微卫星姿态的滑模控制

2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Pub Date : 2010-06-08 DOI:10.1109/ISSCAA.2010.5633071

H. Nemati, M. Bahrami, B. Ebrahimi

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引用次数: 2

摘要

采用滑动控制方法对某微型卫星的姿态控制进行了分析。该方法使卫星姿态动力学具有抗不确定性和未知干扰的鲁棒性。本文采用非线性耦合模型，并引入饱和函数防止抖振。将重力梯度作为扰动施加。滑动方法应用于由欧洲航天局(ESA)发起的SSETI/ESEO微型卫星。通过仿真验证了该控制器的有效性。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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Sliding mode control of a microsatellite attitude

Attitude control of a micro-satellite is analyzed with sliding control method. With this method, attitude dynamics of satellite is robust against uncertainties and unknown disturbances. Nonlinear and coupled model in this paper is utilized and to prevent chattering, saturation functions are invoked. The gravity gradient as a disturbance is applied. The sliding approach is applied to the SSETI/ESEO micro-satellite, initiated by the European Space Agency (ESA). The effectiveness of the controller is demonstrated through simulations.

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来源期刊

2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics

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