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

Data.gov (United States)

National Aeronautics and Space Administration — Autonomous, avionic and robotic systems are used in a variety of applications including launch vehicles, robotic precursor platforms, etc. Most avionic innovations...

Electronics/avionics integrity - Definition, measurement and improvement

Science.gov (United States)

Kolarik, W.; Rasty, J.; Chen, M.; Kim, Y.

The authors report on the results obtained from an extensive, three-fold research project: (1) to search the open quality and reliability literature for documented information relative to electronics/avionics integrity; (2) to interpret and evaluate the literature as to significant concepts, strategies, and tools appropriate for use in electronics/avionics product and process integrity efforts; and (3) to develop a list of critical findings and recommendations that will lead to significant progress in product integrity definition, measurement, modeling, and improvements. The research consisted of examining a broad range of trade journals, scientific journals, and technical reports, as well as face-to-face discussions with reliability professionals. Ten significant recommendations have been supported by the research work.

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

Science.gov (United States)

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

2013-01-01

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

Investigation of an advanced fault tolerant integrated avionics system

Science.gov (United States)

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

1986-01-01

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

MATHEMATICAL MODELS OF PROCESSES AND SYSTEMS OF TECHNICAL OPERATION FOR ONBOARD COMPLEXES AND FUNCTIONAL SYSTEMS OF AVIONICS

Directory of Open Access Journals (Sweden)

Sergey Viktorovich Kuznetsov

2017-01-01

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

Demonstration Advanced Avionics System (DAAS) function description

Science.gov (United States)

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

1982-01-01

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

An assessment of General Aviation utilization of advanced avionics technology

Science.gov (United States)

Quinby, G. F.

1980-01-01

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

Synchronous Modeling of Modular Avionics Architectures using the SIGNAL Language

OpenAIRE

Gamatié , Abdoulaye; Gautier , Thierry

2002-01-01

This document presents a study on the modeling of architecture components for avionics applications. We consider the avionics standard ARINC 653 specifications as basis, as well as the synchronous language SIGNAL to describe the modeling. A library of APEX object models (partition, process, communication and synchronization services, etc.) has been implemented. This should allow to describe distributed real-time applications using POLYCHRONY, so as to access formal tools and techniques for ar...

A Model-based Avionic Prognostic Reasoner (MAPR)

Data.gov (United States)

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

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

Science.gov (United States)

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

1990-01-01

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

Heavy Lift Vehicle (HLV) Avionics Flight Computing Architecture Study

Science.gov (United States)

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

2011-01-01

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

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

Science.gov (United States)

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

2012-01-01

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

Avionic Data Bus Integration Technology

Science.gov (United States)

1991-12-01

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

A method of distributed avionics data processing based on SVM classifier

Science.gov (United States)

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

2018-03-01

Under the environment of system combat, in order to solve the problem on management and analysis of the massive heterogeneous data on multi-platform avionics system, this paper proposes a management solution which called avionics "resource cloud" based on big data technology, and designs an aided decision classifier based on SVM algorithm. We design an experiment with STK simulation, the result shows that this method has a high accuracy and a broad application prospect.

Avionics for Hibernation and Recovery on Planetary Surfaces

Data.gov (United States)

National Aeronautics and Space Administration — Landers and rovers endure on the Martian equator but experience avionics failures in the cryogenic temperatures of lunar nights and Martian winters. The greatest...

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

Science.gov (United States)

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

1978-01-01

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

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

Data.gov (United States)

National Aeronautics and Space Administration — The Integrated Power, Avionics, and Software (IPAS) facility is a flexible, multi-mission hardware and software design environment. This project will develop a...

Sail GTS ground system analysis: Avionics system engineering

Science.gov (United States)

Lawton, R. M.

1977-01-01

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

Rad-hard Smallsat / CubeSat Avionics Board, Phase I

Data.gov (United States)

National Aeronautics and Space Administration — VORAGO will design a rad-hard Smallsat / CubeSat Avionics single board that has the necessary robustness needed for long duration missions in harsh mission...

Micro-Scale Avionics Thermal Management

Science.gov (United States)

Moran, Matthew E.

2001-01-01

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

A critique of reliability prediction techniques for avionics applications

Directory of Open Access Journals (Sweden)

Guru Prasad PANDIAN

2018-01-01

Full Text Available Avionics (aeronautics and aerospace industries must rely on components and systems of demonstrated high reliability. For this, handbook-based methods have been traditionally used to design for reliability, develop test plans, and define maintenance requirements and sustainment logistics. However, these methods have been criticized as flawed and leading to inaccurate and misleading results. In its recent report on enhancing defense system reliability, the U.S. National Academy of Sciences has recently discredited these methods, judging the Military Handbook (MIL-HDBK-217 and its progeny as invalid and inaccurate. This paper discusses the issues that arise with the use of handbook-based methods in commercial and military avionics applications. Alternative approaches to reliability design (and its demonstration are also discussed, including similarity analysis, testing, physics-of-failure, and data analytics for prognostics and systems health management.

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

Science.gov (United States)

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

1991-01-01

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

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

Science.gov (United States)

Nelson, Kurt

1991-01-01

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

Avionics System Development for a Rotary Wing Unmanned Aerial Vehicle

National Research Council Canada - National Science Library

Greer, Daniel

1998-01-01

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

New Technologies for Space Avionics, 1993

Science.gov (United States)

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

1993-01-01

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

Non-functional Avionics Requirements

Science.gov (United States)

Paulitsch, Michael; Ruess, Harald; Sorea, Maria

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

Advanced Avionics and Processor Systems for a Flexible Space Exploration Architecture

Science.gov (United States)

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

2010-01-01

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

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

Directory of Open Access Journals (Sweden)

Peng Wang

2018-01-01

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

Development of a Comprehensive Digital Avionics Curriculum for the Aeronautical Engineer

National Research Council Canada - National Science Library

Hofer, Thomas W

2006-01-01

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

Power, Avionics and Software Communication Network Architecture

Science.gov (United States)

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

2014-01-01

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

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

Science.gov (United States)

Orr, James K.; Peltier, Daryl

2010-01-01

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

The effect of requirements prioritization on avionics system conceptual design

Science.gov (United States)

Lorentz, John

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

Software testability and its application to avionic software

Science.gov (United States)

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

1993-01-01

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

IXV avionics architecture: Design, qualification and mission results

Science.gov (United States)

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

2016-07-01

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

A Modeling Framework for Schedulability Analysis of Distributed Avionics Systems

DEFF Research Database (Denmark)

Han, Pujie; Zhai, Zhengjun; Nielsen, Brian

2018-01-01

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

An electronic flight bag for NextGen avionics

Science.gov (United States)

Zelazo, D. Eyton

2012-06-01

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

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

Science.gov (United States)

Latorella, Kara A.

2015-01-01

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

The MGS Avionics System Architecture: Exploring the Limits of Inheritance

Science.gov (United States)

Bunker, R.

1994-01-01

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

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

Science.gov (United States)

Young, D. A.

1984-01-01

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

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

Data.gov (United States)

National Aeronautics and Space Administration — Substantial progress has been made by NASA in integrating flight avionics and ISHM with well-defined caution and warning system, however, the scope of ACAW alerting...

Development of Integrated Modular Avionics Application Based on Simulink and XtratuM

Science.gov (United States)

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

2013-08-01

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

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

Science.gov (United States)

1974-01-01

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

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

Science.gov (United States)

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

1984-01-01

Fiber optic transmission is emerging as an attractive concept in data distribution onboard civil aircraft. Development of an Optical Data Distribution Network for Integrated Avionics and Control Systems for commercial aircraft will provide a data distribution network that gives freedom from EMI-RFI and ground loop problems, eliminates crosstalk and short circuits, provides protection and immunity from lightning induced transients and give a large bandwidth data transmission capability. In addition there is a potential for significantly reducing the weight and increasing the reliability over conventional data distribution networks. Wavelength Division Multiplexing (WDM) is a candidate method for data communication between the various avionic subsystems. With WDM all systems could conceptually communicate with each other without time sharing and requiring complicated coding schemes for each computer and subsystem to recognize a message. However, the state of the art of optical technology limits the application of fiber optics in advanced integrated avionics and control systems. Therefore, it is necessary to address the architecture for a fiber optics data distribution system for integrated avionics and control systems as well as develop prototype components and systems.

Integrated Modular Avionics for Spacecraft: Earth Observation Use Case Demonstrator

Science.gov (United States)

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

2013-08-01

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

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

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Larsen, William E.; Carro, Anthony

1986-01-01

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

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

Science.gov (United States)

Kulkarni, Nilesh; Krishnakumar, Kalmaje

2005-01-01

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

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

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Feng HE

2017-12-01

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

Industry perspectives on Plug-& -Play Spacecraft Avionics

Science.gov (United States)

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

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

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

Science.gov (United States)

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

1974-01-01

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

NI Based System for Seu Testing of Memory Chips for Avionics

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Boruzdina Anna

2016-01-01

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.

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

Science.gov (United States)

Ferguson, Stan; Savage, Dick

1992-01-01

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

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

Science.gov (United States)

1993-11-01

interaction between a digital data bus and an avionic system. Very Large Scale Integration (VLSI) ICs and multiversion software, which make up digital...1984, the Sperry Corporation developed a fault tolerant system which employed multiversion programming, voting, and monitoring for error detection and...formulate all the significant behavior of a system. MULTIVERSION PROGRAMMING. N-version programming. N-VERSION PROGRAMMING. The independent coding of a

Integrated communication, navigation, and identification avionics: Impact analysis. Executive summary

Science.gov (United States)

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

1985-10-01

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

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

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Coffey, Connor

2015-01-01

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

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

Science.gov (United States)

Ivancic, William D.

2007-01-01

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

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

Science.gov (United States)

1984-12-01

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

Semiautonomous Avionics-and-Sensors System for a UAV

Science.gov (United States)

Shams, Qamar

2006-01-01

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

Validating Avionics Conceptual Architectures with Executable Specifications

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Nils Fischer

2012-08-01

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.

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

Science.gov (United States)

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

2014-01-01

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

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

Science.gov (United States)

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

2014-01-01

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

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

Directory of Open Access Journals (Sweden)

Anna V. Korneenkova

2017-01-01

Full Text Available The framework is made to provide tools to develop the integrated modular avionics (IMA applications, which could be launched on the target platform LynxOs-178 without modifying their source code. The framework usage helps students to form skills for developing modern modules of the avionics. In addition, students obtain deeper knowledge for the development of competencies in the field of technical creativity by using of the framework.The article describes the architecture and implementation of the Linux OS framework for ARINC653 compliant OS application development.The proposed approach reduces ARINC-653 application development costs and gives a unified tool to implement OS vendor independent code that meets specification. To achieve import substitution free and open-source Linux OS is used as an environment for developing IMA applications.The proposed framework is applicable for using as the tool to develop IMA applications and as the tool for development of the following competencies: the ability to master techniques of using software to solve practical problems, the ability to develop components of hardware and software systems and databases, using modern tools and programming techniques, the ability to match hardware and software tools in the information and automated systems, the readiness to apply the fundamentals of informatics and programming to designing, constructing and testing of software products, the readiness to apply basic methods and tools of software development, knowledge of various technologies of software development.

CanOpen on RASTA: The Integration of the CanOpen IP Core in the Avionics Testbed

Science.gov (United States)

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

2013-08-01

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

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

Science.gov (United States)

Seals, J. D.

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

Reconfigurable fault tolerant avionics system

Science.gov (United States)

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

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

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

International Nuclear Information System (INIS)

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

2013-01-01

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

THE UNMANNED MISSION AVIONICS TEST HELICIOPTER – A FLEXIBLE AND VERSATILE VTOL-UAS EXPERIMENTAL SYSTEM

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Dr. H.-W. Schulz

2012-09-01

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.

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

Science.gov (United States)

1982-11-01

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

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

Science.gov (United States)

Kuehl, C. Stephen

1996-06-01

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

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

Science.gov (United States)

Stehura, Aaron; Rozek, Matthew

2013-01-01

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

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

Science.gov (United States)

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

2011-01-01

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

Avionics Systems Laboratory/Building 16. Historical Documentation

Science.gov (United States)

Slovinac, Patricia; Deming, Joan

2011-01-01

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

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

Directory of Open Access Journals (Sweden)

X. Prats

2007-04-01

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

Enabling Wireless Avionics Intra-Communications

Science.gov (United States)

Torres, Omar; Nguyen, Truong; Mackenzie, Anne

2016-01-01

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.

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

Science.gov (United States)

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

1989-01-01

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

DISEÑO E IMPLEMENTACIÓN DEL SISTEMA DE COMUNICACIONES BASADO EN CAN PARA LA AVIÓNICA EN UN VEHÍCULO AÉREO AUTÓNOMO NO TRIPULADO DESIGN AND IMPLEMENTATION OF A COMMUNICATION SYSTEM BASED ON CAN FOR AVIONICS IN A ROBOT MINI-HELICOPTER

Directory of Open Access Journals (Sweden)

Jairo Miguel Vergara Díaz

2007-07-01

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.

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

Energy Technology Data Exchange (ETDEWEB)

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

2004-03-01

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)

Expanding AirSTAR Capability for Flight Research in an Existing Avionics Design

Science.gov (United States)

Laughter, Sean A.

2012-01-01

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

Use of Field Programmable Gate Array Technology in Future Space Avionics

Science.gov (United States)

Ferguson, Roscoe C.; Tate, Robert

2005-01-01

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

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)

Science.gov (United States)

1992-02-01

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

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

Directory of Open Access Journals (Sweden)

Lisong Wang

2018-01-01

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

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

Science.gov (United States)

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

2008-02-01

Low cost and intrinsic performances of 850 nm Vertical Cavity Surface Emitting Lasers (VCSELs) compared to Light Emitting Diodes make them very attractive for high speed and short distances data communication links through optical fibers. Weight saving and Electromagnetic Interference withstanding requirements have led to the need of a reliable solution to improve existing avionics high speed buses (e.g. AFDX) up to 1Gbps over 100m. To predict and optimize the performance of the link, the physical behavior of the VCSEL must be well understood. First, a theoretical study is performed through the rate equations adapted to VCSEL in large signal modulation. Averaged turn-on delays and oscillation effects are analytically computed and analyzed for different values of the on- and off state currents. This will affect the eye pattern, timing jitter and Bit Error Rate (BER) of the signal that must remain within IEEE 802.3 standard limits. In particular, the off-state current is minimized below the threshold to allow the highest possible Extinction Ratio. At this level, the spontaneous emission is dominating and leads to significant turn-on delay, turn-on jitter and bit pattern effects. Also, the transverse multimode behavior of VCSELs, caused by Spatial Hole Burning leads to some dispersion in the fiber and degradation of BER. VCSEL to Multimode Fiber coupling model is provided for prediction and optimization of modal dispersion. Lastly, turn-on delay measurements are performed on a real mock-up and results are compared with calculations.

Computer architecture for efficient algorithmic executions in real-time systems: New technology for avionics systems and advanced space vehicles

Science.gov (United States)

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

1987-01-01

Improvements and advances in the development of computer architecture now provide innovative technology for the recasting of traditional sequential solutions into high-performance, low-cost, parallel system to increase system performance. Research conducted in development of specialized computer architecture for the algorithmic execution of an avionics system, guidance and control problem in real time is described. A comprehensive treatment of both the hardware and software structures of a customized computer which performs real-time computation of guidance commands with updated estimates of target motion and time-to-go is presented. An optimal, real-time allocation algorithm was developed which maps the algorithmic tasks onto the processing elements. This allocation is based on the critical path analysis. The final stage is the design and development of the hardware structures suitable for the efficient execution of the allocated task graph. The processing element is designed for rapid execution of the allocated tasks. Fault tolerance is a key feature of the overall architecture. Parallel numerical integration techniques, tasks definitions, and allocation algorithms are discussed. The parallel implementation is analytically verified and the experimental results are presented. The design of the data-driven computer architecture, customized for the execution of the particular algorithm, is discussed.

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

Science.gov (United States)

Shalkhauser, Mary Jo W.; Roche, Rigoberto

2017-01-01

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.

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

Science.gov (United States)

Shalkhauser, Mary Jo W.; Roche, Rigoberto

2017-01-01

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.

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

Energy Technology Data Exchange (ETDEWEB)

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

1999-07-01

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.)

Highly-hermetic feedthrough fiber pigtailed circular TO-can electro-optic sensor for avionics applications

Science.gov (United States)

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

2012-06-01

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

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

Science.gov (United States)

Gardi, Alessandro; Sabatini, Roberto; Ramasamy, Subramanian

2016-05-01

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

A study of compositional verification based IMA integration method

Science.gov (United States)

Huang, Hui; Zhang, Guoquan; Xu, Wanmeng

2018-03-01

The rapid development of avionics systems is driving the application of integrated modular avionics (IMA) systems. But meanwhile it is improving avionics system integration, complexity of system test. Then we need simplify the method of IMA system test. The IMA system supports a module platform that runs multiple applications, and shares processing resources. Compared with federated avionics system, IMA system is difficult to isolate failure. Therefore, IMA system verification will face the critical problem is how to test shared resources of multiple application. For a simple avionics system, traditional test methods are easily realizing to test a whole system. But for a complex system, it is hard completed to totally test a huge and integrated avionics system. Then this paper provides using compositional-verification theory in IMA system test, so that reducing processes of test and improving efficiency, consequently economizing costs of IMA system integration.

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

Science.gov (United States)

Wray, Richard B.

1991-01-01

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.

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

Science.gov (United States)

Wray, Richard B.

1991-12-01

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.

Integrated Test Bed Facility

Data.gov (United States)

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

Survey of symbology for aeronautical charts and electronic displays : navigation aids, airports, lines, and linear patterns

Science.gov (United States)

2008-09-01

This industry survey documents the symbols for navigation aids, airports, lines, and linear patterns currently in use by avionics manufactureres and chart providers for depicting aeronautical charting information. Nine avionics display manufacturers ...

Euroopa kolm nobedaimat gaselli / Askur Alas

Index Scriptorium Estoniae

Alas, Askur, 1973-

2007-01-01

Euroopas 2006. aastal kõige kiiremini kasvanud keskmise suurusega ettevõtetest: Prantsuse IT-firma Gameloft, Islandi transpordi- ja logistikafirma Avion Group ning Prantsuse tehnoloogiafirma Assystem. Lisa: Gamelofti mängud; Gameloft, Avion Group, Assystem

Next generation space interconnect research and development in space communications

Science.gov (United States)

Collier, Charles Patrick

2017-11-01

Interconnect or "bus" is one of the critical technologies in design of spacecraft avionics systems that dictates its architecture and complexity. MIL-STD-1553B has long been used as the avionics backbone technology. As avionics systems become more and more capable and complex, however, limitations of MIL-STD-1553B such as insufficient 1 Mbps bandwidth and separability have forced current avionics architects and designers to use combination of different interconnect technologies in order to meet various requirements: CompactPCI is used for backplane interconnect; LVDS or RS422 is used for low and high-speed direct point-to-point interconnect; and some proprietary interconnect standards are designed for custom interfaces. This results in a very complicated system that consumes significant spacecraft mass and power and requires extensive resources in design, integration and testing of spacecraft systems.

Design and Development of a Rapid Research, Design, and Development Platform for In-Situ Testing of Tools and Concepts for Trajectory-Based Operations

Science.gov (United States)

Underwood, Matthew C.

2017-01-01

To provide justification for equipping a fleet of aircraft with avionics capable of supporting trajectory-based operations, significant flight testing must be accomplished. However, equipping aircraft with these avionics and enabling technologies to communicate the clearances required for trajectory-based operations is cost-challenging using conventional avionics approaches. This paper describes an approach to minimize the costs and risks of flight testing these technologies in-situ, discusses the test-bed platform developed, and highlights results from a proof-of-concept flight test campaign that demonstrates the feasibility and efficiency of this approach.

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

Science.gov (United States)

Bao, Lin

In the aerospace industry, with the development of avionic systems becomes more and more complex, the integrated modular avionics (IMA) architecture was proposed to replace its predecessor - the federated architecture, in order to reduce the weight, power consumption and the dimension of the avionics equipment. The research work presented in this thesis, which is considered as a part of the research project AVIO509, aims to propose to the aviation industry a set of time-effective and cost-effective solutions for the development and the functional validation of IMA systems. The proposed methodologies mainly focus on two design flows that are based on: 1) the concept of model-driven engineering design and 2) a cosimulation platform. In the first design flow, the modeling language AADL is used to describe the IMA architecture. The environment OCARINA, a code generator initially designed for POK, was modified so that it can generate avionic applications from an AADL model for the simulator SIMA (an IMA simulator compliant to the ARINC653 standards). In the second design flow, Simulink is used to simulate the external world of IMA module thanks to the availability of avionic library that can offer lots of avionics sensors and actuators, and as well as its effectiveness in creating the Simulink models. The cosimulation platform is composed of two simulators: Simulink for the simulation of peripherals and SIMA for the simulation of IMA module, the latter is considered as an ideal alternative for the super expensive commercial development environment. In order to have a good portability, a SIMA partition is reserved as the role of " adapter " to synchronize the communication between these two simulators via the TCP/IP protocol. When the avionics applications are ported to the implementation platform (such as PikeOS) after the simulation, there is only the " adapter " to be modified because the internal communication and the system configuration are the same. An avionics

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

Science.gov (United States)

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

2013-01-01

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

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

Science.gov (United States)

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

2017-01-01

NASA's first Air Traffic Management Technology Demonstration (ATD-1) subproject successfully completed a 19-day flight test of an Interval Management (IM) avionics prototype. The prototype was built based on IM standards, integrated into two test aircraft, and then flown in real-world conditions to determine if the goals of improving aircraft efficiency and airport throughput during high-density arrival operations could be met. The ATD-1 concept of operation integrates advanced arrival scheduling, controller decision support tools, and the IM avionics to enable multiple time-based arrival streams into a high-density terminal airspace. IM contributes by calculating airspeeds that enable an aircraft to achieve a spacing interval behind the preceding aircraft. The IM avionics uses its data (route of flight, position, etc.) and Automatic Dependent Surveillance-Broadcast (ADS-B) state data from the Target aircraft to calculate this airspeed. The flight test demonstrated that the IM avionics prototype met the spacing accuracy design goal for three of the four IM operation types tested. The primary issue requiring attention for future IM work is the high rate of IM speed commands and speed reversals. In total, during this flight test, the IM avionics prototype showed significant promise in contributing to the goals of improving aircraft efficiency and airport throughput.

Software for Avionics.

Science.gov (United States)

1983-01-01

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

Analyzing and Specifying Reusable Security Requirements

Science.gov (United States)

2003-09-01

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

Next Generation Reliable Transport Networks

DEFF Research Database (Denmark)

Zhang, Jiang

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

MINESTRONE

Science.gov (United States)

2015-03-01

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

An Approach for On-Board Software Building Blocks Cooperation and Interfaces Definition

Science.gov (United States)

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

2010-08-01

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

Structuring Formal Requirements Specifications for Reuse and Product Families

Science.gov (United States)

Heimdahl, Mats P. E.

2001-01-01

In this project we have investigated how formal specifications should be structured to allow for requirements reuse, product family engineering, and ease of requirements change, The contributions of this work include (1) a requirements specification methodology specifically targeted for critical avionics applications, (2) guidelines for how to structure state-based specifications to facilitate ease of change and reuse, and (3) examples from the avionics domain demonstrating the proposed approach.

Man-machine interface requirements - advanced technology

Science.gov (United States)

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

1984-01-01

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

An Evaluation of an Ada Implementation of the Rete Algorithm for Embedded Flight Processors

Science.gov (United States)

1990-12-01

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

The Design of Model-Based Training Programs

Science.gov (United States)

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

1997-01-01

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

Primary display latency criteria based on flying qualities and performance data

Science.gov (United States)

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

1993-01-01

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

A Comparison of Bus Architectures for Safety-Critical Embedded Systems

Science.gov (United States)

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

2003-01-01

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.

Orion FSW V and V and Kedalion Engineering Lab Insight

Science.gov (United States)

Mangieri, Mark L.

2010-01-01

NASA, along with its prime Orion contractor and its subcontractor s are adapting an avionics system paradigm borrowed from the manned commercial aircraft industry for use in manned space flight systems. Integrated Modular Avionics (IMA) techniques have been proven as a robust avionics solution for manned commercial aircraft (B737/777/787, MD 10/90). This presentation will outline current approaches to adapt IMA, along with its heritage FSW V&V paradigms, into NASA's manned space flight program for Orion. NASA's Kedalion engineering analysis lab is on the forefront of validating many of these contemporary IMA based techniques. Kedalion has already validated many of the proposed Orion FSW V&V paradigms using Orion's precursory Flight Test Article (FTA) Pad Abort 1 (PA-1) program. The Kedalion lab will evolve its architectures, tools, and techniques in parallel with the evolving Orion program.

Systems Engineering and Integration (SE and I)

Science.gov (United States)

Chevers, ED; Haley, Sam

1990-01-01

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

General Aviation Avionics Statistics.

Science.gov (United States)

1980-12-01

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

Avionics Design for Reliability

Science.gov (United States)

1976-03-01

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

On TTEthernet for Integrated Fault-Tolerant Spacecraft Networks

Science.gov (United States)

Loveless, Andrew

2015-01-01

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

Fleet retrofit report

Science.gov (United States)

1973-01-01

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

Enabling Dedicated, Affordable Space Access Through Aggressive Technology Maturation

Science.gov (United States)

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

2014-01-01

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

Autonomous Flight Rules Concept: User Implementation Costs and Strategies

Science.gov (United States)

Cotton, William B.; Hilb, Robert

2014-01-01

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

Regulatory Compliance in Multi-Tier Supplier Networks

Science.gov (United States)

Goossen, Emray R.; Buster, Duke A.

2014-01-01

Over the years, avionics systems have increased in complexity to the point where 1st tier suppliers to an aircraft OEM find it financially beneficial to outsource designs of subsystems to 2nd tier and at times to 3rd tier suppliers. Combined with challenging schedule and budgetary pressures, the environment in which safety-critical systems are being developed introduces new hurdles for regulatory agencies and industry. This new environment of both complex systems and tiered development has raised concerns in the ability of the designers to ensure safety considerations are fully addressed throughout the tier levels. This has also raised questions about the sufficiency of current regulatory guidance to ensure: proper flow down of safety awareness, avionics application understanding at the lower tiers, OEM and 1st tier oversight practices, and capabilities of lower tier suppliers. Therefore, NASA established a research project to address Regulatory Compliance in a Multi-tier Supplier Network. This research was divided into three major study efforts: 1. Describe Modern Multi-tier Avionics Development 2. Identify Current Issues in Achieving Safety and Regulatory Compliance 3. Short-term/Long-term Recommendations Toward Higher Assurance Confidence This report presents our findings of the risks, weaknesses, and our recommendations. It also includes a collection of industry-identified risks, an assessment of guideline weaknesses related to multi-tier development of complex avionics systems, and a postulation of potential modifications to guidelines to close the identified risks and weaknesses.

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

OpenAIRE

Alvarado Torres, Wilson Emilio; Alvarado Torres, Wilson Emilio

2001-01-01

El mundo moderno a desarrollado el programa LRCSW (Long-Range Conventional Standel Weapon). Este programa fue el encargado de estudiar, desarrollar y probar un vehículo llamado MC LRCSW (MC Tomahawk) también conocido como "Misil de Crucero de Alta Exactitud de Baja Altura (MCAEBA)". Este misil con la configuraci6n de navegaci6n descrita a continuaci6n se instal6 en 1995 en aviones B-52, porta aviones, submarinos y buques. La ruta de vuelo del MCAEBA se divide en dos partes: La parte ope...

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

OpenAIRE

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

2014-01-01

INTRODUCTION – L’exposition au bruit des avions pourrait avoir des conséquences importantes pour la santé. Toutefois, celles-ci sont actuellement insuffisamment évaluées, tout du moins en France. La DGS en collaboration avec l’Acnusa a donc sollicité l’Ifsttar pour mettre en place un programme de recherche épidémiologique appelé DEBATS. OBJECTIF – L’objectif est de mieux connaître et d’évaluer les effets du bruit des avions sur la santé des riverains...

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

OpenAIRE

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

2012-01-01

L’exposition au bruit des avions pourrait avoir des conséquences importantes pour la santé. Toutefois, celles-ci sont actuellement insuffisamment évaluées, tout du moins en France. La DGS en collaboration avec l’Acnusa a donc sollicité l’Ifsttar pour mettre en place un programme de recherche épidémiologique appelé DEBATS. L'objectif est de mieux connaître et mieux quantifier les effets du bruit des avions sur la santé en adoptant une approche globale caractérisant les relati...

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

Science.gov (United States)

Dowden, Donald J.; Bessette, Denis E.

1987-01-01

The AFTI F-16 Automated Maneuvering Attack System has undergone developmental and demonstration flight testing over a total of 347.3 flying hours in 237 sorties. The emphasis of this phase of the flight test program was on the development of automated guidance and control systems for air-to-air and air-to-ground weapons delivery, using a digital flight control system, dual avionics multiplex buses, an advanced FLIR sensor with laser ranger, integrated flight/fire-control software, advanced cockpit display and controls, and modified core Multinational Stage Improvement Program avionics.

An Ada Linear-Algebra Software Package Modeled After HAL/S

Science.gov (United States)

Klumpp, Allan R.; Lawson, Charles L.

1990-01-01

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

Investigation of single event latchup

International Nuclear Information System (INIS)

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

2012-01-01

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

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

OpenAIRE

Izquierdo Gil, Daniel

2011-01-01

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

Integrated Modular Avionics: The Challenges

Science.gov (United States)

Charrier, O.

2009-05-01

The need to reduce Space, Weight, and Power (SWaP) across the embedded market leads many Systems Suppliers to run multiple applications on the same processor. The concept seems deceptively simple. However, a lack of experience using this approach, may lead to many mistakes, resulting in unacceptable system performance and unacceptable costs. The objective of this paper is to review the challenges of controlling the execution of multiple applications on the same processor in a Safety or Mission Critical context and, based on return of experiences, point out some of the common mistakes and the limit of what an operating system can control. As no-one has an unlimited budget, the ability to develop and verify such system at reasonable cost, reduced risk, and re-use of the expended effort will be emphasized.

New technologies for space avionics

Science.gov (United States)

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

1994-01-01

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.

DFRC F-16 aircraft fleet and support crew

Science.gov (United States)

1995-01-01

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

The Legacy of Space Shuttle Flight Software

Science.gov (United States)

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

2011-01-01

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

Methodologie experimentale pour evaluer les caracteristiques des plateformes graphiques avioniques

Science.gov (United States)

Legault, Vincent

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

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

Science.gov (United States)

Rochala, Zdzisław

2012-02-01

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.

Optimisation des trajectoires verticales par la methode de la recherche de l'harmonie =

Science.gov (United States)

Ruby, Margaux

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

Operationally Responsive Spacecraft Subsystem, Phase I

Data.gov (United States)

National Aeronautics and Space Administration — Saber Astronautics proposes spacecraft subsystem control software which can autonomously reconfigure avionics for best performance during various mission conditions....

IVHM Framework for Intelligent Integration for Vehicle Health Management

Science.gov (United States)

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

2005-01-01

Integrated Vehicle Health Management (IVHM) systems for aerospace vehicles, is the process of assessing, preserving, and restoring system functionality across flight and techniques with sensor and communication technologies for spacecraft that can generate responses through detection, diagnosis, reasoning, and adapt to system faults in support of Integrated Intelligent Vehicle Management (IIVM). These real-time responses allow the IIVM to modify the affected vehicle subsystem(s) prior to a catastrophic event. Furthermore, this framework integrates technologies which can provide a continuous, intelligent, and adaptive health state of a vehicle and use this information to improve safety and reduce costs of operations. Recent investments in avionics, health management, and controls have been directed towards IIVM. As this concept has matured, it has become clear that IIVM requires the same sensors and processing capabilities as the real-time avionics functions to support diagnosis of subsystem problems. New sensors have been proposed, in addition to augment the avionics sensors to support better system monitoring and diagnostics. As the designs have been considered, a synergy has been realized where the real-time avionics can utilize sensors proposed for diagnostics and prognostics to make better real-time decisions in response to detected failures. IIVM provides for a single system allowing modularity of functions and hardware across the vehicle. The framework that supports IIVM consists of 11 major on-board functions necessary to fully manage a space vehicle maintaining crew safety and mission objectives. These systems include the following: Guidance and Navigation; Communications and Tracking; Vehicle Monitoring; Information Transport and Integration; Vehicle Diagnostics; Vehicle Prognostics; Vehicle Mission Planning, Automated Repair and Replacement; Vehicle Control; Human Computer Interface; and Onboard Verification and Validation. Furthermore, the presented

Case Study of Using High Performance Commercial Processors in Space

Science.gov (United States)

Ferguson, Roscoe C.; Olivas, Zulema

2009-01-01

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

Case Study of Using High Performance Commercial Processors in a Space Environment

Science.gov (United States)

Ferguson, Roscoe C.; Olivas, Zulema

2009-01-01

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

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

OpenAIRE

ZHOU, MI

2015-01-01

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

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

Data.gov (United States)

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

Health management and controls for Earth-to-orbit propulsion systems

Science.gov (United States)

Bickford, R. L.

1995-03-01

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

An autonomous rendezvous and docking system using cruise missile technologies

Science.gov (United States)

Jones, Ruel Edwin

1991-01-01

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

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

Data.gov (United States)

National Aeronautics and Space Administration — Current and future NASA exploration flight missions require Avionics systems, Computers, Controllers and Data processing units that are capable of enduring extreme...

Aging Methodologies and Prognostic Health Management for Electrolytic Capacitors

Data.gov (United States)

National Aeronautics and Space Administration — Understanding the ageing mechanisms of electronic components critical avionics systems such as the GPS and INAV are of critical importance. Electrolytic capacitors...

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

Data.gov (United States)

National Aeronautics and Space Administration — Electrolytic capacitors are used in several applications rang- ing from power supplies for safety critical avionics equipment to power drivers for electro-mechanical...

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

Data.gov (United States)

National Aeronautics and Space Administration — Electrolytic capacitors are used in several applications rang- ing from power supplies on safety critical avionics equipment to power drivers for electro-mechanical...

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

Data.gov (United States)

National Aeronautics and Space Administration — We are proposing an to develop a direct write electronics and avionics printing capability within the Techshot BioFabrication Facility currently funded and...

NAMMA DC-8 NAVIGATION AND HOUSEKEEPING (ICATS) V1

Data.gov (United States)

National Aeronautics and Space Administration — The NAMMA DC-8 Information Collection and Transmission System (ICATS) is designed to: 1) interface and process avionics and environmental paramaters from the...

Towards Prognostics for Electronics Components

Data.gov (United States)

National Aeronautics and Space Administration — Electronics components have an increasingly critical role in avionics systems and in the development of future aircraft systems. Prognostics of such components is...

CAMEX-4 DC-8 INFORMATION COLLECTION AND TRANSMISSION SYSTEM V1

Data.gov (United States)

National Aeronautics and Space Administration — The Camex-4 DC-8 Information Collection and Transmission System (ICATS) is designed to: 1) interface and process avionics and environmental paramaters from the...

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

Data.gov (United States)

National Aeronautics and Space Administration — Sample return missions, by nature, require high levels of spacecraft autonomy. Developments in hardware avionics have led to more capable real-time onboard computing...

Reliable avionics design for deep space

Science.gov (United States)

Johnson, Stephen B.

The technical and organizational problems posed by the Space Exploration Initiative (SEI) are discussed, and some possible solutions are examined. It is pointed out that SEI poses a whole new set of challenging problems in the design of reliable systems. These missions and their corresponding systems are far more complex than current systems. The initiative requires a set of vehicles and systems which must have very high levels of autonomy, reliability, and operability for long periods of time. It is emphasized that to achieve these goals in the face of great complexity, new technologies and organizational techniques will be necessary. It is noted that the key to a good design is good people. Not only must good people be found, but they must be placed in positions appropriate to their skills. It is argued that the atomistic and autocratic paradigm of vertical organizations must be replaced with more team-oriented and democratic structures.

General Aviation Activity and Avionics Survey

Science.gov (United States)

1988-11-01

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

The Next Great Ship: NASA's Space Launch System

Science.gov (United States)

May, Todd A.

2013-01-01

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

PEAC: A Power-Efficient Adaptive Computing Technology for Enabling Swarm of Small Spacecraft and Deployable Mini-Payloads

Data.gov (United States)

National Aeronautics and Space Administration — This task is to develop and demonstrate a path-to-flight and power-adaptive avionics technology PEAC (Power Efficient Adaptive Computing). PEAC will enable emerging...

Improved UAS Robustness through Augmented Onboard Intelligence, Phase I

Data.gov (United States)

National Aeronautics and Space Administration — This work will focus on the development of a highly capable avionics subsystem and machine learning algorithms to provide early warning of potential failures of...

Lithographically-Scribed Planar Holographic Optical CDMA Devices and Systems

National Research Council Canada - National Science Library

Mossberg, Thomas

2007-01-01

.... The present Phase II effort has harnessed new fabrication tools to perfect disruptive HBR-based multiplexer products for DoD avionics, optical communications systems computer data communications and local area networks...

Radiation Mitigation Methods for Reprogrammable FPGA, Phase I

Data.gov (United States)

National Aeronautics and Space Administration — One of the needs of NASA is the development of avionic systems and components that have the capability to operate in extreme radiation and temperature environments...

A Self-Regulating Freezable Heat Exchanger for Spacecraft, Phase II

Data.gov (United States)

National Aeronautics and Space Administration — A spacecraft thermal control system must keep the vehicle, avionics and atmosphere (if crewed) within a defined temperature range. Since water is non-toxic and good...

DIAGNOSTIC/PROGNOSTIC EXPERIMENTS FOR CAPACITOR DEGRADATION AND HEALTH MONITORING IN DC-DC CONVERTERS

Data.gov (United States)

National Aeronautics and Space Administration — Studying and analyzing the ageing mechanisms of electronic components avionics in systems such as the GPS and INAV are of critical importance. In DC-DC power...

Recent Projects in the KSC Applied Physics Lab

Science.gov (United States)

Starr, Stanley

2013-01-01

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

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

Science.gov (United States)

Yuchnovicz, Daniel; Burgess, Malcolm; Hammers, William

1999-01-01

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.

Towards Prognostics for Electronics Components

Science.gov (United States)

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

2013-01-01

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

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

National Research Council Canada - National Science Library

Ott, David D; Davis, James B

2002-01-01

In 2000, the United States Air Force T-38 Avionics Upgrade System Program Office began to pursue Lean initiatives to reduce out-year program cost and delivery risk at the Boeing T-38C Upgrade facility...

Analysis and Synthesis of Distributed Real-Time Embedded Systems

DEFF Research Database (Denmark)

Pop, Paul; Eles, Petru; Peng, Zebo

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

Pilot visual acquisition of traffic : operational communications from air traffic control operational communication.

Science.gov (United States)

2001-05-01

Avionics devices designed to provide pilots with graphically displayed traffic information will enable pilots to acquire and verify the identity of any intruder aircraft within the general area, either before or in accordance with a controller-issued...

Ada Linear-Algebra Program

Science.gov (United States)

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

1988-01-01

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

Kedalion: NASA's Adaptable and Agile Hardware/Software Integration and Test Lab

Science.gov (United States)

Mangieri, Mark L.; Vice, Jason

2011-01-01

NASA fs Kedalion engineering analysis lab at Johnson Space Center is on the forefront of validating and using many contemporary avionics hardware/software development and integration techniques, which represent new paradigms to heritage NASA culture. Kedalion has validated many of the Orion hardware/software engineering techniques borrowed from the adjacent commercial aircraft avionics solution space, with the intention to build upon such techniques to better align with today fs aerospace market. Using agile techniques, commercial products, early rapid prototyping, in-house expertise and tools, and customer collaboration, Kedalion has demonstrated that cost effective contemporary paradigms hold the promise to serve future NASA endeavors within a diverse range of system domains. Kedalion provides a readily adaptable solution for medium/large scale integration projects. The Kedalion lab is currently serving as an in-line resource for the project and the Multipurpose Crew Vehicle (MPCV) program.

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

Science.gov (United States)

Losh, Charles

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

Predictive Software Cost Model Study. Volume I. Final Technical Report.

Science.gov (United States)

1980-06-01

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

General Aviation Activity and Avionics Survey 1984

Science.gov (United States)

1985-10-01

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

General Aviation Activity and Avionics Survey 1982.

Science.gov (United States)

1983-12-01

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

General Aviation Activity and Avionics Survey 1981.

Science.gov (United States)

1982-12-01

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

Avionics Reliability, Its Techniques and Related Disciplines.

Science.gov (United States)

1979-10-01

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

NextGen Avionics Roadmap, Version 1.2

Science.gov (United States)

2010-09-21

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

NextGen Avionics Roadmap Version 2.0

Science.gov (United States)

2011-09-30

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

SWIFT-nanoLV Avionics Platform, Phase I

Data.gov (United States)

National Aeronautics and Space Administration — With the increased demand for and utility of nano- and micro-satellites, the demand for responsive, low-cost access to space has also increased. To meet this demand,...

Software Engineering and Its Application to Avionics

Science.gov (United States)

1988-01-01

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

75 FR 7345 - Filtered Flight Data

Science.gov (United States)

2010-02-19

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

HIL Tuning of UAV for Exploration of Risky Environments

Directory of Open Access Journals (Sweden)

C. D. Melita

2008-11-01

Full Text Available In this paper the latest results of an HIL architecture, optimized to develop and test UAV platforms are presented. This architecture has been used to realize the different devices involved in the navigation and stability control of the Volcan UAV, a plane designed to operate in volcanic environments. The proposed architecture is strongly modular and flexible and allows the development of avionic hardware and software, testing and tuning the involved algorithms with non-destructive trials. A flight simulator (X-Plane with a suitable plane model and plug-in, has been adopted to simulate the UAV dynamics. The flight simulator, interfaced with the real electronic boards, allows an easy tuning of all the control parameters and data collecting for test and validation. The effectiveness of adopted methodology was confirmed by several flight tests performed subsequently by using the designed avionic modules on the real UAV.

Effects of cosmic radiation on devices and embedded systems in aircrafts

Energy Technology Data Exchange (ETDEWEB)

Prado, Adriane C.M.; Federico, Claudio A.; Pereira Junior, Evaldo C.F.; Goncalez, Odair L., E-mail: claudiofederico@ieav.cta.br, E-mail: odairlelisgoncalez@gmail.com, E-mail: adriane.acm@hotmail.com, E-mail: evaldocarlosjr@gmail.com [Instituto de Estudos Avancados (IEAV/DCTA), Sao Jose dos Campos, SP (Brazil)

2013-07-01

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)

Effects of cosmic radiation on devices and embedded systems in aircrafts

International Nuclear Information System (INIS)

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

2013-01-01

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)

78 FR 30243 - Airworthiness Directives; Eclipse Aerospace, Inc. Airplanes

Science.gov (United States)

2013-05-22

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

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

Science.gov (United States)

2013-12-19

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

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

Science.gov (United States)

1988-10-01

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

Managing Heterogeneous Communication Challenges in Internet of Things using Connector Variability

NARCIS (Netherlands)

Kaya, M.C.; Nikoo, M.S.; Suloglu, S.; Tekinerdogan, B.; Dogru, A.H.

2017-01-01

Internet of Things (IoT) comprises smart systems that embrace computational and physical elements. In these systems, physical and software components are often tightly coupled. They are used widely in today’s technological systems, such as smart buildings, avionics, self-driving cars, etc. IoT

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

Science.gov (United States)

2013-10-31

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

77 FR 53159 - Passenger Use of Portable Electronic Devices on Board Aircraft

Science.gov (United States)

2012-08-31

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

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

Science.gov (United States)

2013-10-01

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

Validation of Flight Critical Control Systems

Science.gov (United States)

1991-12-01

1985. [8] Avizienis, A., and Lyu, M., "On the Effectiveness of Multiversion Software in Digital Avionics", AIAA Computers in Aerospace VI Conference...Experimentation and Modelling. NASA CR-165036, 1982. [12] Eckhardt, D. E.; and Lee, L. D.: A Theoretical Basis for the Analysis of Multiversion

The e-Beam Sustained Laser Technology for Space-based Doppler Wind Lidar

Science.gov (United States)

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

1992-01-01

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

Radiation Fields in High Energy Accelerators and their impact on Single Event Effects

CERN Document Server

García Alía, Rubén; Wrobel, Frédéric; Brugger, Markus

Including calculation models and measurements for a variety of electronic components and their concerned radiation environments, this thesis describes the complex radiation field present in the surrounding of a high-energy hadron accelerator and assesses the risks related to it in terms of Single Event Effects (SEE). It is shown that this poses not only a serious threat to the respective operation of modern accelerators but also highlights the impact on other high-energy radiation environments such as those for ground and avionics applications. Different LHC-like radiation environments are described in terms of their hadron composition and energy spectra. They are compared with other environments relevant for electronic component operation such as the ground-level, avionics or proton belt. The main characteristic of the high-energy accelerator radiation field is its mixed nature, both in terms of hadron types and energy interval. The threat to electronics ranges from neutrons of thermal energies to GeV hadron...

Methodes de calcul des forces aerodynamiques pour les etudes des interactions aeroservoelastiques

Science.gov (United States)

Biskri, Djallel Eddine

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

Investigation of Integrated Vehicle Health Management Approaches

Science.gov (United States)

Paris, Deidre

2005-01-01

This report is to present the work that was performed during the summer in the Advance Computing Application office. The NFFP (NASA Faculty Fellow Program) had ten summer faculty members working on IVHM (Integrated Vehicle Health Management) technologies. The objective of this project was two-fold: 1) to become familiar with IVHM concepts and key demonstrated IVHM technologies; and 2) to integrate the research that has been performed by IVHM faculty members into the MASTLAB (Marshall Avionic Software Test Lab). IVHM is a NASA-wide effort to coordinate, integrate and apply advanced software, sensors and design technologies to increase the level of intelligence, autonomy, and health state of future vehicles. IVHM is an important concept because it is consistent with the current plan for NASA to go to the moon, mars, and beyond. In order for NASA to become more involved in deep exploration, avionic systems will need to be highly adaptable and autonomous.

Unity of Command and Interdiction

Science.gov (United States)

1994-07-01

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

The Way Ahead For Maritime UAVS

Science.gov (United States)

2006-10-23

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

Centre de recherches pour le développement international ...

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

Julie Pépin

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

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

Science.gov (United States)

2013-10-31

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

Deploying a Route Optimization EFB Application for Commercial Airline Operational Trials

Science.gov (United States)

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

2016-01-01

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

Conference P.Aimedieu

CERN Multimedia

Aimedieu,P

1988-01-01

Le conférencier parle de la pollution, du trou d'ozone et cite entre autre l'histoire qui commence dans les années 1970 quand les préoccupations des scientifics se sont focalisées sur les pollutions possibles des avions supersonics dans la stratosphère

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

Science.gov (United States)

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

2003-01-01

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.

Wind Shear Systems Implementation Plan, Benefit/Cost Study.

Science.gov (United States)

1980-08-01

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

75 FR 52246 - Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes

Science.gov (United States)

2010-08-25

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

2015-2016 Travel and Hospitality Expense Reports for Joanne ...

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

Ruxandra Staicu

Ottawa. Billet d'avion. 0.00 $. Frais de transport au sol ou autrement. 0.00 $. Frais de logement. 0.00 $. Repas et frais divers. 73.66 $. Autre frais. 0.00 $. Total. 73.66 $. Commentaires. 2015-2016 Travel and Hospitality Expense. Reports for Joanne Charette, Vice-President,. Corporate Strategy and Communications.

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

NARCIS (Netherlands)

Kerkhoff, Hans G.; Ebrahimi, Hassan

2015-01-01

In avionics, like glide computers, the problem of No Faults Found (NFF) is a very serious and extremely costly affair. The rare occurrences and short bursts of these faults are the most difficult ones to detect and diagnose in the testing arena. Several techniques are now being developed in ICs by

Investigation of Intermittent Resistive Faults in Digital CMOS Circuits

NARCIS (Netherlands)

Kerkhoff, Hans G.; Ebrahimi, Hassan

No fault found (NFF) is a major threat in extremely dependable high-end process node integrated systems, in e.g., avionics. One category of NFFs is the intermittent resistive fault (IRF), often originating from bad (e.g., via- or TSV-based) interconnections. This paper will show the impact of these

Intermittent resistive faults in digital cmos circuits

NARCIS (Netherlands)

Kerkhoff, Hans G.; Ebrahimi, Hassan

2015-01-01

A major threat in extremely dependable high-end process node integrated systems in e.g. Avionics are no failures found (NFF). One category of NFFs is the intermittent resistive fault, often originating from bad (e.g. Via or TSV-based) interconnections. This paper will show the impact of these faults

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

Science.gov (United States)

1991-04-18

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

26 CFR 52.4682-3 - Imported taxable products.

Science.gov (United States)

2010-04-01

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

The BLSTs Role in the Materiel Enterprise

Science.gov (United States)

2016-05-17

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

Harmonics Study of Common Low Wattage LED Lamps

Directory of Open Access Journals (Sweden)

Ioan Dragoş Deaconu

2017-11-01

Full Text Available This article presents experimental data on Light Emitting Diode (LED lamps of low wattage that are commonly found both in commercial and residential applications. A comparison with the existing regulations is performed. The measurements are performed using power and energy quality analyzer intended also for avionic and military systems.

SATWG networked quality function deployment

Science.gov (United States)

Brown, Don

1992-01-01

The initiative of this work is to develop a cooperative process for continual evolution of an integrated, time phased avionics technology plan that involves customers, technologists, developers, and managers. This will be accomplished by demonstrating a computer network technology to augment the Quality Function Deployment (QFD). All results are presented in viewgraph format.

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

National Research Council Canada - National Science Library

Krodel, Jim

2001-01-01

.... The motivation is even a bit beyond monetary resources as the scarcity of highly trained personnel that can develop such systems has also provided fuel to the attractiveness of considering reuse...

Avionics for Scaled Remotely Operated Vehicles, Phase I

Data.gov (United States)

National Aeronautics and Space Administration — The use of UAVs has increased exponentially since 1995, and this growth is expected to continue. Many of these applications require extensive Research and...

Avionics for Scaled Remotely Operated Vehicles, Phase II

Data.gov (United States)

National Aeronautics and Space Administration — The use of UAS's in the military and the commercial field has grown tremendously over the last few years and is set to explode over next several. An...

A Strategy for Reforming Avionics Acquisition and Support

Science.gov (United States)

1988-07-01

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

Prognostic Health Management for Avionics System Power Supplies

National Research Council Canada - National Science Library

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

2005-01-01

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

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

Science.gov (United States)

1981-09-01

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

Modular, Plug and Play, Distributed Avionics, Phase II

Data.gov (United States)

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

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

Energy Technology Data Exchange (ETDEWEB)

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

2015-01-01

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

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

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

Beata Bialic

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

Co Modeling and Co Synthesis of Safety Critical Multi threaded Embedded Software for Multi Core Embedded Platforms

Science.gov (United States)

2017-03-20

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

77 FR 37881 - 36(b)(1) Arms Sales Notification

Science.gov (United States)

2012-06-25

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

Navigation and flight director guidance for the NASA/FAA helicopter MLS curved approach flight test program

Science.gov (United States)

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

1985-01-01

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

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

Directory of Open Access Journals (Sweden)

Martín Zorrilla

2015-10-01

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

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

Directory of Open Access Journals (Sweden)

Alejandro Artopoulos

2013-07-01

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

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

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

Ruxandra Staicu

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

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

Science.gov (United States)

2011-02-09

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

Hexavalent Chrome Free Coatings for Electronics Applications: Joint Test Report

Science.gov (United States)

Rothgeb, Matt; Kessel, Kurt

2013-01-01

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

Hex Chrome Free Coatings for Electronics Overview

Science.gov (United States)

Kessel, Kurt

2013-01-01

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

Near East/South Asia Report

Science.gov (United States)

1985-06-11

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

Hangar con alas, Los Angeles

Directory of Open Access Journals (Sweden)

Editorial, Equipo

1961-04-01

Full Text Available Formando parte de su programa, la TWA ha construido recientemente un hangar para servicio y reparaciones de su flota aérea de naves ordinarias y de aviones de reacción en el aeropuerto internacional de Los Angeles (Estados Unidos. El proyecto de esta obra se encargó a la empresa constructora Holmes & Narver, Inc.

NanoLaunch

Science.gov (United States)

Jones, Jonathan; Harris, Lawanna

2015-01-01

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

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

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

Ruxandra Staicu

But: Participation au Symposium Gartner et ExpoIT 2015. Date(s). 2015-10-03 à 2015-10-08. Destination(s). Orlando, Floride (É.-U.) Billet d'avion. 702.16 $. Frais de transport au sol ou autrement. 137.54 $. Frais de logement. 1 103.85 $. Repas et frais divers. 406.01 $. Autre frais. 33.37 $. Total. 2 382.93 $. Commentaires.

Rapports 2016-2017 sur les frais de voyage pour Sylvain Dufour ...

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

Beata Bialic

But: Participation au Symposium Gartner et ExpoIT 2016. Date(s). 2016-10-15 au 2016-10-21. Destination(s). Orlando, Floride (É.-U.) Billet d'avion. 497.01 $. Frais de transport au sol ou autrement. 181.22 $. Frais de logement. 1 216.70 $. Repas et frais divers. 853.72 $. Autre frais. 53.05 $. Total. 2 801.70 $. Commentaires.

Intelligent Vehicle Health Management

Science.gov (United States)

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

2005-01-01

As a part of the overall goal of developing Integrated Vehicle Health Management systems for aerospace vehicles, the NASA Faculty Fellowship Program (NFFP) at Marshall Space Flight Center has performed a pilot study on IVHM principals which integrates researched IVHM technologies in support of Integrated Intelligent Vehicle Management (IIVM). IVHM is the process of assessing, preserving, and restoring system functionality across flight and ground systems (NASA NGLT 2004). The framework presented in this paper integrates advanced computational techniques with sensor and communication technologies for spacecraft that can generate responses through detection, diagnosis, reasoning, and adapt to system faults in support of INM. These real-time responses allow the IIVM to modify the affected vehicle subsystem(s) prior to a catastrophic event. Furthermore, the objective of this pilot program is to develop and integrate technologies which can provide a continuous, intelligent, and adaptive health state of a vehicle and use this information to improve safety and reduce costs of operations. Recent investments in avionics, health management, and controls have been directed towards IIVM. As this concept has matured, it has become clear the INM requires the same sensors and processing capabilities as the real-time avionics functions to support diagnosis of subsystem problems. New sensors have been proposed, in addition, to augment the avionics sensors to support better system monitoring and diagnostics. As the designs have been considered, a synergy has been realized where the real-time avionics can utilize sensors proposed for diagnostics and prognostics to make better real-time decisions in response to detected failures. IIVM provides for a single system allowing modularity of functions and hardware across the vehicle. The framework that supports IIVM consists of 11 major on-board functions necessary to fully manage a space vehicle maintaining crew safety and mission

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

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

chantal taylor

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

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

Directory of Open Access Journals (Sweden)

Shu-Kun Lin

2013-01-01

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

Air Force Research Laboratory Sensors Directorate Leadership Legacy, 1960-2011

Science.gov (United States)

2011-03-01

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

Rapports 2017-2018 sur les frais de voyage pour Sylvain Dufour ...

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

Chantal Taylor

But: Participer au Symposium Gartner et ExpoIT 2017. Date(s). 2017-09-30 au 2017-10-06. Destination(s). Orlando, Floride (É.-U.) Billet d'avion. 751.97 $. Frais de transport au sol ou autrement. 228.39 $. Frais de logement. 1 102.96 $. Repas et frais divers. 1 342.07 $. Autre frais. 7.51 $. Total. 3 432.90 $. Commentaires.

Complications du traitement traditionnel des fractures : aspects ...

African Journals Online (AJOL)

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

Software engineering of a navigation and guidance system for commercial aircraft

Science.gov (United States)

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

1975-01-01

The avionics experimental configuration of the considered system is briefly reviewed, taking into account the concept of an advanced air traffic management system, flight critical and noncritical functions, and display system characteristics. Cockpit displays and the navigation computer are examined. Attention is given to the functions performed in the navigation computer, major programs in the navigation computer, and questions of software development.

Vector-matrix-quaternion, array and arithmetic packages: All HAL/S functions implemented in Ada

Science.gov (United States)

Klumpp, Allan R.; Kwong, David D.

1986-01-01

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

Five-Segment Solid Rocket Motor Development Status

Science.gov (United States)

Priskos, Alex S.

2012-01-01

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

General Aviation Activity and Avionics Survey. Calendar Year 1989

Science.gov (United States)

1989-01-01

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

A Real-Time Java Virtual Machine for Avionics (Preprint)

National Research Council Canada - National Science Library

Armbruster, Austin; Pla, Edward; Baker, Jason; Cunei, Antonio; Flack, Chapman; Pizlo, Filip; Vitek, Jan; Proch zka, Marek; Holmes, David

2006-01-01

...) in the DARPA Program Composition for Embedded System (PCES) program. Within the scope of PCES, Purdue University and the Boeing Company collaborated on the development of Ovm, an open source implementation of the RTSJ virtual machine...

Advanced Avionics and the Military Aircraft Man/Machine Interface.

Science.gov (United States)

1982-07-01

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

Electromagnetic Effects of (Carbon) Composite Materials Upon Avionics Systems

Science.gov (United States)

1980-10-01

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

Mapping a product-service-system delivering defence avionics availability

OpenAIRE

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

2017-01-01

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

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

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

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

Evaluation of Game-Based Visualization Tools for Military Flight Simulation

Science.gov (United States)

2014-02-01

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

Nodes and Codes: The Reality of Cyber Warfare

Science.gov (United States)

2012-05-17

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

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

Science.gov (United States)

1989-12-01

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

Test case preparation using a prototype

OpenAIRE

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

1998-01-01

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

Evaluation of System Architectures for the Army Aviation Ground Power Unit

Science.gov (United States)

2014-12-01

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

Les β-thalassémies de l'enfant camerounais : étude de la ...

African Journals Online (AJOL)

la variabilité l'expression clinique de la β-thalassémie, no- tamment lorsqu'elle est associée au trait drépanocytaire. A partir de la présente étude nous avions conclus que la β-thalassémie est une hémoglobinopathie assez fréquente au Cameroun. Bibliographie. [1] B. P. Alter, Beta-thalassemia trait: Imprecision of diagnosis ...

A MAG for the Twenty First Century: Lethal, Lighter, Energy Efficient, and Cheaper

Science.gov (United States)

2010-04-14

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

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

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

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

Space Shuttle RTOS Bayesian Network

Science.gov (United States)

Morris, A. Terry; Beling, Peter A.

2001-01-01

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

Efficient and Robust Data Collection Using Compact Micro Hardware, Distributed Bus Architectures and Optimizing Software

Science.gov (United States)

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

2006-01-01

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

Developpements numeriques recents realises en aeroelasticite chez Dassault Aviation pour la conception des avions de combat modernes et des avions d’affaires

Science.gov (United States)

2003-03-01

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

A Framework for Integration of IVHM Technologies for Intelligent Integration for Vehicle Management

Science.gov (United States)

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

2005-01-01

As a part of the overall goal of developing Integrated Vehicle Health Management (IVHM) systems for aerospace vehicles, the NASA Faculty Fellowship Program (NFFP) at Marshall Space Flight Center has performed a pilot study on IVHM principals which integrates researched IVHM technologies in support of Integrated Intelligent Vehicle Management (IIVM). IVHM is the process of assessing, preserving, and restoring system functionality across flight and ground systems (NASA NGLT 2004). The framework presented in this paper integrates advanced computational techniques with sensor and communication technologies for spacecraft that can generate responses through detection, diagnosis, reasoning, and adapt to system faults in support of IIVM. These real-time responses allow the IIVM to modify the effected vehicle subsystem(s) prior to a catastrophic event. Furthermore, the objective of this pilot program is to develop and integrate technologies which can provide a continuous, intelligent, and adaptive health state of a vehicle and use this information to improve safety and reduce costs of operations. Recent investments in avionics, health management, and controls have been directed towards IIVM. As this concept has matured, it has become clear the IIVM requires the same sensors and processing capabilities as the real-time avionics functions to support diagnosis of subsystem problems. New sensors have been proposed, in addition, to augment the avionics sensors to support better system monitoring and diagnostics. As the designs have been considered, a synergy has been realized where the real-time avionics can utilize sensors proposed for diagnostics and prognostics to make better real-time decisions in response to detected failures. IIVM provides for a single system allowing modularity of functions and hardware across the vehicle. The framework that supports IIVM consists of 11 major on-board functions necessary to fully manage a space vehicle maintaining crew safety and mission

Development Status of the Rad-Tolerant TTEthernet Controller

Science.gov (United States)

Fidi, Christian; van Masar, Ivan

2016-08-01

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

Cost, Capability, and the Hunt for a Lightweight Ground Attack Aircraft

Science.gov (United States)

2009-06-12

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

A Comparison of Ada 83 and C++

Science.gov (United States)

1991-06-01

developing large, complex, software systems with long lifetimes. Those interviewed for this study who are familiar with both Ada and C++ believe that Ada is...with those who are familiar with both languages, there was a clear preference for using Ada for large complex systems with long lifetimes. These...University, December 1990 Additions by Nelson H. Weiderman, June 1991. Chile Empresa Nacional de Aeronautica (ENAER), real-time avionics system, Data

The DTIC Review. Volume 1, Number 1: Nuclear Proliferation and Deterrence in a Changing Political World

Science.gov (United States)

1995-08-01

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

A Communication Architecture for an Advanced Extravehicular Mobile Unit

Science.gov (United States)

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

2014-01-01

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

Creating the Future: Research and Technology

Science.gov (United States)

1998-01-01

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

The Use of Modeling for Flight Software Engineering on SMAP

Science.gov (United States)

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

2011-01-01

The Soil Moisture Active Passive (SMAP) mission proposes to deploy an Earth-orbiting satellite with the goal of obtaining global maps of soil moisture content at regular intervals. Launch is currently planned in 2014. The spacecraft bus would be built at the Jet Propulsion Laboratory (JPL), incorporating both new avionics as well as hardware and software heritage from other JPL projects. [4] provides a comprehensive overview of the proposed mission

AIRCRAFT MAINTENANCE ENABLED JOINT CONCEPT FOR ENTRY OPERATIONS

Science.gov (United States)

2017-04-06

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

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

Science.gov (United States)

Hanson, Curt

2015-01-01

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.

Simple Electromagnetic Modeling of Small Airplanes: Neural Network Approach

OpenAIRE

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

2009-01-01

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

AAAIC '88 - Aerospace Applications of Artificial Intelligence; Proceedings of the Fourth Annual Conference, Dayton, OH, Oct. 25-27, 1988. Volumes 1 ampersand 2

International Nuclear Information System (INIS)

Johnson, J.R.

1988-01-01

Topics presented include integrating neural networks and expert systems, neural networks and signal processing, machine learning, cognition and avionics applications, artificial intelligence and man-machine interface issues, real time expert systems, artificial intelligence, and engineering applications. Also considered are advanced problem solving techniques, combinational optimization for scheduling and resource control, data fusion/sensor fusion, back propagation with momentum, shared weights and recurrency, automatic target recognition, cybernetics, optical neural networks

Buy, Build, or Steal: China’s Quest for Advanced Military Aviation Technologies

Science.gov (United States)

2011-12-01

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

A Low Cost Single Chip VDL Compatible Transceiver ASIC

Science.gov (United States)

Becker, Robert

2004-01-01

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

User type certification for advanced flight control systems

Science.gov (United States)

Gilson, Richard D.; Abbott, David W.

1994-01-01

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

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

Science.gov (United States)

1991-08-01

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

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

Science.gov (United States)

1990-03-01

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

JPRS Report, Near East and South Asia.

Science.gov (United States)

1989-01-12

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

Waypoint Generation Based on Sensor Aimpoint

Science.gov (United States)

2009-03-01

United States Government . AFIT/GAE/ENV/09-M01 WAYPOINT GENERATION BASED ON SENSOR AIMPOINT THESIS Presented to the Faculty Department of Aeronautical...BATCAM. Aviones physics parameters for the Procerus testbed, the Unicorn UAV, were provided by Procerus, which allowed another simulated MAV to 48 be...flown in the HIL tests. The AFIT Advanced Navigation Technologies (ANT) Center did not own a Unicorn UAV, so it could not be flown in flight tests

Polymer film strain gauges for measuring large elongations

Science.gov (United States)

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

2018-02-01

The paper shows the possibility to print polymer strain gages, microstrip lines, coplanar waveguides, and other prints for avionics using printing technology and equipment. The methods of screen and inkjet printing have been complemented by three new operations of preparing print films for application of an electrically conductive ink layer. Such additional operations make it possible to enhance the conductive ink layer adhesion to the film and to manufacture strain gages for measuring large elongations.

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

Science.gov (United States)

2000-05-01

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

Generic regional aircraft flying qualities for the approach and landing task

OpenAIRE

Gautrey, Jim

1997-01-01

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

Human Factors Aspects of Aircraft Accidents

Science.gov (United States)

1982-10-01

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

VEST: An Aspect-Based Composition Tool for Real-Time Systems

Science.gov (United States)

2003-01-01

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

Special Course on Subsonic/Transonic Aerodynamic Interference for Aircraft

Science.gov (United States)

1983-07-01

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

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

African Journals Online (AJOL)

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

5-Year Update Environmental Assessment for CV-22 Beddown

Science.gov (United States)

2007-02-01

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

Fourier Transform Spectrometer Controller for Partitioned Architectures

DEFF Research Database (Denmark)

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

2013-01-01

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

Workshop on Design Loads for Advanced Fighters: Meeting of the Structures and Materials Panel of AGARD (64th) Held in Madrid (Spain) on 27 April-1 May 1987.

Science.gov (United States)

1988-02-01

artificial intelligence system. It is posited that combining such a system, referred to informally as "Guardian", with a system incorporating aircraft...Proceedings of the Aerospace Medical Association Annual Scientific Meeting, 1976. 13. Van Patten, R. E. Current research on an artificial intelligence ...avions qui l’ont suivi (MIRAGE 4000, MIR. III NG et RAFALE) avec leur syst~me de commande de vol electrique et leur stabilite artificielle , a achev

A Proposed Logistics Strategy for the Defense of Republic of Korea

Science.gov (United States)

1984-06-01

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

``DMS-R, the Brain of the ISS'', 10 Years of Continuous Successful Operation in Space

Science.gov (United States)

Wolff, Bernd; Scheffers, Peter

2012-08-01

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

COLUMBUS as Engineering Testbed for Communications and Multimedia Equipment

Science.gov (United States)

Bank, C.; Anspach von Broecker, G. O.; Kolloge, H.-G.; Richters, M.; Rauer, D.; Urban, G.; Canovai, G.; Oesterle, E.

2002-01-01

The paper presents ongoing activities to prepare COLUMBUS for communications and multimedia technology experiments. For this purpose, Astrium SI, Bremen, has studied several options how to best combine the given system architecture with flexible and state-of-the-art interface avionics and software. These activities have been conducted in coordination with, and partially under contract of, DLR and ESA/ESTEC. Moreover, Astrium SI has realized three testbeds for multimedia software and hardware testing under own funding. The experimental core avionics unit - about a half double rack - establishes the core of a new multi-user experiment facility for this type of investigation onboard COLUMBUS, which shall be available to all users of COLUMBUS. It allows for the connection of 2nd generation payload, that is payload requiring broadband data transfer and near-real-time access by the Principal Investigator on ground, to test highly interactive and near-realtime payload operation. The facility is also foreseen to test new equipment to provide the astronauts onboard the ISS/COLUMBUS with bi- directional hi-fi voice and video connectivity to ground, private voice coms and e-mail, and a multimedia workstation for ops training and recreation. Connection to an appropriate Wide Area Network (WAN) on Earth is possible. The facility will include a broadband data transmission front-end terminal, which is mounted externally on the COLUMBUS module. This Equipment provides high flexibility due to the complete transparent transmit and receive chains, the steerable multi-frequency antenna system and its own thermal and power control and distribution. The Equipment is monitored and controlled via the COLUMBUS internal facility. It combines several new hardware items, which are newly developed for the next generation of broadband communication satellites and operates in Ka -Band with the experimental ESA data relay satellite ARTEMIS. The equipment is also TDRSS compatible; the open loop

Real-time millimeter-wave imaging radiometer for avionic synthetic vision

Science.gov (United States)

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

1994-07-01

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

The Mars Microprobe Mission: Advanced Micro-Avionics for Exploration Surface

Science.gov (United States)

Blue, Randel

2000-01-01

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

Impact of Advanced Avionics Technology on Ground Attack Weapon Systems.

Science.gov (United States)

1982-02-01

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

A Usability Survey of GPS Avionics Equipment: Some Preliminary Findings

National Research Council Canada - National Science Library

Joseph, Kurt

1999-01-01

The rapid introduction of Global Positioning System (GPS) receivers for airborne navigation has outpaced the capacity of international aviation authorities to resolve human factors issues that concern safe and efficient use of such devices...

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

Energy Technology Data Exchange (ETDEWEB)

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

1958-07-01

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

Use of Soft Computing Technologies for a Qualitative and Reliable Engine Control System for Propulsion Systems

Science.gov (United States)

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

2001-01-01

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

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

Science.gov (United States)

1979-12-01

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

Industrial communication technology handbook

CERN Document Server

Zurawski, Richard

2014-01-01

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

Ciència i pseudociència : un curs obert miniop

OpenAIRE

Canet Pladevall, Roser

2015-01-01

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

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

Science.gov (United States)

1990-06-01

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

Computing Systems Configuration for Highly Integrated Guidance and Control Systems

Science.gov (United States)

1988-06-01

de tableau de bord d’aeronef pour 1’entrainement des equipages); du logiciel LANST concu pour la simulation ae reseau locaux; des ...avioniques a bord d’un aeronef. -3- 225433 C.CEDOCAR titre fr. (Materiel de traitement de donnees pour spatlonef la normae 1750 A ISA Ge l’US Air Force...Instruments pour le traitement a bord des avions tactiques des donnees fournies par les differents capteurs. Une architecture reoondante pour les

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

OpenAIRE

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

2016-01-01

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

Automatic Generation of Safe Handlers for Multi-Task Systems

OpenAIRE

Rutten , Éric; Marchand , Hervé

2004-01-01

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

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

Science.gov (United States)

2003-01-01

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

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

Science.gov (United States)

Curran, R. T.

1971-01-01

A flight computer functional executive design for the reusable shuttle is presented. The design is given in the form of functional flowcharts and prose description. Techniques utilized in the regulation of process flow to accomplish activation, resource allocation, suspension, termination, and error masking based on process primitives are considered. Preliminary estimates of main storage utilization by the Executive are furnished. Conclusions and recommendations for timely, effective software-hardware integration in the reusable shuttle avionics system are proposed.

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

Directory of Open Access Journals (Sweden)

Kohji Kamejima

2007-08-01

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

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

Directory of Open Access Journals (Sweden)

Kohji Kamejima

2007-08-01

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

Mission Management Computer and Sequencing Hardware for RLV-TD HEX-01 Mission

Science.gov (United States)

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

2017-12-01

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

Autonomous, agile micro-satellites and supporting technologies

International Nuclear Information System (INIS)

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

1999-01-01

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

State Machine Modeling of the Space Launch System Solid Rocket Boosters

Science.gov (United States)

Harris, Joshua A.; Patterson-Hine, Ann

2013-01-01

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.

eletrônicos portáteis (PEDs

Directory of Open Access Journals (Sweden)

André Felipe Henriques Librantz

2006-01-01

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

The Ares Launch Vehicles: Critical for America's Continued Leadership in Space

Science.gov (United States)

Cook, Stephen A.

2009-01-01

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

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

OpenAIRE

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

2017-01-01

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

Visual Problems in Night Operations (Problemes de Vision dans les Operations de Nuit)

Science.gov (United States)

1992-05-01

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

Space Vehicle Flight Mechanics (La Mecanique du Vol des Vehicules Spatiaux)

Science.gov (United States)

1990-06-01

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

Coverage Metrics for Model Checking

Science.gov (United States)

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

2001-01-01

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

Design Methodologies for Secure Embedded Systems

CERN Document Server

Biedermann, Alexander

2011-01-01

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

Installation of new Generation General Purpose Computer (GPC) compact unit

Science.gov (United States)

1991-01-01

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

Handbook of RF, microwave, and millimeter-wave components

CERN Document Server

Smolskiy, Sergey M; Kochemasov, Victor N

2012-01-01

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

AGARD Index of Publications 1983-1985

Science.gov (United States)

1987-06-01

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

Comportamiento [del] tanque de material compuesto ante cargas dinámicas

OpenAIRE

Artero Guerrero, José Alfonso

2010-01-01

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

Automated Data Base Implementation Requirements for the Avionics Planning Baseline - Army

Science.gov (United States)

1983-07-01

PJRQT PJRSG .... PRJR owns PJRQTR Item EFT A32 A26 In record EFR Item ESFT A36 A40 In record ESFR Item EQPOC ALCPOC A20 In record EQR Iten EPHONE LPHONE...USING EF DUPLICATES ARE NOT ALLOWED WITHIN EQSEG. EF TYPE CHARACTER 4. EFT TYPE CHARACTER 32. EG TYPE CHARACTER 4. RECORD NAME IS ESFR LOCATION MODE... ESFR MANDATORY AUTOMATIC LINKED TO OWNER ASCENDING KEY IS ESF DUPLICATES NOT SET SELECTION THRU LOCATION MODE OF OWNER. SET NAME IS ESEQ MODE CHAIN

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

Data.gov (United States)

National Aeronautics and Space Administration — Space Micro proposes to build upon our existing space processing and hardening technologies and products e.g (Proton 200K), to research and develop reusable software...

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

Science.gov (United States)

1985-06-20

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

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

Science.gov (United States)

2015-03-01

Retrieved from IEEE Xplore website: http://ieeexplore.ieee.org/stamp/stamp.jsp?arnumber=04702759 Kopetz, H., Ademaj, A., & Grillinger, P. (2005). The...routines, allowing time and space (memory) partitioning, health monitoring (error detection and reporting), and communications via “ports.” ( IEEE , 2008...decided to go with another emerging standard: IEEE 1394, better known by its 13 consumer-electronics trade name “Firewire.” This solution provided

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

CSIR Research Space (South Africa)

Esser, MJD

2009-11-01

Full Text Available In order to demonstrate the feasibility of a helicopter-based application using advanced laser technology, the authors have developed a rugged and compact mid-infrared solid-state laser. The requirement for the laser was to simultaneously emit at 2...

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

Data.gov (United States)

National Aeronautics and Space Administration — NASA is interested in a reliable, robust, and low Size Weight and Power (SWAP) input device that will allow for EVA astronauts to navigate display menu systems. The...

High-Performance 3D Articulated Robot Display

Science.gov (United States)

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

2011-01-01

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

SCaN Testbed Software Development and Lessons Learned

Science.gov (United States)

Kacpura, Thomas J.; Varga, Denise M.

2012-01-01

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

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

Directory of Open Access Journals (Sweden)

Juan José Díaz Benítez

2013-11-01

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

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

Science.gov (United States)

1987-12-01

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

Feasibility Criteria for Interval Management Operations as Part of Arrival Management Operations

Science.gov (United States)

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

2014-01-01

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

Adapting the SpaceCube v2.0 Data Processing System for Mission-Unique Application Requirements

Science.gov (United States)

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

2015-01-01

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

Information Management For Tactical Reconnaissance

Science.gov (United States)

White, James P.

1984-12-01

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

OPALS: A COTS-based Tech Demo of Optical Communications

Science.gov (United States)

Oaida, Bogdan

2012-01-01

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

Turbine Engine Testing.

Science.gov (United States)

1981-01-01

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

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

Science.gov (United States)

1993-11-01

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

SCIENTIFIC RESEARCH ON THE ANTI-STRESS PREPARATION OF SPECIALISTS IN A QUARTER CENTURY

Directory of Open Access Journals (Sweden)

Yuriy Hryshchenko

2014-06-01

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

Radioactive waste disposal via electric propulsion

Science.gov (United States)

Burns, R. E.

1975-01-01

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

Pilot vehicle interface on the advanced fighter technology integration F-16

Science.gov (United States)

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

1986-01-01

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

Application of software technology to a future spacecraft computer design

Science.gov (United States)

Labaugh, R. J.

1980-01-01

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

Static Aeroelastic Effects on High Performance Aircraft

Science.gov (United States)

1987-06-01

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

Sensory redundancy management: The development of a design methodology for determining threshold values through a statistical analysis of sensor output data

Science.gov (United States)

Scalzo, F.

1983-01-01

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

Monitoring Distributed Real-Time Systems: A Survey and Future Directions

Science.gov (United States)

Goodloe, Alwyn E.; Pike, Lee

2010-01-01

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

Ferroelectric memories: A possible answer to the hardened nonvolatile question

International Nuclear Information System (INIS)

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

1988-01-01

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

Towards a new titanium sector: Aerospace

CSIR Research Space (South Africa)

Du Preez, W

2012-10-01

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

FAA/NASA Joint University Program for Air Transportation Research 1994-1995

Science.gov (United States)

Remer, J. H.

1998-01-01

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

Marshall Space Flight Center Faculty Fellowship Program

Science.gov (United States)

Six, N. F.; Karr, G.

2017-01-01

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

INTEGRATED ON-BOARD COMPUTING SYSTEMS: PRESENT SITUATION REVIEW AND DEVELOPMENT PROSPECTS ANALYSIS IN THE AVIATION INSTRUMENT-MAKING INDUSTRY

Directory of Open Access Journals (Sweden)

P. P. Paramonov

2013-03-01

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

An Introduction to TTCN-3

CERN Document Server

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

2011-01-01

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

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.

Science.gov (United States)

1983-10-01

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

Fiber-Optic Communication Links Suitable for On-Board Use in Modern Aircraft

Science.gov (United States)

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

2004-01-01

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

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

Science.gov (United States)

1980-01-01

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

Evaluation de differentes strategies de demantelement de la carcasse d'un avion

Science.gov (United States)

Sainte-Beuve, Damien

At the time when sustainable development of our environment and our society become more and more considered, the issue of the end of life of aircraft arises. With the tightening of regulations and policies to reduce operating costs, aircraft are increasingly removed from service before the end of their operational life. However, the regulations do not only affect the operational life of the aircraft. In the future, there are great chances that the aircraft end of life will be also regulated as the car end of life. Nowadays some deserts serve as a tomb for airplanes skeletons, but what will happen in a few years? Recycling the skeleton is not an operation with very high added value, such as reselling used parts, however intelligent sorting and facing the market can increase the gain. At the level of the aircraft life cycle, recycling its materials reduces its overall impact, and also helps to reduce pollution and land use, even if the main impacts generated by planes are created during the use phase. Similarly, if the recyclability of the aircraft is studied at the source, that is to say in its design, this will help to reduce the use of non-recyclable materials and dangerous compound. The greatest difficulty for recycling aircraft skeletons is that different materials are mixed and attached to each other. Through a thermodynamic study we showed what concentrations of alloying elements in a molten bath could be reduced. By using the Gibbs free energy, we evaluated some of the reactions taking place in a molten bath of aluminum during the injection of oxygen, boron, and chlorine. We focused on the reactions forming dual elements compounds, such as lithium oxide or magnesium chloride. We have shown that the six elements able to react when these reactions occurs are the lithium, the magnesium, the nickel, the titanium, the vanadium and the zirconium. It is necessary to remember that the impurities for alloys used in the aerospace industry are lower and especially those of iron and silicon. The major problem of recycling of aluminum alloys is that some attachments are made from steels, and are not separated from aluminum. Iron binds too easily with aluminum and removing it is expensive and complicated. The separation of these disturbing parts can be performed before or after shredding parts. Present sorting pathways already permit at a certain scale, to make this type of sorting. Adding some type of sorting, such as the LIBS or the use of dry ice blasting can help to increase the purity of the alloys obtained. On the other hand, the number of different aircraft being relatively small, it is possible to develop specific methods to recycle specific aircraft and this according to the technologies available at the end of life of the aircraft. In this context we have studied the wing of a Canadair Regional Jet 200. After characterizing more than 80% by weight of the wing, we looked at determining areas to maximize the alloys recycled in a close loop. We developed a method to create homogenous areas with the data we collected. We have shown that the removal of certain parts, sometimes massive such as landing gear support can reduce the final impurity. In addition, the more massive they are, the more their withdrawal is interesting because while improving the quality of the whole mix, the parts removed are recoverable their self. Unfortunately, for the final work to provide a real gain it is necessary that the data is of high quality, and numerous. This rule is even truer if we apply an algorithm to create homogeneous areas. This algorithm takes into account the market demands, to create areas satisfying this demand. With three-dimensional data, the algorithm is able to take into account the actual average concentration of elements present, and all the parts left during the dismantling of the plane. Due to the complexity of assemblies, neither the post-milling nor the pre-shredding treatment is perfect. This is why it is interesting and productive to combine them. Sorting pre-shredding can save and facilitate the post-shredding.

STOL terminal area operating systems (aircraft and onboard avionics, ATC, navigation aids)

Science.gov (United States)

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

1974-01-01

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

Thermal Control Subsystem Design for the Avionics of a Space Station Payload

Science.gov (United States)

Moran, Matthew E.

1996-01-01

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

Advances in real-time millimeter-wave imaging radiometers for avionic synthetic vision

Science.gov (United States)

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

1995-06-01

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

Acquisition Management: Source Selection Procedures for the C-5 Avionics Modernization Program

National Research Council Canada - National Science Library

Granetto, Paul J; Neville, Douglas P; Mathews, Amy L; Thompson, Lashonda M; Burger, Michael T; Anderson, Lamar; Hepler, Michael T; Borrero, Karen M; Hart, Erin S

2006-01-01

... (Acquisition, Technology, and Logistics) commissioned a study to review acquisition-related actions taken by the former Principal Deputy Assistant Secretary of the Air Force for Acquisition and Management (Principal Deputy...

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

Energy Technology Data Exchange (ETDEWEB)

Richard, A

2002-12-01

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

Method of optimization onboard communication network

Science.gov (United States)

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

2018-02-01

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

It's quicker "Par Avignon"!

CERN Multimedia

2005-01-01

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

Software Engineering Improvement Activities/Plan

Science.gov (United States)

2003-01-01

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

Romagnat – Bois des Goules

OpenAIRE

Leguet, Daniel

2014-01-01

Lien Atlas (MCC) : http://atlas.patrimoines.culture.fr/atlas/trunk/index.php?ap_theme=DOM_2.01.02&ap_bbox=3.027;45.698;3.133;45.745 La parcelle prospectée se situe sur le flanc nord du col des Goules, passage traditionnel vers l’oppidum de Gergovie, dans un profond thalweg emprunté jadis par un chemin descendant sur Romagnat. Sur la pente actuelle entièrement boisée, on trouve des sentiers récents et des pistes de motocross. C’est sur l’une de ces dernières que nous avions recueilli un poids ...

Latte-Abdallah Stéphanie, Images aux frontières, Représentations et constructions sociales et politiques, Palestine, Jordanie 1948-2000, Publications de l’IFPO, 2005, 369 p.

Directory of Open Access Journals (Sweden)

Véronique Bontemps

2008-01-01

Full Text Available Le traitement médiatique du 11 septembre 2001, et les images, diffusées en boucle sur les chaînes de télévision, des avions s’écrasant sur les Twin Towers ont tragiquement confirmé l’immense pouvoir des images sur notre appréhension de la réalité sociale. L’ouvrage Images aux frontières s’inscrit dans cette interrogation. Il regroupe des articles de sociologues, anthropologues, historiens et politologues autour de la notion « d’image » dans la construction des identités collectives en Palesti...

Reuse fo a Cold War Surveillance Drone to Flight Test a NASA Rocket Based Combined Cycle Engine

Science.gov (United States)

Brown, T. M.; Smith, Norm

1999-01-01

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

An expert system environment for the Generic VHSIC Spaceborne Computer (GVSC)

Science.gov (United States)

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

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

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

OpenAIRE

López Liévana, Borja

2007-01-01

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

Inadvertently programmed bits in Samsung 128 Mbit flash devices: a flaky investigation

Science.gov (United States)

Swift, G.

2002-01-01

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

Vehicle health management for guidance, navigation and control systems

Science.gov (United States)

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

1993-01-01

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.

Health management and controls for earth to orbit propulsion systems

Science.gov (United States)

Bickford, R. L.

1992-01-01

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

Desplome Constructivo: World Trade Center

OpenAIRE

González Collado, María José

2017-01-01

Dieciséis años después del desplome de las Torres Gemelas, aún sigue siendo un tema que despierta dudas e incertidumbres entre la sociedad, saber qué pasó exactamente aquel día. Explicar lo ocurrido el 11 de septiembre de 2001 de una manera objetiva, cómo el impacto de los aviones Boeing 767 y el consiguiente incendio afectaron a la estructura de las torres provocando su colapso, así como el espontáneo desplome de ambas no ha sido una tarea fácil. Se propone este trabajo de investigación para...

Research and technology, 1993. Salute to Skylab and Spacelab: Two decades of discovery

Science.gov (United States)

1993-01-01

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

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

Science.gov (United States)

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

2010-01-01

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

Contrôle de l'aérodynamique externe des véhicules aériens par des dispositifs microfluidiques : étude de l’effet de mini et micro-jets synthétiques sur des écoulements pariétaux

OpenAIRE

Batikh, Ahmad

2008-01-01

Le contrôle de l’écoulement est un axe majeur d’amélioration des performances des véhicules terrestres ou aériens (augmentation de la portance par suppression des décollements sur une aile d’avion par exemple). Dans la boucle de contrôle, l’actionneur est un élément essentiel et la caractérisation de son fonctionnement et de son effet sur l’écoulement contrôlé est indispensable pour déterminer les lois de contrôle efficaces. Parmi les technologies employées, les actionneurs fluidi...

Dhaksha, the Unmanned Aircraft System in its New Avatar-Automated Aerial Inspection of INDIA'S Tallest Tower

Science.gov (United States)

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

2013-08-01

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

DHAKSHA,THE UNMANNED AIRCRAFT SYSTEM IN ITS NEW AVATAR-AUTOMATED AERIAL INSPECTION OF INDIA'S TALLEST TOWER

Directory of Open Access Journals (Sweden)

K. S. Kumar

2013-08-01

Full Text Available 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

MC2: A Power Conditionning and Distribution Unit for Stratospherics Balloons

Directory of Open Access Journals (Sweden)

François Bonnet

2017-01-01

Full Text Available For long duration scientific missions with stratospheric balloons (objective of 3 month duration, renewable energy is used. Solar panels with mono crystalline silicon solar cells are mounted on both scientific and avionic gondola. A power conditioning board with Maximum Power Point Tracking (MPPT is designed and currently tested. This board is called MC2: Communicant Conditioning Module. It allows controlling a Li Ion battery charge through PWM regulators. Moreover, outlets ON/OFF commutations associated to overcurrent’s protections are implemented in this board. The battery active thermal control is made by MC2 autonomously. The main design drivers are mass, costs and efficiency. A CAN Bus between MC2 and On Board Computer allows to have a commandability and observability of MC2 through OBC. The overall avionic gondola is designed to be Single Points Failure free by using two segregated chains in order to be compatible with safety rules. The nominal chain is the main chain and use MC2 with renewable energy. The secondary chain uses a primary electrochemical cell which feeds loads in case of undervoltage of the main chain. This overall architecture allows both chains to be designed without SPF free constrains. This paper describes the overall requirements and the design of MC2. The main innovation described in this paper is the way to implement MPPT: the MPPT algorithm is performed at the output of the power converter. This MPPT extracts maximum power of both solar panel characteristics and power converter. The main advantage is that this MPPT uses only one existing sensor (output current of boost converter instead of using current and voltage sensor of each solar panel.

PRINCIPIOS BÁSICOS DE ULTRASONOGRAFÍA VETERINARIA

Directory of Open Access Journals (Sweden)

Carlos Giraldo E.

2003-12-01

Full Text Available La tecnología del ultrasonido nace en 1880 con eldesarrollo de los efectos piezoeléctricos. Luego fueaplicada en forma de SONAR (Sound Navigation andRanging durante la segunda guerra mundial para ladetección de barcos, submarinos y aviones de guerra.La emisión de las ondas de ultrasonido se obtiene pormedio de cristales que son sometidos a una corrienteeléctrica logrando que vibren, la recepción de éstasondas se logra cuando retornan de nuevo a los cristalesal chocar con los tejidos. Estos cristales están contenidosen dispositivos llamados transductores o sondasecográficas conectadas a un monitor

NASA Pathways Internship: Spring 2016

Science.gov (United States)

Alvarez, Oscar, III

2016-01-01

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

Georges et le code secret

CERN Document Server

Hawking, Lucy; Parsons, Gary

2015-01-01

À Foxbridge, Georges et Annie s'ennuient, ils rêvent de repartir dans l'espace pour de nouvelles aventures intergalactiques. Pourtant, sur la terre ferme, il se passe des choses étranges... L'argent s'envole des distributeurs de billets, les avions refusent de décoller et les caisses enregistreuses des supermarchés ne fonctionnent plus... Quel chaos ! Il semblerait qu'un bug planétaire ait déréglé tous les systèmes informatiques. S'ils veulent découvrir ce qui se cache derrière tout ça, les deux amis devront voyager plus loin que jamais dans l'espace...

Should we attempt global (inlet engine airframe) control design?

Science.gov (United States)

Carlin, C. M.

1980-01-01

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

Copilot: Monitoring Embedded Systems

Science.gov (United States)

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

2012-01-01

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.

Smart SPHERES: A Telerobotic Free-Flyer for Intravehicular Activities in Space

Science.gov (United States)

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

2013-01-01

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

Information processing. [in human performance

Science.gov (United States)

Wickens, Christopher D.; Flach, John M.

1988-01-01

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

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

Centers for Disease Control (CDC) Podcasts

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

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

OpenAIRE

Nagumo, F.; Thiombiano, L.

1996-01-01

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

Advanced and tendencies in the development of display technologies

Science.gov (United States)

Kompanets, I. N.

2006-06-01

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

Receptor GNSS multiantena para aplicaciones aeroespaciales

OpenAIRE

Cogo, Jorge; López La Valle, Ramón G.; Puga, Gerardo L.; Smidt, Javier A.; Díaz, Juan G.; García, Javier Gonzalo; Roncagliolo, Pedro Agustín; Muravchik, Carlos Horacio

2013-01-01

La determinación de la posición y velocidad del vehículo es una de las tareas críticas en las aplicaciones aeroespaciales como es el caso de aviones, satélites o cohetes. En los últimos años esta tarea se ha visto favorecida por el despliegue de los Sistemas de Navegación Global por Satélite (GNSS). Estos sistemas, utilizando como base una constelación de satélites que envían señales a la superficie terrestre, permiten que un usuario que cuente con un receptor adecuado pueda obtener esta info...

Benefits of Using Pairwise Trajectory Management in the Central East Pacific

Science.gov (United States)

Chartrand, Ryan; Ballard, Kathryn

2017-01-01

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

ISS Payload Racks Automated Flow Control Calibration Method

Science.gov (United States)

Simmonds, Boris G.

2003-01-01

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

Procedimiento y sistema de detección de la activación de la reversa en el aterrizaje de una aeronave

OpenAIRE

Asensio Rivera, César; Ruiz González, Mariano; Arcas Castro, Guillermo de; Recuero López, Manuel; López Navarro, Juan Manuel

2012-01-01

La invención consiste en un sistema de captación sonoro que es capaz de detectar la activación de la reversa durante el aterrizaje de los aviones a partir de la detección e identificación de los sonidos producidos en el proceso. Así mismo, la invención incluye el procedimiento que debe seguirse con respecto a la ubicación de los sensores. La invención dotará a los aeropuertos de una herramienta con la que velar por el cumplimento de las normativas referidas a la activación de la reversa en ma...

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

Science.gov (United States)

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

1993-01-01

Electrical actuator (ELA) power efficiency and requirements are examined for space system application. Requirements for Space Shuttle effector systems are presented, along with preliminary ELA trades and selection to form a preliminary ELA system baseline. Power and energy requirements for this baseline ELA system are applicable to the Space Shuttle and similar space vehicles.

76 FR 70044 - Airworthiness Directives; ATR-GIE Avions de Transport Régional Airplanes

Science.gov (United States)

2011-11-10

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

Civil mini-RPA's for the 1980's: Avionics design considerations. [remotely piloted vehicles

Science.gov (United States)

Karmarkar, J. S.

1975-01-01

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

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

Directory of Open Access Journals (Sweden)

Tabera García, Antonio

1982-03-01

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

AN ADA LINEAR ALGEBRA PACKAGE MODELED AFTER HAL/S

Science.gov (United States)

Klumpp, A. R.

1994-01-01

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

NH11B-1726: FrankenRaven: A New Platform for Remote Sensing

Science.gov (United States)

Dahlgren, Robert; Fladeland, Matthew M.; Pinsker, Ethan A.; Jasionowicz, John P.; Jones, Lowell L.; Pscheid, Matthew J.

2016-01-01

Small, modular aircraft are an emerging technology with a goal to maximize flexibility and enable multi-mission support. This reports the progress of an unmanned aerial system (UAS) project conducted at the NASA Ames Research Center (ARC) in 2016. This interdisciplinary effort builds upon the success of the 2014 FrankenEye project to apply rapid prototyping techniques to UAS, to develop a variety of platforms to host remote sensing instruments. In 2016, ARC received AeroVironment RQ-11A and RQ-11B Raven UAS from the US Department of the Interior, Office of Aviation Services. These aircraft have electric propulsion, a wingspan of roughly 1.3m, and have demonstrated reliability in challenging environments. The Raven airframe is an ideal foundation to construct more complex aircraft, and student interns using 3D printing were able to graft multiple Raven wings and fuselages into FrankenRaven aircraft. Aeronautical analysis shows that the new configuration has enhanced flight time, payload capacity, and distance compared to the original Raven. The FrankenRaven avionics architecture replaces the mil-spec avionics with COTS technology based upon the 3DR Pixhawk PX4 autopilot with a safety multiplexer for failsafe handoff to 2.4 GHz RC control and 915 MHz telemetry. This project demonstrates how design reuse, rapid prototyping, and modular subcomponents can be leveraged into flexible airborne platforms that can host a variety of remote sensing payloads and even multiple payloads. Modularity advances a new paradigm: mass-customization of aircraft around given payload(s). Multi-fuselage designs are currently under development to host a wide variety of payloads including a zenith-pointing spectrometer, a magnetometer, a multi-spectral camera, and a RGB camera. After airworthiness certification, flight readiness review, and test flights are performed at Crows Landing airfield in central California, field data will be taken at Kilauea volcano in Hawaii and other locations.

FrankenRaven: A New Platform for Remote Sensing

Science.gov (United States)

Dahlgren, R. P.; Fladeland, M. M.; Pinsker, E. A.; Jasionowicz, J. P.; Jones, L. L.; Mosser, C. D.; Pscheid, M. J.; Weidow, N. L.; Kelly, P. J.; Kern, C.; Werner, C. A.; Johnson, M. S.

2016-12-01

Small, modular aircraft are an emerging technology with a goal to maximize flexibility and enable multi-mission support. This reports the progress of an unmanned aerial system (UAS) project conducted at the NASA Ames Research Center (ARC) in 2016. This interdisciplinary effort builds upon the success of the 2014 FrankenEye project to apply rapid prototyping techniques to UAS, to develop a variety of platforms to host remote sensing instruments. In 2016, ARC received AeroVironment RQ-11A and RQ-11B Raven UAS from the US Department of the Interior, Office of Aviation Services. These aircraft have electric propulsion, a wingspan of roughly 1.3m, and have demonstrated reliability in challenging environments. The Raven airframe is an ideal foundation to construct more complex aircraft, and student interns using 3D printing were able to graft multiple Raven wings and fuselages into "FrankenRaven" aircraft. Aeronautical analysis shows that the new configuration has enhanced flight time, payload capacity, and distance compared to the original Raven. The FrankenRaven avionics architecture replaces the mil-spec avionics with COTS technology based upon the 3DR Pixhawk PX4 autopilot with a safety multiplexer for failsafe handoff to 2.4 GHz RC control and 915 MHz telemetry. This project demonstrates how design reuse, rapid prototyping, and modular subcomponents can be leveraged into flexible airborne platforms that can host a variety of remote sensing payloads and even multiple payloads. Modularity advances a new paradigm: mass-customization of aircraft around given payload(s). Multi-fuselage designs are currently under development to host a wide variety of payloads including a zenith-pointing spectrometer, a magnetometer, a multi-spectral camera, and a RGB camera. After airworthiness certification, flight readiness review, and test flights are performed at Crows Landing airfield in central California, field data will be taken at Kilauea volcano in Hawaii and other locations.

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

International Nuclear Information System (INIS)

Kuznetsov, E. V.; Shemyakin, A. V.

2010-01-01

The fields of the application, structure, fabrication, and packaging technology of high-power microwave LDMOS transistors and the main advantages of these devices were analyzed. Basic physical parameters and some technology factors were matched for optimum device operation. Solid-state microwave electronics has been actively developed for the last 10-15 years. Simultaneously with improvement of old devices, new devices and structures are actively being adopted and developed and new semiconductor materials are being commercialized. Microwave LDMOS technology is in demand in such fields as avionics, civil and military radars, repeaters, base stations of cellular communication systems, television and broadcasting transmitters, and transceivers for high-speed wireless computer networks (promising Wi-Fi and Wi-Max standards).

Vibration measurement on composite material with embedded optical fiber based on phase-OTDR

Science.gov (United States)

Franciscangelis, C.; Margulis, W.; Floridia, C.; Rosolem, J. B.; Salgado, F. C.; Nyman, T.; Petersson, M.; Hallander, P.; Hällstrom, S.; Söderquist, I.; Fruett, F.

2017-04-01

Distributed sensors based on phase-optical time-domain reflectometry (phase-OTDR) are suitable for aircraft health monitoring due to electromagnetic interference immunity, small dimensions, low weight and flexibility. These features allow the fiber embedment into aircraft structures in a nearly non-intrusive way to measure vibrations along its length. The capability of measuring vibrations on avionics structures is of interest for what concerns the study of material fatigue or the occurrence of undesirable phenomena like flutter. In this work, we employed the phase-OTDR technique to measure vibrations ranging from some dozens of Hz to kHz in two layers of composite material board with embedded polyimide coating 0.24 numerical aperture single-mode optical fiber.

Voltage Stress on Y Capacitors from Indirect Lightning Pulses According to ED-14/DO-160

Science.gov (United States)

Meier, F.

2012-05-01

Transients due to lightning strikes on an aircraft's fuselage impose stress on the input filters of elec- tronic equipment. Permanent damage can occur when exceeding the voltage handling capacity of filter components causing a short circuit to ground. In ED-14/DO-160, section 22, a number of waveforms and levels are defined which are used to check the airworthiness of avionics equipment. Depending on pro- cedure and level, Y-capacitors are stressed by transient voltages which exceed their dielectric strength. The design engineer's task is a properly select the type and voltage rating of capacitors. With moderate simplifications, a LCR-series network is justified to calculate the peak voltage dependent on the capacitance.

Hardware Testing for the Optical PAyload for Lasercomm Science (OPALS)

Science.gov (United States)

Slagle, Amanda

2011-01-01

Hardware for several subsystems of the proposed Optical PAyload for Lasercomm Science (OPALS), including the gimbal and avionics, was tested. Microswitches installed on the gimbal were evaluated to verify that their point of actuation would remain within the acceptable range even if the switches themselves move slightly during launch. An inspection of the power board was conducted to ensure that all power and ground signals were isolated, that polarized components were correctly oriented, and that all components were intact and securely soldered. Initial testing on the power board revealed several minor problems, but once they were fixed the power board was shown to function correctly. All tests and inspections were documented for future use in verifying launch requirements.

ACCESS: integration and pre-flight performance

Science.gov (United States)

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

2017-09-01

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

Comparing Interval Management Control Laws for Steady-State Errors and String Stability

Science.gov (United States)

Weitz, Lesley A.; Swieringa, Kurt A.

2018-01-01

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

A design procedure for a slotted waveguide with probe-fed slots radiating into plasma

International Nuclear Information System (INIS)

Colborn, J.A.

1989-11-01

A design procedure is developed for slotted-waveguide antennas with probe-fed slots. Radiation into a gyrotropic, plane-stratified medium is considered, nonzero waveguide wall thickness is assumed, and noncosinusoidal slot fields and arbitrary slot length up to about one free-space wavelength are allowed. External mutual coupling is taken into account by matching the tangential fields at the antenna surface. The particular case of longitudinal slots in the broad face of rectangular guide is analyzed. The motivation for this work is the design of such radiators for plasma heating and current-drive on thermonuclear fusion experiments, but some of the analysis is applicable to the probeless slotted waveguide used for avionics and communications. 20 refs., 5 figs

Optical backplane interconnect switch for data processors and computers

Science.gov (United States)

Hendricks, Herbert D.; Benz, Harry F.; Hammer, Jacob M.

1989-01-01

An optoelectronic integrated device design is reported which can be used to implement an all-optical backplane interconnect switch. The switch is sized to accommodate an array of processors and memories suitable for direct replacement into the basic avionic multiprocessor backplane. The optical backplane interconnect switch is also suitable for direct replacement of the PI bus traffic switch and at the same time, suitable for supporting pipelining of the processor and memory. The 32 bidirectional switchable interconnects are configured with broadcast capability for controls, reconfiguration, and messages. The approach described here can handle a serial interconnection of data processors or a line-to-link interconnection of data processors. An optical fiber demonstration of this approach is presented.

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

Directory of Open Access Journals (Sweden)

George Buchanan

2015-02-01

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

Éditorial Editorial

OpenAIRE

Jacques Maurice

2010-01-01

Ainsi que nous l’avions annoncé dans le précédent numéro, cette cinquième livraison des Cahiers propose deux études sur le Bicentenaire de la Guerre d’Indépendance.L’une, reprise des Mélanges de la Casa de Velázquez, analyse le processus révolutionnaire que vécut l’Espagne entre 1808 et 1814 et les différentes interprétations qui en ont été données. Cette étude est complétée par une lecture critique extrêmement fouillée d’un classique de l’historiographie libérale, la Historia del levantamien...

The other side of the safety coin. [aerospace operations

Science.gov (United States)

Roth, Gilbert L.

1986-01-01

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

Laser Spot Center Detection and Comparison Test

Science.gov (United States)

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

2018-04-01

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

Fiber optic systems for mobile platforms IV; Proceedings of the Meeting, San Jose, CA, Sept. 18, 1990

International Nuclear Information System (INIS)

Lewis, N.E.; Moore, E.L.

1991-01-01

The present conference on fiber-optic (FO) systems discusses topics in shipboard, automotive, spacecraft, and aeronautical FO applications. Attention is given to an FO interferometric ellipsoidal shell hydrophone, an FO backbone for a submarine combat system, EM environmental effects on shipboard FO installations, and recent developments in polymeric FO systems for automotive use. Also discussed are a wavelength-multiplexed FO position encoder for aircraft control systems, a code-division multiple-access system for integrated modular avionics, fly-by-light systems for commercial aircraft, FO temperature sensors for aerospace applications, a hybrid FO/electrical network for launch vehicles, the effects of ionizing radiation on FO systems, and FO systems in liquid propellant rocket environments

NASP - Enabling new space launch options

Science.gov (United States)

Froning, David; Gaubatz, William; Mathews, George

1990-10-01

Successful NASP developments in the United States are bringing about the possibility of effective, fully reusable vehicles for transport of people and cargo between earth and space. These developments include: extension of airbreathing propulsion to a much higher speed; densification of propellants for greater energy per unit volume of mass; structures with much greater strength-to-weight at high temperatures; computational advancements that enable more optimal design and integration of airframes, engines and controls; and advances in avionics, robotics, artificial intelligence and automation that enable accomplishment of earth-to-orbit (ETO) operations with much less manpower support and cost. This paper describes the relative magnitude of improvement that these developments may provide.

The R-Shell approach - Using scheduling agents in complex distributed real-time systems

Science.gov (United States)

Natarajan, Swaminathan; Zhao, Wei; Goforth, Andre

1993-01-01

Large, complex real-time systems such as space and avionics systems are extremely demanding in their scheduling requirements. The current OS design approaches are quite limited in the capabilities they provide for task scheduling. Typically, they simply implement a particular uniprocessor scheduling strategy and do not provide any special support for network scheduling, overload handling, fault tolerance, distributed processing, etc. Our design of the R-Shell real-time environment fcilitates the implementation of a variety of sophisticated but efficient scheduling strategies, including incorporation of all these capabilities. This is accomplished by the use of scheduling agents which reside in the application run-time environment and are responsible for coordinating the scheduling of the application.

L’île comme lieu de rédemption dans la télésérie américaine «Lost» (2004-2010)

OpenAIRE

Brouard, Élise

2015-01-01

Les téléséries ont connu un essor au début des années 2000. Lost, créée en 2004 par J.J. Abrams, Jefrey Lieber et Damon Lindelof, marque un tournant quant aux possibilités du format télévisuel. Avec une structure narrative complexe, dense et riche, la série présente des personnages brisés par leur passé qui se retrouvent sur une île semblant déserte après l’écrasement de l’avion dans lequel ils prenaient place. Leur destin et leur cheminement personnel respectif sont au cœur de l’intrigue. Da...

Summer Computer Simulation Conference, Washington, DC, July 15-17, 1981, Proceedings

International Nuclear Information System (INIS)

Anon.

1981-01-01

Aspects of simulation technology are discussed, taking into account microcomputers in simulation, heuristic/adaptive systems, differential equations approaches, available simulation packages, selected operations research applications, and mathematical and statistical tools. Hybrid systems are discussed along with topics of chemical sciences. Subjects related to physical and engineering sciences are explored, giving attention to aeronautics and astronautics, physical processes, nuclear/electrical power technology, advanced computational methods and systems, avionics systems, dynamic systems analysis and control, and industrial systems. Environmental sciences are considered along with biomedical systems, managerial and social sciences, questions of simulation credibility and validation, and energy systems. A description is provided of simulation facilities, and topics related to system engineering and transportation are investigated

An aspect-oriented approach for designing safety-critical systems

Science.gov (United States)

Petrov, Z.; Zaykov, P. G.; Cardoso, J. P.; Coutinho, J. G. F.; Diniz, P. C.; Luk, W.

The development of avionics systems is typically a tedious and cumbersome process. In addition to the required functions, developers must consider various and often conflicting non-functional requirements such as safety, performance, and energy efficiency. Certainly, an integrated approach with a seamless design flow that is capable of requirements modelling and supporting refinement down to an actual implementation in a traceable way, may lead to a significant acceleration of development cycles. This paper presents an aspect-oriented approach supported by a tool chain that deals with functional and non-functional requirements in an integrated manner. It also discusses how the approach can be applied to development of safety-critical systems and provides experimental results.

Le baptistère du Puy-en-Velay (Haute-Loire

Directory of Open Access Journals (Sweden)

Christian Sapin

2008-09-01

Full Text Available Traditionnellement désigné comme baptistère depuis le XIIIe siècle, cet édifice conservé au nord-est de la cathédrale du Puy est daté par la plupart des études antérieures du Xe siècle. En 2006, à partir du plan et des premiers travaux au sol, nous avions suggéré que les vestiges d’un massif quadrangulaire au niveau du sol, contre le mur nord, appartiennent à un rythme originel de piliers et grandes arcades murales, dont pouvaient subsister – selon les premières mesures d’espacement – des élé...

Fiber optic systems for mobile platforms IV; Proceedings of the Meeting, San Jose, CA, Sept. 18, 1990

Science.gov (United States)

Lewis, Norris E.; Moore, Emery L.

The present conference on fiber-optic (FO) systems discusses topics in shipboard, automotive, spacecraft, and aeronautical FO applications. Attention is given to an FO interferometric ellipsoidal shell hydrophone, an FO backbone for a submarine combat system, EM environmental effects on shipboard FO installations, and recent developments in polymeric FO systems for automotive use. Also discussed are a wavelength-multiplexed FO position encoder for aircraft control systems, a code-division multiple-access system for integrated modular avionics, fly-by-light systems for commercial aircraft, FO temperature sensors for aerospace applications, a hybrid FO/electrical network for launch vehicles, the effects of ionizing radiation on FO systems, and FO systems in liquid propellant rocket environments.

Fiber optic systems for mobile platforms IV; Proceedings of the Meeting, San Jose, CA, Sept. 18, 1990

Energy Technology Data Exchange (ETDEWEB)

Lewis, N.E.; Moore, E.L.

1991-01-01

The present conference on fiber-optic (FO) systems discusses topics in shipboard, automotive, spacecraft, and aeronautical FO applications. Attention is given to an FO interferometric ellipsoidal shell hydrophone, an FO backbone for a submarine combat system, EM environmental effects on shipboard FO installations, and recent developments in polymeric FO systems for automotive use. Also discussed are a wavelength-multiplexed FO position encoder for aircraft control systems, a code-division multiple-access system for integrated modular avionics, fly-by-light systems for commercial aircraft, FO temperature sensors for aerospace applications, a hybrid FO/electrical network for launch vehicles, the effects of ionizing radiation on FO systems, and FO systems in liquid propellant rocket environments.

Les Mayas à Hollywood.

Directory of Open Access Journals (Sweden)

Boris Jeanne

2007-02-01

Full Text Available Les Mayas de nos jours ce sont surtout des grandes pyramides au milieu de la forêt à un jet d’avion de Cancún : pour nombre de touristes américains et européens, c’est une occasion de s’acoquiner avec la culture, la grande culture des civilisations perdues, en continuant de boire des piña coladas le soir au bord de la plage. Et puis au mois de décembre les Mayas ont débarqué en force dans le paysage culturel local des Américains et des Européens, dans leurs cinémas, au moyen de deux films in...

Pavimentos de hormigón

Directory of Open Access Journals (Sweden)

Fernández, R.

1973-03-01

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

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

Directory of Open Access Journals (Sweden)

José Meseguer

2010-09-01

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.

Design and development of laser eye protection filter

International Nuclear Information System (INIS)

Ahmed, K; Khan, A N; Rauf, A; Gul, A; Aslam, M

2013-01-01

Laser based devices, have been operational for measurement of distances horizontally and vertically in avionics and surveillance industries. These equipments are functional on pulsed Nd:YAG laser at 1064nm, this wavelength elevate the risk of eye exposure to personnel at unexpected levels. In this paper the eye protection filters, for the wavelength 1064nm were developed with soft (ZnS) and hard (TiO 2 ) coating materials by using thin film vacuum coating technique. The damage threshold of the filter is 0.2 J/cm 2 . Transmission characteristics are measured and discussed. Optical damage threshold (for eye 5 × 10 −6 J/cm2) at various distances is also simulated.

Operation of commercially-based microcomputer technology in a space radiation environment

Science.gov (United States)

Yelverton, J. N.

This paper focuses on detection and recovery techniques that should enable the reliable operation of commercially-based microprocessor technology in the harsh radiation environment of space and at high altitudes. This approach is especially significant in light of the current shift in emphasis (due to cost) from space hardened Class-S parts qualification to a more direct use of commercial parts. The method should offset some of the concern that the newer high density state-of-the-art RISC and CISC microprocessors can be used in future space applications. Also, commercial aviation, should benefit, since radiation induced transients are a new issue arising from the increased quantities of microcomputers used in aircraft avionics.

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

Science.gov (United States)

2016-09-01

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

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

Index Scriptorium Estoniae

Chalvin, Antoine

2005-01-01

Ülevaade sündmustest Eesti poliitikas ja majanduses: valitsuskoalitsiooni lagunemine, sotsiaalpoliitika ning tervishoiu probleemid, Eesti-Vene piirileping, majandusnäitajad, Eesti-Prantsusmaa suhted, EL-iga liitumise mõjud. Tabelid. Lisad: Eesti poliitiliste sündmuste kronoloogia 2004-2005; Valimistulemused alates 2001; Valitsuse koosseis juunis 2005

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

Science.gov (United States)

1980-06-01

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

Flight Test Evaluation of AVOID I (Avionic Observation of Intruder Danger) Collision Avoidance System

Science.gov (United States)

1975-05-01

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

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

Science.gov (United States)

1979-04-01

EQUIPMENT ( SACE ) TECH 011 ACFT CRYPTOGRAPHIC SYS TECI-, IMA 018 ACFT INERTIAL NAVIGATION SYSTEM (INS) SACE TECH 019 ACFT SEARCH/TRACK (SIT) SACE TECH...020 SACE SYS TECH 021 ACFT DECEPTIVE ELECTRONIC COUNTERMEASURES IDECM) TECH 022 ELECTRONIC COUNTERMEASURES (ECM) MODULE REPAIR TECH 023 ACFT ECM TECH

Global navigation satellite systems performance analysis and augmentation strategies in aviation

Science.gov (United States)

Sabatini, Roberto; Moore, Terry; Ramasamy, Subramanian

2017-11-01

In an era of significant air traffic expansion characterized by a rising congestion of the radiofrequency spectrum and a widespread introduction of Unmanned Aircraft Systems (UAS), Global Navigation Satellite Systems (GNSS) are being exposed to a variety of threats including signal interferences, adverse propagation effects and challenging platform-satellite relative dynamics. Thus, there is a need to characterize GNSS signal degradations and assess the effects of interfering sources on the performance of avionics GNSS receivers and augmentation systems used for an increasing number of mission-essential and safety-critical aviation tasks (e.g., experimental flight testing, flight inspection/certification of ground-based radio navigation aids, wide area navigation and precision approach). GNSS signal deteriorations typically occur due to antenna obscuration caused by natural and man-made obstructions present in the environment (e.g., elevated terrain and tall buildings when flying at low altitude) or by the aircraft itself during manoeuvring (e.g., aircraft wings and empennage masking the on-board GNSS antenna), ionospheric scintillation, Doppler shift, multipath, jamming and spurious satellite transmissions. Anyone of these phenomena can result in partial to total loss of tracking and possible tracking errors, depending on the severity of the effect and the receiver characteristics. After designing GNSS performance threats, the various augmentation strategies adopted in the Communication, Navigation, Surveillance/Air Traffic Management and Avionics (CNS + A) context are addressed in detail. GNSS augmentation can take many forms but all strategies share the same fundamental principle of providing supplementary information whose objective is improving the performance and/or trustworthiness of the system. Hence it is of paramount importance to consider the synergies offered by different augmentation strategies including Space Based Augmentation System (SBAS), Ground

Efficient implementation of real-time programs under the VAX/VMS operating system

Science.gov (United States)

Johnson, S. C.

1985-01-01

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.

Nuclear EMP: stripline test method for measuring transfer impedance

International Nuclear Information System (INIS)

Miller, J.S.

1975-11-01

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

Deep space test bed for radiation studies

International Nuclear Information System (INIS)

Adams, James H.; Adcock, Leonard; Apple, Jeffery; Christl, Mark; Cleveand, William; Cox, Mark; Dietz, Kurt; Ferguson, Cynthia; Fountain, Walt; Ghita, Bogdan; Kuznetsov, Evgeny; Milton, Martha; Myers, Jeremy; O'Brien, Sue; Seaquist, Jim; Smith, Edward A.; Smith, Guy; Warden, Lance; Watts, John

2007-01-01

The Deep Space Test-Bed (DSTB) Facility is designed to investigate the effects of galactic cosmic rays on crews and systems during missions to the Moon or Mars. To gain access to the interplanetary ionizing radiation environment the DSTB uses high-altitude polar balloon flights. The DSTB provides a platform for measurements to validate the radiation transport codes that are used by NASA to calculate the radiation environment within crewed space systems. It is also designed to support other exploration related investigations such as measuring the shielding effectiveness of candidate spacecraft and habitat materials, testing new radiation monitoring instrumentation, flight avionics and investigating the biological effects of deep space radiation. We describe the work completed thus far in the development of the DSTB and its current status

FAILSAFE Health Management for Embedded Systems

Science.gov (United States)

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

2010-01-01

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.

A wideband software reconfigurable modem

Science.gov (United States)

Turner, J. H., Jr.; Vickers, H.

A wideband modem is described which provides signal processing capability for four Lx-band signals employing QPSK, MSK and PPM waveforms and employs a software reconfigurable architecture for maximum system flexibility and graceful degradation. The current processor uses a 2901 and two 8086 microprocessors per channel and performs acquisition, tracking, and data demodulation for JITDS, GPS, IFF and TACAN systems. The next generation processor will be implemented using a VHSIC chip set employing a programmable complex array vector processor module, a GP computer module, customized gate array modules, and a digital array correlator. This integrated processor has application to a wide number of diverse system waveforms, and will bring the benefits of VHSIC technology insertion into avionic antijam communications systems.

SEDS MIL-STD-1773 fiber optic data bus: Proton irradiation test results and spaceflight SEU data

Energy Technology Data Exchange (ETDEWEB)

LaBel, K.A.; Stassinopoulos, E.G.; Miller, J.T. (NASA/GSFC, Greenbelt, MD (United States)); Marshall, P. (NRL/SFA, Washington, DC (United States)); Dale, C. (NRL, Washington, DC (United States)); Crabtree, C.M. (Hughes/ST Systems Corp., Seabrook, MD (United States)); Gates, M.M. (Jackson and Tull, Seabrook, MD (United States))

1993-12-01

The Small Explorer Data System (SEDS) was launched in July of 1992 as part of the Solar Anomalous Magnetospheric Particle Explorer (SAMPEX) mission. The SEDS utilizes NASA's first MIL-STD-1773 Fiber Optic Multiplexed Data Bus (or 1773 bus) to communicate with other spacecraft subsystems in the space environment. The 1773 bus is the fiber optic version of the MIL-STD-1553 Data Bus, a electronic wire bus used in many avionics applications. The authors present proton test and space flight single event effect data for NASA's first fiber optic data bus. Bit error rate predictions based on a new proton direct ionization model agree well with flight data for proton belt and solar flare effects.

Saint-André-des-Eaux (Côtes-d’Armor : nouveaux éléments sur l’église et sur ses décors peints

Directory of Open Access Journals (Sweden)

Mathias Dupuis

2009-09-01

Full Text Available Nous avions déjà présenté dans le précédent numéro du Bulletin du Centre d'études médiévales d’Auxerre les premières recherches sur l’ancienne église paroissiale de Saint-André-des-Eaux . La réalisation de sondages en juin 2008 ainsi qu’une dernière série d’observations sur le bâti, préalables à la consolidation des murs de l’église et des vestiges de peintures murales, permettent désormais de mieux cerner l’histoire monumentale de cet édifice et de ses décors peints.Quatre sondages ont été o...

Optical system design, analysis, and production; Proceedings of the Meeting, Geneva, Switzerland, April 19-22, 1983

Science.gov (United States)

Rogers, P. J.; Fischer, R. E.

1983-01-01

Topics considered include: optical system requirements, analysis, and system engineering; optical system design using microcomputers and minicomputers; optical design theory and computer programs; optical design methods and computer programs; optical design methods and philosophy; unconventional optical design; diffractive and gradient index optical system design; optical production and system integration; and optical systems engineering. Particular attention is given to: stray light control as an integral part of optical design; current and future directions of lens design software; thin-film technology in the design and production of optical systems; aspherical lenses in optical scanning systems; the application of volume phase holograms to avionic displays; the effect of lens defects on thermal imager performance; and a wide angle zoom for the Space Shuttle.

Feasibility of modern airships - Preliminary assessment

Science.gov (United States)

Ardema, M. D.

1977-01-01

Attention is given to the NASA program, Feasibility Study of Modern Airships, initiated to investigate potential research and technology programs associated with airship development. A historical survey of the program is presented, including the development of past airship concepts, aerodynamical and design improvements, structure and material concepts, and research in controls, avionics, instrumentation, flight operations, and ground handling. A mission analysis was carried out which considered passenger and cargo transportation, heavy-lift, short-haul applications, surveillance missions, and the transportation of natural gas. A vehicle parametric analysis examined the entire range of airship concepts, discussing both conventional airships and hybrids. Various design options were evaluated, such as choice of structural materials, use of boundary-layer control, and choice of lifting gas.

Assessment of RFID Read Accuracy for ISS Water Kit

Science.gov (United States)

Chu, Andrew

2011-01-01

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

GR712RC- Dual-Core Processor- Product Status

Science.gov (United States)

Sturesson, Fredrik; Habinc, Sandi; Gaisler, Jiri

2012-08-01

The GR712RC System-on-Chip (SoC) is a dual core LEON3FT system suitable for advanced high reliability space avionics. Fault tolerance features from Aeroflex Gaisler’s GRLIB IP library and an implementation using Ramon Chips RadSafe cell library enables superior radiation hardness.The GR712RC device has been designed to provide high processing power by including two LEON3FT 32- bit SPARC V8 processors, each with its own high- performance IEEE754 compliant floating-point-unit and SPARC reference memory management unit.This high processing power is combined with a large number of serial interfaces, ranging from high-speed links for data transfers to low-speed control buses for commanding and status acquisition.

PRIMA Platform capability for satellite missions in LEO and MEO (SAR, Optical, GNSS, TLC, etc.)

Science.gov (United States)

Logue, T.; L'Abbate, M.

2016-12-01

PRIMA (Piattaforma Riconfigurabile Italiana Multi Applicativa) is a multi-mission 3-axis stabilized Platform developed by Thales Alenia Space Italia under ASI contract.PRIMA is designed to operate for a wide variety of applications from LEO, MEO up to GEO and for different classes of satellites Platform Family. It has an extensive heritage in flight heritage (LEO and MEO Satellites already fully operational) in which it has successfully demonstrated the flexibility of use, low management costs and the ability to adapt to changing operational conditions.The flexibility and modularity of PRIMA provides unique capability to satisfy different Payload design and mission requirements, thanks to the utilization of recurrent adaptable modules (Service Module-SVM, Propulsion Module-PPM, Payload Module-PLM) to obtain mission dependent configuration. PRIMA product line development is continuously progressing, and is based on state of art technology, modular architecture and an Integrated Avionics. The aim is to maintain and extent multi-mission capabilities to operate in different environments (LEO to GEO) with different payloads (SAR, Optical, GNSS, TLC, etc.). The design is compatible with a wide range of European and US equipment suppliers, thus maximising cooperation opportunity. Evolution activities are mainly focused on the following areas: Structure: to enable Spacecraft configurations for multiple launch; Thermal Control: to guarantee thermal limits for new missions, more demanding in terms of environment and payload; Electrical: to cope with higher power demand (e.g. electrical propulsion, wide range of payloads, etc.) considering orbital environment (e.g. lighting condition); Avionics : AOCS solutions optimized on mission (LEO observation driven by agility and pointing, agility not a driver for GEO). Use of sensors and actuators tailored for specific mission and related environments. Optimised Propulsion control. Data Handling, SW and FDIR mission customization

Prototype Operational Advances for Atmospheric Radiation Dose Rate Specification

Science.gov (United States)

Tobiska, W. K.; Bouwer, D.; Bailey, J. J.; Didkovsky, L. V.; Judge, K.; Garrett, H. B.; Atwell, W.; Gersey, B.; Wilkins, R.; Rice, D.; Schunk, R. W.; Bell, D.; Mertens, C. J.; Xu, X.; Crowley, G.; Reynolds, A.; Azeem, I.; Wiltberger, M. J.; Wiley, S.; Bacon, S.; Teets, E.; Sim, A.; Dominik, L.

2014-12-01

effective dose rate measurements and a thermal neutron monitor to characterize Single Event Effects (SEEs) in avionics. In this presentation we describe recent ARMAS and USEWX advances that will ultimately provide operational users with real-time dose and dose rate data for human tissue and avionics exposure risk mitigation.

Cognition and procedure representational requirements for predictive human performance models

Science.gov (United States)

Corker, K.

1992-01-01

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

A Cost Effective System Design Approach for Critical Space Systems

Science.gov (United States)

Abbott, Larry Wayne; Cox, Gary; Nguyen, Hai

2000-01-01

NASA-JSC required an avionics platform capable of serving a wide range of applications in a cost-effective manner. In part, making the avionics platform cost effective means adhering to open standards and supporting the integration of COTS products with custom products. Inherently, operation in space requires low power, mass, and volume while retaining high performance, reconfigurability, scalability, and upgradability. The Universal Mini-Controller project is based on a modified PC/104-Plus architecture while maintaining full compatibility with standard COTS PC/104 products. The architecture consists of a library of building block modules, which can be mixed and matched to meet a specific application. A set of NASA developed core building blocks, processor card, analog input/output card, and a Mil-Std-1553 card, have been constructed to meet critical functions and unique interfaces. The design for the processor card is based on the PowerPC architecture. This architecture provides an excellent balance between power consumption and performance, and has an upgrade path to the forthcoming radiation hardened PowerPC processor. The processor card, which makes extensive use of surface mount technology, has a 166 MHz PowerPC 603e processor, 32 Mbytes of error detected and corrected RAM, 8 Mbytes of Flash, and I Mbytes of EPROM, on a single PC/104-Plus card. Similar densities have been achieved with the quad channel Mil-Std-1553 card and the analog input/output cards. The power management built into the processor and its peripheral chip allows the power and performance of the system to be adjusted to meet the requirements of the application, allowing another dimension to the flexibility of the Universal Mini-Controller. Unique mechanical packaging allows the Universal Mini-Controller to accommodate standard COTS and custom oversized PC/104-Plus cards. This mechanical packaging also provides thermal management via conductive cooling of COTS boards, which are typically

Assessing Requirements Quality through Requirements Coverage

Science.gov (United States)

Rajan, Ajitha; Heimdahl, Mats; Woodham, Kurt

2008-01-01

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

Entry Descent and Landing Workshop Proceedings. Volume 1; Commercial Sources for EDL Flight Tests

Science.gov (United States)

Trombetta, Nick; Horan, Steve

2015-01-01

Commercial Off The Shelf is defined as a Federal Acquisition Regulation (FAR) term for commercial items, including services, available in the commercial marketplace that can be bought and used under government contracts. A need for COTS exists to help in reducing avionics cost associated with applicable missions. In a 2014 a Planetary Science Decadal Survey it was stated that it is imperative that NASA expand its investment in fundamental technology areas. Reduced mass and power requirements for spacecraft and their subsystems. New and improved sensors, instruments, and sampling systems; and Mission and trajectory design and optimization Two goals were written as part of the technology investment: 1. Reducing the cost of planetary missions 2. Improving their scientific capability and reliability...." COTS could certainty aid in reducing cost associated with the instrumentation systems.

Fault Tolerance in ZigBee Wireless Sensor Networks

Science.gov (United States)

Alena, Richard; Gilstrap, Ray; Baldwin, Jarren; Stone, Thom; Wilson, Pete

2011-01-01

Wireless sensor networks (WSN) based on the IEEE 802.15.4 Personal Area Network standard are finding increasing use in the home automation and emerging smart energy markets. The network and application layers, based on the ZigBee 2007 PRO Standard, provide a convenient framework for component-based software that supports customer solutions from multiple vendors. This technology is supported by System-on-a-Chip solutions, resulting in extremely small and low-power nodes. The Wireless Connections in Space Project addresses the aerospace flight domain for both flight-critical and non-critical avionics. WSNs provide the inherent fault tolerance required for aerospace applications utilizing such technology. The team from Ames Research Center has developed techniques for assessing the fault tolerance of ZigBee WSNs challenged by radio frequency (RF) interference or WSN node failure.

New Trends on MEMS Sensor Technology for Harsh Environment Applications

Directory of Open Access Journals (Sweden)

Patricia M. NIEVA

2007-10-01

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

NASA Langley Distributed Propulsion VTOL Tilt-Wing Aircraft Testing, Modeling, Simulation, Control, and Flight Test Development

Science.gov (United States)

Rothhaar, Paul M.; Murphy, Patrick C.; Bacon, Barton J.; Gregory, Irene M.; Grauer, Jared A.; Busan, Ronald C.; Croom, Mark A.

2014-01-01

Control of complex Vertical Take-Off and Landing (VTOL) aircraft traversing from hovering to wing born flight mode and back poses notoriously difficult modeling, simulation, control, and flight-testing challenges. This paper provides an overview of the techniques and advances required to develop the GL-10 tilt-wing, tilt-tail, long endurance, VTOL aircraft control system. The GL-10 prototype's unusual and complex configuration requires application of state-of-the-art techniques and some significant advances in wind tunnel infrastructure automation, efficient Design Of Experiments (DOE) tunnel test techniques, modeling, multi-body equations of motion, multi-body actuator models, simulation, control algorithm design, and flight test avionics, testing, and analysis. The following compendium surveys key disciplines required to develop an effective control system for this challenging vehicle in this on-going effort.

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

Centers for Disease Control (CDC) Podcasts

2016-07-11

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

Operations management system

Science.gov (United States)

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

1990-01-01

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.

Field Programmable Gate Array Failure Rate Estimation Guidelines for Launch Vehicle Fault Tree Models

Science.gov (United States)

Al Hassan, Mohammad; Novack, Steven D.; Hatfield, Glen S.; Britton, Paul

2017-01-01

Today's launch vehicles complex electronic and avionic systems heavily utilize the Field Programmable Gate Array (FPGA) integrated circuit (IC). FPGAs are prevalent ICs in communication protocols such as MIL-STD-1553B, and in control signal commands such as in solenoid/servo valves actuations. This paper will demonstrate guidelines to estimate FPGA failure rates for a launch vehicle, the guidelines will account for hardware, firmware, and radiation induced failures. The hardware contribution of the approach accounts for physical failures of the IC, FPGA memory and clock. The firmware portion will provide guidelines on the high level FPGA programming language and ways to account for software/code reliability growth. The radiation portion will provide guidelines on environment susceptibility as well as guidelines on tailoring other launch vehicle programs historical data to a specific launch vehicle.

Field Programmable Gate Array Reliability Analysis Guidelines for Launch Vehicle Reliability Block Diagrams

Science.gov (United States)

Al Hassan, Mohammad; Britton, Paul; Hatfield, Glen Spencer; Novack, Steven D.

2017-01-01

Field Programmable Gate Arrays (FPGAs) integrated circuits (IC) are one of the key electronic components in today's sophisticated launch and space vehicle complex avionic systems, largely due to their superb reprogrammable and reconfigurable capabilities combined with relatively low non-recurring engineering costs (NRE) and short design cycle. Consequently, FPGAs are prevalent ICs in communication protocols and control signal commands. This paper will identify reliability concerns and high level guidelines to estimate FPGA total failure rates in a launch vehicle application. The paper will discuss hardware, hardware description language, and radiation induced failures. The hardware contribution of the approach accounts for physical failures of the IC. The hardware description language portion will discuss the high level FPGA programming languages and software/code reliability growth. The radiation portion will discuss FPGA susceptibility to space environment radiation.

Dual-Use Space Technology Transfer Conference and Exhibition. Volume 2

Science.gov (United States)

Krishen, Kumar (Compiler)

1994-01-01

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

Recommended Changes to Interval Management to Achieve Operational Implementation

Science.gov (United States)

Baxley, Brian; Swieringa, Kurt; Roper, Roy; Hubbs, Clay; Goess, Paul; Shay, Richard

2017-01-01

A 19-day flight test of an Interval Management (IM) avionics prototype was conducted in Washington State using three aircraft to precisely achieve and maintain a spacing interval behind the preceding aircraft. NASA contracted with Boeing, Honeywell, and United Airlines to build this prototype, and then worked closely with them, the FAA, and other industry partners to test this prototype in flight. Four different IM operation types were investigated during this test in the en route, arrival, and final approach phases of flight. Many of the IM operations met or exceeded the design goals established prior to the test. However, there were issues discovered throughout the flight test, including the rate and magnitude of IM commanded speed changes and the difference between expected and actual aircraft deceleration rates.

VLSI 'smart' I/O module development

Science.gov (United States)

Kirk, Dan

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

Spacesuit Data Display and Management System

Science.gov (United States)

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

2009-01-01

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.

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

Science.gov (United States)

Holmes, David C. E.

1986-01-01

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

Analysis of Security Protocols in Embedded Systems

DEFF Research Database (Denmark)

Bruni, Alessandro

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.......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...... in this direction is to extend saturation-based techniques so that enough state information can be modelled and analysed. Finally, we present a methodology for proving the same security properties in the computational model, by means of typing protocol implementations....

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

Energy Technology Data Exchange (ETDEWEB)

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

2008-07-15

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.

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

Science.gov (United States)

Orr, James K.

2010-01-01

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

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

Science.gov (United States)

2010-06-01

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

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

Science.gov (United States)

Maazoun, Wissem

The main objective of this thesis is to develop an optimization method for the preparation of flight plans for aircrafts. The flight plan minimizes all costs associated with the flight. We determine an optimal path for an airplane from a departure airport to a destination airport. The optimal path minimizes the sum of all costs, i.e. the cost of fuel added to the cost of time (wages, rental of the aircraft, arrival delays, etc.). The optimal trajectory is obtained by considering all possible trajectories on a 3D graph (longitude, latitude and altitude) where the altitude levels are separated by 2,000 feet, and by applying a shortest path algorithm. The main task was to accurately compute fuel consumption on each edge of the graph, making sure that each arc has a minimal cost and is covered in a realistic way from the point of view of control, i.e. in accordance with the rules of navigation. To compute the cost of an arc, we take into account weather conditions (temperature, pressure, wind components, etc.). The optimization of each arc is done via the evaluation of an optimum speed that takes all costs into account. Each arc of the graph typically includes several sub-phases of the flight, e.g. altitude change, speed change, and constant speed and altitude. In the initial climb and the final descent phases, the costs are determined by considering altitude changes at constant CAS (Calibrated Air Speed) or constant Mach number. CAS and Mach number are adjusted to minimize cost. The aerodynamic model used is the one proposed by Eurocontrol, which uses the BADA (Base of Aircraft Data) tables. This model is based on the total energy equation that determines the instantaneous fuel consumption. Calculations on each arc are done by solving a system of differential equations that systematically takes all costs into account. To compute the cost of an arc, we must know the time to go through it, which is generally unknown. To have well-posed boundary conditions, we use the horizontal displacement as the independent variable of the system of differential equations. We consider the velocity components of the wind in a 3D system of coordinates to compute the instantaneous ground speed of the aircraft. To consider the cost of time, we use the cost index. The cost of an arc depends on the aircraft mass at the beginning of this arc, and this mass depends on the path. As we consider all possible paths, the cost of an arc must be computed for each trajectory to which it belongs. For a long-distance flight, the number of arcs to be considered in the graph is large and therefore the cost of an arc is typically computed many times. Our algorithm computes the costs of one million arcs in seconds while having a high accuracy. The determination of the optimal trajectory can therefore be done in a short time. To get the optimal path, the mass of the aircraft at the departure point must also be optimal. It is therefore necessary to know the optimal amount of fuel for the journey. The aircraft mass is known only at the arrival point. This mass is the mass of the aircraft including passengers, cargo and reserve fuel mass. The optimal path is determined by calculating backwards, i.e. from the arrival point to the departure point. For the determination of the optimal trajectory, we use an elliptical grid that has focal points at the departure and arrival points. The use of this grid is essential for the construction of a direct and acyclic graph. We use the Bellman-Ford algorithm on a DAG to determine the shortest path. This algorithm is easy to implement and results in short computation times. Our algorithm computes an optimal trajectory with an optimal cost for each arc. Altitude changes are done optimally with respect to the mass of the aircraft and the cost of time. Our algorithm gives the mass, speed, altitude and total cost at any point of the trajectory as well as the optimal profiles of climb and descent. A prototype has been implemented in C. We made simulations of all types of possible arcs and of several complete trajectories to illustrate the behaviour of the algorithm.

3D Navigation and Integrated Hazard Display in Advanced Avionics: Workload, Performance, and Situation Awareness

Science.gov (United States)

Wickens, Christopher D.; Alexander, Amy L.

2004-01-01

We examined the ability for pilots to estimate traffic location in an Integrated Hazard Display, and how such estimations should be measured. Twelve pilots viewed static images of traffic scenarios and then estimated the outside world locations of queried traffic represented in one of three display types (2D coplanar, 3D exocentric, and split-screen) and in one of four conditions (display present/blank crossed with outside world present/blank). Overall, the 2D coplanar display best supported both vertical (compared to 3D) and lateral (compared to split-screen) traffic position estimation performance. Costs of the 3D display were associated with perceptual ambiguity. Costs of the split screen display were inferred to result from inappropriate attention allocation. Furthermore, although pilots were faster in estimating traffic locations when relying on memory, accuracy was greatest when the display was available.

Ionizing Radiation Environment on the International Space Station: Performance vs. Expectations for Avionics and Material

Science.gov (United States)

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

2005-01-01

The role of structural shielding mass in the design, verification, and in-flight performance of International Space Station (ISS), in both the natural and induced orbital ionizing radiation (IR) environments, is reported. Detailed consideration of the effects of both the natural and induced ionizing radiation environment during ISS design, development, and flight operations has produced a safe, efficient manned space platform that is largely immune to deleterious effects of the LEO ionizing radiation environment. The assumption of a small shielding mass for purposes of design and verification has been shown to be a valid worst-case approximation approach to design for reliability, though predicted dependences of single event effect (SEE) effects on latitude, longitude, SEP events, and spacecraft structural shielding mass are not observed. The Figure of Merit (FOM) method over predicts the rate for median shielding masses of about 10g/cm(exp 2) by only a factor of 3, while the Scott Effective Flux Approach (SEFA) method overestimated by about one order of magnitude as expected. The Integral Rectangular Parallelepiped (IRPP), SEFA, and FOM methods for estimating on-orbit (Single Event Upsets) SEU rates all utilize some version of the CREME-96 treatment of energetic particle interaction with structural shielding, which has been shown to underestimate the production of secondary particles in heavily shielded manned spacecraft. The need for more work directed to development of a practical understanding of secondary particle production in massive structural shielding for SEE design and verification is indicated. In contrast, total dose estimates using CAD based shielding mass distributions functions and the Shieldose Code provided a reasonable accurate estimate of accumulated dose in Grays internal to the ISS pressurized elements, albeit as a result of using worst-on-worst case assumptions (500 km altitude x 2) that compensate for ignoring both GCR and secondary particle production in massive structural shielding.

A Survey of Serious Aircraft Accidents Involving Fatigue Fracture. Volume 1. Fixed-Wing Aircraft (Etude sur des Accidents Importants d’Avions du aux Effets des Fractures de Fatigue. Volume 1. Effets sur des Avions).

Science.gov (United States)

1983-04-01

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

Human-in-the-Loop Assessment of Alternative Clearances in Interval Management Arrival Operations

Science.gov (United States)

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

2016-01-01

Interval Management Alternative Clearances (IMAC) was a human-in-the-loop simulation experiment conducted to explore the Air Traffic Management (ATM) Technology Demonstration (ATD-1) Concept of Operations (ConOps), which combines advanced arrival scheduling, controller decision support tools, and aircraft avionics to enable multiple time deconflicted, efficient arrival streams into a high-density terminal airspace. Interval Management (IM) is designed to support the ATD-1 concept by having an "Ownship" (IM-capable) aircraft achieve or maintain a specific time or distance behind a "Target" (preceding) aircraft. The IM software uses IM clearance information and the Ownship data (route of flight, current location, and wind) entered by the flight crew, and the Target aircraft's Automatic Dependent Surveillance-Broadcast state data, to calculate the airspeed necessary for the IM-equipped aircraft to achieve or maintain the assigned spacing goal.

Determining Transmission Loss from Measured External and Internal Acoustic Environments

Science.gov (United States)

Scogin, Tyler; Smith, A. M.

2012-01-01

An estimate of the internal acoustic environment in each internal cavity of a launch vehicle is needed to ensure survivability of Space Launch System (SLS) avionics. Currently, this is achieved by using the noise reduction database of heritage flight vehicles such as the Space Shuttle and Saturn V for liftoff and ascent flight conditions. Marshall Space Flight Center (MSFC) is conducting a series of transmission loss tests to verify and augment this method. For this test setup, an aluminum orthogrid curved panel representing 1/8th of the circumference of a section of the SLS main structure was mounted in between a reverberation chamber and an anechoic chamber. Transmission loss was measured across the panel using microphones. Data measured during this test will be used to estimate the internal acoustic environments for several of the SLS launch vehicle internal spaces.

Spacelab 3 mission

Science.gov (United States)

Dalton, Bonnie P.

1990-01-01

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

High-Payoff Space Transportation Design Approach with a Technology Integration Strategy

Science.gov (United States)

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

2011-01-01

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

The high speed interconnect system architecture and operation

Science.gov (United States)

Anderson, Steven C.

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

Advanced Functionalities for Highly Reliable Optical Networks

DEFF Research Database (Denmark)

An, Yi

This thesis covers two research topics concerning optical solutions for networks e.g. avionic systems. One is to identify the applications for silicon photonic devices for cost-effective solutions in short-range optical networks. The other one is to realise advanced functionalities in order...... to increase the availability of highly reliable optical networks. A cost-effective transmitter based on a directly modulated laser (DML) using a silicon micro-ring resonator (MRR) to enhance its modulation speed is proposed, analysed and experimentally demonstrated. A modulation speed enhancement from 10 Gbit...... interconnects and network-on-chips. A novel concept of all-optical protection switching scheme is proposed, where fault detection and protection trigger are all implemented in the optical domain. This scheme can provide ultra-fast establishment of the protection path resulting in a minimum loss of data...

Sensor equipment of the German earth scientific airplane program

Science.gov (United States)

Seige, P.

1975-01-01

The German airplane program for earth scientific research supports the work of a vast staff of earth scientists from universities and federal agencies. Due to their fields of interest, which are in oceanography, hydrology, geology, ecology, and forestry, five test areas were selected which are spread all over Germany. The sensor package, which was designed in accordance with the requirements of this group of scientists, will be installed in a DO 28 D2 type airplane. The sensor equipment consists of a series of 70-mm cameras having different film/filter combinations, a photogrammetric camera, an infrared radiometer, an 11-channel multispectral line scanner, a LANDSAT-compatible radiometer, and a complex avionic system. Along with the airplane, a truck will be equipped with a set of radiometers and other sensor devices for extensive ground-truth measurement; this also includes a cherry picker.

Signal and image processing systems performance evaluation, simulation, and modeling; Proceedings of the Meeting, Orlando, FL, Apr. 4, 5, 1991

Science.gov (United States)

Nasr, Hatem N.; Bazakos, Michael E.

The various aspects of the evaluation and modeling problems in algorithms, sensors, and systems are addressed. Consideration is given to a generic modular imaging IR signal processor, real-time architecture based on the image-processing module family, application of the Proto Ware simulation testbed to the design and evaluation of advanced avionics, development of a fire-and-forget imaging infrared seeker missile simulation, an adaptive morphological filter for image processing, laboratory development of a nonlinear optical tracking filter, a dynamic end-to-end model testbed for IR detection algorithms, wind tunnel model aircraft attitude and motion analysis, an information-theoretic approach to optimal quantization, parametric analysis of target/decoy performance, neural networks for automated target recognition parameters adaptation, performance evaluation of a texture-based segmentation algorithm, evaluation of image tracker algorithms, and multisensor fusion methodologies. (No individual items are abstracted in this volume)

Use of In-Flight Data to Validate Mars Samle Return Autonomous RvD GNC

DEFF Research Database (Denmark)

Barrena, V.; Colmenarejo, P.; Suatoni, M.

D is based on RF, camera and LIDAR measurements. It includes design, prototyping and verification at three different levels: algorithms design and verification in a Functional Engineering Simulator, SW demonstrator verified in Real Time Avionics Test Benching and Dynamic Test Benching. Moreover...... and testing of a vision based optical stimulator (ViSOS by DTU) to enhance the on-ground validation capabilities. After checking different alternatives for the proposed HARvD-GNC experiment with PRISMA resources, an efficient but cost-effective approach was chosen. The approach is based on designing MSR......-like dedicated manoeuvres sequencing using the already existing on-board PRISMA GNC/AOCS system (based on relative GPS measurements for the closed-loop execution of the manoeuvres sequencing and acquiring RF and camera images as part of the HARvD-GNC experiment data). This option allows downloading the sensor...

Secuenciación heurística de un proyecto con restricciones temporales

Directory of Open Access Journals (Sweden)

Villa Juliá, Mª Fulgencia

2005-01-01

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

SMART SKINS - A Development Roadmap

Science.gov (United States)

Lochocki, Joseph M.

1990-02-01

The Air Force Project Forecast II identified a number of key technology initiatives for development. This paper addresses one such initiative, PT-16, Smart Skins. The concept of the Smart Skin is introduced by briefly highlighting its attributes and potential advantages over standard avionics packaging and maintenance, and then goes on to describe some of the key ingredients necessary for its development. Problem areas are brought out along with some of the required trades that must be made. Finally, a time phased development roadmap is introduced which shows Calspan's proposed sequence of technology development programs that can, in combination, lead to first functional Smart Skins implementations in narrowband form in the late 1990's and in wideband form in first decade of the twenty - first century. A Smart Skins implementation in integral aircraft skin structure form will take at least until 2010.

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

Science.gov (United States)

1980-05-01

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