CN208360508U - Fast changeable tail motive force mould group - Google Patents
Fast changeable tail motive force mould group Download PDFInfo
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- CN208360508U CN208360508U CN201721108295.XU CN201721108295U CN208360508U CN 208360508 U CN208360508 U CN 208360508U CN 201721108295 U CN201721108295 U CN 201721108295U CN 208360508 U CN208360508 U CN 208360508U
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- link block
- support arm
- mould group
- motive force
- threaded hole
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Abstract
The utility model relates to a kind of fast changeable tail motive force mould groups, which is characterized in that including the first link block, first link block is fixedly connected with unmanned aerial vehicle body；Second link block, second link block and first link block are detachably connected；Driving mechanism, the driving mechanism are set to inside the unmanned aerial vehicle body；Propeller module, the propeller are fixedly installed on second link block, and being rotated by the driving mechanism.The utility model can realize the quick-replaceable of power mould group, and replacement step is simply accurate, and it is short to expend the time.
Description
Technical field
The utility model relates to unmanned plane field, especially a kind of fast changeable tail motive force mould group.
Background technique
With the development of unmanned air vehicle technique, unmanned plane using more and more extensive, when unmanned plane executes different task, flight
Height above sea level be also it is different, in general, same frame unmanned plane can be used to execute different task, and different height above sea level fly
When row, need replacing different propellers with meet unmanned plane under Different Altitude cruise duration and client to pulling force and flight
The different of speed require, but the power mould group process of unmanned plane replacement now is complicated, and consuming time is long.
Utility model content
Based on this, it is necessary to provide a kind of fast changeable tail motive force mould group, which is characterized in that including the first connection
Module, first link block are fixedly connected with unmanned aerial vehicle body；Second link block, second link block with it is described
First link block is detachably connected；Driving mechanism, the driving mechanism are set to inside the unmanned aerial vehicle body；Propeller
Module, the propeller are fixedly installed on second link block, and being rotated by the driving mechanism.
Propeller is fixed in the second link block, realizes dismounting propeller by the second link block of dismounting, will
The propeller of obstructed model is mounted in the second different link blocks, when needing replacing propeller, it is only necessary to be connect with first
Second link block of module connection, avoids the propeller of disassembly and assembly structure complexity, improves replacement efficiency, avoids replacing
Journey is complicated and causes to make mistakes.
Preferably, the first mounting hole is offered in first link block, first mounting hole runs through described first
Link block, second link block correspond to first link block and offer the second mounting hole, first mounting hole
It is located at same straight line with the axis of the second mounting hole, the propeller module extends to first mounting hole and extends to described
The driving mechanism of second mounting hole connects.
The second link block is fixed in one end of propeller module, and the other end protrudes into the second mounting hole, and protrudes into
Driving mechanism connection in one mounting hole, so that propeller be driven to rotate.Wherein, a part of propeller module has protruded into second
Mounting hole, but still be located in the second mounting hole, a part of driving mechanism has protruded into the first mounting hole, but is still located at the first peace
It fills in hole, does not extend the first mounting hole, in this way, during installation, will not rub to propeller module and driving mechanism, just
It in installation, while being avoided that and scratching unmanned plane surface, influence the flow-disturbing on unmanned plane surface.
Preferably, first link block includes the first inclined-plane and support arm, and the support arm is convexly equipped in the inclined-plane,
Second link block includes the second inclined-plane corresponding with the first inclined-plane and the support slot that matches with the support arm, institute
It states support slot and is embedded at second inclined-plane.
When installation, the second inclined-plane of support slot is slided along the first inclined-plane of support arm, until support arm is inserted into support
In slot, then the second link block is installed in place.The cooperation on the first inclined-plane and the second inclined-plane and the cooperation of support arm and support slot
It can play the role of positioning the second link block, installation is saved in debugging when avoiding installation to the second link block position
Time.
Further, threaded hole is offered on the support arm, the threaded hole that the support slot corresponds to the support arm is opened
Equipped with threaded hole.
The second link block is fixed on support arm by bolt, can be to avoid unmanned plane in flight course, spiral
Paddle module falls off, while bolt fastening structure is simple, easy to disassemble.
Further, the top and side of the support arm at least offer a threaded hole.
The top and side of support arm are fixed together with the second link block, can play to the second link block perpendicular
Histogram is to the support force with horizontal direction, so that connection structure is more stable.
Further, the junction on the support arm and the inclined-plane is provided with transition part.
When installing the second link block, the smooth transition part in surface can be to avoid the sharp portion of support arm and inclined-plane junction
Divide the components of damage unmanned plane.
Further, the support arm is cavity structure, and the support arm corresponds to be provided at the inner wall of the threaded hole
Stiffening plate, the stiffening plate offer the second threaded hole, and second threaded hole is corresponding with the threaded hole of the support arm.
Hollow support arm configuration can mitigate the fuselage weight of unmanned plane, reduce the flight loss of unmanned plane, meanwhile,
The place for being provided with threaded hole, which installs stiffening plate additional, can increase the length of threaded hole, and the intensity of the part with threaded hole,
Connection structure can be made more stable.
Further, the threaded hole that the surface of second link block corresponds to the support slot is provided with through-hole.
When installation or disassembly, the bolt of connection support arm and support slot can be tightened by passing through through-hole with screwdriver
Or the operation unclamped, it is easy to operate, additional dismounting step is not needed, disassembly and assembly time is saved.
Further, first inclined-plane and the second inclined-plane are shiny surface, the outer surface of the support arm and the support
The inner surface of slot is shiny surface.
Smooth surface be conducive to installation when the first inclined-plane and the second inclined-plane between sliding and support arm outer surface and
Opposite sliding between the inner surface of support slot, keeps installation process more smoothly.
Further, second link block is integrally formed structures.
Integrally formed structure is more solid and reliable.
The principles of the present invention, effect are further illustrated below with reference to above-mentioned technical proposal:
1. first link block includes the first inclined-plane and support arm, the support arm is convexly equipped in the inclined-plane, described
Second link block includes the second inclined-plane corresponding with the first inclined-plane and the support slot that matches with the support arm, the branch
Support slot is embedded at second inclined-plane.When installation, the second inclined-plane of support slot is slided along the first inclined-plane of support arm, until branch
Brace is inserted into support slot, then the second link block is installed in place.The cooperation on the first inclined-plane and the second inclined-plane and support arm
Cooperation with support slot can be played the role of positioning the second link block, to the second link block position when avoiding installation
The set-up time is saved in debugging.
2. the top and side of the support arm at least offer a threaded hole.The top and side of support arm are equal
It is fixed together with the second link block, support force vertically and horizontally can be played to the second link block, made
It is more stable to obtain connection structure.
3. the support arm is cavity structure, the support arm corresponds to and is provided with stiffening plate at the inner wall of the threaded hole,
The stiffening plate offers the second threaded hole, and second threaded hole is corresponding with the threaded hole of the support arm.Hollow branch
Brace structure can mitigate the fuselage weight of unmanned plane, reduce the flight loss of unmanned plane, meanwhile, on the ground for being provided with threaded hole
Side, which installs stiffening plate additional, can increase the length of threaded hole, and the intensity of the part with threaded hole, can make connection structure more
For stabilization.
Detailed description of the invention
Fig. 1 is the structural schematic diagram one for the tail motive force mould group that can be changed quickly described in the utility model embodiment；
Fig. 2 is the structural schematic diagram two for the tail motive force mould group that can be changed quickly described in the utility model embodiment；
Fig. 3 is the structural schematic diagram one of the first link block described in the utility model embodiment；
Fig. 4 is the structural schematic diagram two of the first link block described in the utility model embodiment；
Fig. 5 is the structural schematic diagram of the second link block described in the utility model embodiment；
Description of symbols:
First link block 1, the first inclined-plane 11, support arm 12, threaded hole 121, transition part 13, the first mounting hole 14 add
Strong plate 15, the second link block 2, the second inclined-plane 21, support slot 22, the second mounting hole 23, propeller module 3, driving mechanism 4.
Specific embodiment
In order to facilitate the understanding of those skilled in the art, doing the utility model into one below in conjunction with attached drawing and embodiment
Step detailed description:
Such as Fig. 1, a kind of fast changeable tail motive force mould group, which is characterized in that described including the first link block 1
First link block 1 is fixedly connected with unmanned aerial vehicle body；Second link block 2, second link block 2 connect with described first
Connection module 1 is detachably connected；Driving mechanism 4, the driving mechanism 4 are set to inside the unmanned aerial vehicle body；Propeller mould
Block 3, the propeller are fixedly installed on second link block 2, and being rotated by the driving mechanism 4.
One of embodiment offers the first mounting hole 14 in first link block 1 such as Fig. 3 and Fig. 5, described
First mounting hole 14 runs through first link block 1, and corresponding first link block of second link block 2 offers
The axis of second mounting hole 23, first mounting hole 14 and the second mounting hole 23 is located at same straight line, the propeller module 3
It extends to first mounting hole 14 and is connect with the driving mechanism 4 for extending to second mounting hole 23.
One of embodiment, such as Fig. 3, first link block 1 include the first inclined-plane 11 and support arm 12, the branch
Brace 12 is convexly equipped in the inclined-plane, second link block 2 include second inclined-plane 21 corresponding with the first inclined-plane 11 and with
The support slot 22 that the support arm 12 matches, the support slot 22 are embedded at second inclined-plane 21.
One of embodiment, offers threaded hole 121 as described by using fig. 3 and fig. 5 on support arm 12, the support slot 22 is right
The threaded hole 121 of the support arm 12 is answered to offer threaded hole 121.
One of embodiment, the top and side of support arm 12 as described in Figure 3 at least offer a threaded hole
121。
The junction of one of embodiment, such as Fig. 3, the support arm 12 and the inclined-plane is provided with transition part 13.
One of embodiment, such as Fig. 4, the support arm 12 are cavity structure, the corresponding screw thread of the support arm 12
Stiffening plate 15 is provided at the inner wall in hole 121, the stiffening plate 15 offers the second threaded hole 121, second threaded hole 121
It is corresponding with the threaded hole 121 of the support arm 12.
One of embodiment, such as Fig. 5, the surface of second link block 2 correspond to the threaded hole of the support slot 22
121 are provided with through-hole.
One of embodiment, first inclined-plane 11 and the second inclined-plane 21 are shiny surface, the appearance of the support arm 12
The inner surface of face and the support slot 22 is shiny surface.
One of embodiment, second link block 2 are integrally formed structures.
Above-described embodiments merely represent several embodiments of the utility model, the description thereof is more specific and detailed,
But it cannot be understood as the limitations to utility model patent range.It should be pointed out that for the common skill of this field
For art personnel, without departing from the concept of the premise utility, various modifications and improvements can be made, these are belonged to
The protection scope of the utility model.Therefore, the scope of protection shall be subject to the appended claims for the utility model patent.
Claims (10)
1. a kind of fast changeable tail motive force mould group, which is characterized in that including
First link block, first link block are fixedly connected with unmanned aerial vehicle body；
Second link block, second link block and first link block are detachably connected；
Driving mechanism, the driving mechanism are set to inside the unmanned aerial vehicle body；
Propeller module, the propeller are fixedly installed on second link block, and can be in the driving of the driving mechanism
Lower rotation.
2. fast changeable tail motive force mould group according to claim 1, which is characterized in that first link block
On offer the first mounting hole, first mounting hole runs through first link block, and second link block corresponds to institute
It states the first link block and offers the second mounting hole, the axis of first mounting hole and the second mounting hole is located at same straight line,
The propeller module extends to first mounting hole and connect with the driving mechanism for extending to second mounting hole.
3. fast changeable tail motive force mould group according to claim 1 or 2, which is characterized in that first connection
Module includes the first inclined-plane and support arm, and the support arm is convexly equipped in the inclined-plane, and second link block includes and first
Support slot inclined-plane corresponding second inclined-plane and matched with the support arm, the support slot are embedded at described second tiltedly
Face.
4. fast changeable tail motive force mould group according to claim 3, which is characterized in that opened up on the support arm
There is threaded hole, the threaded hole that the support slot corresponds to the support arm offers threaded hole.
5. fast changeable tail motive force mould group according to claim 4, which is characterized in that the top of the support arm
A threaded hole is at least offered with side.
6. fast changeable tail motive force mould group according to claim 3, which is characterized in that the support arm with it is described
The junction on inclined-plane is provided with transition part.
7. fast changeable tail motive force mould group according to claim 4, which is characterized in that the support arm is cavity
Structure, the support arm correspond to and are provided with stiffening plate at the inner wall of the threaded hole, and the stiffening plate offers the second threaded hole,
Second threaded hole is corresponding with the threaded hole of the support arm.
8. fast changeable tail motive force mould group according to claim 3, which is characterized in that second link block
Surface correspond to the threaded hole of the support slot and be provided with through-hole.
9. fast changeable tail motive force mould group according to claim 3, which is characterized in that first inclined-plane and
Two inclined-planes are shiny surface, and the inner surface of the outer surface of the support arm and the support slot is shiny surface.
10. fast changeable tail motive force mould group according to claim 1 or 2, which is characterized in that second connection
Module is integrally formed structures.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721108295.XU CN208360508U (en) | 2017-08-31 | 2017-08-31 | Fast changeable tail motive force mould group |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721108295.XU CN208360508U (en) | 2017-08-31 | 2017-08-31 | Fast changeable tail motive force mould group |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208360508U true CN208360508U (en) | 2019-01-11 |
Family
ID=64912694
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721108295.XU Active CN208360508U (en) | 2017-08-31 | 2017-08-31 | Fast changeable tail motive force mould group |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208360508U (en) |
-
2017
- 2017-08-31 CN CN201721108295.XU patent/CN208360508U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Quickly replaceable tail propulsion module Effective date of registration: 20230814 Granted publication date: 20190111 Pledgee: Guangdong Huaxing Bank Co.,Ltd. Huizhou Branch Pledgor: GUANGDONG AIRACE TECHNOLOGY DEVELOPMENT CO.,LTD. Registration number: Y2023980052084 |