时间移位调节器用于双圆限制四体问题中航天器轨道与姿态相对运动的约束控制
Time Shift Governor for Constrained Control of Spacecraft Orbit and Attitude Relative Motion in Bicircular Restricted Four-Body Problem
AI总结：
本文提出时间移位调节器，在双圆限制四体问题中约束航天器交会对接，通过逐渐减小时间移位实现轨道与姿态约束控制，并用数值仿真验证。
摘要：
本文在双圆限制四体问题（BCR4BP）背景下，考虑航天器交会对接（RVD）中的约束问题，并计入姿态动力学。我们考虑了在日-地-月系统中的近直线晕轨道（NRHO）上进行RVD任务时的视线（LoS）锥约束、推力限制、推力方向限制以及接近速度约束。为施加这些约束，采用了时间移位调节器（TSG），该调节器使用时间移位的首席航天器轨迹作为副手航天器的目标参考。时间移位逐渐减小至零，使得虚拟目标随时间推移逐渐向首席航天器演化，从而实现RVD任务目标。数值仿真结果验证了所提出的控制方法。
英文摘要：
This paper considers constrained spacecraft rendezvous and docking (RVD) in the setting of the Bicircular Restricted Four-Body Problem (BCR4BP), while accounting for attitude dynamics. We consider Line of Sight (LoS) cone constraints, thrust limits, thrust direction limits, and approach velocity constraints during RVD missions in a near rectilinear halo orbit (NRHO) in the Sun-Earth-Moon system. To enforce the constraints, the Time Shift Governor (TSG), which uses a time-shifted Chief spacecraft trajectory as a target reference for the Deputy spacecraft, is employed. The time shift is gradually reduced to zero so that the virtual target gradually evolves towards the Chief spacecraft as time goes by, and the RVD mission objective can be achieved. Numerical simulation results are reported to validate the proposed control method.
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