基于星敏感器的天文/惯导组合导航仿真研究  

Research on CNS/SINS Integrated Navigation by Simulation

作　　者：罗宁[1] 周磊[2] 张锐[2] 樊建文[2] 

机构地区：[1]成都飞机设计研究所,成都610091 [2]中国电子科技集团公司第二十研究所,西安710068

出　　处：《现代导航》2014年第5期342-346,共5页Modern Navigation

摘　　要：本文通过仿真实验,研究了基于星敏感器的天文/惯导组合导航系统的导航性能和特点。首先分析了天文导航的基本原理,并给出了天文/惯导组合导航算法的理论模型。在此基础上,建立了天文导航和捷联惯性导航的仿真模型,实现了天文/惯导组合导航系统仿真。仿真结果表明:基于星敏感器的天文/惯导组合导航能够有效抑制惯导的长时漂移累积误差,有利于实现机载远程长航时的高精度导航。According to the simulation experiments, the performance and characteristic of CNS/INS integrated navigation are analyzed in this paper. Firstly, the basic theory of celestial navigation is discussed, and the algorithm of CNS/1NS integrated navigation is presented. Then, the celestial navigation and inertial navigation simulation models are set up. What＇s more, the CNS/INS integrated navigation simulation system is realized. The simulation results show that the accumulative errors of inertial navigation are checked effectively by the CNS/INS integrated navigation, which is benefit to realize the high precision airborne navigation with long-distance and long-endurance.

关 键 词：天文/惯导组合导航 星敏感器 捷联惯导 系统仿真 

分 类 号：V249[航空宇航科学与技术—飞行器设计]