CN109436373B - High-ultrasonic rapid force and heat combined test cabin - Google Patents
High-ultrasonic rapid force and heat combined test cabin Download PDFInfo
- Publication number
- CN109436373B CN109436373B CN201811445899.2A CN201811445899A CN109436373B CN 109436373 B CN109436373 B CN 109436373B CN 201811445899 A CN201811445899 A CN 201811445899A CN 109436373 B CN109436373 B CN 109436373B
- Authority
- CN
- China
- Prior art keywords
- test
- cylindrical sleeve
- double
- layer cylindrical
- cabin door
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000001816 cooling Methods 0.000 claims abstract description 24
- 239000000498 cooling water Substances 0.000 claims abstract description 4
- 210000001503 joint Anatomy 0.000 claims description 14
- 238000007789 sealing Methods 0.000 claims description 10
- 239000007921 spray Substances 0.000 claims description 6
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 229910052786 argon Inorganic materials 0.000 claims description 2
- 238000003466 welding Methods 0.000 claims description 2
- 230000010354 integration Effects 0.000 claims 7
- 238000000034 method Methods 0.000 abstract description 5
- 239000010410 layer Substances 0.000 abstract 2
- 238000009434 installation Methods 0.000 abstract 1
- 239000011229 interlayer Substances 0.000 abstract 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000010301 surface-oxidation reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
A high-ultrasonic-speed force-heat combined test cabin body is formed by taking a double-layer cylindrical sleeve as a structural main body of the test cabin body, wherein a test environment is provided for force-heat combined test in the cylindrical sleeve, a cooling water circulation channel is formed in an interlayer of the double-layer cylindrical sleeve and is used for circularly cooling the test cabin body, a cabin door is positioned at the front end of the cabin body, a tensile force model carrying frame of the high-ultrasonic-speed force-heat combined test is conveniently placed, a test model is conveniently installed and removed, and external equipment on the upper portion and the lower portion of the cabin body can effectively isolate vibration conduction of the test model in a test process. The invention ensures the smooth development of the high ultrasonic speed force heat combined test, runs stably for a long time, and has the advantages of reasonable structure, easy processing, convenient installation, convenient test operation and the like.
Description
Technical Field
The invention belongs to hypersonic test technology, and relates to a cabin suitable for hypersonic force heat combination test.
Background
Hypersonic test, the local thermal environment of the hypersonic aircraft is simulated in a test cabin by utilizing a heater and a spray pipe to heat and accelerate air flow, so that the heat-proof material and the heat-proof performance of the structure of the hypersonic aircraft under aerodynamic conditions are researched. In fact, the hypersonic aircraft also bears various severe factors such as aerodynamic load, surface oxidation of the aircraft and the like in the flight process, and the hypersonic force heat combination test is one of important ground test means for researching the problems of high temperature, stress, oxidation and the like of the nose cone, the wing front edge and the like of the novel hypersonic aircraft in long-time high-speed flight, and plays an important role in the design of an aircraft heat protection system. The test cabin is one of important components of the arc wind tunnel test equipment, is an important site for disassembling and assembling a test model and developing an examination test, and bears an important mission for maintaining the low-pressure long-time stable operation of the test environment.
Because the force-heat combined test needs to simulate the mechanical loading, long-time hypersonic pneumatic ablation and oxygen partial pressure environment of the model to be tested, the design of the test cabin body needs to meet various complex requirements such as vacuum, high temperature, long-time operation, cooperation of all subsystems and the like, and meanwhile, the model disassembly and assembly, test process observation, test data acquisition and the like are considered, so that the reliable and stable operation of test equipment is ensured, and real and effective test data are obtained. The traditional hypersonic test cabin body is of a cube structure, two cabin doors are arranged at the left side and the right side, round observation windows are distributed on the cabin doors respectively, and because arc wind tunnel equipment is connected to the front end and the rear end of the test cabin body, when the traditional hypersonic test cabin body is applied to a combined force and heat test, a force bearing frame of a tension prototype for realizing tension loading can prevent the cabin doors from opening and closing and affect model disassembly, and a tension loading mechanism of the prototype can also cause vacuum leakage of the traditional cabin body.
Disclosure of Invention
The technical solution of the invention is as follows: the defect of the traditional hypersonic test cabin body in the process of carrying out the force-heat combined test is overcome, and the test cabin body which is convenient to assemble and disassemble, convenient to acquire data and suitable for the hypersonic force-heat combined test is provided.
The technical solution of the invention is as follows: a high-ultrasonic-speed force-heat combined test cabin comprises a double-layer cylindrical sleeve, a cooling ring, a front flange, a rear flange, a rectangular observation window, a tension loading window, a corrugated pipe, a front cabin door, a nozzle interface and a circular observation window; the two cooling rings are respectively in butt joint with the two ends of the outer sleeve of the double-layer cylindrical sleeve, the front flange is in butt joint with the inner sleeve of the double-layer cylindrical sleeve and one cooling ring, and the rear flange is in butt joint with the inner sleeve of the double-layer cylindrical sleeve and one cooling ring; the two rectangular observation windows are respectively arranged at the left side and the right side of the double-layer cylindrical sleeve, the two tension loading windows are respectively arranged at the upper side and the lower side of the cylindrical sleeve, and the corrugated pipe is in butt joint with the tension loading windows; the front cabin door is in butt joint with the front flange, and the front cabin door is opened and closed through the hinge and the door lock.
The double-layer cylindrical sleeve is welded with the cooling ring, the front flange, the rear flange, the rectangular observation window and the tensile loading window by argon arc welding.
A sealing groove is formed in the tension loading window, and a rubber ring is used for sealing when the tension loading window is in butt joint with the corrugated pipe.
The rectangular observation window and the round observation window are provided with sealing grooves, and the sealing grooves are covered with quartz glass and then sealed by rubber rings.
The front cabin door and the front flange are matched and installed in a snap fit mode, and a rubber sealing ring is bonded on the snap of the front cabin door.
The inner sleeve of the double-layer cylindrical sleeve is 520mm in length, 490mm in inner diameter, 6mm in wall thickness, 406mm in outer sleeve length, 508mm in inner diameter and 6mm in wall thickness.
The maximum inner diameter of the cooling ring is 570mm, and the wall thickness is 6mm.
The cooling ring is uniformly distributed with 4 cooling water interfaces.
The front cabin door is a disc with the diameter of 680mm, the wall thickness of the front cabin door is 15mm, and a spray pipe joint is arranged in the center.
The inner diameter of the nozzle interface is 140mm, and two circular observation windows with the diameter of 150mm are uniformly distributed at a left-right distance of 400 mm.
The rectangular observation window is 280mm long and 80mm wide, extends outwards by 50mm, and the corner is smoothly treated to release stress.
The inner diameter of the tension loading window is 100mm.
The length of the corrugated pipe is 200mm, the inner diameter is 100mm, and the maximum expansion and contraction amount is +/-30 mm.
Compared with the traditional test cabin, the invention has the advantages that:
(1) The invention has exquisite structure, the whole cabin body can be cooled by water through the front cooling ring and the rear cooling ring, the long-time operation of the test is ensured, and the internal closed structural form ensures the vacuum test environment required by the combined force and heat test.
(2) The front cabin door of the invention provides a sufficient position space for the tension prototype and is convenient for the disassembly and assembly of the model.
(3) The corrugated pipe can effectively prevent vibration of equipment in the test process from being transmitted to the model through the tension mechanism, and the corrugated pipe upper cover provides an interface for an oxygen partial pressure system and a test system.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Detailed Description
As shown in fig. 1, the force-heat combined test cabin comprises a double-layer cylindrical sleeve 1, a cooling ring 2, a front flange 3, a rear flange 4, a front cabin door 5, a rectangular observation window 6, a tension loading window 7, a corrugated pipe 8, a spray pipe interface 9 and a circular observation window 10, wherein two ends of an outer sleeve of the double-layer cylindrical sleeve 1 are in butt joint with the two cooling rings 2, the front flange 3 is in butt joint with an inner sleeve of the double-layer cylindrical sleeve 1 and the cooling ring 2, and the rear flange is in butt joint with the inner sleeve of the double-layer cylindrical sleeve 1 and the cooling ring 2; two rectangular observation windows 6 are positioned at the left side and the right side of the double-layer cylindrical sleeve 1, two tension loading windows 7 are positioned at the upper side and the lower side of the cylindrical sleeve, a corrugated pipe 8 is in butt joint with the tension loading windows 7, a front cabin door 5 is in butt joint with a front flange 3, and the opening and the closing of the cabin door can be realized through a hinge and a door lock.
The inner sleeve of the double-layer cylindrical sleeve 1 is 520mm in length, 490mm in inner diameter, 6mm in wall thickness, 406mm in outer sleeve length, 508mm in inner diameter, 6mm in wall thickness, 570mm in maximum inner diameter of the cooling ring 2, 6mm in wall thickness, 4 cooling water connectors uniformly distributed, and four inlets and four outlets of the front cooling ring and the rear cooling ring. The front cabin door is a disc with the diameter of 680mm, the wall thickness is 15mm, the center position is the nozzle interface 9, the inner diameter of the nozzle interface 9 is 140mm, two circular observation windows 10 are uniformly distributed at the left and right distances of 400mm, the inner diameter of each circular observation window 10 is 150mm, the rectangular observation window 6 is 280mm long, 80mm wide and 50mm outwards extends out of the cabin, so that quartz glass on the window can be effectively prevented from being roasted and damaged during long-time test, and the stress is released by smooth treatment at the corners. The inner diameter of the tension loading window 7 is 100mm, the length of the corrugated pipe 8 is 200mm, the inner diameter is 100mm, and the maximum expansion and contraction amount is +/-30 mm.
Claims (8)
1. The utility model provides a high supersound rapid force heat combination test cabin body which characterized in that: the double-layer cylindrical sleeve comprises a double-layer cylindrical sleeve (1), a cooling ring (2), a front flange (3), a rear flange (4), a rectangular observation window (6), a tension loading window (7), a corrugated pipe (8), a front cabin door (5), a spray pipe interface (9) and a circular observation window (10); the two cooling rings (2) are respectively butted with two ends of the outer sleeve of the double-layer cylindrical sleeve (1), the front flange (3) is butted with the inner sleeve of the double-layer cylindrical sleeve (1) and one cooling ring (2), and the rear flange (4) is butted with the inner sleeve of the double-layer cylindrical sleeve (1) and one cooling ring (2); two rectangular observation windows (6) are respectively arranged at the left side and the right side of the double-layer cylindrical sleeve (1), two tension loading windows (7) are respectively arranged at the upper side and the lower side of the cylindrical sleeve (1), and a corrugated pipe (8) is in butt joint with the tension loading windows (7); the front cabin door (5) is in butt joint with the front flange (3), and the front cabin door (5) is opened and closed through a hinge and a door lock;
A sealing groove is formed in the tension loading window (7), and a rubber ring is used for sealing when the tension loading window is in butt joint with the corrugated pipe (8);
The rectangular observation window (6) and the round observation window (10) are provided with sealing grooves, and the sealing grooves are covered with quartz glass and then sealed by rubber rings.
2. The high ultrasonic force heat integration test chamber according to claim 1, wherein: the double-layer cylindrical sleeve (1) is welded with the cooling ring (2), the front flange (3), the rear flange (4), the rectangular observation window (6) and the pulling force loading window (7) by argon arc welding.
3. The high ultrasonic force heat integration test chamber according to claim 1, wherein: the front cabin door (5) and the front flange (3) are mounted in a snap fit manner, and rubber sealing rings are bonded on the snap of the front cabin door (5).
4. The high ultrasonic force heat integration test chamber according to claim 1, wherein: the inner sleeve of the double-layer cylindrical sleeve (1) is 520mm in length, 490mm in inner diameter, 6mm in wall thickness, 406mm in outer sleeve length, 508mm in inner diameter and 6mm in wall thickness.
5. The high ultrasonic force heat integration test chamber according to claim 1, wherein: the maximum inner diameter of the cooling ring (2) is 570mm, and the wall thickness is 6mm; the cooling ring (2) is uniformly distributed with 4 cooling water interfaces.
6. The high ultrasonic force heat integration test chamber according to claim 1, wherein: the front cabin door (3) is a disc with the diameter of 680mm, the wall thickness of the disc is 15mm, and the center position of the front cabin door is provided with a spray pipe interface (9).
7. The high ultrasonic force heat integration test chamber according to claim 1, wherein: the rectangular observation window (6) is 280mm long and 80mm wide, 50mm outwards extends out of the cabin, and the corners are smoothly treated to release stress.
8. The high ultrasonic force heat integration test chamber according to claim 1, wherein: the inner diameter of the spray pipe interface (9) is 140mm, and two circular observation windows (10) with the diameter of 150mm are uniformly distributed at the left and right distances of 400 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811445899.2A CN109436373B (en) | 2018-11-29 | 2018-11-29 | High-ultrasonic rapid force and heat combined test cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811445899.2A CN109436373B (en) | 2018-11-29 | 2018-11-29 | High-ultrasonic rapid force and heat combined test cabin |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109436373A CN109436373A (en) | 2019-03-08 |
| CN109436373B true CN109436373B (en) | 2024-05-03 |
Family
ID=65556520
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811445899.2A Active CN109436373B (en) | 2018-11-29 | 2018-11-29 | High-ultrasonic rapid force and heat combined test cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109436373B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112747890B (en) * | 2020-12-29 | 2023-03-14 | 中国航天空气动力技术研究院 | Pneumatic and thermal combined test system and test method |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048110A (en) * | 2012-12-14 | 2013-04-17 | 中国航空工业集团公司沈阳空气动力研究所 | Experimental facility for realizing thrust deflexion and experimental technique thereof |
| CN103063398A (en) * | 2012-12-28 | 2013-04-24 | 中国人民解放军国防科学技术大学 | Hypersonic wind tunnel experiment module |
| CN103234804A (en) * | 2013-04-25 | 2013-08-07 | 哈尔滨工业大学 | High-power non-contact type rapid laser heating device |
| CN103344777A (en) * | 2013-06-20 | 2013-10-09 | 哈尔滨工业大学 | High-temperature and low-pressure oxygen dissociation environment test device for heat protection material |
| CN104132813A (en) * | 2014-08-08 | 2014-11-05 | 中国航天科技集团公司第四研究院四0一所 | Slidable double-cylinder type structure pressure stabilization bin for solid ramjet direct connection test |
| CN104458189A (en) * | 2014-10-17 | 2015-03-25 | 北京航天益森风洞工程技术有限公司 | Process layout method for conventional hypersonic speed wind tunnel |
| CN105181317A (en) * | 2015-09-22 | 2015-12-23 | 中国航天空气动力技术研究院 | Rudderpost heat sealing test device |
| CN205826262U (en) * | 2016-07-07 | 2016-12-21 | 长沙市天映机械制造有限公司 | A kind of air bubble clashes into the vacuum test cabin of detection testpieces performance parameter |
| CN106568568A (en) * | 2016-10-19 | 2017-04-19 | 北京航天长征飞行器研究所 | High-temperature combustion-gas flow supersonic wind tunnel test system |
| CN108255207A (en) * | 2018-01-02 | 2018-07-06 | 高砂建筑工程(北京)有限公司 | Wind-tunnel idling and spout device and its control method |
| CN108534981A (en) * | 2018-02-07 | 2018-09-14 | 北京航天长征飞行器研究所 | A kind of high-temperature tunnel collection port spraying temperature lowering apparatus |
| CN209506126U (en) * | 2018-11-29 | 2019-10-18 | 中国航天空气动力技术研究院 | A kind of hypersonic power heat integration test cabin |
-
2018
- 2018-11-29 CN CN201811445899.2A patent/CN109436373B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048110A (en) * | 2012-12-14 | 2013-04-17 | 中国航空工业集团公司沈阳空气动力研究所 | Experimental facility for realizing thrust deflexion and experimental technique thereof |
| CN103063398A (en) * | 2012-12-28 | 2013-04-24 | 中国人民解放军国防科学技术大学 | Hypersonic wind tunnel experiment module |
| CN103234804A (en) * | 2013-04-25 | 2013-08-07 | 哈尔滨工业大学 | High-power non-contact type rapid laser heating device |
| CN103344777A (en) * | 2013-06-20 | 2013-10-09 | 哈尔滨工业大学 | High-temperature and low-pressure oxygen dissociation environment test device for heat protection material |
| CN104132813A (en) * | 2014-08-08 | 2014-11-05 | 中国航天科技集团公司第四研究院四0一所 | Slidable double-cylinder type structure pressure stabilization bin for solid ramjet direct connection test |
| CN104458189A (en) * | 2014-10-17 | 2015-03-25 | 北京航天益森风洞工程技术有限公司 | Process layout method for conventional hypersonic speed wind tunnel |
| CN105181317A (en) * | 2015-09-22 | 2015-12-23 | 中国航天空气动力技术研究院 | Rudderpost heat sealing test device |
| CN205826262U (en) * | 2016-07-07 | 2016-12-21 | 长沙市天映机械制造有限公司 | A kind of air bubble clashes into the vacuum test cabin of detection testpieces performance parameter |
| CN106568568A (en) * | 2016-10-19 | 2017-04-19 | 北京航天长征飞行器研究所 | High-temperature combustion-gas flow supersonic wind tunnel test system |
| CN108255207A (en) * | 2018-01-02 | 2018-07-06 | 高砂建筑工程(北京)有限公司 | Wind-tunnel idling and spout device and its control method |
| CN108534981A (en) * | 2018-02-07 | 2018-09-14 | 北京航天长征飞行器研究所 | A kind of high-temperature tunnel collection port spraying temperature lowering apparatus |
| CN209506126U (en) * | 2018-11-29 | 2019-10-18 | 中国航天空气动力技术研究院 | A kind of hypersonic power heat integration test cabin |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109436373A (en) | 2019-03-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3055541B1 (en) | Hybrid inner fixed structure with metallic and composite construction | |
| CN108678871B (en) | Jet pipe heat insulation structure for thrust steering jet engine | |
| EP3696095B1 (en) | Installing or removing aircraft engines | |
| EP3287771B1 (en) | Apparatus for insertion into a cavity of an object | |
| CN104458189B (en) | Process layout method for conventional hypersonic speed wind tunnel | |
| US8777164B2 (en) | Air intake structure for an aircraft nacelle | |
| CN103091065B (en) | Shock wave tunnel for hypersonic air vehicle ground simulation test | |
| CN109436373B (en) | High-ultrasonic rapid force and heat combined test cabin | |
| EP3165449B1 (en) | Nacelle fluid drain | |
| CN109250149A (en) | Flow tunnel testing device for air suction type hypersonic vehicle radome fairing separation simulation | |
| US7721524B2 (en) | Integrated airbreathing and non-airbreathing engine system | |
| EP3617061B1 (en) | Mechanically-distributed propulsion drivetrain and architecture | |
| BRPI0716269A2 (en) | locking system for turbojet engine side movable bonnet, turbojet engine nacelle and powertrain | |
| RU2618831C2 (en) | Method and air vehicle for moving in planetary atmosphere with speeds above the first space and highly integrated hypersonic vehicle apparatus (versions) for implementation of the method | |
| CN112747890B (en) | Pneumatic and thermal combined test system and test method | |
| FR2931799A1 (en) | Aircraft i.e. civil passenger transport aircraft, has reactors located inside envelope surface of theoretical fuselage, where lines of theoretical fuselage correspond to same dimension lines of aircraft fuselage with or without reactors | |
| US10400632B2 (en) | Unducted propeller turboshaft engine provided with a reinforcing shell integrating pipe segments | |
| CN109100110B (en) | Be applied to two throat thrust vectoring nozzle support arm device of ventilating | |
| CN103063398B (en) | Hypersonic wind tunnel experiment module | |
| CN106679923B (en) | A kind of pressure decoupling device influencing dynamometry model for high speed jet | |
| CN113833926B (en) | Push-pull type heat preservation sealing device for high-low temperature test of airplane | |
| US9932846B2 (en) | Aeroengine sealing arrangement | |
| CN208947639U (en) | Flow tunnel testing device for air suction type hypersonic vehicle radome fairing separation simulation | |
| US20110220218A1 (en) | Turbojet engine nacelle | |
| FR3009029A1 (en) | TUBE FOR EJECTING COMBUSTION GAS FROM A FLAT ENGINE PROVIDED WITH A DEVICE FOR SEALING BETWEEN A FIXED PART AND A MOBILE PART OF THE TUYERE |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |