Importance

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Abstract

A monitoring system of the present disclosure reduces the sampling and processing requirements for on-line/in-flight monitoring of structural components and thus facilitates detection of high cycle/low amplitude fatigue damage. Moreover, the monitoring system can develop a physical failure model based on information received from monitoring sensors that can be used to determine the remaining useful life (RUL) of structural components. In an exemplary embodiment, the incorporation of low cost, light weight, bused sensors would facilitate in-flight load tracking and detection of high cycle/low amplitude fatigue damage. In this embodiment, a model based on the physical degradation process of the material under analysis (e.g., a physical failure model based on cumulative damage estimation, i.e., based on an AE events count) can be generated using measurable and quantifiable parameters from these sensors and accordingly the RUL of structural components can be determined.

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