基于微小型弹体的姿态控制系统的设计  

Design of Attitude Control System Based on Miniature Projectile

作　　者：张奴儿[1] 任勇峰[1] 李圣昆[1] 李新楠[1] 

机构地区：[1]中北大学电子测试技术国家重点实验室,太原030051

出　　处：《自动化与仪表》2011年第3期5-8,共4页Automation & Instrumentation

基　　金：国家自然科学基金资助项目(60871041)

摘　　要：现代战争的快速发展要求弹药具有高精度、高灵敏度及高可靠性,常规弹药智能化成为各国研究的方向,姿态控制作为飞行器控制系统的重要部分,对飞行器提高性能具有重要作用。基于微小型弹体姿态控制系统以FPGA为核心控制单元、四象限探测器为信息反馈单元、舵机为基本执行机构、尾翼为最终响应部件完成了设计。并进行了发射实验,实验表明该设计对弹体的姿态控制效果明显:在发射距离为10m、尾翼偏角为30°情况下平均偏转可达0.80°。为主动式激光制导技术在微小型高速运动体中的应用奠定了基础,具有广阔的应用前景。The rapid development of modern warfare demands ammunition with high accuracy,high sensitivity and high reliability,a national study of conventional ammunition,intelligent direction,attitude control as an important part of the aircraft control system,the aircraft has an important role in improving performance.Micro-based missile attitude control system to FPGA as the core control unit,four-quadrant detector is a feedback unit,steering for the basic implementing agencies,tail parts for the final response to the complete of the design.And made many launch experiments,the final experiment shows that the design of the missile＇s attitude control effect is obvious： in the firing distance 10m,tail angle of 30° where the average deflection of up to 0.80°.The system for the active laser-guided technology in the micro and small body of high-speed movement laid the foundation for operations in the future,has a very broad application prospects.

关 键 词：微小型弹体 姿态控制 舵机 现场可编程逻辑器件 

分 类 号：V249[航空宇航科学与技术—飞行器设计] TP273[自动化与计算机技术—检测技术与自动化装置]