摘要
简要介绍了天文/惯性组合导航系统的基本原理,采用速度阻尼技术阻尼惯性导航系统的舒拉周期误差,为天文导航系统提供高精度的姿态信息,从而利用天文导航信息估计补偿惯性导航系统的陀螺漂移,同时,速度阻尼克服了天文导航不能估计补偿加速度计误差的缺点,使天文/惯性组合导航的各种误差得到补偿修正,解决了天文/惯性组合导航长航时导航条件下导航精度不高的问题;对研制的天文/惯性组合导航系统远洋航行的数据进行半物理仿真,仿真分析结果表明:基于速度阻尼的天文/惯性组合导航技术可以实现天文/惯性组合导航系统的长航时高精度组合导航。
The basic principles of the CNS/INS integrated navigation system are introduced briefly in this paper. The speed damping technology （SDT） which constrains Shula period error of the INS is used for providing attitude infor-mation for the CNS, thus the CNS information can be used for compensating the Gyro＇s drift. Meanwhile, the SDT overcomes the difficul- ties of compensating the acceleration＇s drift by the CNS, which compensates all errors of the CNS/INS integrated navigation system. The semi-physical simulation of the CNS/INS integrated navigation system in long-term range is described, the sim- ulation results indicate that the SDT is applied to the CNS/INS integrated system for long-term range and high-precision reauirements.
出处
《光学与光电技术》
2012年第4期62-67,共6页
Optics & Optoelectronic Technology
