Metal embedded part for empennage of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle empennage metal embedded part which comprises a tail fuselage, an embedded assembly, an installation assembly and a locking assembly, the embedded assembly is arranged on the tail fuselage, the installation assembly is arranged on one side of the tail fuselage, and the locking assembly is arranged on one side of the installation assembly. The embedded part is arranged in the direction plate, the lower portion of the embedded part is fixedly connected with the connecting shaft, grooves are formed in the embedded part, one end of the carbon rope is fixedly connected with the embedded part through the grooves, the other end of the carbon rope is fixedly connected with the direction plate, and the other set of grooves in the embedded part are filled with solid carbon cloth. The structural form is properly adjusted according to the layering process, the weight is reduced, the strength of the metal part is improved, the reliability of overall connection with the composite control surface is improved, the multiple carbon ropes wound up and down ensure that the embedded part is not distorted and deformed, and the problem that the strength and the weight cannot be met at the same time at present is solved.

Description

Technical Field

[0001] The utility model belongs to the technical direction of unmanned aerial vehicles (UAVs), and specifically relates to metal embedded parts for the tail wing of a UAV. Background Art

[0002] With the continuous advancement of information technology, more and more products suitable for different scenarios have emerged. Among them, unmanned aircraft, also known as "drones," are unmanned aerial vehicles controlled by radio remote control equipment and self-contained program control devices. Drones are actually a general term for unmanned aerial vehicles.

[0003] Existing drone tail wings have a slender tail rudder shaft, resulting in minimal contact with the servo mounting surface. They also have extremely stringent weight and deflection requirements, resulting in high testing and development costs. They also fail to meet the required strength and rigidity while maintaining the required weight. This has become a pressing issue for researchers in this field. Utility Model Content

[0004] The purpose of the present invention is to solve the problems raised in the above-mentioned background technology by targeting the existing device UAV tail metal embedded parts.

[0005] In order to solve the above technical problems, the utility model provides the following technical solutions: a metal embedded part of a UAV tail wing, comprising a tail fuselage, an embedded component, an installation component and a locking component, wherein the embedded component is arranged on the tail fuselage, the installation component is arranged on one side of the tail fuselage, and the locking component is arranged on one side of the installation component.

[0006] The utility model further describes that the embedded component includes a connecting plate, a vertical tail rudder, a horizontal tail rudder, a direction plate, an embedded part, a carbon rope and a connecting shaft. The connecting plate is arranged on the tail fuselage, the vertical tail rudder is arranged above the connecting plate, the horizontal tail rudder is arranged on both sides of the tail fuselage, the vertical tail rudder is provided with a groove, the direction plate is arranged in the groove of the vertical tail rudder, the embedded part is arranged inside the direction plate, the embedded part is provided with a connecting groove, the carbon rope is arranged in the connecting groove of the embedded part, the connecting shaft is arranged below the embedded part, and the horizontal tail rudder has the same structure as the vertical tail rudder.

[0007] The utility model further describes that the mounting assembly includes an outer shell, a mounting sleeve, a mounting block, a first spring, a limiting ring and a limiting plate. The outer shell is arranged on one side of the tail fuselage, the mounting sleeve is arranged on the inner side of the outer shell, the mounting sleeve is provided with an opening, the mounting block is arranged at the opening on the mounting sleeve, the first spring is arranged on one side of the mounting block, the limiting ring is arranged at the other end of the first spring, and the limiting plate is arranged on one side of the limiting ring.

[0008] The utility model further describes that the locking assembly includes a fixing plate, a fixing column, a locking plate and a second spring, the fixing plate is arranged on one side of the housing, the fixing column is arranged on one side of the fixing plate, the locking plate is arranged on one side of the fixing column, one end of the second spring is fixedly connected to the locking plate, and the other end of the second spring is fixedly connected to another group of locking plates.

[0009] The present invention further describes that a mounting plate is provided on the outer surface of the tail fuselage, the connecting plate is provided above the mounting plate, and the horizontal tail rudder is provided on both sides of the mounting plate.

[0010] The utility model further illustrates that one end of the first spring is fixedly connected to the mounting block, and the other end of the first spring is fixedly connected to the limiting ring.

[0011] Compared with the prior art, the beneficial effects achieved by the present invention are:

[0012] (1) By providing an embedded part, the embedded part is arranged inside the steering plate, the lower part of the embedded part is fixedly connected to the connecting shaft, the embedded part is provided with a groove, one end of the carbon rope is fixedly connected to the embedded part through the groove, and the other end of the carbon rope is fixedly connected to the steering plate, and another group of grooves on the embedded part is filled with solid carbon cloth. The structural form is appropriately adjusted according to the layup process, which not only reduces the weight, but also improves the strength of the metal part and increases the reliability of the overall connection with the composite rudder surface. The multiple carbon ropes wound up and down ensure that the embedded part does not twist or deform;

[0013] (2) A mounting block is provided, the mounting block is a triangular structure, the locking plate and the mounting block are adapted to each other, one end of the first spring is fixedly connected to the mounting block, and a limiting ring is provided on one side of the limiting plate. When the tail fuselage is installed, the outer shell is inserted into the fuselage through the mounting sleeve, and the mounting block is squeezed by the locking plate. The elastic force of the first spring drives the mounting block to reset and enter the side where the locking plate and another set of locking plates are close to each other, so that the tail fuselage and the fuselage can be quickly installed. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0015] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0016] Figure 2 This is a schematic diagram of the installation assembly structure of the utility model;

[0017] Figure 3 This is a schematic diagram of the structure of the embedded component of the utility model;

[0018] In the figure: 1. Tail fuselage; 11. Mounting plate; 2. Embedded component; 21. Connecting plate; 22. Vertical tail rudder; 23. Horizontal tail rudder; 24. Steering plate; 25. Embedded part; 26. Carbon rope; 27. Connecting shaft; 3. Mounting component; 31. Housing; 32. Mounting sleeve; 33. Mounting block; 34. First spring; 35. Limiting ring; 36. Limiting plate; 4. Locking component; 41. Fixing plate; 42. Fixing column; 43. Locking plate; 44. Second spring. DETAILED DESCRIPTION

[0019] The following is a non-limiting detailed description of the technical solution of the present invention in conjunction with preferred embodiments and their accompanying drawings. Obviously, the described embodiments are only a portion of the embodiments of the present invention, and not all of them. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without inventive effort are also within the scope of protection of the present invention.

[0020] See also Figure 1-3 The utility model provides a technical solution: a UAV tail metal embedded part, including a tail fuselage 1, an embedded component 2, an installation component 3 and a locking component 4, the embedded component 2 is arranged on the tail fuselage 1, the installation component 3 is arranged on one side of the tail fuselage 1, and the locking rent 4 is arranged on one side of the installation component 3;

[0021] The embedded component 2 includes a connecting plate 21, a vertical tail rudder 22, a horizontal tail rudder 23, a direction plate 24, an embedded part 25, a carbon rope 26 and a connecting shaft 27. The connecting plate 21 is arranged on the tail fuselage 1, the vertical tail rudder 22 is arranged above the connecting plate 21, the horizontal tail rudder 23 is arranged on both sides of the tail fuselage 1, the vertical tail rudder 22 is provided with a groove, the direction plate 24 is arranged in the groove of the vertical tail rudder 22, the embedded part 25 is arranged inside the direction plate 24, the embedded part 25 is provided with a connecting groove, the carbon rope 26 is arranged in the connecting groove of the embedded part 25, the connecting shaft 27 is arranged below the embedded part 25, and the horizontal tail rudder 23 has the same structure as the vertical tail rudder 22. An embedded part 25 is disposed inside the steering plate 24. The lower portion of the embedded part 25 is fixedly connected to the connecting shaft 27. A groove is provided on the embedded part 25. One end of a carbon rope 26 is fixedly connected to the embedded part 25 through the groove, and the other end of the carbon rope 26 is fixedly connected to the steering plate 24. Another set of grooves on the embedded part 25 is filled with solid carbon cloth. The structural form is appropriately adjusted according to the layup process, which not only reduces weight, but also improves the strength of the metal part and increases the reliability of the overall connection with the composite rudder surface. The multiple carbon ropes 26 wound up and down ensure that the embedded part 25 does not twist or deform.

[0022] The mounting assembly 3 includes a shell 31, a mounting sleeve 32, a mounting block 33, a first spring 34, a limiting ring 35 and a limiting plate 36. The shell 31 is arranged on one side of the tail fuselage 1, the mounting sleeve 32 is arranged on the inner side of the shell 31, the mounting sleeve 32 is provided with an opening, the mounting block 33 is arranged at the opening on the mounting sleeve 32, the first spring 34 is arranged on one side of the mounting block 33, the limiting ring 35 is arranged at the other end of the first spring 34, the limiting plate 36 is arranged on one side of the limiting ring 35, and the mounting block 33 is triangular. The locking plate 43 and the mounting block 33 are adapted to each other, one end of the first spring 34 is fixedly connected to the mounting block 33, and the limiting ring 35 is provided on one side of the limiting plate 36. When installing the tail fuselage 1, the housing 31 is inserted into the fuselage through the mounting sleeve 32, and the mounting block 33 is squeezed by the locking plate 43. The elastic force of the first spring 34 drives the mounting block 33 to reset and enter the side where the locking plate 43 and the other set of locking plates 43 are close to each other, thereby allowing the tail fuselage 1 to be quickly installed on the fuselage.

[0023] The locking assembly 4 includes a fixing plate 41, a fixing post 42, a locking plate 43, and a second spring 44. The fixing plate 41 is arranged on one side of the housing 31, the fixing post 42 is arranged on one side of the fixing plate 41, and the locking plate 43 is arranged on one side of the fixing post 42. One end of the second spring 44 is fixedly connected to the locking plate 43, and the other end of the second spring 44 is fixedly connected to another set of locking plates 43.

[0024] When the user is using it, the embedded part 25 is set inside the direction plate 24, and the lower part of the embedded part 25 is fixedly connected to the connecting shaft 27. A groove is set on the embedded part 25, and one end of the carbon rope 26 is fixedly connected to the embedded part 25 through the groove, and the other end of the carbon rope 26 is fixedly connected to the direction plate 24. Another group of grooves on the embedded part 25 are filled with solid carbon cloth. The structural form is appropriately adjusted according to the layup process, which not only reduces the weight, but also improves the strength of the metal parts and increases the reliability of the overall connection with the composite rudder surface. The multiple carbon ropes 26 wrapped up and down ensure the embedded part 25 does not cause distortion, the mounting block 33 is a triangular structure, the locking plate 43 and the mounting block 33 are adapted to each other, one end of the first spring 34 is fixedly connected to the mounting block 33, and the limiting ring 35 is arranged on one side of the limiting plate 36. When installing the tail fuselage 1, the shell 31 is inserted into the fuselage through the mounting sleeve 32, and the mounting block 33 is squeezed by the locking plate 43. The elastic force of the first spring 34 drives the mounting block 33 to reset and enter the side where the locking plate 43 and the other set of locking plates 43 are close to each other, so that the tail fuselage 1 and the fuselage can be quickly installed.

[0025] In the description of the present invention, it should be understood that the terms "up", "down", "front", "back", "left", "right", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they should not be understood as limitations on the present invention.

[0026] Finally, it should be pointed out that the above embodiments are intended only to illustrate the technical solutions of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art will appreciate that modifications may be made to the technical solutions described in the above embodiments, or that some of the technical features may be replaced with equivalents. Such modifications or replacements do not deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A UAV tail metal embedded component, comprising a tail fuselage (1), an embedded component (2), a mounting component (3) and a locking component (4), characterized in that: The embedded component (2) is arranged on the tail fuselage (1), the mounting component (3) is arranged on one side of the tail fuselage (1), and the locking component (4) is arranged on one side of the mounting component (3).

2. The UAV tail wing metal embedded part according to claim 1, characterized in that: The embedded component (2) comprises a connecting plate (21), a vertical tail rudder (22), a horizontal tail rudder (23), a direction plate (24), an embedded part (25), a carbon rope (26) and a connecting shaft (27); the connecting plate (21) is arranged on the tail fuselage (1); the vertical tail rudder (22) is arranged above the connecting plate (21); the horizontal tail rudder (23) is arranged on both sides of the tail fuselage (1); a groove is provided on the vertical tail rudder (22); the direction plate (24) is arranged in the groove of the vertical tail rudder (22); the embedded part (25) is arranged inside the direction plate (24); a connecting groove is provided on the embedded part (25); the carbon rope (26) is arranged in the connecting groove of the embedded part (25); the connecting shaft (27) is arranged below the embedded part (25); the horizontal tail rudder (23) has the same structure as the vertical tail rudder (22).

3. The UAV tail wing metal embedded part according to claim 1, characterized in that: The mounting assembly (3) comprises a housing (31), a mounting sleeve (32), a mounting block (33), a first spring (34), a limiting ring (35) and a limiting plate (36); the housing (31) is arranged on one side of the tail fuselage (1); the mounting sleeve (32) is arranged on the inner side of the housing (31); an opening is arranged on the mounting sleeve (32); the mounting block (33) is arranged at the opening on the mounting sleeve (32); the first spring (34) is arranged on one side of the mounting block (33); the limiting ring (35) is arranged at the other end of the first spring (34); and the limiting plate (36) is arranged on one side of the limiting ring (35).

4. The UAV tail wing metal embedded part according to claim 1, characterized in that: The locking assembly (4) comprises a fixing plate (41), a fixing column (42), a locking plate (43) and a second spring (44); the fixing plate (41) is arranged on one side of the housing (31); the fixing column (42) is arranged on one side of the fixing plate (41); the locking plate (43) is arranged on one side of the fixing column (42); one end of the second spring (44) is fixedly connected to the locking plate (43); and the other end of the second spring (44) is fixedly connected to another set of the locking plates (43).

5. The UAV tail wing metal embedded part according to claim 2, characterized in that: The outer surface of the tail fuselage (1) is provided with a mounting plate (11), the connecting plate (21) is provided above the mounting plate (11), and the horizontal tail rudder (23) is provided on both sides of the mounting plate (11).

6. The UAV tail wing metal embedded part according to claim 3, characterized in that: One end of the first spring (34) is fixedly connected to the mounting block (33), and the other end of the first spring (34) is fixedly connected to the limiting ring (35).

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