CN109263917A - One kind is mixed to move more rotor manned aircraft - Google Patents
One kind is mixed to move more rotor manned aircraft Download PDFInfo
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- CN109263917A CN109263917A CN201811274877.4A CN201811274877A CN109263917A CN 109263917 A CN109263917 A CN 109263917A CN 201811274877 A CN201811274877 A CN 201811274877A CN 109263917 A CN109263917 A CN 109263917A
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- rotor
- piggyback pod
- electric
- manned aircraft
- wing
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- 239000000203 mixture Substances 0.000 claims description 11
- 239000002131 composite material Substances 0.000 claims description 7
- 230000005611 electricity Effects 0.000 claims description 5
- 238000002485 combustion reaction Methods 0.000 claims description 4
- 238000007666 vacuum forming Methods 0.000 claims description 4
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 1
- 229910052799 carbon Inorganic materials 0.000 claims 1
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- 101100438971 Caenorhabditis elegans mat-1 gene Proteins 0.000 description 3
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- 239000000463 material Substances 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 238000009941 weaving Methods 0.000 description 3
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- 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
- 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
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- 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
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
- Radio Relay Systems (AREA)
Abstract
It is mixed the invention discloses one kind and moves more rotor manned aircraft, including fuselage, fixed-wing, empennage, further include central control system, and the piggyback pod being connect with the central control system, the piggyback pod includes electric-powered cabin and liquid fuel piggyback pod；End of the electric-powered freight space inside the fixed-wing；Brushless motor is provided in the electric-powered cabin, the brushless motor has electronic rotor by dynamic rotation axis connection, and the electronic rotor is located at the end inside the empennage using the double-deck rotor distribution, the liquid fuel piggyback pod；The liquid fuel piggyback pod provides power to fuels and energy rotor.The present invention can effectively mitigate the load of engine fuel, and improve cruise duration, the design method of electronic rotor auxiliary fuel rotor, increase the safety and easily-controllable property of aircraft entirety.
Description
Technical field
The present invention relates to vehicle technology field, a kind of more particularly to mix moves more rotor manned aircraft.
Background technique
With the progress of related art method, existing manned aero-engine has had significantly in performance indicator
Progress, such as oil consumption rate compare the reduction having before this by a relatively large margin with pollutant emission index.But for another aspect,
With international community and civil aviation organization to civil engine the increasingly higher demands in economy and the feature of environmental protection, how to make
Aero-engine meets growing high performance requirements, is still the major issue faced for a long time.
Presently, manned aircraft mostly uses greatly single-power mode, and manned aero-engine mainly passes through compressed gas
Expansion work is heated, converts mechanical energy for chemical energy.Although increasing engine pressure ratio and combustor exit temperature can be improved
The thermal efficiency of complete machine is constrained to the water of design level, level of processing, material capability and cooling technology to reduce oil consumption rate
Flat, the turbine inlet temperature of existing aero-engine has been approached the limiting value of safe handling, if there is aerial engine cut-off, no
It can restart, it will seriously affect manned Flight Safety, be difficult the raising for having obvious degree.
Wind stick structure mainly includes two kinds: fixed-wing and more rotors, wherein fixed gyroplane mainly includes
Two big fixed-wings can take off vertically, vertical landing and forward flight, and flight safety is stablized, but fixed wing aircraft is logical
Longer runway often is required to provide the power to take off, is taken off limited.More gyroplanes take off dynamic without runway offer
Power, and can stagnate in the sky, but single fuels and energy is used to control more gyroplane flight poor operabilities, it can not
Meet the requirement on flexibility of more gyroplane flights.
Accordingly, it would be desirable to there is a kind of cruise duration long, high mixed of safety, easily-controllable property, which moves more rotor manned aircraft, to be become
Those skilled in the art's technical problem urgently to be solved.
Summary of the invention
More rotor manned aircraft are moved in view of this, mixing the present invention provides one kind, can effectively mitigate engine fuel
Load, and improve cruise duration, the design method of electronic rotor auxiliary fuel rotor increases the safety of aircraft entirety
With easily-controllable property.
To achieve the goals above, the present invention adopts the following technical scheme:
One kind is mixed to move more rotor manned aircraft, including fuselage, is set to the fixed-wing of the fuselage two sides, and be set to institute
The empennage for stating afterbody further includes central control system, and the piggyback pod connecting with the central control system, and the piggyback pod includes
Electric-powered cabin and liquid fuel piggyback pod；
End of the electric-powered freight space inside the fixed-wing；It is provided with brushless motor in the electric-powered cabin, institute
Stating brushless motor has electronic rotor by dynamic rotation axis connection, drives the electronic rotor wing rotation, and the electronic rotor uses
The double-deck rotor distribution is separately positioned on the double leaf of the mounting rack two sides including the mounting rack being connected with the dynamic rotation axis
Rotor；
The liquid fuel piggyback pod is located at the end inside the empennage；The liquid fuel piggyback pod is to fuels and energy rotor
Power is provided；The fuels and energy rotor is vertically mounted on the empennage end.
It is provided by the invention it is mixed move more rotor manned aircraft with multi-power system, using 1 liquid fuel piggyback pod,
The three of 2 electric-powered cabins start Force system；The posture of electronic rotor can be changed by the control to two electric-powered cabins
To realize auxiliary electric control, the long endurance oceangoing voyage journey of the dynamic aircraft of oil can be retained and effectively improve oil machine flame-out in flight
The survival ability of aircraft afterwards can also carry out task when necessary with the electric power of low noise and fly in the dynamic flight course of oil
Row.
VTOL, pivot stud, the aerial reversing of aircraft may be implemented in the piggyback pod under the control of central control system
Etc. functions, make aircraft that there is the easily-controllable property of height, so that it meets cruise, disaster area is relieved the people in stricken areas etc. special duties use demand.
Preferably, the brushless motor exports rotating torque to the dynamic rotation axis, and then drives the electronic rotor
Rotation.The electric-powered cabin configures battery, can work independently and provide power to the brushless motor, and this stand alone type is set
The mode of setting makes aircraft be suitable for various operating conditions, without being influenced by liquid fuel piggyback pod.
Preferably, the central control system includes navigation posture selection subsystem, navigation posture selection subsystem output
Signal to powershift subsystem, the powershift subsystem outputs control signals to the piggyback pod.Central control system conduct
Control mechanism directly exports control instruction to piggyback pod, and can be realized different flight state by powershift subsystem to need
Ask the lower orderly selection to power source.
Preferably, the navigation posture selection subsystem selects the offline mode of the aircraft, and according to institute
It states offline mode and exports control instruction to the powershift subsystem；The offline mode includes low cruise, short distance
Drop, hovering, rotor tilt.The presetting flight operation that can satisfy multi-state of plurality of flight, different flight
Mode corresponds to different control instructions.
Preferably, the powershift subsystem connects the brushless motor, for controlling the revolving speed of the brushless motor
And torque；The powershift subsystem is also connected with the liquid fuel piggyback pod, for controlling fuels and energy actuating.
Preferably, the fuels and energy rotor is using the double-deck rotor distribution, and two layers of rotor is coaxially disposed.
Preferably, it is provided with fuel cell in the liquid fuel piggyback pod, for turning extra fuel combustion energy
It is changed to electric energy and stores.Fuel combustion utilization rate is helped to improve, efficiency, air conservation are effectively improved.
Preferably, the central control system further includes emergency starting subsystem, when the electric-powered cabin power consumption finishes
When, call the fuel cell for brushless motor power supply automatically.The setting of fuel cell is for coping with electric-powered cabin electricity
Low emergency case is measured, the problem of energy deficiency when preventing oceangoing voyage.
Preferably, the mounting rack is produced and processed using 3 D weaving carbon fiber composite material.3 D weaving carbon fiber
Tieing up composite material has rigidity by force, the high advantage of toughness, is able to bear the transmission of dynamic rotation axis and windage is brought to electronic rotor
Load.
Preferably, the fuselage and fixed-wing are all made of vacuum forming composite material and produce and process.Vacuum forming is multiple
Condensation material quality is slim and graceful, greatly reduces the own wt of aircraft, is beneficial to the navigation attitude control to aircraft.
It can be seen via above technical scheme that compared with prior art, being mixed the present disclosure provides one kind and moving more rotors
Manned vehicle has the advantages that firstly, mixed moving more rotor manneds by what the piggyback pod in three different dynamic sources formed
Each one, aircraft, i.e. fixed-wing both ends, empennage one, have more rotors and fixed-wing both of which concurrently.It can under more rotor modes
To carry out vertical rise and fall and hovering, make it that can take off landing without runway or other devices, under fixed-wing mode
The flight of high speed can be carried out, flight efficiency is higher；Secondly, electric-powered cabin is mounted on fixed-wing end, facilitate brushless electricity
The power transmission of machine, reduces the living load of dynamic rotation axis, and increases the stability and reliability of electronic rotor；Also, pacify
Mounted in fixed-wing end electric-powered cabin away from the center of gravity of complete machine fuselage farther out, can make aircraft hang down fly when with bigger
Side flies control moment, improves the mobility that aircraft hangs down when flying, realizes the flight of low cruise, short take-off and landing, high stability
Control；Again, oily electric hybrid structure can effectively mitigate the load of engine fuel, and improve cruise duration, electronic
The design method of rotor auxiliary fuel rotor increases the safety and easily-controllable property of aircraft entirety.
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 attached drawing is that provided by the invention mix moves more rotor manned Flight Vehicle Structure schematic diagrames；
Fig. 2 attached drawing is electronic rotor structure enlarged diagram provided by the invention；
Fig. 3 attached drawing is that provided by the invention mix moves more rotor manned aircraft central control system frame diagrams.
In Fig. 1:
1 it is fuselage, 2 be fixed-wing, 3 be empennage, 511 be dynamic rotation axis, 512 be electronic rotor, 513 is mounting rack.
In Fig. 2:
511 it is dynamic rotation axis, 513 be mounting rack, 514 is two-bladed rotor.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
It is mixed the embodiment of the invention discloses one kind and moves more rotor manned aircraft, one kind is mixed to move more rotor manned aircraft,
Including fuselage 1, it is set to the fixed-wing 2 of 1 two sides of fuselage, and is set to the empennage 3 of 1 tail portion of fuselage, further includes central control system
4, and the piggyback pod 5 connecting with central control system 4, piggyback pod 5 include electric-powered cabin 51 and liquid fuel piggyback pod 52；
Electric-powered cabin 51 is located at the end inside fixed-wing 2；Brushless motor 510, brushless electricity are provided in electric-powered cabin 51
Machine 510 is connected with electronic rotor 512 by dynamic rotation axis 511, and electronic rotor 512 is driven to rotate, and electronic rotor 512 is using double
Layer rotor distribution is separately positioned on the double leaf rotation of 513 two sides of mounting rack including the mounting rack 513 being connected with dynamic rotation axis 511
The wing 514；
Liquid fuel piggyback pod 52 is located at the end inside empennage 3；Liquid fuel piggyback pod 52 is provided to fuels and energy rotor 522
Power；Fuels and energy rotor 522 is vertically mounted on 3 end of empennage.
In order to further optimize the above technical scheme, brushless motor 510 exports rotating torque to dynamic rotation axis 511, into
And electronic rotor 512 is driven to rotate.
In order to further optimize the above technical scheme, central control system 4 includes navigation posture selection subsystem 41, navigation posture
Selection subsystem 41 outputs signal to powershift subsystem 42, and powershift subsystem 42 outputs control signals to piggyback pod 5.
In order to further optimize the above technical scheme, navigation posture selection subsystem 41 carries out the offline mode of aircraft
Selection, and control instruction is exported to powershift subsystem 42 according to offline mode；Offline mode includes low cruise, short distance
Landing, hovering, rotor tilt.
In order to further optimize the above technical scheme, powershift subsystem 42 connects brushless motor 510, for controlling nothing
The revolving speed of brush motor 510 and torque；Powershift subsystem 42 is also connected with liquid fuel piggyback pod 52, for controlling fuels and energy
Actuating.
In order to further optimize the above technical scheme, fuels and energy rotor 522 is using the double-deck rotor distribution, and two layers revolves
Wing coaxial arrangement.
In order to further optimize the above technical scheme, it is provided with fuel cell in liquid fuel piggyback pod 52, being used for will be more
Remaining fuel combustion energy is converted to electric energy and stores.
In order to further optimize the above technical scheme, central control system 4 further includes emergency starting subsystem 43, when electric-powered
It is automatic to call fuel cell for the power supply of brushless motor 510 when 51 power consumption of cabin finishes.
In order to further optimize the above technical scheme, mounting rack 513 is added using the production of 3 D weaving carbon fiber composite material
Work forms.
In order to further optimize the above technical scheme, fuselage 1 and fixed-wing 2 are all made of the production of vacuum forming composite material and add
Work forms.
Embodiment 1
In a specific technical solution, when aircraft, which is in, hangs down winged state, due to two electric-powered cabins and electronic rotation
The wing is mounted on fixed-wing both ends, and a bit of wing that the purling that electronic rotor generates only has sub-fraction slightly to be located by the wing blocks,
Most of air-flow can pass through wing, if piggyback pod is mounted in the middle part of the wing, at least 50% downwash flow is by wing
It blocks, has seriously undermined the thrust of propeller；Cautiously slightly locate secondly, piggyback pod is mounted on fixation, dynamic rotation axis can be increased
The stability and reliability of transmission；Again, it is mounted on center of gravity of the electronic rotor away from complete machine that the wing wing is slightly located farther out, can make to fly
Machine flies control moment with bigger side when hanging down winged, improves the mobility that aircraft hangs down when flying.
Embodiment 2
When aircraft is in more rotor modes, the navigation posture of central control system selects subsystem to send out to powershift subsystem 42
Fuel and electric hybrid control instruction out selects the selected aircraft flight mode of subsystem by navigation posture, to electric-powered
Brushless motor in cabin is controlled, and the stability of aircraft is kept.
Electric-powered cabin control dynamic rotation is axially upper or verts downwards, to generate the thrust of different directions.For low speed
The offline mode that cruise, short take-off and landing, hovering, rotor tilt is realized using mode control as follows:
Low cruise: navigation posture selection subsystem controls powershift subsystem starts electric-powered cabin, passes through electronic rotor
Adjust flying speed.When aircraft move forward or back when, the electric-powered cabin synchronously control in fixed-wing both ends, with generate it is powerful to
Preceding or thrust backward；When aircraft side flies, the electric-powered cabin Differential Control in both ends, to generate pressure difference in aircraft two sides,
Achieve the purpose that side flies.
Short take-off and landing: navigation posture selection subsystem controls powershift subsystem starts electric-powered cabin, electric-powered
It is rotated in the synchronously control dynamic rotation axial direction of cabin, so that the double-deck rotor of electronic rotor is parallel with fuselage, to provide upwards
Lift realizes short take-off and landing by more rotor modes.
Hovering: navigation posture selection subsystem controls powershift subsystem starts electric-powered cabin, closing liquid
Fuels and energy cabin, brushless motor adjust the posture of electronic rotor, and keep being in a horizontal position two layers of electronic rotor, realize empty
Middle hovering.
To sum up, unmanned plane can be realized low cruise, short take-off and landing, hovering, rotor tilt etc. in low cruise
Movement.
Embodiment 3
When electric-powered cabin not enough power supply, when can not provide sufficient power for electronic rotor, central control system controls emergency starting
The fuel cell in fuels and energy cabin, is directly transmitted to the electric-powered cabin at fuselage both ends by system starting, to realize persistently continuation of the journey,
Prevent the aerial emergency shut down or special duty can not be executed.For example, needing to fly when relieving the people in stricken areas to outlying disaster area
Device executes the task of rescue personnel and goods and materials conveying, and remote and prolonged rescue action often has exceeded the behaviour of aircraft
Make load, if there is the problem of electric energy deficiency, cannot achieve the flight operation of hovering, by strong influence rescue task
Timely implementation, can not the powerful guarantee disaster area people personal and property safety.Therefore, emergency starting subsystem is mixed for oily electricity
The actual job of mould assembly aircraft is essential.
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.For device disclosed in embodiment
For, since it is corresponded to the methods disclosed in the examples, so being described relatively simple, related place is said referring to method part
It is bright.
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. one kind is mixed to move more rotor manned aircraft, including fuselage, it is set to the fixed-wing of the fuselage two sides, and be set to
The empennage of the afterbody；It is characterized in that, further include central control system, and the piggyback pod being connect with the central control system,
The piggyback pod includes electric-powered cabin and liquid fuel piggyback pod；End of the electric-powered freight space inside the fixed-wing
End；Brushless motor is provided in the electric-powered cabin, the brushless motor has electronic rotor, band by dynamic rotation axis connection
The electronic rotor wing rotation is moved, the electronic rotor is using the double-deck rotor distribution, including the peace being connected with the dynamic rotation axis
It shelves, is separately positioned on the two-bladed rotor of the mounting rack two sides；The liquid fuel piggyback pod is located inside the empennage
End；The liquid fuel piggyback pod provides power to fuels and energy rotor；The fuels and energy rotor is vertically mounted on described
Empennage end.
2. according to claim 1 mix moves more rotor manned aircraft, which is characterized in that the brushless motor is moved to described
Power rotary shaft exports rotating torque, and then drives the electronic rotor wing rotation.
3. according to claim 1 mix moves more rotor manned aircraft, which is characterized in that the central control system includes navigation
Posture selection subsystem, navigation posture selection subsystem output signal to powershift subsystem, powershift
System outputs control signals to the piggyback pod.
4. according to claim 3 mix moves more rotor manned aircraft, which is characterized in that the navigation posture selects subsystem
System selects the offline mode of the aircraft, and is exported and controlled to the powershift subsystem according to the offline mode
System instruction；The offline mode includes low cruise, short take-off and landing, hovering, rotor tilt.
5. according to claim 3 mix moves more rotor manned aircraft, which is characterized in that the powershift subsystem connects
The brushless motor is connect, for controlling revolving speed and the torque of the brushless motor；The powershift subsystem is also connected with described
Liquid fuel piggyback pod, for controlling fuels and energy actuating.
6. according to claim 1 mix moves more rotor manned aircraft, which is characterized in that the fuels and energy rotor uses
The double-deck rotor distribution, and two layers of rotor coaxial arrangement.
7. according to claim 1 mix moves more rotor manned aircraft, which is characterized in that in the liquid fuel piggyback pod
It is provided with fuel cell, for extra fuel combustion energy to be converted to electric energy and is stored.
8. according to claim 7 mix moves more rotor manned aircraft, which is characterized in that the central control system further includes answering
Anxious promoter systems, when the electric-powered cabin power consumption finishes, calling the fuel cell automatically is the brushless electricity
Machine power supply.
9. according to claim 1 mix moves more rotor manned aircraft, which is characterized in that the mounting rack is compiled using three-dimensional
Carbon fibre composite is knitted to produce and process.
10. according to claim 1 mix moves more rotor manned aircraft, which is characterized in that the fuselage and fixed-wing are equal
It is produced and processed using vacuum forming composite material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274877.4A CN109263917A (en) | 2018-10-30 | 2018-10-30 | One kind is mixed to move more rotor manned aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274877.4A CN109263917A (en) | 2018-10-30 | 2018-10-30 | One kind is mixed to move more rotor manned aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109263917A true CN109263917A (en) | 2019-01-25 |
Family
ID=65194534
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274877.4A Withdrawn CN109263917A (en) | 2018-10-30 | 2018-10-30 | One kind is mixed to move more rotor manned aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109263917A (en) |
-
2018
- 2018-10-30 CN CN201811274877.4A patent/CN109263917A/en not_active Withdrawn
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Application publication date: 20190125 |