CN205891208U - A but, assembly jig for multiaxis aircraft - Google Patents
A but, assembly jig for multiaxis aircraft Download PDFInfo
- Publication number
- CN205891208U CN205891208U CN201620917894.5U CN201620917894U CN205891208U CN 205891208 U CN205891208 U CN 205891208U CN 201620917894 U CN201620917894 U CN 201620917894U CN 205891208 U CN205891208 U CN 205891208U
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- CN
- China
- Prior art keywords
- linking arm
- latch
- hole
- fixedly connected
- fastening bolt
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Abstract
The utility model belongs to the technical field of the multiaxis aircraft, concretely relates to a but, assembly jig for multiaxis aircraft, linking arm including four root canals shape structure is equipped with through -hole A on, linking arm the inner is equipped with fixed connector, and fixed connector's outer end is equipped with latch A and fastening bolt, and fastening bolt is of each other parallel with the linking arm, cup jointed the fixed connection cover on the linking arm, fixed connection sheathes in and is equipped with through -hole B, and through -hole B and through -hole A align, and fixed connection cover right flank is equipped with latch B, four linking arms connect gradually constitutes a square frame -shaped construction, and fastening bolt inserts adjacent linking arm from the fixed connection cover right flank on the adjacent linking arm in, in fastening bolt inserted through -hole B and through -hole A at this moment, the fastening bolt outer end was provided with quick detach nut, latch A and latch B intermeshing on the fixed connection spare. The utility model discloses make the frame of multiaxis aircraft can the dismouting, and the dismouting is simple, the structure be firm, is convenient for accomodate and carry.
Description
Technical field
This utility model belong to Multi-axis aircraft technical field and in particular to a kind of for Multi-axis aircraft can assembling machine
Frame.
Background technology
Multi-axis aircraft, i.e. many rotor wing unmanned aerial vehicles, be provided with multiple propellers, by the multiple propeller of multiple motor controls Lai
Realize flight, be widely used in take photo by plane, monitor, searching and rescuing, the every field such as resource exploration, agricultural, there is small volume, lightweight, expense
With low, flexible operation and safe the features such as.In prior art, the frame of Multi-axis aircraft is all fixed structure mostly, no
Can be dismantled, so storage carries inconvenience.
Content of the invention
This utility model is directed to the non-detachable drawback of frame of Multi-axis aircraft in prior art, provides one kind for many
Axle aircraft can assembly jig, this frame is assembled by four linking arms, removes and installs and is quite convenient to, and is easy to receive.
Goal of the invention of the present utility model is achieved through the following technical solutions: a kind of spelling for Multi-axis aircraft
Installation frame, including the linking arm of four tubular-shaped structures, linking arm is provided with the through hole a running through the linking arm left and right sides, linking arm
The inner is provided with fixedly connected part, and the inner of described fixedly connected part embeds in linking arm, and the outer end of fixedly connected part is provided with latch a
And fastening bolt, fastening bolt is parallel to each other with linking arm；It is socketed with fixed operating sleeve on linking arm, be fixedly connected to put and be provided with
Run through the through hole b of the fixed operating sleeve left and right sides, through hole b is alignd with through hole a, and fixed operating sleeve right flank is provided with latch b；Four
Linking arm is sequentially connected one square frame-shaped structure of composition, and when four linking arms are sequentially connected, adjacent linking arm is orthogonal, Gu
The fastening bolt determined on connector is inserted in adjacent linking arm from the fixed operating sleeve right flank adjacent linking arm, now tightly
In fixing bolt insertion through hole b and through hole a, fastening bolt outer end is provided with Fast dismountable screw nut, the latch a in fixedly connected part and latch
B intermeshes.Described Fast dismountable screw nut and fixedly connected part are located at fixed operating sleeve both sides respectively, and Fast dismountable screw nut pins fastening spiral shell
Bolt, prevents fastening bolt from departing from fixed operating sleeve.
Preferably, fixedly connected part is tubular-shaped structures, inside the fixedly connected part of tubular-shaped structures, it is provided with clamp, fasten spiral shell
Bolt is arranged on clamp.
Preferably, the latch a of fixedly connected part outer end setting is arc-shaped structure, all latch a are around being fixedly connected
The center of part outer end is uniformly distributed, and fastening bolt is arranged on fixedly connected part outer end center.
Preferably, fixed operating sleeve right flank is planar structure, fixed operating sleeve right flank is provided with cirque structure
Snap ring, the external diameter of snap ring is equal to the internal diameter of arc-shaped structure latch a, and snap ring embeds inside latch a, and latch b is arc-shaped structure,
All latch b are evenly distributed on outside snap ring, and through hole b right-hand member is located at snap ring center.
Preferably, described Fast dismountable screw nut includes rotating part and columnar part, rotating part and columnar part connect, outside columnar part
Face is provided with cannelure, and columnar part outer end is provided with screw.
Preferably, linking arm upper surface is provided with installing hole.
Preferably, mounting hole site is between fixedly connected part and fixed operating sleeve.
Preferably, being provided with lock-screw between linking arm and fixedly connected part.
Compared with prior art, this utility model has the advantages that this utility model just passes through four linking arms
Frame can be assembled into, by fastening bolt insertion fixed operating sleeve inner for linking arm during installation, then locked with Fast dismountable screw nut,
Only Fast dismountable screw nut need to be unclamped during dismounting, fastening bolt is extracted in fixed operating sleeve, installing/dismounting all very simples,
After linking arm is assembled into frame, the main frame of Multi-axis aircraft is arranged in the frame of four linking arm compositions i.e. by installing hole
Can, four linking arms are passed through fastening bolt and are connected with Fast dismountable screw nut locking, and are prevented even with the mode that latch a is engaged with latch b
Connect and mutually rotate between arm, overall structure is very firm.In actual use, linking arm is the horn of Multi-axis aircraft, thus
Make the single frame of Multi-axis aircraft no language, only need four horns can form frame, simplify the structure of Multi-axis aircraft, with
When so that the frame of Multi-axis aircraft can be dismantled, carry, receive Multi-axis aircraft and become more convenient.
Brief description
Fig. 1 is this utility model structural representation；
Fig. 2 is linking arm sectional view；
Fig. 3 is latch a and latch b attachment structure schematic diagram；
In figure labelling: 1, linking arm, 2, through hole a, 3, fixedly connected part, 4, latch a, 5, fastening bolt, 6, be fixedly connected
Set, 7, through hole b, 8, latch b, 9, Fast dismountable screw nut, 10, clamp, 11, snap ring, 12, rotating part, 13, columnar part, 14, cannelure,
15th, screw, 16, installing hole, 17, lock-screw, 18, square frame-shaped structure.
Specific embodiment
Embodiment represented by 1-3 is further described to this utility model below in conjunction with the accompanying drawings:
Embodiment 1
As Figure 1-3, a kind of for Multi-axis aircraft can assembly jig, including the linking arm 1 of four tubular-shaped structures,
Linking arm 1 is provided with the through hole a2 running through linking arm 1 left and right sides, and linking arm 1 the inner is provided with the fixedly connected part of tubular-shaped structures
3, the inner of described fixedly connected part 3 embeds in linking arm 1, is provided with clamp 10, clamp 10 is connected with inside fixedly connected part 3
Towards the fastening bolt 5 of fixedly connected part 3 outer end setting, fastening bolt 5 is located on the central axis of fixedly connected part 3, fastening
Bolt 5 is parallel to each other with linking arm 1；The outer end of fixedly connected part 3 is provided with the latch a4 of three arc-shaped structures, three latch a4
It is uniformly distributed around fastening bolt 5.
Fixed operating sleeve 6 is socketed with linking arm 1, fixed operating sleeve 6 is provided with and runs through fixed operating sleeve 6 left and right sides
Through hole b7, through hole b7 is alignd with through hole a2, and fixed operating sleeve 6 right flank is planar structure, and fixed operating sleeve 6 right flank is provided with circle
The snap ring 11 of loop configuration, through hole b7 right-hand member is located at snap ring 11 center, and the external diameter of snap ring 11 is equal to arc-shaped structure latch a4's
Internal diameter, is evenly distributed with the latch b8 of three arc-shaped structures outside snap ring 11；Four linking arms 1 are sequentially connected one side of composition
Frame-shaped construction 18, when four linking arms 1 are sequentially connected, adjacent linking arm 1 is orthogonal, the fastening spiral shell in fixedly connected part 3
Bolt 5 inserts in adjacent linking arm 1 from fixed operating sleeve 6 right flank adjacent linking arm 1, and now fastening bolt 5 insertion is logical
In hole b7 and through hole a2, snap ring 11 embeds inside three latch a4, and latch a4 is intermeshed with latch b8, fastening bolt 5 outer end
It is provided with Fast dismountable screw nut 9, described Fast dismountable screw nut 9 includes rotating part 12 and columnar part 13, rotating part 12 and columnar part 13 connect, post
Shape portion 13 lateral surface is provided with cannelure 14, and columnar part 13 outer end is provided with screw 15.
Linking arm 1 upper surface is provided with installing hole 16, and installing hole 16 is located between fixedly connected part 3 and fixed operating sleeve 6.Even
Connect and between arm 1 and fixedly connected part 3, be provided with lock-screw 17.
Specific embodiment described in literary composition is only explanation for example to this utility model spirit.Belonging to this utility model
Those skilled in the art can make various modifications or supplement or using similar to described specific embodiment
Mode substitutes, but without departing from spirit of the present utility model or surmounts scope defined in appended claims.
Claims (8)
1. a kind of for Multi-axis aircraft can assembly jig it is characterised in that include four tubular-shaped structures linking arm (1),
Linking arm is provided with the through hole a(2 running through the linking arm left and right sides), linking arm the inner is provided with fixedly connected part (3), described fixation
The inner of connector embeds in linking arm, and the outer end of fixedly connected part is provided with latch a(4) and fastening bolt (5), fastening bolt and
Linking arm is parallel to each other；Fixed operating sleeve (6) is socketed with linking arm, is fixedly connected to put to be provided with and runs through about fixed operating sleeve
The through hole b(7 of both sides), through hole b is alignd with through hole a, and fixed operating sleeve right flank is provided with latch b(8)；Four linking arms connect successively
Connect one square frame-shaped structure (18) of composition, when four linking arms are sequentially connected, the fastening bolt in fixedly connected part is from adjacent
Linking arm on fixed operating sleeve right flank insert in adjacent linking arm, in now fastening bolt insertion through hole b and through hole a,
Fastening bolt outer end is provided with Fast dismountable screw nut (9), and the latch a in fixedly connected part and latch b intermeshes.
2. according to claim 1 a kind of for Multi-axis aircraft can assembly jig it is characterised in that fixedly connected part
For tubular-shaped structures, it is provided with clamp (10) inside the fixedly connected part of tubular-shaped structures, fastening bolt is arranged on clamp.
3. according to claim 1 a kind of for Multi-axis aircraft can assembly jig it is characterised in that fixedly connected part
The latch a of outer end setting is arc-shaped structure, and all latch a are uniformly distributed around the center of fixedly connected part outer end, fasten spiral shell
Bolt is arranged on fixedly connected part outer end center.
4. according to claim 3 a kind of for Multi-axis aircraft can assembly jig it is characterised in that fixed operating sleeve
Right flank is planar structure, and fixed operating sleeve right flank is provided with the snap ring (11) of cirque structure, and the external diameter of snap ring is equal to circular arc
The internal diameter of shape structure latch a, snap ring embeds inside latch a, and latch b is arc-shaped structure, and all latch b are evenly distributed on snap ring
Outside, through hole b right-hand member is located at snap ring center.
5. according to claim 1 a kind of for Multi-axis aircraft can assembly jig it is characterised in that described Quick Release spiral shell
Main bag includes rotating part (12) and columnar part (13), and rotating part and columnar part connect, and columnar part lateral surface is provided with cannelure (14), post
Shape portion outer end is provided with screw (15).
6. according to claim 1 a kind of for Multi-axis aircraft can assembly jig it is characterised in that linking arm upper table
Face is provided with installing hole (16).
7. according to claim 6 a kind of for Multi-axis aircraft can assembly jig it is characterised in that mounting hole site in
Between fixedly connected part and fixed operating sleeve.
8. according to claim 1 a kind of for Multi-axis aircraft can assembly jig it is characterised in that linking arm with solid
Determine between connector, to be provided with lock-screw (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620917894.5U CN205891208U (en) | 2016-08-19 | 2016-08-19 | A but, assembly jig for multiaxis aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620917894.5U CN205891208U (en) | 2016-08-19 | 2016-08-19 | A but, assembly jig for multiaxis aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205891208U true CN205891208U (en) | 2017-01-18 |
Family
ID=57777788
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620917894.5U Expired - Fee Related CN205891208U (en) | 2016-08-19 | 2016-08-19 | A but, assembly jig for multiaxis aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205891208U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107380418A (en) * | 2017-08-10 | 2017-11-24 | 河南谷翼自动化科技有限公司 | A kind of axle plant protection unmanned plane of modular assembly four |
| CN109153438A (en) * | 2017-12-29 | 2019-01-04 | 深圳市大疆创新科技有限公司 | Centre frame and unmanned vehicle |
-
2016
- 2016-08-19 CN CN201620917894.5U patent/CN205891208U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107380418A (en) * | 2017-08-10 | 2017-11-24 | 河南谷翼自动化科技有限公司 | A kind of axle plant protection unmanned plane of modular assembly four |
| CN109153438A (en) * | 2017-12-29 | 2019-01-04 | 深圳市大疆创新科技有限公司 | Centre frame and unmanned vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190201 Address after: Room 1016, 10th Floor, No. 1 Scientific Research Building, Xianhua Base, 589 Longtan Road, Wucheng District, Jinhua City, Zhejiang Province, 321000 Patentee after: Zhejiang Yijie Nongjia Intelligent Technology Co.,Ltd. Address before: 321000 No. 17 Kangji North Street, Jindong District, Jinhua City, Zhejiang Province Patentee before: ZHEJIANG ZHITIAN TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170118 Termination date: 20210819 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |