Identifying delamination in an experimental composite UAV wing subject to ambient gust loading

Jonathan M. Nichols; Stephen T. Trickey; Mark Seaver; Daniel L. Pecora

doi:10.1117/12.659241

15 March 2006 Identifying delamination in an experimental composite UAV wing subject to ambient gust loading

Jonathan M. Nichols, Stephen T. Trickey, Mark Seaver, Daniel L. Pecora

Proceedings Volume 6177, Health Monitoring and Smart Nondestructive Evaluation of Structural and Biological Systems V; 617704 (2006) https://doi.org/10.1117/12.659241
Event: Nondestructive Evaluation for Health Monitoring and Diagnostics, 2006, San Diego, CA, United States

Abstract

Vibration-based structural health monitoring has largely considered applied excitations as the primary means of inducing structural vibration. Here we consider how ambient vibrations might be used to assess the level of damage in a composite UAV wing. The wing consists of a foam core and a carbon fiber skin. We subject the wing to various amounts of impact damage in order to cause internal delaminations. The wing is then excited using a gust loading waveform in an effort to simulate the forcing the wing is expected to see in flight. We then use a probabilistic description of the structure's dynamics to assess the level of damage-induced nonlinearity in the wing. The approach is capable of making the diagnosis in the absence of a representative baseline data set from the "healthy" wing.

Citation Download Citation

Jonathan M. Nichols, Stephen T. Trickey, Mark Seaver, and Daniel L. Pecora "Identifying delamination in an experimental composite UAV wing subject to ambient gust loading", Proc. SPIE 6177, Health Monitoring and Smart Nondestructive Evaluation of Structural and Biological Systems V, 617704 (15 March 2006); https://doi.org/10.1117/12.659241

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