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研究了近地小行星433 Eros本体悬停轨道的稳定控制问题.用三轴椭球体模型近似Eros引力场分布,建立了航天器在其引力场内的动力学模型,并且应用等加速度变截距时变滑模控制设计了悬停控制器.该方法的滑模面选取与常规滑模控制不同,且不存在到达阶段.仿真分析从不同的初始条件和悬停条件入手,验证控制器的有效性,并讨论了航天器的速度与控制加速度的幅值随滑模面切换时间的变化情况.
The stability control problem of the hovering orbit of the near-Earth asteroid 433 Eros is studied.The dynamics model of the spacecraft in its gravitational field is established by approximating the Eros gravitational field distribution with a triaxial ellipsoid model, and the isokinetic intercept Time-varying sliding mode control design of the hover controller.This method of sliding surface selection and conventional sliding mode control is different, and there is no arrival stage.From the initial analysis of different initial conditions and hover conditions to verify the effective controller This paper also discusses the changes of spacecraft velocity and control acceleration with slip surface switching time.