| 摘要 |
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. |
| 主权项 |
1. A monitoring system for determining the remaining useful life of a component under cyclic stress, the monitoring system comprising:
a first sensor measuring a first signal including a first data representative of crack propagation; a second sensor measuring a second signal including a second data representative of acoustic emissions; a processor in electronic communication with said first sensor and said second sensor and receiving said first data and said second data, said processor determining from said second data at least one condition indicator, and wherein said processor determines, based upon said at least one condition indicator and said first data, the remaining useful life of the component. |
