A Structural Health Monitoring System for the Full Scale Aircraft Fatigue Test

Abstract:

A structural health monitoring system especially for the full scale aircraft fatigue test is being developed to monitor, interpret, and make decisions based on the information from sensors during experiment. The functions of the system are achieved by different subsystems including data acquisition subsystem, control and manage subsystem, data visualization subsystem and data process subsystem. Subsystems communicate each other by the user-defined protocol based upon the TCP protocol. The structural health monitoring system uses five types of sensors, including strain gauge, ultrasonic transducer, PZT sensor, FBG sensor, and ICMS sensor. Finally this system is being used in the extended fatigue test of a certain aircraft, and had captured several structure faults.

• Periodical: Applied Mechanics and Materials (Volumes 427-429)
• Pages: 1752-1755
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.427-429.1752
• Online since: September 2013
• Authors: Yi Shan Zhang, Zhi Wang, Jia Kun Cai
• Keywords: Aircraft, Fatigue Test, Structural Health Monitoring (SHM)

References

[1] P.A. Lloyd: The Aeronautical Journal, May (2008), p.285.

[2] E.A. Douglas: Journal of Failure Analysis and Prevention, Vol. 4 (2004), p.9.

[3] C. Boller: International Journal of Systems Science, Vol. 31 (2000), p.1333.

[4] K.M. Holford, R. Pullin and S.L. Evans: J. Aerospace Engineering, Vol. 223 (2009), p.525.

[5] S.F. Yuan: Journal of Material Science & Technology, Vol. 20 (2002), p.490.

[6] J.G. Liu: China Surface Engineering, Vol. 4 (2009), p.32.

[7] R. Jones and S. Galea: Composite Structures, Vol. 58 (2002), p.397.

[8] Y.S. Zhang: The 3rd International Conference on Maintenance Engineering, China (2012), p.812.