subject:(Systems Engineering AND Multidisciplinary Design Optimization)

University of Tennessee – Knoxville

1. Williams, Samuel Vivek. Automating Real-Time Fault Detection for the University of Tennessee Space Institute, Aviation Systems’ Flight Testing and Airborne Science Applications.

Degree: MS, Aviation Systems, 2011, University of Tennessee – Knoxville

URL: https://trace.tennessee.edu/utk_gradthes/1107

► The UTSI Aviation Systems program has conducted many successful airborne science campaigns in collaboration with premier research organizations including NASA and NOAA. Each airborne… (more)

Subjects/Keywords: Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Williams, S. V. (2011). Automating Real-Time Fault Detection for the University of Tennessee Space Institute, Aviation Systems’ Flight Testing and Airborne Science Applications. (Thesis). University of Tennessee – Knoxville. Retrieved from https://trace.tennessee.edu/utk_gradthes/1107

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):

Williams, Samuel Vivek. “Automating Real-Time Fault Detection for the University of Tennessee Space Institute, Aviation Systems’ Flight Testing and Airborne Science Applications.” 2011. Thesis, University of Tennessee – Knoxville. Accessed March 01, 2021. https://trace.tennessee.edu/utk_gradthes/1107.

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

MLA Handbook (7^th Edition):

Williams, Samuel Vivek. “Automating Real-Time Fault Detection for the University of Tennessee Space Institute, Aviation Systems’ Flight Testing and Airborne Science Applications.” 2011. Web. 01 Mar 2021.

Vancouver:

Williams SV. Automating Real-Time Fault Detection for the University of Tennessee Space Institute, Aviation Systems’ Flight Testing and Airborne Science Applications. [Internet] [Thesis]. University of Tennessee – Knoxville; 2011. [cited 2021 Mar 01]. Available from: https://trace.tennessee.edu/utk_gradthes/1107.

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

Council of Science Editors:

Williams SV. Automating Real-Time Fault Detection for the University of Tennessee Space Institute, Aviation Systems’ Flight Testing and Airborne Science Applications. [Thesis]. University of Tennessee – Knoxville; 2011. Available from: https://trace.tennessee.edu/utk_gradthes/1107

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

Brigham Young University

2. Larson, Bradley Jared. Mathematical Framework for Early System Design Validation Using Multidisciplinary System Models.

Degree: PhD, 2012, Brigham Young University

URL: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=3999&context=etd

► A significant challenge in the design of multidisciplinary systems (e.g., airplanes, robots, cell phones) is to predict the effects of design decisions at the time… (more)

Subjects/Keywords: system design; multidisciplinary design optimization; nonlinear systems; model composition; Mechanical Engineering

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APA (6^th Edition):

Larson, B. J. (2012). Mathematical Framework for Early System Design Validation Using Multidisciplinary System Models. (Doctoral Dissertation). Brigham Young University. Retrieved from https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=3999&context=etd

Chicago Manual of Style (16^th Edition):

Larson, Bradley Jared. “Mathematical Framework for Early System Design Validation Using Multidisciplinary System Models.” 2012. Doctoral Dissertation, Brigham Young University. Accessed March 01, 2021. https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=3999&context=etd.

MLA Handbook (7^th Edition):

Larson, Bradley Jared. “Mathematical Framework for Early System Design Validation Using Multidisciplinary System Models.” 2012. Web. 01 Mar 2021.

Vancouver:

Larson BJ. Mathematical Framework for Early System Design Validation Using Multidisciplinary System Models. [Internet] [Doctoral dissertation]. Brigham Young University; 2012. [cited 2021 Mar 01]. Available from: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=3999&context=etd.

Council of Science Editors:

Larson BJ. Mathematical Framework for Early System Design Validation Using Multidisciplinary System Models. [Doctoral Dissertation]. Brigham Young University; 2012. Available from: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=3999&context=etd

Embry-Riddle Aeronautical University

3. Twahir, Abdulhalim. Preliminary Design of Blade and Disc Fixing for Aerospace Application using Multi-Disciplinary Approach.

Degree: MSin Aerospace Engineering, Aerospace Engineering, 2013, Embry-Riddle Aeronautical University

URL: https://commons.erau.edu/edt/141

► The preliminary design phase of a turbine rotor has an important impact on the architecture of a new engine definition, as it sets the… (more)

Subjects/Keywords: Aerospace Engineering; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Twahir, A. (2013). Preliminary Design of Blade and Disc Fixing for Aerospace Application using Multi-Disciplinary Approach. (Masters Thesis). Embry-Riddle Aeronautical University. Retrieved from https://commons.erau.edu/edt/141

Chicago Manual of Style (16^th Edition):

Twahir, Abdulhalim. “Preliminary Design of Blade and Disc Fixing for Aerospace Application using Multi-Disciplinary Approach.” 2013. Masters Thesis, Embry-Riddle Aeronautical University. Accessed March 01, 2021. https://commons.erau.edu/edt/141.

MLA Handbook (7^th Edition):

Twahir, Abdulhalim. “Preliminary Design of Blade and Disc Fixing for Aerospace Application using Multi-Disciplinary Approach.” 2013. Web. 01 Mar 2021.

Vancouver:

Twahir A. Preliminary Design of Blade and Disc Fixing for Aerospace Application using Multi-Disciplinary Approach. [Internet] [Masters thesis]. Embry-Riddle Aeronautical University; 2013. [cited 2021 Mar 01]. Available from: https://commons.erau.edu/edt/141.

Council of Science Editors:

Twahir A. Preliminary Design of Blade and Disc Fixing for Aerospace Application using Multi-Disciplinary Approach. [Masters Thesis]. Embry-Riddle Aeronautical University; 2013. Available from: https://commons.erau.edu/edt/141

Embry-Riddle Aeronautical University

4. Rocha, Andres E. Perez. Development of Fault Tolerant Adaptive Control Laws for Aerospace Systems.

Degree: PhD, Aerospace Engineering, 2016, Embry-Riddle Aeronautical University

URL: https://commons.erau.edu/edt/289

► The main topic of this dissertation is the design, development and implementation of intelligent adaptive control techniques designed to maintain healthy performance of aerospace… (more)

Subjects/Keywords: Aerospace Engineering; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Rocha, A. E. P. (2016). Development of Fault Tolerant Adaptive Control Laws for Aerospace Systems. (Doctoral Dissertation). Embry-Riddle Aeronautical University. Retrieved from https://commons.erau.edu/edt/289

Chicago Manual of Style (16^th Edition):

Rocha, Andres E Perez. “Development of Fault Tolerant Adaptive Control Laws for Aerospace Systems.” 2016. Doctoral Dissertation, Embry-Riddle Aeronautical University. Accessed March 01, 2021. https://commons.erau.edu/edt/289.

MLA Handbook (7^th Edition):

Rocha, Andres E Perez. “Development of Fault Tolerant Adaptive Control Laws for Aerospace Systems.” 2016. Web. 01 Mar 2021.

Vancouver:

Rocha AEP. Development of Fault Tolerant Adaptive Control Laws for Aerospace Systems. [Internet] [Doctoral dissertation]. Embry-Riddle Aeronautical University; 2016. [cited 2021 Mar 01]. Available from: https://commons.erau.edu/edt/289.

Council of Science Editors:

Rocha AEP. Development of Fault Tolerant Adaptive Control Laws for Aerospace Systems. [Doctoral Dissertation]. Embry-Riddle Aeronautical University; 2016. Available from: https://commons.erau.edu/edt/289

Cal Poly

5. Nugent, Ryan. Integration and Qualification of The P-PODs on The Vega Maiden Flight.

Degree: MS, Aerospace Engineering, 2016, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/1681 ; 10.15368/theses.2016.160

► On February 13, 2012, California Polytechnic State University, San Luis Obispo flew three Poly-Picosatellite Orbital Deployers (P-PODs), carrying seven European University CubeSats sponsored by… (more)

Subjects/Keywords: P-POD; Vega; CubeSat; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Nugent, R. (2016). Integration and Qualification of The P-PODs on The Vega Maiden Flight. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/1681 ; 10.15368/theses.2016.160

Chicago Manual of Style (16^th Edition):

Nugent, Ryan. “Integration and Qualification of The P-PODs on The Vega Maiden Flight.” 2016. Masters Thesis, Cal Poly. Accessed March 01, 2021. https://digitalcommons.calpoly.edu/theses/1681 ; 10.15368/theses.2016.160.

MLA Handbook (7^th Edition):

Nugent, Ryan. “Integration and Qualification of The P-PODs on The Vega Maiden Flight.” 2016. Web. 01 Mar 2021.

Vancouver:

Nugent R. Integration and Qualification of The P-PODs on The Vega Maiden Flight. [Internet] [Masters thesis]. Cal Poly; 2016. [cited 2021 Mar 01]. Available from: https://digitalcommons.calpoly.edu/theses/1681 ; 10.15368/theses.2016.160.

Council of Science Editors:

Nugent R. Integration and Qualification of The P-PODs on The Vega Maiden Flight. [Masters Thesis]. Cal Poly; 2016. Available from: https://digitalcommons.calpoly.edu/theses/1681 ; 10.15368/theses.2016.160

Cal Poly

6. Berrian, Joshua. AN AUTOMATED TEST STATION DESIGN USED TO VERIFY AIRCRAFT COMMUNICATION PROTOCOLS.

Degree: MS, Aerospace Engineering, 2011, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/635 ; 10.15368/theses.2011.192

► Requirements verification is typically the costliest part of the systems engineering design process. In the commercial aircraft industry, as the software and hardware design… (more)

Subjects/Keywords: Automation; Verification; Avionics; Communication; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Berrian, J. (2011). AN AUTOMATED TEST STATION DESIGN USED TO VERIFY AIRCRAFT COMMUNICATION PROTOCOLS. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/635 ; 10.15368/theses.2011.192

Chicago Manual of Style (16^th Edition):

Berrian, Joshua. “AN AUTOMATED TEST STATION DESIGN USED TO VERIFY AIRCRAFT COMMUNICATION PROTOCOLS.” 2011. Masters Thesis, Cal Poly. Accessed March 01, 2021. https://digitalcommons.calpoly.edu/theses/635 ; 10.15368/theses.2011.192.

MLA Handbook (7^th Edition):

Berrian, Joshua. “AN AUTOMATED TEST STATION DESIGN USED TO VERIFY AIRCRAFT COMMUNICATION PROTOCOLS.” 2011. Web. 01 Mar 2021.

Vancouver:

Berrian J. AN AUTOMATED TEST STATION DESIGN USED TO VERIFY AIRCRAFT COMMUNICATION PROTOCOLS. [Internet] [Masters thesis]. Cal Poly; 2011. [cited 2021 Mar 01]. Available from: https://digitalcommons.calpoly.edu/theses/635 ; 10.15368/theses.2011.192.

Council of Science Editors:

Berrian J. AN AUTOMATED TEST STATION DESIGN USED TO VERIFY AIRCRAFT COMMUNICATION PROTOCOLS. [Masters Thesis]. Cal Poly; 2011. Available from: https://digitalcommons.calpoly.edu/theses/635 ; 10.15368/theses.2011.192

Iowa State University

7. Kwasa, Benjamin Jekonia. Incorporation of organization design in a value-based systems engineering framework.

Degree: 2017, Iowa State University

URL: https://lib.dr.iastate.edu/etd/16062

► The design of Large-Scale Complex Engineered Systems (LSCESs) is an undertaking that requires large organizations made up of several teams of individuals, often spread over… (more)

Subjects/Keywords: Multidisciplinary Design Optimization; Organization Design; Systems Design; Systems Engineering; Value-Based Systems Engineering; Value-Driven Design; Aerospace Engineering

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APA (6^th Edition):

Kwasa, B. J. (2017). Incorporation of organization design in a value-based systems engineering framework. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/16062

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):

Kwasa, Benjamin Jekonia. “Incorporation of organization design in a value-based systems engineering framework.” 2017. Thesis, Iowa State University. Accessed March 01, 2021. https://lib.dr.iastate.edu/etd/16062.

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

MLA Handbook (7^th Edition):

Kwasa, Benjamin Jekonia. “Incorporation of organization design in a value-based systems engineering framework.” 2017. Web. 01 Mar 2021.

Vancouver:

Kwasa BJ. Incorporation of organization design in a value-based systems engineering framework. [Internet] [Thesis]. Iowa State University; 2017. [cited 2021 Mar 01]. Available from: https://lib.dr.iastate.edu/etd/16062.

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

Council of Science Editors:

Kwasa BJ. Incorporation of organization design in a value-based systems engineering framework. [Thesis]. Iowa State University; 2017. Available from: https://lib.dr.iastate.edu/etd/16062

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

Iowa State University

8. Murugaiyan, Suresh. Modeling requirements to value formulation in the design of large-scale complex engineered systems: A satellite system case study.

Degree: 2017, Iowa State University

URL: https://lib.dr.iastate.edu/etd/16523

► Large-scale complex engineered systems (LSCES) are naturally a part of different areas of aerospace engineering and are typically characterized by high cost, high risk and… (more)

▼ Large-scale complex engineered systems (LSCES) are naturally a part of different areas of aerospace engineering and are typically characterized by high cost, high risk and complex interactions at different levels. The design of such LSCES involves multiple organizations at different geographical locations with large number of individuals working at various levels of organizational hierarchy. System engineering processes, which is a traditional approach used in the design of such LSCES, uses requirements as a means of communicating the preferences of stakeholder. The use of requirements does not directly communicate the actual preference of the stakeholder and is actually an indirect way by communicating what the stakeholder does not want. Traditional System engineering is a pass/fail approach in which design is considered to be achieved once all the requirements are satisfied. All the designs, which satisfy the set of requirements, are equally weighed and there is no search for the best design within the accepted design sets. MDO paves way for finding the best design through optimization in which the requirements are translated as constraints. The inconsistency in preference communication still exists in traditional MDO due to presence of requirements in the form of constraints and in addition, the use of constraints restricts the design space exploration by creating a hyperspace called feasible region. A Value Based System Engineering Framework (VBSE) as studied by the past researchers addresses this inconsistency in preference communication. In VBSE a decomposable value function that is singular in unit, is used to capture the stakeholder’s preference, representing the system level preference. The system level preference is communicated along the hierarchy, also allowing each of the lower levels to form their own objectives consistent with the system level objective. The approach ensures capturing the true preference of the stakeholder by directly communicating what the stakeholder wants. The main aim of the present work focuses on explaining the process of transitioning from traditional requirements based approach to value based approach and quantifying the impact of requirements based communication using value gap analysis. A commercial communication satellite is used as an example to demonstrate the process of transitioning to a value based system engineering framework. An attribute based DSM is used to explain the process of capturing the attribute relationships. The study on impact of requirements using value gap analysis shows there is a definite value loss, which exists due to use of requirements. Value gap between preference communication due to probabilistic representation of uncertainty and traditional tolerance representation is also studied. The results indicate the existence of significant value gap and hence the uncertainty needs to be captured adequate enough. Further uncertainty study indicates the requirement of knowledge on the risk preference of the stakeholder and utility theory.

Subjects/Keywords: large scale complex engineered systems; Multidisciplinary design optimization; optimization; Requirements; Systems engineering; Value driven design; Aerospace Engineering; Industrial Engineering; Mechanical Engineering

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APA (6^th Edition):

Murugaiyan, S. (2017). Modeling requirements to value formulation in the design of large-scale complex engineered systems: A satellite system case study. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/16523

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):

Murugaiyan, Suresh. “Modeling requirements to value formulation in the design of large-scale complex engineered systems: A satellite system case study.” 2017. Thesis, Iowa State University. Accessed March 01, 2021. https://lib.dr.iastate.edu/etd/16523.

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

MLA Handbook (7^th Edition):

Murugaiyan, Suresh. “Modeling requirements to value formulation in the design of large-scale complex engineered systems: A satellite system case study.” 2017. Web. 01 Mar 2021.

Vancouver:

Murugaiyan S. Modeling requirements to value formulation in the design of large-scale complex engineered systems: A satellite system case study. [Internet] [Thesis]. Iowa State University; 2017. [cited 2021 Mar 01]. Available from: https://lib.dr.iastate.edu/etd/16523.

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

Council of Science Editors:

Murugaiyan S. Modeling requirements to value formulation in the design of large-scale complex engineered systems: A satellite system case study. [Thesis]. Iowa State University; 2017. Available from: https://lib.dr.iastate.edu/etd/16523

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

Cal Poly

9. Ralph, Alyssa M. Pathfinding Interplanetary Bus Capability for the Cal Poly CubeSat Laboratory Through the Development of a Phobos-Deimos Mission Concept.

Degree: MS, Aerospace Engineering, 2020, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/2209

► With the rise of CubeSats and the demonstration of their many space applications, there is interest in interplanetary CubeSats to act for example as… (more)

Subjects/Keywords: small satellites; planetary; systems engineering; mission architecture; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Ralph, A. M. (2020). Pathfinding Interplanetary Bus Capability for the Cal Poly CubeSat Laboratory Through the Development of a Phobos-Deimos Mission Concept. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/2209

Chicago Manual of Style (16^th Edition):

Ralph, Alyssa M. “Pathfinding Interplanetary Bus Capability for the Cal Poly CubeSat Laboratory Through the Development of a Phobos-Deimos Mission Concept.” 2020. Masters Thesis, Cal Poly. Accessed March 01, 2021. https://digitalcommons.calpoly.edu/theses/2209.

MLA Handbook (7^th Edition):

Ralph, Alyssa M. “Pathfinding Interplanetary Bus Capability for the Cal Poly CubeSat Laboratory Through the Development of a Phobos-Deimos Mission Concept.” 2020. Web. 01 Mar 2021.

Vancouver:

Ralph AM. Pathfinding Interplanetary Bus Capability for the Cal Poly CubeSat Laboratory Through the Development of a Phobos-Deimos Mission Concept. [Internet] [Masters thesis]. Cal Poly; 2020. [cited 2021 Mar 01]. Available from: https://digitalcommons.calpoly.edu/theses/2209.

Council of Science Editors:

Ralph AM. Pathfinding Interplanetary Bus Capability for the Cal Poly CubeSat Laboratory Through the Development of a Phobos-Deimos Mission Concept. [Masters Thesis]. Cal Poly; 2020. Available from: https://digitalcommons.calpoly.edu/theses/2209

University of Tennessee – Knoxville

10. Obika, Lumumba Thutmose O. Design of Cessna 210 Radome-Pod Instrument Interface for Flight Testing.

Degree: MS, Aviation Systems, 2012, University of Tennessee – Knoxville

URL: https://trace.tennessee.edu/utk_gradthes/1322

► The purpose of this study was to determine the most appropriate location and design for an instrument interface that can utilize minimum volume within… (more)

Subjects/Keywords: design; Cessna; pod; instrument-interface; flight-testing; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Obika, L. T. O. (2012). Design of Cessna 210 Radome-Pod Instrument Interface for Flight Testing. (Thesis). University of Tennessee – Knoxville. Retrieved from https://trace.tennessee.edu/utk_gradthes/1322

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):

Obika, Lumumba Thutmose O. “Design of Cessna 210 Radome-Pod Instrument Interface for Flight Testing.” 2012. Thesis, University of Tennessee – Knoxville. Accessed March 01, 2021. https://trace.tennessee.edu/utk_gradthes/1322.

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

MLA Handbook (7^th Edition):

Obika, Lumumba Thutmose O. “Design of Cessna 210 Radome-Pod Instrument Interface for Flight Testing.” 2012. Web. 01 Mar 2021.

Vancouver:

Obika LTO. Design of Cessna 210 Radome-Pod Instrument Interface for Flight Testing. [Internet] [Thesis]. University of Tennessee – Knoxville; 2012. [cited 2021 Mar 01]. Available from: https://trace.tennessee.edu/utk_gradthes/1322.

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

Council of Science Editors:

Obika LTO. Design of Cessna 210 Radome-Pod Instrument Interface for Flight Testing. [Thesis]. University of Tennessee – Knoxville; 2012. Available from: https://trace.tennessee.edu/utk_gradthes/1322

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

Cal Poly

11. Harper, James M. Pocket Rocket: A 1U+ Propulsion System Design To Enhance CubeSat Capabilities.

Degree: MS, Aerospace Engineering, 2020, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/2218

► The research presented provides an overview of a 1U+ form factor propulsion system design developed for the Cal Poly CubeSat Laboratory (CPCL). This design… (more)

Subjects/Keywords: Micro-propulsion; Small Satellites; Space Environment; CubeSat Design Specification; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Harper, J. M. (2020). Pocket Rocket: A 1U+ Propulsion System Design To Enhance CubeSat Capabilities. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/2218

Chicago Manual of Style (16^th Edition):

Harper, James M. “Pocket Rocket: A 1U+ Propulsion System Design To Enhance CubeSat Capabilities.” 2020. Masters Thesis, Cal Poly. Accessed March 01, 2021. https://digitalcommons.calpoly.edu/theses/2218.

MLA Handbook (7^th Edition):

Harper, James M. “Pocket Rocket: A 1U+ Propulsion System Design To Enhance CubeSat Capabilities.” 2020. Web. 01 Mar 2021.

Vancouver:

Harper JM. Pocket Rocket: A 1U+ Propulsion System Design To Enhance CubeSat Capabilities. [Internet] [Masters thesis]. Cal Poly; 2020. [cited 2021 Mar 01]. Available from: https://digitalcommons.calpoly.edu/theses/2218.

Council of Science Editors:

Harper JM. Pocket Rocket: A 1U+ Propulsion System Design To Enhance CubeSat Capabilities. [Masters Thesis]. Cal Poly; 2020. Available from: https://digitalcommons.calpoly.edu/theses/2218

Embry-Riddle Aeronautical University

12. Vasjaliya, Naishadh G. Fluid-structure Interaction and Multidisciplinary Design Analysis Optimization of Composite Wind Turbine Blade.

Degree: MSin Aerospace Engineering, Aerospace Engineering, 2013, Embry-Riddle Aeronautical University

URL: https://commons.erau.edu/edt/142

► A multidisciplinary design analysis optimization (MDAO) process is defined for a composite wind turbine blade to optimize its aerodynamic and structural performance by developing… (more)

▼ A multidisciplinary design analysis optimization (MDAO) process is defined for a composite wind turbine blade to optimize its aerodynamic and structural performance by developing a fluid-structural interaction (FSI) system. The objectives are to maximize aerodynamic efficiency and structural robustness while reducing blade mass and total cost. In the previous research, a MDO process of a composite wind turbine blade has been pioneered as an effective process to develop structurally optimized blade design. Present MDAO process is defined in conjunction with structural and aerodynamic performance of the blade which is divided into three steps and the design variables considered are related to the shape parameters, twist distributions, pitch angle, material and the relative thickness based on number of composite layers at different blade sections. Maximum allowable tip deformations, modal frequencies and allowable stresses are set as design constraints. The results of the first step are aerodynamically optimal angle of attack of airfoils for the blade cross-sections along the blade span wise direction, and the uniform pressure distribution along the blade at maximum lift and wind conditions. Airfoil performance is predicted with 2D airfoils analysis, while 3D CFD analysis is performed by ANSYS CFX software. The second step yields optimal material, composite layup distribution of the blade and involves fluid structure interaction system hence actual pressure loads on the blade can be used for the structural analysis. A parameterized finite element model of the blade created in ANSYS ACP composite prepost and used to define the composite layups of the blade. At the last step, the results of the CFD and the structural analysis are used for the optimization process accompanied by the cost estimation to obtain a compromised solution between aerodynamic performance and structural robustness. For the MDAO process number of design of experiments (DOEs) is defined by G-optimality method and a response surface is created. Additionally, by consideration of maximum power output, minimum weight and cost as prior objectives, an optimal blade design is found within the pre-defined design variable parameters and structural constraints. Sensitivity analysis is performed to observe the impact of input parameter on each output parameters for enhanced control of the MDAO process. Further, to improve aerodynamic performance of the blade, new design approach with modified Tip (winglet) and rotor section is studied and substantial improvement in power generated over high quality baseline wind turbine blade is presented.

Subjects/Keywords: Aerodynamics and Fluid Mechanics; Aerospace Engineering; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Vasjaliya, N. G. (2013). Fluid-structure Interaction and Multidisciplinary Design Analysis Optimization of Composite Wind Turbine Blade. (Masters Thesis). Embry-Riddle Aeronautical University. Retrieved from https://commons.erau.edu/edt/142

Chicago Manual of Style (16^th Edition):

Vasjaliya, Naishadh G. “Fluid-structure Interaction and Multidisciplinary Design Analysis Optimization of Composite Wind Turbine Blade.” 2013. Masters Thesis, Embry-Riddle Aeronautical University. Accessed March 01, 2021. https://commons.erau.edu/edt/142.

MLA Handbook (7^th Edition):

Vasjaliya, Naishadh G. “Fluid-structure Interaction and Multidisciplinary Design Analysis Optimization of Composite Wind Turbine Blade.” 2013. Web. 01 Mar 2021.

Vancouver:

Vasjaliya NG. Fluid-structure Interaction and Multidisciplinary Design Analysis Optimization of Composite Wind Turbine Blade. [Internet] [Masters thesis]. Embry-Riddle Aeronautical University; 2013. [cited 2021 Mar 01]. Available from: https://commons.erau.edu/edt/142.

Council of Science Editors:

Vasjaliya NG. Fluid-structure Interaction and Multidisciplinary Design Analysis Optimization of Composite Wind Turbine Blade. [Masters Thesis]. Embry-Riddle Aeronautical University; 2013. Available from: https://commons.erau.edu/edt/142

University of Colorado

13. Coolidge, Collin Jennings. Low Pressure Ratio Cascaded Joule-Thomson Cryogenic Coolers.

Degree: PhD, 2017, University of Colorado

URL: https://scholar.colorado.edu/mcen_gradetds/183

► This thesis presents the design, fabrication, and characterization of several coldstages intended to investigate the feasibility of a low pressure ratio three stage cascaded Joule-Thomson… (more)

▼ This thesis presents the design, fabrication, and characterization of several coldstages intended to investigate the feasibility of a low pressure ratio three stage cascaded Joule-Thomson (JT) based cryogenic cooler. The coldstages investigated use single component refrigerants operating at pressure ratios of less than 0.5:0.1 MPa. Low pressure ratio single component refrigerants offer an order of magnitude higher specific refrigeration capacity but a narrower temperature range of cooling when compared to mixed refrigerants. Cryogenic temperatures can be reached by cascading several self-contained JT refrigeration cycles. A micro-fabricated polyimide based single stage coldstage is built using micro-fabrication techniques developed in previous works. Several processing challenges are identified and recommended solutions and best practices are implemented. Control of the JT restriction is difficult as the polyimide micro-channels expand under high internal pressure. The coldstage is run in a high pressure environment to press the JT restriction into the correct geometry and cools to 280 K. To better control the JT restriction, a glass capillary based coldstage design is identified. The coldstage uses a glass capillary to form the JT restriction. The coldstage cools to 267 K and 283 K when run in a vacuum environment and atmosphere respectively as calculated. The coldstage is integrated with a mini-compressor and intermittently cools to 288 K in atmosphere. The glass capillary design is further developed to make a two stage cascaded coldstage with a Kapton tube-in-tube inter-stage heat exchanger. The coldstage cools to 228 K with a net refrigeration power of 150 mW. A three stage coldstage is demonstrated using the same design. The coldstage cools to 193 K with net refrigeration power of 15 mW. The coldstages presented demonstrate the feasibility of low pressure ratio cascaded JT cryogenic coolers. The efficiencies of the coldstages are low because of large natural heat leak into the systems and inefficiencies of the inter-stage heat exchangers. Future work can improve efficiencies through design optimization of the inter-stage heat exchangers and implementation of more significant thermal insulation. An in-depth review of micro-fabrication techniques based on mechanical design, thermal design, and quality and ease of fabrication is needed for future scalability. Advisors/Committee Members: Y.C. Lee, Ray Radebaugh.

Subjects/Keywords: cryogenic cooler; low pressure ratio; design optimization; glass capillary; coldstage; Mechanical Engineering; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Coolidge, C. J. (2017). Low Pressure Ratio Cascaded Joule-Thomson Cryogenic Coolers. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/mcen_gradetds/183

Chicago Manual of Style (16^th Edition):

Coolidge, Collin Jennings. “Low Pressure Ratio Cascaded Joule-Thomson Cryogenic Coolers.” 2017. Doctoral Dissertation, University of Colorado. Accessed March 01, 2021. https://scholar.colorado.edu/mcen_gradetds/183.

MLA Handbook (7^th Edition):

Coolidge, Collin Jennings. “Low Pressure Ratio Cascaded Joule-Thomson Cryogenic Coolers.” 2017. Web. 01 Mar 2021.

Vancouver:

Coolidge CJ. Low Pressure Ratio Cascaded Joule-Thomson Cryogenic Coolers. [Internet] [Doctoral dissertation]. University of Colorado; 2017. [cited 2021 Mar 01]. Available from: https://scholar.colorado.edu/mcen_gradetds/183.

Council of Science Editors:

Coolidge CJ. Low Pressure Ratio Cascaded Joule-Thomson Cryogenic Coolers. [Doctoral Dissertation]. University of Colorado; 2017. Available from: https://scholar.colorado.edu/mcen_gradetds/183

Cal Poly

14. Lunsford, Ian M. SUBSYSTEM FAILURE ANALYSIS WITHIN THE HORIZON SIMULATION FRAMEWORK.

Degree: MS, Aerospace Engineering, 2016, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/1560 ; 10.15368/theses.2016.40

► System design is an inherently expensive and time consuming process. Engineers are constantly tasked to investigate new solutions for various programs. Model-based systems engineering… (more)

Subjects/Keywords: Horizon Simulation Framework; Model-based Systems Engineering; Simulations; Modeling; Systems Engineering; MBSE; Model-based Engineering; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Lunsford, I. M. (2016). SUBSYSTEM FAILURE ANALYSIS WITHIN THE HORIZON SIMULATION FRAMEWORK. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/1560 ; 10.15368/theses.2016.40

Chicago Manual of Style (16^th Edition):

Lunsford, Ian M. “SUBSYSTEM FAILURE ANALYSIS WITHIN THE HORIZON SIMULATION FRAMEWORK.” 2016. Masters Thesis, Cal Poly. Accessed March 01, 2021. https://digitalcommons.calpoly.edu/theses/1560 ; 10.15368/theses.2016.40.

MLA Handbook (7^th Edition):

Lunsford, Ian M. “SUBSYSTEM FAILURE ANALYSIS WITHIN THE HORIZON SIMULATION FRAMEWORK.” 2016. Web. 01 Mar 2021.

Vancouver:

Lunsford IM. SUBSYSTEM FAILURE ANALYSIS WITHIN THE HORIZON SIMULATION FRAMEWORK. [Internet] [Masters thesis]. Cal Poly; 2016. [cited 2021 Mar 01]. Available from: https://digitalcommons.calpoly.edu/theses/1560 ; 10.15368/theses.2016.40.

Council of Science Editors:

Lunsford IM. SUBSYSTEM FAILURE ANALYSIS WITHIN THE HORIZON SIMULATION FRAMEWORK. [Masters Thesis]. Cal Poly; 2016. Available from: https://digitalcommons.calpoly.edu/theses/1560 ; 10.15368/theses.2016.40

Florida International University

15. Busam, Arvind Kumar. Optimization of waiting time at toll plazas.

Degree: MS, Please see currently inactive department below., 2005, Florida International University

URL: https://digitalcommons.fiu.edu/etd/1898 ; 10.25148/etd.FI14051895 ; FI14051895

► Toll plazas have several toll payment types such as manual, automatic coin machines, electronic and mixed lanes. In places with high traffic flow, the… (more)

Subjects/Keywords: Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Busam, A. K. (2005). Optimization of waiting time at toll plazas. (Thesis). Florida International University. Retrieved from https://digitalcommons.fiu.edu/etd/1898 ; 10.25148/etd.FI14051895 ; FI14051895

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):

Busam, Arvind Kumar. “Optimization of waiting time at toll plazas.” 2005. Thesis, Florida International University. Accessed March 01, 2021. https://digitalcommons.fiu.edu/etd/1898 ; 10.25148/etd.FI14051895 ; FI14051895.

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

MLA Handbook (7^th Edition):

Busam, Arvind Kumar. “Optimization of waiting time at toll plazas.” 2005. Web. 01 Mar 2021.

Vancouver:

Busam AK. Optimization of waiting time at toll plazas. [Internet] [Thesis]. Florida International University; 2005. [cited 2021 Mar 01]. Available from: https://digitalcommons.fiu.edu/etd/1898 ; 10.25148/etd.FI14051895 ; FI14051895.

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

Council of Science Editors:

Busam AK. Optimization of waiting time at toll plazas. [Thesis]. Florida International University; 2005. Available from: https://digitalcommons.fiu.edu/etd/1898 ; 10.25148/etd.FI14051895 ; FI14051895

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

Cal Poly

16. Johnson, Alexander W. CubeSat Astronomy Mission Modeling Using the Horizon Simulation Framework.

Degree: MS, Aerospace Engineering, 2019, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/2067 ; 10.15368/theses.2019.94

► The CubeSat Astronomy Network is a proposed system of multiple CubeSat spacecraft capable of performing follow-up observations of astronomical targets of interest. The system… (more)

Subjects/Keywords: cubesat; astronomy; horizon; simulation; framework; modeling; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Johnson, A. W. (2019). CubeSat Astronomy Mission Modeling Using the Horizon Simulation Framework. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/2067 ; 10.15368/theses.2019.94

Chicago Manual of Style (16^th Edition):

Johnson, Alexander W. “CubeSat Astronomy Mission Modeling Using the Horizon Simulation Framework.” 2019. Masters Thesis, Cal Poly. Accessed March 01, 2021. https://digitalcommons.calpoly.edu/theses/2067 ; 10.15368/theses.2019.94.

MLA Handbook (7^th Edition):

Johnson, Alexander W. “CubeSat Astronomy Mission Modeling Using the Horizon Simulation Framework.” 2019. Web. 01 Mar 2021.

Vancouver:

Johnson AW. CubeSat Astronomy Mission Modeling Using the Horizon Simulation Framework. [Internet] [Masters thesis]. Cal Poly; 2019. [cited 2021 Mar 01]. Available from: https://digitalcommons.calpoly.edu/theses/2067 ; 10.15368/theses.2019.94.

Council of Science Editors:

Johnson AW. CubeSat Astronomy Mission Modeling Using the Horizon Simulation Framework. [Masters Thesis]. Cal Poly; 2019. Available from: https://digitalcommons.calpoly.edu/theses/2067 ; 10.15368/theses.2019.94

Cal Poly

17. Luther, Shaun. SYSML BASED CUBESAT MODEL DESIGN AND INTEGRATION WITH THE HORIZON SIMULATION FRAMEWORK.

Degree: MS, Aerospace Engineering, 2016, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/1591 ; 10.15368/theses.2016.63

► This thesis examines the feasibility of substituting the system input script of Cal Poly’s Horizon Simulation Framework (HSF) with a Model Based Systems Engineering… (more)

Subjects/Keywords: SysML; HSF; CubeSat; Simulation; Model; Space Vehicles; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Luther, S. (2016). SYSML BASED CUBESAT MODEL DESIGN AND INTEGRATION WITH THE HORIZON SIMULATION FRAMEWORK. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/1591 ; 10.15368/theses.2016.63

Chicago Manual of Style (16^th Edition):

Luther, Shaun. “SYSML BASED CUBESAT MODEL DESIGN AND INTEGRATION WITH THE HORIZON SIMULATION FRAMEWORK.” 2016. Masters Thesis, Cal Poly. Accessed March 01, 2021. https://digitalcommons.calpoly.edu/theses/1591 ; 10.15368/theses.2016.63.

MLA Handbook (7^th Edition):

Luther, Shaun. “SYSML BASED CUBESAT MODEL DESIGN AND INTEGRATION WITH THE HORIZON SIMULATION FRAMEWORK.” 2016. Web. 01 Mar 2021.

Vancouver:

Luther S. SYSML BASED CUBESAT MODEL DESIGN AND INTEGRATION WITH THE HORIZON SIMULATION FRAMEWORK. [Internet] [Masters thesis]. Cal Poly; 2016. [cited 2021 Mar 01]. Available from: https://digitalcommons.calpoly.edu/theses/1591 ; 10.15368/theses.2016.63.

Council of Science Editors:

Luther S. SYSML BASED CUBESAT MODEL DESIGN AND INTEGRATION WITH THE HORIZON SIMULATION FRAMEWORK. [Masters Thesis]. Cal Poly; 2016. Available from: https://digitalcommons.calpoly.edu/theses/1591 ; 10.15368/theses.2016.63

Cal Poly

18. Blocher, Andrew Gene. Alternative Mission Concepts for the Exploration of Outer Planets Using Small Satellite Swarms.

Degree: MS, Aerospace Engineering, 2017, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/1820 ; 10.15368/theses.2018.22

► Interplanetary space exploration has thus far consisted of single, expensive spacecraft missions. Mission costs are particularly high on missions to the outer planets and… (more)

▼ Interplanetary space exploration has thus far consisted of single, expensive spacecraft missions. Mission costs are particularly high on missions to the outer planets and while invaluable, finite budgets limit our ability to perform extensive and frequent investigations of the planets. Planetary systems such as Jupiter and Saturn provide extremely complex exploration environments with numerous targets of interest. Exploring these targets in addition to the main planet requires multiple fly-bys and long mission timelines. In LEO, CubeSats have changed the exploration paradigm, offering a fast and low cost alternative to traditional space vehicles. This new mission development philosophy has the potential to significantly change the economics of interplanetary exploration and a number of missions are being developed to utilize CubeSat class spacecraft beyond earth orbit (e.g., NEAScout, Lunar Ice Cube, Marco and BioSentinel). This paper takes the CubeSat philosophical approach one step further by investigating the potential for small satellite swarms to provide extensive studies of the Saturn system. To do this, an architecture was developed to best replicate the Cassini Primary Mission science objectives using swarms of CubeSats. Cassini was chosen because of its complexity and it defines a well-understood baseline to compare against. The paper outlines the overall mission architecture developed and provides a feasible initial design for the spacecraft in the architecture. The number of swarms needed, number of CubeSats per swarm, size of the CubeSats, overall science output and estimated mission cost are all presented. Additional science objectives beyond Cassini's capabilities are also proposed. Significant scientific returns can be achieved by the swarm based architecture and the risk tolerance afforded by the utilization of large numbers of low-cost sensor carriers. This study found a potential architecture that could reduce the cost of replicating Cassini by as much as 63%. The results of this investigation are not constrained to Saturn and can be easily translated to other targets such as Uranus, Neptune or the asteroid belt. Advisors/Committee Members: Jordi Puig Suari.

Subjects/Keywords: Cassini; Saturn; CubeSat; Interplanetary; Architecture; Satellite; Instrumentation; Space Vehicles; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Blocher, A. G. (2017). Alternative Mission Concepts for the Exploration of Outer Planets Using Small Satellite Swarms. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/1820 ; 10.15368/theses.2018.22

Chicago Manual of Style (16^th Edition):

Blocher, Andrew Gene. “Alternative Mission Concepts for the Exploration of Outer Planets Using Small Satellite Swarms.” 2017. Masters Thesis, Cal Poly. Accessed March 01, 2021. https://digitalcommons.calpoly.edu/theses/1820 ; 10.15368/theses.2018.22.

MLA Handbook (7^th Edition):

Blocher, Andrew Gene. “Alternative Mission Concepts for the Exploration of Outer Planets Using Small Satellite Swarms.” 2017. Web. 01 Mar 2021.

Vancouver:

Blocher AG. Alternative Mission Concepts for the Exploration of Outer Planets Using Small Satellite Swarms. [Internet] [Masters thesis]. Cal Poly; 2017. [cited 2021 Mar 01]. Available from: https://digitalcommons.calpoly.edu/theses/1820 ; 10.15368/theses.2018.22.

Council of Science Editors:

Blocher AG. Alternative Mission Concepts for the Exploration of Outer Planets Using Small Satellite Swarms. [Masters Thesis]. Cal Poly; 2017. Available from: https://digitalcommons.calpoly.edu/theses/1820 ; 10.15368/theses.2018.22

University of Tennessee – Knoxville

19. Croxson, Robert Donald. Integration of the Control Display Navigation Unit (CDNU) Into the EA-6B Block 89A Aircraft and its Impact on Navigation Operations.

Degree: MS, Aviation Systems, 2002, University of Tennessee – Knoxville

URL: https://trace.tennessee.edu/utk_gradthes/2041

► This thesis was to evaluate the attributes of the recent modification and installation of the Control Display Navigation Unit (CDNU) into the EA-6B aircraft.… (more)

▼ This thesis was to evaluate the attributes of the recent modification and installation of the Control Display Navigation Unit (CDNU) into the EA-6B aircraft. The author conducted multiple ground and flight test events during a three year evaluation of the EA-6B Block 89A aircraft. The Block 89A modification included an embedded Global Positioning System (GPS)/ Inertial Navigation System (INS) (EGI), enhanced functionality with the recent GPS system modification, and the ability to control the navigation, weapon, and communication on one control panel. This modification was an attempt to replace a failing attitude system and also allow for additional capability. The testing performed included ILS and GPS approaches, holding, air navigation routes, low level military navigation routes, and tactical navigation. The EA-6B is currently not authorized to navigate with the GPS as the sole navigation (NAV) nor authorized to conduct GPS approaches. This evaluation revealed a need for a GPS navigation and approach authorization in the EA-6B. Funding should be started immediately to anticipate meeting the technology requirements once free flight is authorized in the US. This thesis describes the navigation modes currently used in the EA-6B aircraft. The newest 89A upgrade demonstrates great advances in navigation ability with the addition of the EGI. The CDNU as installed in the EA-6B Block 89A aircraft satisfies the FAA requirements of a flight management system (FMS). The CDNU also partially satisfies GPS certification requirements for both the FAA and DOD. The requirement necessary to certify and utilize GPS as a primary navigation source to operate in the NAS not including approaches are RAIM or RAIM equivalent. The CDNU has a function known as EHE that uses an algorithm that was shown to be accurate enough to satisfy this requirement as long as it was used in the blended mode of operation. GPS accuracy was excellent and pilot displays were easy to read and follow. The capability to execute non-precision approaches were demonstrated in the testing and with the addition of RAIM, an unalterable loadable approach, and an alert within the pilot’s primary field of view will allow GPS non-precision approach certification. RAIM capability is available with the GEM IV receivers. An unalterable approach is available with the addition of more memory in the CDNU. An alert is available by physically mounting a new warning light or by activating something on the EFIS displays. Advisors/Committee Members: Dr. Frank. G. Collins, Dr. Ralph D. Kimberlin, Prof. Fred Stellar.

Subjects/Keywords: Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Croxson, R. D. (2002). Integration of the Control Display Navigation Unit (CDNU) Into the EA-6B Block 89A Aircraft and its Impact on Navigation Operations. (Thesis). University of Tennessee – Knoxville. Retrieved from https://trace.tennessee.edu/utk_gradthes/2041

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):

Croxson, Robert Donald. “Integration of the Control Display Navigation Unit (CDNU) Into the EA-6B Block 89A Aircraft and its Impact on Navigation Operations.” 2002. Thesis, University of Tennessee – Knoxville. Accessed March 01, 2021. https://trace.tennessee.edu/utk_gradthes/2041.

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

MLA Handbook (7^th Edition):

Croxson, Robert Donald. “Integration of the Control Display Navigation Unit (CDNU) Into the EA-6B Block 89A Aircraft and its Impact on Navigation Operations.” 2002. Web. 01 Mar 2021.

Vancouver:

Croxson RD. Integration of the Control Display Navigation Unit (CDNU) Into the EA-6B Block 89A Aircraft and its Impact on Navigation Operations. [Internet] [Thesis]. University of Tennessee – Knoxville; 2002. [cited 2021 Mar 01]. Available from: https://trace.tennessee.edu/utk_gradthes/2041.

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

Council of Science Editors:

Croxson RD. Integration of the Control Display Navigation Unit (CDNU) Into the EA-6B Block 89A Aircraft and its Impact on Navigation Operations. [Thesis]. University of Tennessee – Knoxville; 2002. Available from: https://trace.tennessee.edu/utk_gradthes/2041

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

University of Tennessee – Knoxville

20. Clark, Timothy R. Evaluation of a Two-way Datalink for Airborne Surveillance of and Communication with a Remotely Operated Aircraft Operating in the National Airspace System.

Degree: MS, Aviation Systems, 2002, University of Tennessee – Knoxville

URL: https://trace.tennessee.edu/utk_gradthes/2044

► The purpose of this study is to examine the use of a two-way digital datalink to implement the airborne surveillance and communication functions with… (more)

▼ The purpose of this study is to examine the use of a two-way digital datalink to implement the airborne surveillance and communication functions with a Remotely Operated Aircraft in the National Airspace System. These Air Traffic Control functions are currently implemented using primary and secondary radar systems for airborne surveillance, and radio transmissions for voice communications. The present Air Traffic Control system was examined, as well as existing datalink technologies and surveillance and communication equipment. Remotely Operated Aircraft are currently employed almost exclusively by the military, and operational experience in the National Airspace System is very limited. Several key military Remotely Operated Aircraft systems were evaluated, including their operations in the National Airspace System. There are numerous potential uses for commercial Remotely Operated Aircraft operations in the National Airspace System to satisfy varied missions and roles, and the issues associated with large numbers of unmanned aircraft operating in the National Airspace System was investigated. The information used in this study was collected from various published sources, as well as from a number of interviews with knowledgeable persons in the Remotely Operated Aircraft industry and the Federal Aviation Administration. Remotely Operated Aircraft have been established as viable military platforms, and a variety of civilian missions are under consideration to extend their demonstrated usefulness. As civilian Remotely Operated Aircraft system designs and concepts of operation are refined, many cost-effective applications have been identified for using Remotely Operated Aircraft in new roles or in roles currently being performed by manned aircraft. Large numbers of Remotely Operated Aircraft are expected to be operated in the National Airspace System in the future, and the Air Traffic Control system must be able to accommodate their unique needs and facilitate the safe and efficient operation of Remotely Operated Aircraft in the National Airspace System. Two-way digital datalink technology has significant potential for use in implementing the airborne surveillance and communication functions with Remotely Operated Aircraft in the National Airspace System. A datalink-based Air Traffic Control system provides more accurate and comprehensive time-critical surveillance information to the air traffic controller, and facilitates more efficient communications of large amounts of useful information between the air traffic controller and Remotely Operated Aircraft remote operator. It is recommended that two-way digital datalink technology should be pursued for implementing the airborne surveillance and communication functions with a Remotely Operated Aircraft in the National Airspace System. Although this technology has many key benefits, there are several important operational, safety and security issues that must be addressed before the system can be fully implemented in the National Airspace… Advisors/Committee Members: Dr. Frederick W. Stellar, Dr. Ralph D. Kimberlin, Dr. George W. Garrison.

Subjects/Keywords: Systems Engineering and Multidisciplinary Design Optimization

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

APA (6^th Edition):

Clark, T. R. (2002). Evaluation of a Two-way Datalink for Airborne Surveillance of and Communication with a Remotely Operated Aircraft Operating in the National Airspace System. (Thesis). University of Tennessee – Knoxville. Retrieved from https://trace.tennessee.edu/utk_gradthes/2044

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):

Clark, Timothy R. “Evaluation of a Two-way Datalink for Airborne Surveillance of and Communication with a Remotely Operated Aircraft Operating in the National Airspace System.” 2002. Thesis, University of Tennessee – Knoxville. Accessed March 01, 2021. https://trace.tennessee.edu/utk_gradthes/2044.

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

MLA Handbook (7^th Edition):

Clark, Timothy R. “Evaluation of a Two-way Datalink for Airborne Surveillance of and Communication with a Remotely Operated Aircraft Operating in the National Airspace System.” 2002. Web. 01 Mar 2021.

Vancouver:

Clark TR. Evaluation of a Two-way Datalink for Airborne Surveillance of and Communication with a Remotely Operated Aircraft Operating in the National Airspace System. [Internet] [Thesis]. University of Tennessee – Knoxville; 2002. [cited 2021 Mar 01]. Available from: https://trace.tennessee.edu/utk_gradthes/2044.

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

Council of Science Editors:

Clark TR. Evaluation of a Two-way Datalink for Airborne Surveillance of and Communication with a Remotely Operated Aircraft Operating in the National Airspace System. [Thesis]. University of Tennessee – Knoxville; 2002. Available from: https://trace.tennessee.edu/utk_gradthes/2044

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

University of Tennessee – Knoxville

21. Goszkowicz, Brian J. Sidestick Controllers During High Gain Tasks.

Degree: MS, Aviation Systems, 2002, University of Tennessee – Knoxville

URL: https://trace.tennessee.edu/utk_gradthes/2060

► This research attempts to demonstrate the feasibility of a sidestick controller in a high gain environment. The research is assembled from several historical precedents… (more)

▼ This research attempts to demonstrate the feasibility of a sidestick controller in a high gain environment. The research is assembled from several historical precedents and various projects. New technologies have re-ignited interest in the use of sidestick controllers for commercial and military aircraft. There are many advantages and disadvantages utilizing a sidestick in fighter aircraft. Many pilots prefer the feel of a centerstick controller and the designer only needs to develop a few sets of command gradients or gearings to produce adequate handling qualities. However, centersticks require more cockpit room due to their larger size and range of motion. Consequently, designers would have a difficult time fitting a centerstick in small cockpits such as the F-16. The presence of a centerstick could obstruct the view of a center panel Multi-Function Display, preventing the pilot from quickly assimilating valuable information. Sidestick controllers are lightweight, ncan fit in small cockpits, and are better suited for aircraft capable of sustained high normal load factors. From a pilot-vehicle interface standpoint, sidesticks offer an unobstructed view of displays, a clear pathway during an emergency cockpit egress, and allows access to full command inputs for the diverse statures of today’s pilots. The sidestick controller is not without its deficiencies. A sidestick controller prevents easy access to the console under the armrest forcing the designers to use that space for controls that may be set prior to flight. A sidestick also prevents the pilot from using the non-sidestick hand to control the aircraft while trying to do other tasks, such as writing on a kneeboard or using the console under the armrest. Additionally, the tendency toward PIO is more prevalent in air craft equipped with a sidestick than a centerstick. Flight test and simulation has shown that different Command Gradients and Gearings optimize performance for different tasks. However, it is not feasible to collapse the control laws into one usable set for all tasks. Advisors/Committee Members: Dr. R. Kimberlin, Dr. U. P. Solies, Dr. Fred Stellar.

Subjects/Keywords: Systems Engineering and Multidisciplinary Design Optimization

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

APA (6^th Edition):

Goszkowicz, B. J. (2002). Sidestick Controllers During High Gain Tasks. (Thesis). University of Tennessee – Knoxville. Retrieved from https://trace.tennessee.edu/utk_gradthes/2060

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):

Goszkowicz, Brian J. “Sidestick Controllers During High Gain Tasks.” 2002. Thesis, University of Tennessee – Knoxville. Accessed March 01, 2021. https://trace.tennessee.edu/utk_gradthes/2060.

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

MLA Handbook (7^th Edition):

Goszkowicz, Brian J. “Sidestick Controllers During High Gain Tasks.” 2002. Web. 01 Mar 2021.

Vancouver:

Goszkowicz BJ. Sidestick Controllers During High Gain Tasks. [Internet] [Thesis]. University of Tennessee – Knoxville; 2002. [cited 2021 Mar 01]. Available from: https://trace.tennessee.edu/utk_gradthes/2060.

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

Council of Science Editors:

Goszkowicz BJ. Sidestick Controllers During High Gain Tasks. [Thesis]. University of Tennessee – Knoxville; 2002. Available from: https://trace.tennessee.edu/utk_gradthes/2060

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

University of Tennessee – Knoxville

22. Bigalk, Gregory D. Implementation of the Digital Communication System in the F/A-18 Aircraft.

Degree: MS, Aviation Systems, 2002, University of Tennessee – Knoxville

URL: https://trace.tennessee.edu/utk_gradthes/2029

► The F/A-18 Hornet is a Navy/Marine Corps carrier-based strike/fighter built by the Boeing Company. The Hornet is a dual role aircraft designed to have… (more)

▼ The F/A-18 Hornet is a Navy/Marine Corps carrier-based strike/fighter built by the Boeing Company. The Hornet is a dual role aircraft designed to have all weather intercept and ground attack capabilities. The purpose of this study was to examine the Variable Message Format (VMF) communications capability, integration compatibility and technical suitability of the RT-1824(C) ARC-210 radio as integrated into the F/A-18 aircraft. Normally, this aircraft would utilize two ARC-210 voice capable only RT-1556 radio sets designated Comm 1 and Comm 2. Comm 1 is switchable between an upper AS-4129/ARC antenna and lower AS-3557/A antenna. Comm 2 utilizes a separate lower AS-4129/ARC antenna. The RT-1824(C) provides baseline ARC-210 RT-1556 capabilities as well as embedded COMSEC capability, and digital messaging for use during the Close Air Support (CAS) mission. Tests included range performance, aircraft software integration, E3, ECS, Carrier Suitability, TEMPEST, Reliability, Maintainability, and Supportability. Range performance and software integration testing included Air-to-Air testing using an airborne F/A-18 as a Forward Air Controller Airborne (FAC(A)) and Air to Ground testing using a ground FAC with a Target Location Designation Hand-off System (TLDHS). The study revealed a significant reduction in aircrew workload and a tremendous improvement in aircrew and FAC situational awareness after incorporating the new VMF technology. However, the original specification requirements for this program excluded the FAC(A) mission. The author felt that the inclusion of this mission was very important and included it during the research of this thesis. This study will look into the CAS and FAC(A) roles and provide design changes to enhance this system and make it more useful to the fleet user. The author’s analysis was done on information attained during a Navy developmental test program, however all conclusions and recommendations are independent of the test program. The author’s role in this test program was as lead test pilot and project officer. The identified problems are: 1. The need to redesign the touch-sensitive data entry keyboard of the Up Front Control Display to provide an alphanumeric entry capability in addition to providing secondary tactile interface with the weapons system, specifically for the FAC(A) mission. 2. Modify the aircraft software and TLDHS software to display the following commands: “Continue”, “Cleared Hot” and “Abort”. These messages should appear in the Pilot’s HUD, FLIR display, Radar display and Joint Helmet Mounted Cueing Sight display to provide the needed situational awareness (SA) in a highly dynamic mission environment, such as CAS. 3. Design a modified CAS page to appear after the aircrew selects “USE” to facilitate gaining pertinent information faster when conducting CAS missions. 4. Redesign the NETS page to allow more than one “SEND TO” list to appear when the aircraft is serving in the FAC(A) role. 5. Modify the software to allow the… Advisors/Committee Members: Mr. R. B. Richards, Dr. George Garrison, Dr. Ralph Kimberlin.

Subjects/Keywords: Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Bigalk, G. D. (2002). Implementation of the Digital Communication System in the F/A-18 Aircraft. (Thesis). University of Tennessee – Knoxville. Retrieved from https://trace.tennessee.edu/utk_gradthes/2029

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):

Bigalk, Gregory D. “Implementation of the Digital Communication System in the F/A-18 Aircraft.” 2002. Thesis, University of Tennessee – Knoxville. Accessed March 01, 2021. https://trace.tennessee.edu/utk_gradthes/2029.

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

MLA Handbook (7^th Edition):

Bigalk, Gregory D. “Implementation of the Digital Communication System in the F/A-18 Aircraft.” 2002. Web. 01 Mar 2021.

Vancouver:

Bigalk GD. Implementation of the Digital Communication System in the F/A-18 Aircraft. [Internet] [Thesis]. University of Tennessee – Knoxville; 2002. [cited 2021 Mar 01]. Available from: https://trace.tennessee.edu/utk_gradthes/2029.

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

Council of Science Editors:

Bigalk GD. Implementation of the Digital Communication System in the F/A-18 Aircraft. [Thesis]. University of Tennessee – Knoxville; 2002. Available from: https://trace.tennessee.edu/utk_gradthes/2029

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

Cal Poly

23. Kross, Cory Kenneth. A Method for Evaluating Aircraft Electric Power System Sizing and Failure Resiliency.

Degree: MS, Electrical Engineering, 2017, Cal Poly

URL: https://digitalcommons.calpoly.edu/theses/1709 ; 10.15368/theses.2017.14

► With the More Electric Aircraft paradigm, commercial commuter aircraft are increasing the size and complexity of electrical power systems by increasing the number of… (more)

Subjects/Keywords: Aircraft; Power; Optimization; Reliability; Failure; Reconfiguration; Electrical and Computer Engineering; Power and Energy; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Kross, C. K. (2017). A Method for Evaluating Aircraft Electric Power System Sizing and Failure Resiliency. (Masters Thesis). Cal Poly. Retrieved from https://digitalcommons.calpoly.edu/theses/1709 ; 10.15368/theses.2017.14

Chicago Manual of Style (16^th Edition):

Kross, Cory Kenneth. “A Method for Evaluating Aircraft Electric Power System Sizing and Failure Resiliency.” 2017. Masters Thesis, Cal Poly. Accessed March 01, 2021. https://digitalcommons.calpoly.edu/theses/1709 ; 10.15368/theses.2017.14.

MLA Handbook (7^th Edition):

Kross, Cory Kenneth. “A Method for Evaluating Aircraft Electric Power System Sizing and Failure Resiliency.” 2017. Web. 01 Mar 2021.

Vancouver:

Kross CK. A Method for Evaluating Aircraft Electric Power System Sizing and Failure Resiliency. [Internet] [Masters thesis]. Cal Poly; 2017. [cited 2021 Mar 01]. Available from: https://digitalcommons.calpoly.edu/theses/1709 ; 10.15368/theses.2017.14.

Council of Science Editors:

Kross CK. A Method for Evaluating Aircraft Electric Power System Sizing and Failure Resiliency. [Masters Thesis]. Cal Poly; 2017. Available from: https://digitalcommons.calpoly.edu/theses/1709 ; 10.15368/theses.2017.14

Iowa State University

24. Kannan, Hanumanthrao. An MDO augmented value-based systems engineering approach to holistic design decision-making: a satellite system case study.

Degree: 2015, Iowa State University

URL: https://lib.dr.iastate.edu/etd/14843

► The design of large scale complex engineered systems (LSCES) involves hundreds or thousands of designers making decisions at different levels of an organizational hierarchy. Traditionally,… (more)

▼ The design of large scale complex engineered systems (LSCES) involves hundreds or thousands of designers making decisions at different levels of an organizational hierarchy. Traditionally, these LSCES are designed using systems engineering methods and processes, where the preferences of the stakeholder are flowed down the hierarchy using requirements that act as surrogates for preference. Current processes do not provide a system level guidance to subsystem designers. Value-Driven Design (VDD) offers a new perspective on complex system design, where the value preferences of the stakeholder are communicated directly through a decomposable value function, thereby providing a mechanism for improved system consistency. Requirements-based systems engineering approaches do not offer a mathematically rigorous way to capture the couplings present in the system. Multidisciplinary Design Optimization (MDO) was specifically developed to address couplings in both analysis and optimization thereby enabling physics-based consistency. MDO uses an objective function with constraints but does not provide a way to formulate the objective function. Current systems engineering processes do not provide a mathematically sound way to make design decisions when designers are faced with uncertainties. Designers tend to choose designs based on their preferences towards risky/uncertain designs, and past research has shown that there needs to be a consistency in risk preferences to enable design decisions that are consistent with stakeholder’s desires. This research exploits the complimentary nature of VDD, MDO and Decision Analysis (DA) to enable consistency in communication of system preferences, consistency in physics and consistency in risk preferences. The role of VDD in this research is in formulating a value function for true preferences, whereas the role of MDO is to capture couplings and enable optimization using the value function, and the role of DA is to enable consistent design decision-making under uncertainties. A holistic framework for system optimization called the Value-Based Systems Engineering (VBSE) framework is proposed in this research. This framework acts as the first step towards enabling overall system consistency in decision-making in the design of LSCES. A commercial communication geo-stationary satellite model is created and used as a testbed throughout to demonstrate the different aspects of this research.

Subjects/Keywords: Aerospace Engineering; Decision Analysis (DA); Multidisciplinary Design Optimization (MDO); Satellite system design; Spacecraft design; Value-Based Systems Engineering (VBSE); Value-Driven Design (VDD); Aerospace Engineering; Industrial Engineering; Systems Engineering; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Kannan, H. (2015). An MDO augmented value-based systems engineering approach to holistic design decision-making: a satellite system case study. (Thesis). Iowa State University. Retrieved from https://lib.dr.iastate.edu/etd/14843

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):

Kannan, Hanumanthrao. “An MDO augmented value-based systems engineering approach to holistic design decision-making: a satellite system case study.” 2015. Thesis, Iowa State University. Accessed March 01, 2021. https://lib.dr.iastate.edu/etd/14843.

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

MLA Handbook (7^th Edition):

Kannan, Hanumanthrao. “An MDO augmented value-based systems engineering approach to holistic design decision-making: a satellite system case study.” 2015. Web. 01 Mar 2021.

Vancouver:

Kannan H. An MDO augmented value-based systems engineering approach to holistic design decision-making: a satellite system case study. [Internet] [Thesis]. Iowa State University; 2015. [cited 2021 Mar 01]. Available from: https://lib.dr.iastate.edu/etd/14843.

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

Council of Science Editors:

Kannan H. An MDO augmented value-based systems engineering approach to holistic design decision-making: a satellite system case study. [Thesis]. Iowa State University; 2015. Available from: https://lib.dr.iastate.edu/etd/14843

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

Kennesaw State University

25. Sisson, Taylor Jay. The Context of Tool Control in an Aircraft Assembly Environment Related to Productivity.

Degree: 2016, Kennesaw State University

URL: https://digitalcommons.kennesaw.edu/honors_etd/3

► The aircraft industry focuses a large portion of its resources on tool control during the assembly of aircraft. Tool control is a strict process… (more)

Subjects/Keywords: tool control; industrial engineering; optimization; aircraft manufacturing; Other Operations Research, Systems Engineering and Industrial Engineering; Systems Engineering; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Sisson, T. J. (2016). The Context of Tool Control in an Aircraft Assembly Environment Related to Productivity. (Thesis). Kennesaw State University. Retrieved from https://digitalcommons.kennesaw.edu/honors_etd/3

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):

Sisson, Taylor Jay. “The Context of Tool Control in an Aircraft Assembly Environment Related to Productivity.” 2016. Thesis, Kennesaw State University. Accessed March 01, 2021. https://digitalcommons.kennesaw.edu/honors_etd/3.

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

MLA Handbook (7^th Edition):

Sisson, Taylor Jay. “The Context of Tool Control in an Aircraft Assembly Environment Related to Productivity.” 2016. Web. 01 Mar 2021.

Vancouver:

Sisson TJ. The Context of Tool Control in an Aircraft Assembly Environment Related to Productivity. [Internet] [Thesis]. Kennesaw State University; 2016. [cited 2021 Mar 01]. Available from: https://digitalcommons.kennesaw.edu/honors_etd/3.

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

Council of Science Editors:

Sisson TJ. The Context of Tool Control in an Aircraft Assembly Environment Related to Productivity. [Thesis]. Kennesaw State University; 2016. Available from: https://digitalcommons.kennesaw.edu/honors_etd/3

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

University of Cincinnati

26. Houshmand, Arian. Multidisciplinary Dynamic System Design Optimization of Hybrid Electric Vehicle Powertrains.

Degree: MS, Engineering and Applied Science: Mechanical Engineering, 2016, University of Cincinnati

URL: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1479822276400281

► The design of large-scale, complex systems such as plug-in hybrid electric vehicles (PHEVs) motivates the use of formal optimization methods from both multidisciplinary design optimization… (more)

Subjects/Keywords: Mechanical Engineering; Mechanics; combined design and control optimization; multidisciplinary dynamic system design optimizati; large-scale systems; plug-in hybrid electric vehicles

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APA (6^th Edition):

Houshmand, A. (2016). Multidisciplinary Dynamic System Design Optimization of Hybrid Electric Vehicle Powertrains. (Masters Thesis). University of Cincinnati. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=ucin1479822276400281

Chicago Manual of Style (16^th Edition):

Houshmand, Arian. “Multidisciplinary Dynamic System Design Optimization of Hybrid Electric Vehicle Powertrains.” 2016. Masters Thesis, University of Cincinnati. Accessed March 01, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1479822276400281.

MLA Handbook (7^th Edition):

Houshmand, Arian. “Multidisciplinary Dynamic System Design Optimization of Hybrid Electric Vehicle Powertrains.” 2016. Web. 01 Mar 2021.

Vancouver:

Houshmand A. Multidisciplinary Dynamic System Design Optimization of Hybrid Electric Vehicle Powertrains. [Internet] [Masters thesis]. University of Cincinnati; 2016. [cited 2021 Mar 01]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1479822276400281.

Council of Science Editors:

Houshmand A. Multidisciplinary Dynamic System Design Optimization of Hybrid Electric Vehicle Powertrains. [Masters Thesis]. University of Cincinnati; 2016. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1479822276400281

Florida International University

27. Reddy, Sohail. Many-Objective Hybrid Optimization Under Uncertainty With Applications.

Degree: PhD, Mechanical Engineering, 2019, Florida International University

URL: https://digitalcommons.fiu.edu/etd/4369 ; FIDC008890

► A novel method for solving many-objective optimization problems under uncertainty was developed. It is well known that no single optimization algorithm performs best for… (more)

▼ A novel method for solving many-objective optimization problems under uncertainty was developed. It is well known that no single optimization algorithm performs best for all problems. Therefore, the developed method, a many-objective hybrid optimizer (MOHO), uses five constitutive algorithms and actively switches between them throughout the optimization process allowing for robust optimization. MOHO monitors the progress made by each of the five algorithms and allows the best performing algorithm more attempts at finding the optimum. This removes the need for user input for selecting algorithm as the best performing algorithm is automatically selected thereby increasing the probability of converging to the optimum. An uncertainty quantification framework, based on sparse polynomial chaos expansion, to propagate the uncertainties in the input parameter to the objective functions was also developed and validated. Where the samples and analysis runs needed for standard polynomial chaos expansion increases exponentially with the dimensionality, the presented sparse polynomial chaos approach efficiently propagates the uncertainty with only a few samples, thereby greatly reducing the computational cost. The performance of MOHO was investigated on a total of 65 analytical test problems from the DTLZ and WFG test suite, for which the analytical solution is known. MOHO is also applied to two additional real-life cases of aerodynamic shape design of subsonic and hypersonic bodies. Aerodynamic shape optimization is often computationally expensive and is, therefore, a good test case to investigate MOHO`s ability to reduce the computational time through robust optimization and accelerated convergence. The subsonic design optimization had three objectives: maximize lift and minimize drag and moment. The hypersonic design optimization had two objectives: maximize volume and minimize drag. Two accelerated solvers based on fast multipole method and Newton impact theory are developed for simulating subsonic and hypersonic flows. The results show that MOHO performed, on average, better than all five remaining algorithms in 52% of the DTLZ+WFG problems. The results of robust optimization of a subsonic body and hypersonic bodies were in good agreement with theory. The MOHO developed is capable of solving many-objective, multi-objective and single objective, constrained and unconstrained optimization problems with and without uncertainty with little user input. Advisors/Committee Members: George S. Dulikravich, M. Ali Ebadian, Dwayne McDaniel, Sakhrat Khizroev, Marcelo J. Colaco.

Subjects/Keywords: Hybrid Optimization; Uncertainty Quantification; Many-Objective Optimization; Fast Multipole Method; Aerodynamic Optimization; Aerodynamics and Fluid Mechanics; Other Mechanical Engineering; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Reddy, S. (2019). Many-Objective Hybrid Optimization Under Uncertainty With Applications. (Doctoral Dissertation). Florida International University. Retrieved from https://digitalcommons.fiu.edu/etd/4369 ; FIDC008890

Chicago Manual of Style (16^th Edition):

Reddy, Sohail. “Many-Objective Hybrid Optimization Under Uncertainty With Applications.” 2019. Doctoral Dissertation, Florida International University. Accessed March 01, 2021. https://digitalcommons.fiu.edu/etd/4369 ; FIDC008890.

MLA Handbook (7^th Edition):

Reddy, Sohail. “Many-Objective Hybrid Optimization Under Uncertainty With Applications.” 2019. Web. 01 Mar 2021.

Vancouver:

Reddy S. Many-Objective Hybrid Optimization Under Uncertainty With Applications. [Internet] [Doctoral dissertation]. Florida International University; 2019. [cited 2021 Mar 01]. Available from: https://digitalcommons.fiu.edu/etd/4369 ; FIDC008890.

Council of Science Editors:

Reddy S. Many-Objective Hybrid Optimization Under Uncertainty With Applications. [Doctoral Dissertation]. Florida International University; 2019. Available from: https://digitalcommons.fiu.edu/etd/4369 ; FIDC008890

Embry-Riddle Aeronautical University

28. Kazeneh, Ali. Development of Automatic CFD Grid Generation for the Design of the Preliminary Wing Sweep Schedule for the Gulfstream Quiet Supersonic Jet.

Degree: Master of Aerospace Engineering, Aerospace Engineering, 2008, Embry-Riddle Aeronautical University

URL: https://commons.erau.edu/db-theses/95

► The wing sweep schedule for the Gulfstream Quiet Supersonic Jet (wing and body) was investigated using CFD analysis methods. The use of automating the… (more)

Subjects/Keywords: Aerospace Engineering; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Kazeneh, A. (2008). Development of Automatic CFD Grid Generation for the Design of the Preliminary Wing Sweep Schedule for the Gulfstream Quiet Supersonic Jet. (Masters Thesis). Embry-Riddle Aeronautical University. Retrieved from https://commons.erau.edu/db-theses/95

Chicago Manual of Style (16^th Edition):

Kazeneh, Ali. “Development of Automatic CFD Grid Generation for the Design of the Preliminary Wing Sweep Schedule for the Gulfstream Quiet Supersonic Jet.” 2008. Masters Thesis, Embry-Riddle Aeronautical University. Accessed March 01, 2021. https://commons.erau.edu/db-theses/95.

MLA Handbook (7^th Edition):

Kazeneh, Ali. “Development of Automatic CFD Grid Generation for the Design of the Preliminary Wing Sweep Schedule for the Gulfstream Quiet Supersonic Jet.” 2008. Web. 01 Mar 2021.

Vancouver:

Kazeneh A. Development of Automatic CFD Grid Generation for the Design of the Preliminary Wing Sweep Schedule for the Gulfstream Quiet Supersonic Jet. [Internet] [Masters thesis]. Embry-Riddle Aeronautical University; 2008. [cited 2021 Mar 01]. Available from: https://commons.erau.edu/db-theses/95.

Council of Science Editors:

Kazeneh A. Development of Automatic CFD Grid Generation for the Design of the Preliminary Wing Sweep Schedule for the Gulfstream Quiet Supersonic Jet. [Masters Thesis]. Embry-Riddle Aeronautical University; 2008. Available from: https://commons.erau.edu/db-theses/95

Embry-Riddle Aeronautical University

29. Kertesz, Steve, Jr. A comparison of Pseudo 3-Dimensional Collision Avoidance-Predictor Displays for Free Flight.

Degree: Master of Aeronautical Science, Aeronautical Science, 1998, Embry-Riddle Aeronautical University

URL: https://commons.erau.edu/db-theses/96

► This study was the second of two studies to evaluate the use of a pseudo threedimensional display to present information about future possible conflicts.… (more)

Subjects/Keywords: Aerospace Engineering; Aviation; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Kertesz, Steve, J. (1998). A comparison of Pseudo 3-Dimensional Collision Avoidance-Predictor Displays for Free Flight. (Masters Thesis). Embry-Riddle Aeronautical University. Retrieved from https://commons.erau.edu/db-theses/96

Chicago Manual of Style (16^th Edition):

Kertesz, Steve, Jr. “A comparison of Pseudo 3-Dimensional Collision Avoidance-Predictor Displays for Free Flight.” 1998. Masters Thesis, Embry-Riddle Aeronautical University. Accessed March 01, 2021. https://commons.erau.edu/db-theses/96.

MLA Handbook (7^th Edition):

Kertesz, Steve, Jr. “A comparison of Pseudo 3-Dimensional Collision Avoidance-Predictor Displays for Free Flight.” 1998. Web. 01 Mar 2021.

Vancouver:

Kertesz, Steve J. A comparison of Pseudo 3-Dimensional Collision Avoidance-Predictor Displays for Free Flight. [Internet] [Masters thesis]. Embry-Riddle Aeronautical University; 1998. [cited 2021 Mar 01]. Available from: https://commons.erau.edu/db-theses/96.

Council of Science Editors:

Kertesz, Steve J. A comparison of Pseudo 3-Dimensional Collision Avoidance-Predictor Displays for Free Flight. [Masters Thesis]. Embry-Riddle Aeronautical University; 1998. Available from: https://commons.erau.edu/db-theses/96

Embry-Riddle Aeronautical University

30. Tada, Hiroko. An Intermittent-Combustion General Aviation Aircraft Engine Exhaust Noise prediction Algorithm.

Degree: MSin Aerospace Engineering, Aerospace Engineering, 1999, Embry-Riddle Aeronautical University

URL: https://commons.erau.edu/db-theses/195

► From an environmental point of view, the reduction of aircraft noise has become an important factor recently. There are two factors that make airplane… (more)

Subjects/Keywords: Aerospace Engineering; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Tada, H. (1999). An Intermittent-Combustion General Aviation Aircraft Engine Exhaust Noise prediction Algorithm. (Masters Thesis). Embry-Riddle Aeronautical University. Retrieved from https://commons.erau.edu/db-theses/195

Chicago Manual of Style (16^th Edition):

Tada, Hiroko. “An Intermittent-Combustion General Aviation Aircraft Engine Exhaust Noise prediction Algorithm.” 1999. Masters Thesis, Embry-Riddle Aeronautical University. Accessed March 01, 2021. https://commons.erau.edu/db-theses/195.

MLA Handbook (7^th Edition):

Tada, Hiroko. “An Intermittent-Combustion General Aviation Aircraft Engine Exhaust Noise prediction Algorithm.” 1999. Web. 01 Mar 2021.

Vancouver:

Tada H. An Intermittent-Combustion General Aviation Aircraft Engine Exhaust Noise prediction Algorithm. [Internet] [Masters thesis]. Embry-Riddle Aeronautical University; 1999. [cited 2021 Mar 01]. Available from: https://commons.erau.edu/db-theses/195.

Council of Science Editors:

Tada H. An Intermittent-Combustion General Aviation Aircraft Engine Exhaust Noise prediction Algorithm. [Masters Thesis]. Embry-Riddle Aeronautical University; 1999. Available from: https://commons.erau.edu/db-theses/195

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Open Access Theses and Dissertations