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You searched for subject:(Attitude Control). Showing records 1 – 30 of 320 total matches.

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Lehigh University

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

Degree: MS, Mechanical Engineering, 2016, Lehigh University

 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 (6th 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 (16th 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 (7th 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

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 (6th 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 (16th 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 (7th 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

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 (6th 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 (16th 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 (7th 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

 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 (6th 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 (16th 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 (7th 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

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 (6th 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 (16th 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 (7th 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

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 (6th 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 (16th 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 (7th 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

 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)

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

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APA (6th 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 (16th 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 (7th 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

 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)

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

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APA (6th 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 (16th 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 (7th 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

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 (6th 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 (16th 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 (7th 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

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 (6th 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 (16th 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 (7th 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

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 (6th 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 (16th 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 (7th 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

  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 (6th 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 (16th 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 (7th 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

  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)

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

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APA (6th 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 (16th 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 (7th 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

 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)

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

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APA (6th 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 (16th 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 (7th 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

 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 (6th 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 (16th 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 (7th 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

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 (6th 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 (16th 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 (7th 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

 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)

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

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APA (6th 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 (16th 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 (7th 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

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

APA (6th 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 (16th 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 (7th 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

 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)

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

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APA (6th 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 (16th 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 (7th 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

  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 (6th 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 (16th 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 (7th 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

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

APA (6th 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 (16th 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 (7th 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

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

APA (6th 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 (16th 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 (7th 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

 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)

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

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APA (6th 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 (16th 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 (7th 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

 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)

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 (6th 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 (16th 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 (7th 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

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 (6th 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 (16th 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 (7th 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

 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 (6th 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 (16th 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 (7th 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

 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)

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 (6th 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 (16th 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 (7th 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

 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)

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 (6th 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 (16th 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 (7th 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

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 (6th 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 (16th 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 (7th 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

  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 (6th 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 (16th 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 (7th 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

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