摘要
提出了一种基于 GPS/INS 的制导型火箭弹系统概念。制导型火箭弹采用弹载 GPS/INS 组合系统获取实际弹道数据,将其与基准弹道数据进行比较,根据偏差产生控制指令,采用鸭舵对火箭弹进行全程三通道控制,采用自由旋转尾翼实现鸭舵和尾翼之间的气动解耦。此外,对制导型火箭弹的结构布局、主要部件及其功能和大体工作过程进行了分析,指出了有待解决的关键技术。
A system concept of guided artillery rocket based on GPS/INS is brought forward.The guided artillery rocket acquires actual trajectory data with mounted GPS/INS,compares it with a reference trajectory data,creates instructions by the difference,uses canards for all-course control with three-axis autopilot and free-spin tails for aerodynamic decoupling between canards and tails.Furthermore,its structure configuration,main components and their functions,general working process are analyzed,and some key techniques are pointed out.
出处
《弹箭与制导学报》
CSCD
北大核心
2003年第S5期173-175,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
