Fixed-wing electric aircraft capable of vertically taking off and landing

Abstract

The invention provides a fixed-wing electric aircraft capable of vertically taking off and landing, which is characterized in that lifting force provided by a large-diameter vertical rotor wing (1) can bear the weight of the whole aircraft, two tilting small-diameter front rotor wings (3) mounted at two ends of a fixed main wing (21), two tilting small-diameter rear rotor wings (4) mounted at two ends of a horizontal tail wing (23), and a fixed main wing (22) mounted at two ends of the horizontal tail wing (23), the structural design is high in reliability, the large-diameter rotor wing is high in propelling efficiency, the motor power is reduced, and electricity is saved.

Description

Technical Field

[0001] The invention belongs to the technical field of vertical take-off and landing flight, and in particular relates to a technology of electric-driven fixed-wing flight capable of vertical take-off and landing. Technical Background

[0002] Current electric vertical takeoff and landing fixed aircraft, called eVTOL, generally use no less than four vertical rotor structures, regardless of primary or secondary, and tilt-rotor structures (the U.S. Osprey). This type of multi-rotor aircraft has low safety and reliability. As long as one of the rotors has a problem, it can cause an accident. The rotor diameter is small and the propulsion efficiency is low (i.e., high power consumption). When the Osprey-style tilt-rotor structure is converted from vertical flight to horizontal flight, and from horizontal flight to vertical landing, the two rotors not only have to provide sufficient vertical lift to balance the center of gravity, but also provide appropriate horizontal force, and the conversion process is prone to problems. Summary of the invention

[0003] The present invention is based on the above-mentioned problems and proposes a fixed-wing electric aircraft that can take off and land vertically. The lift provided by a large-diameter vertical rotor can bear the weight of the entire aircraft, and four tiltable small-diameter rotors installed at both ends of the fixed main wing and the horizontal wing are responsible for fine-tuning the center of gravity balance and horizontal flight thrust. This has high reliability and high propulsion efficiency of the large-diameter rotor.

[0004] The technical solution of the present invention is as follows: the aircraft includes: a vertical main rotor, a fuselage, a fixed main wing, a horizontal tail, a front rotor, and a rear rotor. The vertical main rotor is equipped with a main wing shaft and a main shaft power cabin. The main shaft power cabin contains a motor. The front rotor and the rear rotor adopt a tilting structure and are equipped with a front wing motor and a rear wing motor respectively. The features are:

[0005] The two tiltable front rotors are respectively arranged at the two ends of the fixed main wing, located in the front side of the fixed main wing, and can be continuously tilted between the horizontal direction and the upward direction, and the direction of the pulling force generated can be continuously changed between the horizontal and vertical directions; the two tiltable rear rotors are respectively arranged at the two ends of the horizontal tail wing, and the direction of the force (thrust or pulling force) generated can be continuously changed between the horizontal and vertical directions. The main shaft power compartment is arranged on the upper side of the fuselage, and the main wing axis is located on the rear side of the connection line of the two front rotors.

[0006] The direction of horizontal flight in the present invention is forward. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] The following will clearly and completely describe the implementation of the present invention in conjunction with the drawings in the embodiments of the present invention. The described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0008] Figure 1 The present invention is a characteristic schematic diagram when hovering.

[0009] Figure 2 The figure is a characteristic schematic diagram of the present invention during horizontal flight.

[0010] Figure 3 This invention is Figure 2 The characteristic diagram of the time is shown in the top view.

[0011] Figure 4 The figure is a characteristic schematic diagram of the present invention during horizontal flight.

[0012] Figure 5 The present invention is a characteristic schematic diagram when hovering.

[0013] In the figure: 1, vertical main rotor, 11, main wing shaft, 12, main shaft power compartment, 2, fuselage, 21, fixed main wing, 22, vertical tail, 23, horizontal tail, 24, flaps, 3, front rotor, 31, front wing motor, 32, arrow, 4, rear rotor, 41, rear wing motor, 42, arrow, 51, front wing horizontal axis, 52, tail vertical axis. DETAILED DESCRIPTION

[0014] Figure 1 , 2 , 3 show the characteristics of the present invention, Figure 1 The aircraft is in a hovering state, or in a vertical take-off or landing state, as shown: the main wing shaft 11 is extended, the main shaft power cabin 12 is arranged on the upper side of the fuselage, and the main motor driving the main wing shaft 11 should be arranged in the main shaft power cabin 12. The front wing motor 31 directly drives the front rotor 3, and the arrow 32 indicates the tilting direction of the front rotor 3 and its front wing motor 31, and the front rotor 3 generates a vertical upward pulling force; the rear wing motor 41 directly drives the rear rotor 4 vertically downward, and generates a downward thrust, which acts on the upward force of the tail of the fuselage 2, and the arrow 42 indicates the tilting direction of the rear rotor 4 and its rear wing motor 41.

[0015] The lift provided by the vertical main rotor 1 should bear most of the total takeoff weight (including load) of the aircraft, at least 60%, reasonably should be no less than 80%, and better should be more than 90%. Figure 3As shown, the two front rotors 3 are respectively arranged at the two ends of the fixed main wing 21, located in front of the fixed main wing 21, the main wing axis 11 is located at the symmetrical center line of the fuselage 2, the rear side of the line connecting the two front rotors 3 (should be the rear side of the front wing horizontal axis 51), the vertical main rotor 1 bears most of the lift (even 100%), the two front rotors 3 and the rear rotor 4 bear part of the remaining lift, in the hovering state, it is more important to adjust the center of gravity balance, the main wing axis 11 is located in the middle of the fixed main wing 2, located at or near the vertical line of the center of gravity of the whole machine, so the center of gravity balance adjustment belongs to a small force adjustment. Only the two ends of the fixed main wing 21 are provided with the tiltable front rotor 3, and only the two ends of the horizontal tail 23 are provided with the tiltable rear rotor 4. These four rotors are sufficient to undertake the task of adjusting the center of gravity balance, and there is no need to add rotors.

[0016] Figure 2 , 3 The aircraft is in level flight, the vertical main rotor 1 stops working, the front rotor 3 generates a horizontal upward pull, and the rear rotor 4 generates a horizontal backward thrust. As shown in the figure, the vertical main rotor 1 adopts a foldable structure, one of the vertical main rotors 1 is foldable, and the two vertical main rotors 1 are folded together. Figure 3 The dotted vertical main rotor 1 in the figure shows the state when the two blades of the vertical main rotor 1 are unfolded. It is also shown that the main wing shaft 11 adopts a telescopic structure, and the main wing shaft 11 is retracted into the main shaft power cabin 12. The vertical main rotor should adopt a fixed installation angle structure, that is, there is no pitch-changing mechanism to adjust the angle of attack of the rotor, the structure is simple and reliable, and high propulsion efficiency can be obtained.

[0017] Figures 1 to 3 It is shown that only the front rotor 3 and its front wing motor 31 are tilted with the front wing horizontal axis 51 as the axis, and the main wing 2 is fixed and immovable. Of course, the main wing 21 and the front wing motor 31 can be partially fixed and tilted integrally to adjust the pulling direction of the front rotor 3. It is also shown that a vertical tail 22 is provided, and a horizontal tail 23 is installed on the vertical tail 22. The horizontal tail 23 is fixed integrally with the rear wing motor 41 and tilted with the rear wing vertical axis 52 as the axis to adjust the force direction of the rear rotor 4 (shown as downward and backward in the figure), and the two rear rotors 4 can be tilted synchronously (the tilt angle is consistent). The battery should be set in the fuselage 2, and it is reasonable that the battery should be set on the lower side of the fuselage 2. Figure 3 It is shown that the fixed main wing 21 includes flaps 24 .

[0018] Figure 4 As shown, the rear of the main wing shaft 11 on the upper side of the fuselage 2 adopts a structure parallel to the vertical main rotor 1. When the vertical main rotor 1 is folded, it fits with the upper side of the fuselage 2. Figure 4 Shown with Figure 2 The differences shown are also, Figure 4 There is no vertical tail.

[0019] Figure 5Shown with Figure 1 The differences shown are: Figure 5 In the figure, the rear rotor 4 is facing upwards, generating a pulling force, pulling the tail upwards, and the arrow 42 indicates the tilting direction.

[0020] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A fixed-wing electric aircraft capable of vertical take-off and landing, comprising: a vertical main rotor (1), a fuselage (2), a fixed main wing (21), a horizontal tail (23), a front rotor (3), and a rear rotor (4), wherein the vertical main rotor (1) is equipped with a main wing shaft (11) and a main shaft power cabin (12), the main shaft power cabin (12) contains a motor, the front rotor (3) and the rear rotor (4) adopt a tilting structure, and are respectively equipped with a front wing motor (31) and a rear wing motor (41), wherein: The two front rotors (3) are respectively arranged at the two ends of the fixed main wing (21) and are located at the front side of the fixed main wing (21); the two rear rotors (4) are respectively arranged at the two ends of the horizontal tail (23); the main shaft power cabin (12) is arranged on the upper side of the fuselage; and the main wing shaft (11) is located at the rear side of the connection line of the two front rotors (3).

2. The aircraft according to claim 1, characterized in that: During vertical take-off, the vertical main rotor (1) bears a lift force of not less than 80% of the total take-off weight of the aircraft.

3. The aircraft according to claim 1, characterized in that: A vertical tail wing (22) is provided, and a horizontal tail wing (23) is installed on the vertical tail wing (22).

4. The aircraft according to claim 1, characterized in that: The horizontal tail wing (23) and the rear wing motor (41) are fixedly integrated and tiltable.

5. The aircraft according to claim 1, characterized in that: The partially fixed main wing (21) and the front wing motor (31) are fixedly tilted as a whole.

6. The aircraft according to claim 1, characterized in that: The rear rotor (4) is located at the rear side of the horizontal tail (23).

7. The aircraft according to claim 1, characterized in that: The vertical main rotor (1) adopts a fixed installation angle structure.

8. The aircraft according to claim 1 or 2 or 3 or 4 or 5 or 6 or 7, characterized in that: The vertical main rotor (1) adopts a foldable structure.

9. The aircraft according to claim 1 or 2 or 3 or 4 or 5 or 6 or 7, characterized in that: The main wing shaft (11) adopts a telescopic structure.

10. The aircraft according to claim 1 or 2 or 3 or 4 or 5 or 6 or 7, characterized in that: The rear of the main wing shaft (11) on the upper side of the fuselage (2) adopts a structure parallel to the vertical main rotor (1), and when the vertical main rotor (1) is folded, it fits with the upper side of the fuselage.

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