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Dissertations / Theses on the topic 'Flight dynamics'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Benedetti, Diego Muniz. "Paragliders flight dynamics." Universidade Federal de Minas Gerais, 2012. http://hdl.handle.net/1843/BUOS-95RGS5.

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Paragliding has become popular in the last three decades, and the development of modern paragliders has shown considerable improvements on performance and safety. However, due to the sportive purpose of paragliders, scientific studies on this subject are still rare. The achievements on paragliders design are mostly originated from industry, and, although there are many manufactures with years of experience designing paragliders, it cannot be found in the available literature works dedicated on paragliders design theory. Taking in account the lack of specific information about paragliders engin

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2

Shankar, Kumar Priya Balaji. "Dynamics of spacecraft formation flight." Thesis, University of Southampton, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.417979.

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3

Pagliuca, Giampaolo. "Model reduction for flight dynamics using computational fluid dynamics." Thesis, University of Liverpool, 2018. http://livrepository.liverpool.ac.uk/3029018/.

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The coupling of computational fluid dynamics and rigid body dynamics promises enhanced multidisciplinary simulation capability for aircraft design and certification. Industrial application of such coupled simulations is limited however by computational cost. In this context, model reduction can retain the fidelity of the underlying model while decreasing the overall computational effort. Thus, investigation of such coupled model reduction is presented in this thesis. The technique described herein relies on an expansion of the full order non-linear residual function in a truncated Taylor serie

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4

Montalvo, Carlos. "Meta aircraft flight dynamics and controls." Diss., Georgia Institute of Technology, 2014. http://hdl.handle.net/1853/51854.

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The field of mobile robotic systems has become a rich area of research and design. These systems can navigate difficult terrain using multiple actuators with conventional ambulation, by hopping, jumping, or for aerial vehicles, using flapping wings, propellers, or engines to maintain aerial flight. Unmanned Aerial Systems(UAS) have been used extensively in both military and civilian applications such as reconnaissance or search and rescue missions. For air vehicles, range and endurance is a crucial design parameter as it governs which missions can be performed by a particular vehicle. In addit

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5

Seigler, Thomas Michael. "Dynamics and Control of Morphing Aircraft." Diss., Virginia Tech, 2005. http://hdl.handle.net/10919/28681.

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The following work is directed towards an evaluation of aircraft that undergo structural shape change for the purpose of optimized flight and maneuvering control authority. Dynamical equations are derived for a morphing aircraft based on two primary representations; a general non-rigid model and a multi-rigid-body. A simplified model is then proposed by considering the altering structural portions to be composed of a small number of mass particles. The equations are then extended to consider atmospheric flight representations where the longitudinal and lateral equations are derived. Two aspect

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6

Zaludin, Zairil A. "Flight dynamics and automatic flight control system of an hypersonic transport aircraft." Thesis, University of Southampton, 1999. https://eprints.soton.ac.uk/47120/.

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7

Leonard, Benjamin Yoshi. "Flapping Wing Flight Dynamic Modeling." Thesis, Virginia Tech, 2011. http://hdl.handle.net/10919/34790.

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Highly agile, hover capable flapping wing flight is a relatively new area of study in engineering. Researchers are looking to flapping flight as a potential source for the next generation of reconnaissance and surveillance vehicles. These systems involve highly complicated physics surrounding the flapping wing motion and unusual characteristics due to a hover requirement not normally associated with conventional aircraft. To that end this study focuses on examining the various models and physical parameters that are considered in various other studies. The importance of these models is conside

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8

Kabaliuk, Natalia. "Dynamics of Blood Drop Formation and Flight." Thesis, University of Canterbury. Mechanical Engineering, 2014. http://hdl.handle.net/10092/8979.

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Violent crimes involving bloodshed may result in the formation of a number of blood drops that move through air and impact onto a surface producing a bloodstain pattern. Bloodstain Pattern Analysis (BPA), the analysis of the position, distribution, size and morphology of the stains within the pattern present at a crime scene, may provide information about the events that gave rise to the bloodshed. The location of blood origin, i.e. victim’s position at the moment of wounding and (or) wound location, determination is of major interest to BPA. This study investigated the dynamics of formation a

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9

Watkiss, Eric John. "Flight dynamics of an unmanned aerial vehicle." Thesis, Monterey, California. Naval Postgraduate School, 1994. http://hdl.handle.net/10945/28222.

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Approved for public release; distribution is unlimited.<br>Moments of inertia were experimentally determined and longitudinal and lateral/directional static and dynamic stability and control derivatives were estimated for a fixed wing Unmanned Air Vehicle (UAV). Dynamic responses to various inputs were predicted based upon the estimated derivatives. A divergent spiral mode was revealed, but no particularly hazardous dynamics were predicted. The aircraft was then instrumented with an airspeed indicator, which when combined with the ability to determine elevator deflection through trim setting o

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10

Charles, Guy Alexander. "Bifurcation tailoring applied to nonlinear flight dynamics." Thesis, University of Bristol, 2003. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.274630.

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11

Marguery, Ulysse. "Flight Dynamics Modelling and Application to SatelliteDeorbitation Strategy." Thesis, KTH, Flygdynamik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-30613.

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In this paper a study to determine the best strategic choice to deorbit satellites incase of system failures is conducted. An orbital mechanic analysis of the deorbitationis done and a matlab code based on Lagrange’s interplanetary equations is developed.The effects of the atmospheric drag and the solar activity are investigated and the fueland delta velocity consumptions are assessed for different deorbitation strategies. Thepaper also investigates the probability to hit or be hit by a piece of debris. A briefoverview of the acquisition and safe hold modes Bdot and Bspin is given. Then thepos

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12

Rashid, Tahir. "The flight dynamics of a full-scale ornithopter." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1995. http://www.collectionscanada.ca/obj/s4/f2/dsk3/ftp04/MQ45437.pdf.

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13

Qiao, Yuqing. "Effect of wing flexibility on aircraft flight dynamics." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7280.

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The purpose of this thesis is to give a preliminary investigation into the effect of wing deformation on flight dynamics. The candidate vehicle is FW-11 which is a flying wing configuration aircraft with high altitude and long endurance characteristics. The aeroelastic effect may be significant for this type of configuration. Two cases, the effect of flexible wing on lift distribution and on roll effectiveness during the cruise condition with different inertial parameters are investigated. For the first case, as the wing bending and twisting depend on the interaction between the wing structura

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14

Taylor, Graham K. "Animal flight dynamics : mechanics of stability and control." Thesis, University of Oxford, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.270179.

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15

Bedford, Ryan Gary. "Bifurcation and continuation analysis of rotorcraft flight dynamics." Thesis, University of Bristol, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.414130.

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16

河村, 耕平, Kohei KAWAMURA, 陽亮上野, Yosuke UENO, 佳朗中村 та Yoshiaki NAKAMURA. "数値流体力学と数値飛行力学の連成に基づく竹とんぼのフライトシュミレーション". 日本航空宇宙学会, 2008. http://hdl.handle.net/2237/13870.

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17

Taha, Haithem Ezzat Mohammed. "Mechanics of Flapping Flight: Analytical Formulations of Unsteady Aerodynamics, Kinematic Optimization, Flight Dynamics and Control." Diss., Virginia Tech, 2013. http://hdl.handle.net/10919/24428.

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A flapping-wing micro-air-vehicle (FWMAV) represents a complex multi-disciplinary system whose analysis invokes the frontiers of the aerospace engineering disciplines. From the aerodynamic point of view, a nonlinear, unsteady flow is created by the flapping motion. In addition, non-conventional contributors, such as the leading edge vortex, to the aerodynamic loads become dominant in flight. On the other hand, the flight dynamics of a FWMAV constitutes a nonlinear, non-autonomous dynamical system. Furthermore, the stringent weight and size constraints that are always imposed on FWMAVs invoke d

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18

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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19

Orfanos, Zacharias. "Dynamics of sarcomere assembly in drosophila indirect flight muscles." Thesis, University of York, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.533510.

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20

Lowenberg, Mark H. "Application of bifurcation analysis to multiple attractor flight dynamics." Thesis, University of Bristol, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.264065.

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21

Dadashi, Shirin. "Modeling and Approximation of Nonlinear Dynamics of Flapping Flight." Diss., Virginia Tech, 2017. http://hdl.handle.net/10919/78224.

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The first and most imperative step when designing a biologically inspired robot is to identify the underlying mechanics of the system or animal of interest. It is most common, perhaps, that this process generates a set of coupled nonlinear ordinary or partial differential equations. For this class of systems, the models derived from morphology of the skeleton are usually very high dimensional, nonlinear, and complex. This is particularly true if joint and link flexibility are included in the model. In addition to complexities that arise from morphology of the animal, some of the external force

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22

Yarger, Alexandra Mead. "Inertial encoding mechanisms and flight dynamics of dipteran insects." Case Western Reserve University School of Graduate Studies / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=case1585688085360805.

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23

Peskett, Jonathan Paul. "The development of unsteady aerodynamic mathematical models." Thesis, University of Bristol, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.299504.

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24

Wakefield, Nigel Hugh. "Helicopter flight in the airwake of non-aviation ships." Thesis, University of Southampton, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.326729.

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25

Aliaga, Rivera Cristhian Neil. "An unsteady multiphase approach to in-flight icing /." Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112552.

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Ice accretion is a purely unsteady phenomenon that is presently approximated by most icing codes using quasi-steady modeling. The accuracy of ice prediction is thus directly related to the arbitrarily prescribed time span during which the impact of ice growth on both flow and droplets is neglected. The objective of this work is to remove this limitation by implementing a cost-effective unsteady approach. This is done by fully coupling, in time, a diphasic flow (interacting air and droplet particles) with the ice accretion model. The two-phase flow is solved using the Navier-Stokes and Eulerian

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26

Mazhar, Hashim. "Dynamics, control and flight testing of an unmanned, finless airship." Thesis, McGill University, 2013. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=117157.

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This thesis discusses a number of developments in the dynamics and control of a novel, autonomous, highly-maneuverable, finless, almost-lighter-than-air vehicle (ALTAV). The airship is inherently unstable due to absence of fins and is highly prone to winds. Four vectored thrusters are used to ensure closed-loop stability. This thesis deals with improvements made to an existing dynamics model, including the incorporation of the rotational damping moments of the airship, the drag resulting from the protuberances on the airship hull, the reaction torques and the gyroscopic moments on the airship

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27

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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28

Richardson, Thomas Stuart. "Continuation methods applied to non linear flight dynamics and control." Thesis, University of Bristol, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.268783.

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29

Hilton, Emily M. (Emily Margaret). "Characterization and analysis of the flight dynamics of fruit flies." Thesis, Massachusetts Institute of Technology, 2007. http://hdl.handle.net/1721.1/40431.

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Thesis (S.B.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2007.<br>Includes bibliographical references (p. 39).<br>For centuries, the human race has been perplexed by the various complex physical manifestations in nature. Much of what we have seen in nature we have tried to recreate, from the migration tendencies and routes of sea creatures to the flight of birds and insects. The flight of the fly, in particular, is of interest because of their natural stabilization techniques. The works of two scientists, Steven Vogel and Michael Dickinson, were researched in orde

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30

Alves, Sandro Bruno Duarte. "Helicopter flight modeling and robust autonomous control with uncertain dynamics." Master's thesis, Universidade da Beira Interior, 2012. http://hdl.handle.net/10400.6/2003.

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Helicopter flight control has gained greater visibility in the last decades due to its characteristics. It is a task of high difficulty due to the system being changeable. Helicopter control is the junction of several variables such as the flying qualities and performance, skill of the pilot, weather conditions, etc. For a given configuration of a helicopter (military, civil, SAR, etc.), we need precise control parameters, and is in flying qualities that we focus our attention. This paper is then dedicated to autonomous modeling and control of conventional rotarywing platforms, so that th

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31

Gupta, Rikin. "Incorporating Flight Dynamics and Control Criteria in Aircraft Design Optimization." Diss., Virginia Tech, 2020. http://hdl.handle.net/10919/104967.

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The NASA Performance Adaptive Aeroelastic Wing (PAAW) project goals include significant reductions in fuel burn, emissions, and noise via efficient aeroelastic design and improvements in propulsion systems. As modern transport airplane designs become increasingly lightweight and incorporate high aspect-ratio wings, aeroservoelastic effects gain prominence in modeling and design considerations. As a result, the influence of the flight dynamics and controls on the optimal structural and aerodynamic design needs to be captured in the design process. There is an increasing interest in more integra

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32

Thompson, Ernest. "Incorporation of Computational Fluid Dynamics into Flight Vehicle Preliminary Design." University of Dayton / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1335270317.

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33

WANG, ZHONG-SHENG. "DYNAMICS ANALYSIS OF SATELLITE FORMATION FLIGHT USING SOLAR RADIATION PRESSURE." University of Cincinnati / OhioLINK, 2001. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1005854591.

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34

Indriyanto, Toto. "Nonlinear flight control system for lateral manoeuvres in wind shear." Thesis, Cranfield University, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.273525.

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35

Krothapalli, Krishnamohan Rao. "Helicopter rotor dynamic inflow modeling for maneuvering flight." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12066.

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36

Soinne, Erkki. "Aerodynamic and Flight Dynamic Simulations of Aileron Characteristics." Doctoral thesis, KTH, Aeronautical Engineering, 2000. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3038.

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37

Patil, Mayuresh J. "Nonlinear aeroelastic analysis, flight dynamics, and control of a complete aircraft." Diss., Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/12099.

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38

Wang, Yi-Ren. "The effect of wake dynamics on rotor eigenvalues in forward flight." Diss., Georgia Institute of Technology, 1992. http://hdl.handle.net/1853/13031.

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39

Walter, Patrick L. "OPTIMIZING FLIGHT SHOCK AND VIBRATION MEASUREMENT BY RF LINKS." International Foundation for Telemetering, 1998. http://hdl.handle.net/10150/609222.

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International Telemetering Conference Proceedings / October 26-29, 1998 / Town & Country Resort Hotel and Convention Center, San Diego, California<br>Acquiring shock and vibration data from flight vehicles through rf telemetry links has numerous associated challenges. Yet, these measurements are important to establish environmental specifications to provide a basis for system or component design and testing. The principal limitation in acquiring these measurements is the frequency bandwidth available for data transmission. This limited bandwidth is often responsible for invalid data being acce

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40

Muir, Ewan Andrew McPherson. "The application of robust inverse dynamics estimation to the control of a thrust vectoring fighter aircraft." Thesis, Lancaster University, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.337552.

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41

Leedy, Jeffrey Quentin. "Real-Time Moment Rate Constrained Control Allocation for Aircraft with a Multiply-Redundant Control Suite." Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/31028.

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The problem of aircraft control allocation is that of finding a combination of control positions that cause the resulting aircraft moments to most closely satisfy a given desired moment vector. The problem is easily solved for the case of an aircraft having three control surfaces, each of which primarily imparts moments in each of the three aircraft axes. In this simple case, the solution to the control allocation problem is uniquely determined. However, many current and future aircraft designs employ a larger set of control effectors, resulting in a control redundancy in the sense that more

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42

Hur, Gi-Bong. "Identification of powered parafoil-vehicle dynamics from modelling and flight test data." Texas A&M University, 2003. http://hdl.handle.net/1969.1/3859.

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During the final approach and landing phase of the X-38/Crew Return Vehicle, a steerable parafoil is used to maneuver and land at a targeted ground base under autonomous control. To simulate and verify performance of the onboard Parafoil Guidance, Navigation and Control system (PGNC), a commercial powered parafoil- vehicle, called the Buckeye consisting of a parafoil and vehicle two-body system like the X-38/CRV was modified to accommodate the avionics and scale-downed parafoil for aerodynamic similarity and a series of flight tests were conducted. Dynamic modelling and system identification r

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43

Goupil, Marc Y. "Dynamic Pressure Sensing for the Flight Test Data System." DigitalCommons@CalPoly, 2019. https://digitalcommons.calpoly.edu/theses/2115.

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This thesis describes the design, assembly, and test of the FTDS-K, a new device in the Boundary Layer Data System (BLDS) family of flight data acquisition systems. The FTDS-K provides high-frequency, high-gain data acquisition capability for up to two pressure sensors and an additional three low-frequency pressure sensors. Development of the FTDS-K was separated into a core module, specialized analog subsystem, and practical testing of the FTDS-K in a flow measurement mission. The core module combines an nRF52840-based microcontroller module, switching regulator, microSD card, real-time clock

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44

Kantsaporidis, Ioannis, and Sadeq Al-Attar. "Dynamics and electronics of a manually chargeable quadcopter for steady-state flight." Thesis, Mälardalens högskola, Akademin för innovation, design och teknik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-37208.

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The objective of this thesis is to investigate how the onboard battery of a quadcopter can be charged through manual rotation of its motors, while understanding the resulting aerodynamical forces acting on the rotors during hover, as well as considering the changes in thrust capabilities when the electronic and structural design are altered. A theoretical approach using the momentum theory will present a general understanding of rotor performance whilst describing the correlation between rotor parameters, thrust and mechanical power. Furthermore, the idea of using the motors as generators are

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45

Ribera, Maria. "Helicopter flight dynamics simulation with a time-accurate free-vortex wake model." College Park, Md. : University of Maryland, 2007. http://hdl.handle.net/1903/6876.

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Thesis (Ph. D.) -- University of Maryland, College Park, 2007<br>Thesis research directed by: Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.

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46

Otto, Gustav. "Critical comparison of control techniques for a flight dynamics controller / Gustav Otto." Thesis, North-West University, 2011. http://hdl.handle.net/10394/8068.

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This dissertation covers the process of modelling and subsequently developing a flight dynamics controller for a quad–rotor unmanned aerial vehicle. It is a theoretical study that focusses on the selection of a controller type by first analysing the problem on a system level and then on a technical level. The craft is modelled using the Newton– Euler model, accounting for multiple reference frames to account for the interpretation of orientation as seen by on–board sensors. The quad–rotor model and selected controllers are characterized and compared. The model is verified through simulation by

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47

Ouellette, Jeffrey. "Flight Dynamics and Maneuver Loads on a Commercial Aircraft with Discrete Source Damage." Thesis, Virginia Tech, 2010. http://hdl.handle.net/10919/32339.

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To improve the recoverability and survivability of aircraft after damage, a better understanding of the flight dynamics and the structural loads is needed. However, damage can introduce asymmetries that complicate the modeling. An extended vortex lattice code is used to model the quasi-steady aerodynamic forces. The vortex lattice method provides the force distribution which is not available elsewhere. Snapshots from the vortex lattice model are used to generate a reduced order model (ROM). This ROM contains non-linear terms to account for non-linearities that the damage can introduce. The ROM

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48

Lee, Jason W. L. "Novel developments in time-of-flight particle imaging." Thesis, University of Oxford, 2016. https://ora.ox.ac.uk/objects/uuid:195be057-7ce0-4a15-b639-b08892fde312.

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In the field of physical chemistry, the relatively recently developed technique of velocity-map imaging has allowed chemical dynamics to be explored with a greater depth than could be previously achieved using other methods. Capturing the scattering image associated with the products resulting from fragmentation of a molecule allows the dissociative pathways and energy landscape to be investigated. In the study of particle physics, the neutron has become an irreplaceable spectroscopic tool due to the unique nature of the interaction with certain materials. Neutron spectroscopy is a non-destruc

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49

Jonnalagadda, V. R. Prasad. "A derivation of rotor blade equations of motion in forward flight and their solution." Diss., Georgia Institute of Technology, 1985. http://hdl.handle.net/1853/12963.

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50

Yeaton, Isaac J. "The Dynamics of Non-Equilibrium Gliding in Flying Snakes." Diss., Virginia Tech, 2018. http://hdl.handle.net/10919/82493.

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This dissertation addresses the question, how and why do 'flying' snakes (Chrysopelea) undulate through the air? Instead of deploying paired wings or wing-like surfaces, flying snakes jump, splay their ribs into a bluff-body airfoil, and undulate through the air. Aerial undulation is the dominant feature of snake flight, but its effects on locomotor performance and stability are unknown. Chapter 2 describes a new non-equilibrium framework to analyze gliding animals and how the pitch angle affects their translational motion. Chapter 3 combines flying snake glide experiments and detailed dynamic

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