Multiple PAMELA SHMTM System for Automated SHM Control During Fatigue Tests of Aircraft Structures

Fatigue testing of aircraft structures is a complex, costly and time-consuming process. Typical primary-component fatigue tests of aircraft structures usually last between one and two years. In addition, this process must be interrupted periodically to check the structure integrity, usually using nondestructive methods, which increases the total duration of the process. The goal of the system described in this paper is to provide a solution for automating structural integrity inspection with structural health monitoring (SHM) methods. This solution would avoid periodic interruptions and produce cost-effective and timely test processes. This paper details the main features of and possibilities for the multiple PAMELA (Phased Array Monitoring for Enhanced Life Assessment) SHM™ system when it is used to automate SHM control during fatigue tests of aircraft structures. A complete software environment is described for automating test execution using the PAMELA III hardware.