|Table of Contents|

Effect of Two-tipical Wing Shapes on Aerodynamic Characteristics ofNon-parachute Terminal-sensitive Projectile

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

Issue:
2012年05期
Page:
739-
Research Field:
Publishing date:

Info

Title:
Effect of Two-tipical Wing Shapes on Aerodynamic Characteristics ofNon-parachute Terminal-sensitive Projectile
Author(s):
HU Zhi-pengLIU Rong-zhongGUO Rui
School of Mechanical Engineering,NUST,Nanjing 210094,China
Keywords:
aerodynamic characteristicsnon-parachute terminal-sensitive projectileswing shapessteady scanningcomputational fluid dynamics
PACS:
TJ011
DOI:
-
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.

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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Last Update: 2012-11-26