CN108791849B - Unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle Download PDFInfo
- Publication number
- CN108791849B CN108791849B CN201810617638.8A CN201810617638A CN108791849B CN 108791849 B CN108791849 B CN 108791849B CN 201810617638 A CN201810617638 A CN 201810617638A CN 108791849 B CN108791849 B CN 108791849B
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- aerial vehicle
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- aircraft
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- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000012856 packing Methods 0.000 claims 1
- 238000000034 method Methods 0.000 description 11
- 210000002414 leg Anatomy 0.000 description 9
- 239000003550 marker Substances 0.000 description 9
- 230000008569 process Effects 0.000 description 9
- 230000006378 damage Effects 0.000 description 6
- 238000012423 maintenance Methods 0.000 description 5
- 230000003139 buffering effect Effects 0.000 description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 230000000007 visual effect Effects 0.000 description 3
- 208000027418 Wounds and injury Diseases 0.000 description 2
- 230000004913 activation Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/54—Floats
- B64C25/56—Floats inflatable
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
- B64D47/06—Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Traffic Control Systems (AREA)
Abstract
The invention discloses an unmanned aerial vehicle, wherein one ends of a plurality of three-dimensional rings are sequentially connected to the tail ends of flight wings, the other ends of the three-dimensional rings bypass flight paddles, form an arc shape protruding outwards and then converge at the same connection point, and the connection point is on the central axis of an aircraft main body. The one end of a plurality of solid rings is connected gradually at the flight wing end, and the other end all walks around the flight oar and upwards gathers in same tie point after forming outside outstanding arc, and the tie point is on the central axis of aircraft main part to, the tie point is connected to the aircraft main part through the telescopic link of vertical setting so that the telescopic link can adjust the distance between tie point and the aircraft main part. The unmanned aerial vehicle is high in flight stability, high in safety performance and long in service life.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle.
Background
Along with more and more unmanned aerial vehicles, model aeroplane and model ship, the aircraft of taking photo by plane is applied to civilian field, and owing to function and the continuous increase of lift limit journey, unmanned vehicles's self weight and volume also are continuously increasing, and this kind of unmanned vehicles' undercarriage has been difficult to bear such weight, leads to at the in-process that descends after the flight, appears the undercarriage and breaks and decreases and then make the damage of aircraft structure and outward appearance appear.
The existing unmanned aerial vehicle is provided with a plurality of flight wings, and after one flight wing is slightly deformed, the aircraft loses balance in the flight process and is easy to crash; and the fragile position of the unmanned aerial vehicle after the crash collides with the hard ground, so that the unmanned aerial vehicle is easy to crack and damage, the unmanned aerial vehicle cannot be used, and the maintenance cost is increased. Meanwhile, the unmanned aerial vehicle has low flight safety at night or in an environment with poor light conditions, and is inconvenient for naked eye positioning. Once the unmanned aerial vehicle has an accidental crash in the flying process and falls into a complicated terrain area, the unmanned aerial vehicle is difficult to find and rescue in time by only visual observation.
Therefore, it is urgently needed to provide an unmanned aerial vehicle with high flight stability, high safety performance and long service life.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle which is high in flight stability, high in safety performance and long in service life.
In order to achieve the above object, the present invention provides an unmanned aerial vehicle comprising an aircraft body for storing transportation goods, flight wings, a connection ring and a three-dimensional ring;
one end of the flying wing is fixedly connected to the outer side wall of the aircraft main body, and the other end of the flying wing extends outwards along the radial direction of the aircraft main body; the number of the flight wings is at least three, and the flight wings are uniformly arranged at intervals along the circumferential direction of the aircraft main body;
the diameters of the flight wings are gradually reduced from inside to outside, the tail ends of the flight wings are provided with flight paddles, the connecting rings are sequentially connected with the tail ends of the flight wings along the circumferential direction, and the connecting rings are concentric with the aircraft main body;
one end of each of the three-dimensional rings is sequentially connected to the tail end of the flying wing, the other end of each of the three-dimensional rings bypasses the flying paddle and upwards forms an arc protruding outwards and then gathers at the same connecting point, the connecting point is arranged on the central axis of the aircraft main body, and the connecting points are connected to the aircraft main body through vertically arranged telescopic rods so that the telescopic rods can adjust the distance between the connecting points and the aircraft main body;
a plurality of outline marker lamps are arranged on the connecting ring and the solid ring at intervals, and the outline marker lamps are also connected with a light sensor;
the unmanned aerial vehicle also comprises at least three supporting legs, the supporting legs are uniformly arranged on the bottom end surface of the main body of the unmanned aerial vehicle at intervals along the circumferential direction, and the supporting legs are mutually connected to form an annular inflatable air cushion; wherein the content of the first and second substances,
be formed with on the lateral wall of aircraft main part and accomodate the chamber, inside is filled with signal bullet or smog bullet to, accomodate the chamber and seal through sealed lid.
Preferably, the connection ring and the space ring are both made of elastic plastic or rubber.
Preferably, the connection between the connection ring and the flight wing is a detachable connection.
Preferably, detachable connection is threaded connection, all is equipped with the internal thread hole on go-between and the flight wing, passes the internal thread hole in proper order through the bolt and can be with go-between rigid coupling to the flight wing.
Preferably, the connection between the three-dimensional ring and the flight wing is a detachable connection.
Preferably, the detachable connection is a threaded connection or a snap connection.
Preferably, the flight paddles are double or triple-bladed paddles.
According to the technical scheme, one end of each flying wing is fixedly connected to the outer side wall of the aircraft body, and the other ends of the flying wings are connected together through the connecting rings, so that the flying wings can always keep original positions through the dragging force of the connecting rings, original included angles are maintained among the flying wings, and the whole aircraft can always keep balance and stably fly in the flying process. Meanwhile, one ends of the three-dimensional rings are sequentially connected to the tail end of the flying wing, the other ends of the three-dimensional rings bypass the flying paddle and upwards form an outwards protruding arc shape to be gathered at the same connecting point, and the connecting point is arranged on the central axis of the aircraft main body. Like this, even the unexpected crash takes place among the flight process, it is that a plurality of solid rings at first collide with ground when unmanned vehicles falls to the ground, because solid ring has certain elasticity, can play fine buffering effect, can also effectively prevent the secondary injury that the secondary bounced back whereabouts through rolling after falling to the ground, guarantee the integrality of each part, the security performance is high, and long service life has practiced thrift the maintenance cost.
The connecting point is also connected to the aircraft main body through a vertically arranged telescopic rod so that the telescopic rod can adjust the distance between the connecting point and the aircraft main body; and the bending and arching degree of the peripheral three-dimensional ring can be changed by adjusting the distance between the connecting point and the aircraft main body, so that the three-dimensional ring has different elasticity, and the elasticity of the three-dimensional ring when the three-dimensional ring collides with the ground is kept, so that the buffering effect of the three-dimensional ring is ensured.
A plurality of outline marker lamps are arranged on the connecting ring and the solid ring at intervals, and the outline marker lamps are further connected with light sensors. Like this, when the night curtain arrives or uses unmanned vehicles under the dim environment of light, light sensor response triggers behind the light and shows the clearance lamp and open and shine for unmanned vehicles still can take off smoothly and instruct the flight region according to showing the clearance lamp in this kind of environment, can also confirm the profile of this aircraft and in time dodge in the dark surrounds, reduces unexpected striking and brings the machine damage, prolongs its life.
When the aircraft lands to the uneven landing of height, in order to avoid aircraft main part, flight wing bottom and ground to take place to collide with, the life of extension aircraft, preferably, unmanned vehicles still includes three at least supporting legss, and the supporting legss set up on the bottom face of aircraft main part along the even interval of circumference direction. Meanwhile, the supporting legs are connected with each other to form an annular inflatable air cushion, the air cushion can be inflated by using the remote control air valve in the actual use process, and the inflated inflatable air cushion is expanded to generate larger buoyancy in water to support the whole aircraft to take off or land under emergency on the water surface, so that the logistics goods are still normally transported in a special terrain environment, the logistics goods arrive on time, and the safety of the logistics goods is greatly improved.
The aircraft is easily influenced by wind or rain during the flight process to crash accidentally, and once the aircraft reaches a complicated terrain area, the aircraft is not exposed on the surface of the earth and is difficult to position and rescue only through visual observation; therefore, a storage cavity is formed on the side wall of the aircraft body, the inside of the storage cavity is filled with a signal bomb or a smoke bomb, and the storage cavity is sealed by a sealing cover. Like this, in case when unmanned aerial vehicle air crash needs the succour, can remote control or automatic activation signal bullet send out signal, smog bullet and send out the smog that the great amount has the colour to this reminds the concrete position that the rescuer aircraft was located, saves search and rescue time, accelerates the rescue speed.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention.
Description of the reference numerals
1-aircraft body 2-flight wing
3-connecting ring and 4-stereo ring
5-flight oar 6-supporting foot
7-inflatable air cushion 8-outline marker lamp
9-telescopic rod 10-containing cavity
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present invention, are given by way of illustration and explanation only, not limitation.
In the present invention, unless otherwise specified, the directional words "top end, bottom end", etc., contained in a term, merely represent the orientation of the term in a normal use state, or are colloquially known by those skilled in the art, and should not be construed as limiting the term.
Referring to fig. 1, the present invention provides an unmanned aerial vehicle, including an aircraft body 1 for storing transportation goods, flying wings 2, a connection ring 3, and a three-dimensional ring 4;
one end of the flying wing 2 is fixedly connected to the outer side wall of the aircraft body 1, and the other end of the flying wing extends outwards along the radial direction of the aircraft body 1; the number of the flight wings 2 is at least three and the flight wings are uniformly arranged at intervals along the circumferential direction of the aircraft body 1;
the diameters of the flying wings 2 are gradually reduced from inside to outside, the tail ends of the flying wings are provided with flying paddles 5, the connecting rings 3 are sequentially connected with the tail ends of the flying wings 2 along the circumferential direction, and the connecting rings 3 are concentric with the aircraft body 1;
one end of each of the plurality of three-dimensional rings 4 is sequentially connected to the tail end of the flying wing 2, the other end of each of the plurality of three-dimensional rings 4 bypasses the flying paddle 5 and upwards forms an arc protruding outwards and then gathers at the same connecting point, the connecting point is arranged on the central axis of the aircraft body 1, and the connecting point is connected to the aircraft body 1 through a vertically arranged telescopic rod 9 so that the telescopic rod 9 can adjust the distance between the connecting point and the aircraft body 1;
a plurality of outline marker lamps 8 are arranged on the connecting ring 3 and the three-dimensional ring 4 at intervals, and the outline marker lamps 8 are also connected with light sensors;
the unmanned aerial vehicle also comprises at least three supporting feet 6, the supporting feet 6 are uniformly arranged on the bottom end surface of the main body 1 of the unmanned aerial vehicle at intervals along the circumferential direction, and the supporting feet 6 are mutually connected to form an annular inflatable air cushion 7; wherein the content of the first and second substances,
be formed with on the lateral wall of aircraft body 1 and accomodate chamber 10, inside is filled with signal bullet or smog bullet to, accomodate chamber 10 and seal through sealed lid.
Through the technical scheme, the one end rigid coupling of wing 2 will fly is on the lateral wall of aircraft main part 1, utilizes go-between 3 to link together a plurality of other ends of flying wing 2, can make a plurality of flying wing 2 remain original position all the time through the power of dragging of go-between 3 like this, maintains original contained angle each other for whole aircraft can remain balanced, stable flight all the time at the flight in-process. Meanwhile, one ends of the plurality of three-dimensional rings 4 are sequentially connected to the tail end of the flying wing 2, the other ends of the three-dimensional rings bypass the flying oar 5, form an arc protruding outwards and then gather at the same connection point, and the connection point is on the central axis of the aircraft body 1. Like this, even the unexpected crash takes place among the flight process, it is that a plurality of stereo rings 4 at first collide with ground when unmanned vehicles falls to the ground, because stereo ring 4 has certain elasticity, can play fine buffering effect, can also effectively prevent the secondary injury that the secondary bounced back whereabouts through rolling after falling to the ground, guarantee the integrality of each part, the security performance is high, and long service life has practiced thrift the maintenance cost.
The connection point is also connected to the aircraft body 1 by a vertically arranged telescopic rod 9 so that the telescopic rod 9 can adjust the distance between the connection point and the aircraft body 1; and the bending and arching degree of the peripheral three-dimensional rings 4 can be changed by adjusting the distance between the connecting point and the aircraft body 1, so that the three-dimensional rings 4 have different elasticity, and the elasticity of the three-dimensional rings in the collision with the ground is kept, so that the buffering effect of the three-dimensional rings is ensured.
A plurality of outline marker lamps 8 are arranged on the connecting ring 3 and the three-dimensional ring 4 at intervals, and the outline marker lamps 8 are further connected with light sensors. Like this, when the night curtain arrives or uses unmanned vehicles under the dim environment of light, light sensor response triggers behind the light and shows the clearance lamp and open and shine for unmanned vehicles still can take off smoothly and instruct the flight region according to showing the clearance lamp in this kind of environment, can also confirm the profile of this aircraft and in time dodge in the dark surrounds, reduces unexpected striking and brings the machine damage, prolongs its life.
When the aircraft lands to the uneven landing of height, in order to avoid aircraft main part 1, 2 bottoms of flight wing to collide with ground, prolong the life of aircraft, preferably, unmanned vehicles still includes three piece at least supporting legss 6, and supporting legss 6 sets up on the bottom face of aircraft main part 1 along the even interval of circumference direction. Meanwhile, the supporting legs 6 are connected with each other to form an annular inflatable air cushion 7, the inflatable air cushion 7 can be inflated by using a remote control air valve in the actual use process, and the inflated inflatable air cushion 7 is bulged to generate large buoyancy in water to support the whole aircraft to take off or land under emergency conditions on the water surface, so that logistics goods are still normally transported in special terrain environments, logistics goods arrive on time, and the safety of the logistics goods is greatly improved.
The aircraft is easily influenced by wind or rain during the flight process to crash accidentally, and once the aircraft reaches a complicated terrain area, the aircraft is not exposed on the surface of the earth and is difficult to position and rescue only through visual observation; therefore, a housing chamber 10 is formed on the side wall of the aircraft body, the inside is filled with a signal bomb or a smoke bomb, and the housing chamber 10 is sealed by a sealing cover. Like this, in case when unmanned aerial vehicle air crash needs the succour, can remote control or automatic activation signal bullet send out signal, smog bullet and send out the smog that the great amount has the colour to this reminds the concrete position that the rescuer aircraft was located, saves search and rescue time, accelerates the rescue speed.
When the unmanned aerial vehicle lands, once the unmanned aerial vehicle lands, the unstable aircraft is out of balance or the ground is uneven, the aircraft is prone to being inclined, the connecting ring 3 or the three-dimensional ring 4 is in contact with the ground and is scratched or even damaged, the service life of the connecting ring 3 or the three-dimensional ring 4 is greatly shortened, and in order to avoid the situation, the connecting ring 3 and the three-dimensional ring 4 are preferably made of elastic plastics or rubber.
In the present embodiment, in order to facilitate the detachment and installation of the connection ring 3 for maintenance of the aircraft body 1, it is preferable that the connection between the connection ring 3 and the flying wing 2 is a detachable connection.
The detachable connection mode can be any one of the quick and convenient connection modes which are common in the field, but from the viewpoint of controlling the product cost and reducing the overall weight of the aircraft, the detachable connection mode is preferably a threaded connection mode, both the connection ring 3 and the flight wings 2 are provided with internal threaded holes, and the connection ring 3 can be fixedly connected to the flight wings 2 by sequentially penetrating through the internal threaded holes through bolts.
Likewise, in order to facilitate the disassembly and assembly of the stereo ring 4 for the maintenance of the aircraft body 1, the connection between the stereo ring 4 and the flight wings 2 is preferably a detachable connection.
The detachable connection may be any quick and convenient connection commonly used in the art, but preferably is a threaded or snap connection in view of controlling product cost and reducing overall weight of the aircraft.
Further, in order to obtain a smooth updraft when the flight paddles 5 rotate at a high speed, and to maintain the stability of the aircraft, it is preferable that the flight paddles 5 are double-bladed paddles or triple-bladed paddles.
The preferred embodiments of the present invention have been described in detail with reference to the accompanying drawings, however, the present invention is not limited to the specific details of the above embodiments, and various simple modifications can be made to the technical solution of the present invention within the technical idea of the present invention, and these simple modifications are within the protective scope of the present invention.
It should be noted that the various technical features described in the above embodiments can be combined in any suitable manner without contradiction, and the invention is not described in any way for the possible combinations in order to avoid unnecessary repetition.
In addition, any combination of the various embodiments of the present invention is also possible, and the same should be considered as the disclosure of the present invention as long as it does not depart from the spirit of the present invention.
Claims (7)
1. An unmanned aerial vehicle is characterized by comprising an aircraft body (1) for storing and transporting goods, flying wings (2), a connecting ring (3) and a three-dimensional ring (4);
one end of the flying wing (2) is fixedly connected to the outer side wall of the aircraft body (1), and the other end of the flying wing extends outwards along the radial direction of the aircraft body (1); the number of the flight wings (2) is at least three, and the flight wings are uniformly arranged at intervals along the circumferential direction of the aircraft main body (1);
the diameter of each flying wing (2) is gradually reduced from inside to outside, the tail end of each flying wing (2) is provided with a flying paddle (5), the connecting ring (3) is sequentially connected with the tail end of each flying wing (2) along the circumferential direction, and the connecting ring (3) is concentric with the aircraft main body (1);
one end of each of the three-dimensional rings (4) is sequentially connected to the tail end of the flying wing (2), the other end of each of the three-dimensional rings bypasses the flying oar (5) and upwards forms an arc protruding outwards to be gathered at the same connecting point, the connecting point is arranged on the central axis of the aircraft body (1), and the connecting point is connected to the aircraft body (1) through a vertically arranged telescopic rod (9) so that the telescopic rod (9) can adjust the distance between the connecting point and the aircraft body (1);
a plurality of clearance lamps (8) are arranged on the connecting ring (3) and the solid ring (4) at intervals, and the clearance lamps (8) are also connected with a light sensor;
the unmanned aerial vehicle also comprises at least three supporting feet (6), the supporting feet (6) are uniformly arranged on the bottom end surface of the main body (1) of the unmanned aerial vehicle at intervals along the circumferential direction, and the supporting feet (6) are mutually connected to form an annular inflatable air cushion (7); wherein the content of the first and second substances,
be formed with on the lateral wall of aircraft main part (1) and accomodate chamber (10), inside packing has signal bullet or smog bullet, and, accomodate chamber (10) and seal through sealed lid.
2. The unmanned aerial vehicle of claim 1, wherein the connection ring (3) and the solid ring (4) are both made of elastic plastic or rubber.
3. The unmanned aerial vehicle of claim 1, wherein the connection between the connection ring (3) and the flight wing (2) is a detachable connection.
4. The unmanned aerial vehicle of claim 3, wherein the detachable connection is a threaded connection, the connection ring (3) and the flying wing (2) are both provided with internal threaded holes, and the connection ring (3) can be fixedly connected to the flying wing (2) through bolts sequentially penetrating through the internal threaded holes.
5. The unmanned aerial vehicle of claim 3, wherein the connection between the three-dimensional ring (4) and the flying wing (2) is a detachable connection.
6. The UAV according to claim 5 wherein the detachable connection is a threaded connection or a snap connection.
7. The unmanned aerial vehicle of claim 1, wherein the flight paddles (5) are double-bladed paddles or triple-bladed paddles.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810617638.8A CN108791849B (en) | 2018-06-15 | 2018-06-15 | Unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810617638.8A CN108791849B (en) | 2018-06-15 | 2018-06-15 | Unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108791849A CN108791849A (en) | 2018-11-13 |
| CN108791849B true CN108791849B (en) | 2020-07-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810617638.8A Expired - Fee Related CN108791849B (en) | 2018-06-15 | 2018-06-15 | Unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN108791849B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109459355A (en) * | 2018-12-11 | 2019-03-12 | 江西众安职业危害评价检测有限公司 | Long-range dust test device |
| CN110211357B (en) * | 2019-06-03 | 2020-04-28 | 淮南师范学院 | Robot wireless communication system based on Corba middleware technology and Ad hoc network |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104097772B (en) * | 2014-06-13 | 2016-06-15 | 芜湖特源鑫复合材料科技有限公司 | A kind of smog tracing type aircraft |
| CN104590554B (en) * | 2015-01-05 | 2017-02-22 | 张晶 | Path-finding lighting equipment |
| CN206750130U (en) * | 2017-05-10 | 2017-12-15 | 深圳市亿联智能有限公司 | A kind of wireless security protection monitoring device for patrol of flying |
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| CN108791849A (en) | 2018-11-13 |
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