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. Avionics Architecture Modelling Language (United States)

    Alana, Elena; Naranjo, Hector; Valencia, Raul; Medina, Alberto; Honvault, Christophe; Rugina, Ana; Panunzia, Marco; Dellandrea, Brice; Garcia, Gerald


    This paper presents the ESA AAML (Avionics Architecture Modelling Language) study, which aimed at advancing the avionics engineering practices towards a model-based approach by (i) identifying and prioritising the avionics-relevant analyses, (ii) specifying the modelling language features necessary to support the identified analyses, and (iii) recommending/prototyping software tooling to demonstrate the automation of the selected analyses based on a modelling language and compliant with the defined specification.

  4. Avionics systems integration technology (United States)

    Stech, George; Williams, James R.


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

  5. Avionics System Architecture Tool (United States)

    Chau, Savio; Hall, Ronald; Traylor, marcus; Whitfield, Adrian


    Avionics System Architecture Tool (ASAT) is a computer program intended for use during the avionics-system-architecture- design phase of the process of designing a spacecraft for a specific mission. ASAT enables simulation of the dynamics of the command-and-data-handling functions of the spacecraft avionics in the scenarios in which the spacecraft is expected to operate. ASAT is built upon I-Logix Statemate MAGNUM, providing a complement of dynamic system modeling tools, including a graphical user interface (GUI), modeling checking capabilities, and a simulation engine. ASAT augments this with a library of predefined avionics components and additional software to support building and analyzing avionics hardware architectures using these components.

  6. Ares I Avionics Introduction (United States)

    Marchant, Christopher C.


    The Ares I is the next generation human-rated launcher for the United States Constellation program. This system is required to provide single fault tolerance within defined crew safety and mission reliability limits. As part of the effort to achieve those safety goals, Ares I includes an avionics subsystem built as a multistring, voting architecture. The avionics design draws upon experience gained from building fly-by-wire systems for Shuttle, X- 38, and Seawolf. Architectural drivers for the avionics design include using proven technologies with existing suppliers of space rated parts for critical functions (to reduce overall development risk), easing the software development effort by using an off-theshelf, DO-178B certifiable, ARINC-653 operating system in the main flight computers, minimizing mutual data and power connections that might lead to a common-mode hardware failure of the redundant avionics strings, and centralizing overall Ares I command & control within the Upper Stage.

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

    Baggerman, Clint


    This viewgraph presentation reviews the Orion Crew Exploration Vehicle avionics architecture. The contents include: 1) What is Orion?; 2) Orion Concept of Operations; 3) Orion Subsystems; 4) Orion Avionics Architecture; 5) Orion Avionics-Network; 6) Orion Network Unification; 7) Orion Avionics-Integrity; 8) Orion Avionics-Partitioning; and 9) Orion Avionics-Redundancy.

  8. 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

  9. Affordable Vehicle Avionics Overview (United States)

    Cockrell, James J.


    Public and private launch vehicle developers are reducing the cost of propulsion for small commercial launchers, but conventional high-performance, high-reliability avionics remain the disproportionately high cost driver for launch. AVA technology performs as well or better than conventional launch vehicle avionics, but with a fraction of the recurring costs. AVA enables small launch providers to offer affordable rides to LEO to nano-satellites as primary payloads meaning, small payloads can afford to specify their own launch and orbit parameters

  10. 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...

  11. Avionics Maintenance Technology Program Standards. (United States)

    Georgia Univ., Athens. Dept. of Vocational Education.

    This publication contains statewide standards for the avionics maintenance technology program in Georgia. The standards are divided into the following categories: foundations, diploma/degree (philosophy, purpose, goals, program objectives, availability, evaluation); admissions, diploma/degree (admission requirements, provisional admission…

  12. Aerospace Avionics and Allied Technologies

    Directory of Open Access Journals (Sweden)

    Jitendra R. Raol


    Full Text Available Avionics is a very crucial and important technology, not only for civil/military aircraft but also for missiles, spacecraft, micro air vehicles (MAVs and unmanned aerial vehicles (UAVs. Even for ground-based vehicles and underwater vehicles (UWVs, avionics is a very important segment of their successful operation and mission accomplishment. The advances in many related and supporting technologies, especially digital electronics, embedded systems, embedded algorithms/software, mobile technology, sensors and instrumentation, computer (network-communication, and realtime operations and simulation, have given a great impetus to the field of avionics. Here, for the sake of encompassing many other applications as mentioned above, the term is used in an expanded sense: Aerospace Avionics (AA, although it is popularly known as Aviation Electronics (or Avionics. However, use of this technology is not limited to aircraft, and hence, we  can incorporate all the three types-ground, land, and underwater vehicles-under the term avionics.Defence Science Journal, 2011, 61(4, pp.287-288, DOI:

  13. 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

  14. 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.

  15. Avionics Maintenance Technology Program Guide. (United States)

    Georgia Univ., Athens. Dept. of Vocational Education.

    This program guide presents the avionics maintenance technology curriculum for technical institutes in Georgia. The general information section contains the following for both the diploma program and the associate degree program: purpose and objectives; program description, including admissions, typical job titles, and accreditation and…

  16. 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.

  17. Single event upset in avionics

    International Nuclear Information System (INIS)

    Data from military/experimental flights and laboratory testing indicate that typical non radiation-hardened 64K and 256K static random access memories (SRAMs) can experience a significant soft upset rate at aircraft altitudes due to energetic neutrons created by cosmic ray interactions in the atmosphere. It is suggested that error detection and correction (EDAC) circuitry be considered for all avionics designs containing large amounts of semi-conductor memory

  18. Generalized Nanosatellite Avionics Testbed Lab (United States)

    Frost, Chad R.; Sorgenfrei, Matthew C.; Nehrenz, Matt


    The Generalized Nanosatellite Avionics Testbed (G-NAT) lab at NASA Ames Research Center provides a flexible, easily accessible platform for developing hardware and software for advanced small spacecraft. A collaboration between the Mission Design Division and the Intelligent Systems Division, the objective of the lab is to provide testing data and general test protocols for advanced sensors, actuators, and processors for CubeSat-class spacecraft. By developing test schemes for advanced components outside of the standard mission lifecycle, the lab is able to help reduce the risk carried by advanced nanosatellite or CubeSat missions. Such missions are often allocated very little time for testing, and too often the test facilities must be custom-built for the needs of the mission at hand. The G-NAT lab helps to eliminate these problems by providing an existing suite of testbeds that combines easily accessible, commercial-offthe- shelf (COTS) processors with a collection of existing sensors and actuators.

  19. 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.

  20. Systems Engineering and Reusable Avionics (United States)

    Conrad, James M.; Murphy, Gloria


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

  1. Broadband antireflection coatings for multifunctional avionic displays (United States)

    Kumari, Neelam; Kumar, Mukesh; Rao, P. K.; Karar, Vinod; Sharma, Amit Lochan


    Broadband Multilayer Antireflection (AR) coatings markedly improve the transmission efficiency of any optical component such as lens, prism, beam-splitter, beam combiner or a window. By reducing surface reflections over a wide wavelength range, broadband antireflection coatings improve transmission and enhance contrast which is desired in avionic displays. The broadband antireflection coating consisting of MgF2, ZrO2 and Al2O3 were designed to cover the whole visible spectrum and fabricated on optical grade glass substrate. The optical characterization of these coatings indicates reduction of the reflection to 2.28% as compared to 8.5 % at 545 nm (i.e. design wavelength of most avionic displays) for bare substrate making them useful in optical displays for avionic applications.

  2. 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.

  3. Avionics Architectures for Exploration: Building a Better Approach for (Human) Spaceflight Avionics (United States)

    Goforth, Montgomery B.; Ratliff, James E.; Hames, Kevin L.; Vitalpur, Sharada V.


    The field of Avionics is advancing far more rapidly in terrestrial applications than in space flight applications. Spaceflight Avionics are not keeping pace with expectations set by terrestrial experience, nor are they keeping pace with the need for increasingly complex automation and crew interfaces as we move beyond Low Earth Orbit. NASA must take advantage of the strides being made by both space-related and terrestrial industries to drive our development and sustaining costs down. This paper describes ongoing efforts by the Avionics Architectures for Exploration (AAE) project chartered by NASA's Advanced Exploration Systems (AES) Program to evaluate new avionic architectures and technologies, provide objective comparisons of them, and mature selected technologies for flight and for use by other AES projects. Results from the AAE project's FY13 efforts are discussed, along with the status of FY14 efforts and future plans.

  4. Ares I Crew Launch Vehicle Upper Stage Avionics and Software Overview (United States)

    Nola, Charles L.


    This viewgraph presentation gives an overall description of the avionics and software functions of the Ares I Upper Stage Crew Launch Vehicle. The contents include: 1) IUA Team - Development Approach Roadmap; 2) Ares I US Avionics and Software Development Approach; 3) NDT Responsibilities; 4) Ares I Upper Stage Avionics Locations; 5) Ares I Overall Avionics & Software Functions; 6) Block Diagram Version of Avionics Architecture; 7) Instrument Unit Avionics Preliminary Design; and 8) Upper Stage Avionics External Interfaces.

  5. Reuse and Interoperability of Avionics for Space Systems (United States)

    Hodson, Robert F.


    The space environment presents unique challenges for avionics. Launch survivability, thermal management, radiation protection, and other factors are important for successful space designs. Many existing avionics designs use custom hardware and software to meet the requirements of space systems. Although some space vendors have moved more towards a standard product line approach to avionics, the space industry still lacks similar standards and common practices for avionics development. This lack of commonality manifests itself in limited reuse and a lack of interoperability. To address NASA s need for interoperable avionics that facilitate reuse, several hardware and software approaches are discussed. Experiences with existing space boards and the application of terrestrial standards is outlined. Enhancements and extensions to these standards are considered. A modular stack-based approach to space avionics is presented. Software and reconfigurable logic cores are considered for extending interoperability and reuse. Finally, some of the issues associated with the design of reusable interoperable avionics are discussed.

  6. Avionics Instrument Systems Specialist (AFSC 32551). (United States)

    Miller, Lawrence B.; Crowcroft, Robert A.

    This six-volume student text is designed for use by Air Force personnel enrolled in a self-study extension course for avionics instrument systems specialists. Covered in the individual volumes are career field familiarization (career field progression and training, security, occupational safety and health, and career field reference material);…

  7. Reference Avionics Architecture for Lunar Surface Systems (United States)

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


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

  8. Avionics. Progress Record and Theory Outline. (United States)

    Connecticut State Dept. of Education, Hartford. Div. of Vocational-Technical Schools.

    This combination progress record and course outline is designed for use by individuals teaching a course in avionics that is intended to prepare students for employment in the field of aerospace electronics. Included among the topics addressed in the course are the following: shop practices, aircraft and the theory of flight, electron physics,…

  9. Simulating Avionics Upgrades to the Space Shuttles (United States)

    Deger, Daniel; Hill, Kenneth; Braaten, Karsten E.


    Cockpit Avionics Prototyping Environment (CAPE) is a computer program that simulates the functions of proposed upgraded avionics for a space shuttle. In CAPE, pre-existing space-shuttle-simulation programs are merged with a commercial-off-the-shelf (COTS) display-development program, yielding a package of software that enables high-fi46 NASA Tech Briefs, September 2008 delity simulation while making it possible to rapidly change avionic displays and the underlying model algorithms. The pre-existing simulation programs are Shuttle Engineering Simulation, Shuttle Engineering Simulation II, Interactive Control and Docking Simulation, and Shuttle Mission Simulator playback. The COTS program Virtual Application Prototyping System (VAPS) not only enables the development of displays but also makes it possible to move data about, capture and process events, and connect to a simulation. VAPS also enables the user to write code in the C or C++ programming language and compile that code into the end-product simulation software. As many as ten different avionic-upgrade ideas can be incorporated in a single compilation and, thus, tested in a single simulation run. CAPE can be run in conjunction with any or all of four simulations, each representing a different phase of a space-shuttle flight.

  10. Developing A Generic Optical Avionic Network

    DEFF Research Database (Denmark)

    Zhang, Jiang; An, Yi; Berger, Michael Stübert; Peucheret, Christophe; Clausen, Anders

    support a wide range of avionic applications. Segregation can be made on different hierarchies according to system criticality and security requirements. The structure of each layer is discussed in detail. Two network configurations are presented, focusing on how to support different network services by...

  11. SMART: The Future of Spaceflight Avionics (United States)

    Alhorn, Dean C.; Howard, David E.


    A novel avionics approach is necessary to meet the future needs of low cost space and lunar missions that require low mass and low power electronics. The current state of the art for avionics systems are centralized electronic units that perform the required spacecraft functions. These electronic units are usually custom-designed for each application and the approach compels avionics designers to have in-depth system knowledge before design can commence. The overall design, development, test and evaluation (DDT&E) cycle for this conventional approach requires long delivery times for space flight electronics and is very expensive. The Small Multi-purpose Advanced Reconfigurable Technology (SMART) concept is currently being developed to overcome the limitations of traditional avionics design. The SMART concept is based upon two multi-functional modules that can be reconfigured to drive and sense a variety of mechanical and electrical components. The SMART units are key to a distributed avionics architecture whereby the modules are located close to or right at the desired application point. The drive module, SMART-D, receives commands from the main computer and controls the spacecraft mechanisms and devices with localized feedback. The sensor module, SMART-S, is used to sense the environmental sensors and offload local limit checking from the main computer. There are numerous benefits that are realized by implementing the SMART system. Localized sensor signal conditioning electronics reduces signal loss and overall wiring mass. Localized drive electronics increase control bandwidth and minimize time lags for critical functions. These benefits in-turn reduce the main processor overhead functions. Since SMART units are standard flight qualified units, DDT&E is reduced and system design can commence much earlier in the design cycle. Increased production scale lowers individual piece part cost and using standard modules also reduces non-recurring costs. The benefit list

  12. Single-event effects in avionics

    International Nuclear Information System (INIS)

    The occurrence of single-event upset (SEU) in aircraft electronics has evolved from a series of interesting anecdotal incidents to accepted fact. A study completed in 1992 demonstrated that SEU's are real, that the measured in-flight rates correlate with the atmospheric neutron flux, and that the rates can be calculated using laboratory SEU data. Once avionics DEU was shown to be an actual effect, it had to be dealt with in avionics designs. The major concern is in random access memories (RAM's), both static (SRAM's) and dynamic (DRAM's), because these microelectronic devices contain the largest number of bits, but other parts, such as microprocessors, are also potentially susceptible to upset. In addition, other single-event effects (SEE's), specifically latch-up and burnout, can also be induced by atmospheric neutrons

  13. 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.

  14. 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...

  15. 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).

  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. 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.

  18. Availability of ARINC 629 Avionic Data Bus

    Directory of Open Access Journals (Sweden)

    Alban Gabillon


    Full Text Available The three traditional objectives of computer security are confidentiality, integrity and availability. Availability can be defined as the prevention of denial of service. Confidentiality and integrity have been addressed in several theoretical works whereas the concept of availability has not been much investigated by the scientific community. This paper is an attempt to define through a case study the concept of availability. We first define a set of availability constraints that avionic data bus protocols should enforce. Then, we consider the ARINC 629 Basic Protocol (BP and the ARINC Combined Protocol (CP which were implemented on the Boeing 777. We check whether these protocols respect our availability constraints or not.

  19. 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.

  20. 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

  1. System Framework for the Design of an Avionics Architecture with Upgrade Potential

    Directory of Open Access Journals (Sweden)

    N. Rao


    Full Text Available The technological growth of ‘avionics systems’ has outpaced the service-life of aircraft, resulting in avionics upgrade as a preferred cost-effective option to new design. Mid-life upgrade of “avionics systems“ by state-of-the-art mission systems has been a challenging engineering task. The complexity of avionics upgrade process is due to the design rigidity of avionics systems architecture. An avionics architecture with growth potential is required to optimise avionics upgrade with state-of-the-art systems. A research program that partially addresses avionics systems upgrade by developing a methodology to design an avionics architecture with in-built growth potential is discussed in this research paper. A ‘system approach’ is adopted to develop a methodology that identifies the design parameters that will facilitate design of an avionics architecture with upgrade potential.

  2. Development of Framework for Acquisition of Avionics Integration Capability

    Directory of Open Access Journals (Sweden)

    Fahad RIAZ


    Full Text Available With the rapid advancement in electronics technology, in the last three decades Avionics systems, have evolved from standalone single function units to functionally correlated and interdependent systems. To harness the potential of this technological growth in the constraints of time, power and space, the specialty of Avionics Integration has emerged. Avionics Integration Technology is a multi-faceted discipline involving a myriad of activities starting from design conception and concluding on final qualification and acceptance of the avionics suite. Currently, only a few advanced countries worldwide possess this technology and no formal framework has been defined in literature or journals that encompass the range of activities involved in avionics Integration. This paper will present a formal framework required for development of Avionics Integration Capability. It will cover the core skill areas required and their interdependencies. The recognized “V” Development model will be presented with complete identification of Integrator and Sub Contractor roles and responsibilities. For the technical execution of Avionics Integration, specialist domains will be identified along broad definition of required tool sets and work flow of activities to be conducted.

  3. 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.

  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. Overview of Avionics and Electrical Ground Support Equipment (United States)

    Clarke, Sean C.


    Presents an overview of the Crew Module Avionics and the associated Electrical Ground Support Equipment for the Pad Abort 1 flight test of the Orion Program. A limited selection of the technical challenges and solutions are highlighted.

  6. 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.

  7. Crew Exploration Vehicle (CEV) Avionics Integration Laboratory (CAIL) Independent Analysis (United States)

    Davis, Mitchell L.; Aguilar, Michael L.; Mora, Victor D.; Regenie, Victoria A.; Ritz, William F.


    Two approaches were compared to the Crew Exploration Vehicle (CEV) Avionics Integration Laboratory (CAIL) approach: the Flat-Sat and Shuttle Avionics Integration Laboratory (SAIL). The Flat-Sat and CAIL/SAIL approaches are two different tools designed to mitigate different risks. Flat-Sat approach is designed to develop a mission concept into a flight avionics system and associated ground controller. The SAIL approach is designed to aid in the flight readiness verification of the flight avionics system. The approaches are complimentary in addressing both the system development risks and mission verification risks. The following NESC team findings were identified: The CAIL assumption is that the flight subsystems will be matured for the system level verification; The Flat-Sat and SAIL approaches are two different tools designed to mitigate different risks. The following NESC team recommendation was provided: Define, document, and manage a detailed interface between the design and development (EDL and other integration labs) to the verification laboratory (CAIL).

  8. 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...

  9. 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...

  10. 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...

  11. 2013 aircrew, avionics, and operations survey, part 2. (United States)

    Greene, Michael J


    In this second half of a 2-part series, chief/lead pilots were invited to complete a 40-question survey modeled on the AirMed 2000 Helicopter Avionics and Operations Survey via an online survey. The survey was available to rotor-wing (RW) and fixed-wing air medical transport services in the United States, although year 2000 comparative data are RW only. Topics surveyed include flight hours, aircraft models, avionics, interiors, staffing, weather minimums, and maintenance facilities. PMID:24182880

  12. Evaluation of New European Technologies for Future Avionics (United States)

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


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

  13. Avionics Architectures for Exploration: Wireless Technologies and Human Spaceflight (United States)

    Goforth, Montgomery B.; Ratliff, James E.; Barton, Richard J.; Wagner, Raymond S.; Lansdowne, Chatwin


    The authors describe ongoing efforts by the Avionics Architectures for Exploration (AAE) project chartered by NASA's Advanced Exploration Systems (AES) Program to evaluate new avionics architectures and technologies, provide objective comparisons of them, and mature selected technologies for flight and for use by other AES projects. The AAE project team includes members from most NASA centers and from industry. This paper provides an overview of recent AAE efforts, with particular emphasis on the wireless technologies being evaluated under AES to support human spaceflight.

  14. 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.

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

    Baggerman, Clint; McCabe, Mary; Verma, Dinesh


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

  16. 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.

  17. 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.

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

    International Nuclear Information System (INIS)

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

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

    Directory of Open Access Journals (Sweden)

    Wang Liang


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

  20. NASA Affordable Vehicle Avionics (AVA): Common Modular Avionics System for Nano-Launchers Offering Affordable Access to Space (United States)

    Cockrell, James


    Small satellites are becoming ever more capable of performing valuable missions for both government and commercial customers. However, currently these satellites can only be launched affordably as secondary payloads. This makes it difficult for the small satellite mission to launch when needed, to the desired orbit, and with acceptable risk. NASA Ames Research Center has developed and tested a prototype low-cost avionics package for space launch vehicles that provides complete GNC functionality in a package smaller than a tissue box with a mass less than 0.84 kg. AVA takes advantage of commercially available, low-cost, mass-produced, miniaturized sensors, filtering their more noisy inertial data with realtime GPS data. The goal of the Advanced Vehicle Avionics project is to produce and flight-verify a common suite of avionics and software that deliver affordable, capable GNC and telemetry avionics with application to multiple nano-launch vehicles at 1 the cost of current state-of-the-art avionics.

  1. 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.

  2. 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)

  3. 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.

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

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


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

  5. Digital Avionics Information System (DAIS): Training Requirements Analysis Model (TRAMOD). (United States)

    Czuchry, Andrew J.; And Others

    The training requirements analysis model (TRAMOD) described in this report represents an important portion of the larger effort called the Digital Avionics Information System (DAIS) Life Cycle Cost (LCC) Study. TRAMOD is the second of three models that comprise an LCC impact modeling system for use in the early stages of system development. As…

  6. Current state of OLED technology relative to military avionics requirements (United States)

    Tchon, Joseph L.; Barnidge, Tracy J.; Hufnagel, Bruce D.; Bahadur, Birendra


    The paper will review optical and environmental performance thresholds required for OLED technology to be used on various military platforms. Life study results will be summarized to highlight trends while identifying remaining performance gaps to make this technology viable for future military avionics platforms.

  7. Wavelength and fiber assignment problems on avionic networks

    DEFF Research Database (Denmark)

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

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

  8. Prediction Tables for Avionics Fundamentals Course, Class A. (United States)

    Baldwin, Robert O.; Johnson, Kirk A.

    This study was conducted in 1966 to provide the avionics fundamentals course, class A, with a number of tables for predicting academic performance, either by precourse variables or by grades made early in the course. A means of identifying potential setbacks and potential failures was also desired. In September 1966 a 16 week course replaced the…

  9. Distributed Avionics and Software Verification for the Constellation Program (United States)

    Hood, Laura E.; Adams, James E.


    This viewgraph presentation reviews the planned verification of the avionics and software being developed for the Constellation program.The Constellation Distributed System Integration Laboratory (DSIL) will consist of multiple System Integration Labs (SILs), Simulators, Emulators, Testbeds, and Control Centers interacting with each other over a broadband network to provide virtual test systems for multiple test scenarios.

  10. Low-Cost Avionics Simulation for Aircrew Training. (United States)

    Edwards, Bernell J.

    This report documents an experiment to determine the training effectiveness of a microcomputer-based avionics system trainer as a cost-effective alternative to training in the actual aircraft. Participants--26 operationally qualified C-141 pilots with no prior knowledge of the Fuel Saving Advisory System (FSAS), a computerized fuel management…

  11. Avionics Technology Contract Project Report Phase I with Research Findings. (United States)

    Sappe', Hoyt; Squires, Shiela S.

    This document reports on Phase I of a project that examined the occupation of avionics technician, established appropriate committees, and conducted task verification. Results of this phase provide the basic information required to develop the program standards and to guide and set up the committee structure to guide the project. Section 1…

  12. 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...

  13. 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

  14. Avionics and airframe options: current usage and future plans. (United States)

    Mayfield, T; Cady, G


    The 1994 Avionics and Airframe Survey was sent to 178 chief or lead pilots of helicopter emergency medical services (HEMS) programs in October 1993, and 100 (56%) were returned. Sixty-four programs (64%) reported that they operate one helicopter exclusively for EMS, 24 (24%) operate two, and 12 (12%) reported using three or more aircraft. Interestingly, the reported percentage of programs with two or more exclusive helicopters continues to rise, increasing by 5.6% to 36%. PMID:10131002

  15. ARINC 818 specification revisions enable new avionics architectures (United States)

    Grunwald, Paul


    The ARINC 818 Avionics Digital Video Bus is the standard for cockpit video that has gained wide acceptance in both the commercial and military cockpits. The Boeing 787, A350XWB, A400M, KC-46A, and many other aircraft use it. The ARINC 818 specification, which was initially release in 2006, has recently undergone a major update to address new avionics architectures and capabilities. Over the seven years since its release, projects have gone beyond the specification due to the complexity of new architectures and desired capabilities, such as video switching, bi-directional communication, data-only paths, and camera and sensor control provisions. The ARINC 818 specification was revised in 2013, and ARINC 818-2 was approved in November 2013. The revisions to the ARINC 818-2 specification enable switching, stereo and 3-D provisions, color sequential implementations, regions of interest, bi-directional communication, higher link rates, data-only transmission, and synchronization signals. This paper discusses each of the new capabilities and the impact on avionics and display architectures, especially when integrating large area displays, stereoscopic displays, multiple displays, and systems that include a large number of sensors.

  16. 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.

  17. 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.

  18. OMAC4S- Open Modular Avionics for Space Applications (United States)

    Herpel, H.-J.; Willich, G.; Vogel, T.; Schuettauf, A.; Pletner, S.; Schoen, F.; Fidi, C.; Loetzke, M.; Dittrich, L.; Schuelke, P.; Wolf, T.


    Today's spacecraft avionics architecture is characterised by a broad variety of processing modules, operating systems and interfaces for exchanging data between different processing modules. The software that implements most of the satellite functionality has to deal with this fact and is one of the reasons why software has become one of the major cost drivers in satellite projects. Similar problems have triggered developments in other industrial domains like AUTOSAR in the automotive area or Integrated Modular Architecture (IMA) in the aerospace industry [8]. All these initiatives are based on the definition of standards for computing platforms and the interfaces between these platforms. The goals of the Open Modular Avionics Architecture for Space Applications (OMAC4S) initiative started by Astrium, Fraunhofer FOKUS, STI, SYSGO and TTTech are to outline a solution that helps to reduce complexity and costs for space avionics significantly. This initiative is partly funded by the German national space agency (DLR) through the project On-Board Computer System Architecture (OBC-SA). In this paper we describe how standardization and the usage of already proven technologies from other industrial domains will help to limit the effect of the software development on schedule and costs of satellite projects. In addition we will demonstrate a migration path to make these technologies available for space applications.

  19. Challenges of Security and Trust of Mobile Devices as Digital Avionics Component


    Akram, Raja Naeem; Markantonakis, Konstantinos


    Mobile devices are becoming part of modern digital avionics. Mobile devices can be applied to a range of scenarios, from Electronic Flight Bags to maintenance platforms, in order to manage and configure flight information, configure avionics networks or perform maintenance tasks (including offloading flight logs). It can be argued that recent developments show an increased use of personal mobile devices playing an integral part in the digital avionics industry. In this paper, we look into dif...

  20. NASA Ares I Crew Launch Vehicle Upper Stage Avionics and Software Overview (United States)

    Nola, Charles L.; Blue, Lisa


    Building on the heritage of the Saturn and Space Shuttle Programs for the Design, Development, Test, and Evaluation (DDT and E) of avionics and software for NASA's Ares I Crew Launch Vehicle (CLV), the Ares I Upper Stage Element is a vital part of the Constellation Program's transportation system. The Upper Stage Element's Avionics Subsystem is actively proceeding toward its objective of delivering a flight-certified Upper Stage Avionics System for the Ares I CLV.

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


    C.M. Ananda; K.G. Venkatanarayana; Preme M.; Raghu M.


    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 tre...

  2. Avionics Architectures for Exploration: Ongoing Efforts in Human Spaceflight (United States)

    Goforth, Montgomery B.; Ratliff, James E.; Hames, Kevin L.; Vitalpur, Sharada V.; Woodman, Keith L.


    The field of Avionics is advancing far more rapidly in terrestrial applications than in spaceflight applications. Spaceflight Avionics are not keeping pace with expectations set by terrestrial experience, nor are they keeping pace with the need for increasingly complex automation and crew interfaces as we move beyond Low Earth Orbit. NASA must take advantage of the strides being made by both space-related and terrestrial industries to drive our development and sustaining costs down. This paper describes ongoing efforts by the Avionics Architectures for Exploration (AAE) project chartered by NASA's Advanced Exploration Systems (AES) Program to evaluate new avionic architectures and technologies, provide objective comparisons of them, and mature selected technologies for flight and for use by other AES projects. The AAE project team includes members from most NASA centers, and from industry. It is our intent to develop a common core avionic system that has standard capabilities and interfaces, and contains the basic elements and functionality needed for any spacecraft. This common core will be scalable and tailored to specific missions. It will incorporate hardware and software from multiple vendors, and be upgradeable in order to infuse incremental capabilities and new technologies. It will maximize the use of reconfigurable open source software (e.g., Goddard Space Flight Center's (GSFC's) Core Flight Software (CFS)). Our long-term focus is on improving functionality, reliability, and autonomy, while reducing size, weight, and power. Where possible, we will leverage terrestrial commercial capabilities to drive down development and sustaining costs. We will select promising technologies for evaluation, compare them in an objective manner, and mature them to be available for future programs. The remainder of this paper describes our approach, technical areas of emphasis, integrated test experience and results as of mid-2014, and future plans. As a part of the AES

  3. Digital Avionics Information System (DAIS): Impact of DAIS Concept on Life Cycle Cost. Final Report. (United States)

    Goclowski, John C.; And Others

    Designed to identify and quantify the potential impacts of the Digital Avionics Information System (DAIS) on weapon system personnel requirements and life cycle cost (LCC), this study postulated a typical close-air-support (CAS) mission avionics suite to serve as a basis for comparing present day and DAIS configuration specifications. The purpose…

  4. 78 FR 54791 - Proposed Additional Airworthiness Design Standards: Advanced Avionics Under the Special Class... (United States)


    ... Regulations and two additional design criteria issued on September 2, 2003 (68 FR 56809). The regulation... 75 FR 32576. In conjunction with the expansion to Night-VFR operations intergrated avionic displays...: Advanced Avionics Under the Special Class (JAR-VLA) Regulations; Aquila Aviation by Excellence GmbH,...

  5. Digital Avionics Information System Preliminary Life-Cycle-Cost Analysis. Final Report (November 1974-May 1975). (United States)

    Pruitt, Gary K.; Dieterly, Duncan L.

    The results of a study to evaluate the potential life-cycle costs and cost savings that could be realized by applying the Digital Avionics Information System (DAIS) concept to future avionic systems were presented. The tasks evaluated included selection of program elements for costing, selection of DAIS installation potential, definition of a…

  6. Digital Avionics Information System (DAIS): Reliability and Maintainability Model. Final Report. (United States)

    Czuchry, Andrew J.; And Others

    The reliability and maintainability (R&M) model described in this report represents an important portion of a larger effort called the Digital Avionics Information System (DAIS) Life Cycle Cost (LCC) Study. The R&M model is the first of three models that comprise a modeling system for use in LCC analysis of avionics systems. The total system will…

  7. Fiber-Optic Network Architectures for Onboard Avionics Applications Investigated (United States)

    Nguyen, Hung D.; Ngo, Duc H.


    This project is part of a study within the Advanced Air Transportation Technologies program undertaken at the NASA Glenn Research Center. The main focus of the program is the improvement of air transportation, with particular emphasis on air transportation safety. Current and future advances in digital data communications between an aircraft and the outside world will require high-bandwidth onboard communication networks. Radiofrequency (RF) systems, with their interconnection network based on coaxial cables and waveguides, increase the complexity of communication systems onboard modern civil and military aircraft with respect to weight, power consumption, and safety. In addition, safety and reliability concerns from electromagnetic interference between the RF components embedded in these communication systems exist. A simple, reliable, and lightweight network that is free from the effects of electromagnetic interference and capable of supporting the broadband communications needs of future onboard digital avionics systems cannot be easily implemented using existing coaxial cable-based systems. Fiber-optical communication systems can meet all these challenges of modern avionics applications in an efficient, cost-effective manner. The objective of this project is to present a number of optical network architectures for onboard RF signal distribution. Because of the emergence of a number of digital avionics devices requiring high-bandwidth connectivity, fiber-optic RF networks onboard modern aircraft will play a vital role in ensuring a low-noise, highly reliable RF communication system. Two approaches are being used for network architectures for aircraft onboard fiber-optic distribution systems: a hybrid RF-optical network and an all-optical wavelength division multiplexing (WDM) network.

  8. MultIMA- Multi-Core in Integrated Modular Avionics (United States)

    Silva, Claudio; Tatibana, Cassia


    Multi-core technologies are the natural trend towards fulfilling recent space applications requirements. However, the adoption of multi-core implies increased complexity that must be addressed by application redesign or the implementation of explicit supporting mechanisms. GMV investigates multi-core and Integrated Modular Avionics as cooperative vehicles to achieve reliable support for future safety critical applications. In this paper, we describe the main challenges met in our investigations and how multi-core solutions were implemented in GMV's IMA simulator (SIMA) and operating system (AIR).

  9. 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.

  10. 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.

  11. 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.

  12. 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.

  13. 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.

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

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


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

  15. 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

  16. 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.

  17. 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.

  18. 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.

  19. 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...

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

    Orr, James K.; Peltier, Daryl


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

  1. 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.

  2. 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.

  3. 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.

  4. 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:

  5. 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.

  6. 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

  7. SAR Aircrew--HH-3F Avionics and HH-3F Flight Preparation. ACH3AV-0442. Second Edition, Revised. (United States)

    Coast Guard Inst., Oklahoma City, OK.

    This document contains two U.S. Coast Guard self-study pamphlets that provide training in helicopter flight preparation and avionics duties. Each pamphlet consists of a number of lessons that include objectives, information illustrated with line drawings and/or photographs, and self-quizzes with answers. The avionics course covers the following…

  8. 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

  9. 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....

  10. 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.

  11. Automatic Implementation of Ttethernet-Based Time-Triggered Avionics Applications (United States)

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


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

  12. Flight controls/avionics research - Impact on future civil helicopter operating efficiency and mission reliability (United States)

    Snyder, W. J.; Christensen, J. V.


    Operational efficiency and mission reliability are key capabilities which will impact the future use of helicopters in the civil segment and areas where flight control/avionics research can play a major role. The present paper reviews flight control/avionics system needs for each major area of civil helicopter use. Technology requirements to meet civil needs are discussed. The review points up the need for the development of all-weather flight control concepts and the validation of cost effective active control/fly-by-wire/fly-by-light system concepts with modular architecture which can be tailored to specific mission requirements.

  13. Avionics Instrument Systems Specialist Career Ladder: AFSCs 32531, 32551, 31571, and 32591. Occupational Survey Report. (United States)

    Air Force Occupational Measurement Center, Lackland AFB, TX.

    The Avionics Instrument Systems career ladder (AFSC 325X1) provides flight line and shop maintenance training on aircraft instrument systems, electromechancial instruments, components, and test equipment. Duties involve inspecting, removing, installing, repairing, operating, troubleshooting, overhauling, and modifying systems such as flight and…

  14. The Avionics SOIS Services of CORDET On-Board Software Architecture (United States)

    Alana, Elena; del Carmen Lomba, Maria; Jung, Andreas; Grenham, Adrian; Fowell, Stuart


    This paper introduces the specification of the Execution Platform Layer of the On-Board Software Reference Architecture (OBSW-RA) presented in COrDeT-2 study. In particular, the paper addresses the avionics services defined within the context of the overall Spacecraft On-board Interface Services (SOIS) available at the Execution Platform Layer of the OBSW-RA.




  16. Digital Avionics Information System (DAIS): Mid-1980's Maintenance Task Analysis. Final Report. (United States)

    Czuchry, Andrew J.; And Others

    The fundamental objective of the Digital Avionics Information System (DAIS) Life Cycle Cost (LCC) Study is to provide the Air Force with an enhanced in-house capability to incorporate LCC considerations during all stages of the system acquisition process. The purpose of this report is to describe the technical approach, results, and conclusions…

  17. Mathematical optimization model of avionics complexation problem on early stage of designing

    Directory of Open Access Journals (Sweden)

    V.M. Vorobyov


    Full Text Available  The article is the sequel of another one of this digest of authors “Approximate optimization solution by Pareto of discrete extremal problem of complexation of new generation avionics” and its development in the direction of creating optimization model and organization under synthesis of avionics structure.

  18. 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.

  19. 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.

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

    Hayhurst, Kelly J.; Shagnea, Anita M.


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

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

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


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

  2. 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:

  3. 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

  4. Workstation-Based Avionics Simulator to Support Mars Science Laboratory Flight Software Development (United States)

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


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

  5. 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.

  6. Avionics-compatible video facial cognizer for detection of pilot incapacitation. (United States)

    Steffin, Morris


    High-acceleration loss of consciousness is a serious problem for military pilots. In this laboratory, a video cognizer has been developed that in real time detects facial changes closely coupled to the onset of loss of consciousness. Efficient algorithms are compatible with video digital signal processing hardware and are thus configurable on an autonomous single board that generates alarm triggers to activate autopilot, and is avionics-compatible. PMID:16404114

  7. ARINC 653 API and its application – An insight into Avionics System Case Study

    Directory of Open Access Journals (Sweden)

    Ananda C.M.


    Full Text Available Traditionally automated systems in aircraft were realised using well defined functions that are implemented as federated functional units. Each functional units possesses its own resources with fault containment compared to multiple functions in single processing node. Integrated architectures are structured over the avionics cabinets or processing cabinets which house the hardware modules and software application partitions along with system software. These integrated modular avionics (IMA applications supports distributed multiprocessor architecture. Both time and memory is shared among multiple avionics functionalities across the same platform with good protection mechanisms provided by ARINC 653. ARINC 653 is an additional layer of protection being embedded as part of real time operating systems supporting the partitioning protections using well defined application executive, and application programming interfaces (API. IMA uses set of partitions, which are scheduled across a major frame M consisting set of partitions Ptn and each partition having set of task/process τn/Psn. The number of partitions and number of processes in each partition is a trade-off between the real time requirements and the resource. The paper also presents in brief, the API functionalities, its components, implementation, required interfaces, restrictions based on criticality of the avionics application. Error detection, control mechanisms for data integrity and validity for reconfiguration is also addressed. The experimental and simulation studies related to the API utilization as part of case study is addressed with four partitioned case study demonstrating the normal and failure scenario.Defence Science Journal, 2013, 63(2, pp.223-229, DOI:

  8. Modeling of signal transmitting of avionic systems based on Volterra series

    Directory of Open Access Journals (Sweden)

    Юрий Владимирович Пепа


    Full Text Available The paper deals with mathematical modeling methods for the formation and transmission of analogue and digital avionics systems using Volterra series. A mathematical model of the modulation in the presence of various initial data is developed, the computer modeling is conducted. The processes of analog modulation is simulated using MATLAB+SIMULINK, which allows you to simulate these processes, as well as explore them.

  9. Qualification of source code generators in the avionics domain : automated testing of model transformation chains


    Richa, Elie


    N the avionics industry, Automatic Code Generators (ACG) are increasingly used to produce parts of the embedded software. Since the generated code is part of critical software, safety standards require a thorough verification of the ACG called qualification. In this thesis in collaboration with AdaCore, we seek to reduce the cost of testing activities by automatic and effective methods.The first part of the thesis addresses the topic of unit testing which ensures exhaustiveness but is difficu...

  10. Validation Methods for Fault-Tolerant avionics and control systems, working group meeting 1 (United States)


    The proceedings of the first working group meeting on validation methods for fault tolerant computer design are presented. The state of the art in fault tolerant computer validation was examined in order to provide a framework for future discussions concerning research issues for the validation of fault tolerant avionics and flight control systems. The development of positions concerning critical aspects of the validation process are given.

  11. Virtual Instrumentation Techniques in Test and Evaluation of Launch Vehicle Avionics


    R. Sethunadh; S. Athuladevi; S. Sankara Iyer


    This paper presents the concept of virtual instrumentation and its importance in test and evaluation of launch vehicle avionics. The experiences at the Vikram Sarabhai Space Centre (VSSC) with virtual instrumentation systems, highlighting the virtual instrumentation-based checkout systems of pyro current monitoring package and video image processing unit are presented. The virtual instrumentation system-based checkouts present cost-effective, compact, and user-friendly human-machine in...

  12. 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...

  14. 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 ...

  15. NEXUS Scalable and Distributed Next-Generation Avionics Bus for Space Missions (United States)

    He, Yutao; Shalom, Eddy; Chau, Savio N.; Some, Raphael R.; Bolotin, Gary S.


    A paper discusses NEXUS, a common, next-generation avionics interconnect that is transparently compatible with wired, fiber-optic, and RF physical layers; provides a flexible, scalable, packet switched topology; is fault-tolerant with sub-microsecond detection/recovery latency; has scalable bandwidth from 1 Kbps to 10 Gbps; has guaranteed real-time determinism with sub-microsecond latency/jitter; has built-in testability; features low power consumption (avionics interconnect requirements without breaking the standard. This unified interconnect technology can be used to meet performance, power, size, and reliability requirements of all ranges of equipment, sensors, and actuators at chip-to-chip, board-to-board, or box-to-box boundary. Early results from in-house modeling activity of Serial RapidIO using VisualSim indicate that the use of a switched, high-performance avionics network will provide a quantum leap in spacecraft onboard science and autonomy capability for science and exploration missions.

  16. 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.

  17. Vertical Guidance Performance Analysis of the L1-L5 Dual-Frequency GPS/WAAS User Avionics Sensor

    Directory of Open Access Journals (Sweden)

    Shau-Shiun Jan


    Full Text Available This paper investigates the potential vertical guidance performance of global positioning system (GPS/wide area augmentation system (WAAS user avionics sensor when the modernized GPS and Galileo are available. This paper will first investigate the airborne receiver code noise and multipath (CNMP confidence (σair. The σair will be the dominant factor in the availability analysis of an L1-L5 dual-frequency GPS/WAAS user avionics sensor. This paper uses the MATLAB Algorithm Availability Simulation Tool (MAAST to determine the required values for the σair, so that an L1-L5 dual-frequency GPS/WAAS user avionics sensor can meet the vertical guidance requirements of APproach with Vertical guidance (APV II and CATegory (CAT I over conterminous United States (CONUS. A modified MAAST that includes the Galileo satellite constellation is used to determine under what user configurations WAAS could be an APV II system or a CAT I system over CONUS. Furthermore, this paper examines the combinations of possible improvements in signal models and the addition of Galileo to determine if GPS/WAAS user avionics sensor could achieve 10 m Vertical Alert Limit (VAL within the service volume. Finally, this paper presents the future vertical guidance performance of GPS user avionics sensor for the United States’ WAAS, Japanese MTSAT-based satellite augmentation system (MSAS and European geostationary navigation overlay service (EGNOS.

  18. Vertical guidance performance analysis of the L1-L5 dual-frequency GPS/WAAS user avionics sensor. (United States)

    Jan, Shau-Shiun


    This paper investigates the potential vertical guidance performance of global positioning system (GPS)/wide area augmentation system (WAAS) user avionics sensor when the modernized GPS and Galileo are available. This paper will first investigate the airborne receiver code noise and multipath (CNMP) confidence (σair). The σair will be the dominant factor in the availability analysis of an L1-L5 dual-frequency GPS/WAAS user avionics sensor. This paper uses the MATLAB Algorithm Availability Simulation Tool (MAAST) to determine the required values for the σair, so that an L1-L5 dual-frequency GPS/WAAS user avionics sensor can meet the vertical guidance requirements of APproach with Vertical guidance (APV) II and CATegory (CAT) I over conterminous United States (CONUS). A modified MAAST that includes the Galileo satellite constellation is used to determine under what user configurations WAAS could be an APV II system or a CAT I system over CONUS. Furthermore, this paper examines the combinations of possible improvements in signal models and the addition of Galileo to determine if GPS/WAAS user avionics sensor could achieve 10 m Vertical Alert Limit (VAL) within the service volume. Finally, this paper presents the future vertical guidance performance of GPS user avionics sensor for the United States' WAAS, Japanese MTSAT-based satellite augmentation system (MSAS) and European geostationary navigation overlay service (EGNOS). PMID:22319263

  19. 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).

  20. 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.

  1. 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


    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.

  3. 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.

  4. 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.

  5. A comparison of computer architectures for the NASA demonstration advanced avionics system (United States)

    Seacord, C. L.; Bailey, D. G.; Larson, J. C.


    The paper compares computer architectures for the NASA demonstration advanced avionics system. Two computer architectures are described with an unusual approach to fault tolerance: a single spare processor can correct for faults in any of the distributed processors by taking on the role of a failed module. It was shown the system must be used from a functional point of view to properly apply redundancy and achieve fault tolerance and ultra reliability. Data are presented on complexity and mission failure probability which show that the revised version offers equivalent mission reliability at lower cost as measured by hardware and software complexity.

  6. 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 ...

  7. Association entre exposition au bruit des avions et mortalité par maladies de l'appareil circulatoire en France


    BOUAOUN, Liacine; Champelovier, Patricia; Lambert, Jacques; Laumon, Bernard; Evrard, Anne-Sophie


    Introduction : En France, peu d’études se sont intéressés aux effets du bruit des avions sur la santé, et en particulier sur la mortalité. L’objectif de l’étude écologique du programme de recherche DEBATS (Discussion sur les Effets du Bruit des Aéronefs Touchant la Santé) est d’étudier l’association entre le niveau d’exposition au bruit des avions et le risque de mortalité par maladies de l’appareil circulatoire. Méthodes : La zone d’étude compr...

  8. Integrated Avionics System (IAS), Integrating 3-D Technology On A Spacecraft Panel (United States)

    Hunter, Don J.; Halpert, Gerald


    As spacecraft designs converge toward miniaturization, and with the volumetric and mass challenges placed on avionics, programs will continue to advance the "state of the art" in spacecraft system development with new challenges to reduce power, mass and volume. Traditionally, the trend is to focus on high-density 3-D packaging technologies. Industry has made significant progress in 3-D technologies, and other related internal and external interconnection schemes. Although new technologies have improved packaging densities, a system packaging architecture is required that not only reduces spacecraft volume and mass budgets, but increase integration efficiencies, provide modularity and flexibility to accommodate multiple missions while maintaining a low recurring cost. With these challenges in mind, a novel system packaging approach incorporates solutions that provide broader environmental applications, more flexible system interconnectivity, scalability, and simplified assembly test and integration schemes. The Integrated Avionics System (IAS) provides for a low-mass, modular distributed or centralized packaging architecture which combines ridged-flex technologies, high-density COTS hardware and a new 3-D mechanical packaging approach, Horizontal Mounted Cube (HMC). This paper will describe the fundamental elements of the IAS, HMC hardware design, system integration and environmental test results.

  9. Requirements Baseline for Integrated Modular Avionics for Space Separation Kernel Qualification (United States)

    Hann, Mark; Deredempt, Marie Helene; Cortier, Alexandre; De Ferluc, Regis; Galizzi, Julien


    In order to address the increasing complexity of spacecraft avionics, ESA have explored technological solutions adopted by the aeronautical domain for this purpose: Integrated Modular Avionics (IMA) and time and space partitioning (TSP). Over the past few years, a number of studies launched by ESA have explored how the solutions from the aeronautical domain could be adopted in the space domain. The technical solutions from the aeronautical domain have been adapted to the requirements of space missions, and an approach named IMA for Space (IMA-SP for short) has been introduced providing an IMA-SP Platform. The IMA-SP platform is dedicated to supporting the time and space partitioning of the spacecraft applications. The core software component is called the System Executive Platform software (SEP). The SEP contains a separation kernel that schedules the execution of partitions and provides the partitioning mechanisms. A small number of separation kernels already exist and have been demonstrated in previous studies [1]. These existing separation kernels must first be qualified before they are used in flight software.

  10. Digital Avionics Information System (DAIS): Reliability and Maintainability Model Users Guide. Final Report, May 1975-July 1977. (United States)

    Czuchry, Andrew J.; And Others

    This report provides a complete guide to the stand alone mode operation of the reliability and maintenance (R&M) model, which was developed to facilitate the performance of design versus cost trade-offs within the digital avionics information system (DAIS) acquisition process. The features and structure of the model, its input data requirements,…

  11. Search and Rescue Aircrewman/HH3F Avionics, 2-11. Military Curriculum Materials for Vocational and Technical Education. (United States)

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

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

  12. Digital Avionics Information System (DAIS): Impact of DAIS Concept on Life Cycle Cost--Supplement. Final Report. (United States)

    Goclowski, John C.; And Others

    This supplement to a technical report providing the results of a preliminary investigation of the potential impact of the Digital Avionics Information System (DAIS) concept on system support personnel requirements and life cycle cost (LCC) includes: (1) additional details of the cost comparison of a hypothetical application of a conceptual…

  13. 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

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

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


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

  15. Experimenting Maintenance of Flight Software in an Integrated Modular Avionics for Space (United States)

    Hardy, Johan; Laroche, Thomas; Creten, Philippe; Parisis, Paul; Hiller, Martin


    This paper presents an experiment of Flight Software partitioning in an Integrated Modular Avionics for Space (IMA-SP) system. This experiment also tackles the maintenance aspects of IMA-SP systems. The presented case study is PROBA-2 Flight Software. The paper addresses and discusses the following subjects: On-Board Software Maintenance in IMA-SP, boot strategy for Time and Space Partitioning, considerations about the ground segment related to On-Board Software Maintenance in IMA-SP, and architectural impacts of Time and Space Partitioning for PROBA software's. Finally, this paper presents the results and the achievements of the study and it appeals at further perspectives for IMA-SP and Time and Space Partitioning.

  16. Virtual Instrumentation Techniques in Test and Evaluation of Launch Vehicle Avionics

    Directory of Open Access Journals (Sweden)

    R. Sethunadh


    Full Text Available This paper presents the concept of virtual instrumentation and its importance in test and evaluation of launch vehicle avionics. The experiences at the Vikram Sarabhai Space Centre (VSSC with virtual instrumentation systems, highlighting the virtual instrumentation-based checkout systems of pyro current monitoring package and video image processing unit are presented. The virtual instrumentation system-based checkouts present cost-effective, compact, and user-friendly human-machine interlaces for the test and evaluation of these packages. The issues of a common hardware-software platform for testing different telemetry packages and the capability of real-time virtual instruments for testing navigation, guidance, and control packages have been investigated.

  17. "STEPS" Avionics for Exploration Systems the Achieved Results and the Next "STEPS-2" (United States)

    Martelli, Andrea; Perino, Maria Antonietta; Gaia, Enrico; Paccagnini, Carlo


    This paper presents the STEPS project reached results in the avionics domains like: vision-based GNC for Mars Descent & Landing, Hazard avoidance and complete spacecraft autonomy; Autonomous Rover Navigation, based on perception, 3D map reconstruction and path planning; Mobility & Mechanisms providing an Integrated Ground Mobility System, Rendezvous & Docking equipment, and protection from Environment effects; Human-machine interface features of a predictive Command and Control System;; novel Design & Development Tools, such as a Rover S/W simulator and prototypes of the DEM viewer and of a S/W Rock Creator/visualizator. This paper presents also the STEPS 2 project that started January 2013 and is aimed at improving the development of the most promising technologies, selected from the results of the first STEP phase, and addressing the needs of the exploration missions as defined in the 2012 ministerial conference, with the ultimate goal of an in-flight validation within next five years.

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

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


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

  19. 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.

  20. Chapitre premier. Des avions américains pour la France


    Bossuat, Gérard


    Les commandes d’avions américains font-elles partie des aides à la France ou appartiennent-elles aux échanges commerciaux ordinaires ? La réponse est évidente. Ce sont des aides puisque les États-Unis vivent sous le régime des lois de neutralité qui établissent un embargo sur les ventes d’armes. Il faut distinguer trois périodes : la période d’avant-guerre, où les ventes d’armes étaient difficiles en raison du non-paiement des dettes de guerre par la France, la période comprise entre le 5 sep...

  1. Multimodalité TGV-avion : considérations sur le cas de Bruxelles


    Dobruszkes, Frédéric


    La mode est à l’interconnexion des réseaux TGV et des aéroports. Si dans certains cas cela est pleinement justifié par une aire d’influence de l’aéroport suffisamment étendue pour correspondre aux distances TGV, dans d’autres ce n’est pas le cas et la correspondance avion / TGV est alors peu utilisée par les voyageurs.Qu’en est-il du cas de l’aéroport de Bruxelles-National ? Cet article se propose d’analyser l’utilité d’une desserte TGV de cet aéroport, du point de vue de l’offre et de la dem...

  2. 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.

  3. Applications of Formal Methods to Specification and Safety of Avionics Software (United States)

    Hoover, D. N.; Guaspari, David; Humenn, Polar


    This report treats several topics in applications of formal methods to avionics software development. Most of these topics concern decision tables, an orderly, easy-to-understand format for formally specifying complex choices among alternative courses of action. The topics relating to decision tables include: generalizations fo decision tables that are more concise and support the use of decision tables in a refinement-based formal software development process; a formalism for systems of decision tables with behaviors; an exposition of Parnas tables for users of decision tables; and test coverage criteria and decision tables. We outline features of a revised version of ORA's decision table tool, Tablewise, which will support many of the new ideas described in this report. We also survey formal safety analysis of specifications and software.

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

    Ivancic, William D.


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

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

    International Nuclear Information System (INIS)

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

  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. TechEdSat - An Educational 1U CubeSat Architecture Using Plug-and-Play Avionics (United States)

    Frost, Chad


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

  9. 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.

  10. Reference Architecture Test-Bed for Avionics (RASTA): A Software Building Blocks Overview (United States)

    Viana Sanchez, Aitor; Taylor, Chris


    This paper presents an overview of the Reference Architecture System Test-bed for Avionics (RASTA) being developed within the ESA Estec Data Systems Division. This activity aims to benefit from interface standardization to provide a hardware/software reference infrastructure into which incoming R&D activities can be integrated, thus providing a generic but standardized test and development environment rather than dedicated facilities for each activity. Rasta is composed of by both HW and SW building blocks constituting the main elements of a typical Data Handling System. This includes a core processor (LEON2), Telemetry and Telecommand links, digital interfaces, and mass memory. The range of digital serial interfaces includes CAN bus, MIL-STD-1553 and SpaceWire. The paper will focus on the Software aspects of RASTA and in particular the software building blocks provided to ease development activities and allow hardware independency. To support the take-up of RASTA by European Industry, all RASTA software developed internally by ESA is provided free under license. Significant outputs are already available and include: Basic SW and SW drivers (CAN/1553/SpW, TT&C), OS abstraction layer, CFDP flight implementation, highly portable and independent file system for space, ground segment telecommand/telemetry router. In the future, additional SW building blocks are planned (e.g. ECSS CAN library). The present focus of RASTA is related to a prototype implementation of the SOIS services and protocols under development by the CCSDS (Consultative committee for Space Data Standards)

  11. 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

  12. 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.

  13. Model-Driven Development of Reliable Avionics Architectures for Lunar Surface Systems (United States)

    Borer, Nicholas; Claypool, Ian; Clark, David; West, John; Somervill, Kevin; Odegard, Ryan; Suzuki, Nantel


    This paper discusses a method used for the systematic improvement of NASA s Lunar Surface Systems avionics architectures in the area of reliability and fault-tolerance. This approach utilizes an integrated system model to determine the effects of component failure on the system s ability to provide critical functions. A Markov model of the potential degraded system modes is created to characterize the probability of these degraded modes, and the system model is run for each Markov state to determine its status (operational or system loss). The probabilistic results from the Markov model are first produced from state transition rates based on NASA data for heritage failure rate data of similar components. An additional set of probabilistic results are created from a representative set of failure rates developed for this study, for a variety of component quality grades (space-rated, mil-spec, ruggedized, and commercial). The results show that careful application of redundancy and selected component improvement should result in Lunar Surface Systems architectures that exhibit an appropriate degree of fault-tolerance, reliability, performance, and affordability.

  14. 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.

  15. Vertical Guidance Performance Analysis of the L1–L5 Dual-Frequency GPS/WAAS User Avionics Sensor (United States)

    Jan, Shau-Shiun


    This paper investigates the potential vertical guidance performance of global positioning system (GPS)/wide area augmentation system (WAAS) user avionics sensor when the modernized GPS and Galileo are available. This paper will first investigate the airborne receiver code noise and multipath (CNMP) confidence (σair). The σair will be the dominant factor in the availability analysis of an L1–L5 dual-frequency GPS/WAAS user avionics sensor. This paper uses the MATLAB Algorithm Availability Simulation Tool (MAAST) to determine the required values for the σair, so that an L1–L5 dual-frequency GPS/WAAS user avionics sensor can meet the vertical guidance requirements of APproach with Vertical guidance (APV) II and CATegory (CAT) I over conterminous United States (CONUS). A modified MAAST that includes the Galileo satellite constellation is used to determine under what user configurations WAAS could be an APV II system or a CAT I system over CONUS. Furthermore, this paper examines the combinations of possible improvements in signal models and the addition of Galileo to determine if GPS/WAAS user avionics sensor could achieve 10 m Vertical Alert Limit (VAL) within the service volume. Finally, this paper presents the future vertical guidance performance of GPS user avionics sensor for the United States’ WAAS, Japanese MTSAT-based satellite augmentation system (MSAS) and European geostationary navigation overlay service (EGNOS). PMID:22319263

  16. 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.

  17. 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.

  18. New capabilities for older aircraft: A study of pilot integration of retro-fit digital avionics to analog-instrumented flight decks (United States)

    Breuer, Glynn E.

    The purpose of this study was to determine whether applying Gilbert's Behavior Engineering Model to military tactical aviation organizations would foster effective user integration of retro-fit digital avionics in analog-instrumented flight decks. This study examined the relationship between the reported presence of environmental supports and personal repertory supports as defined by Gilbert, and the reported self-efficacy of users of retro-fit digital avionics to analog flight decks, and examined the efficacious behaviors of users as they attain mastery of the equipment and procedures, and user reported best practices and criteria for masterful performance in the use of retro-fit digital avionics and components. This study used a mixed methodology, using quantitative surveys to measure the perceived level of organizational supports that foster mastery of retro-fit digital avionic components, and qualitative interviews to ascertain the efficacious behaviors and best practices of masterful users of these devices. The results of this study indicate that there is some relationship between the reported presence of organizational supports and personal repertory supports and the reported self-mastery and perceived organizational mastery of retro-fit digital avionics applied to the operation of the research aircraft. The primary recommendation is that unit leadership decide exactly the capabilities desired from retro-fit equipment, publish these standards, ensure training in these standards is effective, and evaluate performance based on these standards. Conclusions indicate that sufficient time and resources are available to the individual within the study population, and the organization as a whole, to apply Gilbert's criteria toward the mastery of retro-fit digital avionics applied to the operation of the research aircraft.

  19. Investigation of HZETRN 2010 as a Tool for Single Event Effect Qualification of Avionics Systems - Part II (United States)

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


    An accurate prediction of spacecraft avionics single event effect (SEE) radiation susceptibility is key to ensuring a safe and reliable vehicle. This is particularly important for long-duration deep space missions for human exploration where there is little or no chance for a quick emergency return to Earth. Monte Carlo nuclear reaction and transport codes such as FLUKA can be used to generate very accurate models of the expected in-flight radiation environment for SEE analyses. A major downside to using a Monte Carlo-based code is that the run times can be very long (on the order of days). A more popular choice for SEE calculations is the CREME96 deterministic code, which offers significantly shorter run times (on the order of seconds). However, CREME96, though fast and easy to use, has not been updated in several years and underestimates secondary particle shower effects in spacecraft structural shielding mass. Another modeling option to consider is the deterministic code HZETRN 20104, which includes updates to address secondary particle shower effects more accurately. This paper builds on previous work by Rojdev, et al. to compare the use of HZETRN 2010 against CREME96 as a tool to verify spacecraft avionics system reliability in a space flight SEE environment. This paper will discuss modifications made to HZETRN 2010 to improve its performance for calculating SEE rates and compare results with both in-flight SEE rates and other calculation methods.

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

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


    NASA's future missions are focused on deep space for human exploration that do not provide a simple emergency return to Earth. In addition, the deep space environment contains a constant background Galactic Cosmic Ray (GCR) radiation exposure, as well as periodic Solar Particle Events (SPEs) that can produce intense amounts of radiation in a short amount of time. Given these conditions, it is important that the avionics systems for deep space human missions are not susceptible to Single Event Effects (SEE) that can occur from radiation interactions with electronic components. The typical process to minimizing SEE effects is through using heritage hardware and extensive testing programs that are very costly. Previous work by Koontz, et al. [1] utilized an analysis-based method for investigating electronic component susceptibility. In their paper, FLUKA, a Monte Carlo transport code, was used to calculate SEE and single event upset (SEU) rates. This code was then validated against in-flight data. In addition, CREME-96, a deterministic code, was also compared with FLUKA and in-flight data. However, FLUKA has a long run-time (on the order of days), and CREME-96 has not been updated in several years. This paper will investigate the use of HZETRN 2010, a deterministic transport code developed at NASA Langley Research Center, as another tool that can be used to analyze SEE and SEU rates. The benefits to using HZETRN over FLUKA and CREME-96 are that it has a very fast run time (on the order of minutes) and has been shown to be of similar accuracy as other deterministic and Monte Carlo codes when considering dose [2, 3, 4]. The 2010 version of HZETRN has updated its treatment of secondary neutrons and thus has improved its accuracy over previous versions. In this paper, the Linear Energy Transfer (LET) spectra are of interest rather than the total ionizing dose. Therefore, the LET spectra output from HZETRN 2010 will be compared with the FLUKA and in-flight data to validate

  1. 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

  2. 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

  3. Military Curriculum Materials for Vocational and Technical Education. Avionics Instrument Systems Specialist. POI C3ABR32531 000. Classroom Course 2-7. (United States)

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

    This high school-postsecondary-level course for avionics instrument systems specialist is one of a number of military-developed curriculum packages selected for adaptation to vocational instruction and curriculum development in a civilian setting. A plan of instruction outlines five blocks of instruction (281 hours of instruction). Block 1,…

  4. Relationships Between Design Characteristics of Avionics Subsystems and Training Cost, Training Difficulty, and Job Performance. Final Report, Covering Activity from 1 July 1971 Through 1 September 1972. (United States)

    Lintz, Larry M.; And Others

    A study investigated the relationship between avionics subsystem design characteristics and training time, training cost, and job performance. A list of design variables believed to affect training and job performance was established and supplemented with personnel variables, including aptitude test scores and the amount of training and…

  5. 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.

  6. 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.

  7. Space tug point design study. Volume 3: Design definition. Part 1: Propulsion and mechanical, avionics, thermal control and electrical power subsystems (United States)


    A study was conducted to determine the configuration and performance of a space tug. Details of the space tug systems are presented to include: (1) propulsion systems, (2) avionics, (3) thermal control, and (4) electric power subsystems. The data generated include engineering drawings, schematics, subsystem operation, and component description. Various options investigated and the rational for the point design selection are analyzed.

  8. Simulation modeling based method for choosing an effective set of fault tolerance mechanisms for real-time avionics systems (United States)

    Bakhmurov, A. G.; Balashov, V. V.; Glonina, A. B.; Pashkov, V. N.; Smeliansky, R. L.; Volkanov, D. Yu.


    In this paper, the reliability allocation problem (RAP) for real-time avionics systems (RTAS) is considered. The proposed method for solving this problem consists of two steps: (i) creation of an RTAS simulation model at the necessary level of abstraction and (ii) application of metaheuristic algorithm to find an optimal solution (i. e., to choose an optimal set of fault tolerance techniques). When during the algorithm execution it is necessary to measure the execution time of some software components, the simulation modeling is applied. The procedure of simulation modeling also consists of the following steps: automatic construction of simulation model of the RTAS configuration and running this model in a simulation environment to measure the required time. This method was implemented as an experimental software tool. The tool works in cooperation with DYANA simulation environment. The results of experiments with the implemented method are presented. Finally, future plans for development of the presented method and tool are briefly described.

  9. 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...

  10. 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.

  11. 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.

  12. 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...

  13. 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.

  14. 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.

  15. 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

  16. 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。

  17. 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.

  18. Cosmic Radiation Effects on Avionics

    International Nuclear Information System (INIS)

    The earth is bombarded by a nearly isotropic flux of energetic charged particles called cosmic rays which interact with air nuclei to generate a cascade of secondary particles building up to a maximum intensity at 60,000 feet. At normal cruising altitudes the radiation is still several hundred times the ground level intensity. These particles are sufficiently energetic and ionising that they can deposit enough charge in a small volume of semiconductor to change the state of a memory cell, while certain devices can be triggered into a state of high current drain, leading to burn-out and hardware failure. These deleterious interactions of individual particles are referred to as single event effects. The authors have flown Cosmic Radiation Effects detectors in a variety of spacecraft and aircraft and illustrative results are presented together with a review of published instances of such phenomena in flight systems. In the future there is likely to be increased susceptibility due to growing reliance on high performance computers using smaller devices operated at lower voltages and flying at higher altitudes. The influence of cosmic rays will have to be properly considered in the assessment of reliability. (author)

  19. 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 ...

  20. Estudio de factibilidad para formar idóneamente técnicos línea de aviones aprovechando la capacidad ociosa disponible del Centro de Entrenamiento Técnico de Avianca


    Castillo Waltero, Monica Paola; Marín Maya, María Cecilia


    Avianca es una aerolínea colombiana con más de noventa años en la industria del transporte aéreo de pasajeros -- Cuenta además con un aproximado de mil personas capacitadas exclusivamente para la atención técnica de las aeronaves y realiza esta labor en el Centro de Entrenamiento Técnico ubicado en la ciudad de Bogotá -- Los técnicos línea de aviones son personas que realizaron estudios básicos de técnicos en instituciones técnicas y tecnológicas en su mayoría colombianas y posteriorm...

  1. 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

  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. 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.

  5. 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.

  6. FPGA for Power Control of MSL Avionics (United States)

    Wang, Duo; Burke, Gary R.


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

  7. 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.

  8. 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...

  9. 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...

  10. 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...

  11. 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.

  12. 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...

  13. Model-Based Verification and Validation of Spacecraft Avionics (United States)

    Khan, Mohammed Omair


    Our simulation was able to mimic the results of 30 tests on the actual hardware. This shows that simulations have the potential to enable early design validation - well before actual hardware exists. Although simulations focused around data processing procedures at subsystem and device level, they can also be applied to system level analysis to simulate mission scenarios and consumable tracking (e.g. power, propellant, etc.). Simulation engine plug-in developments are continually improving the product, but handling time for time-sensitive operations (like those of the remote engineering unit and bus controller) can be cumbersome.

  14. Shuttle Communications and Tracking, Avionics, and Electromagnetic Compatibility (United States)

    deSilva, K.; Hwu, Shian; Kindt, Kaylene; Kroll, Quin; Nuss, Ray; Romero, Denise; Schuler, Diana; Sham, Catherine; Scully, Robert


    By definition, electromagnetic compatibility (EMC) is the capability of components, sub-systems, and systems, to operate in their intended electromagnetic environment, within an established margin of safety, and at design levels of performance. Practice of the discipline itself incorporates knowledge of various aspects of applied physics, materials science, and engineering across the board, and includes control and mitigation of undesirable electromagnetic interaction between intentional and unintentional emitters and receivers of radio frequency energy, both within and external to the vehicle; identification and control of the hazards of non-ionizing electromagnetic radiation to personnel, ordnance, and fuels and propellants; and vehicle and system protection from the direct and indirect effects of lightning and various other forms of electrostatic discharge (ESD) threats, such as triboelectrification and plasma charging. EMC is extremely complex and far-reaching, affecting in some degree every aspect of the vehicle s design and operation. The most successful efforts incorporate EMC design features and techniques throughout design and fabrication of the vehicle s structure and components, as well as appropriate operational considerations with regard to electromagnetic threats in the operational environment, from the beginning of the design effort to the end of the life cycle of the manufactured product. This approach yields the highest design performance with the lowest cost and schedule impact.




  16. 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.

  17. 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.

  18. System Design Toolkit for Integrated Modular Avionics for Space (United States)

    Hann, Mark; Balbastre Betoret, Patricia; Simo Ten, Jose Enrique; De Ferluc, Regis; Ramachandran, Jinesh


    The IMA-SP development process identified tools were needed to perform the activities of: i) Partitioning and Resource Allocation and ii) System Feasibility Assessment. This paper describes the definition, design, implementation and test of the tool support required to perform the IMA-SP development process activities. This includes the definition of a data model, with associated files and file formats, describing the complete setup of a partitioned system and allowing system feasibility assessment; the development of a prototype of the tool set, that is called the IMA-SP System Design Toolkit (SDT) and the demonstration of the toolkit on a case study.

  19. Solid state microdosimeter for radiation monitoring in spacecraft and avionics

    International Nuclear Information System (INIS)

    An instrument is described which is designed to characterize the complex radiation environments inside spacecraft and airplanes in terms of the risk of SEEs in the present and planned microelectronic systems and in terms of the risk to flight crews and passengers

  20. 2013 aircrew, avionics, and operations survey, part 1. (United States)

    Greene, Michael J


    Air medical transport services (AMTS) depend on the teamwork of aviation professionals, medical caregivers, communications specialists, maintenance staff, and administrative personnel to facilitate the safe medical transportation and care to critically ill and injured patients across the world. Consisting of respondents based in the United States, this 2013 survey revisits contemporary AMTS aircrew (pilot, aviator) experience, compensation, benefits, training, and safety in the industry compared to a survey conducted in 2000. PMID:24182879

  1. 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.

  2. 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.

  3. 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...

  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. Development of Enhanced Avionics Flight Hardware Selection Process (United States)

    Smith, K.; Watson, G. L.


    The primary objective of this research was to determine the processes and feasibility of using commercial off-the-shelf PC104 hardware for flight applications. This would lead to a faster, better, and cheaper approach to low-budget programs as opposed to the design, procurement. and fabrication of space flight hardware. This effort will provide experimental evaluation with results of flight environmental testing. Also, a method and/or suggestion used to bring test hardware up to flight standards will be given. Several microgravity programs, such as the Equiaxed Dendritic Solidification Experiment, Self-Diffusion in Liquid Elements, and various other programs, are interested in PC104 environmental testing to establish the limits of this technology.

  6. 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

  7. 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...

  8. 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.

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

    Orr, James K.


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

  10. Simple Statistical Model to Quantify Maximum Expected EMC in Spacecraft and Avionics Boxes (United States)

    Trout, Dawn H.; Bremner, Paul


    This study shows cumulative distribution function (CDF) comparisons of composite a fairing electromagnetic field data obtained by computational electromagnetic 3D full wave modeling and laboratory testing. Test and model data correlation is shown. In addition, this presentation shows application of the power balance and extention of this method to predict the variance and maximum exptected mean of the E-field data. This is valuable for large scale evaluations of transmission inside cavities.

  11. Digital Avionics Information System (DAIS): Training Requirements Analysis Model Users Guide. Final Report. (United States)

    Czuchry, Andrew J.; And Others

    This user's guide describes the functions, logical operations and subroutines, input data requirements, and available outputs of the Training Requirements Analysis Model (TRAMOD), a computerized analytical life cycle cost modeling system for use in the early stages of system design. Operable in a stand-alone mode, TRAMOD can be used for the…

  12. Altitude and latitude variations in avionics SEU and atmospheric neutron flux

    International Nuclear Information System (INIS)

    The direct cause of single event upsets in SRAMs at aircraft altitudes by the atmospheric neutrons has previously been documented. The variation of the in-flight SEU rate with latitude is demonstrated by new data over a wide range of geographical locations. New measurements and models of the atmospheric neutron flux are also evaluated to characterize its variation with altitude, latitude and solar activity

  13. 78 FR 68687 - Final Additional Airworthiness Design Standards: Advanced Avionics Under the Special Class (JAR... (United States)


    ... on September 2, 2003 (68 FR 56809). The regulation applicable to the Amended Type Certificate (TC... Aquila AT01-100 airplane to include Night-VFR as shown in NPRM 75 FR 32576. In conjunction with the... Register on September 6, 2013, (78 FR 54792). One comment was received from Mr. Alfred Schmiderer...

  14. High-temperature superconductivity for avionic electronic warfare and radar systems

    International Nuclear Information System (INIS)

    The electronic warfare (EW) and radar communities expect to be major beneficiaries of the performance advantages high-temperature superconductivity (HTS) has to offer over conventional technology. Near term upgrades to system hardware can be envisioned using extremely small, high Q, microwave filters and resonators; compact, wideband, low loss, microwave delay and transmission lines; as well as, wideband, low loss, monolithic microwave integrated circuit phase shifters. The most dramatic impact will be in the far term, using HTS to develop new, real time threat identification and response strategy receiver/processing systems designed to utilize the unique high frequency properties of microwave and ultimately digital HTS. To make superconductivity practical for operational systems, however, technological obstacles need to be overcome. Compact cryogenically cooled subsystems with exceptional performance able to withstand rugged operational environments for long periods of time need to be developed

  15. 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.

  16. 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...

  17. 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...

  18. 78 FR 70892 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes (United States)


    ... approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the... of a cockpit forward right-hand side blow out during flight. This proposed AD would require.... FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch,...

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

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


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

  20. Evaluating the Effects of Dimensionality in Advanced Avionic Display Concepts for Synthetic Vision Systems (United States)

    Alexander, Amy L.; Prinzel, Lawrence J., III; Wickens, Christopher D.; Kramer, Lynda J.; Arthur, Jarvis J.; Bailey, Randall E.


    Synthetic vision systems provide an in-cockpit view of terrain and other hazards via a computer-generated display representation. Two experiments examined several display concepts for synthetic vision and evaluated how such displays modulate pilot performance. Experiment 1 (24 general aviation pilots) compared three navigational display (ND) concepts: 2D coplanar, 3D, and split-screen. Experiment 2 (12 commercial airline pilots) evaluated baseline 'blue sky/brown ground' or synthetic vision-enabled primary flight displays (PFDs) and three ND concepts: 2D coplanar with and without synthetic vision and a dynamic multi-mode rotatable exocentric format. In general, the results pointed to an overall advantage for a split-screen format, whether it be stand-alone (Experiment 1) or available via rotatable viewpoints (Experiment 2). Furthermore, Experiment 2 revealed benefits associated with utilizing synthetic vision in both the PFD and ND representations and the value of combined ego- and exocentric presentations.

  1. 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...

  2. 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.

  3. 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.

  4. 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.

  5. 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.

  6. 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.

  7. 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.

  8. Self-ratings of eight factors of quality management at Naval Avionics Center


    Hocevar, Susan Page; Applegate, Carolyn L.; Thomas, Kenneth Wayne


    The focus of this report is the implementation of Total Quality Management in ten DoD organizations. The Participating organizations were all identified by the Federal Quality Institute as either winners or finalists of the Productivity/Quality Management and Budget. Qualitative data collected included interviews with either top executives or TQM coordinators, documentation of quality management activities. A questionnaire survey was also administered to the executive steering committee of ea...

  9. Integrated guidance, navigation and control verification plan primary flight system. [space shuttle avionics integration (United States)


    The verification process and requirements for the ascent guidance interfaces and the ascent integrated guidance, navigation and control system for the space shuttle orbiter are defined as well as portions of supporting systems which directly interface with the system. The ascent phase of verification covers the normal and ATO ascent through the final OMS-2 circularization burn (all of OPS-1), the AOA ascent through the OMS-1 burn, and the RTLS ascent through ET separation (all of MM 601). In addition, OPS translation verification is defined. Verification trees and roadmaps are given.

  10. Definition, analysis and development of an optical data distribution network for integrated avionics and control systems (United States)

    Burns, R. R.


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

  11. 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...

  12. Aircraft and avionic related research required to develop an effective high-speed runway exit system (United States)

    Schoen, M. L.; Hosford, J. E.; Graham, J. M., Jr.; Preston, O. W.; Frankel, R. S.; Erickson, J. B.


    Research was conducted to increase airport capacity by studying the feasibility of the longitudinal separation between aircraft sequences on final approach. The multidisciplinary factors which include the utility of high speed exits for efficient runway operations were described along with recommendations and highlights of these studies.

  13. Etude des defauts apparaissant dans les amenagements interieurs des avions d'affaires (United States)

    Charette, Emilie

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

  14. 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...

  15. 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.

  16. Navigation d'un avion miniature de surveillance aérienne en présence de vent


    Brezoescu, Cornel-Alexandru,


    Ce travail de thèse porte sur le comportement en vol de drones légers à voilure fixe en présence de vent. Ces dispositifs aériens offrent une transition en douceur de la théorie à la pratique dans le domaine de la commande autonome. En outre, ils fournissent une solution appropriée dans des environnements inaccessibles ou dangereux pour les êtres humains. Cependant, ne pas avoir un pilote humain à bord implique que les UAV reposent sur l'automatisation pour naviguer ou pour éviter les obstacl...

  17. 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.

  18. Cognitive Task Analysis and Intelligent Computer-Based Training Systems: Lessons Learned from Coached Practice Environments in Air Force Avionics. (United States)

    Katz, Sandra N.; Hall, Ellen; Lesgold, Alan

    This paper describes some results of a collaborative effort between the University of Pittsburgh and the Air Force to develop advanced troubleshooting training for F-15 maintenance technicians. The focus is on the cognitive task methodology used in the development of three intelligent tutoring systems to inform their instructional content and…

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

    International Nuclear Information System (INIS)

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

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

    Goclowski, John C.; Baran, H. Anthony

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

  1. 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.

  2. 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

  3. 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...

  4. Digital Avionics Information System (DAIS): Life Cycle Cost Impact Modeling System Reliability, Maintainability, and Cost Model (RMCM)--Description. Users Guide. Final Report. (United States)

    Goclowski, John C.; And Others

    The Reliability, Maintainability, and Cost Model (RMCM) described in this report is an interactive mathematical model with a built-in sensitivity analysis capability. It is a major component of the Life Cycle Cost Impact Model (LCCIM), which was developed as part of the DAIS advanced development program to be used to assess the potential impacts…

  5. 75 FR 8476 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Model ATR42 and ATR72 Airplanes (United States)


    ... FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, Transport... Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton... extinguishers, usually fitted or stowed in aircraft passenger cabins and flight decks. EASA published...

  6. 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.

  7. 77 FR 67557 - Special Conditions: ATR-GIE Avions de Transport Regional, Models ATR42-500 and ATR72-212A... (United States)


    ... Privacy Act Statement can be found in the Federal Register published on April 11, 2000 (65 FR 19477-19478... electronic form of all comments received into any FAA docket, including the name of the individual sending... configuration may allow the exploitation of network security vulnerabilities resulting in intentional...

  8. 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...

  9. 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.

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

    Sidibe, Souleymane

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

  11. 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. 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.

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

    Nadeau-Beaulieu, Michel

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

  15. 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.

  16. 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.)

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


    Jorge Joaquín Locane


    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...

  18. 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...

  19. Boron/aluminum shelf for shuttle orbiter

    International Nuclear Information System (INIS)

    Boron/aluminum skins and channels were used in the fabrication of a prototype honeycomb sandwich avionics shelf. The avionic shelves are stiffness-critical and must be vibration tolerant. In conjunction with the shelf mounting system, they must isolate the avionics equipment from the severe vibration of the primary and secondary structure nearby. Design rationale, fabrication procedures, vibration test criteria and test results are presented. (9 fig) (U.S.)

  20. Modelización de aeronaves no tripuladas con Simulink


    Vila Rovira, Oscar


    Desde el principio de la aviacion se han investigado y desarrollado aviones sin tripulacion, como usos de entrenamiento y, sobretodo, misiones militares. A principios de siglo, con la primera y la segunda guerra mundial, se hicieron los primeros aviones no tripulados. Los grandes avances en el campo de los aviones no tripulados, como en la aviacion en general, han surgido a raiz de guerras entre grandes potencias, siendo estos ultimos avances en las guerras del oriente medio. En los ultimos a...

  1. 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...

  2. 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...

  3. 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...

  4. 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...

  5. 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...

  6. 78 FR 70849 - Special Conditions: Boeing Model 777-200, -300, and -300ER Series Airplanes; Aircraft Electronic... (United States)


    ... the EFB architecture and existing airplane network systems. The applicable airworthiness regulations.... The proposed network architecture is used for a diverse set of functions, providing data connectivity..., software-configurable avionics, and fiber-optic avionics networks. The proposed Class 3 EFB architecture...

  7. 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.

  8. 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.

  9. Comparación de los resultados de las mediciones in situ del aislamiento acústico al ruido aéreo de fachadas, mediante la utilización de los métodos globales con altavoces y con ruido de aviones.


    Díaz Sanchidrián, César; Pedrero González, Antonio


    En este trabajo se comparan los resultados experimentales de las mediciones in situ del aislamiento acústico al ruido aéreo de fachadas de recintos, por aplicación en cada uno de los recintos de dos métodos globales de la Norma EN ISO 140-5, Agosto 1998. Se han utilizado como fuentes de ruido un altavoz y el ruido de aeronaves. Las mediciones acústicas se han realizado en 26 dormitorios situados en viviendas de uso residencial privado.

  10. 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...

  11. 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...

  12. Demonstration of 6DOF Arc-mim/mm Control in the FCT Using Proba-3 Metrology and Control System Project (United States)

    National Aeronautics and Space Administration — Implement in FCT avionics and attitude control architecture and software that enables order of magnitude increase in control capability for next-generation...

  13. 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...


    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...

  15. 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...

  16. 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...

  17. 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.

  18. 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...

  19. Ada Linear-Algebra Program (United States)

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


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

  20. 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...

  1. 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....

  2. 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...

  3. 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...

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

    Starr, Stanley


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

  5. SIF – Yet Another Spacecraft Interconnection Standard


    Sinclair, Doug


    SIF is a Standard InterFace for spacecraft electronics. It combines a number of existing standards+28 V avionics power, ISO 11898-3 fault-tolerant Control Area Network (CAN), and the CANopen software protocol. Terminals are connected into a closed loop by identical cables. The resulting network is fail-operational and is easy to modify even late in satellite integration. SpaceQuest experience building a large spacecraft with SIF avionics has demonstrated the cost and schedule savings inherent...

  6. PRISE: An Integrated Platform for Research and Teaching of Critical Embedded Systems


    Hugues, Jérôme; Siron, Pierre; Hamez, Alexandre


    In this paper, we present PRISE, an integrated workbench for Research and Teaching of critical embedded systems at ISAE, the French Institute for Space and Aeronautics Engineering. PRISE is built around state-of-the-art technologies for the engineering of space and avionics systems used in Space and Avionics domain. It aims at demonstrating key aspects of critical, real-time, embedded systems used in the transport industry, but also validating new scientific contributions for the engineering ...

  7. 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.

  8. Artificial Intelligence Research and Applications at the NASA Johnson Space Center, Part Two


    Healey, Kathleen Jurica


    This is the second part of a two-part article describing AI work at the NASA Johnson Space Center (JSC). Research and applications work in AI is being conducted by several groups at JSC. These are primarily independent groups that interact with each other on an informal basis. In the Research and Engineering Directorate, these groups include (1) the Artificial Intelligence and Information Sciences Office, (2) the Simulation and Avionics Integration Division, (3) the Avionics Systems Division,...

  9. Artificial Intelligence Research and Applications at the NASA Johnson Space Center: Part One


    Healey, Kathleen Jurica


    Research and applications work in AI is being conducted by several groups at Johnson Space Center (JSC). These are primarily independent groups that interact with each other on an informal basis. In the Research and Engineering Directorate, these groups include (1) the Artificial Intelligence and Information Sciences Office, (2) the Simulation and Avionics Integration Division, (3) the Avionics Systems Division (ASD), and (4) the Tracking and Communications Division. In the Space Operations D...

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

    Wray, Richard B.


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

  11. 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.)

  12. 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.

  13. 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.

  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. 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.

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

    Klumpp, Allan R.; Lawson, Charles L.


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

  19. Investigation of single event latchup

    International Nuclear Information System (INIS)

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

  20. Orion GN and C Mitigation Efforts for Van Allen Radiation (United States)

    King, Ellis T.; Jackson, Mark


    The Orion Crew Module (CM) is NASA's next generation manned space vehicle, scheduled to return humans to lunar orbit in the coming decade. The Orion avionics and GN&C architectures have progressed through a number of project phases and are nearing completion of a major milestone. The first unmanned test mission, dubbed "Exploration Flight Test One" (EFT-1) is scheduled to launch from NASA Kennedy Space Center late next year and provides the first integrated test of all the vehicle systems, avionics and software.

  1. 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

  2. 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.

  3. 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...

  4. 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

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

    Directory of Open Access Journals (Sweden)

    Shu-Kun Lin


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

  6. 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)

  7. 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.

  8. A bibliography on formal methods for system specification, design and validation (United States)

    Meyer, J. F.; Furchtgott, D. G.; Movaghar, A.


    Literature on the specification, design, verification, testing, and evaluation of avionics systems was surveyed, providing 655 citations. Journal papers, conference papers, and technical reports are included. Manual and computer-based methods were employed. Keywords used in the online search are listed.

  9. 15 CFR 738.2 - Commerce Control List (CCL) structure. (United States)


    ... 15 Commerce and Foreign Trade 2 2010-01-01 2010-01-01 false Commerce Control List (CCL) structure... COMMERCE CONTROL LIST OVERVIEW AND THE COUNTRY CHART § 738.2 Commerce Control List (CCL) structure. (a... Avionics 8—Marine 9—Propulsion Systems, Space Vehicles and Related Equipment (b) Groups. Within...

  10. 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

  11. 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.

  12. Advanced Functionalities for Highly Reliable Optical Networks

    DEFF Research Database (Denmark)

    An, Yi

    This thesis covers two research topics concerning optical solutions for networks e.g. avionic systems. One is to identify the applications for silicon photonic devices for cost-effective solutions in short-range optical networks. The other one is to realise advanced functionalities in order to...

  13. 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.

  14. 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.

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

    Rothgeb, Matt; Kessel, Kurt


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

  16. 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.

  17. Operational efficiency (United States)

    Bland, Dan; Davis, Tom; Griffin, Sandy


    Space transportation avionics technology operational efficiency issues are presented in viewgraph form. Information is given on ascent flight design, autonomous spacecraft control, operations management systems, advanced mission control, telerobotics/telepresence, advanced software integration, advanced test/checkout systems, advanced training systems, and systems monitoring.

  18. 14 CFR Appendix A to Part 65 - Aircraft Dispatcher Courses (United States)


    ... this chapter; C. 49 CFR part 830; D. General Operating Manual. II. Meteorology A. Basic Weather Studies... Processes. (c) Lifting Processes. (d) Divergence. (e) Convergence. (12) Turbulence: (a) Jetstream Associated... Pressurization. (5) Ice and Rain protection. (6) Avionics, Communication, and Navigation. (7) Powerplants...

  19. 77 FR 30053 - Repair Stations (United States)


    ... compounds and advanced polymers (which is fast becoming the standard in the industry). These types of... outdated by further technological advances. The FAA has determined that a better approach is to have the... its report, ARAC indicated that technological advances in avionics have led to much controversy...

  20. Computer Architecture. (Latest Citations from the Aerospace Database) (United States)


    The bibliography contains citations concerning research and development in the field of computer architecture. Design of computer systems, microcomputer components, and digital networks are among the topics discussed. Multimicroprocessor system performance, software development, and aerospace avionics applications are also included. (Contains 50-250 citations and includes a subject term index and title list.)

  1. The implementation of the Future Radio Management Panel


    Chbaly, Khaoula


    [CASTELLÀ] El proyecto consiste en la implementacion de Future Radio Management Panel (FRMP). Un nuevo componenente que utilizaran los pilotos en el futuro para manejar las comunicación entre los controladores en la tierra y los pilotos en al avion.

  2. 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

  3. 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.

  4. 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…

  5. 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...... star tracker integration with the cryogenic telescope structure....

  6. 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.

  7. 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.

  8. 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...

  9. 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...

  10. 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...

  11. 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...

  12. Safe and Secure Virtualization: Answers for IMA next Generation and Beyond (United States)

    Almeida, Jose; Vatrinet, Francis


    This paper presents some of the challenges the aerospace industry is facing for the future and explains why and how a safe and secured virtualization technology can help solving these challenges Efforts around the next generation of IMA have already started, like the European FP7 funded project SCARLETT or the IDEE5 project and many avionics players and working groupware focused on how the new technologies like SMP capabilities introduced in latest CPU architectures, can help increasing system performances in future avionics system. We present PikeOS, a separation micro-kernel, which applies the state-of-the-art techniques and widely recognized standards such as ARINC 653 and MILS in order to guarantee safety and security properties, and still improve overall performance.

  13. 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.

  14. 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:

  15. Simulation/Emulation Techniques: Compressing Schedules With Parallel (HW/SW) Development (United States)

    Mangieri, Mark L.; Hoang, June


    NASA has always been in the business of balancing new technologies and techniques to achieve human space travel objectives. NASA's Kedalion engineering analysis lab has been validating and using many contemporary avionics HW/SW development and integration techniques, which represent new paradigms to NASA's heritage culture. Kedalion has validated many of the Orion HW/SW engineering techniques borrowed from the adjacent commercial aircraft avionics solution space, inserting new techniques and skills into the Multi - Purpose Crew Vehicle (MPCV) Orion program. Using contemporary agile techniques, Commercial-off-the-shelf (COTS) products, early rapid prototyping, in-house expertise and tools, and extensive use of simulators and emulators, NASA has achieved cost effective paradigms that are currently serving the Orion program effectively. Elements of long lead custom hardware on the Orion program have necessitated early use of simulators and emulators in advance of deliverable hardware to achieve parallel design and development on a compressed schedule.

  16. 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.

  17. SAMOSA -ScAnner Micro-Onde pour la Sécurisation des Aéroports Airport Security Microwave Scanner


    Le Fur, Gwenn; Duchesne, Luc; Tessier, Virginie; Castelli, Juan-Carlos; Osmont, Antoine; Crevits, Igor; Rajaonah, Bako; Berger, Joss; Cabrol, Pierre; Braida, Vivien


    – Des événements récents ont montré qu'un terroriste déterminé était encore capable d'introduire à bord d'un avion de ligne des matières explosives pour tenter de le faire exploser en vol. Le risque d'attentat à l'explosif perpétré par un passager kamikaze dans la cabine d'un avion est bel et bien réel. Le projet SAMOSA s'inscrit dans ce contexte ; son objectif est de développer un système de détection basé sur des technologies d'imagerie Radiofréquence permettant la détection d'explosif emba...

  18. 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.

  19. 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.

  20. 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...

  1. AutoNav4D. A co-simulator for unmanned aircraft systems


    Tristancho Martínez, Joshua


    This TFC document shows the requirements and the components needed to integrate in the same scenario, real Unmanned Aircraft Systems (UAS) and simulated systems. This is called co-simulation. An UAS is a series of onboard avionics systems and an on ground platform, which might takeoff, fly a mission and land safe without a human intervention. UAS Service Abstraction Layer (USAL) is a set of available services running on top of the UAV system architecture to give support to most...

  2. 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 ...

  3. 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 ...

  4. 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...

  5. On Component Reliability and System Reliability for Space Missions (United States)

    Chen, Yuan; Gillespie, Amanda M.; Monaghan, Mark W.; Sampson, Michael J.; Hodson, Robert F.


    This paper is to address the basics, the limitations and the relationship between component reliability and system reliability through a study of flight computing architectures and related avionics components for NASA future missions. Component reliability analysis and system reliability analysis need to be evaluated at the same time, and the limitations of each analysis and the relationship between the two analyses need to be understood.

  6. Airport multipath simulation for siting DGPS reference stations


    Macabiau, Christophe; Roturier, Benoit; Chatre, Eric; Renard, Alain


    The siting of a GPS reference station on an airport is achieved by minimizing the influence of the environ-ment on the pseudorange measurements, while comply-ing with the practical operational installation constraints. The CNS Research Laboratory (URE-CNS) of the ENAC, in collaboration with the STNA and SEXTANT AVION-IQUE, has started a study that aims at providing siting guidelines for the French Civil Aviation Authority. As a result, a tool is developed, based on computed error predictions ...

  7. 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

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

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


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

  9. 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

  10. 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.

  11. Lessons Learnt from Gauging Software Metrics of Cabin Software in a Commercial Airliner


    Stefan Burger; Oliver Hummel


    In order to achieve high safety standards, avionic software needs to be developed with very high requirements regarding safety, reliability, and determinism as well as real-time constraints, which are often in conflict with the development of maintainable software systems. Nevertheless, the ability to change the software of an airplane is of increasing importance, since it consists of a multitude of partially hardware-specific subsystems which may need replacement during a plane’s lifespan of...

  12. 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.

  13. 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...

  14. 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.

  15. Early in-flight detection of SO2 via Differential Optical Absorption Spectroscopy: a feasible aviation safety measure to prevent potential encounters with volcanic plumes


    L. Vogel; B. Galle; Kern, C.; H. Delgado Granados; V. Conde; Norman, P.; Arellano, S; Landgren, O.; P. Lübcke; J. M. Alvarez Nieves; Cárdenas Gonzáles, L.; U. Platt


    Volcanic ash constitutes a risk to aviation, mainly due to its ability to cause jet engines to fail. Other risks include the possibility of abrasion of windshields and potentially serious damage to avionic systems. These hazards have been widely recognized since the early 1980s, when volcanic ash provoked several incidents of engine failure in commercial aircraft. In addition to volcanic ash, volcanic gases also pose a threat. Prolonged and/or cumulative exposure to sulphur ...

  16. Early in-flight detection of SO2 via Differential Optical Absorption Spectroscopy: a feasible aviation safety measure to prevent potential encounters with volcanic plumes


    J. M. Alvarez Nieves; Cárdenas Gonzáles, L.; P. Lübcke; Landgren, O.; Arellano, S; Norman, P.; V. Conde; H. Delgado Granados; Kern, C.; B. Galle; L. Vogel; U. Platt


    Volcanic ash constitutes a risk to aviation, mainly due to its ability to cause jet engines to fail. Other risks include the possibility of abrasion of windshields and potentially serious damage to avionic systems. These hazards have been widely recognized since the early 1980s, when volcanic ash provoked several incidents of engine failure in commercial aircraft. In addition to volcanic ash, volcanic gases also pose a threat. Prolonged and/or cumulative exposure to sulphur dioxide (SO2) or s...

  17. 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.

  18. 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 ...

  19. 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...

  20. Pegasus XL Development and L-1011 Pegasus Carrier Aircraft


    Mosier, Marty; Rutkowski, Ed


    The Pegasus air-launched space booster has established itself as America's standard small launch vehicle. Since its first flight on April 5, 1990 Pegasus has delivered 13 payloads to orbit in the four launches conducted to-date. To improve capability and operational flexibility, the Pegasus XL development program was initiated in late 1991. The Pegasus XL vehicle has increased propellant, improved avionics, and a number of design enhancements. To increase the Pegasus launch system's flexibili...

  1. 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...

  2. 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...

  3. 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...

  4. 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...

  5. Integrating a Modular Smart Tool into the Space Exploration Infrastructure through Small Satellite Systems Protocols


    Rodriguez, Gary; Slane, Frederick


    Technical capabilities developed in the Small Satellite community are being translated to other space applications. sysRAND Corporation is developing hardware and software tools for the Air Force Research Laboratory’s Satellite Data Model and Space Plug and Play Avionics. We are also developing an industrial-class excavator for planetary surface exploration and development. Applications include civil engineering at landing sites, and in-situ resource utilization in support of long-range logis...

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

    Hanson, Curt


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

  7. 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

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

    Cook, Stephen A.


    This video is designed to accompany the presentation of the paper delivered at the Joint Army, Navy, NASA, Airforce (JANNAF) Propulsion Meeting held in 2009. It shows various scenes: from the construction of the A-3 test stand, construction of portions of the vehicles, through various tests of the components of the Ares Launch Vehicles, including wind tunnel testing of the Ares V, shell buckling tests, and thermal tests of the avionics, to the construction of the TPS thermal spray booth.

  9. A Mechanized Semantic Framework for Real-Time Systems


    Garnacho, Manuel; Bodeveix, Jean-Paul; Filali, Mamoun


    Concurrent systems consist of many components which may execute in parallel and are complex to design, to analyze, to verify, and to implement. The complexity increases if the systems have real-time constraints, which are very useful in avionic, spatial and other kind of embedded applications. In this paper we present a logical framework for defining and validating real-time formalisms as well as reasoning methods over them. For this purpose, we have implemented in the Coq proof assistant wel...

  10. Polychronous Design of Embedded Real-Time Systems


    Gamatié, Abdoulaye; Gautier, Thierry; Le Guernic, Paul; Talpin, Jean-Pierre


    This report proposes a design methodology for embedded real-time systems using a synchronous multi-clocked framework, which provides a well-defined mathematical model that yields rigorous methodological support for the trusted design, validation and automatic code generation. The presented methodology addresses among others the non trivial issue of modeling asynchronous mechanism using the synchronous paradigm. Among target application domains, we mainly focus on the avionics area. A library ...

  11. Ciència i pseudociència : un curs obert miniop


    Canet Pladevall, Roser; Costa Vila, Marcel; Manuel, Jordi de,


    Les pseudociències estan proliferant extraordinàriament a través de les xarxes. Presentem un curs online (miniop) obert i autoformatiu per desenvolupar l'esperit crític a partir de la interacció entre els participants. Les activitats analitzen tres casos de creences pseudocientífiques: prediccions del futur, chemtrails (esteles químiques dels avions) i corrents antivacunació.

  12. 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.

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

    Directory of Open Access Journals (Sweden)

    Kohji Kamejima


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

  14. Space Shuttle Program Tin Whisker Mitigation (United States)

    Nishimi, Keith


    The discovery of tin whiskers (TW) on space shuttle hardware led to a program to investigate and removal and mitigation of the source of the tin whiskers. A Flight Control System (FCS) avionics box failed during vehicle testing, and was routed to the NASA Shuttle Logistics Depot for testing and disassembly. The internal inspection of the box revealed TW growth visible without magnification. The results of the Tiger Team that was assembled to investigate and develop recommendations are reviewed in this viewgraph presentation.

  15. 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.

  16. Improvements of GNSS/INS Localization's Integrity with Gaussian Mixture Filters in a Bayesian Framework


    Sendorek, Pierre; Abed-Meraim, Karim; Charbit, Maurice; legoll, sebastien


    Gaussian mixture filters model the evolution of the probability density function, inter alia, when the noise on the linear measurements is a gaussian mixture. Such a model is relevant when the measurements are subject to disturbances whose statistcs may vary abruptly, like the GNSS signals in avionics, which are subject to reflections, scintillation, multipath... The naturally resulting probability density of the hidden state given the observations up to the current time is also a Gaussian mixt...

  17. Fourier Transform Spectrometer Controller for Partitioned Architectures

    DEFF Research Database (Denmark)

    Tamas-Selicean, Domitian; Keymeulen, D.; Berisford, D.; Carlson, R.; Hand, K.; Pop, Paul; Wadsworth, W.; Levy, R.


    The current trend in spacecraft computing is to integrate applications of different criticality levels on the same platform using no separation. This approach increases the complexity of the development, verification and integration processes, with an impact on the whole system life cycle......, such as avionics and automotive. In this paper we investigate the challenges of developing and the benefits of integrating a scientific instrument, namely a Fourier Transform Spectrometer, in such a partitioned architecture....

  18. 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

  19. 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...

  20. 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 ...

  1. 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.

  2. 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...

  3. 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...

  4. 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) ...

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

    Directory of Open Access Journals (Sweden)

    Arnstein J. Borstad


    Full Text Available 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.

  6. 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...

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


    José Meseguer; Peter Csaba Ölveczky


    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 autonom...

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

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


    This document describes the communication architecture for the Power, Avionics and Software (PAS) 1.0 subsystem for the Advanced Extravehicular Mobility Unit (AEMU). The following systems are described in detail: Caution Warning and Control System, Informatics, Storage, Video, Audio, Communication, and Monitoring Test and Validation. This document also provides some background as well as the purpose and goals of the PAS subsystem being developed at Glenn Research Center (GRC).

  9. 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...

  10. 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

  11. C-130 Automated Digital Data System (CADDS) (United States)

    Scofield, C. P.; Nguyen, Chien


    Real time airborne data acquisition, archiving and distribution on the NASA/Ames Research Center (ARC) C-130 has been improved over the past three years due to the implementation of the C-130 Automated Digital Data System (CADDS). CADDS is a real time, multitasking, multiprocessing ROM-based system. CADDS acquires data from both avionics and environmental sensors inflight for all C-130 data lines. The system also displays the data on video monitors throughout the aircraft.

  12. 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...

  13. 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.

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

    Energy Technology Data Exchange (ETDEWEB)

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


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

  15. 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).

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

    International Nuclear Information System (INIS)

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


    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 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.

  18. Savremeno naoružanje i vojna oprema za br. 3-2015 / Modern weapons and military equipment for issue 3-2105 / Современное вооружение и военное оборудование за но. 3-2015

    Directory of Open Access Journals (Sweden)

    Mladen R. Tišma


    Full Text Available Rusija ponovo pokreće proizvodnju strategijskih bombardera Tu-160; Italijansko RV predstavilo novi avion za selektivnu i početnu obuku; Kina razvija STOVL borbeni avion pete generacije; Južnoafrički Denels razmatra ponovno pokretanje proizvodnje unapređenog borbenog helikoptera; Uspešan prvi let helikoptera S-97 „rejder“; Indija modernizuje i naoružava školske avione „houk mark 132“; Javno predstavljanje i prvi let transportnog aviona An-178; Indijskom ratnom vazduhoplovstvu predati prvi modernizovani „miraži 2000“; Predstavljena nova verzija izraelske vazduhoplovne rakete „derbi“; Razgovori o mogućnosti opremanja lakih lovaca FA-50 vođenim avio-bombama „al-tarik“; Sažem nudi naoružavanje francuskih transportnih aviona C-130 preciznim avio-bombama; Indija odabrala A330 za razvoj novog avaksa; Brazilska ratna mornarica preuzela prvi modernizovani lovac-bombarder AF-1; Rusija planira izgradnju novog nosača aviona. / Russia to relaunch production of Tu-160 strategic bombers; Italian Air Force presented a new aircraft for selective and initial training; China is developing fifth generationSTOVL fighter aircraft; South Africa’s Denels consider restarting production improved attack helicopters; Successful first flight of S-97 Raider helicopter; India to modernize and arm Hawk Mk 132 trainer aircraft; Public presentation and the first flight of An-178 transport aircraft; Indian Air Force handed over the first modernized Mirage 2000; Introduced a new version of the Israeli Air Force missiles i-Derby; Talks about the possibility of equipping FA-50 light fighters with Al-Tarik precision guided munition; Sagem offers the arming of French C-130 transport aircraft with precision guided bombs; India has selected the A330 to develop a new AWACS; The Brazilian navy took the first modernized AF-1 strike fighter; Russia plans to build a new aircraft carrier.

  19. Multi-physics modelling contributions to investigate the atmospheric cosmic rays on the single event upset sensitivity along the scaling trend of CMOS technologies

    International Nuclear Information System (INIS)

    Particles originating from primary cosmic radiation, which hit the Earth's atmosphere give rise to a complex field of secondary particles. These particles include neutrons, protons, muons, pions, etc. Since the 1980s it has been known that terrestrial cosmic rays can penetrate the natural shielding of buildings, equipment and circuit package and induce soft errors in integrated circuits. Recently, research has shown that commercial static random access memories are now so small and sufficiently sensitive that single event upsets (SEUs) may be induced from the electronic stopping of a proton. With continued advancements in process size, this downward trend in sensitivity is expected to continue. Then, muon soft errors have been predicted for nano-electronics. This paper describes the effects in the specific cases such as neutron-, proton- and muon-induced SEU observed in complementary metal-oxide semiconductor. The results will allow investigating the technology node sensitivity along the scaling trend. This paper proposes to model and investigate the atmospheric cosmic rays impact on the SER along the scaling trend. Neutron, proton and muon environments are considered for two operational altitudes, i.e. avionic and at sea level. A synthesis about the SEU/risk assessment applied to scaling CMOS trend for avionic and ground environments can be proposed due to these investigations. First results indicate that protons/neutrons must be taken into account for avionic environments while muons will be critical for terrestrial applications. Moreover, at a ground level SRAM but also flip flop and combinational logic based on nanometric technologies may become sensitive to the low-energy muon spectrum. Then, future terrestrial error rate predictions will require characterisation of the device LET threshold, consideration of the muon environment and advanced radiation transport computations. (authors)

  20. 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.

  1. 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.

  2. 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.

  3. Fiber-channel audio video standard for military and commercial aircraft product lines (United States)

    Keller, Jack E.


    Fibre channel is an emerging high-speed digital network technology that combines to make inroads into the avionics arena. The suitability of fibre channel for such applications is largely due to its flexibility in these key areas: Network topologies can be configured in point-to-point, arbitrated loop or switched fabric connections. The physical layer supports either copper or fiber optic implementations with a Bit Error Rate of less than 10-12. Multiple Classes of Service are available. Multiple Upper Level Protocols are supported. Multiple high speed data rates offer open ended growth paths providing speed negotiation within a single network. Current speeds supported by commercially available hardware are 1 and 2 Gbps providing effective data rates of 100 and 200 MBps respectively. Such networks lend themselves well to the transport of digital video and audio data. This paper summarizes an ANSI standard currently in the final approval cycle of the InterNational Committee for Information Technology Standardization (INCITS). This standard defines a flexible mechanism whereby digital video, audio and ancillary data are systematically packaged for transport over a fibre channel network. The basic mechanism, called a container, houses audio and video content functionally grouped as elements of the container called objects. Featured in this paper is a specific container mapping called Simple Parametric Digital Video (SPDV) developed particularly to address digital video in avionics systems. SPDV provides pixel-based video with associated ancillary data typically sourced by various sensors to be processed and/or distributed in the cockpit for presentation via high-resolution displays. Also highlighted in this paper is a streamlined Upper Level Protocol (ULP) called Frame Header Control Procedure (FHCP) targeted for avionics systems where the functionality of a more complex ULP is not required.

  4. 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

  5. Microwave de-/anti-icing using the midas-technology. (United States)

    Feher, L; Seitz, T; Nuss, V


    For aviation, a suitable alternative for currently used in-flight anti-/de-icing technologies for today's aircrafts with metal structures and future aircrafts with replaced composite structures is necessary. Intense investigations performed at FZK have been together in collaboration with aircraft manufacturers to design and develop a new avionic microwave technology for monolithic composite structures.The full system integration has been evaluated for several airplanes considering the structural and efficiency demands. The concept of this MIDAS (MIcrowave De-icing Anti-icing System) technology as well their recent results will be presented. A full system integration has been tested and is visualized in the paper. PMID:21384724

  6. 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 ...

  7. 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...

  8. 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

  9. 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.

  10. 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...

  11. 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.

  12. 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.

  13. 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...

  14. Space Shuttle crew compartment debris-contamination (United States)

    Goodman, Jerry R.; Villarreal, Leopoldo J.


    Remedial actions undertaken to reduce debris during manned flights and ground turnaround operations at Kennedy Space Center and Palmdale are addressed. They include redesign of selected ground support equipment and Orbiter hardware to reduce particularization/debris generation; development of new detachable filters for air-cooled avionics boxes; application of tape-on screens to filter debris; and implementation of new Orbiter maintenance and turnaround procedures to clean filters and the crew compartment. Most of these steps were implemented before the return-to-flight of STS-26 in September 1988 which resulted in improved crew compartment habitability and less potential for equipment malfunction.



    Carlos Giraldo E


    La tecnología del ultrasonido nace en 1880 con el desarrollo de los efectos piezoeléctricos. Luego fue aplicada en forma de SONAR (Sound Navigation and Ranging) durante la segunda guerra mundial para la detección de barcos, submarinos y aviones de guerra. La emisión de las ondas de ultrasonido se obtiene por medio de cristales que son sometidos a una corriente eléctrica logrando que vibren, la recepción de éstas ondas se logra cuando retornan de nuevo a los cristales al chocar con los ...

  16. Size, weight, and power in electronic payloads (United States)

    Haislet, Donald A.; Wilson, Larry

    A Tactical SIGINT System Hardware program developed by ESL, a subsidiary of TRW Avionics and Surveillance Group, is discussed. The program studied the parts of typical systems that have the greatest size, weight, and power leverage, namely, the chassis, circuit-card assemblies, thermal management techniques, and interconnections. Mechanical weight savings were achieved in both chassis and modules due to replacement of aluminum with metal matrix composites. Circuit miniaturization based on multichip modules made it possible to reduce a key digital circuit by 8:1.


    Directory of Open Access Journals (Sweden)

    Yuriy Hryshchenko


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

  18. High-repetition-rate closed-cycle rare gas electrical discharge laser

    International Nuclear Information System (INIS)

    The recently developed technology of high-pressure molecular lasers has been combined with ultrahigh-vacuum technology to develop a fast-flow high-pressure laser system capable of long-duration closed-cycle operation with rare gases. The system's economy, reliability, and capability for long-time operation at a high repetition rate make it suitable for avionics, space, and isotope separation applications. High-repetition-rate laser performance has been demonstrated in He--Xe, Ne--Xe, Ar--Xe, and Kr--Xe. Experimental results for high-pressure He--Xe mixtures are given

  19. Integrated Enhanced and Synthetic Vision System for Transport Aircraft

    Directory of Open Access Journals (Sweden)

    N. Shantha Kumar


    Full Text Available A new avionics concept called integrated enhanced and synthetic vision system (IESVS is being developed to enable flight operations during adverse weather/visibility conditions even in non precision airfields. This paper presents the latest trends in IESVS, design concept of the system and the work being carried out at National Aerospace Laboratories, Bangalore towards indigenous development of the same for transport aircraft.Defence Science Journal, 2013, 63(2, pp.157-163, DOI:

  20. 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...

  1. 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.

  2. Fiber-Based 205-mW (27% Efficiency) Power-Delivery System for an All-Fiber Network with Optoelectronic Sensor Units (United States)

    Peña, Rafael; Algora, Carlos; Matías, Ignacio R.; López-Amo, Manuel


    An optical fiber power-delivery system has been developed. An analysis of the spectral response of every component in the system has been carried out. Experimental measurements of the system are presented. We obtained 205 mW of power (5.4 V, 38.3 mA), yielding 27.4% efficiency. As an application, a sensor module is optically powered. This is an electrically isolated system, inasmuch as it also sends the measured data through a fiber. Several other applications are envisaged in the fields of aerospace, avionics, and domotics.

  3. 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...

  4. 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.

  5. Bioturbosina: Producción de cultivos energéticos para la aviación comercial Jet Biofuel: Production of energy-related crops for commercial aircraft


    Ibis Sepúlveda González


    Las más grandes compañías de fabricación de aviones, entre ellas Boeing y Airbus y la asociación internacional de líneas aéreas International Air Transport Association (IATA), decidieron jugar un doble papel: contribuir en la disminución de emisiones de gases efecto invernadero y asegurar la disponibilidad de combustible barato. Para ello se ha hecho un plan para agregar a la turbosina una fracción creciente de bioturbosina. En México esto se trabajó en el "plan de vuelo para los biocombustib...

  6. Terminal-area STOL operating systems experiments program (United States)

    Smith, D. W.; Watson, D.; Christensen, J. V.


    Information which will aid in the choice by the U.S. Government and industry of system concepts, design criteria, operating procedures for STOL aircraft and STOL ports, STOL landing guidance systems, air traffic control systems, and airborne avionics and flight control systems. Ames has developed a terminal-area STOL operating systems experiments program which is a part of the joint DOT/NASA effort is discussed. The Ames operating systems experiments program, its objectives, the program approach, the program schedule, typical experiments, the research facilities to be used, and the program status are described.

  7. Advanced Health Management of a Brushless Direct Current Motor/Controller (United States)

    Pickett, R. D.


    This effort demonstrates that health management can be taken to the component level for electromechanical systems. The same techniques can be applied to take any health management system to the component level, based on the practicality of the implementation for that particular system. This effort allows various logic schemes to be implemented for the identification and management of failures. By taking health management to the component level, integrated vehicle health management systems can be enhanced by protecting box-level avionics from being shut down in order to isolate a failed computer.

  8. Inter-computer communication architecture for a mixed redundancy distributed system (United States)

    Lala, Jaynarayan H.; Adams, Stuart J.


    The triply redundant intercomputer network for the Advanced Information Processing System (AIPS), an architecture developed to serve as the core avionics system for a broad range of aerospace vehicles, is discussed. The AIPS intercomputer network provides a high-speed, Byzantine-fault-resilient communication service between processing sites, even in the presence of arbitrary failures of simplex and duplex processing sites on the IC network. The IC network contention poll has evolved from the Laning Poll. An analysis of the failure modes and effects and a simulation of the AIPS contention poll, demonstrate the robustness of the system.

  9. 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 ...

  10. 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.

  11. Orbiter CIU/IUS communications hardware evaluation (United States)

    Huth, G. K.


    The DOD and NASA inertial upper stage communication system design, hardware specifications and interfaces were analyzed to determine their compatibility with the Orbiter payload communications equipment (Payload Interrogator, Payload Signal Processors, Communications Interface Unit, and the Orbiter operational communications equipment (the S-Band and Ku-band systems). Topics covered include (1) IUS/shuttle Orbiter communications interface definition; (2) Orbiter avionics equipment serving the IUS; (3) IUS communication equipment; (4) IUS/shuttle Orbiter RF links; (5) STDN/TDRS S-band related activities; and (6) communication interface unit/Orbiter interface issues. A test requirement plan overview is included.

  12. Reentry trajectories of a space glider, taking acceleration and heating constraints into account (United States)

    Strauss, Adi


    Three-dimensional trajectories for aerodynamically controlled reentry of an unpowered Space Shuttle-type vehicle from equatorial orbit are investigated analytically, summarizing the results obtained in the author's thesis (Strauss, 1987). Computer programs constructed on the basis of the governing equations of Chern and Yang (1982) and Chern and Vinh (1980) in modified dimensionless Chapman variables are used to optimize the roll angle and lift coefficient of the trajectories. Typical results are presented in graphs and maps and shown to be in good agreement with AVION SPATIAL predictions for the ESA Hermes spacecraft.

  13. 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

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

    Goodloe, Alwyn E.; Pike, Lee


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

  15. 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

  16. A performance evaluation of the software-implemented fault-tolerance computer (United States)

    Palumbo, D. L.; Butler, R. W.


    The results of a performance evaluation of the Software-Implemented Fault-Tolerance (SIFT) computer system conducted in the NASA Avionics Integration Research Laboratory are presented. The essential system functions are described and compared to both earlier design proposals and subsequent design improvements. Using SIFT's specimen task load, the executive tasks, such as reconfiguration, clock synchronization, and interactive consistency, are found to consume significant computing resources. Together with other system overhead (e.g., voting and scheduling), the operating system overhead is in excess of 60 percent. The authors propose specific design changes that reduce this overhead burden significantly.

  17. 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...

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

    International Nuclear Information System (INIS)

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

  19. Métodos estadísticos para la mejora del proceso de fabricación de un avión comercial


    Muñoz Sánchez, David


    El objetivo del presente proyecto es analizar mediante métodos estadísticos la defectología existente en la unión de componentes aeronáuticos y poder dar una solución que pueda paliar o mejorar el problema, el problema estudiado se encuentra en la cola del avión, concretamente en el estabilizador horizontal. Empezaremos con el Capítulo 2 adentrándonos en el fascinante mundo de la aviación, desde sus inicios hasta la era moderna con los grandes aviones de las compañías comerciales. Despu...

  20. 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.

  1. Possibilistic versus probabilistic trade-off for data association (United States)

    Bowman, Christopher L.


    This paper discusses probabilistic, possibilistic, and symbolic logic approaches to data association as part of the multi-sensor integration (MSI) problem. Alternative probabilistic scoring equations are given with specific trades between max a posterori and chi-square scoring. Dempster-Shafer and fuzzy set approaches to treat data with high uncertainty-in-the- uncertainty are compared. The role of symbolic rule-oriented approaches especially as part of a fusion analyst workstation (FAWS) expert system is discussed. Lastly, an avionics MSI design trade example is presented.

  2. 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

  3. IKOS: A Framework for Static Analysis based on Abstract Interpretation (Tool Paper) (United States)

    Brat, Guillaume P.; Laserna, Jorge A.; Shi, Nija; Venet, Arnaud Jean


    The RTCA standard (DO-178C) for developing avionic software and getting certification credits includes an extension (DO-333) that describes how developers can use static analysis in certification. In this paper, we give an overview of the IKOS static analysis framework that helps developing static analyses that are both precise and scalable. IKOS harnesses the power of Abstract Interpretation and makes it accessible to a larger class of static analysis developers by separating concerns such as code parsing, model development, abstract domain management, results management, and analysis strategy. The benefits of the approach is demonstrated by a buffer overflow analysis applied to flight control systems.

  4. Desactivar la guerra: alternativas audaces para consolidar la paz


    González Celis, Paulo Alberto


    “Los bombardearemos hasta devolverlos a la Edad de Piedra". Así, el general de las fuerzas de aire de los Estados Unidos explico la feroz ofensiva que realizaron sus aviones militares en Vietnam, territorio sobre el que lanzaron cerca de ocho millones de bombas, cuatro veces el total de las utilizadas en la Segunda Guerra Mundial. Sin embargo, los dramas humanos sucedidos en tiempos de guerra no cesan con la finalización de las hostilidades, y las sociedades inmersas en procesos y tr...

  5. 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.

  6. 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.

  7. ODICIS (One Display for a Cockpit Interactive Solution) - Final public progress report

    DEFF Research Database (Denmark)

    Bécouarn, Loïc; Dominici, Johanna; Bader, Joachim;

    the operational safety and efficiency while reducing the aircraft development cost. The first objective is to prove the technical feasibility of an avionics large seamless display, which can possibly be curved. This involves optical but also graphic generation challenges. The design of the display must take...... the idea of a single display cockpit, will be reviewed, deepened and tested on the mock-up. Human factors evaluations will seek to ascertain the safety and efficiency gains produced by this novel cockpit concept based on use of a single display....

  8. Diseño y construcción de un avión no tripulado basado en sistemas y dispositivos COTS


    Riquelme Bernal, Mateo


    Como se ha indicado anteriormente, el objetivo del presente proyecto es la creación de un prototipo de avión no tripulado para usos múltiples, utilizando dispositivos de uso comercial o COTS. Para ello se parte de una serie de requisitos fundamentales: -Despegue mediante lanzamiento manual. -Autonomía: 30 minutos aproximadamente. -Carga de pago: Al menos 500 g. Y cuatro fases principales: I. Estudio del estado del arte en el diseño de aviones de aeromodelismo y su aplicación directa a la i...

  9. 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.

  10. 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.

  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. 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.

  13. 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.

  14. 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.

  15. 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...

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

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


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

  17. 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.

  18. 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!

  19. 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...

  20. Generación de mapas temáticos a partir del procesamiento de imágenes satelitales


    Wainschenker, Rubén; Tristán, Paula; Doorn, Jorge Horacio; Ciccimarra, G.


    Las imágenes satelitales son generadas a partir de la teledetección satelital. El término teledetección fue adoptado en los países de habla hispana como traducción del inglés remote sensing, utilizándose para describir las observaciones de un objeto efectuadas sin mediar contacto físico con él. [Pinilla95]. La teledetección espacial se define como aquella técnica que permite adquirir imágenes de la superficie terrestre desde sensores instalados en diferentes plataformas espaciales (aviones...

  1. 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

  2. Use of GNSS signals and their augmentations for Civil Aviation navigation during Approaches with Vertical Guidance and Precision Approaches


    Néri, Pierre


    La navigation par satellite, Global Navigation Satellite System, a été reconnue comme une solution prometteuse afin de fournir des services de navigation aux utilisateurs de l'Aviation Civile. Ces dernières années, le GNSS est devenu l'un des moyens de navigation de référence, son principal avantage étant sa couverture mondiale. Cette tendance globale est visible à bord des avions civils puisqu'une majorité d'entre eux est désormais équipée de récepteurs GNSS. Cependant, les exigences de l'Av...

  3. 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...

  4. Study of compatibilization methods for high density polyethylene and ground tyre rubber : exploring new route to recycle scrap tyres


    Casas Carné, María del Pilar


    Cotxes, camions, tractors, avions... tots necessiten els neumàtics com a component imprescindible per al seu funcionament. Malauradament, degut al desgast per ús, els neumàtics tenen una vida útil limitada que obliga a renovar-los cada cert temps passant a ser Neumàtics Fora d'Ús (NFU). Paradògicament, els neumàtics són formulats per a suportar condicions extremes d'ús i, entre d'altres matèries primeres contenen cautxú vulcanitzat, una elevada quantitat d'estabilitzants i d'altres additius ...

  5. 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

  6. 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.

  7. 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.

  8. Comparison of Extensive Thermal Cycling Effects on Microstructure Development in Micro-alloyed Sn-Ag-Cu Solder Joints

    Energy Technology Data Exchange (ETDEWEB)

    Anderson, Iver E.; Boesenberg, Adam; Harringa, Joel; Riegner, David; Steinmetz, Andrew; Hillman, David


    Pb-free solder alloys based on the Sn-Ag-Cu (SAC) ternary eutectic have promise for widespread adoption across assembly conditions and operating environments, but enhanced microstructural control is needed. Micro-alloying with elements such as Zn was demonstrated for promoting a preferred solidification path and joint microstructure earlier in simple (Cu/Cu) solder joints studies for different cooling rates. This beneficial behavior now has been verified in reworked ball grid array (BGA) joints, using dissimilar SAC305 (Sn-3.0Ag-0.5Cu, wt.%) solder paste. After industrial assembly, BGA components joined with Sn-3.5Ag-0.74Cu-0.21Zn solder were tested in thermal cycling (-55 C/+125 C) along with baseline SAC305 BGA joints beyond 3000 cycles with continuous failure monitoring. Weibull analysis of the results demonstrated that BGA components joined with SAC + Zn/SAC305 have less joint integrity than SAC305 joints, but their lifetime is sufficient for severe applications in consumer, defense, and avionics electronic product field environments. Failure analysis of the BGA joints revealed that cracking did not deviate from the typical top area (BGA component side) of each joint, in spite of different Ag3Sn blade content. Thus, SAC + Zn solder has not shown any advantage over SAC305 solder in these thermal cycling trials, but other characteristics of SAC + Zn solder may make it more attractive for use across the full range of harsh conditions of avionics or defense applications.

  9. 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.

  10. 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:

  11. 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.

  12. 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...

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

    Biskri, Djallel Eddine

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

  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. 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.

  16. 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

  17. 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

  18. 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

  19. 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

  20. Intelligent radar data processing (United States)

    Holzbaur, Ulrich D.

    The application of artificial intelligence principles to the processing of radar signals is considered theoretically. The main capabilities required are learning and adaptation in a changing environment, processing and modeling information (especially dynamics and uncertainty), and decision-making based on all available information (taking its reliability into account). For the application to combat-aircraft radar systems, the tasks include the combination of data from different types of sensors, reacting to electronic counter-countermeasures, evaluation of how much data should be acquired (energy and radiation management), control of the radar, tracking, and identification. Also discussed are related uses such as monitoring the avionics systems, supporting pilot decisions with respect to the radar system, and general applications in radar-system R&D.