The Experts below are selected from a list of 3582 Experts worldwide ranked by ideXlab platform
Jimmy S Issa - One of the best experts on this subject based on the ideXlab platform.
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satellite attitude control using three Reaction Wheels
American Control Conference, 2008Co-Authors: Shahin S Nudehi, U Farooq, Aria Alasty, Jimmy S IssaAbstract:This work addresses the attitude control of a satellite by applying MIMO quantitative feedback approach. The objective is to design a set of proper controllers in presence of unknown disturbances and parametric uncertainties for a nonlinear MIMO system. The physical model of satellite utilizes three Reaction Wheels as actuators. The controller goal is to change the rotational speed of Reaction Wheels to adjust the satellite in desired course. First, the mathematical model of satellite and its actuators using angular kinematics and kinetic equations is developed. Quantitative feedback theory is then applied to synthesize a set of linear controllers that deals with both nonlinearities in the equations and unknown parameters or disturbance sources. By using basically non-interacting desired outputs and extracting sets of linear time invariant equivalent (LTIE) plants, the controllers set is designed for nine SISO systems. Simulation of closed loop system shows that all desired specifications of closed loop (tracking, stability, disturbance rejection) are robustly satisfied.
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ACC - Satellite attitude control using three Reaction Wheels
2008 American Control Conference, 2008Co-Authors: Shahin S Nudehi, U Farooq, Aria Alasty, Jimmy S IssaAbstract:This work addresses the attitude control of a satellite by applying MIMO quantitative feedback approach. The objective is to design a set of proper controllers in presence of unknown disturbances and parametric uncertainties for a nonlinear MIMO system. The physical model of satellite utilizes three Reaction Wheels as actuators. The controller goal is to change the rotational speed of Reaction Wheels to adjust the satellite in desired course. First, the mathematical model of satellite and its actuators using angular kinematics and kinetic equations is developed. Quantitative feedback theory is then applied to synthesize a set of linear controllers that deals with both nonlinearities in the equations and unknown parameters or disturbance sources. By using basically non-interacting desired outputs and extracting sets of linear time invariant equivalent (LTIE) plants, the controllers set is designed for nine SISO systems. Simulation of closed loop system shows that all desired specifications of closed loop (tracking, stability, disturbance rejection) are robustly satisfied.
Jean-francois Tregouet - One of the best experts on this subject based on the ideXlab platform.
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Static Input Allocation for Reaction Wheels Desaturation Using Magnetorquers
IFAC Proceedings Volumes, 2016Co-Authors: Jean-francois Tregouet, Denis Arzelier, Dimitri Peaucelle, Luca ZaccarianAbstract:Abstract Considering a set of Reaction Wheels and an array of magnetorquers, we revisit the classical “cross product control law” solution for achieving attitude stabilization and momentum damping. In particular, we highlight the existence of a quasi-cascade structure for which asymptotic stability can be obtained by selecting a sufficiently high gain of the attitude stabilizer. However, we show how the classical solution renders the actuators more inclined to saturate. This is the reason underlying the introduction of a revisited version of this control law which stabilizes the overall system regardless of the aggressiveness of the attitude stabilizer by transforming the quasi-cascade into a real cascade. We then discuss how both strategies are such that the attitude control is affected by the momentum damping task although it should be treated as a secondary goal. To overcome this drawback, we propose a new allocation-based controller which makes the attitude dynamics completely independent of the momentum damping of the Reaction Wheels while preserving the possibility of considering non-aggressive attitude controllers. Finally, several simulation results enrich these discussions and highlight the pros and cons of the different control strategies.
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Reaction Wheels Desaturation Using Magnetorquers and Static Input Allocation
IEEE Transactions on Control Systems and Technology, 2015Co-Authors: Jean-francois Tregouet, Denis Arzelier, Dimitri Peaucelle, Christelle Pittet, Luca ZaccarianAbstract:Considering the most widely spread configuration of actuators for low orbit satellites, namely a set of Reaction Wheels and set of magnetorquers, we revisit the classical cross-product control law solution for achieving attitude stabilization and momentum dumping. We show how the classical solution has a quasi-cascade structure that, under a suitable input-to-state (ISS) assumption, can be stabilized by high gain, thereby making the actuators more inclined to saturate. Motivated by this, we propose a revisited version of this control law that transforms the quasi-cascade into a real cascade. Then, we show that both strategies are such that the attitude control is affected by the momentum dumping, and that they both require a suitable ISS property. To overcome these drawbacks, we propose a new allocation-based controller, which makes the attitude dynamics completely independent of the momentum dumping and induces global asymptotic stability without any ISS requirement. Several formal statements and simulation results support our discussions and highlight the pros and cons of the different control strategies.
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periodic h 2 synthesis for spacecraft attitude control with magnetorquers and Reaction Wheels
Conference on Decision and Control, 2011Co-Authors: Jean-francois Tregouet, Denis Arzelier, Dimitri Peaucelle, Yoshio Ebihara, Christelle Pittet, Alexandre FalcozAbstract:Particularly attractive for small satellites, the use of magnetic torquers for attitude control is still a difficult problem. Indeed, equations are naturally time-varying and suffers from controllability issues. In this paper, a generic model, taking different kinds of pointing and different kinds of actuators into account, is proposed, linearized and then discretized. Recent studies demonstrate how combining magnetorquers and Reaction Wheels is attractive. Following this line, latest LMI synthesis techniques for static periodic controller are applied in this paper to the attitude control problem of a spacecraft equipped with both actuation systems. Simulation results are provided, showing the performance of the obtained control law.
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Periodic H2 synthesis for spacecraft attitude control with magnetorquers and Reaction Wheels
2011 50th IEEE Conference on Decision and Control and European Control Conference, 2011Co-Authors: Jean-francois Tregouet, Denis Arzelier, Dimitri Peaucelle, Yoshio Ebihara, Christelle Pittet, Alexandre FalcozAbstract:Particularly attractive for small satellites, the use of magnetic torquers for attitude control is still a difficult problem. Indeed, equations are naturally time-varying and suffers from controllability issues. In this paper, a generic model, taking different kinds of pointing and different kinds of actuators into account, is proposed, linearized and then discretized. Recent studies demonstrate how combining magnetorquers and Reaction Wheels is attractive. Following this line, latest LMI synthesis techniques for static periodic controller are applied in this paper to the attitude control problem of a spacecraft equipped with both actuation systems. Simulation results are provided, showing the performance of the obtained control law.
Shahin S Nudehi - One of the best experts on this subject based on the ideXlab platform.
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satellite attitude control using three Reaction Wheels
American Control Conference, 2008Co-Authors: Shahin S Nudehi, U Farooq, Aria Alasty, Jimmy S IssaAbstract:This work addresses the attitude control of a satellite by applying MIMO quantitative feedback approach. The objective is to design a set of proper controllers in presence of unknown disturbances and parametric uncertainties for a nonlinear MIMO system. The physical model of satellite utilizes three Reaction Wheels as actuators. The controller goal is to change the rotational speed of Reaction Wheels to adjust the satellite in desired course. First, the mathematical model of satellite and its actuators using angular kinematics and kinetic equations is developed. Quantitative feedback theory is then applied to synthesize a set of linear controllers that deals with both nonlinearities in the equations and unknown parameters or disturbance sources. By using basically non-interacting desired outputs and extracting sets of linear time invariant equivalent (LTIE) plants, the controllers set is designed for nine SISO systems. Simulation of closed loop system shows that all desired specifications of closed loop (tracking, stability, disturbance rejection) are robustly satisfied.
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ACC - Satellite attitude control using three Reaction Wheels
2008 American Control Conference, 2008Co-Authors: Shahin S Nudehi, U Farooq, Aria Alasty, Jimmy S IssaAbstract:This work addresses the attitude control of a satellite by applying MIMO quantitative feedback approach. The objective is to design a set of proper controllers in presence of unknown disturbances and parametric uncertainties for a nonlinear MIMO system. The physical model of satellite utilizes three Reaction Wheels as actuators. The controller goal is to change the rotational speed of Reaction Wheels to adjust the satellite in desired course. First, the mathematical model of satellite and its actuators using angular kinematics and kinetic equations is developed. Quantitative feedback theory is then applied to synthesize a set of linear controllers that deals with both nonlinearities in the equations and unknown parameters or disturbance sources. By using basically non-interacting desired outputs and extracting sets of linear time invariant equivalent (LTIE) plants, the controllers set is designed for nine SISO systems. Simulation of closed loop system shows that all desired specifications of closed loop (tracking, stability, disturbance rejection) are robustly satisfied.
Ilya Kolmanovsky - One of the best experts on this subject based on the ideXlab platform.
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Geometric Mechanics Based Nonlinear Model Predictive Spacecraft Attitude Control with Reaction Wheels
Journal of Guidance Control and Dynamics, 2017Co-Authors: Dae Young Lee, Rohit Gupta, Uros Kalabic, Stefano Di Cairano, Anthony M. Bloch, James Cutler, Ilya KolmanovskyAbstract:This paper develops a nonlinear model predictive controller for constrained attitude maneuvering of a fully actuated spacecraft with Reaction Wheels. In the proposed control algorithm, a Lie group ...
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Model predictive control of an underactuated spacecraft with two Reaction Wheels
Journal of Guidance Control and Dynamics, 2017Co-Authors: Christopher D. Petersen, Frederick A. Leve, Ilya KolmanovskyAbstract:This paper presents an application of model predictive control to the attitude dynamics of an underactuated spacecraft with two Reaction Wheels and zero angular momentum. Such a system cannot be stabilized by any smooth or continuous time-invariant feedback law. However, model predictive control has a remarkable ability to generate control laws that are discontinuous in the state and, as such, can be applied to this problem. The model predictive control formulation is analyzed in depth and shown to produce an asymptotically stabilizing controller, which is discontinuous and enforces constraints. Simulations on the full nonlinear model demonstrate that model predictive control can successfully control the attitude of an underactuated spacecraft when the attitude maneuvers are sufficiently small.
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constrained model predictive control of spacecraft attitude with Reaction Wheels desaturation
European Control Conference, 2015Co-Authors: Alberto Guiggiani, Ilya Kolmanovsky, Panagiotis Patrinos, Alberto BemporadAbstract:In this paper we propose a Model Predictive Controller for spacecraft attitude tracking with Reaction wheel actuators. The controller is designed for desaturation of the Reaction Wheels. In contrast with standard desaturation techniques, which rely on the activation of thrusters, the proposed strategy does not need to consume fuel as it exploits external torques derived from gravity gradients and/or the Earth magnetic field. The controller also guarantees that the spacecraft attitude is constrained within specified bounds during desaturation.
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ECC - Constrained Model Predictive Control of spacecraft attitude with Reaction Wheels desaturation
2015 European Control Conference (ECC), 2015Co-Authors: Alberto Guiggiani, Ilya Kolmanovsky, Panagiotis Patrinos, Alberto BemporadAbstract:In this paper we propose a Model Predictive Controller for spacecraft attitude tracking with Reaction wheel actuators. The controller is designed for desaturation of the Reaction Wheels. In contrast with standard desaturation techniques, which rely on the activation of thrusters, the proposed strategy does not need to consume fuel as it exploits external torques derived from gravity gradients and/or the Earth magnetic field. The controller also guarantees that the spacecraft attitude is constrained within specified bounds during desaturation.
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Inertia-Free Spacecraft Attitude Control Using Reaction Wheels
Journal of Guidance Control and Dynamics, 2013Co-Authors: Avishai Weiss, Ilya Kolmanovsky, Dennis S. Bernstein, Amit K. SanyalAbstract:This paper extends the continuous inertia-free control law for spacecraft attitude tracking derived in prior work to the case of three axisymmetric Reaction Wheels. The Wheels are assumed to be mounted in a known and linearly independent, but not necessarily orthogonal, configuration with an arbitrary and unknown orientation relative to the unknown spacecraft principal axes. Simulation results for slew and spin maneuvers are presented with torque and momentum saturation.
K Khorasani - One of the best experts on this subject based on the ideXlab platform.
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IMCSIT - Real-time embedded Fault Detection Estimators in a satellite's Reaction Wheels
Proceedings of the International Multiconference on Computer Science and Information Technology, 2010Co-Authors: Nicolae Tudoroiu, K Khorasani, Ehsan Sobhani-tehrani, Tiberiu Letia, Roxana-elena TudoroiuAbstract:The main idea of this paper is the real-time implementation of the Fault Detection Kalman Filter Estimators (FDKFE) in a satellite's Reaction Wheels during its scientific mission. We assume that the satellite's Reaction Wheels are subjected to several failures due to the abnormal changes in power distribution, motor torque, windings current as well as the temperature caused by a motor current increase or friction. The proposed real-time FDKFE strategies consist of two embedded multiple model bank of nonlinear Kalman Filter (Extended/Unscented) estimators. This research work is based on our previous results in this field and we intend to extend this approach by real-time implementations of the developed FDKFE strategies (FDDM-EKF and FDDM-UKF). Furthermore we will construct a benchmark to compare their results to have an overall image how perform these strategies.
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real time embedded fault detection estimators in a satellite s Reaction Wheels
International Multiconference on Computer Science and Information Technology, 2010Co-Authors: Nicolae Tudoroiu, K Khorasani, Tiberiu Letia, Ehsan Sobhanitehrani, Roxana-elena TudoroiuAbstract:The main idea of this paper is the real-time implementation of the Fault Detection Kalman Filter Estimators (FDKFE) in a satellite's Reaction Wheels during its scientific mission. We assume that the satellite's Reaction Wheels are subjected to several failures due to the abnormal changes in power distribution, motor torque, windings current as well as the temperature caused by a motor current increase or friction. The proposed real-time FDKFE strategies consist of two embedded multiple model bank of nonlinear Kalman Filter (Extended/Unscented) estimators. This research work is based on our previous results in this field and we intend to extend this approach by real-time implementations of the developed FDKFE strategies (FDDM-EKF and FDDM-UKF). Furthermore we will construct a benchmark to compare their results to have an overall image how perform these strategies.
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fault detection and isolation in a redundant Reaction Wheels configuration of a satellite
Systems Man and Cybernetics, 2007Co-Authors: Nader Meskin, K KhorasaniAbstract:This paper investigates development of a nonlinear Fault Detection and Isolation (FDI) strategy for redundant Reaction Wheels in the attitude control subsystem (ACS) of a satellite. Due to the coupling effects and dependencies in Reaction Wheels, the necessary condition for applying a standard geometric FDI approach is not satisfied. To remedy this problem, a set of detection filters are designed whereby through a combination of the residuals the FDI decision making is accomplished successfully. The simulation results presented demonstrate the effectiveness of our proposed FDI method.
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SMC - Fault Detection and Isolation in a redundant Reaction Wheels configuration of a satellite
2007 IEEE International Conference on Systems Man and Cybernetics, 2007Co-Authors: Nader Meskin, K KhorasaniAbstract:This paper investigates development of a nonlinear Fault Detection and Isolation (FDI) strategy for redundant Reaction Wheels in the attitude control subsystem (ACS) of a satellite. Due to the coupling effects and dependencies in Reaction Wheels, the necessary condition for applying a standard geometric FDI approach is not satisfied. To remedy this problem, a set of detection filters are designed whereby through a combination of the residuals the FDI decision making is accomplished successfully. The simulation results presented demonstrate the effectiveness of our proposed FDI method.
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SMC - A fault detection, isolation and reconstruction strategy for a satellite’s attitude control subsystem with redundant Reaction Wheels
2007 IEEE International Conference on Systems Man and Cybernetics, 2007Co-Authors: Tao Jiang, K KhorasaniAbstract:In time-critical systems such as spacecraft systems, fault detection and isolation requirements are of paramount importance and necessity. This paper uses a second order nonlinear sliding mode observer to detect actuator faults in the attitude control subsystem of a satellite with four Reaction Wheels in a tetrahedron configuration. Through a postprocessing of residual signals it is shown how to isolate and reconstruct the faults in all four Reaction Wheels. Simulation results show that the proposed strategy can successfully detect, isolate and reconstruct Reaction wheel faults.
