subject:(Attitude Control)

Delft University of Technology

1. van Hengel, Anita (author). Magnetorquer Design and Attitude Control for SHAPE.

Degree: 2018, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:dc8b7355-cf46-410c-94c3-cc85570b94a7

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Designing and modelling a magnetorquer, and developing an attitude control loop, with magnetorquers as only actuators, for the Stable and Highly Accurate Pointing Earth-Imager (SHAPE),… (more)

Subjects/Keywords: Attitude control; SHAPE; Magnetorquer

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APA (6^th Edition):

van Hengel, A. (. (2018). Magnetorquer Design and Attitude Control for SHAPE. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:dc8b7355-cf46-410c-94c3-cc85570b94a7

Chicago Manual of Style (16^th Edition):

van Hengel, Anita (author). “Magnetorquer Design and Attitude Control for SHAPE.” 2018. Masters Thesis, Delft University of Technology. Accessed April 22, 2021. http://resolver.tudelft.nl/uuid:dc8b7355-cf46-410c-94c3-cc85570b94a7.

MLA Handbook (7^th Edition):

van Hengel, Anita (author). “Magnetorquer Design and Attitude Control for SHAPE.” 2018. Web. 22 Apr 2021.

Vancouver:

van Hengel A(. Magnetorquer Design and Attitude Control for SHAPE. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Apr 22]. Available from: http://resolver.tudelft.nl/uuid:dc8b7355-cf46-410c-94c3-cc85570b94a7.

Council of Science Editors:

van Hengel A(. Magnetorquer Design and Attitude Control for SHAPE. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:dc8b7355-cf46-410c-94c3-cc85570b94a7

Delft University of Technology

2. Slinger, B.J.M.M. (author). Attitude Control of a Small Helicopter UAV using Incremental Nonlinear Dynamic Inversion.

Degree: 2016, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:9eba1543-6f55-4708-9d68-09446a95d6d4

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This paper presents an attitude controller for a small helicopter Unmanned Aerial Vehicle (UAV) based on Incremental Nonlinear Dynamic Inversion (INDI). INDI is a sensor-based… (more)

Subjects/Keywords: INDI helicopter uav control attitude

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APA (6^th Edition):

Slinger, B. J. M. M. (. (2016). Attitude Control of a Small Helicopter UAV using Incremental Nonlinear Dynamic Inversion. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:9eba1543-6f55-4708-9d68-09446a95d6d4

Chicago Manual of Style (16^th Edition):

Slinger, B J M M (author). “Attitude Control of a Small Helicopter UAV using Incremental Nonlinear Dynamic Inversion.” 2016. Masters Thesis, Delft University of Technology. Accessed April 22, 2021. http://resolver.tudelft.nl/uuid:9eba1543-6f55-4708-9d68-09446a95d6d4.

MLA Handbook (7^th Edition):

Slinger, B J M M (author). “Attitude Control of a Small Helicopter UAV using Incremental Nonlinear Dynamic Inversion.” 2016. Web. 22 Apr 2021.

Vancouver:

Slinger BJMM(. Attitude Control of a Small Helicopter UAV using Incremental Nonlinear Dynamic Inversion. [Internet] [Masters thesis]. Delft University of Technology; 2016. [cited 2021 Apr 22]. Available from: http://resolver.tudelft.nl/uuid:9eba1543-6f55-4708-9d68-09446a95d6d4.

Council of Science Editors:

Slinger BJMM(. Attitude Control of a Small Helicopter UAV using Incremental Nonlinear Dynamic Inversion. [Masters Thesis]. Delft University of Technology; 2016. Available from: http://resolver.tudelft.nl/uuid:9eba1543-6f55-4708-9d68-09446a95d6d4

University of Minnesota

3. Kukowski, Timothy. Magnetic Attitude Control Development and Simulation for a 3U Cube Satellite.

Degree: MS, Aerospace Engineering and Mechanics, 2020, University of Minnesota

URL: http://hdl.handle.net/11299/213061

► SOCRATES and IMPRESS are two cubesats designed and built by the University of Minnesota's Small Satellite Team. These satellites have similar build and function by… (more)

Subjects/Keywords: attitude; control; cubesat; magnetic; magnetorquers

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APA (6^th Edition):

Kukowski, T. (2020). Magnetic Attitude Control Development and Simulation for a 3U Cube Satellite. (Masters Thesis). University of Minnesota. Retrieved from http://hdl.handle.net/11299/213061

Chicago Manual of Style (16^th Edition):

Kukowski, Timothy. “Magnetic Attitude Control Development and Simulation for a 3U Cube Satellite.” 2020. Masters Thesis, University of Minnesota. Accessed April 22, 2021. http://hdl.handle.net/11299/213061.

MLA Handbook (7^th Edition):

Kukowski, Timothy. “Magnetic Attitude Control Development and Simulation for a 3U Cube Satellite.” 2020. Web. 22 Apr 2021.

Vancouver:

Kukowski T. Magnetic Attitude Control Development and Simulation for a 3U Cube Satellite. [Internet] [Masters thesis]. University of Minnesota; 2020. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/11299/213061.

Council of Science Editors:

Kukowski T. Magnetic Attitude Control Development and Simulation for a 3U Cube Satellite. [Masters Thesis]. University of Minnesota; 2020. Available from: http://hdl.handle.net/11299/213061

Lehigh University

4. Zhu, Shiqiao. Analysis of Spacecraft Attitude Control.

Degree: MS, Mechanical Engineering, 2016, Lehigh University

URL: https://preserve.lehigh.edu/etd/2915

► The thesis studies about repositioning the spacecraft to obtain a moving target problem. We model the spacecraft as a rigid body with axis torque controlling… (more)

Subjects/Keywords: alalysis of spacecraft attitude control; analysis control; attitude; attitude control; attitude of spacecraft; spacecraft control; Engineering; Mechanical Engineering

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APA (6^th Edition):

Zhu, S. (2016). Analysis of Spacecraft Attitude Control. (Thesis). Lehigh University. Retrieved from https://preserve.lehigh.edu/etd/2915

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):

Zhu, Shiqiao. “Analysis of Spacecraft Attitude Control.” 2016. Thesis, Lehigh University. Accessed April 22, 2021. https://preserve.lehigh.edu/etd/2915.

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

MLA Handbook (7^th Edition):

Zhu, Shiqiao. “Analysis of Spacecraft Attitude Control.” 2016. Web. 22 Apr 2021.

Vancouver:

Zhu S. Analysis of Spacecraft Attitude Control. [Internet] [Thesis]. Lehigh University; 2016. [cited 2021 Apr 22]. Available from: https://preserve.lehigh.edu/etd/2915.

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

Council of Science Editors:

Zhu S. Analysis of Spacecraft Attitude Control. [Thesis]. Lehigh University; 2016. Available from: https://preserve.lehigh.edu/etd/2915

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

Kwame Nkrumah University of Science and Technology

5. Danso, Adu Eric. Knowledge, attitude and practices towards malaria.

Degree: 2021, Kwame Nkrumah University of Science and Technology

URL: http://dspace.knust.edu.gh:8080/jspui/handle/123456789/13313

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A clear understanding of the knowledge, attitudes and practices of a particular community can inform the design of Behaviour Change Communication (BCC) campaigns to influence… (more)

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A clear understanding of the knowledge, attitudes and practices of a particular community can inform the design of Behaviour Change Communication (BCC) campaigns to influence acceptance and use of any malaria control measures. Research to clearly determine what interventions to carry out has not been undertaken in towns and villages in Akuapim North Municipal Assembly. In this regard, a study was conducted guided by the following objective: To assess a comprehensive knowledge, attitudes and practice (KAP) level of the community towards malaria and associated factors in Akuapim Municipal, Ghana. A cross-sectional study was conducted in between August and September 2019 in Akuapim North Municipal Assembly. Quantitative data were collected by means of a structured questionnaire covering all 21 towns and villages and subsequently were analyzed using SPSS software and Microsoft Excel. 42.16% of respondents had medium knowledge about malaria prevention and control, scoring either 3 or 4 out of a maximum 6 points (Mean score = 5.26 points, SD = 3.24). On the whole, respondents do recognize the threat posed by malaria as most (98.69%) agreed with the statement: “I think that malaria is a serious and life-threatening disease”. Despite most households (72.85%) owning mosquito nets, participants confirmed that some people do not use the nets because they associate them with breathing difficulties. (11.22%) of the respondents had poor practices towards malaria prevention and control. In general, most people had good knowledge about malaria prevention and control. Most of the respondents see malaria as a threat to their lives and community and majority had good practices towards malaria prevention and control but do not reflect to reality on the ground. Therefore interventions aimed at social and behaviour change are necessary to address the gaps highlighted by the study.

A thesis submitted to the School of Medical Sciences, College of Health Sciences, in partial fulfilment of the requirement for the award of Public Health Degree September, 2019

KNUST

Subjects/Keywords: Knowledge, attitude; Malaria control; Akuapim

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APA (6^th Edition):

Danso, A. E. (2021). Knowledge, attitude and practices towards malaria. (Thesis). Kwame Nkrumah University of Science and Technology. Retrieved from http://dspace.knust.edu.gh:8080/jspui/handle/123456789/13313

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):

Danso, Adu Eric. “Knowledge, attitude and practices towards malaria.” 2021. Thesis, Kwame Nkrumah University of Science and Technology. Accessed April 22, 2021. http://dspace.knust.edu.gh:8080/jspui/handle/123456789/13313.

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

MLA Handbook (7^th Edition):

Danso, Adu Eric. “Knowledge, attitude and practices towards malaria.” 2021. Web. 22 Apr 2021.

Vancouver:

Danso AE. Knowledge, attitude and practices towards malaria. [Internet] [Thesis]. Kwame Nkrumah University of Science and Technology; 2021. [cited 2021 Apr 22]. Available from: http://dspace.knust.edu.gh:8080/jspui/handle/123456789/13313.

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

Council of Science Editors:

Danso AE. Knowledge, attitude and practices towards malaria. [Thesis]. Kwame Nkrumah University of Science and Technology; 2021. Available from: http://dspace.knust.edu.gh:8080/jspui/handle/123456789/13313

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

York University

6. Agarwal, Anirudh. Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages.

Degree: MSc -MS, Earth & Space Science, 2019, York University

URL: http://hdl.handle.net/10315/35911

► This study designs and analyzes a new type of controller that helps improve the performance of single axis attitude control of flexible appendages attached to… (more)

Subjects/Keywords: Aerospace engineering; Spacecraft dynamics; Control systems; Acceleration feedback; PIDA; PID; Attitude control; Classical control; Spacecraft attitude control; Single axis attitude control

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APA (6^th Edition):

Agarwal, A. (2019). Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages. (Masters Thesis). York University. Retrieved from http://hdl.handle.net/10315/35911

Chicago Manual of Style (16^th Edition):

Agarwal, Anirudh. “Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages.” 2019. Masters Thesis, York University. Accessed April 22, 2021. http://hdl.handle.net/10315/35911.

MLA Handbook (7^th Edition):

Agarwal, Anirudh. “Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages.” 2019. Web. 22 Apr 2021.

Vancouver:

Agarwal A. Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages. [Internet] [Masters thesis]. York University; 2019. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/10315/35911.

Council of Science Editors:

Agarwal A. Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages. [Masters Thesis]. York University; 2019. Available from: http://hdl.handle.net/10315/35911

University of Toronto

7. Dutia, Jiten. Magnetic Attitude Control of Microsatellites In Geocentric Orbits.

Degree: 2013, University of Toronto

URL: http://hdl.handle.net/1807/35117

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Attitude control of spacecraft in low Earth orbits can be achieved by exploiting the torques generated by the geomagnetic field. Recent research has demonstrated that… (more)

Subjects/Keywords: hybrid attitude control; magnetic attitudde control; 0538

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APA (6^th Edition):

Dutia, J. (2013). Magnetic Attitude Control of Microsatellites In Geocentric Orbits. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/35117

Chicago Manual of Style (16^th Edition):

Dutia, Jiten. “Magnetic Attitude Control of Microsatellites In Geocentric Orbits.” 2013. Masters Thesis, University of Toronto. Accessed April 22, 2021. http://hdl.handle.net/1807/35117.

MLA Handbook (7^th Edition):

Dutia, Jiten. “Magnetic Attitude Control of Microsatellites In Geocentric Orbits.” 2013. Web. 22 Apr 2021.

Vancouver:

Dutia J. Magnetic Attitude Control of Microsatellites In Geocentric Orbits. [Internet] [Masters thesis]. University of Toronto; 2013. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/1807/35117.

Council of Science Editors:

Dutia J. Magnetic Attitude Control of Microsatellites In Geocentric Orbits. [Masters Thesis]. University of Toronto; 2013. Available from: http://hdl.handle.net/1807/35117

University of Toronto

8. Ibrahim, Najmus. Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking.

Degree: 2013, University of Toronto

URL: http://hdl.handle.net/1807/42965

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Terrestrial target tracking using low Earth orbit satellites provides essential daily services and vital scientific data. In this thesis, the Attitude and Orbit Control System… (more)

Subjects/Keywords: satellite; attitude; attitude and orbit control; microsatellite; control; estimation; tracking; 0538

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APA (6^th Edition):

Ibrahim, N. (2013). Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/42965

Chicago Manual of Style (16^th Edition):

Ibrahim, Najmus. “Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking.” 2013. Masters Thesis, University of Toronto. Accessed April 22, 2021. http://hdl.handle.net/1807/42965.

MLA Handbook (7^th Edition):

Ibrahim, Najmus. “Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking.” 2013. Web. 22 Apr 2021.

Vancouver:

Ibrahim N. Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking. [Internet] [Masters thesis]. University of Toronto; 2013. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/1807/42965.

Council of Science Editors:

Ibrahim N. Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking. [Masters Thesis]. University of Toronto; 2013. Available from: http://hdl.handle.net/1807/42965

University of Texas – Austin

9. Mendes De Almeida Neto, Marcelino. Quaternion regression and finite-time controllers for attitude dynamics.

Degree: PhD, Aerospace Engineering, 2020, University of Texas – Austin

URL: http://dx.doi.org/10.26153/tsw/7431

► This dissertation presents two major research contributions to the field of attitude dynamics and control. The first topic comprises of estimating the angular velocity of… (more)

Subjects/Keywords: Quaternion; Attitude control; Attitude estimation; Slam; Quaternion regression; Finite time control

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APA (6^th Edition):

Mendes De Almeida Neto, M. (2020). Quaternion regression and finite-time controllers for attitude dynamics. (Doctoral Dissertation). University of Texas – Austin. Retrieved from http://dx.doi.org/10.26153/tsw/7431

Chicago Manual of Style (16^th Edition):

Mendes De Almeida Neto, Marcelino. “Quaternion regression and finite-time controllers for attitude dynamics.” 2020. Doctoral Dissertation, University of Texas – Austin. Accessed April 22, 2021. http://dx.doi.org/10.26153/tsw/7431.

MLA Handbook (7^th Edition):

Mendes De Almeida Neto, Marcelino. “Quaternion regression and finite-time controllers for attitude dynamics.” 2020. Web. 22 Apr 2021.

Vancouver:

Mendes De Almeida Neto M. Quaternion regression and finite-time controllers for attitude dynamics. [Internet] [Doctoral dissertation]. University of Texas – Austin; 2020. [cited 2021 Apr 22]. Available from: http://dx.doi.org/10.26153/tsw/7431.

Council of Science Editors:

Mendes De Almeida Neto M. Quaternion regression and finite-time controllers for attitude dynamics. [Doctoral Dissertation]. University of Texas – Austin; 2020. Available from: http://dx.doi.org/10.26153/tsw/7431

University of Toronto

10. Serpelloni, Edoardo. Bang-Bang Practical Stabilization of Rigid Bodies.

Degree: PhD, 2017, University of Toronto

URL: http://hdl.handle.net/1807/79471

► In this thesis, we study the problem of designing a practical stabilizer for a rigid body equipped with a set of actuators generating only constant… (more)

▼ In this thesis, we study the problem of designing a practical stabilizer for a rigid body equipped with a set of actuators generating only constant thrust. Our motivation stems from the fact that modern space missions are required to accurately control the position and orientation of spacecraft actuated by constant-thrust jet-thrusters. To comply with the performance limitations of modern thrusters, we design a feedback controller that does not induce high-frequency switching of the actuators. The proposed controller is hybrid and it asymptotically stabilizes an arbitrarily small compact neighborhood of the target position and orientation of the rigid body. The controller is characterized by a hierarchical structure comprising of two control layers. At the low level of the hierarchy, an attitude controller stabilizes the target orientation of the rigid body. At the high level, after the attitude controller has steered the rigid body sufficiently close to its desired orientation, a position controller stabilizes the desired position. The size of the neighborhood being stabilized by the controller can be adjusted via a proper selection of the controller parameters. This allows us to stabilize the rigid body to virtually any degree of accuracy. It is shown that the controller, even in the presence of measurement noise, does not induce high-frequency switching of the actuators. The key component in the design of the controller is a hybrid stabilizer for the origin of double-integrators affected by bounded external perturbations. Specifically, both the position and the attitude stabilizers consist of multiple copies of such a double-integrator controller. The proposed controller is applied to two realistic spacecraft control problems. First, we apply the position controller to the problem of stabilizing the relative position between two spacecraft flying in formation in the vicinity of the L2 libration point of the Sun-Earth system as a part of a large space telescope. The proposed position controller represents the first feedback strategy to guarantee the accuracy level required by this class of space missions using real-life electric thrusters. The final controller is applied to the control of a large space vehicle performing rendezvous and docking operations with the International Space Station. It is shown that the controller guarantees a safe docking even under the effects of biases in the placement of the on-board thrusters. Advisors/Committee Members: Maggiore, Manfredi, Damaren, Christopher J, Electrical and Computer Engineering.

Subjects/Keywords: Attitude Control; Bang-Bang Control; Double-Integrator Control; Spacecraft Control; 0544

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APA (6^th Edition):

Serpelloni, E. (2017). Bang-Bang Practical Stabilization of Rigid Bodies. (Doctoral Dissertation). University of Toronto. Retrieved from http://hdl.handle.net/1807/79471

Chicago Manual of Style (16^th Edition):

Serpelloni, Edoardo. “Bang-Bang Practical Stabilization of Rigid Bodies.” 2017. Doctoral Dissertation, University of Toronto. Accessed April 22, 2021. http://hdl.handle.net/1807/79471.

MLA Handbook (7^th Edition):

Serpelloni, Edoardo. “Bang-Bang Practical Stabilization of Rigid Bodies.” 2017. Web. 22 Apr 2021.

Vancouver:

Serpelloni E. Bang-Bang Practical Stabilization of Rigid Bodies. [Internet] [Doctoral dissertation]. University of Toronto; 2017. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/1807/79471.

Council of Science Editors:

Serpelloni E. Bang-Bang Practical Stabilization of Rigid Bodies. [Doctoral Dissertation]. University of Toronto; 2017. Available from: http://hdl.handle.net/1807/79471

Virginia Tech

11. VanDyke, Matthew Clark. Constant Orbital Momentum Equilibrium Trajectories of a Gyrostat-Satellite.

Degree: PhD, Aerospace Engineering, 2014, Virginia Tech

URL: http://hdl.handle.net/10919/24911

► This dissertation investigates attitude transition maneuvers of a gyrosat-satellite between relative equilibria. The primary challenge in transitioning between relative equilibria is the proper adjustment of… (more)

▼ This dissertation investigates attitude transition maneuvers of a gyrosat-satellite between relative equilibria. The primary challenge in transitioning between relative equilibria is the proper adjustment of the system angular momentum so that upon completing the transition maneuver the gyrostat-satellite will satisfy all the requirements for a relative equilibrium. The system angular momentum is a function of the attitude trajectory taken during the transition maneuver. A new concept, the constant orbital momentum equilibrium trajectory or COMET, is introduced as a means to a straight-forward solution to a subset of the possible transitions between relative equilbria. COMETs are a class of paths in SO(3) that a gyrostat-satellite may travel along that maintain a constant system angular momentum. The primary contributions of this dissertation are the introduction and analysis of COMETs and their application to the problem of transitioning a gyrostat-satellite between two relative equilibria. The current work introduces, defines, and analyzes COMETs in detail. The requirements for a path in SO(3) to be a COMET are defined. It is shown via example that COMETs are closed-curves in SO(3). Visualizations of families of COMETs are presented and discussed in detail. A subset of COMETs are shown to contain critical points that represent isolated relative equilibrium attitudes or furcations of the COMET. The problem of transitioning between two relative equilibria is split into the sub-problems of transitioning between relative equilibria on the same COMET and transitioning between relative equilibria on different COMETs. For transitions between relative equilibria on the same COMET, an open-loop control law is developed that drives a gyrostat-satellite along the COMET until the target relative equilibrium is reached. For transitions between relative equilibria on different COMETs, an open-loop control law is developed that transfers a gyrostat-satellite from the initial relative equilibrium to a relative equilibrium that resides on the same COMET as the target relative equilbrium. Acquisition of the target relative equilibrium is then accomplished via the application of the open-loop control law for transitions between relative equilibria on the same COMET. The results of numeric simulations of gyrostat-satellites executing these transitions are presented. Advisors/Committee Members: Hall, Christopher D. (committeechair), Woolsey, Craig A. (committeechair), Earle, Gregory D. (committee member), Sultan, Cornel (committee member).

Subjects/Keywords: Gyrostat-Satellite; Relative Equilibrium; Spacecraft Dynamics; Attitude Control; Attitude Guidance; Gravitational Torque; Attitude Maneuvers

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APA (6^th Edition):

VanDyke, M. C. (2014). Constant Orbital Momentum Equilibrium Trajectories of a Gyrostat-Satellite. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/24911

Chicago Manual of Style (16^th Edition):

VanDyke, Matthew Clark. “Constant Orbital Momentum Equilibrium Trajectories of a Gyrostat-Satellite.” 2014. Doctoral Dissertation, Virginia Tech. Accessed April 22, 2021. http://hdl.handle.net/10919/24911.

MLA Handbook (7^th Edition):

VanDyke, Matthew Clark. “Constant Orbital Momentum Equilibrium Trajectories of a Gyrostat-Satellite.” 2014. Web. 22 Apr 2021.

Vancouver:

VanDyke MC. Constant Orbital Momentum Equilibrium Trajectories of a Gyrostat-Satellite. [Internet] [Doctoral dissertation]. Virginia Tech; 2014. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/10919/24911.

Council of Science Editors:

VanDyke MC. Constant Orbital Momentum Equilibrium Trajectories of a Gyrostat-Satellite. [Doctoral Dissertation]. Virginia Tech; 2014. Available from: http://hdl.handle.net/10919/24911

Penn State University

12. Ahn, Young Tae. Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution.

Degree: 2012, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/16015

► Spacecraft need specific attitude control methods that depend on the mission type or special tasks. The dynamics and the attitude control of a spacecraft with… (more)

Subjects/Keywords: spacecraft attitude dynamics; attitude control; combinatorial optimization theory

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APA (6^th Edition):

Ahn, Y. T. (2012). Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/16015

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):

Ahn, Young Tae. “Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution.” 2012. Thesis, Penn State University. Accessed April 22, 2021. https://submit-etda.libraries.psu.edu/catalog/16015.

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

MLA Handbook (7^th Edition):

Ahn, Young Tae. “Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution.” 2012. Web. 22 Apr 2021.

Vancouver:

Ahn YT. Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution. [Internet] [Thesis]. Penn State University; 2012. [cited 2021 Apr 22]. Available from: https://submit-etda.libraries.psu.edu/catalog/16015.

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

Council of Science Editors:

Ahn YT. Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution. [Thesis]. Penn State University; 2012. Available from: https://submit-etda.libraries.psu.edu/catalog/16015

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

University of Toronto

13. Johnston-Lemke, Bryan. High Performance Attitude Determination and Control for Nanosatellite Missions.

Degree: 2011, University of Toronto

URL: http://hdl.handle.net/1807/30644

►

Small satellites are growing in popularity because they offer an effective option that enables missions otherwise too schedule or cost limited. However, many possible missions… (more)

Subjects/Keywords: Attitude Control; Attitude Determination; Satellite; Nanosatellite; Astronomy; Formation Flying; 0538

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APA (6^th Edition):

Johnston-Lemke, B. (2011). High Performance Attitude Determination and Control for Nanosatellite Missions. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/30644

Chicago Manual of Style (16^th Edition):

Johnston-Lemke, Bryan. “High Performance Attitude Determination and Control for Nanosatellite Missions.” 2011. Masters Thesis, University of Toronto. Accessed April 22, 2021. http://hdl.handle.net/1807/30644.

MLA Handbook (7^th Edition):

Johnston-Lemke, Bryan. “High Performance Attitude Determination and Control for Nanosatellite Missions.” 2011. Web. 22 Apr 2021.

Vancouver:

Johnston-Lemke B. High Performance Attitude Determination and Control for Nanosatellite Missions. [Internet] [Masters thesis]. University of Toronto; 2011. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/1807/30644.

Council of Science Editors:

Johnston-Lemke B. High Performance Attitude Determination and Control for Nanosatellite Missions. [Masters Thesis]. University of Toronto; 2011. Available from: http://hdl.handle.net/1807/30644

University of Toronto

14. Shen, Young-Young. Attitude Determination and Control Hardware Acceptance Testing for Next Generation Microsatellites.

Degree: 2015, University of Toronto

URL: http://hdl.handle.net/1807/70675

►

In a spacecraft development cycle, components must undergo a rigorous regime of testing, known as acceptance testing, to ensure that they can operate in the… (more)

Subjects/Keywords: Attitude; Control; Microsatellite; Nanosatellite; Satellite; Small; 0538

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APA (6^th Edition):

Shen, Y. (2015). Attitude Determination and Control Hardware Acceptance Testing for Next Generation Microsatellites. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/70675

Chicago Manual of Style (16^th Edition):

Shen, Young-Young. “Attitude Determination and Control Hardware Acceptance Testing for Next Generation Microsatellites.” 2015. Masters Thesis, University of Toronto. Accessed April 22, 2021. http://hdl.handle.net/1807/70675.

MLA Handbook (7^th Edition):

Shen, Young-Young. “Attitude Determination and Control Hardware Acceptance Testing for Next Generation Microsatellites.” 2015. Web. 22 Apr 2021.

Vancouver:

Shen Y. Attitude Determination and Control Hardware Acceptance Testing for Next Generation Microsatellites. [Internet] [Masters thesis]. University of Toronto; 2015. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/1807/70675.

Council of Science Editors:

Shen Y. Attitude Determination and Control Hardware Acceptance Testing for Next Generation Microsatellites. [Masters Thesis]. University of Toronto; 2015. Available from: http://hdl.handle.net/1807/70675

University of Toronto

15. Findlay, Everett. Investigation of Active Vibration Suppression of a Flexible Satellite using Magnetic Attitude Control.

Degree: 2011, University of Toronto

URL: http://hdl.handle.net/1807/30593

►

The problem of attitude control of a flexible satellite using magnetic attitude control is investigated. The work is motivated by JC2Sat - a joint CSA… (more)

Subjects/Keywords: magnetic attitude control; multibody dynamics; 0538

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APA (6^th Edition):

Findlay, E. (2011). Investigation of Active Vibration Suppression of a Flexible Satellite using Magnetic Attitude Control. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/30593

Chicago Manual of Style (16^th Edition):

Findlay, Everett. “Investigation of Active Vibration Suppression of a Flexible Satellite using Magnetic Attitude Control.” 2011. Masters Thesis, University of Toronto. Accessed April 22, 2021. http://hdl.handle.net/1807/30593.

MLA Handbook (7^th Edition):

Findlay, Everett. “Investigation of Active Vibration Suppression of a Flexible Satellite using Magnetic Attitude Control.” 2011. Web. 22 Apr 2021.

Vancouver:

Findlay E. Investigation of Active Vibration Suppression of a Flexible Satellite using Magnetic Attitude Control. [Internet] [Masters thesis]. University of Toronto; 2011. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/1807/30593.

Council of Science Editors:

Findlay E. Investigation of Active Vibration Suppression of a Flexible Satellite using Magnetic Attitude Control. [Masters Thesis]. University of Toronto; 2011. Available from: http://hdl.handle.net/1807/30593

University of Illinois – Urbana-Champaign

16. Zhao, Hongrui. Development of a low-cost multi-camera star tracker for small satellites.

Degree: MS, Aerospace Engineering, 2020, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/108522

► This thesis presents a novel small satellite star tracker that uses an array of low-cost, off the shelf imaging sensors to achieve high accuracy attitude… (more)

Subjects/Keywords: Star Tracker; Attitude Determination and Control

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APA (6^th Edition):

Zhao, H. (2020). Development of a low-cost multi-camera star tracker for small satellites. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/108522

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):

Zhao, Hongrui. “Development of a low-cost multi-camera star tracker for small satellites.” 2020. Thesis, University of Illinois – Urbana-Champaign. Accessed April 22, 2021. http://hdl.handle.net/2142/108522.

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

MLA Handbook (7^th Edition):

Zhao, Hongrui. “Development of a low-cost multi-camera star tracker for small satellites.” 2020. Web. 22 Apr 2021.

Vancouver:

Zhao H. Development of a low-cost multi-camera star tracker for small satellites. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2020. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/2142/108522.

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

Council of Science Editors:

Zhao H. Development of a low-cost multi-camera star tracker for small satellites. [Thesis]. University of Illinois – Urbana-Champaign; 2020. Available from: http://hdl.handle.net/2142/108522

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

Utah State University

17. Bennett, Steven Russell. Control and Stability of Upper Stage Launch Vehicle With Hybrid Arc-Ignition Attitude Control System.

Degree: MS, Mechanical and Aerospace Engineering, 2019, Utah State University

URL: https://digitalcommons.usu.edu/etd/7518

► The Utah State University Propulsion Research Laboratory (USUPRL) has recently made significant developments in the area of hybrid rocket systems. This type of propulsion… (more)

Subjects/Keywords: Hybrid; Attitude; Control; Rocket; Slosh; Aerospace Engineering

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APA (6^th Edition):

Bennett, S. R. (2019). Control and Stability of Upper Stage Launch Vehicle With Hybrid Arc-Ignition Attitude Control System. (Masters Thesis). Utah State University. Retrieved from https://digitalcommons.usu.edu/etd/7518

Chicago Manual of Style (16^th Edition):

Bennett, Steven Russell. “Control and Stability of Upper Stage Launch Vehicle With Hybrid Arc-Ignition Attitude Control System.” 2019. Masters Thesis, Utah State University. Accessed April 22, 2021. https://digitalcommons.usu.edu/etd/7518.

MLA Handbook (7^th Edition):

Bennett, Steven Russell. “Control and Stability of Upper Stage Launch Vehicle With Hybrid Arc-Ignition Attitude Control System.” 2019. Web. 22 Apr 2021.

Vancouver:

Bennett SR. Control and Stability of Upper Stage Launch Vehicle With Hybrid Arc-Ignition Attitude Control System. [Internet] [Masters thesis]. Utah State University; 2019. [cited 2021 Apr 22]. Available from: https://digitalcommons.usu.edu/etd/7518.

Council of Science Editors:

Bennett SR. Control and Stability of Upper Stage Launch Vehicle With Hybrid Arc-Ignition Attitude Control System. [Masters Thesis]. Utah State University; 2019. Available from: https://digitalcommons.usu.edu/etd/7518

Brigham Young University

18. Argyle, Matthew Elliott. Modeling and Control of a Tailsitter with a Ducted Fan.

Degree: PhD, 2016, Brigham Young University

URL: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=6928&context=etd

► There are two traditional aircraft categories: fixed-wing which have a long endurance and a high cruise airspeed and rotorcraft which can take-off and land… (more)

▼ There are two traditional aircraft categories: fixed-wing which have a long endurance and a high cruise airspeed and rotorcraft which can take-off and land vertically. The tailsitter is a type of aircraft that has the strengths of both platforms, with no additional mechanical complexity, because it takes off and lands vertically on its tail and can transition the entire aircraft horizontally into high-speed flight. In this dissertation, we develop the entire control system for a tailsitter with a ducted fan. The standard method to compute the quaternion-based attitude error does not generate ideal trajectories for a hovering tailsitter for some situations. In addition, the only approach in the literature to mitigate this breaks down for large attitude errors. We develop an alternative quaternion-based error method which generates better trajectories than the standard approach and can handle large errors. We also derive a hybrid backstepping controller with almost global asymptotic stability based on this error method. Many common altitude and airspeed control schemes for a fixed-wing airplane assume that the altitude and airspeed dynamics are decoupled which leads to errors. The Total Energy Control System (TECS) is an approach that controls the altitude and airspeed by manipulating the total energy rate and energy distribution rate, of the aircraft, in a manner which accounts for the dynamic coupling. In this dissertation, a nonlinear controller, which can handle inaccurate thrust and drag models, based on the TECS principles is derived. Simulation results show that the nonlinear controller has better performance than the standard PI TECS control schemes. Most constant altitude transitions are accomplished by generating an optimal trajectory, and potentially actuator inputs, based on a high fidelity model of the aircraft. While there are several approaches to mitigate the effects of modeling errors, these do not fully remove the accurate model requirement. In this dissertation, we develop two different approaches that can achieve near constant altitude transitions for some types of aircraft. The first method, based on multiple LQR controllers, requires a high fidelity model of the aircraft. However, the second method, based on the energy along the body axes, requires almost no aerodynamic information.

Subjects/Keywords: attitude control; attitude error; guidance and control; tailsitter; TECS; VTOL; Electrical and Computer Engineering

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APA (6^th Edition):

Argyle, M. E. (2016). Modeling and Control of a Tailsitter with a Ducted Fan. (Doctoral Dissertation). Brigham Young University. Retrieved from https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=6928&context=etd

Chicago Manual of Style (16^th Edition):

Argyle, Matthew Elliott. “Modeling and Control of a Tailsitter with a Ducted Fan.” 2016. Doctoral Dissertation, Brigham Young University. Accessed April 22, 2021. https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=6928&context=etd.

MLA Handbook (7^th Edition):

Argyle, Matthew Elliott. “Modeling and Control of a Tailsitter with a Ducted Fan.” 2016. Web. 22 Apr 2021.

Vancouver:

Argyle ME. Modeling and Control of a Tailsitter with a Ducted Fan. [Internet] [Doctoral dissertation]. Brigham Young University; 2016. [cited 2021 Apr 22]. Available from: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=6928&context=etd.

Council of Science Editors:

Argyle ME. Modeling and Control of a Tailsitter with a Ducted Fan. [Doctoral Dissertation]. Brigham Young University; 2016. Available from: https://scholarsarchive.byu.edu/cgi/viewcontent.cgi?article=6928&context=etd

Delft University of Technology

19. Maltha, Rutger (author). GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator.

Degree: 2018, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:16c8d9b6-1d07-46fa-9a4f-4c445bd9e3dc

► Given the difficulty that is normally associated with tuning highly nonlinear control systems, such as seen in LEO spacecraft, it is interesting to evaluate how… (more)

Subjects/Keywords: Genetic algorithm; INDI; Attitude control; GOCE; Spacecraft torque models; Magnetic attitude control; NDI

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APA (6^th Edition):

Maltha, R. (. (2018). GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:16c8d9b6-1d07-46fa-9a4f-4c445bd9e3dc

Chicago Manual of Style (16^th Edition):

Maltha, Rutger (author). “GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator.” 2018. Masters Thesis, Delft University of Technology. Accessed April 22, 2021. http://resolver.tudelft.nl/uuid:16c8d9b6-1d07-46fa-9a4f-4c445bd9e3dc.

MLA Handbook (7^th Edition):

Maltha, Rutger (author). “GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator.” 2018. Web. 22 Apr 2021.

Vancouver:

Maltha R(. GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Apr 22]. Available from: http://resolver.tudelft.nl/uuid:16c8d9b6-1d07-46fa-9a4f-4c445bd9e3dc.

Council of Science Editors:

Maltha R(. GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:16c8d9b6-1d07-46fa-9a4f-4c445bd9e3dc

University of California – Berkeley

20. Wang, Yizhou. Attitude Control and Estimation.

Degree: Mechanical Engineering, 2015, University of California – Berkeley

URL: http://www.escholarship.org/uc/item/59b5d7hh

► The attitude control problem, or the control of a spacecraft's orientation with respect to a frame of reference, is a challenging problem in space missions… (more)

▼ The attitude control problem, or the control of a spacecraft's orientation with respect to a frame of reference, is a challenging problem in space missions and has attracted much attention as it involves highly nonlinear characteristics of the governing equations. The attitude control task requires an estimation algorithm that deduces the attitude from strapdown sensor inputs and a control algorithm that computes the necessary torques so that the vehicle can follow a desired attitude.From the perspective of control, feedback control laws are sought for the purpose of asymptotic trajectory tracking, with the ability to reject unexpected external disturbances, and be insensitive to parameter variations. An adaptive sliding mode spacecraft attitude controller that fulfills those requirements is discussed in this dissertation. Unit quaternions and Rodrigues parameters are used to parameterize attitude. Lyapunov stability theory is used to prove the stability of the closed-loop system.For attitude estimation with increased accuracy, strap-down gyroscopes and vector measurements are fused together. Because of the nonlinear nature of the attitude kinematics equation and the measurement model, the problem becomes a nonlinear state estimation problem, which is typically tackled by Bayesian inference. In this dissertation we discuss a marginalized particle filtering algorithm, to possibly increase the estimation accuracy and reduce the computation load compared with other non-parametric methods. We exploit the linear-substructure and further show that the linear state evolution is completely independent of the nonlinear partition. We have also investigated a computationally efficient and easy-to-tune sensor fusion algorithm, based on the complementary filter and the TRIAD algorithm. It is beneficial to use a complementary filter because rate and angle sensor possess benefits and drawbacks in different frequency regimes. The proposed algorithm shows comparable performance to the EKF but with less computational burden. It aims to be implementable on a small portable platform. In applications of mobile robots, the cutoff frequency can be adapted based on a fuzzy logic in real-time to adjust trust to different sensors, to cope with problems such as motion accelerations and magnetic distortions.

Subjects/Keywords: Mechanical engineering; Aerospace engineering; Adaptive control; Attitude control; Attitude estimation; IMU; Particle filter; Sliding mode control

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APA (6^th Edition):

Wang, Y. (2015). Attitude Control and Estimation. (Thesis). University of California – Berkeley. Retrieved from http://www.escholarship.org/uc/item/59b5d7hh

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):

Wang, Yizhou. “Attitude Control and Estimation.” 2015. Thesis, University of California – Berkeley. Accessed April 22, 2021. http://www.escholarship.org/uc/item/59b5d7hh.

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

MLA Handbook (7^th Edition):

Wang, Yizhou. “Attitude Control and Estimation.” 2015. Web. 22 Apr 2021.

Vancouver:

Wang Y. Attitude Control and Estimation. [Internet] [Thesis]. University of California – Berkeley; 2015. [cited 2021 Apr 22]. Available from: http://www.escholarship.org/uc/item/59b5d7hh.

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

Council of Science Editors:

Wang Y. Attitude Control and Estimation. [Thesis]. University of California – Berkeley; 2015. Available from: http://www.escholarship.org/uc/item/59b5d7hh

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

University of Toronto

21. Tarantini, Vincent. Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite.

Degree: 2012, University of Toronto

URL: http://hdl.handle.net/1807/33557

►

Contributions to two missions are presented. The first is a demonstration mission called CanX-7 that uses a 4 square metre drag sail to de-orbit a… (more)

Subjects/Keywords: De-orbit; Drag sail; Thermal control; Attitude determination and control; 0538

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APA (6^th Edition):

Tarantini, V. (2012). Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/33557

Chicago Manual of Style (16^th Edition):

Tarantini, Vincent. “Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite.” 2012. Masters Thesis, University of Toronto. Accessed April 22, 2021. http://hdl.handle.net/1807/33557.

MLA Handbook (7^th Edition):

Tarantini, Vincent. “Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite.” 2012. Web. 22 Apr 2021.

Vancouver:

Tarantini V. Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite. [Internet] [Masters thesis]. University of Toronto; 2012. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/1807/33557.

Council of Science Editors:

Tarantini V. Attitude Dependent De-orbit Lifetime Analysis of an Aerodynamic Drag Sail Demonstration Spacecraft and Detailed Thermal Subsystem Design for a Polar Orbiting Communications Nanosatellite. [Masters Thesis]. University of Toronto; 2012. Available from: http://hdl.handle.net/1807/33557

University of Connecticut

22. Liu, Yuqian. Control and Navigation of Autonomous Underwater Vehicles.

Degree: MS, Mechanical Engineering, 2014, University of Connecticut

URL: https://opencommons.uconn.edu/gs_theses/549

► This thesis presents an efficient attitude control design, which combined L1 adaptive control and backstepping control together. Based on this attitude controller, a design… (more)

Subjects/Keywords: Autonomous Underwater Vehicles; Attitude Control; Adaptive Control; Fixed-point Navigation; Autopilot

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APA (6^th Edition):

Liu, Y. (2014). Control and Navigation of Autonomous Underwater Vehicles. (Masters Thesis). University of Connecticut. Retrieved from https://opencommons.uconn.edu/gs_theses/549

Chicago Manual of Style (16^th Edition):

Liu, Yuqian. “Control and Navigation of Autonomous Underwater Vehicles.” 2014. Masters Thesis, University of Connecticut. Accessed April 22, 2021. https://opencommons.uconn.edu/gs_theses/549.

MLA Handbook (7^th Edition):

Liu, Yuqian. “Control and Navigation of Autonomous Underwater Vehicles.” 2014. Web. 22 Apr 2021.

Vancouver:

Liu Y. Control and Navigation of Autonomous Underwater Vehicles. [Internet] [Masters thesis]. University of Connecticut; 2014. [cited 2021 Apr 22]. Available from: https://opencommons.uconn.edu/gs_theses/549.

Council of Science Editors:

Liu Y. Control and Navigation of Autonomous Underwater Vehicles. [Masters Thesis]. University of Connecticut; 2014. Available from: https://opencommons.uconn.edu/gs_theses/549

Luleå University of Technology

23. Cypriano, Lucas Almeida. Study and Design of an Adaptive Control Law for Spacecraft Attitude Control.

Degree: 2014, Luleå University of Technology

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-50766

►

In this thesis the problem of spacecraft attitude control is investigated. The spacecraft dynamics are modeled as a rigid body system controlled by 4… (more)

Subjects/Keywords: Technology; Adaptive Control; RCAC; Attitude Control; ADCS; AOCS; Spacecraft; Teknik

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APA (6^th Edition):

Cypriano, L. A. (2014). Study and Design of an Adaptive Control Law for Spacecraft Attitude Control. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-50766

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):

Cypriano, Lucas Almeida. “Study and Design of an Adaptive Control Law for Spacecraft Attitude Control.” 2014. Thesis, Luleå University of Technology. Accessed April 22, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-50766.

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

MLA Handbook (7^th Edition):

Cypriano, Lucas Almeida. “Study and Design of an Adaptive Control Law for Spacecraft Attitude Control.” 2014. Web. 22 Apr 2021.

Vancouver:

Cypriano LA. Study and Design of an Adaptive Control Law for Spacecraft Attitude Control. [Internet] [Thesis]. Luleå University of Technology; 2014. [cited 2021 Apr 22]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-50766.

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

Council of Science Editors:

Cypriano LA. Study and Design of an Adaptive Control Law for Spacecraft Attitude Control. [Thesis]. Luleå University of Technology; 2014. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-50766

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

Delft University of Technology

24. Habets, J.M.G. (author). Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft.

Degree: 2015, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:f1bc854a-36f9-4401-a892-2313e4022ea8

► Space debris has become a major issue for the space industry over the last couple of years. The increasing number of uncontrolled objects in space… (more)

▼ Space debris has become a major issue for the space industry over the last couple of years. The increasing number of uncontrolled objects in space increases the chance of collision with a spacecraft. The unexpected loss of contact with ENVISAT, the European Space Agency’s largest environmental spacecraft, added one more piece of debris to the list. It also sparked ESA’s interest in the active removal of space debris. Numerous removal methods are being investigated, one of which uses a chaser spacecraft that will attach itself to the debris by means of a robot arm and tentacles and will then perform a series of braking manoeuvres to re-enter the Earth’s atmosphere. The proximity operations require an accurate attitude control system. In this thesis, these operations have been divided into three phases: an unconnected phase in which the chaser spacecraft synchronises its motion with that of the (spinning) target debris; a semi-connected phase, where the robot arm and tentacles form a flexible connection between the chaser and target; a connected phase, where the two spacecraft are assumed to be rigidly attached to each other (and form a stack). The objective of this thesis is to investigate the stability and controllability of the system in these three phases. Because the system changes in configuration during its mission, it can be classified as an Evolving System; a system with actively controlled components that "mate" to form a single connected system. The connection between components becomes stronger during the evolution and can be represented by connection forces and moments. In this thesis, the connection is modelled as a rotational spring and damper acting between the chaser spacecraft and ENVISAT. By developing a representative simulator environment the stability and controllability of the system is assessed. Two major parts of the simulator comprise the attitude control algorithms and control actuators. The latter consists of a Reaction Control System, reaction wheels, and a control allocation algorithm. The attitude control algorithms that are investigated are a Linear Quadratic Regulator and a model reference adaptive controller. A linear stability analysis of the system showed that the system remains stable during its evolution when the chaser is actively controlled. This is partly because the motion of the chaser has little effect on the motion of ENVISAT due to the large size difference between the two spacecraft. However, for a system with equally sized spacecraft, the linear stability analysis showed that instability can occur. Furthermore, in stack configuration, a gravity-gradient stable attitude was found when the minor axis of the system is parallel to the Earth radial. Moreover, for a suitable deorbit attitude and an unobstructed view to the Earth, the only stable attitude is one which has a roll angle of -90 deg. Next, results of the nonlinear simulations revealed that the combination of reaction wheels and attitude thrusters gives worse performance than when only thrusters are used. This is… Advisors/Committee Members: Mooij, E. (mentor).

Subjects/Keywords: attitude control; space debris; adaptive control; evolving systems; ENVISAT

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APA (6^th Edition):

Habets, J. M. G. (. (2015). Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:f1bc854a-36f9-4401-a892-2313e4022ea8

Chicago Manual of Style (16^th Edition):

Habets, J M G (author). “Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft.” 2015. Masters Thesis, Delft University of Technology. Accessed April 22, 2021. http://resolver.tudelft.nl/uuid:f1bc854a-36f9-4401-a892-2313e4022ea8.

MLA Handbook (7^th Edition):

Habets, J M G (author). “Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft.” 2015. Web. 22 Apr 2021.

Vancouver:

Habets JMG(. Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft. [Internet] [Masters thesis]. Delft University of Technology; 2015. [cited 2021 Apr 22]. Available from: http://resolver.tudelft.nl/uuid:f1bc854a-36f9-4401-a892-2313e4022ea8.

Council of Science Editors:

Habets JMG(. Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft. [Masters Thesis]. Delft University of Technology; 2015. Available from: http://resolver.tudelft.nl/uuid:f1bc854a-36f9-4401-a892-2313e4022ea8

25. Yang, Sungpil. Robustness properties of quaternion-based attitude control systems.

Degree: PhD, Aerospace Engineering, 2016, University of Texas – Austin

URL: http://hdl.handle.net/2152/38095

► Both stabilizing and tracking solutions of the rigid-body attitude control problem, using various attitude representations, are now well understood. Based on the sensor availability, numerous… (more)

▼ Both stabilizing and tracking solutions of the rigid-body attitude control problem, using various attitude representations, are now well understood. Based on the sensor availability, numerous full-state feedback or gyro-free output feedback controllers have been proposed and studied. In the dissertation, we revisit classical proportional-derivative (PD) type attitude controllers when the system is subject to uncertainties like time-delay in the feedback loop, measurement errors, external disturbance torques and modeling uncertainties. We not only analyze existing PD-type controllers while considering various types of uncertainties, but also design tracking controllers robust to the system parameter uncertainties. We adopt the quaternion representation for the attitude kinematics so that we can avoid the geometric singularities coming with minimal 3-dimensional parameter representations. For stability and robustness analysis of the PD-type controllers, we do not rely on the linear system framework in which the original dynamics are considered as the sum of the nominal linear part and the nonlinear perturbation part. Instead, another approach is suggested as suitable for the quaternion kinematic representation so that results are not restricted to a neighborhood of the origin. We first deal with one of the common Lyapunov functions used for quaternion-based attitude control problem. Then, through the strictification process, a new Lyapunov function is constructed which can be analyzed based on the standard Lyapunov stability analysis method. As a result, we establish sufficient conditions for locally stability or boundedness of the system subject to aforementioned uncertainties for both PD full-state feedback and PD-like gyro-free output feedback controllers. When our scope is narrowed to the system parameter uncertainties, we propose adaptive controllers that track predefined reference trajectories and estimate the unknown inertial parameters. Specifically, we apply a dynamic scaling-based Immersion and Invariance method for the first time to the attitude tracking problem. We also provide a way to control and estimate the upper bound of a dynamic scaling factor which has not yet been seen in the literature. Advisors/Committee Members: Akella, Maruthi Ram, 1972- (advisor), Bakolas, Efstathios (committee member), Arapostathis, Aristotle (committee member), Acikmese, Behcet (committee member), Mazenc, Frederic (committee member).

Subjects/Keywords: Attitude control; Quaternion kinematics; Robustness; Adaptive control; Uncertainties; Delay; Disturbances

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

APA (6^th Edition):

Yang, S. (2016). Robustness properties of quaternion-based attitude control systems. (Doctoral Dissertation). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/38095

Chicago Manual of Style (16^th Edition):

Yang, Sungpil. “Robustness properties of quaternion-based attitude control systems.” 2016. Doctoral Dissertation, University of Texas – Austin. Accessed April 22, 2021. http://hdl.handle.net/2152/38095.

MLA Handbook (7^th Edition):

Yang, Sungpil. “Robustness properties of quaternion-based attitude control systems.” 2016. Web. 22 Apr 2021.

Vancouver:

Yang S. Robustness properties of quaternion-based attitude control systems. [Internet] [Doctoral dissertation]. University of Texas – Austin; 2016. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/2152/38095.

Council of Science Editors:

Yang S. Robustness properties of quaternion-based attitude control systems. [Doctoral Dissertation]. University of Texas – Austin; 2016. Available from: http://hdl.handle.net/2152/38095

Luleå University of Technology

26. Svedevall, Anders. Development of attitude determination sensors for miniature satellites.

Degree: 2014, Luleå University of Technology

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-52057

►

Attitude determination is an important subsystem of any satellite application. Several different approaches are available to determine the orientation of a spacecraft. By using… (more)

Subjects/Keywords: Technology; Teknik; Sun sensor; attitude determination; pico satellite; attitude control; PSD sensor

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APA (6^th Edition):

Svedevall, A. (2014). Development of attitude determination sensors for miniature satellites. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-52057

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):

Svedevall, Anders. “Development of attitude determination sensors for miniature satellites.” 2014. Thesis, Luleå University of Technology. Accessed April 22, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-52057.

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

MLA Handbook (7^th Edition):

Svedevall, Anders. “Development of attitude determination sensors for miniature satellites.” 2014. Web. 22 Apr 2021.

Vancouver:

Svedevall A. Development of attitude determination sensors for miniature satellites. [Internet] [Thesis]. Luleå University of Technology; 2014. [cited 2021 Apr 22]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-52057.

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

Council of Science Editors:

Svedevall A. Development of attitude determination sensors for miniature satellites. [Thesis]. Luleå University of Technology; 2014. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-52057

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

University of Illinois – Urbana-Champaign

27. Vedant, -. Improved qualification and algorithms for illinisat-2 attitude determination and control.

Degree: MS, Aerospace Engineering, 2018, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/101238

► The University of Illinois has developed the IlliniSat-2 CubeSat bus, a generic scalable and modular design, utilizing commercially available off the shelf (COTS) parts. The… (more)

Subjects/Keywords: Attitude Determination and Control; Control Systems; Dynamic Programming; Trajectory Planning; Underactuated Control

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APA (6^th Edition):

Vedant, -. (2018). Improved qualification and algorithms for illinisat-2 attitude determination and control. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/101238

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):

Vedant, -. “Improved qualification and algorithms for illinisat-2 attitude determination and control.” 2018. Thesis, University of Illinois – Urbana-Champaign. Accessed April 22, 2021. http://hdl.handle.net/2142/101238.

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

MLA Handbook (7^th Edition):

Vedant, -. “Improved qualification and algorithms for illinisat-2 attitude determination and control.” 2018. Web. 22 Apr 2021.

Vancouver:

Vedant -. Improved qualification and algorithms for illinisat-2 attitude determination and control. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2018. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/2142/101238.

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

Council of Science Editors:

Vedant -. Improved qualification and algorithms for illinisat-2 attitude determination and control. [Thesis]. University of Illinois – Urbana-Champaign; 2018. Available from: http://hdl.handle.net/2142/101238

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

University of Toronto

28. Binette, Mark Richard. An Investigation of Nonlinear Control of Spacecraft Attitude.

Degree: 2013, University of Toronto

URL: http://hdl.handle.net/1807/42688

►

The design of controllers subject to the nonlinear H-infinity criterion is explored. The plants to be controlled are the attitude motion of spacecraft, subject to… (more)

Subjects/Keywords: H-infinity control theory; modified Rodrigues parameters; spacecraft attitude control; control theory; 0538

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APA (6^th Edition):

Binette, M. R. (2013). An Investigation of Nonlinear Control of Spacecraft Attitude. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/42688

Chicago Manual of Style (16^th Edition):

Binette, Mark Richard. “An Investigation of Nonlinear Control of Spacecraft Attitude.” 2013. Masters Thesis, University of Toronto. Accessed April 22, 2021. http://hdl.handle.net/1807/42688.

MLA Handbook (7^th Edition):

Binette, Mark Richard. “An Investigation of Nonlinear Control of Spacecraft Attitude.” 2013. Web. 22 Apr 2021.

Vancouver:

Binette MR. An Investigation of Nonlinear Control of Spacecraft Attitude. [Internet] [Masters thesis]. University of Toronto; 2013. [cited 2021 Apr 22]. Available from: http://hdl.handle.net/1807/42688.

Council of Science Editors:

Binette MR. An Investigation of Nonlinear Control of Spacecraft Attitude. [Masters Thesis]. University of Toronto; 2013. Available from: http://hdl.handle.net/1807/42688

Delft University of Technology

29. Fragoso Trigo, G. (author). Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs.

Degree: 2011, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:ac9a05df-7c33-4dae-9d34-5e667e6168ce

►

In the context of the initiative Formation for Atmospheric Science and Technology demonstration (FAST), this dissertation describes the design and comparison of several nonlinear attitude… (more)

▼

In the context of the initiative Formation for Atmospheric Science and Technology demonstration (FAST), this dissertation describes the design and comparison of several nonlinear attitude controllers for TU Delft’s micro-satellite. The control requirements include robustness against model uncertainties and disturbances. To this end, Backstepping is selected as the base control design for the stability awareness provided and the versatility in rendering the control law robust and adaptive. Five Backstepping schemes are selected for comparison: Standard Static, Static Robust, Integrated Adaptive with tuning functions estimation, Modular Adaptive with nonlinear extended state observation and, finally, Immersion and Invariance Adaptive. The spacecraft model is written using Modified Rodrigues Parameters. Three perturbation sources are considered and applied separately: constant inertia tensor mismatch; saturated reaction wheel; and moving mirror from a payload spectrometer. All perturbations are translated to time-variant disturbance torques. Convergence of the tuning functions estimator to the true disturbance value is proved. The Immersion and Invariance Adaptive Backstepping law is here proved input-to-state stable in case of time-variable perturbation. Command filters are used in all designs allowing the inclusion of magnitude and rate constraints. Simulation reveals similar tracking performances of all controlled systems in a disturbance-free case. In all disturbance scenarios the adaptive laws clearly outperform the static ones. This is especially evident in the presence of a faulty reaction wheel and a moving payload. Sampling time analysis shows higher dependence of the adaptive designs on the control frequency. The Modular Adaptive and the Immersion and Invariance Adaptive Backstepping controllers display the best performances. However, the latter design emerges as, not only the easiest to tune, but also as the one with the most consistent performance.

Control and Simulation

Aerospace Engineering

Advisors/Committee Members: Chu, Q.P. (mentor).

Subjects/Keywords: Spacecraft Attitude Control; Robust Control; Adaptive Control; Backstepping; Immersion and Invariance; Modified Rodrigues Parameters

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

APA (6^th Edition):

Fragoso Trigo, G. (. (2011). Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:ac9a05df-7c33-4dae-9d34-5e667e6168ce

Chicago Manual of Style (16^th Edition):

Fragoso Trigo, G (author). “Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs.” 2011. Masters Thesis, Delft University of Technology. Accessed April 22, 2021. http://resolver.tudelft.nl/uuid:ac9a05df-7c33-4dae-9d34-5e667e6168ce.

MLA Handbook (7^th Edition):

Fragoso Trigo, G (author). “Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs.” 2011. Web. 22 Apr 2021.

Vancouver:

Fragoso Trigo G(. Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs. [Internet] [Masters thesis]. Delft University of Technology; 2011. [cited 2021 Apr 22]. Available from: http://resolver.tudelft.nl/uuid:ac9a05df-7c33-4dae-9d34-5e667e6168ce.

Council of Science Editors:

Fragoso Trigo G(. Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs. [Masters Thesis]. Delft University of Technology; 2011. Available from: http://resolver.tudelft.nl/uuid:ac9a05df-7c33-4dae-9d34-5e667e6168ce

Queensland University of Technology

30. Dando, Aaron John. Robust adaptive control of rigid spacecraft attitude maneuvers.

Degree: 2008, Queensland University of Technology

URL: https://eprints.qut.edu.au/16695/

► In this thesis novel feedback attitude control algorithms and attitude estimation algorithms are developed for a three-axis stabilised spacecraft attitude control system. The spacecraft models… (more)

▼ In this thesis novel feedback attitude control algorithms and attitude estimation algorithms are developed for a three-axis stabilised spacecraft attitude control system. The spacecraft models considered include a rigid-body spacecraft equipped with (i) external control torque devices, and (ii) a redundant reaction wheel configuration. The attitude sensor suite comprises a three-axis magnetometer and three-axis rate gyroscope assembly. The quaternion parameters (also called Euler symmetric parameters), which globally avoid singularities but are subject to a unity-norm constraint, are selected as the primary attitude coordinates. There are four novel contributions presented in this thesis. The first novel contribution is the development of a robust control strategy for spacecraft attitude tracking maneuvers, in the presence of dynamic model uncertainty in the spacecraft inertia matrix, actuator magnitude constraints, bounded persistent external disturbances, and state estimation error. The novel component of this algorithm is the incorporation of state estimation error into the stability analysis. The proposed control law contains a parameter which is dynamically adjusted to ensure global asymptotic stability of the overall closedloop system, in the presence of these specific system non-idealities. A stability proof is presented which is based on Lyapunov's direct method, in conjunction with Barbalat's lemma. The control design approach also ensures minimum angular path maneuvers, since the attitude quaternion parameters are not unique. The second novel contribution is the development of a robust direct adaptive control strategy for spacecraft attitude tracking maneuvers, in the presence of dynamic model uncertainty in the spacecraft inertia matrix. The novel aspect of this algorithm is the incorporation of a composite parameter update strategy, which ensures global exponential convergence of the closed-loop system. A stability proof is presented which is based on Lyapunov's direct method, in conjunction with Barbalat's lemma. The exponential convergence results provided by this control strategy require persistently exciting reference trajectory commands. The control design approach also ensures minimum angular path maneuvers. The third novel contribution is the development of an optimal control strategy for spacecraft attitude maneuvers, based on a rigid body spacecraft model including a redundant reaction wheel assembly. The novel component of this strategy is the proposal of a performance index which represents the total electrical energy consumed by the reaction wheel over the maneuver interval. Pontraygin's minimum principle is applied to formulate the necessary conditions for optimality, in which the control torques are subject to timevarying magnitude constraints. The presence of singular sub-arcs in the statespace and their associated singular controls are investigated using Kelley's necessary condition. The two-point boundary-value problem (TPBVP) is formulated using Pontrayagin's minimum principle. The…

Subjects/Keywords: spacecraft attitude control system; spacecraft attitude manevers; spacecraft attitude estimation; Lyapunov stability theory; adaptive control theory; optimal control theory; state estimation theory

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

APA (6^th Edition):

Dando, A. J. (2008). Robust adaptive control of rigid spacecraft attitude maneuvers. (Thesis). Queensland University of Technology. Retrieved from https://eprints.qut.edu.au/16695/

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):

Dando, Aaron John. “Robust adaptive control of rigid spacecraft attitude maneuvers.” 2008. Thesis, Queensland University of Technology. Accessed April 22, 2021. https://eprints.qut.edu.au/16695/.

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

MLA Handbook (7^th Edition):

Dando, Aaron John. “Robust adaptive control of rigid spacecraft attitude maneuvers.” 2008. Web. 22 Apr 2021.

Vancouver:

Dando AJ. Robust adaptive control of rigid spacecraft attitude maneuvers. [Internet] [Thesis]. Queensland University of Technology; 2008. [cited 2021 Apr 22]. Available from: https://eprints.qut.edu.au/16695/.

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

Council of Science Editors:

Dando AJ. Robust adaptive control of rigid spacecraft attitude maneuvers. [Thesis]. Queensland University of Technology; 2008. Available from: https://eprints.qut.edu.au/16695/

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

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Open Access Theses and Dissertations