GRACE星载GPS非差观测值简化动力学定轨

Reduced-Dynamic Orbit Determination Based on the GRACE GPS Onboard Zero-Difference Observation Data

利用GRACE卫星的实测数据研究了重力卫星精密定轨问题;针对简化动力学精密定轨方法给出了一种有效的星载数据编辑、处理策略。编制了相应的软件,并利用该软件处理了GRACE-B卫星3 d的实测数据;通过与JPL公布的轨道导航解比较,以及激光观测值检验的方式分析了卫星轨道的精度。结果显示,利用简化动力学定轨方法解算的轨道精度在6 cm以内,能够满足重力场反演对轨道精度的要求。

The precise orbit determination （POD） method of the LEO was discussed based on the GRACE ob- servation data. And an effective flow of reduced-dynamic POD was established to clean and process GPS onboard data. The three day GRACE-B data was processed, and the accuracy of the precise orbit was assessed by comparing them with JPL and SLR data. The comparison results confirmed that the RMS of our computed reduced-dynamic orbits was 6 cm, which satisfied the demands of determining the global gravitational model.