Constrained Attitude Control for Flexible Spacecraft: Attitude Pointing Accuracy and Pointing Stability Improvement

被引：29
作者：
Golestani, Mehdi [1 ]
Esmaeilzadeh, Majid [1 ]
Mobayen, Saleh [2 ]
机构：
[1] Iran Univ Sci & Technol, Elect Engn Dept, Tehran 16844, Iran
[2] Natl Yunlin Univ Sci & Technol, Future Technol Res Ctr, Touliu 64002, Yunlin, Taiwan
来源：
IEEE TRANSACTIONS ON SYSTEMS MAN CYBERNETICS-SYSTEMS | 2023年 / 53卷 / 03期
关键词：
Space vehicles; Attitude control; Convergence; Quaternions; Torque; Actuators; Vibrations; Actuator uncertainty; attitude control; constrained control; fixed-time stability; flexible spacecraft; STABILIZATION; TRACKER; DESIGN;
D O I：
10.1109/TSMC.2022.3200481
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
This work deals with the complicated problem of constrained fixed-time attitude control for flexible spacecraft in view of actuator saturations and fault. The proposed controller is composed of two parts. The first part provides fast fixed-time convergence of system trajectories using a novel nonsingular terminal sliding mode control. The second part offers the desired performance specification, such as the rate of convergence, overshoot, and steady-state bounds for attitude/rotation velocity to improve attitude-pointing accuracy and pointing stability. The constrained control method ensures the desired performance in the transient/steady-state phases. It obtains a much simpler structure in comparison with other constrained controls. The simulations on a flexible spacecraft validate the efficacy of the planned scheme.
引用
收藏
页码：1566 / 1572
页数：7
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