Parameter tuning of an active force control for cmg-based controlled small satellite
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Date
2019-06
Authors
Linghan A/L Samanaseh
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Abstract
A control moment gyroscope (CMG) system is the most appropriate actuator to
be actualized in attitude determination and control system (ADCS) of small satellite.
These actuators can provide unique torque, angular momentum and slew rate capabilities
to small satellites without any increase in power, mass or volume. This will help small
satellites become more agile. A four single gimbal control moment gyroscope (4
SGCMG) is actualize by owing to its efficiency and plays a significant role in attitude
control of agile small satellite. However, the efficiency of the CMG system is limited to
in executing rapid attitude maneuver and high precision pointing due to external
disturbance torques from space environment and internal disturbance of actuator. Hence,
an Active Force Control (AFC) technique is enforced and integrated with proportional
derivative (PD) controller to enhance ADCS by rejecting the disturbance torques robustly.
In this research, tuning the mass parameter of the dynamic system and the AFC gain, the
robustness of AFC technique is triggered. So that, the PD-AFC attitude control scheme
able to command the CMG system to give suitable control torque to fulfill the satellite
mission. The singularity robust (SR) steering law is integrated with CMG system in order
to neglect the singularity state of CMG system by setting the initial gimbal angle, that
allowing space missions to be successfully executed. All mathematical models were made
amenable for numerical simulations in MatlabĀ®/SimulinkĀ® in order to study the effect
of AFC parameters tuning on the attitude control performance of the satellite by
considering the presence of external disturbance torques.