Дисертації з теми "Avionics Design and construction"
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Byrne, James Michael Jr. "Resource-constrained avionics design for CubeSats." Thesis, Massachusetts Institute of Technology, 2016. http://hdl.handle.net/1721.1/105559.
Повний текст джерелаThis 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.
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.
Повний текст джерелаTörnblom, 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.
Повний текст джерелаKahn, Aaron David. "The design and development of a modular avionics system." Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/15712.
Повний текст джерелаVetter, 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.
Повний текст джерелаOmelchenko, 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.
Повний текст джерела"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.
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.
Повний текст джерелаGia, M. C. "Design of data structures for terrain reference navigation." Thesis, Cranfield University, 1994. http://hdl.handle.net/1826/4184.
Повний текст джерелаBa, 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.
Повний текст джерелаThe 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.
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.
Повний текст джерелаGonzalez, Gallego Oscar. "Dimensionnement et contrôlabilité de configurations avion innovantes." Toulouse 3, 2013. http://www.theses.fr/2013TOU30340.
Повний текст джерелаThe current aircraft design process focuses on Performance optimization (minimize the airframe drag, reduce noise levels, maximize Range, reduce pollutant emissions, etc. ) and treats all other disciplines sequentially and as design constraints. Among the constraint disciplines, Stability & Control is the most important one, although not always recognized as such. Indeed, in addition to being responsible for equipping the airframe with stabilizers and controls that ensure the proper handling of the vehicle, Stability & Control is strongly tied to Performance, safety, and aircraft certification aspects. In the earliest aircraft design stage (Conceptual Design phase), the Stability & Control discipline is only partially considered and consists of little more than statistical relationships (volume coefficients) and static analyses (Scissors Plot). It is not until later in the aircraft development process (Detailed Design phase and flight tests), that the Stability & Control discipline plays a dominant role and where the airplane design choices made at the conceptual level are validated or not. Although this traditional design procedure proved to be "successful" when sizing the stabilizers and controls of typical airplanes (wing + tubular fuselage + rear empennage), it fails when the aircraft layout under study deviates from the conventional one. Furthermore, the wide discrepancy between the rather sophisticated manner in which the Stability & Control discipline is considered in the Detailed Design phase, compared to the relatively simple approach used during the Conceptual Design level, results in "sub-optimal" airplane designs with stability and/or deficiencies that not only are expensive to fix, but can also be detrimental to the vehicle performance characteristics and jeopardize its safety. This research work introduces a generic, alternative, and fast aircraft conceptual design methodology capable of sizing and optimizing any aircraft configuration by giving further importance to the Stability & Control discipline. In this methodology, the sequential character of the current conceptual design process is replaced with a simultaneous and integrated Multi-Disciplinary Optimization (MDO) approach in which the discipline of Stability & Control, in particular, is considered at the same level as Performance. The proposed design procedure aims at deriving the airplane outer shape satisfying, among others, a set of generic (i. E. Independent of the aircraft configuration) stability and control requirements, while possessing the best operational performance throughout a typical mission profile. Compared to the traditional aircraft design methodology, the derived optimization problem is much more constrained from the Stability & Control perspective and considers not only static requirements, but also dynamic and maneuver criteria. The methodology resembles an "inverse" (or "reverse engineering") design process since the desired stability and control features of the airplane are imposed in advance as constraints of the optimization problem. The conceptual designer therefore seeks to determine the aircraft shape having specific handling characteristics. Integrating the Stability & Control discipline at conceptual level requires a modular and integrated tool, capable of performing MDO, that is not yet available within the civilian aviation industry. To counter this, a "simple" tool was created for partially mimicking the environment required. The methodology is illustrated with two different aircraft configurations of similar size. Although the work presented herein represents only a small fraction of the whole research challenge, the methodology is demonstrated to be viable and it is shown that further performance benefits can be extracted if the stability and control constraints are taken into account from the early design stages. This approach also enables to compare different aircraft configurations from a physical and rational basis and not on subjective and disparate opinions, as is currently the case
Sprague, Kara Lynn 1980. "Design and validation of an avionics system for a miniature acrobatic helicopter." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/87835.
Повний текст джерелаIncludes bibliographical references (leaves 53-54).
by Kara Lynn Sprague.
M.Eng.
Teng, Choon Hon Adrian. "Design and performance evaluation study of a prototype of a tactical unmanned aerial vehicle." Thesis, Monterey, Calif. : Naval Postgraduate School, 2007. http://bosun.nps.edu/uhtbin/hyperion-image.exe/07Dec%5FTeng.pdf.
Повний текст джерелаThesis Advisor(s): Jones, Kevin D. ; Dobrokhodov, Vladimir N. "December 2007." Description based on title screen as viewed on January 18, 2008. Includes bibliographical references (p. 97-98). Also available in print.
Andersson, Henric. "Aircraft Systems Modeling : Model Based Systems Engineering in Avionics Design and Aircraft Simulation." Licentiate thesis, Linköping University, Linköping University, Machine Design, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-17573.
Повний текст джерелаAircraft developers like other development and manufacturing companies, are experiencing increasing complexity in their products and growing competition in the global market. One way to confront the challenges is to make the development process more efficient and to shorten time to market for new products/variants by using design and development methods based on models. Model Based Systems Engineering (MBSE) is introduced to, in a structured way, support engineers with aids and rules in order to engineer systems in a new way.
In this thesis, model based strategies for aircraft and avionics development are studied. A background to avionics architectures and in particular Integrated Modular Avionics is described. The integrating discipline Systems Engineering, MBSE and applicable standards are also described. A survey on available and emerging modeling techniques and tools, such as Hosted Simulation, is presented and Modeling Domains are defined in order to analyze the engineering environment with all its vital parts to support an MBSE approach.
Time and money may be saved by using modeling techniques that enable understanding of the engineering problem, state-of-the-art analysis and team communication, with preserved or increased quality and sense of control. Dynamic simulation is an activity increasingly used in aerospace, for several reasons; to prove the product concept, to validate stated requirements, and to verify the final implementation. Simulation is also used for end-user training, with specialized training simulators, but with the same underlying models. As models grow in complexity, and the set of simulation platforms is expanded, new needs for specification, model building and configuration support arise, which requires a modeling framework to be efficient.
Goodwin, Thomas David. "An implementation study of an accounting system design for the Naval Avionics Center." Thesis, Monterey, California. Naval Postgraduate School, 1991. http://hdl.handle.net/10945/28275.
Повний текст джерелаGlas, Dylan F. (Dylan Fairchild) 1975. "Vehicle concept exploration and avionics architecture design for a fast package delivery system." Thesis, Massachusetts Institute of Technology, 2000. http://hdl.handle.net/1721.1/9253.
Повний текст джерелаAlso available online at the MIT Theses Online homepage
Includes bibliographical references (leaves 96-97).
Fast Package Delivery was explored as a possible commercial application of advanced reusable launch vehicle technologies. The market was divided into two distinct segments: an on-demand charter service for urgent deliveries, and a scheduled service similar to today's overnight delivery services. System reliability is a strong driver for both cases. For the on-demand case, vehicle speed is of critical importance. In order to provide on-demand service, only one customer may be served per vehicle flight. Since the price a customer will pay is highly sensitive to vehicle speed, the optimal vehicle concept was determined to be a Mach 6 hypersonic aircraft. Due to the small payload weight (200 lb) the overall vehicle size and cost are highly sensitive to equipment weight. Therefore substantial savings could be realized if the aircraft were unmanned. Flight operations would most likely be autonomous during cruise, but remotely piloted during launch and landing. Scheduled service, due to its much larger projected payload (6000 lb), is less sensitive to the weight of onboard equipment, and would not need to be unmanned. Packages from many customers would be carried at once, enabling lower prices to be charged to each customer. Lower prices mean that lower vehicle speeds would be acceptable to the customers, and so the optimal vehicle concept for scheduled service was found to be a Mach 2-3 supersonic transport. Unfortunately, due to the inherent unreliability of experimental technologies, Fast Package Delivery does not appear to be a feasible application at this time. However, once supersonic and reusable launch vehicle technologies begin to mature, Fast Package Delivery should be considered as a realistic business prospect. This paper presents the market analysis, system requirements development, vehicle concept selection, and avionics considerations for a Fast Package Delivery system.
by Dylan F. Glas.
M.Eng.
Perez, Alberto, John Hildin, and John Roach. "Design and Implementation of an Avionics Full Duplex Ethernet (A664) Data Acquisition System." International Foundation for Telemetering, 2008. http://hdl.handle.net/10150/606199.
Повний текст джерелаARINC 664 presents the designers of data acquisition systems challenges not previously seen on other aircraft avionic buses. Among the biggest challenges are providing the test instrumentation system with the capacity to process two redundant Ethernet segments that may be carrying packet traffic at near wire-line speed. To achieve this level of performance, the hardware and software must not only perform mundane operations, like time stamping and simple virtual link MAC filtering, but also need to implement core ARINC 664 functions like redundancy management and integrity checking. Furthermore, other TCP/IP operations, such as IP header checksum, must also be offloaded to the hardware in order to maintain real-time operation. This paper describes the implementation path followed by TTC during its development of an ARINC 664 network monitor used in a large commercial aircraft flight test program.
Tondreault, Jeremy P. (Jeremy Peter) 1973. "Improving the management of system development to produce more affordable military avionics systems." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/82698.
Повний текст джерелаThis electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
"February 2003."
Includes bibliographical references (p. 126-127).
by Jeremy P. Tondreault.
S.M.
Silva, Leon M. (Leon Manuel) 1968. "A partitioning methodology for helicopter avionics system with a focus on life cycle cost." Thesis, Massachusetts Institute of Technology, 2001. http://hdl.handle.net/1721.1/82690.
Повний текст джерелаThis electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
Includes bibliographical references (p. 111).
by Leon M. Silva.
S.M.
Vandeveld, Thierry F. R. "Etude expérimentale multisensorielle de la dynamique des impacts d'oiseaux sur structures d'avions." Doctoral thesis, Universite Libre de Bruxelles, 2009. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/210274.
Повний текст джерелаParmi les acteurs qui luttent contre ce danger, les constructeurs d'avions jouent un rôle prépondérant. Contraints par des réglementations internationales, ils s'attachent à produire des éléments de structure qui résistent à l'impact d'oiseaux.
Dans la mise au point de leur produits, les avionneurs démontrent cette résistance à l'aide d'essais d'impact :on accélère un simulant d'oiseau jusqu'à la vitesse voulue -- de l'ordre de la vitesse de croisière nominale de l'avion -- et on le projette sur un aileron ou un morceau de fuselage.
La présente thèse doctorale, co-dirigée par les professeurs Philippe Bouillard de l'ULB et Marc Pirlot de l'ERM, contribue doublement à l'amélioration de ces techniques d'essais dynamiques.
D'une part, elle réalise la mise au point et la validation d'un lanceur pyrotechnique à double étage pour l'accélération du simulant d'oiseau. Un canon de calibre 20 mm est combiné avec un accélérateur de calibre 160 mm. La combustion d'un mélange de poudre propulsive contenu dans une douille adaptée génère les gaz à haute température et à haute pression nécessaires à l'accélération d'un simulant d'oiseau dûment confiné dans un conteneur de protection. Un dispositif de séparation arrête le conteneur afin que seul le simulant d'oiseau percute l'élément d'avion à l'essai. La solution pyrotechnique à double étage mise au point est validée par de nombreux tirs instrumentés en vitesse, en accélération et en pression ;elle se révèle conforme aux exigences de sécurité et de reproductibilité. Le lanceur pyrotechnique présente par rapport aux solutions pneumatiques, utilisées à notre connaissance dans tous les autres centres d'essais, des avantages indéniables de compacité ainsi que de rapidité et de souplesse de mise en oeuvre.
D'autre part, la migration des alliages métalliques vers les matériaux composites est amorcée depuis plusieurs années déjà dans le monde de la construction aéronautique. Pour optimiser les structures, une connaissance des caractéristiques de ces matériaux est indispensable. Les modes de rupture font partie des caractéristiques encore mal connues. La mesure du déplacement hors-plan lors du tir sur panneaux plans est une des manières de quantifier le comportement du matériau sous l'action d'un impact. Cette mesure s'opère généralement de manière statique, après le tir. Une méthode de mesure dynamique a été mise au point, basée sur l'emploi de techniques de stéréoscopie par corrélation numérique d'images. Cette technique a été validée au moyen d'une méthode métrologique indépendante d'extensométrie laser.
ABSTRACT
Countless collisions occur each year between airplanes and birds. Bird strike is a concern to both civilian and militay aircraft. Statistics show that, although the number of serious accidents fortunately remains low, the number of incidents keeps increasing.
Amongst the actors tackling this issue, aircraft manufacturers play an important role. In compliance with international regulations, they have to produce structural elements that withstand bird impact. During the development of their products, aircraft manufacturers have to demonstrate this resistance through bird impact trials :a bird surrogate is accelerated to the required velocity - often close to the nominal cruise speed of the aircraft - and launched onto a flap or a piece of fuselage.
This PhD thesis has been co-supervised by Professor Philippe Bouillard (ULB) and Professor Marc Pirlot (ERM-KMS). Its contribution to the improvement of the aforementioned dynamic trials is twofold.
One one hand, a two-stage pyrotechnical launcher for bird surrogates has been developed and assessed. A 20 mm caliber gun is connected to a 160 mm diameter launcher. The combustion of a propellant mixture in a cartridge case generates high pressure, high temperature gases which accelerate a bird surrogate protected by a cylindrical container. A stripper refrains the container from hitting the target pane.
The pyrotechnical solution has been assessed through an important number of firings where pressure, velocity and acceleration have been measured. The solution has proven compliance with both the safety requirements and the repeatability specifications. Its advantages compared to the pneumatic solutions used, as far as we know, in all other test centres, include compactedness as well as flexibility and high firing rate.
On the other hand, migration towards composite materials has been initiated years ago in the area of aeronautical constructions.
To optimize structures, a thorough knowledge of these new materials is required. Failure modes belong to the still badly known features of carbon reinforced plastics. Measuring the out-of-plane deformation when firing on a flat pane is one way of quantifying the material's behaviour under impact. This measurement is most frequently made in a static way, after completion of the firing. A dynamic measuring method has been developed, based upon stereoscopic digital image correlation techniques. This technique has been validated by means of an independent laser extensometer measuring method.
Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished
Dittrich, Joerg S. "Design and integration of an unmanned aerial vehicle navigation system." Thesis, Georgia Institute of Technology, 2002. http://hdl.handle.net/1853/15669.
Повний текст джерелаWesterhoff, Kevin M. (Kevin Matthew) 1978. "Construction based design." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/84827.
Повний текст джерелаFortunet, Charles. "Une méthode d'optimisation multicritère pour le Design For Manufacturing : application aux portes d'avion." Thesis, Université Clermont Auvergne (2017-2020), 2017. http://www.theses.fr/2017CLFAC048.
Повний текст джерелаNowadays, the aeronautical market grows constantly. To face this, aircraft industry has to restructure and the manufacturing processes must be revised. Indeed, production rate must increase and manufacturing cost decrease while keeping the performances of the parts (weight and mechanical resistance). These objectives are contradictory and compromises must be found. This thesis broaches this problematic in relation to the CORAC. A novel method to optimize an aeronautical structural part and its manufacturing process is developed to tend toward performing compromise solutions. To do so, a three steps multi-criteria method is proposed. First, the industrial expertise is formalized to mathematically express the problem. Then, a genetic algorithm is used to determine a population in which every solution is located on a single Pareto front. At least, a decision step is set up to find the best solution in the population considering the industrial environment of the part. This methodology is applied to an aircraft door manufactured by forging and machining. In this case, it allows choosing the solution that fit the most the industrial environment within a one thousand solutions’ population
Fetter, Bryan J. "Design recovery and implementation of the AYK-14 VHSIC processor module adapter with field programmable gate array technology." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Dec%5FFetter.pdf.
Повний текст джерелаThesis advisor(s): Russell W. Duren, Hersch Loomis. Includes bibliographical references (p. 199). Also available online.
Reilly, Dennis J. "Unitary Joint Standoff Captive Air Training Missile avionics design through operational concepts and functional requirements analysis /." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1996. http://handle.dtic.mil/100.2/ADA309753.
Повний текст джерелаReilly, Dennis J. III. "Unitary Joint Standoff Captive Air Training Missile avionics design through operational concepts and functional requirements analysis." Thesis, Monterey, California. Naval Postgraduate School, 1996. http://hdl.handle.net/10945/9103.
Повний текст джерелаTo accurately simulate the Unitary Joint Standoff (JSOW) weapon functions and provide pilots with the most realistic training, the captive air training missile (CATM) avionics design will fully implement well defined operational concepts and functional requirements in terms of flight simulation characteristics, operational functions, pilot feedback, and electronic interfaces. This would provide the Navy, Marines, and Air Force with a single, multi-capable, light weight CATM that consolidates CATM procurement, decreases aircraft turnaround time and increases aircrew training per flight hour.
Urbain, Francois 1974. "Vehicle design, flight control avionics, and flight tests for the Parent and Child Unmanned Air Vehicle." Thesis, Massachusetts Institute of Technology, 2001. http://hdl.handle.net/1721.1/44900.
Повний текст джерелаIncludes bibliographical references (p. 115).
The Parent and Child Unmanned Aerial Vehicle (PCUAV) is the second project to originate from the MIT / Draper Technology Development Partnership, which aims to develop first-of-a-kind systems. The PCUAV proposes a low-cost solution to long distance closeup observation, using the cooperative action of a fleet of small UAVs. The project team will prove the potential of the system by demonstrating key enablers such as autonomous air rendezvous. This thesis presents the design of the project's vehicles, namely the Mini and Parent vehicles, and the Avionics Testbed Airplane. The avionics architecture is discussed including a detailed description of its components and their selection. The approach to obtain reliable estimates of aircraft attitude using low-cost gyroscopes is introduced. The planning and execution of several flight tests is presented.
by Francois Urbain.
S.M.
Berrian, Joshua. "AN AUTOMATED TEST STATION DESIGN USED TO VERIFY AIRCRAFT COMMUNICATION PROTOCOLS." DigitalCommons@CalPoly, 2011. https://digitalcommons.calpoly.edu/theses/635.
Повний текст джерелаXie, Xiaoling. "Communications in construction design." Thesis, Loughborough University, 2002. https://dspace.lboro.ac.uk/2134/7571.
Повний текст джерелаSoto, Leticia S. M. Massachusetts Institute of Technology. "Construction design as a process for flow : applying lean principles to construction design." Thesis, Massachusetts Institute of Technology, 2007. http://hdl.handle.net/1721.1/42995.
Повний текст джерелаIncludes bibliographical references (p. 108-111).
Delays and cost overruns are the rule rather than the exception in the construction industry. Design changes due to lack of constructability late in the construction phase generating costly ripple effect which create delay and disruption throughout the entire organization, are the largest contributors to the stated rule. In the building construction industry, of increased competitiveness, demand from many companies continued effort to develop new methods and tools, in which the design for quality, cost, construability and reliability play an important role. The planning and management of building design has historically focused upon traditional methods of planning such as Critical Path Method (CPM). Little effort is made to understand the complexities of the design process; instead design managers focus on allocating work packages where the planned output is a set of deliverables. This current design method forces design teams to manage their work on a discipline basis, each working on achieving their deliverable as dictated by the design program with little regard of the relationship with other disciplines and organizations. In addition, because Architect and Engineering firms view design and construction as two separate independent phases of work in project it makes it difficult to verify constructability in a design and create flow in the overall process. The goal of this study is to look at how aligning interests, objectives and practices based on lean fundamentals, during the earliest stages of a project, as a method of improving construction performance.
by Leticia Soto.
S.M.
Zeaiter, Amal. "Thermal Modeling and Cooling of Electric Motors : Application to the Propulsion of Hybrid Aircraft Thermal Sensitivity Analysis of a High Power Density Electric Motor for Aeronautical Application Numerical Approach to Determining Windings’ Thermal Conductivity Electro-thermal Models and Design Approach for High Specific Power Electric Motor for Hybrid Aircraft Determination of electric motor losses and critical temperatures through an inverse approach." Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2020. http://www.theses.fr/2020ESMA0015.
Повний текст джерелаThe concern of this thesis is the thermal modeling of high-specific power electric motors. The aim is to allow finding the efficient and adequate cooling solutions of the motors designed for hybrid aircraft propulsion application. Two specific power values, 5 kW/kg for the short-term (year 2025) and 10 kW/kg for the long-term (year 2035), are targeted, each with specific requirements. The investigated type of electric motors is the synchronous machine with surface-mounted permanent magnets. This motor type is constrained by relatively low values of maximum allowed temperatures in windings and magnets. Once reached, these temperature values lead to a failure in motor operation or at least to shortening its lifetime. Moreover, with a closed motor design and high heat fluxes generated, the optimization of the cooling is essential.To become acquainted with the issue, a detailed state of the art on electric machine cooling is elaborated. Then, the commonly used techniques and the recent technological advancements are analyzed with respect to our case study. Afterward, in order to predict motor thermal behavior and ensure the monitoring of critical temperatures (windings and magnets), a nodal transient model is implemented and solved on Matlab software. This latter is built for the whole system of the motor and cooling circuit. Specific conditions of the flight are taken into account, particularly the outside air temperature variation in terms of altitude and the flight mission profile. Actually, the motor losses, generating the heat in the machine, vary depending on the motor power during the mission. For the identification of crucial parameters, a Finite-Element study was conducted and corresponding correlations were elaborated to estimate the windings thermal conductivity through polynomial interpolation.Several studies were carried out involving the influence of the thermo-physical properties, the outside temperature, the coolant nature, its flow rate as well as the exchanger surface, on the temperature response of the model. This model has allowed studying several motor designs and proposing adequate cooling solutions. For each target, a final optimal configuration of the motor with its cooling system was adopted.Besides, since the electromagnetic and mechanical losses are hardly estimated in this machine type, a chapter was dedicated to identifying them through an inverse approach. A sequential technique, that uses Beck’s function specification for regularization, was developed. Three cases of unknown losses, with increasing complexity, were studied, proving the method's reliability. Finally, using the same developed low-order model, the real-time procedure also allows monitoring low-accessibility motor temperatures (specifically hot spots)
Cranley, Nikki. "The Implications for DAU Design in a Networked Data Acquisition System." International Foundation for Telemetering, 2011. http://hdl.handle.net/10150/595776.
Повний текст джерелаThe higher bandwidth capacities available with the adoption of Ethernet technology for networked FTI data acquisition systems enable more data to be acquired by the Data Acquisition Unit (DAU) from high-speed data busses, with higher channel densities, faster sampling rates, and sample resolution. Ethernet offers increased flexibility, interoperability, and simplicity in terms of the FTI system topology. However, the adoption of Ethernet has numerous implications for the design and operation of the DAU in terms of supporting network protocols for synchronization, configuration, and the transmission of the acquired data. This paper explores these issues and discusses the merits of adopting Ethernet.
Van, Wyk Robin. "Development of an integrated avionics hardware system for unmanned aerial vehicle research purposes." Thesis, Stellenbosch : University of Stellenbosch, 2011. http://hdl.handle.net/10019.1/6485.
Повний текст джерелаENGLISH ABSTRACT: The development of an integrated avionics system containing all the required sensors and actuators for autopilot control is presented. The thesis analyzes the requirements for the system and presents detailed hardware design. The architecture of the system is based on an FPGA which is tasked with interfacing with the sensors and actuators. The FPGA abstracts a microprocessor from these interface modules, allowing it to focus only on the control and user interface algorithms. Firmware design for the FPGA, as well as a conceptualization of the microprocessor software design is presented. Simulation results showing the functionality of firmware modules are presented.
AFRIKAANSE OPSOMMING: Die ontwikkeling van ‘n geïntegreede avionika‐stelsel wat al die vereiste sensors en aktueerders vir outoloods‐beheer bevat, word voorgestel. Die tesis analiseer die vereistes van die stelsel en stel ‘n hardeware‐ontwerp voor. Die argitektuur van die stelsel bevat ‘n FPGA wat ‘n koppelvlak met sensors en aktueerders skep. Die FPGA verwyder die mikroverwerker weg van hierdie koppelvlak modules en stel dit sodoende in staat om slegs op die beheer en gebruikerskoppelvlak‐algoritmes te fokus. Sagteware‐ontwerp vir die FPGA, asook die konseptualisering van die sagtewareontwerp vir die mikroverwerker, word aangebied. Simulasie resultate wat die funksionaliteit van die FPGA‐sagteware modules aandui, word ook voorgestel.
Sebille, Michel. "Design :construction, automorphisms and colourings." Doctoral thesis, Universite Libre de Bruxelles, 2002. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/211428.
Повний текст джерелаChew, En Phin. "Superconducting Transformer Design and Construction." Thesis, University of Canterbury. Electrical and Computer Engineering, 2010. http://hdl.handle.net/10092/4977.
Повний текст джерелаLeung, Chi-ming. "Design consultancy vs design and build consultancy : present trends in the construction industry /." Hong Kong : University of Hong Kong, 1995. http://sunzi.lib.hku.hk/hkuto/record.jsp?B14038869.
Повний текст джерелаAchard, Timothée. "Techniques de calcul de gradient aéro-structure haute-fidélité pour l'optimisation de voilures flexibles." Thesis, Paris, CNAM, 2017. http://www.theses.fr/2017CNAM1140/document.
Повний текст джерелаTo improve the structural design of flexible wings, gradient based Multidisciplinary Design Optimization (MDO) techniques are effective and widely used. However, gradients calculation is not trivial and can be costly when high-fidelity models are considered. Our objective is to study different suitable approaches to compute gradients of aeroelastic loads with respect to structural design parameters.To this end, two high-fidelity aero-structure gradient computation techniques for strongly coupled aeroelastic systems are proposed. The most intrusive technique includes the well-established direct and adjoint formulations that require substantial implementation effort. In contrast, we propose an alternative uncoupled non-intrusive approach easier to implement and yet capable of providing accurate gradients approximations. Both techniques have been implemented in the Onera elsA CFD software.Accuracy, efficiency and applicability of these methods are demonstrated on the civil transport aircraft Common Research Model (CRM) test-case. More specifically, an inverse design problem is set up with the objective of matching an in-flight target twist law distribution. These two methods prove to be comparable in terms of accuracy and cost. Thus they offer additional operational flexibility depending on the level of integration sought in the MDO process
Ferguson, A. J. L. "Dilution refrigerator : Design, construction and performance." Thesis, University of Ulster, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.378638.
Повний текст джерелаBatzer, Rachel E. (Rachel Elizabeth). "Design and construction of a dynamometer." Thesis, Massachusetts Institute of Technology, 2011. http://hdl.handle.net/1721.1/68827.
Повний текст джерела"June 2011." Cataloged from PDF version of thesis.
Includes bibliographical references (p. 20).
Access to a dynamometer is a useful tool for any electrical system where the motors must be selected from various suppliers and fully characterized. Motor suppliers usually provide a torque, speed, efficiency curve, but it frequently lacks complete motor characterization and includes motor controller losses in the total system loss. The dynamometer presented in this thesis is primarily designed for testing of high efficiency motors and motor controllers in the power and speed range requires for competition in the World Solar Challenge, a transcontinental race for solar electric vehicles. The testing specifications of a solar electric vehicles are uncommon among motor testing needs because it requires high torque, low power, high efficiency, and the only a small operating range. This thesis covers the design and construction of the dynamometer.
by Rachel E. Batzer.
S.B.
Bibby, Lee. "Improving design management techniques in construction." Thesis, Loughborough University, 2003. https://dspace.lboro.ac.uk/2134/793.
Повний текст джерелаJeffries, James R. "Construction implications of photolithography equipment design /." May be available electronically:, 2007. http://proquest.umi.com/login?COPT=REJTPTU1MTUmSU5UPTAmVkVSPTI=&clientId=12498.
Повний текст джерелаTisaj, David. "Design and construction of a tachometer." Thesis, Tisaj, David (2014) Design and construction of a tachometer. Other thesis, Murdoch University, 2014. https://researchrepository.murdoch.edu.au/id/eprint/25564/.
Повний текст джерелаAjayi, Saheed O. "Design, procurement and construction strategies for minimizing waste in construction projects." Thesis, University of the West of England, Bristol, 2017. http://eprints.uwe.ac.uk/30123/.
Повний текст джерелаSobron, Alejandro. "Design and Testing of a Flight Control System for Unstable Subscale Aircraft." Thesis, Linköpings universitet, Fluida och mekatroniska system, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-121819.
Повний текст джерелаPetras, James P. "Prefabrication and the Construction Industry: An Examination of Design, Construction, and Efficiency." University of Cincinnati / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1277120331.
Повний текст джерелаRoth, Fabian. "Explicit design, and adaptation in self-construction /." Zürich : ETH, 2007. http://e-collection.ethbib.ethz.ch/show?type=diss&nr=17005.
Повний текст джерелаRehnberg, Adam. "Suspension design for off-road construction machines." Doctoral thesis, KTH, Fordonsdynamik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-33883.
Повний текст джерелаQC 20110531
Law, Gordon Ki-Wai. "Decision support system for construction cycle design." Thesis, University of British Columbia, 1987. http://hdl.handle.net/2429/26715.
Повний текст джерелаApplied Science, Faculty of
Civil Engineering, Department of
Graduate
Morris, Jonathan. "Improving construction design : the lean thinking paradigm." Thesis, Cranfield University, 1999. http://dspace.lib.cranfield.ac.uk/handle/1826/3840.
Повний текст джерелаBrouqueyre, Laurent. "Hydro-acoustic therapy : design, construction and testing." Thesis, Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/18215.
Повний текст джерела