Journal of KSNVE (소음진동)

The Korean Society for Noise and Vibration Engineering (한국소음진동공학회)
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A Parametric Investigation Into the Aeroelasticity of Composite Helicopter Rotor Blades in Forward Flight

전진비행시 복합재료 헬리콥터 회전익의 공탄성에 대한 파라미터 연구

  • 정성남 (전북대학교 우주항공공학과) ;
  • 김경남 (대한항공항공기술연구소) ;
  • 김승조 (서울대학교 항공우주공학과)
  • Published : 1997.10.01
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Abstract

The finite element analyses of a composite hingeless rotor blade in forward flight have been performed to investigate the influence of blade design parameters on the blade stability. The blade structure is represented by a single cell composite box-beam and its nonclassical effects such as transverse shear and torsion-related warping are considered. The nonlinear periodic differential equations of motion are obtained by moderate deflection beam theory and finite element method based on Hamilton principle. Aerodynamic forces are calculated using the quasi-steady strip theiry with compressibility and reverse flow effects. The coupling effects between the rotor blade and the fuselage are included in a free flight propulsive trim analysis. Damping values are calculated by using the Floquet transition matrix theory from the linearized equations perturbed at equilibrium position of the blade. The aeroelastic results were compared with an alternative analytic approch, and they showed good correlation with each other. Some parametric investigations for the helicopter design variables, such as pretwist and precone angles are carried out to know the aeroelastic behavior of the rotor.

Keywords

References

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