Aeroelastic analysis of a hingeless rotor blade in forward flight

The aeroelastic response and stability of isotropic and composite rotor blades are investigated using a large de ection-type beam theory. The Ž nite element equations of motion for beams undergoing arbitrary large displacements and rotations,but small strains, are obtained fromHamilton’s principle. The sectional elastic constants of a composite box beam including warping deformations are determined from the reŽ ned cross-sectional Ž nite element method. The analysis is performed for a soft-in-plane hingeless rotor in free  ight propulsive trim. The nonlinear periodic blade steady response is obtained by integrating the full Ž nite element equation in time through a coupled trim procedure with a vehicle trim. After the coupled trim response is computed, the aeroelastic response is calculated through a time-marching solution procedure under small perturbations assumption, and then the stability analysis is performed by using a moving block analysis.Numerical results of rotating natural frequencies, blade response, and aeroelastic stability are presented. The results of the full Ž nite element analysis using the large de ection-type beam theory are quite different from those of a previously published modal analysis using the moderate de ection-type beam theory.
Publisher
American Institute of Aeronautics and Astronautics
Issue Date
2000-05
Citation

AIAA Journal, Vol.38, No.5, pp.843-850

ISSN
0001-1452
URI
http://hdl.handle.net/10203/6201
Link
http://www.aiaa.org/content.cfm?pageid=322&lupubid=2
Appears in Collection
AE-Journal Papers(저널논문)
  • Hit : 322
  • Download : 1
  • Cited 0 times in thomson ci

qr_code

  • mendeley

    citeulike


rss_1.0 rss_2.0 atom_1.0