Mechanical ejection device for unmanned aerial vehicle catching net

Abstract

The utility model relates to the field of low-altitude air defense, in particular to a mechanical ejection device of an unmanned aerial vehicle catching net. Comprising a launching support, the launching support is movably connected with a base, the launching support is rotationally connected with a trigger, the trigger is matched with the base, the launching support is connected with a first spring, the other end of the first spring is matched with the base, the base is detachably connected with a compression spring cabin, the compression spring cabin is detachably connected with a shell, and the shell is connected with a catching net. The compression spring cabin is connected with a second spring, the other end of the second spring is matched with the clamping plate, the clamping plate is connected with an elastic buffer layer, the launching support is in threaded connection with a trigger nut, the shell is provided with an elastic piece, the elastic piece is matched with the trigger nut, the compression spring cabin is provided with a clamping block, and the clamping block is matched with the elastic piece. The catapulting range and the coverage area of the catching net can be enlarged, the catching probability of the unmanned aerial vehicle is improved, and the catching requirements of unmanned aerial vehicles of different models are met.

Description

Technical Field

[0001] This utility model relates to the field of low-altitude air defense, specifically a mechanical catapult device for capturing nets for unmanned aerial vehicles. Background Technology

[0002] With the rapid development of small unmanned aerial vehicle (UAV) technology, its application scenarios are constantly expanding, but this has also brought many safety hazards. UAVs that illegally enter no-fly zones, carry dangerous items, and may cause harm due to loss of control or malfunction pose a serious threat to the safety of areas such as airports, military bases, and large event venues.

[0003] Traditional net-launching devices are mostly one-piece designs, which are difficult to adapt to the capture needs of different types of drones, and maintenance and replacement of parts are inconvenient. Utility Model Content

[0004] The present invention aims to provide a mechanical ejection device for a net-catching device for unmanned aerial vehicles, so as to solve the problems mentioned in the background art.

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

[0006] A mechanical ejection device for a net-catching device of an unmanned aerial vehicle (UAV) includes a launch bracket, a base movably connected to the launch bracket, a trigger rotatably connected to the launch bracket, the trigger engaging with the base, a first spring connected to the launch bracket, the other end of the first spring engaging with the base, a compression spring chamber detachably connected to the base, a housing detachably connected to the compression spring chamber, a net connected to the housing, a locking plate movably connected to the net, a second spring connected to the compression spring chamber, the other end of the second spring engaging with the locking plate, an elastic buffer layer connected to the locking plate, a trigger nut threadedly connected to the launch bracket, a spring piece provided on the housing engaging with the trigger nut, and a locking block provided on the compression spring chamber engaging with the spring piece.

[0007] Preferably, the base and the compression spring chamber are detachably connected by a snap-fit ​​mechanism.

[0008] Preferably, the base is provided with ball bearings, the launch bracket is provided with a spiral groove, and the ball bearings are slidably connected to the spiral groove.

[0009] Preferably, the outer casing has drag-reducing and flow-guiding grooves.

[0010] Preferably, the elastic buffer layer is made of rubber and has anti-slip serrations.

[0011] The beneficial effects of this technical solution compared to existing technologies are as follows:

[0012] (1) This design incorporates two springs: Spring 1 and Spring 2. Spring 1 functions during the rotation of the launch bracket, releasing its stored elastic potential energy when the trigger is activated, providing initial power for the launch bracket's rotation. Spring 2, located within the compression spring chamber, works in conjunction with the locking plate to provide additional thrust during the net's ejection. The synergistic operation of the two springs allows the net to achieve a more powerful ejection force. When the net flies towards the UAV at a higher speed and with a larger coverage area, it can more accurately envelop the target, reducing the chance of the UAV escaping. This expands the net's ejection range and coverage area, increases the probability of capturing UAVs, adapts to the capture needs of different UAV models, and enhances the device's versatility and practicality.

[0013] (2) By setting a snap-fit ​​mechanism, the base and the compression spring chamber are detachably connected. This allows each component of the device to be easily maintained, replaced, or upgraded individually. In actual use, if the second spring becomes fatigued or damaged, the compression spring chamber can be quickly removed from the base to replace the second spring without disassembling the entire device, greatly shortening maintenance time and reducing maintenance costs.

[0014] (3) By setting ball bearings and spiral grooves, when the launch support rotates, the ball bearings slide in the spiral grooves, converting the rotational motion of the launch support into spiral motion along the spiral grooves, thus giving the net a certain rotational angle during the launch process. This rotational motion not only increases the stability of the net in the air and reduces the influence of air resistance on the flight trajectory of the net, but also allows the net to apply force more evenly when it contacts the UAV, improving the success rate of capture.

[0015] (4) By setting drag-reducing guide channels, air can be guided to form an orderly airflow on the outer shell surface during the ejection of the net, reducing the generation of air vortices and thus reducing air resistance. This not only helps to improve the ejection speed and flight distance of the net, but also enhances the stability of the net during flight, enabling the net to fly more accurately towards the target UAV. The drag-reducing guide channels can also reduce the noise generated by the device during high-speed movement, reduce the impact on the surrounding environment, improve the concealment of the device, and make it suitable for more complex application scenarios.

[0016] (5) The elastic buffer layer is made of rubber, which has good elasticity and cushioning performance. This reduces the chance of damage to the card and extends its service life. Attached Figure Description

[0017] Figure 1 This is a front sectional view of the present invention;

[0018] Figure 2 This is a schematic diagram of the overall structure of this utility model;

[0019] Figure 3 This is a schematic diagram of the exploded structure of this utility model;

[0020] Reference numerals in the attached drawings: 1. Trigger nut; 2. Housing; 3. Net; 4. Spring 2; 5. Clamping plate; 6. Launching bracket; 7. Spring 1; 8. Trigger trigger; 9. Base; 10. Ball bearing; 11. Compression spring chamber; 12. Spring piece; 13. Spiral groove; 14. Drag reduction and flow guide groove; 15. Clamping mechanism; 16. Clamping block. Detailed Implementation

[0021] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments:

[0022] like Figure 1-3 The mechanical ejection device for an unmanned aerial vehicle (UAV) net, as shown, includes a launch bracket 6. A base 9 is movably connected to the top of the launch bracket 6. Two triggers 8 are symmetrically rotatably connected to the inner wall of the launch bracket 6. The two triggers 8 respectively cooperate with both ends of the base 9. The base 9 has grooves corresponding to the triggers 8. The entire ejection device is activated by rotating the triggers 8. A spring 7 is connected to the inner wall of the launch bracket 6. The other end of the spring 7 cooperates with the bottom of the base 9. When the triggers 8 are activated, the compressive potential energy of the spring 7 is released, generating axial thrust, which pushes the base 9 to move the entire net assembly 3. The base 9 is detachably connected to a compression spring chamber 11, which is detachably connected to an outer shell 2. A netting net 3 is connected to the inner wall of the outer shell 2. Five locking plates 5 are evenly arrayed and movably connected around the bottom perimeter of the netting net 3. Five springs 4 are evenly arrayed and connected to the inner wall of the compression spring chamber 11. The other end of each spring 4 engages with a corresponding locking plate 5. During the launch of the netting net 3, the locking plates 5, under the action of the springs 4, launch the five corners of the netting net 3, allowing it to better open and cover the target UAV. During launch, the netting net 3 utilizes centrifugal force and the potential energy of the springs 4 to move the entire net forward, covering the target UAV, rendering it powerless, and completing the capture action. Each locking plate 5 has an elastic buffer layer connected to the side closest to the spring 4. A trigger nut 1 is threaded onto the top of the launch bracket 6. By adjusting the position of the trigger nut 1, the movement and launch process of the netting net 3 assembly can be controlled, achieving precise control of the netting net 3's launch. The inner wall of the outer shell 2 is provided with several spring pieces 12, each of which cooperates with the trigger nut 1. The top of the compression spring chamber 11 is provided with several locking blocks 16, each of which cooperates with the corresponding spring piece 12. When the net 3 moves to the end of the launching bracket 6, the trigger nut 1 triggers the spring piece 12, simultaneously locking the compression spring chamber 11, causing the compression spring chamber 11 to stop moving. Meanwhile, the outer shell 2 continues to move outward under the action of spring 7 and spring 4, thus separating the outer shell 2 from the compression spring chamber 11.

[0023] like Figure 1 As shown, the base 9 and the compression spring chamber 11 are detachably connected by a snap-fit ​​mechanism 15, facilitating the installation, disassembly, and maintenance of the compression spring chamber 11. Ball bearings 10 are respectively provided at both ends of the inner wall of the base 9, and the launching bracket 6 has a double helical groove 13, with the ball bearings 10 slidably connected to the helical groove 13. Under the action of the spring 7, the ball bearings 10 move along the double helical groove 13, driving the base 9 to rotate at high speed. This allows the base 9 to rotate at high speed along the double helical groove 13 during movement, increasing the spreading effect and coverage area of ​​the net 3.

[0024] like Figure 2 As shown, the outer shell 2 has several drag-reducing guide grooves 14. During the launch of the net 3, the drag-reducing guide grooves 14 can reduce air resistance, improve the launch speed and flight stability of the net 3, and enable the net 3 to fly more accurately towards the target UAV. The elastic buffer layer is made of rubber and has anti-slip serrations.

[0025] The specific implementation process is as follows:

[0026] In use, an external force is applied to rotate the trigger 8, causing it to disengage from the groove in the base 9. At this moment, the compressive potential energy of spring 7 is released instantaneously, generating an axial thrust that pushes the base 9 along the axial direction of the launching bracket 6. The ball bearings 10 on the inner wall of the base 9 slide along the double helical groove 13 of the launching bracket 6, converting the axial motion into high-speed rotational motion. Driven by spring 7, the base 9 drives the compression spring chamber 11, the outer shell 2, and the net 3 to accelerate along the launching bracket 6 until they reach the end of the launching bracket 6. When the outer shell 2 reaches the position of the trigger nut 1, the trigger nut 1 contacts and triggers the spring piece 12 on the inner wall of the outer shell 2. Simultaneously, the latch and the spring piece 12 cooperate, causing the outer shell 2 to disengage from the compression spring chamber 11. At this point, the compression spring chamber 11 stops moving, while the outer shell 2 continues to move outward under the inertia of spring 7, separating from the compression spring chamber 11. After the outer shell 2 separates from the compression spring chamber 11, the constraint of spring 4 is released, and the compressive potential energy of the five springs 4 is released instantaneously, pushing the corresponding locking plates 5 outward. The clamp 5 launches the five corners of the capture net 3 at high speed, forming an umbrella-shaped structure. Due to the high-speed rotation of the base 9, the capture net 3 is subjected to centrifugal force during launch, further expanding outward to its maximum area, forming a capture net surface with a larger diameter. The unfolded capture net 3 continues to fly forward under inertia, covering the target drone and causing it to lose balance and flight capability.

[0027] By changing the axial position of the trigger nut 1, the timing of separation between the outer casing 2 and the compression spring chamber 11 can be adjusted. Adjusting the trigger nut 1 forward can delay separation, increase the action distance of the spring 7, and improve the initial ejection velocity.

[0028] The above descriptions are merely embodiments of this utility model. Commonly known technical solutions and / or characteristics are not described in detail here. It should be noted that those skilled in the art can make various modifications and improvements without departing from the technical solution of this utility model. These modifications and improvements should also be considered within the scope of protection of this utility model, and will not affect the effectiveness of the implementation of this utility model or the practicality of the patent. The scope of protection claimed in this application should be determined by the content of its claims, and the specific embodiments described in the specification can be used to interpret the content of the claims.

Claims

1. A mechanical catapult apparatus for unmanned aerial vehicle capture nets, characterized by: The system includes a launching bracket (6), which is movably connected to a base (9). The launching bracket (6) is rotatably connected to a trigger (8), which cooperates with the base (9). The launching bracket (6) is connected to a spring (7), the other end of which cooperates with the base (9). The base (9) is detachably connected to a compression spring chamber (11), which is detachably connected to a housing (2). The housing (2) is connected to a net (3). The net (3) is movably connected to a clamping plate (5), the compression spring chamber (11) is connected to a second spring (4), the other end of the second spring (4) cooperates with the clamping plate (5), the clamping plate (5) is connected to an elastic buffer layer, the launching bracket (6) is threadedly connected to a trigger nut (1), the outer shell (2) is provided with a spring piece (12), the spring piece (12) cooperates with the trigger nut (1), the compression spring chamber (11) is provided with a locking block (16), the locking block (16) cooperates with the spring piece (12).

2. A mechanical catapult for unmanned aerial vehicle catching nets as claimed in claim 1, wherein: The base (9) and the compression spring chamber (11) are detachably connected by a snap-fit ​​mechanism (15).

3. A mechanical catapult for unmanned aerial vehicle catching net as claimed in claim 1 wherein: The base (9) is provided with ball bearings (10), and the launch bracket (6) is provided with a spiral groove (13). The ball bearings (10) are slidably connected to the spiral groove (13).

4. A mechanical catapult for unmanned aerial vehicle catching nets as claimed in claim 1, wherein: The outer shell (2) is provided with a drag-reducing guide groove (14).

5. A mechanical catapult for unmanned aerial vehicle catching nets as claimed in claim 1, wherein: The elastic buffer layer is made of rubber and has anti-slip serrations.

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