过重力补偿GPS/INS末制导炮弹弹道仿真研究  

Simulation of complete integrated GPS/INS navigation system with over-gravity compensation for guided rocket projectiles

作　　者：丁传炳[1] 王良明[1] 郑翠翠[2] 

机构地区：[1]南京理工大学动力工程学院,江苏南京210094 [2]滁州学院经济管理系,安徽滁州239000

出　　处：《飞行力学》2010年第5期47-50,共4页Flight Dynamics

基　　金：兵科院重点预研基金资助(20402020101)

摘　　要：针对采用GPS/INS的复合制导炮弹,采用比例导引作为末制导的导引规律,从制导炮弹弹体运动学和动力学方程出发,进行了低成本组合导航系统的设计,建立了惯导系统的误差模型。针对位置、速度的组合方式,采用卡尔曼滤波算法,完成了组合导航系统的信息融合。根据超远程炮弹的弹道特点,进行了末制导段过重力补偿设计。全弹道仿真计算结果表明,该制导控制系统性能良好,可以精确地将制导炮弹导引到目标捕获区,实现以小脱靶量、大落角对目标的攻击。A proportional navigation is used as the terminal guidance law for the guided projectile on which the SINS/GPS are adopted.The analysis formulae for the guidance based on kinetics and dynamics equations are deduced.A low-cost integrated navigation system is designed.The GPS error model for the navigation system is established.For the combination of both position and velocity,the Kalman filter algorithm is used to complete the navigation system information fusion.According to the ultra-long-range trajectory characteristics of the projectile,the over-gravity compensation is added to the design.The whole trajectory simulation shows that the guidance and control system works well.It can accurately guide the projectiles to the target capturing zone and attack the target with a little position deviation in big impact angles.

关 键 词：制导炮弹 组合导航 过重力补偿 弹道 

分 类 号：TJ413.6[兵器科学与技术—火炮、自动武器与弹药工程]