Loran-C/INS组合导航系统在飞航导弹上的应用  

THE APPLICATION OF LORAN-C/INS COMBINED NAVIGATION SYSTEM TO THE WINGED MISSILE

作　　者：杜祖良[1] 顾文锦[2] 肖昌美[2] 

机构地区：[1]中国航天工业总公司三院 [2]海军航空工程学院

出　　处：《战术导弹技术》1995年第2期34-41,F004,共9页Tactical Missile Technology

摘　　要：建立了用于飞航导弹导航的Loran-C/INS组合导航系统的状态方程和测量方程,并设计了Loran-C/INS系统的次优卡尔曼滤波器。以某地区Loran-C台链为例,针对均方根值为0.1°/h和0.01°/h的陀螺漂移,将飞航导弹的动力学特性看作一阶惯性环节时,对组合系统的导航效果进行了仿真分析,结果显示LoranC/INS组合导航系统能提供较高精度的导航信息,具有较好的应用前景。The states and measurement equations of Loran-C/INS combined navigation system are es- tablished and the Kalman filter of the combined system is designed. Working on the Loran-C chain in some districts, the simulation analysis to the combined system is performed with gyro random drift of rms 0.1 (deg/h)and rms 0.01(deg/h)under the condition that the dynamics characteristics of the winged missile are simplified as a inertial unit. The result indicate that the Loran-C/INS combined system can give accurate nav- igation information and has wide prospect in application.

关 键 词：飞航导弹 导航 组合导航系统 导弹 

分 类 号：TJ761.5[兵器科学与技术—武器系统与运用工程]