摘要
文中分析了某型平台式惯性导航系统航向漂移产生的主要原因。研究了由振动产生的系统水平轴航向效应漂移的机理,以及利用上、下陀螺配对减小系统航向效应漂移的机理,并通过试验测试表明,此项航向效应漂移可达0.2/°h,利用上、下陀螺配对后可将此项漂移减小到原来的十分之一以内。
Main reasons for heading effect drift of an airborne platform inertial navigation system are analyzed in this paper. Horizontal heading effect drift mechanism caused by platform vibration is studied. Also, mechanism of decreasing system heading effect drift with matching the upper and lower gyroscopes is investigated. Experiments show that the heading effect drift can be up to 0.2°/h, and this drift can be decreased within one tenth of the original by matching the upper and lower gyroscopes.
出处
《弹箭与制导学报》
CSCD
北大核心
2006年第1期42-44,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
平台式惯性导航系统
航向效应漂移
不等刚度漂移
平台振动
platform inertial navigation system
heading effect drift, non-equal rigid drift
platform vibration
