摘要
A method for flutter of the very flexible wing with a high-aspect-ratio is developed. Firstly, the very flexible wing subjected to aeroelastic load will undergo a large deformation. So the deformed wing can be regarded as a curve beam and divided into a couple of curve beam elements. The mean curvature of every beam element is obtained by mean of polynomial interpolation method. For each element, the flutter differential equations is established by combining the differential equations of the constant curvature beam vibration and the Therdorson' unsteady aerodynamics model. Then, using the distributed transfer function method and the finite element method, the equilibrium equations of the whole wing are obtained. Finally, the wing flutter was carried out by solving a eigenvalue problem. The results are good agreement to the literature solutions and indicate that the present method is accurate and efficient.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 774-782 |
| 页数 | 9 |
| 期刊 | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| 卷 | 34 |
| 期 | 5 |
| 出版状态 | 已出版 - 1 10月 2016 |