CN109110121A - A kind of novel three rotor wing unmanned aerial vehicles structure - Google Patents
A kind of novel three rotor wing unmanned aerial vehicles structure Download PDFInfo
- Publication number
- CN109110121A CN109110121A CN201811046111.0A CN201811046111A CN109110121A CN 109110121 A CN109110121 A CN 109110121A CN 201811046111 A CN201811046111 A CN 201811046111A CN 109110121 A CN109110121 A CN 109110121A
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- rotor
- fuselage
- short limb
- wind pressure
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- 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
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The present invention relates to a kind of novel three rotor wing unmanned aerial vehicles structures, including bearing keel, fuselage, vertical rotor, rotor, short limb, turntable mechanism, angular transducer, wind pressure sensor and flight control system, bearing keel is coated on fuselage second half section outer surface, vertical rotor is connected with each other by the bearing keel side surface outside short limb and fuselage, rotor is located at bearing keel rear end face, at least three wind pressure sensors are all provided on each short limb, fuselage front side surface is evenly distributed at least three wind pressure sensors.One aspect of the present invention can effectively be the lift of unmanned machine equipment abundance, on the other hand can effectively realize the flexibility and convenience of unmanned plane VTOL, level run operation, can also be achieved quickly to the adjustment of UAV system memory lift system, replacement.
Description
Technical field
The present invention relates to a kind of unmanned plane structures, are exactly a kind of novel three rotor wing unmanned aerial vehicles structures.
Background technique
In the unmanned machine equipment of rotary wind type used at present, rotor mechanism is mounted on fuselage side surface often through attachment beam
Or front end face, rear end face and the upper surface any position of direct position fuselage, although this structure can satisfy mentions for unmanned plane
Required lift when for flight meets the needs of unmanned plane during flying operation, but on the one hand unmanned plane lifting body structure is caused to fix,
The direction that lift suffered by unmanned plane is adjusted flexibly cannot be changed according to air-flow in-flight, on the one hand cause unmanned plane during flying
When operation energy consumption it is relatively high, another party when causing unmanned machine equipment flight to complicated air-flow environment adjustment and adaptability
Difference has seriously affected flexibility and reliability that unmanned machine equipment uses, meanwhile, on the one hand traditional rotor-hub configuration mode needs
To increase additional weight for unmanned plane, influence effective bearing capacity of unmanned plane, on the other hand also easily unmanned plane is caused to set
Standby internal body space is affected, and leads in unmanned machine equipment machine that space utilization rate is low, seriously affects unmanned machine equipment
The flexibility of bearing capacity and carrying operation, simultaneously, the lift system such as rotor, driving engine of current unmanned machine equipment
It connects relatively fixed between system equipment and fuselage, therefore causes when lift system replaced, is safeguarded and when upkeep operation, is torn open
It removes and installation difficulty is big, and working efficiency is low, to seriously affect unmanned plane equipment fault expulsion efficiency and unmanned plane is set
The stability of received shipment row.
Therefore it is directed to this status, there is an urgent need to develop a kind of completely new tire constructions, to meet the needs of actual use.
Summary of the invention
In view of the shortcomings of the prior art, the present invention provides a kind of novel three rotor wing unmanned aerial vehicles structure, the invention knot
Structure is simple, and operational efficiency is high, and control accuracy flexible to lift system regulation is high, on the one hand can be effectively sufficient for unmanned machine equipment
Lift, and the adjustment of lift direction is flexible and convenient, can effectively improve unmanned machine equipment to the resilience of complicated air-flow environment simultaneously
Unmanned machine equipment operation energy consumption is effectively reduced, on the other hand can effectively realize unmanned plane VTOL, level run operation
Flexibility and convenience save space in unmanned machine equipment machine, improve the space utilization rate and payload energy of unmanned machine equipment
Power, so that the stability, reliability, convenience and the airworthiness that greatly improve unmanned machine equipment operation in addition to this can also be real
Now quickly to the adjustment of UAV system memory lift system, replacement, while improving unmanned plane failure expulsion efficiency, effectively
Improve flexibility, the stability of unmanned machine equipment operation.
To achieve the goals above, the present invention is to realize by the following technical solutions:
A kind of novel three rotor wing unmanned aerial vehicles structure, including bearing keel, fuselage, vertical rotor, rotor, short limb, turn
Platform mechanism, angular transducer, wind pressure sensor and flight control system, fuselage is axis and level is in the close of 0 ° -45 ° angles
Cavity body structure is closed, bearing keel is the frame structure being coaxially distributed with fuselage, and bearing keel is coated on fuselage second half section outer surface,
And be slidably connected by least two directive slide tracks with fuselage outer surface, directive slide track and bearing keel inner surface are and outside fuselage
Surface parallelly distribute on, and at least two locating pieces are all provided on every directive slide track, positioning ring is uniformly distributed along directive slide track, its rear end with
It is connected with each other between directive slide track by electromagnetic location pin, front end face is connected with each other by electromagnetic location pin and fuselage outer surface, is erected
Totally two, the direct rotary wing, fuselage two sides are symmetrically distributed in fuselage axis, each vertical rotor passes through the carrying dragon outside short limb and fuselage
Bone side surface is connected with each other, and short limb both ends set turntable structure respectively, and by turntable mechanism and bearing keel outer surface and vertically
Rotor outer surface is hinged, and short limb axis is mutually perpendicular to be distributed with fuselage axis, and short limb lower end surface is horizontal by 0 ° -60 °
Angle, short limb axis and vertical rotor axis are in 0 ° -60 ° angles, and vertical rotor axis is horizontal by ± 45 °, rotor
It one, is coaxially distributed positioned at bearing keel rear end face and with bearing keel, the distance between vertical rotor, rotor not size
In the 1/5 of bearing keel effective length, angular transducer quantity is consistent with turntable mechanism quantity, and is all provided on each turntable mechanism
At least one angular transducer, wind pressure sensor is several, at least three wind pressure sensors is all provided on each short limb, and along short limb axis
Line direction is evenly arranged on upper surface, front end face and the lower end surface of short limb, and each wind pressure of short limb upper surface, front end face and lower end surface
Sensor is spaced apart from each other distribution, and fuselage front side surface is evenly distributed at least three wind pressure sensors, the wind pressure sensor of fuselage side surface
It is uniformly distributed along fuselage axis, and the wind pressure sensor of fuselage two sides is symmetrical with fuselage axis, flight control system is embedded in fuselage
It is interior, and electrically connect with vertical rotor, rotor, turntable mechanism, angular transducer, wind pressure sensor and electromagnetic location pin respectively
It connects.
Further, it is connected with each other between the short limb and bearing keel and vertical rotor by flexible boot, it is described
Flexible boot to be coated on turntable mechanism outer and be coaxially distributed with turntable mechanism.
Further, the corresponding short limb position of the turntable mechanism sets locating slot, the turntable mechanism effective height
1/3-2/3 part is coaxially distributed in locating slot and with locating slot.
Further, the cross face of the short limb front end face and rear end face is arc structure, and short limb upper surface is
Arcuate structure, lower end surface are planar structure, and upper surface length is 1.5-3 times of lower end surface length.
Further, the vertical rotor, rotor include rotor, transmission shaft, gearbox, driving mechanism and hold
Carry shell, the gearbox, driving mechanism are embedded in carrying shell, and the gearbox by transmission shaft and driving mechanism and
Rotor connection, the rotor are located at outside carrying shell and are coaxially distributed with transmission shaft.
Further, the driving mechanism is any one in motor and internal combustion engine.
Further, the turntable mechanism is the three-dimensional state or any one in dimensional turntable of stepping motor driving
Kind.
Further, the flight control system is SCM Based automatic control system, and flight control system
If at least one serial communication port.
The configuration of the present invention is simple, operational efficiency is high, and control accuracy flexible to lift system regulation is high, on the one hand can be effective
For the lift of unmanned machine equipment abundance, and the adjustment of lift direction is flexible and convenient, can effectively improve unmanned machine equipment to complicated air-flow
Simultaneously unmanned machine equipment operation energy consumption is effectively reduced in the resilience of environment, on the other hand can effectively realize that unmanned plane vertically rises
It drops, the flexibility and convenience of level run operation, saves space in unmanned machine equipment machine, improve the space benefit of unmanned machine equipment
With rate and payload capability, to greatly improve stability, reliability, convenience and the seaworthiness of unmanned machine equipment operation
Property, it in addition to this, can also be achieved quickly to the adjustment of UAV system memory lift system, replacement, improving unmanned plane failure row
Out while efficiency, flexibility, the stability of unmanned machine equipment operation are effectively improved.
Detailed description of the invention
The following describes the present invention in detail with reference to the accompanying drawings and specific embodiments.
Fig. 1 is schematic structural view of the invention；
Specific embodiment
To be easy to understand the technical means, the creative features, the aims and the efficiencies achieved by the present invention, below with reference to
Specific embodiment, the present invention is further explained.
The novel three rotor wing unmanned aerial vehicles structure of one kind as described in Figure 1, including bearing keel, fuselage, vertical rotor, horizontal rotation
The wing, short limb, turntable mechanism, angular transducer, wind pressure sensor and flight control system, fuselage be axis and it is horizontal in 0 °-
The airtight cavity structure of 45 ° of angles, bearing keel is the frame structure being coaxially distributed with fuselage, after bearing keel is coated on fuselage
Half section of outer surface, and be slidably connected by least two directive slide tracks with fuselage outer surface, table in directive slide track and bearing keel
Face with fuselage outer surface parallelly distribute on, and is all provided at least two locating pieces on every directive slide track, positioning ring is along directive slide track
It is uniformly distributed, it is connected with each other between its rear end and directive slide track by electromagnetic location pin, front end face passes through electromagnetic location pin and fuselage appearance
Face is connected with each other, and vertical rotor totally two, is symmetrically distributed in fuselage two sides with fuselage axis, each vertical rotor passes through short limb and machine
Bearing keel side surface outside body is connected with each other, and short limb both ends set turntable structure respectively, and pass through turntable mechanism and bearing keel
Outer surface and vertical rotor outer surface are hinged, and short limb axis is mutually perpendicular to be distributed with fuselage axis, short limb lower end surface and water
Plane is in 0 ° -60 ° angles, and short limb axis and vertical rotor axis are in 0 ° -60 ° angles, vertical rotor axis horizontal by
± 45 °, rotor one, be coaxially distributed positioned at bearing keel rear end face and with bearing keel, vertical rotor, rotor it
Between distance be not less than the 1/5 of bearing keel effective length very much, angular transducer quantity is consistent with turntable mechanism quantity, and each
At least one angular transducer is all provided on turntable mechanism, wind pressure sensor is several, and at least three wind pressure biography is all provided on each short limb
Sensor, and along upper surface, front end face and the lower end surface that short limb axis direction is evenly arranged on short limb, and short limb upper surface, front end face
It is spaced apart from each other distribution with each wind pressure sensor of lower end surface, fuselage front side surface is evenly distributed at least three wind pressure sensors, fuselage side
The wind pressure sensor on surface is uniformly distributed along fuselage axis, and the wind pressure sensor of fuselage two sides is symmetrical with fuselage axis, flight
Control system in the fuselage, and respectively with vertical rotor, rotor, turntable mechanism, angular transducer, wind pressure sensor and
The electrical connection of electromagnetic location pin.
In the present embodiment, it is connected with each other between the short limb and bearing keel and vertical rotor by flexible boot, institute
The flexible boot stated is coated on outside turntable mechanism and is coaxially distributed with turntable mechanism.
In the present embodiment, the corresponding short limb position of the turntable mechanism sets locating slot, and the turntable mechanism is effectively high
1/3-2/3 part of degree is coaxially distributed in locating slot and with locating slot.
In the present embodiment, the cross face of the short limb front end face and rear end face is arc structure, and short limb upper surface
For arcuate structure, lower end surface is planar structure, and upper surface length is 1.5-3 times of lower end surface length.
In the present embodiment, the vertical rotor, rotor include rotor, transmission shaft, gearbox, driving mechanism and
Shell is carried, the gearbox, driving mechanism are embedded in carrying shell, and the gearbox passes through transmission shaft and driving mechanism
It is connected with rotor, the rotor is located at outside carrying shell and is coaxially distributed with transmission shaft.
In the present embodiment, the driving mechanism is any one in motor and internal combustion engine.
In the present embodiment, the turntable mechanism is the three-dimensional state or any in dimensional turntable of stepping motor driving
It is a kind of.
In the present embodiment, the flight control system is SCM Based automatic control system, and control system of flying
System sets at least one serial communication port.
The present invention in specific implementation, first to bearing keel, fuselage, vertical rotor, rotor, short limb, turntable machine
Structure, angular transducer, wind pressure sensor and flight control system, and by the master control system of flight control system and unmanned machine equipment
Between be electrically connected, assemble thereby completing the present invention spare.
In unmanned machine equipment landing operation, diameter is run by vertical rotor, and rotor is out of service, while by turning
Angle between platform institutional adjustment short limb and fuselage and vertical rotor, on the one hand by vertical rotor to unmanned machine equipment apply with it is vertical
Direction is in the lift of 0 ° -45 ° range within angles, on the other hand provides volume by flowing through short limb airflow on surface by short limb for fuselage
Outer lift so that fuselage be driven to carry out vertical lift operation, and is realized in lift work and carries out certain model to unmanned aerial vehicle body
Enclose interior translation.
Unmanned plane it is sliding run landing or take off vertically reach certain altitude and carry out horizontal flight when, vertical rotor, horizontal rotation
The wing is run simultaneously, driving power when on the one hand providing flight by rotor for fuselage in the horizontal direction, realizes that fuselage exists
It is run in horizontal direction, is machine by short limb on the other hand by the angle between platform institutional adjustment short limb and fuselage and vertical rotor
Additional lift is provided when body level run, applying unmanned machine equipment with vertical direction by the operation of vertical rotor is in 0 ° -45 °
The lift of range within angle flies for fuselage while providing the lift of vertical direction and the lift of horizontal direction, to realize
It drops or takes off vertically and reach the needs that certain altitude carries out horizontal flight, while separately can be in landing, by adjusting vertical rotor
And short limb, resistance is provided for fuselage, stopping power is improved and shortens ground run distance.
In flight course, by be located at short limb and fuselage on each wind pressure sensor detect in due course fuselage in-flight by
Then on the one hand the airflow influence and lift arrived adjusts the operation power of vertical rotor, rotor, on the other hand adjusts short limb
With the angle between fuselage and vertical rotor, on the one hand being applied unmanned machine equipment with vertical direction by vertical rotor is in 0 ° -45 °
On the other hand the lift of range within angle provides additional lift by flowing through short limb airflow on surface by short limb for fuselage, to disappear
Influence when being run except complicated air-flow to fuselage, it is separately steady when effective raising fuselage flight while ensuring that lift is stablized
It is qualitative.
The equipment such as vertical rotor, rotor, short limb, turntable mechanism, angular transducer are safeguarded, replacing
When, or when needing to be adjusted vertical rotor, rotor power etc. because of flight, the directly positioning that is connect with fuselage of release
Pin, vertical rotor, rotor, short limb, turntable mechanism, the angular transducer then being connect by bearing keel and with bearing keel
Etc. equipment carry out overall pulling down, then will meet need new bearing keel and connect with the bearing keel vertical rotor,
The equipment such as rotor, short limb, turntable mechanism, angular transducer are assembled on fuselage, and quick-replaceable adjustment operation can be realized,
Improve unmanned plane equipment operation stability and successional purpose.
The configuration of the present invention is simple, operational efficiency is high, and control accuracy flexible to lift system regulation is high, on the one hand can be effective
For the lift of unmanned machine equipment abundance, and the adjustment of lift direction is flexible and convenient, can effectively improve unmanned machine equipment to complicated air-flow
Simultaneously unmanned machine equipment operation energy consumption is effectively reduced in the resilience of environment, on the other hand can effectively realize that unmanned plane vertically rises
It drops, the flexibility and convenience of level run operation, saves space in unmanned machine equipment machine, improve the space benefit of unmanned machine equipment
With rate and payload capability, to greatly improve stability, reliability, convenience and the seaworthiness of unmanned machine equipment operation
Property, it in addition to this, can also be achieved quickly to the adjustment of UAV system memory lift system, replacement, improving unmanned plane failure row
Out while efficiency, flexibility, the stability of unmanned machine equipment operation are effectively improved.
It should be understood by those skilled in the art that the present invention is not limited to the above embodiments.Above-described embodiment and explanation
It is merely illustrated the principles of the invention described in book.Without departing from the spirit and scope of the present invention, the present invention also has
Various changes and modifications.These changes and improvements all fall within the protetion scope of the claimed invention.The claimed scope of the invention
It is defined by the appending claims and its equivalent thereof.
Claims (8)
1. a kind of novel three rotor wing unmanned aerial vehicles structure, it is characterised in that: the three rotor wing unmanned aerial vehicle structure of invention includes carrying
Keel, fuselage, vertical rotor, rotor, short limb, turntable mechanism, angular transducer, wind pressure sensor and flight control system
System, the fuselage are axis and the horizontal airtight cavity structure in 0 ° -45 ° angles, and the bearing keel is same with fuselage
The frame structure of axis distribution, the bearing keel are coated on fuselage second half section outer surface, and by least two directive slide tracks with
Fuselage outer surface is slidably connected, and the directive slide track and bearing keel inner surface are and every with fuselage outer surface parallelly distribute on
At least two locating pieces are all provided on directive slide track, the positioning ring is uniformly distributed along directive slide track, between its rear end and directive slide track
It is connected with each other by electromagnetic location pin, front end face is connected with each other by electromagnetic location pin and fuselage outer surface, the vertical rotation
Totally two, the wing, fuselage two sides are symmetrically distributed in fuselage axis, each vertical rotor passes through the bearing keel side outside short limb and fuselage
Surface is connected with each other, and the short limb both ends set turntable structure respectively, and by turntable mechanism and bearing keel outer surface and erect
Direct rotary wing outer surface is hinged, and the short limb axis is mutually perpendicular to be distributed with fuselage axis, short limb lower end surface and horizontal plane
In 0 ° -60 ° angles, the short limb axis and vertical rotor axis are in 0 ° -60 ° angles, the vertical rotor axis with
Horizontal plane is in ± 45 °, and the rotor one is coaxially distributed positioned at bearing keel rear end face and with bearing keel, described
Vertical rotor, the distance between rotor be less less than the 1/5 of bearing keel effective length, the angular transducer number
Amount is consistent with turntable mechanism quantity, and at least one angular transducer is all provided on each turntable mechanism, the wind pressure sensor
It is several, at least three wind pressure sensors are all provided on each short limb, and upper surface, the front end of short limb are evenly arranged on along short limb axis direction
On face and lower end surface, and each wind pressure sensor of short limb upper surface, front end face and lower end surface is spaced apart from each other distribution, the fuselage
Front side surface is evenly distributed at least three wind pressure sensors, and the wind pressure sensor of fuselage side surface is uniformly distributed along fuselage axis, and fuselage two
The wind pressure sensor of side is symmetrical with fuselage axis, and the flight control system is revolved in fuselage, and respectively with vertical
The wing, rotor, turntable mechanism, angular transducer, wind pressure sensor and the electrical connection of electromagnetic location pin.
2. the novel three rotor wing unmanned aerial vehicles structure of one kind according to claim 1, it is characterised in that: the short limb and carrying
Be connected with each other between keel and vertical rotor by flexible boot, the flexible boot be coated on turntable mechanism it is outer and with turn
Platform mechanism is coaxially distributed.
3. the novel three rotor wing unmanned aerial vehicles structure of one kind according to claim 1, it is characterised in that: the turntable mechanism pair
The short limb position answered sets locating slot, and 1/3-2/3 part of turntable mechanism effective height is embedded in locating slot and and locating slot
Coaxial distribution.
4. the novel three rotor wing unmanned aerial vehicles structure of one kind according to claim 1, it is characterised in that: the short limb front end face
Cross face with rear end face is arc structure, and short limb upper surface is arcuate structure, and lower end surface is planar structure, and upper surface is long
Degree is 1.5-3 times of lower end surface length.
5. the novel three rotor wing unmanned aerial vehicles structure of one kind according to claim 1, it is characterised in that: the vertical rotor,
Rotor includes rotor, transmission shaft, gearbox, driving mechanism and carrying shell, and the gearbox, driving mechanism are embedded in
It carries in shell, and the gearbox is connect by transmission shaft with driving mechanism and rotor, the rotor is located at outside carrying shell
And it is coaxially distributed with transmission shaft.
6. the novel three rotor wing unmanned aerial vehicles structure of one kind according to claim 5, it is characterised in that: the driving mechanism is
Any one in motor and internal combustion engine.
7. the novel three rotor wing unmanned aerial vehicles structure of one kind according to claim 1, it is characterised in that: the turntable mechanism is
Stepping motor driving three-dimensional state or dimensional turntable in any one.
8. the novel three rotor wing unmanned aerial vehicles structure of one kind according to claim 1, it is characterised in that: the flight controls system
System is SCM Based automatic control system, and flight control system sets at least one serial communication port.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811046111.0A CN109110121A (en) | 2018-09-07 | 2018-09-07 | A kind of novel three rotor wing unmanned aerial vehicles structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811046111.0A CN109110121A (en) | 2018-09-07 | 2018-09-07 | A kind of novel three rotor wing unmanned aerial vehicles structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109110121A true CN109110121A (en) | 2019-01-01 |
Family
ID=64858709
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811046111.0A Withdrawn CN109110121A (en) | 2018-09-07 | 2018-09-07 | A kind of novel three rotor wing unmanned aerial vehicles structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN109110121A (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101837195A (en) * | 2010-01-21 | 2010-09-22 | 罗之洪 | Model airplane with vertical takeoff and landing |
| CN106672232A (en) * | 2017-03-02 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Efficient vertical takeoff and landing aircraft |
| CN108116643A (en) * | 2018-01-23 | 2018-06-05 | 焦作大学 | A kind of novel automatic water body detection device |
| CN108216616A (en) * | 2018-01-23 | 2018-06-29 | 焦作大学 | A kind of efficient unmanned plane automatic adjustment rotor structure |
| CN108252863A (en) * | 2018-01-23 | 2018-07-06 | 焦作大学 | A kind of novel automatic wind power generation plant |
| CN108312945A (en) * | 2018-02-08 | 2018-07-24 | 焦作大学 | A kind of automobile-used operation cabin of intelligent operation |
-
2018
- 2018-09-07 CN CN201811046111.0A patent/CN109110121A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101837195A (en) * | 2010-01-21 | 2010-09-22 | 罗之洪 | Model airplane with vertical takeoff and landing |
| CN106672232A (en) * | 2017-03-02 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Efficient vertical takeoff and landing aircraft |
| CN108116643A (en) * | 2018-01-23 | 2018-06-05 | 焦作大学 | A kind of novel automatic water body detection device |
| CN108216616A (en) * | 2018-01-23 | 2018-06-29 | 焦作大学 | A kind of efficient unmanned plane automatic adjustment rotor structure |
| CN108252863A (en) * | 2018-01-23 | 2018-07-06 | 焦作大学 | A kind of novel automatic wind power generation plant |
| CN108312945A (en) * | 2018-02-08 | 2018-07-24 | 焦作大学 | A kind of automobile-used operation cabin of intelligent operation |
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Application publication date: 20190101 |