The Tobit-Unscented-Kalman-Filter-Based Attitude Estimation Algorithm Using the Star Sensor and Inertial Gyro Combination
For the orbit operation of spacecraft, due to environmental factors, a star sensor installed on the spacecraft must have data censoring, which greatly reduces the attitude determination ability of the traditional combined-attitude-determination algorithm. To address this problem, this paper proposes...
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| Hauptverfasser: | , , , |
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| Format: | Artigo |
| Sprache: | Inglês |
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MDPI AG
2023-06-01
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| Schriftenreihe: | Micromachines |
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| Online-Zugang: | https://www.mdpi.com/2072-666X/14/6/1243 |
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