CN206984345U - A kind of multi-rotor unmanned aerial vehicle cantilever locking system - Google Patents
A kind of multi-rotor unmanned aerial vehicle cantilever locking system Download PDFInfo
- Publication number
- CN206984345U CN206984345U CN201720900673.1U CN201720900673U CN206984345U CN 206984345 U CN206984345 U CN 206984345U CN 201720900673 U CN201720900673 U CN 201720900673U CN 206984345 U CN206984345 U CN 206984345U
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- CN
- China
- Prior art keywords
- cantilever
- locking
- lockup arm
- fuselage
- aerial vehicle
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
The utility model discloses a kind of multi-rotor unmanned aerial vehicle cantilever locking system,Including device body,Described device body is made up of lockup arm and locking knob,And the quantity of the lockup arm and the locking knob is corresponding with the quantity of cantilever,One end of the lockup arm is provided with two clamping plates,And the lockup arm is fixedly connected with clamping plate every piece described by nut and pad,The other end insertion of the lockup arm is arranged in the fixed plate of fuselage roof,And the fixed plate is closely connected with the lockup arm by locking knob,One end of the cantilever is fixedly connected with the fuselage,The other end of the cantilever is provided with flabellum,And the flabellum is flexibly connected with the cantilever by rotating shaft,The cantilever locking system is by the lockup arm come locking cantilever,And by the locking knob come the state of lockup arm described in locking,So that the cantilever has dual safety locking guarantee,Improve unmanned plane during flying security,It is and simple to operate detachable.
Description
Technical field
Unmanned air vehicle technique field is the utility model is related to, specially a kind of multi-rotor unmanned aerial vehicle cantilever locking system.
Background technology
Referred to as " unmanned plane ", english abbreviation is " UAV " to UAV, using radio robot and is carried
The not manned aircraft that presetting apparatus manipulates.It can be divided into from technical standpoint definition：Unmanned fixed-wing aircraft, unmanned VTOL
Machine, depopulated helicopter, unmanned multi-rotor aerocraft, unmanned parasol etc..Multi-rotor unmanned aerial vehicle, be it is a kind of have three and more than
Cantilever, the special pilotless helicopter of rotor shaft is provided with each cantilever.Its by the motor rotation on each axle,
Rotor is driven, so as to produce a liter thrust.Rotor always away from fixation, it is variable like that rather than general helicopter.It is different by changing
Relative rotation speed between rotor, thus it is possible to vary the size of single shaft propulsive force, so as to control the running orbit of aircraft.
But in existing multi-rotor unmanned aerial vehicle, cantilever is mostly not folding, the cantilever of such a cantilever mounted unmanned plane
Structure is relatively simple, but because cantilever can not fold, is not easy to outgoing carrying, is primarily adapted for use in the unmanned plane of small volume,
In the larger multi-rotor unmanned aerial vehicle of some volumes, its cantilever can fold, so as to when not in use fold cantilever
Get up, also, in flight, connector may loosen, and certain potential safety hazard be present.
So how to design a kind of multi-rotor unmanned aerial vehicle cantilever locking system, turning into us will currently solve the problems, such as.
Utility model content
The purpose of this utility model is to provide a kind of multi-rotor unmanned aerial vehicle cantilever locking system, to solve above-mentioned background skill
The problem of being proposed in art.
To achieve the above object, the utility model provides following technical scheme：A kind of multi-rotor unmanned aerial vehicle cantilever locking dress
Put, including device body, fuselage and chassis, described device body are made up of lockup arm and locking knob, and the lockup arm and
The quantity of the locking knob is corresponding with the quantity of cantilever, and one end of the lockup arm is provided with two clamping plates, and described
Lockup arm is fixedly connected with clamping plate every piece described by nut and pad, and the insertion of the other end of the lockup arm is arranged at described
In the fixed plate of fuselage roof, and the fixed plate is closely connected with the lockup arm by locking knob, the side of the fuselage
Face is provided with multiple cantilevers, and the cantilever is made up of first segment cantilever, the second section cantilever and Section of three cantilever, the first segment
Cantilever and the second section cantilever are closely connected by interface, and fixed knob is provided with the top of the interface, and described second
Section cantilever is flexibly connected with Section of three cantilever by collar, and the side of the collar is provided with turn-button, and the turn-button is embedding
Entering to be arranged in collar, one end of the cantilever is fixedly connected with the fuselage, and the other end of the cantilever is provided with flabellum, and
The flabellum is flexibly connected with the cantilever by rotating shaft, and the bottom of the fuselage is provided with the chassis, and the fuselage with
The chassis is closely connected by support, and the support is made up of first support, retainer ring and second support, and described first
Frame and the second support are closely connected by the retainer ring, and the second support is closely connected with the chassis by bolt
Connect.
Further, one end of the cantilever is provided with screwed hole, and the cantilever passes through the screwed hole with the fuselage
It is fixedly connected.
Further, wire is provided with inside the cantilever, and the wire is closely connected by crystal-tipped and brilliant groove.
Further, the locking knob shape triangular in shape, and it is provided with elastic component inside the locking knob.
Further, the clamping plate of described lockup arm one end is arranged at the interface both sides.
Further, the second section cantilever and Section of three cantilever can be folded by the collar.
Compared with prior art, the beneficial effects of the utility model are：This kind of multi-rotor unmanned aerial vehicle cantilever locking system leads to
Cross first segment cantilever and the second section cantilever is closely connected by interface, the second section cantilever and Section of three cantilever can pass through the collar
Fold, can facilitate and cantilever is folded and dismounted, be easy to use and carry, be provided with wire inside cantilever, and wire passes through
Crystal-tipped and brilliant groove closely connect, and are easy to cantilever to be dismantled, by lockup arm come locking cantilever, and by locking knob come locking
The state of lockup arm, it is provided with so that cantilever has inside dual locking guarantee, locking knob shape triangular in shape, and locking knob
Elastic component, can preferably carry out locking to cantilever, and one end of lockup arm is provided with two clamping plates, and lockup arm and every piece of clamping plate
It is fixedly connected by nut with pad, and clamping plate is arranged at interface both sides, locking can be further carried out to cantilever, and operate
Simply, unmanned plane during flying security is substantially increased, so, have a wide range of applications.
Brief description of the drawings
Fig. 1 is overall structure diagram of the present utility model；
Fig. 2 is cantilever partial structural diagram of the present utility model；
Fig. 3 is clamping plate partial structural diagram of the present utility model；
Fig. 4 is crystal-tipped partial structural diagram of the present utility model；
In figure：1- device bodies；2- fixed plates；3- cantilevers；4- rotating shafts；5- flabellums；6- first segment cantilevers；7- fixes rotation
Button；8- second saves cantilever；Section of three cantilever of 9-；10- locking knobs；11- lockup arms；12- clamping plates；13- chassis；14- bolts；
15- supports；16- interfaces；17- first supports；18- retainer rings；19- second supports；20- screwed holes；21- turn-buttons；22- collars；
23- crystal-tippeds；24- crystalline substance grooves；25- wires；26- nuts；27- pads；28- fuselages.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the embodiment of the utility model is carried out
Clearly and completely describing, it is clear that described embodiment is only the utility model part of the embodiment, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The every other embodiment obtained, belong to the scope of the utility model protection.
Fig. 1-4 are referred to, the utility model provides a kind of technical scheme：A kind of multi-rotor unmanned aerial vehicle cantilever locking system,
Including device body 1, fuselage 28 and chassis 13, it is characterised in that：Described device body 1 is by 10 groups of lockup arm 11 and locking knob
Into, and the quantity of the lockup arm 11 and the locking knob 10 is corresponding with the quantity of cantilever 3, the one of the lockup arm 11
End is provided with two clamping plates 12, and the lockup arm 11 is fixed by nut 26 and pad 27 with every piece of clamping plate 12 and connected
Connect, the other end insertion of the lockup arm 11 is arranged in the fixed plate 2 at the top of fuselage 28, and the fixed plate 2 and institute
State lockup arm 11 closely to connect by locking knob 10, the side of the fuselage 28 is provided with multiple cantilevers 3, and each described outstanding
Arm 3 saves cantilever 8 by first segment cantilever 6, second and Section of three cantilever 9 is formed, and the first segment cantilever 6 and second section are outstanding
Arm 8 is closely connected by interface 16, and the top of the interface 16 is provided with fixed knob 7, the second section cantilever 8 with it is described
Section three, cantilever 9 is flexibly connected by collar 22, and the side of the collar 22 is provided with turn-button 21, and the insertion of the turn-button 21 is set
It is placed in collar 22, one end of the cantilever 3 is fixedly connected with the fuselage 28, and the other end of the cantilever 3 is provided with flabellum
5, and the flabellum 5 is flexibly connected with the cantilever 3 by rotating shaft 4, the bottom of the fuselage 28 is provided with the chassis 13, and
The fuselage 28 is closely connected with the chassis 13 by support 15, and the support 15 is by first support 17, retainer ring 18 and
Two supports 19 are formed, and the first support 17 and the second support 19 are closely connected by the retainer ring 18, and described
Two supports 19 are closely connected with the chassis 13 by bolt 14.
Further, one end of the cantilever 3 is provided with screwed hole 20, and the cantilever 3 with the fuselage 28 by described
Screwed hole 20 is fixedly connected, and very well can be fixed the cantilever 3 and the fuselage 28, so as to reduce flight risk.
Further, the inside of cantilever 3 is provided with wire 25, and the wire 25 is closely connected by crystal-tipped 23 and brilliant groove 24
Connect, separate the wire 25, be simply done the 3 removable unloading functions of cantilever.
Further, 10 shape triangular in shape of locking knob, and the inside of the locking knob 10 is provided with elastic component, more
The fixed effect to the lockup arm 11 is played well, avoids causing to loosen and bring safety issue in flight course.
Further, the clamping plate 12 of described one end of lockup arm 11 is arranged at the both sides of interface 16, to the interface
16 are fixed processing, improve security.
Further, the second section cantilever 8 and Section of three cantilever 9 can be folded by the collar 22, utilize folding
It is folded, it can more preferably carry and bring convenience.
Operation principle：First, when needing to use the unmanned plane, by retainer ring by first support 17 and second support 19
It is fixed, after by crystal-tipped 23 and brilliant groove 24, wire 25 is connected, then by between the section cantilever 8 of first segment cantilever 6 and second
Interface 16 by first segment cantilever 6 with second section cantilever 8 be fixedly connected, using turn-button 21 will adjust cantilever 3, reach one be adapted to
The state of flight, in the clamping plate by the one end of lockup arm 11, fixing interface 16 tightly, then, according to locking knob 10, enter
Lockup arm 11 is fixed one step, because locking knob 10 is internally provided with elastic component, thus more preferably plays to locking
The fixed effect of arm 11, avoid causing to loosen and bring safety issue in flight course, after completing to fly, pass through rotation
Locking knob 10 unclamps lockup arm 11, enters to exercise the clamping plate 12 at interface 16 and unclamps, is rotated further by fixed knob 7, makes interface 16
Unclamp, then extract crystal-tipped 23, it is possible to easily the cantilever 8 of first segment cantilever 6 and second is separately dismantled, is rotated further by turn-button 21,
The 3rd cantilever 9 and the second cantilever 8 are folded, then unclamps retainer ring 18, unclamps first support 17 and second support 19, Jin Erfang
Portable belt.
While there has been shown and described that embodiment of the present utility model, for the ordinary skill in the art,
It is appreciated that these embodiments can be carried out with a variety of changes in the case where not departing from principle of the present utility model and spirit, repaiied
Change, replace and modification, the scope of the utility model are defined by the appended claims and the equivalents thereof.
Claims (6)
1. a kind of multi-rotor unmanned aerial vehicle cantilever locking system, including device body (1), fuselage (28) and chassis (13), its feature
It is：Described device body (1) is made up of lockup arm (11) and locking knob (10), and the lockup arm (11) and the locking
The quantity of knob (10) is corresponding with the quantity of cantilever (3), and one end of the lockup arm (11) is provided with two clamping plates (12),
And the lockup arm (11) is fixedly connected with clamping plate every piece described (12) by nut (26) and pad (27), the lockup arm
(11) other end insertion is arranged in the fixed plate (2) at the top of the fuselage (28), and the fixed plate (2) and the locking
Arm (11) is closely connected by locking knob (10), and the side of the fuselage (28) is provided with multiple cantilevers (3), and each described
Cantilever (3) by first segment cantilever (6), the second section cantilever (8) and Section of three cantilever (9) composition, the first segment cantilever (6) and
The second section cantilever (8) is closely connected by interface (16), and fixed knob (7) is provided with the top of the interface (16),
The second section cantilever (8) is flexibly connected with Section of three cantilever (9) by collar (22), the side peace of the collar (22)
Equipped with turn-button (21), and the turn-button (21) insertion is arranged in collar (22), one end and the fuselage of the cantilever (3)
(28) it is fixedly connected, the other end of the cantilever (3) is provided with flabellum (5), and the flabellum (5) passes through with the cantilever (3)
Rotating shaft (4) is flexibly connected, and the bottom of the fuselage (28) is provided with the chassis (13), and the fuselage (28) and the chassis
(13) closely connected by support (15), the support (15) is by first support (17), retainer ring (18) and second support (19)
Form, and the first support (17) and the second support (19) are closely connected by the retainer ring (18), described second
Support (19) is closely connected with the chassis (13) by bolt (14).
A kind of 2. multi-rotor unmanned aerial vehicle cantilever locking system according to claim 1, it is characterised in that：The cantilever (3)
One end be provided with screwed hole (20), and the cantilever (3) is fixedly connected with the fuselage (28) by the screwed hole (20).
A kind of 3. multi-rotor unmanned aerial vehicle cantilever locking system according to claim 1, it is characterised in that：The cantilever (3)
Inside is provided with wire (25), and the wire (25) is closely connected by crystal-tipped (23) and brilliant groove (24).
A kind of 4. multi-rotor unmanned aerial vehicle cantilever locking system according to claim 1, it is characterised in that：The locking knob
(10) shape triangular in shape, and it is provided with elastic component inside the locking knob (10).
A kind of 5. multi-rotor unmanned aerial vehicle cantilever locking system according to claim 1, it is characterised in that：The lockup arm
(11) clamping plate (12) of one end is arranged at the interface (16) both sides.
A kind of 6. multi-rotor unmanned aerial vehicle cantilever locking system according to claim 1, it is characterised in that：Second section is outstanding
Arm (8) and Section of three cantilever (9) can be folded by the collar (22).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720900673.1U CN206984345U (en) | 2017-07-24 | 2017-07-24 | A kind of multi-rotor unmanned aerial vehicle cantilever locking system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720900673.1U CN206984345U (en) | 2017-07-24 | 2017-07-24 | A kind of multi-rotor unmanned aerial vehicle cantilever locking system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206984345U true CN206984345U (en) | 2018-02-09 |
Family
ID=61416990
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720900673.1U Expired - Fee Related CN206984345U (en) | 2017-07-24 | 2017-07-24 | A kind of multi-rotor unmanned aerial vehicle cantilever locking system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206984345U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112977795A (en) * | 2021-04-10 | 2021-06-18 | 黑龙江工程学院 | Intelligent remote sensing unmanned aerial vehicle structure |
-
2017
- 2017-07-24 CN CN201720900673.1U patent/CN206984345U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112977795A (en) * | 2021-04-10 | 2021-06-18 | 黑龙江工程学院 | Intelligent remote sensing unmanned aerial vehicle structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180209 Termination date: 20180724 |