DocumentCode :
3706939
Title :
Determination and control of the satellites´ attitude by using a pyramidal configuration of four control moment gyros
Author :
Romulus Lungu;Mihai Lungu;Mihai Ioan
Author_Institution :
University of Craiova, Faculty of Electrical Engineering, Carol Blv., no. 6, Romania
Volume :
1
fYear :
2015
fDate :
7/1/2015 12:00:00 AM
Firstpage :
448
Lastpage :
456
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.
Keywords :
"Satellites","Attitude control","Angular velocity","Quaternions","Kinetic theory","Mathematical model","Actuators"
Publisher :
ieee
Conference_Titel :
Informatics in Control, Automation and Robotics (ICINCO), 2015 12th International Conference on
Type :
conf
Filename :
7350508
Link To Document :
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