Quantification of Lamb Wave-based SHM technique through Ground Test under simulated flight environment for commercial airplane

Abstract

This research introduces an advanced Structural Health Monitoring (SHM) methodology for in-service aircraft, with a specific focus on a case study involving 737NG Aft Pressure Bulkhead (APB) coupons. Aimed at achieving FAA first targeted application for FAA certification, the study leverages SMART layer technology to construct a sensor network, facilitating real-time damage assessment through Damage Index (DI) analysis for precise crack detection and localization. The core of our approach involves the utilization of DI values, obtained from the sensor data, to assess crack progression and pinpoint structural anomalies, highlighting the capability of SHM systems in enhancing maintenance efficiency and aircraft safety. Additionally, the Probability of Detection (PoD) analysis incorporated in this study assesses the SHM system's reliability, ensuring compliance with FAA standards. Our findings underscore the potential of SMART layer-based SHM systems in revolutionizing aircraft maintenance protocols by enabling proactive and accurate structural health assessments, particularly at the 4.5mm threshold. This case study not only demonstrates the feasibility of SHM in critical aircraft components but also sets a precedent for the wider application and development of SHM technologies in the aviation industry, promising to elevate safety standards and operational efficiency.