CN108905228A - A kind of electric retractable undercarriage of prototype aircraft - Google Patents
A kind of electric retractable undercarriage of prototype aircraft Download PDFInfo
- Publication number
- CN108905228A CN108905228A CN201810566072.0A CN201810566072A CN108905228A CN 108905228 A CN108905228 A CN 108905228A CN 201810566072 A CN201810566072 A CN 201810566072A CN 108905228 A CN108905228 A CN 108905228A
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- Prior art keywords
- wheel shaft
- shaft
- axis
- electric retractable
- undercarriage
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Classifications
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/14—Starting or launching devices for toy aircraft; Arrangements on toy aircraft for starting or launching
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- Vibration Dampers (AREA)
- Toys (AREA)
Abstract
This application provides a kind of electric retractable undercarriage of prototype aircraft, including：Wheel shaft；Wheel, the wheel are mounted on the right end of the wheel shaft；Elastic rod, the elastic rod inclination are connected between the undercarriage fork of fuselage and the wheel shaft；Flexible support bar, the flexible support bar inclination are connected between the elastic rod and the left end of the wheel shaft；Buffer, the buffer inclination are connected between the flexible support bar and the wheel shaft.Electric retractable undercarriage of prototype aircraft provided by the present application, the buffering when under the action of double elastic deformation of elastic rod and flexible support bar to realize landing, the impact force that the model of an airplane is subject to when effectively reducing landing, to protect the model of an airplane.
Description
Technical field
The present invention relates to a kind of electric retractable undercarriage of prototype aircraft, rise more particularly to a kind of model of an airplane electric retractable
Fall frame.
Background technique
The model of an airplane refers to a kind of toy that can be flown and can realize the control to aircraft by modes such as remote controls, with
The promotion of spiritual life level, requirement of the consumer to artificial model airplane it is higher and higher, it is desirable to the model of an airplane is either outer
Shape is still laid out will be true to nature as much as possible.
Publication CN200910041370.9 discloses a kind of electric retractable undercarriage of prototype aircraft, it is intended to Yi Zhongan
Fill electric retractable undercarriage of prototype aircraft simple, easy to use, safe.The present invention includes bracket, undercarriage fork, institute
It states and is equipped with wiring board, motor, gear set, drive bearing, drive screw, brake bar in bracket, the motor is electrically connected with wiring board
It connects, the input terminal of gear set described in the output axis connection of the motor, the one end of the drive screw and the drive bearing
It matches, and passes through the drive bearing and be connected with the output end of the gear set, the drive screw and the brake bar
Activity cooperation, the undercarriage fork are provided with mating groove, and the brake bar is adapted with the mating groove.But in use
It was found that the cushion performance of wheel assemblies is bad, the model of an airplane, vulnerable to impact, generates damage when landing.
It is those skilled in the art's urgent problem in conclusion how to improve the cushion performance of wheel assemblies.
Summary of the invention
The object of the present invention is to provide a kind of electric retractable undercarriage of prototype aircraft, solve the cushion performance of wheel assemblies
Bad, the model of an airplane, vulnerable to impact, leads to the problem of damage when landing.
In order to solve the above technical problems, the present invention provides the following technical solutions：A kind of electric retractable undercarriage of prototype aircraft,
Including：Wheel shaft；Wheel, the wheel are mounted on the right end of the wheel shaft；Elastic rod, the elastic rod inclination are connected to fuselage
Between undercarriage fork and the wheel shaft；Flexible support bar, the flexible support bar inclination are connected to the elastic rod and institute
It states between the left end of wheel shaft；Buffer, the buffer inclination are connected between the flexible support bar and the wheel shaft.
Further, the elastic rod has straight-bar portion, spire and upper connecting rod, and the lower end in the straight-bar portion is connected to
On the middle shaft part of the wheel shaft, the spire is connected to the upper end in the straight-bar portion, the axis of the spire and the wheel
The axis of axis is in the same plane, and the lower end of the upper connecting rod is connected to the right end of the spire, the upper connecting rod
Upper end be connected on the undercarriage fork.
Further, the included angle B between the axis of the spire and the axis of the wheel shaft is 12 °~16 °.
Further, the included angle B between the axis of the spire and the axis of the wheel shaft is 14 °.
Further, the angle H between the axis of the upper connecting rod and the axis in the straight-bar portion is 0 °~1.5 °.
Further, the spire has several spirals.
Further, the flexible support bar has cylindrical portion, upper plat part, bending part and lower plat part, the cylinder
The upper end in portion is articulated on the fixation bracket on straight-bar portion top of the elastic rod, and the upper plat part is connected to the cylindrical portion
Lower end, the bending part is connected to the lower end of the upper plat part, and the lower plat part is connected to the lower end of the bending part,
The lower end of the lower plat part has a bending section, and the bending section contradicts in the cavity of the left axle section of the wheel shaft.
Further, the buffer has connecting rod, and the left end of the connecting rod is equipped with bulb, the bulb activity setting
In the ball head of the upper right side of the bending section, the right end of the connecting rod is connected to the wheel shaft by elastic joint part
On the lug of middle shaft part.
Further, the elastic joint part has steel shaft, and the right end of the steel shaft, which has, inlays shaft part, described to inlay
There is elastomer, the right end of the connecting rod is set in right section of the locating shaft of the elastomer, a left side for the locating shaft on shaft part
Section is mounted in the inner hole of the lug.
Further, the bending part has several bendings, and the bending is V-shaped.
It can be seen from above-mentioned technical proposal the invention has the advantages that：Elastic rod the model of an airplane land by
Play the role of buffering to deformation is generated when impact, flexible support bar can produce deformation to be subject to when buffer model aircraft landing
Impact, the buffering when under the action of double elastic deformation of elastic rod and flexible support bar to realize landing effectively reduce
The impact force that the model of an airplane is subject to when land, so that the model of an airplane is protected, meanwhile, elastic rod and flexible support bar collective effect, phase
The impact force that the flexible support bar of elastic rod or independent role for independent role is born is smaller, effectively extends undercarriage
Service life；
Elastomer has elasticity, and when flexible support bar is generated deformation by impact and pulls buffer, elastomer generates shape
Become, the junction of buffer and wheel shaft is protected, reduces impact damage caused by buffer and wheel shaft connection place, make
Buffer linking together flexible support bar and wheel shaft elasticity, avoid when being impacted flexible support bar and wheel shaft it
Between generate damage, extend the service life of undercarriage.
The present invention is described in further detail with reference to the accompanying drawings and detailed description.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of invention for those of ordinary skill in the art without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
Fig. 1 is the structural diagram of the present invention.
Fig. 2 is partial structural diagram of the invention.
Fig. 3 is the structural schematic diagram of elastic rod of the invention.
Fig. 4 is another partial structural diagram of the invention.
Fig. 5 is another partial structural diagram of the invention.
Fig. 6 is the structural schematic diagram of elastic joint part of the invention.
Description of symbols：Elastic rod 10, straight-bar portion 11, spire 12, spiral 121, upper connecting rod 13, wheel shaft 20 are right
Shaft part 21, middle shaft part 22, lug 221, angling hole 222,223 left axle section 23 of fixing screws, cavity 231, wheel 30, flexible support
Bar 40, cylindrical portion 41, upper plat part 42, bending part 43, bending 431, lower plat part 44, bending section 45, ball head 46, ball-and-socket
461, buffer 50, connecting rod 51, bulb 52, elastic joint part 53, steel shaft 531 inlays shaft part 5311, annular protrusion 53111, spiral shell
Line shaft part 5312, elastomer 532, locating shaft 533, arc groove 5331, flange 5332, shoulder 534, fixed bracket 60, rubber
Pad 70, locking nut 80.
Specific embodiment
The embodiment of the present invention is described in detail below in conjunction with attached drawing, but the present invention can be defined by the claims
Implement with the multitude of different ways of covering.
The application is described further below with reference to Fig. 1 to Fig. 6, a kind of model of an airplane electric retractable as shown in Figure 1
Undercarriage, including：Elastic rod 10, wheel shaft 20, wheel 30, flexible support bar 40 and buffer 50, the inclination of elastic rod 10 are connected to
Between the undercarriage fork and wheel shaft 20 of fuselage, the work that buffering is played in deformation is generated when the model of an airplane lands and impacted
With, wheel 30 is mounted on the right end of wheel shaft 20, and the inclination of flexible support bar 40 is connected between elastic rod 10 and the left end of wheel shaft 20,
The impact that deformation be can produce to be subject to when buffer model aircraft landing, the inclination of buffer 50 are connected to flexible support bar 40 and wheel shaft
Between 20, plays buffering, landing is realized under the action of the double elastic deformation of elastic rod 10 and flexible support bar 40
When buffering, the impact force that the model of an airplane is subject to when effectively reducing landing, to protect the model of an airplane, meanwhile, 10 He of elastic rod
40 collective effect of flexible support bar is rushed relative to what the elastic rod 10 of independent role or the flexible support bar 40 of independent role undertook
It hits that power is smaller, effectively extends the service life of undercarriage.
In the present embodiment, as shown in Figure 1, Figure 2, Figure 3 shows, elastic rod 10 has straight-bar portion 11, spire 12 and upper connecting rod
13, the lower end in straight-bar portion 11 is connected on the middle shaft part 22 of wheel shaft 20, and spire 12 is connected to the upper end in straight-bar portion 11, spire
The axis of 12 axis and wheel shaft 20 is in the same plane, and the lower end of upper connecting rod 13 is connected to the right end of spire 12, on
The upper end of connecting rod 13 is connected on undercarriage fork, and spire 12 has several spirals 121, and elastic rod 10 is by spring steel
At can produce deformation when model of an airplane landing is impacted and achieve the effect that buffering.
Preferably, the included angle B between the axis of spire 12 and the axis of wheel shaft 20 is 12 °~16 °, in the present embodiment,
Included angle B between the axis of spire 12 and the axis of wheel shaft 20 is 14 °, so that the impact force that elastic rod 10 is received reduces, buffering
Better effect.
Preferably, the angle H between the axis of upper connecting rod 13 and the axis in straight-bar portion 11 is 0 °~1.5 °, so that upper company
The impact force that extension bar 13 is subject to straight-bar portion 11 is decomposed and is slowed down, and buffering effect is further increased.
In the present embodiment, as shown in Figure 1, Figure 2, Figure 5, wheel shaft 20 has right axis section 21, middle shaft part 22 and left axle section 23, right
Shaft part 21, middle shaft part 22 and left axle section 23 are sequentially connected from right to left, and wheel 30 is mounted on the right axis section 21 of wheel shaft 20, axis
Section 22 is equipped with angling hole 222, and the straight-bar portion 11 of elastic rod 10 protrudes into angling hole 222 and passes through fixing screws 223 will be elastic
Bar 10 is fixedly connected on wheel shaft 20, and the top of middle shaft part 22 is equipped with lug 221, and the top of left axle section 23 is equipped with cavity 231.
In the present embodiment, as shown in Figure 1, Figure 2, Figure 4 shows, flexible support bar 40 has cylindrical portion 41, upper plat part 42, bending
Portion 43 and lower plat part 44, flexible support bar 40 are made of spring steel, and the upper end of cylindrical portion 41, which is articulated in, is fixed on elastic rod 10
11 top of straight-bar portion fixation bracket 60 on, upper plat part 42 is connected to the lower end of cylindrical portion 41, and bending part 43 is connected to
The lower end of plat part 42, bending part 43 have several bendings 431, and bending 431 is V-shaped, and deformation is also easy to produce when being impacted,
Lower plat part 44 is connected to the lower end of bending part 43, and the lower end of lower plat part 44 has a bending section 45, and bending section 45 contradicts
In the cavity 231 of the left axle section 23 of wheel shaft 20, when flexible support bar 40 is squeezed impact, bending section 45 can produce deformation,
And sliding rotation is generated along the inner arc of cavity 231 in cavity 231, stress point is decomposed, impact force is decomposed, further increases buffering
Effect, the upper right side in bending section 45 are equipped with ball head 46, and the inside of ball head 46 is equipped with ball-and-socket 461.
In the present embodiment, as Figure 1 and Figure 4, rubber pad 70 is equipped in the cavity 231 of left axle section 23, bending section 45 is supported
Touching plays the role of protection buffering on rubber pad 70, and the bending section 45 of flexible support bar 40 and wheel shaft 20 is avoided to generate collision
Damage, extends the service life of undercarriage.
In the present embodiment, as shown in Figure 1, shown in Figure 5, buffer 50 has connecting rod 51, and the left end of connecting rod 51 is equipped with bulb 52, ball
First 52 are movably arranged in the ball-and-socket 461 of the ball head 46 of the upper right side of bending section 45 and bulb 52 will not be from ball head
It is detached from 46, rotation riveting usually is carried out to the edge of ball head 46, so that bulb 52 is securely contained in ball-and-socket 461, connecting rod
On the lug 221 for the middle shaft part 22 that 51 right end is connected to wheel shaft 20 by elastic joint part 53, buffer 50 is by flexible support
Bar 40 is connected on wheel shaft 20, plays buffering.
In the present embodiment, as shown in Fig. 1, Fig. 5, Fig. 6, elastic joint part 53 has steel shaft 531, and the right end of steel shaft 531 has
Have and inlay shaft part 5311, inlaying has elastomer 532 on shaft part 5311, elastomer 532 has locating shaft 533 and shoulder 534, shoulder
The right end of locating shaft 533 is arranged in portion 534, and locating shaft 533, which is set in, to be inlayed on shaft part 5311, and the right end of connecting rod 51 is set in bullet
Right section of the locating shaft 533 of property body 532, the right end of connecting rod 51 is kept out on the left side of shoulder 534, and left section of locating shaft 533
It is mounted in the inner hole of lug 221, the left end of steel shaft 531 has threaded shaft section 5312, is equipped with locking on threaded shaft section 5312
Nut 80, the right side of locking nut 80 are kept out on lug 221, elastomer 532 have elasticity, flexible support bar 40 by
When impact generates deformation pulling buffer 50, elastomer 532 generates deformation, protects to buffer 50 and the junction of wheel shaft 20
Shield reduces impact damage caused by buffer 50 and 20 junction of wheel shaft so that buffer 50 by flexible support bar 40 with
Linking together for 20 elasticity of wheel shaft, avoids and generates collsion damage between flexible support bar 40 and wheel shaft 20 when being impacted,
Extend the service life of undercarriage.
In the present embodiment, as shown in Fig. 1, Fig. 5, Fig. 6, inlays and be in axial direction equipped with several convex annulars on shaft part 5311
53111 are played, several annular protrusions 53111 are embedded on the inner surface of locating shaft 533, are effectively prevented elastomer 532 from edge
It falls off on embedding shaft part 5311, several arc grooves 5331, two neighboring arc is in axial direction equipped on the periphery of locating shaft 533
Several flanges 5332 are equipped with along circumferential direction on the outer surface of locating shaft 533 between connected in star 5331, flange 5332 has
Preferable elasticity, improves the buffering effect of elastomer 532.
Above composite structure, so that buffering effect of the invention is best, so that the model of an airplane was subject to when landing
Impact force is smaller, to protect the model of an airplane.
These are only the preferred embodiment of the present invention, is not intended to restrict the invention, for those skilled in the art
For member, the invention may be variously modified and varied.All within the spirits and principles of the present invention, it is made it is any modification,
Equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of electric retractable undercarriage of prototype aircraft, which is characterized in that including：
Wheel shaft (20)；
Wheel (30), the wheel (30) are mounted on the right end of the wheel shaft (20)；
Elastic rod (10), elastic rod (10) inclination are connected between the undercarriage fork of fuselage and the wheel shaft (20)；
Flexible support bar (40), flexible support bar (40) inclination are connected to the elastic rod (10) and the wheel shaft (20)
Between left end；
Buffer (50), buffer (50) inclination are connected between the flexible support bar (40) and the wheel shaft (20).
2. electric retractable undercarriage of prototype aircraft according to claim 1, which is characterized in that the elastic rod (10) has
The lower end of straight-bar portion (11), spire (12) and upper connecting rod (13), the straight-bar portion (11) is connected to the wheel shaft (20)
On middle shaft part (22), the spire (12) is connected to the upper end of the straight-bar portion (11), the axis of the spire (12) with
The axis of the wheel shaft (20) is in the same plane, and the lower end of the upper connecting rod (13) is connected to the spire (12)
The upper end of right end, the upper connecting rod (13) is connected on the undercarriage fork.
3. electric retractable undercarriage of prototype aircraft according to claim 2, which is characterized in that the axis of the spire (12)
Included angle B between line and the axis of the wheel shaft (20) is 12 °~16 °.
4. electric retractable undercarriage of prototype aircraft according to claim 3, which is characterized in that the axis of the spire (12)
Included angle B between line and the axis of the wheel shaft (20) is 14 °.
5. electric retractable undercarriage of prototype aircraft according to claim 2, which is characterized in that the upper connecting rod (13)
Angle H between axis and the axis in the straight-bar portion (11) is 0 °~1.5 °.
6. electric retractable undercarriage of prototype aircraft according to claim 2, which is characterized in that the spire (12) has
Several spirals (121).
7. electric retractable undercarriage of prototype aircraft according to claim 1, which is characterized in that the flexible support bar (40)
With cylindrical portion (41), upper plat part (42), bending part (43) and lower plat part (44), the upper end of the cylindrical portion (41) is pivotally connected
On the fixation bracket (60) on straight-bar portion (11) top of the elastic rod (10), the upper plat part (42) is connected to the circle
The lower end in column portion (41), the bending part (43) are connected to the lower end of the upper plat part (42), and the lower plat part (44) is even
The lower end in the bending part (43) is connect, the lower end of the lower plat part (44) has a bending section (45), the bending section
(45) it contradicts in the cavity (231) of the left axle section (23) of the wheel shaft (20).
8. electric retractable undercarriage of prototype aircraft according to claim 7, which is characterized in that the buffer (50) has
The left end of connecting rod (51), the connecting rod (51) is equipped with bulb (52), and the bulb (52) is movably arranged on the bending section (45)
Upper right side ball head (46) in, the right end of the connecting rod (51) is connected to the wheel shaft by elastic joint part (53)
(20) on the lug (221) of middle shaft part (22).
9. electric retractable undercarriage of prototype aircraft according to claim 8, which is characterized in that the elastic joint part (53)
With steel shaft (531), the right end of the steel shaft (531), which has, to be inlayed shaft part (5311), and described inlay has on shaft part (5311)
Elastomer (532), the right end of the connecting rod (51) is set in right section of the locating shaft (533) of the elastomer (532), described fixed
Left section of position axis (533) is mounted in the inner hole of the lug (221).
10. electric retractable undercarriage of prototype aircraft according to claim 7, which is characterized in that bending part (43) tool
There are several bendings (431), the bending (431) is V-shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810566072.0A CN108905228B (en) | 2018-06-04 | 2018-06-04 | Electric retractable landing gear of model airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810566072.0A CN108905228B (en) | 2018-06-04 | 2018-06-04 | Electric retractable landing gear of model airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108905228A true CN108905228A (en) | 2018-11-30 |
| CN108905228B CN108905228B (en) | 2020-06-09 |
Family
ID=64410779
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810566072.0A Active CN108905228B (en) | 2018-06-04 | 2018-06-04 | Electric retractable landing gear of model airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108905228B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024109328A1 (en) * | 2022-11-25 | 2024-05-30 | 峰飞航空科技(昆山)有限公司 | Linkage assembly, steering gear buffer structure, and aircraft |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1890950U (en) * | 1964-01-24 | 1964-04-09 | Wilfried Klinger | UNDERCARRIAGE FOR FLIGHT MODELS. |
| US3739519A (en) * | 1971-12-02 | 1973-06-19 | Rom Air Int Inc | Pressure operated retractable landing gear |
| EP0072720B1 (en) * | 1981-08-12 | 1986-11-26 | Messier-Hispano-Bugatti (S.A) | Aircraft landing gear |
| CN2408005Y (en) * | 2000-01-03 | 2000-11-29 | 环玮企业股份有限公司 | Three wheel hand push cart with spring buffer function |
| CN201086822Y (en) * | 2007-08-03 | 2008-07-16 | 西安大地测绘工程有限责任公司 | Rear kneeing type damping device for undercarriage of pilotless plane |
| CN101637658A (en) * | 2009-07-24 | 2010-02-03 | 珠海海曼电子模型有限公司 | Electric retractable undercarriage of prototype aircraft |
| CN102020014A (en) * | 2010-12-09 | 2011-04-20 | 南京航空航天大学 | Airplane landing gear with deflected airplane wheel retraction jack |
| CN202320638U (en) * | 2011-10-31 | 2012-07-11 | 沙比提·白克热 | Front-back-exchangeable bicycle |
| CN204093040U (en) * | 2014-09-17 | 2015-01-14 | 安徽工程大学 | A kind of operation of landing gear and there are its model plane |
| CN204674823U (en) * | 2015-04-30 | 2015-09-30 | 湖北猎隼智能科技有限公司 | A kind of two-stage buffering automatic deploying and retracting alighting gear |
-
2018
- 2018-06-04 CN CN201810566072.0A patent/CN108905228B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1890950U (en) * | 1964-01-24 | 1964-04-09 | Wilfried Klinger | UNDERCARRIAGE FOR FLIGHT MODELS. |
| US3739519A (en) * | 1971-12-02 | 1973-06-19 | Rom Air Int Inc | Pressure operated retractable landing gear |
| EP0072720B1 (en) * | 1981-08-12 | 1986-11-26 | Messier-Hispano-Bugatti (S.A) | Aircraft landing gear |
| CN2408005Y (en) * | 2000-01-03 | 2000-11-29 | 环玮企业股份有限公司 | Three wheel hand push cart with spring buffer function |
| CN201086822Y (en) * | 2007-08-03 | 2008-07-16 | 西安大地测绘工程有限责任公司 | Rear kneeing type damping device for undercarriage of pilotless plane |
| CN101637658A (en) * | 2009-07-24 | 2010-02-03 | 珠海海曼电子模型有限公司 | Electric retractable undercarriage of prototype aircraft |
| CN102020014A (en) * | 2010-12-09 | 2011-04-20 | 南京航空航天大学 | Airplane landing gear with deflected airplane wheel retraction jack |
| CN202320638U (en) * | 2011-10-31 | 2012-07-11 | 沙比提·白克热 | Front-back-exchangeable bicycle |
| CN204093040U (en) * | 2014-09-17 | 2015-01-14 | 安徽工程大学 | A kind of operation of landing gear and there are its model plane |
| CN204674823U (en) * | 2015-04-30 | 2015-09-30 | 湖北猎隼智能科技有限公司 | A kind of two-stage buffering automatic deploying and retracting alighting gear |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024109328A1 (en) * | 2022-11-25 | 2024-05-30 | 峰飞航空科技(昆山)有限公司 | Linkage assembly, steering gear buffer structure, and aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108905228B (en) | 2020-06-09 |
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