近圆参考轨道卫星编队脉冲控制方法

针对高斯摄动方程在描述近圆轨道时其近地点幅角和平近点角存在奇异性的问题,采用非奇异轨道要素描述卫星轨道运动,推导了适用于近圆参考轨道编队的非奇异轨道要素脉冲控制模型。基于该模型,首先设计了一个法向脉冲同时调整轨道倾角和升交点赤经偏差;然后,先假定采取在两个位置分别同时施加切向和径向脉冲的策略调整其余轨道要素偏差,分析了如在第一个位置施加切向脉冲时将会导致的复杂非线性问题,从而提出了一种在轨道上的某两个位置分别仅施加径向和切向脉冲的双脉冲控制修正算法,并且分析了该算法的燃料消耗情况。最后通过数值仿真验证了算法的简单性和有效性。

Impulsive Control for Near Round Reference Orbit Satellites Formation

For a satellite flying on a round orbit,there exists a singularity problem when the Gauss perturbation is used to describe the satellite's argument of perigee and mean anomaly. Aiming at this situation,satellite motion was described by nonsingular orbit elements and the corresponding impulsive control model for a near round reference satellite formation is derived. Based on this model,first,the inclination and right ascension error is corrected by exerting an impulsive control effort along the normal direction. After that,suppose other elements error is corrected by exerting impulsive control efforts at two positions and at each position,impulsive control efforts are exerted along tangent and radial directions simultaneously,and then the conclusion can be drawn that a complex nonlinear problem is induced by exerting tangent impulsive control at the first position. Taking this situation into account,a two impulsive control algorithm that only exerts control effort along radial direction at the first position and only exerts control effort along tangent direction at the second one is put forward. Morever,the fuel consumption of the given algorithm is analyzed. In the end,the simplicity and effectiveness of the given algorithm is verified by mathematical simulation results.