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Health Monitoring of Aging Aircraft Structures

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1 Health Monitoring of Aging Aircraft Structures
Local-area health monitoring of a helicopter rotor blade. Giurgiutiu, et al (1997) AGING! Damage due to aging All of us are customers of commercial airlines and our major concern is flight safety. A new insitu non destructive technologies based on utilization of piezoelectric active sensors are elaborated to address online health monitoring of vital aircraft parts such as fuselage and wing junctions or engine turbo blades. Active piezoelectric sensors on an engine blade Aging aircraft panel with simulated crack

2 E/M Impedance Method Results by Giurgiutiu, Turner, 1998
The piezoelectric active sensors utilized for E/M impedance method was successfully employed in health monitoring of bolted joint. Due to electro-mechanical coupling, piezoelectric active sensor was able to monitor the dynamic stiffness of a host structure. The stiffness was modified by loosing the bold joint. The complex impedance then was gathered with Impedance Analyzer and processed later with PC to create a damage metric on a simple red, yellow, and green scale. In our example Root Mean Square (RMS) values of Impedance change below 20% correspond to green light which mean normal operational conditions, between 20% and 40% yellow light and above 40% RMS Impedance change correspond to red light which means failure. Results by Giurgiutiu, Turner, 1998

3 Experiments with Aging Aircraft Panel
The full panel and the HP 4194A Impedance Analyzer Piezoelectric sensors installed on the aircraft panel with aging damage simulated by a 10-mm crack originating from a rivet This technique was utilized for real aging aircraft panel supplied by Sandia National Laboratory. The E/M impedance spectrum for each sensor which were located at the different distances from the simulated crack was recorded. The sensor closest to the cracked region revealed quite different behavior represented by a blue line. The active sensor self diagnostic issues were investigated. It was found that disbonded sensor shows noticeable self-sensor resonance in comparable with well bonding neighbor. Experimental results on aging aircraft panel Active Sensor Self-Diagnostics

4 Development of Concepts for Automatic Health Monitoring System
The future of such sensing is conceptualized as integrated part of real structures and could be compared with nervous systems of living organisms, so that the active sensors will “feel” the structure and provide a feedback in terms of information on the structural health. The future development of a Health Monitoring System allows wireless data transmitting from data clusters situated at the vital areas of a structure into central health monitoring station via data concentrators. When the data was analyzed the information about structural health is displayed on a structure’s model on a green, yellow, red scale for user convenience. The goal of the development is to approach the concepts of nervous systems used by living organisms. Wireless health monitoring system on board of civil aircraft


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