CN114673726A - Ceramic matrix composite material fixing hinge and preparation method thereof - Google Patents
Ceramic matrix composite material fixing hinge and preparation method thereof Download PDFInfo
- Publication number
- CN114673726A CN114673726A CN202210346227.6A CN202210346227A CN114673726A CN 114673726 A CN114673726 A CN 114673726A CN 202210346227 A CN202210346227 A CN 202210346227A CN 114673726 A CN114673726 A CN 114673726A
- Authority
- CN
- China
- Prior art keywords
- rotating shaft
- upper support
- lower support
- shaft
- preparing
- 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.)
- Granted
Links
- 239000011153 ceramic matrix composite Substances 0.000 title claims abstract description 33
- 239000000463 material Substances 0.000 title claims abstract description 28
- 238000002360 preparation method Methods 0.000 title claims abstract description 16
- 238000000151 deposition Methods 0.000 claims description 37
- 238000000034 method Methods 0.000 claims description 31
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 28
- 229910002804 graphite Inorganic materials 0.000 claims description 25
- 239000010439 graphite Substances 0.000 claims description 25
- 230000008021 deposition Effects 0.000 claims description 22
- 230000008569 process Effects 0.000 claims description 18
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 15
- 238000004140 cleaning Methods 0.000 claims description 14
- 238000001035 drying Methods 0.000 claims description 14
- 239000000835 fiber Substances 0.000 claims description 14
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 14
- 239000004372 Polyvinyl alcohol Substances 0.000 claims description 13
- 229920002451 polyvinyl alcohol Polymers 0.000 claims description 13
- 230000001680 brushing effect Effects 0.000 claims description 7
- 239000011248 coating agent Substances 0.000 claims description 7
- 238000000576 coating method Methods 0.000 claims description 7
- 238000002156 mixing Methods 0.000 claims description 7
- 238000005498 polishing Methods 0.000 claims description 7
- 244000137852 Petrea volubilis Species 0.000 claims description 5
- 239000002131 composite material Substances 0.000 claims description 5
- 238000010030 laminating Methods 0.000 claims description 4
- 238000003672 processing method Methods 0.000 claims description 4
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 238000009958 sewing Methods 0.000 claims description 3
- 238000004804 winding Methods 0.000 claims description 3
- 238000005229 chemical vapour deposition Methods 0.000 claims description 2
- 239000002245 particle Substances 0.000 claims 1
- 239000002184 metal Substances 0.000 abstract description 4
- 230000003068 static effect Effects 0.000 abstract description 3
- 239000010410 layer Substances 0.000 description 22
- 239000000956 alloy Substances 0.000 description 4
- 229910045601 alloy Inorganic materials 0.000 description 4
- 239000000919 ceramic Substances 0.000 description 4
- 238000003754 machining Methods 0.000 description 3
- 238000009991 scouring Methods 0.000 description 3
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical group C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 229910010271 silicon carbide Inorganic materials 0.000 description 2
- 238000009941 weaving Methods 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009954 braiding Methods 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000001603 reducing effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C11/00—Pivots; Pivotal connections
- F16C11/04—Pivotal connections
-
- 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
-
- 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
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
-
- 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
- C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
- C04B2235/614—Gas infiltration of green bodies or pre-forms
-
- 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
- C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
- C04B2235/74—Physical characteristics
- C04B2235/77—Density
-
- 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
- C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
- C04B2235/96—Properties of ceramic products, e.g. mechanical properties such as strength, toughness, wear resistance
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Materials Engineering (AREA)
- Structural Engineering (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Ceramic Products (AREA)
Abstract
The invention relates to a ceramic matrix composite material fixed hinge and a preparation method thereof. The problems of poor high-temperature resistance and high density of the existing metal hinge are solved. The fixed hinge comprises a lower support, an upper support, a rotating shaft and a rotating shaft fixing screw; the lower support comprises a first base body and two first shaft sleeves arranged on the surface of the first base body at intervals; the upper support comprises a second seat body and a second shaft sleeve arranged on the second seat body; the second shaft sleeve is clamped between the two first shaft sleeves; the rotating shaft penetrates through the two first shaft sleeves and the second shaft sleeve, the lower support is hinged with the upper support, and the upper support can rotate around the rotating shaft relative to the lower support; the rotating shaft fixing screw is inserted into the shaft hole of the first shaft sleeve and/or the second shaft sleeve and is fastened with the rotating shaft to limit the rotation of the rotating shaft; the lower support, the upper support, the rotating shaft and the rotating shaft fixing screw are made of ceramic matrix composite materials and are denseThe degree of the reaction is 2.0 to 2.4g/cm3The porosity is less than or equal to 10%. The static load bearing capacity is more than 95 percent under the temperature condition of-150 ℃ to 1300 ℃.
Description
Technical Field
The invention relates to a ceramic matrix composite material fixed hinge and a preparation method thereof.
Background
Hinges, also known as hinges, are mechanical devices used to connect two solid bodies and allow relative rotation between them.
The existing hinge is generally made of metal, the bearing capacity can be obviously reduced when the temperature is higher than 1000 ℃, the bearing capacity is continuously reduced along with the increase of the temperature until the hinge fails, the metal density is high, and the hinge can bring extra weight load when being applied to aerospace.
Disclosure of Invention
The invention aims to provide a ceramic matrix composite material fixed hinge and a preparation method thereof under a high-temperature environment. The problems of poor high-temperature resistance and high density of the existing metal hinge are solved. The density of the ceramic matrix composite material fixed hinge prepared by the invention is 2.0-2.4 g/cm3The porosity is less than or equal to 10%. The static load bearing capacity is more than 95 percent under the temperature condition of-150 ℃ to 1300 ℃.
The technical scheme of the invention is to provide a hinge fixed by a ceramic matrix composite material in a high-temperature environment, which is characterized in that: comprises a lower support, an upper support, a rotating shaft and a rotating shaft fixing screw;
the lower support comprises a first base body and two first shaft sleeves arranged on the surface of the first base body at intervals, and the two first shaft sleeves are coaxially arranged and are integrated with the first base body into a whole;
the upper support comprises a second seat body and a second shaft sleeve arranged on the second seat body, and the second shaft sleeve and the second seat body are of an integrated structure;
the second shaft sleeve is clamped between the two first shaft sleeves; the rotating shaft penetrates through the two first shaft sleeves and the two second shaft sleeves, the lower support is hinged with the upper support, and the upper support can rotate around the rotating shaft relative to the lower support;
the rotating shaft fixing screw is inserted into the shaft hole of the first shaft sleeve and/or the second shaft sleeve, is fastened with the rotating shaft and is used for limiting the rotation of the rotating shaft;
the lower support, the upper support, the rotating shaft and the rotating shaft fixing screw are all made of ceramic matrix composite materials.
Furthermore, in order to increase the interlayer strength and the high-temperature scouring resistance of the parts, the lower support and the upper support are prepared from fiber preforms with three-dimensional needled felt structures.
Further, in order to ensure the strength of the rotating shaft, the rotating shaft is prepared by adopting a two-dimensional laminated sewing structure fiber prefabricated body.
Furthermore, in order to ensure the connection reliability and the thermal matching of parts at high temperature, the rotating shaft fixing screw is a C/SiC screw.
The invention also provides a preparation method of the ceramic matrix composite material fixed hinge in a high-temperature environment, which is characterized by comprising the following steps:
and 3, inserting the rotating shaft fixing screw into the shaft hole of the first shaft sleeve and/or the second shaft sleeve, fastening the rotating shaft fixing screw with the rotating shaft, and limiting the rotation of the rotating shaft.
Further, the specific preparation process of the lower support and the upper support in the step 1 is as follows:
step 1a, preparing a prefabricated body;
step 1a1, processing a thick flat needled felt by adopting a hardening processing method to form a lower support core mould and an upper support core mould; the concrete structure of the lower support core mould is obtained by inwards offsetting the lower support at equal intervals according to the integral appearance structure of the lower support, and the concrete structure of the upper support core mould is obtained by inwards offsetting at equal intervals according to the integral appearance structure of the upper support, so that the maximum number of continuous fibers of a next layer can be ensured;
step 1a2, preparing a needling preform outside a core mold by adopting an equal-thickness layering scheme;
respectively paving a plurality of layers of three-dimensional needled felts along the using molded surfaces of the lower support core mold and the upper support core mold, wherein the plurality of layers of three-dimensional needled felts have the same thickness;
the length of the three-dimensional needled felt is larger than the unfolding length of the using molded surface of the core mold of the lower support, so that part of the three-dimensional needled felt is mutually laminated when leaving the using molded surface of the core mold of the lower support, and the mutually laminated three-dimensional needled felt forms a first seat body prefabricated body; the lower support core mould and the three-dimensional needled felt positioned on the outer surface of the lower support core mould form two first shaft sleeve prefabricated bodies;
the length of the three-dimensional needled felt is greater than the unfolding length of the using molded surface of the upper support core mold, so that part of the three-dimensional needled felt is mutually laminated when leaving the using molded surface of the upper support core mold, and the mutually laminated three-dimensional needled felt forms a second seat body prefabricated body; forming a second shaft sleeve prefabricated body by the upper support core mould and the three-dimensional needled felt positioned on the outer surface of the upper support core mould;
step 2a, preparing a blank;
step 2a1, fixing the lower support prefabricated body and the upper support prefabricated body which are finished in the step 1a in a graphite mold, wherein the graphite mold is provided with air holes;
step 2a2, placing a lower support preform and an upper support preform with graphite molds in an interface deposition furnace, and depositing interface layers with the thickness of 150 nm-500 nm on the surfaces of the lower support preform and the upper support preform;
step 2a3, placing the lower support preform and the upper support preform with the interface layer in a high-temperature treatment furnace for interface treatment;
step 2a4, placing the lower support preform and the upper support preform treated in the step 2a3 in a CVI deposition furnace, depositing the lower support preform and the upper support preform until the density is not less than 1.25g/cm3, removing a graphite mold, roughly processing rough edges, and repeating the steps until the density is not less than 1.70g/cm 3; obtaining a lower support blank and an upper support blank;
step 3a, processing a lower support and an upper support;
step 3a1, processing the blank by using a high-hardness cutter according to the design size, and ensuring that the overall size is smaller than the theoretical size by 0.1-0.2 mm; cleaning and drying;
step 3a2, adopting the CVI process of step 2a4 to enable the deposition density of the product processed in step 3a1 to be not less than 1.95g/cm 3;
step 3a3, mixing W5-granularity silicon carbide powder, polyvinyl alcohol solution and water according to a set proportion, performing surface brushing treatment, naturally drying, and then performing surface polishing and high-pressure gas cleaning by using sand paper; repeating until no pits are visible on the surface;
and 3a4, adopting the CVI process of the step 2a4 to deposit and prepare a surface coating with the thickness within 350nm on the surface of the product treated in the step 3a 3.
Further, in the step 3a3, the mass ratio of the W5-sized silicon carbide powder to the polyvinyl alcohol solution to the water is 5:1: 8.
Further, in the step 1a1, the lower support core mould is inwards biased to coincide with the upper and lower profile surfaces at equal intervals according to the overall shape structure of the lower support; the upper support mandrel is in a water-drop shape and is inwards biased to be superposed with an upper profile and a lower profile at equal intervals according to the integral shape structure of the upper support.
Further, in step 1a2, a plurality of layers of three-dimensional needled felts are respectively laid along the use molded surfaces of the lower support core mold and the upper support core mold, specifically:
firstly, respectively placing a lower support core mould and an upper support core mould on a layer of tiled three-dimensional needled felt, wrapping the three-dimensional needled felt on a core mould using molded surface along the length direction of the three-dimensional needled felt, and mutually laminating the three-dimensional needled felt at two ends separated from the core mould using molded surface;
and secondly, continuously paving the three-dimensional needled felt with the same thickness on the three-dimensional needled felt in the previous step according to the steps in sequence until the preset thickness is reached.
Further, the specific preparation process of the rotating shaft in the step 1 is as follows:
step 1c, preparing a rotating shaft prefabricated body;
winding a structural preform by using two-dimensional T3001K plain carbon cloth;
step 2c, preparing a blank;
step 2c1, fixing the rotating shaft prefabricated body completed in the step 1c in a graphite mould, wherein the graphite mould is provided with air holes;
step 2c2, placing the rotating shaft preform with the graphite mold in an interface deposition furnace, and depositing an interface layer with the thickness of 150 nm-500 nm on the surface of the rotating shaft preform;
step 2c3, placing the rotating shaft preform with the interface layer in a high-temperature treatment furnace for interface treatment;
step 2c4, placing the rotating shaft preform processed in the step 2c3 in a CVI (composite chemical vapor deposition) furnace, and depositing until the density is not less than 1.25g/cm3Removing the mold, rough machining rough edges, and repeating the steps until the density is not less than 1.70g/cm3(ii) a Obtaining a rotating shaft blank;
step 3c, processing the upper support;
step 3c1, processing the blank by using a high-hardness cutter according to the design size, ensuring that the overall size is 0.1-0.2 mm smaller than the theoretical size, cleaning and drying;
step 3c2, depositing the film with the CVI process of step 2c4 to a deposition density of ≧ 1.95g/cm3；
3c3, mixing the W5-granularity silicon carbide powder, the polyvinyl alcohol solution and water according to a set proportion, brushing the surface, naturally drying, polishing the surface by using sand paper, and cleaning by using high-pressure gas; repeating until no pits are visible on the surface;
and 3c4, adopting the CVI process of the step 2c4 to prepare the surface coating by deposition, wherein the thickness is within 350 nm.
Further, in the step 3c3, the mass ratio of the W5-sized silicon carbide powder to the polyvinyl alcohol solution to the water is 5:1: 8.
The invention has the beneficial effects that:
1. the maximum use temperature is higher
The silicon carbide ceramic phase is introduced into the material in situ by adopting a chemical vapor infiltration process, so that the maximum service temperature of the ceramic matrix composite material hinge prepared by the invention is about 1300 ℃, and compared with the traditional high-temperature alloy hinge component, the service temperature is increased by more than 100 ℃.
2. Obvious weight reduction effect of the structure
The density of the ceramic matrix composite material hinge prepared by the invention is 2.0-2.4 g/cm3Compared with the traditional high-temperature alloy component, on the premise of realizing the same connecting function, the weight is reduced by more than 60 percent, and the weight reduction effect of the structure is obvious;
3. higher structural strength
The ceramic matrix composite material hinge prepared by the invention adopts a process method of profile offset and profile braiding through the design of a prefabricated body, the continuity of a fiber reinforcement is ensured to the greatest extent, and when the hinge is used in an environment with the temperature higher than the preparation temperature (about 1000 ℃) of the ceramic matrix composite material, the residual stress in the composite material is released, the fiber is stretched, and the ceramic matrix is compressed, so that the structural strength is improved by more than 25 percent compared with the existing ceramic material component;
4. reliable connection at high temperature and long service life
Under the high-temperature condition, compared with the traditional high-temperature alloy hinge, the ceramic matrix composite material hinge prepared by the invention has smaller volume change caused by temperature change, and because of the existence of the high-melting-point silicon carbide ceramic phase, the component is more resistant to high-temperature scouring, and the service life is longer.
Drawings
FIG. 1 is a schematic view of an exemplary embodiment of a ceramic matrix composite fixed hinge member;
FIG. 2 is an exploded view of an exemplary ceramic matrix composite fixed hinge component;
FIG. 3 is a schematic view of an embodiment upper pedestal core die;
FIG. 4 is a schematic view of a preform of an upper stand according to an embodiment;
FIG. 5 is a schematic view of an example lower bracket mandrel;
FIG. 6 is a schematic view of an example lower pedestal preform;
the reference numbers in the figures are:
1. an upper support; 11. a second seat body; 12. a second shaft sleeve; 13. an upper support mandrel; 14. an upper support profile; 15. three-dimensional needled felt;
2. a lower support; 21. a first seat body; 22. a first bushing; 23. a lower support mandrel; 24. lower support profile;
3. a rotating shaft;
4. a rotating shaft fixing screw;
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention more comprehensible, embodiments accompanying figures of the present invention are described in detail below, and it is apparent that the described embodiments are a part, not all or all of the embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without making creative efforts based on the embodiments of the present invention, shall fall within the protection scope of the present invention.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, but the present invention may be practiced in other ways than those specifically described and will be readily apparent to those of ordinary skill in the art without departing from the spirit of the present invention, and therefore the present invention is not limited to the specific embodiments disclosed below.
Furthermore, reference herein to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one implementation of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments.
Still further, the present invention is described in detail in connection with the schematic drawings, which are only examples and should not limit the scope of the present invention herein. Meanwhile, in the description of the present invention, it should be noted that the terms "upper" and "lower" and the like indicate orientations and positional relationships based on the orientations and positional relationships shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present invention. Furthermore, the terms first, second, or third are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The maximum service temperature of the ceramic matrix composite material fixed hinge in the high-temperature environment is higher than that of a traditional high-temperature alloy component, and meanwhile, on the premise that the same connecting function is achieved, the weight is reduced by more than 60%, and the weight reducing effect of the structure is obvious. As shown in fig. 1 and fig. 2, the three-dimensional needled felt type rotary shaft component mainly comprises a lower support 2, an upper support 1, a rotary shaft 3 and a rotary shaft fixing screw 4, wherein in order to increase the interlayer strength and the high-temperature scouring resistance of the component, the lower support 2 and the upper support 1 are prepared from fiber preforms with three-dimensional needled felt structures. In order to ensure the strength of the rotating shaft 3, the rotating shaft 3 is prepared by a two-dimensional laminated sewing structure fiber preform. In order to ensure the connection reliability and the thermal matching of parts at high temperature, the rotating shaft fixing screw 4 is a C/SiC screw. As can be seen from fig. 2, the lower base 2 includes a first base 21, two first bushings 22 are disposed on the first base 21 at intervals, and the connecting portion between the outer peripheral surface of the first bushings 22 and the upper surface of the first base 21 is in rounded transition. It should be noted that the first seat 21 and the two first sleeves 22 are integrally formed. The upper support 1 comprises a second seat body 11, a second shaft sleeve 12 is arranged on the second seat body 11, and the second shaft sleeve 12 and the second seat body 11 are of an integrated structure; the second sleeve 12 is dimensioned so as to be insertable between the two first sleeves 22, while being rotatable about the axis of rotation 3 between the two first sleeves 22. The connection part of the outer peripheral surface of the second shaft sleeve 12 and the upper surface of the second seat body 11 is also transited through a fillet. As can be seen from fig. 1, the second sleeve 12 is snapped between the two first sleeves 22; the rotating shaft 3 penetrates through the two first shaft sleeves 22 and the second shaft sleeve 12, the lower support 2 is hinged with the upper support 1, and the upper support 1 can rotate around the rotating shaft 3 relative to the lower support 2; the rotating shaft fixing screw 4 is inserted into the shaft hole of the first shaft sleeve 22 and/or the second shaft sleeve 12 and is fastened with the rotating shaft 3 for limiting the rotation of the rotating shaft 3.
Due to the special pneumatic appearance of the hinge structure, if the traditional 2D, 3DN or other weaving methods are adopted, the continuity of fibers in the force bearing direction of the hinge is poor, and finally, the structural strength is low, so that the hinge structure cannot be applied to the high-low temperature environment and high-load condition of an aerospace vehicle. Therefore, in the embodiment, a process method of profile offset and profile-following weaving is adopted, the continuity of the fiber reinforcement is ensured to the greatest extent, and by adjusting corresponding process conditions and parameters, when the composite material is used in an environment with a temperature higher than the preparation temperature (about 1000 ℃) of the ceramic matrix composite material, the residual stress in the composite material is released, the fibers are stretched, and the ceramic matrix is compressed, so that the structural strength is improved by more than 25% compared with that of the existing ceramic material component.
The preparation method comprises the following steps:
the specific preparation process of the lower support 2 is as follows:
firstly, determining a lower support core mold 23 structure according to the overall appearance structure of the lower support 2; in order to ensure that the next ply has the maximum number of fibres continuous, the lower abutment core 23 is biased inwardly towards the upper and lower profile in accordance with the overall profile configuration of the lower abutment 2. As shown in fig. 3, a two-dot chain line located at the periphery of the under seat core mold 23 represents an under seat contour 24. The present embodiment achieves the lower abutment core 23 by biasing the lower abutment profile 24 inwardly to an equal distance until the upper and lower profiles meet.
Secondly, a flat needled felt is selected according to the maximum thickness of the lower support core mold 23, and the thickness of the flat needled felt needs to be ensured to be larger than the maximum thickness of the lower support core mold 23. And then the thick flat needled felt is processed by adopting a hardening processing method to form a lower support core mould 23.
Secondly, preparing a needling preform outside the lower support mandrel 23 by adopting an equal-thickness layering scheme;
as shown in fig. 4, a plurality of layers of three-dimensional needled felt 15 are laid along the lower support core 23 using a profile, the plurality of layers of three-dimensional needled felt 15 having the same thickness; meanwhile, the length of the three-dimensional needled felt 15 needs to be larger than the using molded surface expanding length of the lower support core mold 23, so that part of the three-dimensional needled felt 15 is mutually laminated when leaving the using molded surface of the lower support core mold 23, and the mutually laminated three-dimensional needled felt 15 forms a first seat body 21 prefabricated body; the lower support core die 23 and the three-dimensional needled felt 15 positioned on the outer surface of the lower support core die 23 form two first axle sleeve 22 prefabricated bodies. The paving can be carried out in the following way: firstly, placing a core mould on a layer of tiled three-dimensional needled felt 15, wrapping the core mould on a core mould use molded surface along the length direction of the three-dimensional needled felt 15, and mutually laminating the three-dimensional needled felt 15 at two ends separated from the core mould use molded surface; and then, according to the steps, continuously paving the three-dimensional needled felt 15 with the same thickness on the three-dimensional needled felt 15 in the previous step until the preset thickness is reached.
Secondly, preparing a blank;
firstly, fixing the finished lower support 2 prefabricated body in a graphite mold, wherein the graphite mold is provided with air holes; then, placing the lower support 2 preform with the graphite mold in an interface deposition furnace, and depositing an interface layer with the thickness of 150 nm-500 nm on the surface of the lower support 2 preform; then placing the lower support 2 preform with the interface layer in a high-temperature treatment furnace for interface treatment; placing the processed lower support 2 preform in a CVI deposition furnace, and depositing until the density is not less than 1.25g/cm3Removing the graphite mold, rough machining rough edges, and repeating the steps until the density is not less than 1.70g/cm3(ii) a Obtaining a lower support 2 blank;
secondly, processing a lower support 2;
firstly, processing a blank by using a high-hardness cutter according to a design size, and ensuring that the overall size is smaller than the theoretical size by 0.1-0.2 mm; cleaning and drying; then adopting a CVI process to ensure that the deposition density of the processed product is not less than 1.95g/cm3(ii) a Mixing W5-granularity silicon carbide powder, polyvinyl alcohol solution and water according to a set proportion, performing surface brushing treatment, naturally drying, and then performing surface polishing and high-pressure gas cleaning by using abrasive paper; repeating until no pits are visible on the surface; in this example, the mass ratio of the W5-sized silicon carbide powder to the polyvinyl alcohol solution to the water was 5:1: 8. And finally, preparing a surface coating with the thickness within 350nm on the surface of the treated product by adopting the same CVI process.
The preparation process of the upper support 1 is basically consistent with that of the lower support 2, and specifically comprises the following steps:
firstly, determining the structure of an upper support core mould 13 according to the overall appearance structure of an upper support 1; in order to ensure that the maximum number of continuous fibers can be formed in the previous layer, the core mould 13 of the upper support is inwards biased to be superposed with the upper and lower profile surfaces at equal intervals according to the overall shape structure of the upper support 1; as shown in fig. 5, the phantom lines at the periphery of upper abutment core mold 13 represent upper abutment profiles 14. This embodiment achieves upper abutment core die 13 by biasing upper abutment profiles 14 inwardly to an equal distance until the upper and lower profiles meet.
Secondly, a flat needle felt is selected according to the maximum thickness of the upper support core mold 13, and the thickness of the flat needle felt needs to be ensured to be larger than the maximum thickness of the upper support core mold 13. And then processing the thick flat needled felt by adopting a hardening processing method to form an upper support core mould 13.
Secondly, preparing a needling preform outside the upper support core mould 13 by adopting an equal-thickness layering scheme;
as shown in fig. 6, a plurality of layers of three-dimensional needled felt 15 are laid along upper support core mold 13 using a profile, and the plurality of layers of three-dimensional needled felt 15 have the same thickness; meanwhile, the length of the three-dimensional needled felt 15 needs to be larger than the using molded surface expanding length of the upper support core mold 13, so that part of the three-dimensional needled felt 15 is mutually laminated when leaving the using molded surface of the upper support core mold 13, and the mutually laminated three-dimensional needled felt 15 forms a first seat body 21 prefabricated body; upper support core die 13 and three-dimensional needled felt 15 located on the outer surface of upper support core die 13 form two first boss 22 preforms. The concrete method can adopt the following steps: firstly, placing a core mould on a layer of tiled three-dimensional needled felt 15, wrapping the core mould on a core mould use molded surface along the length direction of the three-dimensional needled felt 15, and mutually laminating the three-dimensional needled felt 15 at two ends separated from the core mould use molded surface; and then, according to the steps, continuously paving the three-dimensional needled felt 15 with the same thickness on the three-dimensional needled felt 15 in the previous step until the preset thickness is reached. The thickness of this embodiment is 12 mm.
Secondly, preparing a blank;
firstly, fixing the finished upper support 1 prefabricated body in a graphite mold, wherein the graphite mold is provided with air holes; then placing the prefabricated body of the upper support 1 with the graphite mould in an interface deposition furnace, and depositing an interface layer with the thickness of 150 nm-500 nm on the surface of the prefabricated body of the upper support 1; then placing the prefabricated body of the upper support 1 with the interface layer in a high-temperature treatment furnace for interface treatment; placing the processed upper support 1 preform in a CVI deposition furnace, depositing until the density is not less than 1.25g/cm3, removing a graphite mold, roughly processing burrs, and repeating the steps until the density is not less than 1.70g/cm 3; obtaining a blank of the upper support 1;
secondly, processing an upper support 1;
firstly, processing a blank by using a high-hardness cutter according to a design size, and ensuring that the overall size is smaller than the theoretical size by 0.1-0.2 mm; cleaning and drying; then, a CVI process is adopted, and the deposition density of the processed product is not less than 1.95g/cm 3; mixing W5-granularity silicon carbide powder, polyvinyl alcohol solution and water according to a set proportion, performing surface brushing treatment, naturally drying, and then performing surface polishing and high-pressure gas cleaning by using abrasive paper; repeating until no pits are visible on the surface; in this example, the mass ratio of the W5-sized silicon carbide powder to the polyvinyl alcohol solution to the water was 5:1: 8. And finally, preparing a surface coating with the thickness within 350nm on the surface of the treated product by adopting the same CVI process.
The specific preparation process of the rotating shaft 3 is as follows:
firstly, preparing a prefabricated body of a rotating shaft 3;
winding a structural preform by using two-dimensional T3001K plain carbon cloth;
secondly, preparing a blank, namely fixing the finished prefabricated body of the rotating shaft 3 in a graphite mold, wherein the graphite mold is provided with air holes; then, the prefabricated body of the rotating shaft 3 with the graphite mold is placed in an interface deposition furnace, and an interface layer with the thickness of 150 nm-500 nm is deposited on the surface of the prefabricated body of the rotating shaft 3; placing the rotating shaft 3 preform with the interface layer in a high-temperature treatment furnace for interface treatment; placing the processed rotating shaft 3 preform in a CVI deposition furnace, and depositing until the density is not less than 1.25g/cm3Removing the mold, rough machining rough edges, and repeating the steps until the density is not less than 1.70g/cm3(ii) a Obtaining a rotating shaft 3 blank;
secondly, processing the upper support 1, processing a blank according to a design size by using a high-hardness cutter, ensuring that the overall size is 0.1-0.2 mm smaller than the theoretical size, cleaning and drying; depositing the powder by the same CVI process until the deposition density is equal to or larger than 1.95g/cm 3; mixing W5-granularity silicon carbide powder, polyvinyl alcohol solution and water according to the mass ratio of 5:1:8, brushing the surface, naturally drying, polishing the surface by using sand paper, and cleaning by using high-pressure gas; repeating until no pits are visible on the surface; the surface coating is prepared by deposition by adopting a CVI process, and the thickness is within 350 nm.
and 3, inserting the rotating shaft fixing screw 4 into the shaft hole of the first shaft sleeve 22 and/or the second shaft sleeve 12, fastening the rotating shaft fixing screw with the rotating shaft 3, and limiting the rotating shaft 3 to rotate.
The density of the ceramic matrix composite fixed hinge prepared by the embodiment is tested to be 2.0-2.4 g/cm3 by adopting a method of measuring ASD-STAN PREN 6018-1990 by a drainage method, and the porosity is less than or equal to 10%. High and low temperature mechanical property tests are adopted to verify that the static load borne by the ceramic matrix composite fixed hinge prepared in the embodiment is more than 95% at the temperature of-150-1300 ℃.
Claims (11)
1. The utility model provides a fix hinge with ceramic matrix composite under high temperature environment which characterized in that: comprises a lower support (2), an upper support (1), a rotating shaft (3) and a rotating shaft fixing screw (4);
the lower support (2) comprises a first base body (21) and two first shaft sleeves (22) which are arranged on the surface of the first base body (21) at intervals, and the two first shaft sleeves (22) are coaxially arranged and are integrated with the first base body (21) into a whole;
the upper support (1) comprises a second base body (11) and a second shaft sleeve (12) arranged on the second base body (11), and the second shaft sleeve (12) and the second base body (11) are of an integral structure;
the second shaft sleeve (12) is clamped between the two first shaft sleeves (22); the rotating shaft (3) penetrates through the two first shaft sleeves (22) and the second shaft sleeve (12) to hinge the lower support (2) and the upper support (1), and the upper support (1) can rotate around the rotating shaft (3) relative to the lower support (2);
the rotating shaft fixing screw (4) is inserted into the shaft hole of the first shaft sleeve (22) and/or the second shaft sleeve (12), is fastened with the rotating shaft (3) and is used for limiting the rotating shaft (3) to rotate;
the lower support (2), the upper support (1), the rotating shaft (3) and the rotating shaft fixing screw (4) are all made of ceramic matrix composite materials.
2. The hinge according to claim 1, wherein: the lower support (2) and the upper support (1) are prepared from fiber preforms with three-dimensional needled felt structures.
3. The hinge according to claim 2, wherein: the rotating shaft (3) is prepared from a two-dimensional laminated sewing structure fiber preform.
4. The hinge according to any one of claims 1-3, wherein: the rotating shaft fixing screw (4) is a C/SiC screw.
5. A method for preparing a ceramic matrix composite material fixed hinge in a high temperature environment according to claim 1, comprising the following steps:
step 1, preparing a lower support (2), an upper support (1), a rotating shaft (3) and a rotating shaft fixing screw (4) by using a ceramic matrix composite material;
step 2, clamping the second shaft sleeve (12) between the two first shaft sleeves (22), and then inserting the rotating shaft (3) into the two first shaft sleeves (22) and the second shaft sleeve (12) to realize the hinging of the lower support (2) and the upper support (1);
and 3, inserting the rotating shaft fixing screw (4) into the shaft hole of the first shaft sleeve (22) and/or the second shaft sleeve (12), fastening the rotating shaft fixing screw with the rotating shaft (3), and limiting the rotating shaft (3) to rotate.
6. The method for preparing the ceramic matrix composite material fixed hinge in the high-temperature environment according to the claim 5, wherein the specific preparation processes of the lower support (2) and the upper support (1) in the step 1 are as follows:
step 1a, preparing a prefabricated body;
step 1a1, processing a thick flat needled felt by adopting a hardening processing method to form a lower support core mould (23) and an upper support core mould (13); the concrete structure of the lower support core mold (23) is obtained by inwards offsetting at equal intervals according to the overall appearance structure of the lower support (2), and the concrete structure of the upper support core mold (13) is obtained by inwards offsetting at equal intervals according to the overall appearance structure of the upper support (1), so that the maximum number of continuous fibers in the next layer can be ensured;
step 1a2, preparing a needling preform outside a core mould by adopting an equal-thickness layering scheme;
respectively paving a plurality of layers of three-dimensional needled felts along the using molded surfaces of the lower support core mold (23) and the upper support core mold (13), wherein the plurality of layers of three-dimensional needled felts have the same thickness;
the length of the three-dimensional needled felt is greater than the using molded surface unfolding length of the lower support core mold (23), so that part of the three-dimensional needled felt is mutually laminated when leaving the using molded surface of the lower support core mold (23), and the mutually laminated three-dimensional needled felt forms a first seat body (21) prefabricated body; the lower support core die (23) and the three-dimensional needled felt positioned on the outer surface of the lower support core die (23) form two first shaft sleeve (22) prefabricated bodies;
the length of the three-dimensional needled felt is greater than the unfolding length of the using molded surface of the upper support core mold (13), so that partial three-dimensional needled felt is mutually laminated when leaving the using molded surface of the upper support core mold (13), and the mutually laminated three-dimensional needled felt forms a second seat body (11) prefabricated body; an upper support core die (13) and a three-dimensional needled felt positioned on the outer surface of the upper support core die (13) form a second shaft sleeve (12) prefabricated body;
step 2a, preparing a blank;
step 2a1, fixing the prefabricated body of the lower support (2) and the prefabricated body of the upper support (1) which are finished in the step 1a in a graphite mold, wherein the graphite mold is provided with air holes;
step 2a2, placing a lower support (2) prefabricated body with a graphite mold and an upper support (1) prefabricated body in an interface deposition furnace, and depositing interface layers with the thickness of 150 nm-500 nm on the surfaces of the lower support (2) prefabricated body and the upper support (1) prefabricated body;
step 2a3, placing the lower support (2) prefabricated body with the interface layer and the upper support (1) prefabricated body in a high-temperature treatment furnace for interface treatment;
step 2a4, placing the lower support (2) preform and the upper support (1) preform processed in the step 2a3 into a CVI (composite chemical vapor deposition) deposition furnace, depositing until the density is not less than 1.25g/cm3, removing a graphite mold, roughly processing burrs, and repeating the steps until the density is not less than 1.70g/cm 3; obtaining a lower support (2) blank and an upper support (1) blank;
step 3a, processing the lower support (2) and the upper support (1);
step 3a1, processing the blank by using a high-hardness cutter according to the design size, and ensuring that the overall size is smaller than the theoretical size by 0.1-0.2 mm; cleaning and drying;
step 3a2, adopting the CVI process of step 2a4 to enable the deposition density of the product processed in step 3a1 to be not less than 1.95g/cm 3;
step 3a3, mixing W5-granularity silicon carbide powder, polyvinyl alcohol solution and water according to a set proportion, performing surface brushing treatment, naturally drying, and then performing surface polishing and high-pressure gas cleaning by using sand paper; repeating until no pits are visible on the surface;
3a4, adopting the CVI process of the step 2a4 to deposit and prepare a surface coating with the thickness within 350nm on the surface of the product treated by the step 3a 3.
7. The method for preparing the ceramic matrix composite material fixed hinge in the high temperature environment according to claim 6, wherein: in the step 3a3, the mass ratio of the W5 particle size silicon carbide powder to the polyvinyl alcohol solution to the water is 5:1: 8.
8. The method for preparing the ceramic matrix composite material fixed hinge in the high temperature environment according to claim 7, wherein: in the step 1a1, the lower support core mold (23) is inwards biased to coincide with the upper and lower profile surfaces at equal intervals according to the overall appearance structure of the lower support (2); the upper support core die (13) is in a water drop shape and is inwards biased to be superposed with an upper profile and a lower profile at equal intervals according to the overall appearance structure of the upper support (1).
9. The method for preparing a ceramic matrix composite material fixed hinge in a high temperature environment according to claim 8, wherein: in the step 1a2, a plurality of layers of three-dimensional needled felts are respectively paved along the using molded surfaces of the lower support core mold (23) and the upper support core mold (13), specifically:
firstly, respectively placing a lower support core mould (23) and an upper support core mould (13) on a layer of tiled three-dimensional needled felt, wrapping the layers on a core mould use molded surface along the length direction of the three-dimensional needled felt, and mutually laminating the three-dimensional needled felts at two ends separated from the core mould use molded surface;
and secondly, continuously paving the three-dimensional needled felt with the same thickness on the three-dimensional needled felt in the previous step according to the steps in sequence until the preset thickness is reached.
10. The method for preparing the ceramic matrix composite material fixed hinge in the high temperature environment according to any one of claims 5 to 9, wherein the specific preparation process of the rotating shaft (3) in the step 1 is as follows:
step 1b, preparing a prefabricated body of the rotating shaft (3);
winding a structural preform by using two-dimensional T3001K plain carbon cloth;
step 2b, preparing a blank;
step 2b1, fixing the prefabricated body of the rotating shaft (3) finished in the step 1b in a graphite mould, wherein the graphite mould is provided with air holes;
step 2b2, placing the rotating shaft (3) preform with the graphite mold in an interface deposition furnace, and depositing an interface layer with the thickness of 150 nm-500 nm on the surface of the rotating shaft (3) preform;
step 2b3, placing the rotating shaft (3) preform with the interface layer in a high-temperature treatment furnace for interface treatment;
step 2b4, placing the rotating shaft (3) preform processed in the step 2b3 in a BVI deposition furnace, depositing until the density is not less than 1.25g/bm3, removing the die, roughly processing burrs, and repeating the step until the density is not less than 1.70g/bm 3; obtaining a rotating shaft (3) blank;
step 3b, processing the upper support (1);
step 3b1, processing the blank by using a high-hardness cutter according to the design size, ensuring that the overall size is smaller than the theoretical size by 0.1-0.2 mm, cleaning and drying;
step 3b2, adopting the BVI process of step 2b4 to deposit the material with the density of ≧ 1.95g/bm 3;
3b3, mixing the W5-granularity silicon carbide powder, the polyvinyl alcohol solution and water according to a set proportion, brushing the surface, naturally drying, polishing the surface by using sand paper, and cleaning by using high-pressure gas; repeating until no pits are visible on the surface;
and 3b4, preparing a surface coating with the thickness within 350nm by adopting the BVI process deposition of the step 2b 4.
11. The method for preparing a hinge fixed by ceramic matrix composite material in high temperature environment according to claim 10, wherein: in the step 3b3, the mass ratio of the W5-granularity silicon carbide powder to the polyvinyl alcohol solution to the water is 5:1: 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210346227.6A CN114673726B (en) | 2022-03-31 | 2022-03-31 | Ceramic matrix composite fixed hinge and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210346227.6A CN114673726B (en) | 2022-03-31 | 2022-03-31 | Ceramic matrix composite fixed hinge and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114673726A true CN114673726A (en) | 2022-06-28 |
| CN114673726B CN114673726B (en) | 2023-05-16 |
Family
ID=82075451
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210346227.6A Active CN114673726B (en) | 2022-03-31 | 2022-03-31 | Ceramic matrix composite fixed hinge and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114673726B (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040097360A1 (en) * | 2002-09-13 | 2004-05-20 | Bodo Benitsch | Fiber-reinforced composite ceramic, fabrication method and lining material, armor, reflective surface and component having the composite ceramic |
| WO2009125431A1 (en) * | 2008-03-18 | 2009-10-15 | Gosakan Aravamudan | Ceramic hinge and connected ceramic plates |
| CN102775176A (en) * | 2012-07-18 | 2012-11-14 | 西安鑫垚陶瓷复合材料有限公司 | Preparation method of three-dimensional needling carbon/carborundum composite material bolt |
| CN104632861A (en) * | 2014-12-24 | 2015-05-20 | 芜湖市汽车产业技术研究院有限公司 | Manufacture method of fiber composite material automobile transmission shaft |
| CN105272332A (en) * | 2015-11-09 | 2016-01-27 | 山东大学 | High-temperature-resistant ablation carbon/ carborundum composite material fixing hinge and preparation method |
| CN106808708A (en) * | 2015-11-30 | 2017-06-09 | 航天特种材料及工艺技术研究所 | A kind of composite hinge-type shaft joint and integral forming method |
| CN207469979U (en) * | 2017-11-18 | 2018-06-08 | 中山市天朗卫浴设备制造有限公司 | A kind of corrosion resistant hinge |
| CN109721377A (en) * | 2019-01-30 | 2019-05-07 | 湖南兴晟新材料科技有限公司 | Ceramic Matrix Composites Reinforced by Carbon Fibers and preparation method thereof |
| CN111075829A (en) * | 2019-11-26 | 2020-04-28 | 江苏恒神股份有限公司 | Hybrid fiber reinforced resin matrix composite material hinge and manufacturing method thereof |
| CN111425264A (en) * | 2020-03-31 | 2020-07-17 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite elastic sealing element and forming process thereof |
| CN113277867A (en) * | 2021-05-11 | 2021-08-20 | 广州三的投资管理企业（有限合伙） | Preparation method of carbon/silicon carbide composite material crucible |
| CN113603495A (en) * | 2021-07-29 | 2021-11-05 | 西北工业大学 | Method for preparing ceramic matrix composite bolt and pin based on long rod-shaped prefabricated body structure |
-
2022
- 2022-03-31 CN CN202210346227.6A patent/CN114673726B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040097360A1 (en) * | 2002-09-13 | 2004-05-20 | Bodo Benitsch | Fiber-reinforced composite ceramic, fabrication method and lining material, armor, reflective surface and component having the composite ceramic |
| WO2009125431A1 (en) * | 2008-03-18 | 2009-10-15 | Gosakan Aravamudan | Ceramic hinge and connected ceramic plates |
| CN102775176A (en) * | 2012-07-18 | 2012-11-14 | 西安鑫垚陶瓷复合材料有限公司 | Preparation method of three-dimensional needling carbon/carborundum composite material bolt |
| CN104632861A (en) * | 2014-12-24 | 2015-05-20 | 芜湖市汽车产业技术研究院有限公司 | Manufacture method of fiber composite material automobile transmission shaft |
| CN105272332A (en) * | 2015-11-09 | 2016-01-27 | 山东大学 | High-temperature-resistant ablation carbon/ carborundum composite material fixing hinge and preparation method |
| CN106808708A (en) * | 2015-11-30 | 2017-06-09 | 航天特种材料及工艺技术研究所 | A kind of composite hinge-type shaft joint and integral forming method |
| CN207469979U (en) * | 2017-11-18 | 2018-06-08 | 中山市天朗卫浴设备制造有限公司 | A kind of corrosion resistant hinge |
| CN109721377A (en) * | 2019-01-30 | 2019-05-07 | 湖南兴晟新材料科技有限公司 | Ceramic Matrix Composites Reinforced by Carbon Fibers and preparation method thereof |
| CN111075829A (en) * | 2019-11-26 | 2020-04-28 | 江苏恒神股份有限公司 | Hybrid fiber reinforced resin matrix composite material hinge and manufacturing method thereof |
| CN111425264A (en) * | 2020-03-31 | 2020-07-17 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite elastic sealing element and forming process thereof |
| CN113277867A (en) * | 2021-05-11 | 2021-08-20 | 广州三的投资管理企业（有限合伙） | Preparation method of carbon/silicon carbide composite material crucible |
| CN113603495A (en) * | 2021-07-29 | 2021-11-05 | 西北工业大学 | Method for preparing ceramic matrix composite bolt and pin based on long rod-shaped prefabricated body structure |
Non-Patent Citations (1)
| Title |
|---|
| 刘杰等: "3D针刺C/SiC复合材料螺栓的低成本制备及力学性能", 《航空学报》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114673726B (en) | 2023-05-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5117862B2 (en) | Manufacturing method of ceramic matrix composite member | |
| CN108046819B (en) | C/C-SiC friction material with integrated structure and function and preparation method thereof | |
| US5436042A (en) | Ceramic fiber-reinforced composite articles and their production | |
| CN112552065B (en) | Fiber-reinforced ceramic matrix composite bolt and preparation method thereof | |
| US11254092B2 (en) | Three-dimensional multi-reinforced composites and methods of manufacture and use thereof | |
| JP2001524453A (en) | Ceramic network, manufacturing method thereof and use thereof | |
| JP2001505522A (en) | Silicon carbide reinforced silicon carbide composite material | |
| RU99114026A (en) | SILICON CARBIDE COMPOSITE STRENGTHENED BY SILICON CARBIDE | |
| US7168534B2 (en) | Clutch or brake device formed of composite foam | |
| EP2774905B1 (en) | Ceramic matrix composite | |
| CN115108844B (en) | Gradient self-adaptive carbon fiber/quartz fiber composite reinforced metal phosphate-based composite material and preparation method thereof | |
| US20190337859A1 (en) | A method of fabricating a part out of ceramic matrix composite material | |
| CN114673726A (en) | Ceramic matrix composite material fixing hinge and preparation method thereof | |
| CN112936657A (en) | Method for reinforcing phenolic resin composite material by using fiber braid with antioxidant laminated structure | |
| CN113862773B (en) | Long-life guide cylinder and preparation method thereof | |
| US6226866B1 (en) | Method of making carbon-carbon composite valve for high performance internal combustion engines | |
| JP3116005B2 (en) | Manufacturing method of C / C crucible for pulling semiconductor single crystal | |
| CN105774094B (en) | hybrid sandwich ceramic matrix composite | |
| CN114474312A (en) | Tubular structural member mold and method for manufacturing tubular structural member | |
| KR101603835B1 (en) | Mold manufacturing method of carbon composites for using at high temperature and high pressure | |
| CN111995421A (en) | Friction material and preparation method thereof | |
| Canfield | Braided carbon/carbon nozzle development | |
| CN115959917B (en) | Rapid preparation method of high-strength carbon/carbon composite material | |
| CN114810820B (en) | Special-shaped bearing with integrated structure based on ceramic matrix composite and preparation method thereof | |
| CN114773077B (en) | Composite silicon carbide fiber hard felt and preparation method and application thereof |
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 | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 710117 West Section 912 of Biyuan Road, Xi'an High-tech Zone, Shaanxi Province Patentee after: Xi'an Xinyao Ceramic Composite Co.,Ltd. Country or region after: China Address before: 710117 West Section 912 of Biyuan Road, Xi'an High-tech Zone, Shaanxi Province Patentee before: XI'AN GOLDEN MOUNTAIN CERAMIC COMPOSITES CO.,LTD. Country or region before: China |