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자동화된 공력ㆍ구조 연계 시스템을 이용한 소형항공기 날개 샌드위치구조 최적설계
박찬우(Chan Woo Park),추재명(Jae Myeong Chu),설창원(Chang Won Shul),전승문(Seung Moon Jun) Korean Society for Precision Engineering 2013 한국정밀공학회지 Vol.30 No.10
In this research, the design optimization of a composite sandwich has been performed for using as an airplane wing skin. Automated analysis framework for aero-structure interaction is used for calculating load data on the wing. For automated analysis framework, FLUENT is used for computational fluid dynamics (CFD) analysis. CFD mesh is generated automatically by using parametric modeling of CATIA and GAMBIT. A computational structure mechanics (CSM) mesh is generated automatically by the parametric method of the CATIA and visual basic script of NASTRAN-FX. The structure is analyzed by ABAQUS. Composite sandwich optimization is performed by NASTRAN SOL200. Design variables are thicknesses of the sandwich core and composite skin panel plies. The objective is to minimize the weight of the wing and constraints are applied for wing tip displacement, global failure index and local failure indexes.