CN106314815B - Takeoff method of aircraft takeoff device - Google Patents
Takeoff method of aircraft takeoff device Download PDFInfo
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- CN106314815B CN106314815B CN201610876143.8A CN201610876143A CN106314815B CN 106314815 B CN106314815 B CN 106314815B CN 201610876143 A CN201610876143 A CN 201610876143A CN 106314815 B CN106314815 B CN 106314815B
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- 238000000034 method Methods 0.000 title claims description 8
- 230000001174 ascending effect Effects 0.000 claims abstract description 42
- 230000008859 change Effects 0.000 claims abstract description 10
- 238000002955 isolation Methods 0.000 claims description 4
- 230000003993 interaction Effects 0.000 claims description 3
- 238000011017 operating method Methods 0.000 abstract 1
- 238000005452 bending Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000035899 viability Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
Abstract
An operating method of an aircraft takeoff device is characterized by comprising the following steps: the main part includes platform, air outlet, airflow generator of sliding, its characterized in that following step: the aircraft is pushed to move on the sliding platform through the horizontal power A, the airflow generator on the sliding platform generates airflow which flows out through the air outlet to convert ascending airflow, and the ascending airflow is combined with the horizontal power of the aircraft to change the moving direction of the aircraft to deviate from ascending; the body and the bottom of the wing of the aircraft block ascending airflow and relatively generate lift force to touch the inertial force of the aircraft so as to obliquely send the aircraft out of the sliding platform; the front end of the air deflector is obliquely arranged in a group to guide the air outlet flow to be inclined in rows, the bottom surface of the aircraft is blown forwards and upwards to support at least part of the weight of the aircraft, the front end air deflector is arranged from one row to the tail end air deflector, each row is gradually arranged and erected, and the generated vertical ascending air flow is inclined to the erected position and touches the inertial force of the aircraft to obliquely send the aircraft out of the sliding platform.
Description
Technical Field
The invention relates to a take-off device, in particular to a take-off method of an aircraft take-off device.
Background
Chinese patent document No. CN102120497A discloses a steam catapult for a closed cylinder aircraft carrier in 2011, month 07 and 13, and the purpose of catapulting an aircraft to take off can be achieved by providing the steam catapult for the closed cylinder aircraft carrier. The steam catapult for the sealed cylinder aircraft carrier provided by the invention has the advantages that a traction belt penetrates through a well-lubricated and sealed cylinder sliding hole, two ends of the traction belt are respectively connected with a piston and a tractor, and the traction belt is reversed by a reversing tension wheel to form a specific circulating motion mechanism of the catapult. The piston drives the tractor to move by utilizing the traction belt, and further drives the plane to catapult and take off. The traction belt is made of high-elasticity material, the section of the traction belt is flat, and the traction belt has a smaller bending radius in the flat direction. When the traction belt passes through the reversing tension wheel, the traction belt is bent to be in a complete elastic deformation state, and cannot be damaged due to bending fatigue. The device has the advantages of flexible operation, reliable performance, high efficiency, small volume, water saving, simple structure, easy manufacture, small infrared characteristic and the like, is suitable for the installation and the use of the aircraft carrier, and has great significance for accelerating the development speed of the aircraft carrier in China and improving the fighting capacity and the viability of the aircraft carrier.
Due to the complicated structure and large volume of the steam ejector, further improvement is needed.
Disclosure of Invention
The invention aims to provide a takeoff method of an aircraft takeoff device, which has the advantages of simple and reasonable structure, convenient operation, durability and reliable performance, and has simple structure and low cost so as to overcome the defects in the prior art.
The takeoff method of the aircraft takeoff device designed according to the purpose comprises the following steps: a step of changing the moving direction of the aircraft away from the ascent:
the aircraft is pushed to move on the sliding platform through the horizontal power A, the airflow generator on the sliding platform generates airflow which flows out through the air outlet to convert ascending airflow, and the ascending airflow is combined with the horizontal power of the aircraft to change the moving direction of the aircraft to deviate from ascending;
the aircraft obliquely sends the aircraft out of the sliding platform by blocking ascending airflow through the body and the bottom of the wing and generating inertia force of lifting force contacting the aircraft relatively; the tail end of the sliding platform is provided with an air outlet, at least one group of air outlets are transversely arranged at the tail end of the sliding platform, the openings of the air outlets are upward or obliquely upward to form ascending air flow, an included angle is formed between the ascending air flow and the sliding platform, the ascending air flow is blown to the bottom of an aircraft on the sliding platform to form lifting force to change the horizontal moving direction of the aircraft, and the aircraft is obliquely and upwardly sent out of the plane of the sliding platform;
the front end of each air deflector is obliquely arranged, the air outlet flow is guided to be inclined in rows, the bottom surface of the aircraft is blown forwards and upwards to support at least part of the weight of the aircraft, the front end air deflectors are arranged from one row to the tail end air deflectors, each row is gradually arranged and erected, and the generated vertical ascending air flow is inclined to the erected position and touches the inertial force of the aircraft to obliquely send the aircraft out of the sliding platform;
generating a three-dimensional ascending airflow inclined to be vertical to realize deviation ascending; ensuring that the ascending airflow is combined with the horizontal power of the aircraft to change the moving direction of the aircraft to deviate from ascending; the airflow generator is a turbine fan or a blade fan or a cross flow fan and is uniformly distributed at the lower part of the air outlet or the front end of the air outlet;
the air deflector is rotatably connected with the electric control assembly, the electric control assembly is provided with a motor, a gear and a connecting rod, the air deflector is movably connected with the connecting rod, and the connecting rod drives the air deflector to swing back and forth;
the air outlet is arranged into a strip-shaped reticular platform, and the air deflector is arranged to be a part of the strip-shaped reticular platform of the air outlet;
generating airflow diversion: the air outlet is arranged in a directional air outlet mode or in an adjustable direction-changing air outlet mode, the direction-changing air outlet is changed by airflow achieved by rotation of the adjustable air deflector, the air outlet is arranged to intersect with the sliding platform, and the air outlet direction of the air outlet is upward or obliquely upward; the air deflectors of the air outlet are erected to be obliquely and orderly arranged, or the air deflectors of the air outlet are obliquely and orderly arranged along the advancing moving direction of the aircraft; the air outlet is communicated with the airflow generator, the airflow generator is arranged in the sliding platform, and the air inlet of the airflow generator is arranged on one side or two sides or the bottom of the sliding platform or the upper part of the front end of the sliding platform;
the adjustable air deflector can adjust the air outlet direction of the air outlet to adapt to take off of aircrafts with different weights;
through the interaction between the tail end of the sliding platform and the ascending airflow, the horizontal power A of the aircraft is converted into ascending thrust through the obstruction of the ascending airflow and the area of the bottom of the aircraft, and the aircraft is gradually lifted and sent out of the tail end of the sliding platform;
generating a gas flow isolation step: the air deflectors on the outer side of each air outlet are inclined outwards to exhaust air, external ambient airflow is blocked outwards to form an isolated airflow wall, airflow isolation caused by the ambient airflow during take-off of the aircraft is reduced, the air inlet of the airflow generator is arranged on the side or the bottom of the sliding platform, and an included angle is formed between the air inlet and the air outlet to eliminate rotating airflow generated by air intake or air exhaust;
the air deflectors on the outer sides of each group of air outlets obliquely exhaust air to the outside, external ambient airflow is blocked outwards, an isolated airflow wall is formed, the influence of the ambient airflow on the takeoff of the aircraft is reduced, and the aircraft is forced to deviate and ascend.
The invention uses an aircraft take-off device, the main body comprises a sliding platform, an air outlet and an airflow generator, and the aircraft take-off device is characterized in that: the tail end of the sliding platform is provided with an air outlet, at least one group of air outlets are transversely arranged at the tail end of the sliding platform, openings of the air outlets are upward or obliquely upward to form updraft, included angles are formed between the updraft and the sliding platform, the updraft blows towards the bottom of an aircraft on the sliding platform to form lifting force to change the direction of horizontal movement of the aircraft, and the aircraft is obliquely and upwardly conveyed away from the plane of the sliding platform.
The air outlet is intersected with the sliding platform;
the air outlet is arranged in a directional air outlet mode or in an adjustable direction air outlet mode, and the adjustable direction air outlet is realized by rotating the adjustable air deflector.
The air outlet direction of the air outlet is upward or obliquely upward;
the air deflectors of the air outlet are arranged in order from vertical to inclined, or the air deflectors of the air outlet are arranged in order from inclined to vertical along the advancing moving direction of the aircraft.
The front end of the air deflector is obliquely arranged to guide the air outlet flow to be inclined in rows, the bottom surface of the aircraft is blown forwards and upwards to support at least part of the weight of the aircraft, the front end air deflector is arranged from one row to the tail end air deflector, and each row is gradually arranged and erected to generate a three-dimensional ascending air flow inclined to be erected.
The air outlet is communicated with the air flow generator, the air flow generator is arranged in the sliding platform, and the air inlet of the air flow generator is arranged on one side or two sides or the bottom of the sliding platform or the upper part of the front end of the sliding platform.
The airflow generator is a turbine fan or a blade fan or a cross-flow fan and is uniformly distributed at the lower part of the air outlet or the front end of the air outlet;
the air inlet of the airflow generator is arranged at the side part or the bottom part of the sliding platform, and an included angle is formed between the air inlet and the air outlet, so that rotary airflow generated by air inlet or air outlet is eliminated;
the air deflectors on the outer sides of each group of air outlets incline to the outside to exhaust air, so that outside ambient airflow is blocked outwards, an isolated airflow wall is formed, and the influence of the ambient airflow on the takeoff of the aircraft is reduced.
The air deflector is rotatably connected with the electric control assembly, the electric control assembly is provided with a motor, a gear and a connecting rod, the air deflector is movably connected with the connecting rod, and the connecting rod drives the air deflector to swing back and forth.
The air outlet is arranged into a strip-shaped reticular platform, and the air deflector is arranged to be a part of the strip-shaped reticular platform of the air outlet.
According to the invention, through interaction between the sliding platform and the ascending airflow, the horizontal power A of the aircraft is converted into ascending thrust through the ascending airflow and the area blockage at the bottom of the aircraft, and the aircraft is gradually lifted and sent out of the sliding platform, so that the effect of four or two thousands of thousands.
The working procedures can be carried out circularly, and the working efficiency is greatly improved. The device has the characteristics of simple and reasonable structure, convenience in operation, durability and reliable performance.
Drawings
Fig. 1 is a schematic view of a sliding platform according to a first embodiment of the present invention.
Fig. 2 is a schematic top view of a sliding platform according to a first embodiment of the present invention.
Fig. 3 is a front view schematically illustrating a sliding platform according to a first embodiment of the present invention.
Fig. 4 is a partially enlarged schematic view of the sliding platform according to the first embodiment of the present invention.
Detailed Description
The invention is further described with reference to the following figures and examples.
Reference example (see FIGS. 1-4)
The utility model provides an aircraft take-off device, the main part includes that the platform 11, air outlet 10, airflow generator 7 slide, its characterized in that: the tail end of the sliding platform 11 is provided with an air outlet 10, at least one group of air outlets 10 are transversely arranged at the tail end of the sliding platform 11, an opening of the air outlet 10 is upward or obliquely upward to form an ascending air current 8, the ascending air current 8 and the sliding platform 11 form an included angle and blow to the bottom of the aircraft 1 on the sliding platform 11 to form a lifting force to change the horizontal moving direction of the aircraft 1, and the aircraft 1 is obliquely and upwardly conveyed away from the plane of the sliding platform 11.
The air outlet 10 is intersected with the sliding platform 11;
the air outlet 10 is arranged for directional air outlet or adjustable directional air outlet, and the adjustable directional air outlet is realized by rotating the adjustable air deflector 2.
The air outlet direction of the air outlet 10 is upward or obliquely upward;
the air deflectors 2 of the air outlet 10 are arranged in order from vertical to inclined, or the air deflectors 2 of the air outlet 10 are arranged in order from inclined to vertical along the advancing moving direction of the aircraft 1.
The front end of the air deflector 2 is obliquely arranged in a group to guide the air outlet flow to be inclined in rows, the bottom of the aircraft 1 is blown forwards and upwards to support at least part of the weight of the aircraft 1, the front end air deflector 2 is arranged from one row to the tail end air deflector 2, each row is gradually arranged vertically, and a three-dimensional ascending air flow 8 inclined to be vertical is generated.
The air outlet 10 is communicated with the airflow generator 7, the airflow generator 7 is arranged in the sliding platform 11, and the air inlet 9 of the airflow generator 7 is arranged on one side or two sides or the bottom of the sliding platform 11 or the upper part of the front end of the sliding platform 11.
The airflow generator 7 is a turbo fan or a blade fan or a cross flow fan 3 and is uniformly distributed at the lower part of the air outlet 10 or at the front end of the air outlet 10;
the air inlet 9 of the airflow generator 7 is arranged at the side part or the bottom part of the sliding platform 11, and an included angle is formed between the air inlet 9 and the air outlet 10, so that rotary airflow generated by air inlet or air outlet is eliminated; the air inlet 9 sucks external air flow 12, and the air inlet 9 is arranged on the lower side of the sliding platform 11.
The air deflectors on the outer sides of each group of air outlets 10 incline outwards to exhaust air 14, so that external ambient airflow is blocked outwards to form an isolated airflow wall, and the influence of the ambient airflow 13 on the takeoff of the aircraft 1 is reduced.
The air deflector 2 is rotatably connected with the electric control component 4, the electric control component 4 is provided with a motor, a gear and a connecting rod 6, the air deflector 2 is movably connected with the connecting rod 6, and the connecting rod drives the air deflector 2 to swing back and forth.
The air outlet 10 is configured as a strip-shaped mesh platform, and the air deflector 2 is configured as a part of the strip-shaped mesh platform of the air outlet 10.
The foregoing is a preferred embodiment of the present invention, and the basic principles, principal features and advantages of the invention are shown and described. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are intended to illustrate the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, and the invention is intended to be protected by the following claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (1)
1. A takeoff method of an aircraft takeoff device, wherein the aircraft takeoff device comprises a sliding platform, an air outlet, an air deflector and an airflow generator, and the takeoff method comprises the following steps: -letting the direction of movement of the aircraft (1) change away from the ascent step:
the aircraft (1) is pushed to move on the sliding platform (11) through the horizontal power A, the airflow generator (7) on the sliding platform (11) generates airflow and the airflow flows out through the air outlet (10) to convert ascending airflow, and the ascending airflow is combined with the horizontal power of the aircraft (1) to change the moving direction of the aircraft (1) to deviate from ascending;
the aircraft (1) obliquely sends the aircraft (1) out of the sliding platform (11) through the inertial force that the aircraft body and the bottom of the wing block ascending airflow and relatively generate lifting force to touch the aircraft (1); the tail end of the sliding platform is provided with an air outlet, at least one group of air outlets are transversely arranged at the tail end of the sliding platform, the openings of the air outlets are upward or obliquely upward to form ascending air flow, an included angle is formed between the ascending air flow and the sliding platform, the ascending air flow is blown to the bottom of an aircraft on the sliding platform to form lifting force to change the horizontal moving direction of the aircraft, and the aircraft is obliquely and upwardly sent out of the plane of the sliding platform;
the front end of the air deflector (2) is obliquely arranged to guide the outlet air flow to be inclined in rows, the bottom of the aircraft (1) is blown forwards and upwards to support at least part of the weight of the aircraft (1), the front end air deflector (2) is arranged from one row to the tail end air deflector (2) in a row, each row is gradually arranged and erected, and the aircraft (1) is obliquely sent out of the sliding platform (11) by the inertia force generated when the three-dimensional ascending air flow inclined to be erected touches the aircraft (1);
generating a three-dimensional ascending airflow inclined to be vertical to realize deviation ascending; ensuring that the ascending airflow is combined with the horizontal power of the aircraft (1) to change the moving direction of the aircraft (1) to deviate from ascending; the airflow generator is a turbine fan or a blade fan or a cross flow fan and is uniformly distributed at the lower part of the air outlet or the front end of the air outlet;
the air deflector is rotatably connected with the electric control assembly, the electric control assembly is provided with a motor, a gear and a connecting rod, the air deflector is movably connected with the connecting rod, and the connecting rod drives the air deflector to swing back and forth;
the air outlet is arranged into a strip-shaped reticular platform, and the air deflector is arranged to be a part of the strip-shaped reticular platform of the air outlet;
generating airflow diversion: the air outlet is arranged in a directional air outlet mode or in an adjustable direction-changing air outlet mode, the direction-changing air outlet is changed by airflow achieved by rotation of the adjustable air deflector, the air outlet is arranged to intersect with the sliding platform, and the air outlet direction of the air outlet is upward or obliquely upward; the air deflectors of the air outlet are erected to be obliquely and orderly arranged, or the air deflectors of the air outlet are obliquely and orderly arranged along the advancing moving direction of the aircraft; the air outlet is communicated with the airflow generator, the airflow generator is arranged in the sliding platform, and the air inlet of the airflow generator is arranged on one side or two sides or the bottom of the sliding platform or the upper part of the front end of the sliding platform;
the adjustable air deflector (2) can adjust the air outlet direction of the air outlet to adapt to take-off of aircrafts (1) with different weights;
through the interaction between the tail end of the sliding platform and the ascending airflow, the horizontal power A of the aircraft is converted into ascending thrust through the obstruction of the ascending airflow and the area of the bottom of the aircraft, and the aircraft is gradually lifted and sent out of the tail end of the sliding platform;
generating a gas flow isolation step: the air deflectors on the outer side of each group of air outlets (10) obliquely exhaust air (14) to the outside, external ambient airflow (13) is blocked outwards to form an isolated airflow wall, airflow isolation caused by the ambient airflow (13) when the aircraft (1) takes off is reduced, the air inlet of the airflow generator is arranged on the side or the bottom of the sliding platform, an included angle is formed between the air inlet and the air outlets, and rotating airflow generated by air intake or air exhaust is eliminated;
the air deflectors on the outer sides of each group of air outlets obliquely exhaust air to the outside, external ambient airflow is blocked outwards, an isolated airflow wall is formed, the influence of the ambient airflow on the takeoff of the aircraft is reduced, and the aircraft (1) is forced to deviate and ascend.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610876143.8A CN106314815B (en) | 2016-10-08 | 2016-10-08 | Takeoff method of aircraft takeoff device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610876143.8A CN106314815B (en) | 2016-10-08 | 2016-10-08 | Takeoff method of aircraft takeoff device |
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| Publication Number | Publication Date |
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| CN106314815A CN106314815A (en) | 2017-01-11 |
| CN106314815B true CN106314815B (en) | 2020-04-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610876143.8A Active CN106314815B (en) | 2016-10-08 | 2016-10-08 | Takeoff method of aircraft takeoff device |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115871948B (en) * | 2023-02-17 | 2023-06-06 | 秦皇岛优益创联特种车辆制造有限公司 | Motor aircraft runway |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101244764A (en) * | 2008-03-07 | 2008-08-20 | 王刚 | Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane |
| CN102745333A (en) * | 2012-07-31 | 2012-10-24 | 李文铎 | Internal combustion steam boosting take-off unit of airplane |
| CN104670447A (en) * | 2015-01-29 | 2015-06-03 | 赵凤银 | Aircraft carrier, ship and land-water jet runway system with efficient short-range slide or vertical take-off and landing aircraft units |
| CN105035343A (en) * | 2015-08-13 | 2015-11-11 | 济南环太机电技术有限公司 | Vapor emission type shipboard aircraft carrier catapult |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2921964C (en) * | 2013-08-27 | 2022-03-22 | Engineered Arresting Systems Corporation | Electric unmanned aerial vehicle launcher |
-
2016
- 2016-10-08 CN CN201610876143.8A patent/CN106314815B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101244764A (en) * | 2008-03-07 | 2008-08-20 | 王刚 | Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane |
| CN102745333A (en) * | 2012-07-31 | 2012-10-24 | 李文铎 | Internal combustion steam boosting take-off unit of airplane |
| CN104670447A (en) * | 2015-01-29 | 2015-06-03 | 赵凤银 | Aircraft carrier, ship and land-water jet runway system with efficient short-range slide or vertical take-off and landing aircraft units |
| CN105035343A (en) * | 2015-08-13 | 2015-11-11 | 济南环太机电技术有限公司 | Vapor emission type shipboard aircraft carrier catapult |
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| CN106314815A (en) | 2017-01-11 |
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Effective date of registration: 20200313 Address after: 318020, Chengjiang street, Huangyan District, Zhejiang City, Taizhou Province, near the West Village Applicant after: TAIZHOU HAOZIBANG INDUSTRIAL DESIGN Co.,Ltd. Address before: Malibu Xuan No. 200 Jin Lan Bei Lu Chancheng District Guangdong city Foshan province 702 room 528000 Applicant before: Zhou Zihan |
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Denomination of invention: A takeoff method of aircraft takeoff device Effective date of registration: 20211230 Granted publication date: 20200407 Pledgee: Taizhou Huangyan sub branch of Zhejiang Tailong Commercial Bank Co.,Ltd. Pledgor: TAIZHOU HAOZIBANG INDUSTRIAL DESIGN CO.,LTD. Registration number: Y2021980017306 |
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Date of cancellation: 20231027 Granted publication date: 20200407 Pledgee: Taizhou Huangyan sub branch of Zhejiang Tailong Commercial Bank Co.,Ltd. Pledgor: TAIZHOU HAOZIBANG INDUSTRIAL DESIGN CO.,LTD. Registration number: Y2021980017306 |
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