Modal and Aeroelastic Analysis of A High-Aspect-Ratio Wing with Large Deflection Capability
This paper describes a modified structural dynamics model for aeroelastic analysis of high-aspect-ratio wings undergoing large deformation behavior. To gain this aim, a moderate deflection beam model is modified with some important large deflection terms and then coupled with a state space unsteady...
| Main Authors: | , , |
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| Format: | Article |
| Language: | English |
| Published: |
Islamic Azad University-Isfahan (Khorasgan) Branch
2015-03-01
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| Series: | International Journal of Advanced Design and Manufacturing Technology |
| Subjects: | |
| Online Access: | https://admt.isfahan.iau.ir/article_534915_1b27d7674d1a0bf8429c62ae18632df5.pdf |
| Summary: | This paper describes a modified structural dynamics model for aeroelastic analysis of high-aspect-ratio wings undergoing large deformation behavior. To gain this aim, a moderate deflection beam model is modified with some important large deflection terms and then coupled with a state space unsteady aerodynamics model. Finite element method is used to discretize the equations of motion. A dynamic perturbation equation about a nonlinear static equilibrium is applied to determine the flutter boundary. The obtained results show good agreement in comparison with the other existing data such as high-altitude long-endurance (HALE) wing and Goland wing. It is found that the present aeroelastic tool have a good agreement in comparison with valid researches and also considering the effect of the geometric structural nonlinearity and higher order nonlinear terms on the flutter boundary determination is very significant. |
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| ISSN: | 2252-0406 2383-4447 |