Sample records for avionics

  1. Avionics Systems

    Directory of Open Access Journals (Sweden)

    P.M. Soundar Rajan


    Full Text Available ‘Avionics’ systems, over the decades, have grown from simple communication radios and navigation equipments to complex integrated equipments primarily infiuenced by dominance of digital technology. Continuous growth in integrated circuit technology, functional integration of complete system on chip, very high speed communication channels and fault tolerant communication protocols have brought remarkable advancements in avionics systems. Further Mechanical and Pneumatic functional blocks are being replaced by digital systems progressively and decisively. New generation aircraft are being built around powerful avionics assets to provide stress free cockpit to the pilot.Defence Science Journal, 2013, 63(2, pp.129-130, DOI:

  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; Wallace, Shawn


    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. Flight Avionics Hardware Roadmap (United States)

    Some, Raphael; Goforth, Monte; Chen, Yuan; Powell, Wes; Paulick, Paul; Vitalpur, Sharada; Buscher, Deborah; Wade, Ray; West, John; Redifer, Matt; Partridge, Harry; Sherman, Aaron; McCabe, Mary


    The Avionics Technology Roadmap takes an 80% approach to technology investment in spacecraft avionics. It delineates a suite of technologies covering foundational, component, and subsystem-levels, which directly support 80% of future NASA space mission needs. The roadmap eschews high cost, limited utility technologies in favor of lower cost, and broadly applicable technologies with high return on investment. The roadmap is also phased to support future NASA mission needs and desires, with a view towards creating an optimized investment portfolio that matures specific, high impact technologies on a schedule that matches optimum insertion points of these technologies into NASA missions. The roadmap looks out over 15+ years and covers some 114 technologies, 58 of which are targeted for TRL6 within 5 years, with 23 additional technologies to be at TRL6 by 2020. Of that number, only a few are recommended for near term investment: 1. Rad Hard High Performance Computing 2. Extreme temperature capable electronics and packaging 3. RFID/SAW-based spacecraft sensors and instruments 4. Lightweight, low power 2D displays suitable for crewed missions 5. Radiation tolerant Graphics Processing Unit to drive crew displays 6. Distributed/reconfigurable, extreme temperature and radiation tolerant, spacecraft sensor controller and sensor modules 7. Spacecraft to spacecraft, long link data communication protocols 8. High performance and extreme temperature capable C&DH subsystem In addition, the roadmap team recommends several other activities that it believes are necessary to advance avionics technology across NASA: center dot Engage the OCT roadmap teams to coordinate avionics technology advances and infusion into these roadmaps and their mission set center dot Charter a team to develop a set of use cases for future avionics capabilities in order to decouple this roadmap from specific missions center dot Partner with the Software Steering Committee to coordinate computing hardware

  4. Avionics Architecture for Exploration Project (United States)

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

  5. Perspectives of civil aircraft avionics development


    Наумов, А. В.


    Considered are main directions for civil avionics development. General requirements for airborne equipment functions. Analysis of airborne avionics selection per architecture and economical effectiveness in made. Proposed is the necessity of new approach to integrated avionics complex design, first of all, on basis of mathematical method for aircraft equipment and technical characteristics definition

  6. Security audit for embedded avionics systems (United States)

    Rao, K. N.

    The design of security audit subsystems for real-time embedded avionics systems is described. The selection criteria of auditable events and the design of the audit functions are described. The data storage requirements and the data compression features of embedded avionics systems are analyzed. Two data compression algorithms applicable to avionics systems are described. Huffman encoding is optimal, but Fibonacci encoding is shown to be nearly optimal and better suited for airborne avionics systems. The memory capacity needed for audit data storage is computed for typical avionics missions.

  7. EVA Communications Avionics and Informatics (United States)

    Carek, David Andrew


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

  8. 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.

  9. 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.

  10. 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.

  11. Thermal Defects of Avionic Turbojet Engines

    Directory of Open Access Journals (Sweden)

    Szczepankowski Andrzej


    Full Text Available The paper analyzes the most frequent reasons associated with operation of avionic turbojet engines (ATE and leading to initiation of thermal defects affecting turbine units. These reasons are illustrated with examples of gradual deteriorations revealed on surfaces of turbine parts and subassemblies and defected during endoscopic examinations of propelling drives. Attention is paid to various design and technological improvements that are implemented to counteract such deteriorations. The analysis is focused on mistakes that are committed during operation, repairs or manufacturing of avionic turbojet engines and that may affect safety of aircraft operations.

  12. Prognostics for Electronics Components of Avionics Systems (United States)

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


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

  13. Agility in the avionics software world


    Wils, Andrew; Van Baelen, Stefan; Holvoet, Tom; De Vlaminck, Karel


    This paper(1) takes a look at how XP and other agile practices can improve a software process for the development of avionics software. Developers of mission critical airborne software are heavily constrained by the RTCA DO-178B regulations [8]. These regulations impose strict rules regarding traceability and documentation that make it extremely hard to employ an iterative software development process. In particular, the extra validation overhead increases the time spent on small iteration cy...

  14. 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).

  15. Rotorcraft digital advanced avionics system (RODAAS) functional description (United States)

    Peterson, E. M.; Bailey, J.; Mcmanus, T. J.


    A functional design of a rotorcraft digital advanced avionics system (RODAAS) to transfer the technology developed for general aviation in the Demonstration Advanced Avionics System (DAAS) program to rotorcraft operation was undertaken. The objective was to develop an integrated avionics system design that enhances rotorcraft single pilot IFR operations without increasing the required pilot training/experience by exploiting advanced technology in computers, busing, displays and integrated systems design. A key element of the avionics system is the functionally distributed architecture that has the potential for high reliability with low weight, power and cost. A functional description of the RODAAS hardware and software functions is presented.

  16. Bidirectional link mock-up for avionics applications


    Rissons, Angélique; Ly, Khadijetou; Mollier, Jean-Claude; Pez, Mathias; Gambardella, Eddie


    Copper-based networks have been extensively employed on aircraft to ensure the avionics data-communications. Since the Airbus A380 development, Avionic Data Communication Network (ADCN) has been implemented to ensure transmissions between avionic equipment. This system is based on the Avionic Full Duplex Ethernet (AFDX), and transfers data at rates up to 100 Mb/s. The need of faster communications systems, up to 1Gb/s, has led to great interest in fiber optic based networks. Beyond higher dat...

  17. An Automatic Development Process for Integrated Modular Avionics Software

    Directory of Open Access Journals (Sweden)

    Ying Wang


    Full Text Available With the ever-growing avionics functions, the modern avionics architecture is evolving from traditional federated architecture to Integrated Modular Avionics (IMA. ARINC653 is a major industry standard to support partitioning concept introduced in IMA to achieve security isolation between avionics functions with different criticalities. To decrease the complexity and improve the reliability of the design and implementation of IMA-based avionics software, this paper proposes an automatic development process based on Architecture Analysis & Design Language. An automatic model transformation approach from domain-specific models to platform-specific ARINC653 models and safety-critical ARINC653-compliant code generation technology are respectively presented during this process. A simplified multi-task flight application as a case study with preliminary experiment result is given to show the validity of this process.

  18. Evolution of the Space Shuttle Primary Avionics Software and Avionics for Shuttle Derived Launch Vehicles (United States)

    Ferguson, Roscoe C.


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

  19. Avionics electromagnetic interference immunity and environment (United States)

    Clarke, C. A.


    Aircraft electromagnetic spectrum and radio frequency (RF) field strengths are charted, profiling the higher levels of electromagnetic voltages encountered by the commercial aircraft wiring. Selected military, urban, and rural electromagnetic field levels are plotted and provide a comparison of radiation amplitudes. Low frequency magnetic fields and electric fields from 400 H(Z) power systems are charted versus frequency and wire separation to indicate induced voltages on adjacent or neighboring circuits. Induced EMI levels and attenuation characteristics of electric, magnetic, RF fields, and transients are plotted and graphed for common types of wire circuits. The significance of wire circuit returns and shielding is emphasized to highlight the techniques that help block the paths of electromagnetic interference and maintain avionic interface signal quality.

  20. Platform Independent Launch Vehicle Avionics with GPS Metric Tracking Project (United States)

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

  1. Affordable Access to Space (AAS): Affordable Vehicle Avionics Project (United States)

    National Aeronautics and Space Administration — Affordable Vehicle Avionics (AVA) is being developed at NASA Ames Research Center and is sponsored by Space Technology Mission Directorate (STMD) Game Changing...

  2. A General Method for Module Automatic Testing in Avionics Systems

    Directory of Open Access Journals (Sweden)

    Li Ma


    Full Text Available The traditional Automatic Test Equipment (ATE systems are insufficient to cope with the challenges of testing more and more complex avionics systems. In this study, we propose a general method for module automatic testing in the avionics test platform based on PXI bus. We apply virtual instrument technology to realize the automatic testing and the fault reporting of signal performance. Taking the avionics bus ARINC429 as an example, we introduce the architecture of automatic test system as well as the implementation of algorithms in Lab VIEW. The comprehensive experiments show the proposed method can effectively accomplish the automatic testing and fault reporting of signal performance. It greatly improves the generality and reliability of ATE in avionics systems.

  3. 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...

  4. System Engineering Issues for Avionics Survival in the Space Environment (United States)

    Pavelitz, Steven


    This paper examines how the system engineering process influences the design of a spacecraft's avionics by considering the space environment. Avionics are susceptible to the thermal, radiation, plasma, and meteoroids/orbital debris environments. The environment definitions for various spacecraft mission orbits (LEO/low inclination, LEO/Polar, MEO, HEO, GTO, GEO and High ApogeeElliptical) are discussed. NASA models and commercial software used for environment analysis are reviewed. Applicability of technical references, such as NASA TM-4527 "Natural Orbital Environment Guidelines for Use in Aerospace Vehicle Development" is discussed. System engineering references, such as the MSFC System Engineering Handbook, are reviewed to determine how the environments are accounted for in the system engineering process. Tools and databases to assist the system engineer and avionics designer in addressing space environment effects on avionics are described and usefulness assessed.

  5. Wireless avionics for space applications of fundamental physics (United States)

    Wang, Linna; Zeng, Guiming


    Fundamental physics (FP) research in space relies on a strong support of spacecraft. New types of spacecraft including reusable launch vehicles, reentry space vehicles, long-term on-orbit spacecraft or other new type of spacecraft will pave the way for FP missions. In order to test FP theories in space, flight conditions have to be controlled to a very high precision, data collection and handling abilities have to be improved, real-time and reliable communications in critical environments are needed. These challenge the existing avionics of spacecraft. Avionics consists of guidance, navigation & control, TT&C, the vehicle management, etc. Wireless avionics is one of the enabling technologies to address the challenges. Reasons are expatiated of why it is of great advantage. This paper analyses the demands for wireless avionics by reviewing the FP missions and on-board wireless systems worldwide. Main types of wireless communication are presented. Preliminary system structure of wireless avionics are given. The characteristics of wireless network protocols and wireless sensors are introduced. Key technologies and design considerations for wireless avionics in space applications are discussed.

  6. ExoMars 2018 Avionic Architecture (United States)

    Caramia, Maurizio; Musetti, Bruno; Zekry, Eric


    , and a Rover in the vicinity of Mars. The Descent Module will bring the Landing Platform and the Rover to the surface of Mars. After the Rover has egressed from the landing platform, both the Rover and the Platform will start with their dedicated technology and scientific objectives. This mission is designed and "built" in a very tight cooperation between ROSCOSMOS and ESA. Each of the Agencies bringing their know-how and expertise in Space Systems and Planetary Exploration. ROSCOSMOS will supply the Proton-M/Breeze-M launcher, the Descent Module and part of its avionics, and the Landing Platform while ESA will lead the mission, and provide the Carrier, part of the avionics for the DM, and the Rover. This paper describes the Avionic architectural solutions adopted to meet the 2018 mission requirements.

  7. Electronic/electric technology benefits study. [avionics (United States)

    Howison, W. W.; Cronin, M. J.


    The benefits and payoffs of advanced electronic/electric technologies were investigated for three types of aircraft. The technologies, evaluated in each of the three airplanes, included advanced flight controls, advanced secondary power, advanced avionic complements, new cockpit displays, and advanced air traffic control techniques. For the advanced flight controls, the near term considered relaxed static stability (RSS) with mechanical backup. The far term considered an advanced fly by wire system for a longitudinally unstable airplane. In the case of the secondary power systems, trades were made in two steps: in the near term, engine bleed was eliminated; in the far term bleed air, air plus hydraulics were eliminated. Using three commercial aircraft, in the 150, 350, and 700 passenger range, the technology value and pay-offs were quantified, with emphasis on the fiscal benefits. Weight reductions deriving from fuel saving and other system improvements were identified and the weight savings were cycled for their impact on TOGW (takeoff gross weight) and upon the performance of the airframes/engines. Maintenance, reliability, and logistic support were the other criteria.

  8. 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.

  9. 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.

  10. HLLV avionics requirements study and electronic filing system database development (United States)


    This final report provides a summary of achievements and activities performed under Contract NAS8-39215. The contract's objective was to explore a new way of delivering, storing, accessing, and archiving study products and information and to define top level system requirements for Heavy Lift Launch Vehicle (HLLV) avionics that incorporate Vehicle Health Management (VHM). This report includes technical objectives, methods, assumptions, recommendations, sample data, and issues as specified by DPD No. 772, DR-3. The report is organized into two major subsections, one specific to each of the two tasks defined in the Statement of Work: the Index Database Task and the HLLV Avionics Requirements Task. The Index Database Task resulted in the selection and modification of a commercial database software tool to contain the data developed during the HLLV Avionics Requirements Task. All summary information is addressed within each task's section.

  11. Time Triggered Protocol (TTP) for Integration Modular Avionics (IMA) (United States)

    Gwaltney, David A.; Bauer, Guenther; Jakovljevic, Mirko; Gagea,Leonard; Motzet, Guenter


    This viewgraph presentation is a review of the Time Triggered Protocol, designed to work with NASA's Integrated Safety-Critical Advanced Avionics Communication and Control (ISAACC) system. ISAACC is the product of the Propulsion High-Impact Avionics Technologies (PHIAT) project at NASA Marshall Space Flight Center (MSFC) during FY03 to the end of FY05. The goal is an avionics architecture suitable for control and monitoring of safety critical systems of manned spacecraft. It must be scalable to allow its use in robotic vehicles or launch pad and propulsion test stand monitoring and control systems. The developed IMA should have: a common power supply and rugged chassis for a set of modules, many upgradeable software functions on one module (i.e. processing unit Reduced weight, straightforward update and system integration. It is also important that it have Partitioning and a Memory Management Unit (MMU)

  12. Advanced Avionics and Processor Systems for Space and Lunar Exploration (United States)

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


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

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

    DEFF Research Database (Denmark)

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


    Avionics applications need to be certified for the highest criticality standard. This certification includes schedulability analysis and worst-case execution time (WCET) analysis. WCET analysis is only possible when the software is written to be WCET analyzable and when the platform is time-predi...

  14. 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

  15. Time Triggered Protocol (TTP) for Integrated Modular Avionics (United States)

    Motzet, Guenter; Gwaltney, David A.; Bauer, Guenther; Jakovljevic, Mirko; Gagea, Leonard


    Traditional avionics computing systems are federated, with each system provided on a number of dedicated hardware units. Federated applications are physically separated from one another and analysis of the systems is undertaken individually. Integrated Modular Avionics (IMA) takes these federated functions and integrates them on a common computing platform in a tightly deterministic distributed real-time network of computing modules in which the different applications can run. IMA supports different levels of criticality in the same computing resource and provides a platform for implementation of fault tolerance through hardware and application redundancy. Modular implementation has distinct benefits in design, testing and system maintainability. This paper covers the requirements for fault tolerant bus systems used to provide reliable communication between IMA computing modules. An overview of the Time Triggered Protocol (TTP) specification and implementation as a reliable solution for IMA systems is presented. Application examples in aircraft avionics and a development system for future space application are covered. The commercially available TTP controller can be also be implemented in an FPGA and the results from implementation studies are covered. Finally future direction for the application of TTP and related development activities are presented.

  16. Transmission of RF Signals Over Optical Fiber for Avionics Applications (United States)

    Slaveski, Filip; Sluss, James, Jr.; Atiquzzaman, Mohammed; Hung, Nguyen; Ngo, Duc


    During flight, aircraft avionics transmit and receive RF signals to/from antennas over coaxial cables. As the density and complexity of onboard avionics increases, the electromagnetic interference (EM) environment degrades proportionately, leading to decreasing signal-to-noise ratios (SNRs) and potential safety concerns. The coaxial cables are inherently lossy, limiting the RF signal bandwidth while adding considerable weight. To overcome these limitations, we have investigated a fiber optic communications link for aircraft that utilizes wavelength division multiplexing (WDM) to support the simultaneous transmission of multiple signals (including RF) over a single optical fiber. Optical fiber has many advantages over coaxial cable, particularly lower loss, greater bandwidth, and immunity to EM. In this paper, we demonstrate that WDM can be successfully used to transmit multiple RF signals over a single optical fiber with no appreciable signal degradation. We investigate the transmission of FM and AM analog modulated signals, as well as FSK digital modulated signals, over a fiber optic link (FOL) employing WDM. We present measurements of power loss, delay, SNR, carrier-to-noise ratio (CNR), total harmonic distortion (THD), and bit error rate (BER). Our experimental results indicate that WDM is a fiber optic technology suitable for avionics applications.

  17. Intelligent Cost Modeling Based on Soft Computing for Avionics Systems

    Institute of Scientific and Technical Information of China (English)

    ZHU Li-li; LI Zhuang-sheng; XU Zong-ze


    In parametric cost estimating, objections to using statistical Cost Estimating Relationships (CERs) and parametric models include problems of low statistical significance due to limited data points, biases in the underlying data, and lack of robustness. Soft Computing (SC) technologies are used for building intelligent cost models. The SC models are systemically evaluated based on their training and prediction of the historical cost data of airborne avionics systems. Results indicating the strengths and weakness of each model are presented. In general, the intelligent cost models have higher prediction precision, better data adaptability, and stronger self-learning capability than the regression CERs.

  18. Credit Determination of Fibre Channel in Avionics Environment

    Institute of Scientific and Technical Information of China (English)


    Fibre channel (FC) is the main candidate architecture for "unified network". Flow control deals with the problem in which a device receives frames faster than it can process them. Credit is an important service parameter for fibre channel flow control. Configuring the credit reasonably can avoid buffer overflow in nodes. This paper derives the mathematic relationships among credit, bandwidth and message sets under real-time condition according as three main topologies of fibre channel, and proposes the credit determination and the optimal credit for typical message sets. This study is based on the features of hard real-time communications in avionics environment.

  19. 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.

  20. 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.

  1. Flight Avionics Sequencing Telemetry (FAST) DIV Latching Display (United States)

    Moore, Charlotte


    The NASA Engineering (NE) Directorate at Kennedy Space Center provides engineering services to major programs such as: Space Shuttle, Inter national Space Station, and the Launch Services Program (LSP). The Av ionics Division within NE, provides avionics and flight control syste ms engineering support to LSP. The Launch Services Program is respons ible for procuring safe and reliable services for transporting critical, one of a kind, NASA payloads into orbit. As a result, engineers mu st monitor critical flight events during countdown and launch to asse ss anomalous behavior or any unexpected occurrence. The goal of this project is to take a tailored Systems Engineering approach to design, develop, and test Iris telemetry displays. The Flight Avionics Sequen cing Telemetry Delta-IV (FAST-D4) displays will provide NASA with an improved flight event monitoring tool to evaluate launch vehicle heal th and performance during system-level ground testing and flight. Flight events monitored will include data from the Redundant Inertial Fli ght Control Assembly (RIFCA) flight computer and launch vehicle comma nd feedback data. When a flight event occurs, the flight event is ill uminated on the display. This will enable NASA Engineers to monitor c ritical flight events on the day of launch. Completion of this project requires rudimentary knowledge of launch vehicle Guidance, Navigatio n, and Control (GN&C) systems, telemetry, and console operation. Work locations for the project include the engineering office, NASA telem etry laboratory, and Delta launch sites.

  2. 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

  3. Space Tug Avionics Definition Study. Volume 5: Cost and Programmatics (United States)


    The baseline avionics system features a central digital computer that integrates the functions of all the space tug subsystems by means of a redundant digital data bus. The central computer consists of dual central processor units, dual input/output processors, and a fault tolerant memory, utilizing internal redundancy and error checking. Three electronically steerable phased arrays provide downlink transmission from any tug attitude directly to ground or via TDRS. Six laser gyros and six accelerometers in a dodecahedron configuration make up the inertial measurement unit. Both a scanning laser radar and a TV system, employing strobe lamps, are required as acquisition and docking sensors. Primary dc power at a nominal 28 volts is supplied from dual lightweight, thermally integrated fuel cells which operate from propellant grade reactants out of the main tanks.

  4. Model-based robustness testing for avionics-embedded software

    Institute of Scientific and Technical Information of China (English)

    Yang Shunkun; Liu Bin; Wang Shihai; Lu Minyan


    Robustness testing for safety-critical embedded software is still a challenge in its nascent stages.In this paper,we propose a practical methodology and implement an environment by employing model-based robustness testing for embedded software systems.It is a system-level black-box testing approach in which the fault behaviors of embedded software is triggered with the aid of modelbased fault injection by the support of an executable model-driven hardware-in-loop (HIL) testing environment.The prototype implementation of the robustness testing environment based on the proposed approach is experimentally discussed and illustrated by industrial case studies based on several avionics-embedded software systems.The results show that our proposed and implemented robustness testing method and environment are effective to find more bugs,and reduce burdens of testing engineers to enhance efficiency of testing tasks,especially for testing complex embedded systems.

  5. The development process for the space shuttle primary avionics software system (United States)

    Keller, T. W.


    Primary avionics software system; software development approach; user support and problem diagnosis; software releases and configuration; quality/productivity programs; and software development/production facilities are addressed. Also examined are the external evaluations of the IBM process.

  6. Flexible Low Cost Avionics for NanoSatellite Launch Vehicle Control and GPS Metric Tracking Project (United States)

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

  7. 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.

  8. The implementation of fail-operative functions in integrated digital avionics systems (United States)

    Osoer, S. S.


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

  9. An engineering approach to the use of expert systems technology in avionics applications (United States)

    Duke, E. L.; Regenie, V. A.; Brazee, M.; Brumbaugh, R. W.


    The concept of using a knowledge compiler to transform the knowledge base and inference mechanism of an expert system into a conventional program is presented. The need to accommodate real-time systems requirements in applications such as embedded avionics is outlined. Expert systems and a brief comparison of expert systems and conventional programs are reviewed. Avionics applications of expert systems are discussed before the discussions of applying the proposed concept to example systems using forward and backward chaining.

  10. High Performance Interconnection Technology in Avionics (Short Communication

    Directory of Open Access Journals (Sweden)

    C. R. Raghunath


    Full Text Available Avionics subsystems continue to get smaller and more functional, driving the total circuit package itself to become denser, causing the printed wiring board (PWB to evolve new laminates to meet these needs. There is a continuous scope for improvement to match the requirement of wireability demand from high density and high speed integrated circuits. Development of control processing units and rapid expansion of memory device capabilities were realised by the development of large-scale integrated circuits and other electronic devices with higher integration and with new functionalities. Enormous efforts have been put on the development of the system-on-chip (SOC, where a single semiconductor chip constituting complete system is bonded on substrate. These innovations in packaging technology made a big impact on laminates used in printed circuit boards. Aircraft systems are expected to withstand disturbances due to unexpected threats. Under such situations, passengers' safety, emergency landing and timely information to pilot become of paramount importance, hence, new innovative laminate systems are being developed. Various aspects of laminates and the current developments that are taking place are facilitating scientists and engineers in selecting appropriate laminate systems, have been discussed.Defence Science Journal, 2011, 61(4, pp.354-363, DOI:

  11. Integrated performance and reliability specification for digital avionics systems (United States)

    Brehm, Eric W.; Goettge, Robert T.


    This paper describes an automated tool for performance and reliability assessment of digital avionics systems, called the Automated Design Tool Set (ADTS). ADTS is based on an integrated approach to design assessment that unifies traditional performance and reliability views of system designs, and that addresses interdependencies between performance and reliability behavior via exchange of parameters and result between mathematical models of each type. A multi-layer tool set architecture has been developed for ADTS that separates the concerns of system specification, model generation, and model solution. Performance and reliability models are generated automatically as a function of candidate system designs, and model results are expressed within the system specification. The layered approach helps deal with the inherent complexity of the design assessment process, and preserves long-term flexibility to accommodate a wide range of models and solution techniques within the tool set structure. ADTS research and development to date has focused on development of a language for specification of system designs as a basis for performance and reliability evaluation. A model generation and solution framework has also been developed for ADTS, that will ultimately encompass an integrated set of analytic and simulated based techniques for performance, reliability, and combined design assessment.

  12. The Cognitive Pilot Helmet: enabling pilot-aware smart avionics (United States)

    Schnell, Thomas; Melzer, James E.; Robbins, Steve J.


    We hypothesize that human-aware helmet display systems can drastically improve situation awareness (SA), reduce workload, and become the cognitive gateway to two-way human-systems information. We designed a ruggedized prototype helmet liner that was fitted with active electroencephalogram (EEG) electrodes and pulse oxymetry sensor. This liner was integrated into a helmet that was fitted with a binocular SR-100A helmet mounted display. We modified the SR-100A to include dual-eye tracking capability. The resulting system is able to pick up physiological signals from the wearer in real-time for cognitive state characterization by the Cognitive Avionics Tool Set (CATS). We conducted a preliminary test of the cognitive state estimation system in a simulated close-air-support task in the laboratory and found that workload throughout the mission could be gauged using physiological parameters. Cognitively-linked helmet systems can increase situation awareness by metering the amount of information based on available cognitive bandwidth and eventually, we feel that they will be able to provide anticipatory information to the user by means of cognitive intent recognition. Considerable design challenges lie ahead to create robust models of cognitive state characterization and intent recognition. However, the rewards of such efforts could be systems that allow a dramatic increase in human decision making ability and productivity in dynamical complex situations such as air combat or surface warfare.

  13. 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.

  14. Du bruit des avions au silence de la loi

    Directory of Open Access Journals (Sweden)

    Julien Pieret


    Full Text Available Depuis plusieurs années, la question des nuisances sonores générées par l’exploitation de l’aéroport de Bruxelles-National demeure épineuse. Ainsi continue-t-elle encore aujourd’hui de susciter nombre d’actions en justice débouchant sur une quantité invraisemblable de décisions contradictoires obligeant les acteurs concernés, et au premier chef le ministre fédéral en charge de la mobilité, à sans cesse modifier les couloirs aériens empruntés par les avions. Le présent article n’a pas pour objectif d’offrir une synthèse cohérente de ce contentieux particulier. Loin de vouloir coller à tout prix à l’actualité judiciaire, il s’attache, au contraire, à offrir une grille de lecture inédite, permettant de prendre un recul nécessaire à l’analyse des enjeux que soulève une telle question. Cette grille de lecture, empruntée à la sociologie du risque, et plus particulièrement au sociologue allemand Ulrich Beck, offre de séminales pistes de réflexion quant aux paradoxes qui traversent notre société contemporaine. En effet, qu’il s’agisse de la critique du progrès technique, de la politisation de la science ou de la transformation de la société civile, c’est bien l’ensemble des paradigmes de la société du risque qui semblent pleinement illustrés par la question des nuisances sonores aéroportuaires. Le constat posé, reste à identifier les conditions permettant de construire une solution durable. Or cette solution nécessite une modification radicale de notre régulation juridique. Celle-ci devrait en effet abandonner sa prétention à fixer unilatéralement les conditions d’exploitation de l’aéroport et, à l’inverse, poser les balises d’un dialogue constructif entre les parties concernées par la problématique. Animé par une démarche réflexive, ce nouveau cadre normatif existe, ne serait-ce qu’à l’état de projet. Etrangement, il demeure pourtant cruellement absent des

  15. 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

  16. Définition conceptuelle d'avions : vers une optimisation multiobjectif, robuste et incertaine


    Badufle, Céline


    La conception d'avions au stade avant-projet consiste à déterminer les principales caractéristiques d'un avion répondant à un cahier des charges donné. Ces études peuvent être résumées par des problèmes d'optimisation globale sous contraintes avec typiquement un millier de paramètres et presque autant de contraintes. Les contraintes expriment la faisabilité physique ainsi que le cahier des charges à respecter, et les objectifs sont des performances de l'avion guidées par des études de marché....

  17. Rendezvous strategy impacts on CTV avionics design, system reliability requirements, and available collision avoidance maneuvers (United States)

    Donovan, William J.; Davis, John E.

    Rockwell International is conducting an ongoing program to develop avionics architectures that provide high intrinsic value while meeting all mission objectives. Studies are being conducted to determine alternative configurations that have low life-cycle cost and minimum development risk, and that minimize launch delays while providing the reliability level to assure a successful mission. This effort is based on four decades of providing ballistic missile avionics to the United States Air Force and has focused on the requirements of the NASA Cargo Transfer Vehicle (CTV) program in 1991. During the development of architectural concepts it became apparent that rendezvous strategy issues have an impact on the architecture of the avionics system. This is in addition to the expected impact on propulsion and electrical power duration, flight profiles, and trajectory during approach.

  18. 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.

  19. Distributed Fault-Tolerant Avionic Systems - A Real-Time Perspective

    CERN Document Server

    Burke, Michael


    This paper examines the problem of introducing advanced forms of fault-tolerance via reconfiguration into safety-critical avionic systems. This is required to enable increased availability after fault occurrence in distributed integrated avionic systems(compared to static federated systems). The approach taken is to identify a migration path from current architectures to those that incorporate re-configuration to a lesser or greater degree. Other challenges identified include change of the development process; incremental and flexible timing and safety analyses; configurable kernels applicable for safety-critical systems.

  20. Performability analysis of avionics system with multilayer HM/FM using stochastic Petri nets

    Institute of Scientific and Technical Information of China (English)

    Wan Jianxiong; Xiang Xudong; Bai Xiaoying; Lin Chuang; Kong Xiangzhen; Li Jianxiang


    The integrated modular avionics (IMA) architecture is an open standard in avionics industry,in which the number of functionalities implemented by software is greater than ever before.In the IMA architecture,the reliability of the avionics system is highly affected by the software applications.In order to enhance the fault tolerance feature with regard to software application failures,many industrial standards propose a layered health monitoring/fault management (HM/FM) scheme to periodically check the health status of software application processes and recover the malfunctioning software process whenever an error is located.In this paper,we make an analytical study of the HM/FM system for avionics application software.We use the stochastic Petri nets (SPN) to build a formal model of each component and present a method to combine the components together to form a complete system model with respect to three interlayer query strategies.We further investigate the effectiveness of these strategies in an illustrative system.

  1. Orion MPCV Service Module Avionics Ring Pallet Testing, Correlation, and Analysis (United States)

    Staab, Lucas; Akers, James; Suarez, Vicente; Jones, Trevor


    The NASA Orion Multi-Purpose Crew Vehicle (MPCV) is being designed to replace the Space Shuttle as the main manned spacecraft for the agency. Based on the predicted environments in the Service Module avionics ring, an isolation system was deemed necessary to protect the avionics packages carried by the spacecraft. Impact, sinusoidal, and random vibration testing were conducted on a prototype Orion Service Module avionics pallet in March 2010 at the NASA Glenn Research Center Structural Dynamics Laboratory (SDL). The pallet design utilized wire rope isolators to reduce the vibration levels seen by the avionics packages. The current pallet design utilizes the same wire rope isolators (M6-120-10) that were tested in March 2010. In an effort to save cost and schedule, the Finite Element Models of the prototype pallet tested in March 2010 were correlated. Frequency Response Function (FRF) comparisons, mode shape and frequency were all part of the correlation process. The non-linear behavior and the modeling the wire rope isolators proved to be the most difficult part of the correlation process. The correlated models of the wire rope isolators were taken from the prototype design and integrated into the current design for future frequency response analysis and component environment specification.

  2. 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.

  3. The role of standards in lower-cost digital spacecraft avionics (United States)

    Caldwell, Douglas W.


    The use of standard interfaces could result in large savings for the aerospace industry. This paper discusses the philosophy, applicability, and implications of using interface standards in spacecraft applications. It is argued that, while there are some negatives associated with their use, standards should be liberally applied to all aspects of spacecraft avionics because they ultimately reduce end-to-end system costs.

  4. Avionics Systems, Integration, and Technologies of the Light Transport Aircraft (Review Paper

    Directory of Open Access Journals (Sweden)

    C.M. Ananda


    Full Text Available Avionics of the present day comprises advanced technology and software-intensive systems. Earlier generation avionics constituted federated architecture and used line replaceable units (LRUs having individual resources for each application with redundant hardware and software. However with the advancement of technology, methods,and mechanisms, the industry moved quite rapidly towards the integrated architecture called integrated modular avionics (IMA. Over the last decade there has been tremendous growth in these technologies which has resulted in reduced weight, volume, and developmental efforts. Usage of complex systems with advanced technologies and their certification for use in civil aircraft are the key issues to be addressed even today. Avionics of general aviation aircraft consists of typical systems like communication, navigation, display, radar, engine indication and data acquisition and recoding systems. These can be realised in federated as well as integrated architectures. TheLRUs requirements for avionics sub-system depends on the certification standards like FAR 23 or FAR 25. The whole cycle of architecture definition, integration, testing and means of compliance of the complete suite is the major activity in any new aircraft development programme. Development of ground-based test facilities and proper maintenance of the entire system on aircraft are other important activities in such programmes. These issues are presented in this paper for a typical light transport aircraft (LTA. The new technologies with their relevance, merits/de-merits, awareness of the global systems being adopted, etc., which are being attempted as indigenousdesign and development, are also presented.Defence Science Journal, 2011, 61(4, pp.289-298, DOI:

  5. Wireless Avionics Packet to Support Fault Tolerance for Flight Applications (United States)

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


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

  6. Hardware Implementation of COTS Avionics System on Unmanned Aerial Vehicle Platforms (United States)

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


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

  7. Unitary Joint Standoff Captive Air Training Missile avionics design through operational concepts and functional requirements analysis


    Reilly, Dennis J., III


    Approved for public release; distribution is unlimited. To accurately simulate the Unitary Joint Standoff (JSOW) weapon functions and provide pilots with the most realistic training, the captive air training missile (CATM) avionics design will fully implement well defined operational concepts and functional requirements in terms of flight simulation characteristics, operational functions, pilot feedback, and electronic interfaces. This would provide the Navy, Marines, and Air Force with a ...

  8. 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



    Dr. H.-W. Schulz


    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 Fraun...

  10. Silicon Carbide Mixers Demonstrated to Improve the Interference Immunity of Radio-Based Aircraft Avionics (United States)

    Neudeck, Philip G.


    Concern over the interference of stray radiofrequency (RF) emissions with key aircraft avionics is evident during takeoff and landing of every commercial flight when the flight attendant requests that all portable electronics be switched off. The operation of key radio-based avionics (such as glide-slope and localizer approach instruments) depends on the ability of front-end RF receivers to detect and amplify desired information signals while rejecting interference from undesired RF sources both inside and outside the aircraft. Incidents where key navigation and approach avionics malfunction because of RF interference clearly represent an increasing threat to flight safety as the radio spectrum becomes more crowded. In an initial feasibility experiment, the U.S. Army Research Laboratory and the NASA Lewis Research Center recently demonstrated the strategic use of silicon carbide (SiC) semiconductor components to significantly reduce the susceptibility of an RF receiver circuit to undesired RF interference. A pair of silicon carbide mixer diodes successfully reduced RF interference (intermodulation distortion) in a prototype receiver circuit by a factor of 10 (20 dB) in comparison to a pair of commercial silicon-based mixer diodes.

  11. The Design of a Network-On-Chip Architecture Based On An Avionic Protocol


    Achballah, Ahmed Ben; Saoud, Slim Ben


    When the Network-On-Chip (NoC) paradigm was introduced, many researchers have proposed many novelistic NoC architectures, tools and design strategies. In this paper we introduce a new approach in the field of designing Network-On-Chip (NoC). Our inspiration came from an avionic protocol which is the AFDX protocol. The proposed NoC architecture is a switch centric architecture, with exclusive shortcuts between hosts and utilizes the flexibility, the reliability and the performances offered by ...

  12. Research on the Algorithm of Avionic Device Fault Diagnosis Based on Fuzzy Expert System

    Institute of Scientific and Technical Information of China (English)


    Based on the fuzzy expert system fault diagnosis theory, the knowledge base architecture and inference engine algorithm are put forward for avionic device fault diagnosis. The knowledge base is constructed by fault query network, of which the basic element is the test-diagnosis fault unit. Every underlying fault cause's membership degree is calculated using fuzzy product inference algorithm, and the fault answer best selection algorithm is developed, to which the deep knowledge is applied. Using some examples,the proposed algorithm is analyzed for its capability of synthesis diagnosis and its improvement compared to greater membership degree first principle.

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

    Lum, Ben T. F.; Pond, Charles; Dermott, William


    This interim report presents the preliminary results of an electrical actuation (ELA) system study (subtask TA3-1A) to support the NASA strategic avionics technology definition studies. The final report of this ELA study is scheduled for September 30, 1993. The topics are presented in viewgraph form and include the following ELA technology demonstration testing; ELA system baseline; power and energy requirements for shuttle effector systems; power efficiency and losses of ELA effector systems; and power and energy requirements for ELA power sources.


    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.

  15. CSI L2 - Reconstructing Herschel/Planck, Anomalies on the Avionics Bench (United States)

    Bacchetta, Andrea; Cocito, Andrea; Oort, Marc; Procopio, Dorico


    One year after the launch of Herschel and Planck it is time to show the issues which occurred in-flight that have required dedicated analyses. In particular, the role played by the Avionics Test Bench in investigating the anomalies involving the Attitude Control is presented. This verification set-up has been used extensively initially for reproducing the observed behavior and then to validate the various solutions that have been identified and implemented. Different entities, from the equipment suppliers up to the final customer, have been involved in this process and their role is presented.

  16. 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).

  17. Solving Autonomy Technology Gaps through Wireless Technology and Orion Avionics Architectural Principles (United States)

    Black, Randy; Bai, Haowei; Michalicek, Andrew; Shelton, Blaine; Villela, Mark


    Currently, autonomy in space applications is limited by a variety of technology gaps. Innovative application of wireless technology and avionics architectural principles drawn from the Orion crew exploration vehicle provide solutions for several of these gaps. The Vision for Space Exploration envisions extensive use of autonomous systems. Economic realities preclude continuing the level of operator support currently required of autonomous systems in space. In order to decrease the number of operators, more autonomy must be afforded to automated systems. However, certification authorities have been notoriously reluctant to certify autonomous software in the presence of humans or when costly missions may be jeopardized. The Orion avionics architecture, drawn from advanced commercial aircraft avionics, is based upon several architectural principles including partitioning in software. Robust software partitioning provides "brick wall" separation between software applications executing on a single processor, along with controlled data movement between applications. Taking advantage of these attributes, non-deterministic applications can be placed in one partition and a "Safety" application created in a separate partition. This "Safety" partition can track the position of astronauts or critical equipment and prevent any unsafe command from executing. Only the Safety partition need be certified to a human rated level. As a proof-of-concept demonstration, Honeywell has teamed with the Ultra WideBand (UWB) Working Group at NASA Johnson Space Center to provide tracking of humans, autonomous systems, and critical equipment. Using UWB the NASA team can determine positioning to within less than one inch resolution, allowing a Safety partition to halt operation of autonomous systems in the event that an unplanned collision is imminent. Another challenge facing autonomous systems is the coordination of multiple autonomous agents. Current approaches address the issue as one of

  18. The Unmanned Mission Avionics Test Heliciopter - a Flexible and Versatile Vtol-Uas Experimental System (United States)

    Schulz, H.-W., , Dr.


    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. Etude expérimentale multisensorielle de la dynamique des impacts d'oiseaux sur structures d'avions


    Vandeveld, Thierry F.R.


    Chaque année, d'innombrables collisions se produisent entre des avions en vol et des oiseaux. L'impact aviaire, menace redoutée par les pilotes, concerne tant l'aviation civile que son pendant militaire. Les statistiques démontrent que, même si fort heureusement le nombre d'accidents graves reste limité, les incidents sont de plus en plus nombreux.Parmi les acteurs qui luttent contre ce danger, les constructeurs d'avions jouent un rôle prépondérant. Contraints par des réglementations internat...

  20. A framework for the design and specification of hard real-time, hardware-in-the-loop simulations of large, avionic systems (United States)

    Ricks, Kenneth Gerald

    High-level design tools for the design and specification of avionic systems and real-time systems currently exist. However, real-time, hardware-in-the-loop simulations of avionic systems are based upon principles fundamentally different than those used to design avionic systems and represent a specialized case of real-time systems. As a result, the high-level software tools used to design avionic systems and real-time systems cannot be applied to the design of real-time, hardware-in-the-loop simulations of avionic systems. For this reason, such simulations of avionic systems should not be considered part of the domain containing avionic systems or general-purpose real-time systems and should be considered as an application domain unto itself for which design tools are unavailable. To fill this void, this dissertation proposes a framework for the design and specification of real-time, hardware-in-the-loop simulations of avionic systems. This framework is based upon a new specification language called the Simulation Architecture Description Language. This specification language is a graphical language with constructs and semantics defined to provide the user with the capability to completely define the simulation and its software execution characteristics at various levels of abstraction. The language includes a new method for combining precedence constraints for a single software process. These semantics provide a more accurate description of the behavior of software systems having a dynamic job structure than existing semantics. An environment that supports the execution of simulation software having the semantics defined within this language is also described. A toolset that interfaces to the language and provides additional functionality such as design analysis, schedulability analysis, and simulation file generation is also discussed. This framework provides a complete design and specification environment for real-time, hardware-in-the-loop simulations of

  1. Shuttle avionics and the goal language including the impact of error detection and redundancy management (United States)

    Flanders, J. H.; Helmers, C. T.; Stanten, S. F.


    The relationship is examined between the space shuttle onboard avionics and the ground test computer language GOAL when used in the onboard computers. The study is aimed at providing system analysis support to the feasibility analysis of a GOAL to HAL translator, where HAL is the language used to program the onboard computers for flight. The subject is dealt with in three aspects. First, the system configuration at checkout, the general checkout and launch sequences, and the inventory of subsystems are described. Secondly, the hierarchic organization of onboard software and different ways of introducing GOAL-derived software onboard are described. Also the flow of commands and test data during checkout is diagrammed. Finally, possible impact of error detection and redundancy management on the GOAL language is discussed.

  2. Multi-Purpose Avionic Architecture for Vision Based Navigation Systems for EDL and Surface Mobility Scenarios (United States)

    Tramutola, A.; Paltro, D.; Cabalo Perucha, M. P.; Paar, G.; Steiner, J.; Barrio, A. M.


    Vision Based Navigation (VBNAV) has been identified as a valid technology to support space exploration because it can improve autonomy and safety of space missions. Several mission scenarios can benefit from the VBNAV: Rendezvous & Docking, Fly-Bys, Interplanetary cruise, Entry Descent and Landing (EDL) and Planetary Surface exploration. For some of them VBNAV can improve the accuracy in state estimation as additional relative navigation sensor or as absolute navigation sensor. For some others, like surface mobility and terrain exploration for path identification and planning, VBNAV is mandatory. This paper presents the general avionic architecture of a Vision Based System as defined in the frame of the ESA R&T study “Multi-purpose Vision-based Navigation System Engineering Model - part 1 (VisNav-EM-1)” with special focus on the surface mobility application.

  3. Design of Energy-efficient Hierarchical Scheduling for Integrated Modular Avionics Systems

    Institute of Scientific and Technical Information of China (English)

    ZHOU Tianran; XIONG Huagang


    Recently the integrated modular avionics (IMA) architecture which introduces the concept of resource partitions becomes popular as an alternative to the traditional federated architecture.This study investigates the problem of designing hierarchical scheduling for IMA systems.The proposed scheduler model enables strong temporal partitioning,so that multiple hard real-time applications can be easily integrated into an uniprocessor platform.This paper derives the mathematic relationships among partition cycle,partition capacity and schedulability under the real-time condition,and then proposes an algorithm for optimizing partition parameters.Real-time tasks with arbitrary deadlines are considered for generality.To further improve the basic algorithm and reduce the energy consumption for embedded systems in aircraft,a power optimization approach is also proposed by exploiting the slack time.Experimental results show that the designed system can guarantee the hard real-time requirement and reduce the power consumption by at least 14%.

  4. A Modeling Language Based on UML for Modeling Simulation Testing System of Avionic Software

    Institute of Scientific and Technical Information of China (English)

    WANG Lize; LIU Bin; LU Minyan


    With direct expression of individual application domain patterns and ideas, domain-specific modeling language (DSML) is more and more frequently used to build models instead of using a combination of one or more general constructs. Based on the profile mechanism of unified modeling language (UML) 2.2, a kind of DSML is presented to model simulation testing systems of avionic software (STSAS). To define the syntax, semantics and notions of the DSML, the domain model of the STSAS from which we generalize the domain concepts and relationships among these concepts is given, and then, the domain model is mapped into a UML meta-model, named UML-STSAS profile. Assuming a flight control system (FCS) as system under test (SUT), we design the relevant STSAS. The results indicate that extending UML to the simulation testing domain can effectively and precisely model STSAS.

  5. 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.

  6. Proven high-reliability assembly methods applied to avionics fiber-optics high-speed transceivers (United States)

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


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

  7. Energy distribution of cosmic rays in the Earth’s atmosphere and avionic area using Monte Carlo codes

    Indian Academy of Sciences (India)



    Cosmic rays cause significant damage to the electronic equipments of the aircrafts. In this paper, we have investigated the accumulation of the deposited energy of cosmic rays on the Earth’s atmosphere, especially in the aircraft area. In fact, if a high-energy neutron or proton interacts with a nanodevice having only a few atoms, this neutron or proton particle can change the nature of this device and destroy it. Our simulation based on Monte Carlo using Geant4 code shows that the deposited energy of neutron particles ranging between 200MeV and 5 GeV are strongly concentrated in the region between 10 and 15 km from the sea level which is exactly the avionic area. However, the Bragg peak energy of proton particle is slightly localized above the avionic area.

  8. Validation Methods Research for Fault-Tolerant Avionics and Control Systems Sub-Working Group Meeting. CARE 3 peer review (United States)

    Trivedi, K. S. (Editor); Clary, J. B. (Editor)


    A computer aided reliability estimation procedure (CARE 3), developed to model the behavior of ultrareliable systems required by flight-critical avionics and control systems, is evaluated. The mathematical models, numerical method, and fault-tolerant architecture modeling requirements are examined, and the testing and characterization procedures are discussed. Recommendations aimed at enhancing CARE 3 are presented; in particular, the need for a better exposition of the method and the user interface is emphasized.

  9. 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.

  10. Development of MIL-STD-1553B Synthesizable IP Core for Avionic Applications

    Directory of Open Access Journals (Sweden)

    Enumala Srikrishna


    Full Text Available MIL-STD-1553, Digital Time Division Command/Response Multiplex Data Bus, is a military standard (presently in revision B, which has become one of the basic tools being used today for integration of weapon systems. The standard describes the method of communication and the electrical interface requirements for subsystems connected to the data bus. The 1 Mbps serial communication bus is used to achieve aircraft avionic (MIL-STD-1553B and stores management (MILSTD-1760B integration. The standard defines four hardware elements. These are 1 The transmission media, 2 Remote terminals, 3 Bus controllers, 4 Bus monitors. The main objective of this paper is to develop an IP (Intellectual Property core for the MIL-STD-1553 IC. This IP core can be used as bus monitors or remote terminals or bus monitors. The main advantage of this IP core is to provide small foot print, flexibility and reduce the cost of the system, as we can integrate this with other logic

  11. 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.

  12. 军用飞机备件预测仿真研究%Research on Forecasting the Demand of Avion Spares by Simulating Based on SPN and Arena

    Institute of Scientific and Technical Information of China (English)

    杨宜材; 王德功; 常硕


    军用飞机备件需求预测是部队目前研究的一个热点问题.为了有效地进行军用飞机备件需求预测,提出了一种用仿真进行预测的方法.通过仿真结果可以看出,该方法用于军用飞机备件需求预测是非常方便有效的.%The forecast about the demand of avion spares is a hot issue which army troops research on. In order to forecast effectively the demand of avion spares, a method of forecast based simulating is put forward. As can be seen from examination on instance, it's convenient and effectual to forecast the demand of avion spares.

  13. Space Shuttle Program Primary Avionics Software System (PASS) Success Legacy - Major Accomplishments and Lessons Learned Detail Historical Timeline Analysis (United States)

    Orr, James K.


    This presentation focuses on the Space Shuttle Primary Avionics Software System (PASS) and the people who developed and maintained this system. One theme is to provide quantitative data on software quality and reliability over a 30 year period. Consistent data relates to code break discrepancies. Requirements were supplied from external sources. Requirement inspections and measurements not implemented until later, beginning in 1985. Second theme is to focus on the people and organization of PASS. Many individuals have supported the PASS project over the entire period while transitioning from company to company and contract to contract. Major events and transitions have impacted morale (both positively and negatively) across the life of the project.

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

    Gwaltney, David A.; Briscoe, Jeri M.


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

  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. 通用飞机综合航电技术发展综述%Development Overview of Integrated Avionics Technology for General Aircraft

    Institute of Scientific and Technical Information of China (English)



    我国的低空空域开放政策正逐步推进,通用航空产业方兴未艾,对通用飞机航电技术的研究具有重要意义。回顾了通用飞机航电技术的发展历程,指出综合化是其必然的发展趋势。同时,比较了通用飞机和运输类飞机的航电系统,研究了国外典型产品,总结了通用飞机航电系统的特点,指明了发展方向及关键技术,可供相关研究作为参考。%China is carrying out the low-airspace opening policy, and domestic general aviation industry is still at its early stage, so it is significant to take GA( General Aircraft ) Avionics as a topic of research. History of GA avionics is reviewed, and it is pointed out that integration has become an inevitable trend in this field. Meanwhile, a comparison between avionics for GA and transport aircraft is made, worldwide typical products are studied, characteristics of GA avionics are summarized, development direction and key technology are pointed out,which provides a reference for relevant research.

  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. An executable meta-model for safety oriented software and systems development processes within the avionics domain in compliance with RTCA DO 178 B


    Pitchai, Karthik Raja


    "There are two critical points in every aerial flight—its beginning and its end." — Alexander Graham Bell, 1906. From beginning till the end, the safety critical software plays a vital role in avionics and hence its development and its certification are indispensable. “RTCA DO-178B- Software Considerations in Airborne Systems and Equipment Certification” provides the normative guidelines to develop such systems. In particular, this standard provides the safety protocol and processes that shou...

  1. Study and Application of Multi-Redundancy Avionics System%无人机多余度航空电子系统研究与应用

    Institute of Scientific and Technical Information of China (English)

    柳孔明; 黄俊


    无人机航空电子系统余度技术的利用大大提高了无人机系统的可靠性和安全性;通过分析多余度航空电子系统的可靠度方案,选取了合适的航空电子系统余度构型,并提出了适合三余度航空电子系统的余度架构和余度管理策略;另外对采用了基于余度策略的航空电子系统的关键技术——余度管理技术进行了研究,分析了航空电子系统余度管理的任务,在此基础上提出了管理算法方案;最后,建立了系统的可靠性模型,采用数值计算的方法,得到了系统可靠性的变化结果,为无人机航空电了系统余度设计提供了可供参考的依据.%UAV avionics system redundancy technology has greatly enhanced the reliability and security of unmanned aircraft system. The multi- redundant avionics system reliability program is analyzed in this paper, appropriate avionics redundancy configuration is designed, and appropriate architecture and redundant management strategy for three redundant avionics system are proposed. The use of redundant management technology, which is the key technology in redundant avionics system, is also studied, and a redundant management algorithm program is proposed based on the analysis of the redundant management missions. In the end, the system reliability model is built and the results of system reliability achieved by the method of numerical computing, which provides a redundant reference basis for the design of UAV aviation electronic system.

  2. 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.

  3. Prima Platform: A Scheme for Managing Equipment-Dependent Onboard Functions and Impacts on the Avionics Software Production Process (United States)

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


    The Avionics Software (ASW), in charge of controlling the Low Earth Orbit (LEO) Spacecraft PRIMA Platform (Piattaforma Ri-configurabile Italiana Multi-Applicativa), is evolving towards a highly modular and re-usable architecture based on an architectural framework allowing the effective integration of the software building blocks (SWBBs) providing the on-board control functions. During the recent years, the PRIMA ASW design and production processes have been improved to reach the following objectives: (a) at PUS Services level, separation of the mission-independent software mechanisms from the mission-dependent configuration information; (b) at Application level, identification of mission-independent recurrent functions for promoting abstraction and obtaining a more efficient and safe ASW production, with positive implications also on the software validation activities. This paper is dedicated to the characterisation activity which has been performed at Application level for a software component abstracting a set of functions for the generic On-Board Assembly (OBA), a set of hardware units used to deliver an on-board service. Moreover, the ASW production process is specified to show how it results after the introduction of the new design features.

  4. Modeling pilot interaction with automated digital avionics systems: Guidance and control algorithms for contour and nap-of-the-Earth flight (United States)

    Hess, Ronald A.


    A collection of technical papers are presented that cover modeling pilot interaction with automated digital avionics systems and guidance and control algorithms for contour and nap-of-the-earth flight. The titles of the papers presented are as follows: (1) Automation effects in a multiloop manual control system; (2) A qualitative model of human interaction with complex dynamic systems; (3) Generalized predictive control of dynamic systems; (4) An application of generalized predictive control to rotorcraft terrain-following flight; (5) Self-tuning generalized predictive control applied to terrain-following flight; and (6) Precise flight path control using a predictive algorithm.

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


    Bongers Chicano, Aneli María


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

  6. Light weight, high-speed, and self-powered wireless fiber optic sensor (WiFOS) structural health monitor system for avionics and aerospace environments (United States)

    Mendoza, Edgar A.; Kempen, Cornelia; Sun, Sunjian; Esterkin, Yan


    This paper describes recent progress towards the development of an innovative light weight, high-speed, and selfpowered wireless fiber optic sensor (WiFOS™) structural health monitor system suitable for the onboard and in-flight unattended detection, localization, and classification of load, fatigue, and structural damage in advanced composite materials commonly used in avionics and aerospace systems. The WiFOS™ system is based on ROI's advancements on monolithic photonic integrated circuit microchip technology, integrated with smart power management, on-board data processing, wireless data transmission optoelectronics, and self-power using energy harvesting tools such as solar, vibration, thermoelectric, and magneto-electric. The self-powered, wireless WiFOS™ system offers a versatile and powerful SHM tool to enhance the reliability and safety of avionics platforms, jet fighters, helicopters, commercial aircraft that use lightweight composite material structures, by providing comprehensive information about the structural integrity of the structure from a large number of locations. Immediate SHM applications are found in rotorcraft and aircraft, ships, submarines, and in next generation weapon systems, and in commercial oil and petrochemical, aerospace industries, civil structures, power utilities, portable medical devices, and biotechnology, homeland security and a wide spectrum of other applications.

  7. Technical Research of Integrated Modular Avionics%综合模块化航电系统软件技术研究

    Institute of Scientific and Technical Information of China (English)

    李骁丹; 殷永峰; 张弛


    从软件可靠性的角度对综合模块化航电(IMA)系统进行了讨论.从IMA系统的体系结构入手,研究了软件接口定义以及系统失效.具体分析了IMA软件研制过程中各角色的作用以及这种责任的分散所带来的问题.结合国内的发展现状,探讨了IMA系统测试各层次内容,为国内正在进行的四代机项目的研制及测试工作提供了一些思路.%The integrated modular avionics (IMA) is discussed from the perspective of software reliability.Firstly,starting from the architecture of integrated modular avionics,the definition of software interface and System failure are researched.The roles in the development process of IMA software and the problems brought about by this frag-mentation of responsibilities are analyzed.Finally,according to the status of domestic development,the content of all levels of the IMA system testing is explored and some ideas for the ongoing development and testing work of d-omestic four-generation flight project is provided.

  8. Design and Implementation of Avionic Low Power Video Processing Module%机载低功耗视频处理模块的设计与实现

    Institute of Scientific and Technical Information of China (English)

    张东红; 程岳; 王海鹏; 张科英


    Modern aircraft-cabin display technique is developing rapidly, more and more video information needs to be displayed and interacted in the cabin. In a specific power supply display system it is needed to process relative video information and strictly control the power consumption of the module. So it is necessary to research on the avionic low power-consumption video processing technique. Combined with the system requirements, the hardware design and logic software algorithm of the avionic low power-consumption video processing module are studied. In the power and display system, the process of video signals, including video rolling and video zoom is realized, and the power consumption requirement for the video module is met.%现代飞机座舱显示技术的发展日新月异,越来越多的视频信息需要在座舱中显示和交互。在某特定的供电显示系统中,既要处理相关视频信息又要严格控制模块的功耗,因此需要研究机载低功耗视频处理技术。结合系统需求,研究了机载低功耗视频处理模块的硬件设计和逻辑软件算法。在机载供电显示系统中实现了视频信号的相应处理,包括视频旋转和视频缩放,同时满足了系统对视频模块的功耗控制要求。

  9. 复杂电磁环境下机载电子设备的电磁兼容仿真研究%Study on EMC Simulation of Airborne Avionics under Complex Electromagnetic Environment

    Institute of Scientific and Technical Information of China (English)

    孙荣平; 成本茂; 郭龙


    分析了机载电子设备所处的复杂电磁环境,介绍了机载系统内部干扰和典型外界干扰,并据此建立了机载设备电磁兼容仿真模型;最后,给出了仿真算法并介绍了仿真软件.对复杂电磁环境下的航空电子装备的保障进行了有益的探索.%The complex electromagnetic environment that airborne avionics faced was analyzed. The internal interferences and typical external interferences were introduced. The EMC simulation model of airborne avionics was established. The EMC simulation algorithm was given and the simulation software was introduced. The purpose was to provide reference for aviation electronic armament support under complex electromagnetic environment.

  10. A Scheduling Method for Avionics WDM Networks%一种航空电子WDM网络消息调度方法

    Institute of Scientific and Technical Information of China (English)

    宋丽茹; 周立; 何锋; 熊华钢


    针对WDM(wavelength division multiplexing)广播选择型网络结构,提出了一种高信道利用率的航空电子周期和非周期消息的实时调度方法MMAS(multichannel multielass avionics scheduling).对周期消息,采用多信道静态轮转调度策略,其中RL(round length)轮转参数优化方法,可以有效地提高信道负载率,减少带宽碎片;同时提出的多信道消息分配策略能有效减少消息拆分次数.对非周期消息,采用动态预留的多信道调度策略,提出了基于周期消息剩余带宽循环序列矩阵的方法提高了信道利用率,提出了非周期实时消息的准入条件.最后,一个具体的算例验证了MMAS中周期消息RL优化方法、消息分配方法以及非周期消息剩余带宽调度策略.结果表明,周期消息分配方法能降低消息的拆分次数,RL优化设计方法和非周期剩余带宽的调度方法能有效提高信道利用率水平.%On the basis of the WDM broadcasting network structure, a real time scheduling method for avionics periodic or aperiodic real time messages named MMAS (multichannel multiclass avionics scheduling) was proposed to improve the utilization of the channels. For the periodic real time messages, the multichannel static round robin scheduling method was applied, in which the RL parameter optimization strategy was involved to increase the load rate of channels and decrease the fragments of the bandwidth at the same time. The message allocation method was provided to reduce the splitting times of the messages. For the aperiodic real time messages, the dynamic reservation multichannel scheduling method was adopted. The surplus bandwidths of periodic messages in every period were reused to improve the utilization of the channels. Then the admitting control condition for aperiodic messages was presented. The evaluation of an example verifies that the utilization of the channels could be efficiently increased by using the RL parameter

  11. Maintenance Decision-making of the Unmanned Machine Avionics System Based on FMECA%基于FMECA方法的无人机航电系统维修决策

    Institute of Scientific and Technical Information of China (English)

    窦赛; 陈国顺; 吕艳梅


    本文首先介绍了无人机航电系统的功能结构,然后,分析了对无人机航电系统进行FMECA分析的方法;最后,以舵机实例分析结果为依据,研究分析了航电系统的维修工作内容制定、预防性维修间隔期确定和预防性维修工作组合等FEMCA关键技术.%Firstly, this text introduced the function and the main structure of unmanned machine avionics system. Then, it analyzed how to carry on FMECA analysis to the unmanned machine avionics system. At the end, on the basis of the analytic results of the steering engine in the unmanned aerial vehicle system, this text analyzed how to constitute the maintenance work of the avionics system, how to confirm the preventive maintenance interval and how to combine different maintenance works, which are the key of FMECA.

  12. 机载高清视频处理模块的设计与实现%The design and implement of Avionic high definition video processing module

    Institute of Scientific and Technical Information of China (English)

    张东红; 张科英; 杨立成; 王海鹏


    Modern plane information sensor will be used rapidly, more and more video data will be needed to process in the cockpit. In order to the pilot can read more and more video data information, it will be researched to the hardware design and software arithmetic of avionic high definition video processing module. In the system of the cockpit, it have achieved the function of high definition video display, including the video mixing and video scaling, and fulfilled the system requirements of high definition video processing.%现代飞机中各种信息传感器的使用越来越广泛,座舱显示系统需要处理的数据也越来越多。为了使飞行员能够认读更多更清晰地视频信息,研究了机载高清视频处理模块的硬件设计和逻辑软件算法。在座舱显示系统中实现了高清视频的显示,包括高清视频的缩放和叠加。满足系统对高清视频处理的要求。

  13. Successful marriage: American Panel Corporation and LG Philips LCD custom-designed avionic, shipboard, and rugged ground vehicle display modules from a consumer-oriented fabrication facility (United States)

    Dunn, William; Garrett, Kimberly S.


    American panel corporation (APC) believes the use of custom designed (instead of ruggedized commercial) AMLCD cells is the only way to meet the specific environmental and performance requirements of the military/commercial avionic, shipboard and rugged ground vehicle markets. The APC/LG.Philips LCD (LG) custom approach mitigates risk to the end-user in many ways. As a part of the APC/LG long- term agreement LG has committed to provide module level equivalent (form, fit and function equivalent) panels for a period of ten years. No other commercial glass manufacturer has provided such an agreement. With the use of LG's commercial production manufacturing capabilities, APC/LG can provide the opportunity to procure a lifetime buy for any program with delivery of the entire lot within six months of order placement. This ensures that the entire production program will receive identical glass for every unit. The APC/LG relationship works where others have failed due to the number of years spent cultivating the mutual trust and respect necessary for establishing such a partnership, LG's interest in capturing the market share of this niche application, and the magnitude of the initial up-front investment by APC in engineering, tooling, facilities, production equipment, and LCD cell inventory.

  14. 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

  15. A Kind of Double redundancy Design of a Big Size T FT LCD for Avionics%一种大尺寸双冗余机载液晶显示器的设计

    Institute of Scientific and Technical Information of China (English)

    金诗玮; 赵小珍; 刘波; 赵玉冬; 刘陆


    In order to meet the demands of reli-ability and ecology on a big size TFT LCD for a-vionics ,a integrative thought of design for a big size TFT LCD ,the method of double redundan-cy design and a special ruggedization technique will be adopted in the paper .Also ,establishing anti vi-bration and impact model and thermodynamics em-ulation model by ANSYS ,FloT HERM software , stress distributing and temperature distributing on the parts of TFT LCD for avionics will be ob-tained from the model .After experimentation of high and low temperature ,vibration and impact , wetness and mildew by domestic military standard , an important method and reference data for T FT LCD for avionics will be gained .Combined the method of double redundancy design ,a big size TFT LCD for avionics can meet the demand of military domain .%为了满足现代化大尺寸机载液晶显示器环境适应性以及可靠性的要求,采用了一体化大屏设计思想、双冗余设计方法以及特殊加固工艺技术,建立抗振动、冲击模型以及热力学仿真模型,通过ANSYS和FloT HERM 仿真软件,获得机载液晶显示器各组件的应力分布以及温度分布情况。做了高低温、振动、冲击、湿热以及霉菌等国军标要求的相关实验后,得到机载液晶显示器抗振动、冲击以及热设计的重要方法和参考数据,并结合双冗余设计方法,使大尺寸机载液晶显示器能够满足军事领域使用要求。

  16. Design of Hard Real-Time Scheduling Algorithm in Avionic Wavelength Division Multiplexing Network%机载波分复用网络强实时性调度算法设计

    Institute of Scientific and Technical Information of China (English)

    黄金; 许渤; 凌云; 邱昆


    与传统的商业网络不同,航空机载波分复用网络要求强实时性以保证消息的传输性能.实时调度算法是保证机载网络中消息传输性能的关键.针对机载波分复用网络的实时性要求,采用实时通信中的周期性任务模型,提出了满足机载波分复用网络实时性要求的加权轮转调度算法,其中轮转周期的选择、权值匹配方法和多信道分配方法是影响调度算法参数设计的重要过程.通过多信道分配方法有效减少了消息拆分次数;结合实例比较确定了算法中消息分配权值的计算方法;并指出了最优轮转周期无法保证最小的消息延迟时间率.研究结果对机载波分复用网络的工程设计与优化有一定的指导意义.%Different from the commercial applications, the avionic wavelength division multiplexing (WDM) network lays much emphasis on hard real-time characteristics. The real-time scheduling algorithm is a key issue to ensure the message transmission performance. According to the real-time communication requirement of avionic WDM network and the traffic characteristics of the avionic network, a weighted round robin scheduling algorithm is proposed based on the periodic task model of real-time communication to guarantee hard real-time transmission in an airborne WDM network, which is comprised of the rotation cycle selection, weights assignment scheme and multi-channel allocation method. Among them, multi-channel allocation method efficiently reduces the splitting times of the message-, combined with examples, message weights assignment scheme is determined and it is pointed out that the optimal rotation cycle cannot guarantee the minimum message delay ratio. Research results are meaningful for the design of real-time scheduling parameters and the current practice of avionic WDM network.

  17. Application d'une technique de modelisation aerodynamique conceptuelle sur la simulation d'un pilote automatique a commande optimale pour un avion d'affaires (United States)

    Pollender-Moreau, Olivier

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

  18. Modèle mathématique d’optimisation non-linéaire du bruit des avions commerciaux en approche sous contrainte énergétique


    Nahayo, Fulgence,


    Cette thèse traite le développement d'un modèle mathématique d'optimisation acoustique des trajectoires de vol de deux avions commerciaux en approche sous contrainte énergétique, aérodynamique et opérationnelle. C'est un modèle analytique de contrôle optimal non-linéaire et non-convexe régi par un système d'équations différentielles ordinaires issues de la dynamique de vol et des contraintes associées. Notre contribution porte sur la modélisation mathématique des équations, l'optimisation et ...

  19. 基于传输性能降级约束的机载网络可靠性研究%Study on Network Reliability in Avionics Based on Performance Degradation Constraints

    Institute of Scientific and Technical Information of China (English)

    张勇涛; 黄臻; 熊华钢


    为提高因出现故障而导致网络设备资源不足时机载网络的可靠性,定义了两种机载网络传输性能降级约束,降级约束使用3个参数精确描述机载网络中消息实例传输成功或失败的数量及其分布.提出动态失效、关键函数和最小确定性将来序列等概念来对网络传输性能降级约束进行理论分析:通过计算关键函数值预先确定下一条消息实例传输失败是否会产生动态失效;使用最小确定性将来序列确定在不发生动态失效时将来消息实例传输成功的最少数量.给出两种实施约束的策略:消息源节点静态过滤和网络动态仲裁.提出一种适用于网络动态仲裁策略的调度算法:基于网络传输性能降级约束的双层优先级调度,该算法利用关键函数的预判性来避免动态失效;分析了该算法的可调度性条件.理论分析和仿真表明,当机载网络设备资源不足时,通过实施网络传输性能降级约束可以把网络性能降级的程度限制在可控范围内,从而增强机载网络的可靠性.%In order to enhance network reliability in avionics when there is a shortage of network equipment due to malfunction, two performance degradation constraints are defined. Both degradation constraints employ three arguments to accurately describe the number and distribution of message failures or successes during transmission. New concepts, such as dynamic failure, critical function and minimal guaranteed future sequence, are defined to analyze the performance degradation constraints: the value of critical function can predict whether a dynamic failure will occur if the transmission of the next message fails; the minimal guaranteed future sequence can minimize the number of successful transmissions without the occurrence of dynamic failure. Two strategies are proposed to implement the performance degradation constraints in avionic networks: static filtration by message source and dynamic


    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.


    Institute of Scientific and Technical Information of China (English)

    耿宏; 邵灿威; 刘家学


    面向民用航空维修训练领域,提出一种模块化、层次化的故障行为建模仿真方法。针对航电系统结构复杂、故障种类繁多、信息流难以控制等特点,依据飞机相关手册资料,采用离散事件系统 DEVS(Discrete Event System)描述系统的结构和行为,采用电气线性网络 ELN(Electrical Linear Networks)计算模型描述系统的电气特性,在 SystemC /SystemC AMS 仿真环境下对系统进行故障仿真。经验证该方法能真实反映正常和故障情况下航电系统电气特性和功能行为,基本满足维修训练仿真要求。%For civil aviation maintenance and training area,we present a modular and hierarchical simulation method for fault behaviours modelling.Targeted at the characteristics of avionics system such as complex structure,variety of fault types,difficult in information flow control,etc.,it simulates the system faults in the simulation environment of SystemC /SystemC AMS according to related airplane manuals and materials and using the structure and behaviour of Discrete Event System (DEVS)description system as well as adopting the electrical characteristics described by electrical linear network (ELN)computation model.It is verified that the system can factually reflect the electrical characteristics and functional behaviours of avionics system in both normal and fault situations,and basically meets the requirements in maintenance and training simulation.

  2. A Framework of Simulation Testing Environment for Integrated Modular Avionics Software%综合模块化航电软件仿真测试环境研究

    Institute of Scientific and Technical Information of China (English)

    周庆; 刘斌; 余正伟; 冯时雨


    伴随着综合模块化航空电子(IMA)软件在新一代飞机上的应用,其高复杂性、高度综合的特点以及分层的健康监控和故障管理模式给软件测试提出了挑战.传统的仿真测试环境在应对IMA软件测试中难以满足RTCA DO-178B 中规定的对验证过程结果的验证的要求.本文在分析IMA软件特点的基础上,根据DO-178B的要求,综合国外的发展情况和国内的研究进展情况,研究综合模块化航电软件仿真测试环境需求,提出了基于软件故障注入的综合模块化航电软件灰盒仿真测试环境方案,并给出优势分析.该仿真测试环境方案以IMA软件为测试对象,应用软件故障注入技术和代码插装技术满足测试规范文件的要求.其具有通用灵活、适配性强、强实时性等特点,为中国新一代航电软件的系统验证和测试奠定了基础.%It is difficult for the traditional software testing environment to meet the requirements of integrated modular avionics (IMA) software testing and verification of the verification process results in RTCA-DO-178B. It is also difficult for the traditional software testing environment to achieve the goals of functional testing and validation of the IMA software, which includes testability design, health monitoring and redundancy management functions. This paper analyzes the characteristics of integrated modular avionics software, and describes the requirements of the testing environment aimed for IMA software testing. Then, it proposes a program of IMA software grey-box testing environment based on software fault injection. This program is more general, flexible and strong real-time than the traditional software testing environment.

  3. Le bruit des avions comme facteur de dépréciations immobilières, de polarisation sociale et d’inégalités environnementales. Le cas d’Orly.

    Directory of Open Access Journals (Sweden)

    Guillaume Faburel


    Full Text Available Objectif des stratégies de développement durable, la conciliation entre les grands équipements de transport et leurs territoires d’accueil suppose une meilleure compréhension de leurs effets environnementaux et territoriaux. Nous évaluons ici les effets du bruit des avions sur les valeurs immobilières et la mobilité résidentielle des ménages, en appliquant la méthode des prix hédoniques aux valeurs de transactions immobilières observées entre 1995 et 2003 dans huit communes proches de l’aéroport d’Orly. Le bruit des avions déprécie la valeur des logements, et le taux de décote croît depuis 1995 alors que les niveaux de bruit sont restés stables, révélant la sensibilité croissante des ménages à leur environnement. D’autre part, le renouvellement des populations ne s’opère pas à l’identique : les arrivants sont plus jeunes et plus modestes que les partants. Les inégalités environnementales émergent du croisement de ces résultats, des ménages plus modestes supportant des décotes plus importantes.Finding conciliations between large infrastructures of transport and their surrounding area emerges as an important goal of sustanaible development strategies and rests on a better knowledge of their environmental and territorial effects. We report here an Hedonic Price Method (HPM application to housing values and household mobility, for eight cities located near to Orly Airport and exposed to aircraft noise. Results show that aircraft noise causes property values depreciation, and that the Noise depreciation Index is growing since 1995, even with a noise exposure level remaining stable. Moreover, household mobility shows that newcomers are younger and of lower social level than leaving ones. Hence, crossing these results lets have a glimpse of increasing environmental inequities, for more modest households will have in the future to endure more important depreciations.

  4. Evolvement Process and Management Mode of Strategic Alliance of Avionic Manufacturing Industry in China%我国航空制造业战略联盟模式演变及其管理模式研究

    Institute of Scientific and Technical Information of China (English)

    欧立雄; 苗准; 安梦琪; 朱哲然


    以资源依赖等理论为基础,通过分析国内外航空制造业战略联盟模式类型与更替,提炼出我国航空制造企业战略联盟“代加工-契约式-持股式”演变过程模型,并介绍了不同阶段模式的内涵与代表形态。面向战略联盟管理目标,提出了基于项目管理的战略联盟管理框架,及以矩阵式组织结构为静态治理框架、以契约机制、协同管理机制与文化融合机制为核心的运行体系。%Based on resource dependency theory,the taxology of strategic alliance in China’s avionic manufacturing industry is presented, based on which the evolvement historical picture is drawn as"OEM-Contractual-Ownership"each phase of which is also defined and depic-ted.Furthermore,a corresponding management framework is presented based on project management,which comprises the static management framework(matrix organizational structure)and the dynamic running mechanism such as contractual mechanism,coordination management and cultural merging mechanism.

  5. Integrated Modular Avionics Safety Analysis and Airworthiness Evaluation%综合模块化航电的安全性分析理论与适航评估

    Institute of Scientific and Technical Information of China (English)



      综合模块化航电是未来民机发展趋势。IMA系统硬件架构复杂,需要健壮的软件系统支撑,必须予以充分的理论研究,评估系统安全风险以满足适航取证要求。结合系统安全性分析理论和基本方法,本文重点讨论了在IMA研究和应用中需要注意的技术问题,以期为型号研制提供理论和方法支撑。%Integrated Modular Avionics (IMA) is a prominent trend in research and development of civil airplane. Generally IMA has complicated hardware structure and robust software support. Elements research and safety evaluation is prerequisite for airworthiness qualification. Some fundamentals and technique keys have been discussed in details in this program. And these bring forward new thoughts which are good for airplane development.

  6. Autonomous Logistics Refinement in an Avionics On-line Test System%面向自主保障的航空电子设备在线测试系统

    Institute of Scientific and Technical Information of China (English)

    王邑; 肖明清; 周越文


    针对目前面向自主保障的故障预测与健康管理系统的开发与应用缺乏重要的实时数据和应用环境的问题,提出一种面向自主保障的航空电子设备的在线测试系统;该系统应用新的算法和信息处理结构,在维持在线检测基本功能的前提下,通过自主分析航空电子设备的异常,高层次物理模型和外部故障检测与故障预测算法,以及机上不断丰富的传感器和机上测试与健康管理装置,可逐步实现故障预测与健康管理及其相应的自主保障;给出了基于飞机在线检测系统的航空电子设备在线检测面向自主保障的初步方案,构建了基本信息获取途径和基于多元统计分析及混合SOM- RBF神经网络的机上在线异常检测的方法;该系统能够在线监测并识别多种复杂异常,且飞机本身不需进行任何改装,充分利用了储存和实时两种机上环境数据,并为进行在线和线下故障预测提供基础.%To solve the problem of lack of real-time information and application environment, this article focuses on the Autonomous Logistics Refinement in an Avionics On - line Test System and proposed bunch of new algorithms and an information process framework through unsupervised analysis of the anomaly of avionics. Higher- level physics model and external diagnostics and prognostics algorithm as well as evolving onboard sensors and PHM equipments can be add to this framework thus apply full PHM and autonomous logistics gradually while maintaining the legacy on-line test capacity at any time. We proposed the initial application of the refinement, its information portal and the multivariable statistics based unsupervised anomaly detection algorithms under the fusion of SOM-RBF. No changes in on the airplane were needed, and this application method leverages both stored and real-time environmental information therefore can monitor many anomalies as well as be a basic application for on-line and off

  7. Reliability Optimization of Avionics System Based on Cost Function%基于费用函数的航电系统可靠性优化分配方法

    Institute of Scientific and Technical Information of China (English)

    和麟; 黄潇瑶; 马存宝


    Optimum reliability allocation must be solved during avionics design. It is a way to distribute system reliability to the components to achieve the optimum target through balancing the relationship between the reliability and some other source. A reliability optimization method used by BlockSim software is studied based on cost function which allows the system to achieve the goal reliability at minimum cost. And a way based on reliability importance is discussed. Taken an airborne system for an example, simulation results are given through building project and calculation. Results show that the approaches are feasible and there are two aspect to improve system reliability, improving reliability of the components and redundancy.%可靠性优化分配是航空电子系统可靠性设计中必须解决的问题,需要协调各组成部分的可靠度及其它设计因素.针对计算机辅助设计软件BlockSim,深入剖析其在最小费用下达到目标可靠性的优化分配算法以及根据重要度进行可靠性优化的方法.以某机载电子系统为例,分别给出通过提高电子元件可靠性和元件冗余两个方面进行可靠性优化分配的计算结果,对研究系统可靠性优化分配具有一定的参考价值.

  8. 某直升机综合航电显控仿真系统的开发与实现%Development and Realization of Display and Control System in Integrated Avionics Simulation System of Helicopter

    Institute of Scientific and Technical Information of China (English)

    欧爱辉; 卢卫国; 李程鹏; 张海峰


    This paper discusses the design of hardware and software of an integrated avionics simulation system based on a helicopter s bus topological structure. This paper focuses on the modularization of display, control and communication.The system simulates not only the logic of the Pilot Operation Procedure but also the communication of MIL-STD-1553 databus and ARINC429 databus in real-time.The system realizes the intercommunion of the Radar, navigation equipment , atmosphere equipment and integrated displays by emulation mode.It is showed that the system 's structure is rational and the function and the capabilties can serve for the refit requirements.%根据某直升机改装大型综合航电显控系统的需求,依据其拓扑结构,进行了仿真系统的硬件和软件设计,重点论述了基于模块化的显示、控制及通讯软件设计,按照实时性要求,仿真POP操作逻辑及MIL-STD-1553和ARINC429航空总线通讯,实现了仿真直升机上雷达、惯导、大气机通过综合处理计算机与综合显示器之间的交联,结果表明该仿真系统结构合理,功能及性能满足直升机改装验证的要求.

  9. 基于AADL的综合航电分区系统可调度性判定%Schedulability Determination of Integrated Modular Avionics Partitioned System Based on AADL

    Institute of Scientific and Technical Information of China (English)

    袁翔; 胡军; 马金晶; 刘雪


    综合模块化航电( IMA)系统中的分区系统提高了其可靠性和安全性,但在系统设计和实现过程中,应采用各种分析和验证方法确保系统的时间需求得到满足。为此,针对符合ARINC653规范的IMA系统,根据分区系统层级调度的特性,提出一种基于仿真的分区任务集可调度性判定方法。借助Cheddar工具及其自定义调度策略功能,使架构分析和设计语言( AADL)具有对分区系统进行建模的能力,并利用该工具对AADL模型进行仿真以判定系统的可调度性。实例分析结果表明,该方法能自动、准确、快速地进行可调度性判定,并以甘特图的方式绘制任务调度过程,得到直观、详细的结果。%Integrated Modular Avionics( IMA) partitioned system is put forward to improve the reliability and security of the system,but in the process of system design and implementation,analysis and validation should be used to ensure that the system time requirements are met. In allusion to IMA system which meets ARINC653 specification,according to the characteristics of hierarchy scheduling partitioned system,this paper proposes a schedulability determination method based on simulation method. With the aid of Cheddar tool and the function of custom scheduling strategy,Architecture Analysis and Design Language(AADL) has the ability of modeling partitioned system,then the tool operates on the generated AADL model to determine the system schedulable. Example analysis result shows that the tool has automatic, accurate and fast advantages to describe task scheduling process by Gantt chart and the result is accurate and detailed.

  10. Avionics Box Cold Plate Damage Prevention (United States)

    Stambolian, Damon B.; Larchar, Steven W.; Henderson, Gena; Tran, Donald; Barth, Tim


    Problem Introduction: 1. Prevent Cold Plate Damage in Space Shuttle. 1a. The number of cold plate problems had increased from an average of 16.5 per/year between 1990 through 2000, to an average of 39.6 per year between 2001through 2005. 1b. Each complete set of 80 cold plates cost approximately $29 million, an average of $362,500 per cold plate. 1c It takes four months to produce a single cold plate. 2. Prevent Cold Plate Damage in Future Space Vehicles.

  11. Avionics for Scaled Remotely Operated Vehicles Project (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...

  12. Avionics and ATC Technology for Mission Control

    Directory of Open Access Journals (Sweden)

    Elena BALMUS


    Full Text Available This paper presents a review of the old-fashioned communication and radio navigation techniques as a starting point for the development of new technologies for the Air Traffic Control based on 1940’s era radar. Current research tendencies focus on the reduction of delays and overload in a congested airspace. A key step in providing increased situational awareness for controllers and pilots is sharing operational information to improve access and flexibility. Communication between cockpit and controller through audio channels has become insufficient with the growing number of flights that take to skies every day and every year; therefore the need for alternative solutions to meet that demand has appeared. New technologies use messaging to deliver clearances, coordinates and commands determining the operators of aircraft to see the information, acknowledge, and act. Besides the new means of communication, precision navigation guidance based on GPS signals has been developed for exact alignment and descent of aircraft on approach to land on a runway.

  13. Avionics for Scaled Remotely Operated Vehicles Project (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...

  14. Modular, Plug and Play, Distributed Avionics Project (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...

  15. Formal verification of an avionics microprocessor (United States)

    Srivas, Mandayam, K.; Miller, Steven P.


    Formal specification combined with mechanical verification is a promising approach for achieving the extremely high levels of assurance required of safety-critical digital systems. However, many questions remain regarding their use in practice: Can these techniques scale up to industrial systems, where are they likely to be useful, and how should industry go about incorporating them into practice? This report discusses a project undertaken to answer some of these questions, the formal verification of the AAMPS microprocessor. This project consisted of formally specifying in the PVS language a rockwell proprietary microprocessor at both the instruction-set and register-transfer levels and using the PVS theorem prover to show that the microcode correctly implemented the instruction-level specification for a representative subset of instructions. Notable aspects of this project include the use of a formal specification language by practicing hardware and software engineers, the integration of traditional inspections with formal specifications, and the use of a mechanical theorem prover to verify a portion of a commercial, pipelined microprocessor that was not explicitly designed for formal verification.

  16. SWIFT-nanoLV Avionics Platform Project (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...

  17. GPM Avionics Module Heat Pipes Design and Performance Test Results (United States)

    Ottenstein, Laura; DeChristopher, Mike


    GPM is a satellite constellation to study precipitation formed from a partnership between NASA and the Japanese Aerospace Exploration Agency (JAXA). The GPM Core Observatory, being developed and tested at GSFC, serves as a reference standard to unify precipitation measurements from the GPM satellite constellation. The Core Observatory carries an advanced radar/radiometer system to measure precipitation from space. The scientific data gained from GPM will benefit both NASA and JAXA by advancing our understanding of Earth's water and energy cycle, improving forecasts of extreme weather events, and extending our current capabilities in using accurate and timely precipitation information to benefit society.

  18. An avionics touch screen-based control display concept (United States)

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


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

  19. Assuring Quality and Reliability in Complex Avionics Systems hardware & Software

    Directory of Open Access Journals (Sweden)

    V. Haridas


    Full Text Available It is conventional wisdom in defence systems that electronic brains are where much of the present and future weapons system capability is developed. Electronic hardware advances, particularly in microprocessor, allow highly complex and sophisticated software to provide high degree of system autonomy and customisation to mission at hand. Since modern military systems are so much dependent on the proper functioning of electronics, the quality and reliability of electronic hardware and software have a profound impact on defensive capability and readiness. At the hardware level, due to the advances in microelectronics, functional capabilities of today's systems have increased. The advances in the hardware field have an impact on software also. Now a days, it is possible to incorporate more and more system functions through software, rather than going for a pure hardware solution. On the other hand complexities the systems are increasing, working energy levels of the systems are decreasing and the areas of reliability and quality assurance are becoming more and more wide. This paper covers major failure modes in microelectronic devices. The various techniques used to improve component and system reliability are described. The recent trends in expanding the scope of traditional quality assurance techniques are also discussed, considering both hardware and software.

  20. Alternative Suspension System for Space Shuttle Avionics Shelf (United States)

    Biele, Frank H., III


    Engineers working in the Aerospace field under deadlines and strict budgets often miss the opportunity to design something that is considered new or innovative, favoring instead to use the tried-and-true design over those that may, in fact, be more efficient. This thesis examines an electronic equipment stowage shelf suspended from a frame in the cargo bay (mid fuselage) of the United States Space Transportation System (STS), the Space Shuttle, and 3 alternative designs. Four different designs are examined and evaluated. The first design is a conventional truss, representing the tried and true approach. The second is a cable dome type structure consisting of struts and pre-stressed wiring. The third and fourth are double layer tensegrity systems consisting of contiguous struts of the order k=1 and k=2 respectively.

  1. A robust 100 MBPS network for avionics applications (United States)

    Varga, M. P.

    A fiber-optic Local Area Network that operates at a transmission rate of 100 MBPS is designed to feature advantages of random access (contention) networks and deterministic (token) networks. This LAN implements a contention access protocol that dynamically adjusts its performance to that of a token network as the data traffic increases. The statistical relationship between collisions and data traffic load is used to achieve this adjustment in performance. The network and bus interface units (BIUs) incorporate message fault recovery, system statistical monitor, built-in test, low power, high reliability, and radiation resistant features. The network and BIUs were designed to incorporate redundancy with cross-strapping at the physical media, and because the media is a broadcast media with simultaneous transmission over both fiber buses, immediate recovery or many physical layer failures is possible. System level redundancy is supported with BIU internal checks and an automatic switchover to redundant units.

  2. Integrated Power, Avionics, and Software (IPAS) Flexible Systems Integration Project (United States)

    National Aeronautics and Space Administration — iPAS will develop several important technologies required to support system design and integration as well as space technology maturation. These services include:A...

  3. An Avionics Touch Screen based Control Display Concept

    NARCIS (Netherlands)

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


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

  4. Alternate suspension system for space shuttle avionics shelf (United States)

    Biele, Frank H., III

    This thesis examines an equipment stowage shelf suspended from a frame in the cargo bay (mid fuselage) of the U.S. Space Shuttle, and three alternative designs. The first design is a conventional truss, representing the "tried and true" approach. The second is a cable dome type structure consisting of struts and pre-stressed cables. The third and fourth are double layer tensegrity systems consisting of contiguous struts of the order k=1 and k=2 respectively. The four options are compared to each other with an emphasis placed on weight, size, and approximate cost of each option. Results indicate the 4-Way Double Layer Tensegrity grid utilizing carbon fiber composite cables is the most efficient (lightest weight) tensegrity system, however for this particular application the most cost effective design was proven to be the optimized conventional truss. It was determined that the scale of the structure would have to increase substantially or tensegrity structures complexity must decrease for these alternative systems to compete with conventional designs.

  5. Intelligent, Reusable Software for Plug and Play Space Avionics Project (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...

  6. Space Shuttle Avionics: a Redundant IMU On-Board Checkout and Redundancy Management System (United States)

    Mckern, R. A.; Brown, D. G.; Dove, D. W.; Gilmore, J. P.; Landey, M. E.; Musoff, H.; Amand, J. S.; Vincent, K. T., Jr.


    A failure detection and isolation philosophy applicable to multiple off-the-shelf gimbaled IMUs are discussed. The equations developed are implemented and evaluated with actual shuttle trajectory simulations. The results of these simulations are presented for both powered and unpowered flight phases and at operational levels of four, three, and two IMUs. A multiple system checkout philosophy is developed and simulation results presented. The final task develops a laboratory test plan and defines the hardware and software requirements to implement an actual multiple system and evaluate the interim study results for space shuttle application.

  7. 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.

  8. Avionics and Power Management for Low-Cost High-Altitude Balloon Science Platforms (United States)

    Chin, Jeffrey; Roberts, Anthony; McNatt, Jeremiah


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

  9. Analysis of the survivability of the shuttle (ALT) fault-tolerant avionics system (United States)


    An extension of the Complementary-Analytic-Simulative Technique (CAST) is presented which is applicable to the Shuttle Data Processing Subsystem (DPS). A two step process was used. The first step provides models, both analytic and simulative, for analysis of the Approach-Landing Test (ALT) configuration. The ALT modeling and analysis are presented. Since CAST had already been shown to be multicomputer systems, the emphasis was placed on extending the CAST concept so it is applicable to computer systems including the multiplicity of input and output devices found in a real-time control system application. The DPS mission-critical survivability for a six-hour mission was determined to be 0.999863 for the Shuttle ALT baseline configuration. Thus it can be said that for ALT, the survivability is adequate. However, the fact that orbiting missions of up to 30 days are planned illustrates the necessity of extending the ALT work to be applicable to OFT and actual mission scenarios. The above analysis led to the evaluation of three selected options which identified two areas of possible improvement. These improvements would result from use of a recovery technique which combines roll ahead with memory copy, and increased TACAN fault detectability.

  10. 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.

  11. Possible effects on avionics induced by terrestrial gamma-ray flashes

    Directory of Open Access Journals (Sweden)

    M. Tavani


    Full Text Available Terrestrial gamma-ray flashes (TGFs are impulsive (intrinsically sub-millisecond events associated with lightning in powerful thunderstorms. TGFs turn out to be very powerful natural accelerators known to accelerate particles and generate radiation up to hundreds of MeV energies. The number ratio of TGFs over normal lightning has been measured in tropical regions to be near 10−4. We address in this Article the issue of the possible susceptibility of typical aircraft electronics exposed to TGF particle, gamma ray and neutron irradiation. We consider possible scenarios regarding the intensity, the duration, and geometry of TGFs influencing nearby aircraft, and study their effects on electronic equipment. We calculate, for different assumptions, the total dose and the dose-rate, and estimate single-event-effects. We find that in addition to the electromagnetic component (electrons/positrons, gamma rays also secondary neutrons produced by gamma-ray photo production in the aircraft structure substantially contribute to single-event effects in critical semiconductors components. Depending on the physical characteristics and geometry, TGFs may deliver a large flux of neutrons within a few milliseconds in an aircraft. This flux is calculated to be orders of magnitude larger than the natural cosmic-ray background, and may constitute a serious hazard to aircraft electronic equipment. We present a series of numerical simulations supporting our conclusions. Our results suggest the necessity of dedicated measurement campaigns addressing the radiative and particle environment of aircraft near or within thunderstorms.

  12. The development of a range of small mechanical cryocoolers for space and avionic applications (United States)

    Hocking, Barry


    The design features of a mechanical cryocooler, including a compressor, displacer, connecting pipe, and electronic controller are described. The complete system is filled with helium gas to a pressure of 10 bar. Long life, low exported vibration, and good refrigeration within the defined temperature range are emphasized as the main requirements. A number of improvements with regard to the reliability required for long-life space coolers are outlined, and emphasis is placed on the improved sealing for the helium gas and the outgassing properties of all components. Scaling up of the cryocooler design for increased refrigeration is reviewed as well as a space-system interface. Testing of space-rated cryocooler systems producing nominal 0.5 W and 1 W cooling at 65 K from a single system is discussed.

  13. Genesis failure investigation report : JPL Failure Review Board, Avionics Sub-Team (United States)

    Klein, John; Manning, Rob; Barry, Ed; Donaldson, Jim; Rivellini, Tom; Battel, Steven; Savino, Joe; Lee, Wayne; Dalton, Jerry; Underwood, Mark; Surampudi, Rao; Accord, Arden; Perkins, Dave; Barrow, Kirk; Wilson, Bob


    On January 7, 2001, the Genesis spacecraft lifted off from Cape Canaveral. Its mission was to collect solar wind samples and return those samples to Earth for detailed analysis by scientists. The mission proceeded successfully for three-and-a-half years. On September 8, 2004, the spacecraft approached Earth, pointed the Sample Return Capsule (SRC) at its entry target, and then fired pyros that jettisoned the SRC. The SRC carried the valuable samples collected over the prior 29 months. The SRC also contained the requisite hardware (mechanisms, parachutes, and electronics) to manage the process of entry, descent, and landing (EDL). After entering Earthas atmosphere, the SRC was expected to open a drogue parachute. This should have been followed by a pyro event to release the drogue chute, and then by a pyro event to deploy the main parachute at an approximate elevation of 6.7 kilometers. As the SRC descended to the Utah landing site, helicopters were in position to capture the SRC before the capsule touched down. On September 8, 2004, observers of the SRCas triumphant return became concerned as the NASA announcer fell silent, and then became even more alarmed as they watched the spacecraft tumble as it streaked across the sky. Long-distance cameras clearly showed that the drogue parachute had not deployed properly. On September 9, 2004, General Eugene Tattini, Deputy Director of the Jet Propulsion Laboratory formed a Failure Review Board (FRB). This board was charged with investigating the cause of the Genesis mishap in close concert with the NASA Mishap Investigation Board (MIB). The JPL-FRB was populated with experts from within and external to the Jet Propulsion Laboratory. The JPL-FRB participated with the NASA-MIB through all phases of the investigation, working jointly and concurrently as one team to discover the facts of the mishap.

  14. Optimization of an avionic VCSEL-based optical link through large signal characterization (United States)

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


    Optical communication systems have been widely preferred for network communications, especially for Datacoms Local Area Network links. The optical technology is an excellent candidate for on-board systems due to the potential weight saving and EMC immunity. According to the short length of the link and a cost saving, Vertical Cavity Surface Emitting Laser (VCSEL) and multimode fiber are the best solution for gigabit systems. In this context, we propose a modeling of 850nm VCSEL based on the rate equations analysis to predict the optical interconnect performances (jitter, bit error rate). Our aim is to define the operation conditions of VCSEL under large signal modulation in order to maximize the Extinction Ratio (current I OFF below threshold) without affecting link performances. The VCSEL model is developed to provide large signal modulation response. Biasing below threshold causes stochastic turn-on delay. Fluctuations of this delay occur, due to the spontaneous emission. This leads to additional turn-on jitter. These stochastic effects are included in the model by adding the Langevin photon and electron noise sources. The VCSEL behavior under high-speed modulation is studied to observe the transient response and extract the resonance frequency, overshoot and turn-on delay. The associated jitter is evaluated with the standard deviation of the turn-on delay probability density function. Simulations of stochastic and deterministic jitters are realized under different conditions of modulation (OFF current levels). Comparing simulations with measurement results carried out on VCSEL and a short haul gigabit link validates the approach.

  15. Validation Methods Research for Fault-Tolerant Avionics and Control Systems: Working Group Meeting, 2 (United States)

    Gault, J. W. (Editor); Trivedi, K. S. (Editor); Clary, J. B. (Editor)


    The validation process comprises the activities required to insure the agreement of system realization with system specification. A preliminary validation methodology for fault tolerant systems documented. A general framework for a validation methodology is presented along with a set of specific tasks intended for the validation of two specimen system, SIFT and FTMP. Two major areas of research are identified. First, are those activities required to support the ongoing development of the validation process itself, and second, are those activities required to support the design, development, and understanding of fault tolerant systems.

  16. SIFT - Multiprocessor architecture for Software Implemented Fault Tolerance flight control and avionics computers (United States)

    Forman, P.; Moses, K.


    A brief description of a SIFT (Software Implemented Fault Tolerance) Flight Control Computer with emphasis on implementation is presented. A multiprocessor system that relies on software-implemented fault detection and reconfiguration algorithms is described. A high level reliability and fault tolerance is achieved by the replication of computing tasks among processing units.

  17. Ultra-Low Power Extreme Environment Capable Avionics System-on-a-Chip Project (United States)

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

  18. Optimisation de forme aéro-acoustique d'un avion d'affaires supersonique


    Minelli, Andrea


    Ce travail porte sur le developpement de m ethodes num eriques innovantes pour la conception a ero -acoustique optimale de forme des con gurations supersoniques. Ce manuscrit pr esente tout d'abord l'analyse et le d eveloppement des approches num eriques pour la pr evision du bang sonique . Le couplage du calcul CFD tridimensionnel en champ proche prenant en compte la d ecomposition multipolaire de Fourier et la propagation atmosph erique bas ee sur un algorithme de trac e de rayons est am el...

  19. Caracterisation electrique de materiaux en composite pour fuselages d'avions (United States)

    Tse, William


    In the last decade or so, the rise of oil price is being felt all over the world. Oil being one of the primary sources of energy highly exploited, it plays a great role in the today's world economy, especially in the transport domain. To remain competitive, companies striving in this domain need therefore to modify their approach in the design phase of new or improved products. In the aerospace industry for example, weight reduction in aircraft structures have become a primordial aspect in the design phase of new models making them lighter and more efficient. In the framework of this project, the research is related to new weight-reduction of structural materials used in aircrafts. As of today, much research effort has been undertaken to find good substitutes to replace the materials presently used (aluminum). Several materials such as aluminum-lithium and carbon fibre composite bring great interest as substitutes. This last one presents superior mechanical properties over aluminum such as lightweight and rigidity; its electrical properties though remain still ambiguous. The objective of this project, proposed by Bombardier Core EMC, is to find a way to characterize the composite in a conventional way that would allow an extraction of its electrical properties (permittivity (epsilonr), conductivity (sigma), etc). In this Master thesis, the existing studies and characterization approaches for the composite material are presented and discussed. These approaches will help anticipate the electrical behaviour of the composite material under test. A comparison between known elements (ex: aluminum) and the composite material will also be tackled in order to gauge its conductivity level, particularly for low frequencies (≈ MHz), and up to high frequencies (≈ 12 GHz). Finally, some tests have been simulated with electromagnetic modelling software in order to reproduce and validate the experimental results. At the end of the thesis, a discussion/conclusion presenting the results and validating their integrity is given. The results enable us to do an estimation of the composite's conductivity and to observe its attenuation properties in function of the frequency. The tests were made with composite laminated panels without wire mesh. The wire mesh here is a copper matrix integrated at the exterior surface of the composite for added electromagnetic protection.

  20. Contributions au probleme d'affectation des types d'avion (United States)

    Belanger, Nicolas

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

  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. Optimisation multidisciplinaire de pales d'hélice d'avion


    Marinus, Benoît


    Open rotors are known to have significant advantages in terms of propulsive efficiency. These advantages translate directly in reduced fuel burn so that they nowadays benefit from a surge of interest. At the same time, recent advances in numerical simulations make the application of multidisciplinary optimization for the demanding design of transonic propeller blades, an affordable option. Therefore, an optimization method in which the performance objectives of aerodynamics, aeroacoustics and...

  3. 76 FR 70044 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes (United States)


    ... experienced in-flight elevator travel limitations with unusual effort being necessary on pitch axis to control... August 5, 2011 (76 FR 47520). That NPRM proposed to correct an unsafe condition for the specified... received no comments on the NPRM (76 FR 47520), August 5, 2011) or on the determination of the cost to...

  4. Prognostics for electronics components of avionics - NASA IGBT accelerated ageing case study


    Xie, Yuan'an


    Insulate gate bipolar transistors (IGBTs) are widely used in electric vehicles, railway locomotive and new generation aircrafts, due to the IGBTs have advantages in small conduction resistance and small drive current. Hence, the reliability of IGBTs directly affect the reliability and performance of these vehicle systems. In recent years, a series of research works about IGBT reliability, failure mode and ageing analysis have been carried out widely, and a suitable prognosti...

  5. Adaptable and Reconfigurable Modular Systems (GSFC) - Plug and Play, Distributed Avionics Project (United States)

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

  6. Aerospace avionics equipment and integration; Proceedings of the Second Conference, Dallas, TX, Nov. 2-4, 1987 (United States)

    The conference presents papers on hybrid MIL-STD-1553B/1773 electrical/optical buses, the use of interrupts on the IBM PC to generate major and minor frame times, and the use of the IBM PC for MIL-STD-1553 testing. Other topics include single-chip solution of MIL-STD-1553A and MIL-STD-1553B data communications, a simulation model of the SAE AE-9B high speed ring bus, and a high performance dual mode synchronous/asynchronous parallel bus controller utilizing the PI bus standard protocol. Consideration is also given to token rotation timer implementation and global positioning system receiver initialization methods for MIL-STD-1760A.

  7. A highly reliable, high performance open avionics architecture for real time Nap-of-the-Earth operations (United States)

    Harper, Richard E.; Elks, Carl


    An Army Fault Tolerant Architecture (AFTA) has been developed to meet real-time fault tolerant processing requirements of future Army applications. AFTA is the enabling technology that will allow the Army to configure existing processors and other hardware to provide high throughput and ultrahigh reliability necessary for TF/TA/NOE flight control and other advanced Army applications. A comprehensive conceptual study of AFTA has been completed that addresses a wide range of issues including requirements, architecture, hardware, software, testability, producibility, analytical models, validation and verification, common mode faults, VHDL, and a fault tolerant data bus. A Brassboard AFTA for demonstration and validation has been fabricated, and two operating systems and a flight-critical Army application have been ported to it. Detailed performance measurements have been made of fault tolerance and operating system overheads while AFTA was executing the flight application in the presence of faults.

  8. Flight Computer Processing Avionics for Space Station Microgravity Experiments: A Risk Assessment of Commercial Off-the-Shelf Utilization (United States)

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


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

  9. Diagnostic et Pronostic de défaillances dans des composants d'un moteur d'avion


    Diez Lledo, Edouard


    Economic aspects and passengers security make that Fault Diagnostic is a critical problem in Aeronautics. In Aeronautics engines and complementary equipments as regulators, actuators, sensors,& are the most important elements to maintain the aircraft in flight. A preliminary study, based on maintenance data, has shown that hydraulic actuators and lubrication system are among the most critical components. The hydraulic system purpose is to adapt the geometry of the engine to the particular sit...

  10. 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

  11. ACE-MBI Design Meet to Avionics Communication System Requirement%满足航电通信系统要求的ACE-MBI设计

    Institute of Scientific and Technical Information of China (English)

    谢冲; 王奇锋; 党春勃



  12. The ACE-MBI Design Meet to Avionics Communication System Requirement%满足航电通信系统要求的ACE-MBI设计

    Institute of Scientific and Technical Information of China (English)

    谢冲; 王奇锋; 党春勃



  13. Optimisation multidisciplinaire : étude théorique et application à la conception des avions en phase d'avant projet


    Clément, Joël


    L'optimisation multi-disciplinaire propose des solutions aux problèmes de conception de systèmes complexes. Le terme « optimisation multi-disciplinaire » laisse sous-entendre à tort qu'il ne s'agit que d'un problème d'optimisation. Nous lui préférons ici le terme de « conception collaborative ». En effet, l'optimisation ne représente qu'un aspect, qui ne peut être séparée du reste du problème de conception. Le but n'est pas de créer un processus automatique, mais de faciliter les échanges ent...

  14. 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.

  15. 77 FR 67557 - Special Conditions: ATR-GIE Avions de Transport Regional, Models ATR42-500 and ATR72-212A... (United States)


    ...-engine, turbo- propeller driven. The Model ATR42-500 has a maximum takeoff weight of 41,005 pounds and an... Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR...

  16. Production of Reliable Flight Crucial Software: Validation Methods Research for Fault Tolerant Avionics and Control Systems Sub-Working Group Meeting (United States)

    Dunham, J. R. (Editor); Knight, J. C. (Editor)


    The state of the art in the production of crucial software for flight control applications was addressed. The association between reliability metrics and software is considered. Thirteen software development projects are discussed. A short term need for research in the areas of tool development and software fault tolerance was indicated. For the long term, research in format verification or proof methods was recommended. Formal specification and software reliability modeling, were recommended as topics for both short and long term research.

  17. Optimisation d'un systeme d'antigivrage a air chaud pour aile d'avion basee sur la methode du krigeage dual (United States)

    Hannat, Ridha

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

  18. 民用机载航电系统安全性实现方法分析%Study on Civil Avionics System Safety

    Institute of Scientific and Technical Information of China (English)

    施劲松; 步鑫


    Safety is the key base of airworthiness. To achieve safety goal requires complex system engineering process which includes systematic planning, overall program management and application of tools and methods. This paper analyzed how to establish the team,how to use proper development process and analysis tools in order to realize safety goal.%安全性是适航的重要基础,为实现规定的安全性目标,必须系统策划,统筹管理,合理配置资源,综合应用各类分析方法和工具。本文就安全性工作团队的组建,项目开发使用的流程,如何有效使用分析工具等问题阐述了安全性实现的一些方法。

  19. 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.

  20. 76 FR 47520 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Model ATR42 and ATR72 Airplanes (United States)


    ... experienced in-flight elevator travel limitations with unusual effort being necessary on pitch axis to control... ; Internet . You may review copies of the referenced... has experienced in-flight elevator travel limitations with unusual effort being necessary on...

  1. Electromagnetic Interference In New Aircraft (United States)

    Larsen, William E.


    Report reviews plans to develop tests and standards to ensure that digital avionics systems in new civil aircraft immune to electromagnetic interference (EMI). Updated standards reflect more severe environment and vulnerabilities of modern avionics.

  2. 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

  3. 航电设备内冷通道扩展表面的传热与流动特性研究%Thermal Hydraulic Performance of the Extended Surface Use in an Avionic System Internal Cooling Channels

    Institute of Scientific and Technical Information of China (English)



    Numeric simulation on heat transfer and pressure drop characteristic for 25 type CNC milled strip fin were performed.Using the Taguchi experimental design method,deferent design parameters and their levels were investigated.The general correlation for j-factor and f-factor were derived by regression analysis.The numeric has also been valid by wind tunnel and the deviations of the method are less than 15%.Range method has also been performed,and it has been reviled that the most effective factor to f is channel height H and most effective factor to j is x direction fin spacing.%在某航空电子冷却机箱中,综合考虑其使用环境,采用了CNC加工的叉排直肋作为其内冷肋化通道.为找出影响该类扩展表面的传热与流动特性的主要因素,采用正交实验设计的方法,对不同结构参数的25种肋片应用Fluent进行了数值模拟,通过极差分析研究了对传热流动特性影响最大的结构参数,同时获得了流动参数范围内用于工程计算的jf计算关联式.

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

    Directory of Open Access Journals (Sweden)

    Jorge Joaquín Locane


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

  5. 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.)

  6. Optimal Thermal Design of a Stacked Mini-Channel Heat Sink Cooled by a Low Flow Rate Coolant


    Jun Wang; Meng Liu; Wei Wang(College of William and Mary); Liping Pang; Minxing Wang


    Application requirements for avionics are often very strict. For example, the heat sinks of avionics need very good temperature uniformity, but the flow rate of coolant is very restricted. In addition, the use of micro-channels is not recommended due to the potential clogging issue. Considering these design requirements, we will discuss a multiple-objective optimal design method to obtain a good stacked mini-channel structure for avionics applications. In our thermal design, the design variab...

  7. 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...

  8. Improved Design of Radiation Hardened, Wide-Temperature Analog and Mixed-Signal Electronics Project (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...

  9. Improved Design of Radiation Hardened, Wide-Temperature Analog and Mixed-Signal Electronics Project (United States)

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

  10. Operationally Responsive Spacecraft Subsystem Project (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...

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

  12. 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.

  13. Theoretical Issues Associated with the Evaluation of the Technical Condition of Avionic Hydraulic Drives on the Basis of Information Received from Means for Unbiased Flight Control of Aircrafts / Teoretyczne Aspekty Oceny Stanu Technicznego Lotniczego Napędu Hydraulicznego Na Podstawie Informacji Ze Środków Obiektywnej Kontroli Lotu

    Directory of Open Access Journals (Sweden)

    Ułanowicz Leszek


    Full Text Available Celem pracy jest przedstawienie możliwości wykorzystania do oceny stanu technicznego lotniczego napędu hydraulicznego metody polegającej na wykorzystaniu informacji ze środków obiektywnej kontroli lotu. Największą wiarygodność oraz wartość diagnostyczną mają dwa parametry kontrolne uzyskane ze środków obiektywnej kontroli lotu. Pierwszy to czas spadku ciśnienia w lotniczym napędzie hydraulicznym od górnej wartości pomiarowej do dolnej wartości pomiarowej po wyłączeniu zespołu napędowego. Drugi to czas spadku ciśnienia poniżej określonej wartości i jego powrotu do tej wartości w czasie ruchu silnika hydraulicznego. Proponowana metoda daje możliwość bieżącej oceny stanu technicznego lotniczego napędu hydraulicznego, jest szybka i bezkosztowa.

  14. Adaptación de pilotos al glass-cockpit


    Sorin, Jacques


    Se presenta una propuesta de diseño de cabina de pilotaje de aviones cuyo objetivo es ayudar la adaptación de los pilotos al pilotaje de los aviones de pasajeros de tipo glass-cockpit. Se acompaña esta propuesta de una descripción de conjunto de la relación piloto-avión tal como evoluciona desde que el piloto aprende a pilotar la primera avioneta de escuela hasta que aborda los aviones de transporte de pasajeros. Esta descripción abarca elementos cognitivos y afectivo-emocionales de la relaci...

  15. Component-Based QoS-Driven Synthesis of High Assurance Embedded Software Project (United States)

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

  16. A Self-Regulating Freezable Heat Exchanger for Spacecraft Project (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. 14 CFR 129.117 - Flammability reduction means. (United States)


    ... foreign person complies with 14 CFR 26.35 by the applicable date stated in that section. (2) The foreign... 305. (13) Handley Page Herald Type 300. (14) Avions Marcel Dassault—Breguet Aviation Mercure 100C....

  18. 14 CFR 121.1117 - Flammability reduction means. (United States)


    ... holder complies with 14 CFR 26.35 by the applicable date stated in that section. (2) The certificate... Aviation IL 96T. (12) Bristol Aircraft Britannia 305. (13) Handley Page Herald Type 300. (14) Avions...


    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...

  20. COARSE: Convex Optimization based autonomous control for Asteroid Rendezvous and Sample Exploration Project (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...

  1. Stress Studies at Kennedy Space Center: a Backward and Forward Look (United States)

    Decker, A. I.


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

  2. 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.

  3. 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...

  4. Radiation Mitigation Methods for Reprogrammable FPGA Project (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...

  5. 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...

  6. High Spatial Resolution shape Sensing for Adaptive Aerospace Vehicles Project (United States)

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

  7. 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.

  8. SSTAC/ARTS review of the draft Integrated Technology Plan (ITP). Volume 6: Controls and guidance (United States)


    Viewgraphs of briefings from the Space Systems and Technology Advisory Committee (SSTAC)/ARTS review of the draft Integrated Technology Plan (ITP) on controls and guidance are included. Topics covered include: strategic avionics technology planning and bridging programs; avionics technology plan; vehicle health management; spacecraft guidance research; autonomous rendezvous and docking; autonomous landing; computational control; fiberoptic rotation sensors; precision instrument and telescope pointing; microsensors and microinstruments; micro guidance and control initiative; and earth-orbiting platforms controls-structures interaction.

  9. 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.)

  10. Hypervelocity impact testing of the Space Station utility distribution system carrier (United States)

    Lazaroff, Scott


    A two-phase, joint JSC and McDonnell Douglas Aerospace-Huntington Beach hypervelocity impact (HVI) test program was initiated to develop an improved understanding of how meteoroid and orbital debris (M/OD) impacts affect the Space Station Freedom (SSF) avionic and fluid lines routed in the Utility Distribution System (UDS) carrier. This report documents the first phase of the test program which covers nonpowered avionic line segment and pressurized fluid line segment HVI testing. From these tests, a better estimation of avionic line failures is approximately 15 failures per year and could very well drop to around 1 or 2 avionic line failures per year (depending upon the results of the second phase testing of the powered avionic line at White Sands). For the fluid lines, the initial McDonnell Douglas analysis calculated 1 to 2 line failures over a 30 year period. The data obtained from these tests indicate the number of predicted fluid line failures increased slightly to as many as 3 in the first 10 years and up to 15 for the entire 30 year life of SSF.

  11. Design of a smart optically controlled high-power switch for fly-by-light motor actuation systems (United States)

    Bhadri, Prashant; Sukumaran, Deepti; Dasgupta, Samhita; Beyette, Fred R., Jr.


    In avionic systems, data integrity and high data rates are necessary for stable flight control. Unfortunately, conventional electronic control systems are susceptible to electromagnetic interference (EMI) that can reduce the clarity of flight control signals. Fly-by-Light systems that use optical signals to actuate the flight control surfaces of an aircraft have been suggested as a solution to the EMI problem in avionic systems. Fly-by-Light in avionic systems reduces electromagnetic interference hence improving the clarity of the control signals. A hybrid approach combining a silicon photoreceiver module with a SiC power transistor is proposed. The resulting device uses a 5 mW optical control signal to produce a 150 A current suitable for driving an electric motor.

  12. Design and simulation of a smart optically controlled high-power switch based on a Si/SiC hybrid device structure (United States)

    Bhadri, Prashant; Sukumaran, Deepti; Dasgupta, Samhita; Beyette, Fred R., Jr.


    In avionic systems, data integrity and high data rates are necessary for stable flight control. Unfortunately, conventional electronic control systems are susceptible to electromagnetic interference (EMI) that can reduce the clarity of flight control signals. Fly-by-Light systems that use optical signals to actuate the flight control surfaces of an aircraft have been suggested as a solution to the EMI problem in avionic systems. Fly-by-Light in avionic systems reduces electromagnetic interference hence improving the clarity of the control signals. A hybrid approach combining a silicon photoreceiver module with a SiC power transistor is proposed. The resulting device uses a 5 mW optical control signal to produce a 150 A current suitable for driving an electric motor.

  13. High speed bus technology development (United States)

    Modrow, Marlan B.; Hatfield, Donald W.


    The development and demonstration of the High Speed Data Bus system, a 50 Million bits per second (Mbps) local data network intended for avionics applications in advanced military aircraft is described. The Advanced System Avionics (ASA)/PAVE PILLAR program provided the avionics architecture concept and basic requirements. Designs for wire and fiber optic media were produced and hardware demonstrations were performed. An efficient, robust token-passing protocol was developed and partially demonstrated. The requirements specifications, the trade-offs made, and the resulting designs for both a coaxial wire media system and a fiber optics design are examined. Also, the development of a message-oriented media access protocol is described, from requirements definition through analysis, simulation and experimentation. Finally, the testing and demonstrations conducted on the breadboard and brassboard hardware is presented.

  14. 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.

  15. 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.

  16. 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.

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

    Directory of Open Access Journals (Sweden)

    Mladen R. Tišma


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

  18. Measurement of EM Field Inside a Cruising Aircraft: Potential Problems for the Use of Mobile Phones on Board (United States)

    Kohmura, A.; Picard, J.; Yonemoto, N.; Yamamoto, K.

    Electromagnetic (EM) emissions from portable electronic devices (PEDs) carried onboard aircraft can interfere with avionic systems. Several onboard systems using EM waves have been planned, such as mobile communications and UWB (ultra-wideband) entertainment services distribution. Manufacturers of this system develop schemes to avoid electromagnetic interference by the transmissions (emissions) of mobile phones with avionic systems; some local-specific problems still remain. The purpose of this chapter is to investigate to what extent non-GSM transmissions from the ground base stations reach inside a cruising aircraft. The EM field at the base station frequency bands is measured in a cruising small aircraft.

  19. State-of-the-art cockpit design for the HH-65A helicopters (United States)

    Castleberry, D. E.; Mcelreath, M. Y.


    In the design of a HH-65A helicopter cockpit, advanced integrated electronics systems technology was employed to achieve several important goals for this multimission aircraft. They were: (1) integrated systems operation with consistent and simplified cockpit procedures; (2) mission-task-related cockpit displays and controls, and (3) reduced pilot instrument scan effort with excellent outside visibility. The integrated avionics system was implemented to depend heavily upon distributed but complementary processing, multiplex digital bus technology, and multifunction CRT controls and displays. This avionics system was completely flight tested and will soon enter operational service with the Coast Guard.

  20. Effective electromagnetic shielding in multilayer printed circuit boards (United States)

    Wiles, K. G.; Moe, J. L.

    Multilayer printed circuit boards have proven to be recurrent abettors of electromagnetic coupling problems created by the incessantly faster response times in integrated circuit technologies. Coupling within multilayer boards has not only inhibited meeting certain EMI requirements but has also precipitated 'self-inflicted' malfunctions commonly experienced during development of avionic systems. A recent avionic system, interfacing two asynchronous processors through a fourteen-layer motherboard, permitted coupling through ground plane connector apertures of sufficient amplitude and duration as to cause unintentional intercommunication and system malfunctions. The coupling mechanism and ground plane modifications which reduced this coupling by 40 dB and eliminated the incompatibility are discussed in this paper

  1. 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.

  2. Space shuttle main engine hardware simulation (United States)

    Vick, H. G.; Hampton, P. W.


    The Huntsville Simulation Laboratory (HSL) provides a simulation facility to test and verify the space shuttle main engine (SSME) avionics and software system using a maximum complement of flight type hardware. The HSL permits evaluations and analyses of the SSME avionics hardware, software, control system, and mathematical models. The laboratory has performed a wide spectrum of tests and verified operational procedures to ensure system component compatibility under all operating conditions. It is a test bed for integration of hardware/software/hydraulics. The HSL is and has been an invaluable tool in the design and development of the SSME.

  3. 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.

  4. Sistema prototipo Fly-by-Wire


    García Abián, Jonathan


    Este proyecto está destinado a ofrecer una herramienta a la carrera de aeronáutica para realizar experimentos de navegación y seguimiento de aviones, de la forma más real posible. Con este prototipo lo que se pretende es introducir practicas reales a esta carrera. En este documento se presenta un prototipo para guiado de aviones Radio control (RC). Se ha diseñado la implementación de un sistema FLY by WIRE (FbW) reducido, para incorporarlo en un modelo de RC, capaz de recoge...

  5. Multiple IMU system development, volume 1 (United States)

    Landey, M.; Mckern, R.


    A redundant gimballed inertial system is described. System requirements and mechanization methods are defined and hardware and software development is described. Failure detection and isolation algorithms are presented and technology achievements described. Application of the system as a test tool for shuttle avionics concepts is outlined.

  6. Capability Maturity Model (CMM) for Software Process Improvements (United States)

    Ling, Robert Y.


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

  7. 75 FR 30159 - Automatic Dependent Surveillance-Broadcast (ADS-B) Out Performance Requirements To Support Air... (United States)


    ... GNSS--Global Navigation Satellite System GPS--Global Positioning System HAI--Helicopter Association... Which ADS-B is Required 3. Requests for Deviations From ADS-B Out Requirements B. Dual-Link Strategy 1... technology that combines an aircraft's positioning source, aircraft avionics, and a ground infrastructure...

  8. Managing schedule and financial risk in a faster, better, cheaper development (United States)

    Boyd, R. W.


    The X2000 Program is a technology development program that will provide next generation avionics for missions to deep space. The goal of the X2000 Program is to develop revolutionary flight and ground systems which can be replicated by missions at a low cost, affording timely new science and mission opportunities to investigators and institutions.

  9. 76 FR 69709 - 36(b)(1) Arms Sales Notification (United States)


    ... on-board early warning and avionics systems. The AN/ALE-47 uses threat data received over the... modes. Hardware is Unclassified. Technical data and documentation to be provided is Unclassified. 3. The... aircrew. The basic system consists of multiple Optical Sensor Converter (OSC) units, a Computer...

  10. 77 FR 37881 - 36(b)(1) Arms Sales Notification (United States)


    ... and avionics systems. The AN/ALE-47 uses threat data received over the aircraft interfaces to assess... technical data and documentation provided are Unclassified. a. The AN/AAR-47 Missile Warning System is a... multiple Optical Sensor Converter (OSC) units, a Computer Processor (CP) and a Control Indicator (CI)....

  11. Ascending Thermal Localization and Its Strongest Zone Centering by Artificial Neural Networks

    Directory of Open Access Journals (Sweden)

    Ivan Suzdalev


    Full Text Available Thermal localization and their strongest zone centering by artificial neural networks (ANN, and it are used by the automatic or semiautomatic control system of unmanned aerial vehicles (UAV. Artificial neural network take input data from aircraft avionics. Actual thermal model of space and its value’s correlation with other factors are researched as well. Article in Lithuanian

  12. 78 FR 65231 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 series airplanes... (United States)


    ... be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http... engines. Flight controls are fly-by-wire flight with two passive/uncoupled side sticks. Avionics include...-flight fire safety (e.g., toxic gas emission and smoke obscuration) are typically by-products of...

  13. 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.

  14. 75 FR 47249 - Airworthiness Directives; Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440... (United States)


    ... INFORMATION CONTACT: Assata Dessaline, Aerospace Engineer, Avionics and Flight Test Branch, ANE-172, FAA, New... replacement of the harness assembly with tin-plated electrical wires, and the re-orientation of the ADG cannon... 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe...

  15. Sherlock: A Coached Practice Environment for an Electronics Troubleshooting Job. (United States)

    Lesgold, Alan; And Others

    "Sherlock" is a computer-based, supported practice environment for a complex troubleshooting job in Air Force electronics. The program was developed to raise the level of troubleshooting knowledge of avionics technicians. This describes the training problem for which Sherlock was developed, the principles behind its development, and its…

  16. Specially fibers and relevant technologies for fiber optic sensing

    International Nuclear Information System (INIS)

    Fiber optic sensing is one of the most important technologies in phonic sensing. Novel specially fibers and relevant technologies have been developed for various application fields, such as avionics, infrastructures, atomic plants and oil and gas industries. In this paper, recent progress in the fiber optic sensing is reviewed with a focus on the specialty fibers. (author)

  17. Asignación óptima de los asientos de un avión


    Saráchaga Gutiérrez, Fernando


    El presente TFM busca solucionar de manera Óptima asiganción de los asientos de un avion a partir del conocimiento de sus futuras ventas de modo cooperativo empleando técnicas de IO y Estadística.

  18. 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.

  19. Electronics system design techniques for safety critical applications

    CERN Document Server

    Sterpone, Luca


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

  20. 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.

  1. 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.

  2. 78 FR 75284 - Special Conditions: Bombardier Inc., Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Flight... (United States)


    ... the overspeed protection and roll limiting function. The applicable airworthiness regulations do not... the Federal Register published on April 11, 2000 (65 FR 19477-19478), as well as at http://DocketsInfo... side sticks. Avionics includes five landscape primary cockpit displays. The dimension of the...

  3. 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

  4. Research on 14 MeV Neutron Induced Single-event-effects in SRAMs

    Institute of Scientific and Technical Information of China (English)

    FAN; Hui; GUO; Gang; SHEN; Dong-jun; LIU; Jian-cheng


    High energy neutrons are produced in nuclear cascade showers created by nuclear spallation reactions between cosmic rays(mainly protons)and atmospheric nuclei(nitrogen and oxygen).Atmospheric neutrons have been identified as the main cause of single-event-effects(SEE)at elevated altitudes.Avionics are vulnerable to atmospheric neutrons,which can easily produce SEE in

  5. Rotorcraft technology at Boeing Vertol: Recent advances (United States)

    Shaw, John; Dadone, Leo; Wiesner, Robert


    An overview is presented of key accomplishments in the rotorcraft development at Boeing Vertol. Projects of particular significance: high speed rotor development and the Model 360 Advanced Technology Helicopter. Areas addressed in the overview are: advanced rotors with reduced noise and vibration, 3-D aerodynamic modeling, flight control and avionics, active control, automated diagnostics and prognostics, composite structures, and drive systems.

  6. Using Expert Systems For Computational Tasks (United States)

    Duke, Eugene L.; Regenie, Victoria A.; Brazee, Marylouise; Brumbaugh, Randal W.


    Transformation technique enables inefficient expert systems to run in real time. Paper suggests use of knowledge compiler to transform knowledge base and inference mechanism of expert-system computer program into conventional computer program. Main benefit, faster execution and reduced processing demands. In avionic systems, transformation reduces need for special-purpose computers.

  7. 76 FR 17364 - Airworthiness Directives; Dassault-Aviation Model FALCON 7X Airplanes (United States)


    ... certain abnormal conditions while the avionic system switches into landing mode during altitude cruise. * * * * * may cause the crew to be unaware of possible system failures that could require urgent crew's actions.... * * * * * may cause the crew to be unaware of possible system failures that could require urgent crew's...

  8. 15 CFR 738.2 - Commerce Control List (CCL) structure. (United States)


    ... Avionics 8—Marine 9—Propulsion Systems, Space Vehicles and Related Equipment (b) Groups. Within each...) Categories. The CCL is divided into 10 categories, numbered as follows: 0—Nuclear Materials, Facilities and... 1: Missile Technology reasons 2: Nuclear Nonproliferation reasons 3: Chemical & Biological...

  9. 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.

  10. Método Propuesto para Estimar la Altura de Capa de Mezcla en la Atmósfera, con ayuda de la Aviación


    Rodolfo Trejo Vázquez; Leticia Villagómez Parra


    Se presenta un procedimiento, basado en un desarrollo matemático propio, el cual es aplicado al método de Holzworth, para estimar altura de capa de mezcla en la atmósfera utilizando datos proporcionados por aviones comerciales.

  11. "Thumball" Auxiliary Data-Input Device (United States)

    Garner, H. Douglas; Busquets, Anthony M.; Hogge, Thomas W.; Parrish, Russell V.


    Track-ball-type device mounted on joystick and operated by thumb. Thumball designed to enable precise input of data about two different axes to autopilot, avionics computer, or other electronic device without need for operator to remove hands from joystick or other vehicle control levers.

  12. A Stellar Reference Unit Design Study for SIRTF

    DEFF Research Database (Denmark)

    Jørgensen, John Leif; Liebe, Carl Christian


    A design study for a stellar reference unit, or star tracker, for SIRTF was conducted in FY96 in conjunction with the Tracking Sensors Group of the Avionic Equipment Section of JPL. The resulting design was derived from the Oersted, autonomous, Advanced Stellar Compass, star tracker. The projected...

  13. L’objet et le sens anthropologique : deux exemples


    Jacob, Jean-Pierre


    Les rimaïbe, la voiture, l’avion et le vélo « Hanabé Moussa a inventé le fer et parle avec Dieu ; Hanabé Nuhu a construit le bateau et a attendu soixante ans que l’eau arrive jusqu’à lui, il est âgé actuellement de 950 ans ; Hanabé Sulimana a reçu de Dieu l’air qui permet aux voitures, aux avions et aux vélos de se mouvoir. Dieu lui a donné la connaissance des arbres et des plantes. Lorsqu’il se repose les oiseaux font de l’ombre au dessus de sa tête. C’est un demi-dieu, il lui a manqué la ch...

  14. 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.

  15. 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...

  16. 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.

  17. Communication Management Unit : Single Solution of Voice and Data Routing Unit

    Directory of Open Access Journals (Sweden)

    Ravi Shankar


    Full Text Available Challenges faced by present avionics systems are low weight, less power, low volume, high mean time between failure and low mean time to repair. This paper is a feasibility study for single solution of voice and data switching/routing unit. This paper presents a new architecture for voice and data switching unit in the form of communication management unit.  The proposed solution is obtained on integrated modular avionics architecture using commercial-off-the-shelf  hardware. A single board computer is used as a processing engine with add-on audio boards to convert analog voice input and output signals into digital signals.Defence Science Journal, 2013, 63(2, pp.181-185, DOI:

  18. Next Generation Reliable Transport Networks

    DEFF Research Database (Denmark)

    Zhang, Jiang

    -Transport Profile (MPLS-TP) ring networks are addressed. Through the proposed protection structure and protection switching schemes, the recovery mechanism is enhanced in terms of recovery label consumption, operation simplicity and fine traffic engineering granularity. Furthermore, the extensions for existing...... and proposed protection schemes on the interconnected-ring structure are presented, which not only fulfill the requirements suggested by ITU and IETF organizations, but also increase the scalability and applicability of the transport ring networks. Secondly, avionic transport networks are investigated, aiming...... at enabling the full exploitation of key optical networking technologies in future aircrafts. A three-layered optical transport networks over a ring topology is suggested, as it can provide full reconfiguration flexibility and support a wide range of avionic applications. According to different levels...

  19. Optimisation 3D du nez d'un SuperSonic Business Jet basée sur l'adaptation de maillages. Application à la réduction du bang sonique


    Alauzet, Frédéric; Mohammadi, Bijan


    Ce rapport traite d'un problème d'optimisation de forme 3D du nez d'un SuperSonic Business Jet (SSBJ) sous des contraintes aérodynamiques et accoustiques. La contrainte accoustique concerne la génération du bang sonique par l'avion. On présente une méthode d'optimisation de faible dimension pour analyser l'impact du nez sur ces contraintes. Plus précisément, après avoir paramétrisé le nez de l'avion, on échantillonne l'espace de contrôle, puis on construit la surface de réponse qui nous donne...

  20. Aircraft electromagnetic compatibility (United States)

    Clarke, Clifton A.; Larsen, William E.


    Illustrated are aircraft architecture, electromagnetic interference environments, electromagnetic compatibility protection techniques, program specifications, tasks, and verification and validation procedures. The environment of 400 Hz power, electrical transients, and radio frequency fields are portrayed and related to thresholds of avionics electronics. Five layers of protection for avionics are defined. Recognition is given to some present day electromagnetic compatibility weaknesses and issues which serve to reemphasize the importance of EMC verification of equipment and parts, and their ultimate EMC validation on the aircraft. Proven standards of grounding, bonding, shielding, wiring, and packaging are laid out to help provide a foundation for a comprehensive approach to successful future aircraft design and an understanding of cost effective EMC in an aircraft setting.

  1. 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...

  2. On-Board Processor and Network Maturation for Ariane 6 (United States)

    Clavier, Rémi; Sautereau, Pierre; Sangaré, Jérémie; Disson, Benjamin


    In the past three years, innovative avionic technologies for Ariane 6 were evaluated in the tail of three main programs involving various stakeholders: FLPP (Future Launcher Preparatory Program, from ESA), AXE (Avionic-X European, formerly Avionique-X, French public R&T program) and CNES R&T program relying on industrial partnerships. In each avionics’ domain, several technologies were compared, analyzed and tested regarding space launchers system expectations and constraints. Within the frame of on-board data handling, two technologies have been identified as promising: ARM based microprocessors for the computing units and TTEthernet for the on-board network. This paper presents the main outcomes of the data handling preparatory activities performed on the AXE platform in Airbus Defence and Space - Les Mureaux.

  3. Etat d'avancement de la phase d'inclusion de l'étude sommeil


    Evrard, Anne-Sophie


    L'objectif de l'étude sommeil de DEBATS est de caractériser de manière détaillée et spécifique les effets aigus du bruit des avions sur la qualité du sommeil tout en affinant la mesure de l'exposition au bruit. Cette étude permettra également de comparer la pertinence d'indicateurs évènementiels (nombre de survols dépassant 65 dB(A) par exemple) à celle des indicateurs énergétiques (Lden par exemple) pour caractériser plus finement l'exposition au bruit des avions et sa relation avec la quali...

  4. Dynamic partial FPGA reconfiguration in space applications (United States)

    Graczyk, Rafal; Stolarski, Marcin; Palau, Marie-Catherine; Orleanski, Piotr


    Design and implementation of hardware mock-up of high performance system for general avionics testing in reconfigurable FPGAs. Strong emphasis is put on exploiting dynamic partial reconfiguration capability as a method for functionality multiplexing and fault mitigation. Additionally, dynamic reconfiguration can be used for fault injection which makes Single Event Upset in configuration memory simulation possible. LEON3 processors are used to create an avionic systems test-bed, for testing the mock-ups of real system flight software and testing dynamic full and partial reconfiguration. Experiments with different means of reconfiguration are performed to measure reconfiguration times and stability of software. Several solutions for whole system reconfiguration controller have been implemented and tested.

  5. System Software Abstraction Layer - much more than Operating System Abstraction Layer


    Sunita Awasthi Singh; Bineesh P.K.; Satish Shetty K.


    Current and future aircraft systems require real-time embedded software with greater flexibility compared to what was previously available due to the continuous advancements in the technology leading to large and complex systems. Portability of software as one of the aspects of this flexibility is a major concern in application development for avionics domain for fast development and integration of systems. Abstractions of the hardware platform which have been already introduced by the operat...

  6. The reliability analysis of a separated, dual fail operational redundant strapdown IMU. [inertial measurement unit (United States)

    Motyka, P.


    A methodology for quantitatively analyzing the reliability of redundant avionics systems, in general, and the dual, separated Redundant Strapdown Inertial Measurement Unit (RSDIMU), in particular, is presented. The RSDIMU is described and a candidate failure detection and isolation system presented. A Markov reliability model is employed. The operational states of the system are defined and the single-step state transition diagrams discussed. Graphical results, showing the impact of major system parameters on the reliability of the RSDIMU system, are presented and discussed.

  7. Error Propagation in a System Model (United States)

    Schloegel, Kirk (Inventor); Bhatt, Devesh (Inventor); Oglesby, David V. (Inventor); Madl, Gabor (Inventor)


    Embodiments of the present subject matter can enable the analysis of signal value errors for system models. In an example, signal value errors can be propagated through the functional blocks of a system model to analyze possible effects as the signal value errors impact incident functional blocks. This propagation of the errors can be applicable to many models of computation including avionics models, synchronous data flow, and Kahn process networks.

  8. Efficient FPGA implementation and power modelling of image and signal processing IP cores


    Chandrasekaran, Shrutisagar


    This thesis was submitted for the degree of Doctor of Philosophy and awarded by Brunel University. Field Programmable Gate Arrays (FPGAs) are the technology of choice in a number ofimage and signal processing application areas such as consumer electronics, instrumentation, medical data processing and avionics due to their reasonable energy consumption, high performance, security, low design-turnaround time and reconfigurability. Low power FPGA devices are also emerging as competit...

  9. Efeitos da interferência eletromagnética em aeronaves causados por dispositivos eletrônicos portáteis (PEDs)


    André Felipe Henriques Librantz; Hélio Librantz


    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 o...

  10. Low-cost Vision Sensors and Integrated Systems for Unmanned Aerial Vehicle Navigation


    Roberto Sabatini, Celia Bartel, Tesheen Shaid, Anish Kaharkar


    A novel low cost navigation system based on Vision Based Navigation (VBN) and other avionics sensors is presented, which is designed for small size Unmanned Aerial Vehicle (UAV) applications. The main objective of our research is to design a compact, light and relatively inexpensive system capable of providing the required navigation performance in all phases of flight of a small UAV, with a special focus on precision approach and landing, where Vision Based Navigation (VBN) techniques can be...

  11. Portable-Beacon Landing System for Helicopters (United States)

    Davis, Thomas J.; Clary, George R.; Chisholm, John P.; Macdonald, Stanley L.


    Prototype beacon landing system (BLS) allows helicopters to make precise landings in all weather. BLS easily added to existing helicopter avionic equipment and readily deployed at remote sites. Small and light, system employs X-band radar and digital processing. Variety of beams pulsed sequentially by ground station after initial interrogation by weather radar of approaching helicopter. Airborne microprocessor processes pulses to determine glide slope, course deviation, and range.

  12. Using model-driven engineering to support the certification of safety -critical systems



    Critical systems such as those found in the avionics, automotive, maritime, and energy domains are often subject to a formal process known as certification. The goal of certification is to ensure that such systems will operate safely in the presence of known hazards, and without posing undue risks to the users, the public, or the environment. Certification bodies examine such systems based on evidence that the system suppliers provide, to ensure that the relevant safety risks have been suf...

  13. Instrumentation of timed automata for formal verification of timed properties


    Hagman, Mikael


    Embedded systems are used in many technical products of today. The tendency also points to the fact that they are in many ways becoming more and more complex as technology advances. Systems like advanced avionics, air bags, ABS brakes or any real-time embedded system requires reliability, correctness and timeliness. This puts hard pressure on designers, analyzers and developers. The need for high performance and non failing systems has therefore led to a growing interest in modeling and verif...

  14. 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

  15. Testing End-To-End Chains using Domain Specific Languages


    Hartmann, Tobias


    Testing systems is a time consuming (and hence expensive) activity. Nevertheless, it is a very important and necessary step before using systems, especially safety critical systems. Therefore, many different test procedures are used: Unit Tests, Black-Box Tests, Software Integration Tests (SWI), Hardware-Software Integration Tests (HSI), Hardware-In-The-Loop Tests, just to name a few. Especially in the avionics domain, a variety of systems and applications communicate which each other. Furthe...

  16. 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

  17. Quality-Driven Synthesis and Optimization of Embedded Control Systems


    Samii, Soheil


    This thesis addresses several synthesis and optimization issues for embedded control systems. Examples of such systems are automotive and avionics systems in which physical processes are controlled by embedded computers through sensor and actuator interfaces. The execution of multiple control applications, spanning several computation and communication components, leads to a complex temporal behavior that affects control quality. The relationship between system timing and control quality is a...

  18. Investigation into a Layered Approach to Architecting Security-Informed Safety Cases


    Netkachova, K.; Müller, K.; Paulitsch, M.; Bloomfield, R. E.


    The paper describes a layered approach to analysing safety and security in a structured way and creating a security-informed safety case. The approach is applied to a case study – a Security Gateway controlling data flow between two different security domains implemented with a separation kernel based operating system in an avionics environment. We discuss some findings from the case study, show how the approach identifies and ameliorates important interactions between safety and security and...

  19. Survival of Spacecraft-Associated Microorganisms under Simulated Martian UV Irradiation


    Newcombe, David A.; Schuerger, Andrew C.; Benardini, James N.; Dickinson, Danielle; Tanner, Roger; Venkateswaran, Kasthuri


    Spore-forming microbes recovered from spacecraft surfaces and assembly facilities were exposed to simulated Martian UV irradiation. The effects of UVA (315 to 400 nm), UVA+B (280 to 400 nm), and the full UV spectrum (200 to 400 nm) on the survival of microorganisms were studied at UV intensities expected to strike the surfaces of Mars. Microbial species isolated from the surfaces of several spacecraft, including Mars Odyssey, X-2000 (avionics), and the International Space Station, and their a...

  20. 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)

    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

  1. A new acoustic three dimensional intensity and energy density probe


    Ayme, Fabien; Cariou, Charles; Ichchou, Mohamed; Juvé, Daniel


    International audience The acoustic field inside aircraft cavities is very complex. Indeed, there is often a combination of direct, diffuse and modal fields depending on the measurement point and on the frequency band considered. This is directly linked to the fact that different types of sources are present. In such cavities, like a cockpit, sources can be panels radiating not necessary in a normal way, avionics systems, air vents, etc… To find efficient solutions to reduce the noise insi...

  2. Diagnostic d'équipements avioniques par corrélation temporelle


    Lefebvre, Arnaud; Simeu-Abazi, Zineb; Derain, Jean Pierre; Glade, Mathieu


    This article presents a method of diagnosis of avionics equipment based on the temporal correlation of events. A failure is detected thanks to the execution of built-in tests organised in test trees. The method proposed is based on two parameters: the temporal data coming from the test tree execution and the propagation time of failures. The temporal correlation window between the failure messages is obtained thanks to the analysis of the ways of failure propagation. The identification of thi...

  3. An approach to allow safety requirements to be efficiently traced, allocated and validated


    Penna, Achille


    ARP 4754A and ARP 4761 are international standards for the avionics domains. ARP 4761 provides a guidance for the safety assessment process, while the ARP 4754A prescribes close interactions between the safety assessment process and system development process in order to capture safety requirements imposed on the design. According to the ARP 4754A, the safety requirements should be carefully traced and validated.A phase of the safety assessment process is the FHA (Functional Hazard Analysis) ...

  4. Design of self-adaptation in distributed embedded systems


    Weiß, Gereon


    Nowadays, complex computers are integrated in numerous devices and are deployed in diverse application areas, for example in the automotive, avionic, health-care, and industrial automation domain. These embedded systems are evolving towards complex interconnected and adaptive systems. They increasingly integrate more and more functionality and must function under varying conditions and in diverse situations. Therefore, distributed embedded systems become self-adaptive so that they can adjust ...

  5. 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

  6. Computer-aided engineering methods for successful VHSIC application (United States)

    Wood, R. Gary

    Through the example of a VHSIC implementation of a MIL-STD-1750A avionic processor subsystem, an effective approach has applied CAE methods tailored to the job of VHSIC integration. Structured hierarchical design organization combined with rigorous mixed-mode digital simulation permitted an entire VHSIC-based subsystem and its integral application-specific IC design to be verified with a high degree of confidence. Accurate performance data were obtained well in advance of fabrication.

  7. Crafting a Usable Microkernel, Processor, and I/O System with Strict and Provable Information Flow Security


    Tiwari, Mohit; Oberg, Jason K.; Li, Xun; Valamehr, Jonathan; Levin, Timothy; Hardekopf, Ben; Kastner, Ryan; Chong, Frederic T.; Sherwood, Timothy


    High assurance systems used in avionics, medical implants, and cryptographic devices often rely on a small trusted base of hardware and software to manage the rest of the system. Crafting the core of such a system in a way that achieves flexibility, security, and performance requires a careful balancing act. Simple static primitives with hard partitions of space and time are easier to analyze formally, but strict approaches to the problem at the hardware level have been ...

  8. Space Shuttle Usage of z/OS (United States)

    Green, Jan


    This viewgraph presentation gives a detailed description of the avionics associated with the Space Shuttle's data processing system and its usage of z/OS. The contents include: 1) Mission, Products, and Customers; 2) Facility Overview; 3) Shuttle Data Processing System; 4) Languages and Compilers; 5) Application Tools; 6) Shuttle Flight Software Simulator; 7) Software Development and Build Tools; and 8) Fun Facts and Acronyms.

  9. Military display performance parameters (United States)

    Desjardins, Daniel D.; Meyer, Frederick


    The military display market is analyzed in terms of four of its segments: avionics, vetronics, dismounted soldier, and command and control. Requirements are summarized for a number of technology-driving parameters, to include luminance, night vision imaging system compatibility, gray levels, resolution, dimming range, viewing angle, video capability, altitude, temperature, shock and vibration, etc., for direct-view and virtual-view displays in cockpits and crew stations. Technical specifications are discussed for selected programs.

  10. Risk Assessment for Airworthiness Security


    Gil-Casals, Silvia; Owezarski, Philippe; Descargues, Gilles


    International audience The era of digital avionics is opening a fabulous opportunity to improve aircraft operational functions, airline dispatch and service continuity. But arising vulnerabilities could be an open door to malicious attacks. Necessity for security protection on airborne systems has been officially recognized and new standards are actually under construction. In order to provide development assurance and countermeasures effectiveness evidence to certification authorities, se...

  11. Electronics and computer acronyms

    CERN Document Server

    Brown, Phil


    Electronics and Computer Acronyms presents a list of almost 2,500 acronyms related to electronics and computers. The material for this book is drawn from a number of subject areas, including electrical, electronics, computers, telecommunications, fiber optics, microcomputers/microprocessors, audio, video, and information technology. The acronyms also encompass avionics, military, data processing, instrumentation, units, measurement, standards, services, organizations, associations, and companies. This dictionary offers a comprehensive and broad view of electronics and all that is associated wi

  12. Optimal inventories for overhaul of repairable redundant systems - A Markov decision model (United States)

    Schaefer, M. K.


    A Markovian decision model was developed to calculate the optimal inventory of repairable spare parts for an avionics control system for commercial aircraft. Total expected shortage costs, repair costs, and holding costs are minimized for a machine containing a single system of redundant parts. Transition probabilities are calculated for each repair state and repair rate, and optimal spare parts inventory and repair strategies are determined through linear programming. The linear programming solutions are given in a table.

  13. HIL Tuning of UAV for Exploration of Risky Environments


    C. D. Melita; Longo, D.; G. Astuti; Orlando, A.; Muscato, G.


    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 ...

  14. Line search method for solving a non-preemptive strictly periodic scheduling problem


    Pira, Clément; Artigues, Christian


    We study a non-preemptive strictly periodic scheduling problem. This problem arises for example in the avionic eld where a set of N periodic tasks (measure of a sensor, data presentation, etc.) has to be scheduled on P processors distributed on the plane. In this article, we consider an existing heuristic which is based on the notion of equilibrium. Following a game theory analogy, each task tries successively to optimize its own schedule and therefore to produce the best response, given the ...

  15. Navigation systems for approach and landing of VTOL aircraft (United States)

    Schmidt, S. F.; Mohr, R. L.


    The formulation and implementation of navigation systems used for research investigations in the V/STOLAND avionics system are described. The navigation systems prove position and velocity in a cartestian reference frame aligned with the runway. They use filtering techniques to combine the raw position data from navaids (e.g., TACAN, MLS) with data from onboard inertial sensors. The filtering techniques which use both complementary and Kalman filters, are described. The software for the navigation systems is also described.

  16. Development and application of low Reynolds number turbulence models for air-cooled electronics


    Dhinsa, Kulvir Kaur


    Semiconductors are at the heart of electronic devices such as computers, mobile phones, avionics systems, telecommunication racks, etc. Power dissipation from semiconductor devices is continuing to increase due to the growth in the number of transistors on the silicon chip as predicted by Moore's Law. Thermal management techniques, used to dissipate this power, are becoming more and more challenging to design. Air cooling of electronic components is the preferred method for many designs where...

  17. F-5M DTA Program


    Daniel Ferreira V. Mattos; Alberto W. S. Mello Junior; Fabrício N. Ribeiro


    The Brazilian F-5 was submitted to avionics and weapons upgrade. This “new” aircraft has proven to be heavier and more capable. A comprehensive damage tolerance analysis is being performed to evaluate how the new mission profiles and weight distribution may affect the airframe structural integrity. Operational data were collected at the Brazilian Air Force Bases where the fighter is flown. Software was developed in order to acquire, filter and analyze flight data. This data was used for compa...

  18. Histoire de faire l'amour

    Institute of Scientific and Technical Information of China (English)



    A L'UNIVERSITE, je retenais par coeur le verbe aimer, mais je connaissais real l'amour quand il suivait le verbe faire. Les autres étudiants l'ignoraient encore bien plus que moi. Nous avions beau consulter le dictionnaire bilingue, l'expression n'y figurait pas. Notre ignorance persistait.C'était la fin des armées 1970, la Chine venait de s'ouvrir à l'étranger.

  19. 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.

  20. Man-Machine Interface Design for Modeling and Simulation Software


    Arnstein J. Borstad


    Computer aided design (CAD) systems, or more generally interactive software, are today being developed for various application areas like VLSI-design, mechanical structure design, avionics design, cartographic design, architectual design, office automation, publishing, etc. Such tools are becoming more and more important in order to be productive and to be able to design quality products. One important part of CAD-software development is the man-machine interface (MMI) design.

  1. Robustness Evaluation of Software Systems through Fault Injection


    Di Leo, Domenico


    Over the last decades, software has been introduced in desperate safety domains, such as automotive, avionics and railways, just to name a few. For these domains, software is demanded to be highly robust to hardware faults and software faults since its failure may endanger human life, harm the environment, or cause economical loss. Fault injection, the deliberate inoculation of faults, is a powerful means to assess the robustness of software components that goes far beyond traditional test...

  2. Optimal Thermal Design of a Stacked Mini-Channel Heat Sink Cooled by a Low Flow Rate Coolant

    Directory of Open Access Journals (Sweden)

    Jun Wang


    Full Text Available Application requirements for avionics are often very strict. For example, the heat sinks of avionics need very good temperature uniformity, but the flow rate of coolant is very restricted. In addition, the use of micro-channels is not recommended due to the potential clogging issue. Considering these design requirements, we will discuss a multiple-objective optimal design method to obtain a good stacked mini-channel structure for avionics applications. In our thermal design, the design variables are the mini-channel geometry parameters. Temperature uniformity, entropy generation, max temperature of heat sink and pump work are chosen as the objective functions. A Multi Objective Genetic Algorithm (MOGA and Fluent solver are used together to minimize multiple objective functions subject to constraints, and locate the Pareto front. By analyzing the multiple objective optimal results, we can draw the conclusion that the objective functions of Tmax and sg have same effect on the optimization, and the multiple optimal results are a set and not a single value. If mostly focusing on the temperature uniformity, we can recommend some optimal structures to design a stacked mini-channel heat sink.

  3. Network Extender for MIL-STD-1553 Bus (United States)

    Marcus, Julius; Hanson, T. David


    An extender system for MIL-STD-1553 buses transparently couples bus components at multiple developer sites. The bus network extender is a relatively inexpensive system that minimizes the time and cost of integration of avionic systems by providing a convenient mechanism for early testing without the need to transport the usual test equipment and personnel to an integration facility. This bus network extender can thus alleviate overloading of the test facility while enabling the detection of interface problems that can occur during the integration of avionic systems. With this bus extender in place, developers can correct and adjust their own hardware and software before products leave a development site. Currently resident at Johnson Space Center, the bus network extender is used to test the functionality of equipment that, although remotely located, is connected through a MILSTD- 1553 bus. Inasmuch as the standard bus protocol for avionic equipment is that of MIL-STD-1553, companies that supply MIL-STD-1553-compliant equipment to government or industry and that need long-distance communication support might benefit from this network bus extender

  4. A PC based time domain reflectometer for space station cable fault isolation (United States)

    Pham, Michael; McClean, Marty; Hossain, Sabbir; Vo, Peter; Kouns, Ken


    Significant problems are faced by astronauts on orbit in the Space Station when trying to locate electrical faults in multi-segment avionics and communication cables. These problems necessitate the development of an automated portable device that will detect and locate cable faults using the pulse-echo technique known as Time Domain Reflectometry. A breadboard time domain reflectometer (TDR) circuit board was designed and developed at the NASA-JSC. The TDR board works in conjunction with a GRiD lap-top computer to automate the fault detection and isolation process. A software program was written to automatically display the nature and location of any possible faults. The breadboard system can isolate open circuit and short circuit faults within two feet in a typical space station cable configuration. Follow-on efforts planned for 1994 will produce a compact, portable prototype Space Station TDR capable of automated switching in multi-conductor cables for high fidelity evaluation. This device has many possible commercial applications, including commercial and military aircraft avionics, cable TV, telephone, communication, information and computer network systems. This paper describes the principle of time domain reflectometry and the methodology for on-orbit avionics utility distribution system repair, utilizing the newly developed device called the Space Station Time Domain Reflectometer (SSTDR).

  5. Evaluation of Cable Harness Post-Installation Testing. Part B (United States)

    King, M. S.; Iannello, C. J.


    The Cable Harness Post-Installation Testing Report was written in response to an action issued by the Ares Project Control Board (PCB). The action for the Ares I Avionics & Software Chief Engineer and the Avionics Integration and Vehicle Systems Test Work Breakdown Structure (WBS) Manager in the Vehicle Integration Office was to develop a set of guidelines for electrical cable harnesses. Research showed that post-installation tests have been done since the Apollo era. For Ares I-X, the requirement for post-installation testing was removed to make it consistent with the avionics processes used on the Atlas V expendable launch vehicle. Further research for the report involved surveying government and private sector launch vehicle developers, military and commercial aircraft, spacecraft developers, and harness vendors. Responses indicated crewed launch vehicles and military aircraft perform post-installation tests. Key findings in the report were as follows: Test requirements identify damage, human-rated vehicles should be tested despite the identification of statistically few failures, data does not support the claim that post-installation testing damages the harness insulation system, and proper planning can reduce overhead associated with testing. The primary recommendation of the report is for the Ares projects to retain the practice of post-fabrication and post-installation cable harness testing.

  6. Application Research of IP Over IEEE 1394 High-Speed Serial Bus%IP在IEEE1394高速串行总线上的应用研究

    Institute of Scientific and Technical Information of China (English)

    雷宙; 张春熹; 王妍


    High speed data bus technology is one of the core techniques in avionics.IEEE 1394 is a novel high-speed serial data bus,and has been applied in avionics successfully.Its asynchronous transfer mechanism guarantees the reliability of data transferred and is widely used to transfer command and status data.Isochronous transfer also can meet the need of avionics system demanding for real-time transmission of mass data.IP is the basic communication protocols of intemet,using the IP protocol over 1394 and making the best of high speed and reliability of 1394 which will make it widely used.Mainly discuss the necessary methods,data structures and 1394 address resolution protocol(ARP) for the transport of internet protocol datagrams over IEEE 1394.%高速数据总线技术是航空电子中的关键技术之一.IEEE 1394是一种新型的高速串行数据总线,并已成功用于航空电子中.其异步传输保证数据传输的可靠性,广泛用于命令、状态数据的传输;等时传输又能满足航电系统中大容量数据实时传输的需求.IP是互联网中最基本的通信协议,把IP运用在1394串行总线上(IP over 1394),充分利用1394的高速可靠等特点,将使IEEE 1394的应用更加广泛.文中主要讨论了通过1394串行总线传输IP数据包所必然的方法、数据格式和1394 ARP.

  7. 开放式座舱显示系统关键技术研究与实现%Research and Simulation on Open- architect Cockpit Display System

    Institute of Scientific and Technical Information of China (English)

    曹猛; 孙永荣; 王岩; 周晓达; 黄鸣丰


    随着综合化航空电子技术的发展,众多的航空电子设备被开发出来,如何使用一个统一的、开放的显示通信接口变得尤为重要.ARINC 661作为一个标准,对座舱显示系统和用户应用系统进行了定义并规范化,对模块化的航空电子系统的开发具有重要的意义.基于ARINC 661规范,分析研究了开放式CDS(Cockpit Display System)结构,对开放式CDS系统中的窗体部件串行化、ARINC 661指令层实现、坐标系统与部件渲染等关键技术进行了研究,并通过模拟的座舱显示系统进行了实验验证,证明研究所取得的成果是可行的.%As the development of avionic, more and more avionic system was designed. It is very important to use a unified open- architect cockpit display interface. ARINC 661 is a standard which normalizes the interface between CDS (Cockpit Display System) and UA( User Application). This open- architect system is very useful for developing avionic system. This paper is based on ARINC 661 specification and discusses the details of some key techniques including serialization of widgets, ARINC 661 command protocol, coordinate system and rendering widgets of a open- architect CDS. At last it shows a set of UA and CDS software which are running in a emulation environment.

  8. 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.

  9. Traffic Aware Planner (TAP) Flight Evaluation (United States)

    Maris, John M.; Haynes, Mark A.; Wing, David J.; Burke, Kelly A.; Henderson, Jeff; Woods, Sharon E.


    NASA's Traffic Aware Planner (TAP) is a cockpit decision support tool that has the potential to achieve significant fuel and time savings when it is embedded in the data-rich Next Generation Air Transportation System (NextGen) airspace. To address a key step towards the operational deployment of TAP and the NASA concept of Traffic Aware Strategic Aircrew Requests (TASAR), a system evaluation was conducted in a representative flight environment in November, 2013. Numerous challenges were overcome to achieve this goal, including the porting of the foundational Autonomous Operations Planner (AOP) software from its original simulation-based, avionics-embedded environment to an Electronic Flight Bag (EFB) platform. A flight-test aircraft was modified to host the EFB, the TAP application, an Automatic Dependent Surveillance Broadcast (ADS-B) processor, and a satellite broadband datalink. Nine Evaluation Pilots conducted 26 hours of TAP assessments using four route profiles in the complex eastern and north-eastern United States airspace. Extensive avionics and video data were collected, supplemented by comprehensive inflight and post-flight questionnaires. TAP was verified to function properly in the live avionics and ADS-B environment, characterized by recorded data dropouts, latency, and ADS-B message fluctuations. Twelve TAP-generated optimization requests were submitted to ATC, of which nine were approved, and all of which resulted in fuel and/or time savings. Analysis of subjective workload data indicated that pilot interaction with TAP during flight operations did not induce additional cognitive loading. Additionally, analyses of post-flight questionnaire data showed that the pilots perceived TAP to be useful, understandable, intuitive, and easy to use. All program objectives were met, and the next phase of TAP development and evaluations with partner airlines is in planning for 2015.

  10. 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

  11. Midday Meeting- The Noise of Planes

    CERN Multimedia

    Richner; Stucki; Bratschi; Laporte


    Mons.Blackwell demande à Mons.Laporte, chef de la division SP, de présenter les conférenciers: Mons.Marchand, Président de l'association des riverains de l'aèroport et le Docteur Richner, médecin et membre du comité de cette association; Messieurs Stucki et Bratschi prennent aussi la parole. Exposé et questions concernant le bruit des avions et l'effet du bruit à long terme

  12. Contributions to the optimisation of aircraft noise abatement procedures


    Prats i Menéndez, Xavier


    Tot i que en les últimes dècades la reducció del soroll emès pels avions ha estat substancial, el seu impacte a la població ubicada a prop dels aeroports és un problema que encara persisteix. Contenir el soroll generat per les operacions d'aeronaus, tot assumint al mateix temps la creixent demanda de vols, és un dels principals desafiaments a que s'enfronten les autoritats aeroportuàries, els proveïdors de serveis per a la navegació aèria i els operadors de les aeronaus. A part de millorar ...

  13. Estudio, Diseño y Simulación de una Pantala de Vuelo Principal (PFD) para el Simulador de Aviónica de una Cabina de DC-9


    González Cortés, Oliver


    Framed inside the future task set defined by the Project "Design and planning of an avionics system and flying simulator in DC-9", you might find block 4 titled "Digital display of parameters", where steps to include digital data inside the aeronautical cockpit are defined. Within this context, this Final Project is started with the objective to begin the processes that will carry out the digitalization of the DC-9 cockpit, located at the INS Illa Dels Banyols. First of all, an introduction t...

  14. 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

  15. Aerocafé: visión o ilusión para el desarrollo regional


    Duque Escobar, Gonzalo


    Aunque no resulta fácil el ejercicio de la prospectiva en los temas del desarrollo para concebir nuevos proyectos, vale la pena intentar unas miradas a las ventajas del Aeropuerto del Café, dado que los actuales aeropuertos del Eje Cafetero, limitados sólo para aviones medianos o pequeños, no son competitivos, y entonces sólo Aerocafé podría llenar el vacío del Eje Cafetero con una posición de privilegio en el centro de la conurbación Cali-Medellín.

  16. 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.

  17. Quelques cérémonies chez les Oudmourtes du Bachkortostan


    Toulouze, Eva; Niglas, Liivo


    Au cours du mois de juin 2013, nous avons passé un mois dans le village oudmourte de Bal’zuga, au Nord du Bachkortostan dans le raïon de Tatyšly. Les villages oudmourtes de cette région forment une zone compacte où la langue de communication quotidienne, au niveau aussi bien de la famille que du village, de la coopérative de production ou de l’administration, est l’oudmourte. Nous avions, en venant ici, un objectif précis. Le mois de juin en effet, le mois du solstice, marquant la fin des tra...

  18. Conception intégrée par optimisation multicritère d'un système d’actionnement électrique pour l’aéronautique


    De Andrade, André; Sareni, Bruno; Roboam, Xavier; Couderc, Mathieu; Ruelland, Régis


    Le développement des systèmes embarqués, suivant la tendance vers l'avion plus électrique (More Electric Aircraft), présente de nouveaux défis technologiques parmi lesquels se trouvent l'électrification de certaines "grosses charges" telles que les compresseurs de conditionnement d’air ECS (Environmental Conditioning Systems). Un modèle de dimensionnement de la chaîne de conversion électromécanique (filtre d'entrée / onduleur / moteur / mission de vol) a été développé et adapté à la haute vit...

  19. Sistemas de comunicaciones para vuelos no tripulados


    Correa Vila, Alejandro


    La iniciativa ATLANTIDA engloba numerosos estudios de ingeniería con el objetivo de reformar el actual sistema de gestión del tráfico aéreo. Dentro de estos estudios se encuentran diversas investigaciones en el campo de las comunicaciones móviles. La gran variabilidad del entorno aeronáutico promueve el estudio de sistemas de comunicaciones móviles capaces de funcionar en este tipo de entorno. Este proyecto propone un sistema de comunicaciones WiMAX en un entorno aeronáutico con aviones no tr...

  20. Control Actiu en AFDX i Modelització d'ARINC 653


    Ruiz De Azúa Ortega, Juan Adrián


    El proyecto se basa en un análisis sobre la tecnología AVB (Audio/Video Bridging) para ser capaces de caracterizar el delay máximo y así el comportamiento en situaciones crítica The presented work is oriented on explain the experience of the investigation performed on the embedded systems field. Concretely, the investigation is composed of two standards: ARINC 664 and ARINC 653. The investigation about the standard ARINC 664 Part 7, called Avionic Full Duplex Switched Ethernet (AFDX), is o...

  1. Star pattern recognition method based on neural network

    Institute of Scientific and Technical Information of China (English)

    LI Chunyan; LI Ke; ZHANG Longyun; JIN Shengzhen; ZU Jifeng


    Star sensor is an avionics instrument used to provide the absolute 3-axis attitude of a spacecraft by utilizing star observations. The key function is to recognize the observed stars by comparing them with the reference catalogue. Autonomous star pattern recognition requires that similar patterns can be distinguished from each other with a small training set. Therefore, a new method based on neural network technology is proposed and a recognition system containing parallel backpropagation (BP) multi-subnets is designed. The simulation results show that the method performs much better than traditional algorithms and the proposed system can achieve both higher recognition accuracy and faster recognition speed.

  2. Using today's Strategic Defense Initiative (SDI) technologies to accomplish tomorrow's low cost space missions (United States)

    Farmer, Dean A.


    The various core technologies developed from the SDI programs are described and the cost and weight reductions that have resulted from the systematic exploitation of today's aerospace expertise are characterized. Avionics, sensors, and on-orbit propulsion systems can be utilized in developing small, low-cost devices for space exploration with significant performance capabilities. It is shown how the resulting core technologies can be employed in constructing three specific types of miniaturized spacecraft: a 16 kg planetary rover, a 200 kg lunar lander, and a 45 kg space vehicle repair and rescue craft.

  3. De la foi du charbonnier �� celle du héros (et retour

    Directory of Open Access Journals (Sweden)

    Alain Mothu


    Full Text Available « Si nous avions une seule goute de foy, nous remuerions les montagnes de leur place, dict la saincte parole : nos actions, qui seroient guidées et accompaignées de la divinité, ne seroient pas simplement humaines ; elles auroient quelque chose de miraculeux comme nostre croyance. Brevis est institutio vitae beataeque, si credas » (Montaigne, Essais, II, 12, éd. Villey, p. 442.La « foi du charbonnier », ou fides carbonarii / fides carbonaria, the collier’s creed en anglais, der Köhlerglaube ...

  4. The Efficacy of DO-178B


    Daniels, Dewi


    DO-178B was based on the consensus of the avionic software community as it existed in 1992. Twenty two years after publication, we have no publically available experimental data as to its efficacy. It appears to work extremely well, since there have been no hull loss accidents in passenger service ascribed to software failure. This is a comforting and surprising result. However, if we don't know why DO-178B works so well, there is a danger that we could stop doing something that really matter...

  5. 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

  6. Etude des performances et optimisation d'un réseau d'accès par satellite pour les communications


    Tao, Na


    La croissance rapide du trafic aérien et les besoins en nouveaux services notamment pour les passagers imposent l'introduction de nouveaux moyens de communication pour les avions avec une bande passante globale fortement accrue. Les satellites sont appelés à jouer un rôle important dans ce contexte, non seulement en complément des systèmes terrestres pour les services « cockpit » (services ATM, Air Traffic Management) mais aussi pour les services « cabine » (In-Flight Entertainment). L'object...

  7. 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

  8. Computer technology forecast study for general aviation (United States)

    Seacord, C. L.; Vaughn, D.


    A multi-year, multi-faceted program is underway to investigate and develop potential improvements in airframes, engines, and avionics for general aviation aircraft. The objective of this study was to assemble information that will allow the government to assess the trends in computer and computer/operator interface technology that may have application to general aviation in the 1980's and beyond. The current state of the art of computer hardware is assessed, technical developments in computer hardware are predicted, and nonaviation large volume users of computer hardware are identified.

  9. 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.

  10. Création d’applications mobiles via une application Java.




    Au cours de ce modeste travail, nous avions comme objectif principal de réaliser une application JAVA Desktop en respectant l'hiérarchie de l'approche IDM. La particularité de notre travail était dans la manière d’établir une liaison entre l'abstraction de l'ingénierie dirigé par les modèles et de la concrétisé en une application. L’objectif principal est le développement d’une application qui permet aux « utilisateurs ordinaires » de gé...

  11. 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.

  12. Optimal maintenance center inventories for fault-tolerant repairable systems (United States)

    Lawrence, S. H.; Schaefer, M. K.


    A probabilistic approach is taken to determine the optimal repairable parts inventory for a maintenance center, servicing machines which contain several m-out-of-n systems of different parts, with a constraint on the total inventory investment. A model, based on the discrete Markov process, accounts for a typical ultrareliable avionics system, such as one presently being developed by NASA. The dynamic programming algorithm for minimizing the stockout and holding costs is applied to an exemplary maintenance center, and solutions for single-item and multi-item cases are given. The computational burden is noted to be reasonable and a computer program is used to generate optimal solutions.

  13. Entretien avec Ully Pickard


    Niogret, Hubert


    À l’occasion d’un entretien-témoignage pour un documentaire sur Jacques Becker, nous avions rencontré Ully Pickard, assistant de production ou assistant-réalisateur qui avait travaillé avec Jacques Becker (Casque d’or), Robert Siodmak, Max Ophuls, René Clément, Luis Buñuel (pour des films produits en France), et qui au moment de cet entretien était toujours le collaborateur du producteur Serge Silbermann. Parlant de la flexibilité de Becker et de sa faculté d’adaptation aux conditions de tour...

  14. 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.

  15. Plan for the Characterization of HIRF Effects on a Fault-Tolerant Computer Communication System (United States)

    Torres-Pomales, Wilfredo; Malekpour, Mahyar R.; Miner, Paul S.; Koppen, Sandra V.


    This report presents the plan for the characterization of the effects of high intensity radiated fields on a prototype implementation of a fault-tolerant data communication system. Various configurations of the communication system will be tested. The prototype system is implemented using off-the-shelf devices. The system will be tested in a closed-loop configuration with extensive real-time monitoring. This test is intended to generate data suitable for the design of avionics health management systems, as well as redundancy management mechanisms and policies for robust distributed processing architectures.

  16. Impact of emerging technologies on future combat aircraft agility (United States)

    Nguyen, Luat T.; Gilert, William P.


    The foreseeable character of future within-visual-range air combat entails a degree of agility which calls for the integration of high-alpha aerodynamics, thrust vectoring, intimate pilot/vehicle interfaces, and advanced weapons/avionics suites, in prospective configurations. The primary technology-development programs currently contributing to these goals are presently discussed; they encompass the F-15 Short Takeoff and Landing/Maneuver Technology Demonstrator Program, the Enhanced Fighter Maneuverability Program, the High Angle-of-Attack Technology Program, and the X-29 Technology Demonstrator Program.

  17. 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.

  18. the APL Balloonborne High Altitude Research Platform (HARP) (United States)

    Adams, D.; Arnold, S.; Bernasconi, P.


    The Johns Hopkins University Applied Physics Laboratory (APL) has developed and demonstrated a multi-purpose stratospheric balloonborne gondola known as the High Altitude Research Platform (HARP). HARP provides the power, mechanical supports, thermal control, and data transmission for multiple forms of high-altitude scientific research equipment. The platform has been used for astronomy, cosmology and heliophysics experiments but can also be applied to atmospheric studies, space weather and other forms of high altitude research. HARP has executed five missions. The first was Flare Genesis from Antarctica in 1993 and the most recent was the Balloon Observation Platform for Planetary Science (BOPPS) from New Mexico in 2014. HARP will next be used to perform again the Stratospheric Terahertz Observatory mission, a mission that it first performed in 2009. The structure, composed of an aluminum framework is designed for easy transport and field assembly while providing ready access to the payload and supporting avionics. A light-weighted structure, capable of supporting Ultra-Long Duration Balloon (ULDB) flights that can last more than 100 days is available. Scientific research payloads as heavy as 600 kg (1322 pounds) and requiring up to 800 Watts electrical power can be supported. The platform comprises all subsystems required to support and operate the science payload, including both line-of-sight (LOS) and over-the-horizon (0TH) telecommunications, the latter provided by Iridium Pilot. Electrical power is produced by solar panels for multi-day missions and batteries for single-day missions. The avionics design is primarily single-string; however, use of ruggedized industrial components provides high reliability. The avionics features a Command and Control (C&C) computer and a Pointing Control System (PCS) computer housed within a common unpressurized unit. The avionics operates from ground pressure to 2 Torr and over a temperature range from —30 C to +85 C

  19. Small UAV Research and Evolution in Long Endurance Electric Powered Vehicles (United States)

    Logan, Michael J.; Chu, Julio; Motter, Mark A.; Carter, Dennis L.; Ol, Michael; Zeune, Cale


    This paper describes recent research into the advancement of small, electric powered unmanned aerial vehicle (UAV) capabilities. Specifically, topics include the improvements made in battery technology, design methodologies, avionics architectures and algorithms, materials and structural concepts, propulsion system performance prediction, and others. The results of prototype vehicle designs and flight tests are discussed in the context of their usefulness in defining and validating progress in the various technology areas. Further areas of research need are also identified. These include the need for more robust operating regimes (wind, gust, etc.), and continued improvement in payload fraction vs. endurance.

  20. Orbital Spacecraft Consumables Resupply System (OSCRS). Volume 3: Program Cost Estimate (United States)

    Perry, D. L.


    A cost analysis for the design, development, qualification, and production of the monopropellant and bipropellant Orbital Spacecraft Consumable Resupply System (OSCRS) tankers, their associated avionics located in the Orbiter payload bay, and the unique ground support equipment (GSE) and airborne support equipment (ASE) required to support operations is presented. Monopropellant resupply for the Gamma Ray Observatory (GRO) in calendar year 1991 is the first defined resupply mission with bipropellant resupply missions expected in the early to mid 1990's. The monopropellant program estimate also includes contractor costs associated with operations support through the first GRO resupply mission.

  1. Propagation mechanism for a non-preemptive strictly periodic scheduling problem


    Pira, Clément; Artigues, Christian


    We study a non-preemptive strictly periodic scheduling prob- lem. This problem, introduced in [6, 4], arises for example in the avionic field where a set of N periodic tasks (measure of a sensor, etc.) has to be scheduled on P processors distributed on the plane. In the related fi eld of cyclic scheduling, some notable success has been recently achieved through the use of speci c constraint propagation. In this article, we consider a heuristic, first proposed by Al Sheikh et al. 2012, which i...

  2. Mini UAV VTOL control design


    Poinsot, Damien


    A l'heure actuelle, de nombreux projets d'utilisation de drones s'intéressent à la capacité des véhicules à alterner des phases de vols lentes et des phases de vol rapides. Cela permet entre autre, de traiter une plus grande diversité de missions que celles pouvant être accomplies par des avions conventionnels (approche de bâtiments, évolution en milieu urbain, prises de vue). Cette thèse s'intéresse à la commande de ce type de vecteur, avec l'application au VERTIGO, drone de type VTOL a roto...

  3. 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!

  4. Ground Demonstration of Synchronized Formation Rotations for Precision, Multi-Spacecraft Interferometers (United States)

    Scharf, Daniel P.; Keim, Jason A.; Hadaegh, Fred Y.


    This paper reports the ground demonstration of precision synchronized formation rotations with better than 6 arcmin/5 cm performance in the Formation Control Testbed (FCT). The FCT currently consists of two, five degree-of-freedom, air bearing-levitated robots. The sixth degree-of-freedom, vertical translation, is being added in November 2007. Each robot has a suite of flight-like avionics and actuators, including a star tracker, fiber-optic gyroscopes, reaction wheels, cold-gas thrusters, inter-robot communication, and on-board computers that run the Formation and Attitude Control System software.

  5. 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.

  6. Pyroshock testing: Effects of equipment simulators (United States)

    Hughes, William O.


    It is critical to a spacecraft's mission success that flight equipment be properly qualified to its expected shock environment. Simulators of varying fidelity are often used to measure the shock levels during spacecraft shock tests. Pyroshock test data from a recent spacecraft separation test will be shown that illustrates how shock response spectra differ for avionics equipment simulators of both low and high fidelity. The effect of the simulator weight on the shock response will also be shown. Additionally, data showing the attenuation of pyroshock levels, including its reduction with distance and across joints will be discussed. This observed attenuation data generally supports the standard methodologies for predictions of shock attenuation.

  7. Advanced space recovery systems (United States)

    Wailes, William K.


    The design evolution of a space recovery system designed by a NASA-contracted study is described, with particular attention given to the design of a recovery system for a propulsion/avionics module (P/AM), which weighs 60,000 lb at the recovery initiation and achieves subsonic terminal descent at or above 50,000 ft msl. The components of the recovery system concept are described together with the operational sequences of the recovery. The recovery system concept offers low cost, low weight, good performance, a potential for pinpoint landing, and an operational flexibility.

  8. SEPS guidance and navigation autonomy selection via mission analysis. [Solar Electric Propulsion Stage for Space Transportation System (United States)

    Causey, W.; Sohoni, V.; Shenfish, K. L.; Wallace, C. T.


    A systematic rationale for selecting a cost-effective guidance and navigation (G & N) autonomy level for the solar electric propulsion stage (SEPS) vehicle is developed. After a definition of autonomy levels, a mission analysis is performed for representative SEPS missions using realistic G & N sensor hardware. Cost data for fabricating, integrating and refurbishing onboard avionics hardware and the ground costs corresponding to each autonomy level are generated. Results are presented that indicate performance of various G & N sensor hardware sets and the dominating factors which influence G & N autonomy level selection.

  9. 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.

  10. Autonomous, agile micro-satellites and supporting technologies

    International Nuclear Information System (INIS)

    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

  11. Integrated Station Executive requirements and systems design approach (United States)

    Berger, Eugene L.; Morris, C. Doug


    The Avionics Office of the Space Station Projects Office at Johnson Space Center (JSC) is working to define and integrate end-to-end requirements for the Space Station Freedom Program (SSFP) space-ground operations. As part of these efforts, the project office has had the MITRE Corporation perform assessments and analyses in areas where they had particular concern. These areas include the changing concepts for test methodologies, the operation and performance of the communication protocols, end-to-end network management, and the Master Objects Data Base (MODB). Since the recent restructure of the space station design, a new software application, the Integrated Station Executive (ISE), has been established. This application is to act as an executive agent along with the crew and ground controllers, while replacing (or absorbing) many of the system management functions that required a home when distributed element management was eliminated. This document summarizes the current state of the ISE requirements and assesses the characteristics of the current design. MITRE's goals in this assessment and analysis is twofold: first, identify any internal inconsistencies in either the requirements or in the current design; and second, to examine the applicability of the Open System Interconnection (OSI) management standards. Inasmuch as the ISE has been defined as the executive or operations manager application within the integrated avionics of the space station, special attention is given to adapting OSI management for the specification of the ISE functions.

  12. Implementation of Ada protocols on Mil-STD-1553 B data bus (United States)

    Ruhman, Smil; Rosemberg, Flavia


    Standardization activity of data communication in avionic systems started in 1968 for the purpose of total system integration and the elimination of heavy wire bundles carrying signals between various subassemblies. The growing complexity of avionic systems is straining the capabilities of MIL-STD-1553 B (first issued in 1973), but a much greater challenge to it is posed by Ada, the standard language adopted for real-time, computer embedded-systems. Hardware implementation of Ada communication protocols in a contention/token bus or token ring network is proposed. However, during the transition period when the current command/response multiplex data bus is still flourishing and the development environment for distributed multi-computer Ada systems is as yet lacking, a temporary accomodation of the standard language with the standard bus could be very useful and even highly desirable. By concentrating all status informtion and decisions at the bus controller, it was found to be possible to construct an elegant and efficient harware impelementation of the Ada protocols at the bus interface. This solution is discussed.

  13. A hazard analysis via an improved timed colored petri net with time-space coupling safety constraint

    Institute of Scientific and Technical Information of China (English)

    Li Zelin; Wang Shihai; Zhao Tingdi; Liu Bin


    Petri nets are graphical and mathematical tools that are applicable to many systems for modeling, simulation, and analysis. With the emergence of the concept of partitioning in time and space domains proposed in avionics application standard software interface (ARINC 653), it has become difficult to analyze time–space coupling hazards resulting from resource partitioning using classical or advanced Petri nets. In this paper, we propose a time–space coupling safety constraint and an improved timed colored Petri net with imposed time–space coupling safety constraints (TCCP-NET) to fill this requirement gap. Time–space coupling hazard analysis is conducted in three steps: specification modeling, simulation execution, and results analysis. A TCCP-NET is employed to model and analyze integrated modular avionics (IMA), a real-time, safety-critical system. The analysis results are used to verify whether there exist time–space coupling hazards at runtime. The method we propose demonstrates superior modeling of safety-critical real-time systems as it can specify resource allocations in both time and space domains. TCCP-NETs can effectively detect underlying time–space coupling hazards.

  14. 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.

  15. Flight Guidance System Requirements Specification (United States)

    Miller, Steven P.; Tribble, Alan C.; Carlson, Timothy M.; Danielson, Eric J.


    This report describes a requirements specification written in the RSML-e language for the mode logic of a Flight Guidance System of a typical regional jet aircraft. This model was created as one of the first steps in a five-year project sponsored by the NASA Langley Research Center, Rockwell Collins Inc., and the Critical Systems Research Group of the University of Minnesota to develop new methods and tools to improve the safety of avionics designs. This model will be used to demonstrate the application of a variety of methods and techniques, including safety analysis of system and subsystem requirements, verification of key properties using theorem provers and model checkers, identification of potential sources mode confusion in system designs, partitioning of applications based on the criticality of system hazards, and autogeneration of avionics quality code. While this model is representative of the mode logic of a typical regional jet aircraft, it does not describe an actual or planned product. Several aspects of a full Flight Guidance System, such as recovery from failed sensors, have been omitted, and no claims are made regarding the accuracy or completeness of this specification.

  16. VHDL Implementation and Verification of ARINC-429 Core

    CERN Document Server

    Kamaraju, M; Kishore, K Lal; Baburao, K


    Modern Avionics are controlled by sophisticated mission components in the Aircraft. The control function is implemented via a standard ARINC-429 bus interface. It is a two-wire point-topoint serial data bus for control communications in Avionics. The bus operates 12.5 or 100kb/sec, the implementation is envisaged for one transmits and receive channel respectively. Further the code can be modified for more no of independent Tx and Rx channels. An on chip memory allotment on the FPGA will provide a buffer bank for storing the incoming or outgoing data. For this purpose SRAM based FPGAs are utilized. This flexible ARINC429 solution gives exactly what is needed for real time applications. The IP can be programmed to send an interrupt to the host and also prepare it to process the data. Majority of the hardware function of digital natures are embedded into a single FPGA by saving in terms of PCB board space, power consumption and volume results. This paper deals with the development, implementation, simulation, an...

  17. Autonomous, agile micro-satellites and supporting technologies

    Energy Technology Data Exchange (ETDEWEB)

    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.

  18. Evolution of a 100 Mpbps fiber optic serial data bus for aerospace applications (United States)

    Uhlhorn, R. W.; Geeslin, A. E.; Otten, T. H.

    Future aircraft and spacecraft will incorporate high speed data buses connecting avionics subsystems immersed in an electromagnetically hostile environment. The benefits of using fiber optics as the data transfer medium of choice for such systems are well known. Anticipating the use of high speed fiber optic data buses in avionics systems of the future, a company-sponsored program was initiated to explore component-through-system aspects of the technology. This paper describes the evolutionary steps in the development of a 100 Mbps Serial Fiber Optic Data Bus for aerospace applications. Beginning with a discussion of several possible protocols and applications, the development of each major subsystem is discussed. A token passing protocol is used to maximize bus efficiency. Development hardware supporting a 32 terminal network including an LED transmitter, APD receiver and user interface equipment, as well as test results from evaluation of the bus receivers and transmitters in a bus signaling environment, are described. Testing methods are discussed and test results are presented.

  19. 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.

  20. Advances in Atmospheric Radiation Measurements and Modeling Needed to Improve Air Safety (United States)

    Tobiska, W. Kent; Atwell, William; Beck, Peter; Benton, Eric; Copeland, Kyle; Dyer, Clive; Gersey, Brad; Getley, Ian; Hands, Alex; Holland, Michael; Hong, Sunhak; Hwang, Junga; Jones, Bryn; Malone, Kathleen; Meier, Matthias M.; Mertens, Chris; Phillips, Tony; Ryden, Keith; Schwadron, Nathan; Wender, Stephen A.; Wilkins, Richard; Xapsos, Michael A.


    Air safety is tied to the phenomenon of ionizing radiation from space weather, primarily from galactic cosmic rays but also from solar energetic particles. A global framework for addressing radiation issues in this environment has been constructed, but more must be done at international and national levels. Health consequences from atmospheric radiation exposure are likely to exist. In addition, severe solar radiation events may cause economic consequences in the international aviation community due to exposure limits being reached by some crew members. Impacts from a radiation environment upon avionics from high-energy particles and low-energy, thermalized neutrons are now recognized as an area of active interest. A broad community recognizes that there are a number of mitigation paths that can be taken relative to the human tissue and avionics exposure risks. These include developing active monitoring and measurement programs as well as improving scientific modeling capabilities that can eventually be turned into operations. A number of roadblocks to risk mitigation still exist, such as effective pilot training programs as well as monitoring, measuring, and regulatory measures. An active international effort toward observing the weather of atmospheric radiation must occur to make progress in mitigating radiation exposure risks. Stakeholders in this process include standard-making bodies, scientific organizations, regulatory organizations, air traffic management systems, aircraft owners and operators, pilots and crew, and even the public.

  1. Making the Mission Computer Intelligent – A Step Ahead

    Directory of Open Access Journals (Sweden)

    R. Pitchammal


    Full Text Available Increasing the complexity of fighter aircraft like modern cockpit environments, covering highly integrated, and complex automatic functions, pose various demands on the crew and adding a heavy workload. Cognitive systems appear to be a promising approach to overcome these deficiencies in future combat aircraft. Developing human-centered automation and designing advanced technology that will capitalize on the relative strengths of humans and machines, are key to the success. This paper presents the approach of applying the artificial intelligence (AI techniques in the critical mission computer (MC. The mission computer is the central controller of the entire avionics and acts as the front end to the pilot and all other avionic systems  by providing all the sensors information, presenting the pilot-vehicle interface and thereby helping a lot in reducing the heavy workload of the pilot. Hence cognitive processing in the MC will make MC to act as an electronic crew assistant sharing the workload of the pilot and helping him in severe situations. Intricate aircraft systems increase the need for intelligent cooperation between pilots and aircraft which will be fulfilled by making the MC as smart or intelligent MC.Defence Science Journal, 2013, 63(2, pp.174-180, DOI:

  2. 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.

  3. In-flight fiber optic acoustic emission sensor (FAESense) system for the real time detection, localization, and classification of damage in composite aircraft structures (United States)

    Mendoza, Edgar; Prohaska, John; Kempen, Connie; Esterkin, Yan; Sun, Sunjian


    Acoustic emission sensing is a leading structural health monitoring technique use for the early warning detection of structural damage associated with impacts, cracks, fracture, and delaminations in advanced materials. Current AE systems based on electronic PZT transducers suffer from various limitations that prevent its wide dynamic use in practical avionics and aerospace applications where weight, size and power are critical for operation. This paper describes progress towards the development of a wireless in-flight distributed fiber optic acoustic emission monitoring system (FAESense™) suitable for the onboard-unattended detection, localization, and classification of damage in avionics and aerospace structures. Fiber optic AE sensors offer significant advantages over its counterpart electronic AE sensors by using a high-density array of micron-size AE transducers distributed and multiplex over long lengths of a standard single mode optical fiber. Immediate SHM applications are found in commercial and military aircraft, helicopters, spacecraft, wind mil turbine blades, and in next generation weapon systems, as well as in the petrochemical and aerospace industries, civil structures, power utilities, and a wide spectrum of other applications.

  4. Advanced integrated enhanced vision systems (United States)

    Kerr, J. R.; Luk, Chiu H.; Hammerstrom, Dan; Pavel, Misha


    In anticipation of its ultimate role in transport, business and rotary wing aircraft, we clarify the role of Enhanced Vision Systems (EVS): how the output data will be utilized, appropriate architecture for total avionics integration, pilot and control interfaces, and operational utilization. Ground-map (database) correlation is critical, and we suggest that "synthetic vision" is simply a subset of the monitor/guidance interface issue. The core of integrated EVS is its sensor processor. In order to approximate optimal, Bayesian multi-sensor fusion and ground correlation functionality in real time, we are developing a neural net approach utilizing human visual pathway and self-organizing, associative-engine processing. In addition to EVS/SVS imagery, outputs will include sensor-based navigation and attitude signals as well as hazard detection. A system architecture is described, encompassing an all-weather sensor suite; advanced processing technology; intertial, GPS and other avionics inputs; and pilot and machine interfaces. Issues of total-system accuracy and integrity are addressed, as well as flight operational aspects relating to both civil certification and military applications in IMC.

  5. 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

  6. 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

  7. 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

  8. 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

  9. Rapid, optical measurement of the atmospheric pressure on a fast research aircraft using open-path TDLAS

    Directory of Open Access Journals (Sweden)

    B. Buchholz


    Full Text Available Because of the high travel speed, the complex flow dynamics around an aircraft and the complex dependency of the fluid dynamics on numerous airborne parameters, it is quite difficult to obtain accurate pressure values at a specific instrument location of an aircraft's fuselage. Complex simulations using computational fluid dynamics (CFD models can in theory computationally "transfer" pressure values from one location to another. However, for long flight patterns, this process is inconvenient and cumbersome. Furthermore these CFD transfer models require a local experimental validation, which is rarely available. In this paper, we describe an integrated approach for a spectroscopic, calibration-free, in-flight pressure determination in an open-path White cell on an aircraft fuselage using ambient, atmospheric water vapour as the "sensor species". The presented measurements are realized with the HAI (Hygrometer for Atmospheric Investigations instrument, built for multiphase water detection via calibration-free TDLAS (tunable diode laser absorption spectroscopy. The pressure determination is based on raw data used for H2O concentration measurement, but with a different post-flight evaluation method, and can therefore be conducted at deferred time intervals on any desired flight track. The spectroscopic pressure is compared in-flight with the static ambient pressure of the aircraft avionic system and a micro-mechanical pressure sensor, located next to the open-path cell, over a pressure range from 150 hPa to 800 hPa, and a water vapour concentration range of more than three orders of magnitude. The correlation between the micro-mechanical pressure sensor measurements and the spectroscopic pressure measurements show an average deviation from linearity of only 0.14% and a small offset of 9.5 hPa. For the spectroscopic pressure evaluation we derive measurement uncertainties under laboratory conditions of 3.2% and 5.1% during in flight operation on the

  10. Specification and Verification of Distributed Embedded Systems: A Traffic Intersection Product Family

    Directory of Open Access Journals (Sweden)

    José Meseguer


    Full Text Available Distributed embedded systems (DESs are no longer the exception; they are the rule in many application areas such as avionics, the automotive industry, traffic systems, sensor networks, and medical devices. Formal DES specification and verification is challenging due to state space explosion and the need to support real-time features. This paper reports on an extensive industry-based case study involving a DES product family for a pedestrian and car 4-way traffic intersection in which autonomous devices communicate by asynchronous message passing without a centralized controller. All the safety requirements and a liveness requirement informally specified in the requirements document have been formally verified using Real-Time Maude and its model checking features.

  11. Određivanje buke radi sertifikacije mlaznih aviona / Procedures in the noise certification of jet aircraft

    Directory of Open Access Journals (Sweden)

    Gordana Jurin


    Full Text Available U radu su prikazane osnovne teorijske postavke i matematički modeli koji su značajni za obradu akustičkih i neakustičkih podataka u procesu određivanja buke mlaznih aviona prema međunarodnom standardu ICAO, Annex 16, za potrebe sertiflkacije. Proces obuhvata i postupak eliminacije efekata ambijentalnog šuma iz signala avionske buke. Kao primer, data je praktična primena navedenog postupka na rezultate merenja za avion G-2A. / This paper presents a basic theoretical scheme and a mathematical model that is used to calculate jet aircraft noise level for certification purposes in accordance with the international standard ICAO Annex 16. In this process acoustic and nonacoustic data are used. The process also includes the procedure for eliminating ambient noise effects out of the aircraft noise signal. This procedure was applied in the case of noise measurement results for the G-2Ajet aircraft.

  12. Ciudad Juárez, un terrain de recherche


    Zamorano-Villarreal, Claudia Carolina


    Il est sept heures du matin, un jour de septembre 1994. Dans l'avion Mexico/Ciudad Juárez, une voix féminine annonce l'arrivée à destination dans vingt minutes. Par la fenêtre, on aperçoit un ciel bleu-rouge intense, caractéristique des levers de soleil dans les zones désertiques, la terre érodée du désert du Chihuahua et quelques chemins de terre qui vont vers des routes inconnues. Pas une ville, pas un village n'apparaît dans le champ de vision. Il n'y a que le désert, un désert triste et é...


    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

  14. Lessons Learned from the 787 Dreamliner Issue on Lithium-Ion Battery Reliability

    Directory of Open Access Journals (Sweden)

    Michael Pecht


    Full Text Available On 16 January 2013, all Boeing 787 Dreamliners were indefinitely grounded due to lithium-ion battery failures that had occurred in two planes. Subsequent investigations into the battery failures released through the National Transportation Safety Board (NTSB factual report, the March 15th Boeing press conference in Japan, and the NTSB hearings in Washington D.C., never identified the root causes of the failures—a major concern for ensuring safety and meeting reliability expectations. This paper discusses the challenges to lithium-ion battery qualification, reliability assessment, and safety in light of the Boeing 787 battery failures. New assessment methods and control techniques that can improve battery reliability and safety in avionic systems are then presented.

  15. Considerations for NATO satellite communications in the post-2000 era (United States)

    Ince, A. Nejat


    The National Delegates Board of AGARD, upon recommendation by the Avionics Panel of AGARD, approved in March 1986 the establishment of WG-13 to study satellite communications for NATO under the direction of Prof. Dr. Nejat Ince of Turkey. Some 14 scientists/engineers, from research and industrial establishments of Canada, France, the Federal Republic of Germany, Norway, Turkey, the United Kingdom, the United States of America as well as from International Military Staff of NATO and SHAPE Technical Centre, participated in the work of WG-13. This paper is a brief summary of the studies carried out by the group in the period 1988-1990 on the type of satellite communication systems which NATO can have in the post-2000 era including the critical techniques and technologies that need to be developed for this purpose.

  16. 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-...

  17. Art rupestre préhistorique au Yémen

    Directory of Open Access Journals (Sweden)

    Michel-Alain Garcia


    Full Text Available Afin de compléter notre documentation, nous avions projeté pour cette année une courte mission à Saada sur les sites déjà étudiés les années passées. C'est le récit d'un militaire ayant séjourné dans le wadi Nushur qui nous a décidé à entreprendre une prospection nouvelle dans ce secteur au nord-ouest de la grande zone ornée de Saada, sur la route menant à Kifa. Notre espoir de trouver un nouveau site n'a pas été déçu car dans un affluent du Nushur, le wadi Gulat, nous avons découvert une sér...

  18. Assessment of RFID Read Accuracy for ISS Water Kit (United States)

    Chu, Andrew


    The Space Life Sciences Directorate/Medical Informatics and Health Care Systems Branch (SD4) is assessing the benefits Radio Frequency Identification (RFID) technology for tracking items flown onboard the International Space Station (ISS). As an initial study, the Avionic Systems Division Electromagnetic Systems Branch (EV4) is collaborating with SD4 to affix RFID tags to a water kit supplied by SD4 and studying the read success rate of the tagged items. The tagged water kit inside a Cargo Transfer Bag (CTB) was inventoried using three different RFID technologies, including the Johnson Space Center Building 14 Wireless Habitat Test Bed RFID portal, an RFID hand-held reader being targeted for use on board the ISS, and an RFID enclosure designed and prototyped by EV4.

  19. An Autonomous Autopilot Control System Design for Small-Scale UAVs (United States)

    Ippolito, Corey; Pai, Ganeshmadhav J.; Denney, Ewen W.


    This paper describes the design and implementation of a fully autonomous and programmable autopilot system for small scale autonomous unmanned aerial vehicle (UAV) aircraft. This system was implemented in Reflection and has flown on the Exploration Aerial Vehicle (EAV) platform at NASA Ames Research Center, currently only as a safety backup for an experimental autopilot. The EAV and ground station are built on a component-based architecture called the Reflection Architecture. The Reflection Architecture is a prototype for a real-time embedded plug-and-play avionics system architecture which provides a transport layer for real-time communications between hardware and software components, allowing each component to focus solely on its implementation. The autopilot module described here, although developed in Reflection, contains no design elements dependent on this architecture.

  20. Les guides de tourisme, un patrimoine et un objet d’étude

    Directory of Open Access Journals (Sweden)

    Évelyne Cohen


    Full Text Available Comme nous en avions fait la démonstration lors du colloque Les guides imprimés : villes, paysages, voyages en 1998, à l’Université Denis Diderot (Paris 7, pendant longtemps, les guides de tourisme n’ont pas été considérés comme des sources à part entière par les chercheurs qui les utilisaient volontiers comme stock d’informations sans pour autant leur reconnaître un statut de sources légitimes dans leurs corpus. De ce point de vue, il est utile de se référer aux analyses de Roland Barthes d...


    Directory of Open Access Journals (Sweden)

    Shlok Agarwal


    Full Text Available There have been many advancements in the field of aerospace and avionics. Scientists have increasingly started to focus on VTOL (vertical take - off and landing aircrafts. We have built a miniature VTOL twinrotor UAV. UAVs have begun to grab a lot of attention these days due to its numerous applications such as surveillance and relief. Twinrotor is a kind of a helicopter having two main propellers instead of one and no tail fin. All three important motion of the aircraft i.e. roll, pitch, yaw are controlled by thrust vectoring using servo motors and changing the magnitude of thrust using electronics speed controllers. The paper deals with the design of a basic UAV based on application and the construction keeping in mind the different concepts that govern its motion.

  2. F-5M DTA Program

    Directory of Open Access Journals (Sweden)

    Daniel Ferreira V. Mattos


    Full Text Available The Brazilian F-5 was submitted to avionics and weapons upgrade. This “new” aircraft has proven to be heavier and more capable. A comprehensive damage tolerance analysis is being performed to evaluate how the new mission profiles and weight distribution may affect the airframe structural integrity. Operational data were collected at the Brazilian Air Force Bases where the fighter is flown. Software was developed in order to acquire, filter and analyze flight data. This data was used for comparison between the pre and post modernization mission profiles and to determine the stress level in each of the known aircraft fatigue critical locations (FCL. The results show that the change in aircraft weight and balance and the new operational profile can significantly change the inspection intervals of certain fatigue critical locations of the structure. A preliminary result for the horizontal tail has shown that this component will have a much more restrictive maintenance schedule to assure flight safety.

  3. A design of FPGA based intelligent data handling interfacing card.

    Directory of Open Access Journals (Sweden)

    Anandaraj D


    Full Text Available With the increasing demand in the custom built logic for avionics systems, FPGA is used in this proposed interfacing card design. This FPGA based intelligent data handling card (IDHC for the IVHM system, will interface the data from aircraft subsystems to the aircraft digital data bus. This IDHC interfacing card is based on the Virtex-5 FPGA (Field Programmable Gate Array, which provides flexibility by re-programming, so that it can be configured to the required functionality. Fault detection can be done within the FPGA and only the anomalies passed to the computer, so that the bus bandwidth can be utilized effectively and also excessive wiring can be eliminated, that would have been required for multiple individual systems. The work concentrates on designing the schematic using OrCAD.

  4. Knowledge-Based Framework: its specification and new related discussions (United States)

    Rodrigues, Douglas; Zaniolo, Rodrigo R.; Branco, Kalinka R. L. J. C.


    Unmanned Aerial Vehicle is a common application of critical embedded systems. The heterogeneity prevalent in these vehicles in terms of services for avionics is particularly relevant to the elaboration of multi-application missions. Besides, this heterogeneity in UAV services is often manifested in the form of characteristics such as reliability, security and performance. Different service implementations typically offer different guarantees in terms of these characteristics and in terms of associated costs. Particularly, we explore the notion of Service-Oriented Architecture (SOA) in the context of UAVs as safety-critical embedded systems for the composition of services to fulfil application-specified performance and dependability guarantees. So, we propose a framework for the deployment of these services and their variants. This framework is called Knowledge-Based Framework for Dynamically Changing Applications (KBF) and we specify its services module, discussing all the related issues.

  5. Méthodes d'optimisation et d'apprentissage appliquées à des problèmes de trafic aérien


    Gianazza, David


    Mes thématiques de recherche portent sur le traitement de problèmes de trafic aérien par des méthodes d'optimisation et d'apprentissage supervisé. Les sujets étudiés sont par exemple la prévision de la charge de travail des contrôleurs aériens, la prévision des ouvertures de secteurs de contrôle, la prévision de trajectoires d'avions, ou la résolution de conflits aériens.Le traitement de ces problèmes difficiles s'appuie sur diverses méthodes d'optimisation ou d'apprentissage, au besoin en le...

  6. Etude d'un problème d'optimisation en aéroélasticité avec incertitudes


    Arnaud, Rémi


    La recherche en optimisation est un secteur crucial pour les constructeurs aéronautiques. La performance des appareils est un élément déterminant dans la compétition commerciale qui oppose les principaux manufacturiers du marché. L'incorporation de plus en plus massive des matériaux composites dans les avions de ligne dans les années 2000 illustre le désir des constructeurs de réduire la masse de leurs appareils pour en diminuer la consommation de kérozène. Parallèlement, la sécurité est deve...

  7. Eureca, a new element of Europe's space transportation systems (United States)

    Nellessen, W.; Graf, E.


    The technical details and operational features of launch and recovery of the free-flying multiple-payload pallet Eureca from the Shuttle are explored. The Eureca spacecraft is considered in terms of the structural/mechanical, power, avionics, attitude and orbit control, and thermal control subsystems. The core payload designed for the Eureca includes automatic monoellipsoid mirror furnace, solution growth, a protein growth, multifurnace assembly, automatic gradient heating, and botany facilities. The pallet will be carried into 160 nm orbit by the Shuttle, released, will boost itself into a higher orbit, then return in about six months to a 28.5 deg inclination, 160 nm orbit for Shuttle retrieval and return to earth. Payloads will be flown to Europe, where the pallet will be refurbished, reloaded, and returned to the U.S. for launch.

  8. Modeling and Design of Fault-Tolerant and Self-Adaptive Reconfigurable Networked Embedded Systems

    Directory of Open Access Journals (Sweden)

    Jürgen Teich


    Full Text Available Automotive, avionic, or body-area networks are systems that consist of several communicating control units specialized for certain purposes. Typically, different constraints regarding fault tolerance, availability and also flexibility are imposed on these systems. In this article, we will present a novel framework for increasing fault tolerance and flexibility by solving the problem of hardware/software codesign online. Based on field-programmable gate arrays (FPGAs in combination with CPUs, we allow migrating tasks implemented in hardware or software from one node to another. Moreover, if not enough hardware/software resources are available, the migration of functionality from hardware to software or vice versa is provided. Supporting such flexibility through services integrated in a distributed operating system for networked embedded systems is a substantial step towards self-adaptive systems. Beside the formal definition of methods and concepts, we describe in detail a first implementation of a reconfigurable networked embedded system running automotive applications.

  9. Modeling and Design of Fault-Tolerant and Self-Adaptive Reconfigurable Networked Embedded Systems

    Directory of Open Access Journals (Sweden)

    Streichert Thilo


    Full Text Available Automotive, avionic, or body-area networks are systems that consist of several communicating control units specialized for certain purposes. Typically, different constraints regarding fault tolerance, availability and also flexibility are imposed on these systems. In this article, we will present a novel framework for increasing fault tolerance and flexibility by solving the problem of hardware/software codesign online. Based on field-programmable gate arrays (FPGAs in combination with CPUs, we allow migrating tasks implemented in hardware or software from one node to another. Moreover, if not enough hardware/software resources are available, the migration of functionality from hardware to software or vice versa is provided. Supporting such flexibility through services integrated in a distributed operating system for networked embedded systems is a substantial step towards self-adaptive systems. Beside the formal definition of methods and concepts, we describe in detail a first implementation of a reconfigurable networked embedded system running automotive applications.

  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. Symposium on Aviation Psychology, 1st, Ohio State University, Columbus, OH, April 21, 22, 1981, Proceedings (United States)


    The impact of modern technology on the role, responsibility, authority, and performance of human operators in modern aircraft and ATC systems was examined in terms of principles defined by Paul Fitts. Research into human factors in aircraft operations and the use of human factors engineering for aircraft safety improvements were discussed, and features of the man-machine interface in computerized cockpit warning systems are examined. The design and operational features of computerized avionics displays and HUDs are described, along with results of investigations into pilot decision-making behavior, aircrew procedural compliance, and aircrew judgment training programs. Experiments in vision and visual perception are detailed, as are behavioral studies of crew workload, coordination, and complement. The effectiveness of pilot selection, screening, and training techniques are assessed, as are methods for evaluating pilot performance.

  12. 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.

  13. Deterministic digital WDM LAN for controlled configurations (United States)

    Mazurowski, John


    This work introduces the concept of a digital Wavelength Division Multiplexed (WDM) network for small avionic and space platforms. For packaging and heat transfer efficiency, all optical wavelength sources occupy a common location. Addressable wavelengths are allocated to each receiver, which may be reached by selection or tuning of a transmitter wavelength. Individual delays may be applied to assure synchronization at each receiver. The output of each individual source wavelength is pre-modulated with a clock signal. Signal modulation is applied by passing or rejecting the clock signals. Due to the simplicity of the modulation, the control plane functions can be merged with the data plane functions. Although the concept is based on a single data rate, the digital WDM LAN concept can possibly be extended to process packet and analog payloads.

  14. L’étiquette et la distribution des appartements officiels dans les palais baroques


    Baillie, Hugh Murray


    L’origine de cette étude remonte à l’époque où, après la guerre, je travaillais en Allemagne dans l’équipe engagée pour le programme de sauvegarde des Monuments, beaux-arts et archives. À l’occasion de l’inspection que je fis alors, en compagnie d’un collègue allemand, d’un vaste palais du xviiie siècle dont nous avions la charge, ce dernier, peut-être frappé par le terrible voire le scandaleux contraste entre ces splendeurs ternies et la désolation qui les entourait, me dit d’un air presque ...

  15. Admission Control of VL in AFDX Under HRT Constraints

    Institute of Scientific and Technical Information of China (English)

    ZHOU Qiang; QU Zhenliang; LIN Hengqing


    Avionics full duplex switched ethernet (AFDX) is a switched interconnection technology developed to provide reliable data exchange with strong data transmission time guarantees in internal communication of the spacecraft or aircraft. Virtual link (VL) is an important concept of AFDX to meet quality of service (QoS) requirements in terms of end-to-end message deadlines. A VL admission control algorithm in AFDX network under hard real-time (HRT) constraints is studied. Based on the scheduling principle of AFDX protocol, a packet scheduling scheme under HRT constraints is proposed, and after that an efficient VL admission control algorithm is presented. Analytical proof that the algorithm can effectively determine whether VL should be admitted is given. Finally simulative examples are presented to promote the conclusion.

  16. Fiber optic data transmission (United States)

    Shreve, Steven T.


    The Ohio University Avionics Engineering Center is currently developing a fiber optic data bus transmission and reception system that could eventually replace copper cable connections in airplanes. The original form of the system will transmit information from an encoder to a transponder via a fiber optic cable. An altimeter and an altitude display are connected to a fiber optic transmitter by copper cable. The transmitter converts the altimetry data from nine bit parallel to serial form and send these data through a fiber optic cable to a receiver. The receiver converts the data using a cable similar to that used between the altimeter and display. The transmitting and receiving ends also include a display readout. After completion and ground testing of the data bus, the system will be tested in an airborne environment.

  17. Charging system using solar panels and a highly resonant wireless power transfer model for small UAS applications (United States)

    Hallman, Sydney N.; Huck, Robert C.; Sluss, James J.


    The use of a wireless charging system for small, unmanned aircraft system applications is useful for both military and commercial consumers. An efficient way to keep the aircraft's batteries charged without interrupting flight would be highly marketable. While the general concepts behind highly resonant wireless power transfer are discussed in a few publications, the details behind the system designs are not available even in academic journals, especially in relation to avionics. Combining a highly resonant charging system with a solar panel charging system can produce enough power to extend the flight time of a small, unmanned aircraft system without interruption. This paper provides an overview of a few of the wireless-charging technologies currently available and outlines a preliminary design for an aircraft-mounted battery charging system.

  18. Synthesis and Characterization of Multi Wall Carbon Nanotubes (MWCNT) Reinforced Sintered Magnesium Matrix Composites (United States)

    Vijaya Bhaskar, S.; Rajmohan, T.; Palanikumar, K.; Bharath Ganesh Kumar, B.


    Metal matrix composites (MMCs) reinforced with ceramic nano particles (less than 100 nm), termed as metal matrix nano composites (MMNCs), can overcome those disadvantages associated with the conventional MMCs. MMCs containing carbon nanotubes are being developed and projected for diverse applications in various fields of engineering like automotive, avionic, electronic and bio-medical sectors. The present investigation deals with the synthesis and characterization of hybrid magnesium matrix reinforced with various different wt% (0-0.45) of multi wall carbon nano tubes (MWCNT) and micro SiC particles prepared through powder metallurgy route. Microstructure and mechanical properties such as micro hardness and density of the composites were examined. Microstructure of MMNCs have been investigated by scanning electron microscope, X-ray diffraction and energy dispersive X-ray spectroscopy (EDS) for better observation of dispersion of reinforcement. The results indicated that the increase in wt% of MWCNT improves the mechanical properties of the composite.

  19. Analysis of Heat Transfer Behaviour of the Conduction Cold Plate System

    Institute of Scientific and Technical Information of China (English)

    YangChun-xin; DangChao-Bin


    The heat-transfer behaviour of the conduction cold plate system used for avionics is investigated in this paper.The steady-state temperature profile for the cold plate is derived and the relationship between the coolant mass flowrate,the heat load and the highest cold plate temperature is established.A model is proposed to describe the transient thermal rosponse of the cold plate under thermal shock condition.The analytic solution of the transient heat transfer within the cold plate is provided.The results of this paper agree with those of the finite element method and can be used for the structural design and performance evaluation of cold plate system.

  20. Specification and Verification of Distributed Embedded Systems: A Traffic Intersection Product Family

    CERN Document Server

    Ölveczky, Peter Csaba; 10.4204/EPTCS.36.8


    Distributed embedded systems (DESs) are no longer the exception; they are the rule in many application areas such as avionics, the automotive industry, traffic systems, sensor networks, and medical devices. Formal DES specification and verification is challenging due to state space explosion and the need to support real-time features. This paper reports on an extensive industry-based case study involving a DES product family for a pedestrian and car 4-way traffic intersection in which autonomous devices communicate by asynchronous message passing without a centralized controller. All the safety requirements and a liveness requirement informally specified in the requirements document have been formally verified using Real-Time Maude and its model checking features.

  1. Towards Accelerated Aging Methodologies and Health Management of Power MOSFETs (Technical Brief) (United States)

    Celaya, Jose R.; Patil, Nishad; Saha, Sankalita; Wysocki, Phil; Goebel, Kai


    Understanding aging mechanisms of electronic components is of extreme importance in the aerospace domain where they are part of numerous critical subsystems including avionics. In particular, power MOSFETs are of special interest as they are involved in high voltage switching circuits such as drivers for electrical motors. With increased use of electronics in aircraft control, it becomes more important to understand the degradation of these components in aircraft specific environments. In this paper, we present an accelerated aging methodology for power MOSFETs that subject the devices to indirect thermal overstress during high voltage switching. During this accelerated aging process, two major modes of failure were observed - latch-up and die attach degradation. In this paper we present the details of our aging methodology along with details of experiments and analysis of the results.

  2. Dual-Use Space Technology Transfer Conference and Exhibition. Volume 1 (United States)

    Krishen, Kumar (Compiler)


    This document contains papers presented at the Dual-Use Space Technology Transfer Conference and Exhibition held at the Johnson Space Center February 1-3, 1994. Possible technology transfers covered during the conference were in the areas of information access; innovative microwave and optical applications; materials and structures; marketing and barriers; intelligent systems; human factors and habitation; communications and data systems; business process and technology transfer; software engineering; biotechnology and advanced bioinstrumentation; communications signal processing and analysis; new ways of doing business; medical care; applications derived from control center data systems; human performance evaluation; technology transfer methods; mathematics, modeling, and simulation; propulsion; software analysis and decision tools systems/processes in human support technology; networks, control centers, and distributed systems; power; rapid development perception and vision technologies; integrated vehicle health management; automation technologies; advanced avionics; ans robotics technologies. More than 77 papers, 20 presentations, and 20 exhibits covering various disciplines were presented b experts from NASA, universities, and industry.

  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. Creating standardized electronic data sheets for applications and devices (United States)

    Hansen, L. J.; Lanza, D.

    The Air Force Research Laboratory (AFRL) continues to develop infrastructure to enable the modular construction of satellites using an open network architecture and off-the-shelf avionics for space systems. Recent efforts have included the refinement of an ontology to formalize a standard language for the exchange of data and commands between components, including hardware and software, which is still evolving. AFRL is also focusing effort on creating standard interfaces using electronic data sheets based on this recently defined ontology. This paper will describe the development of standard interfaces that are documented in terms of an electronic datasheet for a specific application. The datasheet will identify the standard interfaces between hardware devices and software applications that are needed for a specific satellite function, in this case, a spacecraft guidance, navigation, and control (GN& C) application for Sun pointing. Finally, the benefits of using standardized interfaces will be discussed.

  5. Eye Tracking Metrics for Workload Estimation in Flight Deck Operation (United States)

    Ellis, Kyle; Schnell, Thomas


    Flight decks of the future are being enhanced through improved avionics that adapt to both aircraft and operator state. Eye tracking allows for non-invasive analysis of pilot eye movements, from which a set of metrics can be derived to effectively and reliably characterize workload. This research identifies eye tracking metrics that correlate to aircraft automation conditions, and identifies the correlation of pilot workload to the same automation conditions. Saccade length was used as an indirect index of pilot workload: Pilots in the fully automated condition were observed to have on average, larger saccadic movements in contrast to the guidance and manual flight conditions. The data set itself also provides a general model of human eye movement behavior and so ostensibly visual attention distribution in the cockpit for approach to land tasks with various levels of automation, by means of the same metrics used for workload algorithm development.

  6. The high speed bus technology development program (United States)

    Ludvigson, M. T.; Modrow, M. B.; Goldman, P. C.

    The current development status of a high-speed data bus to link MIL-STD-1750A computers in avionics applications is reviewed and illustrated with diagrams and photographs. The bus requirements include data rate 50 Mb/s, a linear token-passing scheme permitting both electronic and fiber-optic implementation, up to 64-terminal capacity, maximum terminal separation 300 ft, latency control via token-rotation-timer priority, self-test and bus-loop test capability, and automatic clock synchronization. The design concept and performance of a breadboard wire bus tested in July 1986 are discussed in detail, with particular attention to the redundancy manager, the output controller, the input controller, the ringmaster topology manager, and typical initial-placement problems.

  7. 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...

  8. Space tug thermal control equipment thermal requirements, characteristics, and constraints catalogue: Users guide. [spacecraft thermal control components (United States)

    Ward, T. L.


    This manual details the input instructions to the data bank, and explanation of the program and its output. The data bank was developed in satisfaction of two of the study tasks, the equipment thermal requirement catalog and the equipment characteristics and constraints catalog. The data bank contains 109 components within space tug avionics system. Other systems were not included in the data bank due to the available information, however, with some program modification, other systems could be incorporated into the data bank program. The data bank was developed and checked out and is compatible with the Univac 1108, and the CDC 6500 operating systems. The data contained in the data bank is general in content with emphasis on the component thermal design. The data is applicable to any spacecraft program where the components contained in the data bank can be applied in satisfaction of the system and subsystem requirements.

  9. Space tug thermal control equipment thermal requirements, characteristics and constraints catalogue (United States)

    Ward, T. L.


    The Space Tug Thermal Control Study contained two tasks associated with the cataloging of equipment thermal requirements, physical characteristics and constraints. In satisfaction of these tasks a Data Bank program was developed to provide a means of standardizing the method of cataloging while using the computer to handle the data and format the data into the desired catalogues. During the course of the study 109 components were catalogued and included in the Data Bank. A standardized method was selected for describing each component. Each subsystem of the Avionics System is described on a subsystem header page which describes the types of components included within the subsystem, the quantity requirements, target weights, target power and relative comments. The individual components listed within each subsystem are not necessarily a complete list of candidate items but do represent several of the presently available components for consideration in a Tug application.

  10. High-power microwave LDMOS transistors for wireless data transmission technologies (Review)

    International Nuclear Information System (INIS)

    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).

  11. Les grandes mutations de la marine marchande française (1945-1995). Volume II


    Cassagnou, Bernard


    Après avoir été détruite aux deux tiers de son tonnage pendant la seconde guerre mondiale, la Marine marchande française s’est reconstituée en moins de cinq ans. Elle a dû faire face, d’une part à la disparition de ses paquebots de ligne avec l’arrivée sur l’Atlantique nord des premiers avions long-courriers à réaction, d’autre part à la perte de substance du trafic des marchandises sur ses lignes traditionnelles, avec la décolonisation. Précédant en cela les dirigeants des grandes entreprise...

  12. Les grandes mutations de la marine marchande française (1945-1995). Volume I


    Cassagnou, Bernard; Léonard, Pierre; Plessis, Alain


    Après avoir été détruite aux deux tiers de son tonnage pendant la seconde guerre mondiale, la Marine marchande française s’est reconstituée en moins de cinq ans. Elle a dû faire face, d’une part à la disparition de ses paquebots de ligne avec l’arrivée sur l’Atlantique nord des premiers avions long-courriers à réaction, d’autre part à la perte de substance du trafic des marchandises sur ses lignes traditionnelles, avec la décolonisation. Précédant en cela les dirigeants des grandes entreprise...

  13. 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.

  14. 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.

  15. Formalization and Validation of Safety-Critical Requirements

    CERN Document Server

    Cimatti, Alessandro; Susi, Angelo; Tonetta, Stefano


    The validation of requirements is a fundamental step in the development process of safety-critical systems. In safety critical applications such as aerospace, avionics and railways, the use of formal methods is of paramount importance both for requirements and for design validation. Nevertheless, while for the verification of the design, many formal techniques have been conceived and applied, the research on formal methods for requirements validation is not yet mature. The main obstacles are that, on the one hand, the correctness of requirements is not formally defined; on the other hand that the formalization and the validation of the requirements usually demands a strong involvement of domain experts. We report on a methodology and a series of techniques that we developed for the formalization and validation of high-level requirements for safety-critical applications. The main ingredients are a very expressive formal language and automatic satisfiability procedures. The language combines first-order, tempor...

  16. Physics Based Electrolytic Capacitor Degradation Models for Prognostic Studies under Thermal Overstress (United States)

    Kulkarni, Chetan S.; Celaya, Jose R.; Goebel, Kai; Biswas, Gautam


    Electrolytic capacitors are used in several applications ranging from power supplies on safety critical avionics equipment to power drivers for electro-mechanical actuators. This makes them good candidates for prognostics and health management research. Prognostics provides a way to assess remaining useful life of components or systems based on their current state of health and their anticipated future use and operational conditions. Past experiences show that capacitors tend to degrade and fail faster under high electrical and thermal stress conditions that they are often subjected to during operations. In this work, we study the effects of accelerated aging due to thermal stress on different sets of capacitors under different conditions. Our focus is on deriving first principles degradation models for thermal stress conditions. Data collected from simultaneous experiments are used to validate the desired models. Our overall goal is to derive accurate models of capacitor degradation, and use them to predict performance changes in DC-DC converters.

  17. Design Qualification of an External Store for a Fighter Aircraft

    Directory of Open Access Journals (Sweden)

    V.B. Goley


    Full Text Available Defence Avionics Research Establishment (DARE has designed and developed an externalstore for fitment on a fighter aircraft. The external store has the poded structure and can be usedfor installation of a variety of payloads up to 250 kg. The mechanical details of the electronicsto be fitted inside the pod can be worked out as per application. The pod has been designedkeeping this in mind and based on the functional, mechanical, structural, and aerodynamicrequirements. The designed and fabricated pod has undergone various qualification tests. Thepaper brings out the details of the pod design, and the various structural and environmentalqualification tests carried out. The pod thus designed and qualified has been validated throughcarriage trials by fitting the pod on the platform intended for it. The pod is likely to be inductedinto the Services shortly.

  18. During STS-54 IUS/TDRS is released from cradle/tilt table above OV-105's PLB (United States)


    During STS-54, with Endeavour's, Orbiter Vehicle (OV) 105's, reaction control system (RCS) thrusters inhibited, the pyrotechnic separation device physically separates the inertial upper stage (IUS) / Tracking and Data Relay Satellite F (TDRS-F) spacecraft from the payload bay (PLB) at approximately 0.4 foot per second. The airborne support equipment (ASE) aft frame tilt actuator (AFTA) table at 58-degree deployment position, the forward frame cradle, and the released umbilical boom appear below the IUS/TDRS spacecraft combination. Stowed on top of the IUS are TDRS-F's solar array panels, its single access antennas, and the SGL antenna. In the foreground is Diffuse X-ray Spectrometer (DXS) payload. On the left is the DXS starboard and the Hitchhiker avionics. On the right is the port DXS. The entire scene is backdropped against the Earth's limb and its blue and white surface.

  19. Integrated Application of Active Controls (IAAC) technology to an advanced subsonic transport project. ACT/Control/Guidance System study, volume 1 (United States)


    The active control technology (ACT) control/guidance system task of the integrated application of active controls (IAAC) technology project within the NASA energy efficient transport program was documented. The air traffic environment of navigation and air traffic control systems and procedures were extrapolated. An approach to listing flight functions which will be performed by systems and crew of an ACT configured airplane of the 1990s, and a determination of function criticalities to safety of flight, are the basis of candidate integrated ACT/Control/Guidance System architecture. The system mechanizes five active control functions: pitch augmented stability, angle of attack limiting, lateral/directional augmented stability, gust load alleviation, and maneuver load control. The scope and requirements of a program for simulating the integrated ACT avionics and flight deck system, with pilot in the loop, are defined, system and crew interface elements are simulated, and mechanization is recommended. Relationships between system design and crew roles and procedures are evaluated.

  20. Real-Time Hardware-in-the-Loop Simulation of Ares I Launch Vehicle (United States)

    Tobbe, Patrick; Matras, Alex; Walker, David; Wilson, Heath; Fulton, Chris; Alday, Nathan; Betts, Kevin; Hughes, Ryan; Turbe, Michael


    The Ares Real-Time Environment for Modeling, Integration, and Simulation (ARTEMIS) has been developed for use by the Ares I launch vehicle System Integration Laboratory at the Marshall Space Flight Center. The primary purpose of the Ares System Integration Laboratory is to test the vehicle avionics hardware and software in a hardware - in-the-loop environment to certify that the integrated system is prepared for flight. ARTEMIS has been designed to be the real-time simulation backbone to stimulate all required Ares components for verification testing. ARTE_VIIS provides high -fidelity dynamics, actuator, and sensor models to simulate an accurate flight trajectory in order to ensure realistic test conditions. ARTEMIS has been designed to take advantage of the advances in underlying computational power now available to support hardware-in-the-loop testing to achieve real-time simulation with unprecedented model fidelity. A modular realtime design relying on a fully distributed computing architecture has been implemented.

  1. Ariane Transfer Vehicle - Logistic support to Space Station Freedom (United States)

    Cougnet, C.; Ricaud, C.; Deutscher, N.

    The attractiveness of the Ariane 5 and Ariane transfer vehicle (ATV) is described: it avoids the one-sidedness of the National STS, it increases the lift capacity to meet the demands of the Space Station, and it offers a system independent of, but consistent with, the STS in providing backup contingency capability. The Ariane 5/ATV system is able to launch and transfer any cargo module to the Space Station Freedom (SSF) and dispose of it at the end of the mission. Consideration is given to Space Station and SSF logistic support, and ATV operations and design. Diagrams are provided to illustrate the ATV's requirements and capability; an ATV mission toward the SSF; ATV design and components; the ATV's attitude, layout, and the architecture of the main propulsion system and avionic; and the ATV's performance. It is demonstrated that the Ariane 5/ATV system would be an adequate complement to the NSTS for logistic support of the SSF.

  2. 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)

    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

  3. Multi-Axis Accelerometer Calibration System (United States)

    Finley, Tom; Parker, Peter


    A low-cost, portable, and simplified system has been developed that is suitable for in-situ calibration and/or evaluation of multi-axis inertial measurement instruments. This system overcomes facility restrictions and maintains or improves the calibration quality for users of accelerometer-based instruments with applications in avionics, experimental wind tunnel research, and force balance calibration applications. The apparatus quickly and easily positions a multi-axis accelerometer system into a precisely known orientation suitable for in-situ quality checks and calibration. In addition, the system incorporates powerful and sophisticated statistical methods, known as response surface methodology and statistical quality control. These methods improve calibration quality, reduce calibration time, and allow for increased calibration frequency, which enables the monitoring of instrument stability over time.

  4. Éditorial Editorial

    Directory of Open Access Journals (Sweden)

    Jacques Maurice


    Full Text Available 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...

  5. Quadrant Based WSN Routing Technique By Shifting Of Origin

    Directory of Open Access Journals (Sweden)

    Nandan Banerji


    Full Text Available A sensor is a miniaturized, low powered (basically battery powered, limited storage device which can sense the natural phenomenon or things and convert it into electrical energy or vice versa using transduction process. A Wireless Sensor Network (WSN is such a wireless network built using sensors. The sensors communicate with each other’s using wireless medium. They can be deployed in such an environment; inaccessible to human or difficult to reach. Basically there is a vast application on automated world such as robotics, avionics, oceanographic study, space, satellites etc. The routing of a packet from a source node to a destination should be efficient in such a way that must be efficient in case of energy, communication overhead, less intermediate hops. The scheme will help to route the packet with a lesser intermediate nodes as the neighbors are being selected based on their Quadrant position.

  6. 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.

  7. Design and testing of the U.S. Space Station Freedom primary propulsion system (United States)

    Morano, Joseph S.; Delventhal, Rex A.; Chilcot, Kimberly J.


    The primary propulsion system (PPS) for the Space Station Freedom is discussed in terms of salient design characteristics and key testing procedures. The rocket engine modules contain reboost and attitude control thrusters, and their designs are illustrated showing the mounting structures, thruster solenoid valves, and thrust chambers. The propellant tank assembly for storing gaseous N pressurant and hydrazine propellant is described as are the system avionics, thruster solenoid valves, and latching isolation valves. PPS testing conducted on the development systems includes the use of a propulsion-module development unit, a development test article, and system qualification testing. Specific test articles include functional heaters, mass/thermal simulated components, flight-quality structures, and software control operations.

  8. An adaptive guidance algorithm for aerospace vehicles (United States)

    Bradt, J. E.; Hardtla, J. W.; Cramer, E. J.

    The specifications for proposed space transportation systems are placing more emphasis on developing reusable avionics subsystems which have the capability to respond to vehicle evolution and diverse missions while at the same time reducing the cost of ground support for mission planning, contingency response and verification and validation. An innovative approach to meeting these goals is to specify the guidance problem as a multi-point boundary value problen and solve that problem using modern control theory and nonlinear constrained optimization techniques. This approach has been implemented as Gamma Guidance (Hardtla, 1978) and has been successfully flown in the Inertial Upper Stage. The adaptive guidance algorithm described in this paper is a generalized formulation of Gamma Guidance. The basic equations are presented and then applied to four diverse aerospace vehicles to demonstrate the feasibility of using a reusable, explicit, adaptive guidance algorithm for diverse applications and vehicles.

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

    International Nuclear Information System (INIS)

    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

  10. Distributed generation technologies : small turbines/fuel cells

    Energy Technology Data Exchange (ETDEWEB)

    Skowronski, M. [AlliedSignal Power Systems Inc., Torrance, CA (United States)


    Allied Signal Power Systems Inc. is a company with 76,580 employees and $ 14 billion in sales in 1996. The company`s various divisions are major players in aerospace equipment systems, commercial avionics, electronic systems, engines, automotive brake systems, safety restraint systems, turbochargers, premium car care products, chemicals plastics and advanced materials. This paper describes a developed a turbogenerator designed for use in electric power generation. The new engine is inherently simple with high reliability. Its advantages over a conventional engine include: (1) one moving part, (2) no oil system, (3) multi-fuel capability, (4) no gears or gearboxes, (5) no separate starter motor, (6) ultra low emissions, and (7) lower operating costs. Although there are relatively high costs associated with its aerospace design, consumers, the environment and the electrical system/grid could all benefit from the turbogenerator. Installation and variable costs and target markets were discussed. 3 tabs., 12 figs.

  11. Flight Test Evaluation of Mission Computer Algorithms for a Modern Trainer Aircraft

    Directory of Open Access Journals (Sweden)

    Gargi Meharu


    Full Text Available A low cost integrated avionics system has been realized on a modern trainer aircraft. Without using an expensive inertial navigation system onboard, acceptable level of accuracy for navigation, guidance, and weapon aiming is achieved by extensive data fusion within mission computer. The flight test evaluation of mission computer is carried out by assessing the overall performance under various navigation and guidance modes. In flight simulation is carried out for weapon aiming modes. The mission computer interfaces with various subsystems and implements the functional requirements for flight management and mission management. The aim of this paper is to discuss the algorithms of a data fusion intensive mission computer and flight test evaluation of these algorithms, for a typical modern trainer aircraft. The challenges and innovations involved in the work are also discussed.Defence Science Journal, 2013, 63(2, pp.164-173, DOI:

  12. Rezultati modeliranja borbenog manevra napada aviona na zemaljski cilj iz oštrog obrušavanja / The results of combat attack maneuver modelling on ground target using aircraft steep diving

    Directory of Open Access Journals (Sweden)

    Nikola Pekić


    Full Text Available U ovom radu prikazani su rezultati matematičkog modeliranja kretanja aviona u borbenom manevru pri napadu na zemaljski cilj iz oštrog obrušavanja. Kretanje aviona razmatrano je kao kretanje materijalne tačke u prostoru. Takođe, prikazane su prednosti aviona sa otklonom vektora potiska i njegove primene u manevru u odnosu na avion sa klasičnom pogonskom grupom i klasičnim aerodinamičkim upravljačkim površinama. / This paper presents the results of mathematical modeling of aircraft movement in combat maneuver during attack on ground target using steep diving. Aircraft movement is considered as movement of a material point in space. Also, the advantages of aircraft with thrust vector deflection and its applications during maneuver when compared to the aircraft with classical engines and classical aerodynamic controls.

  13. Secuenciación heurística de un proyecto con restricciones temporales

    Directory of Open Access Journals (Sweden)

    Villa Juliá, Mª Fulgencia


    Full Text Available El presente trabajo aborda el análisis de un problema real del mantenimiento que una compañía aeronáutica debe practicar sobre una flota de aviones del tipo Boeing-747. En primer lugar analizamos en qué consiste dicho mantenimiento, los elementos que lo definen y los objetivos que se persiguen. A continuación estudiamos sus similitudes y diferencias con el RCPS (Resource Constrained Project Scheduling, un modelo clásico aplicado a este tipo de problemas. Entre estas diferencias se encuentran la existencia de restricciones temporales para la secuenciación de determinadas tareas así como otros tipos especiales de relaciones entre las actividades además de las clásicas de precedencia. Concretamos, finalmente, la metodología a aplicar para abordar el pro-blema planteado.

  14. Développement d’une approche intégrée de PHM – Prognostics and Health Management : Application au Circuit Carburant d’un Turboréacteur


    LAMOUREUX, Benjamin


    Pour les constructeurs de moteurs d'avions comme Snecma, la disponibilité est un des enjeux clés de l'avenir. En effet, la limitation des retards et annulations de vols ainsi que la réduction de la fréquence et de la durée des opérations de maintenance pourraient entraîner des économies importantes. Pour accroître la disponibilité, l'outil le plus utilisé actuellement est le "prognostics and health management" (PHM). La première contribution de la thèse est de proposer des cadres terminologiq...

  15. Investigation and evaluation of shuttle/GPS navigation system (United States)

    Nilsen, P. W.


    Iterative procedures were used to analyze the performance of two preliminary shuttle/GPS navigation system configurations: an early OFT experimental system and a more sophisticated system which consolidates several separate navigation functions thus permitting net cost savings from decreased shuttle avionics weight and power consumption, and from reduced ground data processing. The GPS system can provide on-orbit navigation accuracy an order of magnitude better than the baseline system, with very adequate link margins. The worst-case link margin is 4.3 dB. This link margin accounts for shuttle RF circuit losses which were minimized under the constraints of program schedule and environmental limitations. Implicit in the link analyses are the location trade-offs for preamplifiers and antennas.

  16. Industrial-Strength Model-Based Testing - State of the Art and Current Challenges

    Directory of Open Access Journals (Sweden)

    Jan Peleska


    Full Text Available As of today, model-based testing (MBT is considered as leading-edge technology in industry. We sketch the different MBT variants that - according to our experience - are currently applied in practice, with special emphasis on the avionic, railway and automotive domains. The key factors for successful industrial-scale application of MBT are described, both from a scientific and a managerial point of view. With respect to the former view, we describe the techniques for automated test case, test data and test procedure generation for concurrent reactive real-time systems which are considered as the most important enablers for MBT in practice. With respect to the latter view, our experience with introducing MBT approaches in testing teams are sketched. Finally, the most challenging open scientific problems whose solutions are bound to improve the acceptance and effectiveness of MBT in industry are discussed.

  17. The Development of Rocketry Capability in New Zealand—World Record Rocket and First of Its Kind Rocketry Course

    Directory of Open Access Journals (Sweden)

    George Buchanan


    Full Text Available The University of Canterbury has developed a rocket research group, UC Rocketry, which recently broke the world altitude record for an I-class motor (impulse of 320–640 Ns and has run a rocketry course for the first time in New Zealand. This paper discusses the development and results of the world record rocket “Milly” and details all the fundamental elements of the rocketry final year engineering course, including the manufacturing processes, wind tunnel testing, avionics, control and the final rocket launch of “Smokey”. The rockets Milly and Smokey are an example of the design, implementation and testing methodologies that have significantly contributed to research and graduates for New Zealand’s space program.

  18. Experience Report: A Do-It-Yourself High-Assurance Compiler (United States)

    Pike, Lee; Wegmann, Nis; Niller, Sebastian; Goodloe, Alwyn


    Embedded domain-specific languages (EDSLs) are an approach for quickly building new languages while maintaining the advantages of a rich metalanguage. We argue in this experience report that the "EDSL approach" can surprisingly ease the task of building a high-assurance compiler.We do not strive to build a fully formally-verified tool-chain, but take a "do-it-yourself" approach to increase our confidence in compiler-correctness without too much effort. Copilot is an EDSL developed by Galois, Inc. and the National Institute of Aerospace under contract to NASA for the purpose of runtime monitoring of flight-critical avionics. We report our experience in using type-checking, QuickCheck, and model-checking "off-the-shelf" to quickly increase confidence in our EDSL tool-chain.

  19. Terrestrial radiation effects in ULSI devices and electronic systems

    CERN Document Server

    Ibe, Eishi H


    A practical guide on how mathematical approaches can be used to analyze and control radiation effects in semiconductor devices within various environments Covers faults in ULSI devices to failures in electronic systems caused by a wide variety of radiation fields, including electrons, alpha -rays, muons, gamma rays, neutrons and heavy ions. Readers will learn the environmental radiation features at the ground or avionics altitude. Readers will also learn how to make numerical models from physical insight and what kind of mathematical approaches should be implemented to analyze the radiation effects. A wide variety of mitigation techniques against soft-errors are reviewed and discussed. The author shows how to model sophisticated radiation effects in condensed matter in order to quantify and control them. The book provides the reader with the knowledge on a wide variety of radiation fields and their effects on the electronic devices and systems. It explains how electronic systems including servers and rout...

  20. 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.

  1. 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.

  2. Application of Artificial Neural Networks in Aircraft Maintenance, Repair and Overhaul Solutions

    CERN Document Server

    Paul, Soumitra; Jasani, Devashish; Dudhwewala, Rachit; Gowda, Vijay Bore; Nair, T R Gopalakrishnan


    This paper reviews application of Artificial Neural Networks in Aircraft Maintenance, Repair and Overhaul (MRO). MRO solutions are designed to facilitate the authoring and delivery of maintenance and repair information to the line maintenance technicians who need to improve aircraft repair turn around time, optimize the efficiency and consistency of fleet maintenance and ensure regulatory compliance. The technical complexity of aircraft systems, especially in avionics, has increased to the point at which it poses a significant troubleshotting and repair challenge for MRO personnel. As per the existing scenario, the MRO systems in place are inefficient. In this paper, we propose the centralization and integration of the MRO database to increase its efficiency. Moreover the implementation of Artificial Neural Networks in this system can rid the system of many of its deficiencies. In order to make the system more efficient we propose to integrate all the modules so as to reduce the efficacy of repair.

  3. Ecriture-sms en Métropole et à La Réunion : 'zones instables et flottantes' du français ordinaire et spécificités du contexte de surdité


    Blondel, Marion; Gonac'H, Jeanne; Ledegen, Gudrun; Seeli, Julia


    La communication médiée par téléphone est une forme d'écrit qui modifie les contours des catégories connues : ses caractéristiques linguistiques relèvent à la fois d'une variété de proximité et d'un moyen de communication à distance. Prenant appui sur quatre corpus " sourds " (1580 sms) et " entendants " de l'espace francophone (Normandie - La Réunion), notre étude se penche sur l'écrit des sourds et l'écrit en situation plurilectale : nous avions formulé l'hypothèse que les caractéristiques ...

  4. Industrial-Strength Formally Certified SAT Solving

    CERN Document Server

    Darbari, Ashish; Marques-Silva, Joao


    Boolean Satisfiability (SAT) solvers are now routinely used in the verification of large industrial problems. However, their application in safety-critical domains such as the railways, avionics, and automotive industries requires some form of assurance for the results, as the solvers can (and sometimes do) have bugs. Unfortunately, the complexity of modern, highly optimized SAT solvers renders impractical the development of direct formal proofs of their correctness. This paper presents an alternative approach where an untrusted, industrial-strength, SAT solver is plugged into a trusted, formally certified, SAT proof checker to provide industrial-strength certified SAT solving. The key novelties and characteristics of our approach are (i) that the checker is automatically extracted from the formal development, (ii), that the combined system can be used as a standalone executable program independent of any supporting theorem prover, and (iii) that the checker certifies any SAT solver respecting the agreed form...

  5. 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...

  6. Bayesian Framework Approach for Prognostic Studies in Electrolytic Capacitor under Thermal Overstress Conditions (United States)

    Kulkarni, Chetan S.; Celaya, Jose R.; Goebel, Kai; Biswas, Gautam


    Electrolytic capacitors are used in several applications ranging from power supplies for safety critical avionics equipment to power drivers for electro-mechanical actuator. Past experiences show that capacitors tend to degrade and fail faster when subjected to high electrical or thermal stress conditions during operations. This makes them good candidates for prognostics and health management. Model-based prognostics captures system knowledge in the form of physics-based models of components in order to obtain accurate predictions of end of life based on their current state of heal th and their anticipated future use and operational conditions. The focus of this paper is on deriving first principles degradation models for thermal stress conditions and implementing Bayesian framework for making remaining useful life predictions. Data collected from simultaneous experiments are used to validate the models. Our overall goal is to derive accurate models of capacitor degradation, and use them to remaining useful life in DC-DC converters.

  7. Analysis of Security Protocols in Embedded Systems

    DEFF Research Database (Denmark)

    Bruni, Alessandro

    .e., protecting the system from the external world). With increased connectivity of these systems to external networks the attack surface has grown, and consequently there is a need for securing the system from external attacks. Introducing security protocols in safety critical systems requires careful......Embedded real-time systems have been adopted in a wide range of safety-critical applications—including automotive, avionics, and train control systems—where the focus has long been on safety (i.e., protecting the external world from the potential damage caused by the system) rather than security (i...... considerations on the available resources, especially in meeting real-time and resource constraints, as well as cost and reliability requirements. For this reason many proposed security protocols in this domain have peculiar features, not present in traditional security literature. In this thesis we tackle...

  8. VLSI 'smart' I/O module development (United States)

    Kirk, Dan

    The developmental history, design, and operation of the MIL-STD-1553A/B discrete and serial module (DSM) for the U.S. Navy AN/AYK-14(V) avionics computer are described and illustrated with diagrams. The ongoing preplanned product improvement for the AN/AYK-14(V) includes five dual-redundant MIL-STD-1553 channels based on DSMs. The DSM is a front-end processor for transferring data to and from a common memory, sharing memory with a host processor to provide improved 'smart' input/output performance. Each DSM comprises three hardware sections: three VLSI-6000 semicustomized CMOS arrays, memory units to support the arrays, and buffers and resynchronization circuits. The DSM hardware module design, VLSI-6000 design tools, controlware and test software, and checkout procedures (using a hardware simulator) are characterized in detail.

  9. 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.

  10. Prototype Common Bus Spacecraft: Hover Test Implementation and Results. Revision, Feb. 26, 2009 (United States)

    Hine, Butler Preston; Turner, Mark; Marshall, William S.


    In order to develop the capability to evaluate control system technologies, NASA Ames Research Center (Ames) began a test program to build a Hover Test Vehicle (HTV) - a ground-based simulated flight vehicle. The HTV would integrate simulated propulsion, avionics, and sensors into a simulated flight structure, and fly that test vehicle in terrestrial conditions intended to simulate a flight environment, in particular for attitude control. The ultimate purpose of the effort at Ames is to determine whether the low-cost hardware and flight software techniques are viable for future low cost missions. To enable these engineering goals, the project sought to develop a team, processes and procedures capable of developing, building and operating a fully functioning vehicle including propulsion, GN&C, structure, power and diagnostic sub-systems, through the development of the simulated vehicle.

  11. Modeling of an Adjustable Beam Solid State Light Project (United States)

    Clark, Toni


    This proposal is for the development of a computational model of a prototype variable beam light source using optical modeling software, Zemax Optics Studio. The variable beam light source would be designed to generate flood, spot, and directional beam patterns, while maintaining the same average power usage. The optical model would demonstrate the possibility of such a light source and its ability to address several issues: commonality of design, human task variability, and light source design process improvements. An adaptive lighting solution that utilizes the same electronics footprint and power constraints while addressing variability of lighting needed for the range of exploration tasks can save costs and allow for the development of common avionics for lighting controls.

  12. De Versalles a la cibérnetica

    Directory of Open Access Journals (Sweden)

    Bateson Gregory


    Full Text Available Debia hablar sobre la historia reciente, tal como se me presento a mi y a mi generacion y a ustedes en la suya, y cuando venia en el avion esta mañana, en mi mente empezaron a resonar algunas palabras. Eran frases mas retumbantes que cualquiera que yo pudiera componer. Una de esas frases era: "Los padres comieron frutos amargos y los hijos tienen dentera". Otra era la asercion de Joyce de que "la historia es esa pesadilla que no tiene despertar". Otra "Los pecados de los padres recaeran sobre los hijos hasta la tercera y cuarta generacion de los que me odian". Y, por ultimo, menos resonante aunque pertinente para el problema del mecanismo social: "Quien desea hacer bien a otros debe hacerlo en cosas minusculas y particulares. El Dios en general es la escusa del bribon, del mentiroso y del adulador".

  13. Recent progress in OLED and flexible displays and their potential for application to aerospace and military display systems (United States)

    Sarma, Kalluri


    Organic light emitting diode (OLED) display technology has advanced significantly in recent years and it is increasingly being adapted in consumer electronics products with premium performance, such as high resolution smart phones, Tablet PCs and TVs. Even flexible OLED displays are beginning to be commercialized in consumer electronic devices such as smart phones and smart watches. In addition to the advances in OLED emitters, successful development and adoption of OLED displays for premium performance applications relies on the advances in several enabling technologies including TFT backplanes, pixel drive electronics, pixel patterning technologies, encapsulation technologies and system level engineering. In this paper we will discuss the impact of the recent advances in LTPS and AOS TFTs, R, G, B and White OLED with color filter pixel architectures, and encapsulation, on the success of the OLEDs in consumer electronic devices. We will then discuss potential of these advances in addressing the requirements of OLED and flexible displays for the military and avionics applications.

  14. Techniques for Assuring NASA Mission Success Using Redundancy and Multi-Functionality Designs (United States)

    Shivers, Herb


    Topics include NASA centers around the country; 2009 highlights of significant successes in space transportation, exploration, and science; significant accomplishments; places to explore include Lagrange points, near-Earth objects, Mars and the Moon, and International Space Station research; Marshall's missions include propulsion and transportation systems, life support systems, and earth and space science spacecraft, systems, and operations; project lifecycle management model; motivation of avionics fault-tolerance, redundancy needs and concerns, redundancy versus reliability; parallel-series configurations; effect of adding redundancy on mission success; example of rules-based approach where reliability and safety interaction impacts design; impact of common cause failure; approach ot bottom-up reliability analysis; three factors that lead to redundant system failure; Apollo 13 multi-functional reliability and example; and mitigating the risk of single string spacecraft architecture;.

  15. Space tug point design study. Volume 1: Summary (United States)


    The design and characteristics of a space tug are discussed. The primary objective of the study is to verify the performance capability of a baseline design to deliver and retrieve payloads between 100 nautical miles, 28.5 degrees inclination, and geosynchronous. The space tug is ground based, reusable for 20 mission cycles, and is shuttled to and from low earth orbit by an earth orbital shuttle (EOS) with a 65,000 pound payload capability. It is shown that the baseline concept can meet the target performance goals. The design analysis encompassed: (1) definition of the vehicle primary structure, (2) thermal control, (3) meteoroid protection, (4) propulsion and mechanical subsystems, and (5) avionics including power generation and distribution.

  16. Pavimentos de hormigón

    Directory of Open Access Journals (Sweden)

    Fernández, R.


    Full Text Available In this paper, the paving of a bay designed for assembling engines in the Citroën factory in Vigo, and of an airplane parlEn este artículo se describen la pavimentación de una nave destinada al montaje de motores en la factoría Citroën, de Vigo, y la de un aparcamiento de aviones en el aeropuerto de Málaga. Ambas obras, realizadas en hormigón en masa, han contado con la colaboración del Servicio de Pavimentos Rígidos (SEPAR del Instituto Eduardo Torroja, en su doble papel de asesor técnico y auxiliar de la contrata (prestación de maquinaria y personal especializado.

  17. NASA Tech Briefs, May 2003 (United States)


    Topics covered include: Using Diffusion Bonding in Making Piezoelectric Actuators; Wireless Temperature-Monitoring System; Analog Binaural Circuits for Detecting and Locating Leaks; Mirrors Containing Biomimetic Shape-Control Actuators; Surface-Micromachined Planar Arrays of Thermopiles; Cascade Back-Propagation Learning in Neural Networks; Perovskite Superlattices as Tunable Microwave Devices; Rollable Thin-Shell Nanolaminate Mirrors; Flight Tests of a Ministick Controller in an F/A-18 Airplane; Piezoelectrically Actuated Shutter for High Vacuum; Bio-Inspired Engineering of Exploration Systems; Microscope Cells Containing Multiple Micromachined Wells; Electrophoretic Deposition for Fabricating Microbatteries; Integrated Arrays of Ion-Sensitive Electrodes; Model of Fluidized Bed Containing Reacting Solids and Gases; Membrane Mirrors With Bimorph Shape Actuators; Using Fractional Clock-Period Delays in Telemetry Arraying; Developing Generic Software for Spacecraft Avionics; Numerical Study of Pyrolysis of Biomass in Fluidized Beds; and Assessment of Models of Chemically Reacting Granular Flows.

  18. Étude de l'influence des défauts de soudage sur le comportement plastique et la durée de vie en fatigue de soudures par friction-malaxage d'un alliage Al-Cu-Li


    Le Jolu, Thomas


    Dans un but de réduction de poids des avions, un alliage Al-Cu-Li (2198-T8) assemblé par friction-malaxage est envisagé par les avionneurs pour des applications de type fuselage et intrados de l'aile. L'objectif de cette étude est de déterminer le comportement en fatigue des soudures par friction-malaxage et l'influence de certains défauts de soudage pour une durée de vie de l'ordre de 105 cycles. Pour cela le matériau de base, des soudures réalisées pleine tôle (sans défaut), des soudures co...

  19. Rapport-bilan de la phase d'inclusion de l'étude sommeil


    Evrard, Anne-Sophie; Lefevre, Marie


    L'objectif de l'étude sommeil du programme de recherche épidémiologique DEBATS (Discussion sur les Effets du Bruit des Aéronefs Touchant la Santé) est de caractériser de manière détaillée et spécifique les effets aigus du bruit des avions sur la qualité du sommeil tout en affinant la mesure de l'exposition au bruit. Cette étude permettra également de comparer la pertinence d'indicateurs évènementiels (nombre de survols dépassant 65 dBA par exemple) à celle des indicateurs énergétiques (Lden 1...

  20. TPS verification with UUT simulation (United States)

    Wang, Guohua; Meng, Xiaofeng; Zhao, Ruixian


    TPS's (Test Program Set) verification or first article acceptance test commonly depends on fault insertion experiment on UUT (Unit Under Test). However the failure modes injected on UUT is limited and it is almost infeasible when the UUT is in development or in a distributed state. To resolve this problem, a TPS verification method based on UUT interface signal simulation is putting forward. The interoperability between ATS (automatic test system) and UUT simulation platform is very important to realize automatic TPS verification. After analyzing the ATS software architecture, the approach to realize interpretability between ATS software and UUT simulation platform is proposed. And then the UUT simulation platform software architecture is proposed based on the ATS software architecture. The hardware composition and software architecture of the UUT simulation is described in details. The UUT simulation platform has been implemented in avionics equipment TPS development, debug and verification.

  1. Global system data bus using the Digital Autonomous Terminal Access Communication protocol (United States)

    Holmes, David C. E.


    Modern digital avionic systems with distributed processing require networking to connect the many elements. Digital Autonomous Terminal Access Communication (DATAC) is one of many such networks. DATAC has been implemented on the Transport Systems Research Vehicle (TSRV), a Boeing 737 aircraft operated by the National Aeronautics and Space Administration's Advanced Transport Operating Systems Program Office (ATOPS). This paper presents the TSRV implementation of the DATAC bus, a description of the DATAC system, a synchronization mechanism, details of data flow throughout the system, and a discussion of the modes available with DATAC. Numerous flight tests have been conducted using DATAC as the only means of communication between systems with outstanding results. DATAC is now an integral part of the TSRV and is expected to satisfy near term as well as future requirements for growth and flexibility.

  2. Bioinspired optical sensors for unmanned aerial systems (United States)

    Chahl, Javaan; Rosser, Kent; Mizutani, Akiko


    Insects are dependant on the spatial, spectral and temporal distributions of light in the environment for flight control and navigation. This paper reports on flight trials of implementations of insect inspired behaviors on unmanned aerial vehicles. Optical flow methods for maintaining a constant height above ground and a constant course have been demonstrated to provide navigation capabilities that are impossible using conventional avionics sensors. Precision control of height above ground and ground course were achieved over long distances. Other vision based techniques demonstrated include a biomimetic stabilization sensor that uses the ultraviolet and green bands of the spectrum, and a sky polarization compass. Both of these sensors were tested over long trajectories in different directions, in each case showing performance similar to low cost inertial heading and attitude systems. The behaviors demonstrate some of the core functionality found in the lower levels of the sensorimotor system of flying insects and shows promise for more integrated solutions in the future.

  3. Cost Optimization and Technology Enablement COTSAT-1 (United States)

    Spremo, Stevan; Lindsay, Michael C.; Klupar, Peter Damian; Swank, Aaron J.


    Cost Optimized Test of Spacecraft Avionics and Technologies (COTSAT-1) is an ongoing spacecraft research and development project at NASA Ames Research Center (ARC). The space industry was a hot bed of innovation and development at its birth. Many new technologies were developed for and first demonstrated in space. In the recent past this trend has reversed with most of the new technology funding and research being driven by the private industry. Most of the recent advances in spaceflight hardware have come from the cell phone industry with a lag of about 10 to 15 years from lab demonstration to in space usage. NASA has started a project designed to address this problem. The prototype spacecraft known as Cost Optimized Test of Spacecraft Avionics and Technologies (COTSAT-1) and CheapSat work to reduce these issues. This paper highlights the approach taken by NASA Ames Research center to achieve significant subsystem cost reductions. The COSTAT-1 research system design incorporates use of COTS (Commercial Off The Shelf), MOTS (Modified Off The Shelf), and GOTS (Government Off The Shelf) hardware for a remote sensing spacecraft. The COTSAT-1 team demonstrated building a fully functional spacecraft for $500K parts and $2.0M labor. The COTSAT-1 system, including a selected science payload, is described within this paper. Many of the advancements identified in the process of cost reduction can be attributed to the use of a one-atmosphere pressurized structure to house the spacecraft components. By using COTS hardware, the spacecraft program can utilize investments already made by commercial vendors. This ambitious project development philosophy/cycle has yielded the COTSAT-1 flight hardware. This paper highlights the advancements of the COTSAT-1 spacecraft leading to the delivery of the current flight hardware that is now located at NASA Ames Research Center. This paper also addresses the plans for COTSAT-2.

  4. High repetition rate sealed CO2 TEA lasers using heterogeneous catalysts (United States)

    Price, H. T.; Shaw, S. R.


    The significant operational advantages offered by CO2 lasers, operating in the 10.6 micron region of the spectrum, over current solid state lasers, emitting in the near IR region, have prompted increased interest in the development of compact, reliable, rugged CO2 laser sources. Perhaps the most critical aspect associated with achieving a laser compatible with military use is the development of lasers which require no gas replenishment. Sealed, single shot, CO2 TEA lasers have been available for a number of years. Stark et al were first to demonstrate reliable sealed operation in single shot CO2 TEA lasers in 1975 using gas catalysis. GEC Avionics reported the compact, environmentally qualified, MKIII CO2 TEA laser with a pulse life of greater than 10 to the 6th power pulses in 1980. A sealed laser lifetime of greater than 10 to the 6th power pulses is acceptable for single shot cases, such as direct detection rangefinders for tank laser sights. However, in many other applications, such as tracking of fast moving targets, it is essential that a repetition rate of typically 30Hz to 100Hz is employed. In such cases, a pulse lifetime of 10 to the 6th power pulses is no longer sufficient and a minimum pulse lifetime 10 to the 7th power pulses is essential to ensure a useful service life. In 1983 Stark el al described a sealed, 100Hz CO2 TEA laser, with a life of greater than 2.6 x 10 to the 6th power, which employed heterogeneous catalysis. Following this pioneering work, GEC Avionics has been engaged in the development of sealed high repetition rate lasers with a pulse lifetime of 20 million pulses.

  5. A multiscale problem in thermal science

    Directory of Open Access Journals (Sweden)

    Casenave Fabien


    Full Text Available We consider a multiscale heat problem in civil aviation: determine the temperature field in a plane in flying conditions, with air conditioning. Ventilated electronic components in the bay bring a heat source, introducing a second scale in the problem. First, we present three levels of modelling for the physical phenomena, which are applied to the two sub-problems: the plane and the electronic component. Then, having reduced the complexity of the problem to a linear non-symmetric coercive PDE, we will use the reduced basis method for the electronic component problem. Nous considérons un problème multi-échelle d’aérothermie en aviation civile. Nous souhai- tons déterminer le champ de température dans un avion en conditions de vol, avec présence d’une climatisation. Des composants électroniques ventilés sont présents dans la soute, et constituent une source de chaleur, introduisant une deuxième échelle dans notre problème. Dans un premier temps, nous présentons trois niveaux de modélisation pour le phénomène d’aérothermie, que nous appliquerons aux deux sous-problèmes : l’avion et le composant électronique. Ensuite, nous appliquons la méthode des bases réduites au problème du composant électronique, en considérant des simplifications de modélisation amenant à la résolution numérique d’une EDP elliptique linéaire coercive non-symétrique.

  6. Airborne laser sensors and integrated systems (United States)

    Sabatini, Roberto; Richardson, Mark A.; Gardi, Alessandro; Ramasamy, Subramanian


    The underlying principles and technologies enabling the design and operation of airborne laser sensors are introduced and a detailed review of state-of-the-art avionic systems for civil and military applications is presented. Airborne lasers including Light Detection and Ranging (LIDAR), Laser Range Finders (LRF), and Laser Weapon Systems (LWS) are extensively used today and new promising technologies are being explored. Most laser systems are active devices that operate in a manner very similar to microwave radars but at much higher frequencies (e.g., LIDAR and LRF). Other devices (e.g., laser target designators and beam-riders) are used to precisely direct Laser Guided Weapons (LGW) against ground targets. The integration of both functions is often encountered in modern military avionics navigation-attack systems. The beneficial effects of airborne lasers including the use of smaller components and remarkable angular resolution have resulted in a host of manned and unmanned aircraft applications. On the other hand, laser sensors performance are much more sensitive to the vagaries of the atmosphere and are thus generally restricted to shorter ranges than microwave systems. Hence it is of paramount importance to analyse the performance of laser sensors and systems in various weather and environmental conditions. Additionally, it is important to define airborne laser safety criteria, since several systems currently in service operate in the near infrared with considerable risk for the naked human eye. Therefore, appropriate methods for predicting and evaluating the performance of infrared laser sensors/systems are presented, taking into account laser safety issues. For aircraft experimental activities with laser systems, it is essential to define test requirements taking into account the specific conditions for operational employment of the systems in the intended scenarios and to verify the performance in realistic environments at the test ranges. To support the

  7. E-2D Advanced Hawkeye: primary flight display (United States)

    Paolillo, Paul W.; Saxena, Ragini; Garruba, Jonathan; Tripathi, Sanjay; Blanchard, Randy


    This paper is a response to the challenge of providing a large area avionics display for the E-2D AHE aircraft. The resulting display design provides a pilot with high-resolution visual information content covering an image area of almost three square feet (Active Area of Samsung display = 33.792cm x 27.0336 cm = 13.304" x 10.643" = 141.596 square inches = 0.983 sq. ft x 3 = 2.95 sq. ft). The avionics display application, design and performance being described is the Primary Flight Display for the E-2D Advanced Hawkeye aircraft. This cockpit display has a screen diagonal size of 17 inches. Three displays, with minimum bezel width, just fit within the available instrument panel area. The significant design constraints of supporting an upgrade installation have been addressed. These constraints include a display image size that is larger than the mounting opening in the instrument panel. This, therefore, requires that the Electromagnetic Interference (EMI) window, LCD panel and backlight all fit within the limited available bezel depth. High brightness and a wide dimming range are supported with a dual mode Cold Cathode Fluorescent Tube (CCFT) and LED backlight. Packaging constraints dictated the use of multiple U shaped fluorescent lamps in a direct view backlight design for a maximum display brightness of 300 foot-Lamberts. The low intensity backlight levels are provided by remote LEDs coupled through a fiber optic mesh. This architecture generates luminous uniformity within a minimum backlight depth. Cross-cockpit viewing is supported with ultra-wide field-of-view performance including contrast and the color stability of an advanced LCD cell design supports. Display system design tradeoffs directed a priority to high optical efficiency for minimum power and weight.

  8. System Software Abstraction Layer - much more than Operating System Abstraction Layer

    Directory of Open Access Journals (Sweden)

    Sunita Awasthi Singh


    Full Text Available Current and future aircraft systems require real-time embedded software with greater flexibility compared to what was previously available due to the continuous advancements in the technology leading to large and complex systems. Portability of software as one of the aspects of this flexibility is a major concern in application development for avionics domain for fast development and integration of systems. Abstractions of the hardware platform which have been already introduced by the operating system community allow the software modules to be reused on different hardware and with different physical resources. Now operating system community has come up with an abstraction layer called operating system abstraction layer (OSAL which along with the hardware abstraction unifies the OS architecture too. It provides a common set of primitives independent of the underlying operating system and its particular architecture. Factors such as reliability, scalability and determinism of any application largely depend on the design and architecture of the application. This is the most important and critical factor of real time systems such as mission computers of avionics systems, missile control system or control computers of space shuttle. It demands developer to perform feasibility of different software architecture to select the best alternative. Authors’ analysis shows that to make any real time application more secure, scalable, deterministic, and highly portable, OSAL has to be extended to more than just operating system abstraction. This new view of OSAL will be called as system software abstraction layer (SSAL. In this paper, authors attempt to highlight the efficiency of SSAL as well as detailed description of its main features and design considerations. Authors have implemented the SSAL on top of two well known OS (WinCE and Vxworks and performed extensive evaluations, which shows that it effectively reduces portability efforts while achieving

  9. Flight evaluation of a computer aided low-altitude helicopter flight guidance system (United States)

    Swenson, Harry N.; Jones, Raymond D.; Clark, Raymond


    The Flight Systems Development branch of the U.S. Army's Avionics Research and Development Activity (AVRADA) and NASA Ames Research Center have developed for flight testing a Computer Aided Low-Altitude Helicopter Flight (CALAHF) guidance system. The system includes a trajectory-generation algorithm which uses dynamic programming and a helmet-mounted display (HMD) presentation of a pathway-in-the-sky, a phantom aircraft, and flight-path vector/predictor guidance symbology. The trajectory-generation algorithm uses knowledge of the global mission requirements, a digital terrain map, aircraft performance capabilities, and precision navigation information to determine a trajectory between mission way points that seeks valleys to minimize threat exposure. This system was developed and evaluated through extensive use of piloted simulation and has demonstrated a 'pilot centered' concept of automated and integrated navigation and terrain mission planning flight guidance. This system has shown a significant improvement in pilot situational awareness, and mission effectiveness as well as a decrease in training and proficiency time required for a near terrain, nighttime, adverse weather system. AVRADA's NUH-60A STAR (Systems Testbed for Avionics Research) helicopter was specially modified, in house, for the flight evaluation of the CALAHF system. The near terrain trajectory generation algorithm runs on a multiprocessor flight computer. Global Positioning System (GPS) data are integrated with Inertial Navigation Unit (INU) data in the flight computer to provide a precise navigation solution. The near-terrain trajectory and the aircraft state information are passed to a Silicon Graphics computer to provide the graphical 'pilot centered' guidance, presented on a Honeywell Integrated Helmet And Display Sighting System (IHADSS). The system design, piloted simulation, and initial flight test results are presented.

  10. Cognition and procedure representational requirements for predictive human performance models (United States)

    Corker, K.


    Models and modeling environments for human performance are becoming significant contributors to early system design and analysis procedures. Issues of levels of automation, physical environment, informational environment, and manning requirements are being addressed by such man/machine analysis systems. The research reported here investigates the close interaction between models of human cognition and models that described procedural performance. We describe a methodology for the decomposition of aircrew procedures that supports interaction with models of cognition on the basis of procedures observed; that serves to identify cockpit/avionics information sources and crew information requirements; and that provides the structure to support methods for function allocation among crew and aiding systems. Our approach is to develop an object-oriented, modular, executable software representation of the aircrew, the aircraft, and the procedures necessary to satisfy flight-phase goals. We then encode in a time-based language, taxonomies of the conceptual, relational, and procedural constraints among the cockpit avionics and control system and the aircrew. We have designed and implemented a goals/procedures hierarchic representation sufficient to describe procedural flow in the cockpit. We then execute the procedural representation in simulation software and calculate the values of the flight instruments, aircraft state variables and crew resources using the constraints available from the relationship taxonomies. The system provides a flexible, extensible, manipulative and executable representation of aircrew and procedures that is generally applicable to crew/procedure task-analysis. The representation supports developed methods of intent inference, and is extensible to include issues of information requirements and functional allocation. We are attempting to link the procedural representation to models of cognitive functions to establish several intent inference methods

  11. Information Management For Tactical Reconnaissance (United States)

    White, James P.


    The expected battlefield tactics of the 1980's and 1990's will be fluid and dynamic. If tactical reconnaissance is to meet this challenge, it must explore all ways of accelerating the flow of information through the reconnaissance cycle, from the moment a tasking request is received to the time the mission results are delivered to the requestor. In addition to near real-time dissemination of reconnaissance information, the mission planning phase needs to be more responsive to the rapidly changing battlefield scenario. By introducing Artificial Intelligence (AI) via an expert system to the mission planning phase, repetitive and computational tasks can be more readily performed by the ground-based mission planning system, thereby permitting the aircrew to devote more of their time to target study. Transporting the flight plan, plus other mission data, to the aircraft is simple with the Fairchild Data Transfer Equipment (DTE). Aircrews are relieved of the tedious, error-prone, and time-consuming task of manually keying-in avionics initialization data. Post-flight retrieval of mission data via the DTE will permit follow-on aircrews, just starting their mission planning phase, to capitalize on current threat data collected by the returning aircrew. Maintenance data retrieved from the recently flown mission will speed-up the aircraft turn-around by providing near-real time fault detection/isolation. As future avionics systems demand more information, a need for a computer-controlled, smart data base or expert system on-board the aircraft will emerge.

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

    Jones, Jonathan; Kibbey, Tim; Lampton, Pat; Brown, Thomas


    A recent explosion in nano-sat, small-sat, and university class payloads has been driven by low cost electronics and sensors, wide component availability, as well as low cost, miniature computational capability and open source code. Increasing numbers of these very small spacecraft are being launched as secondary payloads, dramatically decreasing costs, and allowing greater access to operations and experimentation using actual space flight systems. While manifesting as a secondary payload provides inexpensive rides to orbit, these arrangements also have certain limitations. Small, secondary payloads are typically included with very limited payload accommodations, supported on a non interference basis (to the prime payload), and are delivered to orbital conditions driven by the primary launch customer. Integration of propulsion systems or other hazardous capabilities will further complicate secondary launch arrangements, and accommodation requirements. The National Aeronautics and Space Administration's Marshall Space Flight Center has begun work on the development of small, low cost launch system concepts that could provide dedicated, affordable launch alternatives to small, risk tolerant university type payloads and spacecraft. These efforts include development of small propulsion systems and highly optimized structural efficiency, utilizing modern advanced manufacturing techniques. This paper outlines the plans and accomplishments of these efforts and investigates opportunities for truly revolutionary reductions in launch and operations costs. Both evolution of existing sounding rocket systems to orbital delivery, and the development of clean sheet, optimized small launch systems are addressed. A launch vehicle at the scale and price point which allows developers to take reasonable risks with new propulsion and avionics hardware solutions does not exist today. Establishing this service provides a ride through the proverbial "valley of death" that lies between

  13. AFDX网络协议研究%Research On Network Protocol of AFDX

    Institute of Scientific and Technical Information of China (English)

    赵永库; 李贞; 唐来胜


    Present the generation of AFDX network and it' s development; introduce the sets of specification ARINC664 and the relationship between the OSI model and each part of the specification; figure out the differences between a commercial network and a AFDX network and the relationship between the AFDX network and airborne avionic system; analyzing about the successful usecase in the big aircraft such as A380, show the advantages of AFDX when using in avionic system. AFDX network has been successfully used in practical applications, and it has a full integrated structure in network protocol, is a new type aircraft data network with high performance in Real -time, Determinism and Reliability.%介绍了AFDX网络的产生背景及发展历程;解析了ARINC664规范各个部分的功能及与开放式系统参考模型的关系;总结了AFDX网络相对于商用以太网的特点和AFDX网络与机载系统的关系,通过对AFDX在A380等飞机上的应用研究,归纳了基于AFDX网络的航空电子系统的特点.AFDX网络已成功应用于工程实践,该网络具有完整的协议结构,具有高实时性、高确定性和高可靠性的特点,是一种新型的机载网络总线.

  14. Visualización de Datos Radar en Tres Dimensiones sobre Mapa Geográfico Digital

    Directory of Open Access Journals (Sweden)

    Monserrat del Carmen De León Cedillo


    Full Text Available Esta obra contribuye al control del tránsito aéreo. Particularmente en la detección y seguimiento de las aeronaves en vuelo a través de sistemas electrónicos. El radar le permite al controlador de tráfico aéreo ubicar aeronaves volando bajo su jurisdicción, su destino, la altitud y la velocidad adquirida. Esto le da la oportunidad de proporcionar instrucciones precisas a las tripulaciones, para mantener la separación adecuada entre aeronaves permitiendo un flujo constante y seguro de las mismas. Gracias al empleo de diversas técnicas, el resultado final es la presentación en pantalla, de la posición de cada uno de los aviones detectados por él, en un mapa similar a un plano cartesiano cuyo origen representa el punto donde se encuentra la torre de control. Google Earth permite establecer una visión tridimensional de la ubicación de aeronaves, usando una interfaz de un software como el Visual Basic, y así, se pueden explotar los datos de radar en diferentes áreas del control de tránsito aéreo, desde la planeación de aerovías, la vigilancia, el estudio y solución de fenómenos en la detección de aviones, análisis de accidentes e incidentes, hasta la capacitación de personal. Todo lo anterior utilizando información generada por los sistemas instalados actualmente, sin necesidad de adquirir equipo costoso y poco convencional.

  15. An integrated approach toward recognizing, locating and combating targets from a modern interceptor aircraft (United States)

    Meyhoff, E. G.; Kloeckner, H. W.


    Interceptor aircraft of the future will find themselves in an environment which will not only be significantly more hostile than today but also far more difficult to assess. On the one hand the requirement will be to reduce the detectability of the own aircraft and on the other to enhance the capability of destroying enemy targets. Reduction of detectability can be achieved through a variety of measures such as lowering the radar cross section, the IR emission or the RF emission. Enhancement of the capability to destroy enemy target requires, next to better weapons, longer detection and identification ranges as well as quicker reaction times. Faster reaction times are not only required to gain advantages in combating the designated enemy targets but also to respond to threat situations which may emanate from sources other than the targets. The requirement will exist for an avionic system capable of correlating all relevant data and either reaching decisions itself or presenting the pilot with information in such a way that they support his own making process. This paper describes a typical set of aircraft equipments which would be involved in the data acquisition and decision making processes; it quantifies data volumes and rates and, based on these figures, attempts to define processing and correlation requirements. It then proposes a system architecture which might be suitable for the tasks at hand. The emphasis of the paper will be on assessing the impact of LSI/VHSIC technology on those portions of the avionics system which are utilized in the processes described above.

  16. Dhaksha, the Unmanned Aircraft System in its New Avatar-Automated Aerial Inspection of INDIA'S Tallest Tower (United States)

    Kumar, K. S.; Rasheed, A. Mohamed; Krishna Kumar, R.; Giridharan, M.; Ganesh


    DHAKSHA, the unmanned aircraft system (UAS), developed after several years of research by Division of Avionics, Department of Aerospace Engineering, MIT Campus of Anna University has recently proved its capabilities during May 2012 Technology demonstration called UAVforge organised by Defence Research Project Agency, Department of Defence, USA. Team Dhaksha with its most stable design outperformed all the other contestants competing against some of the best engineers from prestigi ous institutions across the globe like Middlesex University from UK, NTU and NUS from Singapore, Tudelft Technical University, Netherlands and other UAV industry participants in the world's toughest UAV challenge. This has opened up an opportunity for Indian UAVs making a presence in the international scenario as well. In furtherance to the above effort at Fort Stewart military base at Georgia,USA, with suitable payloads, the Dhaksha team deployed the UAV in a religious temple festival during November 2012 at Thiruvannamalai District for Tamil Nadu Police to avail the instant aerial imagery services over the crowd of 10 lakhs pilgrims and also about the investigation of the structural strength of the India's tallest structure, the 300 m RCC tower during January 2013. The developed system consists of a custom-built Rotary Wing model with on-board navigation, guidance and control systems (NGC) and ground control station (GCS), for mission planning, remote access, manual overrides and imagery related computations. The mission is to fulfill the competition requirements by using an UAS capable of providing complete solution for the stated problem. In this work the effort to produce multirotor unmanned aerial systems (UAS) for civilian applications at the MIT, Avionics Laboratory is presented


    Klumpp, A. R.


    This package extends the Ada programming language to include linear algebra capabilities similar to those of the HAL/S programming language. The package is designed for avionics applications such as Space Station flight software. In addition to the HAL/S built-in functions, the package incorporates the quaternion functions used in the Shuttle and Galileo projects, and routines from LINPAK that solve systems of equations involving general square matrices. Language conventions in this package follow those of HAL/S to the maximum extent practical and minimize the effort required for writing new avionics software and translating existent software into Ada. Valid numeric types in this package include scalar, vector, matrix, and quaternion declarations. (Quaternions are fourcomponent vectors used in representing motion between two coordinate frames). Single precision and double precision floating point arithmetic is available in addition to the standard double precision integer manipulation. Infix operators are used instead of function calls to define dot products, cross products, quaternion products, and mixed scalar-vector, scalar-matrix, and vector-matrix products. The package contains two generic programs: one for floating point, and one for integer. The actual component type is passed as a formal parameter to the generic linear algebra package. The procedures for solving systems of linear equations defined by general matrices include GEFA, GECO, GESL, and GIDI. The HAL/S functions include ABVAL, UNIT, TRACE, DET, INVERSE, TRANSPOSE, GET, PUT, FETCH, PLACE, and IDENTITY. This package is written in Ada (Version 1.2) for batch execution and is machine independent. The linear algebra software depends on nothing outside the Ada language except for a call to a square root function for floating point scalars (such as SQRT in the DEC VAX MATHLIB library). This program was developed in 1989, and is a copyrighted work with all copyright vested in NASA.

  18. A Scalable, Out-of-Band Diagnostics Architecture for International Space Station Systems Support (United States)

    Fletcher, Daryl P.; Alena, Rick; Clancy, Daniel (Technical Monitor)


    The computational infrastructure of the International Space Station (ISS) is a dynamic system that supports multiple vehicle subsystems such as Caution and Warning, Electrical Power Systems and Command and Data Handling (C&DH), as well as scientific payloads of varying size and complexity. The dynamic nature of the ISS configuration coupled with the increased demand for payload support places a significant burden on the inherently resource constrained computational infrastructure of the ISS. Onboard system diagnostics applications are hosted on computers that are elements of the avionics network while ground-based diagnostic applications receive only a subset of available telemetry, down-linked via S-band communications. In this paper we propose a scalable, out-of-band diagnostics architecture for ISS systems support that uses a read-only connection for C&DH data acquisition, which provides a lower cost of deployment and maintenance (versus a higher criticality readwrite connection). The diagnostics processing burden is off-loaded from the avionics network to elements of the on-board LAN that have a lower overall cost of operation and increased computational capacity. A superset of diagnostic data, richer in content than the configured telemetry, is made available to Advanced Diagnostic System (ADS) clients running on wireless handheld devices, affording the crew greater mobility for troubleshooting and providing improved insight into vehicle state. The superset of diagnostic data is made available to the ground in near real-time via an out-of band downlink, providing a high level of fidelity between vehicle state and test, training and operational facilities on the ground.

  19. Ampliación del hangar n° 2 Aeropuerto de Madrid-Barajas España

    Directory of Open Access Journals (Sweden)

    Tabera García, Antonio


    Full Text Available The necessity to carry out maintenance work on Iberia's AIRBUS planes obligates this company to enlarge hangar n.° 2, up till now intended for standard type planes. After a study of diverse proposals: isostatic double-supported beam, mixed portico of reinforced concrete and metal beam, etc. and taking into account the limitations of height and the obligation of air space, call for a structure with a maximum thickness of 6,50 m, the solution was adopted of a latticed metalic beam of 125,60 of length (110,60 m between axes of supports and two projections of 7,5 m anchored in the foundations, 3,00 m wide and 6,50 m thick. The beam was partially prefabricated in the factory and it took seven days to position it.La necesidad de realizar trabajos de mantenimiento de los aviones AIRBUS de Iberia obligaron a esta compañía a ampliar el hangar nº 2 hasta ahora destinado a aviones de tipo medio. Después del estudio de diversas propuestas: viga biapoyada isostática, pórtico mixto de hormigón armado y viga metálica, etc., y teniendo en cuenta las limitaciones de altura y la de servidumbre del espacio aéreo, que obligaban a una estructura de 6,50 m de canto máximo, se adoptó la solución de una viga metálica de celosía de 125,60 m de longitud (110,60 m entre ejes de apoyos y dos voladizos de 7,5 m anclados al cimiento, 3,00 m de ancho y 6,50 m de canto. La viga se prefabricó parcialmente en taller y el izado duró siete días.

  20. 虚拟链路精确流模型在 AFDX 网络演算中的应用%Using an Accurate Flow Model of Virtual Link to Optimize Network Calculus Approach in AFDX

    Institute of Scientific and Technical Information of China (English)

    刘成; 周立; 屠晓杰; 王彤


    Avionics Full Duplex Switched Ethernet ( AFDX ) standardized as ARINC 664 is an upgrade from Ethernet for avionics demand .AFDX adopts the mechanisms such as Virtual Link ( VL) and traffic policing for the determinacy of communication task .Network calculus approach is a basic tool to compute the upper bound of end-to-end delay for VL in AFDX network,which give AFDX a useful method to research the real-time performance .However,the network calculus approach used a simple flow model of VL .Based on that model,the result got by network calculus approach is pessimistic .An accurate flow model of VL is adopted in the network calculus approach in this paper,and it helps the network calculus approach to get a tighter upper bound of delay for VL .%航空电子全双工交换式以太网( AFDX)是针对航空电子应用从工业交换式以太网升级而来的。其中,引入的虚拟链路( VL)和流量管制机制为网络通信任务提供了确定性的保障。网络演算是AFDX中常用的VL延时上界计算工具,为AFDX网络的实时性研究提供了理论依据。但是网络演算采用了VL简单流模型,计算得到的延时上界比较悲观。将VL精确流模型应用在网络演算工具中,并展示了基于精确流模型的网络演算能够得到更紧的延时上界计算结果。

  1. Effect of aircraft noise on hearing of ground crew with different positions%飞机噪声对不同岗位机务人员听力的影响

    Institute of Scientific and Technical Information of China (English)

    张方; 冯潇炜; 曹新生; 谢文良; 梁锐明; 高璐璐; 张仲平


    目的:比较噪声对不同岗位机务人员听力的影响。方法选取某军区空军机务人员作为调查对象,按照工作岗位分为机械组(736人)、军械组(294人)、电子组(334人)、特设组(350人)四组。采用电测听仪检查所有被试人员纯音听力。结果四组机务人员均出现一定比例的听力障碍,分别为机械12.0%,军械9.5%,电子10.2%,特设12.0%;高频听力受损分别为机械45.1%,军械45.5%,电子34.8%,特设57.7%。特设组显著高于其他三组(P<0.01)。各组机务人员的高频听力受损的最敏感频率均为6000 Hz,在听力图上呈现典型的V形凹陷。结论噪声对机务人员的听力均有不良影响,高频听力受损发生率高,且以6000 Hz最为敏感,特设人员高频听力受损高于其他工种。%Objective We directed to study the effect of military aircraft noise on hearing of ground crew with different positions. Methods 1714 military ground crew were chosen for the survey. They were divided into 4 groups:Machinery (736), Ordnance (294), Avionics (334), and Special Equipment (350). Hearings of all subjects were tested by electric audiometer. Results Hearing damage occurred in all the four groups of ground crew as follows:Machinery 12.0%,Ordnance 9.5%,Avionics 10.2%, and Special Equipment 12.0%. The high-frequency hearing impairment were very common in ground crew:Machinery 45.1%,Ordnance 45.5%, Avionics 34.8%, and Special Equipment 57.7%, and the incidence for the Special Equipment was significantly higher than the other three groups (P<0.01). Meanwhile, the most sensitive frequency of the high-frequency hearing impairment occurred at 6000 Hz in all the four groups, suggesting a typical"V"-shaped trough in the audiogram. Conclusion For hearing damage, there was no apparent difference among different military ground crew, while high-frequency hearing impairment in the special equipment group was worse than the other

  2. System Software Abstraction Layer - much more than Operating System Abstraction Layer

    Directory of Open Access Journals (Sweden)

    Sunita Awasthi Singh


    Full Text Available Current and future aircraft systems require real-time embedded software with greater flexibility compared to what was previously available due to the continuous advancements in the technology leading to large and complex systems. Portability of software as one of the aspects of this flexibility is a major concern in application development for avionics domain for fast development and integration of systems. Abstractions of the hardware platform which have been already introduced by the operating system community allow the software modules to be reused on different hardware and with different physical resources. Now operating system community has come up with an abstraction layer called operating system abstraction layer (OSAL which along with the hardware abstraction unifies the OS architecture too. It provides a common set of primitives independent of the underlying operating system and its particular architecture. Factors such as reliability, scalability and determinism of any application largely depend on the design and architecture of the application. This is the most important and critical factor of real time systems such as mission computers of avionics systems, missile control system or control computers of space shuttle. It demands developer to perform feasibility of different software architecture to select the best alternative. Authors’ analysis shows that to make any real time application more secure, scalable, deterministic, and highly portable, OSAL has to be extended to more than just operating system abstraction. This new view of OSAL will be called as system software abstraction layer (SSAL. In this paper, authors attempt to highlight the efficiency of SSAL as well as detailed description of its main features and design considerations. Authors have implemented the SSAL on top of two well known OS (WinCE and Vxworks and performed extensive evaluations, which shows that it effectively reduces portability efforts while achieving

  3. Software in military aviation and drone mishaps: Analysis and recommendations for the investigation process

    International Nuclear Information System (INIS)

    Software plays a central role in military systems. It is also an important factor in many recent incidents and accidents. A safety gap is growing between our software-intensive technological capabilities and our understanding of the ways they can fail or lead to accidents. Traditional forms of accident investigation are poorly equipped to trace the sources of software failure, for instance software does not age in the same way that hardware components fail over time. As such, it can be hard to trace the causes of software failure or mechanisms by which it contributed to accidents back into the development and procurement chain to address the deeper, systemic causes of potential accidents. To identify some of these failure mechanisms, we examined the database of the Air Force Accident Investigation Board (AIB) and analyzed mishaps in which software was involved. Although we have chosen to focus on military aviation, many of the insights also apply to civil aviation. Our analysis led to several results and recommendations. Some were specific and related for example to specific shortcomings in the testing and validation of particular avionic subsystems. Others were broader in scope: for instance, we challenged both the investigation process (aspects of) and the findings in several cases, and we provided recommendations, technical and organizational, for improvements. We also identified important safety blind spots in the investigations with respect to software, whose contribution to the escalation of the adverse events was often neglected in the accident reports. These blind spots, we argued, constitute an important missed learning opportunity for improving accident prevention, and it is especially unfortunate at a time when Remotely Piloted Air Systems (RPAS) are being integrated into the National Airspace. Our findings support the growing recognition that the traditional notion of software failure as non-compliance with requirements is too limited to capture the

  4. Cibola flight experiment satellite (United States)

    Davies, P.; Liddle, Doug; Paffett, John; Sweeting, Martin; Curiel, A.; Sun, Wei; Eves, Stuart


    In order to achieve an "economy of scale" with respect to payload capacity the major trend in telecommunications satellites is for larger and larger platforms. With these large platforms the level of integration between platform and payload is increasing leading to longer delivery schedules. The typical lifecycle for procurement of these large telecommunications satellites is now 3-6 years depending on the level of non-recurring engineering needed. Surrey Satellite Technology Ltd (SSTL) has designed a low-cost platform aimed at telecommunications and navigation applications. SSTL's Geostationary Minisatellite Platform (GMP) is a new entrant addressing the lower end of the market with payloads up to 250kg requiring less than 1.5 kW power. The British National Space Centre through the MOSAIC Small Satellite Initiative supported the development of GMP. The main design goals for GMP are low-cost for the complete mission including launch and operations and a platform allowing flexible payload accommodation. GMP is specifically designed to allow rapid development and deployment with schedules typically between 1 and 2 years from contract signature to flight readiness. GMP achieves these aims by a modular design where the level of integration between the platform and payload is low. The modular design decomposes the satellite into three major components - the propulsion bay, the avionics bay and the payload module. Both the propulsion and avionics bays are reusable, largely unchanged, and independent of the payload configuration. Such a design means that SSTL or a 3rd party manufacturer can manufacture the payload in parallel to the platform with integration taking place quite late in the schedule. In July 2003 SSTL signed a contract for ESA's first Galileo navigation satellite known as GSTBV2/A. The satellite is based on GMP and ESA plan to launch it into a MEO orbit late in 2005. The second flight of GMP is likely to be in 2006 carrying a geostationary payload

  5. An Efficient Algorithm for Switcher Flow Control Used for AFDX Network%面向AFDX网络的交换机流量管制算法

    Institute of Scientific and Technical Information of China (English)

    王红春; 张涛; 牛文生


    An integrated avionics system uses the avionics full duplex switched (AFDX) Ethernet to construct the aviation backbone network, which has the characteristics of certainty, broad bandwidth and extension. Sections 1 and 2 explain our new algorithm, which we believe is more efficient than previous ones and whose core consists of; (1) we use the virtual link (VL) and the bandwidth assignment gap (BAG) to achieve network communication certainty; (2) we use redundancy management mechanism, frame filtering mechanism and flow control method to enhance the transmission reliability of the AFDX Ethernet; ( 3) to control the switcher flow 7 we use the token-bucket algorithm to make sure that the incoming frames meet the constraints of switcher flow according to user-specified rules; (4) we use the frame-based token-bucket algorithm to design respectively our flow control algorithm and shared Account flow control algorithm. Section 3 verifies our flow control algorithm with the AFDX Test and Certification System (ATCS) of AIM GmbH; the test results, given in Figs. 3 and 4, and their analysis show preliminarily that; (1) our flow control algorithm can avoid the excessive use of network bandwidth that is occupied by a certain VL, thus ensuring the isolation of transmission bandwidth of various VLs and the communication certainty; ( 2 ) in different scenarios, including shared Account, the flow control algorithm designed by us can efficiently control the incoming flow of the AFDX switcher.%综合化航空电子系统采用ARINC664航空电子全双工交换网(AFDX)构建主干数据通信网络,该网络具有通信带宽高、传输延迟确定、扩展能力强等特点.AFDX交换机采用流量管制技术检测虚链路的数据传输是否满足流量规则约束,能避免虚链路超限使用带宽,有效保证不同虚链路传输带宽隔离和通信确定性.文章基于ARINC664规范,提出了一种AFDX交换机流量管制的设计与验

  6. FC交换机芯片交换端口虚拟验证关键技术研究%Research on Key Techniques of Virtual Test on Switch Port of FC Switch Chip

    Institute of Scientific and Technical Information of China (English)

    王玉欢; 田泽; 杨海波; 蔡叶芳


    The avionics system of new generation aircraft uses fibre channel as the main communication network,FC switch is the core e-quipment among the network topology. So the importance of building avionics FC network is developing a FC switch chip. With develo-ping of the chip,the core circuit of the switch chip—sufficiently virtual platform for validation of switch ports can effectively shorten the error correction time in the design of whole chip. It also can lower risks and speed up the chip design and verification. Combined with the characteristics of multiple FC switch ports chip in this paper,the switch port core circuit verification planning,platform building and im-plementation of verification,and other key technology are studied,and described by the validation strategy is verified. The results show that the function and performance of the switch ports can meet the design requirements.%新一代飞机航电系统采用光纤通道为主干通信网络,FC交换机是其网络拓扑中的核心设备。因此,研制FC交换机核心芯片是构建航电FC网络的关键。在芯片研制过程中,对交换机芯片的核心电路—交换端口进行充分虚拟平台仿真验证,能够有效缩短全芯片设计中的查错纠错时间,从而降低风险,加快芯片的设计、验证进度。文中结合多端口FC交换机芯片特点,对其交换端口核心电路的验证策划、验证平台搭建以及验证实施等关键技术进行了研究,并通过文中描述的验证策略对其进行了验证。结果表明,交换端口的功能和性能均满足设计需求。

  7. Design and Realization of a Missile Tasks and Missile Simulator Simulation System%导弹任务器与导弹模拟器仿真系统设计与实现

    Institute of Scientific and Technical Information of China (English)

    刘明阳; 张建东; 庞敏


    Missile tasks and Missile simulator simulation system is a simulation testing system for the suspender management subsystem of the integrated avionics system. Based on the studies of integrated avionics system, we used the object - oriented technology to establish a simulation design. According to the software engineering specifications, using Visual C+ + 6. 0 software to achieve the real - time communication and management of the Missile tasks simulator with the Missile simulator. The design of the simulation system, system management, the implement process of software and the hardware are mainly discussed. Through modular design , combined with the selection of hardware (1553B PCI -MCH board) , System software achieves the functions of missile category management, mission planning, and loading information. Simulation testing proved that the communication system worked well, good performance, can achieve the 1553B data transmission requirement accurately. It can also achieve the designed functional requirements, and has good practical value.%导弹任务器与导弹模拟器仿真系统是军用综合航电系统外挂物管理子系统的仿真测试系统;运用面向对象技术,基于综合航空电子系统外挂物的研究建立仿真设计,按照软件工程规范,利用Visual C+ +6.0开发软件实现导弹任务仿真器与导弹模拟器实时通讯管理.讨论了整个仿真系统的设计,系统管理,软硬件开发过程;系统软件通过模块化的设计方法实现,结合选用硬件通过1553B数据总线实现对导弹进行分类管理,任务规划,加载信息等功能;仿真测试证明,通信系统工作正常、性能良好,能准确实现1553B数据传输,完成各项功能要求,具有较好的实用价值.

  8. Assessing Requirements Quality through Requirements Coverage (United States)

    Rajan, Ajitha; Heimdahl, Mats; Woodham, Kurt


    In model-based development, the development effort is centered around a formal description of the proposed software system the model. This model is derived from some high-level requirements describing the expected behavior of the software. For validation and verification purposes, this model can then be subjected to various types of analysis, for example, completeness and consistency analysis [6], model checking [3], theorem proving [1], and test-case generation [4, 7]. This development paradigm is making rapid inroads in certain industries, e.g., automotive, avionics, space applications, and medical technology. This shift towards model-based development naturally leads to changes in the verification and validation (V&V) process. The model validation problem determining that the model accurately captures the customer's high-level requirements has received little attention and the sufficiency of the validation activities has been largely determined through ad-hoc methods. Since the model serves as the central artifact, its correctness with respect to the users needs is absolutely crucial. In our investigation, we attempt to answer the following two questions with respect to validation (1) Are the requirements sufficiently defined for the system? and (2) How well does the model implement the behaviors specified by the requirements? The second question can be addressed using formal verification. Nevertheless, the size and complexity of many industrial systems make formal verification infeasible even if we have a formal model and formalized requirements. Thus, presently, there is no objective way of answering these two questions. To this end, we propose an approach based on testing that, when given a set of formal requirements, explores the relationship between requirements-based structural test-adequacy coverage and model-based structural test-adequacy coverage. The proposed technique uses requirements coverage metrics defined in [9] on formal high-level software

  9. Solid Rocket Booster (SRB) Flight System Integration at Its Best (United States)

    Wood, T. David; Kanner, Howard S.; Freeland, Donna M.; Olson, Derek T.


    The Solid Rocket Booster (SRB) element integrates all the subsystems needed for ascent flight, entry, and recovery of the combined Booster and Motor system. These include the structures, avionics, thrust vector control, pyrotechnic, range safety, deceleration, thermal protection, and retrieval systems. This represents the only human-rated, recoverable and refurbishable solid rocket ever developed and flown. Challenges included subsystem integration, thermal environments and severe loads (including water impact), sometimes resulting in hardware attrition. Several of the subsystems evolved during the program through design changes. These included the thermal protection system, range safety system, parachute/recovery system, and others. Because the system was recovered, the SRB was ideal for data and imagery acquisition, which proved essential for understanding loads, environments and system response. The three main parachutes that lower the SRBs to the ocean are the largest parachutes ever designed, and the SRBs are the largest structures ever to be lowered by parachutes. SRB recovery from the ocean was a unique process and represented a significant operational challenge; requiring personnel, facilities, transportation, and ground support equipment. The SRB element achieved reliability via extensive system testing and checkout, redundancy management, and a thorough postflight assessment process. However, the in-flight data and postflight assessment process revealed the hardware was affected much more strongly than originally anticipated. Assembly and integration of the booster subsystems required acceptance testing of reused hardware components for each build. Extensive testing was done to assure hardware functionality at each level of stage integration. Because the booster element is recoverable, subsystems were available for inspection and testing postflight, unique to the Shuttle launch vehicle. Problems were noted and corrective actions were implemented as needed

  10. Fiber-Optic Magnetic-Field-Strength Measurement System for Lightning Detection (United States)

    Gurecki, Jay; Scully, Robert; Davis, Allen; Kirkendall, Clay; Bucholtz, Frank


    A fiber-optic sensor system is designed to measure magnetic fields associated with a lightning stroke. Field vector magnitudes are detected and processed for multiple locations. Since physical limitations prevent the sensor elements from being located in close proximity to highly conductive materials such as aluminum, the copper wire sensor elements (3) are located inside a 4-cubic-in. (.66-cubic-cm) plastic housing sensor head and connected to a fiber-optic conversion module by shielded cabling, which is limited to the shortest length feasible. The signal path between the conversion module and the avionics unit which processes the signals are fiber optic, providing enhanced immunity from electromagnetic radiation incident in the vicinity of the measurements. The sensors are passive, lightweight, and much smaller than commercial B-dot sensors in the configuration which measures a three-dimensional magnetic field. The system is expandable, and provides a standard-format output signal for downstream processing. Inside of the sensor head, three small search coils, each having a few turns on a circular form, are mounted orthogonally inside the non-metallic housing. The fiber-optic conversion module comprises three interferometers, one for each search coil. Each interferometer has a high bandwidth optical phase modulator that impresses the signal received from its search coil onto its output. The output of each interferometer travels by fiber optic cable to the avionics unit, and the search coil signal is recovered by an optical phase demodulator. The output of each demodulator is fed to an analog-to-digital converter, whose sampling rate is determined by the maximum expected rate of rise and peak signal magnitude. The output of the digital processor is a faithful reproduction of the coil response to the incident magnetic field. This information is provided in a standard output format on a 50-ohm port that can be connected to any number of data collection and processing

  11. Fly-by-Light Advanced Systems Hardware (FLASH) program (United States)

    Bedoya, Carlos A.


    Fiber optics are immune to electromagnetic emissions and have the potential to eliminate this concern especially in flight critical applications if they can be developed to the same level of technology as current systems using wire to carry the signals. As aircraft become more and more dependent of digital signals to control all systems, the Electromagnetic Environment (EME) will become more and more a concern for the safe long term operation. The International Severe HIRF electromagnetic environment (EME) is less than 2000 Volts per meter below 400 MHz and reaches a maximum of 6,850 Volts per meter in the 4-6 GHz range. The normal assumption is that a metal or composite aircraft skin with appropriate seals provides 20 dB attenuation of the external environment. This reduces peak levels at the avionics boxes to less than 200 Volts per meter below 400 MHz and a maximum of 685 Volts per meter in the 406 GHz range. MIL-STD-461D imposed an additional box level requirement to 200 Volts per meter from 10 KHz to 40 GHz. This requirement equals or surpasses the attenuated HIRF environment over significant portions of the spectrum and implies that the aircraft must be designed to achieve and maintain this value throughout its service life. Although wires can be shielded and designed to achieve these requirements, it is a more expensive process, adds the weight of shielding and requires maintenance of the shielding integrity at all times. The very light weight and high bandwidth of fiber optics also offer the potential of eliminating the number of connections and weight savings in aircraft. For example on a one to one replacement of wire by fiber, it is estimated that fiber would weight about 1/20 the weight of wire. Current wire buses used for duplex communications in aircraft applications have a bandwidth of about 1 MHz while equivalent buses using fiber optics have a bandwidth of 20 MHz. For other applications such as video and avionics interfaces, fiber buses in the

  12. AERCam Autonomy: Intelligent Software Architecture for Robotic Free Flying Nanosatellite Inspection Vehicles (United States)

    Fredrickson, Steven E.; Duran, Steve G.; Braun, Angela N.; Straube, Timothy M.; Mitchell, Jennifer D.


    The NASA Johnson Space Center has developed a nanosatellite-class Free Flyer intended for future external inspection and remote viewing of human spacecraft. The Miniature Autonomous Extravehicular Robotic Camera (Mini AERCam) technology demonstration unit has been integrated into the approximate form and function of a flight system. The spherical Mini AERCam Free Flyer is 7.5 inches in diameter and weighs approximately 10 pounds, yet it incorporates significant additional capabilities compared to the 35-pound, 14-inch diameter AERCam Sprint that flew as a Shuttle flight experiment in 1997. Mini AERCam hosts a full suite of miniaturized avionics, instrumentation, communications, navigation, power, propulsion, and imaging subsystems, including digital video cameras and a high resolution still image camera. The vehicle is designed for either remotely piloted operations or supervised autonomous operations, including automatic stationkeeping, point-to-point maneuvering, and waypoint tracking. The Mini AERCam Free Flyer is accompanied by a sophisticated control station for command and control, as well as a docking system for automated deployment, docking, and recharge at a parent spacecraft. Free Flyer functional testing has been conducted successfully on both an airbearing table and in a six-degree-of-freedom closed-loop orbital simulation with avionics hardware in the loop. Mini AERCam aims to provide beneficial on-orbit views that cannot be obtained from fixed cameras, cameras on robotic manipulators, or cameras carried by crewmembers during extravehicular activities (EVA s). On Shuttle or International Space Station (ISS), for example, Mini AERCam could support external robotic operations by supplying orthogonal views to the intravehicular activity (IVA) robotic operator, supply views of EVA operations to IVA and/or ground crews monitoring the EVA, and carry out independent visual inspections of areas of interest around the spacecraft. To enable these future benefits

  13. Utilisation d'analyse de concepts formels pour la gestion de variabilite d'un logiciel configure dynamiquement (United States)

    Menguy, Theotime

    Because of its critical nature, avionic industry is bound with numerous constraints such as security standards and certifications while having to fulfill the clients' desires for personalization. In this context, variability management is a very important issue for re-engineering projects of avionic softwares. In this thesis, we propose a new approach, based on formal concept analysis and semantic web, to support variability management. The first goal of this research is to identify characteristic behaviors and interactions of configuration variables in a dynamically configured system. To identify such elements, we used formal concept analysis on different levels of abstractions in the system and defined new metrics. Then, we built a classification for the configuration variables and their relations in order to enable a quick identification of a variable's behavior in the system. This classification could help finding a systematic approach to process variables during a re-engineering operation, depending on their category. To have a better understanding of the system, we also studied the shared controls of code between configuration variables. A second objective of this research is to build a knowledge platform to gather the results of all the analysis performed, and to store any additional element relevant in the variability management context, for instance new results helping define re-engineering process for each of the categories. To address this goal, we built a solution based on a semantic web, defining a new ontology, very extensive and enabling to build inferences related to the evolution processes. The approach presented here is, to the best of our knowledge, the first classification of configuration variables of a dynamically configured software and an original use of documentation and variability management techniques using semantic web in the aeronautic field. The analysis performed and the final results show that formal concept analysis is a way to

  14. Space Shuttle Star Tracker Challenges (United States)

    Herrera, Linda M.


    The space shuttle fleet of avionics was originally designed in the 1970's. Many of the subsystems have been upgraded and replaced, however some original hardware continues to fly. Not only fly, but has proven to be the best design available to perform its designated task. The shuttle star tracker system is currently flying as a mixture of old and new designs, each with a unique purpose to fill for the mission. Orbiter missions have tackled many varied missions in space over the years. As the orbiters began flying to the International Space Station (ISS), new challenges were discovered and overcome as new trusses and modules were added. For the star tracker subsystem, the growing ISS posed an unusual problem, bright light. With two star trackers on board, the 1970's vintage image dissector tube (IDT) star trackers track the ISS, while the new solid state design is used for dim star tracking. This presentation focuses on the challenges and solutions used to ensure star trackers can complete the shuttle missions successfully. Topics include KSC team and industry partner methods used to correct pressurized case failures and track system performance.

  15. Small Autonomous Aircraft Servo Health Monitoring (United States)

    Quintero, Steven


    Small air vehicles offer challenging power, weight, and volume constraints when considering implementation of system health monitoring technologies. In order to develop a testbed for monitoring the health and integrity of control surface servos and linkages, the Autonomous Aircraft Servo Health Monitoring system has been designed for small Uninhabited Aerial Vehicle (UAV) platforms to detect problematic behavior from servos and the air craft structures they control, This system will serve to verify the structural integrity of an aircraft's servos and linkages and thereby, through early detection of a problematic situation, minimize the chances of an aircraft accident. Embry-Riddle Aeronautical University's rotary-winged UAV has an Airborne Power management unit that is responsible for regulating, distributing, and monitoring the power supplied to the UAV's avionics. The current sensing technology utilized by the Airborne Power Management system is also the basis for the Servo Health system. The Servo Health system measures the current draw of the servos while the servos are in Motion in order to quantify the servo health. During a preflight check, deviations from a known baseline behavior can be logged and their causes found upon closer inspection of the aircraft. The erratic behavior nay include binding as a result of dirt buildup or backlash caused by looseness in the mechanical linkages. Moreover, the Servo Health system will allow elusive problems to be identified and preventative measures taken to avoid unnecessary hazardous conditions in small autonomous aircraft.

  16. Equipping an FPGA-Based Mars Rover With an LN-200 IMU (United States)

    Zola, Nicholas J.


    The Mars Exploration Rovers (MER) currently navigating the surface of Mars are outfitted with an advanced stereovision correlation algorithm which allows them to "see" three-dimensionally and autonomously avoid obstac'les in their path. A bottleneck of this system is that it is computationally intense and requires 3 minutes of processing for every correlated image and path choice. Taking advantage of the optimization and reprogrammability of FPGAs, the Mobility Avionics lab has reduced this process to under a second. The lab is demonstrating the advancement with a prototype rover, complete with an LN-200 inertial measurement unit (IMU), which is a flight spare from MER. The LN-200 is a space-grade, six degrees-of-freedom IMU using three fiber-optic gyroscopes and three silicon accelerometers and no moving parts. It has particular power-sequencing needs and communicates with a specialized serial protocol (SDLC over RS-422), requiring specific hardware and software for proper functionality and interfacing with an FPGA. The process of incorporating the LN-200 into the system is described herein.

  17. ISS Propulsion Module Crew Systems Interface Analysis in the Intelligent Synthesis Environment (United States)

    Chen, Di-Wen


    ERGO, a human modeling software for ergonomic assessment and task analysis, was used for the crew systems interface analysis of the International Space Station (ISS) Propulsion Module (PM). The objective of analysis was to alleviate passageway size concerns. Three basic passageway configuration concepts: (1) 45" clear passageway without centerline offset (2) 50" clear passageway, 12" centerline offset, (3) 50" clear passageway, no centerline offset, and were reviewed. 95 percentile male and female models which were provided by the software performed crew system analysis from an anthropometric point of view. Four scenarios in which the crew floats in microgravity through a 50" no-offset passageway as they carry a 16" x 20" x 30" avionics box were simulated in the 10-weeks of intensive study. From the results of the analysis, concept (3) was the preferred option. A full scale, three-dimensional virtual model of the ISS Propulsion Module was created to experience the sense of the Intelligent Synthesis Environment and to evaluate the usability and applicability of the software.

  18. Cost effective optical coupling for polymer optical fiber communication (United States)

    Chandrappan, Jayakrishnan; Zhang, Jing; Mohan, Ramkumar V.; Gomez, Philbert Oliver; Aung, Than Aye; Xiao, Yongfei; Ramana, Pamidighantam V.; Lau, John Hon Shing; Kwong, Dim Lee


    Polymer Optical Fiber (POF) optical modules are gaining momentum due to their applications in short distance communications. POFs offer more flexibility for plug and play applications and provide cost advantages. They also offer significant weight advantage in automotive and avionic networks. One of the most interesting field of application is home networking. Low cost optical components are required, since cost is a major concern in local and home networks. In this publication, a fast and easy to install, low cost solution for efficient light coupling in and out of Step Index- POF is explored. The efficient coupling of light from a large core POF to a small area detector is the major challenge faced. We simulated direct coupling, lens coupling and bend losses for step index POF using ZEMAX R optical simulation software. Simulations show that a lensed fiber tip particularly at the receiver side improves the coupling efficiency. The design is optimized for 85% coupling efficiency and explored the low cost fabrication method to implement it in the system level. The two methods followed for lens fabrication is described here in detail. The fabricated fiber lenses are characterized using a beam analyzer. The fabrication process was reiterated to optimize the lens performance. It is observed that, the fabricated lenses converge the POF output spot size by one fourth, there by enabling a higher coupling efficiency. This low cost method proves to be highly efficient and effective optical coupling scheme in POF communications.

  19. Hydrodynamic impact analysis and testing of an unmanned aerial vehicle (United States)

    Bird, Isabel

    Analysis and testing have been conducted to assess the feasibility of a small UAV that can be landed in the water and recovered for continued use. Water landings may be desirable in a number of situations, for example when testing UAVs outside of the territorial waters of the US to avoid violating FAA regulations. Water landings may also be desirable when conducting surveillance missions in marine environments. Although the goal in landing is to have the UAV lightly set down on the water, rough seas or gusty winds may result in a nose-in landing where the UAV essentially impacts the surface of the water. The tested UAV is a flying wing design constructed of expanded polypropylene foam wings with a hollowed out center-section for the avionics. Acceleration data was collected by means of LIS331 3-axis accelerometers positioned at five locations, including the wingtips. This allowed conclusions to be drawn with respect to the loads experienced on impact throughout the airframe. This data was also used to find loads corresponding to the maximum decelerations experienced during impact. These loads were input into a finite element analysis model of the wing spars to determine stress in the wing spars. Upon impact, the airframe experienced high-frequency oscillation. Surprisingly, peak accelerations at the wingtips were observed at up to 15g greater than corresponding accelerations at the center of the fuselage.

  20. Conformal Patch Antenna Arrays Design for Onboard Ship Deployment Using Genetic Algorithms

    Directory of Open Access Journals (Sweden)

    Stelios A. Mitilineos


    Full Text Available Conformal antennas and antenna arrays (arrays have become necessary for vehicular communications where a high degree of aerodynamic drag reduction is needed, like in avionics and ships. However, the necessity to conform to a predefined shape (e.g., of an aircraft’s nose directly affects antenna performance since it imposes strict constraints to the antenna array’s shape, element spacing, relative signal phase, and so forth. Thereupon, it is necessary to investigate counterintuitive and arbitrary antenna shapes in order to compensate for these constraints. Since there does not exist any available theoretical frame for designing and developing arbitrary-shape antennas in a straightforward manner, we have developed a platform combining a genetic algorithm-based design, optimization suite, and an electromagnetic simulator for designing patch antennas with a shape that is not a priori known (the genetic algorithm optimizes the shape of the patch antenna. The proposed platform is further enhanced by the ability to design and optimize antenna arrays and is intended to be used for the design of a series of antennas including conformal antennas for shipping applications. The flexibility and performance of the proposed platform are demonstrated herein via the design of a high-performance GPS patch antenna.