 - 10-20-40 chaque s6rie temp~rature (. tthole A) de cycle

  8. Nano-Satellite Avionics

    Science.gov (United States)

    Culver, Harry

    1999-01-01

    Abstract NASA's Goddard Space Flight Center (GSFC) is currently developing a new class of satellites called the nano-satellite (nano-sat). A major objective of this development effort is to provide the technology required to enable a constellation of tens to hundreds of nano-satellites to make both remote and in-situ measurements from space. The Nano-sat will be a spacecraft weighing a maximum of 10 kg, including the propellant mass, and producing at least 5 Watts of power to operate the spacecraft. The electronics are required to survive a total radiation dose rate of 100 krads for a mission lifetime of two years. There are many unique challenges that must be met in order to develop the avionics for such a spacecraft. The first challenge is to develop an architecture that will operate on the allotted 5 Watts and meet the diverging requirements of multiple missions. This architecture will need to incorporate a multitude of new advanced microelectronic technologies. The microelectronics developed must be a modular and scalable packaging of technology to solve the problem of developing a solution to both reduce cost and meet the requirements of various missions. This development will utilize the most cost effective approach, whether infusing commercially driven semiconductor devices into spacecraft applications or partnering with industry to design and develop low cost, low power, low mass, and high capacity data processing devices. This paper will discuss the nano-sat architecture and the major technologies that will be developed. The major technologies that will be covered include: (1) Light weight Low Power Electronics Packaging, (2) Radiation Hard/Tolerant, Low Power Processing Platforms, (3) High capacity Low Power Memory Systems (4) Radiation Hard reconfiguragble field programmable gate array (rFPGA)

  9. EVA Communications Avionics and Informatics

    Science.gov (United States)

    Carek, David Andrew

    2005-01-01

    The Glenn Research Center is investigating and developing technologies for communications, avionics, and information systems that will significantly enhance extra vehicular activity capabilities to support the Vision for Space Exploration. Several of the ongoing research and development efforts are described within this presentation including system requirements formulation, technology development efforts, trade studies, and operational concept demonstrations.

  10. Avionics Modification Research Analysis: From Electromechanical to Digital Avionics and from Digital to Integrated Modular Avionics (IMA)

    OpenAIRE

    Shah, Ghazi Muqaddas Ali

    2014-01-01

    The electronic sets that are being used in aviation industry are commonly summarized as “avionic = aviation electronic equipment”. Nearly seventy years ago the first avionics devices used on aircraft were communication and navigation systems based on old gauge instruments and analog systems. Since then, the industry has evolved a lot and today the avionics systems require for new and smarter functionalities thus driving the overall aviation research to an exponential rate to...

  11. Avionic Data Bus Integration Technology

    Science.gov (United States)

    1991-12-01

    address the hardware-software interaction between a digital data bus and an avionic system. Very Large Scale Integration (VLSI) ICs and multiversion ...the SCP. In 1984, the Sperry Corporation developed a fault tolerant system which employed multiversion programming, voting, and monitoring for error... MULTIVERSION PROGRAMMING. N-version programming. 226 N-VERSION PROGRAMMING. The independent coding of a number, N, of redundant computer programs that

  12. Multifiber optical connectors for avionics

    Science.gov (United States)

    Lubowe, Anthony G.; Million, Troy P.; Sayegh, Emile G.; Baumann, Fred

    1996-10-01

    Until now, there has been no reasonably priced high-density avionics fiber optic connector. AVMACTM connector assemblies, designed to meet this need, consist of Berg AVMAC connectors (F/O contacts), Gore ribbon cable, and HiRelcoTM special self-locking plugs and receptacles. Berg Electronics' MACII multifiber array connector has been used in the telecommunications industry for over 10 years. The 18-fiber version was modified to meet the avionics environment, by using high temperature plastic and epoxy. Also, modified cable assembly techniques were developed for the special cable used. W.L. Core and Associates designed and manufactured the high temperature ruggedized ribbon cable, using patented GORE-TEXTM ribbon buffer to protect the 18 polyimide coated fibers in the harsh environments specified for avionics applications. New materials were introduced to the commercial Gore ribbon design to meet the McDonnell Douglas Aerospace temperature specifications. The HiRel connector design incorporates the optical fiber ribbon contact and cable assembly into a modified close tolerance Mil-C-83723 connection system to meet the environmental requirements and withstand the high vibration of modern aircraft, and also provide an environmental seal and strain relief. The ability to assemble the connector around a pre-terminated optical link is a key feature, which minimizes assembly and maintenance time over cable assembly life. McDonnell Douglas Aerospace is testing AVMAC qualification cables.

  13. Avionics Simulation, Development and Software Engineering

    Science.gov (United States)

    2002-01-01

    During this reporting period, all technical responsibilities were accomplished as planned. A close working relationship was maintained with personnel of the MSFC Avionics Department Software Group (ED14), the MSFC EXPRESS Project Office (FD31), and the Huntsville Boeing Company. Accomplishments included: performing special tasks; supporting Software Review Board (SRB), Avionics Test Bed (ATB), and EXPRESS Software Control Panel (ESCP) activities; participating in technical meetings; and coordinating issues between the Boeing Company and the MSFC Project Office.

  14. Outlook at the Future of the Airline Avionics Industry

    Science.gov (United States)

    1998-01-01

    The aviation industry is slowly but surely changing its character. As airlines restructure, what they ask of, and how they relate to their suppliers (including avionics manufacturers) will greatly change as well. The avionics industry is currently fa...

  15. Micro-Avionics Multi-Purpose Platform (MicroAMPP)

    Data.gov (United States)

    National Aeronautics and Space Administration — The Micro-Avionics Multi-Purpose Platform (MicroAMPP) is a common avionics architecture supporting microsatellites, launch vehicles, and upper-stage carrier...

  16. Developing A Generic Optical Avionic Network

    DEFF Research Database (Denmark)

    Zhang, Jiang; An, Yi; Berger, Michael Stübert

    2011-01-01

    We propose a generic optical network design for future avionic systems in order to reduce the weight and power consumption of current networks on board. A three-layered network structure over a ring optical network topology is suggested, as it can provide full reconfiguration flexibility and supp......We propose a generic optical network design for future avionic systems in order to reduce the weight and power consumption of current networks on board. A three-layered network structure over a ring optical network topology is suggested, as it can provide full reconfiguration flexibility...... and support a wide range of avionic applications. Segregation can be made on different hierarchies according to system criticality and security requirements. The structure of each layer is discussed in detail. Two network configurations are presented, focusing on how to support different network services...

  17. HH-65A Dolphin digital integrated avionics

    Science.gov (United States)

    Huntoon, R. B.

    1984-01-01

    Communication, navigation, flight control, and search sensor management are avionics functions which constitute every Search and Rescue (SAR) operation. Routine cockpit duties monopolize crew attention during SAR operations and thus impair crew effectiveness. The United States Coast Guard challenged industry to build an avionics system that automates routine tasks and frees the crew to focus on the mission tasks. The HH-64A SAR avionics systems of communication, navigation, search sensors, and flight control have existed independently. On the SRR helicopter, the flight management system (FMS) was introduced. H coordinates or integrates these functions. The pilot interacts with the FMS rather than the individual subsystems, using simple, straightforward procedures to address distinct mission tasks and the flight management system, in turn, orchestrates integrated system response.

  18. Systems Engineering and Reusable Avionics

    Science.gov (United States)

    Conrad, James M.; Murphy, Gloria

    2010-01-01

    One concept for future space flights is to construct building blocks for a wide variety of avionics systems. Once a unit has served its original purpose, it can be removed from the original vehicle and reused in a similar or dissimilar function, depending on the function blocks the unit contains. For example: Once a lunar lander has reached the moon's surface, an engine controller for the Lunar Decent Module would be removed and used for a lunar rover motor control unit or for a Environmental Control Unit for a Lunar Habitat. This senior design project included the investigation of a wide range of functions of space vehicles and possible uses. Specifically, this includes: (1) Determining and specifying the basic functioning blocks of space vehicles. (2) Building and demonstrating a concept model. (3) Showing high reliability is maintained. The specific implementation of this senior design project included a large project team made up of Systems, Electrical, Computer, and Mechanical Engineers/Technologists. The efforts were made up of several sub-groups that each worked on a part of the entire project. The large size and complexity made this project one of the more difficult to manage and advise. Typical projects only have 3-4 students, but this project had 10 students from five different disciplines. This paper describes the difference of this large project compared to typical projects, and the challenges encountered. It also describes how the systems engineering approach was successfully implemented so that the students were able to meet nearly all of the project requirements.

  19. Reference Avionics Architecture for Lunar Surface Systems

    Science.gov (United States)

    Somervill, Kevin M.; Lapin, Jonathan C.; Schmidt, Oron L.

    2010-01-01

    Developing and delivering infrastructure capable of supporting long-term manned operations to the lunar surface has been a primary objective of the Constellation Program in the Exploration Systems Mission Directorate. Several concepts have been developed related to development and deployment lunar exploration vehicles and assets that provide critical functionality such as transportation, habitation, and communication, to name a few. Together, these systems perform complex safety-critical functions, largely dependent on avionics for control and behavior of system functions. These functions are implemented using interchangeable, modular avionics designed for lunar transit and lunar surface deployment. Systems are optimized towards reuse and commonality of form and interface and can be configured via software or component integration for special purpose applications. There are two core concepts in the reference avionics architecture described in this report. The first concept uses distributed, smart systems to manage complexity, simplify integration, and facilitate commonality. The second core concept is to employ extensive commonality between elements and subsystems. These two concepts are used in the context of developing reference designs for many lunar surface exploration vehicles and elements. These concepts are repeated constantly as architectural patterns in a conceptual architectural framework. This report describes the use of these architectural patterns in a reference avionics architecture for Lunar surface systems elements.

  20. Power, Avionics and Software Communication Network Architecture

    Science.gov (United States)

    Ivancic, William D.; Sands, Obed S.; Bakula, Casey J.; Oldham, Daniel R.; Wright, Ted; Bradish, Martin A.; Klebau, Joseph M.

    2014-01-01

    This document describes the communication architecture for the Power, Avionics and Software (PAS) 2.0 subsystem for the Advanced Extravehicular Mobile Unit (AEMU). The following systems are described in detail: Caution Warn- ing and Control System, Informatics, Storage, Video, Audio, Communication, and Monitoring Test and Validation. This document also provides some background as well as the purpose and goals of the PAS project at Glenn Research Center (GRC).

  1. Avionics Reliability, Its Techniques and Related Disciplines.

    Science.gov (United States)

    1979-10-01

    est garanti dans les conditions d’utilisation suivantes: - Pequipement ne doit pas Wte utilise de faqon continue dans les conditions climatiques cxtr...les Oscarts de maintenance (formation du personnel, temps disponible entre deux vols pour lentretien etc... ) *les 6carts climatiques entre bases - de...exposed to a failure of the avionics function indicated. Vulnerability, in the context of Fig. 2, is the probability of a catastrophic event being

  2. Reference Specifications for SAVOIR Avionics Elements

    Science.gov (United States)

    Hult, Torbjorn; Lindskog, Martin; Roques, Remi; Planche, Luc; Brunjes, Bernhard; Dellandrea, Brice; Terraillon, Jean-Loup

    2012-08-01

    Space industry and Agencies have been recognizing already for quite some time the need to raise the level of standardisation in the spacecraft avionics systems in order to increase efficiency and reduce development cost and schedule. This also includes the aspect of increasing competition in global space business, which is a challenge that European space companies are facing at all stages of involvement in the international markets.A number of initiatives towards this vision are driven both by the industry and ESA’s R&D programmes. However, today an intensified coordination of these activities is required in order to achieve the necessary synergy and to ensure they converge towards the shared vision. It has been proposed to federate these initiatives under the common Space Avionics Open Interface Architecture (SAVOIR) initiative. Within this initiative, the approach based on reference architectures and building blocks plays a key role.Following the principles outlined above, the overall goal of the SAVOIR is to establish a streamlined onboard architecture in order to standardize the development of avionics systems for space programmes. This reflects the need to increase efficiency and cost-effectiveness in the development process as well as account the trend towards more functionality implemented by the onboard building blocks, i.e. HW and SW components, and more complexity for the overall space mission objectives.

  3. Integrating ISHM with Flight Avionics Architectures for Cyber-Physical Space Systems, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — Autonomous, avionic and robotic systems are used in a variety of applications including launch vehicles, robotic precursor platforms, etc. Most avionic innovations...

  4. Avionics : The main contributor to innovation in aviation

    NARCIS (Netherlands)

    Theunissen, E.

    2010-01-01

    Avionics refers to Electronic systems used in Aviation, and the word itself is a blend of Aviation and Electronics. Avionics are not only essential for today’s commercial and military aircraft to fly, but also enable their integration into the overall traffic management system. For safety critical

  5. Digital avionics systems - Principles and practices (2nd revised and enlarged edition)

    Science.gov (United States)

    Spitzer, Cary R.

    1993-01-01

    The state of the art in digital avionics systems is surveyed. The general topics addressed include: establishing avionics system requirements; avionics systems essentials in data bases, crew interfaces, and power; fault tolerance, maintainability, and reliability; architectures; packaging and fitting the system into the aircraft; hardware assessment and validation; software design, assessment, and validation; determining the costs of avionics.

  6. Evolution of the Space Shuttle Primary Avionics Software and Avionics for Shuttle Derived Launch Vehicles

    Science.gov (United States)

    Ferguson, Roscoe C.

    2011-01-01

    As a result of recommendation from the Augustine Panel, the direction for Human Space Flight has been altered from the original plan referred to as Constellation. NASA s Human Exploration Framework Team (HEFT) proposes the use of a Shuttle Derived Heavy Lift Launch Vehicle (SDLV) and an Orion derived spacecraft (salvaged from Constellation) to support a new flexible direction for space exploration. The SDLV must be developed within an environment of a constrained budget and a preferred fast development schedule. Thus, it has been proposed to utilize existing assets from the Shuttle Program to speed development at a lower cost. These existing assets should not only include structures such as external tanks or solid rockets, but also the Flight Software which has traditionally been a "long pole" in new development efforts. The avionics and software for the Space Shuttle was primarily developed in the 70 s and considered state of the art for that time. As one may argue that the existing avionics and flight software may be too outdated to support the new SDLV effort, this is a fallacy if they can be evolved over time into a "modern avionics" platform. The technology may be outdated, but the avionics concepts and flight software algorithms are not. The reuse of existing avionics and software also allows for the reuse of development, verification, and operations facilities. The keyword is evolve in that these assets can support the fast development of such a vehicle, but then be gradually evolved over time towards more modern platforms as budget and schedule permits. The "gold" of the flight software is the "control loop" algorithms of the vehicle. This is the Guidance, Navigation, and Control (GNC) software algorithms. This software is typically the most expensive to develop, test, and verify. Thus, the approach is to preserve the GNC flight software, while first evolving the supporting software (such as Command and Data Handling, Caution and Warning, Telemetry, etc

  7. Avionics Applications on a Time-Predictable Chip-Multiprocessor

    DEFF Research Database (Denmark)

    Rocha, André; Silva, Cláudio; Sørensen, Rasmus Bo

    2016-01-01

    Avionics applications need to be certified for the highest criticality standard. This certification includes schedulability analysis and worst-case execution time (WCET) analysis. WCET analysis is only possible when the software is written to be WCET analyzable and when the platform is time......-predictable. In this paper we present prototype avionics applications that have been ported to the time-predictable T-CREST platform. The applications are WCET analyzable, and T-CREST is supported by the aiT WCET analyzer. This combination allows us to provide WCET bounds of avionic tasks, even when executing on a multicore...

  8. Next Generation Avionics System for Satellite Application

    Science.gov (United States)

    Wiegand, M.; Schmidt, G.; Hahn, M.

    This paper describes the new modular avionics system developed at Astrium GmbH in Munich in the frame of Gammabus, a DLR-funded development for constellation programs. Modularity, reusability and time to market are major goals of the development. The system consists of the on-board computer core modules, namely processor module, telemetry/telecommand/reconfiguration/safeguard-memory module and power converter module, an onboard software computing environment as well as a development and verification environment including a real-time testbed and ground station interface (SCOS) to support mission simulation tests. The new concept is taking advantage of improvements in microelectronics and software technology to improve performance while reducing costs.

  9. Avionics for Hibernation and Recovery on Planetary Surfaces

    Data.gov (United States)

    National Aeronautics and Space Administration — Landers and rovers endure on the Martian equator but experience avionics failures in the cryogenic temperatures of lunar nights and Martian winters. The greatest...

  10. A Model-based Avionic Prognostic Reasoner (MAPR)

    Data.gov (United States)

    National Aeronautics and Space Administration — The Model-based Avionic Prognostic Reasoner (MAPR) presented in this paper is an innovative solution for non-intrusively monitoring the state of health (SoH) and...

  11. Integrated Power, Avionics, and Software (IPAS) Flexible Systems Integration

    Data.gov (United States)

    National Aeronautics and Space Administration — The Integrated Power, Avionics, and Software (IPAS) facility is a flexible, multi-mission hardware and software design environment. This project will develop a...

  12. Synchronous Modeling of Modular Avionics Architectures using the SIGNAL Language

    OpenAIRE

    Gamatié , Abdoulaye; Gautier , Thierry

    2002-01-01

    This document presents a study on the modeling of architecture components for avionics applications. We consider the avionics standard ARINC 653 specifications as basis, as well as the synchronous language SIGNAL to describe the modeling. A library of APEX object models (partition, process, communication and synchronization services, etc.) has been implemented. This should allow to describe distributed real-time applications using POLYCHRONY, so as to access formal tools and techniques for ar...

  13. Evaluation of New European Technologies for Future Avionics

    Science.gov (United States)

    Poupat, Jean-Luc; Chevalier, Laurent; Monchaux, David; Le Meur, Patrick

    2014-08-01

    With the support of CNES DLA as operator, and Airbus DS Space System as architect, Airbus DS Electronics in Elancourt has developed a modular platform to evaluate new technologies for future avionics.This paper presents the Avionic-X project that has initiated this development, the modular platform itself and the status on this activity performed on this evaluation platform which has allowed the use of European technologies such as ARM processing cores or TTEthernet communication bus.

  14. Avionics System Architecture for the NASA Orion Vehicle

    Science.gov (United States)

    Baggerman, Clint; McCabe, Mary; Verma, Dinesh

    2009-01-01

    It has been 30 years since the National Aeronautics and Space Administration (NASA) last developed a crewed spacecraft capable of launch, on-orbit operations, and landing. During that time, aerospace avionics technologies have greatly advanced in capability, and these technologies have enabled integrated avionics architectures for aerospace applications. The inception of NASA s Orion Crew Exploration Vehicle (CEV) spacecraft offers the opportunity to leverage the latest integrated avionics technologies into crewed space vehicle architecture. The outstanding question is to what extent to implement these advances in avionics while still meeting the unique crewed spaceflight requirements for safety, reliability and maintainability. Historically, aircraft and spacecraft have very similar avionics requirements. Both aircraft and spacecraft must have high reliability. They also must have as much computing power as possible and provide low latency between user control and effecter response while minimizing weight, volume, and power. However, there are several key differences between aircraft and spacecraft avionics. Typically, the overall spacecraft operational time is much shorter than aircraft operation time, but the typical mission time (and hence, the time between preventive maintenance) is longer for a spacecraft than an aircraft. Also, the radiation environment is typically more severe for spacecraft than aircraft. A "loss of mission" scenario (i.e. - the mission is not a success, but there are no casualties) arguably has a greater impact on a multi-million dollar spaceflight mission than a typical commercial flight. Such differences need to be weighted when determining if an aircraft-like integrated modular avionics (IMA) system is suitable for a crewed spacecraft. This paper will explore the preliminary design process of the Orion vehicle avionics system by first identifying the Orion driving requirements and the difference between Orion requirements and those of

  15. The Space Technology 5 Avionics System

    Science.gov (United States)

    Speer, Dave; Jackson, George; Stewart, Karen; Hernandez-Pellerano, Amri

    2004-01-01

    The Space Technology 5 (ST5) mission is a NASA New Millennium Program project that will validate new technologies for future space science missions and demonstrate the feasibility of building launching and operating multiple, miniature spacecraft that can collect research-quality in-situ science measurements. The three satellites in the ST5 constellation will be launched into a sun-synchronous Earth orbit in early 2006. ST5 fits into the 25-kilogram and 24-watt class of very small but fully capable spacecraft. The new technologies and design concepts for a compact power and command and data handling (C&DH) avionics system are presented. The 2-card ST5 avionics design incorporates new technology components while being tightly constrained in mass, power and volume. In order to hold down the mass and volume, and quali& new technologies for fUture use in space, high efficiency triple-junction solar cells and a lithium-ion battery were baselined into the power system design. The flight computer is co-located with the power system electronics in an integral spacecraft structural enclosure called the card cage assembly. The flight computer has a full set of uplink, downlink and solid-state recording capabilities, and it implements a new CMOS Ultra-Low Power Radiation Tolerant logic technology. There were a number of challenges imposed by the ST5 mission. Specifically, designing a micro-sat class spacecraft demanded that minimizing mass, volume and power dissipation would drive the overall design. The result is a very streamlined approach, while striving to maintain a high level of capability, The mission's radiation requirements, along with the low voltage DC power distribution, limited the selection of analog parts that can operate within these constraints. The challenge of qualifying new technology components for the space environment within a short development schedule was another hurdle. The mission requirements also demanded magnetic cleanliness in order to reduce

  16. Validating Avionics Conceptual Architectures with Executable Specifications

    Directory of Open Access Journals (Sweden)

    Nils Fischer

    2012-08-01

    Full Text Available Current avionics systems specifications, developed after conceptual design, have a high degree of uncertainty. Since specifications are not sufficiently validated in the early development process and no executable specification exists at aircraft level, system designers cannot evaluate the impact of their design decisions at aircraft or aircraft application level. At the end of the development process of complex systems, e. g. aircraft, an average of about 65 per cent of all specifications have to be changed because they are incorrect, incomplete or too vaguely described. In this paper, a model-based design methodology together with a virtual test environment is described that makes complex high level system specifications executable and testable during the very early levels of system design. An aircraft communication system and its system context is developed to demonstrate the proposed early validation methodology. Executable specifications for early conceptual system architectures enable system designers to couple functions, architecture elements, resources and performance parameters, often called non-functional parameters. An integrated executable specification at Early Conceptual Architecture Level is developed and used to determine the impact of different system architecture decisions on system behavior and overall performance.

  17. Dual backlighting system for avionic AMLCDs

    Science.gov (United States)

    Kalmanash, Michael H.; Sundaresan, Gayathri

    1996-05-01

    Avionic displays are required to be fully functional over a wide range of ambient illumination, encompassing bright sunlight during the day and dim starlit sky at night. Additionally, in most applications the night operation is required to be compliant with night vision imaging system (NVIS A or B) goggles. This article describes a patented dual lighting system, employing a hot cathode fluorescent lamp for the day mode and a filtered cold cathode fluorescent lamp against a light pipe (edgelit) for the night mode of operation. Since the two modes of operation are decoupled from each other, the day mode can be designed for high luminance and broad color gamut, regardless of NVIS requirements, while the night mode can be designed to be compatible with either the NVIS-A or NVIS-B systems with no impact to the day mode. This unique blacklight design provides a wide dimming range for the display and delivers excellent performance under all viewing conditions. Furthermore, this approach provides excellent uniformity in the night mode with minimal color shifts over view angles and has been successfully implemented on two cockpit display programs.

  18. NASA/Princeton digital avionics flight test facility

    Science.gov (United States)

    Downing, D. R.; Bryant, W. H.; Stengel, R. F.

    1979-01-01

    This paper describes a general-aviation digital avionics flight-test facility being jointly developed by the Flight Dynamics Laboratory of Princeton University and NASA/Langley Research Center. This facility consists of the Princeton avionics research aircraft (ARA) and NASA/Langley's digital avionics research (DARE) system. The ARA is a fully instrumented five-degree-of-freedom fly-by-wire aircraft. The DARE system contains a state-of-the-art flight computer system and receiving equipment that permits use of the NASA/Wallops Flight Center's position-tracking ground-based display-generation and ground-to-air digital-data-link equipment. The DARE/ARA system will be used for flight evaluation of advanced control, guidance, and display concepts developed as part of NASA/Langley Research Center's general aviation terminal area operations program.

  19. An assessment of General Aviation utilization of advanced avionics technology

    Science.gov (United States)

    Quinby, G. F.

    1980-01-01

    Needs of the general aviation industry for services and facilities which might be supplied by NASA were examined. In the data collection phase, twenty-one individuals from nine manufacturing companies in general aviation were interviewed against a carefully prepared meeting format. General aviation avionics manufacturers were credited with a high degree of technology transfer from the forcing industries such as television, automotive, and computers and a demonstrated ability to apply advanced technology such as large scale integration and microprocessors to avionics functions in an innovative and cost effective manner. The industry's traditional resistance to any unnecessary regimentation or standardization was confirmed. Industry's self sufficiency in applying advanced technology to avionics product development was amply demonstrated. NASA research capability could be supportive in areas of basic mechanics of turbulence in weather and alternative means for its sensing.

  20. Advanced Avionics and Processor Systems for Space and Lunar Exploration

    Science.gov (United States)

    Keys, Andrew S.; Adams, James H.; Ray, Robert E.; Johnson, Michael A.; Cressler, John D.

    2009-01-01

    NASA's newly named Advanced Avionics and Processor Systems (AAPS) project, formerly known as the Radiation Hardened Electronics for Space Environments (RHESE) project, endeavors to mature and develop the avionic and processor technologies required to fulfill NASA's goals for future space and lunar exploration. Over the past year, multiple advancements have been made within each of the individual AAPS technology development tasks that will facilitate the success of the Constellation program elements. This paper provides a brief review of the project's recent technology advancements, discusses their application to Constellation projects, and addresses the project's plans for the coming year.

  1. Impact of Advanced Avionics Technology on Ground Attack Weapon Systems.

    Science.gov (United States)

    1982-02-01

    de celui de moyens de d~tection et d’acquisition autonomes A bord de l’avion tireur, A mains de faire appel A un avion sp~cialis6 en liaison temps...trajectoire et lea armes d’autod~fense. Remargue Le tableau que l’on fait habituellanent sur les menaces risque fort d’ tre tr~s d~courageant de par...sont en d~veloppement. le procurent des pr~cisions de quelques dizaines de m~ltres, et pourraient servir A recaler lea centrales inertielles

  2. Enabling Wireless Avionics Intra-Communications

    Science.gov (United States)

    Torres, Omar; Nguyen, Truong; Mackenzie, Anne

    2016-01-01

    to model the propagation of a system in a "deployed" configuration versus a "stowed" configuration. The differences in relative field strength provide valuable information about the distribution of the field that can be used to engineer RF links with optimal radiated power and antenna configuration that accomplish the intended system reliability. Such modeling will be necessary in subsequent studies for managing multipath propagation characteristics inside a main cabin and to understand more complex environments, such as the inside wings, landing gear bays, cargo bays, avionics bays, etc. The results of the short research effort are described in the present document. The team puts forth a set of recommendations with the intention of informing the project and program leadership of the future work that, in the opinion of the EWAIC team, would assist the ECON team reach the intended goal of developing an all-wireless aircraft.

  3. Reliability and the design process at Honeywell Avionics Division

    Science.gov (United States)

    Bezat, A.

    1981-01-01

    The division's philosophy for designed-in reliability and a comparison of reliability programs for space, manned military aircraft, and commercial aircraft, are presented. Topics include: the reliability interface with design and production; the concept phase through final proposal; the design, development, test and evaluation phase; the production phase; and the commonality among space, military, and commercial avionics.

  4. Compositional Schedulability Analysis of Multicore Modular Avionic Architectures

    DEFF Research Database (Denmark)

    Boudjadar, Jalil

    2017-01-01

    This paper presents a compositional schedulability analysis of multicore modular avionic systems (IMA). It provides a fine grained description of the software architecture and behavior to reduce the over-approximation, and a holistic analysis to check schedulability while considering computation...

  5. Wavelength and fiber assignment problems on avionic networks

    DEFF Research Database (Denmark)

    Zhang, Jiang; An, Yi; Berger, Michael Stübert

    2011-01-01

    This paper solves the wavelength and fiber assignment problems with systems' isolation requirements on the avionic ring networks. The experiment results give a general glace of the numbers of the wavelengths and fibers are required under certain scale of networks. At the beginning of increasing...

  6. Avionics Configuration Assessment for Flightdeck Interval Management: A Comparison of Avionics and Notification Methods

    Science.gov (United States)

    Latorella, Kara A.

    2015-01-01

    Flightdeck Interval Management is one of the NextGen operational concepts that FAA is sponsoring to realize requisite National Airspace System (NAS) efficiencies. Interval Management will reduce variability in temporal deviations at a position, and thereby reduce buffers typically applied by controllers - resulting in higher arrival rates, and more efficient operations. Ground software generates a strategic schedule of aircraft pairs. Air Traffic Control (ATC) provides an IM clearance with the IM spacing objective (i.e., the TTF, and at which point to achieve the appropriate spacing from this aircraft) to the IM aircraft. Pilots must dial FIM speeds into the speed window on the Mode Control Panel in a timely manner, and attend to deviations between actual speed and the instantaneous FIM profile speed. Here, the crew is assumed to be operating the aircraft with autothrottles on, with autopilot engaged, and the autoflight system in Vertical Navigation (VNAV) and Lateral Navigation (LNAV); and is responsible for safely flying the aircraft while maintaining situation awareness of their ability to follow FIM speed commands and to achieve the FIM spacing goal. The objective of this study is to examine whether three Notification Methods and four Avionics Conditions affect pilots' performance, ratings on constructs associated with performance (workload, situation awareness), or opinions on acceptability. Three Notification Methods (alternate visual and aural alerts that notified pilots to the onset of a speed target, conformance deviation from the required speed profile, and reminded them if they failed to enter the speed within 10 seconds) were examined. These Notification Methods were: VVV (visuals for all three events), VAV (visuals for all three events, plus an aural for speed conformance deviations), and AAA (visual indications and the same aural to indicate all three of these events). Avionics Conditions were defined by the instrumentation (and location) used to

  7. A critique of reliability prediction techniques for avionics applications

    Directory of Open Access Journals (Sweden)

    Guru Prasad PANDIAN

    2018-01-01

    Full Text Available Avionics (aeronautics and aerospace industries must rely on components and systems of demonstrated high reliability. For this, handbook-based methods have been traditionally used to design for reliability, develop test plans, and define maintenance requirements and sustainment logistics. However, these methods have been criticized as flawed and leading to inaccurate and misleading results. In its recent report on enhancing defense system reliability, the U.S. National Academy of Sciences has recently discredited these methods, judging the Military Handbook (MIL-HDBK-217 and its progeny as invalid and inaccurate. This paper discusses the issues that arise with the use of handbook-based methods in commercial and military avionics applications. Alternative approaches to reliability design (and its demonstration are also discussed, including similarity analysis, testing, physics-of-failure, and data analytics for prognostics and systems health management.

  8. Developing Avionics Hardware and Software for Rocket Engine Testing

    Science.gov (United States)

    Aberg, Bryce Robert

    2014-01-01

    My summer was spent working as an intern at Kennedy Space Center in the Propulsion Avionics Branch of the NASA Engineering Directorate Avionics Division. The work that I was involved with was part of Rocket University's Project Neo, a small scale liquid rocket engine test bed. I began by learning about the layout of Neo in order to more fully understand what was required of me. I then developed software in LabView to gather and scale data from two flowmeters and integrated that code into the main control software. Next, I developed more LabView code to control an igniter circuit and integrated that into the main software, as well. Throughout the internship, I performed work that mechanics and technicians would do in order to maintain and assemble the engine.

  9. Electronics/avionics integrity - Definition, measurement and improvement

    Science.gov (United States)

    Kolarik, W.; Rasty, J.; Chen, M.; Kim, Y.

    The authors report on the results obtained from an extensive, three-fold research project: (1) to search the open quality and reliability literature for documented information relative to electronics/avionics integrity; (2) to interpret and evaluate the literature as to significant concepts, strategies, and tools appropriate for use in electronics/avionics product and process integrity efforts; and (3) to develop a list of critical findings and recommendations that will lead to significant progress in product integrity definition, measurement, modeling, and improvements. The research consisted of examining a broad range of trade journals, scientific journals, and technical reports, as well as face-to-face discussions with reliability professionals. Ten significant recommendations have been supported by the research work.

  10. Advanced Avionics and the Military Aircraft Man/Machine Interface.

    Science.gov (United States)

    1982-07-01

    DE PILOTABILITE Cette analyse rapide du comportement de Ilop~rateur humain permet alors de dresser une lite, non exhaustive, de r~gles de pilotabilit6...COMMUICATIOUS IIANAGIE A VITAL LINK Author: W.E. Brierley Marconi Avionics Limited, Airadio Products Division, Christopher Martin Road, Bas ild on, Essex... Christopher Martin Rd., Basildon, Essex. UK BROOKE, M.C. Sqdn. Ldr. ETPS., ADAEE Boscombe Down, Salisbury, Wilts., UK BROWNING, M R.S. Mr Westland

  11. Competition Between Aupark Shopping Center and Avion Shopping Park

    Directory of Open Access Journals (Sweden)

    TAMÁS T. SIKOS

    2011-01-01

    Full Text Available This paper provides an overview of the establishment and historical development of shopping centres in Bratislava, Slovakia. In the framework of a case study we also describe the competition between Aupark and Avion Shopping Park, the two largest shopping centres in Slovakia. Our analysis is based on a field research and on a desk research as well. In the framework of the case study, 300 questionnaires were filled in, 150 in each centre.

  12. Micro-Inspector Avionics Module (MAM): A Self-Contained Low Power, Reconfigurable Avionics Platform for Small Spacecrafts and Instruments

    Science.gov (United States)

    Ashtijou, Mohammad; He, Yutao; Watson, R. Kevin; Bolotin, Gary S.

    2006-01-01

    This paper describes development of a radiation tolerant, low power, reconfigurable avionics module aimed at meeting the avionics needs of the JPL Micro-Inspector spacecraft. This module represents a complete avionics system, consisting of two PowerPC 405 CPUs embedded within a reconfigurable FPGA fabric of over 8 Million logic gates, 64MB of EDAC protected Flash storage and 128MB of EDAC protected DDR SDRAM or SDRAM memories, along with FPGA SEU mitigation logic, and all necessary power conversion. Processor SEU mitigation is achieved by running the two processors in a lock-step and compare configuration. All of these building blocks are integrated into a double sided circuit board that takes as little as 6 square inches of board space. This module can be embedded into a user system as part of a bigger circuit assembly or as a self contained module. This module is being developed as part of a JPL led Micro-Inspector Program, funded by NASA ESMD aimed at producing a 10Kg micro spacecraft.

  13. 78 FR 42898 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes

    Science.gov (United States)

    2013-07-18

    ... Information Avions de Transport R gional has issued Service Bulletin ATR72-28-1026, dated February 26, 2013... exist or develop on other products of the same type design. Costs of Compliance Based on the service... Instructions of Avions de Transport R gional Service Bulletin ATR72-28-1026, dated February 26, 2013. (1) For...

  14. ISHM-oriented adaptive fault diagnostics for avionics based on a distributed intelligent agent system

    Science.gov (United States)

    Xu, Jiuping; Zhong, Zhengqiang; Xu, Lei

    2015-10-01

    In this paper, an integrated system health management-oriented adaptive fault diagnostics and model for avionics is proposed. With avionics becoming increasingly complicated, precise and comprehensive avionics fault diagnostics has become an extremely complicated task. For the proposed fault diagnostic system, specific approaches, such as the artificial immune system, the intelligent agents system and the Dempster-Shafer evidence theory, are used to conduct deep fault avionics diagnostics. Through this proposed fault diagnostic system, efficient and accurate diagnostics can be achieved. A numerical example is conducted to apply the proposed hybrid diagnostics to a set of radar transmitters on an avionics system and to illustrate that the proposed system and model have the ability to achieve efficient and accurate fault diagnostics. By analyzing the diagnostic system's feasibility and pragmatics, the advantages of this system are demonstrated.

  15. A Study of Avionics Time Division Multiplex Bus Simulation.

    Science.gov (United States)

    1980-12-01

    STUDY OF AVIONICS TIME DIVISION MULTIPLEX BUS SIMULATION, For Period Covering ’? *-" . (. I Janu wry k~t-4-31 Decoe 380 tP_: Final Report -, - / -AFOSR...simulation modeling is a type of art work, and therefore requires a talented engineer. Furthermore, the complexity of the sys- tem may be such that it is...used to synchronize the movement of the assembly set. Operand: X field specifies the block number of a MATCH block. Condition for entry acceptance: It

  16. Software testability and its application to avionic software

    Science.gov (United States)

    Voas, Jeffrey M.; Miller, Keith W.; Payne, Jeffery E.

    1993-01-01

    Randomly generated black-box testing is an established yet controversial method of estimating software reliability. Unfortunately, as software applications have required higher reliabilities, practical difficulties with black-box testing have become increasingly problematic. These practical problems are particularly acute in life-critical avionics software, where requirements of 10 exp -7 failures per hour of system reliability can translate into a probability of failure (POF) of perhaps 10 exp -9 or less for each individual execution of the software. This paper describes the application of one type of testability analysis called 'sensitivity analysis' to B-737 avionics software; one application of sensitivity analysis is to quantify whether software testing is capable of detecting faults in a particular program and thus whether we can be confident that a tested program is not hiding faults. We so 80 by finding the testabilities of the individual statements of the program, and then use those statement testabilities to find the testabilities of the functions and modules. For the B-737 system we analyzed, we were able to isolate those functions that are more prone to hide errors during system/reliability testing.

  17. The effect of requirements prioritization on avionics system conceptual design

    Science.gov (United States)

    Lorentz, John

    This dissertation will provide a detailed approach and analysis of a new collaborative requirements prioritization methodology that has been used successfully on four Coast Guard avionics acquisition and development programs valued at $400M+. A statistical representation of participant study results will be discussed and analyzed in detail. Many technically compliant projects fail to deliver levels of performance and capability that the customer desires. Some of these systems completely meet "threshold" levels of performance; however, the distribution of resources in the process devoted to the development and management of the requirements does not always represent the voice of the customer. This is especially true for technically complex projects such as modern avionics systems. A simplified facilitated process for prioritization of system requirements will be described. The collaborative prioritization process, and resulting artifacts, aids the systems engineer during early conceptual design. All requirements are not the same in terms of customer priority. While there is a tendency to have many thresholds inside of a system design, there is usually a subset of requirements and system performance that is of the utmost importance to the design. These critical capabilities and critical levels of performance typically represent the reason the system is being built. The systems engineer needs processes to identify these critical capabilities, the associated desired levels of performance, and the risks associated with the specific requirements that define the critical capability. The facilitated prioritization exercise is designed to collaboratively draw out these critical capabilities and levels of performance so they can be emphasized in system design. Developing the purpose, scheduling and process for prioritization events are key elements of systems engineering and modern project management. The benefits of early collaborative prioritization flow throughout the

  18. 1993 Aerospace Avionic Systems Division Conference, 3rd, Denver, CO, Apr. 22, 1993, Proceedings

    Science.gov (United States)

    Topics addressed include a single-supply monolithic, MIL-STD-1553 transreceiver implemented in BiCMOS wafer fabrication technology, a development methodology for contemporary avionics systems, MIL-STD-1553 remote terminal design using ASIC megacell technology, a modular electrooptic bus coupler, experiences in validating MIL-STD-1553 remote terminals, and the STANAG 3910 data bus for the next generation of European avionics systems. Attention is also given to JIAWG compatible development boards for the i960, high-speed databus evaluation, the space avionics architecture standard tailored to the common lunar lander conceptual design, and 1553 RT mechanizations for data sample consistency and multimessage transfers.

  19. Integrated Modular Avionics for Spacecraft: Earth Observation Use Case Demonstrator

    Science.gov (United States)

    Deredempt, Marie-Helene; Rossignol, Alain; Hyounet, Philippe

    2013-08-01

    Integrated Modular Avionics (IMA) for Space, as European Space Agency initiative, aimed to make applicable to space domain the time and space partitioning concepts and particularly the ARINC 653 standard [1][2]. Expected benefits of such an approach are development flexibility, capability to provide differential V&V for different criticality level functionalities and to integrate late or In-Orbit delivery. This development flexibility could improve software subcontracting, industrial organization and software reuse. Time and space partitioning technique facilitates integration of software functions as black boxes and integration of decentralized function such as star tracker in On Board Computer to save mass and power by limiting electronics resources. In aeronautical domain, Integrated Modular Avionics architecture is based on a network of LRU (Line Replaceable Unit) interconnected by AFDX (Avionic Full DupleX). Time and Space partitioning concept is applicable to LRU and provides independent partitions which inter communicate using ARINC 653 communication ports. Using End System (LRU component) intercommunication between LRU is managed in the same way than intercommunication between partitions in LRU. In such architecture an application developed using only communication port can be integrated in an LRU or another one without impacting the global architecture. In space domain, a redundant On Board Computer controls (ground monitoring TM) and manages the platform (ground command TC) in terms of power, solar array deployment, attitude, orbit, thermal, maintenance, failure detection and recovery isolation. In addition, Payload units and platform units such as RIU, PCDU, AOCS units (Star tracker, Reaction wheels) are considered in this architecture. Interfaces are mainly realized through MIL-STD-1553B busses and SpaceWire and this could be considered as the main constraint for IMA implementation in space domain. During the first phase of IMA SP project, ARINC653

  20. Rad-hard Smallsat / CubeSat Avionics Board, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — VORAGO will design a rad-hard Smallsat / CubeSat Avionics single board that has the necessary robustness needed for long duration missions in harsh mission...

  1. Platform Independent Launch Vehicle Avionics with GPS Metric Tracking, Phase II

    Data.gov (United States)

    National Aeronautics and Space Administration — For this award, Tyvak proposes to develop a complete suite of avionics for a Nano-Launch Vehicle (NLV) based on the architecture determinations performed during...

  2. Integrating ISHM with Flight Avionics Architectures for Cyber-Physical Space Systems, Phase II

    Data.gov (United States)

    National Aeronautics and Space Administration — Substantial progress has been made by NASA in integrating flight avionics and ISHM with well-defined caution and warning system, however, the scope of ACAW alerting...

  3. Estimation of Airline Benefits from Avionics Upgrade under Preferential Merge Re-sequence Scheduling

    Science.gov (United States)

    Kotegawa, Tatsuya; Cayabyab, Charlene Anne; Almog, Noam

    2013-01-01

    Modernization of the airline fleet avionics is essential to fully enable future technologies and procedures for increasing national airspace system capacity. However in the current national airspace system, system-wide benefits gained by avionics upgrade are not fully directed to aircraft/airlines that upgrade, resulting in slow fleet modernization rate. Preferential merge re-sequence scheduling is a best-equipped-best-served concept designed to incentivize avionics upgrade among airlines by allowing aircraft with new avionics (high-equipped) to be re-sequenced ahead of aircraft without the upgrades (low-equipped) at enroute merge waypoints. The goal of this study is to investigate the potential benefits gained or lost by airlines under a high or low-equipped fleet scenario if preferential merge resequence scheduling is implemented.

  4. Space Shuttle Program Primary Avionics Software System (PASS) Success Legacy - Quality and Reliability Date

    Science.gov (United States)

    Orr, James K.; Peltier, Daryl

    2010-01-01

    Thsi slide presentation reviews the avionics software system on board the space shuttle, with particular emphasis on the quality and reliability. The Primary Avionics Software System (PASS) provides automatic and fly-by-wire control of critical shuttle systems which executes in redundant computers. Charts given show the number of space shuttle flights vs time, PASS's development history, and other charts that point to the reliability of the system's development. The reliability of the system is also compared to predicted reliability.

  5. The implementation of fail-operative functions in integrated digital avionics systems

    Science.gov (United States)

    Osoer, S. S.

    1976-01-01

    System architectures which incorporate fail operative flight guidance functions within a total integrated avionics complex are described. It is shown that the mixture of flight critical and nonflight critical functions within a common computer complex is an efficient solution to the integration of navigation, guidance, flight control, display, and flight management. Interfacing subsystems retain autonomous capability to avoid vulnerability to total avionics system shutdown as a result of only a few failures.

  6. Organization and use of a Software/Hardware Avionics Research Program (SHARP)

    Science.gov (United States)

    Karmarkar, J. S.; Kareemi, M. N.

    1975-01-01

    The organization and use is described of the software/hardware avionics research program (SHARP) developed to duplicate the automatic portion of the STOLAND simulator system, on a general-purpose computer system (i.e., IBM 360). The program's uses are: (1) to conduct comparative evaluation studies of current and proposed airborne and ground system concepts via single run or Monte Carlo simulation techniques, and (2) to provide a software tool for efficient algorithm evaluation and development for the STOLAND avionics computer.

  7. A method of distributed avionics data processing based on SVM classifier

    Science.gov (United States)

    Guo, Hangyu; Wang, Jinyan; Kang, Minyang; Xu, Guojing

    2018-03-01

    Under the environment of system combat, in order to solve the problem on management and analysis of the massive heterogeneous data on multi-platform avionics system, this paper proposes a management solution which called avionics "resource cloud" based on big data technology, and designs an aided decision classifier based on SVM algorithm. We design an experiment with STK simulation, the result shows that this method has a high accuracy and a broad application prospect.

  8. A Time-Triggered Constraint-Based Calculus for Avionic Systems

    OpenAIRE

    Hamadou, Sardaouna; Gherbi, Abdelouahed; Mullins, John; Beji, Sofiene

    2014-01-01

    The Integrated Modular Avionics (IMA) architec- ture and the Time-Triggered Ethernet (TTEthernet) network have emerged as the key components of a typical architecture model for recent civil aircrafts. We propose a real-time constraint-based calculus targeted at the analysis of such concepts of avionic embedded systems. We show our framework at work on the modelisation of both the (IMA) architecture and the TTEthernet network, illustrating their behavior by the well-known Flight Management Sys...

  9. Automatic implementation of TTEthernet-based time-triggered avionics applications

    OpenAIRE

    Gorcitz, Raul Adrian; Carle, Thomas; Lesens, David; Monchaux, David; Potop-Butucaru, Dumitru; Sorel, Yves

    2015-01-01

    International audience; The design of safety-critical embedded systems such as those used in avionics still involves largely manual phases. But in avionics the definition of standard interfaces embodied in standards such as ARINC 653 or TTEthernet should allow the definition of fully automatic code generation flows that reduce the costs while improving the quality of the generated code, much like compilers have done when replacing manual assembly coding. In this paper, we briefly present such...

  10. NASA Affordable Vehicle Avionics (AVA). Common Modular Avionics System for Nanolaunchers Offering Affordable Access to Space; [Space Technology: Game Changing Development

    Science.gov (United States)

    Aquilina, Rudy

    2017-01-01

    Small satellites are becoming ever more capable of performing valuable missions for both government and commercial customers. However, currently these satellites can be launched affordably only as secondary payloads. This makes it difficult for the small satellite mission to launch when needed, to the desired orbit, and with acceptable risk. What is needed is a class of low-cost launchers, so that launch costs to low-Earth orbit (LEO) are commensurate with payload costs. Several private and government-sponsored launch vehicle developers are working toward just that-the ability to affordably insert small payloads into LEO. But until now, cost of the complex avionics remained disproportionately high. AVA (Affordable Vehicle Avionics) solves this problem. Significant contributors to the cost of launching nanosatellites to orbit are the avionics and software systems that steer and control the launch vehicles, sequence stage separation, deploy payloads, and telemeter data. The high costs of these guidance, navigation and control (GNC) avionics systems are due in part to the current practice of developing unique, single-use hardware and software for each launch. High-performance, high-reliability inertial sensors components with heritage from legacy launchers also contribute to costs-but can low-cost commercial inertial sensors work just as well? NASA Ames Research Center has developed and tested a prototype low-cost avionics package for space launch vehicles that provides complete GNC functionality in a package smaller than a tissue box (100 millimeters by 120 millimeters by 69 millimeters; 4 inches by 4.7 inches by 2.7 inches), with a mass of less than 0.84 kilogram (2 pounds. AVA takes advantage of commercially available, low-cost, mass-produced, miniaturized sensors, filtering their more noisy inertial data with real-time GPS (Global Positioning Satellite) data. The goal of the AVA project is to produce and light-verify a common suite of avionics and software that

  11. MATHEMATICAL MODELS OF PROCESSES AND SYSTEMS OF TECHNICAL OPERATION FOR ONBOARD COMPLEXES AND FUNCTIONAL SYSTEMS OF AVIONICS

    Directory of Open Access Journals (Sweden)

    Sergey Viktorovich Kuznetsov

    2017-01-01

    Full Text Available Modern aircraft are equipped with complicated systems and complexes of avionics. Aircraft and its avionics tech- nical operation process is observed as a process with changing of operation states. Mathematical models of avionics pro- cesses and systems of technical operation are represented as Markov chains, Markov and semi-Markov processes. The pur- pose is to develop the graph-models of avionics technical operation processes, describing their work in flight, as well as during maintenance on the ground in the various systems of technical operation. The graph-models of processes and sys- tems of on-board complexes and functional avionics systems in flight are proposed. They are based on the state tables. The models are specified for the various technical operation systems: the system with control of the reliability level, the system with parameters control and the system with resource control. The events, which cause the avionics complexes and func- tional systems change their technical state, are failures and faults of built-in test equipment. Avionics system of technical operation with reliability level control is applicable for objects with constant or slowly varying in time failure rate. Avion- ics system of technical operation with resource control is mainly used for objects with increasing over time failure rate. Avionics system of technical operation with parameters control is used for objects with increasing over time failure rate and with generalized parameters, which can provide forecasting and assign the borders of before-fail technical states. The pro- posed formal graphical approach avionics complexes and systems models designing is the basis for models and complex systems and facilities construction, both for a single aircraft and for an airline aircraft fleet, or even for the entire aircraft fleet of some specific type. The ultimate graph-models for avionics in various systems of technical operation permit the beginning of

  12. Školski avion Lasta 95 i Višenamensko oklopno borbeno vozilo Lazar

    Directory of Open Access Journals (Sweden)

    Nebojša N. Gaćeša

    2009-07-01

    Full Text Available Domaći školski avion lasta 95 zvanično je predstavljen 9. aprila 2009. godine, u Tehničkom opitnom centru (TOC na batajničkom aerodromu. Ovo je letelica na kojoj će se ubuduće obučavati piloti Vojske Srbije i koja će u osnovnoj obuci zameniti avion Utva-75, a u delu osnovne obuke i avion supergaleb G-4. Na vojnom poligonu Nikinci, 6. februara 2009. godine, zvanično je promovisano višenamensko oklopno borbeno vozilo lazar, domaće proizvodnje. Lazar predstavlja komercijalni projekat kompanije Jugoimport SDPR i njenog tima istraživača i konstruktora.

  13. Avionics system design for requirements for the United States Coast Guard HH-65A Dolphin

    Science.gov (United States)

    Young, D. A.

    1984-01-01

    Aerospatiale Helicopter Corporation (AHC) was awarded a contract by the United States Coast Guard for a new Short Range Recovery (SRR) Helicopter on 14 June 1979. The award was based upon an overall evaluation of performance, cost, and technical suitability. In this last respect, the SRR helicopter was required to meet a wide variety of mission needs for which the integrated avionics system has a high importance. This paper illustrates the rationale for the avionics system requirements, the system architecture, its capabilities and reliability and its adaptability to a wide variety of military and commercial purposes.

  14. Formal Safety and Security Assessment of an Avionic Architecture with Alloy

    Directory of Open Access Journals (Sweden)

    Julien Brunel

    2014-05-01

    Full Text Available We propose an approach based on Alloy to formally model and assess a system architecture with respect to safety and security requirements. We illustrate this approach by considering as a case study an avionic system developed by Thales, which provides guidance to aircraft. We show how to define in Alloy a metamodel of avionic architectures with a focus on failure propagations. We then express the specific architecture of the case study in Alloy. Finally, we express and check properties that refer to the robustness of the architecture to failures and attacks.

  15. Automatic Implementation of Ttethernet-Based Time-Triggered Avionics Applications

    Science.gov (United States)

    Gorcitz, Raul Adrian; Carle, Thomas; Lesens, David; Monchaux, David; Potop-Butucaruy, Dumitru; Sorel, Yves

    2015-09-01

    The design of safety-critical embedded systems such as those used in avionics still involves largely manual phases. But in avionics the definition of standard interfaces embodied in standards such as ARINC 653 or TTEthernet should allow the definition of fully automatic code generation flows that reduce the costs while improving the quality of the generated code, much like compilers have done when replacing manual assembly coding. In this paper, we briefly present such a fully automatic implementation tool, called Lopht, for ARINC653-based time-triggered systems, and then explain how it is currently extended to include support for TTEthernet networks.

  16. Minimizing the Risks of Diminishing Manufacturing Sources and Material Shortages: Evaluating Electronic Avionics Lifecycle Sustainment Strategies

    Science.gov (United States)

    2011-05-01

    Geiser . (2002). “Determining Optimum Redesign Plans for Avionics Based on Electronic Part Obsolescence Forecasts” Proceedings World Aviation Congress...SAE Int’l. Singh, P., P. Sandborn, T. Geiser , and D. Lorensen. (2003). “Electronic Part Obsolescence Driven Design Refresh Planning” International

  17. Spacecraft Avionics Software Development Then and Now: Different but the Same

    Science.gov (United States)

    Mangieri, Mark L.; Garman, John (Jack); Vice, Jason

    2012-01-01

    NASA has always been in the business of balancing new technologies and techniques to achieve human space travel objectives. NASA s historic Software Production Facility (SPF) was developed to serve complex avionics software solutions during an era dominated by mainframes, tape drives, and lower level programming languages. These systems have proven themselves resilient enough to serve the Shuttle Orbiter Avionics life cycle for decades. The SPF and its predecessor the Software Development Lab (SDL) at NASA s Johnson Space Center (JSC) hosted flight software (FSW) engineering, development, simulation, and test. It was active from the beginning of Shuttle Orbiter development in 1972 through the end of the shuttle program in the summer of 2011 almost 40 years. NASA s Kedalion engineering analysis lab is on the forefront of validating and using many contemporary avionics HW/SW development and integration techniques, which represent new paradigms to NASA s heritage culture in avionics software engineering. Kedalion has validated many of the Orion project s HW/SW engineering techniques borrowed from the adjacent commercial aircraft avionics environment, inserting new techniques and skills into the Multi-Purpose Crew Vehicle (MPCV) Orion program. Using contemporary agile techniques, COTS products, early rapid prototyping, in-house expertise and tools, and customer collaboration, NASA has adopted a cost effective paradigm that is currently serving Orion effectively. This paper will explore and contrast differences in technology employed over the years of NASA s space program, due largely to technological advances in hardware and software systems, while acknowledging that the basic software engineering and integration paradigms share many similarities.

  18. Wireless Avionics Packet to Support Fault Tolerance for Flight Applications

    Science.gov (United States)

    Block, Gary L.; Whitaker, William D.; Dillon, James W.; Lux, James P.; Ahmad, Mohammad

    2009-01-01

    In this protocol and packet format, data traffic is monitored by all network interfaces to determine the health of transmitter and subsystems. When failures are detected, the network inter face applies its recover y policies to provide continued service despite the presence of faults. The protocol, packet format, and inter face are independent of the data link technology used. The current demonstration system supports both commercial off-the-shelf wireless connections and wired Ethernet connections. Other technologies such as 1553 or serial data links can be used for the network backbone. The Wireless Avionics packet is divided into three parts: a header, a data payload, and a checksum. The header has the following components: magic number, version, quality of service, time to live, sending transceiver, function code, payload length, source Application Data Interface (ADI) address, destination ADI address, sending node address, target node address, and a sequence number. The magic number is used to identify WAV packets, and allows the packet format to be updated in the future. The quality of service field allows routing decisions to be made based on this value and can be used to route critical management data over a dedicated channel. The time to live value is used to discard misrouted packets while the source transceiver is updated at each hop. This information is used to monitor the health of each transceiver in the network. To identify the packet type, the function code is used. Besides having a regular data packet, the system supports diagnostic packets for fault detection and isolation. The payload length specifies the number of data bytes in the payload, and this supports variable-length packets in the network. The source ADI is the address of the originating interface. This can be used by the destination application to identify the originating source of the packet where the address consists of a subnet, subsystem class within the subnet, a subsystem unit

  19. Flexible Low Cost Avionics for NanoSatellite Launch Vehicle Control and GPS Metric Tracking, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — In this proposal, Tyvak Nano-Satellite Systems LLC (Tyvak) will develop nano-launch vehicle avionics solutions based on the latest commercial electronics products...

  20. Workstation-Based Avionics Simulator to Support Mars Science Laboratory Flight Software Development

    Science.gov (United States)

    Henriquez, David; Canham, Timothy; Chang, Johnny T.; McMahon, Elihu

    2008-01-01

    The Mars Science Laboratory developed the WorkStation TestSet (WSTS) to support flight software development. The WSTS is the non-real-time flight avionics simulator that is designed to be completely software-based and run on a workstation class Linux PC. This provides flight software developers with their own virtual avionics testbed and allows device-level and functional software testing when hardware testbeds are either not yet available or have limited availability. The WSTS has successfully off-loaded many flight software development activities from the project testbeds. At the writing of this paper, the WSTS has averaged an order of magnitude more usage than the project's hardware testbeds.

  1. Spacecraft guidance, navigation, and control requirements for an intelligent plug-n-play avionics (PAPA) architecture

    Science.gov (United States)

    Kulkarni, Nilesh; Krishnakumar, Kalmaje

    2005-01-01

    The objective of this research is to design an intelligent plug-n-play avionics system that provides a reconfigurable platform for supporting the guidance, navigation and control (GN&C) requirements for different elements of the space exploration mission. The focus of this study is to look at the specific requirements for a spacecraft that needs to go from earth to moon and back. In this regard we will identify the different GN&C problems in various phases of flight that need to be addressed for designing such a plug-n-play avionics system. The Apollo and the Space Shuttle programs provide rich literature in terms of understanding some of the general GN&C requirements for a space vehicle. The relevant literature is reviewed which helps in narrowing down the different GN&C algorithms that need to be supported along with their individual requirements.

  2. Hardware Implementation of COTS Avionics System on Unmanned Aerial Vehicle Platforms

    Science.gov (United States)

    Yeh, Yoo-Hsiu; Kumar, Parth; Ishihara, Abraham; Ippolito, Corey

    2010-01-01

    Unmanned Aerial Vehicles (UAVs) can serve as low cost and low risk platforms for flight testing in Aeronautics research. The NASA Exploration Aerial Vehicle (EAV) and Experimental Sensor-Controlled Aerial Vehicle (X-SCAV) UAVs were developed in support of control systems research at NASA Ames Research Center. The avionics hardware for both systems has been redesigned and updated, and the structure of the EAV has been further strengthened. Preliminary tests show the avionics operate properly in the new configuration. A linear model for the EAV also was estimated from flight data, and was verified in simulation. These modifications and results prepare the EAV and X-SCAV to be used in a wide variety of flight research projects.

  3. NI Based System for Seu Testing of Memory Chips for Avionics

    Directory of Open Access Journals (Sweden)

    Boruzdina Anna

    2016-01-01

    Full Text Available This paper presents the results of implementation of National Instrument based system for Single Event Upset testing of memory chips into neutron generator experimental facility, which used for SEU tests for avionics purposes. Basic SEU testing algorithm with error correction and constant errors detection is presented. The issues of radiation shielding of NI based system are discussed and solved. The examples of experimental results show the applicability of the presented system for SEU memory testing under neutrons influence.

  4. Digital Systems Validation Handbook. Volume 2. Chapter 18. Avionic Data Bus Integration Technology

    Science.gov (United States)

    1993-11-01

    interaction between a digital data bus and an avionic system. Very Large Scale Integration (VLSI) ICs and multiversion software, which make up digital...1984, the Sperry Corporation developed a fault tolerant system which employed multiversion programming, voting, and monitoring for error detection and...formulate all the significant behavior of a system. MULTIVERSION PROGRAMMING. N-version programming. N-VERSION PROGRAMMING. The independent coding of a

  5. Advanced Avionics and Processor Systems for a Flexible Space Exploration Architecture

    Science.gov (United States)

    Keys, Andrew S.; Adams, James H.; Smith, Leigh M.; Johnson, Michael A.; Cressler, John D.

    2010-01-01

    The Advanced Avionics and Processor Systems (AAPS) project, formerly known as the Radiation Hardened Electronics for Space Environments (RHESE) project, endeavors to develop advanced avionic and processor technologies anticipated to be used by NASA s currently evolving space exploration architectures. The AAPS project is a part of the Exploration Technology Development Program, which funds an entire suite of technologies that are aimed at enabling NASA s ability to explore beyond low earth orbit. NASA s Marshall Space Flight Center (MSFC) manages the AAPS project. AAPS uses a broad-scoped approach to developing avionic and processor systems. Investment areas include advanced electronic designs and technologies capable of providing environmental hardness, reconfigurable computing techniques, software tools for radiation effects assessment, and radiation environment modeling tools. Near-term emphasis within the multiple AAPS tasks focuses on developing prototype components using semiconductor processes and materials (such as Silicon-Germanium (SiGe)) to enhance a device s tolerance to radiation events and low temperature environments. As the SiGe technology will culminate in a delivered prototype this fiscal year, the project emphasis shifts its focus to developing low-power, high efficiency total processor hardening techniques. In addition to processor development, the project endeavors to demonstrate techniques applicable to reconfigurable computing and partially reconfigurable Field Programmable Gate Arrays (FPGAs). This capability enables avionic architectures the ability to develop FPGA-based, radiation tolerant processor boards that can serve in multiple physical locations throughout the spacecraft and perform multiple functions during the course of the mission. The individual tasks that comprise AAPS are diverse, yet united in the common endeavor to develop electronics capable of operating within the harsh environment of space. Specifically, the AAPS tasks for

  6. Digital avionics systems - Overview of FAA/NASA/industry-wide briefing

    Science.gov (United States)

    Larsen, William E.; Carro, Anthony

    1986-01-01

    The effects of incorporating digital technology into the design of aircraft on the airworthiness criteria and certification procedures for aircraft are investigated. FAA research programs aimed at providing data for the functional assessment of aircraft which use digital systems for avionics and flight control functions are discussed. The need to establish testing, assurance assessment, and configuration management technologies to insure the reliability of digital systems is discussed; consideration is given to design verification, system performance/robustness, and validation technology.

  7. An integrated autonomous rendezvous and docking system architecture using Centaur modern avionics

    Science.gov (United States)

    Nelson, Kurt

    1991-01-01

    The avionics system for the Centaur upper stage is in the process of being modernized with the current state-of-the-art in strapdown inertial guidance equipment. This equipment includes an integrated flight control processor with a ring laser gyro based inertial guidance system. This inertial navigation unit (INU) uses two MIL-STD-1750A processors and communicates over the MIL-STD-1553B data bus. Commands are translated into load activation through a Remote Control Unit (RCU) which incorporates the use of solid state relays. Also, a programmable data acquisition system replaces separate multiplexer and signal conditioning units. This modern avionics suite is currently being enhanced through independent research and development programs to provide autonomous rendezvous and docking capability using advanced cruise missile image processing technology and integrated GPS navigational aids. A system concept was developed to combine these technologies in order to achieve a fully autonomous rendezvous, docking, and autoland capability. The current system architecture and the evolution of this architecture using advanced modular avionics concepts being pursued for the National Launch System are discussed.

  8. An integrated autonomous rendezvous and docking system architecture using Centaur modern avionics

    Science.gov (United States)

    Nelson, Kurt

    The avionics system for the Centaur upper stage is in the process of being modernized with the current state-of-the-art in strapdown inertial guidance equipment. This equipment includes an integrated flight control processor with a ring laser gyro based inertial guidance system. This inertial navigation unit (INU) uses two MIL-STD-1750A processors and communicates over the MIL-STD-1553B data bus. Commands are translated into load activation through a Remote Control Unit (RCU) which incorporates the use of solid state relays. Also, a programmable data acquisition system replaces separate multiplexer and signal conditioning units. This modern avionics suite is currently being enhanced through independent research and development programs to provide autonomous rendezvous and docking capability using advanced cruise missile image processing technology and integrated GPS navigational aids. A system concept was developed to combine these technologies in order to achieve a fully autonomous rendezvous, docking, and autoland capability. The current system architecture and the evolution of this architecture using advanced modular avionics concepts being pursued for the National Launch System are discussed.

  9. Modélisation des forces de contact entre le pneu d’un avion et la piste

    OpenAIRE

    Jones, Logan

    2012-01-01

    Lorsqu’un avion atterrit, la force principale nécessaire pour arrêter l’avion est obtenue par le freinage. Par une réduction de la vitesse de rotation des roues, les freins provoquent une vitesse de glissement entre les pneus et la piste. C’est cette différence de vitesse qui génère la force de freinage capable de stopper l’avion. La modélisation de cette force est essentielle pour l’estimation de la longueur de piste à l’atterrissage. Les modèles classiques utilisés par les avionneurs sont a...

  10. AVION: A detailed report on the preliminary design of a 79-passenger, high-efficiency, commercial transport aircraft

    Science.gov (United States)

    Mayfield, William; Perkins, Brett; Rogan, William; Schuessler, Randall; Stockert, Joe

    1990-01-01

    The Avion is the result of an investigation into the preliminary design for a high-efficiency commercial transport aircraft. The Avion is designed to carry 79 passengers and a crew of five through a range of 1,500 nm at 455 kts (M=0.78 at 32,000 ft). It has a gross take-off weight of 77,000 lb and an empty weight of 42,400 lb. Currently there are no American-built aircraft designed to fit the 60 to 90 passenger, short/medium range marketplace. The Avion gathers the premier engineering achievements of flight technology and integrates them into an aircraft which will challenge the current standards of flight efficiency, reliability, and performance. The Avion will increase flight efficiency through reduction of structural weight and the improvement of aerodynamic characteristics and propulsion systems. Its design departs from conventional aircraft design tradition with the incorporation of a three-lifting-surface (or tri-wing) configuration. Further aerodynamic improvements are obtained through modest main wing forward sweeping, variable incidence canards, aerodynamic coupling between the canard and main wing, leading edge extensions, winglets, an aerodynamic tailcone, and a T-tail empennage. The Avion is propelled by propfans, which are one of the most promising developments for raising propulsive efficiencies at high subsonic Mach numbers. Special attention is placed on overall configuration, fuselage layout, performance estimations, component weight estimations, and planform design. Leading U.S. technology promises highly efficient flight for the 21st century; the Avion will fulfill this promise to passenger transport aviation.

  11. The Unmanned Mission Avionics Test Heliciopter - a Flexible and Versatile Vtol-Uas Experimental System

    Science.gov (United States)

    Schulz, H.-W., , Dr.

    2011-09-01

    civil customers. These applications cover a wide spectrum from R&D programs for the military customer to special services for the civil customer. This paper focuses on the technical conversion of a commercially available VTOL-UAS to ESG's Unmanned Mission Avionics Test Helicopter (UMAT), its concept and operational capabilities. At the end of the paper, the current integration of a radar sensor is described as an example of the UMATs flexibility. The radar sensor is developed by the Fraunhofer Institute for High Frequency Physics and Radar Techniques (FHR). It is integrated by ESG together with the industrial partner SWISS UAV.

  12. THE UNMANNED MISSION AVIONICS TEST HELICIOPTER – A FLEXIBLE AND VERSATILE VTOL-UAS EXPERIMENTAL SYSTEM

    Directory of Open Access Journals (Sweden)

    Dr. H.-W. Schulz

    2012-09-01

    Full Text Available civil customers. These applications cover a wide spectrum from R&D programs for the military customer to special services for the civil customer. This paper focuses on the technical conversion of a commercially available VTOL-UAS to ESG's Unmanned Mission Avionics Test Helicopter (UMAT, its concept and operational capabilities. At the end of the paper, the current integration of a radar sensor is described as an example of the UMATs flexibility. The radar sensor is developed by the Fraunhofer Institute for High Frequency Physics and Radar Techniques (FHR. It is integrated by ESG together with the industrial partner SWISS UAV.

  13. Customer Avionics Interface Development and Analysis (CAIDA) Lab DEWESoft Display Creation

    Science.gov (United States)

    Coffey, Connor

    2015-01-01

    The Customer Avionics Interface Development and Analysis (CAIDA) Lab supports the testing of the Launch Control System (LCS), NASA's command and control system for the Space Launch System (SLS), Orion Multi-Purpose Crew Vehicle (MPCV), and ground support equipment. The objectives of the year-long internship were to support day-to-day operations of the CAIDA Lab, create prelaunch and tracking displays for Orion's Exploration Flight Test 1 (EFT-1), and create a program to automate the creation of displays for SLS and MPCV to be used by CAIDA and the Record and Playback Subsystem (RPS).

  14. Development of Integrated Modular Avionics Application Based on Simulink and XtratuM

    Science.gov (United States)

    Fons-Albert, Borja; Usach-Molina, Hector; Vila-Carbo, Joan; Crespo-Lorente, Alfons

    2013-08-01

    This paper presents an integral approach for designing avionics applications that meets the requirements for software development and execution of this application domain. Software design follows the Model-Based design process and is performed in Simulink. This approach allows easy and quick testbench development and helps satisfying DO-178B requirements through the use of proper tools. The software execution platform is based on XtratuM, a minimal bare-metal hypervisor designed in our research group. XtratuM provides support for IMA-SP (Integrated Modular Avionics for Space) architectures. This approach allows the code generation of a Simulink model to be executed on top of Lithos as XtratuM partition. Lithos is a ARINC-653 compliant RTOS for XtratuM. The paper concentrates in how to smoothly port Simulink designs to XtratuM solving problems like application partitioning, automatic code generation, real-time tasking, interfacing, and others. This process is illustrated with an autopilot design test using a flight simulator.

  15. Linux OS integrated modular avionics application development framework with apex API of ARINC653 specification

    Directory of Open Access Journals (Sweden)

    Anna V. Korneenkova

    2017-01-01

    Full Text Available The framework is made to provide tools to develop the integrated modular avionics (IMA applications, which could be launched on the target platform LynxOs-178 without modifying their source code. The framework usage helps students to form skills for developing modern modules of the avionics. In addition, students obtain deeper knowledge for the development of competencies in the field of technical creativity by using of the framework.The article describes the architecture and implementation of the Linux OS framework for ARINC653 compliant OS application development.The proposed approach reduces ARINC-653 application development costs and gives a unified tool to implement OS vendor independent code that meets specification. To achieve import substitution free and open-source Linux OS is used as an environment for developing IMA applications.The proposed framework is applicable for using as the tool to develop IMA applications and as the tool for development of the following competencies: the ability to master techniques of using software to solve practical problems, the ability to develop components of hardware and software systems and databases, using modern tools and programming techniques, the ability to match hardware and software tools in the information and automated systems, the readiness to apply the fundamentals of informatics and programming to designing, constructing and testing of software products, the readiness to apply basic methods and tools of software development, knowledge of various technologies of software development.

  16. Combat Aircraft Noise held in Bonn, Germany on 23-25 October 1991 (Le Bruit Genere par les Avions de Combat)

    Science.gov (United States)

    1992-04-01

    installer des et d’un avion d’entratnement frangais au dispositifs spiciaux i bord des avions do combat dicolla,- at I l’atterrissage, on prisentera...l’Ioignomont des oggloodrations ost suffisant. Le tableau do Ia figure I donne les niveaux 1o figure 3 momtro lI’volution du nivosu do do bruit calculis dons...126.5 120.0 108.5 115.0 108.0 96.0 TABLEAU 2 10-6 V - EXAMEN DES RESULTAl’S soumisos au bruit des avions (lorsqueolle est possible). Leoxamen do

  17. Power, Avionics and Software - Phase 1.0:. [Subsystem Integration Test Report

    Science.gov (United States)

    Ivancic, William D.; Sands, Obed S.; Bakula, Casey J.; Oldham, Daniel R.; Wright, Ted; Bradish, Martin A.; Klebau, Joseph M.

    2014-01-01

    This report describes Power, Avionics and Software (PAS) 1.0 subsystem integration testing and test results that occurred in August and September of 2013. This report covers the capabilities of each PAS assembly to meet integration test objectives for non-safety critical, non-flight, non-human-rated hardware and software development. This test report is the outcome of the first integration of the PAS subsystem and is meant to provide data for subsequent designs, development and testing of the future PAS subsystems. The two main objectives were to assess the ability of the PAS assemblies to exchange messages and to perform audio testing of both inbound and outbound channels. This report describes each test performed, defines the test, the data, and provides conclusions and recommendations.

  18. Proven high-reliability assembly methods applied to avionics fiber-optics high-speed transceivers

    Science.gov (United States)

    Lauzon, Jocelyn; Leduc, Lorrain; Bessette, Daniel; Bélanger, Nicolas; Larose, Robert; Dion, Bruno

    2012-06-01

    Harsh environment avionics applications require operating temperature ranges that can extend to, and exceed -50 to 115°C. For obvious maintenance, management and cost arguments, product lifetimes as long as 20 years are also sought. This leads to mandatory long-term hermeticity that cannot be obtained with epoxy or silicone sealing; but only with glass seal or metal solder or brazing. A hermetic design can indirectly result in the required RF shielding of the component. For fiber-optics products, these specifications need to be compatible with the smallest possible size, weight and power consumption. The products also need to offer the best possible high-speed performances added to the known EMI immunity in the transmission lines. Fiber-optics transceivers with data rates per fiber channel up to 10Gbps are now starting to be offered on the market for avionics applications. Some of them are being developed by companies involved in the "normal environment" telecommunications market that are trying to ruggedize their products packaging in order to diversify their customer base. Another approach, for which we will present detailed results, is to go back to the drawing boards and design a new product that is adapted to proven MIL-PRF-38534 high-reliability packaging assembly methods. These methods will lead to the introduction of additional requirements at the components level; such as long-term high-temperature resistance for the fiber-optic cables. We will compare both approaches and demonstrate the latter, associated with the redesign, is the preferable one. The performance of the fiber-optic transceiver we have developed, in terms of qualification tests such as temperature cycling, constant acceleration, hermeticity, residual gaz analysis, operation under random vibration and mechanical shocks and accelerated lifetime tests will be presented. The tests are still under way, but so far, we have observed no performance degradation of such a product after more than

  19. Localisation à partir de données laser d'un robot naviguant autour d'un avion

    OpenAIRE

    Frejaville, Jérémy; Larnier, Stanislas; Vetault, Stéphane

    2016-01-01

    National audience; This article discusses the pose estimation of the mobile platform Air-Cobot relative to the aircraft around which it operates. Autonomous and collaborative, this robot inspects aircrafts. It is equipped with distance sensors laser scans. The presented localization methods have been successfully tested in a real environment.; Cet article traite du calcul de la pose de la plateforme mobile Air-Cobot par rapport à l'avion autour duquel elle évolue. Autonome et collaboratif, ce...

  20. TechEdSat - An Educational 1U CubeSat Architecture Using Plug-and-Play Avionics

    Science.gov (United States)

    Frost, Chad

    2015-01-01

    Mission Objectives: build a 1U cubesat within 6 months from kickoff to launch. Demonstrate and evaluate the Space Plug-and-Play avionics hardware and software from ÅAC Microtec; investigate both Iridium and Orbcomm intersatellite communication as a method of eliminating the requirement for a physical ground station in Nano satellite missions; demonstrate the capabilities of the JAXA J-SSOD aboard the ISS, and be one of the first cubesats to be deployed from the ISS.

  1. Intermediate Experimental Vehicle (IXV): Avionics and Software of the ESA Reentry Demonstrator

    Science.gov (United States)

    Malucchi, Giovanni; Dussy, Stephane; Camuffo, Fabrizio

    2012-08-01

    The IXV project is conceived as a technology platform that would perform the step forward with respect to the Atmospheric Reentry Demonstrator (ARD), by increasing the system maneuverability and verifying the critical technology performances against a wider re- entry corridor.The main objective is to design, develop and to perform an in-flight verification of an autonomous lifting and aerodynamically controlled (by a combined use of thrusters and aerodynamic surfaces) reentry system.The project also includes the verification and experimentation of a set of critical reentry technologies and disciplines:Thermal Protection System (TPS), for verification and characterization of thermal protection technologies in representative operational environment;Aerodynamics - Aerthermodynamics (AED-A TD), for understanding and validation of aerodynamics and aerothermodyamics phenomena with improvement of design tools;Guidance, Navigation and Control (GNC), for verification of guidance, navigation and control techniques in representative operational environment (i.e. reentry from Low Earth Orbit);Flight dynamics, to update and validate the vehicle model during actual flight, focused on stability and control derivatives.The above activities are being performed through the implementation of a strict system design-to-cost approach with a proto-flight model development philosophy.In 2008 and 2009, the IXV project activities reached the successful completion of the project Phase-B, including the System PDR, and early project Phase-C.In 2010, following a re-organization of the industrial consortium, the IXV project successfully completed a design consolidation leading to an optimization of the technical baseline including the GNC, avionics (i.e. power, data handling, radio frequency and telemetry), measurement sensors, hot and cold composite structures, thermal protections and control, with significant improvements of the main system budgets.The project has successfully closed the

  2. Expanding AirSTAR Capability for Flight Research in an Existing Avionics Design

    Science.gov (United States)

    Laughter, Sean A.

    2012-01-01

    The NASA Airborne Subscale Transport Aircraft Research (AirSTAR) project is an Unmanned Aerial Systems (UAS) test bed for experimental flight control laws and vehicle dynamics research. During its development, the test bed has gone through a number of system permutations, each meant to add functionality to the concept of operations of the system. This enabled the build-up of not only the system itself, but also the support infrastructure and processes necessary to support flight operations. These permutations were grouped into project phases and the move from Phase-III to Phase-IV was marked by a significant increase in research capability and necessary safety systems due to the integration of an Internal Pilot into the control system chain already established for the External Pilot. The major system changes in Phase-IV operations necessitated a new safety and failsafe system to properly integrate both the Internal and External Pilots and to meet acceptable project safety margins. This work involved retrofitting an existing data system into the evolved concept of operations. Moving from the first Phase-IV aircraft to the dynamically scaled aircraft further involved restructuring the system to better guard against electromagnetic interference (EMI), and the entire avionics wiring harness was redesigned in order to facilitate better maintenance and access to onboard electronics. This retrofit and harness re-design will be explored and how it integrates with the evolved Phase-IV operations.

  3. Self-Contained Avionics Sensing and Flight Control System for Small Unmanned Aerial Vehicle

    Science.gov (United States)

    Shams, Qamar A. (Inventor); Logan, Michael J. (Inventor); Fox, Robert L. (Inventor); Fox, legal representative, Christopher L. (Inventor); Fox, legal representative, Melanie L. (Inventor); Ingham, John C. (Inventor); Laughter, Sean A. (Inventor); Kuhn, III, Theodore R. (Inventor); Adams, James K. (Inventor); Babel, III, Walter C. (Inventor)

    2011-01-01

    A self-contained avionics sensing and flight control system is provided for an unmanned aerial vehicle (UAV). The system includes sensors for sensing flight control parameters and surveillance parameters, and a Global Positioning System (GPS) receiver. Flight control parameters and location signals are processed to generate flight control signals. A Field Programmable Gate Array (FPGA) is configured to provide a look-up table storing sets of values with each set being associated with a servo mechanism mounted on the UAV and with each value in each set indicating a unique duty cycle for the servo mechanism associated therewith. Each value in each set is further indexed to a bit position indicative of a unique percentage of a maximum duty cycle for the servo mechanism associated therewith. The FPGA is further configured to provide a plurality of pulse width modulation (PWM) generators coupled to the look-up table. Each PWM generator is associated with and adapted to be coupled to one of the servo mechanisms.

  4. A knowledge-based flight status monitor for real-time application in digital avionics systems

    Science.gov (United States)

    Duke, E. L.; Disbrow, J. D.; Butler, G. F.

    1989-01-01

    The Dryden Flight Research Facility of the National Aeronautics and Space Administration (NASA) Ames Research Center (Ames-Dryden) is the principal NASA facility for the flight testing and evaluation of new and complex avionics systems. To aid in the interpretation of system health and status data, a knowledge-based flight status monitor was designed. The monitor was designed to use fault indicators from the onboard system which are telemetered to the ground and processed by a rule-based model of the aircraft failure management system to give timely advice and recommendations in the mission control room. One of the important constraints on the flight status monitor is the need to operate in real time, and to pursue this aspect, a joint research activity between NASA Ames-Dryden and the Royal Aerospace Establishment (RAE) on real-time knowledge-based systems was established. Under this agreement, the original LISP knowledge base for the flight status monitor was reimplemented using the intelligent knowledge-based system toolkit, MUSE, which was developed under RAE sponsorship. Details of the flight status monitor and the MUSE implementation are presented.

  5. Modeling and characterization of VCSEL-based avionics full-duplex ethernet (AFDX) gigabit links

    Science.gov (United States)

    Ly, Khadijetou S.; Rissons, A.; Gambardella, E.; Bajon, D.; Mollier, J.-C.

    2008-02-01

    Low cost and intrinsic performances of 850 nm Vertical Cavity Surface Emitting Lasers (VCSELs) compared to Light Emitting Diodes make them very attractive for high speed and short distances data communication links through optical fibers. Weight saving and Electromagnetic Interference withstanding requirements have led to the need of a reliable solution to improve existing avionics high speed buses (e.g. AFDX) up to 1Gbps over 100m. To predict and optimize the performance of the link, the physical behavior of the VCSEL must be well understood. First, a theoretical study is performed through the rate equations adapted to VCSEL in large signal modulation. Averaged turn-on delays and oscillation effects are analytically computed and analyzed for different values of the on- and off state currents. This will affect the eye pattern, timing jitter and Bit Error Rate (BER) of the signal that must remain within IEEE 802.3 standard limits. In particular, the off-state current is minimized below the threshold to allow the highest possible Extinction Ratio. At this level, the spontaneous emission is dominating and leads to significant turn-on delay, turn-on jitter and bit pattern effects. Also, the transverse multimode behavior of VCSELs, caused by Spatial Hole Burning leads to some dispersion in the fiber and degradation of BER. VCSEL to Multimode Fiber coupling model is provided for prediction and optimization of modal dispersion. Lastly, turn-on delay measurements are performed on a real mock-up and results are compared with calculations.

  6. Condensate minerals from a burning coal-waste heap in Avion, Northern France

    Energy Technology Data Exchange (ETDEWEB)

    Masalehdani, M.N.N.; Mees, F.; Dubois, M.; Coquinot, Y.; Potdevin, J.L.; Fialin, M.; Blanc-Valleron, M.M. [University of Lille 1, Villeneuve Dascq (France)

    2009-06-15

    A coal-waste heap in Avion, northern France, that has been undergoing subsurface combustion for several decades, is marked by the occurrence of efflorescences at combustion sites where gas and water vapor escape from surficial cracks and vents. Analysis of the efflorescences show that twenty different species of mineral are present, comprising various sulfates, as well as halides and native sulfur. The constituents needed for the formation of these minerals are ultimately derived from the heap of coalmine waste, composed mainly of pyrite-bearing carbonaceous shale, coal and minor amounts of sandstone. They may be partly released by acid weathering of waste-heap materials prior to combustion, but largely by thermal decomposition and oxidation of those materials during combustion processes. Formation of the efflorescences near gas-discharge zones indicates transport of constituent to those zones from the inner part of the waste heap, which can occur in the gas phase for some elements (S, N, H and Cl), but would require droplets of water vapor as carriers for most cations. Interaction between condensate solutions and the local debris at the surface of the waste heap may also contribute to cations input prior to the formation of secondary minerals. Most minerals formed from a liquid phase along the rock-debris surface at low temperatures (T {<=}100 {sup o}C), as confirmed by the occurrence of fluid inclusions. Only salammoniac, native sulfur and mascagnite (where crystallized as a monocrystalline phase) were formed directly from a gas phase. The coal-waste heap shows great variations in mineral assemblages among sampling sites, which must be related to variations in waste composition and in conditions at the level at which the elements are released and where mineral formation takes place.

  7. Design of a GN and C system to meet reliability goals. [guidance, navigation and control avionics for space shuttle orbiter

    Science.gov (United States)

    Kayton, M.

    1974-01-01

    This paper analyzes the reliability of the guidance, navigation, and control (GNC) portion of an avionics system for the Space Shuttle Orbiter. This analysis shows how the GNC design is affected by the need to achieve an acceptable probability of successful completion of a mission and of safe return to an airport. It varies the redundancy of the inertial measurement unit (IMU), computers, and other time-critical elements. It also includes the reliability of the flight control electronics and of the nontime-critical sensors on a phase-by-phase basis. It shows that quadruple redundancy in certain subsystems, high quality parts, and cross-strapping on orbit are required.

  8. A Library of Rad Hard Mixed-Voltage/Mixed-Signal Building Blocks for Integration of Avionics Systems for Deep Space

    Science.gov (United States)

    Mojarradi, M. M.; Blaes, B.; Kolawa, E. A.; Blalock, B. J.; Li, H. W.; Buck, K.; Houge, D.

    2001-01-01

    To build the sensor intensive system-on-a-chip for the next generation spacecrafts for deep space, Center for Integration of Space Microsystems at JPL (CISM) takes advantage of the lower power rating and inherent radiation resistance of Silicon on Insulator technology (SOI). We are developing a suite of mixed-voltage and mixed-signal building blocks in Honeywell's SOI process that can enable the rapid integration of the next generation avionics systems with lower power rating, higher reliability, longer life, and enhanced radiation tolerance for spacecrafts such as the Europa Orbiter and Europa Lander. The mixed-voltage building blocks are predominantly for design of adaptive power management systems. Their design centers around an LDMOS structure that is being developed by Honeywell, Boeing Corp, and the University of Idaho. The mixed-signal building blocks are designed to meet the low power, extreme radiation requirement of deep space applications. These building blocks are predominantly used to interface analog sensors to the digital CPU of the next generation avionics system on a chip. Additional information is contained in the original extended abstract.

  9. Multi-objective optimisation of aircraft flight trajectories in the ATM and avionics context

    Science.gov (United States)

    Gardi, Alessandro; Sabatini, Roberto; Ramasamy, Subramanian

    2016-05-01

    The continuous increase of air transport demand worldwide and the push for a more economically viable and environmentally sustainable aviation are driving significant evolutions of aircraft, airspace and airport systems design and operations. Although extensive research has been performed on the optimisation of aircraft trajectories and very efficient algorithms were widely adopted for the optimisation of vertical flight profiles, it is only in the last few years that higher levels of automation were proposed for integrated flight planning and re-routing functionalities of innovative Communication Navigation and Surveillance/Air Traffic Management (CNS/ATM) and Avionics (CNS+A) systems. In this context, the implementation of additional environmental targets and of multiple operational constraints introduces the need to efficiently deal with multiple objectives as part of the trajectory optimisation algorithm. This article provides a comprehensive review of Multi-Objective Trajectory Optimisation (MOTO) techniques for transport aircraft flight operations, with a special focus on the recent advances introduced in the CNS+A research context. In the first section, a brief introduction is given, together with an overview of the main international research initiatives where this topic has been studied, and the problem statement is provided. The second section introduces the mathematical formulation and the third section reviews the numerical solution techniques, including discretisation and optimisation methods for the specific problem formulated. The fourth section summarises the strategies to articulate the preferences and to select optimal trajectories when multiple conflicting objectives are introduced. The fifth section introduces a number of models defining the optimality criteria and constraints typically adopted in MOTO studies, including fuel consumption, air pollutant and noise emissions, operational costs, condensation trails, airspace and airport operations

  10. The Integrated Safety-Critical Advanced Avionics Communication and Control (ISAACC) System Concept: Infrastructure for ISHM

    Science.gov (United States)

    Gwaltney, David A.; Briscoe, Jeri M.

    2005-01-01

    Integrated System Health Management (ISHM) architectures for spacecraft will include hard real-time, critical subsystems and soft real-time monitoring subsystems. Interaction between these subsystems will be necessary and an architecture supporting multiple criticality levels will be required. Demonstration hardware for the Integrated Safety-Critical Advanced Avionics Communication & Control (ISAACC) system has been developed at NASA Marshall Space Flight Center. It is a modular system using a commercially available time-triggered protocol, ?Tp/C, that supports hard real-time distributed control systems independent of the data transmission medium. The protocol is implemented in hardware and provides guaranteed low-latency messaging with inherent fault-tolerance and fault-containment. Interoperability between modules and systems of modules using the TTP/C is guaranteed through definition of messages and the precise message schedule implemented by the master-less Time Division Multiple Access (TDMA) communications protocol. "Plug-and-play" capability for sensors and actuators provides automatically configurable modules supporting sensor recalibration and control algorithm re-tuning without software modification. Modular components of controlled physical system(s) critical to control algorithm tuning, such as pumps or valve components in an engine, can be replaced or upgraded as "plug and play" components without modification to the ISAACC module hardware or software. ISAACC modules can communicate with other vehicle subsystems through time-triggered protocols or other communications protocols implemented over Ethernet, MIL-STD- 1553 and RS-485/422. Other communication bus physical layers and protocols can be included as required. In this way, the ISAACC modules can be part of a system-of-systems in a vehicle with multi-tier subsystems of varying criticality. The goal of the ISAACC architecture development is control and monitoring of safety critical systems of a

  11. Definition, analysis and development of an optical data distribution network for integrated avionics and control systems. Part 2: Component development and system integration

    Science.gov (United States)

    Yen, H. W.; Morrison, R. J.

    1984-01-01

    Fiber optic transmission is emerging as an attractive concept in data distribution onboard civil aircraft. Development of an Optical Data Distribution Network for Integrated Avionics and Control Systems for commercial aircraft will provide a data distribution network that gives freedom from EMI-RFI and ground loop problems, eliminates crosstalk and short circuits, provides protection and immunity from lightning induced transients and give a large bandwidth data transmission capability. In addition there is a potential for significantly reducing the weight and increasing the reliability over conventional data distribution networks. Wavelength Division Multiplexing (WDM) is a candidate method for data communication between the various avionic subsystems. With WDM all systems could conceptually communicate with each other without time sharing and requiring complicated coding schemes for each computer and subsystem to recognize a message. However, the state of the art of optical technology limits the application of fiber optics in advanced integrated avionics and control systems. Therefore, it is necessary to address the architecture for a fiber optics data distribution system for integrated avionics and control systems as well as develop prototype components and systems.

  12. 76 FR 47520 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Model ATR42 and ATR72 Airplanes

    Science.gov (United States)

    2011-08-05

    ... Service Information Avions de Transport R gional has issued Service Bulletin ATR42-55-0014, dated May 11... of Design Authority, we have been notified of the unsafe condition described in the MCAI and service... design. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and...

  13. A Recommended Methodology for Quantifying NDE/NDI Based on Aircraft Engine Experience (Le Projet de Methodologie Pour l’Evaluation du Controle Non- Destructif Fonde sur l’Experience Acquise sur les moteurs d’Avions)

    Science.gov (United States)

    1993-04-01

    A Recommended Methodology for Quantifying NDE/NDI Based on Aircraft Engine Experience--Translation(Le Projet de Methodologie Pour l’Evaluation du Controle Non-Destructif Fonde sur l’Experience Acquise sur les moteurs d’Avions)

  14. An experimental Study using ACSL and Frama-C to formulate and verify Low-Level Requirements from a DO-178C compliant Avionics Project

    Directory of Open Access Journals (Sweden)

    Frank Dordowsky

    2015-08-01

    Full Text Available Safety critical avionics software is a natural application area for formal verification. This is reflected in the formal method's inclusion into the certification guideline DO-178C and its formal methods supplement DO-333. Airbus and Dassault-Aviation, for example, have conducted studies in using formal verification. A large German national research project, Verisoft XT, also examined the application of formal methods in the avionics domain. However, formal methods are not yet mainstream, and it is questionable if formal verification, especially formal deduction, can be integrated into the software development processes of a resource constrained small or medium enterprise (SME. ESG, a Munich based medium sized company, has conducted a small experimental study on the application of formal verification on a small portion of a real avionics project. The low level specification of a software function was formalized with ACSL, and the corresponding source code was partially verified using Frama-C and the WP plugin, with Alt-Ergo as automated prover. We established a couple of criteria which a method should meet to be fit for purpose for industrial use in SME, and evaluated these criteria with the experience gathered by using ACSL with Frama-C on a real world example. The paper reports on the results of this study but also highlights some issues regarding the method in general which, in our view, will typically arise when using the method in the domain of embedded real-time programming.

  15. Computer architecture for efficient algorithmic executions in real-time systems: New technology for avionics systems and advanced space vehicles

    Science.gov (United States)

    Carroll, Chester C.; Youngblood, John N.; Saha, Aindam

    1987-01-01

    Improvements and advances in the development of computer architecture now provide innovative technology for the recasting of traditional sequential solutions into high-performance, low-cost, parallel system to increase system performance. Research conducted in development of specialized computer architecture for the algorithmic execution of an avionics system, guidance and control problem in real time is described. A comprehensive treatment of both the hardware and software structures of a customized computer which performs real-time computation of guidance commands with updated estimates of target motion and time-to-go is presented. An optimal, real-time allocation algorithm was developed which maps the algorithmic tasks onto the processing elements. This allocation is based on the critical path analysis. The final stage is the design and development of the hardware structures suitable for the efficient execution of the allocated task graph. The processing element is designed for rapid execution of the allocated tasks. Fault tolerance is a key feature of the overall architecture. Parallel numerical integration techniques, tasks definitions, and allocation algorithms are discussed. The parallel implementation is analytically verified and the experimental results are presented. The design of the data-driven computer architecture, customized for the execution of the particular algorithm, is discussed.

  16. Waveform Developer's Guide for the Integrated Power, Avionics, and Software (iPAS) Space Telecommunications Radio System (STRS) Radio

    Science.gov (United States)

    Shalkhauser, Mary Jo W.; Roche, Rigoberto

    2017-01-01

    The Space Telecommunications Radio System (STRS) provides a common, consistent framework for software defined radios (SDRs) to abstract the application software from the radio platform hardware. The STRS standard aims to reduce the cost and risk of using complex, configurable and reprogrammable radio systems across NASA missions. To promote the use of the STRS architecture for future NASA advanced exploration missions, NASA Glenn Research Center (GRC) developed an STRS-compliant SDR on a radio platform used by the Advance Exploration System program at the Johnson Space Center (JSC) in their Integrated Power, Avionics, and Software (iPAS) laboratory. The iPAS STRS Radio was implemented on the Reconfigurable, Intelligently-Adaptive Communication System (RIACS) platform, currently being used for radio development at JSC. The platform consists of a Xilinx(Trademark) ML605 Virtex(Trademark)-6 FPGA board, an Analog Devices FMCOMMS1-EBZ RF transceiver board, and an Embedded PC (Axiomtek(Trademark) eBox 620-110-FL) running the Ubuntu 12.4 operating system. The result of this development is a very low cost STRS compliant platform that can be used for waveform developments for multiple applications. The purpose of this document is to describe how to develop a new waveform using the RIACS platform and the Very High Speed Integrated Circuits (VHSIC) Hardware Description Language (VHDL) FPGA wrapper code and the STRS implementation on the Axiomtek processor.

  17. Hardware Interface Description for the Integrated Power, Avionics, and Software (iPAS) Space Telecommunications Radio Ssystem (STRS) Radio

    Science.gov (United States)

    Shalkhauser, Mary Jo W.; Roche, Rigoberto

    2017-01-01

    The Space Telecommunications Radio System (STRS) provides a common, consistent framework for software defined radios (SDRs) to abstract the application software from the radio platform hardware. The STRS standard aims to reduce the cost and risk of using complex, configurable and reprogrammable radio systems across NASA missions. To promote the use of the STRS architecture for future NASA advanced exploration missions, NASA Glenn Research Center (GRC) developed an STRS-compliant SDR on a radio platform used by the Advance Exploration System program at the Johnson Space Center (JSC) in their Integrated Power, Avionics, and Software (iPAS) laboratory. The iPAS STRS Radio was implemented on the Reconfigurable, Intelligently-Adaptive Communication System (RIACS) platform, currently being used for radio development at JSC. The platform consists of a Xilinx ML605 Virtex-6 FPGA board, an Analog Devices FMCOMMS1-EBZ RF transceiver board, and an Embedded PC (Axiomtek eBox 620-110-FL) running the Ubuntu 12.4 operating system. Figure 1 shows the RIACS platform hardware. The result of this development is a very low cost STRS compliant platform that can be used for waveform developments for multiple applications.The purpose of this document is to describe how to develop a new waveform using the RIACS platform and the Very High Speed Integrated Circuits (VHSIC) Hardware Description Language (VHDL) FPGA wrapper code and the STRS implementation on the Axiomtek processor.

  18. Détection d'amers visuels pour la navigation d'un robot autonome autour d'un avion et son inspection

    OpenAIRE

    Villemot, Tanguy; Larnier, Stanislas; Vetault, Stéphane

    2016-01-01

    National audience; This article discusses the detection of visual features for the navigation of the platform Air-Cobot around an aircraft. This autonomous mobile and collaborative robot is dedicated to the inspection of airplane. A new visual detection and inspection approach is proposed.; Cet article traite de la détection d'amers visuels pour la navigation de la plateforme robotique Air-Cobot autour d'un avion. Ce robot mobile autonome et collaboratif est dédié à l'inspection des aéronefs....

  19. Validation of fault-free behavior of a reliable multiprocessor system - FTMP: A case study. [Fault-Tolerant Multi-Processor avionics

    Science.gov (United States)

    Clune, E.; Segall, Z.; Siewiorek, D.

    1984-01-01

    A program of experiments has been conducted at NASA-Langley to test the fault-free performance of a Fault-Tolerant Multiprocessor (FTMP) avionics system for next-generation aircraft. Baseline measurements of an operating FTMP system were obtained with respect to the following parameters: instruction execution time, frame size, and the variation of clock ticks. The mechanisms of frame stretching were also investigated. The experimental results are summarized in a table. Areas of interest for future tests are identified, with emphasis given to the implementation of a synthetic workload generation mechanism on FTMP.

  20. Progreso tecnológico, precios hedónicos y aprendizaje en la práctica: Una aplicación a los aviones de caza a reacción

    OpenAIRE

    Bongers Chicano, Aneli María

    2016-01-01

    La presente Tesis Doctoral tiene como objetivo estudiar diferentes aspectos en relación al progreso tecnológico y al coste de adquisición de los aviones de caza a reacción. La Tesis Doctoral está formada por tres capítulos fundamentales, al margen del capítulo de introducción y del capítulo de conclusiones finales. Estos tres capítulos tienen como objetivo fundamental la medición del progreso tecnológico en los aviones de caza a reacción desde diferentes perspectivas y usando diferentes aprox...

  1. Avionics System Performance Management

    National Research Council Canada - National Science Library

    Damania, Bhavesh

    1998-01-01

    .... The reasons for improved performance management include advances in processor technology and architectures, increasingly integrated systems, and the requirement of reducing costs in developing and deploying the systems...

  2. Survivable Avionics Computer System.

    Science.gov (United States)

    1980-11-01

    T. HALL AFWAL/AAA-1 SCONTRACT F33-615-80-C-1014 SRI Project 1314 E~J Approved by: CHARLES J. SHOENS, Director Systems Techniques Laboratory DAVID A...4 U3.3.3. U3.3.3. 3.3, ~l3.U OXZrZrZr -Z~ 31Zr31Zr I- o - NOIA . 3,3. 3,3. 3𔃽, 3~3, -- Zr -Zr A .4 .4 3, 3, 3, t-~ 3, ~3,3, .03~ .03, 3,3.4 3,3

  3. Avionics Data Base.

    Science.gov (United States)

    1985-01-01

    HSI 5 -BS 4r, INDICATOR $ 10076 REMOTE M;, TD UNIT 1.3 LB $1488 REMARKS 4 INCH SYSTEM FEATURING DIGITAL DME TIME -0 GC CP GS INFORMATION, EC : HE:5G...R AS 4~ 0, - NCL R PCK R )CTE MA 7 D / -:N5L ELi uN7; .ZC*R USE IN 1 NAV w"RRAN7Y IYR OF tT /L INDX 343 01 H, 3 :uOMPCNENN- NAME 33 :E2Y-:ER D NJ- iE... TD Dl I ThNPL;T ;AS DAITE 9/64 1xz 4302072 C mC0N EN T \\NE ~y’ NIPNJAE>P C ER EiENO:X YICZDEu ML S--𔃺 A FA 3 91/12, C0 C104 28~ SVDC 7., /;D & C\\J

  4. Affordable Vehicle Avionics

    Data.gov (United States)

    National Aeronautics and Space Administration — AVA technology will guide and control a class of small launchers with state-of-the-art precision, at a cost 2 orders of magnitude lower than conventional GNCs. Using...

  5. Programmable Logic Device (PLD) Design Description for the Integrated Power, Avionics, and Software (iPAS) Space Telecommunications Radio System (STRS) Radio

    Science.gov (United States)

    Shalkhauser, Mary Jo W.

    2017-01-01

    The Space Telecommunications Radio System (STRS) provides a common, consistent framework for software defined radios (SDRs) to abstract the application software from the radio platform hardware. The STRS standard aims to reduce the cost and risk of using complex, configurable and reprogrammable radio systems across NASA missions. To promote the use of the STRS architecture for future NASA advanced exploration missions, NASA Glenn Research Center (GRC) developed an STRS compliant SDR on a radio platform used by the Advance Exploration System program at the Johnson Space Center (JSC) in their Integrated Power, Avionics, and Software (iPAS) laboratory. At the conclusion of the development, the software and hardware description language (HDL) code was delivered to JSC for their use in their iPAS test bed to get hands-on experience with the STRS standard, and for development of their own STRS Waveforms on the now STRS compliant platform.The iPAS STRS Radio was implemented on the Reconfigurable, Intelligently-Adaptive Communication System (RIACS) platform, currently being used for radio development at JSC. The platform consists of a Xilinx ML605 Virtex-6 FPGA board, an Analog Devices FMCOMMS1-EBZ RF transceiver board, and an Embedded PC (Axiomtek eBox 620-110-FL) running the Ubuntu 12.4 operating system. Figure 1 shows the RIACS platform hardware. The result of this development is a very low cost STRS compliant platform that can be used for waveform developments for multiple applications.The purpose of this document is to describe the design of the HDL code for the FPGA portion of the iPAS STRS Radio particularly the design of the FPGA wrapper and the test waveform.

  6. Aerodynamic Engine/Airframe Integration for High Performance Aircraft and Missiles (L’Integration Aerodynamique des Moteurs et des Cellules dans les Avions et les Missiles a Hautes Performances)

    Science.gov (United States)

    1992-09-01

    d’une part un syst~me d’acquisition, de ENDEVCO I large bande passante. Les numdrisation et de stockage sous forme d’un capteurs stationnaires...rodynamique globale 600 de l’avion qui peut varier considdrablement en fonction des contraintes structurales. thermiques ou de sdcuritE qu’on se tixe...cas du turbofusde-stato. 400- Pour limiter les contraintes thermiques et structurales, une 4 montee b pression dynamnique de 0,6 bar a Etd choisie

  7. Application d'une technique de modelisation aerodynamique conceptuelle sur la simulation d'un pilote automatique a commande optimale pour un avion d'affaires

    Science.gov (United States)

    Pollender-Moreau, Olivier

    Ce document présente, dans le cadre d'un contexte conceptuel, une méthode d'enchaînement servant à faire le lien entre les différentes étapes qui permettent de réaliser la simulation d'un aéronef à partir de ses données géométriques et de ses propriétés massiques. En utilisant le cas de l'avion d'affaires Hawker 800XP de la compagnie Hawker Beechcraft, on démontre, via des données, un processus de traitement par lots et une plate-forme de simulation, comment (1) modéliser la géométrie d'un aéronef en plusieurs surfaces, (2) calculer les forces aérodynamiques selon une technique connue sous le nom de Vortex Lattice Method, (3) construire un modèle de vol servant à la simulation des aéronefs pour leur enveloppe de vol en ajoutant des fonctions supplémentaires, (4) construire un modèle de turbosoufflante simplifié, (5) développer un algorithme d'équilibre (trim) du mouvement longitudinal, (6) développer des algorithmes de contrôle à commande moderne, (7) développer certaines fonctions d'un système de pilotage automatique, et (8) rassembler le tout sous une même plate-forme de simulation. Afin de supporter ce travail, une application publique Matlab, connue sous le nom de Tornado, est utilisée conjointement avec d'autres fonctions pour la conception du modèle de vol aérodynamique. D'ailleurs, il sera démontré que le modèle de vol, quoiqu'il soit quand même crédible, ne concorde pas tout à fait avec les données de référence. Par contre, puisque le modèle des moteurs fonctionne bien, que l'algorithme d'équilibrage du mouvement longitudinal fonctionne bien et que les pôles des systèmes dynamiques concordent avec la littérature, les tests dynamiques effectués au sein de la plate-forme de simulation permettent d'obtenir des résultats fonctionnels et crédibles. D'ailleurs, deux systèmes d'augmentation de la stabilité basés sur la méthode de contrôle moderne LQR et couvrant l'enveloppe de vol de l'aéronef via un

  8. Integrated Modular Avionics: The Challenges

    Science.gov (United States)

    Charrier, O.

    2009-05-01

    The need to reduce Space, Weight, and Power (SWaP) across the embedded market leads many Systems Suppliers to run multiple applications on the same processor. The concept seems deceptively simple. However, a lack of experience using this approach, may lead to many mistakes, resulting in unacceptable system performance and unacceptable costs. The objective of this paper is to review the challenges of controlling the execution of multiple applications on the same processor in a Safety or Mission Critical context and, based on return of experiences, point out some of the common mistakes and the limit of what an operating system can control. As no-one has an unlimited budget, the ability to develop and verify such system at reasonable cost, reduced risk, and re-use of the expended effort will be emphasized.

  9. DISEÑO E IMPLEMENTACIÓN DEL SISTEMA DE COMUNICACIONES BASADO EN CAN PARA LA AVIÓNICA EN UN VEHÍCULO AÉREO AUTÓNOMO NO TRIPULADO DESIGN AND IMPLEMENTATION OF A COMMUNICATION SYSTEM BASED ON CAN FOR AVIONICS IN A ROBOT MINI-HELICOPTER

    Directory of Open Access Journals (Sweden)

    Jairo Miguel Vergara Díaz

    2007-07-01

    Full Text Available La necesidad de diseñar el sistema de comunicaciones para la aviónica de un mini helicóptero robot basada en la arquitectura distribuida CAN es la propuesta presentada. El sistema de comunicaciones involucra los aspectos de hardware y software necesarios para permitir el intercambio de datos sobre una red o bus de aviónica desde los sensores y/o hacia los actuadores con el computador central o computador de vuelo. La principal característica de la arquitectura es que permite escalabilidad en la agregación de nuevos dispositivos, garantizando los requerimientos temporales necesarios para la adquisición de datos. Se presentan resultados de intercambio de datos sobre la red de aviónica mostrando las frecuencias de operación alcanzadas.This paper presents the design of the internal communication system for avionics of a robot mini-helicopter based on the CAN distributed architecture. The communication system involves several hardware and software aspects related to data exchange on avionics bus from sensors and actuators with the flight computer. The main characteristic of the architecture is scalability in the addition of new devices, maintaining time requirements for data acquisition. Results of data exchange on the avionics network showing the reached operating update rates for each node are shown.

  10. Reliable avionics design for deep space

    Science.gov (United States)

    Johnson, Stephen B.

    The technical and organizational problems posed by the Space Exploration Initiative (SEI) are discussed, and some possible solutions are examined. It is pointed out that SEI poses a whole new set of challenging problems in the design of reliable systems. These missions and their corresponding systems are far more complex than current systems. The initiative requires a set of vehicles and systems which must have very high levels of autonomy, reliability, and operability for long periods of time. It is emphasized that to achieve these goals in the face of great complexity, new technologies and organizational techniques will be necessary. It is noted that the key to a good design is good people. Not only must good people be found, but they must be placed in positions appropriate to their skills. It is argued that the atomistic and autocratic paradigm of vertical organizations must be replaced with more team-oriented and democratic structures.

  11. General Aviation Activity and Avionics Survey 1981.

    Science.gov (United States)

    1982-12-01

    6720 1384078 6U184727 138448U 80114737 1383841 80918G720 1384079 801180727 1304408 bL18G737 4" 1384076 BUEING727 - 138385 80196720 138448G HP 0o1...17016 LTC 0145 41503 ALLSN 5010 03004 CON? R670 17018 LTC 0235 41505 ALLSN 5010 03005 DUAVXXGIPSV 20004 LTC 0290 41506 ALLII~ 5010 03006 FCO 6440 26003

  12. General Aviation Activity and Avionics Survey 1983.

    Science.gov (United States)

    1984-10-01

    8217- -0 OW s-O Ct0 -J 2 IC a:2 cc CO- I-- 2 Z Z- a * ujs - n cc <U Ix0 00 COO0-4 U -j at- L- £ C)-4 a2 u Zan LUZ <-ci V) - -. f- C-0 2 2 20 220 0 C4 r... BLANCAS 2110612 BLANCA7 1220438 BLANCA7 1220460 BNORM BN2 *BN2 BLANCA7 1220460 BLANCA7 1220501 BNORM *N2 1520202 BLANCA7 1220501 BLANCA7 1220601 BNORN

  13. Impact of Technology on Avionics Cost Trends,

    Science.gov (United States)

    1981-11-01

    realistic and that future L-band transmitters will feature stripline designs with leadless active and passivo component installation. 4.1.5 Audio Baseband...many standard mechanical units. Automatic- intensity adjustment capabilities are being incorporated into LED displays to compensate for ambient

  14. Optimized Computer Systems for Avionics Applications.

    Science.gov (United States)

    1980-02-01

    processing system . . 10 4. Block diagram of a typical electronic warfare system ....... 12 5. Data compression in communication channels with DPCM ...modulation ( DPCM ) is a time domain compression scheme that is effective for tranamitting both image and voice signals. The basic elements of the system... DPCM has been used successfully’in time domain compression of images, although the quality of the reconstruction is highly dependent on the exact

  15. General Aviation Activity and Avionics Survey

    Science.gov (United States)

    1988-11-01

    8217 t N MA 0 0 - CK ~~~ w z (o 1A ’-0 2-67 C) ’ 0 a do (a r. a1 - 1 cm N a VDE C) - 0 0 0 v m’ 0 ED a v ’I- 0n S - 0 0’ m’C) E 0 0 E 0 - - r- Nl Nl E 1i...N 0 0m 0 N 0 r- 0 0 V N4 0 0 0 .4 3y Nl 0 N C, 0 0 C, 0 W 0 - 0100 0 V 0 N~ M 0 0 m C- v v t- v - a C- 0 V V V m 00 0 0 00 0 00 nv 0 00 0 0 0 V 0 00 V...M - - V 0 0100 ’ U 1* 0(6 - ;D -* N. 4. 1 ’>100 10 co01 in - 4.-U in M - mD10ei N 0l m 1m-WInM’>0 1- 6 0 ’nI MID ’t In CS Cla -- 1 Inin ( I 006 104

  16. FPGA for Power Control of MSL Avionics

    Science.gov (United States)

    Wang, Duo; Burke, Gary R.

    2011-01-01

    A PLGT FPGA (Field Programmable Gate Array) is included in the LCC (Load Control Card), GID (Guidance Interface & Drivers), TMC (Telemetry Multiplexer Card), and PFC (Pyro Firing Card) boards of the Mars Science Laboratory (MSL) spacecraft. (PLGT stands for PFC, LCC, GID, and TMC.) It provides the interface between the backside bus and the power drivers on these boards. The LCC drives power switches to switch power loads, and also relays. The GID drives the thrusters and latch valves, as well as having the star-tracker and Sun-sensor interface. The PFC drives pyros, and the TMC receives digital and analog telemetry. The FPGA is implemented both in Xilinx (Spartan 3- 400) and in Actel (RTSX72SU, ASX72S). The Xilinx Spartan 3 part is used for the breadboard, the Actel ASX part is used for the EM (Engineer Module), and the pin-compatible, radiation-hardened RTSX part is used for final EM and flight. The MSL spacecraft uses a FC (Flight Computer) to control power loads, relays, thrusters, latch valves, Sun-sensor, and star-tracker, and to read telemetry such as temperature. Commands are sent over a 1553 bus to the MREU (Multi-Mission System Architecture Platform Remote Engineering Unit). The MREU resends over a remote serial command bus c-bus to the LCC, GID TMC, and PFC. The MREU also sends out telemetry addresses via a remote serial telemetry address bus to the LCC, GID, TMC, and PFC, and the status is returned over the remote serial telemetry data bus.

  17. Integrated Strike Avionics Study. Volume 1

    Science.gov (United States)

    1980-10-01

    z C, ( LL LUU LL Z CH 1 i zo < NIf ~3 0A.199~ 11 2 1 .86 V_ _ _ _ _ _ _ __ _ _ _ _ __) LLI 0 z w fL w z ZW>Z) coɘ LUU LL.4 LL II II zn- U C) UU 0...costs are decreased and the last major disadvantage of concept I is removed. 156 LL 4-1 If; U 4c0 411 >Y r- L oLfl fl Il Ll U r Ll (AA Im H C6 0 a

  18. General Aviation Activity and Avionics Survey 1986.

    Science.gov (United States)

    1987-12-01

    personal, instructional, research, patrol, and sport flying. General aviation aircraft range in complexity from simple gliders and balloons to four engine...N In N N N ML nm D I N C’) Inncc. 0A 0n w 4 4 NL t---I IN N Z0m l tC) L nL n vmr n 0 nL 4. -n 0 1W M’C) 0I ’) - ’) - In-- - - Ŕa) C’In N In ’IT N I...3802051 SCWZERSGI 8050122 SKRSKYS64 8142604 SPORT GEOPEN 3802433 SCWZERSG1 8050124 SKRSKYS70 8143000 SPTPUZRF40 8451012 SCWZERSG1 8050146 SKRSKYS76

  19. General Aviation Activity and Avionics Survey 1985

    Science.gov (United States)

    1987-03-01

    personal, instructional, research, patrol, and sport flying. General aviation aircraft range in complexity from simple gliders and balloons to four...4 IANInI -00 w Q * 0* VMr r, C’s - . * I: N - in * N . %- N Cm. 0 r - I N a N401 ’n --vW .. r .- 8 .. _ acjua a. crm M SM NMWU NAMl moo - C4 4W 9...SPHRTHVENTUS 3802051 STRMAN3 8560208 TENCO 11A 8890402 SPORT GEOPEN 3802433 STRMAN4 8560302 TENCO 11A 8890404 SPTPUZRF40 8451012 STRMAN4 8560306 TEMCO T35

  20. Software Engineering and Its Application to Avionics

    Science.gov (United States)

    1988-01-01

    DESIGN ES RAI ES EV NEIE EI RE IEW O EE EIW EVIW AO ANACAI -DUNCIONA CTAIURTIN APA PHYSNT ITG I CAON FOUAIR PIGUR .G Rapid Prtoyp SofTtwe. " AIh...at d’Armement deavione de combat. 41-5 Lea coneione entre I** 6qoipsuents don @Yatie. dsrmes micerns doivent respecter des norma techniques qul soot A...perticularisor ]c problime par l’omploi d’une norma spicifique, la seule relation d’ordre qu’il est raisonneble deadoptor edict qu’un vocteur est

  1. Development of Avionics Installation Interface Standards. Revision.

    Science.gov (United States)

    1981-08-01

    strawman standard. The working group noted that for microcircuit and semiconductor devices, the critical operating parameter for reliability is the...be deleted. (2) This standard, as written, defines ’part temperature" as the part surface temperatuLe. In the case of semiconductors , the junction...I> .J1 *i colo ~ 4 0 27N I i c oi i lN ..1 .. . .. "g *! CUO 4z; 0 0 U 28 -_ -- I I-- a ___ I0 FI4 __ I~] -~ L C/ 00c__ all1 *H I U fj CFI H0 29 I

  2. Avionics for Scaled Remotely Operated Vehicles Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The use of UAVs has increased exponentially since 1995, and this growth is expected to continue. Many of these applications require extensive Research and...

  3. Corrosion Control Test Method for Avionic Components

    Science.gov (United States)

    1981-09-25

    IFIED S• ’ECLASSIFICATION "’O14GRAOINU SC4 EMU LE 14 JJS’f’•UUr1N S AT& ME7N ’at .efil pot) Approved for public release; distribucion unlimited 17...Battery Output Increased Gradually as Compared to Normal Fog Effect S0 On 4,4 Took 25 min fur Battery Output to Stabilize S02 Off 2.2 1.8 ’Average...produced by carrier exposure except that there were localized areas where the normally white corrosion produces had a greenish tinge. Since these test

  4. Commercial Off-The-Shelf (COTS) Avionics Software Study

    National Research Council Canada - National Science Library

    Krodel, Jim

    2001-01-01

    .... The motivation is even a bit beyond monetary resources as the scarcity of highly trained personnel that can develop such systems has also provided fuel to the attractiveness of considering reuse...

  5. Avionics Evaluation Program: Multiple Aircraft, Multiple Sorties and Cost Accumulation

    Science.gov (United States)

    1977-01-01

    flight profile, (b) lists the hardware makeup (all aircraft are identically equipped) and (c) defines the functions and associated performance for the...given period of days. The "system" is described by the vehicle hardware makeup , flight profile, and functions/subfunctions. All aircraft must be...known, let Coss [Y] - B IAB AS-sinB (30) Yi Y2 (31) L Y3 Since fX ] = L [Y] (32) and x -3 . H (33) 54 then L - -H/y3 (34) Knowing L the X, Y ground co

  6. A Usability Survey of GPS Avionics Equipment: Some Preliminary Findings

    National Research Council Canada - National Science Library

    Joseph, Kurt

    1999-01-01

    The rapid introduction of Global Positioning System (GPS) receivers for airborne navigation has outpaced the capacity of international aviation authorities to resolve human factors issues that concern safe and efficient use of such devices...

  7. F-22 cockpit avionics: a systems integration success story

    Science.gov (United States)

    Greeley, Kevin W.; Schwartz, Richard J.

    2000-08-01

    The F-22 'Raptor' is being developed and manufactured as multi-role fighter aircraft for the 'air dominance' mission. The F-22 team is led by Lockheed Martin, with Boeing and Pratt & Whitney as partners. The F-22 weapons system combines supersonic cruise, maneuverability, stealth, and an extensive suite of tightly integrated sensors to achieve a high level of lethality and invulnerability against current and projected threat systems such as fighter aircraft and surface to air missiles. Despite high automation of the complex systems installed in the F-22, the pilot is heavily tasked for air battle management. Response timelines are compressed due to supersonic cruise velocities. These factors challenge the Pilot Vehicle Interface (PVI) design. This paper discusses the team's response to these challenges, describing the physical cockpit layout, its controls and displays, and the hardware architecture, software tools, and development process used to mature the F-22 'Raptor' weapons system, including a review of Human Factors design considerations for F-22 displays.

  8. Engineering Effects of Advanced Composite Materials on Avionics.

    Science.gov (United States)

    1981-07-01

    coatings of various kinds, or by other measures (e.g., embedded wire mesh). It is not clear at this time whether metal matrix materials will ever find...ATTN: DRDEL-IL-S 2800 Powder Mill Rd 001 Adelphi, MD 20783 EX, EW, ET, CT, COM, AV, TCS,681 Comander , CECOM TSA Fort Monmouth, NJ 07703 Change all DRDCO

  9. Communication System and Avionics for Deployable Small Free Flying Payloads

    Data.gov (United States)

    National Aeronautics and Space Administration — This IRAD will develop a core part of the communication system for the small free flying payloads.  In particular, this portion of the system will consist of the...

  10. The 727 Approach Energy Management System avionics specification (preliminary)

    Energy Technology Data Exchange (ETDEWEB)

    Jackson, D.O.; Lambregts, A.A.

    1976-08-01

    Hardware and software requirements for an Approach Energy Management System (AEMS) consisting of an airborne digital computer and cockpit displays are presented. The displays provide the pilot with a visual indication of when to manually operate the gear, flaps, and throttles during a delayed flap approach so as to reduce approach time, fuel consumption, and community noise. The AEMS is an independent system that does not interact with other navigation or control systems, and is compatible with manually flown or autopilot coupled approaches. Operational use of the AEMS requires a DME ground station colocated with the flight path reference.

  11. Avionics for Scaled Remotely Operated Vehicles, Phase II

    Data.gov (United States)

    National Aeronautics and Space Administration — The use of UAS's in the military and the commercial field has grown tremendously over the last few years and is set to explode over next several. An...

  12. Improving Training Cost Information at the Naval Avionics Center

    Science.gov (United States)

    1991-12-01

    Interviews with senior NAC managers were conducted to determine the most valuable courses. Senior managers at NAC (civil service GM 13-15) were interviewed...for the services rendered. The only additional training input to the Comptroller Department is the engineer’s weekly labor distribution card. From this...information exchange. 29 RECOMMENDED TRAINING COST ACCOUNTING SYSTEM DIVISION DTIE REPORTS MANAGERS BY INDMDUAL REPORTS BY COST CENTER SOFWARE SOFTWARE N VAX

  13. NAVIGATION AND LANDING AVIONICS INTEGRATED SYSTEM PROGRESS TREND

    Directory of Open Access Journals (Sweden)

    2016-01-01

    Full Text Available Advantages and disadvantages of various navigation methods are considered. The main advantage of an inertial method of navigation consisting in a high noise stability is given. The drawback of this navigation method consisting in accumulating mistakes by the time is given. The benefit of satellite navigation systems from the point of view of their glob- ality and high precision of measurement is proved. Disadvantages and advantages of a rho-rho navigation in comparison with satellite navigation systems are considered. The main activities of a complex using of satellite and radar navigation aids, and also satellite and inertial navigation aids are given. Various systems of complex use of a rho-rho navigation and satellite navigation systems are considered. The common important faults inherent in methods and systems according to patents are in detail considered. Methods of a complex using of inertial and satellite navigation systems in the form of iner- tial system use are given in a complex with the satellite receiver in contours of phase and frequency autocontrol of a satel- lite signal to increase accuracy and continuity of a signal from the receiver, and also in the form of a satellite method use with the differential mode to increase accuracy of an inertial method with correcting the inertial system signal are given. The analysis of various patents for complex methods of navigation is carried out.

  14. Electromagnetic Effects of (Carbon) Composite Materials Upon Avionics Systems

    Science.gov (United States)

    1980-10-01

    6taiout car6n~es at trait6oc par una peinture antiatatique A haute rfiaistiviti. Pans cette configuration, Ie niveau do perturbation 6tait tout d’abord...id.entique I celui do la partie frontalo impactfie do Ilavion ( peinture co0nductrice) ; It radame ftait traitg par un revitemont antistatique radiotrano...des peintures semi-canductrices pour la-e fengtres Alectromaon6tiquea (1 MOl < R < 10 Mnf). 16-5 Loe glaces frontales de la verrigre sont recouvertes

  15. An Avionics Touch Screen based Control Display Concept

    NARCIS (Netherlands)

    Mertens, M.; Damveld, H.J.; Borst, C.

    2012-01-01

    In many cockpits, control display units (CDUs) are vital input and information devices. In order to improve the usability of these devices, Barco, in cooperation with TU-Delft, created a touch screen control unit (TSCU), consisting of a high-quality multi-touch screen. The unit fits in the standard

  16. An Avionics Touch Screen based Control Display Concept

    OpenAIRE

    Mertens, M.; Damveld, H.J.; Borst, C.

    2012-01-01

    In many cockpits, control display units (CDUs) are vital input and information devices. In order to improve the usability of these devices, Barco, in cooperation with TU-Delft, created a touch screen control unit (TSCU), consisting of a high-quality multi-touch screen. The unit fits in the standard dimensions of a conventional CDU and is thus suitable for both retrofit and new installations. The TSCU offers two major advantages. First, the interface can be reconfigured to enable consecutive e...

  17. An avionics touch screen-based control display concept

    Science.gov (United States)

    Mertens, Michael; Damveld, Herman J.; Borst, Clark

    2012-06-01

    In many cockpits, control display units (CDUs) are vital input and information devices. In order to improve the usability of these devices, Barco, in cooperation with TU-Delft, created a touch screen control unit (TSCU), consisting of a high-quality multi-touch screen. The unit fits in the standard dimensions of a conventional CDU and is thus suitable for both retrofit and new installations. The TSCU offers two major advantages. First, the interface can be reconfigured to enable consecutive execution of several tasks on the same display area, allowing for a more efficient usage of the limited display real-estate as well as a potential reduction of cost. Secondly, advanced graphical interface design, in combination with multi-touch gestures, can improve human-machine interaction. To demonstrate the capabilities of this concept, a graphical software application was developed to perform the same operations as a conventional CDU, but now using a direct manipulation interface (DMI) of the displayed graphics. The TSCU can still be used in a legacy CDU mode, displaying a virtual keyboard operated with the touch interface. In addition, the TSCU could be used for a variety of other cockpit functions. The paper concludes with a report of pilot and non-pilot feedback.

  18. Avionics for Scaled Remotely Operated Vehicles, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — The use of UAVs has increased exponentially since 1995, and this growth is expected to continue. Many of these applications require extensive Research and...

  19. Standard Avionics Packaging, Mounting, and Cooling Baseline Study.

    Science.gov (United States)

    1980-01-31

    Modification Cost Element Full Rack / LPU Environ- Common PME Mnting ackagin i m,,ntal -o%5c r Inter faec Engineering/Design Less Less L so Same Sam,, Test and...specifications, human engineering specifications, and all the other how-to-build-it guidance normally imposed on manufacturers of militar’, e guipment. None...ARINC 600 does not address require- ments such as human factors which, when imposed by military specifications, have an adverse effect on equipment cost

  20. A Real-Time Java Virtual Machine for Avionics (Preprint)

    National Research Council Canada - National Science Library

    Armbruster, Austin; Pla, Edward; Baker, Jason; Cunei, Antonio; Flack, Chapman; Pizlo, Filip; Vitek, Jan; Proch zka, Marek; Holmes, David

    2006-01-01

    ...) in the DARPA Program Composition for Embedded System (PCES) program. Within the scope of PCES, Purdue University and the Boeing Company collaborated on the development of Ovm, an open source implementation of the RTSJ virtual machine...

  1. NextGen Avionics Roadmap Version 2.0

    Science.gov (United States)

    2011-09-30

    wheel braking to meet the target runway exit. Less energy will be dissipated by the brakes, reducing brake wear. From an operational perspective...area navigation capability to access airspace under Instrument Flight Rules (IFR) where Very High Frequency (VHF) Omnidirectional Radio...however, most helicopters lack a Weight-on- Wheels sensor. This, combined with horizontal and vertical speed capability largely independent of aircraft

  2. State of the art for digital avionics and controls, 1978

    Science.gov (United States)

    Smyth, R. K.

    1979-01-01

    A brief summary of a comprehensive state of the art survey is presented. The survey includes five broadly applicable technology areas: flight path management, aircraft control systems, crew station & human factors, integration & interfacing technology, and fundamental technology. In addition the survey included military technologies which have a technology transfer potential to the five broadly applicable technology areas.

  3. Design and Implementation of USAF Avionics Integration Support Facilities

    Science.gov (United States)

    1981-12-01

    are executive modules making decisions concerning global matters. Subordinate to the executive modules are worker mod- ules dealing with details of...all simulation/analysis displays and the values of all pertinent/ global simulation parameters on magnetic mass storage. If used with the ESS freeze...and service systems. It provides industrial engineers, buisness . analysts, and operat- ions researchers with a graphical vehicle for modeling analy

  4. Modular, Plug and Play, Distributed Avionics, Phase II

    Data.gov (United States)

    National Aeronautics and Space Administration — The objective of this SBIR effort was to prove the viability of an Ethernet version of the MicroSat Systems, Inc. (MSI) modular, plug and play (PnP) spacecraft...

  5. SWIFT-nanoLV Avionics Platform, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — With the increased demand for and utility of nano- and micro-satellites, the demand for responsive, low-cost access to space has also increased. To meet this demand,...

  6. Ethernet for Space: An Enabler for Next Generation Avionics

    Science.gov (United States)

    Pruvost, Clement; Planche, Thierry; Herpel, Hans-Juergen; Schuettauf, Andreas; Notebaert, Olivier; Rossignol, Alain

    2016-08-01

    This paper relies on work performed in the frame of the FP7 project "MISSION", the CNES study on system aspects of TTEthernet for satellites and the DLR study On-Board Computer System Architecture (OBC-SA). It does not reflect the complete outcome of these studies and goes beyond for some extent.

  7. The Design, Development and Testing of Complex Avionics Systems: Conference Proceedings Held at the Avionics Panel Symposium in Las Vegas, Nevada on 27 April-1 May 1987

    Science.gov (United States)

    1987-12-01

    these guidelines must be specific, applications, not generic " motherhood - statements. Testing also needs improvement. In accordance with MIL-STD-461...the resultant climate tends not to induce flawed theories and myths which can themselves become further obstacles to understanding and progress. The

  8. B-1B Avionics/Automatic Test Equipment: Maintenance Queueing Analysis.

    Science.gov (United States)

    1983-12-01

    8611 2930= 5 9667., 5856 .,967.,5186.,12171.,5877.,6385.,3176.,5037., 2940= 6 2203.,36000.,3(30.. ,198.,289 ..478.,282.,418..1391.,437. 2950= 7 245...170= *180= FUNCTION UF(IFN) 190= 200= COMMON/QVAR/NDE. NFTBU (50) * NREL (500) C NRELF (50). 210= 1 NREL2(50o) qNRUNNRLJNS. NTC lJ(500). FARAM( 100C.4...5.]_,1,12:!•8509., 139 1.,.,’ .. .8611 6150= 5 9667., 5856 . :967. 5186. , 12171. ,5877. 6385. .3176. 5037. 6160= 6 2203., 36000. 3030., 198

  9. Evaluation de differentes strategies de demantelement de la carcasse d'un avion

    Science.gov (United States)

    Sainte-Beuve, Damien

    At the time when sustainable development of our environment and our society become more and more considered, the issue of the end of life of aircraft arises. With the tightening of regulations and policies to reduce operating costs, aircraft are increasingly removed from service before the end of their operational life. However, the regulations do not only affect the operational life of the aircraft. In the future, there are great chances that the aircraft end of life will be also regulated as the car end of life. Nowadays some deserts serve as a tomb for airplanes skeletons, but what will happen in a few years? Recycling the skeleton is not an operation with very high added value, such as reselling used parts, however intelligent sorting and facing the market can increase the gain. At the level of the aircraft life cycle, recycling its materials reduces its overall impact, and also helps to reduce pollution and land use, even if the main impacts generated by planes are created during the use phase. Similarly, if the recyclability of the aircraft is studied at the source, that is to say in its design, this will help to reduce the use of non-recyclable materials and dangerous compound. The greatest difficulty for recycling aircraft skeletons is that different materials are mixed and attached to each other. Through a thermodynamic study we showed what concentrations of alloying elements in a molten bath could be reduced. By using the Gibbs free energy, we evaluated some of the reactions taking place in a molten bath of aluminum during the injection of oxygen, boron, and chlorine. We focused on the reactions forming dual elements compounds, such as lithium oxide or magnesium chloride. We have shown that the six elements able to react when these reactions occurs are the lithium, the magnesium, the nickel, the titanium, the vanadium and the zirconium. It is necessary to remember that the impurities for alloys used in the aerospace industry are lower and especially those of iron and silicon. The major problem of recycling of aluminum alloys is that some attachments are made from steels, and are not separated from aluminum. Iron binds too easily with aluminum and removing it is expensive and complicated. The separation of these disturbing parts can be performed before or after shredding parts. Present sorting pathways already permit at a certain scale, to make this type of sorting. Adding some type of sorting, such as the LIBS or the use of dry ice blasting can help to increase the purity of the alloys obtained. On the other hand, the number of different aircraft being relatively small, it is possible to develop specific methods to recycle specific aircraft and this according to the technologies available at the end of life of the aircraft. In this context we have studied the wing of a Canadair Regional Jet 200. After characterizing more than 80% by weight of the wing, we looked at determining areas to maximize the alloys recycled in a close loop. We developed a method to create homogenous areas with the data we collected. We have shown that the removal of certain parts, sometimes massive such as landing gear support can reduce the final impurity. In addition, the more massive they are, the more their withdrawal is interesting because while improving the quality of the whole mix, the parts removed are recoverable their self. Unfortunately, for the final work to provide a real gain it is necessary that the data is of high quality, and numerous. This rule is even truer if we apply an algorithm to create homogeneous areas. This algorithm takes into account the market demands, to create areas satisfying this demand. With three-dimensional data, the algorithm is able to take into account the actual average concentration of elements present, and all the parts left during the dismantling of the plane. Due to the complexity of assemblies, neither the post-milling nor the pre-shredding treatment is perfect. This is why it is interesting and productive to combine them. Sorting pre-shredding can save and facilitate the post-shredding.

  10. Analysis And Validation of the Field Coupled Through an Aperture in an Avionics Enclosure

    Science.gov (United States)

    Bakore, Rahul

    This work focused on accurately predicting the current response of an equipment under test (EUT) to a random electromagnetic field representing a threat source to model radio frequency directed energy weapons (RFDEWs). The modeled EUT consists of a single wire attached to the interior wall of a shielding enclosure that includes an aperture on one face. An in-house computational electromagnetic (CEM) code based on method of moments (MOM) and accelerated by the multi-level fast multipole algorithm (MLFMA), was enhanced through the implementation of first order vector basis functions that approximates the EUT surface current. The electric field integral equation (EFIE) is solved using MOM/MLFMA. Use of first-order basis functions gives a large savings in computational time over the previous implementation with zero-order Rao-Wilton-Glisson basis functions. A sample EUT was fabricated and tested within an anechoic chamber and a reverberation chamber over a wide frequency band. In the anechoic chamber measurements, the current response on the wire within the EUT due to a single uniform plane wave was found and compared with the numerical simulations. In the reverberation chamber measurements, the mean current magnitude excited on the wire within the EUT by a mechanically stirred random field was measured and compared with the numerical simulations. The measured scattering parameter between the source antenna and the EUT measurement port was used to derive the current response on the wire in both chambers. The numerically simulated currents agree very well with the measurements in both the anechoic and reverberation chambers over the measured frequency band, confirming the validity of the numerical approach for calculating EUT response due to a random field. An artificial neural network (ANN) was trained that can rapidly provide the mean induced current response of an EUT due to a random field under different aperture configurations arbitrarily placed on one face of an EUT. However, ANN proved no better than simple linear interpolation in approximating the induced currents on EUTs that give strong resonances and nulls in the response.

  11. 78 FR 54791 - Proposed Additional Airworthiness Design Standards: Advanced Avionics Under the Special Class...

    Science.gov (United States)

    2013-09-06

    ..., Kansas City, MO 64106. FOR FURTHER INFORMATION CONTACT: Mr. Doug Rudolph, Aerospace Engineer, Standards...-49, ``Electrical bonding and protection against lightning and static electricity'' 14 CFR 23.1307 at... City, MO 64106, between the hours of 7:30 a.m. and 4:00 p.m. weekdays, except Federal holidays. Issued...

  12. E VA Space Suit Power, Avionics, and Software Systems, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — NASA is interested in a reliable, robust, and low Size Weight and Power (SWAP) input device that will allow for EVA astronauts to navigate display menu systems. The...

  13. A survey on electromagnetic interferences on aircraft avionics systems and a GSM on board system overview

    Science.gov (United States)

    Vinto, Natale; Tropea, Mauro; Fazio, Peppino; Voznak, Miroslav

    2014-05-01

    Recent years have been characterized by an increase in the air traffic. More attention over micro-economic and macroeconomic indexes would be strategic to gather and enhance the safety of a flight and customer needing, for communicating by wireless handhelds on-board aircrafts. Thus, European Telecommunications Standards Institute (ETSI) proposed a GSM On Board (GSMOBA) system as a possible solution, allowing mobile terminals to communicate through GSM system on aircraft, avoiding electromagnetic interferences with radio components aboard. The main issues are directly related with interferences that could spring-out when mobile terminals attempt to connect to ground BTS, from the airplane. This kind of system is able to resolve the problem in terms of conformance of Effective Isotropic Radiated Power (EIRP) limits, defined outside the aircraft, by using an On board BTS (OBTS) and modeling the relevant key RF parameters on the air. The main purpose of this work is to illustrate the state-of-the-art of literature and previous studies about the problem, giving also a good detail of technical and normative references.

  14. Strategic avionics technology definition studies. Subtask 3-1A: Electrical Actuation (ELA) systems

    Science.gov (United States)

    Pond, Charles L.; Mcdermott, William A.; Lum, Ben T. F.

    1993-01-01

    Electrical actuator (ELA) power efficiency and requirements are examined for space system application. Requirements for Space Shuttle effector systems are presented, along with preliminary ELA trades and selection to form a preliminary ELA system baseline. Power and energy requirements for this baseline ELA system are applicable to the Space Shuttle and similar space vehicles.

  15. Development and testing of a magnetic position sensor system for automotive and avionics applications

    Science.gov (United States)

    Jacobs, Bryan C.; Nelson, Carl V.

    2001-08-01

    A magnetic sensor system has been developed to measure the 3-D location and orientation of a rigid body relative to an array of magnetic dipole transmitters. A generalized solution to the measurement problem has been formulated, allowing the transmitter and receiver parameters (position, orientation, number, etc.) to be optimized for various applications. Additionally, the method of images has been used to mitigate the impact of metallic materials in close proximity to the sensor. The resulting system allows precise tracking of high-speed motion in confined metal environments. The sensor system was recently configured and tested as an abdomen displacement sensor for an automobile crash-test dummy. The test results indicate a positional accuracy of approximately 1 mm rms during 20 m/s motions. The dynamic test results also confirmed earlier covariance model predictions, which were used to optimize the sensor geometry. A covariance analysis was performed to evaluate the applicability of this magnetic position system for tracking a pilot's head motion inside an aircraft cockpit. Realistic design parameters indicate that a robust tracking system, consisting of lightweight pickup coils mounted on a pilot's helmet, and an array of transmitter coils distributed throughout a cockpit, is feasible. Recent test and covariance results are presented.

  16. Design of bus-on-chip core for micro-satellite avionics

    Science.gov (United States)

    Liu, Youjun; You, Zheng; Li, Bin; Zhang, Xiangqi; Meng, Ziyang

    2007-11-01

    This paper discusses a layout of bus-on-chip core referring to SoC thinking which is composed of six sections based on a physical chip of FPGA: multi-Processor cache coherence unit, external bus control module, TT&C module, Ethernet Mac interface, EDAC/DMA module, and AMBA bridges. Multi-processor cache coherence unit, as a key part of the bus core, is used to serve the rapid parallel computing by means of the breakthrough of write/read speed of EMS memory and enhances the reliability of OBC with the service of supporting the hot standby of redundancy and the reconfiguration of fault-tolerance. External bus control module is made to support the PnP of external components applying varieties of buses, which is designed by means of soft-core in order to adapt the variation of macro-design and improve the flexibility of external application. TT&C module is the interface of subsystems of telemetry, telecommand and communication, which involves the protocols of HDLC. Ethernet Mac interface based on TCP/IP acts as the access of ISL for formation flying, constellation, etc. EDAC/DMA module mainly manages the data exchange between AMBA bus and RAM, and assigns DMA for the payloads.

  17. Etude des defauts apparaissant dans les amenagements interieurs des avions d'affaires

    Science.gov (United States)

    Charette, Emilie

    The evolution of the aeronautic industry led to the development of new materials for these high performance applications. Among other examples, composite sandwich structures are increasingly used for interior body panels of business airplanes. These structures are assembled and fixed to the fuselage using metallic inserts bonded inside the sandwich panels with an epoxy resin adhesive. A thin film of wood veneer covers the visible side of interior furniture in order to bring sophistication and esthetic to the interior design. However, due to multiple factors, surface defects frequently appear on the veneered side of the panel where inserts are located. Moreover the defects tend to appear months after the airplane delivery causing costly reparations. The sources of defects can be mechanical ( deformation due to an excessive tightening), chemical (shrinkage of the epoxy adhesive) or the result of hygrothermal exposition. It is therefore important to understand the source of such surface defects and ultimately prevent or control their appearance. The present thesis deals with defects from chemical and hygrothermal sources appearing on the composite panels used on the interior body of business jets after aging. The main objective was to identify and quantify phenomena causing the defects on the interior panels of business planes. This research project is the first part of a project sponsored by CRIAQ and NSERC. The interaction of several materials can lead to various phenomena causing the apparition of surface defects. The project was thus divided into three parts in order to study an increasingly complex problem. the first study deals with the characterization of the different constitutive materials taken separately. This first part focused on thermal, rheological and mechanical aspects of epoxy adhesives. It was shown that the two adhesives used have different mechanical properties and cure kinetic reactions. In addition, the mechanical properties of sandwich composites panels were studied. The second study focused on the analysis of hygrothermal influence on the adhesive and the composite sandwich panels taken separately. Humidity and temperature can have an important effect on the constitutive materials, it is therefore important to know their influence. Finally, the third part deals with the influence of hygrothermal aging on a structure combining all the different materials. Sample panels including fixing zones (insert and resin) were made at the industrial partner's facility according to the industrial procedure. Subsequently, the samples have undergone an accelerated aging. By using deflectometry system, changes in local curvatures with respect to the aging conditions were observed. A correlation between the material characterization results, the aging effects and the surface defect gravity was performed to evaluate the sources and the occurrence of defects. Recommendations have also been made to ensure the project continuity. This project, carried out in an industrial context with the collaboration of Centre de Recherche Industrielle du Quebec ( CRIQ), 3M Canada and the Chaire de recherche sur les composites hautes performances (CCHP) of the department of mechanical engineering of Ecole Polytechnique de Montreal, highlights the importance of the choice of methods and materials in the manufacturing of composite structures.

  18. Modeling and Simulation of Avionics Systems and Command, Control and Communications Systems

    Science.gov (United States)

    1980-01-01

    BVL qui eat indipandant do l’application au nivoati du code. 11 slagit des programas sulvants geation dos interruptions t ceam modules ant pour...Is the performance of the "Direct Subsystem (DSS)," e.g., SIP (MK X. XXI ) Input to the teetbed? If yes, is this data obtained from reliable sources or

  19. Software-Defined Avionics and Mission Systems in Future Vertical Lift Aircraft

    Science.gov (United States)

    2015-03-01

    with swelling unit acquisition-costs ( Dryden , Britt, & Binnings-Depriester, 1981), and support/ maintenance challenges (USAF Science and Advisory Board...first described in 1984 by noted computer scientist John Rushby (Parkinson & Baker, 2011). A MILS-type architecture is based on two high-credibility...A-4M [1] 10,800 840 7.8% 420 4.0% 10,380 3.9% SH-608 13648* 1,997* 14.6% 996 7.9% 12,652 7.3% [2][3] 1 Dryden , Britt, & Binnings-Depriester

  20. Avionics Aerospace Ground Equipment (AGE) Career Ladder, AFSC 326X0C/D.

    Science.gov (United States)

    1982-02-01

    IIEMD 1 1 lh 1 HQ USAF/ MPPT 11 AFHRL/LRT 1 1 m LTTC 5 2 2h 9 ARMY OCCUPATIONAL SURVEY BRANCHI I CCAF/AYX1 1 3507/DPUI1 1 AFMPC/NPCHS1 1 HQ AFISC/DAP1...troubleshoot AN/APM-307 interceptor control system test sets make entries on PlE Certification Label (AFTO Form 108) remove or replace resistors Personnel...SHOP EQUIPMENT 77 L467 REMOVE OR REPLACE METERS 77 L424 CALIBRATE TORQUE TENSIONETERS 75 J276 TROUBLESHOOT AN/APM-307 INTERCEPTOR CONTROL SYSTEM TEST

  1. Enhancing Autonomy of Aerial Systems Via Integration of Visual Sensors into Their Avionics Suite

    Science.gov (United States)

    2016-09-01

    boundary encompasses natural obstacles, ambient environmental factors such as temperature and wind speed, and the operating environment of the...The wind condition of the POE ranges from 0–27 knots. As Singapore may experience the occasional “Sumatra Squalls,” the upper limit of the wind ...Aircraft are Now Drones .” Popular Science, January 10. http://www.popsci.com/technology/article/2012-01/ drones - now-account-nearly-one-third-militarys

  2. Rugged and compact mid-infrared solid-state laser for avionics applications

    CSIR Research Space (South Africa)

    Esser, MJD

    2009-11-01

    Full Text Available In order to demonstrate the feasibility of a helicopter-based application using advanced laser technology, the authors have developed a rugged and compact mid-infrared solid-state laser. The requirement for the laser was to simultaneously emit at 2...

  3. A Profile of Scientist and Engineer Training Conducted by the Naval Avionics Center

    Science.gov (United States)

    1991-12-01

    AD-A245 925II hiIIi111 llI l ill! 1iJ! i liII NAVAL POSTGRADUATE SCHOOL Monterey, California DTIC S1; tD S iECTE S FEB 141992 ! D THESIS A PROFILE OF...7 GS-9 GS11 GS12 GM13 SING MA;R < IYR -1 5 6-10 11-15 16-20 >20 MEAN RESPONSES BY MAJOR GROUP Figure 29 060 Figure 30 shows the average response for

  4. Integrated Avionics Electronic Warfare Equipment and Component Specialty, AFS 326X3A/B

    Science.gov (United States)

    1981-12-01

    INFORMATION CENTER X AFHRL/MODS X X AFtIEA/MEMD x HQ USAF/ MPPT X X AFHRL/LRT X LTTC (TECHNICAL TRAINING CENTER, CHECK PTT FOR ADDRESS) X X EXTENSION...a useable form involves the use of gases at very low temperatures (cryogenics). The job of these personnel, therefore, includes both electronic...voltage test probes, pressure regulators, frequency dip meters, high voltage toroids, pressure/ temperature test sets, and strobescopes are used almost

  5. Avionic Inertial and Radar Navigation Systems Career Ladder AFSC 328X4.

    Science.gov (United States)

    1984-06-01

    DPAT 3 3 HQ SAC/DPATC (ATCLO) 1 1 HQ TAC/DPAT 3 3 HQ TAC/DPIATC I 1 HQ USAF/LEYM 1 1 HQ USAF/ MPPT 1 1 HQ USAFE/DPAT 3 3 HQ USAFE/DPATC I I HQ USMC (CODE...inspect computer maintenance panels (NSA-14V2) inspect system temperature and voltage monitor (NSA-14V2) 17 4 . q~;&U~~A:d:’::zc - .. ~ ~*~’’~%. *O 5 IV...OR REPLACE INU 96 W670 INSPECT SYSTEM TEMPERATURE AND VOLTAGE MONITOR (NSA-14V2) 96 J291 ISOLATE MALFUNCTIONS TO CHRONOMETERS 96 H232 REMOVE OR REPLACE

  6. Acquisition Management: Source Selection Procedures for the C-5 Avionics Modernization Program

    National Research Council Canada - National Science Library

    Granetto, Paul J; Neville, Douglas P; Mathews, Amy L; Thompson, Lashonda M; Burger, Michael T; Anderson, Lamar; Hepler, Michael T; Borrero, Karen M; Hart, Erin S

    2006-01-01

    ... (Acquisition, Technology, and Logistics) commissioned a study to review acquisition-related actions taken by the former Principal Deputy Assistant Secretary of the Air Force for Acquisition and Management (Principal Deputy...

  7. Ionizing Radiation Environment on the International Space Station: Performance vs. Expectations for Avionics and Material

    Science.gov (United States)

    Koontz, Steven L.; Boeder, Paul A.; Pankop, Courtney; Reddell, Brandon

    2005-01-01

    The role of structural shielding mass in the design, verification, and in-flight performance of International Space Station (ISS), in both the natural and induced orbital ionizing radiation (IR) environments, is reported. Detailed consideration of the effects of both the natural and induced ionizing radiation environment during ISS design, development, and flight operations has produced a safe, efficient manned space platform that is largely immune to deleterious effects of the LEO ionizing radiation environment. The assumption of a small shielding mass for purposes of design and verification has been shown to be a valid worst-case approximation approach to design for reliability, though predicted dependences of single event effect (SEE) effects on latitude, longitude, SEP events, and spacecraft structural shielding mass are not observed. The Figure of Merit (FOM) method over predicts the rate for median shielding masses of about 10g/cm(exp 2) by only a factor of 3, while the Scott Effective Flux Approach (SEFA) method overestimated by about one order of magnitude as expected. The Integral Rectangular Parallelepiped (IRPP), SEFA, and FOM methods for estimating on-orbit (Single Event Upsets) SEU rates all utilize some version of the CREME-96 treatment of energetic particle interaction with structural shielding, which has been shown to underestimate the production of secondary particles in heavily shielded manned spacecraft. The need for more work directed to development of a practical understanding of secondary particle production in massive structural shielding for SEE design and verification is indicated. In contrast, total dose estimates using CAD based shielding mass distributions functions and the Shieldose Code provided a reasonable accurate estimate of accumulated dose in Grays internal to the ISS pressurized elements, albeit as a result of using worst-on-worst case assumptions (500 km altitude x 2) that compensate for ignoring both GCR and secondary particle production in massive structural shielding.

  8. The Ionizing Radiation Environment on the International Space Station: Performance vs. Expectations for Avionics and Materials

    Science.gov (United States)

    Koontz, Steven L.; Boeder, Paul A.; Pankop, Courtney; Reddell, Brandon

    2005-01-01

    The role of structural shielding mass in the design, verification, and in-flight performance of International Space Station (ISS), in both the natural and induced orbital ionizing radiation (IR) environments, is reported.

  9. Modelisation geometrique par NURBS pour le design aerodynamique des ailes d'avion

    Science.gov (United States)

    Bentamy, Anas

    The constant evolution of the computer science gives rise to many research areas especially in computer aided design. This study is part, of the advancement of the numerical methods in engineering computer aided design, specifically in aerospace science. The geometric modeling based on NURBS has been applied successfully to generate a parametric wing surface for aerodynamic design while satisfying manufacturing constraints. The goal of providing a smooth geometry described with few parameters has been achieved. In that case, a wing design including ruled surfaces at the leading edge slat and at the flap, and, curved central surfaces with intrinsic geometric property coming from conic curves, necessitates 130 control points and 15 geometric design variables. The 3D character of the wing need to be analyzed by techniques of investigation of surfaces in order to judge conveniently the visual aspect and detect any sign inversion in both directions of parametrization u and nu. Color mapping of the Gaussian curvature appears to be a very effective tools in visualization. The automation of the construction has been attained using an heuristic optimization algorithm, simulated annealing. The relative high speed of convergence to the solutions confirms its practical interest in engineering problems nowadays. The robustness of the geometric model has been tested successfully with an academic inverse design problem. The results obtained allow to foresee multiple possible applications from an extension to a complete geometric description of an airplane to the interaction with others disciplines belonging to a preliminary aeronautical design process.

  10. Analyse et design aerodynamique haute-fidelite de l'integration moteur sur un avion BWB

    Science.gov (United States)

    Mirzaei Amirabad, Mojtaba

    BWB (Blended Wing Body) is an innovative type of aircraft based on the flying wing concept. In this configuration, the wing and the fuselage are blended together smoothly. BWB offers economical and environmental advantages by reducing fuel consumption through improving aerodynamic performance. In this project, the goal is to improve the aerodynamic performance by optimizing the main body of BWB that comes from conceptual design. The high fidelity methods applied in this project have been less frequently addressed in the literature. This research develops an automatic optimization procedure in order to reduce the drag force on the main body. The optimization is carried out in two main stages: before and after engine installation. Our objective is to minimize the drag by taking into account several constraints in high fidelity optimization. The commercial software, Isight is chosen as an optimizer in which MATLAB software is called to start the optimization process. Geometry is generated using ANSYS-DesignModeler, unstructured mesh is created by ANSYS-Mesh and CFD calculations are done with the help of ANSYS-Fluent. All of these software are coupled together in ANSYS-Workbench environment which is called by MATLAB. The high fidelity methods are used during optimization by solving Navier-Stokes equations. For verifying the results, a finer structured mesh is created by ICEM software to be used in each stage of optimization. The first stage includes a 3D optimization on the surface of the main body, before adding the engine. The optimized case is then used as an input for the second stage in which the nacelle is added. It could be concluded that this study leads us to obtain appropriate reduction in drag coefficient for BWB without nacelle. In the second stage (adding the nacelle) a drag minimization is also achieved by performing a local optimization. Furthermore, the flow separation, created in the main body-nacelle zone, is reduced.

  11. Amelioration de l'aerodynamisme des ailes d'avion par actionnement plasma

    Science.gov (United States)

    Demers, Francis

    The paper will present experimental and numerical investigation of improved aerodynamics performance of a 2D extruded airfoil by plasma actuation. The aim of the research is to develop three promising flow control concepts using solid-state electro-fluidic (plasma) actuators to achieve reduced drag as well as lift control at take-off/landing. Aerodynamic plasma actuators are solid-state devices that convert electricity directly into flow acceleration through partial air ionization. The most common plasma actuator, the dielectric barrier discharge (DBD) actuator, essentially consists of two offset electrodes separated by a dielectric across which a high-voltage low-amperage AC input is applied. The ions in the air created by the high electric field between the two electrodes are accelerated by this field and transfer their momentum to the inert air particles through collisions, resulting in an acceleration of a very thin layer of air adjacent to the surface. This thin, simple, high bandwidth actuator is easy to integrate and thus offer the most practical yet solution for widespread use of flow control to revolutionize aircraft aerodynamics. The three flow control concepts studied involve placing the actuator on the suction surface of a wing to delay boundary layer transition and thus reduced viscous drag and to control boundary layer separation to control lift at take-off and landing without the need for slats, flaps and spoilers. While these concepts had been previously explored, they were only tested empirically at small-scale and very low-speed due to limitations in plasma actuator strength. The current research aimed to test these concepts at higher speeds (up to 30 m/s) using more recent DBD actuators with higher actuator strength and perform more detailed measurements so that these data can be used to validate CFD codes that can be used for assessing the concept at realistic aircraft scales and flight conditions. Wind tunnel experiments were carried out on a 11.67 inch-chord Aerospatiale-A airfoil with a DBD actuator placed on the suction side at a 15, 20 and 30 m/s incoming flow velocity for a Reynolds number of 2,8 x 10 5, 3,8 x 105 and 5,7 x 105, respectively, and an angle of attack (AOA) of 3º for concept one and 13.3° for concept two and three. The experiments were performed in a closed-loop wind tunnel with a square 24 inch x 24 inch test section. The 2D extruded wing was mounted vertically wall to wall at one chord downstream the entrance of the 96 inch long test section. Lift was calculated by pressure integration from 48 static pressure holes placed on the wing surface. Drag was obtained by wake survey with two Pitot-static tubes mounted on 2-D traverse systems placed half a chord upstream and one chord downstream of the wing. All the pressures were acquired simultaneously by four 16-channel piezo electric pressure scanners. The pressure side of the wing is made of aluminium while the suction side consist of 5 mm thick photopolymer panels made by stereolithography. The photopolymer panels also served as the dielectric material for the plasma actuator making the actuator non-intrusive to the flow. Prior 2-D simulations using the commercial RANS CFD code FLUENT solver had been carried out to design the test wing and determine the best placement of the DBD actuator. The plasma actuator was modeled as a time-averaged spatial body force distribution obtained from the DBD actuator model of Lemire and Vo (2011) and implemented in the CFD solver as a source term in the momentum equations. From the results of these simulations the DBD actuator was placed on the test wing at 26 % chord for concept 1, which is inside the laminar separation bubble responsible for bypass transition of the test wing at 3° AOA at nominal upstream flow velocity of 30 m/s without actuation. For the second and third concept, the optimum locations was found to be at 65 % and 54 % chord, which is near the separation of the boundary layer of the wing located at 70 % at 13.3° AOA at nominal upstream flow velocity of 30 m/s without plasma. The characterization of the DBD actuator was performed by thrust measurements on a flat plate with a high precision scale. From these characterization measurements, the plasma actuator used in the experiments were operated with the two electrodes under tension at a frequency of 2.5 kHz, peak-to-peak voltage of 35 kV and a positive ramp saw-tooth shaped signal providing an actuator strength of 100 mN/m. The surface pressure distributions and the measurements in the wake without and with plasma actuation indicate that plasma actuation successfully delays bypass boundary layer transition by changing the location and length of the laminar separation bubble at 3° of AOA. Furthermore, Enhancement of the aerodynamics properties by delaying the separation point of the boundary layer was obtained numerically and experimentally at AOA of 13.3° by plasma actuation. Deterioration of the aerodynamics properties was achieved by using a plasma actuator acting against the flow near the nominal separation point of the boundary layer but only for the upcoming flow velocity of 15 and 20 m/s. Overall, the wind tunnel experiments confirm the effectiveness of the three concepts of delaying bypass transition and separation controle with suction side plasma actuation and the trends predicred in term of decreasing actuation effectiveness versus flow velocity and Reynolds number. However, the results also show that the CFD simulations tend to over predict this effectiveness for all cases.

  12. Contributions au probleme d'affectation des types d'avion

    Science.gov (United States)

    Belanger, Nicolas

    In this thesis, we approach the problem of assigning aircraft types to flights (what is called aircraft fleet assignment) in a strategic planning context. The literature mentions many studies considering this problem on a daily flight schedule basis, but the proposed models do no allow to consider many elements that are either necessary to assure the practical feasibility of the solutions, or relevant to get more beneficial solutions. After describing the practical context of the problem (Chapter 1) and presenting the literature on the subject (Chapter 2), we propose new models and solution approaches to improve the quality of' the solutions obtained. The general scheme of the thesis is presented in Chapter 3. We summarize here the models and solution approaches that we propose; and present the main elements of our conclusions. First, in Chapter 4, we consider the problem of aircraft fleet Assignment over a weekly flight schedule, integrating into the objective an homogeneity factor for driving the choice of the aircraft types for the flights with the same flight number over the week. We present an integer linear model based on a time-space multicommodity network. This model includes, among others, decision variables relative to the aircraft type assigned to each flight and to the dominant aircraft type assigned to each flight number. We present in Chapter 5 the results of a research project made in collaboration with Air Canada within a consulting contract. The project aimed at analyzing the relevance for the planners of using an optimization software to help them to first identify non profitable flight legs in the network, and second to efficiently establish the aircraft fleet assignment. In this chapter, we propose an iterative approach to take into account the fact that the passenger demand is not known on a leg basis, but rather on an origin-destination and departure time basis. Finally, in Chapter 6, we propose a model and a solution approach that aim at solving the fleet assignment problem over a periodic schedule in the case where there is a flexibility on the flight departure times and the fleet size must be minimized. Moreover, the objective of this model includes the impact on the passenger demand for each flight of the variation of the flight departure times and the closing of the departure times of consecutive flights connecting the same pairs of stations. (Abstract shortened by UMI.)

  13. Calcul des coefficients aerodynamiques d'un avion complet par la methode rans

    Science.gov (United States)

    Lux, Quentin

    The evaluation of stability derivatives within the entire flight domain through the use of Computational Fluids Dynamics is one of the next challenges of numerical external aerodynamics. To remain competitive, aircraft manufacturers are increasingly turning to CFD to provide aerodynamic data in an effort to increase the quality of their products while reducing the development turnaround time and costs. However, the numerical analysis need to evolve to insure a higher fidelity and meets the need of the aircraft manufacturers and decrease wind-tunnel experiments. The present study aims to estimate the potential of a high-fidelity 3D CFD analysis in the determination of the aerodynamic behavior of an airplane in incidence and yaw. The complete methodology to obtain the static stability coefficients will be developed and the results compared with the experimental data. All the phases of the methodology will be presented including: the treatment of the geometry, the meshing process and the flow solving by a commercial CFD software. Important points to obtain a high-fidelity will also be developed as well as the verification and validation phase. The results will be presented as raw as well as with an error metric in order to estimate the accuracy of the current method. First, it will be applied on a validation case from the literature: the Drag Prediction Workshop II with the study of the DLR-F6. The test cases including a study at fixed CL as well as an incidence sweeping will be recreated. Then, the methodology will be applied to a Bombardier Research Aircraft. The various associations of components on the fuselage including the wing, the nacelle and the tail will be studied in incidence and yaw sweepings. The study concludes on the potential of such study with regard to its development costs in the cases presented here.

  14. Design conceptuel d'un avion blended wing body de 200 passagers

    Science.gov (United States)

    Ammar, Sami

    The Blended Wing Body is built based on the flying wing concept and performance improvements compared to conventional aircraft. Contrariwise, most studies have focused on large aircraft and it is not sure whether the gains are the same for smaller aircraft. The main of objective is to perform the conceptual design of a BWB of 200 passengers and compare the performance obtained with a conventional aircraft equivalent in terms of payload and range. The design of the Blended Wing Body was carried out under the CEASIOM environment. This platform design suitable for conventional aircraft design has been modified and additional tools have been integrated in order to achieve the aerodynamic analysis, performance and stability of the aircraft fuselage built. A plane model is obtained in the geometric module AcBuilder CEASIOM from the design variables of a wing. Estimates of mass are made from semi- empirical formulas adapted to the geometry of the BWB and calculations centering and inertia are possible through BWB model developed in CATIA. Low fidelity methods, such as TORNADO and semi- empirical formulas are used to analyze the aerodynamic performance and stability of the aircraft. The aerodynamic results are validated using a high-fidelity analysis using FLUENT CFD software. An optimization process is implemented in order to obtain improved while maintaining a feasible design performance. It is an optimization of the plan form of the aircraft fuselage integrated with a number of passengers and equivalent to that of a A320.Les performance wing aircraft merged optimized maximum range are compared to A320 also optimized. Significant gains were observed. An analysis of the dynamics of longitudinal and lateral flight is carried out on the aircraft optimized BWB finesse and mass. This study identified the stable and unstable modes of the aircraft. Thus, this analysis has highlighted the stability problems associated with the oscillation of incidence and the Dutch roll for the absence of stabilizers.

  15. Etude de la stabilite d'un avion BWB (Blended Wing Body) de 200 passagers

    Science.gov (United States)

    Legros, Clement

    The Blended Wing Body (BWB) is a type of innovative aircraft, based on the flying wing concept. This new type of airplane shows several advantages compared to the conventional airplanes : economy of fuel, reduction of the weight of the structure, reduction of the noise and less impact on the environment, increased payload capacity. However, this kind of aircraft has a lack of stability due to the absence of vertical tail. Several studies of stability were already realized on reduced size models of BWB, but there is no study on a 200 passengers BWB. That's why, the main objective of this present study is to integrate the engines and theirs pylons into the existing conceptual design of the BWB to analyze of their impact on its static and dynamic stability over the flight envelope. The conception of the BWB was realized with the platform of design CEASIOM. The airplane, the engines and theirs pylons were obtained in the geometrical module AcBuilder of CEASIOM. The various aerodynamic coefficients are calculated thanks to Tornado program. These coefficients allow realizing the calculations of stability, in particular with the longitudinal and lateral matrices of stability. Afterward, the BWB flight envelope is created based on aeronautical data of a similar airplane, the Airbus A320. From this flight envelope, we get back several thousand possible points of flight. The last step is to check the static and dynamic stability, using the longitudinal and lateral matrices of stability and the Flying Qualities Requirements, for every point of flight. To validate our study of stability, the already existing studies of stability of the Boeing 747 will be used and compared with our model.

  16. Controle du vol longitudinal d'un avion civil avec satisfaction de qualiies de manoeuvrabilite

    Science.gov (United States)

    Saussie, David Alexandre

    2010-03-01

    Fulfilling handling qualities still remains a challenging problem during flight control design. These criteria of different nature are derived from a wide experience based upon flight tests and data analysis, and they have to be considered if one expects a good behaviour of the aircraft. The goal of this thesis is to develop synthesis methods able to satisfy these criteria with fixed classical architectures imposed by the manufacturer or with a new flight control architecture. This is applied to the longitudinal flight model of a Bombardier Inc. business jet aircraft, namely the Challenger 604. A first step of our work consists in compiling the most commonly used handling qualities in order to compare them. A special attention is devoted to the dropback criterion for which theoretical analysis leads us to establish a practical formulation for synthesis purpose. Moreover, the comparison of the criteria through a reference model highlighted dominant criteria that, once satisfied, ensure that other ones are satisfied too. Consequently, we are able to consider the fulfillment of these criteria in the fixed control architecture framework. Guardian maps (Saydy et al., 1990) are then considered to handle the problem. Initially for robustness study, they are integrated in various algorithms for controller synthesis. Incidently, this fixed architecture problem is similar to the static output feedback stabilization problem and reduced-order controller synthesis. Algorithms performing stabilization and pole assignment in a specific region of the complex plane are then proposed. Afterwards, they are extended to handle the gain-scheduling problem. The controller is then scheduled through the entire flight envelope with respect to scheduling parameters. Thereafter, the fixed architecture is put aside while only conserving the same output signals. The main idea is to use Hinfinity synthesis to obtain an initial controller satisfying handling qualities thanks to reference model pairing and robust versus mass and center of gravity variations. Using robust modal control (Magni, 2002), we are able to reduce substantially the controller order and to structure it in order to come close to a classical architecture. An auto-scheduling method finally allows us to schedule the controller with respect to scheduling parameters. Two different paths are used to solve the same problem; each one exhibits its own advantages and disadvantages.

  17. Avionics and Power Management for Low-Cost High-Altitude Balloon Science Platforms

    Science.gov (United States)

    Chin, Jeffrey; Roberts, Anthony; McNatt, Jeremiah

    2016-01-01

    High-altitude balloons (HABs) have become popular as educational and scientific platforms for planetary research. This document outlines key components for missions where low cost and rapid development are desired. As an alternative to ground-based vacuum and thermal testing, these systems can be flight tested at comparable costs. Communication, solar, space, and atmospheric sensing experiments often require environments where ground level testing can be challenging or impossible in certain cases. When performing HAB research the ability to monitor the status of the platform and gather data is key for both scientific and recoverability aspects of the mission. A few turnkey platform solutions are outlined that leverage rapidly evolving open-source engineering ecosystems. Rather than building custom components from scratch, these recommendations attempt to maximize simplicity and cost of HAB platforms to make launches more accessible to everyone.

  18. Ultra-Low Power Extreme Environment Capable Avionics System-on-a-Chip

    Data.gov (United States)

    National Aeronautics and Space Administration — Develop ultra-low-power, wide-temperature (-150° C to +250 ° C), digital System-on-a-Chip (SOC) ASIC technology in a high resolution, inherently rad-hard IBM...

  19. Development of a Comprehensive Digital Avionics Curriculum for the Aeronautical Engineer

    Science.gov (United States)

    2006-03-01

    methods - PWM , delta , hysteresis current control. Rectifiers, inverters, choppers. ECSE 573 MICROWAVE ELECTRONICS-Physical basis of modern microwave... Dirac delta function • Concepts of convolution and correlation • LTI systems, impulse response and transfer function • Filters, frequency response...digital signaling techniques including PCM, DPCM, PAM, PDM, PPM, and DELTA modulation; fundamentals of random signal theory and its application to

  20. Validation of Digital Systems in Avionics and Flight Control Applications Handbook. Volume 1.

    Science.gov (United States)

    1983-07-01

    measures, secondary task measures, spare mental capacity, and subjective opinion; (b) Physiological measures such as electrocardiogram (ECG) or heart...ELEVEN RECOMMENDED CONFIGURATION MANAGEMENT PROCEDURES ’.4 5- III C); -I. z m 4 IcU . -- 4 -4 -4..... -d -J 5- .4 9- J. 9, i 1 -.4 9 4 . . a-. ~ V S p

  1. Digital Avionics Information System (DAIS). Volume I. Impact of DAIS Concept on Life Cycle Cost.

    Science.gov (United States)

    1981-03-01

    vance eeoietPorm 12, KEY WORDS (Continue on1 roet aide it nec..ey and Identify by block number) Digital Avioie csII InfoitWi2IiIIII i ilha illl 121t-Ila1...nonrMaintenani-e 5l pport personnel (ind their ipporf tacilit ies (stich (is barracks, heat . ir l( tood). ilthoi Ih thev ( (n e p 1it ts ,o singje term. t). All

  2. Nonmilitary Specification Procurements in Department of Defense Aviation Avionics Acquisition Programs

    National Research Council Canada - National Science Library

    Wood, Bradley

    1997-01-01

    ...: specifications, logistics, and management training. Research also supports the conclusion that while FASA may eliminate some logistics barriers, it will not likely effect barriers related to specifications, or management, and training.

  3. State of the art survey of technologies applicable to NASA's aeronautics, avionics and controls program

    Science.gov (United States)

    Smyth, R. K. (Editor)

    1979-01-01

    The state of the art survey (SOAS) covers six technology areas including flightpath management, aircraft control system, crew station technology, interface & integration technology, military technology, and fundamental technology. The SOAS included contributions from over 70 individuals in industry, government, and the universities.

  4. Adaptable and Reconfigurable Modular Systems (GSFC) - Plug and Play, Distributed Avionics, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — In order to execute the President's Vision for Space Exploration, NASA must find ways to reduce spacecraft cost, complexity, and integration and test time while...

  5. Intelligent, reusable software for plug and play space avionics, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — Space Micro proposes to build upon our existing space processing and hardening technologies and products e.g (Proton 200K), to research and develop reusable software...

  6. A Human Factors Evaluation of the Space Shuttle Cockpit Avionics Upgrade

    Science.gov (United States)

    2012-09-01

    Table 3.  Principles Based on Attention (From Wickens et al., 2004) .................. 18  Table 4.  Memory Principles (From Wickens et al., 2004...Display HTA Hierarchical Task Analysis IDP Integrated Display Processor LCD Liquid Crystal Display MCC Mission Control Center MDU Multifunction...employed in this evaluation. The first is hierarchical task analysis ( HTA ), which is a method used to define an activity by breaking it down into its

  7. 3D Navigation and Integrated Hazard Display in Advanced Avionics: Workload, Performance, and Situation Awareness

    Science.gov (United States)

    Wickens, Christopher D.; Alexander, Amy L.

    2004-01-01

    We examined the ability for pilots to estimate traffic location in an Integrated Hazard Display, and how such estimations should be measured. Twelve pilots viewed static images of traffic scenarios and then estimated the outside world locations of queried traffic represented in one of three display types (2D coplanar, 3D exocentric, and split-screen) and in one of four conditions (display present/blank crossed with outside world present/blank). Overall, the 2D coplanar display best supported both vertical (compared to 3D) and lateral (compared to split-screen) traffic position estimation performance. Costs of the 3D display were associated with perceptual ambiguity. Costs of the split screen display were inferred to result from inappropriate attention allocation. Furthermore, although pilots were faster in estimating traffic locations when relying on memory, accuracy was greatest when the display was available.

  8. The U.S. Army's Common Avionics Architecture System (CAAS) Product Line: A Case Study

    National Research Council Canada - National Science Library

    Clemente, Paul; Bergey, John

    2005-01-01

    This report is one in a series of Carnegie Mellon Software Engineering Institute case studies of organizations that have adopted a software product line approach for developing a family of software-intensive systems. The U.S...

  9. Human Consequences of Agile Aircraft (Facteurs humains lies au pilotage des avions de combat tres manoeuvrants)

    Science.gov (United States)

    2001-05-01

    Ecologia . - 1995. No 5. - P. 2-7. 20. Palets B.L., Tikhonov M.A., Popov A.A., Arkhangelsky D.Yu., Palets L.D., Bondarenko R.A. Theoretical Analysis of... Ecologia . - 1995. - No 3. - P. 30-34. 46. Chernyakov I.N., Shishov A.A. Maintenance of Vitality and Performance in Pilots by Means of Oxygen Complex in...Emergency Depressurization of the Cabin // Meditsina Truda i Promyshlennaya Ecologia . - 1995. - No 3. - P. 30- 34. 47. Chernyakov I.N., Shishov A.A

  10. 78 FR 70892 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes

    Science.gov (United States)

    2013-11-27

    ... 91342; telephone 818-362-6711; fax 818-362-0603; Internet http://corporateportal.ppg.com/na/aerospace...-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations....easa.europa.eu/blob/easa_ad_2009_0159E_superseded.pdf/EAD_2009-0159-E_1 )] [which corresponds to FAA AD...

  11. Development of advanced avionics systems applicable to terminal-configured vehicles

    Science.gov (United States)

    Heimbold, R. L.; Lee, H. P.; Leffler, M. F.

    1980-01-01

    A technique to add the time constraint to the automatic descent feature of the existing L-1011 aircraft Flight Management System (FMS) was developed. Software modifications were incorporated in the FMS computer program and the results checked by lab simulation and on a series of eleven test flights. An arrival time dispersion (2 sigma) of 19 seconds was achieved. The 4 D descent technique can be integrated with the time-based metering method of air traffic control. Substantial reductions in delays at today's busy airports should result.

  12. Advanced Spacesuit Informatics Software Design for Power, Avionics and Software Version 2.0

    Science.gov (United States)

    Wright, Theodore W.

    2016-01-01

    A description of the software design for the 2016 edition of the Informatics computer assembly of the NASAs Advanced Extravehicular Mobility Unit (AEMU), also called the Advanced Spacesuit. The Informatics system is an optional part of the spacesuit assembly. It adds a graphical interface for displaying suit status, timelines, procedures, and warning information. It also provides an interface to the suit mounted camera for recording still images, video, and audio field notes.

  13. Definition, analysis and development of an optical data distribution network for integrated avionics and control systems

    Science.gov (United States)

    Burns, R. R.

    1981-01-01

    The potential and functional requirements of fiber optic bus designs for next generation aircraft are assessed. State-of-the-art component evaluations and projections were used in the system study. Complex networks were decomposed into dedicated structures, star buses, and serial buses for detailed analysis. Comparisons of dedicated links, star buses, and serial buses with and without full duplex operation and with considerations for terminal to terminal communication requirements were obtained. This baseline was then used to consider potential extensions of busing methods to include wavelength multiplexing and optical switches. Example buses were illustrated for various areas of the aircraft as potential starting points for more detail analysis as the platform becomes definitized.

  14. Advanced Concepts for Avionics/Weapon System Design, Development and Integration: Conference Proceedings of the Avionics Panel Symposium (45th) Held at Ottawa, Canada on 18-22 April 1983.

    Science.gov (United States)

    1983-10-01

    et volumes dans les technologies actuelles sont trop impoi .. ants . 4.4 - Alimentations Les alimentations doivent 6tre distributes vers chacun des... experiments on the human factors aspects of the display system for a television guided lock-on missile for use against ground targets, such as will be...development cycle. Methods of producing functional designs were illuminated and experience to date with the approach summarized. Paper number six was

  15. A Survey of Serious Aircraft Accidents Involving Fatigue Fracture. Volume 1. Fixed-Wing Aircraft (Etude sur des Accidents Importants d’Avions du aux Effets des Fractures de Fatigue. Volume 1. Effets sur des Avions).

    Science.gov (United States)

    1983-04-01

    F127 Cessna 206F 3 Nov 73 0 S Nagoya, Japan. Screw parts of #2 prop blade. Ref: Japan MoT. F128 Mooney M-20A 12 Nov 73 1 D Innisfree , Alta. Canada...M-20E 26 Oct 70 0 S Chugwater, Wy. USA. Propeller blade, 3" from hub. F128 Mooney M-20A 12 Nov 73 1 D Innisfree , Alta. Canada. Propeller. F133 Mooney

  16. Integrated Avionics Computerized Test Station and Component (F-16) Career Ladder AFSCs 32634C, 32654C, and 32674.

    Science.gov (United States)

    1982-04-01

    pilot’s display units (PDUs), radar electro-optical electronics units (REO EUs), and radar electro-optical indicators (REO INDs). Common tasks performed...TESTS OF HUD EU ITAs 93 G174 INSPECT AND CLEAN TESI ’ STATION FILTERS 93 1334 REMOVE OR REPLACI REO IND SRUs 89 G190 PER-FORM PEi,!OIC INSTIIONS OF TEST

  17. Aircraft Avionics and Missile System Installation Cost Study. Volume 1. Technical Report and Appendices A through E

    Science.gov (United States)

    1988-02-12

    Ru17V’US ZXMCSMY SOMIAM C.AJICE TO flAX ?! VIS]CnH A4~ AAd .v C7 Exhbi *.,*. CCB DOCMEN EXAM ~ - PLES I~ T,. -7 ;1 CL IN .( ____ = .450At-Ia .2...530.61 50 581.39 * 51 311.51 * 52 826.44 * 53 105.54 54 -79.58 55 -15.58 : 56 11.80 Ret . #3 osnum osyr boxins wir-chge nonrec fitted residual 47.00...46.55 99.16 69.00 82.00 1.10 1.70 3.01 -1.31 900 I w o O sac’ 3 00- 7- 0 40 so 120 160 200 240 280 th-corz 0 srtuo’ - fithad Ret . t35 OLS -- DEPENDENT

  18. Manufacturing technology program for high burnout silicon Schottky-barrier mixer diodes for Navy air-to-air avionics

    Science.gov (United States)

    Anand, Y.; Ellis, S.

    1982-02-01

    This report describes the establishment of low cost semiconductor processes to manufacture low-barrier-height high-burnout X-band silicon Schottky barrier diodes in production quantities. These devices are thermal-compression-bonded in a rugged low-cost pill (ODS-119) package. They exhibit an overall low noise figure of 7.0 dB (single side band) at 0.5 mW of local oscillator power level and RF burnout of 12 watts (tau = 1 microsec and 1000 Hz rep. rate). Reliability and ruggedness of the design has been demonstrated by tests taken from MIL.S 19500 F.

  19. Strategic avionics technology definition studies. Subtask 3-1A3: Electrical Actuation (ELA) Systems Test Facility

    Science.gov (United States)

    Rogers, J. P.; Cureton, K. L.; Olsen, J. R.

    1994-01-01

    Future aerospace vehicles will require use of the Electrical Actuator systems for flight control elements. This report presents a proposed ELA Test Facility for dynamic evaluation of high power linear Electrical Actuators with primary emphasis on Thrust Vector Control actuators. Details of the mechanical design, power and control systems, and data acquisition capability of the test facility are presented. A test procedure for evaluating the performance of the ELA Test Facility is also included.

  20. Digital Avionics Information System (DAIS): Life Cycle Cost Impact Modeling System (LCCIM)--A Managerial Overview. Final Report.

    Science.gov (United States)

    Goclowski, John C.; Baran, H. Anthony

    This report gives a managerial overview of the Life Cycle Cost Impact Modeling System (LCCIM), which was designed to provide the Air Force with an in-house capability of assessing the life cycle cost impact of weapon system design alternatives. LCCIM consists of computer programs and the analyses which the user must perform to generate input data.…

  1. Aircraft Trajectories Computation-Prediction-Control (La Trajectoire de l’Avion Calcul-Prediction-Controle). Volume 2

    Science.gov (United States)

    1990-05-01

    doute pas ndcessaire de sly attardar ; 116noncd des principes essentiels 6tant en fin de compte inddpcndant du nombre des participants, encore qu’il...n’exclut pas qu’II comporte des changements r6volutionnalres par rapport au syst~me actuel. Ses constituants principaux sont cens6s apparaltre 5 la fin des...concertatian entre les concepteurs du monde a~ronautique et des services de cantrble. 11 est clair que l𔄀valution pr6visible implique un changement

  2. Tanker Avionics/Aircrew Complement Evaluation (TAACE). Phase 0. Analysis and Mockup. Volume II. Summary of Data.

    Science.gov (United States)

    1980-05-01

    duration of most of these TDYs. CP5 15, 15. We deploy TDY to England or Japan once every three months for 30 days. CP6 2, 3 months. Guam/U.K. CP8 12, 11...at material on the window edoe and pilots’ laps. 83 P7 7, 4. Front panel lighting is a 7, but general interior cockpit lighting for such things as...management: Comments: B02 9. It saves time and you don’t have to worry about it and leaves more time to see and avoid. B04 9. Excellent - fuel economy

  3. Integrated Avionics Instrument and Flight Control Systems Career Ladder AFS 326X7A/B/C.

    Science.gov (United States)

    1982-03-01

    3 3 HQ TAC/DPLATC 1 1 1 HQ TAC/DPAT 3 3 3 HQ USAF/ MPPT 1 1 1 HQ USAFE/DPAT 3 3 3 HQ USAFE/DPATC 1 1 1 RQ USMC/OU 1 1 LMDC/AN 1 LTTC 5 2 2h 9p* NODAC...pressure or temperature test sets perform operational checks of attitude heading reference system V (AMRS) remove or install UHP system LRUs remove or...FORM 797) 62 Q486 OPERATE PRESSURE OR TEMPERATURE TEST SETS 62 29 TABLE 15 EXAMPLES OF TASKS WHICH BEST DIFFERENTIATE 32637 AND 32657 FROM 32677

  4. Flight Computer Processing Avionics for Space Station Microgravity Experiments: A Risk Assessment of Commercial Off-the-Shelf Utilization

    Science.gov (United States)

    Estes, Howard; Liggin, Karl; Crawford, Kevin; Humphries, Rick (Technical Monitor)

    2001-01-01

    NASA/Marshall Space Flight Center (MSFC) is continually looking for ways to reduce the costs and schedule and minimize the technical risks during the development of microgravity programs. One of the more prominent ways to minimize the cost and schedule is to use off-the-shelf hardware (OTS). However, the use of OTS often increases the risk. This paper addresses relevant factors considered during the selection and utilization of commercial off-the-shelf (COTS) flight computer processing equipment for the control of space station microgravity experiments. The paper will also discuss how to minimize the technical risks when using COTS processing hardware. Two microgravity experiments for which the COTS processing equipment is being evaluated for are the Equiaxed Dendritic Solidification Experiment (EDSE) and the Self-diffusion in Liquid Elements (SDLE) experiment. Since MSFC is the lead center for Microgravity research, EDSE and SDLE processor selection will be closely watched by other experiments that are being designed to meet payload carrier requirements. This includes the payload carriers planned for the International Space Station (ISS). The purpose of EDSE is to continue to investigate microstructural evolution of, and thermal interactions between multiple dendrites growing under diffusion controlled conditions. The purpose of SDLE is to determine accurate self-diffusivity data as a function of temperature for liquid elements selected as representative of class-like structures. In 1999 MSFC initiated a Center Director's Discretionary Fund (CDDF) effort to investigate and determine the optimal commercial data bus architecture that could lead to faster, better, and lower cost data acquisition systems for the control of microgravity experiments. As part of this effort various commercial data acquisition systems were acquired and evaluated. This included equipment with various form factors, (3U, 6U, others) and equipment that utilized various bus structures, (VME, PC104, STD bus). This evaluation of hardware was performed in conjunction with a trade study that considered over twenty (20) different factors relevant to the selection of an optimum design approach. These factors included; safety, sizing and timing, radiation hardness and single event upset, power consumption, heat dissipation, size and volume, expected service life, maintainability, heritage, operating systems, requirements for software reuse, availability of compatible interface boards, relative cost, schedule, reliability, EMI/EMC factors, "hot swap" capability, standards for conduction cooling, I/O capabilities, unique carrier requirements and operating system considerations. The approach to evaluate Safety as part of this study included a review of the Preliminary Hazard Analysis (PHA) for each of the experiment designs and a determination of how each hazard could be addressed and eliminated when different processors were selected. This included evaluating various design approaches and trade-offs between fault tolerant designs and fail-safe designs in accordance with NSTS 1700.7B. This will include the results of radiation testing where available. Various operating systems, such as VxWorks, Linux, QNX, and Embedded NT are evaluated and the advantages and disadvantages of their utilization are also addressed. Design implementation strategies for the various operating systems are considered and discussed. This paper presents the results and recommendations from this trade study. Preliminary conclusions from this study are that safety concerns from lack or radiation testing on COTS equipment can be addressed by additional testing and design considerations, the PC104 bus provided adequate I/O for the SDLE and EDSE microgravity experiments, and PC104 bus components offered significant advantages over VME and cPCI for weight and space reductions.

  5. Estonie 2004-2005 : y a-t-il un pilote dans l'avion? / Antoine Chalvin

    Index Scriptorium Estoniae

    Chalvin, Antoine

    2005-01-01

    Ülevaade sündmustest Eesti poliitikas ja majanduses: valitsuskoalitsiooni lagunemine, sotsiaalpoliitika ning tervishoiu probleemid, Eesti-Vene piirileping, majandusnäitajad, Eesti-Prantsusmaa suhted, EL-iga liitumise mõjud. Tabelid. Lisad: Eesti poliitiliste sündmuste kronoloogia 2004-2005; Valimistulemused alates 2001; Valitsuse koosseis juunis 2005

  6. Mesure sans contact d'un panneau d'aile d'avion et analyse numerique pour controle dimensionnel

    Science.gov (United States)

    Sok, Michel Christian

    During the manufacturing of the wing skin, the inspection steps are essential to ensure their conformity and thus allow the wings to ensure the required aerodynamic performances. Nowadays, considering the panel's low stiffness which prevents traditional inspection methods, this inspection is done manually with a template gauge and a jig. Iteratively, as long as form compliance is not reached, the panel goes through an additional dimensional refinement before being inspected in a second time. Because the jig is accurate, it is very expensive and furthermore, the inspection of panels is time-consuming by monopolizing the jig, which cannot be used in the meantime. Using this consideration as a starting point, this project seeks to provide a response to the practicability of a methodology based on the automation of that king of operation. This by integrating into the process non-contact measuring machines capable of acquiring numerically the geometrical shape of the panel. Moreover, the opportunity of realizing this operation without the use of a jig is also being considered, which would leave it free for other tasks. The methodology suggested use numerical simulations to check form compliance. Finally, this would provide a tool to assist the operator by allowing a semi automated inspection without jig. The methodology suggested can be describe in three steps, however it is necessary to propose an additional step to validate the results achieved with this methodology. Then, the first step consist of manually acquiring reference values which will served to be compared with the values obtained during the application of the methodology. The second step deals with the numerical acquisition, with a laser scanner, of the object to be inspected settled down on some supporting plate. The third step is the numerical reconstruction of this object with a computer-aided design software. Finally the last step consists of a numerical inspection of the object to predict the form compliance. Considering the large dimensions of the wing skins and of the jigs used in industry, the methodology suggested takes accounts of the available means in laboratory. Then, the objects used have lower dimensions than those used in the industry. That is the reason why a simplifying assumption that the shot peening operation has a negligible effect on the evolution of the thickness of the wing skin is made. Furthermore, the non-contact measurement device is also tested to know its accuracy under real conditions. Those two preliminary studies show that the thickness variation of a plate after being shot peened, with extreme parameters in terms of effects, remains negligible for the study of practicability realized in this thesis. The study on the performance of the REVscan 3D also brings to light that this variation would probably be drown in the uncertainty acquired by the device during the numerical acquisition. In this project, only the steps two and three are dealt with in depth. This study involves essentially to test the measuring device and the software about their capacity of numerically acquiring an object and then to bring it to another state of stresses with the help of a simulation. Indeed, the validation of the free state step is problematic because it is precisely a state that cannot be obtained in an experimental way. As an analogy, it is suggested to pass from a particular state of stress to another because, in a simplified way, the free state step is equivalent to a change of a state of stress. The study of the result allows to put forward a particular phenomenon linked to thin plates : it is a sudden change of the form when the plate is in a particular state of stress. The software is then no more able to predict that kind of comportment. Several tests are carried out to confirm the existence of that phenomenon and show that the stress modulus, the point of application of the stresses and the position of the support points are the more influent parameters. However, even by ensuring to avoid this phenomenon during the tests, the degree of accuracy reached by the software is far from being sufficient. Indeed, the uncertainty of the results is still too high and the next studies will have to focus on improving the results. Currently, the tests realized in this thesis are not enough to validate the steps 2 and 3 of the methodology suggested. Nevertheless, the phenomenon highlighted which can suddenly modify the comportment of thin plates and the information gathered in these tests establishes a base for further research. (Abstract shortened by UMI.).

  7. The Conflicting Forces Driving Future Avionics Acquisition (Les Arguments Contradictoires pour les Futurs Achats d’Equipements d’Avionique)

    Science.gov (United States)

    1991-09-01

    do Terre et de Mer d’un pays, et de plusieurs pays allids. Pour cola, il faut d~finir : let r~seaux interarmes ou intoralli~s sur lequel los...at sa d6finition sur un banc daossais (phases 3 at 4). En France, Ie d6veloppement dle modules do traitoment de donn6es, d’interface pour bus optique ...comn’ercial, or This method is also known as prototyping. The consumer based are rarely on time and within process is repeated until the desired detail

  8. An integrated Rotorcraft Avionics/Controls Architecture to support advanced controls and low-altitude guidance flight research

    Science.gov (United States)

    Jacobsen, Robert A.; Doane, Douglas H.; Eshow, Michelle M.; Aiken, Edwin W.; Hindson, William S.

    1992-01-01

    Salient design features of a new NASA/Army research rotorcraft--the Rotorcraft-Aircrew Systems Concepts Airborne Laboratory (RASCAL) are described. Using a UH-60A Black Hawk helicopter as a baseline vehicle, the RASCAL will be a flying laboratory capable of supporting the research requirements of major NASA and Army guidance, control, and display research programs. The paper describes the research facility requirements of these programs together with other critical constraints on the design of the research system. Research program schedules demand a phased development approach, wherein specific research capability milestones are met and flight research projects are flown throughout the complete development cycle of the RASCAL. This development approach is summarized, and selected features of the research system are described. The research system includes a real-time obstacle detection and avoidance system which will generate low-altitude guidance commands to the pilot on a wide field-of-view, color helmet-mounted display and a full-authority, programmable, fault-tolerant/fail-safe, fly-by-wire flight control system.

  9. Conception et analyse d'un systeme d'optimisation de plans de vol pour les avions

    Science.gov (United States)

    Maazoun, Wissem

    The main objective of this thesis is to develop an optimization method for the preparation of flight plans for aircrafts. The flight plan minimizes all costs associated with the flight. We determine an optimal path for an airplane from a departure airport to a destination airport. The optimal path minimizes the sum of all costs, i.e. the cost of fuel added to the cost of time (wages, rental of the aircraft, arrival delays, etc.). The optimal trajectory is obtained by considering all possible trajectories on a 3D graph (longitude, latitude and altitude) where the altitude levels are separated by 2,000 feet, and by applying a shortest path algorithm. The main task was to accurately compute fuel consumption on each edge of the graph, making sure that each arc has a minimal cost and is covered in a realistic way from the point of view of control, i.e. in accordance with the rules of navigation. To compute the cost of an arc, we take into account weather conditions (temperature, pressure, wind components, etc.). The optimization of each arc is done via the evaluation of an optimum speed that takes all costs into account. Each arc of the graph typically includes several sub-phases of the flight, e.g. altitude change, speed change, and constant speed and altitude. In the initial climb and the final descent phases, the costs are determined by considering altitude changes at constant CAS (Calibrated Air Speed) or constant Mach number. CAS and Mach number are adjusted to minimize cost. The aerodynamic model used is the one proposed by Eurocontrol, which uses the BADA (Base of Aircraft Data) tables. This model is based on the total energy equation that determines the instantaneous fuel consumption. Calculations on each arc are done by solving a system of differential equations that systematically takes all costs into account. To compute the cost of an arc, we must know the time to go through it, which is generally unknown. To have well-posed boundary conditions, we use the horizontal displacement as the independent variable of the system of differential equations. We consider the velocity components of the wind in a 3D system of coordinates to compute the instantaneous ground speed of the aircraft. To consider the cost of time, we use the cost index. The cost of an arc depends on the aircraft mass at the beginning of this arc, and this mass depends on the path. As we consider all possible paths, the cost of an arc must be computed for each trajectory to which it belongs. For a long-distance flight, the number of arcs to be considered in the graph is large and therefore the cost of an arc is typically computed many times. Our algorithm computes the costs of one million arcs in seconds while having a high accuracy. The determination of the optimal trajectory can therefore be done in a short time. To get the optimal path, the mass of the aircraft at the departure point must also be optimal. It is therefore necessary to know the optimal amount of fuel for the journey. The aircraft mass is known only at the arrival point. This mass is the mass of the aircraft including passengers, cargo and reserve fuel mass. The optimal path is determined by calculating backwards, i.e. from the arrival point to the departure point. For the determination of the optimal trajectory, we use an elliptical grid that has focal points at the departure and arrival points. The use of this grid is essential for the construction of a direct and acyclic graph. We use the Bellman-Ford algorithm on a DAG to determine the shortest path. This algorithm is easy to implement and results in short computation times. Our algorithm computes an optimal trajectory with an optimal cost for each arc. Altitude changes are done optimally with respect to the mass of the aircraft and the cost of time. Our algorithm gives the mass, speed, altitude and total cost at any point of the trajectory as well as the optimal profiles of climb and descent. A prototype has been implemented in C. We made simulations of all types of possible arcs and of several complete trajectories to illustrate the behaviour of the algorithm.

  10. Aircraft Trajectories Computation-Prediction-Control (La Trajectoire de l’Avion Calcul-Prediction-Controle). Volume 3

    Science.gov (United States)

    1990-05-01

    Concorde flight)", Rivista di Meteorologia Aeronautics, Vol. 31, p. 301-305, Italia, September 1971 (ATM) BENOIT A. "Applicability of the EROCOA trajectory...flight", Rivista di Meteorologia Aeronautics (Jan 1983) (WND) BENOIT A. (Program Chairman) "Air Traffic Control in Face of User’s Demand and Economy

  11. Outils statistiques de traitement d'indicateurs pour le diagnostic et le pronostic des moteurs d'avions

    OpenAIRE

    Rabenoro, Tsirizo

    2015-01-01

    Identifying early signs of failures in an industrial complex system is one of the main goals of preventive maintenance.It allows to avoid failure and reduce the degradation on a component by doing an earlier maintenance operation. Health monitoring for aircraft engines is one of the industrial fields for which this anomaly detection is very important and meaningful. Aircraft engine manufacturers such as Snecma collect large amount of engine related data during each flight.The idea is to be ab...

  12. Aircraft Trajectories Computation-Prediction-Control. Volume 1 (La Trajectoire de l’Avion Calcul-Prediction-Controle)

    Science.gov (United States)

    1990-03-01

    14 000 a hr18 14 000 0 d6sir6em ¥ libro Vr 00 P(anntros acte(s) h(m M til h,(i) I y() trs) hrm) I YrM li dgorr 0 18.1 10 S101 49 Contr1niton finales...organizations at partners’ design offices themselves. And by the same token it reflects Airbus’ industrial marketing approach, which traditionally

  13. Integrated Test Bed Facility

    Data.gov (United States)

    Federal Laboratory Consortium — The ITB's avionics system is composed of multiple high performance processors, embedded software, and data communication systems. The avionics embedded software is a...

  14. 75 FR 6865 - Airworthiness Directives; The Boeing Company Model 737-700 (IGW) Series Airplanes Equipped With...

    Science.gov (United States)

    2010-02-12

    ... applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as... principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a...

  15. Proceedings Papers of the AFSC (Air Force Systems Command) Avionics Standardization Conference (2nd) Held at Dayton, Ohio on 30 November - 2 December 1982. Volume 10. Addendum.

    Science.gov (United States)

    1982-11-01

    prize. There are many -facets to standardization. There are techical issues, policy issues.budgeting issues, programmatic issues, logistics support...34s’lret, peil of the pfoqraiftq 0wmicamow.t. to Obo to q@Mt daetl to titugo 6. Machinet r oaogo of swll..ltom ptrvinamqIinpu twat& CO000 it% tIt.apof

  16. Mission Planning Systems for Tactical Aircraft (Pre-Flight and In- Flight) (Systemes de Planification des Missions pour Avions Tactiques (Avant Vol et en Vol)

    Science.gov (United States)

    1991-05-01

    electronics Communications may yield delays ( they has-c to be encrypted systems or items of communications-equipment when Transmissions may be corrupted ...tactical global soutions Thnis Process takes Into e’lnsiT, 11r 7,1 i Jia nticwork. The pilot interacts with the sysitt using a keybotard,. allow

  17. Proceedings Papers of the AFSC (Air Force Systems Command) Avionics Standardization Conference (2nd) Held at Dayton, Ohio on 30 November-2 December 1982. Volume 2

    Science.gov (United States)

    1982-11-01

    W-PAFB, OH A xxi Table of Contents Standardized Software Development Page System Planning Tool to Measure Cost Avoidance Resulting 1017 from... Programa Development SFecification for Ada integrated Environment: KAPSE/Database Type B-5, IR-678-1, interinetrics, Inc., 30 June 1982. 2. Computer

  18. Avionic Sensor Systems and Aerospace Photographic Systems Repair Career Ladders AFSCs 322X2A, 322X2C, and 404X1.

    Science.gov (United States)

    1984-07-01

    1 1 HQ USAF/LEYM 1 1 HQ USAF/ MPPT 1 1 HQ USAFE/DPAT 3 3 HQ USAFE/DPATC 1 1 HQ USMC (CODE TPI) 1 LMDC/AN 1 NODAC 1 3400 TCHTW/TTGX (LOWRY AFB CO) 3 3 3...infrared detectors, side-looking radar, data display systems, and associated sensor control systems. The 322X2C personnel perform duties related to electro...optical sensors, such as optical cameras, mounts, viewfinders, aircraft camera parameter controls , and associated control systems. Personnel in the

  19. Analysis of technology requirements and potential demand for general aviation avionics systems in the 1980's. [technology assessment and technological forecasting of the aircraft industry

    Science.gov (United States)

    Cohn, D. M.; Kayser, J. H.; Senko, G. M.; Glenn, D. R.

    1974-01-01

    The trend for the increasing need for aircraft-in-general as a major source of transportation in the United States is presented (military and commercial aircraft are excluded). Social, political, and economic factors that affect the aircraft industry are considered, and cost estimates are given. Aircraft equipment and navigation systems are discussed.

  20. Integrated Avionics Computerized Test Station and Component (F/FB-111) Career Ladder AFS 326X4A. Occupational Survey Report.

    Science.gov (United States)

    1982-06-01

    TTY 2 1 1 HQ SAC/DPAT 3 3 3 HQ SAC/LGMQ (ATCLO) 1 1 1 HQ TAC/DPAT 3 3 3 HQ TAC/DPLATC I 1 1 HQ USAF/LEYM 1 1 1 HQ USAF/ MPPT 1 1 1 HQ USAFE/DPAT 3 3 3...prepared in response to a request by HQ ATC/TTQG. Authority for conducting occupational surveys is contained in AFR 35-2. Computer outputs from which this...RESEARCH MICROFICHE FOR PART INFORMATION 92 J322 ISOLATE MALFUNCTIONS IN F/FB-Ill ARS LOW VOLTAGE POWER SUPPLIES 88 E141 MAKE ENTRIES ON UNSERVICEABLE

  1. Estimation des masses, des centres de gravite ainsi que des moments d'inertie de l'avion cessna citation X

    Science.gov (United States)

    Chahbani, Samia

    The masses, centers of gravity and moments of inertia are the main parameters in the three phases of the design of the aircraft. They are of extreme importance in the studies of the stability and proper functioning of the aircraft by modeling and simulation methods. Unfortunately, these data are not always available given the confidentiality of aerospace field. A question arises naturally: How to estimate the mass, center of gravity and moments of inertia of an aircraft based on only its geometry? In this context in which this thesis is realized, the masses are estimated by Raymer`s methods. The aircraft described in procedures based on mechanical techniques engineers are used for determining the centers of gravity. The DATCOM is applied for obtaining moments of inertia. Finally, the results obtained are validated by using the flight simulator at the LARCASE corresponding to Cessna Citation X. we conclude with a representation of an analytical model that sum up the different step to follow up for estimating masses, centers of gravity and moments of inertia for any commercial aircraft.

  2. Optimisation d'un systeme d'antigivrage a air chaud pour aile d'avion basee sur la methode du krigeage dual

    Science.gov (United States)

    Hannat, Ridha

    The aim of this thesis is to apply a new methodology of optimization based on the dual kriging method to a hot air anti-icing system for airplanes wings. The anti-icing system consists of a piccolo tube placed along the span of the wing, in the leading edge area. The hot air is injected through small nozzles and impact on the inner wall of the wing. The objective function targeted by the optimization is the effectiveness of the heat transfer of the anti-icing system. This heat transfer effectiveness is regarded as being the ratio of the wing inner wall heat flux and the sum of all the nozzles heat flows of the anti-icing system. The methodology adopted to optimize an anti-icing system consists of three steps. The first step is to build a database according to the Box-Behnken design of experiment. The objective function is then modeled by the dual kriging method and finally the SQP optimization method is applied. One of the advantages of the dual kriging is that the model passes exactly through all measurement points, but it can also take into account the numerical errors and deviates from these points. Moreover, the kriged model can be updated at each new numerical simulation. These features of the dual kriging seem to give a good tool to build the response surfaces necessary for the anti-icing system optimization. The first chapter presents a literature review and the optimization problem related to the antiicing system. Chapters two, three and four present the three articles submitted. Chapter two is devoted to the validation of CFD codes used to perform the numerical simulations of an anti-icing system and to compute the conjugate heat transfer (CHT). The CHT is calculated by taking into account the external flow around the airfoil, the internal flow in the anti-icing system, and the conduction in the wing. The heat transfer coefficient at the external skin of the airfoil is almost the same if the external flow is taken into account or no. Therefore, only the internal flow is considered in the following articles. Chapter three concerns the design of experiment (DoE) matrix and the construction of a second order parametric model. The objective function model is based on the Box-Behnken DoE. The parametric model that results from numerical simulations serve for comparison with the kriged model of the third article. Chapter four applies the dual kriging method to model the heat transfer effectiveness of the anti-icing system and use the model for optimization. The possibility of including the numerical error in the results is explored. For the test cases studied, introduction of the numerical error in the optimization process does not improve the results. Dual kriging method is also used to model the distribution of the local heat flux and to interpolate the local heat flux corresponding to the optimal design of the anti-icing system.

  3. Contribution à la gestion et au contrôle de trajectoire d’un avion avec panne totale des moteurs

    OpenAIRE

    Wu , Hongying

    2013-01-01

    Engine-out is an undoubted critical situation for flight safety. The objective of this thesis is to improve the management of emergency manoeuvres for transportation aircraft once all engines go out at a given point during the flight. Here we consider the evolution of the gliding aircraft along a vertical plane possibly leading directly to a safe landing place. The gliding qualities of standard transportation aircraft are first analyzed and reachable areas from given initial situations are es...

  4. Estudio de las cualidades de vuelo lateral-direccional de aviones de transporte con timón de dirección no convencional

    OpenAIRE

    Castillo Acero, Miguel Ángel

    2016-01-01

    La historia de la aviación está vinculada a la investigación y el desarrollo de diferentes ámbitos científicos físicos y matemáticos. En la literatura se pueden encontrar numerosos ejemplos de estudios no sólo de nuevas configuraciones no convencionales de aeronaves, sino también de desarrollos de nuevos materiales y procesos para que las aeronaves sean más ligeras y resistentes. También aparecen publicados desarrollos en la predicción de las cargas aerodinámicas frente a las que el avión se ...

  5. A Decision Support System for Acquisition of F-16 Avionics Intermediate Shop Test Sets Using the System Science Paradigm and Q-GERT.

    Science.gov (United States)

    1982-09-01

    TAPE AT/LSH 111 WSUI weAIIU amU amS 11 NO POSTAGE111111 NCESSARy wnm& um~uIF MAILED UNITED STTS BUSINESS REPLY MAIL - I- POSTAGE WILL N PAID BY ADDESSES...unlimited 17. DISTRIBUTION STATEMENT (f Iho &r@&set eiteed in Stock 0, if dlfforent be" Repmt) 1,. SUPPE ARY NOTES Am V FOR PUBIC RUA% lAW AFR 19Q-17 a5’ SE...290) 27 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ t * F trasmitter /recei Fig. 7. Equipment Cones of Resolution (adapted from 36:290) 28 for those distributions

  6. Amelioration de l'implementation des volets dans un modele de dynamique et controle de vol de l'avion L1011-500

    Science.gov (United States)

    Saafi, Kais

    The aerodynamic model of the aircraft L1011-500 was designed and simulated in Matlab and Simulink by Bombardier to serve the Esterline-CMC Electronics Company in its goals to improve the Flight Management System FMS. In this model implemented in FLSIM by CMC-Electronics Esterline, a longitudinal instability appears during the approach phase and when flaps have a higher or equal angle to 4 degrees. The global project at LARCASE consisted in the improvement of the L1011-500 aerodynamic model stability under Matlab / Simulink and mainly for flaps angles situated between 4 degrees and 22 degrees. The L1011-500 global model was finalized in order to visualize and analyze its dynamic behavior. When the global model of the aircraft L1011-500 was generated, corrections were added to the lift coefficient (CL), the drag coefficient (CD) and the pitching moment coefficient (CM) to ensure the trim of the aircraft. The obtained results are compared with the flight tests data delivered by CMC Electronics-Esterline to validate our numerical studies.

  7. Optimisation des trajectoires d'un systeme de gestion de vol d'avions pour la reduction des couts de vol

    Science.gov (United States)

    Sidibe, Souleymane

    The implementation and monitoring of operational flight plans is a major occupation for a crew of commercial flights. The purpose of this operation is to set the vertical and lateral trajectories followed by airplane during phases of flight: climb, cruise, descent, etc. These trajectories are subjected to conflicting economical constraints: minimization of flight time and minimization of fuel consumed and environmental constraints. In its task of mission planning, the crew is assisted by the Flight Management System (FMS) which is used to construct the path to follow and to predict the behaviour of the aircraft along the flight plan. The FMS considered in our research, particularly includes an optimization model of flight only by calculating the optimal speed profile that minimizes the overall cost of flight synthesized by a criterion of cost index following a steady cruising altitude. However, the model based solely on optimization of the speed profile is not sufficient. It is necessary to expand the current optimization for simultaneous optimization of the speed and altitude in order to determine an optimum cruise altitude that minimizes the overall cost when the path is flown with the optimal speed profile. Then, a new program was developed. The latter is based on the method of dynamic programming invented by Bellman to solve problems of optimal paths. In addition, the improvement passes through research new patterns of trajectories integrating ascendant cruises and using the lateral plane with the effect of the weather: wind and temperature. Finally, for better optimization, the program takes into account constraint of flight domain of aircrafts which utilize the FMS.

  8. Avionics Collaborative Engineering Technology Delivery Order 0035: Secure Knowledge Management (SKM) Technology Research Roadmap - Technology Trends for Collaborative Information and Knowledge Management Research

    National Research Council Canada - National Science Library

    Moody, Russell

    2004-01-01

    ...) this SKM Technology Research Roadmap. The SKM Technology Research Roadmap provides information on the current state, trends, gaps, land research challenges associated with SKM technology research...

  9. Mission Planning for Tactical Aircraft (Preflight and In-Flight) (Systemes de Planification des Missions Pour Avions Tactiques) (Avant Vol et en Vol).

    Science.gov (United States)

    1992-12-01

    type of airborne mission planning is the ABC (’(’ together with that rernetiwbered by the crew. Ideally these com- A.;n whivch a planningornd command...AGARD National Aeronautics and Space Administration Gabinete de Estudos e Programas Langley Research Center CLAFA M’S 180 Base de Alfragide Hampton...O.N.E.R.A. (Direction) Gabinete de Estudos e Programas 29 Avenue de la Division Leclerc CLAFA 92322 Chftillon Cedex Base de AlfragideAlfragide GERMANY

  10. A PC-Based Interactive Simulation of the F-111C Pave Tack System and Related Sensor, Avionics and Aircraft Aspects

    Science.gov (United States)

    1994-03-01

    Computing Optical Sight Set LCP Laser Control Panel LGB Laser Guided Bomb LOS Line-of-sight LRU Line Replaceable Unit LTI Linear time invariant MOAP ...Unit UNCLASSIFIED 10 __________________ UNCLASSIFIED ERL-06S6-RR BCU - Ballistics Computer Unit MOAP - Multiple Offset Aimpoint Panel Prior to flight

  11. Using software metrics and software reliability models to attain acceptable quality software for flight and ground support software for avionic systems

    Science.gov (United States)

    Lawrence, Stella

    1992-01-01

    This paper is concerned with methods of measuring and developing quality software. Reliable flight and ground support software is a highly important factor in the successful operation of the space shuttle program. Reliability is probably the most important of the characteristics inherent in the concept of 'software quality'. It is the probability of failure free operation of a computer program for a specified time and environment.

  12. Caracterisation de la propagation sans-fil dans les avions commerciaux pour une transmission dediee aux services aux passagers et aux systemes avioniques

    Science.gov (United States)

    Saghir, Hassane

    Aircraft systems are interconnected by cable bundles that may represent a hundred kilometres. Those wirings penalize the aircraft weight. Cable bundles favour electromagnetic interference on board aircraft and routing a new cable for integrating new equipment boxes in a sustained aircraft requires a lot of retrofit work. Consequently, the aviation industry and aerospace community are working in the scope of different projects on new alternatives that will better fit to the future generation of aircrafts and help to reduce interconnecting wires on board. Wireless technologies represent a coveted solution that could make significant improvements and benefits to new generations of aircrafts. This research work focuses on the study of the wireless propagation over some frequency bands inside commercial aircrafts. The main objective is to provide conclusions and recommendations on criteria that may help optimizing the wireless communication without impacting the existent systems. Targeted applications are the inflight entertainment (IFE) service and wireless sensing systems. This work was conducted in collaboration with Bombardier-Aerospace based in Montreal (QC) in the frame of AVIO-402 project under the grant of CRIAQ (http://www.criaq.aero/). In this study, an experimental characterization of the propagation channel in the ISM band around 2.4 GHz frequency 5.8 GHz has been performed in a CRJ700 aircraft from Bombardier Aerospace. This characterization allowed to extract the parameters needed to analyze the channel behavior. The measurements results have shown that the propagation characteristics are close to those of both typical indoor medium in terms of the delay spread and a tunnel in terms of path loss. Then, a 3D channel modeling and simulation have been achieved with an RF prediction software (Wireless Insite Remcom). The simulations also consider the millimeter band around 60 GHz. The simulations yielded to analytical models of radio coverage which were subsequently used to evaluate wireless link interference scenarios and performance metrics. Finally, these models were used to design a TDL (Tapped Delay Line) channel model with the goal of an implementation under Matlab in a wireless transmission chain.

  13. Microwave Antennas for Avionics. Lecture Series of the Avionics Panel and the Consultant and Exchange Programme Held in Rome, Italy on 7-8 May 1987; Guenzburg, Germany on 11-12 May 1987 and Ankara, Turkey on 14-15 May 1987.

    Science.gov (United States)

    1987-04-01

    276-283 MJ Cans and RA Semplak (1975), "Some far field studies of an offset launcher", BELL Syst. Tech. J., Vol. 54, 1319-1340 TS Bird (1982...GALLAGHER, J. d.: C/ PARADIS , L. R.; D/SHUKIS, F. A. PAA: D/(Raytheon Co., Bedford, MA) (AIAA, Thermophysics Conference, 19th, Snowmass, CO, dune 25

  14. 75 FR 8330 - Access to Confidential Business Information by Eastern Research Group

    Science.gov (United States)

    2010-02-24

    ...? Under Contract Number EP-W-09-033, contractor ERG of 14555 Avion Parkway, Suite 200, Chantilly, VA, will...'s site located at 14555 Avion Parkway, Suite 200, Chantilly, VA, in accordance with EPA's TSCA CBI...

  15. Euroopa kolm nobedaimat gaselli / Askur Alas

    Index Scriptorium Estoniae

    Alas, Askur, 1973-

    2007-01-01

    Euroopas 2006. aastal kõige kiiremini kasvanud keskmise suurusega ettevõtetest: Prantsuse IT-firma Gameloft, Islandi transpordi- ja logistikafirma Avion Group ning Prantsuse tehnoloogiafirma Assystem. Lisa: Gamelofti mängud; Gameloft, Avion Group, Assystem

  16. Survey of symbology for aeronautical charts and electronic displays : navigation aids, airports, lines, and linear patterns

    Science.gov (United States)

    2008-09-01

    This industry survey documents the symbols for navigation aids, airports, lines, and linear patterns currently in use by avionics manufactureres and chart providers for depicting aeronautical charting information. Nine avionics display manufacturers ...

  17. A Survey of Serious Aircraft Accidents Involving Fatigue Fracture. Volume 2. Rotary-Wing Aircraft (Etude sur des Accidents Importants d’Avions du aux Effets des Fractures de Fatigue. Volume 2. Effets sur des Helicopteres).

    Science.gov (United States)

    1983-04-01

    Japan NoT. NI08 Bell 2063 3 Jun 79 0 D Morgan City, La. USA. Turbine blade. NTSB file 3-2100. N109 Fairchild 25 Jul 79 0 S Riviere Eternite , Que. Canada...transmission lift link strut failed. Role: aerial logging. N109 Fairchild 25 Jul 79 0 S Riviere Eternite , Que. Canada. FH-1100 Abraidable plastic

  18. Formulation d'un modele mathematique par des techniques d'estimation de parametres a partir de donnees de vol pour l'helicoptere Bell 427 et l'avion F/A-18 servant a la recherches en aeroservoelasticite

    Science.gov (United States)

    Nadeau-Beaulieu, Michel

    In this thesis, three mathematical models are built from flight test data for different aircraft design applications: a ground dynamics model for the Bell 427 helicopter, a prediction model for the rotor and engine parameters for the same helicopter type and a simulation model for the aeroelastic deflections of the F/A-18. In the ground dynamics application, the model structure is derived from physics where the normal force between the helicopter and the ground is modelled as a vertical spring and the frictional force is modelled with static and dynamic friction coefficients. The ground dynamics model coefficients are optimized to ensure that the model matches the landing data within the FAA (Federal Aviation Administration) tolerance bands for a level D flight simulator. In the rotor and engine application, rotors torques (main and tail), the engine torque and main rotor speed are estimated using a state-space model. The model inputs are nonlinear terms derived from the pilot control inputs and the helicopter states. The model parameters are identified using the subspace method and are further optimised with the Levenberg-Marquardt minimisation algorithm. The model built with the subspace method provides an excellent estimate of the outputs within the FAA tolerance bands. The F/A-18 aeroelastic state-space model is built from flight test. The research concerning this model is divided in two parts. Firstly, the deflection of a given structural surface on the aircraft following a differential ailerons control input is represented by a Multiple Inputs Single Outputs linear model whose inputs are the ailerons positions and the structural surfaces deflections. Secondly, a single state-space model is used to represent the deflection of the aircraft wings and trailing edge flaps following any control input. In this case the model is made non-linear by multiplying model inputs into higher order terms and using these terms as the inputs of the state-space equations. In both cases, the identification method is the subspace method. Most fit coefficients between the estimated and the measured signals are above 73% and most correlation coefficient are higher than 90%.

  19. Long-term monitoring of air crew exposure onboard of Czech Airlines aircraft; Monitorage a long terme de l'exposition du personnel navigant a bord d'un avion de la compagnie aerienne Czech Airlines

    Energy Technology Data Exchange (ETDEWEB)

    Ploc, O.; Spurny, F. [Nuclear Physics Institute AS CR, Dept. of Radiation Dosimetry, Prague (Czech Republic); Ploc, O. [Czech Technical Univ., Dept. of Dosimetry and Application of Ionizing Radiation, Prague (Czech Republic)

    2007-01-15

    This contribution presents new results related to the aircraft crew exposure onboard aircraft of Czech air companies. First, the results of long term monitoring onboard of an aircraft of Czech Airlines are presented. In the period May-December 2005, 494 individual flights have been followed using MDU-Liulin Si-diode based spectrometer, together with thermoluminescent and track detectors. The results of measurements are analyzed and compared with those of calculation performed with CARI6 and EPCARD3.2 codes. Monitoring period represented about 4.6 times more than usual annual engagement of an aircrew (600 hours). Total effective dose during these 2 755 hours was between Il and 12 mSv, following the considered method of evaluation. Both the measuring and calculation methods correlate well. This fact leads to confirmation of the routine method evaluating the level of aircraft crew exposure using CARI6 code as correct for this purpose. Second, the results of individual monitoring of aircrew members obtained during few last years by this routine method are presented; general tendencies of aircraft crew onboard exposure of Czech air companies are outlined. The contribution of aircrew exposure to total occupational exposure in the Czech Republic represents about 20%. (authors)

  20. Nouvelle methode d'optimisation du cout d'un vol par l'utilisation d'un systeme de gestion de vol et sa validation sur un avion Lockheed L-1011 TriStar

    Science.gov (United States)

    Gagne, Jocelyn

    Usually, flights optimization and planning will take place before flight, on ground. However, it is not always feasible to do such optimization, or sometime unpredictable events may force pilots to change the flight path. In those circumstances, the pilots can only rely on charts or their Flight Management System (FMS) in order to maintain an economic flight. However, those FMS often rely on those same charts, which will not take into consideration different parameters, such as the cost index, the length on the flight or the weather. Even if some FMS take into consideration the weather, they may only rely on manually entered or limited data that could be outdated, insufficient or incomplete. The alleviate these problems, the function program's that was developed is mainly to determine the optimum flight profile for an aircraft, or more precisely, at the lowest overall cost, considering a take-off weight and weather conditions. The total cost is based on the value of time as well as the cost of fuel, resulting in the use of a ratio called the cost index. This index allows both to prioritize either the time or fuel consumption according to the costs related to a specific flight and/or airline. Thus, from a weight, the weather (wind, temperature, pressure), and the cost index, the program will calculate from the "Performance DataBase" (PDB) of a specific airplane an optimal flight profile over a given distance. The algorithm is based on linear interpolations in the performances tables using the Lagrange method. Moreover, in order to fully optimize the flight, the current program can, according to departure date and coordinates, download the latest available forecast from environment Canada website and calculate the optimum flight accordingly. The forecast data use by the program take the form of a 0.6 × 0.6 degrees grid in which the effects of wind, pressure and temperature are interpolated according to the aircraft geographical position and time. Using these tables, performances and forecasts, the program is therefore able to calculate the optimum profile from ground, but also in flight, if any change would occur on the path. Because all data is tabulated and not calculated, the required calculation power remains low, resulting in a short calculation time. Keywords: optimization, algorithm, simulation, cost.

  1. Conference Proceedings on High Altitude and High Acceleration Protection for Military Aircrew Held in Pensacola Florida on 29-30 April 1991 (Les Equipements de Protection pour le Vol Haute Altitude et Grande Acceleration a Bord des Avions Militaires)

    Science.gov (United States)

    1991-10-01

    total electrochemical potential diff- both the Hodgkin - Huxley membrane (unmyel- erence, which is the sum of the concentr- inated nerve cells) and...nave Leen focuses on enaurnir adequate resource: t,, dcfe.o- * -:rainst I tential aggressan y a numerically superior Warsaw Pact, the changed occurlt...sustained +Gz acceleration. Brooks AFB, TX: School of Aerospace Medicine, 1973. Report SAM-TR-73-21. ..... ... . . . . . i 7- Y 3. Bums JW, Baldin UI

  2. Avionics Interface Data Summaries: A-10A, EF-111A, F-4E, F-4G, F-15A, F- 16A, F-111A, F-111E, F-111F, RF-4C

    Science.gov (United States)

    1979-10-01

    selected course. The displacmoent represented by the indicating device will be controlled by UE software and will be dependent upon 3ircraft flight phase...will be Controlled by UE software and will be dependent upon aircraft flight phase. Deflection of the Indicating device may represent angular...15ima Max. 2) gSO’s BDHI (ID-663’ )/U). Distance stutter mechanisr, 28 Vdc, 150ma max. SOURCE: (TBD-11 Interconnection Uata Wire Type & No.: Two Single

  3. Understanding and Modeling Vortical Flows to Improve the Technology Readiness Level for Military Aircraft (Comprehension et Modelisation des Flux de Vortex Pour Ameliorer le Niveau de Maturite Technologique au Profit des Avions Militaires)

    Science.gov (United States)

    2009-10-01

    approximately 2 µm, in order to guarantee sufficient light reflection. For this investigation an air cooled class 3B Argon -Ion-laser has been used...la Défense nationale LUXEMBOURG ROYAUME-UNI 305, rue Rideau, 9e étage Voir Belgique Dstl Knowledge and Information Ottawa, Ontario K1A 0K2...Rideau Street, 9th Floor Via XX Settembre 123 031 19 Liptovský Mikuláš Ottawa, Ontario K1A 0K2 00187 Roma SLOVENIA CZECH REPUBLIC LUXEMBOURG

  4. La virgen de los sicarios leída a contrapelo: para un análisis del flâneur en tiempos de aviones y redefinición del espacio público

    Directory of Open Access Journals (Sweden)

    Jorge Joaquín Locane

    2013-04-01

    Full Text Available El presente artículo presenta una lectura de La virgen de los sicarios (1994 de Fernando Vallejoalgo desviada de los ejes habituales. Tomando distancia de los análisis que se concentran en laviolencia y en la figura del sicario, y, partiendo de una perspectiva narratológica, propone tomarcomo objeto central el desplazamiento que Fernando, en tanto flâneur anacrónico, realiza porla ciudad de Medellín. Desde este enfoque, se muestra cómo este movimiento, guiado por unimpulso de atracción hacia lo siniestro, desafía fronteras y produce una hibridación con el “otro”que se expresa en la evolución del lenguaje del protagonista. Asimismo, se observa cómo elmovimiento realizado por el personaje sirve para dar cuenta críticamente de los atributos queadquiere el espacio local en el contexto del actual diseño geopolítico global.

  5. Anxiété de vol et phobie de l'avion : validation de questionnaires d'auto-évaluation et étude des comportements des passagers

    OpenAIRE

    Bourgoin, Émilie

    2015-01-01

    The literature suggests that fear of flying affects 10-40% of the population and can represent a significant source of anxiety for airline passengers. In some cases flying phobia can develop. Few studies have developed measures that adequately assess anxiety linked to flying; moreover, to our knowledge there is very little research on the behavioral manifestations linked to fear of flying. The research carried out for this thesis seeks to validate French translations of existing flying anxiet...

  6. Integrated Target Acquisition and Fire Control Systems: Avionics Panel Symposium Held in Ottawa, Canada on 7-10 October 1991 (Systemes Integres d’Acquisition d’Objectifs et de Conduite de Tir)

    Science.gov (United States)

    1992-02-01

    ADDRESS by Major-General D.R. Williams Chief Air Doctrine and Operatiols National Defence Headquarters Major-General George R. Pearkes Bui.ding Ottawa...environnement de type champ de bataille , de nombreux objets peuvent r~pondre 4 Le deplaceinent recherch6 est one translation pure ce3 crit~es

  7. Advanced Aircraft Interfaces: The Machine Side of the Man-Machine Interface (Les Interfaces sur les Avions de Pointe: L’Aspect Machine de l’Interface Homme-Machine)

    Science.gov (United States)

    1992-10-01

    vision bio /binoculaire mont interpupillaire des optiques. Elles impliquent la mise supdrieurea k celles de Ia vision monoculaire, en en oeuvre de m...amorphe) et Crystal Liquide visualisation I tube (avionique complet avec ndmatique en h~lice. alimentation , protections, connecteurs,...). . Lampes I

  8. Information note about the protection of nuclear facilities against aircraft crashes; Note d'information sur la protection des installations nucleaires contre les chutes d'avions

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    2001-07-01

    The protection of nuclear facilities against external risks (earthquakes, floods, fires etc..) is an aspect of safety taken into consideration by the French authority of nuclear safety (ASN). Concerning the aircraft crashes, the fundamental safety rules make three categories of aircraft: the small civil aircraft (weight < 5.7 t), the military aircraft, and the commercial aircraft (w > 5.7 t). Nuclear facilities are designed to resist against crashes of aircraft from the first category only, because the probability of the accidental crash of a big aircraft are extremely low. This document comprises an information note about the protection of nuclear facilities against aircraft crashes, a dossier about the safety of nuclear facilities with respect to external risks in general (natural disasters and aircraft crashes), and an article about the protection of nuclear power plants against aircraft crashes (design, safety measures, regulation, surveillance, experience feedback). (J.S.)

  9. Numerical and experimental study of the mixture of engine jets in the wake vortices of an airline aircraft; Etude numerique et experimentale du melange des jets de moteur dans les tourbillons de sillage d'un avion de ligne

    Energy Technology Data Exchange (ETDEWEB)

    Brunet, St.

    1999-07-01

    This study is a contribution to the understanding of the formation and duration of aircraft condensation trails. The development of a numerical code based on the direct resolution of the 3-D compressible Navier-Stokes equations has been done first. Then, an experiment has been carried out in a wind tunnel to analyze the problem of the mixture of heated jets in a wing wake. A first validation of the numerical method has been carried out from bibliographic results and measurements of the mixture evolution of an inert tracer contained in the engine jets during a flight test. In order to characterize the condensation inside the wake, the evolution of the local water vapor saturation ratio has been calculated. The influence of the Crow instability on the mixture of effluents in the high atmosphere is also shown. Finally, a comparison is made between the numerical simulation results and the experimental measurements obtained in this study. The numerical results have also permitted to characterize the low scale exchange mechanisms between a turbulent jet and a swirl flow. (J.S.)

  10. Advanced Computer Aids in the Planning and Execution of Air Warfare and Ground Strike Operations: Conference Proceedings, Meeting of the Avionics Panels of AGARD (51st) Held in Kongsberg, Norway on 12-16 May 1986

    Science.gov (United States)

    1986-02-01

    Natural Language (NL) interface. It is not as generic as Knowleoige Craft, i.e. it doeb not allow different ML procesoing paradigms. Language Craft is...or they may be scheduled to begin at m specific time in the scenario. Sosarion have been developed from the Motorized Rifle Regiment to the ombined

  11. A study of compositional verification based IMA integration method

    Science.gov (United States)

    Huang, Hui; Zhang, Guoquan; Xu, Wanmeng

    2018-03-01

    The rapid development of avionics systems is driving the application of integrated modular avionics (IMA) systems. But meanwhile it is improving avionics system integration, complexity of system test. Then we need simplify the method of IMA system test. The IMA system supports a module platform that runs multiple applications, and shares processing resources. Compared with federated avionics system, IMA system is difficult to isolate failure. Therefore, IMA system verification will face the critical problem is how to test shared resources of multiple application. For a simple avionics system, traditional test methods are easily realizing to test a whole system. But for a complex system, it is hard completed to totally test a huge and integrated avionics system. Then this paper provides using compositional-verification theory in IMA system test, so that reducing processes of test and improving efficiency, consequently economizing costs of IMA system integration.

  12. Aging Methodologies and Prognostic Health Management for Electrolytic Capacitors

    Data.gov (United States)

    National Aeronautics and Space Administration — Understanding the ageing mechanisms of electronic components critical avionics systems such as the GPS and INAV are of critical importance. Electrolytic capacitors...

  13. Data Acquistion Controllers and Computers that can Endure, Operate and Survive Cryogenic Temperatures Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Current and future NASA exploration flight missions require Avionics systems, Computers, Controllers and Data processing units that are capable of enduring extreme...

  14. Improved Design of Radiation Hardened, Wide-Temperature Analog and Mixed-Signal Electronics, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — NASA space exploration projects require avionic systems, components, and controllers that are capable of operating in the extreme temperature and radiation...

  15. Data Acquistion Controllers and Computers that can Endure, Operate and Survive Cryogenic Temperatures, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — Current and future NASA exploration flight missions require Avionics systems, Computers, Controllers and Data processing units that are capable of enduring extreme...

  16. Onboard Generic Fault Detection Algorithm Development and Demonstration for VTOL sUAS, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — In the proposed SBIR study, Empirical Systems Aerospace, Inc. (ESAero) will develop a fault detection and identification avionics system implementing a generic...

  17. Participant Assessments of Aviation Safety Inspector Training for Technically Advanced Aircraft

    National Research Council Canada - National Science Library

    Chidester, Thomas; Hackworth, Carla; Knecht, William

    2007-01-01

    .... Aside from technical challenges presented by learning any new system, pilots report some difficulty in acquiring a conceptual understanding of the functions offered by the avionics, developing system...

  18. Operationally Responsive Spacecraft Subsystem, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — Saber Astronautics proposes spacecraft subsystem control software which can autonomously reconfigure avionics for best performance during various mission conditions....

  19. Design and Development of a Rapid Research, Design, and Development Platform for In-Situ Testing of Tools and Concepts for Trajectory-Based Operations

    Science.gov (United States)

    Underwood, Matthew C.

    2017-01-01

    To provide justification for equipping a fleet of aircraft with avionics capable of supporting trajectory-based operations, significant flight testing must be accomplished. However, equipping aircraft with these avionics and enabling technologies to communicate the clearances required for trajectory-based operations is cost-challenging using conventional avionics approaches. This paper describes an approach to minimize the costs and risks of flight testing these technologies in-situ, discusses the test-bed platform developed, and highlights results from a proof-of-concept flight test campaign that demonstrates the feasibility and efficiency of this approach.

  20. Impact of the european emission trading scheme for the air transportation industry on the valuation of aircraft purchase rights; Impacto de la ley de comercio europeo de emisiones de CO{sub 2} para el sector del transporte aereo en la valoracion de los derechos de compra de aviones

    Energy Technology Data Exchange (ETDEWEB)

    Tarradellas-Espuny, J.; Salamero-Salas, A.; Martinez-Costa, C.

    2009-07-01

    The European Commission issued a legislative proposal in December 2006, suggesting a cap on CO{sub 2} emissions for all planes arriving or departing from EU airports, while allowing airlines to buy and sell pollution credits on the EU carbon market (Emission Trading Scheme, or ETS). In 2008 the new scheme got the final approval. Real options appear to be ab appropriate methodology to capture the extra value brought by the new legislation on new airplane purchase rights: The airline will surely have the purchase right to the new plane if the operation of the plane generates unused pollution credits that the airline can sell at a minimum price in the carbon market. This paper tries to determine if the impact of ETS in the valuation of aircraft purchase rights is significant enough in monetary terms to include the new legislation in a complex real-option model already proposed by the authors recently. The research concludes that even the impact of ETS justifies its inclusion in the model, the quality of the available sets of historical data still raises some questions. Particularly, the assumption of market efficiency for the Carbon Pool over the recent years needs to be treated with caution. (Author) 9 refs.

  1. Human Factors Analysis of Aircrew Operational Tasks in a Fixed-Wing Search and Rescue Aircraft Cargo Compartment (Analyse des facteurs humains lies aux taches operationnelles qui sont executees par les membres d’equipage dans la soute des avions de recherche et de sauvetage)

    Science.gov (United States)

    2011-05-01

    SAR. On a tenu compte de données anthropométriques pertinentes, des tendances de la croissance séculaire, de l’équipement de protection individuelle...Defence, 2011 © Sa Majesté la Reine (en droit du Canada), telle que représentée par le ministre de la Défense nationale, 2011 DRDC Toronto TM...CISHO), à la demande du Directeur, Besoins aérospatiaux (DBA), a effectué une analyse des facteurs humains liés aux tâches opérationnelles qui sont

  2. Component-Based QoS-Driven Synthesis of High Assurance Embedded Software, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — Software is an integral part of many complex embedded systems, such as avionics, scientific exploration, and on-board systems. However, poor software reliability is...

  3. DIAGNOSTIC/PROGNOSTIC EXPERIMENTS FOR CAPACITOR DEGRADATION AND HEALTH MONITORING IN DC-DC CONVERTERS

    Data.gov (United States)

    National Aeronautics and Space Administration — Studying and analyzing the ageing mechanisms of electronic components avionics in systems such as the GPS and INAV are of critical importance. In DC-DC power...

  4. Model-Checking of Component-Based Event-Driven Real-Time Embedded Software

    National Research Council Canada - National Science Library

    Gu, Zonghua; Shin, Kang G

    2005-01-01

    .... We discuss application of model-checking to verify system-level concurrency properties of component-based real-time embedded software based on CORBA Event Service, using Avionics Mission Computing...

  5. Man's role in integrated control and information management systems

    Science.gov (United States)

    Nevins, J. L.; Johnson, I. S.

    1972-01-01

    Display control considerations associated with avionics techniques are discussed. General purpose displays and a prototype interactive display/command design featuring a pushplate CRT overlay for command input are considered.

  6. NAMMA DC-8 NAVIGATION AND HOUSEKEEPING (ICATS) V1

    Data.gov (United States)

    National Aeronautics and Space Administration — The NAMMA DC-8 Navigation and Housekeeping (ICATS) dataset is designed to: 1) interface and process avionics and environmental paramaters from the Navigational...

  7. NAMMA DC-8 NAVIGATION AND HOUSEKEEPING (ICATS) V1

    Data.gov (United States)

    National Aeronautics and Space Administration — The NAMMA DC-8 Information Collection and Transmission System (ICATS) is designed to: 1) interface and process avionics and environmental paramaters from the...

  8. CAMEX-4 DC-8 INFORMATION COLLECTION AND TRANSMISSION SYSTEM V1

    Data.gov (United States)

    National Aeronautics and Space Administration — The Camex-4 DC-8 Information Collection and Transmission System (ICATS) is designed to: 1) interface and process avionics and environmental paramaters from the...

  9. Lithographically-Scribed Planar Holographic Optical CDMA Devices and Systems

    National Research Council Canada - National Science Library

    Mossberg, Thomas

    2007-01-01

    .... The present Phase II effort has harnessed new fabrication tools to perfect disruptive HBR-based multiplexer products for DoD avionics, optical communications systems computer data communications and local area networks...

  10. Ada Linear-Algebra Program

    Science.gov (United States)

    Klumpp, A. R.; Lawson, C. L.

    1988-01-01

    Routines provided for common scalar, vector, matrix, and quaternion operations. Computer program extends Ada programming language to include linear-algebra capabilities similar to HAS/S programming language. Designed for such avionics applications as software for Space Station.

  11. Next generation space interconnect research and development in space communications

    Science.gov (United States)

    Collier, Charles Patrick

    2017-11-01

    Interconnect or "bus" is one of the critical technologies in design of spacecraft avionics systems that dictates its architecture and complexity. MIL-STD-1553B has long been used as the avionics backbone technology. As avionics systems become more and more capable and complex, however, limitations of MIL-STD-1553B such as insufficient 1 Mbps bandwidth and separability have forced current avionics architects and designers to use combination of different interconnect technologies in order to meet various requirements: CompactPCI is used for backplane interconnect; LVDS or RS422 is used for low and high-speed direct point-to-point interconnect; and some proprietary interconnect standards are designed for custom interfaces. This results in a very complicated system that consumes significant spacecraft mass and power and requires extensive resources in design, integration and testing of spacecraft systems.

  12. Recent Projects in the KSC Applied Physics Lab

    Science.gov (United States)

    Starr, Stanley

    2013-01-01

    Topics include: Shuttle heritage; ISRU /RESOLVE: a) Payload for Lunar Lander/Rover on Polar Areas of Moon. b) Avionics/Software. New Technologies for Exploration: a) Radiation Shielding work. b) Cooperative Tractor Beams.

  13. High Spatial Resolution shape Sensing for Adaptive Aerospace Vehicles, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — It is accepted that adaptive aerospace vehicles whose flight avionic systems are reconfigurable are needed to respond to changing flight parameters, vehicle system...

  14. FIRE_AX_SOF_ARAT_FLT

    Data.gov (United States)

    National Aeronautics and Space Administration — First ISCCP Regional Experiment (FIRE) ASTEX Surface of the Ocean, Fluxes and Interaction with the Atmosphere (SOFIA) Avion de Recherche Atmospherique (ARAT) Fokker...

  15. FIRE_AX_SOF_ARAT_TRB

    Data.gov (United States)

    National Aeronautics and Space Administration — First ISCCP Regional Experiment (FIRE) ASTEX Surface of the Ocean, Fluxes and Interaction with the Atmosphere (SOFIA) Avion de Recherche Atmospherique (ARAT) Fokker...

  16. A Self-Regulating Freezable Heat Exchanger for Spacecraft Project

    Data.gov (United States)

    National Aeronautics and Space Administration — A spacecraft thermal control system must keep the vehicle, avionics and atmosphere (if crewed) within a defined temperature range. Since water is non-toxic and good...

  17. Stress Studies at Kennedy Space Center: a Backward and Forward Look

    Science.gov (United States)

    Decker, A. I.

    1971-01-01

    Possible relationships between occupational and other stresses on ischemic heart disease are explored. Three procedures were used: (1) double master 2-step test, (2) dynamic ECG technique using avionics equipment, and (3) submaximal stress testing with Marco bicycle ergometer.

  18. A Self-Regulating Freezable Heat Exchanger for Spacecraft, Phase II

    Data.gov (United States)

    National Aeronautics and Space Administration — A spacecraft thermal control system must keep the vehicle, avionics and atmosphere (if crewed) within a defined temperature range. Since water is non-toxic and good...

  19. PEAC: A Power-Efficient Adaptive Computing Technology for Enabling Swarm of Small Spacecraft and Deployable Mini-Payloads

    Data.gov (United States)

    National Aeronautics and Space Administration — This task is to develop and demonstrate a path-to-flight and power-adaptive avionics technology PEAC (Power Efficient Adaptive Computing). PEAC will enable emerging...

  20. Improved UAS Robustness through Augmented Onboard Intelligence, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — This work will focus on the development of a highly capable avionics subsystem and machine learning algorithms to provide early warning of potential failures of...

  1. Software and Tools for Electronics Printing in Space(STEPS), Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — We are proposing an to develop a direct write electronics and avionics printing capability within the Techshot BioFabrication Facility currently funded and...

  2. Bayesian Framework Approach for Prognostic Studies in Electrolytic Capacitor under Thermal Overstress Conditions

    Data.gov (United States)

    National Aeronautics and Space Administration — Electrolytic capacitors are used in several applications rang- ing from power supplies for safety critical avionics equipment to power drivers for electro-mechanical...

  3. Physics Based Electrolytic Capacitor Degradation Models for Prognostic Studies under Thermal Overstress

    Data.gov (United States)

    National Aeronautics and Space Administration — Electrolytic capacitors are used in several applications rang- ing from power supplies on safety critical avionics equipment to power drivers for electro-mechanical...

  4. Fellowship | Indian Academy of Sciences

    Indian Academy of Sciences (India)

    Specialization: Cosmic Rays, Space Physics, Space Technology, Space Applications, Space Science, Avionics, Electronics, Interplanetary Physics, Satellite & Rocket Technology, High Energy Astronomy Last known address: Chairman, PRL Council, Department of Space, Antariksh Bhavan, New BEL Road, Bengaluru 560 ...

  5. Towards Prognostics for Electronics Components

    Data.gov (United States)

    National Aeronautics and Space Administration — Electronics components have an increasingly critical role in avionics systems and in the development of future aircraft systems. Prognostics of such components is...

  6. COARSE: Convex Optimization based autonomous control for Asteroid Rendezvous and Sample Exploration, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — Sample return missions, by nature, require high levels of spacecraft autonomy. Developments in hardware avionics have led to more capable real-time onboard computing...

  7. Radiation Mitigation Methods for Reprogrammable FPGA, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — One of the needs of NASA is the development of avionic systems and components that have the capability to operate in extreme radiation and temperature environments...

  8. Pilot visual acquisition of traffic : operational communications from air traffic control operational communication.

    Science.gov (United States)

    2001-05-01

    Avionics devices designed to provide pilots with graphically displayed traffic information will enable pilots to acquire and verify the identity of any intruder aircraft within the general area, either before or in accordance with a controller-issued...

  9. Improved Design of Radiation Hardened, Wide-Temperature Analog and Mixed-Signal Electronics, Phase II

    Data.gov (United States)

    National Aeronautics and Space Administration — NASA space exploration missions require the electronics for avionic systems, components, and controllers that are capable of operating in the extreme temperature and...

  10. Prof. Udipi Ramachandra Rao

    Indian Academy of Sciences (India)

    Specialization: Cosmic Rays, Space Physics, Space Technology, Space Applications, Space Science, Avionics, Electronics, Interplanetary Physics, Satellite & Rocket Technology, High Energy Astronomy Last known address: Chairman, PRL Council, Department of Space, Antariksh Bhavan, New BEL Road, Bengaluru 560 ...

  11. The cooling of printed circuit board mounted components using copper ladder heat conduction to a cold wall

    Science.gov (United States)

    Dale, I. C.

    1982-09-01

    A series of experimental tests, designed to investigate the cooling of printed circuit board (PCB) mounted dual-in-line (DIL) components within an avionic box using the copper ladder/cold wall technique is described. Areas of investigation include avionic box orientation, side wall conduction, top plate finning, mixed air-wash, avionic power reduction, cooling air temperature reduction, cooling air mass flow rate reduction, cold wall heat pick-up and avionic box insulation. Results were obtained from thermocouple temperature measurements. The use of an aluminum alloy interplate to cool two adjacent PCBs is discussed. Results in graphic form are included together with a list of conclusions on the effects of all the major parameters considered.

  12. 100TH T-38C Delivery Ceremony (Defense Acquisition Review Journal)

    National Research Council Canada - National Science Library

    Ott, David D; Davis, James B

    2002-01-01

    In 2000, the United States Air Force T-38 Avionics Upgrade System Program Office began to pursue Lean initiatives to reduce out-year program cost and delivery risk at the Boeing T-38C Upgrade facility...

  13. Catalog of Resources for Education in Ada (Trade Name) and Software Engineering (CREASE). Version 4.0.

    Science.gov (United States)

    1986-05-01

    Government Avionics Division 400 Collins Road, N.E Cedar Rapids, Iowa 52498 lnstructo(s) Helen Romanowsky , BS, MS Computer Science hicing information...further information contact Helen E. Romanowsky at telephone (319)395-3868. The best time to call is 8:00 - 4:00 p.m. CST. Rockwell International...Rockwell International Collins Government Avionics Division 400 Collins Road N.E. Cedar Rapids, Iowa 52498 Instructor(s) Helen E. Romanowsky , BS, MS

  14. Defense Acquisition Research Journal. Volume 23, Number 1, Issue 76, January 2016

    Science.gov (United States)

    2016-04-21

    on a complex integrated avionics system to reduce the aircrew size to two pilots and a cargo loadmaster. By comparison the C-141 and the C-5 use two... Integration Avionics is a term that covers the myriad of ultrarefined electronic devices on which moder n air planes rely. (Newhouse, 1982) On the C...Human Systems Integration on system development life-cycle cost and schedule. p. vii DAU Alumni Association p. viii From the Chairman and Executive

  15. Structuring Formal Requirements Specifications for Reuse and Product Families

    Science.gov (United States)

    Heimdahl, Mats P. E.

    2001-01-01

    In this project we have investigated how formal specifications should be structured to allow for requirements reuse, product family engineering, and ease of requirements change, The contributions of this work include (1) a requirements specification methodology specifically targeted for critical avionics applications, (2) guidelines for how to structure state-based specifications to facilitate ease of change and reuse, and (3) examples from the avionics domain demonstrating the proposed approach.

  16. Time-Triggered Ethernet Metamodel: Design and Application

    OpenAIRE

    Robati , Tiyam; El Kouhen , Amine; Gherbi , Abdelouahed; Mullins , John

    2016-01-01

    International audience; The combination of the SAE Time Triggered Ethernet (TTEthernet) standard with the Integrated Modular Avionics (IMA) architectures supports the design, deployment and integration of mixed-critical avionic applications. In order to cope with the complexity of these tasks, we advocate for a model-driven engineering methodology. The key element of such methodology is the modeling language, which enables producing relevant models of the system. In this paper, we present a m...

  17. Cruise Missile Penaid Nonproliferation: Hindering the Spread of Countermeasures Against Cruise Missile Defenses

    Science.gov (United States)

    2014-01-01

    energy thermal radiation, and laser dazzling . Add coverage for items usable for any UAVs. 37 Th e MTCR Annex already includes items for hardening...2004. Acoustic Laser /electronic support/ radar warning receiver Redundant comm. bus Redundant flight controller and navigation sensors...Penaid Nonproliferation 1. Supersonic/Low Altitude Avionics MTCR Item 11.A.1 (Avionics): Current text: “Radar and laser radar systems, including

  18. Requirements analysis notebook for the flight data systems definition in the Real-Time Systems Engineering Laboratory (RSEL)

    Science.gov (United States)

    Wray, Richard B.

    1991-01-01

    A hybrid requirements analysis methodology was developed, based on the practices actually used in developing a Space Generic Open Avionics Architecture. During the development of this avionics architecture, a method of analysis able to effectively define the requirements for this space avionics architecture was developed. In this methodology, external interfaces and relationships are defined, a static analysis resulting in a static avionics model was developed, operating concepts for simulating the requirements were put together, and a dynamic analysis of the execution needs for the dynamic model operation was planned. The systems engineering approach was used to perform a top down modified structured analysis of a generic space avionics system and to convert actual program results into generic requirements. CASE tools were used to model the analyzed system and automatically generate specifications describing the model's requirements. Lessons learned in the use of CASE tools, the architecture, and the design of the Space Generic Avionics model were established, and a methodology notebook was prepared for NASA. The weaknesses of standard real-time methodologies for practicing systems engineering, such as Structured Analysis and Object Oriented Analysis, were identified.

  19. Information report presented in application of article 145 of the regulation by the commission of national defense and armed forces about the propulsion system of the second aircraft carrier; Rapport d'information depose en application de l'article 145 du reglement par la commission de la defense nationale et des forces armees sur le mode de propulsion du second porte-avions

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    2003-11-01

    In the framework of the project of launching of a sister-ship to the Charles de Gaulle aircraft carrier, this report makes an objective analysis of the different possible propulsion systems that can be considered for this battle ship according to different criteria: 1 - two possible energy sources and four possible configurations of aircraft carrier considered: alternative between nuclear propulsion and conventional propulsion, the two nuclear ships eventualities, the hypothesis of an entirely French-made classical propulsion ship, the opportunity of a French-British cooperation for a conventional aircraft carrier project; 2 - decision criteria: operational need, cost, industrial and technological stakes, constraints linked with daily ship and crew life; 3 - propulsion systems alternative: conventional propulsion and reinforcement of the European defense policy, nuclear propulsion for an operational superiority and for a complementarity with the Charles de Gaulle. (J.S.)

  20. Investigación de las causas que con llevan a la creación de rajaduras y/o fisuras en las cámaras de combustión de los motores AI-20D serie 5 de los aviones turbo hélice antonov de la M.G.P. y desarrollo del proceso de su soldadura por microplasma

    OpenAIRE

    Angulo Rebaza, Cesar Adolfo; Angulo Rebaza, Cesar Adolfo

    2000-01-01

    La seguridad de los vuelos con respecto al material aeronáutico está condicionado por la confiabilidad de los principales conjuntos, y accesorios, incluyendo las cámaras de combustión de los motores aeronáuticos. Para resolver las tareas propuestas se ha efectuado investigaciones del proceso de desgastamiento del material de la cámara de combustión del MTH AI-20D SERIE 5 en el proceso de operación en las condiciones geográficas del Perú La construcción de la cámara de combustión (Fig. 1...

  1. Dosimetry and microdosimetry using Let spectrometer based on the track-etch detector: radiotherapy Bremsstrahlung beam, onboard aircraft radiation field; Dosimetrie et micro-dosimetrie au moyen d'un spectrometre a transfert lineique d'energie base sur des detecteurs solides de traces: mesure dans un faisceau de rayonnement X de radiotherapie et du champ de rayonnement a bord d'avion

    Energy Technology Data Exchange (ETDEWEB)

    Jadrneckova, I.; Spurny, F. [Nuclear Physics Institute AS CR, Dept. of Radiation Dosimetry, Prague (Czech Republic); Jadrneckova, I. [Czech Technical Univ., Dept. of Dosimetry and Application of Ionizing Radiation, Prague (Czech Republic)

    2006-10-15

    The spectrometer of linear energy transfer (LET) based on the chemically etched poly-allyl-diglycol-carbonate (PADC) track-etch detector was developed several years ago in our institute. LET spectra are estimated through track parameters determination carried out by an automatic optical image analyzer LUCIA G. This LET spectrometer enables determining LET of particles approximately from 10 to 700 keV/{mu}m. From the LET spectra, dose characteristics can be calculated. This contribution presents the use of this spectrometer in some applications - studies in 18 MV radiotherapy Bremsstrahlung beam and investigation onboard a commercial aircraft during more than 6 months long exposure. The LET spectra obtained in both experiments represent mainly the contribution of secondary or tertiary particles created through the nuclear reactions of photons (Bremsstrahlung beam) or neutrons and neutron-like reacting particles (onboard aircraft) in the detector itself or in the surroundings material. The dose due to the photo-particles represents about 3 x 10{sup -4} of the photon dose; for the dose equivalent this value is about 2 x 10{sup -3} Sv/Gy. Regarding the onboard aircraft exposure, the results obtained using LET spectrometer were compared with those achieved with other methods and a reasonable agreement were stated. (authors)

  2. Results from an Interval Management (IM) Flight Test and Its Potential Benefit to Air Traffic Management Operations

    Science.gov (United States)

    Baxley, Brian; Swieringa, Kurt; Berckefeldt, Rick; Boyle, Dan

    2017-01-01

    NASA's first Air Traffic Management Technology Demonstration (ATD-1) subproject successfully completed a 19-day flight test of an Interval Management (IM) avionics prototype. The prototype was built based on IM standards, integrated into two test aircraft, and then flown in real-world conditions to determine if the goals of improving aircraft efficiency and airport throughput during high-density arrival operations could be met. The ATD-1 concept of operation integrates advanced arrival scheduling, controller decision support tools, and the IM avionics to enable multiple time-based arrival streams into a high-density terminal airspace. IM contributes by calculating airspeeds that enable an aircraft to achieve a spacing interval behind the preceding aircraft. The IM avionics uses its data (route of flight, position, etc.) and Automatic Dependent Surveillance-Broadcast (ADS-B) state data from the Target aircraft to calculate this airspeed. The flight test demonstrated that the IM avionics prototype met the spacing accuracy design goal for three of the four IM operation types tested. The primary issue requiring attention for future IM work is the high rate of IM speed commands and speed reversals. In total, during this flight test, the IM avionics prototype showed significant promise in contributing to the goals of improving aircraft efficiency and airport throughput.

  3. An overview of autonomous rendezvous and docking system technology development at General Dynamics

    Science.gov (United States)

    Kuenzel, Fred

    The Centaur avionics suite is undergoing a dramatic modernization for the commercial, DoD Atlas and Titan programs. The system has been upgraded to the current state-of-the-art in ring laser gyro inertial sensors and Mil-Std-1750A processor technology. The Cruise Missile avionic system has similarly been evolving for many years. Integration of GPS into both systems has been underway for over five years with a follow-on cruise missile system currently in flight test. Rendezvous and Docking related studies have been conducted for over five years in support of OMV, CTV, and Advanced Upper Stages, as well as several other internal IR&D's. The avionics system and AR&D simulator demonstrated to the SATWG in November 1990 has been upgraded considerably under two IR&D programs in 1991. The Centaur modern avionics system is being flown in block upgrades which started in July of 1990. The Inertial Navigation Unit will fly in November of 1991. The Cruise Missile avionics systems have been fully tested and operationally validated in combat. The integrated AR&D system for space vehicle applications has been under development and testing since 1990. A Joint NASA / GD ARD&L System Test Program is currently being planned to validate several aspects of system performance in three different NASA test facilities in 1992.

  4. A Comparison of Bus Architectures for Safety-Critical Embedded Systems

    Science.gov (United States)

    Rushby, John; Miner, Paul S. (Technical Monitor)

    2003-01-01

    We describe and compare the architectures of four fault-tolerant, safety-critical buses with a view to deducing principles common to all of them, the main differences in their design choices, and the tradeoffs made. Two of the buses come from an avionics heritage, and two from automobiles, though all four strive for similar levels of reliability and assurance. The avionics buses considered are the Honeywell SAFEbus (the backplane data bus used in the Boeing 777 Airplane Information Management System) and the NASA SPIDER (an architecture being developed as a demonstrator for certification under the new DO-254 guidelines); the automobile buses considered are the TTTech Time-Triggered Architecture (TTA), recently adopted by Audi for automobile applications, and by Honeywell for avionics and aircraft control functions, and FlexRay, which is being developed by a consortium of BMW, DaimlerChrysler, Motorola, and Philips.

  5. Orion FSW V and V and Kedalion Engineering Lab Insight

    Science.gov (United States)

    Mangieri, Mark L.

    2010-01-01

    NASA, along with its prime Orion contractor and its subcontractor s are adapting an avionics system paradigm borrowed from the manned commercial aircraft industry for use in manned space flight systems. Integrated Modular Avionics (IMA) techniques have been proven as a robust avionics solution for manned commercial aircraft (B737/777/787, MD 10/90). This presentation will outline current approaches to adapt IMA, along with its heritage FSW V&V paradigms, into NASA's manned space flight program for Orion. NASA's Kedalion engineering analysis lab is on the forefront of validating many of these contemporary IMA based techniques. Kedalion has already validated many of the proposed Orion FSW V&V paradigms using Orion's precursory Flight Test Article (FTA) Pad Abort 1 (PA-1) program. The Kedalion lab will evolve its architectures, tools, and techniques in parallel with the evolving Orion program.

  6. Savremeno naoružanje i vojna oprema za broj 4/2013

    Directory of Open Access Journals (Sweden)

    Mladen R. Tišma

    2013-12-01

    Full Text Available Višenamenski borbeni avion MiG-29M/M2 preimenovan u MiG-35/D; Tekstron razvija laki jurišnik i izviđač; Boing i Saab o mogućnosti da ponude Gripen na konkursu T-X za novi avion za obuku američkog ratnog vazduhoplovstva; Predstavljena trenažna verzija ruskog borbenog helikoptera Mi-28; Nemački Evrofajteri dobijaju sposobnost za lovačko-bombarderska dejstva tek 2017. godine; Prikazan prototip S-350 Vitjaz, novog ruskog raketnog sistema za protivvazduhoplovnu odbranu; Poljskom RV-u isporučeni prvi modernizovani lovci MiG-29; Počela proizvodnja argentinskih školsko-borbenih aviona IA-63 Pampa III; Kineska borbena bespilotna letelica spremna za letna opitivanja; Helikopter Mi-8MSB oborio visinski rekord; Turski školski avion HÜRKUŞ izveo prvi let.

  7. Analyse experimentale des performances d'une batterie au lithium pour l'aeronautique

    Science.gov (United States)

    Bonnin, Romain

    Ce memoire a pour objectif d'identifier et d'etudier les performances necessaires pour qu'une batterie au lithium puisse etre utilisee dans le secteur de l'aeronautique. C'est pourquoi dans le cadre de notre recherche, nous allons proposer une procedure de tests permettant d'analyser et de determiner si la batterie au lithium peut etre implantee dans un avion. En vue de repondre a l'analyse des performances, une etude des fonctionnalites demandees par l'avion ainsi que des normes preexistantes vont etre effectuees. Suite a cette etape, nous allons elaborer un banc d'essais. Une fois le banc d'essais acheve, nous allons tester une batterie au lithium qui est supposee disposer de toutes les caracteristiques techniques requises pour etre implantee dans un avion. Ces tests nous permettront donc d'emettre un avis sur l'utilisation des batteries au lithium dans le domaine de l'aeronautique.

  8. Présentation de DEBATS (Discussion sur les Effets du Bruit des Aéronefs Touchant la Santé).

    OpenAIRE

    EVRARD, Anne-Sophie; BOUAOUN, Liacine; LEFEVRE, Marie; CHAMPELOVIER, Patricia; LAMBERT, Jacques; LAUMON, Bernard

    2014-01-01

    INTRODUCTION – L’exposition au bruit des avions pourrait avoir des conséquences importantes pour la santé. Toutefois, celles-ci sont actuellement insuffisamment évaluées, tout du moins en France. La DGS en collaboration avec l’Acnusa a donc sollicité l’Ifsttar pour mettre en place un programme de recherche épidémiologique appelé DEBATS. OBJECTIF – L’objectif est de mieux connaître et d’évaluer les effets du bruit des avions sur la santé des riverains...

  9. Impacts du bruit sur la santé, présentation du projet DEBATS (Discussion sur les Effets du Bruit des Aéronefs Touchant la Santé).

    OpenAIRE

    EVRARD, Anne-Sophie; KHATI, Inès; LAUMON, Bernard; CHAMPELOVIER, Patricia; LAMBERT, Jacques

    2012-01-01

    L’exposition au bruit des avions pourrait avoir des conséquences importantes pour la santé. Toutefois, celles-ci sont actuellement insuffisamment évaluées, tout du moins en France. La DGS en collaboration avec l’Acnusa a donc sollicité l’Ifsttar pour mettre en place un programme de recherche épidémiologique appelé DEBATS. L'objectif est de mieux connaître et mieux quantifier les effets du bruit des avions sur la santé en adoptant une approche globale caractérisant les relati...

  10. An Ada Linear-Algebra Software Package Modeled After HAL/S

    Science.gov (United States)

    Klumpp, Allan R.; Lawson, Charles L.

    1990-01-01

    New avionics software written more easily. Software package extends Ada programming language to include linear-algebra capabilities similar to those of HAL/S programming language. Designed for such avionics applications as Space Station flight software. In addition to built-in functions of HAL/S, package incorporates quaternion functions used in Space Shuttle and Galileo projects and routines from LINPAK solving systems of equations involving general square matrices. Contains two generic programs: one for floating-point computations and one for integer computations. Written on IBM/AT personal computer running under PC DOS, v.3.1.

  11. System data communication structures for active-control transport aircraft, volume 2

    Science.gov (United States)

    Hopkins, A. L.; Martin, J. H.; Brock, L. D.; Jansson, D. G.; Serben, S.; Smith, T. B.; Hanley, L. D.

    1981-01-01

    The application of communication structures to advanced transport aircraft are addressed. First, a set of avionic functional requirements is established, and a baseline set of avionics equipment is defined that will meet the requirements. Three alternative configurations for this equipment are then identified that represent the evolution toward more dispersed systems. Candidate communication structures are proposed for each system configuration, and these are compared using trade off analyses; these analyses emphasize reliability but also address complexity. Multiplex buses are recognized as the likely near term choice with mesh networks being desirable for advanced, highly dispersed systems.

  12. Advanced fighter technology integration (AFTI)/F-16 Automated Maneuvering Attack System final flight test results

    Science.gov (United States)

    Dowden, Donald J.; Bessette, Denis E.

    1987-01-01

    The AFTI F-16 Automated Maneuvering Attack System has undergone developmental and demonstration flight testing over a total of 347.3 flying hours in 237 sorties. The emphasis of this phase of the flight test program was on the development of automated guidance and control systems for air-to-air and air-to-ground weapons delivery, using a digital flight control system, dual avionics multiplex buses, an advanced FLIR sensor with laser ranger, integrated flight/fire-control software, advanced cockpit display and controls, and modified core Multinational Stage Improvement Program avionics.

  13. An Analysis of the Speed Commands from an Interval Management Algorithm during the ATD-1 Flight Test

    Science.gov (United States)

    Watters, Christine; Wilson, Sara R.; Swieringa, Kurt A.

    2017-01-01

    NASA's first Air Traffic Management Technology Demonstration (ATD-1) successfully completed a nineteen-day flight test under a NASA contract with Boeing, with Honeywell and United Airlines as sub-contractors. An Interval Management (IM) avionics prototype was built based on international IM standards, integrated into two test aircraft, and then flown in real-world conditions to determine if the goals of improving aircraft efficiency and airport throughput during high-density arrival operations could be met. This paper describes the speed behavior of the IM avionics prototype, focusing on the speed command rate and the number of speed increases.

  14. Flight Simulation.

    Science.gov (United States)

    1986-09-01

    des simulateurs install~s au sol et as bord des avions. Egalement une large utilisation des simulateurs de vol a &6 faite pour Ia...actualisc& de lNtat de Ia technologic et de l’ing~nierie des simulateurs install~s au sol ou is bord des avions et de les placer dans le contexte de ceurs...guidage o de la taille doun reticule. Ce petit tableau de clefs not dote domne puissance magiqlue, grace as logiciel cooco

  15. Subsystem Testing and Flight Test Instrumentation.

    Science.gov (United States)

    1981-04-01

    fonctionnement dui moteur . Les deux versions, 6colo ot appui tactique do l’avion ALPHAJET ont des form.. do no: diff~rentes (planche 1). Grace A une 6tude...parambtres habituela de vol. et notamnment ceux repr~sentant lea performances (r~gime ro- tr-r, r~gimes moteurs , temp ~ratures mnoteurs, couples, vitesse...MISS DISTANCE INDICATOR 4 by T.W.Chubb t0 COMPATIBILITE DU MOTEUR AVEC LES AUTRES SYSTEMES DE L’AVION par J.Conche I I FUEL SYSTEM TESTING AND TEST

  16. Desarrollo de los métodos de integración G.P.S/S.I.N. con la finalidad de aumentar la exactitud en la navegación

    OpenAIRE

    Alvarado Torres, Wilson Emilio; Alvarado Torres, Wilson Emilio

    2001-01-01

    El mundo moderno a desarrollado el programa LRCSW (Long-Range Conventional Standel Weapon). Este programa fue el encargado de estudiar, desarrollar y probar un vehículo llamado MC LRCSW (MC Tomahawk) también conocido como "Misil de Crucero de Alta Exactitud de Baja Altura (MCAEBA)". Este misil con la configuraci6n de navegaci6n descrita a continuaci6n se instal6 en 1995 en aviones B-52, porta aviones, submarinos y buques. La ruta de vuelo del MCAEBA se divide en dos partes: La parte ope...

  17. Methode de conception dirigee par les modeles pour les systemes avioniques modulaires integres basee sur une approche de cosimulation

    Science.gov (United States)

    Bao, Lin

    In the aerospace industry, with the development of avionic systems becomes more and more complex, the integrated modular avionics (IMA) architecture was proposed to replace its predecessor - the federated architecture, in order to reduce the weight, power consumption and the dimension of the avionics equipment. The research work presented in this thesis, which is considered as a part of the research project AVIO509, aims to propose to the aviation industry a set of time-effective and cost-effective solutions for the development and the functional validation of IMA systems. The proposed methodologies mainly focus on two design flows that are based on: 1) the concept of model-driven engineering design and 2) a cosimulation platform. In the first design flow, the modeling language AADL is used to describe the IMA architecture. The environment OCARINA, a code generator initially designed for POK, was modified so that it can generate avionic applications from an AADL model for the simulator SIMA (an IMA simulator compliant to the ARINC653 standards). In the second design flow, Simulink is used to simulate the external world of IMA module thanks to the availability of avionic library that can offer lots of avionics sensors and actuators, and as well as its effectiveness in creating the Simulink models. The cosimulation platform is composed of two simulators: Simulink for the simulation of peripherals and SIMA for the simulation of IMA module, the latter is considered as an ideal alternative for the super expensive commercial development environment. In order to have a good portability, a SIMA partition is reserved as the role of " adapter " to synchronize the communication between these two simulators via the TCP/IP protocol. When the avionics applications are ported to the implementation platform (such as PikeOS) after the simulation, there is only the " adapter " to be modified because the internal communication and the system configuration are the same. An avionics

  18. 2015-2016 Travel and Hospitality Expense Reports for Joanne ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Ottawa. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 0.00 $. Frais de logement. 0.00 $. Repas et frais divers. 73.66 $. Autre frais. 0.00 $. Total. 73.66 $. Commentaires. 2015-2016 Travel and Hospitality Expense. Reports for Joanne Charette, Vice-President,. Corporate Strategy and Communications.

  19. Hangar con alas, Los Angeles

    Directory of Open Access Journals (Sweden)

    Editorial, Equipo

    1961-04-01

    Full Text Available Formando parte de su programa, la TWA ha construido recientemente un hangar para servicio y reparaciones de su flota aérea de naves ordinarias y de aviones de reacción en el aeropuerto internacional de Los Angeles (Estados Unidos. El proyecto de esta obra se encargó a la empresa constructora Holmes & Narver, Inc.

  20. Validation of Flight Critical Control Systems

    Science.gov (United States)

    1991-12-01

    1985. [8] Avizienis, A., and Lyu, M., "On the Effectiveness of Multiversion Software in Digital Avionics", AIAA Computers in Aerospace VI Conference...Experimentation and Modelling. NASA CR-165036, 1982. [12] Eckhardt, D. E.; and Lee, L. D.: A Theoretical Basis for the Analysis of Multiversion

  1. Pramana – Journal of Physics | Indian Academy of Sciences

    Indian Academy of Sciences (India)

    Article ID 1 Regular. Energy distribution of cosmic rays in the Earth's atmosphere and avionic area using Monte Carlo codes · MOHAMED M OULD DIB A S A BELBACHIR A H · More Details Abstract Fulltext PDF. Cosmic rays cause significant damage to the electronic equipments of the aircrafts. In this paper, we have ...

  2. Continuing Efforts to Upgrade the Aeronautics Curriculum at Jacksonville University

    Science.gov (United States)

    Terrell, Jerry L.; Merkt, Juan; Harrison, Jeffrey; Yates, Rhett

    2012-01-01

    The aviation industry is exceptionally dynamic. Advances in technology have enabled the industry to change drastically in a short period of time. The transition to jet propulsion advances in aerodynamics, avionics improvements, and introduction of revolutionary navigation systems have all occurred within the past 60 years. These advances have…

  3. Combat Aircraft Maneuverability.

    Science.gov (United States)

    1981-12-01

    permet des gains apectacu- laires. En parallble, l’amdliaration du rapport poussde/poids (voir Fig. 5) qui tend A devenir sup~rieur A 1 A basse altitude...c’est-A-dire qu’un r~sultet trouv6 marginal en soufflarie peut se dft~riorer et devenir mauvais en grandeur ; - en ce put concerne lee avions

  4. Hierarchical Scheduling Framework Based on Compositional Analysis Using Uppaal

    DEFF Research Database (Denmark)

    Boudjadar, Jalil; David, Alexandre; Kim, Jin Hyun

    2014-01-01

    , which are some of the inputs for the parameterized timed automata that make up the framework. Components may have different scheduling policies, and each component is analyzed independently using Uppaal. We have applied our framework for the schedulability analysis of an avionics system....

  5. OPTIMAL GUARANTEED SERVICES TIMED TOKEN (OGSTT ...

    African Journals Online (AJOL)

    eobe

    automation, embedded real-time distributed systems, space vehicle systems, and the integration of expert systems into avionics and industrial process controls. The situation has placed an increasing demand for effective and efficient multi- services local area networks. Such networks' MAC protocols must deal with different ...

  6. 78 FR 17187 - Notice of Availability of Government-Owned Inventions; Available for Licensing

    Science.gov (United States)

    2013-03-20

    ... 16, 2012// U.S. Patent Number 8,306,689: Integrated net-centric diagnostics dataflow for avionics..., Technology Transfer Office, 22473 Millstone Road, Building 505, Patuxent River, MD 20670, 301-342-1133. FOR... Millstone Road, Building 505, Patuxent River, MD 20670, 301-342-1133. SUPPLEMENTARY INFORMATION: The DoN...

  7. 76 FR 37796 - Notice of Availability of Government-Owned Inventions; Available for Licensing

    Science.gov (United States)

    2011-06-28

    .../554,147: Integrated Net-Centric Diagnostics Dataflow for Avionics System, Navy Case No. 98492, filed..., Building 505, 22473 Millstone Road, Patuxent River, MD 20670, 301-342- 5586 or e-mail [email protected], Patuxent River, MD 20670, 301-342-5586 or e-mail [email protected] . SUPPLEMENTARY INFORMATION: The U.S...

  8. Participation aux discussions organisées par Munk School of Global ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    (s):. 2016-01-26. Destination(s):. Toronto. Billet d'avion: 471.79 $. Frais de transport au sol ou autrement: 56.46 $. Frais de logement: 0.00 $. Repas et frais divers: 23.08 $. Autre frais: 0.00 $. Total: 551.33 $. Commentaires: 2015-2016 Rapports ...

  9. 14 CFR 431.25 - Application requirements for policy review.

    Science.gov (United States)

    2010-01-01

    ..., by the applicant. (b) Identify all vehicle systems, including structural, thermal, pneumatic, propulsion, electrical, and avionics and guidance systems used in the vehicle(s), and all propellants. (c... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LAUNCH AND REENTRY OF A REUSABLE LAUNCH VEHICLE (RLV...

  10. 75 FR 16646 - Airworthiness Directives; Bombardier, Inc. Model BD-100-1A10 (Challenger 300) Airplanes

    Science.gov (United States)

    2010-04-02

    ... been an incident during a production flight test where the proximity-sensor electronic unit (PSEU... Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Bruce Valentine, Aerospace Engineer, Avionics and Flight Test Branch, ANE-172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue...

  11. 75 FR 52233 - Airworthiness Directives; Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440...

    Science.gov (United States)

    2010-08-25

    ... Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Bruce Valentine, Avionics and Flight Test Branch, ANE-172, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410..., introduces procedures for performing a stall protection system test. Operate the airplane according to the...

  12. 75 FR 31324 - Airworthiness Directives; Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440...

    Science.gov (United States)

    2010-06-03

    .... Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Bruce Valentine, Avionics and Flight Test Branch, ANE-172, FAA, New York Aircraft Certification Office (ACO), 1600... performing a stall protection system test. Operate the airplane according to the limitations and procedures...

  13. Fulltext PDF

    Indian Academy of Sciences (India)

    Energy distribution of cosmic rays in the Earth's atmosphere and avionic area using Monte. Carlo codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . M Ould Mohamed, A S A Dib and A H Belbachir. 1. Influence of nuclear dissipation on fission dynamics of the excited nucleus 248Cf within a stochastic approach .

  14. 75 FR 37712 - Automatic Dependent Surveillance-Broadcast (ADS-B) Out Performance Requirements To Support Air...

    Science.gov (United States)

    2010-06-30

    ... Dependent Surveillance--Broadcast (ADS-B) Out avionics on aircraft operating in Classes A, B, and C airspace, as well as certain other specified classes of airspace within the U.S. National Airspace System (NAS... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 91 [Docket No. FAA-2007...

  15. 75 FR 48552 - Automatic Dependent Surveillance-Broadcast (ADS-B) Out Performance Requirements To Support Air...

    Science.gov (United States)

    2010-08-11

    ... Dependent Surveillance-Broadcast (ADS-B) Out avionics on aircraft operating in Classes A, B, and C airspace, as well as certain other specified classes of airspace within the U.S. National Airspace System (NAS... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 91 [Docket No. FAA-2007...

  16. 78 FR 75285 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Flight...

    Science.gov (United States)

    2013-12-11

    ... issue a finding of regulatory adequacy under Sec. 611 of Public Law 92-574, the ``Noise Control Act of... have a novel or unusual design feature associated with an electronic flight control system that... turbofan engines. Flight controls are fly-by-wire flight with two passive/uncoupled side sticks. Avionics...

  17. 78 FR 75287 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Flight...

    Science.gov (United States)

    2013-12-11

    ... issue a finding of regulatory adequacy under Sec. 611 of Public Law 92-574, the ``Noise Control Act of... flight control system that provides flight envelope protections. The applicable airworthiness regulations... controls are fly-by-wire flight with two passive/uncoupled side sticks. Avionics includes five landscape...

  18. 78 FR 65231 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 series airplanes...

    Science.gov (United States)

    2013-10-31

    ... Law 92-574, the ``Noise Control Act of 1972.'' The FAA issues special conditions, as defined in 14 CFR... engines. Flight controls are fly-by-wire flight with two passive/uncoupled side sticks. Avionics include... series airplanes; Fuselage In-Flight Fire Safety and Flammability Resistance AGENCY: Federal Aviation...

  19. Regulatory Compliance in Multi-Tier Supplier Networks

    Science.gov (United States)

    Goossen, Emray R.; Buster, Duke A.

    2014-01-01

    Over the years, avionics systems have increased in complexity to the point where 1st tier suppliers to an aircraft OEM find it financially beneficial to outsource designs of subsystems to 2nd tier and at times to 3rd tier suppliers. Combined with challenging schedule and budgetary pressures, the environment in which safety-critical systems are being developed introduces new hurdles for regulatory agencies and industry. This new environment of both complex systems and tiered development has raised concerns in the ability of the designers to ensure safety considerations are fully addressed throughout the tier levels. This has also raised questions about the sufficiency of current regulatory guidance to ensure: proper flow down of safety awareness, avionics application understanding at the lower tiers, OEM and 1st tier oversight practices, and capabilities of lower tier suppliers. Therefore, NASA established a research project to address Regulatory Compliance in a Multi-tier Supplier Network. This research was divided into three major study efforts: 1. Describe Modern Multi-tier Avionics Development 2. Identify Current Issues in Achieving Safety and Regulatory Compliance 3. Short-term/Long-term Recommendations Toward Higher Assurance Confidence This report presents our findings of the risks, weaknesses, and our recommendations. It also includes a collection of industry-identified risks, an assessment of guideline weaknesses related to multi-tier development of complex avionics systems, and a postulation of potential modifications to guidelines to close the identified risks and weaknesses.

  20. AIMS, une expérience transformatrice | CRDI - Centre de recherches ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    22 janv. 2014 ... Nous avons rebaptisé AIMS « African Institute for Missing Sleep » (institut africain du manque de sommeil), parce que nous travaillions toute la nuit. Nous avions des ordinateurs à notre disposition, nous étions très motivés. Le Malawien Richard Junganiko Munthali participe à l'AIMS Industry Initiative, qui ...

  1. Evaluating real-time Java for mission-critical large-scale embedded systems

    Science.gov (United States)

    Sharp, D. C.; Pla, E.; Luecke, K. R.; Hassan, R. J.

    2003-01-01

    This paper describes benchmarking results on an RT JVM. This paper extends previously published results by including additional tests, by being run on a recently available pre-release version of the first commercially supported RTSJ implementation, and by assessing results based on our experience with avionics systems in other languages.

  2. 2015-2016 Rapports sur les frais de voyage et d'accueil pour Jean ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    (s). 2015-10-13 à 2015-10-14. Destination(s). Montréal. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 217.23 $. Frais de logement. 200.34 $. Repas et frais divers. 89.25 $. Autre frais. 0.00 $. Total. 506.82 $. Commentaires.

  3. Rapports 2017-2018 sur les frais de voyage pour Jean Lebel ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    SD

    (s). 2017-05-24 au 2017-05-25. Destination(s). Toronto. Billet d'avion. 265.32 $. Frais de transport au sol ou autrement. 59.69 $. Frais de logement. 236.65 $. Repas et frais divers. 68.04 $. Autre frais. 0.00 $. Total. 629.70 $. Commentaires.

  4. 2016-2017 Rapport sur les frais de voyage pour Monte Solberg, ex ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Billet d'avion. 1 209.63 $. Frais de transport au sol ou autrement. 158.36 $. Frais de logement. 590.10 $. Repas et frais divers. 38.42 $. Autre frais. 0.00 $. Total. 1 996.51 $. Commentaires. 2016-2017 Rapport sur les frais de voyage pour. Monte Solberg, ex-gouverneur.

  5. 2015-2016 Rapports sur les frais de voyage et d'accueil pour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    31 à 2015-09-15. Destination(s):. Zurich, London et Nairobi. Billet d'avion: 8 983.64 $. Frais de transport au sol ou autrement: 331.36 $. Frais de logement: 5 088.52 $. Repas et frais divers: 1 736.70 $. Autre frais: 59.00 $. Total: 16 199.22 $.

  6. 2015-2016 Rapports sur les frais de voyage et d'accueil pour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    -10-16 à 2015-10-21. Destination(s):. Beijing, Chine. Billet d'avion: 5 556.66 $. Frais de transport au sol ou autrement: 107.84 $. Frais de logement: 647.23 $. Repas et frais divers: 633.19 $. Autre frais: 144.81 $. Total: 7 089.73 $.

  7. Rapports 2016-2017 sur les frais de voyage pour Uri Rosenthal ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Billet d'avion. 5 981.69 $. Frais de transport au sol ou autrement. 296.45 $. Frais de logement. 393.40 $. Repas et frais divers. 120.80 $. Autre frais. 0.00 $. Total. 6 792.34 $. Commentaires. Rapports 2016-2017 sur les frais de voyage pour Uri Rosenthal, gouverneur.

  8. Rapports 2016-2017 sur les frais de voyage pour Uri Rosenthal ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    chantal taylor

    Billet d'avion. 5 791.85 $. Frais de transport au sol ou autrement. 346.42 $. Frais de logement. 463.24 $. Repas et frais divers. 120.80 $. Autre frais. 0.00 $. Total. 6 722.31 $. Commentaires. Rapports 2016-2017 sur les frais de voyage pour Uri Rosenthal, gouverneur.

  9. 2016-2017 Rapport sur les frais de voyage pour Stephen McGurk ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    s). 2016-06-21. Destination(s). Toronto. Billet d'avion. 232.04 $. Frais de transport au sol ou autrement. 118.84 $. Frais de logement. 0.00 $. Repas et frais divers. 0.00 $. Autre frais. 0.00 $. Total. 350.88 $. Commentaires. 2016-2017 Rapport ...

  10. 2016-2017 Rapport sur les frais de voyage pour Uri Rosenthal ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Billet d'avion. 6 065.80 $. Frais de transport au sol ou autrement. 282.55 $. Frais de logement. 393.40 $. Repas et frais divers. 107.43 $. Autre frais. 0.00 $. Total. 6 849.18 $. Commentaires. 2016-2017 Rapport sur les frais de voyage pour Uri Rosenthal, gouverneur.

  11. Defense AT&L (Volume 36, Number 4, July-August 2007)

    Science.gov (United States)

    2007-08-01

    Falcon Flex: Turning Maintenance Information into Air Power Kevin J. Berk “Can we improve the reliability and availability of F-16 avionics while...director at Headquarters Air Force Materiel Com- mand; Blaise Durante , deputy assistant secretary for Ac- quisition Integration, Office of the Assistant

  12. Air Force Next-Generation Bomber: Background and Issues for Congress

    Science.gov (United States)

    2009-12-22

    blended wing/body configuration, variable -geometry wings and turbofan afterburning engines, combine to provide long range, maneuverability and high...defensive avionics, EDO Corporation Power plant: Four General Electric F101-GE-102 turbofan engine with afterburner Thrust: 30,000-plus pounds with

  13. Conference P.Aimedieu

    CERN Multimedia

    Aimedieu,P

    1988-01-01

    Le conférencier parle de la pollution, du trou d'ozone et cite entre autre l'histoire qui commence dans les années 1970 quand les préoccupations des scientifics se sont focalisées sur les pollutions possibles des avions supersonics dans la stratosphère

  14. Rapports 2017-2018 sur les frais de voyage pour Margaret Ann ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Chantal Taylor

    -04-20 au 2017-04-22. Destination(s). Toronto. Billet d'avion. 608.31 $. Frais de transport au sol ou autrement. 0.00 $. Frais de logement. 0.00 $. Repas et frais divers. 0.00 $. Autre frais. 0.00 $. Total. 608.31 $. Commentaires. À partir de sa ...

  15. Electronics system design techniques for safety critical applications

    CERN Document Server

    Sterpone, Luca

    2008-01-01

    Addresses the development of techniques for the evaluation and the hardening of designs implemented on SRAM-based Field Programmable Gate Arrays. This title presents a design methodology solving industrial designer''s needs for implementing electronic systems using SRAM-based FPGAs in critical environments, like the space or avionic ones.

  16. Participation à la cérémonie de remise des prix Canada Gairdner ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    (s). 2016-10-27 au 2016-10-28. Destination(s). Toronto. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 553.35 $. Frais de logement. 219.25 $. Repas et frais divers. 87.19 $. Autre frais. 0.00 $. Total. 859.79 $. Commentaires.

  17. Foire aux questions sur la bourse du CRDI aux chercheurs ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    IDRC CRDI

    Est-ce que je peux utiliser une partie de la bourse pour payer son billet d'avion ? 1) Je suis étudiant au doctorat et la bourse du CRDI aux chercheurs candidats au doctorat m'intéresse. Pourriez-vous me faire parvenir de la documentation au sujet de cette bourse ? Tous les renseignements concernant la bourse du CRDI ...

  18. Waypoint Generation Based on Sensor Aimpoint

    Science.gov (United States)

    2009-03-01

    BATCAM. Aviones physics parameters for the Procerus testbed, the Unicorn UAV, were provided by Procerus, which allowed another simulated MAV to 48 be...flown in the HIL tests. The AFIT Advanced Navigation Technologies (ANT) Center did not own a Unicorn UAV, so it could not be flown in flight tests

  19. DoD Depot-Level Reparable Supply Chain Management: Process Effectiveness and Opportunities for Improvement

    Science.gov (United States)

    2014-01-01

    Boeing 787 Dreamliner , Boeing began its GoldCare program, 2 J. R. Ashayeri et al., “Inventory Management of Repairable Service Parts for Personal...struggled with maintaining avi- onics systems on the airline’s legacy Boeing 737-300s and 737-400s.5 The turnover rate for avionics systems often far

  20. Number 1, July

    Indian Academy of Sciences (India)

    Energy distribution of cosmic rays in the Earth's atmosphere and avionic area using Monte. Carlo codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . M Ould Mohamed, A S A Dib and A H Belbachir. 1. Influence of nuclear dissipation on fission dynamics of the excited nucleus 248Cf within a stochastic approach .

  1. The Effects of High-Amplitude Impulsive Noise on Hatching Success: A reanalysis of the Sooty Tern Incident

    Science.gov (United States)

    1991-02-01

    the U. S. Air Force. I ( Cottereau, P. 1972. Les incidences du "bang" des avions supersoniques sur les productions et la vie animales . Revue Medicine...Patterson Air Force Base, OH. Haynes, A. M. 1987. Human exploitation of seabirds in Jamaica. Biological Conservation 41: 99-124. Hecock, R., and K

  2. 78 FR 76731 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Rechargeable Lithium...

    Science.gov (United States)

    2013-12-19

    ... series airplanes have fly-by-wire controls, fully software-configurable avionics, and fiber-optic... Series Airplanes; Rechargeable Lithium Ion Batteries and Battery Systems AGENCY: Federal Aviation... Boeing Model 777- 200, -300, and -300ER series airplanes. These airplanes as modified by the ARINC...

  3. Confection D'une Colostomie De Maydl (Sur Baguette) En Situation ...

    African Journals Online (AJOL)

    Abstract. Nous avions présenté une procédure simplifiée et reproductible de réalisation d'une colostomie sur baguette de Maydl, en conditions de précarité. Il s'agissait d'utiliser une seringue stérile de 10 cc et un fil à peau.

  4. Search and Rescue Aircrewman/HH3F Flight Mechanic, 2-10. Military Curriculum Materials for Vocational and Technical Education.

    Science.gov (United States)

    Ohio State Univ., Columbus. National Center for Research in Vocational Education.

    This self-paced, individualized course, adapted from military curriculum materials for use in vocational and technical education, teaches students the skills needed to become a qualified avionics worker on the HH-3F helicopter. The course materials consist of three pamphlets: two student workbooks and a composite ground/flight syllabus. Each…

  5. SATWG networked quality function deployment

    Science.gov (United States)

    Brown, Don

    1992-01-01

    The initiative of this work is to develop a cooperative process for continual evolution of an integrated, time phased avionics technology plan that involves customers, technologists, developers, and managers. This will be accomplished by demonstrating a computer network technology to augment the Quality Function Deployment (QFD). All results are presented in viewgraph format.

  6. 76 FR 8529 - Science and Technology Reinvention Laboratory (STRL) Personnel Management Demonstration Project...

    Science.gov (United States)

    2011-02-14

    ... submissions, several recurring themes were discerned that spanned multiple sections of the proposed regulation.... Morgan F. Park, Alternate OSD Federal Register Liaison Officer, Department of Defense. Table of Contents... is a world leader in Naval aviation whose products and services include: aircraft, avionics, air...

  7. Corrosion Control in the US Navy: Ships & USMC Vehicles

    Science.gov (United States)

    2014-11-18

    Primer Ships Support Equipment Sealants Vehicles Aircraft Prep Components/ Structure Avionics/ Electronics Zinc-Nickel Phosphating Rinse...coats, and can be cleaned rather than repainted - Reduces the gradual “pinking” of traditional silicone alkyd low solar absorption (LSA) formulas

  8. 76 FR 66046 - 36(b)(1) Arms Sales Notification

    Science.gov (United States)

    2011-10-25

    ... avionics upgrade of five (5) C-130H aircraft that includes minor Class IV modifications, ground handling equipment, repair and return, spare and repair parts, support equipment, publications and technical... upgrade of five (5) C-130H aircraft that includes minor Class IV modifications, ground handling equipment...

  9. Advanced Aeroservoelastic Testing and Data Analysis (Les Essais Aeroservoelastiques et l’Analyse des Donnees).

    Science.gov (United States)

    1995-11-01

    shells, AIAA journal, Vol. 8, March 1970. 5 Paret, A., "Essais acoustique et aeroacoustique des tuiles de la protection thermique d’Hermes; Dassault...d’essais de vibrations en l’att6nuation des charges do rafale oo l’amdlioration do vol sur avions h~ CDVE. confort dos passagers en turbulence

  10. Wireless Communication Networks Between Distributed Autonomous Systems Using Self-Tuning Extremum Control

    Science.gov (United States)

    2009-04-01

    SchoolCenter for Autonomous Vehicle Research Piccolo Plus Autopilots 2-Stroke Gas Engine Rascal 110 UAV (ARF Airframe) Engine Mount Avionics bay of... Rascal UAV O b d PC104 & P l d S k Mobile GCS n oar ay oa tac Rapid Flight Test Design Keys Reduce development time Upgrade is flexible Convenience

  11. U.S. Air Force Bomber Sustainment and Modernization: Background and Issues for Congress

    Science.gov (United States)

    2014-06-04

    from the aircraft and install metal plates prohibiting reinstallation of removed equipment to comply with treaty protocols. * Mode S/5 Identification...Display Unit (F3) IFF Mode 5/S/ADS-B On-Board Training Technology Proactive Aircraft Defense Technology CO TS HEMP Protection Technology Avionics Funded

  12. Strategies to Mitigate Obsolescence in Defense Systems Using Commercial Components (Strategies visant a attenuer l’obsolescence des systemes par l’emploi de composants du commerce)

    Science.gov (United States)

    2001-06-01

    the-Shelf (COTS) Technology Insertion During the System Life Cycle Ruben A. Lebron Jr., Robert Rossi, and William Foor Naval Air Systems Command Naval...military aircraft, based on LRUs designed for special functions, represent a symbiosis of multiple LRUs. Thereby the high complexity of avionics systems

  13. An Analysis of Electromagnetic Interference (EMI) of Ultra Wideband(UWB) and IEEE 802.11A Wireless Local Area Network (WLAN) Employing Orthogonal Frequency Division Multiplexing (OFDM)

    Science.gov (United States)

    2004-03-01

    be monitored with an electronic monitoring device that records the ambient temperature periodically. The data is collected and logged daily...Fi) Networking Handbook, McGraw-Hill: NY, 2003. [Sal02]. M.P. Salud , Investigation of RF Emissions from Wireless Networks as a Threat to Avionic

  14. Hex Chrome Free Coatings for Electronics Overview

    Science.gov (United States)

    Kessel, Kurt

    2013-01-01

    The overall objective of the Hex Chrome Free Coatings for Electronics project is to evaluate and test pretreatment coating systems not containing hexavalent chrome in avionics and electronics housing applications. This objective will be accomplished by testing strong performing coating systems from prior NASA and DoD testing or new coating systems as determined by the stakeholders.

  15. Hexavalent Chrome Free Coatings for Electronics Applications: Joint Test Report

    Science.gov (United States)

    Rothgeb, Matt; Kessel, Kurt

    2013-01-01

    The overall objective of the Hexavalent Chrome Free Coatings for Electronics Applications project is to evaluate and test pretreatments not containing hexavalent chrome in avionics and electronics housing applications. This objective will be accomplished by testing strong performing coating systems from prior NASA and DoD testing or new coating systems as determined by the stakeholders.

  16. Capability Maturity Model (CMM) for Software Process Improvements

    Science.gov (United States)

    Ling, Robert Y.

    2000-01-01

    This slide presentation reviews the Avionic Systems Division's implementation of the Capability Maturity Model (CMM) for improvements in the software development process. The presentation reviews the process involved in implementing the model and the benefits of using CMM to improve the software development process.

  17. Harmonics Study of Common Low Wattage LED Lamps

    Directory of Open Access Journals (Sweden)

    Ioan Dragoş Deaconu

    2017-11-01

    Full Text Available This article presents experimental data on Light Emitting Diode (LED lamps of low wattage that are commonly found both in commercial and residential applications. A comparison with the existing regulations is performed. The measurements are performed using power and energy quality analyzer intended also for avionic and military systems.

  18. Minimality of critical scenarios with linear logic and cutsets

    African Journals Online (AJOL)

    DK

    the car and avionic fields has lead to ... safety analysis of dynamic systems, feared scenarios are derived from Petri net model. Based on linear logic as new representation. (using the causality relations) of the Petri net model and proof tree. The hybrid aspect of. MS (both continuous and discrete features) leads us to choose ...

  19. F-16 Media Selection and Utilization Plan Report.

    Science.gov (United States)

    1981-03-01

    complex (e.g., operational flight trainers, computer avionics simula- tions, weapon system trainers), depending on the scope of the enviromental factors...incorrect assumptions of what the developer thinks will be attention-getting or interesting to the student rather than upon data from student trial and

  20. 77 FR 53159 - Passenger Use of Portable Electronic Devices on Board Aircraft

    Science.gov (United States)

    2012-08-31

    ... space by electromagnetic waves on specific radio frequencies that are used to communicate information... using radio waves, such as Wi-Fi,\\4\\ Bluetooth,\\5\\ and various other cellular technologies. These... avoidance, transponder, automatic flight guidance and control, and many other advanced avionics systems...

  1. Defense Small Business Innovation Research Program (SBIR), Volume 4, Defense Agencies Abstracts of Phase 1 Awards 1991

    Science.gov (United States)

    1991-01-01

    BIOPHARMACEUTICAL INDUSTRIES TO PRODUCE DESIRED PRODUCTS. IN THIS CASE HOWEVER, THE HOST ORGANISM WILL BE DEVELOPED TO HAVE THE BASIC PROPERTIES...EXTREMELYRELIABLE, MULTI-PARAMETER, QUASI-DISTRIBUTED SENSING CAPABILITIES. COMMERCIAL APPLICATIONS INCLUDE PLANT ENVIRONMENTS, BUILDING SAFETY, AND QUANTITATIVE...ADDITIONAL AREAS INCLUDING AVIONIC SYSTEMS, INDUSTRIAL PROCESSING PLANTS , ADVANCED WEAPONS SYSTEMS, SMART BUILDINGS, AND OTHER APPLICATIONS. FRANZ, INC

  2. The Flight of Flexible Aircraft in Turbulence - State-of-the-Art in the Description and Modelling of Atmospheric Turbulence: Meeting of the Structures and Materials Panel of AGARD (64th) Held in Athens (Greece) on 28 September-3 October 1986

    Science.gov (United States)

    1987-12-01

    by the Gumbel’s extreme value theory. ,-. -I &r2 INTRODUCTION La motivation pour des recherches nouvelles sur la modSlisation de la turbulence...etS presentee dans ce rapport repose sur 1’analyse de pres d’un million d’heures de vol d’avions commerciaux. Elle a mis en lumiere les points

  3. Managing Heterogeneous Communication Challenges in Internet of Things using Connector Variability

    NARCIS (Netherlands)

    Kaya, M.C.; Nikoo, M.S.; Suloglu, S.; Tekinerdogan, B.; Dogru, A.H.

    2017-01-01

    Internet of Things (IoT) comprises smart systems that embrace computational and physical elements. In these systems, physical and software components are often tightly coupled. They are used widely in today’s technological systems, such as smart buildings, avionics, self-driving cars, etc. IoT

  4. Software engineering of a navigation and guidance system for commercial aircraft

    Science.gov (United States)

    Lachmann, S. G.; Mckinstry, R. G.

    1975-01-01

    The avionics experimental configuration of the considered system is briefly reviewed, taking into account the concept of an advanced air traffic management system, flight critical and noncritical functions, and display system characteristics. Cockpit displays and the navigation computer are examined. Attention is given to the functions performed in the navigation computer, major programs in the navigation computer, and questions of software development.

  5. Multiple IMU system development, volume 1

    Science.gov (United States)

    Landey, M.; Mckern, R.

    1974-01-01

    A redundant gimballed inertial system is described. System requirements and mechanization methods are defined and hardware and software development is described. Failure detection and isolation algorithms are presented and technology achievements described. Application of the system as a test tool for shuttle avionics concepts is outlined.

  6. Untitled

    African Journals Online (AJOL)

    picture. The AGL circuitry, radio receiver and radio telemetry transmitter, electromechanical servo's and power supplies are not visible in this view, but all are accommodated in an airframe weighing 3.5 kg in total, including propulsion unit, batteries, avionic systems and full payload. November 2007, Vol. 97, No. 11 SAM].

  7. Detection of intermittent resistive faults in electronic systems based on the mixed-signal boundary-scan standard

    NARCIS (Netherlands)

    Kerkhoff, Hans G.; Ebrahimi, Hassan

    2015-01-01

    In avionics, like glide computers, the problem of No Faults Found (NFF) is a very serious and extremely costly affair. The rare occurrences and short bursts of these faults are the most difficult ones to detect and diagnose in the testing arena. Several techniques are now being developed in ICs by

  8. Investigation of Intermittent Resistive Faults in Digital CMOS Circuits

    NARCIS (Netherlands)

    Kerkhoff, Hans G.; Ebrahimi, Hassan

    No fault found (NFF) is a major threat in extremely dependable high-end process node integrated systems, in e.g., avionics. One category of NFFs is the intermittent resistive fault (IRF), often originating from bad (e.g., via- or TSV-based) interconnections. This paper will show the impact of these

  9. Intermittent resistive faults in digital cmos circuits

    NARCIS (Netherlands)

    Kerkhoff, Hans G.; Ebrahimi, Hassan

    2015-01-01

    A major threat in extremely dependable high-end process node integrated systems in e.g. Avionics are no failures found (NFF). One category of NFFs is the intermittent resistive fault, often originating from bad (e.g. Via or TSV-based) interconnections. This paper will show the impact of these faults

  10. Simulation/Emulation Techniques: Compressing Schedules With Parallel (HW/SW) Development

    Science.gov (United States)

    Mangieri, Mark L.; Hoang, June

    2014-01-01

    NASA has always been in the business of balancing new technologies and techniques to achieve human space travel objectives. NASA's Kedalion engineering analysis lab has been validating and using many contemporary avionics HW/SW development and integration techniques, which represent new paradigms to NASA's heritage culture. Kedalion has validated many of the Orion HW/SW engineering techniques borrowed from the adjacent commercial aircraft avionics solution space, inserting new techniques and skills into the Multi - Purpose Crew Vehicle (MPCV) Orion program. Using contemporary agile techniques, Commercial-off-the-shelf (COTS) products, early rapid prototyping, in-house expertise and tools, and extensive use of simulators and emulators, NASA has achieved cost effective paradigms that are currently serving the Orion program effectively. Elements of long lead custom hardware on the Orion program have necessitated early use of simulators and emulators in advance of deliverable hardware to achieve parallel design and development on a compressed schedule.

  11. Aircraft electromagnetic compatibility

    Science.gov (United States)

    Clarke, Clifton A.; Larsen, William E.

    1987-06-01

    Illustrated are aircraft architecture, electromagnetic interference environments, electromagnetic compatibility protection techniques, program specifications, tasks, and verification and validation procedures. The environment of 400 Hz power, electrical transients, and radio frequency fields are portrayed and related to thresholds of avionics electronics. Five layers of protection for avionics are defined. Recognition is given to some present day electromagnetic compatibility weaknesses and issues which serve to reemphasize the importance of EMC verification of equipment and parts, and their ultimate EMC validation on the aircraft. Proven standards of grounding, bonding, shielding, wiring, and packaging are laid out to help provide a foundation for a comprehensive approach to successful future aircraft design and an understanding of cost effective EMC in an aircraft setting.

  12. Description and flight performance of two systems for two-segment approach. [for aircraft noise abatement

    Science.gov (United States)

    Wehrend, W. R.; Shigemoto, F. H.; Bourquin, K. R.

    1974-01-01

    This paper describes two different avionic systems which were designed and developed to provide guidance and control for two-segment noise abatement approaches. The concept of a low-cost retrofit avionic system evolved into a special-purpose two-segment computer which required a DME collocated with the ILS glide-slope transmitter. This system was evaluated in a Boeing 727-200 aircraft. The second system is an area navigation (RNAV) system modified to include the two-segment approach. This system is more sophisticated than the first system and does not restrict usage to any specific navigation ground aid. The modified RNAV system is a Collins ANS-70A and is currently being evaluated in a DC-8-61 aircraft.

  13. Radiation Fields in High Energy Accelerators and their impact on Single Event Effects

    CERN Document Server

    García Alía, Rubén; Wrobel, Frédéric; Brugger, Markus

    Including calculation models and measurements for a variety of electronic components and their concerned radiation environments, this thesis describes the complex radiation field present in the surrounding of a high-energy hadron accelerator and assesses the risks related to it in terms of Single Event Effects (SEE). It is shown that this poses not only a serious threat to the respective operation of modern accelerators but also highlights the impact on other high-energy radiation environments such as those for ground and avionics applications. Different LHC-like radiation environments are described in terms of their hadron composition and energy spectra. They are compared with other environments relevant for electronic component operation such as the ground-level, avionics or proton belt. The main characteristic of the high-energy accelerator radiation field is its mixed nature, both in terms of hadron types and energy interval. The threat to electronics ranges from neutrons of thermal energies to GeV hadron...

  14. SOUTHEASTCON '81; Proceedings of the Region 3 Conference and Exhibit, Huntsville, AL, April 5-8, 1981

    Science.gov (United States)

    The subjects discussed are related to microelectronics, radar systems, power systems, systems theory, bio-engineering, pattern recognition, electromagnetics, Kalman filtering, communications, computer systems, digital signal processing, software engineering, multiprocessor systems, digital filters, computerized speech systems, the automation of power distribution systems, aerospace applications, pattern recognition applications, education, energy systems, antennas, filters applications, electronic devices, power applications, missile image processing applications, devices, instrumentation, new sensor systems, modeling and simulation, environmental aspects, military applications, microprocessor systems design aids, control systems, communication systems, computer aided design, avionics, coding, microprocessor applications, and propagation and scattering. Attention is given to a high-g plastic gyro with wide-angle radiant energy pickoffs, an autonomous, fast-reaction strapdown inertial navigation system, a land navigation system with a precision azimuth and elevation, avionics integrated support facility developments, an interconnection system for spacecraft distributed control and data collection, an analysis of a new inertial measuring system for aerospace vehicles, and an aircraft landing system employing observers.

  15. HIL Tuning of UAV for Exploration of Risky Environments

    Directory of Open Access Journals (Sweden)

    C. D. Melita

    2008-11-01

    Full Text Available In this paper the latest results of an HIL architecture, optimized to develop and test UAV platforms are presented. This architecture has been used to realize the different devices involved in the navigation and stability control of the Volcan UAV, a plane designed to operate in volcanic environments. The proposed architecture is strongly modular and flexible and allows the development of avionic hardware and software, testing and tuning the involved algorithms with non-destructive trials. A flight simulator (X-Plane with a suitable plane model and plug-in, has been adopted to simulate the UAV dynamics. The flight simulator, interfaced with the real electronic boards, allows an easy tuning of all the control parameters and data collecting for test and validation. The effectiveness of adopted methodology was confirmed by several flight tests performed subsequently by using the designed avionic modules on the real UAV.

  16. Optical demonstration on Honeywell FLASH program

    Science.gov (United States)

    O'Rourke, Ken; Peterson, Eric

    1996-10-01

    Flight control system architects are increasingly integrating aircraft control and management functionality. This functional integration increases performance and cost of ownership requirements on the communication pathways. Optical signal transmission is an attractive approach to satisfying these system requirements. Investigations and demonstrations of optic signaling are needed to validate applicability of fiber based communication systems to the new system architecture performance and cost requirements. Honeywell's activities associated with the Fly-By-Light Advanced System Hardware (FLASH) program have produced a system including key optical interface elements and accomplished preliminary demonstrations needed to validate flexible, optical based aircraft control and avionic systems. The Honeywell Primary Flight Control System included Active Hand Controllers, Primary Flight Control Computers and smart actuation subsystem elements interfaced through various optical implementations and communication protocols. These successful implementations and demonstrations provide an excellent baseline for the processes, tools and materials required to make Fly-by-Light avionic systems marketable.

  17. Kedalion: NASA's Adaptable and Agile Hardware/Software Integration and Test Lab

    Science.gov (United States)

    Mangieri, Mark L.; Vice, Jason

    2011-01-01

    NASA fs Kedalion engineering analysis lab at Johnson Space Center is on the forefront of validating and using many contemporary avionics hardware/software development and integration techniques, which represent new paradigms to heritage NASA culture. Kedalion has validated many of the Orion hardware/software engineering techniques borrowed from the adjacent commercial aircraft avionics solution space, with the intention to build upon such techniques to better align with today fs aerospace market. Using agile techniques, commercial products, early rapid prototyping, in-house expertise and tools, and customer collaboration, Kedalion has demonstrated that cost effective contemporary paradigms hold the promise to serve future NASA endeavors within a diverse range of system domains. Kedalion provides a readily adaptable solution for medium/large scale integration projects. The Kedalion lab is currently serving as an in-line resource for the project and the Multipurpose Crew Vehicle (MPCV) program.

  18. Investigation of Integrated Vehicle Health Management Approaches

    Science.gov (United States)

    Paris, Deidre

    2005-01-01

    This report is to present the work that was performed during the summer in the Advance Computing Application office. The NFFP (NASA Faculty Fellow Program) had ten summer faculty members working on IVHM (Integrated Vehicle Health Management) technologies. The objective of this project was two-fold: 1) to become familiar with IVHM concepts and key demonstrated IVHM technologies; and 2) to integrate the research that has been performed by IVHM faculty members into the MASTLAB (Marshall Avionic Software Test Lab). IVHM is a NASA-wide effort to coordinate, integrate and apply advanced software, sensors and design technologies to increase the level of intelligence, autonomy, and health state of future vehicles. IVHM is an important concept because it is consistent with the current plan for NASA to go to the moon, mars, and beyond. In order for NASA to become more involved in deep exploration, avionic systems will need to be highly adaptable and autonomous.

  19. On-Board Processor and Network Maturation for Ariane 6

    Science.gov (United States)

    Clavier, Rémi; Sautereau, Pierre; Sangaré, Jérémie; Disson, Benjamin

    2015-09-01

    In the past three years, innovative avionic technologies for Ariane 6 were evaluated in the tail of three main programs involving various stakeholders: FLPP (Future Launcher Preparatory Program, from ESA), AXE (Avionic-X European, formerly Avionique-X, French public R&T program) and CNES R&T program relying on industrial partnerships. In each avionics’ domain, several technologies were compared, analyzed and tested regarding space launchers system expectations and constraints. Within the frame of on-board data handling, two technologies have been identified as promising: ARM based microprocessors for the computing units and TTEthernet for the on-board network. This paper presents the main outcomes of the data handling preparatory activities performed on the AXE platform in Airbus Defence and Space - Les Mureaux.

  20. Static Analysis Numerical Algorithms

    Science.gov (United States)

    2016-04-01

    STATIC ANALYSIS OF NUMERICAL ALGORITHMS KESTREL TECHNOLOGY, LLC APRIL 2016 FINAL TECHNICAL REPORT APPROVED FOR PUBLIC RELEASE; DISTRIBUTION...3. DATES COVERED (From - To) NOV 2013 – NOV 2015 4. TITLE AND SUBTITLE STATIC ANALYSIS OF NUMERICAL ALGORITHMS 5a. CONTRACT NUMBER FA8750-14-C...and Honeywell Aerospace Advanced Technology to combine model-based development of complex avionics control software with static analysis of the

  1. Progress in aeronautical research and technology applicable to civil air transports

    Science.gov (United States)

    Bower, R. E.

    1981-01-01

    Recent progress in the aeronautical research and technology program being conducted by the United States National Aeronautics and Space Administration is discussed. Emphasis is on computational capability, new testing facilities, drag reduction, turbofan and turboprop propulsion, noise, composite materials, active controls, integrated avionics, cockpit displays, flight management, and operating problems. It is shown that this technology is significantly impacting the efficiency of the new civil air transports. The excitement of emerging research promises even greater benefits to future aircraft developments.

  2. IVHM Framework for Intelligent Integration for Vehicle Health Management

    Science.gov (United States)

    Paris, Deidre; Trevino, Luis C.; Watson, Michael D.

    2005-01-01

    Integrated Vehicle Health Management (IVHM) systems for aerospace vehicles, is the process of assessing, preserving, and restoring system functionality across flight and techniques with sensor and communication technologies for spacecraft that can generate responses through detection, diagnosis, reasoning, and adapt to system faults in support of Integrated Intelligent Vehicle Management (IIVM). These real-time responses allow the IIVM to modify the affected vehicle subsystem(s) prior to a catastrophic event. Furthermore, this framework integrates technologies which can provide a continuous, intelligent, and adaptive health state of a vehicle and use this information to improve safety and reduce costs of operations. Recent investments in avionics, health management, and controls have been directed towards IIVM. As this concept has matured, it has become clear that IIVM requires the same sensors and processing capabilities as the real-time avionics functions to support diagnosis of subsystem problems. New sensors have been proposed, in addition to augment the avionics sensors to support better system monitoring and diagnostics. As the designs have been considered, a synergy has been realized where the real-time avionics can utilize sensors proposed for diagnostics and prognostics to make better real-time decisions in response to detected failures. IIVM provides for a single system allowing modularity of functions and hardware across the vehicle. The framework that supports IIVM consists of 11 major on-board functions necessary to fully manage a space vehicle maintaining crew safety and mission objectives. These systems include the following: Guidance and Navigation; Communications and Tracking; Vehicle Monitoring; Information Transport and Integration; Vehicle Diagnostics; Vehicle Prognostics; Vehicle Mission Planning, Automated Repair and Replacement; Vehicle Control; Human Computer Interface; and Onboard Verification and Validation. Furthermore, the presented

  3. Les β-thalassémies de l'enfant camerounais : étude de la ...

    African Journals Online (AJOL)

    la variabilité l'expression clinique de la β-thalassémie, no- tamment lorsqu'elle est associée au trait drépanocytaire. A partir de la présente étude nous avions conclus que la β-thalassémie est une hémoglobinopathie assez fréquente au Cameroun. Bibliographie. [1] B. P. Alter, Beta-thalassemia trait: Imprecision of diagnosis ...

  4. 50 (Fifty) Years of Research on Man in Flight

    Science.gov (United States)

    1985-06-01

    responsible for "intelligent" behavior. This ambitious " Bionics Project" was a joint program between the AM RL and the Avionics Laboratory, which...developed. The Bionics program prepared much of the foundation for work presently continuing under the name of "Artificial Intelligence." (Dr. von Gierke...conditions. The work included control manipulation, human locomotion , body control, use of personal propulsion devices, orbital transfer, and performance of

  5. A Comparison of Ada 83 and C++

    Science.gov (United States)

    1991-06-01

    developing large, complex, software systems with long lifetimes. Those interviewed for this study who are familiar with both Ada and C++ believe that Ada is...with those who are familiar with both languages, there was a clear preference for using Ada for large complex systems with long lifetimes. These...University, December 1990 Additions by Nelson H. Weiderman, June 1991. Chile Empresa Nacional de Aeronautica (ENAER), real-time avionics system, Data

  6. Aerospace Software Engineering for Advanced Systems Architectures (L’Ingenierie des Logiciels Pour les Architectures des Systemes Aerospatiaux)

    Science.gov (United States)

    1993-11-01

    Methods in the HERMES On-Board Software 10 by P. Lacan and P. Colangeli Conception Logicielle de Systkine Raactif avec une Mkthodologie I I d’Automates...developments and studies on going on coding, although provide guidance to users in elaborating executable coding is generally no more seen as the most acute ...localization of the functions within acute problems of system development are generally homogeneous hardware ("modular avionics"), making the • described

  7. 2015-2016 Rapports sur les frais de voyage et d'accueil pour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    But: Participation au Symposium Gartner et ExpoIT 2015. Date(s). 2015-10-03 à 2015-10-08. Destination(s). Orlando, Floride (É.-U.) Billet d'avion. 702.16 $. Frais de transport au sol ou autrement. 137.54 $. Frais de logement. 1 103.85 $. Repas et frais divers. 406.01 $. Autre frais. 33.37 $. Total. 2 382.93 $. Commentaires.

  8. Rapports 2016-2017 sur les frais de voyage pour Sylvain Dufour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    But: Participation au Symposium Gartner et ExpoIT 2016. Date(s). 2016-10-15 au 2016-10-21. Destination(s). Orlando, Floride (É.-U.) Billet d'avion. 497.01 $. Frais de transport au sol ou autrement. 181.22 $. Frais de logement. 1 216.70 $. Repas et frais divers. 853.72 $. Autre frais. 53.05 $. Total. 2 801.70 $. Commentaires.

  9. Rapports 2017-2018 sur les frais de voyage pour Sylvain Dufour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Chantal Taylor

    But: Participer au Symposium Gartner et ExpoIT 2017. Date(s). 2017-09-30 au 2017-10-06. Destination(s). Orlando, Floride (É.-U.) Billet d'avion. 751.97 $. Frais de transport au sol ou autrement. 228.39 $. Frais de logement. 1 102.96 $. Repas et frais divers. 1 342.07 $. Autre frais. 7.51 $. Total. 3 432.90 $. Commentaires.

  10. DEFENSE SCIENCE AND TECHNOLOGY Adopting Best Practices Can Improve Innovation Investments and Management

    Science.gov (United States)

    2017-06-01

    relevant in the marketplace by engaging a wide range of internal stakeholders . These companies also reported that they gain leadership buy-in by...technologies are relevant and can be efficiently integrated into marketable products. Among the key R&D stakeholders are representatives from the business...discussed in this report , is a leading provider of aircraft engines, integrated avionics, systems and service solutions, and related products and

  11. Defense AT&L (Volume 35, Number 6, November-December 2006)

    Science.gov (United States)

    2006-12-01

    displayed July 18 at the Royal International Air Tattoo, RAF Fairford, United Kingdom. Photograph courtesy Raytheon/EADS CASA North America. 55...Air Force C-5 AMP (Avionics Modernization Program)—This is the initial SAR submission since the program exceeded the Major Defense Acquisition...November 2006 to January 2009. New SARs (As of June 30, 2006) The Department of Defense has submitted an initial SAR for the Air Force’s C-5 AMP

  12. Vulnerabilities of the Global Positioning System and the Impact on the Iron Triad: The AWACS, JSTARS, and Rivet Joint Fleets

    Science.gov (United States)

    2010-06-11

    allow changes to the composition and function of its flight crews, trading manpower for equipment. By upgrading the avionics in its aging KC-135...status and composition of the GPS constellation. Research conducted on the vulnerabilities of GPS is extensive and thorough. The research covers...step further, the US GPS constellation is a carefully choreographed geosynchronous web that continually encircles the earth. The collision of two

  13. On Component Reliability and System Reliability for Space Missions

    Science.gov (United States)

    Chen, Yuan; Gillespie, Amanda M.; Monaghan, Mark W.; Sampson, Michael J.; Hodson, Robert F.

    2012-01-01

    This paper is to address the basics, the limitations and the relationship between component reliability and system reliability through a study of flight computing architectures and related avionics components for NASA future missions. Component reliability analysis and system reliability analysis need to be evaluated at the same time, and the limitations of each analysis and the relationship between the two analyses need to be understood.

  14. Fourier Transform Spectrometer Controller for Partitioned Architectures

    DEFF Research Database (Denmark)

    Tamas-Selicean, Domitian; Keymeulen, D.; Berisford, D.

    2013-01-01

    The current trend in spacecraft computing is to integrate applications of different criticality levels on the same platform using no separation. This approach increases the complexity of the development, verification and integration processes, with an impact on the whole system life cycle. Resear......, such as avionics and automotive. In this paper we investigate the challenges of developing and the benefits of integrating a scientific instrument, namely a Fourier Transform Spectrometer, in such a partitioned architecture....

  15. The Use of Modeling for Flight Software Engineering on SMAP

    Science.gov (United States)

    Murray, Alexander; Jones, Chris G.; Reder, Leonard; Cheng, Shang-Wen

    2011-01-01

    The Soil Moisture Active Passive (SMAP) mission proposes to deploy an Earth-orbiting satellite with the goal of obtaining global maps of soil moisture content at regular intervals. Launch is currently planned in 2014. The spacecraft bus would be built at the Jet Propulsion Laboratory (JPL), incorporating both new avionics as well as hardware and software heritage from other JPL projects. [4] provides a comprehensive overview of the proposed mission

  16. Applications of Miniaturized Atomic Magnetic Sensors in Military Systems

    Science.gov (United States)

    2012-10-01

    exercising flight operations ( brushless DC motor running, tail avionics actuated, telemetry systems transmitting). We utilized a simple linear model to...field and the platform. We have conducted a number of tests using various DC motor and other unmanned vehicle components similar to those used in...NOTES See also ADM202976. 2012 Joint Meeting of the Military Sensing Symposia (MSS) held in Washington, DC on October 22-25, 2012. 14. ABSTRACT A

  17. Spaceborne computer executive routine functional design specification. Volume 1: Functional design of a flight computer executive program for the reusable shuttle

    Science.gov (United States)

    Curran, R. T.

    1971-01-01

    A flight computer functional executive design for the reusable shuttle is presented. The design is given in the form of functional flowcharts and prose description. Techniques utilized in the regulation of process flow to accomplish activation, resource allocation, suspension, termination, and error masking based on process primitives are considered. Preliminary estimates of main storage utilization by the Executive are furnished. Conclusions and recommendations for timely, effective software-hardware integration in the reusable shuttle avionics system are proposed.

  18. AAAIC '88 - Aerospace Applications of Artificial Intelligence; Proceedings of the Fourth Annual Conference, Dayton, OH, Oct. 25-27, 1988. Volumes 1 ampersand 2

    International Nuclear Information System (INIS)

    Johnson, J.R.

    1988-01-01

    Topics presented include integrating neural networks and expert systems, neural networks and signal processing, machine learning, cognition and avionics applications, artificial intelligence and man-machine interface issues, real time expert systems, artificial intelligence, and engineering applications. Also considered are advanced problem solving techniques, combinational optimization for scheduling and resource control, data fusion/sensor fusion, back propagation with momentum, shared weights and recurrency, automatic target recognition, cybernetics, optical neural networks

  19. Aircraft Corrosion

    Science.gov (United States)

    1981-08-01

    transport anciens dont il a fallu remplacer les panneaux extrados en raison de is corrosion profonde des lisses. Ce type d’avion a etc mis en service h partir...as six years) where lavatories are placed above the lower section of the aft pressure dome bulkhead (fig.8)., corrosion Is found in the bulkhead web ...due to leakage of toilet fluids. One of the most severe corrosion ever found In this area was with the corrosion completely penetrated through the web

  20. Rapports 2017-2018 sur les frais de voyage pour Stephen McGurk ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Visite à l'Institut de recherche sur l'Asie de l'Université de la Colombie-. Britannique à Vancouver. Date(s). 2017-06-28 au 2017-06-29. Destination(s). Vancouver. Billet d'avion. 1 301.48 $. Frais de transport au sol ou autrement. 78.00 $. Frais de logement. 254.25 $. Repas et frais divers. 161.19 $. Autre frais. 0.00 $. Total.

  1. 2015-2016 Rapports sur les frais de voyage et d'accueil pour Jean ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Participation au Forum mondial des conseils consultatifs nationaux et visite au Bureau régional de l'Amérique latine et des Caraïbes. Date(s). 2015-10-19 à 2015-10-25. Destination(s). Chili et Uruguay. Billet d'avion. 6 907.75 $. Frais de transport au sol ou autrement. 15.84 $. Frais de logement. 1 032.82 $. Repas et frais ...

  2. Rapports 2017-2018 sur les frais de voyage pour Uri Rosenthal ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Billet d'avion. 6 512.03 $. Frais de transport au sol ou autrement. 253.43 $. Frais de logement. 361.86 $. Repas et frais divers. 148.22 $. Autre frais. 0.00 $. Total. 7 275.54 $. Commentaires. À partir de sa résidence à Rotterdam, Pays-Bas. Rapports 2017-2018 sur les frais de voyage pour. Uri Rosenthal, gouverneur.

  3. 2015-2016 Rapports sur les frais de voyage et d'accueil pour Jean ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Participation au souper et à la cérémonie de remise des prix Canada. Gairdner 2015. Date(s). 2015-10-29 à 2015-10-30. Destination(s). Toronto. Billet d'avion. 467.98 $. Frais de transport au sol ou autrement. 59.84 $. Frais de logement. 188.65 $. Repas et frais divers. 60.53 $. Autre frais. 0.00 $. Total. 777.00 $.

  4. 2015-2016 Rapports sur les frais de voyage et d'accueil pour Jean ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    But: Participation au Forum économique international des Amériques à Toronto. Date(s):. 2015-07-09 à 2015-07-10. Destination(s):. Toronto. Billet d'avion: 267.38 $. Frais de transport au sol ou autrement: 86.16 $. Frais de logement: 181.40 $. Repas et frais divers: 58.29 $. Autre frais: 14.58 $. Total: 607.81 $.

  5. Rapports 2017-2018 sur les frais de voyage pour Sylvain Dufour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    SD

    Revue des opérations locales du Bureau régional du Moyen-Orient et. Afrique du Nord. Date(s). 2017-04-22 au 2017-04-29. Destination(s). Le Caire. Billet d'avion. 6 789.78 $. Frais de transport au sol ou autrement. 105.37 $. Frais de logement. 1 472.82 $. Repas et frais divers. 560.97 $. Autre frais. 114.20 $. Total.

  6. 2015-2016 Rapports sur les frais de voyage et d'accueil pour Jean ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    But: Participer à la réunion du Conseil exécutif de Grands Défis Canada. Date(s). 2015-12-10. Destination(s). Toronto. Billet d'avion. 792.27 $. Frais de transport au sol ou autrement. 16.65 $. Frais de logement. 0.00 $. Repas et frais divers. 80.84 $. Autre frais. 0.00 $. Total. 889.76 $. Commentaires. 2015-2016 Rapports sur ...

  7. 2015-2016 Rapports sur les frais de voyage et d'accueil pour Jean ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Rencontre avec les intervenants dans les projets de recherche et dans la diffusion de l'information. Date(s). 2016-01-13 à 2016-01-22. Destination(s). Abidjan, Le Caire, Beyrouth. Billet d'avion. 13 642.40 $. Frais de transport au sol ou autrement. 18.76 $. Frais de logement. 1 776.85 $. Repas et frais divers. 756.64 $.

  8. 2015-2016 Rapports sur les frais de voyage et d'accueil pour Jean ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Visite au Bureau régional du CRDI en Asie et participer au forum Next. Einstein. Date(s). 2016-02-27 à 2016-03-10. Destination(s). Delhi (Inde), Dakar (Sénégal). Billet d'avion. 16 485.93 $. Frais de transport au sol ou autrement. 38.39 $. Frais de logement. 3 282.71 $. Repas et frais divers. 820.36 $. Autre frais. 442.30 $.

  9. 2015-2016 Rapports sur les frais de voyage et d'accueil pour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    But: Visite au Bureau régional de l'Asie. Date(s):. 2015-10-21 à 2015-10-23. Destination(s):. Delhi, Inde. Billet d'avion: 2 381.41 $. Frais de transport au sol ou autrement: 0.00 $. Frais de logement: 721.48 $. Repas et frais divers: 212.93 $. Autre frais: 0.00 $. Total: 3 315.82 $. Commentaires: 2015-2016 Rapports sur les frais ...

  10. Rapports 2016-2017 sur les frais de voyage pour Shainoor Khoja ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Date(s). 2016-11-20 au 2016-11-23. Destination(s). Ottawa. Billet d'avion. 9 053.94 $. Frais de transport au sol ou autrement. 109.25 $. Frais de logement. 786.80 $. Repas et frais divers. 146.39 $. Autre frais. 0.00 $. Total. 10 096.38 $. Commentaires. Rapports 2016-2017 sur les frais de voyage pour. Shainoor Khoja ...

  11. Rapports 2017-2018 sur les frais de voyage pour Jean Lebel ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Chantal Taylor

    Visite au Bureau régional du CRDI à Nairobi et voyage en Afrique de l'Est avec les gouverneurs. Date(s). 2017-06-28 au 2017-07-12. Destination(s). Kenya, Ouganda et Tanzanie. Billet d'avion. 6 578.74 $. Frais de transport au sol ou autrement. 31.08 $. Frais de logement. 3 549.07 $. Repas et frais divers. 1 291.58 $.

  12. 2015-2016 Rapports sur les frais de voyage et d'accueil pour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Participation au souper et à la cérémonie de remise des prix Canada Gairdner. 2015. Date(s):. 2015-10-29 à 2015-10-30. Destination(s):. Toronto. Billet d'avion: 473.19 $. Frais de transport au sol ou autrement: 35.63 $. Frais de logement: 188.91 $. Repas et frais divers: 60.62 $. Autre frais: 0.00 $. Total: 758.35 $.

  13. 2015-2016 Rapports sur les frais de voyage et d'accueil pour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    ... à la Conférence internationale sur l'inégalité territoriale et le développement au Mexique. Participer à des réunions avec les chercheurs et l'ambassadeur du Canada en Haïti. Date(s):. 2016-01-27 à 2016-01-30. Destination(s):. Puebla, Mexique; Port au Prince, Haïti. Billet d'avion: 1 692.70 $. Frais de transport au sol.

  14. 2016-2017 Rapport sur les frais de voyage pour Sylvain Dufour, vice ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Billet d'avion. 5 886.83 $. Frais de transport au sol ou autrement. 67.50 $. Frais de logement. 952.70 $. Repas et frais divers. 1 163.44 $. Autre frais. 121.80 $. Total. 8 192.27 $. Commentaires. 2016-2017 Rapport sur les frais de voyage pour. Sylvain Dufour, vice-président, Ressources, et chef de la direction financière.

  15. 2015-2016 Rapports sur les frais de voyage et d'accueil pour Jean ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    But: Participation au dîner organisé par Grands défis Canada à Toronto. Date(s):. 2015-07-23 à 2015-07-24. Destination(s):. Toronto. Billet d'avion: 914.33 $. Frais de transport au sol ou autrement: 223.89 $. Frais de logement: 188.92 $. Repas et frais divers: 61.77 $. Autre frais: 0.00 $. Total: 1 388.91 $. Commentaires:.

  16. Rapports 2017-2018 sur les frais de voyage pour Sylvain Dufour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Chantal Taylor

    Participer à la table ronde des économistes en chef organisée par la. Banque de développement du Canada. Date(s). 2017-09-21 au 2017-09-22. Destination(s). Montréal. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 334.05 $. Frais de logement. 232.05 $. Repas et frais divers. 88.28 $. Autre frais. 0.00 $.

  17. Rapports 2016-2017 sur les frais de voyage pour Dominique Corti ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    chantal Taylor

    But: Réunion du Conseil des gouverneurs. Date(s). 2016-11-20 au 2016-11-25. Destination(s). Ottawa. Billet d'avion. 6 121.25 $. Frais de transport au sol ou autrement. 0.00 $. Frais de logement. 786.80 $. Repas et frais divers. 0.00 $. Autre frais. 0.00 $. Total. 6 908.05 $. Commentaires. Rapports 2016-2017 sur les frais de ...

  18. Rapports 2016-2017 sur les frais de voyage pour John McArthur ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Date(s). 2016-06-20 à 2016-06-22. Destination(s). Ottawa. Billet d'avion. 1 011.70 $. Frais de transport au sol ou autrement. 0.00 $. Frais de logement. 393.40 $. Repas et frais divers. 0.00 $. Autre frais. 0.00 $. Total. 1 405.10 $. Commentaires. Rapports 2016-2017 sur les frais de voyage pour. John McArthur, gouverneur.

  19. Rapports 2017-2018 sur les frais de voyage pour Jean Lebel ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    SD

    Modérateur d'un panel à la conférence du Conseil des relations internationales de Montréal. Date(s). 2017-04-18 au 2017-04-19. Destination(s). Montréal. Billet d'avion. 112.37 $. Frais de transport au sol ou autrement. 108.13 $. Frais de logement. 177.31 $. Repas et frais divers. 112.59 $. Autre frais. 0.00 $. Total. 510.40 $.

  20. 2015-2016 Rapports sur les frais de voyage et d'accueil pour Jean ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    ... et réseautage en matière d'innovation pour la santé des mères, des nouveau- nés et des enfants avec les IRSC, et visite au Bureau régional de l'Afrique Subsaharienne du CRDI. Date(s):. 2015-09-19 à 2015-10-02. Destination(s):. Tanzanie, Ghana, Ouganda, Kenya. Billet d'avion: 12 864.86 $. Frais de transport au sol.

  1. Rapports 2016-2017 sur les frais de voyage pour John McArthur ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Chantal Taylor

    But: Réunion du comité ad hoc. Date(s). 2016-10-31. Destination(s). Ottawa. Billet d'avion. 1 782.13 $. Frais de transport au sol ou autrement. 124.66 $. Frais de logement. 194.37 $. Repas et frais divers. 41.60 $. Autre frais. 0.00 $. Total. 2 142.76 $. Commentaires. Rapports 2016-2017 sur les frais de voyage pour.

  2. Rapports 2017-2018 sur les frais de voyage pour Stephen McGurk ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    SD

    Rencontrer des partenaires en recherche sur le dvlpt; représenter le CRDI à une conférence à Nairobi. Date(s). 2017-05-14 au 2017-06-01. Destination(s). Mayanmar/Vietnam/India/Kenya. Billet d'avion. 10 557.95 $. Frais de transport au sol ou autrement. 229.01 $. Frais de logement. 3 081.53 $. Repas et frais divers.

  3. Rapports 2017-2018 sur les frais de voyage pour Jean Lebel ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    SD

    But: Participer à la Conférence de Montréal et modérateur d'un panel. Date(s). 2017-06-11 au 2017-06-15. Destination(s). Montréal. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 236.05 $. Frais de logement. 1 209.06 $. Repas et frais divers. 174.14 $. Autre frais. 0.00 $. Total. 1 619.25 $. Commentaires.

  4. Polymer film strain gauges for measuring large elongations

    Science.gov (United States)

    Kondratov, A. P.; Zueva, A. M.; Varakin, R. S.; Taranec, I. P.; Savenkova, I. A.

    2018-02-01

    The paper shows the possibility to print polymer strain gages, microstrip lines, coplanar waveguides, and other prints for avionics using printing technology and equipment. The methods of screen and inkjet printing have been complemented by three new operations of preparing print films for application of an electrically conductive ink layer. Such additional operations make it possible to enhance the conductive ink layer adhesion to the film and to manufacture strain gages for measuring large elongations.

  5. The Ares Launch Vehicles: Critical for America's Continued Leadership in Space

    Science.gov (United States)

    Cook, Stephen A.

    2009-01-01

    This video is designed to accompany the presentation of the paper delivered at the Joint Army, Navy, NASA, Airforce (JANNAF) Propulsion Meeting held in 2009. It shows various scenes: from the construction of the A-3 test stand, construction of portions of the vehicles, through various tests of the components of the Ares Launch Vehicles, including wind tunnel testing of the Ares V, shell buckling tests, and thermal tests of the avionics, to the construction of the TPS thermal spray booth.

  6. Conference Proceedings on Vortex Flow Aerodynamics Held in Scheveningen, The Netherlands on 1-4 October 1990

    Science.gov (United States)

    1991-07-01

    Aeronauticos Department At~rodynamique Dept. de Mecanica de Fluidos Ecole Nationale Sup~rieure de Plaza del Cardena Cisneros 3 l’Aironautique et de l’Espace...SEINE FRANCE I I ~r AGARD CONFERENCE PROCEEDINGS 494 Vortex Flow Aerodynamics (LUA&odynamique des Ecoulements Tourbillonnaires) Best Available Copy i -i...tourbillonnaires Uis au di~collement jouent un r6le important dans les performances normalisi~es et le% performances hors normes des avions de combat

  7. Savremeno naoružanje i vojna oprema za broj 3/2013

    Directory of Open Access Journals (Sweden)

    Mladen R. Tišma

    2013-10-01

    Full Text Available Lasta ponovo leti;Objavljeni novi taktičko-tehnički podaci za MiG-29M/M2;Saab razvija palubni Sea Gripen i opciono bespilotni Gripen OP;Čengdu prikazao model dvosede verzije aviona FC-1;Prikazan transportni avion C296W;Američka Kopnena vojska izabrala Bell V-280 Valor za svoj JMR-TD program 

  8. Rapports 2016-2017 sur les frais de voyage pour Chandra ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    But: Initiation des nouveaux gouverneurs aux impacts de la recherche. Date(s). 2016-08-14 au 2016-08-23. Destination(s). Pérou/Colombie. Billet d'avion. 6 070.40 $. Frais de transport au sol ou autrement. 142.60 $. Frais de logement. 1 512.99 $. Repas et frais divers. 411.51 $. Autre frais. 0.00 $. Total. 8 137.50 $.

  9. Electronics and computer acronyms

    CERN Document Server

    Brown, Phil

    1988-01-01

    Electronics and Computer Acronyms presents a list of almost 2,500 acronyms related to electronics and computers. The material for this book is drawn from a number of subject areas, including electrical, electronics, computers, telecommunications, fiber optics, microcomputers/microprocessors, audio, video, and information technology. The acronyms also encompass avionics, military, data processing, instrumentation, units, measurement, standards, services, organizations, associations, and companies. This dictionary offers a comprehensive and broad view of electronics and all that is associated wi

  10. Rapports 2016-2017 sur les frais de voyage pour Margaret Ann ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Date(s). 2016-09-09 à 2016-09-29. Destination(s). Ottawa. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 66.00 $. Frais de logement. 0.00 $. Repas et frais divers. 0.00 $. Autre frais. 0.00 $. Total. 66.00 $. Commentaires. Rapports 2016-2017 sur les frais de voyage pour. Margaret Ann Biggs, Présidente du ...

  11. président, Ressources, et chef de la directi

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    But: Participation à la 71e Gala de l'Acfas. Date(s). 2015-10-22 à 2015-10-23. Destination(s). Montréal. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 156.01 $. Frais de logement. 232.26 $. Repas et frais divers. 64.25 $. Autre frais. 220.00 $. Total. 672.52 $. Commentaires. 2015-2016 Rapports sur les frais de ...

  12. Rapports 2017-2018 sur les frais de voyage pour Jean Lebel ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    SD

    Participer à un panel lors de la conférence de l'Association francophone pour le savoir. Date(s). 2017-05-10. Destination(s). Montréal. Billet d'avion. 1 690.21 $. Frais de transport au sol ou autrement. 156.60 $. Frais de logement. 0.00 $. Repas et frais divers. 0.00 $. Autre frais. 0.00 $. Total. 1 846.81 $. Commentaires.

  13. Rapports 2016-2017 sur les frais de voyage pour Margaret Ann ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Date(s). 2016-07-14 à 2016-07-21. Destination(s). Ottawa. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 36.00 $. Frais de logement. 0.00 $. Repas et frais divers. 0.00 $. Autre frais. 0.00 $. Total. 36.00 $. Commentaires. Rapports 2016-2017 sur les frais de voyage pour. Margaret Ann Biggs, Présidente du ...

  14. Rapports 2016-2017 sur les frais de voyage pour Margaret Ann ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Date(s). 2016-06-20 à 2016-06-22. Destination(s). Ottawa. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 28.00 $. Frais de logement. 0.00 $. Repas et frais divers. 50.55 $. Autre frais. 0.00 $. Total. 78.55 $. Commentaires. Rapports 2016-2017 sur les frais de voyage pour. Margaret Ann Biggs, Présidente du ...

  15. Réunion du Conseil des gouverneurs

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Réunion du Conseil des gouverneurs. Date(s):. 2015-11-16 à 2015-11-19. Destination(s):. Ottawa. Billet d'avion: 5 596.11 $. Frais de transport au sol ou autrement: 67.54 $. Frais de logement: 340.45 $. Repas et frais divers: 175.39 $. Autre frais: 0.00 $. Total: 6 179.49 $. Commentaires: 2015-2016 Rapports sur les frais de ...

  16. Rapports 2017-2018 sur les frais de voyage pour Alanna Boyd ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    But: Réunion du Conseil des gouverneurs. Date(s). 2017-06-20 au 2017-06-21. Destination(s). Ottawa. Billet d'avion. 380.67 $. Frais de transport au sol ou autrement. 24.60 $. Frais de logement. 180.93 $. Repas et frais divers. 0.00 $. Autre frais. 0.00 $. Total. 586.20 $. Commentaires. À partir de sa résidence à Toronto, ON.

  17. Rapports 2017-2018 sur les frais de voyage pour John McArthur ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Chantal Taylor

    Billet d'avion. 416.31 $. Frais de transport au sol ou autrement. 53.03 $. Frais de logement. 361.86 $. Repas et frais divers. 77.75 $. Autre frais. 0.00 $. Total. 908.95 $. Commentaires. À partir de sa résidence à Washington DC, É.-U.A.. Rapports 2017-2018 sur les frais de voyage pour John McArthur, gouverneur.

  18. Rapports 2017-2018 sur les frais de voyage pour Joanne Charette ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    BB

    Billet d'avion. 3 069.59 $. Frais de transport au sol ou autrement. 317.65 $. Frais de logement. 2 136.60 $. Repas et frais divers. 532.40 $. Autre frais. 0.00 $. Total. 6 056.24 $. Commentaires. Rapports 2017-2018 sur les frais de voyage pour. Joanne Charette, vice-présidente, Stratégie générale et communications.

  19. 2015-2016 Rapports sur les frais de voyage et d'accueil pour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Conférences pancanadiennes sur la transition démocratique avec le chercheur et coéditeur du livre. Date(s):. 2016-03-30 à 2016-04-03. Destination(s):. Montréal, Toronto, Vancouver. Billet d'avion: 968.74 $. Frais de transport au sol ou autrement: 248.71 $. Frais de logement: 461.37 $. Repas et frais divers: 302.96 $.

  20. 2015-2016 Rapports sur les frais de voyage et d'accueil pour Uri ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    But: Réunion du Conseil des gouverneurs. Date(s):. 2016-03-20 à 2016-03-22. Destination(s):. Ottawa. Billet d'avion: 7 285.28 $. Frais de transport au sol ou autrement: 0.00 $. Frais de logement: 510.67 $. Repas et frais divers: 0.00 $. Autre frais: 0.00 $. Total: 7 795.95 $. Commentaires: 2015-2016 Rapports sur les frais de ...

  1. Rapports 2017-2018 sur les frais de voyage pour Joanne Charette ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    BB

    Billet d'avion. 399.92 $. Frais de transport au sol ou autrement. 101.41 $. Frais de logement. 0.00 $. Repas et frais divers. 466.55 $. Autre frais. 0.00 $. Total. 967.88 $. Commentaires. Rapports 2017-2018 sur les frais de voyage pour. Joanne Charette, vice-présidente, Stratégie générale et communications.

  2. Agronomie Africaine: Editorial Policies

    African Journals Online (AJOL)

    Tarif d'abonnement (3 numéros par volume) = 9.000 FCFA : Côte d'Ivoire // 15.000 FCFA : Afrique // 60 $ : étranger, par chèque payable en Côte d'Ivoire ou par mandat lettre (Port avion en sus) Subscription price (3 issues/ volume) = 9.000 FCFA: Côte d'Ivoire // 15.000 FCFA: Africa // $ 60: outside Africa, by check or money ...

  3. 2015-2016 Rapports sur les frais de voyage et d'accueil pour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Réunion du Conseil des gouverneurs. Date(s):. 2016-03-20 à 2016-03-22. Destination(s):. Ottawa. Billet d'avion: 7 604.34 $. Frais de transport au sol ou autrement: 60.14 $. Frais de logement: 510.67 $. Repas et frais divers: 132.81 $. Autre frais: 0.00 $. Total: 8 307.96 $. Commentaires: 2015-2016 Rapports sur les frais de ...

  4. Rapports 2017-2018 sur les frais de voyage pour Barbara Lucille ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Billet d'avion. 436.15 $. Frais de transport au sol ou autrement. 98.00 $. Frais de logement. 361.85 $. Repas et frais divers. 219.51 $. Autre frais. 0.00 $. Total. 1 115.51 $. Commentaires. À partir de sa résidence à Fredericton, NB. Rapports 2017-2018 sur les frais de voyage pour. Barbara Lucille Trenholm, gouverneur, ...

  5. Rapports 2016-2017 sur les frais de voyage pour Chandra ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Réunion du Conseil des gouverneurs. Date(s). 2016-06-20 à 2016-06-22. Destination(s). Ottawa. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 211.96 $. Frais de logement. 393.40 $. Repas et frais divers. 75.83 $. Autre frais. 0.00 $. Total. 681.19 $. Commentaires. Rapports 2016-2017 sur les frais de voyage ...

  6. Rapports 2017-2018 sur les frais de voyage pour Mary Anne ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Chantal Taylor

    Billet d'avion. 368.41 $. Frais de transport au sol ou autrement. 69.95 $. Frais de logement. 542.79 $. Repas et frais divers. 164.42 $. Autre frais. 0.00 $. Total. 1 145.57 $. Commentaires. À partir de sa résidence à Thornhill, Ontario. Rapports 2017-2018 sur les frais de voyage pour. Mary Anne Chambers, gouverneur, ...

  7. Rapports 2016-2017 sur les frais de voyage pour Chandra ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Assister à des réunions internes organisées par le CRDI. Date(s). 2016-08-05. Destination(s). Ottawa. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 202.25 $. Frais de logement. 0.00 $. Repas et frais divers. 0.00 $. Autre frais. 0.00 $. Total. 202.25 $. Commentaires. Rapports 2016-2017 sur les frais de voyage ...

  8. Rapports 2016-2017 sur les frais de voyage pour Margaret Ann ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Beata Bialic

    Date(s). 2016-07-04 à 2016-07-06. Destination(s). Ottawa. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 39.00 $. Frais de logement. 0.00 $. Repas et frais divers. 25.43 $. Autre frais. 0.00 $. Total. 64.43 $. Commentaires. Rapports 2016-2017 sur les frais de voyage pour. Margaret Ann Biggs, Présidente du ...

  9. Le Parlement congolais post-élection dans le processus de ...

    African Journals Online (AJOL)

    D'autres question émergent notamment la question du crash de l'avion 'Antonov' mettant à nu l'inexistence d'une législation rigide dans le secteur de transports aussi crucial pour la sécurité de la population et celle de la convention de collaboration entre la RDC et le groupement des entreprises chinoises. Il se dégage des ...

  10. 2015-2016 Rapports sur les frais de voyage et d'accueil pour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Billet d'avion: 448.24 $. Frais de transport au sol ou autrement: 115.45 $. Frais de logement: 344.56 $. Repas et frais divers: 3.95 $. Autre frais: Total: 912.20 $. Commentaires: 2015-2016 Rapports sur les frais de voyage et d'accueil pour Alanna Heath - gouverneur et présidente du comité des finances et de la vérification.

  11. 2015-2016 Rapports sur les frais de voyage et d'accueil pour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Réunion COP21. Date(s):. 2015-11-30 à 2015-12-07. Destination(s):. Paris, France. Billet d'avion: 6 339.00 $. Frais de transport au sol ou autrement: 449.22 $. Frais de logement: 1 641.66 $. Repas et frais divers: 1 322.69 $. Autre frais: 0.00 $. Total: 9 752.57 $. Commentaires: 2015-2016 Rapports sur les frais de voyage et.

  12. Rapports 2017-2018 sur les frais de voyage pour Jean Lebel ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    SD

    But: Assister au souper offert par le Forum des politiques publiques. Date(s). 2017-04-19 au 2017-04-21. Destination(s). Toronto. Billet d'avion. 159.84 $. Frais de transport au sol ou autrement. 25.25 $. Frais de logement. 490.02 $. Repas et frais divers. 149.03 $. Autre frais. 0.00 $. Total. 824.14 $. Commentaires. Rapports ...

  13. 2015-2016 Rapports sur les frais de voyage et d'accueil pour ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Ruxandra Staicu

    Delhi, Inde; Dhaka,Bangladesh; Bangkok,Thaïlande; Phnom Penh,. Cambodge. Billet d'avion: 11 659.58 $. Frais de transport au sol ou autrement: 106.70 $. Frais de logement: 2 913.67 $. Repas et frais divers: 847.77 $. Autre frais: 259.25 $. Total: 15 786.97 $. Commentaires: 2015-2016 Rapports sur les frais de voyage et.

  14. Rapports 2017-2018 sur les frais de voyage pour Shainoor Khoja ...

    International Development Research Centre (IDRC) Digital Library (Canada)

    Chantal Taylor

    Billet d'avion. 2 396.52 $. Frais de transport au sol ou autrement. 212.16 $. Frais de logement. 0.00 $. Repas et frais divers. 0.00 $. Autre frais. 0.00 $. Total. 2 608.68 $. Commentaires. Résidence à Dubaï, Émirats arabes unis. Ce voyage est en provenance de Los Angeles. Rapports 2017-2018 sur les frais de voyage pour.

  15. Definition and Measurement of Complexity in the Context of Safety Assurance

    Science.gov (United States)

    2016-11-01

    complexity for avionics systems  Task 3 Identify candidate measures of complexity  Task 4 Identify the impact of complexity on safety  Task 5...4 Identify the impact of complexity on safety  Task 5 Quantify the effects of system complexity on aircraft safety and identify relevant com...system representations slightly inflate the “score” returned by applying the Er- ror Propagation Complexity formula without significantly affecting

  16. Space Shuttle Usage of z/OS

    Science.gov (United States)

    Green, Jan

    2009-01-01

    This viewgraph presentation gives a detailed description of the avionics associated with the Space Shuttle's data processing system and its usage of z/OS. The contents include: 1) Mission, Products, and Customers; 2) Facility Overview; 3) Shuttle Data Processing System; 4) Languages and Compilers; 5) Application Tools; 6) Shuttle Flight Software Simulator; 7) Software Development and Build Tools; and 8) Fun Facts and Acronyms.

  17. Workshop on Design Loads for Advanced Fighters: Meeting of the Structures and Materials Panel of AGARD (64th) Held in Madrid (Spain) on 27 April-1 May 1987.

    Science.gov (United States)

    1988-02-01

    artificial intelligence system. It is posited that combining such a system, referred to informally as "Guardian", with a system incorporating aircraft...Proceedings of the Aerospace Medical Association Annual Scientific Meeting, 1976. 13. Van Patten, R. E. Current research on an artificial intelligence ...avions qui l’ont suivi (MIRAGE 4000, MIR. III NG et RAFALE) avec leur syst~me de commande de vol electrique et leur stabilite artificielle , a achev

  18. Modelo para aplicación de RCM aeronáutico en Colombia

    OpenAIRE

    Hoyos Arango, Andrés

    2010-01-01

    La accidentalidad en el mundo aeronáutico en la década de 1950 presentó un promedio de 60 accidentes por cada millón de despegues. Dos tercios de estos accidentes se dieron por fallas presentadas en los aviones. Si no se hubiera hecho nada en ese momento, en este momento habría alrededor de 2 accidentes diarios en algún lugar del mundo.

  19. CONFECTION D'UNE COLOSTOMIE DE MAYDL (SUR BAGUETTE ...

    African Journals Online (AJOL)

    Received 19/02/2009. Accepted in revised form 27/03/2009) Clin Mother Child Health 2009; Vol 6, N° 1 :1055-1056. RESUME: Nous avions présenté une procédure simplifiée et reproductible de réalisation d'une colostomie sur baguette de Maydl, en conditions de précarité. Il s'agissait d'utiliser une seringue stérile de 10 ...

  20. Computing Systems Configuration for Highly Integrated Guidance and Control Systems

    Science.gov (United States)

    1988-06-01

    de tableau de bord d’aeronef pour 1’entrainement des equipages); du logiciel LANST concu pour la simulation ae reseau locaux; des ...avioniques a bord d’un aeronef. -3- 225433 C.CEDOCAR titre fr. (Materiel de traitement de donnees pour spatlonef la normae 1750 A ISA Ge l’US Air Force...Instruments pour le traitement a bord des avions tactiques des donnees fournies par les differents capteurs. Une architecture reoondante pour les