Готові списки джерел за темами / Avionics Design and construction

Добірка наукової літератури з теми "Avionics Design and construction"

Автор: Grafiati
Опубліковано: 10 грудня 2022
Оновлено: 28 січня 2023

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Статті в журналах з теми "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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Анотація:
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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Анотація:
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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Анотація:
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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Анотація:
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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Анотація:
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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Анотація:
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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Анотація:
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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Анотація:
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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Анотація:
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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Анотація:
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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Більше джерел

Дисертації з теми "Avionics Design and construction"

1

Byrne, James Michael Jr. "Resource-constrained avionics design for CubeSats." Thesis, Massachusetts Institute of Technology, 2016. http://hdl.handle.net/1721.1/105559.

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Анотація:
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2016.
This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
Cataloged from student-submitted PDF version of thesis.
Includes bibliographical references (pages 90-92).
We present an optimization approach to CubeSat avionics design which considers the consumption of some resources (electrical power, volume) and production of others (processing power, volatile memory, non-volatile memory, and radiation tolerance) in a quantitative optimization analysis. We present the avionics hardware design for the Microwave Radiometer Technology Acceleration (MiRaTA) 3U CubeSat, funded by the NASA Earth Science Technology Office (ESTO), as a case study for our optimization analysis. MiRaTA will demonstrate a three-band microwave radiometer and GPS radio occultation (GPSRO) sensor suite for profiling atmospheric temperature, humidity, and cloud ice. The goal is to increase the Technology Readiness Level (TRL) of the weather-sensing technology from TRL 5 to TRL 71. The avionics system is the "central nervous system" of the spacecraft, managing interfaces with every subsystem and between the Bus and Payload. MiRaTA's avionics design supports the Payload, which is tasked with the science mission to gather and process appropriate radiometer and GPSRO data, and the Bus, which comprises subsystems to handle attitude determination and control (ADC), power regulation and distribution, communications with the ground station, thermal management, and a suite of sensors and telemetry components. MiRaTA's avionics system uses a custom designed motherboard with a PIC24FJ256GB210 microcontroller to command activity in the Bus and manage data and power for the Payload. This custom Motherboard - dubbed the "Micron Motherboard" - leverages many of the advantages of the popular Pumpkin Motherboard but with reduced complexity and improved performance. The MiRaTA avionics system is also designed to minimize the number and length of cables, simplify connector uniformity, and improve accessibility. The design improvement in avionics hardware from MicroMAS to MiRaTA is quantified using an optimization coefficient: 1.522. We expect optimization coefficients to range typically from -4 to +4, so this design indicates a modest improvement.
by James Michael Byrne, Jr.
S.M.
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2

Ellis, Colleen Laverna, and Allan D. Kraus. "Preliminary design of a water cooled avionics rack." Thesis, Monterey, California: Naval Postgraduate School, 1993. http://hdl.handle.net/10945/24217.

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3

Törnblom, John. "Improving Quality of Avionics Software Using Mutation Testing." Thesis, Linköpings universitet, Databas och informationsteknik, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-105456.

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Анотація:
Mutation testing is a powerful fault-based testing technique that makes syntactic changes to a program under test in order to simulate real faults otherwise caused by a programmer. Similar to structural coverage criteria such as statement coverage, mutation testing is used to assess the quality of a test suite. After a syntactic change has been made, the program is referred to as a mutant that either can survive a test suite, or be killed by one. If a mutant is killed, it means that the test suite has detected the syntactic change and reported it as an error, resulting in an increased mutation score. If a mutant survives, it means that the test suite failed to detect the fault and the mutation score is decreased. Mutation testing is generally considered the strongest testing technique available in terms of fault detection, but also the most expensive one. However, thanks to recent research and the rapid development of computing hardware, the testing technique is starting to become feasible, motivating the creation of tools utilizing the power of mutation testing. Saab AB, the Swedish aircraft manufacturer and stakeholder in this thesis, has experimented with mutation testing in the past, resulting in a tool called BAX that creates textual modifications of the original source code. The initial goal of this thesis is to provide a new tool that is faster than BAX, and that is more systematic in the way mutants are generated. LLVM-P86, the main contribution of this thesis, is a compiler and mutation testing framework intended for the programming language Pascal-86. Unlike BAX, LLVM-P86 is able to encode several mutants into a single program, thus reducing the time spent on compiling source code. In the conducted experiments, LLVM-P86 processed mutants significantly faster than BAX, on average by a factor of 13.6. Since LLVM-P86 is also a compiler, proper type information is available when mutants are generated. The additional type information allows LLVM-P86 to avoid a significant amount of equivalent mutants, i.e. mutants that behave in the same way as the original program. When mutating relational operators found in approximately 10,000 lines of code, distributed amongst 18 different Pascal-86 modules, LLVM-P86 was able to reduce the total number of living mutants by 25%, or 5.7% of the complete set of mutants.
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4

Kahn, Aaron David. "The design and development of a modular avionics system." Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/15712.

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5

Vetter, David B. (David Brian). "Design of multi-passage cooling systems for avionics applications." Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/115475.

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6

Omelchenko, Alexander 1968. "Avionics systems design for cooperative unmanned air and ground vehicles." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/17789.

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Анотація:
Thesis (S.M. and E.A.A.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004.
"June 2004."
Includes bibliographical references (p. 95).
This thesis summarizes the results of the design of avionics systems intended for use onboard unmanned air and ground vehicles, that are parts of a multi-vehicle system whose primary mission objective is to provide up-close surveillance capability from a large stand-off distance. Different types of cooperative action between air and ground vehicles, that can help to enhance the overall system surveillance capability, are analyzed, including communication relay, simultaneous visual surveillance of ground objects from air and ground vehicles, and visual coverage of ground vehicles from air vehicles. Both hardware and software design as well as practical implementation of the designed avionics systems are discussed, and results of field tests are presented.
by Alexander Omelchenko.
S.M.and E.A.A.
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7

Carvalho, Fabiano Costa. "On the design of integrated modular avionics assisted by formal modeling." Instituto Tecnológico de Aeronáutica, 2009. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1218.

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Анотація:
Avionics system manufacturers are currently facing the problem of developing highly-integrated systems under economic pressures. In this scenario, the empirical approach, characterized by trial and error techniques, is not adequate since the correction of design flaws is often related to expensive re-work and schedule overruns. The evolution of airborne systems toward Integrated Modular Avionics (IMA) pushes the need for advanced methods that could enforce correctness of complex designs while minimizing the chances of introducing errors. Considering this problem, this work proposes a systematic conceptual design strategy based on formal methods, aiming at improving the development processes for IMA systems. The basic idea is to concentrate efforts on the construction, simulation, and formal analysis of a mathematical model for the new system at early development lifecycle phases. The proposed approach was exercised on a case study of practical avionics project in order to evaluate the drawbacks and advantages. Results suggest that this work could contribute to the aeronautics industry by offering alternative means to cope with complexity in modern avionics projects.
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8

Gia, M. C. "Design of data structures for terrain reference navigation." Thesis, Cranfield University, 1994. http://hdl.handle.net/1826/4184.

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Анотація:
This thesis describes the design of a data structure for use with Digitised Terrain Elevation Data (DTED) in Terrain Reference Navigation (TRN) systems. The data structure is based on a variant of quad-tree and oct-tree data structures to provide an efficient representation of terrain in terms of storage requirements and acccss operations. These data structure are applied to flight path planning operations in mission management applications. The algorithms developed for flight path planning have becri implemented in the C programming language for a standard PC. Current research in TRN systems is reviewed and attention is given to the use of hierarchical data structures to cope with the potentially large data base needed for DTED files. Data structure combining quad-trees and oct-trees are developed with an emphasis on data reduction using pointerless trees and the use of locational codes to provide straightforward mapping between quad-trees and oct-trees, in other words, between two-dimensional co-ordinates and three-dimensional co-ordinates. Analysis of these algorithms is described for two DTED files to illustrate storage improvements and to verify a set of database access operations. These data structures are applied to problems of flight path planning where the navigation space comprises objects above a specific altitude and this three-dimensional space is searched for a flight path which avoids the obstacles and satisfies specific operational criteria. Algorithms are developed to extract a visibility graph from the terrain database and to determine the preferred flight path from a set of paths which satisfy defined constraints. Several search techniques are developed which exploit the efficiency of the quad-tree and oct-tree data structures. These methods are extended to real-time flight-path planning where predicted times for access operations are used to direct flight path extraction by varying the tree resolution during computation of the flight path. A comprehensive set of results are provided to illustrate: the storage efficiency of quad-tree and oct-tree data structures the application of pyramid structures to represent navigation space analysis of the time to compute the visibility graph and to extract flight paths integration of these methods with a real-time mission management simulation on a PC The thesis draws conclusions on the efficiency of these techniques for the represcntation of DTEDs and to access objects in TRN systems. It is observed that the use of hierarchical data structures in the form of quad-trees and oct-trees offers significant improvement in accessing DTEDS, for future use in TRN systems. The thesis concludes by outlining areas of further work where the techniques can be further &N, cloped for applications in mission management and navigation using DTED files.
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9

Ba, Kadiata. "Intégration de la modélisation du matériau et du procédé pour le design et l'optimisation d'une composante de train d'atterrissage d'avion : procédé de forgeage." Doctoral thesis, Université Laval, 2017. http://hdl.handle.net/20.500.11794/29950.

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Анотація:
Le présent travail concerne l’intégration de la modélisation du matériau et du procédé dans le design et l’optimisation d’une composante de train d’atterrissage d’avion fabriquée par forgeage à chaud en collaboration avec la société Héroux-Devtek. Pour mener à bien cette tâche, un travail d’investigation des différents aspects du matériau, du procédé et des techniques de modélisations numériques a été effectué. Une caractérisation des propriétés mécaniques et métallurgiques de l’alliage d’aluminium 7175 sous différentes conditions a été réalisée, ce qui a conduit à une meilleure connaissance du comportement de cet alliage notamment dans les conditions de forgeage. Le modèle de comportement de Johnson-Cook a été caractérisé et utilisé pour les simulations des différents cas d’analyse. Une investigation au niveau de l’intégration de l’effet de la microstructure dans le modèle de comportement a été faite. Cette étude a conduit à considérer le modèle de Johnson-Cook modifié qui a la particularité de prendre en compte les effets de la recristallisation dynamique dans le modèle d’écoulement du matériau. Une meilleure précision est obtenue en comparaison avec le modèle de Johnson-Cook standard pour des simulations impliquant de hauts niveaux de déformation. De plus, une investigation au niveau des plus récents outils de simulation a été effectuée. Une étude comparative des formulations CEL (Couplage Eulérien-Lagrangien) et SPH (Smoothed Particle Hydrodynamics) vis-à-vis de la méthode classique des ÉF (éléments finis) a permis de classifier les différentes approches selon leurs performances relatives lors des simulations du forgeage de pièces complexes en grandes transformations (écoulement de matière très important). Pour pouvoir utiliser la formulation SPH interne à Abaqus dans le cas de couplage thermomécanique, il a fallu développer un VUMAT («user ’s material») thermomécanique. Une contribution a été apportée au niveau de la méthode SPH pour la simulation plus précise du forgeage, d’abord en extensionnant un code SPH maison afin qu’il puisse résoudre des problèmes thermomécaniques couplés en grandes déformations et ensuite en transformant le code SPH en un élément de l’usager («user’s element») via l’utilitaire VUEL d’Abaqus en formulation Lagrangienne totale. En guise de validation, nous avons réalisé des travaux autant de nature numérique qu’expérimentale. Au niveau numérique, les résultats obtenus avec le code maison ont été validés par comparaison avec les résultats obtenus avec le code commercial Abaqus. Par ailleurs afin d’atteindre l’objectif principal d’intégration de la modélisation du matériau et du procédé, une méthodologie d’analyse appropriée a été développée et validée expérimentalement en concevant et en fabriquant par forgeage, un prototype représentatif de la pièce industrielle. Mots-clés : Forgeage à chaud, train d’atterrissage, caractérisation, alliages d’aluminium, Johnson-Cook, recristallisation dynamique, Abaqus, ÉF, CEL, VUMAT, VUEL SPH, formulation Lagrangienne totale, code SPH.
The present work deals with the development of an integrated material and process modeling methodology for the design and optimization of an aircraft landing gear component manufactured using hot forging process in collaboration with Héroux-Devtek. To carry out this work, an investigative work of the different aspects of the material, process and numerical modeling techniques is performed. A characterization of mechanical and metallurgical properties of the aluminum alloy 7175 under various conditions has been done and the work allowed to better know the behavior of this alloy particularly in our forging conditions. The Johnson-Cook constitutive model was characterized and used for simulations of various processes analysis. An investigation about the integration of the effect of the microstructure in the material behavior law was realized. This study led one to consider a modified Johnson-Cook model that can take account of the effects of dynamic recrystallization during the material flow. A greater accuracy was obtained in comparison with the standard Johnson- Cook model for simulations involving high strain levels. An investigation about the simulation tools was also performed. A comparative study of CEL (Coupling Eulerian-Lagrangian) and SPH (Smoothed Particle Hydrodynamics) formulation with the finite elements method (FEM) allowed to classify the different methods according to their performance in the simulations of complex forged part involving large deformations (very important material flow). To use the SPH formulation existing in Abaqus for the simulation of coupled thermomechanical problems, it was first necessary to develop a thermomechanical VUMAT (user’s material) subroutine. For more accurate simulation of forging process, a contribution was made regarding the SPH method. To do this, an independent in-house SPH code and an ABAQUS VUEL (user’s element) subroutine based on the total Lagrangian formulation of solid mechanic’s equations were developed. For validation purposes, both numerical investigations and experimental works were accomplished. Regarding the numerical simulation, the results obtained with the in-house code were validated by comparing them with results obtained using the Abaqus FE commercial code. Moreover, in order to achieve the main objective of integrated material and process modeling for the product design, a suitable methodology was developed and validated experimentally by designing and manufacturing by the closed die hot forging process, a representative prototype of the industrial part. Keywords: Hot forging, landing gear, aluminum alloys, Johnson-Cook, dynamic recrystallization, Abaqus, FE, CEL, VUMAT, VUEL SPH, total Lagrangian formulation, SPH code.
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Carrillo, Cassandra M. "Continuous biometric authentication for authorized aircraft personnel : a proposed design." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Jun%5FCarrillo.pdf.

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Книги з теми "Avionics Design and construction"

1

Avionic systems design. Boca Raton: CRC Press, 1994.

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Moir, I. Aircraft systems: Mechanical, electrical, and avionics subsystems integration. Reston, VA: American Institute of Aeronautics and Astronautics, 2001.

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Moir, I. Aircraft systems: Mechanical, electrical, and avionics subsystems integration. Chichester, West Sussex, England: Wiley, 2008.

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G, Seabridge A., ed. Aircraft systems: Mechanical, electrical, and avionics subsystems integration. London and Bury St Edmunds, UK: Professional Engineering Publishing Limited, 2001.

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Moir, I. Aircraft systems: Mechanical, electrical, and avionics subsystems integration. 3rd ed. Reston, VA: American Institute of Aeronautics and Astronautics, 2008.

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6

Introduction to aircraft design. Cambridge: Cambridge University Press, 1999.

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7

Thomas, John Tudor. Display technologies and applications for defense, security, and avionics III: 17 April 2009, Orlando, Florida, United States. Edited by SPIE (Society). Bellingham, Wash: SPIE, 2009.

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Thomas, John Tudor. Display technologies and applications for defense, security, and avionics III: 17 April 2009, Orlando, Florida, United States. Bellingham, Wash: SPIE, 2009.

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Martín, Francisco Guillermo San. Historia de la fábrica militar de aviones. [Córdoba]: Ediciones del Corredor Austral, 2005.

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Claus, Weiland, and American Institute of Aeronautics and Astronautics, eds. Selected aerothermodynamic design problems of hypersonic flight vehicles. Berlin: Springer, 2009.

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Частини книг з теми "Avionics Design and construction"

1

Maisel, Jordana L., Edward Steinfeld, Megan Basnak, Korydon Smith, and M. Beth Tauke. "Construction." In Inclusive Design, 97–124. New York : Routledge, 2017. | Series: PocketArchitecture : technical design series: Routledge, 2017. http://dx.doi.org/10.4324/9781315712437-4.

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Chappell, David. "Design." In Construction Contracts, 90–102. Fourth edition. | Abingdon, Oxon; New York: Routledge, 2021.: Routledge, 2020. http://dx.doi.org/10.1201/9781003080930-10.

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Chappell, David. "Design." In Construction Contracts, 90–102. Fourth edition. | Abingdon, Oxon; New York: Routledge, 2021.: Routledge, 2020. http://dx.doi.org/10.4324/9781003080930-10.

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Beadnall, Stuart, and Simon Moore. "Design risk." In Offshore Construction, 47–72. 2nd ed. London: Informa Law from Routledge, 2021. http://dx.doi.org/10.4324/9780367855574-3.

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Mosley, W. H., J. H. Bungey, and R. Hulse. "Composite construction." In Reinforced Concrete Design, 350–73. London: Macmillan Education UK, 1999. http://dx.doi.org/10.1007/978-1-349-14911-7_13.

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McLean, Will, and Pete Silver. "Construction Technology." In Environmental Design Sourcebook, 66–97. London: RIBA Publishing, 2021. http://dx.doi.org/10.4324/9781003189046-3.

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Houben, Hugo, and Hubert Guillard. "10. Design Guidelines." In Earth Construction, 244–303. Rugby, Warwickshire, United Kingdom: Practical Action Publishing, 1989. http://dx.doi.org/10.3362/9781780444826.010.

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Soutsos, Marios, and Peter Domone. "Concrete mix design." In Construction Materials, 249–58. Fifth edition. | Boca Raton : CRC Press, [2017]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315164595-25.

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Dodd, Graham. "Design and applications." In Construction Materials, 453–58. Fifth edition. | Boca Raton : CRC Press, [2017]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315164595-45.

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Delligatti, T. M. "Preparing for Construction." In Costume Design, 88–120. New York, NY : Routledge, 2021. | Series: The basics: Routledge, 2020. http://dx.doi.org/10.4324/9780429354304-5.

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Тези доповідей конференцій з теми "Avionics Design and construction"

1

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

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

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Uhlig, Daniel, Keerti Bhamidipati, and Natasha Neogi. "Safety and Reliability Within UAV Construction." In 2006 ieee/aiaa 25TH Digital Avionics Systems Conference. IEEE, 2006. http://dx.doi.org/10.1109/dasc.2006.313736.

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Jordan, Anthony F. "MIL-STD-1553 Remote Terminal Design Using ASIC Megacell Technology." In Avionics Systems. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1993. http://dx.doi.org/10.4271/931592.

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MORRISON, R., and JONATHON SIMMONS. "Modern avionics connector unreliability." In Aircraft Design and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2099.

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Wray, Richard B., and John R. Stovall. "The Space Avionics Architecture Standard Tailored to the Common Lunar Lander Conceptual Design." In Avionics Systems. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1993. http://dx.doi.org/10.4271/931599.

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Lindsley, Michelle LaBrosse. "Vibration Design Criteria for Avionics." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1987. http://dx.doi.org/10.4271/871768.

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Manyak, Greg, and John M. Bellardo. "PolySat's Next Generation Avionics Design." In 2011 IEEE International Conference on Space Mission Challenges for Information Technology (SMC-IT). IEEE, 2011. http://dx.doi.org/10.1109/smc-it.2011.13.

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SVENSSON, C. "A structured approach to system design." In Digital Avionics Systems Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-3867.

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DOHERTY, RICHARD, DAVID JOHANNSEN, ROBERT ERICKSON, and MATT ROHM. "Optimized VHSIC design using advanced silicon compilation." In Digital Avionics Systems Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-4034.

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Звіти організацій з теми "Avionics Design and construction"

1

Allen, Bradley R., Eric Ruhl, Bryce Fowler, and Dino Sciulli. Advanced Isolation Design for Avionics on Launch Vehicles. Fort Belvoir, VA: Defense Technical Information Center, March 2000. http://dx.doi.org/10.21236/ada451652.

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CORPS OF ENGINEERS WASHINGTON DC. Construction: Design and Construction Evaluation (DCE). Fort Belvoir, VA: Defense Technical Information Center, February 1996. http://dx.doi.org/10.21236/ada404141.

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Chouikha, Mohamed F. Test Generation for Very High-Level Design Language (VHDL) Specifications Used in Avionics. Fort Belvoir, VA: Defense Technical Information Center, August 2002. http://dx.doi.org/10.21236/ada416255.

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Slocum, Alexander H., Laura A. Demsetz, David H. Levy, and Bruce Schena. Design Methodology for Automated Construction Machines. Fort Belvoir, VA: Defense Technical Information Center, December 1987. http://dx.doi.org/10.21236/ada207386.

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Fanella, David A., Amaldo T. Derecho, and S. K. Ghosh. Design and construction of structural systems. Gaithersburg, MD: National Institute of Standards and Technology, 2005. http://dx.doi.org/10.6028/nist.ncstar.1-1av1.

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Collins, James J. Design and Construction of Genetic Applets. Fort Belvoir, VA: Defense Technical Information Center, May 2003. http://dx.doi.org/10.21236/ada417910.

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Jackson, J. G. Y-12 Sustainable Design Principles for Building Design and Construction. Office of Scientific and Technical Information (OSTI), November 2008. http://dx.doi.org/10.2172/969028.

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CORPS OF ENGINEERS WASHINGTON DC. Engineering and Design. Construction with Large Stone. Fort Belvoir, VA: Defense Technical Information Center, October 1990. http://dx.doi.org/10.21236/ada402849.

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McNeese, L. E. ORNL engineering design and construction reengineering report. Office of Scientific and Technical Information (OSTI), January 1998. http://dx.doi.org/10.2172/631227.

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Janet E.R. Mcllvaine, David Beal, and Philip Fairey. INTERIOR DUCT SYSTEM DESIGN, CONSTRUCTION, AND PERFORMANCE. Office of Scientific and Technical Information (OSTI), October 2001. http://dx.doi.org/10.2172/823970.

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