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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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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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Ippolito, Corey A. "Software architectures for flight simulation." Thesis, Georgia Institute of Technology, 2000. http://hdl.handle.net/1853/15749.
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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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Ercin, Gulsum Hilal. "Flight Simulation And Control Of A Helicopter." Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/3/12610194/index.pdf.
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In this thesis the development of a nonlinear simulation model of a utility helicopter and the design of its automatic flight control system is addressed. In the first part of this thesis, the nonlinear dynamic model for a full size helicopter is developed using the MATLAB/SIMULINK environment. The main rotor (composed of inflow and flapping dynamics parts), tail rotor, fuselage, vertical stabilizer, horizontal stabilizer of the helicopter are modeled
in order to obtain the total forces and moments needed for the flight simulation of the helicopter. Total forces and moments are used in 6 degrees of freedom equations of motion model and helicopter states are calculated for the specified flight conditions such as hover and forward flight. Trim and linearization programs are developed. The linearized models of hover and forward flight conditions are used for the automatic flight control system design. Automatic flight control system model consists of necessary systems in order to ease the pilot control of the helicopter. A classical inner stability loop and outer flight directory mode approach is taken to design the automatic flight control system. For the inner stability loop both classical rate feedback and truncated system state feedback control approaches are used. The outer loop modes implemented are heading hold, attitude hold (pitch, roll), altitude acquire and hold mode for hover condition and heading hold, attitude hold (pitch, roll), altitude acquire and hold mode and airspeed hold for forward flight condition. Finally, the success of the controllers are demonstrated through nonlinear simulations for different flight directory modes in hover and forward flight conditions.
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Cooke, Joseph M. "NPSNET : flight simulation dynamic modeling using quaternions." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/27165.
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The Naval Postgraduate School (NPS) has actively explored the design and implementation of networked, realtime, three-dimensional battlefield simulations on low cost, commercially available graphics workstations. The most recent system, NPSNET, has improved in functionality to such an extent, that it is considered a low cost version of the Defense Advanced Research Project Agency's (DARPA) SIMNET system. In order to reach that level, it was necessary to economize in certain areas of the code so that real time performance occurred at an acceptable level. One of those areas was in aircraft dynamics. However, with 'off-the-shelf' computers becoming faster and cheaper, real-time and realistic dynamics are no longer an expensive option. The realistic behavior can now be enhanced through the incorporation of an aerodynamic model. To accomplish this task, a prototype flight simulator was built that is capable of simulating numerous types of aircraft simultaneously within a virtual world. Beside being easily incorporated into NPSNET, such a simulator will also provide the base functionality for the creation of a general purpose aerodynamic simulator that is particularly useful to aerodynamic students for graphically analyzing differing aircraft's stability and control characteristics. This system is designed for use on a Silicon Graphics workstation and uses the GL libraries. Computer Graphics, Animation, Simulation, Aerodynamics, Quaternions
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Waite, John V. "An Ada object oriented missile flight simulation." Thesis, Monterey, California. Naval Postgraduate School, 1991. http://hdl.handle.net/10945/27931.
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Giri, Deepak. "Flight Path Simulation in LabVIEW using LDAR." International Foundation for Telemetering, 2015. http://hdl.handle.net/10150/596453.
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ITC/USA 2015 Conference Proceedings / The Fifty-First Annual International Telemetering Conference and Technical Exhibition / October 26-29, 2015 / Bally's Hotel & Convention Center, Las Vegas, NVThis paper compares the results of the MATLAB flight path simulation earlier with the LabVIEW software defined radio module which is being developed at Morgan State University in collaboration with Georgia Tech. Research Institute under the Link Dependent Adaptive Radio (LDAR) project. In LDAR, the communication parameters such as modulation size and coding rate are updated based on the channel condition. In this simulation QAM size is updated based on the channel throughput in LabVIEW and a flight path using real aeronautical channels is simulated.
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Aslin, P. P. "Aircraft simulation and robust flight control system design." Thesis, University of York, 1985. http://etheses.whiterose.ac.uk/9821/.
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Davenport, Wyatt Emery. "Development, modeling, and simulation of a nano aerial vehicle using empirical data." Diss., Rolla, Mo. : University of Missouri-Rolla, 2007. http://scholarsmine.mst.edu/thesis/pdf/Davenport_09007dcc80413292.pdf.
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Thesis (M.S.)--University of Missouri--Rolla, 2007.Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed January 28, 2008) Includes bibliographical references (p. 83-84).
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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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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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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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Yuan, Duojia, and S3024047@student rmit edu au. "Flight Delay-Cost Simulation Analysis and Airline Schedule Optimization." RMIT University. Aerospace, Mechanical, Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080618.092923.
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In order to meet the fast-growing demand, airlines have applied much more compact air-fleet operation schedules which directly lead to airport congestion. One result is the flight delay, which appears more frequently and seriously; the flight delay can also significantly damage airline's profitability and reputation The aim of this project is to enhance the dispatch reliability of Australian X Airline's fleet through a newly developed approach to reliability modeling, which employs computer-aided numerical simulation of the departure delay distribution and related cost to achieve the flight schedule optimization. The reliability modeling approach developed in this project is based on the probability distributions and Monte Carlo Simulation (MCS) techniques. Initial (type I) delay and propagated (type II) delay are adopted as the criterion for data classification and analysis. The randomicity of type I delay occurrence and the internal relationship between type II delay and changed flight schedule are considered as the core factors in this new approach of reliability modeling, which compared to the conventional assessment methodologies, is proved to be more accurate on the departure delay and cost evaluation modeling. The Flight Delay and Cost Simulation Program (FDCSP) has been developed (Visual Basic 6.0) to perform the complicated numerical calculations through significant amount of pseudo-samples. FDCSP is also designed to provide convenience for varied applications in dispatch reliability modeling. The end-users can be airlines, airports and aviation authorities, etc. As a result, through this project, a 16.87% reduction in departure delay is estimated to be achieved by Australian X Airline. The air-fleet dispatch reliability has been enhanced to a higher level - 78.94% compared to initial 65.25%. Thus, 13.35% of system cost can be saved. At last, this project also achieves to set a more practical guideline for air-fleet database and management upon overall dispatch reliability optimization.
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Eklund, John M. "Aircraft flight control simulation using parallel cascade system identification." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1998. http://www.collectionscanada.ca/obj/s4/f2/dsk2/tape17/PQDD_0004/MQ28194.pdf.
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Kakimpa, Bruce. "The numerical simulation of plate-type windborne debris flight." Thesis, University of Nottingham, 2012. http://eprints.nottingham.ac.uk/12376/.
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Wind borne debris is one of the principal causes of building envelope failure during severe storms. It is often of interest in windstorm risk modelling to estimate the potential flight trajectories and impact energy of a piece of debris. This thesis presents research work aimed at the development and validation of a numerical model for the simulation of plate-type windborne debris. While a number of quasi-steady analytical models are available at present, these models are unable to account for the fluid-plate interaction in highly unstable flows. The analytical models are also limited to simple launch flow conditions and require extensive a-priori knowledge of the debris aerodynamic characteristics. In addition, the use of Euler angle parametrisations of orientation in the analytical models results in mathematical singularities when considering 3D six degree-of-freedom motion. To address these limitations, a 3D Computational Fluid Dynamics (CFD) model is sequentially coupled with a quaternion based singularity-free six degree of freedom Rigid Body Dynamics (RBD) model in order to successfully simulate the flight of plate-type windborne debris. The CFD-RBD model is applied to the numerical investigation of the flow around static, forced rotating, autorotating and free-flying plates as well as the treatment of complex launch conditions. Key insights into the phenomena of plate autorotation are highlighted including the genesis of the aerodynamic damping and acceleration torques that make autorotation possible. The CFD-RBD model is then validated against measurements of rotational speed and surface pressure obtained from recent autorotation experiments. Subsequently a general 3D spinning mode of autorotation is demonstrated and the CFD-RBD model is extended to include plate translation in order to simulate windborne debris flight. Using the CFD-RBD flight model, a parametric study of windborne debris flight is carried out and four distinct flight modes have been identified and are discussed. The flight results are contrasted against available free-flight experiments as well as predictions from existing quasi-steady analytical models and an improved quasi-steady force model based on forced rotation results is proposed. The resulting CFD-RBD model presents the most complete numerical approach to the simulation of plate-type windborne debris, directly simulating debris aerodynamics, and incorporates complex launch flow fields in the initial conditions.
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Best, Russell J. "Javelin aerodynamics, flight simulation and optimisation of javelin release." Thesis, University of Salford, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.360385.
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Hoefener, Carl E. "DISTRIBUTED INTERACTIVE SIMULATION PROVEN IN FLIGHT TEST AIRCRAFT TRACKING." International Foundation for Telemetering, 1994. http://hdl.handle.net/10150/608558.
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International Telemetering Conference Proceedings / October 17-20, 1994 / Town & Country Hotel and Conference Center, San Diego, CaliforniaWith the decline in military budgets worldwide, the need for ever more effective training is becoming apparent. The size of the armed forces is being reduced, so the remaining members have to be trained to be more effective and efficient in doing their jobs. To improve effectiveness and efficiency of performance, military training needs will be increased. Our largest training costs will be in pilot training because of the high cost of keeping aircraft in the air. When we look at the cost of training a pilot to operate in a multiplayer scenario against a large number of unfriendly aircraft and a large number of ground threats, the cost of training is tremendous. It requires a large number of personnel, aircraft and ground equipment to train a limited number of pilots. Our current Red Flag exercises can require as many as 75 aircraft in the air simultaneously plus a large number of ground threats and a large number of support personnel. This can amount to a prohibitive cost to train a limited number of pilots.
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Chlebek, David. "Simulation of ultrasonic time of flight in bolted joints." Thesis, KTH, Hållfasthetslära, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-298342.
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Ultrasonic measurements of the preload in bolted joints is a very accurate method since it does not depend on the friction and other factors which cause difficulties for common methods. The ultrasonic method works by emitting an ultrasonic pulse into the bolt which is reflected at the end and returned to the transducer, the change in the time of flight (TOF) can be related to the elongation of the bolt and therefore the preload. One must account for the acoustoelastic effect which is the change in sound speed due to an initial stress state. The goal of this thesis project was to implement a Murnaghan hyperelastic material model in order to account for the acoustoelastic effect when conducting a numerical simulation using the finite element method (FEM). An experiment was also performed to validate the numerical simulation. The DeltaTOF as a function of a tensile force was obtained for an M8 and M10 test piece from the experiment. The material model was implemented by creating a user subroutine written in Fortran for the explicit solver Radioss. Hypermesh was used to set-up the numerical simulation. The material model has shown an expected behavior with an increased sound speed with compressive stresses and a decreased speed with tensile stresses. The numerical simulation showed a good correspondence to the experimental results.Ultraljudsmätning av klämklraften i skruvförband är en väldigt noggrann metod eftersom att metoden inte påverkas av friktion eller andra faktorer som innebär svårigheter för vanliga metoder. Ultraljudsmetoden fungerar genom att skicka in en ultraljudsvåg i skruven som reflekteras i botten och återvänder tillbaka till sensorn. Skillnaden i tiden för ekot att återvända kan relateras till förlängningen av skruven och därmed klämkraften. Det är viktigt att ta hänsyn till den akustoelastiska effekten, som är fenomenet där ljudhastigheten av en våg i en solid förändras med spänningstillståndet. Målet med det här arbetet är att implementera en hyperelastisk Murnaghan modell som tar hänsyn till den akustoelastiska effekten med FEM simuleringar. Ett experiment har också genomförts för att validera beräkningsmodellen. Tidsfördröjningen som en funktion av förspänningskraften togs fram för ett M8 och M10 provobjekt. Murnaghans hyperelastiska materialmodell implementerades genom att skapa ett användar material skriven i programmeringsspråket Fortran för den explicita lösaren Radioss. Hypermesh användes för att ställa upp FEM simuleringen. Materialmodellen har visat ett väntat beteende med en ökad ljudhastighet med tryckspänningar och minskad ljudhastighet med dragspänningar. Beräkningsmodellen visade en god överenstämmelse med resultatet från experimentet.
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Ford, Keith John. "The modelling and control of a synergistic motion system." Thesis, University of Brighton, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.337849.
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Smith, R. Marshall. "A method for determining and reducing transport delays in the flight simulation environment." Thesis, This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-10242009-020229/.
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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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McGrath, Shaun R. "Leveraging DMO's hi-tech simulation against the F-16 flying training gap /." Montgomery, Ala. : Ft. Belvior, VA : Alexandria, Va. : Air University Press (AUL/LP), Maxwell Air Force Base ; Available to the public through the Defense Technical Information Center ; National Technical Information Service [distributor], 2005. http://www.dtic.mil/dtic/.
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Thesis--Air Command and Staff College, Air University, Maxwell Air Force Base, April 2005."April 2007." Thesis advisor: Lt. Col. James A. Rothenflue. Performed by Air University Press (AUL/LP), Maxwell Air Force Base, Montgomery, Ala. "AU/ACSC/2927/2004-05." Includes bibliographical references (p. 35-37). Also available online from the Air University Research Information Management System (AURIMS) and the DTIC Online Web sites.
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Youssef, Hazim S. "Laser engine simulation using pressure based navier-stokes solver." Diss., This resource online, 1994. http://scholar.lib.vt.edu/theses/available/etd-10052007-143624/.
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Gururajan, Srikanth. "Design and simulation of advanced fault tolerant flight control schemes." Morgantown, W. Va. : [West Virginia University Libraries], 2006. https://eidr.wvu.edu/etd/documentdata.eTD?documentid=4915.
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Thesis (Ph. D.)--West Virginia University, 2006.Title from document title page. Document formatted into pages; contains xii, 132 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 123-128).
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Fredman, Kristin, and Anna Freiholtz. "Use of Simulation Optimization for Clearance of Flight Control Laws." Thesis, Linköping University, Department of Electrical Engineering, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-5595.
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Before a new flight control system is released for flight, a huge number of simulations are evaluated to find weaknesses of the system. This process is called flight clearance. Flight clearance is a very important but time consuming process. There is a need of better flight clearance methods and one of the most promising methods is the use of optimization. In this thesis the flight clearance of a simulation model of JAS 39 Gripen is examined. Two flight clearance algorithms using two different optimization methods are evaluated and compared to each other and to a traditional flight clearance method.
In this thesis the flight clearance process is separated into three cases: search for the worst flight condition, search for the worst manoeuvre and search for the worst flight condition including parameter uncertainties. For all cases the optimization algorithms find a more dangerous case than the traditional method. In the search for worst flight condition, both with and without uncertainties, the optimization algorithms are to prefer to the traditional method with respect to the clearance results and the number of objective function calls. The search for the worst manoeuvre is a much more complex problem. Even as the algorithms find more dangerous manoeuvres than the traditional method, it is not certain that they find the worst manoeuvres. If not other methods should be used the problem has to be rephrased. For example other optimization variables or a few linearizations of the optimization problem could reduce the complexity.
The overall impression is that the need of information and problem characteristics define which method that is most suitable to use. The information required must be weighed against the cost of objective function calls. Compared to the traditional method, the optimization methods used in this thesis give extended information about the problems examined and are better to locate the worst case.
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Kapadoukas, Georgios G. "High fidelity on and near the ground aircraft flight simulation." Thesis, University of Brighton, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.361583.
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Lindberg, Jesper. "Simulation driven reinforcement learning : Improving synthetic enemies in flight simulators." Thesis, Linköpings universitet, Statistik och maskininlärning, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-166593.
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This project focuses on how to implement an Artificial Intelligence (AI) -agent in a Tactical Simulator (Tacsi). Tacsi is a simulator used by Saab AB, one thing that the simulator is used for is pilot training. In this work, Tacsi will be used to simulate air to air combat. The agent uses Reinforcement Learning (RL) to be able to explore and learn how the simulator behaves. This knowledge will then be exploited when the agent tries to beat a computer-controlled synthetic enemy. The result of this study may be used to produce better synthetic enemies for pilot training. The RL-algorithm used in this work is deep Q-Learning, a well-known algorithm in the field. The results of the work show that it is possible to implement an RL-agent in Tacsi which can learn from the environment and be able to defeat the enemy, in some scenarios. The result produced by the algorithm verified that a RL-Agent works within Tacsi at Saab AB. Although the performance of the agent in this work is not impressive, there is a great opportunity for further development of the agent as well as the working environment.
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McCracken, Andrew. "Methods for the calculation of aerodynamic models for flight simulation." Thesis, University of Liverpool, 2014. http://livrepository.liverpool.ac.uk/19873/.
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Flight dynamics analysis using computational models is a key stage in the design of aircraft. The models used in industry consist of two main parts. The first is a tabular aerodynamic model which is essentially a large database of aerodynamic data. The tabular aerodynamic model is a highly dimensional database containing aerodynamic loads and moments for different parameter combinations. In order to reduce the size of the tables, a number of assumptions are made. These include having sufficient resolution of the parameter space to capture the variation in the flow dynamics; decoupling certain parameters to reduce the dimensionality; using a single dynamic derivative, assuming independence from the flow conditions; and finally neglecting flow history effects which are dominant during manoeuvres with highly unsteady flow phenomena. Secondly is the use of dynamic derivatives to simulate unsteady motion effects. These are calculated using small--amplitude forced oscillatory motions. In order to accelerate their computation, frequency domain methods are used. The Linear Frequency Domain and Harmonic Balance are two such methods used in this work. As part of the frequency domain calculations, linear solvers are used to provide solution to the frequency domain problem. These solvers use preconditioners to accelerate the time to solution. An alternative method of preconditioning is proposed in this work based on the first and second order spatial discretisation Jacobian matrices. It is shown that there is significant speed up achieved by varying the proportions of the first and second order terms in the preconditioner matrix. In order to assess the performance of the tabular models, an initial assessment is carried out using a hierarchy of manoeuvres of increasing complexity. For each test case, the replay from the tabular model is compared with the fully unsteady time--accurate CFD solution. This is in line with a framework proposed in the literature. It is shown that the tabular model performs well through the linear aerodynamic regime, although breaks down where history effects become significant. The assessment continues with a study of each of the assumptions used to formulate the tables. Again a hierarchy of test cases of increasing complexity is used. Also used are both forced and free--response manoeuvres. It is shown that the resolution and coupling assumptions have little impact on the performance of the tabular model. The use of a single dynamic derivative is not shown to have an impact either, although it is suggested that for more complicated manoeuvres, this could be important. Finally, the most significant error is introduced through neglecting history effects. It is shown that for manoeuvres where history effects dominate, such as those at the extremes of the flight envelope, the tabular model is not sufficient to effectively model the aerodynamics during these manoeuvres.
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Crozon, Clément. "Coupling flight mechanics and CFD : numerical simulation of shipborne rotors." Thesis, University of Liverpool, 2015. http://livrepository.liverpool.ac.uk/2030079/.
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This thesis demonstrates the use of Computational Fluid Dynamics (CFD) for the simulation of manoeuvring helicopters. Results are presented for the problem of shipborne operations, for which a literature survey showed that little work has been carried out. The CFD solver HMB2 was first validated using available experimental data for isolated ship wakes and helicopter loads at low advance ratios. A rotorcraft flight mechanics model was then developed and integrated into HMB2. The model includes a trimming method and a linearisation routine based on finite differences. The linear model of the aircraft can be used to estimate the controls applied by the pilot during a prescribed manoeuvre via the use of the SYCOS inverse-simulation method or via an LQR auto-pilot. The methods developed in the framework of this thesis include a general multi-body grid motion and an alternative formulation for earth-fixed frame of reference in the CFD. A study of the ship/rotor wake interaction was carried out using the actuator disc method that approximated the effect of the rotor, in a steady fashion and without resolving the flow around the blades. Various positions and thrust of the rotor were tested and the flowfield obtained via coupled simulations were compared with those obtained by super-imposing isolated rotor and ship flowfields. The results show that the superposition principle is not valid and leads to flowfields that have little to do with the real flow that is dominated by the interaction of helicopter and ship airwakes. The case of a rotor hovering in close proximity to a frigate deck was reproduced with fullyresolved blades, and the results shows a significant reduction of thrust due to the flow topology behind the hangar. The Helicopter Flight Mechanics (HFM) method was tested by simulating the aircraft response to a collective pilot input, using simplified models and coupled with CFD. Then, the coupled HFM/HMB2 method was used, in conjunction with the LQR auto-pilot, to simulate the phase of landing of a Sea King helicopter. Simulations were carried-out in free-air and above the frigate deck and the specified trajectories were followed adequately. Results for the ship landing show that the wake of the ship alters the obtained landing trajectory and that the current method captures some of the effects of the wake interaction.
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Timson, Emma. "Flight simulation fidelity for rotorcraft design, certification and pilot training." Thesis, University of Liverpool, 2013. http://livrepository.liverpool.ac.uk/15853/.
Full textAbstract:
The benefits of using flight simulators for rotorcraft design, certification and pilot training include reduced costs, increased safety, and control over external parameters such as environmental conditions and operational situations. The progression of technology and computing power over recent decades has led to the ability to manufacture highly sophisticated flight simulators that can be used to train complex flight operations and accurately predict the behaviour aircraft. However, such sophistication comes at a cost and there is a need to understand the trade-offs between cost and effectiveness to allow the benefits of flight simulation to be transferred to lower cost applications such as initial skills acquisition training. Assessment of simulator capabilities has traditionally been carried out with focus on the physical similarity of individual components of the simulator systems - motion system, visual system, flight model etc. However, this work is focused on the assessment of the fitness for purpose of the integrated system as a whole. This is referred throughout the thesis as perceptual fidelity, which has been defined as 'The simulator's ability to induce the behaviours known to be essential for operation of the actual aircraft in the performance of a specific task'. The novel contribution of the work in this thesis is the development of new quantitative metrics and a subjective evaluation technique that could be utilised across the simulation industry for quantification of perceptual fidelity of the overall simulation. It is intended that the methods detailed in this work could be used to support simulator development and augment current assessment techniques where appropriate. The quantitative measures of perceptual fidelity are based on comparison of ADS-33E PRF style performance metrics and the Attack metric, a control activity measure developed by Padfield et al. In this work, the utility of these metrics was assessed through correlation analyses with pilot subjective opinion. A lack of correlation in multi-axis tasks was seen and, as a result, novel metrics of pilot control strategy and adaptation have been developed in this work that show significant improvement in correlation with pilot subjective opinion. The subjective assessment methodology developed in this work is based around a new subjective rating scale – the Simulation Fidelity Rating (SFR) scale. The author contributed to the development of the SFR scale along with others at the University of Liverpool and the National Research Council (NRC) of Canada. This scale has been designed specifically to be industry applicable a d to determine the overall perceptual fidelity of the integrated simulation in a specific role. A campaign of piloted simulation and flight test trials has been conducted as the core experimental phase of this work. All the pilots completed a series of controlled experiments where a number of flying tasks were completed with a number of varied simulation models. The pilots rated each simulation against a baseline simulation using the SFR scale and their performance and control activity were recorded. This test campaign generated the pilot feedback for the development of the SFR scale and data for development of the quantitative metrics. The tests were also utilised to demonstrate how this assessment methodology can be used in controlled simulation experiments to provide previously lacking supporting evidence to simulator qualification criteria of individual components. From the analysis of the results, it was found that a more aggressive pilot excites the dynamics of the aircraft to a greater extent, thereby exposing more fidelity issues – leading to poorer SFRs. For similar reasons, an aircraft with degraded HQs was found to cause increased pilot sensitivity to transport delay. Perceptual fidelity was also found to be task dependent, In particular, pilots were found to be more susceptible to changes in off-axis response in the Acceleration-Deceleration manoeuvre than in the Precision Hover manoeuvre. These findings prove that here is a true need for simulation qualification criteria that are based on the intended use of the equipment. Significant spread was seen in the pilot ratings of perceptual fidelity in a number of cases. This was attributed partly to differing interpretation of the terminology within the Simulation Fidelity Rating (SFR) scale and also to pilot selection of task strategy. Therefore guidance material has been developed by the author from lessons learnt throughout the test campaign. This guidance material is intended to ensure best utility of the SFR scale in the future, to mitigate against the effects of differing interpretation of SFR terminology and variation in pilot task strategy through pilot briefing and correct experimental design. The SFR scale has been developed in the context of assessing a simulator for the purpose of rotary wing skills acquisition training. However, the methodologies described throughout the thesis are intended to be transferable to more sophisticated training devices for rotary-wing and fixed-wing pilot and crew training as well as for the quantification of the fidelity of certification and design simulators.
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Bagiev, Marat. "Gyroplane handling qualities assessment using flight testing and simulation techniques." Thesis, University of Glasgow, 2005. http://theses.gla.ac.uk/30918/.
Full textAbstract:
Handling qualities are without doubt one of the primary objectives of the design of modem rotary-wing aircraft, where improved handling qualities increase mission effectiveness and flight safety, and reduce pilot workload. This dissertation provides results of an assessment of gyroplane handling qualities using flight testing and simulation techniques. Since at the time of writing, there are no direct handling qualities requirements and criteria developed for light gyroplanes anywhere in the world, objective handling qualities of the G-UNIV research gyroplane are estimated using criteria from numerous fixed and rotary wing aircraft specifications. To obtain subjective handling qualities gyroplane test manoeuvres must be designed. In this thesis inverse simulation is proposed as a preliminary tool in designing gyroplane manoeuvres. A high fidelity, individual blade/blade element coupled rotor-fuselage mathematical model of a gyroplane, GSIM is developed and successfully coupled with a generic inverse simulation algorithm GENISA to form an inverse simulation package GENISA/GSIM. Two gyroplane manoeuvres, slalom and acceleration-deceleration, are designed based on those from the Aeronautical Design Standard ADS-33E-PRF. A flight test programme for the G-UNIV research gyroplane is conducted to demonstrate the use of the designed gyroplane manoeuvres and obtain subjective handling qualities. Preliminary recommendations are proposed regarding suitability of handling qualities criteria of fixed and rotary wing aircraft. In addition, this dissertation proposes two handling qualities criteria for a light gyroplane, roll quickness and pilot attack criteria for the slalom manoeuvre.
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Martin, Justin N. "Nonlinear tracking of natural mechanical systems for HWIL simulation." Auburn, Ala., 2007. http://repo.lib.auburn.edu/07M%20Theses/MARTIN_JUSTIN_8.pdf.
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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.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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Riaz, Jamshed. "A simulation model of atmospheric turbulence for rotorcraft applications." Diss., Georgia Institute of Technology, 1992. http://hdl.handle.net/1853/12940.
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Bromfield, Michael. "Criteria for acceptable stick force gradients of a light aeroplane." Thesis, Brunel University, 2012. http://bura.brunel.ac.uk/handle/2438/6861.
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During the period 1980 to 2008 there were 359 fatal accidents involving UK registered light aeroplanes of which 36% occurred in visual meteorological conditions. In all, 216 lives were lost with accidents being attributed to the pilot 'failing to maintain proper control resulting in a stall or spin'. Dissimilar fatal stallrelated accident rates are evident for aeroplane makes & models of similar design. During the course of this programme of research, flight testing of two similar aeroplane models using a case study method showed marked differences in the variation of stick force with airspeed or stick force gradient in all flight conditions. This suggested that 'control feel' was a contributory factor towards the pilot’s failure to maintain proper control. Current certification standards for light aeroplanes rely upon the subjective assessment of stick force gradients by test pilots, requiring that substantial changes in airspeed are accompanied by clearly perceptible changes in stick force with no specified minimum gradient. This programme of research has been carried out to determine acceptable criteria for stick force gradients of a light aeroplane in all flight conditions. Criteria has been determined from flight tests of aeroplanes with different in-service safety records and subjective pilot workload assessment using simulated flying tasks with different stick force gradients performed by twenty GA pilots. Simulation tests indicated that pilot mental demand increased significantly (p > 0.05) when stick force gradient was reduced to ‘zero’, representing an aeroplane with neutral longitudinal static stability. A predictive model has been developed to estimate stick force gradients for a light aeroplane in any flight condition under quasi-static, longitudinal, non-manoeuvring flight and 1-g loading conditions. The model builds upon previous published work limited to cruising flight, and enables the estimation of stick forces and gradients due to high lift devices in the climb and landing condition by consideration of the combined effects of wing loading, CG, elevator gearing, flaps and elevator trim setting. Implemented using MATLAB, the model has been validated by comparing with flight test results for the case study aeroplanes and showed mean differences of ±0.025 daN/kt. The predictive model should be used in preliminary aeroplane design to assess tendencies towards neutral stability in high workload, safety critical flight conditions such as the take-off and landing. In addition, the model should be used to analyse existing aeroplanes with comparatively low or neutral stick force gradients in safety critical flight phases and to predict the effects of changing CG and/or flap limits to increase stick force gradient and improve control feel. The combined results of these studies suggest that a minimum acceptable stick force gradient for a non-aerobatic light aeroplane in all flight conditions should be nonzero and between 0.10~0.13 daN/kt. A stable and predictable stick force variation with airspeed will ensure that any substantial deviation from trimmed airspeed is accompanied by a stick force change clearly perceptible to the pilot and also provide additional warning of the proximity to the stall. The use of specific criteria to complement qualitative test pilot opinion, will assist in confirming compliance and provide consistency with current standards for sailplanes/powered sailplanes and large commercial aeroplanes, both of which already have defined minimum acceptable gradients.
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Marsh, S. C. "A methodology to define world models for flight simulation visual system databases." Thesis, University of Sussex, 1986. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.374462.
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Pettersson, Henrik Bengt. "Variable Stability Transfer Function Simulation." Thesis, Virginia Tech, 2002. http://hdl.handle.net/10919/33503.
Full textAbstract:
Simulation, whether in-flight or ground-based, is an invaluable tool for testing and
evaluating aircraft. Classically, a simulation model is specific to a single particular airframe,
only able to model those flying characteristics. Vast information can be gained from a
simulation that is able to model a wide range of aircraft, through a comparison of the
performance of these aircraft.
Such a variable stability simulation model was created based on 46 stability parame-ters,
including natural frequencies, damping ratios, time constants, and gains. The simula-tion
was obtained using transfer functions representing the aircraft state responses to control
inputs. These transfer functions were converted into state space systems used to create the
linear equations for the model.
The model was first developed as a desktop simulation and then converted for use
with the Virginia Techâ s 2F122A flight simulator. This conversion required a simple dynamic
inversion of the body axis force and moment terms. To reduce the error in these terms, a
model following scheme was incorporated.
A series of canned inputs and real-time pilot-in-the-loop tests were flown to evaluate
the variable stability model. Results in this paper have demonstrated the successful creation
of a variable stability simulation model.Master of Science
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Gustafsson, Anders. "Use of head mounted virtual reality displays in flight training simulation." Thesis, Linköpings universitet, Programvara och system, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-154016.
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The purpose of this thesis was to evaluate currently commercially available head mounted virtual reality displays for potential use in pilot training simulators. For this purpose acommercial simulator was modified to display the virtual environment in an Oculus RiftDK2 headset. A typical monitor based setup was used to provide a set of hardware requirements which the VR implementation had to meet or exceed to be considered potentially usable for pilot training simulators. User tests were then performed with a group of users representative of those normally using pilot training simulators, including both pilots and engineers working with simulator development. The main focus of the user tests was to evaluate some potential weaknesses found in the technical comparison (such as when a measured parameter was close to the lower limit defined by the monitor based setup) and to make a measurement of the usability of the VR implementation. The results from the technical comparison showed that the technical requirements were met and in most cases also exceeded. There were however some potential weaknesses revealed during the user tests, which included screen resolution and the field of view. There was one main critical deficiency found during the user tests. This was the lack of interaction with the aircraft as users were only able to interact with the flight stick and throttle lever. While this enabled the users to control many aspects of the aircraft (by using buttons and other controls fitted on the flight stick/throttle) in a training scenario a user also has to be able to interact with other switches and/or monitors in the cockpit. This was however a known limitation of the implementation and thus didn’t affect the tested parts of the simulator. The user tests also confirmed that the resolution was a potential problem, but that the overall usability was high. Thus the VR implementation had potential for use in a pilot training simulator, if the critical issues found during the user tests were solved.
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Glenney, Kevin Harold. "Preliminary in-flight ice accretion measurements for validation of simulation methods." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1999. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape8/PQDD_0004/MQ43340.pdf.
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Covelli, Javier. "Field of View Effects on Reflexive Motor Response in Flight Simulation." Doctoral diss., University of Central Florida, 2008. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/3108.
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Virtual Reality (VR) and Augmented Reality (AR) Head Mounted Display (HMD) or Head Worn Display (HWD) technology represents low-cost, wide Field of Regard (FOR), deployable systems when compared to traditional simulation facilities. However, given current technological limitations, HWD flight simulator implementations provide a limited effective Field of View (eFOV) far narrower than the normal human 200[degrees] horizontal and 135[degrees] vertical FOV. Developing a HWD with such a wide FOV is expensive but can increase the aviator's visual stimulus, perception, sense of presence and overall training effectiveness. This research and experimentation test this proposition by manipulating the eFOV of experienced pilots in a flight simulator while measuring their reflexive motor response and task performance. Reflexive motor responses are categorized as information, importance and effort behaviors. Performance metrics taken include runway alignment error (RAE) and vertical track error (VTE). Results indicated a significant and systematic change in visual scan pattern, head movement and flight control performance as the eFOV was sequentially decreased. As FOV decreased, the average visual scan pattern changed to focus less on out-the-window (OTW) and more on the instruments inside the cockpit. The head range of movement significantly increased below 80[degrees] horizontal x 54[degrees] vertical eFOV as well as significantly decreasing runway alignment and vertical track performance, which occurred below 120[degrees] horizontal x 81[degrees] vertical eFOV.Ph.D.
Department of Psychology
Sciences
Modeling and Simulation PhD
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Enright, John Patrick 1974. "A flight software development and simulation framework for advanced space systems." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/29911.
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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2002.Includes bibliographical references (p. 293-302).
Distributed terrestrial computer systems employ middleware software to provide communications abstractions and reduce software interface complexity. Embedded applications are adopting the same approaches, but must make provisions to ensure that hard real-time temporal performance can be maintained. This thesis presents the development and validation of a middleware system tailored to spacecraft flight software development. Our middleware runs on the Generalized Flight Operations Processing Simulator (GFLOPS) and is called the GFLOPS Rapid Real-time Development Environment (GRRDE). GRRDE provides publish-subscribe communication services between software components. These services help to reduce the complexity of managing software interfaces. The hard real-time performance of these services has been verified with General Timed Automata modelling and extensive run-time testing. Several example applications illustrate the use of GRRDE to support advanced flight software development. Two technology-focused studies examine automatic code generation and autonomous fault protection within the GRRDE framework. A complex simulation of the TechSat 21 distributed spacebased radar mission highlights the utility of the approach for large-scale applications.
by John Patrick Enright.
Ph.D.
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Swol, Christopher Douglas. "Simulation-Based Analysis of Wake Turbulence Encounters in Current Flight Operations." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/34809.
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One way to address the need for increased airspace system capacity is to reduce the separation requirements between aircraft in-flight. A key limiting factor to any reduction in separation is wake turbulence. The potential for aircraft to encounter wake turbulence poses a threat to both safety as well as increased efficiency. This research effort seeks to develop a model that can be used to evaluate the potential for wake encounters in todayâ s flight operations, as well as serve as a tool for evaluating future reduced separation scenarios. The wake encounter model (WEM) achieves this goal by integrating results from NASAâ s TDAWP wake turbulence prediction model with a flight operations model based on radar flight track data. Unique in this modelâ s design, is the ability to evaluate the potential for wake encounters throughout the terminal area versus previous research which has largely been restricted to areas near the runway. Expanding the modelâ s reach provides not only for a more thorough analysis of potential wake encounters, but also creates an effective tool for evaluating future reduced separation scenarios.
The WEM model was used to evaluate operations at three metropolitan airspaces in the United States: Atlanta, Los Angeles and New York. The results from these model runs indicated that potential wake encounters in todayâ s operations were few. More importantly, the results from the WEM create a baseline for wake turbulence exposure in todayâ s system, by which future scenarios can be compared against as part of any comprehensive reduced separation safety analysis.
Master of Science
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Reel, Brian H. "A FLIGHT SIMULATION STUDY OF THE SIMULTANEOUS NON-INTERFERING AIRCRAFT APPROACH." DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/80.
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Using a new implementation of a NASA flight simulation of the Quiet Short-Haul Research Aircraft, autopilots were designed to be capable of flying both straight in (ILS) approaches, and circling (SNI) approaches. A standard glideslope coupler was sufficient for most conditions, but a standard Proportional-Integral-Derivative (PID) based localizer tracker was not sufficient for maintaining a lateral track on the SNI course. To track the SNI course, a feed-forward system, using GPS steering provided much better results.
NASA and the FAA embrace the concept of a Simultaneous, Non-Interfering (SNI) approach as a way to increase airport throughput while reducing the noise footprints of aircraft on approach. The NASA concept for the SNI approach for Short Takeoff and Landing (STOL) aircraft involves a straight in segment flown above the flight path of a normal approach, followed by a spiraling descent to the runway. As this is a procedure that would be utilized by regional airliners, it is assumed that it would be conducted under Instrument Flight Rules (IFR).
GPS or INS guidance would be required to fly this approach, and it is likely that it would be necessary to fly the approach with a coupled autopilot: a stabilized, curving, instrument approach to decision altitude would be exceedingly difficult to fly. The autopilots in many current commuter and general aviation aircraft, however, were designed before the event of GPS, and do not have provisions for tracking curved paths. This study identifies problem areas in implementing the SNI circling approach on aircraft and avionics as they stand today and also gives examples of what can be done for the SNI approach to be successful.
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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.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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Glenney, Kevin Harold Carleton University Dissertation Engineering Mechanical and Aerospace. "Preliminary in-flight ice accretion measurements for validation of simulation methods." Ottawa, 1999.
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Lewin, Mark James Chemistry Faculty of Science UNSW. "Instrument development and computational studies of time-of-flight mass spectrometers." Awarded by:University of New South Wales, 2006. http://handle.unsw.edu.au/1959.4/39745.
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A computer program to simulate peak shapes from time-of-flight (TOF) mass spectrometers has been developed and significantly improved from a previous, unpublished version. This program can accurately simulate both TOF and orthogonal acceleration TOF mass analyser peak shapes, with contributions from initial ion properties, instrument geometry, and other factors including high voltage ripple and detector response. Grid effects have also been included, and simulations for two mass spectrometers are compared to actual recorded spectra. The dispersive effect on ion trajectories of parallel wires and grids has been computationally studied and a model derived for each case. The model is based on the effect wire geometry has on the intrinsic focussing effect of the grid. The models for parallel wires and rectangular grids have been coded into the simulation program described above, and the effect of grids on peak shapes in TOF mass spectrometers has been studied. Good correlation between simulated and actual peak shapes for rectangular grids was obtained for grids in different rotational orientations. A pulsed lens has been developed to reduce the velocity spread of ions in matrix assisted laser desorption/ionisation (MALDI) ion sources, with the aim to increase sensitivity in orthogonal acceleration TOF mass analysers. The system gave an increase in sensitivity of approximately five times over a range of masses, however instrument resolving power was reduced. A rotating sample stage was developed for MALDI mass spectrometers which offers the potential of high sample density, high positional accuracy and repeatability, and low seek times. The system involves reading the position of a disk mounted with MALDI sample spots and timing the laser pulse to coincide with spot availability at an aperture. The system was successfully used to perform mass calibration by using a calibrant sample located on a separate spot to the analyte. Mass resolved disk imaging was also performed over a disk radius using inks. The mass resolved image compared well to the optical image.
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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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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.Ph.D.
Department of Industrial Engineering and Management Systems
Engineering and Computer Science
Industrial Engineering and Management Systems