惯性+星光折射定位组合导航技术研究  

Research on Integrated Navigation Based on Inertial Navigation and Stellar Refraction Positioning

作　　者：胡楠希 李小琥 李自行[1] HU Nan-xi;LI Xiao-hu;LI Zi-xing(Beijing Institute of Control and Electronic Technology,Beijing 100038,China)

机构地区：[1]北京控制与电子技术研究所,北京100038

出　　处：《导航定位与授时》2021年第1期90-95,共6页Navigation Positioning and Timing

基　　金：国家安全重大基础研究项目(6133030202)。

摘　　要：由于现有惯性器件精度水平有限,纯惯性导航误差较大,因此需要采用组合导航的方式来提高导航精度。目前,全自主组合导航方式中传统的惯性+星光定姿组合导航方法只能实现定姿,不能实现定位,无法修正加速度表测量误差引起的惯性导航误差,故在精度上可提升空间有限。为此,提出了一种惯性+星光折射定位组合导航方法,重点从星光折射定位原理、大气折射模型、非线性滤波和选星策略几个方面进行论证及分析。通过理论分析与数学仿真相结合的手段,验证了星光折射定位原理的正确性及工程可行性,可将自主导航精度提升至100m,从而为进一步提高自主导航精度提供了一种技术途径。The pure inertial navigation error is relatively large due to the limited accuracy of the existing inertial devices,thus it is necessary to use integrated navigation to improve the navigation accuracy.Traditionally,the fully autonomous inertial/stellar attitude integrated navigation method can not determine the position but the attitude,nor can it correct the inertial navigation error caused by the accelerometer measurement error,so the improvement of navigation accuracy is limited.To solve this problem,a method of integrated navigation based on inertial navigation and stellar refraction positioning is proposed.The research is mainly conducted from several aspects,such as the principle of stellar refraction,the model of starlight atmosphere refraction,nonlinear filer and strategy of star choice.By theoretical analysis and mathematical simulation,the correctness of star refraction positioning principle and engineering feasibility are verified.And the navigation accuracy is improved to 100 m,which provides a technical approach to improve the accuracy of autonomous navigation.

关 键 词：星光折射定位 大气折射模型 非线性滤波 选星策略 

分 类 号：V249.32[航空宇航科学与技术—飞行器设计]