机动天基平台惯性/天文组合导航的研究

为了实现机动天基平台的长时间、高精度和低成本自主导航,采用了低精度惯性导航系统和天文导航系统进行组合。以扩展卡尔曼滤波算法为基础,通过建立系统状态方程和量测方程,并进行量测方程的线性化,将捷联惯导和星敏感器分别测得的姿态信息进行数据融合,估计出组合导航系统的误差状态量,从而修正捷联惯导系统的导航参数。仿真结果表明,在1000s内,平台姿态角误差稳定收敛在20?,定位误差优于纯惯导解算,证实了该方案的实用性。

The Research on the Inertial/Celestial Integrated Navigation System of the Mobile Space-based Platform

In order to achieve the long time, high accuracy and low cost autonomous navigation of a space-based mobile platform, the inertial navigation system and the celestial navigation system of low accuracy are adopted as a combination. After the establishment of the system state equation and the measurement equation and the linearization of the measurement equation, the corresponding measured attitude information from the SINS and the star sensor are fused on the basis of the extended Kalman filter algorithm, th...