Unmanned aerial vehicle capturing device

Abstract

The invention discloses an unmanned aerial vehicle capturing device and relates to the technical field of unmanned aerial vehicle countering equipment. The device comprises a base body, wherein a cavity which is gradually expanded forwards is limited in the base body; the pushing body is accommodated in the cavity and can move along the axial direction of the pushing body under the driving of external force; the plurality of casting bodies are circumferentially arranged between the pushing body and the wall surface of the cavity; the net body is connected to the projectile bodies; wherein the movement of the pushing body can drive the plurality of casting bodies to obliquely move forwards and outwards along the wall surface of the cavity and to be ejected, so that the net body is driven to be unfolded. The capturing device is simple in structure, low in manufacturing cost and suitable for being carried and used by an individual soldier.

Description

Technical Field

[0001] This invention relates to the field of drone countermeasure equipment technology, and in particular to a drone capture device. Background Technology

[0002] In existing drone countermeasures equipment, gunpowder is often used as the power source for launching capture nets. For example, Chinese patent document CN107963218A discloses a drone net capture device that generates power by electrically igniting a gunpowder barrel within an ignition chamber. However, this gunpowder-based power solution has significant drawbacks: firstly, its high cost makes it unsuitable for large-scale deployment; secondly, its large size and heavy weight make it difficult to mount on other mobile platforms; and finally, gunpowder itself poses a high risk during transportation and carrying. These factors collectively limit the application of such devices in individual soldier combat environments. Summary of the Invention

[0003] The purpose of this invention is to provide a drone capture device that is simple in structure, low in cost, and suitable for individual soldier to carry and use.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] A drone capture device, comprising:

[0006] A matrix that defines a progressively expanding chamber.

[0007] A pushing body is housed within the cavity and can move along its axial direction under external force.

[0008] Multiple projectiles are circumferentially disposed between the propulsion body and the chamber wall; and

[0009] A net body is connected to each of the aforementioned projectiles;

[0010] The movement of the propulsion body can drive the multiple projectiles to move obliquely forward and outward along the cavity wall and be launched, thereby causing the net to unfold.

[0011] In the above scheme, there are three projectiles, and three traction cables are provided along the edge of the net, with each traction cable connected to one of the projectiles.

[0012] In the above scheme, the propulsion body is configured such that after it is launched from the base along with the projectile, its flight speed lags behind that of the projectile.

[0013] In the above scheme, the shape of the propulsion body is a tapered cone that tapers forward, and the projectile is circumferentially disposed in the annular space between the tapered outer wall of the propulsion body and the wall of the chamber.

[0014] In the above scheme, the inner wall of the cavity is provided with a guide structure extending along its generatrix direction, and the projectile is slidably engaged with the guide structure; when the pusher moves forward under the drive of external force, it can radially compress the projectile, causing it to move along an oblique forward and outward trajectory under the guidance of the guide structure and be ejected from the front end of the base.

[0015] In the above scheme, the guiding structure is a guiding protrusion or a guiding groove.

[0016] In the above solution, the drone capture device further includes:

[0017] A cover is installed at the front end of the base;

[0018] The cover is configured such that, in the initial state, its inner side can abut against the front end of the pusher (e.g., with a top support) to restrict its forward movement in the initial state; and during launch, it can break or separate under impact from the inside to provide a channel for the ejection of the projectile and the net.

[0019] In the above solution, the part of the cover that abuts against the front end of the pusher (e.g., the top support part located inside / at the rear end of the cover) is provided with a positioning groove.

[0020] In the above scheme, the cover is assembled from multiple separate blocks, which are connected by a first fragile structure (such as a wax seal structure); the outer periphery of the cover is fixed with an mounting sleeve by a second fragile structure (such as a wax seal structure), and the mounting sleeve is detachably connected to the front end of the base (such as a threaded connection).

[0021] In the above scheme, the multiple split blocks are evenly divided sector-shaped bodies.

[0022] In the above scheme, the projectile is connected to the substrate and / or the propulsion body through a fragile connection structure (such as a wax seal structure).

[0023] In the above scheme, the projectile includes a spherical projectile head and a swallowtail-shaped projectile tail.

[0024] In the above scheme, the outer surface of the projectile is constructed with an aerodynamic stabilizing surface, which is used to generate a stable guiding vortex on one side of the projectile during flight, so as to provide a lateral aerodynamic force to maintain its oblique forward and outward flight trajectory.

[0025] In the above scheme, the aerodynamic stabilizing surface is an arc-shaped groove extending forward and backward on the side of the projectile near the inner wall of the base cavity.

[0026] In the above scheme, the net body has a central hole in the middle, and the central hole is sleeved on the pushing body; the net body is housed in the cavity of the base body and is located behind the projectile.

[0027] In the above scheme, the net body is respectively housed in multiple independent spaces along the circumference, which are enclosed by adjacent projectiles, the inner wall of the cavity of the base and the outer wall of the pusher body.

[0028] In the above solution, the drone capture device further includes:

[0029] A connector for detachably mounting the base to the front end of the barrel of a gun body;

[0030] The connecting body has a channel configured to allow the fired projectile to pass through it when the gun is fired and impact the rear end of the propulsion body, thereby transferring kinetic energy to the propulsion body.

[0031] In the above scheme, the connecting sleeve is a split structure, including at least two split sleeves. The split sleeves are connected and fixed by fasteners and are configured to be coaxially clamped and installed on the front end of the barrel.

[0032] The UAV capture device provided by this invention achieves extreme structural simplification through a highly integrated core architecture of "base-propulsion-projectile-net". This device has fewer components and a simpler processing and assembly process, significantly reducing manufacturing costs and logistical burden, making it particularly suitable for large-scale deployment and assembly in battlefield environments.

[0033] In use, the device utilizes an external power source to provide an instantaneous impact, driving the propulsion body to move axially within the base. Through its synergistic action with the base cavity walls, the propulsion body converts the axial linear thrust into a radial expansion force on the circumferential projectiles, ultimately causing all projectiles to be launched synchronously along a pre-set oblique forward-outward trajectory. This then straightens and pulls the net, causing it to rapidly open outwards during flight. The entire process requires no internal power source or complex operation, exhibiting extremely high response speed and ease of use.

[0034] In practical applications, this device, as an independent functional module, can be quickly integrated with standard individual firearms via a standard interface. Its core advantage lies in directly utilizing the firing energy of the firearm as a power source, instantly adding a highly efficient low-altitude UAV capture capability to the individual soldier without altering or affecting any of the firearm's original firing functions. This design breaks down the functional barriers of traditional equipment, achieving instantaneous switching between "killing" and "capturing" modes, significantly enhancing the individual soldier's comprehensive combat and diversified counterattack capabilities in complex modern battlefields. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the overall structure of the drone capture device in the embodiment;

[0036] Figure 2 This is a cross-sectional view of the drone capture device in the embodiment;

[0037] Figure 3 Disassembly of the drone capture device in the embodiment Figure 1 ;

[0038] Figure 4 Disassembly of the drone capture device in the embodiment Figure 2 ;

[0039] Figure 5 Disassembly of the drone capture device in the embodiment Figure 3 ;

[0040] Figure 6 This is a schematic diagram of the structure in which the auxiliary pusher and the flying dart body are installed in the loading cylinder in the embodiment;

[0041] Figure 7 This is a schematic diagram of the loading cylinder in the embodiment;

[0042] Figure 8 This is a schematic diagram of the capture net in the open state in the embodiment.

[0043] In the picture:

[0044] 1 – Loading cylinder; 2 – Auxiliary push block; 2a – Mounting slot; 2b – Notch;

[0045] 2c – Positioning recess; 3 – Dart body; 3a – Dart head;

[0046] 3b – Dart tail; 3c – Arc-shaped groove; 4 – Catching net;

[0047] 4a – Center hole; 5 – Traction cable; 6 – End cap; 7 – Top support;

[0048] 7a – Positioning groove; 8 – Separate block; 9 – Mounting sleeve;

[0049] 10 – Connecting sleeve; 10a – Split sleeve; 11a – Guide protrusion;

[0050] 11a1 – Inclined structure; 11b – Guide groove; 12 – Limiting shoulder;

[0051] 13 - Gun barrel; 14 - Projectile. Detailed Implementation

[0052] The present invention will be further described below with reference to specific embodiments, but the scope of protection of the present invention is not limited thereto.

[0053] This embodiment provides a drone capture device. Through a simple structural design and a small number of core components, this device achieves efficient and low-cost drone capture capabilities. Its low cost makes it particularly suitable for large-scale deployment and use in battlefield environments. Importantly, this device can be used in conjunction with standard firearms. It is detachably mounted to the front of the barrel via a connecting mechanism, directly utilizing the impact force generated by the bullet during firing as its power source. This design allows soldiers to gain the additional ability to capture drones without any structural modifications to their firearms; simply by adding this device, they can maintain the original firing function of the weapon, thereby significantly improving the multi-mission combat effectiveness of individual soldiers at a very low cost.

[0054] The specific structure of the drone capture device in this embodiment will be described below.

[0055] like Figures 1-8 As shown, the drone capture device in this embodiment mainly consists of two parts: a capture mechanism and a connection mechanism, which are functionally independent but related.

[0056] The capture mechanism includes: a base serving as a support frame, defining a forward-expanding chamber; a propulsion body serving as a power conversion element, housed within the chamber; multiple projectiles serving as kinetic energy projectiles, circumferentially disposed between the propulsion body and the chamber wall; a net serving as a deployable interceptor component, its edges connected to each projectile; and a cover serving as a front-end closure, mounted on the front end of the base. Axial movement of the propulsion body drives the multiple projectiles to move obliquely forward and outward along the chamber wall and be ejected, thereby deploying the net. The cover is configured such that, in the initial state, its inner side abuts against the front end of the propulsion body to limit its accidental forward movement; and upon launch, it can rupture or separate under internal impact, providing a passage for the ejection of the projectiles and the net.

[0057] The connecting mechanism includes a connector for detachably mounting the base to the front end of the barrel of a gun body. The connector has a through channel configured to allow the fired projectile to pass through it and directly impact the rear end of the propulsion body when the gun body is fired, thereby transferring kinetic energy to the propulsion body.

[0058] To facilitate understanding by those skilled in the art, a preferred embodiment will be described in detail below. In this embodiment, the base is specifically a loading cylinder 1, the pushing body is specifically an auxiliary pushing block 2, the projectile is specifically a dart body 3, the net is specifically a catching net 4, the cover is specifically an end cap 6, and the connecting body is specifically a connecting sleeve 10.

[0059] In this embodiment, the capture mechanism uses the loading cylinder 1 as the core support component, while the connection mechanism uses a connecting sleeve 10 as the core support component. The loading cylinder 1 and the connecting sleeve 10 are detachably connected by threads; at the same time, the connecting sleeve 10 is configured to be detachably fixed to the front end of the barrel 13 of the gun body, thereby realizing the portability and quick assembly and disassembly of the entire device.

[0060] In practical use, the connecting sleeve 10 can be permanently fixed to the barrel 13. Its internal channel diameter is designed to ensure it does not obstruct normal firing (such as bullet firing). After the capture net 4 inside the loading tube 1 is fired, the operator can quickly unscrew the empty loading tube 1 from the connecting sleeve 10 and install a loading tube 1 pre-loaded with a new capture net 4. This modular design greatly reduces reloading time and ensures operational continuity.

[0061] like Figure 2 , 7 As shown, in this embodiment, the loading cylinder 1 serves as the base of the capture mechanism. Its structure is a cylindrical structure that runs through the front and back, and its inner cavity (i.e., chamber) is cone-shaped and expands outward towards the front end, meaning that the diameter of the inner cavity gradually increases from back to front (expands forward). This inner cavity is used to house core components such as the auxiliary pusher 2, the flying dart body 3, and the capture net 4, and its front end is sealed and protected by an end cap 6.

[0062] Regarding the external shape of the loading cylinder 1, a cylindrical shape is preferred. Specifically, its shape can be a simple straight cylinder or a near-conical shape adapted to its conical inner cavity. Regardless of the shape, its design must adhere to a basic principle: it must not obstruct or interfere with the aiming line of sight (i.e., the "front sight") of the firearm's mechanical or optical sights. To achieve this requirement, various design strategies can be adopted. For example, the overall dimensions of the loading cylinder 1 can be controlled within a certain range to avoid the aiming baseline; or, a through-type observation slot can be opened on its cylinder wall at a specific position corresponding to the line connecting the front and rear sights of the firearm. The specific implementation scheme can be flexibly selected according to the actual firearm model and aiming method being mounted.

[0063] like Figures 2-4 As shown, in this embodiment, the auxiliary pusher 2 serves as the driving body of the capture mechanism. Its shape is a cone that tapers towards the front end, meaning its outer diameter gradually decreases from back to front (forward taper). The auxiliary pusher 2 is coaxially mounted in the conical inner cavity of the loading cylinder 1, with its rear end (large diameter end) facing the rear inlet of the loading cylinder 1. It is used to receive the driving force from an external power source so that it can move forward axially under the drive of this external force.

[0064] The axial movement of the auxiliary pusher 2 within the loading cylinder 1 is constrained in two ways: firstly, its rear end is restricted because its outer diameter is larger than the inner diameter of the rear inlet of the loading cylinder 1, preventing it from detaching from the rear; secondly, its front end is initially held in place by the support portion 7 of the end cover 6, preventing it from moving forward. Therefore, the auxiliary pusher 2 is reliably confined within the loading cylinder 1, and can only be pushed open by a sufficiently large pushing force to move it from the front end of the loading cylinder 1. This constraint design ensures that when replacing a pre-installed loading cylinder 1 module individually, the auxiliary pusher 2 remains securely positioned within the cylinder and will not accidentally detach, thus guaranteeing the convenience and reliability of logistical operations.

[0065] In this embodiment, the dart body 3 serves as the projectile of the capture mechanism, and there are multiple dart bodies (e.g., at least three), circumferentially arranged within the annular space between the loading cylinder 1 and the auxiliary pusher block 2. Preferably, there are three dart bodies 3. This annular space is jointly formed by the conical outer surface of the auxiliary pusher block 2 and the conical inner cavity surface of the loading cylinder 1, with its outer wall (inner wall of the loading cylinder 1) gradually expanding towards the front end and its inner wall (outer wall of the auxiliary pusher block 2) gradually narrowing towards the front end. The movement of the dart body 3 is constrained and guided by a set of guide structures. Specifically, the guide structure is a guide protrusion 11a or guide groove 11b provided on the inner wall of the loading cylinder 1 and extending along the generatrix of the inner wall; correspondingly, the dart body 3 is provided with a matching guide groove 11b or guide protrusion 11a, forming a clearance fit, allowing the dart body 3 to slide along the guide structure. Figure 6 , 7 As shown, in this embodiment, the inner wall of the loading cylinder 1 is provided with a guide protrusion 11a, and the dart body 3 is provided with a guide groove 11b. During operation, the auxiliary pusher 2 is pushed forward by the thrust, and its conical surface radially compresses and drives the dart body 3, causing it to obtain an initial velocity and direction obliquely forward and outward under the guidance of the guide structure (i.e., moving along an obliquely forward and outward trajectory), and be launched from the front end of the loading cylinder 1. After being launched, the dart body 3 will rely on its acquired kinetic energy (initial momentum) to continue flying along the designed trajectory, and drive the capture net 4 to open.

[0066] In some embodiments, the number of dart bodies 3 may also be four or more.

[0067] like Figure 8As shown, in this embodiment, the capture net 4 serves as the net body of the capture mechanism, and its arrangement is as follows: its edges are connected one-to-one with each flying dart body 3 via traction cables 5 (three to three in this embodiment), and the entire net is housed within the inner cavity of the loading cylinder 1 behind the flying dart body 3. The housing structure is specifically divided into two levels: First, the central hole 4a in the middle of the capture net 4 is fitted onto the auxiliary push block 2, achieving center positioning. Based on this, any excess net body is housed within multiple circumferentially independent spaces enclosed by adjacent flying dart bodies 3, the inner wall of the loading cylinder 1, and the outer wall of the auxiliary push block 2, thus achieving a compact and orderly folding.

[0068] Among them, the capture net 4 can be a net structure with an open shape of an equilateral triangle.

[0069] It should be noted that the axial movement of the auxiliary pusher 2 within the loading cylinder 1 is constrained to prevent it from moving backward. This constraint is achieved by the following method: since the outer diameter of the rear end (larger diameter end) of the auxiliary pusher 2 is larger than the inner diameter of the rear inlet of the loading cylinder 1, a natural backward mechanical limit is formed, thus reliably preventing the auxiliary pusher 2 from detaching from the rear end of the loading cylinder 1. Simultaneously, the auxiliary pusher 2 and the loading cylinder 1 are slidably engaged by an independent guiding structure (such as a guide protrusion 11a on the inner wall of the loading cylinder 1 and a guide groove 11b on the outer wall of the auxiliary pusher 2, or vice versa) to guide its forward movement trajectory. Alternatively, an independent mechanical limiting structure can be provided to prevent the auxiliary pusher 2 from moving backward. For example, an inwardly protruding limiting shoulder 12 (which can be a continuous or discontinuous structure) can be provided on the inner side of the rear end of the loading cylinder 1, the inner diameter of which is smaller than the outer diameter of the rear end of the auxiliary pusher 2. When the auxiliary pusher 2 moves backward, its rear end is blocked by the limiting shoulder 12, thereby achieving reliable rearward mechanical limiting. The limiting shoulder 12 for rearward limiting can be designed as an integral structure with the guide protrusion 11a extending along the generatrix of the inner wall of the loading cylinder 1. Specifically, the limiting shoulder 12 can be formed by radially thickening the rear end of the guide protrusion 11a or adding a step, causing its inner edge contour to protrude inward. The limiting shoulder 12 also facilitates the positioning and installation of the auxiliary pusher 2 within the loading cylinder 1.

[0070] As an alternative, to achieve a more compact structural layout, the rear end face of the auxiliary push block 2 and the rear end port of the loading cylinder 1 can be designed to be on the same plane. In this design, the outer diameter of the rear end of the auxiliary push block 2 is basically the same as the inner diameter of the rear end port of the loading cylinder 1, and a rearward limiting is achieved by setting a limiting shoulder 12 on the inner side of the rear end of the loading cylinder 1. At this time, the rear end face of the auxiliary push block 2 directly serves as the bearing surface, abutting against the front end face of the limiting shoulder 12. Of course, the rear end face of the auxiliary push block 2 can also have a notch 2b corresponding to the limiting shoulder 12, with the limiting shoulder 12 abutting against the notch 2b, making the rear end face of the loading cylinder 1 completely flat.

[0071] In some embodiments, to increase the effective range of the device, the front end of the guide structure can be optimized. Specifically, the front end of the guide protrusion 11a extending along the inner wall of the loading cylinder 1 can be designed as an inwardly inclined structure 11a1 towards the central axis of the loading cylinder 1, such as... Figure 7 As shown, this design allows the dart body 3 to have a slightly inward initial tendency of motion the moment it leaves the loading cylinder 1. This tendency effectively suppresses its excessively rapid radial expansion velocity in the early stages of flight, thus using more launch kinetic energy to maintain forward axial flight. The effect is that the overall center of gravity of the dart body 3 and the capture net 4 can fly to a farther position, and then the capture net 4 fully expands under the pull of the traction cable 5, ultimately achieving effective interception of low-altitude, long-range UAVs while ensuring the capture range.

[0072] In this embodiment, the end cap 6 serves as the cover of the capture mechanism. It is disc-shaped and mounted on the front end of the loading cylinder 1. Its inner side can initially abut against the front end of the auxiliary pusher 2, restricting its forward movement. The end cap 6 is configured to open (e.g., break or separate) under impact from internal components (typically the pushing force of the auxiliary pusher 2), providing a passage for the launch of the dart body 3 and the capture net 4. Furthermore, the inner side of the end cap 6 can directly abut against the front end of the auxiliary pusher 2, or it can be provided with a protruding top support 7 to abut against the front end of the auxiliary pusher 2.

[0073] In this embodiment, the inner side of the end cap 6 is provided with a top support 7, and its rear end is provided with a positioning groove 7a, such as... Figure 2 , 4 As shown. The core functions of the positioning groove 7a are: first, radial positioning, which prevents the auxiliary pusher 2 from shaking and ensures initial stability by engaging with the tip of the auxiliary pusher 2; second, stress dispersion, which changes point contact to surface contact and avoids component wear; and third, ensuring coaxiality, which ensures that the auxiliary pusher 2 is coaxial with the loading cylinder 1, so that the auxiliary pusher 2 can evenly squeeze all the flying dart bodies 3 and ensure consistent launch trajectories.

[0074] like Figure 3 , 4As shown, to achieve quick opening, the end cap 6 is designed as a split structure, composed of multiple split blocks 8 (preferably evenly divided fan-shaped bodies) joined together. Each split block 8 is connected and fixed to the others by a first fragile structure (such as a wax seal). The top support 7 is part of the end cap 6, and together they are divided into multiple pieces. Furthermore, an mounting sleeve 9 (preferably a threaded sleeve) is fixed to the outer side of the end cap 6 by a second fragile structure (such as a wax seal). This mounting sleeve 9 is detachably connected (preferably threaded) to the front end of the loading cylinder 1. There are two optional thread designs between the mounting sleeve 9 and the loading cylinder 1: one is that the mounting sleeve 9 has an internal thread and the loading cylinder 1 has an external thread; the other is that the mounting sleeve 9 has an external thread and the loading cylinder 1 has an internal thread. The first option is preferred.

[0075] It should be noted that in this embodiment, a split structure is adopted, and the end cap 6 and the loading cylinder 1 are indirectly fixed together by the mounting sleeve 9. In some alternatives, the end cap 6 may omit the split block 8 and the mounting sleeve 9, and be directly connected and fixed to the front end port of the loading cylinder 1 by a fragile structure (such as a wax seal).

[0076] To ensure the stability of the dart body 3 within the loading cylinder 1 before launch, this embodiment connects the dart body 3 to the loading cylinder 1 and / or the auxiliary pusher block 2 via a fragile connection structure. The fragile connection structure (e.g., a wax seal) is configured to provide sufficient fixing force during storage and transportation, while also being able to be quickly and thoroughly destroyed by the impact force of the auxiliary pusher block 2 during launch, thereby ensuring that its fragments or residues do not interfere with the flight trajectory of the dart body 3.

[0077] In some alternatives, a fragile clamping structure can be used to achieve a more secure hold for the dart body 3 before launch. For example, a filler block made of a low-strength, fragile material (such as wax or a specific plastic) can be embedded in the guide groove 11b of the dart body 3. This filler block creates a slight interference between the guide groove 11b and the guide protrusion 11a, providing an initial clamping force. When the auxiliary pusher 2 pushes the dart body 3, the filler block breaks instantly upon impact, thereby immediately releasing the restraint and ensuring that it does not affect the subsequent normal movement of the dart body 3.

[0078] It should be noted that all the fragile connection structures used in this device, including but not limited to wax seals, are designed and made of the same material: that is, while providing sufficient pre-installed strength, they can be completely broken during launch and avoid interference with flight components.

[0079] like Figure 3 , 4As shown, in this embodiment, the dart body 3 includes a spherical dart head 3a (i.e., projectile head) and a dovetail-shaped dart tail 3b (i.e., projectile tail). Furthermore, the outer surface of the dart body 3 is constructed with an aerodynamic stabilizing surface to generate a stable guiding vortex on one side of the dart body during flight, providing a lateral aerodynamic force to maintain its obliquely forward-outward flight trajectory. Specifically, the aerodynamic stabilizing surface is an arc-shaped groove 3c extending forward and backward on the side of the dart body 3 near the inner wall of the loading cylinder 1.

[0080] Its working principle is as follows:

[0081] After the dart 3 is launched from the loading cylinder 1, its initial "obliquely forward and outward" trajectory tends to converge inward due to air resistance and the inward tilting structure 11a1 at the front end of the guide protrusion 11a. This tendency initially helps the dart 3 propel the partially opened capture net 4 a greater distance. Simultaneously, to address the issue of its continued inward convergence and inability to fully open, this embodiment utilizes the arc-shaped groove 3c—a specific aerodynamic stabilizing surface—to induce a stable guiding vortex on a specific side of the dart during flight. This vortex alters the local air pressure distribution on one side of the dart, generating a continuous and directionally controllable lateral aerodynamic force. This lateral force effectively compensates for or counteracts interference factors that cause the trajectory to converge inward during flight, thereby helping to stabilize and maintain the ideal "obliquely forward and outward" flight trajectory provided by the launching mechanism, ensuring that the capture net 4 fully opens to the predetermined range.

[0082] In this embodiment, the auxiliary pusher 2 is used to contact the conical outer surface of the dart body 3, and a positioning recess 2c adapted to the inner contour of the dart body 3 is provided, such as... Figure 3 , 4 As shown. The positioning recess 2c allows the dart body 3 to be stably fitted onto the surface of the auxiliary push block 2 in the initial state, thereby achieving better circumferential and radial positioning before launch.

[0083] In this embodiment, the auxiliary pusher 2 is configured such that, after being launched from the loading cylinder 1 along with the dart body 3, its flight speed lags behind that of the dart body 3. To achieve this speed difference, the two are designed differently in terms of materials and mass. Specifically, the dart body 3 is preferably made of a high-density metallic material (such as steel) to have sufficient flight inertia and penetrating power; while the auxiliary pusher 2 is preferably made of a low-density, high-strength non-metallic material (such as engineering plastics or composite materials). Under the premise of meeting the impact strength requirements, its lightweight characteristics ensure that its speed lags behind due to greater air resistance during flight.

[0084] To further improve the reliability of power transmission, an impact-resistant pressure-bearing part can be integrally provided at the rear end of the auxiliary push block 2. This pressure-bearing part is designed to have sufficient strength and rigidity to withstand the impact of the projectile 14 without plastic deformation or damage. Alternatively, an independent pressure-bearing part can be fixed to the rear end of the auxiliary push block 2 using methods such as interference fit or bonding to ensure that the two work as a single unit under stress. When using an interference fit, a mounting groove 2a for installing the pressure-bearing part can be provided at the rear end of the auxiliary push block 2, such as... Figure 4 As shown.

[0085] The end cap 6 and the loading cylinder 1 must meet the requirements of strength and lightweight in terms of material selection. Therefore, they can preferably be made of the same low-density, high-strength non-metallic materials (such as engineering plastics or composite materials) as the auxiliary pusher 2 to control the overall weight and ensure structural strength. In addition, the capture net 4 is made of a high-specific-strength flexible material, such as high-strength polyethylene fiber, Kevlar fiber, or nylon. These materials have extremely high tensile strength while maintaining lightweight and soft characteristics, ensuring that the capture net 4 can withstand huge impact forces without being torn when launched at high speed, and can effectively wrap around the UAV propeller blades after unfolding.

[0086] In this embodiment, the connecting mechanism is used to detachably mount the capturing mechanism to the front end of the barrel 13 of the gun body, and to position the rear end of the auxiliary push block 2 facing the barrel 13 to receive the impact force generated by the launched projectile 14. The connecting mechanism includes a connecting sleeve 10. This connecting sleeve 10 serves as a connector and has an internal channel for allowing the projectile 14 launched by the gun body to pass through it when the gun body is fired, so that the projectile 14 can impact the rear end of the auxiliary push block 2 and transfer kinetic energy to the auxiliary push block 2. Figure 5 As shown, the connecting sleeve 10 is designed as a split structure, consisting of at least two (e.g., two) split sleeves 10a, each connected and fixed by fasteners (e.g., quick-release bolts or ordinary bolts). This structure allows it to be coaxially and tightly fixed to the front end of the barrel 13. Specifically, the connecting sleeve 10 and the loading cylinder 1 are detachably connected, preferably by a threaded connection. The inner wall shape of the split sleeve 10a is adapted to the outer shape of the barrel 13 to ensure a tight fit and secure fixation. The inner channel diameter of the connecting sleeve 10 is not smaller than the diameter of the barrel 13 to ensure that it does not interfere with the normal firing and trajectory of the bullet. In practical applications, the connecting sleeve 10 can be pre-fixed to the barrel 13 as a permanent component. When a capture operation is required, the pre-installed capture mechanism can be quickly installed onto the connecting sleeve 10; after use, the capture mechanism can be replaced separately, making operation convenient and greatly improving tactical flexibility.

[0087] In some alternatives, to meet the tactical need for rapid switching between capture and firing modes, the connecting mechanism can be designed as a quick-release structure (e.g., using a snap-fit ​​or lever-locking connection). When direct firing of the firearm is required, the operator can quickly detach the entire capture mechanism from the connecting sleeve 10 at the front of the barrel 13, thereby completely avoiding any potential impact on the ballistics and achieving instantaneous switching of combat modes.

[0088] In summary, the UAV capture device provided in this embodiment, with its simple overall structure and few components, achieves ease of processing and manufacturing and effective control of manufacturing costs, making it particularly suitable for large-scale distribution and deployment in battlefield environments.

[0089] In use, the device utilizes the impact force generated by the projectile 14 launched from the gun body as instantaneous power to drive the auxiliary pusher 2 forward, thereby forcing the dart 3 to fly out rapidly along the guide structure. The entire process is simple to operate, responds quickly, and is extremely convenient to use.

[0090] In actual combat, this device, when used in conjunction with standard firearms, provides individual soldiers with an efficient capability to capture low-altitude drones without affecting their original firing functions. This design significantly expands the functional dimensions of individual weapons, effectively enhancing their comprehensive combat and diversified counterattack capabilities in complex battlefield environments.

[0091] This invention is not limited to the above embodiments. Those skilled in the art will understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of this invention. The scope of this invention is defined by the claims and their equivalents.

Claims

1. A drone capture device, characterized in that, include: A matrix that defines a progressively expanding chamber. A pushing body is housed within the cavity and can move along its axial direction under external force. Multiple projectiles are circumferentially disposed between the propulsion body and the chamber wall; and A net body is connected to each of the aforementioned projectiles; The movement of the propulsion body can drive the multiple projectiles to move obliquely forward and outward along the cavity wall and be launched, thereby causing the net to unfold.

2. The drone capture device according to claim 1, characterized in that, The propellant is shaped like a tapered cone that tapers forward, and the projectile is circumferentially disposed in the annular space between the tapered outer wall of the propellant and the wall of the chamber.

3. The drone capture device according to claim 2, characterized in that, The inner wall of the cavity is provided with a guide structure extending along its generatrix, and the projectile is slidably engaged with the guide structure. When the propulsion body moves forward under the drive of an external force, it can radially compress the projectile, causing it to move along an oblique forward and outward trajectory under the guidance of the guide structure and be ejected from the front end of the base.

4. The drone capture device according to claim 1, characterized in that, Also includes: A cover is installed at the front end of the base; The cover is configured such that, in the initial state, its inner side can abut against the front end of the pusher to restrict its forward movement; and during launch, it can break or separate under impact from the inside to provide a channel for the ejection of the projectile and the net.

5. The drone capture device according to claim 4, characterized in that, The cover is composed of multiple modular blocks, which are connected by a first fragile structure. A mounting sleeve is fixed to the outer periphery of the cover by a second fragile structure ring, and the mounting sleeve is detachably connected to the front end of the base.

6. The drone capture device according to claim 1, characterized in that, The projectile comprises a spherical projectile head and a swallowtail projectile tail.

7. The drone capture device according to claim 1 or 6, characterized in that, The outer surface of the projectile is constructed with an aerodynamic stabilizing surface, which is used to generate a stable guiding vortex on one side of the projectile during flight, so as to provide a lateral aerodynamic force to maintain its oblique forward and outward flight trajectory.

8. The drone capture device according to claim 7, characterized in that, The aerodynamic stabilizing surface is an arc-shaped groove extending forward and backward on the side of the projectile near the inner wall of the base cavity.

9. The drone capture device according to claim 1, characterized in that, The net body has a central hole in the middle, and the central hole is sleeved on the propellant body; the net body is housed in the cavity of the base body and is located behind the projectile.

10. The drone capture device according to claim 1, characterized in that, Also includes: A connector for detachably mounting the base to the front end of the barrel of a gun body; The connecting body has a channel configured to allow the fired projectile to pass through it when the gun is fired and impact the rear end of the propulsion body, thereby transferring kinetic energy to the propulsion body.

Images