传感技术学报2007，Vol.20Issue(1)：237-241,5.
低精度的SINS/GPS组合导航系统中初始航向对准技术
Novel Approach to In-Flight Alignment of Micro-Mechanical SINS/GPS with Heading Uncertainty
严恭敏 1秦永元1
作者信息
- 1. 西北工业大学自动化学院,西安,710072
- 折叠
摘要
Abstract
The paper presents a novel approach to in-flight alignment algorithm for a Strapdown Inertial Navigation System (SINS) with heading uncertainty To handle large heading error during the short-time alignment course, the estimate of large heading error is converted into the estimate of two trigonometric variables. In this algorithm a linear Kalman filter is introduced. The simulation results show that the vehicle heading uncertainty is solved to abou t 3°(1σ) within 20 s.关键词
捷联惯导系统/SINS/GPS组合导航系统/初始对准/卡尔曼滤波Key words
SINS/SINS/GPS integrated navigation system/initial alignment/Kalman filtering分类
航空航天引用本文复制引用
严恭敏,秦永元..低精度的SINS/GPS组合导航系统中初始航向对准技术[J].传感技术学报,2007,20(1):237-241,5.
