[1]胡志鹏,刘荣忠,郭锐.两种典型尾翼形状对无伞末敏弹气动特性的影响[J].南京理工大学学报(自然科学版),2012,36(05):739.
 HU Zhi-peng,LIU Rong-zhong,GUO Rui.Effect of Two-tipical Wing Shapes on Aerodynamic Characteristics ofNon-parachute Terminal-sensitive Projectile[J].Journal of Nanjing University of Science and Technology,2012,36(05):739.
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两种典型尾翼形状对无伞末敏弹气动特性的影响
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《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

卷:
36卷
期数:
2012年05期
页码:
739
栏目:
出版日期:
2012-10-31

文章信息/Info

Title:
Effect of Two-tipical Wing Shapes on Aerodynamic Characteristics ofNon-parachute Terminal-sensitive Projectile
作者:
胡志鹏刘荣忠郭锐
南京理工大学机械工程学院,江苏南京210094
Author(s):
HU Zhi-pengLIU Rong-zhongGUO Rui
School of Mechanical Engineering,NUST,Nanjing 210094,China
关键词:
气动特性无伞末敏弹尾翼形状稳态扫描计算流体力学
Keywords:
aerodynamic characteristicsnon-parachute terminal-sensitive projectileswing shapessteady scanningcomputational fluid dynamics
分类号:
TJ011
摘要:
为研究尾翼形状对双翼无伞末敏弹减速导旋性能的影响,分别对平板尾翼和S-C 形尾翼结构末敏弹的气动特性进行研究。基于计算流体力学方法,获得了末敏弹气动外形的流场特性、表面压力分布和阻力系数、升力系数和转动力矩系数随攻角变化的规律。通过自由飞行试验对平板尾翼和S-C 尾翼末敏弹进行了动态气动特性研究。数值计算结果显示,平板尾翼和S-C 尾翼模型阻力系数在6 ~9 间,其增阻效果明显;两模型升力系数均呈负线性变化,尾翼形状对升力系数影响较小;尾翼形状对转动力矩系数影响明显,平板尾翼几无转动力矩产生,S-C 尾翼转动力矩相对较大并随攻角增加而减小。自由飞行试验表明,S-C 尾翼结构自由飞行状态下增阻效果好于平板尾翼,并可使弹体获得转动力矩而维持稳定转速,能够实现稳态扫描运动。平板尾翼末敏弹自由飞行稳定性差。
Abstract:
To get the effect of wing shapes on the decelerating and spinning performances of double-wing non-parachute terminal-sensitive projectiles, the aerodynamic characteristics of terminal-sensitive projectiles with flat wings and S-C wings are studied here. Based on the computational fluiddynamics method,the flow field characteristics of aerodynamic shapes of two-wing terminal-sensitiveprojectiles and their surface pressure distribution are obtained, and the change laws of dragcoefficients,lift coefficients and torque moment coefficients versus attack angles are calculated. Thedynamic aerodynamic characteristics of terminal-sensitive projectiles with two-shape wings areresearched by free flight tests. Numerical results show that,when the drag coefficients are 6 ~9,thesetwo-tipical wing shapes have the obvious deceleration effects. The lift coefficients of two models arenegative linear versus attack angles, and wing shapes have weak effects on lift coefficient butsignificant effects on torque coefficients. Flat wings bring no torque moments,and the torque moment is big for the S-C wings and it decreases with the increase of the attack angle. Test results show that,under the free flight condition,the S-C wing model has the better deceleration effect than the flatwing model and it can maintain stable spin velocity and realize the steady scanning motion. The flatwing model shows worse free flight stability.

参考文献/References:

[1]Borgstrom D,Paulsson L,Karlsen L. Aerodynamics of arotating body descending from the separation position ofan artillery munition shell [ R]. AIAA - 91 - 0870 -CP,1991.
[2] Dashcund D. IRAAM wind tunnel test task Ⅲ[ R].New Jersey, USA: Avco Corporation Avco SystemsDivision,1983.
[3] Koenig W,Kline R. A samara-type decelerator[ R].AIAA-84-0807,1984.
[4] Crimi P. Finite element analysis of a samara-wingdecelerator[J].Journal of Aircraft,1996,33(4):793-802.
[5] Crimi P. Analysis of samara-wing decelerator steady-state characteristics[J]. Journal of Aircraft,1988,25:41-47.
[6] 舒敬荣. 非对称末敏子弹大攻角扫描特性研究及应用[D]. 南京:南京理工大学动力工程学院,2004
[7] Vicente N M, Angel S A, Alvaro C. Experimentalinvestigation of an autorotating-wing aerodynamicdecelerator system [ A ]. 18th AIAA AerodynamicDecelerator Systems Technology Conference andSeminar[C]. Munich,Alemania:AIAA,2005.
[8] Vicente N M, Piechocki J, Cuerva A, et al.Experimental research on a vertically falling rotatingwing decelerator model[ A]. 19th AIAA AerodynamicDecelerator Systems Technology Conference andSeminar[C]. Williamsburg,VA:AIAA,2007.
[9] Vicente N M, Angel S A, Alvaro C. Model of theaerodynamic behavior of a pararotor [ J]. Journal ofAircraft,2006,43(6):1-15.
[10] 周志超,赵润祥. 不同尾翼灵巧子弹气动特性实验研究[J]. 实验流体力学,2010,24(4):52-55.Zhou Zhichao,Zhao Runxiang. Experimental investigationon aerodynamic characteristics of smart submunitions withdifferent tail fins[J]. Journal of Experiments in Fluid Me-chanics,2010,24(4):52-55.
[11] 任玉新,陈海昕. 计算流体力学基础[ M]. 北京:清华大学出版社,2006.

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备注/Memo

备注/Memo:
收稿日期:2011-12-21修回日期:2012-06-30基金项目:国家自然科学基金(11102088)作者简介:胡志鹏(1983-),男,博士生,主要研究方向:弹药精确化与智能化,E-mail:huzhp@139. com;通讯作者:刘荣忠(1954-),男,教授,博士生导师,主要研究方向:弹药精确化与智能化,E-mail:liurongz116@163. com。
更新日期/Last Update: 2012-11-26