基于Fluent的尾翼弹滚转阻尼特性数值研究  

Numerical Simulation on Roll-Damping Characteristics of Fin-Stabilized Projectile Based on Fluent

作　　者：叶军雄 李强[1] 岳通 蔡涛 YE Junxiong;LI Qiang;YUE Tong;CAI Tao(North University of China, Taiyuan 030051, China)

机构地区：[1]中北大学,太原030051

出　　处：《兵器装备工程学报》2020年第5期43-47,共5页Journal of Ordnance Equipment Engineering

基　　金：中北大学第十五届研究生科技立项项目(20181880)。

摘　　要：为了研究某尾翼弹滚转阻尼特性随不同马赫数、转速、攻角的变化规律,采用基于多参考系模型的计算方法,利用Fluent软件对不同马赫数、转速、攻角下尾翼弹的滚转阻尼特性进行了数值模拟,获得了该弹的滚转阻尼力矩系数曲线。计算结果表明:在全声速段,滚转阻尼力矩系数随着马赫数的增加而降低,随着转速的增加而升高且基本满足线性关系;在亚音速段,滚转阻尼力矩系数随着攻角的增加而增加;在超音速段,滚转阻尼力矩系数随着攻角的增加而降低,并用流场特性分析了其形成原因。To study the roll-damping laws of fin-stabilized projectile under different Mach numbers,rotating velocity,angle of attack,the multi-reference frame model method to calculate the roll-damping characteristics of fin-stabilized projectile under different Mach numbers,rotating velocity,angle of attack was used and the roll-damping moment coefficient were obtained.Matlab was used to fit results of numerical simulation and the rolling damping derivative were given.The results show that rolling damping moment coefficient decrease with the increase of mach number,increase with the increase of rotating velocity and are all in the linearity rule at the same angle of attack.At the subsonic flight regimes,rolling damping moment coefficient increase with the increase of angle of attack,and decrease with the increase of angle of attack at the supersonic flight regime and the causes of the above changes were analyzed with the flow field character.

关 键 词：尾翼弹 攻角 滚转阻尼力矩系数 

分 类 号：TJ011[兵器科学与技术—兵器发射理论与技术]