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首页> 外文期刊>International Journal of Intelligent Systems and Applications >Orbit and Attitude Control of Asymmetric Satellites in Polar Near-Circular Orbit
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Orbit and Attitude Control of Asymmetric Satellites in Polar Near-Circular Orbit

机译：极近圆轨道中非对称卫星的轨道和姿态控制

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In this paper, the general problem about the orbit and attitude dynamic model is discussed. A feedback linearization control method is introduced for this model. Due to the asymmetric structure, the orbital properties of such satellites are the same as traditional symmetric ones, but the attitude properties are greatly different from the symmetric counterparts. With perturbations accumulate with time, the attitude angles increase periodically with time, but the orbital elements change much slower than the attitude angles. In the attitude dynamic model, chaos could appear. Traditional linear controllers can not compensate enough for asymmetric satellite when the mission is complex, especially in maneuver missions. Thus nonlinear control method is required to solve such problem in large scale. A feedback linearization method, one robust nonlinear control method, is introduced and applied to the asymmetric satellite in this paper. Some simulations are also given and the results show that feedback linearization controller not only stabilizes the system, but also exempt the chaos in the system.
机译：本文讨论了关于轨道和姿态动力学模型的一般问题。针对该模型引入了反馈线性化控制方法。由于结构不对称，这类卫星的轨道特性与传统的对称卫星相同，但姿态特性与对称的卫星却大不相同。随着扰动随时间累积，姿态角随时间周期性增加，但轨道元素的变化远比姿态角慢。在态度动态模型中，可能会出现混乱。当任务复杂时，尤其是在机动任务中，传统的线性控制器无法为非对称卫星提供足够的补偿。因此，需要非线性控制方法来大规模解决该问题。介绍了一种反馈线性化方法，一种鲁棒的非线性控制方法，并将其应用于非对称卫星。给出了一些仿真结果，结果表明反馈线性化控制器不仅可以使系统稳定，而且可以避免系统的混乱。

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