Flexible winding type optical fiber cutting device and countermeasure method

Abstract

The application discloses a flexible winding type optical fiber cutting device and a countermeasure method, and belongs to the technical field of low-altitude security and anti-unmanned aerial vehicle. The device comprises a flexible winding cutting body 20 and a directional projection launching device 10. The flexible winding cutting body 20 takes a flexible rope body 21 as a base body, is provided with a plurality of occlusion elements 22 at intervals along an axial direction, and is respectively connected with inertial counterweight members 23 at two ends. After launching, the cutting body is unfolded in the air to form a dynamic interception belt; when a target towed optical guide fiber 30 contacts the interception belt, the occlusion elements 22 guide the optical guide fiber 30 to slide into a gap and be wound by the rope body 21, and the inertial movement of the inertial counterweight members 23 at the two ends exerts a composite shearing force and a limit bending force on the optical guide fiber 30, so that brittle fracture of the optical guide fiber 30 occurs within a millisecond level time, and the unmanned aerial vehicle is out of control. The application has extremely low single-shot cost, has no explosion fragments and incidental damage, effectively solves the technical problems that an optical fiber guided unmanned aerial vehicle is immune to electromagnetic interference and a traditional hard-killing method has excessively high cost, and is especially suitable for cluster defense scenes in urban environments.

Description

Technical Field

[0001] This invention relates to the field of low-altitude security and anti-drone technology, and more specifically, to a flexible winding optical fiber cutting device and countermeasure method for physically cutting off cables towed by drones. Background Technology

[0002] With the rapid development of drone technology, fiber-optic guided drones have become a major threat in the field of low-altitude security. These drones achieve wired communication with the control terminal by towing extremely thin optical fibers, typically 0.2 to 0.5 mm in diameter. They have extremely strong resistance to electromagnetic interference, rendering traditional electronic warfare equipment such as GPS spoofing and communication link interference completely ineffective against them.

[0003] Existing countermeasures against fiber-optic guided drones mainly suffer from the following technical bottlenecks:

[0004] 1. Hard-kill methods are costly and cause significant collateral damage. Destroying drones using missiles, anti-aircraft guns, or laser weapons costs anywhere from tens of thousands to hundreds of thousands of yuan per shot, and poses a serious risk of collateral damage in urban environments, making them unsuitable for swarm defense scenarios.

[0005] 2. Lack of dedicated interception devices for ultra-fine optical fibers. Ordinary ropes or mesh interceptors are difficult to effectively capture ultra-fine optical fibers moving at high speeds—the diameter of the optical fiber is only 0.2~0.5mm, and it is very easy to slip off the surface of the rope under high-speed relative motion; while rigid cutters or blade-type interceptors are difficult to maintain a stable cutting posture during long-distance projection.

[0006] 3. Existing flexible interceptors lack active cutting capability. Even if the optical fiber is wrapped by a flexible body, if sufficient shearing and bending forces cannot be applied in a very short time, the optical fiber may still slip after the tension is released, making reliable cutting impossible.

[0007] Therefore, there is an urgent need for a new type of low-cost interception device that can autonomously deploy in the air using aerodynamic principles, has flexible capture and entanglement capabilities, and can generate instantaneous composite shear force through inertial effects to cut extremely fine optical fibers. Summary of the Invention

[0008] The purpose of this invention is to provide a flexible winding optical fiber cutting device and countermeasure method to solve the technical problem that existing technologies cannot efficiently and cost-effectively cut the optical fibers dragged by drones.

[0009] To achieve the above objectives, the present invention provides the following technical solution:

[0010] A flexible winding optical fiber cutting device includes a flexible winding cutting body 20 and a directional projectile launching device 10.

[0011] The flexible winding and cutting body 20 is a flexible strip structure, including: a flexible rope 21, which forms a bearing base; multiple interlocking elements 22, which are spaced apart along the axial direction of the flexible rope 21, and a gap is formed between adjacent interlocking elements 22 to accommodate the sliding of the optical fiber 30; and inertial counterweights 23, which are respectively connected to both ends of the flexible winding and cutting body 20.

[0012] The directional projectile launching device 10 is used to project the flexible winding cutting body 20, which is in a retracted state, into a preset airspace, so that it unfolds to form a dynamic interception cutting strip.

[0013] Its core working mechanism is as follows: After the flexible winding cutting body 20 exits the barrel, the inertial counterweights 23 at both ends are stretched to both sides under the action of inertia, which drives the flexible rope 21 and the biting element 22 to unfold rapidly in the air. When the optical fiber 30 hits the interception strip, the special configuration of the biting element 22 guides the optical fiber 30 to slide into the gap, and the flexible rope 21 then forms a winding constraint on the optical fiber 30; at the same time, the lateral motion component of the inertial counterweights 23 at both ends applies ultimate bending force and lateral shear force to the optical fiber 30, causing the bending radius of the optical fiber 30 to be compressed to below the critical value in an instant, and brittle fracture occurs within milliseconds.

[0014] The beneficial effects of this invention are as follows:

[0015] 1. Low cost and high efficiency: The manufacturing cost of a single flexible winding cutting body 20 is extremely low, far lower than that of hard-kill methods such as missiles and lasers, making it suitable for large-scale cluster deployment and salvo interception;

[0016] 2. No collateral damage: The flexible winding cutting body 20 is a non-explosive kinetic energy interceptor, with no fragments or shock waves, making it suitable for densely populated environments such as cities;

[0017] 3. Independent of electromagnetic characteristics: This device cuts the optical fiber 30 through physical contact, and is not triggered by the radio frequency radiation or thermal radiation characteristics of the target, which has a natural restraining effect on fiber optic guided drones.

[0018] 4. Reliable cutting mechanism: Through the combined stress of "winding + bending + shearing", the optical fiber 30 is ensured to undergo irreversible brittle fracture in a very short time, resulting in high cutting reliability;

[0019] 5. Autonomous Deployment in the Air: The autonomous deployment in the air is achieved by utilizing the inertial effect of the inertial counterweight 23. It does not require a complex deployment mechanism, and has a simple structure and high reliability. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of the flexible winding and cutting body of the present invention;

[0021] Figure 2A schematic diagram of the structure in which the interlocking element engages with the flexible rope;

[0022] Figure 3 A schematic diagram of the aerial deployment process of the directional projectile launcher and the flexible winding and cutting body;

[0023] Figure 4 A magnified schematic diagram of the physical mechanism of fiber breakage by wrapping an optical fiber around a flexible winding cutter and applying shearing / bending force.

[0024] Explanation of reference numerals in the attached figures:

[0025] mark name 10 directional projectile launcher 11 Transmitter array 20 Flexible winding cutting body 21 flexible rope 22 Engagement element 23 Inertial counterweight 231 Tungsten ball 232 elastic buffer layer 30 optical fiber Detailed Implementation

[0026] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0027] Example 1: Device Structure

[0028] like Figure 1 and Figure 3 As shown, this embodiment provides a flexible winding optical fiber cutting device, which mainly consists of a directional ejection device 10 and several flexible winding cutting bodies 20.

[0029] 1. Directional projectile launching device 10

[0030] like Figure 3 As shown, the directional projectile launching device 10 includes a clustered array of launch tubes 11 for high-speed launching of a folded, coiled cutting body 20 into the air. The power source can be a high-pressure pneumatic system suitable for training and low-threat scenarios, or a low-pressure propellant gas system suitable for high-threat combat scenarios. The directional projectile launching device 10 is configured to drive the flexible coiled cutting body 20 out of the barrel with an initial velocity of 40-80 m / s, preferably 60 m / s.

[0031] II. Flexible winding cutting body 20

[0032] like Figure 1 and Figure 2 As shown, the flexible winding and cutting body 20 is the core component for performing the winding and cutting task. It is a flexible strip structure with a total length of 2.0~6.0 meters, preferably 4.0 meters, and a total mass of 150~300g, preferably 220g.

[0033] 1. Flexible rope body 21: such as Figure 1As shown, the flexible rope 21 constitutes the supporting matrix of the flexible winding and cutting body 20. It is made of multi-strand braided ultra-high molecular weight polyethylene (UHMWPE) fibers or Kevlar fibers, with a diameter of approximately 1.5 mm and a breaking strength greater than 2000 N. The flexible rope 21 has high strength, low elongation, and excellent wear resistance, and can provide sufficient restraint force when winding the optical fiber 30 without breaking itself.

[0034] 2. Occlusal element 22: such as Figure 2 As shown in the side view and partial enlarged view of the interlocking elements, multiple interlocking elements (22) are axially spaced around the outside of the flexible rope (21). The interlocking elements (22) are made of polyurethane (PU) or thermoplastic elastomer (TPE) material and are integrally molded onto the outer surface of the flexible rope (21) by injection molding. As can be seen from the figure, each interlocking element (22) has a spindle-shaped or olive-shaped structure that is wider in the middle and narrower at both ends. Its specific dimensional parameters are as follows: the outer diameter D is 3~6mm (preferably 4mm), the axial length L is 5~10mm (preferably 8mm); a gap for accommodating optical fibers is formed between two adjacent interlocking elements (22), and the axial spacing S of the gap is 5~15mm (preferably 10mm). The core functions of the interlocking element 22 include: ① increasing air resistance to assist the flexible winding and cutting body 20 in unfolding in the air; ② its special shape forms a "V" or "U" shaped gap between adjacent particles, which guides and accommodates the optical fiber 30 when it impacts, guiding the optical fiber 30 to slide in and be wound by the flexible rope 21; ③ providing a mechanical interlocking point similar to a "gear" to prevent the optical fiber 30 from slipping off after winding.

[0035] 3. Inertial counterweight 23: such as Figure 1 As shown, inertial counterweights 23 are fixed at both ends of the flexible winding cutting body 20. The inertial counterweights 23 are made of materials including but not limited to tungsten alloy, weigh approximately 100g, and are designed in a streamlined teardrop shape to reduce air resistance upon exiting the barrel. The core functions of the inertial counterweights 23 are: ① After exiting the barrel, they utilize inertia to stretch the flexible rope (21) to both sides, achieving autonomous deployment in the air; ② After the optical fiber 30 is wound, its lateral motion component applies lateral shear force and ultimate bending force to the optical fiber 30, achieving cutting. Furthermore, as... Figure 2 As shown in the AA cross-sectional structure, the interlocking element 22, the elastic buffer layer 232, and the inertial counterweight 23 are coaxially connected in sequence along the axial direction to form a stable end assembly. Elastic buffer layer 232: as shown... Figure 1As shown, the inertial counterweight 23 contains, but is not limited to, tungsten balls 231, and its outer surface is covered with an elastic buffer layer 232 made of silicone rubber. The functions of the elastic buffer layer 232 are: ① to provide frictional grip in the initial stage of contact with the optical fiber 30, preventing the optical fiber 30 from bouncing off under high-speed impact; ② to protect the body of the inertial counterweight 23 and extend its service life.

[0036] 5. Folding and retracting method: The flexible winding and cutting body 20 is in a folded and retracted state before launch. The folding method can be Z-shaped folding, S-shaped folding or spiral folding to ensure that it can be smoothly unfolded after leaving the barrel without tangling or knotting.

[0037] Example 2: Working Principle and Countermeasures

[0038] like Figure 3 and Figure 4 As shown in the figure, this embodiment discloses a method for countering fiber-optic guided UAVs using the above-mentioned device. The specific steps are as follows:

[0039] S1: Detection and Lock-on. Lock onto the flight path of the enemy's fiber-optic guided UAV using radar, electro-optical detection systems, or acoustic detection systems, identify the trailing fiber optic cable 30, and calculate the predicted intersection point between the target and the interception site.

[0040] S2: Directional Projection. The control system triggers the directional projection launching device 10, driving multiple flexible wound cutting bodies 20 within the launching tube array 11 to fire simultaneously towards the predicted intersection point. In a preferred embodiment, the directional projection launching device 10 fires 4 to 32 flexible wound cutting bodies 20 simultaneously within 1 to 3 seconds, forming a three-dimensional interception net in space with a width of not less than 10 meters and a height of not less than 10 meters, significantly improving the hit probability.

[0041] S3: Deploy in mid-air. (Example) Figure 3 As shown, after the flexible winding cutting body 20 flies out of the nozzle of the launch tube array 11, the inertial counterweights 23 at both ends are stretched to both sides at high speed under the action of inertia, which drives the flexible rope 21 and the interlocking element 22 in the middle to rapidly unfold in the air, forming a dynamic interception and cutting strip covering the airspace. After multiple flexible winding cutting bodies 20 are deployed at the same time, they intertwine in space to form a three-dimensional interception net.

[0042] S4: Wrap and cut. For example... Figure 4As shown, when the optical fiber 30 (0.2~0.5mm in diameter) towed by the drone impacts the intercepting and cutting strip, under the action of relative velocity, the optical fiber 30 slides along the inclined surface of the interlocking element 22 into the gap between adjacent particles. Subsequently, the flexible rope 21 forms a winding constraint on the optical fiber 30 under tension (usually winding 1~2 turns). At the same time, it enters the winding and ultimate bending shearing stage. Due to inertia, the inertial counterweights 23 at both ends continue to move, generating inertial configuration tension (F1, F2). This force forces the bending radius of the optical fiber 30 at the bending point to be instantly compressed below the critical value (usually less than 2mm), thereby generating ultimate bending stress and causing it to break.

[0043] S5: Target Failure. Due to the inability of the fiber optic 30 quartz glass material to withstand the aforementioned combined stress, a brittle fracture occurs within 2 milliseconds, causing the drone to lose control and image transmission signals, resulting in a forced landing or crash.

[0044] Key Notes: This method does not rely on the target's radio frequency radiation or thermal radiation characteristics for triggering. The flexible winding cutting body 20 is a non-explosive kinetic energy interceptor. The entire countermeasure process is free of explosions, fragments, and electromagnetic radiation, making it particularly suitable for low-altitude security applications in urban environments.

[0045] Example 3: Parameter Optimization Design

[0046] For different threat scenarios, the key parameters of the flexible winding cutting body 20 can be optimized as follows:

[0047] parameter Urban close-range defense Field mid-range defense Long-range defense of key locations Total length of the cut body 2.0~3.0m 3.0~4.5m 4.5~6.0m Total mass of the cut body 150~200g 200~250g 250~300g counterweight mass 50~80g 80~120g 120~150g muzzle velocity 40~55m / s 55~70m / s 70~80m / s salvo quantity 4-8 shots 8~16 shots 16-32 rounds interception area ≥5m×5m ≥10m×10m ≥15m×15m

Claims

1. A flexible wound optical fiber cutting device, characterized in that, include: A flexible winding and cutting body 20, wherein the flexible winding and cutting body 20 is a flexible elongated structure, comprising: • The flexible rope 21 constitutes the supporting base of the flexible winding and cutting body 20; • Multiple engagement elements 22 are spaced apart on the flexible rope 21 along the axial direction of the flexible rope 21, and a gap is formed between adjacent engagement elements 22 to accommodate the sliding of the optical fiber 30. • Inertial counterweights 23 are respectively connected to both ends of the flexible winding and cutting body 20; The directional projectile launching device 10 is used to project the flexible winding cutting body 20, which is in a retracted state, into a preset airspace, so that it unfolds to form a dynamic interception cutting strip; The flexible winding and cutting body 20 is configured such that when it contacts the target-draggled optical fiber 30 in the unfolded state, the biting element 22 guides the optical fiber 30 into the gap, the flexible rope 21 forms a winding constraint on the optical fiber 30, and the inertial counterweight 23 applies lateral shear force and bending force to the optical fiber 30 under inertial action, causing the optical fiber 30 to break.

2. The apparatus according to claim 1, characterized in that, The flexible rope 21 is made of high-strength fiber material, including but not limited to at least one of Kevlar fiber, ultra-high molecular weight polyethylene fiber, carbon fiber, basalt fiber or PBO fiber; the diameter of the flexible rope 21 is 1.0~2.0mm, and the breaking strength is not less than 2000N.

3. The apparatus according to claim 1, characterized in that, The engagement element 22 is made of a polymer elastic material, including but not limited to at least one of polyurethane, thermoplastic elastomer, nylon, polyoxymethylene or polypropylene; the engagement element 22 is integrally formed on the outer surface of the flexible rope 21 by injection molding.

4. The apparatus according to claim 1, characterized in that, The shape of the occlusal element 22 includes, but is not limited to, columnar, spindle-shaped, or olive-shaped; the outer diameter of the occlusal element 22 is 3~6mm, the axial length is 5~10mm, and the axial distance between two adjacent occlusal elements 22 is 5~15mm; the distance is configured to allow the optical fiber 30 with a diameter of 0.2~0.5mm to slide in and form a mechanical occlusion.

5. The apparatus according to claim 1, characterized in that, The mass of the inertial counterweight 23 is 50~150g, and the material is including but not limited to at least one of tungsten alloy, lead core coated with rubber, or steel core coated with rubber; the shape of the inertial counterweight 23 is including but not limited to a streamlined teardrop shape or a spherical shape; the outer surface of the inertial counterweight 23 is covered with an elastic buffer layer 232, and the material of the elastic buffer layer 232 is including but not limited to silicone rubber or polyurethane.

6. The apparatus according to claim 1, characterized in that, The total length of the flexible winding cutting body 20 is 2.0 to 6.0 meters, and the total mass is 150 to 300g. The flexible winding cutting body 20 is in a folded and retracted state before launch. The folding method includes, but is not limited to, at least one of Z-shaped folding, S-shaped folding or spiral folding.

7. The apparatus according to claim 1, characterized in that, The directional projectile launching device 10 includes a clustered array of launching tubes 11, and the power source includes, but is not limited to, a high-pressure pneumatic system or a low-pressure propellant gas system; the directional projectile launching device 10 is configured to drive the flexible winding cutting body 20 out of the barrel at an initial velocity of 40~80m / s.

8. The apparatus according to claim 1, characterized in that, The cutting mechanism of the flexible winding cutting body 20 on the optical fiber 30 is as follows: after the flexible rope 21 winds the optical fiber 30, it forces the bending radius of the optical fiber 30 to be compressed instantaneously to less than its critical bending radius. At the same time, the lateral shear stress applied by the inertial counterweight 23 exceeds the shear strength limit of the optical fiber 30, causing the optical fiber 30 to undergo brittle fracture within 2 milliseconds.

9. A method for countering fiber-optic guided unmanned aerial vehicles using the device described in any one of claims 1 to 8, characterized in that, Includes the following steps: S1: Detection and Locking – The flight path of the target UAV and its trailing optical fiber 30 is obtained through the detection system, and the intersection point is calculated and predicted. S2: Directional projectile launch – Control the directional projectile launcher 10 to launch at least one of the flexible winding cutter bodies 20 toward the predicted intersection point; S3: Air Deployment - After the flexible winding cutting body 20 exits the barrel, the inertial counterweights 23 at both ends are stretched to both sides under the action of inertia, which drives the flexible rope 21 and the biting element 22 to unfold and form a dynamic interception cutting strip. S4: Entangling and Cutting - After the optical fiber 30 hits the intercepting and cutting strip, it slides into the gap of the biting element 22 and is entangled by the flexible rope 21. The inertial movement of the inertial counterweight 23 applies a composite stress to the optical fiber 30, causing it to break. S5: Target Failure - The drone goes out of control due to signal transmission interruption caused by the breakage of optical fiber 30.

10. The method according to claim 9, characterized in that, In step S2, the directional projectile launching device 10 fires 4 to 32 flexible winding cutting bodies 20 in 1 to 3 seconds, forming a three-dimensional interception net with a width of not less than 10 meters and a height of not less than 10 meters in space; the method does not rely on the target's radio frequency radiation characteristics or thermal radiation characteristics for triggering, and the flexible winding cutting body 20 is a non-explosive kinetic energy interceptor.

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