Structural Health Monitoring in the Assembly of the Torsion Box and the Semi-Wings

In this work the progression of damage is illustrated by reducing the preload in a bolted joint and subsequently losing one or more joints in a prototype of the assembly between the main beam of a semi-wing with the torsion box of an airplane using the Natural Frequencies Vector Assurance Criterion (NFVAC) and the Damage Natural Frequencies Vector Assurance Criterion (DNFVAC) supported by experimental tests applying Experimental Modal Analysis (EMA) and simulation by means of the Finite Element Method (FEM) for applications in Structural Health Monitoring (SHM).