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CN-122015581-A - Lightweight common-cavity casting net capturing device

CN122015581ACN 122015581 ACN122015581 ACN 122015581ACN-122015581-A

Abstract

The invention relates to a lightweight common-cavity casting net capturing device. The ignition device comprises an ignition component and a net bin component which are detachably connected, wherein the net bin component comprises a shell, a common cavity cap is arranged in the shell, the net bin component further comprises a plurality of casting barrels which are detachably connected with the common cavity cap, a traction body is arranged in each casting barrel, a flexible rope net connected with the traction body is positioned in the shell, a cover plate is arranged at an outlet of the shell and provides a starting pressure threshold value, a high-pressure buffer chamber is formed between the ignition component and the common cavity cap, and the high-pressure buffer chamber enables dynamic pressure of a central axis to be free from attenuation through the grading design of a first-stage diffusion cavity and a second-stage stagnation cavity, and a flow field enters a complete stagnation area. The invention solves the problems of non-sharing cavity and uneven coverage of the traditional net capturing device, has the advantages of compact structure, micro recoil, low collateral damage, high energy conversion efficiency and the like, supports multi-device joint arrangement and quick module replacement, and is particularly suitable for high-efficiency physical interception of unmanned aerial vehicles.

Inventors

  • CHEN XI
  • WANG YANBO
  • SUN QIXIANG
  • GU LU
  • ZHANG JIALE
  • NIU YUXUAN

Assignees

  • 南京理工大学

Dates

Publication Date
20260512
Application Date
20260317

Claims (10)

  1. 1. The lightweight common-cavity casting net capturing device is characterized by comprising an ignition assembly (1) and a net bin assembly (2) which are detachably connected; The net bin assembly (2) comprises a shell (7), a common cavity cap (8) is arranged in the shell (7), a plurality of projectile tubes (10) detachably connected with the common cavity cap are further arranged, a traction body (11) is arranged in each projectile tube (10), a flexible rope net (9) connected with the traction body (11) is positioned in the shell (7), a cover plate (12) is arranged at an outlet of the shell (7), and the cover plate (12) provides a starting pressure threshold value; A high-pressure buffer chamber is formed between the ignition assembly (1) and the common cavity cap (8), and the high-pressure buffer chamber adopts a grading design of a first-stage diffusion cavity and a second-stage stagnation cavity, so that the dynamic pressure of a central axis is not attenuated, a flow field enters a complete stagnation area, and the instantaneous, uniform and common cavity action of the gas pressure on all traction bodies (11) is ensured.
  2. 2. The device according to claim 1, wherein the ignition assembly (1) takes a black powder or a gas generator as a controllable instantaneous power source, generates high-pressure fuel gas under electric triggering, and the instantaneous release pressure of the gas generator is equivalent to the peak pressure generated by the loading mg of the black powder; The ignition component (1) takes black powder as a controllable instantaneous power source, and the ignition component (1) comprises a compression pad (3), a medicine chamber (4), a medicine cover (5) and a connector (6); The outer periphery of the middle lower part of the connector (6) is provided with an annular bulge, and the outer wall of the lower side of the annular bulge of the connector (6) is provided with an external thread connected with the common cavity cap (8), and a high-pressure buffer cavity is formed among the medicine cover (5), the connector (6) and the common cavity cap (8); The inner wall of the lower end of the medicine chamber (4) is provided with threads, the outer wall of the upper end of the medicine cover (5) is provided with threads, the medicine chamber (4) is in threaded connection with the medicine cover (5), black powder is filled in the medicine chamber (4), the bottom of the medicine cover (5) is provided with a prefabricated notch groove in a shape like a Chinese character 'mi'; The upper end of the pressing pad (3) is provided with an annular limiting part which is contacted with and limited by the upper surface of a boss of the medicine chamber (4), and the inner wall surface of the upper part of the connector (6) is provided with a step which is contacted and positioned with the lower surface of the boss of the medicine chamber (4), so that the completion of limiting of the medicine chamber (4) is realized.
  3. 3. Device according to claim 2, characterized in that the housing (7) and the co-chamber cap (8) are screwed together, the number of projectile tubes (10) and traction bodies (11) being six; six threaded holes which are uniformly distributed and at a preset angle are formed in the common cavity cap (8), and the threaded holes are used for being connected with six projectile tubes (10) in a threaded manner; The tail parts of the six traction bodies (11) are connected with the flexible rope net (9) in a rope knotting mode, the traction bodies (11) fly away from the projectile tube (10) and pull the flexible rope net open at the same time, so that a hexagonal flexible rope net is formed; the cover plate (12) is tightly matched with the shell (7), so that the device has a starting threshold value while ensuring good sealing performance, and six traction bodies (11) are thrown out in a common cavity.
  4. 4. The device according to claim 1, wherein the drug cap (5) and the connector (6) are made of aluminum alloy, the flexible rope net (9) is made of a large-force horsepower material, the projectile tube (10) is made of carbon steel, and the traction body (11) is made of tungsten alloy.
  5. 5. The device of claim 4, wherein the diameter of the drug chamber is Satisfies the following formula: , Wherein, the , , In the formula, The method is characterized by comprising the steps of setting an inlet area of a high-pressure buffer chamber, setting A out as a total output flux area of the high-pressure buffer chamber, setting mu as a flow coefficient and a ratio of the total input flux area to the total output flux area, wherein the range of values is defined as: N is the number of outlets, and r is the radius of each projectile tube.
  6. 6. The apparatus of claim 5, wherein the high pressure buffer chamber is configured with a first stage diffuser and a second stage stagnation chamber in a staged configuration comprising: The part corresponding to the common cavity cap and the connector connecting section is a first-stage diffusion cavity, the part corresponding to the common cavity cap is a second-stage stagnation cavity, the tail end of the first-stage diffusion cavity is provided with a transition section with the inner diameter enlarged from the inner diameter of the first-stage diffusion cavity main body to the inner diameter of the second-stage stagnation cavity main body, the outlet of the second-stage stagnation cavity is of a flat bottom structure, the peripheral edge of the flat bottom is provided with a smooth transition chamfer, and the flat bottom main body is uniformly provided with six throwing holes with a preset inclination angle theta.
  7. 7. The apparatus of claim 6, wherein the first stage diffuser has an inner diameter Is calculated as follows: according to the principle of conservation of hydrodynamic energy, a Bernoulli equation containing energy loss terms between an inlet section and a high-pressure buffer chamber section is established: , wherein: To inject the static pressure at the inlet of the channel, To restore static pressure in the high pressure buffer chamber, For the average velocity of the fluid injected into the channel, For the average velocity of the fluid in the high pressure buffer chamber, Is the density of the fuel gas, and the fuel gas is in a high temperature state, The mechanical energy loss for sudden expansion is defined by the "Boda-Carnot equation: , And deriving the pressure recovery amount of conversion of kinetic energy to static pressure by combining the two formulas : , From this, a pressure recovery coefficient for kinetic energy to static pressure conversion is derived Area ratio The relation of (2) is: , To calculate Maximum value of (2), pair of First derivative analysis was performed: , Let the derivative be zero, and solve =0.5, I.e. optimal expansion ratio ; Setting value based on inlet area of high-pressure buffer chamber Optimum cross-sectional area of first stage diffusion chamber in high pressure buffer chamber The method comprises the following steps: , Inner diameter of first stage diffusion cavity in corresponding high-pressure buffer cavity The method comprises the following steps: ; axial distance of first stage diffusion chamber Is calculated as follows: , wherein: for a half-spread angle of the jet, for a limited sudden spread turbulence, The value range is 0.325 to 0.404, Is a first stage diffusion cavity radius, Is the high pressure buffer chamber inlet radius.
  8. 8. The apparatus of claim 7, wherein the diameter D 2 of the second stage stagnation chamber of the high pressure buffer chamber is designed to satisfy the following equation: , , Diameter of the second stage of the high pressure buffer chamber The value is as follows: , The axial distance H 2 of the second-stage stagnation chamber of the high-pressure buffer chamber satisfies the following conditions: Anti-blocking criterion based on continuity equation to prevent The secondary throttling occurs when the lateral air supply area is smaller than the downstream load area due to the excessively small air supply area, the minimum physical height is set, and the deduction formula is as follows: , wherein: , Is an anti-blocking safety coefficient; , on the premise of meeting the requirement of air supply, the height is high Every 1mm increase, the ineffective dead volume is obviously increased, if With continued increase, the dead volume increases resulting in peak pressure Exponential decay, establishing a volume-pressure sensitivity equation according to an adiabatic state equation Is a derivative of: , wherein: taking 1.3 for the heat insulation index of the fuel gas, In order to increase the dead volume, , The total free volume was designed for this system, for a system with a drug loading of m g: , The set pressure fluctuation threshold should not be lower than 10% of the peak pressure, i.e , From the following components Satisfies the following formula: 。
  9. 9. The apparatus according to claim 8, wherein the outer portion of the high-pressure buffer chamber is designed as an isodiametric columnar structure, and the effective bearing outer diameter is set to And meet the following ; Minimum required outer radius of high pressure buffer chamber Is calculated as follows: by utilizing the theory of a Laemet thick-wall cylinder in solid mechanics, the radial displacement of the thick-wall cylinder under the internal pressure effect: , In the formula, For radial displacement of the inner wall of the high pressure buffer chamber, The peak pressure is designed for the cavity, Is the inner radius of the high pressure buffer chamber; Is the outer radius of the high pressure buffer chamber; modulus of elasticity for the chamber material; Poisson's ratio for the material; combined strain rate definition To meet the requirements of Is inversely derived to obtain the minimum outer radius required by the high-pressure buffer chamber The calculation model of (2) is as follows: 。
  10. 10. use of a device according to any one of claims 1-9 for unmanned aerial vehicle countering, in particular: In the standby state, the ignition component is connected with the net bin component, the flexible rope net is folded and accommodated in the shell, the traction body is arranged in the projectile tube, and the cover plate is tightly matched with the shell to form a seal, so that the device is ensured to have a set starting threshold value; After the detection system of the carrier platform identifies and locks the target unmanned aerial vehicle, a trigger instruction is sent to the device; the black powder in the ignition component is electrically triggered and ignited, and high-temperature and high-pressure gas is instantaneously generated in the powder chamber; when the pressure exceeds the starting threshold formed by tight fit of the cover plate and the shell, 6 traction bodies fly out at high speed along the preset direction of the respective throwing barrel under the pushing of the high-pressure fuel gas in the common cavity; the tail part of each traction body is connected with the corresponding corner of the flexible rope net, the flexible rope net is pulled open while the traction body flies away from the shell, a hexagonal interception net is formed in the air, and winding and capturing are realized for the target unmanned aerial vehicle; after the interception is completed, the independent modularized net bin assembly is replaced, so that the device is restored to a standby state, and the repeated use is realized.

Description

Lightweight common-cavity casting net capturing device Technical Field The invention belongs to the technical field of unmanned aerial vehicle countering, and particularly relates to a lightweight common-cavity casting net capturing device. Background With rapid development and wide application of unmanned aerial vehicle technology, potential safety risks are increasingly highlighted, and the unmanned aerial vehicle has a serious challenge to space domain management and important area protection. Particularly, the unmanned aerial vehicle with the characteristics of low altitude, slow speed and small size is often used for unauthorized flying, approaching reconnaissance, article throwing, even malicious attack and other actions due to low cost, easy acquisition and control, strong maneuverability and difficult effective identification and tracking by the traditional detection means. Such behavior not only disturbs normal aviation order and social activities, but may also directly threaten critical infrastructure, key security targets, and personnel security. Therefore, developing an anti-unmanned aerial vehicle device that is efficient, reliable, and highly adaptable has become a current urgent problem to be solved. At present, unmanned aerial vehicle reaction technology can be mainly divided into two types of hard killing and soft killing. The hard killing technology directly damages or captures the target through physical modes such as missile interception, laser destruction and the like, and the soft killing technology mainly causes the soft killing technology to lose the normal working capacity through interference of communication and navigation links. However, each technology has a certain limitation, so that the comprehensive performance of the current anti-unmanned aerial vehicle device is still to be further improved. In the prior art, the patent name discloses a net capturing type unmanned aerial vehicle countering device (CN 119845096A), which comprises a carrier unmanned aerial vehicle and a net capturing device arranged below a body of the carrier unmanned aerial vehicle, wherein the net capturing device mainly comprises a connecting mechanism, a self-releasing mechanism and a capturing net, the connecting mechanism comprises a connecting ring and a contraction rope penetrating through the edge of the capturing net, and the self-releasing mechanism adsorbs the capturing net through magnet assemblies at two ends of a supporting rod to keep unfolding. The device realizes the expansion suspension of catching the net through magnetic force absorption, after the target unmanned aerial vehicle is plugged in, the magnet is fallen off by utilizing the torsion generated by the rotation of the propeller of the target unmanned aerial vehicle, and the catching net is tightened along the shrinkage rope under the action of gravity, so that the catching is completed and the unmanned aerial vehicle can be stably carried and recovered. Although the prior art realizes stable recovery after capturing through magnetic attraction unfolding and gravity net collecting, the net removing mechanism depends on torsion triggering of a rotor wing of the target unmanned aerial vehicle, so that the adaptability to a high-speed or high-maneuvering target is insufficient, and the whole device provides higher requirements for load distribution and flight stability control of the unmanned aerial vehicle. The patent name discloses an interception unmanned aerial vehicle trapper (CN 221425497U), which mainly comprises a square cylinder shell, an ejection assembly and a trigger assembly, wherein the ejection assembly comprises an ejection rod, an elastic element and an ejection cylinder, the capture net is connected to the top end of the ejection rod, the trigger assembly comprises a cutting part and a driving part, and the cutting action is controlled by a traction rope to release the compressed ejection rod so as to eject the capture net. The prior art adopts a mechanical ejection mode, the ejection distance and the net opening effect of the mechanical ejection mode are limited by the spring performance, and the mechanical ejection mode has insufficient applicability to specific scenes. Disclosure of Invention The invention aims to provide a device for intercepting an unmanned aerial vehicle, which has the advantages of compact structure, light weight, safe use, low manufacturing cost and use cost, and can rapidly spread a flexible rope net by throwing a plurality of traction bodies through high-pressure gas, thereby realizing high-efficiency physical interception on 'low, slow and small' unmanned aerial vehicles. The technical proposal for realizing the aim of the invention is that the lightweight common-cavity casting net capturing device comprises an ignition component and a net bin component which are detachably connected; The net bin assembly comprises a shell, a common cavity cap arranged in the shell, a plurality of throwin