Efficient-hit anti-unmanned aerial vehicle capturing bomb

Abstract

The invention relates to an efficient hit anti-unmanned aerial vehicle capturing bomb, relates to the technical field of anti-unmanned aerial vehicle capturing, and solves the technical problems of short capturing range, poor effect, poor ballistic accuracy and poor protection effect of a launching net, and the efficient hit anti-unmanned aerial vehicle capturing bomb comprises a bomb shell upper section and a bomb shell lower section fixedly mounted at the bottom end of the bomb shell upper section, a plurality of symmetrically-distributed bullet cores are clamped in the upper section of the bullet shell, the same connecting pull rope is connected between every two symmetrically-distributed bullet cores, the multiple connecting pull ropes are mutually bound in the middle position, the multiple connecting pull ropes form a net-shaped structure, the upper end face of each bullet core is provided with an inclined structure, and the lower end face of each bullet core is provided with an inclined structure. Through the combination of bullet core impact and pull rope winding, core components of the unmanned aerial vehicle can be directly damaged, forced landing can be achieved, the effective range is farther, the design of the side section and the upper end slope of the bullet core is matched, and operation convenience is higher.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of anti-UAV capture, and particularly relates to an anti-UAV capture projectile with high efficiency. BACKGROUND

[0002] The anti-UAV capture projectile is a non-destructive countermeasure weapon system specially designed to deal with low, slow and small UAVs (i.e. small, low-flying and slow consumer or small civilian UAVs). It is different from traditional damage equipment such as air defense missiles and high-altitude guns. The core logic is not to destroy the target by explosion or kinetic impact, but to achieve precise capture by physical means, such as releasing high-strength nylon nets, carbon fiber rope winding UAV propellers, or grabbing the fuselage by deployable mechanical claws, and then forcibly intercepting, controlling the flight attitude, and finally guiding it to land smoothly.

[0003] The existing UAV capture structure relies on the device to be carried by a launcher or relies on a portable launcher to be launched. The capture net launched is a combination of a columnar weight or a circular weight block and a multi-wire net. However, this structure combination often has the following two situations in actual test use. The first is that the shape of the weight is not conducive to the complete deployment of the capture net, affecting the capture coverage. The second is that the actual air resistance of the multi-wire net structure itself is large due to the large contact with the air, so the actual test capture range is still unsatisfactory.

[0004] In the actual application of the anti-UAV capture projectile, the assembly stability of the anti-UAV capture projectile and the launcher, the transmission efficiency of the trigger signal and the loading convenience directly affect the interception response speed and the combat reliability. At present, the assembly of the mainstream anti-UAV capture projectile and the launcher mainly depends on the general interface design, lacks precise matching positioning structures, and is prone to cause the projectile body to shake during launching due to assembly gaps, affecting the trajectory accuracy, and even causing the risk of jamming.

[0005] In the design of the power system of the current anti-UAV capture projectile, there is a real problem of unbalanced protection of gunpowder and core components. In actual application, the gunpowder box and the connecting pull rope core are arranged in close proximity without effective isolation structures or with poor isolation structure effect. When the gunpowder explodes, the high-temperature gas and impact debris are easy to directly damage the pull rope, causing it to break or melt, so that the subsequent capture and recovery functions are invalid. At the same time, the impact force without buffer will cause the pull rope to be unevenly stressed, and the trajectory is easy to deviate during actual launching, reducing the interception accuracy of the UAV.

[0006] On this basis, the present application provides an anti-UAV capture projectile with high efficiency to solve the above problems. SUMMARY

[0007] In view of the above, in order to overcome the defects of the prior art, the application provides a high-efficiency anti-UAV capturing bullet.

[0008] In order to achieve the above object, the application adopts the following technical scheme:

[0009] The high-efficiency anti-UAV capturing bullet comprises a bullet shell upper section and a bullet shell lower section fixedly installed at the bottom end of the bullet shell upper section.

[0010] Preferably, one end of the bullet shell lower section is fixedly installed with a shell limiting base, and the middle positions of the bullet shell lower section and the shell limiting base are both provided with impact communication grooves.

[0011] Preferably, the bullet shell upper section and the bullet shell lower section are slidably connected with an isolation buffer pad placed below the connecting pull rope, and a powder box is installed in advance between the bullet shell lower section and the isolation buffer pad.

[0012] Preferably, the bullet core is provided with a limiting hole penetrating the position close to the lower end face, and the bottom of the bullet core is provided with a receiving cavity in communication with the limiting hole, the upper end position of the receiving cavity is provided with a tapered groove, and the bottom end position of the receiving cavity is provided with a lower end round corner.

[0013] Preferably, each connecting pull rope is partially placed in the corresponding receiving cavity, and each limiting hole is provided with a fixed pin capable of positioning the connecting pull rope.

[0014] Preferably, the bullet shell upper section and the bullet shell lower section are both thirty-eight millimeters in caliber.

[0015] Preferably, the surface of the bullet shell upper section is one point five millimeters in thin wall, the bullet shell lower section is two millimeters in thin wall, and the height of the bullet core is forty millimeters.

[0016] Preferably, the number of the bullet core is 6-14.

[0017] Preferably, the inclined structure comprises an upper end inclined surface, an upper end flat surface and an upper end round corner all provided on the upper end face of the bullet core.

[0018] The application has the following technical effects.

[0019] 1. The present application can directly destroy the core components of the unmanned aerial vehicle and force the landing by the combination of "elastic core impact and pull rope winding", the effective range is farther, the traditional capture net causes short range due to large air resistance, the net structure is optimized to reduce resistance, the elastic core side section and the upper end slope are designed, the live ammunition test range is improved, the medium and long distance target can be covered, and the operation is more convenient;

[0020] 2. The present application realizes stable assembly by accurately matching the transmitter interface, efficiently transmits the trigger signal by the impact communication groove and the impact pin, and the impact pin is accurately positioned synchronously, so that the loading process is greatly simplified.

[0021] 3. The present application sets the isolation buffer pad to physically isolate the powder from the connecting pull rope to avoid damage, the impact force generated by the powder box explosion stably pushes the isolation buffer pad and the elastic core, and the subsequent function of the pull rope and the smooth launching of the elastic core are ensured. DETAILED DESCRIPTION

[0022] The accompanying drawings are used to provide a further understanding of the present application, and constitute a part of the specification, together with the embodiments of the present application, to explain the present application, and do not constitute a limitation on the present application. In the drawings:

[0023] Figure 1 It is a schematic diagram of the three-dimensional structure of the present application.

[0024] Figure 2 It is a schematic diagram of the assembly structure of the upper segment of the bullet shell, the lower segment of the bullet shell and the shell limiting base in the present application.

[0025] Figure 3 It is a schematic diagram of the connection between the pull rope and the elastic core in the present application.

[0026] Figure 4 It is a schematic diagram of the combination of the connection between the pull rope and the elastic core in the present application.

[0027] Figure 5 It is a schematic diagram of the structure of a single elastic core in the present application.

[0028] Figure 6 It is a schematic diagram of the side section of the elastic core in the present application.

[0029] Figure 7 It is a schematic diagram of the upper view structure of the elastic core in the present application.

[0030] Figure 8 It is a schematic diagram of the bottom view structure of the elastic core in the present application.

[0031] Reference signs:

[0032] 1, bullet shell upper section; 2, bullet shell lower section; 3, shell limiting base; 4, isolation buffer pad; 5, connecting pull rope; 6, bullet core; 601, upper end bevel; 602, upper end plane; 603, upper end round corner; 604, limiting hole; 605, storage cavity; 606, lower end round corner; 607, conical groove; 608, side profile; 609, side curved surface; 7, fixing pin; 8, impact communication groove. DETAILED DESCRIPTION

[0033] The foregoing and other technical contents, features and effects of the present application will be described in detail below with reference to the accompanying drawings. Figures 1 to 8 The detailed description of the embodiments will be clearly presented. The contents mentioned in the following embodiments are all referenced to the drawings of the specification.

[0034] The exemplary embodiments of the present application will be described below with reference to the accompanying drawings.

[0035] Embodiment one, the application is a kind of high-efficiency anti-unmanned aerial vehicle capture bullet, including bullet shell upper section 1 and fixedly installed in the bottom of bullet shell upper section 1 bullet shell lower section 2, shell upper and lower section all adopt seven brass and three zinc alloy brass alloy, through actual combat verification, brass provides excellent ductility and corrosion resistance, can cope with the expansion force of high temperature and high pressure gas when firing, and prolongs the shelf life of ammunition in harsh environment, zinc alloy reduces the material cost by 20%, improves the forming efficiency, meets the batch production demand, bullet shell upper section 1 is the " accurate positioner " of bullet core 6, bullet shell upper section 1 is clamped with multiple symmetrical distributed bullet cores 6 inside, from the specific structural design of bullet core 6, its cross section adopts trapezoidal structure, the shape is verified by fluid mechanics simulation, can reduce air resistance coefficient in flight process, while improving the dispersion uniformity of bullet core 6 group, avoid the aggregation of bullet core 6 caused by air flow disturbance, bullet core 6 adopts high manganese wear-resistant steel as core base material, this material has two key advantages, one is very high impact toughness and hardness, not easy to deform or break when high-speed impacting unmanned aerial vehicle, can effectively transmit kinetic energy to damage target structure;Second, excellent wear resistance can reduce the loss caused by bullet core 6 friction with bore and air in the process of launching, ensure its flight trajectory stability, further guarantee the interception accuracy and knockdown effect, between every two symmetrical distributed bullet cores 6, there is the same connecting pull rope 5, the length of each connecting pull rope 5 is two meters, multiple connecting pull ropes 5 are bound at the middle position, multiple connecting pull ropes 5 form a net structure, core component connecting pull rope 5 is made of multiple kevlar lines precisely twisted and woven, with the characteristics of high strength and high toughness of kevlar material, ensure that the pull rope has excellent anti-fracture ability and winding stability in the process of interception, the key executive component bullet core 6 and connecting pull rope 5 form a unique " only middle connection " net structure after the device is fired out and unfolded, this structure not only retains the coverage advantage of net interception, but also reduces air resistance through non-full closed design, lays a foundation for improving range in the interception application of unmanned aerial vehicle, the device can achieve effective knockdown through two core ways, one is to rely on multiple bullet cores 6 high-speed impacting unmanned aerial vehicle key components (such as propeller, fuselage frame), using impact force to damage its power system and structural integrity;Second, by the winding characteristics of connecting pull rope 5, the moving parts of unmanned aerial vehicle are entangled, so that it loses balance and is forced to land, compared with traditional unmanned aerial vehicle knockdown technology, the present application effectively makes up for the core defects of existing scheme, traditional canister diffusion knockdown can expand the strike range, but canister energy is dispersed, in most cases, only surface damage can be caused to unmanned aerial vehicle, it is difficult to damage the core structure, resulting in low knockdown success rate.And the traditional capture net entanglement type knock down, due to the capture net needs to overcome the larger air resistance when unfolding, limited by the influence of air flow, the actual effective range is shorter, it is difficult to deal with the medium and long distance unmanned aerial vehicle target, the present application through the combination design of "the core 6 impact plus the rope winding", both ensure the damage ability to the core components of unmanned aerial vehicle, ensure reliable knock down effect, and through the optimization of net structure to reduce air resistance, significantly improve the actual effective range, give consideration to the interception efficiency and combat range, the upper end surface of the core 6 is provided with inclined structure, the core 6 is ejected, high speed airflow generates directional component along the slope, a plurality of cores 6 are synchronously unfolded by wind resistance passive push, effectively avoid the problem of insufficient wind resistance and unfolding lag caused by too small angle, and the airflow turbulence and the core 6 attitude deviation phenomenon caused by too large angle, the failure rate of the core 6 cannot be completely unfolded is reduced to less than 0.3%, the optimization of the structure details of the core 6 further improves the unfolding reliability.

[0036] In this embodiment, when the interception system starts the launching program, the core 6 is separated from the launching device under the action of the propelling force, the whole interception process enters the key dynamic unfolding stage, at the moment of the core 6 ejection, a plurality of core 6 components do not fly along a single trajectory, but begin to show a dispersion trend under the action of complex external forces, at this time, the high-speed moving core 6 itself has strong inertial kinetic energy, while the wind resistance and air resistance in the external environment become the core acting force guiding the trajectory differentiation;

[0037] The resistance and other external forces will accurately act on the inclined structure at the top end of the core 6, the inclined structure is specially designed to efficiently convert the wind resistance and air resistance into horizontal component, the side of the inclined surface facing the airflow will receive greater air pressure, pushing the core 6 to deviate to the side with smaller pressure, so that the originally concentrated plurality of cores 6 quickly separate and diffuse in different directions, as the core 6 continues to fly, this dispersion trend continues to intensify, until all the cores 6 completely leave the initial aggregation state and unfold in a radial manner;

[0038] In the process of core 6 separation, the connecting rope 5 connected between each core 6 is also gradually pulled out, the initially contracted and stored rope quickly extends under the traction of the core 6, transitions from a relaxed state to a fully stretched state, and finally forms a wide coverage interception net structure, which synchronously advances to the airspace where the target unmanned aerial vehicle is located;

[0039] When any core 6 or the connecting rope 5 in tension state comes into contact with the target unmanned aerial vehicle, the interception mechanism is immediately started, the flight energy of the unmanned aerial vehicle interacts with the inertia of the core 6 and the rope, so that the connecting rope 5 quickly winds around the key parts such as the propeller, fuselage or wings of the unmanned aerial vehicle, this winding instantly limits the operation of the power system of the unmanned aerial vehicle, destroys its flight balance, and the tension of the rope further restricts the motion trajectory of the unmanned aerial vehicle, finally makes it lose the flight ability, and realizes accurate knock down.

[0040] In one embodiment, the lower section 2 of the bullet shell is fixedly installed at one end with a shell limiting base 3, and the diameter of the shell limiting base 3 is accurately set to 45 mm. This size has been verified for structural adaptability and can accurately match the connection interface specifications of the launcher. When the launcher is stably assembled, the limiting structure effectively limits the displacement of the launcher in the radial direction, ensuring that the launcher always maintains a preset assembly posture after being connected to the base, providing reliable structural support for the normal operation of the subsequent device. Impact communication grooves 8 are provided in the middle positions of the lower section 2 of the bullet shell and the shell limiting base 3. As a key connection structure of the device triggering system, the impact communication grooves 8 are specially used to accurately connect with the impact pin or trigger pin of the launcher. The internal groove size and the pin diameter are precisely adapted and designed, which not only ensures the smooth embedding and stable fixation of the impact pin or trigger pin, but also guides the pin to maintain a preset trajectory during the triggering action through the guide structure of the inner wall of the groove, ensuring efficient transmission of the impact or trigger signal and providing a reliable mechanical connection basis for the start or function switching of the subsequent device.

[0041] In this embodiment, when the entire capture bullet needs to be loaded, the operator can first hold the capture bullet and smoothly push it into the barrel along the axial direction of the launcher barrel, ensuring that the capture bullet is smoothly attached to the inner wall of the barrel. Then, with the help of the pre-set arc-shaped groove on the outside of the launcher barrel, the size of the groove is accurately matched with the shell limiting base 3 on the shell of the capture bullet. By inserting the shell limiting base 3 into the groove, the capture bullet can be axially positioned to prevent it from moving forward and backward in the barrel, and the shell limiting base 3 can be radially fixed to prevent the capture bullet from rotating and shifting. This achieves stable limiting installation. At the same time, the striker inside the launcher adjusts its position synchronously with the loading action of the capture bullet, and finally accurately locates inside the impact communication groove 8 of the capture bullet. The top end of the striker and the trigger contact surface of the impact communication groove 8 maintain a preset distance, which prepares the structure for the subsequent firing and triggering of the capture bullet.

[0042] In Example 3, as an example, an isolation buffer pad 4 is slidably connected between the upper section 1 and the lower section 2 of the bullet casing, and is placed below the connecting rope 5. The isolation buffer pad 4 adopts a circular structure design and is made of a special composite material with excellent high-temperature resistance, possessing excellent heat resistance stability and structural strength. In the internal assembly system of the capturing projectile, the buffer pad is precisely positioned between the gunpowder storage cavity and the installation channel of the connecting rope 5. It can not only completely separate the gunpowder and the connecting rope 5 into two independent spaces through physical isolation, preventing direct contact between the two, but also resist the erosion of the high-temperature shock wave at the moment of gunpowder explosion due to its own high-temperature resistance characteristics. At the same time, it absorbs part of the explosion impact force through the elastic buffering effect of the material, effectively weakening the transmission of explosion energy to the connecting rope 5, avoiding damage such as breakage or deformation of the connecting rope 5 due to high-temperature burning or violent impact, and ensuring its normal traction function in subsequent capturing actions. A gunpowder box is pre-installed between the lower section 2 of the bullet casing and the isolation buffer pad 4. The gunpowder box is a conventional gunpowder box, which is the main driving force.

[0043] In this embodiment, when the projectile core 6 and connecting rope 5 need to be launched in a combat or mission scenario, the operator can activate the gunpowder box through the triggering mechanism of the launcher. After the gunpowder box is triggered, it explodes rapidly. Since the explosion space is concentrated in the narrow area inside the lower section 2 of the bullet casing, the limited space prevents the energy generated by the explosion from spreading quickly, thus forming a powerful instantaneous impact force. This impact force acts on the isolation buffer pad 4, pushing it to move towards the upper section 1 of the bullet casing, while simultaneously driving multiple projectile cores 6 to move synchronously. Finally, the isolation buffer pad 4 and all projectile cores 6 are quickly pushed out from the internal space formed by the lower section 2 and the upper section 1 of the bullet casing. During the entire pushing process, the isolation buffer pad 4 remains between the gunpowder explosion area and the connecting rope 5. With its own high temperature resistance and impact resistance, it prevents the high temperature airflow and debris generated by the explosion from directly contacting the connecting rope 5. On the other hand, it absorbs some of the impact energy through its own deformation, preventing the connecting rope 5 from breaking or being damaged due to high temperature burning or impact overload, ensuring that the projectile core 6 can stably complete the subsequent capture action under the traction of the connecting rope 5.

[0044] In the embodiment, when the connecting pull rope 5 and the elastic core 6 need to be assembled, the operation needs to be carried out according to the standard steps. First, the end of the connecting pull rope 5 is held by hand and is aligned with the opening of the receiving cavity 605 on the elastic core 6, and then the end is smoothly inserted into the cylindrical receiving cavity 605, so that the pull rope is not jammed or wound in the cavity. A plurality of connecting pull ropes 5 that have been connected with the elastic core 6 are centrally knotted at the middle positions, so that the plurality of pull ropes are connected with each other to form a whole, and thus the combination and assembly of the connecting pull rope 5 and the elastic core 6 are completed.

[0045] In the embodiment, when the connecting pull rope 5 and the elastic core 6 need to be assembled, the operation needs to be carried out according to the standard steps. First, the end of the connecting pull rope 5 is held by hand and is aligned with the opening of the receiving cavity 605 on the elastic core 6, and then the end is smoothly inserted into the cylindrical receiving cavity 605, so that the pull rope is not jammed or wound in the cavity. A plurality of connecting pull ropes 5 that have been connected with the elastic core 6 are centrally knotted at the middle positions, so that the plurality of pull ropes are connected with each other to form a whole, and thus the combination and assembly of the connecting pull rope 5 and the elastic core 6 are completed.

[0046] In the embodiment, when the connecting pull rope 5 is fixed, the fixing pin 7 is first taken out, aligned with the limiting hole 604 of the bullet core 6, and slowly inserted into the hole. The position needs to be accurately controlled during the process to ensure that the fixing pin 7 can firmly position part of the connecting pull rope 5 in the reserved space between the receiving cavity 605 and the conical groove 607, avoiding displacement of the pull rope. After the fixing pin 7 is installed in place, the end of the connecting pull rope 5 extending out of the receiving cavity 605 is pulled outwards, and a knot is formed at the end after adjustment to the appropriate length, preventing the pull rope from coming off.

[0047] In the embodiment, when the connecting pull rope 5 is fixed, the fixing pin 7 is first taken out, aligned with the limiting hole 604 of the bullet core 6, and slowly inserted into the hole. The position needs to be accurately controlled during the process to ensure that the fixing pin 7 can firmly position part of the connecting pull rope 5 in the reserved space between the receiving cavity 605 and the conical groove 607, avoiding displacement of the pull rope. After the fixing pin 7 is installed in place, the end of the connecting pull rope 5 extending out of the receiving cavity 605 is pulled outwards, and a knot is formed at the end after adjustment to the appropriate length, preventing the pull rope from coming off.

[0048] In the embodiment, the upper section 1 and the lower section 2 of the bullet shell are both thirty-eight millimeters in caliber, which is the standard caliber and can be directly used with existing launchers.

[0049] In the embodiment, the capture bullet can be directly connected with the adaptive launcher during actual use.

[0050] In the embodiment, the surface of the upper section 1 of the bullet shell is a thin wall of one point five millimeters, and the lower section 2 of the bullet shell is a thin wall of two millimeters. The lower section 2 of the bullet shell needs to withstand three to four times the impact force and recoil force of the upper section 1 of the bullet shell (the gas pressure during firing reaches three hundred to five hundred megapascals), so the thin wall size is thicker than the upper section by zero point three to zero point five millimeters, which increases the anti-deformation ability by more than fifty percent, avoids the risk of blown chamber, and does not require modification of the core equipment, but only needs to adjust the mold, which does not increase the processing difficulty, while ensuring the overall safety of the structure and reducing the weight of the bullet to some extent, assisting in improving the individual load capacity and significantly improving the team combat effectiveness.

[0051] In the embodiment, when the bullet core 6 is launched, the lower section 2 of the bullet shell is subjected to impact force and recoil force, and the upper section 1 of the bullet shell is subjected to part of the impact force, which cooperates to ensure that the bullet core 6 can be accurately launched with small error.

[0052] In the performance test of the anti-drone interceptor projectile core 6 system, the technical team focuses on the two core indicators of range coverage and drone knockdown efficiency. Through multiple variable control experiments (covering different numbers of projectile cores 6, arrangement methods, and flight environment simulation), key conclusions are drawn to ensure the effective range of the interceptor projectile (ensuring long-distance coverage of low-altitude targets), airspace coverage density (reducing target evasion gaps), and the final knockdown effect (achieving drone structure damage through kinetic impact).

[0053] In this embodiment, the height of the projectile core 6 is uniformly set to 40 mm. This size is calculated based on the damage threshold of key components of a drone (such as the propeller and the fuselage frame). It can ensure the kinetic energy reserve of a single projectile core 6 and achieve reasonable arrangement within the limited projectile body space.

[0054] In this embodiment, the number of projectile cores 6 in each group is 6-14, with the optimal configuration number controlled within the three core intervals of six, eight, or ten. It is particularly noted that the technical parameters and structural analysis of this embodiment are only for the specific composition structure of "a group of six projectile cores 6". If the number of projectile cores 6 is adjusted, adaptive testing needs to be carried out to verify the performance stability.

[0055] In the embodiment, the upper end of each core 6 is provided with an upper end inclined surface 601, an upper end plane 602 and an upper end round corner 603. The angle between the upper end inclined surface 601 and the horizontal direction is forty-five to fifty degrees. The length of the upper end plane 602 is one point five millimeters. The upper end round corner 603 is one millimeter. The angle between the upper end inclined surface 601 and the horizontal direction is one of the core technical parameters. After repeated dynamic simulation and live ammunition test verification, when the angle is stable in the range of forty-five to fifty degrees, the optimal aerodynamic effect can be formed. The length of the upper end plane 602 and the radius of the upper end round corner 603 are adjusted by the orthogonal test method. Finally, it is determined that the plane length of one point five millimeters and the round corner radius of one millimeter are the optimal combination, which fully meets the technical requirements of the core 6 coverage range and striking accuracy in the actual combat scene. Each core 6 is provided with two symmetrically distributed side arc surfaces 609. Each core 6 is provided with a side section 608. In the adaptive design of the core 6 and the shell, the size precision of the side section 608 is the key. The width is accurately set to 6.5 millimeters, which can be fully matched with the inner wall size of the upper segment 1 and the lower segment 2 of the bullet shell, realizes the close fit between structures, avoids the radial movement of the core 6 in the standby state, and improves the fit of the core 6 and the inner wall of the shell through the arc design of the side arc surface 609. Through the curved surface contact, the stress is dispersed, the whole bullet remains stable in the standby state, effectively avoids the vibration deviation problem caused by the gap between structures, at the same time, the design of the side section 608 has the advantages of lightweight and drag reduction. The plane structure replaces the traditional solid design, reduces the quality of the core 6 itself under the premise of ensuring the structural strength, reduces the launch load, and fully meets the performance requirements of the medium and long range striking scene.

[0056] In the embodiment, the core 6 forms a short airflow buffer area when it is ejected, avoiding the local pressure mutation caused by the direct impact of airflow on the inclined surface. The one-millimeter upper end round corner 603 processing can reduce the airflow separation phenomenon and reduce the surface turbulence intensity of the core 6. Under the synergistic action of the two, the stability of the core 6 during the unfolding process is improved by twenty-seven percent, and the unfolding angle error is controlled within ±1.2°. Under the design condition of the side section 608 plane contact, the contact area between the core 6 and the inner wall of the shell can be greatly reduced, so that the sliding friction of the core 6 when it is ejected is reduced by more than eighteen percent. The reduction of friction directly reduces the energy loss. After the live ammunition test verification, the actual effective range of the core 6 is improved by nine to twenty-two percent compared with the optimized one.

[0057] Working principle:

[0058] S1, first complete the pre-assembly of the core 6 and the connecting pull rope 5, hand the end of the connecting pull rope 5, align the storage cavity 605 opening at the bottom of the core 6, pull the rope end into the storage cavity 605 inside, then take the fixed pin 7, align the limiting hole 604 through the side of the core 6, slowly into the space between the storage cavity 605 and the tapered groove 607, prevent the pull rope from shifting, pull the end of the connecting pull rope 5 out of the storage cavity 605 to the appropriate length, knot at the end to avoid loosening, finally knot the connecting pull rope 5 of multiple groups of connected cores 6 at the middle position to form a whole connected to each other, complete the assembly of the core 6 and the pull rope;

[0059] S2, the operator holds the capture bullet with the completed core 6-pull rope assembly, smoothly pushes it into the gun barrel along the axis, so that the shell limiting base 3 at one end of the lower section 2 of the bullet shell is clamped into the pre-set arc-shaped groove outside the gun barrel, realizing the axial and radial limiting of the capture bullet, at the same time, the internal striker of the launcher is accurately placed in the impact communication groove 8 between the lower section 2 of the bullet shell and the shell limiting base 3, and the striker top end and the groove trigger contact surface maintain a pre-set distance, completing the structure preparation before firing;

[0060] S3, the firecracker box between the lower section 2 of the bullet shell and the isolation buffer pad 4 is started by the trigger mechanism of the launcher, the instantaneous impact force generated by the explosion of the firecracker box acts on the isolation buffer pad 4 (the buffer pad is made of high-temperature-resistant special composite material, located between the firecracker storage cavity and the connecting pull rope 5 installation channel), pushing the isolation buffer pad 4 to move towards the upper section 1 of the bullet shell, and then driving the multiple cores 6 inside the clamped upper section 1 of the bullet shell to move synchronously, pushing both out of the shell interior space;

[0061] S4, the core 6 (height 40mm, trapezoidal cross section, made of high-manganese wear-resistant steel, containing 45-50° upper end slope 601, 1.5mm upper end plane 602, 1mm upper end round corner 603, one side has two symmetrical side arc surfaces 609 and 6.5mm wide side section 608) is discharged instantly, the high-speed airflow acts on the upper end slope 601 to convert into a horizontal component force, pushing the multiple cores 6 to separate and diffuse in different directions, at the same time, the connecting pull rope 5 (single length 2m, made of multiple strands of Kevlar) inside the core 6 is gradually pulled out, from the relaxed state to the fully tensioned state, and finally forms a "only middle connection" network structure.

[0062] S5, the core 6 and the connecting pull rope 5 of the network structure push towards the target UAV airspace, when the core 6 high-speed hits the key components such as the UAV propeller and the fuselage frame, it destroys the target structure by the impact toughness and hardness of high-manganese wear-resistant steel, if the connecting pull rope 5 contacts the UAV, it will entangle its moving parts by winding characteristics, limit the operation of the power system, and destroy the flight balance, finally realize the forced landing of the UAV, complete the interception.

[0063] The present application has the following technical effects.

[0064] 1. The present application can directly damage the core components of the unmanned aerial vehicle and force it to land by "elastic core 6 impact plus pull rope winding" combination, and the effective range is further. The traditional capture net has short range due to large air resistance, and the present application optimizes the drag reduction of the net structure, and cooperates with the side section 608 and the upper end inclined surface 601 design of the elastic core 6, so that the shooting range is improved in live ammunition test, and the medium and long distance target can be covered, and the operation is more convenient;

[0065] 2. The present application realizes stable assembly by precise matching of the transmitter interface, efficiently transmits the trigger signal through the impact communication groove 8 and the butt joint of the striker, and the shell limiting base 3 is clamped into the gun barrel groove limiting when loading, the striker is synchronized and accurately positioned, and the loading process is greatly simplified.

[0066] 3. The present application sets the isolation buffer pad 4, which physically isolates the gunpowder and the connecting pull rope to avoid damage, and the impact force generated by the explosion of the gunpowder box stably pushes the isolation buffer pad 4 and the elastic core 6, ensuring the subsequent function of the pull rope and the smooth launching of the elastic core 6.

[0067] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. An anti-drone capturing bullet with high efficiency, comprising a bullet shell upper segment (1) and a bullet shell lower segment (2) fixedly installed at the bottom end of the bullet shell upper segment (1), characterized in that, The bullet shell upper section (1) is internally clamped with a plurality of symmetrically distributed bullet cores (6), every two symmetrically distributed bullet cores (6) are connected with the same connecting pull rope (5), a plurality of the connecting pull ropes (5) are bound at the middle position, and the plurality of connecting pull ropes (5) form a net structure.

2. The high efficiency anti-drone capturing projectile of claim 1, wherein, The bullet shell lower section (2) is fixedly installed with a shell limiting base (3) at one end, and the middle positions of the bullet shell lower section (2) and the shell limiting base (3) are provided with impact communication grooves (8).

3. The high efficiency anti-drone capturing projectile of claim 1, wherein, The bullet shell upper section (1) and the bullet shell lower section (2) are slidably connected with the isolation buffer pad (4) below the connecting pull rope (5), and the bullet shell lower section (2) and the isolation buffer pad (4) are provided with a powder box in advance.

4. The high efficiency anti-drone capturing projectile of claim 1, wherein, The bullet core (6) is provided with a penetrating limiting hole (604) near the lower end face, the bottom of the bullet core (6) is provided with a receiving cavity (605) in communication with the limiting hole (604), the upper end position of the receiving cavity (605) is provided with a tapered groove (607), and the bottom end position of the receiving cavity (605) is provided with a lower end round corner (606).

5. The high efficiency anti-drone capturing projectile of claim 4, wherein, Each of the connecting pull ropes (5) is partially placed in the corresponding receiving cavity (605), and each of the limiting holes (604) is provided with a fixed pin (7) capable of positioning the connecting pull rope (5).

6. The high efficiency anti-drone capturing projectile of claim 1, wherein, The bullet shell upper section (1) and the bullet shell lower section (2) are both thirty-eight millimeters in caliber.

7. The high efficiency anti-drone capturing projectile of claim 1, wherein, The surface of the bullet shell upper section (1) is one point five millimeters thick, the bullet shell lower section (2) is two millimeters thick, and the height of the bullet core (6) is forty millimeters.

8. The high efficiency anti-drone capturing projectile of claim 1, wherein, The number of the bullet core (6) is 6-14.

9. The high efficiency anti-drone capturing projectile of claim 1, wherein, The inclined structure includes the upper end inclined surface (601), the upper end flat surface (602) and the upper end round corner (603) provided on the upper end face of the bullet core (6).

10. The high efficiency anti-drone capturing projectile of claim 9, wherein, The angle between the upper end inclined surface (601) and the horizontal direction is forty-five to fifty degrees, the length of the upper end flat surface (602) is one point five millimeters, the upper end round corner (603) is one millimeter, each of the bullet cores (6) is provided with two symmetrically distributed side curved surfaces (609) on one side, and each of the bullet cores (6) is provided with a side section (608) on one side.

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