Attitude control for the rigid spacecraft with the improved extended state observer
- Autores: Yufeng Cao, Qi Liu, Guiqin He, Qiuling Zhao, Fang Liu
- Localización: Applied Mathematics and Nonlinear Sciences, ISSN-e 2444-8656, Vol. 8, Nº. 1, 2023, págs. 121-134
- Idioma: inglés
- Enlaces
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Resumen
In this article, a three-axis attitude manoeuvre spacecraft consisting of a central rigid body and a rotating solar arrayis studied. The rotating solar array is considered a disturbance to the spacecraft. In the design of the controller, thecoupled terms and the rotating solar array are considered a disturbance. The improved extended state observer is proposedby combing the sliding mode observer with the originally extended state observer to estimate the disturbance. The slidingmode control method is adopted to adjust the attitude of the spacecraft. Numerical simulations are presented to demonstratethe outstanding performance of the present observer.
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