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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

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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 man

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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 mode

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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 softwa

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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

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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

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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 av

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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

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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 imp

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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 e

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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-sensiti

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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

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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 modul

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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 platfo

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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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24

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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25

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

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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

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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-d

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30

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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31

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

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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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33

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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34

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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35

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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36

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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37

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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38

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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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 handl

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40

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

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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

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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 in

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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 assiste

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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 in

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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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