Sample records for mgs avionics system

  1. Avionics Systems

    P.M. Soundar Rajan


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

  2. System Testing in the Avionics Domain


    When developing a new aircraft, the airframer encounters various (partly contradictory) demands and requirements. To deal with them, current avionics systems are based on the framework of integrated modular electronics which allows to use COTS products for less critical functions and uses integrated modular avionics (IMA) technology for safety-critical avionics functions. Since this evolution affects the entire development, new processes and means for the development and the verification and ...

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

    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.


    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.

  4. Reference Avionics Architecture for Lunar Surface Systems

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


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

  5. Avionics Instrument Systems Specialist (AFSC 32551).

    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);…

  6. Demonstration Advanced Avionics System (DAAS) function description

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


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

  7. COTS Multicore Processors in Avionics Systems: Challenges and Solutions


    COTS Multicore Processors in Avionics Systems: Challenges and Solutions Dionisio de Niz Bjorn Andersson and Lutz Wrage Avionics Systems: Challenges and Solutions 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) Wrage /Dionisio de Niz Bjorn...NVIDIA Tegra K1 platform • Avionics and defense: – Rugged Intel i7 single board computers – Freescale P4080 8-core CPU 4 Shared Hardware: Multicore Memory

  8. Adaptive MGS Phase Retrieval

    Basinger, Scott A.; Bikkannavar, Siddarayappa; Cohen, David; Green, Joseph J.; Lou, John; Ohara, Catherine; Redding, David; Shi, Fang


    Adaptive MGS Phase Retrieval software uses the Modified Gerchberg-Saxton (MGS) algorithm, an image-based sensing method that can turn any focal plane science instrument into a wavefront sensor, avoiding the need to use external metrology equipment. Knowledge of the wavefront enables intelligent control of active optical systems.

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

    Li Ma


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

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

    N. Rao


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

  11. The Space Technology 5 Avionics System

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


    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

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


    The technological growth of ‘avionics systems’ has outpaced the service-life of aircraft, resulting in avionics upgrade as a preferred cost-effective option to new design. Mid-life upgrade of “avionics systems“ by state-of-the-art mission systems has been a challenging engineering task. The complexity of avionics upgrade process is due to the design rigidity of avionics systems architecture. An avionics architecture with growth potential is required to optimise avionics upgrade with state-of-...

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

    Wang Liang


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

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


    Aircraft avionics system becoming more and more complicated, it is too hard to test and verify real avionics systems. A design and realization method of avionics integration simulation system based on RTX was brought forward to resolve the problem. In this simulation system, computer software and hardware resources were utilized entirely. All kinds of aircraft avionics system HIL (hardware-in-loop) simulations can be implemented in this platform. The simulation method provided the technical f...

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

    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…

  16. Optoelectronic Aspects of Avionic Systems II


    K.C. Trumble of the Information Management Branch (AFAL/AAM). Dr. J.R. Biard was the principal investigator of the program. He was assisted in the...Force Avionics Laboratory, Dr. J.P. Mize, J.E. Shaunfield and J.F. Leezer of Spectronics, Inc., and Dr. K.W. Heizer of Southern Methodist University...Duplex 72 18 Worst Case Power Improvement Factor Radial Duplex/Tapered Duplex 76 19 Scrambler Rod 79 20 Scramber Rod Operation 82 vii -^^^hm

  17. Directions in avionic data distribution systems

    Wilent, C.E.


    The author examines the requirements for data distribution resulting from trends in avionic architecture and the opportunities for lower costs afforded by advancing technology. VLSI technology is providing the opportunity for the development of powerful processing components, the application of which addresses both problems. The concept of time-multiplexing programmable preprocessors, signal, and data processors, which is being explored in programs such as ICNIA, potentially reduces total hardware and provides additional benefits of fault tolerance and graceful degradation. The result is a matrix architecture in which processing tasks are partitioned by signal bandwidth and executed with temporarily assigned strings of processor elements.

  18. Comparison of Communication Architectures for Spacecraft Modular Avionics Systems

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


    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. Intelligent Cost Modeling Based on Soft Computing for Avionics Systems

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


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

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

    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…

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

    Xu, Jiuping; Zhong, Zhengqiang; Xu, Lei


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

  2. New bus architecture for distributed avionic systems

    Leonard, W.B.; Chow, K.K.


    The authors discuss a bus architecture which offers several advantages over conventional buses for a large selection of applications, and which allows for both interrupts and error checking. The bus may be expanded in the form of a tree with many processors, memories, and input/output devices distributed freely throughout the system. Therefore, it is inherently a multiprocessor bus and is well suited for systems in which a central controller controls several subordinate processors and devices. Its low overhead plus large capacity for expansion make it appropriate for a wide range of future systems.

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

    Goclowski, John C.; And Others

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

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

    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…

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

    Orr, James K.; Peltier, Daryl


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


    Sergey Viktorovich Kuznetsov


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

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

    Shams, Qamar


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

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

    Keller, T. W.


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

  9. Accelerated Adaptive MGS Phase Retrieval

    Lam, Raymond K.; Ohara, Catherine M.; Green, Joseph J.; Bikkannavar, Siddarayappa A.; Basinger, Scott A.; Redding, David C.; Shi, Fang


    The Modified Gerchberg-Saxton (MGS) algorithm is an image-based wavefront-sensing method that can turn any science instrument focal plane into a wavefront sensor. MGS characterizes optical systems by estimating the wavefront errors in the exit pupil using only intensity images of a star or other point source of light. This innovative implementation of MGS significantly accelerates the MGS phase retrieval algorithm by using stream-processing hardware on conventional graphics cards. Stream processing is a relatively new, yet powerful, paradigm to allow parallel processing of certain applications that apply single instructions to multiple data (SIMD). These stream processors are designed specifically to support large-scale parallel computing on a single graphics chip. Computationally intensive algorithms, such as the Fast Fourier Transform (FFT), are particularly well suited for this computing environment. This high-speed version of MGS exploits commercially available hardware to accomplish the same objective in a fraction of the original time. The exploit involves performing matrix calculations in nVidia graphic cards. The graphical processor unit (GPU) is hardware that is specialized for computationally intensive, highly parallel computation. From the software perspective, a parallel programming model is used, called CUDA, to transparently scale multicore parallelism in hardware. This technology gives computationally intensive applications access to the processing power of the nVidia GPUs through a C/C++ programming interface. The AAMGS (Accelerated Adaptive MGS) software takes advantage of these advanced technologies, to accelerate the optical phase error characterization. With a single PC that contains four nVidia GTX-280 graphic cards, the new implementation can process four images simultaneously to produce a JWST (James Webb Space Telescope) wavefront measurement 60 times faster than the previous code.

  10. Avionics Systems Laboratory/Building 16. Historical Documentation

    Slovinac, Patricia; Deming, Joan


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

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

    Burke, Michael


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

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

    Young, D. A.


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

  13. Digital Avionics

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


    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.

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

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


    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.

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

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

    Czuchry, Andrew J.; And Others

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

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

    Cockrell, James


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

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

    Boruzdina Anna


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

  19. Optimal Configuration of Virtual Links for Avionics Network Systems

    Dongha An


    Full Text Available As the bandwidth and scalability constraints become important design concerns in airborne networks, a new technology, called Avionics Full Duplex Switched Ethernet (AFDX, has been introduced and standardized as a part 7 in ARNIC 664. However, since previous research interests for AFDX are mainly bounded for analyzing the response time where flows information is given, configuration problem for both Maximum Transmission Unit (MTU and Bandwidth Allocation Gap (BAG over virtual links in AFDX networks has not been addressed yet even though it has great impact on required bandwidth. Thus, in this paper, we present two configuration approaches to set MTU and BAG values on virtual links efficiently while meeting the requirement of AFDX. The first is to search available feasible configuration (MTU, BAG pairs to satisfy application requirements as well as AFDX switch constraints, and the second is to get an optimal pair to minimize required bandwidth through well-known branch-and-bound algorithm. We analyze the complexity of the proposed algorithm and then evaluate the proposed algorithm by simulation. Finally, we prove that the proposed schemes are superior to general approach in the aspects of speed and required bandwidth in AFDX networks.

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

    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.

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

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


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

  2. Perspective on intelligent avionics

    Jones, H.L.


    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.

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

    Юрий Владимирович Пепа


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

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

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


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

  5. Avionics Architecture for Exploration Project

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

  6. B-1B Avionics Systems AFSC 457X3



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

    V. Haridas


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

  8. System Design Toolkit for Integrated Modular Avionics for Space

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


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

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


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

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

    Harris, Richard; Kirkland, Zach


    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.

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

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


    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.

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

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

  13. Alternative Suspension System for Space Shuttle Avionics Shelf

    Biele, Frank H., III


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

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

    Ferguson, Stan; Savage, Dick


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

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

    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…

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

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


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

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

    ZHOU Tianran; XIONG Huagang


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

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

    WANG Lize; LIU Bin; LU Minyan


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

  19. F-35航电系统的发展%Development of the F-35 Avionics System

    罗锐; 李国柱


    F-35 avionics system plays more and more roles in the war today.The process of development of the F-35 avionics system abroad and equipment in some countries in the world and its modification are described.The technique performance and properties of several F-35 avionics system seekers are analyzed;and development trend And analysis of F-35 avionics system are discussed.%F-35航电系统在现代战争中发挥着越来越重要的作用。文章介绍了F-35航电系统的发展历程以及装备的研制、改进情况,指出了在现代战争中发展F-35航电系统的优势和重要性,重点探讨了几种F-35航电系统的性能及其特点,最后论述了F-35航电系统的发展动向与分析。

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

    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…

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

    Dunn, William R.


    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.

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

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


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

  3. Integrated Power, Avionics, and Software (iPAS) Space Telecommunications Radio System (STRS) Radio User's Guide -- Advanced Exploration Systems (AES)

    Roche, Rigoberto; Shalkhauser, Mary Jo Windmille


    The Integrated Power, Avionics and Software (IPAS) software defined radio (SDR) was implemented on the Reconfigurable, Intelligently-Adaptive Communication System (RAICS) platform, for radio development at NASA Johnson Space Center. Software and hardware description language (HDL) code were delivered by NASA Glenn Research Center for use in the IPAS test bed and for development of their own Space Telecommunications Radio System (STRS) waveforms on the RAICS platform. The purpose of this document is to describe how to setup and operate the IPAS STRS Radio platform with its delivered test waveform.

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

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


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

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


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

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

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


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

  7. Aerospace Avionics and Allied Technologies

    Jitendra R. Raol


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

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

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


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

  9. Panoramic projection avionics displays

    Kalmanash, Michael H.


    Avionics projection displays are entering production in advanced tactical aircraft. Early adopters of this technology in the avionics community used projection displays to replace or upgrade earlier units incorporating direct-view CRT or AMLCD devices. Typical motivation for these upgrades were the alleviation of performance, cost and display device availability concerns. In these systems, the upgraded (projection) displays were one-for-one form / fit replacements for the earlier units. As projection technology has matured, this situation has begun to evolve. The Lockheed-Martin F-35 is the first program in which the cockpit has been specifically designed to take advantage of one of the more unique capabilities of rear projection display technology, namely the ability to replace multiple small screens with a single large conformal viewing surface in the form of a panoramic display. Other programs are expected to follow, since the panoramic formats enable increased mission effectiveness, reduced cost and greater information transfer to the pilot. Some of the advantages and technical challenges associated with panoramic projection displays for avionics applications are described below.

  10. Flight Avionics Hardware Roadmap

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


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

  11. Investigation of HZETRN 2010 as a Tool for Single Event Effect Qualification of Avionics Systems - Part II

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


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


    Dr. H.-W. Schulz


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

  13. Military Curriculum Materials for Vocational and Technical Education. Avionics Instrument Systems Specialist. POI C3ABR32531 000. Classroom Course 2-7.

    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,…

  14. Avionics Architecture Modelling Language

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


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

  15. Simulation modeling based method for choosing an effective set of fault tolerance mechanisms for real-time avionics systems

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


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

  16. Avionic Data Bus Integration Technology


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

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

    Shalkhauser, Mary Jo W.; Roche, Rigoberto


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

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

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


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

  19. Avionics: The main contributor to innovation in aviation

    Theunissen, E.


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

  20. Avionics: The main contributor to innovation in aviation

    Theunissen, E.


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

  1. HH-65A Dolphin digital integrated avionics

    Huntoon, R. B.


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

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

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


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

  3. Developing A Generic Optical Avionic Network

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


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

  4. Flight Avionics Hardware Roadmap

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


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

  5. Avionics advanced development strategy

    Dyer, D.


    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.

  6. Affordable Vehicle Avionics Overview

    Cockrell, James J.


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

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



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


    frequency RSD recovery and securing device RTOS real-time operating system SAE Society of Automotive Engineers SCARLETT Scalable and...cognitive aiding and decision making, fused sensor imagery, and interoperable communications/data systems … minimizing crew workload . FOS platforms...cutting-edge automotive systems should not be underestimated. Rapid product-development cycles and intense competition have led to massive

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


    chaz Ia maitre d’oeuvre systeme quo chat lIequipomentler. Cos outils font paitle des moyens ginirauo de I entreprise et couvrent I ensemble des...test6 s’excute. A ce titre, WDAS eat propos6 cosine outii de test our l’atelier ENTREPRISE , atelier de g~nie logt- ciel portable multiiangage d~veloppk...EFFORTS I SKILLED POOLS OF LABOR I AVAILABLE FINANCING I PRESENCE OF CORPORATE HEADQUARTERS I TRANSPORTATION I CLIMATE AND CULTURAL AMENITIES 1* OTHER

  10. Developing A Generic Optical Avionic Network

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


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

  11. Validation Methods Research for Fault-Tolerant Avionics and Control Systems: Working Group Meeting, 2

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


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

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

    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…

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

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


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

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

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

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

    Jacobs, Bryan C.; Nelson, Carl V.


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

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

    Ryan, P.A. [Wright Lab., Wright-Patterson AFB, OH (United States). Avionics Directorate


    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.

  17. Space Shuttle Avionics: a Redundant IMU On-Board Checkout and Redundancy Management System

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


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

  18. Navy Should Join the Air Force and Army Program to Develop an Advanced Integrated Avionics System.


    1990s. Advanced development is expected to cost about $131 million. Full-scale engineering and production costs have not yet been estimated. INTEGRATED...effectiveness, .i tle !CNIA system could be a viable candidate for retrofitting cider aircraft. Finally, the ICNIA program is a laboratory and fliqnt

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


    BASE SIMULATOR IRON BIRD CARC 0 SERVO AND SURFACE 3-AXIS TABLE 0 LOADER CONTROL UNIT I )j/,,a DEVELOPMENT :.T ES T PANELS FIGURE 8-14. IRON BIRD...development and fabrica - tion of the system." (Reference 1) Component Tests. Component testing varies greatly depending upon several factors

  20. GASP-PL/I Simulation of Integrated Avionic System Processor Architectures. M.S. Thesis

    Brent, G. A.


    A development study sponsored by NASA was completed in July 1977 which proposed a complete integration of all aircraft instrumentation into a single modular system. Instead of using the current single-function aircraft instruments, computers compiled and displayed inflight information for the pilot. A processor architecture called the Team Architecture was proposed. This is a hardware/software approach to high-reliability computer systems. A follow-up study of the proposed Team Architecture is reported. GASP-PL/1 simulation models are used to evaluate the operating characteristics of the Team Architecture. The problem, model development, simulation programs and results at length are presented. Also included are program input formats, outputs and listings.

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


    direct method of calculus of variables in this trajectory optimization process. Crucial to the application of the direct method was exploitation of...capable of making decisions on its trajectory from limited input. The direct method of calculus of variations avails as a potential methodology of choice...and Wolter J. Fabrycky. 2011. Systems Engineering and Analysis. 5th ed., Boston: Pearson . Boyle, Rebecca. 2012. “One Third of the Military’s

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


    U.S. Department of Transportation PFe 1rs Aviation Administration DOT/FAA/CT-88/10 HANDBOOK- VOLUME H DIGITAL SYSTEMS VALIDATION - CHAPTER 18 tw...18-29 improve identification, control, and auditing of software. SCM and SQA methods in RTCA/DO-178A are drawn directly from proven methods of hardware...procedures, and practices; reviews and audits ; configuration management; medium control; testing; supplier control; and appropriate records. A brief

  3. Development of Framework for Acquisition of Avionics Integration Capability

    Fahad RIAZ


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

  4. Critical issues regarding SEU in avionics

    Normand, E. (Boeing Aerospace, Seattle, WA (United States)); McNulty, P.J. (Clemson Univ., SC (United States))


    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.

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

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


    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. Generalized Nanosatellite Avionics Testbed Lab

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


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

  7. Evaluation of New European Technologies for Future Avionics

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


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

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

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


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

  9. Power, Avionics and Software Communication Network Architecture

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


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

  10. Modular Avionics for Seamless Reconfigurable UAS Missions


    Abstract Integrated Modular Avionics (IMA) architecture is a trend in current avionics that employs a partitioned environment in which different avionics functions share a unique computing environment. UAS avionics, especially in small UAS, are usually of less complexity than not the present on airliners, however, in real autonomous UAS, the onboard avionics should control not only the flight and navigation but also the mission and payload of the aircraft. This involves more complex softwa...

  11. Wireless avionics for space applications of fundamental physics

    Wang, Linna; Zeng, Guiming


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

  12. Avionics Maintenance Technology Program Standards.

    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…

  13. 基于模型驱动的航电系统安全性分析%Safety Analysis for Avionics System Based on Model Driven

    邢逆舟; 王立松


    针对综合化航空电子系统安全性分析存在的失效模式完备性和动态失效问题以及数据一致性问题,将航电系统分为应用操作层、功能层和资源层3个层次,采用形式化方法分别对每个层次进行建模,利用模型转换技术实现3个层次之间的语义转换,确保语义的一致性。利用AADL语言对系统应用操作和功能层建模,实现对应用操作模式完备性检查,利用AltaRica语言对系统的异常行为建模,实现对系统的动态失效问题分析。本文以飞机自动驾驶系统为例,利用AADL建模工具Osate实现对应用操作模式的分析,借助于基于AltaRica语言的SimFia工具对其安全性进行分析,结果验证了所提出方法的有效性和实用性。%This paper introduces a new model-based method for safety analysis to address the problem of failure modes integrity , dynamic failure and data consistency that currently encountered in safety assessments for integrated avionics system .The method model integrated avionics system hierarchically with layers of application operation , function and resource .It simplifies a large part of the analysis , the development of fault trees , and can guarantee the consistency of results .AADL language is used to model application layer to check the integrity of operations modes and AltaRica is used to model dysfunction of system to solve the prob -lem of dynamic failure .The efficiency and practicality of the method is illustrated by analyzing safety of auto pilot system through Osate tool which used for analyzing operational modes of application and SimFia tool which used for safety analysis .

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

    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.…

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

    窦赛; 陈国顺; 吕艳梅


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

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

    Sims, A.J.; Dyer, C.S.; Peerless, C.L. (Defence Research Agency, Farnborough (United Kingdom). Space and Communications Dept.); Johansson, K.; Pettersson, H. (SAAB Military Aircraft, Linkoeping (Sweden)); Farren, J. (AEA Technology, Oxfordshire (United Kingdom). Harwell Lab.)


    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.

  17. Issues Related To Troubleshooting Of Avionic Hydraulic Units

    Jastrzębski Grzegorz


    Full Text Available The paper outlines workflows associated with troubleshooting of avionic hydraulic systems with detailed description of the troubleshooting algorithm and classification of diagnostic signals provided by avionic hydraulic systems and their subassemblies. Attention is paid to measurement sequences for diagnostic signals from hydraulic systems, circuits and units. Detailed description is dedicated to an innovative design of a troubleshooting device intended for direct measurements of internal leaks from avionic hydraulic units. Advantages of the proposed measurement method are summarized with benefits from use of the presented device and compared against the methods that are currently in use. Subsequent phases of the troubleshooting process are described with examples of measurement results that have been acquired from subassemblies of hydraulic systems of SU-22 aircrafts currently in service at Polish Air Forces with consideration given to cases when the permissible threshold of diagnostic signals were exceeded. Finally, all results from investigations are subjected to thorough analysis.

  18. Simultaneous Mars Express / MGS observations of plasma near Mars

    Brain, D.; Luhmann, J.; Halekas, J.; Frahm, R.; Winningham, D.; Barabash, S.


    Since late 2003, Mars Express (MEX) and Mars Global Surveyor (MGS) have been making complementary in situ measurements (in terms of both instrument and orbit) of the Martian plasma environment. Study of MGS and MEX data in tandem provides an opportunity to mitigate the shortcomings of each dataset and increase our overall understanding of the Martian solar wind interaction and atmospheric escape. Close passes of spacecraft (conjunctions) are one particularly powerful means of increasing the utility of measurements, as evidenced by the Cluster mission at Earth. At Mars, conjunctions might be used to obtain more complete simultaneous and/or co-located plasma measurements, which can be used to study a variety of phenomena, including measurements of auroral-like particle acceleration near crustal fields and the three-dimensional motion and shape of plasma boundaries. We will present an analysis of approximately forty conjunctions (instances with instantaneous spacecraft separation smaller than 400 km) of MEX and MGS identified between January 2004 and February 2006. The closest pass was ~40~km, near the South Pole. Conjunctions occur both at mid-latitudes (when the surface-projected orbit tracks of the two spacecraft nearly overlap), and at the poles. We will present comparisons of MEX Analyzer of Space Plasmas and Energetic Atoms (ASPERA-3) data with MGS Magnetometer and Electron Reflectometer (MAG/ER) data for these events. Our case studies include intercomparison of MEX and MGS electron data, the addition of MGS magnetic field and MEX ion data, and the inclusion of solar wind proxy information to establish context. In addition to these close conjunctions, we will present the preliminary results of a search for times when MEX and MGS pass through the same region of space separated by a delay (for time evolution of plasma populations in certain regions), and times when they occupy the same flux tube (for spatial evolution of particle distributions). Continued study of

  19. Research and Application of Avionic Software System Based on MVC Architecture%基于MVC架构的航电系统软件研究与应用

    郑凤; 昝济国


      针对大规模复杂航电系统软件的设计和开发,引入MVC(模型-视图-控制)的软件体系架构和设计模式,对软件行为主体进行持续抽象和封装,并在项目开发过程中迭代应用。研究结果证明,采用 MVC 架构很好的提高了软件设计和开发的可靠性、可扩展性和可复用性,增强了应用系统软件架构的灵活性和适应性。%To design and develop large-scale and complex avionic software system, we introduce the architecture and design pattern of MVC (mode-view-controller), in order to build abstraction and encapsulation on software actor. We use this iteratively during the course of item development. The results demonstrate that the MVC architecture is more reliable,flexible,dynamic and is reusable for software design and development, improving the agility and adaptability of software architecture.

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

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


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

  1. Perspectives of civil aircraft avionics development

    А. В. Наумов


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

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

    Shalkhauser, Mary Jo W.


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

  3. Magnetic sensors for motion measurement of avionic ballscrews

    E. Cardelli


    Full Text Available This paper deals with a theoretical and experimental study about the motion measurement in ballscrews for avionic system. The measurement system is based on a magnetic sensor optimized by a suitable finite element analysis. In particular the sensor performances are simulated for different configurations in order to maximize the sensitivity. The efficiency and the reliability of the optimal configuration found have been validated by means of a dedicated experiment for the simulation of the operative mode of the ballscrews in the avionic environment.

  4. Space shuttle orbiter avionics software: Post review report for the entry FACI (First Article Configuration Inspection). [including orbital flight tests integrated system

    Markos, H.


    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.

  5. Avionics Maintenance Technology Program Guide.

    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…

  6. Low-Cost Avionics Simulation for Aircrew Training.

    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…

  7. Wavelength and fiber assignment problems on avionic networks

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


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

  8. Wavelength and fiber assignment problems on avionic networks

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


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

  9. Cognitive Task Analysis and Intelligent Computer-Based Training Systems: Lessons Learned from Coached Practice Environments in Air Force Avionics.

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

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

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

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


    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.

  11. Fast Prediction with Sparse Multikernel LS-SVR Using Multiple Relevant Time Series and Its Application in Avionics System

    Yang M. Guo


    Full Text Available Health trend prediction is critical to ensure the safe operation of highly reliable systems. However, complex systems often present complex dynamic behaviors and uncertainty, which makes it difficult to develop a precise physical prediction model. Therefore, time series is often used for prediction in this case. In this paper, in order to obtain better prediction accuracy in shorter computation time, we propose a new scheme which utilizes multiple relevant time series to enhance the completeness of the information and adopts a prediction model based on least squares support vector regression (LS-SVR to perform prediction. In the scheme, we apply two innovative ways to overcome the drawbacks of the reported approaches. One is to remove certain support vectors by measuring the linear correlation to increase sparseness of LS-SVR; the other one is to determine the linear combination weights of multiple kernels by calculating the root mean squared error of each basis kernel. The results of prediction experiments indicate preliminarily that the proposed method is an effective approach for its good prediction accuracy and low computation time, and it is a valuable method in applications.

  12. Flexible Low Cost Avionics for NanoSatellite Launch Vehicle Control and GPS Metric Tracking Project

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

  13. The Gravity Field of Mars From MGS, Mars Odyssey, and MRO Radio Science

    Genova, Antonio; Goossens, Sander; Lemoine, Frank G.; Mazarico, Erwan; Smith, David E.; Zuber, Maria T.


    The Mars Global Surveyor (MGS), Mars Odyssey (ODY), and Mars Reconnaissance Orbiter (MRO) missions have enabled NASA to conduct reconnaissance and exploration of Mars from orbit for sixteen consecutive years. These radio systems on these spacecraft enabled radio science in orbit around Mars to improve the knowledge of the static structure of the Martian gravitational field. The continuity of the radio tracking data, which cover more than a solar cycle, also provides useful information to characterize the temporal variability of the gravity field, relevant to the planet's internal dynamics and the structure and dynamics of the atmosphere [1]. MGS operated for more than 7 years, between 1999 and 2006, in a frozen sun-synchronous, near-circular, polar orbit with the periapsis at approximately 370 km altitude. ODY and MRO have been orbiting Mars in two separate sun-synchronous orbits at different local times and altitudes. ODY began its mapping phase in 2002 with the periapis at approximately 390 km altitude and 4-5pm Local Solar Time (LST), whereas the MRO science mission started in November 2006 with the periapis at approximately 255 km altitude and 3pm LST. The 16 years of radio tracking data provide useful information on the atmospheric density in the Martian upper atmosphere. We used ODY and MRO radio data to recover the long-term periodicity of the major atmospheric constituents -- CO2, O, and He -- at the orbit altitudes of these two spacecraft [2]. The improved atmospheric model provides a better prediction of the annual and semi-annual variability of the dominant species. Therefore, the inclusion of the recovered model leads to improved orbit determination and an improved gravity field model of Mars with MGS, ODY, and MRO radio tracking data.

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

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


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

  15. Photonic technology for switched rf avionics networks

    Hamilton, Michael C.; Thaniyavarn, Suwat; Abbas, Gregory L.; LaGasse, Michael J.; Traynor, Timothy; Lin, Jack P.


    The application of photonics technology in switched RF networks is discussed with emphasis on the benefits for avionics applications. System requirements and performance issues are addressed. A 16 X 16 photonic switch module prototype is described and results for RF fiber-optic links passing through the module are presented. RF channel isolation measured was at least 75 dB. A demonstration is described in which a photonic network using the switch module passed signals from a dynamic electromagnetic environment simulator to two radar warning systems under test. Demonstration modes included simulation of both aperture sharing and processor sharing. Finally, a novel alternative switch module architecture is described that is strictly non-blocking and has inherently better channel isolation.

  16. Tanker avionics and aircrew complement evaluation.

    Moss, R W; Barbato, G J


    This paper describes an effort to determine control and display criteria for operating SAC's KC-135 tanker with a reduced crew complement. The Tanker Avionics and Aircrew Complement Evaluation (TAACE) Program was a four-phase effort addressing the control and display design issues associated with operating the tanker without the navigator position. Discussed are: the mission analysis phase, during which the tanker's operational responsibilities were defined and documented; the design phase, during which alternative crew station design concepts were developed; the mockup evaluation phase, which accomplished initial SAC crew member assessment of cockpit designs; and the simulation phase, which validated the useability of the crew system redesign. The paper also describes a recommended crew station configuration and discusses some of the philosophy underlying the selection of cockpit hardware and systems.

  17. Avionics Data Base.


    8217999’ is the unique sequence number assigned to a model. A * . - .. . ". , - .7- - 7- -k; I .. -- ,1 Listed below are the System/Chapters (XX) of the ATA...WfRRPN-Y I YR AS OF DATE 5/84 INDEX 231222 2 COMPONENT NAME NPY /COM TRPNSCEIV :R MPNUFPCTiURER AURE-SCIENCES MODEL RT-5 53P PRICE $2, 175.00 FAR 91 9rT...D&PRICE: 5.5 S.±S 3.55/. 5/ 11 .625 REMARKS 720 CHANNEL COMMUNIOPTIOCNS-: NPY -./COM SELECT7 ION COVERS 7ULL VOR/’LOC FREQUjENCY &P4NO 108 TO 117.35

  18. An Automatic Development Process for Integrated Modular Avionics Software


    With the ever-growing avionics functions, the modern avionics architecture is evolving from traditional federated architecture to Integrated Modular Avionics (IMA). ARINC653 is a major industry standard to support partitioning concept introduced in IMA to achieve security isolation between avionics functions with different criticalities. To decrease the complexity and improve the reliability of the design and implementation of IMA-based avionics software, this paper proposes an automatic deve...

  19. Validating Avionics Conceptual Architectures with Executable Specifications

    Nils Fischer


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

  20. Society of Automotive Engineers AS4074 family high-speed, fault-tolerant data communications standards for integrated avionics

    Meyer, John W.

    The Society of Automotive Engineers (SAE) has been addressing the need for data buses in advanced avionics systems. Since 1979, the SAE has had task groups developing a family of commercial data bus standards designed specifically for the unique fault-tolerant requirements of avionics applications: AS4074.1 linear, token-passing multiplex data bus (LTPB), and AS4074.2 high-speed ring bus (HSRB). The author explains the background of the two bus standards, gives a brief overview of the two protocols, and reviews current and future SAE activities in the avionics data bus field. It is concluded that the SAE LTPB and HSRB satisfy the data latency needs of emerging avionics architectures, as well as the reliability and fault tolerance requirements. Because of their ability to be supplemented with higher data rate versions, they will continue to support emerging avionics architectures.

  1. Rocksalt MgS solar blind ultra-violet detectors

    Ying-Hoi Lai


    Full Text Available Studies using in-situ Auger electron spectroscopy and reflection high energy electron diffraction, and ex-situ high resolution X-ray diffraction and electron backscatter diffraction reveal that a MgS thin film grown directly on a GaAs (100 substrate by molecular beam epitaxy adopts its most stable phase, the rocksalt structure, with a lattice constant of 5.20 Å. A Au/MgS/n+-GaAs (100 Schottky-barrier photodiode was fabricated and its room temperature photoresponse was measured to have a sharp fall-off edge at 235 nm with rejection of more than three orders at 400 nm and higher than five orders at 500 nm, promising for various solar-blind UV detection applications.

  2. An investigation of washability characteristics of lignites from Yenicubuk-Gemerek districts by MGS; Yenicubuk gemerek linyit komurlerinin MGS ile yikanabilirliginin arastirilmasi

    Aslan, N.; Canbazoglu, M.; Ulusoy, U. [Cumhuriyet Universitesi, Sivas (Turkey). Maden Muhendisligi Bolumu


    Washability and ash removal from Gemerek lignite in a multi gravity separator (MGS) were investigated. Experimental studies were carried out on -0.5 mm coal samples containing 37.75% ash in a laboratory C-900 type MGS. Drum speed, shake amplitude, tilt angle, shake frequency, wash water quantity and feed solid ratio were investigated. Optimum operating conditions were determined. 8 refs., 7 figs.

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

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


    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.

  4. Green software engineering for airbus avionics

    I. Brooks


    Presentation at EU Ashley Project Public Forum 25 October 2016. Presentation examines the risks from Software Engineering without sustainability requirements and looks at the use of the UN Sustainable Development Goals to de-risk avionics software engineering.

  5. Green software engineering for airbus avionics


    Presentation at EU Ashley Project Public Forum 25 October 2016. Presentation examines the risks from Software Engineering without sustainability requirements and looks at the use of the UN Sustainable Development Goals to de-risk avionics software engineering.

  6. The conduction bands of MgO, MgS and HfO2

    Boer, P.K. de; Groot, R.A. de


    Electronic structure calculations for MgO, MgS and HfO2 are reported. It is shown that the conduction bands of MgO and MgS have predominantly anion character, contrary to the common picture of the conduction band being derived from cation states. In transition metal oxides, unoccupied anion states a

  7. Avionics Simulation, Development and Software Engineering


    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.

  8. Development of Avionics Installation Interface Standards. Revision.


    impact on some portion of the avionics suite for Phase III of the Multinational Staged Improvement Pro- gram ( MSIP ). This program has not been fully...have improvement programs similar to that planned under the F-16 MSIP ) and piecemeal retrofit programs that are not shown on the chart. 2-4 * * The...i.e., MS 25212 form factor units) contained intrinsically low-dissi- pation avionics components and the major heat source was the standard inte

  9. OMAC4S- Open Modular Avionics for Space Applications

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


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

  10. ARINC 818 specification revisions enable new avionics architectures

    Grunwald, Paul


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

  11. MgS in detached shells around carbon stars. Mining the mass-loss history

    Hony, S


    We investigate the dust composition of detached shells around carbon stars, with a focus to understand the origin of the cool magnesium-sulfide (MgS) material around warm carbon stars, which has been detected around several of these objects. We build a radiative transfer model of a carbon star surrounded by an expanding detached shell of dust. The shell contains amorphous carbon grains and MgS grains. We find that a small fraction of MgS dust (2% of the dust mass) can give a significant contribution to the IRAS 25 micron flux. However, the presence of MgS in the detached shell cannot be inferred from the IRAS broadband photometry alone but requires infrared spectroscopy. We apply the model to the detached-shell sources R Scl and U Cam, both exhibiting a cool MgS feature in their ISO/SWS spectra. We use the shell parameters derived for the molecular shell, using the CO submillimetre maps. The models, with MgS grains located in the detached shell, explain the MgS grain temperature, as derived from their ISO spe...

  12. Extravehicular Activity (EVA) Power, Avionics, and Software (PAS) 101

    Irimies, David


    EVA systems consist of a spacesuit or garment, a PLSS, a PAS system, and spacesuit interface hardware. The PAS system is responsible for providing power for the suit, communication of several types of data between the suit and other mission assets, avionics hardware to perform numerous data display and processing functions, and information systems that provide crewmembers data to perform their tasks with more autonomy and efficiency. Irimies discussed how technology development efforts have advanced the state-of-the-art in these areas and shared technology development challenges.

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

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


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

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

    Nguyen, Hung D.; Ngo, Duc H.


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

  15. Thermal Defects of Avionic Turbojet Engines

    Szczepankowski Andrzej


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

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

    Julien Brunel


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

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

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


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


    Jairo Miguel Vergara Díaz


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

  19. Avionics. Progress Record and Theory Outline.

    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,…

  20. MultIMA- Multi-Core in Integrated Modular Avionics

    Silva, Claudio; Tatibana, Cassia


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




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

    Latorella, Kara A.


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

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

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


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

  4. Reliability and cost considerations for launch vehicle avionics

    Wensley, John H.; Uhrich, Don D.

    The optimum redundancy for an avionics processor can be determined from cost and reliability considerations. The use and expense of redundant architectures are examined, along with the cost and advantages of using space-qualified parts. The advanced launch system (ALS) vehicle model was used for the comparisons. Avionics redundancy models included duplex, triple modular redundancy, and quad systems. Processors were modeled as simplex, dual self-checking pairs, or triplex checking. Cost factors were those which result in the cost per launched vehicle. These included cost of launch equipment, cost of scrubbing a launch, failure investigation, repair, and the cost of money due to schedule delays. The primary conclusion reached was that the use of redundancy to achieve fault tolerance is required for higher value missions. The use of less-highly qualified parts can lower costs for less expensive payloads, but will require a culture change to allow launching with known faults. The need for greater emphasis on determination of coverage for fault-tolerant systems was demonstrated.

  5. Analysis of Properties of the North Polar Layered Deposits: THEMIS Data in Context of MGS Data

    Ivanov, A. B.; Byrne, S.; Richardson, M. I.; Vasavada, A. R.; Titus, T. N.; Bell, J. F.; McConnochie, T. H.; Christensen, P. R.


    One of the many questions of Martian exploration is to uncover the history of Mars, through analysis of the polar layered deposits (PLD). Martian polar ice caps hold most of the exposed water on the surface on Mars and yet their history and physical processed involved in their formation are unclear. We will attempt to contribute to our knowledge of the composition and stratigraphy of the polar deposits. In this work we present the latest imaging data acquired by the Mars Odyssey THermal EMission Imaging System (THEMIS) and place it into context of the Mars Global Surveyor (MGS) data. THEMIS provides capabilities for imaging in both thermal IR and visible color wavelengths. These observations are affected by atmospheric scattering and topography. The Mars Orbiter Laser Altimeter (MOLA) and Thermal Emission Spectrometer (TES) instruments on board of the MGS spacecraft can provide context information for THEMIS data. Of particular interest are Mars Orbiter Camera (MOC) images, which provide high resolution data. We are primarily interested in the seasonal evolution of ice cap temperatures during the first northern summer of THEMIS observations. Morphology, stratigraphy and composition of the layered deposits can be addressed by THEMIS VIS color images, along with MOC high resolution data and MOLA Digital Elevation Models (DEM). This work is intentionally descriptive. Based on the knowledge obtained by the orbiting spacecraft and described here, we will attempt to expose major directions for modeling and further understanding of of the physical processes involved in the formation of the polar layered terrain 2 Available data 2.1 THEMIS IR The THEMIS IR camera has 10 bands from 6 to 15 m. Due to to signal-to-noise restrictions the most useful band for polar observations is band 9 (12.57 m ). Band 10 (14.88 m ) data can be used for atmospheric calibration. An example of seasonal evolution observed by the THEMIS IR subsystem is shown in Figure 1. We have projected all IR

  6. Enabling Wireless Avionics Intra-Communications

    Torres, Omar; Nguyen, Truong; Mackenzie, Anne


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

  7. Design of development platform for hosted applications in integrated module avionics system%面向综合模块化航电系统的驻留应用开发平台设计

    王运盛; 雷航


    The common computing resources in the Integrated Modular Avionics (IMA) system provide the hosted applications with temporal and spatial partitioning platform. The platform for applications development should comply with the ARINC 653 specification which defines the application executive interfaces for partitioning operation system. By porting and developing the Board Support Package (BSP) and AFDX network driver, for the first time, an IMA platform solution for hosted application development was achieved based on the C2K, a Commercial Off-The-Shelf (COTS) single board computer. The functionality and performance of the COTS based platform are similar to the popular common computing resources in IMA of modern civil transportation aircraft, offering a development platform for hosted applications development and debug at a pretty lower costs.%综合模块化航电系统采用时间和空间分区技术隔离不同的应用程序,驻留在分区中应用程序的开发依赖于符合ARINC 653及相关接口和通信规范的开发平台.通过移植传统操作系统的板级支持包和开发驱动程序,使得商业单板计算机C2K支持符合ARINC 653规范的VxWorks 653分区操作系统并提供AFDX网络接口,首次实现了基于商业单板计算机C2K的驻留应用开发平台,其主要功能和性能与目前主流的大型客机综合模块化航电系统相当,可用来支持驻留应用的开发和调试,大幅度降低了成本.

  8. Optimal Management Of Renewable-Based Mgs An Intelligent Approach Through The Evolutionary Algorithm

    Mehdi Nafar


    Full Text Available Abstract- This article proposes a probabilistic frame built on Scenario fabrication to considerate the uncertainties in the finest action managing of Micro Grids MGs. The MG contains different recoverable energy resources such as Wind Turbine WT Micro Turbine MT Photovoltaic PV Fuel Cell FC and one battery as the storing device. The advised frame is based on scenario generation and Roulette wheel mechanism to produce different circumstances for handling the uncertainties of altered factors. It habits typical spreading role as a probability scattering function of random factors. The uncertainties which are measured in this paper are grid bid alterations cargo request calculating error and PV and WT yield power productions. It is well-intentioned to asset that solving the MG difficult for 24 hours of a day by considering diverse uncertainties and different constraints needs one powerful optimization method that can converge fast when it doesnt fall in local optimal topic. Simultaneously single Group Search Optimization GSO system is presented to vision the total search space globally. The GSO algorithm is instigated from group active of beasts. Also the GSO procedure one change is similarly planned for this algorithm. The planned context and way is applied o one test grid-connected MG as a typical grid.

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

    袁翔; 胡军; 马金晶; 刘雪


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

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

    Yang Shunkun; Liu Bin; Wang Shihai; Lu Minyan


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

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

    Shau-Shiun Jan


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

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

    Jan, Shau-Shiun


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

  13. Method of Display Entity Information of VR-forces on MGS Platform%基于MGS平台的VR-Forces实体信息显示方法

    韩晓光; 赵志军; 蔡郁知


    在同一模拟系统中同时使用MGS与VR-Forces平台,存在实体信息格式转换问题.为实现在MGS平台中显示VR-Forces中实体信息,分析了VR-Forces平台中实体信息的组织方式,基于XML技术构建了VR-Forces平台与MGS平台间的实体ID编码映射关系,实现了VR-Forces平台中实体经纬度、首向角、敌我关系等属性信息的获取方法,解决了基于MGS开发的模拟仿真训练程序与基于VR-Forces开发的模拟训练程序共存的问题,为后续具有类似功能需求的模拟系统开发提供了技术支持.%To use MGS and VR-Forces in the same simulation system, there is an entity information transform problem. To display VR-Forces entity information on MGS, the entity in heritance structure of VR-Forces is analyzed, building a Mapping Table of entity ID between VR-Forces and MGS platforms on XML technology. To achieve the methods to get latitude,heading,the enemy relationship from VR-Forces, the coexistence problem of MGS and VR-Forces are solved. The technical support for the development of simulation system with the similar function is provided.

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

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


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

  15. High-Safety Time Management Technology for Integrated Modular Avionic (IMA) System%综合模块化航电系统高安全性时间管理技术

    杜晓鹏; 孙泓宏; 王立端


    综合模块化航电(IMA)系统中错误信息的传输漏洞会对飞机安全带来严重影响,为了提高IMA系统时间传输的完整性,使子系统能在确定的时间窗口内进行数据传输,提出了一种IMA系统高安全性时间管理技术;通过使用多个时间管理服务,建立每个子系统与时间管理服务的偏差表,确定其本地时间参考(LTR)和与之通信的每个远程子系统时间参考之间的关系;使驻留IMA的子系统具有高安全性时间同步机制,能够协调分离的驻留子系统共同安全地执行同一任务,满足IMA系统时间同步和安全性要求.%False information transmission flaw in Integrated Modular Avionics ( IMA) system would seriously impact the aircraft safety. To improve the integrity of IMA system time transmission, a high-safety time management technology for IMA system was put forward, by which all published data on IMA platform will be transferred to subscribers as requested at one designated time window. By using multi-time management service, deviation table between each subsystem and time management service was set up, to identify the relationship between local time reference ( LTR) and the time reference of each remote subsystem communicating with LTR. The time management technology provides subsystems hosted in IMA with high-safety time synchronization mechanism, coordinates the separated hosted subsystems to safely execute a task together, thus can satisfy the time synchronization and safety requirements of IMA system.

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

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


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

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

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


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

  18. An Automatic Development Process for Integrated Modular Avionics Software

    Ying Wang


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

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


    ation T,\\F Tactical Ai- ’~orce NBC Nuclear Biological Chemical TAMPS Tactical Aircraft Mission Planning System NLR National Aerospace Laboratory TEAMS...features are two dimensional. Once the map has been trans- will appear to flicker. A refresh rate of 60 frames per second is formed from databse

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

    施劲松; 步鑫


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

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

    Sidibe, Souleymane

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

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

    Latorella, Kara; Harden, John W.


    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).

  3. Correcting Mars Global Surveyor Thermal Emission Spectrometer (MGS-TES) High Altitude (40 - 65 km) Temperature Retrievals for Instrumental Correlated Noise and Biases

    McConnochie, T. H.; Smith, M. D.


    Mars Global Surveyor Thermal Emission Spectrometer (MGS-TES) nadir-soundings have been used to derive atmospheric temperatures up to roughly 40 km [Conrath et al., JGR 105 2000, Smith et al., JGR 106, 2001], and MGS-TES limb soundings have been used to extend the atmospheric temperature data set to > 60 km in altitude [Smith et al., JGR 106, 2001]. The ~40 - ~65 km altitude range probed by the MGS-TES limb sounding is particularly important for capturing key dynamical features such as the warm winter polar mesosphere [e.g., Smith et al., JGR 106, 2001; McCleese et al., Nature Geoscience 1, 2008], and the response of thermal tides to dust opacity [e.g. Wilson and Hamilton, J. Atmos. Sci. 53, 1996]. Thus accurate and precise temperature profiles at these altitudes are particularly important for constraining global circulation models. They are also critical for interpreting observations of mesospheric condensate aerosols [e.g., Määttänen et al., Icarus 209, 2010; McConnochie et al., Icarus 210, 2010)]. We have indentified correlated noise components in the MGS-TES limb sounding radiances that propagate into very large uncertainties in the retrieved temperatures. We have also identified a slowly varying radiance bias in the limb sounding radiances. Note that the nadir-sounding-based MGS-TES atmospheric temperatures currently available from the Planetary Data System are not affected by either of these issues. These two issues affect the existing MGS-TES limb sounding temperature data set are as follows: Considering, for example, the 1.5 Pascal pressure level (which typically falls between 50 and 60 km altitude), correlated-noise induced standard errors for individual limb-sounding temperature retrievals were 3 - 5 K in Mars Year 24, rising to 5 - 15 K in Mars Year 25 and 10 - 15 K in Mars Year 26 and 27. The radiance bias, although consistent on ~10-sol time scales, is highly variable over the course of the MGS-TES mission. It results in temperatures (at the 1

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

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


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

  5. A COTS-derived NVG compatible 20.1" avionics display

    Thomas, J.; Cavalcanti, A.


    Many avionics displays, particularly for cockpit applications require NVG compatibility. Unusually, the mission definition for a new maritime helicopter has identified a need for NVG compatibility for all of the mission-system displays, including the 20.1" diagonal, SXGA resolution Tactical Workstation Display (TWD) located in the rear cabin. This paper will describe some design tradeoff considerations and describe both some required and measured performance parameters.

  6. Energy management and its impact on avionics Proceedings of the Symposium, London, England, March 19, 1981


    Topics discussed include design possibilities for improved fuel efficiency of civil transport aircraft, energy management in military combat aircraft, and the control of aircraft gas turbines for fuel economy. Particular attention is given to the impact of increasing cost upon the design of avionic fuel management systems and the operational and performance aspects of fuel management in civil aircraft. Consideration is also given to the FS2 Bedford Civil Flight Research Program as well as current and future developments in thrust management

  7. Affordable Access to Space (AAS): Affordable Vehicle Avionics Project

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

  8. Platform Independent Launch Vehicle Avionics with GPS Metric Tracking Project

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

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

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

  10. 2013 aircrew, avionics, and operations survey, part 2.

    Greene, Michael J


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

  11. Interconnection Optimization for Multi-Cluster Avionics Networks


    National audience; The increasing complexity and heterogeneity of avionics networks make resource optimization a challenging task. In contrast to many previous approaches pursuing the optimization of traffic-source mapping and backbone network analysis, our work presented herein mainly focuses on the optimization of interconnection devices for multi-cluster avionics networks. In this paper, we introduce an optimized interconnection device, integrating novel frame packing strategies and schedu...

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

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


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

  13. Avionic technology testing by using a cognitive neurometric index: A study with professional helicopter pilots.

    Borghini, Gianluca; Aricò, Pietro; Di Flumeri, Gianluca; Salinari, Serenella; Colosimo, Alfredo; Bonelli, Stefano; Napoletano, Linda; Ferreira, Ana; Babiloni, Fabio


    In this study, we investigated the possibility to evaluate the impact of different avionic technologies on the mental workload of helicopter's pilots by measuring their brain activity with the EEG during a series of simulated missions carried out at AgustaWestland facilities in Yeovil (UK). The tested avionic technologies were: i) Head-Up Display (HUD); ii) Head-Mounted Display (HMD); iii) Full Conformal symbology (FC); iv) Flight Guidance (FG) symbology; v) Synthetic Vision System (SVS); and vi) Radar Obstacles (RO) detection system. It has been already demonstrated that in cognitive tasks, when the cerebral workload increases the EEG power spectral density (PSD) in theta band over frontal areas increases, and the EEG PSD in alpha band decreases over parietal areas. A mental workload index (MWL) has been here defined as the ratio between the frontal theta and parietal alpha EEG PSD values. Such index has been used for testing and comparing the different avionic technologies. Results suggested that the HUD provided a significant (ptechnologies. In addition, the simultaneous use of FC and FG technologies (FC+FG) produced a significant decrement of the workload (ptechnology provided on Head Down Display (HDD) with the simultaneous use of FC+FG and the RO seemed to produce a lower cerebral workload when compared with the use of only the FC. Interestingly, the workload estimation by means of subjective measures, provided by pilots through a NASA-TLX questionnaire, did not provide any significant differences among the different flight scenarios. These results suggested that the proposed MWL cognitive neurometrics could be used as a reliable measure of the user's mental workload, being a valid indicator for the comparison and the test of different avionic technologies.

  14. High Performance Interconnection Technology in Avionics (Short Communication

    C. R. Raghunath


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

  15. Flight Crew Survey Responses from the Interval Management (IM) Avionics Phase 2 Flight Test

    Baxley, Brian T.; Swieringa, Kurt A.; Wilson, Sara R.; Roper, Roy D.; Hubbs, Clay E.; Goess, Paul A.; Shay, Richard F.


    The Interval Management (IM) Avionics Phase 2 flight test used three aircraft over a nineteen day period to operationally evaluate a prototype IM avionics. Quantitative data were collected on aircraft state data and IM spacing algorithm performance, and qualitative data were collected through end-of-scenario and end-of-day flight crew surveys. The majority of the IM operations met the performance goals established for spacing accuracy at the Achieve-by Point and the Planned Termination Point, however there were operations that did not meet goals for a variety of reasons. While the positive spacing accuracy results demonstrate the prototype IM avionics can contribute to the overall air traffic goal, critical issues were also identified that need to be addressed to enhance IM performance. The first category was those issues that impacted the conduct and results of the flight test, but are not part of the IM concept or procedures. These included the design of arrival and approach procedures was not ideal to support speed as the primary control mechanism, the ground-side of the Air Traffic Management Technology Demonstration (ATD-1) integrated concept of operations was not part of the flight test, and the high workload to manually enter the information required to conduct an IM operation. The second category was issues associated with the IM spacing algorithm or flight crew procedures. These issues include the high frequency of IM speed changes and reversals (accelerations), a mismatch between the deceleration rate used by the spacing algorithm and the actual aircraft performance, and some spacing error calculations were sensitive to normal operational variations in aircraft airspeed or altitude which triggered additional IM speed changes. Once the issues in these two categories are addressed, the future IM avionics should have considerable promise supporting the goals of improving system throughput and aircraft efficiency.

  16. The Mars Global Surveyor Ka-Band Link Experiment (MGS/KaBLE-II)

    Morabito, D.; Butman, S.; Shambayati, S.


    The Mars Global Surveyor (MGS) spacecraft, launched on November 7, 1996, carries an experimental space-to-ground telecommunications link at Ka-band (32 GHz) along with the primary X-band (8.4-GHz) downlink. The signals are simultaneously transmitted from a 1.5-m-diameter parabolic antenna on MGS and received by a beam-waveguide (BWG) research and development (R&D) 34-meter a ntenna located in NASA's Goldstone Deep Space Network (DSN) complex near Barstow, California. This Ka-band link experiment (KaBLE-II) allows the performances of the Ka-band and X-band signals to be compared under nearly identical conditions. The two signals have been regularly tracked during the past 2 years. This article presents carrier-signal-level data (P_c/N_o) for both X-band and Ka-band acquired over a wide range of station elevation angles, weather conditions, and solar elongation angles. The cruise phase of the mission covered the period from launch (November 7, 1996) to Mars orbit capture (September 12, 1997). Since September 12, 1997, MGS has been in orbit around Mars. The measurements confirm that Ka-band could increase data capacity by at least a factor of three (5 dB) as compared with X-band. During May 1998, the solar corona experiment, in which the effects of solar plasma on the X-band and Ka-band links were studied, was conducted. In addition, frequency and difference frequency (f_x - f_(Ka)/3.8), ranging, and telemetry data results are presented. MGS/KaBLE-II measured signal strengths (for 54 percent of the experiments conducted) that were in reasonable agreement with predicted values based on preflight knowledge, and frequency residuals that agreed between bands and whose statistics were consistent with expected noise sources. For passes in which measured signal strengths disagreed with predicted values, the problems were traced to known deficiencies, for example, equipment operating under certain conditions, such as a cold Ka-band solid-state power amplifier (SSPA

  17. Avionics Panel Symposium on Electronic Counter-Counter Measures for Avionics Sensors and Communication Systems Held in Ottobrunn, Germany on 1-5 October 1990 (Les Contre-Contremeasures Electroniques pour les Capteurs d’Avionique et Les Systemes de Telecommunications).


    natives of Munich contend that their Oktoberfest is the largest carnival in the ,orld. They awe probably nog.. because six to seven million visitors who...enemy’s SATCOM systems can be jammed on the capabilities for designated threat scene- dovnlinks and the uplinks. A jamming rios . The performance of the

  18. Defense Acquisitions: Assessment of Institute for Defense Analyses C-130 Avionics Modernization Program Analysis


    Page 1 GAO-14-547R C-130 Avionics Modernization Program 441 G St. N.W. Washington, DC 20548 May 29, 2014...Congressional Committees Defense Acquisitions: Assessment of Institute for Defense Analyses’ C-130 Avionics Modernization Program Analysis The Air...Force’s C-130 Avionics Modernization Program (AMP), which entered development in 2001, was to standardize and upgrade the cockpit and avionics for

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

    Coffey, Connor


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

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

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


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

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

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


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

  2. Determination of Net Martian Polar Dust Flux from MGS-TES Observations

    Blackmon, M. A.; Murphy, J. R.


    Using atmospheric dust abundance and atmospheric temperature observation data from the Thermal Emission Spectrometer (TES) on board the Mars Global Surveyor (MGS), the net flux of dust into and out of the Martian polar regions will be examined. Mars polar regions possess layered terrain , believed to be comprised of a mixture of ice and dust, with the different layers possibly representing different past climate regimes. These changes in climate may reflect changes in the deposition of dust and volatiles through impacts, volcanism, changes in resources of ice and dust, and response to Milankovitch type cycles (changes in eccentricity of orbit, obliquity and precession of axis). Understanding how rapidly such layers can be generated is an important element to understanding Mars climate history. This study uses the observed vertical temperature data and dust content measurements from TES to analyze the sign (gain or loss) of dust at high latitudes.

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


    Avionics Compartments Table 6-1 A-10A Avionics Configuration Data: 6-2 VHF/AM Radio System, Wilcox 807A (AN/ARC-134) NSN: 5821-00-937-1087 vii LIST OF...scalte eflection for aDorcacn flignt nrodes. nde o f erence: Desired approach course 4:n t Direction Sense: Fly right (+ right) S1eCtrical

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

    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…

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

    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…

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

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


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

  7. Anionic lipid binding to the foreign protein MGS provides a tight coupling between phospholipid synthesis and protein overexpression in Escherichia coli.

    Ariöz, Candan; Ye, Weihua; Bakali, Amin; Ge, Changrong; Liebau, Jobst; Götzke, Hansjörg; Barth, Andreas; Wieslander, Ake; Mäler, Lena


    Certain membrane proteins involved in lipid synthesis can induce formation of new intracellular membranes in Escherichia coli, i.e., intracellular vesicles. Among those, the foreign monotopic glycosyltransferase MGS from Acholeplasma laidlawii triggers such massive lipid synthesis when overexpressed. To examine the mechanism behind the increased lipid synthesis, we investigated the lipid binding properties of MGS in vivo together with the correlation between lipid synthesis and MGS overexpression levels. A good correlation between produced lipid quantities and overexpressed MGS protein was observed when standard LB medium was supplemented with four different lipid precursors that have significant roles in the lipid biosynthesis pathway. Interestingly, this correlation was highest concerning anionic lipid production and at the same time dependent on the selective binding of anionic lipid molecules by MGS. A selective interaction with anionic lipids was also observed in vitro by (31)P NMR binding studies using bicelles prepared with E. coli lipids. The results clearly demonstrate that the discriminative withdrawal of anionic lipids, especially phosphatidylglycerol, from the membrane through MGS binding triggers an in vivo signal for cells to create a "feed-forward" stimulation of lipid synthesis in E. coli. By this mechanism, cells can produce more membrane surface in order to accommodate excessively produced MGS molecules, which results in an interdependent cycle of lipid and MGS protein synthesis.

  8. Space tug point design study. Volume 3: Design definition. Part 1: Propulsion and mechanical, avionics, thermal control and electrical power subsystems


    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.

  9. Seasonal and static gravity field of Mars from MGS, Mars Odyssey and MRO radio science

    Genova, Antonio; Goossens, Sander; Lemoine, Frank G.; Mazarico, Erwan; Neumann, Gregory A.; Smith, David E.; Zuber, Maria T.


    We present a spherical harmonic solution of the static gravity field of Mars to degree and order 120, GMM-3, that has been calculated using the Deep Space Network tracking data of the NASA Mars missions, Mars Global Surveyor (MGS), Mars Odyssey (ODY), and the Mars Reconnaissance Orbiter (MRO). We have also jointly determined spherical harmonic solutions for the static and time-variable gravity field of Mars, and the Mars k2 Love numbers, exclusive of the gravity contribution of the atmosphere. Consequently, the retrieved time-varying gravity coefficients and the Love number k2 solely yield seasonal variations in the mass of the polar caps and the solid tides of Mars, respectively. We obtain a Mars Love number k2 of 0.1697 ± 0.0027 (3-σ). The inclusion of MRO tracking data results in improved seasonal gravity field coefficients C30 and, for the first time, C50. Refinements of the atmospheric model in our orbit determination program have allowed us to monitor the odd zonal harmonic C30 for ∼1.5 solar cycles (16 years). This gravity model shows improved correlations with MOLA topography up to 15% larger at higher harmonics (l = 60-80) than previous solutions.

  10. Developing Avionics Hardware and Software for Rocket Engine Testing

    Aberg, Bryce Robert


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

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

    Mayfield, T; Cady, G


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

  12. Magnetic losses in Si-Fe alloys for avionic applications

    E. Cardelli


    Full Text Available This paper presents an experimental analysis of the rotational power losses of the magnetic materials of transformers, motors and actuators used in avionic environment. A large frequency range is investigated using a suitable experimental test frame developed to measure the power losses for a circular magnetization. The results about different silicon iron alloys with different textures and thickness are considered and compared.

  13. Molecular beam epitaxy-grown wurtzite MgS thin films for solar-blind ultra-violet detection

    Lai, Y. H.; He, Q. L. [Nano Science and Nano Technology Program, The Hong Kong University of Science and Technology, HKSAR, People' s Republic of China (China); Department of Physics and William Mong Institute of Nano Science and Technology, The Hong Kong University of Science and Technology, HKSAR, People' s Republic of China (China); Cheung, W. Y.; Lok, S. K.; Wong, K. S.; Sou, I. K. [Department of Physics and William Mong Institute of Nano Science and Technology, The Hong Kong University of Science and Technology, HKSAR, People' s Republic of China (China); Ho, S. K. [Faculty of Science and Technology, University of Macau, Macau, People' s Republic of China (China); Tam, K. W. [Department of Electrical and Electronics Engineering, University of Macau, Macau, People' s Republic of China (China)


    Molecular beam epitaxy grown MgS on GaAs(111)B substrate was resulted in wurtzite phase, as demonstrated by detailed structural characterizations. Phenomenological arguments were used to account for why wurtzite phase is preferred over zincblende phase or its most stable rocksalt phase. Results of photoresponse and reflectance measurements performed on wurtzite MgS photodiodes suggest a direct bandgap at around 5.1 eV. Their response peaks at 245 nm with quantum efficiency of 9.9% and enjoys rejection of more than three orders at 320 nm and close to five orders at longer wavelengths, proving the photodiodes highly competitive in solar-blind ultraviolet detection.

  14. System 2020 - Strategic Initiative


    avionics ,   automotive   products,   and   financial   analysis   systems.   Organizations   in   these   sectors   report...series   of   Block   Upgrades   (major   aircraft   and   avionics   revisions),   software   and   avionics   (major...automation  mechanisms  may  be  employed,   ala  Microsoft’s   nightly   builds,   developer-­‐tester   buddy

  15. Simulation of the charge collection and signal response of a HPGe double sided strip detector using MGS

    Mateu, I., E-mail: [Université de Toulouse, UPS-OMP, IRAP, Toulouse (France); CNRS, IRAP, 9 Av. colonel Roche, BP 44346, F-31028 Toulouse cedex 4 (France); Medina, P., E-mail: [IPHC, IN2P3 – CNRS/Université Louis Pasteur, 23 rue du Loess, PB28, Strasbourg Cedex 2, F67037 (France); Roques, J.P., E-mail: [Université de Toulouse, UPS-OMP, IRAP, Toulouse (France); CNRS, IRAP, 9 Av. colonel Roche, BP 44346, F-31028 Toulouse cedex 4 (France); Jourdain, E., E-mail: [Université de Toulouse, UPS-OMP, IRAP, Toulouse (France); CNRS, IRAP, 9 Av. colonel Roche, BP 44346, F-31028 Toulouse cedex 4 (France)


    This paper aims to present Multi geometry Simulation (MGS), a software intended for the characterization of the signal response of solid state detectors. Its main feature is the calculation of the pulse shapes induced at the electrodes of the detector by a photon–semiconductor interaction occurring at a specific position inside the detector volume. The program uses numerical methods to simulate the drift of the charge carriers generated by the interaction, as the movement of these particles induces the useful signal for detection to the electrodes. After the description of the tool fundamentals, an example of application is presented where MGS was used for simulating a High Purity Germanium (HPGe) double sided strip detector conceived for hard X-ray astronomy. Simulated and measured pulse shapes are compared for interactions occurring at different depths in the detector volume. The comparison focuses on the difference in time of arrival between the anode and cathode pulses, as this measure allows, together with the X/Y information retrieved from the strips, a 3D determination of the photon interaction point, which is an important feature of the detector. A good matching between simulations and measurements is obtained, with a discrepancy less than 0.5 mm between the measured and the simulated depth of the interaction, for an 11 mm thick detector. -- Highlights: • Description of MGS, a tool for the synthesis of the signal response of solid state detectors. • Validation of the simulator through comparison with measurements on a DSSD prototype. • Discussion on the advantages, drawbacks and possible evolutions of MGS.

  16. Spectroscopy of the X^1Σ^+, A^1Π and B^1Σ^+ Electronic States of MgS

    Caron, Nicholas; Tokaryk, Dennis W.; Adam, Allan G.; Linton, Colan


    The spectra of some astrophysical sources contain signatures from molecules containing magnesium or sulphur atoms. Therefore, we have extended previous studies of the diatomic molecule MgS, which is a possible candidate for astrophysical detection. Microwave spectra of X^1Σ^+ , the ground electronic state, were reported in 1989 and 1997, and the B^1Σ^+-X^1Σ^+ electronic absorption spectrum in the blue was last studied in 1970. We have investigated the B^1Σ^+-X^1Σ^+ 0-0 spectrum of MgS at high resolution under jet-cooled conditions in a laser-ablation molecular source, and have obtained laser-induced fluorescence spectra from four isotopologues. Dispersed fluorescence from this source identified the low-lying A^1Π state near 4520 wn. We also created MgS in a Broida oven, with the help of a stream of activated nitrogen, and took rotationally resolved dispersed fluorescence spectra of the B^1Σ^+-A^1Π transition with a grating spectrometer by laser excitation of individual rotational levels of the B^1Σ^+ state via the B^1Σ^+-X^1Σ^+ transition. These spectra provide a first observation and analysis of the A^1Π state. S. Takano, S. Yamamoto and S. Saito, Chem. Phys. Lett. 159, 563-566 (1989) K. A. Walker and M. C. L. Gerry, J. Mol. Spectrosc 182, 178-183 (1997) M. Marcano and R. F. Barrow, Trans. Faraday Soc. 66, 2936-2938 (1970)

  17. MGS-TES thermal inertia study of the Arsia Mons Caldera

    Cushing, G.E.; Titus, T.N.


    Temperatures of the Arsia Mons caldera floor and two nearby control areas were obtained by the Mars Global Surveyor (MGS) Thermal Emission Spectrometer (TES). These observations revealed that the Arsia Mons caldera floor exhibits thermal behavior different from the surrounding Tharsis region when compared with thermal models. Our technique compares modeled and observed data to determine best fit values of thermal inertia, layer depth, and albedo. Best fit modeled values are accurate in the two control regions, but those in the Arsia Mons' caldera are consistently either up to 15 K warmer than afternoon observations, or have albedo values that are more than two standard deviations higher than the observed mean. Models of both homogeneous and layered (such as dust over bedrock) cases were compared, with layered-cases indicating a surface layer at least thick enough to insulate itself from diurnal effects of an underlying substrate material. Because best fit models of the caldera floor poorly match observations, it is likely that the caldera floor experiences some physical process not incorporated into our thermal model. Even on Mars, Arsia Mons is an extreme environment where CO2 condenses upon the caldera floor every night, diurnal temperatures range each day by a factor of nearly 2, and annual average atmospheric pressure is only around one millibar. Here, we explore several possibilities that may explain the poor modeled fits to caldera floor and conclude that temperature dependent thermal conductivity may cause thermal inertia to vary diurnally, and this effect may be exaggerated by presence of water-ice clouds, which occur frequently above Arsia Mons. Copyright 2008 by the American Geophysical Union.

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

    R. Sethunadh


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

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

    Ivancic, William D.


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

  20. Electronics Principles Avionics Aerospace Ground Equipment (AGE) Career Ladder AFSCS 326X0A, B, C, D.


    This report summarizes the results of the administration of the Electronics Principles survey to airmen assigned to the Avionics Aerospace Ground Equipment (AGE) specialties, including 326XOA, Manually Operated Avionics AGE; 326XOB, Automatic Avionics AGE; 326XOC, F/RF-4 Peculiar AGE, and 326XOD, A-7D Avionics AGE. The report gives a detailed listing of the technical tasks and knowledge needed to

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

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


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

  2. An examination of Mars' north seasonal polar cap using MGS: Composition and infrared radiation balance

    Hansen, Gary B.


    A detailed analysis of data from one revolution of the Mars Global Surveyor (MGS) is presented. Approximately 80% of this revolution observes the mid-winter northern seasonal polar cap, which covers the surface to night. The surface composition and temperature are determined through analysis of 6-50 μm infrared spectra from the Thermal Emission Spectrometer (TES). The infrared radiative balance, which is the entire heat balance in the polar night except for small subsurface and atmospheric advection terms, is calculated for the surface and atmospheric column. The primary constituent, CO2 ice, also dominates the infrared spectral properties by variations in its grain size and by admixtures of dust and water ice, which cause large variations in the 20-50 μm emissivity. This is modified by incomplete areal coverage, and clouds or hazes. This quantitative analysis reveals CO2 grain radii ranging from ˜100 μm in isolated areas, to 1-5 mm in more widespread regions. The water ice content varies from none to about one part per thousand by mass, with a clear increase towards the periphery of the polar cap. The dust content is typically a few parts per thousand by mass, but is as much as an order of magnitude less abundant in "cold spot" regions, where the low emissivity of pure CO2 ice is revealed. This is the first quantitative analysis of thermal spectra of the seasonal polar cap and the first to estimate water ice content. Our models show that the cold spots represent cleaner, dust-free ice rather than finer grained ice than the background. Our guess is that the dust in cold spots is hidden in the center of the CO2 frost particles rather than not present. The fringes of the cap have more dust and water ice, and become patchy, with warmer water snow filling the gaps on the night side, and warmer bare soil on the day side. A low optical depth (night side, and appears with smaller optical depth on the day side. The infrared radiative balance at the surface is typically

  3. Modular, Plug and Play, Distributed Avionics Project

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

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

    Stehura, Aaron; Rozek, Matthew


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

  5. General Aviation Activity and Avionics Survey


    Slope 1154 i44.5%) Microwave System No Par 2.3(.9%) VOR NA VIGA TION EQUIPMENT 100 -7nelVR _1:;:68 1(26.2%) 200 Channel VOR 200 Channel VOR .119 0(45 9...OTHER NA VIGA TION EQUIPMENT Radar Altimeter 19. 1(7.3%) Weather Radar 22.4 (8.6%) Thunderstorm Detection Equipment = 14.3(5.5%) No Navigation

  6. Architecture Specification for PAVE PILLAR Avionics

    1987-01-01 Abort Rate The goal for abort rate shall be 1% or less. Combat Turnaround Time The PAVE PILLAR design will impose no system re...where stringent environmental requirements ars imposed . Class IV - For utilization where class II modules may be exposed to radiation. 2.0 REFERENCED...5-7 Figure 5-2. Header Word A Format - Data Lines .. .......... 5-13 Figura 5-3. SIngle Slave Acknowledge Word Format - Date

  7. Formal verification of an avionics microprocessor

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


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

  8. FPGA for Power Control of MSL Avionics

    Wang, Duo; Burke, Gary R.


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

  9. Fossil gastropods from the MGS3 stratigraphic segment in the Salawusu River Valley and their climatic and environmental implications

    LI BaoSheng; YE JianPing; GUO YunHai; CHEN DeNiu; David Dian ZHANG; WEN XiaoHao; QIU ShiFan; OU XianJiao; DU ShuHuan; NIU DongFeng; YANG Yi


    Contemporaneous with MIS3, the MGS3 segment of the Milanggouwan stratigraphic section in the Salawusu River Valley, Mu Us Desert, China contains fossil gastropods (terrestrial and freshwater snails) in strata 33LS, 35LS, 37FL and 39LS. Examination of these fossils revealed 11 species belonging to 8 families and 10 genera. They can be classified as: (1) assemblage of Gyraulus and Galba mainly consisting of Gyraulus convexiusculus, Gyraulus sibiricus, Galba pervia and Galba superegra Gredler,etc. (2) assemblage of Vallonia mainly consisting of terrestrial snails, such as Vallonia patens, Pupilla muscorum and Discus paupe, etc. Based on the dating results, and the living habits, living conditions,and geographic distribution of their extant species, we suggest that: the ages of 33LS, 35LS, 37FL, and 39LS are 26000, 29000, 33000 and 38000 a, respectively, corresponding well to the interstadial period in GRIP 4,5, 6 and 10 in terms of chronology and climatic characters; 33LS, 35LS and 39LS represent very warm-humid periods, while 37FL represents a less warm-humid period; the four periods of climatic fluctuations recorded in MGS3 were related to the strong impact of the summer monsoon in East Asia in Mu Us Desert of China during the interstadial of MIS3 on a global climatic background.

  10. Fossil gastropods from the MGS3 stratigraphic segment in the Salawusu River Valley and their climatic and environmental implications

    David; Dian


    Contemporaneous with MIS3, the MGS3 segment of the Milanggouwan stratigraphic section in the Salawusu River Valley, Mu Us Desert, China contains fossil gastropods (terrestrial and freshwater snails) in strata 33LS, 35LS, 37FL and 39LS. Examination of these fossils revealed 11 species belonging to 8 families and 10 genera. They can be classified as: (1) assemblage of Gyraulus and Galba mainly consisting of Gyraulus convexiusculus, Gyraulus sibiricus, Galba pervia and Galba superegra Gredler, etc. (2) assemblage of Vallonia mainly consisting of terrestrial snails, such as Vallonia patens, Pupilla muscorum and Discus paupe, etc. Based on the dating results, and the living habits, living conditions, and geographic distribution of their extant species, we suggest that: the ages of 33LS, 35LS, 37FL, and 39LS are 26000, 29000, 33000 and 38000 a, respectively, corresponding well to the interstadial period in GRIP 4, 5, 6 and 10 in terms of chronology and climatic characters; 33LS, 35LS and 39LS represent very warm-humid periods, while 37FL represents a less warm-humid period; the four periods of climatic fluctuations recorded in MGS3 were related to the strong impact of the summer monsoon in East Asia in Mu Us Desert of China during the interstadial of MIS3 on a global climatic background.

  11. An Investigation of the Correlation of Water-Ice and Dust Retrievals Via the MGS TES Data Set

    Qu, Z.; Tamppari, L. K.; Smith, M. D.; Bass, Deborah; Hale, A. S.


    Water-ice in the Martian atmosphere was first identified in the Mariner 9 Infrared Interferometer Spectrometer (IRIS) spectra. The Viking Imaging Subsystem (VIS) instruments aboard the Viking orbiter also observed water-ice clouds and hazes in the Martian atmosphere. The MGS TES instrument is an infrared inferometer/spectrometer which covers the spectral range 6-50 micron with a selectable sampling resolution of either 5 or 10 per cm. Using the relatively independent and distinct spectral signatures for dust and water-ice, these two retrieved quantities have been retrieved simultaneously. Although the interrelations among the two quantities have been analyzed by Smith et al. and the retrievals are thought to be robust, understanding the impact of each quantity on the other during their retrievals as well as the impact from the surface for retrievals is important for correctly interpreting the science, and therefore requires close examination. An understanding of the correlation or a-correlation between dust and water-ice would aid in understanding the physical processes responsible for the transport of aerosols in the Martian atmosphere. In this presentation, we present an investigation of the correlation between water-ice and dust in the MGS TES data set.

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

    Laughter, Sean A.


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

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


    ... Administration 14 CFR Part 21 Final Additional Airworthiness Design Standards: Advanced Avionics Under the... document is an issuance of the final airworthiness design criteria for the inclusion of advance...

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

    Kuehl, C. Stephen


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

  15. Extending MGS-TES Temperature Retrievals in the Martian Atmosphere up to 90 Km: Retrieval Approach and Results

    Feofilov, A. G.; Kutepov, A. A.; Rezac, L.; Smith, M. D.


    This paper describes a methodology for performing a temperature retrieval in the Martian atmosphere in the 50-90 km altitude range using spectrally integrated 15 micrometers C02 limb emissions measured by the Thermal Emission Spectrometer (TES), the thermal infrared spectrometer on board the Mars Global Surveyor (MGS). We demonstrate that temperature retrievals from limb observations in the 75-90 km altitude range require accounting for the non-local thermodynamic equilibrium (non-LTE) populations of the C02(v2) vibrational levels. Using the methodology described in the paper, we have retrieved approximately 1200 individual temperature profiles from MGS TES limb observations in the altitude range between 60 and 90 km. 0ur dataset of retrieved temperature profiles is available for download in supplemental materials of this paper. The temperature retrieval uncertainties are mainly caused by radiance noise, and are estimated to be about 2 K at 60 km and below, 4 K at 70 km, 7 K at 80 km, 10 K at 85 km, and 20 K at 90 km. We compare the retrieved profiles to Mars Climate Database temperature profiles and find good qualitative agreement. Quantitatively, our retrieved profiles are in general warmer and demonstrate strong variability with the following values for bias and standard deviations (in brackets) compared to the Martian Year 24 dataset of the Mars Climate Database: 6 (+/-20) K at 60 km, 7.5 (+/-25) K at 65 km, 9 (+/-27) K at 70 km, 9.5 (+/-27) K at 75 km, 10 (+/-28) K at 80 km, 11 (+/-29) K at 85 km, and 11.5 (+/-31) K at 90 km. Possible reasons for the positive temperature bias are discussed. carbon dioxide molecular vibrations

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

    Gagne, Jocelyn

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

  17. 新一代航空电子综合化及预测与健康管理技术%Technologies of New Generation Avionics Integration and Prognostics and Health Management

    赵宁社; 翟正军; 王国庆


    Based on the introduction of the evolution of avionics systems, the main features of the new generation integrated avionics system are analyzed and the key technology of avionics PHM are probed deeply, including physical-of-failure(POF), stress damage assessment, failure precursor and canary. Moreover, the key technology and applications of the PHM-related information fusion, artificial intelligence, data mining and prognostics are thoroughly analyzed. Finally, the architecture of new generation integrated modular avionics system and PHM are researched and given.%在介绍航空电子系统发展演变历史的基础上,分析了新一代综合化航电系统的主要特征,深入探讨了航空电子预测与健康管理(PHM)的关键技术,包括失效机理分析、应力损伤评估、故障先兆以及预警电路(canary)4个类别,详细分析了PHM相关的信息融合、人工智能、数据挖掘与预测等技术的实现方法与应用,研究并给出了新一代综合模块化航空电子系统与PHM的体系架构.

  18. Micro Coriolis mass flow sensor for chemical micropropulsion systems

    Wiegerink, Remco J.; Lammerink, Theodorus S.J.; Groenesteijn, Jarno; Dijkstra, Pieter J.; Lötters, Joost Conrad


    We have designed a micromachined micro Coriolis flow sensor for the measurement of hydrazine (N2H4, High Purity Grade) propellant flow in micro chemical propulsion systems. The sensor measures mass flow up to 10 mg/s for a single thruster or up to 40 mg/s for four thrusters. The sensor will first be

  19. Digital Avionics Information System (DAIS): Development and Demonstration.


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

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


    ntrensasi are lessa than 60 of ultimate, it wo~uldl appear that no aipe~ itil allowan~ce in necesnairy ii; C.Y.C. structures to achieve the required in...the range 20000 to 30000 C for 30 minutes. On heating to about 2600-2800"C the vapor grown fibers undcrgo an increase in perfection which is shown by

  1. A Survey of Computer Simulations of Digital Avionics Systems.


    62 REFERENCES....................66 BIBLIOGRAPHY...................68 vi LIST OF FIGURES Figure Page 1 The GCSS Batch Run Environment ...Simulator Figure 1 presents a pictorial representation of this environment . The IPP process formats and derives initialization infor- mation from user...modules in the simulation, most are straightforward: RSTA is a flag array, MDIO is the number of direct I/O devices in the simulation. Table 1 contains

  2. Enhancements and Algorithms for Avionic Information Processing System Design Methodology.


    scheduling theory. Generally speaking , a set of tasks is to be scheduled on one or more machines, in order to optimize some performance criterion...0 P 0 4.• efl I I2 0" I I a z - "" K 01) a OR - Uz u4 II u.s;s ) I ; -. Z X 0 V2 I. ?- S 1z -- -’A- - - f. i. A 0o00l Kc mg ii g O~U 00 C u I- Z 11 1

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


    alors qua l’obstacla qua V’on vaut datecter dans la precipitation a up temps de d~corr~lation plut~t de l’ordre de 30 ma. Un gain de traitenant de 8...comme de nuit, par brouillards divers et precipitations relativement importantes, conditions qui couvrent 99 % des cas d’emnloi. Rgf~rences : ( Direct Voice Input ( DVI ) with its counterpart, Synthetic Speech, helping to a lesser extent. These items are now considered in turn. AUTOMATION

  4. Constraints on the Within Season and Between Year Variability of the North Residual Cap from MGS-TES

    Calvin, W. M.; Titus, T. N.; Mahoney, S. A.


    There is a long history of telescopic and spacecraft observations of the polar regions of Mars. The finely laminated ice deposits and surrounding layered terrains are commonly thought to contain a record of past climate conditions and change. Understanding the basic nature of the deposits and their mineral and ice constituents is a continued focus of current and future orbited missions. Unresolved issues in Martian polar science include a) the unusual nature of the CO2 ice deposits ("Swiss Cheese", "slab ice" etc.) b) the relationship of the ice deposits to underlying layered units (which differs from the north to the south), c) understanding the seasonal variations and their connections to the finely laminated units observed in high-resolution images and d) the relationship of dark materials in the wind-swept lanes and reentrant valleys to the surrounding dark dune and surface materials. Our work focuses on understanding these issues in relationship to the north residual ice cap. Recent work using Mars Global Surveyor (MGS) data sets have described evolution of the seasonal CO2 frost deposits. In addition, the north polar residual ice cap exhibits albedo variations between Mars years and within the summer season. The Thermal Emission Spectrometer (TES) data set can augment these observations providing additional constraints such as temperature evolution and spectral properties associated with ice and rocky materials. Exploration of these properties is the subject of our current study.

  5. Game theoretic wireless resource allocation for H.264 MGS video transmission over cognitive radio networks

    Fragkoulis, Alexandros; Kondi, Lisimachos P.; Parsopoulos, Konstantinos E.


    We propose a method for the fair and efficient allocation of wireless resources over a cognitive radio system network to transmit multiple scalable video streams to multiple users. The method exploits the dynamic architecture of the Scalable Video Coding extension of the H.264 standard, along with the diversity that OFDMA networks provide. We use a game-theoretic Nash Bargaining Solution (NBS) framework to ensure that each user receives the minimum video quality requirements, while maintaining fairness over the cognitive radio system. An optimization problem is formulated, where the objective is the maximization of the Nash product while minimizing the waste of resources. The problem is solved by using a Swarm Intelligence optimizer, namely Particle Swarm Optimization. Due to the high dimensionality of the problem, we also introduce a dimension-reduction technique. Our experimental results demonstrate the fairness imposed by the employed NBS framework.

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

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


    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.

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

    Coast Guard Inst., Oklahoma City, OK.

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

  8. Simulation et modélisation de l’aérodynamique des configurations complexes d’avions

    Barth, Marcus


    La prévision de l’aérodynamique des configurations complexes d’avion joue un rôle central dans le développement des avions, tant en termes de conception (e.g. l’optimisation des éléments hyptersustentateurs) qu’en termes de prévision des caractéristiques aérodynamiques de l’avion (e.g. la prévision des performances et des qualités de vol). Cette thèse s’attache uniquement au deuxième aspect, c’est-à-dire à la prévision des caractéristiques aérodynamiques de l’avion. Les configurations d’avion...

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


    ... Federal Aviation Administration 14 CFR Part 21 Proposed Additional Airworthiness Design Standards...: This document announces the issuance of the design criteria for the inclusion of advance avionics with intergrated electronic displays for the Aquila Aviation by Excellence GmbH AT01-100. These...

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


    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.

  11. Proton and neutron test facilities at 1 GeV synchrocyclotron of PNPI for radiation resistance testing of avionic and space electronics

    Ivanov Evgeniy M.


    Full Text Available A description of the proton (IS SC-1000, IS OP-1000 and neutron (IS NP/GNEIS test facilities at the 1 GeV synchrocyclotron SC-1000 of the PNPI used for radiation resistance testing of electronic components and systems intended for avionic and space research is presented. A unique conjunction of proton beams with variable energy 100–1000 MeV and atmospheric like neutron beam with broad energy range (1–1000 MeV spectrum enables to perform complex testing of the semiconductor electronic devices within a single testing cycle.

  12. Occupational Survey Report AFSC 2A0X1A Avionics Test Station and Components (Avionics Systems, F-15)


    on EARTS • Operationally check radar low-voltage power supplies (LVPSs) (610s) on EARTS • Service antenna mounting fixtures ( AMFs ) on EARTS...Tasks Job Enl Emp Dif ATI A0025 Fabricate or rebuild cables 53 65 5.33 5.18 18 A0030 Interpret block diagrams or schematics 47 60 7.08 5.29 18 A0033


    Sri Ayu


    Full Text Available Dalam proses pembelajaran siswa dituntut untuk aktif melaluiaktivitas-aktivitas yang membangun kerja kelompok dan dalam waktu singkatmembuat mereka berfikir tentang materi pelajaran. Keterlibatan siswa secara aktif dalam pembelajaran biologi sangat diperlukan, sehingga apa yang dipelajari akan lebih tertanam dalam pikiran siswa. PenerapanMonopoly Games Smartpada pembelajaranBiologi merupakan salah satu alternatif untuk meningkatkan motivasi dan kreatifitas siswa serta dapat mengurangi kejenuhan belajar siswa, sehingga mendapatkanhasilbelajar siswa yang memuaskan. Adapun yang menjadi tujuan penelitian ini adalah:(1 Untuk mengkaji penerapan media MGS (Monopoly Games Smart pada materi Ekosistem di MTs Al-Wahdah Sumber. (2 Untuk mengkaji hasil belajar siswa pada pembelajaran biologi materi Ekosistem dengan menggunakan media MGS (Monopoly Games Smart di MTs Al-Wahdah Sumber. (3 Untuk mengkaji respon siswa terhadap penggunaan media MGS (Monopoly Games Smart dalam pembelajaran biologi khususnya pada materi Ekosistem di Mts Al-Wahdah Sumber. Penelitian ini dilakukan di MTs Al-Wahdah dengan teknik pengumpulan data yang digunakan adalah instrumen tes (pre-test dan post-test untuk mengukur hasil belajar siswa, observasi untuk mengetahui aktivitas siswa dan angketuntuk mengetahui respon siswa terhadap media pembelajaran. Hasil penelitian menunjukan bahwa (1 berdasarkan hasil analisis observasi, aktivitas siswa meningkat setelah diterapkan media Monopoly Games Smart. (2 Hasil belajar siswa kelas eksperimen menggunakan media pembelajaran Monopoly Games Smart nilai rata-rata pretest sebesar 39, posttest 78 dan n-gain 0,62.. Terbukti dari hasil perhitungan uji T menggunakan SPSS 16 diperoleh nilai Sig. 0,000 < (0,05 yang berarti terdapat peningkatan hasil belajar biologi siswa. (3 berdasarkan hasil analisis angket mengenai respon siswa terhadap penerapan media hampir dari siswa (82% dengan kriteria sangat kuat, menyukai penerapan strategi pembelajaran Monopoly

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

    Gardi, Alessandro; Sabatini, Roberto; Ramasamy, Subramanian


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

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

    Shalkhauser, Mary Jo W.; Roche, Rigoberto


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

  16. Étude du comportement en roulement d'un pneu d'avion

    Kongo-Kondé, Ange; Rosu, Lulian; Lebon, Frédéric; Brardo, Olivier; Dévesa, Bernard


    International audience; Ce travail présente une méthode d'éléments finis pour la simulation du roulement d'un pneu d'avion. Le caractère incompressible des matériaux, les grandes transformations ainsi que le contact unilatéral avec frottement de Coulomb sont pris en compte. Le modèle numérique permettra d'estimer le torseur des efforts au contact pneu–sol sous des conditions critiques et extrêmes pour la sécurité de l'avion. Nous montrerons l'influence des paramètres de chargements et du déra...

  17. Cold Regions Logistic Supportability Testing of Electronic, Avionic and Communications Equipment.


    A18 887 COLD REGIONS LOGISTIC SUPPORTABILITY TESTING OF / AS ELECTRONIC AVIONIC AMD CO..IUI ANY T EST AND EVALUATION COMAND ABERDEEN PROVING GROUND...optimum durability and service life of materiel. (b) To eliminate field maintenance problems encountered in earlier design items. (c) For ease of...heat sensitive). 5.2.2 Analysis. Assess the impact of each supply support anomaly un- covered in relation to the test item. Include comments as to the

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

    Steffin, Morris


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

  19. Avionics/Control co-design for large flexible space structures


    In this paper, a multi-model H1 synthesis scheme for fixed-structure controller design is developed and applied to the attitude control of a highly flexible earth-observation satellite. The particularity of the proposed approach is that the decision variables optimized by the fixed-structure Hinfinity solver include the structured controller parameters but also some parameters which characterize the avionics. Furthermore the proposed control scheme can be very easily adapted to a new confi...

  20. Application of GLUT in SCADE Avionics Display Control Software Design%GLUT在基于SCADE航电显控软件设计中的应用

    傅亮; 潘明罕


      GLUT工具包独立于窗口系统,对窗口和事件的管理工作进行标准化和简化。本文介绍了GLUT程序框架的构建,解析了GLUT回调函数设计思想,阐述了SCADE模型驱动航电显控软件模型嵌入GLUT构架的构建步骤,实现了SCADE航电显控软件模型到Windows平台环境下实际应用程序的转换。%  GLUT toolkit is independent of window system, and the management of graphic windows and events is standardized and simplified by it. This paper introduces the construction of GLUT framework and analyzes the design idea of GLUT callback function, and it expounds construction steps of embedding models of SCADE model-driven avionics display control software in GLUT framework,. it is a successful conversion from models of SCADE avionics display control software to application on Windows platform.

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

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


    A paper discusses NEXUS, a common, next-generation avionics interconnect that is transparently compatible with wired, fiber-optic, and RF physical layers; provides a flexible, scalable, packet switched topology; is fault-tolerant with sub-microsecond detection/recovery latency; has scalable bandwidth from 1 Kbps to 10 Gbps; has guaranteed real-time determinism with sub-microsecond latency/jitter; has built-in testability; features low power consumption (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.

  2. Holocene millennium-scale climatic variations as recorded by Rb and Sr concentrations for the MGS1 stratigraphical segment of Milanggouwan section in the Salawusu River Valley of Southeast Mu Us Desert%萨拉乌苏河流域MGS1 Rb和Sr记录的全新世千年尺度气候变化

    牛东风; 李保生; 魏建国; 温小浩; 舒培仙; 司月君


    萨拉乌苏河流域米浪沟湾剖面全新世地层MGS1层段记录了11个由风成砂与河流相或湖沼相构成的沉积旋回。对该层段63个样品的Rb、Sr数据进行了分析,结果显示由沙丘砂至上覆河湖相Rb和Sr含量由低增高,而Rb/Sr比值的分布则显示出与Rb和Sr含量变化相反的趋势,三者与平均粒径Mz(f)的相关系数都在0.43以上。研究表明MGS1至少经历了11次冷干和11次暖湿的气候波动。米浪沟湾剖面MGS1记录的千年尺度气候波动既是对东亚季风环流演变历史的体现,同时也是对全球气候与环境变化的响应。%The MGS1 stratigraphical segment of Milanggouwan section is located in the Salawusu River Valley of southeast Mu Us Desert. The segment documents 11 sedimentary cycles consisting of aeolian facies and fluvial facies or lacustrine-swamp facies. Totally 63 samples were analyzed for rubidium (Rb) and strontium (Sr) concentrations. The results show that Rb and Sr concentrations increase as the sediments vary from aeolian facies to lacustrine-swamp facies, however, variation of the Rb/Sr ratios shows reversed trends in contrast to that of Rb and Sr concentrations. The line correlation coefficients of Rb and Sr concentrations and Rb/Sr ratios with mean grain size are all above 0.43. All these indicate that the MGS1 stratigraphic segment at least records 11 cold-dry and 11 warm-humid millennium-scale climatic oscillations, which represent the evolution history of East Asian monsoon circulation and show good correspondence to global climatic and environment variations.

  3. 综合化航空电子分区隔离的建模与设计方法%Partition modeling and design in integrated avionics

    李昕颖; 熊华钢


    With the development of integrated modular avionics, partition management has become a necessary technology. To solve the partition management problem under safety critical system constraint, through studying ARINC653 criterion, hierarchical partition architecture model was determined which implement partitioning between applications of different safety critical levels. To guarantee timing constraints and predictability of avionics, a two-level partition schedule model was proposed in which the operation system adopts round-robin scheduling strategy and each individual partition adopts rate monotonic priority scheduling strategy. In addition, for the sehedulable analysis problem of partition tasks, on the premise that fully guarantee real time characteristics of integrated modular avionics systems, a design method for partition critical parameters was developed. The least upper bounds of the system schedulable utilization for the method was derived and formally proved. Computer simulation results indicate this approach can be used to admit much more systems load,while guarantee real time properties.%分区技术是航空电子系统综合化模块化发展中不可缺少的技术.针对航空电子系统安全关键性的要求,基于ARINC653标准,提出了分层分区的体系结构模型,该模型实现了不同安全关键级别应用软件之间的隔离.为了满足航空电子系统强实时可预测性的约束,双层分区模型中系统层采用轮转调度策略,区间层采用单调速率调度策略.然后对分区任务进行可调度分析,在充分保证航空电子系统强实时的前提下,提出了分区关键参数的设计方法,并推导了最坏情况下的系统可调度利用率.计算机仿真结果表明,该方法在保证实时性的同时,能支持更多的系统负载,具有优越性.

  4. Analyzing Magnetic Field and Electrical Current Profiles of the Day Side and Terminator of Mars Using Data from Mars Global Surveyor (MGS)

    Fogle, A. L.; Ponce, N.; Fillingim, M. O.


    Mars does not have a global magnetic field, so the interplanetary magnetic field (IMF) can impact the upper atmosphere and induce currents in the Martian ionosphere. During aerobraking maneuvers, Mars Global Surveyor (MGS) made over 1000 passes through the Martian ionosphere. During the aerobraking phase, MGS measured the local magnetic field in the ionosphere. From measuring changes in the magnetic field, we can calculate the ionospheric currents. By only using measurements where the radial component of the magnetic field is zero and making some assumptions about the gradients in the magnetic field, we are allowed to classify data that meets those conditions as "good" data and calculate horizontal currents in the ionosphere. We focus on data taken over regions of Mars that had negligible crustal magnetic fields to simplify our analysis. The data being analyzed is observed at a maximum altitude of 250 kilometers with a solar zenith angle (SZA) range of 0 degrees to 50 degrees for the day side and 50 to 130 degrees for the terminator. For the day side of Mars, it was found that 24.06% of the data observed was usable data under the initial parameters that were set for "good" data. For the terminator, it was found that 32.08% of the data was usable. The currents that are computed using these "good" magnetic field profiles can give us insights into how the changing solar wind and interplanetary magnetic field can effect the upper atmosphere of mars. For example, induced currents can lead to Joule heating of the atmosphere potentially modifying the neutral dynamics.

  5. Avionics sensor simulation and prototype design workstation using COTS reconfigurable computing technology

    Falasco, James


    This paper reviews hardware and software solutions that allow for rapid prototyping of new or modified embedded avionics sensor designs, mission payloads and functional sub assemblies. We define reconfigurable computing in the context of being able to place various PMC modules depending upon mission scenarios onto a base SBC (Single Board Computer). This SBC could be either a distributed or shared memory architecture concept and have either two or four PPC7447 A/7448 processor clusters. In certain scenarios, various combinations of boards could be combined in order to provide a heterogeneous computing environment.

  6. Modelización computacional del ensayo de evacuación de emergencia de aviones de transporte

    Hedo Rodríguez, José Manuel


    Resumen En la explotación de aviones de transporte se presentan situaciones de riesgo en las que se necesita realizar una evacuación de emergencia, aunque afortunadamente sean cada vez menos. La eficacia de esta operación es crucial para salvar las vidas de los ocupantes. Para garantizar un cierto nivel de seguridad, la certificación de este tipo de aviones exige pasar con éxito el llamado ensayo de evacuación. Este consiste en la obtención del tiempo que tarda en evacuarse completamente el a...

  7. NextGen Avionics Roadmap Version 2.0


    extent. The FAA is working to develop an alternative position navigation and timing strategy to act as a back-up system (e.g. DME / DME /IRU...the na- ture of a TAV’s exotic fuel mixture and possibility for sen- sitive payloads, coupled with the TAV’s inherent kinetic energy/speed:  OI

  8. NextGen Avionics Roadmap, Version 1.2


    operators at remote locations. Cost and Benefit Considerations Costs to an aircraft operator, whether airline or military come in two forms -- capital... sense of the numbers and types of enablers that may be necessary to support operations that will be in- tegral to NextGen. Historical lead-in times...prediction information. Global Navigation Satellite System ( GNSS ), ADS-B Out, Aircraft Characteristic Database, Aircraft Wake Database, Wake

  9. Shuttle Communications and Tracking, Avionics, and Electromagnetic Compatibility

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


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

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

    Ottenstein, Laura; DeChristopher, Mike


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

  11. Model-Based Verification and Validation of Spacecraft Avionics

    Khan, Mohammed Omair


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

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

    Suk, Ho Kim


    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.

  13. Summer season variability of the north residual cap of Mars as observed by the Mars Global Surveyor Thermal Emission Spectrometer (MGS-TES)

    Calvin, W.M.; Titus, T.N.


    Previous observations have noted the change in albedo in a number of North Pole bright outliers and in the distribution of bright ice deposits between Mariner 9, Viking, and Mars Global Surveyor (MGS) data sets. Changes over the summer season as well as between regions at the same season (Ls) in different years have been observed. We used the bolometric albedo and brightness temperature channels of the Thermal Emission Spectrometer (TES) on the MGS spacecraft to monitor north polar residual ice cap variations between Mars years and within the summer season for three northern Martian summers between July 1999 and April 2003. Large-scale brightness variations are observed in four general areas: (1) the patchy outlying frost deposits from 90 to 270??E, 75 to 80??N; (2) the large "tail" below the Chasma Boreale and its associated plateau from 315 to 45??E, 80 to 85??N, that we call the "Boreale Tongue" and in Hyperboreae Undae; (3) the troughed terrain in the region from 0 to 120??E longitude (the lower right on a polar stereographic projection) we have called "Shackleton's Grooves" and (4) the unit mapped as residual ice in Olympia Planitia. We also note two areas which seem to persist as cool and bright throughout the summer and between Mars years. One is at the "source" of Chasma Boreale (???15??E, 85??N) dubbed "McMurdo", and the "Cool and Bright Anomaly (CABA)" noted by Kieffer and Titus 2001. TES Mapping of Mars' north seasonal cap. Icarus 154, 162-180] at ???330??E, 87??N called here "Vostok". Overall defrosting occurs early in the summer as the temperatures rise and then after the peak temperatures are reached (Ls???110) higher elevations and outlier bright deposits cold trap and re-accumulate new frost. Persistent bright areas are associated with either higher elevations or higher background albedos suggesting complex feedback mechanisms including cold-trapping of frost due to albedo and elevation effects, as well as influence of mesoscale atmospheric dynamics

  14. Summer season variability of the north residual cap of Mars as observed by the Mars Global Surveyor Thermal Emission Spectrometer (MGS-TES)

    Calvin, W. M.; Titus, T. N.


    Previous observations have noted the change in albedo in a number of North Pole bright outliers and in the distribution of bright ice deposits between Mariner 9, Viking, and Mars Global Surveyor (MGS) data sets. Changes over the summer season as well as between regions at the same season ( Ls) in different years have been observed. We used the bolometric albedo and brightness temperature channels of the Thermal Emission Spectrometer (TES) on the MGS spacecraft to monitor north polar residual ice cap variations between Mars years and within the summer season for three northern Martian summers between July 1999 and April 2003. Large-scale brightness variations are observed in four general areas: (1) the patchy outlying frost deposits from 90 to 270°E, 75 to 80°N; (2) the large "tail" below the Chasma Boreale and its associated plateau from 315 to 45°E, 80 to 85°N, that we call the "Boreale Tongue" and in Hyperboreae Undae; (3) the troughed terrain in the region from 0 to 120°E longitude (the lower right on a polar stereographic projection) we have called "Shackleton's Grooves" and (4) the unit mapped as residual ice in Olympia Planitia. We also note two areas which seem to persist as cool and bright throughout the summer and between Mars years. One is at the "source" of Chasma Boreale (˜15°E, 85°N) dubbed "McMurdo", and the "Cool and Bright Anomaly (CABA)" noted by Kieffer and Titus 2001. TES Mapping of Mars' north seasonal cap. Icarus 154, 162-180] at ˜330°E, 87°N called here "Vostok". Overall defrosting occurs early in the summer as the temperatures rise and then after the peak temperatures are reached ( Ls˜110) higher elevations and outlier bright deposits cold trap and re-accumulate new frost. Persistent bright areas are associated with either higher elevations or higher background albedos suggesting complex feedback mechanisms including cold-trapping of frost due to albedo and elevation effects, as well as influence of mesoscale atmospheric dynamics.

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

    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…

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

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


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

  17. Optimal energy management system implementation in power networks with multiple Microgrids by using multi-period imperialist competition

    Narges Parhizi


    Full Text Available Optimal energy management in systems based on multiple Microgrids (MG is a vital component to ensure the economic dispatch of generation resources. Energy management system (EMS can be employed to achieve the optimum utilization of resources, to reach the operational performance targets in the MGs as well as to control exchange power among them and with grid as well. In this regard, a double-layer control scheme (DLCS equipped with primary and secondary controllers are proposed in this paper. In primary control level, EMS is operating separately for each MG by considering the problem constraints and uncertainty of renewable resources by using Taguchi’s approach, power set-points of generation resources and possible shortage or surplus of power generation in the MGs. Then, the shortage or surplus generation of the MGs should be submitted to a central energy management system (CEMS at the secondary layer. In order to validate the proposed control structure, a case study including two MGs and a lumped load is simulated and optimized based on multi-period imperialist competition (MICA algorithm. Different scenarios are applied to evaluate the performance of the proposed DLCS. The obtained results clearly show that the proposed DLCS is effective for achieving optimal dispatch of generation resources in systems with multiple MGs. Furthermore, the proposed DLCS is able to control the performance of the MGs in interaction with the grid and with each other as well.

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


    masking shall not be currently considered but near t iearth line of might constraints shall be considered for ground jamnmers. A precomputed ( PEG like) ECM...of simulatcd deta : radar and iFF reports, navigation data, digital 0orn- municatlons information, electronic countermeasure information, and a number

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

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


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

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

    Wray, Richard B.


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

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



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

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


    les donn~es souvent contradictoires qui sont la base de lorentaton des efforts de d6veloppement dans cc domarne. Ces tendarices. ces conflits et ces dr...isation/recalagos Approche Gostion du vol *Communications (modes clair et brouill~s) -Identification - Gestion dos syst~mos avions (servitudes) *Interface H...omme/Systbme (IHS) * Gestion des pannos et des alarmes *Maintenance en ligno -Pr6paration/rbtstitution de mission *Conduites do fir Air/Air -Conduites

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

    Frost, Chad


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

  4. Integrating the Unmanned Aircraft System into the National Airspace System


    and the ground control system. The ground control system is comprised of several integrated components to include: avionics , fuel, navigation...accessed January 15, 2011). U.S. Army Unmanned Aircraft Systems Roadmap 2010-2035: Eyes of the Army. Fort Rucker, Ala .: U.S. Army Unmanned Aircraft

  5. A Three-Stage Optimal Approach for Power System Economic Dispatch Considering Microgrids

    Wei-Tzer Huang


    Full Text Available The inclusion of microgrids (MGs in power systems, especially distribution-substation-level MGs, significantly affects power systems because of the large volumes of import and export power flows. Consequently, power dispatch has become complicated, and finding an optimal solution is difficult. In this study, a three-stage optimal power dispatch model is proposed to solve such dispatch problems. In the proposed model, the entire power system is divided into two parts, namely, the main power grid and MGs. The optimal power dispatch problem is resolved on the basis of multi-area concepts. In stage I, the main power system economic dispatch (ED problem is solved by sensitive factors. In stage II, the optimal power dispatches of the local MGs are addressed via an improved direct search method. In stage III, the incremental linear models for the entire power system can be established on the basis of the solutions of the previous two stages and can be subjected to linear programming to determine the optimal reschedules from the original dispatch solutions. The proposed method is coded using Matlab and tested by utilizing an IEEE 14-bus test system to verify its feasibility and accuracy. Results demonstrated that the proposed approach can be used for the ED of power systems with MGs as virtual power plants.

  6. Space shuttle engineering and operations support. Orbiter to spacelab electrical power interface. Avionics system engineering

    Emmons, T. E.


    The results are presented of an investigation of the factors which affect the determination of Spacelab (S/L) minimum interface main dc voltage and available power from the orbiter. The dedicated fuel cell mode of powering the S/L is examined along with the minimum S/L interface voltage and available power using the predicted fuel cell power plant performance curves. The values obtained are slightly lower than current estimates and represent a more marginal operating condition than previously estimated.

  7. F/FB-111 Avionic Systems Career Ladder, AFSC 452X3



  8. Aircraft Avionics and Missile System Installation Cost Study. Volume 2. Appendices F and G.


    IND, ROD OF 6 0 0 0 0 .𔃻 N77032 YCA542r7’ 00 A C1741/APS-125 DUAL PULSE VTT CONPARATOR,MOD 6 1 2 2 0 77032 YCA542074 00 A C1459/05S125 DIGITAL DATA...UNIT 6 25 386 83063 E-2 1150032 Al A T-56 MATER INJECTION SYS INSTAL 1-2C 6 25 1175 83064 1-2 AIB5021 Al A IMPROVE ECCM CAPABILITY TRAC -A PRIM E-2C 6...650000 65 1000 15 100 " - MT. EST 0s9;I A/C TDI IXI TITLE LVL KIT$ QTY TOTBRS UNHRS MHRS 83164 1-2 AEIB5L� A1 B TRAC -A RADAR ANTENNA/8 CHANNEL

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

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

  10. Core Logistics Capability Policy Applied to USAF Combat Aircraft Avionics Software: A Systems Engineering Analysis


    cannot make a distinction between software maintenance and development” (Sharma, 2004). ISO/ IEC 12207 Software Lifecycle Processes offers a guide to...synopsis of ISO/ IEC 12207, Raghu Singh of the Federal Aviation Administration states “Whenever a software product needs modifications, the development...Sustainment for the F-35 Lightning II. (C. Johnstun, Ed.) Crosstalk: The Journal of Defense Software Engineering , 20 (12), 9-14. 130

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

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


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

  12. Convertisseur DC-DC isolé fort courant à fort rapport d'élévation pour l'avion plus électrique

    Brunello, Julien; FOREST, François; HUSELSTEIN, Jean-Jacques; ASFAUX, Pascal


    International audience; L'avion plus électrique est une cible de développement majeure chez les constructeurs aéronautiques. Cette évolution implique la conception de systèmes de conversion d'énergie électrique fiables, modulaires et performants, en particulier du point de vue de la puissance spécifique. Ces systèmes de conversion sont souvent couplés avec des systèmes de stockage d'énergie (type batterie) permettant dans certaines situations de rendre l'avion énergétiquement autonome grâce à...

  13. Multiple IMU system development, volume 1

    Landey, M.; Mckern, R.


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

  14. Using Expert Systems For Computational Tasks

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


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

  15. Faults in electronic equipment on board planes, due to upper atmosphere neutrons (10 to 20 km); Defauts sur les equipements electroniques a bord d`avions, dus aux neutrons de la haute atmosphere (10 a 20 km)

    Calvet, M.C. [Aerospatiale, 78 - Les Mureaux (France); Feuillatre, O. [Dassault Electronique, 92 - Saint-Cloud (France); Gaillard, R. [Nucletudes, 91 - Les Ulis (France)


    Until now, the effects of the space environment on the electronics of the avionic systems had never been taken into account: given the regions of the earth environment deemed critical, the altitudes of the planes were too low and the electronic components were not integrated enough to become sensitive to the environment. The situation will change with the new generations of planes for which the altitudes become higher than 10 km and on which are integrated submicron components. This paper gives the present state of knowledge of the atmospheric environment and its effects on the components, the available models for events estimation and proposes some disposals to prevent atmospheric environment effects on future planes. (authors). 14 refs., 9 figs., 2 tabs.

  16. Advanced aircraft electric power system

    Segrest, J.D.


    The role of electric energy in both military and commercial aircraft increases in importance with every advancement in airframe performance and avionic technology. Microcircuits and volatile memories impact power continuity and quality, digital flight control and stability augmentation require high reliability. This paper presents the system concept, hardware development and status of the Navy program.

  17. 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.

    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…

  18. Intelligent Control for a DC Micro-Grid System

    Martino, Michele; Quiñones, Yamshid Farhat; Raboni, Pietro


    This paper presents the dynamic response of a DC–micro-grid (DC-MG) controlled in master-slave mode. The benefits of the micro-grids (MGs) are the low cost in terms of power electronics converters and the high reliability and quality, even in case of loss connection to the transmission system. A DC...

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


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

  20. On Board Data Acquisition System with Intelligent Transducers for Unmanned Aerial Vehicles

    Rochala, Zdzisław


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

  1. Design of a smart optically controlled high-power switch for fly-by-light motor actuation systems

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


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

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

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


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

  3. Requirements-Based Conformance Testing of ARINC 653 Real-Time Operating Systems

    Maksimov, Andrey


    Requirements-based testing is emphasized in avionics certification documents because this strategy has been found to be the most effective at revealing errors. This paper describes the unified requirements-based approach to the creation of conformance test suites for mission-critical systems. The approach uses formal machine-readable specifications of requirements and finite state machine model for test sequences generation on-the-fly. The paper also presents the test system for automated test generation for ARINC 653 services built on this approach. Possible application of the presented approach to various areas of avionics embedded systems testing is discussed.

  4. Prediction de l’Eclatement Tourbillonnaire sur les Ailes Delta d’Avions Militaires (CFD Prediction of Vortex Breakdown on Delta Wings for Military Aircraft)


    visualisation de la pression totale tirée du calcul k-ε en lois de paroi. La croissance brusque des cœurs tourbillonnaires dès l’apex est le signe d’un...d’avions militaires. REMERCIEMENTS Ces travaux ont été réalisés dans le cadre d’études sous financement du SPAé. REFERENCES [1] Caractérisation et

  5. Design Methodologies for Secure Embedded Systems

    Biedermann, Alexander


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

  6. Neutron Radiation Tolerance of Two Benchmark Thiophene-Based Conjugated Polymers: the Importance of Crystallinity for Organic Avionics

    Paternò, G. M.; Robbiano, V.; Fraser, K. J.; Frost, C.; García Sakai, V.; Cacialli, F.


    Aviation and space applications can benefit significantly from lightweight organic electronics, now spanning from displays to logics, because of the vital importance of minimising payload (size and mass). It is thus crucial to assess the damage caused to such materials by cosmic rays and neutrons, which pose a variety of hazards through atomic displacements following neutron-nucleus collisions. Here we report the first study of the neutron radiation tolerance of two poly(thiophene)s-based organic semiconductors: poly(3-hexylthiophene-2,5-diyl), P3HT, and the liquid-crystalline poly(2,5-bis (3-tetradecylthiophen-2-yl)thieno[3,2-b]thiophene), PBTTT. We combine spectroscopic investigations with characterisation of intrinsic charge mobility to show that PBTTT exhibits significantly higher tolerance than P3HT. We explain this in terms of a superior chemical, structural and conformational stability of PBTTT, which can be ascribed to its higher crystallinity, in turn induced by a combination of molecular design features. Our approach can be used to develop design strategies for better neutron radiation-tolerant materials, thus paving the way for organic semiconductors to enter avionics and space applications. PMID:28112195

  7. Neutron Radiation Tolerance of Two Benchmark Thiophene-Based Conjugated Polymers: the Importance of Crystallinity for Organic Avionics

    Paternò, G. M.; Robbiano, V.; Fraser, K. J.; Frost, C.; García Sakai, V.; Cacialli, F.


    Aviation and space applications can benefit significantly from lightweight organic electronics, now spanning from displays to logics, because of the vital importance of minimising payload (size and mass). It is thus crucial to assess the damage caused to such materials by cosmic rays and neutrons, which pose a variety of hazards through atomic displacements following neutron-nucleus collisions. Here we report the first study of the neutron radiation tolerance of two poly(thiophene)s-based organic semiconductors: poly(3-hexylthiophene-2,5-diyl), P3HT, and the liquid-crystalline poly(2,5-bis (3-tetradecylthiophen-2-yl)thieno[3,2-b]thiophene), PBTTT. We combine spectroscopic investigations with characterisation of intrinsic charge mobility to show that PBTTT exhibits significantly higher tolerance than P3HT. We explain this in terms of a superior chemical, structural and conformational stability of PBTTT, which can be ascribed to its higher crystallinity, in turn induced by a combination of molecular design features. Our approach can be used to develop design strategies for better neutron radiation-tolerant materials, thus paving the way for organic semiconductors to enter avionics and space applications.

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

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


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

  9. Applications of Miniaturized Atomic Magnetic Sensors in Military Systems


    exercising flight operations ( brushless DC motor running, tail avionics actuated, telemetry systems transmitting). We utilized a simple linear model to...80021 USA ABSTRACT A new generation of miniaturized ultra-high sensitivity atomic magnetometers is being developed and integrated into military...low frequency magnetometry are investigated through preliminary experimental data in addition to modeling and simulations. In particular, we discuss

  10. Electronics system design techniques for safety critical applications

    Sterpone, Luca


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

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

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


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

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



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

  13. Schedulability and Memory Interference Analysis of Multicore Preemptive Real-time Systems

    Boudjadar, Jalil; Nadjm-Tehrani, Simin

    Today’s embedded systems demand increasing computing power to accommodate the ever-growing software functionality. Automotive and avionic systems aim to leverage the high performance capabilities of multicore platforms, but are faced with challenges with respect to temporal predictability...

  14. AGARD Flight Test Techniques Series. Volume 11. The Testing of Fixed Wing Tanker and Receiver Aircraft to Establish Their Air-To-Air Refuelling Capabilities (Les Essais Pratiques sur les Avions Ravitailleurs et Ravitailles afin de Determiner leurs Capacites de Ravitaillement en Vol).


    doivent etre pris en compte lors de la planification des essais de ravitaillement en vol d’un nouvel avion-citerne ou d’un nouvel avion ä ravitailler...en vue de son homologation. Le lecteur est suppose etre familier avec la pratique courante de ravitaillement en vol et le materiel employes dans

  15. Improving manual skills in persons with disabilities (PWD) through a multimodal assistance system.

    Covarrubias, Mario; Gatti, Elia; Bordegoni, Monica; Cugini, Umberto; Mansutti, Alessandro


    In this research work, we present a Multimodal Guidance System (MGS) whose aim is to provide dynamic assistance to persons with disabilities (PWD) while performing manual activities such as drawing, coloring in and foam-cutting tasks. The MGS provides robotic assistance in the execution of 2D tasks through haptic and sound interactions. Haptic technology provides the virtual path of 2D shapes through the point-based approach, while sound technology provides audio feedback inputs related to the hand's velocity while sketching and filling or cutting operations. By combining this Multimodal System with the haptic assistance, we have created a new approach with possible applications to such diverse fields as physical rehabilitation, scientific investigation of sensorimotor learning and assessment of hand movements in PWD. The MGS has been tested by people with specific disorders affecting coordination, such as Down syndrome and developmental disabilities, under the supervision of their teachers and care assistants inside their learning environment. A Graphic User Interface has been designed for teachers and care assistants in order to provide training during the test sessions. Our results provide conclusive evidence that the effect of using the MGS increases the accuracy in the tasks operations. The Multimodal Guidance System (MGS) is an interface that offers haptic and sound feedback while performing manual tasks. Several studies demonstrated that the haptic guidance systems can help people in recovering cognitive function at different levels of complexity and impairment. The applications supported by our device could also have an important role in supporting physical therapist and cognitive psychologist in helping patients to recover motor and visuo-spatial abilities.

  16. The development of a range of small mechanical cryocoolers for space and avionic applications

    Hocking, Barry


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

  17. Diseño de una planta de reciclaje de los productos de deshielo para aviones en el Aeropuerto Adolfo Suárez

    Fuentes Román, Juan Diego


    El proceso para el deshielo de los aviones en temporada de invierno en el Aeropuerto Adolfo Suárez de Madrid consiste en la aplicación de una mezcla de propilenglicol, agua y aditivos (sufractantes y anticorrosivos) sobre la superficie del avión a descongelar mientras está en la pista de aterrizaje. Una parte de estas mezclas cae al suelo junto con el agua del hielo fundido, lo que conlleva una contaminación al medio, a parte de la pérdida de propilenglicol que puede ser reu...

  18. Outcomes of different Class II treatments : Comparisons using the American Board of Orthodontics Model Grading System.

    Akinci Cansunar, Hatice; Uysal, Tancan


    The aim of this study was to evaluate the clinical outcomes of three different Class II treatment modalities followed by fixed orthodontic therapy, using the American Board of Orthodontics Model Grading System (ABO-MGS). As a retrospective study, files of patients treated at postgraduate orthodontic  clinics in different cities in Turkey was randomly selected. From 1684 posttreatment records, 669 patients were divided into three groups: 269 patients treated with extraction of two upper premolars, 198 patients treated with cervical headgear, and 202 patients treated with functional appliances. All the cases were evaluated by one researcher using ABO-MGS. The χ (2), Z test, and multivariate analysis of variance were used for statistical evaluation (p < 0.05). No significant differences were found among the groups in buccolingual inclination, overjet, occlusal relationship, and root angulation. However, there were significant differences in alignment, marginal ridge height, occlusal contact, interproximal contact measurements, and overall MGS average scores. The mean treatment time between the extraction and functional appliance groups was significantly different (p = 0.017). According to total ABO-MGS scores, headgear treatment had better results than functional appliances. The headgear group had better tooth alignment than the extraction group. Headgear treatment resulted in better occlusal contacts than the functional appliances and had lower average scores for interproximal contact measurements. Functional appliances had the worst average scores for marginal ridge height. Finally, the functional appliance group had the longest treatment times.

  19. SIFT - Multiprocessor architecture for Software Implemented Fault Tolerance flight control and avionics computers

    Forman, P.; Moses, K.


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

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


    does not. Rubio, Diaz, Martin and Puente (2004) evaluated several such measures of workload for intrusiveness, sensitivity, validity, diagnosticity...A159080). Atlanta, GA: Georgia Institute of Technology, Center for Human-Machine Systems Research. Rubio, S., Díaz, E., Martín, J., & Puente , J. M

  1. The value of the 2005 International Society of Urological Pathology (ISUP) modified Gleason grading system as a predictor of biochemical recurrence after radical prostatectomy.

    Billis, Athanase; Quintal, Maisa M Q; Meirelles, Luciana; Freitas, Leandro L L; Costa, Larissa B E; Bonfitto, João F L; Diniz, Betina L; Poletto, Paola H; Magna, Luís A; Ferreira, Ubirajara


    To compare time and risk to biochemical recurrence (BR) after radical prostatectomy of two chronologically different groups of patients using the standard and the modified Gleason system (MGS). Cohort 1 comprised biopsies of 197 patients graded according to the standard Gleason system (SGS) in the period 1997/2004, and cohort 2, 176 biopsies graded according to the modified system in the period 2005/2011. Time to BR was analyzed with the Kaplan-Meier product-limit analysis and prediction of shorter time to recurrence using univariate and multivariate Cox proportional hazards model. Patients in cohort 2 reflected time-related changes: striking increase in clinical stage T1c, systematic use of extended biopsies, and lower percentage of total length of cancer in millimeter in all cores. The MGS used in cohort 2 showed fewer biopsies with Gleason score ≤ 6 and more biopsies of the intermediate Gleason score 7. Time to BR using the Kaplan-Meier curves showed statistical significance using the MGS in cohort 2, but not the SGS in cohort 1. Only the MGS predicted shorter time to BR on univariate analysis and on multivariate analysis was an independent predictor. The results favor that the 2005 International Society of Urological Pathology modified system is a refinement of the Gleason grading and valuable for contemporary clinical practice.

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


    devices that convey distributed sensations, rather than devices that provide vector force haptic feedback.) Tactile displays located on the human...stations [124]. This evaluation assessed both a conventional cockpit (F-16/F-15 type cockpit displays) and a virtually- augmented cockpit ( HMD /T system... realities , we had extensive interactions with NATO pilots from several nations. We interviewed pilots at our formal meetings; we asked them fill out

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

    Wright, Theodore W.


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

  4. ATD-1 Avionics Phase 2 Flight Test: Flight Test Operations and Saftey Report (FTOSR)

    Boyle, Dan; Rein-Weston, Karl; Berckefeldt, Rick; Eggling, Helmuth; Stankiewicz, Craig; Silverman, George


    The Air Traffic Management Technology Demonstration-1 (ATD-1) is a major applied research and development activity of NASA's Airspace Operations and Safety Program (AOSP). The demonstration is the first of an envisioned series of Air Traffic Management (ATM) Technology Demonstration sub-projects that will demonstrate innovative NASA technologies that have attained a sufficient level of maturity to merit more in-depth research and evaluation at the system level in relevant environments.

  5. Error Propagation in a System Model

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


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

  6. Stochastic P systems and the simulation of biochemical processes with dynamic compartments.

    Spicher, Antoine; Michel, Olivier; Cieslak, Mikolaj; Giavitto, Jean-Louis; Prusinkiewicz, Przemyslaw


    We introduce a sequential rewriting strategy for P systems based on Gillespie's stochastic simulation algorithm, and show that the resulting formalism of stochastic P systems makes it possible to simulate biochemical processes in dynamically changing, nested compartments. Stochastic P systems have been implemented using the spatially explicit programming language MGS. Implementation examples include models of the Lotka-Volterra auto-catalytic system, and the life cycle of the Semliki Forest virus.

  7. AGARD Flight Test Technique Series. Volume 15. Introduction to Avionics Flight Test (Introduction aux Essais des Systemes D’armes)


    features and thus angular. As a simplistic example, a the signal to noise characteristics of picket fence could be modeled with a the sensor can be...Volume Plans, by Anon., 1992. 12, 1980. 66. U. S. Navy Report No. 533, 54. Smith, Sidney L. and Mosier, Jane Anthropometry of Naval Aviators, N

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


    adj.) = . 9313 SEE = 74 Mean = 209.85 Range = mhrs_100: 1.14 to 817 hw cac; 21 to 262 cabin: 0 to 117 cabrem: 0 to 339.6 IV-25 This CER applies to cases...300 gallon drop tank and the ALQ-99 Tactical Jamming Pod, the EA -6B did not have an ordnance carriage capability. This l.mited both training and...installation of the enhanced digital scan converter group (EDSCG). GFE EDSCG are required, consisting of: 1 ea - Signa. Data Converter, Intra Target

  9. Identification and Reduction of Bottlenecks Concerning MICAP Re-Supply of F-16 Weapons System Avionics Line Replaceable Units


    developed by Eliyahu Goldratt ], is a continual improvement philosophy that focuses on the identification and management of constraints for organizational...FedEx U.S. Government Contract Services Guide. August 1996. 51 Goldratt , Eliyahu M. The Goal: A Process of Ongoing Improvement. Second Edition. North

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

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


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

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

    Chin, Jeffrey; Roberts, Anthony; McNatt, Jeremiah


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

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

    Charette, Emilie

    composites panels were studied. The second study focused on the analysis of hygrothermal influence on the adhesive and the composite sandwich panels taken separately. Humidity and temperature can have an important effect on the constitutive materials, it is therefore important to know their influence. Finally, the third part deals with the influence of hygrothermal aging on a structure combining all the different materials. Sample panels including fixing zones (insert and resin) were made at the industrial partner's facility according to the industrial procedure. Subsequently, the samples have undergone an accelerated aging. By using deflectometry system, changes in local curvatures with respect to the aging conditions were observed. A correlation between the material characterization results, the aging effects and the surface defect gravity was performed to evaluate the sources and the occurrence of defects. Recommendations have also been made to ensure the project continuity. This project, carried out in an industrial context with the collaboration of Centre de Recherche Industrielle du Quebec ( CRIQ), 3M Canada and the Chaire de recherche sur les composites hautes performances (CCHP) of the department of mechanical engineering of Ecole Polytechnique de Montreal, highlights the importance of the choice of methods and materials in the manufacturing of composite structures.

  13. International Space Station Systems Engineering. Case Study


    lack of system configuration.  Lithium thionyl chloride batteries were brought on board over the objection of other ISS partners.  Russian ground...meters (13.5 feet wide) at its widest point. It has an operational lifetime of at least 15 years. Its solar arrays and six nickel- cadmium batteries can...during periodic maintenance. The Equipment airlock has two racks, one for avionics, and the other for cabin air. Batteries , power tools and other

  14. Development of a broadband and squint-free Ku-band phased array antenna system for airborne satellite communications

    Marpaung, D.A.I.; Roeloffzen, C.G.H.; Beeker, W.P.; Beeker, Willem; Noharet, Bertrand; Verpoorte, Jaco; Baggen, Rens

    Novel avionic communication systems are required for various purposes, for example to increase the flight safety and operational integrity as well as to enhance the quality of service to passengers on board. To serve these purposes, a key technology that is essential to be developed is an antenna

  15. Avionic Radome Materials


    UK Dr S.Bomar, Main Contributor Georgia Institute of Technology, Atlanta, USA Dr O.Tornani Aeritalia- Centro Elettronico Avio - Torino, Italy Mr A.Cohen...avoid cracking during sintering has been identified. A second fabrication approach is to slip-cast the skins, machine comercial foam blocks to the

  16. Integrated Circuits for Avionics


    Filters A linear phase filter is one with a phase shift which is a linear function of frequency resulting in a constant time delay for all frequency...components. For a linear phase filter , the coefficients are symmetrical which permits a realization that is more efficient than the direct form. Since h(i...h(N- I -i), the implementation of a linear phase filter can be obtained as shown in Fig. 2.3. By taking advantage of the symmetry of coefficients

  17. Avionics Design for Reliability


    Consultant P.O. Box 181, Hazelwood. Missouri 63042, U.S.A. soup ""•.• • CONTENTS Page LIST OF SPEAKERS iii INTRODUCTION AND OVERVIEW-RELIABILITY UNDER... primordial , d’autant plus quo dans co cam ia procg- dure do st~lection en fiabilitg eat assez peu efficaco. La ripartition des pannes suit

  18. Software for Avionics.


    aorte qu’A chaque pas- sage du programme devant on tel point un signal soft 6mis vera le contr8leur pour que celul -ci s’assure que l’ftat courant du...faire 6voluer celul -ci en conagiquence. 11 ne dapend bien entendu que do type de moda le utilisfi et non de chaque, r~alisation. 4.3. 1hemple 11 eat

  19. Avionics Corrosion Control Study


    found at seacoast (harsn) environnents is the most destructive. Differences in electrolte concentration and oxygen concentration promote corrosion...against corrosion by acting as moisture and gas barriers. CMCVIT B0.4ID *COATINGS Polyurethane’s, cprxies, silicones, and polystyrenes are the most

  20. 改进的航电网络模型仿真与分析%Improved Model of Avionics Network Simulation and Analysis

    王慧文; 张延园; 林奕; 贾鑫


    研究了光纤通道技术的应用,使用OPNET建立了基于光纤通道的航电网络,并且按照协议标准建立了终端节点和交换机节点的有限状态机模型.交换机使用组合输入交叉排队(Combined Input-Crosspoint Queueing,CICQ)结构,在输入端口和输出端口使用差值轮询调度( Deficit Round Robin,DRR)算法,然后使用OPNET进行仿真,分析了网络的端到端延迟和吞吐量.结果显示在航电网络中,使用DRR调度算法,能够显著降低数据包的端到端延迟,满足一定的实时性,提高网络的吞吐量,表明此模型适合航电网络.%The application of fiber channel was studied, a Fiber Channel-based Avionics Network was established by OPNET, according to protocol standards the finite state machine models of terminal nodes and switching node were established. The switch structure was CICQ, using DRR algorithm in input and output ports. Then the network was simulated by OPNET, end to end delay and network throughout were studied. The results show that using the DRR scheduling algorithm can reduce end to end packet delay, meet real time request, increase network throughout, so this model is suitable for avionics network.

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


    blt d’Informations, s£curit£). La gestlon du bus nunSrique est assur^e par le calculateur principal. Celul -cl pent gtre d6doubl§ pour des raisons de...gSnSrer, un blnalre absolu, c’est-ä-dire un programme dlrectement chargeable dans le calculateur. L» meilleur niveau de r6cup£ration est celul qul...beaucoup plus fälble que celul du developpement de 1’application mire. Cependant, lorsqu’on arrive au nlveau du detail, la situation n’est pas aussi

  2. Energy storage systems impact on the short-term frequency stability of distributed autonomous microgrids, an analysis using aggregate models

    Serban, Ioan; Teodorescu, Remus; Marinescu, Corneliu


    of storing and releasing energy when required by the system. Therefore the need of boosting the MG power reserves by adding energy storage systems is often a requirement. The study highlights the improvement in the MG short-term frequency stability brought by an original BESS control structure enhanced......This study analyses the integration impact of battery energy storage systems (BESSs) on the short-term frequency control in autonomous microgrids (MGs). Short-term frequency stability relates with the primary or speed control level, as defined in the regulations of the classical grids. The focus...... is on autonomous MGs that dynamically behave similarly to the classical power systems. This is the systems case with classical distributed generators (DGs), but which can also contain renewable energy sources (RESs) in a certain penetration level. During MG islanded operation, the local generators take over most...

  3. Optimal sizing of energy storage system for microgrids

    Babak Mozafari; Sirus Mohammadi


    Microgrids (MGs) are Low Voltage distribution networks comprising various distributed generators (DG), storage devices and controllable loads that can operate either interconnected or isolated from the main distribution grid as a controlled entity. Energy storage system (ESS) is a vital part of an MG. In this paper, a methodology is proposed for the optimal allocation and economic analysis of ESS in MGs on the basis of net present value (NPV). As the optimal operation of an MG strongly depends on the arrangement and allocation of its ESS, economic operation strategies and optimal allocation methods of the ESS devices are required for the MG. Self-adaptive Bee Swarm Optimization (SBSO) algorithm is applied to optimize the operation strategies and capacities of ESS in MGs in order to find maximal NPV, the generation schedule of ESS and distributed generation sources. This paper is to suggest, among those available ESS, the optimal sizes and types of them and their optimal arrangement, such that the total NPV achieved during the system operational lifetime period is maximized. After introducing the methodology, a case study is presented for illustration.

  4. Aircraft Survivability: Unmanned Aircraft Systems Survivability. Fall 2008


    metadata to GCS and OSRVT manpack. 3. Advance pilot vehicle interface ( PVI ) with display that enables the selection of multiple UAS’ video/metadata...Interface Panel (VIP) and VUIT Power Panel (VPP), allowing for PVI for the Apache VUIT-2 system. The Experimental Fabrication Branch fabricated all...Converter Thermite Video Splitter Amp Figure 6 VUIT-2 Interface Power System Components Right Aft Avionics Assembly Cockpit PVI Assembly VIP KU VPP RCVR

  5. Synthesis from Design Requirements of a Hybrid System for Transport Aircraft Longitudinal Control. Volume 2

    Hynes, Charles S.; Hardy, Gordon H.; Sherry, Lance


    Volume I of this report presents a new method for synthesizing hybrid systems directly from desi gn requirements, and applies the method to design of a hybrid system for longitudinal control of transport aircraft. The resulting system satisfies general requirement for safety and effectiveness specified a priori, enabling formal validation to be achieved. Volume II contains seven appendices intended to make the report accessible to readers with backgrounds in human factors, flight dynamics and control, and formal logic. Major design goals are (1) system design integrity based on proof of correctness at the design level, (2) significant simplification and cost reduction in system development and certification, and (3) improved operational efficiency, with significant alleviation of human-factors problems encountered by pilots in current transport aircraft. This report provides for the first time a firm technical basis for criteria governing design and certification of avionic systems for transport aircraft. It should be of primary interest to designers of next-generation avionic systems.

  6. Design and implementation of a GPS-aided inertial navigation system for a helicopter UAV

    Kastelan, David R.

    Helicopter unmanned aerial vehicles (UAVs) benefit from vertical takeoff and landing, hover, low-speed, and cruising flight capabilities. This versatility has the expense of nonlinear, unstable, and underactuated system dynamics. These challenges and numerous potential applications make the helicopter UAV an interesting testbed for nonlinear control. A platform for such development has been established in the Applied Nonlinear Controls Lab (ANCL). A miniature helicopter was augmented with a manual/autonomous takeover system and the ANCL Avionics. This payload contains a global positioning system (GPS) receiver, inertial sensors, and communications and computing hardware. Allan variance analysis of inertial sensor data enabled the derivation of a GPS-aided inertial navigation system that was implemented on the ANCL Avionics. This extended Kalman filter (EKF)-based algorithm estimates vehicle position, velocity, and attitude necessary for system identification tasks and control system feedback. Performance validation of this algorithm was demonstrated in simulation and in experimental ground and flight tests.

  7. Automated Cooperative Trajectories for a More Efficient and Responsive Air Transportation System

    Hanson, Curt


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

  8. Autonomous precision approach and landing system (APALS)

    Dieffenbach, Otto W.


    The APALSTM system is a precision approach and landing system designed to enable low visibility landings at many more airports than is now possible. It is an autonomous navigation system which uses standard avionics equipment to determine the aircraft position and altitude with respect to unique features over which the aircraft flies. The primary measurement is made with the aircraft's weather radar and provides the range and range rate information necessary to update the precision navigation system. The system makes use of stored terrain map data as references for map matching with Synthetic Aperture Radar maps.

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

    宋丽茹; 周立; 何锋; 熊华钢


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

  10. Flexible alternatives to constant frequency systems

    Stewart-Wilson, John

    The use of hybrid systems in which variable frequency is used as generated, with a proportion being converted to constant frequency by electronic conversion, is examined as a flexible alternative to constant frequency systems. Here, some practical solutions to the technical issues raised by adopting the more flexible approach to electrical system generation are presented. In particular, attention is given to the frequency ranges used, impact on aircraft equipment, motor-driven equipment, transformer rectifier units, lighting, and avionics. The discussion also covers fan-assisted galley ovens, system architecture, special airworthiness requirements, and power quality.

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

    Dunn, William; Garrett, Kimberly S.


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

  12. Operations management system

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


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

  13. Flight Guidance System Requirements Specification

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


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

  14. Vehicle health management for guidance, navigation and control systems

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


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

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


    3ABR322X2C is 98 days; and course 3ABR404X1 is 73 days in duration. The A- and C-shred attend a 226-hour G3AQR32020-005 Electronics Principles Course...The 404X1 receive electronics principles incorporated into their regular curriculum for a total of 183 hours. Successful completion of the tech school... Electronics Principles Inventory (EPI) was recently completed which included the 322X2A AFSC. The goal of an EPI is to obtain information on percent

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


    specifically to meet this requiremnenL 4.2.2. Evaluation of Current Procedures. leelofinterpeability i tues aciebed oreq if an effective Ergonomi , The...include 6.2.6. In-Flight Ergonomi Isue routes, timings, IP, fuel load etc. If a degree of re planning is to be carried out in flight. additional 6-26.1

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

    Goclowski, John C.; And Others

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

  18. Copilot: Monitoring Embedded Systems

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


    Runtime verification (RV) is a natural fit for ultra-critical systems, where correctness is imperative. In ultra-critical systems, even if the software is fault-free, because of the inherent unreliability of commodity hardware and the adversity of operational environments, processing units (and their hosted software) are replicated, and fault-tolerant algorithms are used to compare the outputs. We investigate both software monitoring in distributed fault-tolerant systems, as well as implementing fault-tolerance mechanisms using RV techniques. We describe the Copilot language and compiler, specifically designed for generating monitors for distributed, hard real-time systems. We also describe two case-studies in which we generated Copilot monitors in avionics systems.

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



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

    黄金; 许渤; 凌云; 邱昆


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

  1. Geographic Information Systems and Martian Data: Compatibility and Analysis

    Jones, Jennifer L.


    Planning future landed Mars missions depends on accurate, informed data. This research has created and used spatially referenced instrument data from NASA missions such as the Thermal Emission Imaging System (THEMIS) on the Mars Odyssey Orbiter and the Mars Orbital Camera (MOC) on the Mars Global Surveyor (MGS) Orbiter. Creating spatially referenced data enables its use in Geographic Information Systems (GIS) such as ArcGIS. It has then been possible to integrate this spatially referenced data with global base maps and build and populate location based databases that are easy to access.

  2. Advanced integrated enhanced vision systems

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


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

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

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


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

  4. Vol en formation sans formation: contrôle et planification pour le vol en formation des avions sans pilote


    This thesis presents the study and the implementation of a system that manages autonomously the configuration of a formation of unmanned aerial vehicles, or UAVs. The purposes are to improve the safety and the efficiency of a group of military UAVs, and to fill the gap between mission planning layers and formation control layers. Formation flight is particularly suited for military applications in hostile environments, that require synchronizations on target arrivals or mutual support for jam...

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


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

  6. Integrated Test Bed Facility

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

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

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


    NASA/Marshall Space Flight Center (MSFC) is continually looking for ways to reduce the costs and schedule and minimize the technical risks during the development of microgravity programs. One of the more prominent ways to minimize the cost and schedule is to use off-the-shelf hardware (OTS). However, the use of OTS often increases the risk. This paper addresses relevant factors considered during the selection and utilization of commercial off-the-shelf (COTS) flight computer processing equipment for the control of space station microgravity experiments. The paper will also discuss how to minimize the technical risks when using COTS processing hardware. Two microgravity experiments for which the COTS processing equipment is being evaluated for are the Equiaxed Dendritic Solidification Experiment (EDSE) and the Self-diffusion in Liquid Elements (SDLE) experiment. Since MSFC is the lead center for Microgravity research, EDSE and SDLE processor selection will be closely watched by other experiments that are being designed to meet payload carrier requirements. This includes the payload carriers planned for the International Space Station (ISS). The purpose of EDSE is to continue to investigate microstructural evolution of, and thermal interactions between multiple dendrites growing under diffusion controlled conditions. The purpose of SDLE is to determine accurate self-diffusivity data as a function of temperature for liquid elements selected as representative of class-like structures. In 1999 MSFC initiated a Center Director's Discretionary Fund (CDDF) effort to investigate and determine the optimal commercial data bus architecture that could lead to faster, better, and lower cost data acquisition systems for the control of microgravity experiments. As part of this effort various commercial data acquisition systems were acquired and evaluated. This included equipment with various form factors, (3U, 6U, others) and equipment that utilized various bus structures, (VME

  8. Joint Integrated Avionics Working Group (JIAWG) Object-Oriented Domain Analysis Method (JODA). Version 3.1.


    describing how, when, where, and why to select options, services, and instances. (Rationale is necessary when the reuser must select between options in the...Traceability defines a road map for the reuser during Applications Engineering. 2.2 Applications Engineering For each system that is constructed using reuse...the reuser in understanding the domain is all important. CMU/SEI-92-SR-3 21 Relevant Domain Dmi 3.1 Preare o i om xIai DeleDefin ito domain edomain

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

    Pollender-Moreau, Olivier

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

  10. Plan for the Characterization of HIRF Effects on a Fault-Tolerant Computer Communication System

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


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

  11. High-confidence software for safety-critical process-control systems

    Bastani, F.B. [Univ. of Houston, TX (United States)


    Software for safety-critical systems, such as nuclear power plant control systems; avionic systems; and medical, defense, and manufacturing systems, must be highly reliable because failures can have catastrophic consequences. While existing methods, such as formal techniques, testing, and fault-tolerant software, can significantly enhance software reliability, they have some limitations in achieving ultrahigh reliability requirements. Formal methods are not able to cope with specification faults, testing is not cost-effective for high-assurance systems, and fault-tolerant software based on diverse designs is susceptible to common-mode failures.

  12. Production of Reliable Flight Crucial Software: Validation Methods Research for Fault Tolerant Avionics and Control Systems Sub-Working Group Meeting

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


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

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


    a computer. Many of these come frcm the need for large offchip RAMs or ROMs for the microstore, and the buffer circuits needed to repower the chip set...demanding comparable applications now exist in the commercial market. These include robotics and computerized tomography. Military MCs are also built in

  14. Proceedings Papers of the AFSC (Air Force Systems Command) Avionics Standardization Conference (2nd) Held at Dayton, Ohio on 30 November-2 December 1982. Volume 1.


    Computers, Dr. Clive D. Leedham, Delco Electronics Division, General Motors Corporation 0 The Use of Computer ISA and Software Standards at 447...Carolyn, 39 Lane, J. H., 405 Garcia, Edwin M., 479 Lang, P. H., 93 Geyer, David W., 659 Lautner, D. E., 111, 123 Geyer, Manvel, 447 Leedham, Clive 0., 445... Barker , 󈧔-Bit Radiation-Hard Emulating Computer, Proc. IEEE NAECON, May 1981. MULTIBUS"’ is a trademark of Intel Corporation. This paper copyright

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


    Government procurement operacion , che united States Government thereby incurs no responsibility nor any obligation w atsoever; and the fact that the...layout of data can be explicitly defined in JOVIAL and complex tables of data can be defined to represent vectors, matrices , arrays, etc. J73 permits

  16. Aging Aircraft Fleets: Structural and Other Subsystem Aspects (le Vieillissement des flottes d’avions militaires : aspects structures et autres sous-systemes)


    disbonding between the face sheets and honeycomb core. In addition, core buckling is seen. Figure 11. Typical Impact Damage in Sandwich Structure with...significant research and development efforts currently underway in the area of nondestructive evaluation of aging aircraft . NASA LaRC and several...composite, sandwich construction) 2. Type of structural component to be repaired (skin, spar, rib, longeron, etc.) 3. Type and extent of damage (e.g

  17. ARINC818在航空电子视频系统中的应用%Application of ARINC 818 in Avionics Video System

    冯晓旺; 蓝海文


    @@ 伴随航空电子技术的飞速发展,航空电子系统构造变得更加复杂,整个系统的数字化信息量急剧增加,传统的ARINC429、Mil-STD-1553等总线已经不能满足新型飞机航空电子系统的技术需求[1-2],因此传统的总线技术正逐步被新一代航空数据总线技术所替代,国外新型的商业和军用航李航天项目中的航空电子系统采用的总线已经开始转向光纤通道(Fiber-Channel)和航空电子全双工以太网(AFDX)等新技术[3-4].

  18. Integrated Enhanced and Synthetic Vision System for Transport Aircraft

    N. Shantha Kumar


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

  19. New technologies for space avionics

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


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

  20. Waves in the Martian Atmosphere: Results from MGS Radio Occultations

    Flasar, F. M.; Hinson, D. P.; Tyler, G. L.


    Temperatures retrieved from Mars Global Surveyor radio occultations have been searched for evidence of waves. Emphasis has been on the initial series of occultations between 29(deg) N and 64(deg) S, obtained during the early martian southern summer, L_s=264(deg-308^deg) . The profiles exhibit an undulatory behavior that is suggestive of vertically propagating waves. Wavelengths ~ 10 km are often dominant, but structure on smaller scales is evident. The undulatory structure is most pronounced between latitudes 29(deg) N and 10(deg) S, usually in regions of ``interesting'' topography, e.g., in the Tharsis region and near the edge of Syrtis Major. Several temperature profiles, particularly within 30(deg) of the equator, exhibit lapse rates that locally become superadiabatic near the 0.4--mbar level or at higher altitudes. This implies that the waves are ``breaking'' and depositing horizontal momentum into the atmosphere. Such a deposition may play an important role in modulating the atmospheric winds, and characterizing the spatial and temporal distribution of these momentum transfers can provide important clues to understanding how the global circulation is maintained.

  1. Aerospace power systems technology; Proceedings of the Aerospace Technology Conference and Exposition, Anaheim, CA, Oct. 3-6, 1988


    The present conference on aircraft auxilliary power systems discusses aircraft thermal management, highly reliable DC power sources for avionic subsystems, a cascaded doubly-fed variable-speed/constant-frequency generator, the evolution of battery systems employed by USAF aircraft, electrical power system architectures for future aerospace vehicles, and high-reliability aircraft generators. Also discussed are the benefits of digital control and management system integration in secondary power systems, pneumatic link secondary power systems for military aircraft, the combination of emergency power with an APU, X-29A subsystems integration, and the T-100 multipurpose small power unit.

  2. Developing a Formal Specification for the Mission Systems of a Maritime Surveillance Aircraft

    Petrucci, Laure; Billington, Jonathan; Kristensen, Lars Michael


    of formal techniques to investigate and predict the effects of upgrades on mission system behaviour. This paper reports on a joint research project between the University of South Australia and Australia's Defence Science and Technology Organisation. In previous work we modelled a generic avionics mission......The mission system of an aircraft is a complex real-time distributed system consisting of a mission control computer, different kinds of devices interconnected by a number of serial data buses. The complexity and real-time requirements of mission systems have motivated research into the application...

  3. State Machine Modeling of the Space Launch System Solid Rocket Boosters

    Harris, Joshua A.; Patterson-Hine, Ann


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

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

    Yuchnovicz, Daniel; Burgess, Malcolm; Hammers, William


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

  5. Analysis of Security Protocols in Embedded Systems

    Bruni, Alessandro

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

  6. Exploration EVA System

    Kearney, Lara


    In January 2004, the President announced a new Vision for Space Exploration. NASA's Office of Exploration Systems has identified Extravehicular Activity (EVA) as a critical capability for supporting the Vision for Space Exploration. EVA is required for all phases of the Vision, both in-space and planetary. Supporting the human outside the protective environment of the vehicle or habitat and allow ing him/her to perform efficient and effective work requires an integrated EVA "System of systems." The EVA System includes EVA suits, airlocks, tools and mobility aids, and human rovers. At the core of the EVA System is the highly technical EVA suit, which is comprised mainly of a life support system and a pressure/environmental protection garment. The EVA suit, in essence, is a miniature spacecraft, which combines together many different sub-systems such as life support, power, communications, avionics, robotics, pressure systems and thermal systems, into a single autonomous unit. Development of a new EVA suit requires technology advancements similar to those required in the development of a new space vehicle. A majority of the technologies necessary to develop advanced EVA systems are currently at a low Technology Readiness Level of 1-3. This is particularly true for the long-pole technologies of the life support system.

  7. Energy storage systems impact on the short-term frequency stability of distributed autonomous microgrids, an analysis using aggregate models

    Serban, Ioan; Teodorescu, Remus; Marinescu, Corneliu


    is on autonomous MGs that dynamically behave similarly to the classical power systems. This is the systems case with classical distributed generators (DGs), but which can also contain renewable energy sources (RESs) in a certain penetration level. During MG islanded operation, the local generators take over most...... with both inertial response and an adaptive droop characteristic during battery state-of-charge limitations. The conducted analysis is accomplished by adopting aggregated models for the involved control mechanisms. The developed model is analysed in frequency domain, whereas an experimental test bench...

  8. Digital systems from logic gates to processors

    Deschamps, Jean-Pierre; Terés, Lluís


    This textbook for a one-semester course in Digital Systems Design describes the basic methods used to develop “traditional” Digital Systems, based on the use of logic gates and flip flops, as well as more advanced techniques that enable the design of very large circuits, based on Hardware Description Languages and Synthesis tools. It was originally designed to accompany a MOOC (Massive Open Online Course) created at the Autonomous University of Barcelona (UAB), currently available on the Coursera platform. Readers will learn what a digital system is and how it can be developed, preparing them for steps toward other technical disciplines, such as Computer Architecture, Robotics, Bionics, Avionics and others. In particular, students will learn to design digital systems of medium complexity, describe digital systems using high level hardware description languages, and understand the operation of computers at their most basic level. All concepts introduced are reinforced by plentiful illustrations, examples, ...

  9. Airborne laser sensors and integrated systems

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


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

  10. FAILSAFE Health Management for Embedded Systems

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


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

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

    Sunita Awasthi Singh


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

  12. Cockpit displays and the growing role of the pilot in the ATC system

    Lyman, E. G.


    It is pointed out that advances in avionics and computer technology have reached the point where serious attention may be given to structuring a new controlled air traffic environment. The principal feature of such an environment is related to the capability of pilots to perform certain active ATC functions from the cockpit. The main function is concerned with the ability to maintain safe separation from other aircraft under all meteorological conditions. Technical features available to permit such a functional change include such concepts as the Discrete Address Beacon System, a full capability Beacon Collision Avoidance System, data links, computer generated displays, and flight management computers.

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

    周庆; 刘斌; 余正伟; 冯时雨


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

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

    Guillaume Faburel


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

  15. Intelligent Control for a DC Micro-Grid System

    Martino, Michele; Quiñones, Yamshid Farhat; Raboni, Pietro


    This paper presents the dynamic response of a DC–micro-grid (DC-MG) controlled in master-slave mode. The benefits of the micro-grids (MGs) are the low cost in terms of power electronics converters and the high reliability and quality, even in case of loss connection to the transmission system. A DC......-MG in fact can survive in standalone mode if properly managed. The considered system is made by a photovoltaic array (PV), a wind turbine (WT), a gas engine (GE) and an energy storage system (ESS). The DC-MG behavior is analyzed in different scenarios to demonstrate the efficacy of the control for all...... the units, especially in case of variable weather conditions with different DC loads. Thus the voltage level of the system and the power flow are shown, out of a detailed description of the power electronic interfaces featuring the distributed generators (DGs)....

  16. Spacesuit Data Display and Management System

    Hall, David G.; Sells, Aaron; Shah, Hemal


    A prototype embedded avionics system has been designed for the next generation of NASA extra-vehicular-activity (EVA) spacesuits. The system performs biomedical and other sensor monitoring, image capture, data display, and data transmission. An existing NASA Phase I and II award winning design for an embedded computing system (ZIN vMetrics - BioWATCH) has been modified. The unit has a reliable, compact form factor with flexible packaging options. These innovations are significant, because current state-of-the-art EVA spacesuits do not provide capability for data displays or embedded data acquisition and management. The Phase 1 effort achieved Technology Readiness Level 4 (high fidelity breadboard demonstration). The breadboard uses a commercial-grade field-programmable gate array (FPGA) with embedded processor core that can be upgraded to a space-rated device for future revisions.

  17. Synthesis from Design Requirements of a Hybrid System for Transport Aircraft Longitudinal Control. Volume 1

    Hynes, Charles S.; Hardy, Gordon H.; Sherry, Lance


    Volume I of this report presents a new method for synthesizing hybrid systems directly from design requirements, and applies the method to design of a hybrid system for longitudinal control of transport aircraft. The resulting system satisfies general requirement for safety and effectiveness specified a priori, enabling formal validation to be achieved. Volume II contains seven appendices intended to make the report accessible to readers with backgrounds in human factors, fli ght dynamics and control. and formal logic. Major design goals are (1) system desi g n integrity based on proof of correctness at the design level, (2), significant simplification and cost reduction in system development and certification, and (3) improved operational efficiency, with significant alleviation of human-factors problems encountered by pilots in current transport aircraft. This report provides for the first time a firm technical basis for criteria governing design and certification of avionic systems for transport aircraft. It should be of primary interest to designers of next-generation avionic systems.

  18. Integrated Station Executive requirements and systems design approach

    Berger, Eugene L.; Morris, C. Doug


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

  19. A new method for hardware/software integration of strategic systems Case study for the Space Shuttle

    Ionescu, T. V.; Haque, S. I.; Sripad, A. B.


    A new method for ground testing a complex avionics system in an integrated manner has been developed. A case study for the Space Shuttle, on which the concept has been successfully implemented, is described here. This approach utilizes the actual hardware and software of the vehicle to perform a realistic simulation of its mission, verifying in the process all the critical interfaces and interactions of the software with the hardware. The advantages over current testing techniques are discussed, as well as the extension of the concept to other strategic systems.

  20. Assessment Environment for Complex Systems Software Guide


    This Software Guide (SG) describes the software developed to test the Assessment Environment for Complex Systems (AECS) by the West Virginia High Technology Consortium (WVHTC) Foundation's Mission Systems Group (MSG) for the National Aeronautics and Space Administration (NASA) Aeronautics Research Mission Directorate (ARMD). This software is referred to as the AECS Test Project throughout the remainder of this document. AECS provides a framework for developing, simulating, testing, and analyzing modern avionics systems within an Integrated Modular Avionics (IMA) architecture. The purpose of the AECS Test Project is twofold. First, it provides a means to test the AECS hardware and system developed by MSG. Second, it provides an example project upon which future AECS research may be based. This Software Guide fully describes building, installing, and executing the AECS Test Project as well as its architecture and design. The design of the AECS hardware is described in the AECS Hardware Guide. Instructions on how to configure, build and use the AECS are described in the User's Guide. Sample AECS software, developed by the WVHTC Foundation, is presented in the AECS Software Guide. The AECS Hardware Guide, AECS User's Guide, and AECS Software Guide are authored by MSG. The requirements set forth for AECS are presented in the Statement of Work for the Assessment Environment for Complex Systems authored by NASA Dryden Flight Research Center (DFRC). The intended audience for this document includes software engineers, hardware engineers, project managers, and quality assurance personnel from WVHTC Foundation (the suppliers of the software), NASA (the customer), and future researchers (users of the software). Readers are assumed to have general knowledge in the field of real-time, embedded computer software development.

  1. Space shuttle digital flight control system

    Minott, G. M.; Peller, J. B.; Cox, K. J.


    The space shuttle digital, fly by wire, flight control system presents an interesting challenge in avionics system design. In residence in each of four redundant general purpose computers at lift off are the guidance, navigation, and control algorithms for the entire flight. The mission is divided into several flight segments: first stage ascent, second stage ascent; abort to launch site, abort once around; on orbit operations, entry, terminal area energy management; and approach and landing. The FCS is complicated in that it must perform the functions to fly the shuttle as a boost vehicle, as a spacecraft, as a reentry vehicle, and as a conventional aircraft. The crew is provided with both manual and automatic modes of operations in all flight phases including touchdown and rollout.

  2. Bioinspired optical sensors for unmanned aerial systems

    Chahl, Javaan; Rosser, Kent; Mizutani, Akiko


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

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

    曹猛; 孙永荣; 王岩; 周晓达; 黄鸣丰


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

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


    International Corporation 4031 Colonel Glenn Highway Beavercreek, OH 45431-1673 Nikolaos G. Bourbakis Wright State University Information Technology...NUMBER 2432 5e. TASK NUMBER 04 6. AUTHOR(S) Russell F. Moody (Science Applications International Corporation) Nikolaos G. Bourbakis (Wright...modeling, retrieving, distributing, and publishing documents on the Web ( Bourbakis ) − Research cryptanalysis. − System security. − Self-healing

  5. Terrestrial radiation effects in ULSI devices and electronic systems

    Ibe, Eishi H


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

  6. Dynamic Control System Performance during Commissioning of the Space Technology 7-Disturbance Reduction System Experiment of LISA Pathfinder

    Hsu, Oscar; Maghami, Peiman; O’Donnell, James R., Jr.; Ziemer, John; Romero-Wolf, Andrew


    The Space Technology-7 Disturbance Reduction System (DRS) launched aboard the European Space Agency's LISA Pathfinder spacecraft on December 3, 2015, after more than a decade in development. DRS consists of three primary components: an Integrated Avionics Unit (IAU), Colloidal MicroNewton Thrusters, and Dynamic Control System (DCS) algorithms implemented on the IAU. During the portions of the mission in which the DRS was under control, the DCS was responsible for controlling the spacecraft and the free-floating test masses that were part of the LISA Test Package. The commissioning period was originally divided into two periods: before propulsion separation and after propulsion separation. A recommissioning period was added after an anomaly occurred in the thruster system. The paper will describe the activities used to commission DRS, present results from the commissioning of the DCS and the recommissioning activities per-formed after the thruster anomaly.

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


    ces 22-3 ambigui~s en classant ces cibles potentielles en - Apprentissage "cible" ou "fausse alarme", Parnii lcs objets class~s dans la cat~gorie...from a variety of cockpit instruments in favour of the 2 dedicated "Radio Frequency Indicator". MFDs and I CDU per crew station. Some in- struments...prioritization are relative displays, backup flight instruments are geometry, position within the threat provided for flight safety reasons. The missile

  8. Global system data bus using the Digital Autonomous Terminal Access Communication protocol

    Holmes, David C. E.


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

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

    Jürgen Teich


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

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

    Streichert Thilo


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

  11. Conceptual Design of a Z-Pinch Fusion Propulsion System

    Adams, Robert; Polsgrove, Tara; Fincher, Sharon; Fabinski, Leo; Maples, Charlotte; Miernik, Janie; Stratham, Geoffrey; Cassibry, Jason; Cortez, Ross; Turner, Matthew; Santarius, John; Percy, Thomas


    This slide presentation reviews a project that aims to develop a conceptual design for a Z-pinch thruster, that could be applied to develop advanced thruster designs which promise high thrust/high specific impulse propulsion. Overviews shows the concept of the design, which use annular nozzles with deuterium-tritium (D-T) fuel and a Lithium mixture as a cathode, Charts show the engine performance as a function of linear mass, nozzle performance (i.e., plasma segment trajectories), and mission analysis for possible Mars and Jupiter missions using this concept for propulsion. Slides show views of the concepts for the vehicle configuration, thrust coil configuration, the power management system, the structural analysis of the magnetic nozzle, the thermal management system, and the avionics suite,

  12. Extended Duration Orbiter (EDO) Improved Waste Collection System (IWCS)


    This high angle overall view shows the top side components of the Extended Duration Orbiter (EDO) Waste Collection System (WCS) scheduled to fly aboard NASA's Endeavour, Orbiter Vehicle (OV) 105, for the STS-54 mission. Detailed Test Objective 662, Extended duration orbiter WCS evaluation, will verify the design of the new EDO WCS under microgravity conditions for a prolonged period. OV-105 has been modified with additional structures in the waste management compartment (WMC) and additional avionics to support/restrain the EDO WCS. Among the advantages the new IWCS is hoped to have over the currect WCS are greater dependability, better hygiene, virtually unlimited capacity, and more efficient preparation between shuttle missions. Unlike the previous WCS, the improved version will not have to be removed from the spacecraft to be readied for the next flight. The WCS was documented in JSC's Crew Systems Laboratory Bldg 7.

  13. Practice-Oriented Formal Methods to Support the Software Development of Industrial Control Systems

    Darvas, Daniel; Blanco Viñuela, Enrique

    Formal specification and verification methods provide ways to describe requirements precisely and to check whether the requirements are satisfied by the design or the implementation. In other words, they can prevent development faults and therefore improve the quality of the developed systems. These methods are part of the state-of-the-practice in application domains with high criticality, such as avionics, railway or nuclear industry. The situation is different in the industrial control systems domain. As the criticality of the systems is much lower, formal methods are rarely used. The two main obstacles to using formal methods in systems with low- or medium-criticality are performance and usability. Overcoming these obstacles often needs deep knowledge and high effort. Model checking, one of the main formal verification techniques, is computationally difficult, therefore the analysis of non-trivial systems requires special considerations. Furthermore, the mainly academic tools implementing different model c...

  14. CESAR cost-efficient methods and processes for safety-relevant embedded systems

    Wahl, Thomas


    The book summarizes the findings and contributions of the European ARTEMIS project, CESAR, for improving and enabling interoperability of methods, tools, and processes to meet the demands in embedded systems development across four domains - avionics, automotive, automation, and rail. The contributions give insight to an improved engineering and safety process life-cycle for the development of safety critical systems. They present new concept of engineering tools integration platform to improve the development of safety critical embedded systems and illustrate capacity of this framework for end-user instantiation to specific domain needs and processes. They also advance state-of-the-art in component-based development as well as component and system validation and verification, with tool support. And finally they describe industry relevant evaluated processes and methods especially designed for the embedded systems sector as well as easy adoptable common interoperability principles for software tool integratio...

  15. Assessment of redundant systems with imperfect coverage by means of binary decision diagrams

    Myers, Albert F. [Northrop Grumman Corporation, 1840 Century Park East, Los Angeles, CA 90067-2199 (United States)], E-mail:; Rauzy, Antoine [IML/CNRS, 163, Avenue de Luminy, 13288 Marseille Cedex 09 (France)], E-mail:


    In this article, we study the assessment of the reliability of redundant systems with imperfect fault coverage. We term fault coverage as the ability of a system to isolate and correctly accommodate failures of redundant elements. For highly reliable systems, such as avionic and space systems, fault coverage is in general imperfect and has a significant impact on system reliability. We review here the different models of imperfect fault coverage. We propose efficient algorithms to assess them separately (as k-out-of-n selectors). We show how to implement these algorithms into a binary decision diagrams engine. Finally, we report experimental results on real life test cases that show on the one hand the importance of imperfect coverage and on the other hand the efficiency of the proposed approach.

  16. Flight evaluation of a computer aided low-altitude helicopter flight guidance system

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


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

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

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


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

  18. Iodine Hall Thruster Propellant Feed System for a CubeSat

    Polzin, Kurt A.; Peeples, Steven


    The components required for an in-space iodine vapor-fed Hall effect thruster propellant management system are described. A laboratory apparatus was assembled and used to produce iodine vapor and control the flow through the application of heating to the propellant reservoir and through the adjustment of the opening in a proportional flow control valve. Changing of the reservoir temperature altered the flowrate on the timescale of minutes while adjustment of the proportional flow control valve changed the flowrate immediately without an overshoot or undershoot in flowrate with the requisite recovery time associated with thermal control systems. The flowrates tested spanned a range from 0-1.5 mg/s of iodine, which is sufficient to feed a 200-W Hall effect thruster.

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

    Sunita Awasthi Singh


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

  20. Nonoperating Failure Rates for Avionics Study.


    ENVIRONMENTAL MITDK-1B RA7324 LC.76.1 OPERATING NONOPERATING DUIAION DUTY CYCLE METHOD METHOD FAILURES SAILURES ANALYSIS IMO)I OP NERO NOP NOP AOP AAOP A...Reliability and Maintainability Sym- posium, Wash., DC, January 1975. 21. Balaban, H.S. , Guidelines for Application of Warranties to Air Force

  1. Corrosion Control Test Method for Avionic Components


    Oelionstration and Corrosion Tests Documnentation Task 1 Task 2k3 3 Tent Methods 3 Test Methods 2 Test Methods FIgure 1program Plan 2 NADC 81174-60 04 L...per 10 cubic foot of uhamber velume every 24 hours. The solution is atomized by compressed air humidified by bubbling through 115*F distilled water

  2. General Aviation Activity and Avionics Survey 1984


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  3. General Aviation Activity and Avionics Survey


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  4. General Aviation Activity and Avionics Survey 1982.


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  5. Aging Engines, Avionics, Subsystems and Helicopters


    House Via XX Settembre 123a28850 Torrejón de Ardoz - Madrid 65 Brown Street 00187 Roma Glasgow G2 8EX ETATS-UNIS LUXEMBOURGNASA Center for AeroSpace...str∨edisko R&T ICELAND INTA (RTO/AGARD Publications)VTÚL a PVO Praha Director of Aviation Carretera de Torrejón a Ajalvir, Pk.4Mladoboleslavská ul...Bakanliklar - Ankara Via XX Settembre 123aDK-2100 Copenhagen Ø UNITED KINGDOM00187 Roma FRANCE Defence Research Information LUXEMBOURGO.N.E.R.A. (ISP

  6. Avionics and ATC Technology for Mission Control

    Elena BALMUS


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

  7. Avionics for Scaled Remotely Operated Vehicles Project

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

  8. Avionics for Scaled Remotely Operated Vehicles Project

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

  9. Avionics Box Cold Plate Damage Prevention

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


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

  10. H-60 Mission Avionics Technology Insertion


    single board computer . This is the same single board computer that is utilized in the Primary Mission Computer, so it would be subject to the same...Report Document No. 312-015-002 Page 23 4.2.13 Acoustic Processor The Acoustic Processor contains four single board computer modules in a 15 slot VME

  11. Avionics Reliability, Its Techniques and Related Disciplines.


    de la necessit6 d’effectuer de faqon aussi precise que possible le travail demandA et d’autre part de l’absence d’arri~re pens~e chez l’industriel...Peri, 92240 Malakoff, France CIERI, G. Mr Contraves Italiana, Spa. Via Tiburtina, 965-00156, Roma , Italy CIVIDINO, B.C. Mr LMT, 46, Quai Alphonse Le...d’Evere, B 1140, Brussels, Belgium NERI, A. Mr Contraves Italiana, Spa, Via Tiburtina, 965, 00156, Roma , Italy O’CONNOR, P.D.T. Mr British Aerospace

  12. Integrated Strike Avionics Study. Volume 1


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  13. SWIFT-nanoLV Avionics Platform Project

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

  14. Software Engineering and Its Application to Avionics


    FIGURE I 7-2 On votl dne qiepourdos stieks pou aWnodne (4 1W), Is polds des cots togilets, siuris u’S, osi trils 11W0t. tt saore ntcoesko. ta lrscrime...ii est par isieplo plus urgent de reconnaltro uin hostili proche, qu’une cible lointaino ou pou dangireuso. - Pit - le polds , 6vintuelleuint incertain

  15. Design and testing of the U.S. Space Station Freedom primary propulsion system

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


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

  16. Wireless Data Acquisition System for Launch Vehicles

    Sabooj Ray


    Full Text Available Present launch vehicle integration architecture for avionics uses wired link to transfer data between various sub-systems. Depending on system criticality and complexity, MIL1553 and RS485 are the common protocols that are adopted. These buses have their inherent complexity and failure issues due to harness defects or under adverse flight environments. To mitigate this problem, a prototype wireless, data acquisition system for telemetry applications has been developed and demonstrated. The wireless system simplifies the integration, while reducing weight and costs. Commercial applications of wireless systems are widespread. Few systems have recently been developed for complex and critical environments. Efforts have been underway to make such architectures operational in promising application scenarios. This paper discusses the system concept for adapting a wireless system to the existing bus topology. The protocol involved and the internal implementation of the different modules are described. The test results are presented; some of the issues faced are discussed and the; future course of action is identified.Defence Science Journal, 2013, 63(2, pp.186-191, DOI:

  17. Optimal Scheduling of a Battery-Based Energy Storage System for a Microgrid with High Penetration of Renewable Sources

    Dulout, Jeremy; Hernández, Adriana Carolina Luna; Anvari-Moghaddam, Amjad


    A new scheduling method is proposed to manage efficiently the integration of renewable sources in microgrids (MGs) with energy storage systems (ESSs). The purpose of this work is to take into account the main stress factors influencing the ageing mechanisms of a battery energy storage system (BESS......) in order to make an optimal dispatch of resources in the microgrid and enhance the storage system lifetime while minimizing the cost of electric consumption. The load demand and generation profiles are derived from the analysis of consumption and renewable production (solar photovoltaic sources and wind...... turbines) of the Western Denmark electric grid. Thus, the proposed microgrid is mainly fed by renewable sources and few electricity is coming from the main grid (which helps operating costs minimization). In this respect, a cost analysis is performed to find the optimal hourly power output of the BESS...

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

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


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

  19. Ares I First Stage Propulsion System Status

    Priskos, Alex S.


    With the retirement of the Space Shuttle inevitable, the US is faced with the need to loft a reliable cost-effective, technologically viable solution to bring the nation s fleet of spacecraft back up to industry standard. It must not only support the International Space Station (ISS), it must also be capable of supporting human exploration beyond low Earth orbit (LEO). NASA created the Constellation Program to develop a new fleet including the launch vehicles, the spacecraft, and the mission architecture to meet those objectives. The Ares First Stage Team is tasked with developing a propulsion system capable of safely, dependably and repeatedly lofting that new fleet. To minimize technical risks and development costs, the Solid Rocket Boosters (SRBs) of Shuttle were used as a starting point in the design and production of a new first stage element. While the first stage will provide the foundation, the structural backbone, power, and control for launch, the new propulsive element will also provide a greater total impulse to loft a safer, more powerful, fleet of space flight vehicles. Substantial design and system upgrades were required to meet the mass and trajectory requisites of the new fleet. Noteworthy innovations and design features include new forward structures, new propellant grain geometry, a new internal insulation system, and a state-of-the art avionics system. Additional advances were in materials and composite structures development, case bond liners, and thermal protection systems. Significant progress has been made in the design, development and testing of the propulsion and avionics systems for the new first stage element. Challenges, such as those anticipated with thrust oscillation, have been better characterized, and are being effectively mitigated. The test firing of the first development motor (DM-1) was a success that validated much of the engineering development to date. Substantive data has been collected and analyzed, allowing the Ares

  20. Extratropical Weather Systems on Mars: Radiatively-Active Water Ice Effects

    Hollingsworth, J. L.; Kahre, M. A.; Haberle, R. M.; Urata, R. A.; Montmessin, F.


    Extratropical, large-scale weather disturbances, namely transient, synoptic-period,baroclinic barotropic eddies - or - low- (high-) pressure cyclones (anticyclones), are components fundamental to global circulation patterns for rapidly rotating, differentially heated, shallow atmospheres such as Earth and Mars. Such "wave-like" disturbances that arise via (geophysical) fluid shear instability develop, mature and decay, and travel west-to-east in the middle and high latitudes within terrestrial-like planetary atmospheres. These disturbances serve as critical agents in the transport of heat and momentum between low and high latitudes of the planet. Moreover, they transport trace species within the atmosphere (e.g., water vapor/ice, other aerosols (dust), chemical species, etc). Between early autumn through early spring, middle and high latitudes on Mars exhibit strong equator-to-pole mean temperature contrasts (i.e., "baroclinicity"). Data collected during the Viking era and observations from both the Mars Global Surveyor (MGS) and Mars Reconnaissance Orbiter (MRO) indicate that such strong baroclinicity supports vigorous, large-scale eastward traveling weather systems [Banfield et al., 2004; Barnes et al., 1993]. A good example of traveling weather systems, frontal wave activity and sequestered dust activity from MGS/MOC image analyses is provided in Figure 1 (cf. Wang et al. [2005]). Utilizing an upgraded and evolving version of the NASA Ames Research Center (ARC) Mars global climate model, investigated here are key dynamical and physical aspects of simulated northern hemisphere (NH) large-scale extratropica lweather systems,with and without radiatively-active water ice clouds. Mars Climate Model:

  1. Structural Dynamics of Electronic Systems

    Suhir, E.


    The published work on analytical ("mathematical") and computer-aided, primarily finite-element-analysis (FEA) based, predictive modeling of the dynamic response of electronic systems to shocks and vibrations is reviewed. While understanding the physics of and the ability to predict the response of an electronic structure to dynamic loading has been always of significant importance in military, avionic, aeronautic, automotive and maritime electronics, during the last decade this problem has become especially important also in commercial, and, particularly, in portable electronics in connection with accelerated testing of various surface mount technology (SMT) systems on the board level. The emphasis of the review is on the nonlinear shock-excited vibrations of flexible printed circuit boards (PCBs) experiencing shock loading applied to their support contours during drop tests. At the end of the review we provide, as a suitable and useful illustration, the exact solution to a highly nonlinear problem of the dynamic response of a "flexible-and-heavy" PCB to an impact load applied to its support contour during drop testing.

  2. Safer Systems: A NextGen Aviation Safety Strategic Goal

    Darr, Stephen T.; Ricks, Wendell R.; Lemos, Katherine A.


    The Joint Planning and Development Office (JPDO), is charged by Congress with developing the concepts and plans for the Next Generation Air Transportation System (NextGen). The National Aviation Safety Strategic Plan (NASSP), developed by the Safety Working Group of the JPDO, focuses on establishing the goals, objectives, and strategies needed to realize the safety objectives of the NextGen Integrated Plan. The three goal areas of the NASSP are Safer Practices, Safer Systems, and Safer Worldwide. Safer Practices emphasizes an integrated, systematic approach to safety risk management through implementation of formalized Safety Management Systems (SMS) that incorporate safety data analysis processes, and the enhancement of methods for ensuring safety is an inherent characteristic of NextGen. Safer Systems emphasizes implementation of safety-enhancing technologies, which will improve safety for human-centered interfaces and enhance the safety of airborne and ground-based systems. Safer Worldwide encourages coordinating the adoption of the safer practices and safer systems technologies, policies and procedures worldwide, such that the maximum level of safety is achieved across air transportation system boundaries. This paper introduces the NASSP and its development, and focuses on the Safer Systems elements of the NASSP, which incorporates three objectives for NextGen systems: 1) provide risk reducing system interfaces, 2) provide safety enhancements for airborne systems, and 3) provide safety enhancements for ground-based systems. The goal of this paper is to expose avionics and air traffic management system developers to NASSP objectives and Safer Systems strategies.

  3. systems

    Alexander Leonessa


    Full Text Available A nonlinear robust control-system design framework predicated on a hierarchical switching controller architecture parameterized over a set of moving nominal system equilibria is developed. Specifically, using equilibria-dependent Lyapunov functions, a hierarchical nonlinear robust control strategy is developed that robustly stabilizes a given nonlinear system over a prescribed range of system uncertainty by robustly stabilizing a collection of nonlinear controlled uncertain subsystems. The robust switching nonlinear controller architecture is designed based on a generalized (lower semicontinuous Lyapunov function obtained by minimizing a potential function over a given switching set induced by the parameterized nominal system equilibria. The proposed framework robustly stabilizes a compact positively invariant set of a given nonlinear uncertain dynamical system with structured parametric uncertainty. Finally, the efficacy of the proposed approach is demonstrated on a jet engine propulsion control problem with uncertain pressure-flow map data.

  4. A Domain-Specific Language for Multitask Systems, Applying Discrete Controller Synthesis

    Éric Rutten


    Full Text Available We propose a simple programming language, called Nemo, specific to the domain of multitask real-time control systems, such as in robotic, automotive, or avionics systems. It can be used to specify a set of resources with usage constraints, a set of tasks that consume them according to various modes, and applications sequencing the tasks. We automatically obtain an application-specific task handler that correctly manages the constraints (if there exists one, through a compilation-like process including a phase of discrete controller synthesis. This way, this formal technique contributes to the safety of the designed systems, while being encapsulated in a tool that makes it usable by application experts. Our approach is based on the synchronous modelling techniques, languages, and tools.

  5. A Domain-Specific Language for Multitask Systems, Applying Discrete Controller Synthesis

    Rutten Éric


    Full Text Available We propose a simple programming language, called Nemo, specific to the domain of multitask real-time control systems, such as in robotic, automotive, or avionics systems. It can be used to specify a set of resources with usage constraints, a set of tasks that consume them according to various modes, and applications sequencing the tasks. We automatically obtain an application-specific task handler that correctly manages the constraints (if there exists one, through a compilation-like process including a phase of discrete controller synthesis. This way, this formal technique contributes to the safety of the designed systems, while being encapsulated in a tool that makes it usable by application experts. Our approach is based on the synchronous modelling techniques, languages, and tools.

  6. An Autonomous Autopilot Control System Design for Small-Scale UAVs

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


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

  7. Flight Performance of the AKARI Cryogenic System

    Nakagawa, Takao; Hirabayashi, Masayuki; Kaneda, Hidehiro; Kii, Tsuneo; Kimura, Yoshiyuki; Matsumoto, Toshio; Murakami, Hiroshi; Murakami, Masahide; Narasaki, Katsuhiro; Narita, Masanao; Ohnishi, Akira; Tsunematsu, Shoji; Yoshida, Seiji


    We describe the flight performance of the cryogenic system of the infrared astronomical satellite AKARI, which was successfully launched on 2006 February 21 (UT). AKARI carries a 68.5 cm telescope together with two focal plane instruments, Infrared Cameras (IRC) and Far Infrared Surveyor (FIS), all of which are cooled down to cryogenic temperature to achieve superior sensitivity. The AKARI cryogenic system is a unique hybrid system, which consists of cryogen (liquid helium) and mechanical coolers (2-stage Stirling coolers). With the help of the mechanical coolers, 179 L (26.0 kg) of super-fluid liquid helium can keep the instruments cryogenically cooled for more than 500 days. The on-orbit performance of the AKARI cryogenics is consistent with the design and pre-flight test, and the boil-off gas flow rate is as small as 0.32 mg/s. We observed the increase of the major axis of the AKARI orbit, which can be explained by the thrust due to thermal pressure of vented helium gas.

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


    and P Knight, "The Handbook of Antenna Design. Volume 1". London: Peter Peregrinus Ltd. B Vidal Saint Andre and P Neyret (1980), "The application of...PAA: B/(Pacific- Sierra Research Corp.. Los Angeles. CA); E/(USAF. Rome Air Development Center. Bedford. MA) Radio Science (ISSN 0048-6604). vol...of the enhanced traffic alert and collision avoidance system (TCAS 2) A/ ROJAS , R. G.; B/BURNSIDE, W. D.; C/LAW, P.; D/GRANDCHAMP, B. CORP: Ohio

  9. 基于模型驱动的航电系统安全性分析技术研究%Research on Model Based Safety Analysis Technology for Avionics System

    谷青范; 王国庆; 张丽花; 翟鸣



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



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

  11. The Application of Fibre Channel to MIL-STD-1553 Based Avionics System Networks%光纤通道在基于MIL-STD-1553的航空电子系统网络中的应用



    光纤通道作为新一代的航空电子系统通信网络技术,具有传输速度高、延时低、传输距离远和可靠性高等特性,高达4G bps的数据传输带宽,为其上层通信协议提供了一种通用的高速率的数据传输通道.FC-1553作为光纤通道上层通信协议之一,对MIL-STD-1553通信协议具有完全的兼容性,它继承了传统MIL-STD-1553通信协议的基本特征,实现了向光纤通道链路层的映射,从而扩展了通信网络的结构,提高了网络的通信能力.本文首先介绍MIL-STD-1553和光纤通道的基本特性,然后描述在光纤通道中对1553通信协议的映射,最后,提出了基于光纤通道和MIL-STD-1553的航空电子系统通信网络结构.

  12. SAE航空电子系统分部标准对民机研制适用性研究%Study on Standards Applicability for Civil Plane of Avionics System Division of SAE




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


    THE NAVY HEADQUARTERS NAVAL MATERIAL COMMAND WASHINGTON, D.C. 20360 ON v 0L Afo 08Y/DCR Ser 230 TACTICAL DIGITAL STANDARD (TADSTAND) Afaa aeil~;uyia...HEADQUARTERS NAVAL MATERIAL COMMAND WASHINGTON, D.c. 20360 .N RE,, REFER TADSTAND B (Revision 1) J MAT 08Y 21 June 1982 TACTICAL DIGITAL STANDARD B (Revision...8217 ’ ’ ° " T-9. 2 July 1980 TACTICAL DIGITAL STANDARD (TADSTAND) C From: Chief of Naval Material Subj: Computer Programming Language Standardization Policy

  14. Modeling, Stability Analysis and Active Stabilization of Multiple DC-Microgrids Clusters

    Shafiee, Qobad; Dragicevic, Tomislav; Vasquez, Juan Carlos


    ), and more especially during interconnection with other MGs, creating dc MG clusters. This paper develops a small signal model for dc MGs from the control point of view, in order to study stability analysis and investigate effects of CPLs and line impedances between the MGs on stability of these systems......DC microgrids (MGs), as an alternative option, have attracted increasing interest in recent years due to many potential advantages as compare to the ac system. Stability of these systems can be an important issue under high penetration of load converters which behaves as constant power loads (CPLs....... This model can be also used to synthesis and study dynamics of control loops in dc MGs and also dc MG clusters. An active stabilization method is proposed to be implemented as a dc active power filter (APF) inside the MGs in order to not only increase damping of dc MGs at the presence of CPLs but also...

  15. Architecture for Survivable System Processing (ASSP)

    Wood, Richard J.


    The Architecture for Survivable System Processing (ASSP) Program is a multi-phase effort to implement Department of Defense (DOD) and commercially developed high-tech hardware, software, and architectures for reliable space avionics and ground based systems. System configuration options provide processing capabilities to address Time Dependent Processing (TDP), Object Dependent Processing (ODP), and Mission Dependent Processing (MDP) requirements through Open System Architecture (OSA) alternatives that allow for the enhancement, incorporation, and capitalization of a broad range of development assets. High technology developments in hardware, software, and networking models, address technology challenges of long processor life times, fault tolerance, reliability, throughput, memories, radiation hardening, size, weight, power (SWAP) and security. Hardware and software design, development, and implementation focus on the interconnectivity/interoperability of an open system architecture and is being developed to apply new technology into practical OSA components. To insure for widely acceptable architecture capable of interfacing with various commercial and military components, this program provides for regular interactions with standardization working groups (e.g.) the International Standards Organization (ISO), American National Standards Institute (ANSI), Society of Automotive Engineers (SAE), and Institute of Electrical and Electronic Engineers (IEEE). Selection of a viable open architecture is based on the widely accepted standards that implement the ISO/OSI Reference Model.

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

    YangChun-xin; DangChao-Bin


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

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

    Ölveczky, Peter Csaba; 10.4204/EPTCS.36.8


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

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

    José Meseguer


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

  19. Efficient implementation of real-time programs under the VAX/VMS operating system

    Johnson, S. C.


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

  20. Formal Model Engineering for Embedded Systems Using Real-Time Maude

    Peter Csaba Ölveczky


    Full Text Available This paper motivates why Real-Time Maude should be well suited to provide a formal semantics and formal analysis capabilities to modeling languages for embedded systems. One can then use the code generation facilities of the tools for the modeling languages to automatically synthesize Real-Time Maude verification models from design models, enabling a formal model engineering process that combines the convenience of modeling using an informal but intuitive modeling language with formal verification. We give a brief overview six fairly different modeling formalisms for which Real-Time Maude has provided the formal semantics and (possibly formal analysis. These models include behavioral subsets of the avionics modeling standard AADL, Ptolemy II discrete-event models, two EMF-based timed model transformation systems, and a modeling language for handset software.

  1. Formal Model Engineering for Embedded Systems Using Real-Time Maude

    Ölveczky, Peter Csaba


    This paper motivates why Real-Time Maude should be well suited to provide a formal semantics and formal analysis capabilities to modeling languages for embedded systems. One can then use the code generation facilities of the tools for the modeling languages to automatically synthesize Real-Time Maude verification models from design models, enabling a formal model engineering process that combines the convenience of modeling using an informal but intuitive modeling language with formal verification. We give a brief overview six fairly different modeling formalisms for which Real-Time Maude has provided the formal semantics and (possibly) formal analysis. These models include behavioral subsets of the avionics modeling standard AADL, Ptolemy II discrete-event models, two EMF-based timed model transformation systems, and a modeling language for handset software.

  2. Solid Rocket Booster (SRB) Flight System Integration at Its Best

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


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

  3. systems

    Patrick L. Brockett


    Full Text Available Suppose S={{Xnj,   j=1,2,…,kn}} is an infinitesimal system of random variables whose centered sums converge in law to a (necessarily infinitely divisible distribution with Levy representation determined by the triple (γ,σ2,M. If {Yj,   j=1,2,…} are independent indentically distributed random variables independent of S, then the system S′={{YjXnj,j=1,2,…,kn}} is obtained by randomizing the scale parameters in S according to the distribution of Y1. We give sufficient conditions on the distribution of Y in terms of an index of convergence of S, to insure that centered sums from S′ be convergent. If such sums converge to a distribution determined by (γ′,(σ′2,Λ, then the exact relationship between (γ,σ2,M and (γ′,(σ′2,Λ is established. Also investigated is when limit distributions from S and S′ are of the same type, and conditions insuring products of random variables belong to the domain of attraction of a stable law.

  4. system

    Garcilazo, H.; Valcarce, A.; Vijande, J.


    Using local central Yukawa-type Malfliet-Tjon interactions reproducing the low-energy parameters and phase shifts of the nn system, and the latest updates of the nΛ and ΛΛ Nijmegen ESC08c potentials, we study the possible existence of a bound state. Our results indicate that the is unbound, being just above threshold. We discuss the role played by the 1 S 0 nn repulsive term of the Yukawa-type Malfliet-Tjon interaction. Supported by COFAA-IPN (México), Ministerio de Economía, Industria y Competitividad and EU FEDER (FPA2013-47443, FPA2015-69714-REDT, FPA2016-77177), Junta de Castilla y León (SA041U16) and Generalitat Valenciana PrometeoII/2014/066


    K. Swarnalatha


    Full Text Available Risk analysis of urban aquatic systems due to heavy metals turns significant due to their peculiar properties viz. persis tence, non-degradab ility, toxicity, and accumulation. Akkulam Veli (AV, an urba n tropical lake in south India is subjected to various environmental stresses due to multiple waste discharge, sand mining, developmental activities, tour ism related activitie s etc. Hence, a comprehensive approach is adopted for risk assessment using modified degree of contamination factor, toxicity units based on numerical sediment quality guidelines (SQGs, and potentialecological risk indices. The study revealed the presence of toxic metals such as Cr, C d, Pb and As and the lake is rated under ‘low ecological risk’ category.

  6. Maximizing commonality between military and general aviation fly-by-light helicopter system designs

    Enns, Russell; Mossman, David C.


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

  7. Design and systems analysis of a chemical interorbital shuttle. Volume 1: Executive summary

    Nissim, W.


    An interorbital shuttle that can be utilized to carry payloads between low earth orbit (180 n mi, 37.6 deg) and lunar or geosynchronous orbits, and also to interplanetary trajectories is discussed. After each mission the stage returns to its earth parking orbit where it delivers the inbound payloads, and where it is maintained and refueled for the subsequent missions. The stage can also be utilized to carry large payloads (150 to 200 KLBS) to the Space Station orbit (270 n mi, 55 deg) when it is used as a second or parallel burn stage to the space shuttle booster. The mission and systems analysis, as well as the results of structural, mechanical and propulsion, and avionics subsystems analysis and design are described. A development plan and cost estimates are also included.

  8. Compilation and synthesis for embedded reconfigurable systems an aspect-oriented approach

    Diniz, Pedro; Coutinho, José; Petrov, Zlatko


    This book provides techniques to tackle the design challenges raised by the increasing diversity and complexity of emerging, heterogeneous architectures for embedded systems. It describes an approach based on techniques from software engineering called aspect-oriented programming, which allow designers to control today’s sophisticated design tool chains, while maintaining a single application source code.  Readers are introduced to the basic concepts of an aspect-oriented, domain specific language that enables control of a wide range of compilation and synthesis tools in the partitioning and mapping of an application to a heterogeneous (and possibly multi-core) target architecture.  Several examples are presented that illustrate the benefits of the approach developed for applications from avionics and digital signal processing. Using the aspect-oriented programming techniques presented in this book, developers can reuse extensive sections of their designs, while preserving the original application source-...

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

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


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

  10. Flight Guidance System Validation Using SPIN

    Naydich, Dimitri; Nowakowski, John


    To verify the requirements for the mode control logic of a Flight Guidance System (FGS) we applied SPIN, a widely used software package that supports the formal verification of distributed systems. These requirements, collectively called the FGS specification, were developed at Rockwell Avionics & Communications and expressed in terms of the Consortium Requirements Engineering (CoRE) method. The properties to be verified are the invariants formulated in the FGS specification, along with the standard properties of consistency and completeness. The project had two stages. First, the FGS specification and the properties to be verified were reformulated in PROMELA, the input language of SPIN. This involved a semantics issue, as some constructs of the FGS specification do not have well-defined semantics in CoRE. Then we attempted to verify the requirements' properties using the automatic model checking facilities of SPIN. Due to the large size of the state space of the FGS specification an exhaustive state space analysis with SPIN turned out to be impossible. So we used the supertrace model checking procedure of SPIN that provides for a partial analysis of the state space. During this process, we found some subtle errors in the FGS specification.

  11. A New View of the Surface of Mars: High-Resolution Rock Abundance from MGS TES

    Nowicki, S.; Christensen, P.


    Mars Global Surveyor Thermal Emission Spectrometer data from the most dust-free seasons on Mars were used to calculate the areal percentage of rocks and finer materials such as dust and sand. Rock is defined as a surface material that has a thermal inertia of 1250 J/m2-s1/2-K (30 cal/cm2-s1/2-K) or greater. A surface with a high rock abundance value could be exposed bedrock, blocky debris, well-cemented materials or a combination. Globally, the TES and IRTM data agree well, with no rocks exposed in the large dusty regions such as Tharsis and Arabia, and exposure of rocks in small (a few km) areas where likely eolian or mass-wasting processes actively remove dust from the ancient rocky surface. Analysis of high-resolution TES rock abundance suggests that there are extremely varied surfaces within relatively small regions, and places an upper limit of ~45 % rocks in the rockiest regions. Thermal inertia and rock abundance are correlate to some degree over much of the planet, but the highest thermal inertia surfaces often do not have the highest rock abundances. A global perspective will be presented here, with detailed look at a few high-resolution ares including Ares Vallis/Pathfinder, Valles Marineris, and the proposed landing sites for the 2003 MER landers.

  12. Dhaksha, the Unmanned Aircraft System in its New Avatar-Automated Aerial Inspection of INDIA'S Tallest Tower

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


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

  13. Conception de lois de pilotage robustes et sequencement de gains par l'approche de systemes lineaires a parametres variants

    Hentabli, Kamel

    Cette recherche s'inscrit dans le cadre du projet de recherche Active Control Technology entre l'Ecole de Technologie Superieure et le constructeur Bombardier Aeronautique . Le but est de concevoir des strategies de commandes multivariables et robustes pour des modeles dynamiques d'avions. Ces strategies de commandes devraient assurer a l'avion une haute performance et satisfaire des qualites de vol desirees en l'occurrence, une bonne manoeuvrabilite, de bonnes marges de stabilite et un amortissement des mouvements phugoides et rapides de l'avion. Dans un premier temps, nous nous sommes principalement interesses aux methodes de synthese LTI et plus exactement a l'approche Hinfinity et la mu-synthese. Par la suite, nous avons accorde un interet particulier aux techniques de commande LPV. Pour mener a bien ce travail, nous avons envisage une approche frequentielle, typiquement Hinfinity. Cette approche est particulierement interessante, dans la mesure ou le modele de synthese est construit directement a partir des differentes specifications du cahier des charges. En effet, ces specifications sont traduites sous forme de gabarits frequentiels, correspondant a des ponderations en entree et en sortie que l'on retrouve dans la synthese Hinfinity classique. Par ailleurs, nous avons utilise une representation de type lineaire fractionnelle (LFT), jugee mieux adaptee pour la prise en compte des differents types d'incertitudes, qui peuvent intervenir sur le systeme. De plus, cette representation s'avere tres appropriee pour l'analyse de la robustesse via les outils de la mu-analyse. D'autre part, afin d'optimiser le compromis entre les specifications de robustesse et de performance, nous avons opte pour une structure de commande a 2 degres de liberte avec modele de reference. Enfin, ces techniques sont illustrees sur des applications realistes, demontrant ainsi la pertinence et l'applicabilite de chacune d'elle. Mots cles. Commande de vol, qualites de vol et manoeuvrabilite

  14. Advanced Mission Management System for Unmanned Aerial Vehicles

    R. Anand Raji


    Full Text Available The paper presents advanced mission management system (MMS for unmanned aerial vehicles, based on integrated modular avionics (IMA architecture. IMA architecture enables the MMS to host high end functions for autonomous navigation and attack. MMS is a collection of systems to execute the mission objectives. The system constitutes mission computer (MC, sensors and other sub-systems. The MMS-MC needs to execute advanced algorithms like terrain referenced navigation, vision-aided navigation, automatic target recognition, sensor fusion, online path planning, and tactical planning for autonomy and safety. This demands high-end architecture in terms of hardware, software, and communication. The MMS-MC is designed to exploit the benefits of IMA concepts such as open system architecture, hardware and software architecture catering for portability, technology transparency, scalability, system reconfigurability and fault tolerance. This paper investigates on advanced navigation methods for augmenting INS with terrain-referenced navigation and vision-aided navigation during GPS non-availability. This paper also includes approach to implement these methods and simulation results are provided accordingly, and also discusses in a limited way, the approach for implementing online path planning.Defence Science Journal, Vol. 64, No. 5, September 2014, pp.438-444, DOI:

  15. Measurement and reduction of system latency in see-through helmet mounted display (HMD) systems

    Vincenzi, Dennis A.; Deaton, John E.; Blickenderfer, Elizabeth L.; Pray, Rick; Williams, Barry; Buker, Timothy J.


    Future military aviation platforms such as the proposed Joint Strike Fighter F-35 will integrate helmet mounted displays (HMDs) with the avionics and weapon systems to the degree that the HMDs will become the aircraft's primary display system. In turn, training of pilot flight skills using HMDs will be essential in future training systems. In order to train these skills using simulation based training, improvements must be made in the integration of HMDs with out-thewindow (OTW) simulations. Currently, problems such as latency contribute to the onset of simulator sickness and provide distractions during training with HMD simulator systems that degrade the training experience. Previous research has used Kalman predictive filters as a means of mitigating the system latency present in these systems. While this approach has yielded some success, more work is needed to develop innovative and improved strategies that reduce system latency as well as to include data collected from the user perspective as a measured variable during test and evaluation of latency reduction strategies. The purpose of this paper is twofold. First, the paper describes a new method to measure and assess system latency from the user perspective. Second, the paper describes use of the testbed to examine the efficacy of an innovative strategy that combines a customized Kalman filter with a neural network approach to mitigate system latency. Results indicate that the combined approach reduced system latency significantly when compared to baseline data and the traditional Kalman filter. Reduced latency errors should mitigate the onset of simulator sickness and ease simulator sickness symptomology. Implications for training systems will be discussed.

  16. The Minnesota Grading System Using Fundus Autofluorescence of Eye Bank Eyes: A Correlation To Age-Related Macular Degeneration (An AOS Thesis)

    Olsen, Timothy W.


    Purpose To establish a grading system of eye bank eyes using fundus autofluorescence (FAF) and identify a methodology that correlates FAF to age-related macular degeneration (AMD) with clinical correlation to the Age-Related Eye Disease Study (AREDS). Methods Two hundred sixty-two eye bank eyes were evaluated using a standardized analysis of FAF. Measurements were taken with the confocal scanning laser ophthalmoscope (cSLO). First, high-resolution, digital, stereoscopic, color images were obtained and graded according to AREDS criteria. With the neurosensory retina removed, mean FAF values were obtained from cSLO images using software analysis that excludes areas of atrophy and other artifact, generating an FAF value from a grading template. Age and AMD grade were compared to FAF values. An internal fluorescence reference standard was tested. Results Standardization of the cSLO machine demonstrated that reliable data could be acquired after a 1-hour warm-up. Images obtained prior to 1 hour had falsely elevated levels of FAF. In this initial analysis, there was no statistical correlation of age to mean FAF. There was a statistically significant decrease in FAF from AREDS grade 1, 2 to 3, 4 (P < .0001). An internal fluorescent standard may serve as a quantitative reference. Conclusions The Minnesota Grading System (MGS) of FAF (MGS-FAF) establishes a standardized methodology for grading eye bank tissue to quantify FAF compounds in the retinal pigment epithelium and correlate these findings to the AREDS. Future studies could then correlate specific FAF to the aging process, histopathology AMD phenotypes, and other maculopathies, as well as to analyze the biochemistry of autofluorescent fluorophores. PMID:19277247

  17. Orion Ammonia Boiler System Preflight Test Preparations

    Levitt, Julia L.


    The Environmental Controls and Life Support Systems (ECLSS) branch at Kennedy Space Center (KSC) is currently undergoing preparations for ground testing of the Orion Multi-Purpose Crew Vehicle (MPCV) to prepare its subsystems for EM-1 (Exploration Mission-1). EM-1, Orions second unmanned flight, is a three-week long lunar mission during which the vehicle will complete a 6-day retrograde lunar orbit before returning to Earth. This paper focuses on the work done during the authors 16-week internship with the Mechanical Engineering Branch of KSCs Engineering Directorate. The authors project involved assisting with the preparations for testing the Orion MPCVs ammonia boiler system. The purpose of the ammonia boiler system is to keep the spacecraft sufficiently cool during the reentry portion of its mission, from service module (SM) separation to post-landing. This system is critical for keeping both the spacecraft (avionics and electronics) and crew alive during reentry, thus a successful test of the system is essential to the success of EM-1. XXXX The author was able to draft a detailed outline of the procedure for the ammonia system functional test. More work will need to be done on the vehicle power-up and power-down portions of the procedure, but the ammonia system testing portion of the procedure is thorough and includes vehicle test configurations, vehicle commands, and GSE. The author was able to compile a substantial list of questions regarding the ammonia system functional test with the help of her mentors. A significant number of these questions were answered in the teleconferences with Lockheed Martin.

  18. UAS-Systems Integration, Validation, and Diagnostics Simulation Capability

    Buttrill, Catherine W.; Verstynen, Harry A.


    As part of the Phase 1 efforts of NASA's UAS-in-the-NAS Project a task was initiated to explore the merits of developing a system simulation capability for UAS to address airworthiness certification requirements. The core of the capability would be a software representation of an unmanned vehicle, including all of the relevant avionics and flight control system components. The specific system elements could be replaced with hardware representations to provide Hardware-in-the-Loop (HWITL) test and evaluation capability. The UAS Systems Integration and Validation Laboratory (UAS-SIVL) was created to provide a UAS-systems integration, validation, and diagnostics hardware-in-the-loop simulation capability. This paper discusses how SIVL provides a robust and flexible simulation framework that permits the study of failure modes, effects, propagation paths, criticality, and mitigation strategies to help develop safety, reliability, and design data that can assist with the development of certification standards, means of compliance, and design best practices for civil UAS.

  19. High-bandwidth remote flat panel display interconnect system

    Peterson, Darrel G.


    High performance electronic displays (CRT, AMLCD, TFEL, plasma, etc.) require wide bandwidth electrical drive signals to produce the desired display images. When the image generation and/or image processing circuitry is located within the same line replaceable unit (LRU) as the display media, the transmission of the display drive signals to the display media presents no unusual design problems. However, many aircraft cockpits are severely constrained for available space behind the instrument panel. This often forces the system designer to specify that only the display media and its immediate support circuitry are to be mounted in the instrument panel. A wide bandwidth interconnect system is then required to transfer image data from the display generation circuitry to the display unit. Image data transfer rates of nearly 1.5 Gbits/second may be required when displaying full motion video at a 60 Hz field rate. In addition to wide bandwidth, this interconnect system must exhibit several additional key characteristics: (1) Lossless transmission of image data; (2) High reliability and high integrity; (3) Ease of installation and field maintenance; (4) High immunity to HIRF and electrical noise; (5) Low EMI emissions; (6) Long term supportability; and (7) Low acquisition and maintenance cost. Rockwell Collins has developed an avionics grade remote display interconnect system based on the American National Standards Institute Fibre Channel standard which meets these requirements. Readily available low cost commercial off the shelf (COTS) components are utilized, and qualification tests have confirmed system performance.

  20. Design and Analysis of Architectures for Structural Health Monitoring Systems

    Mukkamala, Ravi; Sixto, S. L. (Technical Monitor)


    During the two-year project period, we have worked on several aspects of Health Usage and Monitoring Systems for structural health monitoring. In particular, we have made contributions in the following areas. 1. Reference HUMS architecture: We developed a high-level architecture for health monitoring and usage systems (HUMS). The proposed reference architecture is shown. It is compatible with the Generic Open Architecture (GOA) proposed as a standard for avionics systems. 2. HUMS kernel: One of the critical layers of HUMS reference architecture is the HUMS kernel. We developed a detailed design of a kernel to implement the high level architecture.3. Prototype implementation of HUMS kernel: We have implemented a preliminary version of the HUMS kernel on a Unix platform.We have implemented both a centralized system version and a distributed version. 4. SCRAMNet and HUMS: SCRAMNet (Shared Common Random Access Memory Network) is a system that is found to be suitable to implement HUMS. For this reason, we have conducted a simulation study to determine its stability in handling the input data rates in HUMS. 5. Architectural specification.

  1. Signal and image processing systems performance evaluation, simulation, and modeling; Proceedings of the Meeting, Orlando, FL, Apr. 4, 5, 1991

    Nasr, Hatem N.; Bazakos, Michael E.

    The various aspects of the evaluation and modeling problems in algorithms, sensors, and systems are addressed. Consideration is given to a generic modular imaging IR signal processor, real-time architecture based on the image-processing module family, application of the Proto Ware simulation testbed to the design and evaluation of advanced avionics, development of a fire-and-forget imaging infrared seeker missile simulation, an adaptive morphological filter for image processing, laboratory development of a nonlinear optical tracking filter, a dynamic end-to-end model testbed for IR detection algorithms, wind tunnel model aircraft attitude and motion analysis, an information-theoretic approach to optimal quantization, parametric analysis of target/decoy performance, neural networks for automated target recognition parameters adaptation, performance evaluation of a texture-based segmentation algorithm, evaluation of image tracker algorithms, and multisensor fusion methodologies. (No individual items are abstracted in this volume)

  2. Testing the Preliminary X-33 Navigation System

    Lomas, James J.; Mitchell, Daniel W.; Freestone, Todd M.; Lee, Charles; Lessman, Craig; Foster, Lee D. (Technical Monitor)


    The X-33 Reusable Launch Vehicle (RLV) must meet the demanding requirements of landing autonomously on a narrow landing strip following a flight that reaches an altitude of up to 200,000 feet and a speed in excess of Mach 9 with significant in-flight energy bleed-off maneuvers. To execute this flight regimen a highly reliable avionics system has been designed that includes three LN-100G Inertial Navigation System/Global Positioning System (INS/GPS) units as the primary navigation system for the X-33. NASA's Marshall Space Flight Center (MSFC) tested an INS/GPS system in real-time simulations to determine the ability of this navigation suite to meet the in flight and autonomous landing requirements of the X-33 RLV. A total of sixty-one open loop tests were performed to characterize the navigation accuracy of the LN-100G. Twenty-seven closed-loop tests were also performed to evaluate the performance of the X-33 Guidance, Navigation and Control (GN&C) algorithms with the real navigation hardware. These closed-loop tests were also designed to expose any integration or operational issues with the real-time X-33 vehicle simulation. Dynamic road tests of the INS/GPS were conducted by Litton to assess the performance of differential and nondifferential INS/GPS hybrid navigation solutions. The results of the simulations and road testing demonstrate that this novel solution is capable of meeting the demanding requirements of take-off, in-flight navigation, and autonomous landing of the X-33 RLV. This paper describes the test environment developed to stimulate the LN-100G and discusses the results of this test effort. This paper also presents recommendations for a navigation system suitable to an operational RLV system.

  3. Programming of Energy Storage System in an Island Microgrid with Photovoltaic and Fuel Cell

    Hossein KHORRAMDEL


    Full Text Available Photovoltaic (PV systems in island microgrids (MGs are becoming increasingly attractive as a means of energy generation, due to new developments in technologies, environmental concerns, and transmission congestion management. Usually, the energy storage system (ESS is used to store the excess power generated during off-peak hours, and to return it to the system when power from PV is not enough for the system, or generation is more expensive. A real-time dynamic programming algorithm for energy storage in a PV/battery system, based on the battery charge and discharge characteristics, and current and temperature dependence of the capacity of the battery, is presented in this paper. The work aims to extend existing battery- aware programming techniques. It differs from previous works, as it takes into consideration many aspects of battery characteristics that were not considered previously. This allows better use of the battery bank and can prolong the battery service time. This paper also builds a simple PV/battery system in an island microgrid. In this paper, fuel cell power plants (FCPPs are permanently used to operate in island microgrids, and 2 batteries are used as reserves for charge and discharge in various hours.

  4. Advanced Microelectronics Technologies for Future Small Satellite Systems

    Alkalai, Leon


    Future small satellite systems for both Earth observation as well as deep-space exploration are greatly enabled by the technological advances in deep sub-micron microelectronics technologies. Whereas these technological advances are being fueled by the commercial (non-space) industries, more recently there has been an exciting new synergism evolving between the two otherwise disjointed markets. In other words, both the commercial and space industries are enabled by advances in low-power, highly integrated, miniaturized (low-volume), lightweight, and reliable real-time embedded systems. Recent announcements by commercial semiconductor manufacturers to introduce Silicon On Insulator (SOI) technology into their commercial product lines is driven by the need for high-performance low-power integrated devices. Moreover, SOI has been the technology of choice for many space semiconductor manufacturers where radiation requirements are critical. This technology has inherent radiation latch-up immunity built into the process, which makes it very attractive to space applications. In this paper, we describe the advanced microelectronics and avionics technologies under development by NASA's Deep Space Systems Technology Program (also known as X2000). These technologies are of significant benefit to both the commercial satellite as well as the deep-space and Earth orbiting science missions. Such a synergistic technology roadmap may truly enable quick turn-around, low-cost, and highly capable small satellite systems for both Earth observation as well as deep-space missions.

  5. Hierarchical Control for Multiple DC-Microgrids Clusters

    Shafiee, Qobad; Dragicevic, Tomislav; Vasquez, Juan Carlos


    DC microgrids (MGs) have gained research interest during the recent years because of many potential advantages as compared to the ac system. To ensure reliable operation of a low-voltage dc MG as well as its intelligent operation with the other DC MGs, a hierarchical control is proposed in this p......DC microgrids (MGs) have gained research interest during the recent years because of many potential advantages as compared to the ac system. To ensure reliable operation of a low-voltage dc MG as well as its intelligent operation with the other DC MGs, a hierarchical control is proposed...

  6. Financial Condition of Government Contractors and Control of Production Costs in the Procurement of Major DoD Aircraft Weapon Systems


    Technology ( FLYTECH )=ASP; 3. Weapons and Avionics System Technology (SYSTECH) =ASP/AP. The SYSTECH measure was derived from the two others and was a rough...PLA7TECH SYSTECH FLYTECH I A-IJ 6.57 0.50837 3.34 2 A- I7EG’H 6.S7 0.s0877 1-.4 A- :AI 1 32.8 0.87645 10.74 4 -4C 6. N !.076: 5.45 5 -464 7.33 i.162S s.S...0001 Variance explained (R’): .5812 Adjusted R’-. .5719 F Value: 62.44 Model Significance: .0001 FLYTECH =-30.943 4 .7063 YEAR 8.386 .0001 Variance

  7. Merging Autopilot/Flight Control and Navigation-Flight Management Systems

    Khaleel Qutbodin


    Full Text Available In this abstract the following commercial aircraft 3 avionics systems will be merged together: (1 Autopilot Flight Director System (APFDS, (2 Flight Control System (FCS and (3 Flight Management Systems (FMS. Problem statement: These systems perform functions that are dependant and related to each other, also they consists of similar hardware components. Each of these systems consists of at least one computer, control panel and displays that place on view the selection and aircraft response. They receive several similar sensor inputs, or outputs of one system are fed as input to the other system. By combining the three systems, repeated and related functions are reduced. Since these systems perform related functions, designers and programmers verify that conflict between these systems is not present. Combining the three systems will eliminate such possibility. Also used space, weight, wires and connections are decreased, consequently electrical consumption is reduced. To keep redundancy, the new system can be made of multiple channels. Approach: The new system (called Autopilot Navigation Management System, APNMS is more efficient and resolves the above mention drawbacks. Results: The APFDS system functions (as attitude-hold or heading-hold are merged with the FCS system main function which is controlling flight control surfaces as well as other functions as flight protection, Turn coordination and flight stability augmentation. Also the Flight Management system functions (as flight planning, aircraft flight performance/engine thrust management are merged in the new system. All this is done through combining all 3 systems logic software’s. Conclusion/Recommendations: The new APNMS system can be installed and tested on prototype aircraft in order to verify its benefits and fruits to the aviation industry.

  8. A highly reliable, autonomous data communication subsystem for an advanced information processing system

    Nagle, Gail; Masotto, Thomas; Alger, Linda


    The need to meet the stringent performance and reliability requirements of advanced avionics systems has frequently led to implementations which are tailored to a specific application and are therefore difficult to modify or extend. Furthermore, many integrated flight critical systems are input/output intensive. By using a design methodology which customizes the input/output mechanism for each new application, the cost of implementing new systems becomes prohibitively expensive. One solution to this dilemma is to design computer systems and input/output subsystems which are general purpose, but which can be easily configured to support the needs of a specific application. The Advanced Information Processing System (AIPS), currently under development has these characteristics. The design and implementation of the prototype I/O communication system for AIPS is described. AIPS addresses reliability issues related to data communications by the use of reconfigurable I/O networks. When a fault or damage event occurs, communication is restored to functioning parts of the network and the failed or damage components are isolated. Performance issues are addressed by using a parallelized computer architecture which decouples Input/Output (I/O) redundancy management and I/O processing from the computational stream of an application. The autonomous nature of the system derives from the highly automated and independent manner in which I/O transactions are conducted for the application as well as from the fact that the hardware redundancy management is entirely transparent to the application.

  9. A method for predicting errors when interacting with finite state systems. How implicit learning shapes the user's knowledge of a system

    Javaux, Denis


    This paper describes a method for predicting the errors that may appear when human operators or users interact with systems behaving as finite state systems. The method is a generalization of a method used for predicting errors when interacting with autopilot modes on modern, highly computerized airliners [Proc 17th Digital Avionics Sys Conf (DASC) (1998); Proc 10th Int Symp Aviat Psychol (1999)]. A cognitive model based on spreading activation networks is used for predicting the user's model of the system and its impact on the production of errors. The model strongly posits the importance of implicit learning in user-system interaction and its possible detrimental influence on users' knowledge of the system. An experiment conducted with Airbus Industrie and a major European airline on pilots' knowledge of autopilot behavior on the A340-200/300 confirms the model predictions, and in particular the impact of the frequencies with which specific state transitions and contexts are experienced.

  10. Future Standardization of Space Telecommunications Radio System with Core Flight System

    Briones, Janette C.; Hickey, Joseph P.; Roche, Rigoberto; Handler, Louis M.; Hall, Charles S.


    NASA Glenn Research Center (GRC) is integrating the NASA Space Telecommunications Radio System (STRS) Standard with the Core Flight System (cFS), an avionics software operating environment. The STRS standard provides a common, consistent framework to develop, qualify, operate and maintain complex, reconfigurable and reprogrammable radio systems. The cFS is a flexible, open architecture that features a plugand- play software executive called the Core Flight Executive (cFE), a reusable library of software components for flight and space missions and an integrated tool suite. Together, STRS and cFS create a development environment that allows for STRS compliant applications to reference the STRS application programmer interfaces (APIs) that use the cFS infrastructure. These APIs are used to standardize the communication protocols on NASAs space SDRs. The cFS-STRS Operating Environment (OE) is a portable cFS library, which adds the ability to run STRS applications on existing cFS platforms. The purpose of this paper is to discuss the cFS-STRS OE prototype, preliminary experimental results performed using the Advanced Space Radio Platform (ASRP), the GRC S- band Ground Station and the SCaN (Space Communication and Navigation) Testbed currently flying onboard the International Space Station (ISS). Additionally, this paper presents a demonstration of the Consultative Committee for Space Data Systems (CCSDS) Spacecraft Onboard Interface Services (SOIS) using electronic data sheets (EDS) inside cFE. This configuration allows for the data sheets to specify binary formats for data exchange between STRS applications. The integration of STRS with cFS leverages mission-proven platform functions and mitigates barriers to integration with future missions. This reduces flight software development time and the costs of software-defined radio (SDR) platforms. Furthermore, the combined benefits of STRS standardization with the flexibility of cFS provide an effective, reliable and

  11. Architecture Level Safety Analyses for Safety-Critical Systems

    K. S. Kushal


    Full Text Available The dependency of complex embedded Safety-Critical Systems across Avionics and Aerospace domains on their underlying software and hardware components has gradually increased with progression in time. Such application domain systems are developed based on a complex integrated architecture, which is modular in nature. Engineering practices assured with system safety standards to manage the failure, faulty, and unsafe operational conditions are very much necessary. System safety analyses involve the analysis of complex software architecture of the system, a major aspect in leading to fatal consequences in the behaviour of Safety-Critical Systems, and provide high reliability and dependability factors during their development. In this paper, we propose an architecture fault modeling and the safety analyses approach that will aid in identifying and eliminating the design flaws. The formal foundations of SAE Architecture Analysis & Design Language (AADL augmented with the Error Model Annex (EMV are discussed. The fault propagation, failure behaviour, and the composite behaviour of the design flaws/failures are considered for architecture safety analysis. The illustration of the proposed approach is validated by implementing the Speed Control Unit of Power-Boat Autopilot (PBA system. The Error Model Annex (EMV is guided with the pattern of consideration and inclusion of probable failure scenarios and propagation of fault conditions in the Speed Control Unit of Power-Boat Autopilot (PBA. This helps in validating the system architecture with the detection of the error event in the model and its impact in the operational environment. This also provides an insight of the certification impact that these exceptional conditions pose at various criticality levels and design assurance levels and its implications in verifying and validating the designs.

  12. 40° image intensifier tubes in an integrated helmet system

    Schreyer, Herbert; Boehm, Hans-Dieter V.; Svedevall, B.


    EUROCOPTER has been under contract to the French and German ministries of defence for five years to develop the TIGER, a second generation anti-tank helicopter. A piloting thermal imager has been installed on a steerable platform in the helicopter nose in order to achieve the possibility of flying round the clock. In addition to this sensor, which is sensitive at a wavelength of 10 micrometers , the German side has proposed using an Integrated Helmet System in the PAH 2. This helmet, manufactured by GEC-Marconi Avionics, incorporates two cathode ray tubes (CRT) and two image intensifier tubes which allow the pilot to use an additional sensor in the visible and near infrared spectrum. The electronic part will be built by Teldix. EUROCOPTER DEUTSCHLAND has received the first demonstrator of this helmet for testing in the EUROCOPTER Visionics Laboratory. Later, the C-prototype will be integrated into a BK 117 helicopter (AVT Avionik Versuchstrager). This new helmet has a field of view of 40 degree(s), and exit pupil of 15 mm and improved possibilities of adjusting the optical part. Laboratory tests have been carried out to test important parameters like optical resolution under low light level conditions, field of view, eye relief or exit pupil. The CRT channels have been tested for resolution, distortion, vignetting and homogeneity. The requirements and the properties of the helmet, test procedures and the results of these tests are presented in the paper.

  13. Telemetry System Utilization for Stress Monitoring of Pilots During Training

    Luboš Socha


    Full Text Available Air transport development brings an increased focus on the safety of piloting. The safety conditions can be assessed by mental workload. Psychic discomfort or excessive stress on pilots can negatively influence the course of flights. Therefore it appears convenient to monitor such parameters, which represent the mental wellbeing, or discomfort of a pilot. Since physiological measurements can provide a good information about mental workload or stress, this work primarily focuses on the observation of the change in heart rate, as it is an indicator of stress during the training of pilots, using the designed modular telemetry system. Another aim of this study is to evaluate the influence of a change in the avionic data visualization. This can have an unfavorable effect on the piloting of an airplane. This work, based on the evaluation of heart rate shows, that the switch from analog visualization to glass cockpit creates increased levels of stress in pilots, which was proved for all examined subjects except one. Significant level of correlation in the heart beat rate change in subjects in the course of training was also discovered.

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

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

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

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

  16. Aging Methodologies and Prognostic Health Management for Electrolytic Capacitors

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

  17. An Energy-Based Control Strategy for Battery Energy Storage Systems: A Case Study on Microgrid Applications

    Rui Hou


    Full Text Available Battery energy storage systems (BESSs with proportional-integral (PI control methods have been widely studied in microgrids (MGs. However, the performance of PI control methods might be unsatisfactory for BESSs due to the nonlinear characteristics of the system. To overcome this problem, an energy-based (EB control method is applied to control the converter of a BESS in this study. The EB method is a robust nonlinear control method based on passivity theory with good performance in both transient and steady states. The detailed design process of the EB method in the BESS by adopting an interconnection and damping assignment (IDA strategy is described. The design process comprises three steps: the construction of the port-controlled Hamiltonian model, the determination of the equilibrium point and the solution of the undetermined matrix. In addition, integral action is combined to eliminate the steady state error generated by the model mismatch. To establish the correctness and validity of the proposed method, we implement several case simulation studies based on a test MG system and compare the control performance of the EB and PI methods carefully. The case simulation results demonstrate that the EB method has better tracking and anti-disturbance performance compared with the classic PI method. Moreover, the proposed EB method shows stronger robustness to the uncertainty of system parameters.

  18. Fiber-Optic Magnetic-Field-Strength Measurement System for Lightning Detection

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


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

  19. Distributed Renewable Generation and Storage System Sizing Based on Smart Dispatch of Microgrids

    Raji Atia


    Full Text Available This paper considers the contribution of independent owners (IOs operating within microgrids (MGs toward green power generation in deregulated energy markets. An optimization scheme is introduced for sizing distributed renewable generation (DRG and a distributed energy storage system (DESS based on a novel energy management system (EMS that accounts for demand response (DR, DESS dispatch and performance degradation, dynamic pricing environments, power distribution loss and irregular renewable generation. The proposed EMS utilizes an iterative Newton-Raphson linear programming algorithm that schedules resources in order to minimize the objective function, to deal with the complicated nonlinear nature of the problem and to enable efficient long-term assessments. The EMS is used to evaluate candidate solutions that are generated by a genetic algorithm (GA to determine the optimal combination of DRG and DESS. A case study for IEEE 34-bus distribution MG in Okinawa, Japan, is used for testing the algorithm and analyzing the potential for IO/MG investments and their strategies.

  20. Demonstration of 6DOF Arc-mim/mm Control in the FCT Using Proba-3 Metrology and Control System Project

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