Selection and Performance Evaluation of Overall Parameters for Rotors in Foldable Tilt-Rotor Aircraft

Based on tilt-rotor technology, the foldable tilt-rotor aircraft employs an axial-fan conversion engine. By transitioning from rotor stalling and folding in propeller airplane mode to engine mode switching, it transforms into a turbofan jet aircraft capable of high subsonic or even supersonic flight. This aircraft combines vertical takeoff and landing capabilities, efficient hovering, and high subsonic cruise performance. Focusing on an assumed mission profile that encompasses five flight modes, this paper employs an iterative algorithm to estimate the overall design weight of the aircraft and conduct the design of the overall parameters for the foldable tilt-rotor. Furthermore, based on the momentum-blade element combination theory, the aerodynamic performance at three critical design points of the foldable tilt-rotor is analyzed and evaluated, including hover efficiency, propulsion efficiency, and negative thrust in autorotation. Additionally, the aerodynamic characteristics during the rotor stalling process are analyzed and evaluated, providing valuable references for the design of foldable tilt-rotors.