Tiltrotor Whirl-flutter Stability Simulation Analysis Based On Actively LQR Control

A comprehensive aeroelastic analytical model of tilt rotor aircraft with flaperons for aeroelasticstability augmentation had been developed. The model was used to analyze the impact of theflaperons deflection on whirl flutter boundary of tilt rotor aircraft. The rotor/nacelle/wing of the tiltrotor aircraft was a typical of rigid-flexible coupled system, rotor and nacelle were rigid, while thewing was flexible body. Dynamic equation used in the analysis derived by Hamilton’s principle, theaccuracy and precision was secured through comparisons with BELL model test.Wing flaperons aerodynamic model of tilt rotor aircraft was established by the Theodorsenquasi-steady aerodynamic theory. Active control law was designed by the peculiarity of actively LQRcontrol as well as the angle restrained of the flaperons. Then modal damping of wing and the whirlflutter boundary had been got. By comparing the modal damping of the system between with wingflaperons and without wing flaperons, the actual effect for stability augmentation of this controlsystem had also been proved.Finally, sensitivity analysis for the main design parameters of the flaperons have been done, therelationship between these design parameters and the effects of theirs stability augmentations havealso been got. It was more important that the thesis had laid the foundation for the layout of tiltrotorswing with flaperons in further studies.