利用UKF的航天器自主导航方法研究  

Study of the Spacecraft Autonomous Navigation Method Using UKF

作　　者：刘伟[1] 杨博[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《航天控制》2005年第3期55-59,共5页Aerospace Control

摘　　要：UKF(Unscented卡尔曼滤波)是一种新型的直接针对非线性系统的滤波方法。用星敏感器和地平仪测量星光与地平之间的“星光仰角”为观测量的天文自主导航方法,其状态方程和量测方程都是非线性的,使用以往的EKF(推广卡尔曼滤波)进行导航滤波,需将上述两方程分别线性化,故精度较低。本文提出在航天器天文自主导航系统中采用UKF方法,并从仿真计算结果中看到,导航精度有显著提高。UKF (Unscented Kalman filtering) is a new filtering method aimed at nonlinear system directly. The elevation angle of star is observed by star sensor and horizontal instrument. Because of the nonlinearity, the state equation and the measure equation must be linearized when the traditional EKF (Extended Kalman filtering) is applied to this celestial autonomous navigation method. Then the precision is poor. UKF is applied to the spacecraft autonomous navigation in this paper. And the computer simulation results demonstrate that the navigation precision is greatly improved.

关 键 词：卡尔曼滤波 星光 仰角 自主导航 滤波 

分 类 号：V448.224[航空宇航科学与技术—飞行器设计]