自主机动条件下的实时定轨方法  

Real-time Orbit Determination Method for Autonomous Maneuvering Satellites

作　　者：张俊丽 何伟平 刘军 

机构地区：[1]北京空间信息中继传输技术研究中心,北京100094

出　　处：《飞行器测控学报》2016年第3期236-241,共6页Journal of Spacecraft TT&C Technology

摘　　要：中继卫星在跟踪自主机动用户目标时,由于机动轨道未知,需要利用中继卫星下传的星载GNSS(Global Navigations Satellite System,全球导航卫星系统)数据进行实时轨道确定与预报,为中继卫星跟踪提供实时的引导信息,以方便中继卫星快速捕获目标和连续稳定跟踪。针对该类用户目标的任务需求,讨论了基于星载GNSS数据自主机动条件下的实时定轨方法,建立了连续推力机动力学模型。以某一型号卫星的实测数据进行分析验证,并对轨道机动进行辨识,计算的机动加速度和机动时间与试验单位提供的结果一致。针对卫星不同机动情况,5min的观测数据定轨预报10min的弧段,最大位置误差小于8km,可以为中继卫星快速捕获提供高精度的引导信息。As the maneuver orbit is unknown when the Tracking and Data Relay Satellite （TDRS） tracks an autono mous maneuvering user satellite, real-time orbit determination and prediction is needed with onboard Global Naviga tions Satellite System （GNSS） data downloaded by TDRS to provide real time tracking guidance information for TDRS rapid capturing and continuous and stable tracking. To meet requirements of similar autonomous maneuvering user satellite, a method of real time orbit determination with GNSS data of autonomous maneuvering satellite is discussed and a continuous thrust model is built up. With measured data of a certain satellite, the method is verified and orbit maneuver is identified. The calculated thrust acceleration and the maneuver time is consistent with results provided by test department. Based on different maneuvering cases, the predicted 10 minutes arc＇s max position error is less than 8 kilometers with 5 minutes measured orbit determination are, and these can provide high precision subsequent tracking arc for TDRSS capturing and tracking.

关 键 词：连续推力 轨道机动 实时定轨 辨识 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]