半球谐振陀螺平台航向效应误差研究  

Heading Effect Error of Hemisphere Resonator Gyro Platform

作　　者：李彬 刘洁瑜 陈伟 

机构地区：[1]火箭军工程大学,西安710025

出　　处：《电光与控制》2016年第12期65-70,共6页Electronics Optics & Control

基　　金：总装探索研究基金(2010TC4303);博士后基金(20090461470)

摘　　要：针对半球谐振陀螺平台惯导系统初始对准过程中存在的航向效应的问题,研究探讨了航向效应误差对半球谐振陀螺平台惯导系统初始对准精度的影响。为了消除航向效应误差的影响,结合导弹实际应用要求,设计了航向效应的自标定方案。实验结果表明,半球谐振陀螺平台惯导系统航向效应标定方法能够有效补偿航向效应误差,提高半球谐振陀螺平台惯导系统的初始对准精度。Aiming at the Navigation System （INS） issue of heading effect during the initial alignm of Hemisphere Resonator Gyro （HRG） platform Inertial ent, we studied the influence of heading effect error on the initial alignment accuracy of HRG INS. In order to eliminate the influence of heading error effect, we designed a self-calibration scheme of the heading effect based on the practical application requirements of the missile. The experimental results shows that this HRG INS heading effect calibration method can effectively compensate for the heading effect error and improve the accuracy of self-aligned HRG platform INS.

关 键 词：半球谐振陀螺 航向效应 自对准 自适应分形插值 

分 类 号：V241.5[航空宇航科学与技术—飞行器设计]