CN111216868A - Frame for aircraft and aircraft - Google Patents
Frame for aircraft and aircraft Download PDFInfo
- Publication number
- CN111216868A CN111216868A CN201910795375.4A CN201910795375A CN111216868A CN 111216868 A CN111216868 A CN 111216868A CN 201910795375 A CN201910795375 A CN 201910795375A CN 111216868 A CN111216868 A CN 111216868A
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- Prior art keywords
- frame
- arm
- fuselage
- aircraft
- horn
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- 239000000758 substrate Substances 0.000 claims description 21
- 239000003814 drug Substances 0.000 abstract description 5
- 238000009331 sowing Methods 0.000 abstract description 5
- 238000002360 preparation method Methods 0.000 abstract description 4
- 230000000007 visual effect Effects 0.000 description 13
- 238000005452 bending Methods 0.000 description 9
- 238000010586 diagram Methods 0.000 description 4
- 238000010030 laminating Methods 0.000 description 3
- 230000003014 reinforcing effect Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- 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
- B64C1/061—Frames
- B64C1/063—Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms
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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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Packaging Of Machine Parts And Wound Products (AREA)
- Catching Or Destruction (AREA)
Abstract
The invention provides a rack for an aircraft and the aircraft, and relates to the technical field of unmanned aerial vehicles and aircrafts. The existing agricultural plant protection unmanned aerial vehicle is provided with a medicine box or a sowing device through a carrying frame, and is provided with a battery through a battery frame. The unmanned aerial vehicle fuselage is owing to included year thing frame and battery frame, consequently need extend the back horn more of and preparation, and back horn length is longer then be difficult for reasonable folding structure that sets up. This a frame for aircraft in order to avoid back horn length overlength to lead to being difficult for setting up beta structure, sets up the linking arm between back horn and base plate, and the back horn passes through linking arm and base plate connection, has shortened the length of back horn like this, can realize the normal folding setting of back horn.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles and aircrafts, in particular to a rack for an aircraft and the aircraft.
Background
Unmanned aerial vehicle is a remote control or the aircraft of independent flight, and unmanned aerial vehicle includes aircraft and control station usually, and the aircraft includes fuselage, power device and navigation flight controller, but the loading tool carries out aerial work, but unmanned aerial vehicle wide application in fields such as industry, agriculture, military affairs now.
The agricultural plant protection unmanned aerial vehicle can be used for replacing manpower to carry out conventional agricultural operation in the air. The existing agricultural plant protection unmanned aerial vehicle is provided with a medicine box or a sowing device through a carrying frame, and is provided with a battery through a battery frame. The unmanned aerial vehicle fuselage is owing to included year thing frame and battery frame, consequently need extend the back horn more of and preparation, and back horn length is longer then be difficult for reasonable folding structure that sets up.
Disclosure of Invention
The invention aims to provide a frame for an aircraft and the aircraft, which aim to solve the problem that a folding structure is not easy to reasonably arrange due to a longer rear arm.
The invention provides a frame for an aircraft, comprising a fuselage, wherein the fuselage comprises a base plate, a front horn and a rear horn. And a connecting arm is arranged between the rear machine arm and the substrate.
Further, a machine body frame is arranged on one side of the rear machine arm of the base plate;
the rear machine arm is arranged on the machine body frame.
Furthermore, the connecting arm includes bending structure, bending structure includes frame support section and extension linkage segment, the frame support section sets up in the fuselage frame outside, it extends to fix in base plate central point to extend the linkage segment.
Further, the fuselage frame comprises a carrying frame and a battery frame, and the frame supporting section of the connecting arm is at least fixed on the outer side of the carrying frame.
Furthermore, the rear horn is connected with the connecting arm through a connecting piece, and the rear horn is foldable and assembled on the connecting arm through the connecting piece.
Furthermore, the rear machine arm is connected with the connecting arm and the machine body frame through a connecting piece.
Further, the connecting arm is a hollow pipe fitting.
Further, the connecting arm is a sectional type pipe fitting.
Furthermore, the sectional type pipe fitting comprises a first sleeve and a second sleeve, the first sleeve is fixedly connected with the base station through a connecting piece, the second sleeve is detachably connected with the first sleeve, and the connecting length of the second sleeve and the first sleeve is adjustable.
Furthermore, a reinforcing piece is further arranged on the connecting arm or the rear machine arm, and the reinforcing piece is at least connected with the battery frame.
Furthermore, one end of the connecting arm is fixedly connected with the base platform of the substrate through a locking piece.
Further, the substrate includes an upper substrate and a lower substrate, and the upper substrate and the lower substrate directly form an accommodating space for accommodating the electronic device.
The present application further provides an aircraft comprising the airframe according to any one of the above.
According to the rack for the aircraft, the connecting arm is arranged between the rear horn and the base plate, and the rear horn is connected with the base plate through the connecting arm, so that the length of the rear horn is shortened, and the normal folding arrangement of the rear horn can be realized.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic structural diagram of a airframe for an aircraft in accordance with an embodiment of the present invention;
FIG. 2 is a schematic loading diagram of a airframe for an aircraft provided by an embodiment of the present invention;
FIG. 3 is a schematic structural diagram illustrating a bottom view of a connecting arm for an aircraft frame according to an embodiment of the present invention;
fig. 4 is a schematic connection diagram of a connecting arm for an aircraft frame according to an embodiment of the present invention.
Icon: 10-a substrate; 11-front arm; 12-rear arm; 13-a carrier frame; 14-a battery frame; 20-a visual support; 30-a linker arm; 31-a connector; 101-lower substrate.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example one
The agricultural plant protection unmanned aerial vehicle can be used for replacing manpower to carry out conventional agricultural operation in the air. In the conventional agricultural plant protection unmanned aerial vehicle, a medicine box or a sowing device is mounted on a carrying frame 13, and a battery is mounted on a battery frame 14. The unmanned aerial vehicle fuselage is owing to included year thing frame 13 and battery frame 14, consequently need extend the back horn 12 longer of preparation, and the longer reasonable beta structure that then is difficult for to set up of back horn 12 length.
In order to solve the above problem, as shown in fig. 1 and fig. 2, the airframe for an aircraft provided in this embodiment includes a fuselage, the fuselage includes a base plate 10, a front horn 11 and a rear horn 12, and a connecting arm 30 is disposed between the rear horn 12 and the base plate 10.
In order to avoid that the rear arm 12 is too long to easily set a folding structure, the connecting arm 30 is arranged between the rear arm 12 and the base plate 10, and the rear arm 12 is connected with the base plate 10 through the connecting arm 30, so that the length of the rear arm 12 is shortened, and the normal folding setting of the rear arm 12 can be realized.
Example two
The connecting arm 30 is arranged between the rear machine arm 12 and the substrate 10, the degree of the connection between the rear machine arm 12 and the connecting arm 30 has high requirements, or the degree of the connection between the rear machine arm 12 and the connecting arm 30 is insufficient, and the connection relationship needs to be strengthened to ensure the stability of the machine body.
In order to solve the above problem, the rack for an aircraft provided by this embodiment includes a fuselage, where the fuselage includes a base plate 10, a front horn 11, and a rear horn 12, and the base plate 10 is provided with a fuselage frame on one side of the rear horn 12; a connecting arm 30 is arranged between the rear arm 12 and the base plate 10.
The rear arm 12 is also arranged on the fuselage frame.
Through the arrangement mode, the rear machine arm 12 is arranged on the connecting arm 30 and the machine body frame at the same time, so that the connection stability and the firmness of the rear machine arm 12 can be improved.
EXAMPLE III
The fuselage includes base plate 10, preceding horn 11 and back horn 12, base plate 10 is provided with the fuselage frame in back horn 12 one side, consequently, needs rationally set up the linking arm 30 structure in order to guarantee that linking arm 30 and fuselage are abundant the adaptation.
In order to solve the above problem, the rack for an aircraft provided by this embodiment includes a fuselage, where the fuselage includes a base plate 10, a front horn 11, and a rear horn 12, and the base plate 10 is provided with a fuselage frame on one side of the rear horn 12; a connecting arm 30 is arranged between the rear arm 12 and the base plate 10.
The rear arm 12 is also arranged on the fuselage frame.
The connecting arm 30 includes a bending structure, the bending structure includes a frame supporting section and an extending connecting section, the frame supporting section is disposed outside the frame of the body, and the extending connecting section extends and is fixed at the central position of the substrate 10.
Through setting linking arm 30 to bending structure, can set up longer frame support section in the fuselage frame outside to fully guarantee linking arm 30 and fuselage frame laminating fixed connection, the fuselage frame provides sufficient support to linking arm 30, and linking arm 30 also provides sufficient protection to the fuselage frame simultaneously, and the two combined action has guaranteed that back horn 12 is stably fixed on the fuselage, and back horn 12 also guarantees fuselage frame non-deformable.
Example four
Usually, the fuselage frame includes year thing frame 13 and battery frame 14, because year thing frame 13 is different with battery frame 14 structure appearance, and battery frame 14 width is less than year thing frame 13 usually, need make more reasonable setting to the structure of connecting arm 30 in order to guarantee that connecting arm 30 and fuselage are abundant to be adapted.
In order to solve the above problem, the rack for an aircraft provided by this embodiment includes a fuselage, where the fuselage includes a base plate 10, a front horn 11, and a rear horn 12, and the base plate 10 is provided with a fuselage frame on one side of the rear horn 12; a connecting arm 30 is arranged between the rear arm 12 and the base plate 10.
The rear arm 12 is also arranged on the fuselage frame.
The connecting arm 30 includes a bending structure, the bending structure includes a frame supporting section and an extending connecting section, the frame supporting section is disposed outside the frame of the body, and the extending connecting section extends and is fixed at the central position of the substrate 10.
The fuselage frame comprises a carrier frame 13 and a battery frame 14, and the frame support section of the connecting arm 30 is fixed at least on the outer side of the carrier frame 13.
Because the structure of carrying thing frame 13 is bigger, the length of joinable is longer, carry the distance that thing frame 13 and base plate 10 are closer, consequently, the preferred frame support section with connecting arm 30 fixes in carrying thing frame 13 outside at least to fully guarantee connecting arm 30 and fuselage frame laminating fixed connection, the fuselage frame provides sufficient support to connecting arm 30, connecting arm 30 also provides sufficient protection to the fuselage frame simultaneously, the two combined action has guaranteed that back horn 12 is stably fixed on the fuselage, back horn 12 also guarantees that the fuselage frame is non-deformable.
EXAMPLE five
Usually, the fuselage frame includes year thing frame 13 and battery frame 14, because year thing frame 13 is different with battery frame 14 structure appearance, and battery frame 14 width is less than year thing frame 13 usually, need make more reasonable setting to the structure of connecting arm 30 in order to guarantee that connecting arm 30 and fuselage are abundant to be adapted.
In order to solve the above problem, the rack for an aircraft provided by this embodiment includes a fuselage, where the fuselage includes a base plate 10, a front horn 11, and a rear horn 12, and the base plate 10 is provided with a fuselage frame on one side of the rear horn 12; a connecting arm 30 is arranged between the rear arm 12 and the base plate 10.
The rear arm 12 is also arranged on the fuselage frame.
The connecting arm 30 includes a bending structure, the bending structure includes a frame supporting section and an extending connecting section, the frame supporting section is disposed outside the frame of the body, and the extending connecting section extends and is fixed at the central position of the substrate 10.
The fuselage frame comprises a loading frame 13 and a battery frame 14, and the frame support section of the connecting arm 30 is fixed on the outer sides of the loading frame 13 and the battery frame 14.
Preferably, the frame support section of the connecting arm 30 is fixed outside the loading frame 13 and the battery frame 14 at the same time, so as to fully ensure the attachment and fixed connection between the connecting arm 30 and the body frame, the body frame provides enough support for the connecting arm 30, meanwhile, the connecting arm 30 also provides enough protection for the body frame, the combined action of the two ensures that the rear machine arm 12 is stably fixed on the body, and the rear machine arm 12 also ensures that the body frame is not easy to deform.
EXAMPLE six
In the rack according to the first embodiment, as shown in fig. 4, the rear arm 12 is connected to the base plate 10 through the connecting arm 30, so that the rear arm 12 is not too long, and the rear arm 12 can be reasonably folded.
This embodiment provides a preferred folding of the rear arm 12.
A frame for an aircraft, comprising a fuselage, said fuselage comprising a base plate 10, a front horn 11 and a rear horn 12;
a connecting arm 30 is arranged between the rear arm 12 and the base plate 10.
The rear arm 12 is connected to the connecting arm 30 through a connecting member 31, and the rear arm 12 is foldably assembled to the connecting arm 30 through the connecting member 31.
The rear horn 12 is foldably assembled on the connecting arm 30 through a connecting piece 31, and the rear horn 12 is folded to facilitate storage, transportation and the like of the aircraft.
EXAMPLE seven
The rear horn 12 is connected to the connecting arm 30 by the connecting member 31, and the impact force generated during the landing of the aircraft still affects the connection stability of the connecting arm 30, so that the connection firmness of the rear horn 12 needs to be further improved.
In order to solve the above problem, the frame for an aircraft provided in this embodiment includes a body, the body includes a base plate 10, a front arm 11 and a rear arm 12, and a connecting arm 30 is disposed between the rear arm 12 and the base plate 10.
The rear arm 12 is connected to the connecting arm 30 and the body frame by a connecting member 31.
Through above-mentioned connected mode, back horn 12 is connected with linking arm 30 and fuselage frame simultaneously, fully guarantees linking arm 30 and fuselage frame laminating fixed connection, and the fuselage frame provides sufficient support to linking arm 30, and linking arm 30 also provides sufficient protection to the fuselage frame simultaneously, and the two combined action has guaranteed that back horn 12 is stably fixed on the fuselage, and fuselage frame non-deformable also is guaranteed to back horn 12.
Example eight
The existing agricultural plant protection unmanned aerial vehicle can be used for replacing manpower to carry out conventional agricultural operation in the air. In the conventional agricultural plant protection unmanned aerial vehicle, a medicine box or a sowing device is mounted on a carrying frame 13, and a battery is mounted on a battery frame 14.
There are many connecting wires between the electron device in back horn 12 and base plate 10 central authorities, and the connecting wire exposes and can receive external influence and easily appear quality problems in the outside, and the installation and the dismantlement operation of the connecting wire of back horn 12 and the electron device of base plate 10 are also inconvenient simultaneously.
In order to solve the above problem, as shown in fig. 3, the rack for an aircraft provided by this embodiment includes a fuselage, where the fuselage includes a base plate 10, a front arm 11, and a rear arm 12, and the base plate 10 is provided with a fuselage frame on one side of the rear arm 12; a connecting arm 30 is arranged between the rear arm 12 and the base plate 10.
The rear arm 12 is also arranged on the fuselage frame.
The connecting arm 30 is a hollow tube.
The substrate 10 includes an upper substrate and a lower substrate 101, and the upper substrate and the lower substrate 101 directly form an accommodating space for accommodating an electronic device.
The plurality of connecting wires between the electronic devices in the center of the substrate 10 and on the rear arm 12 are arranged in the hollow pipe fitting of the connecting arm 30, so that the connecting wires of the rear arm 12 and the electronic devices in the center of the substrate 10 are connected conveniently, the rear arm 12 can be mounted and dismounted conveniently, the connecting wires cannot be exposed in the external environment, and the quality problem caused by the exposure of the connecting wires is avoided.
Example nine
To further facilitate the attachment and detachment of the connecting arm 30, further design of the structure of the connecting arm 30 is required.
In order to solve the above technical problem, the present embodiment provides a frame for an aircraft, including a fuselage, where the fuselage includes a base plate 10, a front horn 11 and a rear horn 12, and the base plate 10 is provided with a fuselage frame on one side of the rear horn 12; a connecting arm 30 is arranged between the rear arm 12 and the base plate 10.
The rear arm 12 is also arranged on the fuselage frame.
The connecting arm 30 is a segmented pipe.
The segmented tube facilitates the mounting and dismounting of the connecting arm 30.
Example ten
Current agricultural plant protection unmanned aerial vehicle carries on the medical kit or scatters the device, in order to strengthen the unmanned aerial vehicle function, visual support 20 has been increased on current unmanned aerial vehicle, be provided with two mesh visual devices on visual support 20, because visual support 20 and visual device set up at the unmanned aerial vehicle front end, original unmanned aerial vehicle's design balance has been changed, consequently, the fuselage balance of the aircraft of having carried on visual support 20 needs readjustment.
In order to solve the above technical problem, the present embodiment provides a frame for an aircraft, including a fuselage, where the fuselage includes a base plate 10, a front horn 11 and a rear horn 12, and the base plate 10 is provided with a fuselage frame on one side of the rear horn 12; a connecting arm 30 is arranged between the rear arm 12 and the base plate 10.
The rear arm 12 is also arranged on the fuselage frame.
The connecting arm 30 is a segmented pipe.
The sectional type pipe fitting comprises a first sleeve and a second sleeve, the first sleeve is fixedly connected with the base station through a connecting piece 31, the second sleeve is detachably connected with the first sleeve, and the connecting length of the second sleeve and the first sleeve is adjustable.
Namely, the distance between the rear arm 12 and the base plate 10 can be adjusted by adjusting the length of the connecting arm 30.
According to the rack for the aircraft provided by the invention, the visual support 20 is arranged on the base plate 10 at one side of the front horn 11, the load of the visual support 20 and the visual device changes the balance of the existing fuselage, the balance adjustment of the aircraft is difficult to realize, so that the weight of the visual support 20 and the visual device is greatly limited, and the rack needs to be improved in order to realize the carrying of more advanced visual devices. The frame of this application has set up linking arm 30 between horn 12 and base plate 10 after, this linking arm 30 is used for adjusting the distance between horn 12 and the base plate 10 after, extends the position of horn 12 to one side of keeping away from vision support 20, vision device through linking arm 30 after to the fuselage balance of current frame has been adjusted, makes the aircraft can carry on more advanced, the bigger vision device of weight.
EXAMPLE eleven
The embodiment provides an aircraft, including the frame, the frame includes the fuselage, the fuselage includes base plate 10, preceding horn 11 and back horn 12, be provided with connecting arm 30 between back horn 12 and the base plate 10.
The technical problem that this aircraft can solve is: the agricultural plant protection unmanned aerial vehicle can be used for replacing manpower to carry out conventional agricultural operation in the air. In the conventional agricultural plant protection unmanned aerial vehicle, a medicine box or a sowing device is mounted on a carrying frame 13, and a battery is mounted on a battery frame 14. The unmanned aerial vehicle fuselage is owing to included year thing frame 13 and battery frame 14, consequently need extend the back horn 12 longer of preparation, and the longer reasonable beta structure that then is difficult for to set up of back horn 12 length.
The aircraft has the technical effects that: in order to avoid that the rear arm 12 is too long to easily set a folding structure, the connecting arm 30 is arranged between the rear arm 12 and the base plate 10, and the rear arm 12 is connected with the base plate 10 through the connecting arm 30, so that the length of the rear arm 12 is shortened, and the normal folding setting of the rear arm 12 can be realized.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A frame for an aircraft, comprising a fuselage, the fuselage comprising a base plate, a front horn and a rear horn, characterized in that:
and a connecting arm is arranged between the rear machine arm and the substrate.
2. A frame for an aircraft according to claim 1, characterized in that the base plate is provided with a fuselage frame on the rear horn side;
the rear machine arm is arranged on the machine body frame.
3. The airframe as defined in claim 2, wherein the connecting arm includes a bent structure, the bent structure includes a frame support section and an extension connecting section, the frame support section is disposed outside the fuselage frame, and the extension connecting section is fixed in a central position of the base plate in an extending manner.
4. A frame for an aircraft according to claim 3, characterized in that the fuselage frame comprises a carrier frame and a battery frame, the frame support section of the connecting arm being fixed at least on the outside of the carrier frame.
5. A frame for an aircraft according to claim 1, characterized in that the rear horn is connected to the connecting arm by means of a connecting piece, by means of which the rear horn is foldably fitted to the connecting arm.
6. A frame for an aircraft according to claim 1, characterized in that the rear horn is connected to the connecting arm and the fuselage frame by means of a connecting piece.
7. The airframe for an aircraft as recited in claim 1, wherein the connecting arm is a hollow tube.
8. The airframe for an aircraft as recited in claim 1, wherein the linking arm is a segmented tube.
9. The airframe as recited in claim 8, wherein the segmented tube comprises a first sleeve and a second sleeve, the first sleeve is fixedly connected to the base through a connector, the second sleeve is detachably connected to the first sleeve, and the length of the second sleeve connected to the first sleeve is adjustable.
10. An aircraft, characterized by comprising a frame for an aircraft according to any one of claims 1-9.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910795375.4A CN111216868A (en) | 2019-08-27 | 2019-08-27 | Frame for aircraft and aircraft |
| PCT/CN2020/111415 WO2021037067A1 (en) | 2019-08-27 | 2020-08-26 | Frame for aircraft and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910795375.4A CN111216868A (en) | 2019-08-27 | 2019-08-27 | Frame for aircraft and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111216868A true CN111216868A (en) | 2020-06-02 |
Family
ID=70828889
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910795375.4A Pending CN111216868A (en) | 2019-08-27 | 2019-08-27 | Frame for aircraft and aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN111216868A (en) |
| WO (1) | WO2021037067A1 (en) |
Cited By (2)
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| WO2021037067A1 (en) * | 2019-08-27 | 2021-03-04 | 苏州极目机器人科技有限公司 | Frame for aircraft and aircraft |
| CN116080946A (en) * | 2022-12-19 | 2023-05-09 | 深圳技术大学 | Unmanned aerial vehicle frame and unmanned aerial vehicle |
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Also Published As
| Publication number | Publication date |
|---|---|
| WO2021037067A1 (en) | 2021-03-04 |
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