subject:(Flight simulation)

Addis Ababa University

1. Mathewos, Essatu. SIMULATION OF FLIGHT FOLLOWING SYSTEM .

Degree: 2012, Addis Ababa University

URL: http://etd.aau.edu.et/dspace/handle/123456789/4410

► The simulation of the flight following system i6 primarily chosen in the interest of Ethiopian Airlines need to implement the system to replace the currently… (more)

Subjects/Keywords: SIMULATION OF FLIGHT

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APA (6^th Edition):

Mathewos, E. (2012). SIMULATION OF FLIGHT FOLLOWING SYSTEM . (Thesis). Addis Ababa University. Retrieved from http://etd.aau.edu.et/dspace/handle/123456789/4410

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Mathewos, Essatu. “SIMULATION OF FLIGHT FOLLOWING SYSTEM .” 2012. Thesis, Addis Ababa University. Accessed January 18, 2021. http://etd.aau.edu.et/dspace/handle/123456789/4410.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Mathewos, Essatu. “SIMULATION OF FLIGHT FOLLOWING SYSTEM .” 2012. Web. 18 Jan 2021.

Vancouver:

Mathewos E. SIMULATION OF FLIGHT FOLLOWING SYSTEM . [Internet] [Thesis]. Addis Ababa University; 2012. [cited 2021 Jan 18]. Available from: http://etd.aau.edu.et/dspace/handle/123456789/4410.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Mathewos E. SIMULATION OF FLIGHT FOLLOWING SYSTEM . [Thesis]. Addis Ababa University; 2012. Available from: http://etd.aau.edu.et/dspace/handle/123456789/4410

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Uppsala University

2. Bylander, Ulf. Flight Path Simulation Application : A flight simulator for charged particle transport.

Degree: High Energy Physics, 2014, Uppsala University

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-227759

► CTF3 is a test facility for a new CLIC high energy linear collider. For this beamsteering and beam focusing is vital. Because physically running… (more)

Subjects/Keywords: Simulation flight path

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APA (6^th Edition):

Bylander, U. (2014). Flight Path Simulation Application : A flight simulator for charged particle transport. (Thesis). Uppsala University. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-227759

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Bylander, Ulf. “Flight Path Simulation Application : A flight simulator for charged particle transport.” 2014. Thesis, Uppsala University. Accessed January 18, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-227759.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Bylander, Ulf. “Flight Path Simulation Application : A flight simulator for charged particle transport.” 2014. Web. 18 Jan 2021.

Vancouver:

Bylander U. Flight Path Simulation Application : A flight simulator for charged particle transport. [Internet] [Thesis]. Uppsala University; 2014. [cited 2021 Jan 18]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-227759.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Bylander U. Flight Path Simulation Application : A flight simulator for charged particle transport. [Thesis]. Uppsala University; 2014. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-227759

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Uppsala University

3. Bylander, Ulf. Flight Path Simulation Application : A flight simulator for charged particle transport.

Degree: High Energy Physics, 2014, Uppsala University

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-231090

►

CTF3 is a test facility for a new CLIC high energy linear collider. For this beamsteering and beam focusing is vital. Because physically running… (more)

Subjects/Keywords: Simulation flight path

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APA (6^th Edition):

Bylander, U. (2014). Flight Path Simulation Application : A flight simulator for charged particle transport. (Thesis). Uppsala University. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-231090

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Bylander, Ulf. “Flight Path Simulation Application : A flight simulator for charged particle transport.” 2014. Thesis, Uppsala University. Accessed January 18, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-231090.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Bylander, Ulf. “Flight Path Simulation Application : A flight simulator for charged particle transport.” 2014. Web. 18 Jan 2021.

Vancouver:

Bylander U. Flight Path Simulation Application : A flight simulator for charged particle transport. [Internet] [Thesis]. Uppsala University; 2014. [cited 2021 Jan 18]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-231090.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Bylander U. Flight Path Simulation Application : A flight simulator for charged particle transport. [Thesis]. Uppsala University; 2014. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-231090

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Brunel University

4. Bromfield, Michael. Criteria for acceptable stick force gradients of a light aeroplane.

Degree: PhD, 2012, Brunel University

URL: http://bura.brunel.ac.uk/handle/2438/6861 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.557870

► 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… (more)

▼ 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…

Subjects/Keywords: 363.12; Flight safety; Control feel; Pilot workload; Flight simulation; Flight test

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APA (6^th Edition):

Bromfield, M. (2012). Criteria for acceptable stick force gradients of a light aeroplane. (Doctoral Dissertation). Brunel University. Retrieved from http://bura.brunel.ac.uk/handle/2438/6861 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.557870

Chicago Manual of Style (16^th Edition):

Bromfield, Michael. “Criteria for acceptable stick force gradients of a light aeroplane.” 2012. Doctoral Dissertation, Brunel University. Accessed January 18, 2021. http://bura.brunel.ac.uk/handle/2438/6861 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.557870.

MLA Handbook (7^th Edition):

Bromfield, Michael. “Criteria for acceptable stick force gradients of a light aeroplane.” 2012. Web. 18 Jan 2021.

Vancouver:

Bromfield M. Criteria for acceptable stick force gradients of a light aeroplane. [Internet] [Doctoral dissertation]. Brunel University; 2012. [cited 2021 Jan 18]. Available from: http://bura.brunel.ac.uk/handle/2438/6861 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.557870.

Council of Science Editors:

Bromfield M. Criteria for acceptable stick force gradients of a light aeroplane. [Doctoral Dissertation]. Brunel University; 2012. Available from: http://bura.brunel.ac.uk/handle/2438/6861 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.557870

Texas A&M University

5. Harris, Joshua A. Nonlinear Adaptive Dynamic Inversion Control for Variable Stability Small Unmanned Aircraft Systems.

Degree: MS, Aerospace Engineering, 2017, Texas A&M University

URL: http://hdl.handle.net/1969.1/169626

► In-flight simulation and variable stability aircraft provide useful capabilities for flight controls development such as testing control laws for new aircraft earlier, identification of adverse… (more)

Subjects/Keywords: adaptive control; dynamic inversion; flight control; in-flight simulation

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APA (6^th Edition):

Harris, J. A. (2017). Nonlinear Adaptive Dynamic Inversion Control for Variable Stability Small Unmanned Aircraft Systems. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/169626

Chicago Manual of Style (16^th Edition):

Harris, Joshua A. “Nonlinear Adaptive Dynamic Inversion Control for Variable Stability Small Unmanned Aircraft Systems.” 2017. Masters Thesis, Texas A&M University. Accessed January 18, 2021. http://hdl.handle.net/1969.1/169626.

MLA Handbook (7^th Edition):

Harris, Joshua A. “Nonlinear Adaptive Dynamic Inversion Control for Variable Stability Small Unmanned Aircraft Systems.” 2017. Web. 18 Jan 2021.

Vancouver:

Harris JA. Nonlinear Adaptive Dynamic Inversion Control for Variable Stability Small Unmanned Aircraft Systems. [Internet] [Masters thesis]. Texas A&M University; 2017. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1969.1/169626.

Council of Science Editors:

Harris JA. Nonlinear Adaptive Dynamic Inversion Control for Variable Stability Small Unmanned Aircraft Systems. [Masters Thesis]. Texas A&M University; 2017. Available from: http://hdl.handle.net/1969.1/169626

Mississippi State University

6. Germann, Kenneth Paul. T-6A TEXAN II IN-FLIGHT SIMULATION AND VARIABLE STABILITY SYSTEM DESIGN.

Degree: PhD, Aerospace Engineering, 2009, Mississippi State University

URL: http://sun.library.msstate.edu/ETD-db/theses/available/etd-12162009-091123/ ;

► In-flight variable stability aircraft and in-flight simulation are described. The uses of these vehicles and the associated requirements are described. Several forms of control architecture… (more)

Subjects/Keywords: control; simulation; flight

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APA (6^th Edition):

Germann, K. P. (2009). T-6A TEXAN II IN-FLIGHT SIMULATION AND VARIABLE STABILITY SYSTEM DESIGN. (Doctoral Dissertation). Mississippi State University. Retrieved from http://sun.library.msstate.edu/ETD-db/theses/available/etd-12162009-091123/ ;

Chicago Manual of Style (16^th Edition):

Germann, Kenneth Paul. “T-6A TEXAN II IN-FLIGHT SIMULATION AND VARIABLE STABILITY SYSTEM DESIGN.” 2009. Doctoral Dissertation, Mississippi State University. Accessed January 18, 2021. http://sun.library.msstate.edu/ETD-db/theses/available/etd-12162009-091123/ ;.

MLA Handbook (7^th Edition):

Germann, Kenneth Paul. “T-6A TEXAN II IN-FLIGHT SIMULATION AND VARIABLE STABILITY SYSTEM DESIGN.” 2009. Web. 18 Jan 2021.

Vancouver:

Germann KP. T-6A TEXAN II IN-FLIGHT SIMULATION AND VARIABLE STABILITY SYSTEM DESIGN. [Internet] [Doctoral dissertation]. Mississippi State University; 2009. [cited 2021 Jan 18]. Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-12162009-091123/ ;.

Council of Science Editors:

Germann KP. T-6A TEXAN II IN-FLIGHT SIMULATION AND VARIABLE STABILITY SYSTEM DESIGN. [Doctoral Dissertation]. Mississippi State University; 2009. Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-12162009-091123/ ;

McMaster University

7. Zeitoun, Omar. A Distributed System Interface for a Flight Simulator.

Degree: MASc, 2014, McMaster University

URL: http://hdl.handle.net/11375/16298

►

The importance of flight training has been realized since the inception of manned flight. In this thesis, a project about the interfacing of hardware cockpit… (more)

Subjects/Keywords: flight simulation; distributed system; interface; cessna 172

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APA (6^th Edition):

Zeitoun, O. (2014). A Distributed System Interface for a Flight Simulator. (Masters Thesis). McMaster University. Retrieved from http://hdl.handle.net/11375/16298

Chicago Manual of Style (16^th Edition):

Zeitoun, Omar. “A Distributed System Interface for a Flight Simulator.” 2014. Masters Thesis, McMaster University. Accessed January 18, 2021. http://hdl.handle.net/11375/16298.

MLA Handbook (7^th Edition):

Zeitoun, Omar. “A Distributed System Interface for a Flight Simulator.” 2014. Web. 18 Jan 2021.

Vancouver:

Zeitoun O. A Distributed System Interface for a Flight Simulator. [Internet] [Masters thesis]. McMaster University; 2014. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/11375/16298.

Council of Science Editors:

Zeitoun O. A Distributed System Interface for a Flight Simulator. [Masters Thesis]. McMaster University; 2014. Available from: http://hdl.handle.net/11375/16298

University of Toronto

8. Khan, Jacek Filip. The Role of Internal Noise in Self-Motion Perception.

Degree: 2016, University of Toronto

URL: http://hdl.handle.net/1807/74961

►

In this study, vestibular-based motion perception was investigated. The vestibular system, located in the inner ear, is responsible for sensing translational and rotational motion. A… (more)

Subjects/Keywords: Flight Simulation; Motion Perception; Threshold; Vestibular; 0538

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APA (6^th Edition):

Khan, J. F. (2016). The Role of Internal Noise in Self-Motion Perception. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/74961

Chicago Manual of Style (16^th Edition):

Khan, Jacek Filip. “The Role of Internal Noise in Self-Motion Perception.” 2016. Masters Thesis, University of Toronto. Accessed January 18, 2021. http://hdl.handle.net/1807/74961.

MLA Handbook (7^th Edition):

Khan, Jacek Filip. “The Role of Internal Noise in Self-Motion Perception.” 2016. Web. 18 Jan 2021.

Vancouver:

Khan JF. The Role of Internal Noise in Self-Motion Perception. [Internet] [Masters thesis]. University of Toronto; 2016. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1807/74961.

Council of Science Editors:

Khan JF. The Role of Internal Noise in Self-Motion Perception. [Masters Thesis]. University of Toronto; 2016. Available from: http://hdl.handle.net/1807/74961

Nanyang Technological University

9. Xie, Zhen. Forecasting, visibility and 3D route optimization for future air traffic management .

Degree: 2018, Nanyang Technological University

URL: http://hdl.handle.net/10220/45896

► Based on time-series Recurrent Neural Network (RNN) forecasting results, air traffic volumes and air passenger volumes will keep increasing for the coming decades. It will… (more)

▼ Based on time-series Recurrent Neural Network (RNN) forecasting results, air traffic volumes and air passenger volumes will keep increasing for the coming decades. It will challenge the current airport capacity including runway capacity and terminal capacity. The airport group can improve the airport service efficiency and resource usage rate or build more facilities to meet the passenger demand. Moreover, air traffic volume forecasting demands better route structure as the number of aircraft goes up rapidly and current rigid route structure cannot meet the future traffic demand. Free flight concept emerged as a result of the development of advanced tracking, prediction and communication equipment. Artificial-Intelligence (AI)-based free flight increases the safety operation of the flight especially in adverse weather conditions and congested airspace as free route leads to more direct or wind-optimal trajectory. In the context of next generation of air traffic management (ATM) and implementation of automatic dependent surveillance – broadcast (ADS-B), the author proposed methods that can help to build safer and more efficient ATM systems. That is to say, the author applies a novel 3D multi-agent path planning method based on the free route airspace (FRA) concept in the ASEAN region and uses visual conspicuity experiments to guide the visual factors in order to obtain maximum visibility of the aircraft for tower controllers. On one hand, in order to better cater the increasing traffic volume, the author invented and validated a novel 3D multi-agent path-planning algorithm for the commercial aircraft to find a more efficient route, especially under adverse weather conditions. By implementing this path-planning algorithm in free-flight route structure, airspace capacity can be increased significantly. Since pilots can plan the aircraft freely between entry points and exit points, there is a decrease in workload for Air Traffic Control Officers (ATCOs). Moreover, the advantages of changing to this route structure include lower flight traveling time and decreased energy consumption. This route structure could contribute significantly to curb climate change impact due to the fact that greenhouse gases are mostly emitted from vehicles and aircraft. On the other hand, visual conspicuity for airplane approaching and departing in the vicinity of the airport or in the airspace is very important for the safety of aircraft. Studies on visual factors can improve visibility for the surrounding environment. Visual conspicuity field tests tend to cost a lot and require huge amount of human resources. Moreover, it is restricted by the schedules and regulations of the airport. Thus, lab simulation can replace field tests and generate the desired scenes easily. We use commercial image processing software to create the desired scenarios with the changing of the visual parameters based on the Airbus A320 and Boeing B737-800 SolidWorks models. The results show that visual conspicuity is related to visual factors including lightness,…

Subjects/Keywords: DRNTU::Engineering::Aeronautical engineering::Flight simulation

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APA (6^th Edition):

Xie, Z. (2018). Forecasting, visibility and 3D route optimization for future air traffic management . (Thesis). Nanyang Technological University. Retrieved from http://hdl.handle.net/10220/45896

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Xie, Zhen. “Forecasting, visibility and 3D route optimization for future air traffic management .” 2018. Thesis, Nanyang Technological University. Accessed January 18, 2021. http://hdl.handle.net/10220/45896.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Xie, Zhen. “Forecasting, visibility and 3D route optimization for future air traffic management .” 2018. Web. 18 Jan 2021.

Vancouver:

Xie Z. Forecasting, visibility and 3D route optimization for future air traffic management . [Internet] [Thesis]. Nanyang Technological University; 2018. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/10220/45896.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Xie Z. Forecasting, visibility and 3D route optimization for future air traffic management . [Thesis]. Nanyang Technological University; 2018. Available from: http://hdl.handle.net/10220/45896

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Toronto

10. Abbasi, Humayoon. Simulation of Flexible Aircraft.

Degree: 2010, University of Toronto

URL: http://hdl.handle.net/1807/24523

►

This study aims to improve flight simulation of flexible aircraft. More specifically, this thesis concentrates on comparing two flexible aircraft flight simulation models. Both modeling… (more)

Subjects/Keywords: Simulation; Flexible; Deformable; Flight Dynamics; 0538

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APA (6^th Edition):

Abbasi, H. (2010). Simulation of Flexible Aircraft. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/24523

Chicago Manual of Style (16^th Edition):

Abbasi, Humayoon. “Simulation of Flexible Aircraft.” 2010. Masters Thesis, University of Toronto. Accessed January 18, 2021. http://hdl.handle.net/1807/24523.

MLA Handbook (7^th Edition):

Abbasi, Humayoon. “Simulation of Flexible Aircraft.” 2010. Web. 18 Jan 2021.

Vancouver:

Abbasi H. Simulation of Flexible Aircraft. [Internet] [Masters thesis]. University of Toronto; 2010. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1807/24523.

Council of Science Editors:

Abbasi H. Simulation of Flexible Aircraft. [Masters Thesis]. University of Toronto; 2010. Available from: http://hdl.handle.net/1807/24523

University of Southern California

11. Kerci, Endri. The effect of Xᵤ and T_{theta_2} on autonomous in-flight refueling: a global Hawk RQ-4A approach.

Degree: MS, Aerospace Engineering, 2013, University of Southern California

URL: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/306375/rec/6632

► The effect of two parameters, Xᵤ and T_theta₂ , are explored for their influence on autonomous in-flight aerial refueling. It is believed that these two… (more)

Subjects/Keywords: autonomous; Global Hawk; in-flight refueling; simulation

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APA (6^th Edition):

Kerci, E. (2013). The effect of Xᵤ and T_{theta_2} on autonomous in-flight refueling: a global Hawk RQ-4A approach. (Masters Thesis). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/306375/rec/6632

Chicago Manual of Style (16^th Edition):

Kerci, Endri. “The effect of Xᵤ and T_{theta_2} on autonomous in-flight refueling: a global Hawk RQ-4A approach.” 2013. Masters Thesis, University of Southern California. Accessed January 18, 2021. http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/306375/rec/6632.

MLA Handbook (7^th Edition):

Kerci, Endri. “The effect of Xᵤ and T_{theta_2} on autonomous in-flight refueling: a global Hawk RQ-4A approach.” 2013. Web. 18 Jan 2021.

Vancouver:

Kerci E. The effect of Xᵤ and T_{theta_2} on autonomous in-flight refueling: a global Hawk RQ-4A approach. [Internet] [Masters thesis]. University of Southern California; 2013. [cited 2021 Jan 18]. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/306375/rec/6632.

Council of Science Editors:

Kerci E. The effect of Xᵤ and T_{theta_2} on autonomous in-flight refueling: a global Hawk RQ-4A approach. [Masters Thesis]. University of Southern California; 2013. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/306375/rec/6632

Linköping University

12. Gustafsson, Anders. Use of head mounted virtual reality displays in flight training simulation.

Degree: Software and Systems, 2018, Linköping University

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-154016

► The purpose of this thesis was to evaluate currently commercially available head mounted virtual reality displays for potential use in pilot training simulators. For… (more)

▼ 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.

Subjects/Keywords: VR; Virtual reality; Flight simulation; Flight training simulation; Head mounted displays; HMD; Computer Engineering; Datorteknik

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APA (6^th Edition):

Gustafsson, A. (2018). Use of head mounted virtual reality displays in flight training simulation. (Thesis). Linköping University. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-154016

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Gustafsson, Anders. “Use of head mounted virtual reality displays in flight training simulation.” 2018. Thesis, Linköping University. Accessed January 18, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-154016.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Gustafsson, Anders. “Use of head mounted virtual reality displays in flight training simulation.” 2018. Web. 18 Jan 2021.

Vancouver:

Gustafsson A. Use of head mounted virtual reality displays in flight training simulation. [Internet] [Thesis]. Linköping University; 2018. [cited 2021 Jan 18]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-154016.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Gustafsson A. Use of head mounted virtual reality displays in flight training simulation. [Thesis]. Linköping University; 2018. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-154016

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Toronto

13. Ko, Shuk Fai (Eska). Investigation of Simulator Motion Drive Algorithms for Airplane Upset Simulation.

Degree: 2012, University of Toronto

URL: http://hdl.handle.net/1807/35019

►

Currently, it is uncertain how well a typical ground-based simulator's hexapod motion system can simulate the aggressive motion during airplane upset. To address this issue,… (more)

Subjects/Keywords: Motion Drive Algorithms; Flight Simulation; Airplane upset; Upset Recovery Simulation; 0538

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APA (6^th Edition):

Ko, S. F. (. (2012). Investigation of Simulator Motion Drive Algorithms for Airplane Upset Simulation. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/35019

Chicago Manual of Style (16^th Edition):

Ko, Shuk Fai (Eska). “Investigation of Simulator Motion Drive Algorithms for Airplane Upset Simulation.” 2012. Masters Thesis, University of Toronto. Accessed January 18, 2021. http://hdl.handle.net/1807/35019.

MLA Handbook (7^th Edition):

Ko, Shuk Fai (Eska). “Investigation of Simulator Motion Drive Algorithms for Airplane Upset Simulation.” 2012. Web. 18 Jan 2021.

Vancouver:

Ko SF(. Investigation of Simulator Motion Drive Algorithms for Airplane Upset Simulation. [Internet] [Masters thesis]. University of Toronto; 2012. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1807/35019.

Council of Science Editors:

Ko SF(. Investigation of Simulator Motion Drive Algorithms for Airplane Upset Simulation. [Masters Thesis]. University of Toronto; 2012. Available from: http://hdl.handle.net/1807/35019

14. Ackerman, Kasey. Development of a pilot-in-the-loop flight simulator using NASA's transport class model.

Degree: MS, 0133, 2014, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/50650

► This thesis presents the development of an immersive flight simulator at the University of Illinois at Urbana-Champaign using NASA's Transport Class Model. Flight simulators are… (more)

Subjects/Keywords: flight simulation; simulation software

…architecture will require extensive software and PITL simulation prior to flight tests using a… …the need to develop a method for improving simulation performance during flight testing, and… …simulations, desktop flight simulation, or full-scale PITL testing without the need to implement the… …and flight control software tools are implemented. Depending on the simulation mode, the… …flight simulation and desktop piloted simulation, a pacer block provided by NASA is used in the…

7 more images…

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APA (6^th Edition):

Ackerman, K. (2014). Development of a pilot-in-the-loop flight simulator using NASA's transport class model. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/50650

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Ackerman, Kasey. “Development of a pilot-in-the-loop flight simulator using NASA's transport class model.” 2014. Thesis, University of Illinois – Urbana-Champaign. Accessed January 18, 2021. http://hdl.handle.net/2142/50650.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Ackerman, Kasey. “Development of a pilot-in-the-loop flight simulator using NASA's transport class model.” 2014. Web. 18 Jan 2021.

Vancouver:

Ackerman K. Development of a pilot-in-the-loop flight simulator using NASA's transport class model. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2014. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/2142/50650.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Ackerman K. Development of a pilot-in-the-loop flight simulator using NASA's transport class model. [Thesis]. University of Illinois – Urbana-Champaign; 2014. Available from: http://hdl.handle.net/2142/50650

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Cranfield University

15. Lone, M. Mudassir. Pilot modelling for airframe loads analysis.

Degree: PhD, 2013, Cranfield University

URL: http://dspace.lib.cranfield.ac.uk/handle/1826/10388

► The development of large lightweight airframes has resulted in what used to be high frequency structural dynamics entering the low frequency range associated with an… (more)

▼ The development of large lightweight airframes has resulted in what used to be high frequency structural dynamics entering the low frequency range associated with an aircraft’s rigid body dynamics. This has led to the potential of adverse interactions between the aeroelastic effects and flight control, especially unwanted when incidents involving failures or extreme atmospheric disturbances occur. Moreover, the pilot’s response in such circumstances may not be reproducible in simulators and unique to the incident. The research described in this thesis describes the development of a pilot model suitable for the investigation of the effects of aeroelasticity on manual control and the study of the resulting airframe loads. After a review of the state-ofthe- art in pilot modelling an experimental approach involving desktop based pilot-in-the-loop simulation was adopted together with an optimal control based control-theoretic pilot model. The experiments allowed the investigation of manual control with a nonlinear flight control system and the derivation of parameter bounds for single-input-single-output pilot models. It was found that pilots could introduce variations of around 15 dB at the resonant frequency of the open loop pilot-vehicle-system. Sensory models suitable for the simulation of spatial disorientation effects were developed together with biomechanical models necessary to capture biodynamic feedthrough effects. A detailed derivation and method for the application of the modified optimal control pilot model, used to generate pilot control action, has also been shown in the contexts of pilot-model-in-the-loop simulations of scenarios involving an aileron failure and a gust encounter. It was found that manual control action particularly exacerbated horizontal tailplane internal loads relative to the limit loads envelope. Although comparisons with digital flight data recordings of an actual gust encounter showed a satisfactory reproduction and highlighted the adverse affects of fuselage flexibility on manual control, it also pointed towards the need for more incident data to validate such simulations.

Subjects/Keywords: Pilot modelling; manual control; pilot-model-in-the-loop simulation; flight loads; aeroelastics; flight control

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APA (6^th Edition):

Lone, M. M. (2013). Pilot modelling for airframe loads analysis. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/10388

Chicago Manual of Style (16^th Edition):

Lone, M Mudassir. “Pilot modelling for airframe loads analysis.” 2013. Doctoral Dissertation, Cranfield University. Accessed January 18, 2021. http://dspace.lib.cranfield.ac.uk/handle/1826/10388.

MLA Handbook (7^th Edition):

Lone, M Mudassir. “Pilot modelling for airframe loads analysis.” 2013. Web. 18 Jan 2021.

Vancouver:

Lone MM. Pilot modelling for airframe loads analysis. [Internet] [Doctoral dissertation]. Cranfield University; 2013. [cited 2021 Jan 18]. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/10388.

Council of Science Editors:

Lone MM. Pilot modelling for airframe loads analysis. [Doctoral Dissertation]. Cranfield University; 2013. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/10388

University of Victoria

16. Klein-Miloslavich, Andreas. Modeling, simulation, hardware development, and testing of a lab-scale airborne wind energy system.

Degree: Department of Mechanical Engineering, 2020, University of Victoria

URL: http://hdl.handle.net/1828/11508

► Airborne Wind Energy Systems (AWES) harness the power of high-altitude winds using tethered planes or kites. Continuous and reliable operation requires that AWES become autonomous… (more)

▼ Airborne Wind Energy Systems (AWES) harness the power of high-altitude winds using tethered planes or kites. Continuous and reliable operation requires that AWES become autonomous devices, but the wind intermittency forces the system to repeatedly take-off to start, and land to shut-off. Therefore, a common approach to facilitate the operation is implementing Vertical take-off and landing (VTOL) functionality. This thesis models and simulates AWES flights working towards the implementation of flight controller hardware and autonomous operation of an AWES demonstrator platform. The Ardupilot open-source autopilot platform provides a convenient tool for modeling, simulation, and hardware implementation of small-scale airplanes. An AWES lab-scale demonstrator was developed to obtain operational insight, get preliminary flight data, and real-world experience in this technology. A quadplane was developed by combining a structurally reinforced glider with VTOL and autopilot components. Its performance is obtained from static and aerodynamic studies and converted into the Ardupilot parameter format to define it in the simulation. An AWES flight model was developed from the ground up to evaluate the performance of a simple flight controller in trajectory tracking. The Ardupilot Software-in-Loop (SIL) tool expands the simulation capabilities by running the flight controller code without requiring any hardware. This allowed controller tuning and flight plan evaluation with a more advanced fight model. AWES crosswind flight simulation was only possible due to the incorporation of an elastic tether and an ideal winch into the physics model. As a result, different trajectories and configurations were tested to find the optimal parameters that were uploaded to the flight controller board. The operational capabilities of the AWES demonstrator were expanded with a flight testing campaign. By targeting individual objectives, each test gradually increased its complexity and ensured that the flight envelope was safely expanded. The results were validated with the simulation before moving on to the next flight test. The testing campaign is still underway due to challenges and limitations presented by the legal and logistical aspects of operating the quadplane. However, preliminary flight tests in VTOL mode have been completed and were consistent with the simulated results in terms of autonomous waypoint navigation and attitude control. Advisors/Committee Members: Crawford, Curran (supervisor).

Subjects/Keywords: Airborne Wind Energy; Flight model; Prototype development; Quadplane; Vertical take-off and landing; Autopilot; Open-source; Flight simulation; Flight test

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APA (6^th Edition):

Klein-Miloslavich, A. (2020). Modeling, simulation, hardware development, and testing of a lab-scale airborne wind energy system. (Masters Thesis). University of Victoria. Retrieved from http://hdl.handle.net/1828/11508

Chicago Manual of Style (16^th Edition):

Klein-Miloslavich, Andreas. “Modeling, simulation, hardware development, and testing of a lab-scale airborne wind energy system.” 2020. Masters Thesis, University of Victoria. Accessed January 18, 2021. http://hdl.handle.net/1828/11508.

MLA Handbook (7^th Edition):

Klein-Miloslavich, Andreas. “Modeling, simulation, hardware development, and testing of a lab-scale airborne wind energy system.” 2020. Web. 18 Jan 2021.

Vancouver:

Klein-Miloslavich A. Modeling, simulation, hardware development, and testing of a lab-scale airborne wind energy system. [Internet] [Masters thesis]. University of Victoria; 2020. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1828/11508.

Council of Science Editors:

Klein-Miloslavich A. Modeling, simulation, hardware development, and testing of a lab-scale airborne wind energy system. [Masters Thesis]. University of Victoria; 2020. Available from: http://hdl.handle.net/1828/11508

Penn State University

17. Saetti, Umberto. Rotorcraft Flight Control Design with Alleviation of Unsteady Rotor Loads.

Degree: 2019, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/16696uxs116

► The objective of this research effort is to develop rotorcraft flight control laws that minimize unsteady rotor loads by acting solely through the primary flight… (more)

▼ The objective of this research effort is to develop rotorcraft flight control laws that minimize unsteady rotor loads by acting solely through the primary flight controls (first harmonic swashplate control). As opposed to Higher-Harmonic Control, this strategy does not affect stationary (periodic trim) loads, and is therefore effective only in maneuvering flight. However, such system could be readily integrated with existing or future Automatic Flight Control Systems (AFCS). The study considers control designs for both conventional and compound configurations. Starting from a non-linear simulation model of the rotorcraft developed in FLIGHTLAB®, which includes sufficient fidelity to simulate rotor loads and vibrations, Linear Time-Periodic models (LTP) are derived via linearization. Next, the Harmonic Decomposition methodology is used to approximate the LTP systems with higher-order Linear Time-Invariant (LTI) systems. Reduced-order systems are subsequently obtained by using singular perturbation theory. By retaining the higher-harmonics of the rotor loads in the output, the reduced-order models are shown to accurately predicted the influence of the zeroth harmonics of the rigid-body and rotor flapping states on the higher-harmonics of the rotor loads. This way, previous limitations such as the reliance on non-physics-based models and curve fits to approximate rotor loads are lifted. Next, model following flight control laws are developed based on the reduced-order models. Parametric studies are performed to provide insights on how both the feed-forward and feedback paths of the model following control laws can be used to alleviate the rotor loads. Also, the impact of load alleviation on handling qualities is studied. It is shown that, for a standard helicopter configuration, load alleviation comes at the cost of a degradation in handling qualities. However, for the case of a compound rotorcraft, allocation of the control signal to the redundant control surfaces provides load alleviation without degradation in the handling qualities. The flight control laws are subsequently optimized using CONDUIT® to meet a comprehensive set of stability, handling qualities, and performance specifications for specific mission task elements while minimizing the unsteady rotor loads. Finally, since industry will not only rely on LTP systems obtained from simulation models, a novel methodology is developed to identify LTP systems from flight test data. The methodology is successfully applied to JUH-60A Black Hawk flight test data using CIFER®. The identified LTP systems capture the Nb/rev component of the rotorcraft dynamics. Further, it is shown how the higher-harmonics of the rotor states contribute to the overall rotorcraft dynamics for up to a 7%. On the other hand, the rigid-body states contribute to the overall rotorcraft dynamics almost entirely through their zeroth harmonic. Flight control design based on LTP systems identified from flight-test data could benefit the Future Vertical Lift (FVL) program. FVL is a plan to… Advisors/Committee Members: Joseph Francis Horn, Dissertation Advisor/Co-Advisor, Joseph Francis Horn, Committee Chair/Co-Chair, Puneet Singla, Committee Member, Edward Smith, Committee Member, Stephanie Stockar, Outside Member, J.V.R. Prasad, Outside Member, Constantino Manuel Lagoa, Special Member.

Subjects/Keywords: rotorcraft; flight controls; flight dynamics and control; flight dynamics; simulation; aerospace; aircraft; rotorcraft control; aircraft control; load alleviation; automatica flight control system; AFCS; control systems

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APA (6^th Edition):

Saetti, U. (2019). Rotorcraft Flight Control Design with Alleviation of Unsteady Rotor Loads. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/16696uxs116

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Saetti, Umberto. “Rotorcraft Flight Control Design with Alleviation of Unsteady Rotor Loads.” 2019. Thesis, Penn State University. Accessed January 18, 2021. https://submit-etda.libraries.psu.edu/catalog/16696uxs116.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Saetti, Umberto. “Rotorcraft Flight Control Design with Alleviation of Unsteady Rotor Loads.” 2019. Web. 18 Jan 2021.

Vancouver:

Saetti U. Rotorcraft Flight Control Design with Alleviation of Unsteady Rotor Loads. [Internet] [Thesis]. Penn State University; 2019. [cited 2021 Jan 18]. Available from: https://submit-etda.libraries.psu.edu/catalog/16696uxs116.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Saetti U. Rotorcraft Flight Control Design with Alleviation of Unsteady Rotor Loads. [Thesis]. Penn State University; 2019. Available from: https://submit-etda.libraries.psu.edu/catalog/16696uxs116

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

18. Reweti, Savern. PC-based aviation training devices for pilot training in visual flight rules procedures : development, validation and effectiveness.

Degree: PhD, Aviation, 2014, Massey University

URL: http://hdl.handle.net/10179/5454

► Flying is a difficult and complex activity that requires a significant level of attention from the pilot as well as a lengthy training period to… (more)

▼ Flying is a difficult and complex activity that requires a significant level of attention from the pilot as well as a lengthy training period to gain sufficient competency. For issues of both cost and safety, flight simulation has been an integral part of flight training from its earliest beginnings. There have been a number of technological developments and improvements in both the level of fidelity and the training effectiveness of flight simulators. As a result, flight simulators in use today are the result of this technological, psychological, and engineering evolution. Indeed, simulator cockpits can now accurately replicate all of the functions of flight controls and instrumentation found in real aircraft. Furthermore, the development of high-resolution display systems utilising computer-generated imagery (CGI), means that flight simulators can now display very realistic terrain and environmental effects. The high cost of modern full motion flight simulators (FFSs) has meant that their use has generally been restricted to commercial airlines, military forces, and government agencies. More recently, rapid advances and decreasing costs in PC-based computer technology has enabled flight-training organisations to conduct more training with less expensive fixed-base flight training devices (FTDs). That said, the first study in this thesis indicated that in NZ, even the cost of certified FTDs is still beyond the reach of most flight training schools and their students. The central tenet of this thesis is that a cost effective strategy for smaller flight training schools could be the utilisation of low-cost personal computer based aviation-training devices (PCATDs) for flight instruction and procedural training tasks. Although a number of studies have indicated that the fidelity of PCATDs may be quite low when compared to FTDs, especially in control loading and flight dynamics, there is some evidence of a positive transfer of training from the PCATD to the aircraft.Significant research has been conducted on the effective use of PCATDs to reduce Instrument Flight Rules (IFR) training time in the aircraft. Conversely, few studies have examined the use of PCATDs for Visual Flight Rules (VFR) training. This lack of research is likely due to the limited fidelity of most PCATDs, especially in the critical area of visual displays. Customised PCATDs were developed to address these fidelity issues by utilising innovative and cost effective software and hardware technologies. The aim of this study was to investigate potential training benefits and cost effectiveness of utilising low cost PCATDs, to improve pilot proficiency in performing VFR procedures. A quasi-transfer study was undertaken to ascertain whether a customised low cost PCATD was as effective as a Civil Aviation Authority certified FTD at improving pilot proficiency in the performance of a standard VFR traffic pattern operation. 1. There was no evidence of a difference in VFR task performance between participants trained on the PCATD and the FTD when tested on…

Subjects/Keywords: Flight simulators; Flight simulation; Aeroplanes; Piloting; Computer simulation; Flight training

…29 2.5 ....The Effect of Fidelity on Flight Simulation… …49 2.8.2 ...... Using PCATDs with Microsoft Flight Simulator… …50 2.8.3 ...... Using PCATDs for Instrument Flight Rules Training… …58 2.8.6 ...... Using PCATDs for Visual Flight Rules Training… …72 vi Chapter 3. Flight Training In New Zealand…

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APA (6^th Edition):

Reweti, S. (2014). PC-based aviation training devices for pilot training in visual flight rules procedures : development, validation and effectiveness. (Doctoral Dissertation). Massey University. Retrieved from http://hdl.handle.net/10179/5454

Chicago Manual of Style (16^th Edition):

Reweti, Savern. “PC-based aviation training devices for pilot training in visual flight rules procedures : development, validation and effectiveness.” 2014. Doctoral Dissertation, Massey University. Accessed January 18, 2021. http://hdl.handle.net/10179/5454.

MLA Handbook (7^th Edition):

Reweti, Savern. “PC-based aviation training devices for pilot training in visual flight rules procedures : development, validation and effectiveness.” 2014. Web. 18 Jan 2021.

Vancouver:

Reweti S. PC-based aviation training devices for pilot training in visual flight rules procedures : development, validation and effectiveness. [Internet] [Doctoral dissertation]. Massey University; 2014. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/10179/5454.

Council of Science Editors:

Reweti S. PC-based aviation training devices for pilot training in visual flight rules procedures : development, validation and effectiveness. [Doctoral Dissertation]. Massey University; 2014. Available from: http://hdl.handle.net/10179/5454

Rochester Institute of Technology

19. Komendat, Andrew. Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors.

Degree: Mechanical Engineering, 2012, Rochester Institute of Technology

URL: https://scholarworks.rit.edu/theses/195

► In this work, a novel algorithm for estimating aircraft center-of-gravity location based solely on traditional aircraft measurements is investigated. The algorithm uses known physics-based kinematic… (more)

Subjects/Keywords: Aircraft; Center of gravity; Estimation; Flight dynamics; Optimization; Simulation

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APA (6^th Edition):

Komendat, A. (2012). Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors. (Thesis). Rochester Institute of Technology. Retrieved from https://scholarworks.rit.edu/theses/195

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Komendat, Andrew. “Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors.” 2012. Thesis, Rochester Institute of Technology. Accessed January 18, 2021. https://scholarworks.rit.edu/theses/195.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Komendat, Andrew. “Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors.” 2012. Web. 18 Jan 2021.

Vancouver:

Komendat A. Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors. [Internet] [Thesis]. Rochester Institute of Technology; 2012. [cited 2021 Jan 18]. Available from: https://scholarworks.rit.edu/theses/195.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Komendat A. Center-of-gravity estimation of an aircraft solely using traditional aircraft measurement sensors. [Thesis]. Rochester Institute of Technology; 2012. Available from: https://scholarworks.rit.edu/theses/195

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Michigan

20. Sharma, Abhinav. Development and Application of a Comprehensive Simulation for Modeling Helicopter Ship Landing.

Degree: PhD, Aerospace Engineering, 2019, University of Michigan

URL: http://hdl.handle.net/2027.42/153342

► This work presents a comprehensive first principles physics-based simulation capability for helicopter ship landing, denoted as "HeliUM2-umich." The simulation incorporates key components of the ship-helicopter… (more)

▼ This work presents a comprehensive first principles physics-based simulation capability for helicopter ship landing, denoted as "HeliUM2-umich." The simulation incorporates key components of the ship-helicopter dynamic interface including: 1) a high fidelity flight dynamics model with coupled rotor-fuselage-landing gear dynamics, 2) an aerodynamic model for the complex Wind Over Deck (WOD) that results from wind interacting with the superstructure of a moving ship, 3) a ground effect model that captures aerodynamics in proximity of the deck, 4) a ship deck motion model for a given sea condition, and 5) a Linear-Quadatric Regulator (LQR) based Flight Control System (FCS) to stabilize the vehicle dynamics and maintain a desired approach trajectory. Initial portion of the work was focused on developing a WOD model and integrating it into the flight dynamics code in order to examine the influence of WOD on the UH-60A helicopter response during approach and landing flight segments. The WOD velocities were generated using unsteady Detached Eddy Simulation of flow over a full-scale Simple Frigate Shape Version 2 ship. The flight trajectory consisted of steady level flight followed by descent along a straight inclined trajectory to a specified hover position. Subsequently, the main rotor collective is gradually decreased to enable vertical descent and landing. Gain scheduling was used to track the approach trajectory. The effect of the WOD on vehicle response was examined for two cases: WOD affecting the rotor only, and WOD affecting the entire helicopter including the fuselage, empennage and tail rotor. The controller was shown to be effective in maintaining the desired approach and landing trajectory. However, additional control effort was needed in the presence of WOD. High frequency oscillations were noted in the CG position coordinates and attitude angles due to WOD. Oblique WOD conditions required greater control effort than the headwind case. A larger effort was also required when WOD affected the entire helicopter as compared to the rotor alone. The combined influence of WOD and ground effect during approach and landing was also examined. The ground effect, which was modeled using a simple scaling factor, caused a decrease of approximately 11.3% in power consumption. Next, a finite-state ground effect model was implemented to study the influence of static deck inclination and deck motion on helicopter dynamics. Rotor performance predictions showed good agreement with results from literature for hover over a level and stationary ground plane. Hover and landing simulations were performed with the deck inclined at constant roll and pitch angles, as well as with the deck excited in isolated roll, pitch and heave motions. For hover over a deck with constant roll inclination, an increase in the lateral inflow coefficient and the longitudinal cyclic control input was noted. Deck heaving motion produced an additional 7.5% change in power requirements relative to static ground effect, thus highlighting the importance of… Advisors/Committee Members: Friedmann, Peretz P (committee member), Epureanu, Bogdan (committee member), Cesnik, Carlos E (committee member), Duraisamy, Karthik (committee member), Padthe, Ashwani Kumar (committee member).

Subjects/Keywords: helicopter ship landing; modeling and simulation; flight dynamics; Aerospace Engineering; Engineering

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APA (6^th Edition):

Sharma, A. (2019). Development and Application of a Comprehensive Simulation for Modeling Helicopter Ship Landing. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/153342

Chicago Manual of Style (16^th Edition):

Sharma, Abhinav. “Development and Application of a Comprehensive Simulation for Modeling Helicopter Ship Landing.” 2019. Doctoral Dissertation, University of Michigan. Accessed January 18, 2021. http://hdl.handle.net/2027.42/153342.

MLA Handbook (7^th Edition):

Sharma, Abhinav. “Development and Application of a Comprehensive Simulation for Modeling Helicopter Ship Landing.” 2019. Web. 18 Jan 2021.

Vancouver:

Sharma A. Development and Application of a Comprehensive Simulation for Modeling Helicopter Ship Landing. [Internet] [Doctoral dissertation]. University of Michigan; 2019. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/2027.42/153342.

Council of Science Editors:

Sharma A. Development and Application of a Comprehensive Simulation for Modeling Helicopter Ship Landing. [Doctoral Dissertation]. University of Michigan; 2019. Available from: http://hdl.handle.net/2027.42/153342

University of Toronto

21. Peterson, Timothy Shaw. Handling Qualities of a Blended Wing Body Aircraft.

Degree: 2011, University of Toronto

URL: http://hdl.handle.net/1807/31384

►

The blended wing body (BWB) is a tailless aircraft with the potential to use 27% less fuel than a conventional aircraft with the same passenger… (more)

Subjects/Keywords: flight simulation; handling qualities; blended wing body; 0538

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APA (6^th Edition):

Peterson, T. S. (2011). Handling Qualities of a Blended Wing Body Aircraft. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/31384

Chicago Manual of Style (16^th Edition):

Peterson, Timothy Shaw. “Handling Qualities of a Blended Wing Body Aircraft.” 2011. Masters Thesis, University of Toronto. Accessed January 18, 2021. http://hdl.handle.net/1807/31384.

MLA Handbook (7^th Edition):

Peterson, Timothy Shaw. “Handling Qualities of a Blended Wing Body Aircraft.” 2011. Web. 18 Jan 2021.

Vancouver:

Peterson TS. Handling Qualities of a Blended Wing Body Aircraft. [Internet] [Masters thesis]. University of Toronto; 2011. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1807/31384.

Council of Science Editors:

Peterson TS. Handling Qualities of a Blended Wing Body Aircraft. [Masters Thesis]. University of Toronto; 2011. Available from: http://hdl.handle.net/1807/31384

Delft University of Technology

22. Martín Fernández, Patricia A (author). Impact of Integrated RPAS Operations in TMA.

Degree: 2019, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:337957d0-1bd2-4d0b-9b36-725636d52826

►

The fastgrowing Unmanned Aircraft scene accounts for an increasing number of new users who should have access to the airspace as any other full-ﬂedged airspace… (more)

Subjects/Keywords: RPAS; UAS; ATM; UTM; Flight Performance; Fast-time simulation

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APA (6^th Edition):

Martín Fernández, P. A. (. (2019). Impact of Integrated RPAS Operations in TMA. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:337957d0-1bd2-4d0b-9b36-725636d52826

Chicago Manual of Style (16^th Edition):

Martín Fernández, Patricia A (author). “Impact of Integrated RPAS Operations in TMA.” 2019. Masters Thesis, Delft University of Technology. Accessed January 18, 2021. http://resolver.tudelft.nl/uuid:337957d0-1bd2-4d0b-9b36-725636d52826.

MLA Handbook (7^th Edition):

Martín Fernández, Patricia A (author). “Impact of Integrated RPAS Operations in TMA.” 2019. Web. 18 Jan 2021.

Vancouver:

Martín Fernández PA(. Impact of Integrated RPAS Operations in TMA. [Internet] [Masters thesis]. Delft University of Technology; 2019. [cited 2021 Jan 18]. Available from: http://resolver.tudelft.nl/uuid:337957d0-1bd2-4d0b-9b36-725636d52826.

Council of Science Editors:

Martín Fernández PA(. Impact of Integrated RPAS Operations in TMA. [Masters Thesis]. Delft University of Technology; 2019. Available from: http://resolver.tudelft.nl/uuid:337957d0-1bd2-4d0b-9b36-725636d52826

Nanyang Technological University

23. Adnan Maqsood. Longitudinal dynamics, optimization and control of aircraft transition maneuver using aerodynamic vectoring .

Degree: 2012, Nanyang Technological University

URL: http://hdl.handle.net/10356/48041

► In order to enhance the flight envelope of Unmanned Air Vehicles (UAVs), there have been efforts to combine the excellent hover capabilities of rotorcraft with… (more)

▼ In order to enhance the flight envelope of Unmanned Air Vehicles (UAVs), there have been efforts to combine the excellent hover capabilities of rotorcraft with the endurance and speed performance of fixed-wing aircraft. Such efforts lead to a type of agile aircraft that can perform hover coupled with efficient flight during forward cruise. An inherent problem for such vehicles is the transition maneuver between forward flight and hover, which usually exhibits significant altitude variation, long transition time, large control effort, high thrust-to-weight ratio and loss of partial control. These characteristics are undesirable and reduce the maneuver potential of the vehicle in tight spaces. Moreover, the underlying flight dynamic characteristics of convertible platforms are still not fully explored. To mitigate the problems associated with the transition maneuvers above, this work proposes the use of variable-incidence wing, where the angle of incidence of the wing with reference to the fuselage of the aircraft can be controlled during flight. This phenomenon is also referred as “aerodynamic vectoring” as the changing of the wing-incidence changes significantly the direction of the resultant aerodynamic force. A feasibility study of the usefulness of the variable-incidence wing scheme is conducted in comparison to a conventional fixed-wing platform. The study is focusing longitudinal motion only. The lateral-directional motion is considered to be de-coupled and is out of the scope of the study. Two kind of transition maneuvers are discussed in the thesis: Steady and Unsteady transition maneuvers. Steady transition maneuvers refer to the category in which the aircraft can sustain flight with certain pitch attitude between hover and cruise. In such transitions the aircraft can be considered to be at trim during the maneuver. Unsteady transition maneuvers refer to fast aerobatic/agile transition maneuvers between hover and cruise. In such maneuvers, the aircraft may not be in trimmed conditions between its initial and final desired states. For the analysis, the aerodynamic forces and moments database is developed over the whole maneuver range using wind-tunnel-testing. For the steady transition case, the advantages of the variable-incidence wing feature are found, however eigenvalue analysis reveals that the dynamics may have some peculiarities. For this reason, further nonlinear dynamic analysis is carried out. Specifically, Multiple Time Scales (MTS) method in conjunction with bifurcation theory is used to uncover the peculiar system behavior and to understand the steady transition dynamics further.

Subjects/Keywords: DRNTU::Engineering::Aeronautical engineering::Aircraft; DRNTU::Engineering::Aeronautical engineering::Flight simulation

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APA (6^th Edition):

Maqsood, A. (2012). Longitudinal dynamics, optimization and control of aircraft transition maneuver using aerodynamic vectoring . (Thesis). Nanyang Technological University. Retrieved from http://hdl.handle.net/10356/48041

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Maqsood, Adnan. “Longitudinal dynamics, optimization and control of aircraft transition maneuver using aerodynamic vectoring .” 2012. Thesis, Nanyang Technological University. Accessed January 18, 2021. http://hdl.handle.net/10356/48041.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Maqsood, Adnan. “Longitudinal dynamics, optimization and control of aircraft transition maneuver using aerodynamic vectoring .” 2012. Web. 18 Jan 2021.

Vancouver:

Maqsood A. Longitudinal dynamics, optimization and control of aircraft transition maneuver using aerodynamic vectoring . [Internet] [Thesis]. Nanyang Technological University; 2012. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/10356/48041.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Maqsood A. Longitudinal dynamics, optimization and control of aircraft transition maneuver using aerodynamic vectoring . [Thesis]. Nanyang Technological University; 2012. Available from: http://hdl.handle.net/10356/48041

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

24. Yogeshwaran Jayaraman. Dynamics models of flexible aircraft .

Degree: 2014, Nanyang Technological University

URL: http://hdl.handle.net/10356/61444

► Recent trends in aircraft design owing to requirements of high performance and weight reduction have resulted in aircraft possessing significant structural flexibility. Under these conditions,… (more)

Subjects/Keywords: DRNTU::Engineering::Aeronautical engineering::Flight simulation; DRNTU::Engineering::Aeronautical engineering::Aircraft

8 more images…

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APA (6^th Edition):

Jayaraman, Y. (2014). Dynamics models of flexible aircraft . (Thesis). Nanyang Technological University. Retrieved from http://hdl.handle.net/10356/61444

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Jayaraman, Yogeshwaran. “Dynamics models of flexible aircraft .” 2014. Thesis, Nanyang Technological University. Accessed January 18, 2021. http://hdl.handle.net/10356/61444.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Jayaraman, Yogeshwaran. “Dynamics models of flexible aircraft .” 2014. Web. 18 Jan 2021.

Vancouver:

Jayaraman Y. Dynamics models of flexible aircraft . [Internet] [Thesis]. Nanyang Technological University; 2014. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/10356/61444.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Jayaraman Y. Dynamics models of flexible aircraft . [Thesis]. Nanyang Technological University; 2014. Available from: http://hdl.handle.net/10356/61444

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Toronto

25. Tse, Bosco Chun Bun. Effects of Inertial and Geometric Nonlinearities in the Simulation of Flexible Aircraft Dynamics.

Degree: 2013, University of Toronto

URL: http://hdl.handle.net/1807/42961

►

This thesis examines the relative importance of the inertial and geometric nonlinearities in modelling the dynamics of a flexible aircraft. Inertial nonlinearities are derived by… (more)

Subjects/Keywords: Flight Simulation; Flexible Aircraft; Geometric Nonlinearities; Inertial Nonlinearities; 0538

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APA (6^th Edition):

Tse, B. C. B. (2013). Effects of Inertial and Geometric Nonlinearities in the Simulation of Flexible Aircraft Dynamics. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/42961

Chicago Manual of Style (16^th Edition):

Tse, Bosco Chun Bun. “Effects of Inertial and Geometric Nonlinearities in the Simulation of Flexible Aircraft Dynamics.” 2013. Masters Thesis, University of Toronto. Accessed January 18, 2021. http://hdl.handle.net/1807/42961.

MLA Handbook (7^th Edition):

Tse, Bosco Chun Bun. “Effects of Inertial and Geometric Nonlinearities in the Simulation of Flexible Aircraft Dynamics.” 2013. Web. 18 Jan 2021.

Vancouver:

Tse BCB. Effects of Inertial and Geometric Nonlinearities in the Simulation of Flexible Aircraft Dynamics. [Internet] [Masters thesis]. University of Toronto; 2013. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1807/42961.

Council of Science Editors:

Tse BCB. Effects of Inertial and Geometric Nonlinearities in the Simulation of Flexible Aircraft Dynamics. [Masters Thesis]. University of Toronto; 2013. Available from: http://hdl.handle.net/1807/42961

University of Manchester

26. Parslew, Ben. Simulating avian wingbeats and wakes.

Degree: PhD, 2012, University of Manchester

URL: https://www.research.manchester.ac.uk/portal/en/theses/simulating-avian-wingbeats-and-wakes(038035c2-fe9e-4104-92dc-544579c7011b).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.553489

► Analytical models of avian flight have previously been used to predict mechanical and metabolic power consumption during cruise. These models are limited, in that they… (more)

▼ Analytical models of avian flight have previously been used to predict mechanical and metabolic power consumption during cruise. These models are limited, in that they neglect details of wing kinematics, and model power by assuming a fixed or rotary wing (actuator disk) weight support mechanism. Theoretical methods that incorporate wing kinematics potentially offer more accurate predictions of power consumption by calculating instantaneous aerodynamic loads on the wing. However, the success of these models inherently depends on the availability and accuracy of experimental kinematic data. The predictive simulation approach offers an alternative strategy, whereby kinematics are neither neglected nor measured experimentally, but calculated as part of the solution procedure. This thesis describes the development of a predictive tool for simulating avian wingbeat kinematics and wakes. The tool is designed in a modular format, in order to be extensible for future research in the biomechanics community. The primary simulation module is an inverse dynamic avian wing model that predicts aerodynamic forces and mechanical power consumption for given wing kinematics. The model is constructed from previous experimental studies of avian wing biomechanics. Wing motion is defined through joint kinematic time histories, and aerodynamic forces are predicted using blade element momentum theory. Mechanical power consumption at the shoulder joint is derived from both aerodynamic and inertial torque components associated with the shoulder joint rotation rate. An optimisation module is developed to determine wing kinematics that generate aerodynamic loads for propulsion and weight support in given flight conditions, while minimising mechanical power consumption. For minimum power cruise, optimisation reveals numerous local minima solutions that exhibit large variations in wing kinematics. Validation of the model against wind tunnel data shows that optimised solutions capture qualitative trends in wing kinematics with varying cruise speed. Sensitivity analyses show that the model outputs are most affected by the defined maximum lift coefficient and wing length, whereby perturbations in these parameters lead to significant changes in the predicted amount of upstroke wing retraction. Optimised solutions for allometrically scaled bird models show only small differences in predicted advance ratio, which is consistent with field study observations. Accelerating and climbing flight solutions also show similar qualitative trends in wing kinematics to experimental measurements, including a reduction in stroke plane inclination for increasing acceleration or climb angle. The model predicts that both climb angle and climb speed should be greater for birds with more available instantaneous mechanical power. Simulations of the wake using a discrete vortex model capture fundamental features of the wake geometry that have been observed experimentally. Reconstruction of the velocity field shows that this method overpredicts induced velocity in…

Subjects/Keywords: 598; Avian; Predictive simulation; Flapping; Wake; Bird flight; Inverse dynamics

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APA (6^th Edition):

Parslew, B. (2012). Simulating avian wingbeats and wakes. (Doctoral Dissertation). University of Manchester. Retrieved from https://www.research.manchester.ac.uk/portal/en/theses/simulating-avian-wingbeats-and-wakes(038035c2-fe9e-4104-92dc-544579c7011b).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.553489

Chicago Manual of Style (16^th Edition):

Parslew, Ben. “Simulating avian wingbeats and wakes.” 2012. Doctoral Dissertation, University of Manchester. Accessed January 18, 2021. https://www.research.manchester.ac.uk/portal/en/theses/simulating-avian-wingbeats-and-wakes(038035c2-fe9e-4104-92dc-544579c7011b).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.553489.

MLA Handbook (7^th Edition):

Parslew, Ben. “Simulating avian wingbeats and wakes.” 2012. Web. 18 Jan 2021.

Vancouver:

Parslew B. Simulating avian wingbeats and wakes. [Internet] [Doctoral dissertation]. University of Manchester; 2012. [cited 2021 Jan 18]. Available from: https://www.research.manchester.ac.uk/portal/en/theses/simulating-avian-wingbeats-and-wakes(038035c2-fe9e-4104-92dc-544579c7011b).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.553489.

Council of Science Editors:

Parslew B. Simulating avian wingbeats and wakes. [Doctoral Dissertation]. University of Manchester; 2012. Available from: https://www.research.manchester.ac.uk/portal/en/theses/simulating-avian-wingbeats-and-wakes(038035c2-fe9e-4104-92dc-544579c7011b).html ; http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.553489

Brno University of Technology

27. Sztefek, Jan. Model chování dynamických systémů: Model of Properties of Dynamic Systems.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/26499

► The thesis deals with modeling algorithm for mathematical description of dynamical system written in status description, which makes it possible to changing coefficients status array… (more)

Subjects/Keywords: MatLab; Simulink; Dynamické systémy; MatLab; Simulink; Dynamic systems; plains flight simulation

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APA (6^th Edition):

Sztefek, J. (2019). Model chování dynamických systémů: Model of Properties of Dynamic Systems. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/26499

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Sztefek, Jan. “Model chování dynamických systémů: Model of Properties of Dynamic Systems.” 2019. Thesis, Brno University of Technology. Accessed January 18, 2021. http://hdl.handle.net/11012/26499.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Sztefek, Jan. “Model chování dynamických systémů: Model of Properties of Dynamic Systems.” 2019. Web. 18 Jan 2021.

Vancouver:

Sztefek J. Model chování dynamických systémů: Model of Properties of Dynamic Systems. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/11012/26499.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Sztefek J. Model chování dynamických systémů: Model of Properties of Dynamic Systems. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/26499

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Toronto

28. Leung, Jordan. Parameter Estimation Methods for High Angle-of-attack Aerodynamic Modelling.

Degree: 2019, University of Toronto

URL: http://hdl.handle.net/1807/102971

►

In recent years, extensive research has been performed in post-stall aerodynamic model development to facilitate the use of simulator-based stall recovery training for commercial pilots.… (more)

Subjects/Keywords: Aerodynamics; Dynamic Modelling; Flight Simulation; Parameter Estimation; Stall; System Identification; 0538

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APA (6^th Edition):

Leung, J. (2019). Parameter Estimation Methods for High Angle-of-attack Aerodynamic Modelling. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/102971

Chicago Manual of Style (16^th Edition):

Leung, Jordan. “Parameter Estimation Methods for High Angle-of-attack Aerodynamic Modelling.” 2019. Masters Thesis, University of Toronto. Accessed January 18, 2021. http://hdl.handle.net/1807/102971.

MLA Handbook (7^th Edition):

Leung, Jordan. “Parameter Estimation Methods for High Angle-of-attack Aerodynamic Modelling.” 2019. Web. 18 Jan 2021.

Vancouver:

Leung J. Parameter Estimation Methods for High Angle-of-attack Aerodynamic Modelling. [Internet] [Masters thesis]. University of Toronto; 2019. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1807/102971.

Council of Science Editors:

Leung J. Parameter Estimation Methods for High Angle-of-attack Aerodynamic Modelling. [Masters Thesis]. University of Toronto; 2019. Available from: http://hdl.handle.net/1807/102971

Reykjavík University

29. Margrét Jóna Gestsdóttir 1988-. Agent based simulation of passenger demand for domestic air transport in Iceland .

Degree: 2016, Reykjavík University

URL: http://hdl.handle.net/1946/23798

► Reykjavík, the capital city of Iceland, has an airport located in the city centre. The central location of the airport has been debated for decades.… (more)

▼ Reykjavík, the capital city of Iceland, has an airport located in the city centre. The central location of the airport has been debated for decades. The city of Reykjavik has developed plans for the airport to be closed down in the near future i.e. no later than 2024 in order to free up valuable land for development. However, the current location of the airport is very convenient for most users of domestic flights. Transfer of the services to Keflavik Airport, the only existing alternative airport, is expected to decrease significantly the number of passengers using domestic air services due to increased travel time and higher cost. In this thesis an agent based simulation model is created to study the possible changes in flight demand given these changes in the location of the hub domestic airport. In the model, the agents representing travellers on a given route select air or road transportation based on the cost of transport and their time value. The model is calibrated using real data from Flugfélag Íslands for the year 2014 for the busiest domestic air route between Akureyri and Reykjavik. It is subsequently used to evaluate changes in demand for air services on this route under various scenarios which represent the changes associated with a new location of the hub airport. The results show a considerable decrease in demand for domestic air transportation if the domestic flight operation are moved from Reykjavik to Keflavik. The simulation model results indicate that an agent based simulation is a feasible approach to estimate the changes in the demand for services if e.g. domestic flight services were to be transferred to a new location. Also, agent based simulation model can be a valuable tool in helping to understand the behaviour of travellers due to changes in travel time and additional cost of transportation. Keywords: Agent based simulation, flight demand, domestic flight, time value; Reykjavíkurflugvöllur er staðsettur stutt frá miðborginni. Staðsetning hans hefur lengi verið til umræðu og verið umdeild. Landsvæði Reykjavíkurflugvallar er mjög verðmætt og þess vegna hafa borgaryfirvöld áform um að flytja starfsemi hans annað, ekki seinna en árið 2024. Fyrir flesta farþega í innanlandsflugi er miðlæg staðsetning flugvallarins þægileg. Í þessari ritgerð var gert hermunarlíkan sem notast við einingarhermun (agent based simulation model) til að kanna mögulega breytingu á eftirspurn eftir innanlandsflugi við flutning á starfsemi Reykjavíkurflugvallar. Í hermilíkaninu þurfa einingar (agents) sem ákveða að ferðast, að velja á milli að ferðast með flugi eða eftir vegi út frá kostnaði og tímavirði þeirra. Líkanið er byggt á raunverulegum gögnum frá Flugfélagi Íslands fyrir árið 2014 á flugleiðinni milli Reykjavíkur og Akureyrar. Það er notað til að meta breytingar á eftirspurn eftir flugi við hinar ýmsu aðstæður í tengslum við nýja staðsetningu flugvallarins. Niðurstöðurnar sýna umtalsverða lækkun á eftirspurn eftir innanlandsflugi við flutning flugvallarins frá Reykjavík til Keflavíkur. Niðurstöður…

Subjects/Keywords: Rekstrarverkfræði; Meistaraprófsritgerðir; Hermilíkön; Innanlandsflug; Engineering management; Simulation; Flight

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APA (6^th Edition):

1988-, M. J. G. (2016). Agent based simulation of passenger demand for domestic air transport in Iceland . (Thesis). Reykjavík University. Retrieved from http://hdl.handle.net/1946/23798

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

1988-, Margrét Jóna Gestsdóttir. “Agent based simulation of passenger demand for domestic air transport in Iceland .” 2016. Thesis, Reykjavík University. Accessed January 18, 2021. http://hdl.handle.net/1946/23798.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

1988-, Margrét Jóna Gestsdóttir. “Agent based simulation of passenger demand for domestic air transport in Iceland .” 2016. Web. 18 Jan 2021.

Vancouver:

1988- MJG. Agent based simulation of passenger demand for domestic air transport in Iceland . [Internet] [Thesis]. Reykjavík University; 2016. [cited 2021 Jan 18]. Available from: http://hdl.handle.net/1946/23798.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

1988- MJG. Agent based simulation of passenger demand for domestic air transport in Iceland . [Thesis]. Reykjavík University; 2016. Available from: http://hdl.handle.net/1946/23798

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Louisiana State University

30. Xia, Kai. Molecular Dynamics Simulation Study of Single DNA Nucleotides Transport Through Nanoslits.

Degree: PhD, Mechanical Engineering, 2015, Louisiana State University

URL: etd-06222015-135811 ; https://digitalcommons.lsu.edu/gradschool_dissertations/2852

► There is potential for flight time based DNA sequencing involving disassembly into individual nucleotides which would pass through a nanochannel with 2 or more detectors.… (more)

▼ There is potential for flight time based DNA sequencing involving disassembly into individual nucleotides which would pass through a nanochannel with 2 or more detectors. Molecular dynamics simulation of electrophoretic motion of single DNA nucleotides through 3 nm wide hydrophobic slits was performed. Electric field strength (E) varied from 0.0 to 0.6 V/nm. Slit walls were smooth or had a roughness similar to nucleotide size. Multiple nucleotide-wall adsorptions occurred. The electric field did not influence the nucleotide adsorption and desorption mechanism for E ¡Ü 0.1 V/nm, but influenced nucleotide orientation relative to the field direction. The nucleotide-wall interactions differed due to nucleotide hydrophobicities and wall roughness, and determined duration and frequency of nucleotide adsorptions and their velocities while adsorbed. Transient association of nucleotides with 1 to 3 sodium ions occurred but the mean association numbers (AN) were weak functions of nucleotide type. ANs for pyrimidine nucleotides were slightly lower than for purine nucleotides. Nucleotide-wall interactions contributed more to separation of nucleotide flight time distributions than ion association. A PMMA slab was built and a CHARMM force field file modified from the force field for a PMMA trimer was verified and then utilized to study the transport of dNMPs through PMMA nanoslits. The simulation studies show that, while moving along the PMMA nanoslit the mononucleotides are adsorbed and desorbed from the walls multiple times. Due to their strong interaction with the PMMA walls the mononucleotides can be trapped in adsorbed state for hundreds of nanoseconds. When dNMPs are in the desorbed state, their traveling velocity along the axis of the nanochannel is mainly affected by the association between Na+ and the phosphate group. The Brownian MD simulation studies show that, the main characteristics of the mononucleotides through a nanochannel can be obtained by performing simulations of the dNMPs-PMMA wall system using a coarse-grained representation of the system. The accuracy of this method depends on the accuracy of the potential of mean force used to describe the interaction between dNMP and the PMMA wall.

Subjects/Keywords: time of flight; DNA sequencing; molecular dynamics simulation; adsorption; ion association

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APA (6^th Edition):

Xia, K. (2015). Molecular Dynamics Simulation Study of Single DNA Nucleotides Transport Through Nanoslits. (Doctoral Dissertation). Louisiana State University. Retrieved from etd-06222015-135811 ; https://digitalcommons.lsu.edu/gradschool_dissertations/2852

Chicago Manual of Style (16^th Edition):

Xia, Kai. “Molecular Dynamics Simulation Study of Single DNA Nucleotides Transport Through Nanoslits.” 2015. Doctoral Dissertation, Louisiana State University. Accessed January 18, 2021. etd-06222015-135811 ; https://digitalcommons.lsu.edu/gradschool_dissertations/2852.

MLA Handbook (7^th Edition):

Xia, Kai. “Molecular Dynamics Simulation Study of Single DNA Nucleotides Transport Through Nanoslits.” 2015. Web. 18 Jan 2021.

Vancouver:

Xia K. Molecular Dynamics Simulation Study of Single DNA Nucleotides Transport Through Nanoslits. [Internet] [Doctoral dissertation]. Louisiana State University; 2015. [cited 2021 Jan 18]. Available from: etd-06222015-135811 ; https://digitalcommons.lsu.edu/gradschool_dissertations/2852.

Council of Science Editors:

Xia K. Molecular Dynamics Simulation Study of Single DNA Nucleotides Transport Through Nanoslits. [Doctoral Dissertation]. Louisiana State University; 2015. Available from: etd-06222015-135811 ; https://digitalcommons.lsu.edu/gradschool_dissertations/2852

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Open Access Theses and Dissertations