Attitude control for a nano-satellite
Nano-satellites are classified as satellites weighing less than 20kg. This dissertation presents the design and development of an Attitude Control System (ACS) for a nanosatellite. The ACS onboard a satellite controls the actuators to orientate the satellite to its desired orientation such...
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| Other Authors: | |
| Format: | Thesis |
| Language: | English |
| Published: |
2013
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| Online Access: | http://hdl.handle.net/10356/54760 |
| _version_ | 1811680896204406784 |
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| author | Xing, YiTong. |
| author2 | Low Kay Soon |
| author_facet | Low Kay Soon Xing, YiTong. |
| author_sort | Xing, YiTong. |
| collection | NTU |
| description | Nano-satellites are classified as satellites weighing less than 20kg. This dissertation
presents the design and development of an Attitude Control System (ACS) for a nanosatellite.
The ACS onboard a satellite controls the actuators to orientate the satellite to its
desired orientation such as facing the solar panels towards the sun or orientating the
camera towards the place of interests to capture images. A Model Predictive Control
(MPC) algorithm has been formulated for the attitude control of VELOX-I. Results show
that the ACS is capable of handling the saturation of actuator. The performance has also
been verified experimentally using an air bearing platform.
In a typical satellite configuration, it is common to have a fourth reaction wheel mounted
on a tilted axis for fault redundancy. Due to the constraint of the weight and size for the
satellite, there is no redundancy of ACS. To address this issue, a distributed MPC has
been proposed for attitude control utilizing both the reaction wheels and magnetic
actuators. The simulation results show that the hybrid control system is able to maintain
3-axis control even if a single axis wheel fails. The distributed control scheme is also
shown to react faster than a centralized control scheme. Harvesting of solar power is
required for a satellite to continue operation. The proposed distributed MPC will be
critical for VELOX-I to maintain the sun pointing orientation for harvesting solar power
in the event of single axis reaction wheel failure. |
| first_indexed | 2024-10-01T03:32:20Z |
| format | Thesis |
| id | ntu-10356/54760 |
| institution | Nanyang Technological University |
| language | English |
| last_indexed | 2024-10-01T03:32:20Z |
| publishDate | 2013 |
| record_format | dspace |
| spelling | ntu-10356/547602023-07-04T16:16:41Z Attitude control for a nano-satellite Xing, YiTong. Low Kay Soon School of Electrical and Electronic Engineering DRNTU::Engineering::Electrical and electronic engineering Nano-satellites are classified as satellites weighing less than 20kg. This dissertation presents the design and development of an Attitude Control System (ACS) for a nanosatellite. The ACS onboard a satellite controls the actuators to orientate the satellite to its desired orientation such as facing the solar panels towards the sun or orientating the camera towards the place of interests to capture images. A Model Predictive Control (MPC) algorithm has been formulated for the attitude control of VELOX-I. Results show that the ACS is capable of handling the saturation of actuator. The performance has also been verified experimentally using an air bearing platform. In a typical satellite configuration, it is common to have a fourth reaction wheel mounted on a tilted axis for fault redundancy. Due to the constraint of the weight and size for the satellite, there is no redundancy of ACS. To address this issue, a distributed MPC has been proposed for attitude control utilizing both the reaction wheels and magnetic actuators. The simulation results show that the hybrid control system is able to maintain 3-axis control even if a single axis wheel fails. The distributed control scheme is also shown to react faster than a centralized control scheme. Harvesting of solar power is required for a satellite to continue operation. The proposed distributed MPC will be critical for VELOX-I to maintain the sun pointing orientation for harvesting solar power in the event of single axis reaction wheel failure. Doctor of Philosophy (EEE) 2013-08-02T08:24:31Z 2013-08-02T08:24:31Z 2013 2013 Thesis http://hdl.handle.net/10356/54760 en 172 p. application/pdf |
| spellingShingle | DRNTU::Engineering::Electrical and electronic engineering Xing, YiTong. Attitude control for a nano-satellite |
| title | Attitude control for a nano-satellite |
| title_full | Attitude control for a nano-satellite |
| title_fullStr | Attitude control for a nano-satellite |
| title_full_unstemmed | Attitude control for a nano-satellite |
| title_short | Attitude control for a nano-satellite |
| title_sort | attitude control for a nano satellite |
| topic | DRNTU::Engineering::Electrical and electronic engineering |
| url | http://hdl.handle.net/10356/54760 |
| work_keys_str_mv | AT xingyitong attitudecontrolforananosatellite |