捷联惯导/天文组合导航  

SINS/CNS Integrated Navigation System

作　　者：王明昊[1] 王仕成[1] 牟建华[1] 

机构地区：[1]第二炮兵工程学院,西安710025

出　　处：《弹箭与制导学报》2009年第2期87-90,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了有效提高惯性导航精度,文中介绍了一种基于星敏感器的捷联惯导组合导航方法,首先分析了捷联惯导/星敏感器组合导航系统的工作原理。其次,对组合导航系统进行建模,分析系统误差,通过捷联惯导和星敏感器的输出构造量测值,建立系统的误差状态方程和量测方程。最后,利用间接卡尔曼滤波,估计出组合导航系统的误差状态量,进而修正捷联惯导系统的位置、速度和姿态角。最终,通过对仿真结果的分析证实了该方法的有效性。To improve the precision of the inertial navigation effectively, this paper introduces the method of integrated navigation based on strapdown inertial navigation and star sensor. Firstly, analyses the working principle of SINS/CNS integrated navigation system. Secondly, analyses the errors of the system, the outputs of the strapdown inertial navigation and star sensor are used to construct the observation, builds the error state equation and the measurement equation of the system. Thirdly, estimates the state errors of the integrated navigation system by using Kalman filtering technology, to correct the position, velocity and the angle of the position of the strapdown inertial navigation. At last, the simulation results show that the way is effective.

关 键 词：捷联惯导系统 星敏感器 组合导航 卡尔曼滤波 

分 类 号：V249.328[航空宇航科学与技术—飞行器设计]