空间激光干涉引力波探测器轨道修正方法

针对空间激光干涉引力波探测器轨道修正问题，提出一种基于虚拟编队构型设计的航天器轨道修正方法。空间激光干涉引力波探测器由3颗航天器组成等边三角形构型。由于入轨误差和摄动的影响，探测器的构型不稳定。假设名义轨道上运行着一颗理想航天器，实际轨道上的真实航天器与之组成虚拟编队，探测器的3颗真实航天器分别与对应的理想航天器组成3个虚拟编队。考虑探测器构型稳定性要求和摄动的影响，对虚拟编队的构型进行设计，进而求解航天器平均轨道要素修正量。求解得到的航天器平均轨道要素修正量小于偏差量，轨道修正通过四脉冲控制实现。数值仿真结果表明，该方法通过部分轨道修正满足了探测器的构型稳定性要求，具有减少燃料消耗、延长任务寿命的潜力。 

Orbit correction method of space-based laser interferometric gravitational wave detector

Aimed at the orbit correction problem of space-based laser interferometric gravitational wave detector, a spacecraft orbit correction method based on virtual formation configuration design is proposed. The detector is composed of three spacecraft forming an equilateral triangle configuration. The configuration of the detector is unstable due to the orbit error and perturbation. It is assumed that an ideal spacecraft is running in nominal orbit, and the real spacecraft in actual orbit forms a virtual formation with the ideal spacecraft. The three spacecraft of detector form three virtual formations with their ideal spacecraft. Considering the stability requirement of detector configuration and the effect of perturbation, the configuration of the virtual formation is designed to solve the correction value of mean orbital elements of spacecraft. The orbit correction value is less than the orbit deviation value, and orbit correction is realized by four-pulse control. The numerical simulation results show that the method meets the stability requirements of the detector configuration through partial orbit correction, and has the potential to reduce fuel consumption and prolong mission life.