CN111056005A - Waterproof dirt-proof unmanned aerial vehicle aircraft nose assembly - Google Patents
Waterproof dirt-proof unmanned aerial vehicle aircraft nose assembly Download PDFInfo
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- CN111056005A CN111056005A CN201911418918.7A CN201911418918A CN111056005A CN 111056005 A CN111056005 A CN 111056005A CN 201911418918 A CN201911418918 A CN 201911418918A CN 111056005 A CN111056005 A CN 111056005A
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- aircraft nose
- unmanned aerial
- aerial vehicle
- radar
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- 238000009434 installation Methods 0.000 claims description 18
- 238000012423 maintenance Methods 0.000 claims description 14
- 230000001681 protective effect Effects 0.000 claims description 7
- 238000003780 insertion Methods 0.000 claims description 2
- 230000037431 insertion Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 10
- 238000013461 design Methods 0.000 abstract description 4
- 108010066057 cabin-1 Proteins 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 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 1
- 230000004308 accommodation Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000008447 perception Effects 0.000 description 1
- 239000000575 pesticide Substances 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000004078 waterproofing Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
- B64C1/403—Arrangement of fasteners specially adapted therefor, e.g. of clips
- B64C1/406—Arrangement of fasteners specially adapted therefor, e.g. of clips in combination with supports for lines, e.g. for pipes or cables
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
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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
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Computer Networks & Wireless Communication (AREA)
- General Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Studio Devices (AREA)
Abstract
The invention discloses a waterproof and dustproof unmanned aerial vehicle handpiece assembly which comprises a handpiece cabin shell, wherein a hatch opening of the handpiece cabin shell is upward and is provided with a handpiece cabin cover for covering the hatch opening, and a slope surface gradually lifted from front to back and downwards is formed on the lower surface of the handpiece cabin shell. The unmanned aerial vehicle is novel in concept, reasonable in design and convenient to use, and the front radar, the camera, the pipeline and the like are matched for arrangement through a special structure, so that good waterproof and dustproof effects are achieved, and the use safety of the unmanned aerial vehicle is guaranteed.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a waterproof and dustproof unmanned aerial vehicle head assembly.
Background
Unmanned aerial vehicle products, as a new thing, have been used to develop boxing feet in the practical application fields such as farm pesticide spraying, geographic mapping and aerial photography, and as for the application in other more fields, urgent needs to be tried and explored. Also, since the unmanned aerial vehicle is an emerging product, there are many defects in the design of the relevant parts of the product, which causes troubles and obstacles in practical application.
The electronic element of the unmanned aerial vehicle comprises a flight control system, a detection sensing system and a camera system, wherein a transmission system is an important component of the unmanned aerial vehicle, and the electronic element has the functions of controlling the unmanned aerial vehicle, detecting physical information, real-time image information, information postback ground and the like required by work such as obstacles and the like. The existing unmanned aerial vehicle is characterized in that required electronic elements are arranged inside a cabin of the unmanned aerial vehicle, and the cabin is internally provided with not only system elements but also signal lines and electric wires.
Because the use environment of the unmanned aerial vehicle is severe, the unmanned aerial vehicle can be used in rainy days, foggy days and environments with corrosive gas fog drop cages, and can also be used in some high-humidity environments, and therefore, the problems of water resistance and insulation of the system, particularly external hanging equipment, are solved.
Common unmanned aerial vehicle control system surveys the perception system, camera system, and transmission system all exposes or adds the shell protection in the electronic component periphery, even so, still can not avoid the exposed shortcoming of wire rod when connecting external module, and to unmanned aerial vehicle, waterproof dustproof is one of the important protection of safe flight.
Disclosure of Invention
In view of the defects that the related system of the existing unmanned aerial vehicle is exposed and protected by the protective shell, but the wire is still exposed, so that the waterproof and dustproof effects are poor, the invention provides the waterproof and dustproof unmanned aerial vehicle head assembly, and the waterproof and dustproof effects are good through the matching arrangement of the structure and the device.
The technical scheme of the invention is as follows: a waterproof and dustproof unmanned aerial vehicle head assembly comprises a head cabin, wherein a hatch of the head cabin is upward and is provided with a head cabin cover for covering the hatch, and a slope which gradually rises from front to back downwards is formed on the lower surface of the head cabin;
the aircraft nose cabin is provided with a front radar mounting position and a pipeline mounting position, the front radar mounting position is provided with a radar line through hole, the radar line through hole is arranged downwards, the pipeline mounting position is provided with a pipeline through hole, the pipeline through hole is arranged downwards, the front radar mounting position is provided with a front radar, and the radar mounting position is matched with the front radar in a shape fitting manner;
the camera cabin is provided with a groove-shaped camera mounting position, the notch of the camera mounting position faces forwards, the bottom of the camera mounting position is provided with a camera wiring through hole, the camera wiring through hole is arranged in the front-back direction, a camera is arranged on the camera mounting position, and the camera mounting position is matched with the shape of the camera in a fitting manner;
the joint of the machine head cabin shell and the machine head cabin cover is provided with a line hole, a protective soft rubber plug with a matched shape is clamped in the line hole, and the protective soft rubber plug is annular.
Further, preferably, a waterproof aviation plug is arranged at the pipeline through hole.
Further, as a preference, the number of the pipeline through holes is three, and correspondingly, the number of the waterproof aviation plugs is also three.
Further, as preferred, the aircraft nose cabin shell passes through the casing and projects downwards and forms pipeline installation position, just pipeline installation position department forms three faces that are the obtuse angle contained angle each other, and three pipeline through-hole establishes respectively one-to-one on three faces.
Further, preferably, the front radar mounting position forms an L-shaped radar contact surface, and the radar line through hole vertically penetrates through the contact surface upwards and extends into the engine head cabin shell.
Further, as preferred, be provided with the maintenance hole on the aircraft nose cabin shell behind the radar line through-hole, detachably is provided with on the aircraft nose cabin shell and is used for the closing cap maintenance hole apron in hole.
Further, preferably, the maintenance access cover plate is arranged on the nose cabin through an insertion structure.
Further, preferably, the nose cabin shell and the nose cabin cover are connected through a plug-in mounting structure.
Further, preferably, the number of the wire holes is two, and the two wire holes are respectively arranged at the left part and the rear part of the joint of the head cabin shell and the head cabin cover.
Has the advantages that: the unmanned aerial vehicle is novel in concept, reasonable in design and convenient to use, and the front radar, the camera, the pipeline and the like are matched for arrangement through a special structure, so that good waterproof and dustproof effects are achieved, and the use safety of the unmanned aerial vehicle is guaranteed.
Drawings
Fig. 1 is a schematic structural diagram of an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of an embodiment of the present invention from another angle.
Fig. 3 is an exploded view of an embodiment of the present invention.
Fig. 4 is an exploded view of another embodiment of the present invention.
Detailed Description
The invention is further illustrated by the following examples in conjunction with the accompanying drawings:
referring to fig. 1 to 4, a waterproof and dustproof unmanned aerial vehicle head assembly comprises a head cabin 1, wherein a hatch of the head cabin 1 faces upwards, a head cabin cover 2 for covering the hatch is arranged, and a slope surface gradually rising from front to back downwards is formed on the lower surface of the head cabin 1; the aircraft nose cabin shell 1 is provided with a front radar mounting position and a pipeline mounting position, the front radar mounting position is provided with a radar line through hole 1a, the radar line through hole 1a is arranged downwards, the pipeline mounting position is provided with a pipeline through hole 1b, the pipeline through hole 1b is arranged downwards, the front radar mounting position is provided with a front radar 8, and the radar mounting position is matched with the front radar 8 in a shape fitting manner; the camera cabin shell 1 is provided with a groove-shaped camera installation position, the notch of the camera installation position faces forwards, the bottom of the camera installation position is provided with a camera wiring through hole 1c, the camera wiring through hole 1c is arranged in the front-back direction, a camera 7 is arranged on the camera installation position, and the camera installation position is matched with the shape of the camera 7 in a fitting manner; the joint of the machine head cabin shell 1 and the machine head cabin cover 2 is provided with a wire hole 3, a protective soft rubber plug 4 with a matched shape is clamped in the wire hole 3, and the protective soft rubber plug 4 is annular.
In the basic scheme of the invention, related electronic devices and the like need to be arranged in the handpiece cabin shell 1, and a front radar 8 and a camera 7 are arranged in combination with actual shooting and navigation needs. For protection of the equipment inside the nacelle cover 1, a nacelle cover 2 is provided to cover the hatch of the nacelle cover 1. Because the engine head cabin shell 1 is of a shell-shaped structure, a cabin is formed at the upper part of the engine head cabin shell and used for accommodating corresponding devices, the volume of the cabin can be enlarged and the accommodation is convenient by gradually lifting downwards to form a slope surface from the front to the back through the lower surface of the engine head cabin shell 1. At the same time, the slope structure is convenient for the arrangement of the related devices in combination with the arrangement requirements of the related auxiliary devices (similar to radar and a camera, the arrangement direction of which needs to be forward). It should be noted that the slope is formed from front to back and gradually downward, which should be understood as a difference between front and back, and the slope is not formed upward, and is not to say, the slope is formed in a linear gradual manner from front to back. Leading radar 8 is arranged in unmanned aerial vehicle flight help to realize the navigation, because the setting of radar all needs corresponding cable, consequently needs to design corresponding contact position and set up the structure to satisfy waterproof and dirt-proof effect. In the scheme of the invention, the front radar 8 is arranged by arranging the front radar mounting position on the nose cabin shell 1, the radar line through hole 1a for penetrating the radar cable is arranged downwards, and the waterproof effect on rainwater and other water falling from top to bottom is good by combining the use scene characteristics of the unmanned aerial vehicle. Meanwhile, the structure and the appearance characteristics of the front radar 8 are combined, the radar mounting position and the front radar 8 are set to be in a shape matched with the shape, so that the front radar 8 is mounted on the nose cabin shell 1 more closely, a smaller gap is formed, and a good dustproof effect is achieved. Based on the same principle, the pipeline through hole 1b is arranged to penetrate through the pipeline, and a good waterproof effect is achieved. Based on same principle, set up camera 7 on the camera installation position, when satisfying the demand of walking the line through-hole 1c through the camera and walking the line, can also have fine waterproof and dustproof effect. In order to satisfy the needs that other circuit arranged, set up line hole 3 and lay wire to play waterproof and dirt-proof effect through protection soft plug 4, specifically the pipeline is through passing protection soft plug 4, and with 4 in close contact with of protection soft plug, and then realize waterproofly and dustproof.
In specific implementation, as a preferable technical scheme, a waterproof aviation plug 5 is arranged at the pipeline through hole 1 b. For better waterproofing, a waterproof aircraft plug 5 is provided.
In specific implementation, as a preferable technical solution, the number of the pipeline through holes 1b is three, and correspondingly, the number of the waterproof aviation plugs 5 is also three. The three pipeline through holes 1b are combined with actual conditions to meet more pipeline arrangement requirements.
In specific implementation, as an optimal technical scheme, the handpiece cabin shell 1 protrudes downwards through the shell to form the pipeline installation position, the pipeline installation position forms three surfaces which form obtuse included angles with each other, and the three pipeline through holes 1b are respectively and correspondingly arranged on the three surfaces. The preferred scheme provides a specific structural form of the pipeline installation position, so that three pipelines can be installed separately and do not interfere with each other.
In specific implementation, as a preferable technical scheme, the front radar mounting position forms an L-shaped radar contact surface, and the radar line through hole 1a vertically and upwards penetrates through the contact surface and extends into the nose cabin shell 1. In this preferred scheme, a concrete structural style of leading radar installation position has been given, and the radar that forms leans on the face to be used for laminating closely and set up leading radar 8, if use the horizon as the reference to and whole unmanned aerial vehicle is just putting, the radar of "L" font leans on a side to be the horizontal plane, and a side is vertical face. The radar line via 1a is provided at the level surface portion.
In specific implementation, as a preferable technical solution, a maintenance hole 1d is provided on the nacelle shell 1 behind the radar line through hole 1a, and a maintenance hole cover plate 6 for covering the maintenance hole 1d is detachably provided on the nacelle shell 1. In the preferred embodiment, the service hole 1d is used for installation and service of devices in the nacelle 1, such as a part of the radar that is arranged inside the nacelle 1. The maintenance hole cover plate 6 is provided to cover the maintenance hole 1d, and is waterproof and dustproof. In practical implementation, the maintenance hole 1d may be configured to be rectangular and have a relatively large size for convenient use.
In specific implementation, as a preferable technical solution, the maintenance hole cover plate 6 is arranged on the nose cabin shell 1 through a plug-in structure. The installation and the disassembly are more convenient by connecting, installing and maintaining the hole cover plate 6 through the plug-in mounting structure, and the quick disassembly and the quick assembly are realized.
In specific implementation, as a preferable technical scheme, the nose cabin shell 1 and the nose cabin cover 2 are connected through a plug-in structure. The aircraft nose cabin shell 1 and the aircraft nose cabin cover 2 are connected through a plug-in mounting structure, so that the installation and the disassembly of the aircraft nose cabin shell and the aircraft nose cabin cover are more convenient, and quick disassembly and quick assembly are realized.
In specific implementation, as a preferable technical solution, the number of the wire holes 3 is two, and the two wire holes 3 are respectively arranged at the left part and the rear part of the joint of the head cabin shell 1 and the head cabin cover 2. In the preferred embodiment, the string holes 3 are provided in two and in different orientations to facilitate the routing in various directions.
The foregoing detailed description of the preferred embodiments of the invention has been presented. It should be understood that numerous modifications and variations could be devised by those skilled in the art in light of the present teachings without departing from the inventive concepts. Therefore, the technical solutions available to those skilled in the art through logic analysis, reasoning and limited experiments based on the prior art according to the concept of the present invention should be within the scope of protection defined by the claims.
Claims (9)
1. The utility model provides a waterproof dirt-proof unmanned aerial vehicle aircraft nose assembly which characterized in that: the aircraft nose cabin comprises a nose cabin shell (1), wherein a hatch opening of the nose cabin shell (1) faces upwards, a nose cabin cover (2) used for covering the hatch opening is arranged, and a slope surface gradually lifted from front to back downwards is formed on the lower surface of the nose cabin shell (1);
the aircraft nose cabin shell (1) is provided with a front radar mounting position and a pipeline mounting position, the front radar mounting position is provided with a radar line through hole (1a), the radar line through hole (1a) is arranged downwards, the pipeline mounting position is provided with a pipeline through hole (1b), the pipeline through hole (1b) is arranged downwards, the front radar mounting position is provided with a front radar (8), and the radar mounting position is matched with the front radar (8) in a shape fit manner;
the camera cabin shell (1) is provided with a groove-shaped camera mounting position, the notch of the camera mounting position faces forwards, the bottom of the camera mounting position is provided with a camera wiring through hole (1c), the camera wiring through hole (1c) is arranged in the front-back direction, a camera (7) is arranged on the camera mounting position, and the camera mounting position is matched with the shape of the camera (7) in a fitting manner;
the machine head cabin cover is characterized in that a line hole (3) is formed in the joint of the machine head cabin shell (1) and the machine head cabin cover (2), a protective soft rubber plug (4) with a matched shape is clamped in the line hole (3), and the protective soft rubber plug (4) is annular.
2. The waterproof dustproof unmanned aerial vehicle aircraft nose assembly of claim 1, characterized in that: and a waterproof aviation plug (5) is arranged at the pipeline through hole (1 b).
3. The waterproof dustproof unmanned aerial vehicle aircraft nose assembly of claim 2, characterized in that: the number of the pipeline through holes (1b) is three, and correspondingly, the number of the waterproof aviation plugs (5) is also three.
4. The waterproof dustproof unmanned aerial vehicle aircraft nose assembly of claim 3, characterized in that: the aircraft nose cabin shell (1) passes through the casing and protrudes downwards and forms pipeline installation position, just pipeline installation position department forms three faces that are the obtuse angle contained angle each other, and is three pipeline through-hole (1b) are established respectively one-to-one on the three faces.
5. The waterproof dustproof unmanned aerial vehicle aircraft nose assembly of claim 1, characterized in that: leading radar installation position forms the radar that is "L" font and leans on the face, radar line through-hole (1a) is vertical to be passed up lean on the face and stretch into in aircraft nose cabin shell (1).
6. The waterproof dustproof unmanned aerial vehicle aircraft nose assembly of claim 1, characterized in that: the aircraft nose cabin shell (1) of radar line through-hole (1a) rear is last to be provided with maintenance hole (1d), detachably is provided with on aircraft nose cabin shell (1) and is used for the closing cap maintenance hole apron (6) of maintenance hole (1 d).
7. The waterproof dustproof unmanned aerial vehicle aircraft nose assembly of claim 6, characterized in that: the maintenance hole cover plate (6) is arranged on the engine head cabin shell (1) through an insertion structure.
8. The waterproof dustproof unmanned aerial vehicle aircraft nose assembly of claim 1, characterized in that: the aircraft nose cabin shell (1) and the aircraft nose cabin cover (2) are connected through a plug-in mounting structure.
9. The waterproof dustproof unmanned aerial vehicle aircraft nose assembly of claim 1, characterized in that: the number of the wire holes (3) is two, and the two wire holes (3) are respectively arranged at the left part and the rear part of the joint of the machine head cabin shell (1) and the machine head cabin cover (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911418918.7A CN111056005A (en) | 2019-12-31 | 2019-12-31 | Waterproof dirt-proof unmanned aerial vehicle aircraft nose assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911418918.7A CN111056005A (en) | 2019-12-31 | 2019-12-31 | Waterproof dirt-proof unmanned aerial vehicle aircraft nose assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111056005A true CN111056005A (en) | 2020-04-24 |
Family
ID=70305862
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911418918.7A Pending CN111056005A (en) | 2019-12-31 | 2019-12-31 | Waterproof dirt-proof unmanned aerial vehicle aircraft nose assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111056005A (en) |
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2019
- 2019-12-31 CN CN201911418918.7A patent/CN111056005A/en active Pending
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Application publication date: 20200424 |
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| WD01 | Invention patent application deemed withdrawn after publication |