대변형 보이론을 사용한 힌지없는 로우터 블레이드의 유한요소 공탄성 해석Aeroelastic Analysis of a Hingeless Rotor Blade Using Finite Elements Based on Large Deflection Beam Theory

Cited 0 time in webofscience Cited 0 time in scopus
  • Hit : 392
  • Download : 0
The coupled flap-lag-torsion aeroelastic stability of a hingeless rotor blade in hover is investigated using finite elements based on the large deflection beam theory. The stability boundary of the blade is calculated assuming blade motions to be small perturbation about the nonlinear steady equilibrium deflections which are obtained through an iterative Newton-Raphson method. The p-k method is used for modal flutter analysis based on coupled rotating natural modes. Various unsteady 2-dimensional strip theories are used to evaluated the aerodynamic loads. The sensitivity of the stability boundary to these aerodynamic assumptions is examined. Numerical results of the steady deflections and stability boundaries are presented for some representative blade configurations, and also compared with those given in the previous moderate deflection type theories.
Publisher
한국항공우주학회
Issue Date
1993-10
Language
Korean
Citation

한국항공우주학회지, v.21, no.5, pp.57 - 66

ISSN
1225-1348
URI
http://hdl.handle.net/10203/65276
Appears in Collection
AE-Journal Papers(저널논문)
Files in This Item
There are no files associated with this item.

qr_code

  • mendeley

    citeulike


rss_1.0 rss_2.0 atom_1.0