光学精密工程2025，Vol.33Issue(17)：2821-2832,12.DOI:10.37188/OPE.20253317.2821
基于卫星星光观测的星惯组合导航技术
Starlight-inertial integrated navigation based on satellite celestial observation
摘要
Abstract
The performance of vehicle inertial navigation systems degrades severely in GNSS-denied envi-ronments.To address this limitation,a starlight-inertial integrated navigation method based on satellite celestial observation is proposed.Targets(stars and satellites)within the sensor field of view are first iden-tified through image preprocessing.Attitude is then determined from star measurements obtained by the star sensor.Using satellite ephemerides,the satellite position in the Earth-centered,Earth-fixed(ECEF)frame at the current epoch is computed,and the resulting geometric vector between vehicle and satellite is formed to establish the measurement equation.By combining this measurement with an inertial navigation error model,a state equation is constructed and position and attitude estimates are updated via Kalman fil-tering.Compared with conventional star-only observations,the relatively limited range to satellites per-mits direct provision of position information from satellite observations,preventing divergence of naviga-tion position error and enhancing practical applicability.The effect of satellite position error is analyzed through simulation,which demonstrates that the proposed integrated navigation algorithm achieves high accuracy.The algorithm was further validated in a static navigation test,yielding a 2-hour navigation posi-tion error of 41.42 m;across tests with varying initial position errors,navigation position error remained below 150 m.关键词
卫星观测/星光惯性组合导航/卡尔曼滤波/误差分析Key words
satellite observation/starlight-inertial integrated navigation/Kalman filtering/error analysis引用本文复制引用
闫蓬勃,李佳豹,张辉,徐晓丹,安悦晗,乔川..基于卫星星光观测的星惯组合导航技术[J].光学精密工程,2025,33(17):2821-2832,12.基金项目
国家自然科学基金青年基金资助项目(No.52405247) （No.52405247）
