CN107933875B - Truss type unmanned aerial vehicle fuselage with light-weight and rigidity adjustable - Google Patents
Truss type unmanned aerial vehicle fuselage with light-weight and rigidity adjustable Download PDFInfo
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- CN107933875B CN107933875B CN201810014657.1A CN201810014657A CN107933875B CN 107933875 B CN107933875 B CN 107933875B CN 201810014657 A CN201810014657 A CN 201810014657A CN 107933875 B CN107933875 B CN 107933875B
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- 238000000034 method Methods 0.000 description 7
- 239000000463 material Substances 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000002146 bilateral effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
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Classifications
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- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/065—Spars
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- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
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- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/08—Geodetic or other open-frame structures
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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Forklifts And Lifting Vehicles (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The invention discloses a light-weight rigidity-adjustable truss type unmanned aerial vehicle body, which comprises a body truss, wherein the body truss comprises a left truss and a right truss, two ends of a rigidity adjusting piece are fixedly connected with the left truss and the right truss, and the fixing positions of the rigidity adjusting piece and the left truss and the right truss are adjustable. The left truss and the right truss are respectively a first rod member group and a second rod member group which are arranged along the front-back direction, the first rod member group and the second rod member group are mutually parallel, two ends of the rigidity adjusting member are respectively fixedly connected with the first rod member group and the second rod member group, the rigidity-adjustable truss type unmanned aerial vehicle body is reasonable in structure, good in light weight effect and long in fatigue life, and the rigidity-adjustable truss type unmanned aerial vehicle body can adapt to load adjustment.
Description
Technical Field
The invention relates to a lightweight unmanned aerial vehicle body, in particular to a lightweight rigidity-adjustable truss type unmanned aerial vehicle body.
Background
Along with the popularization of technology, unmanned aerial vehicles are widely applied to a plurality of fields such as agriculture, forestry, reconnaissance, petroleum, electric power and the like, and are used more and more in daily life such as express delivery and the like.
The fuselage is a key component in the unmanned aerial vehicle, is connected with parts such as power, load and the like, and has higher strength and rigidity, and has different requirements on the rigidity of the fuselage under different load conditions; the weight of the aircraft body occupies a considerable proportion in the dead weight of the whole aircraft, so that the weight is reduced, and the aircraft has great promotion effect on the flight performance; and from the stress condition, the machine body is connected with a power load and the like, but in the process of flying and landing of the unmanned aerial vehicle in the air, the connection between the machine frame and the landing gear or between the machine body and the load is generally hinged or rigid connection, the flying process is in a three-dimensional motion state, the stress of the machine body is necessarily in an omnidirectional stress state, and the reliability of the machine body directly influences the reliability of the flying state.
Although some of the unmanned aerial vehicle body adopts a plate frame structure and is provided with holes for reducing the weight, the weight of the plate frame is quite large, and the key point is that the rigidity cannot be adjusted and cannot be adjusted along with the change of the load, so that the unmanned aerial vehicle is not beneficial to the performance improvement and the flight safety of the unmanned aerial vehicle.
Disclosure of Invention
Aiming at the problems that the prior unmanned aerial vehicle body technology has unreasonable structural design, poor light weight effect, short fatigue life, unadjustable rigidity and the like, the invention provides a truss type body which has reasonable structural design, good light weight effect, long fatigue life and capability of adapting to load to adjust rigidity.
The technical scheme adopted by the invention for solving the technical problem is as follows: the truss type unmanned aerial vehicle fuselage with the adjustable rigidity of lightweight, the truss type unmanned aerial vehicle fuselage with the adjustable rigidity of lightweight includes fuselage truss 2, and fuselage truss 2 includes left side truss 201, right side truss 202, and rigidity adjusting piece 1 both ends and left side truss 201, right side truss 202 fixed connection to with left side truss 201, right side truss 202 fixed position is adjustable.
The left truss 201 of the unmanned aerial vehicle is a first rod set arranged along the front-back direction, the right truss 202 is a second rod set arranged along the front-back direction, the first rod set and the second rod set are arranged in parallel, and two ends of the rigidity adjusting piece 1 are fixedly connected with the first rod set and the second rod set respectively.
The rods in the first rod member set are arranged in parallel, and the rods in the second rod member set are arranged in parallel.
The two ends of the rigidity adjusting part 1 are fixedly connected with rods in the first rod set and the second rod set, and at least one rod in each of the first rod set and the second rod set is not fixedly connected with the rigidity adjusting part 1.
The rigidity adjusting part 1 comprises a left connector 101, a right connector 102 and a screw rod 103, wherein studs are arranged on two sides of the screw rod 103, the threads of the studs on two sides are opposite in screwing direction, the studs on two sides are respectively connected with the threads of the left connector 101 and the right connector 102, and the left connector 101 and the right connector 102 are respectively fixed with a left truss 201 and a right truss 202.
The middle part of the screw rod 103 is provided with a regular hexagonal prism used for clamping the screw rod 103 by a spanner.
The rigidity adjusting part 1 further comprises a left buckling plate 1013 and a right buckling plate, the left connector 101 is in a T shape, the vertical side of the T shape is in threaded connection with the left end of the screw rod 103, two or more grooves first 1014 for accommodating the left truss 201 are formed in the T-shaped horizontal side of the left connector 101, grooves second 1011 are formed in the positions, corresponding to the grooves first 1014, of the left buckling plate 1013, the grooves first 1014 are opposite to the grooves second 1011 and are used for clamping rods of the left truss 201, bolt holes 1012 are formed between the grooves first 1014 and the grooves second 1011 and in the end portions, bolts are arranged in the bolt holes 1012 and used for locking the left buckling plate 1013 and clamping rods of the left truss 201, and the structures of the right connector 102 and the right buckling plate fixed right truss 202 are identical to those of the left connector 101 and the left buckling plate 101 fixed left truss 201.
The rods of the left truss 201 and the right truss 202 are cylindrical, and the first groove 1014 and the second groove 1011 are semicircular.
The end of the fuselage truss 2 is fixedly connected with the front fixing plate 3, the rear end of the fuselage truss 2 is fixedly connected with the rear fixing plate 4, the rear fixing plate 4 is used for fixing the tail spar 300, the front fixing plate 3 is used for fixing an unmanned aerial vehicle engine, the main rotor shaft 100 is arranged on the engine, and the front end and the rear end of the landing gear 400 are respectively fixed at the front part and the rear part of the fuselage truss 2.
The first rod member group and the second rod member group are respectively provided with a plurality of rod members, and the number of the rod members in the first rod member group is equal to that of the rod members in the second rod member group.
The application has the beneficial effects that:
1. The airframe adopts a truss end plate structure, and the rigidity of the airframe truss is adjusted by utilizing a rigidity adjusting piece;
2. the front and the back of the machine body are end plates which are used as mounting bases of tail beams, power parts and the like, so that the rigidity is high and the stability is good;
3. The left side and the right side of the machine body adopt trusses, and the trusses are of plane or space structures formed by straight rods, and the truss rod members bear axial tension or pressure, so that the strength of materials can be fully utilized, more materials are saved compared with the plate frame structure, the dead weight is greatly reduced, the rigidity is increased, and the purpose of light weight is realized;
4. the rigidity adjusting piece is perpendicular to the trusses on two sides of the machine body, and is provided with screw rods with opposite threads on two sides, and the supporting rigidity of the trusses is improved through the screw rods.
Drawings
Fig. 1 is a simplified diagram of forces during flight of an unmanned aerial vehicle.
Fig. 2 is a simplified force diagram of a lightweight adjustable stiffness truss type unmanned aerial vehicle fuselage.
Fig. 3 is a schematic view of the connection of a fuselage section of an unmanned aircraft to other components of the aircraft.
Fig. 4 is a schematic view of a fuselage section of a truss type unmanned aerial vehicle.
Fig. 5 is a perspective view of a fuselage section of the truss type unmanned aerial vehicle.
Detailed Description
Reference numeral 100, main rotor shaft, 1, rigidity adjusting piece, 101, left connector, 102, right connector, 103, screw rod, 2, fuselage truss, 201, left truss, 202, right truss, 3, front fixing plate, 4, rear fixing plate, 300, tail spar, 400 and landing gear.
The application is described in further detail below with reference to the drawings and examples. The specific embodiments of the application described herein are to be considered in an illustrative rather than a restrictive sense, and are intended to be illustrative of the application. It should be further noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The application will be described in detail below with reference to the drawings in connection with embodiments. The application will now be further described with reference to the drawings and examples.
As shown in fig. 1, the unmanned aerial vehicle receives external forces in three directions in the process of flying, steering and lifting, the unmanned aerial vehicle receives a vertical torsional force M1 along the left-right direction, a overturning torsional force M2 along the front-back direction, a horizontal torsional force M3 along the front-back direction, and the magnitudes of the three external forces are dynamically changed and synthesized.
As shown in fig. 2, the unmanned aerial vehicle receives forces in three directions in space mainly borne by the aircraft fuselage, and the unmanned aerial vehicle fuselage of the present application adopts a truss structure, so that the unmanned aerial vehicle fuselage of the present application receives external forces in three directions as well, namely, the unmanned aerial vehicle fuselage receives vertical torsion force M11 in the left-right direction, overturning torsion force M21 in the front-back direction, horizontal torsion force M31 in the front-back direction, and the magnitudes of the above three external forces are dynamically changed and synthesized.
As shown in fig. 3, the connection structure of the fuselage section of the man-machine according to the present application with other components of the aircraft is schematically shown, the end of the fuselage truss 2 is fixedly connected with the front fixing plate 3, the rear end of the fuselage truss 2 is fixedly connected with the rear fixing plate 4, the rear fixing plate 4 fixes the tail spar 300, the front fixing plate 3 fixes the engine of the unmanned aerial vehicle, the main rotor shaft 100 is disposed on the engine, the front and rear ends of the landing gear 400 are respectively fixed on the front and rear parts of the fuselage truss 2, and the fuselage truss 2 bears the force applied by the unmanned aerial vehicle.
As shown in fig. 2-4, the light-weight rigidity-adjustable truss type airframe comprises an airframe truss 2, a rigidity adjusting piece 1, a front fixing plate 3 and a rear fixing plate 4, wherein the airframe truss 2 comprises a left truss 201 and a right truss 202, two ends of the rigidity adjusting piece 1 are fixedly connected with the left truss 201 and the right truss 202, and the fixing positions of the rigidity adjusting piece and the left truss 201 and the right truss 202 are adjustable.
As shown in fig. 4-5, the left truss 201 of the unmanned aerial vehicle is a first rod group and a right truss 202 of the unmanned aerial vehicle are arranged along the front-back direction, the rods are parallel to each other, the first rod group and the second rod group are composed of three rods, two ends of the rigidity adjusting piece 1 are fixedly connected with two adjacent rods in the first rod group and the second rod group, one rod in the first rod group and the second rod group is not fixedly connected with the rigidity adjusting piece 1, on one hand, the left rod in the first rod group and the right rod group is used for ensuring the relative positions of the front fixing plate 3 and the rear fixing plate 4, and on the other hand, the rigidity adjusting piece 1 is adjustable in length to prevent the deformation of the body truss 2 after the rigidity adjusting piece 1 is adjusted to be shortened; on the other hand, the rigidity adjusting part 1 only needs to be fixedly connected with part of rods in the rod group II and the rod group I, so that the rigidity of the airframe truss can be met.
As shown in fig. 4-5, the rigidity adjusting part 1 comprises a left connector 101, a right connector 102 and a screw rod 103, studs are arranged on two sides of the screw rod 103, the studs on two sides are in opposite screwing directions, the studs on two sides are respectively in threaded connection with threaded inner holes of the left connector 101 and the right connector 102, the left connector 101 and the right connector 102 are respectively fixed with a left truss 201 and a right truss 202, a regular hexagonal prism is arranged in the middle of the screw rod 103 and used for clamping the screw rod 103 by a wrench, and the screw rod 103 is rotated to relax or tighten the left truss 201 and the right truss 202, so that the left truss 201 and the right truss 202 are in a pre-tightening state, and rigidity and stability of the left truss 201 and the right truss 202 are improved.
As shown in fig. 5, the rigidity adjusting part 1 further includes a left buckling plate 1013 and a right buckling plate, the left connector 101 is in a T shape, a vertical side of the T shape is in threaded connection with a left end of the screw rod 103, two or more grooves first 1014 for accommodating the left truss 201 are provided on a horizontal side of the T shape of the left connector 101, a second 1011 is provided on a position corresponding to the first 1014, the first 1014 is opposite to the second 1011 for clamping a rod of the left truss 201, bolt holes 1012 are provided between the first 1014 and the second 1011 and at ends of the first 1014 and the second 1011, bolts 1013 are provided in the bolt holes 1012 for locking the left buckling plate 1013 and clamping the rod of the left truss 201, the rods of the left truss 201 and the right truss 202 are cylindrical, and the first 1014 and the second 1011 are semicircular.
The structure of the right connector 102 and the right buckling plate for fixing the right truss 202 is the same as the structure of the left connector 101 and the left buckling plate 101 for fixing the left truss 201. Namely, the right connector 102 and the right buckling plate are bilaterally symmetrical about the bilateral symmetry plane of the front fixing plate 3.
The application aims to reduce the weight of a fuselage by utilizing a fuselage truss 2, and adjust the rigidity of the truss by utilizing an adjustable fulcrum assembly so as to adapt to different load conditions. The airframe adopts a truss end plate structure, and the rigidity of the airframe is adjusted by utilizing an adjustable torsion-resistant fulcrum component; the front and the back of the machine body are end plates which are used as mounting bases of tail beams, power parts and the like, so that the rigidity is high and the stability is good; the left side and the right side of the machine body adopt trusses, and the trusses are of plane or space structures formed by straight rods, and the truss rod members bear axial tension or pressure, so that the strength of materials can be fully utilized, more materials are saved compared with the plate frame structure, the dead weight is greatly reduced, the rigidity is increased, and the light weight purpose is realized; the adjustable torsion-resistant fulcrum component is arranged perpendicular to the truss and is provided with a positive and negative bidirectional screw adjusting device, and the truss 2 is pre-tensioned through the adjusting screw 103, so that the rigidity and stability of the truss of the machine body are improved; the rigidity adjusting part 1 can be further widened by changing the position and increasing or decreasing the number of the left truss 201 and the right truss 202 fixing bars, so that the rigidity adjusting device can be better and wider for application under different loads.
The flying process of the unmanned aerial vehicle is different from the movement of the object on the plane, the stress of the frame is three-dimensional and random in the flying process, and the stability and the reliability of the frame of the machine body are important guarantee of flying safety. The forces received in the flight process are forces and moments in front and back, left and right, up and down, which makes the stress of the airframe particularly complex, thereby requiring higher strength and rigidity of the airframe; an important index affecting the flight performance is the weight of the component, and in order to ensure the performance of the fuselage in general, a plate-frame structure is often adopted to ensure the strength of the fuselage, but the weight of the fuselage is overlarge, and the plate-frame structure also adopts the form of a weight-reducing hole to reduce the weight, but the weight-reducing effect is not obvious due to the limitations in the aspects of the structure, the strength requirement, the gravity center and the like; from unmanned aerial vehicle's load condition, the load of each time flight is not only the same, and the focus is also inconsistent, and from the lightweight, the fuselage is the lightest possible, and rigidity and intensity just do not necessarily be fit for the load condition under the mission of each time, through the adjustable antitorque fulcrum subassembly of facility, adjust the intensity and the rigidity of fuselage. According to the load condition, the number of the rods of the left truss 201 and the right truss 202 is increased or reduced at different positions, and the rods of the left truss 201 and the right truss 202 are expanded or tensioned differently, so that the requirements on the strength and the rigidity of the unmanned aerial vehicle under different loads and complex flight conditions are met, and as the main components of the unmanned aerial vehicle are the rods of the left truss 201 and the right truss 202, the weight of the unmanned aerial vehicle is greatly reduced, and the flight performance of the unmanned aerial vehicle is effectively improved.
According to the lightweight truss type unmanned aerial vehicle body, in the use process, the truss type unmanned aerial vehicle body can be used with a power part, a landing gear or other hanging frames according to requirements, and preferably, the number of the left side trusses 201 and the right side trusses 202 in the truss type unmanned aerial vehicle body or the fixed positions of the truss type unmanned aerial vehicle body and the rigidity adjusting parts 1 can be adjusted according to loads or flight tasks, so that the performance of the unmanned aerial vehicle body is further improved, and the flight performance and reliability of the unmanned aerial vehicle are improved.
The above description is only illustrative of the preferred embodiments of the present application and of the principles of the technology employed. It will be appreciated by persons skilled in the art that the scope of the application is not limited to the specific combinations of the features described above, but also covers other embodiments which may be formed by any combination of the features described above or their equivalents without departing from the spirit of the application. Such as the above-mentioned features and the technical features disclosed in the present application but not limited to those having similar functions are replaced with each other.
Claims (6)
1. Light-weight rigidity-adjustable truss type unmanned aerial vehicle body is characterized in that: the light-weight rigidity-adjustable truss type unmanned aerial vehicle body comprises a body truss (2), wherein the body truss (2) comprises a left truss (201) and a right truss (202), two ends of a rigidity adjusting piece (1) are fixedly connected with the left truss (201) and the right truss (202), and the fixing positions of the rigidity adjusting piece and the left truss (201) and the right truss (202) are adjustable;
the left truss (201) of the unmanned aerial vehicle is a first rod set arranged along the front-back direction, the right truss (202) of the unmanned aerial vehicle is a second rod set arranged along the front-back direction, the first rod set and the second rod set are arranged in parallel, and two ends of the rigidity adjusting piece (1) are fixedly connected with the first rod set and the second rod set respectively;
the two ends of the rigidity adjusting piece (1) are fixedly connected with the rod pieces in the first rod piece group and the second rod piece group, and at least one rod piece of each of the first rod piece group and the second rod piece group is not fixedly connected with the rigidity adjusting piece (1);
The rigidity adjusting piece (1) comprises a left connector (101), a right connector (102) and a screw rod (103), wherein studs are arranged on two sides of the screw rod (103), the threads of the studs on two sides are opposite in rotation, the studs on two sides are respectively connected with the threads of the left connector (101) and the right connector (102), and the left connector (101) and the right connector (102) are respectively fixed with a left truss (201) and a right truss (202);
The rigidity adjusting part (1) further comprises a left buckling plate (1013), a right buckling plate, a left connecting head (101) is in a T shape, the vertical edge of the T shape is in threaded connection with the left end of a screw rod (103), two or more grooves I (1014) for accommodating a left truss (201) are formed in the T-shaped horizontal edge of the left connecting head (101), grooves II (1011) are formed in the positions, corresponding to the grooves I (1013), of the left buckling plate (1013), the grooves I (1014) are oppositely arranged with the grooves II (1011) and are used for clamping rods of the left truss (201), bolt holes (1012) are formed in the grooves I (1014) and the grooves II (1011) and are formed in the ends of the grooves, bolts are used for locking the left buckling plate (1013) and clamping rods of the left truss (201), and the structures of the right connecting head (102) and the right buckling plate are identical to those of the left connecting head (101) and the left buckling plate (1013) for fixing the left truss (201).
2. The lightweight, stiffness-adjustable truss type unmanned aerial vehicle fuselage of claim 1, wherein: the rods in the first rod member set are arranged in parallel, and the rods in the second rod member set are arranged in parallel.
3. The lightweight, stiffness-adjustable truss type unmanned aerial vehicle fuselage of claim 1, wherein: the middle part of the screw rod (103) is provided with a regular hexagonal prism used for clamping the screw rod (103) by a spanner.
4. The lightweight, stiffness-adjustable truss type unmanned aerial vehicle fuselage of claim 1, wherein: the rod pieces of the left truss (201) and the right truss (202) are cylindrical, and the groove I (1014) and the groove II (1011) are semicircular.
5. The lightweight, stiffness-adjustable truss type unmanned aerial vehicle fuselage of any of claims 1-4, wherein: the front end of the fuselage truss (2) is fixedly connected with the front fixing plate (3), the rear end of the fuselage truss (2) is fixedly connected with the rear fixing plate (4), the rear fixing plate (4) is used for fixing the tail spar (300), the front fixing plate (3) is used for fixing an unmanned aerial vehicle engine, a main rotor shaft (100) is arranged on the engine, and the front end and the rear end of the fuselage truss (2) are respectively used for fixing the front end and the rear end of the landing gear (400).
6. The lightweight, stiffness-adjustable truss type unmanned aerial vehicle fuselage of any of claims 1-4, wherein: the first rod member group and the second rod member group are respectively provided with a plurality of rod members, and the number of the rod members in the first rod member group is equal to that of the rod members in the second rod member group.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810014657.1A CN107933875B (en) | 2018-01-08 | 2018-01-08 | Truss type unmanned aerial vehicle fuselage with light-weight and rigidity adjustable |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810014657.1A CN107933875B (en) | 2018-01-08 | 2018-01-08 | Truss type unmanned aerial vehicle fuselage with light-weight and rigidity adjustable |
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| CN107933875A CN107933875A (en) | 2018-04-20 |
| CN107933875B true CN107933875B (en) | 2024-06-07 |
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| CN201810014657.1A Active CN107933875B (en) | 2018-01-08 | 2018-01-08 | Truss type unmanned aerial vehicle fuselage with light-weight and rigidity adjustable |
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| CN109255144B (en) * | 2018-07-09 | 2021-11-23 | 南京航空航天大学 | Lightweight design method for brake component of undercarriage |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7891608B2 (en) * | 2007-05-03 | 2011-02-22 | The Boeing Company | Space frame fuselage structure and related methods |
| US9308988B2 (en) * | 2013-01-16 | 2016-04-12 | Otto Aviation Group | Aircraft main landing gear and method of operating the same |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB128651A (en) * | 1917-08-23 | 1919-07-03 | James Jacob Mayrow | Improvements in Connection with the Fuselages of Aeronautical Machines. |
| US4641477A (en) * | 1986-01-06 | 1987-02-10 | Schleck Herman A | Adjustable modular building |
| CN106507751B (en) * | 2007-11-03 | 2011-11-23 | 成都飞机工业（集团）有限责任公司 | SUAV fuselage |
| CN102139757A (en) * | 2010-07-28 | 2011-08-03 | 北京航空航天大学 | Framed front center fuselage suitable for unmanned plane and model plane |
| CN104386239A (en) * | 2014-11-04 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Rollover prevention airframe steel framework structure |
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| CN207843296U (en) * | 2018-01-08 | 2018-09-11 | 安阳全丰航空植保科技股份有限公司 | Rigidity truss-like unmanned aerial vehicle body is adjusted in lightweight |
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|---|---|
| CN107933875A (en) | 2018-04-20 |
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