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You searched for subject:(Spacecraft dynamics). Showing records 1 – 30 of 41 total matches.

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University of Southern California

1. Reddy, Shalini A. Control of spacecraft with flexible structures using pulse-modulated thrusters.

Degree: PhD, Mechanical Engineering, 2012, University of Southern California

 A methodology for the design of robust control systems for flexible spacecraft undergoing a large angle maneuver using pulse-modulated thrusters is proposed. The need for… (more)

Subjects/Keywords: spacecraft; dynamics; control

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

APA (6th Edition):

Reddy, S. A. (2012). Control of spacecraft with flexible structures using pulse-modulated thrusters. (Doctoral Dissertation). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/84663/rec/1638

Chicago Manual of Style (16th Edition):

Reddy, Shalini A. “Control of spacecraft with flexible structures using pulse-modulated thrusters.” 2012. Doctoral Dissertation, University of Southern California. Accessed March 21, 2019. http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/84663/rec/1638.

MLA Handbook (7th Edition):

Reddy, Shalini A. “Control of spacecraft with flexible structures using pulse-modulated thrusters.” 2012. Web. 21 Mar 2019.

Vancouver:

Reddy SA. Control of spacecraft with flexible structures using pulse-modulated thrusters. [Internet] [Doctoral dissertation]. University of Southern California; 2012. [cited 2019 Mar 21]. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/84663/rec/1638.

Council of Science Editors:

Reddy SA. Control of spacecraft with flexible structures using pulse-modulated thrusters. [Doctoral Dissertation]. University of Southern California; 2012. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/84663/rec/1638


Cornell University

2. Manchester, Zachary. Centimeter-Scale Spacecraft: Design, Fabrication, And Deployment .

Degree: 2015, Cornell University

 The rise of the consumer electronics industry has led to a profusion of ever smaller, cheaper, and more capable devices, from sensors to computers to… (more)

Subjects/Keywords: Small Spacecraft; Spacecraft Dynamics; Space Systems

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APA (6th Edition):

Manchester, Z. (2015). Centimeter-Scale Spacecraft: Design, Fabrication, And Deployment . (Thesis). Cornell University. Retrieved from http://hdl.handle.net/1813/41055

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):

Manchester, Zachary. “Centimeter-Scale Spacecraft: Design, Fabrication, And Deployment .” 2015. Thesis, Cornell University. Accessed March 21, 2019. http://hdl.handle.net/1813/41055.

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

MLA Handbook (7th Edition):

Manchester, Zachary. “Centimeter-Scale Spacecraft: Design, Fabrication, And Deployment .” 2015. Web. 21 Mar 2019.

Vancouver:

Manchester Z. Centimeter-Scale Spacecraft: Design, Fabrication, And Deployment . [Internet] [Thesis]. Cornell University; 2015. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/1813/41055.

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

Council of Science Editors:

Manchester Z. Centimeter-Scale Spacecraft: Design, Fabrication, And Deployment . [Thesis]. Cornell University; 2015. Available from: http://hdl.handle.net/1813/41055

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


Cornell University

3. Zeledon, Rodrigo. Electrolysis Propulsion For Small-Scale Spacecraft .

Degree: 2015, Cornell University

 In the past decade, CubeSats have revolutionized small spacecraft missions. These miniature satellites began as educational projects but have lowered the bar for access to… (more)

Subjects/Keywords: Electrolysis propulsion; Small satellites; Spacecraft dynamics

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APA (6th Edition):

Zeledon, R. (2015). Electrolysis Propulsion For Small-Scale Spacecraft . (Thesis). Cornell University. Retrieved from http://hdl.handle.net/1813/40701

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):

Zeledon, Rodrigo. “Electrolysis Propulsion For Small-Scale Spacecraft .” 2015. Thesis, Cornell University. Accessed March 21, 2019. http://hdl.handle.net/1813/40701.

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

MLA Handbook (7th Edition):

Zeledon, Rodrigo. “Electrolysis Propulsion For Small-Scale Spacecraft .” 2015. Web. 21 Mar 2019.

Vancouver:

Zeledon R. Electrolysis Propulsion For Small-Scale Spacecraft . [Internet] [Thesis]. Cornell University; 2015. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/1813/40701.

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

Council of Science Editors:

Zeledon R. Electrolysis Propulsion For Small-Scale Spacecraft . [Thesis]. Cornell University; 2015. Available from: http://hdl.handle.net/1813/40701

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


University of Illinois – Urbana-Champaign

4. Pukniel, Andrzej. The dynamics and control of the CubeSail mission???A solar sailing demonstration.

Degree: PhD, 4048, 2011, University of Illinois – Urbana-Champaign

 The proposed study addresses two issues related to the slow emergence of solar sailing as a viable space propulsion method. The low technology readiness level… (more)

Subjects/Keywords: Solar Sailing; spacecraft dynamics; space tether

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APA (6th Edition):

Pukniel, A. (2011). The dynamics and control of the CubeSail mission???A solar sailing demonstration. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/18320

Chicago Manual of Style (16th Edition):

Pukniel, Andrzej. “The dynamics and control of the CubeSail mission???A solar sailing demonstration.” 2011. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed March 21, 2019. http://hdl.handle.net/2142/18320.

MLA Handbook (7th Edition):

Pukniel, Andrzej. “The dynamics and control of the CubeSail mission???A solar sailing demonstration.” 2011. Web. 21 Mar 2019.

Vancouver:

Pukniel A. The dynamics and control of the CubeSail mission???A solar sailing demonstration. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2011. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/2142/18320.

Council of Science Editors:

Pukniel A. The dynamics and control of the CubeSail mission???A solar sailing demonstration. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2011. Available from: http://hdl.handle.net/2142/18320


University of Southern California

5. Basilio, Ralph Ramos. Controlled and uncontrolled motion in the circular, restricted three-body problem: dynamically-natural spacecraft formations.

Degree: PhD, Aerospace Engineering, 2007, University of Southern California

Spacecraft formation flying involves operating multiple spacecraft in a pre-determined geometrical shape such that the configuration yields both individual and system benefits. One example is… (more)

Subjects/Keywords: dynamics; spacecraft; formations

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APA (6th Edition):

Basilio, R. R. (2007). Controlled and uncontrolled motion in the circular, restricted three-body problem: dynamically-natural spacecraft formations. (Doctoral Dissertation). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/500238/rec/1641

Chicago Manual of Style (16th Edition):

Basilio, Ralph Ramos. “Controlled and uncontrolled motion in the circular, restricted three-body problem: dynamically-natural spacecraft formations.” 2007. Doctoral Dissertation, University of Southern California. Accessed March 21, 2019. http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/500238/rec/1641.

MLA Handbook (7th Edition):

Basilio, Ralph Ramos. “Controlled and uncontrolled motion in the circular, restricted three-body problem: dynamically-natural spacecraft formations.” 2007. Web. 21 Mar 2019.

Vancouver:

Basilio RR. Controlled and uncontrolled motion in the circular, restricted three-body problem: dynamically-natural spacecraft formations. [Internet] [Doctoral dissertation]. University of Southern California; 2007. [cited 2019 Mar 21]. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/500238/rec/1641.

Council of Science Editors:

Basilio RR. Controlled and uncontrolled motion in the circular, restricted three-body problem: dynamically-natural spacecraft formations. [Doctoral Dissertation]. University of Southern California; 2007. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/500238/rec/1641


University of Michigan

6. Hudson, Jennifer S. Reduction of Low-Thrust Continuous Controls for Trajectory Dynamics and Orbital Targeting.

Degree: PhD, Aerospace Engineering, 2010, University of Michigan

 A novel method to evaluate the trajectory dynamics of low-thrust spacecraft is developed. Using a two-body Newtonian model, the spacecraft thrust vector components are represented… (more)

Subjects/Keywords: Low-thrust Spacecraft Control; Low-thrust Spacecraft Trajectory Dynamics; Orbital Targeting; Aerospace Engineering; Engineering

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APA (6th Edition):

Hudson, J. S. (2010). Reduction of Low-Thrust Continuous Controls for Trajectory Dynamics and Orbital Targeting. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/78860

Chicago Manual of Style (16th Edition):

Hudson, Jennifer S. “Reduction of Low-Thrust Continuous Controls for Trajectory Dynamics and Orbital Targeting.” 2010. Doctoral Dissertation, University of Michigan. Accessed March 21, 2019. http://hdl.handle.net/2027.42/78860.

MLA Handbook (7th Edition):

Hudson, Jennifer S. “Reduction of Low-Thrust Continuous Controls for Trajectory Dynamics and Orbital Targeting.” 2010. Web. 21 Mar 2019.

Vancouver:

Hudson JS. Reduction of Low-Thrust Continuous Controls for Trajectory Dynamics and Orbital Targeting. [Internet] [Doctoral dissertation]. University of Michigan; 2010. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/2027.42/78860.

Council of Science Editors:

Hudson JS. Reduction of Low-Thrust Continuous Controls for Trajectory Dynamics and Orbital Targeting. [Doctoral Dissertation]. University of Michigan; 2010. Available from: http://hdl.handle.net/2027.42/78860


Cal Poly

7. Downs, Matthew C. Adaptive Control Applied to the Cal Poly Spacecraft Attitude Dynamics Simulator.

Degree: MS, Aerospace Engineering, 2010, Cal Poly

 The goal of this thesis is to use the Cal Poly Spacecraft Attitude Dynamics Simulator to provide proof of concept of two adaptive control theories… (more)

Subjects/Keywords: Reaction Wheel Pyramid; Adaptive Control; PRWP; Spacecraft; Spacecraft Control; Acoustics, Dynamics, and Controls; Astrodynamics; Navigation, Guidance, Control and Dynamics; Space Vehicles

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APA (6th Edition):

Downs, M. C. (2010). Adaptive Control Applied to the Cal Poly Spacecraft Attitude Dynamics Simulator. (Masters Thesis). Cal Poly. Retrieved from http://digitalcommons.calpoly.edu/theses/231 ; 10.15368/theses.2010.6

Chicago Manual of Style (16th Edition):

Downs, Matthew C. “Adaptive Control Applied to the Cal Poly Spacecraft Attitude Dynamics Simulator.” 2010. Masters Thesis, Cal Poly. Accessed March 21, 2019. http://digitalcommons.calpoly.edu/theses/231 ; 10.15368/theses.2010.6.

MLA Handbook (7th Edition):

Downs, Matthew C. “Adaptive Control Applied to the Cal Poly Spacecraft Attitude Dynamics Simulator.” 2010. Web. 21 Mar 2019.

Vancouver:

Downs MC. Adaptive Control Applied to the Cal Poly Spacecraft Attitude Dynamics Simulator. [Internet] [Masters thesis]. Cal Poly; 2010. [cited 2019 Mar 21]. Available from: http://digitalcommons.calpoly.edu/theses/231 ; 10.15368/theses.2010.6.

Council of Science Editors:

Downs MC. Adaptive Control Applied to the Cal Poly Spacecraft Attitude Dynamics Simulator. [Masters Thesis]. Cal Poly; 2010. Available from: http://digitalcommons.calpoly.edu/theses/231 ; 10.15368/theses.2010.6


Cal Poly

8. KATO, TOMOYUKI. Modification of the Cal Poly Spacecraft Simulator System for Robust Control Law Verification.

Degree: MS, Aerospace Engineering, 2014, Cal Poly

  The Cal Poly Spacecraft Dynamics Simulator, also known as the Pyramidal Reaction Wheel Platform (PRWP), is an air-bearing four reaction wheel spacecraft simulator designed… (more)

Subjects/Keywords: Spacecraft; Simulator; Adaptive; Control; Robust; Navigation, Guidance, Control and Dynamics

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APA (6th Edition):

KATO, T. (2014). Modification of the Cal Poly Spacecraft Simulator System for Robust Control Law Verification. (Masters Thesis). Cal Poly. Retrieved from http://digitalcommons.calpoly.edu/theses/1201 ; 10.15368/theses.2014.48

Chicago Manual of Style (16th Edition):

KATO, TOMOYUKI. “Modification of the Cal Poly Spacecraft Simulator System for Robust Control Law Verification.” 2014. Masters Thesis, Cal Poly. Accessed March 21, 2019. http://digitalcommons.calpoly.edu/theses/1201 ; 10.15368/theses.2014.48.

MLA Handbook (7th Edition):

KATO, TOMOYUKI. “Modification of the Cal Poly Spacecraft Simulator System for Robust Control Law Verification.” 2014. Web. 21 Mar 2019.

Vancouver:

KATO T. Modification of the Cal Poly Spacecraft Simulator System for Robust Control Law Verification. [Internet] [Masters thesis]. Cal Poly; 2014. [cited 2019 Mar 21]. Available from: http://digitalcommons.calpoly.edu/theses/1201 ; 10.15368/theses.2014.48.

Council of Science Editors:

KATO T. Modification of the Cal Poly Spacecraft Simulator System for Robust Control Law Verification. [Masters Thesis]. Cal Poly; 2014. Available from: http://digitalcommons.calpoly.edu/theses/1201 ; 10.15368/theses.2014.48


Cornell University

9. Streetman, Brett. Lorentz-Augmented Orbit Dynamics and Mission Design .

Degree: 2008, Cornell University

 The concept of Lorentz Augmented Orbits (LAO) is explored and developed. A spacecraft with a controlled net electrostatic charge moves in a planetary magnetic field.… (more)

Subjects/Keywords: Orbit Dynamics; Spacecraft Mission Design; Lorentz Force; Propellantless propulsion

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APA (6th Edition):

Streetman, B. (2008). Lorentz-Augmented Orbit Dynamics and Mission Design . (Thesis). Cornell University. Retrieved from http://hdl.handle.net/1813/11068

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):

Streetman, Brett. “Lorentz-Augmented Orbit Dynamics and Mission Design .” 2008. Thesis, Cornell University. Accessed March 21, 2019. http://hdl.handle.net/1813/11068.

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

MLA Handbook (7th Edition):

Streetman, Brett. “Lorentz-Augmented Orbit Dynamics and Mission Design .” 2008. Web. 21 Mar 2019.

Vancouver:

Streetman B. Lorentz-Augmented Orbit Dynamics and Mission Design . [Internet] [Thesis]. Cornell University; 2008. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/1813/11068.

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

Council of Science Editors:

Streetman B. Lorentz-Augmented Orbit Dynamics and Mission Design . [Thesis]. Cornell University; 2008. Available from: http://hdl.handle.net/1813/11068

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

10. Hashem, Chris. Modified Hybrid Modeling Technique for Flexible Spin-Stabilized Spacecraft Applied to NASA's Magnetospheric MultiScale (MMS) Mission TableSat Generation IC (TableSat IC).

Degree: MS, 2016, University of New Hampshire

 This continued research uses a hybrid dynamic algorithm to mathematically model the attitude dynamics of a flexible spacecraft. While a full finite element model would… (more)

Subjects/Keywords: Control; Dynamics; Flexible; Modeling; Spacecraft; Spin-stabilized; Mechanical engineering

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APA (6th Edition):

Hashem, C. (2016). Modified Hybrid Modeling Technique for Flexible Spin-Stabilized Spacecraft Applied to NASA's Magnetospheric MultiScale (MMS) Mission TableSat Generation IC (TableSat IC). (Thesis). University of New Hampshire. Retrieved from https://scholars.unh.edu/thesis/889

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):

Hashem, Chris. “Modified Hybrid Modeling Technique for Flexible Spin-Stabilized Spacecraft Applied to NASA's Magnetospheric MultiScale (MMS) Mission TableSat Generation IC (TableSat IC).” 2016. Thesis, University of New Hampshire. Accessed March 21, 2019. https://scholars.unh.edu/thesis/889.

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

MLA Handbook (7th Edition):

Hashem, Chris. “Modified Hybrid Modeling Technique for Flexible Spin-Stabilized Spacecraft Applied to NASA's Magnetospheric MultiScale (MMS) Mission TableSat Generation IC (TableSat IC).” 2016. Web. 21 Mar 2019.

Vancouver:

Hashem C. Modified Hybrid Modeling Technique for Flexible Spin-Stabilized Spacecraft Applied to NASA's Magnetospheric MultiScale (MMS) Mission TableSat Generation IC (TableSat IC). [Internet] [Thesis]. University of New Hampshire; 2016. [cited 2019 Mar 21]. Available from: https://scholars.unh.edu/thesis/889.

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

Council of Science Editors:

Hashem C. Modified Hybrid Modeling Technique for Flexible Spin-Stabilized Spacecraft Applied to NASA's Magnetospheric MultiScale (MMS) Mission TableSat Generation IC (TableSat IC). [Thesis]. University of New Hampshire; 2016. Available from: https://scholars.unh.edu/thesis/889

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


North Carolina State University

11. Hays, Scott. A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission.

Degree: MS, Aerospace Engineering, 2007, North Carolina State University

Subjects/Keywords: spacecraft; controls; solar sail; dynamics

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APA (6th Edition):

Hays, S. (2007). A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission. (Thesis). North Carolina State University. Retrieved from http://www.lib.ncsu.edu/resolver/1840.16/604

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):

Hays, Scott. “A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission.” 2007. Thesis, North Carolina State University. Accessed March 21, 2019. http://www.lib.ncsu.edu/resolver/1840.16/604.

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

MLA Handbook (7th Edition):

Hays, Scott. “A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission.” 2007. Web. 21 Mar 2019.

Vancouver:

Hays S. A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission. [Internet] [Thesis]. North Carolina State University; 2007. [cited 2019 Mar 21]. Available from: http://www.lib.ncsu.edu/resolver/1840.16/604.

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

Council of Science Editors:

Hays S. A Study of the Advantages of Using a Tether Ballast Mass as Part of the Control System in a Solar Sail Based Solar Storm Warning Mission. [Thesis]. North Carolina State University; 2007. Available from: http://www.lib.ncsu.edu/resolver/1840.16/604

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

12. 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 March 21, 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. 21 Mar 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 Mar 21]. 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

13. 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 (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 March 21, 2019. http://hdl.handle.net/1807/33545.

MLA Handbook (7th Edition):

Stellini, Julian. “Magnetic Attitude Control For Spacecraft with Flexible Appendages.” 2012. Web. 21 Mar 2019.

Vancouver:

Stellini J. Magnetic Attitude Control For Spacecraft with Flexible Appendages. [Internet] [Masters thesis]. University of Toronto; 2012. [cited 2019 Mar 21]. 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


University of Southern California

14. Schutte, Aaron Dane. On the synthesis of dynamics and control for complex multibody systems.

Degree: PhD, Aerospace Engineering, 2009, University of Southern California

 This dissertation develops in a unified manner a new and simple approach for the modeling and control of complex multibody systems. Complex multibody systems are… (more)

Subjects/Keywords: general constrained systems; multibody dynamics and control; nonlinear systems; quaternions; rigid-body dynamics and control; spacecraft dynamics and control

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APA (6th Edition):

Schutte, A. D. (2009). On the synthesis of dynamics and control for complex multibody systems. (Doctoral Dissertation). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/216110/rec/4547

Chicago Manual of Style (16th Edition):

Schutte, Aaron Dane. “On the synthesis of dynamics and control for complex multibody systems.” 2009. Doctoral Dissertation, University of Southern California. Accessed March 21, 2019. http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/216110/rec/4547.

MLA Handbook (7th Edition):

Schutte, Aaron Dane. “On the synthesis of dynamics and control for complex multibody systems.” 2009. Web. 21 Mar 2019.

Vancouver:

Schutte AD. On the synthesis of dynamics and control for complex multibody systems. [Internet] [Doctoral dissertation]. University of Southern California; 2009. [cited 2019 Mar 21]. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/216110/rec/4547.

Council of Science Editors:

Schutte AD. On the synthesis of dynamics and control for complex multibody systems. [Doctoral Dissertation]. University of Southern California; 2009. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll127/id/216110/rec/4547


University of Colorado

15. Turansky, Craig P. High-Fidelity Dynamic Modeling of Spacecraft in the Continuum–Rarefied Transition Regime.

Degree: PhD, Aerospace Engineering Sciences, 2012, University of Colorado

  The state of the art of spacecraft rarefied aerodynamics seldom accounts for detailed rigid-body dynamics. In part because of computational constraints, simpler models based… (more)

Subjects/Keywords: DSMC; Kinetic Theory; Rarefied Aerodynamics; Rarefied Gas Flows; Satellite Drag; Spacecraft Dynamics; Aerospace Engineering

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APA (6th Edition):

Turansky, C. P. (2012). High-Fidelity Dynamic Modeling of Spacecraft in the Continuum–Rarefied Transition Regime. (Doctoral Dissertation). University of Colorado. Retrieved from http://scholar.colorado.edu/asen_gradetds/53

Chicago Manual of Style (16th Edition):

Turansky, Craig P. “High-Fidelity Dynamic Modeling of Spacecraft in the Continuum–Rarefied Transition Regime.” 2012. Doctoral Dissertation, University of Colorado. Accessed March 21, 2019. http://scholar.colorado.edu/asen_gradetds/53.

MLA Handbook (7th Edition):

Turansky, Craig P. “High-Fidelity Dynamic Modeling of Spacecraft in the Continuum–Rarefied Transition Regime.” 2012. Web. 21 Mar 2019.

Vancouver:

Turansky CP. High-Fidelity Dynamic Modeling of Spacecraft in the Continuum–Rarefied Transition Regime. [Internet] [Doctoral dissertation]. University of Colorado; 2012. [cited 2019 Mar 21]. Available from: http://scholar.colorado.edu/asen_gradetds/53.

Council of Science Editors:

Turansky CP. High-Fidelity Dynamic Modeling of Spacecraft in the Continuum–Rarefied Transition Regime. [Doctoral Dissertation]. University of Colorado; 2012. Available from: http://scholar.colorado.edu/asen_gradetds/53


University of Toronto

16. Magner, Robert. Extending the Capabilities of Terrestrial Target Tracking Spacecraft.

Degree: 2018, University of Toronto

Autonomous terrestrial target tracking is performed by many communications and Earth observation missions to track ground-fixed targets. The DAUNTLESS platform, under development by the Space… (more)

Subjects/Keywords: attitude and orbital control systems; deorbit; microsatellites; spacecraft dynamics; target tracking; trajectory planning; 0538

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APA (6th Edition):

Magner, R. (2018). Extending the Capabilities of Terrestrial Target Tracking Spacecraft. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/91365

Chicago Manual of Style (16th Edition):

Magner, Robert. “Extending the Capabilities of Terrestrial Target Tracking Spacecraft.” 2018. Masters Thesis, University of Toronto. Accessed March 21, 2019. http://hdl.handle.net/1807/91365.

MLA Handbook (7th Edition):

Magner, Robert. “Extending the Capabilities of Terrestrial Target Tracking Spacecraft.” 2018. Web. 21 Mar 2019.

Vancouver:

Magner R. Extending the Capabilities of Terrestrial Target Tracking Spacecraft. [Internet] [Masters thesis]. University of Toronto; 2018. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/1807/91365.

Council of Science Editors:

Magner R. Extending the Capabilities of Terrestrial Target Tracking Spacecraft. [Masters Thesis]. University of Toronto; 2018. Available from: http://hdl.handle.net/1807/91365


University of Michigan

17. Sim, Jaeheon. 3-D Adaptive Eulerian-Lagrangian Method for Multiphase Flows with Spacecraft Applications.

Degree: PhD, Aerospace Engineering, 2010, University of Michigan

 Understanding interfacial dynamics and fluid physics is important in many engineering applications, including spacecraft. Under microgravity, the moving boundaries and associated interfacial transport processes significantly… (more)

Subjects/Keywords: Eulerian-Lagrangian Method; Multiphase Flow; Interfacial Dynamics; Adaptive Grid; Spacecraft Fuel Delivery; Aerospace Engineering; Engineering

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APA (6th Edition):

Sim, J. (2010). 3-D Adaptive Eulerian-Lagrangian Method for Multiphase Flows with Spacecraft Applications. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/78953

Chicago Manual of Style (16th Edition):

Sim, Jaeheon. “3-D Adaptive Eulerian-Lagrangian Method for Multiphase Flows with Spacecraft Applications.” 2010. Doctoral Dissertation, University of Michigan. Accessed March 21, 2019. http://hdl.handle.net/2027.42/78953.

MLA Handbook (7th Edition):

Sim, Jaeheon. “3-D Adaptive Eulerian-Lagrangian Method for Multiphase Flows with Spacecraft Applications.” 2010. Web. 21 Mar 2019.

Vancouver:

Sim J. 3-D Adaptive Eulerian-Lagrangian Method for Multiphase Flows with Spacecraft Applications. [Internet] [Doctoral dissertation]. University of Michigan; 2010. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/2027.42/78953.

Council of Science Editors:

Sim J. 3-D Adaptive Eulerian-Lagrangian Method for Multiphase Flows with Spacecraft Applications. [Doctoral Dissertation]. University of Michigan; 2010. Available from: http://hdl.handle.net/2027.42/78953


University of Colorado

18. Allard, Cody J. Modular Software Architecture for Complex Multi-Body Fully-Coupled Spacecraft Dynamics.

Degree: PhD, 2018, University of Colorado

  Computer simulations of spacecraft dynamics are widely used in industry and academia to predict how spacecraft will behave during proposed mission concepts. Current technology… (more)

Subjects/Keywords: dynamics; modular; multi-body; simulation; software architecture; spacecraft; Aerospace Engineering; Computer Sciences

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APA (6th Edition):

Allard, C. J. (2018). Modular Software Architecture for Complex Multi-Body Fully-Coupled Spacecraft Dynamics. (Doctoral Dissertation). University of Colorado. Retrieved from https://scholar.colorado.edu/asen_gradetds/197

Chicago Manual of Style (16th Edition):

Allard, Cody J. “Modular Software Architecture for Complex Multi-Body Fully-Coupled Spacecraft Dynamics.” 2018. Doctoral Dissertation, University of Colorado. Accessed March 21, 2019. https://scholar.colorado.edu/asen_gradetds/197.

MLA Handbook (7th Edition):

Allard, Cody J. “Modular Software Architecture for Complex Multi-Body Fully-Coupled Spacecraft Dynamics.” 2018. Web. 21 Mar 2019.

Vancouver:

Allard CJ. Modular Software Architecture for Complex Multi-Body Fully-Coupled Spacecraft Dynamics. [Internet] [Doctoral dissertation]. University of Colorado; 2018. [cited 2019 Mar 21]. Available from: https://scholar.colorado.edu/asen_gradetds/197.

Council of Science Editors:

Allard CJ. Modular Software Architecture for Complex Multi-Body Fully-Coupled Spacecraft Dynamics. [Doctoral Dissertation]. University of Colorado; 2018. Available from: https://scholar.colorado.edu/asen_gradetds/197


University of Toronto

19. Bazzocchi, Michael Christopher Francesco. Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization.

Degree: PhD, 2018, University of Toronto

 In this thesis, an overall framework is established for the redirection of near-Earth asteroids using spacecraft formation strategies in order to access and utilize asteroid… (more)

Subjects/Keywords: Asteroid Redirection; Formation Control; Orbital Dynamics; Spacecraft Formation; Space Debris; Transfer Trajectory Design; 0538

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APA (6th Edition):

Bazzocchi, M. C. F. (2018). Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization. (Doctoral Dissertation). University of Toronto. Retrieved from http://hdl.handle.net/1807/89883

Chicago Manual of Style (16th Edition):

Bazzocchi, Michael Christopher Francesco. “Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization.” 2018. Doctoral Dissertation, University of Toronto. Accessed March 21, 2019. http://hdl.handle.net/1807/89883.

MLA Handbook (7th Edition):

Bazzocchi, Michael Christopher Francesco. “Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization.” 2018. Web. 21 Mar 2019.

Vancouver:

Bazzocchi MCF. Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization. [Internet] [Doctoral dissertation]. University of Toronto; 2018. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/1807/89883.

Council of Science Editors:

Bazzocchi MCF. Spacecraft Formation Approach to Asteroid Redirection for Resource Utilization. [Doctoral Dissertation]. University of Toronto; 2018. Available from: http://hdl.handle.net/1807/89883


University of Illinois – Urbana-Champaign

20. Harpale, Abhilash. Scale-bridging molecular dynamics simulations of plasma-surface interactions.

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

 Plasma processing of materials plays a vital part in electronic, aerospace, automobile, metal manufacturing and biomedical industries. Plasma-surface interactions can be divided into two categories:… (more)

Subjects/Keywords: graphene; plasma; molecular dynamics; atomic scale simulations; surfaces; thermal protection system; NASA; spacecraft

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APA (6th Edition):

Harpale, A. (2018). Scale-bridging molecular dynamics simulations of plasma-surface interactions. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/100909

Chicago Manual of Style (16th Edition):

Harpale, Abhilash. “Scale-bridging molecular dynamics simulations of plasma-surface interactions.” 2018. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed March 21, 2019. http://hdl.handle.net/2142/100909.

MLA Handbook (7th Edition):

Harpale, Abhilash. “Scale-bridging molecular dynamics simulations of plasma-surface interactions.” 2018. Web. 21 Mar 2019.

Vancouver:

Harpale A. Scale-bridging molecular dynamics simulations of plasma-surface interactions. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2018. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/2142/100909.

Council of Science Editors:

Harpale A. Scale-bridging molecular dynamics simulations of plasma-surface interactions. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2018. Available from: http://hdl.handle.net/2142/100909


Virginia Tech

21. 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 March 21, 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. 21 Mar 2019.

Vancouver:

VanDyke MC. Constant Orbital Momentum Equilibrium Trajectories of a Gyrostat-Satellite. [Internet] [Doctoral dissertation]. Virginia Tech; 2014. [cited 2019 Mar 21]. 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

22. Rye, Maria del Carmen. Dynamics and Control of a Tensegrity System in Low-Earth Orbit.

Degree: PhD, Aerospace and Ocean Engineering, 2017, Virginia Tech

 Tensegrity is the name given to a system of interconnected bars and tendons that can form a flexible self-standing structure. Its flexibility is due to… (more)

Subjects/Keywords: tensegrity; spacecraft dynamics; gravity gradient

…Begin by deriving the dynamics of a generic tensegrity spacecraft. The Earth is assumed to be… …1 to the number of bars. The dynamics of the spacecraft can be derived using Lagrange’s… …spacecraft, and are derived in Section 2.4. Maria Rye Chapter 2. General Dynamics Figure 2.1… …47 4 Application to Simple Tensegrity Spacecraft 4.1 4.2 51 Spacecraft Base… …Earth-centered inertial frame tiu and spacecraft position. The position vector r0 of the… 

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APA (6th Edition):

Rye, M. d. C. (2017). Dynamics and Control of a Tensegrity System in Low-Earth Orbit. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/77584

Chicago Manual of Style (16th Edition):

Rye, Maria del Carmen. “Dynamics and Control of a Tensegrity System in Low-Earth Orbit.” 2017. Doctoral Dissertation, Virginia Tech. Accessed March 21, 2019. http://hdl.handle.net/10919/77584.

MLA Handbook (7th Edition):

Rye, Maria del Carmen. “Dynamics and Control of a Tensegrity System in Low-Earth Orbit.” 2017. Web. 21 Mar 2019.

Vancouver:

Rye MdC. Dynamics and Control of a Tensegrity System in Low-Earth Orbit. [Internet] [Doctoral dissertation]. Virginia Tech; 2017. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/10919/77584.

Council of Science Editors:

Rye MdC. Dynamics and Control of a Tensegrity System in Low-Earth Orbit. [Doctoral Dissertation]. Virginia Tech; 2017. Available from: http://hdl.handle.net/10919/77584


Indian Institute of Science

23. Akila, S. Orbit Model Analysis And Dynamic Filter Compensation For Onboard Autonomy.

Degree: 2006, Indian Institute of Science

 Orbit of a spacecraft in three dimensional Inertial Reference Frame is in general represented by a standard set of six parameters like Keplerian Orbital Elements… (more)

Subjects/Keywords: Orbit Models; Spacecraft Orbits; Dynamic Filters; Orbit Dynamics; Orbit Determination (OD); Orbit Propagation; Kalman Filter; Dynamics Filter Compensation (DFC); Astronautics

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APA (6th Edition):

Akila, S. (2006). Orbit Model Analysis And Dynamic Filter Compensation For Onboard Autonomy. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/398

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):

Akila, S. “Orbit Model Analysis And Dynamic Filter Compensation For Onboard Autonomy.” 2006. Thesis, Indian Institute of Science. Accessed March 21, 2019. http://hdl.handle.net/2005/398.

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

MLA Handbook (7th Edition):

Akila, S. “Orbit Model Analysis And Dynamic Filter Compensation For Onboard Autonomy.” 2006. Web. 21 Mar 2019.

Vancouver:

Akila S. Orbit Model Analysis And Dynamic Filter Compensation For Onboard Autonomy. [Internet] [Thesis]. Indian Institute of Science; 2006. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/2005/398.

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

Council of Science Editors:

Akila S. Orbit Model Analysis And Dynamic Filter Compensation For Onboard Autonomy. [Thesis]. Indian Institute of Science; 2006. Available from: http://hdl.handle.net/2005/398

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


Cal Poly

24. Currie, Blake J. Control of a Spacecraft Using Mixed Momentum Exchange Devices.

Degree: MS, Aerospace Engineering, 2014, Cal Poly

  Hardware configurations, a control law, and a steering law are developed for a mixed hardware spacecraft that uses both control moment gyros and reaction… (more)

Subjects/Keywords: spacecraft; control; CMG; Gyro; Reaction Wheel; Pointing; Acoustics, Dynamics, and Controls; Navigation, Guidance, Control and Dynamics

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APA (6th Edition):

Currie, B. J. (2014). Control of a Spacecraft Using Mixed Momentum Exchange Devices. (Masters Thesis). Cal Poly. Retrieved from http://digitalcommons.calpoly.edu/theses/1313 ; 10.15368/theses.2014.162

Chicago Manual of Style (16th Edition):

Currie, Blake J. “Control of a Spacecraft Using Mixed Momentum Exchange Devices.” 2014. Masters Thesis, Cal Poly. Accessed March 21, 2019. http://digitalcommons.calpoly.edu/theses/1313 ; 10.15368/theses.2014.162.

MLA Handbook (7th Edition):

Currie, Blake J. “Control of a Spacecraft Using Mixed Momentum Exchange Devices.” 2014. Web. 21 Mar 2019.

Vancouver:

Currie BJ. Control of a Spacecraft Using Mixed Momentum Exchange Devices. [Internet] [Masters thesis]. Cal Poly; 2014. [cited 2019 Mar 21]. Available from: http://digitalcommons.calpoly.edu/theses/1313 ; 10.15368/theses.2014.162.

Council of Science Editors:

Currie BJ. Control of a Spacecraft Using Mixed Momentum Exchange Devices. [Masters Thesis]. Cal Poly; 2014. Available from: http://digitalcommons.calpoly.edu/theses/1313 ; 10.15368/theses.2014.162


University of Colorado

25. Stevenson, Daan. Remote Spacecraft Attitude Control by Coulomb Charging.

Degree: PhD, Aerospace Engineering Sciences, 2015, University of Colorado

  The possibility of inter-spacecraft collisions is a serious concern at Geosynchronous altitudes, where many high-value assets operate in proximity to countless debris objects whose… (more)

Subjects/Keywords: electrostatic modeling; high voltage experimentation; spacecraft attitude control; spacecraft charging; Multi-Vehicle Systems and Air Traffic Control; Navigation, Guidance, Control and Dynamics; Space Vehicles

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APA (6th Edition):

Stevenson, D. (2015). Remote Spacecraft Attitude Control by Coulomb Charging. (Doctoral Dissertation). University of Colorado. Retrieved from http://scholar.colorado.edu/asen_gradetds/94

Chicago Manual of Style (16th Edition):

Stevenson, Daan. “Remote Spacecraft Attitude Control by Coulomb Charging.” 2015. Doctoral Dissertation, University of Colorado. Accessed March 21, 2019. http://scholar.colorado.edu/asen_gradetds/94.

MLA Handbook (7th Edition):

Stevenson, Daan. “Remote Spacecraft Attitude Control by Coulomb Charging.” 2015. Web. 21 Mar 2019.

Vancouver:

Stevenson D. Remote Spacecraft Attitude Control by Coulomb Charging. [Internet] [Doctoral dissertation]. University of Colorado; 2015. [cited 2019 Mar 21]. Available from: http://scholar.colorado.edu/asen_gradetds/94.

Council of Science Editors:

Stevenson D. Remote Spacecraft Attitude Control by Coulomb Charging. [Doctoral Dissertation]. University of Colorado; 2015. Available from: http://scholar.colorado.edu/asen_gradetds/94


Cal Poly

26. Dam, Long H. Applied Mass Properties Identification Method to the Cal Poly's Spacecraft Simulator.

Degree: MS, Aerospace Engineering, 2014, Cal Poly

  The Cal Poly Spacecraft Simulator is currently being developed for future testing and verifying theoretical control applications. This paper details the effort to balance… (more)

Subjects/Keywords: System and Mass Properties Identification; Spacecraft Simulator; Spacecraft Control; Least Square; Batch Estimation; Navigation, Guidance, Control and Dynamics; Systems Engineering and Multidisciplinary Design Optimization

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APA (6th Edition):

Dam, L. H. (2014). Applied Mass Properties Identification Method to the Cal Poly's Spacecraft Simulator. (Masters Thesis). Cal Poly. Retrieved from http://digitalcommons.calpoly.edu/theses/1175 ; 10.15368/theses.2014.25

Chicago Manual of Style (16th Edition):

Dam, Long H. “Applied Mass Properties Identification Method to the Cal Poly's Spacecraft Simulator.” 2014. Masters Thesis, Cal Poly. Accessed March 21, 2019. http://digitalcommons.calpoly.edu/theses/1175 ; 10.15368/theses.2014.25.

MLA Handbook (7th Edition):

Dam, Long H. “Applied Mass Properties Identification Method to the Cal Poly's Spacecraft Simulator.” 2014. Web. 21 Mar 2019.

Vancouver:

Dam LH. Applied Mass Properties Identification Method to the Cal Poly's Spacecraft Simulator. [Internet] [Masters thesis]. Cal Poly; 2014. [cited 2019 Mar 21]. Available from: http://digitalcommons.calpoly.edu/theses/1175 ; 10.15368/theses.2014.25.

Council of Science Editors:

Dam LH. Applied Mass Properties Identification Method to the Cal Poly's Spacecraft Simulator. [Masters Thesis]. Cal Poly; 2014. Available from: http://digitalcommons.calpoly.edu/theses/1175 ; 10.15368/theses.2014.25


University of Toronto

27. Vatankhahghadim, Behrad. Hybrid Magnetic Attitude Control of Spacecraft: Optimality, Passivity, and Stability.

Degree: 2016, University of Toronto

Hybrid spacecraft attitude control schemes that combine magnetic torques with impulsive thrusting in an optimal or passive manner are developed. The optimal controller uses a… (more)

Subjects/Keywords: Hybrid Magnetic Attitude Control; Hybrid Stability Analysis; Optimal Control; Passivity-Based Control; Spacecraft Dynamics and Control; 0538

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APA (6th Edition):

Vatankhahghadim, B. (2016). Hybrid Magnetic Attitude Control of Spacecraft: Optimality, Passivity, and Stability. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/73473

Chicago Manual of Style (16th Edition):

Vatankhahghadim, Behrad. “Hybrid Magnetic Attitude Control of Spacecraft: Optimality, Passivity, and Stability.” 2016. Masters Thesis, University of Toronto. Accessed March 21, 2019. http://hdl.handle.net/1807/73473.

MLA Handbook (7th Edition):

Vatankhahghadim, Behrad. “Hybrid Magnetic Attitude Control of Spacecraft: Optimality, Passivity, and Stability.” 2016. Web. 21 Mar 2019.

Vancouver:

Vatankhahghadim B. Hybrid Magnetic Attitude Control of Spacecraft: Optimality, Passivity, and Stability. [Internet] [Masters thesis]. University of Toronto; 2016. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/1807/73473.

Council of Science Editors:

Vatankhahghadim B. Hybrid Magnetic Attitude Control of Spacecraft: Optimality, Passivity, and Stability. [Masters Thesis]. University of Toronto; 2016. Available from: http://hdl.handle.net/1807/73473


Luleå University of Technology

28. Silva, Luis Ignacio. Modeling and simulation of spacecraft dynamics using bond graph.

Degree: 2007, Luleå University of Technology

A model that describes the orbital dynamics and another for the thermal behavior are obtained. The formalism used to represent them is the so-… (more)

Subjects/Keywords: Technology; Bond Graph; non-linear estimator; Spacecraft Dynamics; Teknik

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APA (6th Edition):

Silva, L. I. (2007). Modeling and simulation of spacecraft dynamics using bond graph. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-45263

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):

Silva, Luis Ignacio. “Modeling and simulation of spacecraft dynamics using bond graph.” 2007. Thesis, Luleå University of Technology. Accessed March 21, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-45263.

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

MLA Handbook (7th Edition):

Silva, Luis Ignacio. “Modeling and simulation of spacecraft dynamics using bond graph.” 2007. Web. 21 Mar 2019.

Vancouver:

Silva LI. Modeling and simulation of spacecraft dynamics using bond graph. [Internet] [Thesis]. Luleå University of Technology; 2007. [cited 2019 Mar 21]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-45263.

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

Council of Science Editors:

Silva LI. Modeling and simulation of spacecraft dynamics using bond graph. [Thesis]. Luleå University of Technology; 2007. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-45263

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


University of Michigan

29. Petersen, Christopher. Advances in Underactuated Spacecraft Control.

Degree: PhD, Aerospace Engineering, 2016, University of Michigan

 This dissertation addresses the control of a spacecraft which either becomes underactuated due to onboard failures or is made underactuated by design. Successfully controlling an… (more)

Subjects/Keywords: Spacecraft Dynamics and Control; Underactuated Control; Attitude Control; Coupled Rotational and Translational Relative Motion; Model Predictive Control; Aerospace Engineering; Engineering

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APA (6th Edition):

Petersen, C. (2016). Advances in Underactuated Spacecraft Control. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/133430

Chicago Manual of Style (16th Edition):

Petersen, Christopher. “Advances in Underactuated Spacecraft Control.” 2016. Doctoral Dissertation, University of Michigan. Accessed March 21, 2019. http://hdl.handle.net/2027.42/133430.

MLA Handbook (7th Edition):

Petersen, Christopher. “Advances in Underactuated Spacecraft Control.” 2016. Web. 21 Mar 2019.

Vancouver:

Petersen C. Advances in Underactuated Spacecraft Control. [Internet] [Doctoral dissertation]. University of Michigan; 2016. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/2027.42/133430.

Council of Science Editors:

Petersen C. Advances in Underactuated Spacecraft Control. [Doctoral Dissertation]. University of Michigan; 2016. Available from: http://hdl.handle.net/2027.42/133430


Virginia Tech

30. Long, Matthew Robert. Spacecraft Attitude Tracking Control.

Degree: MS, Aerospace and Ocean Engineering, 1999, Virginia Tech

 The problem of reorienting a spacecraft to acquire a moving target is investigated. The spacecraft is modeled as a rigid body with N axisymmetric wheels… (more)

Subjects/Keywords: Lyapunov Control Theory; Spacecraft Dynamics; Target Tracking

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APA (6th Edition):

Long, M. R. (1999). Spacecraft Attitude Tracking Control. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/33843

Chicago Manual of Style (16th Edition):

Long, Matthew Robert. “Spacecraft Attitude Tracking Control.” 1999. Masters Thesis, Virginia Tech. Accessed March 21, 2019. http://hdl.handle.net/10919/33843.

MLA Handbook (7th Edition):

Long, Matthew Robert. “Spacecraft Attitude Tracking Control.” 1999. Web. 21 Mar 2019.

Vancouver:

Long MR. Spacecraft Attitude Tracking Control. [Internet] [Masters thesis]. Virginia Tech; 1999. [cited 2019 Mar 21]. Available from: http://hdl.handle.net/10919/33843.

Council of Science Editors:

Long MR. Spacecraft Attitude Tracking Control. [Masters Thesis]. Virginia Tech; 1999. Available from: http://hdl.handle.net/10919/33843

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