Spacecraft Attitude Control

Xie, Yongchun; Lei, Yiyan; Jun, Guo; Meng, Bo

doi:10.1007/978-981-33-6448-6_6

Cited by 1 publication

(3 citation statements)

References 8 publications

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“…Y > O(≥ O) denotes the matrix Y is real symmetric and positive definite (semi-definite). The norm of a vector W(t) is given by kW ðtÞk 2 2 ¼ W T ðtÞW ðtÞ. For square matrix Q, defining sym(Q) = Q + Q T .…”

Section: Notationmentioning

confidence: 99%

“…The control objective is that the signal of reference system (3) can be tracked by the state of system (2). A delay-dependent robust tracking feedback controller based on the DO and FEO will be designed to track reference attitude, which can ensure that the attitude tracking error control system is asymptotically stable (AS) in next section.…”

Section: The Tracking Reference Modelmentioning

confidence: 99%

“…To accomplish space missions, the flexible satellite needs to track desired attitude signal by real-time attitude manoeuvre. 1,2 Due to the highaccuracy tracking demands for flexible satellites, many attitude tracking control methods such as robust control, [3][4][5] sliding mode control (SMC) 6,7 and adaptive control 8,9 have been proposed to achieve ideal attitude tracking performance. In Zhu et al, 10 a stable flexible satellite attitude tracking result was obtained based on the nonsingular terminal SMC and adaptive control methods.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Composite attitude fault tolerant tracking control for flexible satellite with time delay

Xiao-li

Shao

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This article deals with the problem of attitude tracking control for flexible satellite under flexible vibration disturbance, actuator fault and time delay. Based on disturbance observer and fault tolerant control techniques, the flexible vibration disturbance and actuator fault are effectively estimated by disturbance observer and fault estimation observer, respectively. Meanwhile, a delay-dependent attitude tracking feedback controller is designed to ensure that the reference attitude is stably tracked. To reduce the conservatism of the designed algorithm, a time delay correlative decomposition factor is introduced to make the flexible satellite have a better performance for attitude tracking control. Finally, the effectiveness of the proposed method is illustrated by numerical simulations.

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Section: Notationmentioning

confidence: 99%

Section: The Tracking Reference Modelmentioning

confidence: 99%