CN207120878U - Multi-rotor aerocraft - Google Patents
Multi-rotor aerocraft Download PDFInfo
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- CN207120878U CN207120878U CN201720845556.XU CN201720845556U CN207120878U CN 207120878 U CN207120878 U CN 207120878U CN 201720845556 U CN201720845556 U CN 201720845556U CN 207120878 U CN207120878 U CN 207120878U
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Abstract
Multi-rotor aerocraft, including frame and Vertical Dynamic drive device, the power directly-driving that hangs down move the top that device is arranged on frame, there is provided perpendicular to the pulling force of frame；Horizontal power drive device is additionally provided with, horizontal power drive device is arranged on the lower section of frame, there is provided parallel to the thrust of frame.The utility model provides the power to advance by horizontal power drive device, basic to solve the problems, such as to provide horizontal power by oblique attitude, so as to avoid instantaneously falling high possibly even caused air crash problem.
Description
Technical field
Aircraft is the utility model is related to, is specifically related to a kind of multi-rotor aerocraft.
Background technology
Multi-rotor aerocraft is simple in construction, possesses the functions such as VTOL and hovering, has in commercial market extensive
Utilization prospect.It can be used for taking photo by plane, agricultural plant protection, bridge machinery, circuit line walking, forest monitoring, the multiple fields such as the disaster relief.
However, traditional multi-rotor aerocraft is in mobile process, before inclination during such as traveling process by itself posture provides
The power entered.More rotors are produced perpendicular to the power of fuselage to overcome gravity, so as to reach the mesh of airflight by main rotor rotation
, when instantaneous ramp occurs for posture, when the timing of main rotor rotating speed one, the power caused by it perpendicular to fuselage is certain, and is inclined
The presence at oblique angle makes the lift moment perpendicular to ground diminish, and control system has time delay in itself, therefore during attitude angle change
High phenomenon can be produced, when multi-rotor aerocraft low-latitude flying, it could even be possible to producing air crash problem, this will restrict more rotors
Aircraft is greatly developed.
Utility model content
Technical problem to be solved in the utility model is to overcome the shortcomings of above-mentioned background technology, there is provided a kind of more rotors
Aircraft, the power to advance is provided by horizontal power drive device, avoid instantaneously falling high possibly even caused air crash problem.
The utility model solve its technical problem use technical scheme be a kind of multi-rotor aerocraft, including frame and
Vertical Dynamic drive device, Vertical Dynamic drive device are arranged on the top of frame, there is provided perpendicular to the pulling force of frame；It is additionally provided with
Horizontal power drive device, horizontal power drive device are arranged on the lower section of frame, there is provided parallel to the thrust of frame.
Further, the Vertical Dynamic drive device includes main rotor oar, main rotor oar motor and main rotor oar electronics tune
Fast device, main rotor oar electron speed regulator are connected with main rotor oar motor, and main rotor oar motor is connected with main rotor oar, main rotor oar
Installed in the top of frame, main rotor oar is parallel with frame, when main rotor rotates, there is provided perpendicular to the pulling force of frame.
Further, the quantity of the main rotor oar is 4, is evenly distributed in the top of frame, and each main rotor oar is set
There is corresponding main rotor oar motor and main rotor oar electron speed regulator.
Further, the horizontal power drive device includes culvert type rotor slurry, culvert type rotor slurry motor and culvert type
Rotor starches electron speed regulator, and culvert type rotor is starched electron speed regulator and is connected with culvert type rotor slurry motor, culvert type rotor slurry electricity
Machine is connected with culvert type rotor slurry, and for culvert type rotor slurry installed in the lower section of frame, culvert type rotor slurry is vertical with frame, works as culvert
During road formula rotor slurry rotation, there is provided parallel to the thrust of frame.
Further, the quantity of culvert type rotor slurry is 4, is separately mounted to front portion below frame, rear portion, left part
And right part, the slurry rotation of anterior culvert type rotor provide the forward thrust parallel to frame, the culvert type rotor slurry rotation at rear portion
The thrust backward parallel to frame is provided, the culvert type rotor slurry rotation of left part provides the thrust to the left parallel to frame, right
The culvert type rotor slurry rotation in portion provides the thrust to the right parallel to frame；Each culvert type rotor slurry is provided with corresponding culvert
Road formula rotor slurry motor and culvert type rotor slurry electron speed regulator.
Compared with prior art, it is as follows the advantages of the utility model：
Provided with horizontal power drive device, the power to advance is provided by horizontal power drive device, it is basic to solve to lean on appearance
State tilts the problem of providing horizontal power, so as to avoid instantaneously falling high possibly even caused air crash problem.
Brief description of the drawings
Fig. 1 is the structural representation of the utility model embodiment.
Fig. 2 is the schematic diagram of the flight control mode of embodiment illustrated in fig. 1.
In figure：1-frame, 2-Vertical Dynamic drive device, 3-horizontal power drive device.
Embodiment
Below in conjunction with the accompanying drawings and specific embodiment is described in further detail to the utility model.
Reference picture 1, the present embodiment include frame 1, Vertical Dynamic drive device 2 and horizontal power drive device 3, vertical dynamic
Force driving device 2 is arranged on the top of frame 1, there is provided perpendicular to the pulling force of frame 1；Horizontal power drive device 3 is arranged on machine
The lower section of frame 1, there is provided parallel to the thrust of frame 1.
Vertical Dynamic drive device 2 includes main rotor oar, main rotor oar motor and main rotor oar electron speed regulator, main rotor
Oar electron speed regulator is connected with main rotor oar motor, and main rotor oar motor is connected with main rotor oar.
Horizontal power drive device 3 includes culvert type rotor slurry, culvert type rotor slurry motor and culvert type rotor slurry electronics
Speed regulator, culvert type rotor are starched electron speed regulator and are connected with culvert type rotor slurry motor, culvert type rotor slurry motor and culvert type
Rotor slurry is connected.
Main rotor oar is arranged on the top of frame 1, and main rotor oar is parallel with frame 1, when main rotor rotates, there is provided vertical
In the pulling force of frame 1.In the present embodiment, the quantity of main rotor oar is 4, is evenly distributed in the top of frame 1, each main rotation
Wing oar is provided with corresponding main rotor oar motor and main rotor oar electron speed regulator.
Culvert type rotor slurry is installed in the lower section of frame 1, and culvert type rotor slurry is vertical with frame 1, when culvert type rotor is starched
During rotation, there is provided parallel to the thrust of frame 1.In this example, the quantity of culvert type rotor slurry is 4, is separately mounted to frame 1
Front portion, rear portion, left part and the right part of lower section, the slurry rotation of anterior culvert type rotor provide the forward thrust parallel to frame 1, after
The culvert type rotor slurry in portion rotates the thrust backward provided parallel to frame 1, and the culvert type rotor slurry rotation of left part, which provides, to be put down
For row in the thrust to the left of frame 1, the culvert type rotor slurry rotation of right part provides the thrust to the right parallel to frame 1.Each duct
Formula rotor slurry is provided with corresponding culvert type rotor slurry motor and culvert type rotor slurry electron speed regulator.
Thrust of the horizontal power drive device 3 by offer relative to the front, rear, left and right of fuselage 1, so as to promote flight
The front, rear, left and right of device in the horizontal direction accelerate, deceleration or uniform motion, its uniform motion need horizontal power drive device
3, which provide thrust, offsets air drag.
Vertical Dynamic drive device 2 and horizontal power drive device 3 provide corresponding control power and torque is completed.Its water
The culvert type rotor slurry of translation force driving device 3 can provide the thrust of arbitrary orientation in horizontal direction by combination of two, from
And realize flight of the aircraft in arbitrary orientation.
Reference picture 2, the flight control mode of the utility model multi-rotor aerocraft include typical control model and stage die
Formula, typical control model include VTOL, hovering, traveling, and traveling includes straight line traveling mode and curve is advanced.Transition mode
Conversion including VTOL to hovering, the conversion of hovering to VTOL, hovering to the conversion advanced, advance to turning for hovering
Change.
VTOL and hovering are completed by Vertical Dynamic drive device 2, are advanced by Vertical Dynamic drive device 2 and press horizontal mobile
Force driving device 3 is completed to complete jointly.The control of transition mode is by Vertical Dynamic drive device 2 and horizontal power drive device 3
It is common to complete.
VTOL provides the lift perpendicular to ground by the main rotor oar rotation of Vertical Dynamic drive device 2, so as to
Gravity is overcome to realize VTOL.
Hovering is realized by main rotor oar rotation control lift, posture and the position of Vertical Dynamic drive device 2.
The main rotor oar for being advanced through Vertical Dynamic drive device 2 provides upward lift and control posture, and horizontal
The thrust that the culvert type rotor slurry of power drive unit 3 provides horizontal direction is advanced to realize.
Those skilled in the art can carry out various modifications and variations to the utility model, if these modifications and variations
Within the scope of the utility model claims and its equivalent technologies, then these modifications and variations are also in guarantor of the present utility model
Within the scope of shield.
The prior art that the content not being described in detail in specification is known to the skilled person.
Claims (3)
1. a kind of multi-rotor aerocraft, including frame and Vertical Dynamic drive device, Vertical Dynamic drive device are arranged on frame
Top, there is provided perpendicular to the pulling force of frame；It is characterized in that：It is additionally provided with horizontal power drive device, horizontal power driving dress
Put installed in the lower section of frame, there is provided parallel to the thrust of frame；The Vertical Dynamic drive device includes main rotor oar, main rotation
Wing oar motor and main rotor oar electron speed regulator, main rotor oar electron speed regulator are connected with main rotor oar motor, main rotor oar electricity
Machine is connected with main rotor oar, and main rotor oar is arranged on the top of frame, and main rotor oar is parallel with frame, when main rotor rotates,
Pulling force perpendicular to frame is provided；The horizontal power drive device include culvert type rotor, culvert type rotor motor with
Culvert type rotor electron speed regulator, culvert type rotor electron speed regulator are connected with culvert type rotor motor, culvert type rotation
Wing oar motor is connected with culvert type rotor, and culvert type rotor is arranged on the lower section of frame, and culvert type rotor is hung down with frame
Directly, when culvert type rotor rotates, there is provided parallel to the thrust of frame.
2. multi-rotor aerocraft as claimed in claim 1, it is characterised in that：The quantity of the main rotor oar is 4, uniformly
The top of frame is distributed in, each main rotor oar is provided with corresponding main rotor oar motor and main rotor oar electron speed regulator.
3. multi-rotor aerocraft as claimed in claim 1, it is characterised in that：The quantity of the culvert type rotor is 4, point
Front portion, rear portion, left part and right part that An Zhuan be below frame, the rotation of anterior culvert type rotor be provided parallel to frame
Forward thrust, the culvert type rotor rotation at rear portion provide the thrust backward parallel to frame, the culvert type rotor of left part
Rotation provides the thrust to the left parallel to frame, and the culvert type rotor rotation of right part provides the thrust to the right parallel to frame；
Each culvert type rotor is provided with corresponding culvert type rotor motor and culvert type rotor electron speed regulator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720845556.XU CN207120878U (en) | 2017-07-13 | 2017-07-13 | Multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720845556.XU CN207120878U (en) | 2017-07-13 | 2017-07-13 | Multi-rotor aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207120878U true CN207120878U (en) | 2018-03-20 |
Family
ID=61612562
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720845556.XU Active CN207120878U (en) | 2017-07-13 | 2017-07-13 | Multi-rotor aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207120878U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533306A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of full angle vision stealthy aircraft |
| CN112731956A (en) * | 2020-12-28 | 2021-04-30 | 广东工业大学 | Omnibearing mobile detection detector, control system and control method |
-
2017
- 2017-07-13 CN CN201720845556.XU patent/CN207120878U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533306A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of full angle vision stealthy aircraft |
| CN112731956A (en) * | 2020-12-28 | 2021-04-30 | 广东工业大学 | Omnibearing mobile detection detector, control system and control method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: No.204, building 5, phase I, Zhongdian Software Park, No.39, Jianshan Road, high tech Development Zone, Changsha, Hunan 410000 Patentee after: Hunan Zhongdian Jinjun Technology Group Co.,Ltd. Address before: 410217 No. 1733, Fenglin Third Road, Leifeng Town, Yuelu District, Changsha City, Hunan Province Patentee before: HUNAN ZHONGDIAN JINJUN SOFTWARE TECHNOLOGY CO.,LTD. |
|
| 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: Multi rotor aircraft Effective date of registration: 20230323 Granted publication date: 20180320 Pledgee: China Everbright Bank Co.,Ltd. Changsha Yingwan Branch Pledgor: Hunan Zhongdian Jinjun Technology Group Co.,Ltd. Registration number: Y2023980036045 |