Static aeroelastic analysis of composite wingA 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.
Document ID
19910039742
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lee, IN (Korea Advanced Inst. of Science and Technology Seoul (Republic of Korea)., United States)
Hong, Chang Sun (Korea Advanced Institute of Science and Technology Seoul, Republic of Korea, United States)
Miura, Hirokazu (NASA Ames Research Center Moffett Field, CA, United States)
Kim, Seung KO (Korea Advanced Inst. of Science and Technology Seoul (Republic of Korea)., United States)