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http://dx.doi.org/10.5050/KSNVN.2004.14.8.734

Use of Composite Tailoring Techniques for a Low Vibration Rotor  

이주영 (한국항공우주연구원 스마트무인기 기술개발사업단)
박일주 (전북대학교 대학원 항공우주공학)
정성남 (전북대학교 기계항공시스템공학부)
Publication Information
Transactions of the Korean Society for Noise and Vibration Engineering / v.14, no.8, 2004 , pp. 734-740 More about this Journal
Abstract
In this work, the effect of composite couplings and mass distributions on hub loads of a hingeless rotor in forward flight is investigated. The hingeless composite rotor is idealized as a laminated thin-walled box-beam. The nonclassical effects such as transverse shear and torsion warping are considered In the structural formulation. The nonlinear differential equations of motion are obtained by applying Hamilton’s principle. The blade responses and hub loads are calculated using a finite element formulation both in space and time. The aerodynamic forces acting on the blade are calculated using the quasi-steady strip theory. The theory includes the effects of reversed flow and compressibility. The magnitude of elastic couplings obtained by MSC/NASTRAN is compared with the classical pitch-flap($\delta$$_3$) coupling. It Is observed that the elastic couplings and mass distributions of the blade have a substantial effect on the behavior of $N_{b}$ /rev hub loads. About 40％ hub loads is reduced by tailoring or redistributing the structural properties of the blade.e.
Keywords
Hingeless Rotor; Composite Tailoring; Elastic Couplings; $N_{b}$ / rev Hub Loads; Mass Distribution;
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