基于CEI测量的GEO目标快速轨道恢复

连线干涉测量(Connected Element Interferometry, CEI)是一种全天时全天候的被动测角技术, 已用于空间目标的跟踪监视. 地球静止轨道(Geostationary Earth Orbit, GEO)卫星需要频繁机动以保持轨位或完成其他任务, 其机动后的快速轨道恢复能力对于监视预警极为重要. 针对基于CEI的GEO短弧定轨和预报, 分析了定轨算法的形亏和数亏, 在附加先验轨道约束的短弧定轨基础上, 提出了轨道半长轴初值的自适应优化方法. 利用亚太七号卫星的CEI仿真和实测数据进行了短弧定轨和预报, 实验结果表明, 采用优化后的半长轴初值, 30min短弧定轨和10min预报的卫星位置分量精度均优于4km, 能够满足非合作GEO目标机动后快速轨道恢复的需求.

Rapid Orbit Recovery of the GEO Targets Based on CEI Measurement

Connected Element Interferometry (CEI) has been used for space surveillance as an all-day, all-weather passive tracking technique. Geostationary Earth Orbit (GEO) satellite requires frequent maneuver planning to maintain its subsatellite position or accomplish other tasks, which makes rapid orbit recovery extremely important for surveillance and early warning whenever a maneuver ends. This paper is to investigate CEI-based GEO short-arc orbit determination. Firstly, rank-deficiency in the conventional orbit determination algorithm is demonstrated and a priori orbit constraint is given to strengthen the positive definiteness of normal matrix. Then an adaptive optimization method to solve for the initial value of semi-major axis is proposed. Finally, two short-arc orbit determination and prediction experiments are carried out using both the simulated and measured CEI data of Asia-Pacific STAR 7 (APSTAR 7) satellite. The results show that an accuracy of 4 km is achievable for 30-min short-arc orbit determination and 10-min orbit prediction by using the proposed algorithm, which can meet the demands of rapid orbit recovery for non-cooperative GEO targets after maneuvers.