CN209080175U - A kind of aircraft film fuel tank - Google Patents
A kind of aircraft film fuel tank Download PDFInfo
- Publication number
- CN209080175U CN209080175U CN201821802425.4U CN201821802425U CN209080175U CN 209080175 U CN209080175 U CN 209080175U CN 201821802425 U CN201821802425 U CN 201821802425U CN 209080175 U CN209080175 U CN 209080175U
- Authority
- CN
- China
- Prior art keywords
- oil tank
- fuel tank
- oil
- tank
- pipe sleeve
- 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.)
- Expired - Fee Related
Links
- 239000002828 fuel tank Substances 0.000 title claims abstract description 34
- 239000000853 adhesive Substances 0.000 claims abstract description 6
- 230000001070 adhesive effect Effects 0.000 claims abstract description 6
- 239000010408 film Substances 0.000 claims description 31
- 239000010409 thin film Substances 0.000 claims description 29
- 239000012528 membrane Substances 0.000 claims description 8
- 229920001971 elastomer Polymers 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 2
- 239000003921 oil Substances 0.000 abstract description 135
- 239000000295 fuel oil Substances 0.000 abstract description 12
- 230000000694 effects Effects 0.000 abstract description 4
- 239000000446 fuel Substances 0.000 description 18
- 108010066057 cabin-1 Proteins 0.000 description 6
- 239000002699 waste material Substances 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- CBENFWSGALASAD-UHFFFAOYSA-N Ozone Chemical compound [O-][O+]=O CBENFWSGALASAD-UHFFFAOYSA-N 0.000 description 1
- 239000004433 Thermoplastic polyurethane Substances 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 229920002803 thermoplastic polyurethane Polymers 0.000 description 1
Landscapes
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The utility model discloses a kind of aircraft film fuel tanks, including tank bay, the inside of the tank bay offers fuel tank chamber, the fuel tank chamber is internally provided with film fuel tank, the center position on the tank bay top is equipped with oil inlet pipe sleeve, the oil inlet pipe sleeve is fixedly connected by adhesive with film fuel tank, and oil inlet pipe sleeve is connected with fuel tank cap far from the threaded one end of film fuel tank, the center position of the tank bay bottom end is equipped with outlet pipe sleeve, the section of fuel tank chamber on the aircraft film fuel tank is semicircle, and inner wall is smoother, minimum angle is mostly right angle simultaneously, film fuel tank can be made when inside is full of fuel oil, it can be very good to be attached on fuel tank chamber, and gas vent is offered on tank bay, when fuel tank refuels, fuel tank bottom end is improper to increase, and the air of the intracavitary bottom of fuel tank is dishonoured and is squeezed out upward , achieve the effect that mutually to fit closely with fuel tank chamber, substantially increase the space utilization rate of fuel tank chamber.
Description
Technical Field
The utility model relates to an aviation fuel feeding technical field specifically is an airborne vehicle film oil tank.
Background
The thin film oil tank is generally a PUR-T elastic soft oil tank, the material of the thin film oil tank is thermoplastic polyurethane, the oil tank has excellent wear resistance and oil resistance, and has enough resistance to oxygen, ozone, radiation and the like, and the thin film oil tank is mostly used for aircrafts, has strong environmental adaptation, long service life and low maintenance cost, but the existing thin film oil tank for aircrafts still has some defects in the use process.
When the conventional thin-film oil tank is filled with oil, the air is remained in the oil tank cabin, so that the oil tank cabin is poor in bonding performance, and the space of the oil tank cabin is greatly wasted; when the common thin-film oil tank discharges oil, the oil is easy to discharge incompletely, and dead oil exists in the thin film, so that the overall quality of the whole fuel oil is influenced; when the fuel tank works normally, fuel is easy to spill from the vent pipe due to aircraft overload, fuel waste is caused, and the like.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide an aircraft film oil tank to solve the problems that the prior art provided by the background art has poor fitting performance with an oil tank cabin due to air remained in the oil tank cabin, and the space of the oil tank cabin is greatly wasted; during oil drainage, incomplete oil drainage is easily caused, and dead oil exists in the film, so that the overall quality of the whole fuel oil is influenced; the problem of fuel waste is caused by the fact that fuel is easy to spill out of a vent pipe due to overload of an airplane.
In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an aircraft film oil tank, includes the oil tank cabin, the oil tank chamber has been seted up to the inside of oil tank cabin, the inside in oil tank chamber is provided with the film oil tank, the central point on oil tank cabin top puts the department and installs the oil feed pipe box, the oil feed pipe box passes through adhesive and film oil tank fixed connection, and the one end threaded connection that the film oil tank was kept away from to the oil feed pipe box has the oil tank lid, the central point department of oil tank cabin bottom installs out the oil pipe box, it passes through adhesive and film oil tank fixed connection to go out the oil pipe box, and goes out the one end that the film oil tank was kept away from to the oil pipe box and install out oil pipe, install the breather pipe on the lateral wall of oil feed pipe box, the breather pipe,
a butterfly plate is arranged inside the vent pipe and is rotationally connected with the vent pipe through a rotating shaft, a first stop block is arranged at a position, close to the oil inlet pipe sleeve, on one side of the butterfly plate, a second stop block is arranged at a position, far away from the oil inlet pipe sleeve, on one side of the butterfly plate, and the first stop block and the second stop block are both welded on the inner wall of the vent pipe;
the utility model discloses a breather pipe, including breather pipe, butterfly plate, driving gear, pendulum rod, balance weight wheel, driven gear, drive gear, breather pipe, driven gear, pivot and breather pipe swivelling joint, the outer wall of breather pipe and the corresponding position department of axis of rotation on the butterfly plate install driven gear, one side meshing of driven gear is connected with the driving gear, the driving gear is through pivot and breather pipe swivelling joint, the welding has the pendulum rod on the one side body wall of breather pipe is kept away from to the driving gear, the one.
Preferably, the cross section of the oil tank cavity is of a semicircular structure.
Preferably, the vent hole has been seted up on the lateral wall of fuel tank cabin and near the top of film oil tank, the vent hole is provided with two, and two vent holes set up about the axis symmetry of fuel tank cabin respectively.
Preferably, the distance between the first stop block and the second stop block is equal to the thickness of the butterfly plate, and rubber pads are arranged on the side walls, close to the butterfly plate, of the first stop block and the second stop block.
Preferably, the inner wall of the support cover is of an arc-shaped structure, and the counterweight wheel and the support cover form a sliding structure.
Preferably, the radius value of the driving gear is larger than that of the driven gear.
Preferably, a rotating plate is installed on the other side of the rotating shaft of the driven gear, a fixing plate is installed on the side wall of the vent pipe, the top end of the side wall of the vent pipe is close to the rotating plate, and the rotating plate is perpendicular to the butterfly plate.
Compared with the prior art, the beneficial effects of the utility model are that: this aircraft membrane tank:
1. the cross-section of this fuel tank chamber on the airborne vehicle film oil tank is semi-circular, and the inner wall is more level and smooth, and minimum contained angle is mostly the right angle simultaneously, can be so that the film oil tank when being full of the fuel in inside, can be fine paste on the fuel tank chamber, and the exhaust hole has been seted up on the fuel tank cabin, when the oil tank refuels, the increase is not held to the oil tank bottom, and extrude the air of fuel tank intracavity bottom not holding the top, reach the effect of closely laminating mutually with the fuel tank chamber, the space utilization in fuel tank chamber has been improved greatly.
2. This aircraft film oil tank's oil tank chamber bottom is owing to be the arcuation, demonstrate certain slope, when the oil discharge, the fuel can flow down along the film oil tank, make the fuel that is close to film department be in the state of flowing, the film is when not holding to reduce simultaneously, the exhaust hole also can be with during the oil tank chamber is inhaled to the outside air, make inside and outside atmospheric pressure equal, the air current also can promote the top of film, make the fuel in the film oil tank flow as far as, the dead oil phenomenon has been avoided existing, the holistic quality of fuel has been maintained greatly.
3. Install the butterfly plate in this aircraft film oil tank's the breather pipe, when the aircraft transships, when the slope takes place, the counter weight wheel that is close to minimum incline direction can take place to slide because of the dead weight, the pendulum rod swing simultaneously, it is rotatory to drive the driving gear, the driving gear drives driven gear rotatory, thereby make the butterfly plate take place to rotate, and hug closely on the dog lateral wall in the front and back, avoid the fuel owing to rock and splash flow to the breather pipe on, play the effect that blocks, when treating the aircraft recovery balanced navigation, in the film oil tank is flowed back to the fuel on the breather pipe, fuel leakage has been avoided and lead to extravag.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a partial enlarged view of a butterfly plate at A of the present invention;
FIG. 3 is a front view of the present invention;
FIG. 4 is a partial enlarged view of the driving gear at B of the present invention;
FIG. 5 is a diagram illustrating the physical effect of the stopper of the present invention;
FIG. 6 is a schematic side view of the present invention;
fig. 7 is a schematic diagram of the structure of the fixing plate of the present invention.
In the figure: 1. the oil tank comprises an oil tank cabin, 2, an oil tank cavity, 3, a thin film oil tank, 4, an exhaust hole, 5, an oil outlet pipe sleeve, 6, an oil outlet pipe, 7, an oil inlet pipe sleeve, 8, an oil tank cover, 9, a vent pipe, 10, a butterfly plate, 11, a first stop block, 12, a second stop block, 13, a counterweight wheel, 14, a support cover, 15, a driven gear, 16, a swing rod, 17, a driving gear, 18, a rotating plate, 19 and a fixing plate.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-7, the present invention provides a technical solution: an aircraft film oil tank comprises an oil tank cabin 1, an oil tank cavity 2, a film oil tank 3, exhaust holes 4, an oil outlet pipe sleeve 5, an oil outlet pipe 6, an oil inlet pipe sleeve 7, an oil tank cover 8, a vent pipe 9, a butterfly plate 10, a first stop block 11, a second stop block 12, a counterweight wheel 13, a support cover 14, a driven gear 15, a swing rod 16, a driving gear 17, a rotating plate 18 and a fixing plate 19, wherein the oil tank cavity 2 is arranged inside the oil tank cabin 1, the exhaust holes 4 are arranged on the side wall of the oil tank cabin 1 and close to the top end of the film oil tank 3, the two exhaust holes 4 are symmetrically arranged relative to the central axis of the oil tank cabin 1 respectively, when oil is added into the film oil tank 3, the film oil tank 3 is not increased from the bottom end, the air at the bottom in the oil tank cavity 2 is not extruded upwards, and is exhausted from the exhaust holes 4, so that the film oil tank 3 can be tightly attached to the inner wall of the, the thin film oil tank 3 is arranged in the oil tank cavity 2, the cross section of the oil tank cavity 2 is of a semicircular structure, the inner wall of the oil tank cavity is smooth, the minimum included angle is a right angle, the thin film oil tank 3 can be well attached to the oil tank cavity when being filled with fuel oil, the bottom end of the oil tank cavity is arc-shaped and presents a certain gradient, the fuel oil can flow downwards along the thin film oil tank when oil is discharged, the fuel oil close to the thin film is in a flowing state, the phenomenon of dead oil is avoided, the integral quality of the fuel oil is greatly maintained, the central position of the top end of the oil tank cabin 1 is provided with the oil inlet pipe sleeve 7, the oil inlet pipe sleeve 7 is fixedly connected with the thin film oil tank 3 through an adhesive, one end of the oil inlet pipe sleeve 7, far away from the thin film oil tank 3, is in threaded connection with the oil tank cover 8, the central position of the bottom end of the oil tank cabin, an oil outlet pipe 6 is arranged at one end of the oil outlet pipe sleeve 5 far away from the thin film oil tank 3, two vent pipes 9 are arranged on the side wall of the oil inlet pipe sleeve 7, the two vent pipes 9 are symmetrically arranged at the central position of the oil inlet pipe sleeve 7, wherein,
a butterfly plate 10 is installed inside the vent pipe 9, the butterfly plate 10 is rotatably connected with the vent pipe 9 through a rotating shaft, a first stop block 11 is installed at a position, close to the oil inlet pipe sleeve 7, on one side of the butterfly plate 10, a distance between the first stop block 11 and the second stop block 12 is equal to the thickness of the butterfly plate 10, rubber gaskets are installed on side walls, close to the butterfly plate 10, of the first stop block 11 and the second stop block 12, when the butterfly plate 10 rotates, one side of the butterfly plate abuts against the first stop block 11, the other side of the butterfly plate abuts against the second stop block 12, meanwhile, due to the sealing performance of the rubber gaskets, fuel oil can be prevented from flowing out of a gap between the butterfly plate 10 and the first stop block 11 as well as the second stop block 12, the second stop block 12 is installed at a position, far away from the oil inlet pipe sleeve 7, on one side of the butterfly plate 10, and the first stop block 11 and the;
the outer wall of the vent pipe 9 and the position corresponding to the rotating shaft on the butterfly plate 10 are provided with a driven gear 15, the other side of the rotating shaft of the driven gear 15 is provided with a rotating plate 18, the side wall of the vent pipe 9 is provided with a fixed plate 19 near the top end of the rotating plate 18, the rotating plate 18 is perpendicular to the butterfly plate 10, when the aircraft is overloaded, the counterweight wheel 13 near the highest inclination direction swings, when the driven gear 15 is driven by the driving gear 17 to rotate in a meshing manner, the butterfly plate 10 at the center of the rotating shaft of the driven gear 15 cannot rotate because the rotating plate 18 at the edge of the rotating shaft of the driven gear 15 is supported by the fixed plate 19 at one side, so that the vent pipe 9 is not sealed, the internal and external balance between the thin film oil tank 3 and the external air pressure is achieved, one side of the driven gear 15 is meshed with the driving gear 17, and the, the driving gear 17 and the driven gear 15 form an accelerator structure, so that even if the weight wheel 13 swings to a small angle, the butterfly plate 10 can respectively abut against the first stop block 11 and the second stop block 12 due to a large rotation angle, so as to play a role of blocking, the driving gear 17 is rotatably connected with the vent pipe 9 through a rotating shaft, a swing rod 16 is welded on one side body wall of the driving gear 17 away from the vent pipe 9, the weight wheel 13 is installed at one end of the swing rod 16 away from the driving gear 17, a support cover 14 is welded at a position, corresponding to the weight wheel 13, of the bottom end of the vent pipe 9, the inner wall of the support cover 14 is of an arc-shaped structure, the weight wheel 13 and the support cover 14 form a sliding structure, the support cover 14 plays a role of a sliding rail, and simultaneously limits the sliding direction of the weight wheel 13, so as to avoid the weight wheel 13 from being not parallel to, resulting in loosening and causing potential safety hazards.
The working principle is as follows: when the utility model is used, a user can unscrew the oil tank cover 8 and add oil into the thin film oil tank 3, because the section of the oil tank cavity 2 is semicircular, the inner wall is smooth, and the minimum included angle is mostly a right angle, when the thin film oil tank 3 is filled with fuel oil inside, the thin film oil tank can be well pasted on the oil tank cavity 2, and the oil tank cabin 1 is provided with the vent hole 4, the bottom end of the thin film oil tank 3 is not enlarged, and the air at the bottom in the oil tank cavity 2 is not extruded upwards, thereby achieving the effect of being tightly pasted with the oil tank cavity 2, greatly improving the space utilization rate of the oil tank cavity, when oil is discharged, because the bottom end of the oil tank cavity 2 is arc-shaped, presenting a certain gradient, the fuel oil can flow downwards in the thin film oil tank 3, the fuel oil near the thin film is in a flowing state, and simultaneously, the vent hole 4 can also suck the external air into the oil tank cavity, the internal and external air pressures are equal, the airflow can push the top end of the film, so that the fuel in the film fuel tank 3 can flow out as much as possible, the phenomenon of dead fuel is avoided, the integral quality of the fuel is greatly maintained, when the airplane is overloaded, the counterweight wheel 13 close to the lowest inclination direction can slide on the support cover 14 due to the dead weight, the swing rod 16 swings to drive the driving gear 17 to rotate, the driving gear 17 drives the driven gear 15 to rotate, so that the butterfly plate 10 rotates and is tightly attached to the side walls of the first stop block 11 and the second stop block 12, the fuel is prevented from splashing on the vent pipe due to shaking, the blocking effect is achieved, when the airplane returns to the film fuel tank 3 when balanced navigation is carried out, the fuel is prevented from leaking and causing waste, meanwhile, the counterweight wheel 13 close to the highest inclination direction swings, and when the driving driven gear 15 is driven to rotate in a meshed manner through the driving gear 17, because the rotating plate 18 at the edge of the rotating shaft of the driven gear 15 is abutted by the fixing plate 19 at one side, the butterfly plate 10 at the center of the rotating shaft of the driven gear 15 cannot rotate, the vent pipe 9 is not sealed, the internal and external balance between the thin film oil tank 3 and the external air pressure is achieved, and the whole working process of the thin film oil tank of the aircraft is finished. Those not described in detail in this specification are within the skill of the art.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the invention.
Claims (7)
1. An aircraft membrane tank comprising a tank compartment (1), characterized in that: the oil tank comprises an oil tank cabin (1), wherein an oil tank cavity (2) is formed in the oil tank cabin (1), a thin film oil tank (3) is arranged in the oil tank cavity (2), an oil inlet pipe sleeve (7) is installed at the central position of the top end of the oil tank cabin (1), the oil inlet pipe sleeve (7) is fixedly connected with the thin film oil tank (3) through an adhesive, a tank cover (8) is connected to one end, away from the thin film oil tank (3), of the oil inlet pipe sleeve (7) through a thread, an oil outlet pipe sleeve (5) is installed at the central position of the bottom end of the oil tank cabin (1), the oil outlet pipe sleeve (5) is fixedly connected with the thin film oil tank (3) through the adhesive, an oil outlet pipe (6) is installed at one end, away from the thin film oil tank (3), of the oil outlet pipe sleeve (5) is installed on the side wall of the oil inlet pipe sleeve (7), two vent pipes (9, wherein,
a butterfly plate (10) is mounted inside the vent pipe (9), the butterfly plate (10) is rotatably connected with the vent pipe (9) through a rotating shaft, a first stop block (11) is mounted at a position, close to the oil inlet pipe sleeve (7), on one side of the butterfly plate (10), a second stop block (12) is mounted at a position, far away from the oil inlet pipe sleeve (7), on one side of the butterfly plate (10), and the first stop block (11) and the second stop block (12) are both welded on the inner wall of the vent pipe (9);
the utility model discloses a breather pipe, including breather pipe (9), drive gear (17), breather pipe (9), swing rod (16) have been welded on one side body wall that breather pipe (9) was kept away from in drive gear (17), swing rod (16) are installed to the one end that drive gear (17) were kept away from in swing rod (16), balance weight wheel (13) are installed to the bottom of breather pipe (9) and the welding of balance weight wheel (13) corresponding position department have support cover (14).
2. An aircraft membrane fuel tank as claimed in claim 1, wherein: the section of the oil tank cavity (2) is of a semicircular structure.
3. An aircraft membrane fuel tank as claimed in claim 1, wherein: exhaust hole (4) have been seted up on the lateral wall of oil tank cabin (1) and near the top of film oil tank (3), exhaust hole (4) are provided with two, and two exhaust holes (4) are respectively about the axis symmetry setting of oil tank cabin (1).
4. An aircraft membrane fuel tank as claimed in claim 1, wherein: the distance between the first stop block (11) and the second stop block (12) is equal to the thickness of the butterfly plate (10), and rubber pads are arranged on the side walls, close to the butterfly plate (10), of the first stop block (11) and the second stop block (12).
5. An aircraft membrane fuel tank as claimed in claim 1, wherein: the inner wall of the support cover (14) is of an arc-shaped structure, and the counterweight wheel (13) and the support cover (14) form a sliding structure.
6. An aircraft membrane fuel tank as claimed in claim 1, wherein: the radius value of the driving gear (17) is larger than that of the driven gear (15).
7. An aircraft membrane fuel tank as claimed in claim 1, wherein: a rotating plate (18) is installed on the other side of the rotating shaft of the driven gear (15), a fixing plate (19) is installed on the side wall of the vent pipe (9) close to the top end of the rotating plate (18), and the rotating plate (18) is perpendicular to the butterfly plate (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821802425.4U CN209080175U (en) | 2018-11-02 | 2018-11-02 | A kind of aircraft film fuel tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821802425.4U CN209080175U (en) | 2018-11-02 | 2018-11-02 | A kind of aircraft film fuel tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209080175U true CN209080175U (en) | 2019-07-09 |
Family
ID=67122272
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821802425.4U Expired - Fee Related CN209080175U (en) | 2018-11-02 | 2018-11-02 | A kind of aircraft film fuel tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209080175U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113401798A (en) * | 2021-07-21 | 2021-09-17 | 江南造船(集团)有限责任公司 | Method for determining hoisting scheme of rhombic liquid tank |
| CN116353836A (en) * | 2023-04-19 | 2023-06-30 | 南京儒一航空机械装备有限公司 | Pressure maintaining oil tank for aircraft |
-
2018
- 2018-11-02 CN CN201821802425.4U patent/CN209080175U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113401798A (en) * | 2021-07-21 | 2021-09-17 | 江南造船(集团)有限责任公司 | Method for determining hoisting scheme of rhombic liquid tank |
| CN116353836A (en) * | 2023-04-19 | 2023-06-30 | 南京儒一航空机械装备有限公司 | Pressure maintaining oil tank for aircraft |
| CN116353836B (en) * | 2023-04-19 | 2023-09-29 | 南京儒一航空机械装备有限公司 | Pressure maintaining oil tank for aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190709 |