Study of the accuracy provided by small satellite attitude determination & control system

Purpose This paper aims to investigate the attitude control pointing improvement for a small satellite with control moment gyroscopes (CMGs) using the active force control (AFC) method. Design/methodology/approach The AFC method is developed with its governing equations and integrated into the conventional proportional-derivative (PD) controller of a closed-loop satellite attitude control system. Two numerical simulations of an identical attitude control mission namely the PD controller and the PD+AFC controller were carried out using the MATLAB®-SimulinkTM software and their attitude control performances were demonstrated accordingly. Findings Having the PD+AFC controller, the attitude maneuver can be completed within the desired slew rate, which is about 2.14 degree/s and the attitude pointing accuracies for the roll, pitch and yaw angles have improved significantly by more than 85% in comparison with the PD controller alone. Moreover, the implementation of the AFC into the conventional PD controller does not cause significant difference on the physical structure of the four single gimbal CMGs (4-SGCMGs). Practical implications To achieve a precise attitude pointing mission, the AFC method can be applied directly to the existing conventional PD attitude control system of a CMG-based satellite. In this case, the AFC is indeed the backbone for the satellite attitude performance improvement. Originality/value The present study demonstrates that the attitude pointing of a small satellite with CMGs is improved through the implementation of the AFC scheme into the PD controller.

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Kalman Filter Innovation Sequence Based Fault Detection in LEO Satellite Attitude Determination and Control System

2007 3rd International Conference on Recent Advances in Space Technologies ◽

10.1109/rast.2007.4284023 ◽

2007 ◽

Cited By ~ 5

Author(s):

A. Okatan ◽

Ch. Hajiyev ◽

U. Hajiyeva

Keyword(s):

Kalman Filter ◽

Control System ◽

Fault Detection ◽

Attitude Determination ◽

Satellite Attitude ◽

And Control ◽

Leo Satellite

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Developments of attitude determination and control system of microsats: A survey

Proceedings of the Institution of Mechanical Engineers Part I Journal of Systems and Control Engineering ◽

10.1177/0959651819895173 ◽

2020 ◽

pp. 095965181989517

Author(s):

Liang He ◽

Wenjie Ma ◽

Pengyu Guo ◽

Tao Sheng

Keyword(s):

Neural Networks ◽

Control System ◽

Deep Neural Networks ◽

Attitude Determination ◽

Alignment Error ◽

Control Methods ◽

Satellite Attitude ◽

Determination Methods ◽

And Control

This study surveys the developments in satellite attitude determination and control system, especially for microsats. This survey is not intended to be complete but is limited to the most significant developments of sensors, actuators, and algorithms in the last two decades. First, attitude determination methods including algorithms and sensors together with actuator-based control methods are introduced. Furthermore, current problems in alignment error, flexible satellites, and low redundancy of microsats attitude determination and control system are discussed. Moreover, developments of some deep-neural-networks-based methods, which have great potential in solving current problems, are summarized.

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