CN208134652U - Can in-orbit allosteric modular space aircraft - Google Patents
Can in-orbit allosteric modular space aircraft Download PDFInfo
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- CN208134652U CN208134652U CN201820367815.7U CN201820367815U CN208134652U CN 208134652 U CN208134652 U CN 208134652U CN 201820367815 U CN201820367815 U CN 201820367815U CN 208134652 U CN208134652 U CN 208134652U
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Abstract
The utility model discloses it is a kind of can in-orbit allosteric modular space aircraft, the modular space aircraft includes basic module cell body, the basic module cell body includes frame and functional module, the frame is equipped with magnetic connector, two basic module cell bodies can be connected by the magnetic connector to be connected, on said frame, the functional module can be used for completing the assigned tasks of the basic module cell body for the functional module installation.According to the utility model embodiment can in-orbit allosteric modular space aircraft, since the functional module on basic module cell body can make basic module cell body complete assigned tasks, and the magnetic connector on frame can connect multiple basic module cell bodies, therefore modular space aircraft has flexible structure, at low cost, in-orbit fast response time, the long design in the past that overcomes of service life is complicated at high cost, replaces the problem of component hardly possible.
Description
Technical field
The utility model patent is related to spacecraft overall design technique, and in particular to it is a kind of can in-orbit allosteric module
Change spacecraft.
Background technique
With the rapid development of space technology, information technology, new material and advanced manufacturing technology etc., outer space utilization will be sent out
Raw revolutionary variation, space system microminaturization and low cost transmitting become the important trend of the following space flight development.In future
In " elasticity dispersion " type three-dimensional system, various spacecrafts will be completed.From technology trends, module will be provided with
Change, be intelligent, can allosteric, can safeguard, the characteristics of use can be recombinated.
Design and interconnection technique for restructural multiple agent, there has been no perfect solutions at present.Both at home and abroad
Some schemes, such as " phoenix plan ", " F6 ", " iBOSS " plan, " robot for space " plan etc. are substantially all to use isomery formula
Design, and all not by in-orbit test, it is not able to achieve the in-orbit assembling of modularization satellite and splicing of isomorphism formula, and complete specific
Task.
Utility model content
The utility model aims to solve at least one of the technical problems existing in the prior art.For this purpose, the utility model mentions
Out it is a kind of can in-orbit allosteric modular space aircraft, the modular aircraft structure is simple, and versatility is good, at low cost.
According to the utility model embodiment can in-orbit allosteric modular space aircraft, including basic module cell
Body, the basic module cell body include：Frame, the frame are equipped with magnetic connector, two basic module cells
Body can be connected by the magnetic connector to be connected；Functional module, the functional module are installed on said frame, the function
Energy module can be used for completing the assigned tasks of the basic module cell body.
According to the utility model embodiment can in-orbit allosteric modular space aircraft, due to basic module cell body
On functional module basic module cell body can be made to complete assigned tasks, and the magnetic connector on frame can will be multiple
The connection of basic module cell body, therefore modular space aircraft has flexible structure, at low cost, in-orbit fast response time, clothes
The business service life, the long design in the past that overcomes was complicated at high cost, replaced the problem of component hardly possible.
In some embodiments, the frame includes：Core hollow cube, two semi-surrounding outline borders, two described half
Outline border is surrounded to be plugged on the core hollow cube；Wherein, each semi-surrounding outline border is formed generally as C font,
Two semi-surrounding outline borders are plugged in the core hollow cube relative to one another in such a way that 90 ° staggered.
Specifically, each semi-surrounding outline border includes：Interconnecting piece, the interconnecting piece are equipped with the magnetic connector
The frame of two basic module cell bodies to be connected；Two extensions, described two extensions are respectively by described
Two opposite sides of interconnecting piece upwardly extend to be formed, wherein it is hollow vertical that each semi-surrounding outline border is plugged into the core
When in cube, each extending part is in the inside of the core hollow cube.
In some alternative embodiments, the first mounting hole, first mounting hole are offered on each extension
The detection function of the basic module cell body is realized for installing detection piece, offers the second installation on the interconnecting piece
Hole, second mounting hole are thin for installing the electric-controlled plate for controlling the basic module cell body, and for the basic module
The propeller of cell space offer power.
In some alternative embodiments, the interconnecting piece is equipped with the first locating piece, on the core hollow cube
Equipped with the second locating piece cooperated with first locating piece.
In some embodiments, each interconnecting piece is equipped with the first installation mark, and the core hollow cube is equipped with
Second installation mark, when each semi-surrounding outline border is plugged on the core hollow cube, the first installation mark
It corresponds to each other with the second installation mark.
In some embodiments, the basic module cell body further includes protection board, and the protection board is for installing control
The electric-controlled plate of the basic module cell body, the protection board are detachably arranged at and the frame.
In some embodiments, it is described can in-orbit allosteric modular space aircraft, further include solar sail, it is described too
Positive sail is two, and two solar sail are separately mounted on opposite two frames of the frame.
In some embodiments, the structure of described two semi-surrounding outline borders is identical.
In some embodiments, the functional module include power-supply system, dynamical system, power supply system, detection system and
At least one of control system.
The additional aspect and advantage of the utility model will be set forth in part in the description, partially will be from following description
In become obvious, or recognized by the practice of the utility model.
Detailed description of the invention
The above-mentioned and/or additional aspect and advantage of the utility model from the description of the embodiment in conjunction with the following figures will
Become obvious and is readily appreciated that, wherein：
Fig. 1 be the utility model embodiment can in-orbit allosteric modular space aircraft overall structure diagram.
Fig. 2 is the basic module cell body structural schematic diagram of the utility model embodiment.
Fig. 3 is the basic module cell body structural schematic diagram of another embodiment of the utility model.
Fig. 4 is the circuit theory schematic diagram of the basic module cell body of the utility model embodiment.
Fig. 5 is the explosive decomposition schematic diagram of frame described in Fig. 4.
Appended drawing reference：
Modular space aircraft 1,
Basic module cell body 10,
Frame 100,
Core hollow cube 110, the second locating piece 111, second installation mark 112,
Semi-surrounding outline border 120, extension 121, the first mounting hole 1211, interconnecting piece 122, the second mounting hole 1221, first
The installation of locating piece 1222, first mark 1223,
Protection board 130,
Magnetic attachment device 140,
Main thrust device 210, bionical adsorbing mechanism 220, laser warning device 230, laser range finder 240, laser 250,
Multi-panel camera 260, attitude control thruster 270, electric-controlled plate 280, solar sail 290.
Specific embodiment
The embodiments of the present invention are described below in detail, examples of the embodiments are shown in the accompanying drawings, wherein from beginning
Same or similar element or element with the same or similar functions are indicated to same or similar label eventually.Below by ginseng
The embodiment for examining attached drawing description is exemplary, and is only used for explaining the utility model, and should not be understood as to the utility model
Limitation.
In the description of the present invention, it should be understood that term " center ", " longitudinal direction ", " transverse direction ", " length ", " width
Degree ", " thickness ", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside", " suitable
The orientation or positional relationship of the instructions such as hour hands ", " counterclockwise ", " axial direction ", " radial direction ", " circumferential direction " is orientation based on the figure
Or positional relationship, be merely for convenience of describing the present invention and simplifying the description, rather than the device of indication or suggestion meaning or
Element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as the limit to the utility model
System.In addition, defining " first ", the feature of " second " can explicitly or implicitly include one or more of the features.
In the description of the present invention, unless otherwise indicated, the meaning of " plurality " is two or more.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " is pacified
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
The concrete meaning of language in the present invention.
Below with reference to Fig. 1-Fig. 5 description according to the utility model embodiment can in-orbit allosteric modular space aircraft
1。
As shown in Figure 1, according to the utility model embodiment can the modular space aircraft 1 of in-orbit allosteric include basic
Module cell body 10, basic module cell body 10 include frame 100 and functional module, and frame 100 is equipped with magnetic connector
140, two basic module cell bodies 10 can be connected by magnetic connector 140 to be connected, and functional module is mounted on frame 100
On, functional module can be used for completing the assigned tasks of basic module cell body 10.
It is understood that the functional module on basic module cell body 10 can make basic module cell body 10 complete
Assigned tasks, and the magnetic connector 140 on frame 100 can connect multiple basic module cell bodies 10, this means that
It is multiple to execute compared with horn of plenty and powerful aircraft that multiple basic module cell bodies 10 can become function in any combination, after polymerization
Miscellaneous in-orbit task.Compared to Traditional Space aircraft, modular space flight is simplified using multiple basic module cell bodies 10
The structure of device 1.Meanwhile in the task of execution, the modular space aircraft 1 of the utility model embodiment is according to week of landing point
Collarette border complexity changes the relative position of multiple basic module cell bodies 10, so that modular space aircraft 1 is suitable
Answer more complicated task condition.
According to the utility model embodiment can in-orbit allosteric modular space aircraft 1, due to basic module cell
Functional module on body 10 can make basic module cell body 10 complete assigned tasks, and the magnetic connector on frame 100
140 can connect multiple basic module cell bodies 10, thus modular space aircraft 1 have flexible structure, it is at low cost,
Rail fast response time, the long design in the past that overcomes of service life is complicated at high cost, replaces the problem of component hardly possible.
Supplementary explanation is needed exist for, multiple basic module cell bodies 10 are all an independent aircraft, and shell carries
Different functional modules makes each basic module cell body 10 have specific function.
In some embodiments, as shown in fig. 4-5, frame 100 includes core hollow cube 110 and two semi-surroundings
Outline border 120, two semi-surrounding outline borders 120 are plugged on core hollow cube 110, the big bodily form of each semi-surrounding outline border 120
As C font, two semi-surrounding outline borders 120 are plugged in core hollow cube 110 in such a way that 90 ° staggered relative to one another.
Such framework processing and assembly are all more convenient, thus both can simplify the assembly process of frame 100, and can also reduce frame
100 production cost.
Specifically, each semi-surrounding outline border 120 includes interconnecting piece 122 and two extensions 121, is set on interconnecting piece 122
There is magnetic connector 140 so that the frame 100 of two basic module cell bodies 10 to be connected.Two extensions 121 are respectively by connecting
Two opposite sides of portion 122 upwardly extend to be formed, wherein each semi-surrounding outline border 120 is plugged into core hollow cube 110
When upper, each extension 121 is located at the inside of core hollow cube 110.It is possible thereby to guarantee semi-surrounding outline border 120 and core
Stable connection between hollow cube 110.Certainly, in the other embodiments of the utility model, magnetic connector 140 is also
It can be located on two extensions 121.
In some alternative embodiments, as shown in figure 5, offering the first mounting hole 1211 on each extension 121, the
One mounting hole 1211 offers on interconnecting piece 122 for installing detection piece to realize the detection function of basic module cell body 10
Second mounting hole 1221, the second mounting hole 1221 are used to install the electric-controlled plate 280, Yi Jiwei of control basic module cell body 10
The propeller of the offer power of basic module cell body 10.It is understood that detection piece and the installation of electric-controlled plate 280 and propeller
In the different piece that plate surrounds outline border, avoids and have a adverse impact between detection piece and electric-controlled plate 280 or propeller.
In addition, will test part is located at the detection for being conducive to detection piece on extension 121, electric-controlled plate 280 is mounted on interconnecting piece 122
Be conducive to the protection of electric-controlled plate 280.
Specifically, detection piece can for camera, laser or measurement light, electricity, power middle sensor.
Advantageously, electric-controlled plate 280 is fixed on the extension 121 of a semi-surrounding frame 100, by payload/propulsion
Device is plugged on the extension 121 of another semi-surrounding frame 100.Subsequent inside is divided with external component in this way, facilitating
Operation is opened, if internal circuit part corrupted, all external fixation devices can be removed, pull out that of fixed internal
The semi-surrounding frame 1003 on one side carries out reparation operation.
In some alternative embodiments, as shown in figure 5, interconnecting piece 122 is equipped with the first locating piece 1222, core is hollow
Cube 110 is equipped with the second locating piece 111 cooperated with the first locating piece 1222.Thereby ensure that interconnecting piece 122 and core
The connection of hollow cube 110 avoids the phenomenon that interconnecting piece 122 is deviate from from core hollow cube 110.It needs
It is bright, the form of the first locating piece 1222 and the second locating piece 111 can there are many, for example, in the embodiment having, first
Locating piece 1222 is formed as card convex, and the second locating piece 111 is formed as card hole.In the embodiment having, 1222 shape of the first locating piece
As bolt, the second locating piece 111 is formed as nut etc..
In some embodiments, as shown in figure 5, each interconnecting piece 122 is equipped with the first installation mark 1223, core is hollow
Cube 110 is equipped with the second installation mark 112, when each semi-surrounding outline border 120 is plugged on core hollow cube 110,
First installation mark 1223 corresponds to each other with the second installation mark 112.As a result, construction personnel can extremely direction by semi-surrounding
Outline border 120 is plugged on core hollow cube 110.First installation mark 1223 and the second installation mark 112 function only as mentioning
Show the effect of installation site, rising limit is not done to the concrete form of the first installation mark 1223 and the second installation mark 112 herein
It is fixed.
In some embodiments, as shown in figure 3, basic module cell body 10 further includes protection board 130, protection board 130 is used
In the electric-controlled plate 280 of installation control basic module cell body 10, protection board 130 is detachably arranged at and frame 100.It is electric as a result,
Control the available good protection of plate 280.It, can first will be automatically controlled it should be noted that when modular space 1 in-orbit assembling of aircraft
Plate 280 is fixed on protection board 130, then is fixed in some semi-surrounding frame by the first mounting hole 1211 and rivet
On 100, then two 100 grafting of semi-surrounding frame are got up.
In some embodiments, the structure of two semi-surrounding outline borders 120 is identical.As a result, when production semi-surrounding outline border 120 only
A mold is needed, production cost is reduced.
It should be noted that frame 100 can remove hollow core in the case where certain pairs of intensity requirements are not high
Cube 110 directly by two 100 grafting of semi-surrounding frame and fixed is used as frame 100.
In some embodiments, as shown in figure 3, can the modular space aircraft 1 of in-orbit allosteric further include solar sail
290, solar sail 290 is two, and two solar sail 290 are separately mounted on opposite two frames of frame 100.
In some embodiments, functional module includes power-supply system, dynamical system, power supply system, detection system and control
At least one of system.
It should be added that all directions for the frame 100 that detection piece, solar sail 290 and propeller can be installed
On, to ensure that basic module cell body 10 has higher flexibility, safety and enough energy resource supplies.
Below with reference to Fig. 1-Fig. 5 describe one specific embodiment of the utility model can in-orbit allosteric modular space fly
Row device 10.
The present embodiment can in-orbit allosteric modular space aircraft 1 include four basic module cell bodies 10, each
Elementary cell body includes frame 100 and functional module.
As shown in fig. 4-5, frame 100 includes hollow cube 110 and two semi-surrounding outline borders 120, two semi-surroundings
Outline border 120 is plugged on core hollow cube 110, and each semi-surrounding outline border 120 is formed generally as C font, two and half packets
It encloses outline border 120 and is plugged in core hollow cube 110 relative to one another in such a way that 90 ° staggered.Each semi-surrounding outline border 120 is
Including interconnecting piece 122 and two extensions 121, interconnecting piece 122 is equipped with magnetic connector 140 so that two basic modules are thin
The frame 100 of cell space 10 is connected.Two extensions 121 are upwardly extended by two opposite sides of interconnecting piece 122 formed respectively.Often
When a semi-surrounding outline border 120 is plugged on core hollow cube 110, each extension 121 is located at core hollow cube 110
Inside.
Functional module includes individual power-supply system, dynamical system, power supply system, detection system and control system, such as
Shown in Fig. 1-Fig. 3, each elementary cell body has the basic function of modular space aircraft 1, such as detection, communication, power.
The payload on 100 surface of frame of each elementary cell body includes main thrust device 210, bionical adsorbing mechanism 220, and laser is accused
Alarm device 230, laser range finder 240, laser 250, multi-panel camera 260, attitude control thruster 270 etc., for aircraft completion
Assigned tasks.
In 10 polymerization stage of basic module cell body, first in all basic module cell bodies 10 to be polymerize, select
One chief cell body (primary), other are all close to primary from star, with after primary communication negotiation, determine physical planning route,
It is accurately positioned the relative pose state with primary by the laser range finder 240 and multi-panel camera 260 on surface, cooperates main thrust
Device 210 and attitude control thruster 270 control the magnetism and intensity of magnetic connector, are finally completed polymerization, structure required for being formed
Type, as shown in Figure 2.When basic module cell body 10 needs replacing, magnetic connector can control, and cooperate main thrust device
210 and the completion of attitude control thruster 270 separate one by one, after the Replacement and Repair for completing specific basic module cell body 10, then one by one
Polymerization.
The present embodiment can in-orbit allosteric modular space aircraft 1 have following advantages：
1) hardware is flexibly light and small：Using the cell body design method of isomorphism formula so that basic module cell body 10 have it is identical
Structure, pass through self-organizing again can complete complexity function.Plug in construction ensure that basic module cell body 10 intensity and
Flexibility, and reduce costs.
2) in-orbit response quickly：Since the height of each basic module cell body 10 is identical, so that modular space flies
Device 1 obtains in-orbit allosteric ability by self-organizing.Emitting or executing aerial mission on the way, in aggregation rounding state, to reduce
Space accounting；In the task of execution, according to the complexity of landing point ambient enviroment, modular space aircraft 1 can be in-orbit
Allosteric completes particular task.
3) extend in-orbit life-span：It can be quick in the failure of basic module cell body 10 formula by 100 structure of plug-in frame
In-orbit replacement.When the whole damage of basic module cell body 10, any healthy cell body can be chosen and be replaced, and then extended
The service life of aircraft.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " illustrative examples ",
The description of " example ", " specific example " or " some examples " etc. means specific features described in conjunction with this embodiment or example, knot
Structure, material or feature are contained at least one embodiment or example of the utility model.In the present specification, to above-mentioned art
The schematic representation of language may not refer to the same embodiment or example.Moreover, description specific features, structure, material or
Person's feature can be combined in any suitable manner in any one or more of the embodiments or examples.
While there has been shown and described that the embodiments of the present invention, it will be understood by those skilled in the art that：
These embodiments can be carried out with a variety of variations, modification, replacement in the case where not departing from the principles of the present invention and objective
And modification, the scope of the utility model are defined by the claims and their equivalents.
Claims (10)
1. one kind can in-orbit allosteric modular space aircraft, which is characterized in that it is described basic including basic module cell body
Module cell body includes：
Frame, the frame are equipped with magnetic connector, and two basic module cell bodies can be connected by the magnetic
Part connection is connected；
Functional module, on said frame, the functional module can be used for completing the basic module for the functional module installation
The assigned tasks of cell body.
2. it is according to claim 1 can in-orbit allosteric modular space aircraft, which is characterized in that the frame packet
It includes：
Core hollow cube,
Two semi-surrounding outline borders, two semi-surrounding outline borders are plugged on the core hollow cube；Wherein, Mei Gesuo
It states semi-surrounding outline border and is formed generally as C font, two semi-surrounding outline borders are plugged in relative to one another in such a way that 90 ° staggered
The core hollow cube.
3. it is according to claim 2 can in-orbit allosteric modular space aircraft, which is characterized in that each described half wraps
Enclosing outline border includes：
Interconnecting piece, the interconnecting piece are equipped with the magnetic connector with by the frame of two basic module cell bodies
It is connected；
Two extensions, described two extensions are upwardly extended by two opposite sides of the interconnecting piece formed respectively, wherein
When each semi-surrounding outline border is plugged on the core hollow cube, each extending part is hollow in the core
The inside of cube.
4. it is according to claim 3 can in-orbit allosteric modular space aircraft, which is characterized in that each extension
The first mounting hole is offered in portion, first mounting hole is for installing detection piece to realize the inspection of the basic module cell body
Brake, offers the second mounting hole on the interconnecting piece, and to control the basic module thin for installing for second mounting hole
The electric-controlled plate of cell space, and the propeller of power is provided for the basic module cell body.
5. it is according to claim 3 can in-orbit allosteric modular space aircraft, which is characterized in that on the interconnecting piece
Equipped with the first locating piece, the core hollow cube is equipped with the second locating piece cooperated with first locating piece.
6. it is according to claim 3 can in-orbit allosteric modular space aircraft, which is characterized in that on each interconnecting piece
Equipped with the first installation mark, the core hollow cube is equipped with the second installation mark, each semi-surrounding outline border grafting
When on to the core hollow cube, the first installation mark corresponds to each other with the second installation mark.
7. it is according to claim 1 can in-orbit allosteric modular space aircraft, which is characterized in that the basic module
Cell body further includes protection board, and the protection board is for installing the electric-controlled plate for controlling the basic module cell body, the protection
Plate is detachably arranged at and the frame.
8. it is according to claim 1 can in-orbit allosteric modular space aircraft, which is characterized in that further include the sun
Sail, the solar sail are two, and two solar sail are separately mounted on opposite two frames of the frame.
9. it is according to claim 2 can in-orbit allosteric modular space aircraft, which is characterized in that described two half wrap
The structure for enclosing outline border is identical.
10. it is according to claim 1 to 9 can in-orbit allosteric modular space aircraft, which is characterized in that
The functional module includes at least one of power-supply system, dynamical system, power supply system, detection system and control system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201820367815.7U CN208134652U (en) | 2018-03-16 | 2018-03-16 | Can in-orbit allosteric modular space aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820367815.7U CN208134652U (en) | 2018-03-16 | 2018-03-16 | Can in-orbit allosteric modular space aircraft |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108327926A (en) * | 2018-03-16 | 2018-07-27 | 清华大学 | Can in-orbit allosteric modular space aircraft |
| CN110143293A (en) * | 2019-06-06 | 2019-08-20 | 北京理工大学 | One kind can allosteric micro-nano satellite form topology rebuilding and allosteric method |
| CN111003211A (en) * | 2019-11-28 | 2020-04-14 | 北京空间飞行器总体设计部 | Spacecraft configuration capable of being assembled and expanded in orbit |
| CN111449051A (en) * | 2020-03-26 | 2020-07-28 | 天晴干细胞股份有限公司 | Cell cryopreservation device applied to space station |
| CN112158360A (en) * | 2020-10-10 | 2021-01-01 | 北京空间飞行器总体设计部 | On-orbit service and maintenance verification method and system |
-
2018
- 2018-03-16 CN CN201820367815.7U patent/CN208134652U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108327926A (en) * | 2018-03-16 | 2018-07-27 | 清华大学 | Can in-orbit allosteric modular space aircraft |
| CN108327926B (en) * | 2018-03-16 | 2023-10-27 | 清华大学 | Modular spacecraft capable of on-orbit allosteric |
| CN110143293A (en) * | 2019-06-06 | 2019-08-20 | 北京理工大学 | One kind can allosteric micro-nano satellite form topology rebuilding and allosteric method |
| CN111003211A (en) * | 2019-11-28 | 2020-04-14 | 北京空间飞行器总体设计部 | Spacecraft configuration capable of being assembled and expanded in orbit |
| CN111003211B (en) * | 2019-11-28 | 2021-10-01 | 北京空间飞行器总体设计部 | Spacecraft configuration capable of being assembled and expanded in orbit |
| CN111449051A (en) * | 2020-03-26 | 2020-07-28 | 天晴干细胞股份有限公司 | Cell cryopreservation device applied to space station |
| CN111449051B (en) * | 2020-03-26 | 2021-11-16 | 天晴干细胞股份有限公司 | Cell cryopreservation device applied to space station |
| CN112158360A (en) * | 2020-10-10 | 2021-01-01 | 北京空间飞行器总体设计部 | On-orbit service and maintenance verification method and system |
| CN112158360B (en) * | 2020-10-10 | 2022-04-19 | 北京空间飞行器总体设计部 | On-orbit service and maintenance verification method and system |
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