Abstract: The effect of blade vibrations and unbalance force of propeller and the dynamic behavior of propeller shaft-support system are taken into consideration to imporve the accuracy of prediction of the maximum fly speed of a turbo-propeller plane limited by onset of propeller flutter whirl. Vibrations of the blade are expressed in truncated model coordinates of coupled bending-torsion virbration modes. Effecl on flutter whirl of the complicated propeller shaft-support system is considered by use of the experimental dynamic complex stiffness matrix at the flange mounting of propeller. Based on this improved model, governing equations of a parameter time-dependent system excited by unbalance force and nonlinear aeroelastic force are derived. To slove the equations the time domain integration method is employed. Onset of instability is determined by the obtained orbit. A model propeller for analysis and experiment is designed and prepared. Numerical analysis and tunnel test of the model propeller rotor are made. Results of calculation coincide with experiment pretty well. The analysis method presented in this paper is successful and accurate.

Key words: Turbo-propeller plane, rotor stability, propeller vibration