Tilt-rotor based on combination of four rotor wings and fixed wing

Abstract

The invention discloses a tilt-rotor based on combination of four rotor wings and a fixed wing. The tilt-rotor is structurally characterized in that a first rotor wing, a second rotor wing, a third rotor wing and a fourth rotor wing are divided into two groups which are respectively symmetrically mounted on the two sides of a tilt-rotor body by two shafts; (1, 2) is a front motor group; (3, 4) is a rear motor group; a middle wing is horizontally mounted on the tilt-rotor body and is vertical to the tilt-rotor body; backswept wings on the two sides are respectively mounted on the two sides of the middle horizontal wing at a backswept angle of 50 degrees. According to the tilt-rotor disclosed by the invention, the four rotor wings and the fixed wing are enabled to share a set of power system to realize vertical takeoff and landing, hovering and cruise level flying; the front and rear tilting motor groups (1, 2) and (3, 4) share a set of tilting device to realize synchronous tilting by a tilting drive shaft, thereby simplifying a tilting structure and improving the operability and stability of the tilt-rotor.

Description

technical field [0001] The invention relates to aircraft design technology, in particular to a tilt-rotor aircraft based on the combination of four rotors and fixed wings. Background technique [0002] Since the take-off and landing of fixed-wing aircraft are largely restricted by the site, a specific runway is often required for take-off and landing, and it cannot hover in the air, so it cannot perform some specific flight tasks. [0003] None of the four rotors of a traditional quadrotor aircraft can tilt forward or backward. On the one hand, when it realizes horizontal forward flight, the speed of the two rotors at the front end of the fuselage is required to decrease, while that at the rear end of the fuselage The speed of the two rotors increases, so that the lift difference due to the different speeds of the front and rear rotors will inevitably lead to the pitching motion of the fuselage, so that the aircraft's horizontal forward flight and vertical lift will affect e...

AI Technical Summary

Problems solved by technology

Most of the existing tilt-rotor aircraft are two-axis tilting, such as the MV-22 of the United States. The disadvantage of this type of tilt-rotor aircraft is that the load capacity of the aircraft is very limited during vertical take-off and landing, and the two-rotor aircraft is relatively unstable when flying

At the same time, the existing tilting rotorcraft tilting mechanical structure is complex and the tilting process is not safe

It is precisely because of the above-mentioned shortcomings that the application of tilt-rotor aircraft is greatly limited

Images