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Dissertations / Theses on the topic 'Aircraft structure'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Svalstedt, Mats, and Sofia Swedberg. "Commercial Aircraft Wing Structure : - Design of a Carbon Fiber Composite Structure." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-276702.

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This project explores the classical wing structure of an commercial aircraft for an all carbon fiber reinforced polymer unmanned aerial vehicle(UAV). It is part of a collaborative work consisting of several groups researching different parts of the aircraft. The objective of this report is to present the design of the inner wing structure for a greener, more efficient scaled 2:1 version of the Skywalker X8. In order to make the aircraft as efficient as possible, the structure needs to be lightweight. The loads were first approximated using XFLR5 and a first design made. The design was then tes

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2

Eustace, Paul Alan. "Structural mass of innovative concept aircraft." Thesis, Loughborough University, 2001. https://dspace.lboro.ac.uk/2134/7361.

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3

Bingham, Christopher Malcolm. "Application of variable structure control methods to actuator nonlinearities in aerospace systems." Thesis, Cranfield University, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.358823.

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4

Spurgeon, S. K. "An assessment of robustness of flight control systems based on variable structure techniques." Thesis, University of York, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.383881.

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5

Dalton, Roger Patrick. "Propagation of LAMB waves in metallic aircraft fuselage structure." Thesis, Imperial College London, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.392345.

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6

Faddy, James Malcolm Pullin Dale Ian. "Flow structure in a model of aircraft trailing vortices /." Diss., Pasadena, Calif. : California Institute of Technology, 2005. http://resolver.caltech.edu/CaltechETD:etd-05272005-163801.

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7

Reytier, Thomas. "Modelling fatigue spectra of aircraft structure under gust loads." Toulouse 3, 2012. http://thesesups.ups-tlse.fr/1614/.

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Cette thèse est consacrée à l'analyse de fatigue et de tolérance aux dommages des structures d'avions soumis aux rafales de vent. L'analyse de fatigue et de tolérance aux dommages est un enjeu essentiel dans la conception des structures d'avions. Elle permet de définir un programme d'inspection de la structure afin d'assurer sa sécurité tout au long de la vie de l'avion. La première partie passe en revue l'état de l'art dans les différents domaines impliqués dans le processus global d'analyse de fatigue des structures d'avions soumis aux rafales de vent: la modélisation de la turbulence atmosp

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8

Sonelius, Ulrika. "FISST - Fully Integrated Shell Structure : OPTIMIZATION OF AN AIRCRAFT FUSELAGE." Thesis, KTH, Lättkonstruktioner, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-164286.

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In order to reduce the costs of aircraft, the weight of the fuselage has to be reduced. This master thesis, collaboration between the Royal Institute of Technology and Airbus Group, aims to optimize a new aircraft fuselage under development. This new fuselage design, called FISST, consists of a sandwich panel to stiffen the structure instead of the stringers used in baseline fuselage. Apart from the goal of reducing the weight, the new design also has advantages during maintenance and repairing. During this project the FISST-concept has been optimized, by modeling using the Finite Element Meth

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9

Goksel, Lorens Sarim. "Fatigue and damage tolerance assessment of aircraft structure under uncertainty." Thesis, Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/49124.

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This thesis presents a new modeling framework and application methodology for the study of aircraft structures. The framework provides a ‘cradle-to-grave’ approach to structural analysis of a component, where structural integrity encompasses all phases of its lifespan. The methodology examines the holistic structural design of aircraft components by integrating fatigue and damage tolerance methodologies. It accomplishes this by marrying the load inputs from a fatigue analysis for new design, into a risk analysis for an existing design. The risk analysis incorporates the variability found from

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10

Bigand, Audrey. "Damage assessment on aircraft composite structure due to lightning constraints." Thesis, Toulouse, ISAE, 2020. http://www.theses.fr/2020ESAE0027.

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L’utilisation des matériaux composites dans l’industrie aéronautique s’étant largement étendue, ledimensionnement de ces structures et de leur protection vis-à-vis de la foudre est devenu un enjeu majeur. Ilest important de pouvoir développer des outils prédictifs permettant d’obtenir une conception de structurerépondant aux critères de certification avec des temps et coûts de conception maitrisés. L’interaction de lafoudre avec une structure composite est un phénomène multiphysique complexe, avec une difficulté ajoutéepar la présence d’une protection métallique en surface et d’une couche de p

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Mahdi, Stephane. "The performance of bonded repairs to composite structures." Thesis, Imperial College London, 2001. http://hdl.handle.net/10044/1/7815.

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12

Mills, Austin Shelley. "The Structural Suitability of Tensegrity Aircraft Wings." University of Dayton / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1590172090108379.

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13

Mosinyi, Bao Rasebolai Awerbuch Jonathan Lau Alan C. W. Tan Tein-Min. "Fatigue damage assessment of high-usage in-service aircraft fuselage structure /." Philadelphia, Pa. : Drexel University, 2007. http://hdl.handle.net/1860/2762.

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14

Huang, Haidong. "Optimal design of a flying-wing aircraft inner wing structure configuration." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7439.

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Flying-wing aircraft are considered to have great advantages and potentials in aerodynamic performance and weight saving. However, they also have many challenges in design. One of the biggest challenges is the structural design of the inner wing (fuselage). Unlike the conventional fuselage of a tube configuration, the flying-wing aircraft inner wing cross section is limited to a noncircular shape, which is not structurally efficient to resist the internal pressure load. In order to solve this problem, a number of configurations have been proposed by other designers such as Multi Bubble Fuselag

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15

Satterwhite, Matthew Ryan. "Development and Validation of Fluid-Structure Interaction in Aircraft Crashworthiness Studies." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/51559.

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Current Federal Aviation Regulations require costly and time consuming crashworthiness testing to certify aircraft. These tests are only capable of a limited assessment of progressive damage and all crash configurations and scenarios cannot be physically evaluated. Advancements in technology have led to accurate and effective developments in numerical modeling that have the possibility of replacing these rigorous physical experiments. Through finite element analysis, an in-depth investigation of an aircraft equipped with a fabricated composite undercarriage was evaluated during water ditching.

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16

Knöös, Franzén Ludvig, and Erik Magnusson. "Weight Penalty Methods for Conceptual Aircraft Design." Thesis, Linköpings universitet, Fluida och mekatroniska system, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-175012.

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This report addresses a project conducted at Saab Aeronautics during the spring of 2018. The goal of the project was to investigate aircraft weight estimations in the conceptual design phase. The work was divided into two major parts: finding new weight estimation techniques and implementing an existing technique called the Berry Weight Estimation in to the Pacelab APD software. Several weight estimation techniques were found during an extensive literature review but in the end, only one was chosen for further investigation. The chosen technique was the NASA Wing Weight Build-Up which proposed

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17

Foister, Steven A. M. "The interaction of ultrasound with the material structure of titanium alloys." Thesis, University of Surrey, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.301330.

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18

Bail, Justin L. "Non-desctructive investigation & FEA correlation on an aircraft sandwich composite structure." Akron, OH : University of Akron, 2007. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=akron1196702586.

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Thesis (M.S.)--University of Akron, Dept. of Civil Engineering, 2007.<br>"December, 2007." Title from electronic thesis title page (viewed 02/25/2008) Advisor, Wieslaw Binienda; Faculty readers, Craig Menzemer, Robert Goldbert; Department Chair, Wieslaw Binienda; Dean of the College, George K. Haritos; Dean of the Graduate School, George R. Newkome. Includes bibliographical references.

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Bail, Justin. "Non-Destructive Investigation & FEA Correlation on an Aircraft Sandwich Composite STructure." University of Akron / OhioLINK, 2007. http://rave.ohiolink.edu/etdc/view?acc_num=akron1196702586.

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20

Farao, Javon. "Toward a full aircraft model platform for fuel slosh-structure interaction simulations." Master's thesis, University of Cape Town, 2015. http://hdl.handle.net/11427/24315.

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The purpose of this study was to initiate the development of a full aircraft model (FAM) for the purpose of non-linear loads calculation of an aircraft. The FAM is employed during the design process of an aircraft and comprises of various reduced-order models (ROMs). These are mainly structural, slosh and aerodynamic loads. This study focused on the structural and slosh aspects using Ele- mental(TM) software as the base. First, a structural ROM was developed such that it is compatible with Airbus data and processes. The developed code reads in MSC Nastran data, from which Hermitian finite elem

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21

Liu, Hongfen. "A structural design comparison of metallic and composite aircraft pressure retaining doors." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7308.

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The pressure retaining door is obviously a sensible part of an aircraft, and the design criteria is much more critical than for the fuselage, so a problem caused by this critical criteria is the heavy weight of the door structure because it should be strong enough to withstand loads and stiff enough to meet the sealing requirements. In spite of the pressure retaining door being so important, it is difficult to find design references. So, in this thesis, the pressure retaining door is investigated first, and then a typical structure of a type A door is selected as the study case using both meta

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22

Yalcin, Mehmet Efruz. "Design And Analysis Of An Equipment Rack Structure Of A Medium Transport Aircraft." Master's thesis, METU, 2009. http://etd.lib.metu.edu.tr/upload/12611123/index.pdf.

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In this study, equipment rack structure for a medium transport aircraft was designed and finite element analysis of this design was performed. The equipment rack structure, which was designed for a modernization project, was positioned and dimensions were determined by regarding the geometry of primary structures of the aircraft. The structure was designed such that it satisfies the pre-defined margin of safety values. Design of the structure was prepared in Unigraphics, and the finite element modeling and analysis phases were carried out using MSC.Patran and MSC.Nastran programs. For the fast

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23

Crump, Duncan Andrew. "Performance analysis of a reduced cost manufacturing process for composite aircraft secondary structure." Thesis, University of Southampton, 2009. https://eprints.soton.ac.uk/142803/.

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In the current, environmentally-aware, climate aircraft designers are under increasing pressure to produce fuel efficient vehicles. Weight reduction is an important method for increasing fuel efficiency. Fibre reinforced polymer (FRP) composites are known to offer weight savings over traditional metallic components, due to their excellent stiffness and strength to weight ratios. However, the major limiting factor for the use of aerospace quality composites is the manufacturing cost. The costs incurred in the conventional process of prepreg cured in an autoclave are well documented. The researc

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24

Dove-Jay, Ashley. "Development, integration and testing of a 0-v honeycomb structure for aircraft morphing." Thesis, University of Bristol, 2015. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.690034.

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This thesis lays out the development, analysis, integration and testing of a camber morphing concept for control surfaces dealing with fluidic dynamics, with specific focus on replacing the outboard aileron of fixed-wing aircraft in an effort to increase associated fuel efficiency. Core to the development of the morphing concept was a zero Poisson's ratio (O-v) honeycomb. The state-of-the-art was studied, modified for compatibility with the application intended, was subjected to topological optimization to improve relevant performance charactelistics, and was validated through experimental stu

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25

Ma, Leong. "Crack link up and residual strength of aircraft structure containing multiple site damage /." Thesis, Connect to this title online; UW restricted, 1999. http://hdl.handle.net/1773/7039.

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26

Masango, Thubalakhe Patrick. "Condition monitoring of a wing structure for an unmanned aerial vehicle (UAV)." Thesis, Cape Peninsula University of Technology, 2015. http://hdl.handle.net/20.500.11838/2384.

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Thesis (MTech (Mechanical Engineering))--Cape Peninsula University of Technology, 2015.<br>Currently non-destructive testing techniques for composite aircraft structures are disadvantaged when compared to online Structural Health Monitoring (SHM) systems that monitor the structure while in-service and give real time data. The present research work looks at developing a protocol for online structural health monitoring of a UAV wing structure using PVDF film sensors, especially including the monitoring of structural changes caused by defects. Different types of SHM techniques were studied in rel

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27

Sorenson, Daren S. "Preparing for the long war : transformation of UAVs in future force structure planning for close air support operations /." Norfolk, Va. : Joint Forces Staff College, Joint Advanced Warfighting School, 2006. http://handle.dtic.mil/100.2/ADA451217.

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Thesis (M.S. in Joint Campaign Planning and Strategy)--Joint Forces Staff College, Joint Advanced Warfighting School, 2006.<br>Vita. "National Defense Univ Norfolk VA"--DTIC cover. "14 April 2006." Includes bibliographical references (p. 58-61). Also available via the Internet.

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28

Backhouse, R. "Multiaxial non-crimp fabrics : characterisation of manufacturing capability for composite aircraft primary structure applications." Thesis, Cranfield University, 1998. http://dspace.lib.cranfield.ac.uk/handle/1826/1929.

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Carbon composite reinforcement fabrics aimed at flight critical aircraft structure application were designed and the capability of the process used to manufacture them examined. Studies of the LIBA multiaxial non-crimp fabric manufacturing process focused on the effect of changes to four manufacturing parameters using an experimental design process to design the fabrics and analyse the results. The composite properties measured included microstructural features of the fibre tows and resin distribution, and mechanical performance both in-plane and their damage resistance and tolerance character

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29

Doucet, Jeremy. "Fatigue life enhancement of aircraft structures through bonded crack retarders (BCR)." Thesis, Cranfield University, 2015. http://dspace.lib.cranfield.ac.uk/handle/1826/11279.

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The trend in aircraft design is to produce greener airplanes through lighter structures and/or structures with extended life and reduced maintenance. Bonded crack retarders (BCR) are one of the solutions towards that objective. BCR are reinforcing straps bonded to the structure in order to improve the fatigue and damage tolerance properties of the assembly. The aim of this study was to demonstrate that the BCR hybrid technology – beneficial for upper wing cover – could also be applied to lower wing covers. The project also focused on evaluating BCR most important parameters. The fatigue life i

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Che, Yunxiang, and S3145469@student rmit edu au. "Aging structure life prediction and reliability assessment." RMIT University. SAMME, 2008. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20091113.114541.

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Confront with the serious aging problem in aircraft structure field, the profession was tasked to unveil the mysterious in the mechanism of aging. In decades, many endeavours were put into different subjects such as, fatigue and crack calculation, corrosion analysis, reliability evaluation, life prediction, structure monitor and protection, structure repair, etc. In an effort of developing a reasonable model for life prediction and reliability evaluation, a wide range of topics in the field of aging structure reliability are reviewed. Many existing methods and tools are carefully studied

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31

Rosenwasser, Jon Jason. "Governance structure and weapon innovation : the case of unmanned aerial vehicles /." Thesis, Connect to Dissertations & Theses @ Tufts University, 2004.

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Thesis (Ph.D.)--Tufts University, 2004.<br>Adviser: Robert L. Pfaltzgraff, Jr. Submitted to the Fletcher School of Law and Diplomacy. Includes bibliographical references (leaves 421-445). Access restricted to members of the Tufts University community. Also available via the World Wide Web;

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Xu, Rongxin. "Optimal design of a composite wing structure for a flying-wing aircraft subject to multi-constraint." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7290.

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This thesis presents a research project and results of design and optimization of a composite wing structure for a large aircraft in flying wing configuration. The design process started from conceptual design and preliminary design, which includes initial sizing and stressing followed by numerical modelling and analysis of the wing structure. The research was then focused on the minimum weight optimization of the /composite wing structure /subject to multiple design /constraints. The modelling, analysis and optimization process has been performed by using the NASTRAN code. The methodology and

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33

Grun, Eli (Eli Paul). "An application of design structure matrix methods to explore process improvements in aircraft fight line operations." Thesis, Massachusetts Institute of Technology, 2016. http://hdl.handle.net/1721.1/106246.

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Thesis: S.M. in Engineering and Management, Massachusetts Institute of Technology, School of Engineering, System Design and Management Program, Engineering and Management Program, 2016.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 45-47).<br>The complexities around building, testing, and flying aircraft span many different domains. Some of these domains include processes, people, and tools, of which affect the way work is performed on aircraft. In this thesis, communication tools and the organizations involved in troubleshooting and readying aircraft f

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34

Coleman, Robert Mark 1962. "The effects of design, manufacturing processes and operations management on the assembly of aircraft composite structure." Thesis, Massachusetts Institute of Technology, 1991. http://hdl.handle.net/1721.1/42495.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1991 and Thesis (M.S.)--Sloan School of Management, 1991.<br>Includes bibliographical references (leaf 104).<br>by Robert Mark Coleman.<br>M.S.

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35

Pecorella, Daniele. "Methodology for the design and optimization of a morphing wing droop-nose structure for greener aircraft." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2022.

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Droop-Nose Leading Edge (DNLE) morphing wings are one of the most promising devices in order to achieve aerodynamic drag and noise reduction during take-off and landing phases. An accurate design of these structures could lead to the decrease of aircraft fuel consumption in the perspective of reaching a greener aviation, following the objectives indicated by Flightpath 2050 issued by the E.U. However, due to the challenges related to the realization of this technology and TRL reached, DNLE are more likely implemented in Unmanned Aerial Systems (UAS) for testing and evaluation purposes. In the

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36

Houglan, Gary D. "The impact of matrix structure and self-managed teams at the Naval Air Warfare Center, Aircraft Division, Indianapolis." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1993. http://handle.dtic.mil/100.2/ADA276937.

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Thesis (M.S. in Management) Naval Postgraduate School, December 1993.<br>Thesis advisor(s): Susan P. Hocevar ; Gail Fann Thomas ; Frank J. Barrett. "December 1993." Bibliography: p. 122-125. Also available online.

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37

Ančík, Zdeněk. "Mechatronic Design and Verification of Autonomic Thermoelectric Energy Source for Aircraft Application." Doctoral thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2016. http://www.nusl.cz/ntk/nusl-234600.

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Předložená disertační práce řeší komplexní mechatronický návrh autonomního termoelektrického zdroje energie pro letecké aplikace. Na základě dostupných zdrojů a literatury práce popisuje současný stav problematiky. V práci jsou prezentovány simulační modely MEMS termoelektrických článků, které jsou ověřeny experimentálním testováním a hodnotami dostupnými od výrobce. Na základě metodiky model-besed design byly navrženy a vyrobeny tři demonstrátory. Jejich vlastnosti byly testovány v reálných podmínkách na letecké pohonné jednotce.

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38

Marengo, Giovanni. "The use of unidirectional carbon fibre rods in high loaded joints for a composite large civil aircraft wing structure." Thesis, Cranfield University, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.393700.

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39

Muller, Yannick. "Coupled thermomechanical fluid-structure interaction in the secondary air system of aircraft engines : contribution to an integrated design method." Valenciennes, 2009. http://ged.univ-valenciennes.fr/nuxeo/site/esupversions/94032a6b-3a17-4aaf-b07a-ce560f117b33.

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Dans un turboréacteur, le système d'air secondaire remplit de multiples fonctions. Les flux d'air secondaire contrôlent les températures des matériaux et l'expansion thermale des parties moteurs, en particulier les écartements des joints d'étanchéité. Pour s'assurer de la réalisation des diverses fonctions dès la phase de développement, les différentes propriétés du gaz doivent être correctement prédîtes. Actuellement, les calculs aérodynamiques, livrant les flux les températures et les pressions d'air, sont séparés des calculs thermiques, livrant les températures matériaux. Les interactions d

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Rahn, David. "Forcing and structure of the 22-25 June 2006 coastally trapped wind reversal using aircraft observations and numerical simulations." Laramie, Wyo. : University of Wyoming, 2008. http://proquest.umi.com/pqdweb?did=1799961831&sid=1&Fmt=2&clientId=18949&RQT=309&VName=PQD.

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Yousfi, Fayin. "Multistatic ISAR imaging : image formation, structure analysis and motion estimation." Electronic Thesis or Diss., université Paris-Saclay, 2025. http://www.theses.fr/2025UPASG014.

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L'imagerie ISAR (Inverse Synthetic Aperture Radar) monostatique fournit des images haute résolution d'objets en utilisant leur mouvement relatif par rapport à un radar. Ces images peuvent être utilisées pour des tâches d'identification et de classification. L'ajout de récepteurs bistatiques distants peut compléter l'imagerie monostatique en fournissant des géométries d'observation différentes. Cette thèse utilise la diversité d'images fournie par des configuration ISAR multistatiques dans le but d'obtenir des informations sur la structure et le mouvement de rotation d'avions et de satellites.

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42

D'Ermilio, Jessica. "Laser shock peening treatment to control and moderate fatigue crack growth in aircraft structure based on residual stress engineering approach." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2014. http://amslaurea.unibo.it/6865/.

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Laser Shock Peening (LSP) is a surface enhancement treatment which induces a significant layer of beneficial compressive residual stresses of up to several mm underneath the surface of metal components in order to improve the detrimental effects of the crack growth behavior rate in it. The aim of this thesis is to predict the crack growth behavior in metallic specimens with one or more stripes which define the compressive residual stress area induced by the Laser Shock Peening treatment. The process was applied as crack retardation stripes perpendicular to the crack propagation direction with

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43

Lemmens, Yves Claude Jean. "Modelling and analysis of engineering changes in complex systems." Thesis, Cranfield University, 2007. http://dspace.lib.cranfield.ac.uk/handle/1826/5071.

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Complex products are comprised of a large number of tightly integrated components, assemblies and systems resulting in extensive logical and physical interdependences between the constituent parts. Thus a change to one item of a system is highly likely to lead to a change to another item, which in turn can propagate further. The aim of this research therefore is to investigate dependency models that can be used to identify the impact and trace thepropagation of changes in different information domains, such as requirements, physical product architecture or organisation. Cont/d.

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44

Syamsudin, Hendri. "Development of an approach and tool to improve the conceptual design process of the wing box structure of low-subsonic transport aircraft." Thesis, Cranfield University, 2009. http://hdl.handle.net/1826/4418.

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To produce a better airframe design, it is imperative to investigate the problems of design and manufacturing integration early on at the conceptual design stage. A new design approach and support tool is required which will aid the designer in future product development. This is a particular necessity in the current context of increasing complexity and challenging economic situations. The present work focuses on the development of a design approach and design aids for designing metallic wingbox structures of low-subsonic transport aircraft with small wing sweepback angles. Its aims are two-fo

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Cilliers, M. E. "Investigation of an aeroelastic model for a generic wing structure." Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/80317.

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Thesis (MScEng)--Stellenbosch University, 2013.<br>ENGLISH ABSTRACT: Computational Aeroelasticity is a complex research field which combines structural and aerodynamic analyses to describe a vehicle in flight. This thesis investigates the feasibility of including such an analysis in the development of control systems for unmanned aerial vehicles within the Electronic Systems Laboratory at the Department of Electrical and Electronic Engineering at Stellenbosch University. This is done through the development of a structural analysis algorithm using the Finite Element Method, an aerodynami

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Blanc, Maximin. "Optimisation d’une structure de conversion DC/DC réversible pour application aéronautique de forte puissance." Thesis, Université Grenoble Alpes (ComUE), 2017. http://www.theses.fr/2017GREAT115.

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Le véhicule aérien a connu de nombreuses révolutions durant les dernières décennies afin d’être plus économe en énergie et plus respectueux de l’environnement. Dans cet objectif, l’électricité est apparue comme le vecteur énergétique le plus adapté associé aux sources conventionnelles d’énergie. C’est dans ce contexte que nos recherches se sont portées sur ce mode de transport qui va voir des bouleversements structurels importants et de plus en plus d’équipements électriques installés à bord. Ce travail de recherche s’intéresse à une brique de conversion DC/DC nécessaire au transfert d’énergie

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Horner, Michael S. "Determining the fine structure of the entrainment zone in cloud-topped boundary layers." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2005. http://library.nps.navy.mil/uhtbin/hyperion/05Mar%5FHorner.pdf.

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Fortunet, 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.

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Actuellement, le marché aéronautique est en constante augmentation. Pour faire face à cela, les avionneurs doivent se restructurer et revoir les processus de fabrication des pièces. En effet, il est nécessaire d’augmenter les cadences et réduire les prix tout en conservant les performances des pièces (poids et résistance mécanique). Cependant, ces trois objectifs sont contradictoires et un compromis est difficile à trouver. Ces travaux de thèse abordent cette problématique dans le cadre du CORAC. Ils proposent une manière originale d’optimiser une pièce de structure aéronautique qui vise à dév

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Carlsson, Martin. "Design and Testing of Flexible Aircraft Structures." Doctoral thesis, KTH, Aeronautical and Vehicle Engineering, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3761.

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<p>Methods for structural design, control, and testing offlexible aircraft structures are considered. Focus is onnonconventional aircraft con- figurations and control concepts.The interaction between analysis and testing is a central topicand all studies include validation testing and comparisonbetween computational and experimental results.</p><p>The first part of the thesis is concerned with the designand testing of an aeroelastic wind-tunnel model representing aBlended Wing Body (BWB) aircraft. The investigations show thata somewhat simplified wind-tunnel model design concept isuseful and e

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Freeman, Michael James. "The Integration of Iterative Convergent Photogrammetric Models and UAV View and Path Planning Algorithms into the Aerial Inspection Practices in Areas with Aerial Hazards." BYU ScholarsArchive, 2020. https://scholarsarchive.byu.edu/etd/8738.

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Small unmanned aerial vehicles (sUAV) can produce valuable data for inspections, topography, mapping, and 3D modeling of structures. Used by multiple industries, sUAV can help inspect and study geographic and structural sites. Typically, the sUAV and camera specifications require optimal conditions with known geography and fly pre-determined flight paths. However, if the environment changes, new undetectable aerial hazards may intersect new flight paths. This makes it difficult to construct autonomous flight path missions that are safe in post-hazard areas where the flight paths are based on p

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