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Sample records for 23rd digital avionics

  1. Digital Avionics

    NASA Technical Reports Server (NTRS)

    Koelbl, Terry G.; Ponchak, Denise; Lamarche, Teresa

    2003-01-01

    Digital Avionics activities played an important role in the advancements made in civil aviation, military systems, and space applications. This document profiles advances made in each of these areas by the aerospace industry, NASA centers, and the U.S. military. Emerging communication technologies covered in this document include Internet connectivity onboard aircraft, wireless broadband communication for aircraft, and a mobile router for aircraft to communicate in multiple communication networks over the course of a flight. Military technologies covered in this document include avionics for unmanned combat air vehicles and microsatellites, and head-up displays. Other technologies covered in this document include an electronic flight bag for the Boeing 777, and surveillance systems for managing airport operations.

  2. Digital Avionics

    NASA Technical Reports Server (NTRS)

    Koelbl, Terry G.; Ponchak, Denise; Lamarche, Teresa

    2002-01-01

    The field of digital avionics experienced another year of important advances in civil aviation, military systems, and space applications. As a result of the events of 9/11/2001, NASA has pursued activities to apply its aerospace technologies toward improved aviation security. Both NASA Glenn Research Center and Langley Research Center have performed flight research demonstrations using advanced datalink concepts to transmit live pictures from inside a jetliner, and to downlink the contents of the plane's 'black box' recorder in real time. The U.S. Navy and General Electric demonstrated survivable engine control (SEC) algorithms during engine ground tests at the Weapons Survivability Laboratory at China Lake. The scientists at Boeing Satellite Systems advanced the field of stellar inertial technology with the development of a new method for positioning optical star trackers on satellites.

  3. Digital avionics: A cornerstone of aviation

    NASA Technical Reports Server (NTRS)

    Spitzer, Cary R.

    1990-01-01

    Digital avionics is continually expanding its role in communication (HF and VHF, satellite, data links), navigation (ground-based systems, inertial and satellite-based systems), and flight-by-wire control. Examples of electronic flight control system architecture, pitch, roll, and yaw control are presented. Modeling of complex hardware systems, electromagnetic interference, and software are discussed.

  4. Digital avionics design and reliability analyzer

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The description and specifications for a digital avionics design and reliability analyzer are given. Its basic function is to provide for the simulation and emulation of the various fault-tolerant digital avionic computer designs that are developed. It has been established that hardware emulation at the gate-level will be utilized. The primary benefit of emulation to reliability analysis is the fact that it provides the capability to model a system at a very detailed level. Emulation allows the direct insertion of faults into the system, rather than waiting for actual hardware failures to occur. This allows for controlled and accelerated testing of system reaction to hardware failures. There is a trade study which leads to the decision to specify a two-machine system, including an emulation computer connected to a general-purpose computer. There is also an evaluation of potential computers to serve as the emulation computer.

  5. Rotorcraft digital advanced avionics system (RODAAS) functional description

    NASA Technical Reports Server (NTRS)

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

    1985-01-01

    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.

  6. HH-65A Dolphin digital integrated avionics

    NASA Technical Reports Server (NTRS)

    Huntoon, R. B.

    1984-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Spitzer, Cary R.

    1993-01-01

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

  8. Digital Avionics Information System (DAIS): Training Requirements Analysis Model (TRAMOD).

    ERIC Educational Resources Information Center

    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…

  9. Ultra-Reliable Digital Avionics (URDA) processor

    NASA Astrophysics Data System (ADS)

    Branstetter, Reagan; Ruszczyk, William; Miville, Frank

    1994-10-01

    Texas Instruments Incorporated (TI) developed the URDA processor design under contract with the U.S. Air Force Wright Laboratory and the U.S. Army Night Vision and Electro-Sensors Directorate. TI's approach couples advanced packaging solutions with advanced integrated circuit (IC) technology to provide a high-performance (200 MIPS/800 MFLOPS) modular avionics processor module for a wide range of avionics applications. TI's processor design integrates two Ada-programmable, URDA basic processor modules (BPM's) with a JIAWG-compatible PiBus and TMBus on a single F-22 common integrated processor-compatible form-factor SEM-E avionics card. A separate, high-speed (25-MWord/second 32-bit word) input/output bus is provided for sensor data. Each BPM provides a peak throughput of 100 MIPS scalar concurrent with 400-MFLOPS vector processing in a removable multichip module (MCM) mounted to a liquid-flowthrough (LFT) core and interfacing to a processor interface module printed wiring board (PWB). Commercial RISC technology coupled with TI's advanced bipolar complementary metal oxide semiconductor (BiCMOS) application specific integrated circuit (ASIC) and silicon-on-silicon packaging technologies are used to achieve the high performance in a miniaturized package. A Mips R4000-family reduced instruction set computer (RISC) processor and a TI 100-MHz BiCMOS vector coprocessor (VCP) ASIC provide, respectively, the 100 MIPS of a scalar processor throughput and 400 MFLOPS of vector processing throughput for each BPM. The TI Aladdim ASIC chipset was developed on the TI Aladdin Program under contract with the U.S. Army Communications and Electronics Command and was sponsored by the Advanced Research Projects Agency with technical direction from the U.S. Army Night Vision and Electro-Sensors Directorate.

  10. Rotorcraft Digital Advanced Avionics System (rodaas)

    NASA Technical Reports Server (NTRS)

    Taira, B.

    1985-01-01

    A simulator is being built to determine the practicality of using an advanced avionics system in a helicopter. Features include an autopilot; a navigation and flight planning component; an advisory system built into the computer; conventional gages and displays; a clock function; a fuel totalizer; a weight and balance computator; a performance evaluator; and emergency and normal checklists. The translation of a computer program written in PASCAL into a form that can be read by the graphics package for the simulator and basic electronic work in simulator construction are discussed.

  11. IEEE/AIAA/NASA Digital Avionics Systems Conference, 9th, Virginia Beach, VA, Oct. 15-18, 1990, Proceedings

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The present conference on digital avionics discusses vehicle-management systems, spacecraft avionics, special vehicle avionics, communication/navigation/identification systems, software qualification and quality assurance, launch-vehicle avionics, Ada applications, sensor and signal processing, general aviation avionics, automated software development, design-for-testability techniques, and avionics-software engineering. Also discussed are optical technology and systems, modular avionics, fault-tolerant avionics, commercial avionics, space systems, data buses, crew-station technology, embedded processors and operating systems, AI and expert systems, data links, and pilot/vehicle interfaces.

  12. Using Modern Design Tools for Digital Avionics Development

    NASA Technical Reports Server (NTRS)

    Hyde, David W.; Lakin, David R., II; Asquith, Thomas E.

    2000-01-01

    Using Modem Design Tools for Digital Avionics Development Shrinking development time and increased complexity of new avionics forces the designer to use modem tools and methods during hardware development. Engineers at the Marshall Space Flight Center have successfully upgraded their design flow and used it to develop a Mongoose V based radiation tolerant processor board for the International Space Station's Water Recovery System. The design flow, based on hardware description languages, simulation, synthesis, hardware models, and full functional software model libraries, allowed designers to fully simulate the processor board from reset, through initialization before any boards were built. The fidelity of a digital simulation is limited to the accuracy of the models used and how realistically the designer drives the circuit's inputs during simulation. By using the actual silicon during simulation, device modeling errors are reduced. Numerous design flaws were discovered early in the design phase when they could be easily fixed. The use of hardware models and actual MIPS software loaded into full functional memory models also provided checkout of the software development environment. This paper will describe the design flow used to develop the processor board and give examples of errors that were found using the tools. An overview of the processor board firmware will also be covered.

  13. Measurement of fault latency in a digital avionic miniprocessor

    NASA Technical Reports Server (NTRS)

    Mcgough, J. G.; Swern, F. L.

    1981-01-01

    The results of fault injection experiments utilizing a gate-level emulation of the central processor unit of the Bendix BDX-930 digital computer are presented. The failure detection coverage of comparison-monitoring and a typical avionics CPU self-test program was determined. The specific tasks and experiments included: (1) inject randomly selected gate-level and pin-level faults and emulate six software programs using comparison-monitoring to detect the faults; (2) based upon the derived empirical data develop and validate a model of fault latency that will forecast a software program's detecting ability; (3) given a typical avionics self-test program, inject randomly selected faults at both the gate-level and pin-level and determine the proportion of faults detected; (4) determine why faults were undetected; (5) recommend how the emulation can be extended to multiprocessor systems such as SIFT; and (6) determine the proportion of faults detected by a uniprocessor BIT (built-in-test) irrespective of self-test.

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

    ERIC Educational Resources Information Center

    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…

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

    ERIC Educational Resources Information Center

    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…

  16. Digital Avionics Information System (DAIS): Reliability and Maintainability Model. Final Report.

    ERIC Educational Resources Information Center

    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…

  17. Advanced optical network architecture for integrated digital avionics

    NASA Astrophysics Data System (ADS)

    Morgan, D. Reed

    1996-12-01

    For the first time in the history of avionics, the network designer now has a choice in selecting the media that interconnects the sources and sinks of digital data on aircraft. Electrical designs are already giving way to photonics in application areas where the data rate times distance product is large or where special design requirements such as low weight or EMI considerations are critical. Future digital avionic architectures will increasingly favor the use of photonic interconnects as network data rates of one gigabit/second and higher are needed to support real-time operation of high-speed integrated digital processing. As the cost of optical network building blocks is reduced and as temperature-rugged laser sources are matured, metal interconnects will be forced to retreat to applications spanning shorter and shorter distances. Although the trend is already underway, the widespread use of digital optics will first occur at the system level, where gigabit/second, real-time interconnects between sensors, processors, mass memories and displays separated by a least of few meters will be required. The application of photonic interconnects for inter-printed wiring board signalling across the backplane will eventually find application for gigabit/second applications since signal degradation over copper traces occurs before one gigabit/second and 0.5 meters are reached. For the foreseeable future however, metal interconnects will continue to be used to interconnect devices on printed wiring boards since 5 gigabit/second signals can be sent over metal up to around 15 centimeters. Current-day applications of optical interconnects at the system level are described and a projection of how advanced optical interconnect technology will be driven by the use of high speed integrated digital processing on future aircraft is presented. The recommended advanced network for application in the 2010 time frame is a fiber-based system with a signalling speed of around 2

  18. Digital map databases in support of avionic display systems

    NASA Astrophysics Data System (ADS)

    Trenchard, Michael E.; Lohrenz, Maura C.; Rosche, Henry, III; Wischow, Perry B.

    1991-08-01

    The emergence of computerized mission planning systems (MPS) and airborne digital moving map systems (DMS) has necessitated the development of a global database of raster aeronautical chart data specifically designed for input to these systems. The Naval Oceanographic and Atmospheric Research Laboratory''s (NOARL) Map Data Formatting Facility (MDFF) is presently dedicated to supporting these avionic display systems with the development of the Compressed Aeronautical Chart (CAC) database on Compact Disk Read Only Memory (CDROM) optical discs. The MDFF is also developing a series of aircraft-specific Write-Once Read Many (WORM) optical discs. NOARL has initiated a comprehensive research program aimed at improving the pilots'' moving map displays current research efforts include the development of an alternate image compression technique and generation of a standard set of color palettes. The CAC database will provide digital aeronautical chart data in six different scales. CAC is derived from the Defense Mapping Agency''s (DMA) Equal Arc-second (ARC) Digitized Raster Graphics (ADRG) a series of scanned aeronautical charts. NOARL processes ADRG to tailor the chart image resolution to that of the DMS display while reducing storage requirements through image compression techniques. CAC is being distributed by DMA as a library of CDROMs.

  19. Integrated performance and reliability specification for digital avionics systems

    NASA Technical Reports Server (NTRS)

    Brehm, Eric W.; Goettge, Robert T.

    1995-01-01

    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.

  20. A flight test evaluation of the pilot interface with a digital advanced avionics system

    NASA Technical Reports Server (NTRS)

    Hinton, D. A.

    1984-01-01

    A flight study was conducted to study pilot workload and the pilot interface with high levels of avionics capability and automation. The study was done in the context of general aviation, single-pilot IFR operations and utilized an experimental, digital, integrated avionics system. Results indicate that such advanced systems can provide improved information to the pilot and increased functional capability. The results also indicate that additional research is needed to increase the knowledge base required to design the pilot interfaces with highly capable systems. A CRT-based moving map display format tested provided excellent navigational situational awareness but was inferior to an HSI for manual path tracking. The complexity of navigation data management, autopilot management, and maintaining awareness of system status contributed to pilot workload and errors. Suggested guidelines for the design of the pilot/avionics interface for advanced avionics systems are given.

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

    NASA Technical Reports Server (NTRS)

    Larsen, William E.; Carro, Anthony

    1986-01-01

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

  2. Digital avionics susceptibility to high energy radio frequency fields

    NASA Astrophysics Data System (ADS)

    Larsen, William E.

    Generally, noncritical avionic systems for transport category aircraft have been designed to meet radio frequency (RF) susceptibility requirements set forth in RTCA DO 160B, environmental conditions and test procedures for airborne equipment. Section 20 of this document controls the electromagnetic interference (EMI) hardening for avionics equipment to levels of 1 and 2 V/m. Currently, US equipment manufacturers are designing flight-critical fly-by-wire avionics to a much higher level. The US Federal Aviation Administration (FAA) has requested that the RTCA SC-135 high-energy radio frequency (HERF) working group develop appropriate testing procedures for section 20 of RTCA DO 160B for radiated and conducted susceptibility at the box and systems level. The FAA has also requested the SAE AE4R committee to address installed systems testing, airframe shielding effects and RF environment monitoring. Emitters of interest include radar (ground, ship, and aircraft) commercial broadcast and TV station, mobile communication, and other transmitters that could possibly affect commercial aircraft.

  3. Digital avionics susceptibility to high energy radio frequency fields

    NASA Technical Reports Server (NTRS)

    Larsen, William E.

    1988-01-01

    Generally, noncritical avionic systems for transport category aircraft have been designed to meet radio frequency (RF) susceptibility requirements set forth in RTCA DO 160B, environmental conditions and test procedures for airborne equipment. Section 20 of this document controls the electromagnetic interference (EMI) hardening for avionics equipment to levels of 1 and 2 V/m. Currently, US equipment manufacturers are designing flight-critical fly-by-wire avionics to a much higher level. The US Federal Aviation Administration (FAA) has requested that the RTCA SC-135 high-energy radio frequency (HERF) working group develop appropriate testing procedures for section 20 of RTCA DO 160B for radiated and conducted susceptibility at the box and systems level. The FAA has also requested the SAE AE4R committee to address installed systems testing, airframe shielding effects and RF environment monitoring. Emitters of interest include radar (ground, ship, and aircraft) commercial broadcast and TV station, mobile communication, and other transmitters that could possibly affect commercial aircraft.

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

    ERIC Educational Resources Information Center

    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…

  5. 23rd steam-station cost survey

    SciTech Connect

    Friedlander, G.D.; Going, M.C.

    1983-11-01

    The results of the 23rd Steam Station Cost Survey covering the year 1982 are summarized. The major categories of the survey are as follows: general data; output data, 1982; fuel consumption, 1982; operation 1982 (mills/net kWh); investment ($/net kWh); energy cost, 1982 (mills/net kWh); and station performance, 1982. Thirty-one fossil-fuel steam plants and four nuclear stations were included in the survey. Fuel and operating cost increases are felt to be responsible for the moderate rise in total busbar-enery costs. 11 figures, 1 table.

  6. Error propagation in a digital avionic mini processor. M.S. Thesis

    NASA Technical Reports Server (NTRS)

    Lomelino, Dale L.

    1987-01-01

    A methodology is introduced and demonstrated for the study of error propagation from the gate to the chip level. The importance of understanding error propagation derives from its close tie with system activity. In this system the target system is BDX-930, a digital avionic multiprocessor. The simulator used was developed at NASA-Langley, and is a gate level, event-driven, unit delay, software logic simulator. An approach is highly structured and easily adapted to other systems. The analysis shows the nature and extent of the dependency of error propagation on microinstruction type, assembly level instruction, and fault-free gate activity.

  7. Software reliability - Measures and effects in flight critical digital avionics systems

    NASA Technical Reports Server (NTRS)

    Dunn, William R.

    1986-01-01

    The paper discusses software reliability as it applies particularly to design and evaluation of flight-critical digital avionics systems. Measures of software reliability, measurement methods and reliability (macro-) models are discussed. Recent work assessing their accuracy in predicting software errors in 'fly-by-wire' Newtonian applications is presented. Additional, detailed topics are discussed including software error distributions (e.g. catastrophic vs. noncatastrophic) and the effects of system growth/maturity on reliability improvement. In practical flight-critical digital applications, software reliability improvement is sought through use of parallel, redundant software (i.e. N-version programming) or backup software that can be invoked in the event of (primary) software failure. Achievable reliability levels are however highly sensitive to common-mode specification and programming errors. Recent data correlating these errors with net software reliability are discussed.

  8. Applying emerging digital video interface standards to airborne avionics sensor and digital map integrations: benefits outweigh the initial costs

    NASA Astrophysics Data System (ADS)

    Kuehl, C. Stephen

    1996-06-01

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

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

    ERIC Educational Resources Information Center

    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,…

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

    ERIC Educational Resources Information Center

    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…

  11. Avionics systems integration technology

    NASA Technical Reports Server (NTRS)

    Stech, George; Williams, James R.

    1988-01-01

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

  12. EDITORIAL The 23rd Nordic Semiconductor Meeting The 23rd Nordic Semiconductor Meeting

    NASA Astrophysics Data System (ADS)

    Ólafsson, Sveinn; Sveinbjörnsson, Einar

    2010-12-01

    A Nordic Semiconductor Meeting is held every other year with the venue rotating amongst the Nordic countries of Denmark, Finland, Iceland, Norway and Sweden. The focus of these meetings remains 'original research and science being carried out on semiconductor materials, devices and systems'. Reports on industrial activity have usually featured. The topics have ranged from fundamental research on point defects in a semiconductor to system architecture of semiconductor electronic devices. Proceedings from these events are regularly published as a topical issue of Physica Scripta. All of the papers in this topical issue have undergone critical peer review and we wish to thank the reviewers and the authors for their cooperation, which has been instrumental in meeting the high scientific standards and quality of the series. This meeting of the 23rd Nordic Semiconductor community, NSM 2009, was held at Háskólatorg at the campus of the University of Iceland, Reykjavik, Iceland, 14-17 June 2009. Support was provided by the University of Iceland. Almost 50 participants presented a broad range of topics covering semiconductor materials and devices as well as related material science interests. The conference provided a forum for Nordic and international scientists to present and discuss new results and ideas concerning the fundamentals and applications of semiconductor materials. The meeting aim was to advance the progress of Nordic science and thus aid in future worldwide technological advances concerning technology, education, energy and the environment. Topics Theory and fundamental physics of semiconductors Emerging semiconductor technologies (for example III-V integration on Si, novel Si devices, graphene) Energy and semiconductors Optical phenomena and optical devices MEMS and sensors Program 14 June Registration 13:00-17:00 15 June Meeting program 09:30-17:00 and Poster Session I 16 June Meeting program 09:30-17:00 and Poster Session II 17 June Excursion and dinner

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

    NASA Technical Reports Server (NTRS)

    Osoer, S. S.

    1976-01-01

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

  14. New capabilities for older aircraft: A study of pilot integration of retro-fit digital avionics to analog-instrumented flight decks

    NASA Astrophysics Data System (ADS)

    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.

  15. The role of standards in lower-cost digital spacecraft avionics

    NASA Technical Reports Server (NTRS)

    Caldwell, Douglas W.

    1995-01-01

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

  16. Space shuttle avionics system

    NASA Technical Reports Server (NTRS)

    Hanaway, John F.; Moorehead, Robert W.

    1989-01-01

    The Space Shuttle avionics system, which was conceived in the early 1970's and became operational in the 1980's represents a significant advancement of avionics system technology in the areas of systems and redundacy management, digital data base technology, flight software, flight control integration, digital fly-by-wire technology, crew display interface, and operational concepts. The origins and the evolution of the system are traced; the requirements, the constraints, and other factors which led to the final configuration are outlined; and the functional operation of the system is described. An overall system block diagram is included.

  17. A Search for 23rd Magnitude Kuiper Belt Comets

    NASA Technical Reports Server (NTRS)

    Luu, Jane

    1997-01-01

    The goal of the project was to identify a statistically significant sample of large (200 km-sized) Kuiper Belt Objects (KBOs), by covering 10 sq. degrees of the sky to a red limiting magnitude m(sub R) = 23. This work differs from, but builds on, previous surveys of the outer solar system in that it will cover a large area to a limiting magnitude that is deep enough to guarantee positive results. The proposed work should provide us with a significant number of 200 km-size KBOs (approx. 20 are expected) for subsequent studies. Such a sample is crucial if we are to investigate the statistical properties of the Belt and its members. It was modified the original research strategy to accommodate unanticipated problems such as the urgent need for follow-up observations,the original goal was still reached: we have substantially increased the number of Kuiper Belt Objects brighter than 23rd mag.

  18. Low cost HIRF troubleshooting and verification method for digital avionics systems

    NASA Astrophysics Data System (ADS)

    Kendall, Chris; Slattery, K. P.

    In the second phase of DO-160C, Section 20 HIRF type testing, the EUT (equipment under test) is subjected to RF fields in the range 30 MHz-(1.215 or 18 GHz), by radiating the EUT with antenna generated fields. Design engineers are concerned about the high cost of testing to 200(+) V/m. An alternate approach, using 10-15-W amplifiers, a signal generator, and a hand held probe is presented. The total cost of the system is less than $15,000 and yields 90 percent confidence in complying with the DO-160. Alternatively, the equipment can easily be used to pinpoint problems on aircraft. The near-field measurement technique can identify both case and cable penetrations quickly in the 1-100-MHz range. The method has been successfully used for over five years on military aircraft avionic systems.

  19. EDITORIAL: 23rd International Laser Physics Workshop (LPHYS'14)

    NASA Astrophysics Data System (ADS)

    2015-03-01

    Dear Readers, The 23rd annual International Laser Physics Workshop, LPHYS'14, took place in the City of Sofia, Bulgaria. 361 participants from 35 countries attended the conference. It was hosted by the Institute of Electronics at the Bulgarian Academy of Sciences. This year's Workshop was dedicated to paying tribute to two major events: • 50th anniversary of 1964 Nobel Prize in physics, • 145th anniversary of the establishment of the Bulgarian Academy of Sciences. LPHYS'14 has been taken under the High Patronage of Rosen Plevneliev, President of the Republic of Bulgaria. The LPHYS'14 Steering Committee and the Advisory & Program Committee would like to extend their sincere gratitude to Professor Sanka Gateva (Co-Chair) and Professor Ekaterina Borisova (Head of the Local Organizing Committee) and to their team for the outstanding job performed in organizing, arranging, managing and putting in order the conference. Their combined efforts lead to a successful result. In this volume of Journal of Physics: Conference Series you will find selected proceedings of the Workshop in Sofia. Please make a note that the 24th annual International Laser Physics Workshop (LPHYS'15) will take place from August 21 to August 25, 2015 in the city of Shanghai, China hosted by Shanghai Institute of Optics and Fine Mechanics at the Chinese Academy of Sciences. With kind regards, Steering and Advisory & Program committees LPHYS'14

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

    NASA Technical Reports Server (NTRS)

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

    1989-01-01

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

  1. Thermospheric density model biases at the 23rd sunspot maximum

    NASA Astrophysics Data System (ADS)

    Pardini, C.; Moe, K.; Anselmo, L.

    2012-07-01

    Uncertainties in the neutral density estimation are the major source of aerodynamic drag errors and one of the main limiting factors in the accuracy of the orbit prediction and determination process at low altitudes. Massive efforts have been made over the years to constantly improve the existing operational density models, or to create even more precise and sophisticated tools. Special attention has also been paid to research more appropriate solar and geomagnetic indices. However, the operational models still suffer from weakness. Even if a number of studies have been carried out in the last few years to define the performance improvements, further critical assessments are necessary to evaluate and compare the models at different altitudes and solar activity conditions. Taking advantage of the results of a previous study, an investigation of thermospheric density model biases during the last sunspot maximum (October 1999 - December 2002) was carried out by analyzing the semi-major axis decay of four satellites: Cosmos 2265, Cosmos 2332, SNOE and Clementine. Six thermospheric density models, widely used in spacecraft operations, were analyzed: JR-71, MSISE-90, NRLMSISE-00, GOST-2004, JB2006 and JB2008. During the time span considered, for each satellite and atmospheric density model, a fitted drag coefficient was solved for and then compared with the calculated physical drag coefficient. It was therefore possible to derive the average density biases of the thermospheric models during the maximum of the 23rd solar cycle. Below 500 km, all the models overestimated the average atmospheric density by amounts varying between +7% and +20%. This was an inevitable consequence of constructing thermospheric models from density data obtained by assuming a fixed drag coefficient, independent of altitude. Because the uncertainty affecting the drag coefficient measurements was about 3% at both 200 km and 480 km of altitude, the calculated air density biases below 500 km were

  2. Measurement of fault latency in a digital avionic mini processor, part 2

    NASA Technical Reports Server (NTRS)

    Mcgough, J.; Swern, F.

    1983-01-01

    The results of fault injection experiments utilizing a gate-level emulation of the central processor unit of the Bendix BDX-930 digital computer are described. Several earlier programs were reprogrammed, expanding the instruction set to capitalize on the full power of the BDX-930 computer. As a final demonstration of fault coverage an extensive, 3-axis, high performance flght control computation was added. The stages in the development of a CPU self-test program emphasizing the relationship between fault coverage, speed, and quantity of instructions were demonstrated.

  3. V/STOL AND digital avionics system for UH-1H

    NASA Technical Reports Server (NTRS)

    Liden, S.

    1978-01-01

    A hardware and software system for the Bell UH-1H helicopter was developed that provides sophisticated navigation, guidance, control, display, and data acquisition capabilities for performing terminal area navigation, guidance and control research. Two Sperry 1819B general purpose digital computers were used. One contains the development software that performs all the specified system flight computations. The second computer is available to NASA for experimental programs that run simultaneously with the other computer programs and which may, at the push of a button, replace selected computer computations. Other features that provide research flexibility include keyboard selectable gains and parameters and software generated alphanumeric and CRT displays.

  4. V/STOLAND digital avionics system for XV-15 tilt rotor

    NASA Technical Reports Server (NTRS)

    Liden, S.

    1980-01-01

    A digital flight control system for the tilt rotor research aircraft provides sophisticated navigation, guidance, control, display and data acquisition capabilities for performing terminal area navigation, guidance and control research. All functions of the XV-15 V/STOLAND system were demonstrated on the NASA-ARC S-19 simulation facility under a comprehensive dynamic acceptance test. The most noteworthy accomplishments of the system are: (1) automatic configuration control of a tilt-rotor aircraft over the total operating range; (2) total hands-off landing to touchdown on various selectable straight-in glide slopes and on a flight path that includes a two-revolution helix; (3) automatic guidance along a programmed three-dimensional reference flight path; (4) navigation data for the automatic guidance computed on board, based on VOR/DME, TACAN, or MLS navid data; and (5) integration of a large set of functions in a single computer, utilizing 16k words of storage for programs and data.

  5. Modeling pilot interaction with automated digital avionics systems: Guidance and control algorithms for contour and nap-of-the-Earth flight

    NASA Technical Reports Server (NTRS)

    Hess, Ronald A.

    1990-01-01

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

  6. The 23rd Annual Meeting of the European Tissue Repair Society (ETRS) in Reims, France

    PubMed Central

    2014-01-01

    The 23rd Annual Meeting of the European Tissue Repair Society, Reims, France, October 23 to 25, 2013 focused on tissue repair and regenerative medicine covering topics such as stem cells, biomaterials, tissue engineering, and burns. PMID:24552134

  7. Aims and Results of the 23rd International Conference on Vacuum Technique and Technology (VTT2016)

    NASA Astrophysics Data System (ADS)

    Lisenkov, A. A.; Kostrin, D. K.; Pavlova, V. A.

    2016-07-01

    In this preface the main features, aims and results of the 23rd International Conference on Vacuum Technique and Technology (VTT2016) that was held on 7-9 June 2016 in Saint Petersburg, Russia are discussed.

  8. 1999 Digital Avionics Highlights

    NASA Technical Reports Server (NTRS)

    Polites, Michael E.

    1999-01-01

    This article summarizes the highlights of recent events and developments in guidance, navigation, and control in space, aircraft, and weapons. This article is about 1,200 words long. Information for the article was collected from other NASA Centers, DoD, and industry. All information was previously cleared by the originating organizations. Information for the article was also gathered from Aviation Week and Space Technology, and similar sources.

  9. Common Avionics Display Processor (CADP)

    NASA Astrophysics Data System (ADS)

    Farley, Paul E.

    1995-06-01

    The 1970s saw the start of a trend towards integrated digital avionics. In the 1980s, the Air Force's Pave Pillar initiative defined centralized digital processing as the cost- effective approach to tactical avionics. The avionics systems of the two advanced aircraft presently under development, a fixed-wing tactical fighter and an armed scout/reconnaissance helicopter, were based on this architecture. Both platforms relied upon custom, single-purpose hardware and software to generate images for their advanced multifunctional flat panel cockpit displays. The technology to generate real-time synthetic images with common data and signal processors was not available during the development of the platforms. Harris IR&D investigations have focused on an approach that Harris GASD has named the Common Avionics Display Processor (CADP). This programmable device can generate sophisticated images or perform sensor image manipulation and processing. The Common Avionics Display Processor is a general purpose image synthesizer. It consists of software and hardware components configured at run time by a downloaded program. The CADP offers two advantages over custom, special purpose devices. First, it solves a class of problems, not a single one. It can generate many types of images, from alphanumeric to sensor simulation. Only one module type is required for any of these functions. Second, as program schedules become shorter, traditional hardware design time becomes the delivery limiting task. Because both the software and hardware components are programmable at run time, the CADP can adapt to changing requirements without redesign.

  10. Space shuttle engineering and operations support. Avionics system engineering

    NASA Technical Reports Server (NTRS)

    Broome, P. A.; Neubaur, R. J.; Welsh, R. T.

    1976-01-01

    The shuttle avionics integration laboratory (SAIL) requirements for supporting the Spacelab/orbiter avionics verification process are defined. The principal topics are a Spacelab avionics hardware assessment, test operations center/electronic systems test laboratory (TOC/ESL) data processing requirements definition, SAIL (Building 16) payload accommodations study, and projected funding and test scheduling. Because of the complex nature of the Spacelab/orbiter computer systems, the PCM data link, and the high rate digital data system hardware/software relationships, early avionics interface verification is required. The SAIL is a prime candidate test location to accomplish this early avionics verification.

  11. Modular avionics packaging standardization

    NASA Astrophysics Data System (ADS)

    Austin, M.; McNichols, J. K.

    The Modular Avionics Packaging (MAP) Program for packaging future military avionics systems with the objective of improving reliability, maintainability, and supportability, and reducing equipment life cycle costs is addressed. The basic MAP packaging concepts called the Standard Avionics Module, the Standard Enclosure, and the Integrated Rack are summarized, and the benefits of modular avionics packaging, including low risk design, technology independence with common functions, improved maintainability and life cycle costs are discussed. Progress made in MAP is briefly reviewed.

  12. PREFACE: The 23rd EGAS Conference of the European Group for Atomic Spectroscopy

    NASA Astrophysics Data System (ADS)

    Łęgowski, S.

    1992-01-01

    The 23rd conference of the European Group for Atomic Physics took place in Toruń, Poland and was hosted by the Nicholas Copernicus University, from July 9-12th, 1991. Originally the conference was planned to be held in Vilnius, Lithuania but at the end of February the Board of EGAS decided to transfer the Conference to Poland. So the town Toruń where the famous astronomer Nicholas Copernicus was born became the host for the 23rd EGAS Conference. About 168 physicists from 16 countries all over the world met to discuss problems of pure and applied atomic and molecular spectroscopy and related topics. Ten of the invited lectures have been prepared for publication by the authors and are presented in this issue of Physica Scripta.

  13. Statistical analysies of the type III bursts and CMEs during the 23rd solar cycle

    NASA Astrophysics Data System (ADS)

    Ma, Yuan; Wang, De-Yu; Yan, Yi-Hua

    2006-12-01

    The statistics analyses of the microwave type III bursts, coronal mass ejections (CMEs), Hα flares and relevant events observed with 5200-7600MHz spectrograph at the National Astronomical Observatory during the 23rd solar cycle are carried out in this article. It is found that the relation between the microwave type III bursts and CMEs is not closer than that between the type II radio bursts and CMEs; the Hα flares corresponding to the CMEs are all gradual flares.

  14. Flight Avionics Hardware Roadmap

    NASA Technical Reports Server (NTRS)

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

    2013-01-01

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

  15. Conference Support, 23rd Western Photosynthesis Conference 2014, Final Technical Report

    SciTech Connect

    Wachter, Rebekka

    2015-01-12

    The Western Photosynthesis Conference is a regional conference that is held on an annual basis to bring together researchers primarily from the Western United States to share their newest research advances on photosynthetic processes. The 23rd conference was focused on both fundamental and more applied research on the biological conversion of solar energy to various energy storage forms. Several particular areas of solar energy conversion were emphasized in this conference (see below). Some of these topics, such as carbon limitations on photosynthesis, biomimicry and phenotyping, have traditionally not been incorporated extensively in the Western Photosynthesis Conference. We found that these topics have substantially broadened of the scope of this meeting.

  16. The proceedings of the 23rd International Technical Conference on Coal Utilization and Fuel Systems

    SciTech Connect

    Sakkestad, B.A.

    1998-03-01

    This document contains the proceedings of the 23rd International Technical Conference on Coal Utilization and Fuel Systems, held March 9-13, 1998 in Clearwater, Florida. Topics included advanced combustion systems, alternative fuels, coal liquefaction, climate change strategies, international highlights, combustion by-product utilization, co-firing, fuel gas treatment, low nitrogen oxide burners, carbon dioxide mitigation, power plant upgrades, Latin American coal perspective, coal fines utilization, upgraded coal for the power industry, hot gas particulate cleanup, coal conversion, hydraulics and transportation, coal briquetting and coal beneficiation, air toxics, materials and equipment, and coal-water fuels preparation. Separate abstracts have been prepared for the individual papers presented at this conference.

  17. GLE Observations in 23rd Solar Cycle at the Baksan Air Shower Arrays Andyrchy and Carpet

    NASA Astrophysics Data System (ADS)

    Karpov, S. N.; Alekseenko, V. V.; Djappuev, D. D.; Karpova, Z. M.; Khaerdinov, N. S.; Petkov, V. B.; Radchenkov, A. V.; Zaichenko, A. N.

    2003-07-01

    Total counting rates of two Baksan extensive air shower arrays Andyrchy and Carp et were examined during 10 Ground Level Enhancements (GLE) of Solar Cosmic Rays (SCR) observed in current 23rd cycle of solar activity. In this case the threshold primary energy is equal to geomagnetic cut-off, Emin = 5.8 GeV. Significant increases (>3 st.dev.) above the galactic cosmic ray background were found during 6 GLE events from 10. The amplitudes of all increases make the tenth shares of percent. Therefore, they can not be registered by neutron monitors with a close geomagnetic cut-off.

  18. Multiple Miniature Avionic Displays

    NASA Technical Reports Server (NTRS)

    Rye, Jeffrey M. (Inventor); Dorneich, Michael C. (Inventor); Gannon, Aaron J. (Inventor)

    2008-01-01

    A display screen for displaying multiple sets of information is provided. In one embodiment, an aviation display screen includes a main window and a plurality of miniature windows. The main window is adapted to illustrate one set of information. Each miniature window is adapted to display a set of avionic information. The avionic display is further adapted to toggle a select set of avionic information in one of the miniature windows into the main window.

  19. Avionics Architecture Modelling Language

    NASA Astrophysics Data System (ADS)

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

    2014-08-01

    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.

  20. Space Weather and the Ground-Level Solar Proton Events of the 23rd Solar Cycle

    NASA Astrophysics Data System (ADS)

    Shea, M. A.; Smart, D. F.

    2012-10-01

    Solar proton events can adversely affect space and ground-based systems. Ground-level events are a subset of solar proton events that have a harder spectrum than average solar proton events and are detectable on Earth's surface by cosmic radiation ionization chambers, muon detectors, and neutron monitors. This paper summarizes the space weather effects associated with ground-level solar proton events during the 23rd solar cycle. These effects include communication and navigation systems, spacecraft electronics and operations, space power systems, manned space missions, and commercial aircraft operations. The major effect of ground-level events that affect manned spacecraft operations is increased radiation exposure. The primary effect on commercial aircraft operations is the loss of high frequency communication and, at extreme polar latitudes, an increase in the radiation exposure above that experienced from the background galactic cosmic radiation. Calculations of the maximum potential aircraft polar route exposure for each ground-level event of the 23rd solar cycle are presented. The space weather effects in October and November 2003 are highlighted together with on-going efforts to utilize cosmic ray neutron monitors to predict high energy solar proton events, thus providing an alert so that system operators can possibly make adjustments to vulnerable spacecraft operations and polar aircraft routes.

  1. Avionics System Architecture Tool

    NASA Technical Reports Server (NTRS)

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

    2005-01-01

    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.

  2. Solar activity phase diagram and forecast of the coming 23rd cycle.

    NASA Astrophysics Data System (ADS)

    Pankratov, A. K.; Narmanskij, V. Ya.; Vladimirskij, B. M.

    1998-10-01

    The phase diagram method is used for investigation of relations between planetary dynamics and solar activity variations. It was found that the calculated moments of solar activity maxima/minima are disposed regularly in the coordinates of the difference of heliocentric longitudes of Uranus-Neptune versus the difference of heliocentric longitudes of Saturn-Neptune. There are separate zones containing maxima (minima) of only the northern (or southern) polarity of solar mean magnetic field. There is also a region where only maxima of small amplitudes are concentrated (Rz < 100). The regularities obtained are used for prognosis of the 23rd cycle. The minimum of activity must be observed in 1999±2. The maximum is forecast in 2006±2. The amplitude Rz can be as small as 60±20. Probably there will be no change of the polarity of the mean solar magnetic field.

  3. Proceedings of the 23rd Annual Precise Time and Time Interval (PTTI) Applications and Planning Meeting

    SciTech Connect

    Sydnor, R.L.

    1992-07-01

    A compilation of technical papers, from the 23rd annual Precise Time and Time Interval (PTTI) Applications and Planning Meeting, is presented. Papers were given in the following categories: (1) developments in rubidium, cesium, and hydrogen-based frequency standards, and in cryogenic and trapped-ion technology; (2) international and transnational applications of PTTI technology with emphasis on satellite laser tracking networks, GLONASS timing, comparison of national time scales and international communications; (3) applications of PTTI technology to the telecommunications, power distribution, platform positioning, and geophysical survey industries; (4) applications of PTTI technology to evolving military communications and navigation systems; and (5) dissemination of precise time and frequency by means of GPS, GLONASS, MILSTAR, Loran, and synchronous communications satellites.

  4. Proceedings of the 23rd Annual Precise Time and Time Interval (PTTI) Applications and Planning Meeting

    NASA Technical Reports Server (NTRS)

    Sydnor, Richard L. (Editor)

    1992-01-01

    A compilation of technical papers, from the 23rd annual Precise Time and Time Interval (PTTI) Applications and Planning Meeting, is presented. Papers were given in the following categories: (1) developments in rubidium, cesium, and hydrogen-based frequency standards, and in cryogenic and trapped-ion technology; (2) international and transnational applications of PTTI technology with emphasis on satellite laser tracking networks, GLONASS timing, comparison of national time scales and international communications; (3) applications of PTTI technology to the telecommunications, power distribution, platform positioning, and geophysical survey industries; (4) applications of PTTI technology to evolving military communications and navigation systems; and (5) dissemination of precise time and frequency by means of GPS, GLONASS, MILSTAR, Loran, and synchronous communications satellites.

  5. Strategic avionics technology planning

    NASA Technical Reports Server (NTRS)

    Cox, Kenneth J.; Brown, Don C.

    1991-01-01

    NASA experience in development and insertion of technology into programs had led to a recognition that a Strategic Plan for Avionics is needed for space. In the fall of 1989 an Avionics Technology Symposium was held in Williamsburg, Virginia. In early 1990, as a followon, a NASA wide Strategic Avionics Technology Working Group was chartered by NASA Headquarters. This paper will describe the objectives of this working group, technology bridging, and approaches to incentivize both the federal and commercial sectors to move toward rapidly developed, simple, and reliable systems with low life cycle cost.

  6. Ares I Avionics Introduction

    NASA Technical Reports Server (NTRS)

    Marchant, Christopher C.

    2009-01-01

    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. Space tug avionics definition study. Volume 3: Avionics baseline configuration definition

    NASA Technical Reports Server (NTRS)

    1975-01-01

    The baseline avionics systems for the space tug is comprised of a central digital computer that integrates the functions of all of the tug's subsystems by means of a redundant digital data bus. The major subsystems of the avionics system are: data management; communications; guidance, navigation, and control; rendezvous and docking; electrical power; and instrumentation. The baseline avionics system for the space tug resulting from system and subsystem trade studies is defined. Tug interfaces with the spacecraft, orbiter and the ground, and the baseline philosophy and configuration for onboard checkout of the tug are included. Baseline configurations, functional and operational features, component details and characteristics, and the supporting software are included in the subsystem descriptions.

  8. Perspective on intelligent avionics

    SciTech Connect

    Jones, H.L.

    1987-01-01

    Technical issues which could potentially limit the capability and acceptibility of expert systems decision-making for avionics applications are addressed. These issues are: real-time AI, mission-critical software, conventional algorithms, pilot interface, knowledge acquisition, and distributed expert systems. Examples from on-going expert system development programs are presented to illustrate likely architectures and applications of future intelligent avionic systems. 13 references.

  9. Outer radiation belt of relativistic electrons during the minimum of the 23rd solar cycle

    NASA Astrophysics Data System (ADS)

    Tverskaya, L. V.; Balashov, S. V.; Veden'kin, N. N.; Ivanov, V. V.; Karpenko, D. S.; Kochura, S. G.; Maksimov, I. A.; Open'ko, S. I.; Pavlov, N. N.; Reizman, S. Ya.; Rubinshtein, I. A.; Sitnokova, N. N.; Tel'tsov, M. V.; Trofimchuk, D. A.; Tulupov, V. I.

    2012-11-01

    The data on fluxes of electrons with energy Ee > 1 MeV and on radiation doses under the Al shielding of about 2 g/cm2 measured on the GLONASS satellite (circular orbit with altitude 20000 km and inclination 65°) for the period from December 2006 through May 2010 are analyzed. The minimum of the 23rd solar cycle turned out to be the longest for all over the space exploration age. Consequently, average semiannual electron fluxes and daily radiation doses are showing the decrease by more than an order of magnitude in comparison with the levels observed in 2007. We present an example of a diffusion wave of relativistic electrons; the wave develops in a period between magnetic storms. This process may result in a significant increase of the radiation dose measured in the orbit, even under the conditions of weak geomagnetic disturbances. The dynamics of variations in relativistic electron fluxes during the magnetic storm of April 5-6, 2010, is discussed so far as this is the first strong flux enhancement in the 24th solar cycle.

  10. Proceedings of the 23rd Seismic Research Symposium: Worldwide Monitoring of Nuclear Explosions

    SciTech Connect

    Warren, N. Jill; Chavez, Francesca C.

    2001-10-02

    These proceedings contain papers prepared for the 23rd Seismic Research Review: Worldwide Monitoring of Nuclear Explosions, held 2-5 October, 2001 in Jackson Hole, Wyoming. These papers represent the combined research related to ground-based nuclear explosion monitoring funded by the National Nuclear Security Administration (NNSA), Defense Threat Reduction Agency (DTRA), Air Force Technical Applications Center (AFTAC), the Comprehensive Nuclear-Test-Ban Treaty Organization (CTBTO), and other invited sponsors. The scientific objectives of the research are to improve the United States capability to detect, locate, and identify nuclear explosions. The purpose of the meeting is to provide the sponsoring agencies, as well as potential users, an opportunity to review research accomplished during the preceding year and to discuss areas of investigation for the coming year. For the researchers, it provides a forum for the exchange of scientific information toward achieving program goals, and an opportunity to discuss results and future plans. Paper topics include: seismic regionalization and calibration; detection and location of sources; wave propagation from source to receiver; the nature of seismic sources, including mining practices; hydroacoustic, infrasound, and radionuclide methods; on-site inspection; and data processing.

  11. Satellite observations of the volcanic plume from the 23rd April 2015 eruption of Calbuco volcano

    NASA Astrophysics Data System (ADS)

    Hayer, Catherine; Carboni, Elisa; Ventress, Lucy; Povey, Adam; Grainger, Roy

    2016-04-01

    Calbuco volcano, Chile, erupted on 23rd April 2015, producing an eruption column reported to reach 17 km. The eruption was captured on the IASI NRT website (http://www.nrt-atmos.cems.rl.ac.uk/). The data were then reprocessed using the iterative optimal estimation retrieval developed by the EODG group at University of Oxford to determine the SO2 atmospheric loading and the altitude of the plume over time. The atmospheric loading was measured as 0.3 - 0.4 Tg of SO2 over the first 2 days. It is thought that the eruption was relatively ash poor, with the majority of the ash falling out within the first couple of days. The retrieved altitude of the plume is consistent with the range initially reported, with the core of the plume reaching 15 - 18 km. When the SO2 plume reached the west coast of South Africa, it was caught in a cyclonic system, causing it to remain in the same region for several days with a highly constrained core. A SO2 depletion rate and conversion time to H2SO4 are calculated from this data. The data from the IASI instruments are compared to CALIOP lidar overpasses as well as data from the MLS & OSIRIS instruments. The HYSPLIT trajectory model is used to investigate the evolution of the plume and to corroborate the altitudes retrieved by IASI.

  12. Proceedings of the Annual Conference of the Western Australian Science Education Association (23rd, Perth, Western Australia, November 13, 1998).

    ERIC Educational Resources Information Center

    Rennie, Leonie, Ed.

    These proceedings contain reviewed and edited papers from the 23rd annual meeting of the Western Australian Science Education Association (WASEA). Papers include: (1) Using Quantitative and Qualitative Approaches to Validate a Questionnaire to Describe Science Teacher Behavior in Taiwan and Australia (Darrell Fisher, David Henderson, and…

  13. Basic avionics module design for general aviation aircraft

    NASA Technical Reports Server (NTRS)

    Smyth, R. K.; Smyth, D. E.

    1978-01-01

    The design of an advanced digital avionics system (basic avionics module) for general aviation aircraft operated with a single pilot under IFR conditions is described. The microprocessor based system provided all avionic functions, including flight management, navigation, and lateral flight control. The mode selection was interactive with the pilot. The system used a navigation map data base to provide operation in the current and planned air traffic control environment. The system design included software design listings for some of the required modules. The distributed microcomputer uses the IEEE 488 bus for interconnecting the microcomputer and sensors.

  14. Avionics System Architecture for NASA Orion Vehicle

    NASA Technical Reports Server (NTRS)

    Baggerman, Clint

    2010-01-01

    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.

  15. Micro-Avionics Node for Distributed Avionics System

    NASA Technical Reports Server (NTRS)

    Blaes, B. R.

    2001-01-01

    An avionics system is a platform residing on a flight vehicle that provides the resources (hardware and software) needed to manage the flight mission. Distributing the avionics system components, both functionally and spatially, can provide characteristics that benefit the overall system robustness, reliability, testability, and maintainability. This abstract discusses the concept of a distributed avionics system consisting of a network of micro-avionics nodes. Additional information is contained in the original extended abstract.

  16. PREFACE: 23rd International Conference on High Pressure Science and Technology (AIRAPT-23)

    NASA Astrophysics Data System (ADS)

    Gupta, Satish C.

    2012-07-01

    The 23rd AIRAPT International Conference on High Pressure Science and Technology was held at Bhabha Atomic Research Centre, Mumbai, from 25-30 September 2011. This conference is part of the series of AIRAPT International Conferences which are held biennially. AIRAPT is an acronym for the French title which translates as 'International Association for the Advancement of High Pressure Science and Technology'. This was the second time the AIRAPT Conference was organized in India. The first was held 20 years ago at the National Aeronautical Laboratory, Bangalore in 1991. The 23rd Conference covered many important topics in the area of both static and dynamic high pressures including theoretical and experimental investigations on the response of materials under high pressures, new developments using neutron and synchrotron sources, investigations on superconductivity under high pressure, studies of geophysical and planetary sciences, biosciences, and the synthesis of new materials. The conference program included Bridgman award lecture, Jemieson award lecture, seven plenary talks, 85 invited talks, 83 oral presentations and about 195 posters. In all there were 372 presentations. 285 scientists from 19 countries participated in the conference. The countries represented included Austria, Canada, China, Estonia, France, Germany, India, Israel, Italy, Japan, Nepal, New Zealand, Poland, Russia, South Korea, Spain, Sweden, Switzerland, Turkey, UK, Ukraine and USA. Many new developments were presented, for example, measurement techniques using the new generation synchrotron sources, more powerful neutron sources and much brighter laser sources; integration of gas-gun with synchrotron source; the achievement of multi-megabar pressures in shock-less dynamic compressions; and capabilities to synthesize centimeter size diamonds with better quality. All these developments have opened up new opportunities for understanding the physics of materials under high pressures. I would like

  17. Modular avionic architectures

    NASA Astrophysics Data System (ADS)

    Trujillo, Edward

    The author presents an analysis revealing some of the salient features of modular avionics. A decomposition of the modular avionics concept is performed, highlighting some of the key features of such architectures. Several layers of architecture can be found in such concepts, including those relating to software structure, communication, and supportability. Particular emphasis is placed on the layer relating to partitioning, which gives rise to those features of integration, modularity, and commonality. Where integration is the sharing of common tasks or items to gain efficiency and flexibility, modularity is the partitioning of a system into reconfigurable and maintainable items, and commonality is partitioning to maximize the use of identical items across the range of applications. Two architectures, MASA (Modular Avionics System Architecture) and Pave Pillar, are considered in particular.

  18. Flight Avionics Hardware Roadmap

    NASA Technical Reports Server (NTRS)

    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

    2014-01-01

    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

  19. Avionics advanced development strategy

    NASA Technical Reports Server (NTRS)

    Dyer, D.

    1990-01-01

    Discussed here is the problem of how to put together an integrated, phased, and affordable avionics advanced development program that links and applies to operational, evolving, and developing programs/vehicles, as well as those in the planning phases. Collecting technology needs from individual programs/vehicles and proposed technology items from individual developers usually results in a mismatch and something that is unaffordable. A strategy to address this problem is outlined with task definitions which will lead to avionics advanced development items that will fit within an overall framework, prioritized to support budgeting, and support the scope of NASA space transportations needs.

  20. Affordable Vehicle Avionics Overview

    NASA Technical Reports Server (NTRS)

    Cockrell, James J.

    2015-01-01

    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

  1. Affordable Vehicle Avionics Overview

    NASA Technical Reports Server (NTRS)

    Cockrell, James J.

    2015-01-01

    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.

  2. Tug avionics system overview

    NASA Technical Reports Server (NTRS)

    Raaberg, M. T.; Newcomb, J. I.

    1975-01-01

    The recently defined Tug avionics system takes maximum advantage of projected technology advances to attain: low system weight; power system capacity essentially independent of mission duration; sensors for rendezvous, docking, and navigation update; all attitude communications; onboard checkout and redundancy management; and modular fault tolerant computer control. The requirements, selection trades, and configurations are discussed for the major subsystems: data management, guidance navigation and control, communications, rendezvous and docking, and electrical power. The integrated avionics system and the interfaces with the payload, Shuttle and ground are described.

  3. Avionic standard module development

    NASA Astrophysics Data System (ADS)

    Maki, Stanley C.; Cormier, Edmond P.; Piszkin, Thomas A.

    Avionics standard modules with redundancy offer substantial economic benefits compared to special-purpose processor units for the orbital transfer vehicle and advanced launch vehicle programs. A fiber optic, serial vehicle bus provides high throughput with modest hardware. A bistage, split tapered, star optical coupler uses a token-pass/token-demand protocol. It is reported that a standard module implementation of the above is a feasible, cost-effective approach to avionics design using standard buses and standard packaging. The VHSIC integrated package readily accommodates higher-speed VLSI chips as they become available.

  4. PREFACE: 23rd European Cosmic Ray Symposium (and 32nd Russian Cosmic Ray Conference)

    NASA Astrophysics Data System (ADS)

    Erlykin, A. D.; Kokoulin, R. P.; Lidvansky, A. S.; Meroshnichenko, L. I.; Panasyuk, M. I.; Panov, A. D.; Wolfendale, A. W.

    2013-02-01

    The 23rd European Cosmic Ray Symposium (ECRS) took place in Moscow at the Lomonosov Moscow State University (3-7 July 2012), and was excellently organized by the Skobeltsyn Institute of Nuclear Physics of the Lomonosov Moscow State University, with the help of the Russian Academy of Sciences and the Council on the Complex Problem of Cosmic Rays of the Russian Academy of Sciences. The first symposia were held in 1968 in Lodz, Poland (high energy, extensive air showers and astrophysical aspects) and in Bern (solar and heliospheric phenomena) and the two 'strands' joined together in 1976 with the meeting in Leeds. Since then the symposia, which have been very successful, have covered all the major topics with some emphasis on European collaborations and on meeting the demands of young scientists. Initially, a driving force was the need to overcome the divisions caused by the 'Cold War' but the symposia continued even when that threat ceased and they have shown no sign of having outlived their usefulness. 2012 has been an important year in the history of cosmic ray studies, in that it marked the centenary of the discovery of enigmatic particles in the perilous balloon ascents of Victor Hess. A number of conferences have taken place in Western Europe during the year, but this one took place in Moscow as a tribute to the successful efforts of many former USSR and other Eastern European scientists in discovering the secrets of the subject, often under very difficult conditions. The symposium covers a wide range of scientific issues divided into the following topics: PCR-IPrimary cosmic rays I (E < 1015 eV) PCR-IIPrimary cosmic rays II (E > 1015 eV) MNCosmic ray muons and neutrinos GAGeV and TeV gamma astronomy SHEnergetic particles in the heliosphere (solar and anomalous CRs and GCR modulation) GEOCosmic rays and geophysics (energetic particles in the atmosphere and magnetosphere of the Earth) On a personal note, as I step down as co-founder and chairman of the

  5. Critical issues regarding SEU in avionics

    SciTech Connect

    Normand, E. ); McNulty, P.J. )

    1993-01-01

    The energetic neutrons in the atmosphere cause microelectronics in avionic system to malfunction through a mechanism called single-event upsets (SEUs), and single-event latchup is a potential threat. Data from military and experimental flights as well as laboratory testing indicate that typical non-radiation-hardened 64K and 256K static random access memories (SRAMs) can experience a significant SEU rate at aircraft altitudes. Microelectronics in avionics systems have been demonstrated to be susceptible to SEU. Of all device types, RAMs are the most sensitive because they have the largest number of bits on a chip (e.g., an SRAM may have from 64K to 1M bits, a microprocessor 3K to 10K bits, and a logic device like an analog-to-digital converter, 12 bits). Avionics designers will need to take this susceptibility into account in current and future designs. A number of techniques are available for dealing with SEU: EDAC, redundancy, use of SEU-hard parts, reset and/or watchdog timer capability, etc. Specifications should be developed to guide avionics vendors in the analysis, prevention, and verification of neutron-induced SEU. Areas for additional research include better definition of the atmospheric neutrons and protons, development of better calculational models (e.g., those used for protons[sup 11]), and better characterization of neutron-induced latchup.

  6. LPHYS'14: 23rd International Laser Physics Workshop (Sofia, Bulgaria, 14-18 July 2014)

    NASA Astrophysics Data System (ADS)

    Yevseyev, Alexander V.

    2014-04-01

    The 23rd annual International Laser Physics Workshop (LPHYS14) will be held from 14 July to 18 July 2014 in the city of Sofia, Bulgaria, at the Ramada Sofia Hotel hosted this year by the Institute of Electronics, Bulgarian Academy of Sciences. LPHYS14 continues a series of workshops that took place in Dubna,1992; Dubna/Volga river tour, 1993; New York, 1994; Moscow/Volga river tour (jointly with NATO SILAP Workshop), 1995; Moscow, 1996; Prague, 1997; Berlin, 1998; Budapest, 1999; Bordeaux, 2000; Moscow, 2001; Bratislava, 2002; Hamburg, 2003; Trieste, 2004; Kyoto, 2005; Lausanne, 2006; Len, 2007; Trondheim, 2008; Barcelona, 2009; Foz do Iguau, 2010; Sarajevo, 2011; Calgary, 2012 and Prague, 2013. The total number of participants this year is expected to be about 400. In the past, annual participation was typically from over 30 countries. 2014 Chairpersons Sanka Gateva (Bulgaria), Pavel Pashinin (Russia) LPHYS14 will offer eight scientific section seminars and one general symposium: Seminar 1 Modern Trends in Laser Physics Seminar 2 Strong Field and Attosecond Physics Seminar 3 Biophotonics Seminar 4 Physics of Lasers Seminar 5 Nonlinear Optics and Spectroscopy Seminar 6 Physics of Cold Trapped Atoms Seminar 7 Quantum Information Science Seminar 8 Fiber Optics Symposium Extreme Light Technologies, Science and Applications Abstract of your presentation A one-page abstract should contain: title; list of all co-authors (the name of the speaker underlined); affiliations; correspondence addresses including phone numbers, fax numbers, e-mail addresses; and the text of the abstract. Abstracts should be sent to the following co-chairs of the scientific seminars and the symposium: Kirill A Prokhorov (Seminar 1) E-mail: cyrpro@gpi.ru Mikhail V Fedorov (Seminar 2) E-mail: fedorov@ran.gpi.ru Sergey A Gonchukov (Seminar 3) E-mail: gonchukov@mephi.ru Ivan A Shcherbakov (Seminar 4) E-mail: gbufetova@lsk.gpi.ru Vladimir A Makarov (Seminar 5) E-mail: makarov@msu.ilc.edu.ru Vyacheslav

  7. PREFACE: 23rd National Symposium on Plasma Science & Technology (PLASMA-2008)

    NASA Astrophysics Data System (ADS)

    Mago, V. K.; Ananthapadmanabhan, P. V.; Patil, D. S.; Das, A. K.

    2010-01-01

    It is our pleasure to present the proceedings of the 23rd National Symposium on Plasma Science and Technology (PLASMA-2008) held at Bhabha Atomic Research Center, Mumbai, 10- December 2008 in association with the Plasma Science Society of India. The Plasma Science Society of India has been holding regular symposia on general topics related to Plasma. The symposium was designed to provide a forum for young researchers in Plasma Science and Technology to interact with eminent plasma scientists from India and abroad and to present their work. The scope of the symposium included frontline research in Basic Plasma Physics as well as significant advances in Plasma Technology. In view of the ever-growing importance of Plasma Science and Technology to India's Nuclear Energy program, the focal theme of the symposium was chosen as 'Plasmas in Nuclear Fuel Cycle'. The scientific program of this four day symposium consisted of review talks, invited topical lectures, contributed oral and poster presentations in the following areas of Plasma Science & Technology. Basic Plasma Physics, simulations and modeling (BP) Nuclear fusion and Technology (NF) Space & Astrophysical Plasma(SA) Exotic Plasmas, Non-linear Dynamics(EP) Laser Plasma Interaction and Beam Physics (LP) Industrial applications of plasmas (IP) Plasma Diagnostics(PD) Plasmas and clean environment(PC) There was also a Special Session devoted to the focal theme Plasmas in Nuclear Fuel Cycle (PANFC) Applications in Nuclear Fusion Technology (ANFT) Physics and technology of Processing Plasmas in Nuclear Fuel Cycle (PPNFC). Plasma Technology finds wide applications not only in nuclear, space and defense-related industries but also in medical, nano-technology and semiconductor industries. Plasma technologies have distinguished themselves in terms of compactness, process efficiency, techno economics and innovative possibilities. As we advance into the new technology era, there is a need for evolving strategies to apply the

  8. PREFACE: 23rd Congress of the International Commission for Optics (ICO 23)

    NASA Astrophysics Data System (ADS)

    Salgueiro, J. R.; Flores-Arias, M. T.; Vázquez-Dorrío, J. B.; Guzmán, Á.; Arakawa, Y.

    2015-04-01

    The 23rd Congress of the International Commission for Optics (ICO) was held in Santiago de Compostela (Spain) 26-29 August 2014, organized by the Universities of Vigo and Santiago de Compostela. Approximately 450 people attended the conference, sharing their knowledge in the cheerful, warm atmosphere of this lovely city. The conference was extremely successful in contributing to the mission of the ICO: to contribute worldwide, on an international basis, to the progress and diffusion of scientific and technological knowledge on optics and photonics. Optics and photonics have reached a critical level of importance for the development of our societies and are present in a great many aspects of our technological progress, from communication systems supporting the Internet to the most modern techniques in medicine. Consistent with the conference slogan Enlightening the Future, the meeting stressed the importance of optical science as a key to technological progress in the coming years. UNESCO's designation of 2015 as the International Year of Light and Light-Based Technologies (www.light2015.org) acknowledges the importance of raising global awareness of how light and light-based technologies are present in a large fraction of today's advances and how they can address challenges in important areas such as energy, education, agriculture, and health. The four-day conference highlighted eleven plenary talks by outstanding scientists working in important areas of optics and photonics. A. Aspect, T. Kippenberg (2013 ICO Prize awardee) and K. Razewski (2013 ICO Galileo Galilei Award) spoke on quantum optics; P. Russell and Yu. Kivshar lectured on topics related to optical processing devices as optical fibers and metamaterials for light shaping; N. X. Fang (2011 ICO Prize), U. Woggon, and A. Alú (2013 IUPAP Young Scientists Prize) discussed applications of optics to nanoscience; and K. Dholakia and J. Widjaja (2008 Galileo Galilei Award) presented in their plenaries

  9. Investigation of an advanced fault tolerant integrated avionics system

    NASA Technical Reports Server (NTRS)

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

    1986-01-01

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

  10. Integrated Avionics System (IAS)

    NASA Technical Reports Server (NTRS)

    Hunter, D. J.

    2001-01-01

    As spacecraft designs converge toward miniaturization and with the volumetric and mass constraints placed on avionics, programs will continue to advance the 'state of the art' in spacecraft systems development with new challenges to reduce power, mass, and volume. Although new technologies have improved packaging densities, a total system packaging architecture is required that not only reduces spacecraft volume and mass budgets, but increase integration efficiencies, provide modularity and scalability to accommodate multiple missions. With these challenges in mind, a novel packaging approach incorporates solutions that provide broader environmental applications, more flexible system interconnectivity, scalability, and simplified assembly test and integration schemes. This paper will describe the fundamental elements of the Integrated Avionics System (IAS), Horizontally Mounted Cube (HMC) hardware design, system and environmental test results. Additional information is contained in the original extended abstract.

  11. PREFACE: 23rd National Symposium on Plasma Science & Technology (PLASMA-2008)

    NASA Astrophysics Data System (ADS)

    Mago, V. K.; Ananthapadmanabhan, P. V.; Patil, D. S.; Das, A. K.

    2010-01-01

    It is our pleasure to present the proceedings of the 23rd National Symposium on Plasma Science and Technology (PLASMA-2008) held at Bhabha Atomic Research Center, Mumbai, 10- December 2008 in association with the Plasma Science Society of India. The Plasma Science Society of India has been holding regular symposia on general topics related to Plasma. The symposium was designed to provide a forum for young researchers in Plasma Science and Technology to interact with eminent plasma scientists from India and abroad and to present their work. The scope of the symposium included frontline research in Basic Plasma Physics as well as significant advances in Plasma Technology. In view of the ever-growing importance of Plasma Science and Technology to India's Nuclear Energy program, the focal theme of the symposium was chosen as 'Plasmas in Nuclear Fuel Cycle'. The scientific program of this four day symposium consisted of review talks, invited topical lectures, contributed oral and poster presentations in the following areas of Plasma Science & Technology. Basic Plasma Physics, simulations and modeling (BP) Nuclear fusion and Technology (NF) Space & Astrophysical Plasma(SA) Exotic Plasmas, Non-linear Dynamics(EP) Laser Plasma Interaction and Beam Physics (LP) Industrial applications of plasmas (IP) Plasma Diagnostics(PD) Plasmas and clean environment(PC) There was also a Special Session devoted to the focal theme Plasmas in Nuclear Fuel Cycle (PANFC) Applications in Nuclear Fusion Technology (ANFT) Physics and technology of Processing Plasmas in Nuclear Fuel Cycle (PPNFC). Plasma Technology finds wide applications not only in nuclear, space and defense-related industries but also in medical, nano-technology and semiconductor industries. Plasma technologies have distinguished themselves in terms of compactness, process efficiency, techno economics and innovative possibilities. As we advance into the new technology era, there is a need for evolving strategies to apply the

  12. General aviation avionics equipment maintenance

    NASA Technical Reports Server (NTRS)

    Parker, C. D.; Tommerdahl, J. B.

    1978-01-01

    Maintenance of general aviation avionics equipment was investigated with emphasis on single engine and light twin engine general aviation aircraft. Factors considered include the regulatory agencies, avionics manufacturers, avionics repair stations, the statistical character of the general aviation community, and owners and operators. The maintenance, environment, and performance, repair costs, and reliability of avionics were defined. It is concluded that a significant economic stratification is reflected in the maintenance problems encountered, that careful attention to installations and use practices can have a very positive impact on maintenance problems, and that new technologies and a general growth in general aviation will impact maintenance.

  13. BioMEMS and Electrophoresis in 2006: Review of the 23rd Annual Meeting of the American Electrophoresis Society

    PubMed Central

    Minerick, Adrienne R.; Ugaz, Victor M.

    2007-01-01

    The 23rd Annual Meeting of the American Electrophoresis Society (AES) was held at the San Francisco Hilton in San Francisco, California on 12–17 November 2006. This year’s meeting featured a look toward the future, with an emphasis on theoretical and experimental advances in miniaturization of BioMEMS, electrokinetics, and proteomics technologies. A total of 13 sessions accommodating 71 presentations and 18 posters were held in conjunction with the Annual Meeting of the American Institute of Chemical Engineers (AIChE). This review and corresponding special issue of Biomicrofluidics provide a sampling of some of the exciting research presented at the conference. PMID:19693377

  14. Space Tug avionics definition study. Volume 2: Avionics functional requirements

    NASA Technical Reports Server (NTRS)

    1975-01-01

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

  15. Space Transportation Avionics Technology Symposium. Volume 2: Conference Proceedings

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The focus of the symposium was to examine existing and planned avionics technology processes and products and to recommend necessary changes for strengthening priorities and program emphases. Innovative changes in avionics technology development and design processes are needed to support the increasingly complex, multi-vehicle, integrated, autonomous space-based systems. Key technology advances make such a major initiative viable at this time: digital processing capabilities, integrated on-board test/checkout methods, easily reconfigurable laboratories, and software design and production techniques.

  16. Space Transportation Avionics Technology Symposium. Volume 1: Executive summary

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The focus of the symposium was to examine existing and planned avionics technology processes and products and to recommend necessary changes for strengthening priorities and program emphases. Innovative changes in avionics technology development and design processes, identified during the symposium, are needed to support the increasingly complex, multi-vehicle, integrated, autonomous space-based systems. Key technology advances make such a major initiative viable at this time: digital processing capabilities, integrated on-board test/checkout methods, easily reconfigurable laboratories, and software design and production techniques.

  17. Demonstration Advanced Avionics System (DAAS)

    NASA Technical Reports Server (NTRS)

    1982-01-01

    The feasibility of developing an integrated avionics system suitable for general aviation was determined. A design of reliable integrated avionics which provides expanded functional capability that significantly enhances the utility and safety of general aviation at a cost commensurate with the general aviation market was developed. The use of a data bus, microprocessors, electronic displays and data entry devices, and improved function capabilities were emphasized. An avionics system capable of evaluating the most critical and promising elements of an integrated system was designed, built and flight tested in a twin engine general aviation aircraft.

  18. Avionics Maintenance Technology Program Standards.

    ERIC Educational Resources Information Center

    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…

  19. Trends in transport aircraft avionics

    NASA Technical Reports Server (NTRS)

    Berkstresser, B. K.

    1973-01-01

    A survey of avionics onboard present commercial transport aircraft was conducted to identify trends in avionics systems characteristics and to determine the impact of technology advances on equipment weight, cost, reliability, and maintainability. Transport aircraft avionics systems are described under the headings of communication, navigation, flight control, and instrumentation. The equipment included in each section is described functionally. However, since more detailed descriptions of the equipment can be found in other sources, the description is limited and emphasis is put on configuration requirements. Since airborne avionics systems must interface with ground facilities, certain ground facilities are described as they relate to the airborne systems, with special emphasis on air traffic control and all-weather landing capability.

  20. Cockpit avionics integration and automation

    NASA Technical Reports Server (NTRS)

    Pischke, Keith M.

    1990-01-01

    Information on cockpit avionics integration and automation is given in viewgraph form, with a number of photographs. The benefits of cockpit integration are listed. The MD-11 flight guidance/flight deck system is illustrated.

  1. Occurrence of Sporadic -E layer during the Ending Phase of Solar Cycle 23rd and Rising Phase of Solar Cycle 24th over the Anomaly Crest Region Bhopal

    NASA Astrophysics Data System (ADS)

    Bhawre, Purushottam; Gwal, Ashok Kumar; Tripathi, Sharad Chandra; Mansoori, Azad Ahmad; Aslam A., M.; Khan, Parvaiz A.; Purohit, Pramod K.; Waheed, Malik Abdul; Khatarkar, Prakash

    Ionospheric anomaly crest regions are most challenging for scientific community to understand its mechanism and investigation, for this purpose we are investigating some inospheric result for this region. The study is based on the ionogram data recorded by IPS-71 Digital Ionosonde installed over anomaly crust region Bhopal (Geo.Lat.23.2° N, Geo. Long77.4° E, Dip latitude18.4°) over a four year period from January 2007 to December 2010, covering the ending phase of 23rd Solar Cycle and starting phase of 24th solar cycle. This particular period is felt to be very suitable for examining the sunspot number and it encompasses periods of low solar activities. Quarterly ionograms are analyzed for 24 hours during these study years and have been carefully examined to note down the presence of sporadic- E. We also note down the space weather activities along with the study. The studies are divided in mainly four parts with space and geomagnetic activities during these periods. The occurrence probability of this layer is highest in summer solstice, moderate during equinox and low during winter solstice. Remarkable occurrence peaks appear from June to July in summer and from December to January in winter. The layer occurrence showed a double peak variation with distinct layer groups, in the morning (0200 LT) and the other during evening (1800 LT).The morning layer descent was associated with layer density increase indicating the strengthening of the layer while it decreased during the evening layer descent. The result indicates the presence of semi-diurnal tide over the location while the higher descent velocities could be due to the modulation of the ionization by gravity waves along with the tides. The irregularities associated with the gradient-drift instability disappear during the counter electrojet and the current flow is reversed in westward. Keyword: ionosphere, solar cycle, sporadic - E

  2. A report from the 23rd European Academy of Dermatology and Venereology Congress (October 8-12 - Amsterdam, The Netherlands).

    PubMed

    Rabasseda, X

    2014-10-01

    The 23rd Congress of the European Academy of Dermatology and Venereology started in Amsterdam with a day dedicated mostly to courses, during which electronic posters were also available. Scientists and researchers attending the conference had an opportunity for reviewing the latter investigations in dermatology through a series of computer terminals showing posters and allowing for e-mail discussions with the presenters. In a number of presentations, psoriasis was one of the major focuses of interest during EADV. New clinical research with emerging biologics and studies to validate the bioequivalence of biosimilars versus their originator monoclonal antibodies centered the scientific attractions towards which researchers and clinicians attending the conference were drawn. However, among the electronic posters at the conference, the results of initial clinical trials with a number of potential new therapies for other skin conditions were also presented. While shying away from psoriasis, a "late-breaking news in dermatology" session, wherein the results of clinical trials with innovative therapies for cutaneous diseases were reported, included large trials with established drugs aiming at novel indications, as well as first-in-human trials to validate the potential of investigational drugs. This and additional information and data reported during the conference and related with treatment for skin and skin structure diseases are summarized in the following report. PMID:25374969

  3. A Mission To Teach: The California State University, Channel Islands. A Review of the Board of Trustees' Proposal To Build a 23rd Campus. Commission Report.

    ERIC Educational Resources Information Center

    California State Postsecondary Education Commission, Sacramento.

    This report reviews the proposal by the California State University (CSU) to establish a 23rd campus to be know as California State University, Channel Islands. The proposed institution will be a full-service campus with a lower division, upper division, and graduate educational services, located in a former state hospital in Ventura County. The…

  4. "Intelligence and Civilisation": A Ludwig Mond Lecture Delivered at the University of Manchester on 23rd October 1936 by Godfrey H. Thomson. A Reprinting with Background and Commentary

    ERIC Educational Resources Information Center

    Deary, Ian J.; Lawn, Martin; Brett, Caroline E.; Bartholomew, David J.

    2009-01-01

    Here we reprint, and provide background and a commentary on, a recently-rediscovered lecture by Godfrey H. Thomson entitled, "Intelligence and civilisation." It was delivered at the University of Manchester, UK, on 23rd October, 1936, printed in 1937 in the short-lived "Journal of the University of Manchester" and as a pamphlet in Edinburgh. It…

  5. Literacy: Traditional, Cultural, Technological. Selected Papers from the Annual Conference of the International Association of School Librarianship (23rd, Pittsburgh, Pennsylvania, July 17-22, 1994).

    ERIC Educational Resources Information Center

    International Association of School Librarianship, Kalamazoo, MI.

    Themes of the 23rd Annual International Association of School Librarianship conference included "Traditional Literacy,""The Current Status of Libraries,""Literacy in a Technological World," and "Preserving Cultural and Historical Literacy." The following papers were presented at the conference: (1) "Bunko: Private Mini-Libraries for Children in…

  6. Teaching of Psychology: Ideas and Innovations. Proceedings of the Annual Conference on Undergraduate Teaching of Psychology (23rd, Tarrytown, New York, March 20-21, 2009)

    ERIC Educational Resources Information Center

    Howell-Carter, Marya, Ed.; Gonder, Jennifer, Ed.

    2009-01-01

    The document is a summary of the conference proceedings for the 23rd Annual Farmingdale State College Teaching of Psychology Conference held on March 20-21, 2009 at the DoubleTree Hotel in Tarrytown, New York. The conference featured a keynote address by Dr. Jeffrey Nevid on Reaching and teaching the millennials: Helping today's students become…

  7. Avionics for a Small Robotic Inspection Spacecraft

    NASA Technical Reports Server (NTRS)

    Abbott, Larry; Shuler, Robert L., Jr.

    2005-01-01

    A report describes the tentative design of the avionics of the Mini-AERCam -- a proposed 7.5-in. (approximately 19-cm)-diameter spacecraft that would contain three digital video cameras to be used in visual inspection of the exterior of a larger spacecraft (a space shuttle or the International Space Station). The Mini-AERCam would maneuver by use of its own miniature thrusters under radio control by astronauts inside the larger spacecraft. The design of the Mini-AERCam avionics is subject to a number of constraints, most of which can be summarized as severely competing requirements to maximize radiation hardness and maneuvering, image-acquisition, and data-communication capabilities while minimizing cost, size, and power consumption. The report discusses the design constraints, the engineering approach to satisfying the constraints, and the resulting iterations of the design. The report places special emphasis on the design of a flight computer that would (1) acquire position and orientation data from a Global Positioning System receiver and a microelectromechanical gyroscope, respectively; (2) perform all flight-control (including thruster-control) computations in real time; and (3) control video, tracking, power, and illumination systems.

  8. Nano-Satellite Avionics

    NASA Technical Reports Server (NTRS)

    Culver, Harry

    1999-01-01

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

  9. Future Avionics for X2K

    NASA Technical Reports Server (NTRS)

    Karmon, D.; Chau, S.

    1999-01-01

    The JPL X2000 program is for the delivery of advanced avionics systems, cutting edge technologies, and avionics components to spacecraft/orbiter, micro/nano-spacecraft, and in-situ missions. The objective is to develop and deliver avionics systems that will serve a multitude of future missions over the next 12 to 15 years.

  10. Avionics test bed development plan

    NASA Technical Reports Server (NTRS)

    Harris, L. H.; Parks, J. M.; Murdock, C. R.

    1981-01-01

    A development plan for a proposed avionics test bed facility for the early investigation and evaluation of new concepts for the control of large space structures, orbiter attached flex body experiments, and orbiter enhancements is presented. A distributed data processing facility that utilizes the current laboratory resources for the test bed development is outlined. Future studies required for implementation, the management system for project control, and the baseline system configuration are defined. A background analysis of the specific hardware system for the preliminary baseline avionics test bed system is included.

  11. Modular standards for emerging avionics technologies

    NASA Astrophysics Data System (ADS)

    Radcliffe, B.; Boaz, J.

    The present investigation is concerned with modular standards for the integration of new avionics technologies into production aircraft, taking into account also major retrofit programs. It is pointed out that avionics systems are about to undergo drastic changes in the partitioning of functions and judicious sharing of resources. These changes have the potential to significantly improve reliability and maintainability, and to reduce costs. Attention is given to a definition of the modular avionics concept, the existing module program, the development approach, development progress on the modular avionics standard, and the future of avionics installation standards.

  12. Security audit for embedded avionics systems

    NASA Astrophysics Data System (ADS)

    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.

  13. Integrated avionics studies target future technologies

    NASA Astrophysics Data System (ADS)

    Reilly, R. A.; Smead, F. W.; Ward, C. R.

    1981-02-01

    The modular, multifunction, multiband airborne radio system design program (MFBARS) for avionics integration is discussed. The program details a system for all communications, navigation and identification (CNI) functions from 2 MHz to 2 GHz. The first design approach characterized retains the CNI functions as separate entities with size and cost economies coming predominantly from incorporating standardized and miniaturized building blocks in a circuit-level and subsystem-level redesign. The second approach integrates the functions to reduce the total number of circuits and modules with one set of core hardware shared by all or many of the CNI activities. Three system architectures are proposed and schematized. It is noted that the greatest overall savings would be provided by implementing time-sharing, converting signals into digital format early in the signal processing sequence, and using common modules.

  14. EVA Communications Avionics and Informatics

    NASA Technical Reports Server (NTRS)

    Carek, David Andrew

    2005-01-01

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

  15. Avionics Maintenance Technology Program Guide.

    ERIC Educational Resources Information Center

    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. Multi-Platform Avionics Simulator

    NASA Technical Reports Server (NTRS)

    Clark, Micah; Steinke, Robert; McMahon, Elihu

    2006-01-01

    Multi-Platform Avionics Simulator (MPAvSim) is a software library for development of simulations of avionic hardware. MPAvSim facilitates simulation of interactions between flight software and such avionic peripheral equipment as telecommunication devices, thrusters, pyrotechnic devices, motor controllers, and scientific instruments. MPAvSim focuses on the behavior of avionics as seen by flight software, rather than on performing high-fidelity simulations of dynamics. However, MPAvSim is easily integrable with other programs that do perform such simulations. MPAvSim makes it possible to do real-time partial hardware- in-the-loop simulations. An MPAvSim simulation consists of execution chains (see figure) represented by flow graphs of models, defined here as stateless procedures that do some work. During a simulation, MPAvSim walks the execution chain, running each model in turn. Using MPAvSim, flight software can be run against a spacecraft that is all simulation, all hardware, or part hardware and part simulation. With respect to a specific piece of hardware, either the hardware itself or its simulation can be plugged in without affecting the rest of the system. Thus, flight software can be tested before hardware is available, and as items of hardware become available, they can be substituted for their simulations, with minimal disruption.

  17. High security optical tags for automotive/avionics parts anticounterfeiting

    NASA Astrophysics Data System (ADS)

    Boisdur, Enrick; Gesbert, Denis; Kress, Bernard

    2010-04-01

    Horus technologies develops novel optical tags based on planar digital micro-optics. These tags are calculated by computer, fabricated as masters via optical microlithography and replicated in mass by plastic embossing. Such tags are composed of several different levels of anti-counterfeating features, ranging from traditional holographic patterns, to OVIDs, to micro-holograms, to machine readable digital holograms storing holographic 1D and 2D bar codes. These tags have a double aim: anti-counterfeating of automotive/avionic parts and providing the engineer using an appropriate tag reader with all the technical information referring to these parts.

  18. High density modular avionics packaging

    NASA Astrophysics Data System (ADS)

    Poradish, F.

    Requirements and design configurations for high density modular avionics packaging are examined, with particular attention given to new hardware trends, the design of high-density standard modules (HDSM's), and HDSM requirements. The discussion of the HDSM's covers thermal management, system testability, power supply, and performance specifications. The general design of an integrated HDSM demonstration system currently under construction is briefly described, and some test data are presented.

  19. Single event upset in avionics

    SciTech Connect

    Taber, A. ); Normand, E. )

    1993-04-01

    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.

  20. SOFIA Gets Avionics and Mission Systems Upgrades

    NASA Video Gallery

    NASA's Stratospheric Observatory for Infrared Astronomy, or SOFIA, has received major upgrades to its telescope control and avionics systems that will significantly improve their efficiency and ope...

  1. High performance backplane components for modular avionics

    NASA Astrophysics Data System (ADS)

    Groves-Kirkby, C. J.; Goodwin, M. J.; Hall, J. P.; Glynn, G.; Hankey, J.; Salik, M. D.; Goodfellow, R. C.; Jibb, D. J.

    1994-10-01

    The design and development of optoelectronic transceiver and optical pathway components for application in a modular avionics backplane demonstrator system are described and initial performance results are presented.

  2. Advanced Avionics Breadboard Executive Design and Implementation

    NASA Technical Reports Server (NTRS)

    Adams, L. R.

    1972-01-01

    The advanced avionics breadboard (AAB) executive evolved from an effort to design and develop an avionics system. This executive is unique in that it supervises a triple redundant avionics computer system. Three IBM System 4 Pi/CP computers, operating synchronously and executing identical software, comprise the central processors which route data to and from a data bus via an input/output controller. The executive's basic function is to provide application programs with an efficient software structure within which to perform specific avionics application tasks. Although implemented in a triplex data management system, the AAB executive contains the flexibility to be adapted to other systems with minimal change.

  3. Will Today's Electronic Journals Be Accessible in the 23rd Century: Issues in Long-Term Archiving (SIG STI, IFP)

    ERIC Educational Resources Information Center

    Lippert, Margaret

    2000-01-01

    This abstract of a planned session on access to scientific and technical journals addresses policy and standard issues related to long-term archives; digital archiving models; economic factors; hardware and software issues; multi-publisher electronic journal content integration; format considerations; and future data migration needs. (LRW)

  4. ARINC 818 specification revisions enable new avionics architectures

    NASA Astrophysics Data System (ADS)

    Grunwald, Paul

    2014-06-01

    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.

  5. Transmission of RF Signals Over Optical Fiber for Avionics Applications

    NASA Technical Reports Server (NTRS)

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

    2002-01-01

    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.

  6. Abstracts of the 23rd Annual Conference of the International Society of Environmental Epidemiology (ISEE). September 13 - 16, 2011, Barcelona, Spain.

    PubMed

    2011-09-01

    The International Society for Environmental Epidemiology (ISEE) is an international organization with almost 1000 members from more than 60 countries. The annual international conference brings together many members and non-members and provides an excellent forum for the discussion of problems and benefits related to the environment and human health. Specific themes for the 23rd Annual Conference include: Sustainable transport and health: Impact of transport on health and approaches to reduce health impacts, Impact of climate change: from water scarcity to Saharan dust episodes, Early exposure - later life: in utero and early life exposures and effects in later life, New methods and technologies. PMID:21896395

  7. Fiber-Optic Network Architectures for Onboard Avionics Applications Investigated

    NASA Technical Reports Server (NTRS)

    Nguyen, Hung D.; Ngo, Duc H.

    2003-01-01

    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. An avionics scenario and command model description for Space Generic Open Avionics Architecture (SGOAA)

    NASA Technical Reports Server (NTRS)

    Stovall, John R.; Wray, Richard B.

    1994-01-01

    This paper presents a description of a model for a space vehicle operational scenario and the commands for avionics. This model will be used in developing a dynamic architecture simulation model using the Statemate CASE tool for validation of the Space Generic Open Avionics Architecture (SGOAA). The SGOAA has been proposed as an avionics architecture standard to NASA through its Strategic Avionics Technology Working Group (SATWG) and has been accepted by the Society of Automotive Engineers (SAE) for conversion into an SAE Avionics Standard. This architecture was developed for the Flight Data Systems Division (FDSD) of the NASA Johnson Space Center (JSC) by the Lockheed Engineering and Sciences Company (LESC), Houston, Texas. This SGOAA includes a generic system architecture for the entities in spacecraft avionics, a generic processing external and internal hardware architecture, and a nine class model of interfaces. The SGOAA is both scalable and recursive and can be applied to any hierarchical level of hardware/software processing systems.

  9. Recovery of the Space Shuttle Columbia Avionics

    NASA Technical Reports Server (NTRS)

    Hames, Kevin L.

    2003-01-01

    Lessons Learned: a) Avionics data can playa critical role in the investigation of a "close call" or accident. b) Avionics designers should think about the role their systems might play in an investigation. c) Know your data, down to the bit level. d) Know your spacecraft - follow the data. e) Internal placement of circuit cards can affect their survivability. f) Think about how to reconstruct nonvolatile memory (e.g. serialize IC's, etc.) g) Use of external assets can aid in extracting data from avionics.

  10. Space Launch and Temperature System: Avionics System

    NASA Technical Reports Server (NTRS)

    Gillis, Amelia; Luna, Steve; Schrock, Ken; Howard, Ricky; Kilpatrick, John (Technical Monitor)

    2001-01-01

    This paper outlines the approach needed to develop the avionics system for a Space Launch and Transportation System. Avionics systems development, power, range safety, and simulations considerations are covered. Each of these topics includes the project design inputs that must be considered on the outset. Process steps are then provided to obtain the desired outputs. This paper discusses the importance of starting and staying with an overall systems plan that ensures that all avionics internal and external requirements are fulfilled. Key design, development, testing and implementations considerations are provided.

  11. Generalized Nanosatellite Avionics Testbed Lab

    NASA Technical Reports Server (NTRS)

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

    2015-01-01

    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.

  12. Demonstration Advanced Avionics System (DAAS), Phase 1

    NASA Technical Reports Server (NTRS)

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

    1981-01-01

    Demonstration advanced anionics system (DAAS) function description, hardware description, operational evaluation, and failure mode and effects analysis (FMEA) are provided. Projected advanced avionics system (PAAS) description, reliability analysis, cost analysis, maintainability analysis, and modularity analysis are discussed.

  13. Avionics and controls research and technology

    NASA Technical Reports Server (NTRS)

    Rediess, H. A. (Editor); Mciver, D. E. (Editor)

    1979-01-01

    The workshop provided a forum for industry and universities to discuss the state-of-the-art, identify the technology needs and opportunities, and describe the role of NASA in avionics and controls research.

  14. Avionics Box Cold Plate Damage Prevention

    NASA Technical Reports Server (NTRS)

    Stambolian, Damon; Larcher, Steven; Henderson, Gena; Tran, Donald

    2011-01-01

    Over the years there have been several occurrences of damage to Space Shuttle Orbiter cold plates during removal and replacement of avionics boxes. Thus a process improvement team was put together to determine ways to prevent these kinds of damage. From this effort there were many solutions including, protective covers, training, and improved operations instructions. The focus of this paper is to explain the cold plate damage problem and the corrective actions for preventing future damage to aerospace avionics cold plate designs.

  15. Avionics Simulation, Development and Software Engineering

    NASA Technical Reports Server (NTRS)

    2002-01-01

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

  16. Space Tug Avionics Definition Study. Volume 5: Cost and Programmatics

    NASA Technical Reports Server (NTRS)

    1975-01-01

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

  17. Lean spacecraft avionics trade study

    NASA Technical Reports Server (NTRS)

    Main, John A.

    1994-01-01

    Spacecraft design is generally an exercise in design trade-offs: fuel vs. weight, power vs. solar cell area, radiation exposure vs. shield weight, etc. Proper analysis of these trades is critical in the development of lightweight, efficient, 'lean' satellites. The modification of the launch plans for the Magnetosphere Imager (MI) to a Taurus launcher from the much more powerful Delta has forced a reduction in spacecraft weight availability into the mission orbit from 1300 kg to less than 500 kg. With weight now a driving factor it is imperative that the satellite design be extremely efficient and lean. The accuracy of engineering trades now takes on an added importance. An understanding of spacecraft subsystem interactions is critical in the development of a good spacecraft design, yet it is a challenge to define these interactions while the design is immature. This is currently an issue in the development of the preliminary design of the MI. The interaction and interfaces between this spacecraft and the instruments it carries are currently unclear since the mission instruments are still under development. It is imperative, however, to define these interfaces so that avionics requirements ideally suited to the mission's needs can be determined.

  18. Selected papers from the 23rd MicroMechanics and Microsystems Europe Workshop (MME 2012) (Ilmenau, Germany, September 9-12, 2012)

    NASA Astrophysics Data System (ADS)

    Hoffmann, Martin

    2013-07-01

    In September 2012, the 23rd MicroMechanics Europe Workshop (MME) took place in Ilmenau, Germany. With about 120 participants from 20 countries and 76 accepted presentations, the workshop series turned out to be a successful platform for young scientists to present their work to our scientific community. Traditionally, the interaction is an important aspect of this workshop: while short presentations introduce the posters, an extended poster session allows intensive discussion which is quite useful to the participants. The discussion very often extends into the breaks and the evening events. It is also encouraging for them that the best presentations are selected and invited to submit a full paper to this journal. Thanks to the support of IOP Publishing, this next logical step to present work to the scientific world is made possible. In this issue, you can find the best papers that have been selected by a committee during the workshop taking the written workshop contribution, the poster and the presentation into account. Again, all areas of micromechanics from new technology developments up to systems integration were presented at the workshop at different levels of completion. The selected papers present those results which are almost complete. Nevertheless, it is nice to see that in some cases topics grow over the years from 'nice ideas' to realized system concepts. And although this is the 23rd workshop, it is clear that micromechanics is a topic that is not running short of new ideas. First, I would like to thank the authors of the selected papers for each of their individual excellent contributions. My gratitude also goes to my fellow members in the programme committee (Per Ohlckers, Martin Hill and Sami Franssila) for their cooperation in the selection of invited speakers and submitted papers, as well as the anonymous Journal of Micromechanics and Microengineering (JMM) reviewers for their careful selection of the final papers presented here. Last, but not

  19. Remarks on Sentinel-1 Avionic SW Qualification

    NASA Astrophysics Data System (ADS)

    Candia, Sante; Pascucci, Dario

    2013-08-01

    The GMES Sentinel-1 Earth Radar Observatory, a projects co-funded by the European Union and the European Space Agency (ESA), is a constellation of C-band radar satellites. The satellites have been conceived to be a continuous and reliable source of C-band SAR imagery for operational application such as mapping of global landmasses, coastal zones and monitoring of shipping routes. ESA is responsible for the development of the Sentinel-1 satellites that are built by an industrial consortium headed by Thales Alenia Space Italy (TASI) as Prime Contractor. TAS-I is also directly responsible for the production of the Spacecraft Bus and the Avionic S/S including the Avionic SW (ASW), which is characterized by: · The high performances of its attitude and orbit determination and control function; · Scheduling of the imaging activity on position basis with high geo-location performances; · High on board autonomy both in routine and contingency situations. This paper is focused on the Sentinel-1 Avionic SW, which has currently been qualified by TAS-I for Flight. It covers both the SW architecture and development process areas: · Avionic SW context; · Avionic SW architecture; · Flexibility of PUS-based on-board autonomy and FDIR; · Validation and Qualification activities;

  20. Alternate concepts study extension. Volume 2: Part 4: Avionics

    NASA Technical Reports Server (NTRS)

    1971-01-01

    A recommended baseline system is presented along with alternate avionics systems, Mark 2 avionics, booster avionics, and a cost summary. Analyses and discussions are included on the Mark 1 orbiter avionics subsystems, electrical ground support equipment, and the computer programs. Results indicate a need to define all subsystems of the baseline system, an installation study to determine the impact on the crew station, and a study on access for maintenance.

  1. Reconfigurable fault tolerant avionics system

    NASA Astrophysics Data System (ADS)

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

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

  2. Systems Engineering and Reusable Avionics

    NASA Technical Reports Server (NTRS)

    Conrad, James M.; Murphy, Gloria

    2010-01-01

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

  3. Applying Ada to Beech Starship avionics

    NASA Technical Reports Server (NTRS)

    Funk, David W.

    1986-01-01

    As Ada solidified in its development, it became evident that it offered advantages for avionics systems because of it support for modern software engineering principles and real time applications. An Ada programming support environment was developed for two major avionics subsystems in the Beech Starship. The two subsystems include electronic flight instrument displays and the flight management computer system. Both of these systems use multiple Intel 80186 microprocessors. The flight management computer provides flight planning, navigation displays, primary flight display of checklists and other pilot advisory information. Together these systems represent nearly 80,000 lines of Ada source code and to date approximately 30 man years of effort. The Beech Starship avionics systems are in flight testing.

  4. Avionic System for the CIRA USV Program

    NASA Astrophysics Data System (ADS)

    Capuano, G.; Longobardi, P.; Cacace, F.; Richiello, C.; Di Donato, M. P.

    2007-08-01

    This paper describes the Avionic System that TSDev has developed for the Centro Italiano Ricerche Aerospaziali (CIRA) Flight Test Bed (FTB) in the framework of the Italian Unmanned Space Vehicle (USV) program. The FTB Avionic System is composed by a number of units able to provide the vehicle with all the functionality required by an unmanned aerospace flight. The architecture of the avionics has been defined so to guarantee modularity, upgradeability, and high performances. Custom solutions for most of the required functionality have allowed to fulfil the very demanding requirements in terms of mass, power, and volume. Very interesting reliability levels have been obtained by properly selecting the components and adopting hot redundancy at least for the most critical functions.

  5. Broadband antireflection coatings for multifunctional avionic displays

    NASA Astrophysics Data System (ADS)

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

    2015-06-01

    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.

  6. Human Exploration and Avionic Technology Challenges

    NASA Technical Reports Server (NTRS)

    Benjamin, Andrew L.

    2005-01-01

    For this workshop, I will identify critical avionic gaps, enabling technologies, high-pay off investment opportunities, promising capabilities, and space applications for human lunar and Mars exploration. Key technology disciplines encompass fault tolerance, miniaturized instrumentation sensors, MEMS-based guidance, navigation, and controls, surface communication networks, and rendezvous and docking. Furthermore, I will share bottom-up strategic planning relevant to manned mission -driven needs. Blending research expertise, facilities, and personnel with internal NASA is vital to stimulating collaborative technology solutions that achieve NASA grand vision. Retaining JSC expertise in unique and critical areas is paramount to our long-term success. Civil servants will maintain key roles in setting technology agenda, ensuring quality results, and integrating technologies into avionic systems and manned missions. Finally, I will present to NASA, academia, and the aerospace community some on -going and future advanced avionic technology programs and activities that are relevant to our mission goals and objectives.

  7. Wireless optical links for avionics applications

    NASA Astrophysics Data System (ADS)

    Chan, Eric; Koshinz, Dennis; Krug, William; Hager, Harold

    2011-06-01

    Recently there has been strong interest in wireless optical (WO) communication link applications in airplanes and avionics platforms for size, weight, power, cost, and electromagnetic interference (EMI) reduction. Wireless optical link has additional advantage of providing network security because the optical signal from wireless optical link is well confined within an airplane or avionics vehicle. In this paper we discuss some potential wireless optical link applications in commercial airplanes and the challenges in the implementation of wireless optical links for these applications. We will present our experimental results on using white LED (WLED), visible laser source and free-space small-form-factor (SFF) optical transceivers to demonstrate the viability of applying wireless optical links in avionics platforms.

  8. Infrared Avionics Signal Distribution Using WDM

    NASA Technical Reports Server (NTRS)

    Atiquzzaman, Mohammed; Sluss, James J., Jr.

    2004-01-01

    Supporting analog RF signal transmission over optical fibers, this project demonstrates a successful application of wavelength division multiplexing (WDM) to the avionics environment. We characterize the simultaneous transmission of four RF signals (channels) over a single optical fiber. At different points along a fiber optic backbone, these four analog channels are sequentially multiplexed and demultiplexed to more closely emulate the conditions in existing onboard aircraft. We present data from measurements of optical power, transmission response (loss and gain), reflection response, group delay that defines phase distortion, signal-to-noise ratio (SNR), and dynamic range that defines nonlinear distortion. The data indicate that WDM is very suitable for avionics applications.

  9. Avionics-compatible video facial cognizer for detection of pilot incapacitation.

    PubMed

    Steffin, Morris

    2006-01-01

    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

  10. Development and implementation of the verification process for the shuttle avionics system

    NASA Technical Reports Server (NTRS)

    Smith, H. E.; Fouts, W. B.; Mesmer, J.

    1985-01-01

    The background of the shuttle avionics system design and the unique drivers associated with the redundant digital multiplexed data processing system are examined. With flight software pervading to the lowest elements of the flight critical subsystems, it was necessary to identify a unique and orderly approach of verifying the system as flight ready for STS-1. The approach and implementation plan is discussed, and both technical problems and management issues are dealt with.

  11. Philosophy of Education, 1974-1975. Proceedings of the Annual Meeting of the Far Western Philosophy of Education Society (23rd, Long Beach, California, December 6-7, 1974).

    ERIC Educational Resources Information Center

    Jelinek, James J., Ed.

    The proceedings of the 23rd annual meeting of the Far Western Philosophy of Education Society in 1974 are presented. The proceedings consist of 16 addresses. Titles include (1) Leonard Abraham Fels, 1911-1974: A Memoriale; (2) Trying to Make Sense out of "Existential Thought and Education"; (3) Making Sense out of "Existential Thought and…

  12. Mathematics Education beyond 2000: Proceedings of the Annual Meeting of the Mathematics Education Research Group of Australasia (23rd, Fremantle, Western Australia, Australia, July 5-9, 2000). Volume 1 [and] Volume 2.

    ERIC Educational Resources Information Center

    Bana, Jack, Ed.; Chapman, Anne, Ed.

    This document contains Volumes 1 and 2 of the proceedings of the 23rd annual conference of the Mathematics Education Research Group of Australasia Incorporated (MERGA) held at Fremantle, Western Australia, July 5-9, 2000. Papers in Volume 1 include: (1) "Bridging Practices: Intertwining Content and Pedagogy in Teaching and Learning To Teach"…

  13. Avionics Architectures for Exploration: Building a Better Approach for (Human) Spaceflight Avionics

    NASA Technical Reports Server (NTRS)

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

    2014-01-01

    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.

  14. Digital Optical Circuit Technology

    NASA Technical Reports Server (NTRS)

    Dove, B. L. (Editor)

    1985-01-01

    The Proceedings for the 48th Meeting of the AGARD Avionics Panel contain the 18 papers presented a Technical Evaluation Report, and discussions that followed the presentations of papers. Seven papers were presented in the session devoted to optical bistability. Optical logic was addressed by three papers. The session on sources, modulators and demodulators presented three papers. Five papers were given in the final session on all optical systems. The purpose of this Specialists' Meeting was to present the research and development status of digital optical circuit technology and to examine its relevance in the broad context of digital processing, communication, radar, avionics and flight control systems implementation.

  15. Ares I Crew Launch Vehicle Upper Stage Avionics and Software Overview

    NASA Technical Reports Server (NTRS)

    Nola, Charles L.

    2008-01-01

    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.

  16. Reuse and Interoperability of Avionics for Space Systems

    NASA Technical Reports Server (NTRS)

    Hodson, Robert F.

    2007-01-01

    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.

  17. Avionics Instrument Systems Specialist (AFSC 32551).

    ERIC Educational Resources Information Center

    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);…

  18. Reliability measurement for operational avionics software

    NASA Technical Reports Server (NTRS)

    Thacker, J.; Ovadia, F.

    1979-01-01

    Quantitative measures of reliability for operational software in embedded avionics computer systems are presented. Analysis is carried out on data collected during flight testing and from both static and dynamic simulation testing. Failure rate is found to be a useful statistic for estimating software quality and recognizing reliability trends during the operational phase of software development.

  19. Systems engineering and integration: Advanced avionics laboratories

    NASA Technical Reports Server (NTRS)

    1990-01-01

    In order to develop the new generation of avionics which will be necessary for upcoming programs such as the Lunar/Mars Initiative, Advanced Launch System, and the National Aerospace Plane, new Advanced Avionics Laboratories are required. To minimize costs and maximize benefits, these laboratories should be capable of supporting multiple avionics development efforts at a single location, and should be of a common design to support and encourage data sharing. Recent technological advances provide the capability of letting the designer or analyst perform simulations and testing in an environment similar to his engineering environment and these features should be incorporated into the new laboratories. Existing and emerging hardware and software standards must be incorporated wherever possible to provide additional cost savings and compatibility. Special care must be taken to design the laboratories such that real-time hardware-in-the-loop performance is not sacrificed in the pursuit of these goals. A special program-independent funding source should be identified for the development of Advanced Avionics Laboratories as resources supporting a wide range of upcoming NASA programs.

  20. Developing Generic Software for Spacecraft Avionics

    NASA Technical Reports Server (NTRS)

    Smith, Joseph

    2003-01-01

    A proposed approach to the development of software for spacecraft avionics is based partly on a concept of generic software that could be tailored to satisfy requirements for specific missions. The proposed approach would stand in contrast to the conventional approach of first defining avionics requirements for a specific mission, then developing software specific to those requirements. The proposed approach might also be adaptable to programming computers that control and monitor other complex equipment systems that range in scale from automobiles to factories. The concept of a spacecraft avionics functional model (SAFM) is a major element of the proposed approach. An SAFM would be, essentially, a systematic and hierarchical description of the functionality required of the avionics software (and hardware) for a given mission. Although the initial input information used to start the construction of an SAFM would typically amount to a high-level description, the SAFM would thereafter be decomposed to a low level. The resulting low-level version of the model would be used to develop a set of generic requirements that could be expected to include a large fraction of all requirements for a large fraction of all missions. The generic requirements would be used to develop software modules that could be included in, or excluded from, the final flight software to satisfy the requirements of a specific mission.

  1. Avionics. Progress Record and Theory Outline.

    ERIC Educational Resources Information Center

    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,…

  2. Generalized Training Devices for Avionic Systems Maintenance.

    ERIC Educational Resources Information Center

    Parker, Edward L.

    A research study was conducted to determine the feasibility and desirability of developing generalized training equipment for use in avionic systems maintenance training. The study consisted of a group of survey and analytic tasks to provide useful guidance to serve the needs of the Naval Aviation community in future years. The study had four…

  3. Reference Avionics Architecture for Lunar Surface Systems

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

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

  4. Simulating Avionics Upgrades to the Space Shuttles

    NASA Technical Reports Server (NTRS)

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

    2008-01-01

    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.

  5. IBC’s 23rd Annual Antibody Engineering, 10th Annual Antibody Therapeutics International Conferences and the 2012 Annual Meeting of The Antibody Society

    PubMed Central

    Klöhn, Peter-Christian; Wuellner, Ulrich; Zizlsperger, Nora; Zhou, Yu; Tavares, Daniel; Berger, Sven; Zettlitz, Kirstin A.; Proetzel, Gabriele; Yong, May; Begent, Richard H.J.; Reichert, Janice M

    2013-01-01

    The 23rd Annual Antibody Engineering, 10th Annual Antibody Therapeutics international conferences, and the 2012 Annual Meeting of The Antibody Society, organized by IBC Life Sciences with contributions from The Antibody Society and two Scientific Advisory Boards, were held December 3–6, 2012 in San Diego, CA. The meeting drew over 800 participants who attended sessions on a wide variety of topics relevant to antibody research and development. As a prelude to the main events, a pre-conference workshop held on December 2, 2012 focused on intellectual property issues that impact antibody engineering. The Antibody Engineering Conference was composed of six sessions held December 3–5, 2012: (1) From Receptor Biology to Therapy; (2) Antibodies in a Complex Environment; (3) Antibody Targeted CNS Therapy: Beyond the Blood Brain Barrier; (4) Deep Sequencing in B Cell Biology and Antibody Libraries; (5) Systems Medicine in the Development of Antibody Therapies/Systematic Validation of Novel Antibody Targets; and (6) Antibody Activity and Animal Models. The Antibody Therapeutics conference comprised four sessions held December 4–5, 2012: (1) Clinical and Preclinical Updates of Antibody-Drug Conjugates; (2) Multifunctional Antibodies and Antibody Combinations: Clinical Focus; (3) Development Status of Immunomodulatory Therapeutic Antibodies; and (4) Modulating the Half-Life of Antibody Therapeutics. The Antibody Society’s special session on applications for recording and sharing data based on GIATE was held on December 5, 2012, and the conferences concluded with two combined sessions on December 5–6, 2012: (1) Development Status of Early Stage Therapeutic Antibodies; and (2) Immunomodulatory Antibodies for Cancer Therapy. PMID:23575266

  6. On-Board Fiber-Optic Network Architectures for Radar and Avionics Signal Distribution

    NASA Technical Reports Server (NTRS)

    Alam, Mohammad F.; Atiquzzaman, Mohammed; Duncan, Bradley B.; Nguyen, Hung; Kunath, Richard

    2000-01-01

    Continued progress in both civil and military avionics applications is overstressing the capabilities of existing radio-frequency (RF) communication networks based on coaxial cables on board modem aircrafts. Future avionics systems will require high-bandwidth on- board communication links that are lightweight, immune to electromagnetic interference, and highly reliable. Fiber optic communication technology can meet all these challenges in a cost-effective manner. Recently, digital fiber-optic communication systems, where a fiber-optic network acts like a local area network (LAN) for digital data communications, have become a topic of extensive research and development. Although a fiber-optic system can be designed to transport radio-frequency (RF) signals, the digital fiber-optic systems under development today are not capable of transporting microwave and millimeter-wave RF signals used in radar and avionics systems on board an aircraft. Recent advances in fiber optic technology, especially wavelength division multiplexing (WDM), has opened a number of possibilities for designing on-board fiber optic networks, including all-optical networks for radar and avionics RF signal distribution. In this paper, we investigate a number of different novel approaches for fiber-optic transmission of on-board VHF and UHF RF signals using commercial off-the-shelf (COTS) components. The relative merits and demerits of each architecture are discussed, and the suitability of each architecture for particular applications is pointed out. All-optical approaches show better performance than other traditional approaches in terms of signal-to-noise ratio, power consumption, and weight requirements.

  7. SMART: The Future of Spaceflight Avionics

    NASA Technical Reports Server (NTRS)

    Alhorn, Dean C.; Howard, David E.

    2010-01-01

    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

  8. Kiloelectronvolt X-rays Emitted from the Earth's Atmosphere During the Peak and Descending Phases of the 23rd Solar Activity Cycle

    NASA Astrophysics Data System (ADS)

    Spjeldvik, Walther; Gusev, Anatoly; Pugacheva, Galina; Martin, Inacio

    We have studied long-term observations of the low-energy, 3 to 8 keV, X-ray emission during the period July 2001 through December 2005. The data were obtained with CadmiumTelluride (CdTe) solid state detectors flown on the LEO CORONAS-F satellite and used to assess the dynamics of X-ray fluxes radiated by the Earth’s upper atmosphere during the peak and declining phases of the 23rd solar cycle as observed within the shadowed segments of the spacecraft trajectory. We present empirical maps of near-global distributions soft X-ray luminescence with data emphasis on northern hemisphere summer and winter conditions. These observations reveal some irregularities, and the maximum X-ray photon energy does not exceed about 8 keV. We found that the X-rays exhibit seasonal variations in addition to the expected dependence on solar activity levels, and there are definite latitudinal and longitudinal patterns. In year 2001, during the solar maximum activity, the 3 to 8 keV X-ray flux reached a maximum of 170 photons/(cm2 s sr) in the geographic northwestern part of the Earth. The luminosity of the brightest soft X-ray atmospheric emission spot was about 40 kW integrated over an upward atmospheric emission geographic area of 200º longitude and 20º latitude as seem at altitude of about 500 km. For comparison, typical auroral emissions in this soft X-ray band is around 10 to 30 MW. We argue that these X-ray fluxes cannot be scattered solar X-rays since solar X-rays are most often lower in photon energy (< 2 keV) and also lower in intensity -- except in short-lived events. We interpret our observations as being due to Bremsstrahlung X-rays resulting from magnetospheric electrons precipitating into the atmosphere from the radiation belts and depositing their kinetic energy there, an energetic electron precipitation flux that is modulated by electromagnetic disturbances such as magnetospheric ELF waves during and following magnetic storms and substorms, terrestrial lightning

  9. IBC's 23rd Antibody Engineering and 10th Antibody Therapeutics Conferences and the Annual Meeting of The Antibody Society: December 2-6, 2012, San Diego, CA.

    PubMed

    Marquardt, John; Begent, Richard H J; Chester, Kerry; Huston, James S; Bradbury, Andrew; Scott, Jamie K; Thorpe, Philip E; Veldman, Trudi; Reichert, Janice M; Weiner, Louis M

    2012-01-01

    Now in its 23rd and 10th years, respectively, the Antibody Engineering and Antibody Therapeutics conferences are the Annual Meeting of The Antibody Society. The scientific program covers the full spectrum of challenges in antibody research and development from basic science through clinical development. In this preview of the conferences, the chairs provide their thoughts on sessions that will allow participants to track emerging trends in (1) the development of next-generation immunomodulatory antibodies; (2) the complexity of the environment in which antibodies must function; (3) antibody-targeted central nervous system (CNS) therapies that cross the blood brain barrier; (4) the extension of antibody half-life for improved efficacy and pharmacokinetics (PK)/pharmacodynamics (PD); and (5) the application of next generation DNA sequencing to accelerate antibody research. A pre-conference workshop on Sunday, December 2, 2012 will update participants on recent intellectual property (IP) law changes that affect antibody research, including biosimilar legislation, the America Invents Act and recent court cases. Keynote presentations will be given by Andreas Plückthun (University of Zürich), who will speak on engineering receptor ligands with powerful cellular responses; Gregory Friberg (Amgen Inc.), who will provide clinical updates of bispecific antibodies; James D. Marks (University of California, San Francisco), who will discuss a systems approach to generating tumor targeting antibodies; Dario Neri (Swiss Federal Institute of Technology Zürich), who will speak about delivering immune modulators at the sites of disease; William M. Pardridge (University of California, Los Angeles), who will discuss delivery across the blood-brain barrier; and Peter Senter (Seattle Genetics, Inc.), who will present his vision for the future of antibody-drug conjugates. For more information on these meetings or to register to attend, please visit www

  10. IBC’s 23rd Antibody Engineering and 10th Antibody Therapeutics Conferences and the Annual Meeting of The Antibody Society

    PubMed Central

    Marquardt, John; Begent, Richard H.J.; Chester, Kerry; Huston, James S.; Bradbury, Andrew; Scott, Jamie K.; Thorpe, Philip E.; Veldman, Trudi; Reichert, Janice M.; Weiner, Louis M.

    2012-01-01

    Now in its 23rd and 10th years, respectively, the Antibody Engineering and Antibody Therapeutics conferences are the Annual Meeting of The Antibody Society. The scientific program covers the full spectrum of challenges in antibody research and development from basic science through clinical development. In this preview of the conferences, the chairs provide their thoughts on sessions that will allow participants to track emerging trends in (1) the development of next-generation immunomodulatory antibodies; (2) the complexity of the environment in which antibodies must function; (3) antibody-targeted central nervous system (CNS) therapies that cross the blood brain barrier; (4) the extension of antibody half-life for improved efficacy and pharmacokinetics (PK)/pharmacodynamics (PD); and (5) the application of next generation DNA sequencing to accelerate antibody research. A pre-conference workshop on Sunday, December 2, 2012 will update participants on recent intellectual property (IP) law changes that affect antibody research, including biosimilar legislation, the America Invents Act and recent court cases. Keynote presentations will be given by Andreas Plückthun (University of Zürich), who will speak on engineering receptor ligands with powerful cellular responses; Gregory Friberg (Amgen Inc.), who will provide clinical updates of bispecific antibodies; James D. Marks (University of California, San Francisco), who will discuss a systems approach to generating tumor targeting antibodies; Dario Neri (Swiss Federal Institute of Technology Zürich), who will speak about delivering immune modulators at the sites of disease; William M. Pardridge (University of California, Los Angeles), who will discuss delivery across the blood-brain barrier; and Peter Senter (Seattle Genetics, Inc.), who will present his vision for the future of antibody-drug conjugates. For more information on these meetings or to register to attend, please visit www

  11. Avionics system design for high energy fields: A guide for the designer and airworthiness specialist

    NASA Technical Reports Server (NTRS)

    Mcconnell, Roger A.

    1987-01-01

    Because of the significant differences in transient susceptibility, the use of digital electronics in flight critical systems, and the reduced shielding effects of composite materials, there is a definite need to define pracitices which will minimize electromagnetic susceptibility, to investigate the operational environment, and to develop appropriate testing methods for flight critical systems. The design practices which will lead to reduced electromagnetic susceptibility of avionics systems in high energy fields is described. The levels of emission that can be anticipated from generic digital devices. It is assumed that as data processing equipment becomes an ever larger part of the avionics package, the construction methods of the data processing industry will increasingly carry over into aircraft. In Appendix 1 tentative revisions to RTCA DO-160B, Environmental Conditions and Test Procedures for Airborne Equipment, are presented. These revisions are intended to safeguard flight critical systems from the effects of high energy electromagnetic fields. A very extensive and useful bibliography on both electromagnetic compatibility and avionics issues is included.

  12. Prognostics for Electronics Components of Avionics Systems

    NASA Technical Reports Server (NTRS)

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

    2009-01-01

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

  13. Demonstration Advanced Avionics System (DAAS) function description

    NASA Technical Reports Server (NTRS)

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

    1982-01-01

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

  14. Single-event effects in avionics

    SciTech Connect

    Normand, E.

    1996-04-01

    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.

  15. An Integrated Modular Avionics Development Environment

    NASA Astrophysics Data System (ADS)

    Schoofs, T.; Santos, S.; Tatibana, C.; Anjos, J.; Rufino, J.; Windsor, J.

    2009-05-01

    The ARINC 653 standard has taken a leading role within the aeronautical industry in the development of safety-critical systems based upon the Integrated Modular Avionics (IMA) concept. The related cost savings in reduced integration, verification and validation effort has raised interest in the European space industry for developing a spacecraft IMA approach and for the definition of an ARINC 653-for-Space software framework. As part of this process, it is necessary to establish an effective way to develop, test and analyse on-board applications without having access to the final IMA target platform for all engineers. Target platforms are usually extremely expensive considering hardware and software prices as well as training costs. This paper describes the architecture of an Integrated Modular Avionics Development Environment (IMADE) based on the Linux Operating System and the ARINC 653 simulator for Modular On-Board Applications that was developed by Skysoft Portugal, S.A. In cooperation with ESA, 2007-2008.

  16. Integration of Passive Components for Spacecraft Avionics

    NASA Technical Reports Server (NTRS)

    Brandon, E. J.; Wesseling, E.; White, V.; Lieneweg, U.; Mojarradi, M.; Ulrich, R.; Wasef, M.; Mantooth, A.

    2001-01-01

    The NASA roadmap outlining future deep space missions to Europa and other outer planetary destinations calls for continued reductions in the mass and volume of the spacecraft avionics. Spacecraft power electronics, including the power switches and converters, remain difficult to miniaturize due to the need for large numbers of discrete passive components such as resistors, capacitors, inductors and transformers. As part of the System-on-a-chip program at the Center for Integrated Space Microsystems and at the University of Arkansas, we are working to develop integrated or embedded passive components geared specifically for use in power management and distribution (PMAD) in future avionics over the next five to ten years. This will not only enable a scaling down of the power subsystems, but will make possible new architectures such as "distributed" PMAD. Additional information is contained in the original extended abstract.

  17. Advanced avionics concepts: Autonomous spacecraft control

    NASA Technical Reports Server (NTRS)

    1990-01-01

    A large increase in space operations activities is expected because of Space Station Freedom (SSF) and long range Lunar base missions and Mars exploration. Space operations will also increase as a result of space commercialization (especially the increase in satellite networks). It is anticipated that the level of satellite servicing operations will grow tenfold from the current level within the next 20 years. This growth can be sustained only if the cost effectiveness of space operations is improved. Cost effectiveness is operational efficiency with proper effectiveness. A concept is presented of advanced avionics, autonomous spacecraft control, that will enable the desired growth, as well as maintain the cost effectiveness (operational efficiency) in satellite servicing operations. The concept of advanced avionics that allows autonomous spacecraft control is described along with a brief description of each component. Some of the benefits of autonomous operations are also described. A technology utilization breakdown is provided in terms of applications.

  18. Avionics systems on a chip for space exploration

    NASA Astrophysics Data System (ADS)

    Alkalai, Leon; Kolawa, Elizabeth

    1999-01-01

    The advanced miniaturization of all the on-board spacecraft functions into a highly integrated, modular, and reliable architecture is a major enabling technology for future deep-space and Earth orbiting science missions. Avionics miniaturization using advanced deep sub-micron semiconductor digital, analog, as well as Micro Electro Mechanical Systems (MEMS) technologies will revolutionize the way we build future spacecraft systems. So called micro and nano satellites as well as other micro-systems are possible using these advanced technologies. In this paper, we present an overview of work in progress at the newly established JPL Center for Integrated Space Microsystems (CISM) in the area of Avionics Systems On a Chip Program. This long-term research and development program has been established as part of NASA's Advanced Deep Space Systems Program (a.k.a. X2000), which also has a near-term project-oriented element, as well as an even longer term research component called Revolutionary Computing Technologies. This paper will outline the vision, goals and scope of the SOAC program, as well as its target mission insertion opportunities. We also describe a technology roadmap from 1998 to 2006 leading to Systems On A Chip technology elements. Also described are the SOAC technology challenges and research components. The first SOAC prototype has been designed and submitted for fabrication at the MIT/LL 0.25 micron Silicon On Insulator (SOI) foundry in July 1998. It contains a telecommunications unit, power management unit, on-chip computer, non-volatile as well as volatile storage, all on a single chip. The chip will be tested at JPL in the second quarter of 1999.

  19. Space transfer vehicle avionics advanced development needs

    NASA Technical Reports Server (NTRS)

    Huffaker, C. F.

    1990-01-01

    The assessment of preliminary transportation program options for the exploration initiative is underway. The exploration initiative for the Moon and Mars is outlined by mission phases. A typical lunar/Mars outpost technology/advanced development schedule is provided. An aggressive and focused technology development program is needed as early as possible to successfully support these new initiatives. The avionics advanced development needs, plans, laboratory facilities, and benefits from an early start are described.

  20. Power, Avionics and Software Communication Network Architecture

    NASA Technical Reports Server (NTRS)

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

    2014-01-01

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

  1. New Technologies for Space Avionics, 1993

    NASA Technical Reports Server (NTRS)

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

    1993-01-01

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

  2. STS-2: SAIL non-avionics subsystems math model requirements

    NASA Technical Reports Server (NTRS)

    Bennett, W. P.; Herold, R. W.

    1980-01-01

    Simulation of the STS-2 Shuttle nonavionics subsystems in the shuttle avionics integration laboratory (SAIL) is necessary for verification of the integrated shuttle avionics system. The math model (simulation) requirements for each of the nonavionics subsystems that interfaces with the Shuttle avionics system is documented and a single source document for controlling approved changes (by the SAIL change control panel) to the math models is provided.

  3. Study objectives: Will commercial avionics do the job? Improvements needed?

    NASA Technical Reports Server (NTRS)

    Nasr, Hatem

    1992-01-01

    Improvements in commercial avionics are covered in a viewgraph format. Topics include the following: computer architecture, user requirements, Boeing 777 aircraft, cost effectiveness, and implemention.

  4. Nuclear Science Symposium, 23rd, Scintillation and Semiconductor Counter Symposium, 15th, and Nuclear Power Systems Symposium, 8th, New Orleans, La., October 20-22, 1976, Proceedings

    NASA Technical Reports Server (NTRS)

    Wagner, L. J.

    1977-01-01

    The volume includes papers on semiconductor radiation detectors of various types, components of radiation detection and dosimetric systems, digital and microprocessor equipment in nuclear industry and science, and a wide variety of applications of nuclear radiation detectors. Semiconductor detectors of X-rays, gamma radiation, heavy ions, neutrons, and other nuclear particles, plastic scintillator arrays, drift chambers, spark wire chambers, and radiation dosimeter systems are reported on. Digital and analog conversion systems, digital data and control systems, microprocessors, and their uses in scientific research and nuclear power plants are discussed. Large-area imaging and biomedical nucleonic instrumentation, nuclear power plant safeguards, reactor instrumentation, nuclear power plant instrumentation, space instrumentation, and environmental instrumentation are dealt with. Individual items are announced in this issue.

  5. Code Division Multiple Access system candidate for integrated modular avionics

    NASA Astrophysics Data System (ADS)

    Mendez, Antonio J.; Gagliardi, Robert M.

    1991-02-01

    There are government and industry trends towards avionics modularity and integrated avionics. Key requirements implicit in these trends are suitable data communication concepts compatible with the integration concept. In this paper we explore the use ofCode Division Multiple Access (CDMA) techniques as an alternative to collision detection and collision avoidance multiple access techniques.

  6. Micro-Scale Avionics Thermal Management

    NASA Technical Reports Server (NTRS)

    Moran, Matthew E.

    2001-01-01

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

  7. Heat removal key to shrinking avionics

    NASA Astrophysics Data System (ADS)

    Peterson, George P.

    1987-10-01

    An evaluation is made of the consequences for avionics miniaturization and performance improvement of recent advancements in heat pipe technology. In a heat pipe, the phase change of a working fluid can yield levels of thermal conductivity that are several orders of magnitude greater than solid conductors. Current interest extends to large heat pipes (0.3 m or greater in length), medium-sized heat pipes on which electronic components are mounted, and microheat pipes, whose dimensions are of the order of 5 cm length and 1 mm diameter.

  8. Automated Synthesis of Architecture of Avionic Systems

    NASA Technical Reports Server (NTRS)

    Chau, Savio; Xu, Joseph; Dang, Van; Lu, James F.

    2006-01-01

    The Architecture Synthesis Tool (AST) is software that automatically synthesizes software and hardware architectures of avionic systems. The AST is expected to be most helpful during initial formulation of an avionic-system design, when system requirements change frequently and manual modification of architecture is time-consuming and susceptible to error. The AST comprises two parts: (1) an architecture generator, which utilizes a genetic algorithm to create a multitude of architectures; and (2) a functionality evaluator, which analyzes the architectures for viability, rejecting most of the non-viable ones. The functionality evaluator generates and uses a viability tree a hierarchy representing functions and components that perform the functions such that the system as a whole performs system-level functions representing the requirements for the system as specified by a user. Architectures that survive the functionality evaluator are further evaluated by the selection process of the genetic algorithm. Architectures found to be most promising to satisfy the user s requirements and to perform optimally are selected as parents to the next generation of architectures. The foregoing process is iterated as many times as the user desires. The final output is one or a few viable architectures that satisfy the user s requirements.

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

    NASA Technical Reports Server (NTRS)

    Ferguson, Roscoe C.

    2011-01-01

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

  10. Impact of device level faults in a digital avionic processor

    NASA Technical Reports Server (NTRS)

    Suk, Ho Kim

    1989-01-01

    This study describes an experimental analysis of the impact of gate and device-level faults in the processor of a Bendix BDX-930 flight control system. Via mixed mode simulation, faults were injected at the gate (stuck-at) and at the transistor levels and, their propagation through the chip to the output pins was measured. The results show that there is little correspondence between a stuck-at and a device-level fault model, as far as error activity or detection within a functional unit is concerned. In so far as error activity outside the injected unit and at the output pins are concerned, the stuck-at and device models track each other. The stuck-at model, however, overestimates, by over 100 percent, the probability of fault propagation to the output pins. An evaluation of the Mean Error Durations and the Mean Time Between Errors at the output pins shows that the stuck-at model significantly underestimates (by 62 percent) the impact of an internal chip fault on the output pins. Finally, the study also quantifies the impact of device fault by location, both internally and at the output pins.

  11. Software modifications to the Demonstration Advanced Avionics Systems (DAAS)

    NASA Technical Reports Server (NTRS)

    Nedell, B. F.; Hardy, G. H.

    1984-01-01

    Critical information required for the design of integrated avionics suitable for generation aviation is applied towards software modifications for the Demonstration Advanced Avionics System (DAAS). The program emphasizes the use of data busing, distributed microprocessors, shared electronic displays and data entry devices, and improved functional capability. A demonstration advanced avionics system (DAAS) is designed, built, and flight tested in a Cessna 402, twin engine, general aviation aircraft. Software modifications are made to DAAS at Ames concurrent with the flight test program. The changes are the result of the experience obtained with the system at Ames, and the comments of the pilots who evaluated the system.

  12. Next Generation Avionics System for Satellite Application

    NASA Astrophysics Data System (ADS)

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

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

  13. Avionics electromagnetic interference immunity and environment

    NASA Technical Reports Server (NTRS)

    Clarke, C. A.

    1986-01-01

    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.

  14. Industry perspectives on Plug-& -Play Spacecraft Avionics

    NASA Astrophysics Data System (ADS)

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

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

  15. How mechanical engineering issues affect avionics design

    NASA Astrophysics Data System (ADS)

    Leonard, Charles T.

    Environmental questions that involve temperature and heat dissipation in connection with avionics are discussed. The authors describe recent work on (1) passive (no machinery to move coolant) cooling techniques allowing deletion of active (machinery powered) cooling systems, and (2) studies to ascertain the effect of temperature on reliability. It is shown that passive cooling techniques can produce temperatures approximately equivalent to those of active cooling, and that heat-transfer-enhancement techniques can extend the application of passive cooling. In addition, it is noted that active cooling can incur high prices beyond the immediately visible costs of the active cooling systems alone. The influence of temperature as a failure accelerator in moderate temperature ranges cannot be readily confirmed. Passive cooling minimizes the interface definition for application of electronic equipment, thus simplifying use of a box in multiple applications.

  16. Crew Exploration Vehicle (CEV) Avionics Integration Laboratory (CAIL) Independent Analysis

    NASA Technical Reports Server (NTRS)

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

    2009-01-01

    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).

  17. Overview of Avionics and Electrical Ground Support Equipment

    NASA Technical Reports Server (NTRS)

    Clarke, Sean C.

    2011-01-01

    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.

  18. System Engineering Issues for Avionics Survival in the Space Environment

    NASA Technical Reports Server (NTRS)

    Pavelitz, Steven

    1999-01-01

    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.

  19. Assessment of avionics technology in European aerospace organizations

    NASA Technical Reports Server (NTRS)

    Martinec, D. A.; Baumbick, Robert; Hitt, Ellis; Leondes, Cornelius; Mayton, Monica; Schwind, Joseph; Traybar, Joseph

    1992-01-01

    This report provides a summary of the observations and recommendations made by a technical panel formed by the National Aeronautics and Space Administration (NASA). The panel, comprising prominent experts in the avionics field, was tasked to visit various organizations in Europe to assess the level of technology planned for use in manufactured civil avionics in the future. The primary purpose of the study was to assess avionics systems planned for implementation or already employed on civil aircraft and to evaluate future research, development, and engineering (RD&E) programs, address avionic systems and aircraft programs. The ultimate goal is to ensure that the technology addressed by NASa programs is commensurate with the needs of the aerospace industry at an international level. The panel focused on specific technologies, including guidance and control systems, advanced cockpit displays, sensors and data networks, and fly-by-wire/fly-by-light systems. However, discussions the panel had with the European organizations were not limited to these topics.

  20. Transcription of the Workshop on General Aviation Advanced Avionics Systems

    NASA Technical Reports Server (NTRS)

    Tashker, M. (Editor)

    1975-01-01

    Papers are presented dealing with the design of reliable, low cost, advanced avionics systems applicable to general aviation in the 1980's and beyond. Sensors, displays, integrated circuits, microprocessors, and minicomputers are among the topics discussed.

  1. Space Generic Open Avionics Architecture (SGOAA) standard specification

    NASA Technical Reports Server (NTRS)

    Wray, Richard B.; Stovall, John R.

    1994-01-01

    This standard establishes the Space Generic Open Avionics Architecture (SGOAA). The SGOAA includes a generic functional model, processing structural model, and an architecture interface model. This standard defines the requirements for applying these models to the development of spacecraft core avionics systems. The purpose of this standard is to provide an umbrella set of requirements for applying the generic architecture models to the design of a specific avionics hardware/software processing system. This standard defines a generic set of system interface points to facilitate identification of critical services and interfaces. It establishes the requirement for applying appropriate low level detailed implementation standards to those interfaces points. The generic core avionics functions and processing structural models provided herein are robustly tailorable to specific system applications and provide a platform upon which the interface model is to be applied.

  2. Space Generic Open Avionics Architecture (SGOAA) reference model technical guide

    NASA Technical Reports Server (NTRS)

    Wray, Richard B.; Stovall, John R.

    1993-01-01

    This report presents a full description of the Space Generic Open Avionics Architecture (SGOAA). The SGOAA consists of a generic system architecture for the entities in spacecraft avionics, a generic processing architecture, and a six class model of interfaces in a hardware/software system. The purpose of the SGOAA is to provide an umbrella set of requirements for applying the generic architecture interface model to the design of specific avionics hardware/software systems. The SGOAA defines a generic set of system interface points to facilitate identification of critical interfaces and establishes the requirements for applying appropriate low level detailed implementation standards to those interface points. The generic core avionics system and processing architecture models provided herein are robustly tailorable to specific system applications and provide a platform upon which the interface model is to be applied.

  3. Avionics Architectures for Exploration: Wireless Technologies and Human Spaceflight

    NASA Technical Reports Server (NTRS)

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

    2014-01-01

    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.

  4. An Analysis of the Modes and States for Generic Avionics

    NASA Technical Reports Server (NTRS)

    Wray, Richard B.

    1993-01-01

    The objective of this study was to develop a topology for describing the behavior of mission, vehicle and system/substem entities in new flight vehicle designs based on the use of open standards. It also had to define and describe the modes and states which may be used in generic avionics behavioral descriptions, describe their interrelationships, and establish a method for applying generic avionics to actual flight vehicle designs.

  5. A Communication Paradigm for Modular Avionics: The DAPAR Experience

    NASA Astrophysics Data System (ADS)

    Llorca-Cejudo, Roger; Carayon, Jean-Louis; Antolinos, Luc

    2014-08-01

    The DAPAR avionics paradigm was conceived at CNES as a path to reduce avionics subsystem development costs while, at the same time increasing its modularity and flexibility. A demonstrator system has been constructed based on DAPAR concepts with the objective of studying what are the difficulties/benefits of the approach. This paper describes both the characteristics of the DAPAR paradigm and the lessons learned from the demonstrator system.

  6. 2013 aircrew, avionics, and operations survey, part 2.

    PubMed

    Greene, Michael J

    2013-01-01

    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

  7. Evaluation of New European Technologies for Future Avionics

    NASA Astrophysics Data System (ADS)

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

    2014-08-01

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

  8. Avionics architectures for the next generation of launch vehicles

    NASA Astrophysics Data System (ADS)

    Stanley, Jeffrey H.

    The challenges and benefits of utilizing current avionics architecture concepts for the next generation of space launch vehicles are examined. The generic integration approach and architecture produced by the Advanced System Avionics (ASA)-Pave Pillar program is the foundation for avionics development in next generation aircraft for the U.S. Department of Defense, and include aircraft such as the USAF advanced tactical fighter (AFTF) and USN advanced tactical aircraft (ATA). The implementation strategies being used by aircraft avionics include the system-wide utilization of common modular building blocks using advanced microelectronics such as VHSIC, standard electronic module (SEM) sizes and integrated racks, and interconnection networks using fiber optics. It is concluded that the Pave Pillar core architecture objectives of high availability, resiliency, supportability, and low life cycle cost are similar to the desired attributes of future space launch vehicles. The core avionics, with tailoring to those requirements, can be used as the design baseline for launch vehicles, and thereby utilize the experience and investment already committed to the advanced modular avionics architecture program.

  9. Wireless avionics for space applications of fundamental physics

    NASA Astrophysics Data System (ADS)

    Wang, Linna; Zeng, Guiming

    2016-07-01

    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.

  10. ExoMars 2018 Avionic Architecture

    NASA Astrophysics Data System (ADS)

    Caramia, Maurizio; Musetti, Bruno; Zekry, Eric

    2014-08-01

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

  11. Avionics System Architecture for the NASA Orion Vehicle

    NASA Technical Reports Server (NTRS)

    Baggerman, Clint; McCabe, Mary; Verma, Dinesh

    2009-01-01

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

  12. The Space Technology 5 Avionics System

    NASA Technical Reports Server (NTRS)

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

    2004-01-01

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

  13. Digital signal conditioning for flight test instrumentation

    NASA Technical Reports Server (NTRS)

    Bever, Glenn A.

    1991-01-01

    An introduction to digital measurement processes on aircraft is provided. Flight test instrumentation systems are rapidly evolving from analog-intensive to digital intensive systems, including the use of onboard digital computers. The topics include measurements that are digital in origin, as well as sampling, encoding, transmitting, and storing data. Particular emphasis is placed on modern avionic data bus architectures and what to be aware of when extracting data from them. Examples of data extraction techniques are given. Tradeoffs between digital logic families, trends in digital development, and design testing techniques are discussed. An introduction to digital filtering is also covered.

  14. Electronic/electric technology benefits study. [avionics

    NASA Technical Reports Server (NTRS)

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

    1982-01-01

    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.

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

    SciTech Connect

    Sims, A.J.; Dyer, C.S.; Peerless, C.L. . Space and Communications Dept.); Johansson, K.; Pettersson, H. ); Farren, J. . Harwell Lab.)

    1994-12-01

    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.

  16. Avionic architecture requirements for Space Exploration Initiative systems

    NASA Technical Reports Server (NTRS)

    Herbella, C. G.; Brown, D. C.

    1991-01-01

    The authors discuss NASA's Strategic Avionics Technology Working Group (SATWG) and the results of the first study commissioned by the SATWG, the Space Avionics Requirements Study (SARS). The goal of the SARS task was to show that an open avionics architecture, using modular, standardized components, could be applied across the wide range of systems that comprise the Space Exploration Initiative. The study addressed systems ranging from expendable launch vehicles and the space station to surface systems such as Mars or lunar rovers and habitats. Top-level avionics requirements were derived from characterizations of each of the systems considered. Then a set of avionics subsystems were identified, along with estimates of the numbers and types of modules needed to meet the requirements. Applicability of these results across the infrastructure was then illustrated. In addition to these tasks, critical technologies were identified, characterized, and assessed in terms of their criticality and impact on the program. Design, development, test, and evaluation methods were addressed to identify potential areas of improvement.

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

    NASA Technical Reports Server (NTRS)

    Cockrell, James

    2015-01-01

    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.

  18. Time Triggered Protocol (TTP) for Integration Modular Avionics (IMA)

    NASA Technical Reports Server (NTRS)

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

    2006-01-01

    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)

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

    NASA Technical Reports Server (NTRS)

    Quinby, G. F.

    1980-01-01

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

  20. HLLV avionics requirements study and electronic filing system database development

    NASA Technical Reports Server (NTRS)

    1994-01-01

    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.

  1. Space Tug avionics definition study. Volume 1: Executive summary

    NASA Technical Reports Server (NTRS)

    1975-01-01

    A top down approach was used to identify, compile, and develop avionics functional requirements for all flight and ground operational phases. Such requirements as safety mission critical functions and criteria, minimum redundancy levels, software memory sizing, power for tug and payload, data transfer between payload, tug, shuttle, and ground were established. Those functional requirements that related to avionics support of a particular function were compiled together under that support function heading. This unique approach provided both organizational efficiency and traceability back to the applicable operational phase and event. Each functional requirement was then allocated to the appropriate subsystems and its particular characteristics were quantified.

  2. Preliminary design of the Shuttle-C avionics recovery system

    NASA Technical Reports Server (NTRS)

    Brookfield, Morgan; Decker, Deron; Gilbert, Harold; Moore, David; Rist, Mark

    1989-01-01

    The analysis done in developing a recovery system for the Shuttle-C cargo vehicle is presented. This recovery system is comprised of a reentry capsule which houses the vehicles avionics. The avionics are contained in a single package which is extracted from the capsule by the parachute recovery system. The Shuttle-C will be able to satisfy NASA's design and mission requirements. Included, is an analysis of the structural, thermal protection, and parachute recovery systems. A discussion of the merits of the proposed system is also included.

  3. Space Generic Open Avionics Architecture (SGOAA) standard specification

    NASA Technical Reports Server (NTRS)

    Wray, Richard B.; Stovall, John R.

    1993-01-01

    The purpose of this standard is to provide an umbrella set of requirements for applying the generic architecture interface model to the design of a specific avionics hardware/software system. This standard defines a generic set of system interface points to facilitate identification of critical interfaces and establishes the requirements for applying appropriate low level detailed implementation standards to those interface points. The generic core avionics system and processing architecture models provided herein are robustly tailorable to specific system applications and provide a platform upon which the interface model is to be applied.

  4. State-of-the-art multichip modules for avionics

    NASA Astrophysics Data System (ADS)

    Hagge, John K.

    1991-04-01

    The emerging multichip packaging technology offers significant advantages in miniaturization faster electrical performance efficient thermal performance lower cost and significantly improved reliability. Newly available materials and processes have stimulated multichip applications ranging from low-cost consumer electronics and automotive modules to advanced aerospace and supercomputer applications. Avionics multichip modules share the same systems integration issues as other applications: optimum partitioning seamless CAD/CIM tools testability and repairability strategies cost-effective manufacturing availability of vendor support technologies and reliable packaging for long life in environmental stresses. This paper discusses state-of-the-art avionics multichip modules industry developments required to enable wider utilization and evolutionary extensions into next generation technologies.

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

    NASA Technical Reports Server (NTRS)

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

    2009-01-01

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

  6. Heavy Lift Vehicle (HLV) Avionics Flight Computing Architecture Study

    NASA Technical Reports Server (NTRS)

    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.

    2011-01-01

    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.

  7. The 23rd Stirling Physics Meeting

    NASA Astrophysics Data System (ADS)

    1998-01-01

    This was how the chairman, Dennis Chisholm, described the morning's major topic `Higher Still' - the proposed successor to the Scottish Higher Grade and Sixth Year Studies Certificates. It was chosen for this one-day conference on 21 May as the documentation for it had been promised for 1 May. Alas, as the main speaker, Mary Webster, admitted, the materials were still `sitting in a warehouse in Dundee' and the programme has now been postponed for a year! Nevertheless the team, which included Rothwell Glen and Tony Keeley, bravely fielded a series of awkward questions from a critical audience of over 200 physics teachers. Physics with gusto If `Higher Still' was a damp squib Rebecca Crawford's team from Glasgow Science and Technology Outreach set the place ablaze. In their first spectacular demonstration Rebecca lay on a bed of sharp nails while someone stood on top of her! This was followed by a deafening explosion produced by cornflour powder igniting in a tin can used to model a grain silo. Hydrogen was then produced by aluminium foil in a solution of caustic soda, and used to inflate a balloon before exploding it with a flaming torch. Using two 2 mW lasers the green spot produced by one was shown to appear much brighter than the red spot from the other, The Australian demonstrator explained that some of their fire engines were now being painted green instead of red as our eyes are more sensitive to green. A small low-inertia electric motor turned when attached to copper and zinc electrodes inserted first in a glass of Coke and then in a fresh grapefruit. Gas-filled sausage balloons were packed into a flask of liquid nitrogen where they collapsed as the gas inside liquefied. When the bunch of deflated balloons was removed and thrown on to the bench the results were dramatic. As you might expect, the `best wine' was kept to the last. Kenneth Skeldon and two colleagues in the University of Glasgow have built a high voltage generator based on a resonant transformer derived from a standard Tesla coil with a high-Q secondary. This is capable of delivering around a million volts, which produce fantastic lightning flashes. A volunteer from the audience was invited to enter a huge Faraday Cage which was then subjected to these high voltage sparks! For a while the door of the cage jammed but eventually the victim emerged unscathed! This is, of course, not just an entertainment. The Gusto show is taken into schools and targeted at lower secondary pupils about to make their subject choices. The team also gives large scale physics demonstration lectures and could play to 10 000 children in a month. So physics is fun and physics is relevant to everyday life! Support for physics teachers Lesley Glasser chaired the afternoon session, which she opened by introducing the Institute's Education Officer. The Stirling Meeting would not be the same without the `commercial slot' presented again so ably by Catherine Wilson. Physics teachers are an endangered species and the Institute is determined to do whatever it can to support them. Plans are afoot to make sure the Schools Lectures are modified, if necessary, to take account of the educational differences in Scotland. The London-based `Physics in Perspective' course not only introduces sixth-formers to some of the frontiers of physics but gives enough free time for them to visit places of interest in the city - from the Science Museum to Soho. `So they associate physics with enjoyment!' Another Scottish Update Course is planned for teachers, and a brand new glossy booklet, sent free to all schools, will show pupils that choosing physics is a `Smart Move'. Finally the Institute has just started a major post-16 curriculum project which will include a variety of support materials to keep teachers abreast of continuing developments in physics. Each year, IoP Teacher of Physics Awards are given to `outstanding teachers of physics who inspire others to continue with and enjoy their physics'. Ann Jarvie, Deputy Head of St Ninian's High School in Kirkintilloch, certainly felt that this was a fitti

  8. The 23rd Annual Consortium of Geologists

    ERIC Educational Resources Information Center

    Cronin, Jim

    2008-01-01

    Today's scientific theories are the result of a long collaborative process, sometimes over centuries, among many different scientists from various parts of the world. To communicate this concept to middle school students and introduce them to the theory of plate tectonics and continental drift, they are placed in the role of geologists attending a…

  9. The 23rd Stirling Physics Meeting

    NASA Astrophysics Data System (ADS)

    1998-01-01

    This was how the chairman, Dennis Chisholm, described the morning's major topic `Higher Still' - the proposed successor to the Scottish Higher Grade and Sixth Year Studies Certificates. It was chosen for this one-day conference on 21 May as the documentation for it had been promised for 1 May. Alas, as the main speaker, Mary Webster, admitted, the materials were still `sitting in a warehouse in Dundee' and the programme has now been postponed for a year! Nevertheless the team, which included Rothwell Glen and Tony Keeley, bravely fielded a series of awkward questions from a critical audience of over 200 physics teachers. Physics with gusto If `Higher Still' was a damp squib Rebecca Crawford's team from Glasgow Science and Technology Outreach set the place ablaze. In their first spectacular demonstration Rebecca lay on a bed of sharp nails while someone stood on top of her! This was followed by a deafening explosion produced by cornflour powder igniting in a tin can used to model a grain silo. Hydrogen was then produced by aluminium foil in a solution of caustic soda, and used to inflate a balloon before exploding it with a flaming torch. Using two 2 mW lasers the green spot produced by one was shown to appear much brighter than the red spot from the other, The Australian demonstrator explained that some of their fire engines were now being painted green instead of red as our eyes are more sensitive to green. A small low-inertia electric motor turned when attached to copper and zinc electrodes inserted first in a glass of Coke and then in a fresh grapefruit. Gas-filled sausage balloons were packed into a flask of liquid nitrogen where they collapsed as the gas inside liquefied. When the bunch of deflated balloons was removed and thrown on to the bench the results were dramatic. As you might expect, the `best wine' was kept to the last. Kenneth Skeldon and two colleagues in the University of Glasgow have built a high voltage generator based on a resonant transformer derived from a standard Tesla coil with a high-Q secondary. This is capable of delivering around a million volts, which produce fantastic lightning flashes. A volunteer from the audience was invited to enter a huge Faraday Cage which was then subjected to these high voltage sparks! For a while the door of the cage jammed but eventually the victim emerged unscathed! This is, of course, not just an entertainment. The Gusto show is taken into schools and targeted at lower secondary pupils about to make their subject choices. The team also gives large scale physics demonstration lectures and could play to 10 000 children in a month. So physics is fun and physics is relevant to everyday life! Support for physics teachers Lesley Glasser chaired the afternoon session, which she opened by introducing the Institute's Education Officer. The Stirling Meeting would not be the same without the `commercial slot' presented again so ably by Catherine Wilson. Physics teachers are an endangered species and the Institute is determined to do whatever it can to support them. Plans are afoot to make sure the Schools Lectures are modified, if necessary, to take account of the educational differences in Scotland. The London-based `Physics in Perspective' course not only introduces sixth-formers to some of the frontiers of physics but gives enough free time for them to visit places of interest in the city - from the Science Museum to Soho. `So they associate physics with enjoyment!' Another Scottish Update Course is planned for teachers, and a brand new glossy booklet, sent free to all schools, will show pupils that choosing physics is a `Smart Move'. Finally the Institute has just started a major post-16 curriculum project which will include a variety of support materials to keep teachers abreast of continuing developments in physics. Each year, IoP Teacher of Physics Awards are given to `outstanding teachers of physics who inspire others to continue with and enjoy their physics'. Ann Jarvie, Deputy Head of St Ninian's High School in Kirkintilloch, certainly felt that this was a fitting description of their physics master Pat Cleary, who was presented with his Award at the Stirling Meeting. Of him she said `He encourages and supports his pupils. He doesn't talk down to them and he is concerned about all pupils, not just the high fliers. He has a great sense of humour and enthuses his pupils. Pat's passion for physics is all-consuming; he will beg, borrow and (almost) steal for physics! He only tolerates senior management because they supply him with money for physics!' Before giving his keynote lecture Professor Russell Stannard presented Pat Cleary with his Award. Venturing beyond physics In this stimulating presentation Russell Stannard not only summarized current thinking in cosmology, he also considered possible theological implications. The universe is a big place consisting of 1011 galaxies each containing 1011 stars. It may be that 1030 stars have planets and so the universe could be teeming with millions of different forms of life. Is size then the most important thing for us? What goes on in the human head is much more interesting than the nuclear reactions of the sun. Surely human consciousness, associated with the complexity of the brain, is of more importance to us than mere size. In the beginning If we ask about the origin of the universe, e.g. `How did it get started?' then we look to science for an answer. On the other hand we might ask a theological question about creation, e.g. `Why is there something rather than nothing?' Current ideas of the Big Bang are based on several independent strands of evidence which Russell discussed in some detail. Space-time `It is idle to look for time before creation, as if time can be found before time.... We should say that time began with creation rather than creation began with time.' This amazingly modern concept - that space and time were created together - was asserted by St Augustine 1500 years ago! If time and space are `welded' together time didn't exist before the Big Bang and so we cannot ask what caused the Big Bang. Cause precedes effect. The future The universe is expanding but at a reduced rate. Will it eventually stop expanding and start to contract? If so, will it reach a point where it again stops and starts to expand again - the Big Bounce? Or will it collapse completely - the Big Crunch? Alternatively will the universe go on expanding forever? The answers to these questions depend on the density of the universe. The density needed to make the universe start to contract is called the critical density. At present the observed density is around 0.3% of critical density. This would suggest that the universe should continue expanding forever. However, the movements of galaxies and clusters of galaxies indicate that there must be some undetected `dark matter' which, calculations show, increases the density of the universe to within a factor of two of critical density. If this is correct the density at the early stages of the Big Bang would have had to be correct to within 1 part in 1060. DIY universe A final word of warning to anyone who aspires to building a better universe! If you make your Big Bang less violent the universe will expand and then collapse to a Big Crunch before life has time to develop. Make it more violent and gases will disperse quickly so that stars and planets cannot form. If you make gravity (G) weaker, nuclear reactions won't be triggered and only brown dwarfs will form. Life will be impossible. Make gravity stronger and only fast-burning massive stars will form. These blue giants last for only a million years and there will be no time for life to evolve. In summary: are we in one of an infinite number of universes because the conditions happen to be just right for us or is this universe a one-off put-up job designed by God? Cosmology neither proves nor disproves the existence of God. However if, on other grounds, you are a believer, current thinking in cosmology shouldn't worry you. Thanks To circle the world in 80 days may be interesting. To encompass the universe in less than 80 minutes is, in the chairperson's words, mind-blowing. The day ended with votes of thanks to all contributors and to Jack Woolsey and his team for organizing the meeting. Jim Jardine

  10. The 23rd Aerospace Mechanisms Symposium

    NASA Technical Reports Server (NTRS)

    1989-01-01

    Technological areas covered include space lubrication, bearings, aerodynamic devices, spacecraft latches, deployment, positioning, and pointing. Devices for Space Station docking and manipulator and teleoperator mechanisms are also described.

  11. Variation of NmF2 and hmF2 deduced from DPS-4 over Multan (Pakistan) and their comparisons with IRI-2007 & IRI-2012 during the deep solar minimum between 23rd and 24th solar cycles

    NASA Astrophysics Data System (ADS)

    Ayyaz Ameen, Muhammad; Raza, Kazim; Ayub, Muhammad

    Digisonde DPS-4 data of Multan (geog coord. 30.18(°) N, 71.48(°) E) is being reported for the first time. The variations in F2-layer peak electron density NmF2 and its height hmF2 have been studied during the deep solar minimum between 23rd and 24th solar cycles along their comparisons with International Reference Ionosphere, IRI-2007 & IRI-2012 predication. The observation results show that the NmF2 values are greater and smaller during daytime and nighttime, respectively. The hmF2 observations show sunrise peaks along with some prominent pre-sunrise peaks in some months. Seasonal variations show that the daytime NmF2 values are greater in the equinox and summer months, while the daytime hmF2 values are slightly greater in the equinox and winter months. For the comparison of observations with IRI-2007 and IRI-2012, the observed hmF2 values are closer to IRI-2007 than to IRI-2012. The NmF2 values of URSI map of IRI-2012 agree well with the observations in equinox. The IRI-2007 agrees better with the NmF2 observations for winter and summer than IRI-2012, whereas IRI-2012 is closer to the observations for equinox months. The variation in the observed parameters exhibits that the ionosphere over Multan is showing the properties of both equatorial and mid-latitude due to the location of station.

  12. Avionics Technology Contract Project Report Phase I with Research Findings.

    ERIC Educational Resources Information Center

    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…

  13. Low-Cost Avionics Simulation for Aircrew Training.

    ERIC Educational Resources Information Center

    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…

  14. Optimizing the Design of Avionics Lightning Suppression Circuits

    NASA Astrophysics Data System (ADS)

    McCreary, Clay Allen

    This dissertation documents research into optimizing the design of lightning suppression circuits for electronic equipment used on aircraft (avionics). Aircraft manufacturers are increasingly using carbon composite material for the fabrication of the airframe instead of aluminum, and avionics have become more integrated. This has resulted in avionics with higher signal density at the interface being exposed to transients with wider pulse widths and increased levels from the indirect effects of lightning. This dissertation details the development of techniques to select the smallest components and minimum printed circuit board trace dimensions that can tolerate given lightning transient levels. Also, there is a desire to upgrade existing avionics to tolerate the more severe indirect effects of lightning requirements for composite aircraft. This requires evaluation of the immunity of existing designs to new transient levels and different waveforms than those to which they are certified. This evaluation determines if additional protection is needed. The evaluation technique is described, and methods for providing additional protection are given within this document. Lastly, graphical user interfaces (GUI) are created to perform all of the calculations for component selection, minimum PCB trace width, and the first step in evaluating existing designs against new requirements.

  15. Preliminary design document: Ground based testbed for avionics systems

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The design and interface requirements for an avionics Ground Based Test bed (GBT) to support Heavy Lift Cargo Vehicles (HLCV) is presented. It also contains data on the vehicle subsystem configurations that are to be supported during their early, pre-PDR developmental phases. Several emerging technologies are also identified for support. A Preliminary Specification Tree is also presented.

  16. Ensuring Safety and Security for Avionics: A Case Study

    NASA Astrophysics Data System (ADS)

    Laarouchi, Y.; Deswarte, Y.; Powell, D.; Arlat, J.; De Nadai, E.

    2009-05-01

    We present a case study in the avionics context, in which bidirectional information flows exist between critical components and less critical ones. These flows raise security and safety concerns that have to be taken into account to guarantee correct operation of the critical tasks. To allow upwards flows, we propose fault tolerance mechanisms based on diverse operating systems isolated by virtualization.

  17. Time multiplexed optical shutter (TMOS) display technology for avionics platforms

    NASA Astrophysics Data System (ADS)

    Selbrede, M.; Yost, B.

    2006-05-01

    Time Multiplexed Optical Shutter (TMOS) is a new approach to flat panel light valve display technology that addresses display requirements in avionics applications, particularly head-down cockpit deployments. TMOS modulates the local transmission of light from a waveguide coextensive with the screen. The architecture requires fewer, larger on-screen features (e.g., TFTs) than prevailing technologies because it exploits field sequential color techniques. Methods to mitigate color break up are presented. TMOS exhibits lower power consumption, lower weight, a simplified architecture, and better visual quality than incumbent display technologies while overcoming their limitations (e.g., poor light efficiency, and size/weight constraints due to yield and backlighting). TMOS should meet avionics needs without additional ruggedization enhancements, offers high immunity to EMP, and can be constructed from transparent materials (allowing z-axis redundancy to improve cockpit ergonomics). Respecting the avionics market, TMOS has advantages over incumbent display technologies, including lower sensitivity to temperature variation, greater immunity to vibration, higher system efficacy (power in to light out), and larger dimming ratios. The status of TMOS development and its fit within avionics applications is addressed.

  18. Current state of OLED technology relative to military avionics requirements

    NASA Astrophysics Data System (ADS)

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

    2014-06-01

    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.

  19. Prediction Tables for Avionics Fundamentals Course, Class A.

    ERIC Educational Resources Information Center

    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…

  20. Demonstration Advanced Avionics System (DAAS). Phase 1 report

    NASA Technical Reports Server (NTRS)

    1981-01-01

    An integrated avionics system which provides expanded functional capabilities that significantly enhance the utility and safety of general aviation at a cost commensurate with the general aviation market is discussed. Displays and control were designed so that the pilot can use the system after minimum training. Functional and hardware descriptions, operational evaluation and failure modes effects analysis are included.

  1. Reliability and the design process at Honeywell Avionics Division

    NASA Technical Reports Server (NTRS)

    Bezat, A.

    1981-01-01

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

  2. Distributed Avionics and Software Verification for the Constellation Program

    NASA Technical Reports Server (NTRS)

    Hood, Laura E.; Adams, James E.

    2008-01-01

    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.

  3. Design Description of the X-33 Avionics Architecture

    NASA Technical Reports Server (NTRS)

    Reichenfeld, Curtis J.; Jones, Paul G.

    1999-01-01

    In this paper, we provide a design description of the X-33 avionics architecture. The X-33 is an autonomous Single Stage to Orbit (SSTO) launch vehicle currently being developed by Lockheed Martin for NASA as a technology demonstrator for the VentureStar Reusable Launch Vehicle (RLV). The X-33 avionics provides autonomous control of die vehicle throughout takeoff, ascent, descent, approach, landing, rollout, and vehicle safing. During flight the avionics provides communication to the range through uplinked commands and downlinked telemetry. During pre-launch and post-safing activities, the avionics provides interfaces to ground support consoles that perform vehicle flight preparations and maintenance. The X-33 Avionics is a hybrid of centralized and distributed processing elements connected by three dual redundant Mil-Std 1553 data buses. These data buses are controlled by a central processing suite located in the avionics bay and composed of triplex redundant Vehicle Mission Computers (VMCs). The VMCs integrate mission management, guidance, navigation, flight control, subsystem control and redundancy management functions. The vehicle sensors, effectors and subsystems are interfaced directly to the centralized VMCs as remote terminals or through dual redundant Data Interface Units (DIUs). The DIUs are located forward and aft of the avionics bay and provide signal conditioning, health monitoring, low level subsystem control and data interface functions. Each VMC is connected to all three redundant 1553 data buses for monitoring and provides a complete identical data set to the processing algorithms. This enables bus faults to be detected and reconfigured through a voted bus control configuration. Data is also shared between VMCs though a cross channel data link that is implemented in hardware and controlled by AlliedSignal's Fault Tolerant Executive (FTE). The FTE synchronizes processors within the VMC and synchronizes redundant VMCs to each other. The FTE provides

  4. Case Study of the Space Shuttle Cockpit Avionics Upgrade Software

    NASA Technical Reports Server (NTRS)

    Ferguson, Roscoe C.; Thompson, Hiram C.

    2005-01-01

    The purpose of the Space Shuttle Cockpit Avionics Upgrade project was to reduce crew workload and improve situational awareness. The upgrade was to augment the Shuttle avionics system with new hardware and software. An early version of this system was used to gather human factor statistics in the Space Shuttle Motion Simulator of the Johnson Space Center for one month by multiple teams of astronauts. The results were compiled by NASA Ames Research Center and it was was determined that the system provided a better than expected increase in situational awareness and reduction in crew workload. Even with all of the benefits nf the system, NASA cancelled the project towards the end of the development cycle. A major success of this project was the validation of the hardware architecture and software design. This was significant because the project incorporated new technology and approaches for the development of human rated space software. This paper serves as a case study to document knowledge gained and techniques that can be applied for future space avionics development efforts. The major technological advances were the use of reflective memory concepts for data acquisition and the incorporation of Commercial off the Shelf (COTS) products in a human rated space avionics system. The infused COTS products included a real time operating system, a resident linker and loader, a display generation tool set, and a network data manager. Some of the successful design concepts were the engineering of identical outputs in multiple avionics boxes using an event driven approach and inter-computer communication, a reconfigurable data acquisition engine, the use of a dynamic bus bandwidth allocation algorithm. Other significant experiences captured were the use of prototyping to reduce risk, and the correct balance between Object Oriented and Functional based programming.

  5. Lamp-life predictive model for avionics backlights

    NASA Astrophysics Data System (ADS)

    Webster, Richard P.; Nelson, Leonard Y.

    1998-09-01

    Active Matrix Liquid Crystal Displays (AMLCDs) used in avionics applications require high luminance, high efficacy, and long-life backlights. Currently, fluorescent lamps are the favored light sources for these high performance avionics backlights. Their spectral characteristics and high electrical efficiency are well suited to illuminating AMLCDs used in avionics applications. Fluorescent lamps, however, suffer gradual reduction in luminance output caused by various degradation mechanisms. Korry Electronics Co. recently developed a mathematical model for predicting fluorescent lamp life. The model's basis is the well characterized exponential decay of the phosphor output. The primary luminance degradation mechanism of a fluorescent lamp is related to the arc discharge. Consequently, phosphor depreciation is proportional to the discharge arc power divided by the phosphor surface area. This 'wall loading' is a parameter in the computer model developed to extrapolate long-term luminance performance. Our model predicts a rapidly increasing decay rate of the lamp output as the input power is increased to sustain constant luminance. Eventually, a run-away condition occurs -- lamp arc power must be increased by unrealistically large factors (greater than 5x) to maintain the required luminance output. This condition represents the end of the useful lamp life. The lamp life model requires the definition of several key parameters in order to accurately predict the useful lamp life of an avionics backlight. These important factors include the construction of the lamp, lamp arc power, a decay constant based on the phosphor loading, and the operational profile. Based on the above-mentioned factors, our model approximates the useful lamp life of an avionics backlight using fluorescent lamp technology. Comparisons between calculated and experimental lamp depreciation are presented.

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

    NASA Technical Reports Server (NTRS)

    Latorella, Kara A.

    2015-01-01

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

  7. IBC's 23rd Annual Antibody Engineering, 10th Annual Antibody Therapeutics international conferences and the 2012 Annual Meeting of The Antibody Society: December 3-6, 2012, San Diego, CA.

    PubMed

    Klöhn, Peter-Christian; Wuellner, Ulrich; Zizlsperger, Nora; Zhou, Yu; Tavares, Daniel; Berger, Sven; Zettlitz, Kirstin A; Proetzel, Gabriele; Yong, May; Begent, Richard H J; Reichert, Janice M

    2013-01-01

    The 23rd Annual Antibody Engineering, 10th Annual Antibody Therapeutics international conferences, and the 2012 Annual Meeting of The Antibody Society, organized by IBC Life Sciences with contributions from The Antibody Society and two Scientific Advisory Boards, were held December 3-6, 2012 in San Diego, CA. The meeting drew over 800 participants who attended sessions on a wide variety of topics relevant to antibody research and development. As a prelude to the main events, a pre-conference workshop held on December 2, 2012 focused on intellectual property issues that impact antibody engineering. The Antibody Engineering Conference was composed of six sessions held December 3-5, 2012: (1) From Receptor Biology to Therapy; (2) Antibodies in a Complex Environment; (3) Antibody Targeted CNS Therapy: Beyond the Blood Brain Barrier; (4) Deep Sequencing in B Cell Biology and Antibody Libraries; (5) Systems Medicine in the Development of Antibody Therapies/Systematic Validation of Novel Antibody Targets; and (6) Antibody Activity and Animal Models. The Antibody Therapeutics conference comprised four sessions held December 4-5, 2012: (1) Clinical and Preclinical Updates of Antibody-Drug Conjugates; (2) Multifunctional Antibodies and Antibody Combinations: Clinical Focus; (3) Development Status of Immunomodulatory Therapeutic Antibodies; and (4) Modulating the Half-Life of Antibody Therapeutics. The Antibody Society's special session on applications for recording and sharing data based on GIATE was held on December 5, 2012, and the conferences concluded with two combined sessions on December 5-6, 2012: (1) Development Status of Early Stage Therapeutic Antibodies; and (2) Immunomodulatory Antibodies for Cancer Therapy. PMID:23575266

  8. Crew Launch Vehicle (CLV) Avionics and Software Integration Overview

    NASA Technical Reports Server (NTRS)

    Monell, Donald W.; Flynn, Kevin C.; Maroney, Johnny

    2006-01-01

    On January 14, 2004, the President of the United States announced a new plan to explore space and extend a human presence across our solar system. The National Aeronautics and Space Administration (NASA) established the Exploration Systems Mission Directorate (ESMD) to develop and field a Constellation Architecture that will bring the Space Exploration vision to fruition. The Constellation Architecture includes a human-rated Crew Launch Vehicle (CLV) segment, managed by the Marshall Space Flight Center (MSFC), comprised of the First Stage (FS), Upper Stage (US), and Upper Stage Engine (USE) elements. The CLV s purpose is to provide safe and reliable crew and cargo transportation into Low Earth Orbit (LEO), as well as insertion into trans-lunar trajectories. The architecture's Spacecraft segment includes, among other elements, the Crew Exploration Vehicle (CEV), managed by the Johnson Space Flight Center (JSC), which is launched atop the CLV. MSFC is also responsible for CLV and CEV stack integration. This paper provides an overview of the Avionics and Software integration approach (which includes the Integrated System Health Management (ISHM) functions), both within the CLV, and across the CEV interface; it addresses the requirements to be met, logistics of meeting those requirements, and the roles of the various groups. The Avionics Integration and Vehicle Systems Test (ANST) Office was established at the MSFC with system engineering responsibilities for defining and developing the integrated CLV Avionics and Software system. The AIVST Office has defined two Groups, the Avionics and Software Integration Group (AVSIG), and the Integrated System Simulation and Test Integration Group (ISSTIG), and four Panels which will direct trade studies and analyses to ensure the CLV avionics and software meet CLV system and CEV interface requirements. The four panels are: 1) Avionics Integration Panel (AIP), 2) Software Integration Panel, 3) EEE Panel, and 4) Systems Simulation

  9. Digital signal conditioning for flight test, volume 19

    NASA Technical Reports Server (NTRS)

    Bever, G. A.

    1991-01-01

    Flight test instrumentation engineers are provided with an introduction to digital processes on aircraft. Flight test instrumentation systems are rapidly evolving from analog intensive to digital intensive systems, including the use of onboard digital computers. Topics include: measurements that are digital in origin, sampling, encoding, transmitting, and storing of data. Particular emphasis is placed on modern avionic data bus architectures and what to be aware of when extracting data from them. Some example data extractions are given. Tradeoffs between digital logic families, trends in digital development, and design testing techniques are discussed. An introduction to digital filtering is also covered.

  10. Avionics architecture studies for the entry research vehicle

    NASA Technical Reports Server (NTRS)

    Dzwonczyk, M. J.; Mckinney, M. F.; Adams, S. J.; Gauthier, R. J.

    1989-01-01

    This report is the culmination of a year-long investigation of the avionics architecture for NASA's Entry Research Vehicle (ERV). The Entry Research Vehicle is conceived to be an unmanned, autonomous spacecraft to be deployed from the Shuttle. It will perform various aerodynamic and propulsive maneuvers in orbit and land at Edwards AFB after a 5 to 10 hour mission. The design and analysis of the vehicle's avionics architecture are detailed here. The architecture consists of a central triply redundant ultra-reliable fault tolerant processor attached to three replicated and distributed MIL-STD-1553 buses for input and output. The reliability analysis is detailed here. The architecture was found to be sufficiently reliable for the ERV mission plan.

  11. A study of software standards used in the avionics industry

    NASA Technical Reports Server (NTRS)

    Hayhurst, Kelly J.

    1994-01-01

    Within the past decade, software has become an increasingly common element in computing systems. In particular, the role of software used in the aerospace industry, especially in life- or safety-critical applications, is rapidly expanding. This intensifies the need to use effective techniques for achieving and verifying the reliability of avionics software. Although certain software development processes and techniques are mandated by government regulating agencies, no one methodology has been shown to consistently produce reliable software. The knowledge base for designing reliable software simply has not reached the maturity of its hardware counterpart. In an effort to increase our understanding of software, the Langley Research Center conducted a series of experiments over 15 years with the goal of understanding why and how software fails. As part of this program, the effectiveness of current industry standards for the development of avionics is being investigated. This study involves the generation of a controlled environment to conduct scientific experiments on software processes.

  12. Sail GTS ground system analysis: Avionics system engineering

    NASA Technical Reports Server (NTRS)

    Lawton, R. M.

    1977-01-01

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

  13. Design of an Ada expert system shell for the VHSIC avionic modular flight processor

    NASA Technical Reports Server (NTRS)

    Fanning, F. Jesse

    1992-01-01

    The Embedded Computer System Expert System Shell (ES Shell) is an Ada-based expert system shell developed at the Avionics Laboratory for use on the VHSIC Avionic Modular Processor (VAMP) running under the Ada Avionics Real-Time Software (AARTS) Operating System. The ES Shell provides the interface between the expert system and the avionics environment, and controls execution of the expert system. Testing of the ES Shell in the Avionics Laboratory's Integrated Test Bed (ITB) has demonstrated its ability to control a non-deterministic software application executing on the VAMP's which can control the ITB's real-time closed-loop aircraft simulation. The results of these tests and the conclusions reached in the design and development of the ES Shell have played an important role in the formulation of the requirements for a production-quality expert system inference engine, an ingredient necessary for the successful use of expert systems on the VAMP embedded avionic flight processor.

  14. Preliminary candidate advanced avionics system for general aviation

    NASA Technical Reports Server (NTRS)

    Mccalla, T. M.; Grismore, F. L.; Greatline, S. E.; Birkhead, L. M.

    1977-01-01

    An integrated avionics system design was carried out to the level which indicates subsystem function, and the methods of overall system integration. Sufficient detail was included to allow identification of possible system component technologies, and to perform reliability, modularity, maintainability, cost, and risk analysis upon the system design. Retrofit to older aircraft, availability of this system to the single engine two place aircraft, was considered.

  15. Avionics and airframe options: current usage and future plans.

    PubMed

    Mayfield, T; Cady, G

    1994-01-01

    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

  16. Description of the Experimental Avionics Systems Integration Laboratory (EASILY)

    NASA Technical Reports Server (NTRS)

    Outlaw, Bruce K. E.

    1994-01-01

    The Experimental Avionics Systems Integration Laboratory (EASILY) is a comprehensive facility used for development, integration, and preflight validation of hardware and software systems for the Terminal Area Productivity (TAP) Program's Transport Systems Research Vehicle (TSRV) experimental transport aircraft. This report describes the history, capabilities, and subsystems of EASILY. A functional description of the many subsystems is provided to give potential users the necessary knowledge of the capabilities of this facility.

  17. Conformity with the HIRF Environment Applied to Avionic System

    NASA Astrophysics Data System (ADS)

    Tristant, F.; Rotteleur, J. P.; Moreau, J. P.

    2012-05-01

    This paper presents the qualification and certification methodology applied to the avionic system for the HIRF and Lightning environment. Several versions of this system are installed in our legacy Falcon with different variations. The paper presents the compliance process taking into account the criticality and the complexity of the system, its installation, the level of exposition for EM environment and some solutions used by Dassault Aviation to demonstrate the compliance process.

  18. Comparison of Communication Architectures for Spacecraft Modular Avionics Systems

    NASA Technical Reports Server (NTRS)

    Gwaltney, D. A.; Briscoe, J. M.

    2006-01-01

    This document is a survey of publicly available information concerning serial communication architectures used, or proposed to be used, in aeronautic and aerospace applications. It focuses on serial communication architectures that are suitable for low-latency or real-time communication between physically distributed nodes in a system. Candidates for the study have either extensive deployment in the field, or appear to be viable for near-term deployment. Eleven different serial communication architectures are considered, and a brief description of each is given with the salient features summarized in a table in appendix A. This survey is a product of the Propulsion High Impact Avionics Technology (PHIAT) Project at NASA Marshall Space Flight Center (MSFC). PHIAT was originally funded under the Next Generation Launch Technology (NGLT) Program to develop avionics technologies for control of next generation reusable rocket engines. After the announcement of the Space Exploration Initiative, the scope of the project was expanded to include vehicle systems control for human and robotics missions. As such, a section is included presenting the rationale used for selection of a time-triggered architecture for implementation of the avionics demonstration hardware developed by the project team

  19. Time Triggered Protocol (TTP) for Integrated Modular Avionics

    NASA Technical Reports Server (NTRS)

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

    2006-01-01

    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.

  20. OMAC4S- Open Modular Avionics for Space Applications

    NASA Astrophysics Data System (ADS)

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

    2013-08-01

    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.

  1. NASA Ares I Crew Launch Vehicle Upper Stage Avionics and Software Overview

    NASA Technical Reports Server (NTRS)

    Nola, Charles L.; Blue, Lisa

    2008-01-01

    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.

  2. Computer simulation incorporating a helicopter model for evaluation of aircraft avionics systems

    NASA Technical Reports Server (NTRS)

    Ostroff, A. J.; Wood, R. B.

    1977-01-01

    A computer program was developed to integrate avionics research in navigation, guidance, controls, and displays with a realistic aircraft model. A user oriented program is described that allows a flexible combination of user supplied models to perform research in any avionics area. A preprocessor technique for selecting various models without significantly changing the memory storage is included. Also included are mathematical models for several avionics error models and for the CH-47 helicopter used in this program.

  3. Application of VHSIC technology to avionics maintenance

    NASA Astrophysics Data System (ADS)

    Babiak, N.; McDonald, B.; Spencer, D. J.

    A means is examined to significantly increase the availability of weapons systems through use of automatic built-in-test-equipment (BITE) embedded into the weapon system. Such equipment can perform in-flight, flightline, and shop level test and fault isolation. The MADS (Maintenance and Diagnostic System) concept provides a programmable, modular BIT capability for complex digital and analog assemblies based on maintenance network concepts developed within the VHSIC (very high speed integrated circuit) Phase I program. MADS features a modular approach, permitting the designer wide latitude in employing test techniques at a very modest hardware penalty. The first application of MADS is in the ALQ-131 VHSIC insertation program, for which significantly improved operational availability is projected.

  4. Spacelab system analysis: A study of the Marshall Avionics System Testbed (MAST)

    NASA Technical Reports Server (NTRS)

    Ingels, Frank M.; Owens, John K.; Daniel, Steven P.; Ahmad, F.; Couvillion, W.

    1988-01-01

    An analysis of the Marshall Avionics Systems Testbed (MAST) communications requirements is presented. The average offered load for typical nodes is estimated. Suitable local area networks are determined.

  5. Definition of avionics concepts for a heavy lift cargo vehicle. Volume 1: Executive summary

    NASA Technical Reports Server (NTRS)

    1989-01-01

    A cost effective, multiuser simulation, test, and demonstration facility to support the development of avionics systems for future space vehicles is examined. The technology needs and requirements of future Heavy Lift Cargo Vehicles (HLCVs) are analyzed and serve as the basis for sizing of the avionics facility, although the lab is not limited in use to support of HLCVs. Volume 1 provides a summary of the vehicle avionics trade studies, the avionics lab objectives, a summary of the lab's functional requirements and design, physical facility considerations, and cost estimates.

  6. Definition of avionics concepts for a heavy lift cargo vehicle, volume 2

    NASA Technical Reports Server (NTRS)

    1989-01-01

    A cost effective, multiuser simulation, test, and demonstration facility to support the development of avionics systems for future space vehicles is defined. The technology needs and requirements of future Heavy Lift Cargo Vehicles (HLCVs) are analyzed and serve as the basis for sizing of the avionics facility although the lab is not limited in use to support of HLCVs. Volume 2 is the technical volume and provides the results of the vehicle avionics trade studies, the avionics lab objectives, the lab's functional requirements and design, physical facility considerations, and a summary cost estimate.

  7. Avionics Architectures for Exploration: Ongoing Efforts in Human Spaceflight

    NASA Technical Reports Server (NTRS)

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

    2014-01-01

    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

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

    NASA Technical Reports Server (NTRS)

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

    2006-01-01

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

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

    NASA Astrophysics Data System (ADS)

    Viana Sanchez, Aitor; Taylor, Chris

    2010-08-01

    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)

  10. Formal verification of an avionics microprocessor

    NASA Technical Reports Server (NTRS)

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

    1995-01-01

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

  11. Shuttle avionics software trials, tribulations and success

    NASA Technical Reports Server (NTRS)

    Henderson, O. L.

    1985-01-01

    The early problems and the solutions developed to provide the required quality software needed to support the space shuttle engine development program are described. The decision to use a programmable digital control system on the space shuttle engine was primarily based upon the need for a flexible control system capable of supporting the total engine mission on a large complex pump fed engine. The mission definition included all control phases from ground checkout through post shutdown propellant dumping. The flexibility of the controller through reprogrammable software allowed the system to respond to the technical challenges and innovation required to develop both the engine and controller hardware. This same flexibility, however, placed a severe strain on the capability of the software development and verification organization. The overall development program required that the software facility accommodate significant growth in both the software requirements and the number of software packages delivered. This challenge was met by reorganization and evolution in the process of developing and verifying software.

  12. FPGA for Power Control of MSL Avionics

    NASA Technical Reports Server (NTRS)

    Wang, Duo; Burke, Gary R.

    2011-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    2001-01-01

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

  14. Fiber optic interconnect and optoelectronic packaging challenges for future generation avionics

    NASA Astrophysics Data System (ADS)

    Beranek, Mark W.

    2007-02-01

    Forecasting avionics industry fiber optic interconnect and optoelectronic packaging challenges that lie ahead first requires an assumption that military avionics architectures will evolve from today's centralized/unified concept based on gigabit laser, optical-to-electrical-to-optical switching and optical backplane technology, to a future federated/distributed or centralized/unified concept based on gigabit tunable laser, electro-optical switch and add-drop wavelength division multiplexing (WDM) technology. The requirement to incorporate avionics optical built-in test (BIT) in military avionics fiber optic systems is also assumed to be correct. Taking these assumptions further indicates that future avionics systems engineering will use WDM technology combined with photonic circuit integration and advanced packaging to form the technical basis of the next generation military avionics onboard local area network (LAN). Following this theme, fiber optic cable plants will evolve from today's multimode interconnect solution to a single mode interconnect solution that is highly installable, maintainable, reliable and supportable. Ultimately optical BIT for fiber optic fault detection and isolation will be incorporated as an integral part of a total WDM-based avionics LAN solution. Cost-efficient single mode active and passive photonic component integration and packaging integration is needed to enable reliable operation in the harsh military avionics application environment. Rugged multimode fiber-based transmitters and receivers (transceivers) with in-package optical BIT capability are also needed to enable fully BIT capable single-wavelength fiber optic links on both legacy and future aerospace platforms.

  15. Definition of avionics concepts for a heavy lift cargo vehicle, appendix A

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The major objective of the study task was to define a cost effective, multiuser simulation, test, and demonstration facility to support the development of avionics systems for future space vehicles. This volume provides the results of the main simulation processor selection study and describes some proof-of-concept demonstrations for the avionics test bed facility.

  16. GPM Avionics Module Heat Pipes Design and Performance Test Results

    NASA Technical Reports Server (NTRS)

    Ottenstein, Laura; DeChristopher, Mike

    2011-01-01

    The Global Precipitation Measurement (GPM) mission is an international network of satellites that provide the next-generation global observations of rain and snow. The GPM core satellite carries an advanced radar / radiometer system to measure precipitation from space and serve as a reference standard to unify precipitation measurements from a constellation of research and operational satellites. Through improved measurements of precipitation globally, the GPM mission will help to advance our understanding of Earth's water and energy cycle, improve forecasting of extreme events that cause natural hazards and disasters, and extend current capabilities in using accurate and timely information of precipitation to directly benefit society. The avionics module on the core satellite contains a number of electronics boxes which are cooled by a network of aluminum/ammonia heat pipes and a honeycomb radiator which contains thirteen embedded aluminum/ammonia heat pipes. All heat pipes were individually tested by the vendor (Advanced Cooling Technologies, Inc.) prior to delivery. Following delivery to NASA, the flight avionics radiator and the flight spare transport heat pipes were mounted to flight-like test structure and a system level thermal vacuum test was performed. This test, which used simulators in place of all electronics boxes, was done to verify the operation of the thermal control system as a whole. This presentation will discuss the design of the avionics module heat pipes, and then discuss performance tests results for the individual heat pipes prior to delivery and for the system level thermal vacuum test. All heat pipes met their performance requirements. However, it was found that the power was too low in some instances to start all of the smaller radiator spreader heat pipes when they were tested in a reflux configuration (which is the nominal test configuration). Although this lowered the efficiency of the radiator somewhat, it did not impact the operating

  17. Modeling of Large Avionic Structures in Electrical Network Simulations

    NASA Astrophysics Data System (ADS)

    Piche, A.; Perraud, R.; Lochot, C.

    2012-05-01

    The extensive introduction of carbon fiber reinforced plastics (CFRP) in conjunction with an increase of electrical systems in aircraft has led to new electromagnetic issues. This situation has reinforced the need for numerical simulation early in the design phase. In this context, we have proposed [1] a numerical methodology to deal with 3D CFRP avionic structures in time domain simulations at system level. This paper presents the last results on this subject and particularly the modeling of A350 fuselage in SABER computation containing the aircraft power distribution.

  18. MultIMA- Multi-Core in Integrated Modular Avionics

    NASA Astrophysics Data System (ADS)

    Silva, Claudio; Tatibana, Cassia

    2014-08-01

    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).

  19. Design of a hybrid switching architecture for avionic WDM platforms

    NASA Astrophysics Data System (ADS)

    Huang, Jin; Qiu, Kun; Xu, Bo; Ling, Yun

    2014-01-01

    A novel hybrid switching architecture using optical circuit switching for intra-subnet communication and fiber channel (FC) for inter-subnet communication is proposed. The proposed scheme utilizes small-size arrayed waveguide grating routers (AWGRs) and legacy FC switches to construct the large-scale avionic network, thus has the potential of the lower latency, the satisfactory network bandwidth and the lower power consumption. The simulation results verify that the proposed architecture outperforms FC switched architecture in terms of real time performance and power consumption.

  20. A fault-tolerant network architecture for integrated avionics

    NASA Technical Reports Server (NTRS)

    Butler, Bryan; Adams, Stuart

    1991-01-01

    The Army Fault-Tolerant Architecture (AFTA) under construction at the Charles Stark Draper Laboratory is an example of a highly integrated critical avionics system. The AFTA system must connect to other redundant and nonredundant systems, as well as to input/output devices. A fault-tolerant data bus (FTDB) is being developed to provide highly reliable communication between the AFTA computer and other network stations. The FTDB is being designed for Byzantine resilience and is probably capable of tolerating any single arbitrary fault. The author describes a prototype architecture for the fault-tolerant data bus.

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

    NASA Astrophysics Data System (ADS)

    Xu, Jiuping; Zhong, Zhengqiang; Xu, Lei

    2015-10-01

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

  2. A Formal Model of Partitioning for Integrated Modular Avionics

    NASA Technical Reports Server (NTRS)

    DiVito, Ben L.

    1998-01-01

    The aviation industry is gradually moving toward the use of integrated modular avionics (IMA) for civilian transport aircraft. An important concern for IMA is ensuring that applications are safely partitioned so they cannot interfere with one another. We have investigated the problem of ensuring safe partitioning and logical non-interference among separate applications running on a shared Avionics Computer Resource (ACR). This research was performed in the context of ongoing standardization efforts, in particular, the work of RTCA committee SC-182, and the recently completed ARINC 653 application executive (APEX) interface standard. We have developed a formal model of partitioning suitable for evaluating the design of an ACR. The model draws from the mathematical modeling techniques developed by the computer security community. This report presents a formulation of partitioning requirements expressed first using conventional mathematical notation, then formalized using the language of SRI'S Prototype Verification System (PVS). The approach is demonstrated on three candidate designs, each an abstraction of features found in real systems.

  3. IXV avionics architecture: Design, qualification and mission results

    NASA Astrophysics Data System (ADS)

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

    2016-07-01

    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.

  4. Software testability and its application to avionic software

    NASA Technical Reports Server (NTRS)

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

    1993-01-01

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

  5. Flight Avionics Sequencing Telemetry (FAST) DIV Latching Display

    NASA Technical Reports Server (NTRS)

    Moore, Charlotte

    2010-01-01

    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.

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

    NASA Astrophysics Data System (ADS)

    Lorentz, John

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

  7. A Wideband Satcom Based Avionics Network with CDMA Uplink and TDM Downlink

    NASA Technical Reports Server (NTRS)

    Agrawal, D.; Johnson, B. S.; Madhow, U.; Ramchandran, K.; Chun, K. S.

    2000-01-01

    The purpose of this paper is to describe some key technical ideas behind our vision of a future satcom based digital communication network for avionics applications The key features of our design are as follows: (a) Packetized transmission to permit efficient use of system resources for multimedia traffic; (b) A time division multiplexed (TDM) satellite downlink whose physical layer is designed to operate the satellite link at maximum power efficiency. We show how powerful turbo codes (invented originally for linear modulation) can be used with nonlinear constant envelope modulation, thus permitting the satellite amplifier to operate in a power efficient nonlinear regime; (c) A code division multiple access (CDMA) satellite uplink, which permits efficient access to the satellite from multiple asynchronous users. Closed loop power control is difficult for bursty packetized traffic, especially given the large round trip delay to the satellite. We show how adaptive interference suppression techniques can be used to deal with the ensuing near-far problem; (d) Joint source-channel coding techniques are required both at the physical and the data transport layer to optimize the end-to-end performance. We describe a novel approach to multiple description image encoding at the data transport layer in this paper.

  8. C-130 Automated Digital Data System (CADDS)

    NASA Technical Reports Server (NTRS)

    Scofield, C. P.; Nguyen, Chien

    1991-01-01

    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.

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

    NASA Astrophysics Data System (ADS)

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

    2013-08-01

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

  10. 1993 Aerospace Avionic Systems Division Conference, 3rd, Denver, CO, Apr. 22, 1993, Proceedings

    NASA Astrophysics Data System (ADS)

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

  11. Evolution of shuttle avionics redundancy management/fault tolerance

    NASA Technical Reports Server (NTRS)

    Boykin, J. C.; Thibodeau, J. R.; Schneider, H. E.

    1985-01-01

    The challenge of providing redundancy management (RM) and fault tolerance to meet the Shuttle Program requirements of fail operational/fail safe for the avionics systems was complicated by the critical program constraints of weight, cost, and schedule. The basic and sometimes false effectivity of less than pure RM designs is addressed. Evolution of the multiple input selection filter (the heart of the RM function) is discussed with emphasis on the subtle interactions of the flight control system that were found to be potentially catastrophic. Several other general RM development problems are discussed, with particular emphasis on the inertial measurement unit RM, indicative of the complexity of managing that three string system and its critical interfaces with the guidance and control systems.

  12. The vulnerability of commercial aircraft avionics to carbon fibers

    NASA Technical Reports Server (NTRS)

    Meyers, J. A.; Salmirs, S.

    1980-01-01

    Avionics components commonly used in commercial aircraft were tested for vulnerability to failure when operated in an environment with a high density of graphite fibers. The components were subjected to a series of exposures to graphite fibers of different lengths. Lengths used for the tests were (in order) 1 mm, 3 mm, and 10 mm. The test procedure included subjecting the equipment to characteristic noise and shock environments. Most of the equipment was invulnerable or did not fail until extremely high average exposures were reached. The single exception was an air traffic control transponder produced in the early 1960's. It had the largest case open area through which fibers could enter and it had no coated boards.

  13. Review and analysis of avionic helmet-mounted displays

    NASA Astrophysics Data System (ADS)

    Li, Hua; Zhang, Xin; Shi, Guangwei; Qu, Hemeng; Wu, Yanxiong; Zhang, Jianping

    2013-11-01

    With the development of new concepts and principles over the past century, helmet-mounted displays (HMDs) have been widely applied. This paper presents a review of avionic HMDs and shows some areas of active and intensive research. This review is focused on the optical design aspects and is divided into three sections to explore new optical design methods, which include an off-axis design, design with freeform optical surface, and design with holographic optical waveguide technology. Building on the fundamentals of optical design and engineering, the principles section primarily expounds on the five optical system parameters, which include weight, field of view, modulation transfer function, exit pupil size, and eye relief. We summarized the previous design works using new components to achieve compact and lightweight HMDs. Moreover, the paper presents a partial summary of the more notable experimental, prototype, fielded, and future HMD fixed-wing and rotary-wing programs.

  14. Partitioning in Avionics Architectures: Requirements, Mechanisms, and Assurance

    NASA Technical Reports Server (NTRS)

    Rushby, John

    1999-01-01

    Automated aircraft control has traditionally been divided into distinct "functions" that are implemented separately (e.g., autopilot, autothrottle, flight management); each function has its own fault-tolerant computer system, and dependencies among different functions are generally limited to the exchange of sensor and control data. A by-product of this "federated" architecture is that faults are strongly contained within the computer system of the function where they occur and cannot readily propagate to affect the operation of other functions. More modern avionics architectures contemplate supporting multiple functions on a single, shared, fault-tolerant computer system where natural fault containment boundaries are less sharply defined. Partitioning uses appropriate hardware and software mechanisms to restore strong fault containment to such integrated architectures. This report examines the requirements for partitioning, mechanisms for their realization, and issues in providing assurance for partitioning. Because partitioning shares some concerns with computer security, security models are reviewed and compared with the concerns of partitioning.

  15. Flight Deck Interval Management Avionics: Eye-Tracking Analysis

    NASA Technical Reports Server (NTRS)

    Latorella, Kara; Harden, John W.

    2015-01-01

    Interval Management (IM) is one NexGen method for achieving airspace efficiencies. In order to initiate IM procedures, Air Traffic Control provides an IM clearance to the IM aircraft's pilots that indicates an intended spacing from another aircraft (the target to follow - or TTF) and the point at which this should be achieved. Pilots enter the clearance in the flight deck IM (FIM) system; and once the TTF's Automatic Dependent Surveillance-Broadcast signal is available, the FIM algorithm generates target speeds to meet that IM goal. This study examined four Avionics Conditions (defined by the instrumentation and location presenting FIM information) and three Notification Methods (defined by the visual and aural alerts that notified pilots to IM-related events). Current commercial pilots flew descents into Dallas/Fort-Worth in a high-fidelity commercial flight deck simulation environment with realistic traffic and communications. All 12 crews experienced each Avionics Condition, where order was counterbalanced over crews. Each crew used only one of the three Notification Methods. This paper presents results from eye tracking data collected from both pilots, including: normalized number of samples falling within FIM displays, normalized heads-up time, noticing time, dwell time on first FIM display look after a new speed, a workload-related metric, and a measure comparing the scan paths of pilot flying and pilot monitoring; and discusses these in the context of other objective (vertical and speed profile deviations, response time to dial in commanded speeds, out-of-speed-conformance and reminder indications) and subjective measures (workload, situation awareness, usability, and operational acceptability).

  16. Preliminary Candidate Advanced Avionics System (PCAAS). [reduction in single pilot workload during instrument flight rules flight

    NASA Technical Reports Server (NTRS)

    Teper, G. L.; Hon, R. H.; Smyth, R. K.

    1977-01-01

    Specifications which define the system functional requirements, the subsystem and interface needs, and other requirements such as maintainability, modularity, and reliability are summarized. A design definition of all required avionics functions and a system risk analysis are presented.

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

    NASA Technical Reports Server (NTRS)

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

    2013-01-01

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

  18. Flight evaluation results from the general-aviation advanced avionics system program

    NASA Technical Reports Server (NTRS)

    Callas, G. P.; Denery, D. G.; Hardy, G. H.; Nedell, B. F.

    1983-01-01

    A demonstration advanced avionics system (DAAS) for general-aviation aircraft was tested at NASA Ames Research Center to provide information required for the design of reliable, low-cost, advanced avionics systems which would make general-aviation operations safer and more practicable. Guest pilots flew a DAAS-equipped NASA Cessna 402-B aircraft to evaluate the usefulness of data busing, distributed microprocessors, and shared electronic displays, and to provide data on the DAAS pilot/system interface for the design of future integrated avionics systems. Evaluation results indicate that the DAAS hardware and functional capability meet the program objective. Most pilots felt that the DAAS representative of the way avionics systems would evolve and felt the added capability would improve the safety and practicability of general-aviation operations. Flight-evaluation results compiled from questionnaires are presented, the results of the debriefings are summarized. General conclusions of the flight evaluation are included.

  19. Avionic Architecture for Model Predictive Control Application in Mars Sample & Return Rendezvous Scenario

    NASA Astrophysics Data System (ADS)

    Saponara, M.; Tramutola, A.; Creten, P.; Hardy, J.; Philippe, C.

    2013-08-01

    Optimization-based control techniques such as Model Predictive Control (MPC) are considered extremely attractive for space rendezvous, proximity operations and capture applications that require high level of autonomy, optimal path planning and dynamic safety margins. Such control techniques require high-performance computational needs for solving large optimization problems. The development and implementation in a flight representative avionic architecture of a MPC based Guidance, Navigation and Control system has been investigated in the ESA R&T study “On-line Reconfiguration Control System and Avionics Architecture” (ORCSAT) of the Aurora programme. The paper presents the baseline HW and SW avionic architectures, and verification test results obtained with a customised RASTA spacecraft avionics development platform from Aeroflex Gaisler.

  20. VIEW OF KENNEDY AVIONICS TEST SET LABORATORY, ROOM NO. MM6, ...

    Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

    VIEW OF KENNEDY AVIONICS TEST SET LABORATORY, ROOM NO. MM6, FACING NORTH - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  1. Lifelong Learning: An Imperative for Employment in Part of the Avionics Sector.

    ERIC Educational Resources Information Center

    Brodie, Ian

    2001-01-01

    Describes technological developments in the British avionics industry that have engendered higher skill requirements. Discusses challenges of using National Vocational Qualifications in the industry. Reviews implications for employers, workers, and trainers. (SK)

  2. The development process for the space shuttle primary avionics software system

    NASA Technical Reports Server (NTRS)

    Keller, T. W.

    1987-01-01

    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.

  3. An engineering approach to the use of expert systems technology in avionics applications

    NASA Technical Reports Server (NTRS)

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

    1986-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

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

    1975-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Orr, James K.; Peltier, Daryl

    2010-01-01

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

  6. Avionics architecture for the U.S. segment of the international space station alpha

    NASA Technical Reports Server (NTRS)

    Smith, Joseph F.; Mcdonald, Mark; Suchting, Steve; Schikner, Jeff

    1995-01-01

    The International Space Station Alpha (ISSA) is a joint project between the United States, European Space Agency, Japan, Canada and Russia to develop and fly a space station in the later part of the 1990s. The United States will be the largest hardware contributor to this project, and this paper will describe the avionics architecture for the U.S. provided pressurized modules and truss segments. The avionics contained within these U.S. modules and segments will perform many of the core engineering and payload support functions for the ISSA. These functions include: the command and data handling, communications and tracking, guidance navigation and control (in partnership with the Russian elements), and electrical power generation and distribution. This paper will describe the architecture of the avionics systems that will perform these core engineering avionics functions, as well as provide a discussion on the avionics necessary for the proper functioning of the core engineering avionics supported functions such as thermal control, life support, and mechanisms.

  7. Implementing the space shuttle data processing system with the space generic open avionics architecture

    NASA Technical Reports Server (NTRS)

    Wray, Richard B.; Stovall, John R.

    1993-01-01

    This paper presents an overview of the application of the Space Generic Open Avionics Architecture (SGOAA) to the Space Shuttle Data Processing System (DPS) architecture design. This application has been performed to validate the SGOAA, and its potential use in flight critical systems. The paper summarizes key elements of the Space Shuttle avionics architecture, data processing system requirements and software architecture as currently implemented. It then summarizes the SGOAA architecture and describes a tailoring of the SGOAA to the Space Shuttle. The SGOAA consists of a generic system architecture for the entities in spacecraft avionics, a generic processing external and internal hardware architecture, a six class model of interfaces and functional subsystem architectures for data services and operations control capabilities. It has been proposed as an avionics architecture standard with the National Aeronautics and Space Administration (NASA), through its Strategic Avionics Technology Working Group, and is being considered by the Society of Aeronautic Engineers (SAE) as an SAE Avionics Standard. This architecture was developed for the Flight Data Systems Division of JSC by the Lockheed Engineering and Sciences Company, Houston, Texas.

  8. The X-38 Spacecraft Fault-Tolerant Avionics System

    NASA Technical Reports Server (NTRS)

    Kouba,Coy; Buscher, Deborah; Busa, Joseph

    2003-01-01

    In 1995 NASA began an experimental program to develop a reusable crew return vehicle (CRV) for the International Space Station. The purpose of the CRV was threefold: (i) to bring home an injured or ill crewmember; (ii) to bring home the entire crew if the Shuttle fleet was grounded; and (iii) to evacuate the crew in the case of an imminent Station threat (i.e., fire, decompression, etc). Built at the Johnson Space Center, were two approach and landing prototypes and one spacecraft demonstrator (called V201). A series of increasingly complex ground subsystem tests were completed, and eight successful high-altitude drop tests were achieved to prove the design concept. In this program, an unprecedented amount of commercial-off-the-shelf technology was utilized in this first crewed spacecraft NASA has built since the Shuttle program. Unfortunately, in 2002 the program was canceled due to changing Agency priorities. The vehicle was 80% complete and the program was shut down in such a manner as to preserve design, development, test and engineering data. This paper describes the X-38 V201 fault-tolerant avionics system. Based on Draper Laboratory's Byzantine-resilient fault-tolerant parallel processing system and their "network element" hardware, each flight computer exchanges information on a strict timescale to process input data, compare results, and issue voted vehicle output commands. Major accomplishments achieved in this development include: (i) a space qualified two-fault tolerant design using mostly COTS (hardware and operating system); (ii) a single event upset tolerant network element board, (iii) on-the-fly recovery of a failed processor; (iv) use of synched cache; (v) realignment of memory to bring back a failed channel; (vi) flight code automatically generated from the master measurement list; and (vii) built in-house by a team of civil servants and support contractors. This paper will present an overview of the avionics system and the hardware

  9. Semiautonomous Avionics-and-Sensors System for a UAV

    NASA Technical Reports Server (NTRS)

    Shams, Qamar

    2006-01-01

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

  10. Analysis of technology requirements and potential demand for general aviation avionics systems for operation in the 1980's

    NASA Technical Reports Server (NTRS)

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

    1974-01-01

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

  11. ARINC 818 express for high-speed avionics video and power over coax

    NASA Astrophysics Data System (ADS)

    Keller, Tim; Alexander, Jon

    2012-06-01

    CoaXPress is a new standard for high-speed video over coax cabling developed for the machine vision industry. CoaXPress includes both a physical layer and a video protocol. The physical layer has desirable features for aerospace and defense applications: it allows 3Gbps (up to 6Gbps) communication, includes 21Mbps return path allowing for bidirectional communication, and provides up to 13W of power, all over a single coax connection. ARINC 818, titled "Avionics Digital Video Bus" is a protocol standard developed specifically for high speed, mission critical aerospace video systems. ARINC 818 is being widely adopted for new military and commercial display and sensor applications. The ARINC 818 protocol combined with the CoaXPress physical layer provide desirable characteristics for many aerospace systems. This paper presents the results of a technology demonstration program to marry the physical layer from CoaXPress with the ARINC 818 protocol. ARINC 818 is a protocol, not a physical layer. Typically, ARINC 818 is implemented over fiber or copper for speeds of 1 to 2Gbps, but beyond 2Gbps, it has been implemented exclusively over fiber optic links. In many rugged applications, a copper interface is still desired, by implementing ARINC 818 over the CoaXPress physical layer, it provides a path to 3 and 6 Gbps copper interfaces for ARINC 818. Results of the successful technology demonstration dubbed ARINC 818 Express are presented showing 3Gbps communication while powering a remote module over a single coax cable. The paper concludes with suggested next steps for bring this technology to production readiness.

  12. Use of Field Programmable Gate Array Technology in Future Space Avionics

    NASA Technical Reports Server (NTRS)

    Ferguson, Roscoe C.; Tate, Robert

    2005-01-01

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

  13. Serial Back-Plane Technologies in Advanced Avionics Architectures

    NASA Technical Reports Server (NTRS)

    Varnavas, Kosta

    2005-01-01

    Current back plane technologies such as VME, and current personal computer back planes such as PCI, are shared bus systems that can exhibit nondeterministic latencies. This means a card can take control of the bus and use resources indefinitely affecting the ability of other cards in the back plane to acquire the bus. This provides a real hit on the reliability of the system. Additionally, these parallel busses only have bandwidths in the 100s of megahertz range and EMI and noise effects get worse the higher the bandwidth goes. To provide scalable, fault-tolerant, advanced computing systems, more applicable to today s connected computing environment and to better meet the needs of future requirements for advanced space instruments and vehicles, serial back-plane technologies should be implemented in advanced avionics architectures. Serial backplane technologies eliminate the problem of one card getting the bus and never relinquishing it, or one minor problem on the backplane bringing the whole system down. Being serial instead of parallel improves the reliability by reducing many of the signal integrity issues associated with parallel back planes and thus significantly improves reliability. The increased speeds associated with a serial backplane are an added bonus.

  14. MIDEX Advanced Modular and Distributed Spacecraft Avionics Architecture

    NASA Technical Reports Server (NTRS)

    Ruffa, John A.; Castell, Karen; Flatley, Thomas; Lin, Michael

    1998-01-01

    MIDEX (Medium Class Explorer) is the newest line in NASA's Explorer spacecraft development program. As part of the MIDEX charter, the MIDEX spacecraft development team has developed a new modular, distributed, and scaleable spacecraft architecture that pioneers new spaceflight technologies and implementation approaches, all designed to reduce overall spacecraft cost while increasing overall functional capability. This resultant "plug and play" system dramatically decreases the complexity and duration of spacecraft integration and test, providing a basic framework that supports spacecraft modularity and scalability for missions of varying size and complexity. Together, these subsystems form a modular, flexible avionics suite that can be modified and expanded to support low-end and very high-end mission requirements with a minimum of redesign, as well as allowing a smooth, continuous infusion of new technologies as they are developed without redesigning the system. This overall approach has the net benefit of allowing a greater portion of the overall mission budget to be allocated to mission science instead of a spacecraft bus. The MIDEX scaleable architecture is currently being manufactured and tested for use on the Microwave Anisotropy Probe (MAP), an inhouse program at GSFC.

  15. Model-Based Verification and Validation of Spacecraft Avionics

    NASA Technical Reports Server (NTRS)

    Khan, M. Omair; Sievers, Michael; Standley, Shaun

    2012-01-01

    Verification and Validation (V&V) at JPL is traditionally performed on flight or flight-like hardware running flight software. For some time, the complexity of avionics has increased exponentially while the time allocated for system integration and associated V&V testing has remained fixed. There is an increasing need to perform comprehensive system level V&V using modeling and simulation, and to use scarce hardware testing time to validate models; the norm for thermal and structural V&V for some time. Our approach extends model-based V&V to electronics and software through functional and structural models implemented in SysML. We develop component models of electronics and software that are validated by comparison with test results from actual equipment. The models are then simulated enabling a more complete set of test cases than possible on flight hardware. SysML simulations provide access and control of internal nodes that may not be available in physical systems. This is particularly helpful in testing fault protection behaviors when injecting faults is either not possible or potentially damaging to the hardware. We can also model both hardware and software behaviors in SysML, which allows us to simulate hardware and software interactions. With an integrated model and simulation capability we can evaluate the hardware and software interactions and identify problems sooner. The primary missing piece is validating SysML model correctness against hardware; this experiment demonstrated such an approach is possible.

  16. The Cognitive Pilot Helmet: enabling pilot-aware smart avionics

    NASA Astrophysics Data System (ADS)

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

    2009-05-01

    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.

  17. System Software Framework for System of Systems Avionics

    NASA Technical Reports Server (NTRS)

    Ferguson, Roscoe C.; Peterson, Benjamin L; Thompson, Hiram C.

    2005-01-01

    Project Constellation implements NASA's vision for space exploration to expand human presence in our solar system. The engineering focus of this project is developing a system of systems architecture. This architecture allows for the incremental development of the overall program. Systems can be built and connected in a "Lego style" manner to generate configurations supporting various mission objectives. The development of the avionics or control systems of such a massive project will result in concurrent engineering. Also, each system will have software and the need to communicate with other (possibly heterogeneous) systems. Fortunately, this design problem has already been solved during the creation and evolution of systems such as the Internet and the Department of Defense's successful effort to standardize distributed simulation (now IEEE 1516). The solution relies on the use of a standard layered software framework and a communication protocol. A standard framework and communication protocol is suggested for the development and maintenance of Project Constellation systems. The ARINC 653 standard is a great start for such a common software framework. This paper proposes a common system software framework that uses the Real Time Publish/Subscribe protocol for framework-to-framework communication to extend ARINC 653. It is highly recommended that such a framework be established before development. This is important for the success of concurrent engineering. The framework provides an infrastructure for general system services and is designed for flexibility to support a spiral development effort.

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

    NASA Technical Reports Server (NTRS)

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

    1990-01-01

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

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

    NASA Astrophysics Data System (ADS)

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

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

  20. Advanced Launch System Multi-Path Redundant Avionics Architecture Analysis and Characterization

    NASA Technical Reports Server (NTRS)

    Baker, Robert L.

    1993-01-01

    The objective of the Multi-Path Redundant Avionics Suite (MPRAS) program is the development of a set of avionic architectural modules which will be applicable to the family of launch vehicles required to support the Advanced Launch System (ALS). To enable ALS cost/performance requirements to be met, the MPRAS must support autonomy, maintenance, and testability capabilities which exceed those present in conventional launch vehicles. The multi-path redundant or fault tolerance characteristics of the MPRAS are necessary to offset a reduction in avionics reliability due to the increased complexity needed to support these new cost reduction and performance capabilities and to meet avionics reliability requirements which will provide cost-effective reductions in overall ALS recurring costs. A complex, real-time distributed computing system is needed to meet the ALS avionics system requirements. General Dynamics, Boeing Aerospace, and C.S. Draper Laboratory have proposed system architectures as candidates for the ALS MPRAS. The purpose of this document is to report the results of independent performance and reliability characterization and assessment analyses of each proposed candidate architecture and qualitative assessments of testability, maintainability, and fault tolerance mechanisms. These independent analyses were conducted as part of the MPRAS Part 2 program and were carried under NASA Langley Research Contract NAS1-17964, Task Assignment 28.

  1. SAR Aircrew--HH-3F Avionics and HH-3F Flight Preparation. ACH3AV-0442. Second Edition, Revised.

    ERIC Educational Resources Information Center

    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…

  2. Avionics Systems Laboratory/Building 16. Historical Documentation

    NASA Technical Reports Server (NTRS)

    Slovinac, Patricia; Deming, Joan

    2011-01-01

    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

  3. Rendezvous strategy impacts on CTV avionics design, system reliability requirements, and available collision avoidance maneuvers

    NASA Technical Reports Server (NTRS)

    Donovan, William J.; Davis, John E.

    1991-01-01

    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.

  4. Rendezvous strategy impacts on CTV avionics design, system reliability requirements, and available collision avoidance maneuvers

    NASA Astrophysics Data System (ADS)

    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.

  5. The Consolidation of the End-to-End Avionics Systems Testbench

    NASA Astrophysics Data System (ADS)

    Wijnands, Quirien; Torelli, Felice; Blommestijn, Robert; Kranz, Stephan; Koster, Jean-Paul

    2014-08-01

    Over the past years, the Avionics System Test Bench (ATB) has been used to support the demonstration and validation of upcoming space avionics related standards and technologies in a representative environment. Next to this another main use-case of the facility has been to support projects in their needs of assessing particular technology related issues. In doing so, it was necessary to add activity- and project specifics to different configurations of the ATB, leading to a proliferation of facilities and technologies. In some cases however the results and lessons-learned from these efforts and activities were considered valuable to the ATB-concept in general and therefore needed preservation in the ATB mainstream for future reuse. Currently activities are ongoing to consolidate the End-To-End Avionics Systems TestBench (E2E-ATB). In this paper the resulting details of these activities are described as enhancements and improvements per ATB configuration.

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

    NASA Technical Reports Server (NTRS)

    Young, D. A.

    1984-01-01

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

  7. Predicting Cost/Reliability/Maintainability of Advanced General Aviation Avionics Equipment

    NASA Technical Reports Server (NTRS)

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

    1978-01-01

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

  8. Flight controls/avionics research - Impact on future civil helicopter operating efficiency and mission reliability

    NASA Technical Reports Server (NTRS)

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

    1979-01-01

    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.

  9. The Application of Fiber Optic Wavelength Division Multiplexing in RF Avionics

    NASA Technical Reports Server (NTRS)

    Ngo, Duc; Nguyen, Hung; Atiquzzaman, Mohammed; Sluss, James J., Jr.; Refai, Hakki H.

    2004-01-01

    This paper demonstrates a successful application of wavelength division multiplexing (WDM) to the avionics environment to support analog RF signal transmission. We investigate the simultaneous transmission of four RF signals (channels) over a single optical fiber. These four analog channels are sequentially multiplexed and demultiplexed at different points along a fiber optic backbone to more closely emulate the conditions found onboard aircraft. We present data from measurements of signal-to-noise ratio (SNR), transmission response (loss and gain), group delay that defines phase distortion, and dynamic range that defines nonlinear distortion. The data indicate that WDM is well-suited for avionics applications.

  10. Advanced information processing system for advanced launch system: Avionics architecture synthesis

    NASA Technical Reports Server (NTRS)

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

    1991-01-01

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

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

    NASA Astrophysics Data System (ADS)

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

    2015-09-01

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

  12. Design, development, and flight test of a demonstration advanced avionics system

    NASA Technical Reports Server (NTRS)

    Denergy, D. G.; Callas, G. P.; Hardy, G. H.; Nedell, W.

    1983-01-01

    Ames Research Center initiated a program in 1975 to provide the critical information required for the design of integrated avionics suitable for general aviation. The program emphasized the use of data busing, distributed microprocessors, shared electronic displays and data entry devices, and improved functional capability. Design considerations included cost, reliability, maintainability, and modularity. As a final step, a demonstration advanced avionics system (DAAS) was designed, built, and flight tested in a Cessna 402, twin engine, general aviation aircraft. A functional description of the DAAS, including a description of the system architecture, is presented and the program and flight test results are briefly reviewed.

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

    ERIC Educational Resources Information Center

    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…

  14. Infrared Avionics Signal Distribution using Wavelength Division Multiplexing

    NASA Technical Reports Server (NTRS)

    Atiquzzaman, Mohammed; Sluss, Jim; Nguyen, Hung; Ngo, Duc

    2003-01-01

    Pilots in the cockpits of aircrafts currently communicate with ground stations using Radio Frequency (RF) signals. Antennas mounted outside the aircraft receive and transmit RF signals from and to the ground stations. The RF signals received at the antennas are sent to the cockpit using coaxial cables. As the number of antennas needed to provide more than one frequency band in aircrafts increases, RF distribution media (such as coaxial cable) adds to the complexity and weight of the cockpit wiring. Concomitantly, the safety and signal to noise ratio also decreases due to the use of RF signals. The University of Oklahoma is collaborating with the National Aeronautics and Space Administration to develop optical fiber based schemes to replace the coaxial cable used for RF signal distribution within an aircraft. The project aims at exploiting emerging Wavelength Division Multiplexing (WDM) techniques to reduce the weight of cabling, and increase the signal to noise ratio and reliability. This will be achieved by wavelength division multiplexing the signals from the various antennas and then demultiplexing the signals to recover the original signals at the cockpit. This paper will show that (i) RF signals can not only be wavelength multiplexed at the end of a fiber, but additional signals can be inserted into the middle of the fiber using WDM technology, and (ii) the signals can also be successfully extracted by tapping into the middle of the fiber. We are currently extending our previous laboratory prototype (which could multiplex signals only at the end of the fiber) to include additional multiplexing and demultiplexing of RF signals from the middle of the optical backbone with a view to validating the proof of concept, and carrying out measurements to determine the effectiveness of Wavelength Division Multiplexing for avionics applications. A test bed to perform measurements of several relevant parameters for various modulation schemes and frequencies (such as VHF

  15. Avionics Instrument Systems Specialist Career Ladder: AFSCs 32531, 32551, 31571, and 32591. Occupational Survey Report.

    ERIC Educational Resources Information Center

    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…

  16. Guidelines for application of fluorescent lamps in high-performance avionic backlight systems

    NASA Astrophysics Data System (ADS)

    Syroid, Daniel D.

    1997-07-01

    Fluorescent lamps have proven to be well suited for use in high performance avionic backlight systems as demonstrated by numerous production applications for both commercial and military cockpit displays. Cockpit display applications include: Boeing 777, new 737s, F-15, F-16, F-18, F-22, C- 130, Navy P3, NASA Space Shuttle and many others. Fluorescent lamp based backlights provide high luminance, high lumen efficiency, precision chromaticity and long life for avionic active matrix liquid crystal display applications. Lamps have been produced in many sizes and shapes. Lamp diameters range from 2.6 mm to over 20 mm and lengths for the larger diameter lamps range to over one meter. Highly convoluted serpentine lamp configurations are common as are both hot and cold cathode electrode designs. This paper will review fluorescent lamp operating principles, discuss typical requirements for avionic grade lamps, compare avionic and laptop backlight designs and provide guidelines for the proper application of lamps and performance choices that must be made to attain optimum system performance considering high luminance output, system efficiency, dimming range and cost.

  17. MECHANIZATION STUDY OF THE TECHNICAL LIBRARY U.S. NAVAL AVIONICS FACILITY, INDIANAPOLIS, INDIANA.

    ERIC Educational Resources Information Center

    KERSHAW, G.A.; AND OTHERS

    THE NAVAL AVIONICS FACILITY, INDIANAPOLIS (NAFI) TECHNICAL LIBRARY IS PLANNING A MECHANIZED SYSTEM TO PRODUCE A PERMUTED INDEX OF PERTINENT PERIODICAL REFERENCES AND PROCEEDINGS, WITH BOOKS AND DOCUMENTS TO BE ADDED LATER. INPUT TO THE SYSTEM IS PUNCHED PAPER TAPE PREPARED FROM THE SOURCE MATERIAL, AND THE PRIMARY PROGRAM IS A "CANNED" GENERAL…

  18. Flight evaluation results from the general-aviation advanced avionics system program

    NASA Technical Reports Server (NTRS)

    Callas, G. P.; Denery, D. G.; Hardy, G. H.; Nedell, B. F.

    1983-01-01

    A demonstration advanced avionics system (DAAS) for general-aviation aircraft was tested at NASA Ames Research Center to provide information required for the design of reliable, low-cost, advanced avionics systems which would make general-aviation operations safer and more practicable. Guest pilots flew a DAAS-equipped NASA Cessna 402-B aircraft to evaluate the usefulness of data busing, distributed microprocessors, and shared electronic displays, and to provide data on the DAAS pilot/system interface for the design of future integrated avionics systems. Evaluation results indicate that the DAAS hardware and functional capability meet the program objective. Most pilots felt that the DAAS representative of the way avionics systems would evolve and felt the added capability would improve the safety and practicability of general-aviation operations. Flight-evaluation results compiled from questionnaires are presented, the results of the debriefings are summarized. General conclusions of the flight evaluation are included. Previously announced in STAR as N84-10042

  19. General aviation activity and avionics survey. Annual summary report, CY 1985

    SciTech Connect

    Not Available

    1987-03-01

    This report presents the results and a description of the 1985 General Aviation Activity and Avionics Survey. The survey was conducted during 1986 by the FAA to obtain information on the activity and avionics of the United States registered general aviation aircraft fleet, the dominant component of civil aviation in the U.S. The survey was based on a statistically selected sample of about 10.3 percent of the general aviation fleet. A responses rate of 63.7 percent was obtained. Survey results based upon response but are expanded upward to represent the total population. Survey results revealed that during 1985 an estimated 34.1 million hours of flying time were logged and 88.7 million operations were performed by the 210,654 active general aviation aircraft in the U.S. fleet. The mean annual flight time per aircraft was 158.2 hours. The active aircraft represented about 77.9 percent of the registered general aviation fleet. The report contains breakdowns of these and other statistics by manufacturer/model group, aircraft, state and region of based aircraft, and primary use. Also included are fuel consumption, lifetime airframe hours, avionics, engine hours, and miles flown estimates, as well as tables for detailed analysis of the avionics capabilities of the general aviation fleet. New to the report this year are estimates of the number of landings, IFR hours flown, and the cost and grade of fuel consumed by the GA fleet.

  20. General aviation activity and avionics survey. Annual report for CY81

    SciTech Connect

    Schwenk, J.C.; Carter, P.W.

    1982-12-01

    This report presents the results and a description of the 1981 General Aviation Activity and Avionics Survey. The survey was conducted during 1982 by the FAA to obtain information on the activity and avionics of the United States registered general aviation aircraft fleet, the dominant component of civil aviation in the U.S. The survey was based on a statistically selected sample of about 8.9 percent of the general aviation fleet and obtained a response rate of 61 percent. Survey results are based upon response but are expanded upward to represent the total population. Survey results revealed that during 1981 an estimated 40.7 million hours of flying time were logged by the 213,226 active general aviation aircraft in the U.S. fleet, yielding a mean annual flight time per aircraft of 188.1 hours. The active aircraft represented about 83 percent of the registered general aviation fleet. The report contains breakdowns of these and other statistics by manufacturer/model group, aircraft type, state and region of based aircraft, and primary use. Also included are fuel consumption, lifetime airframe hours, avionics, and engine hours estimates. In addition, tables are included for detailed analysis of the avionics capabilities of GA fleet.

  1. SAIL payload accommodations study. [ground handling for payload and avionics verification

    NASA Technical Reports Server (NTRS)

    Neubaur, R. J.

    1977-01-01

    Methods for accommodating payloads in SAIL are evaluated. It is concluded that a special payload be used as the standard method for verifying avionics systems and experiments. It is recommended that the baselined North door entrance method be retained for accommodation of flight type payloads.

  2. Modularity concepts for the Multi-Path Redundant Avionics Suite (MPRAS)

    NASA Astrophysics Data System (ADS)

    Herbella, Gary

    The use of modularity within the Multipath Redundant Avionics Suite project is discussed. Modularity is considered at several levels, including systems, subsystems, electronic circuit assemblies, and even functionality within circuit assemblies. MPRAS maintains the modularity of PAVE PILLAR and extends it to include modules designed to provide efficient input/output functions and to support implementation of multistring redundancy. A method of configuring multiple sets of avionics modules (clusters) into a fault-tolerant redundant subsystem has been developed. These subsystems are intended to be incorporated into the overall system in a modular fashion to support vehicles such as the advanced launch system, which are themselves designed as modular vehicle families. The software operating system is also modular, based on the Ada high order language, and can be configured for specific vehicle functions. Deterministic system software operation and high levels of avionics testability provide an environment intended to keep system operations costs as low as possible. The result is an avionics architecture which can be used in a wide variety of applications, from the simplest launch vehicles to complex systems envisioned for future space exploration.

  3. Space shuttle program: Shuttle Avionics Integration Laboratory. Volume 7: Logistics management plan

    NASA Technical Reports Server (NTRS)

    1974-01-01

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

  4. Software survey for the avionics test bed. [for large space structures

    NASA Technical Reports Server (NTRS)

    Cobb, J. M.

    1981-01-01

    A survey was conducted to itemize software programs that could possibly be used in the development of an avionics test bed for shuttle attached or autonomous large space structures. The results of this survey are presented. Each program is described on a standard form.

  5. An overview of the F-117A avionics flight test program

    SciTech Connect

    Silz, R. )

    1992-02-01

    This paper is an overview of the history of the F-117A avionics flight test program. System design concepts and equipment selections are explored followed by a review of full scale development and full capability development testing. Flight testing the Weapon System Computational Subsystem upgrade and the Offensive Combat Improvement Program are reviewed. Current flight test programs and future system updates are highlighted.

  6. The Avionics SOIS Services of CORDET On-Board Software Architecture

    NASA Astrophysics Data System (ADS)

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

    2013-08-01

    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.

  7. Orion MPCV Service Module Avionics Ring Pallet Testing, Correlation, and Analysis

    NASA Technical Reports Server (NTRS)

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

    2012-01-01

    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.

  8. Application of industry-standard guidelines for the validation of avionics software

    NASA Technical Reports Server (NTRS)

    Hayhurst, Kelly J.; Shagnea, Anita M.

    1990-01-01

    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.

  9. 78 FR 54791 - Proposed Additional Airworthiness Design Standards: Advanced Avionics Under the Special Class...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-06

    ... 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...-49, ``Electrical bonding and protection against lightning and static electricity'' 14 CFR 23.1307...

  10. Industrial Arts for the Elementary School: 23rd Yearbook.

    ERIC Educational Resources Information Center

    Thrower, Robert G., Ed.; Weber, Robert D., Ed.

    Fourth in a series of yearbooks presenting an overview of industrial arts at the various levels of education, the yearbook clarifies the contribution of industrial arts at the elementary school level. Fifteen educators from industrial arts and related field have authored the 12 chapters of the yearbook. Chapter 1 (Mary-Margaret Scobey and Grace…

  11. Minutes of the 23rd Eplosives Safety Seminar, volume 2

    NASA Astrophysics Data System (ADS)

    1988-08-01

    Some areas of discussion at this seminar were: Hazards and risks of the disposal of chemical munitions using a cryogenic process; Special equipment for demilitarization of lethal chemical agent filled munitions; explosive containment room (ECR) repair Johnston Atoll chemical agent disposal system; Sympathetic detonation testing; Blast loads, external and internal; Structural reponse testing of walls, doors, and valves; Underground explosion effects, external airblast; Explosives shipping, transportation safety and port licensing; Explosive safety management; Underground explosion effects, model test and soil rock effects; Chemical risk and protection of workers; and Full scale explosives storage test.

  12. NREL preprints for the 23rd IEEE Photovoltaic Specialists Conference

    SciTech Connect

    Fitzgerald, M.

    1993-05-01

    Topics covered include various aspects of solar cell fabrication and performance. Aluminium-gallium arsenides, cadmium telluride, amorphous silicon, and copper-indium-gallium selenides are all characterized in their applicability in solar cells.

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

    NASA Technical Reports Server (NTRS)

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

    2012-01-01

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

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

    NASA Technical Reports Server (NTRS)

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

    2009-01-01

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

  15. Development and flight test experiences with a flight-crucial digital control system

    NASA Technical Reports Server (NTRS)

    Mackall, Dale A.

    1988-01-01

    Engineers and scientists in the advanced fighter technology integration (AFTI) F-16 program investigated the integration of emerging technologies into an advanced fighter aircraft. AFTI's three major technologies included: flight-crucial digital control, decoupled aircraft flight control, and integration of avionics, flight control, and pilot displays. In addition to investigating improvements in fighter performance, researchers studied the generic problems confronting the designers of highly integrated flight-crucial digital control. An overview is provided of both the advantages and problems of integration digital control systems. Also, an examination of the specification, design, qualification, and flight test life-cycle phase is provided. An overview is given of the fault-tolerant design, multimoded decoupled flight control laws, and integrated avionics design. The approach to qualifying the software and system designs is discussed, and the effects of design choices on system qualification are highlighted.

  16. AFTI/F-16 digital flight control system experience

    NASA Technical Reports Server (NTRS)

    Mackall, D. A.

    1984-01-01

    The Advanced Flighter Technology Integration (AFTI) F-16 program is investigating the integration of emerging technologies into an advanced fighter aircraft. The three major technologies involved are the triplex digital flight control system; decoupled aircraft flight control; and integration of avionics, pilot displays, and flight control. In addition to investigating improvements in fighter performance, the AFTI/F-16 program provides a look at generic problems facing highly integrated, flight-crucial digital controls. An overview of the AFTI/F-16 systems is followed by a summary of flight test experience and recommendations.

  17. The 727 approach energy management system avionics specification (preliminary)

    NASA Technical Reports Server (NTRS)

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

    1976-01-01

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

  18. Development of reliable electronic packaging solutions for spacecraft avionics miniaturization using embedded passice devices

    NASA Technical Reports Server (NTRS)

    Schatzel, Don

    2003-01-01

    Miniaturization of electronic packages will play a key rule in future space avionics systems. Smaller avionics packages will reduce payloads while providing greater functionality for information processing and mission instrumentation. Current surface mount technology discrete passive devices not only take up significant space but also add weight. To that end, the use of embedded passive devices, such as capacitors, inductors and resistors will be instrumental in allowing electronics to be made smaller and lighter. Embedded passive devices fabricated on silicon or like substrates using thin film technology, promise great savings in circuit volume, as well as potentially improving electrical performance by decreasing parasitic losses. These devices exhibit a low physical profile and allow the circuit footprint to be reduced by stacking passive elements within a substrate. Thin film technologies used to deposit embedded passive devices are improving and costs associated with the process are decreasing.

  19. Cross channel dependency requirements of the multi-path redundant avionics suite

    NASA Astrophysics Data System (ADS)

    Martin, Fred; Adams, Darryl

    Requirements for cross channel dependencies in the multipath redundant avionics suite (MPRAS) architecture are described. MPRAS is a data synchronous avionics architecture for space launch vehicle applications. The MPRAS cross channel data link (CCDL) provides the mechanism, required by data synchronous architectures, to exchange data and maintain synchronization among redundant channels. MPRAS architectural requirements impose a variety of characteristics for cross channel dependencies which make traditional CCDL solutions unacceptable for MPRAS target applications. The MPRAS CCDL requirements have led to a CCDL design which maintains resilience to faults, does not introduce large cross channel bandwidth reductions, and meets the other established MPRAS CCDL requirements. A review of fault-tolerant system principles applicable to CCDL issues is presented as well as a top-level functional description of the MPRAS CCDL design.

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

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

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

  1. Is Integrated Modular Avionic a Solution for ATV like Spacecraft Control?

    NASA Astrophysics Data System (ADS)

    Boudillet, Olivier; Dalemagne, Didier; Peron, Thierry

    2010-09-01

    The design of complex flight control avionics, such as the one of the Automated Transfer Vehicle(ATV), first European spaceship built to service the International Space Station(ISS), could be simplified by the use of the Integrated Modular Avionics(IMA) approach. The current ATV architecture implements segregated On Board Computers(OBC) to execute the nominal software(of criticality level C) and the Safety related one(of criticality level A). This paper first presents a case study of implementing mock-ups of these two pieces of software on the same computer in compliance with the ARINC 653 guidelines of the IMA standard. The second part discusses the true advantages and limitations for using such approach in the case of large spaceships such as the ATV.

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

    NASA Technical Reports Server (NTRS)

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

    2008-01-01

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

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

    NASA Technical Reports Server (NTRS)

    Kulkarni, Nilesh; Krishnakumar, Kalmaje

    2005-01-01

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

  4. Validation Methods for Fault-Tolerant avionics and control systems, working group meeting 1

    NASA Technical Reports Server (NTRS)

    1979-01-01

    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.

  5. Demonstration Advanced Avionics System (DAAS) functional description. [Cessna 402B aircraft

    NASA Technical Reports Server (NTRS)

    1980-01-01

    A comprehensive set of general aviation avionics were defined for integration into an advanced hardware mechanization for demonstration in a Cessna 402B aircraft. Block diagrams are shown and system and computer architecture as well as significant hardware elements are described. The multifunction integrated data control center and electronic horizontal situation indicator are discussed. The functions that the DAAS will perform are examined. This function definition is the basis for the DAAS hardware and software design.

  6. Synthetic-vision application: concept, validation, and development in integrated modular avionics architecture

    NASA Astrophysics Data System (ADS)

    Stuetz, Peter; Braemer, Emanuel; Schulte, Axel; White, Colin; Kloeckner, Wolfgang

    2001-08-01

    Enhanced and synthetic vision applications for flight guidance are on the verge of commercialisation and wide-scale employment. The paper will first give an overview at the characteristics and benefits of these types of displays, and focus afterwards on their implementation in an integrated modular avionics environment. The Enhanced/Synthetic Flight Guidance Display is a promising approach to the solution for the problems of poor visibility low-level flight. It yields a computer-generated three-dimensional cockpit view and can optionally be combined with an imaging sensor (e.g. FLIR, mmWR, LL-TV). The paper will provide details on the technical concept and the evaluation of a functional prototype in flight trials. After functional validation, a enhanced/synthetic vision display was chosen to be ESGs first avionics application to be transferred into an integrated modular avionics architecture. This software prototype implementation takes into account the results so far achieved in the Allied Standard Avionics Architecture Council (ASAAC) programme. The effort of this programme to define an open system architecture will be addressed in the paper. The architecture's characteristics of a clearly defined layer structure and its strict hardware-software separation will be explained. Finally the paper addresses the allocation of the functions necessary for the synthetic vision display. It explains how database access, I/O to other systems, numerical calculation and graphics generation are mapped to IMA-based mass memory, data processing and graphics processing components. The paper finishes with the presentation of first successful implementation results.

  7. LCD cutting process: remanufacture of 4:3 aspect commercial into 1:1 avionics displays

    NASA Astrophysics Data System (ADS)

    Craig, David M.

    2000-08-01

    The recent business difficulties in manufacturing avionic grade AMLCDs from scratch has focussed attention on the alternative route of remanufacturing commercial grade AMLCDs to suite the optical and environmental requirements of cockpit displays. A major difficulty in this approach has been the absence of commercially available glass with the 1:1 aspect ratio often requested, particularly for retrofits. A proven method is described which circumvents this difficulty by allowing an AMLCD to be reshaped after its original manufacture.

  8. 78 FR 42898 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-18

    ...We propose to adopt a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R[eacute]gional Model ATR72-101, - 201, -102, -202, -211, -212, and -212A airplanes. This proposed AD was prompted by reports of airplane incidents and accidents that have occurred because of low-level fuel tank situations and fuel starvation that resulted in engine flameouts. This proposed AD would......

  9. 78 FR 65183 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-31

    ...We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR72-101, -201, - 102, -202, -211, -212, and -212A airplanes. This AD was prompted by reports of airplane incidents and accidents that have occurred because of low-level fuel tank situations and fuel starvation that resulted in engine flameouts. This AD requires installing a fuel......

  10. Optimization of a fin-plate heat exchanger for cooling avionic electronics

    NASA Astrophysics Data System (ADS)

    Eby, R. J.; Karam, R. D.

    1980-07-01

    This paper deals with an engineering evaluation of multichanneled cold plates of the type used in avionics components temperature control. The equations of flow and heat transfer are solved in view of the constraints of the geometric parameters, and the results are optimized in terms of minimizing the temperature difference between the components and the cooling air. An example is given to illustrate application of the theory.

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

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

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

  12. General aviation activity and avionics survey. 1978. Annual summary report cy 1978

    SciTech Connect

    Schwenk, J.C.

    1980-03-01

    This report presents the results and a description of the 1978 General Aviation Activity and Avionics Survey. The survey was conducted during early 1979 by the FAA to obtain information on the activity and avionics of the United States registered general aviation aircraft fleet, the dominant component of civil aviation in the U.S. The survey was based on a statistically selected sample of about 13.3 percent of the general aviation fleet and obtained a response rate of 74 percent. Survey results are based upon responses but are expanded upward to represent the total population. Survey results revealed that during 1978 an estimated 39.4 million hours of flying time were logged by the 198,778 active general aviation aircraft in the U.S. fleet, yielding a mean annual flight time per aircraft of 197.7 hours. The active aircraft represented 85 percent of the registered general aviation fleet. The report contains breakdowns of these and other statistics by manufacturer/model group, aircraft type, state and region of based aircraft, and primary use. Also included are fuel consumption, lifetime airframe hours, avionics, and engine hours estimates.

  13. NEXUS Scalable and Distributed Next-Generation Avionics Bus for Space Missions

    NASA Technical Reports Server (NTRS)

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

    2011-01-01

    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 (< 100 mW per Gbps); is lightweight with about a 5,000-logic-gate footprint; and is implemented in a small Bus Interface Unit (BIU) with reconfigurable back-end providing interface to legacy subsystems. NEXUS enhances a commercial interconnect standard, Serial RapidIO, to meet 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.

  14. Silicon Carbide Mixers Demonstrated to Improve the Interference Immunity of Radio-Based Aircraft Avionics

    NASA Technical Reports Server (NTRS)

    Neudeck, Philip G.

    1998-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Nelson, Kurt

    1991-01-01

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

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

    NASA Astrophysics Data System (ADS)

    Nelson, Kurt

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

  17. Avionics of the Cyclone Global Navigation Satellite System (CYGNSS) microsat constellation

    NASA Astrophysics Data System (ADS)

    Dickinson, John R.; Alvarez, Jennifer L.; Rose, Randall J.; Ruf, Christopher S.; Walls, Buddy J.

    The Cyclone Global Navigation Satellite System (CYGNSS), which was recently selected as the Earth Venture-2 investigation by NASA's Earth Science System Pathfinder (ESSP) Program, measures the ocean surface wind field with unprecedented temporal resolution and spatial coverage, under all precipitating conditions, and over the full dynamic range of wind speeds experienced in a tropical cyclone (TC). The CYGNSS flight segment consists of 8 microsatellite-class observatories, which represent SwRI's first spacecraft bus design, installed on a Deployment Module for launch. They are identical in design but provide their own individual contribution to the CYGNSS science data set. Subsystems include the Attitude Determination and Control System (ADCS), the Communication and Data Subsystem (CDS), the Electrical Power Supply (EPS), and the Structure, Mechanisms, and Thermal Subsystem (SMT). This paper will present an overview of the mission and the avionics, including the ADCS, CDS, and EPS, in detail. Specifically, we will detail how off-the-shelf components can be utilized to do ADCS and will highlight how SwRI's existing avionics solutions will be adapted to meet the requirements and cost constraints of microsat applications. Avionics electronics provided by SwRI include a command and data handling computer, a transceiver radio, a low voltage power supply (LVPS), and a peak power tracker (PPT).

  18. A Fault Tolerant System for an Integrated Avionics Sensor Configuration

    NASA Technical Reports Server (NTRS)

    Caglayan, A. K.; Lancraft, R. E.

    1984-01-01

    An aircraft sensor fault tolerant system methodology for the Transport Systems Research Vehicle in a Microwave Landing System (MLS) environment is described. The fault tolerant system provides reliable estimates in the presence of possible failures both in ground-based navigation aids, and in on-board flight control and inertial sensors. Sensor failures are identified by utilizing the analytic relationships between the various sensors arising from the aircraft point mass equations of motion. The estimation and failure detection performance of the software implementation (called FINDS) of the developed system was analyzed on a nonlinear digital simulation of the research aircraft. Simulation results showing the detection performance of FINDS, using a dual redundant sensor compliment, are presented for bias, hardover, null, ramp, increased noise and scale factor failures. In general, the results show that FINDS can distinguish between normal operating sensor errors and failures while providing an excellent detection speed for bias failures in the MLS, indicated airspeed, attitude and radar altimeter sensors.

  19. Deterministic digital WDM LAN for controlled configurations

    NASA Astrophysics Data System (ADS)

    Mazurowski, John

    2013-09-01

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

  20. Vertical guidance performance analysis of the L1-L5 dual-frequency GPS/WAAS user avionics sensor.

    PubMed

    Jan, Shau-Shiun

    2010-01-01

    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

  1. System requirements for head down and helmet mounted displays in the military avionics environment

    SciTech Connect

    Flynn, M.F.; Kalmanash, M.; Sethna, V.

    1996-12-31

    The introduction of flat panel display technologies into the military avionics cockpit is a challenging proposition, due to the very difficult system level requirements which must be met. These relate to environmental extremes (temperature and vibrational), sever ambient lighting conditions (10,000 fL to nighttime viewing), night vision system compatibility, and wide viewing angle. At the same time, the display system must be packaged in minimal space and use minimal power. The authors will present details on the display system requirements for both head down and helmet mounted systems, as well as information on how these challenges may be overcome.

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

    NASA Technical Reports Server (NTRS)

    Coffey, Connor

    2015-01-01

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

  3. A comparison of computer architectures for the NASA demonstration advanced avionics system

    NASA Technical Reports Server (NTRS)

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

    1979-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

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

    1993-01-01

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

  5. Cycle O (CY 1991) NLS trade studies and analyses, book 2. Part 1: Avionics and systems

    NASA Technical Reports Server (NTRS)

    Harris, Richard; Kirkland, Zach

    1992-01-01

    An assessment was conducted to determine the maximum LH2 tank stretch capability based on the constraints of the manufacturing, tooling and facilities at the Michoud Assembly Facility in New Orleans, Louisiana. The maximum tank stretch was determined to be 5 ft. with minor or no modifications, a stretch of 11 ft. with some possible facility modifications and beyond 11 ft. significant new facilities are required. A cost analysis was performed to evaluate the impacts for various stretch lengths. Tasks that were defined to perform trades and studies regarding the best approach to meet requirements for the National Launch System Avionics are also discussed.

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

    NASA Astrophysics Data System (ADS)

    Schulz, H.-W., , Dr.

    2011-09-01

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

  7. Investigation of RF Emissions From Wireless Networks as a Threat to Avionic Systems

    NASA Technical Reports Server (NTRS)

    Salud, Maria Theresa P.; Williams, Reuben A. (Technical Monitor)

    2002-01-01

    The paper focuses on understanding and obtaining preliminary measurements of radiated field (RF) emissions of laptop/wireless local area network (WLAN) systems. This work is part of a larger research project to measure radiated emissions of wireless devices to provide a better understanding for potential interference with crucial aircraft avionics systems. A reverberation chamber data collection process is included, as well as recommendations for additional tests. Analysis of measurements from devices under test (DUTs) proved inconclusive for addressing potential interference issues. Continued effort is expected to result in a complete easily reproducible test protocol. The data and protocol presented here are considered preliminary.

  8. Safe and Secure Partitioning with Pikeos: Towards Integrated Modular Avionics in Space

    NASA Astrophysics Data System (ADS)

    Almeida, J.; Prochazka, M.

    2009-05-01

    This paper presents our approach to logical partitioning of spacecraft onboard software. We present PikeOS, a separation micro-kernel which applies the state-of-the- art techniques and widely recognised standards such as ARINC 653 and MILS in order to guarantee safety and security properties of partitions executing software with different criticality and confidentiality. We provide an overview of our approach, also used in the Securely Partitioning Spacecraft Computing Resources project, an ESA TRP contract, which shifts spacecraft onboard software development towards the Integrated Modular Avionics concept with relevance for dual-use military and civil missions.

  9. Solving Autonomy Technology Gaps through Wireless Technology and Orion Avionics Architectural Principles

    NASA Astrophysics Data System (ADS)

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

    2008-01-01

    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

  10. CSI L2 - Reconstructing Herschel/Planck, Anomalies on the Avionics Bench

    NASA Astrophysics Data System (ADS)

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

    2010-08-01

    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.

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

    NASA Technical Reports Server (NTRS)

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

    1990-01-01

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

  12. Digital Libraries.

    ERIC Educational Resources Information Center

    Fox, Edward A.; Urs, Shalini R.

    2002-01-01

    Provides an overview of digital libraries research, practice, and literature. Highlights include new technologies; redefining roles; historical background; trends; creating digital content, including conversion; metadata; organizing digital resources; services; access; information retrieval; searching; natural language processing; visualization;…

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

    NASA Technical Reports Server (NTRS)

    Hunter, Don J.; Halpert, Gerald

    1999-01-01

    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.

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

    NASA Astrophysics Data System (ADS)

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

    2013-08-01

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

  15. Requirements Baseline for Integrated Modular Avionics for Space Separation Kernel Qualification

    NASA Astrophysics Data System (ADS)

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

    2015-09-01

    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.

  16. Improving geolocation and spatial accuracies with the modular integrated avionics group (MIAG)

    NASA Astrophysics Data System (ADS)

    Johnson, Einar; Souter, Keith

    1996-05-01

    The modular integrated avionics group (MIAG) is a single unit approach to combining position, inertial and baro-altitude/air data sensors to provide optimized navigation, guidance and control performance. Lear Astronics Corporation is currently working within the navigation community to upgrade existing MIAG performance with precise GPS positioning mechanization tightly integrated with inertial, baro and other sensors. Among the immediate benefits are the following: (1) accurate target location in dynamic conditions; (2) autonomous launch and recovery using airborne avionics only; (3) precise flight path guidance; and (4) improved aircraft and payload stability information. This paper will focus on the impact of using the MIAG with its multimode navigation accuracies on the UAV targeting mission. Gimbaled electro-optical sensors mounted on a UAV can be used to determine ground coordinates of a target at the center of the field of view by a series of vector rotation and scaling computations. The accuracy of the computed target coordinates is dependent on knowing the UAV position and the UAV-to-target offset computation. Astronics performed a series of simulations to evaluate the effects that the improved angular and position data available from the MIAG have on target coordinate accuracy.

  17. Highly Survivable Avionics Systems for Long-Term Deep Space Exploration

    NASA Technical Reports Server (NTRS)

    Alkalai, L.; Chau, S.; Tai, A. T.

    2001-01-01

    The design of highly survivable avionics systems for long-term (> 10 years) exploration of space is an essential technology for all current and future missions in the Outer Planets roadmap. Long-term exposure to extreme environmental conditions such as high radiation and low-temperatures make survivability in space a major challenge. Moreover, current and future missions are increasingly using commercial technology such as deep sub-micron (0.25 microns) fabrication processes with specialized circuit designs, commercial interfaces, processors, memory, and other commercial off the shelf components that were not designed for long-term survivability in space. Therefore, the design of highly reliable, and available systems for the exploration of Europa, Pluto and other destinations in deep-space require a comprehensive and fresh approach to this problem. This paper summarizes work in progress in three different areas: a framework for the design of highly reliable and highly available space avionics systems, distributed reliable computing architecture, and Guarded Software Upgrading (GSU) techniques for software upgrading during long-term missions. Additional information is contained in the original extended abstract.

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

    NASA Technical Reports Server (NTRS)

    Ferguson, Stan; Savage, Dick

    1992-01-01

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

  19. Digital Preservation.

    ERIC Educational Resources Information Center

    Yakel, Elizabeth

    2001-01-01

    Reviews research on digital preservation issues, including born-digital and digitally recreated documents. Discusses electronic records research; metadata and other standards; electronic mail; Web-based documents; moving images media; selection of materials for digitization, including primary sources; administrative issues; media stability…

  20. Search and Rescue Aircrewman/HH3F Avionics, 2-11. Military Curriculum Materials for Vocational and Technical Education.

    ERIC Educational Resources Information Center

    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…

  1. A framework for the design and specification of hard real-time, hardware-in-the-loop simulations of large, avionic systems

    NASA Astrophysics Data System (ADS)

    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

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

    NASA Technical Reports Server (NTRS)

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

    2014-01-01

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

  3. Digital control of highly augmented combat rotorcraft

    NASA Technical Reports Server (NTRS)

    Tischler, Mark B.

    1987-01-01

    Proposed concepts for the next generation of combat helicopters are to be embodied in a complex, highly maneuverable, multiroled vehicle with avionics systems. Single pilot and nap-of-the-Earth operations require handling qualities which minimize the involvement of the pilot in basic stabilization tasks. To meet these requirements will demand a full authority, high-gain, multimode, multiply-redundant, digital flight-control system. The gap between these requirements and current low-authority, low-bandwidth operational rotorcraft flight-control technology is considerable. This research aims at smoothing the transition between current technology and advanced concept requirements. The state of the art of high-bandwidth digital flight-control systems are reviewed; areas of specific concern for flight-control systems of modern combat are exposed; and the important concepts are illustrated in design and analysis of high-gain, digital systems with a detailed case study involving a current rotorcraft system. Approximate and exact methods are explained and illustrated for treating the important concerns which are unique to digital systems.

  4. Is the avionics system of the Hermes Spaceplane centralized or decentralized?

    NASA Astrophysics Data System (ADS)

    Vannier, Jean-Claude

    The avionics system of Hermes is called spacionics. Spacionics is defined as a set of onboard items which treat, exchange, or store information in electrical form, and provide and distribute electrical power. The main drivers for spacionics design are mass and safety. The spacionics organization depends on the priorities assigned to different criteria. These priorities can lead to either a centralized or a decentralized data processing architecture. It has been necessary to centralize the widest part of the data processing, which is split into two pools of computers, one dedicated to guidance, navigation and control and one dedicated to mission and vehicle management. The first one, made of 4 computers and 4 data busses, is able to perform its functions autonomously and automatically even after 2 failures. The second one, including only 2 strings, requires the implementation of safety protection, activated, if necessary, either by the crew or by the control.

  5. Shuttle avionics and the goal language including the impact of error detection and redundancy management

    NASA Technical Reports Server (NTRS)

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

    1973-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

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

    2014-01-01

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

  7. Experimenting Maintenance of Flight Software in an Integrated Modular Avionics for Space

    NASA Astrophysics Data System (ADS)

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

    2014-08-01

    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.

  8. Multi-Purpose Avionic Architecture for Vision Based Navigation Systems for EDL and Surface Mobility Scenarios

    NASA Astrophysics Data System (ADS)

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

    2015-09-01

    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.

  9. Applications of Formal Methods to Specification and Safety of Avionics Software

    NASA Technical Reports Server (NTRS)

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

    1996-01-01

    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.

  10. "STEPS" Avionics for Exploration Systems the Achieved Results and the Next "STEPS-2"

    NASA Astrophysics Data System (ADS)

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

    2013-08-01

    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.

  11. Modular, Cost-Effective, Extensible Avionics Architecture for Secure, Mobile Communications

    NASA Technical Reports Server (NTRS)

    Ivancic, William D.

    2007-01-01

    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.

  12. Modular, Cost-Effective, Extensible Avionics Architecture for Secure, Mobile Communications

    NASA Technical Reports Server (NTRS)

    Ivancic, William D.

    2006-01-01

    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.

  13. Next-generation avionics packaging and cooling 'test results from a prototype system'

    NASA Astrophysics Data System (ADS)

    Seals, J. D.

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

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

    NASA Astrophysics Data System (ADS)

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

    2012-06-01

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

  15. Digital Citizenship

    ERIC Educational Resources Information Center

    Isman, Aytekin; Canan Gungoren, Ozlem

    2014-01-01

    Era in which we live is known and referred as digital age.In this age technology is rapidly changed and developed. In light of these technological advances in 21st century, schools have the responsibility of training "digital citizen" as well as a good citizen. Digital citizens must have extensive skills, knowledge, Internet and …

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

    ERIC Educational Resources Information Center

    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.…

  17. Digital Natives or Digital Tribes?

    ERIC Educational Resources Information Center

    Watson, Ian Robert

    2013-01-01

    This research builds upon the discourse surrounding digital natives. A literature review into the digital native phenomena was undertaken and found that researchers are beginning to identify the digital native as not one cohesive group but of individuals influenced by other factors. Primary research by means of questionnaire survey of technologies…

  18. An independent review of the Multi-Path Redundant Avionics Suite (MPRAS) architecture assessment and characterization report

    SciTech Connect

    Johnson, M.R.

    1991-02-01

    In recent years the NASA Langley Research Center has funded several contractors to conduct conceptual designs defining architectures for fault tolerant computer systems. Such a system is referred to as a Multi-Path Redundant Avionics Suite (MPRAS), and would form the basis for avionics systems that would be used in future families of space vehicles in a variety of missions. The principal contractors were General Dynamics, Boeing, and Draper Laboratories. These contractors participated in a series of review meetings, and submitted final reports defining their candidate architectures. NASA then commissioned the Research Triangle Institute (RTI) to perform an assessment of these architectures to identify strengths and weaknesses of each. This report is a separate, independent review of the RTI assessment, done primarily to assure that the assessment was comprehensive and objective. The report also includes general recommendations relative to further MPRAS development.

  19. Validation Methods Research for Fault-Tolerant Avionics and Control Systems Sub-Working Group Meeting. CARE 3 peer review

    NASA Technical Reports Server (NTRS)

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

    1980-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Frost, Chad

    2015-01-01

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

  1. An innovative approach to supplying an environment for the integration and test of the Space Station distributed avionics systems

    NASA Technical Reports Server (NTRS)

    Barry, Thomas; Scheffer, Terrance; Small, L. R.

    1988-01-01

    This paper describes an innovative approach to supplying an environment for the integration and testing of the Space Station distributed avionics systems. The environment's relationship to the process flow of the Space Station verification from systems development to on-orbit verification is presented. This paper also describes the uses of the environment's hardware implementation called Data Management System (DMS) kits. The way in which this environment allows system developers to independently verify their system's performance, fault detection, and recovery capability is explained.

  2. Synthetic vision meets ARINC 661: feasibility study of the integration of terrain visualization in ARINC 661 avionic displays

    NASA Astrophysics Data System (ADS)

    Lipinski, Erik; Ebrecht, L.

    2014-06-01

    ARINC 661-Cockpit Display System Interfaces to User Systems represents an evolving standard for the next generation of avionic systems. The standard defines a client-server architecture including user applications which control layers in certain windows of a cockpit display system (CDS). When creating avionic displays for a CDS, one can use a predefined set of simple to complex widgets. These are very useful when designing and implementing avionic displays. However, a proper widget and concept enabling synthetic vision, e.g. for terrain visualization, is not provided by the standard. Due to the fact that synthetic vision systems become more and more popular there is the need enabling synthetic vision with ARINC 661. This contribution deals with the question how synthetic vision (SV) might be realized, e.g. in an ARINC 661 compliant primary flight display (PFD) or navigation display (ND). Hence, different approaches for the implementation of SV will be discussed. One approach has been implemented to perform the feasibility study. A first study was done using the open source software project j661 managed by Dassault Aviation. Secondly, another implementation of a SV PFD was done using the SCADE ARINC 661 tools provided by ESTEREL Technologies. XPlane was used as terrain rendering application. The paper will give some rough figures of the programmed SV PFD as well as it will present the results of the feasibility study.

  3. Digital metamaterials

    NASA Astrophysics Data System (ADS)

    Della Giovampaola, Cristian; Engheta, Nader

    2014-12-01

    Balancing complexity and simplicity has played an important role in the development of many fields in science and engineering. One of the well-known and powerful examples of such balance can be found in Boolean algebra and its impact on the birth of digital electronics and the digital information age. The simplicity of using only two numbers, ‘0’ and ‘1’, in a binary system for describing an arbitrary quantity made the fields of digital electronics and digital signal processing powerful and ubiquitous. Here, inspired by the binary concept, we propose to develop the notion of digital metamaterials. Specifically, we investigate how one can synthesize an electromagnetic metamaterial with a desired permittivity, using as building blocks only two elemental materials, which we call ‘metamaterial bits’, with two distinct permittivity functions. We demonstrate, analytically and numerically, how proper spatial mixtures of such metamaterial bits lead to elemental ‘metamaterial bytes’ with effective material parameters that are different from the parameters of the metamaterial bits. We then apply this methodology to several design examples of optical elements, such as digital convex lenses, flat graded-index digital lenses, digital constructs for epsilon-near-zero (ENZ) supercoupling and digital hyperlenses, thus highlighting the power and simplicity of the methodology.

  4. Digital metamaterials.

    PubMed

    Della Giovampaola, Cristian; Engheta, Nader

    2014-12-01

    Balancing complexity and simplicity has played an important role in the development of many fields in science and engineering. One of the well-known and powerful examples of such balance can be found in Boolean algebra and its impact on the birth of digital electronics and the digital information age. The simplicity of using only two numbers, '0' and '1', in a binary system for describing an arbitrary quantity made the fields of digital electronics and digital signal processing powerful and ubiquitous. Here, inspired by the binary concept, we propose to develop the notion of digital metamaterials. Specifically, we investigate how one can synthesize an electromagnetic metamaterial with a desired permittivity, using as building blocks only two elemental materials, which we call 'metamaterial bits', with two distinct permittivity functions. We demonstrate, analytically and numerically, how proper spatial mixtures of such metamaterial bits lead to elemental 'metamaterial bytes' with effective material parameters that are different from the parameters of the metamaterial bits. We then apply this methodology to several design examples of optical elements, such as digital convex lenses, flat graded-index digital lenses, digital constructs for epsilon-near-zero (ENZ) supercoupling and digital hyperlenses, thus highlighting the power and simplicity of the methodology. PMID:25218061

  5. Model-Driven Development of Reliable Avionics Architectures for Lunar Surface Systems

    NASA Technical Reports Server (NTRS)

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

    2010-01-01

    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.

  6. Miniature high-let radiation spectrometer for space and avionics applications

    NASA Astrophysics Data System (ADS)

    Stassinopoulos, E. G.; Stauffer, Craig A.; Brucker, G. J.

    This paper reports on the design and characterization of a small, low-power, and low-weight instrument, a High-LET Radiation Spectrometer (HiLRS), that measures energy deposited by heavy ions in microelectronic devices. The HiLRS operates on pulse-height analysis principles and is designed for space and avionics applications. The detector component in the instrument is based on large scale arrays of p-n junctions. In this system, the pulse amplitude from a particle hit is directly proportional to the particle LET. A prototype flight unit has been fabricated and calibrated using several heavy ions with varying LETs and protons with several energies. The unit has been delivered to the Ballistic Missile Defense Organization (BMDO) c/o the Air Force Research Laboratory in Albuquerque, NM, for integration into the military Space Technology Research Vehicle (STRV), a US-UK cooperative mission. Another version of HiLRS is being prepared for delivery in April to the Hubble Space Telescope (HST) project, to fly on the HST Orbital Systems Test (HOST) platform on a shuttle mission.

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

    NASA Technical Reports Server (NTRS)

    Laughter, Sean A.

    2012-01-01

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

  8. A validation study of the Del Mar Avionics Pressurometer IV according to AAMI guidelines.

    PubMed

    Harshfield, G A; Hwang, C; Grim, C E

    1988-11-01

    Guidelines for the evaluation of automatic non-invasive blood pressure (BP) measurement devices have recently been established by the Association for the Advancement of Medical Instrumentation (AAMI). We evaluated the Del Mar Avionics Pressurometer IV (P4) in tests on 109 subjects, according to these guidelines. Three readings by two observers using a double stethoscope were first compared to each other to determine a standard and then averaged and compared to readings obtained using the P4. The two observers agreed within +/- 6 mmHg or 90% of the readings for both systolic and diastolic BP, with correlations of 0.99 and 0.98 for systolic and diastolic BP, respectively. The observers and the P4 in turn agreed to within +/- 6 mmHg for 85% of the readings for systolic BP, with a correlation of 0.98, and 65% of the readings for diastolic BP, with a correlation of 0.69. The correlations for both systolic and diastolic BP increased to 0.99 when readings were restricted to those obtained in individuals who fulfilled our previously defined calibration criterion of +/- 5 mmHg. In addition, we evaluated nine measurements of performance over 60 ambulatory recordings. The most serious problem was that of missing data which occurred in 85% of the recordings, primarily during sleep hours, and was generally attributed to either detection of Korotkoff sounds below 40 mmHg or a failure to detect Korotkoff sounds. PMID:3235838

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

    NASA Technical Reports Server (NTRS)

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

    2011-01-01

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

  10. Testing of the high accuracy inertial navigation system in the Shuttle Avionics Integration Lab

    NASA Technical Reports Server (NTRS)

    Strachan, Russell L.; Evans, James M.

    1991-01-01

    The description, results, and interpretation is presented of comparison testing between the High Accuracy Inertial Navigation System (HAINS) and KT-70 Inertial Measurement Unit (IMU). The objective was to show the HAINS can replace the KT-70 IMU in the space shuttle Orbiter, both singularly and totally. This testing was performed in the Guidance, Navigation, and Control Test Station (GTS) of the Shuttle Avionics Integration Lab (SAIL). A variety of differences between the two instruments are explained. Four, 5 day test sessions were conducted varying the number and slot position of the HAINS and KT-70 IMUs. The various steps in the calibration and alignment procedure are explained. Results and their interpretation are presented. The HAINS displayed a high level of performance accuracy previously unseen with the KT-70 IMU. The most significant improvement of the performance came in the Tuned Inertial/Extended Launch Hold tests. The HAINS exceeded the 4 hr specification requirement. The results obtained from the SAIL tests were generally well beyond the requirements of the procurement specification.

  11. Miniature High-Let Radiation Spectrometer for Space and Avionics Applications

    NASA Technical Reports Server (NTRS)

    Stassinopoulos, E. G.; Stauffer, Craig A.; Brucker, G. J.

    1998-01-01

    This paper reports on the design and characterization of a small, low power, and low weight instrument, a High-LET Radiation Spectrometer (HiLRS), that measures energy deposited by heavy ions in microelectronic devices. The HILRS operates on pulse-height analysis principles and is designed for space and avionics applications. The detector component in the instrument is based on large scale arrays of p-n junctions. In this system, the pulse amplitude from a particle hit is directly proportional to the particle LET. A prototype flight unit has been fabricated and calibrated using several heavy ions with varying LETs and protons with several energies. The unit has been delivered to the Ballistic Missile Defense Organization (BMDO) c/o the Air Force Research Laboratory in Albuquerque, NM, for integration into the military Space Technology Research Vehicle (STRV), a US-UK cooperative mission. Another version of HILRS is being prepared for delivery in April to the Hubble Space Telescope (HST) project, to fly on the HST Orbital Systems Test (HOST) Platform on a shuttle mission.

  12. Digital Opportunity

    ERIC Educational Resources Information Center

    Azzam, Amy M.

    2006-01-01

    This article details the content of a recently released report from the Children's Partnership titled "Measuring Digital Opportunity for America's Children: Where We Stand and Where We Go From Here". On the basis of 40 indicators, the report's Digital Opportunity Measuring Stick showed how U.S. children and young adults use information and…

  13. Digital TMI

    NASA Technical Reports Server (NTRS)

    Rios, Joseph

    2012-01-01

    Presenting the current status of the Digital TMI project to visiting members of the FAA Command Center. Digital TMI is an effort to store national-level traffic management initiatives in a standards-compliant manner. Work is funded by the FAA.

  14. Digital Discrimination

    ERIC Educational Resources Information Center

    Blansett, Jim

    2008-01-01

    In recent years, the Internet has become a digital commons of commerce and education. However, accessibility standards have often been overlooked online, and the digital equivalents to curb-cuts and other physical accommodations have only rarely been implemented to serve those with print disabilities. (A print disability can be a learning…

  15. Digital Roundup

    ERIC Educational Resources Information Center

    Horn, Michael B.

    2013-01-01

    State policy is crucial to the spread of digital-learning opportunities at the elementary and secondary level. A review of recent legislative action reveals policies that are constantly in flux and differ quite markedly from one state to another. Some have hoped for model digital-learning legislation that could handle all the various issues…

  16. Why Digitize?

    ERIC Educational Resources Information Center

    Smith, Abby

    This paper is a response to discussions of digitization at meetings of the National Humanities Alliance (NHA). NHA asked the Council on Library and Information Resources (CLIR) to evaluate the experiences of cultural institutions with digitization projects to date and to summarize what has been learned about the advantages and disadvantages of…

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

    PubMed Central

    Jan, Shau-Shiun

    2010-01-01

    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

  18. Digital clubbing

    PubMed Central

    Sarkar, Malay; Mahesh, D. M.; Madabhavi, Irappa

    2012-01-01

    Digital clubbing is an ancient and important clinical signs in medicine. Although clubbed fingers are mostly asymptomatic, it often predicts the presence of some dreaded underlying diseases. Its exact pathogenesis is not known, but platelet-derived growth factor and vascular endothelial growth factor are recently incriminated in its causation. The association of digital clubbing with various disease processes and its clinical implications are discussed in this review. PMID:23243350

  19. Digital Epidemiology

    PubMed Central

    Salathé, Marcel; Bengtsson, Linus; Bodnar, Todd J.; Brewer, Devon D.; Brownstein, John S.; Buckee, Caroline; Campbell, Ellsworth M.; Cattuto, Ciro; Khandelwal, Shashank; Mabry, Patricia L.; Vespignani, Alessandro

    2012-01-01

    Mobile, social, real-time: the ongoing revolution in the way people communicate has given rise to a new kind of epidemiology. Digital data sources, when harnessed appropriately, can provide local and timely information about disease and health dynamics in populations around the world. The rapid, unprecedented increase in the availability of relevant data from various digital sources creates considerable technical and computational challenges. PMID:22844241

  20. Managing Complexity in the MSL/Curiosity Entry, Descent, and Landing Flight Software and Avionics Verification and Validation Campaign

    NASA Technical Reports Server (NTRS)

    Stehura, Aaron; Rozek, Matthew

    2013-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

    Orr, James K.

    2010-01-01

    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.

  2. A 3D Model to Compute Lightning and HIRF Coupling Effects on Avionic Equipment of an Aircraft

    NASA Astrophysics Data System (ADS)

    Perrin, E.; Tristant, F.; Guiffaut, C.; Terrade, F.; Reineix, A.

    2012-05-01

    This paper describes the 3D FDTD model of an aircraft developed to compute the lightning and HIRF (High Intentity Radiated Fields) coupling effects on avionic equipment and all the wire harness associated. This virtual prototype aims at assisting the aircraft manufacturer during the lightning and HIRF certification processes. The model presented here permits to cover a frequency range from lightning spectrum to the low frequency HIRF domain, i.e. 0 to 100 MHz. Moreover, the entire aircraft, including the frame, the skin, the wire harness and the equipment are taken into account in only one model. Results obtained are compared to measurements on a real aircraft.

  3. Digital photography

    PubMed Central

    Windsor, J S; Rodway, G W; Middleton, P M; McCarthy, S

    2006-01-01

    Objective The emergence of a new generation of “point‐and‐shoot” digital cameras offers doctors a compact, portable and user‐friendly solution to the recording of highly detailed digital photographs and video images. This work highlights the use of such technology, and provides information for those who wish to record, store and display their own medical images. Methods Over a 3‐month period, a digital camera was carried by a doctor in a busy, adult emergency department and used to record a range of clinical images that were subsequently transferred to a computer database. Results In total, 493 digital images were recorded, of which 428 were photographs and 65 were video clips. These were successfully used for teaching purposes, publications and patient records. Conclusions This study highlights the importance of informed consent, the selection of a suitable package of digital technology and the role of basic photographic technique in developing a successful digital database in a busy clinical environment. PMID:17068281

  4. Digital radiography.

    PubMed

    Mattoon, J S

    2006-01-01

    Digital radiography has been used in human medical imaging since the 1980s with recent and rapid acceptance into the veterinary profession. Using advanced image capture and computer technology, radiographic images are viewed on a computer monitor. This is advantageous because radiographic images can be adjusted using dedicated computer software to maximize diagnostic image quality. Digital images can be accessed at computer workstations throughout the hospital, instantly retrieved from computer archives, and transmitted via the internet for consultation or case referral. Digital radiographic data can also be incorporated into a hospital information system, making record keeping an entirely paperless process. Digital image acquisition is faster when compared to conventional screen-film radiography, improving workflow and patient throughput. Digital radiography greatly reduces the need for 'retake' radiographs because of wide latitude in exposure factors. Also eliminated are costs associated with radiographic film and x-ray film development. Computed radiography, charged coupled devices, and flat panel detectors are types of digital radiography systems currently available. PMID:16971994

  5. Digital Collections, Digital Libraries & the Digitization of Cultural Heritage Information.

    ERIC Educational Resources Information Center

    Lynch, Clifford

    2002-01-01

    Discusses digital collections and digital libraries. Topics include broadband availability; digital rights protection; content, both non-profit and commercial; digitization of cultural content; sustainability; metadata harvesting protocol; infrastructure; authorship; linking multiple resources; data mining; digitization of reference works;…

  6. Acceleration ground test program to verify GAS payload No. 559 structure/support avionics and experiment structural integrity

    NASA Technical Reports Server (NTRS)

    Cassanto, John M.; Cassanto, Valerie A.

    1988-01-01

    Acceleration ground tests were conducted on the Get Away Special (GAS) payload 559 to verify the structural integrity of the structure/support avionics and two of the planned three flight experiments. The ITA (Integrated Test Area) Standardized Experiment Module (ISEM) structure was modified to accommodate the experiments for payload 559. The ISEM avionics consisted of a heavy duty sliver zinc power supply, three orthogonal-mounted low range microgravity accelerometers, a tri-axis high range accelerometer, a solid state recorder/programmer sequencer, and pressure and temperature sensors. The tests were conducted using the Gravitational Plant Physiology Laboratory Centrifuge of the University City Science Center in Philadelphia, PA. The launch-powered flight steady state acceleration profile of the shuttle was simulated from lift-off through jettison of the External Tank (3.0 g's). Additional tests were conducted at twice the nominal powered flight acceleration levels (6 g's) and an over-test condition of four times the powered flight loads to 12.6 g's. The present test program has demonstrated the value of conducting ground tests to verify GAS payload experiment integrity and operation before flying on the shuttle.

  7. Flight tests of advanced 3D-PFD with commercial flat-panel avionics displays and EGPWS system

    NASA Astrophysics Data System (ADS)

    He, Gang; Feyereisen, Thea; Gannon, Aaron; Wilson, Blake; Schmitt, John; Wyatt, Sandy; Engels, Jary

    2005-05-01

    This paper describes flight trials of Honeywell Advanced 3D Primary Flight Display System. The system employs a large-format flat-panel avionics display presently used in Honeywell PRIMUS EPIC flight-deck products and is coupled to an on-board EGPWS system. The heads-down primary flight display consists of dynamic primary-flight attitude information, flight-path and approach symbology similar to Honeywell HUD2020 heads-up displays, and a synthetic 3D perspective-view terrain environment generated with Honeywell"s EGPWS terrain data. Numerous flights are conducted on-board Honeywell Citation V aircraft and significant amount of pilot feedback are collected with portion of the data summarized in this paper. The system development is aimed at leveraging several well-established avionics components (HUD, EGPWS, large-format displays) in order to produce an integrated system that significantly reduces pilot workload, increases overall situation awareness, and is more beneficial to flight operations than achievable with separated systems.

  8. CanOpen on RASTA: The Integration of the CanOpen IP Core in the Avionics Testbed

    NASA Astrophysics Data System (ADS)

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

    2013-08-01

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

  9. Investigation of HZETRN 2010 as a Tool for Single Event Effect Qualification of Avionics Systems - Part II

    NASA Technical Reports Server (NTRS)

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

    2015-01-01

    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.

  10. Embedded algorithms for the SS-411 digital sun sensor

    NASA Astrophysics Data System (ADS)

    Enright, John; Sinclair, Doug; Li, Chris

    2009-05-01

    This paper discusses the evolution of the SS-411 series digital sun sensor. The earlier SS-256 and SS-330 models have proven themselves in orbit on low-cost satellite missions. The SS-411 represents a further hardware revision with enhanced robustness and improved attitude estimation performance. To complement the latest hardware improvements, researchers in the Space Avionics and Instrumentation Laboratory (SAIL) at Ryerson University in Toronto have developed advanced signal processing routines compatible with the SS-411. These routines significantly improve the accuracy of the sensor's estimation without increasing manufacturing complexity. With this advanced processing, the sensor maintains a 2-σ accuracy of 0.11° over the entire field-of-view.

  11. Investigation of HZETRN 2010 as a Tool for Single Event Effect Qualification of Avionics Systems

    NASA Technical Reports Server (NTRS)

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

    2014-01-01

    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

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

    NASA Technical Reports Server (NTRS)

    Gwaltney, David A.; Briscoe, Jeri M.

    2005-01-01

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

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

    NASA Astrophysics Data System (ADS)

    Gardi, Alessandro; Sabatini, Roberto; Ramasamy, Subramanian

    2016-05-01

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

  14. Digital caliper

    USGS Publications Warehouse

    Cable, Louella E.

    1967-01-01

    The large number of measurements needed to describe fully the characteristics of biological specimens and other objects has always been tedious and time consuming. The work can be done much more rapidly and with greater accuracy with a digital caliper recently developed by us. The digital caliper is a new electronic instrument built to measure objects precisely throughout the range of 0.1 mm to 1.0 m. Calipers of several different discrete sizes make it possible to select the most convenient unit for the particular range of length and degree of accuracy desired.

  15. Digital Radiography

    NASA Technical Reports Server (NTRS)

    1986-01-01

    System One, a digital radiography system, incorporates a reusable image medium (RIM) which retains an image. No film is needed; the RIM is read with a laser scanner, and the information is used to produce a digital image on an image processor. The image is stored on an optical disc. System allows the radiologist to "dial away" unwanted images to compare views on three screens. It is compatible with existing equipment and cost efficient. It was commercialized by a Stanford researcher from energy selective technology developed under a NASA grant.

  16. Military Curriculum Materials for Vocational and Technical Education. Avionics Instrument Systems Specialist. POI C3ABR32531 000. Classroom Course 2-7.

    ERIC Educational Resources Information Center

    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,…

  17. Space shuttle orbiter avionics software: Post review report for the entry FACI (First Article Configuration Inspection). [including orbital flight tests integrated system

    NASA Technical Reports Server (NTRS)

    Markos, H.

    1978-01-01

    Status of the computer programs dealing with space shuttle orbiter avionics is reported. Specific topics covered include: delivery status; SSW software; SM software; DL software; GNC software; level 3/4 testing; level 5 testing; performance analysis, SDL readiness for entry first article configuration inspection; and verification assessment.

  18. 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.

    ERIC Educational Resources Information Center

    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…

  19. Space tug point design study. Volume 3: Design definition. Part 1: Propulsion and mechanical, avionics, thermal control and electrical power subsystems

    NASA Technical Reports Server (NTRS)

    1973-01-01

    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.

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

    NASA Technical Reports Server (NTRS)

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

    1984-01-01

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

  1. Digital Tidbits

    ERIC Educational Resources Information Center

    Kumaran, Maha; Geary, Joe

    2011-01-01

    Technology has transformed libraries. There are digital libraries, electronic collections, online databases and catalogs, ebooks, downloadable books, and much more. With free technology such as social websites, newspaper collections, downloadable online calendars, clocks and sticky notes, online scheduling, online document sharing, and online…

  2. Digital Batteries

    NASA Astrophysics Data System (ADS)

    Hubler, Alfred

    2009-03-01

    The energy density in conventional capacitors is limited by sparking. We present nano-capacitor arrays, where - like in laser diodes and quantum wells [1] - quantization prevents dielectric breakthrough. We show that the energy density and the power/weight ratio are very high, possibly larger than in hydrogen [2]. Digital batteries are a potential clean energy source for cars, laptops, and mobile devices. The technology is related to flash drives. However, because of the high energy density, safety is a concern. Digital batteries can be easily and safely charged and discharged. In the discharged state they pose no danger. Even if a charged digital battery were to explode, it would produce no radioactive waste, no long-term radiation, and probably could be designed to produce no noxious chemicals. We discuss methodologies to prevent shorts and other measures to make digital batteries safe. [1] H. Higuraskh, A. Toriumi, F. Yamaguchi, K. Kawamura, A. Hubler, Correlation Tunnel Device, U. S. Patent No. 5,679,961 (1997) [2] Alfred Hubler, http://server10.how-why.com/blog/

  3. Digital books.

    PubMed

    Wink, Diane M

    2011-01-01

    In this bimonthly series, the author examines how nurse educators can use the Internet and Web-based computer technologies such as search, communication, and collaborative writing tools; social networking and social bookmarking sites; virtual worlds; and Web-based teaching and learning programs. This article describes digital books. PMID:22024672

  4. Digital Badges

    ERIC Educational Resources Information Center

    Frederiksen, Linda

    2013-01-01

    Unlike so much of the current vocabulary in education and technology that seems to stir more confusion than clarity, most public service librarians may already have a general idea about digital badges. As visual representations of individual accomplishments, competencies or skills that are awarded by groups, institutions, or organizations, they…

  5. Digital psychiatry.

    PubMed

    Tang, S; Helmeste, D

    2000-02-01

    The American managed care movement has been viewed as a big experiment and is being watched closely by the rest of the world. In the meanwhile, computer-based information technology (IT) is changing the practice of medicine, much more rapidly than managed care. A New World of digitized knowledge and information has been created. Although literature on IT in psychiatry is largely absent in peer-reviewed psychiatric journals, IT is finding its way into all aspects of medicine, particularly psychiatry. Telepsychiatry programs are becoming very popular. At the same time, medical information sites are flourishing and evolving into a new health-care industry. Patient-physician information asymmetry is decreasing as patients are gaining easy access to medical information hitherto only available to professionals. Thus, psychiatry is facing another paradigm shift, at a time when most attention has been focused on managed care. In this new digital world, knowledge and information are no longer the sole property of professionals. Value will migrate from traditional in-person office-based therapy to digital clinical products, from in-person library search and classroom didactic instruction to interactive on-line searches and distance learning. In this time of value migration, psychiatrists have to determine what their 'distinctive competence' is and where best to add value in the health-care delivery value chain. The authors assess the impact of IT on clinical psychiatry and review how clinical practice, education and research in psychiatry are expected to change in this emerging digital world. PMID:15558872

  6. Simulation modeling based method for choosing an effective set of fault tolerance mechanisms for real-time avionics systems

    NASA Astrophysics Data System (ADS)

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

    2013-12-01

    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.

  7. A tutorial on the CARE III approach to reliability modeling. [of fault tolerant avionics and control systems

    NASA Technical Reports Server (NTRS)

    Trivedi, K. S.; Geist, R. M.

    1981-01-01

    The CARE 3 reliability model for aircraft avionics and control systems is described by utilizing a number of examples which frequently use state-of-the-art mathematical modeling techniques as a basis for their exposition. Behavioral decomposition followed by aggregration were used in an attempt to deal with reliability models with a large number of states. A comprehensive set of models of the fault-handling processes in a typical fault-tolerant system was used. These models were semi-Markov in nature, thus removing the usual restrictions of exponential holding times within the coverage model. The aggregate model is a non-homogeneous Markov chain, thus allowing the times to failure to posses Weibull-like distributions. Because of the departures from traditional models, the solution method employed is that of Kolmogorov integral equations, which are evaluated numerically.

  8. Global system data bus using the Digital Autonomous Terminal Access Communication protocol

    NASA Technical Reports Server (NTRS)

    Holmes, David C. E.

    1986-01-01

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

  9. Kokes Awards for the 23rd North American Catalysis Society Meeting

    SciTech Connect

    Jacobs, Gary

    2014-01-31

    The Tri-State Catalysis Society awarded 107 Kokes Travel Awards. The program was very successful and to date this was the most Kokes Travel Awards ever awarded at a North American Catalysis Society Meeting. It provided students who merited an award the opportunity to attend the meeting, present a paper in the form of either an oral presentation or a poster presentation, and to serve the North American Catalysis Society by participating in the organization of the meeting. Students worked very hard during the week of the meeting to make it a success. Financial support for the Kokes awards was provided by DOE, NSF, NACS, as well as the Tri-State Catalysis Society, the latter through fund raising activities, and other donations. AT the meeting, each student received over $1050 in kind to offset the costs of registration fees ($260), hotel accommodations ($295.7), transportation ($400 travel allowance), as well as T-shirts ($20), and banquet tickets ($95 provided by donations from society members). In addition, for the first time, students received certificates that were signed by the President of NACS, Professor Enrique Iglesia, and by the Kokes Awards Chair, Gary Jacobs (see last page). A list of meeting co-chairs (i.e., Uschi M. Graham, Umit S. Ozkan, and Madan Bhassin) and the honorary chair (Burtron H. Davis) was also included on the certificate, along with the name of the recipient. The awardees were chosen on a merit-based guideline which also included the requirements of having a presentation accepted at the meeting and being a student at a North American University. The Richard J. Kokes Student Travel Award Committee (Gary Jacobs, Rodney Andrews, and Peter Smirniotis) with help from the Organizing Committee were able to secure money from four sources as detailed in Table 1. As detailed by our Treasurer, Dr. Helge Toufar of Clariant, the total amount spent was $105,000.

  10. The proceedings of the 23rd international technical conference on coal utilization and fuel systems

    SciTech Connect

    Sakkestad, B.A.

    1998-07-01

    Papers are arranged under the following topical sections: Advanced combustion systems; Alternative fuels; Coal liquefaction; New strategies for coal to accommodate climate change and deregulation; International highlights; Combustion by-product utilization; Co-firing; Flue gas treatment; Low NOx burners; CO{sub 2} mitigation; Power plant upgrades; Latin American coal perspective; Coal fines utilization; Upgraded coal for the power industry; Hot gas particulate cleanup; Coal conversion; Hydraulics and transportation; Coal briquetting and coal beneficiation; Air toxics; Materials and equipment; and Coal-water fuels preparation. 104 papers have been processed separately for inclusion on the database.

  11. International SAMPE Technical Conference, 23rd, Kiamesha Lake, NY, Oct. 21-24, 1991, Proceedings

    SciTech Connect

    Carri, R.L.; Poveromo, L.M.; Gauland, J. )

    1991-01-01

    The present conference discusses the cost of composite structures, microwave processing of thermoset resin-matrix composites at high pressure, the impact damage-tolerance of helicopter sandwich structures, novel fluorinated polybenzoxazole thermoplastics, low expansion coefficient polyimides containing metal-ion additives, thermoplastic polyimides for supersonic airframes, material properties and laser cutting of composites, fiber-matrix bond tests in composites, and a global/local stress analysis of stitched composites. Also discussed are moldless composite aircraft wing structural design modifications, advances in anhydride epoxy systems, medical applications of advanced composites, metal-joining processes for space fabrication, close-tolerance plastic master molds, the ballistic energy absorption of composites, soft and hard composite armors, resin-transfer molding of 3D composites, toughened cyanate ester resins, and thermoforming of thermoplastics.

  12. CRYSTAL-FACE Analysis and Simulations of the July 23rd Extended Anvil Case

    NASA Technical Reports Server (NTRS)

    Starr, David

    2003-01-01

    A key focus of CRYSTAL-FACE (Cirrus Regional Study of Tropical Anvils and cirrus Layers - Florida Area Cirrus Experiment) was the generation and subsequent evolution of cirrus outflow from deep convective cloud systems. Present theoretical background and motivations will be discussed. An integrated look at the observations of an extended cirrus anvil cloud system observed on 23 July 2002 will be presented, including lidar and millimeter radar observation; from NASA s ER-2 and in-situ observations from NASA s WB-57 and University of North Dakota Citation. The observations will be compared to results of simulations using 1-D and 2-D high-resolution (100 meter) cloud resolving models. The CRMs explicitly account for cirrus microphysical development by resolving the evolving ice crystal size distribution (bin model) in time and space. Both homogeneous and heterogeneous nucleation are allowed in the model. The CRM simulations are driven using the output of regional simulations using MM5 that produces deep convection similar to what was observed. The MM5 model employs a 2 km inner grid (32 layers) over a 360 km domain, nested within a 6-km grid over a 600-km domain. Initial and boundary conditions for the 36-hour MM5 simulation are taken from NCEP Eta model analysis at 32 km resolution. Key issues to be explored are the settling of the observed anvil versus the model simulations, and comparisons of dynamical properties, such as vertical motions, occurring in the observations and models. The former provides an integrated measure of the validity of the model microphysics (fallspeed) while the latter is the key factor in forcing continued ice generation.

  13. Higher Education and Service to Our States. Proceedings of the 23rd Legislative Work Conference.

    ERIC Educational Resources Information Center

    Southern Regional Education Board, Atlanta, GA.

    Papers include: Faculty Collective Bargaining in Higher Education; The University in Service to State Government; The New Environment for State Planning and Coordination of Higher Education; American Medical Education in the Year 209; Meeting the Needs of the States for Optometrists; and Meeting the Needs of States in Veterinary Medicine. (MJM)

  14. The Academic Senate for California Community Colleges Resolutions, 23rd Fall Session.

    ERIC Educational Resources Information Center

    Academic Senate for California Community Colleges, Sacramento.

    Documenting the 1991 fall session, this report provides resolutions adopted by the Academic Senate for the California Community Colleges. The resolutions are divided into the following 13 categories and topics: (1) the Academic Senate, including research, rules and procedures, and attendance at meetings; (2) accreditation, including self-study…

  15. FOREWORD: 23rd National Symposium on Plasma Science & Technology (PLASMA-2008)

    NASA Astrophysics Data System (ADS)

    Das, A. K.

    2010-01-01

    The Twentieth Century has been a defining period for Plasma Science and Technology. The state of ionized matter, so named by Irving Langmuir in the early part of twentieth century, has now evolved in to a multidisciplinary area with scientists and engineers from various specializations working together to exploit the unique properties of the plasma medium. There have been great improvements in the basic understanding of plasmas as a many body system bound by complex collective Coulomb interactions of charges, atoms, molecules, free radicals and photons. Simultaneously, many advanced plasma based technologies are increasingly being implemented for industrial and societal use. The emergence of the multination collaborative project International Thermonuclear Experimental Reactor (ITER) project has provided the much needed boost to the researchers working on thermonuclear fusion plasmas. In addition, the other plasma applications like MHD converters, hydrogen generation, advanced materials (synthesis, processing and surface modification), environment (waste beneficiation, air and water pollution management), nanotechnology (synthesis, deposition and etching), light production, heating etc are actively being pursued in governmental and industrial sectors. For India, plasma science and technology has traditionally remained an important area of research. It was nearly a century earlier that the Saha ionization relation pioneered the way to interpret experimental data from a vast range of near equilibrium plasmas. Today, Indian research contributions and technology demonstration capabilities encompass thermonuclear fusion devices, nonlinear plasma phenomena, plasma accelerators, beam plasma interactions, dusty and nonneutral plasmas, industrial plasmas and plasma processing of materials, nano synthesis and structuring, astrophysical and space plasmas etc. India's participation in the ITER programme is now reflected in increased interest in the research and development efforts on Tokamak technology and physics of magnetized fusion plasmas. Our industries have already adopted a large number of plasma processes related to manufacturing, lighting and surface engineering. Indian universities and National Institutes have successfully taken up research projects and building of demonstration equipment that are being used in strategic as well as other industrial applications. In addition, and more importantly, plasma science has triggered research and development effort in many related areas like power supplies, specialized instrumentation and controls, magnets, diagnostics and monitoring, lasers, electron beams, vacuum systems, thermal engineering, material science, fluid dynamics, molecular and nano engineering, molecular chemistry etc. In short, plasma science and technology in India has reached a stage of maturity that can be harnessed for industrial and societal use. The expertise and core competence developed over the years need to be sustained through interactions among researchers as well as nurturing of new research efforts. The Annual Plasma Symposiums have eminently worked towards achievement of that purpose. Like all years, Plasma - 2008 is built around the entire national effort in this field with a special focus on 'Plasmas in Nuclear Fuel Cycle (PANFC)'. The program includes several plenary lectures, invited talks and contributed papers. The manuscripts have been peer reviewed and compiled in the form of Conference Proceedings. I am sure that the online proceedings will be useful and serve as a valuable reference material for active researchers in this field. I would like to take this opportunity to gratefully acknowledge the help and guidance of the National Advisory Committee Chaired by Professor P K Kaw, Director, Institute of Plasma Research, Gandhinagar during the organization of this symposium. My sincere thanks to Dr S Banerjee, Director, Bhabha Atomic Research Center, an acknowledged expert in the field of Materials Science and Technology, for delivering the key note address to set the tenor of the symposium. I wo

  16. FOREWORD: 23rd National Symposium on Plasma Science & Technology (PLASMA-2008)

    NASA Astrophysics Data System (ADS)

    Das, A. K.

    2010-01-01

    The Twentieth Century has been a defining period for Plasma Science and Technology. The state of ionized matter, so named by Irving Langmuir in the early part of twentieth century, has now evolved in to a multidisciplinary area with scientists and engineers from various specializations working together to exploit the unique properties of the plasma medium. There have been great improvements in the basic understanding of plasmas as a many body system bound by complex collective Coulomb interactions of charges, atoms, molecules, free radicals and photons. Simultaneously, many advanced plasma based technologies are increasingly being implemented for industrial and societal use. The emergence of the multination collaborative project International Thermonuclear Experimental Reactor (ITER) project has provided the much needed boost to the researchers working on thermonuclear fusion plasmas. In addition, the other plasma applications like MHD converters, hydrogen generation, advanced materials (synthesis, processing and surface modification), environment (waste beneficiation, air and water pollution management), nanotechnology (synthesis, deposition and etching), light production, heating etc are actively being pursued in governmental and industrial sectors. For India, plasma science and technology has traditionally remained an important area of research. It was nearly a century earlier that the Saha ionization relation pioneered the way to interpret experimental data from a vast range of near equilibrium plasmas. Today, Indian research contributions and technology demonstration capabilities encompass thermonuclear fusion devices, nonlinear plasma phenomena, plasma accelerators, beam plasma interactions, dusty and nonneutral plasmas, industrial plasmas and plasma processing of materials, nano synthesis and structuring, astrophysical and space plasmas etc. India's participation in the ITER programme is now reflected in increased interest in the research and development efforts on Tokamak technology and physics of magnetized fusion plasmas. Our industries have already adopted a large number of plasma processes related to manufacturing, lighting and surface engineering. Indian universities and National Institutes have successfully taken up research projects and building of demonstration equipment that are being used in strategic as well as other industrial applications. In addition, and more importantly, plasma science has triggered research and development effort in many related areas like power supplies, specialized instrumentation and controls, magnets, diagnostics and monitoring, lasers, electron beams, vacuum systems, thermal engineering, material science, fluid dynamics, molecular and nano engineering, molecular chemistry etc. In short, plasma science and technology in India has reached a stage of maturity that can be harnessed for industrial and societal use. The expertise and core competence developed over the years need to be sustained through interactions among researchers as well as nurturing of new research efforts. The Annual Plasma Symposiums have eminently worked towards achievement of that purpose. Like all years, Plasma - 2008 is built around the entire national effort in this field with a special focus on 'Plasmas in Nuclear Fuel Cycle (PANFC)'. The program includes several plenary lectures, invited talks and contributed papers. The manuscripts have been peer reviewed and compiled in the form of Conference Proceedings. I am sure that the online proceedings will be useful and serve as a valuable reference material for active researchers in this field. I would like to take this opportunity to gratefully acknowledge the help and guidance of the National Advisory Committee Chaired by Professor P K Kaw, Director, Institute of Plasma Research, Gandhinagar during the organization of this symposium. My sincere thanks to Dr S Banerjee, Director, Bhabha Atomic Research Center, an acknowledged expert in the field of Materials Science and Technology, for delivering the key note address to set the tenor of the symposium. I would also like to thank the Plasma Science Society of India (PSSI) for agreeing to hold this important event at BARC. Thanks are due to Dr L M Gantayet, Director, BTDG, BARC and chairman, Scientific Program Committee and all my colleagues in the Symposium Organizing Committee who have made this symposium possible. Finally, our thanks to all the Funding agencies, Board of Research in Nuclear Science, Department of Science and Technology, The Board of Fusion Research, and all industrial exhibitor and sponsors for their unstinted support and encouragement. Dr A K Das Chairman, Organizing Committee Bhabha Atomic Research Center, Mumbai

  17. Michael Shaffer, 6th July 1936 to 23rd March 2009: A heartfelt tribute

    Technology Transfer Automated Retrieval System (TEKTRAN)

    Mr. Michael Shaffer, Retired Pyraloidea Curator, at the Natural History Museum, London, England, passed away on March 23, 2009. He was an acknowledged world expert on Pyraloidea, a group of agriculturally important moths. He was curator of the largest Pyraloidea type collection in the world, and a...

  18. Examining the Issues. Proceedings of the American Council on Consumer Interests 23rd Annual Conference.

    ERIC Educational Resources Information Center

    American Council on Consumer Interests, Columbia, MO.

    The document contains proceedings of a conference on consumer interests. The proceedings are proposed for those who attended the conference and other interested professionals. The major purpose of these proceedings is to stimulate thought and discussion regarding consumer issues. The first general session focuses on consumer representation. Three…

  19. 23rd IAEA Fusion Energy Conference: Summary Of Sessions EX/C and ICC

    SciTech Connect

    Richard J. Hawryluk

    2011-01-05

    An overview is given of recent experimental results in the areas of innovative confinement concepts, operational scenarios and confinement experiments as presented at the 2010 IAEA Fusion Energy Conference. Important new findings are presented from fusion devices worldwide, with a strong focus towards the scientific and technical issues associated with ITER and W7-X devices, presently under construction.

  20. Space Congress, 23rd, Cocoa Beach, FL, April 22-25, 1986, Proceedings

    SciTech Connect

    Not Available

    1986-01-01

    Papers concerned with developing space for tomorrow's society are presented. Consideration is given to international space activities, the use of computers in space, low-cost Shuttle payloads, streamling ground operations, and the commercialization of space. Topics discussed include contracts and management, Space Station technology, the effects of satellites on daily activities, second generation space transportation systems and launch vehicles technology, and the use of robotics and AI in aerospace operations.

  1. Proceedings of the 23rd International Conference of Safety in Mines Research Institutes: Abstracts

    SciTech Connect

    Not Available

    1991-01-01

    The proceedings contain 100 papers from the conference, grouped into the following topics: mine fires, conveyor fires, spontaneous combustion, methane, ventilation, rescue and recovery, outbursts of coal and rock, explosives, explosions (of dust and gas), new technologies, and engineering. Even though most of the papers are published in English, several are included in their entirety in another language in addition to the English paper, and several are published only in a foreign language. However, all papers have abstracts available in five languages (English, French, German, Russian, and Chinese). All papers have been processed separately for inclusion on the data base.

  2. High Achievers: 23rd Annual Survey. Attitudes and Opinions from the Nation's High Achieving Teens.

    ERIC Educational Resources Information Center

    Who's Who among American High School Students, Northbrook, IL.

    This report presents data from an annual survey of high school student leaders and high achievers. It is noted that of the nearly 700,000 high achievers featured in this edition, 5,000 students were sent the survey and 2,092 questionnaires were completed. Subjects were high school juniors and seniors selected for recognition by their principals or…

  3. Pamela Measurements of Galactic and Solar Cosmic Rays in the 23rd Solar Minimum (Invited)

    NASA Astrophysics Data System (ADS)

    Casolino, M.; PAMELA Collaboration

    2010-12-01

    We will discuss the measurements of protons and helium of galactic, solar and trapped origin taken with PAMELA detector in the period 2006-2010. PAMELA was launched in 2006 and is currently orbiting the Earth in a 350*600 km, 70 degree inclination polar orbit in a pressurized container located on one side of the Russian Resurs-DK1 satellite. Data were acquired at solar minimum, but show the effect of solar modulation on p and he low energy spectra (about 100 MeV/n - 1 GeV/n). Galactic protons and helium particles are measured up to 1 TV. Trapped and secondary proton component will be compared with existing models; the spectra of solar particle events of 13 and 14 December 2006 will also be discussed.

  4. Proceedings of the Annual State Conference on Educational Research "Accountability and the Curriculum" (23rd).

    ERIC Educational Resources Information Center

    California Advisory Council on Educational Research, Burlingame.

    Papers presented at the Conference include: "Biopsy of an Educational Growth" (J.R. Harsh), "Performance Contracting--The Dallas Experiment" (D.R. Waldrip), "Teaching Performance Tests at Three Levels of Accountability" (W.J. Popham), "Problems of Implementing the Writing of Behavioral Objectives" (R.M. Carson), "Program Planning Impact…

  5. Education, Section J. Extracted from the 1998 New York State Statistical Yearbook. 23rd Edition.

    ERIC Educational Resources Information Center

    State Univ. of New York, Albany. Nelson A. Rockefeller Inst. of Government.

    The 41 tables from the Section of the "Statistical Yearbook" describe the condition of education in New York state in the 1990s and provide information that allows comparisons with early years and with other states. In 1996, the year of latest data, New York's elementary and secondary schools served 3,290,150 students, and 995,885 students were…

  6. American Chemical Society. 23rd Great Lakes Regional Meeting. Program and abstracts

    SciTech Connect

    Not Available

    1990-01-01

    The technical program includes some 250 papers in 38 sessions, featuring 16 symposia with 99 invited speakers. Program highlights include a plenary lecture, The Origin and Consequences of Scientific Illiteracy, by Jon D. Miller. Sessions for general technical papers are scheduled in the following categories: analytical chemistry; biochemistry; inorganic chemistry; organic chemistry; and physical chemistry. Papers have been processed for inclusion on the data base.

  7. Study of the Fe Ion Generating Gradual SEP Events of the 23rd Solar Cycle

    NASA Astrophysics Data System (ADS)

    Nymmik, Rikho; Korzhov, Roman; Yakobovski, Evgeny; Baranov, Dmitry; Dergachov, Vadim; Gagarin, Yuri; Panasyuk, Michail

    We continue the investigation of solar energetic particles on the board of the orbital stations, carried out from 1978 on. According to our plans, PLATAN-M No. 1 chamber with the solidstate track detector (polyethylene terephthalate) was exposed from 26.01.2002 to 03.08.2004 on the outside surface of the International Space Station. The thickness of the detector allows registration of iron particles with energy from 30 up to 160 MeV/nucleon. At present the search and the measurement of particle tracks in the chamber is carried out. The main contribution to particle fluxes during the exposition is made by a major flare in October 29, 2003. To determine and refine the transmission function of particles penetrating into the Earth's magnetosphere, it is necessary to estimate expected particle fluxes on the International Space Station orbit, using the data obtained outside the magnetosphere by the SIS spectrometer of the ACE station. In the analogous investigation of SEP events in September - October, 1989 we have determined the ionic charge of Fe increasing with energy and obtained the detailed energy spectrum of these particles in the wide energy range. We are going to continue these investigations considering the new data in the framework of the SEP probability model.

  8. Fault tolerant topologies for fiber optic networks and computer interconnects operating in the severe avionics environment

    NASA Astrophysics Data System (ADS)

    Glista, Andrew S., Jr.

    1991-02-01

    The history of fiber optics technology development for naval aircraft is reviewed, and the current status of network and fly-by-light flight control development is examined. Fiber-optic component selection for aircraft is addressed, covering fiber and cables, optical sources, couplers, and connectors. Novel fault-tolerant network topologies for both analog and digital fiber optic transmission, which will permit both packet- and circuit-switched operation of robust fiber optic networks are discussed. The application of smart skin technology, i.e., fibers embedded in composite materials, to optical computer backplanes is briefly considered.

  9. Scanning for Digitization Projects

    ERIC Educational Resources Information Center

    Wentzel, Larry

    2007-01-01

    Librarians and archivists find themselves facing the prospect of digitization. Everyone is doing it, everyone needs it. Discussions rage nationally and internationally concerning what to digitize and the best means to present and retain digital objects. Digitization is the act of making something digital, expressing a physical object "in numerical…

  10. A rapid-acquisition architecture for advanced avionics and spread-spectrum applications

    NASA Astrophysics Data System (ADS)

    Jordan, Michael T.; Luecke, James R.

    A rapid-acquisition architecture for frequency hopping (FH), direct sequence (DS), and various forms of hybrid spread-spectrum waveforms is presented. This concept offers extraordinary improvements in flexibility and adaptability, as well as significant advantages in size, weight, and power reduction over those of conventional systems. The general concept is based on matching application-specific IC variable-length digital matched filter technology to programmable digital frequency synthesizers for an adaptable FH/DS spread-spectrum system. Within a given time interval a specific set of outputs from each code-matched filter (CMF) appears which represents the correlation of the received signal against a certain code offset. This is the key function for fast and reliable acquisition of the spread-spectrum signals. The basic configuration consists of the fast-acquisition subsystem, which receives the signals and downconverts, or dehops, by a frequency-hopping local oscillator driven by the known pseudonoise frequency hop pattern. This architecture configuration offers ease of technology insertion as new developments in technology may emerge. The modular philosophy allows for future expansion of the initial architecture in a cost-effective manner.

  11. Digital demodulator

    NASA Technical Reports Server (NTRS)

    Shull, T. A. (Inventor)

    1982-01-01

    A digital demodulator for converting pulse code modulated data from phase shift key (PSK) to non return to zero (NRZ) and to biphase data is described. The demodulator is composed of standard integrated logic circuits. The key to the demodulation function is a pair of cross coupled one shot multivibrators and which with a flip-flop produce the NRZ-L is all that is required, the circuitry is greatly simplified and the 2(v) times bit rate contraint can be removed from the carrier. A flip-flop, an OR gate, and AND gate and a binary counter generate the bit rate clock (BTCK) for the NRZ-L. The remainder of the circuitry is for converting the NRZ-L and BTCK into biphase data. The device was designed for use in the space shuttle bay environment measurements.

  12. Digital structural

    USGS Publications Warehouse

    Dohm, J.M.; Anderson, R.C.; Tanaka, K.L.

    1998-01-01

    Magmatic and tectonic activity have both contributed significantly to the surface geology of Mars. Digital structural mapping techniques have now been used to classify and date centers of tectonic activity in the western equatorial region. For example, our results show a center of tectonic activity at Valles Marineris, which may be associated with uplift caused by intrusion. Such evidence may help explain, in part, the development of the large troughs and associated outflow channels and chaotic terrain. We also find a local centre of tectonic activity near the source region of Warrego Valles. Here, we suggest that the valley system may have resulted largely from intrusive-related hydrothermal activity. We hope that this work, together with the current Mars Global Surveyor mission, will lead to a better understanding of the geological processes that shaped the Martian surface.

  13. Digital communication systems

    NASA Astrophysics Data System (ADS)

    Peebles, Peyton Z., Jr.

    The fundamental principles of digital communication and the design of practical digital communication systems are explored in an introductory textbook for senior and graduate students of electrical engineering. Chapters are devoted to sampling principles, baseband digital waveforms, baseband digital systems, bandpass binary digital systems, and M-ary digital systems. Deterministic signals, networks, and random-signal theory are reviewed in extensive appendices, and graphs, flow charts, diagrams, and problems are provided.

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

    SciTech Connect

    Ryan, P.A.

    1994-12-31

    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. Can We Teach Digital Natives Digital Literacy?

    ERIC Educational Resources Information Center

    Ng, Wan

    2012-01-01

    In recent years, there has been much debate about the concept of digital natives, in particular the differences between the digital natives' knowledge and adoption of digital technologies in informal versus formal educational contexts. This paper investigates the knowledge about educational technologies of a group of undergraduate students…

  16. Digital photorefraction

    NASA Astrophysics Data System (ADS)

    Costa, Manuel F.; Jorge, Jorge M.

    1997-12-01

    The early evaluation of the visual status of human infants is of a critical importance. It is of utmost importance to the development of the child's visual system that she perceives clear, focused, retinal images. Furthermore if the refractive problems are not corrected in due time amblyopia may occur. Photorefraction is a non-invasive clinical tool rather convenient for application to this kind of population. A qualitative or semi-quantitative information about refractive errors, accommodation, strabismus, amblyogenic factors and some pathologies (cataracts) can the easily obtained. The photorefraction experimental setup we established using new technological breakthroughs on the fields of imaging devices, image processing and fiber optics, allows the implementation of both the isotropic and eccentric photorefraction approaches. Essentially both methods consist on delivering a light beam into the eyes. It is refracted by the ocular media, strikes the retina, focusing or not, reflects off and is collected by a camera. The system is formed by one CCD color camera and a light source. A beam splitter in front of the camera's objective allows coaxial illumination and observation. An optomechanical system also allows eccentric illumination. The light source is a flash type one and is synchronized with the camera's image acquisition. The camera's image is digitized displayed in real time. Image processing routines are applied for image's enhancement and feature extraction.

  17. Digital photorefraction

    NASA Astrophysics Data System (ADS)

    Costa, Manuel F. M.; Jorge, Jorge M.

    1998-01-01

    The early evaluation of the visual status of human infants is of a critical importance. It is of utmost importance to the development of the child's visual system that she perceives clear, focused, retinal images. Furthermore if the refractive problems are not corrected in due time amblyopia may occur. Photorefraction is a non-invasive clinical tool rather convenient for application to this kind of population. A qualitative or semi-quantitative information about refractive errors, accommodation, strabismus, amblyogenic factors and some pathologies (cataracts) can the easily obtained. The photorefraction experimental setup we established using new technological breakthroughs on the fields of imaging devices, image processing and fiber optics, allows the implementation of both the isotropic and eccentric photorefraction approaches. Essentially both methods consist on delivering a light beam into the eyes. It is refracted by the ocular media, strikes the retina, focusing or not, reflects off and is collected by a camera. The system is formed by one CCD color camera and a light source. A beam splitter in front of the camera's objective allows coaxial illumination and observation. An optomechanical system also allows eccentric illumination. The light source is a flash type one and is synchronized with the camera's image acquisition. The camera's image is digitized displayed in real time. Image processing routines are applied for image's enhancement and feature extraction.

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

    NASA Technical Reports Server (NTRS)

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

    1987-01-01

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

  19. Prima Platform: A Scheme for Managing Equipment-Dependent Onboard Functions and Impacts on the Avionics Software Production Process

    NASA Astrophysics Data System (ADS)

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

    2010-08-01

    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.

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

    SciTech Connect

    Carroll, C.C.; Youngblood, J.N.; Saha, A.

    1987-12-01

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