INS全温六方位速率标定及分段线性插值补偿  

Six-position rotation rate calibration and piecewise linear interpolation compensation for INS in full temperatures

作　　者：李建利[1] 房建成[1] 马艳海[1] 程骏超[1] 

机构地区：[1]北京航空航天大学惯性技术重点实验室,北京100191

出　　处：《北京航空航天大学学报》2012年第10期1331-1335,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家973计划资助项目(2009CB72400);国家自然科学基金资助项目(60904093);国家自然科学基金创新研究群体资助项目(61121003);国家863计划重点资助项目(2008AA121302);国家杰出青年科学基金资助项目(60825305)

摘　　要：针对捷联惯性导航系统(INS,Inertial Navigation System)全温动态环境下测量误差问题,提出一种全温六方位正反速率标定及分段线性插值补偿方法.根据工作环境设定标定温度点,在每个恒温点设计六方位正反速率标定方案;采用分段线性插值算法实时补偿系统零偏和标度因数温度误差,提高了系统温度及动态环境下的测量精度.实验结果表明:采用该方法系统的车载和飞行实验纯惯性导航误差均值分别由1.501 n mile/h和5.811 n mile/h减小到0.393 n mile/h和0.681n mile/h,为进一步提高合成孔径雷达(SAR,Synthetic ApertureRadar)成像分辨率奠定基础.For decreasing measurement error of inertial navigation system （INS） , a novel scheme was pro- posed in which a six-position rotation calibration and piecewise linear interpolation compensation in full tem- peratures. A six-position rotation rate calibration experiment was implemented in a series of constant tempera- ture. Moreover, a piecewise linear interpolation algorithm was used to compensate for bias and scale factor temperature errors of gyroscopes and accelerometers, and to improve the measurement precision of INS. The experimental results show that the inertial navigation average errors are reduced to 0. 393 n mile/h and 0. 681 n mile/h from 1. 501 n mile/h and 5. 811 n mile/h for vehicle and airborne experiments. The proposed method i~ helpful to further improving image resolution of synthetic aperture radar （SAR）.

关 键 词：惯性导航系统 误差标定 分段插值 补偿 

分 类 号：V249.32[航空宇航科学与技术—飞行器设计]