1997•38th Structures, Structural Dynamics, and Materials ConferenceRequires access
Modeling issues related to vibration prediction of a coupled rotor/fuselage system
Hyeonsoo Yeo, Inderjit Chopra, Hyeonsoo Yeo, Inderjit Chopra
Open publisher page 4 citations
Abstract
Coupled rotor/fuselage vibration model is formulated incorporating consistent structural, aerodynamic and inertial coupling effects. The elastic line model of the AH-1G helicopter in conjunction with a typical 4-bladed hingeless rotor is used in the analysis. The coupled nonlinear, periodic equations of elastic rotor, elastic body and rigid body trim are solved using finite element methods in space and time. For calculation of inflow and blade loads, a pseudo-implicit free wake model and the time-domain unsteady aerodynamics are incorporated. Rotor/fuselage coupling effects usually increase oscillatory hub loads and these are significant at low and high advance ratios. Unsteady aerodynamics plays an important role at high advance ratio and free wake is essential in the prediction fuselage vibration at all forward speeds. CT rotor thrust coefficient