Transient Aeroelastic Responses of Folding Wing in Morphing Motion

DOI

10.2991/ameii-15.2015.253How to use a DOI?

Keywords

folding wing; time-varying system; rational function approximation; double lattice method.

Abstract

To investigate the transient aeroelastic responses of a folding wing during morphing motion, a time-varying aeroelastic equation in state space is presented. The structural model is established based on the component modal synthesis method. A time-dependent transformation is introduced to establish the compatibility equations. The aerodynamic force is obtained by double lattice method, and then the rational function fitting method is adopted to deduce the approximate expressions of the aerodynamic force in time domain which is used in conjunction with the structural model. The equations of motion in state space are solved using the Runge-Kutta numerical integration technique to predict the transient aeroelastic responses. The effects of the flow velocity and the morphing velocity are studied to deeply understand the aeroelastic characteristics of a folding wing. The numerical results indicate that the aerodynamic force contributes to the morphing motion. With a greater flow velocity or a slower morphing motion, the reaction moment will decrease. So a better aeroelastic performance can been obtained.

Copyright

© 2015, 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  - Yingge Ni
AU  - Chi Hou
AU  - Xiaopeng Wan
AU  - Meiying Zhao
PY  - 2015/04
DA  - 2015/04
TI  - Transient Aeroelastic Responses of Folding Wing in Morphing Motion
BT  - Proceedings of the International Conference on Advances in Mechanical Engineering and Industrial Informatics
PB  - Atlantis Press
SP  - 1373
EP  - 1379
SN  - 2352-5401
UR  - https://doi.org/10.2991/ameii-15.2015.253
DO  - 10.2991/ameii-15.2015.253
ID  - Ni2015/04
ER  -