CN111953106B - Self-adaptive stability maintaining method for aircraft - Google Patents
Self-adaptive stability maintaining method for aircraft Download PDFInfo
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- CN111953106B CN111953106B CN202010808824.7A CN202010808824A CN111953106B CN 111953106 B CN111953106 B CN 111953106B CN 202010808824 A CN202010808824 A CN 202010808824A CN 111953106 B CN111953106 B CN 111953106B
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- rotor framework
- rotor
- cooperative
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- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000004804 winding Methods 0.000 claims abstract description 98
- 230000003139 buffering effect Effects 0.000 claims abstract description 12
- 230000001133 acceleration Effects 0.000 claims abstract description 7
- 230000005284 excitation Effects 0.000 claims description 18
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000003044 adaptive effect Effects 0.000 claims 1
- 230000005662 electromechanics Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 238000007792 addition Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
Images
Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K23/00—DC commutator motors or generators having mechanical commutator; Universal AC/DC commutator motors
- H02K23/02—DC commutator motors or generators having mechanical commutator; Universal AC/DC commutator motors characterised by arrangement for exciting
-
- 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
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/22—Rotating parts of the magnetic circuit
- H02K1/28—Means for mounting or fastening rotating magnetic parts on to, or to, the rotor structures
- H02K1/30—Means for mounting or fastening rotating magnetic parts on to, or to, the rotor structures using intermediate parts, e.g. spiders
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K23/00—DC commutator motors or generators having mechanical commutator; Universal AC/DC commutator motors
- H02K23/02—DC commutator motors or generators having mechanical commutator; Universal AC/DC commutator motors characterised by arrangement for exciting
- H02K23/22—DC commutator motors or generators having mechanical commutator; Universal AC/DC commutator motors characterised by arrangement for exciting having compensating or damping windings
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K3/00—Details of windings
- H02K3/46—Fastening of windings on the stator or rotor structure
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/24—Casings; Enclosures; Supports specially adapted for suppression or reduction of noise or vibrations
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Permanent Magnet Type Synchronous Machine (AREA)
Abstract
The invention provides an aircraft self-adaptive stability maintaining method, and belongs to the technical field of electromechanics. When the electrified current of the main winding is artificially controlled to be increased to drive the rotating speed of the paddle to be accelerated and the lifting force to be increased, the reset spring provides buffering for the machine body for the first time, meanwhile, the rotating shaft moves upwards due to the inertia force between the machine body and the paddle, the resistance winding participates in the driving of the rotor framework, so that the rotor framework rotates with resistance, and the rotating acceleration of the rotating shaft and the paddle is slowed; when the current of the main winding is controlled to be reduced manually, the driving paddle rotates to form negative acceleration, the lift force is reduced or reversed, the reset spring provides buffering for the machine body for the first time, meanwhile, the reset spring is pressed, the cooperative winding participates in driving the rotor framework, so that the rotation torque of the rotor framework is supplied by the main winding and the cooperative winding at the same time, the rotation speed of the rotor framework is relatively improved, or the deceleration is slowed down. The invention has the advantages of improving the stability of the aircraft and the like.
Description
Technical Field
The invention belongs to the technical field of electromechanics, and relates to an aircraft self-adaptive stability maintaining method.
Background
Unmanned aerial vehicle develops rapidly, and the fuselage is controlled through the rotatory lift that produces of screw, and unmanned aerial vehicle is responsible for work such as monitoring, shooting, and the important embodiment that makes its performance operates steadily.
Disclosure of Invention
The invention aims to provide an aircraft self-adaptive stability maintaining method aiming at the problems in the prior art, and the technical problem to be solved by the invention is how to improve the stability of the aircraft body of the aircraft.
The purpose of the invention can be realized by the following technical scheme: the self-adaptive stability maintaining method of the aircraft is characterized in that the aircraft comprises a motor, an aircraft body and blades, the motor comprises a shell, a rotating shaft, a rotor framework, a rotating drum, a main excitation winding, a cooperative excitation winding and a resistance excitation winding, the rotating drum is rotatably connected to the shell and is of a hollow structure, the rotating shaft is longitudinally and slidably connected into the rotating drum, the rotating drum is provided with a plurality of longitudinal guide grooves penetrating through the inner wall and the outer wall of the rotating drum, the rotor framework is connected with the rotating shaft through a plurality of radial plates, and each radial plate is inserted into the corresponding longitudinal guide groove; the machine body is fixedly connected with the shell;
the main excitation winding comprises a mounting cylinder fixed on a shell between the rotor framework and the rotary cylinder, a main winding arranged on the outer wall surface of the mounting cylinder, and a plurality of first permanent magnet strips fixed on the inner side surface of the rotor framework;
the cooperative excitation winding comprises a first winding framework fixed on the shell, a cooperative winding arranged on the first winding framework, and a plurality of permanent magnet strips II fixed on the outer side surface of the rotor framework;
the resistance excitation winding comprises a second winding frame fixed on the shell and a resistance winding arranged on the second winding frame;
a return spring is connected between the bottom end of the rotating shaft and the shell;
the top end of the rotating shaft is fixedly connected with the paddle;
in a natural state of the reset spring, the resistance winding and the cooperative winding are respectively positioned at the upper side and the lower side of the permanent magnet strip, the rotation direction of the cooperative winding capable of driving the rotor framework to rotate is consistent with the rotation direction of the main winding capable of driving the rotor framework to rotate, and the rotation direction of the resistance winding capable of driving the rotor framework to rotate is opposite to the rotation direction of the main winding capable of driving the rotor framework to rotate;
the self-adaptive stability maintaining method comprises the following steps: when the electrified current of the main winding is artificially controlled to be increased to drive the rotating speed of the paddle to be accelerated and the lifting force to be increased, the reset spring provides buffering for the machine body for the first time, so that the quick response of the machine body to a longitudinal external force is avoided, meanwhile, the rotating shaft is moved upwards by the inertia force between the machine body and the paddle, the resistance winding participates in the driving of the rotor framework, the rotor framework rotates to have resistance, and the rotating acceleration of the rotating shaft and the paddle is slowed until the reset spring resets; when the electrification current of the main winding is controlled to be reduced manually, the driving paddle rotates to form negative acceleration, the lift force is reduced or reversed, the reset spring provides buffering for the machine body for the first time, the quick response of the machine body to longitudinal external force is avoided, meanwhile, the reset spring is pressed, the cooperative winding participates in the driving of the rotor framework, the rotation torque of the rotor framework is supplied by the main winding and the cooperative winding simultaneously, the rotation speed of the rotor framework is relatively improved, or the deceleration is slowed down, and therefore the buffering effect is good when the shell responds to active speed regulation.
In the aircraft self-adaptive stability maintaining method, the rotor framework is made of a magnetic shielding material.
For example, aluminum films are respectively coated on the inner side and the outer side of the rotor framework, and then the permanent magnet strip I and the permanent magnet strip II are fixed.
The rotation direction in which the cooperative winding can drive the rotor frame to rotate is consistent with the rotation direction in which the main winding drives the rotor frame to rotate, and the rotation direction in which the resistance winding can drive the rotor frame to rotate is opposite to the rotation direction in which the main winding drives the rotor frame to rotate, for example, the winding direction and the current direction of the main winding are the same as those of the cooperative winding, but the inner side of the first permanent magnet strip is provided with a magnetic pole opposite to the outer magnetic pole of the second permanent magnet strip, the winding direction of the resistance winding is the same as that of the cooperative winding, and the electrifying direction is opposite to that of the cooperative winding, so that the method can be realized.
Of course, the above effect can be produced when the unstable effect of the external air flow is applied to the housing.
Drawings
Fig. 1 is a schematic view of the structure of an electric machine in an aircraft.
In the figure, 1, a housing; 2. a rotating shaft; 3. a rotor frame; 4. a rotating drum; 51. a longitudinal guide groove; 52. a web; 53. mounting the cylinder; 61. a main winding; 62. a first permanent magnet strip; 71. a first bobbin; 72. a cooperative winding; 73. a second permanent magnet strip; 81. a second bobbin; 82. a resistance winding; 9. a return spring.
Detailed Description
The following are specific embodiments of the present invention and are further described with reference to the drawings, but the present invention is not limited to these embodiments.
As shown in fig. 1, the motor comprises a housing 1, a rotating shaft 2, a rotor frame 3, a rotating drum 4, a main excitation winding, a cooperative excitation winding and a resistance excitation winding, wherein the rotating drum 4 is rotatably connected to the housing, the rotating drum 4 is of a hollow structure, the rotating shaft 2 is longitudinally slidably connected in the rotating drum 4, a plurality of longitudinal guide grooves 51 penetrating through the inner wall and the outer wall of the rotating drum 4 are formed in the rotating drum 4, the rotor frame 3 is connected with the rotating shaft 2 through a plurality of radial plates 52, and each radial plate 52 is inserted in the corresponding longitudinal guide groove 51;
the main excitation winding comprises a mounting cylinder 53 fixed on the shell between the rotor framework 3 and the rotary cylinder 4, a main winding 61 arranged on the outer wall surface of the mounting cylinder 53, and a plurality of permanent magnet strips 62 fixed on the inner side surface of the rotor framework 3;
the cooperative excitation winding comprises a first bobbin 71 fixed on the shell, a cooperative winding 72 arranged on the first bobbin 71, and a plurality of second permanent magnet strips 73 fixed on the outer side surface of the rotor frame 3;
the resistance excitation winding comprises a second bobbin 81 fixed on the shell and a resistance winding 82 arranged on the second bobbin 81;
a return spring 9 is connected between the bottom end of the rotating shaft 2 and the shell;
the top end of the rotating shaft 2 is fixedly provided with a paddle;
in a natural state of the return spring 9, the resistance winding 82 and the cooperative winding 72 are respectively located at the upper side and the lower side of the permanent magnet strip, the rotation direction in which the cooperative winding 72 can drive the rotor frame 3 to rotate is consistent with the rotation direction in which the main winding 61 drives the rotor frame 3 to rotate, and the rotation direction in which the resistance winding 82 can drive the rotor frame 3 to rotate is opposite to the rotation direction in which the main winding 61 drives the rotor frame 3 to rotate.
The rotor frame 3 is made of magnetic shielding material. For example, aluminum films are respectively coated on the inner side and the outer side of the rotor framework 3, and then the first permanent magnet strip 62 and the second permanent magnet strip 73 are fixed.
There are many ways to realize that the rotation direction in which the cooperative winding 72 can drive the rotor frame 3 to rotate is the same as the rotation direction in which the main winding 61 drives the rotor frame 3 to rotate, and the rotation direction in which the resistance winding 82 can drive the rotor frame 3 to rotate is opposite to the rotation direction in which the main winding 61 drives the rotor frame 3 to rotate, for example, the winding direction and the current direction of the main winding 61 are the same as those of the cooperative winding 72, but the inner side of the first permanent magnet strip is a magnetic pole opposite to the outer magnetic pole of the second permanent magnet strip, the winding direction of the resistance winding 82 is the same as that of the cooperative winding 72, and the energization direction is opposite to that of the cooperative winding 72.
This motor can realize following function, the example: the shell is connected with an aircraft body, the blade rotates to drive the aircraft body to move upwards, when the electrification current of the main winding 61 is artificially controlled to be increased to drive the rotating speed of the blade to be accelerated and the lift force to be increased, the reset spring 9 provides buffering for the aircraft body for the first time, the aircraft body is prevented from quickly responding to longitudinal external force, meanwhile, the rotating shaft 2 is moved upwards by the inertia force between the aircraft body and the blade, the resistance winding 82 participates in driving the rotor framework 3, the rotor framework 3 rotates to have resistance, and the rotating speed of the rotating shaft 2 and the blade is slowed down until the reset spring 9 resets; when the electrification current of the main winding 61 is controlled to be reduced manually, the driving paddle rotates to form negative acceleration, the lift force is reduced or reversed, the reset spring 9 provides buffering for the machine body for the first time, the machine body is prevented from responding to longitudinal external force quickly, meanwhile, the reset spring 9 is pressed, the cooperative winding 72 participates in driving the rotor framework 3, the rotation torque of the rotor framework 3 is enabled to be supplied with the main winding 61 and the cooperative winding 72 simultaneously, the rotation speed of the rotor framework 3 is relatively improved, or the speed is reduced to slow down, therefore, the shell can respond to active speed regulation, the buffering effect is good, and the shell can have better stability in practical application, for example, a more stable shooting environment can be provided during shooting tasks.
Of course, the above effect can be produced when the unstable effect of the external air flow is applied to the housing. The overall size can be reduced and the buffering function can be optimized by properly adjusting the structure of each part in the attached drawings.
The specific embodiments described herein are merely illustrative of the spirit of the invention. Various modifications or additions may be made to the described embodiments or alternatives may be employed by those skilled in the art without departing from the spirit or ambit of the invention as defined in the appended claims.
Claims (2)
1. The aircraft self-adaptive stability maintaining method is characterized in that the motor comprises a shell (1), a rotating shaft (2), a rotor framework (3), a rotating drum (4), a main excitation winding, a cooperative excitation winding and a resistance excitation winding, the rotating drum (4) is rotatably connected to the shell, the rotating drum (4) is of a hollow structure, the rotating shaft (2) is longitudinally and slidably connected into the rotating drum (4), the rotating drum (4) is provided with a plurality of longitudinal guide grooves (51) penetrating through the inner wall and the outer wall of the rotating drum (4), the rotor framework (3) is connected with the rotating shaft (2) through a plurality of radial plates (52), and each radial plate (52) is inserted into the corresponding longitudinal guide groove (51);
the main excitation winding comprises a mounting cylinder (53) fixed on the shell between the rotor framework (3) and the rotary cylinder (4), a main winding (61) arranged on the outer wall surface of the mounting cylinder (53), and a plurality of first permanent magnet strips (62) fixed on the inner side surface of the rotor framework (3);
the cooperative excitation winding comprises a first bobbin (71) fixed on the shell, a cooperative winding (72) arranged on the first bobbin (71), and a plurality of second permanent magnet strips (73) fixed on the outer side surface of the rotor frame (3);
the resistance excitation winding comprises a second bobbin (81) fixed on the shell and a resistance winding (82) arranged on the second bobbin (81);
a return spring (9) is connected between the bottom end of the rotating shaft (2) and the shell;
the top end of the rotating shaft (2) is fixedly connected with the paddle, and the machine body is connected with the shell;
in a natural state of the reset spring (9), the resistance winding (82) and the cooperative winding (72) are respectively positioned at the upper side and the lower side of the permanent magnet strip, the rotation direction of the cooperative winding (72) capable of driving the rotor framework (3) to rotate is consistent with the rotation direction of the main winding (61) capable of driving the rotor framework (3) to rotate, and the rotation direction of the resistance winding (82) capable of driving the rotor framework (3) to rotate is opposite to the rotation direction of the main winding (61) capable of driving the rotor framework (3) to rotate;
the aircraft stability maintaining method comprises the following steps: when the electrified current of the main winding (61) is artificially controlled to be increased to drive the rotating speed of the blade to be accelerated and the lifting force to be increased, the reset spring (9) provides buffering for the shell for the first time, so that the shell is prevented from rapidly responding to a longitudinal external force, meanwhile, the rotating shaft (2) is moved upwards by the inertia force between the shell and the blade, the resistance winding (82) participates in the driving of the rotor framework (3), the rotor framework (3) is rotated to have resistance, and the rotating acceleration of the rotating shaft (2) and the blade is slowed until the reset spring (9) resets; when the current of the main winding (61) is controlled to be reduced manually, the driving paddle rotates to form negative acceleration, the lift force is reduced or reversed, the return spring (9) provides buffering for the shell for the first time, the shell is prevented from responding to longitudinal external force quickly, meanwhile, the return spring (9) is pressed, the cooperative winding (72) participates in driving of the rotor framework (3), the rotating torque of the rotor framework (3) is supplied by the main winding (61) and the cooperative winding (72), the rotating speed of the rotor framework (3) is relatively improved, or the speed is reduced, and therefore the buffering effect is good when the shell responds to active speed regulation.
2. The aircraft adaptive stability maintaining method according to claim 1, characterized in that the rotor skeleton (3) is made of magnetic shielding material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010808824.7A CN111953106B (en) | 2019-10-23 | 2019-10-23 | Self-adaptive stability maintaining method for aircraft |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911008955.0A CN110677001B (en) | 2019-10-23 | 2019-10-23 | Three-winding motor with lifting force buffering function |
| CN202010808824.7A CN111953106B (en) | 2019-10-23 | 2019-10-23 | Self-adaptive stability maintaining method for aircraft |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911008955.0A Division CN110677001B (en) | 2019-10-23 | 2019-10-23 | Three-winding motor with lifting force buffering function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111953106A CN111953106A (en) | 2020-11-17 |
| CN111953106B true CN111953106B (en) | 2022-08-05 |
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Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911008955.0A Active CN110677001B (en) | 2019-10-23 | 2019-10-23 | Three-winding motor with lifting force buffering function |
| CN202010808824.7A Active CN111953106B (en) | 2019-10-23 | 2019-10-23 | Self-adaptive stability maintaining method for aircraft |
| CN202010808836.XA Expired - Fee Related CN111884464B (en) | 2019-10-23 | 2019-10-23 | Aircraft with lift buffer function |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911008955.0A Active CN110677001B (en) | 2019-10-23 | 2019-10-23 | Three-winding motor with lifting force buffering function |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010808836.XA Expired - Fee Related CN111884464B (en) | 2019-10-23 | 2019-10-23 | Aircraft with lift buffer function |
Country Status (1)
| Country | Link |
|---|---|
| CN (3) | CN110677001B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112600353B (en) * | 2020-12-24 | 2024-05-24 | 湖北科技学院 | Stepless speed regulating punching device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4626726A (en) * | 1984-12-14 | 1986-12-02 | General Electric Company | Dynamoelectric machine with cushioning device |
| JPH09149621A (en) * | 1995-11-24 | 1997-06-06 | Denso Corp | Damper structure for rotating body |
| CN109728695A (en) * | 2019-03-08 | 2019-05-07 | 孙建林 | A kind of permanent magnet synchronous motor of high power density |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104065236B (en) * | 2013-03-22 | 2017-05-03 | 林英楠 | Permanent magnetic speed regulation, brake or load apparatus capable of stepless adjustment of magnetic field intensity |
| CN106063095B (en) * | 2014-03-05 | 2018-01-05 | 三菱电机株式会社 | Permanent-magnet type electric rotating machine |
| CN106516143A (en) * | 2016-12-22 | 2017-03-22 | 深圳市万至达电机制造有限公司 | High-performance tripod head |
| DE102018102750A1 (en) * | 2018-02-07 | 2019-08-08 | IPGATE Capital Holding AG | Stator for induction machine with axial heat dissipation |
| CN110337774B (en) * | 2018-06-27 | 2022-02-18 | 深圳市大疆创新科技有限公司 | Motor, radar subassembly, power device, cloud platform and unmanned aerial vehicle |
-
2019
- 2019-10-23 CN CN201911008955.0A patent/CN110677001B/en active Active
- 2019-10-23 CN CN202010808824.7A patent/CN111953106B/en active Active
- 2019-10-23 CN CN202010808836.XA patent/CN111884464B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4626726A (en) * | 1984-12-14 | 1986-12-02 | General Electric Company | Dynamoelectric machine with cushioning device |
| JPH09149621A (en) * | 1995-11-24 | 1997-06-06 | Denso Corp | Damper structure for rotating body |
| CN109728695A (en) * | 2019-03-08 | 2019-05-07 | 孙建林 | A kind of permanent magnet synchronous motor of high power density |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111884464A (en) | 2020-11-03 |
| CN110677001B (en) | 2020-12-04 |
| CN111884464B (en) | 2022-08-05 |
| CN111953106A (en) | 2020-11-17 |
| CN110677001A (en) | 2020-01-10 |
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Effective date of registration: 20220707 Address after: 437000 Building 5, Changjiang Industrial Park, Xianning Economic Development Zone, Hubei Province Applicant after: Hubei hukecheng Technology Development Co.,Ltd. Address before: Beijing University of Aeronautics and Astronautics, 37 Xueyuan Road, Haidian District, Beijing 100080 Applicant before: Chen Siyu |
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