鸭舵后掠角对火箭弹尾翼的滚转性能研究  

Research of Rolling Characteristics on Rocket Wing by Canard Sweepback

作　　者：郭向向 曹红松[1] 程登华 张晓东[1] 

机构地区：[1]中北大学机电工程学院 [2]78098部队

出　　处：《弹箭与制导学报》2017年第2期170-172,F0003,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：根据具有较大翼面的鸭式布局火箭弹难以进行滚转控制的特性,文中采用数值流体力学分析手段,建立鸭式布局火箭弹外流场模型,仿真分析了鸭舵滚转效应产生机理、鸭舵下洗对尾翼气动耦合规律以及后掠角对火箭弹滚转性能的影响。仿真结果表明由于鸭舵下洗作用,在尾翼上诱导出一个舵控方向相反的滚转力距,使滚转控制能力降低甚至反效;在后缘后掠角χ≠0°时,随着后缘后掠角的减小火箭弹的滚转控制能力基本不变。Since canard-controlled rocket with larger airfoil is difficult for rolling control, numerical fluid mechanics analysis method was applied in this paper, and canard-controlled rocket＇ s exterior flow field model was established, mechanism of canard rolling effect, the effect of washing on wing sweep angle of aerodynamic coupling law and rocket roll performance at canard were analyzed by simulation. Sim- ulation results show that roiling moments could be reduced, even the phenomenon of anti-effect disappears completely due to revered rolling moment induced fin＇s downwash flow, the trailing edge sweepback angle χ≠0°, the rocket rolling control ability keeps substantially con- stant with trailing edge sweepback angle decrease.

关 键 词：鸭式布局 后缘后掠角 滚转特性 数值仿真 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]