CN204694437U - Whole cabin level pyroshock test loads and controls integrated apparatus with spectral pattern - Google Patents
Whole cabin level pyroshock test loads and controls integrated apparatus with spectral pattern Download PDFInfo
- Publication number
- CN204694437U CN204694437U CN201520166498.9U CN201520166498U CN204694437U CN 204694437 U CN204694437 U CN 204694437U CN 201520166498 U CN201520166498 U CN 201520166498U CN 204694437 U CN204694437 U CN 204694437U
- Authority
- CN
- China
- Prior art keywords
- level
- inter
- uniform distribution
- loaded ring
- distribution formula
- 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.)
- Withdrawn - After Issue
Links
Landscapes
- Geophysics And Detection Of Objects (AREA)
Abstract
The utility model relates to dynamics Explosive separation shock environmental test and observation technology field, be specifically related to the level pyroshock test loading of a kind of whole cabin and control integrated apparatus with spectral pattern, object is the test loading method, the spectral pattern control imperfection that solve existing whole cabin level pyroshock test means, cannot meet the problem of the development needs of new model completely.It is characterized in that, it comprises section cone section, boundary condition simulation device, measuring system and waveform generator between three-dimensional non-uniform Distribution formula loaded ring, mild detonating fuze, border rope, three level Four inter-stage section shell of columns, three or four inter-stages.The all standing that the utility model adopts whole cabin level pyroshock test to load to control with spectral pattern integrated apparatus can realize measured curve, the shock response spectrum maximum amount level produced is about 28000g, and break frequency is between 1500Hz-3500Hz.Meet test specification completely.Enforcement shows, this device can be applicable to each model whole cabin level pyroshock test, and test effect is remarkable.
Description
Technical field
The utility model relates to dynamics Explosive separation shock environmental test and observation technology field, is specifically related to the level pyroshock test loading of a kind of whole cabin and controls integrated apparatus with spectral pattern.
Background technology
Certain model rocket three level Four inter-stage section upper surface and lower surface in flight course adopt blasting bolt and cutting mode to carry out Explosive separation respectively, and this process experienced by harsh pyroshock environment.Three level Four inter-stage section shock measurement data show, the pyroshock environment of three level Four in Explosive separation process is severe, and shock response spectrum magnitude is the highest at more than 20000g.Three level Four inter-stage segment structures are compact, instrument and equipment is many, product installation site impact magnitude and high reliability request contradiction more outstanding, can these products bear this pyroshock environment, vital to the designed reliability of whole rocket, may cause that instrument and equipment is malfunctioning, data-transmission interruptions, the even problem such as abortive launch.Three level Four inter-stage section instrument and equipments are many, and it is long to carry out the unit test period, and cost is high, cannot meet this Project R&D progress needs, and this model clearly proposes whole cabin level pyroshock environment certification test.
Ground certification test is divided into unit level and the test of whole cabin level by test specimen.Generally adopt unit to test for the development of mini-plant and qualification, reception test, and generally adopt whole cabin level to test for the system of annexation complexity or the online certification test of multisystem.The test of whole cabin level can the mounting means of truer analog equipment, annexation between system, can also the impact transitive relation of different mounting points in truer boiler-plate.
Generally adopt the mode opening quick-fried true tripping device on formal cargo tank structure to produce the environment of requirement for the test of whole cabin level, but this method cannot meet the requirement increasing and impact magnitude.And each separation all causes structural failure, and the consumption of repairing isolating construction is huge.Adopt true cargo tank structure to carry out certification test, cost is high, difficulty is large.At present, domestic whole cabin structure high-magnitude shock response spectrum test technology investigation is less, lacks related data and experience.Test loading method, the spectral pattern of existing pyroshock test ability, particularly whole cabin level pyroshock test means control imperfection, cannot meet the development needs of new model completely.For meeting model growth requirement, needing badly and carrying out whole cabin level pyroshock test and load and control integrated technique research with spectral pattern.
Utility model content
The purpose of this utility model is the test loading method solving existing whole cabin level pyroshock test means, spectral pattern controls imperfection, the problem of the development needs of new model cannot be met completely, provide a kind of by driving source design loading, three-dimensional non-uniform Distribution formula loaded ring, whole cabin level pyroshock test condition three Combined design, the multiple reference mark of level blast impulse simulation test, whole cabin can be met, multiple directions shock response spectral pattern spreadability, load spectral pattern and measured curve break frequency, the whole cabin level pyroshock test that shock response spectrum magnitude basic simlarity all standing measured curve require loads and controls integrated apparatus with spectral pattern.
The utility model is achieved in that
A kind of whole cabin level pyroshock test loads and controls integrated apparatus with spectral pattern, comprises section cone section, boundary condition simulation device, measuring system and waveform generator between three-dimensional non-uniform Distribution formula loaded ring, mild detonating fuze, border rope, three level Four inter-stage section shell of columns, three or four inter-stages; Border rope is connected with three level Four inter-stage section shell of columns; Between three or four inter-stages, section cone section is positioned at the lower end of three level Four inter-stage section shell of columns; Three-dimensional non-uniform Distribution formula loaded ring is arranged on section between three level Four inter-stage section shell of columns and three or four inter-stages and bores the outside of section transition position; Mild detonating fuze is arranged on three-dimensional non-uniform Distribution formula loaded ring; Waveform generator is between three-dimensional non-uniform Distribution formula loaded ring and mild detonating fuze; Border rope is fixed on boundary condition simulation device; Measuring system is arranged on three level Four inter-stage section shell of columns.
Three-dimensional non-uniform Distribution formula loaded ring entirety as above is annular, the top of annular is provided with multiple loaded ring and is connected butt hole with inter-stage section, the outside surface of annular bottom is provided with mild detonating fuze and installs troughs for collecting energy; Three-dimensional non-uniform Distribution formula loaded ring is connected butt hole by loaded ring with inter-stage section and three level Four inter-stage section shell of columns are bolted; Three-dimensional non-uniform Distribution formula loaded ring entirety adopts A3 steel to make.
Mild detonating fuze as above is fixed on mild detonating fuze and installs troughs for collecting energy inside, and waveform generator is pressed on mild detonating fuze and installs in troughs for collecting energy by mild detonating fuze.
Mild detonating fuze as above is fixed on the inside surface of three-dimensional non-uniform Distribution formula loaded ring, waveform generator is pressed on the inside surface of three-dimensional non-uniform Distribution formula loaded ring by mild detonating fuze, and mild detonating fuze and waveform generator are pressed on the outside surface of three level Four inter-stage section shell of columns by three-dimensional non-uniform Distribution formula loaded ring.
Border as above rope adopts wire rope to realize.
Boundary condition simulation device as above is made up of pedestal and crossbeam, and pedestal is connected with ground base, and crossbeam is connected with pedestal, and the lower end of crossbeam is connected with hoist, and border rope is articulated on hoist; Boundary condition simulation device entirety adopts cast steel to realize.
Measuring system as above comprises Dewetron data acquisition unit, measures cable, charge amplifier, jerk acceleration transducer and electric charge-voltage transformation module; Jerk acceleration transducer is arranged on the outside surface of three level Four inter-stage section shell of columns, is connected with one end of charge amplifier by cable; The other end of charge amplifier is connected by cable one end with electric charge-voltage transformation module; The other end of electric charge-voltage transformation module is connected with Dewetron data acquisition unit.
The beneficial effects of the utility model are:
The utility model comprises section cone section, boundary condition simulation device, measuring system and waveform generator between three-dimensional non-uniform Distribution formula loaded ring, mild detonating fuze, border rope, three level Four inter-stage section shell of columns, three or four inter-stages.The utility model can realize whole cabin level pyroshock test shock response spectrum magnitude 28000g; Devise brand-new three-dimensional non-uniform Distribution formula loaded ring can realize three oriented energy non-uniform Distribution formula Loading Control and produce higher pyroshock environment simultaneously; Achieve the multi-control point of whole cabin level blast impulse simulation test, multi-direction shock response spectral pattern spreadability, load spectral pattern and measured curve break frequency, shock response spectrum magnitude basic simlarity all standing measured curve; Achieve whole cabin level pyroshock test to load and control integrated fused controlling with spectral pattern and parameter regulates; Adopt this device, solve certain emphasis carrier rocket model three level Four inter-stage section whole cabin pyroshock test problem of country, for Project R&D work provides effective support.
Accompanying drawing explanation
Fig. 1 is that whole cabin of the present utility model level pyroshock test loads the structural drawing controlling integrated apparatus with spectral pattern;
Fig. 2 is that whole cabin of the present utility model level pyroshock test loads the structural drawing controlling the three-dimensional non-uniform Distribution formula loaded ring of integrated apparatus with spectral pattern;
Fig. 3 is that whole cabin of the present utility model level pyroshock test loads the upward view controlling the three-dimensional non-uniform Distribution formula loaded ring of integrated apparatus with spectral pattern;
Fig. 4 is that whole cabin of the present utility model level pyroshock test loads and spectral pattern controls the A1 of the three-dimensional non-uniform Distribution formula loaded ring of integrated apparatus to cut-open view;
Fig. 5 is that whole cabin of the present utility model level pyroshock test loads and spectral pattern controls the A2 of the three-dimensional non-uniform Distribution formula loaded ring of integrated apparatus to cut-open view.
Wherein: 1. three-dimensional non-uniform Distribution formula loaded ring, 2. mild detonating fuze, 3. border rope, 4. three level Four inter-stage section shell of columns, 5. section cone section, 6. boundary condition simulation device between three or four inter-stages, 7. measuring system, 101. loaded rings are connected butt hole with inter-stage section, and troughs for collecting energy installed by 102. mild detonating fuzes.
Embodiment
Below in conjunction with drawings and Examples, the utility model is described further.
As shown in Figure 1, a kind of whole cabin level pyroshock test loads and controls integrated apparatus with spectral pattern, comprises section cone section 5, boundary condition simulation device 6, measuring system 7 and waveform generator between three-dimensional non-uniform Distribution formula loaded ring 1, mild detonating fuze 2, border rope 3, three level Four inter-stage section shell of column 4,34 inter-stage.Border rope 3 is arranged on the upper end of three level Four inter-stage section shell of columns 4.Between three or four inter-stages, section cone section 5 and three level Four inter-stage section shell of columns are structure as a whole.Three-dimensional non-uniform Distribution formula loaded ring 1 is arranged on section between three level Four inter-stage section shell of column 4 and 34 inter-stages and bores the outside of section 5 transition position.Three-dimensional non-uniform Distribution formula loaded ring 1 is for realizing mild detonating fuze three oriented energy non-uniform Distribution formula Loading Control and produce pyroshock environment simultaneously.Mild detonating fuze 2 is arranged on three-dimensional non-uniform Distribution formula loaded ring 1.Mild detonating fuze 2 is for explosive driven source.Waveform generator is between three-dimensional non-uniform Distribution formula loaded ring 1 and mild detonating fuze 2.Waveform generator is used for controlled loading spectral pattern.Border rope 3 is arranged on the lower end of boundary condition simulation device 6.Border rope 3 and boundary condition simulation device 6 are for fixing whole device.Measuring system 7 is arranged on the upper of three level Four inter-stage section shell of columns 4.The impact acceleration that measuring system 7 produces for measuring blast.
As shown in Figures 2 to 5, three-dimensional non-uniform Distribution formula loaded ring 1 entirety is annular, the top of annular is provided with multiple loaded ring and is connected butt hole 101 with inter-stage section, the outside surface of annular bottom is provided with mild detonating fuze and installs troughs for collecting energy 102.Three-dimensional non-uniform Distribution formula loaded ring 1 is connected butt hole 101 by loaded ring with inter-stage section and three level Four inter-stage section shell of columns 4 are bolted.Three-dimensional non-uniform Distribution formula loaded ring 1 entirety adopts A3 steel to make.
Mild detonating fuze 2 can be fixed on mild detonating fuze and install troughs for collecting energy 102 inside, and waveform generator is pressed on mild detonating fuze and installs in troughs for collecting energy 102 by mild detonating fuze 2.Mild detonating fuze 2 also can be fixed on the inside surface of three-dimensional non-uniform Distribution formula loaded ring 1, waveform generator is pressed on the inside surface of three-dimensional non-uniform Distribution formula loaded ring 1 by mild detonating fuze 2, and mild detonating fuze 2 and waveform generator are pressed on the outside surface of three level Four inter-stage section shell of columns 4 by three-dimensional non-uniform Distribution formula loaded ring 1.
Border rope 3 adopts wire rope to realize.
Boundary condition simulation device 6 is made up of pedestal and crossbeam, and pedestal is connected with ground base, and crossbeam is connected with pedestal, and the lower end of crossbeam is connected with hoist, and border rope 3 is articulated on hoist.Boundary condition simulation device 6 entirety adopts cast steel to realize.
Measuring system 7 comprises Dewetron data acquisition unit, measures cable, charge amplifier, jerk acceleration transducer and electric charge-voltage transformation module.Jerk acceleration transducer is arranged on the outside surface of three level Four inter-stage section shell of columns 4, is connected with one end of charge amplifier by cable.The other end of charge amplifier is connected by cable one end with electric charge-voltage transformation module.The other end of electric charge-voltage transformation module is connected with Dewetron data acquisition unit.
After on-test, first bore section 5 with three level Four inter-stage section shell of columns 4 with section between three or four inter-stages by border rope 3 and be connected, be fixed on boundary condition simulation device 6.Then the jerk acceleration transducer in measuring system 7 is arranged on three level Four inter-stage section shell of columns 4, checks that whether jerk acceleration transducer signal is normal, and the whole duty of measuring system 7 is checked.After measuring system is normal, then three-dimensional non-uniform Distribution formula loaded ring 1, waveform generator and mild detonating fuze 2 and detonator is installed, finally whole pilot system is connected with boundary condition simulation device 6.After having connected, check whole system, the rear preparation working properly of all subsystems is tested.During on-test, primer detonator ignites mild detonating fuze 2, and measuring system 7 obtains the impact acceleration data on three level Four inter-stage section shell of columns 4.Shock response analysis of spectrum is carried out to the impact acceleration data gathered, by adjustment boundary condition, the material of three-dimensional non-uniform Distribution formula loaded ring 1, structure and size and the connected mode with three level Four inter-stage section shell of columns 4 thereof, the kind of explosive, distribution form, explosive yield and waveform generator in mild detonating fuze 2, the groove depth, physical dimension, position etc. of troughs for collecting energy 102 control shock response spectral pattern, realize the level pyroshock test loading of whole cabin and control integrated with spectral pattern.
The utility model comprises section cone section 5, boundary condition simulation device 6, measuring system 7 and waveform generator between three-dimensional non-uniform Distribution formula loaded ring 1, mild detonating fuze 2, border rope 3, three level Four inter-stage section shell of column 4,34 inter-stage.Adopt the level pyroshock test loading of whole cabin to control integrated apparatus with spectral pattern and can realize multi-control point, multi-direction shock response spectral pattern spreadability, load spectral pattern and measured curve break frequency, shock response spectrum magnitude basic simlarity all standing measured curve, the shock response spectrum maximum amount level produced is about 28000g, and break frequency is between 1500Hz-3500Hz.Meet test specification completely.Enforcement shows, the method can be applicable to the model such as carrying space and missile armament whole cabin level pyroshock test, and test effect is remarkable.
In conjunction with the accompanying drawings and embodiments the present invention is explained in detail above, but the present invention is not limited to above-described embodiment, in the ken that those of ordinary skill in the art possess, can also makes a variety of changes under the prerequisite not departing from present inventive concept.The content be not described in detail in the present invention all can adopt prior art.
Claims (7)
1. whole cabin level pyroshock test loads and controls an integrated apparatus with spectral pattern, it is characterized in that: it comprises section cone section (5), boundary condition simulation device (6), measuring system (7) and waveform generator between three-dimensional non-uniform Distribution formula loaded ring (1), mild detonating fuze (2), border rope (3), three level Four inter-stage sections shell of column (4), three or four inter-stages; Border rope (3) is connected with three level Four inter-stage sections shell of column (4); Between three or four inter-stages, section cone section (5) is positioned at the lower end of three level Four inter-stage sections shell of column (4); Three-dimensional non-uniform Distribution formula loaded ring (1) is arranged on section between three level Four inter-stage sections shell of column (4) and three or four inter-stages and bores the outside of section (5) transition position; Mild detonating fuze (2) is arranged in three-dimensional non-uniform Distribution formula loaded ring (1); Waveform generator is positioned between three-dimensional non-uniform Distribution formula loaded ring (1) and mild detonating fuze (2); Border rope (3) is fixed on boundary condition simulation device (6); Measuring system (7) is arranged in three level Four inter-stage sections shell of column (4).
2. whole cabin according to claim 1 level pyroshock test loads and controls integrated apparatus with spectral pattern, it is characterized in that: described three-dimensional non-uniform Distribution formula loaded ring (1) entirety is annular, be provided with multiple loaded ring on the top of annular and be connected butt hole (101) with inter-stage section, the outside surface of annular bottom is provided with mild detonating fuze troughs for collecting energy (102) is installed; Three-dimensional non-uniform Distribution formula loaded ring (1) is connected butt hole (101) by loaded ring with inter-stage section and is bolted with three level Four inter-stage sections shell of column (4); Three-dimensional non-uniform Distribution formula loaded ring (1) entirety adopts A3 steel to make.
3. whole cabin according to claim 2 level pyroshock test loads and controls integrated apparatus with spectral pattern, it is characterized in that: described mild detonating fuze (2) is fixed on mild detonating fuze and installs troughs for collecting energy (102) inside, and waveform generator is pressed on mild detonating fuze and installs in troughs for collecting energy (102) by mild detonating fuze (2).
4. whole cabin according to claim 2 level pyroshock test loads and controls integrated apparatus with spectral pattern, it is characterized in that: described mild detonating fuze (2) is fixed on the inside surface of three-dimensional non-uniform Distribution formula loaded ring (1), waveform generator is pressed on the inside surface of three-dimensional non-uniform Distribution formula loaded ring (1) by mild detonating fuze (2), and mild detonating fuze (2) and waveform generator are pressed on the outside surface of three level Four inter-stage sections shell of column (4) by three-dimensional non-uniform Distribution formula loaded ring (1).
5. whole cabin according to claim 1 level pyroshock test loads and controls integrated apparatus with spectral pattern, it is characterized in that: described border rope (3) adopts wire rope to realize.
6. whole cabin according to claim 1 level pyroshock test loads and controls integrated apparatus with spectral pattern, it is characterized in that: described boundary condition simulation device (6) is made up of pedestal and crossbeam, pedestal is connected with ground base, crossbeam is connected with pedestal, the lower end of crossbeam is connected with hoist, and border rope (3) is articulated on hoist; Boundary condition simulation device (6) entirety adopts cast steel to realize.
7. whole cabin according to claim 1 level pyroshock test loads and controls integrated apparatus with spectral pattern, it is characterized in that: described measuring system (7) comprises Dewetron data acquisition unit, measures cable, charge amplifier, jerk acceleration transducer and electric charge-voltage transformation module; Jerk acceleration transducer is arranged on the outside surface of three level Four inter-stage sections shell of column (4), is connected with one end of charge amplifier by cable; The other end of charge amplifier is connected by cable one end with electric charge-voltage transformation module; The other end of electric charge-voltage transformation module is connected with Dewetron data acquisition unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520166498.9U CN204694437U (en) | 2015-03-24 | 2015-03-24 | Whole cabin level pyroshock test loads and controls integrated apparatus with spectral pattern |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520166498.9U CN204694437U (en) | 2015-03-24 | 2015-03-24 | Whole cabin level pyroshock test loads and controls integrated apparatus with spectral pattern |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204694437U true CN204694437U (en) | 2015-10-07 |
Family
ID=54234714
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520166498.9U Withdrawn - After Issue CN204694437U (en) | 2015-03-24 | 2015-03-24 | Whole cabin level pyroshock test loads and controls integrated apparatus with spectral pattern |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204694437U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106153284A (en) * | 2015-03-24 | 2016-11-23 | 北京强度环境研究所 | Whole cabin level pyroshock test loads and controls integrated apparatus with spectral pattern |
| CN106482970A (en) * | 2016-09-30 | 2017-03-08 | 北京强度环境研究所 | A kind of spacecraft Explosive separation guide type safe retrieving assay device |
| CN107192521A (en) * | 2016-03-15 | 2017-09-22 | 北京强度环境研究所 | Cryogenic media exciting force loads protection device |
| CN108534976A (en) * | 2018-03-16 | 2018-09-14 | 西北工业大学 | A kind of shock response spectrum generator applied on vertical impact testing machine |
-
2015
- 2015-03-24 CN CN201520166498.9U patent/CN204694437U/en not_active Withdrawn - After Issue
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106153284A (en) * | 2015-03-24 | 2016-11-23 | 北京强度环境研究所 | Whole cabin level pyroshock test loads and controls integrated apparatus with spectral pattern |
| CN106153284B (en) * | 2015-03-24 | 2019-02-26 | 北京强度环境研究所 | Whole cabin grade pyroshock test load controls integrated apparatus with spectral pattern |
| CN107192521A (en) * | 2016-03-15 | 2017-09-22 | 北京强度环境研究所 | Cryogenic media exciting force loads protection device |
| CN107192521B (en) * | 2016-03-15 | 2023-10-03 | 北京强度环境研究所 | Low-temperature medium exciting force loading protection device |
| CN106482970A (en) * | 2016-09-30 | 2017-03-08 | 北京强度环境研究所 | A kind of spacecraft Explosive separation guide type safe retrieving assay device |
| CN108534976A (en) * | 2018-03-16 | 2018-09-14 | 西北工业大学 | A kind of shock response spectrum generator applied on vertical impact testing machine |
| CN108534976B (en) * | 2018-03-16 | 2019-09-24 | 西北工业大学 | A kind of shock response spectrum generator applied on vertical impact testing machine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204694437U (en) | Whole cabin level pyroshock test loads and controls integrated apparatus with spectral pattern | |
| CN104155538B (en) | Comprehensive experiment testing system for small satellite antenna | |
| CN107121254B (en) | A kind of large size guided missile on-hook vibration rig and method | |
| CN106372355B (en) | General perpendicular load simulating device | |
| CN102351046B (en) | Load-variable loading test device and method for detecting load by using same | |
| CN102636398B (en) | Experiment method for simulating impact type rock burst | |
| CN110207963B (en) | Free-free boundary simulation device for air spring elastic support vertical structure | |
| CN104236836B (en) | Pressure balancing system and method for rocket conveying pipeline system vibration test | |
| CN103776609B (en) | Integrated test system and technology for falling-object protective structure and roll-over protective structure | |
| CN104931219B (en) | A kind of landing shock experimental rig and its test method | |
| US20130061683A1 (en) | Systems and methods for performing structural tests on wind turbine blades | |
| CN102147342A (en) | Static test system for min-aircraft structure | |
| KR101837406B1 (en) | Apparatus and method for performing flight environment simulation test of missile | |
| CN110761341A (en) | Horizontal and vertical load loading test device and method for offshore pile cap foundation | |
| CN105486493B (en) | A kind of Hold down and release simulation test device and its application method | |
| CN105300679B (en) | A kind of arrester hook falls warship simulation test device | |
| CN101260807B (en) | Rock laneway primary blasting and delayed concrete-spraying technology | |
| CN106153284B (en) | Whole cabin grade pyroshock test load controls integrated apparatus with spectral pattern | |
| CN210152696U (en) | Constant-resistance anchor cable | |
| CN211318054U (en) | Experimental system for researching action mechanism of explosive stress wave of surrounding rock | |
| CN111022219B (en) | Ground test simulation device and method for separation device | |
| RU2338169C1 (en) | Method for high-intensity impact tests for instruments and equipment | |
| CN102879168B (en) | Multi-drop-hammer millisecond delay loading experiment system | |
| CN111392074B (en) | Landing buffer device test system | |
| CN101672743A (en) | Simulation test estimation system and test method for construction of inner stayguy suspended holding rod split tower |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20151007 Effective date of abandoning: 20190226 |
|
| AV01 | Patent right actively abandoned |