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Simulation of satellite attitude control using Single Gimbal Control Moment Gyro (SGCMG) system
Courie I.A.a, Jenie Y.I.a, Poetro R.E.a
a Faculty of Mechanical and Aerospace Engineering, Institut Teknologi Bandung, Indonesia
[vc_row][vc_column][vc_row_inner][vc_column_inner][vc_separator css=”.vc_custom_1624529070653{padding-top: 30px !important;padding-bottom: 30px !important;}”][/vc_column_inner][/vc_row_inner][vc_row_inner layout=”boxed”][vc_column_inner width=”3/4″ css=”.vc_custom_1624695412187{border-right-width: 1px !important;border-right-color: #dddddd !important;border-right-style: solid !important;border-radius: 1px !important;}”][vc_empty_space][megatron_heading title=”Abstract” size=”size-sm” text_align=”text-left”][vc_column_text]© Published under licence by IOP Publishing Ltd.Control Moment Gyro (CMG) is a type Attitude Control System (ACS), a system used to change the attitude of satellite along its orbit. CMG generates required gyroscopic torque by spinning a number of rotors, and directs the torque by changing the orientation of those rotors using gimbals. CMG is capable of generating a large amount of torque with relatively low power which makes it suitable for high agility mission requiring 1-10 deg/s slew rate. A major problem encountered with the use of CMG in practice is the presence of singularity, a state in which, the CMG is unable to generate torque along certain direction. Various steering algorithms have been developed to overcome the singularity problems. In this paper, the attitude control performance of Single Gimbal Control Moment Gyro (SGCMG) system is investigated. Steering algorithm also implemented to overcome singularity problem that might be encountered. The results show that SGCMG capable of generating torque required for agile attitude maneuver in the presence of singularity.[/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”Author keywords” size=”size-sm” text_align=”text-left”][vc_column_text]Attitude maneuver,Control moment gyros,Control performance,Gyroscopic torques,Satellite attitude control,Single gimbal control moment gyros (SGCMG),Singularity problems,Steering algorithms[/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”Indexed keywords” size=”size-sm” text_align=”text-left”][vc_column_text][/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”Funding details” size=”size-sm” text_align=”text-left”][vc_column_text][/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”DOI” size=”size-sm” text_align=”text-left”][vc_column_text]https://doi.org/10.1088/1742-6596/1130/1/012003[/vc_column_text][/vc_column_inner][vc_column_inner width=”1/4″][vc_column_text]Widget Plumx[/vc_column_text][/vc_column_inner][/vc_row_inner][/vc_column][/vc_row][vc_row][vc_column][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][/vc_column][/vc_row]