A vibration based damage identification algorithm is implemented to assess the damage of a thin-walled composite structure. The structure analysed is a skin with stiffeners, as frequently applied in aircraft components. Both experimental and numerical studies on a single composite skin--stiffener structure showed that the modal strain energy damage index (MSE--DI) algorithm is a suitable method for the detection and localization of a delamination of the stiffener from the skin. A recent study on a strip with a single stiffener and an artificial delamination is extended to a study on a plate with two stiffeners and an impact induced delamination damage.
|Title of host publication||Proceedings of the ISMA conference|
|Place of Publication||Leuven|
|Publisher||Katholieke Universiteit Leuven|
|Publication status||Published - 22 Sep 2010|
|Event||24th International Conference on Noise and Vibration Engineering, ISMA 2010 - Leuven, Belgium|
Duration: 20 Sep 2010 → 22 Sep 2010
Conference number: 24
|Conference||24th International Conference on Noise and Vibration Engineering, ISMA 2010|
|Period||20/09/10 → 22/09/10|
Loendersloot, R., Ooijevaar, T. H., Warnet, L., de Boer, A., & Akkerman, R. (2010). Vibration based structural health monitoring of a composite plate with stiffeners. In P. Sas (Ed.), Proceedings of the ISMA conference (pp. 909-924). Leuven: Katholieke Universiteit Leuven.