弹道导弹捷联惯导/天文组合导航方案研究

Research on scheme of SINS/celestial integrated navigation for ballistic missile

通过分析捷联惯性导航和天文导航的特点,提出利用扩展卡尔曼滤波方法融合捷联惯导和星光测量信息以提高弹道导弹落点精度的可行方案。研究了捷联惯导系统误差模型,建立了滤波误差状态方程和星敏感器原始信息测量方程。星敏感器从发动机关机后开始工作,在滤波过程中对捷联惯导测量误差进行了反馈校正。仿真结果表明,星敏感器开始工作后导弹的位置、速度和姿态误差的方差立即减小,导弹的落点精度也大幅度提高。

The characteristics of strap-down inertial navigation and celestial navigation are analyzed.Based on these characteristics,a practicable scheme of increasing the ballistic missile precision is given.In the scheme,the information fusion of SINS and starlight is realized by the EKF.The error model of SINS is studied in this article,then the error state equation and the measurement equation are derived.The starlight sensor goes into operation after the engine flameout.The error of SINS is corrected during the process of filtering.At last,the simulation is made,which proves that the precision of position,velocity and attitude are improved immediately after the fusion,and the landing error is decreased by a wide margin.