Study on technology of using flaky hinge moment balance for high-aspect-ratio wings based on external electric bridge correction method
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摘要: 传统的大展弦比机翼片式铰链力矩天平在应用过程中存在测量精准度不高的问题。该问题由机翼受载变形引发的附加干扰信号产生。针对此现象，为提高大展弦比飞机操纵舵面铰链力矩风洞试验数据的精度与准度，探索了一种"利用一组信号修正天平信号"的外置电桥修正法，详细阐述了其工作原理以及方法步骤。以某型号风洞试验为例，通过在机翼上布置外置电桥，将修正后测量结果与未修正的测量结果进行对比。由对比结果可知：未经信号修正的天平测量误差最高达到54%，将信号修正后其测量误差降低为6%，天平测量准度有所提高。本研究为大展弦比飞机操纵舵面铰链力矩天平的应用提供新思路。Abstract: In application, the precision and accuracy of the traditional flaky hinge moment balance for the high-aspect-ratio wings are not high enough. The problem is caused by the additional interference signal resulted from the aerofoil transformation. Aiming at enhancing the hinge moment wind tunnel test data's precision and accuracy for the high-aspect-ratio plane, the External Electric Bridge Correction Method (EEBCM) is explored. It is a new type of signal correction method using a set of signals to correct other signals, and its operational principle, steps and workflow are expounded in detail. Taking a wind tunnel test as an example:the external bridge is arranged on the wing, and the measurement results are compared with those without correction. The comparison shows that without the signal correction the balance measurement error is up to 54%, after the signal correction the measurement error is reduced to 6%, and the balance measurement accuracy has been improved. The present study provides a new idea for the application of the hinge moment balance to the high aspect ratio wings.
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表 1 未经修正的某型号铰链力矩天平加载值和不确定度
Table 1. Loading loads and uncertainty for uncorrected results of the model's hinge moment balance
某型号铰链力矩天平 法向力Y/% 铰链力矩Mj/% 滚转力矩Mx/% 正升力方向 10kg 20 25 18 正升力方向 20kg 14 48 54 负升力方向 10kg 7 31 30 负升力方向 20kg 13 51 44 
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表 2 修正后的某型号铰链力矩天平加载值和不确定度
Table 2. Loading loads and uncertainty for corrected results of the model's hinge moment balance
某型号铰链力矩天平 法向力Y/% 铰链力矩Mj/% 滚转力矩Mx/% 正升力方向 10kg 0.7 1 5 正升力方向 20kg 1 0.2 5 负升力方向 10kg 1.5 0.9 6 负升力方向 20kg 1.5 2 5
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[1] 王发祥.高速风洞试验[M].北京:国防工业出版社, 2003. [2] 李周复.风洞特种试验技术[M].北京:航空工业出版社, 2010. [3] 张书浚, 王运涛.大展弦比联接翼静气动弹性研究[J].空气动力学学报, 2013, 31(2):170-174. doi: 10.7638/kqdlxxb-2011.0178Zhang S J, Wang Y T. Study on static aeroelasticity for high aspect ratio joined-wings[J]. Acta Aerodynamica Sinica, 2013, 31(2):170-174. doi: 10.7638/kqdlxxb-2011.0178 [4] 熊琳, 刘展, 陈河梧.舵面天平技术及其在高超声速风洞的应用研究[J].实验流体力学, 2007, 21(3):55-57. http://www.syltlx.com/CN/abstract/abstract9569.shtmlXiong L, Liu Z, Chen H W. Hinge moment balance technique and application in hypersonic wind tunnel[J]. Journal of Experments in Fluid Mechanics, 2007, 21(3):55-57. http://www.syltlx.com/CN/abstract/abstract9569.shtml [5] 白静, 解亚军.风洞翼型天平校准技术[J].弹箭与制导学报, 2011, 31(6):169-172. http://www.cnki.com.cn/Article/CJFDTOTAL-DJZD201106052.htm [6] 贺德馨.风洞天平[M].北京:国防工业出版社, 2001. [7] 苏翼林.材料力学[M].北京:高等教育出版社, 1986. [8] 刘维亮, 贾巍. 某型号无人飞机舵面铰链力矩风洞试验天平设计图[R]. CARDC-2, 2010. [9] 国防科工委. 风洞应变天平规范(GJB2244A)[S]. 国防科工委军标部, 2011. -
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