摘要
地磁辅助导航是组合导航技术的新方向,而导航误差的研究是分析惯性/地磁组合导航性能的重要内容之一。以等高或近似等高飞行的巡航飞行器为应用对象,建立了惯性/地磁组合导航系统的卡尔曼滤波器;通过仿真结果并结合理论分析重点讨论了校正方式、惯性器件测量精度、地磁场特征与磁测误差、基准图的网格间距、滤波周期、初始位置与初始速度误差等各种因素对位置和速度等导航误差的影响。
Geomagnetic aided navigation is a new branch of integrated navigation technology, and the research on navigation error is an important part in analyzing the performance of inertial/geomagnetic integrated navigation system. This paper chooses the cruise aircraft flying at a constant or near constant height as its application object, establishes a Kalman filter for the inertial/geomagnetic integrated navigation system, and discusses the influences of each factor on the position and velocity errors by theoretical analysis and simulation results. These factors include revised method, accuracy of inertial sensors, geomagnetic feature, measurement error of magnetometer, grid interval of geomagnetic map, filtering period, and initial navigation errors.
出处
《中国惯性技术学报》
EI
CSCD
北大核心
2010年第1期70-75,共6页
Journal of Chinese Inertial Technology
基金
国家自然基金(40704008)
教育部博士点专项基金(20070699001)
关键词
惯性/地磁组合导航
导航误差
巡航飞行器
卡尔曼滤波
inertial/geomagnetic integrated navigation
navigation error
cruise aircraft
Kalman filter
