机翼结构超声除冰系统数值模拟与实验

doi:10.13229/j.cnki.jdxbgxb20210114

摘要/Abstract

摘要：

利用数值和实验方法，对NACA 0015机翼结构超声除冰系统进行了研究。针对覆冰双层板模型，通过全局矩阵法（GMM）研究了覆冰厚度和覆冰弹性模量对冰层界面剪应力集中系数（ISCC）和除冰频率的影响；同时，对压电激励器进行了参数设计，并应用阻抗曲线验证了设计结果的准确性。最后，根据NACA 0015机翼的几何特点，对压电激励器布置和除冰效率进行了研究，并开展了除冰实验，验证了NACA 0015机翼结构超声除冰系统的可行性，实验结果表明：该机翼结构的除冰功耗仅为传统电热除冰的16%左右。

关键词: 固体力学, 机翼结构, 超声除冰, 全局矩阵法, 界面应力集中系数, 除冰效率, 除冰实验

Abstract:

Numerical and experimental methods were used to study the NACA 0015 airfoil structure ultrasonic deicing system. For the ice-coated double-layer plate model， the effects of the thickness and Young's modulus of ice layer on the interface shear stress concentration coefficient （ISCC） and deicing frequency were explored by the global matrix method （GMM）. At the same time， specific piezoelectric actuators were designed based on the theoretical research results and the accuracy of the finite element simulation was verified by the impedance curve. Finally， according to the geometric characteristics of the airfoil， the location of piezoelectric actuators and deicing efficiency were studied. Related deicing experiments were conducted to verify the feasibility of the ultrasonic deicing system. The experimental results showed that the deicing power of this airfoil structure is only around 16% of the traditional electro-thermal deicing.

Key words: solid mechanics, airfoil structure, ultrasonic deicing, global matrix method, interface shear stress concentration coefficient, deicing efficiency, deicing experiments

中图分类号:

V244.1

石忠华,宋权威,康振航,谢强,章继峰. 机翼结构超声除冰系统数值模拟与实验[J]. 吉林大学学报(工学版), 2022, 52(7): 1561-1573.

Zhong-hua SHI,Quan-wei SONG,Zhen-hang KANG,Qiang XIE,Ji-feng ZHANG. Numerical simulation and experiment on ultrasonic deicing system of airfoil structure[J]. Journal of Jilin University(Engineering and Technology Edition), 2022, 52(7): 1561-1573.

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压电片直径/mm	弦长位置/mm
压电片直径/mm	60	90	120	150
50	1.109	0.682	0.486	0.369
60	1.618	0.999	0.703	0.535