Unmanned aerial vehicle electric steering engine electric connector capable of improving assembly efficiency

Abstract

The utility model discloses an unmanned aerial vehicle electric steering engine electric connector capable of improving assembly efficiency, and relates to the technical field of unmanned aerial vehicles, the unmanned aerial vehicle electric steering engine electric connector comprises a fuselage, a male head connecting assembly and a female head connecting assembly, wings are arranged on the fuselage, the fuselage is connected with the male head connecting assembly, the wings are connected with the female head connecting assembly, and the male head connecting assembly is connected with the female head connecting assembly. The male head connecting assembly comprises a male head shell, a male head terminal circuit board and a male head elastic piece terminal, the male head shell is connected with the fuselage, the male head elastic piece terminal is installed on the male head terminal circuit board, the female head connecting assembly comprises a female head shell, a female head terminal circuit board and a female head sheet-shaped terminal, the female head shell is connected with the wing, and the female head sheet-shaped terminal is installed on the female head terminal circuit board. The male head shell and the female head shell are connected through a clamping assembly; according to the utility model, through optimizing the structural design of the electric connector, the assembling difficulty is greatly reduced, the assembling working hours of the connecting part of the electric steering engine of the unmanned aerial vehicle are obviously shortened, and the overall assembling efficiency is effectively improved.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to an electric connector for an UAV electric servo motor that can improve assembly efficiency. Background Technology

[0002] With the rapid development of drone technology, drones are now widely used in various fields such as aerial surveying and mapping, agricultural plant protection, power line inspection, and emergency rescue. Their performance stability and assembly efficiency directly affect the quality of operations and the pace of industrial development. As the core actuator for drone flight attitude control, the electric servo motor needs to transmit signals and supply power to the fuselage control system through an electrical connector. The reliability and ease of assembly of the electrical connector have become one of the key factors determining the overall assembly efficiency and flight safety of the drone.

[0003] Currently, most mainstream electric servo connectors for drones on the market adopt a traditional pin-and-socket design. During assembly, this type of structure requires operators to precisely align the pins and sockets, performing each insertion step individually. This not only demands a high level of operator skill but also, in mass production scenarios, significantly extends the overall assembly time of the drone due to the cumbersome alignment and insertion steps, failing to meet the industry's demand for efficient production. Especially in the assembly of the drone fuselage and wings, where electric servos are typically integrated inside the wing, their electrical connectors need to mate with connecting components on the fuselage side. Due to the limited assembly space in the wing and fuselage, the assembly operation of traditional pin-and-socket connectors becomes even more difficult, easily leading to misalignment and incomplete insertion, resulting in poor contact, affecting the signal transmission stability of the electric servo, and potentially causing the drone to lose flight control, posing serious safety hazards. Therefore, those skilled in the art have provided a drone electric servo connector that can improve assembly efficiency to solve the problems mentioned in the background. Utility Model Content

[0004] The purpose of this invention is to provide an electric connector for an unmanned aerial vehicle (UAV) electric servo motor that can improve assembly efficiency, thereby solving the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] An electrical connector for an unmanned aerial vehicle (UAV) electric servo motor that improves assembly efficiency includes:

[0007] The fuselage has wings, a male connector assembly is connected to the fuselage, and a female connector assembly is connected to the wings;

[0008] A male connector assembly, comprising a male connector housing, a male connector terminal circuit board, and a male connector spring contact terminal, wherein the male connector housing is connected to the machine body, and the male connector spring contact terminal is mounted on the male connector terminal circuit board;

[0009] A female connector assembly includes a female connector housing, a female connector terminal circuit board, and a female connector sheet terminal. The female connector housing is connected to the wing, and the male connector housing is connected to the female connector housing via a snap-fit ​​assembly.

[0010] Preferably, the male connector circuit board is disposed on the first mounting frame, and a first silicone layer is provided between the male connector housing and the first mounting frame.

[0011] Preferably, the female terminal circuit board is disposed on the second mounting frame, a second silicone layer is provided between the female housing and the second mounting frame, and the female sheet terminal is disposed on the female terminal circuit board.

[0012] Preferably, the male terminal circuit board has a mounting groove, one end of the male spring-loaded terminal is mounted in the mounting groove by a mounting bolt, and the other end of the male spring-loaded terminal is in close contact with the female plate terminal.

[0013] Preferably, the engaging assembly includes a limiting rod, an engaging block, a push plate, a side plate, and a return spring. The limiting rod is connected to a first mounting frame. A through hole is provided on the second mounting frame for the other end of the limiting rod to pass through. The side plate is fixedly connected to the second mounting frame. The two ends of the return spring are respectively connected to the side plate and the engaging block. An engaging groove is provided on the limiting rod for the engaging block to engage. The push plate is fixedly connected to the engaging block.

[0014] Preferably, the male head housing and the female head housing are both connected to the fuselage and the wing respectively by bolts. Both the male head housing and the female head housing are provided with sealing rings. Both the fuselage and the wing are provided with sealing grooves for the sealing rings to engage. A rubber layer is provided in the sealing grooves, and the rubber layer is in contact with the sealing rings.

[0015] Preferably, the male connector spring terminal is made of beryllium bronze, and both the male connector housing and the female connector housing are provided with a waterproof coating.

[0016] Compared with the prior art, the beneficial effects of this utility model are:

[0017] 1. By optimizing the structural design of the electrical connector, this utility model enables the terminals to be properly engaged and conductive during the overall assembly of the fuselage and wing by simply connecting the male and female housings. This eliminates the need for operators to perform tedious and precise alignment and individual insertion operations in a confined space, significantly reducing assembly difficulty, shortening the assembly time of the UAV's electric servo motor connection parts, effectively improving overall assembly efficiency, and better meeting the high-efficiency operation requirements of mass production scenarios.

[0018] 2. This utility model adds a locking component between the male and female connector housings. Compared with the existing technology that relies solely on the interference fit of the terminals for fixation, the locking structure can reliably lock the housing connection parts, preventing the male and female connectors from relative displacement or separation due to airflow disturbances and vibration impacts during UAV flight. At the same time, the elasticity of the male connector spring terminal itself can ensure the tightness of the terminal fit. With this dual protection, the connection stability of the electrical connector is significantly improved, reducing the occurrence of problems such as poor contact and signal transmission interruption. This further reduces the safety hazards of UAV flight attitude loss and provides strong support for the stable operation of the electric servo motor. Attached Figure Description

[0019] Figure 1 This is a front view schematic diagram of an electric connector for an unmanned aerial vehicle (UAV) servo motor that can improve assembly efficiency, as described in an embodiment of this application.

[0020] Figure 2 This is a schematic diagram of the front cross-sectional structure of an electric connector for an unmanned aerial vehicle (UAV) servo motor that can improve assembly efficiency, as described in an embodiment of this application.

[0021] Figure 3 for Figure 2 Enlarged view of point A in the middle;

[0022] Figure 4 This is a side cross-sectional view of an electric connector for an unmanned aerial vehicle (UAV) servo motor that can improve assembly efficiency, as described in an embodiment of this application.

[0023] Figure 5 for Figure 4 Enlarged view of section B in the middle.

[0024] In the diagram: 1. Fuselage; 2. Wing; 3. Male connector housing; 4. Male connector terminal circuit board; 5. Male connector spring contact terminal; 6. Female connector housing; 7. Female connector terminal circuit board; 8. Female connector sheet terminal; 9. First mounting frame; 10. First silicone layer; 11. Second mounting frame; 12. Second silicone layer; 13. Mounting groove; 14. Mounting bolt; 15. Limiting rod; 16. Engaging block; 17. Push plate; 18. Side plate; 19. Return spring; 20. Through hole; 21. Engaging groove; 22. Sealing ring; 23. Sealing groove; 24. Rubber layer. Detailed Implementation

[0025] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0026] Please see Figures 1-5 This utility model provides a technical solution:

[0027] An electrical connector for an unmanned aerial vehicle (UAV) electric servo motor that improves assembly efficiency includes:

[0028] The fuselage 1 has wings 2 on it, a male connector is connected to the fuselage 1, and a female connector is connected to the wings 2.

[0029] The male connector assembly includes a male connector housing 3, a male connector terminal circuit board 4, and a male connector spring contact terminal 5. The male connector housing 3 is connected to the body 1. The male connector spring contact terminal 5 is mounted on the male connector terminal circuit board 4. The male connector terminal circuit board 4 is set on a first mounting frame 9. A first silicone layer 10 is provided between the male connector housing 3 and the first mounting frame 9. A mounting groove 13 is provided on the male connector terminal circuit board 4. One end of the male connector spring contact terminal 5 is installed in the mounting groove 13 by a mounting bolt 14, and the other end of the male connector spring contact terminal 5 is in close contact with the female connector plate terminal 8.

[0030] The female connector assembly includes a female connector housing 6, a female connector terminal circuit board 7, and a female connector sheet terminal 8. The female connector housing 6 is connected to the wing 2. The male connector housing 3 is connected to the female connector housing 6 through a snap-fit ​​assembly. The female connector terminal circuit board 7 is disposed on the second mounting frame 11. A second silicone layer 12 is provided between the female connector housing 6 and the second mounting frame 11. The female connector sheet terminal 8 is disposed on the female connector terminal circuit board 7.

[0031] During the pre-assembly stage of the UAV electric servo connector, the male spring-loaded terminal 5 is fixed in the mounting groove 13 of the male terminal circuit board 4 with mounting bolts 14. Then, the male terminal circuit board 4 is installed on the first mounting frame 9, and the male housing 3 is fixed to the fuselage 1 with bolts, so that the sealing ring 22 is inserted into the sealing groove 23 of the fuselage 1 and makes tight contact with the rubber layer 24. Similarly, the female plate terminal 8 is installed on the female terminal circuit board 7, and the female housing 6 is fixed to the wing 2 with bolts, thus completing the engagement of the sealing ring 22 with the sealing groove 23 of the wing 2.

[0032] During the flight of the drone, the fuselage 1 and wings 2 will vibrate due to various factors. A first silicone layer 10 is disposed between the male connector housing 3 and the first mounting frame 9, and a second silicone layer 12 is disposed between the female connector housing 6 and the second mounting frame 11. These layers can absorb vibration energy through their elastic deformation. This elastic deformation effectively reduces the stress transmitted to the connection between the circuit board and the housing due to vibration, preventing loosening or breakage at the connection due to long-term vibration. This protects the solder joints and circuitry on the circuit board, improving the reliability and lifespan of the electrical connector.

[0033] Furthermore, both the male head housing 3 and the female head housing 6 are connected to the fuselage 1 and the wing 2 respectively by bolts. Both the male head housing 3 and the female head housing 6 are provided with sealing rings 22. Both the fuselage 1 and the wing 2 are provided with sealing grooves 23 for the sealing rings 22 to engage. A rubber layer 24 is provided in the sealing groove 23. The rubber layer 24 is in contact with the sealing ring 22. The male head spring terminal 5 is made of beryllium bronze. Both the male head housing 3 and the female head housing 6 are provided with a waterproof coating.

[0034] The sealing ring 22 of the male head housing 3 and the sealing groove 23 are tightly fitted with the rubber layer 24 inside, which, together with the waterproof coating on the surface of the housing, forms a double waterproof and dustproof barrier. The first silicone layer 10 and the second silicone layer 12 absorb vibration energy through elastic deformation, reduce the stress at the connection between the circuit board and the housing, and protect the solder joints and circuits.

[0035] Specifically, the locking assembly includes a limiting rod 15, a locking block 16, a push plate 17, a side plate 18, and a return spring 19. The limiting rod 15 is connected to the first mounting frame 9. The second mounting frame 11 has a through hole 20 for the other end of the limiting rod 15 to pass through. The side plate 18 is fixedly connected to the second mounting frame 11. The two ends of the return spring 19 are connected to the side plate 18 and the locking block 16, respectively. The limiting rod 15 has a locking groove 21 for the locking block 16 to engage. The push plate 17 is fixedly connected to the locking block 16.

[0036] During the docking phase, when assembling the fuselage 1 and wing 2, the male connector assembly is pushed closer to the female connector assembly, causing the limiting rod 15 of the male housing 3 to insert into the through hole 20 of the female housing 6. At this time, the locking block 16, under the elastic force of the return spring 19, locks into the locking groove 21 of the limiting rod 15, achieving rapid locking of the male and female housings 6 and preventing them from separating during UAV flight vibrations. During disassembly, the locking is released by the push plate 17 overcoming the spring force, balancing connection stability and ease of operation. Simultaneously, the male spring contact terminal 5, under its own elasticity, tightly adheres to the female plate terminal 8, completing the circuit conduction. In terms of circuit conduction, the male spring contact terminal 5 is made of beryllium bronze, which has high elasticity and conductivity. One end is fixed by the mounting bolt 14, and the other end, during docking, relies on elastic deformation to tightly adhere to the female plate terminal 8, forming a stable electrical connection channel and ensuring reliable transmission of signals and power.

[0037] During the disassembly stage, when it is necessary to separate the connector, push the push plate 17 to drive the locking block 16 to compress the return spring 19, so that the locking block 16 disengages from the locking groove 21, and the limit rod 15 can be pulled out to separate the male and female connector assemblies.

[0038] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An electrical connector for an unmanned aerial vehicle (UAV) electric servo motor that improves assembly efficiency, characterized in that: include: The fuselage (1) is provided with wings (2), and a male connector is connected to the fuselage (1) and a female connector is connected to the wings (2). A male connector assembly, comprising a male connector housing (3), a male connector terminal circuit board (4), and a male connector spring contact terminal (5), wherein the male connector housing (3) is connected to the body (1), and the male connector spring contact terminal (5) is mounted on the male connector terminal circuit board (4); The female connector assembly includes a female connector housing (6), a female connector terminal circuit board (7), and a female connector sheet terminal (8). The female connector housing (6) is connected to the wing (2), and the male connector housing (3) is connected to the female connector housing (6) through a snap-fit ​​assembly.

2. The UAV electric servo motor electrical connector for improving assembly efficiency according to claim 1, characterized in that: The male terminal circuit board (4) is disposed on the first mounting frame (9), and a first silicone layer (10) is provided between the male housing (3) and the first mounting frame (9).

3. The UAV electric servo motor electrical connector for improving assembly efficiency according to claim 2, characterized in that: The female terminal circuit board (7) is disposed on the second mounting frame (11), and a second silicone layer (12) is provided between the female housing (6) and the second mounting frame (11). The female sheet terminal (8) is disposed on the female terminal circuit board (7).

4. The UAV electric servo motor electrical connector for improving assembly efficiency according to claim 3, characterized in that: The male terminal circuit board (4) has an installation groove (13). One end of the male spring contact terminal (5) is installed in the installation groove (13) by a mounting bolt (14), and the other end of the male spring contact terminal (5) is in close contact with the female plate terminal (8).

5. The UAV electric servo motor electrical connector for improving assembly efficiency according to claim 4, characterized in that: The locking assembly includes a limiting rod (15), a locking block (16), a push plate (17), a side plate (18), and a return spring (19). The limiting rod (15) is connected to the first mounting frame (9). The second mounting frame (11) has a through hole (20) for the other end of the limiting rod (15) to pass through. The side plate (18) is fixedly connected to the second mounting frame (11). The two ends of the return spring (19) are respectively connected to the side plate (18) and the locking block (16). The limiting rod (15) has a locking groove (21) for the locking block (16) to engage. The push plate (17) is fixedly connected to the locking block (16).

6. The UAV electric servo motor electrical connector for improving assembly efficiency according to claim 1, characterized in that: The male head housing (3) and the female head housing (6) are respectively connected to the fuselage (1) and the wing (2) by bolts. Both the male head housing (3) and the female head housing (6) are provided with sealing rings (22). Both the fuselage (1) and the wing (2) are provided with sealing grooves (23) for the sealing rings (22) to engage. The sealing grooves (23) are provided with rubber layers (24), and the rubber layers (24) are in contact with the sealing rings (22).

7. The UAV electric servo motor electrical connector for improving assembly efficiency according to claim 1, characterized in that: The male connector spring terminal (5) is made of beryllium bronze, and both the male connector housing (3) and the female connector housing (6) are provided with a waterproof coating.

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