飞机导航系统中多套惯导融合方案仿真分析研究  

Simulation Study and Analysis on the Multi-Inertial Navigation Fusion Scheme in Aircraft Navigation System

作　　者：白俊强[1,2] 昌敏 汪辉[3] 郭彬 刘成茂 BAI Junqiang;CHANG Min;WANG Hui;GUO Bin;LIU Chengmao(Unmanned System Research Institute,Northwestern Polytechnical University,Xi’an 710072,China;Xi’an Sogea Aviation Technology Co.,Ltd.,Xi’an 710065,China;School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学无人系统技术研究院,西安710072 [2]西安索格亚航空科技有限公司,西安710065 [3]西北工业大学航空学院,西安710072

出　　处：《无人系统技术》2020年第6期79-91,共13页Unmanned Systems Technology

摘　　要：针对民航飞机飞行过程中提高导航精度和可靠性的问题,提出了一种多套惯导融合方案,研究了三套惯导平行安装冗余配置条件下最优导航解的求解方法。根据已有导航结果与每次飞行过程结束时刻和起始时刻飞机位置点已知的特点,通过前一次导航误差计算三套惯导的加权系数融合一个较好的位置并能够对惯导故障进行诊断。结果表明,在IRS无故障时,三套惯导根据历史信息加权融合后,最佳混合位置误差在400 m之内;在IRS有故障时,最佳混合位置误差在500 m之内。惯导融合方案能够大幅提高基于一套惯导的位置更新误差,为民机导航提供更加准确的导航信息和依据。Aiming at the problem of low navigation accuracy in the flight of civil aviation aircraft,a multi-inertial navigation fusion scheme is proposed and the optimal navigation solution under the condition of three inertial navigation parallel installation redundant configuration is studied.According to the existing navigation results and the known characteristics of aircraft position points at the end and beginning of each flight process,the weighted coefficients of the three sets of INS are calculated through the previous navigation error to fuse a better position.The results show that when IRS is fault-free,the optimal mixing position error is within 400 m after the weighted fusion of the three inertial navigation sets according to the historical information.In the case of IRS failure,the optimal mixed position error is within 500 m.The multi-inertial navigation fusion scheme provides a high accuracy position update method,which leads to a reliable navigation system.

关 键 词：惯性导航系统 多惯导融合 航空导航技术 导航精度 导航可靠性 惯导故障诊断 

分 类 号：V249.[航空宇航科学与技术—飞行器设计]