This paper investigates the stability control of body-fixed hovering orbit over the near-Earth asteroid 433 Eros.Its gravitational field is approximated simulated by using the triaxial ellipsoidal model.Dynamical equations of the spacecraft near 433 Eros are derived.The time-varying sliding mode control with the same acceleration and variable intercept is adopted to design the hovering controller.Meanwhile,the sliding surface in this method is different from the conventional sliding mode control,where there is no reaching phase.Numerical simulations are then carried out with different initial conditions and hovering conditions to evaluate the effectiveness of the designed controller.The maximum values of spacecraft velocity and acceleration are analyzed by varying the switching time of sliding surface.%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.
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