固体力学与飞行器总体设计

压电双晶片悬臂梁结构用于结冰探测的研究

  • 白天 ,
  • 朱春玲 ,
  • 李清英 ,
  • 朱程香
展开
  • 南京航空航天大学 航空宇航学院, 江苏 南京 210016
白天 男, 博士研究生。主要研究方向: 飞机防除冰技术。 Tel: 025-84896297 E-mail: mydaytime2005@yahoo.com.cn;朱春玲 女, 博士, 教授, 博士生导师。主要研究方向: 飞行器环境控制、 飞机结冰与防除冰技术。 Tel: 025-84896667 E-mail: clzhu@nuaa.edu.cn;李清英 女, 博士研究生。主要研究方向: 飞机防除冰技术。 E-mail: li_qingying@nuaa.edu.cn;朱程香 女, 博士研究生, 讲师。主要研究方向: 飞机结冰与防除冰技术。 E-mail: cxzhu@nuaa.edu.cn

收稿日期: 2012-06-07

  修回日期: 2012-09-19

  网络出版日期: 2012-09-28

基金资助

江苏省博士后科研资助计划项目(1201033C);南京航空航天大学基本科研业务费专项科研项目(56XZA11059)

Study of Bimorph Piezoelectric Cantilever Structure Used on Icing Detection

  • BAI Tian ,
  • ZHU Chunling ,
  • LI Qingying ,
  • ZHU Chengxiang
Expand
  • College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2012-06-07

  Revised date: 2012-09-19

  Online published: 2012-09-28

Supported by

Jiangsu Postdoctoral Research Funded Projects (1201033C);NUAA Research Funding (56XZA11059)

摘要

采用一种压电双晶片悬臂梁结构作为结冰探测的传感元件,使用有限元方法(FEM)计算其在有水附着与结冰两种状态下的谐振频率变化,同时使用Agilent 35670A动态信号分析仪与传统的传输法进行实验测量,通过误差对比检验计算结果的正确性,并找出谐振频率的变化与压电梁局部质量和刚度等结构特征改变之间的联系,发现随着结冰的发生以及厚度的增加,相应的局部质量和刚度的改变对谐振频率的综合影响多变。针对压电双晶片悬臂梁结构的特殊性,采用一种反馈法接线进行测量,并与传输法测量结果以及FEM计算结果进行比较,证明这种测量方法的准确性。最后根据计算与实验测量结果确定合适的工作模态,总结整个结冰过程对该模态谐振频率的影响。结果表明,压电双晶片悬臂梁结构用于结冰探测是可行的,它能够准确检测出不同结冰状态对其结构特征的影响,并且结构简单、便于测量。

本文引用格式

白天 , 朱春玲 , 李清英 , 朱程香 . 压电双晶片悬臂梁结构用于结冰探测的研究[J]. 航空学报, 2013 , 34(5) : 1073 -1082 . DOI: 10.7527/S1000-6893.2013.0196

Abstract

A bimorph piezoelectric cantilever structure is introduced as sensor for icing detection. First of all, the resonant frequencies of the piezoelectric cantilever with water droplet and ice attached are calculated by using the finite element method (FEM), and the results are inspected through error evaluation with the help of an Agilent 35670A dynamic signal analyzer and a traditional transmission measuring method. In this way, the relationship between the variation of resonant frequencies and the change of piezoelectric cantilever structure, such as partial mass and stiffness, is revealed. The result shows that the combined effects of corresponding partial mass and stiffness on resonant frequencies of a piezoelectric cantilever are multivariant with the occurrence of freezing and accretion of ice. Then a substituted feedback measuring method based on the special structure of the bimorph piezoelectric cantilever is employed to obtain the resonant frequencies. The effectiveness of this measuring method is confirmed by comparing its results with those of the transmission measuring method and FEM. Finally, an appropriate operational mode is determined according to previous measured and calculated results, and the variation of the resonant frequency of the sensor throughout the icing process is summarized as well. The conclusions indicate that the employment of bimorph piezoelectric cantilevers on icing detection is feasible. It is simple in structure and measurement, yet it can effectively detect the existence of different icing conditions.

参考文献

[1] Thomas S, Cassoni R, MacArthur C. Aircraft anti-icing and de-icing techniques and modeling. Journal of Aircraft, 1996, 33(5): 841-854.
[2] Palacios J L, Smith E C, Huidong G, et al. Ultrasonic shear wave anti-icing system for helicopter rotor blades. AHS 62nd International Annual Forum, 2006.
[3] Li G Z, Cao Y H. Effect of rotor icing on helicopter flight dynamic characteristics. Acta Aeronautica et Astronautica Sinica, 2011, 32(2): 187-194. (in Chinese) 李国知, 曹义华. 旋翼结冰对直升机飞行动力学特性的影响. 航空学报, 2011, 32(2): 187-194.
[4] Baumgardner D, Rodi A. Laboratory and wind tunnel evaluations of the rosemount icing detector. Journal of Atmospheric and Oceanic Technology, 1989, 6(6): 971-979.
[5] Roy S, DeAnna R G. Miniature ice detection sensor systems for aerospace applications. The 11th Annual International Workshop on Micro Electro Mechanical Systems, 1998.
[6] Li X P, Shih W Y, Vartuli J, et al. Detection of water-ice transition using a lead zirconate titanate/brass transducer. Journal of Applied Physics, 2002, 92(1): 106-111.
[7] Zhang J, Zhou L, Zhang H, et al. Aircraft icing detection technology. Chinese Journal of Scientific Instrument, 2006, 27(12): 1578-1586. (in Chinese) 张杰, 周磊, 张洪, 等. 飞机结冰探测技术. 仪器仪表学报, 2006, 27(12): 1578-1586.
[8] Ye L. A new ice sensor based on piezoelectric device. Instrument Technique and Sensor, 2001(9): 6-8. (in Chinese) 叶林. 基于压电器件的冰传感器. 仪器技术与传感器, 2001(9): 6-8.
[9] Zhang B H, Wang H, Wang J S, et al. A method for ice detecting based on the principle of vibration. Chinese Journal of Scientific Instrument, 2003, 24(4): 384-386. (in Chinese) 张滨华, 王华, 王劲松, 等. 一种基于振动原理的结冰探测方法. 仪器仪表学报, 2003, 24(4): 384-386.
[10] Roy S, DeAnna R G, Mehregany M, et al. Smart ice detection systems based on resonant piezoelectric transducers. Sensors and Actuators: A, 1998, 69(3): 243-250.
[11] Ajitsaria J, Choe S Y, Shen D, et al. Modeling and analysis of a bimorph piezoelectric cantilever beam for voltage generation. Smart Materials and Structures, 2007, 16(2): 447-454.
[12] Zhao C S. Ultrasonic motors technologies and applications. Beijing: Science Press, 2007: 137-139. (in Chinese) 赵淳生. 超声电机技术与应用. 北京: 科学出版社, 2007: 137-139.
[13] Song D R, Xiao M S. Piezoelectric effect and its application. Beijing: Popular Science Press, 1987: 136-139. (in Chinese) 宋道仁, 肖鸣山. 压电效应及其应用. 北京: 科学普及出版社, 1987: 136-139.
[14] Haftka R T, Adelman H M. Recent developments in structural sensitivity analysis. Structural and Multidisciplinary Optimization, 1989, 1(3): 137-151.
[15] Kannappan L, Shankar K, Sreenatha A G. Damage detection using frequency measurements. 25th International Modal Analysis Conference, 2007.
[16] Fang Y. Vibration modal analysis technique. Beijing: National Defense Industry Press, 1993: 148. (in Chinese) 方远. 振动模态分析技术. 北京: 国防工业出版社, 1993: 148.
[17] Qiu X G, Han F H. Aircraft icing protection system. Nanjing: Nanjing University of Aeronautics and Astronautics University Press, 1996: 190. (in Chinese) 裘燮纲, 韩凤华. 飞机防冰系统. 南京: 南京航空航天大学出版社, 1996: 190.
[18] Heinrich A, Ross R, Zumwalt G, et al. Aircraft icing handbook-Volumes 1 of 3. DOT/FAA/CT-88/8-1, 1991.
文章导航

/