空间高精度惯性导航的后牛顿模型  

Post-Newtonian Model of High-precision Inertial Navigation in Space

作　　者：费保俊[1] 贺珍妮[1] 杜健[1] 

机构地区：[1]装甲兵工程学院基础部,北京100072

出　　处：《空间科学学报》2016年第1期70-76,共7页Chinese Journal of Space Science

摘　　要：将广义相对论中的惯性系概念引入惯性导航,根据后牛顿引力理论,提出一种新的航天器惯性导航模型.以地球周围的测地运动物体为随动惯性参考系,利用航天器机载加速度计测量的比力和引力梯度作为观测量,通过求解航天器相对于随动惯性系的状态量达到导航定位目的.该方法用于高轨卫星时可以获得较高的测量精度,误差主要来源于惯性元件的测量以及随动惯性系测地轨迹设计,不存在现有惯性导航模型中随时间而累积的误差.The concept of inertial system in general theory of relativity is introduced to inertial navigation using post-Newtonian theory of gravity, and a new model of inertial navigation of spacecraft is proposed. It utilizes the geodesic motion objects around the Earth as the follow-up inertial frame of reference. The special force and gravity gradient measured by accelerometers in spacecraft are employed as the observable, and navigation can be realized by solving the status of the spacecraft relative to the follow-up inertial frame. The method used for high orbit satellite can obtain high measurement accuracy, and its errors mainly come from the measurement accuracy of inertial components as well as the design of geodesic trajectory. There is no error accumulated over time which has existed in current inertial navigation model.

关 键 词：惯性导航 卫星轨迹 后牛顿引力理论 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]