一种基于高精度数学地平的惯性/天文组合导航方案  

A SINS/CNS Integrated Navigation System Based on High Precision Mathematical Horizon Reference

作　　者：袁丁 王新龙[1] Yuan Ding;Wang Xinlong(School of Astronautics,Beihang University,Beijing 100083,China)

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《航空兵器》2024年第6期120-126,共7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);重点基础研究项目(2020-JCJQ-ZD-136-12);试验技术项目(1700050405);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)。

摘　　要：惯性/天文组合导航具有自主性高、抗干扰能力强的优势,在弹道导弹、空天再入式飞行器的导航任务中具有重要的应用价值。在传统惯性/天文组合导航系统中,惯导提供的数学地平误差随时间发散,导致天文定位精度逐渐降低,进而造成惯性/天文组合导航系统长时间工作时定位精度严重发散。为此,本文给出了惯导系统提供数学地平的机理,分析了数学地平精度与天文定位误差的耦合关系,建立了惯导误差与数学地平精度的关系模型,提出了一种高精度数学地平获取方法;在此基础上,设计了一种基于高精度数学地平的惯性/天文组合导航方案。利用高精度数学地平获取天文观测角,引入高度计获取不随时间发散的高度信息,实现了对组合导航误差的全面估计与校正。仿真结果表明,与传统方法相比,所提方法通过抑制数学地平误差发散,能够显著提高组合导航精度,满足再入式飞行器长时高精度导航的需求。SINS/CNS integrated navigation system has the advantages of high autonomy and strong anti-interference ability.It has important application value in the navigation tasks of ballistic missiles and reentry vehicles.However,in traditional SINS/CNS integrated navigation system,the mathematical horizon error provided by the SINS diverges over time,leading to a decrease in the accuracy of celestial positioning.As a result,the positioning accuracy of the SINS/CNS integrated navigation system is seriously divergent in long-duration flight.Therefore,this paper elucidates the mechanism by which the inertial navigation system supplies the mathematical horizon reference,analyzes the relationship between mathematical horizon accuracy and celestial positioning error,establishes the relationship model between inertial navigation error and mathematical horizon accuracy,and proposes a high-precision mathematical horizon acquisition scheme.On this basis,a SINS/CNS integrated navigation system is designed based on high precision mathematical horizon reference.The celestial observation angle is obtained by using high-precision mathematical horizon reference,and the altitude information is obtained by introducing an altimeter to estimate and correct the integrated navigation error.Simulation results show that,compared to traditional method,the proposed method significantly improves the precision of integrated navigation by suppressing the divergence of mathematical horizon errors,thereby meeting the requirements for long-duration high-precision navigation missions.

关 键 词：惯性导航 天文导航 组合导航 数学地平 天文观测角 高度计 

分 类 号：TJ760[兵器科学与技术—武器系统与运用工程] V249[航空宇航科学与技术—飞行器设计]