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Computational Structural Dynamic Analysis of a Gyrocopter Using CFD Coupled Method  

Kim Hyun-Jung (국립경상대학교 기계항공공학부 대학원)
Jung Se-Un (한국항공우주산업(주))
Park Hyo-Keun (국립경상대학교 기계항공공학부 대학원)
Yang Chang-Hak ((주)동해기계항공)
Kim Dong-Hyun (국립경상대학교 기계항공공학부 및 항공기 부품기술연구소)
Publication Information
Journal of the Computational Structural Engineering Institute of Korea / v.19, no.3, 2006 , pp. 295-302 More about this Journal
Abstract
In this study, computational structural dynamic analyses of a gyrocopter have been conducted considering unsteady dynamic hub-loads due to rotating blades. 3D CATIA models with detailed mechanical parts we constructed and virtually assembled into the complete aircraft configuration. The dynamic loading generated by rotating blades in the forward flight condition are calculated by a commercial computational fluid dynamics (CFD) code such as FLUENT. Modal based transient and frequency response analyses are used to efficiently investigate vibration characteristics of the gyrocopter. Free vibration analysis results for different fuel and pilot conditions, frequency responses and transient responses for critical flight conditions are also presented in detail.
Keywords
computational structural dynamics; gyrocopter; dynamic hub load; transient response analysis; frequency response analysis; FEM; CFD; CATIA;
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  • Reference
1 김동현 (2005), DAMBI 초경량 항공기 인증을 위한 설계 및 해석기법 연구, (주)동해기계학공 보고서
2 Bathe, K.J. (1996). Finite Element Procedures, Prentice-Hall. Inc
3 Caradona, F.X., Laub, G.H., Tung, C. (1984), An Experimental Investigation of the Parallel Blade-Vortex Interaction, NASA TM-86005
4 Herting, D.N. (1997), MSC/NASTRAN Advanced Dynamic Analysis: User's Guide. Ver.69, The MacNeal-Schwendler Corporation
5 Meirovitch, L. (1986). Elements of Vibrational Analysis, McGraw-Hill. 2nd Ed