旋转式尾翼弹箭气动特性仿真计算  

Simulation and Calculation of Aerodynamic Characteristics of Rotating Missile with Tail Fins

作　　者：张超 王永祥 杨文凤[1] 王学德[3] ZHANG Chao;WANG Yongxiang;YANG Wenfeng;WANG Xuede(Chinese Flight Test Establishment,Xi'an 710089,China;Unit 93987 of PLA,Xining 810007,China;School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]中国飞行试验研究院,陕西西安710089 [2]中国人民解放军93987部队,青海西宁810007 [3]南京理工大学能源与动力工程学院,江苏南京210094

出　　处：《弹道学报》2024年第4期88-96,共9页Journal of Ballistics

摘　　要：为了深入研究尾翼式弹箭的气动特性变化规律,基于滑移网格方法开展了旋转式尾翼弹箭非定常绕流流场的仿真计算,利用ANF标模风洞实验结果验证了数值仿真方法的正确性。以某十字布局尾翼式弹箭为研究对象,在不同马赫数(Ma=0.9~2.0)、攻角(2°,4°)、旋转速度(πrad/s,2πrad/s,4πrad/s)、尾翼斜切角(0°,1°,2°)下,分析了旋转式尾翼弹箭的各气动特性参数变化规律及其影响机理。计算结果表明:旋转速度对弹箭的纵向气动特性(阻力、升力、俯仰力矩特性)基本没有影响,主要影响滚转特性和马格努斯特性;斜切尾翼角对弹箭的升力特性参数和俯仰力矩特性基本没有影响,主要影响阻力、滚转以及马格努斯特性;弹箭绕其纵轴旋转(0°~360°)过程中,阻力特性参数和升力特性参数呈现周期性变化规律,并且当弹箭旋转至45°时,瞬时升阻比最小;弹体是产生阻力特性的主导因素(85%左右);弹体和尾翼对升力特性的贡献各占50%左右。因此,在弹箭设计过程中要注意斜切尾翼角度以及转速所带来的影响,选取合适的斜切角。In order to study the aerodynamic characteristics of the missiles with tail fins,simulation was conducted to study the unsteady flow-field of the missiles with rotating tail fins based on sliding mesh method.The numerical simulation method adopted in this paper was verified by the wind tunnel experimental results of army-navy finner(ANF)standard model.Taking a certain cross-shaped layout tail-fin missile as the research object,the variation laws and influencing mechanisms of various aerodynamic-characteristic-parameters at different Ma(Ma=0.9-2.0),attack angles(2°,4°),rotation speeds(πrad/s,2πrad/s,4πrad/s),and tail-fin inclination angles(0°,1°,2°),were analyzed.The calculation results show that the rotation speed has little effect on the longitudinal aerodynamic characteristics(drag,lift,pitch moment characteristics)of the missile,mainly affecting the roll characteristics and Magnus effect.The inclination angle of the tail fin has little effect on the lift characteristics parameters and pitch moment characteristics of the missile,mainly affecting the drag,roll characteristics and Magnus effect.The resistance characteristics parameters and lift characteristics parameters of the missile show periodic variation during missile rotating around its longitudinal axis(0°-360°),and the instantaneous coefficient of lift and drag is the smallest when the missile rotates to 45°.The body is the dominant factor in generating the resistance characteristic(about 85%).The contribution of the body and tail to the lift characteristics is basically about 50%each.Therefore,in the design process of the projectile and arrow,attention should be paid to the advantages and disadvantages of the fin cant angle and rotation speed,and a suitable oblique angle should be selected.

关 键 词：弹箭 旋转速度 斜切尾翼角 气动特性 数值仿真 

分 类 号：TJ385[兵器科学与技术—火炮、自动武器与弹药工程]