Anti-loosening quick plug structure of airborne communication module

Abstract

The utility model relates to airborne communication equipment technical field, concretely is a kind of anti-loosening quick plug-in structure of airborne communication module, include: unmanned aerial vehicle and detachably installed communication module on its fuselage;Equipment groove is set up on unmanned aerial vehicle fuselage, and the butt joint groove is equipped in equipment groove inside tail end, and communication module is slidably connected with equipment groove by guide structure;Communication module includes the sealing shell for protecting communication module, and sealing shell front end bottom is equipped with a joint part, and the bottom surface of unmanned aerial vehicle fuselage is equipped with the limiting protrusion matched with joint part;Limiting protrusion is connected with locking bolt axially.The utility model passes through the double locking mechanism of rigid buckle and bolt compression, effectively solved the technical contradiction that module both fast dismounting and absolute anti-loosening under high vibration environment, realized the unity of bare-handed fast dismounting and absolute locking under extreme environment, greatly promoted maintenance efficiency and task reliability, while integrated sealing and heat dissipation design, and environment adaptability is strong.

Description

Technical Field

[0001] This utility model relates to the field of airborne communication equipment technology, specifically to an anti-loosening quick-connection structure for an airborne communication module. Background Technology

[0002] For certain drones performing special missions, their onboard communication and data processing units integrate sensitive components such as multimode radio frequency and high-speed digital circuits, requiring extremely high levels of electromagnetic shielding. Therefore, the industry commonly uses a separate metal shielding box to encapsulate this unit as a single module, and then secures it to the drone fuselage using a specialized connection structure.

[0003] In practical applications, this module often needs to be separated from the fuselage to adapt to different tasks, for technical upgrades, or for maintenance. Currently, there are two main types of fixing methods: one is rigid fastening with multiple screws. This provides high fixing strength, but the disassembly and assembly efficiency is low, and the screws are prone to loosening under high-frequency vibration. To improve replacement efficiency, maintenance personnel often use power tools to disassemble and assemble the screws. In the field or in situations with speed requirements, improper operation can easily cause the screws to strip. The second method is using simple plug-in or elastic clips. Although this method is quick to operate, its locking force and rigidity are insufficient. Under the high-frequency vibration and impact of the aircraft, it is easy to cause micro-movements at the connection interface, which not only affects the reliability of electrical contact but also disrupts the electrical continuity of the shielding interface, leading to a decrease in electromagnetic shielding effectiveness. Utility Model Content

[0004] To overcome the above deficiencies, this utility model provides an anti-loosening quick-connection structure for an airborne communication module.

[0005] The technical solution of this utility model is: A quick-connect structure for preventing loosening of an airborne communication module includes: The drone and its detachable communication module; The drone has a device slot on its body, and a docking slot is provided at the end of the device slot. The communication module is slidably connected to the device slot through a guide structure. The communication module includes a sealed housing for protecting the communication module. The sealed housing is inserted into the device slot and its end is inserted into the docking slot for electrical connection with the UAV. The tail end of the sealed housing is provided with an external interface. The sealed outer shell has a snap-fit ​​part at the bottom front end, and the bottom surface of the drone fuselage has a limiting protrusion that cooperates with the snap-fit ​​part; when the communication module is inserted into place, the limiting protrusion engages with the snap-fit ​​part to restrict the movement of the communication module along its disengagement direction; The limiting protrusion is axially connected to a locking bolt, which is used to press and fix the snap-fit ​​part to the limiting protrusion.

[0006] Preferably, the guide structure includes a guide limiting structure located at the top of the inner side of the equipment slot, and the top surface of the sealed housing is provided with a non-through guide slot that cooperates with the guide limiting structure. The communication module can only move along the axial direction of the guide limiting structure.

[0007] Preferably, the docking groove is provided with a plurality of spring pins, and the end face of the sealing shell is provided with communication contacts adapted to the spring pins at corresponding positions.

[0008] Preferably, the mating groove is provided with a sealing element, which is used to seal between the mating groove and the sealing shell.

[0009] Preferably, the snap-fit ​​portion includes a insert plate, and the front end of the insert plate is provided with a C-shaped buckle. The buckle is used to cooperate with the limiting protrusion to achieve the initial fixation of the communication module.

[0010] Preferably, the bottom surface of the buckle is coaxially provided with an annular groove, and the outer side of the root of the locking bolt is provided with a limiting ring adapted to the annular groove. An elastic friction element is provided inside the limiting ring. When the locking bolt is screwed into place, the limiting ring is inserted into the annular groove.

[0011] Preferably, the bottom surface of the sealed outer casing is provided with a plurality of heat dissipation fins, which are arranged along the axis of the casing and protrude from the bottom surface of the casing.

[0012] Compared with the prior art, the beneficial effects of this utility model are: This invention provides the first layer of protection against vibration and detachment through the rigid engagement of the snap-fit ​​and the limiting protrusion, ensuring the basic safety of the module during flight. A second layer of highly reliable locking is formed by the axial compression of a single locking bolt, combined with the precise engagement of the limiting ring and the ring groove, preventing accidental detachment of the communication module. Elastic friction elements further prevent the bolts from rotating and loosening. The guide and limiting structure ensures precise and rapid insertion. This structure achieves a balance between quick manual assembly and disassembly and absolute locking in extreme environments, greatly improving maintenance efficiency and mission reliability. It also integrates sealing and heat dissipation design, making it highly adaptable to various environments. Attached Figure Description

[0013] Figure 1 This is a first schematic diagram of the overall structure of this utility model; Figure 2 This is a second schematic diagram of the overall structure of this utility model; Figure 3 for Figure 2 Enlarged schematic diagram of the structure at point A in the middle; Figure 4 This is an exploded view of the overall structure of this utility model; Figure 5 for Figure 4 Enlarged schematic diagram of the structure at point B; Figure 6 This is a schematic diagram of the communication module structure in this utility model. The meanings of the labels in the diagram are as follows: 1. Unmanned aerial vehicle (UAV); 2. Equipment slot; 3. Guide and limiting structure; 4. Docking slot; 5. Spring ejector pin; 6. Guide post; 7. Seal; 8. Limiting protrusion; 9. Communication module; 901. Sealed housing; 902. External interface; 903. Communication contact; 904. Guide socket; 905. Guide slot; 906. Heat sink fins; 907. Insert plate; 908. Clip; 909. Circular groove; 10. Locking bolt; 1001. Limiting ring; 11. Elastic friction element. Detailed Implementation

[0014] 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.

[0015] Example 1: Please see Figure 1-6 The present invention will describe the above technical solution in detail through the following embodiments: A quick-connect structure for preventing loosening of an airborne communication module includes: The drone 1 and the communication module 9 which can be detachably mounted on its fuselage; The drone 1 has an equipment slot 2 on its body, and a docking slot 4 is provided at the end of the equipment slot 2. The communication module 9 is slidably connected to the equipment slot 2 through a guide structure.

[0016] Equipment slot 2 is preferably located at the lower rear of the fuselage.

[0017] The guiding structure includes a guide limiting structure 3 located at the top of the inner side of the equipment slot 2. The top surface of the sealed housing 901 is provided with a non-through guide slot 905 that cooperates with the guide limiting structure 3. The communication module 9 can only move along the axial direction of the guide limiting structure 3.

[0018] The guide and limiting structure 3 is preferably a T-shaped or wedge-shaped guide rail, which is integrally formed with the machine body.

[0019] The guide and limit structure 3 restricts the movement direction of the communication module 9.

[0020] The communication module 9 includes a sealed housing 901 for protecting the communication module. The sealed housing 901 is inserted into the device slot 2 and its end is inserted into the docking slot 4 for electrical connection with the UAV 1. The tail end of the sealed housing 901 is provided with an external interface 902.

[0021] The sealed housing 901 is preferably made of aluminum alloy. The communication module is installed inside the sealed housing 901 and is electrically connected to the external interface 902.

[0022] External interfaces 902 include, but are not limited to, HDMI, USB 3.0, LAN port and serial port, used for data exchange between communication module 9 and external devices.

[0023] The docking groove 4 is provided with several spring pins 5, and the end face of the sealing housing 901 is provided with communication contacts 903 that are adapted to the spring pins 5.

[0024] The elastic force of the spring pin 5 allows for slight displacement between the communication module 9 and the docking groove 4, ensuring data exchange under vibration conditions.

[0025] One side of the communication module 9 has a communication contact 903. The communication contact 903 is not affected by bumps or water, which facilitates the sealing and carrying of the communication module 9.

[0026] The mating groove 4 is provided with a sealing element 7, which is used to seal the mating groove 4 and the sealing housing 901.

[0027] The seal 7 is preferably a rubber sealing ring, which can prevent water ingress.

[0028] Guide posts 6 can be set at both ends of the docking groove 4, and guide holes 904 can be set at the corresponding positions of the front end of the sealing shell 901.

[0029] The guide post 6 and the guide socket 904 work together to limit the shaking of the communication module 9 and ensure the stability of the connection.

[0030] The sealed outer shell 901 has a snap-fit ​​part at the bottom front end, and the bottom surface of the UAV 1 has a limiting protrusion 8 that cooperates with the snap-fit ​​part; when the communication module 9 is inserted into place, the limiting protrusion 8 engages with the snap-fit ​​part to restrict the movement of the communication module 9 in its disengagement direction.

[0031] The snap-fit ​​part includes a plug plate 907, and the front end of the plug plate 907 is provided with a C-shaped buckle 908. The buckle 908 is used to cooperate with the limiting protrusion 8 to achieve the initial fixation of the communication module 9.

[0032] The insert plate 907 and the buckle 908 are preferably made of metal, and the limiting protrusion 8 is preferably cylindrical.

[0033] The limiting protrusion 8 is axially connected to a locking bolt 10, which is used to press and fix the snap-fit ​​part to the limiting protrusion 8.

[0034] The bottom surface of the buckle 908 is coaxial with the limiting protrusion 8 and has an annular groove 909. The outer side of the root of the locking bolt 10 is provided with a limiting ring 1001 that is adapted to the annular groove 909. An elastic friction element 11 is provided inside the limiting ring 1001. When the locking bolt 10 is screwed into place, the limiting ring 1001 is inserted into the annular groove 909.

[0035] The elastic friction element 11 preferably uses an O-ring or rubber pad to provide axial elasticity and circumferential friction to prevent the locking bolt 10 from loosening.

[0036] For locking bolt 10, hand-tightening bolts are preferred.

[0037] The cooperation between the limiting ring 1001 and the ring groove 909 can limit the radial deformation of the buckle 908 and limit the movement of the communication module 9 in the disengagement direction, thereby preventing the communication module 9 from falling off during flight.

[0038] Hand-tightened bolts allow for easy disassembly in field conditions.

[0039] The bottom surface of the sealed outer casing 901 is provided with several heat dissipation fins 906, which are arranged along the axis of the casing and protrude from the bottom surface of the casing.

[0040] The heat dissipation fins 906 protrude from the bottom of the fuselage. Under flight conditions, this facilitates airflow and improves heat dissipation. In addition, the protruding heat dissipation fins 906 can serve as a leverage point for the hands when disassembling the communication module 9, making it easier to remove the communication module 9.

[0041] Working principle: The working principle of this utility model is based on a dual insurance mechanism of "rigid snap-fit ​​initial lock + bolt tightening final lock", combined with precise guidance and flexible electrical connection.

[0042] The linear guide pair formed by the guide limiting structure 3 and the guide slot 905 ensures that the communication module 9 can be inserted into the device slot 2 in the only correct path and posture, and enables the communication contact 903 to be precisely aligned with the spring pin 5 in the docking slot 4. The spring pin 5 actively compensates for tolerances and vibrations by utilizing its axial elasticity to maintain reliable contact; at the same time, it presses the sealing element 7 to ensure environmental sealing.

[0043] When the communication module 9 is pushed into place, the latch 908 engages with the cylindrical limiting protrusion 8. This is a purely mechanical, rigid "hook" structure. Any force attempting to pull the module out in the release direction will be directly transmitted from the hook wall of the latch 908 to the limiting protrusion 8, and then to the robust fuselage structure. This structure is effective before the locking bolt 10 is operated, providing initial vibration resistance and anti-detachment capability.

[0044] Tightening the locking bolt 10 generates enormous axial pressure, firmly pressing the insert plate 907 against the bottom of the fuselage, completely eliminating the play between the latch 908 and the limiting protrusion 8. The engagement of the limiting ring 1001 and the ring groove 909 restricts radial deformation of the latch 908 and limits the movement of the communication module 9 in the disengagement direction, thereby preventing the communication module 9 from falling off during flight. The elastic friction element 11 is compressed, providing axial pressure and circumferential friction to prevent the locking bolt 10 from loosening.

[0045] The downward-facing heat dissipation fins 906 guide airflow to enhance heat dissipation during flight, and serve as natural gripping points on the ground, facilitating disassembly.

[0046] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely preferred examples and are not intended to limit the utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A quick-connect structure for preventing loosening of an airborne communication module, characterized in that, include: The drone (1) and a communication module (9) that can be detachably mounted on its body; The UAV (1) has an equipment slot (2) on its body, and a docking slot (4) is provided at the end of the inside of the equipment slot (2). The communication module (9) is slidably connected to the equipment slot (2) through a guide structure. The communication module (9) includes a sealed housing (901) for protecting the communication module. The sealed housing (901) is inserted into the device slot (2) and its end is inserted into the docking slot (4) for electrical connection with the UAV (1). The tail end of the sealed housing (901) is provided with an external interface (902). The sealed outer shell (901) has a snap-fit ​​part at the bottom front end, and the drone (1) has a limiting protrusion (8) on the bottom surface of the fuselage that cooperates with the snap-fit ​​part; when the communication module (9) is inserted into place, the limiting protrusion (8) engages with the snap-fit ​​part to restrict the movement of the communication module (9) along its disengagement direction; The limiting protrusion (8) is axially connected to a locking bolt (10), which is used to press and fix the snap-fit ​​part to the limiting protrusion (8).

2. The anti-loosening quick-connection structure for an airborne communication module as described in claim 1, characterized in that: The guide structure includes a top guide limiting structure (3) located inside the equipment slot (2). The top surface of the sealed housing (901) is provided with a non-through guide slot (905) that cooperates with the guide limiting structure (3). The communication module (9) can only move along the axial direction of the guide limiting structure (3).

3. The anti-loosening quick-connect structure for an airborne communication module as described in claim 1, characterized in that: The docking groove (4) is provided with a number of spring pins (5), and the end face of the sealing shell (901) is provided with communication contacts (903) adapted to the spring pins (5).

4. The anti-loosening quick-connect structure for an airborne communication module as described in claim 3, characterized in that: The docking groove (4) is provided with a sealing element (7), which is used for sealing between the docking groove (4) and the sealing shell (901).

5. The anti-loosening quick-connection structure for an airborne communication module as described in claim 1, characterized in that: The snap-fit ​​part includes a plug plate (907), and the front end of the plug plate (907) is provided with a C-shaped buckle (908). The buckle (908) is used to cooperate with the limiting protrusion (8) to achieve the initial fixation of the communication module (9).

6. The anti-loosening quick-connect structure for an airborne communication module as described in claim 5, characterized in that: The buckle (908) has an annular groove (909) coaxial with the limiting protrusion (8) on its bottom surface. The locking bolt (10) has a limiting ring (1001) on the outer side of the screw root that is adapted to the annular groove (909). The limiting ring (1001) has an elastic friction element (11) inside. When the locking bolt (10) is screwed into place, the limiting ring (1001) is inserted into the annular groove (909).

7. The anti-loosening quick-connect structure for an airborne communication module as described in claim 1, characterized in that: The bottom surface of the sealed outer shell (901) is provided with a plurality of heat dissipation fins (906), which are arranged along the axis of the body and protrude from the bottom surface of the body.

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