Verification of control moment gyroscopes based attitude control systems for agile satellite missions

2011 ◽  
Author(s):  
Emre Yavuzoglu ◽  
Erhan Topal ◽  
Aykut Kutlu ◽  
Halime Urek ◽  
M. Emin Gulluoglu ◽  
...  
Keyword(s):  
Control Systems ◽  
Attitude Control ◽  
Control Moment ◽  
Control Moment Gyroscopes ◽  
Agile Satellite ◽  
Satellite Missions

Control moment gyroscopes for spacecraft attitude control systems: Current status and prospects

2015 ◽  
Vol 6 (3) ◽  
pp. 236-240 ◽  
Author(s):  
A. R. Mkrtychyan ◽  
N. I. Bashkeev ◽  
D. O. Yakimovskii ◽  
D. I. Akashev ◽  
O. B. Yakovets
Keyword(s):  
Control Systems ◽  
Attitude Control ◽  
Current Status ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Control Moment ◽  
Control Moment Gyroscopes

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

2005 ◽  
Vol 29 (3) ◽  
pp. 389-402 ◽  
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.

Optimum Design of the Support Structure of the CMG Based on CAE

2012 ◽  
Vol 184-185 ◽  
pp. 364-367
Author(s):  
Yong Xin Gao ◽  
Dong Yang ◽  
Zhi Jia Liu
Keyword(s):  
Attitude Control ◽  
3D Models ◽  
Optimized Design ◽  
Original Design ◽  
Support Structure ◽  
3D Design ◽  
Control Moment ◽  
Design Structure ◽  
Control Moment Gyroscopes ◽  
Design Software

A Control Moment Gyroscopes (CMG) is a torque generator for attitude control of a high resolution and high agility satellite without any increase in power, mass or volume. In this paper, a new support structure of the CMG is proposed. According to the configuration idea of the CMGs, the original design model of the support structure is established. Furthermore, the topology optimization is performed by the FEM software ANSYS and after that came up with a suitable layout of the support structure of the CMG. Based on the optimized design results, the 3D models of the CMG and its support structure are established by the 3D design software Pro/E. Frequency of the assembly is analyzed and calculated. Finally, took the launch dynamics environments into consideration, the vibration testing are carried out to verify the rationality of the new design structure.

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

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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