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Parameter Tuning Of An Active Force Control For Cmg-Based Controlled Small Satellite

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,...

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Main Author: Linghan, Samanaseh
Format: Monograph
Language:English
Published: Universiti Sains Malaysia 2019
Subjects:
T Technology
Online Access:http://eprints.usm.my/58685/1/Parameter%20Tuning%20Of%20An%20Active%20Force%20Control%20For%20Cmg-Based%20Controlled%20Small%20Satellite.pdf
http://eprints.usm.my/58685/
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spelling my.usm.eprints.58685 http://eprints.usm.my/58685/ Parameter Tuning Of An Active Force Control For Cmg-Based Controlled Small Satellite Linghan, Samanaseh T Technology 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 Matlab®/Simulink® 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. Universiti Sains Malaysia 2019-06-01 Monograph NonPeerReviewed application/pdf en http://eprints.usm.my/58685/1/Parameter%20Tuning%20Of%20An%20Active%20Force%20Control%20For%20Cmg-Based%20Controlled%20Small%20Satellite.pdf Linghan, Samanaseh (2019) Parameter Tuning Of An Active Force Control For Cmg-Based Controlled Small Satellite. Project Report. Universiti Sains Malaysia, Pusat Pengajian Kejuruteraan Aeroangkasa. (Submitted)
institution Universiti Sains Malaysia
building Hamzah Sendut Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Sains Malaysia
content_source USM Institutional Repository
url_provider http://eprints.usm.my/
language English
topic T Technology
spellingShingle T Technology
Linghan, Samanaseh
Parameter Tuning Of An Active Force Control For Cmg-Based Controlled Small Satellite
description 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 Matlab®/Simulink® 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.
format Monograph
author Linghan, Samanaseh
author_facet Linghan, Samanaseh
author_sort Linghan, Samanaseh
title Parameter Tuning Of An Active Force Control For Cmg-Based Controlled Small Satellite
title_short Parameter Tuning Of An Active Force Control For Cmg-Based Controlled Small Satellite
title_full Parameter Tuning Of An Active Force Control For Cmg-Based Controlled Small Satellite
title_fullStr Parameter Tuning Of An Active Force Control For Cmg-Based Controlled Small Satellite
title_full_unstemmed Parameter Tuning Of An Active Force Control For Cmg-Based Controlled Small Satellite
title_sort parameter tuning of an active force control for cmg-based controlled small satellite
publisher Universiti Sains Malaysia
publishDate 2019
url http://eprints.usm.my/58685/1/Parameter%20Tuning%20Of%20An%20Active%20Force%20Control%20For%20Cmg-Based%20Controlled%20Small%20Satellite.pdf
http://eprints.usm.my/58685/
_version_ 1768007917277020160
score 13.211869

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