基于输入成形的挠性航天器自适应滑模控制
收稿日期: 2012-10-23
修回日期: 2013-01-04
网络出版日期: 2013-01-15
基金资助
国家自然科学基金(61104153);国家"973"计划(2012CB720000)
Adaptive Sliding Mode Control of Flexible Spacecraft on Input Shaping
Received date: 2012-10-23
Revised date: 2013-01-04
Online published: 2013-01-15
Supported by
National Natural Science Foundation of China (61104153);National Basic Research Program of China (2012CB720000)
苗双全 , 丛炳龙 , 刘向东 . 基于输入成形的挠性航天器自适应滑模控制[J]. 航空学报, 2013 , 34(8) : 1906 -1914 . DOI: 10.7527/S1000-6893.2013.0322
In order to deal with vibration suppression in the process of a large flexible spacecraft attitude maneuver, this paper puts forward a method which combines input shaping (IS) with adaptive sliding mode control (ASMC). This strategy suppresses the flexible nominal system residual vibration by input shaping, and the sliding mode control ensures an actual system tracking the nominal system under the influence of parameter uncertainties and external disturbances, solving the problem of the sensitivity of input shaping to parameter uncertainty and external disturbance. Furthermore, when the adaptive law for the switch gain is utilized for the sliding mode, the prior knowledge of the upper bounds on the external disturbance and parameter uncertainty is not required for switching gain tuning. Finally, simulation results show that the proposed control method can ensure the desired attitude maneuver and residual vibration suppression under parameter uncertainty and external disturbance.
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