基于比力积分匹配的惯导系统传递对准  

Transfer Alignment of Inertial Navigation System Using Specific Force Integration

作　　者：赵宾[1] 刘建业[1] 曾庆化[1] 钱伟行[1] 

机构地区：[1]南京航空航天大学导航研究中心,南京210016

出　　处：《应用科学学报》2009年第4期425-429,共5页Journal of Applied Sciences

基　　金：国家"863"高技术研究发展计划基金(No.2006AA12A108);航空科学基金(No.20070852009)资助项目

摘　　要：某些机载装备的传递对准过程要求在机体升空阶段进行。受飞行速度的限制,采用传统匹配方案使传递对准精度受到很大影响。本文提出一种适合机体低速运行条件的"比力积分"匹配方案,利用主子惯导比力差的积分作为卡尔曼滤波的观测值,未引入陀螺误差,且SINS仅作比力积分计算,减少了SINS对准期间的计算量,保证了传递对准的实时性。在考虑安装误差角和挠曲变形角的条件下建立了系统误差的数学模型。仿真结果表明,该方案能在机体低速运行条件下有效提高机载装备的传递对准精度,对于中低精度的捷联惯导系统有工程实用价值。Transfer alignment of some airborne equipment is executed during takeoff of the aircraft. With traditional matching schemes, the transfer alignment accuracy is affected due to the limited speed of aircraft. To solve this problem, a specific force integration matching scheme is proposed to adapt to the aircraft＇s low speed. Observation of Kalman filtering is the integration of specific force difference between master inertial navigation system （MINS） and slave inertial navigation system （SINS）, and gyro error is not imported. Since SINS only performs calculation of the specific force integral, computation complexity is reduced. Taking into account error angle in installation and the flexural distortion angle, a system error model is established. Simulation results indicate that the proposed method can improve transfer alignment accuracy at low aircraft speed. It is potentially useful in medium and low-precision strap-down inertial navigation systems.

关 键 词：惯性导航 传递对准 低速 卡尔曼滤波 

分 类 号：V448[航空宇航科学与技术—飞行器设计]