不同尾翼和数量对卷弧翼干扰弹在亚声速下的静稳定性分析研究  

Study on the stability of the spinner with different tail fins and number at subsonic velocity

作　　者：曹德恒 王健[1] 黄智康 Cao Deheng;Wang Jian;Huang Zhikang(School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学能源与动力工程学院,江苏南京210094

出　　处：《江苏科技信息》2023年第10期60-67,共8页Jiangsu Science and Technology Information

摘　　要：针对不同卷弧翼尾翼的结构和数量对小长径比干扰弹稳定性的影响,建立3种尾翼布局干扰弹的三维简化模型,同时能够保证3种不同尾翼布局的尾翼展长都能够折叠到弹径尺寸。文章分别对3种尾翼布局干扰弹进行数值模拟,重点分析攻角α=0°时,在亚声速状态下不同马赫数(Ma)变化对干扰弹气动特性的影响,以及Ma=0.5,不同攻角下干扰弹气动特性的差异,并验证了文中所采用数值计算方法的可行性。结果表明:总展长不变,增加尾翼的数量会使得干扰弹的阻力系数减小,升力系数减小,俯仰力矩系数减小;相同尾翼数量的带有前缘后掠角尾翼会使得干扰弹阻力系数减小,升力系数减小,滚转力矩减小,俯仰力矩系数减小;同时,四翼0°前缘后掠角的尾翼气动特性在Ma=0.5、不同攻角影响下出现先增加后减小的趋势。Aiming at the influence of the structure and number of different tail fins with curved fins on the stability of small aspect ratio jamming projectiles,a three-dimensional simplified model of three tail configurations of jamming projectiles is established,which can ensure that the tail extensions of three different tail configurations can be folded to the size of the projectile diameter.In this paper,numerical simulations are conducted for three types of tail configuration jammers,with emphasis on analyzing the angle of attack atα=0°,the influence of different Mach number(Ma)changes on the aerodynamic characteristics of the interfering projectile at subsonic speed and the difference of Ma=0.5 under different attack angles on the aerodynamic characteristics of the interfering projectile have been verified,and the feasibility of the numerical calculation method used in this paper has been verified.The results show that the drag coefficient,lift coefficient,and pitch moment coefficient of the interfering projectile decrease with the increase of the number of tail fins while the total span length remains unchanged.The same number of tail fins with leading edge sweepback angles will reduce the drag coefficient,lift coefficient,rolling torque,and pitch torque coefficient of the interfering projectile.At the same time,the aerodynamic characteristics of a four wing tail with a 0°leading edge sweep angle first increase and then decrease under the influence of Ma=0.5 and different angles of attack.

关 键 词：卷弧翼 马赫数 攻角 数值模拟 气动特性 

分 类 号：TJ011.3[兵器科学与技术—兵器发射理论与技术]