Volume 31 Issue 1
Jan.  2016
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YU Chang-an, WANG Luo, HE Xian-zhong, QIU Rong-kai, YAO Cheng-wei. 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. doi: 10.13224/j.cnki.jasp.2016.01.004
Citation: YU Chang-an, WANG Luo, HE Xian-zhong, QIU Rong-kai, YAO Cheng-wei. 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. doi: 10.13224/j.cnki.jasp.2016.01.004

Design on structure of six-component box balance for the aero-engine vector nozzle measuring platform

doi: 10.13224/j.cnki.jasp.2016.01.004
  • Received Date: 2014-05-21
  • Publish Date: 2016-01-28
  • In order to meet the high precision measurement needs of aero-engine thrust vector, a compact six-component box balance enabling complete decomposition of thrust vector was developed.The balance was mainly composed of three parts: three-component sensors, fixed frame and floating frame.The elastic component of three-component sensor adopted the form of series-parallel combined structure.The simulation of the sensor's elastic component by using the finite element analysis methods showed each measuring component's sensitivity to its own component loading was much higher than other components, and the support components also preferably cut off the interference among measuring components.This conclusion was also verified by the sensor calibration.Through the stiffness and modal analysis of the six-component box balance, the results prove that the balance doesn't need elastic angle correction and the first order natural frequency of the balance is 218.8Hz, which is superior to the design index 180Hz.The six-component box balance calibration shows that the precision of the balance is lower than 3‰ and the accuracy is lower than 5‰.

     

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  • [1]
    Messina M D.Simulation model of the F/A-18 high angle-of-attack research vehicle utilized for the design of advanced control laws[R].NASA TM-110216,1996.
    [2]
    赵景云,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)
    [3]
    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)
    [4]
    王志勇,孙宝元,张军,等.对火箭发动机推力矢量测试系统的标定[J].传感器与微系统,2007,26(1):64-66. WANG Zhiyong,SUN Baoyuan,ZHANG Jun,et al.Calibration on rocket thrust vector measuring system[J].Transducer and Microsystem Technologies,2007,26(1):64-66.(in Chinese)
    [5]
    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. YANG Enxia,DIAO Yanfei,PANG Yonggang.Spraying pipe test-bed with multi-component vectors[J].Journal of Harbin Engineering University,2001,22(4):84-86.(in Chinese)
    [6]
    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.Experiment and researches in six-component balance for metal bellows expansion joints[J].Journal of Aerospace Power,2013,28(4):736-742.(in Chinese)
    [7]
    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 We,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)
    [8]
    徐铁军,李聪,刘伯均,等.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,LIU Bojun,et al.Wind tunnel research on statics thrust characteristics of vectoring nozzle[J].Journal of Experiments in Fluid Mechanics,2003,17(2):49-53.(in Chinese)
    [9]
    于常安,李平,王罗.三分量应变传感器弹性体结构设计[J].传感技术学报,2012,25(3):333-337. YU Changan,LI Ping,WANG Luo.Design of elastic component of three-component strain gauge sensor[J].Chinese Journal of Sensors and Actuators,2012,25(3):333-337.(in Chinese)
    [10]
    贺德馨.风洞天平[M].北京:国防工业出版社,1999.
    [11]
    于常安,湛华海,邱荣凯,等.一种应变式三维力传感器:中国,ZL201220737114.0[P].2012-12-28.
    [12]
    王勖成,邵敏.有限单元法基本原理与数值方法[M].北京:清华大学出版社,1988.
    [13]
    《低速风洞天平手册》编写组.低速风洞天平手册[M].北京:航空气动力协作攻关办公室,1985.
    [14]
    《风洞应变天平手册》编写组.风洞应变天平手册[M].北京:航空气动力协作攻关办公室,1983.
    [15]
    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):67-76. LUO Huayun,LAI Chuanxin,WANG Yuegui,et al.Six-component balance calibration technology for nozzle model testing facility[J].Journal of Aerospace Power,2013,28(1):67-76.(in Chinese)
    [16]
    Quade M,Hufnagel K.The development of modern manual calibration and measuring system for internal balance[R].NASA/CP-19990209101/PT2,1999.
    [17]
    陈德江,吴东,刘伟强.六分量烧蚀/滚转天平静校装置研制[J].实验流体力学,2006,20(2):68-71. CHEN Dejiang,WU Dong,LIU Weiqiang.Design of six-component ablating and rotation balance calibration system[J].Journal of Experiments in Fluid Mechanics,2006,20(2):68-71.(in Chinese)
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