CN108974350A - Rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan - Google Patents
Rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan Download PDFInfo
- Publication number
- CN108974350A CN108974350A CN201810546112.5A CN201810546112A CN108974350A CN 108974350 A CN108974350 A CN 108974350A CN 201810546112 A CN201810546112 A CN 201810546112A CN 108974350 A CN108974350 A CN 108974350A
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- China
- Prior art keywords
- wing
- ducted fan
- compound auxiliary
- compound
- airfreighter
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- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
Abstract
The present invention is a kind of rear single ducted fan formula composite wing airfreighter of compound auxiliary wing of double ducted fans, and the rear list compound rotor aircraft of ducted fan formula includes body, is fixedly mounted on body two sides hybrid lift wing, screw propeller；Wherein, body is set as deck platform；Self-enclosed ducted fan built in hybrid lift wing, the outside design of hybrid lift wing have wing hinge；Self-enclosed ducted fan is provided in the compound auxiliary wing of ducted fan thrust self energizing, the one or both sides of the compound auxiliary wing of ducted fan thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and be flexibly connected by wing hinge with hybrid lift wing, shipping storehouse is mounted on the lower section of body.The present invention not only has landing apart from short, flying speed is fast, wing structure intensity is high, wing can with energy storage, flight low energy consumption, the hang time is long the features such as, the hybrid lift wing of large area, it can play the role of aerodone under case of emergency, greatly improve the safety of aircraft, the safety of support personnel and goods and materials.
Description
Technical field
The present invention relates to a kind of aircraft, rear single ducted fan formula of specifically a kind of double compound auxiliary wings of ducted fan is compound
Wing airfreighter belongs to aircraft equipment technology field.
Background technique
Existing aircraft is broadly divided into fixed-wing and vertically taking off and landing flyer (such as helicopter and more rotors) two major classes.When
So also there is this product of VTOL fixed-wing.Traditional fixed-wing have the advantages that flying speed is fast, low energy consumption, but have
It is not connected to before and after main wing and tailplane, wing structure intensity is not high, is easily damaged, and landing requires high, landing distance disadvantage；
Traditional vertically taking off and landing flyer has the advantages that landing is convenient, but has that energy consumption is high, safety coefficient is low, and load capacity is poor, water
Flat flying speed is slow, is easy the disadvantages of air crash；Although current VTOL fixed-wing has the characteristics that landing is convenient, but in water
Controllability when flat flight is not satisfactory, and that there is flight resistances is big, energy consumption is high, blade is easy to hurt sb.'s feelings, be easy on the outside of blade
It damages, the disadvantages of safety coefficient is not still high.
Summary of the invention
In view of the above-mentioned problems of the prior art, the present invention not only has landing apart from short, flying speed is fast, wing knot
Structure intensity height, wing can be with energy storage, the features such as low energy consumption, the hang time is long of flying, the hybrid lift wing of large area, feelings of meeting an urgent need
It can play the role of aerodone under condition, greatly improve the safety of aircraft, the safety of support personnel and goods and materials.Ducted fan
More can be well protected propelling screws, at the same also ensured personnel up and down aircraft when safety, and improve propeller
Efficiency.
To achieve the goals above, rear single ducted fan formula composite wing goods of a kind of double compound auxiliary wings of ducted fan of the present invention
Aircraft is transported, it is compound by the compound rotor aircraft of rear single ducted fan formula, the ducted fan thrust self energizing for being assemblied in its wing two sides
The auxiliary wing and shipping storehouse composition；Wherein, rear single compound rotor aircraft of ducted fan formula includes body, is fixedly mounted on body
Two sides hybrid lift wing, propeller；Wherein, body is set as deck platform；Self-enclosed duct wind built in hybrid lift wing
Fan, the outside design of hybrid lift wing have wing hinge；Propeller is ducted fan propeller；Ducted fan thrust self energizing is multiple
The front end for closing the auxiliary wing is provided with ducted fan propeller, and being internally provided with for the compound auxiliary wing of ducted fan thrust self energizing is self-enclosed
Ducted fan, the one or both sides of the compound auxiliary wing of ducted fan thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and
It is flexibly connected by wing hinge with hybrid lift wing；The compound auxiliary wing of ducted fan thrust self energizing can be divided into the auxiliary wing of lift with
And auxiliary two parts of empennage of balance, the front and back of the compound auxiliary wing of no thrust self energizing is separately positioned on wherein, inside the auxiliary wing of lift
One self-enclosed ducted fan is at least installed.Shipping storehouse is mounted on the lower section of body.
Further, hybrid lift wing can be divided into lift main wing and balance two parts of empennage, be separately positioned on compound
Lifting wing front and back；Lift main wing) and balance empennage between be reserved with space, the horizontal lifting rudder wing is provided in space；Its
In, a self-enclosed ducted fan is at least installed inside lift main wing.
It further, further include vertical tail, the vertical tail is arranged above or below body；The vertical tail is set
It sets in wing two sides；The vertical tail may be implemented to fold；Mobilizable vertical rudder wing is installed behind the vertical tail.
Further, the vertical rudder wing is movably connected in the rear of vertical tail,.
Further, vertical tail, forms an angle with body planar shaped, and traction mechanism is equipped on vertical tail, realizes vertical
The deflection of the rudder wing.
Further, body is set as deck platform；The fixation hole of the regular arrangement in deck platform two sides；The first
Design has socket on plate platform；The socket is female or male.
Further, electro-hydraulic gas interface has lid.
Further, it is provided with video camera in front of body, video camera is PTZ camera.
Further, battery/fuel is provided on the compound auxiliary wing of ducted fan thrust self energizing.
The prior art is compared, the main feature having is invented:
1, the present invention has landing apart from short, and flying speed is fast, maneuverability, obstacle avoidance ability are strong, wing structure intensity is high, wing
It can be with energy storage, the features such as low energy consumption of flying.It relies on self-enclosed vertical ducted fan, aircraft can be provided in horizontal flight
Additional maneuverability realizes the super maneuver ability of moment change of flight posture and track.
2, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity,
Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are cooperated
Function is also able to achieve the forced landing of aerodone formula, greatly improves winged even if lift ducted fan and horizontal propeller damage simultaneously
The safety of row device has ensured the safety of personnel and goods and materials.
3, the present invention uses hardware and software platform, modularized design, is able to achieve multiple functions,
4, the present invention using two sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when
Lift, improve load capacity.
6. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention
Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil
The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.
Modular design reduces the disposable investment of client, reduces buying and operation cost.
7. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, synchronization is controlled by hybrid lift aircraft main control unit, is expanded again
And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
8. thrust device modularization can very easily realize maintenance replacement.
9. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, the auxiliary wing and hybrid lift aircraft are realized
Energy intercommunication between main plane, and the control by hybrid lift aircraft is acted, improve the flexibility of complete machine.
10. aerofoil type energy device efficiently uses space.
11. the present invention uses modularized design, compound different types of machines are used, and have saved cost.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is side view of the invention；
Fig. 3 is rearview of the invention；
Fig. 4 is plan view of the invention；
Fig. 5 is oblique view of the invention；
In figure: 101: body；102: hybrid lift wing；104: self-enclosed ducted fan；105: vertical tail；1051. vertical
The rudder wing；106: propeller；107: Energy Management System；1021: lift main wing；1022: the horizontal lifting rudder wing；1023: balance tail
The wing；1028: wing hinge；1001: socket；1002: cavity；1003: fixation hole；1006: battery/fuel；10311, lift is auxiliary
The wing；10312, auxiliary empennage is balanced；1036, electro-hydraulic gas interface；10361, lid；108, video camera；1063, ducted fan promotes
Device；113, shipping storehouse.
Specific embodiment
The present invention will be further described with reference to the accompanying drawing.
As shown in Figure 1, a kind of rear single ducted fan formula composite wing airfreighter of compound auxiliary wing of double ducted fans, feature
It is, it is compound auxiliary by the compound rotor aircraft of rear single ducted fan formula, the ducted fan thrust self energizing for being assemblied in its wing two sides
The wing and shipping storehouse 113 form；Wherein, rear single compound rotor aircraft of ducted fan formula includes body 101, is fixedly mounted on
101 two sides hybrid lift wing 102 of body, propeller 106；Wherein, the body 101 is set as deck platform；Described
Self-enclosed ducted fan 104 built in hybrid lift wing 102, design has wing hinge 1028 on the outside of hybrid lift wing 102；Institute
The propeller 106 stated is ducted fan propeller；The front end of the compound auxiliary wing of ducted fan thrust self energizing is provided with culvert
Road fan propeller 1063, the compound auxiliary wing of ducted fan thrust self energizing are internally provided with self-enclosed ducted fan 104, duct
The one or both sides of the compound auxiliary wing of fan thrust self energizing are provided with electro-hydraulic gas interface 1036 and wing hinge 1028, and pass through machine
Wing hinge 1028 is flexibly connected with hybrid lift wing 102；The compound auxiliary wing of ducted fan thrust self energizing can be divided into the auxiliary wing of lift
10311 and auxiliary 10,312 two parts of empennage of balance, it is separately positioned on the front and back of the compound auxiliary wing of no thrust self energizing wherein,
One self-enclosed ducted fan 104 is at least installed, shipping storehouse 113 is mounted under body 101 inside the auxiliary wing 10311 of lift
Side.
As further improvement of the invention, hybrid lift wing 102 can be divided into lift main wing 1021 and balance empennage
1023 two parts, are separately positioned on the front and back of hybrid lift wing 102；Between lift main wing 1021 and balance empennage 1023
It is reserved with space, the horizontal lifting rudder wing 1022 is provided in space；Wherein, one is at least equipped with inside lift main wing 1021 certainly
Close ducted fan 104.
It further include vertical tail 105, the vertical tail 105 is arranged in body 101 as further improvement of the invention
Above or below；The vertical tail 105 is arranged in wing two sides；The vertical tail 105 may be implemented to fold；It is described vertical
Mobilizable vertical rudder wing 1051 is installed behind empennage 105.
As further improvement of the invention, the vertical rudder wing 1051 is movably connected in the rear of vertical tail, 105.
As further improvement of the invention, vertical tail, 105 forms an angle with body planar shaped, and installs on vertical tail,
There is traction mechanism, realizes the deflection of the vertical rudder wing.
As further improvement of the invention, body 101 is set as deck platform；The deck platform two sides are regular
The fixation hole 1003 of arrangement；Design has socket 1001 in the deck platform；The socket 1001 is female or male.
As further improvement of the invention, electro-hydraulic gas interface 1036 has lid 10361.
As further improvement of the invention, video camera 108 is provided in front of body 101, video camera 108 is holder camera shooting
Machine.
As further improvement of the invention, battery/fuel is provided on the compound auxiliary wing of ducted fan thrust self energizing
1006。
The prior art is compared, the main feature having is invented:
1, the present invention has landing apart from short, and flying speed is fast, maneuverability, obstacle avoidance ability are strong, wing structure intensity is high, wing
It can be with energy storage, the features such as low energy consumption of flying.It relies on self-enclosed vertical ducted fan, aircraft can be provided in horizontal flight
Additional maneuverability realizes the super maneuver ability of moment change of flight posture and track.
2, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity,
Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are cooperated
Function is also able to achieve the forced landing of aerodone formula, greatly improves winged even if lift ducted fan and horizontal propeller damage simultaneously
The safety of row device has ensured the safety of personnel and goods and materials.
3, the present invention uses hardware and software platform, modularized design, is able to achieve multiple functions,
4, the present invention using two sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when
Lift, improve load capacity.
5, the present invention also has successive socket, and the cluster of aircraft is facilitated to fly, and further decreases cluster flight
When power consumption.When front and back is connected in series, the aircraft at rear only needs a small amount of energy consumption, can be achieved with flying for long range
Row, the cluster flight of only aircraft does not provide the low-power consumption scheme of clustering, it might even be possible to realize the sky between aircraft
Faulty aircraft dragging below is taken off, realizes and mutually come to sb.'s rescue between aircraft not seen before by middle rescue, i.e., preceding aircraft
Help phenomenon.
6. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention
Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil
The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.
Modular design reduces the disposable investment of client, reduces buying and operation cost.
7. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, synchronization is controlled by hybrid lift aircraft main control unit, is expanded again
And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
8. thrust device modularization can very easily realize maintenance replacement.
9. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, the auxiliary wing and hybrid lift aircraft are realized
Energy intercommunication between main plane, and the control by hybrid lift aircraft is acted, improve the flexibility of complete machine.
10. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility.
11. aerofoil type energy device efficiently uses space.
12. the present invention uses modularized design, compound different types of machines are used, and have saved cost.
Schematically the present invention and embodiments thereof are described above, description is not limiting, institute in attached drawing
What is shown is also one of embodiments of the present invention, and actual structure is not limited to this.So if the common skill of this field
Art personnel are enlightened by it, without departing from the spirit of the invention, are not inventively designed and the technical solution
Similar frame mode and embodiment, are within the scope of protection of the invention.
Claims (9)
1. a kind of rear single ducted fan formula composite wing airfreighter of compound auxiliary wing of double ducted fans, which is characterized in that by rear list
The compound rotor aircraft of ducted fan formula, the compound auxiliary wing of ducted fan thrust self energizing for being assemblied in its wing two sides, shipping storehouse
(113) it forms；
Wherein, rear single compound rotor aircraft of ducted fan formula includes body (101), is fixedly mounted on body (101) two
Side hybrid lift wing (102), propeller (106)；Wherein, the body (101) is set as deck platform；Described is compound
Self-enclosed ducted fan (104) built in lifting wing (102), the design of hybrid lift wing (102) outside have wing hinge
(1028)；The propeller (106) is ducted fan propeller；
The front end of the compound auxiliary wing of ducted fan thrust self energizing is provided with ducted fan propeller (1063), ducted fan
The compound auxiliary wing of thrust self energizing is internally provided with self-enclosed ducted fan (104), the compound auxiliary wing of ducted fan thrust self energizing
One or both sides be provided with electro-hydraulic gas interface (1036) and wing hinge (1028), and by wing hinge (1028) with it is compound
Lifting wing (102) is flexibly connected；The compound auxiliary wing of ducted fan thrust self energizing can be divided into the auxiliary wing of lift (10311) and balance
(10312) two parts of auxiliary empennage are separately positioned on the front and back of the compound auxiliary wing of no thrust self energizing wherein, the auxiliary wing of lift
(10311) internal that a self-enclosed ducted fan (104) is at least installed；
The shipping storehouse (113) is mounted on the lower section of body (101).
2. a kind of rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan according to claim 1
, which is characterized in that the hybrid lift wing (102) can be divided into lift main wing (1021) and balance empennage (1023) two
Part is separately positioned on the front and back of hybrid lift wing (102)；It is pre- between lift main wing (1021) and balance empennage (1023)
There are space, the horizontal lifting rudder wing (1022) is provided in space；Wherein, one is at least equipped with inside lift main wing (1021)
Self-enclosed ducted fan (104).
3. a kind of rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan according to claim 1
, which is characterized in that it further include vertical tail (105), the vertical tail (105) is arranged above or below body (101)；Institute
Vertical tail (105) are stated to be arranged in wing two sides；The vertical tail (105) may be implemented to fold；The vertical tail (105)
Mobilizable vertical rudder wing (1051) is installed below.
4. a kind of rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan according to claim 3
, which is characterized in that the vertical rudder wing (1051) is movably connected in the rear of vertical tail, (105).
5. a kind of rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan according to claim 3
, which is characterized in that the vertical tail, (105) forms an angle with body planar shaped, and traction mechanism is equipped on vertical tail,
Realize the deflection of the vertical rudder wing.
6. a kind of rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan according to claim 1
, which is characterized in that the body (101) is set as deck platform；The fixation of the regular arrangement in deck platform two sides
Hole (1003)；Design has socket (1001) in the deck platform；The socket (1001) is female or male.
7. a kind of rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan according to claim 1
, which is characterized in that the electro-hydraulic gas interface (1036) has lid (10361).
8. a kind of rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan according to claim 1
, which is characterized in that video camera (108) are provided in front of the body (101)；Video camera (108) is PTZ camera.
9. a kind of rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan according to claim 1
, which is characterized in that battery/fuel (1006) are provided on the compound auxiliary wing of ducted fan thrust self energizing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810546112.5A CN108974350A (en) | 2018-05-31 | 2018-05-31 | Rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810546112.5A CN108974350A (en) | 2018-05-31 | 2018-05-31 | Rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108974350A true CN108974350A (en) | 2018-12-11 |
Family
ID=64542807
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810546112.5A Pending CN108974350A (en) | 2018-05-31 | 2018-05-31 | Rear single ducted fan formula composite wing airfreighter of double compound auxiliary wings of ducted fan |
Country Status (1)
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Citations (9)
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|---|---|---|---|---|
| US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
| US20040245374A1 (en) * | 2003-01-06 | 2004-12-09 | Morgan Brian H. | Vertical take-off and landing aircraft |
| US20100051741A1 (en) * | 2008-09-03 | 2010-03-04 | Anvar Ismailov | Unmanned air vehicle |
| CN102530248A (en) * | 2011-12-12 | 2012-07-04 | 周景荣 | Design method for multifunctional helicopter |
| CN102616096A (en) * | 2012-04-24 | 2012-08-01 | 赵辉 | Solar flying automobile with folding wings |
| CN102658866A (en) * | 2012-05-25 | 2012-09-12 | 辽宁通用航空研究院 | Conjoined aircraft with straight layout |
| CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
| CN107651168A (en) * | 2017-09-30 | 2018-02-02 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane wingfold mechanism and method for folding |
| WO2018078388A1 (en) * | 2016-10-27 | 2018-05-03 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
-
2018
- 2018-05-31 CN CN201810546112.5A patent/CN108974350A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
| US20040245374A1 (en) * | 2003-01-06 | 2004-12-09 | Morgan Brian H. | Vertical take-off and landing aircraft |
| US20100051741A1 (en) * | 2008-09-03 | 2010-03-04 | Anvar Ismailov | Unmanned air vehicle |
| CN102530248A (en) * | 2011-12-12 | 2012-07-04 | 周景荣 | Design method for multifunctional helicopter |
| CN102616096A (en) * | 2012-04-24 | 2012-08-01 | 赵辉 | Solar flying automobile with folding wings |
| CN102658866A (en) * | 2012-05-25 | 2012-09-12 | 辽宁通用航空研究院 | Conjoined aircraft with straight layout |
| CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
| WO2018078388A1 (en) * | 2016-10-27 | 2018-05-03 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
| CN107651168A (en) * | 2017-09-30 | 2018-02-02 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane wingfold mechanism and method for folding |
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Application publication date: 20181211 |