大气层内载体星光折射间接敏感地平定位可行性分析  

Feasibility Analysis of Stellar Refraction Indirect Horizon Sensing Positioning on the Carrier inside the Atmosphere

作　　者：詹先军 王新龙[1] 胡晓东[2] 丁小昆[2] Zhan Xianjun;Wang Xinlong;Hu Xiaodong;Ding Xiaokun(School of Astronautics,Beihang University,Beijing 100191,China;AVIC Xi’an Flight Automatic Control Research Institute,Xi’an 710065,China)

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]航空工业西安飞行自动控制研究所,西安710065

出　　处：《航空兵器》2022年第1期107-112,共6页Aero Weaponry

基　　金：国家自然科学基金项目(61673040);航空科学基金项目(20170151002);天地一体化信息技术国家重点实验室基金项目(2015-SGIIT-KFJJ-DH-01);重点基础研究项目(2020-JCJQ-ZD-136-12)。

摘　　要：星光折射间接敏感地平定位方法具有自主性强、精度高、成本低等特点,是一种很有应用前景的新型天文导航方法。目前,传统的星光折射间接敏感地平定位方法是以大气层外载体为应用对象而提出的一种天文定位方法,然而绝大部分载体主要工作在大气层内,为了分析这种星光折射间接敏感地平定位方法应用于大气层内载体的可行性,本文首先基于折射定律和球形大气模型建立了星光大气折射模型,分析了根据星光折射角与载体位置之间的关系进行星光折射间接敏感地平定位的工作机理,进而通过定量分析载体在大气层内、外观测的折射角偏差,对星光折射间接敏感地平定位方法在大气层内应用的可行性进行论证与分析。结果表明,传统星光折射间接敏感地平定位方法只适用于在40 km以上至大气层外飞行的载体,若能利用高度计获得载体的粗略高度,可以将星光折射间接敏感地平定位方法应用于大气层内飞行高度在20~40 km的飞行载体。The stellar refraction indirect horizon sensing positioning method has the characteristics of strong auto-nomy,high accuracy and low cost,which is a new celestial navigation method with great application prospect.At pre-sent,the traditional stellar refraction indirect horizon sensing positioning method is a celestial positioning method based on the carrier outside the atmosphere.However,most of carriers mainly work in the atmosphere.In order to analyze the feasibility of this stellar refraction positioning method on the carrier inside the atmosphere,the starlight atmospheric refraction model is established based on the refraction law and spherical atmospheric model,and the working mechanism of stellar refraction indirect horizon sensing positioning is analyzed according to the relationship between the stellar refraction angle and the carrier position.Then,the feasibility of the application of the stellar refraction indirect horizon sensing positioning method inside the atmosphere is demonstrated and analyzed by quantitatively analyzing the refraction angle deviation of the carrier inside and outside the atmosphere.The results show that the conventional stellar refraction positioning method is only applicable to the carrier flying above 40 km.If the rough height of the carrier can be obtained by altimeter,the stellar refraction indirect horizon sensing positioning method can be applied to the carrier with a flying altitude of 20~40 km inside the atmosphere.

关 键 词：天文导航 星光折射导航 间接敏感地平定位 星光大气折射 折射角 数学模型 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] V249.323[航空宇航科学与技术—飞行器设计]