喷管模型试验器六分量天平校准技术

罗华云; 赖传兴; 王月贵; 叶巍

喷管模型试验器六分量天平校准技术

中国航空工业集团公司中国燃气涡轮研究院,四川江油 621703

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出版历程
- 收稿日期: 2011-12-28
- 刊出日期: 2013-01-28

Six-component balance calibration technology for nozzle model testing facility

China Gas Turbine Establishment, Aviation Industry Corporation of China,Jiangyou Sichuan 621703,China

摘要

摘要: 为了提高喷管内流试验台六分量测力天平的静态和动态校准的精度和准度,采用了理论计算与标模试验相结合的方法,开展了天平校准技术研究.对静校的原始数据进行1次项与3次项对比分析,得出了天平在安装、调试阶段的经验模型,重复性标模试验表明完善的数据处理方法可以极大地提高天平动校精度和准度,试验结果与四分量天平比较,证明了天平性能的可靠性以及以喷管落压比为基准修正测力系统附加力、附加力矩的正确性.该六分量天平校准方法可对其他多分量测力系统的校准提供参考.
- 喷管模型试验器 /
- 内流 /
- 六分量天平 /
- 天平校准 /
- 喷管落压比 /
- 修正
Abstract: The balance calibration technology was developed with the method that theoretical computation was associated with model test in order to improve precision and accuracy of static and dynamic calibrations of six-component force-measuring balance for nozzle internal flow model testing facility.The original data of static calibration were processed by the method in which once quantic was compared to thrice quantic and the experiential model was obtained on phases of balance installation and test.The repeatability test indicates that precision and accuracy of dynamic calibration can be enhanced greatly with perfect method for data processing.The credibility of balance performance and correctness of correcting test data including added-force and added-moment of force-measuring system with the nozzle pressure ratio (NPR) were validated by being compared to the results of dynamic calibration for four-component balance.The method of six-component force-measuring balance calibration offers references for other multi-component force-measuring system calibrations.
- nozzle model testing facility /
- internal flow /
- six-component balance /
- balance calibration /
- nozzle pressure ratio(NPR) /
- correction

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参考文献(15)

[1]	赵景芸,金捷.推力矢量技术的研究与发展[J].燃气涡轮试验与研究,1999,12(1):51-54. ZHAO Jingyun,JIN Jie.Development and investingation of thrust-vectoring technology[J].Gas Turbine Experiment and Research,1999,12(1):51-54.(in Chinese)
[2]	Miller D N,Catt J A.Conceptual development of fixed-geometry nozzles using fluidic injection for throat area control .AIAA 95-2603,1995.
[3]	金捷,赵景芸,张明恒,等.轴对称矢量喷管内流特性的模型试验[J].推进技术,2005,26(2):144-146. JIN Jie,ZHAO Jingyun,ZHANG Mingheng,et al.Exp-erimental investigation of static internal performance for an axisymmetric vectoring thrust nozzle[J].Journal of Propulsion Technology,2005,26(2):144-146.(in Chinese)
[4]	金捷,雷金春,廖华琳,等.激波诱导轴对称气动矢量喷管壁面静压分布的试验[J].航空动力学报,2007,22(10):1700-1703. JIN Jie,LEI Jinchun,LIAO Hualin,et al.Experimental investigation of wall static pressure distributions of shock induced axisymmetric fluidic vectoring nozzle[J].Journal of Aerospace Power,2007,22(10):1700-1703.(in Chinese)
[5]	付尧明,王强,额日其太,等.矢量喷管六分量测力试验台的研制[J].流体力学实验与测量,2002,16(1):87-93. FU Yaoming,WANG Qing,ERIQITAI,et al.Development of the six-component force-measuring balance for thrust-vectoring nozzle testing[J].Experiments and Measurements in Fluid Mechanics,2002,16(1):87-93.(in Chinese)
[6]	姚裕,张召明.整体式盒式应变天平有限元设计[J].南京航空航天大学学报,2010,42(1):58-61. YAO Yu,ZHANG Zhaoming.Finite element design on integrated box balance[J].Journal of Nanjing University of Aeronautics and Astronautics,2010,42(1):58-61.(in Chinese)
[7]	程厚梅,张其威,田学诗,等.风洞实验干扰与修正[M].北京:国防工业出版社,2003.
[8]	陈德华,尹陆平,吴文华,等.2.4米跨声速风洞大展弦比飞机测力试验技术研究[J].空气动力学学报,2009,27(5):542-546. CHEN Dehua,YIN Luping,WU Wenhua,et al.The test technique for aircraft with high aspect ratio in the 2.4 meter transonic wind tunnel[J].Acta Aerodynamica Sinica,2009,27(5):542-546.(in Chinese)
[9]	贺伟,童泽润,李宏斌.单模块超燃发动机推力测量天平研制[J].航空动力学报,2010,25(10):2285-2289. HE Wei,TONG Zerun,LI Hongbin.Investigation of thrust balance for the single module scramjet[J].Journal of Aerospace Power,2010,25(10):2285-2289.(in Chinese)
[10]	贺德馨.风洞天平[M].北京:国防工业出版社,2001.
[11]	王铁城.空气动力学实验技术[M].修订版.北京:航空工业出版社,2003.
[12]	恽起麟.风洞实验数据的误差与修正[M].北京:国防工业出版社,1996.
[13]	Greathouse W K,Beale W T.Performance characteristics of several divergent shroud ejectors .NACA RM E55G21a,1955.
[14]	Little F K.Internal aerodynamics manual[M].Fort Belvoir:Defense Technical Information Center,1968.
[15]	潘锦珊,方人淞,邢宋文,等.气体动力学基础 [M].修订版.北京:国防工业出版社,1989.