CN113048843A - A catch net balanced emitter for catching unmanned aerial vehicle - Google Patents
A catch net balanced emitter for catching unmanned aerial vehicle Download PDFInfo
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- CN113048843A CN113048843A CN202110363084.5A CN202110363084A CN113048843A CN 113048843 A CN113048843 A CN 113048843A CN 202110363084 A CN202110363084 A CN 202110363084A CN 113048843 A CN113048843 A CN 113048843A
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- 239000000843 powder Substances 0.000 claims abstract description 24
- 230000005540 biological transmission Effects 0.000 claims abstract description 12
- 239000003380 propellant Substances 0.000 claims description 9
- 230000000712 assembly Effects 0.000 claims description 5
- 238000000429 assembly Methods 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 5
- 238000003825 pressing Methods 0.000 claims description 4
- 239000003814 drug Substances 0.000 claims description 3
- 239000011148 porous material Substances 0.000 claims 1
- 239000003721 gunpowder Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 229910001369 Brass Inorganic materials 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 229910000737 Duralumin Inorganic materials 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000010951 brass Substances 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 238000003892 spreading Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
- F41H11/00—Defence installations; Defence devices
- F41H11/02—Anti-aircraft or anti-guided missile or anti-torpedo defence installations or systems
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- General Engineering & Computer Science (AREA)
- Catching Or Destruction (AREA)
Abstract
The invention discloses a net catching balance launching device for capturing an unmanned aerial vehicle, which comprises an igniter, a charging component, a launching component and a balance component, wherein the launching component, the charging component and the balance component are sequentially connected, and the igniter is arranged on the charging component; launch subassembly and balanced subassembly pass through the connecting piece and hang in the unmanned aerial vehicle below. The launching assembly comprises a launching barrel, a catching net and N traction bodies, and the balance assembly comprises a balance barrel and a balance body. The launching tube and the balance tube have the same structure and the same size, and the mass of the N traction bodies is equal to that of the balance body. Some firearm ignition, the powder charge subassembly produces high-pressure gas, and high-pressure gas promotes the transmission of transmission subassembly and catches the net, and high-pressure gas promotes balanced subassembly transmission balancing body simultaneously, and some firearm are connected in unmanned aerial vehicle power on, and it stimulates through remote control ignition.
Description
Technical Field
The invention belongs to the technical field of aerial security of unmanned aerial vehicles, and particularly relates to a capture net balance launching device for capturing an unmanned aerial vehicle.
Background
Due to the gradual opening of the low-altitude flight field and the rapid development of the unmanned aerial vehicle technology, the harm of the unmanned aerial vehicle to air traffic caused by 'black flight' is increasingly serious. Because unmanned aerial vehicle has the flight characteristics of "little slow", hardly constitute effective threat to it through ordinary weapon, consequently anti-unmanned aerial vehicle technique arouses the attention gradually. Present counter-unmanned aerial vehicle systems can be generally divided into three categories: (1) the unmanned aerial vehicle is damaged by ammunition or directional energy weapons; (2) the unmanned aerial vehicle is interfered by electronic countermeasure or hacker technology; (3) and directly capturing the unmanned aerial vehicle by using the capturing net. Due to the low cost of the capture net, the complete machine prototype can be captured, and the enemy unmanned aerial vehicle is deeply researched, so that the capture net mode becomes the most ideal mode for countering the unmanned aerial vehicle. For the emission of the capture net, Zhongwei adopts the quantity of pipes to emit a plurality of traction bodies to drive the capture net to emit in 'numerical simulation and optimization of the emission process of the anti-unmanned aerial vehicle capture net device', and designs the capture net device with multi-pipe emission. This approach not only reduces the portability of the weapon, but also does not guarantee the synchronicity of the firing of the tow bodies well. 202011470010.3 discloses a rapid capture function unmanned aerial vehicle with a transmitting net, which adopts a cylinder to transmit, utilizes a buffer spring to relieve the disturbance of the recoil force to the fuselage, but still cannot avoid the interference of the recoil force to the flight stability of the unmanned aerial vehicle, and uses the cylinder as transmitting power, so the power is not ideal.
Disclosure of Invention
The invention aims to provide a net catching balance launching device for catching an unmanned aerial vehicle, which increases the portability of weapons, ensures the launching synchronism, can effectively realize the catching operation of the unmanned aerial vehicle, and can effectively avoid the interference of a launching backseat on the stability of the unmanned aerial vehicle body by adopting a balance launching principle. The unique structural design makes full use of the space of the gun body, and realizes the integration and portability of the device.
The technical solution for realizing the purpose of the invention is as follows: a net catching balance launching device for capturing an unmanned aerial vehicle comprises an igniter, a charging component, a launching component and a balance component, wherein the launching component, the charging component and the balance component are sequentially connected, and the igniter is arranged on the charging component; launch subassembly and balanced subassembly pass through the connecting piece and hang in the unmanned aerial vehicle below.
The launching assembly comprises a launching barrel, a catching net and N traction bodies, and the balance assembly comprises a balance barrel and a balance body. The launching tube and the balance tube have the same structure and the same size, and the mass of the N traction bodies is equal to that of the balance body.
Some firearm ignition, the powder charge subassembly produces high-pressure gas, and high-pressure gas promotes the transmission of transmission subassembly and catches the net, and high-pressure gas promotes balanced subassembly transmission balancing body simultaneously, and some firearm are connected in unmanned aerial vehicle power on, and it stimulates through remote control ignition.
The launching tube comprises an end cover pressing ring, a sealing end cover, a tube body, an outer rifling tube and M guide blocks, wherein M = N, the outer rifling tube is positioned in the tube body, a ring cavity is formed between the outer rifling tube and the sealing end cover, the M guide blocks are arranged in the ring cavity and slide along the outer rifling tube, one end of the outer rifling tube is a closed end, the other end of the outer rifling tube is an open end, the sealing end cover is fixed at the open end through the end cover pressing ring, a tapered blind hole serving as a low-pressure chamber is formed in the end surface of the closed end in an inward opening mode, a circle of first groove is formed in the outer wall of the closed end, the first groove is positioned at the tail end of the tapered blind hole, the first groove and the tapered blind hole are communicated through; m rifling grooves are processed on the outer wall of the external rifling pipe; the closed end of the outer bore tube and one end of the barrel body are fixedly connected with the charging component respectively.
Compared with the prior art, the invention has the remarkable advantages that:
(1) the capture net balance launching device can meet the requirements of low recoil and low disturbance by adopting a high-low pressure balance launching mode, and can be directly loaded on the rotor unmanned aerial vehicle to realize the long-distance capture of the unmanned aerial vehicle by the unmanned aerial vehicle. The influence on the flight stability of the rotor unmanned aerial vehicle during launching is very small.
(2) The balanced launching device for the catching net of the invention launches promptly, and the catching of the spreading net is integrated, thereby overcoming the defects of small space utilization rate of the traditional multi-barrel, effectively utilizing the space of the gun body, and realizing the miniaturization and integration of the system.
(3) According to the catching net balance launching mechanism, the outer bore line pipe, the high-pressure chamber and the cylinder body are in threaded connection, and the connection mode can effectively guarantee the coaxiality of all parts, guarantees the connection strength and is beneficial to the stability of an inner trajectory.
Drawings
FIG. 1 is a cross-sectional view of the structure of a balanced emission device of a capture net of the present invention.
Fig. 2 is a sectional view of an external bore pipe in the balanced emitter of the present invention.
Fig. 3 is an axial view of an outer bore tube in the balanced emitter of the invention.
Fig. 4 is a cross-sectional view of the chamber core in the balanced emission device of the present invention.
FIG. 5 is an end view of a chamber cover of the trap balance emitting device of the present invention.
Fig. 6 is a matching view of an outer bore pipe and a traction body in the catching net balance launching device.
Detailed Description
The present invention is described in further detail below with reference to the attached drawing figures.
With reference to fig. 1 to 6, the net catching balance launching device for capturing the unmanned aerial vehicle comprises an igniter 8, a launching assembly, a charging assembly and a balance assembly, wherein the launching assembly, the charging assembly and the balance assembly are sequentially connected, and the igniter 8 is arranged on the charging assembly. Launch subassembly and balanced subassembly pass through the connecting piece and hang in the unmanned aerial vehicle below.
8 ignition of some firearm ignites the propellant powder in the charge subassembly, and the charge subassembly produces high-pressure gas, and high-pressure gas promotes the transmission of transmission subassembly and catches the net, and high-pressure gas promotes balanced subassembly transmission balance body simultaneously, and some firearm 8 is connected in unmanned aerial vehicle power on, ignites through remote control ignition.
The launching assembly comprises a launching barrel, a catching net and N traction bodies 3, N =4, 6 and 8, the balance assembly comprises a balance barrel and a balance body 11, the launching barrel and the balance barrel are identical in structure and size, and the mass of the N traction bodies 3 is equal to that of the balance body 11.
Taking the launch canister as an example, the structural composition of the launch canister and the balance canister will be described.
The launch canister includes end cover clamping ring 1, end cover 2, the stack shell 4, outer bore pipe 5, M guide block 6, M = N, outer bore pipe 5 is located stack shell 4, form the annular chamber between the two, M guide block 6 sets up in the annular chamber, can follow the slide of bore line groove 55 on the outer wall of outer bore pipe 5, outer bore pipe 5 one end is the blind end, the other end is open end, end cover 2 fixes at open end through end cover clamping ring 1, it has a convergent blind hole 52 as the low-pressure chamber to open from the closed end terminal, be equipped with the first recess 51 of round on the outer wall of blind end, first recess 51 is located the end of convergent blind hole 52, communicate through P air vent 53 that are annular equidistant distribution between first recess 51 and the convergent blind hole 52, P =4~10, first recess 51 communicates with the annular chamber. The closed end of the outer bore tube 5 and one end of the barrel 4 are fixedly connected with the charging component through threads respectively.
When the launching assembly is used, the catching net is arranged in the cavity 54 of the outer bore tube 5, the traction bodies 3 are long-strip arc-shaped pieces, and the N traction bodies 3 are distributed in the annular cavity in an annular mode and cover the outer wall of the outer bore tube 5, as shown in fig. 6. The bottom of each traction body 3 is fixedly connected with a guide block 6. The catching net is connected to the top end of the traction body 3 through a connecting rope.
When the balance assembly is used, the balance body 11 is cylindrical and is arranged in the annular cavity to cover the outer wall of the outer bore tube 5, and the M guide blocks 6 are fixed at the bottom of the balance body 11 at equal intervals and are embedded in the bore line groove 55 on the outer bore tube 5.
The charge assembly comprises a charge chamber 7 and two cover plate assemblies, the cover plate assemblies comprise a charge chamber cover 10 and a spout diaphragm 9, the charge chamber 7 is cylindrical, as shown in fig. 4, a fifth-order through hole is formed in the direction of the central axis of the charge chamber, a first-order hole 62, a second-order hole 63, a third-order hole 64, a fourth-order hole 65 and a fifth-order hole 66 are sequentially formed in the charge chamber, the diameters of the first-order hole 62, the second-order hole 63 and the third-order hole 64 are sequentially reduced, and the first-order hole 62, the fifth-order hole 66, the second-order hole 63 and the fourth-order hole 65 are respectively and symmetrically equal about the third-order hole. The first-step hole 62 and the fifth-step hole 66 are fixedly connected with an outer bore pipe 5 respectively, the outer walls of the first-step hole 62 and the fifth-step hole 66 are fixedly connected with a barrel 4 respectively, the second-step hole 63 and the fourth-step hole 65 are respectively provided with a cover plate assembly, the spout diaphragm 9 is close to the third-step hole 63, and the third-step hole 63 is used as a high-pressure cavity filled with propellant powder. An ignition mounting hole 61 is formed in the middle of the hole wall of the third-step hole 63 and used for fixing the igniter 8.
The spout diaphragm 9 is made of brass sheet, duralumin sheet or red copper sheet and is used for accumulating gas pressure in the high-pressure chamber.
The center of the medicine chamber cover 10 is provided with a first through hole 101, and a plurality of second through holes 102 are annularly distributed by taking the first through hole as a circle center and used for transmitting high-pressure gas generated by propellant to the low-pressure chamber.
The invention relates to a balanced launching device of a catching net, which takes gunpowder gas as launching power. When the powder is launched, the igniter 8 ignites the propellant powder in the high-pressure chamber, the propellant powder is combusted to generate high-pressure powder gas, when the pressure of the powder gas reaches a certain pressure, the nozzle diaphragm 9 is sheared and damaged, the powder gas respectively enters the low-pressure chambers at two sides through the through holes on the powder chamber cover 10, and respectively reaches the end faces of the bottoms of the traction body 3 and the balance body 11 through the vent holes 53 communicated with the gun cavity through the low-pressure chambers. When the pressure reaches the starting pressure of the traction body 3 and the balance body 11, the gunpowder gas starts to push the traction body 3 and the balance body 11 to advance. The traction body 3 starts to move along the axial direction under the action of gunpowder gas, and at the moment, the guide block 6 arranged on the traction body 3 is subjected to the circumferential guide effect of the rifling groove 55 on the external rifling pipe 3, so that the traction body starts to rotate under the circumferential deflection force in the advancing process. The counterweight 11 advances away from the traction body 3 and rotates opposite to the traction body 3 to counteract the recoil generated during firing and the moment generated by the rotational movement of the traction body 3.
The traction body 3 obtains the rotation speed and the axial movement speed under the constraint and guide action of the bore line groove 55 on the outer wall of the outer bore line pipe 5 and the pushing work of gunpowder gas, and after the constraint of the barrel body 4 is removed, the rotation movement of the traction body 3 is changed into the linear movement speed along the tangential direction. The combined speed of the axial speed and the tangential speed enables the traction body 3 to be dispersed along the circumferential direction after the traction body is taken out of the chamber, and the net bag is unfolded through the traction rope, so that the catching net is unfolded. Different rifling angles can be processed according to different target capture distances, so that the traction body 3 can obtain different rotating speeds in the in-bore movement process, different circumferential speeds can be obtained when flying away from a muzzle, and the time for expanding the maximum area of the net bag is determined by the height of the circumferential speeds. Thereby affecting capture performance. And when the target contacts the catching net, the catching operation of the target unmanned aerial vehicle is completed.
Although the present invention has been described with reference to a preferred embodiment, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (9)
1. The utility model provides a catch net balanced emitter for catching unmanned aerial vehicle, includes some firearm (8), charge subassembly, its characterized in that: the device also comprises a launching assembly and a balancing assembly, wherein the launching assembly, the charging assembly and the balancing assembly are sequentially connected, and an igniter (8) is arranged on the charging assembly; the launching assembly and the balance assembly are suspended below the unmanned aerial vehicle through a connecting piece;
the launching assembly comprises a launching barrel, a catching net and N traction bodies (3), N =4, 6 and 8, and the balance assembly comprises a balance barrel and a balance body (11);
some firearm (8) are igniteed, and the powder charge subassembly produces high-pressure gas, and high-pressure gas promotes the transmission subassembly transmission and catches the net, and high-pressure gas promotes balanced subassembly transmission balance body simultaneously, and some firearm (8) are connected in unmanned aerial vehicle power on, and it arouses to ignite through remote control.
2. A capture net balanced launch device for capturing drones according to claim 1, characterized in that: the launching tube and the balance tube have the same structure and the same size, and the mass of the N traction bodies (3) is equal to that of the balance body (11).
3. A capture net balanced launch device for capturing drones according to claim 2, characterized in that: the launching tube comprises an end cover pressing ring (1), a sealing end cover (2), a tube body (4), an outer bore tube (5), M guide blocks (6), M = N, the outer bore tube (5) is positioned in the tube body (4), a ring cavity is formed between the outer bore tube and the tube body, the M guide blocks (6) are arranged in the ring cavity, the bore tube (55) slides along the outer wall of the outer bore tube (5), one end of the outer bore tube (5) is a closed end, the other end of the outer bore tube is an open end, the sealing end cover (2) is fixed at the open end through the end cover pressing ring (1), a gradually-reduced blind hole (52) is arranged in the end surface of the self-closed end to serve as a low-pressure chamber, a circle of first groove (51) is arranged on the outer wall of the closed end, the first groove (51) is positioned at the tail end of the gradually-reduced blind hole (52), the first groove (51) is, p = 4-10, the first groove (51) is communicated with the annular cavity; the closed end of the outer bore tube (5) and one end of the barrel body (4) are fixedly connected with the charging component respectively.
4. A capture net balanced launch device for capturing drones according to claim 3, characterized in that: when the catching net is used as a launching assembly, the catching net is arranged in a tube cavity (54) of an outer bore tube (5), the traction bodies (3) are long-strip-shaped arc-shaped pieces, N traction bodies (3) are distributed in the annular cavity in an annular shape, the outer wall of the outer bore tube (5) is coated, the bottom of each traction body (3) is fixedly connected with a guide block (6), and the catching net is connected to the top end of each traction body (3) through a connecting rope.
5. A capture net balanced launch device for capturing drones according to claim 3, characterized in that: when the balance assembly is used, the balance body (11) is cylindrical and is arranged in the annular cavity to cover the outer wall of the outer bore pipe (5), and the M guide blocks (6) are fixed at the bottom of the balance body (11) at equal intervals.
6. A capture net balanced launch device for capturing drones according to claim 3, characterized in that: the powder charging assembly comprises a powder chamber (7) and two cover plate assemblies, the cover plate assemblies comprise a powder chamber cover (10) and a nozzle diaphragm (9), the powder chamber (7) is cylindrical, a fifth-step through hole is formed in the direction of the central axis of the powder chamber, the two ends of the fifth-step through hole are symmetrical about the center and sequentially comprise a first-step hole (62), a second-step hole (63), a third-step hole (64), a fourth-step hole (65) and a fifth-step hole (66), the diameters of the first-step hole (62), the second-step hole (63) and the third-step hole (64) are sequentially reduced, an outer bore pipe (5) is fixedly connected in each of the first-step hole (62) and the fifth-step hole (66), the outer walls of the first-step hole (62) and the fifth-step hole (66) are fixedly connected with a cylinder body (4), the second-step hole (63) and the fourth-step hole (65) are respectively provided with one cover plate assembly, wherein the nozzle diaphragm (9) is close to the third-step, the third-step hole (63) is used as a high-pressure cavity and is filled with propellant powder; an ignition mounting hole (61) is formed in the middle of the hole wall of the third-step hole (63) and used for fixing the igniter (8).
7. A capture net balanced launch device for capturing drones according to claim 6, characterized in that: the center of the medicine chamber cover (10) is provided with a first through hole (101), and a plurality of second through holes (102) are annularly distributed by taking the first through hole as a circle center and used for transmitting high-pressure gas generated by propellant to the low-pressure chamber.
8. A capture net balanced launch device for capturing drones according to claim 1, characterized in that: the powder charging assembly comprises a powder chamber (7) and two cover plate assemblies, each cover plate assembly comprises a powder chamber cover (10) and a nozzle diaphragm (9), the powder chamber (7) is cylindrical, a five-step through hole is formed in the direction of the central axis of the powder chamber, two ends of the five-step through hole are symmetrical about the center, and a first-step hole (62), a second-step hole (63), a third-step hole (64), a fourth-step hole (65) and a fifth-step hole (66) are sequentially formed in the five-step through hole;
first order hole (62), second order hole (63), third order hole (64) diameter reduce in proper order, five order through-holes both ends link firmly emission subassembly and balanced subassembly respectively, respectively are equipped with a cover plate subassembly in second order hole (63) and the fourth order hole (65), and wherein spout diaphragm (9) are close to third order hole (63), and third order hole (63) fill the propellant powder as high-pressure chamber in, and open in third order hole (63) pore wall middle section has ignition mounting hole (61) for fixed some firearm (8).
9. A capture net balanced launch device for capturing drones according to claim 8, characterized in that: the center of the medicine chamber cover (10) is provided with a first through hole (101), and a plurality of second through holes (102) are annularly distributed by taking the first through hole as a circle center and used for transmitting high-pressure gas generated by propellant to the low-pressure chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110363084.5A CN113048843A (en) | 2021-04-02 | 2021-04-02 | A catch net balanced emitter for catching unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110363084.5A CN113048843A (en) | 2021-04-02 | 2021-04-02 | A catch net balanced emitter for catching unmanned aerial vehicle |
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| CN113048843A true CN113048843A (en) | 2021-06-29 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115892471A (en) * | 2023-02-15 | 2023-04-04 | 北京天赢测控技术有限公司 | Catch unmanned aerial vehicle |
| CN116573158A (en) * | 2023-05-15 | 2023-08-11 | 南京理工大学 | High-low pressure chamber folding wing unmanned aerial vehicle catapulting test device based on gaseous fuel |
| CN118560709A (en) * | 2024-08-05 | 2024-08-30 | 中南大学 | Aircraft launching device |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102141357A (en) * | 2011-01-06 | 2011-08-03 | 北京机械设备研究所 | Recoil-free ejecting device |
| CN105730698A (en) * | 2016-04-28 | 2016-07-06 | 山西阿瑞斯自动化科技有限公司 | Small fire extinguishing unmanned helicopter |
| CN205602134U (en) * | 2016-04-28 | 2016-09-28 | 山西阿瑞斯自动化科技有限公司 | Small -size unmanned helicopter of putting out a fire |
| CN106288963A (en) * | 2015-06-25 | 2017-01-04 | 株式会社迪思科 | Small-sized pilotless aircraft beats back device |
| CN207050575U (en) * | 2017-07-04 | 2018-02-27 | 鹰眼电子科技有限公司 | Unmanned plane carry catches net rifle in the air |
| CN109850151A (en) * | 2019-04-02 | 2019-06-07 | 广州鼎飞航空科技有限公司 | A kind of unmanned plane arrest net device and unmanned plane |
| CN109916225A (en) * | 2019-03-13 | 2019-06-21 | 北京天剑维安科技发展有限公司 | A kind of net for capturing unmanned plane catches bullet |
| CN110360890A (en) * | 2019-08-30 | 2019-10-22 | 中国人民解放军空军工程大学 | A kind of unmanned aerial vehicle onboard with anti-squat power penetrates net device |
| KR102152739B1 (en) * | 2020-02-06 | 2020-09-07 | 주식회사 이노컨 | illegality drone capture for drone have chain carbon fiber capture net |
-
2021
- 2021-04-02 CN CN202110363084.5A patent/CN113048843A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102141357A (en) * | 2011-01-06 | 2011-08-03 | 北京机械设备研究所 | Recoil-free ejecting device |
| CN106288963A (en) * | 2015-06-25 | 2017-01-04 | 株式会社迪思科 | Small-sized pilotless aircraft beats back device |
| CN105730698A (en) * | 2016-04-28 | 2016-07-06 | 山西阿瑞斯自动化科技有限公司 | Small fire extinguishing unmanned helicopter |
| CN205602134U (en) * | 2016-04-28 | 2016-09-28 | 山西阿瑞斯自动化科技有限公司 | Small -size unmanned helicopter of putting out a fire |
| CN207050575U (en) * | 2017-07-04 | 2018-02-27 | 鹰眼电子科技有限公司 | Unmanned plane carry catches net rifle in the air |
| CN109916225A (en) * | 2019-03-13 | 2019-06-21 | 北京天剑维安科技发展有限公司 | A kind of net for capturing unmanned plane catches bullet |
| CN109850151A (en) * | 2019-04-02 | 2019-06-07 | 广州鼎飞航空科技有限公司 | A kind of unmanned plane arrest net device and unmanned plane |
| CN110360890A (en) * | 2019-08-30 | 2019-10-22 | 中国人民解放军空军工程大学 | A kind of unmanned aerial vehicle onboard with anti-squat power penetrates net device |
| KR102152739B1 (en) * | 2020-02-06 | 2020-09-07 | 주식회사 이노컨 | illegality drone capture for drone have chain carbon fiber capture net |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115892471A (en) * | 2023-02-15 | 2023-04-04 | 北京天赢测控技术有限公司 | Catch unmanned aerial vehicle |
| CN115892471B (en) * | 2023-02-15 | 2023-12-15 | 北京天赢测控技术有限公司 | Capturing unmanned aerial vehicle |
| CN116573158A (en) * | 2023-05-15 | 2023-08-11 | 南京理工大学 | High-low pressure chamber folding wing unmanned aerial vehicle catapulting test device based on gaseous fuel |
| CN118560709A (en) * | 2024-08-05 | 2024-08-30 | 中南大学 | Aircraft launching device |
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Application publication date: 20210629 |
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