摘要
传统的惯性/天文位置组合导航系统中,由于天文定位观测输出耦合了水平观测平台基准误差,往往存在系统噪声与量测噪声不完全独立的问题。针对此问题,分析了利用天文观测量修正惯性系下陀螺漂移的原理,提出了一种直接敏感地平进行天文解析定位及组合滤波的空天飞行器自主导航定位方案,并建立了相应的组合滤波模型。所提出的方法采用星敏感器和陀螺仪构造惯性基准,并在此基础上进行基于红外地平仪的天文定位解算,最后进行惯性/天文组合定位。该方案充分利用了星光敏感器在惯性系下姿态测量精度高的优点,并使惯性/天文组合定位滤波中状态噪声和观测噪声完全独立,仿真结果验证了该定位方法的有效性。
In the traditional INS/CNS integrated algorithm, the system noise is correlated with the measured noise because the celestial observation output couples the horizontal platform benchmark error. To fix this problem, the principle of using celestial observation to modify gyroscope excursion was analyzed, and an aerospace vehicle positioning and navigation theme based on directly sensing horizon to achieve celestial analytical positioning and integrated filtering was proposed, then the relevant integrated filter model was built. In the theme, an inertia benchmark was built by star sensor and gyro, then celestial positioning based on infrared horizon sensor was calculated, and at last the INS/CNS integrated filtering was implemented. This theme fully takes the advantage of the accurate celestial information and succeeds in making the system noise and the measured noise independent. The simulation results show the validity of the proposed theme.
出处
《中国空间科学技术》
EI
CSCD
北大核心
2013年第3期64-71,共8页
Chinese Space Science and Technology
基金
国家自然科学基金(91016019)
航空科学基金(2011ZC52044)
江苏省高校青蓝工程
江苏高校优势学科建设工程
中央高校基本科研业务费专项
南京航空航天大学博士学位论文创新与创优基金(BCXJ10-05)资助项目
关键词
卡尔曼滤波
红外地平仪
星敏感器
组合导航
惯性导航系统
空天飞行器
Kalman filtering Infrared horizon sensor Star sensor Integrated navigationInertial navigation system Aerospace vehicle
