CN103274714B - Improved Z-pin method for two-dimensional ceramic matrix composite - Google Patents
Improved Z-pin method for two-dimensional ceramic matrix composite Download PDFInfo
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- CN103274714B CN103274714B CN201310221587.4A CN201310221587A CN103274714B CN 103274714 B CN103274714 B CN 103274714B CN 201310221587 A CN201310221587 A CN 201310221587A CN 103274714 B CN103274714 B CN 103274714B
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Abstract
The invention provides an improved Z-pin method for a two-dimensional ceramic matrix composite. The improved Z-pin method comprises the following steps of (1) preparing a two-dimensional carbon fiber plain woven preform; (2) preparing carbon fiber Z-pin members by using a pultrusion process; (3) drilling inclined holes in the two-dimensional carbon fiber plain woven preform according to a certain distribution rule; (4) embedding the carbon fiber Z-pin members in the inclined holes of the two-dimensional carbon fiber plain woven perform; (5) depositing the two-dimensional carbon fiber plain woven perform with the carbon fiber Z-pin members to densify the same, and thus a two-dimensional ceramic matrix composite plate is obtained; and (6) trimming the parts of the carbon fiber Z-pin members. The Z-pin members are inclinedly embedded according to a certain distribution rule, thereby transferring connection shear loading into a combination of extrusion loading and shear loading, more effectively enhancing Z-direction strength of the two-dimensional ceramic matrix composite and inhibiting stratified damages.
Description
Technical field
The invention belongs to matrix material Z-pin(is that Z-direction strengthens) technical field.Be specifically related to the improved Z-pin method of two-dimentional C/SiC ceramic matric composite under a kind of heat-sound-composite moving mechanics environment that shakes.
Background technology
Ceramic matric composite (CeramicMatrixComposite, CMC) there is the advantages such as high temperature resistant, high specific strength, high specific stiffness, Heat stability is good, become the ideal material of hypersonic aircraft thermal protection system (Thermal ProtectionSystem, TPS) and heat structure (Thermal-structure).Flight Vehicle Structure is generally designed to thin wall reinforced plate and shell structure, and control of two-dimensional braided ceramic matric composite veneer sheet is more suitable in this class formation compared with D braided composites.As the main raw of current hypersonic aircraft solar heat protection and load integral structure, two-dimentional C/SiC plain weave ceramic matric composite has advantages of that in-plane mechanical properties is good, preparation technology is simple, low for equipment requirements, can significantly reduce material preparation cost.
But, there is the shortcoming that interlaminar strength is low in two-dimentional C/SiC ceramic matric composite prepared by traditional technology, its main failure mode is delamination failure, particularly for high frequency noise incentive environment, transverse inertia load magnitude is huge, layering was lost efficacy serious, and therefore, Z direction strength becomes the restraining factors of two-dimentional C/SiC ceramic matric composite large-scale application.
The shortcoming that laminate structure interlaminar strength is low in order to overcome, delamination resistance can differ from, interlaminar improvement method is arisen at the historic moment, wherein to sew up and the tool of Z-pin technology represents.Strength of joint and the reliability of Z-pin technology are higher, and use temperature is unaffected, the manufacturing processed of ceramic matric composite and connection procedure can be combined together, do not need use extra linking device and be connected technique; Simultaneously; comparing bolt connects; ceramic matric composite Z-pin diameter less (being generally 0.2～1.0mm); destroy less to the fibrous bundle of ceramic matric composite inside; in the face of bulk ceramics matrix composite sheet, performance has also obtained maximum protection; in addition, the tooling cost of Z-pin is also low more than ceramic base compound material bolt.Therefore, control of two-dimensional braided ceramic matric composite veneer sheet Z-pin technology has broad application prospects.
The control of two-dimensional braided ceramic matric composite Z-pin of existing vertical implantation can improve interlaminar shear strength, the changing of the relative positions of limiting layer and layer, and layering is played to certain restraining effect, but under transverse load operating mode, due to CMC and Z-pin matrix depositional plane shearing carrying, supporting capacity still a little less than, the performance of Z-pin is not not fully exerted.For this reason, further improve the carrying form of Z-pin, bring into play its structure properties and there is important construction value with the Z direction strength that improves CMC.
Summary of the invention
Goal of the invention: the object of the invention is to cannot give full play to for existing vertical implantation Z-pin mode the deficiency of its mechanical property, provide a kind of two-dimentional ceramic matric composite Z-direction to strengthen improved Z-pin method.
Technical scheme: improved two-dimentional ceramic matric composite Z-pin method of the present invention, comprises the following steps:
(1) prepare Two-dimensional Carbon fiber plain weave precast body;
(2) adopt pultrusion molding process to prepare carbon fiber Z-pin member, through intensification mold cured, cutting processing, obtain the carbon fiber Z-pin member of design length and diameter;
(3) on Two-dimensional Carbon fiber plain weave precast body, join and bore tilting hole, the regularity of distribution of tilting hole on Two-dimensional Carbon fiber plain weave precast body is as follows: defining tilting hole angle axial and Two-dimensional Carbon fiber plain weave precast body normal direction is oblique angle θ, taking Two-dimensional Carbon fiber plain weave precast body lower surface center as coordinate origin O, lower surface is XOY plane, by XOY plane be straight up+Z axis, in 1-4 octant, respectively there is N parallel tilting hole, in each octant, the adjacent tilting hole distance between XOY plane Shang center equates, this distance is with from nearest first the tilting hole of initial point O, the distance between XOY plane Shang center and initial point O equates, the first octant is (cos α with the direction cosine of N parallel tilting hole in the 3rd octant, cos β, cos θ), the second octant is (cos α with the direction cosine of N parallel tilting hole in the 4th octant,-cos β, cos θ), wherein cos
2α+cos
2β+cos
2θ=1, θ=[15 °, 45 °]
(4) by the tilting hole of the tilting embedding Two-dimensional Carbon of carbon fiber Z-pin member fiber plain weave precast body;
(5) the Two-dimensional Carbon fiber plain weave precast body of employing CVI process deposits band carbon fiber Z-pin member, makes its densification, obtains two-dimentional ceramic matric composite plate;
(6) carbon fiber Z-pin member position is processed and repaired: remove carbon fiber Z-pin member redundance, make carbon fiber Z-pin member concordant with two-dimentional ceramic matric composite plate outside surface; Then adopt CVI technique to prepare SiC coating at two-dimentional ceramic matric composite plate outside surface, carbon fiber Z-pin member position is covered and protected.
Preferably, the diameter of described carbon fiber Z-pin member is 0.2-1.0mm.
Preferably, the volume of described tilting hole accounts for 0.5%～4% of Two-dimensional Carbon fiber plain weave precast body volume, determines N value by this volume fraction.More preferably, the volume of described tilting hole accounts for 1%～2.5% of Two-dimensional Carbon fiber plain weave precast body volume, determines N value by this volume fraction.
Preferably, the volume fraction of described Two-dimensional Carbon fiber plain weave precast body is 40%.
Preferably, adopt isothermal chemical vapor infiltration (Iso-thermalChemicalVaporInfiltration, ICVI) technique: 1) Two-dimensional Carbon fiber plain weave precast body is placed in to temperature evenly and without in the mobile reaction chamber of forced gas; 2) with CH
3siCl
3(MTS) be reactant gases, H
2for carrier gas, Ar is diluent gas, penetrates in Two-dimensional Carbon fiber plain weave precast body, at carbon fiber surface generation chemical reaction in-situ deposition by diffusion.
Preferably, described CVI processing parameter is: temperature is controlled at 800～1100 DEG C, and pressure is 1～10kPa, the about 100h of depositing time.More preferably, temperature is controlled at 1000 DEG C, and pressure is 5kPa, the about 100h of depositing time.
Beneficial effect of the present invention is: 1, the present invention overcomes existing two-dimentional ceramic matric composite and vertically implants Z-pin member to improving composite thin plate Z direction strength effect limited deficiency, thereby shear the combination that stand under load changes into extruding stand under load and shears stand under load, improved the Z direction strength of two-dimentional ceramic matric composite by Z-pin member being connected according to the tilting implantation of certain regularity of distribution Z-pin member; 2, the present invention is conducive to the application of larger diameter matrix material Z-pin member, ruptures, extracts the probability of inefficacy by greatly reducing Z-pin member; 3, the present invention does not lose two-dimentional ceramic matric composite plate interlaminar shear strength; 4, the present invention does not affect aircraft aerodynamic configuration.
Figure of description
Fig. 1 is the single Z-pin member of two-dimentional ceramic matric composite plate implantation schematic diagram in prior art;
Fig. 2 is the tilting implantation schematic diagram of the single Z-pin member of two-dimentional ceramic matric composite plate.
Fig. 3 is the tilting implantation schematic diagram of 4 Z-pin members of two-dimentional ceramic matric composite plate.
Embodiment
Below by the mode of embodiment, technical solution of the present invention is elaborated, but protection scope of the present invention is not limited to described embodiment.
Improved two-dimentional ceramic matric composite Z-pin method of the present invention, comprises the following steps:
(1) prepare Two-dimensional Carbon fiber plain weave precast body;
(2) adopt pultrusion molding process to prepare carbon fiber Z-pin member, through intensification mold cured, cutting processing, obtain the carbon fiber Z-pin member of design length and diameter;
(3) on Two-dimensional Carbon fiber plain weave precast body, join and bore tilting hole, the regularity of distribution of tilting hole on Two-dimensional Carbon fiber plain weave precast body is as follows: defining tilting hole angle axial and Two-dimensional Carbon fiber plain weave precast body normal direction is oblique angle θ, taking Two-dimensional Carbon fiber plain weave precast body lower surface center as coordinate origin O, lower surface is XOY plane, by XOY plane be straight up+Z axis, in 1-4 octant, respectively there is N parallel tilting hole, in each octant, the adjacent tilting hole distance between XOY plane Shang center equates, this distance is with from nearest first the tilting hole of initial point O, the distance between XOY plane Shang center and initial point O equates, the first octant is (cos α with the direction cosine of N parallel tilting hole in the 3rd octant, cos β, cos θ), the second octant is (cos α with the direction cosine of N parallel tilting hole in the 4th octant,-cos β, cos θ), wherein cos
2α+cos
2β+cos
2θ=1, θ=[15 °, 45 °],
(4) by the tilting hole of the tilting embedding Two-dimensional Carbon of carbon fiber Z-pin member fiber plain weave precast body;
(5) the Two-dimensional Carbon fiber plain weave precast body of employing CVI process deposits band carbon fiber Z-pin member, makes its densification, obtains two-dimentional ceramic matric composite plate;
(6) carbon fiber Z-pin member position is processed and repaired: remove carbon fiber Z-pin member redundance, make carbon fiber Z-pin member concordant with two-dimentional ceramic matric composite plate outside surface; Then adopt CVI technique to prepare SiC coating at two-dimentional ceramic matric composite plate outside surface, carbon fiber Z-pin member position is covered and protected.
The diameter of described carbon fiber Z-pin member is 0.2-1.0mm.
The volume of described tilting hole accounts for 0.5%～4% of Two-dimensional Carbon fiber plain weave precast body volume, determines N value by this volume fraction.
Described CVI processing parameter is: temperature is controlled at 800～1100 DEG C, and pressure is 1～10kPa, the about 100h of depositing time.
Embodiment 1
(1) prepare Two-dimensional Carbon fiber plain weave precast body, precast body is of a size of 50 × 50 × 5mm
3;
(2) adopt pultrusion molding process to prepare carbon fiber Z-pin member, through intensification mold cured, cutting processing, the carbon fiber Z-pin member that obtains design length and diameter (0.2～1.0mm) (is prepared the carbon fiber Z-pin member that diameter is 0.28mm with 1k carbon fiber, is prepared the carbon fiber Z-pin member that diameter is 0.50mm with 3k carbon fiber;
(3) on Two-dimensional Carbon fiber plain weave precast body, join and bore tilting hole, the regularity of distribution of tilting hole on Two-dimensional Carbon fiber plain weave precast body is as follows: defining tilting hole angle axial and Two-dimensional Carbon fiber plain weave precast body normal direction is oblique angle θ, taking Two-dimensional Carbon fiber plain weave precast body lower surface center as coordinate origin O, lower surface is XOY plane, by XOY plane be straight up+Z axis, in 1-4 octant, respectively there is N parallel tilting hole, in each octant, the adjacent tilting hole distance between XOY plane Shang center equates, this distance is with from nearest first the tilting hole of initial point O, the distance between XOY plane Shang center and initial point O equates, the first octant is (cos α with the direction cosine of N parallel tilting hole in the 3rd octant, cos β, cos θ), the second octant is (cos α with the direction cosine of N parallel tilting hole in the 4th octant,-cos β, cos θ), wherein cos
2α+cos
2β+cos
2θ=1, θ=45 °, composite panel total thickness h=5mm, carbon fiber Z-pin member length l must meet: l>=h/cos θ=5mm/cos45 °
7.071mm, the volume of described tilting hole accounts for 0.5% of Two-dimensional Carbon fiber plain weave precast body volume, determines N value by this volume fraction.
(4) by the tilting hole of the tilting embedding Two-dimensional Carbon of carbon fiber Z-pin member fiber plain weave precast body;
(5) the Two-dimensional Carbon fiber plain weave precast body of employing CVI process deposits band carbon fiber Z-pin member, makes its densification, obtains two-dimentional ceramic matric composite plate;
(6) carbon fiber Z-pin member position is processed and repaired: remove carbon fiber Z-pin member redundance, make carbon fiber Z-pin member concordant with two-dimentional ceramic matric composite plate outside surface; Then adopt CVI technique to prepare SiC coating at two-dimentional ceramic matric composite plate outside surface, carbon fiber Z-pin member position is covered and protected.
Described CVI processing parameter is: temperature is controlled at 800 DEG C, and pressure is 10kPa, the about 100h of depositing time.
Force analysis:
If elementary cell region lower surface of two-dimentional C/SiC ceramic matric composite precast body is clamped, precast body elementary cell upper surface is subject to the uniform peeling force of normal direction, makes a concerted effort for F
i:
Existing implantation, the shearing force that single carbon fiber Z-pin member linkage interface need to bear is made a concerted effort
Tilting implantation, the normal force F that carbon fiber Z-pin member bears
ibe decomposed into along carbon fiber Z-pin members shaft to shear component and perpendicular to the extruding component of carbon fiber Z-pin member axis;
Tilting implantation, the shearing force that linkage interface need to bear is made a concerted effort
Tilting implantation, the squeeze of carbon fiber Z-pin member and hole
If final condition is precast body elementary cell, four limits are clamped, and carbon fiber Z-pin member is subject to uniform body force, make a concerted effort for F
i:
Existing implantation, the shearing force that single carbon fiber Z-pin member linkage interface need to bear is made a concerted effort
Tilting implantation, the normal force F that carbon fiber Z-pin member bears
ibe decomposed into along carbon fiber Z-pin members shaft to shear component and perpendicular to the extruding component of rivet axis;
Tilting implantation, the shearing force that linkage interface need to bear is made a concerted effort
Tilting implantation, the squeeze of carbon fiber Z-pin member and hole
Embodiment 2
Described θ=15 °, all the other are with embodiment 1
Embodiment 3
Described θ=30 °, all the other are with embodiment 1
Embodiment 4
The volume of described tilting hole accounts for 1% of Two-dimensional Carbon fiber plain weave precast body volume, and all the other are with embodiment 1.
Embodiment 5
The volume of described tilting hole accounts for 2.5% of Two-dimensional Carbon fiber plain weave precast body volume, and all the other are with embodiment 1.
Embodiment 6
The volume of described tilting hole accounts for 4% of Two-dimensional Carbon fiber plain weave precast body volume, and all the other are with embodiment 1.
Embodiment 7
Described CVI processing parameter is: temperature is controlled at 1000 DEG C, and pressure is 5kPa, depositing time approximately 100
H, all the other are with embodiment 1.
Embodiment 8
Described CVI processing parameter is: temperature is controlled at 1100 DEG C, and pressure is 1kPa, the about 100h of depositing time, and all the other are with embodiment 1.
Claims (6)
1. an improved two-dimentional ceramic matric composite Z-pin method, is characterized in that comprising the following steps:
(1) prepare Two-dimensional Carbon fiber plain weave precast body;
(2) adopt pultrusion molding process to prepare carbon fiber Z-pin member, through intensification mold cured, cutting processing, obtain the carbon fiber Z-pin member of design length and diameter;
(3) on Two-dimensional Carbon fiber plain weave precast body, join and bore tilting hole, the regularity of distribution of tilting hole on Two-dimensional Carbon fiber plain weave precast body is as follows: defining tilting hole angle axial and Two-dimensional Carbon fiber plain weave precast body normal direction is oblique angle θ, taking Two-dimensional Carbon fiber plain weave precast body lower surface center as coordinate origin O, lower surface is XOY plane, by XOY plane be straight up+Z axis, in 1-4 octant, respectively there is N parallel tilting hole, in each octant, the adjacent tilting hole distance between XOY plane Shang center equates, this distance is with from nearest first the tilting hole of initial point O, the distance between XOY plane Shang center and initial point O equates, the first octant is (cos α with the direction cosine of N parallel tilting hole in the 3rd octant, cos β, cos θ), the second octant is (cos α with the direction cosine of N parallel tilting hole in the 4th octant,-cos β, cos θ), wherein cos
2α+cos
2β+cos
2θ=1,15 °≤θ≤45 °,
(4) by the tilting hole of the tilting embedding Two-dimensional Carbon of carbon fiber Z-pin member fiber plain weave precast body;
(5) the Two-dimensional Carbon fiber plain weave precast body of employing CVI process deposits band carbon fiber Z-pin member, makes its densification, obtains two-dimentional ceramic matric composite plate;
(6) carbon fiber Z-pin member position is processed and repaired: remove carbon fiber Z-pin member redundance, make carbon fiber Z-pin member concordant with two-dimentional ceramic matric composite plate outside surface; Then adopt CVI technique to prepare SiC coating at two-dimentional ceramic matric composite plate outside surface, carbon fiber Z-pin member position is covered and protected.
2. improved two-dimentional ceramic matric composite Z-pin method according to claim 1, is characterized in that: the diameter of described carbon fiber Z-pin member is 0.2-1.0mm.
3. improved two-dimentional ceramic matric composite Z-pin method according to claim 1 and 2, is characterized in that: the volume of described tilting hole accounts for 0.5%～4% of Two-dimensional Carbon fiber plain weave precast body volume, determines N value by this volume fraction.
4. improved two-dimentional ceramic matric composite Z-pin method according to claim 3, is characterized in that: the volume of described tilting hole accounts for 1%～2.5% of Two-dimensional Carbon fiber plain weave precast body volume, determines N value by this volume fraction.
5. improved two-dimentional ceramic matric composite Z-pin method according to claim 1, is characterized in that: described CVI processing parameter is: temperature is controlled at 800～1100 DEG C, and pressure is 1～10kPa, the about 100h of depositing time.
6. improved two-dimentional ceramic matric composite Z-pin method according to claim 5, is characterized in that: described CVI processing parameter is: temperature is controlled at 1000 DEG C, and pressure is 5kPa, the about 100h of depositing time.
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| CN107908151B (en) * | 2017-12-18 | 2024-03-26 | 哈尔滨工业大学（威海） | Z-PIN contact PIN control system and interpolation method |
| CN109605775A (en) * | 2018-12-11 | 2019-04-12 | 天津工业大学 | A kind of composite three dimensional preform |
| CN109503188B (en) * | 2018-12-14 | 2021-03-02 | 上海康碳复合材料科技有限公司 | CVI (chemical vapor infiltration) process method for preparing carbon/carbon crucible based on flow field optimization |
| CN112876269B (en) * | 2021-01-18 | 2023-04-28 | 湖南碳康生物科技有限公司 | Length-adjustable carbon fiber composite artificial rib and preparation method thereof |
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| GB0112893D0 (en) * | 2001-05-25 | 2001-07-18 | Dunlop Aerospace Ltd | Refractory-carbon composite brake friction elements |
| CN100460359C (en) * | 2005-03-21 | 2009-02-11 | 西安航天复合材料研究所 | Method for producing carbon/carbon skid of magnetic suspension train |
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| CN102503502B (en) * | 2011-10-21 | 2013-05-08 | 南京航空航天大学 | Method for manufacturing Z-pin reinforced carbon/carbon composite prefabricated part and Z-pin freezing pultrusion and implantation integrated machine |
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