Steering Law of Control Moment Gyros Using Optimization of Initial Gimbal Angles for Satellite Attitude Control

2008 ◽  
Vol 74 (747) ◽  
pp. 2698-2704 ◽  
Author(s):  
Yasuyuki NANAMORI ◽  
Masaki TAKAHASHI
Keyword(s):  
Attitude Control ◽  
Satellite Attitude ◽  
Control Moment ◽  
Satellite Attitude Control ◽  
Steering Law

Combined Use of Control Moment Gyros and Magnetic Torque Rods for Satellite Attitude Control

2010 ◽  
Author(s):  
Tuba C. Elmas ◽  
Ozan Tekinalp
Keyword(s):  
Attitude Control ◽  
Magnetic Torque ◽  
Inverse Algorithm ◽  
New Approach ◽  
Satellite Attitude ◽  
Control Moment ◽  
Satellite Attitude Control ◽  
Control Moment Gyroscopes ◽  
Combined Use ◽  
Pseudo Inverse

A new approach to the attitude control of an over actuated satellite is presented. A control moment gyroscopes cluster containing four actuators in a pyramid mounting configuration, and a set of three orthogonal magnetic torque rods are considered to steer the satellite. Two steering algorithms, Moore-Penrose pseudo inverse, and the recently developed blended-inverse, are considered. The success of the blended-inverse algorithm to select the desired actuators in the system is demonstrated. It is also shown through simulations that the blended-inverse algorithm successfully carries out the maneuver without getting trapped in singular configurations, while the classical Moore-Penrose pseudo inverse algorithm fails to realize.

scholarly journals Satellite Attitude Control Using Control Moment Gyroscopes

2020 ◽  
pp. 94-105
Author(s):  
Kenedy Matiasso Portella ◽  
Wilcker Neuwald Schinestzki ◽  
Róger Mateus Sehnem ◽  
Leonardo Barros da Luz ◽  
Lorenzzo Quevedo Mantovani ◽  
...  
Keyword(s):  
Attitude Control ◽  
Angular Momentum Vector ◽  
Attitude Control System ◽  
Linear Quadratic ◽  
Control Laws ◽  
Final Choice ◽  
Satellite Attitude ◽  
Control Moment ◽  
Satellite Attitude Control ◽  
Control Moment Gyroscopes

In space missions, there is often a need for an attitude control system capable of maintaining the desired attitude. In situations that require agile and accurate responses, which also require large torques, control moment gyroscopes (CMGs) may be used. Control moment gyroscopes are high angular moment gyros mounted on gimbals and are responsible for changing the direction of the angular momentum vector, consequently generating the control torques. There are several linear and nonlinear techniques that can be employed in the design of control laws with the final choice being a compromise between simplicity, effectiveness, efficiency and robustness. The main objective of this study is to evaluate the performance of control systems techniques with 4 CMGs in a pyramidal arrangement, either by using Linear Quadratic Tracker (LQT) with integral compensator or Exponential Mapping Control (EMC). A reference attitude will be defined to be traced in the presence of disturbance torques caused by the gravitational gradient.

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