subject:(Attitude Control)

Lehigh University

1. 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 June 20, 2019. 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. 20 Jun 2019.

Vancouver:

Zhu S. Analysis of Spacecraft Attitude Control. [Internet] [Thesis]. Lehigh University; 2016. [cited 2019 Jun 20]. 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

University of Toronto

2. Philip, Adam Neil. Attitude Sensing, Actuation, and Control of the BRITE and CanX-4&5 Satellites.

Degree: 2008, University of Toronto

URL: http://hdl.handle.net/1807/17213

►

An attitude control system for the BRITE and CanX-4&5 nanosatellites is developed. BRITE and CanX-4&5 are research satellites based on the Space Flight Laboratory’s Generic… (more)

Subjects/Keywords: Attitude; Control; Satellite; Sensing; 0538

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APA (6^th Edition):

Philip, A. N. (2008). Attitude Sensing, Actuation, and Control of the BRITE and CanX-4&5 Satellites. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/17213

Chicago Manual of Style (16^th Edition):

Philip, Adam Neil. “Attitude Sensing, Actuation, and Control of the BRITE and CanX-4&5 Satellites.” 2008. Masters Thesis, University of Toronto. Accessed June 20, 2019. http://hdl.handle.net/1807/17213.

MLA Handbook (7^th Edition):

Philip, Adam Neil. “Attitude Sensing, Actuation, and Control of the BRITE and CanX-4&5 Satellites.” 2008. Web. 20 Jun 2019.

Vancouver:

Philip AN. Attitude Sensing, Actuation, and Control of the BRITE and CanX-4&5 Satellites. [Internet] [Masters thesis]. University of Toronto; 2008. [cited 2019 Jun 20]. Available from: http://hdl.handle.net/1807/17213.

Council of Science Editors:

Philip AN. Attitude Sensing, Actuation, and Control of the BRITE and CanX-4&5 Satellites. [Masters Thesis]. University of Toronto; 2008. Available from: http://hdl.handle.net/1807/17213

University of Toronto

3. Seth, Nitin. Hybrid Magnetic Attitude Controller for Low Earth Orbit Satellites using the Time-varying Linear Quadratic Regulator.

Degree: 2009, University of Toronto

URL: http://hdl.handle.net/1807/17711

►

The following is a study of an attitude control system (ACS) for a low earth orbit nanosatellite. Control actuation is applied using three reaction wheels… (more)

Subjects/Keywords: Attitude Control; LQR; 0538

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APA (6^th Edition):

Seth, N. (2009). Hybrid Magnetic Attitude Controller for Low Earth Orbit Satellites using the Time-varying Linear Quadratic Regulator. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/17711

Chicago Manual of Style (16^th Edition):

Seth, Nitin. “Hybrid Magnetic Attitude Controller for Low Earth Orbit Satellites using the Time-varying Linear Quadratic Regulator.” 2009. Masters Thesis, University of Toronto. Accessed June 20, 2019. http://hdl.handle.net/1807/17711.

MLA Handbook (7^th Edition):

Seth, Nitin. “Hybrid Magnetic Attitude Controller for Low Earth Orbit Satellites using the Time-varying Linear Quadratic Regulator.” 2009. Web. 20 Jun 2019.

Vancouver:

Seth N. Hybrid Magnetic Attitude Controller for Low Earth Orbit Satellites using the Time-varying Linear Quadratic Regulator. [Internet] [Masters thesis]. University of Toronto; 2009. [cited 2019 Jun 20]. Available from: http://hdl.handle.net/1807/17711.

Council of Science Editors:

Seth N. Hybrid Magnetic Attitude Controller for Low Earth Orbit Satellites using the Time-varying Linear Quadratic Regulator. [Masters Thesis]. University of Toronto; 2009. Available from: http://hdl.handle.net/1807/17711

4. 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 June 20, 2019. 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. 20 Jun 2019.

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 2019 Jun 20]. 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

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

Degree: 2013, University of Toronto

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

►

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 June 20, 2019. http://hdl.handle.net/1807/35117.

MLA Handbook (7^th Edition):

Dutia, Jiten. “Magnetic Attitude Control of Microsatellites In Geocentric Orbits.” 2013. Web. 20 Jun 2019.

Vancouver:

Dutia J. Magnetic Attitude Control of Microsatellites In Geocentric Orbits. [Internet] [Masters thesis]. University of Toronto; 2013. [cited 2019 Jun 20]. 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

6. 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

►

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 June 20, 2019. 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. 20 Jun 2019.

Vancouver:

Ibrahim N. Attitude and Orbit Control of Small Satellites for Autonomous Terrestrial Target Tracking. [Internet] [Masters thesis]. University of Toronto; 2013. [cited 2019 Jun 20]. 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 Toronto

7. 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 June 20, 2019. http://hdl.handle.net/1807/79471.

MLA Handbook (7^th Edition):

Serpelloni, Edoardo. “Bang-Bang Practical Stabilization of Rigid Bodies.” 2017. Web. 20 Jun 2019.

Vancouver:

Serpelloni E. Bang-Bang Practical Stabilization of Rigid Bodies. [Internet] [Doctoral dissertation]. University of Toronto; 2017. [cited 2019 Jun 20]. 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

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

Degree: PhD, Aerospace and Ocean 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 June 20, 2019. 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. 20 Jun 2019.

Vancouver:

VanDyke MC. Constant Orbital Momentum Equilibrium Trajectories of a Gyrostat-Satellite. [Internet] [Doctoral dissertation]. Virginia Tech; 2014. [cited 2019 Jun 20]. 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

University of Toronto

9. 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 June 20, 2019. 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. 20 Jun 2019.

Vancouver:

Johnston-Lemke B. High Performance Attitude Determination and Control for Nanosatellite Missions. [Internet] [Masters thesis]. University of Toronto; 2011. [cited 2019 Jun 20]. 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

10. 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 June 20, 2019. 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. 20 Jun 2019.

Vancouver:

Findlay E. Investigation of Active Vibration Suppression of a Flexible Satellite using Magnetic Attitude Control. [Internet] [Masters thesis]. University of Toronto; 2011. [cited 2019 Jun 20]. 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 Toronto

11. 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 June 20, 2019. 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. 20 Jun 2019.

Vancouver:

Shen Y. Attitude Determination and Control Hardware Acceptance Testing for Next Generation Microsatellites. [Internet] [Masters thesis]. University of Toronto; 2015. [cited 2019 Jun 20]. 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

Utah State University

12. 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 June 20, 2019. 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. 20 Jun 2019.

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 2019 Jun 20]. 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

13. 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 June 20, 2019. 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. 20 Jun 2019.

Vancouver:

Argyle ME. Modeling and Control of a Tailsitter with a Ducted Fan. [Internet] [Doctoral dissertation]. Brigham Young University; 2016. [cited 2019 Jun 20]. 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

University of California – Berkeley

14. 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 June 20, 2019. 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. 20 Jun 2019.

Vancouver:

Wang Y. Attitude Control and Estimation. [Internet] [Thesis]. University of California – Berkeley; 2015. [cited 2019 Jun 20]. 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 Colorado

15. Diaz Ramos, Manuel Francisco. Kinematic Steering Law for Conically-Constrained Torque-Limited Spacecraft Attitude Control.

Degree: MS, 2017, University of Colorado

URL: http://scholar.colorado.edu/asen_gradetds/165

► Orientation constrained attitude control is a requirement in most spacecraft missions. A novel technique for attitude control of a spacecraft subjected to an arbitrary number… (more)

Subjects/Keywords: attitude control; constrained control; Lyapunov theory; Modified Rodrigues Parameters; Aerospace Engineering

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APA (6^th Edition):

Diaz Ramos, M. F. (2017). Kinematic Steering Law for Conically-Constrained Torque-Limited Spacecraft Attitude Control. (Masters Thesis). University of Colorado. Retrieved from http://scholar.colorado.edu/asen_gradetds/165

Chicago Manual of Style (16^th Edition):

Diaz Ramos, Manuel Francisco. “Kinematic Steering Law for Conically-Constrained Torque-Limited Spacecraft Attitude Control.” 2017. Masters Thesis, University of Colorado. Accessed June 20, 2019. http://scholar.colorado.edu/asen_gradetds/165.

MLA Handbook (7^th Edition):

Diaz Ramos, Manuel Francisco. “Kinematic Steering Law for Conically-Constrained Torque-Limited Spacecraft Attitude Control.” 2017. Web. 20 Jun 2019.

Vancouver:

Diaz Ramos MF. Kinematic Steering Law for Conically-Constrained Torque-Limited Spacecraft Attitude Control. [Internet] [Masters thesis]. University of Colorado; 2017. [cited 2019 Jun 20]. Available from: http://scholar.colorado.edu/asen_gradetds/165.

Council of Science Editors:

Diaz Ramos MF. Kinematic Steering Law for Conically-Constrained Torque-Limited Spacecraft Attitude Control. [Masters Thesis]. University of Colorado; 2017. Available from: http://scholar.colorado.edu/asen_gradetds/165

University of Toronto

16. 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 June 20, 2019. 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. 20 Jun 2019.

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 2019 Jun 20]. 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

Delft University of Technology

17. Habets, J.M.G. 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..

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

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

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. “Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft:.” 2015. Masters Thesis, Delft University of Technology. Accessed June 20, 2019. http://resolver.tudelft.nl/uuid:f1bc854a-36f9-4401-a892-2313e4022ea8.

MLA Handbook (7^th Edition):

Habets, J M G. “Evolving Systems Approach to the Attitude Control of a Large-Space-Debris Removal Spacecraft:.” 2015. Web. 20 Jun 2019.

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 2019 Jun 20]. 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

Luleå University of Technology

18. 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 June 20, 2019. 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. 20 Jun 2019.

Vancouver:

Cypriano LA. Study and Design of an Adaptive Control Law for Spacecraft Attitude Control. [Internet] [Thesis]. Luleå University of Technology; 2014. [cited 2019 Jun 20]. 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

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

Degree: 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

3 more images…

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APA (6^th Edition):

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

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):

Yang, Sungpil. “Robustness properties of quaternion-based attitude control systems.” 2016. Thesis, University of Texas – Austin. Accessed June 20, 2019. http://hdl.handle.net/2152/38095.

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

MLA Handbook (7^th Edition):

Yang, Sungpil. “Robustness properties of quaternion-based attitude control systems.” 2016. Web. 20 Jun 2019.

Vancouver:

Yang S. Robustness properties of quaternion-based attitude control systems. [Internet] [Thesis]. University of Texas – Austin; 2016. [cited 2019 Jun 20]. Available from: http://hdl.handle.net/2152/38095.

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

Council of Science Editors:

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

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

University of Connecticut

20. 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 June 20, 2019. https://opencommons.uconn.edu/gs_theses/549.

MLA Handbook (7^th Edition):

Liu, Yuqian. “Control and Navigation of Autonomous Underwater Vehicles.” 2014. Web. 20 Jun 2019.

Vancouver:

Liu Y. Control and Navigation of Autonomous Underwater Vehicles. [Internet] [Masters thesis]. University of Connecticut; 2014. [cited 2019 Jun 20]. 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

21. 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 June 20, 2019. 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. 20 Jun 2019.

Vancouver:

Svedevall A. Development of attitude determination sensors for miniature satellites. [Internet] [Thesis]. Luleå University of Technology; 2014. [cited 2019 Jun 20]. 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 Toronto

22. 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 June 20, 2019. http://hdl.handle.net/1807/42688.

MLA Handbook (7^th Edition):

Binette, Mark Richard. “An Investigation of Nonlinear Control of Spacecraft Attitude.” 2013. Web. 20 Jun 2019.

Vancouver:

Binette MR. An Investigation of Nonlinear Control of Spacecraft Attitude. [Internet] [Masters thesis]. University of Toronto; 2013. [cited 2019 Jun 20]. 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

23. Fragoso Trigo, G. 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. Advisors/Committee Members: Chu, Q.P..

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. “Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs:.” 2011. Masters Thesis, Delft University of Technology. Accessed June 20, 2019. http://resolver.tudelft.nl/uuid:ac9a05df-7c33-4dae-9d34-5e667e6168ce.

MLA Handbook (7^th Edition):

Fragoso Trigo, G. “Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs:.” 2011. Web. 20 Jun 2019.

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 2019 Jun 20]. 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

24. 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 (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 June 20, 2019. 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. 20 Jun 2019.

Vancouver:

Dando AJ. Robust adaptive control of rigid spacecraft attitude maneuvers. [Internet] [Thesis]. Queensland University of Technology; 2008. [cited 2019 Jun 20]. 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

University of Toronto

25. Stellini, Julian. Magnetic Attitude Control For Spacecraft with Flexible Appendages.

Degree: 2012, University of Toronto

URL: http://hdl.handle.net/1807/33545

►

The design of an attitude control system for a flexible spacecraft using magnetic actuation is considered. The nonlinear, linear, and modal equations of motion are… (more)

Subjects/Keywords: aerospace; engineering; magnetic attitude control; attitude control; flexible spacecraft; spacecraft attitude control; control of flexible appendages; spacecraft control; magnetic control; geomagnetic field; aerospace control; aerospace engineering; spacecraft dynamics; dynamics and control; dynamics; control; 0538

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

APA (6^th Edition):

Stellini, J. (2012). Magnetic Attitude Control For Spacecraft with Flexible Appendages. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/33545

Chicago Manual of Style (16^th Edition):

Stellini, Julian. “Magnetic Attitude Control For Spacecraft with Flexible Appendages.” 2012. Masters Thesis, University of Toronto. Accessed June 20, 2019. http://hdl.handle.net/1807/33545.

MLA Handbook (7^th Edition):

Stellini, Julian. “Magnetic Attitude Control For Spacecraft with Flexible Appendages.” 2012. Web. 20 Jun 2019.

Vancouver:

Stellini J. Magnetic Attitude Control For Spacecraft with Flexible Appendages. [Internet] [Masters thesis]. University of Toronto; 2012. [cited 2019 Jun 20]. Available from: http://hdl.handle.net/1807/33545.

Council of Science Editors:

Stellini J. Magnetic Attitude Control For Spacecraft with Flexible Appendages. [Masters Thesis]. University of Toronto; 2012. Available from: http://hdl.handle.net/1807/33545

Massey University

26. Makarov, Kirill. Design of attitude determination and control system for KIWISAT amateur satellite.

Degree: Masters of Engineering, Mechatronics, 2015, Massey University

URL: http://hdl.handle.net/10179/6857

► This thesis is to present the design of “ADAC” system for “KiwiSat” cube satellite. An array of sensors were used: CMOS low resolution camera, sun… (more)

Subjects/Keywords: Artificial satellites; Attitude control systems; Attitude determination and control system (ADAC); KiwiSat; Sensors; Research Subject Categories::TECHNOLOGY::Other technology::Space engineering

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

APA (6^th Edition):

Makarov, K. (2015). Design of attitude determination and control system for KIWISAT amateur satellite. (Masters Thesis). Massey University. Retrieved from http://hdl.handle.net/10179/6857

Chicago Manual of Style (16^th Edition):

Makarov, Kirill. “Design of attitude determination and control system for KIWISAT amateur satellite.” 2015. Masters Thesis, Massey University. Accessed June 20, 2019. http://hdl.handle.net/10179/6857.

MLA Handbook (7^th Edition):

Makarov, Kirill. “Design of attitude determination and control system for KIWISAT amateur satellite.” 2015. Web. 20 Jun 2019.

Vancouver:

Makarov K. Design of attitude determination and control system for KIWISAT amateur satellite. [Internet] [Masters thesis]. Massey University; 2015. [cited 2019 Jun 20]. Available from: http://hdl.handle.net/10179/6857.

Council of Science Editors:

Makarov K. Design of attitude determination and control system for KIWISAT amateur satellite. [Masters Thesis]. Massey University; 2015. Available from: http://hdl.handle.net/10179/6857

University of Florida

27. Leve, Frederick. Development of Spacecraft Orientation Buoyancy Experimental Kiosk.

Degree: MS, Aerospace Engineering - Mechanical and Aerospace Engineering, 2009, University of Florida

URL: http://ufdc.ufl.edu/UFE0022280

► DEVELOPMENT OF THE SPACECRAFT ORIENTATION BUOYANCY EXPERIMENTAL KIOSK TESTBED Most satellites are unique and therefore usually take 10 to 15 years to design, fabricate, test,… (more)

▼ DEVELOPMENT OF THE SPACECRAFT ORIENTATION BUOYANCY EXPERIMENTAL KIOSK TESTBED Most satellites are unique and therefore usually take 10 to 15 years to design, fabricate, test, and finally launch. To expedite future advances in space technology, setting standards in terms of ?black-boxed? subsystems and interfaces, drastically reduces the time and long term costs needed to complete these tasks. What is meant by ?black-boxed? is a stand alone subsystem that is adaptable enough to work with any other subsystems without alteration. Government organizations such as the Department of Defense?s (DoD?s) Operationally Responsive Space (ORS) office take these tasks into consideration and look to change this pattern by expediting the processes of design, fabrication, test, evaluation, and launch. To accomplish these tasks, smallsats which range from 1 to 1000 kg in mass, are considered for their cheaper platforms and launch costs. With utilization of smallsats of the pico- (0.1-1 kg), nano- (1 to 10 kg), and micro-classes (10-100 kg) for space missions, obstacles occur in terms of power, mass, and volume constraints. Many of these same smallsats obstacles relate to the attitude control system (ACS). Despite these obstacles for many space missions, small satellites must be held to the same pointing requirements as their larger counterparts to be of use. To compensate for these obstacles while maintaining close pointing requirements, innovations in attitude control actuators and determination sensors that satisfy these constraints need to be developed. An excellent choice for attitude control actuators of smallsats are those of the flywheel sort known as zero-momentum and momentum bias actuators. These actuators have the ability to perform precision attitude maneuvers without use of propellant. There are two classes of flywheel attitude control actuators that are used in satellites, reaction/momentum wheels (RWs/MWs) and control moment gyroscopes (CMGs). Due to the scarcity of CMGs available for small satellites below the micro-class, RWs are presently utilized. An analysis completed in this thesis shows that although the current state-of-the-art CMGs are too massive to fit inside smallsats, the performance relationships in terms of output torque per mass and input power are more favorable than that for RWs. This analysis is an additional motivation for the research in this thesis, which is carried out on the premise that an ACS consisting of single-gimbal control moment gyroscopes (SGCMGs) can meet the performance requirements providing rapid-retargeting and precision-pointing (R2P2) for smallsats while enduring their power, mass, and volume constraints. To further test this premise the topic of this thesis is the development of a ground based SGCMG testbed known as Spacecraft Orientation Buoyancy Experimental Kiosk (SOBEK) was developed to validate the utility of using SGCMGs for smallsat attitude control. The thesis justifies the reasons for using SGCMGs on SOBEK, discusses the spacecraft and actuator dynamics and kinematics… Advisors/Committee Members: Fitz-Coy, Norman G. (committee chair), Wiens, Gloria J. (committee member), Dixon, Warren E. (committee member).

Subjects/Keywords: Angular momentum; Artificial satellites; Attitude control; Flywheels; Gimbals; Momentum; Quaternions; Simulations; Spacecraft; Torque; attitude, control, reaction, satellite, spacecraft, testbed

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

APA (6^th Edition):

Leve, F. (2009). Development of Spacecraft Orientation Buoyancy Experimental Kiosk. (Masters Thesis). University of Florida. Retrieved from http://ufdc.ufl.edu/UFE0022280

Chicago Manual of Style (16^th Edition):

Leve, Frederick. “Development of Spacecraft Orientation Buoyancy Experimental Kiosk.” 2009. Masters Thesis, University of Florida. Accessed June 20, 2019. http://ufdc.ufl.edu/UFE0022280.

MLA Handbook (7^th Edition):

Leve, Frederick. “Development of Spacecraft Orientation Buoyancy Experimental Kiosk.” 2009. Web. 20 Jun 2019.

Vancouver:

Leve F. Development of Spacecraft Orientation Buoyancy Experimental Kiosk. [Internet] [Masters thesis]. University of Florida; 2009. [cited 2019 Jun 20]. Available from: http://ufdc.ufl.edu/UFE0022280.

Council of Science Editors:

Leve F. Development of Spacecraft Orientation Buoyancy Experimental Kiosk. [Masters Thesis]. University of Florida; 2009. Available from: http://ufdc.ufl.edu/UFE0022280

Indian Institute of Science

28. Vivek Chandran, K P. Development Of Gyroless Attitude And Angular Rate Estimation For Satellites.

Degree: 2009, Indian Institute of Science

URL: http://hdl.handle.net/2005/1121

► Studies aimed at the development of indigenous low cost star tracker and gyroless attitude and angular rate estimation is presented in the thesis. This study… (more)

▼ Studies aimed at the development of indigenous low cost star tracker and gyroless attitude and angular rate estimation is presented in the thesis. This study is required for the realization of low cost micro satellites. A target specification of determining the attitude with accuracy (3σ) of 0.05 degrees and attitude rate with accuracy (3σ) in the range of 50rad/sec at a rate of 10 samples/second in all the axes is set as a goal for the study. Different sensor arrays available in the market are evaluated on the basis of their noise characteristics, resolution of the analog-to-digital converter (ADC) present and ability to work in low light conditions, for possible use in the hardware realization of star tracker. STAR1000 APS CMOS array, manufactured by Cypress Semiconductors, qualified these performance criteria, is used for the simulation study. An algorithm is presented for scanning the sensor array, detection of star image and retrieving the information concerning the photoelectron counts corresponding to a star image. The exact designation of the center of the star image becomes crucial as it has direct implications on the accuracy of the estimated attitude. Various algorithms concerning the centroid estimation of a defocused star image on the sensor array to subpixel accuracy are studied and Gaussian Weighed Center of Gravity algorithm is adapted with some modifications and an accuracy of 0.039 pixels is obtained in both horizontal and vertical direction of the array. A one-to-one relationship is established between the stars obtained in the field-of-view (FOV) of the star tracker with the stars present in the star catalog resident in the star tracker through star identification algorithm. A star identification algorithm which relies on the interstar angles and brightness of the stars is developed in this thesis. The interstar angles of the stars visible in the FOV of the star sensor is recorded, compared with the inter-star angles made by the stars selected in the catalog, based on initial brightness match with stars formed on image plane. After identification at the initial epoch, consequent instants can drive information from the previous matches so as to decrease the computational complexity and storage requirement for the subsequent instants. The memory constraints and computational overhead on the processor and the dynamic range of the image detector used in the star tracker are the limiting factors. The stars thus identified with the stars in the catalog are used for the estimation of attitude. A point solution to the attitude estimation problem is computed using a least square based algorithm called ESOQ-2. The algorithm for centroiding of star images and ESOQ-2 for finding the point solution satellite attitude is coded and tested on Da Vinci based emulator. This exercise shows that it is possible to implement above algorithm for real time operations. Estimation of attitude at a given epoch using algorithms like ESOQ-2 does not minimize the noise and error covariance as the attitude estimated at each… Advisors/Committee Members: Bhat, M Seetharama.

Subjects/Keywords: Gyroless Attitude; Satellites - Angular Rate; Star Trackers; Satellites - Attitude Estimation; Star Sensors; Stars - Catalogs; Satellite Attitude Control; Gyroless Satellite Attitude Estimation; Angular Rate Estimation; Micro-Satellites; Astronautics

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

APA (6^th Edition):

Vivek Chandran, K. P. (2009). Development Of Gyroless Attitude And Angular Rate Estimation For Satellites. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/1121

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):

Vivek Chandran, K P. “Development Of Gyroless Attitude And Angular Rate Estimation For Satellites.” 2009. Thesis, Indian Institute of Science. Accessed June 20, 2019. http://hdl.handle.net/2005/1121.

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

MLA Handbook (7^th Edition):

Vivek Chandran, K P. “Development Of Gyroless Attitude And Angular Rate Estimation For Satellites.” 2009. Web. 20 Jun 2019.

Vancouver:

Vivek Chandran KP. Development Of Gyroless Attitude And Angular Rate Estimation For Satellites. [Internet] [Thesis]. Indian Institute of Science; 2009. [cited 2019 Jun 20]. Available from: http://hdl.handle.net/2005/1121.

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

Council of Science Editors:

Vivek Chandran KP. Development Of Gyroless Attitude And Angular Rate Estimation For Satellites. [Thesis]. Indian Institute of Science; 2009. Available from: http://hdl.handle.net/2005/1121

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

University of Toronto

29. Lukaszynski, Pawel. Attitude Control Hardware and Software for Nanosatellites.

Degree: 2013, University of Toronto

URL: http://hdl.handle.net/1807/43095

►

The analysis, verification and emulation of attitude control hardware for nanosatellite spacecraft is described. The overall focus is on hardware that pertains to a multitude… (more)

Subjects/Keywords: nanosatellites; reaction wheel; hysteresis rod; acceptance test; hardware emulation in software; attitude determination and control; attitude determination; attitude control; torque jitter; 0538

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

APA (6^th Edition):

Lukaszynski, P. (2013). Attitude Control Hardware and Software for Nanosatellites. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/43095

Chicago Manual of Style (16^th Edition):

Lukaszynski, Pawel. “Attitude Control Hardware and Software for Nanosatellites.” 2013. Masters Thesis, University of Toronto. Accessed June 20, 2019. http://hdl.handle.net/1807/43095.

MLA Handbook (7^th Edition):

Lukaszynski, Pawel. “Attitude Control Hardware and Software for Nanosatellites.” 2013. Web. 20 Jun 2019.

Vancouver:

Lukaszynski P. Attitude Control Hardware and Software for Nanosatellites. [Internet] [Masters thesis]. University of Toronto; 2013. [cited 2019 Jun 20]. Available from: http://hdl.handle.net/1807/43095.

Council of Science Editors:

Lukaszynski P. Attitude Control Hardware and Software for Nanosatellites. [Masters Thesis]. University of Toronto; 2013. Available from: http://hdl.handle.net/1807/43095

University of Colorado

30. Blenden, Robin M. Regenerative Power Optimal Reaction Wheel Attitude Control.

Degree: MS, Aerospace Engineering Sciences, 2011, University of Colorado

URL: http://scholar.colorado.edu/asen_gradetds/21

► The thesis work develops an instantaneous power optimal attitude control for a spacecraft utilizing an integrated reaction wheel - flywheel system allowing for energy… (more)

Subjects/Keywords: Attitude Control; Power Optimal; Reaction Wheel; Aerospace Engineering; Space Vehicles

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

APA (6^th Edition):

Blenden, R. M. (2011). Regenerative Power Optimal Reaction Wheel Attitude Control. (Masters Thesis). University of Colorado. Retrieved from http://scholar.colorado.edu/asen_gradetds/21

Chicago Manual of Style (16^th Edition):

Blenden, Robin M. “Regenerative Power Optimal Reaction Wheel Attitude Control.” 2011. Masters Thesis, University of Colorado. Accessed June 20, 2019. http://scholar.colorado.edu/asen_gradetds/21.

MLA Handbook (7^th Edition):

Blenden, Robin M. “Regenerative Power Optimal Reaction Wheel Attitude Control.” 2011. Web. 20 Jun 2019.

Vancouver:

Blenden RM. Regenerative Power Optimal Reaction Wheel Attitude Control. [Internet] [Masters thesis]. University of Colorado; 2011. [cited 2019 Jun 20]. Available from: http://scholar.colorado.edu/asen_gradetds/21.

Council of Science Editors:

Blenden RM. Regenerative Power Optimal Reaction Wheel Attitude Control. [Masters Thesis]. University of Colorado; 2011. Available from: http://scholar.colorado.edu/asen_gradetds/21

Open Access Theses and Dissertations