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浙江大学学报(工学版)
Journal of ZheJiang University (Engineering Science)  2024, Vol. 58 Issue (3): 635-645    DOI: 10.3785/j.issn.1008-973X.2024.03.020
    
Measurement of movable wing surface deflection based on wireless inclination sensor
Peiqi ZHANG1(),Bofeng LIU2,Mingqi CUI1,Zheng HU2,Qing WANG1,*()
1. Key Laboratory of Advanced Manufacturing Technology of Zhejiang Province, School of Mechanical Engineering, Zhejiang University, Hangzhou 310027, China
2. Xi’an Aircraft Industrial (Group) Co. Ltd, Xi’an 710089, China
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Abstract  

The dual measurement axis spatial rotation model was deduced and improved, by referring to the existing spatial angle measurement models and considering the system error of the aircraft testing site, based on the analysis of the underlying measurement principle of the inclination sensor. The purpose was to resolve the problems during the movable wing surface deflection test, such as high installation parallelism requirement, long cables and complex manual operations, so as to improve the measurement accuracy and the test efficiency. A spatial angle measurement error model around the horizontal axis and a calibration method for inclination sensor were proposed, to meet the requirement for the deflection testing. A large aircraft movable wing surface deflection testing system based on wireless inclination sensors was designed and implemented, capitalizing on this model and the calibration method. Results of the rotation angle accuracy testing on the experimental platform and the on-site testing on the movable wing surface show that, compared with the existing methods, the proposed calibration method can obtain a larger effective measurement range to meet the actual working conditions, improve the angle calibration accuracy, and significantly improve the testing efficiency.

Key words： movable wing surface      angle measurement      inclination sensor      calibration algorithm      deflection test     
Received: 30 March 2023      Published: 05 March 2024
CLC:  V 262.4  
Fund:  国家重点研发计划资助项目（2019YFB1707504）.
Corresponding Authors: Qing WANG     E-mail: 22125032@zju.edu.cn;wqing@zju.edu.cn
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Peiqi ZHANG
Bofeng LIU
Mingqi CUI
Zheng HU
Qing WANG
Cite this article:

Peiqi ZHANG,Bofeng LIU,Mingqi CUI,Zheng HU,Qing WANG. Measurement of movable wing surface deflection based on wireless inclination sensor. Journal of ZheJiang University (Engineering Science), 2024, 58(3): 635-645.

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https://www.zjujournals.com/eng/10.3785/j.issn.1008-973X.2024.03.020     OR     https://www.zjujournals.com/eng/Y2024/V58/I3/635


基于无线倾角传感器的活动翼面偏转测试

为了解决传统活动翼面偏转测试中传感器安装平行度要求高、线缆长、人工操作复杂繁琐等问题，提高空间角度测量准确性和现场测试效率，在分析倾角传感器底层测量原理的基础上，综合考虑飞机测试现场系统误差，参考已有的空间角度测量模型，对双测量轴空间旋转模型进行推导和改进. 得到适用于机翼活动翼面绕水平轴偏转情况下的空间角度测量误差模型，提出适用于活动翼面偏转测试需求的倾角传感器校准方法. 以该模型和校准方法为基础设计实现基于无线倾角传感器的大型飞机活动翼面偏转测试系统. 实验平台旋转角度精度测试和活动翼面现场测试的结果表明，相对于现有方法，该校准方法能够获得更大有效测量量程以满足实际工况需求，提升角度校准精度，并显著提升测试效率.


关键词： 活动翼面,  角度测量,  倾角传感器,  校准算法,  偏转测试 
Fig.1 Micro inertial measurement system
Fig.2 Schematic diagram of gravity acceleration sensing device based on capacitance principle
Fig.3 Measurement of three axis inclination angle with micro accelerometer
Fig.4 Spatial measurement model of single axis inclination sensor
Fig.5 Schematic diagram of horizontal measurement axis of dual axis sensor
Fig.6 Schematic diagram of dual axis measurement principle without installation error
Fig.7 Dual axis inclination measurement model
Fig.8 Schematic diagram of coordinate solution process for dual axis inclination measurement without error
Fig.9 Inclination measurement with biaxial error
Fig.10 Relationship between biaxial models with and without error
Fig.11 Schematic diagram of actual biaxial measurement error
Fig.12 Schematic diagram of improved biaxial measurement error model
Fig.13 Overall architecture diagram of movable wing test system based on wireless inclination sensors
Fig.14 Physical system and wireless network diagram of movable wing deflection test system
Fig.15 Software functional framework diagram of movable wing deflection test system
Fig.16 Software main interface diagram
$\beta $${Y_0}$${Y_1}$${E_0}$${E_1}$
00.390.000.390.00
3030.3430.000.340.00
6060.2059.990.20?0.01
00.390.000.390.00
?30?29.66?29.990.340.01
?60?59.77?59.960.230.04
Tab.2 Angle data before and after sensor measurement axis calibration with center frame angle of 30 ° (°)
Fig.17 Installation drawing of three-axis independently controlled precision turntable and sensor adhesive
Fig.18 Calibration experiment site
$\beta $${Y_0}$${Y_1}$${E_0}$${E_1}$
00.000.000.000.00
3030.0130.01—0.01
6059.9859.98—?0.02
00.000.000.000.00
?30?29.99?29.99—0.01
?60?59.95?59.95—0.05
Tab.1 Angle data before and after sensor measurement axis calibration with center frame angle of 0 ° (°)
$\beta $${Y_0}$${Y_1}$${E_0}$${E_1}$
01.130.001.130.00
2021.0719.991.07?0.01
4545.8744.990.87?0.01
6060.5759.990.57?0.01
01.120.001.120.00
?20?18.95?19.991.050.01
?45?44.20?44.960.800.04
?60?59.42?59.940.580.06
Tab.3 Angle data before and after sensor measurement axis calibration with center frame angle of 60 ° (°)
Fig.19 Physical diagram of movable wing surface deflection testing system
时间X/(°)Y/(°)U/VS/dBm
17:02:31?1.18?1.443.7?27
17:02:31?1.21?1.443.7?27
17:02:31?1.19?1.443.7?27
17:02:31?1.19?1.453.7?27
17:02:31?1.20?1.453.7?27
17:02:31?1.17?1.443.7?27
17:02:31?1.22?1.443.7?27
17:02:31?1.19?1.453.7?27
17:02:31?1.18?1.433.7?27
17:02:31?1.21?1.443.7?27
17:02:32?1.21?1.443.7?27
17:02:32?1.18?1.453.7?27
17:02:32?1.21?1.453.7?27
17:02:32?1.16?1.433.7?27
17:02:32?1.21?1.453.7?27
17:02:32?1.19?1.433.7?27
17:02:32?1.18?1.443.7?27
17:02:32?1.20?1.453.7?27
17:02:32?1.20?1.443.7?27
17:02:32?1.19?1.443.7?27
17:02:33?1.19?1.453.7?27
17:02:33?1.19?1.453.7?27
17:02:33?1.20?1.453.7?27
17:02:33?1.19?1.443.7?27
17:02:33?1.19?1.453.7?27
17:02:33?1.20?1.443.7?27
17:02:33?1.20?1.443.7?27
17:02:33?1.19?1.453.7?27
17:02:33?1.20?1.453.7?27
17:02:33?1.18?1.443.7?27
Tab.4 Part of result table for moving wing deflection test
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