A high subsonic stratospheric whole machine static electricity elimination UAV

Abstract

The utility model discloses a high-subsonic stratospheric whole-machine static elimination drone, comprising a fuselage and a nose cover, wings, a left tail wing, and a right tail wing installed on the fuselage, copper braids are provided on both sides of the nose cover, fuselage, and wings, and copper braids are provided on the left tail wing and the right tail wing; the tops of the left tail wing and the right tail wing are respectively installed with a left tail wing discharge brush and a right tail wing discharge brush; each copper braid is electrically connected to the left tail wing discharge brush and the right tail wing discharge brush. The utility model can effectively release the charge energy on the surface of the drone body into the atmosphere, avoiding the potential danger caused by large-area charge accumulation, solving the problem that local discharge may cause poor discharge effect, generate interference and affect the work of the drone communication and navigation system, and can more effectively release the charge energy on the surface of the drone body into the atmosphere, avoiding the potential danger caused by large-area charge accumulation.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles, and in particular relates to a high-subsonic stratospheric whole-machine static electricity elimination unmanned aerial vehicle. Background Art

[0002] When a drone moves at high altitude and high speed, especially when passing through clouds, the friction between the fuselage and the air will generate static electricity. If static electricity is not released in time, it will cause static electricity accumulation. If the various parts of the fuselage are not well connected electrically, the static electricity accumulated in each part will be different. When this different charge accumulation reaches a certain level, it will produce arcs or sparks. This electrical interference will seriously affect the operation of the drone's communication and navigation systems. Therefore, the various parts of the drone must be electrically connected to achieve a state of equipotential between the parts, provide a low-resistance path for the balance of static electricity, and then release the static electricity through the discharge brush.

[0003] Static electricity is usually evenly distributed on the surface of the aircraft. Since the earth itself is a large electromagnetic field, when the drone is flying, it will cut the magnetic flux lines. Under the action of the electromagnetic field, these charges are more likely to be concentrated on the sharp and thin edge areas of the drone, such as the wing tips, stabilizer edges, vertical tail, etc. Therefore, installing discharge brushes in these areas can release static electricity into the atmosphere.

[0004] The principle of drone discharge brush is to use the tip discharge phenomenon to safely release the static charge accumulated on the surface of the drone. Generally speaking, the top surface curvature of a sharp and small object is larger, the charge density is greater, and the electric field around it is also stronger, so the static charge accumulated on its top will be neutralized by the opposite charge in the air.

[0005] Traditional drones do not have static elimination technology, or only have it in parts such as wings and tails. Local discharge may result in poor discharge effect, causing interference that will affect the operation of drone communication and navigation systems. Utility Model Content

[0006] Based on the above deficiencies in the prior art, the technical problem solved by the utility model is to provide a high-subsonic stratospheric whole-machine static electricity elimination UAV, which solves the problem that local discharge may cause poor discharge effect and generate interference that will affect the operation of the UAV communication and navigation system.

[0007] In order to solve the above technical problems, the utility model is achieved through the following technical solutions: The utility model provides a high-subsonic stratospheric whole-machine static elimination UAV, including a fuselage and a nose cover, wings, a left tail wing and a right tail wing installed on the fuselage, copper braids are provided on both sides of the nose cover, fuselage and wings, and copper braids are provided on the left tail wing and the right tail wing; a left tail wing discharge brush and a right tail wing discharge brush are respectively installed on the top of the left tail wing and the right tail wing; each copper braid is electrically connected to the left tail wing discharge brush and the right tail wing discharge brush.

[0008] Furthermore, a pitot tube is provided at the front end of the nose cover, and a pitot tube mounting nut and a nose cover copper braid connecting nut are provided at one end of the pitot tube located inside the nose cover; a left copper braid of the nose cover and a right copper braid of the nose cover are provided on both sides of the nose cover, and one end of the left copper braid of the nose cover and the right copper braid of the nose cover are connected to the pitot tube mounting nut and the nose cover copper braid connecting nut to form an electrical connection.

[0009] Furthermore, the two sides of the fuselage are provided with a copper braided belt on the left side of the fuselage and a copper braided belt on the right side of the fuselage, and the front ends of the copper braided belt on the left side of the fuselage and the copper braided belt on the right side of the fuselage are respectively provided with a copper braided belt connecting spring on the left side of the nose cover and a copper braided belt connecting spring on the right side of the nose cover; the other ends of the copper braided belt on the left side of the nose cover and the copper braided belt on the right side of the nose cover are respectively provided with a copper braided belt connecting plug on the left side of the nose cover and a copper braided belt connecting plug on the right side of the nose cover, and the copper braided belt connecting plug on the left side of the nose cover and the copper braided belt connecting plug on the right side of the nose cover are respectively connected to the copper braided belt connecting spring on the left side of the nose cover and the copper braided belt connecting spring on the right side of the nose cover on the fuselage.

[0010] Preferably, the two sides of the wing are provided with a copper braided belt on the left side of the wing and a copper braided belt on the right side of the wing, one end of the copper braided belt on the left side of the wing and the copper braided belt on the right side of the wing are respectively provided with a copper braided belt connecting plug on the left side of the wing and a copper braided belt connecting plug on the right side of the wing, and the middle ends of the copper braided belt on the left side of the fuselage and the copper braided belt on the right side of the fuselage are respectively provided with a copper braided belt connecting spring on the left side of the wing and a copper braided belt connecting spring on the right side of the wing; the copper braided belt connecting plug on the left side of the wing and the copper braided belt connecting plug on the right side of the wing are respectively connected to the copper braided belt connecting spring on the left side of the wing and the copper braided belt connecting spring on the right side of the wing on the fuselage.

[0011] Optionally, the left tail and the right tail are respectively provided with a left tail copper braided belt and a right tail copper braided belt, one end of the left tail copper braided belt and the right tail copper braided belt are respectively provided with a left tail copper braided belt connecting plug and a right tail copper braided belt connecting plug, and the tail ends of the left side copper braided belt and the right side copper braided belt of the fuselage are respectively provided with a left tail copper braided belt connecting plug spring and a right tail copper braided belt connecting plug spring; the left tail copper braided belt connecting plug and the right tail copper braided belt connecting plug are respectively connected to the left tail copper braided belt connecting plug spring and the right tail copper braided belt connecting plug spring.

[0012] Furthermore, the tops of the left and right tail wings are respectively provided with left tail wing copper braided belt connecting embedded parts and right tail wing copper braided belt connecting embedded parts, and the left tail wing discharge brush and the right tail wing discharge brush are respectively connected to the left tail wing copper braided belt connecting embedded parts and the right tail wing copper braided belt connecting embedded parts through the left tail wing discharge brush mounting screws and the right tail wing discharge brush mounting screws.

[0013] Optionally, metal needles are provided at the top ends of the left tail wing discharge brush and the right tail wing discharge brush.

[0014] From the above, the high subsonic stratospheric whole machine static elimination UAV of the utility model has at least the following beneficial effects:

[0015] 1. Electrical connections are made between the various parts of the drone to achieve an equipotential state for each part, providing a low-resistance path for the balance of static electricity, and then releasing the static charge through the discharge brush.

[0016] 2. The static charge accumulated on the top of the discharge brush can easily be neutralized with the opposite charge in the air to complete the discharge. It can effectively release the charge energy on the surface of the drone body into the atmosphere, avoiding the potential danger caused by large-area charge accumulation, and solving the problem that local discharge may cause poor discharge effect and generate interference that will affect the operation of the drone communication and navigation system. It can more effectively release the charge energy on the surface of the drone body into the atmosphere, avoiding the potential danger caused by large-area charge accumulation.

[0017] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention, it can be implemented in accordance with the contents of the specification. In order to make the above and other purposes, features and advantages of the invention more obvious and easy to understand, the following is a detailed description in combination with the preferred embodiments and the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solution of the embodiment of the utility model, the drawings of the embodiment will be briefly introduced below.

[0019] Figure 1 This is a schematic diagram of the structure of a UAV for high subsonic stratospheric whole machine static elimination according to the utility model;

[0020] Figure 2 This is a schematic diagram of the structure of the drone after the copper braided belt is installed;

[0021] Figure 3 It is a structural schematic diagram of the nose cover of the utility model;

[0022] Figure 4 It is a schematic diagram of the connection between the nose cover and the fuselage of the utility model;

[0023] Figure 5 It is a schematic diagram of the connection between the wing and the fuselage of the utility model;

[0024] Figure 6 It is a schematic diagram of the connection between the tail wing and the fuselage of the utility model;

[0025] Figure 7 It is a structural schematic diagram of the left tail wing of the utility model;

[0026] Figure 8 It is a structural schematic diagram of the right tail wing of the utility model.

[0027] In the figure: 1- pitot tube, 2- nose cover, 3- fuselage, 4- wing, 5- left tail, 6- right tail, 7- left copper braided belt of nose cover, 8- right copper braided belt of nose cover, 9- left copper braided belt of fuselage, 10- right copper braided belt of fuselage, 11- left copper braided belt of wing, 12- right copper braided belt of wing, 13- left tail copper braided belt, 14- right tail copper braided belt, 15- left tail discharge brush, 16- right tail discharge brush, 17- pitot tube mounting nut, 18- nose cover copper braided belt connecting nut, 19- left copper braided belt connecting plug of nose cover, 20- right copper braided belt connecting plug of nose cover, 21- The left side copper braided belt of the hood is connected with a spring, 22-the right side copper braided belt of the hood is connected with a spring, 23-the left side copper braided belt of the wing is connected with a spring, 24-the right side copper braided belt of the wing is connected with a spring, 25-the left side copper braided belt of the wing is connected with a plug, 26-the right side copper braided belt of the wing is connected with a plug, 27-the left tail copper braided belt is connected with a spring, 28-the right tail copper braided belt is connected with a spring, 29-the left tail copper braided belt is connected with a plug, 30-the right tail copper braided belt is connected with a plug, 31-the left tail copper braided belt is connected with an embedded part, 32-the right tail copper braided belt is connected with an embedded part, 33-the left tail discharge brush is mounted with a screw, and 34-the right tail discharge brush is mounted with a screw. DETAILED DESCRIPTION

[0028] The following is a detailed description of the specific implementation of the utility model in conjunction with the accompanying drawings, which is a part of this specification and illustrates the principle of the invention through examples. Other aspects, features and advantages of the utility model will become clear through this detailed description. In the referenced drawings, the same or similar parts in different figures are represented by the same reference numerals.

[0029] like Figures 1 to 8 As shown, the high subsonic stratospheric whole machine static elimination UAV of the utility model is mainly composed of a nose cover 2, a fuselage 3, a wing 4, a left tail 5 and a right tail 6, wherein the nose cover 2, the wing 4, the left tail 5 and the right tail 6 are respectively mounted on the fuselage 3. The pitot tube 1 is arranged at the front end of the nose cover 2, and the end of the pitot tube 1 located inside the nose cover 2 is provided with a pitot tube mounting nut 17 and a nose cover copper braided belt connecting nut 18. The two sides of the nose cover 2 are provided with a nose cover left copper braided belt 7 and a nose cover right copper braided belt 8, and one end of the nose cover left copper braided belt 7 and the nose cover right copper braided belt 8 are connected to the pitot tube mounting nut 17 and the nose cover copper braided belt connecting nut 18 to form an electrical connection.

[0030] like Figure 2 and Figure 4 As shown, the fuselage 3 is provided with a left copper braided belt 9 and a right copper braided belt 10 on both sides, and the front ends of the left copper braided belt 9 and the right copper braided belt 10 are respectively provided with a left copper braided belt connecting spring 21 and a right copper braided belt connecting spring 22 of the nose cover. The other ends of the left copper braided belt 7 and the right copper braided belt 8 of the nose cover are respectively provided with a left copper braided belt connecting plug 19 and a right copper braided belt connecting plug 20 of the nose cover, and the left copper braided belt connecting plug 19 and the right copper braided belt connecting plug 20 of the nose cover are respectively connected to the left copper braided belt connecting plug 21 and the right copper braided belt connecting plug 22 of the nose cover on the fuselage 3.

[0031] like Figure 2 and Figure 5 As shown, the left copper braided belt 11 and the right copper braided belt 12 are provided on both sides of the wing 4, and the left copper braided belt 11 and the right copper braided belt 12 are provided with the left copper braided belt connecting plug 25 and the right copper braided belt connecting plug 26 respectively at one end of the left copper braided belt 11 and the right copper braided belt 12, and the left copper braided belt connecting plug spring 23 and the right copper braided belt connecting plug spring 24 are provided at the middle end of the left copper braided belt 9 and the right copper braided belt 10 of the fuselage. The left copper braided belt connecting plug 25 and the right copper braided belt connecting plug 26 of the wing are respectively connected to the left copper braided belt connecting plug spring 23 and the right copper braided belt connecting plug spring 24 of the wing on the fuselage 3.

[0032] like Figure 2 and Figure 6As shown, the left tail 5 and the right tail 6 are provided with a left tail copper braided belt 13 and a right tail copper braided belt 14 respectively, and one end of the left tail copper braided belt 13 and the right tail copper braided belt 14 is provided with a left tail copper braided belt connecting plug 29 and a right tail copper braided belt connecting plug 30 respectively, and the tail ends of the left side copper braided belt 9 and the right side copper braided belt 10 of the fuselage are provided with a left tail copper braided belt connecting plug spring 27 and a right tail copper braided belt connecting plug spring 28 respectively. The left tail copper braided belt connecting plug 29 and the right tail copper braided belt connecting plug 30 are connected to the left tail copper braided belt connecting plug spring 27 and the right tail copper braided belt connecting plug spring 28 respectively.

[0033] like Figure 7 and Figure 8 As shown, the tops of the left tail 5 and the right tail 6 are respectively provided with a left tail copper braided belt connecting embedded part 31 and a right tail copper braided belt connecting embedded part 32, and the left tail discharge brush 15 and the right tail discharge brush 16 are respectively connected to the left tail copper braided belt connecting embedded part 31 and the right tail copper braided belt connecting embedded part 32 through the left tail discharge brush mounting screws 33 and the right tail discharge brush mounting screws 34.

[0034] When the shells of various parts of the drone body are paste-formed, the copper braided belt 7 on the left side of the nose cover, the copper braided belt 8 on the right side of the nose cover, the copper braided belt 9 on the left side of the fuselage, the copper braided belt 10 on the right side of the fuselage, the copper braided belt 11 on the left side of the wing, the copper braided belt 12 on the right side of the wing, the copper braided belt 13 on the left tail, the copper braided belt 14 on the right tail, the left tail copper braided belt connecting embedded part 31, and the right tail copper braided belt connecting embedded part 32 are respectively embedded in the corresponding positions in the shell interlayer, and the copper braided belts are led out at the position where they need to be connected with other parts.

[0035] When assembling the drone, the left copper braided belt 7 of the nose cover and the right copper braided belt 8 of the nose cover are connected to the pitot tube mounting nut 17 and the nose cover copper braided belt connecting nut 18 to form an electrical connection. The left copper braided belt connecting plug 19 of the nose cover and the right copper braided belt connecting plug 20 of the nose cover are respectively connected to the left copper braided belt connecting plug spring 21 of the nose cover and the right copper braided belt connecting plug spring 22 of the nose cover on the fuselage 3. The left copper braided belt connecting plug 25 of the wing and the right copper braided belt connecting plug 26 of the wing 4 are respectively connected to the left copper braided belt connecting plug spring 23 of the wing and the right copper braided belt connecting plug spring 24 of the wing on the fuselage 3. The left tail copper braided belt connecting plug 29 and the right tail copper braided belt connecting plug 30 are respectively connected to the left tail copper braided belt connecting plug spring 27 and the right tail copper braided belt connecting plug spring 28. Use the left tail discharge brush mounting screw 33 and the right tail discharge brush mounting screw 34 to connect the left tail discharge brush 15 and the right tail discharge brush 16 to the left tail copper braided belt connecting embedded part 31 and the right tail copper braided belt connecting embedded part 32 respectively.

[0036] At this point, the UAV's pitot tube 1, nose cover 2, fuselage 3, wing 4, left tail 5, right tail 6, left tail discharge brush 15, right tail discharge brush 16 and other parts are electrically connected, achieving the purpose of equal potential of various parts of the UAV, and finally static electricity can be released through the left tail discharge brush 15 and the right tail discharge brush 16.

[0037] The tops of the left tail discharge brush 15 and the right tail discharge brush 16 are provided with metal needles, and the metal needles at the tops of the discharge brushes are designed to be very small, so that the charges in these small areas will accumulate more and more, forming a strong electric field, so the static electricity accumulated at the tops of the discharge brushes can easily be neutralized with the opposite charges in the air to complete the discharge. The utility model can effectively release the charge energy on the surface of the drone body into the atmosphere, avoiding the potential danger caused by the accumulation of charges over a large area.

[0038] The above is only a preferred implementation of the present utility model, which certainly cannot be used to limit the scope of rights of the present utility model. It should be pointed out that for ordinary technicians in this technical field, several improvements and changes can be made without departing from the principle of the present invention, and these improvements and changes are also regarded as the protection scope of the present utility model.

Claims

1. A high-subsonic stratospheric whole-machine static elimination drone, comprising a fuselage (3) and a nose cover (2), wings (4), a left tail wing (5), and a right tail wing (6) mounted on the fuselage (3), characterized in that: Copper braided belts are provided on both sides of the nose cover (2), fuselage (3) and wing (4), and copper braided belts are provided on the left tail wing (5) and the right tail wing (6); A left tail wing discharge brush (15) and a right tail wing discharge brush (16) are respectively installed on the top of the left tail wing (5) and the top of the right tail wing (6); Each copper braided belt is electrically connected to the left tail wing discharge brush (15) and the right tail wing discharge brush (16).

2. The high subsonic stratospheric whole machine static elimination UAV as claimed in claim 1, characterized in that: A pitot tube (1) is arranged at the front end of the nose cover (2); a pitot tube mounting nut (17) and a nose cover copper braided belt connecting nut (18) are arranged at one end of the pitot tube (1) located inside the nose cover (2); A copper braided belt (7) on the left side of the nose cover and a copper braided belt (8) on the right side of the nose cover are provided on both sides of the nose cover, and one end of the copper braided belt (7) on the left side of the nose cover and the copper braided belt (8) on the right side of the nose cover are connected to the pitot tube mounting nut (17) and the nose cover copper braided belt connecting nut (18) to form an electrical connection.

3. The high subsonic stratospheric whole machine static elimination UAV as claimed in claim 2, characterized in that: The fuselage (3) is provided with a left copper braided belt (9) and a right copper braided belt (10) on both sides thereof, and the front ends of the left copper braided belt (9) and the right copper braided belt (10) are provided with a left copper braided belt connecting spring (21) and a right copper braided belt connecting spring (22) on the nose cover respectively; The other ends of the left copper braided belt (7) of the nose cover and the right copper braided belt (8) of the nose cover are respectively provided with a left copper braided belt connecting plug (19) of the nose cover and a right copper braided belt connecting plug (20) of the nose cover. The left copper braided belt connecting plug (19) of the nose cover and the right copper braided belt connecting plug (20) of the nose cover are respectively connected to the left copper braided belt connecting spring (21) of the nose cover and the right copper braided belt connecting spring (22) of the nose cover on the fuselage (3).

4. The high subsonic stratospheric whole machine static elimination UAV as claimed in claim 3, characterized in that: The two sides of the wing (4) are provided with a left copper braided belt (11) and a right copper braided belt (12), one end of the left copper braided belt (11) and the right copper braided belt (12) are provided with a left copper braided belt connecting plug (25) and a right copper braided belt connecting plug (26), respectively, and the middle ends of the left copper braided belt (9) and the right copper braided belt (10) are provided with a left copper braided belt connecting plug spring (23) and a right copper braided belt connecting plug spring (24); The left copper braided belt connecting plug-in piece (25) of the wing and the right copper braided belt connecting plug-in piece (26) of the wing are respectively connected to the left copper braided belt connecting plug-in spring (23) of the wing and the right copper braided belt connecting plug-in spring (24) of the wing on the fuselage (3).

5. The high subsonic stratospheric whole machine static elimination UAV as claimed in claim 4, characterized in that: The left tail (5) and the right tail (6) are respectively provided with a left tail copper braided belt (13) and a right tail copper braided belt (14); one end of the left tail copper braided belt (13) and the right tail copper braided belt (14) are respectively provided with a left tail copper braided belt connecting plug (29) and a right tail copper braided belt connecting plug (30); the tail ends of the left fuselage copper braided belt (9) and the right fuselage copper braided belt (10) are respectively provided with a left tail copper braided belt connecting plug spring (27) and a right tail copper braided belt connecting plug spring (28); The left tail wing copper braided belt connecting plug-in piece (29) and the right tail wing copper braided belt connecting plug-in piece (30) are respectively connected to the left tail wing copper braided belt connecting plug-in spring (27) and the right tail wing copper braided belt connecting plug-in spring (28).

6. The high subsonic stratospheric whole machine static elimination UAV as claimed in claim 1, characterized in that: The tops of the left tail wing (5) and the right tail wing (6) are respectively provided with a left tail wing copper braided belt connecting embedded part (31) and a right tail wing copper braided belt connecting embedded part (32); the left tail wing discharge brush (15) and the right tail wing discharge brush (16) are respectively connected to the left tail wing copper braided belt connecting embedded part (31) and the right tail wing copper braided belt connecting embedded part (32) via a left tail wing discharge brush mounting screw (33) and a right tail wing discharge brush mounting screw (34).

7. The high subsonic stratospheric whole machine static elimination UAV as claimed in claim 1 or 6, characterized in that: Metal needles are provided at the top ends of the left tail wing discharge brush (15) and the right tail wing discharge brush (16).

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