CN109436313A - Multi-rotor unmanned aerial vehicle - Google Patents
Multi-rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN109436313A CN109436313A CN201811572604.8A CN201811572604A CN109436313A CN 109436313 A CN109436313 A CN 109436313A CN 201811572604 A CN201811572604 A CN 201811572604A CN 109436313 A CN109436313 A CN 109436313A
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- China
- Prior art keywords
- horn
- unmanned aerial
- aerial vehicle
- rotor unmanned
- engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 238000007789 sealing Methods 0.000 claims description 8
- 230000008450 motivation Effects 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims 1
- 239000003921 oil Substances 0.000 description 8
- 238000000034 method Methods 0.000 description 3
- 230000003014 reinforcing effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000000356 contaminant Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of multi-rotor unmanned aerial vehicles, and including fuselage, rotating device and the horn being mounted on fuselage, horn is equipped with propeller and drives the engine of propeller motion, and rotating device is for driving engine to rotate relative to fuselage.The rotating device of engine rotation is driven by setting, due to driven by engine propeller rotational, when rotating device drives engine rotation, propeller rotation, when rotating device drives engine rotation, propeller is swung therewith, realizes a variety of job site situations of propeller, and the service performance of multi-rotor unmanned aerial vehicle improves.
Description
Technical field
The present invention relates to air vehicle technique field, in particular to a kind of multi-rotor unmanned aerial vehicle.
Background technique
Unmanned plane refers to the not manned aircraft using radio robot and self-contained program's control device.As China is low
The all-round opening in empty field, multi-rotor unmanned aerial vehicle since its cost of manufacture is cheap, it is easy to operate the features such as, be widely used in army
The multiple fields such as thing, civil and scientific research.
Traditional unmanned plane includes fuselage and the horn that is mounted on fuselage, and wherein horn is equipped with propeller and driving spiral shell
Revolve the engine of paddle movement, the rotation axis of the rotation axis of usual propeller and the axis parallel of fuselage or propeller
It is obliquely installed with the central axes of fuselage.
Summary of the invention
The object of the present invention is to provide a kind of multi-rotor unmanned aerial vehicle, the service performance of the multi-rotor unmanned aerial vehicle is improved.
To achieve the above object, the present invention provides a kind of multi-rotor unmanned aerial vehicle, including fuselage and is mounted on the fuselage
Horn, it further includes for driving the hair that the horn, which is equipped with propeller and drives the engine of the propeller motion,
The rotating device that motivation is rotated relative to fuselage.
Preferably, the horn includes the inside horn being fixedly connected with fuselage and the outside machine being connected with the engine
Arm, the rotating device are fixedly connected on the inside horn, and for driving the outside horn to rotate.
Preferably, the rotating device includes that the horn on motor and the output shaft for being fixedly connected on the motor is solid
Determine component, the horn fixation kit is fixedly connected with the outside horn.
Preferably, the horn fixation kit includes the first fixed pin, the second fixed pin and turnbarrel, the rotary sleeve
The inner side and outer side of cylinder is respectively sleeved on the outside of the output end of the motor and is located on the inside of the outside horn, described electronic
The output shaft of machine is fixedly connected with the turnbarrel by first fixed pin, second fixed pin and the outside machine
Arm is fixedly connected with the turnbarrel.
Preferably, the opposite sides of the outside horn is fixed at the both ends of second fixed pin, and described second is solid
The middle part of rationed marketing passes through the output shaft of the motor.
Preferably, the rotating device is rotary cylinder.
Preferably, the sealing that the outer end of the inside horn is connected with the inner end of the outside horn by slidable sealing
Circle linking.
Preferably, the outside horn and the inside horn are hollow pipe fitting.
Preferably, the engine is the dynamic engine of oil.
It preferably, further include cable sleeve that both ends are connect with the horn end and the fuselage respectively, the cable
It is equipped in sleeve for the oil pipe to the engine oil transportation, the cable sleeve includes the to be rotatably connected with the fuselage
One sleeve and the second sleeve being rotatably connected with the engine, the first sleeve and the second sleeve are slidably socketed.
In the above-mentioned technical solutions, multi-rotor unmanned aerial vehicle provided by the invention, including fuselage, rotating device and it is mounted on machine
Horn with it, horn are equipped with propeller and drive the engine of propeller motion, and rotating device is for driving engine phase
Fuselage is rotated.
As can be seen from the above description, in multi-rotor unmanned aerial vehicle provided by the present application, engine rotation is driven by setting
Rotating device, due to driven by engine propeller rotational, when rotating device drives engine rotation, propeller rotation, rotation
When rotary device drives engine rotation, propeller is swung therewith, realizes a variety of job site situations of propeller, multi-rotor unmanned aerial vehicle
Service performance improve.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of invention for those of ordinary skill in the art without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
Fig. 1 is the partial structural diagram of multi-rotor unmanned aerial vehicle provided by the embodiment of the present invention；
Fig. 2 is the installation site figure of rotating device provided by the embodiment of the present invention；
Fig. 3 structure chart that the first is obliquely installed for propeller in multi-rotor unmanned aerial vehicle provided by the embodiment of the present invention；
Fig. 4 is second of the propeller structure chart being obliquely installed in multi-rotor unmanned aerial vehicle provided by the embodiment of the present invention.
Wherein in Fig. 1-4: horn, 3- motor, 4- output shaft, the first fixed pin of 5-, 6- rotary sleeve on the inside of 1- fuselage, 2-
Horn, 9- engine, 10- sealing ring, 11- first sleeve, 12- second sleeve, 13- oil on the outside of cylinder, the second fixed pin of 7-, 8-
Pipe, the first universal joint of 14-, the second universal joint of 15-.
Specific embodiment
Core of the invention is to provide a kind of multi-rotor unmanned aerial vehicle, and the service performance of the multi-rotor unmanned aerial vehicle improves.
In order to make those skilled in the art more fully understand technical solution of the present invention, with reference to the accompanying drawing and embodiment party
The present invention is described in further detail for formula.
Please refer to figs. 1 to 4, in a specific embodiment, the specific embodiment of the invention provide more rotors nobody
Machine, including fuselage 1, the horn of rotating device and installation on the fuselage 1, horn is equipped with propeller and drives propeller motion
Engine 9, rotating device is for driving engine 9 to rotate relative to fuselage 1, as shown in Figure 3 and Figure 4, the rotation axis of propeller
There are the structural schematic diagrams of inclination angle a relative to fuselage central axes for line.Wherein the number of horn is decided according to the actual requirements, excellent
Choosing, all horns along fuselage to be circumferentially uniformly distributed.
Specifically, 9 direct-driven airscrew of engine moves, preferred engine 9 is mounted on horn end, and rotating device can
The rotation of engine 9 is directly driven to be mounted on the end of horn.
As can be seen from the above description, in the multi-rotor unmanned aerial vehicle provided by the application specific embodiment, by the way that band is arranged
The rotating device that dynamic engine 9 rotates, since engine 9 drives propeller rotational, when rotating device drives engine 9 to rotate
When, propeller rotation, when rotating device drives engine rotation, propeller is swung therewith, realizes a variety of operating positions of propeller
State, and then the pivot center of propeller may be implemented relative to two kinds of working conditions of fuselage axis parallel or inclination, more rotations
The service performance of wing unmanned plane improves.
Specifically, horn includes the inside horn 2 being fixedly connected with fuselage 1 and the outside horn 8 connecting with engine 9,
Rotating device is fixedly connected on the horn 2 of inside, and for driving outside horn 8 to rotate.Specifically, for the ease of external substance
Damage rotating device, it is preferable that rotating device is mounted on inside the horn 2 of inside.It is preferred that outside horn 8 is coaxially set with inside horn 2
It sets.
Further, rotating device includes motor 3 and the fixed group of the horn being fixedly connected on the output shaft 4 of motor 3
Part, horn fixation kit are fixedly connected with outside horn 8.In order to improve motion accuracy, it is preferable that motor 3 is stepper motor,
Wherein motor 3 controls work by multi-rotor unmanned aerial vehicle built-in controller.
In order to improve stability, it is preferable that horn fixation kit includes the first fixed pin 5, the second fixed pin 7 and turnbarrel
6, the inner side and outer side of turnbarrel 6 is respectively sleeved on the outside of the output end of motor 3 and is located at 8 inside of outside horn, electronic
The output shaft 4 of machine 3 is fixedly connected with turnbarrel 6 by the first fixed pin 5, the second fixed pin 7 and outside horn 8 and rotary sleeve
Cylinder 6 is fixedly connected.When needing electric rotating motivation 3, the work of motor 3 drives the first fixed pin 5, the second fixed pin 7 and rotation
Sleeve 6 rotates, and then drives outside horn 8 to rotate, then engine 9 is driven to rotate, final to realize that propeller is swung, by the
One fixed pin 5 and the second fixed pin 7 realize power transmitting and link position positioning.
In order to extend the service life of multi-rotor unmanned aerial vehicle, it is preferable that outside horn 8 is fixed at the both ends of the second fixed pin 7
Opposite sides, and the middle part of the second fixed pin 7 pass through motor 3 output shaft 4.
Further, which further includes the horn reinforcing rod for connecting two neighboring horn end, due to starting
Machine 9 and propeller are generally arranged at horn end, and gravity is larger, by adding horn reinforcing rod in two neighboring horn end,
So that the horn of multi-rotor unmanned aerial vehicle connects to form reticular structure, and then improve integral strength, further extend more rotors nobody
The service life of machine.In order to reduce resistance, it is preferable that horn reinforcing rod is cylindrical straight rod structure.
In another embodiment, rotating device is rotary cylinder.
In view of multi-rotor unmanned aerial vehicle is for open air, in order to avoid introduced contaminants entrance, the outer end and outside of inside horn 2
The inner end of horn 8 is connected by the sealing ring 10 that slidable sealing connects.Specifically, sealing ring 10 can be fixedly connected on inside
On horn 2 or outside horn 8, sliding contact then is sealed with another one.
While proof strength, in order to mitigate overall weight, it is preferable that outside horn 8 and inside horn 2 are hollow pipe
Part.
On the basis of above-mentioned each scheme, engine 9 is the dynamic engine of oil.Certainly, in the specific use process, engine
9 can pass through electrical energy drive.
When engine 9 is the dynamic engine of oil, it is preferable that the multi-rotor unmanned aerial vehicle further include both ends respectively with horn end and
The cable sleeve that fuselage 1 connects is equipped in cable sleeve for the oil pipe 13 to 9 oil transportation of engine, and cable sleeve includes and machine
The first sleeve 11 that body 1 is rotatably connected and the second sleeve 12 being rotatably connected with engine 9, first sleeve 11 and second set
Cylinder 12 is slidably socketed.Oil pipe 13 and cable are arranged in cable sleeve, reduce by external interference, improve multi-rotor unmanned aerial vehicle
Safety in utilization.It is rotated for the ease of first sleeve 11 and second sleeve 12, it is preferable that first sleeve 11 passes through the first universal joint
14 connect with fuselage 1, and second sleeve 12 is connect by the second universal joint 15 with engine 9.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (10)
1. a kind of multi-rotor unmanned aerial vehicle is equipped with including fuselage (1) and the horn being mounted on the fuselage (1), the horn
Propeller and the engine (9) for driving the propeller motion, which is characterized in that further include for driving the engine (9)
Rotating device relative to the fuselage (1) rotation.
2. multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that the horn includes and fuselage (1) is fixed and connected
The inside horn (2) connect and the outside horn (8) connecting with the engine (9), the rotating device are fixedly connected on described
On inside horn (2), and for driving the outside horn (8) to rotate.
3. multi-rotor unmanned aerial vehicle according to claim 2, which is characterized in that the rotating device include motor (3) and
The horn fixation kit being fixedly connected on the output shaft (4) of the motor (3), the horn fixation kit and the outside
Horn (8) is fixedly connected.
4. multi-rotor unmanned aerial vehicle according to claim 3, which is characterized in that the horn fixation kit includes first fixed
Pin (5), the second fixed pin (7) and turnbarrel (6), the inner side and outer side of the turnbarrel (6) are respectively sleeved at the electricity
On the outside of the output end of motivation (3) and it is located on the inside of the outside horn (8), the output shaft (4) of the motor (3) and the rotation
Rotaring sleeve (6) is fixedly connected by first fixed pin (5), second fixed pin (7) and the outside horn (8) and institute
Turnbarrel (6) is stated to be fixedly connected.
5. multi-rotor unmanned aerial vehicle according to claim 4, which is characterized in that the both ends of second fixed pin (7) are fixed
In the opposite sides of the outside horn (8), and the middle part of second fixed pin (7) passes through the output of the motor (3)
Axis (4).
6. multi-rotor unmanned aerial vehicle according to claim 2, which is characterized in that the rotating device is rotary cylinder.
7. multi-rotor unmanned aerial vehicle according to claim 2, which is characterized in that the outer end of the inside horn (2) and described
Sealing ring (10) linking that the inner end of outside horn (8) is connected by slidable sealing.
8. multi-rotor unmanned aerial vehicle according to claim 1, which is characterized in that the outside horn (8) and the inside machine
Arm (2) is hollow pipe fitting.
9. multi-rotor unmanned aerial vehicle according to claim 1 to 8, which is characterized in that the engine (9) is oil
Dynamic engine.
10. multi-rotor unmanned aerial vehicle according to claim 9, which is characterized in that further include that both ends are last with the horn respectively
The cable sleeve at end and the fuselage (1) connection, the cable sleeve is interior to be equipped with for the oil pipe to the engine (9) oil transportation
(13), the cable sleeve includes the first sleeve (11) being rotatably connected with the fuselage (1) and can with the engine (9)
The second sleeve (12) of rotation connection, the first sleeve (11) and the second sleeve (12) are slidably socketed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811572604.8A CN109436313A (en) | 2018-12-21 | 2018-12-21 | Multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811572604.8A CN109436313A (en) | 2018-12-21 | 2018-12-21 | Multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109436313A true CN109436313A (en) | 2019-03-08 |
Family
ID=65534968
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811572604.8A Pending CN109436313A (en) | 2018-12-21 | 2018-12-21 | Multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109436313A (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102126553A (en) * | 2010-01-12 | 2011-07-20 | 北京航空航天大学 | Vertically taking off and landing small unmanned aerial vehicle |
| CN104802985A (en) * | 2015-04-30 | 2015-07-29 | 江苏数字鹰科技发展有限公司 | Variable axial multi-rotor aircraft and flight attitude adjustment method thereof |
| CN205738070U (en) * | 2016-05-10 | 2016-11-30 | 深圳市旋翼捷科技有限公司 | There is the unmanned plane of thrust line variset |
| CN206243446U (en) * | 2016-08-31 | 2017-06-13 | 北京臻迪科技股份有限公司 | A kind of bindiny mechanism of unmanned plane horn |
| CN206394865U (en) * | 2016-12-26 | 2017-08-11 | 重庆零度智控智能科技有限公司 | A kind of telescopic machine arm component and unmanned plane |
| CN206528631U (en) * | 2017-02-28 | 2017-09-29 | 上海拓攻机器人有限公司 | A kind of multi-rotor unmanned aerial vehicle |
| US20180002026A1 (en) * | 2016-07-01 | 2018-01-04 | Bell Helicopter Textron Inc. | Aircraft having a Versatile Propulsion System |
| CN107757897A (en) * | 2017-07-01 | 2018-03-06 | 珠海磐磊智能科技有限公司 | Three axle aircraft and mobile takeoff method |
| CN108313285A (en) * | 2018-03-15 | 2018-07-24 | 中国人民解放军国防科技大学 | Propeller tilting mechanism |
| US20180312246A1 (en) * | 2015-11-05 | 2018-11-01 | Yang Woo NAM | Flying Object |
| CN209290678U (en) * | 2018-12-21 | 2019-08-23 | 辽宁壮龙无人机科技有限公司 | Multi-rotor unmanned aerial vehicle |
-
2018
- 2018-12-21 CN CN201811572604.8A patent/CN109436313A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102126553A (en) * | 2010-01-12 | 2011-07-20 | 北京航空航天大学 | Vertically taking off and landing small unmanned aerial vehicle |
| CN104802985A (en) * | 2015-04-30 | 2015-07-29 | 江苏数字鹰科技发展有限公司 | Variable axial multi-rotor aircraft and flight attitude adjustment method thereof |
| US20180312246A1 (en) * | 2015-11-05 | 2018-11-01 | Yang Woo NAM | Flying Object |
| CN205738070U (en) * | 2016-05-10 | 2016-11-30 | 深圳市旋翼捷科技有限公司 | There is the unmanned plane of thrust line variset |
| US20180002026A1 (en) * | 2016-07-01 | 2018-01-04 | Bell Helicopter Textron Inc. | Aircraft having a Versatile Propulsion System |
| CN206243446U (en) * | 2016-08-31 | 2017-06-13 | 北京臻迪科技股份有限公司 | A kind of bindiny mechanism of unmanned plane horn |
| CN206394865U (en) * | 2016-12-26 | 2017-08-11 | 重庆零度智控智能科技有限公司 | A kind of telescopic machine arm component and unmanned plane |
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| CN107757897A (en) * | 2017-07-01 | 2018-03-06 | 珠海磐磊智能科技有限公司 | Three axle aircraft and mobile takeoff method |
| CN108313285A (en) * | 2018-03-15 | 2018-07-24 | 中国人民解放军国防科技大学 | Propeller tilting mechanism |
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| PB01 | Publication | ||
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Application publication date: 20190308 |