Modal Analysis for Trailing Edge of Morphing Wing of Composite Material
Abstract
Based on the handmade of trailing edge of morphing wing and flexible composite skin, this paper develops modal analysis both on finite element models in PATRAN and MSC.NASTRAN and experiment. The results show that the deviation of the first-four natural frequencies from the finite element software results is within 10% and the natural modes are basically the same, which provides the effectiveness of the finite element analysis method. Through the vibration modal analysis experiment of the trailing edge, the first-order natural frequency of the structure is obtained as 13.08Hz, which provides useful data for the subsequent study of strain characteristics.
- Publication:
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Materials Science and Engineering Conference Series
- Pub Date:
- July 2018
- DOI:
- 10.1088/1757-899X/382/2/022013
- Bibcode:
- 2018MS&E..382b2013Q