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Dissertations / Theses on the topic 'Flying wing'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Farrell, Joseph H. "DYNAMICALLY SCALED OBLIQUE FLYING WING." Thesis, The University of Arizona, 2009. http://hdl.handle.net/10150/192337.

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2

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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3

Saeed, Tariq Issam. "Conceptual design for a laminar-flying-wing aircraft." Thesis, University of Cambridge, 2012. https://www.repository.cam.ac.uk/handle/1810/243926.

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The laminar-flying-wing aircraft appears to be an attractive long-term prospect for reducing the environmental impact of commercial aviation. In assessing its potential, a relatively straightforward initial step is the conceptual design of a version with restricted sweep angle. Such a design is the topic of this thesis. In addition to boundary layer laminarisation (utilising distributed suction) and limited sweep, a standing-height passenger cabin and subcritical aerofoil flow are imposed as requirements. Subject to these constraints, this research aims to: provide insight into the parameters

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4

Levis, Errikos. "Design synthesis of advanced technology, flying wing seaplanes." Thesis, Imperial College London, 2012. http://hdl.handle.net/10044/1/9943.

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Over the past decades there has been increasing pressure for ever more efficient and environmentally friendly aircraft to be designed. The use of waterborne aircraft could be a means of satisfying those requirements in the future. The aim of the PhD research program presented in this thesis was to develop the methodologies necessary for the preliminary design of large passenger seaplanes and evaluate the performance of such an aircraft compared to the current state of the art. The major technological and operational constraints in designing large waterborne aircraft were identified through an

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5

Aguirre, John. "Study of 3-Dimensional Co-Flow Jet Airplane and High-Rise Building Flow Using CFD Simulation." Scholarly Repository, 2009. http://scholarlyrepository.miami.edu/oa_theses/181.

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The purpose of this thesis is to design and study an aircraft which implements the Co-Flow Jet (CFJ) airfoil concept, as well as to study the CAARC standard highrise building. The design concept is verified mainly by the use of a Computational Fluid Dynamics (CFD) package. A thorough methodology for geometry and mesh generation is developed, and subsequently applied to the two cases. The first case studied is that of the CFJ Airplane (CFJA). It consists of a threedimensional, highly blended, ying wing geometry implementing the Co-Flow Jet airfoil concept. Though a thorough comparison to a bas

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6

Zhu, Yan. "Longitudinal control laws design for a flying wing aircraft." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7423.

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This research is concerned with the flight dynamic, pitch flight control and flying qualities assessment for the reference BWB aircraft. It aims to develop the longitudinal control laws which could satisfy the flying and handing qualities over the whole flight envelope with added consideration of centre of gravity (CG) variation. In order to achieve this goal, both the longitudinal stability augmentation system (SAS) and autopilot control laws are studied in this thesis. Using the pole placement method, two sets of local Linear-Time-Invariant (LTI) SAS controllers are designed from the viewpoi

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7

Iglesias, Sergio. "Optimum Spanloads Incorporating Wing Structural Considerations And Formation Flying." Thesis, Virginia Tech, 2000. http://hdl.handle.net/10919/35718.

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The classic minimum induced drag spanload is not necessarily the best choice for an aircraft. For a single aircraft configuration, variations from the elliptic, minimum drag optimum load distribution can produce wing weight savings that result in airplane performance benefits. For a group of aircraft flying in formation, non-elliptic lift distributions can give high induced drag reductions both for the formation and for each airplane. <p> For single aircraft, a discrete vortex method which performs the calculations in the Trefftz plane has been used to calculate optimum spanloads for non-copl

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8

Geyman, Matthew Kenneth. "Wing/Wall Aerodynamic Interactions in Free Flying, Maneuvering MAVs." University of Dayton / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1335113432.

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9

Cheng, Yun. "Preliminary fuselage structural configuration of a flying-wing type airline." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7419.

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The flying-wing is a type of configuration which is a tailless airplane accommodating all of its parts within the outline of a single airfoil. Theoretically, it has the most aerodynamic efficiency. The fuel consumption can be more efficient than the existed conventional airliner. It seems that this configuration can achieve the above mentioned requirements. According to these outstanding advantages, many aircraft companies did a great deal of projects on the flying-wing concept. However, the application was only for sport and military use; for airliner, none of them entered production. FW-11 i

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10

Tonti, Jacopo. "Development of a Flight Dynamics Modelof a Flying Wing Configuration." Thesis, KTH, Aerodynamik, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-159873.

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The subject of UCAV design is an important topic nowadays and many countries have their own programmes. An international group, under the initiative of the NATO RTO AVT-201 Task group, titled “Extended Assessment of Reliable Stability & Control Prediction Methods for NATO Air Vehicles”, is currently performing intensive analysis on a generic UCAV configuration, named SACCON. In this thesis the stability and control characteristics of the SACCON are investigated, with the purpose of carrying out a comprehensive assessment of the flying qualities of the design. The study included the generat

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11

Ikeda, Toshihiro, and toshi ikeda@gmail com. "Aerodynamic Analysis of a Blended-Wing-Body Aircraft Configuration." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2006. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20070122.163030.

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In recent years unconventional aircraft configurations, such as Blended-Wing-Body (BWB) aircraft, are being investigated and researched with the aim to develop more efficient aircraft configurations, in particular for very large transport aircraft that are more efficient and environmentally-friendly. The BWB configuration designates an alternative aircraft configuration where the wing and fuselage are integrated which results essentially in a hybrid flying wing shape. The first example of a BWB design was researched at the Loughead Company in the United States of America in 1917. T

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12

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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13

Tsagarakis, Mikis. "Project Solaris - Analysis of airfoil for solar powered flying wing UAV." Thesis, Mälardalens högskola, Akademin för innovation, design och teknik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-13168.

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This study is part of the second phase of the Solaris project, where the aim is to develop a solar powered Unmanned Aerial Vehicle (UAV). The second phase involves the design and optimization of the aircraft. One of the important focuses in this phase is the determination of the airfoils shape. This report sole objective is to determine which airfoil that is best suited for the aircraft, as well as presenting the airfoils characteristic properties, in comparison to other similarly airfoils.This analysis has been carried out using XFOIL, an airfoil analysis tool developed by the MIT professor M

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14

McFarlane, Cormac. "An investigation of flying qualities for fixed wing unmanned aerial vehicles." Thesis, University of Bristol, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.508060.

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15

Fan, Xiaozhou. "Canonical Decomposition of Wing Kinematics for a Straight Flying Insectivorous Bat." Thesis, Virginia Tech, 2018. http://hdl.handle.net/10919/91469.

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Bats are some of the most agile flyers in nature. Their wings are highly articulated which affords them very fine control over shape and form. This thesis investigates the flight of Hipposideros Pratti. The flight pattern studied is nominally level and straight. Measured wing kinematics are used to describe the wing motion. It is shown that Proper Orthogonal Decomposition (POD) can be used to effectively to filter the measured kinematics to eliminate outliers which usually manifest as low energy higher POD modes, but which can impact the stability of aerodynamic simulations. Through aerodyna

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16

Mokrane, Adel. "Autonomous navigation of a rotary wing flying vehicles for precision agriculture." Electronic Thesis or Diss., université Paris-Saclay, 2023. http://www.theses.fr/2023UPAST200.

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Alors que les applications d'agriculture de préecision (AP) sont déjà bien établies pour les quadrirotors, la navigation autonome, en particulier dans les champs agricoles complexes, non structurés et capricieux, reste un défi permanent pour ces véhicules. Les stratégies de navigation aérienne autonome ne doivent pas se limiter à garantir que la cible est atteinte sans entrer en collision avec les obstacles. Elles doivent également viser à identifier le chemin et la trajectoire optimaux (ou sous-optimaux) que le quadrirotor doit utiliser pour déplacer de son point de départ à sa destination, e

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17

Miao, Zhisong. "Aircraft engine performance and integration in a flying wing aircraft conceptual design." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7249.

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The increasing demand of more economical and environmentally friendly aero engines leads to the proposal of a new concept – geared turbofan. In this thesis, the characteristics of this kind of engine and relevant considerations of integration on a flying wing aircraft were studied. The studies can be divided into four levels: GTF-11 engine modelling and performance simulation; aircraft performance calculation; nacelle design and aerodynamic performance evaluation; preliminary engine installation. Firstly, a geared concept engine model was constructed using TURBOMATCH software. Based on paramet

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18

Plumley, Ryan W. "Conceptual Assessment of an Oblique Flying Wing Aircraft Including Control and Trim Characteristics." Thesis, Virginia Tech, 2008. http://hdl.handle.net/10919/31417.

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A method was developed to assist with the understanding of a unique configuration and investigate some of its stability and control attributes. Oblique wing aircraft concepts are a design option that is well understood, but has yet to be used in a production aircraft. Risk involved in choosing such a design can be averted through additional knowledge early in the concept evaluation phase. Analysis tools commonly used in early conceptual level analysis were evaluated for applicability to a non-standard aircraft design such as an oblique flying wing. Many tools used in early analyses make assum

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19

Mardanpour, Pezhman. "Effects of engine placement and morphing on nonlinear aeroelastic behavior of flying wing aircraft." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50268.

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Effects of engine placement on flutter characteristics of a very flexible high-aspect-ratio wing are investigated using the code NATASHA (Nonlinear Aeroelastic Trim And Stability of HALE Aircraft). The analysis was validated against published results for divergence and flutter of swept wings and found to be in excellent agreement with the experimental results of the classical wing of Goland. Moreover, modal frequencies and damping obtained for the Goland wing were found in excellent agreement with published results based on a new continuum-based unsteady aerodynamic formulation. Gravity for th

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20

de, Castro Helena V. "Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft." Thesis, Cranfield University, 2003. http://hdl.handle.net/1826/119.

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The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of large transport aircraft. The idea of blending the wing with the fuselage and eliminating the tail is not new, it has long been known that tailless aircraft can suffer from stability and control problems that must be addressed early in the design. This thesis is concerned with identifying and then evaluating the flight dynamics, stability, flight controls and handling qualities of a generic BWB large transport aircraft concept. Longitudinal and lateral-directional static and dynamic stability

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21

Wang, Xiaoyang. "Aircraft fuel system prognostics and health management." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7214.

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This thesis contains the specific description of Group Design Project (GDP) and Individual Research Project (IRP) that are undertaken by the author and form part of the degree of Master of Science. The target of GDP is to develop a novel and unique commercial flying wing aircraft titled FW-11. FW-11 is a three-year collaborative civil aircraft project between Aviation Industry Corporation of China (AVIC) and Cranfield University. According to the market analysis result conducted by the author, 250 seats capacity and 7500 nautical miles were chosen as the design targets. The IRP is the further

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22

Saeed, Burhan. "Exploring the aerodynamic characteristics of a blown-annular wing for V/STOL aircraft." Thesis, Brunel University, 2010. http://bura.brunel.ac.uk/handle/2438/5173.

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This research programme explores, theoretically and experimentally, a new liftsystem for Vertical/Short Take-off and Landing (V/STOL) Aircraft. It is based upon an annular wing wrapped around a centrifugal flow generator, potentially creating a vehicle with no external moving parts, reduced vehicle aerodynamic losses compared to previous V/STOL technologies and substantially eliminating induced drag. It is shown that such a wing works best with a thick aerofoil section, and appears to offer greatest potential at a micro-aerial vehicle scale with regard to fundamental performance parameter “lif

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23

Bagheri, Shahriar. "Modeling, Simulation and Control System Design for Civil Unmanned Aerial Vehicle (UAV)." Thesis, Umeå universitet, Institutionen för tillämpad fysik och elektronik, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:umu:diva-96458.

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Unmanned aerial systems have been widely used for variety of civilian applications over the past few years. Some of these applications require accurate guidance and control. Consequently, Unmanned Aerial Vehicle (UAV) guidance and control attracted many researchers in both control theory and aerospace engineering. Flying wings, as a particular type of UAV, are considered to have one of the most efficient aerodynamic structures. It is however difficult to design robust controller for such systems. This is due to the fact that flying wings are highly sensitive to control inputs. The focus of thi

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24

Deslich, Joshua. "Effects of a Bell-Shaped Lift Distribution on an Oblique Flying Wing and its Impact on Aerodynamic Performance." University of Dayton / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1590560243607956.

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25

Al-Kayiem, Hussain Hammod. "Separated flow on a high lift wing : a study of the characteristics of the separated flow region on a lift wing under normal and wing/body conditions by means of a flying hot-wire technique." Thesis, University of Bradford, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.235558.

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26

Masiulis, Paulius. "Bepiločio skraidančio sparno aerodinaminių charakteristikų tyrimas." Master's thesis, Lithuanian Academic Libraries Network (LABT), 2014. http://vddb.library.lt/obj/LT-eLABa-0001:E.02~2014~D_20140625_094638-60072.

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Šiame darbe nagrinėjamos bepiločio skraidančio sparno aerodinaminės charakteristikos. Pasirinktas sparno profilis EPPLER 328. Pirmiausia išanalizuojami skaitiniai aerodinaminių charakteristikų tyrimo metodai. Atlikus skaičiavimus pagal pasirinktus aspektus, naudojant programą XFLR5 gauti duomenys apibendrinami bei išanalizuojami. Ištirtos keliamosios jėgos koeficientų, pasipriešinimo jėgos koeficientų, aerodinaminės kokybės reikšmės esant atitinkamiems atakos kampams. Naudojantis tyrimo rezultatais padarytas bepilotis skraidančio sparno orlaivis ir atlikti skrydžiai. Visa informacija apibendri

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27

Zhou, Weiguo. "Cabin environment and air quality in civil transport aircraft." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7305.

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The cabin environment of a commercial aircraft, including cabin layout and the quality of air supply, is crucial to the airline operators. These aspects directly affect the passengers’ experience and willing to travel. This aim of this thesis is to design the cabin layout for flying wing aircraft as part of cabin environment work, followed by the air quality work, which is to understand what effect the ECS can have in terms of cabin air contamination. The project, initially, focuses on the cabin layout, including passenger cabin configuration, seat arrangement and its own size due to the top r

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28

Pettersson, Emil. "Design of a drone system for maritime search and rescue missions." Thesis, KTH, Flygdynamik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-290180.

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The work summarized in this report aims to investigate how a drone airplane design can be optimized to create a safer and more efficient sea rescue by providing staff with an early picture, performing search missions and aiding communication through visual contact. A flying wing is in theory one of the most efficient designs for a fixed wing aircraft, at the same time as it also offers high structural efficiency for its given size. In this report, an overview of aerodynamics, stability and flying quality for a flying wing is discussed and analysed. XFLR5 was used for this project, and a compar

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29

Mohd, Nasir Mohd Nazri [Verfasser], Tropea [Akademischer Betreuer] Cameron, and Lehmann [Akademischer Betreuer] Fritz-Olaf. "Dynamics of high-speed-resolved wing and body kinematics of freely flying houseflies responding to directed and undirected air turbulence / Mohd Nazri Mohd Nasir ; Tropea Cameron, Lehmann Fritz-Olaf." Darmstadt : Universitäts- und Landesbibliothek Darmstadt, 2017. http://d-nb.info/1123729441/34.

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30

Voß, Arne [Verfasser], Andreas [Akademischer Betreuer] Bardenhagen, Andreas [Gutachter] Bardenhagen, Wolf-Reiner [Gutachter] Krüger, and Hartmut [Gutachter] Zingel. "Design and structural optimization of a flying wing of low aspect ratio based on flight loads / Arne Voß ; Gutachter: Andreas Bardenhagen, Wolf-Reiner Krüger, Hartmut Zingel ; Betreuer: Andreas Bardenhagen." Berlin : Technische Universität Berlin, 2020. http://d-nb.info/1208764500/34.

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31

Ekstam, Hanna, and Benjamin Quarmochi. "Design av infästningsanordning för virveldämpare på drönare." Thesis, Linnéuniversitetet, Institutionen för maskinteknik (MT), 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:lnu:diva-106215.

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Arbetet syftar till att ta fram en hållbar infästning för virveldämpare till SSRS drönare av modell flygande vinge. Drönaren är specifikt framtagen för att användas till maritima sök och räddningsuppdrag och för att bidra till att utöka den svenska kustens säkerhet. Arbetet studerar ett landningsscenario för drönaren och utifrån detta tas en ny infästning fram. Infästningen av virveldämparen skall vara lätt att hantera för personalen, kräva minimalt med reparation och hålla för 50 landningar. Infästningen skall kunna utlösa och separera virveldämparen från vingen om det under landningen uppstå

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32

Silva, Rafael. "Projeto conceptual de uma aeronave pequena de baixo custo para aplicação em controlo cooperativo." Master's thesis, Academia da Força Aérea, 2020. http://hdl.handle.net/10400.26/39752.

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Tendo como objetivo principal a busca por uma estrutura capaz de satisfazer as necessidades previstas para o desenvolvimento do controlo cooperativo, integrado no plano de Investigação e Desenvolvimento do Centro de Investigação da Academia da Força Aérea, encontra-se na presente dissertação um modelo de aeronave proposto e validado. Após serem salientados os requisitos essenciais ao sistema de controlo cooperativo, é apresentado um tipo de arquitetura do qual se destacam os sistemas de voo associados à mesma. Deste modo, após dimensionar o corpo onde estarão presentes os sistemas, opta-se po

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GARBUGLIA, FRANCESCO. "L'uso di sistemi aeromobili a pilotaggio remoto per la diagnosi non distruttiva di sistemi energetici." Doctoral thesis, Università Politecnica delle Marche, 2018. http://hdl.handle.net/11566/253140.

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L’uso dei sistemi aeromobili a pilotaggio remoto per la diagnosi non distruttiva di sistemi energetici necessita di un approccio quantitativo e sistematico. L’ispezione mediante drone di pale di turbine eoliche nel visibile e nell’infrarosso presenta dei notevoli vantaggi in termini di tempi, sicurezza e qualità rispetto alla tradizionale ispezione con un operatore su fune. Per questo si fa una review delle opportunità scientifiche e commerciali attuali. Si considera quindi la necessità di usare i sistemi aeromobili a pilotaggio remoto anche per analisi di tipo ambientale all’interno del proge

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Shinagawa, Yuto. "Propulsion considerations for supersonic oblique flying wings." Thesis, Massachusetts Institute of Technology, 2006. http://hdl.handle.net/1721.1/35565.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2006.<br>Includes bibliographical references (p. 111-113).<br>Propulsion considerations unique to the supersonic oblique flying wing, including cycle selection, sizing, and integration were investigated via the development and interrogation of aerodynamic and propulsive synthesis models. These models were an amalgamation of computational tools (MSES), linearized theory, parametric estimation, and quasi D thermodynamic cycle analysis. Lift-to-drag ratio, thrust specific fuel consumption, and nacelle wav

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Murthy, Raghuram Ananda, University of Western Sydney, and of Mechatronic Computer and Electrical Engineering School. "Dynamics of tethering cables for a flying electric generator." THESIS_XXX_MCEE_Murthy_R.xml, 2000. http://handle.uws.edu.au:8081/1959.7/674.

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The dynamics of a tether cable for a flying wind generator, employed to generate electricity by utilising the high velocity jet-stream winds in the troposphere, is analysed. A non-linear mathematical model for the study of the dynamics of the cable is described by a partial differential equation, which is solved analytically without damping. For unsteady and damped states, ordinary differential equations are obtained by adopting a discrete analysis approach, which are solved numerically with the aid of MATLAB software. Solutions are found for a range of lumped masses to represent the cable and

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Murthy, Raghuram Ananda. "Dynamics of tethering cables for a flying electric generator." Thesis, View thesis View thesis, 2000. http://handle.uws.edu.au:8081/1959.7/674.

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The dynamics of a tether cable for a flying wind generator, employed to generate electricity by utilising the high velocity jet-stream winds in the troposphere, is analysed. A non-linear mathematical model for the study of the dynamics of the cable is described by a partial differential equation, which is solved analytically without damping. For unsteady and damped states, ordinary differential equations are obtained by adopting a discrete analysis approach, which are solved numerically with the aid of MATLAB software. Solutions are found for a range of lumped masses to represent the cable and

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Murthy, Raghuram Ananda. "Dynamics of tethering cables for a flying electric generator /." View thesis View thesis, 2000. http://library.uws.edu.au/adt-NUWS/public/adt-NUWS20030509.162730/index.html.

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Thesis (M.Sc. (Hons)) -- University of Western Sydney, 2000.<br>"Thesis submitted to the University of Western Sydney, Nepean for the degree of Master of Engineering (Hons)" "School of Mechatronics, Computer and Electrical Engineering, December 2000" Includes bibliographical references (leaves 111-113).

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Raghavan, Brijesh. "Flight Dynamics and Control of Highly Flexible Flying-Wings." Diss., Virginia Tech, 2009. http://hdl.handle.net/10919/26829.

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High aspect-ratio flying wing configurations designed for high altitude, long endurance missions are characterized by high flexibility, leading to significant static aeroelastic deformation in flight, and coupling between aeroelasticity and flight dynamics. As a result of this coupling, an integrated model of the aeroelasticity and flight dynamics has to be used to accurately model the dynamics of the flexible flying wing. Such an integrated model of the flight dynamics and the aeroelasticity developed by Patil and Hodges is reviewed in this dissertation and is used for studying the unique fli

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Christiansen, Reed Siefert. "Design Of An Autopilot For Small Unmanned Aerial Vehicles." Diss., CLICK HERE for online access, 2004. http://contentdm.lib.byu.edu/ETD/image/etd445.pdf.

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Molter, Christian [Verfasser]. "Development of a Flying Wind Measurement System for Collective Operation / Christian Molter." München : Verlag Dr. Hut, 2020. http://d-nb.info/1220568155/34.

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41

Tomić, Teodor [Verfasser]. "Model-based control of flying robots for robust interaction under wind influence / Teodor Tomić." Hannover : Gottfried Wilhelm Leibniz Universität Hannover, 2018. http://d-nb.info/1172414645/34.

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Molter, Christian [Verfasser], and Po Wen [Akademischer Betreuer] Cheng. "Development of a flying wind measurement system for collective operation / Christian Molter ; Betreuer: Po Wen Cheng." Stuttgart : Universitätsbibliothek der Universität Stuttgart, 2020. http://d-nb.info/1220692840/34.

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43

Metalli, Matteo. "Sviluppo di un modello di drone di tipo flying wings in ambiente FlightGear interfacciato con autopiloti di Arduino implementati in Simulink." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2012. http://amslaurea.unibo.it/3009/.

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Fraser, Neil James. "Mechanisms for wintertime fjord-shelf heat exchange in Greenland and Svalbard." Thesis, University of Edinburgh, 2018. http://hdl.handle.net/1842/31289.

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No region has felt the effects of global climate change more acutely than the cryosphere, which has changed at an unprecedented rate in the past two decades. The scientific consensus is that these changes are driven largely by increasing ocean heat content at high latitudes. In southeast Greenland, acceleration and retreat of the marine-terminating glaciers contributes significantly towards global sea level rise. Circulation in the fjords which accommodate these glaciers is thought to be driven both by freshwater input and by barrier wind-driven shelf exchange. Due to a scarcity of data, parti

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Anderson, Elaine Susan. "Flying on the wings of trust : the story of the Delta farmland and wildlife trust an example of collaborative community based resource management." Thesis, University of British Columbia, 2009. http://hdl.handle.net/2429/22482.

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Competition over resources is threatening both agricultural viability and wildlife habitat around the world. One of the ways this problem can be addressed is through agri-environmental non-government organizations (NGOs) that practice community based collaborative resource management. However, there is a lack of academic research on both the formation and development of agri-environmental NGOs in First World industrialized nations and the role that policy plays in their formation and development. It is important to understand how policy affects the formation and development of such organizatio

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Reuveni, Yifat. "Iron wings and flying bodies: ideology and practice in the new economy - a case study of the middle-class workforce in the hi-tech industry." Thesis, McGill University, 2010. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=92241.

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At the end of the last century, a promising mode of economy emerged. Resting on developments in information and communication technologies, it became known as the New Economy. It offered a liberating ethos of work, claiming to value such traits as autonomy, flexibility, inventiveness and entrepreneurial spirit. Replacing the aloofness of mechanist Taylorism and the alienation of Fordist mass production, it succeeded in recruiting a young, educated and enthusiastic workforce that was willing to work long days in pursuit of success.<br>This study investigates the commitment of the white-collar

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Hu-MingShen and 沈胡茗. "Lateral Stability Control Design for the Flying Wing." Thesis, 2013. http://ndltd.ncl.edu.tw/handle/98651109242224500987.

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碩士<br>國立成功大學<br>航空太空工程學系碩博士班<br>101<br>This thesis focuses on the lateral stability control design for an unsteady tailless aircraft. The aircraft configuration reference design is based on Northrop YB-49 which was developed by Northrop Corporation. The aerodynamic coefficients were determined by DATCOM software and the results show that the stability of the tailless aircraft is unsteady. Instead of traditional root locus method, the eigenvalues assignment method suitable for multi-input multi-output (MIMO) systems is adopted for the analysis of two forms of control designs, P and PID. The equ

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Tsung-HsienLi and 李聰賢. "Longitudinal Stability Control Design for the Flying Wing." Thesis, 2013. http://ndltd.ncl.edu.tw/handle/24924446406879533272.

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碩士<br>國立成功大學<br>航空太空工程學系碩博士班<br>101<br>In this thesis, the major objective is to synthesizes the longitudinal stability control design for a flying-wing type aircraft. The flying-wing geometrical configuration is established and the digital DATCOM program is used to estimate its aerodynamic coefficients in order to analyze its stability characteristics and tracking performance. The results show that its stability characteristics is poor and a control system is needed to be designed in order to enhance the stability. It is known that PID method is very useful for control design, as it can impro

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LIAO, CHIEN-HSUN, and 廖建薰. "Preliminary Flight Performance Analysis of a Flying-Wing UAV." Thesis, 2019. http://ndltd.ncl.edu.tw/handle/jfwvx2.

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碩士<br>逢甲大學<br>智能製造與工程管理碩士在職學位學程<br>107<br>The technology of design and manufacture of Unmanned Aerial Vehicle (UAV), has been rapidly improved in the world. At present, the industry in which UAV are used is quite extensive. Take the military mission as an example, for the execution of short-range front-line reconnaissance missions and even long-range reconnaissance missions, it is necessary to have a carrier with excellent aerodynamic efficiency for the mission, regardless of whether the power system of the vehicle is equipped with an internal combustion engine or an electric brushless DC (BLD

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Challa, Vinay Reddy. "Analysis of Kinematic Constraints in Fixed-Wing UAV Formation Flying." Thesis, 2020. https://etd.iisc.ac.in/handle/2005/4694.

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Rise in autonomy has led to increase in usage of Unmanned Aerial Vehicles (UAVs) for various applications and has allowed the UAVs to perform complex and hazardous missions with ease. Formation of multiple UAVs finds applications in both military and civilian operations. Tasks like image mosaicking, mapping and target triangulation require multiple UAVs to maintain rigid formation while performing the mission. While maneuvering, rigid formation flying requires different speeds and bank angles from individual UAVs. However, fixed-wing UAVs have operational limits on bank-angle and speed.

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