Sample records for avionics

  1. Avionics and Software Project (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 (United States)

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


    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 (United States)

    Stech, George; Williams, James R.


    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 (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. Space Tug avionics definition study. Volume 2: Avionics functional requirements (United States)


    Flight and ground operational phases of the tug/shuttle system are analyzed to determine the general avionics support functions that are needed during each of the mission phases and sub-phases. Each of these general support functions is then expanded into specific avionics system requirements, which are then allocated to the appropriate avionics subsystems. This process is then repeated at the next lower level of detail where these subsystem requirements are allocated to each of the major components that comprise a subsystem.

  6. Avionic Data Bus Integration Technology (United States)


    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

  7. Development of Avionics Installation Interface Standards. Revision. (United States)


    Shakil Rockwell Collins William Rupp Bendix Air Transport, Avionics Division * D. T. Engen Bendix Air Transport, Avionics Division J. C. Hoelz Bendix...flow is specified in recognition of the situation in whichj 220 kilograms per hour per kilowatt air flow available in a civil configuration D-1

  8. Non-functional Avionics Requirements (United States)

    Paulitsch, Michael; Ruess, Harald; Sorea, Maria

    Embedded systems in aerospace become more and more integrated in order to reduce weight, volume/size, and power of hardware for more fuel-effi ciency. Such integration tendencies change architectural approaches of system ar chi tec tures, which subsequently change non-functional requirements for plat forms. This paper provides some insight into state-of-the-practice of non-func tional requirements for developing ultra-critical embedded systems in the aero space industry, including recent changes and trends. In particular, formal requi re ment capture and formal analysis of non-functional requirements of avionic systems - including hard-real time, fault-tolerance, reliability, and per for mance - are exemplified by means of recent developments in SAL and HiLiTE.

  9. Avionics Simulation, Development and Software Engineering (United States)


    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.

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

  11. Reconfigurable fault tolerant avionics system (United States)

    Ibrahim, M. M.; Asami, K.; Cho, Mengu

    This paper presents the design of a reconfigurable avionics system based on modern Static Random Access Memory (SRAM)-based Field Programmable Gate Array (FPGA) to be used in future generations of nano satellites. A major concern in satellite systems and especially nano satellites is to build robust systems with low-power consumption profiles. The system is designed to be flexible by providing the capability of reconfiguring itself based on its orbital position. As Single Event Upsets (SEU) do not have the same severity and intensity in all orbital locations, having the maximum at the South Atlantic Anomaly (SAA) and the polar cusps, the system does not have to be fully protected all the time in its orbit. An acceptable level of protection against high-energy cosmic rays and charged particles roaming in space is provided within the majority of the orbit through software fault tolerance. Check pointing and roll back, besides control flow assertions, is used for that level of protection. In the minority part of the orbit where severe SEUs are expected to exist, a reconfiguration for the system FPGA is initiated where the processor systems are triplicated and protection through Triple Modular Redundancy (TMR) with feedback is provided. This technique of reconfiguring the system as per the level of the threat expected from SEU-induced faults helps in reducing the average dynamic power consumption of the system to one-third of its maximum. This technique can be viewed as a smart protection through system reconfiguration. The system is built on the commercial version of the (XC5VLX50) Xilinx Virtex5 FPGA on bulk silicon with 324 IO. Simulations of orbit SEU rates were carried out using the SPENVIS web-based software package.

  12. HH-65A Dolphin digital integrated avionics (United States)

    Huntoon, R. B.


    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.

  13. Projection display technology for avionics applications (United States)

    Kalmanash, Michael H.; Tompkins, Richard D.


    Avionics displays often require custom image sources tailored to demanding program needs. Flat panel devices are attractive for cockpit installations, however recent history has shown that it is not possible to sustain a business manufacturing custom flat panels in small volume specialty runs. As the number of suppliers willing to undertake this effort shrinks, avionics programs unable to utilize commercial-off-the-shelf (COTS) flat panels are placed in serious jeopardy. Rear projection technology offers a new paradigm, enabling compact systems to be tailored to specific platform needs while using a complement of COTS components. Projection displays enable improved performance, lower cost and shorter development cycles based on inter-program commonality and the wide use of commercial components. This paper reviews the promise and challenges of projection technology and provides an overview of Kaiser Electronics' efforts in developing advanced avionics displays using this approach.

  14. Developing A Generic Optical Avionic Network

    DEFF Research Database (Denmark)

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


    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...... by such a network. Finally, three redundancy scenarios are discussed and compared....

  15. Demonstration Advanced Avionics System (DAAS) function description (United States)

    Bailey, A. J.; Bailey, D. G.; Gaabo, R. J.; Lahn, T. G.; Larson, J. C.; Peterson, E. M.; Schuck, J. W.; Rodgers, D. L.; Wroblewski, K. A.


    The Demonstration Advanced Avionics System, DAAS, is an integrated avionics system utilizing microprocessor technologies, data busing, and shared displays for demonstrating the potential of these technologies in improving the safety and utility of general aviation operations in the late 1980's and beyond. Major hardware elements of the DAAS include a functionally distributed microcomputer complex, an integrated data control center, an electronic horizontal situation indicator, and a radio adaptor unit. All processing and display resources are interconnected by an IEEE-488 bus in order to enhance the overall system effectiveness, reliability, modularity and maintainability. A detail description of the DAAS architecture, the DAAS hardware, and the DAAS functions is presented. The system is designed for installation and flight test in a NASA Cessna 402-B aircraft.

  16. New Technologies for Space Avionics, 1993 (United States)

    Aibel, David W.; Harris, David R.; Bartlett, Dave; Black, Steve; Campagna, Dave; Fernald, Nancy; Garbos, Ray


    The report reviews a 1993 effort that investigated issues associated with the development of requirements, with the practice of concurrent engineering and with rapid prototyping, in the development of a next-generation Reaction Jet Drive Controller. This report details lessons learned, the current status of the prototype, and suggestions for future work. The report concludes with a discussion of the vision of future avionics architectures based on the principles associated with open architectures and integrated vehicle health management.

  17. Power, Avionics and Software Communication Network Architecture (United States)

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


    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).

  18. Reference Specifications for SAVOIR Avionics Elements (United States)

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


    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.

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

  20. Advanced Avionics Architecture and Technology Review. Executive Summary and Volume 1, Avionics Technology. Volume 2. Avionics Systems Engineering (United States)


    JIAWG core avionics are described in the section below. The JIAWO architecture standard (187-01) describes an open. system architeture which provides...0.35 microns (pRm). Present technology is in the 0.8 npm to 0.5 pm range for aggressive producers. Since the area of a die is approximately proportional ...analog (D/A) converters. The I A/D converter is a device or circuit that examines an analog voltage or current and converts it to a proportional binary

  1. Micro-Scale Avionics Thermal Management (United States)

    Moran, Matthew E.


    Trends in the thermal management of avionics and commercial ground-based microelectronics are converging, and facing the same dilemma: a shortfall in technology to meet near-term maximum junction temperature and package power projections. Micro-scale devices hold the key to significant advances in thermal management, particularly micro-refrigerators/coolers that can drive cooling temperatures below ambient. A microelectromechanical system (MEMS) Stirling cooler is currently under development at the NASA Glenn Research Center to meet this challenge with predicted efficiencies that are an order of magnitude better than current and future thermoelectric coolers.

  2. Customer Avionics Interface Development and Analysis (CAIDA): Software Developer for Avionics Systems (United States)

    Mitchell, Sherry L.


    The Customer Avionics Interface Development and Analysis (CAIDA) 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 objective of the semester-long internship was to support day-to-day operations of CAIDA and help prepare for verification and validation of CAIDA software.

  3. Industry perspectives on Plug-& -Play Spacecraft Avionics (United States)

    Franck, R.; Graven, P.; Liptak, L.

    This paper describes the methodologies and findings from an industry survey of awareness and utility of Spacecraft Plug-& -Play Avionics (SPA). The survey was conducted via interviews, in-person and teleconference, with spacecraft prime contractors and suppliers. It focuses primarily on AFRL's SPA technology development activities but also explores the broader applicability and utility of Plug-& -Play (PnP) architectures for spacecraft. Interviews include large and small suppliers as well as large and small spacecraft prime contractors. Through these “ product marketing” interviews, awareness and attitudes can be assessed, key technical and market barriers can be identified, and opportunities for improvement can be uncovered. Although this effort focuses on a high-level assessment, similar processes can be used to develop business cases and economic models which may be necessary to support investment decisions.

  4. Avionics System Development for a Rotary Wing Unmanned Aerial Vehicle

    National Research Council Canada - National Science Library

    Greer, Daniel


    .... A helicopter with sufficient lift capability was selected and a lightweight aluminum structure was built to serve as both an avionics platform for the necessary equipment and also as a landing skid...

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

  6. Avionics for Hibernation and Recovery on Planetary Surfaces (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...

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

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


    Gamatié , Abdoulaye; Gautier , Thierry


    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...

  9. Avionics System Architecture for the NASA Orion Vehicle (United States)

    Baggerman, Clint; McCabe, Mary; Verma, Dinesh


    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

  10. Validating Avionics Conceptual Architectures with Executable Specifications

    Directory of Open Access Journals (Sweden)

    Nils Fischer


    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.

  11. Design and Realization of Avionics Integration Simulation System Based on RTX

    Directory of Open Access Journals (Sweden)

    Wang Liang


    Full Text Available Aircraft avionics system becoming more and more complicated, it is too hard to test and verify real avionics systems. A design and realization method of avionics integration simulation system based on RTX was brought forward to resolve the problem. In this simulation system, computer software and hardware resources were utilized entirely. All kinds of aircraft avionics system HIL (hardware-in-loop simulations can be implemented in this platform. The simulation method provided the technical foundation of testing and verifying real avionics system. The research has recorded valuable data using the newly-developed method. The experiment results prove that the avionics integration simulation system was used well in some helicopter avionics HIL simulation experiment. The simulation experiment results provided the necessary judgment foundation for the helicopter real avionics system verification.

  12. Towards a distributed information architecture for avionics data (United States)

    Mattmann, Chris; Freeborn, Dana; Crichton, Dan


    Avionics data at the National Aeronautics and Space Administration's (NASA) Jet Propulsion Laboratory (JPL consists of distributed, unmanaged, and heterogeneous information that is hard for flight system design engineers to find and use on new NASA/JPL missions. The development of a systematic approach for capturing, accessing and sharing avionics data critical to the support of NASA/JPL missions and projects is required. We propose a general information architecture for managing the existing distributed avionics data sources and a method for querying and retrieving avionics data using the Object Oriented Data Technology (OODT) framework. OODT uses XML messaging infrastructure that profiles data products and their locations using the ISO-11179 data model for describing data products. Queries against a common data dictionary (which implements the ISO model) are translated to domain dependent source data models, and distributed data products are returned asynchronously through the OODT middleware. Further work will include the ability to 'plug and play' new manufacturer data sources, which are distributed at avionics component manufacturer locations throughout the United States.

  13. The single event upset environment for avionics at high latitude

    International Nuclear Information System (INIS)

    Sims, A.J.; Dyer, C.S.; Peerless, C.L.; Farren, J.


    Modern avionic systems for civil and military applications are becoming increasingly reliant upon embedded microprocessors and associated memory devices. The phenomenon of single event upset (SEU) is well known in space systems and designers have generally been careful to use SEU tolerant devices or to implement error detection and correction (EDAC) techniques where appropriate. In the past, avionics designers have had no reason to consider SEU effects but is clear that the more prevalent use of memory devices combined with increasing levels of IC integration will make SEU mitigation an important design consideration for future avionic systems. To this end, it is necessary to work towards producing models of the avionics SEU environment which will permit system designers to choose components and EDAC techniques which are based on predictions of SEU rates correct to much better than an order of magnitude. Measurements of the high latitude SEU environment at avionics altitude have been made on board a commercial airliner. Results are compared with models of primary and secondary cosmic rays and atmospheric neutrons. Ground based SEU tests of static RAMs are used to predict rates in flight

  14. An assessment of General Aviation utilization of advanced avionics technology (United States)

    Quinby, G. F.


    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.

  15. Investigation of an advanced fault tolerant integrated avionics system (United States)

    Dunn, W. R.; Cottrell, D.; Flanders, J.; Javornik, A.; Rusovick, M.


    Presented is an advanced, fault-tolerant multiprocessor avionics architecture as could be employed in an advanced rotorcraft such as LHX. The processor structure is designed to interface with existing digital avionics systems and concepts including the Army Digital Avionics System (ADAS) cockpit/display system, navaid and communications suites, integrated sensing suite, and the Advanced Digital Optical Control System (ADOCS). The report defines mission, maintenance and safety-of-flight reliability goals as might be expected for an operational LHX aircraft. Based on use of a modular, compact (16-bit) microprocessor card family, results of a preliminary study examining simplex, dual and standby-sparing architectures is presented. Given the stated constraints, it is shown that the dual architecture is best suited to meet reliability goals with minimum hardware and software overhead. The report presents hardware and software design considerations for realizing the architecture including redundancy management requirements and techniques as well as verification and validation needs and methods.

  16. Heavy Lift Vehicle (HLV) Avionics Flight Computing Architecture Study (United States)

    Hodson, Robert F.; Chen, Yuan; Morgan, Dwayne R.; Butler, A. Marc; Sdhuh, Joseph M.; Petelle, Jennifer K.; Gwaltney, David A.; Coe, Lisa D.; Koelbl, Terry G.; Nguyen, Hai D.


    A NASA multi-Center study team was assembled from LaRC, MSFC, KSC, JSC and WFF to examine potential flight computing architectures for a Heavy Lift Vehicle (HLV) to better understand avionics drivers. The study examined Design Reference Missions (DRMs) and vehicle requirements that could impact the vehicles avionics. The study considered multiple self-checking and voting architectural variants and examined reliability, fault-tolerance, mass, power, and redundancy management impacts. Furthermore, a goal of the study was to develop the skills and tools needed to rapidly assess additional architectures should requirements or assumptions change.

  17. Enabling Wireless Avionics Intra-Communications (United States)

    Torres, Omar; Nguyen, Truong; Mackenzie, Anne


    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.

  18. The MGS Avionics System Architecture: Exploring the Limits of Inheritance (United States)

    Bunker, R.


    Mars Global Surveyor (MGS) avionics system architecture comprises much of the electronics on board the spacecraft: electrical power, attitude and articulation control, command and data handling, telecommunications, and flight software. Schedule and cost constraints dictated a mix of new and inherited designs, especially hardware upgrades based on findings of the Mars Observer failure review boards.

  19. A Modeling Framework for Schedulability Analysis of Distributed Avionics Systems

    DEFF Research Database (Denmark)

    Han, Pujie; Zhai, Zhengjun; Nielsen, Brian


    This paper presents a modeling framework for schedulability analysis of distributed integrated modular avionics (DIMA) systems that consist of spatially distributed ARINC-653 modules connected by a unified AFDX network. We model a DIMA system as a set of stopwatch automata (SWA) in UPPAAL...

  20. Avionics Configuration Assessment for Flightdeck Interval Management: A Comparison of Avionics and Notification Methods (United States)

    Latorella, Kara A.


    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

  1. A critique of reliability prediction techniques for avionics applications

    Directory of Open Access Journals (Sweden)

    Guru Prasad PANDIAN


    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.

  2. Electronics/avionics integrity - Definition, measurement and improvement (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.

  3. Sail GTS ground system analysis: Avionics system engineering (United States)

    Lawton, R. M.


    A comparison of two different concepts for the guidance, navigation and control test set signal ground system is presented. The first is a concept utilizing a ground plate to which crew station, avionics racks, electrical power distribution system, master electrical common connection assembly and marshall mated elements system grounds are connected by 4/0 welding cable. An alternate approach has an aluminum sheet interconnecting the signal ground reference points between the crew station and avionics racks. The comparison analysis quantifies the differences between the two concepts in terms of dc resistance, ac resistance and inductive reactance. These parameters are figures of merit for ground system conductors in that the system with the lowest impedance is the most effective in minimizing noise voltage. Although the welding cable system is probably adequate, the aluminum sheet system provides a higher probability of a successful system design.

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

    National Research Council Canada - National Science Library

    Hofer, Thomas W


    ... avionics curriculum does not yet exist that satisfies the needs of graduates who will serve as aeronautical engineers involved with the development, integration, testing, fielding, and supporting...

  5. ISHM-oriented adaptive fault diagnostics for avionics based on a distributed intelligent agent system (United States)

    Xu, Jiuping; Zhong, Zhengqiang; Xu, Lei


    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.

  6. Integrated communication, navigation, and identification avionics: Impact analysis. Executive summary (United States)

    Veatch, M. H.; McManus, J. C.


    This paper summarizes the approach and findings of research into reliability, supportability, and survivability prediction techniques for fault-tolerant avionics systems. Since no technique existed to analyze the fault tolerance of reconfigurable systems, a new method was developed and implemented in the Mission Reliability Model (MIREM). The supportability analysis was completed by using the Simulation of Operational Availability/Readiness (SOAR) model. Both the Computation of Vulnerable Area and Repair Time (COVART) model and FASTGEN, a survivability model, proved valuable for the survivability research. Sample results are presented and several recommendations are also given for each of the three areas investigated under this study: reliability supportablility and survivability.

  7. An electronic flight bag for NextGen avionics (United States)

    Zelazo, D. Eyton


    The introduction of the Next Generation Air Transportation System (NextGen) initiative by the Federal Aviation Administration (FAA) will impose new requirements for cockpit avionics. A similar program is also taking place in Europe by the European Organisation for the Safety of Air Navigation (Eurocontrol) called the Single European Sky Air Traffic Management Research (SESAR) initiative. NextGen will require aircraft to utilize Automatic Dependent Surveillance-Broadcast (ADS-B) in/out technology, requiring substantial changes to existing cockpit display systems. There are two ways that aircraft operators can upgrade their aircraft in order to utilize ADS-B technology. The first is to replace existing primary flight displays with new displays that are ADS-B compatible. The second, less costly approach is to install an advanced Class 3 Electronic Flight Bag (EFB) system. The installation of Class 3 EFBs in the cockpit will allow aircraft operators to utilize ADS-B technology in a lesser amount of time with a decreased cost of implementation and will provide additional benefits to the operator. This paper describes a Class 3 EFB, the NexisTM Flight-Intelligence System, which has been designed to allow users a direct interface with NextGen avionics sensors while additionally providing the pilot with all the necessary information to meet NextGen requirements.

  8. Software testability and its application to avionic software (United States)

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


    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.

  9. IXV avionics architecture: Design, qualification and mission results (United States)

    Succa, Massimo; Boscolo, Ilario; Drocco, Alessandro; Malucchi, Giovanni; Dussy, Stephane


    The paper details the IXV avionics presenting the architecture and the constituting subsystems and equipment. It focuses on the novelties introduced, such as the Ethernet-based protocol for the experiment data acquisition system, and on the synergy with Ariane 5 and Vega equipment, pursued in order to comply with the design-to-cost requirement for the avionics system development. Emphasis is given to the adopted model philosophy in relation to OTS/COTS items heritage and identified activities necessary to extend the qualification level to be compliant with the IXV environment. Associated lessons learned are identified. Then, the paper provides the first results and interpretation from the flight recorders telemetry, covering the behavior of the Data Handling System, the quality of telemetry recording and real-time/delayed transmission, the performance of the batteries and the Power Protection and Distribution Unit, the ground segment coverage during visibility windows and the performance of the GNC sensors (IMU and GPS) and actuators. Finally, some preliminary tracks of the IXV follow on are given, introducing the objectives of the Innovative Space Vehicle and the necessary improvements to be developed in the frame of PRIDE.

  10. The effect of requirements prioritization on avionics system conceptual design (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

  11. Integrated Modular Avionics for Spacecraft: Earth Observation Use Case Demonstrator (United States)

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


    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

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

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

  14. Estimation of Airline Benefits from Avionics Upgrade under Preferential Merge Re-sequence Scheduling (United States)

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


    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.

  15. A method of distributed avionics data processing based on SVM classifier (United States)

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


    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.

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

    Orr, James K.; Peltier, Daryl


    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.

  17. Analysis of technology requirements and potential demand for general aviation avionics systems for operation in the 1980's (United States)

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


    Avionics systems are identified which promise to reduce economic constraints and provide significant improvements in performance, operational capability and utility for general aviation aircraft in the 1980's.

  18. Semiautonomous Avionics-and-Sensors System for a UAV (United States)

    Shams, Qamar


    Unmanned Aerial Vehicles (UAVs) autonomous or remotely controlled pilotless aircraft have been recently thrust into the spotlight for military applications, for homeland security, and as test beds for research. In addition to these functions, there are many space applications in which lightweight, inexpensive, small UAVS can be used e.g., to determine the chemical composition and other qualities of the atmospheres of remote planets. Moreover, on Earth, such UAVs can be used to obtain information about weather in various regions; in particular, they can be used to analyze wide-band acoustic signals to aid in determining the complex dynamics of movement of hurricanes. The Advanced Sensors and Electronics group at Langley Research Center has developed an inexpensive, small, integrated avionics-and-sensors system to be installed in a UAV that serves two purposes. The first purpose is to provide flight data to an AI (Artificial Intelligence) controller as part of an autonomous flight-control system. The second purpose is to store data from a subsystem of distributed MEMS (microelectromechanical systems) sensors. Examples of these MEMS sensors include humidity, temperature, and acoustic sensors, plus chemical sensors for detecting various vapors and other gases in the environment. The critical sensors used for flight control are a differential- pressure sensor that is part of an apparatus for determining airspeed, an absolute-pressure sensor for determining altitude, three orthogonal accelerometers for determining tilt and acceleration, and three orthogonal angular-rate detectors (gyroscopes). By using these eight sensors, it is possible to determine the orientation, height, speed, and rates of roll, pitch, and yaw of the UAV. This avionics-and-sensors system is shown in the figure. During the last few years, there has been rapid growth and advancement in the technological disciplines of MEMS, of onboard artificial-intelligence systems, and of smaller, faster, and


    Directory of Open Access Journals (Sweden)

    Sergey Viktorovich Kuznetsov


    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

  20. Advanced Information Processing System (AIPS)-based fault tolerant avionics architecture for launch vehicles (United States)

    Lala, Jaynarayan H.; Harper, Richard E.; Jaskowiak, Kenneth R.; Rosch, Gene; Alger, Linda S.; Schor, Andrei L.


    An avionics architecture for the advanced launch system (ALS) that uses validated hardware and software building blocks developed under the advanced information processing system program is presented. The AIPS for ALS architecture defined is preliminary, and reliability requirements can be met by the AIPS hardware and software building blocks that are built using the state-of-the-art technology available in the 1992-93 time frame. The level of detail in the architecture definition reflects the level of detail available in the ALS requirements. As the avionics requirements are refined, the architecture can also be refined and defined in greater detail with the help of analysis and simulation tools. A useful methodology is demonstrated for investigating the impact of the avionics suite to the recurring cost of the ALS. It is shown that allowing the vehicle to launch with selected detected failures can potentially reduce the recurring launch costs. A comparative analysis shows that validated fault-tolerant avionics built out of Class B parts can result in lower life-cycle-cost in comparison to simplex avionics built out of Class S parts or other redundant architectures.

  1. Avionics Systems Laboratory/Building 16. Historical Documentation (United States)

    Slovinac, Patricia; Deming, Joan


    As part of this nation-wide study, in September 2006, historical survey and evaluation of NASA-owned and managed facilities that was conducted by NASA s Lyndon B. Johnson Space Center (JSC) in Houston, Texas. The results of this study are presented in a report entitled, "Survey and Evaluation of NASA-owned Historic Facilities and Properties in the Context of the U.S. Space Shuttle Program, Lyndon B. Johnson Space Center, Houston, Texas," prepared in November 2007 by NASA JSC s contractor, Archaeological Consultants, Inc. As a result of this survey, the Avionics Systems Laboratory (Building 16) was determined eligible for listing in the NRHP, with concurrence by the Texas State Historic Preservation Officer (SHPO). The survey concluded that Building 5 is eligible for the NRHP under Criteria A and C in the context of the U.S. Space Shuttle program (1969-2010). Because it has achieved significance within the past 50 years, Criteria Consideration G applies. At the time of this documentation, Building 16 was still used to support the SSP as an engineering research facility, which is also sometimes used for astronaut training. This documentation package precedes any undertaking as defined by Section 106 of the NHPA, as amended, and implemented in 36 CFR Part 800, as NASA JSC has decided to proactively pursue efforts to mitigate the potential adverse affects of any future modifications to the facility. It includes a historical summary of the Space Shuttle program; the history of JSC in relation to the SSP; a narrative of the history of Building 16 and how it supported the SSP; and a physical description of the structure. In addition, photographs documenting the construction and historical use of Building 16 in support of the SSP, as well as photographs of the facility documenting the existing conditions, special technological features, and engineering details, are included. A contact sheet printed on archival paper, and an electronic copy of the work product on CD, are

  2. Predicting Cost/Reliability/Maintainability of Advanced General Aviation Avionics Equipment (United States)

    Davis, M. R.; Kamins, M.; Mooz, W. E.


    A methodology is provided for assisting NASA in estimating the cost, reliability, and maintenance (CRM) requirements for general avionics equipment operating in the 1980's. Practical problems of predicting these factors are examined. The usefulness and short comings of different approaches for modeling coast and reliability estimates are discussed together with special problems caused by the lack of historical data on the cost of maintaining general aviation avionics. Suggestions are offered on how NASA might proceed in assessing cost reliability CRM implications in the absence of reliable generalized predictive models.

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

    Young, D. A.


    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.

  4. Advanced information processing system for advanced launch system: Avionics architecture synthesis (United States)

    Lala, Jaynarayan H.; Harper, Richard E.; Jaskowiak, Kenneth R.; Rosch, Gene; Alger, Linda S.; Schor, Andrei L.


    The Advanced Information Processing System (AIPS) is a fault-tolerant distributed computer system architecture that was developed to meet the real time computational needs of advanced aerospace vehicles. One such vehicle is the Advanced Launch System (ALS) being developed jointly by NASA and the Department of Defense to launch heavy payloads into low earth orbit at one tenth the cost (per pound of payload) of the current launch vehicles. An avionics architecture that utilizes the AIPS hardware and software building blocks was synthesized for ALS. The AIPS for ALS architecture synthesis process starting with the ALS mission requirements and ending with an analysis of the candidate ALS avionics architecture is described.

  5. Application of industry-standard guidelines for the validation of avionics software (United States)

    Hayhurst, Kelly J.; Shagnea, Anita M.


    The application of industry standards to the development of avionics software is discussed, focusing on verification and validation activities. It is pointed out that the procedures that guide the avionics software development and testing process are under increased scrutiny. The DO-178A guidelines, Software Considerations in Airborne Systems and Equipment Certification, are used by the FAA for certifying avionics software. To investigate the effectiveness of the DO-178A guidelines for improving the quality of avionics software, guidance and control software (GCS) is being developed according to the DO-178A development method. It is noted that, due to the extent of the data collection and configuration management procedures, any phase in the life cycle of a GCS implementation can be reconstructed. Hence, a fundamental development and testing platform has been established that is suitable for investigating the adequacy of various software development processes. In particular, the overall effectiveness and efficiency of the development method recommended by the DO-178A guidelines are being closely examined.

  6. Space shuttle program: Shuttle Avionics Integration Laboratory. Volume 7: Logistics management plan (United States)


    The logistics management plan for the shuttle avionics integration laboratory defines the organization, disciplines, and methodology for managing and controlling logistics support. Those elements requiring management include maintainability and reliability, maintenance planning, support and test equipment, supply support, transportation and handling, technical data, facilities, personnel and training, funding, and management data.

  7. Spacecraft Avionics Software Development Then and Now: Different but the Same (United States)

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


    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.

  8. Research on the Reliability Analysis of the Integrated Modular Avionics System Based on the AADL Error Model

    Directory of Open Access Journals (Sweden)

    Peng Wang


    Full Text Available In recent years, the integrated modular avionics (IMA concept has been introduced to replace the traditional federated avionics. Different avionics functions are hosted in a shared IMA platform, and IMA adopts partition technologies to provide a logical isolation among different functions. The IMA architecture can provide more sophisticated and powerful avionics functionality; meanwhile, the failure propagation patterns in IMA are more complex. The feature of resource sharing introduces some unintended interconnections among different functions, which makes the failure propagation modes more complex. Therefore, this paper proposes an architecture analysis and design language- (AADL- based method to establish the reliability model of IMA platform. The single software and hardware error behavior in IMA system is modeled. The corresponding AADL error model of failure propagation among components, between software and hardware, is given. Finally, the display function of IMA platform is taken as an example to illustrate the effectiveness of the proposed method.

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

    Kulkarni, Nilesh; Krishnakumar, Kalmaje


    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.

  10. Digital avionics systems - Overview of FAA/NASA/industry-wide briefing (United States)

    Larsen, William E.; Carro, Anthony


    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.

  11. Advanced Avionics and Processor Systems for a Flexible Space Exploration Architecture (United States)

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


    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

  12. Digital Systems Validation Handbook. Volume 2. Chapter 18. Avionic Data Bus Integration Technology (United States)


    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

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

    Directory of Open Access Journals (Sweden)

    Boruzdina Anna


    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.

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

  15. Deterministic bound for avionics switched networks according to networking features using network calculus

    Directory of Open Access Journals (Sweden)

    Feng HE


    Full Text Available The state of the art avionics system adopts switched networks for airborne communications. A major concern in the design of the networks is the end-to-end guarantee ability. Analytic methods have been developed to compute the worst-case delays according to the detailed configurations of flows and networks within avionics context, such as network calculus and trajectory approach. It still lacks a relevant method to make a rapid performance estimation according to some typically switched networking features, such as networking scale, bandwidth utilization and average flow rate. The goal of this paper is to establish a deterministic upper bound analysis method by using these networking features instead of the complete network configurations. Two deterministic upper bounds are proposed from network calculus perspective: one is for a basic estimation, and another just shows the benefits from grouping strategy. Besides, a mathematic expression for grouping ability is established based on the concept of network connecting degree, which illustrates the possibly minimal grouping benefit. For a fully connected network with 4 switches and 12 end systems, the grouping ability coming from grouping strategy is 15–20%, which just coincides with the statistical data (18–22% from the actual grouping advantage. Compared with the complete network calculus analysis method for individual flows, the effectiveness of the two deterministic upper bounds is no less than 38% even with remarkably varied packet lengths. Finally, the paper illustrates the design process for an industrial Avionics Full DupleX switched Ethernet (AFDX networking case according to the two deterministic upper bounds and shows that a better control for network connecting, when designing a switched network, can improve the worst-case delays dramatically. Keywords: Deterministic bound, Grouping ability, Network calculus, Networking features, Switched networks

  16. Avionics Integrity Issues Presented during NAECON (National Aerospace and Electronics Convention) 1984. (United States)


    insistence on * reliability by our program offices combined with the Avionics Integrity Program. Second: competition based or rellabi]Jty. Tbird: some...typically 0 hinges unless they are wedge clamped]~ (wedge clamps give a very high L 2.0 I I-6.5 mechanical advantage such that theLi n ni boundary...aj &02Lt.e may have been diideten Soot IkeAe Ctot. The j4U AM1S uteA ame the 4A" AFM 64-1 det 4oit the Adue Usne 14we a6 4,en the CENT teatA woe

  17. Customer Avionics Interface Development and Analysis (CAIDA) Lab DEWESoft Display Creation (United States)

    Coffey, Connor


    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).


    Directory of Open Access Journals (Sweden)

    Dr. H.-W. Schulz


    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.

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

    Directory of Open Access Journals (Sweden)

    Anna V. Korneenkova


    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.

  20. Development of Integrated Modular Avionics Application Based on Simulink and XtratuM (United States)

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


    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.

  1. Aerodynamics of the advanced launch system (ALS) propulsion and avionics (P/A) module (United States)

    Ferguson, Stan; Savage, Dick


    This paper discusses the design and testing of candidate Advanced Launch System (ALS) Propulsion and Avionics (P/A) Module configurations. The P/A Module is a key element of future launch systems because it is essential to the recovery and reuse of high-value propulsion and avionics hardware. The ALS approach involves landing of first stage (booster) and/or second stage (core) P/A modules near the launch site to minimize logistics and refurbishment cost. The key issue addressed herein is the aerodynamic design of the P/A module, including the stability characteristics and the lift-to-drag (L/D) performance required to achieve the necessary landing guidance accuracy. The reference P/A module configuration was found to be statically stable for the desired flight regime, to provide adequate L/D for targeting, and to have effective modulation of the L/D performance using a body flap. The hypersonic aerodynamic trends for nose corner radius, boattail angle and body flap deflections were consistent with pretest predictions. However, the levels for the L/D and axial force for hypersonic Mach numbers were overpredicted by impact theories.

  2. Investigation of HZETRN 2010 as a Tool for Single Event Effect Qualification of Avionics Systems (United States)

    Rojdev, Kristina; Koontz, Steve; Atwell, William; Boeder, Paul


    NASA's future missions are focused on long-duration deep space missions for human exploration which offers no options for a quick emergency return to Earth. The combination of long mission duration with no quick emergency return option leads to unprecedented spacecraft system safety and reliability requirements. It is important that spacecraft avionics systems for human deep space missions are not susceptible to Single Event Effect (SEE) failures caused by space radiation (primarily the continuous galactic cosmic ray background and the occasional solar particle event) interactions with electronic components and systems. SEE effects are typically managed during the design, development, and test (DD&T) phase of spacecraft development by using heritage hardware (if possible) and through extensive component level testing, followed by system level failure analysis tasks that are both time consuming and costly. The ultimate product of the SEE DD&T program is a prediction of spacecraft avionics reliability in the flight environment produced using various nuclear reaction and transport codes in combination with the component and subsystem level radiation test data. Previous work by Koontz, et al.1 utilized FLUKA, a Monte Carlo nuclear reaction and transport code, to calculate SEE and single event upset (SEU) rates. This code was then validated against in-flight data for a variety of spacecraft and space flight environments. However, FLUKA has a long run-time (on the order of days). CREME962, an easy to use deterministic code offering short run times, was also compared with FLUKA predictions and in-flight data. CREME96, though fast and easy to use, has not been updated in several years and underestimates secondary particle shower effects in spacecraft structural shielding mass. Thus, this paper will investigate the use of HZETRN 20103, a fast and easy to use deterministic transport code, similar to CREME96, that was developed at NASA Langley Research Center primarily for

  3. Power, Avionics and Software - Phase 1.0:. [Subsystem Integration Test Report (United States)

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


    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.

  4. Modular, Cost-Effective, Extensible Avionics Architecture for Secure, Mobile Communications (United States)

    Ivancic, William D.


    Current onboard communication architectures are based upon an all-in-one communications management unit. This unit and associated radio systems has regularly been designed as a one-off, proprietary system. As such, it lacks flexibility and cannot adapt easily to new technology, new communication protocols, and new communication links. This paper describes the current avionics communication architecture and provides a historical perspective of the evolution of this system. A new onboard architecture is proposed that allows full use of commercial-off-the-shelf technologies to be integrated in a modular approach thereby enabling a flexible, cost-effective and fully deployable design that can take advantage of ongoing advances in the computer, cryptography, and telecommunications industries.

  5. Next-generation avionics packaging and cooling 'test results from a prototype system' (United States)

    Seals, J. D.

    The author reports on the design, material characteristics, and test results obtained under the US Air Force's advanced aircraft avionics packaging technologies (AAAPT) program, whose charter is to investigate new designs and technologies for reliable packaging, interconnection, and thermal management. Under this program, AT&T Bell Laboratories has completed the preliminary testing of and is evaluating a number of promising materials and technologies, including conformal encapsulation, liquid flow-through cooling, and a cyanate ester backplane. A fifty-two module system incorporating these and and other technologies has undergone preliminary cooling efficiency, shock, sine and random vibration, and maintenance testing. One of the primary objectives was to evaluate the interaction compatibility of new materials and designs with other components in the system.

  6. Loop thermosyphon thermal management of the avionics of an in-flight entertainment system

    International Nuclear Information System (INIS)

    Sarno, C.; Tantolin, C.; Hodot, R.; Maydanik, Yu.; Vershinin, S.


    A new generation of in-flight entertainment systems (IFEs) used on board commercial aircrafts is required to provide more and more services (audio, video, internet, multimedia, phone, etc.). But, unlike other avionics systems most of the IFE equipment and boxes are installed inside the cabin and they are not connected to the aircraft cooling system. The most critical equipment of the IFE system is a seat electronic box (SEB) installed under each passenger seat. Fans are necessary to face the increasing power dissipation. But this traditional approach has some drawbacks: extra cost multiplied by the seat number, reliability and maintenance. The objective of this work is to develop and evaluate an alternative completely passive cooling system (PCS) based on a two-phase technology including heat pipes and loop thermosyphons (LTSs) adequately integrated inside the seat structure and using the benefit of the seat frame as a heat sink. Previous works have been performed to evaluate these passive cooling systems which were based on loop heat pipe. This paper presents results of thermal tests of a passive cooling system of the SEB consisting of two LTSs and R141b as a working fluid. These tests have been carried out at different tilt angles and heat loads from 10 to 100 W. It has been shown that the cooled object temperature does not exceed the maximum given value in the range of tilt angles ±20° which is more wider than the range which is typical for ordinary evolution of passenger aircrafts. -- Highlights: ► A passive cooling system has been developed for avionics application. ► The system consists of loop thermosyphons and a passenger seat as a heat sink. ► Successful system tests have been run at heat loads to 100 W and angle tilts to 20°

  7. Expanding AirSTAR Capability for Flight Research in an Existing Avionics Design (United States)

    Laughter, Sean A.


    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.

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

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


    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.

  9. A knowledge-based flight status monitor for real-time application in digital avionics systems (United States)

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


    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.

  10. Self-Contained Avionics Sensing and Flight Control System for Small Unmanned Aerial Vehicle (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)


    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.

  11. Autonomous safety and reliability features of the K-1 avionics system

    Energy Technology Data Exchange (ETDEWEB)

    Mueller, G.E.; Kohrs, D.; Bailey, R.; Lai, G. [Kistler Aerospace Corp., Kirkland, WA (United States)


    Kistler Aerospace Corporation is developing the K-1, a fully reusable, two-stage-to-orbit launch vehicle. Both stages return to the launch site using parachutes and airbags. Initial flight operations will occur from Woomera, Australia. K-1 guidance is performed autonomously. Each stage of the K- 1 employs a triplex, fault tolerant avionics architecture, including three fault tolerant computers and three radiation hardened Embedded GPS/INS units with a hardware voter. The K-1 has an Integrated Vehicle Health Management (IVHM) system on each stage residing in the three vehicle computers based on similar systems in commercial aircraft. During first-stage ascent, the IVHM system performs an Instantaneous Impact Prediction (IIP) calculation 25 times per second, initiating an abort in the event the vehicle is outside a predetermined safety corridor for at least three consecutive calculations. In this event, commands are issued to terminate thrust, separate the stages, dump all propellant in the first-stage, and initiate a normal landing sequence. The second-stage flight computer calculates its ability to reach orbit along its state vector, initiating an abort sequence similar to the first stage if it cannot. On a nominal mission, following separation, the second-stage also performs calculations to assure its impact point is within a safety corridor. The K-1's guidance and control design is being tested through simulation with hardware-in-the-loop at Draper Laboratory. Kistler's verification strategy assures reliable and safe operation of the K-1. (author)

  12. Formal Verification Method for Configuration of Integrated Modular Avionics System Using MARTE

    Directory of Open Access Journals (Sweden)

    Lisong Wang


    Full Text Available The configuration information of Integrated Modular Avionics (IMA system includes almost all details of whole system architecture, which is used to configure the hardware interfaces, operating system, and interactions among applications to make an IMA system work correctly and reliably. It is very important to ensure the correctness and integrity of the configuration in the IMA system design phase. In this paper, we focus on modelling and verification of configuration information of IMA/ARINC653 system based on MARTE (Modelling and Analysis for Real-time and Embedded Systems. Firstly, we define semantic mapping from key concepts of configuration (such as modules, partitions, memory, process, and communications to components of MARTE element and propose a method for model transformation between XML-formatted configuration information and MARTE models. Then we present a formal verification framework for ARINC653 system configuration based on theorem proof techniques, including construction of corresponding REAL theorems according to the semantics of those key components of configuration information and formal verification of theorems for the properties of IMA, such as time constraints, spatial isolation, and health monitoring. After that, a special issue of schedulability analysis of ARINC653 system is studied. We design a hierarchical scheduling strategy with consideration of characters of the ARINC653 system, and a scheduling analyzer MAST-2 is used to implement hierarchical schedule analysis. Lastly, we design a prototype tool, called Configuration Checker for ARINC653 (CC653, and two case studies show that the methods proposed in this paper are feasible and efficient.

  13. Use of Field Programmable Gate Array Technology in Future Space Avionics (United States)

    Ferguson, Roscoe C.; Tate, Robert


    Fulfilling NASA's new vision for space exploration requires the development of sustainable, flexible and fault tolerant spacecraft control systems. The traditional development paradigm consists of the purchase or fabrication of hardware boards with fixed processor and/or Digital Signal Processing (DSP) components interconnected via a standardized bus system. This is followed by the purchase and/or development of software. This paradigm has several disadvantages for the development of systems to support NASA's new vision. Building a system to be fault tolerant increases the complexity and decreases the performance of included software. Standard bus design and conventional implementation produces natural bottlenecks. Configuring hardware components in systems containing common processors and DSPs is difficult initially and expensive or impossible to change later. The existence of Hardware Description Languages (HDLs), the recent increase in performance, density and radiation tolerance of Field Programmable Gate Arrays (FPGAs), and Intellectual Property (IP) Cores provides the technology for reprogrammable Systems on a Chip (SOC). This technology supports a paradigm better suited for NASA's vision. Hardware and software production are melded for more effective development; they can both evolve together over time. Designers incorporating this technology into future avionics can benefit from its flexibility. Systems can be designed with improved fault isolation and tolerance using hardware instead of software. Also, these designs can be protected from obsolescence problems where maintenance is compromised via component and vendor availability.To investigate the flexibility of this technology, the core of the Central Processing Unit and Input/Output Processor of the Space Shuttle AP101S Computer were prototyped in Verilog HDL and synthesized into an Altera Stratix FPGA.

  14. Managing Complexity in the MSL/Curiosity Entry, Descent, and Landing Flight Software and Avionics Verification and Validation Campaign (United States)

    Stehura, Aaron; Rozek, Matthew


    The complexity of the Mars Science Laboratory (MSL) mission presented the Entry, Descent, and Landing systems engineering team with many challenges in its Verification and Validation (V&V) campaign. This paper describes some of the logistical hurdles related to managing a complex set of requirements, test venues, test objectives, and analysis products in the implementation of a specific portion of the overall V&V program to test the interaction of flight software with the MSL avionics suite. Application-specific solutions to these problems are presented herein, which can be generalized to other space missions and to similar formidable systems engineering problems.

  15. CanOpen on RASTA: The Integration of the CanOpen IP Core in the Avionics Testbed (United States)

    Furano, Gianluca; Guettache, Farid; Magistrati, Giorgio; Tiotto, Gabriele; Ortega, Carlos Urbina; Valverde, Alberto


    This paper presents the work done within the ESA Estec Data Systems Division, targeting the integration of the CanOpen IP Core with the existing Reference Architecture Test-bed for Avionics (RASTA). RASTA is the reference testbed system of the ESA Avionics Lab, designed to integrate the main elements of a typical Data Handling system. It aims at simulating a scenario where a Mission Control Center communicates with on-board computers and systems through a TM/TC link, thus providing the data management through qualified processors and interfaces such as Leon2 core processors, CAN bus controllers, MIL-STD-1553 and SpaceWire. This activity aims at the extension of the RASTA with two boards equipped with HurriCANe controller, acting as CANOpen slaves. CANOpen software modules have been ported on the RASTA system I/O boards equipped with Gaisler GR-CAN controller and acts as master communicating with the CCIPC boards. CanOpen serves as upper application layer for based on CAN defined within the CAN-in-Automation standard and can be regarded as the definitive standard for the implementation of CAN-based systems solutions. The development and integration of CCIPC performed by SITAEL S.p.A., is the first application that aims to bring the CANOpen standard for space applications. The definition of CANOpen within the European Cooperation for Space Standardization (ECSS) is under development.

  16. Multi-objective optimisation of aircraft flight trajectories in the ATM and avionics context (United States)

    Gardi, Alessandro; Sabatini, Roberto; Ramasamy, Subramanian


    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

  17. Definition, analysis and development of an optical data distribution network for integrated avionics and control systems. Part 2: Component development and system integration (United States)

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


    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.

  18. 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 (United States)


    validation will result in sustainable avionics. 747 .l REFERENCES 1. Hitt, Ellis F., Webb, Jeff J., Lucius, Charles E., Bridgman, Michael S., Eldredge...There is * software requirement for cross compiler facilities for a t~rget computer system. The Project Manager for the effort has bezo assigned the

  19. Applying emerging digital video interface standards to airborne avionics sensor and digital map integrations: benefits outweigh the initial costs (United States)

    Kuehl, C. Stephen


    Video signal system performance can be compromised in a military aircraft cockpit management system (CMS) with the tailoring of vintage Electronics Industries Association (EIA) RS170 and RS343A video interface standards. Video analog interfaces degrade when induced system noise is present. Further signal degradation has been traditionally associated with signal data conversions between avionics sensor outputs and the cockpit display system. If the CMS engineering process is not carefully applied during the avionics video and computing architecture development, extensive and costly redesign will occur when visual sensor technology upgrades are incorporated. Close monitoring and technical involvement in video standards groups provides the knowledge-base necessary for avionic systems engineering organizations to architect adaptable and extendible cockpit management systems. With the Federal Communications Commission (FCC) in the process of adopting the Digital HDTV Grand Alliance System standard proposed by the Advanced Television Systems Committee (ATSC), the entertainment and telecommunications industries are adopting and supporting the emergence of new serial/parallel digital video interfaces and data compression standards that will drastically alter present NTSC-M video processing architectures. The re-engineering of the U.S. Broadcasting system must initially preserve the electronic equipment wiring networks within broadcast facilities to make the transition to HDTV affordable. International committee activities in technical forums like ITU-R (former CCIR), ANSI/SMPTE, IEEE, and ISO/IEC are establishing global consensus on video signal parameterizations that support a smooth transition from existing analog based broadcasting facilities to fully digital computerized systems. An opportunity exists for implementing these new video interface standards over existing video coax/triax cabling in military aircraft cockpit management systems. Reductions in signal

  20. Computer architecture for efficient algorithmic executions in real-time systems: New technology for avionics systems and advanced space vehicles (United States)

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


    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.

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

    Shalkhauser, Mary Jo W.; Roche, Rigoberto


    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.

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

    Shalkhauser, Mary Jo W.; Roche, Rigoberto


    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.

  3. Memory device sensitivity trends in aircraft's environment; Evolution de la sensibilite de composants memoires en altitude avion

    Energy Technology Data Exchange (ETDEWEB)

    Bouchet, T.; Fourtine, S. [Aerospatiale-Matra Airbus, 31 - Toulouse (France); Calvet, M.C. [Aerospatiale-Matra Lanceur, 78 - Les Mureaux (France)


    The authors present the SEU (single event upset) sensitivity of 31 SRAM (static random access memory) and 8 DRAM (dynamic random access memory) according to their technologies. 2 methods have been used to compute the SEU rate: the NCS (neutron cross section) method and the BGR (burst generation rate) method, the physics data required by both methods have been either found in scientific literature or directly measured. The use of new technologies implies a quicker time response through a dramatic reduction of chip size and of the amount of energy representing 1 bit. The reduction of size makes less particles are likely to interact with the chip but the reduction of the critical charge implies that these interactions are more likely to damage the chip. The SEU sensitivity is then parted between these 2 opposed trends. Results show that for technologies beyond 0,18 {mu}m these 2 trends balance roughly. Nevertheless the feedback experience shows that the number of errors is increasing. This is due to the fact that avionics requires more and more memory to perform numerical functions, the number of bits is increasing so is the risk of errors. As far as SEU is concerned, RAM devices are less and less sensitive comparatively for 1 bit, and DRAM seem to be less sensitive than SRAM. (A.C.)

  4. Highly-hermetic feedthrough fiber pigtailed circular TO-can electro-optic sensor for avionics applications (United States)

    Lauzon, Jocelyn; Leduc, Lorrain; Bessette, Daniel; Bélanger, Nicolas


    Electro-optic sensors made of lasers or photodetectors assemblies can be associated with a window interface. In order to use these sensors in an avionics application, this interface has to be set on the periphery of the aircraft. This creates constraints on both the position/access of the associated electronics circuit card and the aircraft fuselage. Using an optical fiber to guide the light signal to a sensor being situated inside the aircraft where electronics circuit cards are deployed is an obvious solution that can be readily available. Fiber collimators that adapt to circular TO-can type window sensors do exist. However, they are bulky, add weight to the sensor and necessitate regular maintenance of the optical interface since both the sensor window and the collimator end-face are unprotected against contamination. Such maintenance can be complex since the access to the electronics circuit card, where the sensor is sitting, is usually difficult. This interface alignment can also be affected by vibrations and mechanical shocks, thus impacting sensor performances. As a solution to this problem, we propose a highly-hermetic feedthrough fiber pigtailed circular TO-can package. The optical element to optical fiber interface being set inside the hermetic package, there is no risk of contamination and thus, such a component does not require any maintenance. The footprint of these sensors being identical to their window counterparts, they offer drop-in replacement opportunities. Moreover, we have validated such packaged electro-optic sensors can be made to operate between -55 to 115°C, sustain 250 temperature cycles, 1500G mechanical shocks, 20Grms random vibrations without any performance degradations. Their water content is much smaller than the 0.5% limit set by MIL-STD-883, Method 1018. They have also been verified to offer a fiber pigtail strain relief resistance over 400g. Depending on the electronics elements inside these sensors, they can be made to have a

  5. General Aviation Avionics Statistics. (United States)


    designed to produce standard errors on these variables at levels specified by the FAA. No controls were placed on the standard errors of the non-design...Transponder Encoding Requirement. and Mode CAutomatic (11as been deleted) Altitude Reporting Ca- pabili.,; Two-way Radio; VOR or TACAN Receiver. Remaining 42

  6. Software for Avionics. (United States)


    fonctions gfinbrales et lea uti- litaires fournis en particulier grice 41 UNIX, sont intfigrfs aelon divers points de vue: - par leur accas 41 travers le...Are They Really A Problem? Proceedings, 2nd International Conference On Software Engineering, pp 91-68. Long acCA : IEEE Computer Society. Britton...CD The Hague. Nc KLEINSCIIMIDT, M. Dr Fa. LITEF. Poatfach 774. 7800 Freiburg i. Br., Ge KLEMM, R. Dr FGAN- FFM , D 5 307 Watchberg-Werthhoven. Ge KLENK

  7. Avionics Design for Reliability (United States)


    user and a supplier arfue to determine if a failure is, or is not to be ascribed to the equipment, some disputable cases are difficult to nettle ... combat action, or tampering by Government personnel, provided there is clear and c~nvincing evidence of such cause. In addition, the contrac- tor...satellite there in are described The OR of resulting module pest fail signals an bood preocoistr4 A K Geiqer MU S Navy. Electronic Systems indicates

  8. Optimización de trayectorias de aviones para minimizar la molestia acústica modelizada mediante lógica borrosa

    Directory of Open Access Journals (Sweden)

    X. Prats


    Full Text Available Resumen: El aumento sostenido del tráfico aéreo de las últimas décadas y el crecimiento de numerosas zonas urbanizadas alrededor de los aeropuertos hace que cada vez sea más importante tomar medidas para mitigar los ruidos generados por los aviones. Este trabajo presenta una estrategia para diseñar trayectorias de despegue o aterrizaje en un determinado aeropuerto y para un determinado modelo de aeronave utilizando la lógica borrosa y la optimización multicriterio. Palabras clave: control óptimo, optimización multiobjetivo, ruido, lógica borrosa, generación de trayectorias

  9. 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) (United States)


    quality imagery and engagement3 witth rapid imagery indirect fire to maximize interpretation to provide the effect of long range timely information...blackwht Fig 8 Accumulated histogram We used an LSI Logic L64250 Histogram Hough Processor ( HtP ) chip to perform histogram equalization. This device...serving as main controllers of the basic transmitted via data link or inserted manually by avionic system to ensure the moding and monitoring the crew

  10. Helicopter Field Testing of NASA's Autonomous Landing and Hazard Avoidance Technology (ALHAT) System fully Integrated with the Morpheus Vertical Test Bed Avionics (United States)

    Epp, Chirold D.; Robertson, Edward A.; Ruthishauser, David K.


    The Autonomous Landing and Hazard Avoidance Technology (ALHAT) Project was chartered to develop and mature to a Technology Readiness Level (TRL) of six an autonomous system combining guidance, navigation and control with real-time terrain sensing and recognition functions for crewed, cargo, and robotic planetary landing vehicles. The ALHAT System must be capable of identifying and avoiding surface hazards to enable a safe and accurate landing to within tens of meters of designated and certified landing sites anywhere on a planetary surface under any lighting conditions. This is accomplished with the core sensing functions of the ALHAT system: Terrain Relative Navigation (TRN), Hazard Detection and Avoidance (HDA), and Hazard Relative Navigation (HRN). The NASA plan for the ALHAT technology is to perform the TRL6 closed loop demonstration on the Morpheus Vertical Test Bed (VTB). The first Morpheus vehicle was lost in August of 2012 during free-flight testing at Kennedy Space Center (KSC), so the decision was made to perform a helicopter test of the integrated ALHAT System with the Morpheus avionics over the ALHAT planetary hazard field at KSC. The KSC helicopter tests included flight profiles approximating planetary approaches, with the entire ALHAT system interfaced with all appropriate Morpheus subsystems and operated in real-time. During these helicopter flights, the ALHAT system imaged the simulated lunar terrain constructed in FY2012 to support ALHAT/Morpheus testing at KSC. To the best of our knowledge, this represents the highest fidelity testing of a system of this kind to date. During this helicopter testing, two new Morpheus landers were under construction at the Johnson Space Center to support the objective of an integrated ALHAT/Morpheus free-flight demonstration. This paper provides an overview of this helicopter flight test activity, including results and lessons learned, and also provides an overview of recent integrated testing of ALHAT on the second

  11. New technologies for space avionics (United States)

    Aibel, David W.; Dingus, Peter; Lanciault, Mark; Hurdlebrink, Debra; Gurevich, Inna; Wenglar, Lydia


    This report reviews a 1994 effort that continued 1993 investigations into issues associated with the definition of requirements, with the practice concurrent engineering and rapid prototyping in the context of the development of a prototyping of a next-generation reaction jet driver controller. This report discusses lessons learned, the testing of the current prototype, the details of the current design, and the nature and performance of a mathematical model of the life cycle of a pilot operated valve solenoid.

  12. Integrated Modular Avionics: The Challenges (United States)

    Charrier, O.


    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.


    Directory of Open Access Journals (Sweden)

    Jairo Miguel Vergara Díaz


    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.

  14. Reliable avionics design for deep space (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.

  15. General Aviation Activity and Avionics Survey 1984 (United States)


    1-r- 0sn r-C) 1-n4 A rW IniC lol o oo i.VA Cd )’ a .3 -- - I, CdA xd j Cd ’Am. " ’ Ai I-W wU g t 8 weR at lz at w betl wg at i w~ a w~ at ix 8 OM I0at...S ’ TABLE D-1. SDR AIRCRAFT GROUP NAME - FAA MANUFACTURER/MODEL CODES (CONTINUED) SDR FAA SDR FAA SDR FAA PIPER 600 106001... PIPER PAlS 101828 PIPER PA31T 103128 PIPER 600 106010 PIPER PAl8 101832 PIPER PA32 103206 PIPER 600 106012 PIPER PAlS 101834 PIPER PA32 103207 PIPER 600

  16. Avionics Reliability, Its Techniques and Related Disciplines. (United States)


    CENTRALCENTIE DESE DONNEESTDFNTO uv UV EVENTULFLUX ACTNFNS MAINSLIN CORPEancheE3 15-12 A M *1 = Z ]3i 04 1 CD- Le~ ..s2 At 15-13 PILOTES FORMES DE SqLt PARCS...the manufacturing process to incorporate the design changes, and, possibly, retrofit those units already fielded. This not only costs money , but also...initial studies but is useful to control counterfeiting , substitution, unauthorized change, and any lapse of compliance with the military specification

  17. General Aviation Activity and Avionics Survey 1982. (United States)


    is F- C- i I.. <Z< 04K 4 K 4 K mm <.1 -.5 9.JO M 5 I. .J0 - AI. C 1.-’ 01- 1 0 0 -. t- 0 t- a 00 o 0 o0 mo0 w 0 is owe ao Ewa wm wo iso - 24 .0 4%~ 4...0540 41531 PCKARDV1650 49001 FRNKLN4AC50 27002 LYC 0540 41532 PWA 6T02 dT12 FRNKLN4AC0 27003 LYC 0540 41533 PWA JT12 52042 FRNKLN4AC10 27004 LYC 0540

  18. General Aviation Activity and Avionics Survey (United States)


    0 us 4 U 0 ZN i s-~w-w 0 0 09 .j 04 1-. -w N 0I.. 0m Mo N 4% NO N 0 - 0 N MD N 0n0- 0- 0 -0. * 4. M - o* V* 0 0* v0 2j Ge 4cJ 0- ON l 0M M4t 4 0 isO ...0540 41530 RROYCETYNE 54510 FRNKLN4AC150 27002 LYC 0540 41531 RROYCEVIPER 10201 FRNKLN4ACISO 27003 LYC 0540 41533 FRNKLN4ACI5O 27004 LYC 0540 41534

  19. General Aviation Activity and Avionics Survey 1981. (United States)


    iso Is188.1 185- SUMk TAM 2-1 19 118 1976 I0 191 YEAR L. TU DAMWD UNU RKVZSWT A 96X CONVID&NCU INIUL FOR T23 IVŕ - 1661 TRUB UM SIM APPUNIX D. Tot...LYC 0320 41500 NT4CNCCULNACO 2002 LTC 0320 4150 ARSRCMF9731 ’?fB7 FRNKLN4AC150 27003 LVC 0320 41509 ARSkCHW1731 01518 FRNILN4ACISO 27003 LTC 0320 4150

  20. Software Engineering and Its Application to Avionics (United States)


    separate packages. These routines should be documented to include purpose, requirements, flowcharts ; emphasis should be placed on details of the interface...user interface should be easy to learn for the beginner (as are menu driven systems) yet it should not slow down the expert. A typical compromise is to...diagrams (DFDs). Other less used techniques were the State Machine approach and Petri Nets. Traditional mathematical flowcharts ae good for

  1. 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


    ...) 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...

  2. A Strategy for Reforming Avionics Acquisition and Support (United States)


    are observable: " Some problems manifest symptoms in one operating mode but not in another. The pilot directly controls some radar operating modes by...for each flight. Their removals occurred in the flight controls , inertial navigation, head-up display, radar, and instru- ments. Although removals...accrue a comparable amount of service time. 6Automatic stations can test 50 LRU types although the Air Force has chosen to test only 37 of them at the

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

    National Research Council Canada - National Science Library

    Krodel, Jim


    .... 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...

  4. General Aviation Activity and Avionics Survey. Calendar Year 1989 (United States)


    gasoline, 76 million gallons were 100 octane gasoline, 237 million gallons were 100 octane low lead gasoline, and 11 million gallons were automobile ...0 CQI vH 0z Cl0) c 0 0 p. 0l 2: HRM -0 0 P4 E-4 E-4E- HD a. E-0H4 4 AH H H OH) ID IDIDa) Q a4 ) cn H l OH~ a) L) UI H 0~~~ H- 44 O 0 wwHwC. 4 H U la

  5. Avionics for Scaled Remotely Operated Vehicles, Phase I (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...

  6. Advanced Avionics and the Military Aircraft Man/Machine Interface. (United States)


    technItrqtiJ pour d V,’II ’] ITIOU V eau Ut retentis,ement phys1i0l,ZiqUe. iettpor~ CeLt (qUC OUS Seron, trnenes ioarfoi, a evcquer cet aspect te’chnique... traitement en plusleurs 6tapes -L’acquisition du signal acoustique, et sa num~risation apr~s passage dans un banc de filtres on obtient ainsi un sonagraune

  7. Avionics for Scaled Remotely Operated Vehicles, Phase II (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...

  8. NextGen Avionics Roadmap, Version 1.2 (United States)


    addressed through other actions. 6. Work with the JPDO’s Interagency Portfolio and System Analysis ( IPSA ) division to refine benefits, risk...Meteorological Conditions IPSA Interagency Portfolio and System Analysis IRAC Intelligent Resilient Aircraft Control IVHM Integrated Vehicle Health

  9. NextGen Avionics Roadmap Version 2.0 (United States)


    Systems Analysis ( IPSA ) Division has defined multiple NextGen Operational (NGOps) Levels, projecting relative performance and risk based on differing...degrees of capability improvements, as shown in Figure 4. IPSA forecasts include the most likely performance NGOps level (i.e., NGOps 3-4), as the near-term. Figures 5 through 9 de- pict the various programs and capabilities aligned with the various NGOps levels. Factors from the IPSA

  10. Prognostic Health Management for Avionics System Power Supplies

    National Research Council Canada - National Science Library

    Orsagh, Rolf; Brown, Douglas; Roemer, Michael; Dabney, Thomas; Hess, Andrew


    This paper presents an integrated approach to switching mode power supply health management that implements techniques from engineering disciplines including statistical reliability modeling, damage...

  11. Digital Avionics Information System (DAIS): Development and Demonstration. (United States)


    V) - >1 (a 4) cU C - 0 Va ’(1 ) 0 0A*4 (A4-. 4-) C (C (U~ LI) <: kn C V H 3 ) ACCA C 4-) eo V)C CC clO ca cy a: m2 cc co C )co 4) I--V( 0. 4- A a...Polling P 2 BCI Undefined Mode Coitriands P P 3 UCI MTU Shutdown Mode Lo"ands F 4 ULI Mude Commands With interrupts F(Note I) p 5 P7 Undefined Mode

  12. Impact of Advanced Avionics Technology on Ground Attack Weapon Systems. (United States)


    notation, small letters will be used to denote electro-magnetic wave complex amplitudes in the input and output planes whilst capital letters lordre de 20 mn 4 eat possible sans intervention humaine particuliare. Une redondance tras utile peut atre ajoutge sans addition notable de

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

    National Research Council Canada - National Science Library

    Joseph, Kurt


    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...

  14. SWIFT-nanoLV Avionics Platform, Phase I (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,...

  15. Modular, Plug and Play, Distributed Avionics, Phase II (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...

  16. Mapping a product-service-system delivering defence avionics availability


    Settanni, E.; Thenent, N.; Newnes, L.; Parry, G.; Goh, Y. M.


    Long-term support agreements such as availability-based contracts are often associated with the servitization of business models in such sectors as defence aerospace. In practice, there is no unambiguous way of linking availability and service outcomes from an operational perspective; rather, the focus tends to be placed almost exclusively on product-related metrics. To address this gap, this paper outlines a conceptual model of how advanced service outcomes should be delivered under an avail...

  17. Electromagnetic Effects of (Carbon) Composite Materials Upon Avionics Systems (United States)


    travail. La tenue A Il’humiditd est en effet la preoccupation majcure des utilisateurs de plastiques arm~s, la manifestation essontielle du...Resizing The mass saving described in te.e previous piragraph would, if applied to an all-metal concept , result in an improved aircraft performance in terms...8217 - " -;" r 3-10 Fig.7 CFC, items for future concepts TITANIUM WING/FUSELAGE I’ I~ ATTACHM4ENT FITTING TORSION BOX: ~ ~ ~ ,- C.RC SKINS, SPARS it.\\~ U h

  18. Distribution of Aerially Applied Malathion-S{sup 35} in a Forest Ecosystem; Distribution du malathion- {sup 35}S pulverise par avion dans un ensemble ecologique forestier; Raspredelenie malationa, mechennogo S35 i raspylyaemogo s vozdukha dlya izucheniya ehkologicheskoj sistemy lesnykh massivov; Distribucion en un sistema ecologico forestal de malation- 35S pulverizado desde el aire

    Energy Technology Data Exchange (ETDEWEB)

    Giles, Jr., R. H.; Peterle, T. J. [Ohio Co-Operative Wildlife Research Unit, Columbus, OH (United States)


    xylene, du triton X-155 comme emulsifiant et de l'eau. Le malathion avait ete marque avec {sup 35}S par le Radiochemical Centre d'Amersham (Royaume-Uni). On a pulverise par avion une quantite correspondant a une activite de 1 c dans l'un des deux secteurs forestiers de huit hectares, les 15 et 25 mai 1962. L'activite specifique du malathion marque etait de 17,5 m c/m M. On a mesure la distribution des composants de la pulverisation aerienne dans la foret. Des echantillonneurs d'air electriques ont permis d'estimer les quantites emportees hors du secteur d'experience; des ballons d'helium portant des disques de verre depoli ont permis de mesurer la quantite en suspension au-dessus de la frondaison; des disques de verre suspendus verticalement et des echantillons d'ecorces ont permis de mesurer les quantites a diverses hauteurs de la frondaison; des disques de verre et du papier pour analyse a la touche ont permis, non seulement de mesurer la distribution horizontale, mais aussi, de controler un appareil courant de detection de la distribution des produits pulverises. Des echantillons du sol et des pieux marques ont permis d'etudier la distribution au-dessous de la surface. Des echantillons d'eau provenant de cours d'eau intermittents,'des insectes, des mammiferes, des reptiles et des oiseaux ont indique la distribution initiale et ulterieure de l'insecticide et de ses metabolites dans l'ensemble ecologique. Des etudes de la faune ont continue pendant les etes 1961 et 1962 et certaines observations seront encore faites au cours de l'ete 1963. Les resultats preliminaires indiquent que les populations d'insectes sont revenues a la normale au bout d'environ trois semaines et qu'il n'y a pas eu d'effets decelables sur la densite des vertebres dans la surface traitee. (author) [Spanish] Durante el verano de 1962 se estudio la distribucion del malation (0,0-dimetil ditiofosfato del mercaprosuccinato de dietilo) en una zona forestal de la region centro-oriental de Ohio (Estados

  19. 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 (United States)


    la d6finition, pour chaque variable, d’un type analogue aux dclarations de variables FORTRAN, A savoir - Zool en, tableau de boolsens, logique, r~el...reference. 11 est alars possible ds Ilutiliser (sass reserve d’une ergonomic soffisante) cosine one "documentation vivante " et representative du...ou cognitives sur son tableau de bord, sur sa mission. Il dispose aussi de connaissances plus dynamiques, plus fonctionnelles groupees de faqon

  20. Developpements numeriques recents realises en aeroelasticite chez Dassault Aviation pour la conception des avions de combat modernes et des avions d’affaires (United States)


    Cost through Advanced Modelling and Virtual Simulation [La reduction des couts et des delais d’acquisition des vehicules militaires par la modelisation...sont les 6quations de restitution, par le mod~e, des frdquences et des amortissements des modes adrodlastiques mesurds h une prdcision F- donnde. Afin... amortissements mesurds h 37800 Pa et 60000 Pa (points nettemnent inferieurs A la vitesse critique). Comme le montre ce diagramme, le calcul, recal6 h

  1. Civil mini-RPA's for the 1980's: Avionics design considerations. [remotely piloted vehicles (United States)

    Karmarkar, J. S.


    A number of remote sensing or surveillance tasks (e.g., fire fighting, crop monitoring) in the civilian sector of our society may be performed in a cost effective manner by use of small remotely piloted aircraft (RPA). This study was conducted to determine equipment (and the associated technology) that is available, and that could be applied to the mini-RPA and to examine the potential applications of the mini-RPA with special emphasis on the wild fire surveillance mission. The operational considerations of using the mini-RPA as affected by government regulatory agencies were investigated. These led to equipment requirements (e.g., infra-red sensors) over and above those for the performance of the mission. A computer technology survey and forecast was performed. Key subsystems were identified, and a distributed microcomputer configuration, that was functionally modular, was recommended. Areas for further NASA research and development activity were also identified.

  2. 76 FR 70044 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes (United States)


    ... was discovered that the LH [left-hand] elevator lower stop assembly was broken at the level of the... post-flight inspection, it was discovered that the LH [left-hand] elevator lower stop assembly was... to be jammed. During the post-flight inspection, it was discovered that the LH elevator lower stop...

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

    CSIR Research Space (South Africa)

    Esser, MJD


    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...

  4. Core Logistics Capability Policy Applied to USAF Combat Aircraft Avionics Software: A Systems Engineering Analysis (United States)


    cannot make a distinction between software maintenance and development” (Sharma, 2004). ISO /IEC 12207 Software Lifecycle Processes offers a guide to...synopsis of ISO /IEC 12207 , Raghu Singh of the Federal Aviation Administration states “Whenever a software product needs modifications, the development...Corporation. Singh, R. (1998). International Standard ISO /IEC 12207 Software Life Cycle Processes. Washington: Federal Aviation Administration. The Joint

  5. Software-Defined Avionics and Mission Systems in Future Vertical Lift Aircraft (United States)


    Retrieved from IEEE Xplore website: Kopetz, H., Ademaj, A., & Grillinger, P. (2005). The...routines, allowing time and space (memory) partitioning, health monitoring (error detection and reporting), and communications via “ports.” ( IEEE , 2008...decided to go with another emerging standard: IEEE 1394, better known by its 13 consumer-electronics trade name “Firewire.” This solution provided

  6. A survey on electromagnetic interferences on aircraft avionics systems and a GSM on board system overview (United States)

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


    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.

  7. Modeling and Simulation of Avionics Systems and Command, Control and Communications Systems (United States)


    CONDITIONS: ALL BEGIN IN THINK STATE _ ~(2) - F6 w 4(3) NTm35 E(RT)98.246 4 (1 -4-0NT a25 E’(RT) 3.415 L0 1OO 200 300 400 500 600 700 800 900 NUMBER OF...vibrations ou acca - llretions, Li En offet. is vol tactique tel qua le pratique l’Armle de Terra Frangalse, consiste A4 valer au plus prls du sal (hauteur

  8. Advances in real-time millimeter-wave imaging radiometers for avionic synthetic vision (United States)

    Lovberg, John A.; Chou, Ri-Chee; Martin, Christopher A.; Galliano, Joseph A., Jr.


    Millimeter-wave imaging has advantages over conventional visible or infrared imaging for many applications because millimeter-wave signals can travel through fog, snow, dust, and clouds with much less attenuation than infrared or visible light waves. Additionally, passive imaging systems avoid many problems associated with active radar imaging systems, such as radar clutter, glint, and multi-path return. ThermoTrex Corporation previously reported on its development of a passive imaging radiometer that uses an array of frequency-scanned antennas coupled to a multichannel acousto-optic spectrum analyzer (Bragg-cell) to form visible images of a scene through the acquisition of thermal blackbody radiation in the millimeter-wave spectrum. The output from the Bragg cell is imaged by a standard video camera and passed to a computer for normalization and display at real-time frame rates. An application of this system is its incorporation as part of an enhanced vision system to provide pilots with a synthetic view of a runway in fog and during other adverse weather conditions. Ongoing improvements to a 94 GHz imaging system and examples of recent images taken with this system will be presented. Additionally, the development of dielectric antennas and an electro- optic-based processor for improved system performance, and the development of an `ultra- compact' 220 GHz imaging system will be discussed.

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

  10. Automated Data Base Implementation Requirements for the Avionics Planning Baseline - Army (United States)



  11. Space Shuttle Program Primary Avionics Software System (PASS) Success Legacy -Major Accomplishments and Lessons Learned (United States)

    Orr, James K.


    This presentation has shown the accomplishments of the PASS project over three decades and highlighted the lessons learned. Over the entire time, our goal has been to continuously improve our process, implement automation for both quality and increased productivity, and identify and remove all defects due to prior execution of a flawed process in addition to improving our processes following identification of significant process escapes. Morale and workforce instability have been issues, most significantly during 1993 to 1998 (period of consolidation in aerospace industry). The PASS project has also consulted with others, including the Software Engineering Institute, so as to be an early evaluator, adopter, and adapter of state-of-the-art software engineering innovations.

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

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


    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.

  13. Thermal Control Subsystem Design for the Avionics of a Space Station Payload (United States)

    Moran, Matthew E.


    A case study of the thermal control subsystem development for a space based payload is presented from the concept stage through preliminary design. This payload, the Space Acceleration Measurement System 2 (SAMS-2), will measure the acceleration environment at select locations within the International Space Station. Its thermal control subsystem must maintain component temperatures within an acceptable range over a 10 year life span, while restricting accessible surfaces to touch temperature limits and insuring fail safe conditions in the event of loss of cooling. In addition to these primary design objectives, system level requirements and constraints are imposed on the payload, many of which are driven by multidisciplinary issues. Blending these issues into the overall system design required concurrent design sessions with the project team, iterative conceptual design layouts, thermal analysis and modeling, and hardware testing. Multiple tradeoff studies were also performed to investigate the many options which surfaced during the development cycle.

  14. Enhancing Autonomy of Aerial Systems Via Integration of Visual Sensors into Their Avionics Suite (United States)


    context of Singapore. a. Natural Environment • The lighting conditions of the POE range from full sunlight to minimal outdoor moonlight at night...possible route that visits all the cities exactly once before returning to the city of origin, a target-acquisition search path attempts to find the

  15. Real-time millimeter-wave imaging radiometer for avionic synthetic vision (United States)

    Lovberg, John A.; Chou, Ri-Chee; Martin, Christopher A.


    ThermoTrex Corporation (TTC) has developed an imaging radiometer, the passive microwave camera (PMC), that uses an array of frequency-scanned antennas coupled to a multi-channel acousto-optic (Bragg cell) spectrum analyzer to form visible images of a scene through acquisition of thermal blackbody radiation in the millimeter-wave spectrum. The output of the Bragg cell is imaged by a standard video camera and passed to a computer for normalization and display at real-time frame rates. One application of this system could be its incorporation into an enhanced vision system to provide pilots with a clear view of the runway during fog and other adverse weather conditions. The unique PMC system architecture will allow compact large-aperture implementations because of its flat antenna sensor. Other potential applications include air traffic control, all-weather area surveillance, fire detection, and security. This paper describes the architecture of the TTC PMC and shows examples of images acquired with the system.

  16. STOL terminal area operating systems (aircraft and onboard avionics, ATC, navigation aids) (United States)

    Burrous, C.; Erzberger, H.; Johnson, N.; Neuman, F.


    Operational procedures and systems onboard the STOL aircraft which are required to enable the aircraft to perform acceptably in restricted airspace in all types of atmospheric conditions and weather are discussed. Results of simulation and flight investigations to establish operational criteria are presented.

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

  18. Cold Regions Logistic Supportability Testing of Electronic, Avionic and Communications Equipment. (United States)


    Comment : 2. Have all data collected been reviewed for correctness and completeness? YES NO . Comment : 3. Were the facilities, test equipment...insufficient test planning? YES NO . Comment : 5. Were the test results compromised in any way due to test performance procedures? YES NO . Comment : 6. Were the...test results compromised in any way due to test control pro- cedures? YES NO Comment : 7. Were the test results compromised in any way due to data

  19. The Mars Microprobe Mission: Advanced Micro-Avionics for Exploration Surface (United States)

    Blue, Randel


    The Mars Microprobe Mission is the second spacecraft developed as part of the New Millennium Program deep space missions. The objective of the Microprobe Project is to demonstrate the applicability of key technologies for future planetary missions by developing two probes for deployment on Mars. The probes are designed with a single stage entry, descent, and landing system and impact the Martian surface at speeds of approximately 200 meters per second. The microprobes are composed of two main sections, a forebody section that penetrates to a depth below the Martian surface of 0.5 to 2 meters, and an aftbody section that remains on the surface. Each probe system consists of a number of advanced technology components developed specifically for this mission. These include a non-erosive aeroshell for entry into. the atmosphere, a set of low temperature batteries to supply probe power, an advanced microcontroller to execute the mission sequence, collect the science data, and react to possible system fault conditions, a telecommunications subsystem implemented on a set of custom integrated circuits, and instruments designed to provide science measurements from above and below the Martian surface. All of the electronic components have been designed and fabricated to withstand the severe impact shock environment and to operate correctly at predicted temperatures below -100 C.

  20. Validation of the Operating and Support Cost Model for Avionics Automatic Test Equipment (OSCATE). (United States)


    AFLCR 65-1 (56) DOD 4140 -32 (74) CODES DATA LISTED BY. ALC code, Division Code, Equipment Specialist Code, NSN DATA ORDERING SEQUENCEs This data is...PAJ6A 4140 -01-043-5035 .... IL0UERft1TfR 1002 1 319.55 22720 1 0 0 1003 0 14.55 0 0 0 10.00 0 0 1004 0 0 32.454 16.42 0 0 0 0 0 0 0 127 1101 PAJHA 4920...5320 480 CONTINUE 5330 60 To 150 5340 5350C *...*~****.*.s*..** 5360C *****eOUTPUT OPTION 7 5370C e**ss*** sae ******* 5380 500 PRINT 510 5390 510

  1. 3D Navigation and Integrated Hazard Display in Advanced Avionics: Workload, Performance, and Situation Awareness (United States)

    Wickens, Christopher D.; Alexander, Amy L.


    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.

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

  3. Ionizing Radiation Environment on the International Space Station: Performance vs. Expectations for Avionics and Material (United States)

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


    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.

  4. The Ionizing Radiation Environment on the International Space Station: Performance vs. Expectations for Avionics and Materials (United States)

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


    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.

  5. Flight Test Evaluation of AVOID I (Avionic Observation of Intruder Danger) Collision Avoidance System (United States)


    memory registers A through G ( 2048 bit shift registers) for each of the basic altitude bands (1+26, 113 1+6) to store intruder responses. Since the EV 11z iIIV~ ~l~~ NADlC-75056-60_ _ _- 2 w< -I- LI- ~jw 0IU oo2 W I aJ W %L6fI9~~AVdI tVOV~ aN9Ao ccH % VdI I11813iA-di V GN Ed a3IV0 %AIII1IilV11W...tei mix ;;; c le z - Is’ %~~~~~~~~~~;s AJIiV1 VdI ~ %AIIV~ v~iO VIR 1ý 123 Lz NADC-7056-6 w, M w o ~2IV ONY Ed CIRNIGVNOO at p 00 CLt % 118I3iAVldSIC3

  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


    ... (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. Suicide plane crash against nuclear power plants; Avion suicide contre centrales nucleaires

    Energy Technology Data Exchange (ETDEWEB)

    Richard, A


    Cea (French atomic energy commission) and EDF (Electricity of France) are reassessing their safety standards concerning suicide plane attacks against nuclear facilities. The general idea is to study the non-linear behaviour of reinforced concrete in case of mechanical impact. American studies carried out in 1988 show that a F-14 phantom crashing into a 3,6 meter thick wall at a speed of 774 km/h penetrates only the first 5 cm of the wall. More recent studies performed in Germany and based on computerized simulations show that the reactor containment can sustain impacts from a F15 plane or even from a 747-Boeing but contiguous buildings like the one which houses spent fuels might be more easily damaged because of their metal roofing. (A.C.)

  8. Occupational Field 66 (Avionics) Less MOS’s 6682, 6683 and 6689 Task Analysis. (United States)



  9. 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. (United States)


    BIT A,, M 115V ACBB N 270V DC RETURN p 115V ACCA R IW DC POWER S INTERLOCK RETURN T STRUCTURE GROUND U FIBER OPTICS BUS V ADDRESS BIT A,, w...Ontario Kl A 0K2 Canada FGAN- FFM , D-5307 Wachtberg-Werthhoven Germany Concordia University, 7141 Sherbrooke St. W. Montreal, QueH4BlRG Canada

  10. 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). (United States)


    17 Jan 68 0 S Dell Rapidis, S.Dak. USA. Bonanza Propeller cylinder attach screws. Propeller in service approx. 170 hr . F85 Beech K35 5 Sep 69 4 D Provo...Ice land Iraq Ireland Jamaica (1966 -1981) Japan (1973 - Feb. 81) Kenya Lethoso Malaysia Ma law i Mal ta Mexico Netherlands New Zealand Norway...Laboratories, Australia. E. Keller Federal Aircraft Accident Investigation Bureau, Switzerland. Quek Seng Kiew Civil Aviation Dept., Malaysia . Tor B

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


    the turning aircraft passes ahead of its straight-line companion , possibly with a vertical spacing of several hundred feet. Between 40 secs. and 20... Chef du contr8le d’approche et d’a6rodrome (tour) At Bruxelles-National ** Chef du contr6le At Bruxelles-National 20F-9 RE RCIEMENTS Nous tenons A...Voies adriennes (Belgique), compdtent en contr6le en route et en contr6le d’approche et actuellemont chef du Service de contr8le d’approche-tour et

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

  13. Accelerated tests for the soft error rate determination of single radiation particles in components of terrestrial and avionic electronic systems

    International Nuclear Information System (INIS)

    Flament, O.; Baggio, J.


    This paper describes the main features of the accelerated test procedures used to determine reliability data of microelectronics devices used in terrestrial environment.This paper focuses on the high energy particle test that could be performed through spallation neutron source or quasi-mono-energetic neutron or proton. Improvements of standards are illustrated with respect to the state of the art of knowledge in radiation effects and scaling down of microelectronics technologies. (authors)

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

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


    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.

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


    Vigilance and Performance in Automatized Systems. Org.: Prof A. Coblentz Laboratoire d’Anthropologie et d’Ecologie Humaine - Universit& Rene Descartes , PARIS...Humaine - Universit6 Ren6 Descartes , PARIS, September 1988 BOY G., CEP-Onera "Assistance A l’Opdrateur: Une Approche de l’Intelligence Artificielle...Appliqi6e, Universit6 Ren6 Descartes - Paris V "Effect of Monotony on Vigilance and Biomechanical Behaviour" In: Commission of European Communities

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

    Index Scriptorium Estoniae

    Chalvin, Antoine


    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

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


    However, the TF-33s would greatly enhance the mission capabilities of the aircraft. The addition of winglets will increase range and decrease fuel...a sound and capable system. There are certainly some improvements that can be made. A better boom with better aerodynamic design would help

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


    rates. A 4D RNAV capability is most easily achieved by "wrapping" a time-navigation capability around a 3D FMS. It is estimated that fifty percent of...U.S. jet transports will have been delivered with a full 3D FMS by 1995 without any special effort to implement 4D RNAV ATC operations. Inclusion of...Mechanics, Vol. 84, No. 3, pp. 247-257, 1962 EICHENBERGER W. "Flugwetterkunde", Schweizer Druck - und Verlagshaus AG, ZUrich, 2. Auflage, 1962 KELLEY H.J

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


    Sep 1983 "Reliability Parameter of Additive Plated Through Hoics," William E. Greiner , Kollmorgen Corporation, 1rAnnual "Guidelines for Surface Mounting...Militare Etat-Major delIs Force Adienne Ufficio del Delegato Nazionaic all*AGARD Quartier Reine Elisabeth Aeroporto Pratica di Mare Rue d’Evere, 1140

  20. A Logistic Life Cycle Cost-Benefit Analysis of Power Quality Management in the Avionics Repair Facility

    National Research Council Canada - National Science Library

    Kennedy, Christopher


    .... The implementation of power quality management can result in wide scale logistical support changes in regards to the life cycle costs of maintaining the DoD's current inventory of sensitive electronic equipment...

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

  2. Integrated Test Bed Facility (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...

  3. Injury Prevention in Aircraft Crashes: Investigative Techniques and Applications (la Prevention des lesions lors des accidents d’ avions: les techniques d’investigation et leurs applications) (United States)


    tissue produces compression stress. The negative of compression stress is tension or distraction stress, produced by force which tends to pull tissue...feasible. Anatomic sites, such as maxillary and frontal sinuses which are important in aviation physiology but seldom examined 6-5 at autopsy, are... distraction or partial incapacitation during a critical phase of flight. Detection of quinidine would suggest a history of heart disease not

  4. 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. (United States)


    represent only a software cast problem or pose a logistics problem as well. If the problem is purely one of software support costs, then the team during the requirements phase resulted in a 174-page Ada requirements document. This document restated the " Alevel " specifications in a mre...Instructions in addition to AN/UYK-20(V) J. AN/AYIC-14(V) Extended Arithmetic Unit (EAU) instructions added to MATH PAC. k. Page registers increased from 1 to 4

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


    Chef de Departement Propulsion Institut ffir Strahlantriebe Dassault Aviation Wemer Heisenberg-Weg 39 78 quai Marcel Dassaiult W-8014 Neubiberg 92214...annoyance that adds out-of-bounds selection* available for a to tne annoyance produced by the acoustlc total nlne-point scale. Two companion level of...NAVIGATION AERIENNE CHEF DE LA DIVISION NUISANCE 245, RUE LECOURBE . 75732 PARIS - FRANCE RESUME Pendant longtemps Is bruit a iti considiri Apris un exposi

  6. 76 FR 47520 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Model ATR42 and ATR72 Airplanes (United States)


    .... The elevators seemed to be jammed. During the post-flight inspection, it was discovered that the LH [left-hand] elevator lower stop assembly was broken at the level of the angles, which may have prevented... [left-hand] elevator lower stop assembly was broken at the level of the angles, which may have prevented...

  7. 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)



    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.)

  8. Workshop on Avionics Corrosion Control: Meeting of the Structures and Materials Panel of AGARD (62nd) Held in Hovik (Norway) on 16-17 April 1986. (United States)


    operator not smoke in the recording area and that the heads not be cleaned with a halogenated cleaning solvent. Use an alcohol . J. Connector 1. Radar...frplaed a drop of sealant is placed in the area where wott is accmplshe. RTN’- 118 has been replaed with dlear RTV-3 140 which is a dlear alcohol isolate 7-6 Alumimue Effects of corrosion on aluminum runs ae open circuits caused by oxydes . The mechanism Is simple : chloride Ions make

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

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

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


    NIilitary,%ircsTai R ite P I tti71gSI ’ --- -’I Uttotmmand. Conttrol. Cumin ITtcatituns anti IBegye Intelligence ACS Manetiver Control Ssisrnm (’A~IAL...has either been introduced recently or is high workload and stress on the unaided operator, and it is imminent. These are reviewed elsewhere in this

  12. Using software metrics and software reliability models to attain acceptable quality software for flight and ground support software for avionic systems (United States)

    Lawrence, Stella


    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.

  13. 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 (United States)

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


    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.

  14. 77 FR 67557 - Special Conditions: ATR-GIE Avions de Transport Regional, Models ATR42-500 and ATR72-212A... (United States)


    ..., Models ATR42-500 and ATR72-212A Airplanes; Aircraft Electronic System Security Protection From... exploited by unauthorized access to airplane systems, data buses, and servers. Therefore, these special... ATR42-500 and ATR72-212A airplanes. 1. Airplane Electronic System Security Protection from Unauthorized...

  15. 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. (United States)


    of Aperture Phase Distribution In our version of the synthesis technique, the phase of the aperture field is expanded into Zernike or circle...polynomials, i.e., $(p ,<!.)= Z S c„„e^"* IV„(p), (34) n=1 m=-n )^ where p and ^ are the polar aperture coordinates and c_ = c . The Zernike ...scenarios. The experiments on the SH- 3D helicopter compared the loop antennas and existing wire antennas. Groundwave radiated field at different

  16. Euroopa kolm nobedaimat gaselli / Askur Alas

    Index Scriptorium Estoniae

    Alas, Askur, 1973-


    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

  17. Survey of symbology for aeronautical charts and electronic displays : navigation aids, airports, lines, and linear patterns (United States)


    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 ...

  18. Détermination des performances aéro-thermo-propulsives des avions civils par une analyse exergétique de solutions haute-fidélité CFD-RANS


    Arntz , A.


    A new exergy-based formulation is derived for the assessment of the aerothermopropulsive performance of civil aircraft. The choice of exergy is motivated by its ability to provide a well-established and consistent framework for the design of aerospace vehicles. The output of the derivation process is an exergy balance between the exergy supplied by a propulsion system or by heat transfer, the mechanical equilibrium of the aircraft, and the exergy outflow and destruction within the control vol...

  19. 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


    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.

  20. 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) (United States)


    baisse du niveas da plateau supersonique (Fig.9). L’onde de choc DCZ 0,30 0068avance de 1% dc Ia corde ci cc dilplacement ye rilperesic sur toute CX 104...propulsion component, which is very helpful for a better understanding of the underlying pheno- mena and finding possible areas of improve- men t.I...of excessive, and for a plane and plug nozzle of a hypersonic aircraft, for probably prohibitive, fine meshes. It has to be men - a highly integrated

  1. The Utilization of Advanced Composites in Military Aircraft Held in San Diego, California on 7-11 October 1991 (L’Emploi des Materiaux Composites de Pointe pour les Avions Militaires) (United States)


    layered media , a (4.17). we may express this as for example in Kennett 191. P(x,,0) - exp((x,- -1 )Rr)exa(hr -1 R-., The advantage of the formulation...riuinii.iiuL-e S.P 11(17 .IS 1- 4(19 I hic ’’oict i 0i .1t I CL 101 irk .1rujiiiuuiid int tetd IC t 11 R It Krieger. filIe RV(iiitifl htst ~k:’ rI lir i;C

  2. 新一代航空电子总线系统结构研究%A Preliminary Study on Architecture of Data Bus System of New Generation Avionics

    Institute of Scientific and Technical Information of China (English)




  3. Research on the High-level Lightweight Protocol of Fibre Channel in Avionics Environment%航空电子光纤通道高层轻量协议的研究

    Institute of Scientific and Technical Information of China (English)

    王世奎; 王国庆; 王红春; 李新民



  4. 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) (United States)


    passive distension (and lower perfusion). Pertinent to the present discussion resistance to flow) of the capillaries, and to the is that acceleration...chest counterpressuse is used to prevent over- distension of the lungs, and sufficient counter- pressure is applied elsewhere to limit venous pooling and...musculature. the same position in the absence of muscular contraction and in the absence of a pressure InadeQuate &unpor from thoacic counter-oreasure

  5. Analytical Qualification of Aircraft Structures: Meeting of the Structures and Materials Panel of AGARD (70th) Held in Sorrento, Italy on 1-6 April 1990 (La Qualification Analytique des Structures d’Avion). (United States)


    sources of preliminary evalution are the software theor and validation documents. E amination of the theoretical bsis and numerical algorithms, together...knowledge reflected In production models. However, It Is a horror for him to see that production models are composed by stress people who insufficiently

  6. 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) (United States)


    cooperation Spanish but we could say : El Lado Maquina en la in which scientists of NATO Countries can exchange Tecnologia de ia Relacion Hombre-Maquina en los...growing additive mixing are supported. graphical power in 2D- and 3D aspects we decided on a general purpose architecture (Texas 34020). 3.7. Displays...display a target wireframe image with 100 3D points, connected via 300 3D -vectors, in realtime (60 Hz.) update rate to the HMD. 7.3. X31A-HDD One aspect of

  7. Applications of Superconductivity to Avionics: Proceedings of a Conference Held in Bath, England on May 7-8, 1990 (Les Applications de la Supraconductivite dans le Domains de l’Avionique) (United States)


    old. Lanthanum Gallate may avoid this problem. The progress has been rapid since the discovery Sapphire has also been studied, but results were of...surface resistance 43 times lower than that of Cryostat copper has been measured by this method for YBCO deposited on Lanthanum Aluminate (Ref. 5...temperature and 10 GHz. It At the present time, Lanthanum Aluminate seems varies like the square root of the frequency while to be the best candidate. Its

  8. Avionics Interface Data Summaries: A-10A, EF-111A, F-4E, F-4G, F-15A, F- 16A, F-111A, F-111E, F-111F, RF-4C (United States)


    producing an error signal "nc:t•:.; that a" invalid verd has beer -eceived. h.2.2 f•rLn•5-Irt1 M4ole - When operating in the transmitting mode, the...ES Gose 0 kint SCALE FACTOR: J * I RESOLUTIOiN: (TBOo1) Electrical Chrarte-i’stics (Continued on next page) SOURCE: Aux1li:ry Flight Reference System

  9. 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)



    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.)

  10. 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). (United States)


    Convention on International Civil Aviation, Second Edition , March 1966. 5. WORLD AIRLINE ACCIDENT SUMMARY. Civil Aviation Authority, (Great Britain...people who either provided information, or who suggested other sources of information for the current edition of this survey. E.M.R. Alexander Civil...Waverley, New Zealand. F-28C Tail rotor drive shaft. Fatigue strength reduc- ed by softened condition & surface decarbur- isation. AISA 4130 steel. Ref: NZ

  11. Proceedings Papers of the AFSC (Air Force Systems Command) Avionics Standardization Conference (2nd) Held at Dayton, Ohio on 30 November-2 December 1982. Volume 3. Embedded Computer Resources Governing Documents. (United States)


    1. Validation of computer resource requirements, including soft - ware, risk analyses, planning, preliminary design, security where applicable (DoD...Technology Base Program for soft - ware basic research, exploratory development, advanced devel- opment, and technology demonstrations addressing critical... chancres including agement Procedures (O/S CMP). The basic alose iact of Cr other clu configuration management approach con- tained in the CRISP will be

  12. 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 (United States)


    souries of radio andrada emsin in theevironment. heSO syte prvie va.luableemt gter cla&-,tfication intformation "*to the hoot platform’s Commtand and...inforsation is available, only its essence need be rapeited here. Aircraft The principal attack aircraft Involved in CAS will be the AV-aB, A-61, and F/ systIme automatics. En effet . It systime expert slpare clairement I* savoir-faire (bass de connaissence) de IPenimation informatique (le moteur

  13. Contribution à la simulation en 3D des mouvements de précession générés par des contraintes de contact unilatérales dans les moteurs d'avion


    Paltrinieri , J; Nyssen , F; Parent , M.-O; Batailly , Alain


    International audience; The reduction of nominal clearances between a rotating bladed-disk and its surrounding casing yields a very significant increase of the overall engine efficiency. However, the smaller the clearances, the higher the risk of structural contacts between static and rotating components that may lead to hazardous interaction phenomena. In particular, at the fan stage of an aircraft engine, impacts between the rotating bladed-disk and the casing may generate forward or backwa...

  14. 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.


    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.)

  15. A study of compositional verification based IMA integration method (United States)

    Huang, Hui; Zhang, Guoquan; Xu, Wanmeng


    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.

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

  17. Aging Methodologies and Prognostic Health Management for Electrolytic Capacitors (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...

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

  19. Operationally Responsive Spacecraft Subsystem, Phase I (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....

  20. Analyzing and Specifying Reusable Security Requirements (United States)


    avionics applications and ecommerce applications need to specify levels of identification, authentication, authorization, integrity, privacy , etc. At...sections specifying functional requirements. Thus, the functional requirements for an embedded avionics application and an ecommerce website may have... Privacy (a.k.a., confidentiality), which is the degree to which sensitive data and communications are kept private from unauthorized individuals and

  1. Design and Development of a Rapid Research, Design, and Development Platform for In-Situ Testing of Tools and Concepts for Trajectory-Based Operations (United States)

    Underwood, Matthew C.


    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.

  2. 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.


    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.

  3. Radiation Mitigation Methods for Reprogrammable FPGA, Phase I (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...

  4. The Next Great Ship: NASA's Space Launch System (United States)

    May, Todd A.


    Topics covered include: Most Capable U.S. Launch Vehicle; Liquid engines Progress; Boosters Progress; Stages and Avionics Progress; Systems Engineering and Integration Progress; Spacecraft and Payload Integration Progress; Advanced Development Progress.

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


    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...


    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...

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

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

  10. Pilot visual acquisition of traffic : operational communications from air traffic control operational communication. (United States)


    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...


    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...

  12. Analysis and Synthesis of Distributed Real-Time Embedded Systems

    DEFF Research Database (Denmark)

    Pop, Paul; Eles, Petru; Peng, Zebo

    like automotive electronics, real-time multimedia, avionics, medical equipment, and factory systems. The proposed analysis and synthesis techniques derive optimized implementations that fulfill the imposed design constraints. An important part of the implementation process is the synthesis...

  13. National Skills Standards Development Program: Organization and Operation of Technical Committees To Develop National Skill Standards for Competency in the Electronics Industry. The Third Party Summative Evaluation of the Electronic Industries Foundation Project. Phase I & II. Final Report. (United States)

    Losh, Charles

    The Electronics Industries Foundation was awarded a project to develop national entry-level standards and a certification system. Ten specialties were included: automotive electronics, avionics, biomedical electronics, business machines, consumer products electronics, general electronics, industrial electronics, instrumentation, microcomputer, and…

  14. Next generation space interconnect research and development in space communications (United States)

    Collier, Charles Patrick


    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.

  15. 100TH T-38C Delivery Ceremony (Defense Acquisition Review Journal)

    National Research Council Canada - National Science Library

    Ott, David D; Davis, James B


    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...

  16. A Self-Regulating Freezable Heat Exchanger for Spacecraft, Phase II (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. PEAC: A Power-Efficient Adaptive Computing Technology for Enabling Swarm of Small Spacecraft and Deployable Mini-Payloads (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...

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

    National Research Council Canada - National Science Library

    Mossberg, Thomas


    .... 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...

  19. Ada Linear-Algebra Program (United States)

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


    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.

  20. Improved UAS Robustness through Augmented Onboard Intelligence, Phase I (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. Predictive Software Cost Model Study. Volume I. Final Technical Report. (United States)


    development phase to identify computer resources necessary to support computer programs after transfer of program manangement responsibility and system... classical model development with refinements specifically applicable to avionics systems. The refinements are the result of the Phase I literature search

  2. Towards Prognostics for Electronics Components (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...

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

  4. Recent Projects in the KSC Applied Physics Lab (United States)

    Starr, Stanley


    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.

  5. MINESTRONE (United States)


    Symbiote to operate within Android and other mobile computing devices. The use of Symbiotes represents a practical and effective protection mechanism...was accepted at EuroSys. AppDoctor was successfully used to find real bugs in Android apps made by large companies, and demonstrated an over 10x...DAVID G. HAGSTROM, Chief Program Manager Avionics Vulnerability Mitigation Branch Avionics Vulnerability Mitigation Branch Spectrum Warfare

  6. An Evaluation of an Ada Implementation of the Rete Algorithm for Embedded Flight Processors (United States)


    computers was desired. The VAX VMS operating system has many built-in methods for determining program performance (including VAX PCA), but these methods... overviev , of the target environment-- the MIL-STD-1750A VHSIC Avionic Modular Processor ( VA.IP, running under the Ada Avionics Real-Time Software (AARTS... computers . Mil-STD-1750A, the Air Force’s standard flight computer architecture, however, places severe constraints on applications software processing

  7. Structuring Formal Requirements Specifications for Reuse and Product Families (United States)

    Heimdahl, Mats P. E.


    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.

  8. Man-machine interface requirements - advanced technology (United States)

    Remington, R. W.; Wiener, E. L.


    Research issues and areas are identified where increased understanding of the human operator and the interaction between the operator and the avionics could lead to improvements in the performance of current and proposed helicopters. Both current and advanced helicopter systems and avionics are considered. Areas critical to man-machine interface requirements include: (1) artificial intelligence; (2) visual displays; (3) voice technology; (4) cockpit integration; and (5) pilot work loads and performance.

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

    Wray, Richard B.


    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.

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

    Wray, Richard B.


    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.

  11. 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


    Angulo Rebaza, Cesar Adolfo; Angulo Rebaza, Cesar Adolfo


    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...

  12. 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)



    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.)

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

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


    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.

  14. A Comparison of Bus Architectures for Safety-Critical Embedded Systems (United States)

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


    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.

  15. An Approach for On-Board Software Building Blocks Cooperation and Interfaces Definition (United States)

    Pascucci, Dario; Campolo, Giovanni; Candia, Sante; Lisio, Giovanni


    This paper provides an insight on the Avionic SW architecture developed by Thales Alenia Space Italy (TAS-I) to achieve structuring of the OBSW as a set of self-standing and re-usable building blocks. It is initially described the underlying framework for building blocks cooperation, which is based on ECSSE-70 packets forwarding (for services request to a building block) and standard parameters exchange for data communication. Subsequently it is discussed the high level of flexibility and scalability of the resulting architecture, reporting as example an implementation of the Failure Detection, Isolation and Recovery (FDIR) function which exploits the proposed architecture. The presented approach evolves from avionic SW architecture developed in the scope of the project PRIMA (Mult-Purpose Italian Re-configurable Platform) and has been adopted for the Sentinel-1 Avionic Software (ASW).

  16. Next Generation Reliable Transport Networks

    DEFF Research Database (Denmark)

    Zhang, Jiang

    the wavelength and fiber assignment problem is proposed and implemented for avionic optical transport networks. Simulation results give out resource consumptions and prove the efficiency of the proposed mechanisms. Finally, a Home Environment Service Knowledge Management system is proposed. Through ontology...... technologies, a knowledge base is constructed to represent the whole information of a home environment. By applying the reasoner tool, the proposed system manages to keep the consistency in a home environment and helps all software configure and update procedures across multiple vendors....... of criticality and security, there are certain physical or logical segregation requirements between the avionic systems. Such segregations can be implemented on the proposed avionic networks with different hierarchies. In order to fulfill the segregation requirements, a tailored heuristic approach for solving...

  17. Fleet retrofit report (United States)


    Flight tests are evaluated of an avionics system which aids the pilot in making two-segment approaches for noise abatement. The implications are discussed of equipping United's fleet of Boeing 727-200 aircraft with two-segment avionics for use down to Category 2 weather operating minima. The experience is reported of incorporating two-segment approach avionics systems on two different aircraft. The cost of installing dual two-segment approach systems is estimated to be $37,015 per aircraft, including parts, labor, and spares. This is based on the assumption that incremental out-of-service and training costs could be minimized by incorporating the system at airframe overhaul cycle and including training in regular recurrent training. Accelerating the modification schedule could add up to 50 percent to the modification costs. Recurring costs of maintenance of the installation are estimated to be of about the same magnitude as the potential recurrent financial benefits due to fuel savings.

  18. Orion FSW V and V and Kedalion Engineering Lab Insight (United States)

    Mangieri, Mark L.


    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.

  19. Systems Engineering and Integration (SE and I) (United States)

    Chevers, ED; Haley, Sam


    The issue of technology advancement and future space transportation vehicles is addressed. The challenge is to develop systems which can be evolved and improved in small incremental steps where each increment reduces present cost, improves, reliability, or does neither but sets the stage for a second incremental upgrade that does. Future requirements are interface standards for commercial off the shelf products to aid in the development of integrated facilities; enhanced automated code generation system slightly coupled to specification and design documentation; modeling tools that support data flow analysis; and shared project data bases consisting of technical characteristics cast information, measurement parameters, and reusable software programs. Topics addressed include: advanced avionics development strategy; risk analysis and management; tool quality management; low cost avionics; cost estimation and benefits; computer aided software engineering; computer systems and software safety; system testability; and advanced avionics laboratories - and rapid prototyping. This presentation is represented by viewgraphs only.

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

    Dowden, Donald J.; Bessette, Denis E.


    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.

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

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


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


    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...

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


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


    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...

  4. Investigation of single event latchup

    International Nuclear Information System (INIS)

    Xue Yuxiong; Yang Shengsheng; Cao Zhou; Ba Dedong; An Heng; Chen Luojing; Guo Gang


    Radiation effects on avionics microelectronics are important reliability issues for many space applications. In particular, single-event latchup (SEL) phenomenon is a major threat to CMOS integrated circuits in space systems. To effectively circumvent the failure, it is important to know the behavior of such devices during latchup. In this paper, the mechanisms for SEL in CMOS devices are investigated. Several microelectronic devices used in avionics are tested using heavy ion beams, pulsed laser and 252 Cf source. Based on the SEL test results, SEL-hardening and monitoring methods for preventing SEL from the systems design level are proposed. (authors)

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


    Alvarado Torres, Wilson Emilio; Alvarado Torres, Wilson Emilio


    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...

  6. On Board Data Acquisition System with Intelligent Transducers for Unmanned Aerial Vehicles (United States)

    Rochala, Zdzisław


    This report presents conclusions from research project no. ON50900363 conducted at the Mechatronics Department, Military University of Technology in the years 2007-2010. As the main object of the study involved the preparation of a concept and the implementation of an avionics data acquisition system intended for research during flight of unmanned aerial vehicles of the mini class, this article presents a design of an avionics system and describes equipment solutions of a distributed measurement system intended for data acquisition consisting of intelligent transducers. The data collected during a flight controlled by an operator confirmed proper operation of the individual components of the data acquisition system.

  7. An Ada Linear-Algebra Software Package Modeled After HAL/S (United States)

    Klumpp, Allan R.; Lawson, Charles L.


    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.

  8. Enabling Dedicated, Affordable Space Access Through Aggressive Technology Maturation (United States)

    Jones, Jonathan E.; Kibbey, Timothy P.; Cobb, C. Brent; Harris, Lawanna L.


    A launch vehicle at the scale and price point which allows developers to take reasonable risks with high payoff propulsion and avionics hardware solutions does not exist today. Establishing this service provides a ride through the proverbial technology "valley of death" that lies between demonstration in laboratory and flight environments. NASA's NanoLaunch effort will provide the framework to mature both earth-to-orbit and on-orbit propulsion and avionics technologies while also providing affordable, dedicated access to low earth orbit for cubesat class payloads.

  9. Autonomous Flight Rules Concept: User Implementation Costs and Strategies (United States)

    Cotton, William B.; Hilb, Robert


    The costs to implement Autonomous Flight Rules (AFR) were examined for estimates in acquisition, installation, training and operations. The user categories were airlines, fractional operators, general aviation and unmanned aircraft systems. Transition strategies to minimize costs while maximizing operational benefits were also analyzed. The primary cost category was found to be the avionics acquisition. Cost ranges for AFR equipment were given to reflect the uncertainty of the certification level for the equipment and the extent of existing compatible avionics in the aircraft to be modified.

  10. 78 FR 60186 - Airworthiness Directives; AgustaWestland S.p.A. (Agusta) Helicopters (United States)


    ... deactivating the Full Icing Protection System (FIPS) and installing a placard next to the FIPS controller... avionics bay and the baggage compartment resulting from an Auto Transformer Rectifier Unit internal circuit... between the national Government and the States, or on the distribution of power and responsibilities among...

  11. The Way Ahead For Maritime UAVS (United States)


    of possible contract winners including Scan Eagle, Silver Fox, Wasp, Coyote and the USMC Tier I winner Dragon Eye. Technical data for these UAVs are...Neptune’s engine and avionics are placed above the waterline and the airframe is sealed for flotation as well as providing corrosion/water intrusion

  12. 75 FR 7345 - Filtered Flight Data (United States)


    ... digital flight data recorder regulations affecting certain air carriers and operators. This final rule prohibits the filtering of some original flight recorder sensor signals unless a certificate holder can show... A. Verna, Avionics Systems Branch, Aircraft Certification Service, AIR-130, Federal Aviation...

  13. Conference P.Aimedieu

    CERN Multimedia



    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. Unity of Command and Interdiction (United States)


    CSR ) program. Col Bob Johnston brought tremendous energy and intellect to the Airpower Research Institute, much to the benefit of the CSR fellows. His...Targets," Aviation Week & Space Technology, 11 February 1991, 17. " John D. Morocco , "U.S. Tactics Exploit Advances In Avionics, Air-to-Surface

  15. NAVAIR Progress in Assessing, Validating and Implementing Non-Chromate Primers (Briefing charts) (United States)


    logistics for any new coating or coating system NAVAIR Application Areas for Hexavalent Chromium Alternatives: Status Components/ Structure... Hexavalent chromium alternatives Sacrificial Coating Post Treatment MIL-A-8625 Anodize Avionics/ Electronics Magnesium/Titanium Conversion Aluminum Anodizing...Aluminum Pretreatment Type IC Seal Type IIB Seal Type II Seal Phosphating Rinse (Aluminum)Rinse (Steel) Cadmium Zinc-Nickel Aluminum Bonding Chrome

  16. Hexavalent Chrome Free Coatings for Electronics Applications: Joint Test Report (United States)

    Rothgeb, Matt; Kessel, Kurt


    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.

  17. Hex Chrome Free Coatings for Electronics Overview (United States)

    Kessel, Kurt


    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.

  18. 26 CFR 52.4682-3 - Imported taxable products. (United States)


    ... Electronic integrated circuits and microassemblies 8542 CFC-113 0.0002 Signal generators 8543.20 CFC-113 0.6518 Avionics 8543.90.40 CFC-113 0.915 Signal generators subassemblies 8543.90.80 CFC-113 0.1265...:CORP:T:R (Imported Products Table), room 5228, Washington, DC 20044. (4) Public inspection and copying...

  19. Regulatory Compliance in Multi-Tier Supplier Networks (United States)

    Goossen, Emray R.; Buster, Duke A.


    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. 77 FR 53159 - Passenger Use of Portable Electronic Devices on Board Aircraft (United States)


    ... systems. In today's avionics, there are various systems--global positioning, traffic collision and... name of the individual sending the comment (or signing the comment for an association, business, labor... technology are still in service and are as susceptible today to interference as they were when they first...

  1. 78 FR 30243 - Airworthiness Directives; Eclipse Aerospace, Inc. Airplanes (United States)


    ... Engineer, FAA, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines... with ETT, or Avio NG 1.0 avionics suites that could result in uncommanded fire suppression system... uncommanded fire suppression system activation and simultaneous shutdown of both engines. (f) Compliance...

  2. Validation of Flight Critical Control Systems (United States)


    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

  3. 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.

  4. Handbook of RF, Microwave, and Millimeter-Wave Components. Edited by Leonid A. Belov, Sergey M. Smolskiy and Victor N. Kochemasov, Artech House, 2012; 504 pages. Price: £119.00, ISBN 978-1-60807-209-5

    Directory of Open Access Journals (Sweden)

    Shu-Kun Lin


    Full Text Available This unique and comprehensive resource offers you a detailed treatment of the operations principles, key parameters, and specific characteristics of active and passive RF, microwave, and millimeter-wave components. The book covers both linear and nonlinear components that are used in a wide range of application areas, from communications and information sciences, to avionics, space, and military engineering.

  5. 78 FR 76731 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Rechargeable Lithium... (United States)


    ... series airplanes have fly-by-wire controls, fully software-configurable avionics, and fiber-optic... Regulations (14 CFR) 25.1353, the FAA provided an airworthiness standard for lead acid batteries and nickel... maintenance characteristics that differ significantly from those of the nickel cadmium and lead acid...

  6. Co Modeling and Co Synthesis of Safety Critical Multi threaded Embedded Software for Multi Core Embedded Platforms (United States)


    Kaiserslautern Kaiserslautern, Germany Sandeep Shukla FERMAT Lab Electrical and Computer Engineering Department Virginia Tech 900 North Glebe Road...Software Engineering , Software Producibility, Component-based software design, behavioral types, behavioral type inference, Polychronous model of...near future, many embedded applications including safety critical ones as used in avionics, automotive , mission control systems will run on

  7. Centre de recherches pour le développement international ...

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

    Julie Pépin

    employé est un voyageur occasionnel (selon la définition donnée à la section 4); ou ... droit à une avance de déplacement ni à un remboursement des frais ..... incluses dans le coût des billets d'avion à divulguer au public. 14.

  8. Hangar con alas, Los Angeles

    Directory of Open Access Journals (Sweden)

    Editorial, Equipo


    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.

  9. Near East/South Asia Report (United States)


    Mirage 2000 can also take off on less than 1,200m at full load. It reaches a speed greater than Mach 2.2 and a service ceilling of over 18,000m. The...all necessary data in either head-down configuration on a wide screen radar or HUD using superposition on the windshield glass . Its avionics contains

  10. Evaluating real-time Java for mission-critical large-scale embedded systems (United States)

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


    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.

  11. 75 FR 52246 - Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes (United States)


    ... required by paragraphs (g)(1) and (g)(2) of this AD, as applicable. A review of airplane maintenance..., notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate... 2006. Table of Contents 1-TOC 9 November 2006. Section 1--Introduction 1--7 9 November 2006. Section 2...

  12. Wind Shear Systems Implementation Plan, Benefit/Cost Study. (United States)


    not. Accordingly, the three self contained Wind Shear Systems currently being marketed by avionics manufacturers are considered to have lower relative... RESEARC { AND I’iVEIOPMEN1 The FAA research ni d development ffort has taken a threefold appro,,ch to the vind sh#ear problem. Ore. approach was to

  13. Space Propulsion Hazards Analysis Manual (SPHAM). Volume 2. Appendices (United States)


    Vanderwall, E.M. and Schaplowsky, R.F., USAF PROPELLANT HA& nBOOKS , Volume III, Part B, "Nitrogen Trifluoride, Bibliography," p. 4-508, Aerojeft Liquid...not economically desirable to maintain two different avionic configurations in the space-based program. Guidance and navigation information is

  14. NanoLaunch (United States)

    Jones, Jonathan; Harris, Lawanna


    NASA's NanoLaunch effort will provide the framework to mature both Earth-to-orbit and on-orbit propulsion and avionics technologies while also providing affordable, dedicated access to low-Earth orbit for CubeSat-class payloads. The project will also serve as an early career personnel training opportunity with mentors to gain hands-on project experience.

  15. Detection of intermittent resistive faults in electronic systems based on the mixed-signal boundary-scan standard

    NARCIS (Netherlands)

    Kerkhoff, Hans G.; Ebrahimi, Hassan


    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

  16. 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

  17. Intermittent resistive faults in digital cmos circuits

    NARCIS (Netherlands)

    Kerkhoff, Hans G.; Ebrahimi, Hassan


    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

  18. The BLSTs Role in the Materiel Enterprise (United States)


    CECOM AVN LAR AMCOM LAR PM UAS CECOM AVN LAR AMCOM LAR PM UAS CECOM AVN LAR PM UAS Ba gr am Sh an k M ar m al Ja la la ba d Legend Coordinating...relationship Administrative control AED = Aviation Engineering Directorate AMCOM = Aviation and Missile Command AVN = Avionics BLST = Brigade logistics

  19. The e-Beam Sustained Laser Technology for Space-based Doppler Wind Lidar (United States)

    Brown, M. J.; Holman, W.; Robinson, R. J.; Schwarzenberger, P. M.; Smith, I. M.; Wallace, S.; Harris, M. R.; Willetts, D. V.; Kurzius, S. C.


    An overview is presented of GEC Avionics activities relating to the Spaceborne Doppler Wind Lidar. In particular, the results of design studies into the use of an e-beam sustained CO2 laser for spaceborne applications, and experimental work on a test bed system are discussed.

  20. Harmonics Study of Common Low Wattage LED Lamps

    Directory of Open Access Journals (Sweden)

    Ioan Dragoş Deaconu


    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.

  1. 78 FR 65233 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes... (United States)


    ... provide different levels of protection from post-crash fire threats than similar aircraft constructed from... turbofan engines. Flight controls are fly-by-wire systems with two passive/uncoupled side sticks. Avionics... models of airplanes. Maximum operating altitude is 41,000 feet for both models of airplanes. The fuselage...

  2. 77 FR 37881 - 36(b)(1) Arms Sales Notification (United States)


    ...) Sensitivity of Technology: 1. The AN/ALE-47 Counter-Measures Dispensing System (CMDS) is an integrated, threat... internally mounted and may be operated as a stand-alone system or may be integrated with other on-board EW and avionics systems. The AN/ALE-47 uses threat data received over the aircraft interfaces to assess...

  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.


    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 (United States)

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


    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. SATWG networked quality function deployment (United States)

    Brown, Don


    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. 78 FR 65153 - Special Conditions: Learjet Model 45 Series Airplanes; Aircraft Electronic System Security... (United States)


    ... design feature associated with the architecture and connectivity capabilities of the airplanes' computer... the comment (or signing the comment for an association, business, labor union, etc.). DOT's complete... passengers and two crew members. The proposed Learjet Model 45 avionics architecture is new and novel for...

  7. United States Air Force High School Apprenticeship Program. 1990 Program Management Report. Volume 2 (United States)


    49-3 documentation application. The demonstration was created with Apple Computer’s HyperCard using a flowchart -like format with which the user could...Software, Inc.,1989. F-1_6 A/B Avionic System Manual. Fort Worth, TX: General Dynamics, 1990.I 5HyperCard Beginners Guide: An Introduction to

  8. The Design of Model-Based Training Programs (United States)

    Polson, Peter; Sherry, Lance; Feary, Michael; Palmer, Everett; Alkin, Marty; McCrobie, Dan; Kelley, Jerry; Rosekind, Mark (Technical Monitor)


    This paper proposes a model-based training program for the skills necessary to operate advance avionics systems that incorporate advanced autopilots and fight management systems. The training model is based on a formalism, the operational procedure model, that represents the mission model, the rules, and the functions of a modem avionics system. This formalism has been defined such that it can be understood and shared by pilots, the avionics software, and design engineers. Each element of the software is defined in terms of its intent (What?), the rationale (Why?), and the resulting behavior (How?). The Advanced Computer Tutoring project at Carnegie Mellon University has developed a type of model-based, computer aided instructional technology called cognitive tutors. They summarize numerous studies showing that training times to a specified level of competence can be achieved in one third the time of conventional class room instruction. We are developing a similar model-based training program for the skills necessary to operation the avionics. The model underlying the instructional program and that simulates the effects of pilots entries and the behavior of the avionics is based on the operational procedure model. Pilots are given a series of vertical flightpath management problems. Entries that result in violations, such as failure to make a crossing restriction or violating the speed limits, result in error messages with instruction. At any time, the flightcrew can request suggestions on the appropriate set of actions. A similar and successful training program for basic skills for the FMS on the Boeing 737-300 was developed and evaluated. The results strongly support the claim that the training methodology can be adapted to the cockpit.

  9. Primary display latency criteria based on flying qualities and performance data (United States)

    Funk, John D., Jr.; Beck, Corin P.; Johns, John B.


    With a pilots' increasing use of visual cue augmentation, much requiring extensive pre-processing, there is a need to establish criteria for new avionics/display design. The timeliness and synchronization of the augmented cues is vital to ensure the performance quality required for precision mission task elements (MTEs) where augmented cues are the primary source of information to the pilot. Processing delays incurred while transforming sensor-supplied flight information into visual cues are unavoidable. Relationships between maximum control system delays and associated flying qualities levels are documented in MIL-F-83300 and MIL-F-8785. While cues representing aircraft status may be just as vital to the pilot as prompt control response for operations in instrument meteorological conditions, presently, there are no specification requirements on avionics system latency. To produce data relating avionics system latency to degradations in flying qualities, the Navy conducted two simulation investigations. During the investigations, flying qualities and performance data were recorded as simulated avionics system latency was varied. Correlated results of the investigation indicates that there is a detrimental impact of latency on flying qualities. Analysis of these results and consideration of key factors influencing their application indicate that: (1) Task performance degrades and pilot workload increases as latency is increased. Inconsistency in task performance increases as latency increases. (2) Latency reduces the probability of achieving Level 1 handling qualities with avionics system latency as low as 70 ms. (3) The data suggest that the achievement of desired performance will be ensured only at display latency values below 120 ms. (4) These data also suggest that avoidance of inadequate performance will be ensured only at display latency values below 150 ms.

  10. Estrategias avanzadas de control, modelado, diseño e implementación de controladores de potencia de estado sólido (SSPC) para su aplicación en sistemas de distribución de potencia eléctrica embarcados


    Izquierdo Gil, Daniel


    Actualmente, existe una fuerte tendencia en los nuevos diseños de aviones militares y civiles hacia el concepto de avión más eléctrico ó totalmente eléctrico. Esto es debido principalmente a la substitución de los sistemas mecánicos, neumáticos e hidráulicos por sistemas parcial o totalmente eléctricos. El concepto de avión más eléctrico presenta una serie de ventajas o mejoras frente a los aviones convencionales, desde el punto de vista de eficiencia, peso, volumen, impacto ambiental, etc. E...

  11. HIL Tuning of UAV for Exploration of Risky Environments

    Directory of Open Access Journals (Sweden)

    C. D. Melita


    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.

  12. Kedalion: NASA's Adaptable and Agile Hardware/Software Integration and Test Lab (United States)

    Mangieri, Mark L.; Vice, Jason


    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.

  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. Comparación de los modelos de negocio de las tres aerolíneas estatales chinas Air China, China Southern Airlines y China Eastern Airlines


    ZHOU, MI


    De acuerdo a las predicciones de Airbus publicadas en Diciembre de 2014, una de las compañías líderes en fabricación de aviones, China va a necesitar más de 5.300 aviones de pasajeros y de carga nuevos entre 2014 y 2033. Esto supone el 17% de la demanda mundial que está estimada en 31.000 unidades en los próximos 20 años. Según esta estimación de Airbus, China se convertirá en el país líder en cuanto a tráfico aéreo de pasajeros tanto para el mercado doméstico como el internacional. El núm...

  15. Towards Prognostics for Electronics Components (United States)

    Saha, Bhaskar; Celaya, Jose R.; Wysocki, Philip F.; Goebel, Kai F.


    Electronics components have an increasingly critical role in avionics systems and in the development of future aircraft systems. Prognostics of such components is becoming a very important research field as a result of the need to provide aircraft systems with system level health management information. This paper focuses on a prognostics application for electronics components within avionics systems, and in particular its application to an Isolated Gate Bipolar Transistor (IGBT). This application utilizes the remaining useful life prediction, accomplished by employing the particle filter framework, leveraging data from accelerated aging tests on IGBTs. These tests induced thermal-electrical overstresses by applying thermal cycling to the IGBT devices. In-situ state monitoring, including measurements of steady-state voltages and currents, electrical transients, and thermal transients are recorded and used as potential precursors of failure.

  16. Investigation of Integrated Vehicle Health Management Approaches (United States)

    Paris, Deidre


    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.

  17. The Use of Modeling for Flight Software Engineering on SMAP (United States)

    Murray, Alexander; Jones, Chris G.; Reder, Leonard; Cheng, Shang-Wen


    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

  18. Computing Systems Configuration for Highly Integrated Guidance and Control Systems (United States)


    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

  19. Test case preparation using a prototype


    Treharne, Helen; Draper, J.; Schneider, Steve A.


    This paper reports on the preparation of test cases using a prototype within the context of a formal development. It describes an approach to building a prototype using an example. It discusses how a prototype contributes to the testing activity as part of a lifecycle based on the use of formal methods. The results of applying the approach to an embedded avionics case study are also presented.



    The “off-equipment” AFSs have been reduced as well. Gone are the backshops of Electrical/Environmental, Hydraulics , Avionics, and Armament. The 5th...area (A2/AD) denial battlefronts. While this is a great concept, more must be done to reduce the logistics footprint, improve logistics agility and... reduce costs of logistics operations. Logisticians must always find a way to enable the operations that our Services require. Thesis From the

  1. Benefits of Computer Assisted Translation to Information Managers and End-Users (L’Interet de la Traduction Assistee par Ordinateur Pour les Responsables de Centres d’Information et Pour Les Utilisateurs Finaux) (United States)


    licensing agreement) mnay not be the key factor. Most users have found that integration and further development costs - particularly on dictionaries - are...soient con~us dans une optique monoLingue . possible d usavoir faire d’experts qui ici Cheque nation est en charge de I’anatyse de pourraient bien-etre...LIElectronic Dictionary Research meteo, horaires des trains ou avions, Institute (1,5 miLLiirds de francs, avec stations d’autobus, synthttiseurs~de huit

  2. Waypoint Generation Based on Sensor Aimpoint (United States)


    United States Government . AFIT/GAE/ENV/09-M01 WAYPOINT GENERATION BASED ON SENSOR AIMPOINT THESIS Presented to the Faculty Department of Aeronautical...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

  3. Nodes and Codes: The Reality of Cyber Warfare (United States)


    respectively. The avionics in Boeing’s 787 Dreamliner require approximately 6.5 million lines of code while the current S-Class Mercedes Benz requires over 20...leaders (demonstrated through outdated policy, theory, and doctrine) and the reality of warfare in 1914 (dictated by innovation, technology , and...or the guidelines to military action codified in doctrine? How are states using the latest technological innovations as violent instruments of

  4. Polymer film strain gauges for measuring large elongations (United States)

    Kondratov, A. P.; Zueva, A. M.; Varakin, R. S.; Taranec, I. P.; Savenkova, I. A.


    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. 5-Year Update Environmental Assessment for CV-22 Beddown (United States)


    supersonic flight. Activities do not include intentional fuel dumping below 6,000 feet. No new facilities or utilities will be necessary to support IOT&E...the ground, climb a ladder from the ground in to the aircraft, or ride the rescue hoist from the ground in to the aircraft. Once forces are secured...Crew Chief and specialists in the fields of Integrated Avionics, Propulsion, Hydraulics , and Electro- Environmental maintenance. The majority of the

  6. Industrial communication technology handbook

    CERN Document Server

    Zurawski, Richard


    Featuring contributions from major technology vendors, industry consortia, and government and private research establishments, the Industrial Communication Technology Handbook, Second Edition provides comprehensive and authoritative coverage of wire- and wireless-based specialized communication networks used in plant and factory automation, automotive applications, avionics, building automation, energy and power systems, train applications, and more.New to the Second Edition:46 brand-new chapters and 21 substantially revised chaptersInclusion of the latest, most significant developments in spe

  7. Evaluation of Game-Based Visualization Tools for Military Flight Simulation (United States)


    accepted that game-based flight simulators cannot approach the complexity and realism of the high fidelity avionics simulations employed in...modern Air Force training systems. However, low cost Commercial Off the Shelf (COTS) gaming technology is rapidly approaching many of the...pitch, and yaw) then converts this position to WGS84 geocentric coordinates to conform to DIS standards prior to broadcast. The position data of

  8. Electronic Transfer of Information and Its Impact on Aerospace and Defence Research and Development Held in the Technical Information Panel Specialists’ Meeting, Brussels, Belgium on 17-19 October 1989 (United States)


    with 33,0(100 emiployees, at turnover of 28 billion French Francs, atid involvcd in the production of Concorde, Airbus and Ariane. A number of...nco or orntia~blo magnoto-opticai disco has boen announced by market obsevrvers as an areai of conaiderable growth over tho -4oxt five yearti. Among...frangaise. Ses produits et sos Etudes sont parfaitement connus. On pout citer pour e~n~oire Concorde, Airbus pour les avions, Gazelle, Dauphin pour

  9. JPRS Report, Near East and South Asia. (United States)


    favour. The highlight of the "electoral reforms" resolution was not any meaningful step to curb malpractices or reduce the role of money in elections...facility, avionics repair, electronics manufactur- ing, and medical products. The British do not have to concentrate on such high technology ventures...circumventing the land ceiling law in Uttar Pra- desh to save his farm. The prime minister, Mr Rajiv Gandhi, himself took the opportunity of a talk with

  10. Rapports 2016-2017 sur les frais de voyage pour Sophie d'Amours ...

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

    chantal taylor

    But: Réunion du Conseil des gouverneurs. Date(s). 2016-11-21 à 2016-11-23. Destination(s). Ottawa. Billet d'avion. 350.81 $. Frais de transport au sol ou autrement. 61.61 $. Frais de logement. 590.10 $. Repas et frais divers. 172.79 $. Autre frais. 0.00 $. Total. 1 175.31 $. Commentaires. Rapports 2016-2017 sur les frais ...

  11. Rapports 2016-2017 sur les frais de voyage pour Sophie d'Amours ...

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

    Beata Bialic

    Date(s). 2016-07-06. Destination(s). Ottawa. Billet d'avion. 866.40 $. Frais de transport au sol ou autrement. 83.50 $. Frais de logement. 0.00 $. Repas et frais divers. 84.53 $. Autre frais. 0.00 $. Total. 1 034.43 $. Commentaires. Rapports 2016-2017 sur les frais de voyage pour Sophie d'Amours, gouverneur.

  12. A Communication Architecture for an Advanced Extravehicular Mobile Unit (United States)

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


    This document describes the communication architecture for the Power, Avionics and Software (PAS) 1.0 subsystem for the Advanced Extravehicular Mobility Unit (AEMU). The following systems are described in detail: Caution Warning 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 subsystem being developed at Glenn Research Center (GRC).

  13. Cost, Capability, and the Hunt for a Lightweight Ground Attack Aircraft (United States)


    or Foe IFR Instrument Flight Rules ISR Intelligence Surveillance and Reconnaissance JP Joint Publication JTAC Joint Terminal Attack...capable, combat range, loiter time, weapons payloads, ejection seats, NVG compatible cockpits, IFR avionics, etc.8 One of the primary enablers for threats. In cases where radar guided air defense systems are present, the lack of an RWR puts the aircraft at a definite disadvantage and is

  14. IVHM Framework for Intelligent Integration for Vehicle Health Management (United States)

    Paris, Deidre; Trevino, Luis C.; Watson, Michael D.


    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

  15. Case Study of Using High Performance Commercial Processors in Space (United States)

    Ferguson, Roscoe C.; Olivas, Zulema


    The purpose of the Space Shuttle Cockpit Avionics Upgrade project (1999 2004) was to reduce crew workload and improve situational awareness. The upgrade was to augment the Shuttle avionics system with new hardware and software. A major success of this project was the validation of the hardware architecture and software design. This was significant because the project incorporated new technology and approaches for the development of human rated space software. An early version of this system was tested at the Johnson Space Center for one month by teams of astronauts. The results were positive, but NASA eventually cancelled the project towards the end of the development cycle. The goal to reduce crew workload and improve situational awareness resulted in the need for high performance Central Processing Units (CPUs). The choice of CPU selected was the PowerPC family, which is a reduced instruction set computer (RISC) known for its high performance. However, the requirement for radiation tolerance resulted in the re-evaluation of the selected family member of the PowerPC line. Radiation testing revealed that the original selected processor (PowerPC 7400) was too soft to meet mission objectives and an effort was established to perform trade studies and performance testing to determine a feasible candidate. At that time, the PowerPC RAD750s were radiation tolerant, but did not meet the required performance needs of the project. Thus, the final solution was to select the PowerPC 7455. This processor did not have a radiation tolerant version, but had some ability to detect failures. However, its cache tags did not provide parity and thus the project incorporated a software strategy to detect radiation failures. The strategy was to incorporate dual paths for software generating commands to the legacy Space Shuttle avionics to prevent failures due to the softness of the upgraded avionics.

  16. Case Study of Using High Performance Commercial Processors in a Space Environment (United States)

    Ferguson, Roscoe C.; Olivas, Zulema


    The purpose of the Space Shuttle Cockpit Avionics Upgrade project was to reduce crew workload and improve situational awareness. The upgrade was to augment the Shuttle avionics system with new hardware and software. A major success of this project was the validation of the hardware architecture and software design. This was significant because the project incorporated new technology and approaches for the development of human rated space software. An early version of this system was tested at the Johnson Space Center for one month by teams of astronauts. The results were positive, but NASA eventually cancelled the project towards the end of the development cycle. The goal to reduce crew workload and improve situational awareness resulted in the need for high performance Central Processing Units (CPUs). The choice of CPU selected was the PowerPC family, which is a reduced instruction set computer (RISC) known for its high performance. However, the requirement for radiation tolerance resulted in the reevaluation of the selected family member of the PowerPC line. Radiation testing revealed that the original selected processor (PowerPC 7400) was too soft to meet mission objectives and an effort was established to perform trade studies and performance testing to determine a feasible candidate. At that time, the PowerPC RAD750s where radiation tolerant, but did not meet the required performance needs of the project. Thus, the final solution was to select the PowerPC 7455. This processor did not have a radiation tolerant version, but faired better than the 7400 in the ability to detect failures. However, its cache tags did not provide parity and thus the project incorporated a software strategy to detect radiation failures. The strategy was to incorporate dual paths for software generating commands to the legacy Space Shuttle avionics to prevent failures due to the softness of the upgraded avionics.

  17. A Comparison of Ada 83 and C++ (United States)


    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

  18. Le sans fil, un outil de gestion des ressources au Mozambique ...

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

    3 févr. 2011 ... ... nouvelle réserve naturelle de la province septentrionale de Niassa. Heureusement, son téléphone sans fil à haute fréquence lui a permis d'appeler sa station de base à l'aide. Malgré la distance, ses collègues ont pu lui porter secours en demandant à une pourvoirie d'envoyer un petit avion le cueillir.

  19. The DTIC Review. Volume 1, Number 1: Nuclear Proliferation and Deterrence in a Changing Political World (United States)


    Mathematical Expectation" by David Schmeidler and Peter Wakker, "Expected Utility Hypothesis" by Mark Machina, "Rational Behavior" by Amartya Sen ...other regional adversaries are not secure and, hence, are highly sen - sitive to this form of pressure. The question is whether such threats can be used...Warsaw Pact." Moreover, conventional military capabilities are constantly changing through advances in armor, avionics, sen - sors, munitions. etc

  20. 2015-2016 Rapports sur les frais de voyage et d'accueil pour Scott ...

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

    Ruxandra Staicu

    Réunion du Conseil des gouverneurs. Date(s):. 2015-07-13 à 2015-07-14. Destination(s):. Ottawa. Billet d'avion: Frais de transport au sol ou autrement: 31.46 $. Frais de logement: Repas et frais divers: Autre frais: Total: 31.46 $. Commentaires: 2015-2016 Rapports sur les frais de voyage et d'accueil pour Scott Gilmore, ...

  1. MAS Bulletin. Papers Presented at Advisory Group for Aerospace Research and Development (AGARD) Symposium on Machine Intelligence for Aerospace Electronic Systems. (United States)


    neural networks, and machine learning . This list ie not all 9. Future ESM Systems and the Potential for Neural Processing inclusive. This research could...U.S. CAPT James M. Skinner , USAF, Air Force Space Technology 17. Development of Tactical Doecisiont Akid. Center, and Prof. Georg* F. Luger...ntegrat11111ng Macine I~1e900enc Into the Co~pi to Aid t" Pilot 26. Integrated Communications, Navigatlion. Ideintiflocation Avionics Dr. Edward J

  2. 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.

  3. 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.

  4. 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.

  5. Simple Electromagnetic Modeling of Small Airplanes: Neural Network Approach


    Koudelka, V.; Raida, Zbyněk; Tobola, P.


    The paper deals with the development of simple electromagnetic models of small airplanes, which can contain composite materials in their construction. Electromagnetic waves can penetrate through the surface of the aircraft due to the specific electromagnetic properties of the composite materials, which can increase the intensity of fields inside the airplane and can negatively influence the functionality of the sensitive avionics. The airplane is simulated by two parallel dielectric layers (t...

  6. DFRC F-16 aircraft fleet and support crew (United States)


    The support crew for the F-16A, the F-16XL no. 1, and the F-16 AFTI are, top row, left to right: Randy Weaver; mechanic, Susan Ligon; mechanic, Bob Garcia; Crew Chief, Rich Kelly; mechanic, Dale Edminister; Avionics Technician. Bottom row, left to right, Art Cope; mechanic, John Huffman; Avionics Technician, Jaime Garcia; Avionics Technician, Don Griffith, Avionics Tech. Co-op student. The F-16A (NASA 516), the only civil registered F-16 in existence, was transferred to Dryden from Langley, and is primarily used in engine tests and for parts. Although it is flight-worthy, it is not currently flown at Dryden. The single-seat F-16XL no. 1 (NASA 849) was most recently used in the Cranked-Arrow Wing Aerodynamics Project (CAWAP) to test boundary layer pressures and distribution. Previously it had been used in a program to investigate the characteristics of sonic booms for NASA's High Speed Research Program. Data from the program will be used in the development of a high speed civilian transport. During the series of sonic boom research flights, the F-16XL was used to probe the shock waves being generated by a NASA SR-71 and record their shape and intensity. The Advanced Fighter Technology Integration (AFTI) F-16 was used to develop and demonstrate technologies to improve navigation and a pilot's ability to find and destroy enemy ground targets day or night, including adverse weather. Earlier research in the joint NASA-Air Force AFTI F-16 program demonstrated voice actuated controls, helmet-mounted sighting and integration of forward-mounted canards with the standard flight control system to achieve uncoupled flight.

  7. An Analysis of the RCA Price-S Cost Estimation Model as it Relates to Current Air Force Computer Software Acquisition and Management. (United States)


    because of the use of complex computational algorithms (Ref 25). Another important factor effecting the cost of soft- ware is the size of the development...involved the alignment and navigational algorithm portions of the software. The second avionics system application was the development of an inertial...001 1 COAT CONL CREA CINT CMAT CSTR COPR CAPP New Code .001 .001 .001 .001 1001 ,OO .00 Device TDAT T03NL TREA TINT Types o * Quantity OGAT OONL OREA

  8. The Ares Launch Vehicles: Critical for America's Continued Leadership in Space (United States)

    Cook, Stephen A.


    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.

  9. Complications du traitement traditionnel des fractures : aspects ...

    African Journals Online (AJOL)

    Tous les patients reçus avec des complications du traitement traditionnel des fractures ont été inclus dans ce travail. Le diagnostic des lésions était clinique et radiologique. Nous avions reçu 51 patients porteurs de complications suite à des traitements de médecine traditionnelle, soit 13,7% du total des patients hospitalisés ...

  10. Creating the Future: Research and Technology (United States)


    With the many different technical talents, Marshall Space Flight Center (MSFC) continues to be an important force behind many scientific breakthroughs. The MSFC's annual report reviews the technology developments, research in space and microgravity sciences, studies in space system concepts, and technology transfer. The technology development programs include development in: (1) space propulsion and fluid management, (2) structures and dynamics, (3) materials and processes and (4) avionics and optics.

  11. United States Air Force Summer Faculty Research Program 1989. Program Technical Report. Volume 3 (United States)


    351-2807 R. H. Cofer Degree: PhD Professor Specialty: Electrical Eng. Florida Institute Assigned: Avionics Laboratory 150 W. University Blvd. Melbourne ...West University Blvd. Melbourne , FL 32901 407\\768-8000 Ernest Hallford Degree: PhD Assistant Prof. Specialty: Psychology Moorhead State Univ. Assigned...3. Henisch, Heinz K., Semiconductor Contacts: An Approach to Ideas and Models, Oxford, England, Clarendon Press, 1984. 118-15 1989 USAF-UES SUMMER

  12. Design Methodologies for Secure Embedded Systems

    CERN Document Server

    Biedermann, Alexander


    Embedded systems have been almost invisibly pervading our daily lives for several decades. They facilitate smooth operations in avionics, automotive electronics, or telecommunication. New problems arise by the increasing employment, interconnection, and communication of embedded systems in heterogeneous environments: How secure are these embedded systems against attacks or breakdowns? Therefore, how can embedded systems be designed to be more secure? And how can embedded systems autonomically react to threats? Facing these questions, Sorin A. Huss is significantly involved in the exploration o

  13. Evaluation of System Architectures for the Army Aviation Ground Power Unit (United States)


    air cycle machine fed by APU compressor bleed air to provide avionics cooling, so the AGPU was required to provide pneumatic power simultaneous with...broad categories of compressors : positive displacement and aerodynamic. Of the positive displacement compressors , reciprocating, rotary screw , and... compressor the single stage piston and the rot:aiy screw compressors are best suited. The rotmy screw machines m·e close tolerance complicated machines

  14. Special Course on Subsonic/Transonic Aerodynamic Interference for Aircraft (United States)


    memory requirements. Small disturbance methods are inadequate, and they offer no reduction in computer costs. 4-5 3.2 BOUNDARY LAYER METHODS Widely...20th Ludwig Prandtl Memorial Lecture 1141 in 1977. A study of the flow in a right angled streanraise corner with fully turbulent boundary layers...manoctivrant, ofi line orientation variable die jet propulsif perinet die faire participer le nioteur A la sustentation die I’avion (et gaknient 5 qon

  15. Coverage Metrics for Model Checking (United States)

    Penix, John; Visser, Willem; Norvig, Peter (Technical Monitor)


    When using model checking to verify programs in practice, it is not usually possible to achieve complete coverage of the system. In this position paper we describe ongoing research within the Automated Software Engineering group at NASA Ames on the use of test coverage metrics to measure partial coverage and provide heuristic guidance for program model checking. We are specifically interested in applying and developing coverage metrics for concurrent programs that might be used to support certification of next generation avionics software.

  16. Automatic Generation of Safe Handlers for Multi-Task Systems


    Rutten , Éric; Marchand , Hervé


    We are interested in the programming of real-time control systems, such as in robotic, automotive or avionic systems. They are designed with multiple tasks, each with multiple modes. It is complex to design task handlers that control the switching of activities in order to insure safety properties of the global system. We propose a model of tasks in terms of transition systems, designed especially with the purpose of applying existing discrete controller synthesis techniques. This provides us...

  17. 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 ...

  18. VEST: An Aspect-Based Composition Tool for Real-Time Systems (United States)


    VEST: An Aspect-Based Composition Tool for Real - Time Systems * John A. Stankovic Ruiqing Zhu Ram Poornalingam Chenyang Lu Zhendong Yu Marty Humphrey...Composition Tool for Real - Time Systems 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. is obvious that designers of embedded real - time systems face many difficult problems. By working through various product scenarios with avionics

  19. Human Factors Aspects of Aircraft Accidents (United States)


    invaatiaaamanta traa important« : chainaa da grand entratian avion, revision daa motaura at banca d’aaaala, reviaion daa Equipements nEceaaitant daa...defectueux. Sur le plan des accidents d’apparells militaires, qui sort quelque peu de ma specia- lite, les renseignements disponibles dans la presse ...Undoubtedly, a compelling reason for staying with the aircraft was to try to regain pitch attitude control in view of a large audience of press and

  20. The development of eye tracking in aviation (ETA) technique to investigate pilot's cognitive processes of attention and decision-making


    Li, Wen-Chin; Lin, John J. H.; Braithwaite, Graham; Greaves, Matt


    Eye tracking device had provided researchers a promising way to investigate what pilot‘s cognitive processes when they see information present on the flight deck. There are 35 participants consisted by pilots and avionics engineers participated in current research. The research apparatus include an eye tracker and a flight simulator divided by five AOIs for data collection. The research aims are to develop cost-efficiency of eye tracking technique in order to facilitate scientific research of...

  1. Generic regional aircraft flying qualities for the approach and landing task


    Gautrey, Jim


    Many changes have occurred in the past 20 years in aircraft manufacture and development. New technologies have appeared, spanning the entire aircraft design environment, such as new production methods, new materials and new avionics systems. These new methods have been developed for two reasons. For military aircraft, they have arisen through the need to improve performance. However, for civil aircraft they have arisen through the need to reduce the overall cost. This report co...

  2. Air Force Research Laboratory Sensors Directorate Leadership Legacy, 1960-2011 (United States)


    Area, Tinker AFB, Okla- homa . The mission of this 200 engineer organization was providing engineering sup- port to the current operational fleet...advanced development of ESM, ELINT, IR warning receiver technology. 1980-1984 Avionics Directorate, Air Force Wright Laboratory, WPAFB, OH - Chief...Wright Laboratory, WPAFB, OH - Deputy Chief of Electronic Warfare Division. Major technology areas included RF/ IR /EO/ COM countermeasures, stealth

  3. Methode d’Identification des Forces Aerodynamiques Instationnaires sur les Essais en Vol, Validation Experimentale (Method of Mathematical Identification of Unsteady Airloads From Flight Measurements, Experimental Validation) (United States)


    gage en vol de rdponses de jauges de contraintes en responses in maneuver, illustrated by an example manoeuvre, illustrd par un exemple issu de la coming...sous ddrapage, ... , braquages gouvernes,..) la forme: -Les mesures sont directement les rkponses de - minimiser Z = Q(k - Xj tb) 2 jauges de...3, la rdponse - les facteurs de ponddration des mesures, fli ou incidence de l’avion, la rdponse de la jauge plus ou momns subjectifs, sont remplacds

  4. 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.


    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

  5. Automated Cooperative Trajectories for a More Efficient and Responsive Air Transportation System (United States)

    Hanson, Curt


    The NASA Automated Cooperative Trajectories project is developing a prototype avionics system that enables multi-vehicle cooperative control by integrating 1090 MHz ES ADS-B digital communications with onboard autopilot systems. This cooperative control capability will enable meta-aircraft operations for enhanced airspace utilization, as well as improved vehicle efficiency through wake surfing. This briefing describes the objectives and approach to a flight evaluation of this system planned for 2016.

  6. International Space Station (ISS) Expedite the Process of Experiments to Space Station (EXPRESS) Racks Software Support (United States)


    bd Systems personnel accomplished the technical responsibilities for this reporting period, as planned. A close working relationship was maintained with personnel of the MSFC Avionics Department Software Group (ED 14), the MSFC EXPRESS Project Office (FD3 l), and the Huntsville Boeing Company. Work accomplishments included the support of SRB activities, ATB activities, ESCP activities, participating in technical meetings, coordinating issues between the Boeing Company and the MSFC Project Office, and performing special tasks as requested.

  7. Spaceborne computer executive routine functional design specification. Volume 1: Functional design of a flight computer executive program for the reusable shuttle (United States)

    Curran, R. T.


    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.

  8. Buy, Build, or Steal: China’s Quest for Advanced Military Aviation Technologies (United States)


    from Britain (1975) SA–321 Super Frelon helicopter from France (1977) Coproduce Chengdu J–5A: Chinese MiG–17PF (1964) Spey fan-jet engine...affected by the Cultural Revolution as capable individuals with managerial and planning roles in key enterprises were branded bourgeoisie ...helicopter (1980) U.S. “Peace Pearl” transfer of advanced avionics for J–8 fighters (1984) Coproduce France gives China production rights for

  9. The Legacy of Space Shuttle Flight Software (United States)

    Hickey, Christopher J.; Loveall, James B.; Orr, James K.; Klausman, Andrew L.


    The initial goals of the Space Shuttle Program required that the avionics and software systems blaze new trails in advancing avionics system technology. Many of the requirements placed on avionics and software were accomplished for the first time on this program. Examples include comprehensive digital fly-by-wire technology, use of a digital databus for flight critical functions, fail operational/fail safe requirements, complex automated redundancy management, and the use of a high-order software language for flight software development. In order to meet the operational and safety goals of the program, the Space Shuttle software had to be extremely high quality, reliable, robust, reconfigurable and maintainable. To achieve this, the software development team evolved a software process focused on continuous process improvement and defect elimination that consistently produced highly predictable and top quality results, providing software managers the confidence needed to sign each Certificate of Flight Readiness (COFR). This process, which has been appraised at Capability Maturity Model (CMM)/Capability Maturity Model Integration (CMMI) Level 5, has resulted in one of the lowest software defect rates in the industry. This paper will present an overview of the evolution of the Primary Avionics Software System (PASS) project and processes over thirty years, an argument for strong statistical control of software processes with examples, an overview of the success story for identifying and driving out errors before flight, a case study of the few significant software issues and how they were either identified before flight or slipped through the process onto a flight vehicle, and identification of the valuable lessons learned over the life of the project.

  10. Fourier Transform Spectrometer Controller for Partitioned Architectures

    DEFF Research Database (Denmark)

    Tamas-Selicean, Domitian; Keymeulen, D.; Berisford, D.


    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....

  11. 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. (United States)


    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

  12. Planificateur de réunions (h/f) | CRDI - Centre de recherches pour le ...

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

    Fournir à des clients des estimations de coûts et des renseignements budgétaires pour les divers services associés aux activités planifiées, y compris : billets d'avion, frais d'hébergement et de séjour, installations de conférence, services audiovisuels et de traiteur, interprétation, transport routier et appui sur place.

  13. A MAG for the Twenty First Century: Lethal, Lighter, Energy Efficient, and Cheaper (United States)


    implementation of this concept. Since this concept does not create additional commands beyond the VMLA FRS , the plans already underway for 24 TACAIR...rules (VFR/ IFR ) operations. 2. Properly certified to meet acquisition requirements and allow for U.S. Military operation. Systems/capability must...protect .from small arms fire. Self-sealing fuel tanks required. 33. Infrared (IR) suppression for engine(s) 34. Avionics: IFR capable. Dual

  14. A Proposed Logistics Strategy for the Defense of Republic of Korea (United States)


    business such as the computer industrye electronics,, and avionics ;the informa- tion expaasioa and industrial automation. The ispact of any cae cf these...interrelated. it is vital to seek harmony amons the national and internaticnal ioUi- cies, strategic plans, and military programs . While it is naive...forvazding roles contributed to export efficiency in that one function can achieve an overviev of the export process. •he ttird task elesemt, dispatch order

  15. Randomness-Based Scale-Chromatic Image Analysis for Interactive Mapping on Satellite-Roadway-Vehicle Network

    Directory of Open Access Journals (Sweden)

    Kohji Kamejima


    Full Text Available A new framework is presented for integrating satellite/avionics sensors with onboard vision to support information intensive maneuvering. Real time bindings of the bird's eye observation and the driver's view via GPS provides \\textit{as-is} basis for perception and decision. Randomness-based roadway pattern model is implemented by fractal coding scheme associating bird's eye and frontal views. The feasibility of the framework with resquirements for vison system is discussed through concept modeling and experimental studies.

  16. Randomness-Based Scale-Chromatic Image Analysis for Interactive Mapping on Satellite-Roadway-Vehicle Network

    Directory of Open Access Journals (Sweden)

    Kohji Kamejima


    Full Text Available A new framework is presented for integrating satellite/avionics sensors with onboard vision to support information intensive maneuvering. Real time bindings of the bird's eye observation and the driver's view via GPS provides extit{as-is} basis for perception and decision. Randomness-based roadway pattern model is implemented by fractal coding scheme associating bird's eye and frontal views. The feasibility of the framework with resquirements for vison system is discussed through concept modeling and experimental studies.

  17. On TTEthernet for Integrated Fault-Tolerant Spacecraft Networks (United States)

    Loveless, Andrew


    There has recently been a push for adopting integrated modular avionics (IMA) principles in designing spacecraft architectures. This consolidation of multiple vehicle functions to shared computing platforms can significantly reduce spacecraft cost, weight, and de- sign complexity. Ethernet technology is attractive for inclusion in more integrated avionic systems due to its high speed, flexibility, and the availability of inexpensive commercial off-the-shelf (COTS) components. Furthermore, Ethernet can be augmented with a variety of quality of service (QoS) enhancements that enable its use for transmitting critical data. TTEthernet introduces a decentralized clock synchronization paradigm enabling the use of time-triggered Ethernet messaging appropriate for hard real-time applications. TTEthernet can also provide two forms of event-driven communication, therefore accommodating the full spectrum of traffic criticality levels required in IMA architectures. This paper explores the application of TTEthernet technology to future IMA spacecraft architectures as part of the Avionics and Software (A&S) project chartered by NASA's Advanced Exploration Systems (AES) program.

  18. Effects of cosmic radiation on devices and embedded systems in aircrafts

    Energy Technology Data Exchange (ETDEWEB)

    Prado, Adriane C.M.; Federico, Claudio A.; Pereira Junior, Evaldo C.F.; Goncalez, Odair L., E-mail:, E-mail:, E-mail:, E-mail: [Instituto de Estudos Avancados (IEAV/DCTA), Sao Jose dos Campos, SP (Brazil)


    Modern avionics systems use new electronic technologies devices that, due to their high degree of sophistication and miniaturization, are more susceptible to the effects of ionizing radiation, particularly the effect called 'Single Event Effect' (SEE) produced by neutron. Studies regarding the effects of radiation on electronic systems for space applications, such as satellites and orbital stations, have already been in progress for several years. However, tolerance requirements and specific studies, focusing on testing dedicated to avionics, have caused concern and gained importance in the last decade as a result of the accidents attributed to SEE in aircraft. Due to the development of a higher ceiling, an increase in airflow and a greater autonomy of certain aircrafts, the problem regarding the control of ionizing radiation dose received by the pilots, the crew and sensitive equipment became important in the areas of occupational health, radiation protection and flight safety. This paper presents an overview of the effects of ionizing radiation on devices and embedded systems in aircrafts, identifying and classifying these effects in relation to their potential risks in each device class. The assessment of these effects in avionics is a very important and emerging issue nowadays, which is being discussed by groups of the international scientific community; however, in South America, groups working in this area are still unknown. Consequently, this work is a great contribution and significantly valuable to the area of aeronautical engineering and flight safety associated to the effects of radiation on electronic components embedded in aircraft. (author)

  19. Methodologie experimentale pour evaluer les caracteristiques des plateformes graphiques avioniques (United States)

    Legault, Vincent

    Within a context where the aviation industry intensifies the development of new visually appealing features and where time-to-market must be as short as possible, rapid graphics processing benchmarking in a certified avionics environment becomes an important issue. With this work we intend to demonstrate that it is possible to deploy a high-performance graphics application on an avionics platform that uses certified graphical COTS components. Moreover, we would like to bring to the avionics community a methodology which will allow developers to identify the needed elements for graphics system optimisation and provide them tools that can measure the complexity of this type of application and measure the amount of resources to properly scale a graphics system according to their needs. As far as we know, no graphics performance profiling tool dedicated to critical embedded architectures has been proposed. We thus had the idea of implementing a specialized benchmarking tool that would be an appropriate and effective solution to this problem. Our solution resides in the extraction of the key graphics specifications from an inherited application to use them afterwards in a 3D image generation application.

  20. Health management and controls for Earth-to-orbit propulsion systems (United States)

    Bickford, R. L.


    Avionics and health management technologies increase the safety and reliability while decreasing the overall cost for Earth-to-orbit (ETO) propulsion systems. New ETO propulsion systems will depend on highly reliable fault tolerant flight avionics, advanced sensing systems and artificial intelligence aided software to ensure critical control, safety and maintenance requirements are met in a cost effective manner. Propulsion avionics consist of the engine controller, actuators, sensors, software and ground support elements. In addition to control and safety functions, these elements perform system monitoring for health management. Health management is enhanced by advanced sensing systems and algorithms which provide automated fault detection and enable adaptive control and/or maintenance approaches. Aerojet is developing advanced fault tolerant rocket engine controllers which provide very high levels of reliability. Smart sensors and software systems which significantly enhance fault coverage and enable automated operations are also under development. Smart sensing systems, such as flight capable plume spectrometers, have reached maturity in ground-based applications and are suitable for bridging to flight. Software to detect failed sensors has reached similar maturity. This paper will discuss fault detection and isolation for advanced rocket engine controllers as well as examples of advanced sensing systems and software which significantly improve component failure detection for engine system safety and health management.

  1. An Assessment of Technical and Production Risks of Candidate Low-Cost Attitude/Heading Reference Systems(AHRS) (United States)

    Yuchnovicz, Daniel; Burgess, Malcolm; Hammers, William


    This report provides an assessment of technical and production risks of candidate low-cost attitude/heading reference systems (AHRS) for use in the Advanced General Aviation Transport Experiments (AGATE) airplanes. A low-cost AHRS is a key component of modem "glass cockpit" flight displays for General Aviation (GA) aircraft. The technical capabilities of several candidate low-cost AHRS were examined and described along with the technical issues involved with using all solid-state components for attitude measurement. An economic model was developed which describes the expected profit, rate of return, and volume requirements for the manufacture of low-cost AHRS for GA aircraft in the 2000 to 2020 time frame. The model is the result of interviews with GA airframe manufacturers, avionics manufacturers and historical analysis of avionics of similar complexity. The model shows that a manufacturer will break even after three years of AHRS production, realizing an 18 percent rate of return (23 percent profit) on an investment of $3.5M over the 20 year period. A start-up production estimate showed costs of $6-12M for a new company to build and certify an AHRS from scratch, considered to be a high-risk proposition, versus $0.25-0.75M for an experienced avionics manufacturer to manufacture a design under license, a low-risk proposition.

  2. An autonomous rendezvous and docking system using cruise missile technologies (United States)

    Jones, Ruel Edwin


    In November 1990 the Autonomous Rendezvous & Docking (AR&D) system was first demonstrated for members of NASA's Strategic Avionics Technology Working Group. This simulation utilized prototype hardware from the Cruise Missile and Advanced Centaur Avionics systems. The object was to show that all the accuracy, reliability and operational requirements established for a space craft to dock with Space Station Freedom could be met by the proposed system. The rapid prototyping capabilities of the Advanced Avionics Systems Development Laboratory were used to evaluate the proposed system in a real time, hardware in the loop simulation of the rendezvous and docking reference mission. The simulation permits manual, supervised automatic and fully autonomous operations to be evaluated. It is also being upgraded to be able to test an Autonomous Approach and Landing (AA&L) system. The AA&L and AR&D systems are very similar. Both use inertial guidance and control systems supplemented by GPS. Both use an Image Processing System (IPS), for target recognition and tracking. The IPS includes a general purpose multiprocessor computer and a selected suite of sensors that will provide the required relative position and orientation data. Graphic displays can also be generated by the computer, providing the astronaut / operator with real-time guidance and navigation data with enhanced video or sensor imagery.

  3. Effects of cosmic radiation on devices and embedded systems in aircrafts

    International Nuclear Information System (INIS)

    Prado, Adriane C.M.; Federico, Claudio A.; Pereira Junior, Evaldo C.F.; Goncalez, Odair L.


    Modern avionics systems use new electronic technologies devices that, due to their high degree of sophistication and miniaturization, are more susceptible to the effects of ionizing radiation, particularly the effect called 'Single Event Effect' (SEE) produced by neutron. Studies regarding the effects of radiation on electronic systems for space applications, such as satellites and orbital stations, have already been in progress for several years. However, tolerance requirements and specific studies, focusing on testing dedicated to avionics, have caused concern and gained importance in the last decade as a result of the accidents attributed to SEE in aircraft. Due to the development of a higher ceiling, an increase in airflow and a greater autonomy of certain aircrafts, the problem regarding the control of ionizing radiation dose received by the pilots, the crew and sensitive equipment became important in the areas of occupational health, radiation protection and flight safety. This paper presents an overview of the effects of ionizing radiation on devices and embedded systems in aircrafts, identifying and classifying these effects in relation to their potential risks in each device class. The assessment of these effects in avionics is a very important and emerging issue nowadays, which is being discussed by groups of the international scientific community; however, in South America, groups working in this area are still unknown. Consequently, this work is a great contribution and significantly valuable to the area of aeronautical engineering and flight safety associated to the effects of radiation on electronic components embedded in aircraft. (author)

  4. Optimisation des trajectoires verticales par la methode de la recherche de l'harmonie = (United States)

    Ruby, Margaux

    Face au rechauffement climatique, les besoins de trouver des solutions pour reduire les emissions de CO2 sont urgentes. L'optimisation des trajectoires est un des moyens pour reduire la consommation de carburant lors d'un vol. Afin de determiner la trajectoire optimale de l'avion, differents algorithmes ont ete developpes. Le but de ces algorithmes est de reduire au maximum le cout total d'un vol d'un avion qui est directement lie a la consommation de carburant et au temps de vol. Un autre parametre, nomme l'indice de cout est considere dans la definition du cout de vol. La consommation de carburant est fournie via des donnees de performances pour chaque phase de vol. Dans le cas de ce memoire, les phases d'un vol complet, soit, une phase de montee, une phase de croisiere et une phase de descente, sont etudies. Des " marches de montee " etaient definies comme des montees de 2 000ft lors de la phase de croisiere sont egalement etudiees. L'algorithme developpe lors de ce memoire est un metaheuristique, nomme la recherche de l'harmonie, qui, concilie deux types de recherches : la recherche locale et la recherche basee sur une population. Cet algorithme se base sur l'observation des musiciens lors d'un concert, ou plus exactement sur la capacite de la musique a trouver sa meilleure harmonie, soit, en termes d'optimisation, le plus bas cout. Differentes donnees d'entrees comme le poids de l'avion, la destination, la vitesse de l'avion initiale et le nombre d'iterations doivent etre, entre autre, fournies a l'algorithme pour qu'il soit capable de determiner la solution optimale qui est definie comme : [Vitesse de montee, Altitude, Vitesse de croisiere, Vitesse de descente]. L'algorithme a ete developpe a l'aide du logiciel MATLAB et teste pour plusieurs destinations et plusieurs poids pour un seul type d'avion. Pour la validation, les resultats obtenus par cet algorithme ont ete compares dans un premier temps aux resultats obtenus suite a une recherche exhaustive qui a

  5. Space Shuttle RTOS Bayesian Network (United States)

    Morris, A. Terry; Beling, Peter A.


    With shrinking budgets and the requirements to increase reliability and operational life of the existing orbiter fleet, NASA has proposed various upgrades for the Space Shuttle that are consistent with national space policy. The cockpit avionics upgrade (CAU), a high priority item, has been selected as the next major upgrade. The primary functions of cockpit avionics include flight control, guidance and navigation, communication, and orbiter landing support. Secondary functions include the provision of operational services for non-avionics systems such as data handling for the payloads and caution and warning alerts to the crew. Recently, a process to selection the optimal commercial-off-the-shelf (COTS) real-time operating system (RTOS) for the CAU was conducted by United Space Alliance (USA) Corporation, which is a joint venture between Boeing and Lockheed Martin, the prime contractor for space shuttle operations. In order to independently assess the RTOS selection, NASA has used the Bayesian network-based scoring methodology described in this paper. Our two-stage methodology addresses the issue of RTOS acceptability by incorporating functional, performance and non-functional software measures related to reliability, interoperability, certifiability, efficiency, correctness, business, legal, product history, cost and life cycle. The first stage of the methodology involves obtaining scores for the various measures using a Bayesian network. The Bayesian network incorporates the causal relationships between the various and often competing measures of interest while also assisting the inherently complex decision analysis process with its ability to reason under uncertainty. The structure and selection of prior probabilities for the network is extracted from experts in the field of real-time operating systems. Scores for the various measures are computed using Bayesian probability. In the second stage, multi-criteria trade-off analyses are performed between the scores

  6. Single Event Effects Test Facility Options at the Oak Ridge National Laboratory

    Energy Technology Data Exchange (ETDEWEB)

    Riemer, Bernie [ORNL; Gallmeier, Franz X [ORNL; Dominik, Laura J [ORNL


    Increasing use of microelectronics of ever diminishing feature size in avionics systems has led to a growing Single Event Effects (SEE) susceptibility arising from the highly ionizing interactions of cosmic rays and solar particles. Single event effects caused by atmospheric radiation have been recognized in recent years as a design issue for avionics equipment and systems. To ensure a system meets all its safety and reliability requirements, SEE induced upsets and potential system failures need to be considered, including testing of the components and systems in a neutron beam. Testing of integrated circuits (ICs) and systems for use in radiation environments requires the utilization of highly advanced laboratory facilities that can run evaluations on microcircuits for the effects of radiation. This paper provides a background of the atmospheric radiation phenomenon and the resulting single event effects, including single event upset (SEU) and latch up conditions. A study investigating requirements for future single event effect irradiation test facilities and developing options at the Spallation Neutron Source (SNS) is summarized. The relatively new SNS with its 1.0 GeV proton beam, typical operation of 5000 h per year, expertise in spallation neutron sources, user program infrastructure, and decades of useful life ahead is well suited for hosting a world-class SEE test facility in North America. Emphasis was put on testing of large avionics systems while still providing tunable high flux irradiation conditions for component tests. Makers of ground-based systems would also be served well by these facilities. Three options are described; the most capable, flexible, and highest-test-capacity option is a new stand-alone target station using about one kW of proton beam power on a gas-cooled tungsten target, with dual test enclosures. Less expensive options are also described.

  7. Radioactive waste disposal via electric propulsion (United States)

    Burns, R. E.


    It is shown that space transportation is a feasible method of removal of radioactive wastes from the biosphere. The high decay heat of the isotopes powers a thermionic generator which provides electrical power for ion thrust engines. The massive shields (used to protect ground and flight personnel) are removed in orbit for subsequent reuse; the metallic fuel provides a shield for the avionics that guides the orbital stage to solar system escape. Performance calculations indicate that 4000 kg. of actinides may be removed per Shuttle flight. Subsidiary problems - such as cooling during ascent - are discussed.

  8. Software Engineering Improvement Activities/Plan (United States)


    bd Systems personnel accomplished the technical responsibilities for this reporting period, as planned. A close working relationship was maintained with personnel of the MSFC Avionics Department Software Group (ED14). Work accomplishments included development, evaluation, and enhancement of a software cost model, performing literature search and evaluation of software tools available for code analysis and requirements analysis, and participating in other relevant software engineering activities. Monthly reports were submitted. This support was provided to the Flight Software Group/ED 1 4 in accomplishing the software engineering improvement engineering activities of the Marshall Space Flight Center (MSFC) Software Engineering Improvement Plan.

  9. Turbine Engine Testing. (United States)


    English climate. (c) Functional Testing Functional testing is a ’catch all’ title for the multitude of tests required to examine and confirm or correct the...rage I I I , I ’s slot envs Atar ONK propulsent les Miraiges IV de la levce A~rientic Strat~giqiie l-vanlaisc, tanilis tilit leg mcters Atar 91K50 sent...moignent. Irtuwi Atar 9 ~K50 est tine version MANv~ du motenr Atar 9K proptilsant le hirdaceur vi1 *c ~Ik (lttur 11 et dest in 5 6qtiiper I ’avion polyvalent

  10. Flight Trajectory Planning for Fixed-Wing Aircraft in Loss of Thrust Emergencies


    Paul, Saswata; Hole, Frederick; Zytek, Alexandra; Varela, Carlos A.


    Loss of thrust emergencies-e.g., induced by bird/drone strikes or fuel exhaustion-create the need for dynamic data-driven flight trajectory planning to advise pilots or control UAVs. While total loss of thrust trajectories to nearby airports can be pre-computed for all initial points in a 3D flight plan, dynamic aspects such as partial power and airplane surface damage must be considered for accuracy. In this paper, we propose a new Dynamic Data-Driven Avionics Software (DDDAS) approach which...

  11. Handbook of RF, microwave, and millimeter-wave components

    CERN Document Server

    Smolskiy, Sergey M; Kochemasov, Victor N


    This unique and comprehensive resource offers you a detailed treatment of the operations principles, key parameters, and specific characteristics of active and passive RF, microwave, and millimeter-wave components. The book covers both linear and nonlinear components that are used in a wide range of application areas, from communications and information sciences, to avionics, space, and military engineering. This practical book presents descriptions and clear examples and of the best materials and products used in the field, including laminates, prepregs, substrates; microstrip, coaxial and wa

  12. Pilot vehicle interface on the advanced fighter technology integration F-16 (United States)

    Dana, W. H.; Smith, W. B.; Howard, J. D.


    This paper focuses on the work load aspects of the pilot vehicle interface in regard to the new technologies tested during AMAS Phase II. Subjects discussed in this paper include: a wide field-of-view head-up display; automated maneuvering attack system/sensor tracker system; master modes that configure flight controls and mission avionics; a modified helmet mounted sight; improved multifunction display capability; a voice interactive command system; ride qualities during automated weapon delivery; a color moving map; an advanced digital map display; and a g-induced loss-of-consciousness and spatial disorientation autorecovery system.

  13. Controle los mosquitos que están en el exterior (Controlling Mosquitoes Outside)

    Centers for Disease Control (CDC) Podcasts

    Los mosquitos pueden transmitir virus como el del zika. En este podcast, el Sr. Francisco le enseñará a usted y a su vecina Adriana diferentes maneras para ayudar a reducir la cantidad de mosquitos fuera de su casa. Los consejos incluyen eliminar áreas de agua estancada donde los mosquitos ponen sus huevos, usar larvicidas para matar mosquitos jóvenes, y reparar grietas y cubrir las ventilaciones de los pozos sépticos. También aprenderá cómo se usan los aviones que ayudan a rociar insecticida para los mosquitos.

  14. Application of software technology to a future spacecraft computer design (United States)

    Labaugh, R. J.


    A study was conducted to determine how major improvements in spacecraft computer systems can be obtained from recent advances in hardware and software technology. Investigations into integrated circuit technology indicated that the CMOS/SOS chip set being developed for the Air Force Avionics Laboratory at Wright Patterson had the best potential for improving the performance of spaceborne computer systems. An integral part of the chip set is the bit slice arithmetic and logic unit. The flexibility allowed by microprogramming, combined with the software investigations, led to the specification of a baseline architecture and instruction set.

  15. The other side of the safety coin. [aerospace operations (United States)

    Roth, Gilbert L.


    The development, inspection and testing requirements for successful production and launch and safe operation of spaceflight hardware are discussed. Emphasis is placed on paying acute attention to malfunctions, which could be caused by contaminants (particles in docking rings), insufficiently durable materials (Orbiter brakes), etc. Generic and specific problems which occur in propulsion, avionics, mechanical and computer systems and in configuration management, manufacturing and process control efforts are explored. Case histories of deficiencies found in LOX fuel lines, contaminated hydraulic control systems, the Solar Maximum Mission thermal insulation grommets, are summarized. Thorough inspection and testing procedures and design change recording during manufacture of spacecraft components are identified as requisites for successful space missions.

  16. Information processing. [in human performance (United States)

    Wickens, Christopher D.; Flach, John M.


    Theoretical models of sensory-information processing by the human brain are reviewed from a human-factors perspective, with a focus on their implications for aircraft and avionics design. The topics addressed include perception (signal detection and selection), linguistic factors in perception (context provision, logical reversals, absence of cues, and order reversals), mental models, and working and long-term memory. Particular attention is given to decision-making problems such as situation assessment, decision formulation, decision quality, selection of action, the speed-accuracy tradeoff, stimulus-response compatibility, stimulus sequencing, dual-task performance, task difficulty and structure, and factors affecting multiple task performance (processing modalities, codes, and stages).

  17. Towards a new titanium sector: Aerospace

    CSIR Research Space (South Africa)

    Du Preez, W


    Full Text Available Commercial partners Downstream Products LAM large parts (Aeroswift) Upscaling, Qualification, Industrialisation Additive Manufacturing Potential Impact on South African Aerospace ? CSIR 2012 Slide 16 Se rvi ce s AERONAUTICS SPACE Lau n ch V... ehic le s Sa tel lit e s Long h aul a ir cr af t R egi o n al a ir cr af t Gene ra l a ir cr af t He lico p te rs Se cu rit y U A V ?s Se rvi ce s Other Systems Avionics Propulsion Aero structures...

  18. Research and technology, 1993. Salute to Skylab and Spacelab: Two decades of discovery (United States)


    A summary description of Skylab and Spacelab is presented. The section on Advanced Studies includes projects in space science, space systems, commercial use of space, and transportation systems. Within the Research Programs area, programs are listed under earth systems science, space physics, astrophysics, and microgravity science and applications. Technology Programs include avionics, materials and manufacturing processes, mission operations, propellant and fluid management, structures and dynamics, and systems analysis and integration. Technology transfer opportunities and success are briefly described. A glossary of abbreviations and acronyms is appended as is a list of contract personnel within the program areas.

  19. Prise en charge de l'hematurie au chu Sylvanus Olympio de Lome ...

    African Journals Online (AJOL)

    Une transfusion sanguine avait été réalisée dans 64,8% des cas et nous avions enregistré 4 cas de décès. Conclusion : Les hématuries sont relativement fréquentes au Togo et souvent de causes tumorales. Elles nécessitent une prise en charge précoce pour un meilleur pronostic. Mots clés : hématurie, épidémiologie, ...

  20. NASA Pathways Internship: Spring 2016 (United States)

    Alvarez, Oscar, III


    I was selected to contribute to the Data Systems and Handling Branch under the Avionics Flight Systems Division at the Lyndon B. Johnson Space Center in Houston, Texas. There I used my knowledge from school, as well as my job experience from the military, to help me comprehend my assigned project and contribute to it. With help from my mentors, supervisors, colleagues, and an excellent NASA work environment, I was able to learn, as well as accomplish, a lot towards my project. Not only did I understand more about embedded systems, microcontrollers, and low-level programming, I also was given the opportunity to explore the NASA community.

  1. Installation of new Generation General Purpose Computer (GPC) compact unit (United States)


    In the Kennedy Space Center's (KSC's) Orbiter Processing Facility (OPF) high bay 2, Spacecraft Electronics technician Ed Carter (right), wearing clean suit, prepares for (26864) and installs (26865) the new Generation General Purpose Computer (GPC) compact IBM unit in Atlantis', Orbiter Vehicle (OV) 104's, middeck avionics bay as Orbiter Systems Quality Control technician Doug Snider looks on. Both men work for NASA contractor Lockheed Space Operations Company. All three orbiters are being outfitted with the compact IBM unit, which replaces a two-unit earlier generation computer.

  2. Ciència i pseudociència : un curs obert miniop


    Canet Pladevall, Roser


    Les pseudociències estan proliferant extraordinàriament a través de les xarxes. Presentem un curs online (miniop) obert i autoformatiu per desenvolupar l'esperit crític a partir de la interacció entre els participants. Les activitats analitzen tres casos de creences pseudocientífiques: prediccions del futur, chemtrails (esteles químiques dels avions) i corrents antivacunació. Pseudosciences are extraordinarily proliferating across networks. We present an online course (miniop) open and sel...

  3. A Framework for Integration of IVHM Technologies for Intelligent Integration for Vehicle Management (United States)

    Paris, Deidre E.; Trevino, Luis; Watson, Mike


    As a part of the overall goal of developing Integrated Vehicle Health Management (IVHM) systems for aerospace vehicles, the NASA Faculty Fellowship Program (NFFP) at Marshall Space Flight Center has performed a pilot study on IVHM principals which integrates researched IVHM technologies in support of Integrated Intelligent Vehicle Management (IIVM). IVHM is the process of assessing, preserving, and restoring system functionality across flight and ground systems (NASA NGLT 2004). The framework presented in this paper integrates advanced computational techniques with sensor and communication technologies for spacecraft that can generate responses through detection, diagnosis, reasoning, and adapt to system faults in support of IIVM. These real-time responses allow the IIVM to modify the effected vehicle subsystem(s) prior to a catastrophic event. Furthermore, the objective of this pilot program is to develop and integrate 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 the 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

  4. Intelligent Vehicle Health Management (United States)

    Paris, Deidre E.; Trevino, Luis; Watson, Michael D.


    As a part of the overall goal of developing Integrated Vehicle Health Management systems for aerospace vehicles, the NASA Faculty Fellowship Program (NFFP) at Marshall Space Flight Center has performed a pilot study on IVHM principals which integrates researched IVHM technologies in support of Integrated Intelligent Vehicle Management (IIVM). IVHM is the process of assessing, preserving, and restoring system functionality across flight and ground systems (NASA NGLT 2004). The framework presented in this paper integrates advanced computational techniques with sensor and communication technologies for spacecraft that can generate responses through detection, diagnosis, reasoning, and adapt to system faults in support of INM. These real-time responses allow the IIVM to modify the affected vehicle subsystem(s) prior to a catastrophic event. Furthermore, the objective of this pilot program is to develop and integrate 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 the INM 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

  5. It's quicker "Par Avignon"!

    CERN Multimedia


    For a few years, the CERN Library has been receiving books from the University of Hanover sent via Avignon, at least that's what it says on the envelope. Such a detour would mean that parcels were travelling 720 km more than the distance separating Geneva and Hanover, which would be a very strange state of affairs. The explanation lies in a spelling mistake. The sender has been stamping parcels with a stamp that says "Par Avignon prioritaire" (first-class via Avignon) instead of "Par Avion prioritaire" (First Class Air Mail), a source of much amusement to the librarians!

  6. Method of optimization onboard communication network (United States)

    Platoshin, G. A.; Selvesuk, N. I.; Semenov, M. E.; Novikov, V. M.


    In this article the optimization levels of onboard communication network (OCN) are proposed. We defined the basic parameters, which are necessary for the evaluation and comparison of modern OCN, we identified also a set of initial data for possible modeling of the OCN. We also proposed a mathematical technique for implementing the OCN optimization procedure. This technique is based on the principles and ideas of binary programming. It is shown that the binary programming technique allows to obtain an inherently optimal solution for the avionics tasks. An example of the proposed approach implementation to the problem of devices assignment in OCN is considered.

  7. OPALS: A COTS-based Tech Demo of Optical Communications (United States)

    Oaida, Bogdan


    I. Objective: Deliver video from ISS to optical ground terminal via an optical communications link. a) JPL Phaeton/Early Career Hire (ECH) training project. b) Implemented as Class-D payload. c) Downlink at approx.30Mb/s. II. Flight System a) Optical Head Beacon Acquisition Camera. Downlink Transmitter. 2-axis Gimbal. b) Sealed Container Laser Avionics Power distribution Digital I/O board III. Implementation: a) Ground Station - Optical Communications Telescope Laboratory at Table Mountain Facility b) Flight System mounted to ISS FRAM as standard I/F. Attached externally on Express Logistics Carrier.

  8. Inadvertently programmed bits in Samsung 128 Mbit flash devices: a flaky investigation (United States)

    Swift, G.


    JPL's X2000 avionics design pioneers new territory by specifying a non-volatile memory (NVM) board based on flash memories. The Samsung 128Mb device chosen was found to demonstrate bit errors (mostly program disturbs) and block-erase failures that increase with cycling. Low temperature, certain pseudo- random patterns, and, probably, higher bias increase the observable bit errors. An experiment was conducted to determine the wearout dependence of the bit errors to 100k cycles at cold temperature using flight-lot devices (some pre-irradiated). The results show an exponential growth rate, a wide part-to-part variation, and some annealing behavior.

  9. Smart SPHERES: A Telerobotic Free-Flyer for Intravehicular Activities in Space (United States)

    Fong, Terrence; Micire, Mark J.; Morse, Ted; Park, Eric; Provencher, Chris; To, Vinh; Wheeler, D. W.; Mittman, David; Torres, R. Jay; Smith, Ernest


    Smart SPHERES is a prototype free-flying space robot based on the SPHERES platform. Smart SPHERES can be remotely operated by astronauts inside a spacecraft, or by mission controllers on the ground. We developed Smart SPHERES to perform a variety of intravehicular activities (IVA), such as operations inside the International Space Station (ISS). These IVA tasks include environmental monitoring surveys (radiation, sound levels, etc.), inventory, and mobile camera work. In this paper, we first discuss the motivation for free-flying space robots. We then describe the development of the Smart SPHERES prototype, including avionics, software, and data communications. Finally, we present results of initial flight tests on-board the ISS.

  10. FAA/NASA Joint University Program for Air Transportation Research 1994-1995 (United States)

    Remer, J. H.


    The Joint University Program for Air Transportation Research (JUP) is a coordinated set of three grants co-sponsored by the Federal Aviation Administration (FAA) and the National Aeronautics and Space Administration (NASA). Under JUP, three institutions: the Massachusetts Institute of Technology, Princeton, and Ohio Universities receive research grants and collaborate with FAA and NASA in defining and performing civil aeronautics research in a multitude of areas. Some of these disciplines are artificial intelligence, control theory, atmospheric hazards, navigation, avionics, human factors, flight dynamics, air traffic management, and electronic communications.

  11. Recent Advances in Long Range and Long Endurance Operation of Aircraft (Les Progres Recents dans le Domaine des Operations Aeriennes a Longue Distance et de Longdue Duree) (United States)


    decargur rayon 00 . d’ctonsi(y colmpri Ca misson de auconoyages vde ), respeciement pordes cargois locu uour du [5mon,(igd3a et 2d0es00 00 pons6ur le c...volumineux, done Cependant, les flottes d’avions cargos sp~cialises impossibles A transporter par voje terrestre . Cest grace disponibles ou en projet hi court...n’importe quel point du classiqlue de m~me capacite et m~mes performances monde), et aussi par rapport aux transports terrestres (WB-900), due A une

  12. Should we attempt global (inlet engine airframe) control design? (United States)

    Carlin, C. M.


    The feasibility of multivariable design of the entire airplane control system is briefly addressed. An intermediate step in that direction is to design a control for an inlet engine augmentor system by using multivariable techniques. The supersonic cruise large scale inlet research program is described which will provide an opportunity to develop, integrate, and wind tunnel test a control for a mixed compression inlet and variable cycle engine. The integrated propulsion airframe control program is also discussed which will introduce the problem of implementing MVC within a distributed processing avionics architecture, requiring real time decomposition of the global design into independent modules in response to hardware communication failures.


    Directory of Open Access Journals (Sweden)

    Yuriy Hryshchenko


    Full Text Available This article provides an analytical overview of the work on training of human operator counteract the simultaneous action of negative factors, carried out by experts from the Avionics Department. The focus is on the method of training of operators by removing the negative effects of the flight, which are associated with the phenomenon of amplification of the dynamic stereotype in aviation specialists. It should be noted that the author does not fully cover all the anti-stress training methods that have been developed by our experts

  14. Vehicle health management for guidance, navigation and control systems (United States)

    Radke, Kathleen; Frazzini, Ron; Bursch, Paul; Wald, Jerry; Brown, Don


    The objective of the program was to architect a vehicle health management (VHM) system for space systems avionics that assures system readiness for launch vehicles and for space-based dormant vehicles. The platforms which were studied and considered for application of VHM for guidance, navigation and control (GN&C) included the Advanced Manned Launch System (AMLS), the Horizontal Landing-20/Personnel Launch System (HL-20/PLS), the Assured Crew Return Vehicle (ACRV) and the Extended Duration Orbiter (EDO). This set was selected because dormancy and/or availability requirements are driving the designs of these future systems.

  15. Health management and controls for earth to orbit propulsion systems (United States)

    Bickford, R. L.


    Fault detection and isolation for advanced rocket engine controllers are discussed focusing on advanced sensing systems and software which significantly improve component failure detection for engine safety and health management. Aerojet's Space Transportation Main Engine controller for the National Launch System is the state of the art in fault tolerant engine avionics. Health management systems provide high levels of automated fault coverage and significantly improve vehicle delivered reliability and lower preflight operations costs. Key technologies, including the sensor data validation algorithms and flight capable spectrometers, have been demonstrated in ground applications and are found to be suitable for bridging programs into flight applications.

  16. Ferroelectric memories: A possible answer to the hardened nonvolatile question

    International Nuclear Information System (INIS)

    Messenger, G.C.; Coppage, F.N.


    Ferroelectric memory cells have been fabricated using a process compatible with semiconductor VLSI (Very Large-Scale Integration) manufacturing techniques which are basically nonvolatile and radiation hard. The memory can be made NDRO (Nondestructive Readout) for strategic systems using several techniques; the most practical is probably a rapid read/restore in combination with EDAC software. This memory can replace plated wire and will have substantial advantages in cost, weight, size, power and speed. It provides a practical cost-competitive solution to the need for nonvolatile RAM in all hardened tactical, avionic, and space systems

  17. Advanced and tendencies in the development of display technologies (United States)

    Kompanets, I. N.


    Advances and key display applications are discussed. Computer, compact mobile, TV and collective large screen displays are mentioned. Flat panel displays step on CRT devices to leave them behind in 2007. Materials, active matricies and applications of bright radiative field emission and organic LED displays are developing successively and pressing other technologies to be used in photo-cameras, cellular phones, auto-cars and avionics. Progress in flexible screens can substantially extend the display design and application soon. 3D display systems are under intensive development, and laser is an important unit in some vaiants of holographic and volumetric 3D displays. Value forecast of different display markets is presented.

  18. Space Vehicle Flight Mechanics (La Mecanique du Vol des Vehicules Spatiaux) (United States)


    Space Telescope, an astrophysics spacelab mission, Astro , the Gamma Ray Observatory, Spacelab Life Sciences -1 and ESA/NASA Ulysses. The Great...all the hardware/avionics subsystems, the flight software, and the astro - nauts. Here, the software and the interfaces can be thoroughly checked out...rm6di ai re de Il’angl e G ,(F,,, Fz,)~ = h,, 7 (171) de rotatioa des axes lies 5 la Terre F ,U3P rapport aux axes Fxc ; (Fg.30. Iqest la vitesse de

  19. Estación de seguimiento SKY-EYE para UAVs: modelización y tratamiento de planes de vuelo


    López Liévana, Borja


    El sector aeronáutico se encuentra en una nueva era de crecimiento gracias a numerosos avances tecnológicos. Uno de ellos son los UAV, aviones no tripulados que son capaces de volar por sí solos y con capacidad de tomar decisiones. Este trabajo forma parte del proyecto SKY-EYE, el cual está desarrollando un nuevo sistema con tecnología UAV para uso civil. Es cierto que este tipo de tecnología ya se usa en el ámbito militar desde hace años, pero es ahora en el uso civil dónde se...

  20. Monitoring Distributed Real-Time Systems: A Survey and Future Directions (United States)

    Goodloe, Alwyn E.; Pike, Lee


    Runtime monitors have been proposed as a means to increase the reliability of safety-critical systems. In particular, this report addresses runtime monitors for distributed hard real-time systems. This class of systems has had little attention from the monitoring community. The need for monitors is shown by discussing examples of avionic systems failure. We survey related work in the field of runtime monitoring. Several potential monitoring architectures for distributed real-time systems are presented along with a discussion of how they might be used to monitor properties of interest.

  1. Visual Problems in Night Operations (Problemes de Vision dans les Operations de Nuit) (United States)


    conference proceedings (FR) Progrqbs r~cents concernant l05 aides au pilote clans I habitacle d’un aaroi’ef milltaire en operations. Nouveau drone ...allleurs) traitelit doe la sophistication des La firme isra~lienne tAt teste un nouveau drone appel6 ’Impact’. tacnes domanda~es aus pilotes d-avionS- doe...une camara do tala6vision A vision nocturne. 151 met aussl relations liomlme-macfline.ces syst~mws (lndiff~remesmnt dasignds au point une station

  2. Reuse fo a Cold War Surveillance Drone to Flight Test a NASA Rocket Based Combined Cycle Engine (United States)

    Brown, T. M.; Smith, Norm


    Plans for and early feasibility investigations into the modification of a Lockheed D21B drone to flight test the DRACO Rocket Based Combined Cycle (RBCC) engine are discussed. Modifications include the addition of oxidizer tanks, modern avionics systems, actuators, and a vehicle recovery system. Current study results indicate that the D21B is a suitable candidate for this application and will allow demonstrations of all DRACO engine operating modes at Mach numbers between 0.8 and 4.0. Higher Mach numbers may be achieved with more extensive modification. Possible project risks include low speed stability and control, and recovery techniques.

  3. Sensory redundancy management: The development of a design methodology for determining threshold values through a statistical analysis of sensor output data (United States)

    Scalzo, F.


    Sensor redundancy management (SRM) requires a system which will detect failures and reconstruct avionics accordingly. A probability density function to determine false alarm rates, using an algorithmic approach was generated. Microcomputer software was developed which will print out tables of values for the cummulative probability of being in the domain of failure; system reliability; and false alarm probability, given a signal is in the domain of failure. The microcomputer software was applied to the sensor output data for various AFT1 F-16 flights and sensor parameters. Practical recommendations for further research were made.

  4. An expert system environment for the Generic VHSIC Spaceborne Computer (GVSC) (United States)

    Cockerham, Ann; Labhart, Jay; Rowe, Michael; Skinner, James

    The authors describe a Phase II Phillips Laboratory Small Business Innovative Research (SBIR) program being performed to implement a flexible and general-purpose inference environment for embedded space and avionics applications. This inference environment is being developed in Ada and takes special advantage of the target architecture, the GVSC. The GVSC implements the MIL-STD-1750A ISA and contains enhancements to allow access of up to 8 MBytes of memory. The inference environment makes use of the Merit Enhanced Traversal Engine (METE) algorithm, which employs the latest inference and knowledge representation strategies to optimize both run-time speed and memory utilization.

  5. Static Aeroelastic Effects on High Performance Aircraft (United States)


    davis la rffrence 9. L’avion est instrurnent6, en plus des capteurs classiques des param~tres de n~ca- nique du vol. de plusleurs centaines de jauges de...crites §2.3.5, et lensemble dv l’analyse, pernet- tent le calcul des r~ponues des jauges en fonction dv X soit ar ( X) , lv procesnus de d~rivation...travissonique. Rema rque La smine technique d’identification par rtponne dv jauges s’applique (plus simple- ment) sur len essais en soufflerie, pour la

  6. ISS Payload Racks Automated Flow Control Calibration Method (United States)

    Simmonds, Boris G.


    Payload Racks utilize MTL and/or LTL station water for cooling of payloads and avionics. Flow control range from valves of fully closed, to up to 300 Ibmhr. Instrument accuracies are as high as f 7.5 Ibm/hr for flow sensors and f 3 Ibm/hr for valve controller, for a total system accuracy of f 10.5 Ibm/hr. Improved methodology was developed, tested and proven that reduces accuracy of the commanded flows to less than f 1 Ibmhr. Uethodology could be packed in a "calibration kit" for on- orbit flow sensor checkout and recalibration, extending the rack operations before return to earth. -

  7. Benefits of Using Pairwise Trajectory Management in the Central East Pacific (United States)

    Chartrand, Ryan; Ballard, Kathryn


    Pairwise Trajectory Management (PTM) is a concept that utilizes airborne and ground-based capabilities to enable airborne spacing operations in procedural airspace. This concept makes use of updated ground automation, Automatic Dependent Surveillance-Broadcast (ADS-B) and on board avionics generating real time guidance. An experiment was conducted to examine the potential benefits of implementing PTM in the Central East Pacific oceanic region. An explanation of the experiment and some of the results are included in this paper. The PTM concept allowed for an increase in the average time an aircraft is able to spend at its desired flight level and a reduction in fuel burn.

  8. Spacecraft Conceptual Design for the 8-Meter Advanced Technology Large Aperture Space Telescope (ATLAST) (United States)

    Hopkins, Randall C.; Capizzo, Peter; Fincher, Sharon; Hornsby, Linda S.; Jones, David


    The Advanced Concepts Office at Marshall Space Flight Center completed a brief spacecraft design study for the 8-meter monolithic Advanced Technology Large Aperture Space Telescope (ATLAST-8m). This spacecraft concept provides all power, communication, telemetry, avionics, guidance and control, and thermal control for the observatory, and inserts the observatory into a halo orbit about the second Sun-Earth Lagrange point. The multidisciplinary design team created a simple spacecraft design that enables component and science instrument servicing, employs articulating solar panels for help with momentum management, and provides precise pointing control while at the same time fast slewing for the observatory.

  9. AGARD Index of Publications 1983-1985 (United States)


    NUMERIGUE DU MOTEUR ET LES T. C. ADEN In AGARD integration of Fire Control, Flight Control AUTRES FONCTIONS DE L’AVION] and Propulsion Control Systems 14 DE SPECTRE I has been performed. The performance gains that are achieved M. SCHILLIGER and C. LELOUP In AGARD Propagation with the use of a...A distributfed aran signal processor erth laulfttolerance ADEN . T. C. erarhatro, ot flying personnel p,1f0 N842r0a9 attributes p 190 Nt6 28360

  10. Marshall Space Flight Center Faculty Fellowship Program (United States)

    Six, N. F.; Karr, G.


    The research projects conducted by the 2016 Faculty Fellows at NASA Marshall Space Flight Center included propulsion studies on propellant issues, and materials investigations involving plasma effects and friction stir welding. Spacecraft Systems research was conducted on wireless systems and 3D printing of avionics. Vehicle Systems studies were performed on controllers and spacecraft instruments. The Science and Technology group investigated additive construction applied to Mars and Lunar regolith, medical uses of 3D printing, and unique instrumentation, while the Test Laboratory measured pressure vessel leakage and crack growth rates.

  11. Deploying a Route Optimization EFB Application for Commercial Airline Operational Trials (United States)

    Roscoe, David A.; Vivona, Robert A.; Woods, Sharon E.; Karr, David A.; Wing, David J.


    The Traffic Aware Planner (TAP), developed for NASA Langley Research Center to support the Traffic Aware Strategic Aircrew Requests (TASAR) project, is a flight-efficiency software application developed for an Electronic Flight Bag (EFB). Tested in two flight trials and planned for operational testing by two commercial airlines, TAP is a real-time trajectory optimization application that leverages connectivity with onboard avionics and broadband Internet sources to compute and recommend route modifications to flight crews to improve fuel and time performance. The application utilizes a wide range of data, including Automatic Dependent Surveillance Broadcast (ADS-B) traffic, Flight Management System (FMS) guidance and intent, on-board sensors, published winds and weather, and Special Use Airspace (SUA) schedules. This paper discusses the challenges of developing and deploying TAP to various EFB platforms, our solutions to some of these challenges, and lessons learned, to assist commercial software developers and hardware manufacturers in their efforts to implement and extend TAP functionality in their environments. EFB applications (such as TAP) typically access avionics data via an ARINC 834 Simple Text Avionics Protocol (STAP) server hosted by an Aircraft Interface Device (AID) or other installed hardware. While the protocol is standardized, the data sources, content, and transmission rates can vary from aircraft to aircraft. Additionally, the method of communicating with the AID may vary depending on EFB hardware and/or the availability of onboard networking services, such as Ethernet, WIFI, Bluetooth, or other mechanisms. EFBs with portable and installed components can be implemented using a variety of operating systems, and cockpits are increasingly incorporating tablet-based technologies, further expanding the number of platforms the application may need to support. Supporting multiple EFB platforms, AIDs, avionics datasets, and user interfaces presents a


    Directory of Open Access Journals (Sweden)

    P. P. Paramonov


    Full Text Available The article deals with present situation review and analysis of development prospects for integrated on-board computing systems, used in the aviation instrument-making industry. The main attention is paid to the projects carried out in the framework of an integrated modular avionics. Hierarchical levels of module design, crates (onboard systems and aviation complexes are considered in detail. Examples of the existing products of our country and from abroad and their brief technical characteristics are given and voluminous bibliography on the subject matter as well.

  13. Comportamiento [del] tanque de material compuesto ante cargas dinámicas


    Artero Guerrero, José Alfonso


    Este proyecto fin de carrera analiza los impactos de fragmento a alta velocidad sobre estructuras de material compuesto que contienen líquidos. En este proyecto se estudia la vulnerabilidad de la estructura cuando está fabricada en material compuesto. Las excelentes propiedades que tienen los plásticos reforzados de fibras de carbono en cuanto a baja densidad y alta resistencia mecánica los sitúan en una situación clave para desarrollarse como material estructural en fabricación de aviones. E...

  14. An Introduction to TTCN-3

    CERN Document Server

    Willcock, Colin; Tobies, Stephan; Keil, Stefan; Engler, Federico; Schulz, Stephan; Wiles, Anthony


    This unique book provides a fully revised and up-to-date treatment of the TTCN-3 language TTCN-3 is an internationally standardised test language with a powerful textual syntax which has established itself as a global, universal testing language. Application of TTCN-3 has been widened beyond telecommunication systems to areas such as the automotive industry, internet protocols, railway signalling, medical systems, and avionics.An Introduction to TTCN-3 gives a solid introduction to the TTCN-3 language and its uses, guiding readers though the TTCN-3 standards, methodologies and tools with examp

  15. A Low Cost Single Chip VDL Compatible Transceiver ASIC (United States)

    Becker, Robert


    Recent trends in commercial communications system components have focussed almost exclusively on cellular telephone technology. As many of the traditional sources of receiver components have discontinued non-cellular telephone products, the designers of avionics and other low volume radio applications find themselves increasingly unable to find highly integrated components. This is particularly true for low power, low cost applications which cannot afford the lavish current consumption of the software defined radio approach increasingly taken by certified device manufacturers. In this paper, we describe a low power transceiver chip targeting applications from low VHF to low UHF frequencies typical of avionics systems. The chip encompasses a selectable single or double conversion design for the receiver and a low power IF upconversion transmitter. All local oscillators are synthesized and integrated into the chip. An on-chip I-Q modulator and demodulator provide baseband modulation and demodulation capability allowing the use of low power, fixed point signal processing components for signal demodulation. The goal of this program is to demonstrate a low cost VDL mode-3 transceiver using this chip to receive text weather information sent using 4-slot TDMA with no support for voice. The data will be sent from an experimental ground station. This work is funded by NASA Glenn Research Center.

  16. Autonomous, agile micro-satellites and supporting technologies

    International Nuclear Information System (INIS)

    Breitfeller, E; Dittman, M D; Gaughan, R J; Jones, M S; Kordas, J F; Ledebuhr, A G; Ng, L C; Whitehead, J C; Wilson, B


    This paper updates the on-going effort at Lawrence Livermore National Laboratory to develop autonomous, agile micro-satellites (MicroSats). The objective of this development effort is to develop MicroSats weighing only a few tens of kilograms, that are able to autonomously perform precision maneuvers and can be used telerobotically in a variety of mission modes. The required capabilities include satellite rendezvous, inspection, proximity-operations, docking, and servicing. The MicroSat carries an integrated proximity-operations sensor-suite incorporating advanced avionics. A new self-pressurizing propulsion system utilizing a miniaturized pump and non-toxic mono-propellant hydrogen peroxide was successfully tested. This system can provide a nominal 25 kg MicroSat with 200-300 m/s delta-v including a warm-gas attitude control system. The avionics is based on the latest PowerPC processor using a CompactPCI bus architecture, which is modular, high-performance and processor-independent. This leverages commercial-off-the-shelf (COTS) technologies and minimizes the effects of future changes in processors. The MicroSat software development environment uses the Vx-Works real-time operating system (RTOS) that provides a rapid development environment for integration of new software modules, allowing early integration and test. We will summarize results of recent integrated ground flight testing of our latest non-toxic pumped propulsion MicroSat testbed vehicle operated on our unique dynamic air-rail

  17. User type certification for advanced flight control systems (United States)

    Gilson, Richard D.; Abbott, David W.


    Advanced avionics through flight management systems (FMS) coupled with autopilots can now precisely control aircraft from takeoff to landing. Clearly, this has been the most important improvement in aircraft since the jet engine. Regardless of the eventual capabilities of this technology, it is doubtful that society will soon accept pilotless airliners with the same aplomb they accept driverless passenger trains. Flight crews are still needed to deal with inputing clearances, taxiing, in-flight rerouting, unexpected weather decisions, and emergencies; yet it is well known that the contribution of human errors far exceed those of current hardware or software systems. Thus human errors remain, and are even increasing in percentage as the largest contributor to total system error. Currently, the flight crew is regulated by a layered system of certification: by operation, e.g., airline transport pilot versus private pilot; by category, e.g., airplane versus helicopter; by class, e.g., single engine land versus multi-engine land; and by type (for larger aircraft and jet powered aircraft), e.g., Boeing 767 or Airbus A320. Nothing in the certification process now requires an in-depth proficiency with specific types of avionics systems despite their prominent role in aircraft control and guidance.

  18. Errores comunes de un piloto de Lancair frente a condiciones de tiempo adversas

    Directory of Open Access Journals (Sweden)

    Martín Zorrilla


    Full Text Available Este artículo analiza el origen de las causas principales de accidentes que se presentan en aeronaves experimentales Lancair. Por su naturaleza, los aviones experimentales exhiben unas condiciones de vuelo únicas que podrían volverse difíciles durante condiciones climáticas adversas. Para este estudio, fue utilizada la base de datos del Buró Nacional de Seguridad en el Transporte (NTSB de los Estados Unidos desde enero 2005 a diciembre de 2014, teniendo en cuenta diez casos de accidentes fatales relacionados con aviones provenientes de esta marca. Se concluyó que la desorientación y la toma de decisiones relacionadas con errores fueron las razones principales, que están asociadas directamente con habilidades de pilotos en el momento del accidente. Asimismo, se recomienda un análisis exhaustivo a esta investigación para una posterior aplicación a casos reales como en la Fuerza Aérea Colombiana.

  19. Navigation and flight director guidance for the NASA/FAA helicopter MLS curved approach flight test program (United States)

    Phatak, A. V.; Lee, M. G.


    The navigation and flight director guidance systems implemented in the NASA/FAA helicopter microwave landing system (MLS) curved approach flight test program is described. Flight test were conducted at the U.S. Navy's Crows Landing facility, using the NASA Ames UH-lH helicopter equipped with the V/STOLAND avionics system. The purpose of these tests was to investigate the feasibility of flying complex, curved and descending approaches to a landing using MLS flight director guidance. A description of the navigation aids used, the avionics system, cockpit instrumentation and on-board navigation equipment used for the flight test is provided. Three generic reference flight paths were developed and flown during the test. They were as follows: U-Turn, S-turn and Straight-In flight profiles. These profiles and their geometries are described in detail. A 3-cue flight director was implemented on the helicopter. A description of the formulation and implementation of the flight director laws is also presented. Performance data and analysis is presented for one pilot conducting the flight director approaches.

  20. Fiber-Optic Communication Links Suitable for On-Board Use in Modern Aircraft (United States)

    Nguyen, Hung; Ngo, Duc; Alam, Mohammad F.; Atiquzzaman, Mohammed; Sluse, James; Slaveski, Filip


    The role of the Advanced Air Transportation Technologies program undertaken at the NASA Glenn Research Centers has been focused mainly on the improvement of air transportation safety, with particular emphasis on air transportation communication systems in on-board aircraft. The conventional solutions for digital optical communications systems specifically designed for local/metro area networks are, unfortunately, not capable of transporting the microwave and millimeter RF signals used in avionics systems. Optical networks capable of transporting RF signals are substantially different from the standard digital optical communications systems. The objective of this paper is to identify a number of different communication link architectures for RF/fiber optic transmission using a single backbone fiber for carrying VHF and UHF RF signals in the aircraft. To support these architectures, two approaches derived from both hybrid RF-optical and all-optical processing methodologies are discussed with single and multiple antennas for explicitly transporting VHF and UHF signals, while the relative merits and demerits of each architecture are also addressed. Furthermore, the experimental results of wavelength division multiplexing (WDM) link architecture from our test-bed platform, configured for aircraft environment to support simultaneous transmission of multiple RF signals over a single optical fiber, exhibit no appreciable signal degradation at wavelengths of both 1330 and 1550 nm, respectively. Our measurements of signal to noise ratio carried out for the transmission of FM and AM analog modulated signals at these wavelengths indicate that WDM is a fiber optic technology which is potentially suitable for avionics applications.

  1. Mission Management Computer and Sequencing Hardware for RLV-TD HEX-01 Mission (United States)

    Gupta, Sukrat; Raj, Remya; Mathew, Asha Mary; Koshy, Anna Priya; Paramasivam, R.; Mookiah, T.


    Reusable Launch Vehicle-Technology Demonstrator Hypersonic Experiment (RLV-TD HEX-01) mission posed some unique challenges in the design and development of avionics hardware. This work presents the details of mission critical avionics hardware mainly Mission Management Computer (MMC) and sequencing hardware. The Navigation, Guidance and Control (NGC) chain for RLV-TD is dual redundant with cross-strapped Remote Terminals (RTs) interfaced through MIL-STD-1553B bus. MMC is Bus Controller on the 1553 bus, which does the function of GPS aided navigation, guidance, digital autopilot and sequencing for the RLV-TD launch vehicle in different periodicities (10, 20, 500 ms). Digital autopilot execution in MMC with a periodicity of 10 ms (in ascent phase) is introduced for the first time and successfully demonstrated in the flight. MMC is built around Intel i960 processor and has inbuilt fault tolerance features like ECC for memories. Fault Detection and Isolation schemes are implemented to isolate the failed MMC. The sequencing hardware comprises Stage Processing System (SPS) and Command Execution Module (CEM). SPS is `RT' on the 1553 bus which receives the sequencing and control related commands from MMCs and posts to downstream modules after proper error handling for final execution. SPS is designed as a high reliability system by incorporating various fault tolerance and fault detection features. CEM is a relay based module for sequence command execution.

  2. eletrônicos portáteis (PEDs

    Directory of Open Access Journals (Sweden)

    André Felipe Henriques Librantz


    Full Text Available Great concern has been demonstrated by different aeronautic operators about the effects of electromagnetic interference in avionics and electronic equipments of airplanes, due to the use of portable electronic devices (PEDs, which can be easily carried by the passengers. Among the suspect devices, there are laptops and palmtops, audio recorders and reproducers, electronic games and toys, laser pointers, cell phones, communication radios and pagers. Uncouplings or automatic pilot deviations, mistaken indications in displays and, even, the unadverted disconnection of the avionics or variations not commanded in the control surfaces are flaws attributed to these devices. In spite of suffering critics, several regulation agencies in aeronautics, all over the world, have prohibited the use of these portable devices, specially in the critical phases of the flight – landing and take off. Nevertheless, it’s getting bigger the passengers desire of using, uninterruptely, laptops and cell phones, what makes necessary the adoption of safety procedures to satisfy this demand. Besides the concern over these dangerous effects, there are yet, doubts over the topic, and, therefore, it’s indicated the need of more investigations over these phenomenons. In this work, we relate the main accomplished experiments with the intent to clarify how the PEDs, more specifically the cell phones, cause an undesirable electromagnetic interference.

  3. Feasibility Criteria for Interval Management Operations as Part of Arrival Management Operations (United States)

    Levitt, Ian M.; Weitz, Lesley A.; Barmore, Bryan E.; Castle, Michael W.


    Interval Management (IM) is a future airborne spacing concept that aims to provide more precise inter-aircraft spacing to yield throughput improvements and greater use of fuel efficient trajectories for arrival and approach operations. To participate in an IM operation, an aircraft must be equipped with avionics that provide speeds to achieve and maintain an assigned spacing interval relative to another aircraft. It is not expected that all aircraft will be equipped with the necessary avionics, but rather that IM fits into a larger arrival management concept developed to support the broader mixed-equipage environment. Arrival management concepts are comprised of three parts: a ground-based sequencing and scheduling function to develop an overall arrival strategy, ground-based tools to support the management of aircraft to that schedule, and the IM tools necessary for the IM operation (i.e., ground-based set-up, initiation, and monitoring, and the flight-deck tools to conduct the IM operation). The Federal Aviation Administration is deploying a near-term ground-automation system to support metering operations in the National Airspace System, which falls within the first two components of the arrival management concept. This paper develops a methodology for determining the required delivery precision at controlled meter points for aircraft that are being managed to a schedule and aircraft being managed to a relative spacing interval in order to achieve desired flow rates and adequate separation at the meter points.

  4. Adapting the SpaceCube v2.0 Data Processing System for Mission-Unique Application Requirements (United States)

    Petrick, David; Gill, Nat; Hasouneh, Munther; Stone, Robert; Winternitz, Luke; Thomas, Luke; Davis, Milton; Sparacino, Pietro; Flatley, Thomas


    The SpaceCube (sup TM) v2.0 system is a superior high performance, reconfigurable, hybrid data processing system that can be used in a multitude of applications including those that require a radiation hardened and reliable solution. This paper provides an overview of the design architecture, flexibility, and the advantages of the modular SpaceCube v2.0 high performance data processing system for space applications. The current state of the proven SpaceCube technology is based on nine years of engineering and operations. Five systems have been successfully operated in space starting in 2008 with four more to be delivered for launch vehicle integration in 2015. The SpaceCube v2.0 system is also baselined as the avionics solution for five additional flight projects and is always a top consideration as the core avionics for new instruments or spacecraft control. This paper will highlight how this multipurpose system is currently being used to solve design challenges of three independent applications. The SpaceCube hardware adapts to new system requirements by allowing for application-unique interface cards that are utilized by reconfiguring the underlying programmable elements on the core processor card. We will show how this system is being used to improve on a heritage NASA GPS technology, enable a cutting-edge LiDAR instrument, and serve as a typical command and data handling (C&DH) computer for a space robotics technology demonstration.

  5. Vector-matrix-quaternion, array and arithmetic packages: All HAL/S functions implemented in Ada (United States)

    Klumpp, Allan R.; Kwong, David D.


    The HAL/S avionics programmers have enjoyed a variety of tools built into a language tailored to their special requirements. Ada is designed for a broader group of applications. Rather than providing built-in tools, Ada provides the elements with which users can build their own. Standard avionic packages remain to be developed. These must enable programmers to code in Ada as they have coded in HAL/S. The packages under development at JPL will provide all of the vector-matrix, array, and arithmetic functions described in the HAL/S manuals. In addition, the linear algebra package will provide all of the quaternion functions used in Shuttle steering and Galileo attitude control. Furthermore, using Ada's extensibility, many quaternion functions are being implemented as infix operations; equivalent capabilities were never implemented in HAL/S because doing so would entail modifying the compiler and expanding the language. With these packages, many HAL/S expressions will compile and execute in Ada, unchanged. Others can be converted simply by replacing the implicit HAL/S multiply operator with the Ada *. Errors will be trapped and identified. Input/output will be convenient and readable.

  6. State Machine Modeling of the Space Launch System Solid Rocket Boosters (United States)

    Harris, Joshua A.; Patterson-Hine, Ann


    The Space Launch System is a Shuttle-derived heavy-lift vehicle currently in development to serve as NASA's premiere launch vehicle for space exploration. The Space Launch System is a multistage rocket with two Solid Rocket Boosters and multiple payloads, including the Multi-Purpose Crew Vehicle. Planned Space Launch System destinations include near-Earth asteroids, the Moon, Mars, and Lagrange points. The Space Launch System is a complex system with many subsystems, requiring considerable systems engineering and integration. To this end, state machine analysis offers a method to support engineering and operational e orts, identify and avert undesirable or potentially hazardous system states, and evaluate system requirements. Finite State Machines model a system as a finite number of states, with transitions between states controlled by state-based and event-based logic. State machines are a useful tool for understanding complex system behaviors and evaluating "what-if" scenarios. This work contributes to a state machine model of the Space Launch System developed at NASA Ames Research Center. The Space Launch System Solid Rocket Booster avionics and ignition subsystems are modeled using MATLAB/Stateflow software. This model is integrated into a larger model of Space Launch System avionics used for verification and validation of Space Launch System operating procedures and design requirements. This includes testing both nominal and o -nominal system states and command sequences.

  7. ¿Por qué el Pulqui II no llegó a la serie? Una sociología histórica de la innovación tecnológica en tiempos de Perón.

    Directory of Open Access Journals (Sweden)

    Alejandro Artopoulos


    Full Text Available El Pulqui II fue un proyecto de avión caza desarrollado en la Argentina durante un poco más de cuatro años entre 1949 y 1953. No solo se trató del diseño número treinta y tres de la estatal Fábrica de Aviones de Córdoba, también representó para la Argentina la oportunidad única de formar parte de la élite de países que dominaron tempranamente la tecnología de aviones propulsados por motores jet. Si bien los prototipos fueron probados en vuelo con relativo éxito, el proyecto industrial de producción en serie nunca se concretó. La administración peronista lo abandonó para fundar un polo de industria automotriz en Córdoba. Un proyecto industrial con menosambición tecnológica pero con proyección estratégica, ya que pondría a la Argentina, por al menosuna década, al frente del proceso de industrialización de Latinoamérica.

  8. Five-Segment Solid Rocket Motor Development Status (United States)

    Priskos, Alex S.


    In support of the National Aeronautics and Space Administration (NASA), Marshall Space Flight Center (MSFC) is developing a new, more powerful solid rocket motor for space launch applications. To minimize technical risks and development costs, NASA chose to use the Space Shuttle s solid rocket boosters as a starting point in the design and development. The new, five segment motor provides a greater total impulse with improved, more environmentally friendly materials. To meet the mass and trajectory requirements, the motor incorporates substantial design and system upgrades, including new propellant grain geometry with an additional segment, new internal insulation system, and a state-of-the art avionics system. Significant progress has been made in the design, development and testing of the propulsion, and avionics systems. To date, three development motors (one each in 2009, 2010, and 2011) have been successfully static tested by NASA and ATK s Launch Systems Group in Promontory, UT. These development motor tests have validated much of the engineering with substantial data collected, analyzed, and utilized to improve the design. This paper provides an overview of the development progress on the first stage propulsion system.

  9. Methodes de calcul des forces aerodynamiques pour les etudes des interactions aeroservoelastiques (United States)

    Biskri, Djallel Eddine

    L'aeroservoelasticite est un domaine ou interagissent la structure flexible d'un avion, l'aerodynamique et la commande de vol. De son cote, la commande du vol considere l'avion comme une structure rigide et etudie l'influence du systeme de commande sur la dynamique de vol. Dans cette these, nous avons code trois nouvelles methodes d'approximation de forces aerodynamiques: Moindres carres corriges, Etat minimal corrige et Etats combines. Dans les deux premieres methodes, les erreurs d'approximation entre les forces aerodynamiques approximees par les methodes classiques et celles obtenues par les nouvelles methodes ont les memes formes analytiques que celles des forces aerodynamiques calculees par LS ou MS. Quant a la troisieme methode, celle-ci combine les formulations des forces approximees avec les methodes standards LS et MS. Les vitesses et frequences de battement et les temps d'executions calcules par les nouvelles methodes versus ceux calcules par les methodes classiques ont ete analyses.

  10. ``DMS-R, the Brain of the ISS'', 10 Years of Continuous Successful Operation in Space (United States)

    Wolff, Bernd; Scheffers, Peter


    Space industries on both sides of the Atlantic were faced with a new situation of collaboration in the beginning of the 1990s.In 1995, industrial cooperation between ASTRIUM ST, Bremen and RSC-E, Moscow started aiming the outfitting of the Russian Service Module ZVEZDA for the ISS with computers. The requested equipments had to provide not only redundancy but fault tolerance and high availability. The design and development of two fault tolerant computers, (FTCs) responsible for the telemetry (Telemetry Computer: TC) and the central control (CC), as well as the man machine interface CPC were contracted to ASTRIUM ST, Bremen. The computer system is responsible e.g. for the life support system and the ISS re-boost control.In July 2000, the integration of the Russian Service Module ZVEZDA with Russian ZARYA FGB and American Node 1 bears witness for transatlantic and European cooperation.The Russian Service module ZVEZDA provides several basic functions as Avionics Control, the Environmental Control and Life Support (ECLS) in the ISS and control of the docked Automatic Transfer Vehicle (ATV) which includes re-boost of ISS. If these elementary functions fail or do not work reliable the effects for the ISS will be catastrophic with respect to Safety (manned space) and ISS mission.For that reason the responsible computer system Data Management System - Russia (DMS-R) is also called "The brain of the ISS".The Russian Service module ZVEZDA, including DMS-R, was launched on 12th of July, 2000. DMS-R was operational also during launch and docking.The talk provide information about the definition, design and development of DMS-R, the integration of DMS-R in the Russian Service module and the maintenance of the system in space. Besides the technical aspects are also the German - Russian cooperation an important subject of this speech. An outlook finalises the talk providing further development activities and application of fault tolerant systems.The importance of the DMS

  11. The use aeroplanes and vehicles for prospecting. The technique of the detection radioactivity. The future opened up by the use of the discrimination of energies; Methodes de prospection autoportee et aeroportee. La technique de la detection des rayonnements. Les perspectives offertes par la discrimination des energies

    Energy Technology Data Exchange (ETDEWEB)

    Guitton, J; Berbezier, J; Blangy, B; Lallemant, C [Commissariat a l' Energie Atomique, Saclay (France). Centre d' Etudes Nucleaires


    The idea of installing activity detectors on aeroplanes and vehicles has been widely applied by the CEA since the start of prospecting in the arid and tropical regions of the Communaute Francaise. Three systems of detection have been developed and compared in a systematic manner: a group of 50 G.M. tubes; the sodium iodide scintillator; the plastic scintillator. The sodium iodide scintillator is used as a standard reference; the results are compared by graphical recording. Airborne prospecting is carried out in two stages: the initial flights, which follow a kilometre square network, make possible the discovery of the most likely zones; these likely zones are then examined in greater detail using light aeroplanes or helicopters. The two types of airborne scintillation measuring devices which have been developed by the CEA are described in this article. The practical results obtained during systematic and detailed airborne prospecting campaigns in the Hoggar are described. The difficulty in airborne uranium prospecting is to be able to immediately distinguish while in flight, anomalies caused by uranium from those caused by thorium. (author) [French] L'idee de monter des detecteurs de rayonnements sur des avions ou des vehicules a ete largement appliquee par le CEA des le debut des prospections dans les pays sahariens et tropicaux de la Communaute Fran ise. On a realise et compare d'une maniere systematique trois moyens de detection: groupe de 50 tubes GM; scintillateur d'iodure de sodium, scintillateur plastique. L'appareil de reference sera le scintillateur d'iodure de sodium; les resultats sont compares par enregistrement graphique. La prospection aeroportee se fait en deux etapes; les premiers vols systematiques suivant un quadrillage kilometrique permettent de reperer les zones interessantes; ces dernieres font l'objet d'examens plus detailles effectues en avion leger ou en helicoptere. Dans cet article, on decrit les deux types de scintillometres aeroportes

  12. High-Performance 3D Articulated Robot Display (United States)

    Powell, Mark W.; Torres, Recaredo J.; Mittman, David S.; Kurien, James A.; Abramyan, Lucy


    In the domain of telerobotic operations, the primary challenge facing the operator is to understand the state of the robotic platform. One key aspect of understanding the state is to visualize the physical location and configuration of the platform. As there is a wide variety of mobile robots, the requirements for visualizing their configurations vary diversely across different platforms. There can also be diversity in the mechanical mobility, such as wheeled, tracked, or legged mobility over surfaces. Adaptable 3D articulated robot visualization software can accommodate a wide variety of robotic platforms and environments. The visualization has been used for surface, aerial, space, and water robotic vehicle visualization during field testing. It has been used to enable operations of wheeled and legged surface vehicles, and can be readily adapted to facilitate other mechanical mobility solutions. The 3D visualization can render an articulated 3D model of a robotic platform for any environment. Given the model, the software receives real-time telemetry from the avionics system onboard the vehicle and animates the robot visualization to reflect the telemetered physical state. This is used to track the position and attitude in real time to monitor the progress of the vehicle as it traverses its environment. It is also used to monitor the state of any or all articulated elements of the vehicle, such as arms, legs, or control surfaces. The visualization can also render other sorts of telemetered states visually, such as stress or strains that are measured by the avionics. Such data can be used to color or annotate the virtual vehicle to indicate nominal or off-nominal states during operation. The visualization is also able to render the simulated environment where the vehicle is operating. For surface and aerial vehicles, it can render the terrain under the vehicle as the avionics sends it location information (GPS, odometry, or star tracking), and locate the vehicle

  13. SCaN Testbed Software Development and Lessons Learned (United States)

    Kacpura, Thomas J.; Varga, Denise M.


    National Aeronautics and Space Administration (NASA) has developed an on-orbit, adaptable, Software Defined Radio (SDR)Space Telecommunications Radio System (STRS)-based testbed facility to conduct a suite of experiments to advance technologies, reduce risk, and enable future mission capabilities on the International Space Station (ISS). The SCAN Testbed Project will provide NASA, industry, other Government agencies, and academic partners the opportunity to develop and field communications, navigation, and networking technologies in the laboratory and space environment based on reconfigurable, SDR platforms and the STRS Architecture.The SDRs are a new technology for NASA, and the support infrastructure they require is different from legacy, fixed function radios. SDRs offer the ability to reconfigure on-orbit communications by changing software for new waveforms and operating systems to enable new capabilities or fix any anomalies, which was not a previous option. They are not stand alone devices, but required a new approach to effectively control them and flow data. This requires extensive software to be developed to utilize the full potential of these reconfigurable platforms. The paper focuses on development, integration and testing as related to the avionics processor system, and the software required to command, control, monitor, and interact with the SDRs, as well as the other communication payload elements. An extensive effort was required to develop the flight software and meet the NASA requirements for software quality and safety. The flight avionics must be radiation tolerant, and these processors have limited capability in comparison to terrestrial counterparts. A big challenge was that there are three SDRs onboard, and interfacing with multiple SDRs simultaneously complicatesd the effort. The effort also includes ground software, which is a key element for both the command of the payload, and displaying data created by the payload. The verification of

  14. Incidentes en la zona aérea de Canarias y Africa occidental durante la II Guerra Mundial

    Directory of Open Access Journals (Sweden)

    Juan José Díaz Benítez


    Full Text Available La política exterior española durante la II Guerra Mundial empezó a virar hacia la neutralidad con la llegada de Gómez Jordana al Ministerio de Asuntos Exteriores en 1942. Sin embrago, la colaboración con el Eje, aún no concluida, provocó, fuertes presiones por parte de los aliados durante el resto de la guerra y alentó la sospecha de que aún continuaba el abastecimiento clandestino de submarinos alemanes en Canarias. Por ello. los aviones aliados sobrevolaron frecuentemente la Zona Aérea de Canarias y África Occidental entre principios de 1943 y el verano de 1944, provocando la reacción de las baterías de artillería antiaérea españolas e incluso la intervenci6n de los cazas con base en Gando. En ningún momento las fuerzas españolas intentaron derribar a los aviones aliados que atravesaban las aguas territoriales, sino sólo avisarlos para que se retiraran. No obstante, los aviones aliados persistieron, dando lugar a graves incidentes que estuvieron punto de ocasionar una fatalidad. Finalmente, las prolongadas gestiones diplomáticas emprendidas a finales de 1943 acabaron con estos incidentes, los cuales son un ejemplo olvidado de las tensas relaciones entre España y los aliados durante el declive del Eje.Spanish foreign policy through World War II turned to the way of neutrality after Gómez Jordana arrived at the Ministry of Foreign Affaires in 1943.  Howver, the persistent aid to tha Axis rose strong pressures by the Allies for the rest of the war and encouraged them for searching German U-boots at the Canary Islands. So Allied airplanes frequently flew over the Canary Islands and West Africa Aerial Zone between the beginning of 1943 and the summer of 1944, tempting the Spanish anti-aircraft batteries and the fighters based in Gaildo Gando reaction. The Spanish forces never tried to destroy the Allied aircrafts, but baut only warned them to keep away from yje Spanish aerial zone. Nevertheless, Allied planes still went on

  15. Use of Soft Computing Technologies for a Qualitative and Reliable Engine Control System for Propulsion Systems (United States)

    Trevino, Luis; Brown, Terry; Crumbley, R. T. (Technical Monitor)


    The problem to be addressed in this paper is to explore how the use of Soft Computing Technologies (SCT) could be employed to improve overall vehicle system safety, reliability, and rocket engine performance by development of a qualitative and reliable engine control system (QRECS). Specifically, this will be addressed by enhancing rocket engine control using SCT, innovative data mining tools, and sound software engineering practices used in Marshall's Flight Software Group (FSG). The principle goals for addressing the issue of quality are to improve software management, software development time, software maintenance, processor execution, fault tolerance and mitigation, and nonlinear control in power level transitions. The intent is not to discuss any shortcomings of existing engine control methodologies, but to provide alternative design choices for control, implementation, performance, and sustaining engineering, all relative to addressing the issue of reliability. The approaches outlined in this paper will require knowledge in the fields of rocket engine propulsion (system level), software engineering for embedded flight software systems, and soft computing technologies (i.e., neural networks, fuzzy logic, data mining, and Bayesian belief networks); some of which are briefed in this paper. For this effort, the targeted demonstration rocket engine testbed is the MC-1 engine (formerly FASTRAC) which is simulated with hardware and software in the Marshall Avionics & Software Testbed (MAST) laboratory that currently resides at NASA's Marshall Space Flight Center, building 4476, and is managed by the Avionics Department. A brief plan of action for design, development, implementation, and testing a Phase One effort for QRECS is given, along with expected results. Phase One will focus on development of a Smart Start Engine Module and a Mainstage Engine Module for proper engine start and mainstage engine operations. The overall intent is to demonstrate that by

  16. Efficient and Robust Data Collection Using Compact Micro Hardware, Distributed Bus Architectures and Optimizing Software (United States)

    Chau, Savio; Vatan, Farrokh; Randolph, Vincent; Baroth, Edmund C.


    Future In-Space propulsion systems for exploration programs will invariably require data collection from a large number of sensors. Consider the sensors needed for monitoring several vehicle systems states of health, including the collection of structural health data, over a large area. This would include the fuel tanks, habitat structure, and science containment of systems required for Lunar, Mars, or deep space exploration. Such a system would consist of several hundred or even thousands of sensors. Conventional avionics system design will require these sensors to be connected to a few Remote Health Units (RHU), which are connected to robust, micro flight computers through a serial bus. This results in a large mass of cabling and unacceptable weight. This paper first gives a survey of several techniques that may reduce the cabling mass for sensors. These techniques can be categorized into four classes: power line communication, serial sensor buses, compound serial buses, and wireless network. The power line communication approach uses the power line to carry both power and data, so that the conventional data lines can be eliminated. The serial sensor bus approach reduces most of the cabling by connecting all the sensors with a single (or redundant) serial bus. Many standard buses for industrial control and sensor buses can support several hundreds of nodes, however, have not been space qualified. Conventional avionics serial buses such as the Mil-Std-1553B bus and IEEE 1394a are space qualified but can support only a limited number of nodes. The third approach is to combine avionics buses to increase their addressability. The reliability, EMI/EMC, and flight qualification issues of wireless networks have to be addressed. Several wireless networks such as the IEEE 802.11 and Ultra Wide Band are surveyed in this paper. The placement of sensors can also affect cable mass. Excessive sensors increase the number of cables unnecessarily. Insufficient number of sensors

  17. Comparing Interval Management Control Laws for Steady-State Errors and String Stability (United States)

    Weitz, Lesley A.; Swieringa, Kurt A.


    Interval Management (IM) is a future airborne spacing concept that leverages avionics to provide speed guidance to an aircraft to achieve and maintain a specified spacing interval from another aircraft. The design of a speed control law to achieve the spacing goal is a key aspect in the research and development of the IM concept. In this paper, two control laws that are used in much of the contemporary IM research are analyzed and compared to characterize steady-state errors and string stability. Numerical results are used to illustrate how the choice of control laws gains impacts the size of steady-state errors and string performance and the potential trade-offs between those performance characteristics.

  18. Development Status of the Rad-Tolerant TTEthernet Controller (United States)

    Fidi, Christian; van Masar, Ivan


    The use of switched networking technologies for aerospace and more recently automotive brings additional advantages for space applications like the increase in performance of the overall avionics of a spacecraft. These networks are characterized by a central device (switch) and a point-to-point structure between switch and terminal devices that eases electrical and logical insulation.However, for a use in highly-reliable or highly-available applications as in launchers or satellites systems, these network technologies need to provide built-in determinism and redundancy to fulfill the tight latency and jitter requirements of the avionics control loops and the respective hardware redundancy. Therefore a state of the art networking technology already provides these features and allows the modularity and scalability to be used for the different space applications and would allow combining the deterministic avionics with the high speed payload network in a spacecraft [1].Introducing the time-triggered principle to Ethernet allows combining the open industry standard IEE802.3 Ethernet currently use in almost all GSE platforms, with full control of latency and jitter of the time-triggered approach. To allow the time-triggered data flow over Ethernet, a network- wide synchronization time-base has to be established to allow deriving all network events on a globally known time which is typically done in software in almost all spacecrafts. The additional synchronization service of Time-triggered Ethernet has been implemented as additional quality of service (QoS) on layer 2 of the ISO/OSI network model and been standardized in the SAE AS6802 [3].Within a launcher, the communication system ensured the data exchanges between avionic functions during all phases of the launcher lifecycle which is composed of three areas: AIT operations, ground phase and flight phase. To ensure the use of a single network for the different phases, the network needs to support features like the

  19. ACCESS: integration and pre-flight performance (United States)

    Kaiser, Mary Elizabeth; Morris, Matthew J.; Aldoroty, Lauren N.; Pelton, Russell; Kurucz, Robert; Peacock, Grant O.; Hansen, Jason; McCandliss, Stephan R.; Rauscher, Bernard J.; Kimble, Randy A.; Kruk, Jeffrey W.; Wright, Edward L.; Orndorff, Joseph D.; Feldman, Paul D.; Moos, H. Warren; Riess, Adam G.; Gardner, Jonathan P.; Bohlin, Ralph; Deustua, Susana E.; Dixon, W. V.; Sahnow, David J.; Perlmutter, Saul


    Establishing improved spectrophotometric standards is important for a broad range of missions and is relevant to many astrophysical problems. ACCESS, "Absolute Color Calibration Experiment for Standard Stars", is a series of rocket-borne sub-orbital missions and ground-based experiments designed to enable improvements in the precision of the astrophysical flux scale through the transfer of absolute laboratory detector standards from the National Institute of Standards and Technology (NIST) to a network of stellar standards with a calibration accuracy of 1% and a spectral resolving power of 500 across the 0.35 - 1.7μm bandpass. This paper describes the sub-system testing, payload integration, avionics operations, and data transfer for the ACCESS instrument.

  20. Satellite Servicing's Autonomous Rendezvous and Docking Testbed on the International Space Station (United States)

    Naasz, Bo J.; Strube, Matthew; Van Eepoel, John; Barbee, Brent W.; Getzandanner, Kenneth M.


    The Space Servicing Capabilities Project (SSCP) at NASA's Goddard Space Flight Center (GSFC) has been tasked with developing systems for servicing space assets. Starting in 2009, the SSCP completed a study documenting potential customers and the business case for servicing, as well as defining several notional missions and required technologies. In 2010, SSCP moved to the implementation stage by completing several ground demonstrations and commencing development of two International Space Station (ISS) payloads-the Robotic Refueling Mission (RRM) and the Dextre Pointing Package (DPP)--to mitigate new technology risks for a robotic mission to service existing assets in geosynchronous orbit. This paper introduces the DPP, scheduled to fly in July of 2012 on the third operational SpaceX Dragon mission, and its Autonomous Rendezvous and Docking (AR&D) instruments. The combination of sensors and advanced avionics provide valuable on-orbit demonstrations of essential technologies for servicing existing vehicles, both cooperative and non-cooperative.

  1. Efficient implementation of real-time programs under the VAX/VMS operating system (United States)

    Johnson, S. C.


    Techniques for writing efficient real-time programs under the VAX/VMS oprating system are presented. Basic operations are presented for executing at real-time priority and for avoiding needlless processing delays. A highly efficient technique for accessing physical devices by mapping to the input/output space and accessing the device registrs directly is described. To illustrate the application of the technique, examples are included of different uses of the technique on three devices in the Langley Avionics Integration Research Lab (AIRLAB): the KW11-K dual programmable real-time clock, the Parallel Communications Link (PCL11-B) communication system, and the Datacom Synchronization Network. Timing data are included to demonstrate the performance improvements realized with these applications of the technique.

  2. New Trends on MEMS Sensor Technology for Harsh Environment Applications

    Directory of Open Access Journals (Sweden)

    Patricia M. NIEVA


    Full Text Available MEMS and NEMS sensor systems that can operate in the presence of high temperatures, corrosive media, and/or high radiation hold great promise for harsh environment applications. They would reduce weight, improve machine reliability and reduce cost in strategic market sectors such as automotive, avionics, oil well logging, and nuclear power. This paper presents a review of the recent advances in harsh-environment MEMS and NEMS sensors focusing on materials and devices. Special emphasis is put on high-temperature operation. Wide-bandgap semiconductor materials for high temperature applications are discussed from the device point of view. Micro-opto mechanical systems (MOEMS are presented as a new trend for high temperature applications. As an example of a harsh environment MOEMS sensor, a vibration sensor is presented.

  3. Pre-flight physical simulation test of HIMES reentry test vehicle (United States)

    Kawaguchi, Jun'ichiro; Inatani, Yoshifumi; Yonemoto, Koichi; Hosokawa, Shigeru

    ISAS is now developing a small reentry test vehicle, which is 2m long with a 1.5m wing span and weighs about 170 kg, for the purpose of exploring high angle-of-attack aerodynamic attitude control issue in supersonic and hypersonic speed. The flight test, employing 'Rockoon' launch system, is planned as a preliminary design verification for a fully reusable winged rocket named HIMES (Highly Maneuverable Experimental Space) vehicle. This paper describes the results of preflight ground test using a motion table system. This ground system test is called 'physical simulation' aimed at: (1) functional verification of side-jet system, aerodynamic surface actuators, battery and onboard avionics; and (2) guidance and control law evaluation, in total hardware-in-the-loop system. The pressure of side-jet nozzles was measured to provide exact thrust characteristics of reaction control. The dynamics of vehicle motion was calculated in real-time by the ground simulation computer.

  4. Nuclear EMP: stripline test method for measuring transfer impedance

    International Nuclear Information System (INIS)

    Miller, J.S.


    A method for measuring the transfer impedance of flat metal joints for frequencies to 100 MHz has been developed which makes use of striplines. The stripline method, which has similarities to the quadraxial method used for cylindrical components, is described and sets of test results are given. The transfer impedance of a simple joint is modeled as a spurious hyperbolic curve, and a close curve fit to transfer impedance test data from various samples is demonstrated for both the stripline and the quadraxial methods. Validity checks of the test data are discussed using the curve model and other criteria. The method was developed for testing riveted joints which form the avionics bays on B-1s. The joints must provide shielding from EMP currents

  5. High-Payoff Space Transportation Design Approach with a Technology Integration Strategy (United States)

    McCleskey, C. M.; Rhodes, R. E.; Chen, T.; Robinson, J.


    A general architectural design sequence is described to create a highly efficient, operable, and supportable design that achieves an affordable, repeatable, and sustainable transportation function. The paper covers the following aspects of this approach in more detail: (1) vehicle architectural concept considerations (including important strategies for greater reusability); (2) vehicle element propulsion system packaging considerations; (3) vehicle element functional definition; (4) external ground servicing and access considerations; and, (5) simplified guidance, navigation, flight control and avionics communications considerations. Additionally, a technology integration strategy is forwarded that includes: (a) ground and flight test prior to production commitments; (b) parallel stage propellant storage, such as concentric-nested tanks; (c) high thrust, LOX-rich, LOX-cooled first stage earth-to-orbit main engine; (d) non-toxic, day-of-launch-loaded propellants for upper stages and in-space propulsion; (e) electric propulsion and aero stage control.

  6. Laser Spot Center Detection and Comparison Test (United States)

    Zhu, Jun; Xu, Zhengjie; Fu, Deli; Hu, Cong


    High efficiency and precision of the pot center detection are the foundations of avionics instrument navigation and optics measurement basis for many applications. It has noticeable impact on overall system performance. Among them, laser spot detection is very important in the optical measurement technology. In order to improve the low accuracy of the spot center position, the algorithm is improved on the basis of the circle fitting. The pretreatment is used by circle fitting, and the improved adaptive denoising filter for TV repair technology can effectively improves the accuracy of the spot center position. At the same time, the pretreatment and de-noising can effectively reduce the influence of Gaussian white noise, which enhances the anti-jamming capability.

  7. Operations management system (United States)

    Brandli, A. E.; Eckelkamp, R. E.; Kelly, C. M.; Mccandless, W.; Rue, D. L.


    The objective of an operations management system is to provide an orderly and efficient method to operate and maintain aerospace vehicles. Concepts are described for an operations management system and the key technologies are highlighted which will be required if this capability is brought to fruition. Without this automation and decision aiding capability, the growing complexity of avionics will result in an unmanageable workload for the operator, ultimately threatening mission success or survivability of the aircraft or space system. The key technologies include expert system application to operational tasks such as replanning, equipment diagnostics and checkout, global system management, and advanced man machine interfaces. The economical development of operations management systems, which are largely software, will require advancements in other technological areas such as software engineering and computer hardware.

  8. Kitephotography as a tool for land surface observation in the White Volta region


    Nagumo, F.; Thiombiano, L.


    Parmi les diverses méthodes d'observation de la surface du terrain, qui diffèrent selon leur étendue et leur échelle, les photographies aériennes prises à basse altitude sont utiles pour obtenir une information plus détaillée à une échelle large. La photographie aérienne par cerf-volant est une de ces techniques. Cette méthode a deux avantages. Elle coûte moins cher que les autres méthodes comme la photographie par avion télécommandé. Le cerf-volant est facile à fabriquer, à manier, à réparer...

  9. The high speed interconnect system architecture and operation (United States)

    Anderson, Steven C.

    The design and operation of a fiber-optic high-speed interconnect system (HSIS) being developed to meet the requirements of future avionics and flight-control hardware with distributed-system architectures are discussed. The HSIS is intended for 100-Mb/s operation of a local-area network with up to 256 stations. It comprises a bus transmission system (passive star couplers and linear media linked by active elements) and network interface units (NIUs). Each NIU is designed to perform the physical, data link, network, and transport functions defined by the ISO OSI Basic Reference Model (1982 and 1983) and incorporates a fiber-optic transceiver, a high-speed protocol based on the SAE AE-9B linear token-passing data bus (1986), and a specialized application interface unit. The operating modes and capabilities of HSIS are described in detail and illustrated with diagrams.

  10. Controle los mosquitos que están en el exterior (Controlling Mosquitoes Outside)

    Centers for Disease Control (CDC) Podcasts


    Los mosquitos pueden transmitir virus como el del zika. En este podcast, el Sr. Francisco le enseñará a usted y a su vecina Adriana diferentes maneras para ayudar a reducir la cantidad de mosquitos fuera de su casa. Los consejos incluyen eliminar áreas de agua estancada donde los mosquitos ponen sus huevos, usar larvicidas para matar mosquitos jóvenes, y reparar grietas y cubrir las ventilaciones de los pozos sépticos. También aprenderá cómo se usan los aviones que ayudan a rociar insecticida para los mosquitos.  Created: 7/11/2016 by National Center for Emerging and Zoonotic Infectious Diseases (NCEZID).   Date Released: 7/11/2016.

  11. Maximizing commonality between military and general aviation fly-by-light helicopter system designs (United States)

    Enns, Russell; Mossman, David C.


    In the face of shrinking defense budgets, survival of the United States rotorcraft industry is becoming increasingly dependent on increased sales in a highly competitive civil helicopter market. As a result, only the most competitive rotorcraft manufacturers are likely to survive. A key ingredient in improving our competitive position is the ability to produce more versatile, high performance, high quality, and low cost of ownership helicopters. Fiber optic technology offers a path of achieving these objectives. Also, adopting common components and architectures for different helicopter models (while maintaining each models' uniqueness) will further decrease design and production costs. Funds saved (or generated) by exploiting this commonality can be applied to R&D used to further improve the product. In this paper, we define a fiber optics based avionics architecture which provides the pilot a fly-by-light / digital flight control system which can be implemented in both civilian and military helicopters. We then discuss the advantages of such an architecture.

  12. FAILSAFE Health Management for Embedded Systems (United States)

    Horvath, Gregory A.; Wagner, David A.; Wen, Hui Ying; Barry, Matthew


    The FAILSAFE project is developing concepts and prototype implementations for software health management in mission- critical, real-time embedded systems. The project unites features of the industry-standard ARINC 653 Avionics Application Software Standard Interface and JPL s Mission Data System (MDS) technology (see figure). The ARINC 653 standard establishes requirements for the services provided by partitioned, real-time operating systems. The MDS technology provides a state analysis method, canonical architecture, and software framework that facilitates the design and implementation of software-intensive complex systems. The MDS technology has been used to provide the health management function for an ARINC 653 application implementation. In particular, the focus is on showing how this combination enables reasoning about, and recovering from, application software problems.

  13. Spacelab 3 mission (United States)

    Dalton, Bonnie P.


    Spacelab-3 (SL-3) was the first microgravity mission of extended duration involving crew interaction with animal experiments. This interaction involved sharing the Spacelab environmental system, changing animal food, and changing animal waste trays by the crew. Extensive microbial testing was conducted on the animal specimens and crew and on their ground and flight facilities during all phases of the mission to determine the potential for cross contamination. Macroparticulate sampling was attempted but was unsuccessful due to the unforseen particulate contamination occurring during the flight. Particulate debris of varying size (250 micron to several inches) and composition was recovered post flight from the Spacelab floor, end cones, overhead areas, avionics fan filter, cabin fan filters, tunnel adaptor, and from the crew module. These data are discussed along with solutions, which were implemented, for particulate and microbial containment for future flight facilities.

  14. MIL-STD-1553B Marconi LSI chip set in a remote terminal application (United States)

    Dimarino, A.


    Marconi Avionics is utilizing the MIL-STD-1553B LSI Chip Set in the SCADC Air Data Computer application to perform all of the required remote terminal MIL-STD-1553B protocol functions. Basic components of the RTU are the dual redundant chip set, CT3231 Transceivers, 256 x 16 RAM and a Z8002 microprocessor. Basic transfers are to/from the RAM command of the bus controller or Z8002 processor. During transfers from the processor to the RAM, the chip set busy bit is set for a period not exceeding 250 microseconds. When the transfer is complete, the busy bit is released and transfers to the data bus occur on command. The LSI Chip Set word count lines are used to locate each data word in the local memory and 4 mode codes are used in the application: reset remote terminal, transmit status word, transmitter shut-down, and override transmitter shutdown.

  15. NASA Langley Distributed Propulsion VTOL Tilt-Wing Aircraft Testing, Modeling, Simulation, Control, and Flight Test Development (United States)

    Rothhaar, Paul M.; Murphy, Patrick C.; Bacon, Barton J.; Gregory, Irene M.; Grauer, Jared A.; Busan, Ronald C.; Croom, Mark A.


    Control of complex Vertical Take-Off and Landing (VTOL) aircraft traversing from hovering to wing born flight mode and back poses notoriously difficult modeling, simulation, control, and flight-testing challenges. This paper provides an overview of the techniques and advances required to develop the GL-10 tilt-wing, tilt-tail, long endurance, VTOL aircraft control system. The GL-10 prototype's unusual and complex configuration requires application of state-of-the-art techniques and some significant advances in wind tunnel infrastructure automation, efficient Design Of Experiments (DOE) tunnel test techniques, modeling, multi-body equations of motion, multi-body actuator models, simulation, control algorithm design, and flight test avionics, testing, and analysis. The following compendium surveys key disciplines required to develop an effective control system for this challenging vehicle in this on-going effort.

  16. Les Mayas à Hollywood.

    Directory of Open Access Journals (Sweden)

    Boris Jeanne


    Full Text Available Les Mayas de nos jours ce sont surtout des grandes pyramides au milieu de la forêt à un jet d’avion de Cancún : pour nombre de touristes américains et européens, c’est une occasion de s’acoquiner avec la culture, la grande culture des civilisations perdues, en continuant de boire des piña coladas le soir au bord de la plage. Et puis au mois de décembre les Mayas ont débarqué en force dans le paysage culturel local des Américains et des Européens, dans leurs cinémas, au moyen de deux films in...

  17. High-power microwave LDMOS transistors for wireless data transmission technologies (Review)

    International Nuclear Information System (INIS)

    Kuznetsov, E. V.; Shemyakin, A. V.


    The fields of the application, structure, fabrication, and packaging technology of high-power microwave LDMOS transistors and the main advantages of these devices were analyzed. Basic physical parameters and some technology factors were matched for optimum device operation. Solid-state microwave electronics has been actively developed for the last 10-15 years. Simultaneously with improvement of old devices, new devices and structures are actively being adopted and developed and new semiconductor materials are being commercialized. Microwave LDMOS technology is in demand in such fields as avionics, civil and military radars, repeaters, base stations of cellular communication systems, television and broadcasting transmitters, and transceivers for high-speed wireless computer networks (promising Wi-Fi and Wi-Max standards).

  18. A method for predicting errors when interacting with finite state systems. How implicit learning shapes the user's knowledge of a system

    International Nuclear Information System (INIS)

    Javaux, Denis


    This paper describes a method for predicting the errors that may appear when human operators or users interact with systems behaving as finite state systems. The method is a generalization of a method used for predicting errors when interacting with autopilot modes on modern, highly computerized airliners [Proc 17th Digital Avionics Sys Conf (DASC) (1998); Proc 10th Int Symp Aviat Psychol (1999)]. A cognitive model based on spreading activation networks is used for predicting the user's model of the system and its impact on the production of errors. The model strongly posits the importance of implicit learning in user-system interaction and its possible detrimental influence on users' knowledge of the system. An experiment conducted with Airbus Industrie and a major European airline on pilots' knowledge of autopilot behavior on the A340-200/300 confirms the model predictions, and in particular the impact of the frequencies with which specific state transitions and contexts are experienced

  19. A design procedure for a slotted waveguide with probe-fed slots radiating into plasma

    International Nuclear Information System (INIS)

    Colborn, J.A.


    A design procedure is developed for slotted-waveguide antennas with probe-fed slots. Radiation into a gyrotropic, plane-stratified medium is considered, nonzero waveguide wall thickness is assumed, and noncosinusoidal slot fields and arbitrary slot length up to about one free-space wavelength are allowed. External mutual coupling is taken into account by matching the tangential fields at the antenna surface. The particular case of longitudinal slots in the broad face of rectangular guide is analyzed. The motivation for this work is the design of such radiators for plasma heating and current-drive on thermonuclear fusion experiments, but some of the analysis is applicable to the probeless slotted waveguide used for avionics and communications. 20 refs., 5 figs


    Directory of Open Access Journals (Sweden)

    Carlos Giraldo E.


    Full Text Available La tecnología del ultrasonido nace en 1880 con eldesarrollo de los efectos piezoeléctricos. Luego fueaplicada en forma de SONAR (Sound Navigation andRanging durante la segunda guerra mundial para ladetección de barcos, submarinos y aviones de guerra.La emisión de las ondas de ultrasonido se obtiene pormedio de cristales que son sometidos a una corrienteeléctrica logrando que vibren, la recepción de éstasondas se logra cuando retornan de nuevo a los cristalesal chocar con los tejidos. Estos cristales están contenidosen dispositivos llamados transductores o sondasecográficas conectadas a un monitor

  1. Georges et le code secret

    CERN Document Server

    Hawking, Lucy; Parsons, Gary


    À Foxbridge, Georges et Annie s'ennuient, ils rêvent de repartir dans l'espace pour de nouvelles aventures intergalactiques. Pourtant, sur la terre ferme, il se passe des choses étranges... L'argent s'envole des distributeurs de billets, les avions refusent de décoller et les caisses enregistreuses des supermarchés ne fonctionnent plus... Quel chaos ! Il semblerait qu'un bug planétaire ait déréglé tous les systèmes informatiques. S'ils veulent découvrir ce qui se cache derrière tout ça, les deux amis devront voyager plus loin que jamais dans l'espace...

  2. Determining Transmission Loss from Measured External and Internal Acoustic Environments (United States)

    Scogin, Tyler; Smith, A. M.


    An estimate of the internal acoustic environment in each internal cavity of a launch vehicle is needed to ensure survivability of Space Launch System (SLS) avionics. Currently, this is achieved by using the noise reduction database of heritage flight vehicles such as the Space Shuttle and Saturn V for liftoff and ascent flight conditions. Marshall Space Flight Center (MSFC) is conducting a series of transmission loss tests to verify and augment this method. For this test setup, an aluminum orthogrid curved panel representing 1/8th of the circumference of a section of the SLS main structure was mounted in between a reverberation chamber and an anechoic chamber. Transmission loss was measured across the panel using microphones. Data measured during this test will be used to estimate the internal acoustic environments for several of the SLS launch vehicle internal spaces.

  3. Fault Tolerance in ZigBee Wireless Sensor Networks (United States)

    Alena, Richard; Gilstrap, Ray; Baldwin, Jarren; Stone, Thom; Wilson, Pete


    Wireless sensor networks (WSN) based on the IEEE 802.15.4 Personal Area Network standard are finding increasing use in the home automation and emerging smart energy markets. The network and application layers, based on the ZigBee 2007 PRO Standard, provide a convenient framework for component-based software that supports customer solutions from multiple vendors. This technology is supported by System-on-a-Chip solutions, resulting in extremely small and low-power nodes. The Wireless Connections in Space Project addresses the aerospace flight domain for both flight-critical and non-critical avionics. WSNs provide the inherent fault tolerance required for aerospace applications utilizing such technology. The team from Ames Research Center has developed techniques for assessing the fault tolerance of ZigBee WSNs challenged by radio frequency (RF) interference or WSN node failure.

  4. Voltage Stress on Y Capacitors from Indirect Lightning Pulses According to ED-14/DO-160 (United States)

    Meier, F.


    Transients due to lightning strikes on an aircraft's fuselage impose stress on the input filters of elec- tronic equipment. Permanent damage can occur when exceeding the voltage handling capacity of filter components causing a short circuit to ground. In ED-14/DO-160, section 22, a number of waveforms and levels are defined which are used to check the airworthiness of avionics equipment. Depending on pro- cedure and level, Y-capacitors are stressed by transient voltages which exceed their dielectric strength. The design engineer's task is a properly select the type and voltage rating of capacitors. With moderate simplifications, a LCR-series network is justified to calculate the peak voltage dependent on the capacitance.

  5. Copilot: Monitoring Embedded Systems (United States)

    Pike, Lee; Wegmann, Nis; Niller, Sebastian; Goodloe, Alwyn


    Runtime verification (RV) is a natural fit for ultra-critical systems, where correctness is imperative. In ultra-critical systems, even if the software is fault-free, because of the inherent unreliability of commodity hardware and the adversity of operational environments, processing units (and their hosted software) are replicated, and fault-tolerant algorithms are used to compare the outputs. We investigate both software monitoring in distributed fault-tolerant systems, as well as implementing fault-tolerance mechanisms using RV techniques. We describe the Copilot language and compiler, specifically designed for generating monitors for distributed, hard real-time systems. We also describe two case-studies in which we generated Copilot monitors in avionics systems.

  6. Romagnat – Bois des Goules


    Leguet, Daniel


    Lien Atlas (MCC) :;45.698;3.133;45.745 La parcelle prospectée se situe sur le flanc nord du col des Goules, passage traditionnel vers l’oppidum de Gergovie, dans un profond thalweg emprunté jadis par un chemin descendant sur Romagnat. Sur la pente actuelle entièrement boisée, on trouve des sentiers récents et des pistes de motocross. C’est sur l’une de ces dernières que nous avions recueilli un poids ...

  7. Understanding and Using the Controller Area Network Communication Protocol Theory and Practice

    CERN Document Server

    Di Natale, Marco; Giusto, Paolo; Ghosal, Arkadeb


    This is the first book to offer a hands-on guide to designing, analyzing and debugging a communication infrastructure based on the Controller Area Network (CAN) bus.  Although the CAN bus standard is well established and currently used in most automotive systems, as well as avionics, medical systems and other devices, its features are not fully understood by most developers, who tend to misuse the network. This results in lost opportunities for better efficiency and performance.   This book offers a comprehensive range of architectural solutions and domains of analysis. It also provides formal models and analytical results, with thorough discussion of their applicability, so that it serves as an invaluable reference for researchers and students, as well as practicing engineers.    Offers the first comprehensive guide to bridging the gap between theory and implementation of the widely accepted Controller Area Network (CAN) bus; Provides examples and best practices for design of communication systems, as w...

  8. Vibration measurement on composite material with embedded optical fiber based on phase-OTDR (United States)

    Franciscangelis, C.; Margulis, W.; Floridia, C.; Rosolem, J. B.; Salgado, F. C.; Nyman, T.; Petersson, M.; Hallander, P.; Hällstrom, S.; Söderquist, I.; Fruett, F.


    Distributed sensors based on phase-optical time-domain reflectometry (phase-OTDR) are suitable for aircraft health monitoring due to electromagnetic interference immunity, small dimensions, low weight and flexibility. These features allow the fiber embedment into aircraft structures in a nearly non-intrusive way to measure vibrations along its length. The capability of measuring vibrations on avionics structures is of interest for what concerns the study of material fatigue or the occurrence of undesirable phenomena like flutter. In this work, we employed the phase-OTDR technique to measure vibrations ranging from some dozens of Hz to kHz in two layers of composite material board with embedded polyimide coating 0.24 numerical aperture single-mode optical fiber.

  9. Hardware Testing for the Optical PAyload for Lasercomm Science (OPALS) (United States)

    Slagle, Amanda


    Hardware for several subsystems of the proposed Optical PAyload for Lasercomm Science (OPALS), including the gimbal and avionics, was tested. Microswitches installed on the gimbal were evaluated to verify that their point of actuation would remain within the acceptable range even if the switches themselves move slightly during launch. An inspection of the power board was conducted to ensure that all power and ground signals were isolated, that polarized components were correctly oriented, and that all components were intact and securely soldered. Initial testing on the power board revealed several minor problems, but once they were fixed the power board was shown to function correctly. All tests and inspections were documented for future use in verifying launch requirements.

  10. Signal and image processing systems performance evaluation, simulation, and modeling; Proceedings of the Meeting, Orlando, FL, Apr. 4, 5, 1991 (United States)

    Nasr, Hatem N.; Bazakos, Michael E.

    The various aspects of the evaluation and modeling problems in algorithms, sensors, and systems are addressed. Consideration is given to a generic modular imaging IR signal processor, real-time architecture based on the image-processing module family, application of the Proto Ware simulation testbed to the design and evaluation of advanced avionics, development of a fire-and-forget imaging infrared seeker missile simulation, an adaptive morphological filter for image processing, laboratory development of a nonlinear optical tracking filter, a dynamic end-to-end model testbed for IR detection algorithms, wind tunnel model aircraft attitude and motion analysis, an information-theoretic approach to optimal quantization, parametric analysis of target/decoy performance, neural networks for automated target recognition parameters adaptation, performance evaluation of a texture-based segmentation algorithm, evaluation of image tracker algorithms, and multisensor fusion methodologies. (No individual items are abstracted in this volume)

  11. Procedimiento y sistema de detección de la activación de la reversa en el aterrizaje de una aeronave


    Asensio Rivera, César; Ruiz González, Mariano; Arcas Castro, Guillermo de; Recuero López, Manuel; López Navarro, Juan Manuel


    La invención consiste en un sistema de captación sonoro que es capaz de detectar la activación de la reversa durante el aterrizaje de los aviones a partir de la detección e identificación de los sonidos producidos en el proceso. Así mismo, la invención incluye el procedimiento que debe seguirse con respecto a la ubicación de los sensores. La invención dotará a los aeropuertos de una herramienta con la que velar por el cumplimento de las normativas referidas a la activación de la reversa en ma...

  12. Compilation and synthesis for embedded reconfigurable systems an aspect-oriented approach

    CERN Document Server

    Diniz, Pedro; Coutinho, José; Petrov, Zlatko


    This book provides techniques to tackle the design challenges raised by the increasing diversity and complexity of emerging, heterogeneous architectures for embedded systems. It describes an approach based on techniques from software engineering called aspect-oriented programming, which allow designers to control today’s sophisticated design tool chains, while maintaining a single application source code.  Readers are introduced to the basic concepts of an aspect-oriented, domain specific language that enables control of a wide range of compilation and synthesis tools in the partitioning and mapping of an application to a heterogeneous (and possibly multi-core) target architecture.  Several examples are presented that illustrate the benefits of the approach developed for applications from avionics and digital signal processing. Using the aspect-oriented programming techniques presented in this book, developers can reuse extensive sections of their designs, while preserving the original application source-...

  13. COLUMBUS as Engineering Testbed for Communications and Multimedia Equipment (United States)

    Bank, C.; Anspach von Broecker, G. O.; Kolloge, H.-G.; Richters, M.; Rauer, D.; Urban, G.; Canovai, G.; Oesterle, E.


    The paper presents ongoing activities to prepare COLUMBUS for communications and multimedia technology experiments. For this purpose, Astrium SI, Bremen, has studied several options how to best combine the given system architecture with flexible and state-of-the-art interface avionics and software. These activities have been conducted in coordination with, and partially under contract of, DLR and ESA/ESTEC. Moreover, Astrium SI has realized three testbeds for multimedia software and hardware testing under own funding. The experimental core avionics unit - about a half double rack - establishes the core of a new multi-user experiment facility for this type of investigation onboard COLUMBUS, which shall be available to all users of COLUMBUS. It allows for the connection of 2nd generation payload, that is payload requiring broadband data transfer and near-real-time access by the Principal Investigator on ground, to test highly interactive and near-realtime payload operation. The facility is also foreseen to test new equipment to provide the astronauts onboard the ISS/COLUMBUS with bi- directional hi-fi voice and video connectivity to ground, private voice coms and e-mail, and a multimedia workstation for ops training and recreation. Connection to an appropriate Wide Area Network (WAN) on Earth is possible. The facility will include a broadband data transmission front-end terminal, which is mounted externally on the COLUMBUS module. This Equipment provides high flexibility due to the complete transparent transmit and receive chains, the steerable multi-frequency antenna system and its own thermal and power control and distribution. The Equipment is monitored and controlled via the COLUMBUS internal facility. It combines several new hardware items, which are newly developed for the next generation of broadband communication satellites and operates in Ka -Band with the experimental ESA data relay satellite ARTEMIS. The equipment is also TDRSS compatible; the open loop

  14. Use of In-Flight Data to Validate Mars Samle Return Autonomous RvD GNC

    DEFF Research Database (Denmark)

    Barrena, V.; Colmenarejo, P.; Suatoni, M.

    D is based on RF, camera and LIDAR measurements. It includes design, prototyping and verification at three different levels: algorithms design and verification in a Functional Engineering Simulator, SW demonstrator verified in Real Time Avionics Test Benching and Dynamic Test Benching. Moreover...... and testing of a vision based optical stimulator (ViSOS by DTU) to enhance the on-ground validation capabilities. After checking different alternatives for the proposed HARvD-GNC experiment with PRISMA resources, an efficient but cost-effective approach was chosen. The approach is based on designing MSR......-like dedicated manoeuvres sequencing using the already existing on-board PRISMA GNC/AOCS system (based on relative GPS measurements for the closed-loop execution of the manoeuvres sequencing and acquiring RF and camera images as part of the HARvD-GNC experiment data). This option allows downloading the sensor...

  15. Latte-Abdallah Stéphanie, Images aux frontières, Représentations et constructions sociales et politiques, Palestine, Jordanie 1948-2000, Publications de l’IFPO, 2005, 369 p.

    Directory of Open Access Journals (Sweden)

    Véronique Bontemps


    Full Text Available Le traitement médiatique du 11 septembre 2001, et les images, diffusées en boucle sur les chaînes de télévision, des avions s’écrasant sur les Twin Towers ont tragiquement confirmé l’immense pouvoir des images sur notre appréhension de la réalité sociale. L’ouvrage Images aux frontières s’inscrit dans cette interrogation. Il regroupe des articles de sociologues, anthropologues, historiens et politologues autour de la notion « d’image » dans la construction des identités collectives en Palesti...

  16. Deep space test bed for radiation studies

    International Nuclear Information System (INIS)

    Adams, James H.; Adcock, Leonard; Apple, Jeffery; Christl, Mark; Cleveand, William; Cox, Mark; Dietz, Kurt; Ferguson, Cynthia; Fountain, Walt; Ghita, Bogdan; Kuznetsov, Evgeny; Milton, Martha; Myers, Jeremy; O'Brien, Sue; Seaquist, Jim; Smith, Edward A.; Smith, Guy; Warden, Lance; Watts, John


    The Deep Space Test-Bed (DSTB) Facility is designed to investigate the effects of galactic cosmic rays on crews and systems during missions to the Moon or Mars. To gain access to the interplanetary ionizing radiation environment the DSTB uses high-altitude polar balloon flights. The DSTB provides a platform for measurements to validate the radiation transport codes that are used by NASA to calculate the radiation environment within crewed space systems. It is also designed to support other exploration related investigations such as measuring the shielding effectiveness of candidate spacecraft and habitat materials, testing new radiation monitoring instrumentation, flight avionics and investigating the biological effects of deep space radiation. We describe the work completed thus far in the development of the DSTB and its current status

  17. Entry Descent and Landing Workshop Proceedings. Volume 1; Commercial Sources for EDL Flight Tests (United States)

    Trombetta, Nick; Horan, Steve


    Commercial Off The Shelf is defined as a Federal Acquisition Regulation (FAR) term for commercial items, including services, available in the commercial marketplace that can be bought and used under government contracts. A need for COTS exists to help in reducing avionics cost associated with applicable missions. In a 2014 a Planetary Science Decadal Survey it was stated that it is imperative that NASA expand its investment in fundamental technology areas. Reduced mass and power requirements for spacecraft and their subsystems. New and improved sensors, instruments, and sampling systems; and Mission and trajectory design and optimization Two goals were written as part of the technology investment: 1. Reducing the cost of planetary missions 2. Improving their scientific capability and reliability...." COTS could certainty aid in reducing cost associated with the instrumentation systems.

  18. Human-in-the-Loop Assessment of Alternative Clearances in Interval Management Arrival Operations (United States)

    Baxley, Brian T.; Wilson, Sara R.; Swieringa, Kurt A.; Johnson, William C.; Roper, Roy D.; Hubbs, Clay E.; Goess, Paul A.; Shay, Richard F.


    Interval Management Alternative Clearances (IMAC) was a human-in-the-loop simulation experiment conducted to explore the Air Traffic Management (ATM) Technology Demonstration (ATD-1) Concept of Operations (ConOps), which combines advanced arrival scheduling, controller decision support tools, and aircraft avionics to enable multiple time deconflicted, efficient arrival streams into a high-density terminal airspace. Interval Management (IM) is designed to support the ATD-1 concept by having an "Ownship" (IM-capable) aircraft achieve or maintain a specific time or distance behind a "Target" (preceding) aircraft. The IM software uses IM clearance information and the Ownship data (route of flight, current location, and wind) entered by the flight crew, and the Target aircraft's Automatic Dependent Surveillance-Broadcast state data, to calculate the airspeed necessary for the IM-equipped aircraft to achieve or maintain the assigned spacing goal.

  19. Initial Investigations of Controller Tools and Procedures for Schedule-Based Arrival Operations with Mixed Flight-Deck Interval Management Equipage (United States)

    Callantine, Todd J.; Cabrall, Christopher; Kupfer, Michael; Omar, Faisal G.; Prevot, Thomas


    NASA?s Air Traffic Management Demonstration-1 (ATD-1) is a multi-year effort to demonstrate high-throughput, fuel-efficient arrivals at a major U.S. airport using NASA-developed scheduling automation, controller decision-support tools, and ADS-B-enabled Flight-Deck Interval Management (FIM) avionics. First-year accomplishments include the development of a concept of operations for managing scheduled arrivals flying Optimized Profile Descents with equipped aircraft conducting FIM operations, and the integration of laboratory prototypes of the core ATD-1 technologies. Following each integration phase, a human-in-the-loop simulation was conducted to evaluate and refine controller tools, procedures, and clearance phraseology. From a ground-side perspective, the results indicate the concept is viable and the operations are safe and acceptable. Additional training is required for smooth operations that yield notable benefits, particularly in the areas of FIM operations and clearance phraseology.

  20. Éditorial Editorial


    Jacques Maurice


    Ainsi que nous l’avions annoncé dans le précédent numéro, cette cinquième livraison des Cahiers propose deux études sur le Bicentenaire de la Guerre d’Indépendance.L’une, reprise des Mélanges de la Casa de Velázquez, analyse le processus révolutionnaire que vécut l’Espagne entre 1808 et 1814 et les différentes interprétations qui en ont été données. Cette étude est complétée par une lecture critique extrêmement fouillée d’un classique de l’historiographie libérale, la Historia del levantamien...