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You searched for subject:(Wing based). Showing records 1 – 15 of 15 total matches.

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Cranfield University

1. Mohd Saleh, Siti Juita Mastura. Modelling and analysis of thin-walled structures for optimal design of composite wing.

Degree: PhD, 2017, Cranfield University

 At present, the option for composite usage in aircraft components and the associated manufacturing process is largely based on experience, knowledge, benchmarking, and partly market… (more)

Subjects/Keywords: Composite structure; aircraft wing structure; optimal wing design; knowledge-based; optimisation tool

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APA (6th Edition):

Mohd Saleh, S. J. M. (2017). Modelling and analysis of thin-walled structures for optimal design of composite wing. (Doctoral Dissertation). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/14308 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783253

Chicago Manual of Style (16th Edition):

Mohd Saleh, Siti Juita Mastura. “Modelling and analysis of thin-walled structures for optimal design of composite wing.” 2017. Doctoral Dissertation, Cranfield University. Accessed September 30, 2020. http://dspace.lib.cranfield.ac.uk/handle/1826/14308 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783253.

MLA Handbook (7th Edition):

Mohd Saleh, Siti Juita Mastura. “Modelling and analysis of thin-walled structures for optimal design of composite wing.” 2017. Web. 30 Sep 2020.

Vancouver:

Mohd Saleh SJM. Modelling and analysis of thin-walled structures for optimal design of composite wing. [Internet] [Doctoral dissertation]. Cranfield University; 2017. [cited 2020 Sep 30]. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/14308 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783253.

Council of Science Editors:

Mohd Saleh SJM. Modelling and analysis of thin-walled structures for optimal design of composite wing. [Doctoral Dissertation]. Cranfield University; 2017. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/14308 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.783253


Indian Institute of Science

2. Marianandam, Peter Arun. Vision-based Strategies for Landing of Fixed Wing Unmanned Aerial Vehicles.

Degree: PhD, Faculty of Engineering, 2018, Indian Institute of Science

 Vision-based conventional landing of a fixed wing UAV is addressed in this thesis. The work includes mathematical modeling, interface to a software for rendering the… (more)

Subjects/Keywords: Computer Vision; Image Processing; Fixed Wing Unmanned Aerial Vehicles; Vision-in-the-Loop-Simulation (VILS); Vision Based Runway Alignment; Autonomous Landing Control; Vision Based Landing; Manned Fixed Wing Aircraft Landing Data; Cross Wind Landing; Vision-Based Landing; Vision-Based Cross Wind Landing; Fixed Wing UAVs; Aerospace Engineering

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APA (6th Edition):

Marianandam, P. A. (2018). Vision-based Strategies for Landing of Fixed Wing Unmanned Aerial Vehicles. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/3529

Chicago Manual of Style (16th Edition):

Marianandam, Peter Arun. “Vision-based Strategies for Landing of Fixed Wing Unmanned Aerial Vehicles.” 2018. Doctoral Dissertation, Indian Institute of Science. Accessed September 30, 2020. http://etd.iisc.ac.in/handle/2005/3529.

MLA Handbook (7th Edition):

Marianandam, Peter Arun. “Vision-based Strategies for Landing of Fixed Wing Unmanned Aerial Vehicles.” 2018. Web. 30 Sep 2020.

Vancouver:

Marianandam PA. Vision-based Strategies for Landing of Fixed Wing Unmanned Aerial Vehicles. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2018. [cited 2020 Sep 30]. Available from: http://etd.iisc.ac.in/handle/2005/3529.

Council of Science Editors:

Marianandam PA. Vision-based Strategies for Landing of Fixed Wing Unmanned Aerial Vehicles. [Doctoral Dissertation]. Indian Institute of Science; 2018. Available from: http://etd.iisc.ac.in/handle/2005/3529


Delft University of Technology

3. Lambers, A.C. (author). Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design.

Degree: 2016, Delft University of Technology

Aircraft concepts with high aspect ratio wings have been investigated more extensively in the recent past, as such configurations would reduce the induced drag significantly.… (more)

Subjects/Keywords: Mutlidisciplinary Design Optimization; MDO; surrogate modelling; SBO; surrogate-based optimization; strut-braced wing; flutter

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APA (6th Edition):

Lambers, A. C. (. (2016). Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:a8f151f0-1c47-4a8a-9cef-b9784a1662cd

Chicago Manual of Style (16th Edition):

Lambers, A C (author). “Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design.” 2016. Masters Thesis, Delft University of Technology. Accessed September 30, 2020. http://resolver.tudelft.nl/uuid:a8f151f0-1c47-4a8a-9cef-b9784a1662cd.

MLA Handbook (7th Edition):

Lambers, A C (author). “Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design.” 2016. Web. 30 Sep 2020.

Vancouver:

Lambers AC(. Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design. [Internet] [Masters thesis]. Delft University of Technology; 2016. [cited 2020 Sep 30]. Available from: http://resolver.tudelft.nl/uuid:a8f151f0-1c47-4a8a-9cef-b9784a1662cd.

Council of Science Editors:

Lambers AC(. Development of surrogate-based multidisciplinary optimization methodology with flutter constraints for aircraft conceptual design. [Masters Thesis]. Delft University of Technology; 2016. Available from: http://resolver.tudelft.nl/uuid:a8f151f0-1c47-4a8a-9cef-b9784a1662cd


Delft University of Technology

4. Mangano, Marco (author). Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes.

Degree: 2019, Delft University of Technology

 The second-generation of supersonic civil transport has to match ambitious targets in terms of noise reduction and efficiency to become economically and environmentally viable. High-fidelity… (more)

Subjects/Keywords: Optimization; Aerodynamics; MDO; CFD; Supersonic; wing design; Airfoil; morphing; Gradient-based Optimization

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APA (6th Edition):

Mangano, M. (. (2019). Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:4a40e302-bdf1-4319-81de-a6aad9376d65

Chicago Manual of Style (16th Edition):

Mangano, Marco (author). “Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes.” 2019. Masters Thesis, Delft University of Technology. Accessed September 30, 2020. http://resolver.tudelft.nl/uuid:4a40e302-bdf1-4319-81de-a6aad9376d65.

MLA Handbook (7th Edition):

Mangano, Marco (author). “Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes.” 2019. Web. 30 Sep 2020.

Vancouver:

Mangano M(. Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes. [Internet] [Masters thesis]. Delft University of Technology; 2019. [cited 2020 Sep 30]. Available from: http://resolver.tudelft.nl/uuid:4a40e302-bdf1-4319-81de-a6aad9376d65.

Council of Science Editors:

Mangano M(. Multi-point aerodynamic shape optimization for airfoils and wings at supersonic and subsonic regimes. [Masters Thesis]. Delft University of Technology; 2019. Available from: http://resolver.tudelft.nl/uuid:4a40e302-bdf1-4319-81de-a6aad9376d65


Texas Tech University

5. Ferguson, Lauren A. A computational model for flexible wing based micro air vehicles.

Degree: Mathematics, 2006, Texas Tech University

 Due to the complexities of the wing structure of a micro air vehicle, MAV, a computational model of the aircraft wing requires a combination of… (more)

Subjects/Keywords: Wing based; Micro air vehicles (MAV)

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APA (6th Edition):

Ferguson, L. A. (2006). A computational model for flexible wing based micro air vehicles. (Thesis). Texas Tech University. Retrieved from http://hdl.handle.net/2346/1333

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

Chicago Manual of Style (16th Edition):

Ferguson, Lauren A. “A computational model for flexible wing based micro air vehicles.” 2006. Thesis, Texas Tech University. Accessed September 30, 2020. http://hdl.handle.net/2346/1333.

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

MLA Handbook (7th Edition):

Ferguson, Lauren A. “A computational model for flexible wing based micro air vehicles.” 2006. Web. 30 Sep 2020.

Vancouver:

Ferguson LA. A computational model for flexible wing based micro air vehicles. [Internet] [Thesis]. Texas Tech University; 2006. [cited 2020 Sep 30]. Available from: http://hdl.handle.net/2346/1333.

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

Council of Science Editors:

Ferguson LA. A computational model for flexible wing based micro air vehicles. [Thesis]. Texas Tech University; 2006. Available from: http://hdl.handle.net/2346/1333

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


Queensland University of Technology

6. Mills, Steven John. Visual guidance for fixed-wing unmanned aerial vehicles using feature tracking : application to power line inspection.

Degree: 2013, Queensland University of Technology

 This thesis presents novel vision based control solutions that enable fixed-wing Unmanned Aerial Vehicles to perform tasks of inspection over infrastructure including power lines, pipe… (more)

Subjects/Keywords: Locally Linear Infrastructure; Automated Inspection; Fixed Wing Unmanned Aerial Vehicles; Skid-to-Turn Manoeuvres; Forward-Slip Manoeuvres; Feature Tracking; Vision Based Control; Image Based Visual Servoing; Position Based Visual Servoing

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APA (6th Edition):

Mills, S. J. (2013). Visual guidance for fixed-wing unmanned aerial vehicles using feature tracking : application to power line inspection. (Thesis). Queensland University of Technology. Retrieved from https://eprints.qut.edu.au/62558/

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

Chicago Manual of Style (16th Edition):

Mills, Steven John. “Visual guidance for fixed-wing unmanned aerial vehicles using feature tracking : application to power line inspection.” 2013. Thesis, Queensland University of Technology. Accessed September 30, 2020. https://eprints.qut.edu.au/62558/.

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

MLA Handbook (7th Edition):

Mills, Steven John. “Visual guidance for fixed-wing unmanned aerial vehicles using feature tracking : application to power line inspection.” 2013. Web. 30 Sep 2020.

Vancouver:

Mills SJ. Visual guidance for fixed-wing unmanned aerial vehicles using feature tracking : application to power line inspection. [Internet] [Thesis]. Queensland University of Technology; 2013. [cited 2020 Sep 30]. Available from: https://eprints.qut.edu.au/62558/.

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

Council of Science Editors:

Mills SJ. Visual guidance for fixed-wing unmanned aerial vehicles using feature tracking : application to power line inspection. [Thesis]. Queensland University of Technology; 2013. Available from: https://eprints.qut.edu.au/62558/

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

7. Mohd Saleh, Siti Juita Mastura. Modelling and analysis of thin-walled structures for optimal design of composite wing.

Degree: 2017, Cranfield University

 At present, the option for composite usage in aircraft components and the associated manufacturing process is largely based on experience, knowledge, benchmarking, and partly market… (more)

Subjects/Keywords: Composite structure; aircraft wing structure; optimal wing design; knowledge-based; optimisation tool

…Knowledge Based Search Advisor on aircraft wing design domain. The search advisor contains the… …6.1 FE model of baseline wing… …Figure 6.3 Composite wing skin thickness distributions (min t=1.46mm, max t=9.15mm)… …136 Figure 6.4 Wing box sections along the span… …Bending stiffness of the baseline wing sections from NASTRAN .. 145 Figure 6.9 Bending stiffness… 

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Mohd Saleh, S. J. M. (2017). Modelling and analysis of thin-walled structures for optimal design of composite wing. (Thesis). Cranfield University. Retrieved from http://dspace.lib.cranfield.ac.uk/handle/1826/14308

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

Chicago Manual of Style (16th Edition):

Mohd Saleh, Siti Juita Mastura. “Modelling and analysis of thin-walled structures for optimal design of composite wing.” 2017. Thesis, Cranfield University. Accessed September 30, 2020. http://dspace.lib.cranfield.ac.uk/handle/1826/14308.

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

MLA Handbook (7th Edition):

Mohd Saleh, Siti Juita Mastura. “Modelling and analysis of thin-walled structures for optimal design of composite wing.” 2017. Web. 30 Sep 2020.

Vancouver:

Mohd Saleh SJM. Modelling and analysis of thin-walled structures for optimal design of composite wing. [Internet] [Thesis]. Cranfield University; 2017. [cited 2020 Sep 30]. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/14308.

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

Council of Science Editors:

Mohd Saleh SJM. Modelling and analysis of thin-walled structures for optimal design of composite wing. [Thesis]. Cranfield University; 2017. Available from: http://dspace.lib.cranfield.ac.uk/handle/1826/14308

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


Delft University of Technology

8. van der Schaft, Luuk (author). Development, Model Generation and Analysis of a Flying V Structure Concept.

Degree: 2017, Delft University of Technology

 The Flying V, a concept aircraft configuration, has been proposed by Airbus and TU Berlin. The initial indications of potential improvements in performance over conventional… (more)

Subjects/Keywords: Flying V; structure concept; kbe; knowledge-base engineering; knowledge-based engineering; model generation automation; automated modelling; parapy; airbus; oval fuselage; unconventional configuration; flying wing; blended wing body; BWB; FW; salome; patran; zorro; latticebeta; lattice beta; preliminary design; aircraft; airplane; aerospace; numerical sizing

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APA (6th Edition):

van der Schaft, L. (. (2017). Development, Model Generation and Analysis of a Flying V Structure Concept. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:d9c9c02f-d67a-4e3c-93a7-eb20ed67cd03

Chicago Manual of Style (16th Edition):

van der Schaft, Luuk (author). “Development, Model Generation and Analysis of a Flying V Structure Concept.” 2017. Masters Thesis, Delft University of Technology. Accessed September 30, 2020. http://resolver.tudelft.nl/uuid:d9c9c02f-d67a-4e3c-93a7-eb20ed67cd03.

MLA Handbook (7th Edition):

van der Schaft, Luuk (author). “Development, Model Generation and Analysis of a Flying V Structure Concept.” 2017. Web. 30 Sep 2020.

Vancouver:

van der Schaft L(. Development, Model Generation and Analysis of a Flying V Structure Concept. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2020 Sep 30]. Available from: http://resolver.tudelft.nl/uuid:d9c9c02f-d67a-4e3c-93a7-eb20ed67cd03.

Council of Science Editors:

van der Schaft L(. Development, Model Generation and Analysis of a Flying V Structure Concept. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:d9c9c02f-d67a-4e3c-93a7-eb20ed67cd03


Carnegie Mellon University

9. Hwangbo, Myung. Vision-Based Navigation for a Small Fixed-Wing Airplane in Urban Environment.

Degree: 2012, Carnegie Mellon University

 An urban operation of unmanned aerial vehicles (UAVs) demands a high level of autonomy for tasks presented in a cluttered environment. While fixed-wing UAVs are… (more)

Subjects/Keywords: Unmanned aerial vehicle; fixed-wing airplane; autonomous navigation; visionbased attitude estimation; sensor calibration; sampling-based motion planning; air-slalom task; Artificial Intelligence and Robotics

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APA (6th Edition):

Hwangbo, M. (2012). Vision-Based Navigation for a Small Fixed-Wing Airplane in Urban Environment. (Thesis). Carnegie Mellon University. Retrieved from http://repository.cmu.edu/dissertations/201

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

Chicago Manual of Style (16th Edition):

Hwangbo, Myung. “Vision-Based Navigation for a Small Fixed-Wing Airplane in Urban Environment.” 2012. Thesis, Carnegie Mellon University. Accessed September 30, 2020. http://repository.cmu.edu/dissertations/201.

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

MLA Handbook (7th Edition):

Hwangbo, Myung. “Vision-Based Navigation for a Small Fixed-Wing Airplane in Urban Environment.” 2012. Web. 30 Sep 2020.

Vancouver:

Hwangbo M. Vision-Based Navigation for a Small Fixed-Wing Airplane in Urban Environment. [Internet] [Thesis]. Carnegie Mellon University; 2012. [cited 2020 Sep 30]. Available from: http://repository.cmu.edu/dissertations/201.

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

Council of Science Editors:

Hwangbo M. Vision-Based Navigation for a Small Fixed-Wing Airplane in Urban Environment. [Thesis]. Carnegie Mellon University; 2012. Available from: http://repository.cmu.edu/dissertations/201

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

10. Lugo Cárdenas, Israel. Autonomous take-off and landing for a fixed wing UAV : Décollage et atterrissage autonome pour un UAV d’aile fixe.

Degree: Docteur es, Automatique : Unité de recherche Heudyasic (UMR-7253), 2017, Compiègne

Ce travail étudie certains des problèmes les plus pertinents dans le sens de la navigation et contrôle présentés dans une classe particulière de mini-véhicules aériens.… (more)

Subjects/Keywords: Ailes fixes; Voilures fixes; Trajectoires; Décollages autonomes; Atterrissages autonomes; UAV; Fixed wing; Lyapunov based control; Autonomous take-off; Autonomous landing; Drone aircraft; Automatic control

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APA (6th Edition):

Lugo Cárdenas, I. (2017). Autonomous take-off and landing for a fixed wing UAV : Décollage et atterrissage autonome pour un UAV d’aile fixe. (Doctoral Dissertation). Compiègne. Retrieved from http://www.theses.fr/2017COMP2364

Chicago Manual of Style (16th Edition):

Lugo Cárdenas, Israel. “Autonomous take-off and landing for a fixed wing UAV : Décollage et atterrissage autonome pour un UAV d’aile fixe.” 2017. Doctoral Dissertation, Compiègne. Accessed September 30, 2020. http://www.theses.fr/2017COMP2364.

MLA Handbook (7th Edition):

Lugo Cárdenas, Israel. “Autonomous take-off and landing for a fixed wing UAV : Décollage et atterrissage autonome pour un UAV d’aile fixe.” 2017. Web. 30 Sep 2020.

Vancouver:

Lugo Cárdenas I. Autonomous take-off and landing for a fixed wing UAV : Décollage et atterrissage autonome pour un UAV d’aile fixe. [Internet] [Doctoral dissertation]. Compiègne; 2017. [cited 2020 Sep 30]. Available from: http://www.theses.fr/2017COMP2364.

Council of Science Editors:

Lugo Cárdenas I. Autonomous take-off and landing for a fixed wing UAV : Décollage et atterrissage autonome pour un UAV d’aile fixe. [Doctoral Dissertation]. Compiègne; 2017. Available from: http://www.theses.fr/2017COMP2364

11. Andersson, Michael. Fault diagnosis of a Fixed Wing UAV Using Hardware and Analytical Redundancy.

Degree: The Institute of Technology, 2013, Linköping UniversityLinköping University

  In unmanned aerial systems an autopilot controls the vehicle without human interference. Modern autopilots use an inertial navigation system, GPS, magnetometers and barometers to… (more)

Subjects/Keywords: Fault Diagnosis; Model based diagnosis; Redundancy; Autopilot; UAV; fixed-wing

…contribution of this master thesis is a model based diagnosis system for a fixed wing UAV autopilot… …model based diagnosis systems for fixed wing UAVs. The diagnosis system should be able to… …to perform fault diagnosis is model based diagnosis, where observations of the system are… …compared with a mathematical model of the system. Model based diagnosis is a common technique in… …diagnosis system based on the redundancy obtained with three autopilots on a single airframe. The… 

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APA (6th Edition):

Andersson, M. (2013). Fault diagnosis of a Fixed Wing UAV Using Hardware and Analytical Redundancy. (Thesis). Linköping UniversityLinköping University. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-94139

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

Chicago Manual of Style (16th Edition):

Andersson, Michael. “Fault diagnosis of a Fixed Wing UAV Using Hardware and Analytical Redundancy.” 2013. Thesis, Linköping UniversityLinköping University. Accessed September 30, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-94139.

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

MLA Handbook (7th Edition):

Andersson, Michael. “Fault diagnosis of a Fixed Wing UAV Using Hardware and Analytical Redundancy.” 2013. Web. 30 Sep 2020.

Vancouver:

Andersson M. Fault diagnosis of a Fixed Wing UAV Using Hardware and Analytical Redundancy. [Internet] [Thesis]. Linköping UniversityLinköping University; 2013. [cited 2020 Sep 30]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-94139.

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

Council of Science Editors:

Andersson M. Fault diagnosis of a Fixed Wing UAV Using Hardware and Analytical Redundancy. [Thesis]. Linköping UniversityLinköping University; 2013. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-94139

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


Delft University of Technology

12. Liu, Xinyuan (author). Design of Swirl Recovery Vanes for Wing-Mounted Tractor Propeller Propulsion System.

Degree: 2018, Delft University of Technology

 Increasing pressure of reducing fuel consumption has led to renewed interests in propeller propulsion devices for their high propulsive efficiency. In a propeller propulsion system,… (more)

Subjects/Keywords: Swirl Recovery Vane; SRV; propeller; Shape-preserving response prediction; SPRP; Surrogate-based optimization; DIRECT; Wing optimization; slipstream; Multi-fidelity optimization; Global optimization

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APA (6th Edition):

Liu, X. (. (2018). Design of Swirl Recovery Vanes for Wing-Mounted Tractor Propeller Propulsion System. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:64e2c6bb-6f8e-4ba3-a684-61872a89a156

Chicago Manual of Style (16th Edition):

Liu, Xinyuan (author). “Design of Swirl Recovery Vanes for Wing-Mounted Tractor Propeller Propulsion System.” 2018. Masters Thesis, Delft University of Technology. Accessed September 30, 2020. http://resolver.tudelft.nl/uuid:64e2c6bb-6f8e-4ba3-a684-61872a89a156.

MLA Handbook (7th Edition):

Liu, Xinyuan (author). “Design of Swirl Recovery Vanes for Wing-Mounted Tractor Propeller Propulsion System.” 2018. Web. 30 Sep 2020.

Vancouver:

Liu X(. Design of Swirl Recovery Vanes for Wing-Mounted Tractor Propeller Propulsion System. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2020 Sep 30]. Available from: http://resolver.tudelft.nl/uuid:64e2c6bb-6f8e-4ba3-a684-61872a89a156.

Council of Science Editors:

Liu X(. Design of Swirl Recovery Vanes for Wing-Mounted Tractor Propeller Propulsion System. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:64e2c6bb-6f8e-4ba3-a684-61872a89a156

13. Flores Colunga, Gerardo Ramón. Design, modeling and control of a convertible mini airplane having four tiliting rotors : Conception, modélisation et commande d'un drone convertible à quatre hélices pivotantes.

Degree: Docteur es, Technologies de l'Information et des Systèmes, 2014, Compiègne

Cette thèse étudie certains problèmes plus importants dans le sens de guidage, navigation et contrôle présentés dans une catégorie particulière de mini véhicules aériens (MVA)… (more)

Subjects/Keywords: Aéronefs à voilure fixe; Systèmes de vision; Manoeuvre de transition; Aéronefs convertibles; Quadrirotors; Commande basée de Lyapunov; Modélisation; Fixed-wing aircraft; Quadrotor; Modeling; Stability; Vision systems; Convertible aircraft; Tilt-rotor; Lyapunov-based control; Transition maneuver; Nonlinear systems; Planar Vertical Helicopter-Airplane Transition (PVHAT)

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APA (6th Edition):

Flores Colunga, G. R. (2014). Design, modeling and control of a convertible mini airplane having four tiliting rotors : Conception, modélisation et commande d'un drone convertible à quatre hélices pivotantes. (Doctoral Dissertation). Compiègne. Retrieved from http://www.theses.fr/2014COMP2095

Chicago Manual of Style (16th Edition):

Flores Colunga, Gerardo Ramón. “Design, modeling and control of a convertible mini airplane having four tiliting rotors : Conception, modélisation et commande d'un drone convertible à quatre hélices pivotantes.” 2014. Doctoral Dissertation, Compiègne. Accessed September 30, 2020. http://www.theses.fr/2014COMP2095.

MLA Handbook (7th Edition):

Flores Colunga, Gerardo Ramón. “Design, modeling and control of a convertible mini airplane having four tiliting rotors : Conception, modélisation et commande d'un drone convertible à quatre hélices pivotantes.” 2014. Web. 30 Sep 2020.

Vancouver:

Flores Colunga GR. Design, modeling and control of a convertible mini airplane having four tiliting rotors : Conception, modélisation et commande d'un drone convertible à quatre hélices pivotantes. [Internet] [Doctoral dissertation]. Compiègne; 2014. [cited 2020 Sep 30]. Available from: http://www.theses.fr/2014COMP2095.

Council of Science Editors:

Flores Colunga GR. Design, modeling and control of a convertible mini airplane having four tiliting rotors : Conception, modélisation et commande d'un drone convertible à quatre hélices pivotantes. [Doctoral Dissertation]. Compiègne; 2014. Available from: http://www.theses.fr/2014COMP2095

14. Laughlin, Trevor William. A parametric and physics-based approach to structural weight estimation of the hybrid wing body aircraft.

Degree: MS, Aerospace Engineering, 2012, Georgia Tech

 Estimating the structural weight of a Hybrid Wing Body (HWB) aircraft during conceptual design has proven to be a significant challenge due to its unconventional… (more)

Subjects/Keywords: Surrogate modeling; Hybrid wing body; Aircraft structural weight estimation; Physics-based; Parametric design; Modeling and simulation; Simulation methods; Estimation theory

…stiffener type, rib spacing, and spar locations used for conventional wing study… …99 Aircraft takeoff weights, materials, and fuel weights used for conventional wing study… …99 24 25 Engine weight and locations used for conventional wing study. . . . . 100 26… …2 2 Hybrid wing body configurations (a) after a 1988 McDonnell Douglas design… …define the planform leading and trailing edges and the outboard wing… 

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Laughlin, T. W. (2012). A parametric and physics-based approach to structural weight estimation of the hybrid wing body aircraft. (Masters Thesis). Georgia Tech. Retrieved from http://hdl.handle.net/1853/45829

Chicago Manual of Style (16th Edition):

Laughlin, Trevor William. “A parametric and physics-based approach to structural weight estimation of the hybrid wing body aircraft.” 2012. Masters Thesis, Georgia Tech. Accessed September 30, 2020. http://hdl.handle.net/1853/45829.

MLA Handbook (7th Edition):

Laughlin, Trevor William. “A parametric and physics-based approach to structural weight estimation of the hybrid wing body aircraft.” 2012. Web. 30 Sep 2020.

Vancouver:

Laughlin TW. A parametric and physics-based approach to structural weight estimation of the hybrid wing body aircraft. [Internet] [Masters thesis]. Georgia Tech; 2012. [cited 2020 Sep 30]. Available from: http://hdl.handle.net/1853/45829.

Council of Science Editors:

Laughlin TW. A parametric and physics-based approach to structural weight estimation of the hybrid wing body aircraft. [Masters Thesis]. Georgia Tech; 2012. Available from: http://hdl.handle.net/1853/45829

15. Mines, John Mark. A bi-Level framework for aircraft design uncertainty quantification and management.

Degree: PhD, Aerospace Engineering, 2019, Georgia Tech

 Aircraft design and development is a high-risk process. The recent obstacles with the Boeing 787 Dreamliner and Lockheed Martin F-35 show that the level of… (more)

Subjects/Keywords: Aircraft design; Uncertainty quantification; Optimization; Risk assessment; Reliability-based design optimization; Finite element modeling; Aircraft wing design; Uncertainty propagation; Conceptual design selection; Design decision-making

…gap is addressed by integrating a wing-level, physics-based design environment (the… …4.3.2 4.4 Research Question 3.2: Effect of Wing-Level Constraints on VehicleLevel… …137 Chapter 5: Physics-Based Modeling Environment . . . . . . . . . . . . . . . . 5.1… …Bridging Models of Differing Fidelity . . . . . . . 192 7.1.1 Vehicle-Level and Wing-Level… …Variables . . . . . . . . . . . . . . . 192 7.1.2 Experiment 3.1a: Design Point Structural Wing… 

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Mines, J. M. (2019). A bi-Level framework for aircraft design uncertainty quantification and management. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/61281

Chicago Manual of Style (16th Edition):

Mines, John Mark. “A bi-Level framework for aircraft design uncertainty quantification and management.” 2019. Doctoral Dissertation, Georgia Tech. Accessed September 30, 2020. http://hdl.handle.net/1853/61281.

MLA Handbook (7th Edition):

Mines, John Mark. “A bi-Level framework for aircraft design uncertainty quantification and management.” 2019. Web. 30 Sep 2020.

Vancouver:

Mines JM. A bi-Level framework for aircraft design uncertainty quantification and management. [Internet] [Doctoral dissertation]. Georgia Tech; 2019. [cited 2020 Sep 30]. Available from: http://hdl.handle.net/1853/61281.

Council of Science Editors:

Mines JM. A bi-Level framework for aircraft design uncertainty quantification and management. [Doctoral Dissertation]. Georgia Tech; 2019. Available from: http://hdl.handle.net/1853/61281

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