Evaluating the Influence of SHM on Damage Tolerant Aircraft Structures Considering Fatigue

Abstract

First patents concerning the integration of Structural Health Monitoring (SHM) capabilities into aircraft have been granted over 70 years ago (Green ). Since then, numerous potential applications of SHM along the entire aircraft lifecycle have been identified in scientific literature. However, the application of this technology in commercial aviation is currently limited to field studies carried out primarily within aging fleets. Aside from recent advances in sensor technology, growing research effort has been committed to identify and quantify promising business cases for SHM (Bos ). Even though numerous individual applications have been investigated with regard to their lifecycle cost impact, current studies yield varying results. In order to facilitate the integration of SHM in commercial aviation we plan to put forward an integrated analysis framework for SHM technologies covering the entire aircraft lifecycle including design, operation and retirement. As part of this framework the work at hand introduces an expanded evaluation approach based on (Schmidt and Schmidt‐Brandecker ) to identify the impact of SHM on aircraft structural design considering structural weight, risk of structural failure and inspection intervals. The proposed methodology is limited to damage tolerant structures prone to fatigue and considers only component sizing rather than the redesign of structures. By using the established relation between structural dimensions, weight, inspection intervals and aircraft end of life, the approach is calibrated with inspection intervals provided by the manufacturer. Subsequently, the influence of SHM can be analyzed using an ideal sensor system (no false alarms). Finally, a case study is presented demonstrating the suggested methodology using the example of a commercial narrow-body passenger aircraft.