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首页> 外文期刊>Mechatronics, IEEE/ASME Transactions on >Robust Magnetic Attitude Control of Satellites
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Robust Magnetic Attitude Control of Satellites

机译：卫星的稳健磁姿控制

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Magnetic torquers are frequently adopted as primary actuators for the attitude control of small satellites in low Earth orbit. Such actuators generate a magnetic dipole which, in turn, leads to control torques thanks to the interaction with the magnetic field of the Earth. The design of attitude control laws based on magnetic torquers is a challenging problem as the torques generated by the coils are instantaneously constrained to lie in the plane orthogonal to the local direction of the geomagnetic field vector, which varies according to the current orbital position of the spacecraft. This implies that the attitude regulation problem is formulated over a time-varying model. In this paper, the design of control laws for magnetically actuated spacecraft is considered and an approach guaranteeing robustness to parametric uncertainty and optimal performance in terms of disturbance attenuation is presented. The proposed method is based on linear time-periodic models and $H_infty$ control theory. The results obtained by applying the proposed approach in a simulation study are also presented and discussed.
机译：电磁转矩调节器通常被用作主要执行器，以控制低地球轨道上的小型卫星的姿态。这样的致动器产生磁偶极子，由于与地球磁场的相互作用，该偶极子又导致控制转矩。基于电磁转矩器的姿态控制定律的设计是一个具有挑战性的问题，因为线圈产生的转矩被瞬时约束在与地磁场矢量的局部方向正交的平面中，该平面根据地磁场的当前轨道位置而变化。飞船。这意味着姿态调节问题是在时变模型上提出的。本文考虑了磁致航天器的控制律设计，并提出了一种确保对参数不确定性的鲁棒性和在干扰衰减方面的最佳性能的方法。所提出的方法基于线性时间周期模型和 $ H_infty $ 控制理论。通过提出的方法在模拟研究中获得的结果也被介绍和讨论。

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