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基于单星测量的星光惯性组合导航
引用本文:乔川,李晓,庞少龙,闫蓬勃,李丹凤,夏梦绮,徐卿. 基于单星测量的星光惯性组合导航[J]. 光学精密工程, 2021, 29(3): 503-512
作者姓名:乔川  李晓  庞少龙  闫蓬勃  李丹凤  夏梦绮  徐卿
作者单位:北京控制工程研究所,北京100190;空间光电测量与感知实验室,北京100190
基金项目:国家自然科学基金资助项目(No.11903004,No.51905034)。
摘    要:为减小杂光影响,全天时星光定向仪一般采用小视场,同一时刻只能观测一颗恒星无法输出姿态信息.本文提出一种基于单星测量的星光惯性组合导航系统,首先根据惯导输出的姿态和位置信息,控制转台和星光定向仪摆镜保证星光定向仪对目标导航星的观测,之后根据惯导的误差模型建立系统状态方程,根据星光定向仪测量的导航星方向矢量建立测量方程,利...

关 键 词:星光惯性组合导航  安装误差估计  误差分析  卡尔曼滤波

Starlight-inertial integrated navigation based on single star vector
QIAO Chuan,LI Xiao,PANG Shao-long,YAN Peng-bo,LI Dan-feng,XIA Meng-qi,XU Qing. Starlight-inertial integrated navigation based on single star vector[J]. Optics and Precision Engineering, 2021, 29(3): 503-512
Authors:QIAO Chuan  LI Xiao  PANG Shao-long  YAN Peng-bo  LI Dan-feng  XIA Meng-qi  XU Qing
Affiliation:(Beijing Institute of Control Engineering,Beijing 100190,China;Space Optoelectronic Measurement and Perception Lab,Beijing 100190,China)
Abstract:A small-field optical system is typically used in an all-day star sensor to reduce the stray light ef?fect.Generally,only one star can be observed at a particular time by an all-day star sensor,and attitude in?formation cannot be output.Therefore,a method of starlight-inertial integrated navigation based on a sin?gle star vector was developed in this study.First,the turntable and the mirror were controlled using the position and attitude information provided by the inertial navigation system to track the star.Next,the state equation was derived using the inertial navigation error model,and the measurement equation was es?tablished based on the direction vector of a single star,which was measured using the star sensor.The po?sition and the attitude information were corrected through Kalman filtering.Because the installation attitude error was pulled in the state quantity,the installation attitude error and the navigation information were estimated simultaneously.It was unnecessary to calibrate the installation attitude between the star sensor and inertial navigation in the laboratory.Therefore,this method was proven to show stronger proj?ect practicability.The effects of the star sensor and inertial navigation error and the calibration error of the installation attitude were analyzed through simulation,which showed that the position and attitude errors after 1 h were less than 90 m and 8″,respectively.Compared to the navigation method,which is typically used for installation attitude calibration in the laboratory,this integrated navigation algorithm showed bet?ter accuracy.Finally,the validity of the integrated navigation algorithm was verified through static naviga?tion tests.The navigation position error was 102.90 m,which was lower than that obtained based on the calibrated installation attitude by 45.39%.
Keywords:starlight-inertial integrated navigation  installation attitude error  error analysis  Kalman fil?tering
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