CN112572792A - Unmanned aerial vehicle capable of automatically intercepting and capturing unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle capable of automatically intercepting and capturing unmanned aerial vehicle Download PDFInfo
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- CN112572792A CN112572792A CN201910933750.7A CN201910933750A CN112572792A CN 112572792 A CN112572792 A CN 112572792A CN 201910933750 A CN201910933750 A CN 201910933750A CN 112572792 A CN112572792 A CN 112572792A
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- 235000017166 Bambusa arundinacea Nutrition 0.000 claims description 7
- 235000017491 Bambusa tulda Nutrition 0.000 claims description 7
- 241001330002 Bambuseae Species 0.000 claims description 7
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims description 7
- 239000011425 bamboo Substances 0.000 claims description 7
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 230000006378 damage Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000000903 blocking effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 238000004804 winding Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 238000006467 substitution reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/80—Vertical take-off or landing, e.g. using rockets
- B64U70/83—Vertical take-off or landing, e.g. using rockets using parachutes, balloons or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/50—Glider-type UAVs, e.g. with parachute, parasail or kite
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/15—UAVs specially adapted for particular uses or applications for conventional or electronic warfare
- B64U2101/16—UAVs specially adapted for particular uses or applications for conventional or electronic warfare for controlling, capturing or immobilising other vehicles
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Abstract
The invention discloses an unmanned aerial vehicle capable of automatically intercepting and capturing an unmanned aerial vehicle, which comprises a machine head, a machine body and a machine tail, wherein the machine head consists of a seeker and a connecting piece arranged in the seeker, the connecting piece is divided into a microcontroller and a first wing mounting seat, the rear end of the machine body is fixedly provided with a second wing mounting seat, a front wing and a rear wing are respectively and fixedly arranged on the first wing mounting seat and the second wing mounting seat, the rear end of the machine body is fixedly provided with a rear cover plate, the rear cover plate is fixedly connected with a motor through a locking bolt, a propeller and a load cylinder are respectively and fixedly arranged on a motor shaft of the motor, an automatically opened capturing net is arranged in the load cylinder, and the microcontroller controls and connects the capturing net, and the unmanned aerial vehicle has the beneficial effects that: the interceptor power requirement is reduced, the capture net is prevented from being wound, the safety of the double parachutes is high, the unmanned aerial vehicle is prevented from colliding with the captured target, the unmanned aerial vehicle can be remotely controlled and tracked, and the capture success rate is high.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle capable of automatically intercepting and capturing the unmanned aerial vehicle.
Background
Along with the increasing appearance of unmanned aerial vehicle in people's life, some unmanned aerial vehicles that do not conform to "black flight" of unmanned air vehicle safety control regulation often can bring the trouble for other people even influence public safety. In order to prevent the illegal abuse of the unmanned aerial vehicle, a new thing is urged: anti-unmanned aerial vehicle system.
The existing anti-unmanned aerial vehicle means mainly comprise an interference blocking type, a direct destroying type and a monitoring control type. The interference blocking type is that all signals of a target unmanned aerial vehicle are interfered by transmitting specific electromagnetic wave signals, so that the signals of the unmanned aerial vehicle are cut off, and the unmanned aerial vehicle is triggered to return, and the counter braking force of the method is poor; the direct destruction type is that the laser gun is used for directly knocking down the unmanned aerial vehicle, the counter force of the method is strong, but the knocked down unmanned aerial vehicle is easy to cause damage to ground personnel; the monitoring control method mainly utilizes a hacker technology to invade an operating system of the unmanned aerial vehicle, hijack radio control and pay the unmanned aerial vehicle, and the method has high technical content and technical cost and is difficult to popularize. Nowadays, a capture device for intercepting an unmanned aerial vehicle gradually appears, the capture device captures a target unmanned aerial vehicle by launching a net bomb or utilizing an unmanned aerial vehicle to carry an interception frame, the net bomb can only fly by means of inertia after being launched, the flying angle cannot be adjusted, the target unmanned aerial vehicle is easy to escape, the capture rate is low, and the risk of falling to hurt people can exist; and intercept target unmanned aerial vehicle through unmanned aerial vehicle delivery interception frame, because unmanned aerial vehicle carries the interception frame, its speed is difficult to surpass target unmanned aerial vehicle, and the flexibility of removing is poor, and the capture rate is low, and the practicality is relatively poor.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle capable of automatically intercepting and capturing unmanned aerial vehicles, so as to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides an automatic unmanned aerial vehicle's unmanned aerial vehicle is caught in interception, includes aircraft nose, fuselage and tail, the tail includes a load section of thick bamboo, the aircraft nose comprises seeker and the connecting piece of setting in seeker inside, the connecting piece divide into microcontroller and first wing mount pad, the rear end fixed mounting of fuselage has second wing mount pad, on first wing mount pad and the second wing mount pad respectively fixed mounting have preceding wing and back wing, the rear end fixed mounting back shroud of fuselage, the back shroud passes through locking bolt fixed connection motor, on the motor shaft of motor respectively fixed mounting screw and a load section of thick bamboo, be provided with the net of catching of automatic opening in the load section of thick bamboo, microcontroller control connection catches the net.
Preferably, the first wing mounting seat and the second wing mounting seat have the same structure, and both comprise a rotating shaft, and the first wing mounting seat and the second wing mounting seat are fixedly connected with the front wing and the rear wing through the adapter respectively.
Preferably, the front wing is located below the fuselage, the rear wing is located above the fuselage, the rear wing further comprises an aileron, a steering engine is fixedly mounted on an adapter of the rear wing, a rotating shaft of the steering engine is fixedly connected with the aileron, and the other end of the aileron is movably connected with the rear wing through a rotating rod.
Preferably, the number of the locking bolts on the rear cover plate is a plurality, the locking bolts are distributed in an annular arrangement manner, and the locking bolts are fixedly connected with the bottom of the motor.
Preferably, one end of the adapter is provided with a round hole matched with the rotating shaft, the other end of the adapter is provided with a protruding long rod, and the adapter is inserted into the wing through the long rod and is fixedly connected with the wing.
Preferably, a vertical wing is further arranged below the fuselage, and a receiver for receiving ground signals is arranged on the vertical wing.
Preferably, a gap is reserved between the aileron and the rear wing, the rear wing is of an L-shaped structure, and the combination of the aileron and the rear wing is of a rectangular structure.
Preferably, the top of fuselage is provided with power battery cabin and parachute cabin, be provided with emergent parachute in the parachute cabin, still be provided with in the load section of thick bamboo and catch the net parachute, catch the net parachute and catch the net and link to each other, set up the apron on the parachute cabin, be provided with the apron steering wheel that is used for opening the apron in the parachute cabin, the bottom of emergent parachute is provided with the compression spring that is used for popping out.
Compared with the prior art, the invention has the beneficial effects that:
1. the interceptor adopts a folding fixed wing form, so that the power requirement of the interceptor can be greatly reduced, conditions are created for selecting pure electric motor drive, and the interceptor has the characteristics of long range, high flying speed and reusability.
2. Catch the problem that net winding self was caught to the net rearmounted capture that can effectively prevent to launch, catch the net behind the winding target, under wind-force and the combined action that the target was caught and pulled, drag the parachute in the load section of thick bamboo, the parachute portability is caught the slow landing of target subaerial, the problem of damage has been reduced, the damage of self can be avoided to the parachute that interceptor self carried simultaneously, the two parachutes of independent setting can avoid the interceptor and catch both to collide together of unmanned aerial vehicle of target.
3. Can carry out remote control aircraft to the interceptor through ground remote control, track the target of catching to make the target of catching difficult for escaping, the capture rate is high.
Drawings
FIG. 1 is an exploded view of the structure of the present invention;
FIG. 2 is a schematic view of the overall structure of the present invention;
fig. 3 is a schematic diagram of the tail structure of the present invention.
In the figure: 1 machine head, 101 seeker, 102 connecting piece, 1021 microcontroller, 1022 first wing mounting base, 2 machine body, 3 tail, 4 second wing mounting base, 5 front wing, 6 rear wing, 7 rear cover plate, 9 motor, 10 propeller, 11 load cylinder, 12 capture net, 13 adaptor, 14 aileron, 15 steering engine, 16 vertical wing, 17 receiver, 18 power battery cabin and 19 parachute cabin.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-3, the present invention provides a technical solution: an unmanned aerial vehicle capable of automatically intercepting and capturing unmanned aerial vehicles comprises a machine head 1, a machine body 2 and a machine tail 3, the machine tail 3 comprises a loading cylinder, the machine head 1 consists of a guide head 101 and a connecting piece 102 arranged in the inner part of the guide head 101, the connector 102 is divided into a microcontroller 1021 and a first wing mount 1022, the rear end of the fuselage 2 is fixedly provided with a second wing mounting base 4, the first wing mounting base 1022 and the second wing mounting base 4 are respectively fixedly provided with a front wing 5 and a rear wing 6, a rear cover plate 7 is fixedly arranged at the rear end of the machine body 2, the rear cover plate 8 is fixedly connected with a motor 9 through a locking bolt, a propeller 10 and a load cylinder 11 are respectively and fixedly installed on a motor shaft of the motor 9, a capture net 12 which is automatically opened by a fuse to trigger the opening is arranged in the load cylinder 11, and the capture net 12 is controlled and connected by the microcontroller 1021.
It is worth noting that the first wing mount 1022 and the second wing mount 4 have the same structure, both the first wing mount 1022 and the second wing mount 4 include a rotating shaft, and the first wing mount 1022 and the second wing mount 4 are respectively fixedly connected with the front wing 5 and the rear wing 6 through the adapter 13; the front wing 5 is located below the fuselage 2, the rear wing 6 is located above the fuselage 2, the rear wing 6 further comprises an aileron 14, a steering engine 15 is fixedly mounted on an adapter 13 of the rear wing 6, a rotating shaft of the steering engine 15 is fixedly connected with the aileron 14, the other end of the aileron 14 is movably connected with the rear wing 6 through a rotating rod, a gap is reserved between the aileron 14 and the rear wing 6, the rear wing 6 is of an L-shaped structure, the aileron 14 and the rear wing 6 are combined into a rectangular structure, the tops of the first wing mounting seat 1022, the second wing mounting seat 4 and the aileron 14 are arched, the first wing mounting seat 1022, the second wing mounting seat 4 and the aileron 14 are of a left-right double-wing structure, and the horizontal heights of the wings on the left side and the right side are the same although the horizontal heights of the adapter 13 on the front wing 5 and the rear wing 6 are different; a gap is reserved between the aileron 14 and the rear wing 6, the rear wing 6 is of an L-shaped structure, the aileron 14 and the rear wing 6 are combined to be of a rectangular structure, and the rear wing 6 and the aileron 14 are connected by a miniature hinge piece, so that no air gap is generated to influence the aerodynamic performance of the airplane.
It is worth noting that the number of the locking bolts on the rear cover plate 8 is a plurality, and the locking bolts are distributed in a circular arrangement, and are fixedly connected with the bottom of the motor 9, so that the locking bolts and the motor are connected more firmly, a firm foundation is laid for installing the load cylinder 11 on the motor 9, and the capture net 12 in the load cylinder 11 is popped up by gunpowder.
It is worth noting that a round hole matched with the rotating shaft is formed in one end of the adapter piece 13, a protruding long rod is arranged at the other end of the adapter piece 13, and the adapter piece 13 is inserted into the wing through the long rod and is fixedly connected with the wing.
It is noted that a vertical wing 16 is further disposed below the fuselage 2, and a receiver 17 for receiving ground signals is disposed on the vertical wing 16.
It is worth noting that the top of fuselage 2 is provided with power battery cabin 18 and parachute cabin 19, be provided with emergent parachute in the parachute cabin 19, still be provided with in the load section of thick bamboo 11 and catch the net parachute, catch the net parachute and catch net 12 and link to each other, set up the apron on the parachute cabin 19, be provided with the apron steering wheel that is used for opening the apron in the parachute cabin 19, the bottom of emergent parachute is provided with the compression spring that is used for popping out.
Example (b):
track the target of catching through ground remote control unmanned aerial vehicle, receive signal by receiver 17 on the vertical wing 16, then open through microcontroller 1021 control and catch net 12 and emergent parachute, wherein catch the net parachute and open the back at catching net 12 completely, rely on the strength of catching the target through wind-force and inertia and pull out catching the net parachute, then in the time of pulling out, catch the net parachute through inertia and will open, catch the net parachute and take the target of catching to fall down, emergent parachute then when the unmanned aerial vehicle body meets emergency, take the unmanned aerial vehicle body to fall down, under normal conditions, unmanned aerial vehicle retrieves through hitting net or other modes.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. The utility model provides an automatic unmanned aerial vehicle is caught in interception, includes aircraft nose (1), fuselage (2) and tail (3), its characterized in that: the tail (3) comprises a load cylinder (11), the nose (1) consists of a guide head (101) and a connecting piece (102) arranged in the guide head (101), the connector (102) is divided into a microcontroller (1021) and a first wing mount (1022), a second wing mounting seat (4) is fixedly arranged at the rear end of the fuselage (2), a front wing (5) and a rear wing (6) are respectively and fixedly arranged on the first wing mounting seat (1022) and the second wing mounting seat (4), a rear cover plate (7) is fixedly arranged at the rear end of the machine body (2), the rear cover plate (7) is fixedly connected with a motor (9) through a locking bolt, a propeller (10) and a load cylinder (11) are respectively and fixedly arranged on a motor shaft of the motor (9), an automatically opened capturing net (12) is arranged in the load cylinder (11), and the microcontroller (1021) controls and is connected with the capturing net (12).
2. The unmanned aerial vehicle for automatically intercepting and capturing unmanned aerial vehicle of claim 1, wherein: the first wing mounting base (1022) and the second wing mounting base (4) are identical in structure, the first wing mounting base (1022) and the second wing mounting base (4) both comprise rotating shafts, and the first wing mounting base (1022) and the second wing mounting base (4) are fixedly connected with the front wing (5) and the rear wing (6) through the adaptor (13) respectively.
3. The unmanned aerial vehicle for automatically intercepting and capturing unmanned aerial vehicle of claim 1, wherein: front wing (5) are located the below of fuselage (2), back wing (6) are located the top of fuselage (2), back wing (6) still include aileron (14), fixed mounting has steering wheel (15) on adaptor (13) of back wing (6), the axis of rotation fixed connection aileron (14) of steering wheel (15), the other end of aileron (14) passes through dwang swing joint back wing (6).
4. The unmanned aerial vehicle for automatically intercepting and capturing unmanned aerial vehicle of claim 1, wherein: the number of the locking bolts on the rear cover plate (7) is a plurality of and the locking bolts are distributed in an annular arrangement mode and are fixedly connected with the bottom of the motor (9).
5. The unmanned aerial vehicle for automatically intercepting and capturing unmanned aerial vehicle of claim 1, wherein: one end of the adapter piece (13) is provided with a round hole matched with the rotating shaft, the other end of the adapter piece (13) is provided with a convex long rod, and the adapter piece (13) is inserted into the wing through the long rod and is fixedly connected with the wing.
6. The unmanned aerial vehicle for automatically intercepting and capturing unmanned aerial vehicle of claim 1, wherein: a vertical wing (16) is further arranged below the machine body (2), and a receiver (17) for receiving ground signals is arranged on the vertical wing (16).
7. The unmanned aerial vehicle for automatically intercepting and capturing unmanned aerial vehicle of claim 3, wherein: a gap is reserved between the aileron (14) and the rear wing (6), the rear wing (6) is of an L-shaped structure, and the aileron (14) and the rear wing (6) are combined to form a rectangular structure.
8. The unmanned aerial vehicle for automatically intercepting and capturing unmanned aerial vehicle of claim 1, wherein: the top of fuselage (2) is provided with power battery cabin (18) and parachute cabin (19), be provided with emergent parachute in parachute cabin (19), still be provided with in load section of thick bamboo (11) and catch the net parachute, it links to each other with catching net (12) to catch the net parachute, set up the apron on parachute cabin (19), be provided with the apron steering wheel that is used for opening the apron in parachute cabin (19), the bottom of emergent parachute is provided with the compression spring who is used for popping out emergent parachute.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910933750.7A CN112572792A (en) | 2019-09-29 | 2019-09-29 | Unmanned aerial vehicle capable of automatically intercepting and capturing unmanned aerial vehicle |
| PCT/CN2020/070268 WO2021056925A1 (en) | 2019-09-29 | 2020-01-03 | Unmanned aircraft for automatically intercepting and capturing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910933750.7A CN112572792A (en) | 2019-09-29 | 2019-09-29 | Unmanned aerial vehicle capable of automatically intercepting and capturing unmanned aerial vehicle |
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| CN112572792A true CN112572792A (en) | 2021-03-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910933750.7A Pending CN112572792A (en) | 2019-09-29 | 2019-09-29 | Unmanned aerial vehicle capable of automatically intercepting and capturing unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN112572792A (en) |
| WO (1) | WO2021056925A1 (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114389741A (en) * | 2021-12-06 | 2022-04-22 | 特金智能科技(上海)有限公司 | Unmanned aerial vehicle counter-braking method, system and device and storage medium |
| CN114132506B (en) * | 2021-12-31 | 2025-01-03 | 长春长光博翔无人机有限公司 | Airborne anti-UAV target capture device and method |
| CN114229026B (en) * | 2021-12-31 | 2023-07-07 | 西北工业大学 | An unmanned aerial vehicle simulation interception device |
| CN115158670A (en) * | 2022-08-05 | 2022-10-11 | 西安羚控电子科技有限公司 | Folding wing unmanned aerial vehicle and carrier buffer separation control method |
| CN115384788A (en) * | 2022-08-24 | 2022-11-25 | 湖南省蓝鹰科技有限公司 | A reconnaissance UAV applied to combat training scenarios |
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| WO2021056925A1 (en) | 2021-04-01 |
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