Experimental Determination of Damaged Location on Thin Plate Using Frequency Measurement

Abstract

With advances in technology, the request for monitoring the integrity of aerospace structures is developed in the direction to integrate the low-cost, light and reliable sensors. The new types of sensors can monitor structures continuously for detection and assessment of damage progression in modern concept of aircraft structural health monitoring (SHM). This paper deals with experimental determination the presence of damage on thin aluminium alloy plate using the PVDF sensors and measures change in plate frequency before and after damage. Damage in structure alters its dynamic characteristics. The change is characterized by variations in plate parameters i.e. frequencies, damping values and mode shapes. Measurement of vibration with using the piezo film sensors (PVDF) and analysis with adequate tools can determine the crack presence of damaged structure. The results of the presented experiment can be implemented in different types of aircrafts structures in order to advance two modern concepts Aircraft Life Extending (ALE) and SHM of aircraft and aircraft weapons pods.