A tilt-powered six-rotor electric vertical take-off and landing aircraft using wingtip slipstream rudders

Abstract

A tilt-powered six-rotor electric vertical take-off and landing aircraft using a wingtip slipstream rudder comprises a fuselage, an aircraft main wing, an aircraft horizontal tail, an aircraft canard, a propeller, a tilt-propeller nacelle and a tilt mechanism; the aircraft main wing is arranged in the middle of the fuselage, and the aircraft horizontal tail and the aircraft canard are arranged at the head and tail of the fuselage respectively; the wing tips of the aircraft main wing, the aircraft horizontal tail and the aircraft canard are all provided with a tilt-propeller nacelle, each tilt-propeller nacelle is provided with a propeller and a short wing with a slipstream rudder, the tilt mechanism is arranged inside the tilt-propeller nacelle, the output end of the tilt mechanism is connected to the wing tip, and the tilt mechanism drives the tilt-propeller nacelle to rotate in two positions, horizontally and vertically. The tilt mechanism of the present invention is fixedly connected to the engine nacelle, and the tilt mechanism is arranged in the engine nacelle, so there is no need to arrange other structures on the aircraft wing, so that the overall structure of the aircraft is simple and efficient, and the maintenance of the tilt mechanism is convenient.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft, and in particular relates to a tilt-powered six-rotor electric vertical take-off and landing aircraft adopting a wingtip slipstream rudder. Background Art

[0002] The widespread use of aerial vehicles will build a three-dimensional urban transportation network, effectively supplementing ground transportation and greatly alleviating the increasingly serious congestion problem in cities.

[0003] Urban aircraft need to adopt a vertical take-off and landing design to meet their take-off and landing requirements in the small spaces of the city. The key indicators to focus on are safety, noise level and clean energy use. Currently existing urban aircraft mostly use multi-rotor, fixed-wing or hybrid layout designs with distributed electric propulsion.

[0004] In the design of vertical take-off and landing aircraft, the tilt mechanism of the engine nacelle is crucial. Usually, the tilt mechanism requires additional design of the aircraft's wing structure to accommodate the placement of the tilt mechanism. This makes the tilt-rotor aircraft usually complex in structure and inconvenient to maintain. Summary of the invention

[0005] The purpose of the present invention is to provide a tilt-rotor powered six-rotor electric vertical take-off and landing aircraft using wingtip slipstream rudders, so as to solve the problem that tilt-rotor aircraft are usually complex in structure and inconvenient to maintain.

[0006] To achieve the above object, the present invention adopts the following technical solutions:

[0007] A tilt-powered six-rotor electric vertical take-off and landing aircraft using wingtip slipstream rudders comprises a fuselage, an aircraft main wing, an aircraft horizontal tail wing, an aircraft canard wing, a propeller, a tilt-propeller nacelle and a tilt mechanism; the aircraft main wing is arranged in the middle of the fuselage, and the aircraft horizontal tail wing and the aircraft canard wing are arranged at the head and tail of the fuselage respectively; the wing tips of the aircraft main wing, the aircraft horizontal tail wing and the aircraft canard are all provided with tilt-propeller nacelles, each tilt-propeller nacelle is provided with a propeller, the tilt mechanism is arranged inside the tilt-propeller nacelle, the output end of the tilt mechanism is connected to the wing tip, and the tilt mechanism drives the tilt-propeller nacelle to rotate in both horizontal and vertical positions.

[0008] Furthermore, the tilting mechanism includes an electric motor, a gear reducer, a worm gear mechanism, an angle monitoring device and a rotating shaft; the output end of the electric motor is connected to the gear reducer, the output end of the gear reducer is connected to the worm of the worm gear mechanism, the worm drives the worm wheel to rotate, the worm wheel is arranged on the rotating shaft, and the angle monitoring device is coaxially arranged on the side of the worm wheel; the rotating shaft is connected to the tip of the wing.

[0009] Furthermore, the angle monitoring device includes an angular displacement sensor, a gear and a driven wheel; the angular displacement sensor is arranged in the tilt propeller nacelle, the gear is arranged on the rotating shaft, the gear is connected to the driven wheel through a belt, and the driven wheel is arranged on the angular displacement sensor.

[0010] Furthermore, the tilt mechanism is fixed in the tilt propeller nacelle through a supporting structure, and the motor, the angular displacement sensor and the rotating shaft are all fixed on the supporting structure.

[0011] Furthermore, the installation positions of the aircraft canard, the aircraft main wing and the aircraft horizontal tail are not on the same horizontal plane, and the horizontal heights increase in the order of the aircraft canard, the aircraft main wing and the aircraft horizontal tail. The propeller planes of each wing are staggered from each other, and the projection surfaces of the propellers of each wing do not overlap.

[0012] Furthermore, a vertical tail fin is disposed at the tail of the fuselage, and a horizontal tail fin is vertically disposed on the vertical tail fin. The vertical tail fin and the horizontal tail fin form a T-shaped tail fin of the aircraft.

[0013] Furthermore, the outer side surface of each tilt-propeller nacelle is provided with a short wing stabilizer of a slipstream rudder surface.

[0014] Furthermore, a slipstream control surface is provided at the tail end of the short wing stabilizer of the slipstream control surface.

[0015] Furthermore, the slipstream control surface is connected to the short wing stabilizer of the slipstream control surface through a rotating shaft, and the slipstream control surface can deflect around the short wing stabilizer of the slipstream control surface.

[0016] Furthermore, a propeller driving mechanism is provided in the tilt-propeller nacelle near the propeller.

[0017] Compared with the prior art, the present invention has the following technical effects:

[0018] The tilt mechanism of the present invention is fixedly connected to the engine nacelle, and the tilt mechanism is arranged in the engine nacelle, so there is no need to arrange other structures on the aircraft wing, so that the overall structure of the aircraft is simple and efficient, and the tilt mechanism is convenient for maintenance.

[0019] The present invention uses a turbine worm gear mechanism to enable the engine nacelle to achieve self-locking at any angle relative to the wing, and no accidental rotation occurs between the engine nacelle and the wing due to external loads.

[0020] The pulley coaxially arranged with the worm gear and driven in reverse can measure the angle of rotation of the engine nacelle relative to the wing by driving the angular displacement sensor, so that the rotation angle of the engine nacelle can be accurately controlled.

[0021] The six-rotor of the present invention has no overlapping of the projected areas of the propeller discs in the arrangement during vertical take-off and landing and level flight, thereby ensuring the maximum efficiency of the rotor.

[0022] The three-wing aerodynamic layout of the present invention does not require major adjustments to the aircraft layout when the load capacity needs to be increased, and has good scalability.

[0023] The slipstream control surface of the present invention has a rudder effect in any state, can directly participate in the attitude control of the aircraft, and unload the tilt mechanism, thereby improving flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 Front view of level flight;

[0025] Figure 2 Top view of vertical take-off and landing state;

[0026] Figure 3 Illustration of three-wing layout;

[0027] Figure 4 Schematic diagram of slipstream control surface;

[0028] Figure 5 Cross-sectional view of the nacelle tilting mechanism;

[0029] in:

[0030] 1 is an aircraft propeller, 7 is an aircraft front wing, 8 is an aircraft main wing, 9 is an aircraft horizontal tail, 10 is an aircraft vertical tail, 11 is a fuselage, 12 is a tilt propeller nacelle, 13 is a short wing stabilizer of a slipstream control surface, 14 is a slipstream control surface, 15 is a worm gear mechanism, 17 is a rotating shaft, 18 is an angular displacement sensor, 19 is a gear, 20 is a driven wheel, 21 is a supporting structure, 22 is an electric motor, and 23 is a gear reducer. DETAILED DESCRIPTION

[0031] The present invention is further described below in conjunction with the accompanying drawings:

[0032] See also Figures 1 to 5 The present invention adopts a three-wing aerodynamic layout, that is, the aircraft has three sets of wings, namely, a front wing, a main wing, and a tail wing. The three sets of wings are arranged from low to high in the direction from the nose to the tail.

[0033] The three-wing tiltable six-rotor configuration has a tilting propeller nacelle located symmetrically on both sides of the wingtips of the three sets of wing surfaces. During vertical takeoff and landing, the rotor thrust is in the vertical direction, and during horizontal cruising flight, the rotor thrust is converted to the horizontal direction.

[0034] The tilting nacelle has a slipstream rudder design, that is, each tilting power nacelle has a short wing surface and a rudder is arranged at the trailing edge.

[0035] The aircraft has a total of 6 propellers. In level flight and vertical takeoff, the propeller planes of the aircraft are staggered from each other, and there is no large area overlap on the projection surface. Figure 3 , where 7 is the front wing of the aircraft, 8 is the main wing of the aircraft, 9 is the horizontal tail of the aircraft, 10 is the vertical tail of the aircraft, and 11 is the fuselage. 7, 8, and 9 are arranged from front to back and from low to high in order to prevent interference between each other. The propellers are installed at the tips of the three wing surfaces. 10 and 9 form the T-shaped tail of the aircraft. When the number of passengers or cargo needs to be increased, it is only necessary to increase the fuselage 11 and enlarge and increase the distance between 7, 8, and 9 at the same time. Figure 4 As shown, 12 is a tilt propeller nacelle, a rotating shaft is arranged at the position 12, driving the propeller nacelle to rotate in two positions horizontally and vertically, 13 is a short wing stabilizer of a slipstream control surface, installed on the outside of each engine nacelle, 14 is a slipstream control surface, installed on the trailing edge of the short wing, can be deflected, and is continuously affected by the propeller slipstream during flight.

[0036] like Figure 5 The figure shows a schematic diagram of the installation of the tilting nacelle and the wing tip, wherein 17 is a rotating shaft, 12 is a tilting propeller nacelle, and 1 is a propeller. The present invention is a mechanism arranged in the tilting propeller nacelle 12, fixedly connected to the structure of the tilting propeller nacelle 12, and driving the engine nacelle to rotate relative to the wing through the rotating shaft 17. After the engine nacelle shell is cut open, 21 is a supporting structure in the tilting propeller nacelle 12, and the tilting mechanism body is fixedly connected to the structure 21.

[0037] The operating principle of the tilt mechanism is described below: First, after the motor 22 is connected to the driving current, it outputs a high-speed, low-torque driving force, which is reduced to a low-speed, high-torque driving force through the gear reducer 23 and drives the worm in the worm gear mechanism 15 to rotate. The worm drives the turbine to further reduce the speed and drive the engine nacelle to rotate relative to the wing fixed point. At the same time, a gear 19 is designed coaxially with the turbine in the worm gear mechanism. The gear 19 drives the driven wheel 20 through a pulley transmission. An angular displacement sensor 18 is installed at the driven wheel to measure the angle of rotation of the driven wheel 20. The transmission ratio between the driven wheel 20 and the gear 19 is a fixed value. The angle of rotation of the engine nacelle relative to the wing can be calculated through the transmission ratio.

Claims

1. A tilt-powered six-rotor electric vertical take-off and landing aircraft using wingtip slipstream rudders, characterized in that: The invention comprises a fuselage (11), an aircraft main wing (8), an aircraft horizontal tail wing (9), an aircraft canard wing (7), a propeller (1), a tilting propeller nacelle (12) and a tilting mechanism; the aircraft main wing (8) is arranged at the middle part of the fuselage (11), the aircraft horizontal tail wing (9) and the aircraft canard wing (7) are arranged at the head and tail of the fuselage respectively; the wing tips of the aircraft main wing (8), the aircraft horizontal tail wing (9) and the aircraft canard wing (7) are all provided with tilting propeller nacelles (12), each tilting propeller nacelle (12) is provided with a propeller (1), the tilting mechanism is arranged inside the tilting propeller nacelle (12), the output end of the tilting mechanism is connected to the wing tip, and the tilting mechanism drives the tilting propeller nacelle (12) to rotate in two positions, horizontal and vertical. The outer side surface of each tilt propeller nacelle (12) is provided with a short wing stabilizer (13) of a slipstream control surface, and the tail end of the short wing stabilizer (13) of the slipstream control surface is provided with a slipstream control surface (14); Among them, the slipstream control surface has a steering effect in any state and unloads the tilting mechanism.

2. The tilt-powered six-rotor electric vertical take-off and landing aircraft using wingtip slipstream rudders according to claim 1, characterized in that: The tilt mechanism comprises an electric motor (22), a gear reducer (23), a worm gear mechanism (15), an angle monitoring device and a rotating shaft (17); the output end of the electric motor (22) is connected to the gear reducer (23), the output end of the gear reducer (23) is connected to the worm of the worm gear mechanism (15), the worm drives the worm wheel to rotate, the worm wheel is arranged on the rotating shaft (17), and the angle monitoring device is coaxially arranged on the side of the worm wheel; the rotating shaft (17) is connected to the tip of the wing.

3. The tilt-powered six-rotor electric vertical take-off and landing aircraft using wingtip slipstream rudders according to claim 2, characterized in that: The angle monitoring device comprises an angular displacement sensor (18), a gear (19) and a driven wheel (20); the angular displacement sensor (18) is arranged in a tilt propeller nacelle (12), the gear (19) is arranged on a rotating shaft (17), the gear (19) is connected to the driven wheel (20) via a belt, and the driven wheel (20) is arranged on the angular displacement sensor (18).

4. The tilt-powered six-rotor electric vertical take-off and landing aircraft using wingtip slipstream rudders according to claim 3, characterized in that: The tilt mechanism is fixed in the tilt propeller nacelle (12) via a support structure (21), and the motor (22), the angular displacement sensor (18) and the rotating shaft (17) are all fixed on the support structure (21).

5. The tilt-powered six-rotor electric vertical take-off and landing aircraft using wingtip slipstream rudders according to claim 1, characterized in that: The installation positions of the aircraft canard (7), the aircraft main wing (8) and the aircraft horizontal tail (9) are not on the same horizontal plane, the horizontal heights increase in the order of the aircraft canard (7), the aircraft main wing (8) and the aircraft horizontal tail (9), the propeller planes of each wing are in a staggered state, and the projection planes of the propellers of each wing do not overlap.

6. The tilt-powered six-rotor electric vertical take-off and landing aircraft using wingtip slipstream rudders according to claim 1, characterized in that: An aircraft vertical tail (10) is arranged at the tail of the fuselage (11), and an aircraft horizontal tail (9) is vertically arranged on the aircraft vertical tail (10). The aircraft vertical tail (10) and the aircraft horizontal tail (9) form a T-shaped tail of the aircraft.

7. The tilt-powered six-rotor electric vertical take-off and landing aircraft using wingtip slipstream rudders according to claim 1, characterized in that: The slipstream control surface (14) is connected to the short wing stabilizer (13) of the slipstream control surface through a rotating shaft, and the slipstream control surface (14) can deflect around the short wing stabilizer (13) of the slipstream control surface.

8. The tilt-powered six-rotor electric vertical take-off and landing aircraft using wingtip slipstream rudders according to claim 1, characterized in that: A propeller driving mechanism is also provided in the tilt-propeller nacelle (12) at a position close to the propeller (1).

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