CN206968997U - Rotor unmanned aircraft actuating unit - Google Patents
Rotor unmanned aircraft actuating unit Download PDFInfo
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- CN206968997U CN206968997U CN201720903155.5U CN201720903155U CN206968997U CN 206968997 U CN206968997 U CN 206968997U CN 201720903155 U CN201720903155 U CN 201720903155U CN 206968997 U CN206968997 U CN 206968997U
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Abstract
It the utility model is related to a kind of rotor unmanned aircraft actuating unit, it is characterised in that the device is made up of three sets of synchronization belt transmission systems：Main-rotor drive system, tail transmission system and tail pipe transmission system, it is specially：Engine output shaft（1）Connect main rotor driving wheel（2）, main rotor driving wheel（2）Pass through main rotor timing belt（4）Connect main rotor driven pulley（5）, main rotor driven pulley（5）Connect main rotor shaft（6）, main rotor shaft（6）It is also connected with tail transmission driving wheel（7）, tail transmission driving wheel（7）Pass through tail drive coordination band（9）Connect tail driven transmission wheel（10）, tail driven transmission wheel（10）Pass through transition axis union tail driving wheel（11）, tail pipe driving wheel（11）Pass through tail pipe timing belt（12）Union tail driven pulley（13）, tail pipe driven pulley（13）Connect caudal wing shaft（14）.Increase an intermediate transition synchronous belt transmission device, because shortening single synchronous strip length, can effectively mitigate the influence of transmission vibration, transmission slip and timing belt elastic deformation, the power of unmanned plane can be made to transmit more safety and steady.
Description
Technical field
The utility model belongs to depopulated helicopter field, and in particular to a kind of rotor unmanned aircraft actuating unit.
Background technology
Rotor unmanned aircraft semi arch power synchronous belt driver, change the output of unmanned vehicle engine power
Axle is to main rotor and the power transmission form of empennage.Filled in the toothed belt transmission of engine power output shaft to main rotor and empennage
In putting, single synchronous strip length is larger, and transmission vibration is strong, and timing belt easily skids and deformed, and the power of unmanned plane is transmitted stabilization
Property reduce.
The content of the invention
The defects of the purpose of this utility model is to overcome prior art, there is provided a kind of rotor unmanned aircraft power passes
Dynamic device, so that the power transmission more safety and steady of unmanned plane.
To achieve the above object, the utility model adopts the technical scheme that：A kind of rotor unmanned aircraft power transmission
Device, it is characterised in that the device is made up of three sets of synchronization belt transmission systems：Main-rotor drive system, tail transmission system and tail pipe
Transmission system, it is specially：Engine output shaft（1）Connect main rotor driving wheel（2）, main rotor driving wheel（2）Pass through main rotor
Timing belt（4）Connect main rotor driven pulley（5）, main rotor driven pulley（5）Connect main rotor shaft（6）, main rotor shaft（6）It is also connected with
Tail is driven driving wheel（7）, tail transmission driving wheel（7）Pass through tail drive coordination band（9）Connect tail driven transmission wheel（10）, tail transmission
Driven pulley（10）Pass through transition axis union tail driving wheel（11）, tail pipe driving wheel（11）Pass through tail pipe timing belt（12）Connect tail
Pipe driven pulley（13）, tail pipe driven pulley（13）Connect caudal wing shaft（14）.
The main rotor timing belt（4）Upper connection tensioning wheel A（3）, tail drive coordination band（9）Upper connection tensioning wheel B（8）.
The main rotor shaft（6）With main rotor driven pulley（5）Driving wheel is driven with tail（7）Axis is vertically arranged.
The beneficial effects of the utility model are：Increase an intermediate transition synchronous belt transmission device, it is single same because shortening
Strip length is walked, can effectively mitigate the influence of transmission vibration, transmission slip and timing belt elastic deformation, the power of unmanned plane can be made
Transmission more safety and steady, while main rotor is reached and empennage stabilization of speed is reliable, unmanned vehicle is set to install and safeguard
It is more convenient.It can adapt to a variety of working environments simultaneously.
Brief description of the drawings
Fig. 1 is the utility model structure diagram；
Fig. 2 is the utility model overall schematic；
In figure：1- engine output shafts, 2- main rotor driving wheels, 3- tensioning wheels A, 4- main rotor timing belt, 5- main rotors
Driven pulley, 6- main rotor shafts, 7- tails transmission driving wheel, 8- tensioning wheels B, 9- tail drive coordination band, 10- tail driven transmission wheels, 11-
Tail pipe driving wheel, 12- tail pipe timing belts, 13- tail pipe driven pulleys, 14- caudal wing shafts.
Embodiment
Principle of the present utility model and feature are described below in conjunction with accompanying drawing, example is served only for explaining this practicality
It is new, it is not intended to limit the scope of the utility model.
Embodiment 1, see Fig. 1-2, a kind of rotor unmanned aircraft actuating unit, it is characterised in that the device is by three sets
Synchronization belt transmission system forms：Main-rotor drive system, tail transmission system and tail pipe transmission system, it is specially：Engine exports
Axle 1 connects main rotor driving wheel 2, and main rotor driving wheel 2 connects main rotor driven pulley 5 by main rotor timing belt 4, main rotor from
Driving wheel 5 connects main rotor shaft 6, and main rotor shaft 6 is also connected with tail transmission driving wheel 7, and tail transmission driving wheel 7 passes through tail drive coordination band
9 connection tail driven transmission wheels 10, by transition axis union tail driving wheel 11, tail pipe driving wheel 11 passes through tail driven transmission wheel 10
The union tail driven pulley 13 of tail pipe timing belt 12, tail pipe driven pulley 13 connect caudal wing shaft 14.
Tensioning wheel A3 is connected on the main rotor timing belt 4, tensioning wheel B8 is connected on tail drive coordination band 9.
The main rotor shaft 6 is vertically arranged with main rotor driven pulley 5 and the tail transmission axis of driving wheel 7.
Power is transmitted to tail transmission system and tail pipe by power output shaft by main-rotor drive system when engine works
Transmission system, a set of unmanned plane dynamic transfer system is formed by synchronous band connection between each synchronous pulley, finally by engine
Power is transferred to main rotor and empennage workmanship.
Claims (3)
1. a kind of rotor unmanned aircraft actuating unit, it is characterised in that the device is by three sets of synchronization belt transmission system groups
Into：Main-rotor drive system, tail transmission system and tail pipe transmission system, it is specially：Engine output shaft（1）Connect main rotor master
Driving wheel（2）, main rotor driving wheel（2）Pass through main rotor timing belt（4）Connect main rotor driven pulley（5）, main rotor driven pulley（5）
Connect main rotor shaft（6）, main rotor shaft（6）It is also connected with tail transmission driving wheel（7）, tail transmission driving wheel（7）It is same by tail transmission
Walk band（9）Connect tail driven transmission wheel（10）, tail driven transmission wheel（10）Pass through transition axis union tail driving wheel（11）, tail pipe
Driving wheel（11）Pass through tail pipe timing belt（12）Union tail driven pulley（13）, tail pipe driven pulley（13）Connect caudal wing shaft（14）.
2. rotor unmanned aircraft actuating unit as claimed in claim 1, it is characterised in that：The main rotor timing belt
（4）Upper connection tensioning wheel A（3）, tail drive coordination band（9）Upper connection tensioning wheel B（8）.
3. rotor unmanned aircraft actuating unit as claimed in claim 1, it is characterised in that：The main rotor shaft（6）
With main rotor driven pulley（5）Driving wheel is driven with tail（7）Axis is vertically arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720903155.5U CN206968997U (en) | 2017-07-25 | 2017-07-25 | Rotor unmanned aircraft actuating unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720903155.5U CN206968997U (en) | 2017-07-25 | 2017-07-25 | Rotor unmanned aircraft actuating unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206968997U true CN206968997U (en) | 2018-02-06 |
Family
ID=61397412
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720903155.5U Active CN206968997U (en) | 2017-07-25 | 2017-07-25 | Rotor unmanned aircraft actuating unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206968997U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791855A (en) * | 2018-07-25 | 2018-11-13 | 重庆大学 | The quadrotor drone of pure V belt translation |
| CN110450962A (en) * | 2019-08-20 | 2019-11-15 | 深圳市赛为智能股份有限公司 | Oil electric mixed dynamic unmanned plane and its working method |
| CN111776231A (en) * | 2020-07-30 | 2020-10-16 | 天津曙光天成科技有限公司 | Tail rotor transmission structure of helicopter |
-
2017
- 2017-07-25 CN CN201720903155.5U patent/CN206968997U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791855A (en) * | 2018-07-25 | 2018-11-13 | 重庆大学 | The quadrotor drone of pure V belt translation |
| CN110450962A (en) * | 2019-08-20 | 2019-11-15 | 深圳市赛为智能股份有限公司 | Oil electric mixed dynamic unmanned plane and its working method |
| CN111776231A (en) * | 2020-07-30 | 2020-10-16 | 天津曙光天成科技有限公司 | Tail rotor transmission structure of helicopter |
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|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 730900 No.8 Road, Science Park, hi tech Industrial Development Zone, Baiyin District, Baiyin City, Gansu Province Patentee after: Gansu Shenlong Aviation Technology Co., Ltd Address before: 730900 hi tech Zone, Baiyin District, Gansu, Baiyin Patentee before: BAIYIN SHENLONG AVIATION TECHNOLOGY Co.,Ltd. |