Abstract
Part of the structural inspections done to modern military aircraft can be technically replaced by automatic structural health monitoring systems (SHMS). One option for the system’s sensor is traditional strain gauge, whose capabilities in structural damage detection were evaluated. A series of finite element analysis were done according to different damage cases in order to predict the output of strain gauge in crack affected area. Results from two fatigue tests have been used to test the strain gauge and prediction tool capabilities in real structural damage cases. The experience gained showed noteworthy potential for the strain gauge based SHMS to be further developed into a flying prototype, as the formation and growth of fatigue cracks could be detected early enough in view of maintaining the flight safety. Biggest problems to be solved are in areas of damage size classification.
| Original language | English |
|---|---|
| Title of host publication | Structural Health Monitoring 2003 |
| Subtitle of host publication | From Diagnosis & Prognostics to Structural Health Management |
| Editors | Fu-Kuo Chang |
| Publisher | DEStech Publications Inc. |
| Number of pages | 8 |
| ISBN (Print) | 978-1-932078-20-6 |
| Publication status | Published - 2003 |
| MoE publication type | A4 Article in a conference publication |
| Event | 4th International Workshop on Structural Health Monitoring - Stanford, United States Duration: 15 Sept 2003 → 17 Sept 2003 |
Conference
| Conference | 4th International Workshop on Structural Health Monitoring |
|---|---|
| Country/Territory | United States |
| City | Stanford |
| Period | 15/09/03 → 17/09/03 |