Authors:
Romulus Lungu
1
;
Mihai Lungu
1
and
Mihai Ioan
2
Affiliations:
1
University of Craiova and Faculty of Electrical Engineering, Romania
;
2
University “Politehnica” of Bucharest and Faculty of Aerospace Engineering, Romania
Keyword(s):
Control Moment Gyro, Pyramidal Configuration, Satellite, Attitude Control.
Related
Ontology
Subjects/Areas/Topics:
Engineering Applications
;
Informatics in Control, Automation and Robotics
;
Intelligent Control Systems and Optimization
;
Real-Time Systems Control
;
Robotics and Automation
;
Signal Processing, Sensors, Systems Modeling and Control
;
System Modeling
Abstract:
The paper presents a new architecture for mini-satellites’ attitude control using a cluster consisting of four
control moment gyros, in pyramidal configuration, and feedback from the quaternion and angular velocity
vectors. The designed control law modifies the cluster’s equivalent gyroscopic moment, the equivalent kinetic
moment and the angular velocities’ vector, this leading to the modification of the quaternion vector and to the
change of the satellite‘s attitude. Matlab environment is used for the architecture’s software implementation
and validation, this being achieved for a mini-satellite involved in a typical motion around its own axis.