Today the assessment of a harsh landing condition for helicopters is based on the pilot's judgment. This finding can lead to a misclassification of the landing condition, thus affecting system safety or requiring unnecessary maintenance. The availability of a tool for automatic assessment of the harshness of the landing condition would improve the efficiency of current helicopter operations. However, the development of systems for harsh landing monitoring is complex and costly, as it requires knowledge of the structural dynamic behavior under different landing conditions and a sufficient prior experience of structural damage examples. In this framework, numerical models provide simulated experience through virtual tests that can be used to predict harsh landing damage under different landing conditions.We describe the preliminary step for the validation of a coupled multibody-finite element modeling environment, useful to estimate the most critical zones within the fuselage as well as the occurrence of plastic damage. Experimental harsh landing tests were carried out on a retiredMil Mi-8 helicopter, and three-dimensional (3D) scan measures of the helicopter geometry were taken during helicopter tests. Repeated drops from increasing altitude were performed, each time recording the 3D surface geometry at some critical locations, thus allowing the validation of the numerical model.
|Titolo:||Experimental validation of a computational hybrid methodology to estimate fuselage damage due to harsh landing|
|Data di pubblicazione:||2016|
|Appare nelle tipologie:||01.1 Articolo in Rivista|
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