CN206466171U - A kind of multi-rotor unmanned aerial vehicle with twin rotor system - Google Patents
A kind of multi-rotor unmanned aerial vehicle with twin rotor system Download PDFInfo
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- CN206466171U CN206466171U CN201720155877.7U CN201720155877U CN206466171U CN 206466171 U CN206466171 U CN 206466171U CN 201720155877 U CN201720155877 U CN 201720155877U CN 206466171 U CN206466171 U CN 206466171U
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Abstract
The utility model discloses a kind of multi-rotor unmanned aerial vehicle with twin rotor system, including fuselage, actuating unit, main rotor and multiple secondary rotors, actuating unit drives main rotor and multiple secondary rotor rotationals, and the Plane of rotation of main rotor is horizontal plane；Also include connector, the horn of multiple secondary rotors is fixedly installed in the lateral surface of connector, and the center line of multiple secondary rotor horns is located in approximately the same plane；Connector is rotatably installed on fuselage so that secondary rotor and horn can be in vertical rotation in surface.The rotation of main rotor provides power for the lift-off and suspension of unmanned plane, when needing to turn to, the rotation speed change of each secondary rotor is controlled, each secondary rotor is produced different thrusts, because connector is rotatably installed on fuselage, secondary rotor is in air reaction force lower band follower link in vertical rotation in surface, planar tilt where horn, completes to turn to, and fuselage and main rotor remain level, fuselage inclination is avoided, fuselage is always maintained at smooth flight.
Description
Technical field
The utility model belongs to unmanned plane field, especially a kind of multi-rotor unmanned aerial vehicle with twin rotor system.
Background technology
At present, unmanned plane is more maturely applied to multiple fields, plays an important role.Existing many rotors without
Man-machine to have diversified forms, such as utility model patent of Application No. 201520895185.7 is mixed there is provided a kind of multi-rotor unmanned aerial vehicle
Dynamical system, including main rotor and multiple secondary rotors are closed, main rotor provides the lifting of unmanned plane, and secondary rotor controls flying for unmanned plane
Row posture, such as accelerates, slows down, turns to.During steering, by changing the rotating speed of each secondary rotor, different size of thrust is produced,
Unmanned plane force unbalance and change of flight direction.Because this unmanned plane is when turning to, the Plane of rotation and fuselage of main rotor
Certain inclination can be produced, the stability of unmanned plane during flying is influenceed.
Utility model content
The purpose of this utility model be to provide a kind of flight control flexibly, flight stability preferably many rotors nobody
Machine.
What the purpose of this utility model was realized in：A kind of multi-rotor unmanned aerial vehicle with twin rotor system, including machine
Body, actuating unit, main rotor and multiple secondary rotors, the actuating unit drive main rotor and multiple secondary rotor rotationals,
The Plane of rotation of the main rotor is horizontal plane；
Also include connector, the horn of multiple secondary rotors is uniformly fixedly installed in the lateral surface of connector, and multiple secondary rotations
The center line of wing horn is located in approximately the same plane；The connector is rotatably installed on fuselage so that secondary rotor and horn
Can be in vertical rotation in surface.
Further, the actuating unit includes oily power engine and battery, and the main rotor starts with oily power
Machine is connected, and motor is provided with the horn of the secondary rotor, and the secondary rotor is connected with motor, and the motor is with storing
Battery is electrically connected.
Further, the main rotor includes coaxial mounted rotating forward main rotor and reversion main rotor, the main rotation of the rotating forward
The wing and reversion main rotor are connected by differential transmission with oily power engine.
Further, the differential transmission includes housing, input shaft, driving wheel, differential gear, follower, the first output
Axle and the second output shaft, the driving wheel and follower are horizontally disposed with, and one end of the input shaft is connected with oily power engine,
The other end is fixedly connected with driving wheel, and the differential gear is installed on housing by bearing, the differential gear be arranged at driving wheel with
Engaged between follower and with driving wheel with follower, second output shaft is fixedly connected with follower and is provided with center
Hole, first output shaft is fixedly connected with driving wheel and sequentially passes through follower and the centre bore of the second output shaft, it is described just
Turn main rotor and be fixedly installed in the first output shaft, reversion main rotor is fixedly installed in the second output shaft.
Further, the oily power engine side is provided with steering wheel, and the steering wheel is connected with toggle, institute
Toggle is stated with horn to be connected.
Further, the oily power engine is connected with battery, for being charged for battery.
Further, the battery is removably installed in fuselage.
Further, the connector is universal joint.
Further, the quantity of the secondary rotor is 4,6 or 8.
The beneficial effects of the utility model are：The rotation of main rotor provides power, main rotation for the lift-off and suspension of unmanned plane
The Plane of rotation of the wing is horizontal plane, it is ensured that standard of fuselage；Multiple secondary rotors are evenly mounted on around connector, when needs turn
Xiang Shi, controls the rotation speed change of each secondary rotor, each secondary rotor is produced different thrusts, because connector is rotationally pacified
Loaded on fuselage, secondary rotor inclines in air reaction force lower band follower link in the plane where vertical rotation in surface, multiple horns
Tiltedly, there is certain angle between horizontal plane, complete to turn to, and fuselage and main rotor remain level, it is to avoid fuselage
Tilt, fuselage is always maintained at smooth flight.
Brief description of the drawings
Fig. 1 is overall schematic of the present utility model.
Fig. 2 is the schematic diagram of differential transmission.
Reference：1-fuselage；2-main rotor；21-rotate forward main rotor；22-reversion main rotor；3-pair rotor；
4-connector；5-horn；6-oil power engine；7-battery；8-motor；9-differential transmission；91-housing；
92-input shaft；93-driving wheel；94-differential gear；95-follower；96-the first output shaft；97-the second output shaft；
10-steering wheel；11-toggle.
Embodiment
The utility model is further illustrated with reference to the accompanying drawings and examples.
As depicted in figs. 1 and 2, multi-rotor unmanned aerial vehicle of the present utility model, including fuselage 1, actuating unit, the and of main rotor 2
Multiple secondary rotors 3, the actuating unit drives main rotor 2 and multiple secondary rotors 3 to rotate,
The Plane of rotation of the main rotor 2 is horizontal plane；
Also include connector 4, the horn 5 of multiple secondary rotors 3 is circumferentially uniformly fixedly installed in the lateral surface of connector 4, and
The center line of multiple horns 5 of secondary rotor 3 is located in approximately the same plane；The connector 4 is rotatably installed on fuselage 1 so that
Secondary rotor 3 and horn 5 can be in vertical rotation in surface.
Fuselage 1 is using the common structure of existing unmanned plane, and the executing agency comprising control system and execution task may be used also
Undercarriage etc. is set.Main rotor 2 is arranged at the top center of fuselage 1, and it produces thrust when rotating, and promotes fuselage 1 on the whole
Rise or suspend in the air.Connector 4 is also disposed on the center of fuselage 1, secondary rotor 3 is evenly provided on around fuselage 1,
In order to control the flight attitude of fuselage 1 exactly.By changing the rotating speed of secondary rotor 3, the acceleration of fuselage 1 can be realized, subtracted
Speed turns to flight.Connector 4 be rotatably installed on fuselage 1, i.e. connector 4 can around connector 4 and fuselage 1 connection
Point is freely rotated forward, backward, to the left, to the right.When turning to, the rotation speed change of each secondary rotor 3 is controlled, secondary rotor 3 is produced
Thrust variation, when the rotating speed of each secondary rotor 3 is different, the secondary force unbalance of rotor 3, horn 5 produces inclination, prior art
In, horn 5 is fixedly connected with fuselage 1, and the Integral synchronous of fuselage 1 can be driven to tilt, but the utility model is using rotatable connection
Part 4 installs horn 5 so that horn 5 is rotated with follower link 4, and horn 5 is tilted, and fuselage 1 and main rotor 2 keep level, make machine
Body 1 keeps stable flight.
Main rotor 2 rotates that the thrust produced is greater than or the gravity overall equal to unmanned plane is, it is necessary to consume more energy,
And secondary rotor 3 rotates the thrust produced and is used for the deceleration of unmanned plane, accelerates and turn to, it is only necessary to less thrust, therefore,
The energy that secondary rotor 3 is consumed is less, and the utility model can use single actuating unit, such as battery or engine, but main rotor 2
It is different with the rotating speed of secondary rotor 3, it is necessary to control respectively, if using battery as actuating unit, endurance is poor, if adopted
With engine as actuating unit, then need multiple extra transmission mechanisms to be connected with secondary rotor 3, add the weight of unmanned plane
Amount, construction is more complicated, is unfavorable for manufacturing and overhauls.Therefore, the actuating unit includes oily power engine 6 and battery 7,
The main rotor 2 is connected with oily power engine 6, and motor 8, the secondary rotor are provided with the horn 5 of the secondary rotor 3
3 are connected with motor 8, and the motor 8 is electrically connected with battery 7.Battery 7 is that motor 8 provides electric energy, rotates motor 8.
Oily power engine 6 can provide enough energy, advantageously ensure that endurance, because the energy that secondary rotor 3 needs is less,
Demand can be met using general battery 7, oily power engine 6 and battery 7 are used in combination, can not only significantly carried
Long battery life, additionally it is possible to simplify the mechanism of unmanned plane, reduction manufacture and maintenance cost, the convenient control to secondary rotor 3.
Main rotor 2 can not only produce downward thrust when rotating, additionally it is possible to produce the thrust of horizontal direction, be unfavorable for pair
The control of unmanned plane during flying state, therefore, the main rotor 2 include coaxial mounted rotating forward main rotor 21 and reversion main rotor
22, the rotating forward main rotor 21 and reversion main rotor 22 are connected by differential transmission 9 with oily power engine 6.Rotate forward main rotation
The wing 21 with reversion main rotor 22 rotation direction on the contrary, rotating speed is identical, the power in horizontal direction is cancelled out each other, and is conducive to fuselage 1
Keep balance.
It is defeated that the differential transmission 9 includes housing 91, input shaft 92, driving wheel 93, differential gear 94, follower 95, first
The output shaft 97 of shaft 96 and second, the driving wheel 93 and follower 95 are horizontally disposed with, and one end and the oil of the input shaft 92 are moved
Force engine 6 is connected, and the other end is fixedly connected with driving wheel 93, and the differential gear 94 is installed on housing 91 by bearing, described
Differential gear 94 is arranged between driving wheel 93 and follower 95 and engaged with driving wheel 93 with follower 95, second output shaft
97 are fixedly connected with follower 95 and are provided with centre bore, and first output shaft 96 is fixedly connected with driving wheel 93 and worn successively
The centre bore of the output shaft 97 of follower 95 and second is crossed, the rotating forward main rotor 21 is fixedly installed in the first output shaft 96, inverted
Main rotor 22 is fixedly installed in the second output shaft 97.Driving wheel 93, differential gear 94, follower 95 are bevel gear.Input shaft 92
It is connected with the output shaft of oily power engine 6, is rotated for band driven input shaft 92, input shaft 92 drives driving wheel 93 to rotate, it is main
Driving wheel 93 drives the first output shaft 96 and differential gear 94 to rotate, and the first output shaft 96 drives rotating forward main rotor 21 to rotate, differential gear
94 drive followers 95 are rotated, and follower 95 drives the second output shaft 97 to rotate, and the second output shaft 97 drives reversion main rotor 22
Rotate.Because differential gear 94 by bearing is installed on housing 91 so that differential gear 94 is merely able to autobiography, it is impossible in driving wheel 93
Revolved round the sun between follower 95, it is ensured that driving wheel 93 is consistent with the rotating speed of follower 95.
The side of oily power engine 6 is provided with steering wheel 10, and the steering wheel 10 is connected with toggle 11, described
Toggle 11 is connected with horn 5.Steering wheel 10 is subjected to control signal, then controls toggle 11 to drive horn
5 rotate, and change the angle between horn 5 and horizontal plane, flight attitude is more rapidly adjusted in order to realize.
The oily power engine 6 is connected with battery 7, for being charged for battery 7, can further improve continuation of the journey
Ability.
The battery 7 is removably installed in fuselage 1, in order to the battery 7 for charging or more renewing.
Connector 4 can be the attachment structure being arbitrarily hinged with fuselage 1, it is preferred that the connector 4 is universal joint.
It is preferred that, the quantity of the secondary rotor 3 is 4,6 or 8.
Preferred embodiment of the present utility model is the foregoing is only, the utility model is not limited to, for this
For the technical staff in field, the utility model can have various modifications and variations.It is all it is of the present utility model spirit and principle
Within, any modification, equivalent substitution and improvements made etc. should be included within protection domain of the present utility model.
Claims (9)
1. a kind of multi-rotor unmanned aerial vehicle with twin rotor system, including fuselage（1）, actuating unit, main rotor（2）With multiple pairs
Rotor（3）, the actuating unit drive main rotor（2）With multiple secondary rotors（3）Rotate, it is characterised in that：
The main rotor（2）Plane of rotation be horizontal plane；
Also include connector（4）, multiple secondary rotors（3）Horn（5）It is fixedly installed in connector（4）Lateral surface, it is and multiple
Secondary rotor（3）Horn（5）Center line be located at approximately the same plane in；The connector（4）It is rotatably installed on fuselage（1）,
So that secondary rotor（3）And horn（5）Can be in vertical rotation in surface.
2. a kind of multi-rotor unmanned aerial vehicle with twin rotor system according to claim 1, it is characterised in that：The power
Mechanism includes oily power engine（6）And battery（7）, the main rotor（2）With oily power engine（6）Drive connection, institute
State secondary rotor（3）Horn（5）On be provided with motor（8）, the secondary rotor（3）With motor（8）Drive connection, the motor
（8）With battery（7）Electrical connection.
3. a kind of multi-rotor unmanned aerial vehicle with twin rotor system according to claim 2, it is characterised in that：The main rotation
The wing（2）Including coaxial mounted rotating forward main rotor（21）With reversion main rotor（22）, the rotating forward main rotor（21）With reversion master
Rotor（22）Pass through differential transmission（9）With oily power engine（6）It is connected.
4. a kind of multi-rotor unmanned aerial vehicle with twin rotor system according to claim 3, it is characterised in that：The differential
Speed changer（9）Including housing（91）, input shaft（92）, driving wheel（93）, differential gear（94）, follower（95）, the first output shaft
（96）With the second output shaft（97）, the driving wheel（93）And follower（95）It is horizontally disposed, the input shaft（92）One end
With oily power engine（6）It is connected, the other end and driving wheel（93）It is fixedly connected, the differential gear（94）It is installed on by bearing
Housing（91）, the differential gear（94）It is arranged at driving wheel（93）With follower（95）Between and and driving wheel（93）With follower
（95）Engagement, second output shaft（97）With follower（95）It is fixedly connected and is provided with centre bore, first output shaft
（96）With driving wheel（93）It is fixedly connected and sequentially passes through follower（95）With the second output shaft（97）Centre bore, the rotating forward
Main rotor（21）It is fixedly installed in the first output shaft（96）, invert main rotor（22）It is fixedly installed in the second output shaft（97）.
5. a kind of multi-rotor unmanned aerial vehicle with twin rotor system according to claim 2, it is characterised in that：The oil is dynamic
Force engine（6）Side is provided with steering wheel（10）, the steering wheel（10）It is connected with toggle（11）, the crank connecting link
Mechanism（11）With horn（5）It is connected.
6. a kind of multi-rotor unmanned aerial vehicle with twin rotor system according to claim 2, it is characterised in that：The oil is dynamic
Force engine（6）With battery（7）It is connected, for for battery（7）Charging.
7. a kind of multi-rotor unmanned aerial vehicle with twin rotor system according to claim 2, it is characterised in that：The electric power storage
Pond（7）It is removably installed in fuselage（1）.
8. a kind of multi-rotor unmanned aerial vehicle with twin rotor system according to claim 1 to 7 any one claim,
It is characterized in that：The connector（4）For universal joint.
9. a kind of multi-rotor unmanned aerial vehicle with twin rotor system according to claim 1 to 7 any one claim,
It is characterized in that：The secondary rotor（3）Quantity be 4,6 or 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720155877.7U CN206466171U (en) | 2017-02-21 | 2017-02-21 | A kind of multi-rotor unmanned aerial vehicle with twin rotor system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720155877.7U CN206466171U (en) | 2017-02-21 | 2017-02-21 | A kind of multi-rotor unmanned aerial vehicle with twin rotor system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206466171U true CN206466171U (en) | 2017-09-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720155877.7U Expired - Fee Related CN206466171U (en) | 2017-02-21 | 2017-02-21 | A kind of multi-rotor unmanned aerial vehicle with twin rotor system |
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| Country | Link |
|---|---|
| CN (1) | CN206466171U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628154A (en) * | 2017-02-21 | 2017-05-10 | 云南高科新农科技有限公司 | Multiple-rotor-wing unmanned aerial vehicle with double rotor wing systems |
| JPWO2018139661A1 (en) * | 2017-01-30 | 2019-11-14 | 日本電産株式会社 | Unmanned aerial vehicle |
-
2017
- 2017-02-21 CN CN201720155877.7U patent/CN206466171U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPWO2018139661A1 (en) * | 2017-01-30 | 2019-11-14 | 日本電産株式会社 | Unmanned aerial vehicle |
| CN106628154A (en) * | 2017-02-21 | 2017-05-10 | 云南高科新农科技有限公司 | Multiple-rotor-wing unmanned aerial vehicle with double rotor wing systems |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170905 |
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| CF01 | Termination of patent right due to non-payment of annual fee |