航天器多脉冲悬停控制的非线性方法

为解决连续推力空间悬停控制技术对航天器控制推进系统要求较高、工程上难于实现的问题，提出基于Clohessy-Wiltshire方程的多脉冲悬停控制方法。以轨道要素外推的飞行状态非线性预测方法和脉冲悬停控制量优化算法，对悬停脉冲进行了优化，可以实现主动航天器在目标航天器附近任意点的近似稳定悬停。给出的多脉冲悬停控制方法及控制量非线性优化算法考虑了地球非球形引力摄动J2项影响，补偿了Clohessy-Wiltshire方程的线性化误差，能有效提高悬停精度。仿真结果表明，多脉冲悬停控制方法的燃料消耗与连续推力悬停方法相比没有明显增加，不会对主动航天器带来过大的燃料消耗压力。

Nonlinear Method for Multiple Impulse Hovering Control of Spacecraft

Continuous thrust hovering could be difficult to implement, which needs strict control and propulsion systems of spacecraft. For solving the problem, a method of spacecraft multiple-impulse hovering,based on the Clohessy-Wiltshire equations, is proposed in this paper. The hovering method includes the nonlinear predictive method of spacecraft states and the optimization algorithm of impulse. With this method, the active spacecraft can hover approximately at any selected position near the target spacecraft. For considering the effect of linearization and J2 perturbation, the method improves the hovering accuracy. The numerical simulation shows that the two spacecraft can maintain a stable hovering, and the energy requirements of the active spacecraft are not much more than the one based on the continuous thrust.