Attitude Control and Vibration Suppression for Flexible Spacecraft Using Control Moment Gyroscopes

Dynamic equations describing the attitude motion of flexible spacecraft with scissored pairs of control moment gyroscopes are established. A nonlinear controller is designed to drive the flexible spacecraft to implement three-axis large-angle attitude maneuvers with the vibration suppression. Singularity analysis for three orthogonally mounted scissored pairs of control moment gyros shows that there exists no internal singularity in this configuration. A new pseudo-inverse steering law is designed based on the synchronization of gimbal angles of the twin gyros in each pair. To improve the synchronization performance, an adaptive nonlinear feedback controller is designed for each pairs of control moment gyros by using the stability theory of Lyapunov. Simulation results are provided to show the validity of the controllers and the steering law.

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A COMPARISON OF THE EFFECTIVENESS OF DOUBLE- AND SINGLE-GIMBALED CONTROL MOMENT GYROSCOPES FOR VIBRATION SUPPRESSION

Transactions of the Canadian Society for Mechanical Engineering ◽

10.1139/tcsme-2005-0024 ◽

2005 ◽

Vol 29 (3) ◽

pp. 389-402 ◽

Cited By ~ 1

Author(s):

Aaron Muise ◽

Robert J. Bauer

Keyword(s):

Attitude Control ◽

Vibration Suppression ◽

Flexible Structures ◽

Low Frequency ◽

Design System ◽

Control Moment ◽

Control Moment Gyroscopes ◽

And Control ◽

Orbiting Spacecraft ◽

Prototype Design

Control Moment Gyroscopes (CMGs) have typically been used for attitude control of satellites. This paper extends the application of CMGs to regulate vibrations in the flexible appendages of orbiting spacecraft using a novel double- and single-gimbaled CMG prototype design. System Identification and control experiments were carried out to compare the effectiveness of this new CMG to regulate lightly damped, low frequency vibrations in a single flexible rib. Experimental results conclude that the CMG can be effectively used to regulate vibrations in flexible structures and, for equivalent values of gyricity and disturbance, the double-gimbaled CMG performance can be two to three times more effective and independent of the direction of applied disturbance.

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Extended harmonic disturbance observer-based attitude control for flexible spacecraft with control moment gyroscopes

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410019842503 ◽

2019 ◽

Vol 233 (14) ◽

pp. 5331-5346

Author(s):

Liya Huang ◽

Zhong Wu

Keyword(s):

Attitude Control ◽

Disturbance Observer ◽

Wide Frequency Range ◽

Flexible Spacecraft ◽

Space Environment ◽

Harmonic Model ◽

External Disturbances ◽

Control Moment ◽

Control Moment Gyroscopes ◽

Rotor Dynamic

In the flexible spacecraft with control moment gyroscopes, there are multiple disturbances including not only internal disturbances from actuators and flexible appendages, but also external disturbances from space environment. These disturbances are characterized by a wide frequency range and may degrade attitude control performance to a great extent. In this paper, the lumped disturbance is modeled as a harmonic plus a polynomial model, and an extended harmonic disturbance observer (EHDO) is proposed to estimate the total disturbance. Since the rotor dynamic imbalance disturbance from control moment gyroscopes is described by an internal harmonic model, the lumped disturbance can be estimated precisely via EHDO even with a lower bandwidth. Afterwards, a backstepping-based composite controller is designed to compensate the disturbances by combining the output of EHDO and realize high-precision attitude control for flexible spacecraft with control moment gyroscopes. Simulation results are presented to demonstrate the effectiveness of the proposed method.

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Agile Attitude Control and Vibration Suppression of Flexible Spacecraft Using Control Moment Gyros

IFAC Proceedings Volumes ◽

10.3182/20130902-5-de-2040.00138 ◽

2013 ◽

Vol 46 (19) ◽

pp. 417-422 ◽

Cited By ~ 2

Author(s):

Hiroshi Okubo ◽

Shinsuke Kuwamoto

Keyword(s):

Attitude Control ◽

Vibration Suppression ◽

Flexible Spacecraft ◽

Control Moment

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Adaptive robust attitude control for flexible spacecraft with control moment gyroscopes

2016 12th World Congress on Intelligent Control and Automation (WCICA) ◽

10.1109/wcica.2016.7578603 ◽

2016 ◽

Cited By ~ 1

Author(s):

Lu Wang ◽

Yu Guo ◽

Wei Yao ◽

Qingwei Chen

Keyword(s):

Attitude Control ◽

Flexible Spacecraft ◽

Control Moment ◽

Control Moment Gyroscopes

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Active Control Comparison of Vibration in Flexible Spacecraft Using Different Active Friction Joints

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.446-447.1160 ◽

2013 ◽

Vol 446-447 ◽

pp. 1160-1164

Author(s):

Sahar Bakhtiari Mojaz ◽

Hamed Kashani

Keyword(s):

Energy Dissipation ◽

Attitude Control ◽

Vibration Suppression ◽

Excitation Amplitude ◽

Step Function ◽

Flexible Spacecraft ◽

Control Effort ◽

Stick Slip ◽

Control Comparison ◽

Frictional Joints

Vibration properties of most assembled mechanical systems depend on frictional damping in joints. The nonlinear transfer behavior of the frictional interfaces often provides the dominant damping mechanism in structure and plays an important role in the vibratory response of it. For improving the performance of systems, many studies have been carried out to predict measure and enhance the energy dissipation of friction. This paper presents a new approach to vibration reduction of flexible spacecraft with enhancing the energy dissipation of frictional dampers. Spacecraft is modeled as a 3 degree of freedom mass-spring system which is controlled by a lead compensator and System responses to step function evaluated. Coulomb and Jenkins element has been used as vibration suppression mechanisms in joints and sensitivity of their performance to variations of spacecraft excitation amplitude and damper properties is analyzed. The relation between frictional force and displacement derived and used in optimization of control performance. Responses of system and control effort needed for the vibration control are compared for these two frictional joints. It is shown that attitude control effort reduces, significantly with coulomb dampers and response of system improves. On the other hand, due to stick-slip phenomena in Jenkins element, we couldn’t expect the same performance from Jenkins damper.

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