CN107271298A - Launching tube end cap breaks through pilot system and its test method - Google Patents
Launching tube end cap breaks through pilot system and its test method Download PDFInfo
- Publication number
- CN107271298A CN107271298A CN201710482012.6A CN201710482012A CN107271298A CN 107271298 A CN107271298 A CN 107271298A CN 201710482012 A CN201710482012 A CN 201710482012A CN 107271298 A CN107271298 A CN 107271298A
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- end cap
- tube end
- launching tube
- assembly
- guide rail
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/30—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight
- G01N3/303—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight generated only by free-falling weight
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/003—Generation of the force
- G01N2203/0032—Generation of the force using mechanical means
- G01N2203/0033—Weight
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- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Train Traffic Observation, Control, And Security (AREA)
Abstract
Pilot system is broken through the invention provides a kind of launching tube end cap, it includes workbench, the both sides of the workbench are respectively provided with a mounting rod, the surface of workbench is provided with guide rail slide block component, clamping assembly and two Buffer Units, two Buffer Units are located at the both sides of guide rail slide block component respectively, the clamping assembly is arranged at the front portion of guide rail slide block component, the guide rail slide block component includes four line slideways, four contiguous blocks and four pairs of sliding blocks, one contiguous block is embedded the inner side with straight line guide rail, sliding block described in a pair is fixedly connected with a contiguous block, balance weight assembly is provided between four pairs of sliding blocks.Compared with prior art, the present invention has following beneficial effect：Break through that point location is accurate, shock-absorbing capacity is good, can test the speed, launching tube end cap installs simple and efficient, the accuracy of test data, the antenna house that protection is installed, measurement can be improved and break through momentary rate, improve test efficiency.
Description
Technical field
Pilot system and its test method are broken through the present invention relates to a kind of launching tube end cap, belongs to military industrial technology field.
Background technology
In the prior art, launching tube end cap is broken through in pilot system, and launching tube end cap is directly anchored on workbench more,
Operating space is narrow and small, and installation difficulty, installation effectiveness is low；It is existing that to break through experimental rig few using being oriented to more than 4 guide rails
Mode, it is poor that it breaks through point location accuracy, easily deviates launching tube end cap and specifies shock point；Many use springs and building rubber compound
Mode enters row buffering, and its snubber energy is small, and buffering effect is poor, and reaction force is big after impact, so that the antenna easily to installation
Cover quartz portions cause damage；It is that missile armament is ground to the instantaneous velocity that breaks through without directly and accurately data without velocity-measuring system
Work processed brings certain difficulty.
The content of the invention
Pilot system and its test method are broken through it is an object of the invention to provide a kind of launching tube end cap, point location is broken through
Accurately, shock-absorbing capacity is good, can test the speed, launching tube end cap installs simple and efficient, can improve the accuracy of test data, protection and install
Antenna house, measurement break through momentary rate, improve test efficiency.
The present invention is achieved by the following technical solutions：
Pilot system is broken through the invention provides a kind of launching tube end cap, it includes workbench, the both sides of the workbench
A mounting rod is respectively provided with, the surface of workbench is provided with guide rail slide block component, clamping assembly and two buffers, and two described slow
The both sides that component is located at guide rail slide block component respectively are rushed, the clamping assembly is arranged at the front portion of guide rail slide block component, described to lead
Rail slide block assembly includes four line slideways, four contiguous blocks and four pairs of sliding blocks, and a contiguous block is embedded at straight line
The inner side of guide rail, sliding block described in a pair is fixedly connected with a contiguous block, and balance weight assembly, the counterweight are provided between four pairs of sliding blocks
The top of component is provided with electromagnetism grabbing assembly, and the both sides of the balance weight assembly are respectively equipped with left buffering wing plate and right buffering wing plate,
The left buffering wing plate and right buffering wing plate can be in contact with two buffers respectively in lower backwardness, a mounting rod
Generating laser is provided with, another described mounting rod is provided with laser pickoff, and the center of the balance weight assembly is provided with dynamometry
Sensor.
Preferably, the electromagnetism grabbing assembly includes magnechuck, motor, steel wire rope and pulley, the electricity
The top that magnetic-disc is arranged at piece, the pulley is arranged at the top of magnechuck, and the steel wire loop is located on pulley, institute
Motor is stated with one end of steel wire rope to be connected.The balance weight assembly includes upper balancing weight, middle balancing weight and lower balancing weight.
Preferably, the center of the magnechuck is equipped with insurance screw rod, and the insurance screw rod exposes electromagnetism
Threaded one end at the top of sucker is connected with check screw.When the insurance screw rod passes through the magnechuck center through hole and described
When check screw is connected fastening with the insurance screw flight, the magnechuck is mechanically connected with the balance weight assembly and fixed,
Can effectively prevent because of the magnechuck accident power-off and caused by accident.
Preferably, the clamping assembly includes hand runner, lifting screw, linking arm, clamping plate and safety dog
Plate, the safety screen is arranged at the both sides of linking arm, and the linking arm is nested on the outside of lifting screw, and the hand runner is same
Axle is connected to the top of lifting screw, and the clamping plate is arranged at the end of linking arm.
Preferably, the surface of the clamping plate is additionally provided with pinboard.
Preferably, the edge of the armour plate is provided with positioning hole.
Preferably, the surface of the workbench is provided with the locating dowel matched with the positioning hole.
Preferably, when portion to be measured is antenna house, screw rod, institute are provided between the lower balancing weight and middle balancing weight
Force cell is stated to be fixedly arranged in screw rod.
Preferably, when the portion to be measured is dummy warhead, it is equipped with described lower piece for fixed-analog bullet
Connecting rod, the connecting rod is connected with force cell.
A kind of test method that pilot system is broken through using foregoing launching tube end cap, it comprises the following steps：
Magnechuck, which is declined, makes magnechuck center through hole through insurance screw rod, by check screw and insurance screw flight
Tighten；
Antenna house or dummy warhead are connected on force cell；
Launching tube end cap is installed in clamping assembly, and make launching tube end cap be located at antenna house or dummy warhead just under
Side；
Specified altitude assignment is promoted to by controlling motor by balance weight assembly, to meet experiment to antenna house tip or simulation
Point reach launching tube end cap break through at rate request；
Magnechuck is powered, and unclamps check screw；
Open velocity package switch, and dynamometric system switch；
Magnechuck is powered off, and discharges balance weight assembly, and balance weight assembly does freely to fall under the guiding of slide block guide rail slide block assembly
Body is moved, and antenna house tip or dummy warhead tip break through Dian Chu in launching tube end cap and break through launching tube end cap；
Balance weight assembly steadily stops after the cushioning effect of Buffer Unit.
Record data.
Compared with prior art, the present invention has following beneficial effect：
Break through that point location is accurate, shock-absorbing capacity is good, can test the speed, launching tube end cap installs simple and efficient, can improve experiment number
According to accuracy, protection install antenna house, measurement break through momentary rate, improve test efficiency.
Brief description of the drawings
By reading the detailed description made with reference to the following drawings to non-limiting example, further feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is structural representation of the invention；
Fig. 2 breaks through front view of the pilot system in test simulation bullet for the launching tube end cap of the present invention；
Fig. 3 breaks through front view of the pilot system when testing antenna house for the launching tube end cap of the present invention；
The side view that Fig. 4 is launching tube end cap a in the present invention；
The upward view that Fig. 5 is launching tube end cap a in the present invention；
The side view that Fig. 6 is launching tube end cap b in the present invention；
The upward view that Fig. 7 is launching tube end cap b in the present invention；
In figure：1st, guide rail slide block component；2nd, balance weight assembly；3rd, clamping assembly；4th, magnechuck；5th, Arming Assembly；6th, delay
Rush component；7th, dynamometry component；8th, velocity package；9th, launching tube end cap；10th, workbench；11st, console；12nd, a upper counterweight
Block；13rd, No. two upper balancing weights；14th, No. three upper balancing weights；15th, middle balancing weight；16th, a lower balancing weight；17th, screw rod；18th, two
Number lower balancing weight；19th, connecting rod；20th, dummy warhead；21st, antenna house；22nd, line slideway；23rd, sliding block；24th, contiguous block；25、
Chan frame；26th, regulating bolt；27th, magnechuck；28th, motor；29th, steel wire rope；30th, pulley；31st, screw rod is insured；32、
Check screw；33rd, left buffering wing plate；34th, right buffering wing plate；35th, reinforcement；36th, buffer；37th, bumper bracket；38th, it is fixed
Bit slice；39th, hand runner；40th, lifting screw；41st, linking arm；42nd, clamping plate；43rd, pinboard；44th, safety screen；45th, it is fixed
Position hole；46th, locating dowel；47th, left mounting rod；48th, right mounting rod；49th, generating laser；50th, laser pickoff；51st, data are adopted
Collect processing system；52nd, force cell；53rd, computer is tested.
Embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that to the ordinary skill of this area
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
Buffer, the manufacturer of laser velocimeter device and magnechuck and the model being related in the present invention are as shown in table 1.
Table 1
| Sequence number | Title | Model | Manufacturer |
| 1 | Buffer | MC64150M-1 | U.S. ACE |
| 2 | Laser velocimeter device | BETA laser velocimeters | Upper Hypon Accipitridae skill Development Co., Ltd |
| 3 | Magnechuck | φ300*250/1000kg | The power magnetic equipment Co., Ltd of Shanghai hundred million |
Note：Laser velocimeter device includes transmitter-receiver device.
As shown in figure 1, the launching tube end cap of the embodiment of the present invention, which breaks through pilot system, includes workbench 10, guide rail slide block group
Part 1, balance weight assembly 2, clamping assembly 3, magnechuck 4, Arming Assembly 5, Buffer Unit 6, dynamometry component 7, velocity package 8, hair
Shooting cylinder end cap 9, workbench 10, console 11.
As shown in Figures 1 to 3, launching tube end cap of the invention, which breaks through pilot system, includes workbench 10, the two of workbench 10
Side point is provided with left mounting rod 47 and right mounting rod 48, and the surface of workbench 10 is provided with guide rail slide block component 1, the and of clamping assembly 3
Two buffers 36, two Buffer Units 6 are located at the both sides of guide rail slide block component 1 respectively, and clamping assembly 3 is arranged at guide rail slide block
The front portion of component 1, guide rail slide block component 1 includes four line slideways 22, four contiguous blocks 24 and four pairs of sliding blocks 23, each company
The inner side that block 24 is embedded at straight line guide rail 22 is connect, every a pair of sliding blocks 23 are fixedly connected with a contiguous block 24, four pairs of sliding blocks
Balance weight assembly 2 is provided between 23, the top of balance weight assembly 2 is provided with electromagnetism grabbing assembly, and the both sides of balance weight assembly 2 are respectively equipped with a left side
Buffer wing plate 33 and it is right buffering wing plate 34, it is left buffering wing plate 33 and it is right buffering wing plate 34 lower backwardness can respectively with two buffers
36 are in contact, and left mounting rod 47 is provided with generating laser 49, and right mounting rod 48 is provided with laser pickoff 50, balance weight assembly 2
Center be provided with dynamometry component 7, the bottom of dynamometry component 7 is provided with force cell 52, left mounting rod 47, right mounting rod 48, swashs
Optical transmitting set 49 and laser absorption device 50 collectively constitute velocity package 8.
The outside of left buffering wing plate 33 and right buffering wing plate 34 is respectively provided with a reinforcement 35, and left buffering wing plate 33 and the right side are slow
Rush wing plate 34 by way of balancing weight in insertion 15 with balance weight assembly to be connected, each buffer 36 passes through a buffering respectively
Device bearing 37 is fixedly arranged on workbench 10, and left buffering wing plate 33, right buffering wing plate 34, buffer 36, bumper bracket 37 are together
Constitute and spacer 38 is also provided with by regulating bolt 26 on Buffer Unit 6, workbench 10, spacer 38 is sheathed on four straight lines
The outside of guide rail 22, available for the relative position adjusted in a small range between four line slideways 22.
Balance weight assembly 2 include a upper balancing weight 12, No. two upper balancing weights 13, No. three upper balancing weights 14, middle balancing weight 15,
A number lower balancing weight 16 and No. two lower balancing weights 18, electromagnetism grabbing assembly include magnechuck 4, motor 28, the and of steel wire rope 29
Pulley 30, magnechuck 4 is arranged at the top of a upper balancing weight 12, and pulley 30 is arranged at the top of magnechuck 4, steel wire rope
29 are set on pulley 30, and motor 28 is connected with one end of steel wire rope 29.
The center of magnechuck 4 is equipped with insurance screw rod 31, one end spiral shell for exposing the top of magnechuck 4 of insurance screw rod 31
Line is connected with check screw 32, insurance screw rod 31 and the composition Arming Assembly 5 of check screw 32.When insurance screw rod 31 is inhaled through electromagnetism
When the center through hole and check screw 32 of disk 4 are threadedly coupled fastening with insurance screw rod 31, magnechuck 4 and the machinery of balance weight assembly 2
Be connected, can effectively prevent because of the magnechuck accident power-off and caused by accident.
Clamping assembly 3 includes hand runner 39, lifting screw 40, linking arm 41, clamping plate 42 and safety screen 44, insurance
Baffle plate 44 is arranged at the both sides of linking arm 41, and linking arm 41 is nested in the outside of lifting screw 40, hand runner 39 it is coaxially connected in
The top of lifting screw 40, clamping plate 42 is arranged at the end of linking arm 41.The surface of clamping plate 42 is additionally provided with pinboard 43.Even
Connecing arm 41 can be rotated by 360 ° with lifting screw 40 for axle；Can rise or fall linking arm 41 by rotating hand runner 39；Dress
Clamping plate 42 can be rotated by 360 ° by the rotating shaft of linking arm 41；Clamping plate 42 has a positioning hole 45, workbench 10 specific bit be equipped with
The locating dowel 46 that clamping assembly 3 is engaged, positioning hole 45 may pass through locating dowel 46；According to test requirements document, launching tube end cap 9 can lead to
Bolt is crossed to be connected with clamping plate 42, or pinboard 43 is first connected by screw with clamping plate 42, then by launching tube end cap 9 with turning
Fishplate bar 43 is connected by screw.
When portion to be measured is antenna house 21, screw rod 17 is provided between lower a balancing weight 16 and middle balancing weight 15, dynamometry is passed
Sensor 52 is fixedly arranged in screw rod 17；When portion to be measured is dummy warhead 20, it is equipped with No. two lower balancing weights 18 for stent
Intend the connecting rod 19 of bullet 20, connecting rod 19 is connected with force cell 52.
Dynamometry component 7 and velocity package 8 are electrically connected with console 11, and data acquisition processing system is provided with console 11
51 and test computer 53.
As shown in Fig. 2~7, the operation principle that the launching tube end cap of the embodiment of the present invention breaks through pilot system is：
1st, declining magnechuck makes magnechuck center through hole through insurance screw rod, by check screw and insurance screw rod spiral shell
Line is tightened.
2nd, required according to different tests, force cell can be connected by screw rod with block under No. two, or force cell
It can be connected by connecting rod with dummy warhead.
3rd, according to test requirements document, antenna house is installed if it need to use antenna house without installing connecting rod and dummy warhead, if
Then antenna house is not installed without the use of antenna house and connecting rod and dummy warhead are installed.
4th, clamping plate is rotated to beyond workbench, rotating hand runner makes clamping plate rise to highest, rotating dress clamping plate
Make its reverse side upwards, when needing to test launching tube end cap a, pinboard is not installed, launching tube end cap a is directly passed through
Bolt is attached with clamping plate；When needing to test launching tube end cap b, pinboard is entered by screw with clamping plate
Row connection, then launching tube end cap b is attached by screw with pinboard；Rotating dress clamping plate makes it face up, by clamping
Plate is rotated to workbench, and rocking-turn wheel is changed hands in choosing makes clamping plate drop to minimum point while the locating dowel of workbench passes through clamping plate
Positioning hole.
5th, specified altitude assignment is promoted to by controlling motor by balance weight assembly, to meet experiment to antenna house tip or mould
Intend point reach launching tube end cap break through at rate request.
6th, magnechuck is powered, and unclamps check screw.
7th, velocity package switch is opened.
8th, dynamometric system switch is opened.
9th, magnechuck is powered off, and discharges balance weight assembly, and balance weight assembly does freedom under the guiding of slide block guide rail slide block assembly
Falling, antenna house tip or dummy warhead tip break through Dian Chu in launching tube end cap and break through launching tube end cap.
10th, balance weight assembly steadily stops after the cushioning effect of Buffer Unit.
The specific embodiment of the present invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (10)
1. a kind of launching tube end cap breaks through pilot system, it is characterised in that including workbench, the both sides of the workbench are respectively provided with
One mounting rod, the surface of workbench is provided with guide rail slide block component, clamping assembly and two buffers, and the clamping assembly is set
In the front portion of guide rail slide block component, the guide rail slide block component includes four line slideways, four contiguous blocks and four pairs of sliding blocks, one
The individual contiguous block is embedded the inner side with straight line guide rail, and sliding block described in a pair is fixedly connected with a contiguous block, four pairs of cunnings
Balance weight assembly is provided between block, the top of the balance weight assembly is provided with electromagnetism grabbing assembly, and the both sides of the balance weight assembly are distinguished
Provided with left buffering wing plate and right buffering wing plate, the left buffering wing plate and right buffering wing plate lower backwardness can respectively with described in two
Buffer is in contact, and a mounting rod is provided with generating laser, and another described mounting rod is provided with laser pickoff,
The center of the balance weight assembly is provided with force cell.
2. launching tube end cap as claimed in claim 1 breaks through pilot system, it is characterised in that the electromagnetism grabbing assembly includes
Magnechuck, motor, steel wire rope and pulley, the top that the magnechuck is arranged at piece, the pulley are arranged at electromagnetism
The top of sucker, the steel wire loop is located on pulley, and the motor is connected in one end of steel wire rope；The balance weight assembly
Including upper balancing weight, middle balancing weight and lower balancing weight.
3. launching tube end cap as claimed in claim 2 breaks through pilot system, it is characterised in that wear in the center of the magnechuck
Provided with insurance screw rod, the threaded one end exposed at the top of magnechuck of the insurance screw rod is connected with check screw.
4. launching tube end cap as claimed in claim 1 breaks through pilot system, it is characterised in that the clamping assembly includes hand
Runner, lifting screw, linking arm, clamping plate and safety screen, the safety screen are arranged at the both sides of linking arm, the connection
Arm is nested on the outside of lifting screw, and the coaxially connected top in lifting screw of hand runner, the clamping plate is arranged at company
Connect the end of arm；The buffer is fixedly arranged on workbench by bumper bracket.
5. launching tube end cap as claimed in claim 4 breaks through pilot system, it is characterised in that the surface of the clamping plate is also set
There is pinboard.
6. launching tube end cap as claimed in claim 4 breaks through pilot system, it is characterised in that the edge of the clamping plate is provided with
Positioning hole.
7. launching tube end cap as claimed in claim 6 breaks through pilot system, it is characterised in that the surface of the workbench is provided with
The locating dowel matched with the positioning hole.
8. launching tube end cap as claimed in claim 1 breaks through pilot system, it is characterised in that when the portion to be measured is antenna house
When, screw rod is provided between the lower balancing weight and middle balancing weight, the force cell is fixedly arranged in screw rod.
9. launching tube end cap as claimed in claim 1 breaks through pilot system, it is characterised in that when the portion to be measured is imitating shell
During head, the connecting rod for fixed-analog bullet is equipped with described lower piece, the connecting rod is connected with force cell.
10. the launching tube end cap described in a kind of utilization claim 1 breaks through the test method of pilot system, it is characterised in that bag
Include following steps：
Magnechuck, which is declined, makes magnechuck center through hole through insurance screw rod, and check screw is twisted with insurance screw flight
Tightly；
Antenna house or dummy warhead are connected on force cell；
Launching tube end cap is installed in clamping assembly, and makes launching tube end cap positioned at the underface of antenna house or dummy warhead；
Specified altitude assignment is promoted to by controlling motor by balance weight assembly, to meet experiment to antenna house tip or dummy warhead
Tip reach launching tube end cap break through at rate request；
Magnechuck is powered, and unclamps check screw；
Open velocity package switch, and dynamometric system switch；
Magnechuck is powered off, and discharges balance weight assembly, and balance weight assembly does freely falling body fortune under the guiding of slide block guide rail slide block assembly
Dynamic, antenna house tip or dummy warhead tip break through Dian Chu in launching tube end cap and break through launching tube end cap；
Balance weight assembly steadily stops after the cushioning effect of Buffer Unit；
Record data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710482012.6A CN107271298B (en) | 2017-06-22 | 2017-06-22 | Launch canister end cover burst test system and test method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710482012.6A CN107271298B (en) | 2017-06-22 | 2017-06-22 | Launch canister end cover burst test system and test method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107271298A true CN107271298A (en) | 2017-10-20 |
| CN107271298B CN107271298B (en) | 2020-04-07 |
Family
ID=60069417
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710482012.6A Active CN107271298B (en) | 2017-06-22 | 2017-06-22 | Launch canister end cover burst test system and test method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107271298B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110207540A (en) * | 2019-05-27 | 2019-09-06 | 西安昆仑工业（集团）有限责任公司 | A kind of smoke bomb discharger control circuit detection device and detection method |
| CN110319996A (en) * | 2019-08-20 | 2019-10-11 | 武汉市云竹机电新技术开发有限公司 | Novel free fall pilot system |
| CN111397865A (en) * | 2019-12-10 | 2020-07-10 | 北京航空航天大学 | Performance test platform for piston buffer device of launching tube |
| CN112683698A (en) * | 2020-12-21 | 2021-04-20 | 西安交通大学 | Tensile impact test stand with medium strain rate for material |
| CN113959655A (en) * | 2021-10-25 | 2022-01-21 | 上海机电工程研究所 | Performance test device and method for launching tube film front cover |
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| CN109104907B (en) * | 2007-04-28 | 2012-07-18 | 上海航天精密机械研究所 | The experimental rig of guided missile made of metal mantle buffer |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111397865A (en) * | 2019-12-10 | 2020-07-10 | 北京航空航天大学 | Performance test platform for piston buffer device of launching tube |
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| CN112683698A (en) * | 2020-12-21 | 2021-04-20 | 西安交通大学 | Tensile impact test stand with medium strain rate for material |
| CN113959655A (en) * | 2021-10-25 | 2022-01-21 | 上海机电工程研究所 | Performance test device and method for launching tube film front cover |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107271298B (en) | 2020-04-07 |
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