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Journal articles on the topic 'Avionic systems'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 May 2024

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1

Sun, Yi Gang, and Li Sun. "The Design of Avionics System Interfaces Emulation and Verification Platform Based on QAR Data." Applied Mechanics and Materials 668-669 (October 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

Nadesakumar, A., R. M. Crowder, and 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, no. 4 (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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3

Dove, Billy L. "Validation Methods for Programmable Avionic Systems." Safety and Reliability 6, no. 3 (1986): 7–17. http://dx.doi.org/10.1080/09617353.1986.11691130.

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4

Huang, Jin, Bo Xu, and Kun Qiu. "Modeling and Simulation of FC-AE-ASM Network." Advanced Materials Research 748 (August 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

Burger, Stefan, and Oliver Hummel. "Lessons Learnt from Gauging Software Metrics of Cabin Software in a Commercial Airliner." ISRN Software Engineering 2012 (October 15, 2012): 1–11. http://dx.doi.org/10.5402/2012/162305.

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In order to achieve high safety standards, avionic software needs to be developed with very high requirements regarding safety, reliability, and determinism as well as real-time constraints, which are often in conflict with the development of maintainable software systems. Nevertheless, the ability to change the software of an airplane is of increasing importance, since it consists of a multitude of partially hardware-specific subsystems which may need replacement during a plane’s lifespan of typically numerous decades. Thus, as a first step towards optimizing maintainability of avionic software we have benchmarked the cabin software of a commercial airliner with common software metrics. Such a benchmarking of avionic software contributes valuable insights into the current practice of developing critical software and the application of software metrics in this context. We conclude from the obtained results that it is important to pay more attention to long-term maintainability of aviation software. Additionally we have derived some initial recommendations for the development of future avionic software systems.

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6

Aakash, Kislaya, Armaan Aditya, and G. Srinivas. "Recent Developments of Modern Avionic Systems in Aeronautical Applications." Journal of Advanced Research in Dynamical and Control Systems 11, no. 12-SPECIAL ISSUE (2019): 923–29. http://dx.doi.org/10.5373/jardcs/v11sp12/20193294.

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7

Jastrzębski, Grzegorz, Paweł Szczepaniak, and Michał Jóźko. "Issues Related To Troubleshooting Of Avionic Hydraulic Units." Journal of KONBiN 30, no. 1 (2014): 59–73. http://dx.doi.org/10.2478/jok-2014-0015.

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

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8

Zhang, Jian Dong, En Long Cao, Yong Wu, and Guo Qing Shi. "Designing and Realizing of Universal Test and Analysis System of Avionics Data Bus." Applied Mechanics and Materials 284-287 (January 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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9

Banerjee, P. Pat, David He, Shenliang Wu, and Eric Bechhoefer. "Discriminant Analysis Based Prognostics of Avionic Systems." IEEE Transactions on Systems, Man, and Cybernetics, Part C (Applications and Reviews) 37, no. 6 (2007): 1318–26. http://dx.doi.org/10.1109/tsmcc.2007.905838.

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10

Johar, Harminder Singh, Abhijit Bhattacharyya, and Srinivas Rao S. "Fault Tolerant Power Supply for Aircraft Store Interface." Defence Science Journal 72, no. 5 (2022): 679–86. http://dx.doi.org/10.14429/dsj.72.17737.

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This paper brings out the design of a fault-tolerant power supply unit for the aircraft-store interface. This switched mode power supply provides multiple 30 V regulated and isolated DC outputs required for pre-launch preparations and auto-launch operations of avionic sub-systems in a store. 3Ø-115V-400Hz-AC supply as well as 27V-DC supply are available from a fighter aircraft for powering up of any store. Power (wattage) output from 27V/10A DC is inadequate to power up various onboard avionic sub-systems in guided stores involving seekers and other avionics. Hence, it is planned to convert available high power 3Ø-115V-400Hz-AC supply for applications requiring higher wattages (of the order of 500 watts or more). This power supply provides multiple output options of 30V regulated and isolated DC supply with multiple input supplies from Aircraft, viz. 3Ø-115V-400Hz-AC, 1Ø-115V-400Hz-AC and 27V DC. One of the outputs provided is with hold-up capacitors, to cater for any input power interruptions as per requirements of MIL-STD-704F and GOST-19705-89 standards. This power supply is a ready-to-connect device and essentially consists of housing, components of DC to DC conversions, EMI/EMC filters, solid state power controllers, control switches, and control circuitry for monitoring signals.

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11

Fiszer, Roman, Zbigniew Matuszczak, Hubert Jakubowski, and Sebastian Jaskowiak. "Electrical supply of aircraft during parking." Journal of KONBiN 48, no. 1 (2018): 359–70. http://dx.doi.org/10.2478/jok-2018-0060.

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Abstract The elaboration discusses selected aspects of parking supply of aircraft with electricity generated by mobile, airfield sources. In terms of sublime electrical and electronic systems, as well as avionic systems installed on-board of contemporary aircraft, the quality of electricity supplied by ground sources results in their manufacturers facing with high requirements that are contained in relevant standards and regulations. The quality of electricity generated by ground sources and their compatibility have a direct impact, among others, on the calibration of aircraft avionics systems during the ground flight preparation, which directly contributes to the safety of air operations. Therefore, the possibility of constant real-time monitoring of the supplied electricity (specific parameters) enabling immediate identification, recording, adjusting the deviations, hence, preventing damage or improper preparation of an aircraft for flight, becomes a non-trivial issue.

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12

Zieja, Mariusz, Andrzej Szelmanowski, Andrzej Pazur, and Grzegorz Kowalczyk. "Computer Life-Cycle Management System for Avionics Software as a Tool for Supporting the Sustainable Development of Air Transport." Sustainability 13, no. 3 (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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13

Cui, Yiqian, Junyou Shi, and Zili Wang. "Backward Reconfiguration Management for Modular Avionic Reconfigurable Systems." IEEE Systems Journal 12, no. 1 (2018): 137–48. http://dx.doi.org/10.1109/jsyst.2016.2562020.

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14

Thomson, G. "Advances in electro-optic systems for targeting." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 212, no. 1 (1998): 1–19. http://dx.doi.org/10.1243/0954410981532090.

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Throughout history, ‘optics’ have been used as the primary sense for weapon aiming. Military aircraft have now been using electro-optic avionic systems for more than 50 years to provide aiming precision in a variety of targeting applications. Recent conflicts have made significant use of the precision of electro-optic (E-O) systems such as the thermal imaging and airborne laser designator (TIALD) to strike specific targets, by day and night, while minimizing the risk of unintentional collateral damage. Many of these E-O systems provide a convenient ‘CNN news compatible’ video and the use and effectiveness of the TIALD have been witnessed by many people on television. Perhaps not so obvious are the underlying advances in E-O technology and the extensive enhancements that have made this all possible. The United Kingdom is a world leader in E-O technology and continues to research and develop new systems to meet anticipated future needs. The author examines the basis for use of electro-optic avionics in targeting applications and describes the depth of the technology employed to meet the precision requirements. A few examples of E-O systems are examined, together with a discussion of future directions.

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15

Weiland, Monica Z., Brian A. Convery, Allen L. Zaklad, Wayne W. Zachary, Clarence A. Fry, and James W. Voorhees. "Active Man Machine Interface for Advanced Rotorcraft." Proceedings of the Human Factors and Ergonomics Society Annual Meeting 37, no. 15 (1993): 1032. http://dx.doi.org/10.1177/154193129303701504.

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The proliferation of digital avionic information presented to pilots has produced a critical need for intelligent avionic information management, particularly in the area of Caution, Warning, and Advisory (CWA) systems. This demonstration illustrates the role of an Active Man Machine Interface (AMMI) in the context of CWA systems in rotorcraft of the future. The basis of the AMMI's intelligence demonstrated here is provided by a cognitive model that 1) prunes the alert stream to only those messages that have meaning to the pilot depending on the tactical context, and 2) provide context-sensitive advice on the basis of the tactical context. The CWA AMMI is currently being designed using COGNET, an cognitive modelling methodology (Zachary, 1989), and implemented using BATON, a set of software tools used to implement and embed COGNET models into existing systems (Zachary et al, 1991).

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16

Swetha, K., Archana Sreekumar, Nithish N. Nath, and V. Radhamani Pillay. "Optimizing Resources in m-Redundant Avionic Systems - Comparative Evaluation." Procedia Computer Science 57 (2015): 1376–83. http://dx.doi.org/10.1016/j.procs.2015.07.453.

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17

Budroweit, Jan, Mattis Jaksch, Rubén Garcia Alía, Andrea Coronetti, and Alexander Kölpin. "Heavy Ion Induced Single Event Effects Characterization on an RF-Agile Transceiver for Flexible Multi-Band Radio Systems in NewSpace Avionics." Aerospace 7, no. 2 (2020): 14. http://dx.doi.org/10.3390/aerospace7020014.

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Nowadays, technologies have a massive impact on the design of avionic systems, even for the conservative space industry. In this paper, the single event effect (SEE) characterization of a highly integrated and radio frequency (RF) agile transceiver is being presented which is an outstanding candidate for future radio systems in NewSpace applications and space avionics. The device being investigated allows programmable re-configuration of RF specifications, where classical software-defined radios (SDR) only define an on-demand re-configuration of the signal processing. RF related configurations are untouched for common SDR and developed discretely by the specific application requirements. Due to the high integrity and complexity of the device under test (DUT), state-of-the-art radiation test procedures are not applicable and customized testing procedures need to be developed. The DUT shows a very robust response to linear energy transfer (LET) values up to 62.5 MeV.cm²/mg, without any destructives events and a moderate soft error rate.

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18

Ellis, S. M. "Dynamic software reconfiguration for fault-tolerant real-time avionic systems." Microprocessors and Microsystems 21, no. 1 (1997): 29–39. http://dx.doi.org/10.1016/s0141-9331(97)00017-3.

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19

Wilcock, G., A. Gleave, T. Totten, and R. Wilson. "The application of COTS technology in future modular avionic systems." Electronics & Communication Engineering Journal 13, no. 4 (2001): 183–92. http://dx.doi.org/10.1049/ecej:20010405.

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20

Suchenek, Marek A., Xitong Zheng та Golam Sarwar. "Non-invasive testing of real-time avionic μ-processor systems". Microprocessing and Microprogramming 27, № 1-5 (1989): 665–71. http://dx.doi.org/10.1016/0165-6074(89)90129-4.

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21

Sener, Eralp, and Gurhan Ertasgin. "Current-source 1-Ph inverter design for aircraft applications." Aircraft Engineering and Aerospace Technology 92, no. 8 (2020): 1295–305. http://dx.doi.org/10.1108/aeat-10-2019-0194.

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Purpose This paper aims to present an inverter with a current-source input for 400 Hz avionic systems to have a system which removes DC-link capacitors and presents a high efficiency. Design/methodology/approach A battery-powered DC link inductor generates a constant-current source. A single high-frequency switch is used to provide a sinusoidally modulated current before the inverter. The output of the switch is “unfolded” by a thyristor-based H-bridge inverter to generate an AC output current. The system uses a CL low-pass filter to obtain a 400 Hz pure sine wave by removing pulse width modulation components. Findings Simulations and Typhoon HIL real-time experiments were performed with closed-loop control to validate the proposed inverter concept while meeting the critical standards of MIL-STD-704F. Originality/value This current source inverter topology is suitable for avionic systems that require 400 Hz output frequency. The topology uses small DC-link inductor and eliminates bulky capacitor which determines the inverter lifetime.

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22

Smith, Kevin M. "Mission Performance Aid for Aerial Combat." International Journal of Aviation Systems, Operations and Training 3, no. 1 (2016): 1–19. http://dx.doi.org/10.4018/ijasot.2016010101.

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This paper addresses the concepts, methods, apparatus, and tools used to establish the operational requirements and system architecture for an advanced mission performance aid (the smart cockpit) that targets aerial combat operations. As the complexity of our modern avionic systems increase, it is important to define operational requirements and crew station display features early in the design cycle. Many observers insist higher quality front-end work be performed to reduce the growing number of back-end mistakes and cost overruns. This paper provides a top-down orientation that treats platform, avionics, weapons, and flight crew as an integrated system. This facilitates the analysis of system-wide functional attributes that represent key design drivers. Topics include mission decomposition, critical task analysis, information requirements, function allocation, and crew station display features. This material is intended for managers, engineers, human factor professionals, and test and evaluation flight crews improving mission performance in an increasingly complex environment.

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23

Szczepański, Cezary. "UAVS AND THEIR AVIONIC SYSTEMS: DEVELOPMENT TRENDS AND THEIR INFLUENCE ON POLISH RESEARCH AND MARKET." Aviation 19, no. 1 (2015): 49–57. http://dx.doi.org/10.3846/16487788.2015.1015295.

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In the paper the current status of development of UAVs and their avionic systems in Poland and worldwide is presented. Technology and operation development trends, as well as key factors influencing them are described. On this basis, research plans and suggested topics for development are proposed. The possibility of carrying them out in Poland under present conditions is taken into consideration.

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Hu, Menglan, Jun Luo, Yang Wang, and Bharadwaj Veeravalli. "Scheduling periodic task graphs for safety-critical time-triggered avionic systems." IEEE Transactions on Aerospace and Electronic Systems 51, no. 3 (2015): 2294–304. http://dx.doi.org/10.1109/taes.2015.140063.

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Weindorf, P. "The C-17 multifunction display: a building block for avionic systems." IEEE Aerospace and Electronic Systems Magazine 7, no. 7 (1992): 32–39. http://dx.doi.org/10.1109/62.149792.

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26

Pearson, Sheena, Steve Riddle, and Amer Saeed. "1.4.3 Traceability for the Development and Assessment of Safe Avionic Systems." INCOSE International Symposium 8, no. 1 (1998): 455–62. http://dx.doi.org/10.1002/j.2334-5837.1998.tb00066.x.

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27

Dudziak, Jacek, and Paweł Guła. "Design practice in the translation traditional and glass cockpit based on General Aviation I-31T aircraft." Aircraft Engineering and Aerospace Technology 89, no. 6 (2017): 749–56. http://dx.doi.org/10.1108/aeat-04-2016-0058.

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Purpose The aim of this paper is to present the results preparation of a new glass cockpit for a general aviation category airplane with a TP100 turboprop 180 kW engine. All the works were carried out within the framework of the European programme: “Efficient Systems and Propulsion for Small Aircraft” – ESPOSA. Design/methodology/approach As a part of the ongoing work, the avionics equipment available on the market were thoroughly analysed. Optimization of choice was defined at the level of costs, ergonomics and development requirements of the engine manufacturer. The paper presents the issues of the realized project and discusses its specific characteristics, such as advantages and disadvantages in comparison to the conventional analogue cockpit and the possibility of adaptation for the plane. Findings New avionics, ground and in-flight tests were carried out. The data were collected, which, together with an ergonomics assessment done by the pilot and the observer, confirmed the previously established technical and operational objectives. Practical implications Most airplanes, when being modernized, encounter minor or major problems. A new approach to upgrading the avionics, involving the exchange of a piston engine with a turbine engine, which is supported by 3D software, has allowed a significant reduction of working time and costs. Originality/value The achieved results allow specifying a plan of changes, necessary to adapt the aircraft to a new avionic system. However, an important value is to show a new development direction of the turbine engine implementation in general aviation aircrafts.

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Thistle, Harold W., Lucas Amos-Binks, Jane A. S. Bonds, et al. "Evaluation of Automated, In-Cockpit Swath Displacement." Transactions of the ASABE 63, no. 1 (2020): 177–88. http://dx.doi.org/10.13031/trans.13551.

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HighlightsAutomated swath displacement works well in high drift conditions.System relevance and performance are limited in low drift conditions.Testing against pilot skill without an automated system is necessary.ABSTRACT. A set of spray trials was designed to evaluate the onboard swath displacement feature that is offered as part of some avionic systems and used to aid in targeting aerial spray applications. The trials were flown in Miramichi, New Brunswick, Canada, and were intended to provide basic information on the capabilities of these systems. A total of 32 trials were run, of which 24 provided coverage data that could be used in this evaluation. Two aircraft types were tested, each with distinct avionics systems and automated swath displacement capabilities. Each aircraft was flown with two application setups, resulting in four application scenarios. The systems were generally able to allow the pilot to apply the spray with a swath peak within 5 m of the target line on average, even in high wind conditions. Other relationships that were anticipated in the data, such as a direct correlation between offset distance and targeting accuracy, were not observed. The systems do not appear to add much capability in low drift conditions when not much displacement is expected. It is recognized that a control data set is necessary to evaluate the extent to which the systems improve targeting accuracy. Keywords: Aerial management system, Aerial pesticide application, Drift offset, Precision application, Real-time modeling, Spray deposition, Spray drift, Swath displacement.

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Kononchuk, Rodion, Joshua Feinberg, Joseph Knee, and Tsampikos Kottos. "Enhanced avionic sensing based on Wigner’s cusp anomalies." Science Advances 7, no. 23 (2021): eabg8118. http://dx.doi.org/10.1126/sciadv.abg8118.

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Typical sensors detect small perturbations by measuring their effects on a physical observable, using a linear response principle (LRP). It turns out that once LRP is abandoned, new opportunities emerge. A prominent example is resonant systems operating near Nth-order exceptional point degeneracies (EPDs) where a small perturbation ε ≪ 1 activates an inherent sublinear response ∼εN≫ε in resonant splitting. Here, we propose an alternative sublinear optomechanical sensing scheme that is rooted in Wigner’s cusp anomalies (WCAs), first discussed in the framework of nuclear reactions: a frequency-dependent square-root singularity of the differential scattering cross section around the energy threshold of a newly opened channel, which we use to amplify small perturbations. WCA hypersensitivity can be applied in a variety of sensing applications, besides optomechanical accelerometry discussed in this paper. Our WCA platforms are compact, do not require a judicious arrangement of active elements (unlike EPD platforms), and, if chosen, can be cavity free.

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Martelli, Samuele, Luca Mazzei, Carlo Canali, et al. "Deep Endoscope: Intelligent Duct Inspection for the Avionic Industry." IEEE Transactions on Industrial Informatics 14, no. 4 (2018): 1701–11. http://dx.doi.org/10.1109/tii.2018.2807797.

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Sener, Eralp, and Gurhan Ertasgin. "Design of a Half-Bridge Current-Source Inverter Topology for Avionic Systems." Aerospace 9, no. 7 (2022): 354. http://dx.doi.org/10.3390/aerospace9070354.

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This paper analyses a new half-bridge current–source inverter for avionic systems. In the circuit, two 28 V batteries are used as inputs. These voltage sources are connected to inductors which create a constant current source. Then only two high-frequency switches are used to waveshape the positive and negative half-cycles. The SCR-based half-bridge allows positive and negative current flow properly. The inverter output uses a CL filter to remove PWM components and to obtain 400 Hz sinewave output. Simulation and HIL experiment results are provided with feedback control to prove the concept of the proposed topology. The study shows that the new current–source topology provides promising results while complying with aviation standards.

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32

Rufino, José. "Towards integration of adaptability and non-intrusive runtime verification in avionic systems." ACM SIGBED Review 13, no. 1 (2016): 60–65. http://dx.doi.org/10.1145/2907972.2907981.

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Youn, Won Keun, Seung Bum Hong, Kyung Ryoon Oh, and Oh Sung Ahn. "Software certification of safety-critical avionic systems: DO-178C and its impacts." IEEE Aerospace and Electronic Systems Magazine 30, no. 4 (2015): 4–13. http://dx.doi.org/10.1109/maes.2014.140109.

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Probst, D. K., L. G. Perrymore, B. C. Johnson, R. J. Blackwell, J. A. Priest, and C. L. Balestra. "Demonstration of an integrated, active 4*4 photonic crossbar (for avionic systems)." IEEE Photonics Technology Letters 4, no. 10 (1992): 1139–41. http://dx.doi.org/10.1109/68.163758.

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Grigg, Alan, and Neil C. Audsley. "Towards a scheduling and timing analysis solution for integrated modular avionic systems." Aircraft Engineering and Aerospace Technology 70, no. 4 (1998): 271–80. http://dx.doi.org/10.1108/00022669810225304.

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Grigg, Alan, and Neil C. Audsley. "Towards a scheduling and timing analysis solution for integrated modular avionic systems." Microprocessors and Microsystems 22, no. 8 (1999): 423–31. http://dx.doi.org/10.1016/s0141-9331(98)00101-x.

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Youn, Wonkeun, and Baeck-jun Yi. "Software and hardware certification of safety-critical avionic systems: A comparison study." Computer Standards & Interfaces 36, no. 6 (2014): 889–98. http://dx.doi.org/10.1016/j.csi.2014.02.005.

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Johnson, David M. "A review of fault management techniques used in safety-critical avionic systems." Progress in Aerospace Sciences 32, no. 5 (1996): 415–31. http://dx.doi.org/10.1016/0376-0421(96)82785-0.

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39

Fakih, Maher, Kim Grüttner, Sören Schreiner, et al. "Experimental Evaluation of SAFEPOWER Architecture for Safe and Power-Efficient Mixed-Criticality Systems." Journal of Low Power Electronics and Applications 9, no. 1 (2019): 12. http://dx.doi.org/10.3390/jlpea9010012.

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With the ever-increasing industrial demand for bigger, faster and more efficient systems, a growing number of cores is integrated on a single chip. Additionally, their performance is further maximized by simultaneously executing as many processes as possible. Even in safety-critical domains like railway and avionics, multicore processors are introduced, but under strict certification regulations. As the number of cores is continuously expanding, the importance of cost-effectiveness grows. One way to increase the cost-efficiency of such a System on Chip (SoC) is to enhance the way the SoC handles its power consumption. By increasing the power efficiency, the reliability of the SoC is raised because the lifetime of the battery lengthens. Secondly, by having less energy consumed, the emitted heat is reduced in the SoC, which translates into fewer cooling devices. Though energy efficiency has been thoroughly researched, there is no application of those power-saving methods in safety-critical domains yet. The EU project SAFEPOWER (Safe and secure mixed-criticality systems with low power requirements) targets this research gap and aims to introduce certifiable methods to improve the power efficiency of mixed-criticality systems. This article provides an overview of the SAFEPOWER reference architecture for low-power mixed-criticality systems, which is the most important outcome of the project. Furthermore, the application of this reference architecture in novel railway interlocking and flight controller avionic systems was demonstrated, showing the capability to achieve power savings up to 37%, while still guaranteeing time-triggered task execution and time-triggered NoC-based communication.

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Krebs, Thomas. "Considerations for Sintering in High Temperature Electronics." Additional Conferences (Device Packaging, HiTEC, HiTEN, and CICMT) 2019, HiTen (2019): 000071–73. http://dx.doi.org/10.4071/2380-4491.2019.hiten.000071.

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Abstract High temperature electronics are used in a wide range of applications especially in extreme environments. There is a clear trend in aircrafts to have electrical controls mounted closer to the engine [1]. In cars more and more mechanical and hydraulic systems are replaced by electromechanical or mechatronic systems [2]. They are getting closer to high temperature environments like the engine or brakes. To its nature, avionic and automotive applications require predictable, highly reliable systems. Because elevated temperatures will increase the speed of material aging, the combination of high operation temperatures and high reliability is quite challenging. This applies in particular to interconnect materials such as solders or bonding wires.

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Singh, Anurag, Sandip Vijay, and Rudra Narayan Baral. "Performance analysis of high gain beamforming conformal array for avionic applications." International Journal of Systems, Control and Communications 9, no. 3 (2018): 266. http://dx.doi.org/10.1504/ijscc.2018.093408.

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Ouhammou, Yassine, Anh Toan Bui Long, Emmanuel Grolleau, et al. "A model-based process for the modelling and the analysis of avionic architectures." International Journal of Intelligent Information and Database Systems 10, no. 1/2 (2017): 117. http://dx.doi.org/10.1504/ijiids.2017.086200.

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SUHIR, E. "STRUCTURAL DYNAMICS OF ELECTRONIC SYSTEMS." Modern Physics Letters B 27, no. 07 (2013): 1330004. http://dx.doi.org/10.1142/s0217984913300044.

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The published work on analytical ("mathematical") and computer-aided, primarily finite-element-analysis (FEA) based, predictive modeling of the dynamic response of electronic systems to shocks and vibrations is reviewed. While understanding the physics of and the ability to predict the response of an electronic structure to dynamic loading has been always of significant importance in military, avionic, aeronautic, automotive and maritime electronics, during the last decade this problem has become especially important also in commercial, and, particularly, in portable electronics in connection with accelerated testing of various surface mount technology (SMT) systems on the board level. The emphasis of the review is on the nonlinear shock-excited vibrations of flexible printed circuit boards (PCBs) experiencing shock loading applied to their support contours during drop tests. At the end of the review we provide, as a suitable and useful illustration, the exact solution to a highly nonlinear problem of the dynamic response of a "flexible-and-heavy" PCB to an impact load applied to its support contour during drop testing.

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Kennedy, Damian, and Sergey Nesterov. "3.2.1 Issues with Third Party Maintenance of Software Intensive Legacy Systems: A Case Study - Avionic Mission Systems." INCOSE International Symposium 18, no. 1 (2008): 341–56. http://dx.doi.org/10.1002/j.2334-5837.2008.tb00810.x.

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Terescenko, Jevgenijs, Vladimir Shestakov, and Andris Vaivads. "Analysis of Failure States of Functional Systems of Aircraft Such as Boeing 737 in the Airline." Transactions on Aerospace Research 2023, no. 4 (2023): 71–78. http://dx.doi.org/10.2478/tar-2023-0024.

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Abstract The article presents the results of analysis of failures of the main functional systems units of aircraft Boeing 737 during the last 10 years of its operation in the national airline of Latvia ‘Air Baltic Corporation’. Total flight time was T∑ = 322,529 h and 184,538 cycles [1]. These data were obtained from daily reports of defects and unplanned consumption of spare parts for these systems. Failures of instrumental equipment of avionic systems were investigated in detail. Based on calculations of their failure probability and component replacement frequency, a comprehensive system including measures and their technical and instrumental support has been developed to improve maintenance productivity. Such a system requires relatively inexpensive components, is simple and can be used in the operation of this type of aircraft.

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Pendem, Rajyalaxmi. "Fly by Wire Advancements in Aviation over Conventional Flight Control Systems." International Journal for Research in Applied Science and Engineering Technology 11, no. 6 (2023): 1771–75. http://dx.doi.org/10.22214/ijraset.2023.52971.

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Abstract: This report shows the advancement of flight control systems, from the old human controlled mechanical systems to the modern fly by wire systems in use today. It also compares the two systems, and investigates the reasons behind the change. This change is a significant and an extraordinary representation of the advancements made in the avionic industry and of the development of aeronautical technologies. The fly-by wire system represents a large fast forwarding in the industry, from complex mechanically controlled systems, to large hydraulically controlled systems, to computer assisted fly by wire system. The use of fly-by wire systems has significantly reduce the weight of the flight control systems, while increasing the scope to add multiple redundancy flight control systems, which can increase the safety in case of failures in a particular system. Further development in fly-by wire systems comes in the form of advancing from analog to digital computing systems

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Mousavi, Seyyed Hassan, and Ammar B. Kouki. "Highly Compact VHF/UHF Dual-Band/Dual-Function LTCC Circuits: Application to Avionic Systems." IEEE Transactions on Components, Packaging and Manufacturing Technology 6, no. 1 (2016): 12–22. http://dx.doi.org/10.1109/tcpmt.2015.2505320.

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Alexander, Amy L., Lawrence J. Prinzel, Christopher D. Wickens, Lynda J. Kramer, Jarvis J. Arthur, and Randall E. Bailey. "Evaluating the Effects of Dimensionality in Advanced Avionic Display Concepts for Synthetic Vision Systems." International Journal of Aviation Psychology 19, no. 2 (2009): 105–30. http://dx.doi.org/10.1080/10508410902766192.

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Mudawar, Issam, Peter E. Jimenez, and Robert E. Morgan. "Immersion-Cooled Standard Electronic Clamshell Module: A Building Block for Future High-Flux Avionic Systems." Journal of Electronic Packaging 116, no. 2 (1994): 116–25. http://dx.doi.org/10.1115/1.2905499.

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An 820-Watt clamshell module was fabricated and tested in order to assess the feasibility of cooling future high heat flux avionic hardware via subcooled phase change. One half of the module was constructed from aluminum 7075-T6 and populated with 16 heat sources simulating microelectronic chips. The other half was substituted with a transparent plastic cover to facilitate optical access to the boiling taking place in the module cavity. A dielectric coolant, Fluorinert FC-72, was supplied to, and rejected from the module via sleeveless quick connection couplers. Tests were performed with an inlet coolant pressure of 1.52 bar (22 psia) and inlet temperatures ranging from 27 to 47°C. These tests yielded power dissipation exceeding 410 W per half module for coolant flow rates and pressure drops as small as 0.023 kg/s (0.221 gpm) and 0.149 bar (2.16 psia), respectively, and the device and rib guide temperatures were maintained below 80 and 60°C, respectively. The pressure drop remained constant with increasing module power proving, as was confirmed visually, it is possible to condensate all the vapor within the module cavity, allowing only liquid to exit the module. Thus, coolant conditioning external to the module can be greatly simplified by employing a simple single-phase liquid flow loop.

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Baron, Claude, and Vincent Louis. "Framework and tooling proposals for Agile certification of safety-critical embedded software in avionic systems." Computers in Industry 148 (June 2023): 103887. http://dx.doi.org/10.1016/j.compind.2023.103887.

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