摘要
分别建立了发射点惯性坐标系和当地地理坐标系下的惯导误差传播模型,以及典型匹配模式下的传递对准基本方程。基于运载火箭主动段飞行,分析了姿态机动运动对两种坐标系下传递对准的不同影响。数学模型和仿真分析表明,两种坐标系下的传递对准在原理和系统特性上均有较大差异。典型匹配方案的对准效果对比表明,发射点惯性坐标系内的"角速度+加速度"匹配是一种能够实现子惯导快速、准确初始化的有效方法。
The error transfer models of inertial navigation system（INS） in launch-point inertial coordinate and local geographical coordinate are built respectively,and the transfer alignment algorithms （such as ＂velocity ＋ attitude＂,＂angular velocity ＋ acceleration） in these two coordinates are derived and applied respectively.Based on the powered flight trajectory of launch vehicle,the effects of attitude maneuvers on the INS transfer alignment in these two coordinates are analyzed through typical flight simulations.Theoretical models and simulation analyses show that the transfer alignments in the two coordinates have obvious differences in terms of principle,model and system characteristics.The effects of typical alignment schemes are presented,which show that the match scheme of ＂angular velocity ＋ acceleration＂ in launch-point inertial coordinate is an effective method for realizing rapid and accurate initialization of sub-INS.
出处
《中国惯性技术学报》
EI
CSCD
北大核心
2010年第3期272-278,共7页
Journal of Chinese Inertial Technology
基金
航天技术支撑基金项目(0712105)
关键词
传递对准
机动
发射点惯性坐标系
当地地理坐标系
transfer alignment
maneuver
launch-point
inertial coordinate
local geographical coordinate
作者简介
韩鹏鑫（1983-），男，博士研究生，研究方向为飞行器组合导航技术、惯导系统传递对准、GNC系统设计。E-mail：huangtgh@163．com
联系人：崔乃刚（1965-），男，教授，博士生导师。E-mail：Cui_Naigang@163．com
