CN116604840A - Double-layer structure composite material containing casing and preparation method thereof - Google Patents
Double-layer structure composite material containing casing and preparation method thereof Download PDFInfo
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- CN116604840A CN116604840A CN202310473440.8A CN202310473440A CN116604840A CN 116604840 A CN116604840 A CN 116604840A CN 202310473440 A CN202310473440 A CN 202310473440A CN 116604840 A CN116604840 A CN 116604840A
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- 239000002131 composite material Substances 0.000 title claims abstract description 81
- 238000002360 preparation method Methods 0.000 title abstract description 10
- 239000010410 layer Substances 0.000 claims abstract description 125
- 239000000835 fiber Substances 0.000 claims abstract description 77
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 43
- 239000004917 carbon fiber Substances 0.000 claims abstract description 43
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical class C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 43
- 239000012792 core layer Substances 0.000 claims abstract description 41
- 238000000034 method Methods 0.000 claims description 18
- 238000009941 weaving Methods 0.000 claims description 17
- 238000009954 braiding Methods 0.000 claims description 14
- 239000004642 Polyimide Substances 0.000 claims description 9
- 229920001721 polyimide Polymers 0.000 claims description 9
- 239000011347 resin Substances 0.000 claims description 9
- 229920005989 resin Polymers 0.000 claims description 9
- 230000000149 penetrating effect Effects 0.000 claims description 8
- 229920006231 aramid fiber Polymers 0.000 claims description 7
- 238000005516 engineering process Methods 0.000 claims description 5
- 238000010438 heat treatment Methods 0.000 claims description 5
- 239000004760 aramid Substances 0.000 claims description 4
- 230000002452 interceptive effect Effects 0.000 claims description 4
- 238000000465 moulding Methods 0.000 claims description 4
- 101100134058 Caenorhabditis elegans nth-1 gene Proteins 0.000 claims description 3
- ICXAPFWGVRTEKV-UHFFFAOYSA-N 2-[4-(1,3-benzoxazol-2-yl)phenyl]-1,3-benzoxazole Chemical compound C1=CC=C2OC(C3=CC=C(C=C3)C=3OC4=CC=CC=C4N=3)=NC2=C1 ICXAPFWGVRTEKV-UHFFFAOYSA-N 0.000 claims description 2
- 239000004705 High-molecular-weight polyethylene Substances 0.000 claims description 2
- 125000000843 phenylene group Chemical group C1(=C(C=CC=C1)*)* 0.000 claims 1
- 239000011229 interlayer Substances 0.000 abstract description 6
- 238000004804 winding Methods 0.000 description 13
- 230000000052 comparative effect Effects 0.000 description 10
- 239000004744 fabric Substances 0.000 description 3
- 238000009940 knitting Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000002356 single layer Substances 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 125000001140 1,4-phenylene group Chemical group [H]C1=C([H])C([*:2])=C([H])C([H])=C1[*:1] 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000805 composite resin Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 230000002787 reinforcement Effects 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
- B29C70/34—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
-
- D—TEXTILES; PAPER
- D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
- D04C—BRAIDING OR MANUFACTURE OF LACE, INCLUDING BOBBIN-NET OR CARBONISED LACE; BRAIDING MACHINES; BRAID; LACE
- D04C1/00—Braid or lace, e.g. pillow-lace; Processes for the manufacture thereof
- D04C1/02—Braid or lace, e.g. pillow-lace; Processes for the manufacture thereof made from particular materials
-
- D—TEXTILES; PAPER
- D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
- D04C—BRAIDING OR MANUFACTURE OF LACE, INCLUDING BOBBIN-NET OR CARBONISED LACE; BRAIDING MACHINES; BRAID; LACE
- D04C1/00—Braid or lace, e.g. pillow-lace; Processes for the manufacture thereof
- D04C1/06—Braid or lace serving particular purposes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/614—Fibres or filaments
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Composite Materials (AREA)
- Combustion & Propulsion (AREA)
- Manufacturing & Machinery (AREA)
- Textile Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Woven Fabrics (AREA)
Abstract
The invention provides a double-layer structure composite material containing casing and a preparation method thereof. The double-layer structure containing casing is in a structure form of a carbon fiber composite material core layer and an organic fiber containing layer, and the organic fiber containing layer fiber is integrally woven on the carbon fiber composite material core layer. The high-strength carbon fiber composite material is adopted as the bearing layer of the containing casing structure, so that the capability of the containing casing for maintaining structural integrity under impact load is effectively improved; the organic fiber containing layer adopts continuous staggered interlocking of warp yarns and weft yarns, so that the interlayer failure risk of the containing case after being impacted is eliminated, and the containing capacity of the case is improved.
Description
Technical Field
The invention belongs to the technical field of composite materials with integrated structural and functional functions, and relates to a double-layer composite material containing casing and a preparation method thereof.
Background
The turbofan engine containment casing not only provides access for the outside air, but also needs to contain high-speed and high-energy dangerous chips when the blades rotating at high speed are impacted by the outside or are broken by internal defects, so that the turbofan engine containment casing needs to have sufficient structural rigidity and broken blade containment capability. The traditional containing casing mostly adopts a half composite material structure of winding metal inner rings by using all-metal materials or aramid fibers, and compared with the traditional containing casing, the resin-based composite material has the characteristics of low density, specific strength, specific modulus and the like, and the preparation of the composite material containing casing becomes a necessary trend under the drive of continuously improving the thrust-weight ratio and the efficiency of an engine.
At present, a composite material containing casing is generally prepared by adopting a carbon fiber composite material, such as a carbon fiber woven preform which is adopted by U.S. Pat. No. 3,979B 2, european patent EP1674244 and European patent EP1674671, on a winding mandrel, and then the composite material containing casing is prepared by resin liquid molding. Compared with organic fibers, the carbon fiber composite material has high density, high modulus and low toughness, and has larger weight and limited weight-reducing effect than the organic fiber composite material under the condition of realizing the same containing capacity; experiments prove that the containing casing prepared by the preform winding process is bonded by resin only at the interlayer interface of the multilayer preform, fiber reinforcement is avoided, resin matrix breakage is easy to occur when the multilayer preform is impacted, so that layering failure is caused, meanwhile, the tail end of the outermost preform in the winding process belongs to a free end, large-area tearing and debonding are easy to occur after the multilayer preform is impacted, layering of the casing is caused, even disassembly of the casing occurs, and high potential safety hazard exists.
Disclosure of Invention
The purpose of the invention is that: in order to overcome the technical defect that the winding of a preform in the prior art has interlayer interface weak points, the invention provides a double-layer structure composite material containing casing and a preparation method thereof.
In order to solve the technical problem, the technical scheme of the invention is as follows:
on one hand, a double-layer composite material containing casing is provided, which consists of a carbon fiber composite material core layer and an organic fiber composite material containing layer, wherein,
the carbon fiber composite material core layer is prepared by paving unidirectional carbon fiber prepreg and adopting autoclave molding technology;
the organic fiber composite material containing layer is prepared by integrally weaving organic fiber fibers on the carbon fiber composite material core layer and adopting an RTM forming technology; the integral braiding rule of the organic fiber of the containing layer is as follows:
the organic fiber yarns of the containing layer take the axial direction of the case as the weaving warp direction and the circumferential direction of the case as the weaving weft direction, wherein the warp yarns and the weft yarns of the organic fiber yarns are continuous yarns;
the total number of the organic fiber weft yarns is P/b, wherein P is the width of the containing layer required by the axial direction, and b is the distance of the weft yarns moving along the axial direction of the core layer;
the warp yarns of the crossing openings through which the weft yarns of the odd columns pass are the same, the warp yarns of the crossing openings through which the weft yarns of the even columns pass are the same, the warp yarns of the crossing openings through which the weft yarns of the odd columns and the weft yarns of the even columns pass are different, an interactive interlocking structure is formed along the circumferential direction of the case, and the interface between the warp yarn rows is eliminated; after passing through one layer of warp yarn opening around the machine case, the continuous weft yarn continuously passes through the next layer of warp yarn opening after moving along the thickness direction until reaching the designated thickness H, and eliminating the interface between warp yarn distributing layers;
the warp yarn and the weft yarn of the organic fiber yarn of the containing layer are continuous yarns, and are continuously woven through the weft yarns, so that the warp yarn and the weft yarn form an integral braided fabric, and the interface of pure resin bonding is eliminated.
On one hand, the preparation method of the double-layer structure composite material containing casing is provided, and the preparation method comprises the following steps:
(1) Preparing a carbon fiber composite material core layer: paving the carbon fiber prepreg on a forming core mold, and solidifying and demolding to obtain a carbon fiber composite material core layer with a net size;
(2) Preparing an organic fiber composite material containing layer:
a) Determining the number of layers N of organic fiber warp yarns according to the thickness H requirement of a containing layer, arranging M rows of warp yarns on the surface of a carbon fiber composite material core layer along the circumferential direction of a casing, starting from the upper end of the containing area, introducing a first row of first circle of weft yarns from the cross opening of the warp yarns of adjacent rows, sequentially penetrating through the openings of the ith row and the (i+1) th row of warp yarns of the first layer along the circumferential direction of the casing, returning to the initial position of the first row of first circle of weft yarns after totally penetrating through the openings of the ith row and the (i+1) th row of warp yarns of the M rows of warp yarns, continuously penetrating through the openings of the ith row and the (i+1) th row of warp yarns along the circumferential direction of the casing along the distance H/N, returning to the initial position of the first row of second circle of weft yarns after totally penetrating through the M rows of warp yarns, sequentially completing the N-circle warp yarns to be interlocked to reach the appointed thickness H, and completing the weaving of the first row of weft yarns, wherein the weft yarns are positioned at the nth position of the first row;
b) The weft yarn sequentially passes through the openings of the ith+1th row and the (i+2) th row of warp yarns of the nth layer after moving a distance b along the axial direction of the core layer to form a second row of nth weft yarn, the weft yarn returns to the starting position of the second row of nth weft yarn after passing through the M rows of warp yarns in total, the weft yarn continuously passes through the openings of the ith+1th row and the (i+2) th row of warp yarns of the (n+1) th layer along the circumferential direction of the casing along the thickness direction to form a second row of nth-1 weft yarn, N layers of warp yarns are interlocked to reach a specified thickness H after N layers of weft yarns are wound in sequence, the second row of weft yarn braiding is completed, the weft yarn reaches the first circle position of the second row, and the weft yarn axially moves a distance b along the core layer to start braiding of the next first circle of weft yarn; wherein i is a positive integer, and i is less than or equal to M-1.
c) Repeating the step a) and the step b), and after weaving the weft yarns in the row P/b, reaching the width P required by the containing layer along the axial direction to obtain the integrally woven organic fiber containing layer.
d) Curing and forming the composite material containing casing: and filling resin in the organic fiber containing layer, and heating and curing to obtain the double-layer composite material containing casing.
The laying method of the carbon fiber composite material core layer on the forming core mold is one or more of manual laying, self-feeding wire laying or automatic tape laying.
The organic fiber yarns of the containing layer take the axial direction of the casing as the weaving warp direction and the circumferential direction of the casing as the weaving weft direction. The warp yarns and the weft yarns in the organic fibers of the containing layer are continuous yarns.
The warp yarns of the crossing openings, through which the weft yarns of the odd columns pass, in the organic fiber weft yarns of the containing layer are the same, the warp yarns of the crossing openings, through which the weft yarns of the even columns pass, are the same, the warp yarns of the crossing openings, through which the weft yarns of the odd columns and the weft yarns of the even columns pass, are different, an interactive interlocking structure is formed along the circumferential direction of the case, and the interface between the warp yarn rows is eliminated; after passing through one layer of warp yarn openings around the machine case, the continuous weft yarn continuously passes through the next layer of warp yarn openings after moving along the thickness direction until reaching the designated thickness H, and the interface between warp yarn distributing layers is eliminated.
The organic fiber of the containing layer is one or more of aramid fiber, high molecular weight polyethylene fiber, poly-p-phenylene benzobisoxazole fiber, poly-p-benzimidazole fiber, poly-p-phenylene pyridobisimidazole fiber and polyimide fiber.
The beneficial effects of the invention are as follows:
the organic fiber in the containing area sequentially passes through the warp openings by adopting the continuous weft yarns, the warp yarns of the crossing openings through which the weft yarns in the odd columns pass are the same, the warp yarns of the crossing openings through which the weft yarns in the even columns pass are the same, the warp yarns of the crossing openings through which the weft yarns in the odd columns and the weft yarns in the even columns pass are different, an interactive interlocking structure is formed along the circumferential direction of the case, the integral weaving is realized through the continuous weft yarns through the designed warp openings, and the interface between the warp arrangement columns is eliminated; after the continuous weft yarn passes through one layer of warp yarn opening around the casing, the weft yarn moves along the thickness direction and then passes through the next layer of warp yarn opening continuously until reaching the designated thickness H, the interface between warp yarn distributing layers is eliminated, the containing layer of the integral weaving structure is formed, the interlayer failure risk of the containing casing after being impacted is effectively avoided, and the containing capacity of the casing is improved.
Compared with organic fibers, the carbon fiber composite material has the advantages of high density, high modulus and low toughness, and under the condition of realizing the same containing capacity, the carbon fiber composite material has larger thickness than the organic fiber composite material, so that the weight of the case is larger.
Compared with the existing braiding preform winding process, the method adopts the integral braiding technology, does not need secondary winding, requires less production equipment and has higher production efficiency.
The structure bearing function and the containing function are separated, the structure bearing capacity and the containing capacity are respectively realized through the carbon fiber composite material and the organic fiber composite material, and the structure bearing function and the containing capacity can be designed and checked separately according to the function requirements, so that the development period is greatly shortened.
Drawings
In order to more clearly illustrate the technical solution of the implementation of the present invention, the following will make a simple solution to the drawings that are needed in the examples of the present invention. It is evident that the drawings described below are only some embodiments of the invention and that other drawings may be obtained from these drawings without inventive effort for a person skilled in the art. The dimensions of the various elements shown in the figures are not drawn to actual scale.
FIG. 1 is a schematic view of a double-layer composite containment casing;
FIG. 2 is a schematic axial cross-section of a double-layer composite containment casing;
FIG. 3 is a schematic view showing the circumferential arrangement of the warp yarns of the organic fiber in the case in an embodiment;
FIG. 4 is an axial cross-sectional schematic view of the woven structure of organic fibers at position L1 along the casing circumferential direction;
FIG. 5 is an axial cross-sectional schematic view of the woven structure of organic fibers at position L2 along the casing circumferential direction;
FIG. 6 is a schematic view of the structure of the case of comparative example 1;
FIG. 7 is a diagram of a damaged case of the embodiment 1;
FIG. 8 is a diagram of a damaged case of comparative example 1;
in the figure: 1. a carbon fiber composite core layer; 2. an organic fiber containment layer; 21. a first row of weft yarns; 211. a first row of first turns of weft yarns; 212. a first row of second turns of weft yarns; 21N, the first row of N-th weft yarns; 22. a second row of weft yarns; 221. second columnA first turn of weft yarns; 222. a second row of second weft yarns; 22N, the second row of N-th weft yarns; m is M i An ith column of warp yarns; m is M i+1 An i+1th column warp yarn; m is M i+2 An i+2th column warp yarn; 231. a third row of first turns of weft yarns; 23N third column N-th weft yarn.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without making any inventive effort are intended to fall within the scope of the present invention.
Features of various aspects of embodiments of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. Well-known structures and techniques have not been shown in detail in the various drawings and the following description in order not to unnecessarily obscure the present invention.
Fig. 1 shows a double-layer structure composite material containing casing, a carbon fiber composite material core layer 1 is arranged on the inner layer of the casing, an organic fiber containing layer 2 is arranged on the outer ring of the carbon fiber composite material core layer, the axial width of the organic fiber containing layer along the casing is P, the thickness of the organic fiber containing layer is H, the length L=pi D of the organic fiber containing layer is the outer diameter of the carbon fiber composite material core layer. Fig. 2 shows an axial sectional schematic view of a double-layer composite material containing casing, wherein a carbon fiber composite material core layer 1 is of a double-flanging structure with front and rear flange edges, and an organic fiber containing layer 2 is tightly attached to the surface of the carbon fiber composite material core layer.
Fig. 3 shows a schematic view of a circumferential arrangement of M columns of organic fiber warp yarns of N layers along a casing in an embodiment, where a certain column of warp yarns is an ith column of warp yarns, and the relative positional relationship of the ith+1th column of warp yarns is a circumferentially counterclockwise next column, and similarly, the ith+2th column of warp yarns is a circumferentially counterclockwise next column relative to the ith+1th column of warp yarns.
For better illustration of the warp and weft interlocking structure, fig. 4 and 5 show schematic axial sectional views of the organic fiber woven structure at positions L1 and L2 along the circumferential direction of the casing, wherein L1 and L2 are any two positions of the organic fiber containing layer in fig. 1 along the outer length L of the carbon fiber composite core, and for convenience of understanding, fig. 4 specifically shows a first row of weft yarns 21 and a second row of weft yarns 22, from the upper end of the containing area, the adjacent row of warp yarns cross-open to introduce a first row of weft yarns 211, the first row of weft yarns sequentially pass through the openings of the ith row of warp yarns and the (i+1) th row of warp yarns along the circumferential direction of the casing, and in total pass through the M row of warp yarns and return to the first row of weft yarn starting position, the weft yarns continue to sequentially pass through the openings of the second layer ith row of warp yarns along the circumferential direction of the thickness H to form a first row of weft yarns 212, in total pass through the M row of warp yarns and then return to the first row of weft yarn starting position to sequentially complete N number of weft yarns to complete the winding of N number of weft yarns, and then the first row 21 is at the designated position of weft yarns is reached;
as shown in fig. 5, after the weaving of the nth weft yarn 21N in the first row is completed, the weft yarn sequentially passes through the openings of the ith+1th row and the ith+2th row of the nth layer after moving b distance along the axial direction of the core layer to form a second row of nth weft yarn 22N, and after the sum passes through the M rows of warp yarns, the weft yarn sequentially passes back to the starting position of the nth weft yarn in the second row, the weft yarn sequentially passes through the openings of the ith+1th row and the ith+2th row of the ith weft yarn in the thickness direction of the case and forms the second row of the nth-1 weft yarn after continuously passing through the openings of the ith+1th row and the ith+2th row of the nth weft yarn in the thickness direction of the case in the inward direction of H/N distance, the N layers of weft yarn is sequentially wound, the N layers of the warp yarns are interlocked to reach the designated thickness H after sequentially completing the winding of the N layers of weft yarns, the weaving of the second row of weft yarn is completed, the weft yarn reaches the position of the first row 221, the weft yarn is axially moved b distance along the core layer to start the weaving of the first row of the first weft yarn 231, the third row of the weft yarn sequentially passes through the opening of the ith+1th row of the ith warp yarn 21 in the first row, and the first row of weft yarn is consistent with the opening of the first row weft yarn 21 in the thickness, and the first row of the weft yarn is sequentially, after the weft yarn is sequentially moved in the thickness.
The warp yarns of the intersecting openings through which the weft yarns of the odd columns pass in the weft yarns of the P/b columns of the organic fibers of the containing layer prepared in this way are identical, and the warp yarns of the intersecting openings through which the weft yarns of the even columns pass are identical.
Example 1
Sequentially paving 32 layers of carbon fiber composite material prepregs on a molding core mold in a manual paving mode, wherein the paving mode is [ -45/0/45/90 [ -45/0 ]] 4s And packaging and vacuumizing the carbon fiber composite material core layer by adopting a vacuum bag, putting the carbon fiber composite material core layer into an autoclave, and curing at high temperature and high pressure to obtain the carbon fiber composite material core layer.
The method comprises the steps that a containing layer fiber is selected from polyimide fibers, the thickness of the containing layer fiber is designed according to 15mm, the single-layer thickness of the polyimide fiber warp yarn is 1mm, the number of polyimide fiber warp yarn layers is 15, 15 layers of 100-row warp yarns are arranged on the surface of a carbon fiber composite material core layer along the axial direction of a case, a first-row weft yarn is introduced from the upper end of a containing area, the first-row weft yarn case passes through openings of the 1 st-row warp yarn and the 2 nd-row warp yarn in sequence in the circumferential direction of the first-row weft yarn case, the total passes through 100-row warp yarns and returns to the first-row weft yarn starting position in sequence, 15-layer warp yarns are interlocked to reach the appointed thickness 15mm after 15-row weft yarn winding is completed in sequence, the weft yarn is positioned at the 15-th-row position of the first-row weft yarn knitting at the moment, and the weft yarn is moved outwards by 1mm along the thickness direction and continuously passes through the openings of the 1 st-row warp yarn and the 2 nd-row warp yarn in sequence in the circumferential direction of the thickness direction of the case;
the weft yarn moves along the axial direction of the core layer by 0.2mm distance and sequentially passes through openings of the 15 th layer, the 2 nd row and the 3 rd row of warp yarns to form a second row, 15 th circle of weft yarns, and returns to the starting position of the second row, 15 th circle of weft yarns after totally passing through 100 rows of warp yarns, the weft yarn moves inwards by 1mm distance along the thickness direction and continuously passes through openings of the 14 th layer, the 2 nd row and the 3 rd row of warp yarns along the circumferential direction of the machine case to form a second row, 14 th circle of weft yarns, 15 layers of warp yarns are interlocked to reach the designated thickness of 15mm after 15 circles of weft yarns are wound in sequence, the second row of weft yarns are woven, the weft yarns reach the first circle position of the second row, and the weft yarns move along the axial direction of the core layer by 0.2mm distance to start the 3 rd row of weft yarns to weave;
and (3) repeating the weft yarn winding and braiding process, and after completing the braiding of 100 rows of weft yarns, reaching the width of 20mm of the containing layer along the axial direction, thereby obtaining the integrally braided polyimide fiber containing layer.
And filling resin in the polyimide fiber integral braiding containing layer, and heating and solidifying to obtain the double-layer structure composite material containing casing.
Example 2
Carbon fiber composite core preparation reference example 1.
The method comprises the steps that aramid fibers are selected as a containing layer fiber, the thickness of the containing layer is designed according to 15mm, the single-layer thickness of the aramid fibers is 0.5mm, the number of polyimide fiber warp yarns is 30, 30 layers of 100 rows of warp yarns are arranged on the surface of a carbon fiber composite material core layer along the axial direction of a machine case, from the upper end of the containing region, the first row of first circle weft yarns are introduced into the adjacent warp yarns, the machine case of the first circle passes through openings of the 1 st row and the 2 nd row of warp yarns in sequence in the circumferential direction of the first circle, the total of the first circle weft yarns passes through openings of the 100 th row of warp yarns in sequence and returns to the first row of second circle weft yarns in the circumferential direction of the machine case, 15 layers of warp yarns are interlocked to reach the appointed thickness of 15mm after the first row of weft yarns are wound, the weft yarns are positioned at the 30 th row of first circle position of the first row of warp yarns in sequence, the weft yarns are moved outwards by 1mm along the thickness direction of the machine case, and the total of the weft yarns pass through the openings of the 2 nd row of warp yarns in sequence in the circumferential direction of the first row of the 30 th position;
the weft yarn moves along the axial direction of the core layer by 0.2mm distance and sequentially passes through openings of the 30 th layer of warp yarns and the 3 rd layer of warp yarns to form a second row of 30 th weft yarn, and returns to the starting position of the second row of 30 th weft yarn after totally passing through 100 th layer of warp yarns, the weft yarn moves inwards by 1mm distance along the thickness direction and continuously passes through openings of the 29 th layer of warp yarns and the 3 rd layer of warp yarns along the circumferential direction of the casing to form a second row of 14 th weft yarn, 30 layers of warp yarns are interlocked to reach the designated thickness of 15mm after 30 layers of weft yarns are wound in sequence, the second row of weft yarn knitting is completed, the weft yarn reaches the first circle position of the second row, and the weft yarn moves along the axial direction of the core layer by 0.2mm distance to start the knitting of the 3 rd row of first weft yarn;
and (3) repeating the weft yarn winding and braiding process, and after completing the braiding of 100 rows of weft yarns, reaching the width of 20mm of the containing layer along the axial direction, thereby obtaining the integrally braided aramid fiber containing layer.
And filling resin in the aramid fiber integral braiding containing layer, and heating and solidifying to obtain the double-layer structure composite material containing casing.
Comparative example 1
Preparation of carbon fiber composite core layer reference example 1
As shown in fig. 6, a polyimide fiber fabric with the thickness of 1mm is wound on a carbon fiber composite material core layer 1, a composite material containing casing with the containing area thickness of 15mm is obtained after 15 layers are wound, the fabric is filled with the same resin matrix as that of the embodiment 1, and the composite material containing casing is obtained after heating and solidifying.
Comparative example 2
Referring to example 1, a difference from example 1 is that the weft yarn is broken once every 2 columns of weft yarns are completed to form 50 weft yarn junctions.
Comparative example 3
Referring to example 1, the difference from example 1 is that the warp yarn is broken 3 times in the axial direction of the case, forming 3 warp yarn junctions.
The case is contained in the case that the simulated blade with the mass of 1000g flies to break and strike at a high speed rotation state, the containing state of the case is determined under different containing energies by carrying out the test of the blade flying to break and strike the case under different rotation speeds, and the test data are shown in table 1.
Table 1 comparative table of the containment properties of the case of composite materials of different structures
Compared with the comparative example, the method provided by the invention can obviously improve the inclusion performance of the composite material inclusion casing. For example, the composite material containing cases in the examples 1 and 2 have the containing energies of 77769J and 61839J, respectively, and the blades do not puncture the containing case to form a containing state, the containing case adopting the prefabricated body winding structure in the comparative example 1 has interlayer interface failure at the 52758J energy level to form an unconditioned state, and weak points exist at the weft/warp yarn joints in the comparative examples 2 and 3, and the condition of failure of the yarn connecting points also occurs to form an unconditioned state.
The test result shows that the double-layer composite material casing prepared in the embodiment 1 damages a real object, and after the double-layer composite material casing is impacted by the high-speed flying-off blades, the double-layer composite material casing is only internally scratched and does not have layering failure. The composite material casing prepared in comparative example 1 has damaged material, and it can be seen that after the composite material casing is impacted by the high-speed flying-off blade, the casing containing layer has obvious interlayer interface failure, and the multi-layer wound prefabricated body is separated after being impacted and fails to contain the failed blade. As shown in fig. 7 and 8.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think about various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered in the scope of the present invention.
Claims (8)
1. The double-layer structure composite material containing casing consists of a carbon fiber composite material core layer and an organic fiber composite material containing layer, and is characterized in that: wherein,,
the carbon fiber composite material core layer is prepared by paving unidirectional carbon fiber prepreg and adopting autoclave molding technology;
the organic fiber composite material containing layer is prepared by integrally weaving organic fiber fibers on the carbon fiber composite material core layer and adopting an RTM forming technology; the integral braiding rule of the organic fiber of the containing layer is as follows:
the organic fiber yarns of the containing layer take the axial direction of the case as the weaving warp direction and the circumferential direction of the case as the weaving weft direction, wherein the warp yarns and the weft yarns of the organic fiber yarns are continuous yarns;
the total number of the organic fiber weft yarns is P/b, wherein P is the width of the containing layer required by the axial direction, and b is the distance of the weft yarns moving along the axial direction of the core layer;
the warp yarns of the crossing openings through which the weft yarns of the odd columns pass are the same, the warp yarns of the crossing openings through which the weft yarns of the even columns pass are the same, the warp yarns of the crossing openings through which the weft yarns of the odd columns and the weft yarns of the even columns pass are different, an interactive interlocking structure is formed along the circumferential direction of the case, and the interface between the warp yarn rows is eliminated; after passing through one layer of warp yarn openings around the machine case, the continuous weft yarn continuously passes through the next layer of warp yarn openings after moving along the thickness direction until reaching the designated thickness H, and the interface between warp yarn distributing layers is eliminated.
2. The method for preparing the double-layer structure composite material containing casing according to claim 1, which is characterized by comprising the following steps:
(1) Preparing a carbon fiber composite material core layer: paving the carbon fiber prepreg on a forming core mold, and solidifying and demolding to obtain a carbon fiber composite material core layer with a net size;
(2) Preparing an organic fiber composite material containing layer:
a) Determining the number of layers N of organic fiber warp yarns according to the thickness H requirement of a containing layer, arranging M rows of warp yarns on the surface of a carbon fiber composite material core layer along the circumferential direction of a casing, starting from the upper end of the containing area, introducing a first row of first circle of weft yarns from the cross opening of the warp yarns of adjacent rows, sequentially penetrating through the openings of the ith row and the (i+1) th row of warp yarns of the first layer along the circumferential direction of the casing, returning to the initial position of the first row of first circle of weft yarns after totally penetrating through the openings of the ith row and the (i+1) th row of warp yarns of the M rows of warp yarns, continuously penetrating through the openings of the ith row and the (i+1) th row of warp yarns along the circumferential direction of the casing along the distance H/N, returning to the initial position of the first row of second circle of weft yarns after totally penetrating through the M rows of warp yarns, sequentially completing the N-circle warp yarns to be interlocked to reach the appointed thickness H, and completing the weaving of the first row of weft yarns, wherein the weft yarns are positioned at the nth position of the first row;
b) The weft yarn sequentially passes through the openings of the ith+1th row and the (i+2) th row of warp yarns of the nth layer after moving a distance b along the axial direction of the core layer to form a second row of nth weft yarn, the weft yarn returns to the starting position of the second row of nth weft yarn after passing through the M rows of warp yarns in total, the weft yarn continuously passes through the openings of the ith+1th row and the (i+2) th row of warp yarns of the (n+1) th layer along the circumferential direction of the casing along the thickness direction to form a second row of nth-1 weft yarn, N layers of warp yarns are interlocked to reach a specified thickness H after N layers of weft yarns are wound in sequence, the second row of weft yarn braiding is completed, the weft yarn reaches the first circle position of the second row, and the weft yarn axially moves a distance b along the core layer to start braiding of the next first circle of weft yarn;
c) Repeating the step a) and the step b), and after weaving the weft yarns in the row P/b, reaching the width P required by the containing layer along the axial direction to obtain the integrally woven organic fiber containing layer.
d) Curing and forming the composite material containing casing: and filling resin in the organic fiber containing layer, and heating and curing to obtain the double-layer composite material containing casing.
3. The method of claim 2, wherein the carbon fiber composite core layer is applied to the forming mandrel by one or more of manual application, self-feeding wire application, or automatic tape application.
4. The method of claim 2, wherein the containment layer of organic fiber yarns has a casing axial direction as a weave warp direction and a casing circumferential direction as a weave weft direction.
5. The method of claim 2, wherein the warp and weft yarns in the organic fiber of the containment layer are continuous yarns.
6. The method of claim 2, wherein the intersecting openings of the containing layer for the organic fiber weft yarns are identical in warp yarns for the intersecting openings through which the weft yarns of the odd columns pass, the intersecting openings of the weft yarns of the even columns pass are identical in warp yarns for the intersecting openings through which the weft yarns of the odd columns and the weft yarns of the even columns pass, and the intersecting openings of the weft yarns of the odd columns and the warp yarns of the intersecting openings of the weft yarns of the even columns pass are different, so that an alternate interlocking structure is formed along the circumferential direction of the casing, and interfaces between the warp rows are eliminated; after passing through one layer of warp yarn openings around the machine case, the continuous weft yarn continuously passes through the next layer of warp yarn openings after moving along the thickness direction until reaching the designated thickness H, and the interface between warp yarn distributing layers is eliminated.
7. The method according to claim 2, wherein i is a positive integer, i.ltoreq.M-1.
8. The method of claim 2, wherein the organic fibers of the containment layer are one or more of aramid fibers, high molecular weight polyethylene fibers, poly-p-phenylene benzobisoxazole fibers, poly-p-benzimidazole fibers, poly-phenylene pyridobisimidazole fibers, and polyimide fibers.
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