摘要
研究了利用惯性导航系统与天文导航系统进行组合定姿的方法;构造了惯导/天文组合导航系统的状态方程和量测方程;采用卡尔曼滤波技术设计了惯导/天文组合定姿算法。设计飞行器的典型飞行轨迹,通过数学仿真对该算法的有效性进行了验证。结果表明,天文导航能够有效地补偿惯性导航因陀螺漂移带来的误差,非常适用于飞行器的高精度定姿。
The method of integrated attitude determination based on inertial navigation system and celestial navigation system is researched in this paper, the state equation and measurement equation of integrated navigation systems were established. Thus the algorithm of integrated attitude determination is designed by kalman filtering technology. By designing a typical flight route of aerocraft, its mathematical simulation was made which proved the algorithm＇ s effectivity and showed that the CNS can effectively compensate the INS error caused by gyro drift. It＇s very fit for the precise attitude determination of aerocraft.
出处
《测绘科学技术学报》
北大核心
2009年第2期82-85,共4页
Journal of Geomatics Science and Technology
关键词
飞行器
惯导/天文
组合定姿
卡尔曼滤波
aerocraft
INS/CNS
integrated attitude determination
Kalman filter
