Bibliografías temáticas / Avionics

Literatura académica sobre el tema "Avionics"

Autor: Grafiati
Publicado: 4 de junio de 2021
Última modificación: 29 de julio de 2024

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Artículos de revistas sobre el tema "Avionics"

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Sun, Yi Gang y Li Sun. "The Design of Avionics System Interfaces Emulation and Verification Platform Based on QAR Data". Applied Mechanics and Materials 668-669 (octubre de 2014): 879–83. http://dx.doi.org/10.4028/www.scientific.net/amm.668-669.879.

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In order to avoid the complex mathematical modeling and ensure the reliability of avionics system verification, this paper has designed an interfaces emulation and verification platform of avionics system based on QAR data. Platform includes 2 parts: Emulator and Simulator. Simulator generates the flight environmental data which is come from QAR and transforms the data into excitation signal of devices. Emulator emulates the interface features of avionic devices according to the ICD and can be replaced with real devices. By comparing the actual input-output data of devices with QAR theoretical data, this platform can evaluate the running performance of avionic systems or devices and the rationality of the ICD.
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2

Sahputra, Afandi, Abdul Rasyid y Dika Aprillia. "Pemanfaatan Automatic Direction Finder KR87 Pada Avionics System Trainer AT-01 Untuk Meningkatkan Kompetensi Lulusan SMK Penerbangan". TRIDARMA: Pengabdian Kepada Masyarakat (PkM) 5, n.º 1 (30 de mayo de 2022): 272–81. http://dx.doi.org/10.35335/abdimas.v5i1.2513.

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SMK PBD adalah salah satu sekolah penerbangan yang ada di kota Medan. SMK PBD Medan menanamkan kepada setiap murid-murid untuk memiliki karakter mandiri dan kreatif. Hal ini juga didukung oleh matapelajaran Airframe maupun Avionics. PKM POLTEKBANG Medan mengusulkan program pelatihan Pemanfaatan Automatic Direction Finder KR87 Pada Avionics System Trainer AT-01 untuk meningkatkan Kompetensi Lulusan SMK Penerbangan. Program tersebut diharapkan dapat meningkatkan kemampuan proses mengoperasikan ADF pada Avionic System Trainer AT- 01 dan membantu peseta menambah wawasan dan ilmu pengetahuan mengenai ADF yang diperoleh dari pelatihan. Hasil dari kegitan ini adalah pelatihan berupa pemanfaatan Automatic Direction Finder KR87 Pada Avionics System Trainer AT-01 selama 3 hari untuk meningkatkan kompetensi lulusan SMK Penerbangan Pulo Brayan Darat
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3

Nadesakumar, A., R. M. Crowder y C. J. Harris. "Advanced System Concepts for Future Civil Aircraft—an Overview of Avionic Architectures". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 209, n.º 4 (diciembre de 1995): 265–72. http://dx.doi.org/10.1243/pime_proc_1995_209_300_02.

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The avionics systems of state-of-the-art commercial aircraft have become increasingly complex and sophisticated, in order to meet the ever increasing performance and reliability requirements. With the capability of the avionics technology improving by an order of magnitude every few years, it is envisaged that the current philosophy of one box-per-function will soon reach its limits in terms of cost, functionality, reliability, and certification. The proposed solution is the integrated systems configuration, using distributed processing, where the computational resources are shared between many functions, therefore improving the reliability, availability, survivability, and extensibility of the overall system. Futhermore, this approach will also provide the potential for reducing the acquisition, maintenance and operating costs. The paper discusses the limitations of the current avionic system's architecture in dealing with the high levels of functionality required by the state-of-the-art aircraft, and discusses the philosophy of the integrated modular avionics, which represents a change in philosophy of avionics design to a decentralized, distributed architecture that allows interchangeable components within a distributed aircraft avionic system. The paper also addresses a number of specific issues considered necessary for the implementation of a decentralized, distributed architecture such as data bus requirements, electromagnetic and radio frequency prevention, and fault tolerance But it also argues that for true systems integration, a new culture is required based on open systems with a set of inherent quality features such as conformance, robustness, extendibility, compatibility, and reusability built into the architecture.
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Huang, Jin, Bo Xu y Kun Qiu. "Modeling and Simulation of FC-AE-ASM Network". Advanced Materials Research 748 (agosto de 2013): 941–45. http://dx.doi.org/10.4028/www.scientific.net/amr.748.941.

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Fibre Channel (FC) as a Universal Avionics Network (UAN) candidate solution for the advanced integrated avionics systems can enable high-bandwidth, low-latency, high-reliability and hard real-time communication on aircraft platforms spanning military and commercial applications. Fibre Channel Avionics Environment-Anonymous Subscriber Messaging protocol (FC-AE-ASM) is one of the five high level protocols in fiber channel avionic environment which is used to transport command, control, signal processing and sensor / video data of the aircraft[1,2].The objective of this paper is to conduct a modeling and simulation on the performance of the FC–AE-ASM network. Through modeling the message transmission of the FC-AE-ASM with accompanying Eclipse, some network performance parameters such as bandwidth, throughput and end-to-end message delay can be gained and analyzed.
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5

Wang, Ying, Jian Yong Wang y Lei Wang. "A Transformation-Based Integrated Modular Avionics Software Model Construction Approach". Applied Mechanics and Materials 668-669 (octubre de 2014): 343–46. http://dx.doi.org/10.4028/www.scientific.net/amm.668-669.343.

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Modern avionic software usually runs on the ARINC653-compatible OS based on the Integrated Modular Avionics (IMA) architecture. Although existing ARINC653 annex of Architecture Analysis & Design Language (AADL) can be used to construct IMA models straightforward, it is still hard and error-prone work for avionics engineers because of the complexity of ARINC653 and manual modeling. Therefore, a hierarchical transformation-based approach is proposed to obtain correct IMA models step by step from general AADL models, rather than its ARINC653 annex. The typical transformation algorithm is given and a tool is also developed to help accomplish this approach automatically and effectively.
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6

Zhang, Jian Dong, En Long Cao, Yong Wu y Guo Qing Shi. "Designing and Realizing of Universal Test and Analysis System of Avionics Data Bus". Applied Mechanics and Materials 284-287 (enero de 2013): 2371–74. http://dx.doi.org/10.4028/www.scientific.net/amm.284-287.2371.

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In modern combat aircrafts, avionics integrated systems play an increasingly important role. Bus test and analysis system is used as a testing platform for the testing, debugging, maintenance and monitoring of airborne electronic equipment, which could rapidly detect and identify the working status of the bus. This paper discusses the general avionics data bus test system design and implementation, which focuses on the test system design, system management, software development, and the bus information flow management of the whole system. The universal test and analysis system is based on the bus test analysis platform of ICD database that can effectively test ARINC429 bus and 1553B bus. Through integrating the platform into the simulation system, it can complete the closed-loop test of the integrated avionics simulation test system, analyze the state changes of various information flows during the process of bus communication, test and verify the active status and logical sequence of avionic fire control test systems, which has achieved very good results in the practical engineering applications.
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7

Jiang, Na, Chunpeng Zhang, Yang Cao y Rixin Zhan. "Application of prognostic and health management in avionics system". Highlights in Science, Engineering and Technology 7 (3 de agosto de 2022): 1–9. http://dx.doi.org/10.54097/hset.v7i.988.

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Currently, most aircraft avionics systems are maintained based on reported failures or periodic system replacement. However, the evolution of prognostic and health management (PHM) concepts from mechanical to electronic systems and further to avionics system maintenance has been driven by changes in weapon platform procurement and support requirements. At the same time, with the increasing complexity of avionics design, integrated modular avionics (IMA) came into being. The appearance of IMA design concept marks the gradual transition of avionics system from distributed joint architecture to integrated architecture, which also provides the foundation for PHM technology to be applied to avionics system. This paper reviews the application and research status of predictive and health management system technology in avionics system.
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8

Zieja, Mariusz, Andrzej Szelmanowski, Andrzej Pazur y Grzegorz Kowalczyk. "Computer Life-Cycle Management System for Avionics Software as a Tool for Supporting the Sustainable Development of Air Transport". Sustainability 13, n.º 3 (2 de febrero de 2021): 1547. http://dx.doi.org/10.3390/su13031547.

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The article presents selected results of analytical and design works undertaken at the Air Force Institute of Technology (AFIT) in the field of building a computer support and software lifecycle management system that is critical for flight safety. The aim of the work undertaken is to develop methods and carry out verification and testing in order to detect errors in the developed avionics software for compliance with the requirements of the DO-178C standard and its production, certification, and implementation on board aircraft. The authors developed an original computer system within the implemented requirements used in the construction and certification of avionic onboard devices and their software (among others, DO-254, DO-178C, AQAP 2210, ARP 4761, ARP 4754A). The conducted analysis involved three basic groups of avionics software development processes, i.e., software planning, creation, and integration. Examples of solutions implemented in the constructed computer system were presented for each of these process groups. The theoretical basis of the new method for predicting vulnerabilities in the software implemented within integrated avionic systems using branching processes is discussed. It was demonstrated that the possibility of predicting vulnerabilities in future software versions could have a significant impact on assessing the risk associated with software safety in the course of its lifecycle. It was indicated that some of the existing quantitative models for analyzing software vulnerabilities were developed based on dedicated software data, which is why actual scenario implementation may be limited. DO-178C standard requirements for the process of developing avionics software were implemented in the helmet-mounted flight parameter display system constructed at AFIT. The requirements of the DO-178C and AQAP 2210 standards were shown to be met in the example of the software developed for a graphics computer, managing the operating modes of this system.
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9

Guryanov, A. V. "RESSEARCH OF VARIANTS FOR ORGANIZING THE SUPPLY CHAIN OF AVIONIC EQUIPMENT TO MAINTAIN THE SERVICEABILITY OF AVIONICS OBJECTS". System analysis and logistics 4, n.º 30 (22 de diciembre de 2021): 106–13. http://dx.doi.org/10.31799/2077-5687-2021-4-106-113.

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The presented study deals with the organization of supply chains for spare serviceable avionics equipment from the perspective of decision makers, heads of instrument-making enterprises. An extremely important issue is the determination of key parameters of avionics spares objects. On the basis of the conducted research, the element base of the serviceable avionics equipment facilities and conditions of operation, recovery of serviceability are considered. Due to the complexity of approaches to avionics objects, the article provides a fixation of key parameters, defines the distinctive features of exactly the avionics spare serviceable avionics equipment, which will determine new requirements and conditions of building the future supply chain. As a result of the conducted research, the article presents a classification of methods for calculating serviceable avionics equipment, based also on the theory of recovery processes. On the basis of the performed system approach to the objects of avionics inventory and spare parts management, examples of supply chain organization variants are given. The presented research is of practical significance both when designing a new chain of supply of spares, and when modernizing the existing supply chains for spare serviceable avionics equipment.
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10

Zhang, Xiao-Jun. "Research on Anti-saturation Feedback Control Method for UAV Avionics System". MATEC Web of Conferences 232 (2018): 04008. http://dx.doi.org/10.1051/matecconf/201823204008.

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UAV avionics system is prone to saturation distortion under unsteady conditions, so anti-saturation control is needed. A control method of UAV avionics system based on anti-saturation feedback compensation is proposed. The anti-saturation control process of UAV avionics system is a multi-objective optimization process with multi-variables. The constrained parameter model of UAV avionics system control is constructed. Electromagnetic loss, torque, output power and other parameters are taken as constraint indexes, the original control information of UAV avionics system is treated with self-stabilization, the equivalent control circuit is designed, and the magnetic resonance transmission mode of avionics system is analyzed. An anti-saturation feedback tracking control method is used for steady-state control of the output voltage of the avionics system. The error compensation function is constructed to adjust the output adaptive parameters of the avionics system and the static anti-saturation compensator is constructed to compensate the power gain. The yaw error and the output steady-state error of the avionics system are reduced. The simulation results show that the proposed method has better output stability, lower output error, better real-time performance and better linear auto-disturbance rejection control performance.
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Tesis sobre el tema "Avionics"

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
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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.
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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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4

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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5

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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7

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, California
Fibre 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, NV
In 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, California
SAIC, 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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Libros sobre el tema "Avionics"

1

), Brinkman David (Ed, ed. Jane's Avionics. Coulsdon: Jane's Information Group, 1995.

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2

inc, United Air Lines, ed. Avionics fundamentals. Casper, WY: IAP, Inc., 1991.

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3

Collinson, R. P. G., ed. Introduction to Avionics. Dordrecht: Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-011-0007-6.

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Moir, Ian y Allan G. Seabridge. Military Avionics Systems. Chichester, UK: John Wiley & Sons, Ltd, 2006. http://dx.doi.org/10.1002/0470035463.

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Moir, Ian, Allan Seabridge y Malcolm Jukes. Civil Avionics Systems. Chichester, UK: John Wiley & Sons, Ltd, 2013. http://dx.doi.org/10.1002/9781118536704.

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Kayton, Myron y Walter R. Fried, eds. Avionics Navigation Systems. Hoboken, NJ, USA: John Wiley & Sons, Inc., 1997. http://dx.doi.org/10.1002/9780470172704.

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Collinson, R. P. G. Introduction to avionics. London: New York, 1996.

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Malcolm, Jukes, ed. Military avionics systems. Hoboken, NJ: John Wiley & Sons, 2006.

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Seabridge, A. G. (Allan G.) y Jukes Malcolm, eds. Civil avionics systems. Chichester, West Sussex: Wiley, 2013.

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Moir, I. Military avionics systems. Chichester, England: John Wiley & Sons Ltd., 2006.

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Capítulos de libros sobre el tema "Avionics"

1

Weik, Martin H. "avionics". En Computer Science and Communications Dictionary, 93. Boston, MA: Springer US, 2000. http://dx.doi.org/10.1007/1-4020-0613-6_1210.

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Sarma, Kalluri R., Steve Grothe y Aaron Gannon. "Avionics Displays". En Handbook of Visual Display Technology, 253–74. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-14346-0_168.

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Sarma, Kalluri R., Steve Grothe y Aaron Gannon. "Avionics Displays". En Handbook of Visual Display Technology, 1–17. Berlin, Heidelberg: Springer Berlin Heidelberg, 2015. http://dx.doi.org/10.1007/978-3-642-35947-7_168-1.

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Weik, Martin H. "avionics architecture". En Computer Science and Communications Dictionary, 93. Boston, MA: Springer US, 2000. http://dx.doi.org/10.1007/1-4020-0613-6_1211.

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Collinson, R. P. G. "Avionics systems integration". En Introduction to Avionics, 406–30. Dordrecht: Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-011-0007-6_9.

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Collinson, R. P. G. "Avionics Systems Integration". En Introduction to Avionics Systems, 459–87. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-0708-5_9.

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Collinson, R. P. G. "Avionics Systems Integration". En Introduction to Avionics Systems, 433–58. Boston, MA: Springer US, 2003. http://dx.doi.org/10.1007/978-1-4419-7466-2_9.

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Weik, Martin H. "open avionics architecture". En Computer Science and Communications Dictionary, 1143. Boston, MA: Springer US, 2000. http://dx.doi.org/10.1007/1-4020-0613-6_12805.

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Weik, Martin H. "integrated modular avionics". En Computer Science and Communications Dictionary, 801. Boston, MA: Springer US, 2000. http://dx.doi.org/10.1007/1-4020-0613-6_9228.

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Reichel, Reinhard. "Integrated avionics architectures". En Proceedings, 921. Wiesbaden: Springer Fachmedien Wiesbaden, 2019. http://dx.doi.org/10.1007/978-3-658-25939-6_71.

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Actas de conferencias sobre el tema "Avionics"

1

Watkins, Mike y Doug Garrette. "Advancing airlift avionics - C-17 avionics suite". En Aerospace Design Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-986.

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WATKINS, MIKE y DOUG GARRETTE. "Advancing airlift avionics - C-17 avionics suite". En Aerospace Design Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-1243.

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Shibata, Minoru y Haruo Notoh. "Avionics simulator". En Aerospace/Defense Sensing and Controls, editado por Robert Lee Murrer, Jr. SPIE, 1996. http://dx.doi.org/10.1117/12.241115.

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VanderLeest, Steven H. "Avionics Linux". En 2023 IEEE/AIAA 42nd Digital Avionics Systems Conference (DASC). IEEE, 2023. http://dx.doi.org/10.1109/dasc58513.2023.10311247.

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Watkins, Christopher B. y Randy Walter. "Transitioning from federated avionics architectures to Integrated Modular Avionics". En 2007 IEEE/AIAA 26th Digital Avionics Systems Conference. IEEE, 2007. http://dx.doi.org/10.1109/dasc.2007.4391842.

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Samraj, Selvadhas. "Avionics systems integration using avionics full duplex swithched ethernet". En 2007 IEEE/AIAA 26th Digital Avionics Systems Conference. IEEE, 2007. http://dx.doi.org/10.1109/dasc.2007.4391867.

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Zheng Li, Qiao Li y Huagang Xiong. "Avionics clouds: A generic scheme for future avionics systems". En 2012 IEEE/AIAA 31st Digital Avionics Systems Conference (DASC). IEEE, 2012. http://dx.doi.org/10.1109/dasc.2012.6382402.

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Zheng Li. "Avionics clouds: A generic scheme for future avionics systems". En 2012 IEEE/AIAA 31st Digital Avionics Systems Conference (DASC). IEEE, 2012. http://dx.doi.org/10.1109/dasc.2012.6383082.

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Dandekar, A. J. y L. E. Farhner. "Avionics Display Systems". En Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1988. http://dx.doi.org/10.4271/881371.

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MORRISON, R. y JON SIMMONS. "Advanced avionics interconnection". En Digital Avionics Systems Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-3856.

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Informes sobre el tema "Avionics"

1

Bedzyk, William L., Donald R. Czech, Thomas J. Dickman, Frank S. Gruber, John F. Myers y John F. Myers. Advanced Avionics System Analysis. Modular Avionics Cost Benefit Study Formulation. Fort Belvoir, VA: Defense Technical Information Center, febrero de 1987. http://dx.doi.org/10.21236/ada189019.

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NAVAL AIR SYSTEMS COMMAND ARLINGTON VA. Advanced Avionics Architecture and Technology Review. Executive Summary and Volume 1, Avionics Technology. Volume 2. Avionics Systems Engineering. Fort Belvoir, VA: Defense Technical Information Center, agosto de 1993. http://dx.doi.org/10.21236/ada273630.

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Risko, Theodore. Avionics Diagnostic System (ADS). Fort Belvoir, VA: Defense Technical Information Center, junio de 1999. http://dx.doi.org/10.21236/ada368423.

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Kellog, David L., J. K. Henderson, Mike J. Harris y Anthony J. Schiavone. Core Avionics and Standardization. Fort Belvoir, VA: Defense Technical Information Center, marzo de 1992. http://dx.doi.org/10.21236/ada248326.

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Damania, Bhavesh, Steve Vestal, Devesh Bhatt y Rashmi Bhatt. Avionics System Performance Management. Fort Belvoir, VA: Defense Technical Information Center, mayo de 1998. http://dx.doi.org/10.21236/ada388145.

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NATIONAL RESEARCH COUNCIL WASHINGTON DC. Aging Avionics in Military Aircraft. Fort Belvoir, VA: Defense Technical Information Center, mayo de 2001. http://dx.doi.org/10.21236/ada397119.

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Havey, G., S. Lewis y G. Seifert. Avionics/Electronics Quick Reliability Assessment. Fort Belvoir, VA: Defense Technical Information Center, marzo de 1998. http://dx.doi.org/10.21236/ada342681.

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Guiliano, John E. Rapid Avionics Test Modification Capability. Fort Belvoir, VA: Defense Technical Information Center, octubre de 1999. http://dx.doi.org/10.21236/ada388094.

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Jones, Sid. Fibre Channel Avionics Bus Monitor. Fort Belvoir, VA: Defense Technical Information Center, febrero de 2001. http://dx.doi.org/10.21236/ada389673.

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Andrews, Robert B. Networked Avionics Part Task Trainer. Fort Belvoir, VA: Defense Technical Information Center, junio de 2000. http://dx.doi.org/10.21236/ada378377.

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