Modeling and Analysis of Micro-Spacecraft Attitude Sensing with Gyrowheel
This paper proposes two kinds of approaches of angular rate sensing for micro-spacecraft with a gyrowheel (GW), which can combine attitude sensing with attitude control into one single device to achieve a compact micro-spacecraft design. In this implementation, during the three-dimensional attitude...
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| Format: | Article |
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MDPI AG
2016-08-01
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| Series: | Sensors |
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| Online Access: | http://www.mdpi.com/1424-8220/16/8/1321 |
| _version_ | 1817992072911650816 |
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| author | Xiaokun Liu Hui Zhao Yu Yao Fenghua He |
| author_facet | Xiaokun Liu Hui Zhao Yu Yao Fenghua He |
| author_sort | Xiaokun Liu |
| collection | DOAJ |
| description | This paper proposes two kinds of approaches of angular rate sensing for micro-spacecraft with a gyrowheel (GW), which can combine attitude sensing with attitude control into one single device to achieve a compact micro-spacecraft design. In this implementation, during the three-dimensional attitude control torques being produced, two-dimensional spacecraft angular rates can be sensed from the signals of the GW sensors, such as the currents of the torque coils, the tilt angles of the rotor, the motor rotation, etc. This paper focuses on the problems of the angular rate sensing with the GW at large tilt angles of the rotor. For this purpose, a novel real-time linearization approach based on Lyapunov’s linearization theory is proposed, and a GW linearized measurement model at arbitrary tilt angles of the rotor is derived. Furthermore, by representing the two-dimensional rotor tilt angles and tilt control torques as complex quantities and separating the twice periodic terms about the motor spin speed, the linearized measurement model at smaller tilt angles of the rotor is given and simplified. According to the respective characteristics, the application schemes of the two measurement models are analyzed from the engineering perspective. Finally, the simulation results are presented to demonstrate the effectiveness of the proposed strategy. |
| first_indexed | 2024-04-14T01:20:37Z |
| format | Article |
| id | doaj.art-678e3d097b4540f3b85cf6bae65cf866 |
| institution | Directory Open Access Journal |
| issn | 1424-8220 |
| language | English |
| last_indexed | 2024-04-14T01:20:37Z |
| publishDate | 2016-08-01 |
| publisher | MDPI AG |
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| series | Sensors |
| spelling | doaj.art-678e3d097b4540f3b85cf6bae65cf8662022-12-22T02:20:38ZengMDPI AGSensors1424-82202016-08-01168132110.3390/s16081321s16081321Modeling and Analysis of Micro-Spacecraft Attitude Sensing with GyrowheelXiaokun Liu0Hui Zhao1Yu Yao2Fenghua He3School of Astronautics, Harbin Institute of Technology, No. 2 Yikuang Street, Nangang District, Harbin 150080, ChinaSchool of Astronautics, Harbin Institute of Technology, No. 2 Yikuang Street, Nangang District, Harbin 150080, ChinaSchool of Astronautics, Harbin Institute of Technology, No. 2 Yikuang Street, Nangang District, Harbin 150080, ChinaSchool of Astronautics, Harbin Institute of Technology, No. 2 Yikuang Street, Nangang District, Harbin 150080, ChinaThis paper proposes two kinds of approaches of angular rate sensing for micro-spacecraft with a gyrowheel (GW), which can combine attitude sensing with attitude control into one single device to achieve a compact micro-spacecraft design. In this implementation, during the three-dimensional attitude control torques being produced, two-dimensional spacecraft angular rates can be sensed from the signals of the GW sensors, such as the currents of the torque coils, the tilt angles of the rotor, the motor rotation, etc. This paper focuses on the problems of the angular rate sensing with the GW at large tilt angles of the rotor. For this purpose, a novel real-time linearization approach based on Lyapunov’s linearization theory is proposed, and a GW linearized measurement model at arbitrary tilt angles of the rotor is derived. Furthermore, by representing the two-dimensional rotor tilt angles and tilt control torques as complex quantities and separating the twice periodic terms about the motor spin speed, the linearized measurement model at smaller tilt angles of the rotor is given and simplified. According to the respective characteristics, the application schemes of the two measurement models are analyzed from the engineering perspective. Finally, the simulation results are presented to demonstrate the effectiveness of the proposed strategy.http://www.mdpi.com/1424-8220/16/8/1321gyrowheelmicro-spacecraft angular rate sensingreal-time Lyapunov linearizationcomplex quantitystatic measurementdynamic measurement |
| spellingShingle | Xiaokun Liu Hui Zhao Yu Yao Fenghua He Modeling and Analysis of Micro-Spacecraft Attitude Sensing with Gyrowheel Sensors gyrowheel micro-spacecraft angular rate sensing real-time Lyapunov linearization complex quantity static measurement dynamic measurement |
| title | Modeling and Analysis of Micro-Spacecraft Attitude Sensing with Gyrowheel |
| title_full | Modeling and Analysis of Micro-Spacecraft Attitude Sensing with Gyrowheel |
| title_fullStr | Modeling and Analysis of Micro-Spacecraft Attitude Sensing with Gyrowheel |
| title_full_unstemmed | Modeling and Analysis of Micro-Spacecraft Attitude Sensing with Gyrowheel |
| title_short | Modeling and Analysis of Micro-Spacecraft Attitude Sensing with Gyrowheel |
| title_sort | modeling and analysis of micro spacecraft attitude sensing with gyrowheel |
| topic | gyrowheel micro-spacecraft angular rate sensing real-time Lyapunov linearization complex quantity static measurement dynamic measurement |
| url | http://www.mdpi.com/1424-8220/16/8/1321 |
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