星载加速度计数据在卫星定轨中的应用  

Application of Accelerometer Data to Orbit Determination

作　　者：韩健[1] 杨龙[1] 董绪荣[1] 

机构地区：[1]装备指挥技术学院,北京101416

出　　处：《上海航天》2006年第4期20-22,26,共4页Aerospace Shanghai

摘　　要：基于传统的动力学法,以加速度计数据替代非保守力加速度,提出了一种用加速度计数据进行卫星精密定轨的模型。用美喷气推进实验室(JPL)提供的GRACE星星载加速度计实测数据进行了验证。结果表明,用加速度计可获得较准确的卫星瞬时加速度,其积分轨道的误差小于纯力学模型,从而提高卫星定轨精度。但由于动力学定轨法的固有特点,其定轨误差会随时间而增大。A model used for satellite orbit precision determination by accelerometer data was put forward based on classic dynamics method in this paper, in which acceleration of non-gravitational force was instead by accelerometer data. The method in this paper was approved by the on-board accelerometer data measured of Gravity Recovery and Climate Experiment satellite provided by USA Jet Propulsion Laboratory. The analysis results showed that more accuracy instantaneous acceleration of satellite would be acquired by accelerometer, which error of integral orbit was smaller than that of pure mechanics model. The method could improve the orbit determination accuracy. But the error would be larger with in the time because of the inherent characteristics of orbit determination by dynamics method.

关 键 词：卫星 动力学定轨 加速度计 非保守力 GRACE星 定轨精度 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]