| Autor: |
Hajnorouzali, Yasaman, Malekzadeh, Maryam, Ataei, Mohammad |
| Předmět: |
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| Zdroj: |
Journal of Vibration & Control; Jan2023, Vol. 29 Issue 1/2, p346-361, 16p |
| Abstrakt: |
This paper aims to design an attitude controller for a flexible spacecraft under external disturbance and uncertainty. The spacecraft's attitude is controlled by a super twisting controller based on a disturbance observer. This paper's spacecraft system is non-minimum phase since mode-shapes are included in the output; thus, the following four methods are designed to compensate for the constraint: (1) The output redefinition method, where outputs are redefined as a combination of mode-shapes and quaternions. (2) The flexible spacecraft is controlled without measuring the mode-shapes, and only the quaternion parameters are selected as the output. (3) An advanced sliding surface is proposed, in which the mode-shapes are considered in the sliding surface. (4) The difference between flexible and rigid spacecraft dynamics is considered as disturbance, and its effect on the system is compensated. The finite-time stability of the closed-loop system is proved by leveraging the Lyapunov theory. The numerical simulation illustrates the closed-loop system's effectiveness in terms of robustness compared to the existing controller and the four mentioned methods. [ABSTRACT FROM AUTHOR] |
| Databáze: |
Complementary Index |
| Externí odkaz: |
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