A traction-propulsion tilting wing vertical take-off and landing manned aircraft

Abstract

The invention discloses a traction-propulsion vertical take-off and landing manned aircraft with tilting wings. The tiltable front wings are arranged on both sides of the front end of the fuselage, and the tiltable rear wings are mounted on both sides of the rear of the fuselage; The system includes a traction front propeller mounted on the front end of the fuselage by the tiltable front wing, and a pusher rear propeller set on the tiltable rear wing and located on both sides of the fuselage; the empennage is set at the tail of the fuselage ; The fuselage has space to accommodate at least two passengers and the operating system. The tail of the aircraft improves the stability and maneuverability of the aircraft in the transition phase of tilting and cruising; the multi-point symmetrical power layout composed of multi-rotors makes the aircraft have sufficient pitch and roll in the vertical take-off and landing and hovering states. The rotation balance margin improves the safety redundancy of the whole machine; the relatively independent tilting mechanism enables the aircraft to have stronger maneuverability in the vertical take-off and landing and hovering states; the rotor ring improves the propeller efficiency and the safety of the high-energy rotor sex.

Description

technical field [0001] The invention belongs to the field of tilting-wing aircraft, and in particular relates to a traction-propulsion type tilting-wing vertical take-off and landing manned aircraft. Background technique [0002] With the rapid development of battery energy density and power density and the application of related products, as well as the further increase of motor output power, the conditions of the era for the development and application of distributed electric power manned aircraft have become increasingly mature. As far as the field of distributed electric vertical take-off and landing manned aircraft is concerned, four types of layouts are currently known: multi-rotor, tilt-rotor, tilt-wing and compound. For multi-rotor aircraft such as patent CN206087301U, which need to adjust the flight attitude by controlling the propeller pitch, its attitude control efficiency is far inferior to that of aerodynamic rudder surfaces or even type vector power units. How...

AI Technical Summary

Problems solved by technology

[0005] At present, the single-wing tilting aircraft is still mainly traction type, and it is mainly an upper wing. Although there is a large adjustment margin in avoiding the threat range of the high-energy rotor, its high main wing makes the propeller on it vertically The take-off state hangs high above the whole machine, and the utilization rate of the ground effect is not ideal, which indirectly leads to greater energy consumption in the take-off state

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