一种强跟踪UKF及其在GPS/SINS深组合导航中的应用  

Strong Tracking UKF and Its Application in GPS/SINS Deeply Integrated Navigation

作　　者：叶晨 崔双喜[1] Ye Chen;Cui Shuang-xi(College of Electrical Engineering,Xinjiang University,Urumchi,830047)

机构地区：[1]新疆大学电气工程学院,乌鲁木齐830047

出　　处：《导弹与航天运载技术》2018年第2期61-64,74,共5页Missiles and Space Vehicles

基　　金：新疆维吾尔自治区自然科学基金项目(2014211A007)

摘　　要：针对弹道导弹的特点,研究了发射惯性系下GPS/SINS深组合导航下的一种强跟踪无迹卡尔曼滤波算法。该算法根据渐消的思想,通过引入多重次优渐消因子到UKF滤波器,自适应地在线调整UKF滤波器的预测状态协方差阵,从而有效跟踪快速变化的状态量。仿真结果显示,UKF引入次优多重衰落因子对算法进行改进后,对高度机动目标的跟踪能力更强,强跟踪无迹卡尔曼滤波器对快速变化的状态将具有更强的跟踪。改进算法在保证原有的UKF滤波算法精度的同时,使系统误差在较短的时间内收敛。Aiming at characteristics of Ballistic missile,the GPS/SINS deeply integrated navigation algorithm based on strong tracking unscented Kalman filter(STUKF)in the Launch inertial coordinates is studied in this paper.The algorithm is based on the thought of fading,by introducing suboptimal multiple fading factor into UKF filter,perform real-time adjustment on the error covariance of predicted state adaptively,so as to effectively track the rapidly changing state quantities.The simulation results show that the UKF introduces the suboptimal multiple fading factor to improve the algorithm,and the tracking capability of the high maneuvering target is stronger.The STUKF filter will have a stronger tracking of the fast changing state.The improved algorithm ensures the original UKF filtering algorithm accuracy,at the same time,the system error is shown to converge in a shorter period of time.

关 键 词：发射惯性系 深组合 强跟踪 渐消因子 

分 类 号：V249.3[航空宇航科学与技术—飞行器设计]