CN208484836U - The more hanging point structures of unmanned plane - Google Patents
The more hanging point structures of unmanned plane Download PDFInfo
- Publication number
- CN208484836U CN208484836U CN201820515848.1U CN201820515848U CN208484836U CN 208484836 U CN208484836 U CN 208484836U CN 201820515848 U CN201820515848 U CN 201820515848U CN 208484836 U CN208484836 U CN 208484836U
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- China
- Prior art keywords
- carbon plate
- carry
- carry carbon
- unmanned plane
- fixing buckle
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 170
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 170
- 238000000034 method Methods 0.000 abstract description 6
- 238000010586 diagram Methods 0.000 description 3
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Abstract
The utility model discloses a kind of more hanging point structures of unmanned plane, belongs to air vehicle technique field, including being fixed on the fuselage bottom carbon plate of uav bottom and and being fixed on the carry carbon plate matched on the carbon plate of the fuselage bottom with fuselage bottom carbon plate.It realizes single unmanned plane while carrying multiple tasks load, improve working efficiency when unmanned plane carries out multiple-task；The fixation of carry carbon plate has double shield, and front, rear, left and right ensure the fixation of carry carbon plate and mission payload in all directions, ensure that stability when safety and the unmanned plane during flying when UAV flight's mission payload works；It can be realized being rapidly assembled and disassembled for load and fuselage bottom carbon plate, and there is ease for operation；Loading tasks load only needs to install carry carbon plate, thus the problem of avoiding fixed screw service life on body well.
Description
Technical field
The utility model belongs to air vehicle technique field, specifically a kind of more hanging point structures of unmanned plane.
Background technique
As global unmanned plane industry development is persistently raised speed, will be used wider and wider for unmanned plane is general.And different extension
It carries module and provides different functions to unmanned plane, greatly extend the application range of unmanned plane, apply unmanned plane
In different fields.For example, the unmanned plane of carry high-definition digital video camera and camera, along power grid can position and independently patrol
Boat, real-time transmission filmed image realize the purpose of electric inspection process；Nobody of carry catalyst flusher and meteorological detecting devices
Machine is sprayed in the sky, eliminates haze within a certain area, realizes the purpose of environmental improvement；Carry thermal camera nobody
The tasks such as night investigation may be implemented in machine.Unmanned machine operation on the market only carries a kind of mission payload at present, leads to unmanned plane
It has a single function, and just needs multiple UAVs or unmanned plane repeatedly to fly in the operating environment for needing multiple functions.And it is more
The mission payload of number unmanned planes is to be fixed on unmanned plane using integral type or by screw to need single unmanned plane to execute a variety of
It needs to disassemble and install mission payload with tool when task.Screw can wear skidding, unmanned plane during flying after being used for multiple times
The high-frequency vibration generated under state can make loosened screw that mission payload be caused to fall, and use screw pinned task load
The a large amount of disassembly set-up time can be expended.For these disadvantages, it is necessary to it is more to propose that one kind can be such that unmanned plane disposably carries
The quick carry component of a mission payload.
Utility model content
To solve the above problems existing in the prior art, the utility model provides a kind of more hanging point structures of unmanned plane.
The technical solution of the utility model is as follows: a kind of more hanging point structures of unmanned plane, including being fixed on uav bottom
Fuselage bottom carbon plate and and it is fixed on the carry carbon plate matched on the carbon plate of the fuselage bottom with fuselage bottom carbon plate.
Further, fuselage bottom carbon plate includes carry carbon plate fixing buckle, is had on the carry carbon plate and carry carbon plate
The corresponding carry carbon plate fixing buckle aperture of fixing buckle.
Further, fuselage bottom carbon plate includes carry carbon plate fixing buckle screw, and the carry carbon plate fixing buckle is by hanging
Carbon plate fixing buckle screw is carried to be fixed on the carbon plate of the fuselage bottom.
Further, the carry carbon plate fixing buckle is stepped cylindrical shape, the carry carbon plate fixing buckle hole shape
For small one and large one circle intersection, the axis of great circle of the carry carbon plate fixing buckle aperture is greater than the big straight of the carry carbon plate fixing buckle
Diameter end, the axis of small circle of the carry carbon plate fixing buckle aperture are greater than the smaller diameter end of the carry carbon plate fixing buckle and are less than institute
State the larger diameter end of carry carbon plate fixing buckle.
Further, fuselage bottom carbon plate includes the lock aperture of carry carbon plate, includes carry carbon on the carry carbon plate
Plate lock, the carry carbon plate lock can stick into the lock aperture of carry carbon plate.
Further, carry carbon plate further includes carry carbon plate lock elastic slice, carry carbon plate lock elastic slice fluting, the carry
Carbon plate latches three faces fluting and separates with the carry carbon plate, and the carry carbon plate lock latches fixed countersunk head screw by carry carbon plate
It is connected on the carry carbon plate lock elastic slice, the carry carbon plate lock elastic slice is connected on carry carbon plate.
Further, there are multiple regions surrounded by the carry carbon plate fixing buckle, Mei Gequ on the carbon plate of the fuselage bottom
There are several carry carbon plate fixing buckles in domain, makes single unmanned plane that can carry multiple tasks load simultaneously.
Further, there are 3 rectangles surrounded by the carry carbon plate fixing buckle, each rectangle on the carbon plate of the fuselage bottom
There are 4 carry carbon plate fixing buckles, makes single unmanned plane that can at most carry 3 mission payloads simultaneously.
Further, each load is equipped with the carry carbon plate (9).
Further, the central axis of fuselage bottom carbon plate is equipped with 4 carry carbon plates and latches aperture.
The beneficial effects of the utility model are:
(1) it can be realized single unmanned plane while carrying multiple tasks load, when improving unmanned plane progress multiple-task
Working efficiency.
(2) fixation of carry carbon plate has double shield, and front, rear, left and right ensure that carry carbon plate and task carry in all directions
The fixation of lotus ensure that stability when safety and the unmanned plane during flying when UAV flight's mission payload works.
(3) after mission payload installs carry carbon plate, the process that entire mission payload carries only needs two steps that can take
It carries and completes, process is simple and fast, can be realized being rapidly assembled and disassembled for load and fuselage bottom carbon plate, and with easy to operate
Property.
(4) carry carbon plate light weight, it is at low cost, it is small in size, it does not need often to dismantle later on being installed to mission payload,
Loading tasks load only needs to install carry carbon plate, thus the problem of avoiding fixed screw service life on body well.
Detailed description of the invention
Fig. 1 is the utility model overall structure diagram；
Fig. 2 is the structural schematic diagram of Fig. 1 middle fuselage bottom carbon plate 1；
Fig. 3 is the structural schematic diagram of carry carbon plate 9 in Fig. 1.
In figure: 1, fuselage bottom carbon plate, 2, carry carbon plate latch aperture, 3, carry carbon plate fixing buckle, 4, carry carbon plate fixes
Detain screw, 5, carry carbon plate lock, 6, carry carbon plate lock elastic slice, 7, carry carbon plate lock elastic slice fluting, 8, carry carbon plate lock
Detain fixed countersunk head screw, 9, carry carbon plate, 10, carry carbon plate fixing buckle aperture.
Specific embodiment
The present invention will be further explained below with reference to the attached drawings.
As shown in Figure 1, the more hanging point structures of unmanned plane provided by the embodiment of the utility model include being fixed on uav bottom
Fuselage bottom carbon plate 1 and and be fixed on the carry carbon plate matched on fuselage bottom carbon plate 1 with fuselage bottom carbon plate 1
9。
Referring to figure 2. and Fig. 3, further, fuselage bottom carbon plate 1 includes carry carbon plate fixing buckle 3, the carry carbon
There is carry carbon plate fixing buckle aperture 10 corresponding with carry carbon plate fixing buckle 3 on plate 9.
Further, fuselage bottom carbon plate 1 include carry carbon plate fixing buckle screw 4, the carry carbon plate fixing buckle 3 by
Carry carbon plate fixing buckle screw 4 is fixed on fuselage bottom carbon plate 1.
Further, the carry carbon plate fixing buckle 3 is stepped cylindrical shape, 10 shape of carry carbon plate fixing buckle aperture
Shape is small one and large one circle intersection, and the axis of great circle of the carry carbon plate fixing buckle aperture 10 is greater than the carry carbon plate fixing buckle 3
Larger diameter end, the axis of small circle of the carry carbon plate fixing buckle aperture 10 is greater than the minor diameter of the carry carbon plate fixing buckle 3
End and the larger diameter end for being less than the carry carbon plate fixing buckle 3.
Further, fuselage bottom carbon plate 1 includes that carry carbon plate latches aperture 2, includes carry on the carry carbon plate 9
Carbon plate lock 5, the carry carbon plate lock 5 can stick into the lock aperture 2 of carry carbon plate.
Further, carry carbon plate 9 further includes that carry carbon plate latches elastic slice 6, carry carbon plate lock elastic slice fluting 7, described
Carry carbon plate latches 5 three faces fluting and separates with the carry carbon plate 9, and the carry carbon plate lock 5 is latched by carry carbon plate to be fixed
Countersunk head screw 8 is connected on the carry carbon plate lock elastic slice 6, and the carry carbon plate lock elastic slice 6 is connected to carry carbon plate 9
On.
Further, there are multiple regions surrounded by the carry carbon plate fixing buckle 3 on fuselage bottom carbon plate 1, each
There are several carry carbon plate fixing buckles 3 in region, makes single unmanned plane that can carry multiple tasks load simultaneously.
Further, there are 3 rectangles surrounded by the carry carbon plate fixing buckle 3, Mei Geju on fuselage bottom carbon plate 1
Shape has 4 carry carbon plate fixing buckles 3, makes single unmanned plane that can at most carry 3 mission payloads simultaneously.
Further, each load is equipped with the carry carbon plate 9.
Further, the central axis of fuselage bottom carbon plate 1 is equipped with 4 carry carbon plates and latches aperture 2.
It is used to prevent in use, the carry carbon plate fixing buckle aperture 10 on carry carbon plate 9 is first sticked into carry carbon plate fixing buckle 3
Only carry carbon plate moving left and right and falls.It is mobile then up to allow carry carbon plate lock 5 to block carry carbon plate lock and open 2 to prevent
The back-and-forth motion of carry carbon plate 9.Two steps are only needed just to complete the carrying of mission payload, it is convenient and efficient.
It should be noted that term " on ", "lower", "front", "rear", "left", "right" etc. in the description of the present invention,
The orientation or positional relationship of instruction is to be merely for convenience of retouching based on the orientation or positional relationship under utility model works state
State the utility model and simplify description, rather than the device or element of indication or suggestion meaning must have a particular orientation, with
Specific orientation construction and operation, therefore should not be understood as limiting the present invention.
Combine specific embodiment that the utility model is described in detail above.But it is to be understood that, these
Specific embodiment is only the illustrative explanations to the utility model, does not constitute any limit to the protection scope of the utility model
System.It, can be to the utility model technology contents and its implementation without departing from the spirit of the present invention and protection scope
Mode carries out various improvement, equivalencing or modification, these each fall in the protection scope of the utility model.The utility model
Protection scope is determined by the appended claims.
Claims (9)
1. a kind of more hanging point structures of unmanned plane, which is characterized in that including be fixed on uav bottom fuselage bottom carbon plate (1) and
And it is fixed on the carry carbon plate (9) matched on fuselage bottom carbon plate (1) with fuselage bottom carbon plate (1), the fuselage
Bottom carbon plate (1) includes carry carbon plate fixing buckle (3), is had on the carry carbon plate (9) corresponding with carry carbon plate fixing buckle (3)
Carry carbon plate fixing buckle aperture (10).
2. the more hanging point structures of unmanned plane as described in claim 1, which is characterized in that fuselage bottom carbon plate (1) includes carry
Carbon plate fixing buckle screw (4), the carry carbon plate fixing buckle (3) are fixed on the fuselage by carry carbon plate fixing buckle screw (4)
On bottom carbon plate (1).
3. the more hanging point structures of unmanned plane as described in claim 1, which is characterized in that the carry carbon plate fixing buckle (3) is rank
Terraced cylindrical shape, carry carbon plate fixing buckle aperture (10) shape are small one and large one circle intersection, the carry carbon plate fixing buckle
The axis of great circle of aperture (10) is greater than the larger diameter end of the carry carbon plate fixing buckle (3), the carry carbon plate fixing buckle aperture
(10) axis of small circle is greater than the smaller diameter end of the carry carbon plate fixing buckle (3) and is less than the carry carbon plate fixing buckle (3)
Larger diameter end.
4. the more hanging point structures of unmanned plane as described in claim 1, which is characterized in that fuselage bottom carbon plate (1) includes carry
Carbon plate latches aperture (2), includes carry carbon plate lock (5) on the carry carbon plate (9), and the carry carbon plate lock (5) can block
Aperture (2) are latched into carry carbon plate.
5. the more hanging point structures of unmanned plane as claimed in claim 4, which is characterized in that further include carry carbon plate lock elastic slice (6),
Carry carbon plate latches elastic slice fluting (7), and the carry carbon plate latches (5) three faces fluting and separates with the carry carbon plate (9), described
Carry carbon plate latches (5) and is connected on carry carbon plate lock elastic slice (6) by carry carbon plate lock fixed countersunk head screw (8),
Carry carbon plate lock elastic slice (6) is connected on carry carbon plate (9).
6. the more hanging point structures of unmanned plane as claimed in claim 5, which is characterized in that have on fuselage bottom carbon plate (1) multiple
There are several carry carbon plate fixing buckles (3) in the region surrounded by the carry carbon plate fixing buckle (3), each region, make list
A unmanned plane can carry multiple tasks load simultaneously.
7. the more hanging point structures of unmanned plane as claimed in claim 6, which is characterized in that have on fuselage bottom carbon plate (1) 3 by
The rectangle that the carry carbon plate fixing buckle (3) surrounds, each rectangle have 4 carry carbon plate fixing buckles (3), make it is single nobody
Machine can at most carry 3 mission payloads simultaneously.
8. the more hanging point structures of unmanned plane as claimed in claims 6 or 7, which is characterized in that each load is equipped with the carry
Carbon plate (9).
9. the more hanging point structures of unmanned plane as claimed in claim 4, which is characterized in that the central axis of fuselage bottom carbon plate (1)
It is equipped with 4 carry carbon plates and latches aperture (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820515848.1U CN208484836U (en) | 2018-04-12 | 2018-04-12 | The more hanging point structures of unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820515848.1U CN208484836U (en) | 2018-04-12 | 2018-04-12 | The more hanging point structures of unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208484836U true CN208484836U (en) | 2019-02-12 |
Family
ID=65252123
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820515848.1U Expired - Fee Related CN208484836U (en) | 2018-04-12 | 2018-04-12 | The more hanging point structures of unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208484836U (en) |
-
2018
- 2018-04-12 CN CN201820515848.1U patent/CN208484836U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190620 Address after: 100096 West Building, 1126 Yard, 12 Zhonglu Building Materials City, Haidian District, Beijing Patentee after: ZHONGYU HANGTONG (BEIJING) TECHNOLOGY Co.,Ltd. Address before: 101200 Ma Fang Industrial Park, Zhongguancun Science and Technology Park, Pinggu District, Beijing, No. 17, Area 2 Patentee before: BEIJING YIJIA ZHUOYANG TECHNOLOGY CO.,LTD. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190816 Address after: 101200 Block 1-2, E15, Mafang Industrial Park, Pinggu District, Beijing Patentee after: China Aerospace Enterprise Management (Beijing) Co.,Ltd. Address before: 100096 West Building, 1126 Yard, 12 Zhonglu Building Materials City, Haidian District, Beijing Patentee before: ZHONGYU HANGTONG (BEIJING) TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 101200 Block 1-2, E15, Mafang Industrial Park, Pinggu District, Beijing Patentee after: China Aerospace (Beijing) Aviation Group Co.,Ltd. Address before: 101200 Block 1-2, E15, Mafang Industrial Park, Pinggu District, Beijing Patentee before: Zhongyutong enterprise management (Beijing) Group Co.,Ltd. Address after: 101200 Block 1-2, E15, Mafang Industrial Park, Pinggu District, Beijing Patentee after: Zhongyutong enterprise management (Beijing) Group Co.,Ltd. Address before: 101200 Block 1-2, E15, Mafang Industrial Park, Pinggu District, Beijing Patentee before: China Aerospace Enterprise Management (Beijing) Co.,Ltd. |
|
| CP01 | Change in the name or title of a patent holder | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190212 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |