CN105711857A - Membrane aerospace craft deploying and locking mechanism - Google Patents
Membrane aerospace craft deploying and locking mechanism Download PDFInfo
- Publication number
- CN105711857A CN105711857A CN201610274269.8A CN201610274269A CN105711857A CN 105711857 A CN105711857 A CN 105711857A CN 201610274269 A CN201610274269 A CN 201610274269A CN 105711857 A CN105711857 A CN 105711857A
- Authority
- CN
- China
- Prior art keywords
- side plate
- cylinder block
- piston rod
- hinge
- top board
- 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
- 239000012528 membrane Substances 0.000 title abstract 5
- 230000000712 assembly Effects 0.000 claims abstract description 8
- 238000000429 assembly Methods 0.000 claims abstract description 8
- 230000006835 compression Effects 0.000 claims description 25
- 238000007906 compression Methods 0.000 claims description 25
- 239000010409 thin film Substances 0.000 claims description 13
- 230000000694 effects Effects 0.000 claims description 9
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 238000003032 molecular docking Methods 0.000 claims description 2
- 230000000452 restraining effect Effects 0.000 abstract 2
- 238000010586 diagram Methods 0.000 description 5
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 210000000078 claw Anatomy 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000002195 synergetic effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
Abstract
The invention discloses a membrane aerospace craft deploying and locking mechanism, belonging to the technical field of the aerospace engineering. The membrane aerospace craft deploying and locking mechanism comprises rotational hinge assemblies, side plates I, side plates II, a bottom plate, a top plate and restraining assemblies, wherein a limit plate perpendicular to a plane where the side plate II is arranged is arranged on the side plate II, the bottom plate, the top plate, two opposite side plates I and two opposite side plates II constitute a closed cuboid shell, the side plates I are movably connected with the bottom plate and the top plate by the rotational hinge assemblies, the side plates II are movably connected with the bottom plate and the top plate by the rotational hinge assemblies, the top plate is formed by two slabs through butt-jointing, the butt-jointed ends of two slabs are limited by step-shaped seam allowances, the lower end surface of the top plate pushes against the limit plate of the side plate II, and the upper end surface of the top plate is limited by two restraining assemblies fixed on the top plate. The membrane aerospace craft deploying and locking mechanism is applied to a membrane aerospace craft platform, is integrated with deploying and locking functions, has the characteristics of simple structure, reliable function, small volume and light weight, uses a spring to store energy and does not require an additional energy source.
Description
Technical field
The invention belongs to space technology field, be specifically related to a kind of thin film spacecraft and launch and locking mechanism.
Background technology
Extension means is that in spacecraft mechanism, early start uses with the tight relieving mechanism of lock (pressure), is also the most widely used class of establishment.Stretch (expansion) mechanism and substantially can be divided into four main Types, i.e. collapsible development mechanism, telescopic extension mechanism, shaft-like framework type extension means and inflated type development mechanism；The tight relieving mechanism of lock (pressure) can be divided into three main Types: the tight relieving mechanism of the semi-rigid lock of banding (pressure), the tight relieving mechanism of lock claw formula lock (pressure) and the tight relieving mechanism of link-type lock (pressure), above expansion is many with lock function to be completed by two sets or more assembly synergistic, therefore volume is big, weight is big, reliability is not high, is not suitable for thin film spacecraft platform.
Summary of the invention
In view of this, the present invention provides a kind of thin film spacecraft to launch and locking mechanism, is applied to thin film spacecraft platform, expansion and lock function can be integrated, have simple in construction, function is reliable, volume is little and lightweight feature, and takes spring energy-storage, it is not necessary to additional energy source.
The present invention is achieved through the following technical solutions:
The invention discloses a kind of thin film spacecraft to launch and locking mechanism, including: turning joint assembly, side plate I, side plate II, base plate, top board and restraint assembly；
Described side plate II is provided with the limiting plate being perpendicular to side plate II place plane；
Base plate, top board, two relative side plate I and two relative side plate II form a cuboid housing closed；Wherein, side plate I and base plate and top board and side plate II are flexibly connected each through turning joint assembly with base plate and top board；
Described top board is formed by two flat board docking, and the butt end of two flat boards is spacing by stepped seam；The lower surface of top board is inconsistent with the limiting plate of side plate II, and upper surface is spacing by two restraint assemblies being fixed on top board.
Further, described turning joint assembly includes: male hinge, female hinge, rotation axle, torsion spring, securing rod and the second compression spring；The described upper processing of female hinge has lock hole；The described upper processing of public hinge has notch cuttype through hole；
Described public hinge is arranged on the edge of base plate and top board, female hinge is arranged on side plate I and the edge of side plate II, male hinge is flexibly connected by rotating axle with female hinge, torsion spring set fills on the rotating shaft, and the two ends of torsion spring conflict respectively in male hinge and female hinge, securing rod is arranged in the notch cuttype through hole of public hinge, and the axis of securing rod is vertical with the axis rotating axle；Second compression spring housing is contained on securing rod, and the two ends of the second compression spring are inconsistent with the step surface of the step surface of the notch cuttype through hole of public affairs hinge and securing rod respectively, and securing rod is conflicted at the outer surface of mother's hinge under the second effect compressing spring；When male hinge and female hinge relatively rotate under the effect of torsion spring and put in place, securing rod coordinates realization locking with the lock hole of female hinge.
Further, described restraint assembly includes: piston rod, cylinder block, the first compression spring and termination；
The centre position of described side plate II top edge extends upward auricle, and auricle is processed limited location hole；
The outer circumference surface processing of described piston rod has annular boss；
One end processing of described cylinder block has the axially extending bore communicated with its inner chamber, and the other end is open, and cylinder block has the cylinder body air inlet through with its inner chamber with the outer circumference surface processing of axially extending bore one end；
Cylinder block is fixed on top board, and piston rod is through the inner chamber of cylinder block, after one end coordinates with the axially extending bore hole axle of cylinder block, inserts in the spacing hole of side plate II and locks, and the other end carries out hole axle with the termination being fixed on cylinder block open end and coordinates；The inner peripheral surface of the annular boss of piston rod and cylinder block inner chamber is fitted, and cylinder block inner chamber is divided into the cavity with cylinder body air inlet and the cavity without cylinder body air inlet；First compression spring is positioned at the cylinder block intracavity without cylinder body air inlet, and installs on the piston rod, and the two ends of the first compression spring are inconsistent with the annular boss of piston rod and termination respectively；When unlocked, inflated to the inner chamber with cylinder body air inlet of cylinder block by cylinder body air inlet, piston rod compression the first compression spring so that piston rod departs from the spacing hole of side plate II and realizes unlocking.
Further, described piston rod coordinates with the hole axle of cylinder block contact surface and the annular boss of piston rod are mounted on sealing ring with the contact surface of cylinder block.
Beneficial effect: the present invention utilizes potential energy that torsion spring stores as launching power source, by the first of the external gas constraint relief assembly of cylinder body air inlet the compression spring retainer, securing rod is promoted to lock by the second compression spring of turning joint assembly when launching to put in place, ensure to expand into plane, integrating expansion, lock function, simple in construction, function is reliable, take spring energy-storage, it is not necessary to additional energy source.
Accompanying drawing explanation
Fig. 1 is the structure composition diagram of the present invention.
Fig. 2 is the partial schematic diagram of the turning joint assembly of the present invention.
Fig. 3 is the schematic diagram during turning joint assembly non-locking of the present invention.
Fig. 4 is the schematic diagram during turning joint assembly locking of the present invention.
Fig. 5 is the structure chart during restraint assembly locking of the present invention.
Fig. 6 is the restraint assembly of present invention structure chart when not locking.
Fig. 7 is the fundamental diagram of the present invention.
Fig. 8 is the structure chart after the present invention launches.
Wherein, 1-turning joint assembly, 2-side plate I, 3-side plate II, 4-base plate, 5-top board, 6-restraint assembly, 7-spacing hole, 8-piston rod, 9-cylinder body air inlet, 10-cylinder block, 11-first compresses spring, 12-termination, 13-securing rod, 14-second compresses spring, 15-lock hole, and 16-public affairs are cut with scissors, mother 17-cuts with scissors, and 18-rotates axle, 19-torsion spring.
Detailed description of the invention
Develop simultaneously embodiment below in conjunction with accompanying drawing, describe the present invention.
The invention provides a kind of thin film spacecraft to launch and locking mechanism, referring to accompanying drawing 1, including: turning joint assembly 1, side plate I2, side plate II3, base plate 4, top board 5 and restraint assembly 6；
The centre position of described side plate II3 top edge extends upward auricle, and auricle is processed limited location hole 7, and side plate II3 is provided with the limiting plate being perpendicular to auricle place plane；
Base plate 4,5, two relative side plate I2 of top board and two relative side plate II3 form a cuboid housing closed；Wherein, side plate I2 and base plate 4 and top board 5 and side plate II3 are flexibly connected each through turning joint assembly 1 with base plate 4 and top board 5；Top board 5 is docked by flat board A and flat board B and forms, spacing by stepped seam between flat board A and flat board B；The lower surface of flat board A butt end is inconsistent with the limiting plate of side plate II3, and upper surface is spacing by flat board B；Conflicting on flat board A in the lower surface of flat board B butt end, upper surface is spacing by two restraint assemblies 6 being fixed on flat board B；
Referring to accompanying drawing 2-4, described turning joint assembly 1 includes: male hinge 16, female hinge 17, rotation axle 18, torsion spring 19, securing rod 13 and the second compression spring 14；In described female hinge 17, processing has lock hole 15；In described public hinge 16, processing has notch cuttype through hole；
Described public hinge 16 is arranged on the edge of base plate 4 and top board 5, female hinge 17 is arranged on the edge of side plate I2 and side plate II3, male hinge 16 is flexibly connected by rotating axle 18 with female hinge 17, torsion spring 19 is sleeved on rotation axle 18, and the two ends of torsion spring 19 conflict respectively in male hinge 16 and female hinge 17, securing rod 13 is arranged in the notch cuttype through hole of public hinge 16, the axis of securing rod 13 is vertical with the axis rotating axle 18, second compression spring 14 is sleeved on securing rod 13, and second the two ends of compression spring 14 cut with scissors with public affairs respectively 16 the step surface of notch cuttype through hole and the step surface of securing rod 13 inconsistent, securing rod 13 second compress spring 14 effect under conflict cut with scissors mother 17 outer surface；When male hinge 16 and female hinge 17 relatively rotate under the effect of torsion spring 19 and put in place, securing rod 13 coordinates realization locking with the lock hole 15 of female hinge 17；
Referring to accompanying drawing 5-6, described restraint assembly 6 includes: piston rod 8, cylinder block 10, first compress spring 11 and termination 12；The outer circumference surface processing of described piston rod 8 has annular boss；One end processing of described cylinder block 10 has the axially extending bore communicated with its inner chamber, the other end is open, cylinder block 10 has the radial screw bore through with its inner chamber with the outer circumference surface processing of axially extending bore one end, and described radial screw bore is cylinder body air inlet 9, is used for connecting air inlet pipe to cylinder charge；
Cylinder block 10 is fixed on the flat board B of top board 5, the inner chamber of piston rod 8 traverse cylinder block 10, after one end coordinates with the axially extending bore hole axle of cylinder block 10, inserting in the spacing hole 7 of side plate II3 and lock, the other end carries out hole axle with the termination 12 being fixed on cylinder block 10 open end and coordinates；The inner peripheral surface of the annular boss of piston rod 8 and cylinder block 10 inner chamber is fitted, and cylinder block 10 inner chamber is divided into the cavity with cylinder body air inlet 9 and the cavity without cylinder body air inlet 9；And the contact surface that coordinates with the hole axle of cylinder block 10 of piston rod 8 and the annular boss of piston rod 8 are mounted on sealing ring with the contact surface of cylinder block 10, to ensure the air-tightness of cylinder block 10 inner chamber with cylinder body air inlet 9.First compression spring 11 is positioned at cylinder block 10 intracavity without cylinder body air inlet 9, and is arranged on piston rod 8, and the two ends of the first compression spring 11 are inconsistent with the annular boss of piston rod 8 and termination 12 respectively；When unlocked, being inflated to the inner chamber with cylinder body air inlet 9 of cylinder block 10 by cylinder body air inlet 9, piston rod 8 compresses the first compression spring 11 so that piston rod 8 departs from the spacing hole 7 of side plate II3 and realizes unlocking；
Operation principle: referring to accompanying drawing 7-8, described expansion is used for installing other assembly as frame after being connected by base plate 4 and thin film spacecraft platform are fixing with locking mechanism；
In an initial condition, the top board of described expansion and locking mechanism is in open mode, after thin film sail body proceeds to described expansion and locking mechanism, carry out once locking by hand: now by turning joint assembly 1, base plate 4, top board 5 are connected as a cuboid housing closed with side plate I2 and side plate II3, and the piston rod 8 in restraint assembly 6 is positioned at the spacing hole 7 of side plate II3 under the first effect compressing spring 11, complete limit function；Now mechanism is in locking station；
Under in working order, described expansion and locking mechanism elder generation constraint relief assembly 6 spacing, by cylinder body air inlet 9 to the nitrogen filling 1MPa in cylinder block 10, promotes piston rod 8 to overcome the elastic force of the first compression spring 11, spacing hole 7, spacing releasing is moved to the inner chamber without cylinder body air inlet 9；Then, first side plate II3 launches to both sides under the effect of torsion spring 19 in turning joint assembly 1；Release the flat board A and flat board B of spacing top board 5 to be launched to vertical state by level by torsion spring 19 in the turning joint assembly 1 that is connected with side plate I2；Finally, side plate I2 relies on two kinds of potential expression: a kind of is inertia force in top board 5 expansion process, and two is the energy of torsion spring 19 in the turning joint assembly 1 being connected with base plate 4；
When top board 5, side plate I2 and side plate II3 continue to be deployed into be in base plate 4 flush state time, securing rod 13 in turning joint assembly 1, under the second effect compressing spring 14, inserts in lock hole 15, completes lock function, described expansion and locking mechanism are launched into a plane, end-of-job.
In sum, these are only presently preferred embodiments of the present invention, be not intended to limit protection scope of the present invention.All within the spirit and principles in the present invention, any amendment of making, equivalent replacement, improvement etc., should be included within protection scope of the present invention.
Claims (4)
1. a thin film spacecraft launches and locking mechanism, it is characterized in that, including: turning joint assembly (1), side plate I (2), side plate II (3), base plate (4), top board (5) and restraint assembly (6)；
Described side plate II (3) is provided with the limiting plate being perpendicular to side plate II (3) place plane；
Base plate (4), top board (5), two relative side plate I (2) and two relative side plate II (3) form a cuboid housing closed；Wherein, side plate I (2) and base plate (4) and top board (5) and side plate II (3) are flexibly connected each through turning joint assembly (1) with base plate (4) and top board (5)；
Described top board (5) is formed by two flat board docking, and the butt end of two flat boards is spacing by stepped seam；The lower surface of top board (5) is inconsistent with the limiting plate of side plate II (3), and upper surface is spacing by two restraint assemblies (6) being fixed on top board (5).
2. a kind of thin film spacecraft stated such as claim 1 launches and locking mechanism, it is characterized in that, described turning joint assembly (1) including: male hinge (16), female hinge (17), rotation axle (18), torsion spring (19), securing rod (13) and the second compression spring (14)；The described upper processing of female hinge (17) has lock hole (15)；The described upper processing of public hinge (16) has notch cuttype through hole；
Described public hinge (16) is arranged on base plate (4) and the edge of top board (5), female hinge (17) is arranged on side plate I (2) and the edge of side plate II (3), male hinge (16) is flexibly connected by rotating axle (18) with female hinge (17), torsion spring (19) is sleeved in rotation axle (18), and the two ends of torsion spring (19) conflict respectively male hinge (16) and female cut with scissors on (17), securing rod (13) is arranged in the notch cuttype through hole of public hinge (16), the axis of securing rod (13) is vertical with the axis rotating axle (18)；Second compression spring (14) is sleeved on securing rod (13), and second cut with scissors the step surface of the step surface of notch cuttype through hole of (16) and securing rod (13) respectively with public affairs inconsistent the two ends of compression spring (14), securing rod (13) is conflicted under the second effect compressing spring (14) and is cut with scissors the outer surface of (17) mother；When male hinge (16) and female hinge (17) relatively rotate under the effect of torsion spring (19) and put in place, securing rod (13) coordinates realization locking with the lock hole (15) of female hinge (17).
3. a kind of thin film spacecraft stated such as claim 1 launches and locking mechanism, it is characterized in that, described restraint assembly (6) including: piston rod (8), cylinder block (10), the first compression spring (11) and termination (12)；
The centre position of described side plate II (3) top edge extends upward auricle, and auricle is processed limited location hole (7)；
The outer circumference surface processing of described piston rod (8) has annular boss；
One end processing of described cylinder block (10) has the axially extending bore communicated with its inner chamber, and the other end is open, and cylinder block (10) has the cylinder body air inlet (9) through with its inner chamber with the outer circumference surface processing of axially extending bore one end；
Cylinder block (10) is fixed on top board (5), the inner chamber of piston rod (8) traverse cylinder block (10), after one end coordinates with the axially extending bore hole axle of cylinder block (10), inserting in the spacing hole (7) of side plate II (3) and lock, the other end carries out hole axle with the termination (12) being fixed on cylinder block (10) open end and coordinates；The inner peripheral surface of the annular boss of piston rod (8) and cylinder block (10) inner chamber is fitted, and cylinder block (10) inner chamber is divided into the cavity with cylinder body air inlet (9) and the cavity without cylinder body air inlet (9)；First compression spring (11) is positioned at cylinder block (10) intracavity without cylinder body air inlet (9), and be arranged on piston rod (8), and the two ends of the first compression spring (11) are inconsistent with the annular boss of piston rod (8) and termination (12) respectively；When unlocked, inflated to the inner chamber with cylinder body air inlet (9) of cylinder block (10) by cylinder body air inlet (9), piston rod (8) compression the first compression spring (11) so that piston rod (8) departs from the spacing hole (7) of side plate II (3) and realizes unlocking.
4. a kind of thin film spacecraft as claimed in claim 3 launches and locking mechanism, it is characterized in that, contact surface and the annular boss of piston rod (8) that described piston rod (8) coordinates with the hole axle of cylinder block (10) are mounted on sealing ring with the contact surface of cylinder block (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610274269.8A CN105711857B (en) | 2016-04-28 | 2016-04-28 | A kind of film spacecraft expansion and locking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610274269.8A CN105711857B (en) | 2016-04-28 | 2016-04-28 | A kind of film spacecraft expansion and locking mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105711857A true CN105711857A (en) | 2016-06-29 |
| CN105711857B CN105711857B (en) | 2017-11-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610274269.8A Active CN105711857B (en) | 2016-04-28 | 2016-04-28 | A kind of film spacecraft expansion and locking mechanism |
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| Country | Link |
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| CN (1) | CN105711857B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106402120A (en) * | 2016-07-28 | 2017-02-15 | 长沙天仪空间科技研究院有限公司 | Fast locking mechanism |
| CN108298108A (en) * | 2017-12-22 | 2018-07-20 | 兰州空间技术物理研究所 | A kind of expansion locking mechanism based on torsionspring |
| CN111361761A (en) * | 2020-03-17 | 2020-07-03 | 上海宇航系统工程研究所 | Flexible foldable large porthole spacecraft structure |
| CN112298610A (en) * | 2020-09-30 | 2021-02-02 | 北京空间飞行器总体设计部 | Solar wing and sectional type secondary unfolding hinge thereof |
| CN113371230A (en) * | 2021-07-30 | 2021-09-10 | 长沙天仪空间科技研究院有限公司 | Unfolding mechanism of aerospace craft |
| CN113428384A (en) * | 2021-06-30 | 2021-09-24 | 中国科学院空间应用工程与技术中心 | Expandable cube star for space material experiment |
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| US5810296A (en) * | 1996-08-29 | 1998-09-22 | Trw Inc. | Integrated restraint/release/deployment initiation device |
| CN102826236A (en) * | 2012-09-13 | 2012-12-19 | 上海微小卫星工程中心 | Satellite |
| CN103466197A (en) * | 2013-09-26 | 2013-12-25 | 中国空间技术研究院 | Supporting packaging structure oriented to solar sail adopting inflatable auxiliary self-rebounding supporting arm |
| US20140263844A1 (en) * | 2013-03-15 | 2014-09-18 | The Boeing Company | Component Deployment System |
| CN105197256A (en) * | 2015-09-29 | 2015-12-30 | 中国空间技术研究院 | Modularized spacecraft capable of conducting on-orbit unfolding |
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2016
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US5810296A (en) * | 1996-08-29 | 1998-09-22 | Trw Inc. | Integrated restraint/release/deployment initiation device |
| CN102826236A (en) * | 2012-09-13 | 2012-12-19 | 上海微小卫星工程中心 | Satellite |
| US20140263844A1 (en) * | 2013-03-15 | 2014-09-18 | The Boeing Company | Component Deployment System |
| CN103466197A (en) * | 2013-09-26 | 2013-12-25 | 中国空间技术研究院 | Supporting packaging structure oriented to solar sail adopting inflatable auxiliary self-rebounding supporting arm |
| CN105197256A (en) * | 2015-09-29 | 2015-12-30 | 中国空间技术研究院 | Modularized spacecraft capable of conducting on-orbit unfolding |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106402120A (en) * | 2016-07-28 | 2017-02-15 | 长沙天仪空间科技研究院有限公司 | Fast locking mechanism |
| CN106402120B (en) * | 2016-07-28 | 2019-07-23 | 长沙天仪空间科技研究院有限公司 | A kind of quick-connect mechanism |
| CN108298108A (en) * | 2017-12-22 | 2018-07-20 | 兰州空间技术物理研究所 | A kind of expansion locking mechanism based on torsionspring |
| CN111361761A (en) * | 2020-03-17 | 2020-07-03 | 上海宇航系统工程研究所 | Flexible foldable large porthole spacecraft structure |
| CN112298610A (en) * | 2020-09-30 | 2021-02-02 | 北京空间飞行器总体设计部 | Solar wing and sectional type secondary unfolding hinge thereof |
| CN112298610B (en) * | 2020-09-30 | 2022-07-12 | 北京空间飞行器总体设计部 | Solar wing and sectional type secondary unfolding hinge thereof |
| CN113428384A (en) * | 2021-06-30 | 2021-09-24 | 中国科学院空间应用工程与技术中心 | Expandable cube star for space material experiment |
| CN113371230A (en) * | 2021-07-30 | 2021-09-10 | 长沙天仪空间科技研究院有限公司 | Unfolding mechanism of aerospace craft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105711857B (en) | 2017-11-03 |
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