非旋转钝锥高超声速双平面拍摄风洞自由飞试验

蒋增辉; 宋威; 陈农

doi:10.6052/0459-1879-14-332

非旋转钝锥高超声速双平面拍摄风洞自由飞试验

中国航天空气动力技术研究院, 北京100074

基金项目: 国家自然科学基金资助项目(11202200).

详细信息

通讯作者:
蒋增辉,高级工程师,研究方向:非定常空气动力学、超空泡流体动力学.E-mail:jzhhit@163.com

中图分类号: V211.7;V212.1
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出版历程
- 收稿日期: 2014-10-22
- 修回日期: 2015-02-04
- 刊出日期: 2015-05-17

HYPERSONIC WIND TUNNEL FREE-FLIGHT TEST WITH BIPLANAR OPTICAL SYSTEM ON THE NON-SPINNING BLUNT CONE

China Academy of Aerospace Aerodynamics, Beijing 100074, China

Funds: The project was supported by the National Natural Science Foundation of China (11202200).

摘要

摘要: 在高超声速下(6 马赫) 开展了双平面拍摄风洞自由飞试验,对非旋转钝锥在小攻角下的运动特性和圆锥摆动问题进行了研究. 试验结果表明,虽然只预置了攻角而无侧滑角,模型仍然全部出现了圆锥摆动,且在观察窗范围内侧滑角幅值均大于攻角幅值. 模型角运动虽均处于小于10° 的小攻角和小侧滑角状态,但阻尼力矩项呈现较为明显的非线性,而静力矩项的非线性较弱,近似为线性. 5 组实验中,有1 组模型的角运动可能趋于极限平面运动或者是攻角幅值较小的极限圆锥运动,另外4 组试验模型角运动显示出了趋于极限圆锥运动的趋势. 尾端盖对模型的角运动影响不明显,而尾部对称布置的片条状凸起物对整个角运动幅值变化的稳定性存在明显影响,有凸起物的两组模型角运动幅值波动明显较小.
- 风洞自由飞试验 /
- 双平面拍摄 /
- 极限圆锥运动 /
- 极限平面运动 /
- 高超声速
Abstract: To investigate the dynamic stability of the non-spinning blunt cone, wind-tunnel free-flight tests with biplanar optical system, were conducted at Mach 6 in the hypersonic wind tunnel. The tests show that coning motion appears for all the models,and in the range of viewing area the amplitude of angle of sideslip is larger than that of angle of attack, though only angle of attack is preset. For all the models, the amplitude of both angles of attack and sideslip is no more than 10 degree, while damping moment shows obvious nonlinearity and static moment exhibits approximate linearity. One of the models shows the tendency of limit planar motion or limit coning motion with small amplitude of angle of attack, others all tend to limit coning motion. End cover has little effect on the angular motion of the models, while the protuberance symmetrically placed on the model tail can affect the transformation of amplitude of angular motion, and the fluctuation of angular motion amplitude is obviously smaller for models with strake.
- wind tunnel free-flight test /
- biplanar optical system /
- limit coning motion /
- limit planar motion /
- hypersonic

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参考文献(22)

Lewis HO, East RA. Measurement of free-flight dynamic stability derivatives of cones in a hypersonic gun tunnel. AIAA No.95-6082, 1995

马家驩, 唐宗衡, 张小平等. 激波管风洞中锥模型静、动稳定性导数的测量. 力学学报,1980,16(1): 84-89 (Ma Jiahuan, Tang Zongheng, Zhang Xiaoping, et al. The measurements of the static and dynamic stability derivatives of conical models in the shock tunnel. Acta Mechanica Sinica, 1980, 16(1): 84-89 (in Chinese))

Prislin RH. High-amplitude dynamic-stability characteristics of blunt 10-degree cones. In: Proc. of AIAA 4th Aerospace Sciences Metting, 66-465, 1966

Nicolaides JD, Ingram CW, Clare TA. An investigation of the non-linear flight dynamics of ordnance weapons. AIAA No. 69-135, 1969

Ingram CW, Nicolaides JD. Obtaining nonlinear aerodynamic stability coefficients from free-angular motion of rigid bodies. J Spacecraft, 1969, 8(4): 390-395

Nicolaides JD, Ingram CW, Martin JM. Nonlinear aerodynamic stability characteristics of the 2.75 wrap-around fin configuration. In: Proc. of 8th Navy Symposium on Aeroballistics, 1969, 3: 751-832

Nicolaides JD, Eikenberry RS, Ingram CW, et al. Flight dynamics of the basic finner in various degrees of freedom. AFATL-TR-68-32, 1968

许可法, 何龙德, 李明娟等. 大攻角风洞自由飞动导数实验研究. 航空学报, 1993,14(8): B394-B397 (Xu Kefa, He Longde, Li Mingjuan, et al. Experimental investigation of dynamic stability derivatives at high angle of attack in wind tunnel free-flight. Acta Aeronautica et Astronautica Sinica, 1993, 14(8): B394-B397 (in Chinese))

Wey P, Seiler F, Srulijes J, et al. Determination of aerodynamic coefficients from shock tunnel free flight trajectories. AIAA2012-3321, 2012

Tanno H, Komuro T, Sato K, et al. Free-flight tests of reentry capsule models in free-piston shock tunnel. AIAA2013-2979, 2013

Prislin RH, Holway HP. A wind tunnel free flight testing technique for nonplanar motion of spinning models. AIAA66-774

Jaffe P. Nonplanar tests using the wind-tunnel free-flight technique. J Spacecraft, 1973, 10(7): 435-442

许可法, 王陵志, 李明娟等. 旋转导弹风洞六自由度自由飞动导数实验研究. 空气动力学学报, 1993, 11(3): 257-262 (Xu Kefa, Wang Lingzhi, Li Mingjuan, et al. Research on dynamic derivative of Spinning missile by six-degree-of-freedom free-flight test in wind tunnel. Acta Aerodynamica Sinica, 1993, 11(3): 257-262 (in Chinese))

蒋增辉,陈农. 旋转钝锥双平面拍摄风洞自由飞试验. 力学学报, 2013,45(5): 777-781 (Jiang Zenghui, Chen Nong. Wind tunnel free-flight test with biplanar optical system on the spinning blunt cone. Chinese Journal of Theoretical and Applied Mechanics, 2013, 45(5): 777-781 (in Chinese))

马家驩, 李江, 潘文欣等. 有翼飞行器高超声速动导数的风洞自由飞测量.流体力学实验与测量, 2001, 15(4): 70-76 (Ma Jiahuan, Li Jiang, Pan Wenxin, et al. Hypersonic pitching damp measurements for a winged vehicle by model free flight. Experiments and Measurements in Fluid Mechanics, 2001, 15(4): 70-76 (in Chinese))

李江, 马家驩, 潘文欣等. 两种有翼飞行器高超声速动态气动特性的对比实验研究. 空气动力学学报, 2001, 19(2): 217-222 (Li Jiang, Ma Jiahuan, Pan Wenxin, et al. Comparative experiments of two kinds of space shuttle like model for hypersonic pitching damp by model free flight technology. Acta Aerodynamica Sinica, 2001, 19(2): 217-222 (in Chinese))

韩子鹏. 弹箭外弹道学. 北京:北京理工大学出版社, 2008: 302-307 (Han Zipeng. Exterior Ballistics of Projectiles and Rockets. Beijing: Beijing Institute of Technology Press, 2008: 302-307 (in Chinese))

李臣明, 刘怡昕. 非对称赤道阻尼力矩对远程火箭弹道的影响. 弹道学报, 2009, 21(2): 36-39 (Li Chenming, Liu Yixin. Influence of unsymmetrical equatorial damp moment on long-range rockets trajectory. Journal of Ballistics, 2009, 21(2): 36-39 (in Chinese))

Eikenbery RS. Analysis of the angular motion of missiles. SC-CR-70-6051,1970

李周复. 风洞特种试验技术. 北京:航空工业出版社, 2010: 328-368 (Li Zhoufu. Wind Tunnel Special Tests Technique. Beijing: Aviation Industry Press, 2010: 328-368 (in Chinese))

李臣明, 刘怡昕. 大长径比远程弹箭的极限平面摆动及其抑制. 系统仿真学报, 2009, 21(23): 7390-7396 (Li Chenming, Liu Yixin. Limit plane swing motion and its restraining measure of un-rotary long-range missile with large ratio of length to diameter. Journal of System Simulation, 2009, 21(23): 7390-7396 (in Chinese))

邓超. 弹箭非线性角运动规律研究. [硕士论文]. 南京:南京理工大学,2013. (Deng Chao. Research about the regular pattern of nonlinear angualar movement of projectile. [Master Thesis]. Nanjing: Nanjing University of Science & Technology, 2013 (in Chinese))