Unmanned aerial vehicle catching net gun grenade

Abstract

The invention discloses an unmanned aerial vehicle catching gun grenade, and relates to the technical field of unmanned aerial vehicle defense. The gun grenade comprises an air cap, a heavy hammer part sleeve, a catching net, a net expanding exploder and a cartridge case. The heavy hammer part sleeve is formed by combining a plurality of split heavy hammer blocks, and the rear end of the heavy hammer part sleeve is hooped by a brittle constraint ring. The net expanding exploder comprises a delay ignition unit and an explosion initiation unit. After launching, the delay ignition unit triggers the detonation unit after delaying a preset time to generate impact to crush the brittle constraint ring, so that the heavy hammer block carries the catching net to be scattered and unfolded at a high speed, and interception is realized. The device is compact in structure, low in cost and high in reliability, can be launched through a gun grenade launcher, is particularly suitable for being carried and used by an individual soldier, and can effectively cope with the threat of a small-sized high-speed unmanned aerial vehicle.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) defense technology, specifically to a UAV netting grenade, which is particularly suitable for individual soldier use and adapts to the needs of infantry operations in modern dispersed offensive and defensive scenarios. Background Technology

[0002] With the rapid popularization of drone technology, small FPV drones, with their advantages of small size, high speed, and high maneuverability, are increasingly being abused in scenarios such as military reconnaissance and illegal intrusion into security areas, posing a new threat to regional security. In modern battlefields, infantry operations are mostly based on dispersed offense and defense, and the drone threat faced by individual soldiers is becoming increasingly prominent. However, existing interception methods are difficult to adapt to the needs of individual soldier operations: laser interception equipment is expensive and bulky, making it inconvenient for individual soldiers to carry; missile-based interception weapons are uneconomical and prone to causing collateral damage, making them unsuitable for close-range dispersed operations.

[0003] Therefore, there is an urgent need to develop a drone netting grenade that is small in size, suitable for individual soldiers to carry, can be launched from a grenade launcher, and is low in cost, highly reliable, quick to deploy, and has a wide interception range, in order to fill the gap in existing technology and meet the drone defense needs of infantry in modern dispersed combat scenarios. Summary of the Invention

[0004] 1. Technical problems to be solved

[0005] The purpose of this invention is to overcome the shortcomings of the prior art and provide a drone-launched net grenade, which solves the problem of high cost of existing interception methods, meets the needs of individual soldiers to carry, adapt to grenade launchers, and be used by infantry in modern dispersed offensive and defensive scenarios.

[0006] 2. Technical Solution

[0007] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0008] A drone-launched net-catching grenade, the core technical solution of which includes a wind cap (1), a hammer sleeve (2), a net (3), a time-delay detonator (4), and a cartridge case (7). The hammer sleeve (2) is composed of multiple separate hammer blocks (12) arranged circumferentially, forming a hollow cavity inside to accommodate the net (3); the front end of the hammer sleeve (2) is secured by a fixing ring (11), and the rear end is clamped by a brittle constraint ring (13) to maintain the assembled state; the time-delay detonator (4) is located behind the hammer sleeve (2), and includes a time-delay ignition unit and a detonation unit. The time-delay ignition unit triggers the detonation unit after a predetermined delay after launch. The detonation unit generates an impact that shatters the brittle constraint ring (13), causing the hammer blocks (12) to scatter and separate and unfold the net (3).

[0009] This rifle grenade has a compact structure, small size, and light weight, meeting the standards for individual soldier carrying. It can be directly adapted to existing individual soldier rifle grenade launchers for firing without the need for additional special equipment. It is a perfect fit for modern infantry combat scenarios involving dispersed offense and defense, enabling infantry to quickly respond to sudden drone threats during mobile operations.

[0010] • Wind cap (1): The wind cap (1) is installed at the front end of the projectile. Its function is to reduce air resistance, protect the internal structure, and ensure that the grenade maintains a stable trajectory during flight.

[0011] • The weighted hammer sleeve (2): The weighted hammer sleeve (2) is composed of multiple (preferably 4) separate weighted hammer blocks (12) arranged circumferentially, forming a hollow cavity inside to accommodate the net (3). The front end of the weighted hammer sleeve (2) is equipped with a fixing ring (11) and a wind cap (1), and the rear end is equipped with a brittle restraint ring (13) and a sealing ring (14). The contact surfaces at the front ends of adjacent weighted hammer blocks (12) are provided with mutually cooperating inclined surfaces so that after the brittle restraint ring (13) breaks, the weighted hammer blocks (12) can smoothly detach from the fixing ring (11) and scatter. The weighted hammer blocks (12) are provided with radially extending partitions to fix the net (3) and prevent entanglement when the weighted hammer sleeve (2) rotates. The rear end of the hammer sleeve (2) is clamped by a brittle constraint ring (13). In this embodiment, the brittle constraint ring (13) is a tempered glass ring, which has the characteristic of being able to be crushed as a whole after being broken at a single point. It can release the constraint without simultaneously detonating multiple points of the ring body. Compared with ring bodies made of other materials, it greatly improves the separation reliability. The rear end of the hammer block (12) is provided with a circular groove. This groove allows the cartridge case (7) to be fixed after installation, and also allows the hammer sleeve (2) and the cartridge case (7) to rotate relative to each other, providing a basis for adjusting the delay time. The rear end of the hammer block (12) has a concave surface. Four hammers (12) are combined to form a cross slot, and the cross block of the delay detonator (4) is locked in this slot.

[0012] • Net (3): The net (3) is housed in the hollow cavity of the counterweight sleeve (2), and its four corners are fixed to the corresponding counterweight blocks (12). The net (3) is woven from high-strength polymer wire, and the mesh size is slightly smaller than the typical fuselage width of the target UAV. This reduces wind resistance while ensuring that the UAV does not slip through the mesh, thus guaranteeing the interception effect.

[0013] • Delayed detonator (4): The delayed detonator (4) is located behind the hammer sleeve (2) and includes a delayed ignition unit and a detonation unit.

[0014] ○ Delayed ignition unit: Includes a pressure plate (6) fixed relative to the cartridge case (7), with an ignition hole on the pressure plate (6); also includes a delayed detonation plate (42) that rotates synchronously with the counterweight sleeve (2), with a fuse groove on the delayed detonation plate (42). To improve reliability, an S-shaped fuse groove is used, consisting of a straight section and an arc section connecting both ends. A delayed fuse (44) is laid in the groove. The ignition end of the delayed fuse (44) is opposite to the ignition hole on the pressure plate (6), and the burning end is connected to the detonation unit. By rotating the counterweight sleeve (2) and the cartridge case (7) relative to each other, the relative position of the ignition end and the ignition hole can be changed, and the effective burning length of the delayed fuse (44) can be adjusted, thereby setting a predetermined delay time. A timing plate (5) is provided between the pressure plate (6) and the delayed detonation plate (42). The timing plate (5) is a thin circular plate made of copper with a thickness of no more than 0.3 mm. The timing plate (5) has an ignition hole at the same position as the pressure plate (6). When the propellant burns, the delay fuse (42) is ignited through this ignition hole. Before firing, the timing plate (5) and the pressure plate (6) are locked together to prevent relative rotation, but they can rotate relative to the delay detonation plate (42). During firing, under the action of firing pressure, the timing plate (5) undergoes plastic deformation and couples with the edge groove of the delay detonation plate (42). During flight, it rotates synchronously with the delay detonation plate (42) to avoid the delay time being changed due to the displacement of the ignition position.

[0015] ○ Detonation unit: includes a block (i.e., the cross block part of the delayed detonation plate 42), which has two to four axially extending guide holes that are evenly distributed circumferentially; the firing pin (41) is set in the guide hole in a clearance fit, forming a piston structure with the guide hole; the front end of the firing pin (41) faces the brittle restraint ring (13), and there are broken particles (diamond particles in this embodiment) with a hardness higher than that of the brittle restraint ring (13) at the front end of the firing pin (41); the detonating charge (43) is set at the rear of the firing pin (41), and after being ignited by the delayed fuse (44), it generates high-pressure gas, which drives the firing pin (41) to impact the brittle restraint ring (13) forward.

[0016] • Cartridge Case (7): The cartridge case (7) is used to install the primer (72) and propellant (71), and houses components such as the delayed ignition unit and the detonation unit, protecting the components from damage during transportation. The rear end of the counterweight sleeve (2) is inserted into the cartridge case (7), and the two are connected by a ring-shaped interlocking tenon structure and can rotate relative to each other, which is used to adjust the delay length.

[0017] 3. Beneficial effects

[0018] The drone net-catching grenade of the present invention has the following beneficial effects:

[0019] (1) High overall practicality: It adopts the core design of "segmented heavy hammer block + brittle constraint ring + delayed detonation", which is compact in structure and low in cost, and does not require complex precision manufacturing process. It is small in size and lightweight, suitable for individual soldier to carry and for firing with existing rifle grenade launchers. It perfectly meets the needs of infantry use in modern dispersed offensive and defensive scenarios, and enables individual soldiers to have real-time drone defense capabilities in mobile operations.

[0020] (2) High separation reliability: The tempered glass ring is used as a brittle constraint ring. Its characteristic of being pulverized as a whole after being broken at a single point solves the drawback of traditional rings requiring multiple points of detonation, greatly reducing the risk of separation failure. Combined with four circumferentially evenly distributed impact pins, it effectively avoids interception failure caused by the failure of a single impact pin, further improving the reliability of detonation and separation.

[0021] (3) Precise delay control: The S-shaped fuse groove on the delay detonation plate extends the fuse laying length in a limited space, expands the delay adjustment range, and the smooth path ensures stable fuse combustion; the timing plate made of copper with a thickness of no more than 0.3mm is locked with the pressure plate before launch and can rotate relative to the delay detonation plate. After launch, it is coupled with the delay detonation plate to move synchronously, ensuring that the delay time is precise and controllable and avoiding the ignition position deviation during flight.

[0022] (4) Excellent net deployment effect: The partition design in the weight block avoids the phenomenon of entanglement when the net rotates, ensuring that the net can be deployed quickly and without obstruction when the weight block separates; the guide slope design of adjacent weight blocks makes the weight blocks separate more smoothly, and the net can quickly form an effective interception diameter of 3-5 meters with a wide coverage area.

[0023] (5) High interception success rate: The piston structure formed by the firing pin and the guide hole ensures that the high-pressure gas generated by the combustion of the detonator does not leak, providing sufficient impact speed for the firing pin; the high-hardness crushing particles at the front end of the firing pin can reliably shatter the tempered glass ring; the net is woven with high-strength polymer wire, and the mesh size is smaller than the width of the target UAV, ensuring that the UAV will not escape the net during the interception process, effectively dealing with highly maneuverable small UAVs. Attached Figure Description

[0024] Appendix Figure 1 : Overall structural diagram of the net-catching grenade.

[0025] In the picture: 1-Wind cap, 2-Weighted hammer cover, 3-Catching net, 4-Delayed detonator, 5-Timer plate, 6-Pressure plate, 7-Cartridge casing.

[0026] Appendix Figure 2 : Structural diagram of the counterweight sleeve.

[0027] In the diagram: 11-fixed ring, 12-weighted hammer block, 3-catch net, 13-brittle restraint ring, 14-sealing ring.

[0028] Appendix Figure 3 : Structure diagram of the heavy hammer block (12).

[0029] Appendix Figure 4 : Schematic diagram of the structure of the time-delay detonator (4).

[0030] In the diagram: 41-Firing pin, 42-Delay detonation plate, 43-Detonating charge, 44-Fuse.

[0031] Appendix Figure 5 : Structural diagram of the delayed detonation plate (42).

[0032] Appendix Figure 6 : Schematic diagram of the pressure plate (6).

[0033] Appendix Figure 7 :Structure diagram of cartridge case (7).

[0034] In the diagram: 71 - propellant, 72 - primer.

[0035] Appendix Figure 8 : Structural diagram of timing board (5). Detailed Implementation

[0036] The specific embodiments of the present invention will be further described in detail below with reference to the accompanying drawings.

[0037] Appendix Figure 1 This is an overall structural diagram of the net-catching grenade. The UAV net-catching grenade of this embodiment includes a wind cap (1), a hammer sleeve (2), a net (3), a time-delay detonator (4), a timing plate (5), a pressure plate (6), and a cartridge case (7). The wind cap (1) is installed at the front of the hammer sleeve (2), and the hammer sleeve (2) and the cartridge case (7) are connected by a ring-shaped tenon and mortise structure. The time-delay detonator (4) is installed at the rear of the hammer (2), and the hammer blocks (12) are respectively locked on the cross block structure of the time-delay detonator plate (42); the circular plate plane of the time-delay detonator plate (42) is connected to the timing plate (5), and the timing plate (5) is connected to the pressure plate (6).

[0038] The junction of the cartridge case (7) and the hammer sleeve (2) is marked with graduations. Before actual use, infantrymen can determine the delayed detonation distance by rotating the hammer sleeve (2) and the cartridge case (7) according to the battlefield environment, the flight speed and distance requirements of the small drones to be intercepted. The principle of the delay is as follows: the hammer sleeve (2) and the cartridge case (7) are connected by a ring-shaped tenon and mortise structure and can rotate relative to each other; the cross block structure of the delayed detonation plate (42) is connected to the slot at the tail of the hammer sleeve (2), so rotating the hammer sleeve (2) will drive the delayed detonation plate (42) to rotate synchronously; at this time, the timing plate (5) and the pressure plate (6) are locked and do not rotate with the delayed detonation plate (42). Through this operation, the relative position of the fuse ignition end of the delayed detonation plate (42) and the ignition hole of the pressure plate (6) can be changed, the effective burning length of the delayed fuse can be adjusted, and the required delay time can be set.

[0039] At launch, the infantryman fires the grenade through a grenade launcher. The grenade launcher ignites the primer (72) of the cartridge case (7), causing the propellant (71) inside the cartridge case (7) to burn and generate high-pressure gas. This gas propels the projectile structure (excluding the cartridge case (7)) toward the target area and ignites the delay fuse (44) through the ignition hole on the pressure plate (6). At the same time, the launch pressure causes the timing plate (5) to undergo plastic deformation and couple with the edge groove of the delay detonation plate (42). During flight, the two rotate synchronously to avoid the delay time being changed due to the displacement of the ignition position.

[0040] Appendix Figure 2 This is a structural diagram of the hammer sleeve (2). As shown, several hammer blocks (12) are combined together, with a net (3) installed inside. The front is fixed with a fixing ring (11), and the back is fixed with a brittle restraint ring (13) to form a whole hammer sleeve (2). The brittle restraint ring (13) is made of brittle material, preferably tempered glass. Tempered glass has internal stress, which increases the strength of the glass. Another feature is that it will shatter immediately if it cracks even slightly. At the junction of the brittle restraint ring (13) with the hammer blocks (12) and the delayed detonator (4), a non-Newtonian fluid flexible material is used as a buffer to prevent the brittle restraint ring (13) from breaking prematurely due to excessive stress when it comes into contact with other parts. A mixture of polyethylene glycol and silica is preferred.

[0041] Appendix Figure 3This is a structural diagram of the weight block (12). As shown in the figure, the front end of the weight block (12) has a slope at the right-angle contact surface with the adjacent weight block (12). This slope allows the weight block (12) to be smoothly dislodged from the fixing ring (11) when they separate. There is also an annular groove at the rear of the weight block, in which a sealing ring (14) is installed. The sealing ring (14) is fan-shaped. The function of the sealing ring is to seal and prevent the propellant from becoming damp and ineffective. If the sealing ring is not used, applying glass glue to the annular groove can also achieve a sealing effect. There is a groove on the right-angled plane of the weight block (12). When several weight blocks (12) are combined together, this groove forms a barrel-shaped space, in which the net (3) is installed. There is also a flat surface at the rear of the groove for fixing the connecting rope of the net (3). When the weight blocks (12) are scattered and separated, the net (3) is unfolded. However, after the hammer sleeve (2) is launched, it begins to rotate. To prevent the net (3) from becoming entangled due to inertia, there is a long partition inside the groove of the hammer block (12). The partition's function is to push the net (3) and the hammer block (12) to rotate together. There is also a cartridge band on the arc surface of the hammer block (12), which causes the rifle grenade to spin and fly out under the action of the rifling when it is launched. The last section of the hammer block (12) has a concave surface. When the hammer sleeve (2) uses 4 hammer blocks (12), the concave surface forms a cross groove, and the cross block of the delayed detonator (4) is stuck in this cross groove.

[0042] Appendix Figure 4 : Schematic diagram of the delayed detonator (4). The delayed detonator (4) consists of a firing pin (41) and a delayed detonation plate (42). The firing pin (41) is installed inside the delayed detonation plate (42). The detonating charge (43) is installed at the rear of the firing pin (41), and the fuse (44) is installed below it. There is a channel connecting the fuse (44) and the detonating charge (43). When the delayed fuse (44) is ignited, it burns to the detonating charge (43), which is then ignited and explodes. The high-pressure gas generated pushes the firing pin (41) to move at high speed along the axial direction of the guide hole. The front end of the firing pin (41) is coated with high-hardness crushing particles (preferably diamond particles). As long as one of the firing pins (41) hits the brittle restraint ring (13) (in this embodiment, it is a tempered glass ring), the brittle restraint ring (13) can be instantly crushed as a whole, quickly releasing the restraint on the hammer sleeve (2).

[0043] Appendix Figure 5This is a structural diagram of the delayed detonation plate (42). The delayed detonation plate (42) is a combination of a cross block and a circular plate with a groove. The cross block is coupled to the counterweight sleeve (2), and there is a guide hole in the cross block. The guide hole and the firing pin (41) form a piston structure, which pushes the firing pin (41) forward to strike the brittle restraint ring (13) after the detonation of the explosive (43). There is at least one firing pin, and the increased number is to improve the reliability of breaking the brittle restraint ring (13). The flat surface of the circular plate has a groove to prevent the fuse (44). The groove shape can be E-shaped, and the horizontal segment has a channel connecting to the guide hole in the cross block. The radius of the arc portion of the E-shaped groove is the same, so that when the delayed detonation plate (42) rotates, the ignition hole of the timing plate (5) is always aligned with the delayed fuse (44). To improve the ignition success rate, two ignition points can be set, the groove can be made into an S-shape, the middle part of the S-shape can be made into a straight line segment, and there is a channel on the straight line segment that connects to the guide hole in the cross block. The two ignition holes of the timing plate (5) correspond to the arc segment of the S-shape respectively.

[0044] Appendix Figure 6 : Schematic diagram of the pressure plate (6). The pressure plate (6) is a disc-shaped plate with ignition holes. The function of the ignition holes is to allow the high-temperature gas of the propellant to ignite the fuse (44) through the ignition holes of the pressure plate (6) and the timing plate (5). The outer ring of the pressure plate (6) has several circular holes, which are used to couple with the timing plate (5) so that the timing plate (5) is fixed in position with the pressure plate (6) before firing. At the same time, the holes allow the explosive pressure of the propellant to act on the timing plate (5), causing the coupling protrusion of the timing plate (5) to deform and press into the groove of the delay plate (42), so that the timing plate (5) is decoupled from the pressure plate (6) and coupled together with the delay detonation plate (42), moving with the delay detonation plate (42). The number and position of the ignition holes on the pressure plate (6) are the same as those on the timing plate (5).

[0045] Appendix Figure 7 This is a structural diagram of the cartridge case (7).

[0046] Appendix Figure 8 This is a structural diagram of the timing plate (5). The timing plate (5) has ignition holes and protrusions. The ignition holes allow the high-temperature gas from the propellant to ignite the fuse (44), while the protrusions are for coupling with the pressure plate (6). The timing plate (5) is made of a relatively soft and ductile material so that the protrusions of the timing plate (5) deform under the high pressure of the propellant, coupling them to the delayed detonation plate (42). The material of the timing plate (5) is preferably a thin copper plate. The number of ignition holes is related to the shape of the groove on the delayed detonation plate (42) where the fuse (44) is placed. When an E-shaped groove is used, there is one ignition hole; when an S-shaped groove is used, there are two ignition holes. The timing plate (5) has at least two protrusions; increasing the number of protrusions can improve reliability.

[0047] The grenade launching process is as follows: The grenade is loaded into the grenade launcher, and the grenade launcher detonates the primer (72) of the cartridge case (7) to ignite the propellant (71). The high-temperature and high-pressure gas after the propellant (71) burns pushes the pressure plate (6), timing plate (5), delayed detonator (4), hammer sleeve (2), and wind cap (1) forward. At the same time, the fuse (44) is ignited through the ignition holes of the pressure plate (6) and timing plate (5). Under high pressure, the coupling protrusion of the timing plate (5) is deformed and pressed into the groove of the delayed detonator (42). The hammer sleeve (2) begins to rotate under the action of the rifling of the grenade launcher and flies out together with the pressure plate (6), timing plate (5), and delayed detonator (4). When the fuse (44) burns to the detonator (43), the detonator (43) explodes, pushing the firing pin (41) to break the brittle restraint ring (13). The rear part of the hammer block (12) is released from restraint and flies outward. At the same time, it breaks away from the front fixing ring (11) and the wind cap (1) and flies away, while driving the net (3) to open.

Claims

1. A type of unmanned aerial vehicle (UAV) net-catching grenade, characterized in that, include: The components include a wind cap (1), a hammer sleeve (2), a net (3), a delayed detonator (4), a timing plate (5), a pressure plate (6), and a cartridge case (7). The hammer sleeve (2) is composed of multiple (preferably four) separate hammer blocks (12) arranged circumferentially, forming a hollow cavity inside to accommodate the net (3). The front end of the hammer sleeve (2) is secured by a steel fixing ring (11), and the rear end is clamped by a brittle constraint ring (13) to maintain its assembled state. The delayed detonator (4) is located behind the hammer sleeve (2) and includes a delayed ignition unit and a detonation unit. The delayed ignition unit is used to trigger the detonation unit after a predetermined delay time after firing. When the detonation unit is triggered, it generates an impact to shatter the brittle constraint ring (13), thereby causing the hammer blocks (12) to scatter and unfold the net (3).

2. The UAV net-catching grenade according to claim 1, characterized in that, The delayed ignition unit includes: a pressure plate (6) fixed relative to the cartridge case (7), the pressure plate (6) having an ignition hole; a delayed detonation plate (42) rotating synchronously with the counterweight sleeve (2); a timing plate (5) between the pressure plate (6) and the delayed detonation plate (42); a meandering delayed fuse (44) on the delayed detonation plate (42), the ignition end of the delayed fuse (44) being opposite to the ignition hole, and its burning end being connected to the detonation unit; wherein, by rotating the counterweight sleeve (2) and the cartridge case (7) relative to each other, the relative position of the ignition end and the ignition hole can be changed to adjust the effective burning length of the delayed fuse (44), thereby setting the predetermined time.

3. The drone-borne net-catching grenade according to claim 2, characterized in that, The timing plate (5) is a circular thin plate made of copper with a thickness of no more than 0.3 mm. The timing plate (5) has ignition holes. When the fuse groove is e-shaped, there is one ignition hole. When the fuse groove is S-shaped, there are two ignition holes. The timing plate (5) has protrusions that are coupled with the circular holes around the pressure plate (6) to fix the position of the timing plate (5) and the pressure plate (6). When firing, the gunpowder pressure causes the protrusions of the timing plate (5) to deform in the opposite direction and embed into the edge groove of the delayed detonation plate (42) and couple with the delayed detonation plate (42). The timing plate (5) has at least two protrusions.

4. The drone net-catching grenade according to claim 2, characterized in that, The upper part of the delayed detonation plate (42) is a cross block, and the lower end is a circular plane. The fuse groove on the plane is composed of a straight line segment and an arc segment with the same radius. In order to improve the reliability of detonation and ignition, it is preferable to use two ignition holes and an S-shaped fuse groove. The S-shaped fuse groove is composed of a straight line segment and two arc segments with the same radius. The edge of the circular plane of the delayed detonation plate (42) has a groove. When firing, the timing plate (5) deforms and presses into the groove under the pressure of the propellant.

5. The UAV net-catching grenade according to claim 1, characterized in that, The brittle material of the brittle constraint ring (13) is preferably tempered glass.

6. The drone-borne net-catching grenade according to claim 1, characterized in that, The detonation unit includes: a cross-shaped block portion of a time-delay detonation plate (42) with two to four axially extending guide holes inside; a firing pin (41) disposed in the guide holes with clearance fit, forming a piston structure with the guide holes, the front end of the firing pin (41) facing the brittle constraint ring (13); and an initiating explosive (43) disposed at the rear of the firing pin (41), the high-pressure gas generated after the initiating explosive (43) is ignited by the time-delay fuse (44) drives the firing pin (41) to impact forward.

7. The drone net-catching grenade according to claim 6, characterized in that, The front end of the striker (41) is provided with crushing particles with a hardness higher than that of the brittle constraint ring (13), and the crushing particles are preferably artificial diamonds.

8. The drone net-catching grenade according to claim 1, characterized in that, The cavity of the hammer sleeve (2) is provided with a radially extending partition. The partition is formed on the inner wall of the hammer block (12) and is used to separate and fix the net (3) when the hammer sleeve (2) rotates. It rotates synchronously with the hammer block (12) to prevent the net (3) from getting tangled. The front end of the hammer block (12) has a bevel so that the front end of the hammer block (12) can be released from the fixing ring (11) after the brittle restraint ring (13) breaks. The four corner rope ends of the net (when four hammer blocks are used) are respectively fixed on each hammer block (12). There is a groove at the rear of the hammer block (12) to facilitate the installation of the fan-shaped sealing ring (14), which has the function of sealing to prevent the propellant from getting damp and failing.

9. The UAV net-catching grenade according to claim 1, characterized in that, The rear end of the hammer block (12) has a concave surface. The concave surface of the hammer block (12) after assembly forms a groove that couples with the cross block of the delayed detonation plate (42). When the hammer sleeve (2) is assembled, the brittle restraint ring (13) uses a non-Newtonian mechanical fluid flexible material buffer pad on the contact surface of the hammer block (12) and the delayed detonation plate (42) to prevent excessive local pressure from causing the brittle restraint ring (13) to break. The buffer pad is preferably made of a mixture of polyethylene glycol and silica.

10. The UAV net-catching grenade according to claim 1, characterized in that, The pressure plate (6) is provided with an ignition hole and a round hole around it; the position of the ignition hole is the same as that of the timing plate (5), and the number of round holes is the same as that of the protrusions of the timing plate (5).

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