Halo轨道维持的线性周期控制策略

Stationkeeping Strategy of Halo Orbit in Linear Periodic Control

共线型平动点附近的Halo轨道具有指数不稳定性,轨道维持是必不可少的。推导了基于Halo轨道的误差动力学方程,并证明其一阶近似即为线性周期系统。以一次维持的作用时间为离散步长,并通过定常变换,将所得误差动力学化为线性离散定常系统;则仅需通过极点配置,即可实现Halo轨道镇定。研究结果表明,利用Halo轨道周期性设计的线性周期控制策略,可以满足轨道维持任务的需要。

Halo orbit about collinear libration point has the exponential instability, so the stationkeeping maneuver is necessary. Based on the periodicity of Halo orbit, it is illustrated that the error equation from Halo orbit has the linear periodic form in the first order. Discretization on every maneuver and time-invariant reformulation can transform the error dynamics into a discrete-time linear steady system, and then the desired poles can be allocated to drive the spacecraft to the Halo orbit. Numerical results using the linear periodic control strategy demonstrate the potential of this method.