Optimization and experimentation of remote field eddy current testing probe for hidden defects of aircraft riveting parts

被引:0
|
作者
Zhao B. [1 ]
Song K. [1 ]
Ning N. [2 ]
Huang H. [2 ]
Zhang L. [1 ]
机构
[1] Key Laboratory of Nondestructive Testing, Ministry of Education, Nanchang Hangkong University, Nanchang
[2] Aircraft Strength Research Institute, Xi'an
基金
中国国家自然科学基金;
关键词
Defect around hole; Nondestructive testing; Remote field eddy current; Riveted structure; Shield damping;
D O I
10.7527/S1000-6893.2019.23111
中图分类号
学科分类号
摘要
The remote field eddy current testing technique features a deep depth of detection, high reliability of detection results, and many other advantages, which make it suitable for rapid detection of multi-layer metal riveting components. Aiming at the in-situ detection of hidden cracks along the rivet holes of aircraft riveting, the finite element model for the remote field eddy current detection of the hidden crack plane of multi-layer metal riveting members is established. The inner diameter of exciting coli, magnetic circuit structure, and shielding damping are simulated and optimized. The exciting coil and the detecting coil are combined with the shielding structure. The characteristics of hidden crack signals along the rivet holes of multi-layer metal riveting members are studied. The simulation and experimental results show that the tank shape of the magnetic core is 1.85 times that of the cylindrical of the magnetic core. The shield of the aluminum cover + copper cover can advance the remote field by 10 mm. When the detection coil is directly above the defect, the detected amplitude of the signal value and phase reach the maximum values. And the maximum value decreases with the increase of the buried depth of the defect. The research results are expected to be used to guide the engineering inspection practice of the multi-layer metal riveted components of the aircraft. © 2020, Press of Chinese Journal of Aeronautics. All right reserved.
引用
收藏
相关论文
共 22 条
  • [1] Wang L.M., Feng T.N., Application of digital automatic drill-riveting technology in aircraft manufacture, Aeronautical Manufacturing Technology, 11, pp. 32-35, (2008)
  • [2] Du H.Z., Fatigue Strength and Fracture Analysis of Aircraft Structure, (1996)
  • [3] Tian D.F., Research on fatigue property of riveted component for aircraft fuselage, (2013)
  • [4] Zhang A.L., Efficient and accurate drilling technology for fuselage circumferential splice of large aircraft, (2016)
  • [5] Yang B.F., Luo F.L., Zhang Y.H., Et al., Application research of pulse eddy current in nondestructive testing of aircraft riveted structure, Metrology Technology, 12, pp. 15-17, (2005)
  • [6] Geng R.S., Jing P., Application of acoustic emission technique to full scale aircraft fatigue tests, Applied Acoustics, 32, 4, pp. 14-19, (2013)
  • [7] Kang J.Z., Wu R.G., Du Z.Y., Et al., Cause analysis on rivet falling off and breaking the engine in aircraft inlet, Aviation Maintenance & Engineering, 8, pp. 89-91, (2015)
  • [8] Peng Z.W., Jiang Y.J., Wang Z.L., In-situ ultrasonic inspection for cracks around holes of bolted joints, Nondestructive Testing, 38, 10, pp. 67-71, (2016)
  • [9] Tian Y.F., Cao Z.J., The Analysis of aging aircraft skin lap joint structure based on infrared NDI, Aircraft Design, 3, pp. 31-35, (2013)
  • [10] Xu M., Huang H.B., Wang Z.L., Research on detection method of aircraft skin crack in fatigue testing, Structural Strength Study, 2, pp. 53-56, (2014)