CN219806973U - Integrated compact unmanned aerial vehicle with shell - Google Patents
Integrated compact unmanned aerial vehicle with shell Download PDFInfo
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- CN219806973U CN219806973U CN202320586688.0U CN202320586688U CN219806973U CN 219806973 U CN219806973 U CN 219806973U CN 202320586688 U CN202320586688 U CN 202320586688U CN 219806973 U CN219806973 U CN 219806973U
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- unmanned aerial
- aerial vehicle
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- horn
- shell
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- 210000005056 cell body Anatomy 0.000 claims abstract description 8
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 7
- 239000004917 carbon fiber Substances 0.000 claims abstract description 7
- 230000006978 adaptation Effects 0.000 claims abstract description 4
- 230000004308 accommodation Effects 0.000 claims description 6
- 238000007789 sealing Methods 0.000 claims description 6
- 230000017525 heat dissipation Effects 0.000 claims description 5
- 230000005611 electricity Effects 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 230000002035 prolonged effect Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 4
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007175 bidirectional communication Effects 0.000 description 1
- 210000004027 cell Anatomy 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Abstract
The utility model provides a shell integrated compact unmanned aerial vehicle, which comprises a shell, a cover plate and a horn, wherein the horn is symmetrically arranged around the shell, the horn and the shell are integrally formed by carbon fibers, a hollow pipeline is arranged in the horn, one end of a connecting wire is electrically connected with a motor through the hollow pipeline, and the other end of the connecting wire is electrically connected with an electric regulator; be equipped with the holding chamber in the casing, unmanned aerial vehicle control module arranges the holding intracavity in, and the casing upper surface is equipped with the mounting groove in and is equipped with waterproof gasket, the apron pass through waterproof gasket with the casing is sealed fixed, the casing bottom be equipped with unmanned aerial vehicle power module form adaptation's cell body, unmanned aerial vehicle power module is fixed in the cell body provides the electric energy for unmanned aerial vehicle. The structure can adapt to middle rain and weather flight below, the flight condition of the unmanned aerial vehicle is greatly improved, the influence of weather factors on the unmanned aerial vehicle working flight is reduced, the unmanned aerial vehicle structure is more compact, the size of the unmanned aerial vehicle is reduced, and the endurance time of the unmanned aerial vehicle is prolonged.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a shell integrated compact unmanned aerial vehicle.
Background
Unmanned aerial vehicles ("UAVs") are unmanned aerial vehicles that are operated using radio remote control equipment and self-contained programmed control devices. Compared with manned aircraft, it has the advantages of small size, low cost, convenient use, low requirement for battle environment, strong battlefield survivability, etc. In recent years, with the progress of technology, the unmanned aerial vehicle industry has also developed rapidly, and the unmanned aerial vehicle is gradually applied to a plurality of fields such as aerial mapping, police affairs, fire fighting and disaster relief.
At present, a shell and a horn are fixed by a mode of locking screws, and the traditional unmanned aerial vehicle does not have a waterproof function and cannot work in rainy days. The circuit control system of the unmanned aerial vehicle plays a role in master control, particularly electronic parts such as a master control board and the like, if any water inflow phenomenon exists in the using process, the normal operation of the whole machine can be influenced, even serious explosion accidents can be generated, and harm and immeasurable loss are caused. Meanwhile, the endurance time of the unmanned aerial vehicle becomes the biggest bottleneck for preventing the unmanned aerial vehicle from developing, and although the lithium battery is the battery with the best comprehensive performance in the current market, the endurance requirement of the unmanned aerial vehicle still cannot be completely met. The reduction of the weight and the volume of the unmanned aerial vehicle and the improvement of the endurance time of the unmanned aerial vehicle become the most direct and effective mode. In addition, can hold unmanned aerial vehicle and for unmanned aerial vehicle automatic replacement battery's unmanned aerial vehicle airport application with unmanned aerial vehicle is born, unmanned aerial vehicle's volume directly influences the size of unmanned aerial vehicle airport.
Disclosure of Invention
The utility model aims to provide a shell integrated compact unmanned aerial vehicle, and aims to solve the technical problems that in the prior art, the unmanned aerial vehicle cannot work under the rainy day condition without water resistance, and the unmanned aerial vehicle is large in size, so that the endurance is influenced, and the corresponding size of an airport for accommodating the unmanned aerial vehicle is large.
In order to solve the technical problems, the utility model adopts the following technical scheme: the utility model provides an integrative compact unmanned aerial vehicle of casing, including casing, apron and horn, the horn is located around the casing symmetrically, the horn adopts carbon fiber integrated into one piece with the casing, the inside hollow pipeline that is of horn, the motor is installed to the horn end, install the screw on the motor in order to drive the screw and rotate, the motor is connected with unmanned aerial vehicle power module through electric accent, and connecting wire one end is through hollow pipeline and motor electricity connection, the other end is connected with electric accent electricity; be equipped with the accommodation chamber in the casing, unmanned aerial vehicle control module arranges in the accommodation intracavity, the casing upper surface is equipped with the mounting groove, be equipped with waterproof gasket in the mounting groove, the apron pass through waterproof gasket with the casing is sealed fixed, the casing bottom be equipped with unmanned aerial vehicle power module form adaptation's cell body, unmanned aerial vehicle power module is fixed for unmanned aerial vehicle provides the electric energy in the cell body.
Further, the number of the machine arms is four, the machine arms are respectively arranged around the machine shell, the machine without a body is divided into a machine head and a machine tail, two motors and two propellers at the tail ends of the machine arms in the machine head direction are respectively and upwards installed, and two motors and two propellers at the tail ends of the machine arms in the machine tail direction are respectively and downwards installed.
Furthermore, two 1.4G antennas are respectively arranged at the tail ends of the two horn arms in the machine head direction downwards.
Furthermore, two RTK spiral antennas are respectively installed upwards at the tail ends of the two horn in the tail direction.
Further, a first fixing block is arranged on the machine head direction shell, and the cradle head is installed on the unmanned aerial vehicle shell through the first fixing block.
Further, a second fixed block is arranged on the machine head direction shell, and the megaphone is installed on the unmanned aerial vehicle shell through the second fixed block.
Furthermore, a connecting piece is arranged between the two arms in the tail direction, and the parachute is fixed on the unmanned aerial vehicle shell through the connecting piece.
Furthermore, the two symmetrical sides of the shell are respectively provided with a foot rest.
Further, a 5G feeder and an RTK feeder are fixed on the foot rest.
Further, a through hole is formed in the outer side of the shell, a heat dissipation plate is arranged on the through hole, and the heat dissipation plate is in shape-fit sealing connection with the through hole.
The utility model has the beneficial effects that: according to the utility model, the horn and the shell are integrally formed by adopting carbon fibers, the hollow pipeline is arranged in the horn, one end of the connecting wire is electrically connected with the motor through the hollow pipeline, and the other end of the connecting wire is electrically connected with the electric regulator. In addition, the casing is internally provided with a containing cavity, the unmanned aerial vehicle control module is arranged in the containing cavity, the upper surface of the casing is provided with a mounting groove, a waterproof gasket is arranged in the mounting groove, the cover plate is fixed with the casing in a sealing manner through the waterproof gasket, the bottom of the casing is provided with a groove body matched with the form of the unmanned aerial vehicle power supply module, the unmanned aerial vehicle structure is more compact, the size of the unmanned aerial vehicle is reduced, the resistance during flying is further reduced, and the endurance time of the unmanned aerial vehicle is prolonged. Meanwhile, the size of an airport which is matched with the unmanned aerial vehicle and used for accommodating the unmanned aerial vehicle is correspondingly reduced.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are needed in the embodiments or the description of the prior art will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a perspective view of an integrated compact unmanned aerial vehicle mounting of the present utility model;
FIG. 2 is a top view of the integrated compact unmanned aerial vehicle of the present utility model;
FIG. 3 is a perspective view of the integrated compact unmanned aerial vehicle of the present utility model;
FIG. 4 is a schematic diagram of a chassis of the integrated compact unmanned aerial vehicle of the present utility model;
fig. 5 is a perspective view of the nose direction of the integrated compact unmanned aerial vehicle of the present utility model.
Description of the reference numerals:
10. a housing; 101. A mounting groove; 11. A cover plate; 111. A magnetic compass;
12. a horn; 13. A propeller; 14. A motor; 15. A foot rest;
16. a 5G feeder and an RTK feeder; 17. A heat dissipation plate; 18. 1.4G antenna;
19. an RTK helical antenna; 20. A cradle head; 201. A first fixed block;
30. a megaphone; 301. A second fixed block; 40. A parachute;
401. and a connecting piece.
Detailed Description
Embodiments of the present utility model are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present utility model and should not be construed as limiting the utility model.
In the description of the present utility model, it should be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientation or positional relationships shown in the drawings, merely to facilitate describing the present utility model and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present utility model.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present utility model, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the present utility model, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.
As shown in fig. 1 to 5, the embodiment of the utility model provides a housing integrated compact unmanned aerial vehicle, which comprises a housing 10, a cover plate 11 and a horn 12, wherein the horn 12 is symmetrically arranged around the housing 10, the horn 12 and the housing 10 are integrally formed by carbon fibers, a hollow pipeline is arranged in the horn 12, a motor 14 is arranged at the tail end of the horn, a propeller 13 is arranged on the motor 14 to drive the propeller to rotate, the motor 14 is connected with an unmanned aerial vehicle power supply module through an electric regulator, one end of a connecting wire is electrically connected with the motor through the hollow pipeline, and the other end of the connecting wire is electrically connected with the electric regulator; be equipped with the accommodation chamber in the casing 10, unmanned aerial vehicle control module arranges in the accommodation intracavity, casing 10 upper surface is equipped with mounting groove 101, be equipped with waterproof gasket in the mounting groove 101, apron 11 pass through waterproof gasket with casing 10 is sealed fixed, in some embodiments, installs magnetic compass 111 on apron 11, the casing bottom is equipped with the cell body with unmanned aerial vehicle power module form adaptation, unmanned aerial vehicle power module fixes for unmanned aerial vehicle provides the electric energy in the cell body.
The most key concept of the utility model is that the horn and the shell are integrally formed by adopting carbon fibers, the inside of the horn is provided with a hollow pipeline, one end of a connecting wire is electrically connected with the motor through the hollow pipeline, and the other end of the connecting wire is electrically connected with the electric regulator. In addition, the casing is internally provided with a containing cavity, the unmanned aerial vehicle control module is arranged in the containing cavity, the upper surface of the casing is provided with a mounting groove, a waterproof gasket is arranged in the mounting groove, the cover plate is fixed with the casing in a sealing manner through the waterproof gasket, the bottom of the casing is provided with a groove body matched with the form of the unmanned aerial vehicle power supply module, the unmanned aerial vehicle structure is more compact, the size of the unmanned aerial vehicle is reduced, the resistance during flying is further reduced, and the endurance time of the unmanned aerial vehicle is prolonged. Meanwhile, the size of an airport which is matched with the unmanned aerial vehicle and used for accommodating the unmanned aerial vehicle is correspondingly reduced.
Further, the number of the machine arms 12 is four, and the machine arms 12 are respectively arranged around the machine shell 10, so that the inorganic machine is divided into a machine head and a machine tail, two motors and two propellers at the tail ends of the machine arms in the machine head direction are respectively and upwards installed, and two motors and two propellers at the tail ends of the machine arms in the machine tail direction are respectively and downwards installed. The propeller in the machine head direction is upwards installed, and the propeller in the machine tail direction is downwards installed, so that the unmanned aerial vehicle body is more compact and balanced.
Further, as shown in fig. 1 and 3, two 1.4G antennas 18 are respectively installed at the ends of the two arms in the machine head direction. The screw is installed to two horn tops of aircraft nose direction, and 1.4G antenna is installed to the below, effectively utilizes the space, need not to drill at other positions of casing and installs the antenna, further improves the water-proof effects.
Further, as shown in fig. 1 and 3, two RTK helical antennas 19 are respectively installed at the tail ends of the two arms in the tail direction. The space is effectively utilized, and the antenna is not required to be installed at other positions of the shell in a drilling way, so that the waterproof effect is further improved.
Further, as shown in fig. 1 and 5, the machine head direction casing is provided with a first fixing block 201, and the cradle head 20 is mounted on the unmanned aerial vehicle casing by the first fixing block 201. Install the cloud platform on unmanned aerial vehicle casing through the fixed block, increase unmanned aerial vehicle's anti-shake nature, slow down unmanned aerial vehicle camera's vibrations, can also shoot some pictures through cloud platform adjustment camera lens, the stability of reinforcing shooting.
Further, as shown in fig. 1 and 5, the machine head direction casing is provided with a second fixing block 301, and the megaphone 30 is mounted on the unmanned aerial vehicle casing through the second fixing block 301. The area flown by the unmanned aerial vehicle is shouted through the megaphone 30, and the large-scale broadcasting is carried out from the sky, so that clear real-time sound transmission can be realized, and audio or real-time voice transmission can be played and recorded. The unmanned aerial vehicle plays notes in the overhead circulation, and the sound energy is transmitted to the outside of hundreds of meters.
Further, as shown in fig. 1 and 5, a connector 401 is disposed between the two arms in the tail direction, and the parachute 40 is fixed on the unmanned aerial vehicle casing through the connector 401. The parachute 40 is provided with built-in sensors and battery cells, and the control unit can independently operate or can be connected with an unmanned aerial vehicle flight control system for cooperation. The system can be in bidirectional communication with unmanned aerial vehicle flight control, and can receive and feed back the system state in real time. The parachute 40 can be ejected to open the parachute at the first time after the unmanned aerial vehicle is detected to be out of control, so that the unmanned aerial vehicle can slowly descend safely, and loss caused by the explosion of the unmanned aerial vehicle and personal injury is prevented.
Further, as shown in fig. 1, 2, 3 and 5, the two symmetrical sides of the casing are respectively provided with a foot rest 15. When the unmanned aerial vehicle is static, the balance of the unmanned aerial vehicle body is kept.
Further, as shown in fig. 1, 3 and 5, the stand 15 is fixed with a 5G feeder and an RTK feeder 16. Install 5G feeder and RTK feeder 16 on the foot rest, need not to set up the mounting hole alone on the casing for unmanned aerial vehicle is compacter.
Further, a through hole is formed in the outer side of the casing 10, and a heat dissipation plate is arranged on the through hole and is in shape-adaptive sealing connection with the through hole. External heating panel improves the radiating effect for unmanned aerial vehicle flies to control, and the picture signal is more stable.
In summary, according to the utility model, the horn and the shell are integrally formed by adopting the carbon fiber, the hollow pipeline is arranged in the horn, one end of the connecting wire is electrically connected with the motor through the hollow pipeline, and the other end of the connecting wire is electrically connected with the electric regulator. In addition, the casing is internally provided with a containing cavity, the unmanned aerial vehicle control module is arranged in the containing cavity, the upper surface of the casing is provided with a mounting groove, a waterproof gasket is arranged in the mounting groove, the cover plate is fixed with the casing in a sealing manner through the waterproof gasket, the bottom of the casing is provided with a groove body matched with the form of the unmanned aerial vehicle power supply module, the unmanned aerial vehicle structure is more compact, the size of the unmanned aerial vehicle is reduced, the resistance during flying is further reduced, and the endurance time of the unmanned aerial vehicle is prolonged. Meanwhile, the size of an airport which is matched with the unmanned aerial vehicle and used for accommodating the unmanned aerial vehicle is correspondingly reduced. Install motor, screw and 1.4G antenna, RTK helical antenna respectively in horn end upper and lower both sides, effectively save space and need not to drill in addition on the casing and install, further improve unmanned aerial vehicle's water-proof effects. The cradle head, the megaphone and the parachute are arranged on the unmanned aerial vehicle, so that the application scene of the unmanned aerial vehicle is improved.
The foregoing description is only illustrative of the present utility model and is not intended to limit the scope of the utility model, and all equivalent changes made by the specification and drawings of the present utility model, or direct or indirect application in the relevant art, are included in the scope of the present utility model.
Claims (10)
1. The utility model provides a casing integrative compact unmanned aerial vehicle, includes casing, apron and horn, its characterized in that, the horn is located around the casing symmetrically, the horn adopts carbon fiber integrated into one piece with the casing, the inside hollow pipeline that is of horn, the motor is installed to the horn end, install the screw on the motor in order to drive the screw rotation, the motor is connected with unmanned aerial vehicle power module through electric accent, and connecting wire one end is through hollow pipeline and motor electricity connection, the other end is connected with electric accent electricity; be equipped with the accommodation chamber in the casing, unmanned aerial vehicle control module arranges in the accommodation intracavity, the casing upper surface is equipped with the mounting groove, be equipped with waterproof gasket in the mounting groove, the apron pass through waterproof gasket with the casing is sealed fixed, the casing bottom be equipped with unmanned aerial vehicle power module form adaptation's cell body, unmanned aerial vehicle power module is fixed for unmanned aerial vehicle provides the electric energy in the cell body.
2. The integrated compact unmanned aerial vehicle with the shell according to claim 1, wherein the number of the arms is four, the four arms are respectively arranged on the periphery of the shell, the unmanned aerial vehicle is divided into a machine head and a machine tail, two motors and two propellers on the tail ends of the two arms in the machine head direction are respectively installed upwards, and two motors and two propellers on the tail ends of the two arms in the machine tail direction are respectively installed downwards.
3. The integrated compact unmanned aerial vehicle of claim 2, wherein the two horn ends in the nose direction are each provided with two 1.4G antennas downwards.
4. The integrated compact unmanned aerial vehicle of claim 2, wherein two RTK helical antennas are respectively mounted upwardly at the ends of the two arms in the tail direction.
5. The integrated compact unmanned aerial vehicle of claim 2, wherein the machine head direction housing is provided with a first fixing block, and the cradle head is mounted on the unmanned aerial vehicle housing through the first fixing block.
6. The integrated compact unmanned aerial vehicle of claim 2, wherein the machine head direction housing is provided with a second fixing block, and the megaphone is mounted on the unmanned aerial vehicle housing through the second fixing block.
7. The integrated compact unmanned aerial vehicle of claim 2, wherein a connector is provided between the two arms in the tail direction, and the parachute is fixed to the unmanned aerial vehicle housing via the connector.
8. The integrated compact unmanned aerial vehicle of claim 1, wherein the legs are provided on each of the symmetrical sides of the housing.
9. The integrated compact unmanned aerial vehicle of claim 8, wherein the foot rest has a 5G feeder and an RTK feeder secured thereto.
10. The integrated compact unmanned aerial vehicle of claim 1, wherein a through hole is formed in the outer side of the housing, and a heat dissipation plate is arranged on the through hole and is in shape-fit sealing connection with the through hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320586688.0U CN219806973U (en) | 2023-03-17 | 2023-03-17 | Integrated compact unmanned aerial vehicle with shell |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320586688.0U CN219806973U (en) | 2023-03-17 | 2023-03-17 | Integrated compact unmanned aerial vehicle with shell |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219806973U true CN219806973U (en) | 2023-10-10 |
Family
ID=88210094
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320586688.0U Active CN219806973U (en) | 2023-03-17 | 2023-03-17 | Integrated compact unmanned aerial vehicle with shell |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219806973U (en) |
-
2023
- 2023-03-17 CN CN202320586688.0U patent/CN219806973U/en active Active
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