CN115535277A - Aircraft splash protection system - Google Patents
Aircraft splash protection system Download PDFInfo
- Publication number
- CN115535277A CN115535277A CN202211553217.6A CN202211553217A CN115535277A CN 115535277 A CN115535277 A CN 115535277A CN 202211553217 A CN202211553217 A CN 202211553217A CN 115535277 A CN115535277 A CN 115535277A
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- Prior art keywords
- pressure
- air
- aircraft
- nozzle
- air compressor
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 28
- 230000002596 correlated effect Effects 0.000 claims description 9
- 238000010408 sweeping Methods 0.000 claims description 5
- 238000005452 bending Methods 0.000 claims description 4
- 230000037303 wrinkles Effects 0.000 claims description 2
- 230000008676 import Effects 0.000 claims 5
- 239000002352 surface water Substances 0.000 claims 1
- 230000003116 impacting effect Effects 0.000 abstract description 4
- 238000005096 rolling process Methods 0.000 abstract description 4
- 238000005299 abrasion Methods 0.000 abstract description 3
- 230000015572 biosynthetic process Effects 0.000 abstract description 2
- 230000036555 skin type Effects 0.000 description 9
- 238000009792 diffusion process Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 108010066114 cabin-2 Proteins 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- 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
- B64D47/00—Equipment not otherwise provided for
-
- E—FIXED CONSTRUCTIONS
- E01—CONSTRUCTION OF ROADS, RAILWAYS, OR BRIDGES
- E01H—STREET CLEANING; CLEANING OF PERMANENT WAYS; CLEANING BEACHES; DISPERSING OR PREVENTING FOG IN GENERAL CLEANING STREET OR RAILWAY FURNITURE OR TUNNEL WALLS
- E01H1/00—Removing undesirable matter from roads or like surfaces, with or without moistening of the surface
- E01H1/08—Pneumatically dislodging or taking-up undesirable matter or small objects; Drying by heat only or by streams of gas; Cleaning by projecting abrasive particles
- E01H1/0809—Loosening or dislodging by blowing ; Drying by means of gas streams
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Tires In General (AREA)
Abstract
The application belongs to the technical field of aircraft design, and discloses an aircraft splash protection system which comprises an air inlet pipeline, a high-pressure air compressor, a high-pressure air cabin and a high-pressure nozzle; when the aircraft takes off or lands, the high-pressure air compressor works, the air outside the aircraft body is sucked by the air inlet pipeline and enters the air inlet pipeline, the air sucked later enters the high-pressure air compressor to form compressed air, the compressed air enters the high-pressure air cabin to be stored, and then is sprayed out through the high-pressure nozzle, the accumulated water existing on the runway of the airport is divided by the high-pressure jet flow area formed after the compressed air is sprayed out, a follow-up local anhydrous area is formed, the accumulated water flows out from the two sides of the tire, the running tire is prevented from rolling/impacting the accumulated water, and the formation of water splashing is prevented. Meanwhile, the accumulated water is only contacted with the compressed air in the high-pressure jet flow area, so that the accumulated water cannot expand with a structure on the airplane and cannot generate any abrasion or deformation. Simple structure, high stability and long service life.
Description
Technical Field
The application belongs to the technical field of aircraft design, in particular to an aircraft splash protection system.
Background
During the process of taking off and landing of the airplane, when thick accumulated water exists on a runway of an airport, rolling/impacting action exists between the ratchet wheel and the accumulated water on the ground, the accumulated water can be flushed by the airplane wheel to two sides of a tire, water waves are formed by splashing, splashed water can possibly enter an air inlet passage or an auxiliary power system of an engine, and the engine or the auxiliary power system is flamed out and fails.
In order to avoid splash entering an engine air inlet or an auxiliary power system, the splash is blocked by a mode of arranging a waterproof baffle in front of the undercarriage at present, but when ponding on the ground has a certain height, the waterproof baffle in front of the undercarriage and other parts are deformed or damaged, and the water retaining efficiency is low.
Therefore, how to more effectively prevent the entry of the engine air inlet or the auxiliary power system is a problem to be solved.
Disclosure of Invention
The utility model provides an aircraft protection system that dabbles to adopt waterproof baffle to be difficult to carry out the problem that effectively blocks to ponding on the airport runway among the solution prior art.
The technical scheme of the application is as follows: an aircraft splash protection system is arranged between an aircraft body and an undercarriage and comprises an air inlet pipeline, a high-pressure air compressor, a high-pressure air cabin and a high-pressure nozzle; the utility model discloses a high pressure jet of high pressure jet, including air inlet pipe, high-pressure air compressor, undercarriage, high-pressure nozzle, admission line, high-pressure air compressor, high-pressure nozzle, undercarriage, the front upper side of the continuous tire of undercarriage, the export orientation of high-pressure nozzle forms conical high-pressure jet district to the front lower side and in the place ahead of tire, the high-pressure air compressor locates in the aircraft fuselage and the entry of high-pressure air compressor and the export sealing connection of admission line, the high-pressure air cabin is located on the undercarriage, the entry and the export intercommunication of high-pressure air compressor and high-pressure air cabin of high-pressure air cabin are used for receiving high-pressure air compressor exhaust compressed gas, high-pressure nozzle sealing connection in the export sealing connection of high-pressure air cabin, high-pressure nozzle locates the undercarriage, and in the place ahead of tire.
Preferably, the high-pressure air exhaust device further comprises a high-pressure air exhaust hose, the high-pressure air exhaust hose is connected between an outlet of the high-pressure air compressor and an inlet of the high-pressure air cabin, and the high-pressure air exhaust hose is arranged between the high-pressure air compressor and the high-pressure air cabin in a bent mode in an arc mode.
Preferably, the inner wall of the high-pressure exhaust hose is smooth and free of wrinkles, the high-pressure exhaust hose can bear not less than 2 standard ground air pressures, and the maximum bending angle of the high-pressure exhaust hose is less than 90 degrees.
Preferably, the aircraft body is provided with a skin type inlet, the air inlet of the air inlet pipeline is arranged at the skin type inlet, the shape of the skin type inlet is rectangular or similar to rectangular, and the inlet area of the skin type inlet is positively correlated with the air pressure ratio which is promoted after the high-pressure air compressor works.
Preferably, the outlet of the air inlet duct is circular.
Preferably, the high-pressure air compressor is started in advance before the operation of the airplane in a takeoff stage or a landing stage, the air pressure ratio of the high-pressure air compressor after being lifted is not less than 1.3, and the compressed air flow is positively correlated with the maximum depth of the water accumulated on the ground of the runway.
Preferably, the section of the pipeline in the high-pressure nozzle is a rectangular section, the chamfer angle at the outlet of the high-pressure nozzle is 30 degrees, the length of the section of the pipeline is greater than 1/4 of the width of the tire, and the width of the section of the pipeline is in positive correlation with the air flow and the maximum pressure ratio of compressed air in the high-pressure nozzle.
Preferably, the forward length of the high-pressure nozzle is L1, the oblique downward length of the high-pressure nozzle is L2, the forward length L1 and the oblique downward length L2 are positively correlated with the diameter of a tire of an undercarriage, and an included angle ALP between the forward direction and the oblique direction of the high-pressure nozzle is 120-145 degrees; the distance between the nozzle end of the high-pressure nozzle and the tire is D1, and the minimum distance of the D1 is 50-100 mm.
Preferably, the size of the diffusion angle of the high-pressure jet area is in positive correlation with the total pressure of the air at the outlet of the high-pressure nozzle, and the size of the ground scanning area of the high-pressure nozzle is in positive correlation with the total pressure of the airflow, the jet flow diffusion angle and the ground clearance of the high-pressure nozzle.
The application discloses an aircraft splash protection system, which comprises an air inlet pipeline, a high-pressure air compressor, a high-pressure air cabin and a high-pressure nozzle; when the aircraft takes off or lands, the high-pressure air compressor works, the air outside the aircraft body is sucked by the air inlet pipeline and enters the air inlet pipeline, the air sucked later enters the high-pressure air compressor to form compressed air, the compressed air enters the high-pressure air cabin to be stored, and then is sprayed out through the high-pressure nozzle, the accumulated water existing on the runway of the airport is divided by the high-pressure jet flow area formed after the compressed air is sprayed out, a follow-up local anhydrous area is formed, the accumulated water flows out from the two sides of the tire, the running tire is prevented from rolling/impacting the accumulated water, and the formation of water splashing is prevented. Meanwhile, the accumulated water is only contacted with the compressed air in the high-pressure jet flow area, so that the accumulated water cannot expand with a structure on the airplane and cannot generate any abrasion or deformation. Simple structure, high stability and long service life.
Drawings
In order to more clearly illustrate the technical solutions provided in the present application, the drawings will be briefly described below. It is to be understood that the drawings described below are merely exemplary of some embodiments of the application.
FIG. 1 is a schematic view of the overall structure of the present application;
fig. 2 is a schematic diagram of a high-pressure jet separation water body structure in the application.
1. An aircraft body; 2. a landing gear; 3. an air intake duct; 4. a high pressure air compressor; 5. a high pressure gas cabin; 6. a high pressure nozzle; 7. an air inlet; 8. a high pressure exhaust hose; 9. a high pressure jet zone; 10. a tire.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
An aircraft splash protection system, as shown in fig. 1, is provided between the bottom of the aircraft body 1 and the landing gear 2.
Comprises an air inlet pipeline 3, a high-pressure air compressor 4, a high-pressure air cabin 5 and a high-pressure nozzle 6; the high-pressure jet aircraft is characterized in that the air inlet pipeline 3 is arranged in the aircraft body 1, an air inlet 7 of the air inlet pipeline 3 is communicated with the outside of the aircraft body 1, the high-pressure air compressor 4 is arranged in the aircraft body 1, an inlet of the high-pressure air compressor 4 is hermetically connected with an outlet of the air inlet pipeline 3, the high-pressure air cabin 5 is arranged on the undercarriage 2, an inlet of the high-pressure air cabin 5 is communicated with an outlet of the high-pressure air compressor 4, the high-pressure air cabin 5 is used for receiving compressed air discharged by the high-pressure air compressor 4, the high-pressure nozzle 6 is hermetically connected with an outlet of the high-pressure air cabin 5, the high-pressure nozzle 6 is arranged above the front portion of a tire 10 connected with the undercarriage 2, and an outlet of the high-pressure nozzle 6 faces to the front lower portion and forms a conical high-pressure jet area 9 in front of the tire 10.
When the airplane takes off or lands, the high-pressure air compressor 4 is in a working state, so that negative pressure is formed at the air inlet 7 of the air inlet pipeline 3, air outside the airplane body 1 is sucked into the air inlet pipeline 3, the sucked air enters the high-pressure air compressor 4, the high-pressure air compressor 4 compresses the air to form compressed air, the compressed air enters the high-pressure air cabin 5 to be stored, the stored compressed air is sprayed out through the high-pressure nozzle 6, a high-pressure jet area 9 formed after the compressed air is sprayed out can form resistance to shunt accumulated water on an airport runway to form a follow-up local water-free area, the accumulated water flows out from two sides of the tire 10, rolling/impacting of the accumulated water by the moving tire 10 is prevented, splashing water waves are prevented from being formed, impact on the airplane body is prevented, and normal operation of a power system and an auxiliary power system is guaranteed, as shown in fig. 2. Meanwhile, the accumulated water is only contacted with the compressed air in the high-pressure jet flow region 9, so that the accumulated water cannot expand with a structure on the airplane and cannot generate any abrasion or deformation. Simple structure, high stability and long service life.
Preferably, the high-pressure air exhaust hose 8 is further included, the high-pressure air exhaust hose 8 is connected between an outlet of the high-pressure air compressor 4 and an inlet of the high-pressure air chamber 5, and the high-pressure air exhaust hose 8 is arranged between the high-pressure air compressor 4 and the high-pressure air chamber 5 in an arc bending mode.
In the process of retraction and extension of the undercarriage 2 of the airplane, the angle of the high-pressure air cabin 5 can be changed along with the retraction and extension of the undercarriage 2, and the high-pressure exhaust hose 8 is arranged, so that the high-pressure air cabin 2 can deform when retracted and extended, and can be stably and hermetically connected with the high-pressure air cabin 5 all the time.
Preferably, the inner wall of the high-pressure exhaust hose 8 is smooth and wrinkle-free, and the compressed air can still efficiently flow in the high-pressure exhaust hose 8 when the high-pressure exhaust hose 8 is deformed. The inside of the high-pressure exhaust hose 8 can bear standard air pressure of not less than 2 ground surfaces, the maximum bending angle of the high-pressure exhaust hose 8 is less than 90 degrees, and the working stability of the high-pressure exhaust hose 8 is ensured. In the actual working process, the high-pressure exhaust hose 8 is compared with the outside and is lifted by about 1 ground standard air pressure, and the stable shunting of the water accumulated on the ground of the runway can be realized.
Preferably, the aircraft body 1 is provided with a skin-type inlet, the air inlet 7 of the air inlet pipeline 3 is arranged at the skin-type inlet, the shape of the skin-type inlet is rectangular or similar to rectangular, the inlet area of the skin-type inlet is positively correlated with the air pressure ratio lifted by the high-pressure air compressor 4 after working, and the air pressure ratio lifted by the high-pressure air compressor 4 after working can be ensured within the range of the required air pressure ratio by limiting the inlet area of the skin-type inlet so as to ensure the stability of the working.
Preferably, the outlet of the air intake duct 3 is circular.
Preferably, the high-pressure air compressor 4 is started in advance before the operation of the airplane in the takeoff stage or the landing stage, the air pressure ratio after the lifting of the high-pressure air compressor 4 is not less than 1.3, the compressed air flow is in positive correlation with the maximum depth of the runway surface ponding, the air pressure ratio is also improved along with the lifting of the maximum depth of the runway surface ponding, and the formed high-pressure jet area 9 can stably shunt the runway surface ponding.
Preferably, the section of the pipeline inside the high-pressure nozzle 6 is a rectangular section, the chamfer angle at the outlet of the high-pressure nozzle 6 is 30 degrees, the length of the section of the pipeline is more than 1/4 of the width of the tire 10, the width of the section of the pipeline is in positive correlation with the air flow and the maximum pressure ratio of the compressed air in the high-pressure nozzle 6, and when the air flow and the maximum pressure ratio of the compressed air are increased, the high-pressure nozzle 6 with the larger width is correspondingly used to meet the use requirement.
Preferably, the forward length of the high-pressure nozzle 6 is L1, the slant downward length is L2, the forward length L1 and the slant downward length L2 are positively correlated with the diameter of the tire 10 of the undercarriage 2, and the included angle ALP between the forward direction and the slant direction of the high-pressure nozzle 6 is 120 to 145 °; the distance between the nozzle end of the high-pressure nozzle 6 and the tire 10 is D1, and the minimum distance of D1 is 50-100 mm.
Preferably, the size of the diffusion angle of the high-pressure jet area 9 is positively correlated with the total pressure of the air at the outlet of the high-pressure nozzle 6, and the size of the ground scanning area of the high-pressure nozzle 6 is positively correlated with the total pressure of the air flow, the jet flow diffusion angle and the ground clearance of the high-pressure nozzle 6. When the required ground sweeping area is larger, the larger ground sweeping area is achieved by adjusting the installation parameters of the high pressure nozzle 6, or another high pressure nozzle 6 is replaced. The shape of the ground sweeping area of the high pressure nozzle 6 is also related to the shape of the outlet of the high pressure nozzle 6, and by selecting the high pressure nozzle 6 with a suitable outlet shape, a desired ground sweeping area can be formed.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. The utility model provides an aircraft protection system that splashes water, locates between aircraft organism (1) and undercarriage (2), its characterized in that: comprises an air inlet pipeline (3), a high-pressure air compressor (4), a high-pressure air chamber (5) and a high-pressure nozzle (6); the aircraft is characterized in that the air inlet pipeline (3) is arranged in the aircraft body (1) and an air inlet (7) of the air inlet pipeline (3) is communicated with the exterior of the aircraft body (1), the high-pressure air compressor (4) is arranged in the aircraft body (1) and an inlet of the high-pressure air compressor (4) is hermetically connected with an outlet of the air inlet pipeline (3), the high-pressure air cabin (5) is arranged on the undercarriage (2), an inlet of the high-pressure air cabin (5) is communicated with an outlet of the high-pressure air compressor (4) and the high-pressure air cabin (5) is used for receiving compressed air discharged from the high-pressure air compressor (4), the high-pressure nozzle (6) is hermetically connected with the outlet of the high-pressure air cabin (5), the high-pressure nozzle (6) is arranged above the front of a tire (10) connected with the undercarriage (2), and an outlet of the high-pressure nozzle (6) faces the front lower side and forms a conical jet area (9) in front of the tire (10).
2. The aircraft splash guard system of claim 1, wherein: still include high-pressure exhaust hose (8), high-pressure exhaust hose (8) are connected between the export of high-pressure air compressor (4) and the import of hyperbaric air chamber (5), high-pressure exhaust hose (8) are the circular arc setting of buckling between high-pressure air compressor (4) and hyperbaric air chamber (5).
3. The aircraft splash protection system of claim 2, wherein: the inner wall of the high-pressure exhaust hose (8) is smooth and free of wrinkles, the interior of the high-pressure exhaust hose (8) can bear standard air pressure of not less than 2 ground surfaces, and the maximum bending angle of the high-pressure exhaust hose (8) is less than 90 degrees.
4. The aircraft splash protection system of claim 1, wherein: be equipped with skin formula import on aircraft organism (1), skin formula import department is located in air inlet (7) of admission line (3), the shape of skin formula import is rectangle or quasi-rectangle, the imported area of skin formula import is compared positive correlation with the air pressure that high-pressure air compressor (4) work back promotes.
5. The aircraft splash guard system of claim 1, wherein: the outlet of the air inlet pipeline (3) is circular.
6. The aircraft splash protection system of claim 1, wherein: the high-pressure air compressor (4) is started in advance before the operation of the airplane in a takeoff stage or a landing stage, the air pressure ratio of the high-pressure air compressor (4) after being lifted is not less than 1.3, and the compressed air flow is positively correlated with the maximum depth of the surface water of the runway.
7. The aircraft splash protection system of claim 1, wherein: the pipeline section inside the high-pressure nozzle (6) is a rectangular section, the chamfer angle at the outlet of the high-pressure nozzle (6) is 30 degrees, the length of the pipeline section is greater than 1/4 of the width of the tire (10), and the air flow and the maximum pressure ratio of compressed air in the width and the high-pressure nozzle (6) are in positive correlation.
8. The aircraft splash protection system of claim 1, wherein: the forward length of the high-pressure nozzle (6) is L1, the oblique downward length of the high-pressure nozzle is L2, the forward length L1 and the oblique downward length L2 are positively correlated with the diameter of a tire (10) of the undercarriage (2), and an included angle ALP between the forward direction and the oblique direction of the high-pressure nozzle (6) is 120-145 degrees; the distance between the nozzle end of the high-pressure nozzle (6) and the tire (10) is D1, and the minimum distance of D1 is 50-100 mm.
9. The aircraft splash protection system of claim 1, wherein: the divergence angle size of high pressure jet flow district (9) is positive correlation with the total pressure of high pressure nozzle (6) export air, the regional size of ground sweeping of high pressure nozzle (6) is positive correlation with the total pressure of air current, jet flow divergence angle and high pressure nozzle (6) terrain clearance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211553217.6A CN115535277A (en) | 2022-12-06 | 2022-12-06 | Aircraft splash protection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211553217.6A CN115535277A (en) | 2022-12-06 | 2022-12-06 | Aircraft splash protection system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115535277A true CN115535277A (en) | 2022-12-30 |
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ID=84722737
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211553217.6A Pending CN115535277A (en) | 2022-12-06 | 2022-12-06 | Aircraft splash protection system |
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| Country | Link |
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| CN (1) | CN115535277A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4834320A (en) * | 1987-12-22 | 1989-05-30 | Rockwell International Corporation | Method and system for reducing aircraft stopping distance |
| DE4334164A1 (en) * | 1993-10-04 | 1994-03-24 | Michael Passler | Prevention of aquaplaning of aircraft tyres on landing - involves special nozzle located in front of aircraft tyres fed with air tapped from engines |
| CN201626551U (en) * | 2009-11-26 | 2010-11-10 | 徐天元 | Blowing aircraft landing gear |
| CN104859846A (en) * | 2014-02-26 | 2015-08-26 | 成都智利达科技有限公司 | Safe automatic control device for undercarriage and undercarriage compartment |
| CN105576573A (en) * | 2015-12-13 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear line protection method |
| CN107539453A (en) * | 2017-09-04 | 2018-01-05 | 陶文英 | A kind of low-latitude flying operation unmanned plane and its control system and application |
-
2022
- 2022-12-06 CN CN202211553217.6A patent/CN115535277A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4834320A (en) * | 1987-12-22 | 1989-05-30 | Rockwell International Corporation | Method and system for reducing aircraft stopping distance |
| DE4334164A1 (en) * | 1993-10-04 | 1994-03-24 | Michael Passler | Prevention of aquaplaning of aircraft tyres on landing - involves special nozzle located in front of aircraft tyres fed with air tapped from engines |
| CN201626551U (en) * | 2009-11-26 | 2010-11-10 | 徐天元 | Blowing aircraft landing gear |
| CN104859846A (en) * | 2014-02-26 | 2015-08-26 | 成都智利达科技有限公司 | Safe automatic control device for undercarriage and undercarriage compartment |
| CN105576573A (en) * | 2015-12-13 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear line protection method |
| CN107539453A (en) * | 2017-09-04 | 2018-01-05 | 陶文英 | A kind of low-latitude flying operation unmanned plane and its control system and application |
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Application publication date: 20221230 |
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| RJ01 | Rejection of invention patent application after publication |