The Study of Nonlinear Flutter Analysis Method for an Aircraft Full Composite Wing with High-aspect-ratio

DOI

10.2991/ame-16.2016.135How to use a DOI?

Keywords

Nonlinear Flutter, Corotational, Thin Shell Element, High-aspect-ratio Wing.

Abstract

A nonlinear flutter analysis method using CFD/CSD was presented in this paper. The computational method couples a nonlinear finite element method model with CFD solver. The structural analysis was based on a 4-node thin shell element and a new corotational (CR) formulation, which can be employed to analyze geometric nonlinearities arising from large deflections. The expression of tangent stiffness equations under geometric nonlinear structure was derived. Aerodynamic load was calculated by CFD solver with the Navier-Stokes equations as the control equations. This paper showed that the geometric nonlinear method is computationally high efficient and good agreement by examined. The geometric nonlinear method can be successfully applied for the nonlinear flutter analysis to full composite wing with high-aspect-ratio. The flutter speed of the composite wing is near 0.65Ma.

Copyright

© 2016, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Sheng-Jun Qiao
AU  - Hang-Shan Gao
AU  - Jun-Ran Zhang
PY  - 2016/06
DA  - 2016/06
TI  - The Study of Nonlinear Flutter Analysis Method for an Aircraft Full Composite Wing with High-aspect-ratio
BT  - Proceedings of the 2nd Annual International Conference on Advanced Material Engineering (AME 2016)
PB  - Atlantis Press
SP  - 818
EP  - 824
SN  - 2352-5401
UR  - https://doi.org/10.2991/ame-16.2016.135
DO  - 10.2991/ame-16.2016.135
ID  - Qiao2016/06
ER  -