CN104828419A - Propellant storage tank support - Google Patents
Propellant storage tank support Download PDFInfo
- Publication number
- CN104828419A CN104828419A CN201510159201.0A CN201510159201A CN104828419A CN 104828419 A CN104828419 A CN 104828419A CN 201510159201 A CN201510159201 A CN 201510159201A CN 104828419 A CN104828419 A CN 104828419A
- Authority
- CN
- China
- Prior art keywords
- radial
- hole
- radial axle
- block
- fixed
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65D—CONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
- B65D90/00—Component parts, details or accessories for large containers
- B65D90/12—Supports
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
A propellant storage tank support comprises a base, an axial rotation assembly, a V-shaped supporting frame and radial rotation fixing assemblies. One end of the axial rotation assembly is fixed on the base, and the other end of the axial rotation assembly is fixedly provided with the V-shaped supporting frame. The two upper endpoints of the V-shaped supporting frame are each provided with one radial rotation fixing assembly, and the two ends of a storage box are fixed on the V-shaped supporting frame through the radial rotation fixing assemblies. Each radial rotation fixing assembly comprises a radial supporting base, a radial shaft, a fixing device and a rotation positioning device. One end of each supporting base is fixed at one endpoint of the V-shaped supporting frame. Through holes are formed in the middles of the supporting bases, and the radial shafts and the through holes are in clearance fit. After being inserted into the through holes, the radial shafts can rotate along the through holes. Each fixing device is mounted at one end of the corresponding radial shaft, and the two ends of the storage tank are fixed through the fixing devices. The rotation positioning devices are mounted at the other ends of the radial shafts, and are used for achieving the positioning function after the radial shafts are rotated.
Description
Technical field
The invention belongs to spacecraft technology field, particularly a kind of support being suitable for spacecraft propulsion agent tank heat.
Background technology
Spacecraft propulsion agent tank, before being installed to spacecraft, first will carry out thermal control enforcement to Tank of Spacecraft.Comprise the installation of temperature booster, heater circuit is connected in series, thermally dependent resistor is installed and the installation of multilayer insulation assembly.When carrying out thermal control to spacecraft propulsion agent tank and implementing, first to ensure that spacecraft propulsion agent tank is fixed reliable and secure, facilitate the implementation and operation of workman simultaneously.
Existing spacecraft propulsion agent tank fixing means is, first take off the packing chest upper cover of spacecraft propulsion agent tank, then spacecraft propulsion agent tank is placed in the packing chest of spacecraft propulsion agent tank, makes the upper sphere of spacecraft propulsion agent tank or lower peripheral surface upward.Because the packing chest of spacecraft propulsion agent tank has limitation, this fixing means has the following disadvantages: 1, the packing chest mainly spacecraft propulsion agent tank transport of spacecraft propulsion agent tank, the carrier deposited, design function is not considered the fixing when thermal control of spacecraft propulsion agent tank is implemented, so the deformation in compression of spacecraft propulsion agent tank appendix and implementation of port likely can be caused when spacecraft propulsion agent tank being placed on when the thermal control of spacecraft propulsion agent tank is implemented the packing chest internal fixtion of spacecraft propulsion agent tank, also the extrusion damage having implemented thermal control may be caused.2, the packing chest height height of spacecraft propulsion agent tank differs, thermal control is carried out when implementing in packing chest spacecraft propulsion agent tank being placed on spacecraft propulsion agent tank, work man-hour needs to bend over, sometimes need to stand sometimes, and spacecraft propulsion agent tank position motionless time, can only be worked around spacecraft propulsion agent tank back and forth by workman, labour intensity is large, easily causes the fatigue of workman, indirectly threatens work efficiency and workmanship.3, because spacecraft propulsion agent tank two spheres all need thermal control to implement, but a sphere can only be ensured upward in packing chest spacecraft propulsion agent tank being placed on spacecraft propulsion agent tank, so the thermal control of spacecraft propulsion agent tank two spheres is implemented to carry out simultaneously, cause work efficiency low.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, provides a kind of and can fix spacecraft propulsion agent tank support that is safe and reliable, that meet human engineering, increase work efficiency.
Technical solution of the present invention is:
A kind of propellant tank support, comprises base, axial-rotation assembly, V-arrangement bracing frame, radial rotary fixation kit; Wherein, one end of axial-rotation assembly is fixed on base, other end fixed installation V-arrangement bracing frame; Two upper extreme points of described V-arrangement bracing frame respectively install a radial rotary fixation kit, and described V-arrangement bracing frame is fixed on respectively by radial rotary fixation kit in the two ends of storage tank; Described radial rotary fixation kit comprises radial support seat, radial axle, anchor fitting, rotary positioning apparatus; Wherein one end of two supporting seats is individually fixed on an end points of V-arrangement bracing frame, the centre of supporting seat is provided with through hole, radial axle and described through hole are free-running fit, after described radial axle inserts through hole, radial axle can rotate along described through hole, at one end fixing device for installing of radial axle, the two ends of storage tank are fixed by anchor fitting; Rotary positioning apparatus is installed, for realizing the postrotational positioning function of radial axle at the other end of radial axle.
Described anchor fitting comprises back-up block and clamp, and the upper end fixed installation clamp of back-up block, two ends of storage tank are fixed respectively by back-up block and clamp.
Described rotary positioning apparatus comprises and radially slides block, radial locating dowel pin, lock screw; Radially slide block and be provided with the second through hole, radially sliding block is arranged on described radial axle by described second through hole, the diameter of described second through hole is greater than the external diameter of radial axle, the one end radially sliding block has tapped bore, after lock screw is screwed into tapped bore, block moving along described radial axle is radially slided for limiting, the direction radially sliding block and be parallel to described radial axle has pin-and-hole, supporting seat is provided with knock hole with described pin-and-hole relative position, after radial axle rotates, by radial locating dowel pin is inserted described knock hole, realize the location of radial axle.
The knock hole that described supporting seat is arranged is 8, and supporting seat is angularly arranged.
Described radial axle is provided with banking stop, radially slides block from landing radial axle for control.
The present invention's beneficial effect compared with prior art:
(1) because the present invention adopts radial rotary fixation kit to be fixedly clamped to spacecraft propulsion agent tank, the inflation inlet of such spacecraft propulsion agent tank, implementation of port and the thermal control assembly implemented can not be squeezed, and ensure that the fixing safe and reliable of spacecraft propulsion agent tank.
(2) height of the present invention is suitable, and workman can sedentary; Because the present invention adopts axial-rotation assembly, radial rotary fixation kit, spacecraft propulsion agent tank can be made freely to rotate in axis and radial direction and fix, workman at work position need not move and just can finish the work; So just facilitate the work of workman, reduce labour intensity.
(3) because the present invention adopts bracing frame, radial rotary fixation kit, the upper lower peripheral surface of spacecraft propulsion agent tank is completely exposed, can carry out thermal control enforcement simultaneously, which improves work efficiency.
Accompanying drawing explanation
Fig. 1 propellant tank supporting structure of the present invention schematic diagram;
Fig. 2 is the structural representation of radial rotary fixation kit.
Detailed description of the invention
Below in conjunction with drawings and Examples, the invention will be further described.
As shown in Figure 1, support is implemented in the Tank of Spacecraft thermal control that the thermal control of spacecraft propulsion agent tank is implemented, and comprising: base 1, axial-rotation assembly 2, V-arrangement bracing frame 3, two radial rotary fixation kits 4.Base 1 is the basic design that support is implemented in whole spacecraft propulsion agent tank 6 thermal control, be used for supporting whole spacecraft propulsion agent tank 6 thermal control and implement support, axial-rotation assembly 2 to be fixed on described base 1, is used for realizing the axial-rotation of spacecraft propulsion agent tank 6; V-arrangement bracing frame 3 is fixed on described axial-rotation assembly 2, is used for supporting spacecraft propulsion agent tank 6; Two radial rotary fixation kits 4 be separately fixed at two support beams on bracing frame 3 have been used for spacecraft propulsion agent tank 6 be fixedly clamped and radial rotary is fixed.
Described axial-rotation assembly 2 is mainly used in realizing rotating and positioning function, spinfunction mainly realizes by the bearing of its underpart, axostylus axostyle is fixedly mounted above bearing, axostylus axostyle is by bearing rotary, V-arrangement bracing frame 3 is fixedly mounted above it, therefore V-shaped rest 3 rotates relative to base 1 by bearing, axostylus axostyle arranged outside has outside thread in addition, locking piece is provided with negative thread, both cooperatively interact, after locking piece is tightened, the upper surface close contact of its lower surface and base 1, and then the rotation of locking piece is limited, the rotation of axostylus axostyle is also restricted, therefore the axial rotation of propellant tank is limited, one end of axial-rotation assembly 2 is fixed on base 1 by bearing, the other end fixed installation axostylus axostyle of bearing, axostylus axostyle fixedly mounts V-arrangement bracing frame 3, during bearing rotary, spindle rotation can be driven, and then driving V-arrangement bracing frame 3 axial-rotation, be also provided with a locking piece outside the axostylus axostyle of axial-rotation assembly 2, it is positioned at the outside of axostylus axostyle, match with the negative thread of axostylus axostyle, after locking piece is tightened, the axial motion of axial-rotation assembly 2 is restricted, and propellant tank 6 can axially be stablized.First locking piece and axostylus axostyle are unclamped when when needs, it rotates, rotate after unclamping, after being rotated in place, then by tightening the motion of locking piece restrictive axial rotary components 2, the mode of its constrained motion is closely cooperated by the lower surface of locking piece and the upper surface of base 1 to realize, namely locking piece is unclamped, the lower surface of locking piece departs from the upper surface of base 1, now, propellant tank can axial-rotation, when tightening locking piece, the lower surface of locking piece and the upper surface close contact of base 1, and then motion is limited, locking piece is for arranging female column structure, outside is also provided with the handle for tightening.
Two upper extreme points of described V-arrangement bracing frame 3 respectively install a radial rotary fixation kit 4, and described V-arrangement bracing frame 3 is fixed on respectively by radial rotary fixation kit 4 in the two ends of storage tank 6, as shown in Figure 2, described radial rotary fixation kit 4 comprises supporting seat 41, radial axle 42, anchor fitting, rotary positioning apparatus, wherein one end of two supporting seats 41 is individually fixed on a support beam of V-arrangement bracing frame 3, the centre of supporting seat 41 is provided with through hole, radial axle 42 and described through hole are free-running fit, after described radial axle 42 inserts through hole, radial axle 42 can rotate along described through hole, at one end fixing device for installing of radial axle 42, the two ends of storage tank 6 are fixed by anchor fitting, this anchor fitting comprises back-up block 43 and clamp 44, the upper end fixed installation clamp 44 of back-up block 43, two ends of storage tank 6 are fixed respectively by back-up block 43 and clamp 44, it should be noted that the two ends of storage tank 6 also match with back-up block 43 and clamp 44, a kind of embodiment is the two ends of storage tank 6 is sheet plate, after clamp 44 is fixed on back-up block 43, form a gap, sheet plate is placed between described gap, and by tightening clamp 44, make to tighten block 44 with back-up block 43, sheet plate to be fixed, if the shape of the Liang Ge bearing of storage tank 6 changes, the back-up block 43 of its anchor fitting is also corresponding with clamp 44 to change, also can be other structure, rotary positioning apparatus is installed, for realizing the postrotational positioning function of radial axle 42 at the other end of radial axle 42.Radial rotary fixation kit 4 can move along described axle supporting base 41 according to the specification of fixed spacecraft propulsion agent tank, realizes the fixing of different propellant tank and rotates location.
Described rotary positioning apparatus comprises and radially slides block 45, radial locating dowel pin 46, lock screw 47, radially slide block 45 and be provided with the second through hole, radially sliding block 45 is arranged on described radial axle 42 by described second through hole, radially sliding between block 45 and radial axle 42 can only linear slide, the diameter of described second through hole is greater than the external diameter of radial axle 42, the one end radially sliding block 45 has tapped bore, after lock screw 47 is screwed into tapped bore, block 45 moving along described radial axle 42 is radially slided for limiting, the direction radially sliding block 45 and be parallel to described radial axle 42 has pin-and-hole, supporting seat 41 is provided with knock hole with described pin-and-hole relative position, knock hole is angularly arranged along on supporting seat 41 surface relative with slide block, have eight, be evenly arranged by 45° angle, also can the quantity in regioselective hole and distribution as required, knock hole is more, distribute more intensive, the orientation angle that can realize propellant is more, after radial axle 42 rotates, by radial locating dowel pin 46 is inserted described knock hole, realize the location of radial axle 42, because supporting seat 41 is fixed on the support beam of V-arrangement bracing frame 3, therefore it is radial relative to sliding shoe 45 fixing, and sliding shoe 45 is rotating to as rear, is limited the relative motion of itself and radial axle 42 by lock screw 47, therefore locating dowel pin 46 inserts after in the knock hole of supporting seat 41, and sliding shoe 46 can be made to fix relative to supporting seat 41, on described radial axle 42, the reversing sense end of propellant tank is provided with banking stop 48, for preventing sliding shoe 45 from this direction landing.
Above-mentioned example be the present invention application one enumerate, those skilled in the art can carry out various improvement and replacing according to different designing requirements and design parameters when not departing from technical solution of the present invention, fall into protection scope of the present invention equally.
The content be not described in detail in specification sheets of the present invention belongs to the known technology of those skilled in the art.
Claims (5)
1. a propellant tank support, is characterized in that, comprises base (1), axial-rotation assembly (2), V-arrangement bracing frame (3), radial rotary fixation kit (4); Wherein, one end of axial-rotation assembly (2) is fixed on base (1), other end fixed installation V-arrangement bracing frame (3); Two upper extreme points of described V-arrangement bracing frame (3) respectively install a radial rotary fixation kit (4), and described V-arrangement bracing frame (3) is fixed on respectively by radial rotary fixation kit (4) in the two ends of storage tank; Described radial rotary fixation kit (4) comprises supporting seat (41), radial axle (42), anchor fitting, rotary positioning apparatus; Wherein one end of two supporting seats (41) is individually fixed on a support beam of V-arrangement bracing frame (3), the centre of supporting seat (41) is provided with through hole, radial axle (42) and described through hole are free-running fit, after described radial axle (42) inserts through hole, radial axle (42) can rotate along described through hole, at one end fixing device for installing of radial axle (42), the two ends of storage tank are fixed by anchor fitting; Rotary positioning apparatus is installed, for realizing radial axle (42) postrotational positioning function at the other end of radial axle (42).
2. a kind of propellant tank support according to claim 1, it is characterized in that, described anchor fitting comprises back-up block (43) and clamp (44), upper end fixed installation clamp (44) of back-up block (43), two ends of storage tank are fixed respectively by back-up block (43) and clamp (44).
3. a kind of propellant tank support according to claim 1, is characterized in that, described rotary positioning apparatus comprises and radially slides block (45), radial locating dowel pin (46), lock screw (47), radially slide block (45) and be provided with the second through hole, radially sliding block (45) is arranged on described radial axle (42) by described second through hole, the diameter of described second through hole is greater than the external diameter of radial axle (42), the one end radially sliding block (45) has tapped bore, after lock screw (47) is screwed into tapped bore, the motion of block (45) along described radial axle (42) is radially slided for restriction, the direction radially sliding block (45) and be parallel to described radial axle (42) has pin-and-hole, supporting seat (41) is upper is provided with knock hole with described pin-and-hole relative position, after radial axle (42) rotates, by radial locating dowel pin (46) is inserted described knock hole, realize the location of radial axle (42).
4. a kind of propellant tank support according to claim 3, is characterized in that, the upper knock hole arranged of described supporting seat (41) is 8, and supporting seat (41) is angularly arranged.
5. a kind of propellant tank support according to claim 1, it is characterized in that, described radial axle (42) is provided with banking stop (48), radially slides block (45) from landing radial axle (42) for control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510159201.0A CN104828419B (en) | 2015-04-03 | 2015-04-03 | A kind of propellant tank support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510159201.0A CN104828419B (en) | 2015-04-03 | 2015-04-03 | A kind of propellant tank support |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104828419A true CN104828419A (en) | 2015-08-12 |
| CN104828419B CN104828419B (en) | 2017-07-28 |
Family
ID=53806700
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510159201.0A Active CN104828419B (en) | 2015-04-03 | 2015-04-03 | A kind of propellant tank support |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104828419B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111550327A (en) * | 2020-04-02 | 2020-08-18 | 上海空间推进研究所 | Connecting and supporting structure of spacecraft low-temperature storage tank and assembling method |
| CN112658587A (en) * | 2020-12-28 | 2021-04-16 | 安徽优环环保设备制造有限公司 | Processing and manufacturing device of acid mist purification tower |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2015177A1 (en) * | 1969-04-02 | 1970-10-22 | VEB Chemie- und Tankanlagenbau-Kombinat Fürstenwalde, Fürstenwalde, Spree | Construction and welding device for - spherical vessels used in the storage of |
| GB2283447A (en) * | 1993-11-01 | 1995-05-10 | Joseph Augustine Higgins | A welding jig |
| CN101975641A (en) * | 2010-09-29 | 2011-02-16 | 航天东方红卫星有限公司 | Microsatellite quality characteristic bidirectional testing equipment and method |
| CN202074193U (en) * | 2011-03-15 | 2011-12-14 | 毛加兵 | Turnover stand of automobile engine |
| CN102489926A (en) * | 2011-11-16 | 2012-06-13 | 安徽博微长安电子有限公司 | Steel ball welding device capable of continuously rotating workpieces |
| CN102513768A (en) * | 2012-01-05 | 2012-06-27 | 南车二七车辆有限公司 | Flexible assembling and welding device for cross beams of railway wagon bodies and installation method thereof |
| CN102849227A (en) * | 2012-03-31 | 2013-01-02 | 航天东方红卫星有限公司 | Butt joint and regulation equipment for solar wings of moonlet |
| CN103057729A (en) * | 2012-12-26 | 2013-04-24 | 北京空间飞行器总体设计部 | Fixing device of helium bottle of propulsion system of spacecraft |
| CN103133862A (en) * | 2013-02-05 | 2013-06-05 | 上海空间推进研究所 | Bearing surface tension storage box |
| CN103770047A (en) * | 2013-11-13 | 2014-05-07 | 浙江吉利控股集团有限公司 | Multifunctional integrated engine assembly fixture |
| CN104227412A (en) * | 2014-09-22 | 2014-12-24 | 安徽江淮汽车股份有限公司 | Device for installing gearbox valve body |
-
2015
- 2015-04-03 CN CN201510159201.0A patent/CN104828419B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2015177A1 (en) * | 1969-04-02 | 1970-10-22 | VEB Chemie- und Tankanlagenbau-Kombinat Fürstenwalde, Fürstenwalde, Spree | Construction and welding device for - spherical vessels used in the storage of |
| GB2283447A (en) * | 1993-11-01 | 1995-05-10 | Joseph Augustine Higgins | A welding jig |
| CN101975641A (en) * | 2010-09-29 | 2011-02-16 | 航天东方红卫星有限公司 | Microsatellite quality characteristic bidirectional testing equipment and method |
| CN202074193U (en) * | 2011-03-15 | 2011-12-14 | 毛加兵 | Turnover stand of automobile engine |
| CN102489926A (en) * | 2011-11-16 | 2012-06-13 | 安徽博微长安电子有限公司 | Steel ball welding device capable of continuously rotating workpieces |
| CN102513768A (en) * | 2012-01-05 | 2012-06-27 | 南车二七车辆有限公司 | Flexible assembling and welding device for cross beams of railway wagon bodies and installation method thereof |
| CN102849227A (en) * | 2012-03-31 | 2013-01-02 | 航天东方红卫星有限公司 | Butt joint and regulation equipment for solar wings of moonlet |
| CN103057729A (en) * | 2012-12-26 | 2013-04-24 | 北京空间飞行器总体设计部 | Fixing device of helium bottle of propulsion system of spacecraft |
| CN103133862A (en) * | 2013-02-05 | 2013-06-05 | 上海空间推进研究所 | Bearing surface tension storage box |
| CN103770047A (en) * | 2013-11-13 | 2014-05-07 | 浙江吉利控股集团有限公司 | Multifunctional integrated engine assembly fixture |
| CN104227412A (en) * | 2014-09-22 | 2014-12-24 | 安徽江淮汽车股份有限公司 | Device for installing gearbox valve body |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111550327A (en) * | 2020-04-02 | 2020-08-18 | 上海空间推进研究所 | Connecting and supporting structure of spacecraft low-temperature storage tank and assembling method |
| CN111550327B (en) * | 2020-04-02 | 2021-06-04 | 上海空间推进研究所 | Connecting and supporting structure of spacecraft low-temperature storage tank and assembling method |
| CN112658587A (en) * | 2020-12-28 | 2021-04-16 | 安徽优环环保设备制造有限公司 | Processing and manufacturing device of acid mist purification tower |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104828419B (en) | 2017-07-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104828419A (en) | Propellant storage tank support | |
| CN103410896A (en) | Locking device of two-dimensional rotating equipment | |
| CN104747587A (en) | Angle regulating device and application thereof | |
| CN203384267U (en) | Locking device for two-dimensional rotating equipment | |
| CN203863339U (en) | Airplane assembling tool | |
| CN108274214A (en) | A kind of CPU automatic clamping and placings method | |
| CN103192282B (en) | Support frame in cylinder | |
| CN205852308U (en) | A kind of hydraulic drilling machine fixture for processing auto parts machinery mould | |
| CN207497183U (en) | A kind of highway engineering pipeline arranging frame | |
| CN104475815A (en) | Multi-axis cutter adjustment structure | |
| CN102107416B (en) | Detaching device for thyristor of converter valve | |
| CN105328471B (en) | A kind of straight type bone plate clamp for machining | |
| CN104385215B (en) | A kind of oil seal for automobile engine disassembles frock and oil seal demounting method | |
| CN211565224U (en) | Positioning device for machining aircraft parts | |
| CN105312927B (en) | Rear cover pivoted arm bilateral ball cutting tool and its application method | |
| CN202789272U (en) | Fuel injector clamping device | |
| CN207171441U (en) | Nonstandard constitutional detail rotary joint device | |
| CN106272999A (en) | A kind of multiple degrees of freedom Gypsum Fibrosum cutting support | |
| CN202458644U (en) | Orthopedic fixing support | |
| CN203542162U (en) | Clamp for clamping hub of wind generating set | |
| CN206855230U (en) | A kind of cavity inner plane lapping device | |
| CN205520794U (en) | A positioning and clamping device that is used for grinding of axle type part hole | |
| CN211163617U (en) | Small-bore pipeline fixing clamp | |
| CN204397089U (en) | Gear-hobbing machine shaft forgings assists loading and unloading frock | |
| CN204705468U (en) | Main shaft running-in system Placement Cell |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |