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首页> 外文期刊>International Journal of Uncertainty, Fuzziness, and Knowledge-based Systems >FUZZY CONTROL OF RIGID SPACECRAFT ATTITUDE MANEUVER WITH DECAY RATE AND INPUT CONSTRAINTS
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FUZZY CONTROL OF RIGID SPACECRAFT ATTITUDE MANEUVER WITH DECAY RATE AND INPUT CONSTRAINTS

机译：具有衰减率和输入约束的刚性航天器姿态机动的模糊控制

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摘要

The spacecraft attitude control systems are becoming more and more sophisticated with the increasing complex system configurations. This paper investigates the problem of three-axis rigid spacecraft maneuver control. The rigid spacecraft model consisting of the dynamic and kinematics equation is firstly provided. This nonlinear model is converted into a Takagi-Sugeno fuzzy model. Then, based on the parallel distributed compensation scheme, a fuzzy state feedback controller is designed for the obtained T-S fuzzy model with considering the decay rate and input constraints. Next, sufficient conditions for the existence of such a controller are derived in terms of linear matrix inequalities and the controller design is cast into a convex optimization problem subject to linear matrix inequalities constraints, which can be readily solved via Matlab LMI toolbox. At last, a design example shows that the time of spacecraft attitude maneuver is shortened and the input constraint is realized. The simulation results show the effectiveness of the proposed methods.
机译：随着复杂系统配置的增加，航天器姿态控制系统也变得越来越复杂。本文研究了三轴刚性航天器的机动控制问题。首先提出了由动力学方程和运动学方程组成的刚性航天器模型。该非线性模型被转换为高木-杉野模糊模型。然后，基于并行分布补偿方案，在考虑衰减率和输入约束的情况下，针对获得的T-S模糊模型设计了模糊状态反馈控制器。接下来，根据线性矩阵不等式推导出存在这种控制器的充分条件，并将控制器设计转化为受线性矩阵不等式约束的凸优化问题，可以通过Matlab LMI工具箱轻松解决该问题。最后，通过一个设计实例表明，该方法可以缩短航天器姿态操纵的时间，并实现输入约束。仿真结果表明了所提方法的有效性。

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