The new-concept variable diameter tilt rotor (VDTR) which has a combined aerodynamic advantage of a large-diameter rotor in hovering flight and a small-diameter rotor in cruise flight represents a key developmental direction of the tilt rotor.

Modeling and analytical investigation on rotor/wing aerodynamic interaction for tiltrotor aircraft;

Calculated method and parametric effect investigation of wing download of tiltrotor aircraft;

Experiment on aeroelastic characteristics of tiltrotor aircraft in transition flight;

Multidisciplinary design optimization for aerodynamics/structural dynamics of tilt rotor blade;

Considering the operational characters of tilt rotor/propeller,a design method for tilt rotor/propeller is presented.

The new-concept variable diameter tilt rotor (VDTR) which has a combined aerodynamic advantage of a large-diameter rotor in hovering flight and a small-diameter rotor in cruise flight represents a key developmental direction of the tilt rotor.

<Abstrcat> In the present paper, the rotor wake of tilt-rotor aircraft is classified into the steady wake in hover and forward flight and the unsteady wake in transition flight, and a rotor free-wake analytical method for tilt-rotor aircraft has been developed based upon the Weissinger-L lifting-surface theory and rolled-up tip vortex model.

In this paper, the aerodynamic interactions between rotor/wing/ fuselage of tilt-rotor in hover and transition flight was calculated.

This thesis is aimed at the interaction aerodynamics problem on the rotor flowfield of a helicopter and a tilt-rotor aircraft by applying the rotor vortex theory and the panel method, and the major contributions of the author s research work are as follows:Based on the blade Weissinger-L model, rotor roll-up tip vortex model .

The parameter uncertainty in tiltrotor model caused by the variation of nacelle angle was considered in controller designing for flight mode conversion of tiltrotor.

The airplane mode s model of tiltrotor was founded.

The multi-body analysis of the aeroelastic stability of the tiltrotor aircraft is presented.

Dynamic stability analysis of tiltrotor aircraft in forward flight;

Considering the characteristics of the thrust vector/aerodynamic force multiple control for tiltrotor aircraft, this paper,based on the model of the tiltrotor aircraft, designs the flight control system using variable structure control with sliding mode.

In this paper the flight control system of tiltrotor aircraft is designed by using linear model following method to resolve the coupling of lateral channel.