单组舵控火箭弹控制能力及精度研究  

The Study on Control Ability and Accuracy of Single Group Rudder Control Rocket

作　　者：杜韩东[1] 曹红松[1] 赵捍东[1] 苑大威[1] 王泉[1] 

机构地区：[1]中北大学弹箭模拟仿真研究中心,太原030051

出　　处：《弹箭与制导学报》2011年第2期157-160,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：简易控制弹药由于其成本低、精度高,一直是国内外研究灵巧弹药的一个重要方向。文中在某常规火箭弹上加上两片气动舵,对火箭弹弹道进行数值仿真。主要分析了舵起控时间和舵偏角大小对修正能力的影响,并计算了舵的修正能力和控制精度。结果表明:在文中的假设条件下,选择10°舵偏角,出炮口47.55s时进行控制,能保证弹箭稳定飞行且修正能力最强,舵机的控制精度在0.8%以内。Low cost, high accuracy, simple control ammunition is one of important directions for smart munitions. Two pneumatic rudders were added to a conventional rocket, numerical simulation was studied on the rocket trajectory in this paper. The control time and the rudder angle effect on the correction ability were mainly analyzed, and the correction ability and control accuracy of the rudder were calculated. The results show that under the assumption in this paper, 10° rudder angle,47.55s after the muzzle when conducting control, the rocket can fly stably and the correction ability with the largest and the control accuracy is within 0.8%.

关 键 词：气动舵 修正能力 控制精度 

分 类 号：TJ013[兵器科学与技术—兵器发射理论与技术] TJ714