You searched for subject:(spacecraft attitude control).
Showing records 1 – 30 of
49 total matches.
◁ [1] [2] ▶
Lehigh University
1.
Zhu, Shiqiao.
Analysis of Spacecraft Attitude Control.
Degree: MS, Mechanical Engineering, 2016, Lehigh University
URL: https://preserve.lehigh.edu/etd/2915 
► The thesis studies about repositioning the spacecraft to obtain a moving target problem. We model the spacecraft as a rigid body with axis torque controlling…
(more)
▼ 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 N axial symmetry wheels, and kinematic parameters by ADCS. Reference trajectory represented a virtual space generated by the same actual
spacecraft. Open loop reference posture, angular velocity and angular acceleration tracking order is constructed, making solar panels vector is perpendicular to the carrier tracking the movement of the sun. We developed a nonlinear feedback tracking
control law, derived from the ADCS stability and
control theory, the target tracking
control torque. Asymptotic tracking controller make the main body frame, there are in the
attitude and angular velocity error of initial reference movement.
Spacecraft model, on the basis of resource manager in Tian Tuo-1
spacecraft, for demonstration in tracking the given target ADCS controller is effective.
Advisors/Committee Members: Hart, Terry.
Subjects/Keywords: alalysis of spacecraft attitude control; analysis control; attitude; attitude control; attitude of spacecraft; spacecraft control; Engineering; Mechanical Engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
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 March 01, 2021.
https://preserve.lehigh.edu/etd/2915.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Zhu, Shiqiao. “Analysis of Spacecraft Attitude Control.” 2016. Web. 01 Mar 2021.
Vancouver:
Zhu S. Analysis of Spacecraft Attitude Control. [Internet] [Thesis]. Lehigh University; 2016. [cited 2021 Mar 01].
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
York University
2.
Agarwal, Anirudh.
Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages.
Degree: MSc -MS, Earth & Space Science, 2019, York University
URL: http://hdl.handle.net/10315/35911
► This study designs and analyzes a new type of controller that helps improve the performance of single axis attitude control of flexible appendages attached to…
(more)
▼ 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 a rigid
spacecraft. Conventionally, PID with position feedback was used to
control single axis
attitude manoeuvre of flexible appendages on a
spacecraft but designing a PID to
control a higher order system is a limited strategy. Also, PID controllers are inherently unstable for third order systems and higher as will be demonstrated later. Thus, acceleration feedback is included in the design to demonstrate a more stable way of designing controllers for these systems and it is called PDA (Proportional Derivative Acceleration) controller. The controller is first designed using a root locus method and then applied to a simulated third order system om MATLAB. Then a higher order system model (rigid body with flexible appendage) is created on SIMULINK and the controller is applied to it. Finally, an experiment is performed and demonstrated to show the practical implementation of the
control design.
Advisors/Committee Members: Zhu, George (advisor).
Subjects/Keywords: Aerospace engineering; Spacecraft dynamics; Control systems; Acceleration feedback; PIDA; PID; Attitude control; Classical control; Spacecraft attitude control; Single axis attitude control
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
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 01, 2021.
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. 01 Mar 2021.
Vancouver:
Agarwal A. Proportional-Derivative-Acceleration Feedback Controller Design for Single Axis Attitude Control of Rigid Spacecraft with Flexible Appendages. [Internet] [Masters thesis]. York University; 2019. [cited 2021 Mar 01].
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
3.
Serpelloni, Edoardo.
Bang-Bang Practical Stabilization of Rigid Bodies.
Degree: PhD, 2017, University of Toronto
URL: http://hdl.handle.net/1807/79471
► In this thesis, we study the problem of designing a practical stabilizer for a rigid body equipped with a set of actuators generating only constant…
(more)
▼ In this thesis, we study the problem of designing a practical stabilizer for a rigid body equipped with a set of actuators generating only constant thrust. Our motivation stems from the fact that modern space missions are required to accurately
control the position and orientation of
spacecraft actuated by constant-thrust jet-thrusters. To comply with the performance limitations of modern thrusters, we design a feedback controller that does not induce high-frequency switching of the actuators.
The proposed controller is hybrid and it asymptotically stabilizes an arbitrarily small compact neighborhood of the target position and orientation of the rigid body. The controller is characterized by a hierarchical structure comprising of two
control layers. At the low level of the hierarchy, an
attitude controller stabilizes the target orientation of the rigid body. At the high level, after the
attitude controller has steered the rigid body sufficiently close to its desired orientation, a position controller stabilizes the desired position. The size of the neighborhood being stabilized by the controller can be adjusted via a proper selection of the controller parameters. This allows us to stabilize the rigid body to virtually any degree of accuracy. It is shown that the controller, even in the presence of measurement noise, does not induce high-frequency switching of the actuators. The key component in the design of the controller is a hybrid stabilizer for the origin of double-integrators affected by bounded external perturbations. Specifically, both the position and the
attitude stabilizers consist of multiple copies of such a double-integrator controller.
The proposed controller is applied to two realistic
spacecraft control problems. First, we apply the position controller to the problem of stabilizing the relative position between two
spacecraft flying in formation in the vicinity of the L2 libration point of the Sun-Earth system as a part of a large space telescope. The proposed position controller represents the first feedback strategy to guarantee the accuracy level required by this class of space missions using real-life electric thrusters. The final controller is applied to the
control of a large space vehicle performing rendezvous and docking operations with the International Space Station. It is shown that the controller guarantees a safe docking even under the effects of biases in the placement of the on-board thrusters.
Advisors/Committee Members: Maggiore, Manfredi, Damaren, Christopher J, Electrical and Computer Engineering.
Subjects/Keywords: Attitude Control; Bang-Bang Control; Double-Integrator Control; Spacecraft Control; 0544
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
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 March 01, 2021.
http://hdl.handle.net/1807/79471.
MLA Handbook (7th Edition):
Serpelloni, Edoardo. “Bang-Bang Practical Stabilization of Rigid Bodies.” 2017. Web. 01 Mar 2021.
Vancouver:
Serpelloni E. Bang-Bang Practical Stabilization of Rigid Bodies. [Internet] [Doctoral dissertation]. University of Toronto; 2017. [cited 2021 Mar 01].
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
Penn State University
4.
Ahn, Young Tae.
Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution.
Degree: 2012, Penn State University
URL: https://submit-etda.libraries.psu.edu/catalog/16015
► Spacecraft need specific attitude control methods that depend on the mission type or special tasks. The dynamics and the attitude control of a spacecraft with…
(more)
▼ Spacecraft need specific
attitude control methods that depend on the mission type or special tasks. The dynamics and the
attitude control of a
spacecraft with a shifting mass distribution within the system are examined. The behavior and use of conventional
attitude control actuators are widely developed and performing at the present time. However, the advantage of a shifting mass distribution concept can complement
spacecraft attitude control, save mass, and extend a satellite’s life. This can be adopted in practice by moving mass from one tank to another, similar to what an airplane does to balance weight. Using this shifting mass distribution concept, in conjunction with other
attitude control devices, can augment the three-axis
attitude control process. Shifting mass involves changing the center-of-mass of the system, and/or changing the moments of inertia of the system, which then ultimately can change the
attitude behavior of the system.
This dissertation consists of two parts. First, the equations of motion for the shifting mass concept (also known as morphing) are developed. They are tested for their effects on
attitude control by showing how shifting the mass changes the spacecraft’s
attitude behavior. Second, a method for optimal mass redistribution is shown using a combinatorial optimization theory under constraints. It closes with a simple example demonstrating an optimal reconfiguration.
The procedure of optimal reconfiguration from one mass distribution to another to accomplish
attitude control has been demonstrated for several simple examples. Mass shifting could work as an
attitude controller for fine-tuning
attitude behavior in small satellites. Various constraints can be applied for different situations, such as no mass shift between two tanks connected by a failed pipe or total amount of shifted mass per pipe being set for the time optimum solution. Euler angle changes influenced by the mass reconfiguration are accomplished while stability conditions are satisfied. In order to increase the accuracy, generally, more than two
control systems are installed in a satellite. Combination with another actuator will be examined to fulfill the full
attitude control maneuver. Future work can also include more realistic
spacecraft design and operational considerations on the behavior of this type of
control system.
Advisors/Committee Members: David Bradley Spencer, Dissertation Advisor/Co-Advisor, Robert Graham Melton, Committee Member, Sven G Bilen, Committee Member, Christopher Rahn, Committee Member.
Subjects/Keywords: spacecraft attitude dynamics; attitude control; combinatorial optimization theory
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Ahn, Y. T. (2012). Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/16015
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Chicago Manual of Style (16th Edition):
Ahn, Young Tae. “Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution.” 2012. Thesis, Penn State University. Accessed March 01, 2021.
https://submit-etda.libraries.psu.edu/catalog/16015.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Ahn, Young Tae. “Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution.” 2012. Web. 01 Mar 2021.
Vancouver:
Ahn YT. Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution. [Internet] [Thesis]. Penn State University; 2012. [cited 2021 Mar 01].
Available from: https://submit-etda.libraries.psu.edu/catalog/16015.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Ahn YT. Attitude Dynamics and Control of a Spacecraft Using Shifting Mass Distribution. [Thesis]. Penn State University; 2012. Available from: https://submit-etda.libraries.psu.edu/catalog/16015
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Queensland University of Technology
5.
Dando, Aaron John.
Robust adaptive control of rigid spacecraft attitude maneuvers.
Degree: 2008, Queensland University of Technology
URL: https://eprints.qut.edu.au/16695/
► In this thesis novel feedback attitude control algorithms and attitude estimation algorithms are developed for a three-axis stabilised spacecraft attitude control system. The spacecraft models…
(more)
▼ In this thesis novel feedback attitude control algorithms and attitude estimation algorithms are developed for a three-axis stabilised spacecraft attitude control system. The spacecraft models considered include a rigid-body spacecraft equipped with (i) external control torque devices, and (ii) a redundant reaction wheel configuration. The attitude sensor suite comprises a three-axis magnetometer and three-axis rate gyroscope assembly. The quaternion parameters (also called Euler symmetric parameters), which globally avoid singularities but are subject to a unity-norm constraint, are selected as the primary attitude coordinates. There are four novel contributions presented in this thesis. The first novel contribution is the development of a robust control strategy for spacecraft attitude tracking maneuvers, in the presence of dynamic model uncertainty in the spacecraft inertia matrix, actuator magnitude constraints, bounded persistent external disturbances, and state estimation error. The novel component of this algorithm is the incorporation of state estimation error into the stability analysis. The proposed control law contains a parameter which is dynamically adjusted to ensure global asymptotic stability of the overall closedloop system, in the presence of these specific system non-idealities. A stability proof is presented which is based on Lyapunov's direct method, in conjunction with Barbalat's lemma. The control design approach also ensures minimum angular path maneuvers, since the attitude quaternion parameters are not unique. The second novel contribution is the development of a robust direct adaptive control strategy for spacecraft attitude tracking maneuvers, in the presence of dynamic model uncertainty in the spacecraft inertia matrix. The novel aspect of this algorithm is the incorporation of a composite parameter update strategy, which ensures global exponential convergence of the closed-loop system. A stability proof is presented which is based on Lyapunov's direct method, in conjunction with Barbalat's lemma. The exponential convergence results provided by this control strategy require persistently exciting reference trajectory commands. The control design approach also ensures minimum angular path maneuvers. The third novel contribution is the development of an optimal control strategy for spacecraft attitude maneuvers, based on a rigid body spacecraft model including a redundant reaction wheel assembly. The novel component of this strategy is the proposal of a performance index which represents the total electrical energy consumed by the reaction wheel over the maneuver interval. Pontraygin's minimum principle is applied to formulate the necessary conditions for optimality, in which the control torques are subject to timevarying magnitude constraints. The presence of singular sub-arcs in the statespace and their associated singular controls are investigated using Kelley's necessary condition. The two-point boundary-value problem (TPBVP) is formulated using Pontrayagin's minimum principle. The…
Subjects/Keywords: spacecraft attitude control system; spacecraft attitude manevers; spacecraft attitude estimation; Lyapunov stability theory; adaptive control theory; optimal control theory; state estimation theory
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
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 March 01, 2021.
https://eprints.qut.edu.au/16695/.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Dando, Aaron John. “Robust adaptive control of rigid spacecraft attitude maneuvers.” 2008. Web. 01 Mar 2021.
Vancouver:
Dando AJ. Robust adaptive control of rigid spacecraft attitude maneuvers. [Internet] [Thesis]. Queensland University of Technology; 2008. [cited 2021 Mar 01].
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
Virginia Tech
6.
VanDyke, Matthew Clark.
Constant Orbital Momentum Equilibrium Trajectories of a Gyrostat-Satellite.
Degree: PhD, Aerospace Engineering, 2014, Virginia Tech
URL: http://hdl.handle.net/10919/24911
► This dissertation investigates attitude transition maneuvers of a gyrosat-satellite between relative equilibria. The primary challenge in transitioning between relative equilibria is the proper adjustment of…
(more)
▼ This dissertation investigates
attitude transition maneuvers of a gyrosat-satellite between relative equilibria. The primary challenge in transitioning between relative equilibria is the proper adjustment of the system angular momentum so that upon completing the transition maneuver the gyrostat-satellite will satisfy all the requirements for a relative equilibrium. The system angular momentum is a function of the
attitude trajectory taken during the transition maneuver. A new concept, the constant orbital momentum equilibrium trajectory or COMET, is introduced as a means to a straight-forward solution to a subset of the possible transitions between relative equilbria. COMETs are a class of paths in SO(3) that a gyrostat-satellite may travel along that maintain a constant system angular momentum. The primary contributions of this dissertation are the introduction and analysis of COMETs and their application to the problem of transitioning a gyrostat-satellite between two relative equilibria.
The current work introduces, defines, and analyzes COMETs in detail. The requirements for a path in SO(3) to be a COMET are defined. It is shown via example that COMETs are closed-curves in SO(3). Visualizations of families of COMETs are presented and discussed in detail. A subset of COMETs are shown to contain critical points that represent isolated relative equilibrium attitudes or furcations of the COMET.
The problem of transitioning between two relative equilibria is split into the sub-problems of transitioning between relative equilibria on the same COMET and transitioning between relative equilibria on different COMETs. For transitions between relative equilibria on the same COMET, an open-loop
control law is developed that drives a gyrostat-satellite along the COMET until the target relative equilibrium is reached. For transitions between relative equilibria on different COMETs, an open-loop
control law is developed that transfers a gyrostat-satellite from the initial relative equilibrium to a relative equilibrium that resides on the same COMET as the target relative equilbrium. Acquisition of the target relative equilibrium is then accomplished via the application of the open-loop
control law for transitions between relative equilibria on the same COMET. The results of numeric simulations of gyrostat-satellites executing these transitions are presented.
Advisors/Committee Members: Hall, Christopher D. (committeechair), Woolsey, Craig A. (committeechair), Earle, Gregory D. (committee member), Sultan, Cornel (committee member).
Subjects/Keywords: Gyrostat-Satellite; Relative Equilibrium; Spacecraft Dynamics; Attitude Control; Attitude Guidance; Gravitational Torque; Attitude Maneuvers
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
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 01, 2021.
http://hdl.handle.net/10919/24911.
MLA Handbook (7th Edition):
VanDyke, Matthew Clark. “Constant Orbital Momentum Equilibrium Trajectories of a Gyrostat-Satellite.” 2014. Web. 01 Mar 2021.
Vancouver:
VanDyke MC. Constant Orbital Momentum Equilibrium Trajectories of a Gyrostat-Satellite. [Internet] [Doctoral dissertation]. Virginia Tech; 2014. [cited 2021 Mar 01].
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
Luleå University of Technology
7.
Cypriano, Lucas Almeida.
Study and Design of an Adaptive Control Law for Spacecraft Attitude Control.
Degree: 2014, Luleå University of Technology
URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-50766
► In this thesis the problem of spacecraft attitude control is investigated. The spacecraft dynamics are modeled as a rigid body system controlled by 4…
(more)
▼ In this thesis the problem of spacecraft attitude control is investigated. The spacecraft dynamics are modeled as a rigid body system controlled by 4 thrusters, and the kinematics are represented by direction cosine matrix. In this thesis, the effectiveness of retrospective cost adaptive control for spacecraft attitude control is evaluated. The prominent feature of this adaptive controller is that it requires little knowledge of the system to be controlled. This makes this controller attractive since for most spacecraft knowledge of the spacecraft’s inertia tensor is limited and will sometimes change over the spacecraft lifetime.
Validerat; 20140728 (global_studentproject_submitter)
Subjects/Keywords: Technology; Adaptive Control; RCAC; Attitude Control; ADCS; AOCS; Spacecraft; Teknik
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
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 March 01, 2021.
http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-50766.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Cypriano, Lucas Almeida. “Study and Design of an Adaptive Control Law for Spacecraft Attitude Control.” 2014. Web. 01 Mar 2021.
Vancouver:
Cypriano LA. Study and Design of an Adaptive Control Law for Spacecraft Attitude Control. [Internet] [Thesis]. Luleå University of Technology; 2014. [cited 2021 Mar 01].
Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-50766.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Cypriano LA. Study and Design of an Adaptive Control Law for Spacecraft Attitude Control. [Thesis]. Luleå University of Technology; 2014. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-50766
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Delft University of Technology
8.
Maltha, Rutger (author).
GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator.
Degree: 2018, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:16c8d9b6-1d07-46fa-9a4f-4c445bd9e3dc
► Given the difficulty that is normally associated with tuning highly nonlinear control systems, such as seen in LEO spacecraft, it is interesting to evaluate how…
(more)
▼ Given the difficulty that is normally associated with tuning highly nonlinear
control systems, such as seen in LEO
spacecraft, it is interesting to evaluate how new controller types perform. The measured data from the GOCE mission has led to the creation of high fidelity torque models describing the angular perturbations acting on a
spacecraft. These torque models present an excellent opportunity to test the performance of new magnetically actuated
attitude control methods. The work done in this thesis used these torque models in a simulation environment to evaluate the performance of an INDI-based
control architecture for controlling the
attitude of a GOCE-type
spacecraft, using magnetic
control actuation only. The goal was to evaluate whether an INDI-based
control architecture can meet the same requirements that were set for the GOCE mission, and simultaneously evaluate the difficulty of tuning the controller and its sensitivity to errors and changes in gains once it is tuned. To achieve this a PD-controller was used as a reference controller, and two INDI-based controllers were set-up. One with a linear
control outer loop (LINDI), and one with an NDI outer loop (NINDI). All three controllers have been tuned using a genetic algorithm.
Advisors/Committee Members: Doornbos, Eelco (mentor), Visser, Tim (mentor), Visser, Pieter (graduation committee), van Kampen, Erik-jan (graduation committee), Delft University of Technology (degree granting institution).
Subjects/Keywords: Genetic algorithm; INDI; Attitude control; GOCE; Spacecraft torque models; Magnetic attitude control; NDI
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Maltha, R. (. (2018). GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:16c8d9b6-1d07-46fa-9a4f-4c445bd9e3dc
Chicago Manual of Style (16th Edition):
Maltha, Rutger (author). “GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator.” 2018. Masters Thesis, Delft University of Technology. Accessed March 01, 2021.
http://resolver.tudelft.nl/uuid:16c8d9b6-1d07-46fa-9a4f-4c445bd9e3dc.
MLA Handbook (7th Edition):
Maltha, Rutger (author). “GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator.” 2018. Web. 01 Mar 2021.
Vancouver:
Maltha R(. GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Mar 01].
Available from: http://resolver.tudelft.nl/uuid:16c8d9b6-1d07-46fa-9a4f-4c445bd9e3dc.
Council of Science Editors:
Maltha R(. GOCE Spacecraft Attitude Control: A magnetic attitude controller simulator. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:16c8d9b6-1d07-46fa-9a4f-4c445bd9e3dc
University of Toronto
9.
Stellini, Julian.
Magnetic Attitude Control For Spacecraft with Flexible Appendages.
Degree: 2012, University of Toronto
URL: http://hdl.handle.net/1807/33545
► The design of an attitude control system for a flexible spacecraft using magnetic actuation is considered. The nonlinear, linear, and modal equations of motion are…
(more)
▼ 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 developed for a general flexible body. Magnetic control is shown to be instantaneously underactuated, and is only controllable in the time-varying sense. A PD-like control scheme is proposed to address the attitude control problem for the linear system. Control gain limitations are shown to exist for the purely magnetic control. A hybrid control scheme is also proposed that relaxes these restrictions by adding a minimum control effort from an alternate three-axis actuation system. Floquet and passivity theory are used to obtain gain selection criteria that ensure a stable closed-loop system, which would aid in the design of a hybrid controller for a flexible spacecraft. The ability of the linearized system to predict the stability of the corresponding nonlinear system is also investigated.
MAST
Advisors/Committee Members: Damaren, Christopher John, Aerospace Science and Engineering.
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
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
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 March 01, 2021.
http://hdl.handle.net/1807/33545.
MLA Handbook (7th Edition):
Stellini, Julian. “Magnetic Attitude Control For Spacecraft with Flexible Appendages.” 2012. Web. 01 Mar 2021.
Vancouver:
Stellini J. Magnetic Attitude Control For Spacecraft with Flexible Appendages. [Internet] [Masters thesis]. University of Toronto; 2012. [cited 2021 Mar 01].
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
Rochester Institute of Technology
10.
Dubill, Amber.
Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails.
Degree: MS, Mechanical Engineering, 2020, Rochester Institute of Technology
URL: https://scholarworks.rit.edu/theses/10388
► A solar sail making use of the physics of diffracted light enables the transfer of optical to mechanical momentum for in-space propulsion. In this…
(more)
▼ A solar sail making use of the physics of diffracted light enables the transfer of optical to mechanical momentum for in-space propulsion. In this thesis we describe advantages of diffractive solar sailing for trajectory and
attitude control. In particular, a high inclination angle heliophysics mission is examined. A simple roll maneuver of a diffractive sail is described to attain an inclination angle of 60º. A comparison of idealized diffractive and reflective sails for a five-year solar polar orbiter mission, showing higher inclination angles and a smaller orbital radius for the former is performed. As a result, a constellation of diffractive solar sails for heliophysics imaging and data gathering can be envisioned. A series of 14 [kg], 400 [m2] lightsails at various inclination angles could be in place at 0.32 [AU] within six years of launch. Based on our survey of current solar sailing and
attitude control systems, the feasibility of performing these maneuvers and the advantages diffractive elements can enable are explored. A theoretical model of the sailcraft is derived and various
attitude control systems are numerically modeled. This analysis includes classical
control devices such as reaction wheels and novel approaches with electro-optically controlled devices. It is concluded that while a fully electro-optic system is sufficient in the long term, a hybrid system of both small reaction wheels and electrically controlled diffractive elements provides an advantageous solution and could be expanded for other solar sailing applications in the near future.
Advisors/Committee Members: Grover Swartzlander.
Subjects/Keywords: Attitude control; Diffractice; Heliophysics; Orbital mechanics; Solar sailing; Spacecraft
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Dubill, A. (2020). Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails. (Masters Thesis). Rochester Institute of Technology. Retrieved from https://scholarworks.rit.edu/theses/10388
Chicago Manual of Style (16th Edition):
Dubill, Amber. “Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails.” 2020. Masters Thesis, Rochester Institute of Technology. Accessed March 01, 2021.
https://scholarworks.rit.edu/theses/10388.
MLA Handbook (7th Edition):
Dubill, Amber. “Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails.” 2020. Web. 01 Mar 2021.
Vancouver:
Dubill A. Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails. [Internet] [Masters thesis]. Rochester Institute of Technology; 2020. [cited 2021 Mar 01].
Available from: https://scholarworks.rit.edu/theses/10388.
Council of Science Editors:
Dubill A. Attitude Control for Circumnavigating the Sun with Diffractive Solar Sails. [Masters Thesis]. Rochester Institute of Technology; 2020. Available from: https://scholarworks.rit.edu/theses/10388
San Jose State University
11.
Westfall, Alexander Joseph.
Design of an Attitude Control System for Spin-Axis Control of a 3U CubeSat.
Degree: MS, Aerospace Engineering, 2015, San Jose State University
URL: https://doi.org/10.31979/etd.u6fr-6t4m
;
https://scholarworks.sjsu.edu/etd_theses/4672
► This paper describes the design process of developing a spin-axis control system for a 3U CubeSat, a relatively small satellite. Design requires the CubeSat…
(more)
▼ This paper describes the design process of developing a spin-axis control system for a 3U CubeSat, a relatively small satellite. Design requires the CubeSat to de-spin after deployment and direct its antenna to track Earth nadir position. The one degree of freedom controller is developed for the TechEdSat, which is a CubeSat with a payload that allows for the assumption that rotation pitch and yaw rates are sufficiently close to zero. Satellite torqueing disturbances are modeled with reaction wheel noise for a more complete system analysis. Sensor noise is unmodeled. Frequency domain and time domain analyses are presented; the entire system bandwidth operates at 0.08 hertz with 43.2 decibels of gain and 67.7o of phase margin. During nominal operations, pointing accuracy with perfect state knowledge assumption maintains position with steady state error of 13.7 arc seconds and oscillates by 16.7 arc seconds at a rate of 0.7 mHertz. Artificial wheel noise is injected into the model causing the pointing accuracy to drop to ± 15 arc seconds. Environmental disturbances are modeled extensively; the magnetic field torque is the worst disturbance, at 4.2e-7 Newton-meters. A 0.2 Amp·m2 magnetorquer dumps the excess momentum every 7.75 hours and require 1.5 hours to complete. In the deployment simulation, a 1 rotation per minute spin is arrested with no angular offset in 60 seconds. Future plans include utilizing the model to build and fly a prototype reaction wheel on a future TechEdSat mission to verify modeled expectations.
Subjects/Keywords: ADCS; Aerospace; Attitude Control; CubeSat; Reaction Wheel; Spacecraft
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Westfall, A. J. (2015). Design of an Attitude Control System for Spin-Axis Control of a 3U CubeSat. (Masters Thesis). San Jose State University. Retrieved from https://doi.org/10.31979/etd.u6fr-6t4m ; https://scholarworks.sjsu.edu/etd_theses/4672
Chicago Manual of Style (16th Edition):
Westfall, Alexander Joseph. “Design of an Attitude Control System for Spin-Axis Control of a 3U CubeSat.” 2015. Masters Thesis, San Jose State University. Accessed March 01, 2021.
https://doi.org/10.31979/etd.u6fr-6t4m ; https://scholarworks.sjsu.edu/etd_theses/4672.
MLA Handbook (7th Edition):
Westfall, Alexander Joseph. “Design of an Attitude Control System for Spin-Axis Control of a 3U CubeSat.” 2015. Web. 01 Mar 2021.
Vancouver:
Westfall AJ. Design of an Attitude Control System for Spin-Axis Control of a 3U CubeSat. [Internet] [Masters thesis]. San Jose State University; 2015. [cited 2021 Mar 01].
Available from: https://doi.org/10.31979/etd.u6fr-6t4m ; https://scholarworks.sjsu.edu/etd_theses/4672.
Council of Science Editors:
Westfall AJ. Design of an Attitude Control System for Spin-Axis Control of a 3U CubeSat. [Masters Thesis]. San Jose State University; 2015. Available from: https://doi.org/10.31979/etd.u6fr-6t4m ; https://scholarworks.sjsu.edu/etd_theses/4672
University of Manchester
12.
Hao, Zhou.
Orbital aerodynamic attitude control for spacecraft.
Degree: PhD, 2018, University of Manchester
URL: https://www.research.manchester.ac.uk/portal/en/theses/orbital-aerodynamic-attitude-control-for-spacecraft(b080a1ab-f954-4071-89bd-0d86969aa0ed).html
;
https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.756900
► This dissertation introduces novel techniques for exploiting the environmental aerodynamic forces to actively control the attitude of the spacecraft operating in the lower and middle…
(more)
▼ This dissertation introduces novel techniques for exploiting the environmental aerodynamic forces to actively control the attitude of the spacecraft operating in the lower and middle thermosphere. It includes both simulations and real spacecraft attitude determination and control subsystem development, which provide a complete picture of the application of the aerodynamic forces to benefit space missions that are operating very close to Earth, as well as contribute to the knowledge of rarefied gas aerodynamics in the lower and middle part of the thermosphere. The research starts by reviewing the current progress of thermosphere science and rarefied gas aerodynamics to construct a high fidelity aerodynamic model for spacecraft operating in the rarefied gas (mainly atomic oxygen) environment in very low Earth orbits (below 450 km) and following by a brief system level analysis of the benefits and challenges for the spacecraft flying lower to Earth. A real spacecraft is also developed to validate of the application of the aerodynamic forces for attitude control. The aspect of the design included in this dissertation focuses mainly on the attitude determination and control system development of satellite. The CubeSat has a generic design with deployable solar panels that can be rotated to control the aerodynamic torques. Based on the common attitude control requirements of spacecraft operating in very low Earth orbits, and the hardware capability of the satellite three novel orbital aerodynamic attitude control strategies are proposed: Energy Optimized B-dot Detumbling into an Aerostable State; Active Orbital Aerodynamic Coarse Pitch/Yaw Control; a 3-axis Orbital Aerodynamic Torques Adaptive Sliding Mode Control. The control performance for each control algorithm is validated numerically in high-fidelity attitude propagators. Knowledge of the thermospheric winds is important as they influence the control performance and the dynamic response of the spacecraft, aerostable designs steering into the thermosphere wind vector. Two novel computational methods to measure the thermospheric wind from the dynamic response of the spacecraft due to aerodynamic forces are proposed. The in-situ measured wind vector benefits the attitude observation in the feedback control systems, which helps to improve the adapting performance and to increase the control accuracy. The proposed novel aerodynamic attitude control algorithms can be adapted for similar spacecraft operating in the very low Earth orbits with modifications to the deployable solar panels or adding movable aerodynamic control surfaces. In addition, this proposed orbital aerodynamic attitude control system works not only in the very low Earth orbits but can also be potentially implemented for spacecraft operating in the rarefied gas region of the atmospheres of other planets.
Subjects/Keywords: 629.132; space mission; CubeSat; Attitude Control; spacecraft; ADCS; rarefied aerodynamics; AOCS
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Hao, Z. (2018). Orbital aerodynamic attitude control for spacecraft. (Doctoral Dissertation). University of Manchester. Retrieved from https://www.research.manchester.ac.uk/portal/en/theses/orbital-aerodynamic-attitude-control-for-spacecraft(b080a1ab-f954-4071-89bd-0d86969aa0ed).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.756900
Chicago Manual of Style (16th Edition):
Hao, Zhou. “Orbital aerodynamic attitude control for spacecraft.” 2018. Doctoral Dissertation, University of Manchester. Accessed March 01, 2021.
https://www.research.manchester.ac.uk/portal/en/theses/orbital-aerodynamic-attitude-control-for-spacecraft(b080a1ab-f954-4071-89bd-0d86969aa0ed).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.756900.
MLA Handbook (7th Edition):
Hao, Zhou. “Orbital aerodynamic attitude control for spacecraft.” 2018. Web. 01 Mar 2021.
Vancouver:
Hao Z. Orbital aerodynamic attitude control for spacecraft. [Internet] [Doctoral dissertation]. University of Manchester; 2018. [cited 2021 Mar 01].
Available from: https://www.research.manchester.ac.uk/portal/en/theses/orbital-aerodynamic-attitude-control-for-spacecraft(b080a1ab-f954-4071-89bd-0d86969aa0ed).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.756900.
Council of Science Editors:
Hao Z. Orbital aerodynamic attitude control for spacecraft. [Doctoral Dissertation]. University of Manchester; 2018. Available from: https://www.research.manchester.ac.uk/portal/en/theses/orbital-aerodynamic-attitude-control-for-spacecraft(b080a1ab-f954-4071-89bd-0d86969aa0ed).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.756900
Utah State University
13.
Schreiner, John N.
A Neural Network Approach to Fault Detection in Spacecraft Attitude Determination and Control Systems.
Degree: MS, Mechanical and Aerospace Engineering, 2015, Utah State University
URL: https://digitalcommons.usu.edu/etd/4164
► This thesis proposes a method of performing fault detection and isolation in spacecraft attitude determination and control systems. The proposed method works by deploying…
(more)
▼ This thesis proposes a method of performing fault detection and isolation in
spacecraft attitude determination and
control systems. The proposed method works by deploying a trained neural network to analyze a set of residuals that are dened such that they encompass the
attitude control, guidance, and
attitude determination subsystems. Eight neural networks were trained using either the resilient backpropagation, Levenberg-Marquardt, or Levenberg-Marquardt with Bayesian regularization training algorithms. The results of each of the neural networks were analyzed to determine the accuracy of the networks with respect to isolating the faulty component or faulty subsystem within the ADCS. The performance of the proposed neural network-based fault detection and isolation method was compared and contrasted with other ADCS FDI methods. The results obtained via simulation showed that the best neural networks employing this method successfully detected the presence of a fault 79% of the time. The faulty subsystem was successfully isolated 75% of the time and the faulty components within the faulty subsystem were isolated 37% of the time.
Advisors/Committee Members: Rees Fullmer, ;.
Subjects/Keywords: Neural Network; Fault Detection; Spacecraft Attitude; Control Systems; Aerospace Engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Schreiner, J. N. (2015). A Neural Network Approach to Fault Detection in Spacecraft Attitude Determination and Control Systems. (Masters Thesis). Utah State University. Retrieved from https://digitalcommons.usu.edu/etd/4164
Chicago Manual of Style (16th Edition):
Schreiner, John N. “A Neural Network Approach to Fault Detection in Spacecraft Attitude Determination and Control Systems.” 2015. Masters Thesis, Utah State University. Accessed March 01, 2021.
https://digitalcommons.usu.edu/etd/4164.
MLA Handbook (7th Edition):
Schreiner, John N. “A Neural Network Approach to Fault Detection in Spacecraft Attitude Determination and Control Systems.” 2015. Web. 01 Mar 2021.
Vancouver:
Schreiner JN. A Neural Network Approach to Fault Detection in Spacecraft Attitude Determination and Control Systems. [Internet] [Masters thesis]. Utah State University; 2015. [cited 2021 Mar 01].
Available from: https://digitalcommons.usu.edu/etd/4164.
Council of Science Editors:
Schreiner JN. A Neural Network Approach to Fault Detection in Spacecraft Attitude Determination and Control Systems. [Masters Thesis]. Utah State University; 2015. Available from: https://digitalcommons.usu.edu/etd/4164
University of Toronto
14.
Binette, Mark Richard.
An Investigation of Nonlinear Control of Spacecraft Attitude.
Degree: 2013, University of Toronto
URL: http://hdl.handle.net/1807/42688
► The design of controllers subject to the nonlinear H-infinity criterion is explored. The plants to be controlled are the attitude motion of spacecraft, subject to…
(more)
▼ 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 some disturbance torque. Two cases are considered: the regulation about an inertially-fixed direction, and an Earth-pointing spacecraft in a circular orbit, subject to the gravity-gradient torque. The spacecraft attitude is described using the modified Rodrigues parameters. A series of controllers are designed using the nonlinear H-infinity control criterion, and are subsequently generated using a Taylor series expansion to approximate solutions of the relevant Hamilton-Jacobi equations. The controllers are compared, using both input-output and initial condition simulations. A proof is used to demonstrate that the linearized controller solves the H-infinity control problem for the inertial pointing problem when describing the plant using the modified Rodrigues parameters.
MAST
Advisors/Committee Members: Damaren, Christopher John, Pavel, Lacra, Aerospace Science and Engineering.
Subjects/Keywords: H-infinity control theory; modified Rodrigues parameters; spacecraft attitude control; control theory; 0538
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
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 March 01, 2021.
http://hdl.handle.net/1807/42688.
MLA Handbook (7th Edition):
Binette, Mark Richard. “An Investigation of Nonlinear Control of Spacecraft Attitude.” 2013. Web. 01 Mar 2021.
Vancouver:
Binette MR. An Investigation of Nonlinear Control of Spacecraft Attitude. [Internet] [Masters thesis]. University of Toronto; 2013. [cited 2021 Mar 01].
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
15.
Fragoso Trigo, G. (author).
Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs.
Degree: 2011, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:ac9a05df-7c33-4dae-9d34-5e667e6168ce
► In the context of the initiative Formation for Atmospheric Science and Technology demonstration (FAST), this dissertation describes the design and comparison of several nonlinear attitude…
(more)
▼ In the context of the initiative Formation for Atmospheric Science and Technology demonstration (FAST), this dissertation describes the design and comparison of several nonlinear attitude controllers for TU Delft’s micro-satellite. The control requirements include robustness against model uncertainties and disturbances. To this end, Backstepping is selected as the base control design for the stability awareness provided and the versatility in rendering the control law robust and adaptive. Five Backstepping schemes are selected for comparison: Standard Static, Static Robust, Integrated Adaptive with tuning functions estimation, Modular Adaptive with nonlinear extended state observation and, finally, Immersion and Invariance Adaptive. The spacecraft model is written using Modified Rodrigues Parameters. Three perturbation sources are considered and applied separately: constant inertia tensor mismatch; saturated reaction wheel; and moving mirror from a payload spectrometer. All perturbations are translated to time-variant disturbance torques. Convergence of the tuning functions estimator to the true disturbance value is proved. The Immersion and Invariance Adaptive Backstepping law is here proved input-to-state stable in case of time-variable perturbation. Command filters are used in all designs allowing the inclusion of magnitude and rate constraints. Simulation reveals similar tracking performances of all controlled systems in a disturbance-free case. In all disturbance scenarios the adaptive laws clearly outperform the static ones. This is especially evident in the presence of a faulty reaction wheel and a moving payload. Sampling time analysis shows higher dependence of the adaptive designs on the control frequency. The Modular Adaptive and the Immersion and Invariance Adaptive Backstepping controllers display the best performances. However, the latter design emerges as, not only the easiest to tune, but also as the one with the most consistent performance.
Control and Simulation
Aerospace Engineering
Advisors/Committee Members: Chu, Q.P. (mentor).
Subjects/Keywords: Spacecraft Attitude Control; Robust Control; Adaptive Control; Backstepping; Immersion and Invariance; Modified Rodrigues Parameters
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
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 (author). “Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs.” 2011. Masters Thesis, Delft University of Technology. Accessed March 01, 2021.
http://resolver.tudelft.nl/uuid:ac9a05df-7c33-4dae-9d34-5e667e6168ce.
MLA Handbook (7th Edition):
Fragoso Trigo, G (author). “Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs.” 2011. Web. 01 Mar 2021.
Vancouver:
Fragoso Trigo G(. Robust and Adaptive Nonlinear Attitude Control of a Spacacraft: A Comparison of Backstepping-based Designs. [Internet] [Masters thesis]. Delft University of Technology; 2011. [cited 2021 Mar 01].
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
University of Toronto
16.
Cotten, Scott Bradley.
Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission.
Degree: 2014, University of Toronto
URL: http://hdl.handle.net/1807/68553
► In the context of space debris mitigation, a major challenge currently facing the space community is the removal of nano and microsatellites from orbit following…
(more)
▼ In the context of space debris mitigation, a major challenge currently facing the space community is the removal of nano and microsatellites from orbit following the completion of their missions. To address this problem, the Space Flight Laboratory has developed the CanX-7 mission; a technology demonstration mission to validate the use of a mechanically deployed drag sail for de-orbiting satellites from low-Earth orbit. This thesis report describes the design, analysis, implementation, and testing of both the attitude determination and control system, and thermal control system for the CanX-7 mission. The attitude determination and control system uses an entirely magnetic solution to meet mission level pointing requirements with a limited set of hardware, and the thermal control system relies primarily on passive control measures to allow the spacecraft to survive the harsh thermal environment in space. Both subsystems are essential to the success of the CanX-7 mission.
M.A.S.
Advisors/Committee Members: Zee, E Robert, Aerospace Science and Engineering.
Subjects/Keywords: Magnetic Attitude Control; Microsatellite Technology; Orbital Debris; Spacecraft Deorbiting; Thermal Control of Space Systems; 0538
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Cotten, S. B. (2014). Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/68553
Chicago Manual of Style (16th Edition):
Cotten, Scott Bradley. “Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission.” 2014. Masters Thesis, University of Toronto. Accessed March 01, 2021.
http://hdl.handle.net/1807/68553.
MLA Handbook (7th Edition):
Cotten, Scott Bradley. “Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission.” 2014. Web. 01 Mar 2021.
Vancouver:
Cotten SB. Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission. [Internet] [Masters thesis]. University of Toronto; 2014. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/1807/68553.
Council of Science Editors:
Cotten SB. Design, Analysis, Implementation, and Testing of the Thermal Control, and Attitude Determination and Control Systems for the CanX-7 Nanosatellite Mission. [Masters Thesis]. University of Toronto; 2014. Available from: http://hdl.handle.net/1807/68553
University of Toronto
17.
Magner, Robert.
Extending the Capabilities of Terrestrial Target Tracking Spacecraft.
Degree: 2018, University of Toronto
URL: http://hdl.handle.net/1807/91365
► 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)
▼ 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 Flight Laboratory will employ novel attitude trajectory generation schemes to achieve high-performance ground target tracking for a wide range of targets, across a wide range of potential orbits. The development of the guidance and control algorithms employed by this platform and their implementation on-board a prototype mission will be presented in detail. In addition, this thesis will present the development of an end-of-life spacecraft deorbit maneuver, and the associated attitude and orbit control challenges. These engineering problems will be discussed as focal points in the broader context of attitude and orbital control system development for microsatellites. Particular attention will be given to the use of modern numerical optimization approaches as a means to achieve robust solutions for complex multi-variable problems.
M.A.S.
Advisors/Committee Members: Zee, Robert E, Liu, Hugh HT, Aerospace Science and Engineering.
Subjects/Keywords: attitude and orbital control systems; deorbit; microsatellites; spacecraft dynamics; target tracking; trajectory planning; 0538
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
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 01, 2021.
http://hdl.handle.net/1807/91365.
MLA Handbook (7th Edition):
Magner, Robert. “Extending the Capabilities of Terrestrial Target Tracking Spacecraft.” 2018. Web. 01 Mar 2021.
Vancouver:
Magner R. Extending the Capabilities of Terrestrial Target Tracking Spacecraft. [Internet] [Masters thesis]. University of Toronto; 2018. [cited 2021 Mar 01].
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
18.
Petersen, Christopher.
Advances in Underactuated Spacecraft Control.
Degree: PhD, Aerospace Engineering, 2016, University of Michigan
URL: http://hdl.handle.net/2027.42/133430
► 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)
▼ 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 underactuated
spacecraft can extend
spacecraft operational life in orbit and improve the robustness of space missions. The novel contributions of the dissertation include the following.
Firstly, switching feedback controllers are developed for the
attitude control of an underactuated
spacecraft equipped with two pairs of thrusters, or two reaction wheels (RWs), or two
control moment gyros (CMGs). The problem is challenging; e.g., even in the zero total angular momentum case, no smooth or even continuous time-invariant feedback law for stabilizing a desired orientation exists. The method exploits the separation of the system into inner-loop base variables and outer-loop fiber variables. The base variables track periodic reference trajectories, the amplitude of which is governed by parameters that are adjusted to induce an appropriate change in the fiber variables towards the desired pointing configuration.
Secondly, nonlinear Model Predictive
Control (MPC) is applied to the
attitude dynamics of an underactuated
spacecraft with two RWs and zero angular momentum. MPC has the remarkable ability to generate
control laws that are discontinuous in the state. By utilizing nonlinear MPC, the obstruction to stabilizability is overcome and
attitude maneuvers can be performed while enforcing constraints.
Thirdly, an unconventional pathway is discussed for recovering the linear controllability of an underactuated
spacecraft with two RWs by accounting for the effects of solar radiation pressure (SRP) in the
spacecraft attitude model. Necessary and sufficient conditions for recovering linear controllability are given, and with linear controllability restored, conventional controllers can be designed for underactuated
spacecraft.
Lastly, two sets of coupled translational and rotational equations of motion for a
spacecraft in a central gravity field are derived. The
spacecraft is assumed to have only internal
attitude actuators and the equations of motion are relative with respect to an equilibrium orbit. Under reasonable assumptions on the
spacecraft configuration and equilibrium orbit, the coupled dynamics are small-time locally controllable (STLC), which opens a path to utilizing conventional
control techniques to move translationally in space by employing
attitude control only.
Advisors/Committee Members: Kolmanovsky, Ilya Vladimir (committee member), Bloch, Anthony M (committee member), Leve, Frederick A (committee member), Girard, Anouck Renee (committee member).
Subjects/Keywords: Spacecraft Dynamics and Control; Underactuated Control; Attitude Control; Coupled Rotational and Translational Relative Motion; Model Predictive Control; Aerospace Engineering; Engineering
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
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 01, 2021.
http://hdl.handle.net/2027.42/133430.
MLA Handbook (7th Edition):
Petersen, Christopher. “Advances in Underactuated Spacecraft Control.” 2016. Web. 01 Mar 2021.
Vancouver:
Petersen C. Advances in Underactuated Spacecraft Control. [Internet] [Doctoral dissertation]. University of Michigan; 2016. [cited 2021 Mar 01].
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
University of Toronto
19.
Vatankhahghadim, Behrad.
Hybrid Magnetic Attitude Control of Spacecraft: Optimality, Passivity, and Stability.
Degree: 2016, University of Toronto
URL: http://hdl.handle.net/1807/73473
► 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)
▼ 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 hybrid linear quadratic regulator formulation, while explicitly accounting for a priori estimates of the disturbances. Previous results on optimal impulse timing are extended to remain valid under disturbance accommodation, and the special case of a multi-orbit mission with repeating impulse patterns is considered.
The passivity-based approach relies on a hybrid and time-varying extension of Kalman-Yakubovich-Popov conditions, and judiciously designs the output dynamics to guarantee passivity of the plant and stability of the closed-loop system subject to sufficiently small disturbances.
Lastly, input/output stability of the disturbance-accommodating controller and Lyapunov stability of the passive controller are studied by introducing a hybrid state transition matrix. Extensions of the classical Floquet theory and its counterpart for inhomogeneous systems provide stability analysis tools for the proposed hybrid controllers.
M.A.S.
Advisors/Committee Members: Damaren, Christopher J., Aerospace Science and Engineering.
Subjects/Keywords: Hybrid Magnetic Attitude Control; Hybrid Stability Analysis; Optimal Control; Passivity-Based Control; Spacecraft Dynamics and Control; 0538
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
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 01, 2021.
http://hdl.handle.net/1807/73473.
MLA Handbook (7th Edition):
Vatankhahghadim, Behrad. “Hybrid Magnetic Attitude Control of Spacecraft: Optimality, Passivity, and Stability.” 2016. Web. 01 Mar 2021.
Vancouver:
Vatankhahghadim B. Hybrid Magnetic Attitude Control of Spacecraft: Optimality, Passivity, and Stability. [Internet] [Masters thesis]. University of Toronto; 2016. [cited 2021 Mar 01].
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
Delft University of Technology
20.
Acquatella, B.P.J. (author).
Robust Nonlinear Spacecraft Attitude Control: An Incremental Backstepping Approach.
Degree: 2011, Delft University of Technology
URL: http://resolver.tudelft.nl/uuid:a56090a3-bbce-404b-8e4b-d0e9050b518a
► In order to meet requirements in terms of robustness, stability, and performance for future generations of advanced attitude control systems, a sensor-based approach using Incremental…
(more)
▼ In order to meet requirements in terms of robustness, stability, and performance for future generations of advanced attitude control systems, a sensor-based approach using Incremental Backstepping control is developed and proposed in this thesis. Assuming full state availability and fast control action, the resulting time-scale separation between the state of the system and the state of the controller allows to consider an incremental form of the attitude dynamics, where backstepping controllers can be designed to achieve stability and convergence with incremental inputs. This results in integral-control action where information of angular acceleration and actuator output measurements is required. The robustness and the full potential of Incremental Backstepping are evidenced in face of external disturbances, uncertainties, and unknown parameters. External disturbances are well suppressed in contrast with conventional backstepping and Lyapunov-based (non)linear controllers. Furthermore, the attitude stabilization results to be insensitive to parametric uncertainties and robust against model uncertainties. However, this comes at the expense of higher control effort. Moreover, with the influence of model and parametric uncertainties the resulting closed-loop dynamic performance can be better accounted for by studying the convergence and stability properties in terms of Lyapunov theory. This methodology results in a simple, yet effective, family of robust nonlinear attitude controllers which aims to meet demanding requirements in terms of robustness, stability and performance, which in turn, close the gap towards the development of future advanced attitude control systems.
Dynamics and Control of Aerospace Vehicles
Control and Operations (C&O) - Control and Simulation Division (C&S)
Aerospace Engineering
Advisors/Committee Members: Chu, Q.P. (mentor), Falkena, W. (mentor), Van Kampen, E. (mentor).
Subjects/Keywords: Spacecraft Attitude Control; Nonlinear Control; Backstepping; Incremental Backstepping; Incremental Nonlinear Dynamic Inversion; Lyapunov-based control; Modified Rodrigues Parameters
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Acquatella, B. P. J. (. (2011). Robust Nonlinear Spacecraft Attitude Control: An Incremental Backstepping Approach. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:a56090a3-bbce-404b-8e4b-d0e9050b518a
Chicago Manual of Style (16th Edition):
Acquatella, B P J (author). “Robust Nonlinear Spacecraft Attitude Control: An Incremental Backstepping Approach.” 2011. Masters Thesis, Delft University of Technology. Accessed March 01, 2021.
http://resolver.tudelft.nl/uuid:a56090a3-bbce-404b-8e4b-d0e9050b518a.
MLA Handbook (7th Edition):
Acquatella, B P J (author). “Robust Nonlinear Spacecraft Attitude Control: An Incremental Backstepping Approach.” 2011. Web. 01 Mar 2021.
Vancouver:
Acquatella BPJ(. Robust Nonlinear Spacecraft Attitude Control: An Incremental Backstepping Approach. [Internet] [Masters thesis]. Delft University of Technology; 2011. [cited 2021 Mar 01].
Available from: http://resolver.tudelft.nl/uuid:a56090a3-bbce-404b-8e4b-d0e9050b518a.
Council of Science Editors:
Acquatella BPJ(. Robust Nonlinear Spacecraft Attitude Control: An Incremental Backstepping Approach. [Masters Thesis]. Delft University of Technology; 2011. Available from: http://resolver.tudelft.nl/uuid:a56090a3-bbce-404b-8e4b-d0e9050b518a
Virginia Tech
21.
Lennox, Scott Evan.
Coupled Attitude And Orbital Control System Using Spacecraft Simulators.
Degree: MS, Aerospace and Ocean Engineering, 2004, Virginia Tech
URL: http://hdl.handle.net/10919/10003
► Translational and rotational motion are coupled for spacecraft performing formation flying missions. This motion is coupled because orbital control is dependent on the spacecraft attitude…
(more)
▼ Translational and rotational motion are coupled for
spacecraft performing formation flying missions. This motion is coupled because orbital
control is dependent on the
spacecraft attitude for vectored thrust. Formation flying
spacecraft have a limited mass and volume for propulsion systems. We want to maximize the efficiency of the
spacecraft, which leads to minimizing the error introduced by thrusting in the wrong direction. This thrust direction error leads to the need for a coupled
attitude and orbital
control strategy. In this thesis a coupled
control system is developed using a nonlinear Lyapunov
attitude controller and a nonlinear Lyapunov-based orbital controller. A nonlinear Lyapunov
attitude controller is presented for a
spacecraft with three-axis momentum wheel
control. The nonlinear Lyapunov-based orbital controller is combined with a mean motion
control strategy to provide a globally asymptotically stable controller. The
attitude and orbit
control laws are verified separately using numerical simulation, and then are integrated into a coupled
control strategy. The coupled system simulations verify that the coupled
control strategy is able to correct for an initial relative position error between two
spacecraft.
Advisors/Committee Members: Hall, Christopher D. (committeechair), Woolsey, Craig A. (committee member), Schaub, Hanspeter (committee member).
Subjects/Keywords: Orbital Control; Spacecraft; Attitude Control; Coupled Control
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Lennox, S. E. (2004). Coupled Attitude And Orbital Control System Using Spacecraft Simulators. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/10003
Chicago Manual of Style (16th Edition):
Lennox, Scott Evan. “Coupled Attitude And Orbital Control System Using Spacecraft Simulators.” 2004. Masters Thesis, Virginia Tech. Accessed March 01, 2021.
http://hdl.handle.net/10919/10003.
MLA Handbook (7th Edition):
Lennox, Scott Evan. “Coupled Attitude And Orbital Control System Using Spacecraft Simulators.” 2004. Web. 01 Mar 2021.
Vancouver:
Lennox SE. Coupled Attitude And Orbital Control System Using Spacecraft Simulators. [Internet] [Masters thesis]. Virginia Tech; 2004. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/10919/10003.
Council of Science Editors:
Lennox SE. Coupled Attitude And Orbital Control System Using Spacecraft Simulators. [Masters Thesis]. Virginia Tech; 2004. Available from: http://hdl.handle.net/10919/10003
University of Texas – Austin
22.
Srikant, Sukumar.
Persistence filters for controller and observer design in singular gain systems.
Degree: PhD, Aerospace Engineering, 2011, University of Texas – Austin
URL: http://hdl.handle.net/2152/ETD-UT-2011-05-3118
► This dissertation develops a general framework for designing stabilizing feedback controllers and observers for dynamics with state/time dependent gains on the control signals and measured…
(more)
▼ This dissertation develops a general framework for designing stabilizing feedback controllers and observers for dynamics with state/time dependent gains on the
control signals and measured outputs. These gains have potential singularity periods but satisfy a technically non-trivial condition referred to as persistence of excitation. A persistence filter design constitutes the primary theoretical innovation of this work around which the controller and observer development is centered. Application areas of singular gain systems considered in this study include robotics, biomechanics, intelligent structures and spacecrafts.
Several representative problems involving singular, time-dependent gains are addressed. The specific contributions of this dissertation are outlined as follows: (i) a stabilizing feedback for linear, single-input systems with time-varying, singular
control scaling is designed that allows arbitrary exponential convergence rate for the closed-loop dynamics. An adaptive
control generalization of this result allows asymptotic convergence in presence of unknown plant parameters. An extension to a special, single-input nonlinear system in the controller canonical form is also proposed. It is proven that this
control design results in bounded tracking error signals for a trajectory tracking objective; (ii) observer design for linear, single-output systems with time-varying, singular measurement gains is considered. A persistence filter similar in structure to the
control counterpart aids an observer design that guarantees exponential state reconstruction with arbitrary convergence rates; (iii) the observer and controller designs are combined to obtain an exponentially stabilizing output feedback controller for linear, single-input, single-output dynamics with singular gains on both the
control and measurements. A novel separation property is established as a consequence. The construction motivates applications to stabilization with reversible transducers which can switch between sensor and actuator modes. The results are verified on two illustrative applications, vibration
control using piezoelectric devices and inverted pendulum stabilization with a DC motor. The linear result is further generalized to include state dependent gains; (iv) application of the persistence filter theory to
spacecraft attitude stabilization using intermittent actuation is explored. The intermittence is characterized by a time-varying, periodically singular
control gain. A nonlinear persistence filter allows construction of an exponentially stabilizing controller and simulations verify convergence with intermittent actuation where conventional proportional-derivative
control fails; (v) a stabilization result for a special multi-input, linear system with time-varying matrix
control gains is presented. The matrix gain is assumed to be diagonal but allows fewer controls than states
subject to a controllability assumption in absence of the singular gain matrix. The single-input adaptive
control results are shown to extend to the…
Advisors/Committee Members: Akella, Maruthi Ram, 1972- (advisor), Lightsey, E G. (committee member), Bennighof, Jeffrey K. (committee member), Hull, David G. (committee member), Griffin, Lisa (committee member).
Subjects/Keywords: Feedback control systems; Magnetic actuation; Magnetic torquers; Feedback controllers; Adaptive control; Singular gain systems; Intermittent control; Spacecraft attitude stabilization; Space vehicles
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Srikant, S. (2011). Persistence filters for controller and observer design in singular gain systems. (Doctoral Dissertation). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/ETD-UT-2011-05-3118
Chicago Manual of Style (16th Edition):
Srikant, Sukumar. “Persistence filters for controller and observer design in singular gain systems.” 2011. Doctoral Dissertation, University of Texas – Austin. Accessed March 01, 2021.
http://hdl.handle.net/2152/ETD-UT-2011-05-3118.
MLA Handbook (7th Edition):
Srikant, Sukumar. “Persistence filters for controller and observer design in singular gain systems.” 2011. Web. 01 Mar 2021.
Vancouver:
Srikant S. Persistence filters for controller and observer design in singular gain systems. [Internet] [Doctoral dissertation]. University of Texas – Austin; 2011. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/2152/ETD-UT-2011-05-3118.
Council of Science Editors:
Srikant S. Persistence filters for controller and observer design in singular gain systems. [Doctoral Dissertation]. University of Texas – Austin; 2011. Available from: http://hdl.handle.net/2152/ETD-UT-2011-05-3118
University of Colorado
23.
Stevenson, Daan.
Remote Spacecraft Attitude Control by Coulomb Charging.
Degree: PhD, Aerospace Engineering Sciences, 2015, University of Colorado
URL: https://scholar.colorado.edu/asen_gradetds/94
► 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)
▼ 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 orbits experience no natural means of decay. The ability to rendezvous with these derelict satellites would enable active debris removal by servicing or repositioning missions, but docking procedures are generally inhibited by the large rotational momenta of uncontrolled satellites. Therefore, a contactless means of reducing the rotation rate of objects in the space environment is desired. This dissertation investigates the viability of Coulomb charging to achieve such remote
spacecraft attitude control. If a servicing craft imposes absolute electric potentials on a nearby nonspherical debris object, it will impart electrostatic torques that can be used to gradually arrest the object's rotation.
In order to simulate the relative motion of charged
spacecraft with complex geometries, accurate but rapid knowledge of the Coulomb interactions is required. To this end, a new electrostatic force model called the Multi-Sphere Method (MSM) is developed. All aspects of the Coulomb de-spin concept are extensively analyzed and simulated using a system with simplified geometries and one dimensional rotation. First, appropriate
control algorithms are developed to ensure that the nonlinear Coulomb torques arrest the rotation with guaranteed stability. Moreover, the complex interaction of the
spacecraft with the plasma environment and charge
control beams is modeled to determine what hardware requirements are necessary to achieve the desired electric potential levels. Lastly, the
attitude dynamics and feedback
control development is validated experimentally using a scaled down terrestrial testbed. High voltage power supplies
control the potential on two nearby conductors, a stationary sphere and a freely rotating cylinder. The nonlinear feedback
control algorithms developed above are implemented to achieve rotation rate and absolute
attitude control. Collectively, these studies decisively validate the feasibility of Coulomb charging for remote
spacecraft attitude control.
Advisors/Committee Members: Hanspeter Schaub, Webster Cash, Brandon Jones, Daniel Moorer, Zoltan Sternovsky.
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
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Stevenson, D. (2015). Remote Spacecraft Attitude Control by Coulomb Charging. (Doctoral Dissertation). University of Colorado. Retrieved from https://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 01, 2021.
https://scholar.colorado.edu/asen_gradetds/94.
MLA Handbook (7th Edition):
Stevenson, Daan. “Remote Spacecraft Attitude Control by Coulomb Charging.” 2015. Web. 01 Mar 2021.
Vancouver:
Stevenson D. Remote Spacecraft Attitude Control by Coulomb Charging. [Internet] [Doctoral dissertation]. University of Colorado; 2015. [cited 2021 Mar 01].
Available from: https://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: https://scholar.colorado.edu/asen_gradetds/94
Virginia Tech
24.
Skelton, Claude Eugene II.
Mixed Control Moment Gyro and Momentum Wheel Attitude Control Strategies.
Degree: MS, Aerospace and Ocean Engineering, 2003, Virginia Tech
URL: http://hdl.handle.net/10919/9677
► Attitude control laws that use control moment gyros (CMGs) and momentum wheels are derived with nonlinear techniques. The control laws command the CMGs to provide…
(more)
▼ Attitude control laws that use
control moment gyros (CMGs) and momentum wheels are derived with nonlinear techniques. The
control laws command the CMGs to provide rapid angular acceleration and the momentum wheels to reject tracking and initial condition errors. Numerical simulations of derived
control laws are compared. A trend analysis is performed to examine the benefits of the derived controllers. We describe the design of a CMG built using commercial off-the-shelf (COTS) equipment. A mixed
attitude control strategy is implemented on the
spacecraft simulator at Virginia Tech.
Advisors/Committee Members: Hall, Christopher D. (committeechair), Woolsey, Craig A. (committee member), Lutze, Frederick H. Jr. (committee member).
Subjects/Keywords: momentum wheel; control moment gyro; spacecraft simulator; attitude control
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Skelton, C. E. I. (2003). Mixed Control Moment Gyro and Momentum Wheel Attitude Control Strategies. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/9677
Chicago Manual of Style (16th Edition):
Skelton, Claude Eugene II. “Mixed Control Moment Gyro and Momentum Wheel Attitude Control Strategies.” 2003. Masters Thesis, Virginia Tech. Accessed March 01, 2021.
http://hdl.handle.net/10919/9677.
MLA Handbook (7th Edition):
Skelton, Claude Eugene II. “Mixed Control Moment Gyro and Momentum Wheel Attitude Control Strategies.” 2003. Web. 01 Mar 2021.
Vancouver:
Skelton CEI. Mixed Control Moment Gyro and Momentum Wheel Attitude Control Strategies. [Internet] [Masters thesis]. Virginia Tech; 2003. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/10919/9677.
Council of Science Editors:
Skelton CEI. Mixed Control Moment Gyro and Momentum Wheel Attitude Control Strategies. [Masters Thesis]. Virginia Tech; 2003. Available from: http://hdl.handle.net/10919/9677
University of Texas – Austin
25.
-7636-3233.
An attitude determination and control system for small satellites.
Degree: MSin Engineering, Aerospace Engineering, 2015, University of Texas – Austin
URL: http://hdl.handle.net/2152/31715
► A flexible, robust attitude determination and control (ADC) system is presented for small satellite platforms. Using commercial-off-the-shelf sensors, reaction wheels, and magnetorquers which fit within…
(more)
▼ A flexible, robust
attitude determination and
control (ADC) system is presented for small satellite platforms. Using commercial-off-the-shelf sensors, reaction wheels, and magnetorquers which fit within the 3U CubeSat form factor, the system delivers arc-minute pointing precision. The ADC system includes a multiplicative extended Kalman filter for
attitude determination and a slew rate controller that acquires a view of the Sun for navigation purposes. A pointing system is developed that includes a choice of two pointing controllers – a proportional derivative controller and a nonlinear sliding mode controller. This system can reorient the
spacecraft to satisfy a variety of mission objectives, but it does not enforce
attitude constraints. A constrained
attitude guidance system that can enforce an arbitrary set of
attitude constraints is then proposed as an improvement upon the unconstrained pointing system. The momentum stored by the reaction wheels is managed using magnetorquers to prevent wheel saturation. The system was thoroughly tested in realistic software- and hardware-in-the-loop simulations that included environmental disturbances, parameter uncertainty, actuator dynamics, and sensor bias and noise.
Advisors/Committee Members: Fowler, Wallace T. (advisor), Lightsey, E. Glenn (advisor).
Subjects/Keywords: Attitude; Determination; Control; Estimation; CubeSat; Satellite; ADC; Guidance; Convex optimization; Constrained attitude guidance; Attitude constraint; Texas Spacecraft Laboratory; TSL; Bevo-2; ARMADILLO
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
-7636-3233. (2015). An attitude determination and control system for small satellites. (Masters Thesis). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/31715
Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
Chicago Manual of Style (16th Edition):
-7636-3233. “An attitude determination and control system for small satellites.” 2015. Masters Thesis, University of Texas – Austin. Accessed March 01, 2021.
http://hdl.handle.net/2152/31715.
Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
MLA Handbook (7th Edition):
-7636-3233. “An attitude determination and control system for small satellites.” 2015. Web. 01 Mar 2021.
Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
Vancouver:
-7636-3233. An attitude determination and control system for small satellites. [Internet] [Masters thesis]. University of Texas – Austin; 2015. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/2152/31715.
Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
Council of Science Editors:
-7636-3233. An attitude determination and control system for small satellites. [Masters Thesis]. University of Texas – Austin; 2015. Available from: http://hdl.handle.net/2152/31715
Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete
University of Michigan
26.
Rui, Chunlei.
Dynamics and nonlinear attitude control of multibody space systems.
Degree: PhD, Applied Sciences, 1997, University of Michigan
URL: http://hdl.handle.net/2027.42/130814
► In this dissertation, we study dynamics and attitude control problems for a multibody system in space. The key feature of this work is the systematic…
(more)
▼ In this dissertation, we study dynamics and
attitude control problems for a multibody system in space. The key feature of this work is the systematic use of shape changes as three dimensional
attitude controls.
Control models are identified for a general class of multibody space systems that are controlled by thrusters, reaction wheels, and/or joint actuators. The important role of shape change in
attitude maneuvers for a multibody space system is identified and shape change is recognized as a means of
attitude control. Formulas that quantify three dimensional
attitude changes induced by periodic shape changes, rotation of reaction wheels and nonzero angular momentum are developed. The formulas prove fundamental for development of numerous
attitude control algorithms. Explicit construction procedures are developed for shape changes that accomplish a desired three dimensional reconfiguration of a free-floating multibody space system with zero angular momentum with prescribed accuracy. The
control computation involves evaluation of certain Lie brackets and solution of a simple system of algebraic equations. Explicit construction procedures are developed for shape changes that accomplish a desired three dimensional reorientation of a free-floating multibody space system with constant nonzero angular momentum with prescribed accuracy.
Control algorithms are provided for reorientation of a multibody space system to one of its relative equilibria. Explicit
control algorithms are developed for reaction wheel and shape changes that accomplish a desired three dimensional reorientation for a
spacecraft system containing a single reaction wheel and a single movable appendage. Characterization of shape changes that enhance effectiveness of reaction wheels and joint actuators is given, and
control algorithms are provided for effective simultaneous
attitude changes and shape changes. Feedback
attitude control laws are developed for three dimensional
attitude maneuvers of a multibody space system.
Advisors/Committee Members: McClamroch, N. H. (advisor).
Subjects/Keywords: Attitude; Dynamics; Multibody; Nonlinear Control; Space; Spacecraft; Systems
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Rui, C. (1997). Dynamics and nonlinear attitude control of multibody space systems. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/130814
Chicago Manual of Style (16th Edition):
Rui, Chunlei. “Dynamics and nonlinear attitude control of multibody space systems.” 1997. Doctoral Dissertation, University of Michigan. Accessed March 01, 2021.
http://hdl.handle.net/2027.42/130814.
MLA Handbook (7th Edition):
Rui, Chunlei. “Dynamics and nonlinear attitude control of multibody space systems.” 1997. Web. 01 Mar 2021.
Vancouver:
Rui C. Dynamics and nonlinear attitude control of multibody space systems. [Internet] [Doctoral dissertation]. University of Michigan; 1997. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/2027.42/130814.
Council of Science Editors:
Rui C. Dynamics and nonlinear attitude control of multibody space systems. [Doctoral Dissertation]. University of Michigan; 1997. Available from: http://hdl.handle.net/2027.42/130814
University of Illinois – Urbana-Champaign
27.
Haddox, Patrick.
A novel magnetic field approach to simulate spacecraft attitude determination and control.
Degree: MS, 4048, 2014, University of Illinois – Urbana-Champaign
URL: http://hdl.handle.net/2142/49696
► The University of Illinois is developing a CubeSat bus, known as IlliniSat-2, which will be capable of achieving 3-axis attitude control via magnetic torque coils…
(more)
▼ The University of Illinois is developing a CubeSat bus, known as IlliniSat-2, which will be capable of achieving 3-axis
attitude control via magnetic torque coils and
attitude determination via Kalman-filtered magnetometer data with an optional Sun vector measurement. This innovative new
attitude determination and
control (ADC) method is more sophisticated than those traditionally employed on CubeSats and will require extensive pre-flight testing to ensure that IlliniSat-2 functions properly after it is launched. To accommodate such testing, a hardware-in-the-loop ADC simulation suite, known as CubeSim, is being developed. CubeSim uses a large triaxial Helmholtz coil, known as the HC3, to dynamically manipulate the magnetic field around a CubeSat to simulate an orbital environment. In the case of an IlliniSat-2 bus, the HC3 testbed allows the CubeSat to determine its
attitude in real-time. CubeSim will also receive
control feedback from the CubeSat and update the simulated
attitude accordingly. This thesis will discuss the development of CubeSim, including the theory and design of the HC3 and the associated software interfaces. Results from initial simulations and testing will be presented and the path for future work will be discussed.
Advisors/Committee Members: Coverstone, Victoria L. (advisor).
Subjects/Keywords: attitude; determination; control; magnetic field; Helmholtz coil; Helmholtz cage; cubesat; nanosatellite; satellite; spacecraft; systems toolkit (STK); LabVIEW
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Haddox, P. (2014). A novel magnetic field approach to simulate spacecraft attitude determination and control. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/49696
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):
Haddox, Patrick. “A novel magnetic field approach to simulate spacecraft attitude determination and control.” 2014. Thesis, University of Illinois – Urbana-Champaign. Accessed March 01, 2021.
http://hdl.handle.net/2142/49696.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
MLA Handbook (7th Edition):
Haddox, Patrick. “A novel magnetic field approach to simulate spacecraft attitude determination and control.” 2014. Web. 01 Mar 2021.
Vancouver:
Haddox P. A novel magnetic field approach to simulate spacecraft attitude determination and control. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2014. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/2142/49696.
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Council of Science Editors:
Haddox P. A novel magnetic field approach to simulate spacecraft attitude determination and control. [Thesis]. University of Illinois – Urbana-Champaign; 2014. Available from: http://hdl.handle.net/2142/49696
Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation
Virginia Tech
28.
Makovec, Kristin Lynne.
A Nonlinear Magnetic Controller for Three-Axis Stability of Nanosatellites.
Degree: MS, Aerospace and Ocean Engineering, 2001, Virginia Tech
URL: http://hdl.handle.net/10919/34131
► The problem of magnetic control for three-axis stability of a spacecraft is examined. Two controllers, a proportional-derivative controller and a constant coefficient linear quadratic regulator,…
(more)
▼ The problem of magnetic
control for three-axis stability of a
spacecraft is examined. Two
controllers, a proportional-derivative controller and a constant coefficient linear quadratic
regulator, are applied to the system of equations describing the motion of the
spacecraft.
The stability of each is checked for different
spacecraft configurations through simulations,
and the results for gravity-gradient stable and non gravity-gradient stable
spacecraft are
compared. An optimization technique is implemented in an attempt to obtain the best
performance from the controller. For every
spacecraft configuration, a set of gains can be
chosen for implementation in the controller that stabilizes the linear and nonlinear equations of motion for the
spacecraft.
Advisors/Committee Members: Hall, Christopher D. (committeechair), Lutze, Frederick H. Jr. (committee member), Kasarda, Mary E. F. (committee member).
Subjects/Keywords: Spacecraft Attitude Dynamics; Magnetic Control; Three-Axis Stability
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Makovec, K. L. (2001). A Nonlinear Magnetic Controller for Three-Axis Stability of Nanosatellites. (Masters Thesis). Virginia Tech. Retrieved from http://hdl.handle.net/10919/34131
Chicago Manual of Style (16th Edition):
Makovec, Kristin Lynne. “A Nonlinear Magnetic Controller for Three-Axis Stability of Nanosatellites.” 2001. Masters Thesis, Virginia Tech. Accessed March 01, 2021.
http://hdl.handle.net/10919/34131.
MLA Handbook (7th Edition):
Makovec, Kristin Lynne. “A Nonlinear Magnetic Controller for Three-Axis Stability of Nanosatellites.” 2001. Web. 01 Mar 2021.
Vancouver:
Makovec KL. A Nonlinear Magnetic Controller for Three-Axis Stability of Nanosatellites. [Internet] [Masters thesis]. Virginia Tech; 2001. [cited 2021 Mar 01].
Available from: http://hdl.handle.net/10919/34131.
Council of Science Editors:
Makovec KL. A Nonlinear Magnetic Controller for Three-Axis Stability of Nanosatellites. [Masters Thesis]. Virginia Tech; 2001. Available from: http://hdl.handle.net/10919/34131
University of Florida
29.
Leve, Frederick Aaron.
Development of the Spacecraft Orientation Buoyancy Experimental Kiosk.
Degree: MS, Aerospace Engineering - Mechanical and Aerospace Engineering, 2009, University of Florida
URL: https://ufdc.ufl.edu/UFE0022280
► DEVELOPMENT OF THE SPACECRAFT ORIENTATION BUOYANCY EXPERIMENTAL KIOSK TESTBED Most satellites are unique and therefore usually take 10 to 15 years to design, fabricate, test,…
(more)
▼ DEVELOPMENT OF THE
SPACECRAFT ORIENTATION BUOYANCY EXPERIMENTAL KIOSK TESTBED Most satellites are unique and therefore usually take 10 to 15 years to design, fabricate, test, and finally launch. To expedite future advances in space technology, setting standards in terms of ?black-boxed? subsystems and interfaces, drastically reduces the time and long term costs needed to complete these tasks. What is meant by ?black-boxed? is a stand alone subsystem that is adaptable enough to work with any other subsystems without alteration. Government organizations such as the Department of Defense?s (DoD?s) Operationally Responsive Space (ORS) office take these tasks into consideration and look to change this pattern by expediting the processes of design, fabrication, test, evaluation, and launch. To accomplish these tasks, smallsats which range from 1 to 1000 kg in mass, are considered for their cheaper platforms and launch costs. With utilization of smallsats of the pico- (0.1-1 kg), nano- (1 to 10 kg), and micro-classes (10-100 kg) for space missions, obstacles occur in terms of power, mass, and volume constraints. Many of these same smallsats obstacles relate to the
attitude control system (ACS). Despite these obstacles for many space missions, small satellites must be held to the same pointing requirements as their larger counterparts to be of use. To compensate for these obstacles while maintaining close pointing requirements, innovations in
attitude control actuators and determination sensors that satisfy these constraints need to be developed. An excellent choice for
attitude control actuators of smallsats are those of the flywheel sort known as zero-momentum and momentum bias actuators. These actuators have the ability to perform precision
attitude maneuvers without use of propellant. There are two classes of flywheel
attitude control actuators that are used in satellites, reaction/momentum wheels (RWs/MWs) and
control moment gyroscopes (CMGs). Due to the scarcity of CMGs available for small satellites below the micro-class, RWs are presently utilized. An analysis completed in this thesis shows that although the current state-of-the-art CMGs are too massive to fit inside smallsats, the performance relationships in terms of output torque per mass and input power are more favorable than that for RWs. This analysis is an additional motivation for the research in this thesis, which is carried out on the premise that an ACS consisting of single-gimbal
control moment gyroscopes (SGCMGs) can meet the performance requirements providing rapid-retargeting and precision-pointing (R2P2) for smallsats while enduring their power, mass, and volume constraints. To further test this premise the topic of this thesis is the development of a ground based SGCMG testbed known as
Spacecraft Orientation Buoyancy Experimental Kiosk (SOBEK) was developed to validate the utility of using SGCMGs for smallsat
attitude control. The thesis justifies the reasons for using SGCMGs on SOBEK, discusses the
spacecraft and actuator dynamics and kinematics…
Advisors/Committee Members: Fitz-Coy, Norman G. (committee chair), Wiens, Gloria J. (committee member), Dixon, Warren E. (committee member).
Subjects/Keywords: Angular momentum; Artificial satellites; Attitude control; Flywheels; Gimbals; Momentum; Quaternions; Simulations; Spacecraft; Torque; attitude, control, reaction, satellite, spacecraft, testbed
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Leve, F. A. (2009). Development of the Spacecraft Orientation Buoyancy Experimental Kiosk. (Masters Thesis). University of Florida. Retrieved from https://ufdc.ufl.edu/UFE0022280
Chicago Manual of Style (16th Edition):
Leve, Frederick Aaron. “Development of the Spacecraft Orientation Buoyancy Experimental Kiosk.” 2009. Masters Thesis, University of Florida. Accessed March 01, 2021.
https://ufdc.ufl.edu/UFE0022280.
MLA Handbook (7th Edition):
Leve, Frederick Aaron. “Development of the Spacecraft Orientation Buoyancy Experimental Kiosk.” 2009. Web. 01 Mar 2021.
Vancouver:
Leve FA. Development of the Spacecraft Orientation Buoyancy Experimental Kiosk. [Internet] [Masters thesis]. University of Florida; 2009. [cited 2021 Mar 01].
Available from: https://ufdc.ufl.edu/UFE0022280.
Council of Science Editors:
Leve FA. Development of the Spacecraft Orientation Buoyancy Experimental Kiosk. [Masters Thesis]. University of Florida; 2009. Available from: https://ufdc.ufl.edu/UFE0022280
30.
Pan, Hejia.
INTEGRATED OPTIMAL AND ROBUST CONTROL OF SPACECRAFT IN PROXIMITY OPERATIONS.
Degree: PhD, Aerospace Engineering, 2011, Mississippi State University
URL: http://sun.library.msstate.edu/ETD-db/theses/available/etd-10272011-115726/
;
► With the rapid growth of space activities and advancement of aerospace science and technology, many autonomous space missions have been proliferating in recent decades.…
(more)
▼ With the rapid growth of space activities and advancement of aerospace science
and technology, many autonomous space missions have been proliferating in recent
decades.
Control of
spacecraft in proximity operations is of great importance to
accomplish these missions. The research in this dissertation aims to provide a precise,
efficient, optimal, and robust controller to ensure successful
spacecraft proximity
operations. This is a challenging
control task since the problem involves highly nonlinear
dynamics including translational motion, rotational motion, and flexible structure
deformation and vibration. In addition, uncertainties in the system modeling parameters
and disturbances make the precise
control more difficult. Four
control design approaches
are integrated to solve this challenging problem. The first approach is to consider the
spacecraft rigid body translational and rotational dynamics together with the flexible
motion in one unified optimal
control framework so that the overall system performance
and constraints can be addressed in one optimization process. The second approach is to
formulate the robust
control objectives into the optimal
control cost function and prove
the equivalency between the robust stabilization problem and the transformed optimal
control problem. The third approach is to employ the è-D technique, a novel optimal
control method that is based on a perturbation solution to the Hamilton-Jacobi-Bellman
equation, to solve the nonlinear optimal
control problem obtained from the indirect robust
control formulation. The resultant optimal
control law can be obtained in closed-form,
and thus facilitates the onboard implementation. The integration of these three
approaches is called the integrated indirect robust
control scheme. The fourth approach is
to use the inverse optimal adaptive
control method combined with the indirect robust
control scheme to alleviate the conservativeness of the indirect robust
control scheme by
using online parameter estimation such that adaptive, robust, and optimal properties can
all be achieved.
To show the effectiveness of the proposed
control approaches, six degree-offreedom
spacecraft proximity operation simulation is conducted and demonstrates
satisfying performance under various uncertainties and disturbances.
Advisors/Committee Members: Ming Xin (chair), Keith Koenig (committee member), Yang Cheng (committee member), Burak Eksioglu (committee member), Randolph F. Follett (committee member).
Subjects/Keywords: Robust Control; Attitude Control; Nonlinear Systems; Spacecraft; Optimal Control
…reviews several adaptive control methods in spacecraft attitude tracking with standard
model… …framework for spacecraft attitude control problem is presented
in [37]. After proposing… …spacecraft rotational motion
Attitude tracking control problem has been studied in many works [… …29, 37, 90].
The spacecraft attitude control problem is to find a feedback control… …SDRE)
technique is employed to control the position and attitude of a spacecraft…
Record Details
Similar Records
Cite
Share »
Record Details
Similar Records
Cite
« Share
❌
APA ·
Chicago ·
MLA ·
Vancouver ·
CSE |
Export
to Zotero / EndNote / Reference
Manager
APA (6th Edition):
Pan, H. (2011). INTEGRATED OPTIMAL AND ROBUST CONTROL OF SPACECRAFT IN PROXIMITY OPERATIONS. (Doctoral Dissertation). Mississippi State University. Retrieved from http://sun.library.msstate.edu/ETD-db/theses/available/etd-10272011-115726/ ;
Chicago Manual of Style (16th Edition):
Pan, Hejia. “INTEGRATED OPTIMAL AND ROBUST CONTROL OF SPACECRAFT IN PROXIMITY OPERATIONS.” 2011. Doctoral Dissertation, Mississippi State University. Accessed March 01, 2021.
http://sun.library.msstate.edu/ETD-db/theses/available/etd-10272011-115726/ ;.
MLA Handbook (7th Edition):
Pan, Hejia. “INTEGRATED OPTIMAL AND ROBUST CONTROL OF SPACECRAFT IN PROXIMITY OPERATIONS.” 2011. Web. 01 Mar 2021.
Vancouver:
Pan H. INTEGRATED OPTIMAL AND ROBUST CONTROL OF SPACECRAFT IN PROXIMITY OPERATIONS. [Internet] [Doctoral dissertation]. Mississippi State University; 2011. [cited 2021 Mar 01].
Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-10272011-115726/ ;.
Council of Science Editors:
Pan H. INTEGRATED OPTIMAL AND ROBUST CONTROL OF SPACECRAFT IN PROXIMITY OPERATIONS. [Doctoral Dissertation]. Mississippi State University; 2011. Available from: http://sun.library.msstate.edu/ETD-db/theses/available/etd-10272011-115726/ ;
◁ [1] [2] ▶
. 
Open Access Theses and Dissertations
