CN108216616A - A kind of efficient unmanned plane automatic adjustment rotor structure - Google Patents
A kind of efficient unmanned plane automatic adjustment rotor structure Download PDFInfo
- Publication number
- CN108216616A CN108216616A CN201810062080.1A CN201810062080A CN108216616A CN 108216616 A CN108216616 A CN 108216616A CN 201810062080 A CN201810062080 A CN 201810062080A CN 108216616 A CN108216616 A CN 108216616A
- Authority
- CN
- China
- Prior art keywords
- bearing base
- unmanned plane
- driving mechanism
- automatic adjustment
- air hose
- 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.)
- Granted
Links
Classifications
-
- 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
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
Abstract
The present invention relates to a kind of efficient unmanned plane automatic adjustment rotor structures, including bearing base, rotor, driving mechanism, turntable mechanism, air hose and control circuit, bearing base is rectangular plate-like structure, at least one locating slot is set on bearing base, bearing base end is hinged by turntable structure and unmanned aerial vehicle body, air hose is in locating slot, rotor, driving mechanism are in air hose, driving mechanism is connected with each other by locating rack and air hose, control circuit is electrically connected in bearing base with driving mechanism, turntable mechanism respectively.Present device is simple in structure, it is flexible and convenient to use, the degree of automation, integration degree, degree of modularity height are run, help to improve the convenience and reliability of the assembling of unmanned plane equipment, dismounting and part replacement and improves bearing capacity and flight control stability, the purpose of flexibility and reliability of unmanned machine equipment operation.
Description
Technical field
The present invention relates to a kind of efficient unmanned plane automatic adjustment rotor structures, belong to technical field of wind power generation.
Background technology
Rotary wind type unmanned plane is one of main form in current unmanned plane structure at present, and usage amount is huge, but in reality
It is found in use, the rotor mechanism of current rotor wing unmanned aerial vehicle is often an integral structure with unmanned plane body, although can be with
Meet the needs used, but result in current rotary wind type unmanned plane and install, dismantle and replace there are rotor mechanism in operation
Operating flexibility is poor, has seriously affected the flexibility that uses of rotor wing unmanned aerial vehicle equipment operation, at the same also result in current rotary wind type without
In man-machine device's operation, generated driving force size, direction controlling and flexible adjustment are opposite in operation for rotor equipment
Poor and adjustable range is narrow, has on the one hand seriously affected unmanned plane rotor power performance and operational efficiency is relatively poor, and makes
Increase into operation energy consumption, on the other hand also cause the flexibility, reliability and the flight stability that run currently without man-machine device equal
It is relatively poor, for this problem, there is an urgent need to develop a kind of completely new unmanned plane rotor structure, to meet the need of actual use
It will.
Invention content
The object of the invention, which is that, overcomes above-mentioned deficiency, provides a kind of uniaxial loading coal body ultrasonic velocity test system dress
It puts.
To achieve the above object, the present invention is to be achieved through the following technical solutions：
A kind of efficient unmanned plane automatic adjustment rotor structure, including bearing base, rotor, driving mechanism, turntable mechanism, air hose and
Control circuit, bearing base are rectangular plate-like structure, set at least one locating slot on bearing base, and locating slot is along bearing base axis
Line direction is evenly distributed with, and locating slot axis is vertical with bearing base axis and intersects, and bearing base end passes through turntable structure and nothing
Man-machine fuselage is hinged, and bearing base axis intersects with unmanned aerial vehicle body axis and is in 0 ° -180 ° angles, and air hose is embedded in
In locating slot, and it is hinged with positioning groove sidewall by least two turntable mechanisms, and air hose axis and bearing base following table
Face is in 30 ° -90 ° angles, and rotor, driving mechanism are in air hose, and wherein rotor is located at right over driving mechanism and passes through biography
Moving axis is connected with each other with driving mechanism, and rotor, driving mechanism are coaxially distributed with air hose, and driving mechanism passes through locating rack and air hose
It is connected with each other, control circuit is electrically connected in bearing base with driving mechanism, turntable mechanism respectively.
Further, the bearing base cross section is any one in fusiformis structure and droplet-shaped structure.
Further, the bearing base is airtight cavity structure, including bearing keel, guard shield and inner liner wall,
The bearing keel is frame structure, and the guard shield is coated on bearing keel outer surface, inner liner wall cladding
Closed cushion chamber is formed between bearing keel inner surface, the guard shield and inner liner wall, the inner liner wall is formed
The bearing cavity of closed structure.
Further, elastic insert is set in the cushion chamber, at least one booster pump is set in the bearing cavity, it is described
Booster pump one end moved gas-guide tube and connect with air hose side wall, the booster pump other end is by least one gas-guide tube with holding
Pedestal upper surface connection is carried, and the bearing base is evenly distributed in the upper surface several open-works, each open-work is interconnected with gas-guide tube.
Further, the air hose includes tube body carrying tube body, deflector and nozzle, wherein the carrying tube body is
Hollow tubular structures carry and are all provided with several deflectors at tube body upper surface and lower face, and the deflector passes through turntable mechanism
It is hinged with carrying inner surface of tube body, and the deflector and carrier pipe body axis be in 0 ° -90 ° angles, and two neighboring water conservancy diversion
Spacing between plates is carry pipe diameter 1/6-1/3, and the nozzle at least two in carrying tube wall, and respectively sprays
Mouth is evenly distributed with around carrier pipe body axis, and with carrier pipe body axis in 0 ° -90 ° angles, parallel with one another between the nozzle and lead to
Control valve is crossed to be interconnected with gas-guide tube.
Further, the carrying tube body cross section is any one in rectangle, isosceles trapezoidal structure.
Further, the driving mechanism is any one in motor, internal combustion engine.
Further, the turntable mechanism is three-dimensional turntable, and the turntable mechanism upper angle sensor, and angle
Sensor is electrically connected with control circuit.
Further, the control circuit includes data processing module, data communication module, data bus module, number
According to communication terminal, wireless data communication antenna and drive module, the data bus module respectively with data processing module, number
It is electrically connected according to communication module and drive module, the data communication module and data communication terminal, wireless data communication day
Line is electrically connected, and is passed through data communication terminal, wireless data communication antenna and unmanned plane operating system and be electrically connected, described
Drive module is electrically connected respectively with driving mechanism, turntable mechanism.
Present device is simple in structure, flexible and convenient to use, operation the degree of automation, integration degree, the degree of modularity
On the one hand height can effectively improve the intensity of unmanned plane rotor installation positional flexibility and bearing structure, help to improve nobody
The convenience and reliability of machine equipment assembling, dismounting and part replacement, on the other hand can effectively improve unmanned plane rotor system
The power performance of system and flexibility and the reliability of driving power adjustment control, holding for unmanned machine equipment operation is improved so as to reach
Loading capability and flight control stability, the purpose of flexibility and reliability.
Description of the drawings
Fig. 1 is schematic structural view of the invention；
Fig. 2 electrical block diagrams in order to control.
Specific embodiment
As shown in Figure 1, 2, a kind of efficient unmanned plane automatic adjustment rotor structure, including bearing base 1, rotor 2, driving machine
Structure 3, turntable mechanism 4, air hose 5 and control circuit 6, bearing base 1 are rectangular plate-like structure, are set on bearing base 1 at least one
Locating slot 7, locating slot 7 are evenly distributed with along 1 axis direction of bearing base, and 7 axis of locating slot is vertical with 1 axis of bearing base and phase
It hands over, 1 end of bearing base is hinged by turntable structure 4 and unmanned aerial vehicle body 8, and 1 axis of bearing base and unmanned plane machine
8 axis of body intersects and is in 0 ° -180 ° angles, and air hose 5 passes through at least two turns in locating slot 7 with 7 side wall of locating slot
Platform mechanism 4 is hinged, and 5 axis of air hose and 1 lower surface of bearing base are in 30 ° -90 ° angles, and rotor 2, driving mechanism 3 are equal
In air hose 5, wherein rotor 2 is located at right over driving mechanism 3 and passes through transmission shaft 9 and is connected with each other with driving mechanism 3, rotor
2nd, with the coaxial distribution of air hose 5, driving mechanism 3 is connected with each other 3 structure of driving machine by locating rack 10 and air hose 5, and control circuit 6 is embedding
In in bearing base 1, and it is electrically connected respectively with driving mechanism 3, turntable mechanism 4.
In the present embodiment, 1 cross section of bearing base is any one in fusiformis structure and droplet-shaped structure.
In the present embodiment, the bearing base 1 is airtight cavity structure, including bearing keel 101, guard shield 102
And inner liner wall 103, the bearing keel 101 are frame structure, the guard shield 102 is coated on outside bearing keel 101
Surface, the inner liner wall 103 is coated on 101 inner surface of bearing keel, between the guard shield 102 and inner liner wall 103
Closed cushion chamber 104 is formed, the inner liner wall 103 forms the bearing cavity 105 of closed structure.
In the present embodiment, elastic insert 11 is set in the cushion chamber 104, is set in the bearing cavity 105 at least one
Booster pump 12, described 12 one end of booster pump were moved gas-guide tube 13 and were connect with 5 side wall of air hose, and 12 other end of booster pump leads to
It crosses at least one gas-guide tube 13 to connect with 1 upper surface of bearing base, and the bearing base 1 is evenly distributed in the upper surface several open-works
14, each open-work 14 is interconnected with gas-guide tube 13.
In the present embodiment, the air hose 5 includes tube body carrying tube body 51, deflector 52 and nozzle 53, wherein described
Carrying tube body 51 is hollow tubular structures, carries and is all provided with several deflectors 52 at 51 upper surface of tube body and lower face, described leads
Flowing plate 52 is hinged by turntable mechanism 4 and carrying 51 inner surface of tube body, and the deflector 52 is in carrying 51 axis of tube body
0 °-90 ° angles, and 52 spacing of two neighboring deflector be carry 51 diameter of tube body 1/6-1/3, the nozzle 53 to
Two few, in carrying 51 side wall of tube body, and each nozzle ring 53 is evenly distributed with around carrying 51 axis of tube body, and with carrying 51 axis of tube body
Line is in 0 ° -90 ° angles, parallel with one another between the nozzle 53 and pass through control valve 15 and be interconnected with gas-guide tube 13.
In the present embodiment, 51 cross section of carrying tube body is any one in rectangle, isosceles trapezoidal structure.
In the present embodiment, the driving mechanism 3 is any one in motor, internal combustion engine.
In the present embodiment, the turntable mechanism 4 is three-dimensional turntable, and the 4 upper angle sensor 15 of turntable mechanism,
And angular transducer 15 is electrically connected with control circuit 6.
In the present embodiment, the control circuit 6 include data processing module, data communication module, data bus module,
Data communication terminal 61, wireless data communication antenna 62 and drive module, the data bus module respectively with data processing
Module, data communication module and drive module electrical connection, the data communication module and data communication terminal 61, without line number
It is electrically connected according to communication antenna 62, and passes through data communication terminal 61, wireless data communication antenna 62 and unmanned plane operating system
Electrical connection, the drive module are electrically connected respectively with driving mechanism 3, turntable mechanism 4.
Present device is simple in structure, flexible and convenient to use, operation the degree of automation, integration degree, the degree of modularity
On the one hand height can effectively improve the intensity of unmanned plane rotor installation positional flexibility and bearing structure, help to improve nobody
The convenience and reliability of machine equipment assembling, dismounting and part replacement, on the other hand can effectively improve unmanned plane rotor system
The power performance of system and flexibility and the reliability of driving power adjustment control, holding for unmanned machine equipment operation is improved so as to reach
Loading capability and flight control stability, the purpose of flexibility and reliability.
The basic principles, main features and the advantages of the invention have been shown and described above.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and the above embodiments and description only describe this
The principle of invention, without departing from the spirit and scope of the present invention, various changes and improvements may be made to the invention, these changes
Change and improvement all fall within the protetion scope of the claimed invention.The claimed scope of the invention by appended claims and its
Equivalent thereof.
Claims (9)
- A kind of 1. efficient unmanned plane automatic adjustment rotor structure, which is characterized in that the efficient unmanned plane automatic adjustment rotor Structure includes bearing base, rotor, driving mechanism, turntable mechanism, air hose and control circuit, and the bearing base is rectangular slab Shape structure sets at least one locating slot on the bearing base, and the locating slot is evenly distributed with along bearing base axis direction, and The locating slot axis is vertical with bearing base axis and intersects, and the bearing base end passes through turntable structure and nobody Machine fuselage is hinged, and the bearing base axis intersects with unmanned aerial vehicle body axis and is in 0 ° -180 ° angles, described Air hose be hinged in the locating slot, and with positioning groove sidewall by least two turntable mechanisms, and the air hose axis Line is with bearing base lower surface in 30 ° -90 ° angles, and the rotor, driving mechanism are in air hose, wherein the rotation The wing is located at right over driving mechanism and passes through transmission shaft to be connected with each other with driving mechanism, and the rotor, driving mechanism are and wind The coaxial distribution of pipe, the driving mechanism are connected with each other by locating rack and air hose, and the control circuit is embedded in bearing base It is interior, and be electrically connected respectively with driving mechanism, turntable mechanism.
- 2. a kind of efficient unmanned plane automatic adjustment rotor structure according to claim 1, it is characterised in that：The carrying Pedestal cross section is any one in fusiformis structure and droplet-shaped structure.
- 3. a kind of efficient unmanned plane automatic adjustment rotor structure according to claim 1, it is characterised in that：The carrying Pedestal be airtight cavity structure, including bearing keel, guard shield and inner liner wall, the bearing keel be frame structure, institute The guard shield stated is coated on bearing keel outer surface, and the inner liner wall is coated on bearing keel inner surface, the protection Closed cushion chamber is formed between shell and inner liner wall, the inner liner wall forms the bearing cavity of closed structure.
- 4. a kind of efficient unmanned plane automatic adjustment rotor structure according to claim 3, it is characterised in that：The buffering Intracavitary sets elastic insert, and at least one booster pump is set in the bearing cavity, and gas-guide tube and wind were moved in described booster pump one end Pipe side wall connects, and the booster pump other end is connected, and described by least one gas-guide tube with bearing base upper surface Bearing base is evenly distributed in the upper surface several open-works, and each open-work is interconnected with gas-guide tube.
- 5. a kind of efficient unmanned plane automatic adjustment rotor structure according to claim 1, it is characterised in that：The air hose Including tube body carrying tube body, deflector and nozzle, wherein the carrying tube body is hollow tubular structures, carrying tube body upper surface Be all provided with several deflectors at lower face, the deflector is hinged, and described by turntable mechanism and carrying inner surface of tube body Deflector and carrier pipe body axis in 0 ° -90 ° angles, and 1/ that two neighboring water conservancy diversion spacing between plates be carrying pipe diameter 6-1/3, the nozzle at least two, in carrying tube wall, and each nozzle ring is evenly distributed with around carrier pipe body axis, and It is parallel with one another between the nozzle and pass through control valve and be interconnected with gas-guide tube with carrier pipe body axis in 0 ° -90 ° angles.
- 6. a kind of efficient unmanned plane automatic adjustment rotor structure according to claim 1, it is characterised in that：The carrying Tube body cross section is any one in rectangle, isosceles trapezoidal structure.
- 7. a kind of efficient unmanned plane automatic adjustment rotor structure according to claim 1, it is characterised in that：The driving Mechanism is any one in motor, internal combustion engine.
- 8. a kind of efficient unmanned plane automatic adjustment rotor structure according to claim 1, it is characterised in that：The turntable Mechanism is three-dimensional turntable, and the turntable mechanism upper angle sensor, and angular transducer is electrically connected with control circuit.
- 9. a kind of efficient unmanned plane automatic adjustment rotor structure according to claim 1, it is characterised in that：The control Circuit includes data processing module, data communication module, data bus module, data communication terminal, wireless data communication antenna And drive module, the data bus module electrically connect respectively with data processing module, data communication module and drive module It connects, the data communication module is electrically connected with data communication terminal, wireless data communication antenna, and passes through data communication end Son, the electrical connection of wireless data communication antenna and unmanned plane operating system, the drive module respectively with driving mechanism, turntable Mechanism is electrically connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810062080.1A CN108216616B (en) | 2018-01-23 | 2018-01-23 | High-efficient unmanned aerial vehicle automatically regulated rotor structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810062080.1A CN108216616B (en) | 2018-01-23 | 2018-01-23 | High-efficient unmanned aerial vehicle automatically regulated rotor structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108216616A true CN108216616A (en) | 2018-06-29 |
| CN108216616B CN108216616B (en) | 2021-03-30 |
Family
ID=62668532
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810062080.1A Active CN108216616B (en) | 2018-01-23 | 2018-01-23 | High-efficient unmanned aerial vehicle automatically regulated rotor structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108216616B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109110120A (en) * | 2018-09-07 | 2019-01-01 | 佛山皖和新能源科技有限公司 | A kind of three rotor wing unmanned aerial vehicle lift systems |
| CN109110121A (en) * | 2018-09-07 | 2019-01-01 | 佛山皖和新能源科技有限公司 | A kind of novel three rotor wing unmanned aerial vehicles structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102105357A (en) * | 2008-05-30 | 2011-06-22 | 吉洛工业有限公司 | A flying machine comprising twin contra-rotating vertical axis propellers |
| US20140231582A1 (en) * | 2012-10-03 | 2014-08-21 | Sean Headrick | Methods and Systems of Constructing a Multi Rotor Aircraft Fuselage |
| CN105882959A (en) * | 2015-02-13 | 2016-08-24 | 空中客车防卫和太空有限责任公司 | Aircraft capable of vertical takeoff |
| CN106628161A (en) * | 2017-01-17 | 2017-05-10 | 深圳市哈威飞行科技有限公司 | Rapidly-disassembled duct structure |
| CN107117297A (en) * | 2017-05-06 | 2017-09-01 | 安徽省先胜农业发展有限公司 | A kind of multi-rotor aerocraft for pesticide spraying |
-
2018
- 2018-01-23 CN CN201810062080.1A patent/CN108216616B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102105357A (en) * | 2008-05-30 | 2011-06-22 | 吉洛工业有限公司 | A flying machine comprising twin contra-rotating vertical axis propellers |
| US20140231582A1 (en) * | 2012-10-03 | 2014-08-21 | Sean Headrick | Methods and Systems of Constructing a Multi Rotor Aircraft Fuselage |
| CN105882959A (en) * | 2015-02-13 | 2016-08-24 | 空中客车防卫和太空有限责任公司 | Aircraft capable of vertical takeoff |
| CN106628161A (en) * | 2017-01-17 | 2017-05-10 | 深圳市哈威飞行科技有限公司 | Rapidly-disassembled duct structure |
| CN107117297A (en) * | 2017-05-06 | 2017-09-01 | 安徽省先胜农业发展有限公司 | A kind of multi-rotor aerocraft for pesticide spraying |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109110120A (en) * | 2018-09-07 | 2019-01-01 | 佛山皖和新能源科技有限公司 | A kind of three rotor wing unmanned aerial vehicle lift systems |
| CN109110121A (en) * | 2018-09-07 | 2019-01-01 | 佛山皖和新能源科技有限公司 | A kind of novel three rotor wing unmanned aerial vehicles structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108216616B (en) | 2021-03-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206125436U (en) | Many rotors of abnormal shape plant protection unmanned aerial vehicle | |
| CN108216616A (en) | A kind of efficient unmanned plane automatic adjustment rotor structure | |
| CN108502188A (en) | A kind of plant protection drone spraying operation wind field test system and method | |
| CN213168607U (en) | Special test platform of unmanned aerial vehicle | |
| CN108252863B (en) | Novel automatic wind power generation device | |
| CN105510885B (en) | A kind of hermetically sealed safety monitoring radar arrangement of lightweight | |
| CN110082060A (en) | A kind of plant protection unmanned aerial vehicle wind resistance test equipment and method | |
| CN211329952U (en) | Spraying device for electric power grid outdoor equipment | |
| CN111005837A (en) | Air turbine and power generation device | |
| CN104787322A (en) | Power system and multi-rotor aircraft | |
| CN106733936B (en) | A kind of dust exhaust apparatus on the automatic assembly line of stator | |
| CN104743109B (en) | Dynamical system and aircraft | |
| CN110996647A (en) | Five-axis linkage chip mounter | |
| CN108528545B (en) | A kind of efficient vehicle intelligent spoiler | |
| CN210687400U (en) | 360-degree rotating mechanism of vacuum gas circuit | |
| KR102321192B1 (en) | Power generator using wind power | |
| TWM621488U (en) | Unmanned aerial device having cleaning function | |
| CN211598911U (en) | Air turbine and power generation device | |
| CN204866358U (en) | Digital shower nozzle of miniature two dimension | |
| CN109159902B (en) | Drainage mechanism for air inlet of unmanned aerial vehicle engine | |
| CN209729669U (en) | A kind of energy-economic transformer cooling device | |
| CN111022245A (en) | Air turbine and power generation device | |
| CN109159903A (en) | A kind of unmanned vehicle engine progress implication flow modulation device | |
| CN208291491U (en) | A kind of formation unmanned plane performance is anti-settling to use system | |
| CN208278330U (en) | A kind of plant protection drone spraying operation wind field test macro |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |