Anti-drone micro winding bullet

Abstract

The present application belongs to anti-UAV intercept equipment technical field, especially relates to a kind of anti-UAV micro winding bullet, comprising: shell;Rear cover, is fixed with shell by locking module;Counterweight inertia block, elastically sliding fit in shell and away from rear cover one end, air cavity is arranged between counterweight inertia block and shell, air cavity is communicated with air release hole;Counterweight inertia block is drivingly connected with unlocking module by transmission slide bar;Unlocking module drives locking module to make rear cover separate from shell;Unmanned aerial vehicle winding module is set in shell and is connected with rear cover.Shell shoots out, and counterweight inertia block is stationary due to inertia, makes transmission slide bar displacement relative to shell, so that unlocking module is unlocked, then counterweight inertia block expels air in air cavity by air release hole under the action of elastic force, drives diameter change pin rod to move forward and release rear cover pin, and rear cover separates from shell and drives unmanned aerial vehicle winding module to move out of shell and unfold.The present application uses launch inertia to complete charging, and uses air damping to realize delay unlocking.

Description

Technical Field

[0001] This invention belongs to the technical field of anti-drone interception equipment, and in particular relates to a miniature anti-drone entanglement bullet. Background Technology

[0002] With the widespread adoption of micro-drones in both civilian and military fields, the security threats they pose, such as unauthorized flights, illegal spying, and terrorist attacks, are becoming increasingly prominent. Due to the small size, maneuverability, and low flight altitude of micro-drones, traditional air defense weapons suffer from extremely low cost-effectiveness and significant collateral damage. While conventional electromagnetic interference equipment can cut off drone control signals, it has drawbacks such as easily causing drones to lose control and crash, resulting in secondary damage, and being ineffective against drones with autonomous cruise or satellite navigation capabilities. Therefore, physical interception, as a precise means of hazard control and forced landing / capture, is gradually becoming an important development direction in the field of counter-drone warfare. Among these methods, launching wire-entangled projectiles is currently one of the more efficient physical interception techniques. By launching projectiles carrying flexible wire nets at the drone, the wires become entangled in the drone's propellers, using aerodynamic damping and mechanical jamming to disrupt the rotor's aerodynamic shape and rotational balance, forcing the drone to lose lift and fall safely.

[0003] Based on a review and analysis of existing anti-drone wire-entangled projectile technologies, the following technical shortcomings are currently identified in commercially available wire-entangled projectiles: Integral projectile-type or pyrotechnic-explosive-deployable wire-entangled projectiles use propellant or miniature pyrotechnics to instantly detonate and launch the entire wire net. However, the deployment is uncontrollable at the moment of detonation, the randomness of the wire net's attitude in the air leads to a low probability of entanglement, and the pyrotechnic explosion can easily cause physical damage to the drone itself.

[0004] Parachute-dropped or parachute-tethered tethered projectiles rely on air resistance to deploy their canopies, which are greatly affected by wind speed and direction. In calm or light wind conditions, their deployment rate is low, and the flexible parachute rope system is more likely to rub against the drone's fuselage rather than wrap around the propeller, resulting in unstable actual interception effectiveness.

[0005] Spring- or mechanically stored micro-wound bullets employ a firing spring release mechanism. The spring is released after a delay using a delay charge or mechanical clock mechanism to push the cable out. However, micro-delay charges are prone to misfires or severe delay time drift after experiencing high overload during bullet firing. The miniaturized mechanical clock mechanism has an extremely complex structure, high manufacturing costs, and a sharply increased failure rate. At the same time, the spring occupies a large amount of valuable space inside the bullet. Existing micro-mechanical locking pins are prone to premature unlocking or jamming under the violent vibration and chamber pressure impact during firing, which can lead to fatal malfunctions.

[0006] Therefore, there is an urgent need for a miniature anti-drone entanglement bullet to solve this problem. Summary of the Invention

[0007] The purpose of this invention is to provide a miniature anti-drone entanglement projectile to solve the above-mentioned problems.

[0008] To achieve the above objectives, the present invention provides the following solution: A type of anti-drone miniature entangled bullet, comprising: shell; The back cover is fixed to the outer shell by a locking module, and the outer shell and the back cover are elastically slidably engaged. The locking module is driven by an unlocking module, which is connected to the back cover. The unlocking module drives the locking module to unlock the back cover from the outer shell, and the back cover (6) separates from the outer shell under the action of elastic force. A counterweight inertia block is elastically slidably fitted inside the outer shell, and the counterweight inertia block is located at one end away from the rear cover. An air cavity is provided between the counterweight inertia block and the outer shell, and the air cavity is connected to a vent hole. The counterweight inertia block is connected to the unlocking module via a transmission slide rod. After the outer shell is ejected, the counterweight inertia block, due to inertia, stops, causing the transmission slide rod to shift relative to the outer shell and push the movable end of the unlocking module. Subsequently, under the action of elasticity, the counterweight inertia block discharges the air in the air cavity through the vent hole. After the movable end of the unlocking module is reset, the unlocking is completed, and the outer shell separates from the back cover. A drone winding module is disposed inside the housing. After the rear cover is separated from the housing, the drone winding module is removed from the housing and unfolded.

[0009] Optionally, the unlocking module includes a fixed guide rail, which is coaxially fixed with the back cover. An upper end face ratchet is slidably fitted inside the fixed guide rail. One end of the upper end face ratchet contacts the end of the transmission slide rod that is away from the counterweight inertia block. The upper end ratchet engages with the lower end ratchet, and the bottom end of the lower end ratchet is coaxially rotatably fitted with a variable diameter unlocking slide bar, which is elastically slidably fitted with the rear cover. The fixed guide rail is provided with a long guide rail and a short guide rail. The bottom ends of the long guide rail and the short guide rail are both engaged with the lower end face ratchet. The upper end face ratchet is vertically slidably engaged with the long guide rail. After the upper end face ratchet pushes the teeth of the lower end face ratchet to slide out of the short guide rail, the lower end face ratchet is deflected by the engagement between the short guide rail and the lower end face ratchet, so that the teeth of the lower end face ratchet enter the long guide rail and slide. The variable diameter unlocking slide has a stepped structure. The small diameter end of the variable diameter unlocking slide is vertically slidably engaged with the back cover, and the large diameter end of the variable diameter unlocking slide is limited by the locking module. After the large diameter end of the variable diameter unlocking slide is displaced, it separates from the locking module, so that one end of the locking module contacts the small diameter end of the variable diameter unlocking slide. At this time, the outer shell and the back cover are unlocked.

[0010] Optionally, the locking module includes a rear cover locking pin, which slides horizontally and is elastically connected to the rear cover. One end of the rear cover locking pin is engaged with the outer shell for limiting, and the other end of the rear cover locking pin abuts against the large-diameter end of the variable-diameter unlocking slide. After the variable-diameter unlocking slide is displaced, the other end of the rear cover locking pin abuts against the small-diameter end of the variable-diameter unlocking slide, and at the same time, one end of the rear cover locking pin separates from the outer shell, thus unlocking the rear cover from the outer shell.

[0011] Optionally, a third spring is provided between the rear cover locking pin and the rear cover. The third spring is sleeved on the outside of the rear cover locking pin, and the third spring causes the rear cover locking pin to move towards the variable diameter unlocking slide bar. The rear cover is coaxially arranged with the outer shell, and the rear cover and the outer shell are axially slidingly engaged. A fourth spring is provided between the rear cover and the outer shell.

[0012] Optionally, a second spring is provided between the variable diameter unlocking slide and the rear cover. The second spring is sleeved on the outside of the variable diameter unlocking slide, and the second spring causes the variable diameter unlocking slide to move toward the rear cover and then reset.

[0013] Optionally, a first spring is provided between the counterweight inertia block and the outer shell. The first spring is coaxially arranged with the counterweight inertia block, and the first spring causes the counterweight inertia block to move away from the rear cover.

[0014] Optionally, the drone winding module includes a sliding sleeve, which is coaxially sleeved on the outside of the transmission slide rod and slides in cooperation with the inner wall of the housing; Multiple elastic skirt frame skeletons, one end of which is fixed to the sliding sleeve, and the multiple elastic skirt frame skeletons are arranged circumferentially along the sliding sleeve; The umbrella canopy is fixed to multiple elastic skirt frame frames; Multiple winding lines correspond one-to-one with the elastic skirt frame. One end of each winding line is fixed to the corresponding elastic skirt frame, and the other end of each winding line is connected to a spool located inside the outer casing. The winding thread is housed inside the outer casing; The umbrella canopy unfolds after the multiple elastic skirt frames are removed from the outer shell.

[0015] Optionally, the mass of the spool is greater than 1.5 to 3 times the mass of a single strand of the winding thread.

[0016] Optionally, the elastic skirt frame has 8 supports.

[0017] Optionally, multiple elastic skirt skeletons are arranged at equal intervals along the circumference of the sliding sleeve.

[0018] Compared with the prior art, the present invention has the following advantages and technical effects: This invention achieves a fully physical triggering logic for launch inertia loading and air damping delay through the coordinated action of a counterweight inertia block, a transmission slide rod, an unlocking module, and a locking module, eliminating the need for pyrotechnics, electronic components, or complex clockwork mechanisms. The air cavity and vent between the counterweight inertia block and the outer shell create adjustable delay damping, allowing the unlocking time to adapt to flight speed and facilitating control of the interception distance. The unlocking module employs a ratchet-type meshing structure with a fixed guide rail and ratchet wheels on both the upper and lower ends, isolating state switching from physical unlocking in time. High launch overload only changes the internal state without triggering unlocking, eliminating the risk of premature release within the chamber. The stepped structure of the variable-diameter unlocking slide rod, in conjunction with the rear cover locking pin and a third spring, achieves instantaneous zero-energy ejection and unlocking after the large-diameter end yields, resulting in a crisp and reliable action. In the drone entangling module, the sliding sleeve, elastic skirt frame, and canopy form an integrated projectile structure. After exiting the shell, it automatically opens and utilizes wind resistance differences to draw the winding line. Multiple elastic skirt frames are evenly spaced circumferentially, forcibly constraining the beginnings of the winding line to different directions, preventing multiple lines from intertwining and forming a multi-directional three-dimensional line curtain. The overall structure is miniaturized, adaptable to rapid-fire firearms for dense array interception, low-cost, and suitable for mass production. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 This is a schematic diagram of the structure of the UAV winding module of the present invention; Figure 3 This is a schematic diagram of the structure of the present invention, in which the linear shaft surrounds the transmission slide rod and is located on the rear cover; The components include: 1. Counterweight inertia block; 2. Transmission slide rod; 3. Variable diameter unlocking slide rod; 4. First spring; 5. Vent hole; 6. Back cover; 7. Elastic skirt frame; 8. Winding line; 9. Umbrella canopy; 10. Sliding sleeve; 11. Back cover locking pin; 12. Second spring; 13. Third spring; 14. Upper end ratchet; 15. Lower end ratchet; 16. Fixed guide rail. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0022] Reference Figures 1 to 3 This invention discloses a micro entangled bullet for anti-drone use, comprising: shell; The rear cover 6 is fixed to the outer shell by a locking module, and the outer shell and the rear cover 6 are elastically slidably engaged. The locking module is driven by an unlocking module, which is connected to the rear cover 6. The unlocking module drives the locking module to unlock the rear cover 6 from the outer shell, and the rear cover 6 separates from the outer shell under the action of elastic force. The counterweight inertia block 1 is elastically slidably fitted inside the outer shell, and the counterweight inertia block 1 is located at the end away from the rear cover 6. An air cavity is provided between the counterweight inertia block 1 and the outer shell, and the air cavity is connected to the vent hole 5. The counterweight inertia block 1 is connected to the unlocking module via the transmission slide rod 2. After the outer shell is ejected, the counterweight inertia block 1 stops due to inertia, causing the transmission slide rod 2 to shift relative to the outer shell and push the movable end of the unlocking module. Then, under the action of elasticity, the counterweight inertia block 1 discharges the air in the air cavity through the vent hole 5. After the movable end of the unlocking module is reset, the unlocking is completed, and the outer shell is separated from the back cover 6. The drone winding module is located inside the outer shell. After the rear cover 6 is separated from the outer shell, the drone winding module is removed from the outer shell and unfolds.

[0023] In use, after the anti-drone miniature entanglement munition is launched, the counterweight inertia block 1 remains stationary due to inertia, causing the transmission slide rod 2 to shift relative to the outer shell and push the movable end of the unlocking module. At this time, the locking module still keeps the rear cover 6 fixed to the outer shell. Subsequently, the counterweight inertia block 1 resets under the action of elastic force, expelling the air in the air cavity through the vent 5. After the movable end of the unlocking module resets, the unlocking action is completed, causing the locking module to release the lock on the rear cover 6. The rear cover 6 separates from the outer shell under the action of elastic force, and the drone entanglement module moves out of the outer shell and unfolds in the air to form an interception line curtain. This process utilizes the launch inertia to complete the loading and uses air damping to achieve delayed unlocking, without the need for pyrotechnics or electronic components, achieving miniaturized and reliable interception through all-physical triggering.

[0024] As an optional implementation, the unlocking module includes a fixed guide rail 16, which is coaxially fixed with the back cover 6. An upper end ratchet 14 is slidably fitted inside the fixed guide rail 16. One end of the upper end ratchet 14 contacts the end of the transmission slide bar 2 that is away from the counterweight inertial block 1. The upper end ratchet 14 engages with the lower end ratchet 15. The bottom end of the lower end ratchet 15 is coaxially rotated with a variable diameter unlocking slide bar 3. The variable diameter unlocking slide bar 3 is elastically slidably engaged with the rear cover 6. The fixed guide rail 16 is provided with a long guide rail and a short guide rail. The bottom ends of the long guide rail and the short guide rail are both engaged with the lower end face ratchet 15. The upper end face ratchet 14 is vertically slidably engaged with the long guide rail. After the upper end face ratchet 14 pushes the teeth of the lower end face ratchet 15 to slide out of the short guide rail, the lower end face ratchet 15 is deflected under the engagement of the short guide rail and the lower end face ratchet 15, so that the teeth of the lower end face ratchet 15 enter the long guide rail and slide. The variable diameter unlocking slide bar 3 has a stepped structure. The small diameter end of the variable diameter unlocking slide bar 3 is vertically slidably engaged with the back cover 6, and the large diameter end of the variable diameter unlocking slide bar 3 is limited to the locking module. After the large diameter end of the variable diameter unlocking slide bar 3 is displaced, it separates from the locking module, so that one end of the locking module contacts the small diameter end of the variable diameter unlocking slide bar 3. At this time, the outer shell and the back cover 6 are unlocked.

[0025] The transmission slide rod 2 pushes the upper end ratchet 14 to slide within the long guide rail of the fixed guide rail 16. After the upper end ratchet 14 pushes the teeth of the lower end ratchet 15 to slide out of the short guide rail, the lower end ratchet 15 deflects due to the meshing action between the short guide rail and the lower end ratchet 15. The teeth of the lower end ratchet 15 enter the long guide rail and continue to slide along the long guide rail under the elastic sliding action of the variable diameter unlocking slide rod 3 relative to the rear cover 6. The variable diameter unlocking slide rod 3 has a stepped structure. Its large diameter end initially engages with the locking module for limiting. After the large diameter end is displaced, it separates from the locking module, causing the locking module to switch from contacting the large diameter end to contacting the small diameter end, thus completing the unlocking.

[0026] The structure and mating relationship of the fixed guide rail 16, the upper end ratchet 14 and the lower end ratchet 15 can be referenced from the pressing structure of a press-type ballpoint pen.

[0027] As an optional implementation, the locking module includes a rear cover locking pin 11, which slides horizontally and is elastically connected to the rear cover 6. One end of the rear cover locking pin 11 is limited and engaged with the outer shell, and the other end of the rear cover locking pin 11 abuts against the large diameter end of the variable diameter unlocking slide bar 3. After the variable diameter unlocking slide bar 3 is displaced, the other end of the rear cover locking pin 11 abuts against the small diameter end of the variable diameter unlocking slide bar 3, and at the same time, one end of the rear cover locking pin 11 separates from the outer shell, and the rear cover 6 is unlocked from the outer shell.

[0028] In the initial state, one end of the rear cover locking pin 11 is engaged with the outer shell for limiting, and the other end abuts against the large-diameter end of the variable-diameter unlocking slide bar 3. When the variable-diameter unlocking slide bar 3 moves, the large-diameter end moves aside, and the other end of the rear cover locking pin 11 abuts against the small-diameter end of the variable-diameter unlocking slide bar 3. At the same time, one end of the rear cover locking pin 11 separates from the outer shell, and the rear cover 6 unlocks from the outer shell. This locking module utilizes the step difference of the variable-diameter slide bar to achieve the instantaneous pop-out of the pin, resulting in a crisp unlocking action.

[0029] As an optional implementation, a third spring 13 is provided between the rear cover locking pin 11 and the rear cover 6. The third spring 13 is sleeved on the outside of the rear cover locking pin 11, and the third spring 13 causes the rear cover locking pin 11 to move towards the variable diameter unlocking slide bar 3. The rear cover 6 is coaxially arranged with the outer shell, and the rear cover 6 and the outer shell are axially slidingly fitted. A fourth spring is provided between the rear cover 6 and the outer shell.

[0030] A third spring 13 is provided between the rear cover locking pin 11 and the rear cover 6. The third spring 13 is sleeved on the outside of the rear cover locking pin 11 and always applies a spring force to the rear cover locking pin 11 towards the variable diameter unlocking slide bar 3. When the large diameter end of the variable diameter unlocking slide bar 3 is retracted, the third spring 13 pushes the rear cover locking pin 11 to move quickly towards the variable diameter unlocking slide bar 3, causing it to disengage from the outer shell, ensuring that the unlocking action is completed quickly and reliably. Afterwards, the rear cover 6 separates from the outer shell under the action of a fourth spring.

[0031] As an optional implementation, a second spring 12 is provided between the variable diameter unlocking slide bar 3 and the rear cover 6. The second spring 12 is sleeved on the outside of the variable diameter unlocking slide bar 3. The second spring 12 causes the variable diameter unlocking slide bar 3 to move towards the rear cover 6 and then reset.

[0032] A second spring 12 is provided between the variable diameter unlocking slide bar 3 and the rear cover 6. The second spring 12 is sleeved on the outside of the variable diameter unlocking slide bar 3 and applies an elastic force to the variable diameter unlocking slide bar 3 to move towards the rear cover 6 and then reset.

[0033] As an optional implementation, a first spring 4 is provided between the counterweight inertia block 1 and the outer shell. The first spring 4 is coaxially arranged with the counterweight inertia block 1, and the first spring 4 causes the counterweight inertia block 1 to move away from the rear cover 6.

[0034] A first spring 4 is provided between the counterweight inertia block 1 and the outer shell. The first spring 4 is coaxially arranged with the counterweight inertia block 1 and applies a spring force to the counterweight inertia block 1 to move it away from the rear cover 6. During firing, the counterweight inertia block 1 compresses the first spring 4 due to inertia and pushes the transmission slide rod 2; after leaving the barrel, the acceleration disappears, the first spring 4 pushes the counterweight inertia block 1 to reset, and at the same time, the air in the air cavity is discharged through the vent hole 5, realizing the dual functions of delayed reset and damping pressure relief.

[0035] As an optional implementation, the drone winding module includes a sliding sleeve 10, which is coaxially sleeved on the outside of the transmission slide rod 2 and slides in cooperation with the inner wall of the housing. Multiple elastic skirt frame skeletons 7 are fixed at one end to the sliding sleeve 10, and the multiple elastic skirt frame skeletons 7 are arranged around the sliding sleeve 10. The umbrella surface 9 is fixed to multiple elastic skirt frame frames 7; Multiple winding lines 8 correspond one-to-one with the elastic skirt frame 7. One end of the winding line 8 is fixed to the corresponding elastic skirt frame 7, and the other end of the winding line 8 is connected to a spool, which is located inside the outer shell. The winding thread 8 is stored inside the outer casing; Multiple elastic skirt frame 7 are removed from the outer shell, causing the umbrella surface 9 to unfold.

[0036] The drone winding module includes a sliding sleeve 10, multiple elastic skirt frames 7, a canopy 9, and multiple winding lines 8. The sliding sleeve 10 is coaxially sleeved on the outside of the transmission slide rod 2. One end of each elastic skirt frame 7 is fixed to the sliding sleeve 10 and arranged circumferentially. The canopy 9 is fixed on the elastic skirt frames 7. The winding lines 8 correspond one-to-one with the elastic skirt frames 7, with one end fixed to the frame and the other end connected to the spool. After the rear cover 6 is separated from the outer shell, the sliding sleeve 10 and the elastic skirt frames 7 are pulled out of the outer shell. The elastic skirt frames 7 automatically open to unfold the canopy 9, and the winding lines 8 are extracted using air resistance to form a three-dimensional interception line curtain.

[0037] As an alternative implementation, the mass of the spool is 1.5 to 3 times greater than the mass of a single strand of winding thread 8.

[0038] The spool configuration ensures that the end counterweight provides stable downward tension when the spool is deployed, preventing the tangled threads 8 from swaying or tangling in the high-speed airflow.

[0039] As an optional implementation, the elastic skirt frame 7 has 8 members.

[0040] The elastic skirt frame 7 is set to 8 pieces. This number is optimized to accommodate a sufficient number of winding lines 8 within the limited space of the projectile, and to ensure that the skirt frame 7 forms a uniform multi-directional interception line curtain after it is opened. Each direction corresponds to one winding line 8, achieving all-round physical interception coverage and increasing the probability of entanglement of the UAV propeller.

[0041] As an optional implementation, multiple elastic skirt skeletons 7 are arranged at equal intervals along the circumference of the sliding sleeve 10.

[0042] Multiple elastic skirt frame skeletons 7 are evenly spaced along the circumference of the sliding sleeve 10, meaning that the included angle between adjacent skeletons is equal. This uniform distribution ensures that the umbrella surface 9 is subjected to balanced force after the skirt frame skeletons 7 are opened, resulting in a symmetrical and stable unfolded posture. At the same time, the beginnings of each winding line 8 are forcibly constrained in space to different equally divided positions, effectively preventing multiple lines from intertwining in the air and forming a regular multi-directional three-dimensional line curtain.

[0043] Specifically, the present invention includes: Counterweight inertia block 1: During launch, the launch inertia of counterweight inertia block 1 pushes the transmission slide bar 2 to put the unlocking module in the loaded state; after launch, it continues to suppress the locking module to maintain the lock after the inertia disappears due to wind resistance.

[0044] Transmission slide 2: Transmits inertial force to the state switching unlock module.

[0045] Unlocking module: Internally integrates upper ratchet 14, lower ratchet 15, fixed guide rail 16 and second spring 12, adopts a pressing structure similar to a press pen, the upper ratchet 14 is connected to the transmission slide bar 2, and has two stable states: "locked extension" and "released".

[0046] The variable diameter unlocking slide bar 3 has a thick section at the front and a thin section at the back, with a right-angle step transition between the two sections.

[0047] The work process includes: Loading process (firing acceleration phase): Before firing, keep the thicker end of the variable diameter unlocking slide bar 3 aligned with the rear cover locking pin 11 of the rear cover 6 locking hole, so that the rear cover 6 remains connected to the outer casing; after firing, as the outer casing accelerates forward inside the barrel, the counterweight inertia block 1 generates inertia that pulls the transmission slide bar 2 backward. Under the action of the inertia of the counterweight inertia block 1, the transmission slide bar 2 pushes the variable diameter unlocking slide bar 3 to move, switching it from the "locked extended" state to the "ready to release" state. At this time, the thicker end of the variable diameter unlocking slide bar 3 still presses against the rear cover locking pin 11, and the rear cover remains stationary.

[0048] Gas lock process: After leaving the barrel, the acceleration disappears, and the first spring 4 inside pushes the counterweight inertia block 1 forward. Before this, the counterweight inertia block 1 forms an air chamber between the outer shell and the counterweight inertia block 1 due to inertia. The air in the air chamber forms an air cushion. Since the outer shell has acceleration when it is fired, while the counterweight inertia block 1 is stationary due to inertia, after the outer shell and the counterweight inertia block 1 are relatively stationary, the counterweight inertia block 1 resets under the action of the first spring 4. Therefore, the air intake speed of the vent hole 5 is higher than the air exhaust speed of the vent hole 5. At this time, an air cushion is formed between the outer shell and the counterweight inertia block 1, which can delay the separation of the outer shell and the rear cover 6.

[0049] The unlocking module remains in the "pending release" state; as long as the air pressure persists, the back cover 6 will remain locked.

[0050] Air leakage and depressurization process of vent hole 5: As the flight time and distance increase, the gas in the air chamber gradually and slowly leaks through vent hole 5, the air cushion resistance gradually weakens, and the first spring 4 pushes the counterweight inertial block 1 to drive the transmission slide rod 2 to move towards the projectile.

[0051] Since the unlocking module has entered the "waiting to release" state, the forward movement of the transmission slide bar 2 causes the variable diameter unlocking slide bar 3 to pass the locking position, and the rear cover locking pin 11 pops out instantly under the action of its own external spring, disengaging from the locking groove of the rear cover 6; the rear cover 6 separates backward.

[0052] Drone winding module release process: The drone winding module is fitted outside the slide bar and floats freely inside the outer shell, without being rigidly connected to the outer shell or the transmission slide bar 2. The front end of the drone winding module abuts against the step inside the projectile, and the rear end is blocked by the rear cover 6.

[0053] One end of multiple (e.g., 8) 0.2mm UHMWPE winding threads 8 is connected to different endpoints of the elastic skirt frame 7, and the other end of the winding threads 8 is wound around the spool. The spool is located inside the housing. Multiple spools are arranged around the transmission slide rod 2, or they can be sleeved on the outside of the transmission slide rod 2. As the back cover 6 separates from the housing, the spool also separates from the transmission slide rod 2.

[0054] In this embodiment, multiple spools are arranged around the transmission slide bar 2 and located on the rear cover 6. The rear cover 6 separates from the outer shell and releases the winding line 8 during the descent.

[0055] The elastic skirt frame 7 is made of elastic material. The drone winding module resembles a miniature umbrella folded up, with each elastic skirt frame 7 connected to a winding line 8. The sliding sleeve 10 is fitted onto the outside of the transmission slide rod 2, and the umbrella surface 9 is folded and placed inside the outer shell to reduce space occupation. After the drone winding module is released, it opens instantly, forming an umbrella shape resembling half an eggshell.

[0056] Integral ejection: After the rear cover locking pin 11 is pulled out, the drone winding module and the rear cover 6 are separated from the outer shell as a whole.

[0057] Wind resistance differential cable deployment: After the UAV winding module emerges from its shell, the canopy 9 opens instantly, releasing the winding cables 8. The first ends of the eight winding cables 8 are fixed to one end of the elastic skirt frame 7, and the spools connected to the tail ends of the winding cables 8 serve as miniature counterweights. The mass of the miniature counterweights is 1.5 to 3 times greater than the total mass of the single winding cable connected to them. During the cable unfolding process, the spools use their own mass to provide downward tension, overcoming the swaying and cable convergence effects of the flexible cables in high-speed airflow. At the same time, because the first ends of the eight winding cables 8 are spatially constrained to different divergent directions by the elastic skirt frame 7, as the winding cables 8 are continuously pulled backward, the spools naturally disperse under gravity and wake disturbance. Combined with the geometric misalignment distribution of the first ends of the winding cables 8, this effectively avoids the mutual entanglement of multiple winding cables 8 in the air, ultimately unfolding behind the projectile to form a three-dimensional line curtain array with multi-directional physical interception thickness.

[0058] Furthermore, the end counterweight is a microparticle structure with the same polarity charge. At the instant the spindle assembly decouples from the skirt, the ends of each wound thread are in a state of millimeter-level dense spacing. At this time, the short-range Coulomb repulsion force generated between the electret particles serves as the initial bias force, overcoming the surface friction and convergence tendency when the wire bundle exits the shell, and giving each thread a small initial divergent displacement. As the wire curtain is continuously drawn out and the spacing between the lines exceeds the range of electrostatic action, it transforms into the final unfolding form of the wire curtain dominated by aerodynamic drag.

[0059] See Table 1 for the complete sequence of actions.

[0060] Table 1 Action Sequence Table In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0061] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A miniature anti-drone entangled bullet, characterized in that, include: shell; The back cover (6) is fixed to the outer shell by a locking module, and the outer shell and the back cover (6) are elastically slidably engaged. The locking module is driven by an unlocking module, which is connected to the back cover (6). The unlocking module drives the locking module to unlock the back cover (6) from the outer shell, and the back cover (6) separates from the outer shell under the action of elastic force. A counterweight inertia block (1) is elastically slidably fitted inside the outer shell, and the counterweight inertia block (1) is located at one end away from the rear cover (6). An air cavity is provided between the counterweight inertia block (1) and the outer shell, and the air cavity is connected to a vent hole (5). The counterweight inertia block (1) is connected to the unlocking module via the transmission slide rod (2). After the outer shell is ejected, the counterweight inertia block (1) stops due to inertia, causing the transmission slide rod (2) to move relative to the outer shell and push the movable end of the unlocking module. Subsequently, the counterweight inertia block (1) discharges the air in the air cavity through the vent hole (5) under the action of elasticity. After the movable end of the unlocking module is reset, the unlocking is completed, and the outer shell separates from the rear cover (6). The drone winding module is disposed inside the housing. After the rear cover (6) is separated from the housing, the drone winding module is removed from the housing and unfolded.

2. The anti-drone miniature entangled bullet according to claim 1, characterized in that, The unlocking module includes a fixed guide rail (16) which is coaxially fixed with the back cover (6). The fixed guide rail (16) has an upper end face ratchet (14) that is slidably engaged. One end of the upper end face ratchet (14) is in contact with the end of the transmission slide bar (2) that is away from the counterweight inertia block (1). The upper end ratchet (14) engages with the lower end ratchet (15), and the bottom end of the lower end ratchet (15) is coaxially rotated with a variable diameter unlocking slide bar (3). The variable diameter unlocking slide bar (3) is elastically slidably engaged with the rear cover (6). The fixed guide rail (16) is provided with a long guide rail and a short guide rail. The bottom ends of the long guide rail and the short guide rail are both engaged with the lower end face ratchet (15). The upper end face ratchet (14) is vertically slidably engaged with the long guide rail. After the upper end face ratchet (14) pushes the teeth of the lower end face ratchet (15) to slide out of the short guide rail, the lower end face ratchet (15) is deflected under the engagement of the short guide rail and the lower end face ratchet (15), so that the teeth of the lower end face ratchet (15) enter the long guide rail and slide. The variable diameter unlocking slide (3) has a stepped structure. The small diameter end of the variable diameter unlocking slide (3) is vertically slidably engaged with the rear cover (6). The large diameter end of the variable diameter unlocking slide (3) is limitedly engaged with the locking module. After the large diameter end of the variable diameter unlocking slide (3) is displaced, it separates from the locking module, so that one end of the locking module contacts the small diameter end of the variable diameter unlocking slide (3). At this time, the outer shell and the rear cover (6) are unlocked.

3. The anti-drone miniature entangled bullet according to claim 2, characterized in that, The locking module includes a rear cover locking pin (11), which slides horizontally and is elastically connected to the rear cover (6). One end of the rear cover locking pin (11) is limited to the outer shell, and the other end of the rear cover locking pin (11) abuts against the large diameter end of the variable diameter unlocking slide bar (3). After the variable diameter unlocking slide bar (3) is displaced, the other end of the rear cover locking pin (11) abuts against the small diameter end of the variable diameter unlocking slide bar (3), and at the same time, one end of the rear cover locking pin (11) separates from the outer shell, and the rear cover (6) unlocks from the outer shell.

4. The anti-drone miniature entangled bullet according to claim 3, characterized in that, A third spring (13) is provided between the rear cover locking pin (11) and the rear cover (6). The third spring (13) is sleeved on the outside of the rear cover locking pin (11). The third spring (13) causes the rear cover locking pin (11) to move closer to the variable diameter unlocking slide bar (3). The rear cover (6) is coaxially arranged with the outer shell, and the rear cover (6) and the outer shell are axially slidingly engaged. A fourth spring is provided between the rear cover (6) and the outer shell.

5. The anti-drone miniature entangled bullet according to claim 2, characterized in that, A second spring (12) is provided between the variable diameter unlocking slide (3) and the rear cover (6). The second spring (12) is sleeved on the outside of the variable diameter unlocking slide (3). The second spring (12) causes the variable diameter unlocking slide (3) to move toward the rear cover (6) and then reset.

6. The anti-drone miniature entangled bullet according to claim 1, characterized in that, A first spring (4) is provided between the counterweight inertia block (1) and the outer shell. The first spring (4) is coaxially arranged with the counterweight inertia block (1). The first spring (4) causes the counterweight inertia block (1) to move away from the rear cover (6).

7. The anti-drone miniature entangled bullet according to claim 1, characterized in that, The UAV winding module includes a sliding sleeve (10), which is coaxially sleeved on the outside of the transmission slide rod (2) and slides in cooperation with the inner wall of the outer shell; Multiple elastic skirt frame skeletons (7) are fixed at one end to the sliding sleeve (10), and the multiple elastic skirt frame skeletons (7) are arranged circumferentially along the sliding sleeve (10); The umbrella canopy (9) is fixed to multiple elastic skirt frame frames (7); Multiple winding lines (8) correspond one-to-one with the elastic skirt frame (7). One end of the winding line (8) is fixed to the corresponding elastic skirt frame (7), and the other end of the winding line (8) is connected to a spool, which is located inside the outer shell. The winding thread (8) is housed inside the outer casing; After the multiple elastic skirt frames (7) are removed from the outer shell, the umbrella canopy (9) unfolds.

8. The anti-drone miniature entangled bullet according to claim 7, characterized in that, The mass of the spool is 1.5 to 3 times greater than the mass of a single strand of the winding thread (8).

9. A miniature anti-drone entanglement projectile according to claim 7, characterized in that, The elastic skirt frame (7) has 8 supports.

10. A miniature anti-drone entanglement projectile according to claim 7, characterized in that, Multiple elastic skirt skeletons (7) are arranged at equal intervals along the circumference of the sliding sleeve (10).

Images