同济大学学报（自然科学版）2011，Vol.39Issue(12)：1865-1870,6.DOI:10.3969/j.issn.0253-374x.2011.12.025
机载捷联惯导的导航计算模型与精度分析
Navigation Calculation Model for Airborne SINS and Its Accuracy Analysis
摘要
Abstract
A study was made of the navigation calculation model in local frame and detailed steps for strapdown inertial navigation system (SINS). Then the error characteristics of SINS was analyzed through navigation calculation with the measured data. Finally, GPS/SINS loose coupling was implemented by using Kalman filter and Kalman smooth. The results show that, coordinate error of SINS grows as parabola function, in a short time it can provide accurate navigation parameters, with coordinate error less than 2 meters within one minute. SINS/GPS integrated navigation system, which combines advantages of the two systems, gains more reliability and integrity respect to each subsystem.关键词
捷联惯性导航系统/导航计算/捷联导航算法/松散组合Key words
strapdown inertial navigation systems navigation calculation/strapdown navigation algorithm/loose coupling分类
航空航天引用本文复制引用
刘春,周发根..机载捷联惯导的导航计算模型与精度分析[J].同济大学学报（自然科学版）,2011,39(12):1865-1870,6.基金项目
国家"八六三"高技术研究发展计划(2009AA12Z310) （2009AA12Z310）
