GNSS/INS组合导航在飞行进近着陆中的应用  

Research on Flight Approach Landing based on GNSS/INS Navigation

作　　者：杨姝[1] 韩宇康 加松 YANG Shu;HAN Yu-kang;JIA Song(Civil Aviation Flight University of China,Guanghan 618000,China)

机构地区：[1]中国民用航空飞行学院,四川广汉618000

出　　处：《航空计算技术》2025年第1期114-118,共5页Aeronautical Computing Technique

基　　金：中国民用航空局安全能力建设资金项目资助(MHAQ2024029);基于北斗的星基导航增强系统时空性能测量装置研制项目资助(2021YFF0603903-5)。

摘　　要：针对航空器进近着陆中全球卫星导航系统(Global Navigation Satellite System,GNSS)易受干扰导致精度变差的情况,将惯性导航系统(Inertial Navigation System,INS)和GNSS系统融合成GNSS/INS组合导航系统,模拟仿真了包含航空器进近着陆的轨迹并进行算法验证。结果显示进近着陆阶段的姿态角误差、速度误差和位置误差均值分别比巡航阶段减少98.95%、76.84%、60.65%。最后通过组合导航系统实验和Septentrio高精度GNSS接收机进行验证。结果显示东向、北向及天向位置误差均值分别为0.503688 m、0.482033 m和1.774242 m,满足民航一类精密进近水平和垂直精度要求,进一步验证了系统算法。In view of the vulnerability of Global Navigation Satellite System(GNSS)to interference during aircraft approach and landing,Inertial Navigation System(INS)and GNSS system are integrated into GNSS/INS integrated navigation system,which simulates the trajectory of aircraft including approach and landing and verifies the algorithm.The results show that the mean attitude Angle error,velocity error and position error are reduced by 98.95%,76.84%and 60.65%,respectively,compared with the cruise stage.Finally,through the integrated navigation system experiment and the Septentrio high-precision GNSS receiver,the results show that the mean position errors of the east,north and sky positions are 0.503688 m,0.482033 m and 1.774242 m,respectively,meeting the horizontal and vertical accuracy requirements of a class of precision approach in civil aviation.The system algorithm is further verified.

关 键 词：全球卫星导航系统 进近着陆 惯性导航系统 组合导航 信息融合 

分 类 号：P228.4[天文地球—大地测量学与测量工程] V328[天文地球—测绘科学与技术]