Articoli di riviste: "Avionics"

1

Sun, Yi Gang, e Li Sun. "The Design of Avionics System Interfaces Emulation and Verification Platform Based on QAR Data". Applied Mechanics and Materials 668-669 (ottobre 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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Sahputra, Afandi, Abdul Rasyid e 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. 1 (30 maggio 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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Nadesakumar, A., R. M. Crowder e 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. 4 (dicembre 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 e Kun Qiu. "Modeling and Simulation of FC-AE-ASM Network". Advanced Materials Research 748 (agosto 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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Wang, Ying, Jian Yong Wang e Lei Wang. "A Transformation-Based Integrated Modular Avionics Software Model Construction Approach". Applied Mechanics and Materials 668-669 (ottobre 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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Zhang, Jian Dong, En Long Cao, Yong Wu e Guo Qing Shi. "Designing and Realizing of Universal Test and Analysis System of Avionics Data Bus". Applied Mechanics and Materials 284-287 (gennaio 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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Jiang, Na, Chunpeng Zhang, Yang Cao e Rixin Zhan. "Application of prognostic and health management in avionics system". Highlights in Science, Engineering and Technology 7 (3 agosto 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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Zieja, Mariusz, Andrzej Szelmanowski, Andrzej Pazur e Grzegorz Kowalczyk. "Computer Life-Cycle Management System for Avionics Software as a Tool for Supporting the Sustainable Development of Air Transport". Sustainability 13, n. 3 (2 febbraio 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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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. 30 (22 dicembre 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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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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11

Ford, Terry. "Helicopter Avionics". Aircraft Engineering and Aerospace Technology 59, n. 4 (aprile 1987): 2–5. http://dx.doi.org/10.1108/eb036422.

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Ford, Terry. "Integrated Avionics". Aircraft Engineering and Aerospace Technology 66, n. 2 (febbraio 1994): 2–4. http://dx.doi.org/10.1108/eb037474.

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13

Jameson, Editor Angela. "Avionics displays". Displays 11, n. 2 (aprile 1990): 111. http://dx.doi.org/10.1016/0141-9382(90)90114-9.

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AEG (UK) Ltd. "Avionics CRT". Displays 8, n. 1 (gennaio 1987): 46. http://dx.doi.org/10.1016/0141-9382(87)90018-7.

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Ge, Xing Guo, Zhong Xiang Tao e Chun Yan Tian. "Analysis of the Development Trend of Avionics System". Advanced Materials Research 850-851 (dicembre 2013): 1102–5. http://dx.doi.org/10.4028/www.scientific.net/amr.850-851.1102.

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Avionics system has been existed for over 80 years and plays more and more important roles in the war today. The process of development of the avionics system in general and its modification are described. The technique performance and properties of several avionics system seekers are analyzed, and development trend of avionics system are discussed.

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16

Zhou, Qiang, Yongan Wei e Longjiang Zhu. "Research on reliability modeling of unmanned aircraft system avionics systems based on 5G". International Journal of Distributed Sensor Networks 15, n. 7 (luglio 2019): 155014771986038. http://dx.doi.org/10.1177/1550147719860381.

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With the development of technology, an unmanned aircraft system will play a significant role in Internet of things based on 5G. Avionics system is an important part of the unmanned aircraft system, and the reliability of the avionics system directly determines the ability to perform missions. This article deals with the problem of reliability modeling with unmanned aircraft system avionics systems built on Internet of things in the 5G scenario. First, based on the composition of the avionics system, the network structure of the unmanned aircraft system avionics system is presented. Then, to evaluate the reliability, a task model of the unmanned aircraft system avionics system is proposed. Finally, an illustration of unmanned aircraft system reliability performing reconnaissance is also presented. By analyzing the task performance, it is shown that redundancy design of the units can improve the reliability of the unmanned aircraft system avionics system.

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Li, Dan, Jian Dong Zhang, Yong Wu e Gou Qing Shi. "Integrated Avionics Network Dynamics Analysis". Applied Mechanics and Materials 721 (dicembre 2014): 689–92. http://dx.doi.org/10.4028/www.scientific.net/amm.721.689.

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To evaluate the message transmission mechanism of avionics network, we propose the method for studying important performance parameters of integrated avionics system by using complex network knowledge. Consider the topological characteristics of the network and analyze the degree, degree distribution, average path length, clustering coefficients and other important performance parameters. Finally, analyze the calculation approach of robustness through the maximal connected sub-graph. We also analyze the priority and message processing capabilities of avionics subsystem, establish a random failure model of integrated avionics system network, and simulate the robustness of integrated avionics network when random failure occurs with several nodes.

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Dudziak, Jacek, e Paweł Guła. "Design practice in the translation traditional and glass cockpit based on General Aviation I-31T aircraft". Aircraft Engineering and Aerospace Technology 89, n. 6 (2 ottobre 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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Du, Xiaoyan, Chenglie Du, Jinchao Chen, Mei Yang e Wenquan Yu. "A Simulation and Verification Platform for Avionics Systems Based on Future Airborne Capability Environment Architecture". Applied Sciences 12, n. 22 (13 novembre 2022): 11533. http://dx.doi.org/10.3390/app122211533.

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Avionics systems, which determine the performance, stability, and safety of aircraft, are a crucial part of aircraft. With the rapid development of the aviation industry, there are many serious problems in the process of the traditional simulation and verification of avionics systems, especially in the aspects of poor reusability of the hardware and software, poor real-time data interaction, and the high cost of development. In order to solve these problems, a simulation and verification platform for avionics systems based on the Future Airborne Capability Environment (FACE) architecture has been designed by using component and memory database technology. First, a general architecture is designed by referencing the FACE architecture, which allows flexible access to software and hardware resources of avionics systems. Second, the key technologies involved in the platform are described in detail, including scheduling management, communication management, and configuration management, which provide technical support for the simulation and verification of avionics systems. Finally, the simulation and verification environment of avionics systems is established, which realizes data interaction and management of various models, and improves the efficiency of the development and implementation of avionics systems.

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FitzPatrick, R. "Avionics extrapolations(A foray into the future of avionics)". Aeronautical Journal 105, n. 1047 (maggio 2001): 241–54. http://dx.doi.org/10.1017/s0001924000012057.

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The past has been interesting, but what of the future? As Fig. 1 shows, extrapolation is an attractive tool, with pitfalls for the incautious - most often exemplified in aerospace by the prediction that by 2015 the entire US defence budget would fund one aeroplane, or more recently by the belief that avionics will expand into infallibility and reduce costs to invisibility. The first extrapolation is premature, and the latter two as near as makes no difference wrong. In the case of the single affordable US defence aircraft the extrapolation probably correctly estimated the 2015 US defence budget, but erred in expressing the US Department of Defence requirement in terms of aircraft rather than damage-effects on target. The subsequent step change in avionics miniaturisation undermined the extrapolation and now looks likely to enable the DoD’s damage-effect requirements to be attained using products that lie on a different cost-effectiveness trend line.

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Wang, Ying, e Lei Wang. "Automatic C Code Generation for Avionics Software Based on VxWorks653 Platform". Applied Mechanics and Materials 687-691 (novembre 2014): 3124–27. http://dx.doi.org/10.4028/www.scientific.net/amm.687-691.3124.

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At present, model-driven development method has been gradually applied in safety-critical avionics software to improve reliability and productivity. Existing ARINC653 annex of the Architecture Analysis & Design Language (AADL) is used to model avionic software based on ARINC653-compatible OS, such as VxWorks653 commercial platform. In this paper, a refined C code generation algorithm is proposed to enable automatically generate VxWorks653-runnable code from the AADL ARINC653 models. Finally, a simplified autopilot system example is as a case study to show the validity of our approch.

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Antсev, I. G., G. G. Bundin, V. I. Ischuk e S. A. Mochalov. "NAVAL AVIATION ON-BOARD AVIONICS COMPLEX: FROM FIFTH TO SIXTH GENERATION". Issues of radio electronics, n. 1 (20 gennaio 2019): 6–12. http://dx.doi.org/10.21778/2218-5453-2019-1-6-12.

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It is proposed the appearance and the main architectural concepts of distributed hardware and information‑calculating medium construction for sixth generation aviation complexes. An essence of characteristics and principles of sixth generation on‑board avionics complexes construction is revealed. There are shown the main principles of sixth generation on‑board avionics complexes, such as: centralized architecture of integrated information and control medium; high‑intelligence cockpit designed based of interactive technique and expert systems; unified core part of on‑board avionics complexes’ units; jam‑resistant communication system with use of Internet technologies. There are defined the main principles of sixth generation on‑board avionics complexes designing: integration of on‑board avionics complexes’ elements and flight vehicles, centralized architecture of information‑and‑control computing system, wide use of self-earning expert systems, communication system with use of Internet technologies, decision‑making self-earning expert systems, construction of high‑intelligence cockpit on the basis of interactive technique, maximal unification of on‑board avionics complexes’ elements.

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Ma, Teng Da, e De Xin Zhou. "Design of Civil Aircraft Avionics System Bus Excitation System". Advanced Materials Research 1037 (ottobre 2014): 193–96. http://dx.doi.org/10.4028/www.scientific.net/amr.1037.193.

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The avionics system is a core component of the civil aircraft. To reduce the risk and cost of developing avionics system, shorten the development cycle, through the development process of avionics systems, variety of simulation and verification must be done. The bus excitation signals need to be provided for each avionics unit and the signals from each avionics unit need to be received and processed. The multilayer abstract model and organizational structure model of the bus excitation system was established. And a complete bus excitation system was designed. In this system, the ARINC429 bus signals and discrete signals for communication and navigation equipments were provided, and the signals from the equipments were received and processed. This system has been tested, and one practical application example of the system was given.

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Xu, Jiuping, e Lei Xu. "Integrated system health management-based condition assessment for manned spacecraft avionics". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 227, n. 1 (9 gennaio 2012): 19–32. http://dx.doi.org/10.1177/0954410011431395.

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This article presents a condition assessment model to evaluate the health condition of manned spacecraft avionics that enables the essential capabilities of a manned spacecraft and guarantees the mission success of space flight. Condition assessment based on the integrated system health management is introduced into manned spacecraft avionics to cope with the safety and maintenance necessity. Due to the complexity and the uncertainty of the system, it is a tough task before modular avionics emerged, and there is a rare research-concerning condition assessment for manned spacecraft avionics with fuzziness and simultaneous consideration in system level. A numerical example illustrates the proposed fuzzy evaluation model which takes all criteria into account from a holistic perspective, combines objective tests with subjective judgments and incorporates fuzziness and uncertainty into ranking the manned spacecraft avionics health level using fuzzy analytic hierarchy process with quantitative reliability analytical approaches. The proposed model is demonstrated to solve the condition assessment problem and the impact condition factors for the manned spacecraft avionics health management are revealed.

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Chernogor, L. F. "FUNCTIONAL DAMAGE OF RADIO ELECTRONIC SYSTEMS". Radio physics and radio astronomy 26, n. 4 (24 novembre 2021): 358–69. http://dx.doi.org/10.15407/rpra26.04.358.

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Purpose: The most important problem of any state is protection of the control and management systems used for the country, national armed forces, high-risk facilities (nuclear power plants, large chemical plants, airports, etc.). Here, the fact that the means of attack can be deployed on ballistic and cruise missiles, aircraft, and drones should be accounted for. The flight altitude of these vehicles varies from ≈300 km to ≈ 10 m. Any attack vehicle is equipped with complex avionics consisting of circuit elements sensitive to electromagnetic fields. Since the 1980s, a new scientific and engineering direction has been developing, being termed as a “functional damage to avionics”. It is based on the creation of powerful means of electromagnetic radiation possessing the energetic capabilities of incapacitating avionics at significant distances (from ~ 100 m to ~ 1000 km). The purpose of this work is to analyze the possible functional damage to avionics with account for the tendencies in avionics technologies. Design/methodology/approach: The analysis is made on the capability of inflicting functional damage to avionics accounting for the modern trends in developing the powerful means of electromagnetic energy generation in the microwave and shorter wavelength ranges, miniaturization and integration of avionics circuit elements. The regression is constructed for the critical energy time dependence. It has been determined that for decades the critical energy required to damage the circuit elements shows a tendency to decrease. This is due to the further miniaturization and integration of microcircuits according to the Moore’s law, which is still valid for now. For a number of circuit elements, the critical energy is found to be in the range of 10-11–10-10 J. At the same time, a reverse tendency arises to protect avionics from being functionally damaged. In this case, the critical energy makes 10-7–10-6 J and greater. From the derived version of the basic equation of functional damage to avionics, the maximum distance at which the damage is possible with the energetics of the existing radio systems is estimated. For the ground-based facilities, this distance can attain hundreds of kilometers. For mobile vehicles, it can reach 10–100 km. Combining target detection, identification and avionics damage capabilities in one radio system has been validated and advised. The transition from the first mode of operation to the second one occurs at shorter distances with an increase of 2–3 orders of magnitude in the pulse energy. Findings: The regression equation has been obtained for the time dependence of the critical energy required for inflicting functional damage to avionics. Its constant decrease has been confirmed. Such a behavior is closely related to the Moore’s law, which characterizes the degree of miniaturization and integration of avionics circuit elements. It has been predicted that for a number of instruments the critical energy can be smaller than 10-11–10-10 J. A version of the basic equation of functional damage to avionics has been obtained. The maximum distance for a modern radio system to damage the avionics has been shown to attain many hundreds of kilometers. For the radio systems installed on mobile vehicles, this distance makes 10–100 km. Target detection, tracking and identification, as well as avionics damage capabilities, have been proved to be rationally combined in one radio system. To cause damage at a corresponding range, the pulse energy needs to be increased by a factor of 102–103. Conclusions: There are all science and technology prerequisites for developing effective radio systems inflicting functional damage to avionics and for the state defense and protection, armed forces, and high-risk facility controlling systems. Key words: functional damage; avionics; critical energy; Moore’s law; functional damage equation; radiolocation equation; detection and destruction range

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Gao, Chi, Bin Li e Zhen Dai. "Medium and Long-Term Fault Prediction of Avionics Based on Echo State Network". Mobile Information Systems 2022 (16 settembre 2022): 1–9. http://dx.doi.org/10.1155/2022/5343909.

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As one of the core equipment of aircraft, avionics provide a power source for flight. Avionics are complex and highly susceptible to environmental factors. Failure in the long flight process is also relatively large, affecting the stability and safety of aircraft operation. Therefore, it is of great significance to predict the typical faults of avionics. At present, a lot of research achievements have been made on the fault diagnosis of avionics, but the failure prediction of avionics is rarely involved, especially the middle and long-term fault prediction. Hence, this paper proposes a fault prediction method for avionics based on an echo state network. In particular, one-dimensional wavelet denoising filtering and z-score standardized preprocessing are carried out to obtain pure useable data first. Then, the set training data are input into the ESN model. When the model is well trained, the test data can be used to test the model. Finally, the experimental results demonstrate that the proposed ESN model can effectively improve the medium and long-term prediction accuracies of the faults in avionics equipment. Besides, the proposed model can not only identify the types of faults but also predict the specific time when the faults occur. It guarantees the safe and stable operation of the equipment and supports the stable development of the air transport industry, which has great theoretical and practical application value.

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Jiang, Lian Xiang, Ming Rui Xin e Zhan Guo Cui. "A Fault Detection Method Based on BIT for Satellite Avionics". Applied Mechanics and Materials 182-183 (giugno 2012): 431–35. http://dx.doi.org/10.4028/www.scientific.net/amm.182-183.431.

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Satellite avionics was introduced to gain mass reduction, lower cost, modular and standard equipment. Fault detection, isolation and recovery is one of the main way to upgrade the autonomy of satellites. Built-in-test is one of the most prevalent and effective fault detection method, according to the structure and characteristics of satellite avionics, the BIT of satellite avionics was designed and introduced.

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28

Wang, Hong Chun, e Wen Sheng Niu. "Design and Analysis of AFDX Network Based High-Speed Avionics System of Civil Aircraft". Advanced Materials Research 462 (febbraio 2012): 445–51. http://dx.doi.org/10.4028/www.scientific.net/amr.462.445.

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Avionics Full Duplex Switched Ethernet (AFDX) standardized as ARINC 664 is a major upgrade for integrated avionics systems of civil aircraft. It becomes the current communication technology in the context of avionics and provides a backbone network for the civil avionics system. This paper focuses on features of AFDX network protocol. Architecture of AFDX switch based on shared memory is proposed to meet the requirements of avionics real-time system. In addition, frame filtering, traffic policing and frame schedule function are used to eliminate uncertainties in huge traffic flows. End System (ES) host-target architecture is also researched in this paper. Virtual link scheduler, redundancy management, and protocol stack in ES are designed to ensure determinism and reliability of data communication. AFDX switch and ES have been successfully developed, and configuration tool, ARINC 615A loader and simulation tool related to AFDX network are also provided as package solution to support avionics system construction. Finally, AFDX switch and ESes have passed ARINC 664 protocol conformance test and certification, the test results show that our AFDX products meet the requirements of real-time communication, determinism and reliability defined in ARINC 664

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29

ZHANG, Shuang, Deqi KONG, Yuanxun WANG, Xinyu WAN, Hongjing YAO e Yangming GUO. "Secure communication technology between network domains based on virtualization avionics platform". Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 40, n. 3 (giugno 2022): 530–37. http://dx.doi.org/10.1051/jnwpu/20224030530.

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In the information interconnection scenario of the new generation wide-body aircraft, there is a large amount of real-time bi-directional data exchange between aircraft control domain and airline information services domain in civil aircraft avionics system, and its security isolation and information flow protection are facing increasingly serious information security threats. Therefore, a bi-directional secure communication architecture based on virtualization avionics platform is proposed in this study. The attribute-based access control for multiple avionics domain is modeling and the designs of protection for contract security critical data and real-time monitoring for security critical component effectiveness are given. Physical implementation and verification results based on the domestic ACoreOS operating system and avionics hardware platform show that the bi-directional secure communication method based on virtualization avionics platform achieves the spatial isolation of security critical components, the data transmit and receive time of ACD network is less than 50 ms, and the message transmit and receive rate of ACD network is greater than 70 Mb/s. These results can meet the performance requirements of secure communication between avionics network domains of wide-body aircraft, which have high practical value.

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30

Fielding, J. P., e M. A. F. Vaziry-Z. "Avionics cooling-rate trade-off modelling for ultra-high capacity aircraft". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 211, n. 6 (1 giugno 1997): 403–12. http://dx.doi.org/10.1243/0954410971532767.

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A computer aided conceptual aircraft design methodology (CACAD) has been developed to size ultra-high capacity jet transport aircraft. Modules were also developed for predicting maintenance costs of each airframe and avionics system and these were incorporated into CACAD. A methodology was developed to enhance the reliability of avionics systems, based on experimentally-proven engineering design solutions. A number of avionics cooling techniques were investigated, and reliability and maintainability models of thermal management were developed and linked to an avionics maintenance cost module. Further models were produced to investigate the impact of proposed changes on the environmental control systems, engine-provided bleeds and power off-takes. It was found that increased flowrates above the normally recommended values for the avionics bay, and to the flight deck instruments, may increase the reliability of the avionics systems, and also increase aircraft dispatch reliability. They may not, however, greatly improve direct operating costs (DOC), due to significant fuel penalties. A separate refrigeration unit was investigated and found to be a feasible cost-effective measure, even allowing for increased engine fuel consumption caused by the effect of the engine power off-take required to drive the refrigeration unit.

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31

Collins, P. H., e B. L. Perry. "Systems and avionics". Aeronautical Journal 107, n. 1072 (giugno 2003): 359–67. http://dx.doi.org/10.1017/s0001924000013695.

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This paper looks to future developments and concepts in Systems and Avionics. One hundred years ago neither ‘avionics’ nor even ‘systems’ would have been recognised as having a place in aeronautics. The concept of aircraft systems developed, as the complexity of each element of the aircraft grew, requiring specialism in the design, operation and maintenance of those elements. Early examples would have been the propulsion and flying controls systems. By the 1930s passenger aircraft might have carried, in addition to the pilots, a navigator, flight engineer and radio operator, each responsible for his own collection of systems, with the aircraft itself probably having an embryonic electrical system.

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32

Shaw, Brian M. "Introduction to Avionics". International Journal of Electrical Engineering & Education 35, n. 4 (ottobre 1998): 381–83. http://dx.doi.org/10.1177/002072099803500415.

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33

Dowling, D., e T. Rupinski. "Avionics Maintenance 2010". IEEE Journal on Selected Areas in Communications 4, n. 7 (ottobre 1986): 1090–96. http://dx.doi.org/10.1109/jsac.1986.1146422.

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34

Coombs, Les. "Flight deck avionics". Aircraft Engineering and Aerospace Technology 67, n. 4 (aprile 1995): 2–3. http://dx.doi.org/10.1108/eb037578.

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35

Ford, Terry. "Developments in avionics". Aircraft Engineering and Aerospace Technology 70, n. 2 (aprile 1998): 120–23. http://dx.doi.org/10.1108/00022669810202426.

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36

Parr, Gordon R., e R. Edwards. "Integrated modular avionics". Air & Space Europe 1, n. 2 (marzo 1999): 72–75. http://dx.doi.org/10.1016/s1290-0958(99)80018-5.

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37

Foley, R. D., e S. Suresh. "Avionics reliability analysis". Annals of Operations Research 9, n. 1 (dicembre 1987): 589–611. http://dx.doi.org/10.1007/bf02054757.

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38

Hoyme, K., e K. Driscoll. "SAFEbus (for avionics)". IEEE Aerospace and Electronic Systems Magazine 8, n. 3 (marzo 1993): 34–39. http://dx.doi.org/10.1109/62.199819.

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39

Калашник, Г. А., e М. А. Калашник-Рибалко. "Methodology for ensuring the functional stability of aircraft integrated modular avionics complex". Наука і техніка Повітряних Сил Збройних Сил України, n. 4 (53) (28 febbraio 2024): 30–40. http://dx.doi.org/10.30748/nitps.2023.53.04.

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The article presents the methodology of ensuring the functional stability of aircraft avionics complexes under the influence of failure and destabilizing factors. It is based on the procedure of maintaining valid knowledge bases of individual modules of the avionics complex through the organization of dynamic verification of such knowledge bases during their application on the principle of the probabilistic diagnostic core with system recovery without significant restructuring of verification means. The results of calculations of indicators of functional stability of the integrated avionics complex of the D-42 aircraft are presented in the article. To increase the efficiency of the integrated avionics complex under conditions of destabilizing influences, the optimal structure of the avionics complex of the D-42 aircraft was synthesized according to the criterion of the maximum indicator of functional stability with the limitation of the cost of construction the system. In the calculations, an increase in the generalized indicator of functional stability was achieved in comparison with the original structure by 30.8 % (from 294.2 to 384.9) for the given conditional cost 20,000 с.u. It is the most acceptable according to the generalized indicator of functional stability, as a criterion of preference under the specified cost limitations and taking into account the limitations of other parameters of the effective operation of the complex. Increasing the functional stability of the avionics complex according to the presented methodology will allow timely detection of implicit failures and parry their consequences. Based on the results of these studies there is a possibility: substantiation of requirements for the structures of avionics complexes to be designed, solving the problem of synthesis of optimal structure on the criterion of maximum functional stability with limited construction costs, as well as a reasonable increase in the structure of the distributed system of the aircraft avionics complex.

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40

Amari, Ahmed, e Ahlem Mifdaoui. "Specification and Performance Indicators of AeroRing—A Multiple-Ring Ethernet Network for Avionics Embedded Systems". Sensors 18, n. 11 (10 novembre 2018): 3871. http://dx.doi.org/10.3390/s18113871.

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The complexity and costs of the avionics communication architecture are increasing exponentially with the increasing number of embedded computers over the last few decades. To limit the cabling complexity and the deployment costs of such a communication architecture, we specify a new Gigabit multiple-ring Ethernet network, called AeroRing, while meeting the avionics requirements. First, we describe the current Aircraft Data Communication Network (ADCN) to highlight the main characteristics and requirements that have to be fulfilled by our solution. Then, we give an overview of the most relevant solutions to improve ADCN performance and relate them to AeroRing. Afterwards, we detail the specifications and the main Performance Indicators (PIs) of AeroRing. Finally, sensitivity and validation analyses of AeroRing are conducted through a realistic avionics application, regarding the various PIs, in comparison to the backbone network of the ADCN, the Avionics Full DupleX Switched Ethernet (AFDX). The computed AeroRing performance metrics show its ability to guarantee the avionics requirements.

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41

Wu, Jian Jun, Da Hai Zhao e Wei Wan. "Digital Research of Unmanned Aerial Vehicle Avionics System Based on CAN Bus". Advanced Materials Research 271-273 (luglio 2011): 844–48. http://dx.doi.org/10.4028/www.scientific.net/amr.271-273.844.

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Small unmanned aircraft for civil and military has a wide range of applications. The design of traditional UAV avionics system is use discrete lines which link one point to another to communicate. It will make the system complexity, and the anti-jamming performance is poor. A new kind of design idea of unpiloted aircraft digital avionics system based on CAN bus is introduced, and this article also made a further study in the avionics systems’ critical subsystems, components and redundant design. The new avionics system, which used bus communication system has many good points, such as strong anti-interference ability, easily extended, simply configuration and so on. The system also has a certain value to promotion.

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42

Du, Qiliang, Mingde Sheng, Lubin Yu, Zhenwei Zhou, Lianfang Tian e Shilie He. "Avionics Module Fault Diagnosis Algorithm Based on Hybrid Attention Adaptive Multi-Scale Temporal Convolution Network". Entropy 26, n. 7 (27 giugno 2024): 550. http://dx.doi.org/10.3390/e26070550.

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Since the reliability of the avionics module is crucial for aircraft safety, the fault diagnosis and health management of this module are particularly significant. While deep learning-based prognostics and health management (PHM) methods exhibit highly accurate fault diagnosis, they have disadvantages such as inefficient data feature extraction and insufficient generalization capability, as well as a lack of avionics module fault data. Consequently, this study first employs fault injection to simulate various fault types of the avionics module and performs data enhancement to construct the P2020 communications processor fault dataset. Subsequently, a multichannel fault diagnosis method, the Hybrid Attention Adaptive Multi-scale Temporal Convolution Network (HAAMTCN) for the integrated functional circuit module of the avionics module, is proposed, which adaptively constructs the optimal size of the convolutional kernel to efficiently extract features of avionics module fault signals with large information entropy. Further, the combined use of the Interaction Channel Attention (ICA) module and the Hierarchical Block Temporal Attention (HBTA) module results in the HAAMTCN to pay more attention to the critical information in the channel dimension and time step dimension. The experimental results show that the HAAMTCN achieves an accuracy of 99.64% in the avionics module fault classification task which proves our method achieves better performance in comparison with existing methods.

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43

Qi, Zhen Tao, Xue Jun Zhang e Dong Han. "Avionics System Simulation of General Aviation Aircraft Based on HLA". Applied Mechanics and Materials 229-231 (novembre 2012): 1944–49. http://dx.doi.org/10.4028/www.scientific.net/amm.229-231.1944.

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Simulation is an effective means for system development. A simulation system of the General aviation (GA) avionics using HLA is designed in this paper. The design and implementation process of federates is also described, taking the Cockpit Display federate as an example. The system has good interoperability, reusability and scalability, which meet the requirements of avionics simulation. The system can be widely used in GA avionics design and the training of pilots.

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44

Sahputra, Afandi, Sonoib Sonoib e Amri Akbar Gultom. "Pemanfaatan Instrument Landing System (ILS) Avionics System Trainer AT-01 untuk meningkatkan kompetensi Lulusan SMK Penerbangan". TRIDARMA: Pengabdian Kepada Masyarakat (PkM) 5, n. 1 (30 maggio 2022): 261–71. http://dx.doi.org/10.35335/abdimas.v5i1.2512.

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SMK PBD adalah salah satus ekolah 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 Instrument Landing System (ILS) Avionics System Trainer AT- 01 untuk meningkatkan kompetensi Lulusan SMK PBD. Program tersebut diharapkan dapat meningkatkan wawasan maupun menambah pengetahuan tentang dunia penerbangan khususnya ILS karena nantinya mereka akan memasuki dunia kerja. Hasil dari kegitan ini adalah pelatiahn pemberian materi ILS serta penggunaannya pada Avionics System Trainer AT- 01 dan mempraktekkan kepada peserta penggunaan ILS pada Avionics System Trainer AT- 01 kepada siswa SMK Penerbangan selama 3 hari untuk meningkatkan kompetensi lulusan SMK Penerbangan Pulo Brayan Darat

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45

Deng, Pingyu, Qing Zhou, Dong An, Shihai Wang e Kui Li. "A Modeling Method of Agents and SOA in Advanced Avionics System Based on AADL". Applied Sciences 12, n. 16 (15 agosto 2022): 8157. http://dx.doi.org/10.3390/app12168157.

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The modeling method of agents and service-oriented architecture (SOA) in avionics systems describes agents and SOA in avionics systems with models. To our knowledge, however, the current modeling methods cannot describe the behavior of agents and SOA accurately and do not fit well with the existing avionics system models. This paper addresses the above problems by presenting a modeling method based on architecture analysis and design language (AADL). In this method, the working states of agents are described by the mode components, with the working process being triggered by the input of agents; and the services are described by the process component. The application of the software system is described by the system components that contain several process components. Moreover, different modes of the system are used to describe different applications, and the transitions of application are triggered by specific application requests. Software architecture of an avionics system is modeled by the proposed method. This case demonstrates that the proposed method can accurately describe how agents and SOA work in a new way and fit well with the existing avionics system models.

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46

Schroer, R. "Impact Of Avionics On The Future, And The "Future Of Avionics"". IEEE Aerospace and Electronic Systems Magazine 12, n. 8 (agosto 1997): 10–14. http://dx.doi.org/10.1109/maes.1997.609524.

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47

Zabunov, Svetoslav, e Roumen Nedkov. "Edge controller – a small UAVs distributed avionics paradigm". Aircraft Engineering and Aerospace Technology 92, n. 2 (9 dicembre 2019): 229–36. http://dx.doi.org/10.1108/aeat-04-2019-0087.

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Abstract (sommario):

Purpose This paper aims to reveal the authors’ conceptual and experimental work on an innovative avionics paradigm for small unmanned aerial vehicles (UAVs). Design/methodology/approach This novel approach stipulates that, rather than being centralized at the autopilot, control of avionics devices is instead distributed among controllers – spread over the airframe span, in response to avionics devices’ natural location requirements. The latter controllers are herein referred to as edge controllers by the first author. Findings The edge controller manifests increased efficiency in a number of functions, some of which are unburdened from the autopilot. The edge controller establishes a new paradigm of structure and design of small UAVs avionics such that any functionality related to the periphery of the airframe is implemented in the controller. Research limitations/implications The research encompasses a workbench prototype testing on a breadboard, as the presented idea is a novel concept. Further, another test has been conducted with four controllers mounted on a quadcopter; results from the vertical attitude sustenance are disclosed herein. Practical implications The motivation behind developing this paradigm was the need to position certain avionics devices at different locations on the airframe. Due to their inherent functional requirements, most of these devices have hitherto been placed at the periphery of the aircraft construction. Originality/value The current paper describes the novel avionics paradigm, compares it to the standard approach and further reveals two experimental setups with testing results.

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48

Scott, Winfield. "Solving Electronic System Failures in Aerospace Applications". AM&P Technical Articles 173, n. 9 (1 ottobre 2015): 29–31. http://dx.doi.org/10.31399/asm.amp.2015-09.p029.

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Abstract Determining the root cause of avionics failures requires a disciplined and systematic analytical process supported by sophisticated equipment. This article reviews some of the analytical tools and techniques used to understand and prevent avionics failures.

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49

Fossett, A. J., M. T. Maguire, A. A. Kudirka, F. E. Mills e D. A. Brown. "Avionics Passive Cooling With Microencapsulated Phase Change Materials". Journal of Electronic Packaging 120, n. 3 (1 settembre 1998): 238–42. http://dx.doi.org/10.1115/1.2792628.

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Abstract (sommario):

Analysis for an avionics application typical of remotely located, intermittently operated avionics on aircraft and missiles show that a large weight reduction (about 9:1) can be obtained by using recently developed microencapsulated phase change materials technology instead of a solid aluminum plate for a passive heat sink. Tests with a configuration based on the typical avionics application used for analysis show good agreement with analysis. Use of microencapsulated rather than bulk phase change materials avoids a number of design problems previously encountered with application of such materials.

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Zhang, Hui Nan, Shi Hai Wang, Xiao Xu Diao e Bin Liu. "Test Case Generating for Integrated Modular Avionics Software Health Monitoring". Applied Mechanics and Materials 494-495 (febbraio 2014): 873–80. http://dx.doi.org/10.4028/www.scientific.net/amm.494-495.873.

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Abstract (sommario):

Avionics software is safe-critical embedded system and its architecture is evolving from traditional federated architecture to Integrated Modular Avionics (IMA) to improve resource usability. As an architecture widely employed in the avionics industry, supports partitioning concepts. To insure the development of the avionics software constructed on IMA operating system with high reliability and efficiency Health Monitoring (HM) has been shown to be a key step in reducing the life cycle costs for structural maintenance and inspection. In this paper , we propose a model-driven test methodology using Architecture Analysis &Design Language (AADL). It proposes modeling patterns of IMA errors to support the test case generating mechanisms of the HM module, proposing 3 kinds of test cases that can be injected in the HM to stimulate these kinds of errors, and we present the preliminary results that can meet the satisfactory from a ongoing project based on IMA system.

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