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