AEROELASTIC STABILITY OF HINGELESS ROTOR BLADE IN HOVER USING LARGE DEFLECTION THEORY

Cited 27 time in webofscience Cited 0 time in scopus
  • Hit : 575
  • Download : 5
The coupled flap-lag-torsion aeroelastic stability of a hingeless rotor blade in hover is investigated using finite elements based on large deflection beam theory. The finite element equations of motion for beams arbitrary large displacements and rotations, but small strains, are obtained from Hamilton's principle. The stability boundary is calculated assuming blade motions to be small perturbations about the nonlinear steady equilibrium deflections, which are obtained through an iterative Newton-Raphson method. The p-k modal flutter analysis based on coupled rotating natural modes is used. Various unsteady two-dimensional strip theories am used to evaluate 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 previous moderate deflection type theories.
Publisher
AMER INST AERONAUT ASTRONAUT
Issue Date
1994-07
Language
English
Article Type
Article
Keywords

NONLINEAR-ANALYSIS; BEAMS

Citation

AIAA JOURNAL, v.32, no.7, pp.1472 - 1477

ISSN
0001-1452
URI
http://hdl.handle.net/10203/6271
Appears in Collection
AE-Journal Papers(저널논문)
Files in This Item
This item is cited by other documents in WoS
⊙ Detail Information in WoSⓡ Click to see webofscience_button
⊙ Cited 27 items in WoS Click to see citing articles in records_button

qr_code

  • mendeley

    citeulike


rss_1.0 rss_2.0 atom_1.0