Citation

Stumpf WM, Peters DA. Math. Comput. Model. 1993; 18(3-4): 115-129.

Copyright

(Copyright © 1993, Elsevier Publishing)

DOI

10.1016/0895-7177(93)90108-B

PMID

unavailable

Abstract

This article describes a model for aeroelastic loads on a rotor in forward flight, expressed in terms of a finite number of state variables, and incorporating advanced aerodynamic modeling. The model includes elastic flap, lag and torsion blade deformations, unsteady linear and stalled airloads, and an unsteady, higher harmonic inflow distribution, all described by ordinary differential equations for the state variables. These components, together with a set of autopilot trim equations, are coupled to describe a complete rotor, and are integrated in time until a periodic solution is reached. Model validation using airloads data gathered in flight tests are shown. Normal force predictions correlate fairly well, but pitching moment correlations are less successful, due to the sensitivity of the pitching moment.