MATHEMATICAL MODEL AND NUMERICAL METHOD FOR FLAP-TORSIONAL FLUTTER ANALYSIS OF HELICOPTER MAIN ROTOR BLADE

摘要

We considered the mathematical model of coupled flap-torsional vibrations of a rigid rotor blade. The method for computing main rotor flutter characteristics in forward flight was proposed. We present the calculation results for a certain helicopter that was obtained both by the method developed and by the well-known method, based on the Floquet - Lyapunov theorem. By comparing the results it was shown that the method proposed is sufficiently accurate and needs considerably less computational time than the conventional approach.