Front wing for unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a front wing for an unmanned aerial vehicle, which comprises a front wing body used for being connected to a fuselage of the unmanned aerial vehicle, and further comprises a lifting aileron connected to the leeward side of the front wing body through a flexible connecting piece, the lifting aileron is used for being regulated and controlled by the lifting aileron control device to conduct pitching deflection, so that in the flight process of the unmanned aerial vehicle, the lifting aileron is regulated and controlled through the lifting aileron control device to conduct pitching deflection, and the flight attitude of the unmanned aerial vehicle is controlled. According to the unmanned aerial vehicle lifting aileron, the lifting aileron and the front wing body are flexibly connected through the flexible connecting piece, the flexible connecting piece limits the moving position of the lifting aileron, meanwhile, the connecting rigidity of the lifting aileron and the front wing body is weakened, and the operability of the unmanned aerial vehicle lifting aileron is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, concretely relates to a front wing for unmanned plane. BACKGROUND

[0002] During the flight of the unmanned plane, the up-down deflection of the elevators is needed to maintain the stability of the flight and adjust the flight posture of the micro unmanned plane. Because the size of the unmanned plane is limited, the overall structure is quite different from that of the traditional plane, the connecting structure of the existing elevators and the wings is large in size and heavy in weight, the rigidity of the connection between the elevators and the wings is large, which leads to poor operability of the elevators, and thus the operability of the elevators of the unmanned plane needs to be improved.

[0003] In the prior art, for example, the unmanned plane elevator driving structure of invention patent CN107097936B, in this patent, a connecting rod mechanism is used to drive the elevators to swing in cooperation with a servo, but the connecting rod mechanism cooperates with the servo to drive, which is large in structure size and heavy in weight, and the rigidity of the connection between the elevators and the wings of the unmanned plane is large, which leads to poor operability of the elevators.

[0004] Therefore, how to improve the operability of the elevators of the unmanned plane is a problem to be solved in this technical field. UTILITY MODEL CONTENT

[0005] In view of the deficiencies of the connecting structure of the existing elevators and wings, which is large in size and heavy in weight, and the rigidity of the connection between the elevators and the wings is large, leading to poor operability of the elevators, a front wing for unmanned plane is provided, which flexibly connects the elevators and the front wing body through a flexible connecting piece, limits the activity position of the elevators, and at the same time, reduces the rigidity of the connection between the elevators and the front wing body, thereby improving the operability of the elevators of the unmanned plane.

[0006] In order to achieve the above-mentioned utility model purposes, the utility model provides the following technical scheme:

[0007] A front wing for unmanned plane, comprising a front wing body, the front wing body is used for being connected on the fuselage of the unmanned plane, and further comprising:

[0008] Elevators, the elevators are connected on the leeward side of the front wing body through a flexible connecting piece, the elevators are used for being adjusted by an elevator control device to perform up-down deflection, so that, during the flight of the unmanned plane, the up-down deflection of the elevators is adjusted by the elevator control device, and the flight posture of the unmanned plane is controlled.

[0009] As a preferred embodiment, the flexible connecting piece is arranged as a flexible carbon fiber cloth, and the flexible carbon fiber cloth is connected between the elevators and the front wing body.

[0010] As a preferred embodiment, the flexible carbon fiber cloth is connected between the elevating aileron and the front wing body in the following manner:

[0011] One side of the flexible carbon fiber cloth is connected to the leeward side of the front wing body by flexible glue, and the other side of the flexible carbon fiber cloth is connected to the elevating aileron by flexible glue.

[0012] As a preferred embodiment, the length of the flexible carbon fiber cloth is equal to the length of the leeward side of the front wing body.

[0013] As a preferred embodiment, the length of the elevating aileron is equal to the length of the flexible carbon fiber cloth.

[0014] As a preferred embodiment, the elevating aileron is further provided with an adjusting contact plate protruding therefrom, which is used to eliminate the height difference caused by the stacking of the front wing bodies, so that the driving assembly of the elevating aileron control device is in contact with the adjusting contact plate to adjust the pitch and roll of the elevating aileron.

[0015] As a preferred embodiment, the width of the flexible carbon fiber cloth is 3-8 mm.

[0016] As a preferred embodiment, the thickness of the flexible carbon fiber cloth is 0.1-0.2 mm.

[0017] As a preferred embodiment, the front end of the front wing body is further provided with a connecting ring plate, which is used to rotate the front wing body and connect it to the body of the unmanned aerial vehicle, so that the front wing body can be unfolded or folded on the body of the unmanned aerial vehicle.

[0018] As a preferred embodiment, the leeward side of the front wing body is further provided with a clamping plate, which is used to be clamped with a V-shaped socket on the body, so that the clamping plate is clamped with the V-shaped socket to position and limit the unfolded position of the front wing body.

[0019] Compared with the prior art, the beneficial effects of the utility model are as follows:

[0020] The flexible connecting piece is used to flexibly connect the elevating aileron and the front wing body, limits the activity position of the elevating aileron, and reduces the connection rigidity of the elevating aileron and the front wing body, thereby improving the operability of the elevating aileron of the unmanned aerial vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiments, and it should be understood that the following drawings only show some embodiments of the present application, and therefore should not be regarded as limiting the scope, for those skilled in the art, without creative labor, other related drawings can also be obtained according to these drawings.

[0022] Figure 1 The structural schematic diagram of the present application is shown in the figure.

[0023] Figure 2 The partial enlarged view of the present application is shown in the figure.

[0024] Figure 3 The application schematic diagram of the present application is shown in the figure.

[0025] Figure 4 The explosion view of the driving assembly of the present application is shown in the figure. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical scheme and advantages of the embodiments of the present application more clear, the following will combine the drawings in the embodiments of the present application to clearly and completely describe the technical scheme in the embodiments of the present application, obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments.

[0027] In the description of the present application, it should be pointed out that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, or the orientation or positional relationship commonly used when the product of the present application is used, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the indicated device or element must have a particular orientation, structure and operation, and therefore cannot be understood as limiting the present application.

[0028] In addition, the terms "horizontal", "vertical" and the like do not mean that the components must be absolutely horizontal or vertical, but can be slightly inclined. For example, "horizontal" only means that its direction is relatively more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly inclined.

[0029] In the description of the utility model, still need to explain, unless another explicit provision and limitation, term "arrangement", "installation", "link", "connection" should do broad sense understanding, for example, can be fixed connection, also can be detachable connection, or integrally connected, can be mechanical connection, also can be electrical connection, can be direct connection, also can through intermediate medium indirectly connect, can be two element internal communication. For ordinary skilled in the art, can understand the specific meaning of the above terms in the utility model according to specific circumstances.

[0030] Embodiments, as Figures 1-2 Indicated,

[0031] A front wing for unmanned aerial vehicle, including front wing body 1, the front wing body 1 is used to be connected on the fuselage 4 of unmanned aerial vehicle, still including:

[0032] Elevon 2, the elevon 2 is connected on the leeward side of the front wing body 1 by flexible connecting piece, the elevon 2 is used to be controlled by elevon control device and carry out pitch deflection, so that, unmanned aerial vehicle is in the process of flight, by elevon control device and carry out pitch deflection control to elevon 2, control the flight attitude of unmanned aerial vehicle.

[0033] Unmanned aerial vehicle is in the process of flight, by elevon control device and carry out pitch deflection control to elevon 2, by flexible connecting piece and limit the active position of elevon 2, so that elevon 2 carries out pitch deflection along the leeward side of the front wing body 1, and by flexible connecting piece and the flexible connection of elevon 2 with the leeward side of the front wing body 1, weaken the connection rigidity of elevon 2 and the front wing body 1, so that elevon 2 can carry out pitch deflection in real time after being controlled by elevon control device, in this technical scheme, by flexible connecting piece and the flexible connection of elevon 2 with the front wing body 1, flexible connecting piece and limit the active position of elevon 2, weaken the connection rigidity of elevon 2 and the front wing body 1 simultaneously, improve the operability of unmanned aerial vehicle elevon 2.

[0034] As Figures 3-4 Indicated, elevon control device, including:

[0035] Drive assembly 5, the drive assembly 5 is fixedly connected on the fuselage 4, the drive assembly 5 is transmission connected with the lower end surface of the adjusting contact plate 21;

[0036] Elastic limit component, the elastic limit component is fixedly connected on the front wing body 1, the elastic limit component is abutted with the upper end surface of the elevon 2, the elastic limit component is staggered with the drive assembly 5.

[0037] The drive assembly 5 includes:

[0038] A rudder 51 is fixedly connected to the fuselage 4, and a gear 52 is connected to a transmission shaft of the rudder 51;

[0039] A rocker arm 53 is provided with a clamping groove 54, the gear 52 is engaged in the clamping groove 54, the rocker arm 53 is fixedly connected to the transmission shaft of the rudder 51 through a screw 55, and an end of the rocker arm 53 is integrally provided with a circular abutting plate 56, and a circumferential wall of the circular abutting plate 56 is abutted against a lower end surface of the adjusting contact plate 21 through deflection.

[0040] The elastic limiting assembly comprises:

[0041] The aileron pressing plate 6 comprises a connecting plate 61 which is integrally formed and protrudingly provided with an arc-shaped plate 62, the connecting plate 61 is fixedly connected to the front wing body 1, an end of the arc-shaped plate 62 is abutted against an upper end surface of the elevating aileron 2, and the arc-shaped plate 62 is used to apply a downward deflection thrust to the elevating aileron 2 after being pressed.

[0042] As a preferred embodiment, the flexible connecting piece is a flexible carbon fiber cloth 3 which is connected between the elevating aileron 2 and the front wing body 1.

[0043] The carbon fiber mainly comprises carbon elements, has the characteristics of high temperature resistance, friction resistance, heat conduction and corrosion resistance, etc., the flexible connecting piece is set as the flexible carbon fiber cloth 3, the connecting rigidity of the elevating aileron 2 and the front wing body 1 is weakened, the elevating aileron 2 can be adaptively tilted and deflected when being controlled by the elevating aileron control device, and the connecting strength of the elevating aileron 2 and the front wing body 1 is guaranteed.

[0044] As a preferred embodiment, the flexible carbon fiber cloth 3 is connected between the elevating aileron 2 and the front wing body 1 in the following manner:

[0045] One side of the flexible carbon fiber cloth 3 is adhesively connected to a leeward side of the front wing body, and the other side of the flexible carbon fiber cloth 3 is adhesively connected to the elevating aileron 2.

[0046] Further, the length of the flexible carbon fiber cloth 3 is equal to the length of the leeward side of the front wing body 1.

[0047] Further, the length of the adhesively connected side of the elevating aileron 2 is equal to the length of the flexible carbon fiber cloth 3.

[0048] The length of the flexible carbon fiber cloth 3 is equal to the length of the leeward side of the front wing body 1, and the length of the bonding side of the elevating aileron 2 is equal to the length of the flexible carbon fiber cloth 3. The connection area of the flexible carbon fiber cloth 3 and the front wing body 1 is increased, thereby further limiting the activity position of the elevating aileron 2, so that the elevating aileron 2 can only be adjusted to pitch by the elevating aileron control device, and the elevating aileron 2 cannot be offset during the pitch.

[0049] As a preferred embodiment, the elevating aileron 2 is further integrally provided with an adjusting contact plate 21, which is used to eliminate the height difference caused by the stacking of the front wing body 1, so that the driving assembly 5 of the elevating aileron control device is in contact with the adjusting contact plate 21, and the elevating aileron 2 is adjusted to pitch.

[0050] The front wing body 1 is installed on the left and right sides of the unmanned aerial vehicle. When the front wing bodies 1 on the left and right sides are stacked, the front wing bodies 1 on the left and right sides are staggered in height. The two front wing bodies 1 staggered in height are not conducive to the driving adjustment of the elevating aileron control device. Therefore, the adjusting contact plate 21 is integrally provided on the elevating aileron 2. The height difference between the two front wing bodies 1 is eliminated by the adjusting contact plate 21, so that the two front wing bodies 1 staggered in height can be in contact with the driving assembly 5 of the elevating aileron control device at the same height, so as to facilitate the driving adjustment of the driving assembly 5 of the elevating aileron control device to the front wing body 1.

[0051] As a preferred embodiment, the width of the flexible carbon fiber cloth 3 is 3-8 mm.

[0052] By setting the width of the flexible carbon fiber cloth 3 to 3-8 mm, the flexibility of the flexible carbon fiber cloth 3 is ensured, and the limiting effect of the flexible carbon fiber cloth 3 on the elevating aileron 2 is ensured, so as to avoid the offset of the elevating aileron 2 during the pitch.

[0053] Further, the thickness of the flexible carbon fiber cloth 3 is 0.1-0.2 mm. By setting the thickness of the flexible carbon fiber cloth 3 to 0.1-0.2 mm, the flexibility of the flexible carbon fiber cloth 3 is ensured, and the structural strength of the flexible carbon fiber cloth 3 is ensured.

[0054] As a preferred embodiment, the front end of the front wing body 1 is further integrally provided with a connecting ring plate 11, which is used to rotate the front wing body 1 and connect it to the fuselage 4 of the unmanned aerial vehicle, so that the front wing body 1 can be unfolded or folded on the fuselage 4 of the unmanned aerial vehicle.

[0055] The existing unmanned aerial vehicle occupies a large space when being folded, which is not conducive to the storage and carrying of the unmanned aerial vehicle; therefore, a connecting ring plate 11 is integrally arranged at the first end of the front wing body 1, the front wing body 1 is rotationally connected to the fuselage 4 of the unmanned aerial vehicle through the connecting ring plate 11, when the unmanned aerial vehicle is folded, the connecting ring plate 11 rotates on the fuselage 4 of the unmanned aerial vehicle, so that the front wing body 1 is deflected to be parallel to the fuselage 4, thereby reducing the space occupancy of the wing when the unmanned aerial vehicle is folded, and making the unmanned aerial vehicle easy to store and carry.

[0056] As a preferred embodiment, the windward side of the front wing body 1 is also integrally provided with a clamping plate 12, which is used to be clamped with a V-shaped socket on the fuselage 4, so that the clamping plate 12 is clamped with the V-shaped socket, and the deployment position of the front wing body 1 is positioned and limited.

[0057] When the unmanned aerial vehicle is unfolded, the front wing body 1 is deflected, and the clamping plate 12 is clamped with the V-shaped socket on the fuselage 4, so that the deployment position of the front wing body 1 is positioned and limited, which ensures that the front wing body 1 can be unfolded in place, and also ensures the stability of the front wing body 1 during flight.

[0058] The above is only a preferred embodiment of the utility model, and is not used to limit the technical scheme of the utility model. For those skilled in the art, the utility model can have various changes and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the technical scheme of the utility model shall be included in the protection scope of the utility model.

Claims

1. A front wing for a drone, comprising a front wing body for attachment to a fuselage of a drone, characterized in that, Also include: The elevators are connected to the leeward side of the front wing body through flexible connectors, and the elevators are used for pitch deflection controlled by elevator control devices, so that the flight attitude of the unmanned aerial vehicle is controlled by the pitch deflection of the elevators controlled by the elevator control devices during flight, The flexible connection between the elevators and the front wing body is achieved by flexible connectors, which limits the activity position of the elevators and reduces the connection rigidity between the elevators and the front wing body, improving the operability of the elevators of the unmanned aerial vehicle.

2. The front wing for a drone according to claim 1, wherein, The flexible connector is a flexible carbon fiber cloth connected between the elevators and the front wing body.

3. The front wing for a drone according to claim 2, wherein, The flexible carbon fiber cloth is connected between the elevators and the front wing body in the following way: One side of the flexible carbon fiber cloth is connected to the leeward side of the front wing body through flexible glue, and the other side of the flexible carbon fiber cloth is connected to the elevators through flexible glue.

4. The front wing for a drone according to claim 3, wherein, The length of the flexible carbon fiber cloth is equal to the length of the leeward side of the front wing body.

5. The front wing for a drone according to claim 3, wherein, The length of the elevators is equal to the length of the flexible carbon fiber cloth.

6. The front wing for a drone according to claim 1, wherein, The elevators are also integrally formed with a protruding adjustment contact plate, which is used to eliminate the height difference caused by the stacking of multiple front wing bodies, so that the driving assembly of the elevator control device is in contact with the adjustment contact plate, and the pitch deflection of the elevators is adjusted.

7. The front wing for a drone according to claim 2, wherein, The width of the flexible carbon fiber cloth is 3-8 mm.

8. The front wing for a drone according to claim 2, wherein, The thickness of the flexible carbon fiber cloth is 0.1-0.2 mm. 9.The front wing for a drone according to claim 1, wherein The front end of the front wing body is also integrally provided with a connecting ring plate, which is used to rotate the front wing body to the fuselage of the unmanned aerial vehicle, so that the front wing body can be deployed or retracted on the fuselage of the unmanned aerial vehicle. 10.The front wing for a drone according to claim 1, wherein The windward side of the front wing body is also integrally provided with a clamping plate, which is used to be clamped with the V-shaped clamp on the fuselage, so that the clamping plate is clamped with the V-shaped clamp, and the deployment position of the front wing body is positioned and limited.

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