An Aeroelastic Analysis Methodology for Bearingless Main Rotor Helicopters

摘要

A methodology for the aeroelastic analysis of bearingless main rotor helicopters in forward flight is presented. The large elas- tic twist experienced by the flexbeam during pitch control application can influence the nonlinear aeroelastic behavior. In- cluding its effects by eliminating the rigid pitch control rotation,θand using an angle, φ to represent the spanwise distribu- tion of cross-sectional torsional orientation would preclude the use of normal mode equations in the evaluation of blade periodic response in forward flight.