基于参数估计的捷联惯组整弹标定方法研究  

Research on Calibration of SINS by Kalman Filter

作　　者：赵星宇 戚红向[1] 王世会[1] 张英[1,2] 周悦 

机构地区：[1]北京航天自动控制研究所,北京100854 [2]北京大学软件与微电子学院,北京100871 [3]中国科学院高能物理研究所,北京100049

出　　处：《航天控制》2017年第6期14-18,共5页Aerospace Control

摘　　要：针对传统方法对弹上惯组标定时间长、工作量大、成本高的问题,提出了一种基于参数估计的弹载捷联惯导系统整弹标定方法,对系统的误差参数通过大维数卡尔曼滤波器进行估算。建立了陀螺仪和加速度计的误差模型,加入了惯性导航解算,并进行了状态变量可观性分析。设定了发射车的路径轨迹,让每个误差参数均可被激励,并进行了较为详细的仿真研究,验证了该方法的有效性。Regarding the problems of heavy work and high cost in SINS Calibration, an improved method based on Kalman filter is proposed. Meanwhile, the error model of the inertial system has been established. The measurement equations of different kinds of match type is derived. The observability analysis of different maneuvers is performed to evaluate the estimable level of each system state. Accordingly, a proper path is designed according to the result of observability analysis so that all kinds of the SINS error are actuated. And a detailed simulation is implemented to verify the effectiveness of the method.

关 键 词：捷联惯组 可观性分析 误差参数 卡尔曼滤波 

分 类 号：TP316.2[自动化与计算机技术—计算机软件与理论]