机动式再入弹头小滚转气动力风洞试验技术

赵俊波; 梁彬; 付增良; 张石玉; 高清

doi:10.7638/kqdlxxb-2015.0037

机动式再入弹头小滚转气动力风洞试验技术

中国航天空气动力技术研究院, 北京 100074

基金项目: 国家自然科学基金项目(11402253,11302214)

详细信息

作者简介:
赵俊波(1979-),博士,高级工程师,研究方向:风洞特种试验技术研究.

通讯作者:
梁彬(1987-),博士,工程师,研究方向:风洞特种试验技术研究.

中图分类号: V211.78
计量
- 文章访问数: 267
- HTML全文浏览量: 8
- PDF下载量: 534
出版历程
- 收稿日期: 2015-03-30
- 修回日期: 2015-05-14
- 网络出版日期: 2021-01-07
- 刊出日期: 2016-01-24

Experimental technique for micro rolling aerodynamics of a maneuvering reentry body

China Academy of Aerospace Aerodynamics, Beijing 100074, China

摘要

摘要: 基于气浮轴承的自由滚转式小滚转力矩测量系统的风洞试验技术,针对传统的惯性再入武器向再入机动武器发展需求,利用多孔光栅及高灵敏度光电传感器测量带小突起(如边条,小配平翼)的非轴对称模型自由滚转状态下的角速度随时间的变化过程。采用理论验证、最小二乘拟合、动力学仿真计算等方法,建立相应滚转力矩气动力模型进行试验数据处理和分析。风洞试验结果显示,数据大小合理,规律性好,同时可获得试验模型在滚转运动中的滚转气动力随时间的变化曲线,以及任意滚转角位置的小滚转静力矩,能够满足机动式再入弹头小滚转气动力测量试验的发展需求。
- 机动式再入弹头 /
- 烧蚀 /
- 小滚转气动力 /
- 风洞试验 /
- 动力学仿真
Abstract: Micro rolling aerodynamics of a maneuvering reentry body is investigated using wind tunnel test techniques with gas bearing and grating-high sensitivity photoelectric sensor system, so as to meet the continuing developed design requirements of maneuvering reentry vehicles. The measurement system can test the change rules of rotation speed of the asymmetric models, including model with strake and model with trimming wings. According to the change of the rotation speed, the motion equation is rebuilt to simulate the asymmetric model's motions, the rolling motion equations are solved using the method of engineering estimation and numerical simulation. The micro rolling aerodynamics can be deducted and analyzed. The time courses of rolling aerodynamics and the static rolling moment at various model attitude can be obtained, and the result obtained shows rational regularity, the requirement of micro-aerodynamic measuring of maneuvering reentry body is satisfied.
- Maneuvering reentry body /
- ablation /
- micro-rolling-aerodynamics /
- wind tunnel test /
- dynamics simulation

HTML全文

参考文献(12)

[1]	Glover L S, Hagen, J C. The motion of ballistic missiles[R]. AD731662, 1971.
[2]	Fu Guangming, Feng Mingxi. Experiment for rolling aerodynamic damping of slight asymmetric re-entry body[R]. Beijing:BeijingInstitute of Aerodynamics, 1996.(in Chinese)付光明, 冯明溪. 小不对称弹头滚转气动阻尼试验[R]. 北京:北京空气动力研究所, 1996.
[3]	Jiang Zhongdong, Zhao Zhongliang, Wang Suming, et al. Research on the measurement techniques for micro rolling moment in a hypersonic wind tunne[J]. Acta Aeronautica et Astronautica Sinica, 2001, 22(6):486-490.(in Chinese)蒋忠东, 赵忠良, 王树民, 等. 高超声速风洞小滚转力矩测量技术研究[J]. 航空学报, 2001, 22(6):486-490.
[4]	Williams E P. Experimental studies of ablation surface pattern and resulting roll torques[J]. AIAA Journal, 1971, 9(7):1315-1321.
[5]	Swaim C E. Aerodynamics of re-entry vehicle with asymmetric nosetip shape change[R]. AIAA-77-782, 1977.
[6]	Bai Kui, Feng Mingxi, Fu Guangming. Experiment technique for rolling aerodynamic of slight asymmetric re-entry body[J]. Experiments and Measurements in Fluid Mechanics, 2002, 16(3):63-72.(in Chinese)白葵, 冯明溪, 付光明. 小不对称再入体滚转气动力测量技术[J]. 流体力学实验与测量, 2002, 16(3):63-72.
[7]	Ma Qiang. Aerodynamic desigh of re-entry vehicle[D]. Mianyang:China Aerodynamics Research and Development Center, 2005.(in Chinese)马强. 再入飞行器气动设计[D]. 绵阳:中国空气动力研究与发展中心, 2005.
[8]	Petsopoulos T, Regan F. A moving-mass roll control system for a fixed-trim re-entry vehicle[R]. AIAA Paper 1994-0033.
[9]	Zhang Hongjun, Chen Yingwen, Zhang Weimin. Research on aerodynamics characteristic of hypersonic high lift-drag ratio vehicle based on engineer rapid prediction method[J]. Tactical Missile Technology, 2011,(1):37-43.(in Chinese)张红军, 陈英文, 张卫民. 基于工程快速计算方法的高超声速高升阻比飞行器气动特性研究[J]. 战术导弹技术, 2011,(1):37-43.
[10]	Ling Fuhua. A numerical treatment of the periodic solutions of non-linear vibrations systems[J]. Applied Mathematics and Mechanics, 1983, 4(4):489-506.(in Chinese)凌复华. 非线性振动系统周期解的数值分析[J]. 应用数学与力学, 1983, 4(4):489-506.
[11]	Wang L W, Zhang Y, Feng J F. On the euclidean distance of images[J]. IEEE Transactions on Pattern Anaysis and Machine Intelligence, 2005, 27(8):1334-1339.
[12]	Kheir N A, Holmes W M. On validating simulation models of missile systems[J]. Simulation, 1978, 30(4):117-128.

施引文献

资源附件(0)

计量

文章访问数: 267
HTML全文浏览量: 8
PDF下载量: 534
被引次数: 0

机动式再入弹头小滚转气动力风洞试验技术

作者简介: 赵俊波(1979-),博士,高级工程师,研究方向:风洞特种试验技术研究.

通讯作者: 梁彬(1987-),博士,工程师,研究方向:风洞特种试验技术研究.

计量

出版历程

Experimental technique for micro rolling aerodynamics of a maneuvering reentry body

计量

出版历程

目录

作者简介:
赵俊波(1979-),博士,高级工程师,研究方向:风洞特种试验技术研究.

通讯作者:
梁彬(1987-),博士,工程师,研究方向:风洞特种试验技术研究.