CN207141380U - A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure - Google Patents
A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure Download PDFInfo
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- CN207141380U CN207141380U CN201720835882.2U CN201720835882U CN207141380U CN 207141380 U CN207141380 U CN 207141380U CN 201720835882 U CN201720835882 U CN 201720835882U CN 207141380 U CN207141380 U CN 207141380U
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 4
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 4
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000010276 construction Methods 0.000 abstract description 2
- 230000004308 accommodation Effects 0.000 description 3
- 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
- 230000005611 electricity Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005194 fractionation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
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- 238000003032 molecular docking Methods 0.000 description 1
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Abstract
The utility model discloses a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure, including latch, spacing, the sleeve that latches guide rail, fulcrum A, fuselage socket, fulcrum B, horn liner, horn socket, horn, horn；The lock, lock guide rail, fulcrum A, fuselage socket, fulcrum B are arranged on fuselage central plate, and fuselage central plate is provided with installation fulcrum A, fulcrum B screw hole position；The horn liner, horn socket, horn are spacing, sleeve is arranged on horn；The horn is 25mm diameter carbon pipes, is fixedly connected with horn liner；It is spacing that horn is cased with the horn, horn is spacing to pass through sleeve connection with fulcrum B.The horn quick-disassembly structure has monoblock type Quick Release ability, greatly reduces the storage volume needed for multi-rotor unmanned aerial vehicle, is convenient for carrying transport, while ensure development rate, it is not necessary to assist to install using instrument, it is simple in construction, and it is easy to maintenance.
Description
Technical field
It the utility model is related to multi-rotor unmanned aerial vehicle field, more particularly to a kind of multi-rotor unmanned aerial vehicle horn Quick Release knot
Structure.
Background technology
Common flight device is divided into fixed-wing, helicopter and more rotors (four rotors main flow the most), in recent years in, because excellent
Handling, more rotors rapidly become the nova taken photo by plane with model plane Sports Field.At present, more rotors have become microminiature without
Man-machine or model plane main flows.Because unmanned plane transition needs compact car to transport, for convenience of transporting, miniature nothing of the wheelbase in 1m or so
The man-machine main trend as current industry.In existing miniature multi-rotor unmanned aerial vehicle, when its wheelbase reaches 1m or so, for convenience
House, collapsible horn is often the first choice of this kind of type, considers directly to consolidate horn and frame for protection there is also part
It is fixed, it is non-dismountable, and the containing box of these types is larger, can not deposit in the less compact car of part boot.
For existing miniature multi-rotor unmanned aerial vehicle, there is provided the overall flight control system component of the work flight control of source blade
Size is little, even if the size including electrokinetic cell will not still take too many volume, and its lift space is then whole more rotations
The part most to be taken up space on wing unmanned plane, for wheelbase is in 1m or so multi-rotor unmanned aerial vehicle, horn is fixed on nothing in frame
A large amount of accommodation spaces will be taken by doubting, and to avoid influence of the horn vertical vibration to fold mechanism, collapsible horn is often using vertical
To the form of folding, and this folding mode, due to horn length, foot stool highly will have to increase, and this causes fuselage
Certain space is wasted in height；For aerial survey field, not photograph foot stool, it is necessary to reduce as far as possible when ensureing camera shooting
Height of the camera in unmanned plane, to ensure that camera is sufficiently low after the increasing of foot stool, the mounting bracket of fixed camera also needs to lengthen,
This can cause unnecessary weightening.Therefore, it is necessary to which a kind of structure, ensures that horn is not take up accommodation space in all directions, together
When, this structure can not influence the convenience that unmanned plane uses.
Utility model content
In view of this, the utility model design completes a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure.
The utility model is solved the above problems by following technological means：
A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure, including supporting plate, fulcrum, fuselage socket, fulcrum B, horn,
Horn is spacing, sleeve；The fulcrum A, fulcrum B are connected by screw with supporting plate；The horn sequentially passes through what is be arranged in parallel
Fulcrum A, fulcrum B circular hole, and the inner surface of fuselage socket is withstood on, fuselage socket is connected by screw with fulcrum A；It is described
It is spacing that horn is cased with horn, horn is spacing to be connected with fulcrum B by sleeve connection, fulcrum B with bush whorl.
Further, the sleeve is provided with locking buckle, and locking buckle is provided with oblique angle, and adjacent oblique angle forms neck；Branch
Fagging connecting fulcrum B one end is provided with lock guide rail, and lock guide rail is flexibly connected with lock, and the hook that lock is provided with is stuck in card
In groove.
Further, the horn is spacing is provided with spacing preiection, and fulcrum B is provided with recessed with spacing preiection mating connection
Groove.
Further, the horn is 25mm diameter carbon pipes, and horn is fixedly connected with horn liner.
Further, for the lock with lock guide rail by 4mm compression springs interval, fulcrum A, fulcrum B are aluminium alloy material
Material, is connected by M2.5 screws with fuselage central plate.
Further, the fuselage socket is connected by M2 screws with fulcrum A, the 4mm diametric holes peace of fuselage socket
Fill XT60 plugs, 1mm diametric holes installation XH2.54 sockets.
Further, the horn liner is connected by M2 screws with horn socket, the 4mm diameters of horn socket
Hole is installed by XT60 plugs, 1mm diametric holes installation XH2.54 sockets.
A kind of multi-rotor unmanned aerial vehicle of the present utility model is had the advantages that with horn quick-disassembly structure：The quick-disassembly structure
With monoblock type Quick Release ability, the storage volume needed for multi-rotor unmanned aerial vehicle is greatly reduced, transport is convenient for carrying, ensures simultaneously
Development rate, it is not necessary to assist to install using instrument, it is simple in construction, it is easy to maintenance.
Brief description of the drawings
In order to illustrate more clearly of the technical solution of the utility model, below by embodiment it is required use it is attached
Figure is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the present utility model, for
For those of ordinary skill in the art, on the premise of not paying creative work, other can also be obtained according to these accompanying drawings
Accompanying drawing.
Fig. 1 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure overall structure diagram of the utility model；
Fig. 2 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure fractionation structural representation；
Fig. 3 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure fulcrum A front views of the utility model；
Fig. 4 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure fuselage socket top view of the utility model；
Fig. 5 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure fulcrum B front views of the utility model；
Fig. 6 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure lock guide rail top view of the utility model；
Fig. 7 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure lock front view of the utility model；
Fig. 8 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure horn liner front view of the utility model；
Fig. 9 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure horn socket top view of the utility model；
Figure 10 is a kind of spacing front view of multi-rotor unmanned aerial vehicle horn quick-disassembly structure horn of the utility model；
Figure 11 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure sleeve front view of the utility model；
In figure：1. lock；11. hook；2. supporting plate；21. latch guide rail；3. fulcrum A；4. fuselage socket；5. fulcrum
B；51. groove；6. horn liner；7. horn socket；8. horn；9. spacing collar；91. spacing preiection；10. sleeve；It is 101. anti-
Loose buckle；102. oblique angle.
Embodiment
The utility model is described in detail with reference to the accompanying drawings and examples.
Embodiment
As depicted in figs. 1 and 2, a kind of multi-rotor unmanned aerial vehicle is divided into two parts with horn quick-disassembly structure, wherein lock 1, branch
Fagging 2, lock guide rail 21, fulcrum A3, fuselage socket 4, fulcrum B5 are arranged on fuselage central plate, and fuselage central plate needs basis
Fulcrum A3, fulcrum B5 mounting hole site design relevant position, fulcrum A3, fulcrum B5 are sequentially provided with the coaxial circular hole of center line, and
Pass through screw connection with supporting plate 2；Horn liner 6, horn socket 7, horn are spacing 9, sleeve 10 is arranged on horn 8, machine
Arm 8 need to use 25mm diameter carbon pipes, need to be fixed according to the mounting hole site reserved location of horn liner 6, and with horn liner 6
Connect, be cased with horn spacing 9 on horn 8, horn spacing 9 and fulcrum B5 are connected by sleeve 10；The fulcrum A3, fulcrum B5,
Horn liner 6, horn 8, horn are spacing 9, the center line of sleeve 10 is coaxial；The horn 8 sequentially pass through be arranged in parallel fulcrum A3,
Fulcrum B5 circular hole, and the inner surface of fuselage socket 4 is withstood on, fuselage socket 4 is connected by screw with fulcrum A3；It is described
Horn spacing 9 is provided with spacing preiection 91, and fulcrum B5 is provided with the groove 51 being connected with spacing preiection 91.
As shown in Figure 3 and Figure 5, fulcrum A3, fulcrum B5 are provided with four screw hole positions, using M2.5 screws and fuselage central plate
It is connected；As shown in Figure 6 and Figure 7, the top of lock 1 is provided with spanner, and 4mm compression bullets are installed while fulcrum A3, fulcrum B5 is installed
Spring, 4mm compression springs interval is then used between lock 1 and lock guide rail 21, is flexibly connected；Fulcrum B5 passes through screw thread and sleeve 10
Connection, sleeve 10 are provided with locking buckle 101, and locking buckle 101 is provided with oblique angle 102, and adjacent oblique angle 102 forms neck, lock
Button hook 11 is stuck in neck.
As shown in figure 4, the symmetrical four a diameter of 2.1mm in four angles of fuselage socket 4 hole, will with M2 screws
It is connected with fulcrum A3, and two 4mm diametric holes of fuselage socket 4 are distributed in symmetry axis both sides up and down, install XT60 plugs, left
The symmetrical 6 1mm diametric holes of right septum 6mm, XH2.54 sockets are installed.
As shown in figure 9, two a diameter of 2.1mm of the symmetrical distribution in the axis of horn socket 7 hole, will with M2 screws
It is connected with horn liner 6, and two 4mm diametric holes of horn socket 7 are distributed in symmetry axis both sides up and down, and installation XT60 is inserted
Head, between left and right every the symmetrical 6 1mm diametric holes installation XH2.54 sockets of 6mm.
As shown in figs, the end of horn 8 is provided with front and rear symmetrical two counter sinks, by M3 countersunk head screws through pre-
Position box out by horn liner 6 and 9 spacing fixation of horn, before fixing, as shown in figure 11, sleeve 10 need to be first enclosed on
Horn 8 is inserted in fulcrum B5 on horn 8, during use, machine after the guide rail on horn spacing 9 is aligned with the groove reserved on fulcrum B5
Arm 8 can continue into, horn 8 reach it is spacing plug is completed to connect simultaneously simultaneously, sleeve 10 and fulcrum B5 is connected by screw thread
Connect, while sleeve 10 is tightened, lock 1 is automatic locking due to spring effect；During dismounting, lock 1 is promoted away from spacing, set
Cylinder 10 can rotate, and complete dismounting,
The requires of the utility model multi-rotor unmanned aerial vehicle frame structure is at least bilayer, and motor, blade, electricity are adjusted, horn 8 is used as one
Individual entirety dismounts together；Make corresponding aluminium alloy perforate part, fulcrum A3, fulcrum B5, while fulcrum is installed as horn 8,
Frame bulk strength and rigidity requirement are undertaken, is conducted oneself with dignity to mitigate, while ensures the rigidity of horn 8, fulcrum A3, fulcrum B5 are 2 shapes
Formula, ensure a certain distance between two parts；Installation fuselage socket 4 is added on the part of frame central, is a kind of
Location-plate with Quick Release plug, ensure horn 8 while installation, the electricity on horn 8 adjusts set related in the frame of center
It is standby to complete docking；Spacing part on horn 8 is horn spacing 9, and is provided with groove 91, ensures that horn 8 accurately slips into installation position
Put, fuselage socket 4 can also be docked accurately, and horn 8 is threadedly coupled with frame using sleeve 10, and sleeve 10 can directly pass through people
The mode that work screws manually is installed in place, while locking card 101 is designed with sleeve 10, directly avoids horn sleeve due to horn
8 vibrations cause thread looseness, the subsidiary oblique angle 102 of locking buckle 101, ensure only to need turnbarrel 10 during installation, install
After the completion of, lock 1 will be locked automatically, be stuck in the groove that adjacent oblique angle 102 is formed, and during dismounting, promotes latch 1 manually, revolve simultaneously
Twisting sleeve 10 can complete to dismantle.
Compared with existing power is set with, the beneficial effects of the utility model are：The utility model provides a kind of do not need
The responsible horn quick-disassembly structure form of additional means, can be rapidly completed the expansion and storage of related multi-rotor unmanned aerial vehicle, reduce
The accommodation space of related type, meanwhile, structure and using simple, easy to maintenance.
Finally it should be noted that：Above example is only to illustrate the technical solution of the utility model, rather than its limitations；
Although the utility model is described in detail with reference to the foregoing embodiments, it will be understood by those within the art that：
It can still modify to the technical scheme described in foregoing embodiments, or which part technical characteristic is carried out etc.
With replacement；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the utility model technology
The spirit and scope of scheme.
Claims (7)
- A kind of 1. multi-rotor unmanned aerial vehicle horn quick-disassembly structure, it is characterised in that：Inserted including supporting plate (2), fulcrum A (3), fuselage Seat board (4), fulcrum B (5), horn (8), horn spacing (9), sleeve (10)；The fulcrum A (3), fulcrum B (5) by screw with Supporting plate (2) connects；The horn (8) sequentially passes through the fulcrum A (3) be arrangeding in parallel, fulcrum B (5) circular hole, and withstands on fuselage The inner surface of socket (4), fuselage socket (4) are connected by screw with fulcrum A (3)；Horn limit is cased with the horn (8) Position (9), horn spacing (9) are connected with fulcrum B (5) by sleeve (10), and fulcrum B (5) is threadedly coupled with sleeve (10).
- A kind of 2. multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 1, it is characterised in that the sleeve (10) locking buckle (101) is provided with, locking buckle (101) is provided with oblique angle (102), and adjacent oblique angle (102) forms neck；Support Plate (2) connecting fulcrum B (5) one end is provided with lock guide rail (21), and lock guide rail (21) is flexibly connected with lock (1), is latched (1) The hook (11) being provided with is stuck in neck.
- A kind of 3. multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 1, it is characterised in that the horn limit Position (9) is provided with spacing preiection (91), and fulcrum B (5) is provided with the groove (51) being connected with spacing preiection (91).
- A kind of 4. multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 1, it is characterised in that the horn (8) it is 25mm diameter carbon pipes, horn (8) is fixedly connected with horn liner (6).
- A kind of 5. multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 2, it is characterised in that the lock (1) with lock guide rail (21) by 4mm compression springs interval, fulcrum A (3), fulcrum B (5) are aluminum alloy materials, pass through M2.5 spiral shells Silk is connected with fuselage central plate.
- 6. a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 1, it is characterised in that the fuselage is inserted Seat board (4) is connected by M2 screws with fulcrum A (3), the 4mm diametric holes installation XT60 plugs of fuselage socket (4), 1mm diameters Hole is installed by XH2.54 sockets.
- 7. a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 4, it is characterised in that in the horn Lining (6) is connected by M2 screws with horn socket (7), the 4mm diametric holes installation XT60 plugs of horn socket (7), and 1mm is straight Footpath hole is installed by XH2.54 sockets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720835882.2U CN207141380U (en) | 2017-07-11 | 2017-07-11 | A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720835882.2U CN207141380U (en) | 2017-07-11 | 2017-07-11 | A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure |
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| Publication Number | Publication Date |
|---|---|
| CN207141380U true CN207141380U (en) | 2018-03-27 |
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| CN201720835882.2U Active CN207141380U (en) | 2017-07-11 | 2017-07-11 | A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229350A (en) * | 2017-07-11 | 2019-01-18 | 上海伯镭智能科技有限公司 | A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure |
| CN113665785A (en) * | 2021-08-11 | 2021-11-19 | 西安羚控电子科技有限公司 | Hang up fixed wing unmanned aerial vehicle |
| CN114537637A (en) * | 2022-04-22 | 2022-05-27 | 北京卓翼智能科技有限公司 | A fixing device and unmanned aerial vehicle for unmanned aerial vehicle horn |
-
2017
- 2017-07-11 CN CN201720835882.2U patent/CN207141380U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229350A (en) * | 2017-07-11 | 2019-01-18 | 上海伯镭智能科技有限公司 | A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure |
| CN113665785A (en) * | 2021-08-11 | 2021-11-19 | 西安羚控电子科技有限公司 | Hang up fixed wing unmanned aerial vehicle |
| CN114537637A (en) * | 2022-04-22 | 2022-05-27 | 北京卓翼智能科技有限公司 | A fixing device and unmanned aerial vehicle for unmanned aerial vehicle horn |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210302 Address after: 028000 Dianchang street, Tongliao Economic and Technological Development Zone, Inner Mongolia Autonomous Region Patentee after: Tongliao Tongfa new energy Co.,Ltd. Address before: Room 401-01, building 1, No. 800, Naxian Road, China (Shanghai) pilot Free Trade Zone, Pudong New Area, Shanghai, 200120 Patentee before: SHANGHAI BOONRAY INTELLIGENT TECHNOLOGY Co.,Ltd. |
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| TR01 | Transfer of patent right |