基于机动力模型的GEO卫星恢复期间定轨

北斗卫星导航系统(BDS)中GEO卫星频繁的轨道机动对高精度、实时不间断的导 航服务需求提出了更高要求, 如何在短弧跟踪条件下提高GEO卫星轨道快速 恢复能力, 是提升导航系统服务精度的关键因素. 针对该问题, 本文提出了基 于机动力模型的动力学定轨方法, 尝试利用高精度的C波段转发式测距数据, 辅 以机动期间的遥测遥控信息建立机动力模型, 联合轨控前后的观测数据进行动 力学长弧定轨. 利用BDS中GEO卫星实测数据进行了定轨试验与分析, 结果表明, 恢复期间需要采用解算机动推力的定轨方法, 联合机动前、机动期间和机 动后4h数据定轨的轨道位置精度在20m量级, 径向精度优于2.5m. 该方 法克服了短弧跟踪条件下动力学法定轨和单点定位中的诸多问题, 提供了解决 GEO卫星机动后轨道快速恢复问题的技术方法. 

Orbit Determination Method Based on Thrust Force Model for GEO Satellite in the Period of Orbit Recovery

Real time, continuous and high precision navigation service is needed due to the frequent geostationary satellite (GEO) orbit maneuver. How to recover orbit rapidly for geostationary satellite based on short-arc tracking is the key factor. A new orbit determination method uniting the data before, during and after satellite maneuver is studied, and C-band transfer ranging data as well as the telemetry and telecontrol parameters during satellite maneuver are all used. The results based on observation data for geostationary satellite in Beidou System (BDS) indicate that the integrated solution strategy of orbit parameters and thrust force parameters needs to be adopted in the period of orbit recovery. The accuracy of 3-dimensional positions is about 20m, and the orbital precision in radial component is better than 2.5m using the data 4 hours after orbit maneuver. The method provides a solution to resolve several problems of dynamic orbit determination and point positioning in short-arc tracking.