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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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Scamps, Alexander. "Development of a Variable Stability Flight Simulation Facility Re-engineering of Flight Control Loading and Motion Systems." Thesis, The University of Sydney, 2003. http://hdl.handle.net/2123/567.
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A Variable Stability Flight Simulator is being developed in the School of Aerospace, Mechanical and Mechatronic Engineering at the University of Sydney, Australia. The device is being developed both as a teaching tool for use in flight mechanics courses in the department and as a research tool. It is reasonable to state that learning is enhanced through the experience of concepts outside of the classroom environment. It is intended that the device will be integrated into the department�s teaching program in aircraft flight mechanics. Initial studies centred around a PC based flight simulation developed at the Cranfield College of Aeronautics in the United Kingdom. This system utilises a distributed architecture with several computers connected via Ethernet. It also employs a Primary Image three channel visual system. The system has been further enhanced by the addition of a Link flight simulator provided by the Royal Australian Air Force (RAAF). The RAAF had been using the simulator as a training tool for some years until it had become surplus to requirements. Most of the work in the project has centred around re-engineering this simulator into a viable research/education tool. The Cranfield system has been incorporated into the Link simulator�s hardware to provide a fixed base simulation. The majority of the work described in this thesis revolved around the re-engineering of the flight control loading and motion systems. Previously these items were controlled by analogue circuitry with minimal digital interfaces to the main simulation software. The systems have been re-designed to replace much of the single model analogue circuitry with re-configurable digital control software. Doing so allows changes to be made to the systems in real time through a software interface. The software resides on a common computer that extensively interfaces with the rest of the simulation. To support the hardware involved and to provide for system operation and safety, an extensive Supervisory system has also been implemented. This system along with the motion and control loading software has been implemented in the Matlab / Real-Time Workshop environment. This gives the capability of making real-time changes to any part of the overall simulation. A variable stability module (vsm) is under development. The addition of this module will allow changes to be made to the simulation itself in real-time. The simulator is now functional with the motion and control loading systems operating as designed. Tuning of both systems has been done subjectively by the author. An initial objective analysis of the motion system has been undertaken in an attempt to verify the fidelity of the motion cues generated. A significant outcome of this project has been to create a safe, easily maintainable, re-configurable flight simulator from a large, complex, legacy system. The facility now forms a significant research and teaching tool in areas such as flight mechanics, propulsion, aircraft handling qualities and human factors.
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Scamps, Alexander. "Development of a Variable Stability Flight Simulation Facility Re-engineering of Flight Control Loading and Motion Systems." University of Sydney. Aerospace, Mechanical, 2003. http://hdl.handle.net/2123/567.
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A Variable Stability Flight Simulator is being developed in the School of Aerospace, Mechanical and Mechatronic Engineering at the University of Sydney, Australia. The device is being developed both as a teaching tool for use in flight mechanics courses in the department and as a research tool. It is reasonable to state that learning is enhanced through the experience of concepts outside of the classroom environment. It is intended that the device will be integrated into the department�s teaching program in aircraft flight mechanics. Initial studies centred around a PC based flight simulation developed at the Cranfield College of Aeronautics in the United Kingdom. This system utilises a distributed architecture with several computers connected via Ethernet. It also employs a Primary Image three channel visual system. The system has been further enhanced by the addition of a Link flight simulator provided by the Royal Australian Air Force (RAAF). The RAAF had been using the simulator as a training tool for some years until it had become surplus to requirements. Most of the work in the project has centred around re-engineering this simulator into a viable research/education tool. The Cranfield system has been incorporated into the Link simulator�s hardware to provide a fixed base simulation. The majority of the work described in this thesis revolved around the re-engineering of the flight control loading and motion systems. Previously these items were controlled by analogue circuitry with minimal digital interfaces to the main simulation software. The systems have been re-designed to replace much of the single model analogue circuitry with re-configurable digital control software. Doing so allows changes to be made to the systems in real time through a software interface. The software resides on a common computer that extensively interfaces with the rest of the simulation. To support the hardware involved and to provide for system operation and safety, an extensive Supervisory system has also been implemented. This system along with the motion and control loading software has been implemented in the Matlab / Real-Time Workshop environment. This gives the capability of making real-time changes to any part of the overall simulation. A variable stability module (vsm) is under development. The addition of this module will allow changes to be made to the simulation itself in real-time. The simulator is now functional with the motion and control loading systems operating as designed. Tuning of both systems has been done subjectively by the author. An initial objective analysis of the motion system has been undertaken in an attempt to verify the fidelity of the motion cues generated. A significant outcome of this project has been to create a safe, easily maintainable, re-configurable flight simulator from a large, complex, legacy system. The facility now forms a significant research and teaching tool in areas such as flight mechanics, propulsion, aircraft handling qualities and human factors.
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Magnusson, Nählinder Staffan. "Flight Simulator Training : Assessing the Potential." Doctoral thesis, Linköpings universitet, Institutionen för ekonomisk och industriell utveckling, 2009. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-17546.
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Mental workload is an important concept and has been proven to be a precursor to situation awareness and operative performance. This thesis describes methods to measure mental workload through self-ratings and psychophysiological measurements. Similarities and differences in psychophysiological reactions and rated mental workload between simulated and real flights are described. The consequences of such similarities and differences are discussed and its possible effect on training potential. A number of empirical studies are presented. They describe the experience and the psychophysiological reactions of pilots flying in a simulator and in real flight. In most cases, the reactions are similar – there is a high degree of accordance in rated mental workload and psychophysiological reaction between simulated and real flight. The studies show, that even though the responses are similar, there are also interesting differences. In one study, the pilots have consistently lower heart rate, higher heart rate variability and less eye movements in the simulator than in real flight. In another study, during certain events, the pilots have higher heart rate in the simulator than in real flight. The results are important in order to understand the training potential of simulators from a human factors perspective. Further, two measurement equipments for psychophysiological recording are compared and various psychophysiological measures are tested in applied settings. The thesis also discusses some methodological aspects, such as methods to create reliable and valid variables in dynamic applied research and how to deal with individual differences. An algorithm is suggested to remove differences between individuals. This facilitates the finding of within-participant effects. Finally, results from a study on embedded training tools are presented. In this study, student pilots and instructors rated the usefulness of several embedded training tools. These tools were built into a simulator to facilitate learning and teaching by illustrating concepts that can be difficult to understand. The results show clearly that such training tools are appreciated by both students and instructors. Well implemented, thoroughly selected training tools can dramatically improve the training potential of future training simulators.<br>Mental arbetsbelastning är ett viktigt begrepp som har visat sig kunna predicera bland annat situationsmedvetande och operativ prestation. Avhandlingen visar olika sätt att mäta mental arbetsbelastning, bland annat genom självskattningar och psykofysiologiska mått. Skillnader och likheter i psykofysiologisk reaktion och skattad mental arbetsbelastning mellan simulerad och verklig flygning beskrivs. Betydelsen av sådana skillnader och dess konsekvenser för möjligheten till träningseffekt diskuteras. Ett antal studier beskrivs som handlar om upplevelsen och de fysiologiska reaktionerna hos piloter som flyger i simulatorer och i verklig flygning. I de flesta fall förekommer likartade reaktioner i simulatorn som i verkligheten. Det finns en stor grad av överensstämmelse både vad gäller psykofysiologisk reaktion och upplevd mental arbetsbelastning. Men studierna visar också att även om reaktionerna är lika, så skiljer de sig också åt på några viktiga punkter. Piloter som genomför ett uppdrag i en simulator är inte lika stressade som i verklig flygning. De har lägre puls och högre pulsvariabilitet. I vissa enstaka fall har piloterna högre puls i simulatorn än i motsvarande fall i verklig flygning. Resultaten är viktiga för att förstå hur nyttan av simulatorer kan utvärderas ur ett användningsperspektiv. Vidare jämförs två olika utrustningar för psykofysiologisk mätning och olika psykofysiologiska mått testas i tillämpade miljöer. Olika utrustningar för att mäta psykofysiologisk reaktion jämförs och olika psykofysiologiska mått diskuteras. Avhandlingen problematiserar olika metodologiska aspekter, såsom metoder för att skapa reliabla och valida mått i dynamisk tillämpad forskning, samt metoder för att hantera individuella skillnader. En algoritm föreslås för att eliminera olikheter mellan individer. Den underlättar upptäckandet av inomindividseffekter. Avslutningsvis presenteras resultaten från en studie avsedd att mäta inställning till ett antal inbyggda pedagogiska träningsverktyg. De verktyg som fanns inbyggda i simulatorn var framtagna för att förbättra träningseffekten genom att konkretisera koncept och relationer som kan vara svåra att förstå. Pilotelever och instruktörer fick flyga i en simulator och gavs sedan möjligheten att pröva olika träningsverktyg. Resultaten visar tydligt ett positivt intresse för träningsverktygen både från elever och från instruktörer. Väl implementerade noggrant utvalda träningsverktyg, kan kraftigt förbättra träningseffektiviteten i framtida träningssimulatorer.
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Kenney, Laurence P. J. "Flight simulator for special educational needs." Thesis, University of Salford, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.357202.
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Sikström, Tilda. "Flight Simulator Integration in Test Rig." Thesis, KTH, Flygdynamik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-299413.
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Integrating hardware in simulations is useful in many applications, for example to investigate the performance of an aircraft with the non-ideal response of a physical system. This thesis aims to integrate a flight simulator, JSBSim, with an actuator test rig, FLUMES Iron Bird. Two aircraft models were replicated in JSBSim, a passenger aircraft and a delta winged fighter aircraft. The models were analyzed to ensure proper flight performance in regards to stability. The stability analysis was conducted from both the aerodynamic data provided as well as through state-space theory. The fighter aircraft was unstable in the subsonic region and in need of a flight control system to fly properly. The integration with the test rig was implemented using Simulink S-functions and a real-time target computer ensuring synchronous communication with the actuator test rig. The passenger aircraft was successfully integrated and tested with the actuator test rig.<br>Att integrera hårdvara med simuleringar är behjälpligt i många situationer, exempelvis för att undersöka hur ett flygplan reagerar med ett icke-idealt svar från ett fysiskt system. I det här examensarbetet är målet att utveckla ett gränssnitt mellan en flygsimulator, JSBSim, och en aktuatortestrigg, FLUMES Iron Bird. Två flygplansmodeller skapades i JSBSim, ett passagerarflygplan och ett stridsflygplan. För att vara säker på flygplansmodellernas prestanda analyserades modellerna med avseende på stabilitet. Stabilitetsanalysen beräknades både utifrån aerodynamisk data såväl som utifrån tillståndsanalys, där både statisk och dynamisks stabilitet inkluderades. Stridsflyget var instabilt i underljudsfart och behöver därför ett styrsystem för att vara flygbart. Integreringen med testriggen utfördes i Simulink med hjälp av S-funktioner och en realtidsdator för att garantera synkronisk kommunikation mellan flygsimulatorn och testriggen. Det modellerade passagerarflygplanet kunde integreras och testas med testriggen.
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Helgesson, Fredrik. "Analysis of a flight mechanics simulator." Thesis, KTH, Flygdynamik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-265616.
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Aircraft design is an act of art requiring dedication and careful work to ensure good results. An essential tool in that work is a flight mechanics simulator. Such simulators are often built up of modules/models that are executed in a sequential order in each time iteration. This project aims to analyze potential improvements to the model execution order based on the dependency structure of one such simulator. The analysis method Design Structure Matrix (DSM), was used to define/map the dependencies and then Binary Linear Programming (BLP) was utilized to find five new potentially improved model orders to minimize the number of feedbacks from one iteration to the next one. Those five proposed execution orders were next compared and evaluated. The result is a model order that reduce the number of models receiving feedbacks from the previous iteration from 13 to 6, with insignificant changes in the precision of the simulator.<br>Vid flygplanskonstruktion krävs hårt och noggrant arbete för att säkerställa gott resultat. Ett oumbärligt verktyg är då en flygmekanisk simulator. Den typen av simulatorer är ofta uppbyggda av moduler/modeller som exekveras i en bestämd sekventiellt ordning i varje tidsteg. Syftet med detta projekt är att undersöka möjliga förbättringar av exekverings ordningen av de olika modellerna i en existerande simulator, baserat på beroendestrukturen. Analysmetoden Design Structure Matrix (DSM) användes för att bestämma beroendestrukturen och sedan utnyttjades Binär Linjär Programmering (BLP) för att hitta fem förbättrade modellordningar med avseende på att minimera antalet modeller som erhåller indata från föregående tidsiteration. De fem förbättringsförslagen jämfördes och utvärderades. Resultatet är en modellordning som kan minska antalet återkopplande modeller från 13 till 6, med insignifikanta skillnader i precisionen av simulatorn.
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Elias, Joerg. "Advanced integrated helicopter flight simulator cockpit design." Thesis, Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/12469.
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Johansson, Daniel. "Extending a battlefield simulator with large scale terrain rendering and flight simulator functionality." Thesis, Linköping University, Department of Science and Technology, 2005. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-5623.
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<p>Simulation of modern battlefield scenarios on consumer PC:s deal with a number of limitations, many of them related to the limited performance of a normal PC compared to workstations and servers. Specifically, the visualization of realistic large scale outdoor environments is problematic because of the large amount of data required to describe its contents. This becomes especially problematic in simulations of fast moving vehicles such as aircrafts, where one needs to maintain high frame rates while having high visual detail for orientation and targeting. This thesis proposes a method of generating realistic outdoor environments from actual geological data and then rendering it efficiently using an improved level of detail algorithm within a proprietary battle simulation framework. We also show how to integrate an open source Flight Dynamics Model (FDM) into the simulation framework for future hybrid simulations involving aircrafts.</p>
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Vazquez, Alan Andrew. "Touch screen use on flight simulator Instructor/Operator Stations." Thesis, Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA239524.
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Thesis (M.S. in Information Systems)--Naval Postgraduate School, September 1990.<br>Thesis Advisor(s): Lind, Judith H. ; Mitchell, Thomas. Second Reader: Haga, William J. "September 1990." Description based on title screen as viewed on December 18, 2009. Author(s) subject terms: Alternative Input, Touch Screen, Mouse, Trackball, Instructor/Operator Station, IOS, Data Entry Devices, Flight Simulators, User-Computer Interface. Includes bibliographical references (p. 70-71). 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.<br>Doctor of Philosophy
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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.<br>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).
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Root, Eric. "A Re-Configurable Hardware-in-the-Loop Flight Simulator." Ohio University / OhioLINK, 2004. http://www.ohiolink.edu/etd/view.cgi?ohiou1090939388.
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O'Neill, Jennifer K. "Backdriving a full motion simulator using flight recorder data." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2000. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape3/PQDD_0015/MQ53325.pdf.
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Benet, C., M. Wickham, and J. Balzer. "THE COMSAT ATTITUDE AND ORBIT CONTROL SYSTEM FLIGHT SIMULATOR." International Foundation for Telemetering, 1986. http://hdl.handle.net/10150/615296.
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International Telemetering Conference Proceedings / October 13-16, 1986 / Riviera Hotel, Las Vegas, Nevada<br>The success of a communications satellite mission depends not only on the proper operation of the on-board Attitude and Orbit Control System (AOCS), but also on the complex interaction between the spacecraft and the ground control center.
In support of a satellite program from its inception to launch and throughout the inorbit life, COMSAT has developed a SATELLITE ATTITUDE AND ORBIT CONTROL SYSTEM FLIGHT SIMULATOR.
This paper describes the design and operations of the COMSAT FLIGHT SIMULATOR. The simulator is a real-time, high fidelity, operator interactive, spacecraft hardware in the loop system. The heart of the system is a high precision minicomputer in which the spacecraft dynamics, sensors, actuators and most likely failure modes are modeled. A significant feature of the simulator is a faithful duplication of the command and telemetry functions. The operator can send commands and review telemetered data in the same format as during the mission. The simulator operates in real-time and is flexible enough to either simulate or fully integrate parts of the flight hardware. Such is the case for instance for the on-board computer with its complex programmable control algorithms. However, flight hardware in the loop is in no way limited to any particular unit of the flight subsystem. The simulator can also be remotely linked to the ground station and use actual commands as direct inputs for its operation. A colorgraphics driven by the simulated dynamics displays the spacecraft motions and warns the operator of eventual losses of telemetry and command capabilities during attitude anomalies.
Following is a partial list of the FLIGHT SIMULATOR capabilities.
S Provide an independent means to evaluate and validate a control system design; S Support the development of Control Center (hardware and software) and serve as a training facility for the control operators; S Develop and verify the spacecraft sequence of events; S Help in developing and evaluating, in real time, the on-orbit Operational and Recovery Procedures;
S Maximize satellite life through maneuver optimization, and S Support the satellite mission throughout the spacecraft life, providing a test bed for flight anomaly investigation.
This last point is significant since, in general, a satellite operator has no guarantee as to the availability of a spacecraft manufacturer’s facility for the full duration of a satellite mission.
The COMSAT FLIGHT SIMULATOR is fully operational and is already supporting the STC/DBS (Satellite Television Corporation/Direct Broadcast Satellite) program. COMSAT concurrently developed a flight simulator for INTELSAT VI. These two simulators represent second-generation designs compared to the first real-time, hardwarein-the-loop simulator which was built for INTELSAT V.
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Rogerson, Stuart Peter. "Implementation of a distributed interactive simulation interface in a Sea King flight simulator." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1997. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp04/mq29371.pdf.
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Dennis, K. A. "An evaluation of the utility of a Personal Computer-based Aviation Training Device (PCATD) for private pilot's licence training." Thesis, Cranfield University, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.267495.
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Le-Ngoc, Luan. "Augmenting low-fidelity flight simulation training devices via amplified head rotations." Thesis, Loughborough University, 2013. https://dspace.lboro.ac.uk/2134/14441.
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Due to economic and operational constraints, there is an increasing demand from aviation operators and training manufacturers to extract maximum training usage from the lower fidelity suite of flight simulators. It is possible to augment low-fidelity flight simulators to achieve equivalent performance compared to high-fidelity setups but at reduced cost and greater mobility. In particular for visual manoeuvres, the virtual reality technique of head-tracking amplification for virtual view control enables full field-of-regard access even with limited field-of-view displays. This research quantified the effects of this technique on piloting performance, workload and simulator sickness by applying it to a fixed-base, low-fidelity, low-cost flight simulator. In two separate simulator trials, participants had to land a simulated aircraft from a visual traffic circuit pattern whilst scanning for airborne traffic. Initially, a single augmented display was compared to the common triple display setup in front of the pilot. Starting from the base leg, pilots exhibited tighter turns closer to the desired ground track and were more actively conducting visual scans using the augmented display. This was followed up by a second experiment to quantify the scalability of augmentation towards larger displays and field of views. Task complexity was increased by starting the traffic pattern from the downwind leg. Triple displays in front of the pilot yielded the best compromise delivering flight performance and traffic detection scores just below the triple projectors but without an increase in track deviations and the pilots were also less prone to simulator sickness symptoms. This research demonstrated that head augmentation yields clear benefits of quick user adaptation, low-cost, ease of systems integration, together with the capability to negate the impact of display sizes yet without incurring significant penalties in workload and incurring simulator sickness. The impact of this research is that it facilitates future flight training solutions using this augmentation technique to meet budgetary and mobility requirements. This enables deployment of simulators in large numbers to deliver expanded mission rehearsal previously unattainable within this class of low-fidelity simulators, and with no restrictions for transfer to other training media.
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Sherman, Kim L. "The design and construction of a hang glider flight simulator /." Online version of thesis, 1992. http://hdl.handle.net/1850/11260.
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Donati, Dario. "Analysis of aircraft load spectrum by means of flight simulator." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2015. http://amslaurea.unibo.it/9346/.
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Damage tolerance analysis is a quite new methodology based on prescribed inspections. The load spectra used to derive results of these analysis strongly influence the final defined inspections programs that for this reason must be as much as possible representative of load acting on the considered structural component and at the same time, obtained reducing both cost and time.
The principal purpose of our work is in improving the actual condition developing a complete numerical Damage Tolerance analysis, able to prescribe inspection programs on typical aircraft critical components, respecting DT regulations, starting from much more specific load spectrum then those actually used today. In particular, these more specific load spectrum to design against fatigue have been obtained through an appositively derived flight simulator developed in a Matlab/Simulink environment. This dynamic model has been designed so that it can be used to simulate typical missions performing manually (joystick inputs) or completely automatic (reference trajectory need to be provided) flights. Once these flights have been simulated, model’s outputs are used to generate load spectrum that are then processed to get information (peaks, valleys) to perform statistical and/or comparison consideration with other load spectrum. However, also much more useful information (loads amplitude) have been extracted from these generated load spectrum to perform the previously mentioned predictions (Rainflow counting method is applied for this purpose). The entire developed methodology works in a complete automatic way, so that, once some specified input parameters have been introduced and different typical flights have been simulated both, manually or automatically, it is able to relate the effects of these simulated flights with the reduction of residual strength of the considered component.
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Misovec, Kathleen. "The effect of flight simulator motion on modelled vestibular response." Thesis, Massachusetts Institute of Technology, 1986. http://hdl.handle.net/1721.1/83660.
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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1986.<br>Microfiche copy available in Archives and Barker.<br>Bibliography: leaves [133]-[134].<br>by Kathleen M. Misovec.<br>M.S.
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Joensen, Daniel Eide. "Let's Go--Home Depot : development of a management flight simulator." Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/12382.
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Olsson, Tobias, and Oscar Ullberg. "Mixed Reality for Gripen Flight Simulators." Thesis, Linköpings universitet, Medie- och Informationsteknik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-173831.
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This thesis aims to evaluate how different mixed reality solutions can be built and whetheror not it could be used for flight simulators. A simulator prototype was implemented usingUnreal Engine 4 with Varjo’s Unreal Engine plugin giving the foundation for the evaluations done through user studies. Three user studies were performed to test subjectivelatency with Varjo XR-1 in a mixed reality environment, test hand-eye coordination withVarjo XR-1 in a video see-through environment, and test the sense of immersion betweenan IR depth sensor and chroma key flight simulator prototype. The evaluation was seenfrom several perspectives, consisting of: an evaluation from a latency perspective on howa mixed reality solution would compare to an existing dome projector solution, how wellthe masking could be done when using either chroma keying or IR depth sensors, andlastly, which of the two evaluated mixed reality techniques are preferred to use in a senseof immersion and usability.The investigation conducted during the thesis showed that while using a mixed realityenvironment had a minimal impact on system latency compared to using a monitor setup.However, the precision in hand-eye coordination while using VST-mode was evaluated tohave a decreased interaction accuracy while conducting tasks. The comparison betweenthe two mixed reality techniques presented in which areas the techniques excel and wherethey are lacking, therefore, a decision needs to be made to what is more important for eachindividual use case while developing a mixed reality simulator.
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Fujizawa, Brian T. "Control Law Design and Validation for a Helicopter In-Flight Simulator." DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/240.
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In-flight simulation allows one aircraft to simulate the dynamic response of another aircraft. A control system designed to give RASCAL, a JUH-60A Black Hawk helicopter based at Moffett Field, CA, in-flight simulation capabilities has been designed, optimized and validated in this research. A classical explicit model following control system with a frequency dependent feedback controller was used. The frequency dependent controller allows model following of the attitude in the short term and the velocity in the long term. Controller gains were optimized using a high order, linearized model of UH-60 dynamics. Non-linear simulations of the control laws were performed, first on a desktop computer based simulation, then in the RASCAL development facility, a hardware-in-the-loop simulator. Comparing quantitative results of the non-linear simulations with the results of the optimization using the linearized model ensured that the control system designed with the linearized model was valid in non-linear environments. Finally, a piloted evaluation in the hardware-in-the-loop simulator was performed to obtain qualitative information on the behavior of the control laws.
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Pradipta, Justin [Verfasser]. "Development of a Pneumatically Driven Flight Simulator Motion Platform / Justin Pradipta." Aachen : Shaker, 2016. http://d-nb.info/1138177989/34.
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Beluzo, Carlos Eduardo. "Programa computacional para um simulador de vôo." Universidade de São Paulo, 2006. http://www.teses.usp.br/teses/disponiveis/18/18135/tde-08012016-114920/.
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Os simuladores de vôo têm sido uma importante ferramenta para treinamento de pilotos e análise de vôo sem ter que se desembolsar grandes quantias monetárias, economizando combustível e evitando acidentes. Conseqüentemente, a demanda por simuladores de vôo tem aumentado tanto na indústria quanto na pesquisa. Com o intuito de futuramente construir um simulador de vôo, foi desenvolvido um projeto para elaboração de um software capaz de simular uma aeronave em vôo, do ponto de vista de dinâmica de vôo. O software SIMAERO foi desenvolvido na linguagem de programação C++ e simula a dinâmica de vôo de uma aeronave. Esta simulação consiste em resolver as equações de movimento da aeronave, utilizando o modelo matemático de equações diferenciais ordinárias proposto por ETKIN & REID, et al (1996). O modelo matemático é solucionado através do método de integração numérica Runge-Kutta de 4ª ordem conforme apresentado em CONTE (1977). Como parâmetros de entrada são informadas as seguintes características da aeronave: dados geométricos, dados aerodinâmicos e derivadas de estabilidade. Os resultados das simulações são apresentados em gráficos cartesianos e gravados em arquivos. Os gráficos são úteis para que possa ser feita uma posterior análise do comportamento da aeronave. Os arquivos gravados com os resultados das simulações podem ser utilizados em alguma aplicação futura, como sinas de entrada para uma plataforma de simulação, por exemplo. Neste trabalho será descrito como o SIMAERO foi desenvolvido e ao final serão apresentados alguns resultados obtidos.<br>Flight simulators have been an important tool for pilots training and for flight analyses, without having to spend a high quantity of money, saving gas and prevent accidents. Because of this, the demand for flight simulators has increased both in industry and in research centers. With the objective of in future build a flight simulator, a project to develop a software that is able to simulate the dynamics of flight of a flying aircraft was developed. The SIMAERO software was developed using C++ and its principal functionality is to simulate the dynamics of flight of an aircraft. This simulation basically is the solution of the system of motion equations of the aircraft, using the mathematical model described by ETKIN & REID, et al (1996). The mathematical model is solved using the 4th order Runge-Kutta numeric integration method, as presented in CONTE (1977). For the simulation, the geometric data, the aerodynamic data, and the dimensional derivates are passed to the software as input arguments. The results of the simulations are displayed as cartesians graphics and recorded as data files. The graphics are useful for visual analyses of the aircraft behavior, and the file, with the results of the simulation, can be used as input data for ground based simulator, for example. In this work, the development of the software SIMAERO will be presented, and then some results of the simulation of one aircraft will be shown.
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Jurta, Daniel S. "Validation of the USNTPS simulator for the advanced flight controls design exercise." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2005. http://library.nps.navy.mil/uhtbin/hyperion/05Dec%5FJurta.pdf.
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Lawn, Peter. "The enhancement of a flight simulator system with teaching and research applications." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1998. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp01/MQ39982.pdf.
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McKavitt, Thomas Patrick Jr. "Parameter identification studies on the NASAAMES Research Center Advanced Concepts Flight Simulator." Thesis, Monterey, California: Naval Postgraduate School, 1990. http://hdl.handle.net/10945/34911.
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Approved for public release; distribution unlimited.<br>The results of an aircraft parameters identification study conducted on the National Aeronautics and Space AdministrationAmes Research Center Advanced Concepts Flight Simulator (ACFS) in conjunction with the Navy-NASA joint Institute of Aeronautics are given. The ACFS is a commercial airline simulator with a design based on future technology. The simulator is used as a laboratory for human factors research and engineering as applied to the commercial airline industry. Parametric areas examined were engine pressure ratio (EPR), optimum long range cruise Mach number, flap reference speed, and critical take-off speeds. Results were compared with corresponding parameters of the Boeing 757 and 767 aircraft. This comparison identified two areas where improvements can be made: (1) low maximum lift coefficients (on the order of 20%-25% less than those of a 757; and (2) low optimum cruise Mach numbers. Recommendations were made to those anticipated with the application of future technologies.
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Palmqvist, Tor. "Night Vision in an Unreal Engine 4-Based Virtual Reality Flight Simulator." Thesis, Linköpings universitet, Institutionen för datavetenskap, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-166650.
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Att utnyttja simuleringsteknologi är både ett effektivt och sparsamt sätt att träna piloter utan att utsätta sig själv eller andra för fara. Flygsimuleringar i Virtual Reality blir mer och mer eftersökta tack vare sin unika nivå av immersion. Detta arbete undersöker, utvärderar och visar hur night vision implementeras i Unreal Engine 4. Undersökningen kommer fram till sex specificerade nyckelfaktorer att följa för att korrekt kunna simulera night vision och visar hur detta uppnås huvudsakligen genom att konfigurera post process-effekter. Dessutom utvärderas implementationens prestanda baserat på frame time. Arbetet resulterar i en fullt fungerande night vision-effekt som uppnår alla sex nyckelfaktorer. På grund av den höga prestandakostnaden av Depth of Field uppnås inte en acceptabel nivå prestandamässigt, men genom att minska skärmupplösningen när night vision är aktivt uppnås även prestandamålet utan att kvalitén på implementationen påverkas märkbart.
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Bauer, Maria. "EVALUATING THE EFFECTIVENESS OF TRAINING SYSTEM APPROACHES FOR HIGHLY COMPLEX FLIGHT TRAINING." Doctoral diss., University of Central Florida, 2005. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/3020.
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This research investigates the Training Effectiveness of a low-cost, PC-based training system when compared with two modes (motion and no motion) of a cab training system with large screen for various aviation flying tasks. While much research on this topic has been done in the past, advances in technology have significantly altered what is considered a "low-cost" "simulator." The technology advances have in effect increased the ability of a "low-cost" "simulator" to deliver desired experiences to the user. These "simulators" often are nothing more than PC training system, with only notional representations of the actual aircraft. This research considers the use of such training systems in training for a highly complex and dynamic task situation, that task being a search and rescue mission. A search and rescue mission is far more complex task than those studied for possible "low-cost" simulation substitution in the past. To address that aspect, one mode of the cab involves motion in two degrees of freedom. The results of this research advances the body of literature on the capability of "low-cost" simulation to deliver the experiences necessary to learn highly complex tasks associated with search and rescue as well as further clarify the extent to which a motion platform aides in flight training. This research utilizes available platforms provided by the US Army Research, Development and Engineering Command Simulation and Training Technology Center. Additionally, all the participants in the research are in training to be helicopter pilots. Participants were randomly assigned to one of three training configurations: a) Cab with motion turned ON, b) Cab with motion turned OFF and c) PC-based simulator. Training effectiveness is evaluated using measures for learning, task performance, and human factors. Statistically significant results are shown for the Cab with Motion and the Cab with No Motion configurations.<br>Ph.D.<br>Department of Industrial Engineering and Management Systems<br>Engineering and Computer Science<br>Industrial Engineering and Management Systems
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Persson, Daniel. "Passenger Flight Experience of Urban Air Mobility." Thesis, Uppsala universitet, Observationell astrofysik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-399699.
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The first part of a study of passenger flight experience of Urban Air Mobility was completed. This first part included the design of different Urban Air Mobility vehicle models, in which the passenger flight experience would be quantitatively measured. A first version of a simulator setup, in which the measurements were performed, was also developed. Three concept vehicle models, a single main rotor, a side-by-side rotor and a quadrotor, were designed in the conceptual design software NDARC. The vehicles were electrically propelled with battery technology based on future technology predictions and were designed for autonomous flight with one passenger. The emissions of the vehicles were analyzed and compared with an existing turboshaft helicopter. The interface between NDARC and the flight dynamics analysis and control system software FlightCODE, which was used to create control systems to the NDARC models, was developed to fit the vehicle configurations considered. The simulator setup was created with a VR headset, the flight simulation software X-Plane, an external autopilot software and stress sensors. Trial runs with the simulator setup were performed and gave important data for the continued development. Planned upgrades of the simulation station were presented and the continuation of the study was discussed.
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Senneberg, Sofia. "Methods for validating a flight mechanical simulation model for dynamic maneuvering." Thesis, KTH, Flygdynamik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-299412.
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Flight mechanical simulators play an important role in the design steps during development of a new aircraft. To be able to simulate and evaluate flight mechanical characteristics during development it is important to minimize development time and cost while keeping flight safety high during early flights. The aim of the project presented in this thesis is to develop a method for validating a flight mechanical simulator against flight test data from dynamic maneuvering. An important part in this thesis is about how deviations in the result data can be found and analyzed, for example deviations between aircraft individuals or store configurations. The work presented here results in a good model for comparison of a big amount of data where it is easy to backtrace where the deviation occurs.<br>Flygmekaniska simulatorer är av stor betydelse under utvecklingen av ett nytt stridsflygplan. Möjligheten att simulera och utvärdera under tidens gång har stor betydelse både ur tid- och kostnadsbesparings perspektiv men även ur flygsäkerhetsperspektiv när det är dags för första flygning. Syftet med det här projektet är att utveckla en metod för jämförelse mellan simulering och flygprov för att validera hur bra den flygmekaniska simulatorn kan förutspå flygplansbeteende. En viktig del i projektet syftar till hur skillnader i resultaten kan hittas och analyseras, till exempel skillnader mellan olika flygplansindivider eller lastkonfigurationer. Arbetet presenterat här har resulterat i en modell som är bra för jämförelse av en stor mängd data där det är enkelt att spåra var skillnaderna har uppstått.
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Hernandez, Luis. "Causality tracing user interface design and development for a software management flight simulator." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1995. http://handle.dtic.mil/100.2/ADA305650.
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Thesis (M.S. in Information Technology Management) Naval Postgraduate School, December 1995.<br>Thesis advisor(s): T. Hamid, B. Ramesh. "December 1995." Bibliography: p. 177-178. Also available online.
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MacInnis, Daniel V. 1964. "Development of a system dynamics based management flight simulator for new product development." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/34732.
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Thesis (S.M.)--Massachusetts Institute of Technology, System Design & Management Program, 2004.<br>Includes bibliographical references (p. 152-153).<br>All firms in any mature product development industry are being pressured into performing 'better, faster, and cheaper' by both customers and competitors. In short, firms are being tasked with doing more, with less, faster. This leads to product development organizations being unrealistically tasked to deliver on these programs that often lead to projects falling behind schedule, over budget, and with inadequate quality. While striving to do the right actions to survive, the management of these firms may be leading their firms to disaster through over commitment, and short-term management actions to address the quality, budget, and schedule shortfalls. An understanding of the system dynamics associated with the program management of new product development (NPD) programs is essential to reversing this trend. Several corporations are instituting system dynamics in their management and executive training curricula to affect correct policies, procedures, and behaviors that lead to success. However, because the correct policies, procedures, and behaviors as revealed by system dynamics analysis are counter-intuitive and opposite those policies currently employed in program management, a method is needed to drive the learning of system dynamics so that it becomes ingrained in the program management thought processes. A management flight simulator (MFS) of the program management of a new product development project based on system dynamics provides the hands on experience that managers can learn the consequences of non systems-thinking policies on project performance and how system dynamics based policies can lead to greater success. This thesis provides an overview of the system dynamics of project management in new product development and insight into the<br>(cont.) correct policies, procedures, and behaviors that lead to success. Research on the role of MFSs in driving the learning of system dynamics principles is explored. A single-phase system dynamics model for a new product development program and a MFS is developed to teach the fundamental lessons of system dynamics applied to product development project management and is to be incorporated in the BP Project Academy. Insight from my own experiences in product development is incorporated in this MFS as well as in recommendations for further development.<br>by Daniel V. MacInnis.<br>S.M.
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McKavitt, Thomas P. "Parameter identification studies on the NASA/AMES Research Center Advanced Concepts Flight Simulator." Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA240587.
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Thesis (M.S. in Aeronautical and Astronautical Engineer)--Naval Postgraduate School, September 1990.<br>Thesis Advisor(s): Schmidt, Louis V. Second Reader: Howard, Richard M. "September 1990." Description based on title screen as viewed on March 19, 2010. DTIC Identifier(s): Parameter Identification, Aircraft Simulator. Author(s) subject terms: Parameter Identification, Aircraft Simulator, Advanced Concepts Flight Simulator, ACFS. Includes bibliographical references (p. 57). Also available in print.
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Lindqvist, Daniel. "Methodology For Evaluating Flying Qualities From Desktop Simulator." Thesis, Luleå tekniska universitet, Rymdteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-77354.
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A modern ghter aircraft has an advanced ight control system which highly augmentsthe control inputs from the pilot. To verify a new iteration of the control system is a timeconsuming and expensive task. It is desired to nd qualities that is not satisfactory to thepilot as early as possible in the verication process to reduce the cost for design changes.The primary objective of this thesis is to develop methods that can be used for automaticalevaluation of aircraft ying qualities from the data provided by a desktop simulator. A desktopsimulator is cheap to use compared to ight tests and tests with a pilot in a simulator.Only ghter aircraft in the precision ight phase are studied however the methods developedcould easily be extended to include other types of aircraft and other phases of ight.To evaluate the ying qualities two sets of criteria are used the MIL-F-8785C standardand the Gibson criteria. The MIL-F-8785C standard uses a second order linear system toevaluate the aircraft's ying qualities. The linear system is estimated from the nonlineardata and evaluated against the MIL-F-8785C standard. The Gibson criteria studies the timeand frequency domain directly and are designed to work with highly augmented aircraft.The set of Gibson criteria used in this thesis primary evaluates data from the time domainhowever one criterion from the frequency domain is studied.The methods developed to evaluate the ying qualities from the MIL-F-8785C standardonly works for a small part of the ight envelope furthermore they show a large dierencefor what is considered acceptable ying qualities. Because of this the methods developed forthe MIL-F-8785C standard are considered not to be suited for evaluating ying qualities forhighly augmented aircraft. The methods developed to evaluate the ying qualities againstthe Gibson criteria works for a large part of the ight and also show a high accuracy. Thismakes the methods suited for evaluation of the ying qualities.
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Rekleitis, Georgios. "Modeling and evaluation of a new parallel mechanism as a flight simulator motion base." Thesis, McGill University, 2003. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=80137.
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In this thesis, a novel 6 degree-of-freedom parallel mechanism is evaluated as a flight simulator motion base. The mechanism consists of three fixed-length legs, each supported by a three-wheeled mobile robot. The three legs support a platform, which acts as the end-effector of the mechanism. Thus, the mechanism has the advantage of portability and simple design, because of the specific actuating system. Two different designs are evaluated: one with ball joints at the upper ends of the legs and revolute joints at the lower ends and one with the opposite configuration. The inverse kinematics and inverse dynamics analysis of the mechanism, including its actuation system, is conducted. Our simulations lead us to conclude that the configuration with the ball joints at the lower ends of the legs performs better. The mechanism is then evaluated as a motion base for a flight simulator, using typical aircraft maneuvers. Certain problems are observed that make this application questionable. However, the mechanism shows potential as a motion base for a driving simulator, which is certainly worth exploring further.
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Sullivan, Robert Bryan. "The use of vestibular models in flight simulator motion washout systems : an experimental evaluation." Thesis, Massachusetts Institute of Technology, 1985. http://hdl.handle.net/1721.1/80443.
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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1985.<br>Microfiche copy available in Archives and Barker.<br>Bibliography: leaves 114-115.<br>by Robert Bryan Sullivan.<br>M.S.
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Grogan, Andrew S. "A Low Cost, Portable Stewart Platform Study for Flight Simulation and Gaming Simulation." Ohio University / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1606121360298874.
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McNamara, William G., Page Stanley, and Jay Nichols. "RTPS Telemetry - Simulator Link at Naval Air Warfare Center." International Foundation for Telemetering, 1995. http://hdl.handle.net/10150/611514.
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International Telemetering Conference Proceedings / October 30-November 02, 1995 / Riviera Hotel, Las Vegas, Nevada<br>Over the last 3 years the Naval Air Warfare Center Aircraft Division (NAWCAD), Patuxent River, MD, has been in the process of developing a link between its secure Manned Flight Simulator (MFS) and Real Time Processing System (RTPS) facilities. The MFS hosts a wide variety of high fidelity fixed and rotary wing aircraft simulation models. The RTPS is used as a telemetry ground station for conduct of Navy flight testing at Patuxent River MD. The ability to integrate simulation with flight testing in a real time environment provides new potential for increased flight safety, enhanced engineering training, optimized flight test planning, real time simulation fidelity assessments, improved engineering analysis and other applications for enhanced flight testing, data analysis and data processing. A prototype system has been successfully designed and operated at NAWCAD in support of an F/A-18C flight test project which required simultaneous merging and display of real time and simulation data to reduce the risk of departure from controlled flight. As currently designed the link (encryption and decryption gear in the loop) can be operated in three modes: (1) Simulation sending data to RTPS (e.g. pilot-engineer pre-first flight preparation/training scenario, (2) simulation is driven by real aircraft control surface inputs and response is compared with that of the real aircraft for simulation fidelity assessments and (3) simulation "rides along" with the real aircraft and data are extracted from the simulation which are otherwise unavailable from the aircraft (e.g. flight control law interconnect signals, control law feedback signals, aerodynamic data, propulsion model data, avionics model data, other model data etc.). This paper discusses, design and implementation aspects of the RTPS-Simulator link, and includes a description of how the link was used to support a real time flight test program by providing critical safety of flight data. Other potential uses for the link will also be highlighted.
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McMullen, Eric L., and Brian Shane Grass. "EFFECTS OF UAV SUPERVISORY CONTROL ON F-18 FORMATION FLIGHT PERFORMANCE IN A SIMULATOR ENVIRONMENT." Monterey, California. Naval Postgraduate School, 2013. http://hdl.handle.net/10945/32870.
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Continual advances in technology, along with increased cockpit workload particularly the shift from two-seat to single-seat fighters to save money and reduce risk to lifepush the limits of human mental capacity. Additionally, there is interest within the military aviation community to integrate Unmanned Aerial Vehicle (UAV) control into the cockpit in order to expand force projection capability. This study compared the effects on formation flight performance of two different secondary tasks, specifically a traditional secondary task such as target prosecution with an electro-optical Forward Looking Infra-Red (FLIR) pod, and a futuristic secondary task such as UAV supervisory control. A total of 34 military fighter aviators volunteered to fly three five-minuteF-18 simulator sessions in close formation with no secondary task, and then treated with each of the two secondary tasks. Results provided clear indication that the futuristic task was significantly more challenging than the traditional task, and that both secondary tasks significantly increased the average mean following distance and variance compared to the undistracted flying baseline scenario. Additionally, we found no evidence that increased flight experience (total flight hours) significantly improved performance of the prescribed primary task when treated with the futuristic task distraction. Knowledge gained from the results could contribute to improved crew resource management (CRM) and pilot workload management as well as flight safety resulting from the modification of flight procedures based on known effects of distractions in the cockpit.
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Söderström, Arvid, and Johanna Thorheim. "Design and evaluation of an educational tool for understanding functionality in flight simulators : Visualising ARINC 610C." Thesis, Linköpings universitet, Interaktiva och kognitiva system, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-137686.
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The use of simulation in aircraft development and pilot training is essential as it saves time and money. The ARINC 610C standard describes simulator functionality, and is developed to streamline the use of flight simulators. However, the text based standard lacks overview and function descriptions are hard to understand for the simulator developers, who are the main users. In this report, an educational software tool is conceptualised to increase usability of ARINC 610C. The usability goals and requirements were established through multiple interviews and two observation studies. Consequently, six concepts were produced, and evaluated in a workshop with domain experts. Properties from the evaluated concepts were combined in order to form one concluding concept. A prototype was finally developed and evaluated in usability tests with the potential user group. The results from the heuristic evaluation, the usability tests, and a mean system usability score of 79.5 suggests that the prototyped system, developed for visualising ARINC 610C, is a viable solution.
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Davis, Richard D. "Design and development of a user interface and user manual for the Software Management Flight Simulator." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1995. http://handle.dtic.mil/100.2/ADA303352.
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Thesis (M.S. in Information Technology Management) Naval Postgraduate School, September 1995.<br>Thesis advisor(s): T. Hamid, H.K. Bhargava. "September 1995." Includes bibliographical references. Also available online.
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Cetin, Yasemin. "Evaluation Of Visual Cues Of Three Dimensional Virtual Environments For Helicopter Simulators." Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/2/12610100/index.pdf.
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Flight simulators are widely used by the military, civil and commercial aviation. Visual cues
are an essential part of helicopter flight. The required cues for hover are especially large
due to closeness to the ground and small movements.
In this thesis, density and height parameters of the 3D (Three Dimensional) objects in the
scene are analyzed to find their effect on hovering and low altitude flight. An experiment is
conducted using a PC-based flight simulator with three LCD monitors and flight control set.
Ten professional military pilots participated in the experiment.
v
Results revealed that object density and object height are effective on the horizontal and
vertical hovering performance. There is a peak point after which increasing the density does
not improve the performance. In low altitude flight, altitude control is positively affected by
smaller object height. However, pilots prefer the scenes composed of the high and mixture
objects while hovering and flying at low altitude. Distance estimation is affected by the
interaction of the object density and height.
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Diab, Hassan Bahaeddine. "Microprocessor based real-time modelling in relation to the visual systems of an aircraft flight-training simulator." Thesis, University of Bath, 1985. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.353694.
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The purpose of this thesis is to show the application of modern digital techniques to produce a high speed computational system that has the capability of producing a faster than real-time model for the visual systems associated with flight simulator systems. A distributed/multiprocessing system was chosen due to the increased reliability, flexibility and throughput of the computational process. The system also has the advantage of providing increased modularity and ease of expansion. This research is firstly concerned with the development of a high resolution graphics system (providing a 1024 by 1024 point screen resolution), and the techniques for the production of moving visual scenes observed by a pilot when flying over a region of terrain in a flight simulator. In particular, this work is concerned with the real-time simulation of the aerodynamics of the aircraft and considers the problems of designing and accessing a data base which represents a model of the terrain. There are three major design considerations for the real-time CGI (Computer Generated Imagery) system of the type required. The first is to ensure that all processing for each picture frame is performed within a specified time limit. Secondly, the picture must have a realistic appearance and requires realism functions to be performed in real-time. The third design consideration is the cost.
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Friedenthal, Stephen R. (Stephen Roger). "Developing a risk management "flight simulator" for manned space programs : a user interface to a system dynamic simulation of system safety at NASA." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/34630.
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Thesis (S.M.)--Massachusetts Institute of Technology, System Design and Management Program, February 2006.<br>Includes bibliographical references (p. 81-82).<br>Simulators are a staple of any engineering project and manned space flight in particular. From pilot and crew training to maintenance and emergency repairs, very little is done without it first being thoroughly practiced and refined during advance simulation. Whether the simulation uses a computerized flight simulator that recreates the physics and experience of flight, or a simple mock-up with paper cutouts and hand tools, the end result is the same: people learn to make. better and safer decisions through advanced simulation and practice. However, there are no simulation tools in use to help NASA managers to understand the dynamics of systemic risk, or how to evaluate the inherent risk within an organization. This thesis describes the development of a risk management simulator that will enable NASA managers to explore the dynamics of risk using an advanced system dynamics simulation of the NASA safety culture prior to the Columbia Shuttle accident. This simulation model was developed by MIT Professor Nancy Leveson and her students as part of a NASA USRA research grant and has over 700 variables and several sub models.<br>(cont.) While the model is eminently useful to those familiar with system dynamics, the Vensim software application and the specific model structure, it is not very useful as a learning tool for those who are not. The simulator tool developed for this thesis simplifies and consolidates the overall model behavior into 8 decision variables and 35 display variables. Moreover, 18 of those display variables are grouped into one of 5 categories of "leading indicators" of risk. This simulator enables any user to quickly begin to explore the system model and to discover the consequences of different decisions on system risk, without any need for the user to know system dynamics theory or any details of the model design. In a video game the user doesn't know how it is programmed, but is still able to learn the rules of the game, how it behaves and-most importantly-how to win. Similarly, the goal of the risk management flight simulator is to help NASA managers to learn the rules of system risk, how system risk behaves in response to management decisions, and, most importantly, how to make the best informed risk decisions.<br>y Stephen R. Friedenthal.<br>S.M.
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Casto, Kristen Lee. "An Examination of Headset, Hearing Sensitivity, Flight Workload, and Communication Signal Quality on Black Hawk Helicopter Simulator Pilot Performance." Diss., Virginia Tech, 2009. http://hdl.handle.net/10919/28664.
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Among the many occupational hazards to which Army rotary-wing aviators are exposed is intense noise generated from the aircraft. The potential for permanent hearing loss and difficulty communicating in helicopter noise is well known; an appropriate way to evaluate a hearing-impaired pilotâ s safety risk due to hearing loss is not as well known. Previous research has studied communication ability in helicopter cockpit noise under different headsets, but there are not conclusive data on the combined effects of degraded speech intelligibility due to noise and flight workload under the headset technology currently available to Army helicopter pilots. In particular, there is a scarcity of information on pilots with hearing loss. Currently, Army Aeromedical standards stipulate audiometric threshold criteria for rated helicopter pilots to ensure their safe flying. If the standard is not met, a flight waiver for hearing is generally granted if the pilot demonstrates good (at least 84%) binaural word recognition ability in a quiet environment.
A research study was conducted to evaluate Army helicopter pilot performance with regard to flight workload, communication signal quality, headset configuration, and pilot hearing ability. Objectives of the study included the ability to refine current Army audiometric hearing waiver criteria, and to yield data on which to base flight and headset selection recommendations for pilots. In general, it was believed that flight performance and ratings of situation awareness (SA) would decrease as flight workload increased and communication signal quality decreased, and that assistive communication devices coupled with headsets would afford improved flight performance over their passive counterpart. It was also hypothesized that normal-hearing pilots would perform better than hearing-impaired pilots would.
Twenty Army helicopter pilots (one group of 10 pilots without a hearing waiver and one group of 10 pilots with a hearing waiver) participated in this study. The pilots flew three flights in a Black Hawk flight simulator, each with a different headset configuration and with varying flight workload levels and varying air traffic control (ATC) communication signal quality. Objective flight performance parameters of heading, altitude, and airspeed deviation and ATC command readbacks were measured. Additionally, measurements were taken on subjective measures of workload, SA, and headset comfort/speech intelligibility.
Experimental results partially supported the research hypotheses. Results indicated that flight performance and ratings of SA were negatively affected by increased flight workload and decreased communication signal quality for both groups of pilots. Results also showed that a passive headset/passive earplug combination use by the hearing-impaired group of pilots led to degradation of certain flight performance parameters and lower ratings of SA than the headsets equipped with assistive communication technology; however, the same headset effect was not seen with the group of normal-hearing pilots.
This study yielded results that support a conclusion that factors other than hearing thresholds and word recognition ability in a quiet environment should be considered when evaluating Army helicopter pilots flight safety with regard to hearing sensitivity. Rather, the synergistic effects of flight workload and communication signal quality with individual hearing levels should be considered when making continued flight recommendations and headset choice recommendations. Results also support a recommendation requiring hearing-impaired pilots to use assistive communication technology and not be permitted to fly with passive headset devices. Further research should include a functional hearing assessment in which pilot hearing requirements are determined and individual hearing abilities are compared to the requirements.<br>Ph. D.
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Eliasson, Carl, and Alexander Hedberg. "VR-flygsimulatorer, för ökad upplevelse och som läroverktyg i flygutbildningar." Thesis, Mälardalens högskola, Akademin för innovation, design och teknik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-35667.
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Virtual reality (VR) är ett begrepp som blivit allt mer välkänt de senaste åren. VR kan beskrivas som en datorgenererad virtuell omvärld som användaren omsluts av. VR-miljön upplevs genom människans sinnen såsom syn, hörsel och känsel.Syftet med examensarbetet är att undersöka hur realistisk en kommersiellt tillgänglig VR-flygsimulator upplevs av piloter och undersöka om VR-teknik kan vara ett användbart läroverktyg för t.ex. flygskolor. VR-tekniken har under de senaste åren utvecklats väldigt mycket vilket gjort att många av de implementations svårigheter som VR-tekniken inneburit till stor del lösts. Nya helintegrerade head mounted displays (HMD) med inbyggd kompatibilitet gör att integreringsproblemen nästan helt försvunnit. Eftersom VR-tekniken nu är mer tillgänglig och lätthanterlig ligger det helt rätt i tiden att undersöka hur VR-teknik kan användas inom flygbranschen.Metoden för examensarbetet inleddes med informationsinsamling om VR-teknik och traditionella flygsimulatorer. Utifrån denna information skapades sedan en undersökning som bestod av två delar. Den första delen var ett experiment med en VR-flygsimulator och den andra delen var en intervju som utfördes direkt efter experimentet. Sju stridspiloter deltog i undersökningen.Resultaten av undersökningen visar att VR-flygsimulatorer upplevs som mer realistiska jämfört med traditionella flygsimulatorer. Undersökningen tyder också på att VR-teknik kan vara ett bra läroverktyg om de problem som identifierats lösts på ett tillfredsställande sätt.<br>Virtual reality (VR) is a rising phenomenon that has skyrocket in popularity the past year. VR is often referred to as a computer generated virtual environment the user gets immersed in. The VR environment is experienced through different types of sensory stimuli.The purpose of this thesis is to examine how realistic a commercially available VR flight simulator is being perceived by real pilots as well as examine if VR technology could be a viable educational tool for flight schools. The motivations of this thesis are the facts that the VR-technology has advanced in a quick phase. Many of the past difficulties with implementing VR technology have been addressed with new fully integrated head mounted displays therefor capability issues are no longer a big problem. Because of the simplicity of new VR-systems it’s a good time to investigate VR uses and how it compares to traditional flight simulator techniques.The method used for the thesis started with collecting information about VR technology and traditional flight simulators. With that information a survey consisting of two parts was created. The first part was an experiment with a VR flight simulator, and the second part was an interview conducted directly after the experiment. Seven jet fighter pilots participated in the survey.Our results show that a VR flight simulator is perceived as more realistic compared to a traditional flight simulator. It is also shown that VR technology could be a good educational tool if some of the issues that were found are resolved or improved upon.
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Nikolic, Mark I. "The human-machine teams create, explain, and recover from coordination breakdowns: a simulator study of disturbance management on modern flight decks." The Ohio State University, 2004. http://rave.ohiolink.edu/etdc/view?acc_num=osu1092808745.
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