TY - GEN
T1 - A validation study for a crack-detected method by intelligent coating under operational environment
AU - Liu, Mabao
AU - Li, Liren
AU - Sun, Jianjiang
N1 - Publisher Copyright:
Copyright © 2015 by DEStech Publica tions, Inc.
PY - 2015
Y1 - 2015
N2 - A newly invented Structure Health Monitoring (SHM) technology, named as Intelligent Coating Monitoring (ICM), was verified by various lab-scale experiments along with full-scale fatigue tests to investigate ICM capability for monitoring crack initiation and propagation in metal substances. In order to apply the technology to civil aircraft, the ICM system was validated under real service conditions. Firstly, ICM is briefly introduced, including the principle of the intelligent coating sensor, the makeup of the system and various lab-scale experiments as well as full-scale fatigue tests for verification and application. Then the installation of ICM system on an operational aircraft structure was given which includes the determination of critical locations that need monitoring, the selection of sensors corresponding to each monitoring point with certain geometry, the method of sensors splicing and main-/sub- interrogation units fixing and the connection of the above hardware through wires laid to form an ICM system. Finally, the operating situation and the effectiveness of the ICM system under operational environment were validated and summarized. It can be proven by the present study that ICM system installed on the aircraft structure can monitor cracks which might occur at any specified location, and most sensors along with other hardware can work effectively under actual condition.
AB - A newly invented Structure Health Monitoring (SHM) technology, named as Intelligent Coating Monitoring (ICM), was verified by various lab-scale experiments along with full-scale fatigue tests to investigate ICM capability for monitoring crack initiation and propagation in metal substances. In order to apply the technology to civil aircraft, the ICM system was validated under real service conditions. Firstly, ICM is briefly introduced, including the principle of the intelligent coating sensor, the makeup of the system and various lab-scale experiments as well as full-scale fatigue tests for verification and application. Then the installation of ICM system on an operational aircraft structure was given which includes the determination of critical locations that need monitoring, the selection of sensors corresponding to each monitoring point with certain geometry, the method of sensors splicing and main-/sub- interrogation units fixing and the connection of the above hardware through wires laid to form an ICM system. Finally, the operating situation and the effectiveness of the ICM system under operational environment were validated and summarized. It can be proven by the present study that ICM system installed on the aircraft structure can monitor cracks which might occur at any specified location, and most sensors along with other hardware can work effectively under actual condition.
UR - https://www.scopus.com/pages/publications/84945586702
U2 - 10.12783/shm2015/69
DO - 10.12783/shm2015/69
M3 - 会议稿件
AN - SCOPUS:84945586702
T3 - Structural Health Monitoring 2015: System Reliability for Verification and Implementation - Proceedings of the 10th International Workshop on Structural Health Monitoring, IWSHM 2015
SP - 538
EP - 545
BT - Structural Health Monitoring 2015
A2 - Chang, Fu-Kuo
A2 - Kopsaftopoulos, Fotis
PB - DEStech Publications
T2 - 10th International Workshop on Structural Health Monitoring: System Reliability for Verification and Implementation, IWSHM 2015
Y2 - 1 September 2015 through 3 September 2015
ER -