Research progress of hinge moment test technique in hypersonic wind tunnel

XIANG Liguang; SHU Haifeng; XU Xiaobin

doi:10.11729/syltlx20210087

Volume 36 Issue 5

Oct. 2022

Turn off MathJax

Article Contents

Article Navigation > Journal of Experiments in Fluid Mechanics > 2022 > 36(5): 57-68

XIANG L G，SHU H F，XU X B. Research progress of hinge moment test technique in hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2022，36（5）：57-68. doi: 10.11729/syltlx20210087

Citation:

PDF( 12598 KB)

Research progress of hinge moment test technique in hypersonic wind tunnel

doi: 10.11729/syltlx20210087

Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang　621000, China

Received Date: 2021-08-09
Accepted Date: 2022-02-21
Rev Recd Date: 2022-02-16
Publish Date: 2022-10-01

Abstract

Abstract

Compared with hinge moment tests in the low speed and high speed wind tunnel, the hypersonic wind tunnel hinge moment test has smaller model size, larger effect of temperature and gap interporosity flow, and larger test difficulty. The research on the hypersonic hinge moment test technique is to seek the method to solve these difficulties. Since the 11^th Five-Year Plan, relevant work have been done by Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center in Ф1 m Hypersonic Wind Tunnel. The design technology of the balance and test equipment based on the vertical axis, horizontal axis and other layout modes has been developed successively. The measures to reduce the temperature effect, the rudder deflection transformation method and the balance calibration method suitable for hypersonic wind tunnel test conditions were explored, and several rounds of verification tests were carried out. Experimental results show that the developed test method, test device, balance structure, rudder deflection transformation method, and balance calibration method can meet the requirements of aerodynamics measurement of the control rudder of different hypersonic flight vehicles. The temperature effect of the balance and the effect of the gapinterporosity flow can be reduced effectively by installing the heat insulation sleeve at both ends of the balance and using the electric bridge compensation. The test technology has been successfully applied to the measurement of aerodynamic characteristics of the rudder surface in Ф1 m Hypersonic Wind Tunnel with Mach number 4–8 and total temperature of 273–740 K, and the repeatability accuracy of the hinge moment is better than 1.50%.
- hypersonic wind tunnel,
- hinge moment,
- balance,
- temperature effect,
- layout of test equipment,
- test technique

FullText(HTML)

References(28)

References

[1]	恽起麟. 实验空气动力学[M]. 北京: 国防工业出版社, 1991. YUN Q L. Experimental aerodynamics[M]. Beijing: National Defense Industry Press, 1991.
[2]	NIELSEN J, KAATTARI G E, DRAKE W. Comparison between prediction and experiment for all-movable wing and body combinations at supersonic speeds: lift, pitching moment, and hinge moment[R]. NACA-RM-A52D29, 1952.
[3]	NIELSEN J, GOODWIN F. Preliminary method for estimat-ing hinge moments of all-movable controls[R]. ADA-139726, 1982.
[4]	SMITH C A, NIELSEN J. Prediction of aerodynamic cha-racteristics of cruciform missiles to high angles of attack utilizing a distributed vortex wake[R]. AIAA 79-0024, 1979.
[5]	NIELSEN J, GOODWIN F, DILLENIUS M, et al. Pre-diction of cruciform all-movable control characteristics at transonic speeds[C]//Proc of the 22nd Aerospace Sciences Meeting. 1984. doi: 10.2514/6.1984-312
[6]	AUGUST H. Improved control surface effectiveness for missiles[C]//Proc of the 20th Aerospace Sciences Meeting. 1982. doi: 10.2514/6.1982-318
[7]	HEMSCH M J. 战术导弹空气动力学（下）[M]. 洪金森, 杨其德, 毛国良, 等译. 北京: 宇航出版社, 1999. HEMSCH M J. Tactical missile aerodynamics[M]. Trans-lated by HONG J S, YANG Q D, MAO G L, et al. Beijing: Aerospace Press, 1999.
[8]	LANDERS M G,LANDRUM D B. Hinge moment co-efficient prediction for nose-mounted canard controls at supersonic speeds[J]. Journal of Spacecraft and Rockets,1998,35(3):303-311. doi: 10.2514/2.3355
[9]	SANDERS G. A study to determine the accuracy of two computer programs in predicting hinge moments for all movable tail fins on missile bodies[R]. ADA 133399, 1983.
[10]	ALONS H J. Wind tunnel models with remote control systems with integrated hinge moment balances[C]//Proc of the 8th International Symposium on Strain-Gauge Balances. 2012.
[11]	陈丽,赵协和,刘维亮,等. 提高测量最大铰链力矩试验数据精准度的有效模拟技术研究[J]. 流体力学实验与测量,2002,16(3):51-56. CHEN L,ZHAO X H,LIU W L,et al. Simulation technique for improving data precision and accuracy of maximum hinge moment test[J]. Experiments and Measurements in Fluid Mechanics,2002,16(3):51-56.
[12]	潘华烨,王树民,苗磊,等. 高速风洞铰链力矩天平进展[J]. 弹箭与制导学报,2017,37(4):117-122. PAN H Y,WANG S M,MIAO L,et al. Development of hinge moment balance used in high speed wind tunnel[J]. Journal of Projectiles, Rockets, Missiles and Guidance,2017,37(4):117-122.
[13]	舒海峰, 向立光, 许晓斌, 等. 轴对称通气模型舵面铰链力矩测量试验装置: 中国, CN111307401A[P]. 2020-06-19. SHU H F, XIANG L G, XU X B, et al. Axisymmetric ventilation model control surface hinge moment measure-ment test device: China, CN111307401A[P]. 2020-06-19.
[14]	舒海峰, 向立光. 用于轴对称通气模型舵面气动力测量的铰链力矩天平: 中国, CN211784181U[P]. 2020-10-27. SHU H F, XIANG L G. Hinge moment balance for measuring aerodynamic force of axisymmetric ventilation model control surface: China, CN211784181U[P]. 2020-10-27.
[15]	舒海峰. 高超声速风洞铰链力矩试验技术研究[D]. 绵阳: 中国空气动力研究与发展中心, 2006.
[16]	舒海峰, 向立光, 许晓斌, 等. 一种飞行器多片减速板铰链力矩测量装置: 中国, CN211717750U[P]. 2020-10-20.
[17]	许晓斌,舒海峰,谢飞,等. 吸气式飞行器高超声速风洞气动力试验技术研究进展[J]. 实验流体力学,2018,32(5):29-40. doi: 10.11729/syltlx20180053 XU X B,SHU H F,XIE F,et al. Research progress on aerodynamic test technology of hypersonic wind tunnel for air-breathing aerocraft[J]. Journal of Experiments in Fluid Mechanics,2018,32(5):29-40. doi: 10.11729/syltlx20180053
[18]	王友循. 高超声速舵（翼）面铰链特性试验技术研究[C]//第十届全国高超声速气动力（热）学术交流会议论文集. 1999.
[19]	张尚彬, 马洪强, 岳才谦, 等. 带发动机进气道导弹的铰链力矩试验方法[C]//第一届近代实验空气动力学会议论文集. 2007.
[20]	熊琳,刘展,陈河梧. 舵面天平技术及其在高超声速风洞的应用研究[J]. 实验流体力学,2007,21(3):54-57. doi: 10.3969/j.issn.1672-9897.2007.03.011 XIONG L,LIU Z,CHEN H W. Hinge moment balance technique and application in hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2007,21(3):54-57. doi: 10.3969/j.issn.1672-9897.2007.03.011
[21]	陈河梧,刘展,熊琳. 高超声速风洞舵面测力双天平技术及应用[J]. 实验流体力学,2011,25(1):76-78. doi: 10.3969/j.issn.1672-9897.2011.01.015 CHEN H W,LIU Z,XIONG L. Double balance technology and its application on control surface force test in hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2011,25(1):76-78. doi: 10.3969/j.issn.1672-9897.2011.01.015
[22]	高胜南. 基于压电石英的舵面铰链力矩测量研究[D]. 大连: 大连理工大学, 2014. GAO S N. Measurement of control surface hinge moment with piezoelectric quartz[D]. Dalian: Dalian University of Technology, 2014.
[23]	范洁川. 风洞试验手册[M]. 北京: 航空工业出版社, 2002. FAN J C. Handbook of wind tunnel test[M]. Beijing: Aviation Industry Press, 2002.
[24]	董祥瑞,陈耀慧,董刚,等. 高超声速激波/边界层干扰及MVG阵列流动控制研究[J]. 工程力学,2016,33(7):23-30. DONG X R,CHEN Y H,DONG G,et al. Studies on hypersonic shock wave/boundary layer interactions and flow control based on mvg array[J]. Engineering Mechanics,2016,33(7):23-30.
[25]	龚安龙,解静,刘晓文,等. 近空间高超声速气动力数据天地换算研究[J]. 工程力学,2017,34(10):229-238. doi: 10.6052/j.issn.1000-4750.2016.05.0404 GONG A L,XIE J,LIU X W,et al. Study on ground-to-flight extrapolation of near space hypersonic aerodynamic data[J]. Engineering Mechanics,2017,34(10):229-238. doi: 10.6052/j.issn.1000-4750.2016.05.0404
[26]	窦怡彬,徐敏,安效民,等. 高超声速舵面颤振分析[J]. 工程力学,2009,26(11):232-237. DOU Y B,XU M,AN X M,et al. Flutter analysis for a fin in hypersonic flow[J]. Engineering Mechanics,2009,26(11):232-237.
[27]	贺德馨. 风洞天平[M]. 北京: 国防工业出版社, 2001. HE D X. Wind Tunnel Balance[M]. Beijing: National Defense Industry Press, 2001.
[28]	舒海峰,许晓斌,孙鹏. 高超声速风洞多天平测力试验技术研究[J]. 实验流体力学,2014,28(4):49-53. doi: 10.11729/syltlx20130018 SHU H F,XU X B,SUN P. Technique investigation on force test with multi-balance in hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2014,28(4):49-53. doi: 10.11729/syltlx20130018