CN206068172U - Fixed-wing formula hybrid power aeroplane - Google Patents
Fixed-wing formula hybrid power aeroplane Download PDFInfo
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- CN206068172U CN206068172U CN201621062676.4U CN201621062676U CN206068172U CN 206068172 U CN206068172 U CN 206068172U CN 201621062676 U CN201621062676 U CN 201621062676U CN 206068172 U CN206068172 U CN 206068172U
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- electromotor
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- hybrid power
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
This utility model provides a kind of fixed-wing formula hybrid power aeroplane for being applied to engine product technical field, propeller (3) is installed on the fuselage (1) of described fixed-wing formula hybrid power aeroplane, propeller (3) is connected with motor (4), motor (4) is connected with electrokinetic cell (5), motor (4) is connected with the motor control unit (6) that can control motor (4), electromotor (7) is also set up in fuselage (1), electromotor (7) is connected with electromotor (8), electromotor (8) is connected with electrokinetic cell (5), electromotor (8) is while be connected with motor control unit (6), electromotor (7) is connected with the engine control device (9) that can control electromotor (7).Fixed-wing formula hybrid power aeroplane of the present utility model, can realize being used alternatingly for electric energy and fuel oil, effectively meet aircraft property indices, and energy saving consumption reduces flight cost, reduces environmental pollution.
Description
Technical field
This utility model belongs to aircraft product technical field, more specifically, is to be related to a kind of fixed-wing formula hybrid power
Aircraft.
Background technology
As energy crisis is increasingly serious with environmental pollution, development new forms of energy aircraft is an inexorable trend, wherein electricity
It is then preferred option as clean energy resource.Due to being restricted by battery technology, it is desirable to have individual transition scheme, oily electricity is this generates
Hybrid power system scheme.At present, oil electric mixed dynamic aircraft also locates blank stage, external actual popularization and application at home substantially
Do not have, be substantially at development yet.The technological difficulties of this programme predominantly tradition by cluster engine into power assembly, more
The power-driven system of oily electricity mixing is changed to, and is required to meet the property indices of aircraft.And cannot also expire in prior art
The above-mentioned technical requirements of foot.
Utility model content
Technical problem to be solved in the utility model is：For the deficiencies in the prior art, there is provided a kind of simple structure, energy
Being used alternatingly for electric energy and fuel oil is enough realized, aircraft property indices are effectively met, while energy saving consumption, reduces aircraft
Flight cost, alleviating energy crisis pressure reduce the fixed-wing formula hybrid power aeroplane of environmental pollution.
Techniques discussed above is solved the problems, such as, the technical scheme that this utility model is taken is：
This utility model is a kind of fixed-wing formula hybrid power aeroplane, and fixed-wing formula hybrid power aeroplane includes fuselage, machine
The wing, installs propeller on fuselage, propeller is connected with motor, and motor is connected with electrokinetic cell, motor and energy
Motor start and stop and the motor control unit connection of rotating speed and torque are enough controlled, electromotor in fuselage, is also set up,
Electromotor is connected with electromotor, and electromotor is connected with electrokinetic cell, and electromotor is connected with motor control unit simultaneously, is started
Machine is connected with the engine control device that can control electromotor start and stop and rotating speed.
Described electrokinetic cell includes respectively arranging multiple battery components in multiple battery components, fuselage and in wing.
Described motor control unit and engine control device are connected with high voltage power distribution part, and described high pressure is matched somebody with somebody
Electric part is configured to the structure that the electric energy of electrokinetic cell is passed to motor control unit, and high voltage power distribution part is simultaneously
It is configured to for the electric energy that the electromotor being connected with electromotor is sent to be delivered separately to motor control unit and power current
The structure in pond.
Described motor be permanent magnet synchronous AC machine, motor control unit be configured to by unidirectional current turn
The structure of alternating current is changed to, described propeller is fixedly connected with the motor shaft of motor, described fixed-wing formula mixing is dynamic
Power aircraft also includes generator set control part, and group of motors control unit is configured to be received electrokinetic cell and driven by network
The load information of galvanic electricity machine, and the structure of the output of rotary engine is adjusted according to aforesaid load information demand.
When the fixed-wing formula hybrid power aeroplane takes off or lands, engine control device is configured to control and starts
The out-of-work structure of machine, motor control unit are configured to control the structure that motor drives propeller rotational.
When described fixed-wing formula hybrid power aeroplane rises to after taking off more than setting height or is in cruising condition, institute
The motor control unit stated is configured to control the out-of-work structure of motor, described engine control device
It is configured to control the in running order structure for driving electrical power generators of electromotor.
Described fixed-wing formula hybrid power aeroplane also includes fuel tank, and fuel tank is arranged in fuselage, and fuel tank is connected with electromotor
Connect, described wing includes left side wing and right side wing, arranges multiple battery components, also set on the wing of right side on the wing of left side
Put multiple battery components.
Described engine control device control electromotor is in running order when driving electrical power generators, electromotor control
Part is configured to control the structure that electromotor delivers power to high voltage power distribution part.
Described engine control device control electromotor is in running order when driving electrical power generators, high voltage power distribution portion
Part is configured to while the structure of electric energy is conveyed to electrokinetic cell and motor control unit.
Described fixed-wing formula hybrid power aeroplane also includes battery management system, hybrid power system control unit and flies
Machine central control part.
Using the technical solution of the utility model, following beneficial effect can be obtained：
Fixed-wing formula hybrid power aeroplane described in the utility model, motor can drive propeller rotational, so as to
Electromotor work is driven, and the electric energy of motor is from the supply with electrokinetic cell.And the setting of electromotor, Main Function
It is the driven by engine electrical power generators for power electric generators source, the electric energy that electromotor sends can both supply control and drive
The motor control unit of motor work, to guarantee that motor works, the electricity that electromotor sends can also be conveyed to power
Battery, as electrical power storage.During the larger electric energy of structure of the present utility model, such as loading demand, then the electric energy that electromotor sends is complete
Portion is used for motor, inadequate electric energy can be supplemented by electrokinetic cell, such as loading demand small electric energy when, then send out
The electric energy of motor be mostly used in motor load, another part to power battery charging, as electrical power storage.Above-mentioned knot
Structure, determines the power supply of motor by electrokinetic cell or generator powered according to different operating modes, can the effectively save energy disappear
Consumption, reduces aircraft flight cost, while the pressure of alleviating energy crisis, and the pollution to environment can be reduced.This practicality is new
Fixed-wing formula hybrid power aeroplane described in type, simple structure can realize being used alternatingly for electric energy and fuel oil, effectively meet and fly
Machine property indices, energy saving consumption reduce aircraft flight cost, reduce environmental pollution.
Description of the drawings
Brief description is made to the content and the labelling in figure expressed by each accompanying drawing of this specification below：
Fig. 1 is the structural representation of fixed-wing formula hybrid power aeroplane described in the utility model；
Fig. 2 is the part annexation schematic diagram of fixed-wing formula hybrid power aeroplane described in the utility model；
Accompanying drawing acceptance of the bid note is respectively：1st, fuselage；2nd, wing；3rd, propeller；4th, motor；5th, electrokinetic cell；6th, drive
Motor control component；7th, electromotor；8th, electromotor；9th, engine control device；10th, battery component；11st, high voltage power distribution part；
12nd, motor shaft；13rd, fuel tank；14th, left side wing；15th, right side wing；16th, empennage；17th, driving cabin；18th, generator set control portion
Part.
Specific embodiment
Below against accompanying drawing, by the description to embodiment, to specific embodiment of the present utility model as involved by
The shape of each component, the mutual alignment between construction, each several part and annexation, the effect of each several part and operation principle etc. make into
The detailed description of one step：
As shown in accompanying drawing 1, accompanying drawing 2, this utility model is a kind of fixed-wing formula hybrid power aeroplane, and fixed-wing formula mixes dynamic
Power aircraft includes fuselage 1, wing 2, and propeller 3 is installed on described fuselage 1, and propeller 3 is connected with motor 4, drives electricity
Machine 4 is connected with electrokinetic cell 5, motor 4 and the motor that can control 4 start and stop of motor and rotating speed and torque
Control unit 6 connects, and also sets up electromotor 7 in fuselage 1, and electromotor 7 is connected with electromotor 8, and electromotor 8 is connected with electrokinetic cell 5
Connect, electromotor 8 is connected with motor control unit 6 simultaneously, electromotor 7 with can control sending out for 7 start and stop of electromotor and rotating speed
Motivation control unit 9 connects.Said structure is arranged, and motor can drive propeller rotational, so as to drive electromotor to work,
And the electric energy of motor is from the supply with electrokinetic cell.And the setting of electromotor, Main Function be to provide for electromotor
Power source, driven by engine electrical power generators, the electric energy that electromotor sends can both supply the driving of control motor work
Motor control component, to guarantee that motor works, the electricity that electromotor sends can also be conveyed to electrokinetic cell, store up as electric energy
Deposit.During the larger electric energy of fixed-wing formula hybrid power aeroplane described in the utility model, such as loading demand, then the electricity that electromotor sends
All can use for motor, inadequate electric energy can be supplemented by electrokinetic cell, such as loading demand small electric energy when,
Then the electric energy of electromotor be mostly used in motor load, another part to power battery charging, as electrical power storage.It is above-mentioned
According to different operating modes, structure, determines that the power supply of motor, being capable of the effectively save energy by electrokinetic cell or generator powered
Consume, reduce aircraft flight cost, while the pressure of alleviating energy crisis, and the pollution to environment can be reduced.This practicality
New described fixed-wing formula hybrid power aeroplane, simple structure can be realized being used alternatingly for electric energy and fuel oil, effectively meet
Aircraft property indices, energy saving consumption reduce aircraft flight cost, reduce environmental pollution.
Described electrokinetic cell 5 includes multiple battery components 10, respectively arranges multiple battery components in fuselage 1 and in wing 2
10.Electrokinetic cell volume is excessive, using distributed arrangement, is placed in wing 2 with fuselage 1, is realizing electrokinetic cell reliability
While installation, meet the requirement of the balanced arrangement of electrokinetic cell, it is to avoid aircraft local weight is excessive, the normal of aircraft will not be flown
Row produces impact, improves the overall performance of aircraft.
Described motor control unit 6 and engine control device 9 are connected with high voltage power distribution part 11, described height
Pressure power distribution unit 11 is configured to the electric energy of electrokinetic cell 5 is passed to the structure of motor control unit 6, high voltage power distribution
The electric energy that electromotor 8 sends that part 11 is configured to be connected with electromotor 7 simultaneously is delivered separately to motor control
The structure of part 6 and electrokinetic cell 5.Such structure setting, for the electric energy that the electromotor of driven by engine is produced, Neng Goutong
Cross high voltage power distribution part to be allocated, during electric energy as larger such as loading demand, high voltage power distribution part 11 then distributes what electromotor sent
Electric energy is all used for motor, and inadequate electric energy high voltage power distribution part 11 can be such as negative to be supplemented from electrokinetic cell
During load demand small electric energy, the generation electric energy of electromotor is then mostly used in motor load by high voltage power distribution part 11, separately
A part gives power battery charging, as electrical power storage, so as to both ensure the normal use of aircraft, electric energy can be closed again
The Distribution utilization of reason, it is to avoid the waste of electric energy, saves the flight energy and cost.
Described motor 4 is permanent magnet synchronous AC machine, and motor control unit 6 is configured to unidirectional current
The structure of alternating current is converted to, propeller 3 is fixedly connected with the motor shaft 12 of motor 4.Such structure, the work of propeller
Work is directly controlled by motor completely, therefore only needs to carry out reasonable distribution to the electric energy of electromotor and electrokinetic cell, with regard to energy
Enough control aircraft to fly reliable and securely, described fixed-wing formula hybrid power aeroplane also includes generator set control part 18
(i.e. APU controllers), group of motors control unit 18 are configured to negative with motor 4 by network reception electrokinetic cell 5
Information carrying ceases, and the structure of the output of rotary engine is adjusted according to aforementioned load information demand.Generator set control part
18 setting, obtains the load information of the part such as electrokinetic cell 5 and motor 4 by network, then to engine control section
9 one input quantities (signal) of part, engine control device become according to the signal, the rotating speed height and payload for controlling electromotor
Change, and output meets the output of loading demand, so that it is guaranteed that aircraft reliably working.
When described fixed-wing formula hybrid power aeroplane takes off, engine control device 9 is configured to control electromotor 7
Out-of-work structure, motor control unit 6 are configured to control the structure that motor 4 drives propeller 3 to rotate.
When fixed-wing formula hybrid power aeroplane takes off or lands, because taking off the dirt for being that Aircraft noise is maximum, causing to environment with landing
The stage of most serious is contaminated, at this moment electromotor does not work, and provides electric energy for motor by electrokinetic cell, so as to avoid electromotor work
Cause pollution on the environment.
When described fixed-wing formula hybrid power aeroplane rises to after taking off more than setting height or is in cruising condition, institute
The engine control device 9 stated is configured to control the in running order structure for driving electromotor 8 to generate electricity of electromotor 7.Gu
When determining to rise to after wing formula hybrid power aeroplane takes off more than setting height or be in cruising condition, electromotor work disappears to the energy
Consumption is less, and environmental pollution is also less.Therefore engine control device control electromotor works, and energy source based on electromotor is moved
Power battery then aids in powering for motor.
Described fixed-wing formula hybrid power aeroplane also includes fuel tank 13, and fuel tank 13 is arranged in fuselage 1, fuel tank 13 with send out
Motivation 7 connects, and described wing 2 includes left side wing 14 and right side wing 15, and multiple battery components are arranged on left side wing 14
10, multiple battery components 10 are also provided with right side wing 15.On the wing 14 of left side and on right side wing 15, multiple batteries are respectively set
Component 10, meets the requirement of the balanced arrangement of electrokinetic cell, it is to avoid aircraft local weight is excessive, will not produce shadow to aircraft flight
Ring, improve aeroplane performance.
When the described in running order drive electromotor 8 of the control electromotor 7 of engine control device 9 generates electricity, electromotor
Control unit 9 is configured to control the structure that electromotor 8 delivers power to high voltage power distribution part 11.So, electromotor is produced
Electric energy reasonable distribution can be carried out by high voltage power distribution part 11.
When the described in running order drive electromotor 8 of the control electromotor 7 of engine control device 9 generates electricity, high pressure is matched somebody with somebody
Electric part 11 is configured to while the structure of electric energy is conveyed to electrokinetic cell 5 and motor control unit 6.Described fixation
Wing formula hybrid power aeroplane also includes battery management system, hybrid power system control unit (HCU) and aircraft central control
Part.Above-mentioned part is arranged, and realizes the reliable control overall to aircraft.
Fixed-wing formula hybrid power aeroplane of the present utility model, motor can drive propeller rotational, drive to start
Machine works, and the electric energy of motor is from the supply with electrokinetic cell.And the Main Function of electromotor is provided for electromotor
Power source, driven by engine electrical power generators, the electric energy that electromotor sends can both supply the driving of control motor work
Motor control component, to guarantee that motor works, the electricity that electromotor sends can also be conveyed to electrokinetic cell, store up as electric energy
Deposit.During the larger electric energy of this utility model structure, such as loading demand, then the electric energy that electromotor sends all is used for motor,
Inadequate electric energy can be supplemented by electrokinetic cell, such as loading demand small electric energy when, then the electric energy of electromotor is most of
For motor load, another part to power battery charging, as electrical power storage.Said structure, it is true according to different operating modes
Determine the power supply of motor by electrokinetic cell or generator powered, can effectively save energy resource consumption, reduce aircraft flight into
This, while the pressure of alleviating energy crisis, and the pollution to environment can be reduced.Fixed-wing formula described in the utility model is mixed
Motor plane is closed, simple structure can be realized being used alternatingly for electric energy and fuel oil, effectively meet aircraft property indices, save
About energy resource consumption, reduces aircraft flight cost, reduces environmental pollution.
Exemplary description is carried out to this utility model above in conjunction with accompanying drawing, it is clear that this utility model concrete implementation is simultaneously
Do not limited by aforesaid way, if the various improvement that method design of the present utility model and technical scheme are carried out are employed, or
It is not improved that design of the present utility model and technical scheme are directly applied to into other occasions, in protection of the present utility model
In the range of.
Claims (10)
1. a kind of fixed-wing formula hybrid power aeroplane, fixed-wing formula hybrid power aeroplane include fuselage (1), wing (2), its feature
It is：Propeller (3) is installed on described fuselage (1), propeller (3) is connected with motor (4), motor (4) with move
Power battery (5) connection, motor (4) and the motor that motor (4) start and stop and rotating speed and torque can be controlled
Control unit (6) connects, and also sets up electromotor (7) in fuselage (1), and electromotor (7) is connected with electromotor (8), electromotor (8) and
Electrokinetic cell (5) connects, electromotor (8) while be connected with motor control unit (6), electromotor (7) with can control
Engine control device (9) connection of motivation (7) start and stop and rotating speed.
2. fixed-wing formula hybrid power aeroplane according to claim 1, it is characterised in that：Described electrokinetic cell (5) bag
Include in multiple battery components (10), fuselage (1) and multiple battery components (10) are respectively set in wing (2).
3. fixed-wing formula hybrid power aeroplane according to claim 1, it is characterised in that：Described motor control unit
Part (6) and engine control device (9) are connected with high voltage power distribution part (11), and described high voltage power distribution part (11) is arranged to
Enough structures that the electric energy of electrokinetic cell (5) is passed to motor control unit (6), high voltage power distribution part (11) is while arrange
The electric energy that the electromotor (8) being connected with electromotor (7) is sent to be delivered separately to motor control unit (6) and be moved
The structure of power battery (5).
4. fixed-wing formula hybrid power aeroplane according to claim 1, it is characterised in that：Described motor (4) is
Permanent magnet synchronous AC machine, described motor control unit (6) are configured to the knot that unidirectional current is converted to alternating current
Structure, described propeller (3) are fixedly connected with the motor shaft (12) of motor (4), and described fixed-wing formula hybrid power flies
Machine also includes generator set control part (18), and group of motors control unit (18) is configured to receive electrokinetic cell by network
(5) load information with motor (4), and the output of rotary engine is adjusted according to aforesaid load information demand
Structure.
5. fixed-wing formula hybrid power aeroplane according to claim 3, it is characterised in that：Fixed-wing formula hybrid power aeroplane
When taking off or landing, engine control device (9) is configured to control the out-of-work structure of electromotor (7), motor
Control unit (6) is configured to control the structure that motor (4) drives propeller (3) to rotate.
6. fixed-wing formula hybrid power aeroplane according to claim 5, it is characterised in that：Described fixed-wing formula mixing is dynamic
When power rises to after taking off more than setting height or is in cruising condition, described motor control unit (6) is arranged
To control the out-of-work structure of motor (4), described engine control device (9) is configured to control and starts
The in running order structure for driving electromotor (8) to generate electricity of machine (7).
7. fixed-wing formula hybrid power aeroplane according to claim 2, it is characterised in that：Described fixed-wing formula mixing is dynamic
Power aircraft also includes fuel tank (13), and fuel tank (13) is arranged in fuselage (1), and fuel tank (13) is connected with electromotor (7), described machine
The wing (2) includes left side wing (14) and right side wing (15), and multiple battery components (10), right side machine are arranged on left side wing (14)
Multiple battery components (10) are also provided with the wing (15).
8. fixed-wing formula hybrid power aeroplane according to claim 6, it is characterised in that：Described engine control device
(9), when the in running order drive electromotor (8) of control electromotor (7) generates electricity, engine control device (9) is configured to control
Electromotor (8) processed delivers power to the structure of high voltage power distribution part (11).
9. fixed-wing formula hybrid power aeroplane according to claim 7, it is characterised in that：Engine control device (9) is controlled
Electromotor (7) processed is in running order when driving electromotor (8) to generate electricity, and high voltage power distribution part (11) is configured to simultaneously to moving
Power battery (5) and motor control unit (6) convey the structure of electric energy.
10. fixed-wing formula hybrid power aeroplane according to claim 3, it is characterised in that：Described fixed-wing formula mixing
Motor plane also includes battery management system, hybrid power system control unit and aircraft central control part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621062676.4U CN206068172U (en) | 2016-09-19 | 2016-09-19 | Fixed-wing formula hybrid power aeroplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621062676.4U CN206068172U (en) | 2016-09-19 | 2016-09-19 | Fixed-wing formula hybrid power aeroplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206068172U true CN206068172U (en) | 2017-04-05 |
Family
ID=58438300
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621062676.4U Active CN206068172U (en) | 2016-09-19 | 2016-09-19 | Fixed-wing formula hybrid power aeroplane |
Country Status (1)
| Country | Link |
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| CN (1) | CN206068172U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106314809A (en) * | 2016-09-19 | 2017-01-11 | 中电科芜湖钻石飞机设计研究院有限公司 | Fixed wing type hybrid power motorplane |
| CN106970642A (en) * | 2017-04-20 | 2017-07-21 | 佛山科学技术学院 | A kind of multi-rotor unmanned aerial vehicle state monitoring apparatus |
| WO2019217920A1 (en) | 2018-05-10 | 2019-11-14 | Joby Aero, Inc. | Electric tiltrotor aircraft |
| CN112429247A (en) * | 2020-12-01 | 2021-03-02 | 飞的科技有限公司 | Aircraft with a flight control device |
| CN113665824A (en) * | 2021-08-20 | 2021-11-19 | 浙江点辰航空科技有限公司 | Small-size aerocraft hybrid device |
-
2016
- 2016-09-19 CN CN201621062676.4U patent/CN206068172U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106314809A (en) * | 2016-09-19 | 2017-01-11 | 中电科芜湖钻石飞机设计研究院有限公司 | Fixed wing type hybrid power motorplane |
| CN106970642A (en) * | 2017-04-20 | 2017-07-21 | 佛山科学技术学院 | A kind of multi-rotor unmanned aerial vehicle state monitoring apparatus |
| WO2019217920A1 (en) | 2018-05-10 | 2019-11-14 | Joby Aero, Inc. | Electric tiltrotor aircraft |
| EP3790798A1 (en) * | 2018-05-10 | 2021-03-17 | Joby Aero, Inc. | Electric tiltrotor aircraft |
| EP3790798A4 (en) * | 2018-05-10 | 2022-01-19 | Joby Aero, Inc. | Electric tiltrotor aircraft |
| CN112429247A (en) * | 2020-12-01 | 2021-03-02 | 飞的科技有限公司 | Aircraft with a flight control device |
| CN113665824A (en) * | 2021-08-20 | 2021-11-19 | 浙江点辰航空科技有限公司 | Small-size aerocraft hybrid device |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information |
Inventor after: Ping Lihao Inventor after: Zeng Rui Inventor after: Li Huiying Inventor after: Zhou Yi Inventor after: Liu Xin Inventor after: Guo Mao Inventor after: Wu Tianrui Inventor after: Sun Xinyu Inventor before: Ping Lihao Inventor before: Zeng Rui Inventor before: Li Huiying Inventor before: Zhou Yi Inventor before: Zhang Huiqin Inventor before: Wu Tianrui |
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| CB03 | Change of inventor or designer information | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 241100 Anhui city of Wuhu province Wuhu Aviation Industrial Park Wuhu County Economic and Technological Development Zone office building two floor Patentee after: Wuhu Dianke in General Industrial Technology Research Institute of Aviation Company Limited Address before: 241100 Anhui city of Wuhu province Wuhu Aviation Industrial Park Wuhu County Economic and Technological Development Zone office building two floor Patentee before: CETC Wuhu diamond Aircraft Design Institute Co. Ltd. |
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| CP01 | Change in the name or title of a patent holder |