CN206012942U - A kind of Multi-axis aircraft folded piece with auto-lock function - Google Patents
A kind of Multi-axis aircraft folded piece with auto-lock function Download PDFInfo
- Publication number
- CN206012942U CN206012942U CN201621052755.7U CN201621052755U CN206012942U CN 206012942 U CN206012942 U CN 206012942U CN 201621052755 U CN201621052755 U CN 201621052755U CN 206012942 U CN206012942 U CN 206012942U
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- CN
- China
- Prior art keywords
- mounting seat
- folded piece
- horn
- auto
- lock function
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Abstract
The utility model discloses a kind of Multi-axis aircraft folded piece with auto-lock function, including the folded piece mounting seat, horn mounting seat and the self-locking mechanism being connected between folded piece mounting seat and horn mounting seat that are connected with central plate；The horn mounting seat includes that the otic placode being sequentially connected and horn sleeve, the free end end of the otic placode are rotated by rotary shaft with folded piece mounting seat and be connected；Spacing draw-in groove is offered in the folded piece mounting seat, offer waist-shaped hole in the middle part of the otic placode, spring fix bar that the self-locking mechanism includes being fixedly connected in folded piece mounting seat, the self-locking spring between the kelly being plugged in waist-shaped hole and connecting spring fix bar and kelly；The kelly can be in close contact and can be connected in spacing draw-in groove with the gabarit of folded piece mounting seat in the presence of self-locking spring.The characteristics of having easy to use, Stability Analysis of Structures is simple, easy to operate compared with prior art.
Description
Technical field
This utility model is related to unmanned thermomechanical components field, specifically, is a kind of folding of the Multi-axis aircraft with auto-lock function
Overlapping piece.
Background technology
Referred to as " unmanned plane ", english abbreviation is " UAV " to UAV, using radio robot and provides for oneself
The not manned aircraft that presetting apparatus is manipulated.Can be divided into from technical standpoint definition：Unmanned fixed-wing aircraft, unmanned VTOL
Machine, unmanned airship, depopulated helicopter, unmanned multi-rotor aerocraft, unmanned parasol etc..At present, for multi-rotor unmanned aerial vehicle
Speech, in order to transport the convenience of carrying, adopts Quick Release accordion structure its horn more, especially for the unmanned plane that wheelbase is larger,
Horn must be turned up in transport, otherwise, taken up room larger, it is impossible to normal transport, therefore existing many using folded piece in industry
Connect for bearing pin plug, or be fixedly connected for bolt, or the bindiny mechanism of very complicated；However, the folding for plug
Part, in frequently plug folding process, it is easy to lose bearing pin and its attachment component, if working site do not have corresponding
Adnexa, not only so that assembling process is slower, thereby increases and it is possible to causes larger loss；For the folded piece being bolted easily exists
Folded piece is caused damage in use, reduce operation stability；And the bindiny mechanism for very complicated, due to its complexity,
The burden of unmanned plane therefore parts are more, then will necessarily be increased, while certainly will also reduce the reliability of unmanned plane；Also, at present
Folded piece mounting seat be often multiple assembling parts so as to there is deviation in assembling in flatness or axiality, lead
Uniform stability declines.Now need one kind easy to use, on the premise of Stability Analysis of Structures is ensured multiaxis easy to use can fly
Row device folded piece is solving the above problems.
Utility model content
The purpose of this utility model is to design a kind of Multi-axis aircraft folded piece with auto-lock function, with user
Just, the characteristics of Stability Analysis of Structures is simple, easy to operate.
This utility model is achieved through the following technical solutions：A kind of Multi-axis aircraft folded piece with auto-lock function, including
The folded piece mounting seat that is connected with central plate, horn mounting seat and be connected between folded piece mounting seat and horn mounting seat from
Latch mechanism；The horn mounting seat includes the otic placode being sequentially connected and horn sleeve, the free end end of the otic placode and folding
Part mounting seat rotates connection by rotary shaft；Spacing draw-in groove is offered in the folded piece mounting seat, is opened in the middle part of the otic placode
Waist-shaped hole is provided with, the self-locking mechanism includes the spring fix bar being fixedly connected in folded piece mounting seat, is plugged on waist-shaped hole
Self-locking spring between interior kelly and connecting spring fix bar and kelly；The kelly can in the presence of self-locking spring with
The gabarit of folded piece mounting seat is in close contact along its gabarit movement, and can be connected to limit when kelly is moved at spacing draw-in groove
In the draw-in groove of position.
Further is preferably to realize this utility model, especially adopts following setting structures：The folded piece mounting seat
Be the U-shape structure part with two wing plates and a backboard, the backboard is connected with one end of two wing plates respectively, wing plate from
Arc convex portion is provided with by end；The otic placode is rotatably connected on the middle part of the arc convex portion and the wing plate by rotary shaft
Junction；The spacing draw-in groove includes the spacing draw-in groove of the work for being opened in arc convex portion end and to be opened in the arc convex
Portion's gabarit and the spacing draw-in groove of the folding of wing plate junction.
Further is preferably to realize this utility model, especially adopts following setting structures：The pipe of the horn sleeve
A plurality of expansion slot is offered on wall；The expansion slot can make horn sleeve improve its suitability, Neng Gou when being socketed with horn
Also can smoothly be inserted in wherein when horn is not exclusively directed at horn sleeve, improve the convenience for using.
Further is preferably to realize this utility model, especially adopts following setting structures：The otic placode is triangle
Structure, triangular structure have less volume and weight while ensure that part strength, can mitigate the whole of folded piece
The convenient transport of body weight is carried.
Further is preferably to realize this utility model, especially adopts following setting structures：The folded piece mounting seat
Integrally manufactured using 6061-T6 duralumin materials with horn mounting seat, make folded piece that there is the lightweight greatly feature of intensity.
Further is preferably to realize this utility model, especially adopts following setting structures：The folded piece mounting seat
Backboard on offer through wires hole, through wires hole is used for passing through the electric wire of motor, can make the circuit arrangement of aircraft more
Plus regular, improve unmanned plane during flying device stability.
Further is preferably to realize this utility model, especially adopts following setting structures：The folded piece mounting seat
Wing plate on offer hollow out window, the weight for being designed to mitigate folded piece of hollow out, convenient transport are carried.
Further is preferably to realize this utility model, especially adopts following setting structures：Open the side of the wing plate
It is provided with the installing hole for connecting central plate.
This utility model compared with prior art, with advantages below and beneficial effect：
（1）In this utility model, folded piece mounting seat and horn mounting seat are integrally manufactured using 6061-T6 duralumin materials
And folded piece mounting seat offers hollow out window, the characteristics of make folded piece have lightweight intensity big, transport is not only facilitated to carry
Also improve the stability of folded piece structure；
（2）In this utility model, self-locking spring can turn to the spacing draw-in groove of work in horn mounting seat and fold spacing
Kelly is drawn in when at draw-in groove and be wherein fixed, eliminate the time using fixture fixed fold part, improve and use
Convenience, has saved the time；
（3）In this utility model, the through wires hole that backboard is opened up can make the connecting line of the aircraft components such as motor pass through which
In, the circuit arrangement of aircraft can be made more regular, the stability of unmanned plane during flying device is improved；
（4）In this utility model, on the tube wall of horn sleeve, expansion slot is offered, horn can be not exclusively directed in horn
Also smoothly can be inserted in wherein during sleeve, simple to operation when making installation；
（5）In this utility model, self-locking mechanism is separately provided and passes through spring fix bar and kelly connects folded piece respectively
Mounting seat and horn mounting seat, have bigger space arrangement self-locking mechanism, provide more clamping from the higher spring of elastic force
Power, improves wind loading rating and the stability of aircraft.
Description of the drawings
Fig. 1 is a kind of signal of kelly of the Multi-axis aircraft folded piece with auto-lock function in the spacing draw-in groove of work
Figure；
Fig. 2 is a kind of signal of kelly of the Multi-axis aircraft folded piece with auto-lock function in folding in spacing draw-in groove
Figure；
Fig. 3 is the structural representation of the folded piece mounting seat；
Fig. 4 is the structural representation of the horn mounting seat；
Fig. 5 is the schematic diagram of the rotary shaft；
Fig. 6 is the schematic diagram of the kelly；
Wherein, 1- folded pieces mounting seat, 2- self-locking springs, 3- spring fix bars, 4- rotary shafts, 5- kellies, 6- horns are pacified
Dress seat, 11- work stopper slots, 12- fold stopper slot, 13- through wires holes, 14- installing holes, 61- otic placodes, 62- horn sleeves, 611-
Waist-shaped hole, 621- expansion slots.
Specific embodiment
This utility model is described in further detail with reference to embodiment, but embodiment of the present utility model is not
It is limited to this.
Embodiment 1：
A kind of Multi-axis aircraft folded piece with auto-lock function, with easy to use, Stability Analysis of Structures is simple, easily to operate
Feature, as shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4, Fig. 5, Fig. 6, is specifically arranged to following structures：Including the length being connected with central plate
It is 35mm, is highly the folded piece mounting seat 1 of 35mm, horn mounting seat 6 and is connected to folded piece mounting seat 1 for 55mm, width
With the self-locking mechanism between horn mounting seat 6；
The horn mounting seat 6 includes the otic placode 61 being sequentially connected and the horn sleeve 62 for connecting carbon fiber horn,
Wherein, the external diameter of horn sleeve 62 be 25mm, internal diameter be 23mm, length be 40mm, the free end end of the otic placode 61 and folding
Overlapping piece mounting seat 1 rotates connection by rotary shaft 4, enables folded piece mounting seat 1 and horn mounting seat 6 around the axle of rotary shaft 4
Line does gyration, and wherein, a diameter of 3mm of the axle body of rotary shaft 4, length are that 7mm, a diameter of 5mm thickness in shaft end of both sides are
1mm, fixed fold part mounting seat 1 and horn mounting seat 6 can make which not to be moved in the axial direction；The folded piece is installed
Spacing draw-in groove is offered on seat 1, the middle part of the otic placode 61 offers waist-shaped hole 611；Wherein, the self-locking mechanism includes fixing
The spring fix bar 3 being connected in folded piece mounting seat 1, the kelly 5 being plugged in waist-shaped hole 611 and it is connected to spring fix bar
Self-locking spring 2 between 3 and kelly 5, self-locking spring 2 are in extended state all the time, and kelly 5 can be in the pulling force of self-locking spring 2
The lower gabarit with folded piece mounting seat 1 of effect is in close contact along its gabarit movement, and can be moved at spacing draw-in groove in kelly 5
When be connected in spacing draw-in groove；Wherein, a diameter of 3mm of the axle body of the kelly 5, length be 41mm, a diameter of 5mm in shaft end, length
Spend for 6mm, it is 8mm that the width of waist-shaped hole 611 is 3mm, length, the width of the shaft end of kelly 5 with diameter greater than waist-shaped hole 611, energy
Kelly 5 is enough made not occur axial to move and skid off in waist-shaped hole 611.Wherein, the folded piece mounting seat 1 is with two wings
The U-shape structure part of plate and a backboard, the backboard are connected with one end of two wing plates respectively, and the free end of wing plate is provided with arc
Shape convex portion；The otic placode 61 is rotatably connected on the middle part of the arc convex portion and the junction of the wing plate by rotary shaft 4；Institute
Stating spacing draw-in groove includes the spacing draw-in groove 11 of the work for being opened in arc convex portion end and is opened in arc convex portion gabarit
The spacing draw-in groove 12 of folding with wing plate junction.
During use, driving the kelly 5 in folding at spacing draw-in groove 12 to the free end of waist-shaped hole 611 with handss makes kelly
5 depart from and fold spacing draw-in groove 12, the horn that is subsequently stirred horn mounting seat 6 or be connected in horn mounting seat 6 with handss make its to
Work, kelly 5 tightly touch the gabarit movement of arc convex portion under the pulling force effect of self-locking spring 2,
Last kelly 5 is moved at the spacing draw-in groove 11 of work and is drawn in kelly 5 in the spacing draw-in groove 11 of work by self-locking spring 2 and fixes,
Now folded piece mounting seat 1, horn and horn mounting seat 6 are on same straight line；When needing to pack up horn mounting seat 6, only
Kelly 5 need to be stirred the restriction for making kelly 5 depart from the spacing draw-in groove 11 of work to the free end handss of waist-shaped hole 611, while downwards
Upset horn installation in side's does 6 makes kelly 5 snap in the spacing draw-in groove 12 of folding.
Embodiment 2：
The present embodiment is further optimized on the basis of above-described embodiment, and further is preferably to realize that this practicality is new
Type, as shown in Figure 2, Figure 3, Figure 4, especially adopts following setting structures：A plurality of edge is offered on the tube wall of the horn sleeve 62
The expansion slot 621 that the width of its axis direction is 1.5mm, length is 25mm；The expansion slot 621 can make horn sleeve 62 with
Horn improves its suitability when being socketed, can i.e. horn is different from horn sleeve 62 when horn is not exclusively directed at horn sleeve 62
Also can smoothly be inserted in wherein during the heart, improve the convenience for using.
Wherein, structural member of the otic placode 61 for triangle, triangular structure have while ensure that part strength
Less volume and weight, can mitigate the overall weight of folded piece so as to mitigate the charge of aircraft, and convenient transport is carried simultaneously
The lift-launch amount of aircraft can be improved, the performance of aircraft is improved indirectly.
Wherein, the through wires hole 13 of a diameter of 16mm is offered on the backboard of the folded piece mounting seat 1, and through wires hole 13 can
For make the electrical equipments such as motor be routed through wherein make the circuit arrangement of aircraft more regular, improve unmanned plane fly
The stability of row device.
Wherein, hollow out window is offered on the wing plate of the folded piece mounting seat 1, and the design of hollow out alleviates folded piece
Weight, can conveniently transport carrying.
Wherein, the side of the wing plate offers the installing hole 14 of a diameter of 3mm for connecting central plate, is connected with each other
Folded piece mounting seat and horn mounting seat fixed on the central plate by installing hole 14.
Wherein, the folded piece mounting seat 1 and horn mounting seat 6 are integrally manufactured using 6061-T6 duralumin materials, make folding
Overlapping piece has the lightweight greatly feature of intensity.
The above, is only preferred embodiment of the present utility model, not does any pro forma limit to this utility model
System, every any simple modification that above example is made according to technical spirit of the present utility model, equivalent variations, each falls within
Within protection domain of the present utility model.
Claims (8)
1. a kind of Multi-axis aircraft folded piece with auto-lock function, it is characterised in that：Including the folded piece peace being connected with central plate
Dress seat（1）, horn mounting seat（6）Be connected to folded piece mounting seat（1）With horn mounting seat（6）Between self-locking mechanism；Institute
State horn mounting seat（6）Including the otic placode being sequentially connected（61）With horn sleeve（62）, the otic placode（61）Free end end
With folded piece mounting seat（1）By rotary shaft（4）Rotate connection；The folded piece mounting seat（1）On offer spacing draw-in groove, institute
State otic placode（61）Middle part offer waist-shaped hole（611）, the self-locking mechanism includes being fixedly connected on folded piece mounting seat（1）On
Spring fix bar（3）, be plugged on waist-shaped hole（611）Interior kelly（5）With connecting spring fix bar（3）With kelly（5）Between
Self-locking spring（2）；The kelly（5）Can be in self-locking spring（2）In the presence of with folded piece mounting seat（1）Gabarit tight
Contact simultaneously can be connected in spacing draw-in groove.
2. a kind of Multi-axis aircraft folded piece with auto-lock function according to claim 1, it is characterised in that：The folding
Part mounting seat（1）It is the U-shape structure part with two wing plates and a backboard, the backboard is connected with one end of two wing plates respectively
Connect, the free end of wing plate is provided with arc convex portion；The otic placode（61）By rotary shaft（4）It is rotatably connected on the arc convex portion
Middle part and the wing plate junction；The spacing draw-in groove includes the spacing draw-in groove of the work for being opened in arc convex portion end
（11）With the spacing draw-in groove of the folding that is opened in arc convex portion gabarit and wing plate junction（12）.
3. a kind of Multi-axis aircraft folded piece with auto-lock function according to claim 1, it is characterised in that：The horn
Sleeve（62）Tube wall on offer a plurality of expansion slot（621）.
4. a kind of Multi-axis aircraft folded piece with auto-lock function according to claim 1, it is characterised in that：The otic placode
（61）For triangular structure.
5. a kind of Multi-axis aircraft folded piece with auto-lock function according to claim 1, it is characterised in that：The folding
Part mounting seat（1）With horn mounting seat（6）Integrally manufactured using 6061-T6 duralumin materials.
6. a kind of Multi-axis aircraft folded piece with auto-lock function according to claim 2, it is characterised in that：The folding
Part mounting seat（1）Backboard on offer through wires hole（13）.
7. a kind of Multi-axis aircraft folded piece with auto-lock function according to claim 2, it is characterised in that：The folding
Part mounting seat（1）Wing plate on offer hollow out window.
8. a kind of Multi-axis aircraft folded piece with auto-lock function according to claim 2, it is characterised in that：The wing plate
Side offer the installing hole for connecting central plate（14）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621052755.7U CN206012942U (en) | 2016-09-13 | 2016-09-13 | A kind of Multi-axis aircraft folded piece with auto-lock function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621052755.7U CN206012942U (en) | 2016-09-13 | 2016-09-13 | A kind of Multi-axis aircraft folded piece with auto-lock function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206012942U true CN206012942U (en) | 2017-03-15 |
Family
ID=58260169
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621052755.7U Expired - Fee Related CN206012942U (en) | 2016-09-13 | 2016-09-13 | A kind of Multi-axis aircraft folded piece with auto-lock function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206012942U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106892086A (en) * | 2017-03-28 | 2017-06-27 | 卢旭升 | A kind of multi-rotor unmanned aerial vehicle |
| CN106965920A (en) * | 2017-05-05 | 2017-07-21 | 安元（徐州）大数据科技有限公司 | A kind of self-locking mechanism and unmanned plane |
| CN107161320A (en) * | 2017-04-28 | 2017-09-15 | 深圳思博航空科技有限公司 | Multi-rotor unmanned aerial vehicle horn contracting mechanism |
| CN113795424A (en) * | 2020-06-01 | 2021-12-14 | 深圳市大疆创新科技有限公司 | Arm subassembly and unmanned vehicles |
| CN114368467A (en) * | 2021-12-22 | 2022-04-19 | 之江实验室 | A horn prevents clearance folding device for large aircraft |
-
2016
- 2016-09-13 CN CN201621052755.7U patent/CN206012942U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106892086A (en) * | 2017-03-28 | 2017-06-27 | 卢旭升 | A kind of multi-rotor unmanned aerial vehicle |
| CN107161320A (en) * | 2017-04-28 | 2017-09-15 | 深圳思博航空科技有限公司 | Multi-rotor unmanned aerial vehicle horn contracting mechanism |
| CN106965920A (en) * | 2017-05-05 | 2017-07-21 | 安元（徐州）大数据科技有限公司 | A kind of self-locking mechanism and unmanned plane |
| CN113795424A (en) * | 2020-06-01 | 2021-12-14 | 深圳市大疆创新科技有限公司 | Arm subassembly and unmanned vehicles |
| CN114368467A (en) * | 2021-12-22 | 2022-04-19 | 之江实验室 | A horn prevents clearance folding device for large aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170315 Termination date: 20210913 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |