Jesse Eyer - Academia.edu (original) (raw)
Papers by Jesse Eyer
Lunar and Planetary Science Conference, Mar 1, 2020
The Institute for Telecommunications Research (ITR) at the University of South Australia has led ... more The Institute for Telecommunications Research (ITR) at the University of South Australia has led a consortium, including COM DEV International, to design a low Earth orbit microsatellite constellation mission with a customized communications systems architecture, using specialized waveform designs to create a Global Sensor Network (GSN). The GSN provides a low-cost mechanism for gathering data from a very large number of remote land and marine sensors in the field of view of the satellite, and delivering information to end users. The system allows users to control and upgrade their remotely deployed devices, if necessary. One of the principal requirements of the GSN is that it be able to handle up to 100,000 sensor-terminals during a ten minute satellite pass. This is accomplished by novel waveforms and high-efficiency communication protocols resulting in a flexible and scalable satellite system that communicates with large numbers of terminals using low bandwidth. The techniques have been successfully validated in airborne and limited satellite trials using existing space assets and a bent-pipe system to demonstrate proof of concept. A key differentiator between the GSN and existing constellations such as Iridium, Globalstar etc., is that the low cost is achieved by recognizing that large classes of sensors don’t necessarily require continuous access to a satellite, and only need to transmit short burst data at relatively long intervals. Populating the planet with sensors of all types expands the concept of the “internet of things” to remote locations such as the polar caps, the oceans, and remote forests and deserts, and can potentially tie together diverse datasets for natural resource management, security, research and environmental monitoring.
Proceedings Of The Institution Of Mechanical Engineers, Part G: Journal Of Aerospace Engineering, Apr 1, 2009
The development of an LQR-based control algorithm for the Canadian advanced nanospace eXperiment ... more The development of an LQR-based control algorithm for the Canadian advanced nanospace eXperiment (CanX)-4&5 formation flying nanosatellite mission is described. To facilitate an analytical stability proof of the algorithm, elements of the non-linear and continuous system are linearized and discretized. A suitable state for the system is selected and the algorithm is converted into a discrete linear time-varying system that is very nearly periodic. The stability of the system is then determined by means of discrete Floquet theory. This analysis is applied to the CanX-4&5 algorithm during its primary mission of testing along track orbit formations and projected circular orbit formations. The analysis is also applied to the algorithm while executing a quasi J 2-invariant formation. The results in all cases indicate stability. Finally, for the quasi J 2-invariant formation the control authority of the algorithm is reduced until the stability limit is approached and the minimum V required to maintain the formation is found.
An innovative dynamics and control algorithm is developed for a dual-nanosatellite formation flyi... more An innovative dynamics and control algorithm is developed for a dual-nanosatellite formation flying mission. The principal function of this algorithm is to use regular GPS state measurements to determine the controlled satellite's tracking error from a set of reference trajectories in the localvertical/local-horizontal reference frame. A linear state-feedback control law-designed using a linear quadratic regulator method-calculates the optimal thrusts necessary to correct this error and communicates the thrust directions to the attitude control system and the thrust durations to the propulsion system. The control system is developed to minimize the conflicting metrics of tracking error and ∆V requirements. To reconfigure the formation, an optimization algorithm is designed using the analytical solution to the state-space equation and the Hill-Clohessy-Wiltshire state transition matrix to solve for dual-thrust reconfiguration maneuvers. The resulting trajectories require low ∆V, use finite-time thrusts and are accurate in a fully nonlinear orbital environment. This algorithm will be used to control the CanX-4&5 formation flying demonstration mission. In addition, an iterative method which numerically generates quasi periodic trajectories for a satellite formation is presented. This novel technique utilizes a shooting approach to the Newton method to close the relative deputy trajectory over a specific number of orbits, then fits the actual perturbed motion of the deputy with a Fourier series to enforce periodicity. This process is applied to two well-known satellite formations: a projected circular orbit and a J 2-invariant formation. Compared to conventional formations, these resulting quasi-periodic trajectories require a dramatically lower control effort to maintain and could therefore be used to extend ∆V-limited formation flying missions. Finally, an analytical study of the stability of the formation flying algorithm is conducted. To facilitate the proof, the control algorithm is converted into a discrete-time linear time-varying system. Stability of the system is determined via discrete Floquet theory. This analysis is applied to the CanX-4&5 control laws for tracking along-track orbits, projected circular orbits, and quasi J 2-invariant formations. Far from being a solitary effort, the research and writing of this Ph.D. thesis was accomplished with the invaluable help and support of a large number of people. First and foremost, I would like to gratefully thank my supervisor, Dr. Christopher Damaren for his attentive guidance, encouragement and patience during the past four years. His enthusiasm for spacecraft dynamics and controls has been a source of inspiration and his style of supervision, hands-off-but-always-there, has suited me perfectly. The students and staff at the Space Flight Laboratory have been my friends and colleagues during this degree. Their ideas, suggestions and questions have helped to keep my research grounded in reality. As a group of friends, they have made my time in Toronto immeasurably more entertaining and enjoyable. Other students at UTIAS, in particular Markus Rumpfkeil and James Forbes, have been adept "listening posts" who have tolerated my rambling thought processes and have often given me valuable insights to my formation flying problems. Finally, I would like to thank my parents, David and Dodie Eyer, for their unflagging love, empathy and support. They have always encouraged me to pursue my dreams; whether it be traveling the world or getting a Ph.D., they've been behind me all the way and I am truly grateful. When it comes to parents, I definitely won the lottery. Thank you all.
Acta Astronautica, Aug 1, 2012
The method of controlling a spacecraft formation using mean relative states as the inputs is an e... more The method of controlling a spacecraft formation using mean relative states as the inputs is an effective technique if control actuation is sought to be reduced. In this paper, we extend the efficacy of this method by including the linearized J2 terms in the system dynamics and derive the linear mapping between the actual and the mean relative states. The resultant control equation has J2 related gains that are shown to improve the tracking of the states and increase system performance for a phase planebased controller performing formation maneuvering.
Engineering Optimization, May 1, 2009
The on-orbit reconfiguration of a pair of formation-flying satellites in low Earth orbit is studi... more The on-orbit reconfiguration of a pair of formation-flying satellites in low Earth orbit is studied in the presence of J 2-J 6 gravitational perturbations. A methodology for determining a robust and accurate impulsive thrusting scheme is developed with the aim of minimizing reconfiguration overshoot errors and fuel expenditure (V). The method uses a state transition matrix based on the Hill-Clohessy-Wiltshire linear equations of relative motion and the analytical solution to the state-space model to solve for a pair of impulsive thrusts. The manoeuvre is then propagated through a fully nonlinear orbital simulator with the thrusts implemented non-impulsively. A Sequential Quadratic Programming optimizer adjusts the inputs to the linear state transition matrix to produce impulses that, when applied in the high-fidelity orbital propagator, mitigates the V of the manoeuvre while maintaining acceptable overshoot errors.
An innovative dynamics and control algorithm is developed for a dual-nanosatellite formation flyi... more An innovative dynamics and control algorithm is developed for a dual-nanosatellite formation flying mission. The principal function of this algorithm is to use regular GPS state measurements to determine the controlled satellite's tracking error from a set of reference trajectories in the localvertical/local-horizontal reference frame. A linear state-feedback control law-designed using a linear quadratic regulator method-calculates the optimal thrusts necessary to correct this error and communicates the thrust directions to the attitude control system and the thrust durations to the propulsion system. The control system is developed to minimize the conflicting metrics of tracking error and ∆V requirements. To reconfigure the formation, an optimization algorithm is designed using the analytical solution to the state-space equation and the Hill-Clohessy-Wiltshire state transition matrix to solve for dual-thrust reconfiguration maneuvers. The resulting trajectories require low ∆V, use finite-time thrusts and are accurate in a fully nonlinear orbital environment. This algorithm will be used to control the CanX-4&5 formation flying demonstration mission. In addition, an iterative method which numerically generates quasi periodic trajectories for a satellite formation is presented. This novel technique utilizes a shooting approach to the Newton method to close the relative deputy trajectory over a specific number of orbits, then fits the actual perturbed motion of the deputy with a Fourier series to enforce periodicity. This process is applied to two well-known satellite formations: a projected circular orbit and a J 2-invariant formation. Compared to conventional formations, these resulting quasi-periodic trajectories require a dramatically lower control effort to maintain and could therefore be used to extend ∆V-limited formation flying missions. Finally, an analytical study of the stability of the formation flying algorithm is conducted. To facilitate the proof, the control algorithm is converted into a discrete-time linear time-varying system. Stability of the system is determined via discrete Floquet theory. This analysis is applied to the CanX-4&5 control laws for tracking along-track orbits, projected circular orbits, and quasi J 2-invariant formations. Far from being a solitary effort, the research and writing of this Ph.D. thesis was accomplished with the invaluable help and support of a large number of people. First and foremost, I would like to gratefully thank my supervisor, Dr. Christopher Damaren for his attentive guidance, encouragement and patience during the past four years. His enthusiasm for spacecraft dynamics and controls has been a source of inspiration and his style of supervision, hands-off-but-always-there, has suited me perfectly. The students and staff at the Space Flight Laboratory have been my friends and colleagues during this degree. Their ideas, suggestions and questions have helped to keep my research grounded in reality. As a group of friends, they have made my time in Toronto immeasurably more entertaining and enjoyable. Other students at UTIAS, in particular Markus Rumpfkeil and James Forbes, have been adept "listening posts" who have tolerated my rambling thought processes and have often given me valuable insights to my formation flying problems. Finally, I would like to thank my parents, David and Dodie Eyer, for their unflagging love, empathy and support. They have always encouraged me to pursue my dreams; whether it be traveling the world or getting a Ph.D., they've been behind me all the way and I am truly grateful. When it comes to parents, I definitely won the lottery. Thank you all.
developing enabling technologies in collaboration with the University of Calgary for future preci... more developing enabling technologies in collaboration with the University of Calgary for future precise formation flying missions. These technologies will be validated on two nanosatellites under development as part of SFL’s Canadian Advanced Nanospace eXperiment (CanX) program. These nanosatellites, named CanX-4 and CanX-5, will be launched together to be among the first to demonstrate autonomous formation flight in orbit. These identical satellites will achieve position determination to within a few centimeters, while controlling their relative position to an accuracy of less than one meter. This paper describes the enabling nanosatellite technologies that have been developed at UTIAS/SFL for this mission, including formation flying control algorithms, a low power intersatellite communication system, a liquid-fuel cold-gas propulsion system, a three-axis attitude control system, and an intersatellite separation system. CanX-4&5 are currently targeting a 2009 launch.
Autonomous formation flight has long been studied as a means to provide high resolution sensing f... more Autonomous formation flight has long been studied as a means to provide high resolution sensing from multiple satellites equipped with lower resolution sensors. The Space Flight Laboratory (SFL) at the University of Toronto Institute for Aerospace Studies (UTIAS) is developing enabling technologies in collaboration with the University of Calgary for future precise formation flying missions. These technologies will be validated on two nanosatellites under development as part of SFL’s Canadian Advanced Nanospace eXperiment (CanX) program. These nanosatellites, named CanX-4 and CanX-5, will be launched together to be among the first to demonstrate autonomous formation flight in orbit. With a mass of only 7kg and size of 20x20x20 cm, these identical satellites will achieve position determination to within a few centimeters, while controlling their relative position to an accuracy of less than one meter. This paper describes the enabling nanosatellite technologies that have been develope...
A DYNAMICS AND CONTROL ALGORITHM FOR LOW EARTH ORBIT PRECISION FORMATION FLYING SATELLITES Jesse ... more A DYNAMICS AND CONTROL ALGORITHM FOR LOW EARTH ORBIT PRECISION FORMATION FLYING SATELLITES Jesse Koovik Eyer Doctor of Philosophy Graduate Department of Aerospace Science and Engineering University of Toronto 2009 An innovative dynamics and control algorithm is developed for a dual-nanosatellite formation flying mission. The principal function of this algorithm is to use regular GPS state measurements to determine the controlled satellite’s tracking error from a set of reference trajectories in the localvertical/local-horizontal reference frame. A linear state-feedback control law—designed using a linear quadratic regulator method—calculates the optimal thrusts necessary to correct this error and communicates the thrust directions to the attitude control system and the thrust durations to the propulsion system. The control system is developed to minimize the conflicting metrics of tracking error and ∆V requirements. To reconfigure the formation, an optimization algorithm is designed...
The latest Canadian Advanced Nanospace eXperiment (CanX-4&5) is a dual-satellite formation fl yin... more The latest Canadian Advanced Nanospace eXperiment (CanX-4&5) is a dual-satellite formation fl ying demonstration mission. The mission objective is to prove that satellite formation fl ying can be accomplished with submeter tracking error accuracy for low DV requirements. The formation fl ying maneuvers for this mission require the development of control algorithms for autonomous formation maintenance and reconfi guration in the presence of orbital perturbations. In this paper, the development of suitable relative reference trajectories is discussed, and a linear quadratic regulator state-feedback solution for the control problem is described. A discrete thrusting scheme, using pulse width modulation, is applied to account for the fi xed impulse limitation of the real spacecraft. A navigation algorithm uses Global Positioning System (GPS) carrier phase and Doppler data to obtain relative position and velocity measurements to within 2–5 cm and 1–3 cm/s, respectively. Using an extended...
Proc Inst Mech Eng G J a E, 2009
AIAA's 3rd Annual Aviation Technology, Integration, and Operations (ATIO) Forum, 2003
32nd AIAA International Communications Satellite Systems Conference, 2014
Space Technology- …, 2007
The latest Canadian Advanced Nanospace eXperiment, CanX-4&5, is a dual-satellite formation flying... more The latest Canadian Advanced Nanospace eXperiment, CanX-4&5, is a dual-satellite formation flying demonstration mission. The mission objective is to prove that satellite formation flying can be accomplished with sub-meter tracking error accuracy for ...
Journal of Guidance, Control, and Dynamics, 2009
Engineering Optimization, 2009
Space Flight Laboratory, University of …
Lunar and Planetary Science Conference, Mar 1, 2020
The Institute for Telecommunications Research (ITR) at the University of South Australia has led ... more The Institute for Telecommunications Research (ITR) at the University of South Australia has led a consortium, including COM DEV International, to design a low Earth orbit microsatellite constellation mission with a customized communications systems architecture, using specialized waveform designs to create a Global Sensor Network (GSN). The GSN provides a low-cost mechanism for gathering data from a very large number of remote land and marine sensors in the field of view of the satellite, and delivering information to end users. The system allows users to control and upgrade their remotely deployed devices, if necessary. One of the principal requirements of the GSN is that it be able to handle up to 100,000 sensor-terminals during a ten minute satellite pass. This is accomplished by novel waveforms and high-efficiency communication protocols resulting in a flexible and scalable satellite system that communicates with large numbers of terminals using low bandwidth. The techniques have been successfully validated in airborne and limited satellite trials using existing space assets and a bent-pipe system to demonstrate proof of concept. A key differentiator between the GSN and existing constellations such as Iridium, Globalstar etc., is that the low cost is achieved by recognizing that large classes of sensors don’t necessarily require continuous access to a satellite, and only need to transmit short burst data at relatively long intervals. Populating the planet with sensors of all types expands the concept of the “internet of things” to remote locations such as the polar caps, the oceans, and remote forests and deserts, and can potentially tie together diverse datasets for natural resource management, security, research and environmental monitoring.
Proceedings Of The Institution Of Mechanical Engineers, Part G: Journal Of Aerospace Engineering, Apr 1, 2009
The development of an LQR-based control algorithm for the Canadian advanced nanospace eXperiment ... more The development of an LQR-based control algorithm for the Canadian advanced nanospace eXperiment (CanX)-4&5 formation flying nanosatellite mission is described. To facilitate an analytical stability proof of the algorithm, elements of the non-linear and continuous system are linearized and discretized. A suitable state for the system is selected and the algorithm is converted into a discrete linear time-varying system that is very nearly periodic. The stability of the system is then determined by means of discrete Floquet theory. This analysis is applied to the CanX-4&5 algorithm during its primary mission of testing along track orbit formations and projected circular orbit formations. The analysis is also applied to the algorithm while executing a quasi J 2-invariant formation. The results in all cases indicate stability. Finally, for the quasi J 2-invariant formation the control authority of the algorithm is reduced until the stability limit is approached and the minimum V required to maintain the formation is found.
An innovative dynamics and control algorithm is developed for a dual-nanosatellite formation flyi... more An innovative dynamics and control algorithm is developed for a dual-nanosatellite formation flying mission. The principal function of this algorithm is to use regular GPS state measurements to determine the controlled satellite's tracking error from a set of reference trajectories in the localvertical/local-horizontal reference frame. A linear state-feedback control law-designed using a linear quadratic regulator method-calculates the optimal thrusts necessary to correct this error and communicates the thrust directions to the attitude control system and the thrust durations to the propulsion system. The control system is developed to minimize the conflicting metrics of tracking error and ∆V requirements. To reconfigure the formation, an optimization algorithm is designed using the analytical solution to the state-space equation and the Hill-Clohessy-Wiltshire state transition matrix to solve for dual-thrust reconfiguration maneuvers. The resulting trajectories require low ∆V, use finite-time thrusts and are accurate in a fully nonlinear orbital environment. This algorithm will be used to control the CanX-4&5 formation flying demonstration mission. In addition, an iterative method which numerically generates quasi periodic trajectories for a satellite formation is presented. This novel technique utilizes a shooting approach to the Newton method to close the relative deputy trajectory over a specific number of orbits, then fits the actual perturbed motion of the deputy with a Fourier series to enforce periodicity. This process is applied to two well-known satellite formations: a projected circular orbit and a J 2-invariant formation. Compared to conventional formations, these resulting quasi-periodic trajectories require a dramatically lower control effort to maintain and could therefore be used to extend ∆V-limited formation flying missions. Finally, an analytical study of the stability of the formation flying algorithm is conducted. To facilitate the proof, the control algorithm is converted into a discrete-time linear time-varying system. Stability of the system is determined via discrete Floquet theory. This analysis is applied to the CanX-4&5 control laws for tracking along-track orbits, projected circular orbits, and quasi J 2-invariant formations. Far from being a solitary effort, the research and writing of this Ph.D. thesis was accomplished with the invaluable help and support of a large number of people. First and foremost, I would like to gratefully thank my supervisor, Dr. Christopher Damaren for his attentive guidance, encouragement and patience during the past four years. His enthusiasm for spacecraft dynamics and controls has been a source of inspiration and his style of supervision, hands-off-but-always-there, has suited me perfectly. The students and staff at the Space Flight Laboratory have been my friends and colleagues during this degree. Their ideas, suggestions and questions have helped to keep my research grounded in reality. As a group of friends, they have made my time in Toronto immeasurably more entertaining and enjoyable. Other students at UTIAS, in particular Markus Rumpfkeil and James Forbes, have been adept "listening posts" who have tolerated my rambling thought processes and have often given me valuable insights to my formation flying problems. Finally, I would like to thank my parents, David and Dodie Eyer, for their unflagging love, empathy and support. They have always encouraged me to pursue my dreams; whether it be traveling the world or getting a Ph.D., they've been behind me all the way and I am truly grateful. When it comes to parents, I definitely won the lottery. Thank you all.
Acta Astronautica, Aug 1, 2012
The method of controlling a spacecraft formation using mean relative states as the inputs is an e... more The method of controlling a spacecraft formation using mean relative states as the inputs is an effective technique if control actuation is sought to be reduced. In this paper, we extend the efficacy of this method by including the linearized J2 terms in the system dynamics and derive the linear mapping between the actual and the mean relative states. The resultant control equation has J2 related gains that are shown to improve the tracking of the states and increase system performance for a phase planebased controller performing formation maneuvering.
Engineering Optimization, May 1, 2009
The on-orbit reconfiguration of a pair of formation-flying satellites in low Earth orbit is studi... more The on-orbit reconfiguration of a pair of formation-flying satellites in low Earth orbit is studied in the presence of J 2-J 6 gravitational perturbations. A methodology for determining a robust and accurate impulsive thrusting scheme is developed with the aim of minimizing reconfiguration overshoot errors and fuel expenditure (V). The method uses a state transition matrix based on the Hill-Clohessy-Wiltshire linear equations of relative motion and the analytical solution to the state-space model to solve for a pair of impulsive thrusts. The manoeuvre is then propagated through a fully nonlinear orbital simulator with the thrusts implemented non-impulsively. A Sequential Quadratic Programming optimizer adjusts the inputs to the linear state transition matrix to produce impulses that, when applied in the high-fidelity orbital propagator, mitigates the V of the manoeuvre while maintaining acceptable overshoot errors.
An innovative dynamics and control algorithm is developed for a dual-nanosatellite formation flyi... more An innovative dynamics and control algorithm is developed for a dual-nanosatellite formation flying mission. The principal function of this algorithm is to use regular GPS state measurements to determine the controlled satellite's tracking error from a set of reference trajectories in the localvertical/local-horizontal reference frame. A linear state-feedback control law-designed using a linear quadratic regulator method-calculates the optimal thrusts necessary to correct this error and communicates the thrust directions to the attitude control system and the thrust durations to the propulsion system. The control system is developed to minimize the conflicting metrics of tracking error and ∆V requirements. To reconfigure the formation, an optimization algorithm is designed using the analytical solution to the state-space equation and the Hill-Clohessy-Wiltshire state transition matrix to solve for dual-thrust reconfiguration maneuvers. The resulting trajectories require low ∆V, use finite-time thrusts and are accurate in a fully nonlinear orbital environment. This algorithm will be used to control the CanX-4&5 formation flying demonstration mission. In addition, an iterative method which numerically generates quasi periodic trajectories for a satellite formation is presented. This novel technique utilizes a shooting approach to the Newton method to close the relative deputy trajectory over a specific number of orbits, then fits the actual perturbed motion of the deputy with a Fourier series to enforce periodicity. This process is applied to two well-known satellite formations: a projected circular orbit and a J 2-invariant formation. Compared to conventional formations, these resulting quasi-periodic trajectories require a dramatically lower control effort to maintain and could therefore be used to extend ∆V-limited formation flying missions. Finally, an analytical study of the stability of the formation flying algorithm is conducted. To facilitate the proof, the control algorithm is converted into a discrete-time linear time-varying system. Stability of the system is determined via discrete Floquet theory. This analysis is applied to the CanX-4&5 control laws for tracking along-track orbits, projected circular orbits, and quasi J 2-invariant formations. Far from being a solitary effort, the research and writing of this Ph.D. thesis was accomplished with the invaluable help and support of a large number of people. First and foremost, I would like to gratefully thank my supervisor, Dr. Christopher Damaren for his attentive guidance, encouragement and patience during the past four years. His enthusiasm for spacecraft dynamics and controls has been a source of inspiration and his style of supervision, hands-off-but-always-there, has suited me perfectly. The students and staff at the Space Flight Laboratory have been my friends and colleagues during this degree. Their ideas, suggestions and questions have helped to keep my research grounded in reality. As a group of friends, they have made my time in Toronto immeasurably more entertaining and enjoyable. Other students at UTIAS, in particular Markus Rumpfkeil and James Forbes, have been adept "listening posts" who have tolerated my rambling thought processes and have often given me valuable insights to my formation flying problems. Finally, I would like to thank my parents, David and Dodie Eyer, for their unflagging love, empathy and support. They have always encouraged me to pursue my dreams; whether it be traveling the world or getting a Ph.D., they've been behind me all the way and I am truly grateful. When it comes to parents, I definitely won the lottery. Thank you all.
developing enabling technologies in collaboration with the University of Calgary for future preci... more developing enabling technologies in collaboration with the University of Calgary for future precise formation flying missions. These technologies will be validated on two nanosatellites under development as part of SFL’s Canadian Advanced Nanospace eXperiment (CanX) program. These nanosatellites, named CanX-4 and CanX-5, will be launched together to be among the first to demonstrate autonomous formation flight in orbit. These identical satellites will achieve position determination to within a few centimeters, while controlling their relative position to an accuracy of less than one meter. This paper describes the enabling nanosatellite technologies that have been developed at UTIAS/SFL for this mission, including formation flying control algorithms, a low power intersatellite communication system, a liquid-fuel cold-gas propulsion system, a three-axis attitude control system, and an intersatellite separation system. CanX-4&5 are currently targeting a 2009 launch.
Autonomous formation flight has long been studied as a means to provide high resolution sensing f... more Autonomous formation flight has long been studied as a means to provide high resolution sensing from multiple satellites equipped with lower resolution sensors. The Space Flight Laboratory (SFL) at the University of Toronto Institute for Aerospace Studies (UTIAS) is developing enabling technologies in collaboration with the University of Calgary for future precise formation flying missions. These technologies will be validated on two nanosatellites under development as part of SFL’s Canadian Advanced Nanospace eXperiment (CanX) program. These nanosatellites, named CanX-4 and CanX-5, will be launched together to be among the first to demonstrate autonomous formation flight in orbit. With a mass of only 7kg and size of 20x20x20 cm, these identical satellites will achieve position determination to within a few centimeters, while controlling their relative position to an accuracy of less than one meter. This paper describes the enabling nanosatellite technologies that have been develope...
A DYNAMICS AND CONTROL ALGORITHM FOR LOW EARTH ORBIT PRECISION FORMATION FLYING SATELLITES Jesse ... more A DYNAMICS AND CONTROL ALGORITHM FOR LOW EARTH ORBIT PRECISION FORMATION FLYING SATELLITES Jesse Koovik Eyer Doctor of Philosophy Graduate Department of Aerospace Science and Engineering University of Toronto 2009 An innovative dynamics and control algorithm is developed for a dual-nanosatellite formation flying mission. The principal function of this algorithm is to use regular GPS state measurements to determine the controlled satellite’s tracking error from a set of reference trajectories in the localvertical/local-horizontal reference frame. A linear state-feedback control law—designed using a linear quadratic regulator method—calculates the optimal thrusts necessary to correct this error and communicates the thrust directions to the attitude control system and the thrust durations to the propulsion system. The control system is developed to minimize the conflicting metrics of tracking error and ∆V requirements. To reconfigure the formation, an optimization algorithm is designed...
The latest Canadian Advanced Nanospace eXperiment (CanX-4&5) is a dual-satellite formation fl yin... more The latest Canadian Advanced Nanospace eXperiment (CanX-4&5) is a dual-satellite formation fl ying demonstration mission. The mission objective is to prove that satellite formation fl ying can be accomplished with submeter tracking error accuracy for low DV requirements. The formation fl ying maneuvers for this mission require the development of control algorithms for autonomous formation maintenance and reconfi guration in the presence of orbital perturbations. In this paper, the development of suitable relative reference trajectories is discussed, and a linear quadratic regulator state-feedback solution for the control problem is described. A discrete thrusting scheme, using pulse width modulation, is applied to account for the fi xed impulse limitation of the real spacecraft. A navigation algorithm uses Global Positioning System (GPS) carrier phase and Doppler data to obtain relative position and velocity measurements to within 2–5 cm and 1–3 cm/s, respectively. Using an extended...
Proc Inst Mech Eng G J a E, 2009
AIAA's 3rd Annual Aviation Technology, Integration, and Operations (ATIO) Forum, 2003
32nd AIAA International Communications Satellite Systems Conference, 2014
Space Technology- …, 2007
The latest Canadian Advanced Nanospace eXperiment, CanX-4&5, is a dual-satellite formation flying... more The latest Canadian Advanced Nanospace eXperiment, CanX-4&5, is a dual-satellite formation flying demonstration mission. The mission objective is to prove that satellite formation flying can be accomplished with sub-meter tracking error accuracy for ...
Journal of Guidance, Control, and Dynamics, 2009
Engineering Optimization, 2009
Space Flight Laboratory, University of …