摘要
针对单频点地基增强系统不能满足飞机CAT III类精密进近与着陆导航需求问题,提出一种机载差分GPS(DGPS)与捷联式惯性导航系统(SINS)紧组合导航工作模式,利用SINS提高组合后系统的导航特性。分析了SINS/DGPS紧组合滤波模型,并构建了紧组合导航状态方程和量测方程,利用改进的Kalman滤波器对滤波状态进行最优估计与补偿。进行了计算机仿真与实际系统验证实验,实验结果表明,SINS/DGPS组合导航系统中,当卫星信号不可用时,利用SINS具备的自主性能够提高导航系统的连续性和可用性,同时组合导航系统位置误差标准差相比机载DGPS单系统减小了50%以上,提高了导航系统位置引导精度。
To solve the problem that the single-frequency ground-based augmentation system cannot meet the requirements of precision approach and landing navigation of aircraft category III,a navigation mode which tightly integrates airborne Differential GPS(DGPS)with Strapdown Inertial Navigation System(SINS)is proposed,and SINS is used to improve the navigation characteristics of the integrated navigation system.The tightly integrated SINS/DGPS filtering model is analyzed,and the state equation and measurement equation of tightly integrated navigation are constructed.The filtering states are estimated and compensated by using the improved Kalman filter.Computer simulation and actual system validation experiments are carried out.The experiment results show that when the satellite signal is not available in SINS/DGPS integrated navigation system,the autonomy of SINS can improve the continuity and availability of the navigation system.Meanwhile,the standard deviation of position error of the integrated navigation system is reduced by more than 50%compared with that of the single airborne DGPS system,and the position guidance accuracy of the navigation system is improved.
作者
胡杰
严勇杰
石潇竹
HU Jie;YAN Yongjie;SHI Xiaozhu(The 28th Research Institute of China Electronics Technology Group Corporation,Nanjing 210007,China;State Key Laboratory of Air Traffic Management System and Technology,Nanjing 210007,China)
出处
《电光与控制》
CSCD
北大核心
2020年第4期38-43,共6页
Electronics Optics & Control
基金
国家重点研发计划(2017YFB0503401)。
关键词
地基增强系统
捷联式惯性导航系统
紧组合
改进Kalman滤波器
ground-based augmentation system
strapdown inertial navigation system
tight integration
improved Kalman filter
