Volume 35 Issue 12
Dec.  2020
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2020  >  35(12): 2521-2531
MIAO Lei, LI Yaohua, LI Jianqiang. Development of force measuring device for an aircraft thrust vectoring test[J]. Journal of Aerospace Power, 2020, 35(12): 2521-2531. doi: 10.13224/j.cnki.jasp.2020.12.006
Citation: MIAO Lei, LI Yaohua, LI Jianqiang. Development of force measuring device for an aircraft thrust vectoring test[J]. Journal of Aerospace Power, 2020, 35(12): 2521-2531. doi: 10.13224/j.cnki.jasp.2020.12.006
shu

Development of force measuring device for an aircraft thrust vectoring test

doi: 10.13224/j.cnki.jasp.2020.12.006
  • 1.

    High Speed Aerodynamics Institute,China Aerodynamics Research and ,Development Center,Mianyang Sichuan 621000,China

  • 2.

    College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

  • Received Date: 2020-05-25
  • Publish Date: 2020-12-28
    Abstract
  • For aircraft thrust vectoring test, two six-component strain-gauge balances and an air-line bridge were applied to respectively measure the performance of the whole aircraft and nozzle at the same time. Based on the finite element software, the strains of two balances and the interference of the air-line bridge on balance were analyzed. The results showed that the interference values of air-line bridge to the force components were better than 5%, and the interference values to the moment components (except for rolling moment) were better than 15%, which reached the design index. By calibration, the formulas of single balance and balance with air-line bridge (pressurized and non-pressurized states) were obtained. The calibration results showed that the comprehensive loading error of each component of the two balances was better than 0.3%, the comprehensive loading error of each component of balance with air-line bridge (pressurized and non-presswrized states) was better than 0.5%, and the interference values of air-line bridge to balance were consistent with the results of finite element analysis. Theoretical analysis and test results show that the development of balances and air-line bridge has reached the predetermined goal and its accuracy is high, which meets the requirements of the thrust vectoring wind tunnel test.

     

    • FullText(HTML)
  • loading
    • References(23)
  • [1]
    肖宇,张兴有.战斗机推力矢量控制技术的应用［J］.航空发动机,2008,34(4):56-58. XIAO Yu,ZHANG Xingyou.Application of thrust vector control technology on fighter engine［J］.Aeroengine,2008,34(4):56-58.(in Chinese)
    [2]
    YVETTE S W,DOUGLAS L B.Advancements in exhaust system technology for the 21st century［J］.AIAA 98-3100,1998.
    [3]
    THOMAS M B.Thrust vector behavior of highly integrated asymmetric nozzles for advanced fighter aircraft［R］.AIAA 98-0948,1998.
    [4]
    金镭,张曙光,孙金标.现代战斗机空战能力评估及敏感性分析［J］.北京航空航天大学学报,2009,35(1):82-86. JIN Lei,ZHANG Shuguang,SUN Jinbiao.Air-combat ability and sensitivity analysis of modern fighter aircraft［J］.Journal of Beijing University of Aeronautics and Astronautics,2009,35(1):82-86.(in Chinese)
    [5]
    BRAMAN K B,SCHWEIHARD W G,YECHOUT T R.Thrust modeling:a simplified in-flight thrust and airflow prediction technique for flight test performance measurements［J］.AIAA 83-2751,1983.
    [6]
    CROSE J,MACK T,MARX D.NASA/MFSC nozzle test bed［J］.AIAA 89-2871,1989.
    [7]
    WONGKIN C.Derivation of the data reduction equations for the calibration of the six-component thrust stand in the CE-22 advanced nozzle test facility［R］.NASA/TM-2003-212326,2003.
    [8]
    SCHNELL W C,GROSSMAN R L.Vectoring non-axisymmetric nozzle jet induced effects on a V/STOL fighter model［J］.Journal of Aircraft,1979,16(12):863-870.
    [9]
    FERRI A.Improved nozzle testing techniques in transonic flow［R］.New York：Aerospace and Energetics Laboratory AGARD-AG-208,1974.
    [10]
    PAULSON J W,WHITTEN P D,STUMPFL S C.Wind tunnel investigation of the powered low speed longitudinal aerodynamics of the vectored-engine-over (VEO) wing fighter configuration［R］.NASA Technical Memorandum 86263,1982.
    [11]
    MCWATER M A.F-35 conventional mode jet-effects testing methodology［R］.AIAA 2015-2404,2015.
    [12]
    徐铁军,李聪,曲芳亮.矢量喷管静推力特性风洞实验研究［J］.流体力学实验与测量,2003,17(2):49-53. XU Tiejun,LI Cong,QU Fangliang.Wind tunnel research on statics thrust characteristics of vectoring nozzle［J］.Experiments and Measurements in Fluid Mechanics,2003,17(2):49-53.(in Chinese)
    [13]
    高静,李聪,杨勇,等.低速风洞推力矢量试验背撑干扰特性试验研究［J］.实验流体力学,2005,19(3):10-20. GAO Jing,LI Cong,YANG Yong,et al.Researches of dorsal support interference in low speed wind tunnel thrust vector test［J］.Journal of Experiments in Fluid Mechanics,2005,19(3):10-20.(in Chinese)
    [14]
    王彤,白玉平,宋文成,等.高速喷流干扰及控制技术研究［J］.实验流体力学,2010,24(6):22-26. WANG Tong,BAI Yuping,SONG Wencheng,et al.The investigation of high-speed jet interference and control technique［J］.Journal of Experiments in Fluid Mechanics,2010,24(6):22-26.(in Chinese)
    [15]
    贾毅,郑芳,黄浩,等.低速风洞推力矢量试验技术研究［J］.实验流体力学,2014,28(6):92-97. JIA Yi,ZHENG Fang,HUANG Hao,et al.Research on vectoring thrust test technology in low-speed wind tunnel［J］.Journal of Experiments in Fluid Mechanics,2014,28(6):92-97.(in Chinese)
    [16]
    李建强,李耀华,郭旦平,等.2.4米跨声速风洞推力矢量试验技术［J］.空气动力学学报,2016,34(1):20-26. LI Jianqiang,LI Yaohua,GUO Danping,et al.The thrust vectoring experiment technique in the 2.4 m×2.4 m transonic wind tunnel［J］.Acta Aerodynamica Sinica,2016,34(1):20-26.(in Chinese)
    [17]
    苗磊,谢斌,李建强,等.2.4 m跨声速风洞推力矢量试验测力系统研制与应用［J］.实验流体力学,2017,31(6):78-85. MIAO Lei,XIE Bin,LI Jianqiang,et al.Development and application of the measurement system for thrust vectoring tests at 2.4 m×2.4 m transonic wind tunnel［J］.Journal of Experiments in Fluid Mechanics,2017,31(6):78-85.(in Chinese)
    [18]
    于常安,王罗,何显中,等.航空矢量喷管测试平台用六分量盒式天平结构设计［J］.航空动力学报,2016,31(1):23-30. YU Changan,WANG Luo,HE Xianzhong,et al.Design on structure of six-component box balance for the aero-engine vector nozzle measuring platform［J］.Journal of Aerospace Power,2016,31(1):23-30.(in Chinese)
    [19]
    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 Qiang,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)
    [20]
    汤伟,刘李涛,陈洪,等.矢量喷管推力特性的风洞试验技术［J］.航空动力学报,2018,33(4):858-864. TANG Wei,LIU Litao,CHEN Hong,et al.Thrust characteristics test technique of vectoring nozzle in wind tunnel［J］.Journal of Aerospace Power,2018,33(4):858-864.(in Chinese)
    [21]
    罗华云,侯敏杰,王月贵,等.金属波形膨胀节在六分量天平中的试验［J］.航空动力学报,2013,28(4):736-742. LUO Huayun,HOU Minjie,WANG Yuegui,et al.Experiments on metal bellows expansion joints in six-component balance［J］.Journal of Aerospace Power,2013,28(4):736-742.(in Chinese)
    [22]
    罗华云,赖传兴,王月贵,等.喷管模型试验器六分量天平校准技术［J］.航空动力学报,2013,28(1):67-73. LUO Huayun,LAI Chuanxing,WANG Yuegui,et al.Six-component balance calibration technology for nozzle model testing facility［J］.Journal of Aerospace Power,2013,28(1):67-73.(in Chinese)
    [23]
    罗华云,侯敏杰,王月贵,等.盒式六分量应变天平热态试验气动结构特性［J］.航空动力学报,2014,29(9):2024-2030.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(2472.0KB)
    XML

    Article Metrics

    Article views (362) PDF downloads(192) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return