Unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle which comprises a vehicle body, a fixed wing and four linear supporting pieces. Wherein the fixed wing comprises a left main wing and a right main wing, and the left main wing and the right main wing are symmetrically arranged along the central axis of the fuselage and connected to the two sides of the fuselage correspondingly; the four linear supporting pieces comprise the first linear supporting piece, the second linear supporting piece, the third linear supporting piece and the fourth linear supporting piece which are parallel to the central axis of the fuselage, the first linear supporting piece is connected to the left canard and the portion, close to the left main wing of the fuselage, of the left canard, and the second linear supporting piece is connected to the right canard and the portion, close to the right main wing of the fuselage, of the right canard. The third and fourth linear support pieces are respectively connected to the parts of the left and right main wings far away from the fuselage; the left main wing and the right main wing sweep backwards at the same time so as to adjust the position of the lift center of the unmanned aerial vehicle.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a unmanned aerial vehicle. Background Art

[0002] The size of existing transport drones is generally relatively large, which causes the center of mass of the entire machine to be relatively backward, affecting the static stability of the entire machine during flight. Therefore, it is necessary to adjust the angle of the drone's wings to adjust the position of the drone's lift center. Summary of the invention

[0003] An object of the present invention is to provide a drone with improved flight performance.

[0004] To achieve this object, the present invention adopts the following technical solutions:

[0005] A human-machine, comprising:

[0006] body;

[0007] The fixed wing comprises a left main wing and a right main wing, wherein the left main wing and the right main wing are symmetrically arranged along the central axis of the fuselage and are respectively connected to two sides of the fuselage;

[0008] Four linear supports, the four linear supports include a first, a second, a third, and a fourth linear support, the first, the second, the third, and the fourth linear support are parallel to the fuselage centerline, the first linear support is connected to the left canard and the portion of the left main wing close to the fuselage, the second linear support is connected to the right canard and the portion of the right main wing close to the fuselage, and the third and fourth linear supports are respectively connected to the portions of the left main wing and the right main wing away from the fuselage;

[0009] The left main wing and the right main wing are swept back simultaneously to adjust the position of the lift center of the UAV.

[0010] Preferably, the left main wing comprises a leading edge, wherein the leading edge comprises an inner leading edge close to the fuselage and an outer leading edge away from the fuselage, and the sweep angles of the inner leading edge and the outer leading edge are inconsistent.

[0011] Preferably, the right main wing comprises a trailing edge, wherein the trailing edge comprises an inner trailing edge close to the fuselage and an outer trailing edge away from the fuselage, and the sweep angles of the inner trailing edge and the outer trailing edge are consistent.

[0012] Preferably, the inner leading edge sweep angle is 8° to 15°, and the outer leading edge sweep angle is 15° to 21°.

[0013] Preferably, the sweep angles of the inner trailing edge and the outer trailing edge are 2° to 10°.

[0014] Preferably, the center of gravity of the UAV is closer to the canard than the lift center, so that the UAV is in a statically stable state during flight.

[0015] Preferably, the center of gravity is located ahead of the lift center by a distance of 5% to 15% of the average aerodynamic chord length.

[0016] Preferably, the sweep angle of the inner leading edge is smaller than the sweep angle of the outer leading edge, so as to increase the chord length of the leading edge and improve the rigidity of the linear support.

[0017] Preferably, the center of gravity of the UAV ranges from 2% to 25% of the average aerodynamic chord length.

[0018] Preferably, the inner leading edge, the outer leading edge, the inner trailing edge and the outer trailing edge together form the fixed wing.

[0019] Beneficial effects of the present invention:

[0020] The present invention sets a certain sweep angle on the leading and trailing edges of the main wings of the UAV to adjust the lift center of the whole machine, and places the adjusted lift center behind the center of gravity of the whole machine and at a position 5% to 15% of the average aerodynamic chord length, thereby achieving the purpose of balancing the center of gravity before the aircraft takes off and realizing static stability of the whole machine during flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 Schematic diagram of the overall UAV provided by the present invention. DETAILED DESCRIPTION

[0022] The technical solution of the present invention is further described below in conjunction with the accompanying drawings and implementation methods. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only the parts related to the present invention are shown in the accompanying drawings, rather than all of them.

[0023] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0024] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0025] In the description of this embodiment, the terms "upper", "lower", "right", etc., directions or positional relationships are based on the directions or positional relationships shown in the drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0026] like Figure 1 As shown, the invention of the present application generally depicts a drone, including: a fuselage, fixed wings, and four linear supports.

[0027] Specifically, the fixed wing includes a left main wing and a right main wing, the left main wing and the right main wing are symmetrically arranged along the central axis of the fuselage and are respectively connected to both sides of the fuselage;

[0028] The four linear supports include a first, a second, a third and a fourth linear support, wherein the first, the second, the third and the fourth linear support are parallel to the central axis of the fuselage, wherein the first linear support is connected to the left canard and the portion of the left main wing close to the fuselage, the second linear support is connected to the right canard and the portion of the right main wing close to the fuselage, and the third and the fourth linear support are respectively connected to the portions of the left main wing and the right main wing away from the fuselage;

[0029] In addition, the left main wing and the right main wing are swept back at the same time to adjust the position of the lift center of the UAV.

[0030] In the present application, a certain sweep angle is set on the leading and trailing edges of the main wings of the UAV, which can be used to adjust the lift center of the entire machine. The adjusted lift center is set behind the center of gravity of the entire machine and at a position that is 5% to 15% of the average aerodynamic chord length, thereby achieving the purpose of balancing the center of gravity and realizing static stability of the entire machine during flight.

[0031] The mean aerodynamic chord in this application specifically refers to the chord length of a certain airfoil at a certain distance from the centerline of the aircraft fuselage.

[0032] Further, in the present application, the left main wing includes a leading edge, and the leading edge further includes an inner leading edge 101 close to the fuselage and an outer leading edge 102 away from the fuselage. The sweep angles of the inner leading edge 101 and the outer leading edge 102 are inconsistent. This is because when the aircraft is flying, when the airflow velocity perpendicular to the leading edge of the wing is too fast, the airflow in a local area of ​​the upper surface of the wing is affected by the raised wing surface and a local shock wave appears, thereby sharply increasing the flight resistance. The swept wing can make the airflow velocity component perpendicular to the leading edge of the wing lower than the flight speed, thereby increasing the critical number of the wing and reducing the resistance during flight.

[0033] Likewise, the right main wing includes a trailing edge, which further includes an inner trailing edge 201 close to the fuselage and an outer trailing edge 202 away from the fuselage, and the sweep angles of the inner trailing edge 201 and the outer trailing edge 202 are consistent.

[0034] Preferably, in the present application, the sweep angle of the inner leading edge 101 is b, where b ranges from 8° to 15°, the sweep angle of the outer leading edge 102 is c, where c ranges from 15° to 21°, and the sweep angles of the inner trailing edge 201 and the outer trailing edge 202 are a, where a ranges from 2° to 10°.

[0035] Furthermore, in the present application, the center of gravity of the UAV is closer to the canard than the center of lift, so that the UAV is in a statically stable state during flight. Preferably, the center of gravity range of the UAV is set to 2% to 25% of the average aerodynamic chord length, and the position of the center of gravity is set before the center of lift, with an advance distance of 5% to 15% of the average aerodynamic chord length, thereby achieving the purpose of balancing the center of gravity and realizing static stability of the entire machine during flight.

[0036] In the figure, X is the position of the center of gravity and Y is the position of the center of lift.

[0037] Furthermore, in the present application, the sweep angle of the inner leading edge 101 is smaller than the sweep angle of the outer leading edge 102 , so as to increase the chord length of the leading edge and improve the rigidity of the linear support.

[0038] Exemplarily, in the present application, the inner leading edge 101, the outer leading edge 102, the inner trailing edge 201 and the outer trailing edge 202 of the drone together form the fixed wing of the drone.

[0039] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A drone, characterized in that: include: body; The fixed wing comprises a left main wing and a right main wing, wherein the left main wing and the right main wing are symmetrically arranged along the central axis of the fuselage and are respectively connected to two sides of the fuselage; Four linear supports, the four linear supports include a first, a second, a third, and a fourth linear support, the first, the second, the third, and the fourth linear support are parallel to the fuselage centerline, the first linear support is connected to the left canard and the portion of the left main wing close to the fuselage, the second linear support is connected to the right canard and the portion of the right main wing close to the fuselage, and the third and fourth linear supports are respectively connected to the portions of the left main wing and the right main wing away from the fuselage; The left main wing and the right main wing are swept back simultaneously to adjust the position of the lift center of the UAV.

2. The drone according to claim 1, characterized in that: The left main wing comprises a leading edge, wherein the leading edge comprises an inner leading edge close to the fuselage and an outer leading edge far away from the fuselage, and sweep angles of the inner leading edge and the outer leading edge are inconsistent.

3. The drone according to claim 2, characterized in that: The right main wing comprises a trailing edge, wherein the trailing edge comprises an inner trailing edge close to the fuselage and an outer trailing edge away from the fuselage, and the sweep angles of the inner trailing edge and the outer trailing edge are consistent.

4. The drone according to claim 2, characterized in that: The inner leading edge sweep angle is 8° to 15°, and the outer leading edge sweep angle is 15° to 21°.

5. The drone according to claim 3, characterized in that: The sweep angles of the inner trailing edge and the outer trailing edge are 2° to 10°.

6. The drone according to claim 1, characterized in that: The center of gravity of the UAV is closer to the canard than the lift center, so that the UAV is in a statically stable state during flight.

7. The drone according to claim 6, characterized in that: The center of gravity is located ahead of the center of lift by a distance of 5% to 15% of the average aerodynamic chord length.

8. The drone according to claim 3, characterized in that: The sweep angle of the inner leading edge is smaller than the sweep angle of the outer leading edge, so as to increase the chord length of the leading edge and improve the rigidity of the linear support.

9. The drone according to claim 1, characterized in that: The center of gravity of the drone ranges from 2% to 25% of the average aerodynamic chord.

10. The drone according to claim 3, characterized in that: The inner leading edge, the outer leading edge, the inner trailing edge and the outer trailing edge together form the fixed wing.

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