Structural Health Monitoring (SHM) on High Stress Loading of Wing Bracket

Abstract

This paper presents a Structural Health Monitoring (SHM) approach by addressing the modeling based on Cessna 310 wing bracket to collect its baseline data. SHM is a novel technology application in most engineering field including aircraft and aerospace field for defect detection including crack and other damage area. The main purpose of this project is to assess their structural integrity due to designated loading and boundary conditions using ABAQUS modeling technique application. These parts were selected as its structures are specifically complex and considered as ageing aircraft parts. The work can be also regarded as platform for CAD model database for ageing aircraft parts investigation upon their structural analyses and design preference. The works begins with a precise measurement using basic gauges and transfer to a 3-D solid modeling using CATIA V6. The optimization technique introduces in this work will be of a novel approach since the CATIA will be combined with the Matlab programming software and Finite Element Analysis (FEA) model in order to predict the damage location with respect to the prescribing boundaries and loadings conditions. The present works shows the application of the FEA of Abaqus / CAE software programming to build its graphical user interface (GUI) and Matlab software used to control its algorithms for its structural analysis in relation to the components.