CN117549577A - H-shaped composite material member forming method - Google Patents
H-shaped composite material member forming method Download PDFInfo
- Publication number
- CN117549577A CN117549577A CN202311521295.2A CN202311521295A CN117549577A CN 117549577 A CN117549577 A CN 117549577A CN 202311521295 A CN202311521295 A CN 202311521295A CN 117549577 A CN117549577 A CN 117549577A
- Authority
- CN
- China
- Prior art keywords
- layering
- support beam
- middle support
- composite material
- preform
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 38
- 239000002131 composite material Substances 0.000 title claims abstract description 36
- 239000011248 coating agent Substances 0.000 claims abstract description 5
- 238000000576 coating method Methods 0.000 claims abstract description 5
- 229910052751 metal Inorganic materials 0.000 claims description 22
- 239000002184 metal Substances 0.000 claims description 22
- 239000000853 adhesive Substances 0.000 claims description 8
- 230000001070 adhesive effect Effects 0.000 claims description 8
- 238000005253 cladding Methods 0.000 claims description 7
- 239000000835 fiber Substances 0.000 claims description 5
- 238000007906 compression Methods 0.000 claims description 4
- 239000002313 adhesive film Substances 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 238000005056 compaction Methods 0.000 claims 1
- 238000013007 heat curing Methods 0.000 claims 1
- 230000008569 process Effects 0.000 abstract description 14
- 238000004519 manufacturing process Methods 0.000 description 6
- 238000005452 bending Methods 0.000 description 3
- 238000001723 curing Methods 0.000 description 3
- 238000000465 moulding Methods 0.000 description 3
- 238000004804 winding Methods 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 238000009966 trimming Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000001680 brushing effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000006082 mold release agent Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
- 239000011800 void material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/382—Automated fiber placement [AFP]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/001—Profiled members, e.g. beams, sections
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses a forming method of an H-shaped composite material component. The method comprises the following steps: layering the inner core structure of the middle support beam to obtain a middle support beam preform, and processing the two ends of the middle support beam preform to obtain a first connection structure; layering the inner core structure of the side beam to obtain a side beam preform, and processing the middle of the side beam preform to obtain a second connecting structure matched with the first connecting structure; assembling the middle support beam and the side beam by the first and second connection structures; and integrally coating the assembled middle support beam and side beams by adopting a skin to obtain the H-shaped composite material component. The H-shaped structure composite forming process provided by the invention is suitable for the H-shaped structure composite forming with complex bearing requirements, and the member formed by the method has the characteristics of high strength and light weight.
Description
Technical Field
The invention belongs to the technical field of composite material forming, and particularly relates to a forming method of an H-shaped composite material member.
Background
The "H" shaped member is a common structural form in aerospace pylon products that primarily bears axial tension, compression, torsion and bending loads. The traditional H-shaped components are mostly of titanium alloy, aluminum alloy and other metal structures, and the structural weight is large, so that the requirement of lightweight aviation products cannot be met. The connection design difficulty of the middle supporting part and the two side structures of the common composite material H-shaped structure is high, and the bearing performance and the process realizability of the structure are difficult to be considered. Therefore, the traditional metal scheme or composite material process cannot meet the technical requirements.
Disclosure of Invention
Aiming at one or more of the defects or improvement demands of the prior art, the invention provides a composite forming process of an H-shaped structure, which is suitable for composite forming of the H-shaped structure with complex bearing requirements, and a member formed by the method has the characteristics of high strength and light weight.
The technical scheme adopted by the invention is as follows:
in a first aspect, the present invention provides a method of forming an "H" shaped composite member, comprising the steps of:
layering the inner core structure of the middle support beam to obtain a middle support beam preform, and processing the two ends of the middle support beam preform to obtain a first connection structure;
layering the inner core structure of the side beam to obtain a side beam preform, and processing the middle of the side beam preform to obtain a second connecting structure matched with the first connecting structure;
assembling the middle support beam and the side beam by the first and second connection structures;
and integrally coating the assembled middle support beam and side beams by adopting a skin to obtain the H-shaped composite material component.
Furthermore, the side beams are of composite material rod structures with metal bushings, the metal bushings are arranged at two ends of the side beams, and the composite material is wound on the metal bushings in a design mode of laying around a shaft and is transited to an equal straight section.
Further, the layering of the internal core structure of the side sill comprises a class A layering and a class B layering, wherein the class A layering is a winding shaft layering, and the class B layering is an axial layering.
Further, the first connecting structure and the second connecting structure are grooves, and the middle supporting beam and the side beams are assembled together through the grooves to realize alternate layering.
Further, adhesive is smeared at the corresponding positions of the grooves of the middle supporting beam and the side beams, the middle supporting beam and the side beams are assembled together, after the whole is formed, adhesive is smeared or adhesive films are paved on the whole outer surface of the H-shaped blank, and then the whole H-shaped blank is coated by adopting fiber unidirectional prepreg and fabric.
Further, the thickness of the integral cladding is controlled to be more than 1mm, and the fiber angle is adopted to be +/-45 degrees.
And further, placing the prefabricated member obtained after the whole coating is finished into a mould for precompaction and then removing, trimming in combination with the theoretical appearance of the product, trimming the part exceeding the theoretical outer profile, filling the concave area deviating from the product profile, and then placing the prefabricated member into the mould for compression, heating and curing by adopting a press.
Further, the method also comprises the following steps: machining shaft sleeve mounting holes at corresponding positions of the side beams; installing a metal shaft sleeve through a shaft sleeve installation hole; and (5) finishing the appearance of the polished product.
In a second aspect, the present invention provides an "H" shaped composite member shaped according to the above method.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
according to the component composite molding process, the metal embedded part (namely the metal lining) is embedded in the paving process, and compared with a component formed by paving pure prepreg, the component composite molding process is not easy to cause product cracking in the subsequent mechanical connection process (such as hole matching and other processing) with other products. Compared with the traditional metal component production cycle, the process has the advantages that all production operations can be completed by one workshop, the time consumption of multi-workshop part turnover is avoided, the production speed can be increased by 1-2 days, the strength of the component can be maintained while the weight of the component is reduced, the production operation is simple, and the production operation is easy to carry out.
The H-shaped member forming process is suitable for forming all composite material structures with middle connecting rods, so that the axial tension-compression bearing and torsion bearing functions of the H-shaped structure are realized.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and do not constitute a limitation on the invention. In the drawings:
FIG. 1 is a schematic view of the overall H-shaped member of the present invention;
FIG. 2 is a schematic view of an intermediate support beam of the present invention;
FIG. 3 is a schematic view of the structure of the side member of the present invention;
fig. 4 is a schematic cross-sectional layering of a side sill of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
The invention provides a forming method of an H-shaped composite material component, which comprises a component structural design scheme and a component forming process. Fig. 1 is a schematic view of the whole H-shaped member including a center support beam 10, side members 20, and metal bushings 30 provided at the ends of the side members 20.
The structural design scheme of the component comprises the following contents:
the side beam 20 is constructed as a unitary composite rod structure with a metal bushing 30 at the end, with the composite being laid about the axis in a manner that the composite is wrapped around the metal bushing 30 and transitions to an equal straight section. The metal bush 30 may be made of a titanium alloy or the like. The metal bushing 30 is used to form a mounting hole for connecting the H-shaped member to other components, such as a metal sleeve.
On the other hand, the cross section of the side beam is designed to be a 'skin-core' structure, the inner core structure is designed to be a rod member structure with high orientation, and the rod member structure comprises a class A pavement and a class B pavement, wherein the class A pavement is a winding shaft pavement, bears the main body tensile load of the structure, and the class B pavement is an axial pavement (perpendicular to the direction of the class A pavement) and provides structural rigidity. The outer layer area is a skin structure, so that structural integrity is guaranteed, and torsional rigidity is provided.
As shown in fig. 2 and 3, the middle support beam 10 is assembled with the grooves 11 at both ends (i.e., the first connecting structure of the present invention) and the grooves 21 on the side members 20 (i.e., the second connecting structure of the present invention) to achieve interpenetration and layering, and is integrally cured after covering the skin.
The component forming process comprises the following steps:
firstly, performing layering, including blank layering of the middle support beam 10 and class A layering and class B layering of the side beams 20, preferably performing class B layering firstly and then class A layering, so as to perform preforming of the middle support beam 10 and the side beams 20;
then, grooves are machined, that is, grooves 11 on the center support beam 10 and grooves 21 on the side beams 20 are machined.
Then, the surface of the grooves 11 on both sides of the middle support beam 10 is coated with an adhesive, and the lay-up of the middle support beam 10 and the side beams 20 are assembled together;
then, paving the overall covered skin;
and finally, placing the material into a mould for curing and forming, and demoulding to obtain the H-shaped structural member.
As a further improvement of the present invention, the preparation before laying comprises mold cleaning, mold release agent brushing, mold preheating and prepreg cutting in the component forming process.
In a specific embodiment of the present invention, a process for forming an "H" shaped composite member is provided, wherein the key point is a special connection structure design and a layering design, and the implementation method includes the following forming steps:
1) Firstly, a structural blank (namely a middle support beam preform) of a middle support beam mainly comprising axial fibers is paved by adopting unidirectional prepreg, and then, the blank is mechanically processed to manufacture groove structures on two sides of the middle support beam. It is noted that positive tolerances are used in machining the void in the middle of the groove to ensure subsequent assembly operations.
2) And (5) layering a side beam structure by adopting a unidirectional prepreg to obtain the side beam preform. Because the side beam needs to have tensile and bidirectional bending rotation functions, prepreg layering in different layering directions is creatively introduced into one section, as shown in fig. 4, wherein the layering direction of an area A is the up-down direction (winding layering), which is called an area A layering, the layering direction of an area B is the left-right direction (axial layering), which is called an area B layering, and the prepreg layering and the area B have good tensile functions and respectively bear bending functions in the left-right direction and the up-down direction. It should be noted that a groove plug interface is reserved in the structure corresponding to the area B, and the structure is pressed and molded by a die;
3) And (3) applying adhesive to corresponding positions of the grooves of the middle support beam and the side beam and assembling the two. And after the whole is formed, the outer surface of the H-shaped blank is wholly smeared with adhesive or adhesive film is paved.
4) The carbon fiber unidirectional prepreg and the fabric are adopted to carry out integral cladding on the blank, the stress level of the H-shaped member at the joint of the middle supporting beam is higher when the structure bears torsional load, the thickness of the integral cladding is controlled to be more than 1mm, and the main fiber angle is +/-45 degrees.
5) And after the integral coating is finished, the prefabricated part is placed into a die to be precompacted and removed, the theoretical appearance of the product is combined to be trimmed, the part exceeding the theoretical outer profile is trimmed, and the concave area deviating from the product profile is filled. And placing the prefabricated part into a mould, and performing pressurizing, heating and curing by adopting a press.
6) After the carbon fiber part is manufactured, the metal shaft sleeve mounting areas at the two ends of the side beam are processed. Finally, the metal shaft sleeve is mounted on the composite member by adopting an adhesive, so that the final molding preparation of the product is realized, and the finally formed H-shaped composite member is shown in figure 1.
The H-shaped composite material member forming method adopts the middle support beam structure with the groove form, and can realize the connection between the middle support beam and the side beam without introducing the traditional connection forms such as a fastener, a metal corner box and the like.
According to the H-shaped composite material member forming method, the side beams adopt the layering forms with different orientation directions in the same plane, layering is carried out in a limited layering space in combination with the stress condition, and the forming quality problem caused by overlarge thickness of the composite material lamination is avoided under the condition of ensuring structural bearing.
According to the H-shaped composite material component forming method, the parts are connected in an integral cladding mode, the cross braces, the side beams and the skin are made of the same material, the interface binding force of the connection is strong, and effective integral cladding can be achieved.
The above-disclosed embodiments of the present invention are intended to aid in understanding the contents of the present invention and to enable the same to be carried into practice, and it will be understood by those of ordinary skill in the art that various alternatives, variations and modifications are possible without departing from the spirit and scope of the invention. The invention should not be limited to what has been disclosed in the examples of the specification, but rather by the scope of the invention as defined in the claims.
Claims (9)
1. The H-shaped composite material member forming method is characterized by comprising the following steps of:
layering the inner core structure of the middle support beam to obtain a middle support beam preform, and processing the two ends of the middle support beam preform to obtain a first connection structure;
layering the inner core structure of the side beam to obtain a side beam preform, and processing the middle of the side beam preform to obtain a second connecting structure matched with the first connecting structure;
assembling the middle support beam and the side beam by the first and second connection structures;
and integrally coating the assembled middle support beam and side beams by adopting a skin to obtain the H-shaped composite material component.
2. The method of claim 1, wherein the side beams are of a composite material rod structure with metal bushings, the metal bushings are arranged at two ends of the side beams, and the composite material is wound on the metal bushings in a shaft-surrounding laying design mode and is transited to an equal straight section.
3. The method of claim 2, wherein the layering of the inner core structure of the side sill comprises a class a layering and a class B layering, wherein the class a layering is a roll-to-roll layering and the class B layering is an axial layering.
4. The method of claim 1, wherein the first and second connection structures are grooves, and the center support beam and the side beams are assembled together through the grooves to achieve interpenetration of the layers.
5. The method of claim 4, wherein the adhesive is applied to the corresponding positions of the grooves of the middle support beam and the side sill and the middle support beam and the side sill are assembled together, and the outer surface of the H-shaped blank is integrally applied with the adhesive or the adhesive film, and then the H-shaped blank is integrally coated with the fibrous unidirectional prepreg and the fabric.
6. The method of claim 1, wherein the thickness of the integral cladding is controlled to be 1mm or more and the fiber angle is ±45°.
7. The method of claim 1, wherein the preform obtained after the complete overall cladding is put into a mold for pre-compaction and then ejected, trimmed in combination with the theoretical profile of the product, trimmed for the portion exceeding the theoretical outer profile, filled for the recessed area deviating from the product profile, and then put into the mold for compression heat curing using a press.
8. The method of claim 1, further comprising the step of: machining shaft sleeve mounting holes at corresponding positions of the side beams; installing a metal shaft sleeve through a shaft sleeve installation hole; and (5) finishing the appearance of the polished product.
9. An "H" shaped composite member formed according to the method of any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311521295.2A CN117549577A (en) | 2023-11-15 | 2023-11-15 | H-shaped composite material member forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311521295.2A CN117549577A (en) | 2023-11-15 | 2023-11-15 | H-shaped composite material member forming method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117549577A true CN117549577A (en) | 2024-02-13 |
Family
ID=89812192
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311521295.2A Pending CN117549577A (en) | 2023-11-15 | 2023-11-15 | H-shaped composite material member forming method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117549577A (en) |
-
2023
- 2023-11-15 CN CN202311521295.2A patent/CN117549577A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101351327B (en) | Technology for manufacturing compound structure with embedded precuring mold | |
| CN109849368B (en) | Method for processing composite material belt taper section variable-thickness revolving body connecting structure | |
| CA2719717A1 (en) | Method for manufacturing a core composite provided with cover layers on both sides | |
| CN101758923B (en) | Composite material box-shaped rib and manufacturing method thereof | |
| FR2831479A1 (en) | METHOD FOR MANUFACTURING PROFILES HAVING A SPECIFIC SURFACE CONDITION IN FIBER REINFORCED SYNTHETIC RESINS AND MACHINE FOR CARRYING OUT THE METHOD | |
| CN103029293B (en) | Connection method for resin-based carbon fiber composite truss rod members | |
| WO2023216673A1 (en) | Modular blade connection structure, method, and tooling | |
| CN108032696A (en) | passenger car composite material control arm | |
| CN109676958B (en) | Co-curing molded carbon fiber composite material airfoil and preparation method thereof | |
| CN113829638B (en) | Integrated molding method for composite material cabin section | |
| CN106426987B (en) | A kind of monolithic molding airfoil structure manufacturing process | |
| CN110549654A (en) | Integrated manufacturing method of fan blade and fan blade | |
| CN212400409U (en) | Variable cross-section fiber reinforced composite pipe | |
| CN117549577A (en) | H-shaped composite material member forming method | |
| CN112009001A (en) | Variable cross-section fiber reinforced composite material pipe and pipe-die integrated forming method | |
| CN214582823U (en) | Integrated formed composite cabin capable of performing electromagnetic shielding | |
| US20120321479A1 (en) | Method for production of a rotor blade for a wind turbine generator and a rotor blade | |
| CN115742343A (en) | Tenon-and-mortise connected composite material airfoil and forming method thereof | |
| CN115742367A (en) | High-modulus carbon fiber composite main frame, preparation method and preparation mold | |
| CN216836882U (en) | Fiber composite beam structure, arm section, arm support and mechanical equipment | |
| TWI530419B (en) | Method for forming core shell layer of carbon fiber bicycle and the forming structure thereof | |
| CN113119490A (en) | Integrally-formed composite cabin capable of performing electromagnetic shielding and forming process thereof | |
| CN110667821B (en) | Aircraft wing trailing edge composite material bulkhead structure and manufacturing method thereof | |
| CN115196141A (en) | High-temperature-resistant lightweight thin-wall reinforced cabin and forming method | |
| CN114654761B (en) | Z-splicing preparation method of corrugated sandwich board |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |