Tiltrotor controlled by double-propeller vertical duct

Abstract

The invention provides a tiltrotor controlled by a double-propeller vertical duct. The tiltrotor, using the design of parallel twin-rotor and conventional aerodynamic configuration, consists of a fuselage, straight wings, rotors, a nacelle, an aileron, a vertical empennage, a rudder, an elevator, a horizontal empennage, a duct end cover, a vertical duct, an undercarriage, a power and decelerationsystem, a propeller power input shaft, a lower propeller, an upper propeller, louver-type slipstream sheets, a propeller gearing and collective-pitch controlling device, a propeller gear box supporting structure, a duct end cover driving device, a duct end cover motion slide rail and a slipstream sheet controlling device. Compared with the cyclic pitch control mode, the tiltrotor of the inventionsimplifies the operations during the vertical flight and the flight conversion and improves the reliability by using the structure of the double-propeller vertical duct to control the vertical flightand the conversion of the flight mode, and the tiltrotor has the advantages of long control force arm, high control efficiency and simple structure. Therefore, the tiltrotor constitutes a novel aircraft with significant development potential and promising future.

Description

(1) Technical field [0001] The invention relates to a tilt-rotor aircraft, in particular to a tilt-rotor aircraft controlled by a double-propeller vertical duct, and belongs to the technical field of aviation vehicle design. (2) Background technology [0002] A tiltrotor aircraft combines features of a helicopter and a fixed-wing aircraft. Compared with fixed-wing aircraft, this type of aircraft can take off and land vertically, without relying on the airport runway, and can achieve hovering and low-speed forward flight; compared with traditional helicopters, tilt-rotor aircraft have greater cruising speed and range , the lift generated by the wings in the cruising process is more economical than the helicopter, so this kind of aircraft has been widely concerned since its birth. The earliest and most systematic research on tilt rotor aircraft is the United States. After decades of research, demonstration and testing, the United States has developed the V22, a representative...

AI Technical Summary

Problems solved by technology

[0009] It can be seen from the control method of the tiltrotor aircraft represented by the V22 to control the vertical flight and switch the flight mode by periodic pitch change that all attitude control is based on periodic control when the efficiency of the aircraft control rudder surface is insufficient. Variable distance to control, the control method is complex

When using cyclic pitch control to control the longitudinal attitude, it will cause the coupling effect of the aircraft flying forward

Moreover, the structure of the periodic variable pitch mechanism is complex, and the complex structure and control methods are detrimental to the safety and reliability of the tilt rotor aircraft.

At the same time, the attitude of the aircraft is controlled by the periodic pitch change method. Due to the short arm of the control force, the efficiency of generating the control torque is not high.

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