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1
Omiecinski, Tomasz Adam. "Reconfigurable integrated modular avionics". Thesis, University of Bristol, 1999. http://hdl.handle.net/1983/e9e10bd7-72c6-4aff-9027-f297dded5e41.
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Integrated Modular Avionics standardises hardware and software platforms of Line Replaceable Modules (LRMs) and other system components in order to reduce the overall cost of system development. operation and maintenance. Several identical processing units within a cabinet. and fast communication media in the form of a backplane bus introduces further possibility of reconfiguring the system in terms of changing the applications performed by particular core LRMs. In this thesis a study into Reconfigurable Integrated Modular Avionics is presented. The main objectives of the project were to investigate the benefits, and feasibility of, employing autonomous dynamic in-tlight reconfiguration of the system as a means for providing fault-tolerance. In this approach, allowing processing modules to change their function permits the system to share the redundant modules as well as sacrificing less important avionics functions to sustain the more critical applications. Various architecture examples are reviewed in order to establish a system design that would support reconfiguration at a minimal cost. Two modified ARINC 651 architecture examples are proposed for implementation of dynamic in-flight reconfiguration. The benefits of reconfiguration are identified with the use of Markov state space analysis, and are found to be substantial with respect to the reduced number of redundant processing modules required to implement the system functions within the safety requirements. Suitable reconfiguration schemes are identified, and the most promising one is formally specified with the use of the Vienna Development Method. The safety properties of the scheme are shown based on the specification. In order to study the feasibility of autonomous dynamic reconfiguration, the scheme is implemented into two distinct systems, and the results of the practical observation of the system behaviour are presented and discussed. As the project was sponsored by the UK Civil Aviation Authority, a number of certification issues related to reconfigurable avionics systems are identified and discussed based on the practical implementation and previous theoretical analysis. It is concluded that dynamic in-flight reconfiguration of avionics systems can lead to substantial savings in terms of the reduced number of required core LRMs, and greater fault-tolerance than traditional non-reconfigurable systems
2
Pyatrin, D. K., O. V. Kozhokhina, G. Y. Marinchenko, L. V. Blahaia, Д. К. Пятрін, О. В. Кожохіна, Г. Є. Марінченко y Л. В. Благая. "Weibull distribution avionics application". Thesis, National aviation university, 2021. https://er.nau.edu.ua/handle/NAU/50499.
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1. Reliability of avionics systems. Textbook/Gribov V.M., Kozhokhina O.V., Marinchenko H.Y., Strelnikov V.P., - K.: Aliant, 2021, - 264p.
2. Weibull W. A statistical distribution function of wide application. ASME paper 51-A-6, Nov 1951.
3. Sherwin D J and Lees F P. An investigation of the application of failure data analysis to decision making in the maintenance of process plant. Proc Instn Mech Engrs, Vol 194, No 29, 1980.The paper deals with the weibull distribution in avionics application. During the operation of aircraft, the events that determine the transition of the product to different technical states occur randomly. Intervals of time of stay of a product in this or that condition have casual values of duration. The Weibull distribution is a fairly flexible function that can well align a variety of failure statistics and can be a model for the reliability of both electronic and mechanical products. The Weibull distribution successfully can be used in reliability engineering and failure analysis.
У тезах розглядається розподіл Вейбулла в застосуванні до авіоніки. Під час експлуатації літальних апаратів події, що визначають перехід виробу в різні технічні стани, відбуваються випадковим чином. Інтервали часу перебування виробу в тому чи іншому стані мають випадкові значення тривалості. Розподіл Вейбулла — це досить гнучка функція, яка може добре узгоджувати різноманітні статистичні дані про відмови та може бути взірцем надійності як електронних, так і механічних виробів. Розподіл Вейбулла може бути використаний в прогнозуванні надійності авіоніки та аналізі відмов.
3
Tybrandt, Ola. "Distribution of Cooling to Avionics". Thesis, Linköpings universitet, Reglerteknik, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-79031.
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In modern aircraft, one of the most difficult issues has been how to provide avionics with adequate cooling. Future versions of the fighter aircraft JAS 39 Gripen is equipped with new applications that have increased heat loads. In previous versions of the JAS 39 Gripen avionics was cooled by zero degree air and fuel, but in the next version a liquid loop will be installed to cool the new radar.The fluid in the liquid loop is cooled to proper temperature by pressurized bleed air from the engine which is cooled by ram air. The air to cool the avionics is produced the same way and this is a very expensive process for the airplane which lowers its performance. It is important to minimize the production of cooling air and therefore three new adjustable valves that provide various components of cooling air are installed in the next version of the JAS 39 Gripen. The cooled and pressure controlled air from the engine is distributed between different avionic shelves, each containing a set of components. Depending on the type of tasks performed and current flight mode of the aircraft the requirement of functions which should be active varies and therefore also the cooling demand to avionics. The first part of this thesis studies the overall priority of how the engine bleed shall be used. This part of the thesis results in a decision basis for the distribution of cooling air to be regulated in the absence of full cooling capacity. The amount of cooling which must be distributed to the radar is proportional to its developed power which varies widely depending on the radar’s operational mode. Since the pump which determines the liquid flow velocity operates at a constant speed is the regulation of cooling to the radar is controlled by varying the bleed air flow into the heat exchanger which cools the fluid and thus the temperature of the fluid has when it reaches the radar. This part of the thesis creates a control algorithm for controlling the airflow into the heat exchanger. The regulation keeps the fluid inlet temperature to the radar within the range of +25 ± 5 ˚ C and the gradient of the temperature less than 0.5° C per second. The PI-controller with the feed-forward filter succeeded in controlling the temperature of the liquid as it reached the radar within +25 ± 1° C, the temperature gradient requirement, 0.5° C per second, was also passed in all flight cases which were used to evaluate the controller. The PI-controller with feed-forward has a low convergence time and no static error. It also performs well when the measurement signals contain a lot of noise because of the controllers integrated low pass filter. The three new adjustable valves saves 12 to 97 g/s of cooling air for the different valve positions studied in this thesis, this corresponds to 9 - 70% of the total amount of controllable air to the avionics. Since the production of cooling air is a costly process for the aircraft, the use of all 3 valves is recommended.
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Czerwonka, Stephen P. (Stephen Paul) 1976. "Avionics life-cycle forecasting model". Thesis, Massachusetts Institute of Technology, 2000. http://hdl.handle.net/1721.1/9242.
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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2000.Also available online at the MIT Theses Online homepage
Includes bibliographical references (p. 116-119).
by Stephen P. Czerwonka.
S.M.
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Sukardjo, Wishnu. "Methods of avionics systems maintenance procedures". Thesis, University of Central Lancashire, 1995. http://clok.uclan.ac.uk/21166/.
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Avionics System Maintenance Procedures are discussed in this thesis in the context of a BPhil project involving formal training in research methods and includes information obtained by investigating issues pertinent to aircraft avionics systems maintenance. Personnel matters, problem specification and identification, maintenance procedures, health and safety issues, and quality control issues are discussed in terms of their influence in effectively carrying out required maintenance. The work described in the thesis demonstrates that several research methods are applicable to, and effective for, gathering information on avionics systems maintenance. Evidence is presented to support the view that research of maintenance procedures can produce considerable benefits in terms of improved overall maintenance performance. A critical comparison of maintenance procedures used by British Aerospace and the Indonesian Air Force is included, and conclusions are drawn which highlight a number of significant possibilities for developing improved procedures. Specific recommendations for improving maintenance productivity are given, and the benefits of addressing issues of Continuing Professional Development, Health and Safety matters, problem identification, use of computer databases, particularly for information governed by Standards, are discussed.
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Byrne, James Michael Jr. "Resource-constrained avionics design for CubeSats". Thesis, Massachusetts Institute of Technology, 2016. http://hdl.handle.net/1721.1/105559.
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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2016.This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
Cataloged from student-submitted PDF version of thesis.
Includes bibliographical references (pages 90-92).
We present an optimization approach to CubeSat avionics design which considers the consumption of some resources (electrical power, volume) and production of others (processing power, volatile memory, non-volatile memory, and radiation tolerance) in a quantitative optimization analysis. We present the avionics hardware design for the Microwave Radiometer Technology Acceleration (MiRaTA) 3U CubeSat, funded by the NASA Earth Science Technology Office (ESTO), as a case study for our optimization analysis. MiRaTA will demonstrate a three-band microwave radiometer and GPS radio occultation (GPSRO) sensor suite for profiling atmospheric temperature, humidity, and cloud ice. The goal is to increase the Technology Readiness Level (TRL) of the weather-sensing technology from TRL 5 to TRL 71. The avionics system is the "central nervous system" of the spacecraft, managing interfaces with every subsystem and between the Bus and Payload. MiRaTA's avionics design supports the Payload, which is tasked with the science mission to gather and process appropriate radiometer and GPSRO data, and the Bus, which comprises subsystems to handle attitude determination and control (ADC), power regulation and distribution, communications with the ground station, thermal management, and a suite of sensors and telemetry components. MiRaTA's avionics system uses a custom designed motherboard with a PIC24FJ256GB210 microcontroller to command activity in the Bus and manage data and power for the Payload. This custom Motherboard - dubbed the "Micron Motherboard" - leverages many of the advantages of the popular Pumpkin Motherboard but with reduced complexity and improved performance. The MiRaTA avionics system is also designed to minimize the number and length of cables, simplify connector uniformity, and improve accessibility. The design improvement in avionics hardware from MicroMAS to MiRaTA is quantified using an optimization coefficient: 1.522. We expect optimization coefficients to range typically from -4 to +4, so this design indicates a modest improvement.
by James Michael Byrne, Jr.
S.M.
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Warden, Gary y Bill Fleissner. "FIBRE CHANNEL TESTING FOR AVIONICS APPLICATIONS". International Foundation for Telemetering, 2004. http://hdl.handle.net/10150/605804.
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International Telemetering Conference Proceedings / October 18-21, 2004 / Town & Country Resort, San Diego, CaliforniaFibre Channel is being implemented as an avionics communication architecture for a variety of new military aircraft and upgrades to existing aircraft. The Fibre Channel standard (see T11 web site www.t11.org) defines various network topologies and multiple data protocols. Some of the topologies and protocols (ASM, 1553, RDMA) are suited for Avionics applications, where the movement of data between devices must take place in a deterministic fashion and needs to be delivered very reliably. All aircraft flight hardware needs to be tested to be sure that it will communicate information properly in the Fibre Channel network. The airframe manufacture needs to test the integrated network to verify that all flight hardware is communicating properly. Continuous maintenance testing is required to insure that all communication is deterministic and reliable. This paper provides an overview of a Fibre Channel Avionics network and protocols being used for Avionics. The paper also discusses a practical implementation of avionics level testing and testing challenges associated with these applications.
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Gavrilets, Vladislav 1975. "Avionics systems development for small unmanned aircraft". Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/50382.
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Buckley, Dave. "New Monitoring Paradigms for Modern Avionics Buses". International Foundation for Telemetering, 2013. http://hdl.handle.net/10150/579530.
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ITC/USA 2013 Conference Proceedings / The Forty-Ninth Annual International Telemetering Conference and Technical Exhibition / October 21-24, 2013 / Bally's Hotel & Convention Center, Las Vegas, NVIn modern aircraft there is a proliferation of avionics buses. Some of these buses use industry wide standards such as ARINC 429 or AFDX while others are based on proprietary protocols. For many of the newer bus types there can be thousands of parameters on each bus. In a distributed data acquisition system the flight test engineer needs to record all of the data from each bus and monitor selected parameters in real time. There are numerous different approaches to acquiring, transmitting and recording data from avionics buses. In modern FTI there is also a proliferation of standards for recording and transmission including IRIG 106 Chapter 10, iNET and IENA. In this paper some common approaches to bus monitoring are compared and contrasted for popular buses such as ARINC 429, AFDX and Time Triggered Protocol. For each bus type the best approach is selected for reliable acquisition, speed of configuration, low latency telemetry and compact recording which is optimized for playback.
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Black, James A. "HIGH SPEED AVIONICS DATA INSTRUMENTATION SYSTEM (HADIS)". International Foundation for Telemetering, 1992. http://hdl.handle.net/10150/608905.
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International Telemetering Conference Proceedings / October 26-29, 1992 / Town and Country Hotel and Convention Center, San Diego, CaliforniaSAIC, under contract with the Air Force Wright Laboratory, has developed and demonstrated a prototype High Speed Avionics Data Instrumentation System (HADIS). The HADIS system is designed to operate in both the laboratory and in an airborne environment. This paper briefly describes the features of the system including its ability to collect and record data at up to 13.25 MBytes per second, its ability to provide real-time processing of the data, and its ability to rapidly reconfigure its interfaces based on field programmable gate arrays. The paper discusses the need for multiple data paths within the system to allow parallel operations to take place, the need for dedicated access to the recorder subsystem, and methods for allowing selective recording based on the information content of the data. The effort was sponsored by the Test Facility Working Group to provide a common data collection system for Air Force logistics and test and evaluation facilities. The design is owned by the government and may be cost-effectively used by any government agency.
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Block, Max. "Pre-Runtime Scheduling of an Avionics System". Thesis, Uppsala universitet, Institutionen för informationsteknologi, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-300679.
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This master's thesis addresses a scheduling problem arising when designing avionics – the electronic systems used on aircraft. Currently, the problem is commonly solved using mixed integer programming (MIP). We prove the scheduling problem at-hand, which is similar to the well-studied cyclic job shop scheduling problem, is NP-hard. Furthermore, we propose an approach using constraint programming (CP) – a programming paradigm where entities called constraints define the relations between variables. Constraints do not specify a step or sequence of steps to execute, but rather the necessary properties of a solution. The CP approach implemented in the high-quality free OscaR CP solver manages around 1500 tasks in total over 10 processors within a 10 minute timeout, which is good enough for CP to be investigated further as a possible paradigm for solving the considered scheduling problem. We also compare Gurobi Optimizer, a high-quality commercial MIP solver, to Gecode, another high-quality free CP solver, when run on a model for the problem described in the MiniZinc modelling language.
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Stenlund, Sebastian. "Testing Safety Critical Avionics Software Using LBTest". Thesis, Linköpings universitet, Programvara och system, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-133645.
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A case study for the tool LBTest illustrating benets and limitations of the tool along the terms of usability, results and costs. The study shows the use of learning based testing on a safety critical application in the avionics industry. While requiring the user to have the oretical knowledge of the tools inner workings, the process of using the tool has benefits in terms of requirement analysis and the possibility of finding design and implementation errors in both the early and late stages of development
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Switzer, Earl, Michael Whelan y Farncisco Lagunas. "AIR TRAFFIC CONTROL COMMUNICATIONS TEST FACILITY AND AVIONICS SYSTEM TEST (ACTFAST): GEARING UP FOR NEXT GENERATION AVIONICS SYSTEMS TESTING". International Foundation for Telemetering, 2000. http://hdl.handle.net/10150/608285.
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International Telemetering Conference Proceedings / October 23-26, 2000 / Town & Country Hotel and Conference Center, San Diego, CaliforniaGrowth in civil aviation is overwhelming worldwide airspace and air traffic services. The International Civil Aviation Organization (ICAO), Federal Aviation Administration (FAA) and Department of Defense (DoD) are proposing or implementing numerous changes to address this growth. The changes are broadly contained in what the civil aviation community calls Communication, Navigation, and Surveillance/Air Traffic Management (CNS/ATM) and the DoD calls Global Air Traffic Management (GATM). A major component of both civil and DoD proposed changes are data link systems digitally transmitting information between aircraft, air traffic control centers, and aircraft operations centers. The real-time interactive nature of these data-link systems and the integration of the aircraft avionics into a worldwide network are forcing aircraft test agencies to acquire access to this capability. Aircraft flighttesting must address both the specific aircraft avionics test requirements and the system-of-systems aspects of data-link applications. This paper describes the factors driving changes in the worldwide CNS/ATM system and identifies specific proposed or implemented changes. Various flight-test requirements, both civil and military, of the proposed changes are enumerated. Particular attention is paid to the DoDs GATM certification requirements. Finally, we present the Air Traffic Control Communications Test Facility and Avionics System Test (ACTFAST) program and explain its capabilities. Rationale for ACTFAST component parts is included along with a brief outline of how the capabilities represented by each component part are used during flight test to acquire the necessary information to meet civil and DoD aircraft certification requirements.
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Bilen, Celal Can y John Alcalde. "Performance Evaluation of Embedded Microcomputers for Avionics Applications". Thesis, Jönköping University, JTH, Computer and Electrical Engineering, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:hj:diva-11955.
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Embedded microcomputers are used in a wide range of applications nowadays. Avionics is one of these areas and requires extra attention regarding reliability and determinism. Thus, these issues should also be born in mind in addition to performance when evaluating embedded microcomputers.
This master thesis suggests a framework for performance evaluation of two members of the PowerPC microprocessor family, namely the MPC5554 from Freescale and PPC440EPx from AMCC, and analyzes the results within and between these processors. The framework can be generalized to be used in any microprocessor family, if required.
Apart from performance evaluation, this thesis also suggests also a new terminology by introducing the concept of determinism levels to be able to estimate determinism issues in avionics applications more clearly, which is crucial regarding the requirements and working conditions of this very application. Such estimation does not include any practical results as in performance evaluation, but rather remains theoretical. Similar to Automark™ used by AutoBench™ in the EEMBC Benchmark Suite, we introduce a new performance metric score that we call ”Aviomark” and we carry out a detailed comparison of Aviomark with the traditional Automark™ score to be able to see how Aviomark differs from Automark™ in behavior.
Finally, we have developed a graphical user interface (GUI) which works in parallel with the Green Hills MULTI Integrated Development Environment (IDE) in order to simplify and automate the evaluation process. By the help of the GUI, the users will be able to easily evaluate their specific PowerPC processors by starting the debugging from MULTI IDE.
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Törnblom, John. "Improving Quality of Avionics Software Using Mutation Testing". Thesis, Linköpings universitet, Databas och informationsteknik, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-105456.
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Mutation testing is a powerful fault-based testing technique that makes syntactic changes to a program under test in order to simulate real faults otherwise caused by a programmer. Similar to structural coverage criteria such as statement coverage, mutation testing is used to assess the quality of a test suite. After a syntactic change has been made, the program is referred to as a mutant that either can survive a test suite, or be killed by one. If a mutant is killed, it means that the test suite has detected the syntactic change and reported it as an error, resulting in an increased mutation score. If a mutant survives, it means that the test suite failed to detect the fault and the mutation score is decreased. Mutation testing is generally considered the strongest testing technique available in terms of fault detection, but also the most expensive one. However, thanks to recent research and the rapid development of computing hardware, the testing technique is starting to become feasible, motivating the creation of tools utilizing the power of mutation testing. Saab AB, the Swedish aircraft manufacturer and stakeholder in this thesis, has experimented with mutation testing in the past, resulting in a tool called BAX that creates textual modifications of the original source code. The initial goal of this thesis is to provide a new tool that is faster than BAX, and that is more systematic in the way mutants are generated. LLVM-P86, the main contribution of this thesis, is a compiler and mutation testing framework intended for the programming language Pascal-86. Unlike BAX, LLVM-P86 is able to encode several mutants into a single program, thus reducing the time spent on compiling source code. In the conducted experiments, LLVM-P86 processed mutants significantly faster than BAX, on average by a factor of 13.6. Since LLVM-P86 is also a compiler, proper type information is available when mutants are generated. The additional type information allows LLVM-P86 to avoid a significant amount of equivalent mutants, i.e. mutants that behave in the same way as the original program. When mutating relational operators found in approximately 10,000 lines of code, distributed amongst 18 different Pascal-86 modules, LLVM-P86 was able to reduce the total number of living mutants by 25%, or 5.7% of the complete set of mutants.
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Cuevas, Vannesa, Michael Diehl y Tab Wilcox. "INSTRUMENTING AN ETHERNET AVIONICS BUS FOR APACHE TESTING". International Foundation for Telemetering, 2017. http://hdl.handle.net/10150/626967.
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Last year, the U.S. Army Yuma Proving Ground (YPG) faced a short suspense requirement to instrument an Apache's Ethernet bus. YPG was able to implement an effective method to satisfy this requirement; however, more capable and effective methodologies could not be developed and utilized due to time constraints. While continuing to support ongoing Apache testing, YPG is working to implement more efficient methods to capture and utilize the Ethernet data. This paper will discuss YPG’s initial implementation and the follow-on efforts being pursued.
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Bessant, Michael F. "Lightweight avionics platform to access atmospheric environmental science". Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/9198.
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There is a region of the atmosphere between approximately 10-40 km above the Earth’s
surface that is inaccessible to most winged aircraft and that rockets visit only fleetingly,
but where small unmanned balloons are increasingly being used to carry lightweight
(<5 Kg) scientific payloads. A major disadvantage of using these inexpensive ‘weather’
balloons is that researchers often have to develop telemetry and support avionics in
addition to the core experiment. The aim of this thesis project was to significantly
reduce this challenge by developing a Lightweight Avionics Platform (LAP) that would
be able to support a wide range of experiments by providing data from a suite of sensors
and a GPS receiver, together with an Iridium satellite link for communicating with
internet enabled ground stations. The LAP also provides non-volatile storage for the
sensor, GPS and experiment generated data.
The LAP design is based on a low power consumption microcomputer that is
compatible with the Arduino Integrated Development Environment (IDE) and its
associated open-source communication and sensor interface libraries. Modular systems
architecture was employed as an aid to rapid hardware development. A major design
goal was to allow researchers to interface their experiments without affecting the
integrity of the LAP’s embedded operating software. A dedicated Science Interface Port
(SIP) is provided for this purpose that allows experiments to be powered and data
exchanged, via a single electrically robust connector. This part of the project was
completed with the construction and testing of a flight-capable LAP that weighs less
than 0.2 Kg.
In order to ascertain the reliability of the above platform when subjected to the low
temperatures and pressures expected during stratospheric flight, the project included the
development of an environmental test chamber and associated monitoring/logging
system. A unique feature of this low cost chamber is that it is both portable and
transparent to satellite communications’ signals. Finally, design details for a proposed
atmospheric dust sampling experiment are provided as an example LAP application.
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Ellis, Colleen Laverna y Allan D. Kraus. "Preliminary design of a water cooled avionics rack". Thesis, Monterey, California: Naval Postgraduate School, 1993. http://hdl.handle.net/10945/24217.
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Mason, Paul Andrew James. "MATrA : meta-modelling approach to traceability for avionics". Thesis, University of Newcastle Upon Tyne, 2002. http://hdl.handle.net/10443/582.
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Traceability is the common term for mechanisms to record and navigate relationships between artifacts produced by development and assessment processes. Effective management of these relationships is critical to the success of projects involving the development of complex aerospace products. Practitioners use a range of notations to model aerospace products (often as part of a defined technique or methodology). Those appropriate to electrical and electronic systems (avionics) include Use Cases for requirements, Ada for development and Fault Trees for assessment (others such as PERT networks support product management). Most notations used within the industry have tool support, although a lack of well-defined approaches to integration leads to inconsistencies and limits traceability between their respective data sets (internal models). Conceptually, the artifacts produced using such notations populate four traceability dimensions. Of these, three record links between project artifacts (describing the same product), while the fourth relates artifacts across different projects (and hence products), and across product families within the same project. The scope of this thesis is to define a meta-framework that characterises traceability dimensions for aerospace projects, and then to propose a concrete framework capturing the syntax and semantics of notations used in developing avionics for such projects which enables traceability across the four dimensions. The concrete framework is achieved by exporting information from the internal models of tools supporting these notations to an integrated environment consisting of. i) a Workspace comprising a set of structures or meta-models (models describing models) expressed in a common modelling language representing selected notations (including appropriate extensions reflecting the application domain); ii) well-formedness constraints over these structures capturing properties of the notations (and again, reflecting the domain); and iii) associations between the structures. To maintain consistency and identify conflicts, elements of the structures are verified against a system model that defines common building blocks underlying the various notations. The approach is evaluated by (partial) tool implementation of the structures which are populated using case study material derived from actual commercial specifications and industry standards.
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Rodittis, Kathy y Alan Cooke. "Next Generation End to End Avionics Bus Monitoring". International Foundation for Telemetering, 2013. http://hdl.handle.net/10150/579512.
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ITC/USA 2013 Conference Proceedings / The Forty-Ninth Annual International Telemetering Conference and Technical Exhibition / October 21-24, 2013 / Bally's Hotel & Convention Center, Las Vegas, NVWith the advent of networked based data acquisition systems comes the opportunity to acquire, transmit and store potentially very large volumes of data. Despite this, and the increased size of the data acquisition networks, the use of tightly integrated hardware, and setup and analysis software enable the FTI engineer to save time and increase productivity. This paper outlines how the use of innovative bus packetizer technology and the close integration of FTI software can simplify this process. The paper describes how packetizer technology is used to acquire data from avionics buses, and how it packages this data in a format that is optimized for network based systems. The paper further describes how software can simplify the process of configuring avionics bus monitors in addition to automating and optimizing the transport of data from various nodes in the acquisition network for transmission to either network recorders or via a telemetry link.
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Грищенко, Юрій Віталійович. "ANALYTICAL STUDIES OF COMPLEX TECHNOLOGY INTERRUPTIONS OF AVIONICS". Thesis, Національний авіаційний університет, 2013. http://er.nau.edu.ua/handle/NAU/11518.
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Currently, it is provided avionics of modern aircrafts is a very reliable, which is asso¬ciated with a complete set of modern microelectronics. However, modern digital techniques is sometimes there are some interruptions that impact on safety. Ways for solving this negative phenomenon dedicated our report.
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Löfwenmark, Andreas. "Timing Predictability in Future Multi-Core Avionics Systems". Licentiate thesis, Linköpings universitet, Programvara och system, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-134427.
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With more functionality added to safety-critical avionics systems, new platforms are required to offer the computational capacity needed. Multi-core platforms offer a potential that is now being explored, but they pose significant challenges with respect to predictability due to shared resources (such as memory) being accessed from several cores in parallel. Multi-core processors also suffer from higher sensitivity to permanent and transient faults due to shrinking transistor sizes. This thesis addresses several of these challenges. First, we review major contributions that assess the impact of fault tolerance on worst-case execution time of processes running on a multi-core platform. In particular, works that evaluate the timing effects using fault injection methods. We conclude that there are few works that address the intricate timing effects that appear when inter-core interferences due to simultaneous accesses of shared resources are combined with the fault tolerance techniques. We assess the applicability of the methods to COTS multi-core processors used in avionics. We identify dark spots on the research map of the joint problem of hardware reliability and timing predictability for multi-core avionics systems. Next, we argue that the memory requests issued by the real-time operating systems (RTOS) must be considered in resource-monitoring systems to ensure proper execution on all cores. We also adapt and extend an existing method for worst-case response time analysis to fulfill the specific requirements of avionics systems. We relax the requirement of private memory banks to also allow cores to share memory banks.
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DiBenedetto, Michael F. "Citing criteria for the microwave landing system (MLS) MLS/ILS collocation and runway hump shadowing". Ohio : Ohio University, 1988. http://www.ohiolink.edu/etd/view.cgi?ohiou1182785020.
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Bach, Quoc Thang. "Přesné přiblížení na přistání GNSS CAT II/III". Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2013. http://www.nusl.cz/ntk/nusl-230767.
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The content of this work is an overview of precision approach used by GNSS and avionics for operation in low visibility conditions. This thesis describes existing requirements and proposals for new standards that are important to define GBAS performance. The objective of this work is to compare the alternative systems to guide aircraft during precision approach CAT II/III. GBAS operational implementation is additionally devised in this thesis.
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Chiappetti, Charles F. "Evaluation of the Haworth-Newman avionics display readability scale". Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1994. http://handle.dtic.mil/100.2/ADA286127.
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Hubbard, Peter D. "Fault management via dynamic reconfiguration for integrated modular avionics". Thesis, Loughborough University, 2015. https://dspace.lboro.ac.uk/2134/20957.
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The purpose of this research is to investigate fault management methodologies within Integrated Modular Avionics (IMA) systems, and develop techniques by which the use of dynamic reconfiguration can be implemented to restore higher levels of systems redundancy in the event of a systems fault. A proposed concept of dynamic configuration has been implemented on a test facility that allows controlled injection of common faults to a representative IMA system. This facility allows not only the observation of the response of the system management activities to manage the fault, but also analysis of real time data across the network to ensure distributed control activities are maintained. IMS technologies have evolved as a feasible direction for the next generation of avionic systems. Although federated systems are logical to design, certify and implement, they have some inherent limitations that are not cost beneficial to the customer over long life-cycles of complex systems, and hence the fundamental modular design, i.e. common processors running modular software functions, provides a flexibility in terms of configuration, implementation and upgradability that cannot be matched by well-established federated avionic system architectures. For example, rapid advances of computing technology means that dedicated hardware can become outmoded by component obsolescence which almost inevitably makes replacements unavailable during normal life-cycles of most avionic systems. To replace the obsolete part with a newer design involves a costly re-design and re-certification of any relevant or interacting functions with this unit. As such, aircraft are often known to go through expensive mid-life updates to upgrade all avionics systems. In contrast, a higher frequency of small capability upgrades would maximise the product performance, including cost of development and procurement, in constantly changing platform deployment environments. IMA is by no means a new concept and work has been carried out globally in order to mature the capability. There are even examples where this technology has been implemented as subsystems on service aircraft. However, IMA flexible configuration properties are yet to be exploited to their full extent; it is feasible that identification of faults or failures within the system would lead to the exploitation of these properties in order to dynamically reconfigure and maintain high levels of redundancy in the event of component failure. It is also conceivable to install redundant components such that an IMS can go through a process of graceful degradation, whereby the system accommodates a number of active failures, but can still maintain appropriate levels of reliability and service. This property extends the average maintenance-free operating period, ensuring that the platform has considerably less unscheduled down time and therefore increased availability. The content of this research work involved a number of key activities in order to investigate the feasibility of the issues outlined above. The first was the creation of a representative IMA system and the development of a systems management capability that performs the required configuration controls. The second aspect was the development of hardware test rig in order to facilitate a tangible demonstration of the IMA capability. A representative IMA was created using LabVIEW Embedded Tool Suit (ETS) real time operating system for minimal PC systems. Although this required further code written to perform IMS middleware functions and does not match up to the stringent air safety requirements, it provided a suitable test bed to demonstrate systems management capabilities. The overall IMA was demonstrated with a 100kg scale Maglev vehicle as a test subject. This platform provides a challenging real-time control problem, analogous to an aircraft flight control system, requiring the calculation of parallel control loops at a high sampling rate in order to maintain magnetic suspension. Although the dynamic properties of the test rig are not as complex as a modern aircraft, it has much less stringent operating requirements and therefore substantially less risk associated with failure to provide service. The main research contributions for the PhD are: 1. A solution for the dynamic reconfiguration problem for assigning required systems functions (namely a distributed, real-time control function with redundant processing channels) to available computing resources whilst protecting the functional concurrency and time critical needs of the control actions. 2. A systems management strategy that utilises the dynamic reconfiguration properties of an IMA System to restore high levels of redundancy in the presence of failures. The conclusion summarises the level of success of the implemented system in terms of an appropriate dynamic reconfiguration to the response of a fault signal. In addition, it highlights the issues with using an IMA to as a solution to operational goals of the target hardware, in terms of design and build complexity, overhead and resources.
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Kahn, Aaron David. "The design and development of a modular avionics system". Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/15712.
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Berg, Dale Douglas. "Analysis of management training for the Naval Avionics Center". Thesis, Monterey, California. Naval Postgraduate School, 1991. http://hdl.handle.net/10945/27969.
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Burke, Gerald Francis. "Improving trading cost information at the Naval Avionics Center". Thesis, Monterey, California. Naval Postgraduate School, 1991. http://hdl.handle.net/10945/28280.
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Vetter, David B. (David Brian). "Design of multi-passage cooling systems for avionics applications". Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/115475.
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Troshynski, Troy. "Bridging Legacy Avionics Data Busses to Ethernet Based Networks". International Foundation for Telemetering, 2012. http://hdl.handle.net/10150/581449.
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ITC/USA 2012 Conference Proceedings / The Forty-Eighth Annual International Telemetering Conference and Technical Exhibition / October 22-25, 2012 / Town and Country Resort & Convention Center, San Diego, CaliforniaEthernet is becoming more widely used as the network backbone in Integrated Modular Avionics (IMA) architectures. The advantages provided by Ethernet solutions include higher data throughput rates, ubiquitous use, lower costs, and high availability of components. Because of these advantages, new aircraft system designs and technology updates to existing system designs are considering Ethernet to replace legacy data bus technologies including MIL-STD-1553, ARINC-429, and CANbus based networks. Despite the advantages of Ethernet over these legacy technologies, latencies in standard IEEE 802.3 Ethernet networks is unpredictable. Defining when a data packet leaves a node and is received by another in absolute terms, and guaranteeing that the data will be received at its intended destination cannot be accurately predicted or guaranteed. Enhancements to IEEE 802.3 such as ARINC-664, and AS6802 enable determinism and guaranteed quality of service that the legacy data bus technologies provided. This paper provides an overview of deterministic Ethernet technologies such as ARINC-664 and AS6802 (TTEthernet) that define deterministic, guaranteed quality of service networks. It also considers the advantages, disadvantages, and possible applications utilizing bridges between MIL-STD-1553 data busses and these Ethernet protocols and considers other related protocols such as IRIG 106 Chapter 10.
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Seybert, Audrey, Jay Fuller y Bryan Townley. "Detect Sense and Avoid Radar for UAV Avionics Telemetry". International Foundation for Telemetering, 2011. http://hdl.handle.net/10150/595802.
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ITC/USA 2011 Conference Proceedings / The Forty-Seventh Annual International Telemetering Conference and Technical Exhibition / October 24-27, 2011 / Bally's Las Vegas, Las Vegas, NevadaThis paper describes the development and test results of a Frequency Modulated Continuous Wave (FMCW) L-Band radar testbed designed to detect obstacles in the proximity of an Unmanned Aerial Vehicle (UAV). From laboratory loopback tests, it was calculated that with pulse compression and a transmit power of 150 mW (22 dBm), the radar is capable of detecting an object with a 0.014-m2 radar cross-sectional area at ranges between 500 ft to 1 mi. Analysis shows that post processing of the collected data would reveal information about the obstacle such as its range and location relative to the aircraft. Design and testing procedures are discussed.
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Клочан, Арсен Євгенійович. "THE PECULIARITIES OF MAINTENANCE AND EXPLOITATION OF MODERN AVIONICS". Thesis, К.: НАУ, 2013. http://er.nau.edu.ua/handle/NAU/11709.
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Kamkin, Y. V. "MAINTENANCE INTERVALS PLANNING OPTIMIZATION OF NEW GENERATION AIRCRAFTS AVIONICS". Thesis, Національний авіаційний університет, 2015. http://er.nau.edu.ua/handle/NAU/17208.
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One of the major reasons of aviation accident is unsuitable maintenance program.
Nowadays maintenance steering group-3, the “Operator/Manufacturer Scheduled Maintenance Development Document” is used.
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Riedlinger, Marc [Verfasser]. "Architecture of an Adaptive Avionics Platform Supervisor / Marc Riedlinger". München : Verlag Dr. Hut, 2020. http://d-nb.info/1222352613/34.
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Greer, Daniel S. "Avionics System development for a Rotary Wing Unmanned Aerial Vehicle". Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1998. http://handle.dtic.mil/100.2/ADA350437.
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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, June 1998."June 1998." Thesis advisor(s): Russ W. Duren. Includes bibliographical references (p. 79). Also available online. Mode of access: World Wide Web.
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Bruneau, Daniel Pierre Jacques. "A study of predictive information aids in an avionics application". Thesis, University of Bristol, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.425149.
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Omelchenko, Alexander 1968. "Avionics systems design for cooperative unmanned air and ground vehicles". Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/17789.
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Thesis (S.M. and E.A.A.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004."June 2004."
Includes bibliographical references (p. 95).
This thesis summarizes the results of the design of avionics systems intended for use onboard unmanned air and ground vehicles, that are parts of a multi-vehicle system whose primary mission objective is to provide up-close surveillance capability from a large stand-off distance. Different types of cooperative action between air and ground vehicles, that can help to enhance the overall system surveillance capability, are analyzed, including communication relay, simultaneous visual surveillance of ground objects from air and ground vehicles, and visual coverage of ground vehicles from air vehicles. Both hardware and software design as well as practical implementation of the designed avionics systems are discussed, and results of field tests are presented.
by Alexander Omelchenko.
S.M.and E.A.A.
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Тризна, Олександра Олександрівна y Ann Panasyuk. "PERFORMANCE PROBLEMS OF AVIONICS VISUALIZATION OBSERVATION IN NEW AIRCRAFTS GENERATION". Thesis, К.: НАУ. 2014,- 164 с, 2014. http://er.nau.edu.ua/handle/NAU/12091.
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Doverfelt, Rickard. "An Evaluation of Ethernet as Data Transport System in Avionics". Thesis, KTH, Skolan för elektroteknik och datavetenskap (EECS), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-284584.
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ÅF Digital Solutions AB are looking to replace their current legacy system for audio transmissions within aircrafts with a new system based on Ethernet. They also want the system to be as closely matching the current Audio Integration System as possible as well as preferably using commercial off the shelf components. The issue evaluated in this thesis is whether it is feasible to port the legacy protocol over to an Ethernet based solution with as few modifications as possible, what performance requirements are present on the Ethernet solution as well as what remaining capacity is available in the network. Furthermore is ÅF Digital Solutions AB interested in what avionics related Ethernet based protocols and standards are already present on the market.The work is conducted in two tracks - one track of experimental measurements and statistical analysis of the latency present in the proposed solutions and one track with a survey regarding the integration of the present Audio Integration System protocol into the propesed Ethernet based solutions. The study finds two standards present on the market: Avionics Full-Duplex Ethernet (AFDX) and Time-Triggered Ethernet (TTEthernet). Two prototype implementations are built, one implementing AFDX and one custom built upon Ethernet and UDP. The latency of these are measured and found to be largely similar at ideal conditions. Ethernet is found to be more flexible, whilst AFDX allow for interoperation with other manufacturers and TTEthernet facilitates strict timing requirements at the cost of specialised hardware. The bandwidth utilisation of AFDX at ideal conditions is found to be 0.980% per stream and for the Ethernet solution 0.979% per stream.It is proposed that ÅF Digital Solutions AB pursue a custom Ethernet based solution unless they require interoperability on the same network with other manufacturers as a custom solution with full control over the network allows the largest flexibility in regards to timings and load. If interoperability is required is AFDX proposed instead as it is a standardised protocol and without the, for ÅF Digital Solutions AB, unnecessary overhead of TTEthernet.Åf Digital Solutions AB vill undersöka möjligheterna att byta sitt nuvarande legacysystem för kommunikation inom flygplan till ett Ethernet-baserat system. Detta på ett sätt som håller implementationen så nära deras nuvarande Audio Integration System som möjligt. Problemet som undersöks är huruvida det är rimligt att flytta legacyprotokollet till Ethernet med så lite modifikationer som möjligt. Utöver detta vill ÅF Digital Solutions AB veta prestandakraven som blir på en Ethernet-lösning samt hur mycket resterande kapacitet som eventuellt finns kvar för framtida användning. Vidare vill de veta vilka standarder som redan finns på marknaden.Arbetet genomförs genom två spår - ett med experimentella mätningar och statistisk analys och en med ett case-study av integrationen av Audio Integration System och Ethernet. Undersökningen finner två standarder på marknaden relaterat till avionik; Avionics Full-Duplex Ethernet (AFDX) samt Time-Triggered Ethernet (TTEthernet).Två prototyper byggs, en baserad på AFDX och en baserad på UDP och Ethernet. Latencyn för dessa två mäts och finns vara snarlika vid deras respektive ideala scenarion. Ethernet finns vara mer flexibelt, AFDX merinteroperabel och TTEthernet mer lämplig vid strikta tidskrav. Bandbreddsutnyttjandet för AFDX finns vara 0.980% vid ideala förhållanden och 0.979% för Ethernetvid ideala förhållanden.Det rekommenderas att ÅF Digital Solutions använder sig av en egenutformad Ethernetbaserad lösning om de inte har krav på interoperabilitet ty det ger mer flexibilietet gällande tidskrav, protokoll och dataflödet.
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Seppi, Antony. "A Case for Avionics in Greene County and Southwestern Ohio". University of Cincinnati / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1277003167.
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Aman, Shah Shahani. "System level airborne avionics prognostics for maintenance, repair and overhaul". Thesis, Cranfield University, 2016. http://dspace.lib.cranfield.ac.uk/handle/1826/11844.
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The aim of this study is to propose an alternative approach in prognostics for
airborne avionics system in order to enhance maintenance process and aircraft
availability. The objectives are to analyse the dependency of avionic systems
for fault propagation behaviour degradation, research and develop methods to
predict the remaining useful life of avionics Line Replaceable Units (LRU),
research and develop methods to evaluate and predict the degradation
performances of avionic systems, and lastly to develop software simulation
systems to evaluate methods developed.
One of the many stakeholders in the aircraft lifecycle includes the Maintenance,
Repair and Overhaul (MRO) industry. The predictable logistics process to some
degree as an outcome of IVHM gives benefit to the MRO industry.
In this thesis, a new integrated numerical methodology called ‘System Level
Airborne Avionic Prognostics’ or SLAAP is developed; looking at a top level
solution in prognostics. Overall, this research consists of two main elements.
One is to thoroughly understand and analyse data that could be utilised.
Secondly, is to apply the developed methodology using the enhanced
prognostic methodology.
Readily available fault tree data is used to analyse the dependencies of each
component within the LRUs, and performance were simulated using the linear
Markov Model to estimate the time to failure. A hybrid approach prognostics
model is then integrated with the prognostics measures that include
environmental factors that contribute to the failure of a system, such as
temperature. This research attempts to use data that is closest to the data
available in the maintenance repair and overhaul industry.
Based on a case study on Enhanced Ground Proximity Warning System
(EGPWS), the prognostics methodology developed showed a sufficiently close
approximation to the Mean Time Before Failure (MTBF) data supplied by the Original Equipment Manufacturer (OEM). This validation gives confidence that
the proposed methodology will achieve its objectives and it should be further
developed for use in the systems design process.
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Palacios, Medinacelli Luis. "Knowledge Discovery for Avionics Maintenance : An Unsupervised Concept Learning Approach". Thesis, Université Paris-Saclay (ComUE), 2019. http://www.theses.fr/2019SACLS130/document.
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Dans cette thèse, nous étudions le problème de l’analyse de signatures de pannes dans le domaine de la maintenance avionique, afin d’identifier les défaillances au sein d’équipements en panne et suggérer des actions correctives permettant de les réparer. La thèse a été réalisée dans le cadre d’une convention CIFRE entre Thales Research & Technology et l’Université Paris-Sud. Les motivations sont donc à la fois théoriques et industrielles. Une signature de panne devrait fournir toutes les informations nécessaires pour identifier, comprendre et réparer la panne. Pour comprendre le mécanisme la panne son identification doit donc être explicable. Nous proposons une approche à base d’ontologies pour modéliser le domaine d’étude, permettant une interprétation automatisée des tests techniques réalisés afin d’identifier les pannes et obtenir les actions correctives associées. Il s’agit d’une approche d’apprentissage de concepts permettant de découvrir des concepts représentant les signatures de pannes tout en fournissant des explications sur les choix de propositions de réparations. Comme les signatures ne sont pas connues a priori, un algorithme d’apprentissage automatique non supervisé approxime les définitions des concepts. Les signatures apprises sont fournies sous forme de définitions de la logique de description (DL) et ces définitions servent d’explications. Contrairement aux techniques courantes d’apprentissage de concepts conçues pour faire de l’apprentissage supervisé ou basées sur l’analyse de patterns fréquents au sein de gros volumes de données, l’approche proposée adopte une perspective différente. Elle repose sur une construction bottom-up de l’ontologie. Le processus d’apprentissage est réalisé via un opérateur de raffinement appliqué sur l’espace des expressions de concepts et le processus est guidé par les données, c’est-à-dire les individus de l’ontologie. Ainsi, les notions de justifications, de concepts plus spécifiques et de raffinement de concepts ont été révisées et adaptées pour correspondre à nos besoins. L’approche a ensuite été appliquée au problème de la maintenance avionique. Un prototype a été implémenté et mis en œuvre au sein de Thales Avionics à titre de preuve de conceptIn this thesis we explore the problem of signature analysis in avionics maintenance, to identify failures in faulty equipment and suggest corrective actions to resolve the failure. The thesis takes place in the context of a CIFRE convention between Thales R&T and the Université Paris-Sud, thus it has both a theoretical and an industrial motivation. The signature of a failure provides all the information necessary to understand, identify and ultimately repair a failure. Thus when identifying the signature of a failure it is important to make it explainable. We propose an ontology based approach to model the domain, that provides a level of automatic interpretation of the highly technical tests performed in the equipment. Once the tests can be interpreted, corrective actions are associated to them. The approach is rooted on concept learning, used to approximate description logic concepts that represent the failure signatures. Since these signatures are not known in advance, we require an unsupervised learning algorithm to compute the approximations. In our approach the learned signatures are provided as description logics (DL) definitions which in turn are associated to a minimal set of axioms in the A-Box. These serve as explanations for the discovered signatures. Thus providing a glass-box approach to trace the reasons on how and why a signature was obtained. Current concept learning techniques are either designed for supervised learning problems, or rely on frequent patterns and large amounts of data. We use a different perspective, and rely on a bottom-up construction of the ontology. Similarly to other approaches, the learning process is achieved through a refinement operator that traverses the space of concept expressions, but an important difference is that in our algorithms this search is guided by the information of the individuals in the ontology. To this end the notions of justifications in ontologies, most specific concepts and concept refinements, are revised and adapted to our needs. The approach is then adapted to the specific avionics maintenance case in Thales Avionics, where a prototype has been implemented to test and evaluate the approach as a proof of concept
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Sung-Yuan, Ko. "Investigation and development of DSP algorithms/hardware for real time power spectral density estimation". Thesis, Cranfield University, 1993. http://hdl.handle.net/1826/4197.
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This research is concerned with the Power Spectrum Density Estimation with em-
phasIze on the bigh-resolution algorithms and their real-time implementations.
Tl-ie classical PSD estimation methods are fast and robust. but their resolutions may
not be adequate when the record length is short. On the other hand when the
record length is short the autoregressive parametric methods have higher resolution
capability, but they may have spurious peaks if the order of the model is chosen too
high in the attempt to increase the resolution when the SNR is low. An algorithm
is proposed to combine the spectrum of the classical method and the autoregressive
model. This allows the overestimation of the order of the autoregressive model. The
spuriot-is peaks that result are then suppressed by the low values in the spectrum of the
classical nict liods. I'lic wide specl ral mairilobe of the classical method, on the other
liand, serves to indicate the area where the true signals are located. This alleviates the
difficult order selection problem of the parametric methods. An adaptive version of
this method is also proposed. It is based on the adaptive autoregressive and adaptive
maximum eigenvector concept. It can track a slowly changing environment. With
I lie combination of these txN, o methods. it is shown that it. has the high-resolution
performance of AR method ýN, ith improved performance in the noisy environment.
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Weston, Bron O. Duren Russell Walker Thompson Michael Wayne. "Data compression application to the MIL-STD 1553 avionics data bus". Waco, Tex. : Baylor University, 2005. http://hdl.handle.net/2104/2882.
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Bolinder, Richard. "Atmospheric Radiation Effects Study on Avionics : An Analysis of NFF Errors". Thesis, Linköpings universitet, Programvara och system, 2013. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-96726.
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No fault found (NFF) errors, i.e. errors which origin has not been established, irregularly occur in electronic devices. The actual cause of such errors varies but one, possibly more prominent, source for these soft errors is atmospheric radiation. The overarching aim of this thesis is to demonstrate: 1) the importance of keeping the atmospheric radiation environment in mind when designing robust airborne systems, 2) how to take this environment into consideration when applying mitigation techniques which may drastically reduce the risk of SEEs (Single Event Effects) which can cause NFF errors. To achieve these goals, Part 1 of this thesis describes how cosmic rays affect electronics (i.e. what kind of errors may be induced), which types of devices are susceptible to radiation, and why this subject is of extra importance for airborne systems. In addition, soft error mitigation techniques, which may be applied at different design levels to reduce the soft error rate (SER) or the impact of soft errors, are also presented. The aim is further corroborated by Part 2. Five subsystems of a modern aircraft are studied and real examples of failures potentially induced by atmospheric radiation are presented. For each of the five systems, all errors that have been reported for these (in the past few years) have been studied, and the number of errors found to be potentially induced by cosmic radiation has been listed and compared to number of expected soft errors based on calculations and previous experimental tests.
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Dova, Vincent H. "Software-defined avionics and mission systems in future vertical lift aircraft". Thesis, Monterey, California: Naval Postgraduate School, 2015. http://hdl.handle.net/10945/45181.
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Approved for public release; distribution is unlimitedIntegrated Modular Avionics, or IMA, has been a notable trend in aircraft avionics for the past two decades, promising significant size, weight, and power-consumption (SWAP) gains, radically increased sensors fusion, and streamlined support costs. Despite the demonstrated success of IMA systems in commercial airliners such as the Airbus A380 and the Boeing 787, military rotorcraft in the service of the United States Joint services have yet to benefit significantly from this technology. At long last, that may be about to change. The Future Vertical Lift Family of Systems (FVL) initiative was launched in 2008, with the aim of re-inventing the entire U.S. rotary wing fleet. Within the FVL program’s projected timeline, many signs point to the emergence of a second-generation IMA technology (IMA2G), which will leverage extensive virtualization and software-defined functionality to deliver further SWAP gains, fault-tolerance, and system capability. Development efforts are indeed already underway to integrate such advanced IMA features into the FVL’s Joint Common Architecture. This thesis assesses the maturity of IMA2G critical path technologies, validates the alignment between IMA2G benefits and desired FVL attributes, and describes the operational impact that software-defined avionics and mission systems might have on future rotary wing aircraft.
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Westenhaver, Michael S. "A Human Factors Evaluation of the Space Shuttle Cockpit Avionics Upgrade". Thesis, Monterey, California. Naval Postgraduate School, 2012. http://hdl.handle.net/10945/17476.
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Approved for public release; distribution is unlimitedDuring the late 90s, NASA retrofitted the Space Shuttle fleet with a glass cockpit. The new displays replicated legacy formats developed in the 70s, and did not leverage 20 years of display technology and human factors advances. To address this shortcoming the Cockpit Avionics Upgrade (CAU) was initiated to reduce mental workload (MW), increase situational awareness (SA), and enhance performance. Despite the CAU demonstrating improvements in MW, SA, and performance, it was cancelled. Consequently, recorded astronaut data from using the baseline and CAU cockpit configurations was never tied back to cockpit design. This study assesses the CAU design employing human factors principles, evaluates baseline and CAU simulation data, and traces MW and SA differences back to CAU design modifications. Significant improvements were found in all measures and across all conditions. These improvements were found to be greater for ascent scenarios than for entry. From the findings, recommendations for the design and evaluation of future spacecraft cockpits are made.
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Chang, Daniel W. "Profile of an effective engineering manager at the Naval Avionics Center". Thesis, Monterey, California. Naval Postgraduate School, 1991. http://hdl.handle.net/10945/28472.
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Wölfl, Andreas [Verfasser] y Harald [Akademischer Betreuer] Kosch. "Data Management in Certified Avionics Systems / Andreas Wölfl ; Betreuer: Harald Kosch". Passau : Universität Passau, 2018. http://d-nb.info/1168473349/34.
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