Fault-tolerant control and vibration suppression of flexible spacecraft: An interconnected system approach
نویسندگان
چکیده
منابع مشابه
Active Vibration Suppression of a Nonlinear Flexible Spacecraft
In this article, the issue of attitude control and active vibration suppression of a nonlinear flexible spacecraft is assessed through piezoelectric patches as actuator and sensors. Two controller loops are applied: the inner loop, to make the panel vibration damped through piezoelectric patches; and the outer loop, to perform spacecraft maneuver using the reaction wheel acting on the hub. An o...
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Fault-tolerant constrained attitude controllers are proposed for flexible spacecraft in the presence of input saturation and actuator fault, as well as model uncertainty and external disturbance. Two input saturations, that is amplitude saturation and, amplitude and rate saturation are considered and simple and effective compensators are designed to deal with the effect of input saturation. Two...
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A desired characteristic of future spacecraft and space structures is the possibility of reducing the costs inherent with their transport in the space. Hence, it is necessary to decrease their weight; the main drawback consists of the decreased rigidity of the structure. Therefore, the elimination of vibrations becomes an important issue in spacecraft maneuvers. Another issue, related to the pr...
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ENGINEERING NOTES are short manuscripts describing new developments or important results of a preliminary nature. These Notes cannot exceed 6 manuscript pages and 3 figures; a page of text may be substituted for a figure and vice versa. After informal review by the editors, they may be published within a few months of the date of receipt. Style requirements are the same as for regular contribut...
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This paper presents a dual-stage control system design method for the rotational maneuver and vibration stabilization of a spacecraft with flexible appendages. In this design approach, attitude control system and vibration suppression were designed separately using lower order model. The design of attitude controller was based on sliding mode control (SMC) theory leading to a discontinuous cont...
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ژورنال
عنوان ژورنال: Chinese Journal of Aeronautics
سال: 2020
ISSN: 1000-9361
DOI: 10.1016/j.cja.2020.02.014