CN104192305A - Multi-element wing - Google Patents
Multi-element wing Download PDFInfo
- Publication number
- CN104192305A CN104192305A CN201410363967.6A CN201410363967A CN104192305A CN 104192305 A CN104192305 A CN 104192305A CN 201410363967 A CN201410363967 A CN 201410363967A CN 104192305 A CN104192305 A CN 104192305A
- Authority
- CN
- China
- Prior art keywords
- wing
- net
- location
- aircraft
- sensor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Tires In General (AREA)
Abstract
The invention provides a multi-element wing, which is used for providing power to an aircraft. The multi-element wing comprises a support frame, a locating net, and a plurality of wing elements, wherein the boundary of the locating net is fixedly arranged on the support frame; the locating net is provided with net knots for limiting; the wing elements are defined on the net knots. As the rotating wing elements are defined inside the locating net and the support frame, the safety of the multi-element wing is improved.
Description
Technical field
The present invention relates to a kind of multiple wing.
Background technology
Use propeller type aircraft of the prior art, is exposed to outer screw propeller easily and foreign object is interfered, and causes blade fracture, hurt sb.'s feelings or damage foreign object.
Therefore, be necessary to design a kind of safe multiple wing.
Summary of the invention
The defect existing for prior art, the invention provides the multiple wing, is used to aircraft that power is provided, and comprising:
Bracing frame;
Network for location, bracing frame is fixed on the border of network for location, and network for location is provided with for spacing anastomose;
Some wings are first, and wing unit is defined to anastomose.
Alternative, support frame as described above is the ring-type of sealing.
Alternative, support frame as described above center of curvature points to network for location.
Alternative, the elevation profile of support frame as described above is curved, and bracing frame has two end faces, and the radius of curvature of bracing frame midway location is greater than the radius of curvature of end face.
Alternative, described network for location at least comprises two-layer, network for location is combined with bracing frame and is formed a receiving space.
Alternative, described network for location at least comprises that the first net is dry, the first net is done as flexible cable.
Alternative, described anastomose comprises that the first net is dry, the second net is dry, the 3rd net is dry and mesh, mesh is dry by the first net, the second net is dry and dry encirclement of the 3rd net forms.
Alternative, the described multiple wing also comprises base station, wing unit is installed on base station.
Alternative, described base station is sticked in mesh.
Alternative, described wing unit has several, is distributed in equably network for location.
Alternative, the described multiple wing is provided with public sensor, and public sensor is positioned at multiple wing middle part.
Alternative, described wing unit comprises controller and the private sensor of controlling motor, and between controller and private sensor, interactive information is controlled machine operation.
Alternative, described wing unit comprises the controller of controlling motor, and the described multiple wing is provided with public sensor, and between public sensor and wing unit, communication modes is the parallel way of N-N or 1-N.
Alternative, the inner private sensor that guarantees safety forced landing function of installing of described wing unit, the described multiple wing is provided with public sensor, and private sensor comprises: gyroscope, accelerometer, both are built in wing unit.
Alternative, the inefficacy quantity of described wing unit is less than that three of total quantity/for the moment, the load of aircraft is greater than rated load.
Alternative, when the inefficacy quantity of described wing unit surpasses the sixth of total quantity, cause the forced landing of aircraft or public sensor failure quantity surpass total quantity 2/3rds time, cause the forced landing of aircraft; Or during the communicating interrupt between public sensor and wing unit, cause the forced landing of aircraft.
Compared with prior art, the present invention at least has following technique effect: in network for location and bracing frame are defined in the wing unit of rotation, and the safety that has improved the multiple wing.
Accompanying drawing explanation
Fig. 1 is a kind of embodiment schematic diagram of aircraft of the present invention.
Fig. 2 is the another kind of embodiment schematic diagram of aircraft of the present invention.
Fig. 3 is the third embodiment schematic diagram of aircraft of the present invention.
Fig. 4 is the schematic diagram of the multiple wing of aircraft of the present invention.
Fig. 5 is the birds-eye view of the multiple wing of aircraft of the present invention.
Fig. 6 is the schematic diagram of the network for location of aircraft of the present invention.
Fig. 7 is the schematic diagram of the wing unit of aircraft of the present invention.
Fig. 8 is the reliability block diagram of aircraft of the present invention.
The specific embodiment
A lot of details have been set forth in the following description so that fully understand the present invention.But the present invention can implement to be much different from alternate manner described here, and those skilled in the art can do similar popularization without prejudice to intension of the present invention in the situation that, so the present invention is not subject to the restriction of following public specific embodiment.
The present invention has disclosed a kind of aircraft 100.
The defined aircraft 100 of the present invention refers to all aircraft 100 that rely on the multiple wing 1 flight.Concrete, aircraft 100 can be autogyro, dirigible or other flight instrumentses.This aircraft 100 can be used for shipping, also can be for passenger traffic.Should offer some clarification, the concrete form of aircraft 100 and purposes, not should be understood to the restriction that essence of the present invention is done.
Aircraft 100, comprises aircraft body 2, the multiple wing 1 and the multiple wing 1 is connected in to the bindiny mechanism 3 of aircraft body 2.Please refer to shown in Fig. 1 to Fig. 3, disclosed respectively three kinds of different aircraft 100, difference is the position difference between aircraft body 2 and the multiple wing 1.In Fig. 1, the multiple wing 1 is positioned at the top of aircraft body 2.In Fig. 2, the multiple wing 1 is positioned at the below of aircraft body 2.In Fig. 3, aircraft body 2 is positioned at the middle part of the multiple wing 1.
Aircraft body 2 comprises cargo hold and/or main cabin in definition of the present invention.
Cargo hold is mainly used in bearing goods.Main cabin is mainly used in carrying passenger.
Refer to Fig. 4 and Fig. 5, the multiple wing 1 is used to aircraft 100 that power is provided, and comprising:
Bracing frame 11;
Network for location 12 refers to Fig. 6, and bracing frame 11 is fixed on the border of network for location 12, and network for location 12 is provided with for spacing anastomose 121;
Fig. 7 is referred in wing unit 13, and wing unit 13 has several, is defined to anastomose 121.
Network for location 12 and bracing frame 11 have been isolated turning unit in the wing unit 13 of rotation is defined in, and have improved the safety of the multiple wing 1.
Bracing frame 11 is for providing the assembling structure of the multiple wing 1.Preferably, bracing frame 11 is the ring-type of sealing.Such bracing frame 11 structures are more firm, shock resistance.When bracing frame 11 occurs to clash into, impulsive force can be dispersed to whole bracing frame 11, thereby not fragile.Certainly, bracing frame 11 also can be formed by a plurality of segmental arcs, and bracing frame 11 center of curvatures point to network for location 12.Such bracing frame 11 also has certain anti-impact force effect.Center of curvature points to network for location 12, and the segmental arc appearance of formation is shunk and prevented people around or deposits yields to damage.The elevation profile of bracing frame 11 is curved, and bracing frame 11 has two end faces, and the radius of curvature of bracing frame 11 midways location is greater than the radius of curvature of end face.The appearance of bracing frame 11 is further smooth like this, prevents people or deposits yields to damage, and anti-impact force further strengthens simultaneously.
Network for location 12 at least comprises two-layer, and network for location 12 forms a receiving space with bracing frame 11 combinations.The multiple wing 1 is defined in receiving space.Like this, network for location 12 and bracing frame 11 are fully isolated from the outside the flabellum of rotation 131, prevent that the wing unit 13 of rotation from hurting sb.'s feelings or damaging object, reach the effect of protection wing unit 13, the service life of having improved the multiple wing 1 simultaneously.While particularly there is scraping, the isolated multiple wing 13 can not produce damage.
Certainly, in some occasions, one deck network for location 12 is only set and is also fine.
Network for location 12 at least comprises the first net dry 122.The first net dry 122 can be rigid rod, can be also flexible cable cable.Flexible cable can reduce the impact to bracing frame 11 on the one hand when occurring to impact, thereby is difficult for losing efficacy.Can cushion the multiple wing 1 on the other hand, prevent the damage of the multiple wing 1.And the pulling force that flexible cable can bear is much larger than the rigid rod of same diameter, so long service life.The first net dry 122 is mainly made by polyacrylonitrile-based carbon fibre, and such network for location 12 quality are light, intensity is large.Preferably, in this carbon fiber, be compounded with fire-retardant material, when the multiple wing 1 burning, play and prevent further enlargement loss.
Network for location 12 is provided with the anastomose 121 for the spacing multiple wing 1.Anastomose 121 comprises dry the 123, the 3rd net dry 124 and the mesh 125 of dry the 122, second net of the first net.Mesh 125 is surrounded and is formed by dry the 123 and the 3rd net dry 124 of dry the 122, second net of the first net.It is 122 identical that the materials that dry the 123, the 3rd net dry 124 of the second net is used and manufacture craft and the first net are done.
The multiple wing 1 also comprises base station, and base station is sticked in mesh 125.Wing unit 13 is installed on base station.Such benefit is to be convenient to the assembling of wing unit 13 with fixing, improves the packaging efficiency of the multiple wing 1.
The multiple wing 1 is provided with hollow area, and wing unit 13 is positioned at outside hollow area.Aircraft 100 is provided with public sensor, and public sensor is positioned at hollow area.Public like this sensor has symmetry with communicating by letter of wing unit 13 and can reduce design and productive costs.
The multiple wing 1, consists of some wings unit 13.Improved like this safety of aircraft 100, traditional single-blade flabellum helicopter, needs only any one parts et out of order in flabellum, motor, transmission, all can cause the generation of tragedy.And the multiple wing 1 type aircraft 100, the single wing first 13 lost efficacy, and can rely on all the other wings units 13 to keep balances, the safety that has improved aircraft 100.Wing unit 13 distributes in the mode of decentralization.
Wing unit 13 comprises flabellum 131 and wing unit main body 132.The concrete blade that refers to screw propeller, the flabellum 131 of tunnel fan or all of turbine blade of this flabellum 131 drive Air Flow by extruding, obtain the parts of hoisting force by antagonistic force.
Wing unit 13 main bodys comprise housing, are installed on the motor in housing, controller, the private sensor of control motor.Controller refers to that this at least comprises and controls electric motor starting and stop and the controller of rotating speed.Certainly, in order to obtain better effect, the integrated level of controller can be improved.
Private sensor comprises and guarantees force-land the safely sensor of function of aircraft 100.Private sensor comprises gyroscope, accelerometer.
Wing unit is provided with signal receiver.Signal receiver receives from public sensor and sends signal in the mode of wireless telecommunications or wire communication.Preferably, be wireless communication mode, when such wing unit 13 is on fire, can not feed through to other wing units 13.Between controller and private sensor, interactive information is controlled machine operation.When channel block between public sensor and wing unit, controller relies on private sensor to control machine operation to drive aircraft 100 to force-land safely.The packaging efficiency of the multiple wing 1 has improved in the wing unit 13 of individual packages.Between public sensor and wing unit, communication modes is the parallel way of N-N or 1-N.Thereby only cause while making single motor, single controller, individual signals receptor fault this wing unit 13 to be lost efficacy, and do not affect other wing units 13.
The multiple wing 1 is provided with public sensor.Public sensor comprises GPS orientator, height sensor, airspeed sensor, gyroscope, accelerometer, light stream sensor, compass, operating handle, remote control reception instrument, fault sensor etc.Public sensor refers to because volume is large, weight large, complex structure etc. is not easy to be encapsulated into the sensor in wing unit.
The control of a kind of preferred wing provided by the invention unit 13 is distributed management mode.When wherein a certain wing first 13 lost efficacy, the multiple wing 1 dynamic compensation.Concrete, public sensor guide vane unit sends signal.Controller, according to current state and sensing state, is controlled the rotation of motor, until current state and sensing state consistency.This current state is provided jointly by public sensor and private sensor, only has when there is communication failure between public sensor and wing unit 13, and current state and sensing state are only provided by private sensor.
Refer to the reliability block diagram in Fig. 8.In order to guarantee load and the safety of flight, wing unit 13 has certain surplus.Be that the inefficacy quantity of wing unit 13 is less than that three of total quantity/for the moment, the load of aircraft 100 is greater than rated load.When the inefficacy quantity of wing unit 13 surpasses the sixth of total quantity, cause the forced landing of aircraft 100.In addition, the public sensor loss of the multiple wing 1 surpass total quantity 2/3rds time, cause the forced landing of aircraft 100.This kind of failure mode and surplus design have been obtained balance between the efficiency of aircraft 100 safe and effective loads.
The distribution control mode of another kind of wing unit 13 is as follows: wing unit's 13 Central Symmetries or distribute axisymmetrically, and when single wing unit 13 lost efficacy, with quitting work of inefficacy wing unit's 13 Central Symmetries or axisymmetric wing unit 13.The wing unit 13 that is different spacing with center forms first 13 rings of the multistage wing, and when certain grade of wing unit 13 ring inefficacy numbers surpass half, this grade of first 13 rings of the wing quit work.Wing unit 13 is regular hexagon and distributes.Like this, when first order wing unit 13 rings have at least three wing units 13 to lose efficacy, just can cause first order wing unit 13 rings to lose efficacy.Even if first order wing unit 13 rings lost efficacy, close first order wing unit 13 rings, rely on second stage wing unit 13 rings still can work on, greatly improved the safety of aircraft 100.The 13 ring inefficacies of second stage wing unit equally at least need three wing units 13 on first 13 rings of the second stage wings to lose efficacy, and the wing unit 13 of two-stage occurs extremely low over the probability of half inefficacy simultaneously, so the safety performance of aircraft 100 improves greatly.When inefficacy wing unit 13 rings surpass two-stage, aircraft 100 landing.
In housing, be provided with battery mounting groove, battery is installed on battery mounting groove.Can further improve the integrated level of wing unit 13 like this, improve packaging efficiency.Battery is unremovably packaged in housing, and housing is provided with the charging inlet with battery electrical communication.So further improved the integrated level of wing unit 13.
In a kind of embodiment, motor has the outer rotor of the outside of being exposed to, and flabellum 131 detouchables are installed on outer rotor.Certainly, flabellum 131 outer rotors are one-body molded is also fine.Stator is for fixing.
In another kind of alternative embodiment, motor is connected with the output shaft that extends housing, and flabellum 131 is removably installed in output shaft.When flabellum 131 damages, only change flabellum 131 like this, reduced maintenance cost.
Bindiny mechanism 3 has a plurality of.Can improve like this stability that the multiple wing 1 is connected with aircraft body 2.A plurality of bindiny mechanisms 3 are distributed in around the multiple wing 1 equably.Certainly, bindiny mechanism 3 also can be connected in the multiple wing 1 inside.In a kind of embodiment, bindiny mechanism 3 is connected in bracing frame 11.In another kind of alternative embodiment, bindiny mechanism 3 is connected in network for location 12.Bindiny mechanism 3 provided by the invention is distributed in around the multiple wing 1 in orthohexagonal mode equally.Bindiny mechanism 3 is pipe link or cable.In the preferred embodiment of the present invention, bindiny mechanism 3 is cable.The benefit of doing is like this on the one hand, can reduce the space requirement while shutting down.Second point is when aircraft body 2 or the multiple wing 1 shock, to slow down impact, the service life of improving aircraft 100.
Although the present invention with preferred embodiment openly as above; but it is not for limiting the present invention; any those skilled in the art without departing from the spirit and scope of the present invention; can make possible change and modification, so protection scope of the present invention should be as the criterion with the scope that the claims in the present invention were defined.
Claims (16)
1. a multiple wing, is used to aircraft that power is provided, and it is characterized in that, comprising:
Bracing frame;
Network for location, bracing frame is fixed on the border of network for location, and network for location is provided with for spacing anastomose;
Some wings are first, and wing unit is defined to anastomose.
2. the multiple wing according to claim 1, is characterized in that: support frame as described above is the ring-type of sealing.
3. the multiple wing according to claim 1, is characterized in that: support frame as described above center of curvature points to network for location.
4. the multiple wing according to claim 1, is characterized in that: the elevation profile of described flight frame is curved, and bracing frame has two end faces, and the radius of curvature of bracing frame midway location is greater than the radius of curvature of end face.
5. the multiple wing according to claim 1, is characterized in that: described network for location at least comprises two-layer, and network for location is combined with bracing frame and is formed a receiving space.
6. the multiple wing according to claim 1, is characterized in that: described network for location at least comprises that the first net is dry, and the first net is done as flexible cable.
7. the multiple wing according to claim 1, is characterized in that: described anastomose comprises that the first net is dry, the second net is dry, the 3rd net is dry and mesh, and mesh is dry by the first net, the second net is dry and dry encirclement of the 3rd net forms.
8. the multiple wing according to claim 1, is characterized in that: the described multiple wing also comprises base station, and wing unit is installed on base station.
9. the multiple wing according to claim 8, is characterized in that: described base station is sticked in mesh.
10. the multiple wing according to claim 1, is characterized in that: described wing unit has several, is distributed in equably network for location.
The 11. multiple wings according to claim 1, is characterized in that: the described multiple wing is provided with public sensor, and public sensor is positioned at multiple wing middle part.
The 12. multiple wings according to claim 1, is characterized in that: described wing unit comprises controller and the private sensor of controlling motor, interactive information control machine operation between controller and private sensor.
The 13. multiple wings according to claim 1, is characterized in that: described wing unit comprises the controller of controlling motor, and the described wing of answering is provided with public sensor, and between public sensor and wing unit, communication modes is the parallel way of N-N or 1-N.
The 14. multiple wings according to claim 1, is characterized in that: the inner private sensor that guarantees safety forced landing function of installing of described wing unit, and the described multiple wing is provided with public sensor, and private sensor comprises: gyroscope, accelerometer, both are built in wing unit.
The 15. multiple wings of stating according to claim 1, is characterized in that: the inefficacy quantity of described wing unit is less than that three of total quantity/for the moment, the load of aircraft is greater than rated load.
The 16. multiple wings of stating according to claim 1, is characterized in that: when the inefficacy quantity of described wing unit surpasses the sixth of total quantity, cause the forced landing of aircraft or public sensor failure quantity surpass total quantity 2/3rds time, cause the forced landing of aircraft; Or during the communicating interrupt between public sensor and wing unit, cause the forced landing of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410363967.6A CN104192305A (en) | 2014-07-29 | 2014-07-29 | Multi-element wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410363967.6A CN104192305A (en) | 2014-07-29 | 2014-07-29 | Multi-element wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104192305A true CN104192305A (en) | 2014-12-10 |
Family
ID=52077737
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410363967.6A Pending CN104192305A (en) | 2014-07-29 | 2014-07-29 | Multi-element wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104192305A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104925263A (en) * | 2015-06-29 | 2015-09-23 | 田悦丰 | Aircraft with multiple driving devices |
| US10683098B2 (en) | 2015-06-29 | 2020-06-16 | Yuefeng TIAN | Driving device assembly with multiple drive devices and application thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU2007249724A1 (en) * | 2006-05-12 | 2007-11-22 | Bell Helicopter Textron Inc. | Yoke with notched arm roots |
| CN102225704A (en) * | 2009-07-06 | 2011-10-26 | 周景荣 | Designing method of high-speed multifunctional helicopter aero-flying saucer |
| CN202728572U (en) * | 2012-06-25 | 2013-02-13 | 田瑜 | Multi-rotor aircraft |
| CN203528819U (en) * | 2013-11-08 | 2014-04-09 | 珠海羽人飞行器有限公司 | Agricultural unmanned aircraft |
| CN203544370U (en) * | 2013-08-06 | 2014-04-16 | 陈博 | Agricultural multi-rotor unmanned helicopter |
| CN203623965U (en) * | 2013-10-31 | 2014-06-04 | 夏桂书 | Rotor wing device applied to fixed wing aircraft |
-
2014
- 2014-07-29 CN CN201410363967.6A patent/CN104192305A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU2007249724A1 (en) * | 2006-05-12 | 2007-11-22 | Bell Helicopter Textron Inc. | Yoke with notched arm roots |
| CN102225704A (en) * | 2009-07-06 | 2011-10-26 | 周景荣 | Designing method of high-speed multifunctional helicopter aero-flying saucer |
| CN202728572U (en) * | 2012-06-25 | 2013-02-13 | 田瑜 | Multi-rotor aircraft |
| CN203544370U (en) * | 2013-08-06 | 2014-04-16 | 陈博 | Agricultural multi-rotor unmanned helicopter |
| CN203623965U (en) * | 2013-10-31 | 2014-06-04 | 夏桂书 | Rotor wing device applied to fixed wing aircraft |
| CN203528819U (en) * | 2013-11-08 | 2014-04-09 | 珠海羽人飞行器有限公司 | Agricultural unmanned aircraft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104925263A (en) * | 2015-06-29 | 2015-09-23 | 田悦丰 | Aircraft with multiple driving devices |
| CN104925263B (en) * | 2015-06-29 | 2018-10-26 | 田悦丰 | A kind of aircraft with more driving devices |
| CN109110140A (en) * | 2015-06-29 | 2019-01-01 | 田悦丰 | A kind of aircraft with more driving devices |
| US10683098B2 (en) | 2015-06-29 | 2020-06-16 | Yuefeng TIAN | Driving device assembly with multiple drive devices and application thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR102242857B1 (en) | A thrust producing unit with at least two rotor assemblies and a shrouding | |
| CN107074366B (en) | Helicopter | |
| US11912404B2 (en) | Vertical takeoff and landing aircraft | |
| ES2605421T3 (en) | System and procedure of wind power production in flight | |
| EP3483064B1 (en) | Tilting proprotor with segmented duct | |
| RU2538737C2 (en) | Rotor "air wheel", gyrostabilised aircraft and wind-driven electric plant using rotor "air wheel", surface/deck devices for their start-up | |
| JP3677748B1 (en) | Aircraft created by fixing the rapid airflow generating wind direction changing device directly on the side or side wall of the aircraft. | |
| JP2020040660A (en) | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades | |
| WO2016032356A1 (en) | "air wheel" rotor. gyro-stabilized aircraft and wind-energy installation utilizing "air wheel" rotor, and ground-based or ship-based device for launching same | |
| KR101967249B1 (en) | Drone | |
| EP2459441A2 (en) | Improved self-righting aerostat and relative takeoff and recovery system | |
| US9555879B1 (en) | Aircraft having circular body and blades | |
| CN111542476A (en) | Flight module | |
| JP2013079034A (en) | Rotorcraft for aerial photographing | |
| US9840323B1 (en) | Drone aircraft | |
| US20200290718A1 (en) | Unmanned aerial vehicle | |
| CN105314105A (en) | Hybrid multi-rotor aircraft with retractable wings | |
| CN102910285A (en) | Rotor aircraft | |
| CN114616177A (en) | Aircraft, in particular unmanned aerial vehicle or aircraft for personal air movement, having a high-efficiency propeller rotor | |
| CN104192305A (en) | Multi-element wing | |
| CN204776020U (en) | Unmanned vehicles with many rotors of major -minor structure | |
| CN102424104A (en) | Four-rotor-wing indoor airship | |
| CN104176249B (en) | A kind of non co axial anti-oar many rotors unmanned gyroplane | |
| CN104176231A (en) | Wing element and composite wing | |
| CN104181919A (en) | Aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20141210 |