GPS/INS组合导航在制导火箭弹中的应用  

Study on the Application of GPS/INS Integrated Navigation System to Guided Rocket Projectile

作　　者：丁传炳[1] 王良明[1] 常思江[1] 

机构地区：[1]南京理工大学动力学院,南京210094

出　　处：《火力与指挥控制》2010年第11期138-141,共4页Fire Control & Command Control

基　　金：兵科院重点预研基金资助项目(20402020101)

摘　　要：为实时、精确获得火箭弹飞行过程中的状态参数,针对火箭弹的导航环境,研究了GPS/INS组合导航系统在制导火箭弹中的应用,建立了组合系统的动态方程及位置、速度组合误差模型,采用卡尔曼滤波器对该组合系统进行最优估计并进行了仿真分析。仿真结果表明,组合导航系统能为火箭弹制导提供高精度的位置姿态信息,进而为控制系统提供较精确的测量信息,从而大大提高了火箭弹的射击精度。考虑到导航系统成本较低、工作可靠,算法可以实时实现,因此研究结果具有一定的实际应用价值。In order to obtain the state parameters of the rocket during its flight rapidly and accurately,aiming at the navigation environment of the rocket projectiles,the application of GPS/INS integrated navigation system in guided rocket projectile was studied.The dynamic equations of composite system and error model of position and velocity were both established.Kalman filtering was adopted to conduct the optimal estimation for the system and finally the simulation was done.The simulation result shows that the integrated navigation system can provide relatively accurate position and attitude information for projectiles and then give more accurate measurement information to the control system so as to enhance firing precision.Considering that the integrated navigation system has low cost and high reliability and the algorithm can be realized in real time,some results concluded are useful for further research.

关 键 词：制导火箭弹 GPS INS 卡尔曼滤波 组合导航 

分 类 号：TJ413.6[兵器科学与技术—火炮、自动武器与弹药工程]