俯仰阻尼导数分量的CFD数值模拟

席柯; 阎超; 黄宇; 王文; 袁武

doi:10.13700/j.bh.1001-5965.2014.0094

俯仰阻尼导数分量的CFD数值模拟

doi: 10.13700/j.bh.1001-5965.2014.0094

席柯¹,
阎超^1, ,,
黄宇¹,
王文¹,
袁武²

1.
北京航空航天大学航空科学与工程学院, 北京 100191
2. 中国科学院计算机网络信息中心, 北京 100190

基金项目: 国家973计划资助项目(2009CB724104)

详细信息

作者简介:
席柯(1986—), 男, 河南南阳人, 博士生, cauchy86@163.com

通讯作者:
阎超(1962—), 男, 江苏邳州人, 教授, yanchao@buaa.edu.cn, 主要研究方向为空气动力学、计算流体力学.

中图分类号: V221⁺.3
计量
- 文章访问数: 1235
- HTML全文浏览量: 81
- PDF下载量: 3417
- 被引次数: 0
出版历程
- 收稿日期: 2014-03-05
- 网络出版日期: 2015-02-20

Numerical simulation of individual components of pitch-damping coefficient sum

XI Ke¹,
YAN Chao^{1
, ,},
HUANG Yu¹,
WANG Wen¹,
YUAN Wu²

1.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2. Computer Network Information Center, Chinese Academy of Sciences, Beijing 100190, China

摘要

摘要: 提出一种直接求解直接阻尼导数的方法,该方法不仅适用于轴对称外形,也适用于非轴对称外形.数值模拟飞行器的非定常强迫沉浮运动和强迫角振动,并在Etkin的非定常气动力模型基础上,辨识得到飞行器的洗流时差导数和俯仰阻尼导数,研究飞行器俯仰通道各阻尼导数的数值计算方法.对弹道外形和基本带翼导弹标模外形及Hyflex升力体外形进行研究分析表明,将阻尼导数分量相加得到的俯仰阻尼导数与直接求解强迫角振动得到的俯仰阻尼导数与试验结果吻合很好,各阻尼导数分量随质心位置的变化趋势也与理论预测相符.对于带翼飞行器,超声速条件下,洗流时差导数在俯仰阻尼导数中占主导作用.
- 计算流体力学 /
- 数值模拟 /
- 直接阻尼导数 /
- 洗流时差导数 /
- 俯仰阻尼导数
Abstract: An approach for predicting the direct damping derivatives that formed the pitch-damping sum was presented. Application of the technique was made to the axisymmetric projectile configuration as well as the non-axisymmetric winged vehicle. The plunging derivatives and pitch-damping sum were obtained using forced heave and angular motions that excited the different angular rates under the basis of Etkin's unsteady aerodynamic model. The numerical calculation method of pitch damping derivatives was studied. The investigations of HBS and Basic Finner standard model and Hyflex show that the predicted pitch-damping coefficient sum obtained by adding the individually determined coefficients is in excellent agreement with the pitch-damping coefficient sum predicted by forced angular motions and with experimental data, and the variation of the damping derivative components with the location of gravity center is also consistent with the theoretical prediction. As for winged vehicle, the plunging derivative plays a leading role in the pitch-damping coefficient sum in the supersonic region.
- computational fluid dynamics /
- numerical simulation /
- direct damping derivative /
- plunging derivative /
- pitch-damping coefficient sum

HTML全文

参考文献(15)

[1]	李周复. 风洞特种试验技术[M].北京:航空工业出版社,2010:210-250. Li Z F.Special wind tunnel testing technology[M].Beijing:Aviation Industry Press,2010:210-250(in Chinese).
[2]	Ren Y X. Evaluation of the stability derivatives using the sensitivity equations[J].AIAA Journal,2008,46(4):912-917.
[3]	刘伟, 杨小亮,赵云飞.高超声速飞行器加速度导数数值模拟[J].空气动力学学报,2010,28(4):426-429. Liu W,Yang X L,Zhao Y F.Numerical simulation of acceleration derivative of hypersonic aircraft[J].Acta Aerodynamica Sinica,2010,28(4):426-429(in Chinese).
[4]	孙海生. 飞行器大攻角升沉平移加速度导数测量技术[J].流体力学实验与测量,2001,15(4):15-19. Sun H S.A measurement technique for derivatives of aircraft due to acceleration in heave and sideslip at high angle of attack[J].Experiments and Measurements in Fluid Mechanics,2001,15(4): 15-19(in Chinese).
[5]	Weinacht P. Navier-Stokes predictions of the individual components of the pitch-damping coefficient sum,ARL-TR-3169[R].Adelphi:Army Research Laboratory,2004.
[6]	Weinacht P. Projectile performance,stability and free flight motion prediction using computational fluid dynamics[J].Journal of Spacecraft and Rockets,2004,41(2):257-263.
[7]	Qin N, Ludlow D K,Shaw S T,et al.Calculation of pitch damping coefficients for projectiles,AIAA-1997-0405[R].Reston:AIAA,1997.
[8]	阎超. 计算流体力学方法及应用[M].北京:北京航空航天大学出版社,2006:18-25. Yan C.The methodology and application of computational fluid dynamics[M].Beijing:Beihang University Press,2006:18-25(in Chinese).
[9]	McGowan G Z, Kurzen M J,Nance R P,et al.High fidelity approaches for pitch damping prediction at high angles of attack,AIAA-2012-2903[R].Reston:AIAA,2012.
[10]	Hashimoto A, Hashizume M,Sunada S,et al.Unsteady analysis of aerodynamic derivatives on standard dynamics model,AIAA-2013-0343[R].Reston:AIAA,2013.
[11]	East R A, Hutt G R.Comparison of predictions and experimental data for hypersonic pitching motion stability[J].Journal of Spacecraft and Rockets,1988,25(3):225-233.
[12]	Uselton B L, Uselton J C.Test mechanism for measuring pitch damping derivatives of missile configurations at high angles of attack,AEDC-TR-75-43[R].Tennessee:AEDC,1975.
[13]	Uselton B L, Jenke L M.Experimental missile pitch- and roll-damping characteristics at large angles of attack[J].Journal of Spacecraft and Rockets,1977,14(4):241-247.
[14]	Murphy C H. Free flight motion of symmetric missiles,NO.1216[R].Aberdeen:Army Ballistic Research Lab,1963.
[15]	Shirouzu M, Yamamoto M.Overview of the hyflex project,AIAA-1996-4524[R].Reston:AIAA,1996.