CN219277812U - Can section of thick bamboo shoot horizontal folding unmanned aerial vehicle - Google Patents
Can section of thick bamboo shoot horizontal folding unmanned aerial vehicle Download PDFInfo
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- CN219277812U CN219277812U CN202223546705.2U CN202223546705U CN219277812U CN 219277812 U CN219277812 U CN 219277812U CN 202223546705 U CN202223546705 U CN 202223546705U CN 219277812 U CN219277812 U CN 219277812U
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Abstract
The utility model discloses a cylindrical horizontal folding unmanned aerial vehicle, which comprises a transmitting cylinder and an unmanned aerial vehicle body; the unmanned aerial vehicle body comprises a barrel-type frame, a wing group and an avionic device; the barrel type frame is provided with four wing bins which are arranged on the same barrel axis plane in a pair of two groups along the barrel axis, and the wing groups are provided with four wings which are respectively in one-to-one correspondence with the four wing bins; each wing is assembled with a corresponding wing cabin through a rebound piece, and the automatic horizontal unfolding or folding in the wing cabin in the cylindrical shaft plane is realized; the free end of each wing is respectively provided with a propeller component, the propeller component and the avionics device are electrically controlled and connected, and the avionics device is arranged in the barrel type frame. The novel structural design is succinct, adopts the cylinder to load, and installation, convenient to carry realize handheld, fixed platform transmission and the effect of launching take-off on arbitrary narrow environment, mobile carrier.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicle equipment, in particular to a cylindrical horizontal folding unmanned aerial vehicle.
Background
With the development of science and technology, various individual combat weapons and intelligent ammunition play an important role, and have become an important killing tool for high-technology warfare and play an increasingly important role. The individual soldier patrol device is used as a product of technical fusion of guided ammunition and a small unmanned aerial vehicle, and has the capabilities of reconnaissance, detection, target positioning, aerial wireless relay, electronic interference, damage evaluation, accurate striking and the like. Can fly over a designated area for a long time, scout and track enemy targets, and return information such as images and the like to a ground operation platform through a bidirectional data link, the situation awareness capability of soldiers in complex environments can be remarkably enhanced, and compared with the traditional direct aiming type weapon, the soldiers can strike time-sensitive targets and hidden targets accurately, and the soldiers have higher efficiency-cost ratio.
The existing common miniature military unmanned aerial vehicle is mainly a fixed rotor unmanned aerial vehicle, a rotor of the unmanned aerial vehicle is fixed, so that the size of the unmanned aerial vehicle is large, the unmanned aerial vehicle is disassembled and then boxed when the unmanned aerial vehicle is not used generally, the unmanned aerial vehicle is assembled when the unmanned aerial vehicle is used, and the defect that the unmanned aerial vehicle cannot be used quickly exists. Moreover, the common fixed unmanned aerial vehicle adopts a ground take-off mode, and can not take off while moving in some narrow environments on a battlefield or on a moving carrier (vehicle or armored vehicle).
In view of the above, the present disclosure is an intensive study on the above problems, and proposes a horizontal foldable unmanned aerial vehicle capable of being shot in a barrel to overcome the above technical problems.
Disclosure of Invention
The utility model aims to provide a cylindrical horizontal folding unmanned aerial vehicle which is simple in structural design, convenient to install and carry and convenient to install by adopting cylindrical filling, and achieves the effects of being handheld, capable of being launched by a fixed platform and capable of being launched and taken off in any narrow environment and on a movable carrier.
In order to achieve the above object, the solution of the present utility model is:
a horizontal folding unmanned aerial vehicle capable of being shot in a barrel comprises a shooting barrel and an unmanned aerial vehicle body, wherein a barrel opening for filling the unmanned aerial vehicle body is formed in the head of the shooting barrel; the unmanned aerial vehicle body comprises a barrel-type frame, a wing group and an avionic device; the barrel type frame is provided with four wing bins which are arranged on the same barrel axis plane in a pair of two groups along the barrel axis, and the wing groups are provided with four wings which are respectively in one-to-one correspondence with the four wing bins; each wing is assembled with a corresponding wing cabin through a rebound piece, and the automatic horizontal unfolding or folding in the wing cabin in the cylindrical shaft plane is realized; the free end of each wing is respectively provided with a propeller component, the propeller component and the avionics device are electrically controlled and connected, and the avionics device is arranged in the barrel type frame.
The propeller assembly comprises a motor and two propellers arranged on the motor, and the motor is electrically connected with the avionics device.
A hollow structure convenient for cable routing is arranged in the wing, and a supporting seat for installing a propeller component is outwards formed at one end of the hollow structure.
A bracket disc is arranged at the central position in the cylinder type rack and comprises a front disc seat, a rear disc seat and an avionic cabin positioned between the front disc seat and the rear disc seat; the four wings are divided into a front group and a rear group which correspond to the four wing cabins, and the front group and the rear group of wings are movably installed on the front tray seat and the rear tray seat respectively.
The avionics device comprises a battery pack, a power supply PCB and a flight control board which are electrically connected in sequence, wherein the power supply PCB and the flight control board are arranged in an avionics bin; the battery pack comprises two batteries, and two battery bins which are distributed front and back are arranged at the back of the corresponding front and back wing bins in the barrel type frame.
A partition plate is arranged between the battery bin and the wing bin, and a heat dissipation hole group is formed in the partition plate.
The avionics device also comprises a four-in-one electric tone, a GNSS antenna and a signal communication module; the GNSS antenna and the signal communication module are respectively arranged on the front tray seat and the rear tray seat, and the four-in-one electric tuning and the flight control board and the power supply PCB board are sequentially arranged in the avionics cabin in a stacked manner by adopting a flying tower.
The avionics device further comprises an image sensor which is arranged at a position close to the front end part in the barrel type rack, and the front end part of the barrel type rack is provided with a head hatch cover.
An ammunition bin is arranged in the rear end part of the barrel type frame, and a tail cabin cover is arranged at the rear end part of the barrel type frame.
After the scheme is adopted, the utility model relates to a horizontal folding unmanned aerial vehicle can be penetrated to section of thick bamboo for prior art's beneficial effect lies in: the novel folding unmanned aerial vehicle adopts a cylinder type horizontal mode design, and the structural design is simple and compact; the unmanned aerial vehicle is folded and then is filled in the inner cylinder type of the transmitting cylinder, so that the operation is very simple and convenient, and the carrying is convenient. The launching adopts the barrel type launching, can be launched by the hand of an operator, can be launched on a fixed or mobile ground platform, can be launched on a mobile carrier in any narrow environment, can be launched for take-off, can remotely control the unmanned aerial vehicle to fly through a remote controller after launching and lifting, and can finish the tasks of reconnaissance, tracking monitoring, suicide type attack and the like.
Drawings
FIG. 1 is a schematic illustration of the loading state of the present novel unmanned aerial vehicle;
FIG. 2 is a schematic view of the wing fold state of the present novel unmanned aerial vehicle body;
FIG. 3 is a schematic view of the wing deployment state of the novel unmanned aerial vehicle body;
FIG. 4 is an exploded view of the structure of the present novel unmanned aerial vehicle body;
fig. 5 is another structural exploded view of the present novel drone body.
Description of the reference numerals
A launch canister 100, a canister port 101, an unmanned aerial vehicle body 200, a canister type frame 1,
wing magazine 11, rebound member 12, bracket tray 13, front tray 131, rear tray 132,
the wing 2, the support seat 21, the propeller assembly 3, the motor 31, the propeller 32,
avionics 4, battery 41, power supply PCB board 42, flight control board 43, four-in-one electric regulator 44,
a GNSS antenna 45, a signal communication module 46 and an image sensor 47.
Detailed Description
The present utility model will now be described in further detail with reference to the accompanying drawings and detailed description.
The present disclosure relates to a drum-shooter horizontal folding unmanned aerial vehicle, as shown in fig. 1-5, comprising a launch drum 100 and an unmanned aerial vehicle body 200. The launch canister 100 is cylindrical, and has a canister mouth 101 at its head, and the unmanned aerial vehicle body 200 is folded and then loaded from the canister mouth 101. Specifically, the folding unmanned aerial vehicle body 200 is filled with grenades from the head 101 of the launch canister 200 into the launch canister 100; the launching canister 100 may be a grenade launcher or a special launching canister, and is small in size, convenient to carry, and capable of launching the unmanned aerial vehicle body 200 in a narrow environment or on a mobile carrier.
The unmanned aerial vehicle body 200 comprises a barrel type frame 1, a wing group and an avionics device 4. The barrel type frame 1 is provided with four wing cabins 11 in total, and the four wing cabins 11 are distributed in a front-back mode in a one-by-one mode along the barrel axial direction on the barrel type frame 1 and are arranged on the same barrel axial plane.
The wing group is provided with four wings 2 which are respectively in one-to-one correspondence with the four wing cabins 11. The wing bin 11 is arranged on the barrel body in an extending manner parallel to the axial direction of the barrel body, the wings 2 are movably assembled in the wing bin 11 in a horizontal folding manner, the horizontal folding is represented by the fact that the plane formed by the four wings 2 after being unfolded is the same barrel axis plane, and the plane is parallel to the barrel axial direction of the barrel frame 1. Each wing 2 is assembled in a corresponding wing pocket 11 by means of a resilient member 12, and each wing 2 is automatically and horizontally unfolded or folded in the corresponding wing pocket 11 by means of the resilient action of the resilient member 12. One embodiment of the rebound member 12 may employ a torsion spring member.
The free end of each wing 2 is respectively provided with a propeller assembly 3, the propeller assemblies 3 and the avionics device 4 are electrically controlled and connected, and the avionics device 4 is arranged in the barrel type frame 1. The preferred embodiment of the propeller assembly 3 comprises a motor 31 and two propellers 32 arranged on the motor 31, wherein the motor 31 is electrically connected with the avionics device 4, and the avionics device 4 controls the motor 31 to work so as to drive the two propellers 32 to rotate, so that the unmanned aerial vehicle can start flying.
In a further embodiment, the inside of the wing 2 is preferably provided with a hollow structure, so that the cable is conveniently routed from the hollow structure, and the routing connection between the propeller assembly 3 and the avionics device 4 is facilitated. Further, a support seat 21 is formed outwardly at one end of the hollow structure for mounting the motor 31 of the propeller assembly 3.
To facilitate the installation design of the horizontal type integral structure, the preferred embodiment of the cartridge type frame 1 is formed with a bracket tray 13 at a central position in the cartridge type frame 1, and the bracket tray 13 includes a front tray 131, a rear tray 132, and an avionics bay 133 between the front tray 131 and the rear tray 132. Corresponding to the front-back layout of the four wing bins 11, the four wings 2 are divided into two groups of front and back wings, and the front and back wings 2 are movably installed on the front tray 131 and the back tray 132 respectively.
The avionics device 4 preferably comprises a battery pack, a power supply PCB 42 and a flight control board 43 which are electrically connected with each other in sequence. The power supply PCB board 42 and the flight control board 43 are installed in the avionics bay 133. The battery pack comprises two batteries 41 which are arranged front and back, two battery bins which are distributed front and back are formed at the back of the corresponding front and back wing bins 11 in the barrel type frame 1, and the two batteries 41 are respectively contained in the two battery bins. Further, the battery compartment and the wing compartment 11 are separated by a partition 14, and the partition 14 is preferably provided with a heat dissipation hole set 141. When the unmanned aerial vehicle works, the wings 2 extend out of the wing cabins 11, the wing cabins 11 are in an open and empty state, and the batteries 41 positioned at the back sides of the partition plates 14 can achieve excellent heat dissipation effects by means of the heat dissipation hole groups 141 and the wing cabins 11.
Further, the avionics device 4 further includes a four-in-one electric tuner 44, a GNSS antenna 45, and a signal communication module 46. The GNSS antenna 45 and the signal communication module 46 are respectively mounted on the front chassis 131 and the rear chassis 132, specifically, on the front chassis 131, the GNSS antenna 45, the front wing set 2A, and a battery 41 are sequentially disposed, and on the rear chassis 132, the signal communication module 46, the rear wing set 2B, and the battery 41 are sequentially disposed. The four-in-one electric regulator 44, the flight control board 43 and the power supply PCB 42 are sequentially arranged and installed in the avionics cabin 133 in a stacked manner by adopting a fly tower. The structure is simple, compact and stable.
Furthermore, the avionics device 4 further includes an image sensor 47, the image sensor 47 is mounted in the barrel frame 1 at a position close to the front end, and the front end of the barrel frame 1 is provided with a head hatch 15, which is beneficial to structural assembly and protection. In addition, an ammunition bin is arranged in the rear end part of the barrel type frame 1 and is used for filling ammunition, and after the unmanned aerial vehicle finds an attack target, an operator gives an instruction through the signal communication module 46 to initiate a suicide attack to the target. The tail of the barrel type frame 1 is provided with a tail cabin cover 16.
This novel foldable unmanned aerial vehicle adopts the design of cylinder level mode, and overall structure design is succinct, compact. The shrapnel type loading in the launching tube 100 after the wing group of the unmanned aerial vehicle body 200 is folded is quite simple and convenient to operate and convenient to carry. The launching adopts the barrel type launching, can be launched by the hand of an operator, can be launched on a fixed or mobile ground platform, can be launched on a mobile carrier in any narrow environment, can be launched for take-off, can remotely control the unmanned aerial vehicle to fly through a remote controller after launching and lifting, and can finish the tasks of reconnaissance, tracking monitoring, suicide type attack and the like.
The foregoing description is only of the preferred embodiments of the present utility model, and all equivalent changes and modifications that come within the scope of the following claims are intended to be embraced therein.
Claims (8)
1. Can section of thick bamboo shoot horizontal folding unmanned aerial vehicle, its characterized in that: the unmanned aerial vehicle comprises a transmitting barrel and an unmanned aerial vehicle body, wherein a barrel opening for filling the unmanned aerial vehicle body is formed in the head of the transmitting barrel; the unmanned aerial vehicle body comprises a barrel-type frame, a wing group and an avionic device; the barrel type frame is provided with four wing bins which are arranged on the same barrel axis plane in a pair of two groups along the barrel axis, and the wing groups are provided with four wings which are respectively in one-to-one correspondence with the four wing bins; each wing is assembled with a corresponding wing cabin through a rebound piece, and the automatic horizontal unfolding or folding in the wing cabin in the cylindrical shaft plane is realized; the free end of each wing is respectively provided with a propeller assembly, the propeller assemblies are electrically connected with the avionics device, and the avionics device is arranged in the barrel-type frame; a bracket disc is arranged at the central position in the cylinder type rack and comprises a front disc seat, a rear disc seat and an avionic cabin positioned between the front disc seat and the rear disc seat; the four wings are divided into a front group and a rear group which correspond to the four wing cabins, and the front group and the rear group of wings are movably installed on the front tray seat and the rear tray seat respectively.
2. A drum-jet horizontal folding unmanned aerial vehicle as claimed in claim 1, wherein: the propeller assembly comprises a motor and two propellers arranged on the motor, and the motor is electrically connected with the avionics device.
3. A telescopic horizontal folding unmanned aerial vehicle according to claim 1 or 2, wherein: a hollow structure convenient for cable routing is arranged in the wing, and a supporting seat for installing a propeller component is outwards formed at one end of the hollow structure.
4. A drum-jet horizontal folding unmanned aerial vehicle as claimed in claim 1, wherein: the avionics device comprises a battery pack, a power supply PCB and a flight control board which are electrically connected in sequence, wherein the power supply PCB and the flight control board are arranged in an avionics bin; the battery pack comprises two batteries, and two battery bins which are distributed front and back are arranged at the back of the corresponding front and back wing bins in the barrel type frame.
5. A drum-jet horizontal folding unmanned aerial vehicle as claimed in claim 4, wherein: a partition plate is arranged between the battery bin and the wing bin, and a heat dissipation hole group is formed in the partition plate.
6. A drum-jet horizontal folding unmanned aerial vehicle as claimed in claim 4, wherein: the avionics device also comprises a four-in-one electric tone, a GNSS antenna and a signal communication module; the GNSS antenna and the signal communication module are respectively arranged on the front tray seat and the rear tray seat, and the four-in-one electric tuning and the flight control board and the power supply PCB board are sequentially arranged in the avionics cabin in a stacked manner by adopting a flying tower.
7. A drum-jet horizontal folding unmanned aerial vehicle as claimed in claim 1, wherein: the avionics device further comprises an image sensor which is arranged at a position close to the front end part in the barrel type rack, and the front end part of the barrel type rack is provided with a head hatch cover.
8. A drum-jet horizontal folding unmanned aerial vehicle as claimed in claim 1, wherein: an ammunition bin is arranged in the rear end part of the barrel type frame, and a tail cabin cover is arranged at the rear end part of the barrel type frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223546705.2U CN219277812U (en) | 2022-12-27 | 2022-12-27 | Can section of thick bamboo shoot horizontal folding unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223546705.2U CN219277812U (en) | 2022-12-27 | 2022-12-27 | Can section of thick bamboo shoot horizontal folding unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219277812U true CN219277812U (en) | 2023-06-30 |
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ID=86920554
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223546705.2U Active CN219277812U (en) | 2022-12-27 | 2022-12-27 | Can section of thick bamboo shoot horizontal folding unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219277812U (en) |
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2022
- 2022-12-27 CN CN202223546705.2U patent/CN219277812U/en active Active
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