惯导双位置对准精度分析  

Precision Analysis on Two-position Alignment Method of INS

作　　者：徐海刚[1] 

机构地区：[1]北京航空航天大学仪器科学与光电工程学院。北京100191

出　　处：《弹箭与制导学报》2009年第4期1-3,共3页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：“985工程”(222105)资助

摘　　要：针对惯导的双位置对准问题,提出了双位置对准精度极限的概念,指出最根本的影响因素是陀螺一次启动漂移特性和双位置转换时间;定性阐述了这两种因素如何影响对准精度,并以一阶马尔可夫过程为陀螺随机漂移模型,推导了对准误差与这两种因素间的定量关系;计算机仿真结果表明,陀螺漂移波动越小,相关时间越长,位置转换时间越短,越有利于实现高精度初始对准。Focused on INS two-position alignment, the concept of alignment accuracy limit was put forward. The qualitatively stated prime error sources were found to be instability of gyro drift and transformation time between two positions; Based on the gyro drift model of one-order Markov process, relationship between the accuracy limit and error sources was presented. The simulation results show that better alignment accuracy results from gyro drift of small variation, long relative time, and short transformation time.

关 键 词：双位置对准 零偏稳定性 零偏重复性 位置转换时间 一阶马尔可夫过程 

分 类 号：V249.322[航空宇航科学与技术—飞行器设计]