Using of H-Infinity Control Method in Attitude Control System of Rigid-Flexible Satellite

The attitude control systems of satellites with rigid and flexible components are demanding more and more better performance resulting in the development of several methods control. For that reason, control design methods presently available, including parameters and states estimation, robust and adaptive control, as well as linear and nonlinear theory, need more investigation to know their capability and limitations. In this paper the investigated technique is H-Infinity method in the performance of the Attitude Control System of a Rigid-Flexible Satellite.

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Optimal Control for Combined Energy Storage and Attitude Control System (CEACS) in Small Satellites

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.110-116.3587 ◽

2011 ◽

Vol 110-116 ◽

pp. 3587-3592 ◽

Cited By ~ 1

Author(s):

Ban Ying Siang ◽

Renuganth Varatharajoo

Keyword(s):

Control System ◽

Energy Storage ◽

Attitude Control ◽

Control Methods ◽

Attitude Control System ◽

H Infinity ◽

Small Satellites ◽

Satellite Attitude Control ◽

H Infinity Control ◽

Control Modules

The combined energy storage and attitude control system (CEACS) combines both energy storage and attitude control modules via the flywheel technology. Previously only the conventional control methods were tested for CEACS. In this paper, H2 and H-infinity control methods are implemented in CEACS. The satellite attitude control performances show that both control options can be employed for a good attitude pointing accuracy. (Abstract)

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H∞ Control Design for a Rigid-Flexible Spacecraft under a Fuel Slosh Influence

WSEAS TRANSACTIONS ON SYSTEMS ◽

10.37394/23202.2020.19.36 ◽

2020 ◽

Vol 19 ◽

Keyword(s):

Attitude Control ◽

Control Method ◽

Rigid Motion ◽

Attitude Control System ◽

Control Effort ◽

H Infinity ◽

Longitudinal Dynamic ◽

H Infinity Control ◽

Pointing Accuracy ◽

Fuel Slosh

The spacecraft Attitude Control System (ACS) performance and robustness depend on the interactioneffects between the fuel slosh motion, the panel's flexible motion, and the spacecraft rigid motion, mainly duringtranslational and/or rotational maneuvers. In regards to satellite pointing accuracy flexibility and fuel, slosh is thetwo most important effects that should be considered in the satellite ACS design since their interactions can damage the ACS performance and robustness. Once, the lowest vibration frequencies, normally of the sloshing modeare about six times less than of the ACS bandwidth. Therefore, there is a strong possibility that this mode can destabilize the ACS pointing accuracy. This phenomenon is called spillover because the control effort spills over outside the control bandwidth. As a result, the designer needs to explore the limits between the conflicting requirements of performance, that is, increase of the bandwidth without introduction noise in the ACS keeping the systemrobustness to parameters variation. In this paper, one applies the H infinity control method which can deal withthese two design requirements (performance and robustness) considering the controller error pointing that may belimited by the minimum time necessary to suppress disturbances that affect the satellite attitude acquisition. Theequations of motions are obtained considering the Lagrange method for small flexible deformations and a mechanical model of liquid sloshing which allows modeling and investigating the longitudinal dynamic characteristics of apartially filled liquid tank during a pitch maneuver, satisfying performance and robustness requirements.

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H∞ Control Design for a Flexible Spacecraft with Fuel Slosh Dynamics

WSEAS TRANSACTIONS ON SYSTEMS ◽

10.37394/23202.2020.19.35 ◽

2020 ◽

Vol 19 ◽

Keyword(s):

Attitude Control ◽

Control Method ◽

Rigid Motion ◽

Attitude Control System ◽

Control Effort ◽

H Infinity ◽

Longitudinal Dynamic ◽

H Infinity Control ◽

Pointing Accuracy ◽

Fuel Slosh

The spacecraft Attitude Control System (ACS) performance and robustness depend on the interaction effects between the fuel slosh motion, the panel's flexible motion and the spacecraft rigid motion, mainly during translational and/or rotational maneuvers. In regards to satellite pointing accuracy flexibility and fuel slosh are the two most important effects that should be considered in the satellite ACS design since their interactions can damage the ACS performance and robustness. Once, the lowest vibration frequencies, normally of the slosh mode are about six times less than of the ACS bandwidth. Therefore, there is a strong possibility that this mode can destabilize the ACS pointing. This phenomenon is called spillover, because the control effort spills over outside the control bandwidth. As a result, the designer needs to explore the limits between the conflicting requirements of performance, that is, increase of the bandwidth without introduction noise in the ACS keeping the system robustness to parameters variation. In this paper one applies the H infinity control method which is able to deal with these two design requirements (performance and robustness) considering the controller error pointing that may be limited by the minimum time necessary to suppress disturbances that affects the satellite attitude acquisition. The equations of motions are obtained considering Lagrange method for small flexible deformations and a mechanical model of liquid sloshing which allows modeling and investigating the longitudinal dynamic characteristics of partially filled liquid tank during a pitch maneuver. The results of the simulations have shown that the H-infinity controller was able to control the rigid motion and suppress the vibrations

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Comparison between H2 and H∞ Optimal Control Solutions for a Combined Energy and Attitude Control System

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.225.464 ◽

2012 ◽

Vol 225 ◽

pp. 464-469 ◽

Cited By ~ 1

Author(s):

Ban Ying Siang ◽

Renuganth Varatharajoo

Keyword(s):

Optimal Control ◽

Control System ◽

Pid Control ◽

Attitude Control ◽

Disturbance Rejection ◽

Control Method ◽

Proportional Integral Derivative ◽

Attitude Control System ◽

Control Option ◽

Optimal Control Methods

The paper focuses on applying optimal control solutions to combined energy storage and attitude control system (CEACS) under different reference missions. In previous researches, the proportional-integral-derivative (PID) control method, the PID-active force control method and H2 control were tested for CEACS and achieved its mission requirement. However, problems such as the in-orbit system uncertainties affect the PID control performances. Thus, two optimal control methods, H2 and H∞ controls are proposed and tested on CEACS under different mission scenarios to improve its pitch attitude accuracy. Results show that both H2 and H∞ are able to achieve the reference mission requirement even under the influence of uncertainties (non-ideal). Moreover comparison between H2 and H∞ shows the H2 is a better control option for CEACS in terms of disturbance rejection.

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Adaptive control of free-flying space robot with position/attitude control system

10.2514/6.1997-3557 ◽

1997 ◽

Cited By ~ 1

Author(s):

Kei Senda ◽

Hideyuki Nagaoka ◽

Yoshisada Murotsu ◽

Kei Senda ◽

Hideyuki Nagaoka ◽

...

Keyword(s):

Adaptive Control ◽

Control System ◽

Attitude Control ◽

Space Robot ◽

Attitude Control System

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H-Infinity Control Design Considering Packet Loss as a Disturbance for Networked Control Systems

IEICE Transactions on Fundamentals of Electronics Communications and Computer Sciences ◽

10.1587/transfun.e100.a.353 ◽

2017 ◽

Vol E100.A (2) ◽

pp. 353-360 ◽

Cited By ~ 2

Author(s):

Takashi OGURA ◽

Kentaro KOBAYASHI ◽

Hiraku OKADA ◽

Masaaki KATAYAMA

Keyword(s):

Control Systems ◽

Packet Loss ◽

Networked Control Systems ◽

Control Design ◽

Networked Control ◽

H Infinity ◽

H Infinity Control

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Adaptive control applied to Space Station attitude control system

10.2514/6.1992-4483 ◽

1992 ◽

Cited By ~ 6

Author(s):

QUANG LAM ◽

RICHARD CHIPMAN ◽

TSAY-HSIN HU ◽

ERIC HOLMES ◽

JOHN SUNKEL

Keyword(s):

Adaptive Control ◽

Control System ◽

Attitude Control ◽

Space Station ◽

Attitude Control System

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Design of Attitude Control System for UAV Based on Feedback Linearization and Adaptive Control

Mathematical Problems in Engineering ◽

10.1155/2014/492680 ◽

2014 ◽

Vol 2014 ◽

pp. 1-8 ◽

Cited By ~ 4

Author(s):

Wenya Zhou ◽

Kuilong Yin ◽

Rui Wang ◽

Yue-E Wang

Keyword(s):

Adaptive Control ◽

Control System ◽

Attitude Control ◽

Feedback Linearization ◽

Control Law ◽

Attitude Control System ◽

Model Uncertainties ◽

Performance Indexes ◽

Attitude Dynamic ◽

Adaptive Control Law

Attitude dynamic model of unmanned aerial vehicles (UAVs) is multi-input multioutput (MIMO), strong coupling, and nonlinear. Model uncertainties and external gust disturbances should be considered during designing the attitude control system for UAVs. In this paper, feedback linearization and model reference adaptive control (MRAC) are integrated to design the attitude control system for a fixed wing UAV. First of all, the complicated attitude dynamic model is decoupled into three single-input single-output (SISO) channels by input-output feedback linearization. Secondly, the reference models are determined, respectively, according to the performance indexes of each channel. Subsequently, the adaptive control law is obtained using MRAC theory. In order to demonstrate the performance of attitude control system, the adaptive control law and the proportional-integral-derivative (PID) control law are, respectively, used in the coupling nonlinear simulation model. Simulation results indicate that the system performance indexes including maximum overshoot, settling time (2% error range), and rise time obtained by MRAC are better than those by PID. Moreover, MRAC system has stronger robustness with respect to the model uncertainties and gust disturbance.

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A New Approach to Fault Diagnosis for Satellite Control Systems Based on Machine Learning

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.457-458.1070 ◽

2012 ◽

Vol 457-458 ◽

pp. 1070-1076 ◽

Cited By ~ 1

Author(s):

Fei Yan ◽

Ming Jian Li

Keyword(s):

Machine Learning ◽

Control System ◽

Fault Diagnosis ◽

Control Systems ◽

Attitude Control ◽

Support Vector ◽

Learning Technology ◽

Attitude Control System ◽

Satellite Control ◽

Intelligent Approach

Based on the traditional method of analytical redundancy fault diagnosis, the advanced machine learning technology is combined with the model-based fault diagnosis so as to form a new intelligent approach to the fault diagnosis for satellite control systems. The support vector regression technique in statistical learning theory is employed to model the control system with a little sampling data firstly. Then the feasibility of detecting and identifying faults for the satellite attitude control system with the Mahalanobis distance is analyzed in detail. Finally a set of fault-detection observers are designed and implemented based on the residual evaluation. The simulation result indicates that the diagnosing method proposed in this paper is characterized with light computation burden and good real-time performance.

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