CN111039687B - Damage-free hole making method for continuous fiber reinforced ceramic matrix composite - Google Patents
Damage-free hole making method for continuous fiber reinforced ceramic matrix composite Download PDFInfo
- Publication number
- CN111039687B CN111039687B CN201911297763.6A CN201911297763A CN111039687B CN 111039687 B CN111039687 B CN 111039687B CN 201911297763 A CN201911297763 A CN 201911297763A CN 111039687 B CN111039687 B CN 111039687B
- Authority
- CN
- China
- Prior art keywords
- fiber
- ceramic matrix
- continuous fiber
- hole
- matrix composite
- 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.)
- Active
Links
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/01—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
- C04B35/56—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides
- C04B35/565—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide
- C04B35/571—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide obtained from Si-containing polymer precursors or organosilicon monomers
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
- C04B35/58—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on borides, nitrides, i.e. nitrides, oxynitrides, carbonitrides or oxycarbonitrides or silicides
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/522—Oxidic
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5244—Silicon carbide
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5248—Carbon, e.g. graphite
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5252—Fibers having a specific pre-form
- C04B2235/5256—Two-dimensional, e.g. woven structures
Abstract
The invention relates to a damage-free hole making method for a continuous fiber reinforced ceramic matrix composite, which realizes hole making and keeps the structural integrity of the continuous fiber reinforced ceramic matrix composite at the same time through the process control of fiber laying template design and preparation, continuous fiber laying, matrix filling, damage-free hole making and the like, compared with the existing material reduction processing hole making method, the damage-free hole making method can not cause damage to continuous fibers and avoid other defect damage caused by processing, and can improve the mechanical property of the continuous fiber reinforced ceramic matrix composite containing a hole structure by 10-60%.
Description
Technical Field
The invention relates to a method for manufacturing a hole in a continuous fiber reinforced ceramic matrix composite without damage, belonging to the technical field of preparation of ceramic matrix composites.
Background
The continuous fiber reinforced ceramic matrix composite has the advantages of high temperature resistance, oxidation resistance, wear resistance, corrosion resistance and the like of ceramic materials, and has excellent external impact load resistance due to the reinforcing and toughening effects of the continuous fibers. The continuous fiber reinforced ceramic matrix composite is more and more widely applied in the fields of advanced aircraft engine hot end parts, advanced aircraft thermal protection systems and the like by virtue of good high-temperature stability and high-temperature mechanical properties.
Continuous fiber reinforced ceramic matrix composites typically require fabrication of holes, such as assembly holes for joining, film holes for cooling, etc., for practical applications. At present, the commonly used hole making mode is to adopt a material reducing processing mode to make holes on a complete material, such as machining drilling hole making, laser hole making, water cutting hole making, linear cutting hole making and the like, and all the modes can cause continuous fibers in the material to be damaged, so that the mechanical property of the material is reduced, and the integral use performance of a component is further influenced. How to realize hole making and simultaneously maintain the structural integrity of the continuous fiber reinforced ceramic matrix composite material is a problem to be solved urgently in the application field of the continuous fiber reinforced ceramic matrix composite material.
Disclosure of Invention
The invention provides a method for manufacturing a hole in a continuous fiber reinforced ceramic matrix composite material without damage aiming at the prior art, and aims to realize that the structure of the continuous fiber reinforced ceramic matrix composite material is not damaged when the hole is manufactured, so that the mechanical property of the continuous fiber reinforced ceramic matrix composite material with the hole structure is improved.
The technical solution of the invention is as follows:
the method for manufacturing the hole without damage of the continuous fiber reinforced ceramic matrix composite material comprises the following steps:
designing and preparing a fiber laying template according to the requirements of the size, the shape and the position of a hole, wherein a pre-filler is arranged at the corresponding position of the fiber laying template where the hole needs to be made, and the pre-filler has the characteristics of size, shape, position and the like corresponding to the hole;
laying the continuous fibers on a fiber laying template according to preset parameters, wherein the preset parameters comprise fiber running direction, fiber volume fraction and fiber preform thickness, and the positions needing hole making are occupied by the pre-fillers and are bypassed by the fibers to obtain a continuous fiber preform;
filling ceramic matrixes in pores of the continuous fiber preform to complete densification of the continuous fiber reinforced ceramic matrix composite;
and step four, removing the fiber laying template and the pre-filler to finish the damage-free hole making.
In one implementation, the fiber placement template has a molded surface which is adaptive to the structural characteristics of the continuous fiber reinforced ceramic matrix composite member and has a function of shaping the continuous fiber reinforced ceramic matrix composite, the shapes, the positions and the sizes of the fiber placement template and the pre-filler are kept unchanged in the continuous fiber placement and matrix filling processes, the physical and chemical properties of the fiber placement template and the pre-filler are stable, and the materials are selected from graphite, ceramics, high-temperature alloys and high polymers.
In one implementation, the fiber placement template restrains the pre-filler to ensure accurate positioning of the pre-filler in the continuous fiber placement and ceramic matrix filling processes, and the restraining mode can adopt integrated forming, joggling, bonding and welding.
In one implementation, the cross-sectional shapes of the holes are circular holes and profiled holes, and the hole diameter is not less than 0.1 mm.
In one implementation, the continuous fibers are carbon fibers, silicon carbide fibers, nitride fibers, or oxide fibers.
In one implementation, the continuous fiber laying mode is filament laying, tape laying, ply laying, weaving or hand knitting, and the continuous fiber preform structure is a unidirectional tape, a 2D ply, a 2.5D fabric or a 3D fabric.
In one implementation, the ceramic matrix is a silicon carbide, nitride ceramic, or oxide ceramic.
In one implementation, the fiber placement template and the pre-filler are removed from the continuous fiber reinforced ceramic matrix composite by direct stripping, subtractive processing.
The invention has the advantages and beneficial effects that:
firstly, the method for manufacturing the hole without damage of the continuous fiber reinforced ceramic matrix composite realizes the hole manufacturing and simultaneously keeps the structural integrity of the continuous fiber reinforced ceramic matrix composite through the process control of the design and preparation of the fiber laying template, the continuous fiber laying, the matrix filling, the hole manufacturing without damage and the like, compared with the existing method for manufacturing the hole by reducing the material, the method can not damage the continuous fiber and avoid the damage of other defects caused by the processing, and can improve the mechanical property of the continuous fiber reinforced ceramic matrix composite containing the hole structure by 10 to 60 percent.
Secondly, the method for manufacturing the hole in the continuous fiber reinforced ceramic matrix composite without damage has strong designability on the shape and the direction of the hole, particularly provides a high-efficiency and low-cost solution for preparing the special-shaped hole, and greatly improves the hole manufacturing precision because the hole manufacturing precision is not limited by processing conditions.
The invention is also suitable for making holes in other continuous fiber reinforced composite materials.
Description of the drawings:
FIG. 1 is a schematic illustration of an example fiber placement template, wherein a: isobologram, b: a top view;
FIG. 2 is a schematic representation of continuous fiber placement in the examples;
FIG. 3 is a schematic illustration of matrix filling in an example;
FIG. 4 is a schematic view of an example of a non-damaged hole.
The specific implementation mode is as follows:
the invention is described in further detail below with reference to the following embodiments and with reference to the following figures:
referring to the attached drawings 1-4, in the present embodiment, the size of the continuous silicon carbide fiber reinforced silicon carbide ceramic matrix composite flat plate member is 100mm × 50mm × 5mm, the center of the flat plate member contains 1 straight hole 5 with a diameter of 6mm, and the steps of the method for making the hole without damage of the continuous fiber reinforced ceramic matrix composite are as follows:
designing and preparing a fiber laying template 1 according to the requirements of the size, the shape and the position of a hole 5, wherein the size of the fiber laying template 1 is 100mm multiplied by 50mm multiplied by 10mm, a pre-filler 2 is arranged in the center of the fiber laying template 1, the diameter of the pre-filler 2 is 6mm, the thickness of the pre-filler 2 is 5mm, and the fiber laying template 1 and the pre-filler 2 are integrally formed by high-purity graphite;
step two, laying the continuous silicon carbide fiber 3 on a fiber laying template 1 according to preset parameters, wherein the fiber laying mode is one-way fiber laying, the fiber direction is along the length direction of the component, the fiber volume fraction is 40%, the thickness of the fiber preform is 5mm, and the position needing to be drilled 5 is occupied by the pre-filler 2 and is bypassed by the continuous silicon carbide fiber 3;
thirdly, preparing a pyrolytic carbon interface layer on the continuous silicon carbide fiber preform by adopting a precursor impregnation cracking process, finishing densification by using polycarbosilane as an impregnant through impregnation-cracking circulation, and filling the silicon carbide ceramic matrix 4 in pores of the continuous silicon carbide fiber preform to finish densification of the continuous silicon carbide fiber reinforced silicon carbide ceramic matrix composite 6;
and step four, directly stripping the fiber placement template 1 and the pre-filler 2 from the continuous silicon carbide fiber reinforced silicon carbide ceramic matrix composite 6 to finish the non-destructive preparation of the hole 5, thereby obtaining the continuous silicon carbide fiber reinforced silicon carbide ceramic matrix composite 6 with the structure containing the hole 5.
Claims (3)
1. A method for manufacturing a hole in a continuous fiber reinforced ceramic matrix composite without damage is characterized by comprising the following steps: the method comprises the following steps:
designing and preparing a fiber laying template according to the requirements of the size, the shape and the position of a hole, wherein a pre-filler is arranged at the corresponding position of the fiber laying template where the hole needs to be made, and the pre-filler has the size, the shape and the position characteristics corresponding to the hole;
the fiber placement template has a molded surface which is adaptive to the structural characteristics of the continuous fiber reinforced ceramic matrix composite member and has a function of shaping the continuous fiber reinforced ceramic matrix composite, the shapes, positions and sizes of the fiber placement template and the pre-filler are kept unchanged in the continuous fiber placement and matrix filling processes, therefore, the fiber placement template and the pre-filler are accurately positioned in the continuous fiber placement and ceramic matrix filling processes by adopting integral forming, the fiber placement template and the pre-filler have stable physical and chemical properties, and the material is graphite;
laying continuous fibers on a fiber laying template according to preset parameters, wherein the continuous fiber laying mode is silk laying, tape laying, layer laying, weaving or hand knitting, the structure of the continuous fiber preform is a unidirectional tape, a 2D layer, a 2.5D fabric or a 3D fabric, the preset parameters comprise fiber running direction, fiber volume fraction and fiber preform thickness, and the position needing hole making is occupied by a pre-filler and is bypassed by the fibers to obtain the continuous fiber preform;
the section of the non-damage hole is in the shape of a round hole and a special-shaped hole, and the aperture is not less than 0.1 mm;
filling the silicon carbide ceramic matrix in the pores of the continuous fiber preform to complete the densification of the continuous fiber reinforced ceramic matrix composite;
and step four, removing the fiber laying template and the pre-filler to finish the damage-free hole making.
2. The continuous fiber reinforced ceramic matrix composite atraumatic hole method of claim 1, wherein: the continuous fiber is carbon fiber, silicon carbide fiber, nitride fiber or oxide fiber.
3. The continuous fiber reinforced ceramic matrix composite atraumatic hole method of claim 1, wherein: the fiber laying template and the pre-filler are directly stripped and processed in a material reducing mode from the continuous fiber reinforced ceramic matrix composite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911297763.6A CN111039687B (en) | 2019-12-13 | 2019-12-13 | Damage-free hole making method for continuous fiber reinforced ceramic matrix composite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911297763.6A CN111039687B (en) | 2019-12-13 | 2019-12-13 | Damage-free hole making method for continuous fiber reinforced ceramic matrix composite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111039687A CN111039687A (en) | 2020-04-21 |
| CN111039687B true CN111039687B (en) | 2022-04-19 |
Family
ID=70236920
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911297763.6A Active CN111039687B (en) | 2019-12-13 | 2019-12-13 | Damage-free hole making method for continuous fiber reinforced ceramic matrix composite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111039687B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112251906A (en) * | 2020-10-12 | 2021-01-22 | 南京航空航天大学 | Air film cooling hole braided structure suitable for ceramic matrix composite material member and manufacturing method thereof |
| GB2606342A (en) * | 2021-04-27 | 2022-11-09 | Rolls Royce Plc | Fibre reinforced gas turbine engine component |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10133635A1 (en) * | 2001-07-11 | 2003-02-06 | Sgl Carbon Ag | Multi-layer ceramic composite |
| FR3041890B1 (en) * | 2015-10-05 | 2017-11-24 | Snecma | PROCESS FOR MANUFACTURING A COMPOSITE MATERIAL PART BY INJECTING A BARBOTIN CHARGED IN A POROUS MOLD |
| CN107903067A (en) * | 2017-12-01 | 2018-04-13 | 苏州宏久航空防热材料科技有限公司 | A kind of growth in situ SiC nanowire enhancing SiC ceramic based composites and preparation method thereof |
| CN110183239A (en) * | 2019-04-22 | 2019-08-30 | 湖南远辉复合材料有限公司 | A kind of combined type preparation method of ceramic matric composite lattice structure |
| CN110204319B (en) * | 2019-04-22 | 2021-11-12 | 湖南远辉复合材料有限公司 | Integral preparation method of ceramic matrix composite lattice structure |
| CN110357648A (en) * | 2019-07-09 | 2019-10-22 | 中国航发北京航空材料研究院 | A method of preparing multistage multiple dimensioned fiber reinforced ceramic matric composite |
-
2019
- 2019-12-13 CN CN201911297763.6A patent/CN111039687B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN111039687A (en) | 2020-04-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113563091B (en) | Extreme-high-temperature ablation-resistant thermal dredging composite material and preparation method thereof | |
| US10584070B2 (en) | Ceramic matrix composites having monomodal pore size distribution and low fiber volume fraction | |
| CN111039687B (en) | Damage-free hole making method for continuous fiber reinforced ceramic matrix composite | |
| RU2668431C2 (en) | Method of fabricating composite parts by low melting point impregnation | |
| WO2000061518A9 (en) | Chordal preforms for fiber-reinforced articles and method for the production thereof | |
| CN109721376B (en) | Preparation method of SiCw oriented high-strength and high-toughness thick-wall ceramic matrix composite | |
| CN113956061B (en) | Preparation method of continuous fiber reinforced ceramic matrix composite screw | |
| KR20140015436A (en) | Method for producing a composite including a ceramic matrix | |
| CN108191432B (en) | Connection method of SiC/SiC composite material | |
| CN110078516A (en) | The quasi-isotropic SiC of high-volume fractional short fiber reinforcedfThe preparation method of/SiC ceramic matrix composite material | |
| CN113603495A (en) | Method for preparing ceramic matrix composite bolt and pin based on long rod-shaped prefabricated body structure | |
| US20100119299A1 (en) | Composite fastener for ceramic components | |
| CN104926342A (en) | Alumina fiber fabric-reinforced silicon carbide ceramic and preparation method thereof | |
| CN111039686B (en) | Preparation method of continuous fiber reinforced ceramic matrix composite material containing in-situ pores | |
| KR101956683B1 (en) | Manufacturing method of fiber reinforced ceramic matrix composites containing metal carbide filler | |
| CN117529598A (en) | Abradable coating in the form of a honeycomb made of a composite material having a ceramic matrix made of short fibers | |
| JP2005205902A (en) | Ceramic matrix composite material having improved layer strength and method therefor | |
| JP5862234B2 (en) | Ceramic matrix composite member having smooth surface and method for producing the same | |
| CN114230357B (en) | Preparation method of composite material slot waveguide antenna | |
| JP2001289226A (en) | Screw made of carbon fiber reinforced carbon composite material | |
| CN115974570A (en) | Preparation method of thin-wall component made of ceramic/resin hybrid matrix composite material | |
| CN117820000A (en) | Fiber toughened sintered silicon carbide/silicon nitride ceramic matrix composite material and preparation method thereof | |
| CN117627733A (en) | Ceramic-based rotor blade and preparation method thereof | |
| JP2018199589A (en) | METHOD OF PRODUCING SiC FIBER/SiC COMPOSITE MATERIAL | |
| CN114920576A (en) | Preparation method of novel carbon/silicon carbide honeycomb sandwich structure |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |