Rapid dismounting and mounting device for rudder control system of modular unmanned aerial vehicle

Abstract

The utility model discloses a modularized unmanned aerial vehicle rudder control system quick dismounting and mounting device, which relates to the technical field of unmanned aerial vehicle steering engine mounting and comprises a control surface structure, a mounting frame is arranged on the control surface structure, a buffer plate is connected in the mounting frame through a buffer component, a steering engine body is clamped on the buffer plate, and the steering engine body is connected with a steering wheel. A mounting hole is formed in the control surface structure, a mounting cover is clamped at the mounting hole, a driving motor is mounted on the control surface structure, and the output end of the driving motor is connected with the fixing plate; a refrigeration plate is mounted on the mounting frame, a plurality of cooling fins are arranged on the refrigeration plate, and thermistor sensors are mounted on the two sides of an inner cavity of the mounting frame; according to the steering engine, rapid clamping of the installation cover and the control surface structure is achieved through matching of the clamping piece and the clamping groove, the disassembly and assembly process is greatly simplified, the maintenance efficiency is improved, and heat generated when the steering engine body works can be efficiently dissipated through the refrigeration plate and the cooling fins arranged on the installation frame.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) servo motor installation technology, specifically a modular UAV servo control system quick disassembly and assembly device. Background Technology

[0002] With the continuous innovation of drone technology, its applications have broadly covered multiple fields such as agricultural plant protection, power line inspection, geographic surveying, and emergency rescue. Different scenarios place increasingly diverse demands on the performance, maintenance efficiency, and adaptability of drone control systems. As the core execution component for drones to achieve flight attitude adjustment and precise control, the ease of installation and disassembly of the control system, as well as its stability during operation, directly affects the drone's operational efficiency and mission completion quality.

[0003] From the perspective of ease of disassembly and assembly, traditional UAV control systems mostly use rigid connections such as bolt fixing. When replacing, maintaining, or upgrading servos, various specialized tools are required to gradually disassemble the bolts, making the operation cumbersome and time-consuming. This disassembly and assembly mode not only increases the workload of on-site maintenance but may also lead to delays due to inconvenient tool carrying and limited operating space. Especially in emergency operation scenarios requiring rapid response, it is difficult to meet the needs of efficient operation and maintenance. At the same time, some simplified connection structures designed to simplify disassembly and assembly often lack connection stability and cannot cope with the complex conditions such as high vibration and airflow impact encountered by UAVs during flight. This can easily lead to loose connections, component displacement, and other issues, which in turn affect the control surface accuracy and may even cause flight safety hazards.

[0004] Regarding operational stability and environmental adaptability, the servo motors in a servo control system generate heat during continuous operation. If this heat cannot be dissipated in time, the internal temperature of the servo motor will rise, affecting its performance and service life. Therefore, those skilled in the art have provided a modular UAV servo control system quick-assembly and disassembly device to solve the problems mentioned in the background art. Utility Model Content

[0005] The purpose of this invention is to provide a modular unmanned aerial vehicle (UAV) servo control system quick assembly and disassembly device to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] A modular unmanned aerial vehicle (UAV) control system quick-assembly and disassembly device, comprising:

[0008] The control surface structure includes a mounting frame, a buffer plate connected to the mounting frame via a buffer assembly, a servo motor body engaged on the buffer plate, mounting holes on the control surface structure, mounting covers engaged at the mounting holes, engaging components at both ends of the mounting covers, engaging slots on the control surface structure for engaging the engaging components, a drive motor mounted on the control surface structure, and the output end of the drive motor connected to a fixed plate, with the fixed plate in contact with the mounting cover.

[0009] A cooling plate is mounted on the mounting frame, and the cooling plate is provided with several heat dissipation fins. Thermistor sensors are installed on both sides of the inner cavity of the mounting frame.

[0010] Preferably, the buffer assembly includes a plurality of dampers and a plurality of disc springs, the two ends of which are respectively connected to the rudder surface structure and the buffer plate.

[0011] Preferably, both the buffer plate and the mounting cover are provided with a rubber layer, and the rubber layer is in contact with the servo motor body.

[0012] Preferably, the buffer plate is provided with a limiting frame, and the servo motor body is engaged within the limiting frame.

[0013] Preferably, a sealing ring is provided at the mounting hole, and the sealing ring is in contact with the mounting cover.

[0014] Preferably, the engaging component includes a U-shaped spring sheet, a lever plate, a triangular engaging block, and a connecting plate. The connecting plate is disposed on both sides of the mounting cover. The two ends of the U-shaped spring sheet are respectively connected to the connecting plate and the lever plate. The triangular engaging block is connected to the lever plate. The U-shaped spring sheet and the triangular engaging block are engaged in the engaging groove.

[0015] Preferably, the rudder surface structure is provided with an L-shaped plate, and one end of the fixing plate is engaged with the L-shaped plate.

[0016] Preferably, a controller is mounted on the control surface structure, and the controller is electrically connected to the drive motor, the cooling plate and the thermistor sensor respectively.

[0017] Compared with the prior art, the beneficial effects of this utility model are:

[0018] 1. This utility model achieves quick engagement between the mounting cover and the control surface structure through the cooperation of the engaging parts and engaging slots. Combined with the engagement and fixation of the servo body by the buffer plate, the disassembly and assembly of the servo control system can be completed without the need for special tools, which greatly simplifies the disassembly and assembly process and improves maintenance efficiency. At the same time, the drive motor drives the fixing plate to form a resistive fixation on the mounting cover, which enhances the stability of the connection structure and effectively avoids the problem of loosening or displacement of components due to vibration and airflow impact during the flight of the UAV.

[0019] 2. This utility model can efficiently dissipate the heat generated by the servo motor body during operation by setting a cooling plate and heat dissipation fins on the mounting frame. In conjunction with the thermistor sensor in the inner cavity of the mounting frame, the temperature change can be monitored in real time, which can facilitate timely adjustment of the heat dissipation state, ensure that the servo motor body operates stably in a suitable temperature environment, and extend its service life. At the same time, the setting of the buffer component can effectively buffer and protect the servo motor body, reducing the risk of damage caused by collisions and vibrations during the take-off, landing or operation of the UAV. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure of a modular unmanned aerial vehicle (UAV) rudder control system quick assembly / disassembly device according to an embodiment of this application;

[0021] Figure 2 This is a cross-sectional view of a modular unmanned aerial vehicle (UAV) rudder control system quick-assembly and disassembly device according to an embodiment of this application.

[0022] Figure 3 for Figure 2 Enlarged view of point A in the middle;

[0023] Figure 4 This is an exploded structural diagram of a modular unmanned aerial vehicle (UAV) rudder control system quick assembly / disassembly device according to an embodiment of this application.

[0024] In the diagram: 1. Rudder surface structure; 2. Mounting frame; 3. Buffer plate; 4. Servo body; 5. Mounting hole; 6. Mounting cover; 7. Engaging groove; 8. Drive motor; 9. Cooling plate; 10. Heat dissipation fins; 11. Thermistor sensor; 12. Damper; 13. Disc spring; 14. Rubber layer; 15. Limiting frame; 16. Sealing ring; 17. U-shaped spring sheet; 18. Paddle plate; 19. Triangular engaging block; 20. Connecting plate; 21. L-shaped plate; 22. Controller; 23. Fixing plate. 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 1-4 This utility model provides a technical solution:

[0027] A modular unmanned aerial vehicle (UAV) control system quick-assembly and disassembly device, comprising:

[0028] The control surface structure 1 has a mounting frame 2, and a buffer plate 3 is connected to the mounting frame 2 through a buffer assembly. The buffer plate 3 is fitted with a servo motor body 4. The control surface structure 1 has a mounting hole 5, and a mounting cover 6 is fitted at the mounting hole 5. A sealing ring 16 is provided at the mounting hole 5 and is in contact with the mounting cover 6. Both the buffer plate 3 and the mounting cover 6 are provided with a rubber layer 14, which is in contact with the servo motor body 4. The buffer plate 3 is provided with a limiting frame 15, and the servo motor body 4 is fitted within the limiting frame 15. The mounting cover 6 has locking parts at both ends. The control surface structure 1 has a locking groove 7 for locking parts to engage. The control surface structure 1 is equipped with a drive motor 8, and the output end of the drive motor 8 is connected to a fixing plate 23. The fixing plate 23 is in contact with the mounting cover 6. The control surface structure 1 is provided with an L-shaped plate 21, and one end of the fixing plate 23 is fitted with the L-shaped plate 21.

[0029] Specifically, the buffer assembly includes several dampers 12 and several disc springs 13, with both ends of the dampers 12 and disc springs 13 connected to the rudder surface structure 1 and the buffer plate 3, respectively.

[0030] When the device is working, multiple mechanisms work together to ensure performance: the damper 12 of the buffer component and the disc spring 13 form a composite buffer structure, which, together with the rubber layer 14, reduces hard contact and can absorb vibration and impact, significantly reducing the risk of mechanical damage; the limit frame 15 accurately positions the servo motor to avoid installation misalignment, while the sealing ring 16 and the rubber layer 14 enhance the sealing performance and prevent dust and moisture from entering.

[0031] Furthermore, the engaging component includes a U-shaped spring sheet 17, a lever plate 18, a triangular engaging block 19, and a connecting plate 20. The connecting plate 20 is disposed on both sides of the mounting cover 6. The two ends of the U-shaped spring sheet 17 are connected to the connecting plate 20 and the lever plate 18, respectively. The triangular engaging block 19 is connected to the lever plate 18. The U-shaped spring sheet 17 and the triangular engaging block 19 are engaged in the engaging groove 7.

[0032] When installing the servo motor body 4, simply snap it into the limiting frame 15 of the buffer plate 3. The buffer plate 3 and the rubber layer 14 on the mounting cover 6 form initial fixation and protection. Then, align the mounting cover 6 with the mounting hole 5 of the servo surface structure 1 and press it down. This causes the U-shaped spring plates 17 of the two end locking parts to deform and drive the triangular locking block 19 to lock into the locking groove 7, completing the initial fixation. Then, start the drive motor 8 through the controller 22 to rotate the fixing plate 23 until it locks into the L-shaped plate 21 and abuts against the mounting cover 6, achieving secondary locking. At the same time, the sealing ring 16 at the mounting hole 5 fits against the mounting cover 6 to enhance the sealing. When disassembling, reverse the operation of the drive motor 8 to loosen the fixing plate 23, and move the lever 18 to compress the U-shaped spring plates 17 to remove the mounting cover 6 and take out the servo motor. This design relies on the elastic deformation of the locking components and the locking structure of the drive motor 8, allowing for disassembly and assembly without tools. This simplifies the maintenance process and ensures connection strength through multiple fixations, effectively resisting vibrations and airflow impacts during flight. It solves the problem of "difficulty in balancing convenience and stability" in traditional devices.

[0033] A cooling plate 9 is installed on the mounting frame 2. The cooling plate 9 is provided with several heat dissipation fins 10. Thermistor sensors 11 are installed on both sides of the inner cavity of the mounting frame 2.

[0034] The thermistor sensor 11 monitors the temperature in real time, and the controller 22 links the cooling plate 9 and the heat dissipation fins 10 to actively dissipate heat when the temperature exceeds the limit, ensuring that the servo motor operates at a suitable temperature.

[0035] In terms of modular design, this device boasts excellent compatibility and adaptability. Its modular structure allows it to accommodate servos of different specifications. For example, for servos of different sizes and power ratings, simply adjusting the dimensions or parameters of components such as the limit frame 15 and the buffer plate 3 according to their specifications allows for easy installation. Simultaneously, the device is equipped with a universal interface. This standardized interface features a unified connection method and signal transmission protocol, ensuring stable connection to the device for any servo, regardless of its specifications, greatly enhancing adaptability. Furthermore, the precise positioning of the limit frame 15 and the accurate engagement of the mounting cover 6 and the locking slot 7 during each disassembly and assembly ensure precise reset of the servo after each removal and reassembly. This effectively reduces the impact of installation errors on control accuracy, guaranteeing stable and precise execution of control commands by the servo during UAV flight.

[0036] In the above embodiment, a controller 22 is installed on the rudder surface structure 1, and the controller 22 is electrically connected to the drive motor 8, the cooling plate 9 and the thermistor sensor 11 respectively.

[0037] It should be noted that the specific models and specifications of the controller 22, drive motor 8, cooling plate 9 and thermistor sensor 11 need to be selected and determined according to the actual specifications of the device. The specific selection calculation method adopts the existing technology in this field, so it will not be described in detail.

[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. A modular unmanned aerial vehicle (UAV) control system quick-assembly and disassembly device, characterized in that, include: The rudder surface structure (1) is provided with a mounting frame (2). A buffer plate (3) is connected to the mounting frame (2) through a buffer assembly. A servo motor body (4) is engaged on the buffer plate (3). A mounting hole (5) is provided on the rudder surface structure (1). A mounting cover (6) is engaged at the mounting hole (5). A locking component is provided at both ends of the mounting cover (6). A locking groove (7) for the locking component to engage is provided on the rudder surface structure (1). A drive motor (8) is installed on the rudder surface structure (1). The output end of the drive motor (8) is connected to a fixing plate (23). The fixing plate (23) is in contact with the mounting cover (6). A cooling plate (9) is installed on the mounting frame (2), and a number of heat dissipation fins (10) are provided on the cooling plate (9). Thermistor sensors (11) are installed on both sides of the inner cavity of the mounting frame (2).

2. The modular unmanned aerial vehicle (UAV) control system quick assembly / disassembly device according to claim 1, characterized in that: The buffer assembly includes several dampers (12) and several disc springs (13), with both ends of the dampers (12) and the disc springs (13) connected to the rudder surface structure (1) and the buffer plate (3), respectively.

3. The modular unmanned aerial vehicle (UAV) rudder control system quick assembly / disassembly device according to claim 1, characterized in that: Both the buffer plate (3) and the mounting cover (6) are provided with a rubber layer (14), which is in contact with the servo motor body (4).

4. The modular unmanned aerial vehicle (UAV) control system quick assembly / disassembly device according to claim 1, characterized in that: The buffer plate (3) is provided with a limiting frame (15), and the servo motor body (4) is engaged in the limiting frame (15).

5. A modular unmanned aerial vehicle (UAV) control system quick-assembly and disassembly device according to claim 1, characterized in that: A sealing ring (16) is provided at the mounting hole (5), and the sealing ring (16) is in contact with the mounting cover (6).

6. The modular unmanned aerial vehicle (UAV) control system quick-assembly and disassembly device according to claim 1, characterized in that: The engaging component includes a U-shaped spring sheet (17), a lever plate (18), a triangular engaging block (19), and a connecting plate (20). The connecting plate (20) is disposed on both sides of the mounting cover (6). The two ends of the U-shaped spring sheet (17) are respectively connected to the connecting plate (20) and the lever plate (18). The triangular engaging block (19) is connected to the lever plate (18). The U-shaped spring sheet (17) and the triangular engaging block (19) are engaged in the engaging groove (7).

7. The modular unmanned aerial vehicle (UAV) control system quick assembly / disassembly device according to claim 1, characterized in that: The rudder surface structure (1) is provided with an L-shaped plate (21), and one end of the fixing plate (23) is engaged with the L-shaped plate (21).

8. A modular unmanned aerial vehicle (UAV) rudder control system quick assembly / disassembly device according to claim 1, characterized in that: A controller (22) is installed on the rudder surface structure (1), and the controller (22) is electrically connected to the drive motor (8), the cooling plate (9) and the thermistor sensor (11).

Images