基于Simulink高精度组合导航系统研究与仿真  

Research and Simulation on Precise Integrated Navigation System Based on Simulink

作　　者：齐鑫[1] 彭勤素[1] 李丽娜[1] 陈华兵[1] 

机构地区：[1]中国航天科技集团公司第四研究院四十一所,西安710025

出　　处：《系统仿真学报》2009年第12期3773-3777,共5页Journal of System Simulation

摘　　要：建立了基于MATLAB/Simulink的组合导航系统仿真模型,并将系统分解成一系列功能相对独立的模块,如轨迹发生模块,捷联惯导解算模块,卡尔曼滤波器模块等。研究并设计了SINS/GPS(RDSS)/CNS/SAR组合导航算法,利用无重置联邦型卡尔曼滤波技术,将各子滤波器输出的系统状态局部最优估计值送入主滤波器,采用全局最优融合算法计算得到系统状态的全局最优估计值;通过每15分钟对导航系统进行重置,有效抑制了无重置联邦滤波器在长时间运行时的发散问题,并进行了仿真验证,仿真结果表明,该组合导航系统具有很高的导航精度,定位精度为5米,姿态精度为0.5角分,仿真模型建立正确,方法采用得当、有效。Integrator Navigation System simulation modes based on MATLAB/Simulink were designed, and the system was divided into a series of independent functional units, such as track generate unit, strap-down inertial navigation unit, Kalman filter unit and so on. The algorithm of SINS/GPS （RDSS）/CNS/SAR integrated navigation was researched and designed, and then by using the federated Kalman filtering, the local optimal estimations of system states from the local filters were passed into the master filter, and the master filter could give the global optimal estimates of states through the global optimal fusion algorithm. Resetting the Navigation System every 15 minute could restrain the distortion problem when Non-reset Federal Filter running longtime. Simulation results show that the integrated navigation system has high navigation accuracy, the positioning accuracy up to 5 meters, and the attitude accuracy up to 0.5 angle minute, the model is sound and the method is valid.

关 键 词：捷联惯导系统 全球定位系统 北斗导航系统 天文导航系统 合成孔径雷达 联邦滤波 组合导航 

分 类 号：V249.328[航空宇航科学与技术—飞行器设计]