| タイトル | Static aeroelastic analysis of composite wing |
| 著者（英） | Lee, IN; Hong, Chang Sun; Kim, Seung KO; Miura, Hirokazu |
| 著者所属（英） | NASA Ames Research Center; Korea Advanced Inst. of Science and Technology |
| 発行日 | 1990-01-01 |
| 言語 | eng |
| 内容記述 | A static aeroelastic analysis capability that can predict aerodynamic loads for the deformed shape of the composite wing has been developed. The finite element method (FEM) was used for composite plate structural analysis, and the linear vortex lattice method (VLM) was used for steady aerodynamic analysis. The final deformed shape of the wing due to applied forces is determined by iterative manner using FEM and VLM. FEM and VLM analysis are related by a surface spline interpolation procedure. The wing with Gr/Ep composite material has been investigated to see the wing deformation effect. Aerodynamic load change due to wing flexibility has been investigated. Also, the effect of fiber orientation and sweep angle on the deformation pattern and aerodynamic coefficients are examined. For a certain fiber orientation, the deflection and aerodynamic loading of the composite wing is very much reduced. The swept forward wing has more significant effect of wing flexibility on aerodynamic coefficient than the swept back wing does. |
| NASA分類 | AIRCRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 91A24365 |
| 権利 | Copyright |
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