Development and application of the force-measuring balance in impulse combustion wind tunnel tests

He Wei; Gao Chang; Zhang Xiaoqing; Yu Shien

doi:10.11729/syltlx20160011

Volume 30 Issue 4

Turn off MathJax

Article Contents

Article Navigation > Journal of Experiments in Fluid Mechanics > 2016 > 30(4): 66-70

He Wei, Gao Chang, Zhang Xiaoqing, et al. Development and application of the force-measuring balance in impulse combustion wind tunnel tests[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(4): 66-70. doi: 10.11729/syltlx20160011

Citation:

PDF( 4815 KB)

Development and application of the force-measuring balance in impulse combustion wind tunnel tests

doi: 10.11729/syltlx20160011

He Wei^1
,,
Gao Chang^{1
,
,},
Zhang Xiaoqing²,
Yu Shien²

1.
Science and Technology on Scramjet Laboratory, Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China
2.
Air-breathing Hypersonic Technology Research Center, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2016-01-08
Rev Recd Date: 2016-04-26
Publish Date: 2016-08-25

Abstract

Abstract

A design scheme of strutting internal six-component strain gage balance is developed to meet the requirements of aerodynamic load tests for big-weight hypersonic models under cold and hot conditions in the impulse combustion wind tunnel. The fast-response ability of balances is crucial in hypersonic force-measuring tests because of short test duration, serious impulsive load and big model weight. The mutually exclusive stiffness and sensitivity are coordinated. The balance is qualified according to static calibration results. Demonstrated by the test results, the consistency between the output signal of the balance and the combustor pressure is good, which indicates that the balance accurately reflects the aerodynamic loads of the model. Stability of the balance is confirmed by the axial force coefficient precision of 1.6% in the repeated calibration tests, and the eigen frequencies of the axial force, normal force and pitch moment signal satisfy the criteria in impulse wind tunnel tests. In conclusion, the balance has met the requirements of aerodynamic load tests of hypersonic vehicle models in impulse combustion wind tunnels.
- strain gage balance,
- impulse combustion wind tunnel,
- fast-response

FullText(HTML)

References(13)

References

[1]	Holland S D, Woods W C, Engelund W C. Hyper-X research vehicle experimental aerodynamics test program overview[J]. Journal of Spacecraft and Rockets, 2001, 38(6): 828-835. doi: 10.2514/2.3772
[2]	Hank J M, Murphy J S, Mutzman R C. The X-51A scramjet engine flight demonstration program[C]. 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Dayton, Ohio, 2008. AIAA-2008-2540. http://cn.bing.com/academic/profile?id=26152275&encoded=0&v=paper_preview&mkt=zh-cn
[3]	吴颖川, 贺元元, 贺伟, 等. 吸气式高超声速飞行器机体推进一体化技术研究进展[J]. 航空学报, 2015, 36(1): 245-260. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201501019.htm Wu Y C, He Y Y, He Wei, et al. Progress in airframe-propulsion integration technology of air-breathing hypersonic vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1): 245-260. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201501019.htm
[4]	贺元元, 乐嘉陵, 倪鸿礼. 吸气式高超声速机体-推进一体化飞行器数值和试验研究[J]. 实验流体力学, 2007, 21(2): 29-34. http://www.syltlx.com/CN/abstract/abstract9860.shtml He Y Y, Le J L, Ni H L. Evaluation of aero-propulsive performance for integrated hypersonic vehicle[J]. Journal of Experiments in Fluid Mechanics, 2007, 21(2): 29-34. http://www.syltlx.com/CN/abstract/abstract9860.shtml
[5]	Guy R W, Rogers R C, Puster R L, et al. The NASA Langley Scramjet Test Complex[R]. AIAA-1996-3243, 1996. doi: 10.1007/s00193-015-0605-0/fulltext.html
[6]	乐嘉陵, 刘伟雄, 贺伟, 等. 脉冲燃烧风洞及其在火箭和超燃发动机研究中的应用[J]. 实验流体力学, 2005, 19(1): 1-10. http://www.syltlx.com/CN/abstract/abstract9335.shtml Le J L, Liu W X, He W, et al. Impulse combustion wind tunnel and its application in rocket and scramjet research[J]. Journal of Experiments in Fluid Mechanics, 2005, 19(1): 1-10. http://www.syltlx.com/CN/abstract/abstract9335.shtml
[7]	Le J L, Liu W X, Yu G. Recent progress of our scramjet research [C]//ISABE2005-1009, 17th International Symposium on Airbreathing Engines, Munich, Germany, 2005.
[8]	刘伟雄, 谭宇, 毛雄兵, 等. 一种新运行方式脉冲燃烧风洞研制及初步应用[J]. 实验流体力学, 2007, 21(4): 59-64. http://www.syltlx.com/CN/abstract/abstract9590.shtml Liu W X, Tan Y, Mao X B, et al. The development and preliminary application of a pulse combustion wind tunnel with new running way[J]. Journal of Experiments in Fluid Mechanics, 2007, 21(4): 59-64. http://www.syltlx.com/CN/abstract/abstract9590.shtml
[9]	乐嘉陵. 吸气式高超声速技术研究进展[J]. 推进技术, 2010, 31(6): 641-649. http://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201006002.htm Le J L. Progress in air-breathing hypersonic technology [J]. Journal of Propulsion Technology, 2010, 31(6): 641-649. http://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201006002.htm
[10]	中国人民解放军总装备部. GJB2244A-2011风洞应变天平规范[S]. 北京: 总装备部军标出版发行部, 2011.
[11]	费叶泰. 误差理论与数据处理[M]. 第4版. 北京: 机械工业出版社, 2000: 211-217.
[12]	吕金洲, 张小庆, 高宏力, 等. 脉冲燃烧风洞测力天平动力学建模与分析[J]. 噪声与振动控制, 2015, 35(1): 182-186. http://www.cnki.com.cn/Article/CJFDTOTAL-ZSZK201501039.htm Lvy J Z, Zhang X Q, Gao H L, et al. Structural dynamics modeling and analysis of the force balance for an impulse combustion wind tunnel[J]. Noise and Vibration Control, 2015, 35(1): 182-186. http://www.cnki.com.cn/Article/CJFDTOTAL-ZSZK201501039.htm
[13]	王玉花, 孙良, 郑粤蓉. 高超声速风洞大轴向力中温天平的研制[J]. 实验流体力学, 2006, 20(1): 86-90. http://www.syltlx.com/CN/abstract/abstract9443.shtml Wang Y H, Sun L, Zheng Y R. The development of the larger axial force intermediate temperature balance in the hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2006, 20(1): 86-90. http://www.syltlx.com/CN/abstract/abstract9443.shtml