Dissertations / Theses on the topic 'Flight'
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1
Urban, Margaret Mary. "Flight Signs, Flight Symbols." VCU Scholars Compass, 2005. http://scholarscompass.vcu.edu/etd/956.
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I am investigating the significance of historic events of flight through image making; particularly incidents that captured the collective imagination and became part of our cultural memory. These events have surpassed mere entries in historical texts and become mythic. In the terms of Jungian psychology, they have become symbolic. In terms of Semiotics, they have become signs. Through photographs and installation, I seek to understand their presence in my, and our, unconscious mind.
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Gao, Yanjia. "Bumblebee flights on a novel flight mill system." Thesis, University of Cambridge, 2014. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.708357.
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Суворов, Гліб Вікторович. "RADIOTELEPHONY PHRASEOLOGY EFFECT ON FLIGHT DURING INTERNATIONAL FLIGHTS." Thesis, К.: НАУ, 2013. http://er.nau.edu.ua/handle/NAU/11711.
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Christian, Mark Jay. "Post crash flight analysis: visualizing flight recorder data." Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/27214.
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Tow, David, and Dennis Arce. "ENHANCED FLIGHT TERMINATION SYSTEM FLIGHT DEMONSTRATION AND RESULTS." International Foundation for Telemetering, 2007. http://hdl.handle.net/10150/604579.
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ITC/USA 2007 Conference Proceedings / The Forty-Third Annual International Telemetering Conference and Technical Exhibition / October 22-25, 2007 / Riviera Hotel & Convention Center, Las Vegas, NevadaThis paper discusses the methodology, requirements, tests, and implementation plan for the live demonstration of the Enhanced Flight Termination System (EFTS) using a missile program at two locations in Florida: Eglin Air Force Base (AFB) and Tyndall AFB. The demonstration included the integration of EFTS Flight Termination Receivers (FTRs) onto the missile and the integration of EFTS-program-developed transmitter assets with the mission control system at Eglin and Tyndall AFBs. The initial test stages included ground testing and captive-carry flights, followed by a launch in which EFTS was designated as the primary flight termination system for the launch.
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Kesserwan, Nader. "Flight simulation." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1999. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape7/PQDD_0018/MQ55071.pdf.
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Holmgren, Staffan. "Optimization of flight deck crew assignments on Scandinavian Airlines' intercontinental flights." Thesis, Linköping University, Department of Science and Technology, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-6506.
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The harsh competition in the airline industry continuously forces airline carriers to streamline their production and cut back on costs. Manpower constitutes the largest expense in Scandinavian Airline System, closely followed by fuel costs. Thus effective crew planning is vital to face the competition from international actors and low cost carriers.
Creating efficient schedules for airline crew is a very complex combinatorial task and the process is heavily dependent on optimization. A large set of constraints comprised of union- and governmental rules as well as company policies and quality factors must be taken into consideration when the schedules are created.
This master thesis examines how the distribution of rank in the SAS international pilot corps affects the total cost associated with flight deck crew.
Long haul flights at SAS intercontinental are manned with a captain, a first officer and a relief pilot. Pilots may man lower ranking positions on any given flight in order to make efficient use of the pilot corps and to minimize the need of full time equivalents.
This work discusses the development and evaluation of a simulation environment developed in order to create and analyze fictitious crew populations with different distributions of rank. Furthermore the solution methods to the scheduling problem implemented at SAS and the optimization theory associated with them are discussed.
The project has resulted in an evaluation of the developed simulation environment and a discussion about the difficulties of analyzing crew populations with the systems currently in use at SAS.
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Kole, Merlin. "PoGOLite: 2011 flight results and 2012 pre-flight predictions." Licentiate thesis, KTH, Partikel- och astropartikelfysik, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-98812.
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Magill, Samantha Anne. "Compound Aircraft Transport: Wingtip-Docked Flight Compared to Formation Flight." Diss., Virginia Tech, 1998. http://hdl.handle.net/10919/11122.
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Compound Aircraft Transport (CAT) flight involves two or more aircraft using the resources of each other; a symbiotic relationship exists consisting of a host, the mothership aircraft and a parasite, the hitchhiker aircraft. Wingtip-docked flight is just as its name implies; the two aircraft are connected wingtip-to-wingtip. Formation flight describes multiple aircraft or flying objects that maintain a pattern or shape in the air. There are large aerodynamic advantages in CAT flight. The aforementioned wingtip-docked flight increases total span of the aircraft system, and formation flight utilizes the upwash from the trailing wingtip vortex of the lead aircraft (mothership) to reduce the energy necessary to achieve and/or maintain a specific flight goal for the hitchhiker and the system.
The Stability Wind Tunnel (6 X 6 X 24 foot test section) at Virginia Tech, computational aerodynamic analysis with the vortex lattice method (VLM), and a desktop aircraft model were used to answer questions of the best location for a hitchhiker aircraft and analyze stability of the CAT system. Wind tunnel tests implemented a 1/32 scale F-84E model (hitchhiker) and an outboard wing portion representing a B-36 (mothership). These models were chosen to simulate flight tests of an actual wingtip-docked project, Tom Tom, in the 1950s. That project was terminated after a devastating accident that demonstrated a possible "flapping" motion instability. The wind tunnel test included a broad range of hitchhiker locations: varying spanwise gap distance, longitudinal or streamwise distance, and vertical location (above or below wing) with respect to a B-36-like wing. The data showed very little change in the aerodynamic forces of the mothership, and possibilities of large benefits in lift and drag for the hitchhiker when located slightly aft and inboard with respect to the mothership. Three CAT flight configurations were highlighted: wingtip-docked, close formation, and towed formation. The wingtip-docked configuration had a 20-40 percent performance benefit for the hitchhiker compared to solo flight. The close formation configuration had performance benefits for the hitchhiker approximately 10 times that of solo flight, and the towed formation was approximately 8 times better than solo flight.
The VLM analysis completed and reenforced the experimental wind tunnel data. A modified VLM program (VLM CAT) incorporated multiple aircraft in various locations as well as additional calculations for induced drag. VLM CAT results clearly followed the trends seen in the wind tunnel data, but since VLM did not model the fuselage, has assumptions like a flat wake, and is an inviscid computation it did not predict the large benefits or excursions as seen in the wind tunnel data. Increases in performance for the hitchhiker in VLM CAT were on the order of 3 to 4 times that of the hitchhiker in solo flight, while the wind tunnel study saw up to 10 times that of solo flight. VLM CAT is a valuable tool in supplying quick analysis of position and planform effects in CAT flight.
Modifications to a desktop F-16 dynamic simulation have been developed to investigate the stability of wingtip-docked flight. These modifications analyze the stability issues linked with sideslip angle as seen by the Tom Tom Project test pilot, when he entered docking maneuvers with 5 degrees yaw to simulate a ``tired pilot". The wingtip-docked system was determined to have an unstable aperiodic mode for sideslip angle greater than 0.0 degrees and an unstable oscillatory mode for sideslip angle greater than 2.0 degrees. There is a small range of sideslip angle that is a stable oscillatory mode, sideslip angle between 0.0 and 2.0 degrees. The variables, altitude and speed, yield little effect on the stability of the system. The sensitivity analysis was indeterminate in distinguishing a state driving the instability, but the analysis was conclusive in verifying the lateral-longitudinal (roll-pitch) coupled motion observed by test pilots in wingtip-docked flight experiments. The parameter with the largest influence on the instability was the change in pitch angular acceleration with respect to roll angle.
The aerodynamic results presented in this study have determined some important parameters in the location of a hitchhiker with respect to a mothership. The largest aerodynamic benefits are seen when the hitchhiker wingtip is slightly aft, inboard and below the wingtip of the mothership. In addition, the stability analysis has identified an instability in the CAT system in terms of sideslip angle, and that the wingtip-docked hitchhiker is coupled in lateral and longitudinal motion, which does concur with the divergent "flapping" motion about the hinged rotational axis experienced by the Tom Tom Project test pilot.Ph. D.
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Sevillian, Dujuan Brandez. "Flight deck engineering : impact of flight deck crew alerting and information systems on English as a second language flight crewmembers performance in airline flight operations." Thesis, Cranfield University, 2017. http://dspace.lib.cranfield.ac.uk/handle/1826/12078.
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There are many pieces of flight deck research on general use of written English language
technical information and problem solving using technical documentation. Contributory
causes of aircraft accidents have been due to misunderstandings of crew alerts and procedural
divergence by English as-a-second language flight crewmembers (ESL). Research was
conducted to understand impact of written English language technical information on ESL
flight crewmembers’ performance. Two types of systems were evaluated, technical
documentation and crew alerting systems that contain technical information, with respect to
their impact on ESL flight crewmember performance. Preliminary analysis results indicated
written English language technical information can be confusing, difficult to read and
interpret, and leads to misunderstandings by ESL flight crewmembers during aircraft nonnormal
conditions. English as-a-second language flight crewmembers indicated they often
experience problems executing written English language technical procedures after outset of
crew alerts.
Conversely, experimental trials revealed ESL flight crewmembers did not experience many
cognitive performance issues with use of crew alerting systems and technical information
designed with an English language emphasis. English as-a second language flight
crewmembers’ English language proficiency, background knowledge, and use of use of
metacognitive strategies to read and comprehend written English language on crew alerting
and information systems, indicated they utilized written English technical information with
ease. Particularly, ESL flight crewmembers’ workload was low, they had fast response times
to system faults, and they experienced minimal procedural deviations. On the contrary, when
ESL flight crewmembers utilized written English language technical procedures translated
into their native language during non-normal conditions, they experienced several cognitive
performance challenges. English as-a second language flight crewmembers’ background
knowledge of written English language technical information translated into their native
language, use of metacognitive strategies to read and comprehend written English language
translated into their native language, indicated they experienced difficulties with reading and
comprehending translated technical information on information systems. Particularly, ESL
flight crewmembers were challenged cognitively when they responded to crew alerts through
execution of decision-making processes. They indicated translation of written English
language technical information into their native language was a pre-cursor to procedural
deviation, long response times to system issues, as well as high workload during
experimental trials.
It is recommended that further research focus on design and use of written English language
technical documentation by ESL flight crewmembers during non-normal conditions. It is also
recommended that if deemed practical by the aviation industry, further research should focus
on design, integration, and utilization of technical documentation in a language(s) other than
English, and measurement of ESL flight crewmembers performance on the flight deck.
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Давиденко, Алла Олександрівна. "AVIATION FLIGHT SAFETY." Thesis, АВІА–2015: м-ли ХІІ міжнар. наук.-техн. конф., 29–30 травня 2015 р. – К., 2015. – К., 2015. – С. 9.187-190, 2015. http://er.nau.edu.ua/handle/NAU/15479.
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The article deals with issues concerning aviation flight safety. We know that air transport will continue to grow, it has a good relative safety record but pulbic perception focuses on total accidents rather than relative safety. This has led to the setting of ambitious new safety targets for air transport whose attainment will require improved knowledge of causes of accidents and better understanding of the effects of new technologies and procedures, Human factors and operational environments are key elements while aircraft design construction and maintenance, together with ATC operations and accident mitigation, also play important roles.
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Lehocký, Gabriel. "Electronic Flight Bag." Master's thesis, Vysoké učení technické v Brně. Fakulta informačních technologií, 2017. http://www.nusl.cz/ntk/nusl-363806.
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Tato diplomová práce popisuje standardy, typy a použití leteckého systému Electronic Flight Bag. Dále se zabývá návrhem a implementací aplikace pro tablety s operačním systémem Android. Tato aplikace vychází z evropských směrnic pro piloty všeobecného letectví. Mezi hlavní vlastnosti vytvořené aplikace patří letový manuál, prohlížeč letových publikací a dokumentů, letová navigace zaměřena na uživatele, kalkulace hmotnosti a těžiště, a další interaktivní výpočty.
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Mitchell, Sean. "Long Flight Home." Master's thesis, University of Cape Town, 2009. http://hdl.handle.net/11427/14707.
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Long Flight Home follows events in the life of James Van Gogh, who grapples with two fundamental tensions: his split from his adopted family and his dislocation from the society in which he finds himself. The novel begins in Johannesburg with James returning, for the first time since their ruction, to his family home, where his mother is dying of cancer. In many ways, he is still tormented by the issues surrounding his adoption. The visit ends badly, with James fleeing her funeral service. Nevertheless, he gains a deep friendship with his mother's caretaker, a woman named Mel. His intimacy with her is one of two important relationships the novel tracks. The other is between James and a pair of young beggars - a boy and a girl - who interest him initially on a professional plane: he is researching an investigative work on street children. Although Mel is a married woman, James influences her to take up work in Cape Town, where he lives - a decision made easier by the dubious state of her marriage. They begin a tentative affair. Mel is not sure of herself, aware at all times that she is betraying her principles. James has no such scruples, however, and he plays a wily game. Eventually, they consummate their relationship. But shortly thereafter Mel disappears. Her body is found in a patch of veld - she is dead. James uses his connections to the streets to find out the identity of the killer. The boy introduces him to an informer, who takes him into the Flats. There, James comes face to face with the man who murdered Mel, but finds himself impotent, unable to act. After that, to distract himself, he concentrates on his work. Determined to regain control of his surroundings, to reassert his will, he takes in one of the street children w the girl. But the boy, who has become involved in an underworld of drugs and crime, exerts a negative influence. James makes arrangements for the authorities to take him in, but, with the plans in place, the children disappear.
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Kúšik, Lukáš. "Electronic Flight Bag." Master's thesis, Vysoké učení technické v Brně. Fakulta informačních technologií, 2021. http://www.nusl.cz/ntk/nusl-449169.
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Cieľom tejto diplomovej práce je vytvoriť Electronic Flight Bag (EFB) aplikáciu pre mobilné telefóny s operačným systémom Android. Pre splnenie tejto úlohy bola preskúmaná aktuálna legislatíva ohľadom EFB aplikácií spolu s najmodernejšími EFB aplikáciami dostupnými na aplikačnom trhu. Na základe týchto informácií je navrhnutá a implementovaná EFB aplikácia určená pre pilotov všeobecného letectva. Výsledný produkt obsahuje funkcie pre plánovanie letu, vlastnú leteckú mapu, pilotný denník, katalóg letísk s dátami z celého sveta a ďalšie. Podpora offline zaručuje funkčnosť v reálnych podmienkach letu. Konečný produkt sa taktiež snaží inovovať nad existujúcimi EFB aplikáciami zahrnutím funkcionalít, akými sú napríklad automatické kontrolné zoznamy a náhľad v rozšírenej realite.
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Shain, Jeanne Ungemach. "Portraits in flight /." Online version of thesis, 1996. http://hdl.handle.net/1850/11905.
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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 engineering, a dedicate work in
applied flight mechanics has been developed with the purpose of explain paragliders flight, and specially the relations between flight characteristics and design parameters. The main aspects of flight dynamics as performance, stability, and controllability, are addressed applying the concepts from classical aeronautical engineering adapted to the specificity of these aircrafts. In this work, a complete theoretical assessment of paragliders flight dynamics is provided. This is supposed to provide a base for future developments using flight test data, and a first focused material in order to incentivize the international aeronautical engineering community to dedicate some attention to this particular branch.A prática do vôo de paraglider tem se popularizado nas últimas três décadas, e o desenvolvimento da tecnologia associada ao esporte resultou avanços consideráveis em termos de desempenho e segurança. Entretanto, devido à finalidade desportiva dessas aeronaves, ainda são raros os estudos científicos aplicados ao tema. Os avanços tecnológicos no projeto de paragliders devem-se principalmente aos esforços da indústria , sendo que, apesar de existirem diversos fabricantes com anos de experiência, não é possível encontrar na literatura disponível trabalhos acerca da teoria de projeto de paragliders. Considerando a falta de informações específicas sobre engenharia de paragliders, uma linha de pesquisa ligada a área de dinâmica de vôo aplicada está sendo desenvolvida no intuito de explicar o vôo de paraglider e, principalmente, relacionar as características de vôo aos parâmetros de projeto dessas aeronaves. Os principais aspectos relacionados à dinâmica de vôo como o desempenho, a estabilidade e a controlabilidade serão investigados aplicando-se conceitos clássicos da engenharia aeronáutica adaptados às singularidades destas aeronaves. Neste trabalho é feita uma análise completa da dinâmica de vôo dos paragliders. Com isso, tem-se uma base para futuros desenvolvimentos com base em dados de ensaio e um primeiro material no sentido de incentivar a comunidade aeronáutica internacional a dedicar atenção a este campo em particular.
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Stanfield, Robin. "Influence of flight-path variability of conditions upon in-flight icing." Thesis, Cranfield University, 2008. http://hdl.handle.net/1826/3530.
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In design and development of aircraft, standard practice uses `the icing design
envelopes' to select atmospheric conditions for modelling icing encounters.
Over the duration of these encounters, atmospheric conditions are assumed
to be constant and to exhibit no variability. In reality variability exists, to an
extent where it may adversely affect the severity of ice accretions beyond that
identified by ground-based modelling. Similarly, certain tools and systems
employed by industry may sacrifice efficiency & effectiveness in neglecting
the variability that exists.
This project considered what operational and safety bene ts might be derived
from an enhanced knowledge of ice accretion under more realistic, variable
conditions; in contrast with a reference case identified to have equivalent
constant conditions. In doing so, variable encounters were modelled experimentally
in an icing tunnel to compare against a constant-condition reference;
aerodynamic penalty was assessed numerically using CFD, allowing a comparison
to be made between variable and constant-condition profiles; and
desk-research considered variable conditions in the context of existing and
emerging technology.
Considerable differences were observed between variable profiles themselves
and with the reference profile, with aerodynamic penalty being considerably
enhanced for 25% of variable cases, and considerably reduced for a further
25%.
Desk-research suggests that in understanding variability, to reduce costs asso-
iciated with aircraft icing, more realistic ground-based modelling capabilities
could reduce the need for natural
flight-testing in the long term, though this
would require substantial enhancement to current numerical prediction capabilities.
Similarly, the power applied to ice protection systems could be
tailored more speci cally to demand, enhancing e ciency. On the basis of
current instrumentation, this would first require development of more accurate
and robust LWC measurement systems.
It was therefore recommended that specialists in meteorology, icing physics,
ice protection systems and aerodynamics; conduct more extensive research
towards understanding variability and assessing its potential to enhance
flight-safety, whilst simultaneously reducing cost.
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Bylander, Ulf. "Flight Path Simulation Application : A flight simulator for charged particle transport." Thesis, Uppsala universitet, Högenergifysik, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-227759.
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CTF3 is a test facility for a new CLIC high energy linear collider. For this beamsteering and beam focusing is vital. Because physically running a beamline and changingsetup is expensive and takes much effort it is beneficial to use a simulator for thebeamline. The transportation of the beam through the beamline can be representedwith matrix multiplications and for this reason MATLAB is a fitting environment tosimulate in. A Flight Path Simulator was written in MATLAB and was succefullyimplemented and tested for the CALIFES beamline of the two-beam test stand that ispart of the CTF3 facility.
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Zorro, Sara Marques. "Pilots performance and flight safety: flight physiology in unpressurized aircraft cabins." Master's thesis, Universidade da Beira Interior, 2012. http://hdl.handle.net/10400.6/2002.
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Light aviation pilots are exposed to many different environmental situations due to the nonpressurized and non-acclimatized aircraft cabin. Some of those variations can push the human body to some limits, which associated with psychological factors may culminate in incidentes or even fatalities. Actually, a literature review on this theme suggests that a significant part of the incidents and fatalities, within the light aviation that uses non-pressurized aircraft
cabins, are related to the human factor. This analysis might bring up a concealed but
significant and worrying phenomenon in terms of flight safety: changes of pilot performance in the amendment of psychological and physiological parameters, concerning to diferente stress levels and to pressure variations during the various flight stages, respectively. This may
be a concerning situation due to the disparity of human body reaction between diferente pilots to the same flight conditions. Nature, both in terms of environmental factors, as pressure and temperature, or in human physiological and psychological behaviour, during the
different flight phases, is unpredictable. Therefore, it is very difficult to establish safety boundaries.
This study general objective is to analyse the influence of flight environmental conditions and pilots psychophysiological parameters on task performance, during different flight situations, considering some of his everyday habits. To this end, a statistical analysis of a survey, regarding specific questions about the need for pilot’s attention monitoring systems, was
made, and, in parallel, a portable and ergonomic monitoring system was built. This system equipment records cerebral oximetry, to study the hypoxia phenomenon and its importance, electrocardiography (ECG), and electroencephalography (EEG), in order to establish a correlation between the influence of mental workload and other physiological parameters during different flight stages.
The specific purpose of this study is to define physiological limits for each pilot, through simulation tests contemplating different flight scenarios, in order to create an on board alert system to prevent possible incidents. With this research is also intended to suggest that a potential restriction on pilots licensing
legislation for light aviation, within physiological limits definitions, would be a positive contribution to a safer flight environment.Os pilotos de aviação ligeira estão expostos a diferentes situações ambientais devido às cabines não pressurizadas e não climatizadas. Algumas dessas variações podem levar o corpo humano aos seus limites, que associados a fatores psicológicos podem culminar em incidentes ou até mesmo fatalidades. Na verdade, uma revisão da literatura sobre o tema sugere que uma parte significativa dos incidentes e acidentes neste tipo de aviação, estão relacionados com o fator humano. Esta análise pode revelar um fenómeno oculto, mas significativo e preocupante em termos de segurança de voo: as mudanças de desempenho dos pilotos aquando da alteração de parâmetros psicológicos e fisiológicos, referentes a diferentes níveis de stress e variações de pressão durante as diferentes fases do voo, respetivamente. Esta pode ser uma situação preocupante devido à disparidade da reação do corpo humano entre pilotos diferentes, para as mesmas condições de voo. A natureza, quer em termos de fatores ambientais, como a pressão e a temperatura, quer a nível de comportamento fisiológico e psicológico humano, durante as diferentes fases de voo, é imprevisível. Portanto, torna-se muito difícil estabelecer limites de segurança. O objetivo geral deste trabalho consiste em analisar a influência das condições ambientais de voo e dos parâmetros psicofisiológicos do piloto sobre o desempenho de tarefas, durante situações de voo diferentes, considerando alguns dos seus hábitos quotidianos. Para este fim, foi feita uma análise estatística a um inquérito sobre questões específicas referentes à necessidade de sistemas de monitorização da atenção do piloto, e, em paralelo, foi construído um sistema portátil e ergonómico de monitorização. Este permite registar a oximetria cerebral, para estudar o fenómeno da hipoxia e a sua importância, ECG e EEG, a fim de se estabelecer uma correlação entre a influência da carga de trabalho mental e outros parâmetros fisiológicos, durante as diferentes fases de voo. O objetivo específico deste estudo é definir os limites fisiológicos de cada piloto, por meio de testes de simulação de voo, contemplando cenários diferentes, a fim de criar um sistema de alerta a bordo para evitar possíveis incidentes ou acidentes. Com esta investigação pretende-se também sugerir que uma eventual restrição na legislação referente ao licenciamento de pilotos de aviação ligeira, dentro das definições dos limites fisiológicos, seria uma contribuição positiva para um ambiente de voo mais seguro.
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Shukla, Poorva Jahnukumar. "Active Flight Path Control for an Induced Spin Flight Termination System." Thesis, Virginia Tech, 2017. http://hdl.handle.net/10919/78881.
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In this thesis, we describe a method for controlling the cycle-averaged velocity direction of a fixed-wing aircraft in an unpowered, helical descent. While the aircraft propulsion system is disabled, either intentionally or due to a failure, the aerodynamic control surfaces (aileron, elevator, and rudder) are assumed to be functional. Our approach involves two steps: (i) establishing a stable, steady, helical motion for which the control surfaces are not fully deflected and (ii) modulating the aircraft control surfaces about their nominal positions to ``slant'' the helical flight path in a desired direction relative to the atmosphere, whether to attain a desired impact location, to counter a steady wind, or both. The effectiveness of the control law was evaluated in numerical simulations of a general transport model (GTM).Master of Science
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Compton, Timothy James Shauck Maxwell Eustace. "Flight performance testing of ethanol/100LL fuel blends during cruise flight." Waco, Tex. : Baylor University, 2008. http://hdl.handle.net/2104/5150.
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Burkland, Katharine E. "Hitting Turbulence: A Crisis Management Analysis of ValuJet Flight 592, Trans World Airlines Flight 800, and EgyptAir Flight 990." Thesis, Boston College, 2013. http://hdl.handle.net/2345/3023.
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Thesis advisor: Donald FishmanThe purpose of this thesis is two-fold: to analyze the corporate responses of three major airplane crashes that occurred in the 1990s, and to examine how the strategies that each airline used and the nature of the crisis environments both served to help, and hurt, the companies’ futures. ValuJet Flight 592, Trans World Airlines Flight 800 and EgyptAir Flight 990 will be analyzed through the lens of two prominent crisis communication theories, Fink’s stage analysis theory and Benoit’s image restoration strategies, in order to provide a comprehensive assessment of each crisis. I will then give insight as to the effectiveness of each airline in response to its crash, keeping in mind the unique environment that surrounded each situation. ValuJet made poor crisis management decisions that, when combined with its lack of satisfactory safety standards both before and after the crash of Flight 592, irreparably damaged the airline’s public image. TWA, like ValuJet, made errors in its strategy choices after the crash of Flight 800, but was able to escape blame and restore public confidence because of the heavy media focus on the unsuccessful criminal investigation. EgyptAir made appropriate crisis management choices after the crash of Flight 990, and also took advantage of the tense political situation in which no obvious regulating presence exerted authority, and thus successfully evaded responsibility for its crash
Thesis (BA) — Boston College, 2013
Submitted to: Boston College. College of Arts and Sciences
Discipline: Communication Honors Program
Discipline: College Honors Program
Discipline: Communication
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Chakravorty, Samya. "Role of the Drosophila Melanogaster Indirect Flight Muscles in Flight and Male Courtship Song: Studies on Flightin and Mydson Light Chain - 2." ScholarWorks @ UVM, 2013. http://scholarworks.uvm.edu/graddis/1.
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Complex behaviors using wings have facilitated the insect evolutionary success and diversification. The Drosophila indirect flight muscles (IFM) have evolved a highly ordered myofilament lattice structure and uses oscillatory contractions by pronounced stretch activation mechanism to drive the wings for high powered flight subject to natural selection. Moreover, the IFM is also utilized during small amplitude wing vibrations for species-specific male courtship song (sine and pulse), an important Drosophila mating behavior subject to sexual selection. Unlike flight, the contractile mechanism and contribution of any muscle gene in courtship song is not known. To gain insight into how separate selection regimes are manifested at the molecular level, we investigated the effect on flight and mating behaviors of mutations in two contractile proteins essential for IFM functions: an IFM-specific protein, flightin (FLN), known to be essential for structural and mechanical integrity of the IFM, and a ubiquitous muscle protein, myosin regulatory light chain (MLC2), known to enhance IFM stretch activation.
Comparison of FLN sequences across Drosophila spp., reveal a dual nature with the N-terminal region (63 aa) evolving faster (dN/dS=0.4) than the rest of the protein (dN/dS=0.08). A deletion of the N-terminal region (fln�N62) resulted in reduced IFM fiber stiffness, oscillatory work and power output leading to a decreased flight ability (flight score: 2.8±0.1 vs 4.2±0.4 for fln+ rescued control) despite a normal wing beat frequency. Interestingly, the FLN N-terminal deletion reduced myofilament lattice spacing and order suggesting that this region is required to improve IFM lattice for enhancing power output and flight performance. Moreover, fln�N62 males sing the pulse song abnormally with a longer interpulse interval (IPI, 56±2.5 vs 37±0.7 ms for fln+) and a reduced pulse duty cycle (PDC, 2.6±0.2 vs 7.3±0.2 % for fln+) resulting in a 92% reduction in their courtship success. This suggested that FLN N-terminal region fine-tunes sexually selected song parameters in D. melanogaster, possibly explaining its hypervariability under positive selection. That FLN N-terminal region is not essential but required to optimize IFM functions of both flight and song, indicate that FLN could be an evolutionary innovation for IFM-driven behaviors, possibly through its role in lattice improvement.
Mutations of the highly conserved MLC2 [N-terminal 46 aa deletion (Ext), disruption of myosin light chain kinase phosphorylations (Phos), and the two mutations put together (Dual)] are known to impair or abolish flight through severe reductions in acto-myosin contractile kinetics and magnitude of the stretch activation response. Unlike FLN, these MLC2 mutations do not show a pleitropic effect on flight and song. Flight abolished Phos and Dual mutants are capable of singing suggesting that these mutations affect song minimally compared to flight. Moreover, unlike FLN, none of these mutations affect interpulse interval, the most critical sexually selected song parameter in Drosophila. Also, in contrary to the known additive effects of Ext and Phos in the Dual mutant on flight wing beat frequency, a subtractive effect on sine song frequency is found in this study. That mutations in MLC2 are manifested differently for song and flight suggest that stretch activation plays a minimal or no role in song production.
The results in this study suggest that the conserved regions of FLN and MLC2 are essential to support underlying IFM contractile structure and function necessary for flight, whereas the fast evolving FLN N-terminal region optimizes IFM's biological performance in flight and species-specific song possibly under positive selection regime.
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Black, Prudence. "Lines Of Flight: The Design History of the Qantas Flight Attendants' Uniform." University of Sydney, 2009. http://hdl.handle.net/2123/5397.
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Doctor of Philosophy(PhD)This thesis maps the sixty year history of the Qantas flight attendants’ uniform. It figures the Qantas uniform as a prism through which to explore a history of modern Australian fashion and design, and the social and cultural web that gives life to the image of the Qantas flight attendant, rather than a history of the airline itself. Qantas, with its humble origins in the rural town of Longreach, Queensland, became the national carrier when it combined interests with Britain’s Imperial Airways to form Qantas Empire Airways in 1934. From the time the first female Qantas flight hostess appeared on board in 1948, the aircraft aisle became a 'catwalk for the image-makers'. It is particularly important to the role of the flight hostess, later the flight attendant, that the dress of the cabin crew, although clearly defined as uniforms, also responded to current fashion from the beginning of this history. Although the story of Qantas has been well documented, this thesis will focus on the uncharted area of the evolving design history of flight uniforms from the clinical white dress of the 1940s, through the military designs of the 1950s and the synthetics and stilettos of the 1960s, right through to the corporate designs of the present day. The analysis of such corporate design is a relatively new field. This study uses the flight attendants’ uniform to chart the links between the Australian fashion and textile industry and with militarism, versions of Australian nationalism and cosmopolitanism, the corporate world and the role of international designers in Australian design history. While the method of this thesis is largely archival, meticulously detailing the changing facets of the Qantas uniforms and unfolding those details into an engagement with these historical context, there are other theoretical influences on this study. In particular, it is underpinned by the ‘semiotics of uniformity’ drawn from fashion and design studies and by an equal focus on discourse analysis. The flight hostess’s uniform was always a complex ‘articulation of discourses’ as national image had to be played off against international trends, dominant and emerging gender norms, and the language of professional 'decorum' for people with high levels of responsibility and public exposure. Across each of these registers, the frisson of glamour was also a factor, morphing across this history from images of modernism and internationalism via the quasi-erotics of uniform fetishism into ‘postmodern’ performativity.
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Doepke, Edward Brady. "DESIGN AND FLIGHT TESTING OF A WARPING WING FOR AUTONOMOUS FLIGHT CONTROL." UKnowledge, 2012. http://uknowledge.uky.edu/me_etds/20.
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Inflatable-wing Unmanned Aerial Vehicles (UAVs) have the ability to be packed in a fraction of their deployed volume. This makes them ideal for many deployable UAV designs, but inflatable wings can be flexible and don’t have conventional control surfaces. This thesis will investigate the use of wing warping as a means of autonomous control for inflatable wings. Due to complexities associated with manufacturing inflatable structures a new method of rapid prototyping deformable wings is used in place of inflatables to decrease cost and design-cycle time. A UAV testbed was developed and integrated with the warping wings and flown in a series of flight tests. The warping wing flew both under manual control and autopilot stabilization.
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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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Lee, Hongchul. "Advanced aircraft service life monitoring method via flight-by-flight load spectra." Diss., Online access via UMI:, 2009.
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Thesis (Ph. D.)--State University of New York at Binghamton, Thomas J. Watson School of Engineering and Applied Science, Department of Mechanical Engineering, 2009.Includes bibliographical references.
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Black, Prudence Sarah. "Lines of flight the design history of the Qantas flight attendants' uniforms /." Connect to full text, 2008. http://hdl.handle.net/2123/5397.
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Thesis (Ph. D.)--University of Sydney, 2009.Title from title screen (viewed September 18, 2009) Submitted in fulfilment of the requirements for the degree of Doctor of Philosophy to the Dept. of Gender and Cultural Studies, Faculty of Arts. Degree awarded 2009; thesis submitted 2008. Includes bibliographical references.
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Kornfeld, Richard P. "The impact of GPS velocity based flight control on flight instrumentation architecture." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/9482.
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Thesis (Ph.D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.Includes bibliographical references (p. 191-195).
This thesis explores the use of velocity information obtained by a Global Positioning System (GPS) receiver to close the aircraft's flight control loop. A novel framework to synthesize attitude information from GPS velocity vector measurements is discussed. The framework combines the benefits of high-quality GPS velocity measurements with a novel velocity vector based flight control paradigm to provide a means for the human operator or autopilot to close the aircraft flight control loop. Issues arising from limitations in GPS as well as the presence of a human in the aircraft control loop are addressed. Results from several flight tests demonstrate the viability of this novel concept and show that GPS velocity based attitude allows for equivalent aircraft control as traditional attitude. Two possible applications of GPS velocity based attitude, an autopilot and a tunnel-in- the-sky trajectory guidance system, are demonstrated in flight. Unlike traditional autopilot and trajectory guidance systems, these applications rely solely on the information obtained from a single-antenna GPS receiver which makes them affordable to the larger General Aviation aircraft community. Finally, the impact of GPS velocity based flight control on the instrumentation architecture of flight vehicles is investigated.
by Richard P. Kornfeld.
Ph.D.
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SAAD, SHAIKH MUHAMMAD. "Quadrocopter Fuzzy Flight Controller." Thesis, Örebro universitet, Institutionen för naturvetenskap och teknik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:oru:diva-26421.
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Quadrocopter is an aerial vehicle platform which has become very popular among researchers in the recent past due to the advantages it offers over conventional helicopters. Quadrocopter is very simple and unique, but it is inherently unstable from aerodynamics point of view. In recent past researchers have proposed many control schemes for quadrocopter. In this thesis we present fuzzy logic controller for quadrocopter. After brief introduction brief hardware details are given that is used in this thesis. After that design procedure for the fuzzy controller is presented. Then the designed fuzzy controller is tested in Hardware In Loop (HIL) setup. The experimentation to validate the functionality and applicability of the designed controller were performed in contrained setup due to some technical problems. The results of the experiments were satisfactory and it is concluded that it is possible to stabilize quadrocopter with fuzzy logic controller.
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Jaehn, Florian. "Robust flight gate assignment." Frankfurt, M. Berlin Bern Bruxelles New York, NY Oxford Wien Lang, 2007. http://d-nb.info/987654136/04.
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Jaehn, Florian. "Robust flight gate assignment /." Frankfurt am Main [u.a.] : Lang, 2008. http://d-nb.info/987654136/04.
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Rysdyk, Rolf T. "Adaptive nonlinear flight control." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12108.
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Edmonds, V. L. "Gliding flight in megabats." Thesis, University of Cambridge, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.598761.
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Measurements of overall wing morphology were taken from two species of megabat, Rousettus aegyptiacus and Pteropus rodricensis. Differences in wing morphological parameters can largely be attributed to differences in flight behaviour and ecology. The cross-sectional geometry of the arm wing bones suggests adaptations to torsional loading as well as bending, or axial, loading during flight. The mechanical properties of the arm wing bones were also investigated using microhardness and cantilever bending techniques. The results were indicative of a low Young’s modulus, perhaps an adaptation to increase resilience and prevent buckling of the elongated bat wing bones during flight. 2D membranous wing profile models were constructed using these morphological parameters and wind tunnel test were used to measure aerodynamic force production at Re = 50 000. High life coefficients (CLmax about 2.4) and low L/D ratios (L/Dmax about 10.4) were consistent with values obtained from previous studies on membranous wings. The lift and drag curves also suggested the occurrence of leading edge separation and turbulent reattachment at high angles of attack. Smoke flow visualisation studies confirmed this phenomenon. They also indicated that the protruding spanwise spar improved performance at low angles of attack, yet began to interfere with the process of leading edge separation and turbulent reattachment at higher angles of attack. This strongly suggests that bats should tend to hold their wings at low angles of attack during glide and do not achieve the high lift coefficients of which they are capable. The interplay between leading edge flap angle, spar depth and chord-wise spar position is significantly important in regulating flow separation and force production during gliding flight in such a difficult flow regime.
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Fosnough-Osburn, Jennifer L. "Flight and Hand Imagery." Digital Commons @ Butler University, 1995. http://digitalcommons.butler.edu/grtheses/23.
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This paper will fill in the gaps in the current criticism regarding Toni Morrison's use of flight imagery and will also introduce a parallel line of criticism regarding Morrison's narrative focus on hands and hand gestures, an important and overlapping phenomenon in her novels. This phenomenon serves to elucidate Morrison's larger ideological project, in which she points out the core of one's life is creativity. Flight imagery and hand gestures work together to show a progression in Morrison's novels; thus, they must be considered together in order to completely comprehend characters and their actions as Morrison had intended.
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Aishwar, Ravichandran. "Aerodynamics of Bird Flight." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-154492.
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It is the objective of this thesis project to understand the physics behind the different modes of bird flight and to do numerical two dimensional simulations of pure plunging, pure pitching and combined pitch-plunging motion of an aerofoil. First, the different physical models used to understand the generation of thrust are explained. Then the numerical model used for the simulation is explained briefly. Then the results and analysis of the numerical simulations are presented.
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Wakley, Glenn Keith. "Space flight and bone." Thesis, University of Bristol, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.246296.
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Auger, Daniel Jarrett. "Modelling for flight control." Thesis, University of Cambridge, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.615016.
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Kale, Mangesh M. "Robust reconfigurable flight control." Thesis, University of Southampton, 2004. https://eprints.soton.ac.uk/45932/.
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From the perspective control practitioners, control of dynamics systems subjected to varying parameters is not a new topic. However systematic methods to accommodate such problems are relatively few and recent. This thesis addresses a subset of such problems falling under the nomenclature of Reconfigurable Control Systems in relation to flight control applications. A survey in the initial phase of research indicated a wide range of ad-hoc solutions with relatively brittle or non-existent theoretical guarantees towards to the stability of the entire system. Often the reconfigurable architecture consists of multiple conceptual components performing task of identifying system parameter changes, monitoring degradation in system performance and eventually finding some corrective action to regain lost performance. The change in system parameters if attributed to faults and damages to system, then the task of the control system is to achieve fault tolerance. Such fault tolerance is of high interest for flight control community since such a control system adaptation may lead to accommodation of real life faults during aircraft operation such as control surface damages, hydraulic actuation failures etc. The thesis work aims towards developing online control redesign methods capable of taking into account realistic requirements. The goals are 1) To find control input values in presence of faults. 2) Accommodate changes in performance criterion in presence of faults and, 3) Incorporate actuator limitations such as rate and position bounds. The research work is divided in three subparts. The initial phase consists of a study of existing solutions and methods capable of providing reconfigurable flight control architectures. This phase also covers some flight control literature relevant in the context of faults. Though the conclusions of this initial phase seem theoretically simple and straight forward, it is interesting to understand the amount of time and efforts invested by real world flight control practitioners to deduce these results. Essentially the work flow of this research work stems from practical requirement eventually leading to theoretical developments that can approximate the requirements often demanded by the people in field. The second phase consists of study and application of existing Model Predictive Control methods to the field of reconfigurable flight control. MPC has been successful in major complex control problems due to its online constrained optimisation methodology. Along-with certain theoretical extensions it is well capable of providing a successful means to redesign control action online in presence of failures. Simulation studies of sufficient fidelity and complexity on a full envelop fighter aircraft nonlinear model prove such control reconfiguration capabilities of MPC. Some new extensions of MPC have been developed to show it performing in a superior manner to conventional nominal formulations. The third phase of the research work focuses on further theoretical developments in the field robust adaptive control in MPC frame of operation. A new MPC formulation is derived which can accommodate constraints, uncertainty and constant disturbances (due to failed inputs). The novelty lies in the theoretical properties of this MPC as under certain conditions it is guaranteed to be asymptotically stable. This setup implements an optimization problem more complex than that of the nominal case. Typically, when disturbances and uncertainties are incorporated into the performance measure within MPC formulations, mini-max (worst-case) NP-hard problems can arise. The thesis contributes to the theory of robust synthesis by proposing a convex relaxation of a mini-max based MPC controller by adopting a Linear Matrix Inequality (LMI) optimisation formulation.
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Hovendon, Gabrielle. "Signs of Flight: Stories." Bowling Green State University / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=bgsu1394106931.
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Almbro, Maria. "Escape flight in butterflies /." Stockholm : Department of Zoology, Stockholm University, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:su:diva-25968.
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Price, William O'Neil. "Corona Onset in Flight." Thesis, Griffith University, 2009. http://hdl.handle.net/10072/366634.
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Corona on electrified conductors (power lines, transmission lines, and antennas) is a significant source of electromagnetic interference to aircraft. When corona occurs in radio frequency equipment, it usually signals the failure of the system to operate as designed. The Townsend integral, which describes breakdown in low-frequency non-uniform fields, was derived from the electron continuity equation. Predictions of corona onset were developed using new formulas for net ionization. Measurements of 60 Hz corona onset for an isolated cylindrical monopole were compared with these predictions. A corona onset criterion, which describes breakdown in non-uniform radio frequency (RF) fields, was also derived from the electron continuity equation. Measurements of corona onset at 300 MHz for the same isolated cylindrical monopole were compared with predictions. The results confirm that the derived breakdown criteria are good predictors of corona onset at both 60 Hz and 300 MHz for cylindrical geometries in the range 0:1 rp 10:0 cm torr. A discussion of the transition frequency between power frequency and high frequency corona onset is included. The argument is made that corona onset criteria developed for cylindrical geometries are useful for any geometry where the local electric field strength can be characterized.Thesis (PhD Doctorate)
Doctor of Philosophy (PhD)
Griffith School of Engineering
Science, Environment, Engineering and Technology
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Franěk, Lukáš. "Flight Management System Model." Master's thesis, Vysoké učení technické v Brně. Fakulta elektrotechniky a komunikačních technologií, 2011. http://www.nusl.cz/ntk/nusl-219075.
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Diplomová práce shrnuje nejdůležitější informace o letectví, jako například základní používané termíny, popis letových fází apod. V této práci je popsán flight management system, jeho funkce a schopnosti vytvořit cenově příznivý a současně absolutně spolehlivý letový plán. V další části práce je nastíněna důležitost předpovědi počasí pro bezpečnou a současně cenově příznivou leteckou dopravu. Tato práce je vytvořena v programu Matlab a všechny bloky jsou naprogramovány jako m-funkce. Důležité části kódu jsou z důvodu názornosti zobrazeny jako vývojové diagramy. Praktická část práce je rozdělena do několika podkapitol, kde každá podkapitola popisuje jeden blok z blokového schématu pro výpočet nejistoty odhadované doby příletu. Současně je zde vysvětlena funkce ostatních bloků pro plánování letu, předpověď počasí, kombinování větrů a výpočet odhadnuté doby příletu a její nejistoty.
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Smart, Edward. "Detecting abnormalities in aircraft flight data and ranking their impact on the flight." Thesis, University of Portsmouth, 2011. https://researchportal.port.ac.uk/portal/en/theses/detecting-abnormalities-in-aircraft-flight-data-and-ranking-their-impact-on-the-flight(d9678b70-41e6-459a-82fb-ba2d12a0f971).html.
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To the best of the author’s knowledge, this is one of the first times that a large quantity of flight data has been studied in order to improve safety. A two phase novelty detection approach to locating abnormalities in the descent phase of aircraft flight data is presented. It has the ability to model normal time series data by analysing snapshots at chosen heights in the descent, weight individual abnormalities and quantitatively assess the overall level of abnormality of a flight during the descent. The approach expands on a recommendation by the UK Air Accident Investigation Branch to the UK Civil Aviation Authority. The first phase identifies and quantifies abnormalities at certain heights in a flight. The second phase ranks all flights to identify the most abnormal; each phase using a one class classifier. For both the first and second phases, the Support Vector Machine (SVM), the Mixture of Gaussians and the K-means one class classifiers are compared. The method is tested using a dataset containing manually labelled abnormal flights. The results show that the SVM provides the best detection rates and that the approach identifies unseen abnormalities with a high rate of accuracy. Furthermore, the method outperforms the event based approach currently in use. The feature selection tool F-score is used to identify differences between the abnormal and normal datasets. It identifies the heights where the discrimination between the two sets is largest and the aircraft parameters most responsible for these variations.
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Schuite, Gerard. "FLIGHT TESTING IS OUR PROFESSION – AN OVERVIEW OF TEST FLIGHT AND DEVELOPMENT CENTRE." International Foundation for Telemetering, 1999. http://hdl.handle.net/10150/608309.
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International Telemetering Conference Proceedings / October 25-28, 1999 / Riviera Hotel and Convention Center, Las Vegas, NevadaThe aim of this presentation is to give an overview of TFDC’s capabilities as a flight test centre and the approach with respect to the management of flight testing.
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Olson, Nicholai Kenneth Keeney. "Validation and Uncertainty Quantification of Doublet Lattice Flight Loads using Flight Test Data." Thesis, Virginia Tech, 2018. http://hdl.handle.net/10919/84345.
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This paper presents a framework for tuning, validating, and quantifying uncertainties for flight loads. The flight loads are computed using a Nastran doublet lattice model and are validated using measured data from a flight loads survey for a Cessna Model 525B business jet equipped with Tamarack® Aerospace Group’s active winglet modification, ATLAS® (Active Technology Load Alleviation System). ATLAS® allows for significant aerodynamic improvements to be realized by reducing loads to below the values of the original, unmodified airplane. Flight loads are measured using calibrated strain gages and are used to tune and validate a Nastran doublet-lattice flight loads model. Methods used to tune and validate the model include uncertainty quantification of the Nastran model form and lead to an uncertainty quantified model which can be used to estimate flight loads at any given flight condition within the operating envelope of the airplane. The methods presented herein improve the efficiency of the loads process and reduce conservatism in design loads through improved prediction techniques. Regression techniques and uncertainty quantification methods are presented to more accurately assess the complexities in comparing models to flight test results.Master of Science
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McClernon, Christopher K. "Stress effects on transfer from virtual environment flight training to stressful flight environments." Monterey, Calif. : Naval Postgraduate School, 2009. http://handle.dtic.mil/100.2/ADA501682.
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Dissertation (Ph.D. in Modeling, Virtual Environments, and Simulation)--Naval Postgraduate School, June 2009.Dissertation supervisor: McCauley, Michael E. "June 2009." Description based on title screen as viewed on July 14, 2009. DTIC Identifiers: Flight simulator, virtual environment, human physiology, transfer of training, human performance, stress coping, stress exposure training. Author(s) subject terms: Stress, training, transfer of training, flight simulator, virtual environment, human physiology, human performance, strain, stress coping, stress exposure training. Includes bibliographical references (p. 163-170). Also available in print.
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Harvey, William. "Investigating the configuration of a flight training device for visual flight rules navigation." Thesis, Federation University Australia, 2020. http://researchonline.federation.edu.au/vital/access/HandleResolver/1959.17/174503.
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The acquisition of pilot navigational skills utilising visual landmarks is a crucial skill that is required as part of Visual Flight Rules navigation towards obtaining a Private Pilot License. Due to the high cost of pilot training simulators, industry has identified a need for research in efficient utilisation of low-end, low cost personal compute flight simulators to assist in developing pilot skills. Analysis of the effectiveness of the use of such personal computer simulators depend on proper configuration determined by measurable errors to define simulator fidelity. To date, research has shown that the configuration of these simulators appears to have been done in an ad-hoc fashion and not in a scientific fashion. Therefore, the problem that needed to be solved was how to effectively configure such simulators. This thesis research attempted to solve this problem and present the process for effectively configuring a personal computer simulator, or flight training device, capable of successful Visual Flight Rules navigation. The simulator was configurated utilising a process that followed an interpretation of the Design Science research method, and an error correction model to determine the errors in the simulator configuration. This was done by comparing two probability distributions to measure the maximum error variable distance in order to configure a simulator suitable for the acquisition of Visual Flight Rules navigation piloting skills required for obtaining a Private Pilot Licence in Australia. This error identification method was then used to indicate simulator configuration efficiency and fidelity in order to achieve a minimum suitable configuration and setup. Further application of the findings of this research could potentially lead to the configuration of different types of non-aviation simulators, in particular Part-Task-Trainers and other training devices, including Virtual Reality Augmented Reality devices utilising various types of platforms such as Windows, Apple, and Android.Doctor of Philosophy
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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 considered through their effect on the trim and stability of the overall system. The equations of motion are modeled through a quasi coordinate Lagrangian scheme while the aerodynamic forces are calculated using quasi-steady potential flow aerodynamics. Trim solutions are calculated using periodic shooting for several different conditions including hover, climb, and forward flight. The stability of the trim is calculated and examined using stroke-averaged and Floquet theory. Inflow and viscous effects are added and their effects on trim and stability examined. The effects of varying hinge location and the inclusion of stroke deviation in the wing kinematics are also explored. The stroke-averaged system was not found to be a direct replacement for the periodic system as the stability was different for the two systems. Inflow and viscosity were found to have large effects on the stability of the system and models accounting for the two should be included in future flight dynamic models.Master of Science
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Sagoo, Girish Kumar. "Pilot in loop assessment of fault tolerant flight control schemes in a motion flight simulator." Morgantown, W. Va. : [West Virginia University Libraries], 2008. https://eidr.wvu.edu/etd/documentdata.eTD?documentid=5800.
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Thesis (M.S.)--West Virginia University, 2008.Title from document title page. Document formatted into pages; contains xiv, 121 p. : ill. (some col.), col. map. Includes abstract. Includes bibliographical references (p. 116-121).