Damage Detection Technology for CFRP Structure Using MFC/FBG Hybrid Sensor System

Abstract

We have been developing a Structural Health Monitoring (SHM) System for Carbon Fiber Reinforced Plastic (CFRP) structure of an aircraft. This system consists of piezoelectric transducer (PZT) actuators, fiber Bragg grating (FBG) optical fiber sensors and a control device. This SHM system can monitor debonding in interface between a skin panel and stringer flange by analysis of a Lamb wave which is a type of ultrasonic wave. Namely, this system is suitable to detect fatal damages for an aircraft structure in “Hot-Spotâ€. Development of this system will make it possible to reduce maintenance costs on airlines, to improve safety and reliability of aircraft, and in future, to achieve innovative aircraft structure which is lighter than present aircraft. We are conducting research and development with Airbus and SOKEIZAI center for practical applications of the SHM system for the near future. In this article, we will present a general outline of process and our achievement about JASTAC project with Airbus and SOKEIZAI center, and foresight of future works. Moreover, probability of detection (POD) assessment test will be reported in this paper.