Citation

Fulton MV, Hodges DH. Math. Comput. Model. 1993; 18(3-4): 1-17.

Copyright

(Copyright © 1993, Elsevier Publishing)

DOI

10.1016/0895-7177(93)90101-4

PMID

unavailable

Abstract

A finite-element-based stability analysis is presented for isolated hingeless, composite rotor blades in the hovering flight condition. The formulation is comprised of separate, but compatible, cross-sectional (two-dimensional) and global or beam (one-dimensional) equations. The sectional analyses used account for all possible deformation in the three-dimensional representation of the blade. The global analysis is based on a mixed variational statement for the dynamics of moving beams; it can account for 6 6 cross-sectional stiffness and inertia matrices which, respectively, allow for the treatment of shear deformation and rotary inertia. There are no restrictions on the magnitudes of the displacements and rotations if the strain remains small compared to unity. The lift, drag, and pitching moment models are based on two-dimensional, quasi-steady strip theory, with induced inflow taken from momentum theory. The equilibrium operating configuration of the blade is obtained by an iterative solution of the complete nonlinear equations. The dynamic equations are linearized about this position, yielding an eigenproblem. In Part II, numerical results are presented for both extension-twist and bending-twist coupled rotor blades, which indicate that certain