舵偏角对二维修正火箭弹气动特性的影响  

Effect of Rudder Angle on Aerodynamic Characteristics of Trajectory-Correction Rocket Missile

作　　者：刘琦 杨新民[1] 管军[1] LIU Qi;YANG Xinmin;GUAN Jun(State Key Laboratory of Transient Physics,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学瞬态物理国家重点实验室,南京210094

出　　处：《兵器装备工程学报》2018年第9期59-63,共5页Journal of Ordnance Equipment Engineering

摘　　要：为研究不同舵偏角对某弹道修正火箭弹流场特性和气动特性的影响,基于3D N-S方程和S-A湍流模型,采用FLUENT软件对弹丸在不同舵偏角、不同马赫数、不同攻角下进行气动仿真计算,得到不同舵偏角下弹丸的升力系数和稳定储备量。仿真结果表明:舵偏角越大,平衡攻角越大,升力系数越大,稳定储备量呈先减小后增大的趋势。In order to study the influence of different rudder angles on the flow field characteristics and aerodynamic characteristics of a ballistic correction rocket,based on 3 D N-S equation and SA turbulence model,FLUENT software was used to simulate different rudder angles,different Mach numbers,and different angles of attack of projectiles. The aerodynamic simulation calculations were carried out to obtain the lift coefficient and steady reserve of the projectile under different rudder angles at balanced angle of attack. The simulation results show that the larger the rudder angle is,the larger the lift coefficient is at the balanced angle of attack,and the steady reserve decreases first and then increases.

关 键 词：舵偏角 气动仿真 FLUENT 升力系数 稳定储备量 

分 类 号：TJ303.4[兵器科学与技术—火炮、自动武器与弹药工程]