星载加速度数据在动力学定轨中的应用

APPLICATION OF ACCELERATION DATA TO PRECISE DYNAMIC ORBIT DETERMINATION OF EARTH ORBIT SATELLITE

在对空间飞行环境十分复杂的低轨卫星进行动力学定轨时,常规的摄动力模型化方法难以胜任厘米级精度的定轨任务。利用星载加速度计数据代替卫星所受非保守摄动力进行动力学定轨的方法,研究对重力卫星CHAMP和GRACE的定轨试验。结果表明,该方法能获得厘米级的定轨精度,比常规的对所有摄动力进行模型化的方法精度高,与经验力模型误差补偿方法精度相当。

The variation of perturbation forces and the complexity of special flying environments of low earth orbit satellites make traditional dynamics orbit determination method can not be competent for cm-level accuracy. It studies the application of acceleration data as a substitutive method for non-conservative perturbation force to dynamic orbit determination. Experimental results for gravity satellite CHAMP and GRACE show that cm-level orbit accuracy can be reached by using acceleration observation. The accuracy is the same as compared with the experienced force compensation model method and better than the traditional method which deals with all force by modeling.