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大膨胀比喷管试验台的六分量天平研究 被引量:3

Six-component Force Balance for Big Expansion Ratio Nozzle Test-bed
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摘要 为了研究非对称大膨胀比喷管试验台的喷管气动性能,准确地测量矢量喷管的六分量气动力,该文依据喷管试验台的测试要求,提出一种新颖的基于T型梁S弯变形的框架式整体六分量天平。通过分析天平的各元微应变与安装结构,设计并制造出天平,依据静态标定获得天平的工作系数矩阵。最后,用有限元方法验证设计结果。研究表明:天平的结构简单,精、准度高,满足试验台的六分量力测量要求。 To study the dynamic performance of a big expansion ratio nozzle with asymmetric structure,and measure the six-component dynamic force accurately for the thrust vectoring,a novel integrated six-component force balance is introduced in the paper based on S-bend deformation of T-beams.By analyzing the measuring microstrain and the assembled structure of the test-bed,the balance is designed and fabricated.The static calibration is employed to obtain the matrix of working coefficients for the balance and the finite element method is included to demonstrate the presented design method.Research result shows that the presented balance has a simple structure and high precision and accuracy,which can meet the demands of a six-component force measurement for the big expansion ratio nozzle test-beds.
作者 姚裕 吴洪涛
出处 《南京理工大学学报》 EI CAS CSCD 北大核心 2011年第4期547-551,共5页 Journal of Nanjing University of Science and Technology
基金 国家自然科学基金(50876042) 南京航空航天大学青年科技创新基金(56V1029) 江苏省数字化制造重点实验室基金(HGDML-0905)
关键词 大膨胀比 喷管试验台 六分量天平 静态标定 有限元方法 big expansion ratios nozzle test-beds six-component balances static calibration finite element method
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参考文献10

  • 1Wilson J W, Johnson W O, Sottosanti P C. Dual flex-A low horsepower flexible seal nozzle [ J ]. Journal of Spacecraft and Rockets, 1972,9 ( 8 ) :567-568. 被引量:1
  • 2Chu C W,Der J J, Ortiz V M, et al. Effect of swirl on the potential core in two-dimensional ejector nozzle [ J ]. Journal of Aircraft, 1983,20 (2) : 191 - 192. 被引量:1
  • 3Deere K A, Flamm J D, Berrier B L, et al. Computational study of an axisymmetric dual throat fluidic thrust vectoring nozzle for a supersonic aircraft application[ A]. 43rd AIAA/ASME/SAE/ASEE Joint Propul- sion Conference [ C ]. Reston, USA : American Institute of Aeronautics and Astronautics Inc,2007:918-940. 被引量:1
  • 4Liu J S, Parks G T, Clarkson P J. Shape optimisation of axisymmetric cylindrical nozzles in spherical pressure vessels subject to stress constraints [ J ]. International Journal of Pressure Vessels and Piping,2001,78:1-9. 被引量:1
  • 5张强,杨永,李喜乐.双喉道射流推力矢量喷管的数值模拟研究[J].西北工业大学学报,2009,27(6):754-759. 被引量:2
  • 6金捷,赵景芸,张明恒,赖传兴.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. 被引量:13
  • 7付尧明,王强,额日其太,仇畔祥,熊章荣.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. 被引量:15
  • 8杨恩霞,刁彦飞,庞永刚.多分力矢量喷管试验台的开发设计和研究[J].哈尔滨工程大学学报,2001,22(4):84-86. 被引量:5
  • 9Ramaswamy M A, Alvi F S, Krothapalli A. Special 6- component jet rig balance for studying new thrust vectoring concepts [ A ]. International Congress on Instrumentation in Aerospace Simulation Facilities [ C ]. Pacific Grove, CA, USA : IEEE Press, 1997:202-213. 被引量:1
  • 10贺德馨主编..风洞天平[M].北京:国防工业出版社,2001:379.

二级参考文献13

  • 1陈立周.机械优化设计方法[M].冶金工业出版社,1985.. 被引量:26
  • 2费业泰.误差理论与数据处理[M].北京:机械工业出版社,1995.. 被引量:21
  • 3杨世均.航空测试系统[M].国防工业出版社,1984.. 被引量:7
  • 4A.波普 J.J.哈珀.低速风洞实验[M].北京:国防工业出版社出版,1976,2.. 被引量:1
  • 5[美]F.K.利特儿等 钱翼稷等(译).内流空气动力学手册(第二册)[M].北京:国防工业出版社出版,1982,12.7-18. 被引量:1
  • 6Mace J,Smereczniak P, Bowers D,et al. Advanced thrust vectoring nozzles for supersonic fighter aircraft [R]. AIAA 89 - 2816. 被引量:1
  • 7Weber Yvette S, Bowers Douglas L. Advancements in exhaust system technology for the 21st century[R]. AIAA 98- 3100. 被引量:1
  • 8Capone F, Smereczniak P, Spetnagel D, et al. Comparative investigation of multiplane thrust vectoring nozzles [R].AIAA 92 - 3263. 被引量:1
  • 9Carson Geroge T, Capone Francis J. Static internal performance of an axisymmertic nozzle with mutiaxis thrustvectoring capability[R] . NASA TM 4237, 1991. 被引量:1
  • 10Orme J S, Wing D J, Anderson C J, et al. Initial flight test evaluation of the F-15 active axisymmetric vectoring nozzle performance[R]. AIAA 98 -3871. 被引量:1

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