Publications
2017 |
Jewison, Christopher Michael Guidance and Control for Multi-stage Rendezvous and Docking Operations in the Presence of Uncertainty PhD Thesis 2017. @phdthesis{Jewison2017, title = {Guidance and Control for Multi-stage Rendezvous and Docking Operations in the Presence of Uncertainty}, author = {Christopher Michael Jewison}, year = {2017}, date = {2017-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
Setterfield, Timothy P On-Orbit Inspection of a Rotating Object Using a Moving Observer PhD Thesis 2017. @phdthesis{Setterfield2017, title = {On-Orbit Inspection of a Rotating Object Using a Moving Observer}, author = {Timothy P Setterfield}, year = {2017}, date = {2017-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
Sternberg, David Charles Optimal Docking to Tumbling Objects with Uncertain Properties By PhD Thesis 2017. @phdthesis{Sternberg2017a, title = {Optimal Docking to Tumbling Objects with Uncertain Properties By}, author = {David Charles Sternberg}, year = {2017}, date = {2017-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
2016 |
James, Jillian Development of a Verification and Validation Framework for Autonomous Soft-Docking of Spacecraft with Uncertain Dynamic Properties PhD Thesis 2016. @phdthesis{jamesDevelopmentVerificationValidation2016, title = {Development of a Verification and Validation Framework for Autonomous Soft-Docking of Spacecraft with Uncertain Dynamic Properties}, author = {Jillian James}, year = {2016}, date = {2016-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
2015 |
Miller, Duncan Lee Development of Resource-Constrained Sensors and Actuators for In-Space Satellite Docking and Servicing PhD Thesis 2015, ISSN: 1098-6596. Abstract | BibTeX | Tags: icle, ★ @phdthesis{millerDevelopmentResourceConstrainedSensors2015, title = {Development of Resource-Constrained Sensors and Actuators for In-Space Satellite Docking and Servicing}, author = {Duncan Lee Miller}, issn = {1098-6596}, year = {2015}, date = {2015-01-01}, number = {June}, abstract = {applicability for this approach.}, keywords = {icle, ★}, pubstate = {published}, tppubtype = {phdthesis} } applicability for this approach. |
2014 |
Jewison, Christopher Michael Reconfigurable Thruster Selection Algorithms for Aggregative Spacecraft Systems PhD Thesis 2014. @phdthesis{Jewison2014, title = {Reconfigurable Thruster Selection Algorithms for Aggregative Spacecraft Systems}, author = {Christopher Michael Jewison}, year = {2014}, date = {2014-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
2013 |
Minier, Alain Vision-Based Navigation for the Inspection of a Spinning Spacecraft PhD Thesis 2013. @phdthesis{Minier2013, title = {Vision-Based Navigation for the Inspection of a Spinning Spacecraft}, author = {Alain Minier}, year = {2013}, date = {2013-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
Tweddle, Brent Edward Computer Vision-Based Localization and Mapping of an Unknown, Uncooperative and Spinning Target for Spacecraft Proximity Operations PhD Thesis 2013. @phdthesis{Tweddle2013, title = {Computer Vision-Based Localization and Mapping of an Unknown, Uncooperative and Spinning Target for Spacecraft Proximity Operations}, author = {Brent Edward Tweddle}, year = {2013}, date = {2013-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
2012 |
O'Connor, Michael C Design and Implementation of Small Satellite Inspection Missions PhD Thesis 2012, ISBN: 9786026258076. Abstract | BibTeX | Tags: pronunciation, similar sounds, teaching media, ★ @phdthesis{oconnorDesignImplementationSmall2012, title = {Design and Implementation of Small Satellite Inspection Missions}, author = {Michael C O'Connor}, isbn = {9786026258076}, year = {2012}, date = {2012-01-01}, volume = {66}, number = {June}, abstract = {textbullet גרינבלט, י. (2012). ענף הקיווי: תמונת מצב 2012, עלון הנוטע שה``מ, מחוז צפון, משרד החקלאות.}, keywords = {pronunciation, similar sounds, teaching media, ★}, pubstate = {published}, tppubtype = {phdthesis} } textbullet גרינבלט, י. (2012). ענף הקיווי: תמונת מצב 2012, עלון הנוטע שה``מ, מחוז צפון, משרד החקלאות. |
2010 |
Burke, Caley A Nutation in the Spinning SPHERES Spacecraft and Fluid Slosh PhD Thesis 2010. @phdthesis{burkeNutationSpinningSPHERES2010, title = {Nutation in the Spinning SPHERES Spacecraft and Fluid Slosh}, author = {Caley A Burke}, year = {2010}, date = {2010-01-01}, number = {June}, abstract = {Spacecraft today are often spin-stabilized during a portion their launch or mission. Though the basics of spin stabilization are well understood, there remains uncertainty in predicting the likelihood of rapid nutation growth due to onboard liquids. Solely analytical methods of prediction are mainly unsuccessful and physical tests to gather slosh data have only been done for a few specific spacecraft. Data from past spacecraft is subject to a number complex physical factors and anomalies during the launch or mission.}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } Spacecraft today are often spin-stabilized during a portion their launch or mission. Though the basics of spin stabilization are well understood, there remains uncertainty in predicting the likelihood of rapid nutation growth due to onboard liquids. Solely analytical methods of prediction are mainly unsuccessful and physical tests to gather slosh data have only been done for a few specific spacecraft. Data from past spacecraft is subject to a number complex physical factors and anomalies during the launch or mission. |
Pong, Christopher Masaru Autonomous Thruster Failure Recovery for Underactuated Spacecraft PhD Thesis 2010. @phdthesis{Pong2010, title = {Autonomous Thruster Failure Recovery for Underactuated Spacecraft}, author = {Christopher Masaru Pong}, year = {2010}, date = {2010-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
2009 |
Katz, Jacob Estimation and Control of Flexible Space Structures for Autonomous On-Orbit Assembly PhD Thesis 2009. @phdthesis{katzEstimationControlFlexible2009, title = {Estimation and Control of Flexible Space Structures for Autonomous On-Orbit Assembly}, author = {Jacob Katz}, year = {2009}, date = {2009-01-01}, number = {June}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
2008 |
Edwards, Christine M Proximity Operations of a Miniature Inspector Satellite Using Emulated Computer Vision PhD Thesis 2008. @phdthesis{Edwards2008, title = {Proximity Operations of a Miniature Inspector Satellite Using Emulated Computer Vision}, author = {Christine M Edwards}, year = {2008}, date = {2008-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
2007 |
Aoudé, Georges Salim Two-Stage Path Planning Approach for Designing Multiple Spacecraft Reconfiguration Maneuvers and Application to SPHERES Onboard ISS PhD Thesis 2007. @phdthesis{Aoude2007a, title = {Two-Stage Path Planning Approach for Designing Multiple Spacecraft Reconfiguration Maneuvers and Application to SPHERES Onboard ISS}, author = {Georges Salim Aoudé}, year = {2007}, date = {2007-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
Baldesarra, Mark A Decision-Making Framework to Determine the Value of On-Orbit Servicing Compared to Replacement of Space Telescopes PhD Thesis 2007. @phdthesis{Baldesarra2007, title = {A Decision-Making Framework to Determine the Value of On-Orbit Servicing Compared to Replacement of Space Telescopes}, author = {Mark Baldesarra}, year = {2007}, date = {2007-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
Berkovitz, Dustin System Characterization and Online Mass Property Identification of the SPHERES Formation Flight Testbed PhD Thesis 2007. @phdthesis{Berkovitz, title = {System Characterization and Online Mass Property Identification of the SPHERES Formation Flight Testbed}, author = {Dustin Berkovitz}, year = {2007}, date = {2007-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
Chung, Soon-Jo Nonlinear Control and Synchronization of Multiple Lagrangian Systems with Application to Tethered Formation Flight Spacecraft PhD Thesis 2007. @phdthesis{Chung2007, title = {Nonlinear Control and Synchronization of Multiple Lagrangian Systems with Application to Tethered Formation Flight Spacecraft}, author = {Soon-Jo Chung}, year = {2007}, date = {2007-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
Huntington, G T Advancement and Analysis of a Gauss Pseudospectral Transcription for Optimal Control Problems PhD Thesis 2007. @phdthesis{Huntington2007, title = {Advancement and Analysis of a Gauss Pseudospectral Transcription for Optimal Control Problems}, author = {G T Huntington}, year = {2007}, date = {2007-01-01}, abstract = {As optimal control problems become increasingly complex, innovative numerical methods are needed to solve them. Direct transcription methods, and in particular, methods involving orthogonal collocation have become quite popular in several field areas due to their high accuracy in approximating non-analytic solutions with relatively few discretization points. Several of these methods, known as pseudospectral methods in the aerospace engineering community, have also established costate estimation procedures which can be used to verify the optimality of the resulting solution. This work examines three of these pseudospectral methods in detail, specifically the Legendre, Gauss, and Radau pseudospectral methods, in order to assess their accuracy, efficiency, and applicability to optimal control problems of varying complexity. Emphasis is placed on improving the Gauss pseudospectral method, where advancements to the method include a revised pseudospectral transcription for problems with path constraints and differential dynamic constraints, a new algorithm for the computation of the control at the boundaries, and an analysis of a local versus global implementation of the method. The Gauss pseudospectral method is then applied to solve current problems in the area of tetrahedral spacecraft formation flying. These optimal control problems involve multiple finite-burn maneuvers, nonlinear dynamics, and nonlinear inequality path constraints that depend on both the relative and inertial positions of all four spacecraft. Contributions of this thesis include an improved numerical method for solving optimal control problems, an analysis and numerical comparison of several other competitive direct methods, and a greater understanding of the relative motion of tetrahedral formation flight.}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } As optimal control problems become increasingly complex, innovative numerical methods are needed to solve them. Direct transcription methods, and in particular, methods involving orthogonal collocation have become quite popular in several field areas due to their high accuracy in approximating non-analytic solutions with relatively few discretization points. Several of these methods, known as pseudospectral methods in the aerospace engineering community, have also established costate estimation procedures which can be used to verify the optimality of the resulting solution. This work examines three of these pseudospectral methods in detail, specifically the Legendre, Gauss, and Radau pseudospectral methods, in order to assess their accuracy, efficiency, and applicability to optimal control problems of varying complexity. Emphasis is placed on improving the Gauss pseudospectral method, where advancements to the method include a revised pseudospectral transcription for problems with path constraints and differential dynamic constraints, a new algorithm for the computation of the control at the boundaries, and an analysis of a local versus global implementation of the method. The Gauss pseudospectral method is then applied to solve current problems in the area of tetrahedral spacecraft formation flying. These optimal control problems involve multiple finite-burn maneuvers, nonlinear dynamics, and nonlinear inequality path constraints that depend on both the relative and inertial positions of all four spacecraft. Contributions of this thesis include an improved numerical method for solving optimal control problems, an analysis and numerical comparison of several other competitive direct methods, and a greater understanding of the relative motion of tetrahedral formation flight. |
Kim, Susan C Mission Design and Trajectory Analysis for Inspection of a Host Spacecraft by a Microsatellite PhD Thesis 2007, ISSN: 1095323X. Abstract | Links | BibTeX | Tags: ★ @phdthesis{kimMissionDesignTrajectory2007, title = {Mission Design and Trajectory Analysis for Inspection of a Host Spacecraft by a Microsatellite}, author = {Susan C Kim}, doi = {10.1109/AERO.2007.352811}, issn = {1095323X}, year = {2007}, date = {2007-01-01}, abstract = {The trajectory analysis and mission design for inspection of a host spacecraft by a microsatellite is motivated by the current developments in designing and building prototypes of a microsatellite inspector vehicle. A mission in which a host spacecraft is in orbit about Earth is covered in this paper. A toolset has been created, composed of both natural and forced motion trajectories. The toolset evaluates an inspection mission concept based on figures of merit over four primary operational modes: deployment mode, global inspection mode, point inspection mode, and disposal mode. Merit figures investigated include the quality of inspection through resolution, lighting conditions, viewing angles, total inspection coverage, tracking spacecraft constraints and consumables regarding telecommunications, spacecraft power, and fuel expenditure. This paper presents the design of the inspection mission design toolset and summarizes the performance of a baseline inspection mission concept of a host in Earth orbit. textcopyright 2007 IEEE.}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } The trajectory analysis and mission design for inspection of a host spacecraft by a microsatellite is motivated by the current developments in designing and building prototypes of a microsatellite inspector vehicle. A mission in which a host spacecraft is in orbit about Earth is covered in this paper. A toolset has been created, composed of both natural and forced motion trajectories. The toolset evaluates an inspection mission concept based on figures of merit over four primary operational modes: deployment mode, global inspection mode, point inspection mode, and disposal mode. Merit figures investigated include the quality of inspection through resolution, lighting conditions, viewing angles, total inspection coverage, tracking spacecraft constraints and consumables regarding telecommunications, spacecraft power, and fuel expenditure. This paper presents the design of the inspection mission design toolset and summarizes the performance of a baseline inspection mission concept of a host in Earth orbit. textcopyright 2007 IEEE. |
Mohan, Swati Reconfiguration Methods for On-orbit Servicing, Assembly, and Operations with Application to Space Telescopes PhD Thesis 2007. @phdthesis{Mohan2007a, title = {Reconfiguration Methods for On-orbit Servicing, Assembly, and Operations with Application to Space Telescopes}, author = {Swati Mohan}, year = {2007}, date = {2007-01-01}, abstract = {Reconfiguration is an important characteristic in furthering on-orbit servicing, assembly, and operations. Previous work has focused on large assemblers manipulating small payloads, where the dynamics of the assembler is not significantly changed. This work seeks to identify the impact of reconfiguration on maneuver performance. Reconfiguration is considered in two categories: implementation and application. Implementation of reconfiguration consisted of developing a method for defining and updating a configuration, implementation on the SPHERES testbed, and execution of tests (in simulation and on the International Space Station) to assess the control performance improvement after reconfiguration. Four applications were considered in this work, two hardware applications and two systems applications modeled through simulation. The objective of the SWARM application was to demonstrate autonomous assembly capability through docking and undocking maneuvers. The objective of the SIFFT application was to demonstrate formation reconfiguration capability, through the expansion and rotation of an equilateral triangle of three satellites. The objective of the systems applications was to determine the impact of reconfiguration in a larger mission context. One application, Mass Property Update, considered how the choice of method for obtaining the mass property information impacts operations. The other application, Modularity Analysis, considered how the implementation of modularity is driven by the mission objectives. Overall, this work has served to demonstrate the control impact of reconfiguration though implementation on the SPHERES testbed. This implementation was used on two hardware applications to determine the performance of reconfiguration for assembly and formation reconfiguration missions. Also, the impact of reconfiguration has been studied in the broader systems context. The choice of method of mass property update was demonstrated to have an impact on operations, in terms of reliability and mass. Finally, the method incorporation of modularity for purposes of on-orbit servicing and assembly was demonstrated to be driven by mission design parameters.}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } Reconfiguration is an important characteristic in furthering on-orbit servicing, assembly, and operations. Previous work has focused on large assemblers manipulating small payloads, where the dynamics of the assembler is not significantly changed. This work seeks to identify the impact of reconfiguration on maneuver performance. Reconfiguration is considered in two categories: implementation and application. Implementation of reconfiguration consisted of developing a method for defining and updating a configuration, implementation on the SPHERES testbed, and execution of tests (in simulation and on the International Space Station) to assess the control performance improvement after reconfiguration. Four applications were considered in this work, two hardware applications and two systems applications modeled through simulation. The objective of the SWARM application was to demonstrate autonomous assembly capability through docking and undocking maneuvers. The objective of the SIFFT application was to demonstrate formation reconfiguration capability, through the expansion and rotation of an equilateral triangle of three satellites. The objective of the systems applications was to determine the impact of reconfiguration in a larger mission context. One application, Mass Property Update, considered how the choice of method for obtaining the mass property information impacts operations. The other application, Modularity Analysis, considered how the implementation of modularity is driven by the mission objectives. Overall, this work has served to demonstrate the control impact of reconfiguration though implementation on the SPHERES testbed. This implementation was used on two hardware applications to determine the performance of reconfiguration for assembly and formation reconfiguration missions. Also, the impact of reconfiguration has been studied in the broader systems context. The choice of method of mass property update was demonstrated to have an impact on operations, in terms of reliability and mass. Finally, the method incorporation of modularity for purposes of on-orbit servicing and assembly was demonstrated to be driven by mission design parameters. |
Nolet, Simon Development of a Guidance, Navigation and Control Architecture and Validation Process Enabling Autonomous Docking to a Tumbling Satellite PhD Thesis 2007. @phdthesis{Nolet2007a, title = {Development of a Guidance, Navigation and Control Architecture and Validation Process Enabling Autonomous Docking to a Tumbling Satellite}, author = {Simon Nolet}, year = {2007}, date = {2007-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
2005 |
Saenz-Otero, Alvar Design Principles for the Development of Space Technology Maturation Laboratories Aboard the International Space Station PhD Thesis MIT, 2005. @phdthesis{saenz-oteroDesignPrinciplesDevelopment2005, title = {Design Principles for the Development of Space Technology Maturation Laboratories Aboard the International Space Station}, author = {Alvar {Saenz-Otero}}, year = {2005}, date = {2005-01-01}, number = {June}, school = {MIT}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
2004 |
Woffinden, David C On-Orbit Satellite Inspection: Navigation and Delta-V Analysis PhD Thesis 2004. @phdthesis{woffindenOnOrbitSatelliteInspection2004, title = {On-Orbit Satellite Inspection: Navigation and Delta-V Analysis}, author = {David C Woffinden}, year = {2004}, date = {2004-01-01}, volume = {Masters Th}, number = {Massachussetts Institute of Technology}, abstract = {Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004.}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004. |
2003 |
How, Jonathan P Real-Time Trjaectory Design for Unmanned Aerial Vehicles Using Receding Horizion Control PhD Thesis 2003. @phdthesis{How2003, title = {Real-Time Trjaectory Design for Unmanned Aerial Vehicles Using Receding Horizion Control}, author = {Jonathan P How}, year = {2003}, date = {2003-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
McConnell, Josh Technical and Policy Issues Surrounding the Use of Autonomous Manueverable Earth Observing Satellites PhD Thesis 2003. Abstract | BibTeX | Tags: Embedded systems, satellite policy, scheduling, ★ @phdthesis{McConnell2003, title = {Technical and Policy Issues Surrounding the Use of Autonomous Manueverable Earth Observing Satellites}, author = {Josh McConnell}, year = {2003}, date = {2003-01-01}, abstract = {To better respond to transient Earth phenomenon that can cause loss of life or damage to economic assets (tornadoes, mudslides, flash floods, etc.), an increase in the amount and timeliness of information collected on phenomenon is needed. One method for collecting this information is by using groups of Earth observing satellites with the ability to perform autonomous orbital maneuvers and view phenomenon on demand. However, as satellites are very costly, creating a group of satellites large enough to perform this task is currently beyond the abilities of any one organization. One method of gathering a group of satellites that is large enough is by several organizations ``pooling'' their satellite resources together temporarily. In order to pool autonomous maneuverable satellites, several technical and policy problems must be overcome. The technical problem addressed is how to schedule large numbers of satellites to effectively collect critical information on phenomenon, even in the face of unexpected events, such as satellite failures that can prohibit the collection of this information. The policy problem addressed is how to overcome barriers that prevent organizations from temporarily loaning their satellite resources to a pooling system. To overcome the technical problem of effectively scheduling large numbers of satellites, an integrated planner is developed using Draper Laboratory's EPOS 1.0 optimal planner and the ALLIANCE behavioral planning algorithm. The optimal planner efficiently allocates satellite and fuel resources, while the reaction planner modifies the optimal plan if an unexpected event occurs that would decrease the group's ability to collect information. To overcome the policy problem of assembling a large number of satellites, a public-private partnership pooling organization is proposed. As satellites are currently a highly expensive and limited resource, the willingness and ability of organizations with satellite resources to contribute part of their satellite resources is in question. Barriers identified when forming a pooling organization and ways to overcome these barriers are identified. Through the analysis of several simulations it was found that it is possible to achieve the technical results of responding to unexpected events in a timely manner without a substantial increase in fuel usage. Through a policy analysis it was determined that the liability issues associated with satellite pooling and organizational cultural inertia are the primary barriers inhibiting organizations from participating in a pool, but that these are possible to overcome, as there are examples where similar cross organizational relationships have succeeded with great effort. This thesis finds that the critical barriers that must be resolved before creating a group of autonomous maneuverable Earth observing satellites are not technical in nature, but are legal and cultural changes in organizations.}, keywords = {Embedded systems, satellite policy, scheduling, ★}, pubstate = {published}, tppubtype = {phdthesis} } To better respond to transient Earth phenomenon that can cause loss of life or damage to economic assets (tornadoes, mudslides, flash floods, etc.), an increase in the amount and timeliness of information collected on phenomenon is needed. One method for collecting this information is by using groups of Earth observing satellites with the ability to perform autonomous orbital maneuvers and view phenomenon on demand. However, as satellites are very costly, creating a group of satellites large enough to perform this task is currently beyond the abilities of any one organization. One method of gathering a group of satellites that is large enough is by several organizations ``pooling'' their satellite resources together temporarily. In order to pool autonomous maneuverable satellites, several technical and policy problems must be overcome. The technical problem addressed is how to schedule large numbers of satellites to effectively collect critical information on phenomenon, even in the face of unexpected events, such as satellite failures that can prohibit the collection of this information. The policy problem addressed is how to overcome barriers that prevent organizations from temporarily loaning their satellite resources to a pooling system. To overcome the technical problem of effectively scheduling large numbers of satellites, an integrated planner is developed using Draper Laboratory's EPOS 1.0 optimal planner and the ALLIANCE behavioral planning algorithm. The optimal planner efficiently allocates satellite and fuel resources, while the reaction planner modifies the optimal plan if an unexpected event occurs that would decrease the group's ability to collect information. To overcome the policy problem of assembling a large number of satellites, a public-private partnership pooling organization is proposed. As satellites are currently a highly expensive and limited resource, the willingness and ability of organizations with satellite resources to contribute part of their satellite resources is in question. Barriers identified when forming a pooling organization and ways to overcome these barriers are identified. Through the analysis of several simulations it was found that it is possible to achieve the technical results of responding to unexpected events in a timely manner without a substantial increase in fuel usage. Through a policy analysis it was determined that the liability issues associated with satellite pooling and organizational cultural inertia are the primary barriers inhibiting organizations from participating in a pool, but that these are possible to overcome, as there are examples where similar cross organizational relationships have succeeded with great effort. This thesis finds that the critical barriers that must be resolved before creating a group of autonomous maneuverable Earth observing satellites are not technical in nature, but are legal and cultural changes in organizations. |
2002 |
Chen, Allen Propulsion System Characterization for the SPHERES Formation Flight and Docking Testbed PhD Thesis 2002. Abstract | BibTeX | Tags: SPHERES propulsion system characterization, ★ @phdthesis{Chen2002, title = {Propulsion System Characterization for the SPHERES Formation Flight and Docking Testbed}, author = {Allen Chen}, year = {2002}, date = {2002-01-01}, abstract = {The MIT Space Systems Laboratory is developing the SPHERES Formation Flight and Docking testbed for the validation of high risk metrology, control, and autonomy technologies. Knowledge of the testbeddbend s actuation system is critical both to the performance of SPHERES as a controls testbed and to the operations of the testbed onboard the International Space Station. This thesis presents work that characterizes the SPHERES propulsion system, the testbeddbend s actuator. The flight design of the SPHERES testbed is presented with particular focus and detail given to the design of the propulsion system. Performance and performance variations of the system are first theoretically determined and then compared to data generated experimentally. Trends in the experimental results are identified and modeled, yielding greater insight into the propulsion systemdbend s workings. Better knowledge of the propulsion system allows refinement of the plant control model, resulting in better estimation of propellant consumption and truer performance when evaluating control algorithms. Performance variations resulting from manufacturing, system settings, and usage are identified and quantified. This leads directly to the development of correction schemes that help to mitigate the undesirable and unintended performance variations that affect tracking. Finally, a process for extending the work in this thesis is presented.}, keywords = {SPHERES propulsion system characterization, ★}, pubstate = {published}, tppubtype = {phdthesis} } The MIT Space Systems Laboratory is developing the SPHERES Formation Flight and Docking testbed for the validation of high risk metrology, control, and autonomy technologies. Knowledge of the testbeddbend s actuation system is critical both to the performance of SPHERES as a controls testbed and to the operations of the testbed onboard the International Space Station. This thesis presents work that characterizes the SPHERES propulsion system, the testbeddbend s actuator. The flight design of the SPHERES testbed is presented with particular focus and detail given to the design of the propulsion system. Performance and performance variations of the system are first theoretically determined and then compared to data generated experimentally. Trends in the experimental results are identified and modeled, yielding greater insight into the propulsion systemdbend s workings. Better knowledge of the propulsion system allows refinement of the plant control model, resulting in better estimation of propellant consumption and truer performance when evaluating control algorithms. Performance variations resulting from manufacturing, system settings, and usage are identified and quantified. This leads directly to the development of correction schemes that help to mitigate the undesirable and unintended performance variations that affect tracking. Finally, a process for extending the work in this thesis is presented. |
2001 |
Uebelhart, Scott Alan Conditioning, Reduction, and Disturbance Analysis of Large Order Integrated Models for Space-Based Telescopes PhD Thesis 2001. @phdthesis{Uebelhart, title = {Conditioning, Reduction, and Disturbance Analysis of Large Order Integrated Models for Space-Based Telescopes}, author = {Scott Alan Uebelhart}, year = {2001}, date = {2001-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
Yung, J H Gain Scheduling for Geometrically Nonlinear Flexible Space Structures PhD Thesis 2001. @phdthesis{Yung2001, title = {Gain Scheduling for Geometrically Nonlinear Flexible Space Structures}, author = {J H Yung}, year = {2001}, date = {2001-01-01}, abstract = {A gain-scheduling approach for the control of geometrically nonlinear structures is developed. The objective is to improve performance over current linear design techniques that are applied to the same control problem. The approach is applicable to a variety of structures that have complex dynamics with slow variations such as flexible robotic arms and space structures with gimballing solar arrays. The modeling approach is motivated by the lack of in situ test data available for design of 0-g controllers. A Linear Fractional form allows the nonlinear and uncertain aspects of the structure to be modeled independently. The geometric nonlinearity is modeled using a feedback description of structural coupling. The uncertainty model is based on a physical parameter description, so that an experimentally identified 1-g parametric uncertainty model can be extrapolated to 0-g. The control approach is motivated by the success of linear control design synthesis and analysis techniques for space structures. Graphical heuristics for linear control design using Linear Quadratic Gaussian (LQG) and Sensitivity Weighted LQG techniques are introduced. A procedure to realize reduced-order gain-scheduled controllers from a family of linear state-space controllers is developed. A nonlinear analysis framework suitable for the slow variations of geometrically nonlinear structures is also presented. The realization procedure and nonlinear analysis is combined with the graphical linear design heuristics to form an iterative gain scheduled design process. The complete gain scheduling approach is applied to the MIT/MACE-II experiment flown on the International Space Station. Gain scheduled controller designs are shown to provide improved performance and robustness over a Multiple Model linear controllerdesign.}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } A gain-scheduling approach for the control of geometrically nonlinear structures is developed. The objective is to improve performance over current linear design techniques that are applied to the same control problem. The approach is applicable to a variety of structures that have complex dynamics with slow variations such as flexible robotic arms and space structures with gimballing solar arrays. The modeling approach is motivated by the lack of in situ test data available for design of 0-g controllers. A Linear Fractional form allows the nonlinear and uncertain aspects of the structure to be modeled independently. The geometric nonlinearity is modeled using a feedback description of structural coupling. The uncertainty model is based on a physical parameter description, so that an experimentally identified 1-g parametric uncertainty model can be extrapolated to 0-g. The control approach is motivated by the success of linear control design synthesis and analysis techniques for space structures. Graphical heuristics for linear control design using Linear Quadratic Gaussian (LQG) and Sensitivity Weighted LQG techniques are introduced. A procedure to realize reduced-order gain-scheduled controllers from a family of linear state-space controllers is developed. A nonlinear analysis framework suitable for the slow variations of geometrically nonlinear structures is also presented. The realization procedure and nonlinear analysis is combined with the graphical linear design heuristics to form an iterative gain scheduled design process. The complete gain scheduling approach is applied to the MIT/MACE-II experiment flown on the International Space Station. Gain scheduled controller designs are shown to provide improved performance and robustness over a Multiple Model linear controllerdesign. |
2000 |
Saenz-Otero, Alvar The SPHERES Satellite Formation Flight Testbed: Design and Initial Control PhD Thesis 2000. @phdthesis{Otero2000, title = {The SPHERES Satellite Formation Flight Testbed: Design and Initial Control}, author = {Alvar {Saenz-Otero}}, year = {2000}, date = {2000-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
1998 |
Kong, Edmund M Optimal Trajectories and Orbit Design for Separated Spacecraft Interferometry PhD Thesis 1998. @phdthesis{kongOptimalTrajectoriesOrbit1998, title = {Optimal Trajectories and Orbit Design for Separated Spacecraft Interferometry}, author = {Edmund M Kong}, year = {1998}, date = {1998-01-01}, number = {November}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |
1997 |
Blaurock, Carl Modeling of Geometrically Nonlinear Flexible Structures for Control PhD Thesis 1997. @phdthesis{blaurockModelingGeometricallyNonlinear1997, title = {Modeling of Geometrically Nonlinear Flexible Structures for Control}, author = {Carl Blaurock}, year = {1997}, date = {1997-01-01}, keywords = {★}, pubstate = {published}, tppubtype = {phdthesis} } |