Статті в журналах: "Avionics Design and construction"

1

Wang, Ying, Jian Yong Wang, and Lei Wang. "A Transformation-Based Integrated Modular Avionics Software Model Construction Approach." Applied Mechanics and Materials 668-669 (October 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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2

Zhao, Ke, Shuang Wu, Shao Xiao, and Yong Sheng Xiao. "Based on the Aviation Electronic Laboratory Construction and Practice of Engineering Education." Applied Mechanics and Materials 556-562 (May 2014): 6620–23. http://dx.doi.org/10.4028/www.scientific.net/amm.556-562.6620.

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For integrated avionics maintenance personnel training, construction of take the student as the main body, teacher as the guidance of the aviation electronic experiment center, aviation bus as the core, constitute the integrated avionics system, integrated into the verification, comprehensive design and professional innovative of experiment level and the assessment and management, form the concept of engineering education teaching experiment system, the construction idea of significance of reference to the relevant professional laboratory construction in similar colleges and universities.

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3

Wang, Hong Chun, and Wen Sheng Niu. "Design and Analysis of AFDX Network Based High-Speed Avionics System of Civil Aircraft." Advanced Materials Research 462 (February 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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4

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 (February 2, 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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5

Zabunov, Svetoslav, and Roumen Nedkov. "Edge controller – a small UAVs distributed avionics paradigm." Aircraft Engineering and Aerospace Technology 92, no. 2 (December 9, 2019): 229–36. http://dx.doi.org/10.1108/aeat-04-2019-0087.

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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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6

Kozlyuk, Iryna, and Yuliia Kovalenko. "Reliability of computer structures of integrated modular avionics for hardware configurations." System research and information technologies, no. 2 (September 14, 2021): 84–93. http://dx.doi.org/10.20535/srit.2308-8893.2021.2.07.

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The problem of designing advanced computing systems in the class of structures of integrated modular avionics is considered. The unified topology of the internal network of the computer on the basis of Space Wire exchange channels and variants of its execution for various onboard applications is offered. Equivalent reliability schemes of each of the specific structures are introduced and the probabilities of trouble-free operation of each structure are analyzed. Families of graphic dependencies are given. The analysis of the existing principles and algorithms for testing multiprocessor multimodal onboard digital computer systems is given; the new testing algorithm for the multiprocessor systems which follows the software design standards for products of integrated modular avionics is offered. The structure of the unified automated workplace for checking the functional modules of integrated modular avionics is considered. Specific requirements inherent in the workplaces for testing integrated avionics are identified: an increased level of control of the hardware component of products; the ability to simulate the failure state of individual components of avionics to check the mode of reconfiguration of the computer system; modular construction of software with the division of verification tests into components performed at the level of each CPM and the computer as a whole in single-task and multitasking modes; openness of architecture of a workplace, which provides an ability to change the level of control complexity of a product and control of one class of complexity; intra-project unification of both hardware and software of the workstation of the inspection.

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7

Wang, Lisong, Miaofang Chen, and Jun Hu. "Formal Verification Method for Configuration of Integrated Modular Avionics System Using MARTE." International Journal of Aerospace Engineering 2018 (2018): 1–22. http://dx.doi.org/10.1155/2018/7019838.

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The configuration information of Integrated Modular Avionics (IMA) system includes almost all details of whole system architecture, which is used to configure the hardware interfaces, operating system, and interactions among applications to make an IMA system work correctly and reliably. It is very important to ensure the correctness and integrity of the configuration in the IMA system design phase. In this paper, we focus on modelling and verification of configuration information of IMA/ARINC653 system based on MARTE (Modelling and Analysis for Real-time and Embedded Systems). Firstly, we define semantic mapping from key concepts of configuration (such as modules, partitions, memory, process, and communications) to components of MARTE element and propose a method for model transformation between XML-formatted configuration information and MARTE models. Then we present a formal verification framework for ARINC653 system configuration based on theorem proof techniques, including construction of corresponding REAL theorems according to the semantics of those key components of configuration information and formal verification of theorems for the properties of IMA, such as time constraints, spatial isolation, and health monitoring. After that, a special issue of schedulability analysis of ARINC653 system is studied. We design a hierarchical scheduling strategy with consideration of characters of the ARINC653 system, and a scheduling analyzer MAST-2 is used to implement hierarchical schedule analysis. Lastly, we design a prototype tool, called Configuration Checker for ARINC653 (CC653), and two case studies show that the methods proposed in this paper are feasible and efficient.

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8

Bejan, Adrian, and Sylvie Lorente. "Stepping on the Water." Mechanical Engineering 135, no. 10 (October 1, 2013): 38–41. http://dx.doi.org/10.1115/1.2013-oct-2.

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This study explores various uses of engineering as a tool for solving problems and improving the quality of life. The experiments in the article show that competitive athletes swim with their fingers spread slightly, because this configuration generates greater speed, the research being based on a principle known as constructional law. The constructional law has been applied to predict all the key features of the design of animal locomotion, which includes human running and swimming. In engineering, the discovery expands a domain of constructal-design results that has been growing fast. Bodies that generate heat volumetrically are endowed with maximum heat transfer density when the spacing between the solid surfaces internal to the volume have certain sizes that are smaller in forced convection than in natural convection. The volumetric cooling of future electronics, avionics, and self-cooling materials rests on this class of constructal designs. The swimming with spread fingers is the corresponding design of a body for maximum momentum transfer density.

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9

Lin, Feng, Kevin Z. Y. Ang, Fei Wang, Ben M. Chen, Tong H. Lee, Beiqing Yang, Miaobo Dong, et al. "Development of an Unmanned Coaxial Rotorcraft for the DARPA UAVForge Challenge." Unmanned Systems 01, no. 02 (October 2013): 211–45. http://dx.doi.org/10.1142/s2301385013400049.

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In this paper, we present a comprehensive design for a fully functional unmanned rotorcraft system: GremLion. GremLion is a new small-scale unmanned aerial vehicle (UAV) concept using two contra-rotating rotors and one cyclic swash-plate. It can fit within a rucksack and be easily carried by a single person. GremLion is developed with all necessary avionics and a ground control station. It has been employed to participate in the 2012 UAVForge competition. The proposed design of GremLion consists of hardware construction, software development, dynamics modeling and flight control design, as well as mission algorithm investigation. A novel computer-aided technique is presented to optimize the hardware construction of GremLion to realize robust and efficient flight behavior. Based on the above hardware platform, a real-time flight control software and a ground control station (GCS) software have been developed to achieve the onboard processing capability and the ground monitoring capability respectively. A GremLion mathematical model has been derived for hover and near hover flight conditions and identified from experimental data collected in flight tests. We have combined H∞ technique, a robust and perfect tracking (RPT) approach, and custom-defined flight scheduling to design a comprehensive nonlinear flight control law for GremLion and successfully realized the automatic control which includes take-off, hovering, and a variety of essential flight motions. In addition, advanced mission algorithms have been presented in the paper, including obstacle detection and avoidance, as well as target following. Both ground and flight experiments of the complete system have been conducted including autonomous hovering, waypoint flight, etc. The test results have been presented in this paper to verify the proposed design methodology.

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10

Roshanbin, A., H. Altartouri, M. Karásek, and A. Preumont. "COLIBRI: A hovering flapping twin-wing robot." International Journal of Micro Air Vehicles 9, no. 4 (March 28, 2017): 270–82. http://dx.doi.org/10.1177/1756829317695563.

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This paper describes the results of a six-year project aiming at designing and constructing a flapping twin-wing robot of the size of hummingbird ( Colibri in French) capable of hovering. Our prototype has a total mass of 22 g, a wing span of 21 cm and a flapping frequency of 22 Hz; it is actively stabilized in pitch and roll by changing the wing camber with a mechanism known as wing twist modulation. The proposed design of wing twist modulation effectively alters the mean lift vector with respect to the center of gravity by reorganization of the airflow. This mechanism is modulated by an onboard control board which calculates the corrective feedback control signals through a closed-loop PD controller in order to stabilize the robot. Currently, there is no control on the yaw axis which is passively stable, and the vertical position is controlled manually by tuning the flapping frequency. The paper describes the recent evolution of the various sub-systems: the wings, the flapping mechanism, the generation of control torques, the avionics and the PD control. The robot has demonstrated successful hovering flights with an on-board battery for the flight autonomy of 15–20 s.

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11

Antсev, I. G., G. G. Bundin, V. I. Ischuk, and S. A. Mochalov. "NAVAL AVIATION ON-BOARD AVIONICS COMPLEX: FROM FIFTH TO SIXTH GENERATION." Issues of radio electronics, no. 1 (January 20, 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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12

Altukhov, A. A. "Radio-Electronic Modules and Radiation Monitoring Systems based on Diamond Detectors." Nano- i Mikrosistemnaya Tehnika 23, no. 5 (October 22, 2021): 266–76. http://dx.doi.org/10.17587/nmst.23.266-276.

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An overview of the current state and promising areas of application of semiconductor diamond detectors for creating radio-electronic monitoring systems for ionizing studies based on them is given. The main attention is paid to the creation of multifunctional space radiation monitoring systems that combine a set of diamond detectors and hardware and software tools that provide diagnostics of dose and spectrometric characteristics of various types of radiation. The data on the developed and manufactured samples of blocks and on-board control systems for cosmic and ionizing radiation are presented. The overview shows that diamond ionizing radiation detectors (IRD) are actively used in the creation of radio-electronic devices and monitoring systems for ionizing and cosmic radiation. The use of diamond IRD in combination with the developed design and technological solutions, hardware and software principles for the construction of such devices make it possible to create samples of on-board onboard avionics for separate measurement of the parameters of cosmic radiation and neutron fluxes, gamma radiation, characterized by small dimensions, high speed, hardness to radiation, mechanical and temperature influences. Multifunctional systems for ionizing radiation detection based on diamond detectors use the accumulated experience of successful development and application of discrete diamond IRD allowed us to start creating multifunctional modules and radiation monitoring systems (RMS) based on them. Theыыыыыы creation of such devices allows us to practically demonstrate the traditional advantages of discrete DIRD (high speed, the highest radiation hardness, high resistance to mechanical and thermal influences) in on-board equipment with smaller mass dimensions. The main structural and technological solutions that ensure the creation and effective functioning of RMS based on diamond IRD are the following: (1) separation the IR flow into energy sub-bands; (2) the use of software and hardware processing of data received from the IRD; (3) using a multi-detector system. Further development of research and development in these areas, in addition to solving the target tasks of radio-electronic instrumentation, will stimulate technological progress in various areas of solid-state electronics, including materials science and physics of wide-band semiconductors, the development of an experimental and technological base for the synthesis of diamond bulk crystals and multilayer structures, the creation of new technologies for ion-plasma processing of semiconductors, and a number of others.

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13

Ma, Teng Da, and De Xin Zhou. "Design of Civil Aircraft Avionics System Bus Excitation System." Advanced Materials Research 1037 (October 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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14

Jiang, Na, Chunpeng Zhang, Yang Cao, and Rixin Zhan. "Application of prognostic and health management in avionics system." Highlights in Science, Engineering and Technology 7 (August 3, 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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15

Wu, Jian Jun, Da Hai Zhao, and Wei Wan. "Digital Research of Unmanned Aerial Vehicle Avionics System Based on CAN Bus." Advanced Materials Research 271-273 (July 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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16

Shim, Jae Ick, Jae Won Choi, Yong Tae Kim, Dong Wan Yoo, Kook Bo Yang, Hyun Seok Ha, Sang Jin Kim, Seung Yul Lee, and Sang Jun Jung. "Avionics Architecture Design for Military Unmanned Aerial Vehicles." Journal of the Korea Institute of Military Science and Technology 25, no. 6 (December 5, 2022): 628–36. http://dx.doi.org/10.9766/kimst.2022.25.6.628.

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This paper describes the design of the avionics architecture for military unmanned aerial vehicles considering the airworthiness requirements for the first time. This design considers the redundancy in the system data bus and the power system and the data link system to meet the system safety requirements of the airworthiness requirements of military UAVs. This avionics architecture design has been verified through the system integration test and the flight test after manufacturing the UAV.

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17

Qi, Zhen Tao, Xue Jun Zhang, and Dong Han. "Avionics System Simulation of General Aviation Aircraft Based on HLA." Applied Mechanics and Materials 229-231 (November 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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18

Collins, P. H., and B. L. Perry. "Systems and avionics." Aeronautical Journal 107, no. 1072 (June 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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19

Quinn, Gordon F., and Michael J. Breza. "Integrating Avionics in the Conceptual Design Phase." IEEE Aerospace and Electronic Systems Magazine 2, no. 11 (November 1987): 2–4. http://dx.doi.org/10.1109/maes.1987.5005267.

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20

Leonard, C. T. "How mechanical engineering issues affect avionics design." IEEE Aerospace and Electronic Systems Magazine 5, no. 4 (April 1990): 3–8. http://dx.doi.org/10.1109/62.54608.

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21

Zhou, Qiang, Yongan Wei, and Longjiang Zhu. "Research on reliability modeling of unmanned aircraft system avionics systems based on 5G." International Journal of Distributed Sensor Networks 15, no. 7 (July 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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22

Indriyanto, Toto, and Hedi Hartalita. "Affordable and Reliable Avionics Architecture Design for Advanced Regional Turboprop Aircraft." Applied Mechanics and Materials 842 (June 2016): 233–40. http://dx.doi.org/10.4028/www.scientific.net/amm.842.233.

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Integrated avionics architectures offer advantages such as higher flexibility, reliability, simplicity, future upgradeability and weight saving over previous federated designs. Successful implementations of integrated modular avionics (IMA) are onboard Boeing B777, B787, Airbus A380 and A350. These applications often result in development and maintenance cost not suitable for regional and general aviation aircraft. One popular approach to overcome this problem is by using integrated flight deck (IFD) supplied by avionics manufacturers such as Garmin or Honeywell. These manufacturers often optimize IFDs for applications in developed countries. For example, with the development and widespread use of satellite-based global positioning system (GPS) in the US, Canada and Europe, some terrestrial navigation equipment (e.g. ADF and DME) are no longer included in the standard IFD packages offered for commercial aviation. However, many areas in the rest of the world still use and rely largely on the availability of the ADF, DME, etc. Aircraft flying in these areas need to comply with the local requirements for terrestrial navigation systems already deployed. In this paper a study on the implementation of additional avionics equipment on Garmin G1000 for advanced regional turboprop aircraft is presented. G1000 is an integrated avionics system that integrates many electronic components including navigation, communication, course, attitude, display, etc. It has been widely used in all kinds of civil aviation aircraft. In order to conform to local and modern requirements, ADF receiver, DME transceiver, traffic alerting system and weather radar need to be integrated. Preliminary reliability analysis using fault tree method is performed for the designs to ascertain their safety as set out in the requirements for advanced regional turboprop aircraft.

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23

Fielding, J. P., and 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, no. 6 (June 1, 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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24

Guryanov, A. V. "RESEARCH OF ORGANIZATION OF SUPPLY CHAIN MANAGEMENT TO MAINTAIN THE FUNCTIONALITY OF AVIONIC EQUIPMENT." System analysis and logistics 4, no. 26 (December 17, 2020): 26–34. http://dx.doi.org/10.31799/2007-5687-2020-4-26-34.

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The article reveals the issues of replacing spare serviceable devices (spare parts) for avionics objects for aircraft, discusses the organization and construction of supply chains, discusses the features of the functioning of avionics objects and their repair. The necessity of including blocks for modeling various scenarios of supply chains into the decision-making loop for the assembly and launch of spare devices is substantiated. Particular attention is paid to the classification of methods for calculating spare parts, based on the theory of restoration processes. The graphs of the function of increasing the functioning of avionics objects, graphs of the reliability of objects and graphs of forecasting the number of deliveries are given. The article discusses the possibilities of organizing supplies and their unique features. The necessity of modeling various delivery options and the limited data obtained on the basis of standard parameters, which include the technical reliability of the parameters of specific devices, are proved. Key words: SPTA, avionics, instrument, supply chain, aviation instrument reliability.

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25

Peng, Yuyang. "Forward Design Method of Avionics System Based on Communication." Mobile Information Systems 2021 (November 8, 2021): 1–6. http://dx.doi.org/10.1155/2021/5984066.

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With the rapid development of computer technology, electronic technology, and control technology, communication-based avionics systems can provide greater potential for the improvement of aircraft combat capabilities. Moreover, during the flight, passengers have an increasing demand for space communications. How to provide passengers with a communication-based aerospace electronic system that is indistinguishable from the ground during the flight is a problem that needs to be solved urgently. The research on the forward design method of this system has been highly valued by experts at home and abroad. This article is a communication-based forward design method for avionics systems. Based on the development of aerospace data communication technology, this article discusses the advantages of the application of the CCSDS (Consultative Committee for Space Data Systems) protocol in the design of aerospace electronic communication systems. This research designs the technical scheme of the entire aerospace communication electronic system and refers to the relevant CCSDS protocol to complete the design of the distributor’s fast transmission telemetry package and the distributor’s slow transmission telemetry package. This article introduces the two existing architectures of the integrated avionics system, compares and analyzes them, and then elaborates the integrated avionics system architecture based on trusted computing and the trust chain transfer mechanism. The experimental results show that the method designed in this paper uses the NBSP basic protocol in an aeronautical communication environment with a nesting depth of 2 s. When the data transmission delay is 2 s, the NBSP scheme is 0.9 and the NERON scheme is 0.4. This shows that the design method of this study is able to meet the requirements of the system and technical indicators.

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26

Zhang, Peng, Hou Jun Wang, Li Li, and Ping Wang. "Design and Implementation of Intermediate Frequency Generation and Analysis Module for Avionics Test." Advanced Materials Research 1049-1050 (October 2014): 1147–53. http://dx.doi.org/10.4028/www.scientific.net/amr.1049-1050.1147.

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To test airborne avionics device, it is necessary to provide signal stimulus for the device under test (DUT) to simulate the real work environment. This paper proposes a hardware module which used to signal generate and analyze. The hardware structure and diagram of logic design are described. The generated waveforms and measurement results are presented. This test module combined with other necessary modules can achieve the test of L band airborne avionics such as ATC, TCAS and TACAN.

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27

Kim, Joo Nyun, and You-Chol Lim. "Avionics System Design Trend for The Launch Vehicle." Journal of the Korean Society of Propulsion Engineers 24, no. 4 (August 1, 2020): 48–54. http://dx.doi.org/10.6108/kspe.2020.24.4.048.

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28

Park, Han-Joon, Kwang-Chun Go, and Jae-Hyun Kim. "Design Method for Integrated Modular Avionics System Architecture." Journal of Korea Information and Communications Society 39C, no. 11 (November 28, 2014): 1094–103. http://dx.doi.org/10.7840/kics.2014.39c.11.1094.

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29

Li Ma, XiuBin Zhang, Ke Wang, and YueHua Luo. "BIT Design of Hierarchical Structure of Avionics System." International Journal of Digital Content Technology and its Applications 6, no. 5 (March 31, 2012): 58–66. http://dx.doi.org/10.4156/jdcta.vol6.issue5.8.

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30

Buzdalov, D. V., S. V. Zelenov, E. V. Kornykhin, A. K. Petrenko, A. V. Strakh, A. A. Ugnenko, and A. V. Khoroshilov. "Tools for System Design of Integrated Modular Avionics." Proceedings of the Institute for System Programming of RAS 26, no. 1 (2014): 201–30. http://dx.doi.org/10.15514/ispras-2014-26(1)-6.

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31

Subramanyam, V. R., and L. R. Stine. "Design for testability for future digital avionics systems." IEEE Aerospace and Electronic Systems Magazine 3, no. 6 (June 1988): 2–6. http://dx.doi.org/10.1109/62.874.

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32

Crisci, M., W. Geri, and G. Bertoni. "DEIS UAV: GNC Design and Avionics Implementation Issues." IFAC Proceedings Volumes 37, no. 6 (June 2004): 747–52. http://dx.doi.org/10.1016/s1474-6670(17)32266-8.

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33

Succa, Massimo, Ilario Boscolo, Alessandro Drocco, Giovanni Malucchi, and Stephane Dussy. "IXV avionics architecture: Design, qualification and mission results." Acta Astronautica 124 (July 2016): 67–78. http://dx.doi.org/10.1016/j.actaastro.2016.01.006.

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34

Ilarslan, Mustafa, M. Kemal Bayrakceken, and Aydemir Arisoy. "Avionics system design of a mini VTOL UAV." IEEE Aerospace and Electronic Systems Magazine 26, no. 10 (October 2011): 35–40. http://dx.doi.org/10.1109/maes.2011.6065657.

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35

Fossett, A. J., M. T. Maguire, A. A. Kudirka, F. E. Mills, and D. A. Brown. "Avionics Passive Cooling With Microencapsulated Phase Change Materials." Journal of Electronic Packaging 120, no. 3 (September 1, 1998): 238–42. http://dx.doi.org/10.1115/1.2792628.

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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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36

Riley, Daniel D., and Paul G. Stringer. "Cockpit Automation Concept Development for the NUH-60 (STAR) Aircraft." Proceedings of the Human Factors Society Annual Meeting 31, no. 12 (September 1987): 1383–87. http://dx.doi.org/10.1177/154193128703101218.

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A study was performed to derive an automation and avionics integration design concept for the NUH-60 Systems Testbed for Avionics Research (STAR) aircraft. The STAR, a one-of-a-kind reconfiguration of the UH-60 Black Hawk helicopter, is being developed by the U.S. Army Avionics Research and Development Activity to provide a flight demonstrator and research vehicle for state-of-the-art cockpit technology. The work was directed toward determining cockpit design preferences associated with single-pilot performance of the Army scout and utility missions. Emphasis was placed on high workload phases of the missions during which eyes-out-of-the-cockpit and hands-on-controls performance capabilities would be most crucial. A number of cockpit-based design alternatives in the areas of communication, navigation, aircraft survivability equipment (ASE) operations, subsystem status monitoring, and aircraft performance computation and prediction were systematically derived and proposed.

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37

Kothari, Rushabh, and CT Sun. "Design and analysis of multifunctional structures with embedded electronics for thermomechanical loads." Journal of Sandwich Structures & Materials 14, no. 6 (November 2012): 734–52. http://dx.doi.org/10.1177/1099636212460541.

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Multifunctional structures, of various forms, are being used in aerospace industry and there have been increasing efforts to enhance their performance. The design and analysis of a composite sandwich beam embedded avionics and integrated cooling systems is presented in this article. The integrated electronics inside a sandwich beam reduces the overall weight of a vehicle by eliminating most of the avionics housing, cables, interconnects, etc. The foam core of a sandwich beam is modified with a cavity to embed avionics. Since the presence of a cavity degrades the strength of the structure, various methods of reinforcement have been presented. The heat dissipation system has been designed to protect the structure from excessive thermal loads. The design of heat dissipating system consists of two parts, thermal interface materials and a highly efficient heat transfer device. Design guidelines for a thermal interface material consisting of particulate composites are presented here. Among various choices, heat pipes have been chosen as the preferred heat transfer device. An example is given for an unmanned aerial vehicle skin acting as the heat sink to maintain embedded electronics within their operational limit at subsonic air speeds.

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38

Jiang, Lian Xiang, and Ming Rui Xin. "Research on FDIR Technology of Satellite Avionics." Applied Mechanics and Materials 198-199 (September 2012): 1136–40. http://dx.doi.org/10.4028/www.scientific.net/amm.198-199.1136.

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Fault discovery, isolation and recovery has become more and more important in the satellite avionics design with more and more autonomous and intelligent requirement to satellite. A brief review of fault discovery, isolation and recovery technologies are introduced in the sort of fault detection, fault isolation and fault recovery. A fault discovery, isolation and recovery system architecture for satellite avionics is proposed, the specific fault detection and isolation design is introduced in detail, the possible recovery solutions is also suggested.

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39

Deng, Pingyu, Qing Zhou, Dong An, Shihai Wang, and Kui Li. "A Modeling Method of Agents and SOA in Advanced Avionics System Based on AADL." Applied Sciences 12, no. 16 (August 15, 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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40

Baldi, Mario, and Guido Marchetto. "Design of a Deterministic Service Switch for Avionics Networks." Journal of Aerospace Information Systems 11, no. 6 (June 2014): 386–96. http://dx.doi.org/10.2514/1.i010176.

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41

Hammett, R. "Design by extrapolation: an evaluation of fault tolerant avionics." IEEE Aerospace and Electronic Systems Magazine 17, no. 4 (April 2002): 17–25. http://dx.doi.org/10.1109/62.995184.

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42

Watkins, Christopher, and Randy Waiter. "Design considerations for systems hosted on integrated modular avionics." IEEE Aerospace and Electronic Systems Magazine 24, no. 10 (October 2009): 30–35. http://dx.doi.org/10.1109/maes.2009.5317784.

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43

Romdhani, M., P. de Chazelles, A. Jeffroy, A. E. K. Sahraoui, and A. A. Jerraya. "Co-Specifications for Co-Design in Avionics Systems Development." IFAC Proceedings Volumes 28, no. 22 (September 1995): 73–76. http://dx.doi.org/10.1016/s1474-6670(17)46671-7.

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44

Du, Xiaoyan, Chenglie Du, Jinchao Chen, Chunhui Dong, and Yifan Liu. "Ontology-Based Resource Modeling and Matching Framework in Avionics Systems." International Journal of Aerospace Engineering 2022 (September 12, 2022): 1–11. http://dx.doi.org/10.1155/2022/8284857.

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In order to realize rapid service-oriented construction of resources and efficient supply-demand matching in avionics systems, an ontology-based resource modeling and matching framework in avionics systems is proposed. First, this paper constructs a hierarchical resource organization framework based on virtual resource pool, covering dispersed and heterogeneous avionics resources and shielding the differences and diversity of resources; next, introduces ontology technology into resource modeling and encapsulates resources as services using the idea of “resource as a service,” facilitating the access and control of resources; in addition, proposes a matching framework which takes into account the energy consumption, in which it firstly tries to find a list of resources which can meet task requirements by a stepwise intelligent matching strategy based on semantic similarity, and the resources in the list will then be sorted according to the energy consumption. Finally, a radar detection case is taken to demonstrate that the proposed model and method are feasible and effective.

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45

Shen, Xueqiang, and Yan Bai. "Architectural considerations in integrated modular avionics (IMA) system safety case construction." IEEE Aerospace and Electronic Systems Magazine 29, no. 10 (October 2014): 26–33. http://dx.doi.org/10.1109/maes.2014.130085.

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46

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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47

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

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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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48

Wang, Peng, Changxiao Zhao, and Fang Yan. "Research on the Reliability Analysis of the Integrated Modular Avionics System Based on the AADL Error Model." International Journal of Aerospace Engineering 2018 (2018): 1–11. http://dx.doi.org/10.1155/2018/9358461.

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In recent years, the integrated modular avionics (IMA) concept has been introduced to replace the traditional federated avionics. Different avionics functions are hosted in a shared IMA platform, and IMA adopts partition technologies to provide a logical isolation among different functions. The IMA architecture can provide more sophisticated and powerful avionics functionality; meanwhile, the failure propagation patterns in IMA are more complex. The feature of resource sharing introduces some unintended interconnections among different functions, which makes the failure propagation modes more complex. Therefore, this paper proposes an architecture analysis and design language- (AADL-) based method to establish the reliability model of IMA platform. The single software and hardware error behavior in IMA system is modeled. The corresponding AADL error model of failure propagation among components, between software and hardware, is given. Finally, the display function of IMA platform is taken as an example to illustrate the effectiveness of the proposed method.

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49

Ha, Ok Kyoon, Eu Teum Choi, and Yong Kee Jun. "Design and Implementation of Software Configuration Tool for Integrated Modular Avionics." Applied Mechanics and Materials 651-653 (September 2014): 1827–30. http://dx.doi.org/10.4028/www.scientific.net/amm.651-653.1827.

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ARINC 653 specification has been introduced as a standardized interface definition of real-time operating system to simplify the development of Integrated Modular Avionics. The ARINC 653 provides a strict and robust time and space partitioning to guarantee the reliability of avionics by isolating the failures of the system. Configuration data for the time and space partitions in the ARINC 653 can be defined as the XML configuration file that can be accessed only by system OS. Unfortunately, it is quite tedious activity to confirm the integrity of partition scheduling and to check the syntax errors of XML during the integration tasks. In this paper, we present a software configuration tool that provides generating the configuration data and verifying the integrity of partitioning based on XML Scheme of the ARINC 653 standard.

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50

Kovalenko, Yuliia. "METHODS OF DEVELOPING INTEGRATED MODULAR AVIONICS SYSTEMS." Scientific Journal of Polonia University 43, no. 6 (June 18, 2021): 324–34. http://dx.doi.org/10.23856/4341.

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The development of modern avionics systems makes the design of such systems impossible without the use of automation tools. Currently, the area of such tools is represented by patented tools developed by major aircraft manufacturers such as Boeing and Airbus, as well as a number of open or partially open international projects, differing in terms of validity, availability of source code and documentation. All tools are based on architectural models of the developed system. This article discusses the languages available for describing architectural models of avionics systems and shows which programming language is most appropriate due to its textual notation and embedded concepts that are well suited to represent most of the elements of embedded systems. The article then presents a set of tools for designing modern avionics systems. The toolbox provides both a general platform for designing and analyzing architectural models and a specialized solution for a specific area of avionics systems. It supports creating, editing and manipulating models in both text and graphic formats.

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