CN113218251A

CN113218251A - Air flying net capturing bomb and working method thereof

Info

Publication number: CN113218251A
Application number: CN202110636444.4A
Authority: CN
Inventors: 白澔烔; 石仲仑; 陈柏屹; 陈金宝; 刘燕斌
Original assignee: Nanjing University of Aeronautics and Astronautics
Current assignee: Nanjing University of Aeronautics and Astronautics
Priority date: 2021-06-08
Filing date: 2021-06-08
Publication date: 2021-08-06
Anticipated expiration: 2041-06-08
Also published as: CN113218251B

Abstract

The invention discloses an air flying net capturing bomb which comprises a net opening capturing device, wherein the net opening capturing device comprises a plurality of traction blocks, a capturing net, a hood shell, a shell sleeved in the direction around an axis, a positioning cylinder and an ejection base plate; a plurality of tooth gaps are uniformly arranged at the front end of the positioning cylinder in the circumferential direction; a flange is arranged on the peripheral surface of the front end of the ejection base plate, a guide part is arranged at the front end of the ejection base plate, and the rear end of the ejection base plate is provided with the screen opening gunpowder; the engine is provided with a programming fuse module to control the ignition of the open-net gunpowder; a plurality of traction blocks are arranged in a circumferential array around the guide part and correspond to the flange, the hood shell is in sliding fit with the shell, the end part of the hood shell is in circumferential fit with the traction blocks, and the capture net is connected with the traction blocks.

Description

Air flying net capturing bomb and working method thereof

Technical Field

The invention relates to the technical field of aviation systems, air attack and defense unmanned system equipment and particularly relates to an air flying net capturing bomb and a working method thereof.

Background

In the field of small unmanned aerial vehicle countermeasures, the mainly adopted unmanned aerial vehicle countermeasures are divided into four measures, namely an interference blocking measure, a direct destroying measure, an interception capturing measure and a trapping control measure. The intercepting and capturing means has the advantages of no damage capturing and high realizability, and can be particularly divided into unmanned plane capturing, flying net capturing and biological capturing.

The fly net capturing means has the advantages of good target universality, capability of intercepting most targets, controllable target falling risk and convenience for target evidence collection. However, the fly net capturing means has high requirements on guiding precision, short acting distance, high operation requirements and low success rate, so that the fly net capturing means is not adopted in large quantity at present.

At present, the fly net capturing means is researched at home and abroad to a certain extent, but a product for large application is not formed yet. For example, DARPA in the united states has evaluated a small air defense concept weapon, in which foam or a mesh enclosure is sprayed from a tubular launcher, the mesh enclosure is woven from conductive carbon fibers, which can cause the communication system of an unmanned aerial vehicle to malfunction, and the foam can wrap an unmanned aerial vehicle, causing the unmanned aerial vehicle to malfunction and fall. The Russian Sky Wall 100 small unmanned aerial vehicle interception system also belongs to the weapons, has an action range of 100m, and comprises a shoulder-carried type launching cylinder, an interception net cover and a parachute, wherein the interception net cover is driven by compressed gas to launch and then forms a large coverage surface in the air to wrap a target unmanned aerial vehicle so as to lose power, and the target unmanned aerial vehicle is landed by the parachute (see: Compan, Huangyun, Zhonghao, State review of the state of development of the foreign unmanned aerial vehicle system [ J ]. flying missile, 2017(9): 24-28.). A net opening capturing device of Tian Net I of a domestic aerospace Changfeng company is characterized in that a fighting part is a flying net with the diameter of 3m, smokeless small equivalent gunpowder is adopted for emission, the range is 400m, and the device is suitable for being used in urban environment (see: Liu super Peak, inverse micro unmanned aerial vehicle technical scheme investigation [ J ] modern defense technology, 2017, 45(4): 17-22.).

Although the cost of the flying net capturing means is reduced compared with that of an accurate guided weapon (see: Liu Dong Wei and other net exhaustion-new attack and defense [ J ] aviation weapons in the unmanned cluster era, 2019, 26(1): 70-75.), the hitting distance is relatively shortened, and the defense efficiency and the expense ratio of the clustered small unmanned aerial vehicle are still high. However, compared with other interception and capture modes, the fly net capture mode still has the advantages of good anti-interference performance, safety, reliability, capability of abundantly countering the unmanned aerial vehicle striking system and the like, and is still a research hotspot for countering the unmanned aerial vehicle.

For this reason, a new technical solution is needed to solve the above technical problems.

Disclosure of Invention

Aiming at the problems of air reverse control, ground-air reverse control and airspace intrusion of a non-cooperative light and small unmanned aerial vehicle of the unmanned aerial vehicle, the invention provides a novel air-to-air net capturing bomb and a working method thereof.

In order to solve the problems, the invention adopts the technical scheme that:

a net-opening capturing device for airborne flying comprises a turbine type rocket engine and a net-opening capturing device connected with the front end of the turbine type rocket engine along an axial direction, wherein the net-opening capturing device comprises a plurality of traction blocks, a capturing net, a hood shell, a programming fuze module, a shell, a positioning barrel and an ejection base plate which are sequentially sleeved around the axial direction; wherein the rear end of the shell is connected with the turbo type rocket engine; a plurality of tooth gaps are uniformly arranged at the front end of the positioning cylinder in the circumferential direction and are positioned in the shell; a flange arranged in a corresponding tooth gap is arranged on the outer side of the ejection base plate, and a guide part is convexly arranged at the axis of the front end of the ejection base plate; the rear end of the ejection base plate is provided with a screen opening powder; the programming fuse module is arranged at the front end of the turborocket engine to control the ignition of the net opening gunpowder; a plurality of the traction block is around the guide part is that circumference array arranges and corresponds the flange sets up, hood shell rear end with shell front end sliding fit just rear end tip with traction block front end circumference sealing fit, it is a plurality of to catch the net traction block just accept in the hood shell.

Furthermore, the programming fuse module is provided with a delay circuit, and the delay circuit comprises a timer chip, a capacitor, a power supply battery and a resistor; the timer chip is connected with two ends of the capacitor and provided with an ignition signal output end; before the turborocket engine is launched from a launching platform, the programming fuse module is electrically communicated with a main control module on the launching platform, and the main control module is used for providing a time signal for the programming fuse module; the main control module is provided with a digital-to-analog converter for converting the time signal into an output voltage; the main control module is provided with a signal output end for outputting the output voltage; the two ends of the capacitor are respectively connected to the signal output end, and the timer chip is used for charging the capacitor to the output voltage; after the turbo rocket engine is launched, the main control module is disconnected with the programming fuse module, the timer chip is used for charging the capacitor to a trigger voltage, the time delay of the timer chip is finished, and the ignition signal output end is used for outputting the ignition trigger signal and controlling the ignition of the grid-opening gunpowder.

Further, evenly be provided with a plurality of tooth portions in the front end circumference of a location section of thick bamboo, tooth portion encircles the axis direction is that the circumference array arranges and two liang of intervals set up, the tooth seam encircles the axis direction is that the circumference array arranges and two liang of intervals set up, tooth portion with the tooth seam sets up in turn in proper order.

Further, the flange comprises a plurality of recesses and a plurality of protrusions which are arranged in an array along the circumferential direction of the flange, and the recesses and the protrusions are sequentially and alternately arranged; before the net-opening gunpowder is ignited, the protrusions are correspondingly clamped and embedded in the tooth gaps one by one, and the outer surfaces of the recesses are correspondingly contacted and matched with the inner surfaces of the tooth parts one by one.

Furthermore, a convex block is convexly arranged on the outer surface of each traction block, and before the screening gunpowder is ignited, the convex blocks correspond to the protrusions one by one and are in limit fit with the corresponding tooth gaps and then are in contact fit with the inner peripheral surface of the shell.

Furthermore, a pressing plate positioned on the axis and a spring with two ends respectively connected with the blast cap shell and the pressing plate are arranged in the blast cap shell; the catching net comprises a main body and a plurality of connecting parts connected with the main body, the main body is folded and is positioned at the rear end of the pressing plate, and each connecting part is arranged in one traction block; before the hood housing is detached from the housing, the spring is in a compressed state; after the blast cap shell is separated from the shell, the spring drives the pressing plate to pop out the catching net.

Furthermore, the front end of the turbine rocket engine is provided with a plug, and the inner circumferential surface of the rear end of the shell is fixedly connected with the outer circumferential surface of the plug; the positioning cylinder is fixedly arranged in the shell; the flange and the guide part are integrally connected with the ejection base plate; the outer peripheral surface of the rear end of the hood outer shell is in sliding fit with the inner peripheral surface of the front end of the outer shell; the number of the traction blocks and the number of the tooth gaps are both 6.

The air flying net capturing bomb provided by the invention has the beneficial effects that: the method is designed aiming at the problem of airspace intrusion of an aerial reverse system, an aerial reverse system and a non-cooperative light and small unmanned aerial vehicle of the unmanned aerial vehicle, the aerial fly net capture bomb comprises a net opening capture device and a turbo-type rocket engine, the turbo-type rocket engine provides propulsion power for the net opening capture device to enable the net opening capture device to fly, the characteristic of high-speed spinning of the turbo-type rocket engine is utilized, meanwhile, the turbo-type rocket engine is utilized as initial kinetic energy obtained by rocket power to provide net opening power for the net opening capture device, the net opening capture device realizes quick and efficient net opening based on the structural layout of traction blocks of the net opening capture device, and the net opening capture device realizes inertia net opening and winding capture in a large range according to the inertia principle, for example, the aerial small and medium unmanned aerial vehicles realize capture; the turbo rocket engine is used as a rocket power system, so that the effective range of direct aiming acquisition weapons is improved.

The air flying net capturing bomb is designed based on the advantages of low launching condition, small disturbance on an outer trajectory, simple structure, low production cost and the like of the conventional air flying net capturing bomb, and the defects of high cost and short hitting distance of the existing flying net capturing means are overcome; the invention can complete the capture and reaction of the non-cooperative light and small unmanned aerial vehicle in the sight distance range, can be loaded on an air-based platform or a land-based platform or carried by personnel for emission, has low cost of related structural materials, high portability, flexible loading and high task reliability, and has wide application prospect for air defense and air defense confrontation and urban airspace management; the unmanned aerial vehicle anti-braking and anti-air reconnaissance device has the characteristics of low emission condition, good flight stability, simple structure, low cost, high task reliability and convenience in loading, and has certain reference significance for the anti-braking and anti-air reconnaissance work of the unmanned aerial vehicle based on the fly net capture mode.

The invention also provides a working method suitable for the airborne flying net capturing bomb, wherein the airborne flying net capturing bomb comprises a turbo-type rocket engine and a net opening capturing device which is connected with the turbo-type rocket engine along an axial direction, and the working method comprises the following steps:

after the turbo-type rocket engine is launched and before the net opening capturing device works, the turbo-type rocket engine provides translational thrust along an axial direction and spinning power around the axial direction for the net opening capturing device; the open-net capturing device comprises a plurality of traction blocks, a capturing net, a hood shell, a programming fuze module, a shell, a positioning cylinder and an ejection base plate, wherein the shell, the positioning cylinder and the ejection base plate are sequentially sleeved around the axis direction; the ejection base plate is internally provided with screen opening gunpowder;

the programming fuse module outputs an ignition trigger signal and controls the ignition of the net opening gunpowder;

the net opening powder is ignited to generate gas and push the net opening catching device to start working, the ejection base plate, the traction block, the catching net and the hood shell move forwards until the traction block is separated from the end part of the front end of the shell, the traction block moves forwards through translational thrust in the axis direction, and the traction block winds the self-rotating power in the axis direction to pull the catching net to open the net along the tangential direction of a self-rotating track.

Further, before the step of operating the open net capture device after the turbo rocket engine is launched, the method further comprises the following steps:

before the turbo rocket engine is launched, the programming fuse module is electrically communicated with a main control module on the launching platform, the main control module inputs a time signal to the programming fuse module, the main control module converts the time signal into output voltage through a digital-to-analog converter, and the main control module outputs the output voltage to a signal output end; the programming fuse module is provided with a time delay circuit, the time delay circuit comprises a timer chip, a capacitor, a power supply battery and a resistor, the two ends of the capacitor are connected with the timer chip, the two ends of the capacitor are respectively connected with the signal output end, and the timer chip is provided with an ignition signal output end.

Further, in the step of outputting an ignition trigger signal by the programming fuse module and controlling the ignition of the grid-opening powder, the method further comprises the following steps:

the timer chip charges the voltage at the two ends of the capacitor to the output voltage;

after the turbo rocket engine is launched, the main control module is disconnected from the programming fuse module, and the timer chip charges the capacitor to a trigger voltage;

and after the time delay of the timer chip is finished, outputting an ignition trigger signal through the ignition signal output end and controlling the ignition of the grid-opening gunpowder.

According to the working method, the pure digital circuit is used as the programming fuse module of the delay circuit, so that the delay unlocking of the open-net capturing device can be completed, the open-net time precision of the open-net capturing device is improved, the design difficulty and the production cost of the air flying net capturing bomb are reduced, compared with a mechanical fuse, the weight of the fuse is reduced, the flying dry weight of the air flying net capturing bomb is further reduced, and the portability and the task execution reliability are improved; the visual aiming system of the loading platform can be matched to quickly acquire the target position and position information.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.

FIG. 1a is a schematic structural diagram of an air-fly net capture bomb according to the invention;

FIG. 1b is a schematic view in the direction A of FIG. 1 a;

fig. 2 is an exploded view of the open net capture device for an airborne fly net capture bomb shown in fig. 1;

FIG. 3 is a schematic half-section view of the open net capture apparatus shown in FIG. 2;

FIG. 3a is a schematic cross-sectional view in the direction A-A of the open-net capture device shown in FIG. 3;

FIG. 3B is a schematic cross-sectional view of the open-net capture device shown in FIG. 3 in the direction B-B;

FIG. 3C is a schematic cross-sectional view of the open net capture device shown in FIG. 3 in the direction C-C;

FIG. 4a is a schematic structural view of the open-net capture device of the present invention with the capture net in an expanded state;

FIG. 4b is a schematic view of the catching net shown in FIG. 4a in a folded state in cooperation with a traction block of the open net catching device;

fig. 5 is a schematic circuit diagram of a programming fuze module in a second cavity (programming fuze capsule) of the open-net capture device shown in fig. 3;

FIG. 6 is a schematic half-section view of the rocket motor of the turbo type for airborne fly net capture of projectiles shown in FIG. 1;

FIG. 7a is a schematic structural view of a nozzle of the turborocket engine shown in FIG. 6;

FIG. 7b is a schematic cross-sectional view of the nozzle shown in FIG. 7a taken in the direction E-E;

FIG. 7c is a schematic cross-sectional view of the nozzle of FIG. 7a taken in the direction F-F;

FIG. 8a is a state diagram of the open net capture apparatus of the present invention when not in operation;

fig. 8b is a state diagram of the open net capture apparatus shown in fig. 3 in a first operating mode;

fig. 8c is a state diagram of the open net capture apparatus shown in fig. 3 in the second operation mode;

fig. 8d is a state diagram of the open net capturing apparatus shown in fig. 3 in the third operation mode;

FIG. 8e is a diagram showing the state of the present invention in which the net-capturing missile spins at high speed around the missile axis during flying;

FIG. 9 is a flow chart of the operation of the present invention for capturing an air-fly net;

fig. 10 is a flowchart of the operation of the programming fuze module shown in fig. 5.

Detailed Description

The invention is further described below with reference to the figures and examples.

Please refer to fig. 1a, fig. 1b, fig. 2, and fig. 3; the invention provides an air-to-air net capturing bomb, which is provided with a bomb shaft, and flies along the bomb shaft; the pair of airborne net-capturing bombs comprises a net-opening capturing device 100 and a turbo-type rocket engine 200, wherein the net-opening capturing device 100 is connected to the turbo-type rocket engine 200 along an axis 110, and the axis 110 is coincident with a bomb axis of the pair of airborne net-capturing bombs. In the present invention, the turbo rocket motor 200 is disposed on a launching platform and used to provide turbo rocket power for the open net capture device 100, the turbo-rocket engine 200 is a self-rotating structural member, and the turbo-rocket engine 200 is enabled to spin around the missile axis at a high speed during flying by utilizing the self-rotating launching function of the turbo-rocket engine in the prior art, wherein the turbo rocket engine 200 is fixedly connected with the open net capture device 100, so as to form the airborne rocket projectile, namely the rocket projectile, the spinning of the turbo rocket engine 200 can drive the open net capture device 100 and the airborne rocket projectile to spin, the turbo rocket engine is used for providing translational thrust along the axis 110 and spinning power around the axis 110 for the open net capture device 100 after being launched.

It should be noted that, in the embodiment of the present invention, the flight end point direction of the pair of airborne flynet captured bombs is defined as the front end, and the flight start point direction of the pair of airborne flynet captured bombs is defined as the rear end; the radial direction of the pair of airborne flynet capture projectiles is defined as any direction perpendicular to the axis 110.

In the embodiment of the invention, as shown in fig. 2 and 3, the front end of the turbo-rocket engine 200 is provided with a plug 220, the open-net capture device 100 is arranged at the front end of the plug 220, and the open-net capture device 100 comprises an ejection mechanism, a plurality of traction blocks 5, a capture net 500 (shown in fig. 4 a), a programming fuze module 300 and a hood housing 1. Before the turbo rocket engine 200 is launched, the plurality of traction blocks 5 are movably adapted to the front end of the ejection mechanism, the open-net gunpowder is arranged in the rear end of the ejection mechanism, the programming fuse module 300 is arranged in the front end of the plug 220 to control the ignition of the open-net gunpowder, and the catching net 500 is connected with the plurality of traction blocks 5 and is accommodated in the hood housing 1.

As shown in fig. 3, the ejection mechanism includes a housing 8, a positioning cylinder 7, and an ejection pad 6, which are sequentially sleeved around the axis 110. Specifically, the rear end of the housing 8 is fixedly connected with the front end of the plug 220; the positioning cylinder 7 is positioned inside the outer shell 8, the outer peripheral surface of the positioning cylinder 7 is matched with the inner peripheral surface of the outer shell 8, and the rear end of the positioning cylinder 7 is opposite to the front end of the plug 220; the ejection base plate 6 is fitted in the positioning cylinder 7.

With reference to fig. 2 and fig. 3, after the rear end of the ejection cushion plate 6 is fitted inside the positioning cylinder 7, the rear end of the ejection cushion plate 6 is opposite to the front end of the plug 220 connected to the rear end of the housing 8, and the rear end of the ejection cushion plate 6 is provided with an open-mesh propellant chamber 10 for installing and placing the open-mesh propellant, wherein the open-mesh propellant chamber 10 is a cavity. And a programming fuse cabin 11 is formed between the rear end part of the ejection base plate 6 and the front end of the plug 220 in an enclosing manner, the programming fuse cabin 11 is a cavity and is communicated with the cavity of the grid-opening explosive cabin 10, the programming fuse cabin 11 is used for placing the programming fuse module 300, and the programming fuse module 300 is used for controlling the grid-opening explosive arranged in the grid-opening explosive cabin 10 to be ignited in a delayed manner.

Referring to fig. 3, the hood housing 1 has a tip cavity, a pressing plate 3 located on the axis 110 and a spring 2 having two ends connected to the hood housing and the pressing plate, respectively, are disposed in the tip cavity; the rear end of the blast cap shell 1 is used for being in circumferential sliding fit with the front end of the shell 8, and the pressing plate 3 is positioned in the blast cap shell 1 and elastically moves between the shell 8 and the blast cap shell 1; the plug 220, the shell 8, the positioning barrel 7, the ejection base plate 6, the traction block 5, the hood shell 1, the spring 2 and the pressing plate 3 are coaxially arranged around the axis 110.

Referring to fig. 4a and 4b, the catching net 500 is disposed between the traction block 5 and the pressing plate 3, the catching net 500 is connected to the traction block 5, and the traction block 5 is used for weighting the catching net 500 and drawing the catching net 500.

In a particularly preferred embodiment of the present invention, referring to fig. 3a and 3b, and continuing to fig. 3, a plurality of tooth gaps 70 are uniformly arranged at the front end of the positioning cylinder 7 in the circumferential direction; a flange 60 is arranged on the outer peripheral surface of the front end of the ejection base plate 6, and the flange 60 is used for being in limit fit with the tooth gaps 70 of the positioning cylinder 7; a guide part 61 is arranged at the front end of the ejection base plate 6 and at the position of the axis 110, and the guide part 61 is arranged around the axis 110 and protrudes out of the end face of the front end of the ejection base plate 6; before the ignition of the mesh opening gunpowder, the plurality of traction blocks 5 are arranged in a circumferential array around the guide part 61 and are arranged corresponding to the flange 60, the traction blocks 5 and the flange 60 are arranged in a limiting manner after the tooth gaps 70 and are in contact fit with the inner peripheral surface of the shell 8, and the rear end of the blast cap shell 1 is in sliding fit with the front end of the shell 8.

Specifically, the positioning cylinder 7 is a cylindrical structural member, the tooth gaps 70 are formed on the cylinder wall of the front end of the positioning cylinder 7, each tooth gap 70 is recessed from the end portion of the front end of the positioning cylinder 7 toward the rear end and extends to a certain position on the cylinder wall of the positioning cylinder 7, the tooth gap 70 does not penetrate through the cylinder wall of the positioning cylinder 7, the recessed extending direction of the tooth gap 70 is the same as the direction of the axis 110, and the tooth gap 70 is equivalent to an arc-shaped groove. Further, a plurality of the tooth gaps 70 are all the same structural members. That is, as shown in fig. 2, the depth lengths of the plurality of slits 70 in the direction along the axis 110 are the same and the depth length value is smaller than the length value of the positioning cylinder 7 in the direction along the axis 110; as shown in fig. 3a and 3b, the plurality of slits 70 have the same cross-sectional shape and size in a certain radial direction.

Further, as shown in fig. 3, 3a, and 3b, a plurality of tooth portions 71 are uniformly circumferentially disposed at the front end of the positioning cylinder 7, the tooth portions 71 are circumferentially arrayed and arranged at intervals in pairs around the axis 110, the tooth gaps 70 are circumferentially arrayed and arranged at intervals in pairs around the axis 110, and the tooth portions 71 and the tooth gaps 70 are sequentially and alternately disposed to form the positioning portion. The guide part 61, the flange 60, tooth part 71 and the shell 8 encloses to set up and forms a location chamber, works as a plurality of the pull block 5 encircles the guide part 61 is array adaptation in the location intracavity, the guide part 61 and tooth part 71 are used for doing for the pull block 5 leads, the flange 60 is used for to the pull block 5 plays spacing, support, ejection effect.

As shown in fig. 2, 3a and 3b, any two adjacent slots 70 form a tooth portion 71 at an interval, and the tooth portion 71 corresponds to an arc tile. Further, the plurality of teeth 71 are all the same structural member. Correspondingly, the lengths of the plurality of teeth 71 in the direction along the axis 110 are the same, and the length of the length is equal to the depth length of the tooth gap 70; as shown in fig. 3a and 3b, the cross-sectional shapes and sizes of the plurality of portions 71 in a certain radial direction are the same.

With reference to fig. 2, 3a, and 3b, the flange 60 includes a plurality of recesses 62 and a plurality of protrusions 63 respectively disposed on the front end of the ejection pad 6, the recesses 62 are arranged in a circumferential array around the axis 110, the protrusions 63 are arranged in a circumferential array around the axis 110, and the recesses 62 and the protrusions 63 are alternately disposed to form the flange 60. A projection 63 for snap-fitting into a slot 70, and a recess 62 having an outer surface for contact engagement with the inner surface of the housing 8; when the flange 60 is fitted into the tooth gaps 70 of the positioning cylinder 7, the protrusions 63 are arranged in one-to-one correspondence with the tooth gaps 70, and the outer surfaces of the protrusions 63 are in surface contact fit with the inner surface of the housing 8.

As shown in fig. 3a and 3b, the traction blocks 5 are axisymmetric structural members, and the number of the traction blocks 5 is the same as the number of the slots 70. A lug 52 is arranged on the outer surface of each traction block 5, when a plurality of traction blocks 5 are fitted in the positioning cavity, the lug 52 extends towards the direction away from the traction block 5 along the direction perpendicular to the axis 110, any lug 52 is used for being fitted in one tooth gap 70 and correspondingly arranged on one protrusion 63 of the flange 60, and the traction block 5 and the protrusion 63 of the flange 60 are limited and arranged behind the tooth gap 70 and are in contact fit with the inner peripheral surface of the shell 8.

The traction block 5 is provided with a groove 53 between two adjacent lugs 52, and one groove 53 is correspondingly matched with the inner surface of one tooth part 71; the convex blocks 52 and the concave grooves 53 are alternately arranged; and when the protrusions 52 are fitted on the protrusions 63 in a one-to-one correspondence manner, the traction block 5, the ejection pad 6 and the positioning cylinder 7 are coaxial, and the traction block 5 and the ejection pad 6 can only move forward relative to the positioning cylinder 7, but cannot rotate around the axis 110.

In a preferred embodiment, the inner circumferential surface of the rear end of the housing 8 is fixedly connected with the outer circumferential surface of the front end of the plug 220; the positioning cylinder 7 is fixedly arranged on the shell 8, and the positioning cylinder 7 is integrally connected with the shell 8; the tooth part 71 is integrally connected with the positioning cylinder 7; the flange 60 and the guide part 61 are integrally connected with the ejection cushion plate 6, and the recess 62 and the protrusion 63 are integrally connected to form the flange 60; the projection 52 is integrally connected to the traction block 5.

As shown in fig. 2 and fig. 3, the hood housing 1, the spring 2, and the pressing plate 3 are sequentially and fixedly connected, two ends of the spring 2 are respectively and fixedly connected between the inside of the tip cavity and the pressing plate 3, and the pressing plate 3 is perpendicular to the axis 110 and can freely and elastically move along the axis 110 relative to the hood housing 1. The rear end of the hood housing 1 is circumferentially matched with the front end of the housing 8, further, the outer circumferential surface of the rear end of the hood housing 1 is matched with the inner circumferential surface of the front end of the housing 8, and the hood housing 1 is slidable relative to the housing 8 along the axis 110 direction; and, the rear end of the hood housing 1 is in sealing fit with the front end face of the traction block 5 through a seal ring 4.

Referring to fig. 4a and 4b, the catching net 500 includes a main body 510 and a plurality of connecting parts 520 integrally connected to the main body 510. In this embodiment, each of the pulling blocks 5 is provided with a through hole 51 along the direction of the axis 110, and the number of the pulling blocks 5, the through holes 51, the connecting portions 520, the tooth gaps 70, the tooth portions 71, the protrusions 63, and the recesses 62 is 6. The catching net 500 is a hexagonal structure, six vertexes of the catching net 500 are respectively fixed on six traction blocks 5, after the catching net 500 is folded, the main body 510 is filled in a tip cavity of the hood shell 1, specifically, the main body 510 is accommodated in the tip cavity and is located in an area between the rear end of the pressing plate 3 and the traction blocks 5, the pressing plate 3 is pushed upwards by the catching net 500, the spring 2 is compressed, and the spring 2 is in a compressed state to store energy for the open net catching device 100; and each of the connection parts 520 of the catching net 500 is connected and received in the through hole 51 of the traction block 5.

Preferably, the front end of hood shell 1 has arc portion, arc portion has a diameter and is 5.5 mm's calotte, hood shell 1 the material of clamp plate 2 is resin material, sealing washer 4 is the rubber packing ring, catch net 500 for the nylon fine rule, the line footpath is 0.8mm, the hexagon length of side after the expansion is 1m, the material of traction block 5 is the brass, launch backing plate 6 a location section of thick bamboo 7 the material of shell 8 is high performance nylon.

Referring to fig. 5, before the turbo rocket motor 200 is launched from a launching platform, the programming fuse module 300 is electrically connected to a main control module 400 on the launching platform, the main control module 400 forms a path with the programming fuse module 300 through a wire or an elastic contact, the main control module 400 is not a component of the programming fuse module 300, and the main control module 400 is used for inputting a time signal to the programming fuse module 300; as shown in fig. 5, the main control module 400 has a digital-to-analog converter (DAC)410 for converting the time signal into an output voltage, and the main control module 400 has a signal output terminal 401 for outputting the output voltage. Referring to fig. 3 and 3c, a fuse slot 2202 is formed on the front end of the plug 220, and the programming fuse module 300 is connected to the signal output terminal 401 through a wire passing through the fuse slot 2202 and receives the output voltage.

As shown in fig. 5, the programming fuse module 300 has a delay circuit, which is a peripheral rc circuit, the delay circuit comprises a timer chip 310, a power supply battery, a resistor 322 and a capacitor 323, the power supply battery is provided with a positive pole and a negative pole, the positive pole of the fuze power supply battery is connected to a VCC (power supply voltage) end, the negative pole of the power supply battery is connected to the GND (ground) terminal, the timer chip 310 is connected to both ends of the capacitor 323, the capacitor 323 is connected to the signal output terminal 401 at two ends, the programming fuze module 300 further has an ignition signal output terminal (OUT terminal) 324, the OUT terminal 324 is connected to the timer chip 310, and the OUT terminal 324 is used for outputting an ignition trigger signal and controlling ignition of the grid-opening powder in the grid-opening explosive chamber 10, specifically, the ignition of the screened gunpowder in the screened gunpowder chamber 10 through the ignition head is controlled by an electronic switch (not shown).

Referring to fig. 6, the turbo rocket engine 200 is a light-duty turbo rocket engine, and as shown in fig. 6, the turbo rocket engine 200 includes an engine case 210, a plug 220, a nozzle 230, a fuel layer 240, a coating layer 250, and a combustion chamber 260, all of which are disposed around the axis 110.

As shown in fig. 6, the engine housing 210 is an elongated tubular hollow structure, and the engine housing 210 is also referred to as a launcher; the plug 220 is disposed at a front end of the engine housing 210, and the plug 220 is fastened to the engine housing 210 by bolts (not shown) disposed laterally to the engine housing 210; the nozzle 230 is disposed at the rear end of the engine housing 210, and the nozzle 230 is fastened to the engine housing 210 by bolts (not shown) disposed laterally with respect to the engine housing 210; the fuel layer 240 is circumferentially disposed inside the engine housing 210 and is disposed along a longitudinal direction of the engine housing 210, and the fuel layer 240 is used for loading rocket fuel, specifically rocket propellant; the fuel layer 240 is substantially cylindrical, and the fuel layer 240 has a cavity as a combustion chamber 260 on the axis 110, i.e. the turbo-rocket engine 200 has the combustion chamber 260 at the position of the axis 110; the cladding 250 is circumferentially disposed between an inner circumferential surface of the engine case 210 and an outer circumferential surface of the fuel bed 240, and the cladding 250 is for cladding the fuel bed 240.

In addition, the plug 220 serves as a front centering portion of the empty flynet capturing bomb, the nozzle 230 serves as a rear centering portion of the empty flynet capturing bomb, and the plug 220 and the nozzle 230 are attached to the inner wall of the engine housing 210, namely the launcher, so that a centering effect is achieved, and initial disturbance is reduced.

Referring to fig. 6, the rear end of the plug 220 has a receiving cavity, the receiving cavity is used as an ignition cartridge 2201 of the turbine rocket engine 200, the ignition cartridge 2201 is an ignition device of the turbine rocket engine 200, an ignition charge is contained in the ignition cartridge 2201, and the turbine rocket engine 200 further has an ignition circuit (not shown) for controlling ignition of the ignition charge in the ignition cartridge 2201; specifically, the ignition circuit is configured to output an ignition signal to the ignition medicine box 2201, and the ignition medicine box 2201 has an ignition tube and ignites the ignition medicine through the ignition tube according to the ignition signal. The ignition charge contained in the ignition cartridge 2201 ignites and produces a large amount of hot combustion gases and molten material as a fuel product that enters the engine combustion chamber 260 and ignites the rocket propellant contained in the fuel bed 240; after the ignition powder contained in the ignition powder box 2201 is ignited for about 100ms to 200ms, the pressure in the combustion chamber 260 reaches a threshold value, the threshold value is a designed ignition pressure, and the turbo-rocket engine 200 starts to work and is launched from the launching platform.

Referring to fig. 7a, 7b and 7c, the nozzle 230 of the turbo-rocket engine 200 is embodied as a turbo-rocket engine nozzle, i.e. a turbo-nozzle. As shown in fig. 7a, the nozzle 230 has a nozzle body 2300 and 5 nozzle holes 2301 disposed on the nozzle body 2300, as shown in fig. 7b, each nozzle hole 2301 is a through pipe, each nozzle hole 2301 is disposed obliquely, each nozzle hole 2301 has a certain inclination angle with respect to the axis 110, which may also be referred to as an oblique angle, and is capable of providing a spin torque to the airborne flyer projectiles (also referred to as rocket projectiles) while pushing the airborne flyer projectiles (also referred to as rocket projectiles) to advance; as shown in fig. 7c, each of the injection holes 2301 has a throat 2302, the throat 2302 is defined as the minimum diameter of the injection hole 2301, wherein the throat 2302 is also inclined, and a throat gasket 2303 is disposed at the throat 2302 of each of the injection holes 2301.

Thus, after the ignition powder in the ignition cartridge 2201 is ignited and the turbo-rocket engine 200 starts to operate, the injection holes 2301 of the injection nozzle 230 inject high-speed airflow, and generate a propelling force in the direction of the axis 110 to push the pair of airborne trapping bombs (i.e. rocket bombs) to advance, and simultaneously generate a rolling torque to make the pair of airborne trapping bombs start to spin for providing the propelling power and the spinning power for the open-net trapping device 100.

Preferably, the inclined angle of the injection holes 2301 is 17 °, the diameter of the single throat 2302 is 3.2mm, the length is 7mm, the expansion ratio is 7.7, the half angle of the expansion section is 12.5 °, the convergence ratio is 7.5, and the half angle of the convergence section is 25 °. The material of the nozzle main body 2300 is a phenolic composite material, the material of the throat insert 2303 is an ablation-resistant material, and the material of the throat insert 2303 is a stainless steel capillary.

Preferably, the turborocket engine 200 has a diameter of 37mm, a length of 160mm, a total mass of 240g, a rocket fuel mass of 100g loaded by the fuel layer 240, a working chamber pressure in the fuel chamber 260 of the turborocket engine 200, i.e., a designed ignition pressure of 6.8MPa, an operating time, i.e., a time from ignition of the ignition charge in the ignition charge case 2201 to start of the turborocket engine 200, of 0.5S, and a total thrust of 200 ns; the engine housing 210 is made of a light material, preferably an aluminum alloy, and further is a 6065-T3 aluminum alloy; the plug 220 and the nozzle 230 are made of phenolic composite materials, and the rocket fuel loaded in the fuel layer 240 is epoxy composite propellant.

Preferably, the diameter of the pair of flying net capturing bullets, that is, the diameter of the turbine rocket bullets is 37mm, the length of the pair of flying net capturing bullets is 290mm, the total mass is about 370g, the inertial flying mass is 270g, the highest flying speed is 500m/s, the spinning speed is 11000rad/s, and the maximum ballistic height is 2m, and the range of the pair of flying net capturing bullets can reach 600 m.

In the embodiment of the present invention, about 0.5s after the ignition charge in the ignition charge box 2201 of the turbo-type rocket engine 200 is ignited, the turbo-type rocket engine 200 starts to operate, the rocket propellant contained in the fuel layer 240 is burned out, the pair of empty flying net trapped projectiles, that is, the rocket projectiles enter an inertial flight state, at this time, the rocket projectiles are about 150m away from the launch point, the flight speed is about 1.7Ma, the rotation speed is about 11000r/min, and both the flight speed and the rotation speed reach the highest.

The invention further provides a working method of the airborne flying net capturing bomb, which comprises a turbo-type rocket engine 200 and a net-opening capturing device 100 connected with the turbo-type rocket engine 200 along an axis 110 direction, and referring to fig. 9, the working method comprises the following steps:

s01, after the turbo rocket engine 200 is launched from the launching platform and before the open net capture device 100 works, the turbo rocket engine 200 provides translational thrust along an axis 110 direction and spinning power around the axis 110 direction for the open net capture device 100; the open-net capturing device comprises a plurality of traction blocks 5, a capturing net 500, a hood shell 1, a programming fuze module 300, a shell 8, a positioning cylinder 7 and an ejection base plate 6 which are sequentially sleeved around the axis 110, wherein open-net gunpowder is arranged in the ejection base plate 6;

the plurality of traction blocks 5 are adapted between the shell 8 and the positioning cylinder 7 around the axis 110 direction and are correspondingly arranged at the front end of the ejection base plate 6, the rear end of the hood shell 1 is in sliding fit with the front end of the shell 8, the end part of the rear end is in circumferential fit with the front end of the traction block 5, and the catching net 500 is connected with the plurality of traction blocks 5 and is accommodated in the hood shell 1;

before this step, that is, after the turbo rocket engine 200 is launched from the launching platform and before the open-net capturing device 100 is operated, the method further includes the steps of:

s001: before the turbo rocket engine 200 is launched, the programming fuse module 300 is electrically connected to a main control module 400 on the launching platform, the main control module 400 inputs a time signal to the programming fuse module 300, the main control module 400 converts the time signal into an output voltage through a digital-to-analog converter 410, and the main control module 400 outputs the output voltage to a signal output end 401; the output voltage is specifically the voltage V required by the programming fuze module 300 for time delay₀I.e. the output voltage is V₀；

In this step, please refer to fig. 8 a; as shown in fig. 8a, after the turbo rocket engine 200 is launched, when the empty captured projectile flies normally, and the open net capture device 100 is in a non-operating state, the positioning cylinder 7 of the open net capture device 100 positions the ejection base plate 6 and the traction block 5 through the tooth gaps 70, so that the hood 110 and the housing 8 are tightly fitted, and the internal structural components of the open net capture device 100 do not move relative to each other and spin around the projectile axis, i.e., the axis 110.

S02: the programming fuse module 300 outputs an ignition trigger signal to control the ignition of the grid-opening gunpowder;

in the step S02, that is, in the step of the programming fuse module 300 outputting an ignition trigger signal to control the ignition of the grid-opening powder, please refer to fig. 10, the method further includes the following steps:

step S21: the timer chip 310 charges the voltage across the capacitor 323 to the output voltage;

in this embodiment, the programming fuse module 300 controls the ignition of the pyrotechnic composition, the programming fuse module 300 has a delay circuit, the delay circuit includes a timer chip 310, a capacitor 323, a power supply battery (not shown), and a resistor 322, two ends of the capacitor 323 are connected to the timer chip 310, two ends of the capacitor 323 are respectively connected to the signal output terminal 401, and the timer chip 310 has an ignition signal output terminal 324;

step S22: after the turbo rocket engine 200 is launched, the main control module 400 is disconnected from the programming fuze module 300, and the timer chip 310 charges the capacitor 323 to a trigger voltage;

specifically, the turbo-rocket engine 200 is ignited by another engine ignition circuit on the launching platform, the turbo-rocket engine 200 starts to work, the air flying net trapping projectile (also called rocket projectile) flies away from the launching platform, and the main control module 400 is disconnected from the programming fuze module 300; the timer chip 310 is used for charging the capacitor 323 to a trigger voltage V₁And the timer chip 310 finishes delaying, the trigger voltage V₁For the withstand voltage of the capacitor 323, the charging process duration is the delay duration T of the programming fuze module 300, and the delay duration T passes through the trigger voltage V₁And the output voltage V₀The difference value of (A) is directly controlled;

step S23: after the time delay of the timer chip 310 is finished, an ignition trigger signal is output through the ignition signal output end 324 and the ignition of the grid-opening gunpowder is controlled;

specifically, the voltage across the capacitor 323 reaches the trigger voltage V₁After the rear delay is finished, the OUT terminal 324 outputs an ignition trigger signal, and the ignition trigger signal output by the OUT terminal 324 controls an ignition head to ignite the grid-opening powder contained in the grid-opening powder capsule 10 through an electronic switch (not shown), so that the grid-opening capturing device 100 starts to work;

in this embodiment, the longest delay time T of the delay circuit is 1.1RC, where R is the resistance of the resistor 322 and C is the capacitance of the capacitor 323. Preferably, the timer chip 310 is NE555, and the voltage of the power supply battery is 5V, that is, the output voltage V₀The resistor 322 is a 0603 chip resistor, and the capacitor 323 has a withstand voltage of 16V, that is, the trigger voltage V is 5V₁The delay precision of the delay circuit is 10ms when the voltage is 16V.

S03, after the net opening gunpowder is ignited, the net opening catching device 100 starts to work, the ejection backing plate 6, the traction block 5, the catching net 500 and the hood shell 1 move forwards until the traction block 5 is separated from the front end of the shell 8, the traction block 5 moves forwards through translational thrust in the direction of the axis 110, and the catching net 500 is pulled to open the net by the self-rotating power of the traction block 5 around the direction of the axis 110 in the tangential direction of the self-rotating track.

In step S03, please refer to fig. 8b, 8c, 8d and 8 e; at the moment when the OUT terminal 324 of the programming fuse module 300 outputs an ignition trigger signal, ignition of the grid-opening gunpowder contained in the grid-opening gunpowder chamber 10 is controlled, and the grid-opening capturing device 100 starts to work; as shown in fig. 8b, the ignited charge generates a large amount of high-temperature and high-pressure gas and is used to push the ejection plate 6 to move forward relative to the slits 70 of the positioning cylinder 7, and at the same time, the gas expands the cavity of the charge chamber 10 at the rear end of the ejection plate 6, but the flange 60 of the ejection plate 6 is not separated from the slits 70 of the positioning cylinder 7 and the flange 60 abuts against the teeth 71 and the inner circumferential surface of the housing 8 to have airtightness, and the ejection plate 6 moves forward and simultaneously pushes the traction block 5, the capture net 500 and the hood housing 1 at the front end thereof to move forward.

In step S03, the ejector pad 6 moves forward, and when the end of the rear end of the ejector pad 6 is separated from the bottom end of the tooth gap 70 of the positioning cylinder 7, the ignited gas is rushed into the gap between the outer shell 8 and the rear end of the hood outer shell 1. As shown in fig. 8c, since the close fit between the hood housing 1 and the housing 8 is achieved and the ignited gas pushes the ejector pad 6, the traction block 5, the catching net 500 and the hood 1 to move forward, the traction block 5 generates a great pressure on the rear end of the hood housing 1, so that the sealing gasket 4 disposed between the hood housing 1 and the traction block 5 is compressed, the ignited gas neither gushes into the tip cavity of the hood housing 1 nor overflows from the housing 8 to the outside, and the ejector pad 6, the traction block 5, the catching net 500 and the hood 1 will continue to move forward.

In step S03, when the rear end of the hood outer housing 1 is separated from the front end of the housing 8, the ignited gas escapes from the inside of the open net capture device 100 toward the outside, and the ejector pad 6, the drag block 5, the capture net 500, and the hood 110 continue to move forward due to inertia.

In step S03, as shown in fig. 8d, after the traction block 5 is disengaged from the end of the front end of the housing 8, the traction block 5 is out of constraint; in contrast, as shown in fig. 8a, before the open net capture device 100 starts to work, the traction block 5 spins around the axis 110 at a high speed, and after the traction block 5 is out of the constraint of the housing 8, the traction block 5 flies around the axis 110 in a tangential direction of a spin trajectory circle under the action of inertial centrifugal force.

As shown in fig. 8e, the drawing block 5 draws the catching net 500 accommodated in the hood 110 in a folded state while the drawing block 5 is scattered all around, and the catching net 500 is drawn out from the tip end cavity of the hood casing 1 and unfolded. Namely, the passive unfolding process of the catching net 500 is completed through the inertia characteristic when the turbo rocket engine 200 drives the traction block 5 to spin; during the process of unfolding the catching net 500, the spring 2 which is originally in the compressed state is released, and the spring 2 in the compressed state pushes the pressing plate 3 to move towards the rear end so as to help the traction block 5 to draw the catching net 500 out of the tip cavity of the hood housing 1. After the capture net 500 is deployed, the capture net 500 will fly inertially in the flight direction of the airborne net capture bomb before the net-opening capture device 100 is in the first working mode, so as to capture the target drone in the direction of the bomb axis, i.e. the axis 110, and wind the rotor or other power structure of the target drone, so as to force the target drone to stop working and land.

The invention relates to an airborne-net capturing bomb, which is designed aiming at the problems of air reaction, ground-air reaction and airspace intrusion of a non-cooperative light and small unmanned aerial vehicle of the unmanned aerial vehicle, and comprises an open-net capturing device 100 and a turbo-type rocket engine 200, wherein the open-net capturing device 100 comprises a hood shell 1, a spring 2, a pressing plate 3, a shell 8, a positioning cylinder 7, an ejection base plate 6, a traction block 5, a capturing net 500 and a programming fuse module 300; the turbo rocket engine 200 is used for providing propelling power for the net-opening capturing device 100 to enable the net-opening capturing device 100 to fly, the characteristics of high-speed spinning and initial kinetic energy of the turbo rocket engine 200 are utilized to provide net-opening power for the net-opening capturing device 100, and quick and efficient net opening is realized based on the structural layout of the traction blocks 5, namely, the traction blocks 5 are used for positioning the capturing net 500 in an array mode, the traction blocks 5 are coaxially clamped and matched with the flange 60 of the ejection backing plate 6, the guide part 61 and the positioning part of the positioning barrel 7 and are fixedly connected to the plug 220 of the turbo rocket engine 200, so that after the programming fuse module 300 is used for controlling the net-opening capturing device 100 to be unlocked, the net-opening capturing device 100 obtains larger inertia and realizes the inertia net opening of the capturing net 500 according to the inertia principle, smooth net opening is ensured, large-range winding capture along the depth of the missile axis is realized based on the initial kinetic energy obtained by the turbo-type rocket engine 200, including translational kinetic energy and rotational kinetic energy, and capture of an empty small and medium unmanned aerial vehicle is realized; the turbo-type rocket engine 200 is used as a rocket power system, so that the effective range of direct aiming capture weapons is improved; the programming fuse module 300 can complete delayed unlocking of the open-net capturing device 100 by adopting the pure-digital delay circuit, so that the open-net time precision of the open-net capturing device 100 is improved, the design difficulty and the production cost of the airborne flying net capturing bomb are reduced, compared with a mechanical fuse, the weight of the fuse is reduced, the flying dry weight of the airborne flying net capturing bomb is further reduced, and the portability and the task execution reliability are improved; the visual aiming system of the loading platform can be matched to quickly acquire the target position and position information.

In the above embodiment of the present invention, the ignited net-opening powder is used as the powder of the ejection mechanism to complete the active working process of the net-opening capturing device 100, the programming fuse module 300 is used as the programming fuse of the ejection mechanism to control the on-off of the powder of the ejection mechanism, the programming fuse module 300 is further used for controlling the net-opening time of the net-opening capturing device 100 through the delay circuit, so as to realize the delayed unlocking of the net-opening capturing device 100, reduce the design difficulty and the production cost of an electronic system for an airborne net-capturing bomb, and compared with a mechanical fuse, reduce the quality of the fuse, further reduce the flying dry weight of the airborne net-capturing bomb, and improve the portability and the task execution reliability of the airborne net-capturing bomb.

The air flying net capturing bomb provided by the invention combines the advantages of good flexibility of capturing by an unmanned aerial vehicle, good target universality of capturing by the flying net bomb and the like, is designed based on the advantages and characteristics of low launching condition, small disturbance on an outer trajectory, simple structure, low production cost and the like of the conventional air flying net capturing bomb, and overcomes the defects of high cost and short hitting distance of a flying net capturing means at the present stage; the capture countercheck of the non-cooperative small unmanned aerial vehicle in the sight distance range can be completed, the air flying net capture bomb can be loaded through the unmanned aerial vehicle and is used as a direct aiming weapon of a target unmanned aerial vehicle, namely an enemy plane, so that the aerial confrontation of the unmanned aerial vehicle is realized, and the enemy plane is captured; the fly-to catch bomb can also be loaded through a ground weapon platform and is used for countering the small aerial vehicle; the flying net capture bomb can also be deployed in flight-forbidden areas such as civil airports, military management areas and the like, is launched by ground personnel, realizes damage-free capture on small unmanned aerial vehicles, aerial robots and aerial military animals of enemies, and performs anti-aerial reconnaissance tasks; the air-fly net capture bomb has the advantages of low launching condition, good flying stability, simple structure, low cost, high task reliability, high portability, flexible loading and the like, has wide application prospect for air attack and defense countermeasure and urban airspace management, and has certain reference significance for unmanned aerial vehicle countercheck and anti-air reconnaissance work based on a net capture mode.

The invention embodies a number of methods and approaches to this solution and the foregoing is only a preferred embodiment of the invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can be made, and these improvements and modifications should also be construed as the protection scope of the present invention. All the components not specified in the present embodiment can be realized by the prior art.

Claims

1. An airborne net-capture bomb comprising a turbo rocket engine (200), and a net-opening capturing device (100) connected to the front end of the engine along an axis (110), characterized in that: the open-net capturing device (100) comprises a plurality of traction blocks (5), a capturing net (500), a hood shell (1), a programming fuze module (300), a shell (8), a positioning cylinder (7) and an ejection base plate (6), wherein the shell (8), the positioning cylinder (7) and the ejection base plate are sequentially sleeved around the axis (110); wherein the content of the first and second substances,

the rear end of the shell (8) is connected with the turbo type rocket engine (200); a plurality of tooth gaps (70) are uniformly arranged at the front end of the positioning cylinder (7) in the circumferential direction and are positioned in the shell (8); a flange (60) arranged in a corresponding tooth gap is arranged on the outer side of the ejection base plate (6), and a guide part (61) is arranged at the front end of the ejection base plate (6) in a protruding mode on the axis (110); the rear end of the ejection base plate (6) is provided with a screen opening powder; the front end of the turborocket engine (200) is provided with the programming fuse module (300) to control the ignition of the open-net gunpowder;

a plurality of pull block (5) wind guide part (61) are circumference array and arrange and correspond flange (60) set up, hood shell (1) rear end with shell (8) front end sliding fit just hood shell (1) rear end tip with pull block (5) front end circumference sealing fit, it is a plurality of to catch net (500) connection pull block (5) and accept in hood shell (1).

2. The airborne fly-net capture bomb according to claim 1, wherein: the programming fuse module is provided with a delay circuit, and the delay circuit comprises a timer chip (310), a capacitor (323), a power supply battery and a resistor (322); the timer chip (310) is connected with two ends of the capacitor (323), and the timer chip (310) is provided with an ignition signal output end (324) for outputting an ignition trigger signal and controlling the ignition of the screened gunpowder; wherein the content of the first and second substances,

before the turborocket engine (200) is launched from the launching platform, the programming fuse module (300) is electrically communicated with a main control module (400) on the launching platform, and the main control module (400) is used for providing a time signal for the programming fuse module (300); the main control module (400) is provided with a digital-to-analog converter (410) for converting the time signal into an output voltage; the main control module (400) is provided with a signal output end (401) for outputting the output voltage; two ends of the capacitor (323) are respectively connected to the signal output end (401), and the timer chip (310) is used for charging the capacitor (323) to the output voltage;

after the turborocket engine (200) is launched, the main control module (400) is disconnected from the programming fuse module (300), the timer chip (310) is used for charging the capacitor (323) to a trigger voltage, the timer chip (310) is delayed to finish, and the ignition signal output end (324) is used for outputting the ignition trigger signal and controlling the ignition of the grid-opening gunpowder.

3. The airborne fly-net capture bomb according to claim 1, wherein: a plurality of tooth portions (71) are evenly provided with in the front end circumference of a location section of thick bamboo (7), tooth portion (71) encircle axis (110) direction is that the circumference array arranges and two liang of intervals set up, tooth seam (70) encircle axis (110) direction is that the circumference array arranges and two liang of intervals set up, tooth portion (71) with tooth seam (70) set up in turn in proper order.

4. The air fly net capturing bomb according to claim 3, wherein: the flange (60) comprises a plurality of recesses (62) and a plurality of protrusions (63) which are arrayed along the circumferential direction of the flange (60), and the recesses (62) and the protrusions (63) are sequentially and alternately arranged; before the ignition of the net-opening gunpowder, the bulges (63) are correspondingly clamped in the tooth gaps (70), and the outer surfaces of the depressions (62) are correspondingly contacted and matched with the inner surfaces of the tooth parts (71).

5. The air fly net capturing bomb according to claim 4, wherein: the outer surface of each traction block (5) is convexly provided with a lug (52), and before the screening gunpowder is ignited, the lugs (52) are in one-to-one correspondence with the bulges (63) and are in contact fit with the inner peripheral surface of the shell (8) after being in limit fit with the corresponding tooth gaps (70).

6. The airborne fly-net capture bomb according to claim 5, wherein: a pressing plate (3) positioned on the axis (110) and a spring (2) with two ends respectively connected with the blast cap shell (1) and the pressing plate (3) are arranged in the blast cap shell (1); the catching net (500) comprises a main body (510) and a plurality of connecting parts (520) connected with the main body (510), wherein the main body (510) is folded and is positioned at the rear end of the pressing plate (3), and each connecting part (520) is arranged in one traction block (5); before the hood housing (1) is separated from the housing (8), the spring (2) is in a compressed state; after the hood shell (1) is separated from the shell (8), the spring (2) is used for driving the pressing plate (3) to eject the catching net (500).

7. The airborne fly-net capture bomb according to claim 1, wherein: the front end of the turbine rocket engine is provided with a plug (220), and the inner peripheral surface of the rear end of the shell (8) is fixedly connected with the outer peripheral surface of the plug (220); the positioning cylinder (7) is fixedly arranged in the shell (8); the flange (60) and the guide part (61) are integrally connected with the ejection base plate (6); the outer peripheral surface of the rear end of the hood shell (1) is in sliding fit with the inner peripheral surface of the front end of the shell (8); the number of the traction blocks (5) and the number of the tooth gaps (70) are both 6.

8. An operating method for the airborne rocket projectile according to any one of claims 1 to 7, wherein the airborne rocket projectile includes a turbo-rocket engine (200), and an open-net capturing device (100) connected to the turbo-rocket engine (200) along an axis (110), the operating method comprising the steps of:

after the turbo rocket engine (200) is launched and before the net opening capture device (100) works, the turbo rocket engine (200) provides translational thrust along an axis (110) direction and spinning power around the axis (110) direction for the net opening capture device (100); the open-net capturing device (100) comprises a plurality of traction blocks (5), a capturing net (500), a hood shell (1), a programming fuze module (300), a shell (8), a positioning cylinder (7) and an ejection base plate (6), wherein the shell (8), the positioning cylinder (7) and the ejection base plate are sequentially sleeved around the axis (110); the ejection base plate (6) is internally provided with net opening gunpowder;

the programming fuse module (300) outputs an ignition trigger signal to control the ignition of the grid-opening gunpowder;

the net opening powder is ignited to generate gas and push the net opening capturing device (100) to start working, the ejection base plate (6), the traction block (5), the capturing net (500) and the hood shell (1) move forwards until the traction block (5) is separated from the end part of the front end of the shell (8), the traction block (5) moves forwards through translational thrust in the direction of the axis (110), and the traction block (5) winds the spinning power in the direction of the axis (110) and pulls the capturing net (500) to open the net along the tangential direction of the spinning track.

9. The working method of the airborne fly-net capture bomb according to claim 8, wherein: the method also comprises the following steps after the turbo rocket engine (200) is launched and before the step of operating the open net capture device (100):

before the turbo rocket engine (200) is launched, the programming fuse module (300) is electrically communicated with a main control module (400) on the launching platform, the main control module (400) inputs a time signal to the programming fuse module (300), the main control module (400) converts the time signal into an output voltage through a digital-to-analog converter (410), and the main control module (400) outputs the output voltage to a signal output end (401); the programming fuse module (300) is provided with a delay circuit, the delay circuit comprises a timer chip (310), a capacitor (323), a power supply battery and a resistor (322), two ends of the capacitor (323) are connected with the timer chip (310), two ends of the capacitor (323) are respectively connected with the signal output end (401), and the timer chip (310) is provided with an ignition signal output end (324).

10. The method of operating an airborne web trap bomb according to claim 9, further comprising: in the step of outputting an ignition trigger signal by the programming fuse module (300) to control the ignition of the grid-opening powder, the method further comprises the following steps:

the timer chip (300) charges the voltage across the capacitor (323) to the output voltage;

after the turbo rocket engine (200) is launched, the main control module (400) is disconnected from the programming fuze module (300), and the timer chip (310) charges the capacitor (323) to a trigger voltage;

and after the time delay of the timer chip (310) is finished, outputting an ignition trigger signal through the ignition signal output end (324) and controlling the ignition of the grid-opening gunpowder.