CN108911776A - A kind of surface antiscour flexibility heat-insulation composite material and preparation method thereof - Google Patents
A kind of surface antiscour flexibility heat-insulation composite material and preparation method thereof Download PDFInfo
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- CN108911776A CN108911776A CN201810687877.0A CN201810687877A CN108911776A CN 108911776 A CN108911776 A CN 108911776A CN 201810687877 A CN201810687877 A CN 201810687877A CN 108911776 A CN108911776 A CN 108911776A
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- 238000009413 insulation Methods 0.000 title claims abstract description 51
- 239000002131 composite material Substances 0.000 title claims abstract description 37
- 238000002360 preparation method Methods 0.000 title claims abstract description 24
- 230000002787 reinforcement Effects 0.000 claims abstract description 69
- 238000007598 dipping method Methods 0.000 claims abstract description 32
- 239000000919 ceramic Substances 0.000 claims abstract description 20
- 238000000034 method Methods 0.000 claims abstract description 17
- 238000000280 densification Methods 0.000 claims abstract description 8
- 239000000835 fiber Substances 0.000 claims description 84
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 51
- PNEYBMLMFCGWSK-UHFFFAOYSA-N Alumina Chemical compound [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 38
- 239000000463 material Substances 0.000 claims description 36
- 230000002209 hydrophobic effect Effects 0.000 claims description 22
- 239000010453 quartz Substances 0.000 claims description 17
- 239000000377 silicon dioxide Substances 0.000 claims description 17
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 claims description 15
- 229910052863 mullite Inorganic materials 0.000 claims description 15
- 238000005470 impregnation Methods 0.000 claims description 10
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 claims description 8
- 229910001928 zirconium oxide Inorganic materials 0.000 claims description 8
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 7
- 239000011230 binding agent Substances 0.000 claims description 7
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 7
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 7
- 229920005989 resin Polymers 0.000 claims description 5
- 239000011347 resin Substances 0.000 claims description 5
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims description 4
- 230000002708 enhancing effect Effects 0.000 claims description 4
- 125000001495 ethyl group Chemical group [H]C([H])([H])C([H])([H])* 0.000 claims description 4
- BFXIKLCIZHOAAZ-UHFFFAOYSA-N methyltrimethoxysilane Chemical compound CO[Si](C)(OC)OC BFXIKLCIZHOAAZ-UHFFFAOYSA-N 0.000 claims description 4
- 125000001997 phenyl group Chemical group [H]C1=C([H])C([H])=C(*)C([H])=C1[H] 0.000 claims description 4
- 239000002243 precursor Substances 0.000 claims description 4
- 230000001680 brushing effect Effects 0.000 claims description 3
- 238000003763 carbonization Methods 0.000 claims description 3
- 239000002994 raw material Substances 0.000 claims description 3
- -1 methylsiloxane Chemical class 0.000 claims description 2
- 239000004890 Hydrophobing Agent Substances 0.000 claims 1
- RMAQACBXLXPBSY-UHFFFAOYSA-N silicic acid Chemical compound O[Si](O)(O)O RMAQACBXLXPBSY-UHFFFAOYSA-N 0.000 claims 1
- 239000007921 spray Substances 0.000 claims 1
- 239000004575 stone Substances 0.000 claims 1
- 239000002023 wood Substances 0.000 claims 1
- 239000010410 layer Substances 0.000 description 36
- 239000004744 fabric Substances 0.000 description 13
- 230000000052 comparative effect Effects 0.000 description 11
- 239000000047 product Substances 0.000 description 10
- 150000001875 compounds Chemical class 0.000 description 9
- 239000004753 textile Substances 0.000 description 9
- 230000008569 process Effects 0.000 description 7
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 6
- 239000001301 oxygen Substances 0.000 description 6
- 229910052760 oxygen Inorganic materials 0.000 description 6
- 230000037396 body weight Effects 0.000 description 5
- 125000002496 methyl group Chemical group [H]C([H])([H])* 0.000 description 5
- 238000005507 spraying Methods 0.000 description 5
- 235000019786 weight gain Nutrition 0.000 description 5
- BLRPTPMANUNPDV-UHFFFAOYSA-N Silane Chemical compound [SiH4] BLRPTPMANUNPDV-UHFFFAOYSA-N 0.000 description 4
- 229910000077 silane Inorganic materials 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000005524 ceramic coating Methods 0.000 description 3
- 239000003795 chemical substances by application Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000000465 moulding Methods 0.000 description 3
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 description 2
- 239000004793 Polystyrene Substances 0.000 description 2
- 239000004964 aerogel Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 239000003153 chemical reaction reagent Substances 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000003475 lamination Methods 0.000 description 2
- 229920002223 polystyrene Polymers 0.000 description 2
- 229920002050 silicone resin Polymers 0.000 description 2
- 239000002196 Pyroceram Substances 0.000 description 1
- 229910003978 SiClx Inorganic materials 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- YCIVSJFIXXVSRH-UHFFFAOYSA-N amino-methyl-phenylsilicon Chemical compound C[Si](N)C1=CC=CC=C1 YCIVSJFIXXVSRH-UHFFFAOYSA-N 0.000 description 1
- 229910052810 boron oxide Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- JKWMSGQKBLHBQQ-UHFFFAOYSA-N diboron trioxide Chemical compound O=BOB=O JKWMSGQKBLHBQQ-UHFFFAOYSA-N 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000686 essence Substances 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000001965 increasing effect Effects 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- LQFNMFDUAPEJRY-UHFFFAOYSA-K lanthanum(3+);phosphate Chemical compound [La+3].[O-]P([O-])([O-])=O LQFNMFDUAPEJRY-UHFFFAOYSA-K 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000005416 organic matter Substances 0.000 description 1
- 229910052573 porcelain Inorganic materials 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 238000009958 sewing Methods 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 239000002002 slurry Substances 0.000 description 1
- 230000010148 water-pollination Effects 0.000 description 1
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
- C04B35/71—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
- C04B35/82—Asbestos; Glass; Fused silica
-
- 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
- C04B35/14—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 based on silica
-
- 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
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- 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
-
- 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
- C04B2235/9607—Thermal properties, e.g. thermal expansion coefficient
Abstract
The present invention relates to a kind of preparation methods of surface antiscour flexibility heat-insulation composite material, including：(1) the first reinforcement is mutually laminated and is sutured at least one second reinforcement and connect, suture needle distance is 10 × 10-50 × 50mm, and the density of the first reinforcement is 0.05-0.60g/cm3, the density of the second reinforcement is 1.0-1.6g/cm3, obtain precast body；(2) it is at least partly dried after for the dipping object of densification dipping on precast body, obtains heat-insulation composite material.It further relates to a kind of using surface antiscour flexibility heat-insulation composite material made from above-mentioned preparation method.Surface antiscour flexibility heat-insulation composite material panel controllable precise prepared by the present invention avoids a large amount of panel ceramic matrixes and penetrates into middle layer heat insulation felt, improves structural stability, reliability.Surface antiscour flexibility heat-insulation composite material operational sequence prepared by the present invention is simple, has designability, so that reducing technique requires complexity, can meet the outer heat shield of different use environment high-speed aircrafts extensively.
Description
Technical field
The present invention relates to a kind of preparation method of surface antiscour flexibility heat-insulation composite material, further relate to described in a kind of use
Antiscour flexibility heat-insulation composite material in surface made from preparation method.
Background technique
High velocity of sound aircraft atmosphere or empty day back and forth on the way thermal protection system surface and air Pneumatic friction generate it is high
Mild Pneumatic pressure etc., the thermally protective materials that can be born at present are rigid thermal insulation tile and ablator.
Ablator is a kind of widely used solar heat protection method of current reentry vehicle, is mainly inhaled using ablator cracking
Heat and gas diffusion take away heat, reach solar heat protection purpose, but there are density height, and heat-proof quality difference and linear ablation are fairly obvious etc.
Disadvantage.
Rigid ceramic tile is U.S. space shuttle large area thermal protection major programme, by pyroceram fibre high temperature sintering
It forms, technical maturity with higher.However, that there are brittleness is big, deformability is poor, assembly is complicated, the period for the type material
The disadvantages of length, maintenance cost is high, it is difficult to meet the thermal protection demand of the following high velocity of sound aircraft.
For the relatively low part of flight vehicle aerodynamic environment, Boeing develops a kind of novel flexible heat-barrier material-
Conformal reusable heat-barrier material (Comformal reusable insulation, CRI), is soaked by high-temperature-resistant fiber fabric
The upper surface of stain ceramic coating formation plate is constituted, table with certain rigid fiber bat heat-barrier material, fabric lower panel
Face ceramic coating can effectively improve the scour resistance and temperature tolerance of original material, using temperature up to 1204 DEG C.Boeing is
Produce with different antiscour surfaces, suture way, fiber bat CRI material, and dependence test has been carried out to its performance and has been ground
Study carefully, associated materials are succeeded on the windward side of X-37A, X-37B application.Its basic preparation flow is：It selects
For the high-temperature-resistant fiber fabrics such as Nextel440 as top panel reinforcing material, the lower fabric of the heatproofs such as E- glass is following
Plate material；The fiber bat made of the ceramic fibres such as aluminium oxide, silica, boron oxide with certain rigidity is heat-barrier material,
Its hardness indicates with Shore Durometer type OOO, minimum 90；Upper and lower panel and heat-barrier material are sutured,
440 fiber of Nextel is upper thread, and S-glass fiber is baseline, and suture way is similar with space shuttle AFRSI, and suture spacing is
2.54cm square；The rigidity of heat-barrier material can avoid occurring recess situation in sewing process, guarantee the thickness of material surface after suture
Spend homogeneity；Top panel fabric and with the ceramic slurries such as the boundary layer oxide impregnation silicon, aluminium oxide, lanthanum orthophosphate of heat-barrier material, benefit
With mould shape, solidify, be formed in formation ceramic coating in surface after high-temperature process, and high temperature removes the impurity such as organic matter, preparation
CRI is obtained, surface flatness is ± 0.38mm, and thickness fluctuation is ± 0.760mm；However, if middle layer heat-barrier material not
By pretreatment, dipping sizing agent is easily infiltrated into inside heat-barrier material, not only increases the density of component, and heat-proof quality also will receive sternly
Ghost image is rung, and needing to formulate stringent technology controlling and process, to be just able to achieve structural behaviour controllable.
In view of this, the present invention is specifically proposed.
Summary of the invention
The first object of the present invention is to provide a kind of preparation method of surface antiscour flexibility heat-insulation composite material, with reality
The purpose of existing optimizing surface antiscour flexibility heat-insulation composite material heat-proof quality；The second object of the present invention is that providing one kind adopts
The surface antiscour flexibility heat-insulation composite material made from the preparation method.
To realize that the first purpose, the present invention adopt the following technical scheme that：
A kind of preparation method of surface antiscour flexibility heat-insulation composite material, including：
(1) the first reinforcement is mutually laminated and is sutured at least one second reinforcement and connect, suture needle distance is 10 × 10-
50 × 50mm, the density of the first reinforcement are 0.05-0.60g/cm3, the density of the second reinforcement is 1.0-1.6g/cm3, obtain
Precast body；
(2) it is at least partly dried, obtains heat-insulated multiple after for the dipping object of densification dipping on precast body
Condensation material.
For surface antiscour flexibility heat-insulation composite material is made, present invention employs the different enhancings of at least two density
Body, the big reinforcement of density is for being made surface anti-impact brush layer, and the small reinforcement of density is for being made thermal insulation layer the experiment has found that
It is respectively 0.05-0.60g/cm when using density3And 1.0-1.6g/cm3Two reinforcements when, precursor structure obtained is more
Dipping object is not easy to immerse to another reinforcement when adding reliably, and carrying out densification to a reinforcement.When densification,
Due to the presence of density variation and dipping difference, the active force that two reinforcements are subject to is different, occurs therebetween opposite
Displacement, the present invention are 10 × 10-50 × 50mm by control suture needle distance, make two reinforcements on the basis of being reliably connected,
There is also moveable spaces between each other, to avoid connection structure and damage with adaptability to changes, to ensure that table
Face antiscour flexibility heat-insulation composite material reliability of structure, optimizes material property.
In step (1), the line density of the first reinforcement and the second reinforcement seam binder fibers is 190-1200tex, the twist
For 0-220 twirl/10cm.
When the line density for stitching binder fibers is 190-1200tex, dipping object is easier to enter and pass through for seam binder fibers
It is in hole and compound, while the structure of the first reinforcement and the second reinforcement will not be destroyed, so that it is compound to optimize aerogel heat-proof
Material property.
In step (1), the first reinforcement and the second reinforcement seam binder fibers are hydrophilic fibers, including quartz fibre, oxygen
Change aluminum fiber.
When stitch binder fibers be hydrophilic fibers when, thereon also can compound dipping object, so that it is compound to optimize aerogel heat-proof
Material property.
In step (1), the density of the first reinforcement is 0.20-0.60g/cm3, with a thickness of 3-110mm, preferred thickness 5-
25mm, the density of the second reinforcement are 1.2-1.6g/cm3。
In step (1), the first reinforcement be fibre, the raw material of fibre include high silica fiber, quartz fibre,
Alumina fibre, Zirconium oxide fibre, mullite fiber, silicon carbide fibre；Second reinforcement is fibre, the original of fibre
Material includes quartz fibre, alumina fibre, mullite fiber, high silica fiber, Zirconium oxide fibre, silicon carbide fibre, fiber system
The structure type of product is 2.5d, twill or satin weave.
In step (1), hydrophobic treatment first is carried out to the first reinforcement, then the first reinforcement is connected with the second reinforcement
It connects, in step (2), including at least the part of the second reinforcement through dipping object dipping on precast body；It is hydrophobic used in hydrophobic treatment
Agent includes methyltrimethoxysilane, methylsiloxane resin, ethyl organic siliconresin, phenyl organic siliconresin.
In step (2), dipping object includes ceramic base precursor, and ceramic base presoma includes that alumina sol, silica are molten
The combination of one or more of glue, mullite sol, zirconia sol, carbonization silica solution；Impregnation method include vacuum impregnation,
Brushing or spary.
In step (2), after dry, 0.5~5h is handled under the conditions of 600~1000 DEG C.
In step (1), by the first reinforcement and two second increasings for being respectively arranged on the two sides that the first reinforcement is oppositely arranged
Strong body is mutually laminated and sutures through same fiber and connects；The second reinforcement set on the first reinforcement side is excellent with a thickness of 0.1-5mm
Choosing is with a thickness of 0.5-2mm；The second reinforcement set on the other side that the first reinforcement is oppositely arranged is with a thickness of 0.1-5mm, preferably
With a thickness of 0.2-0.5mm.
First reinforcement and the second reinforcement not only include fibre, further include by densification at least once
Fibre is such as compounded with the fibre of aeroge.
Specifically, the preparation process of the surface antiscour flexibility heat-insulation composite material is as follows：
The first step prepares above-mentioned precast body
Preparing high-temperature fibre precast body by way of wet process or dry method or needle thorn to high-temperature fibre first, (correspondence is above-mentioned
First reinforcement).Then, hydrophobic treatment is carried out using hydrophobic organic.The effect of the hydrophobic treatment can prevent next
Hydrophily panel ceramic base presoma (corresponding above-mentioned dipping object) dipping Low-density high temperature resistant fibrofelt in step.Described hydrophobic have
Machine object is the organic reagents such as methyltrimethoxysilane or methyl, ethyl, phenyl, the hydrophobic types resin such as silicone resin, polystyrene.
By upper layer of fabric (corresponding above-mentioned second reinforcement), layer fabric (corresponding above-mentioned second reinforcement) respectively tiling with
The upper and lower surface of intermediate heat insulation felt (i.e. above-mentioned high-temperature fibre precast body) then forms sandwich structure using suture, obtains
Above-mentioned precast body.Suturing spacing is 10 × 10mm between 50 × 50mm, and suture is quartz fibre, alumina fibre etc.,
190tex between twist 0-220tex, (is handled, removal between 1200tex by hydrophilic pretreatment by acetone or 550 DEG C
Parent's profit agent).Here it can be divided into two methods：Fiber preform passes through monoblock type needle thorn molding (not having to suture).First
Hydrophobic type intermediate prefabricated body is prepared, then upper and lower deck panels fabric tiles and is superimposed, then carries out needle thorn, needling density 2-30
Between needle.
Second step prepares above-mentioned surface antiscour flexibility heat-insulation composite material
By hydrophilic ceramic base presoma by vacuum impregnation, brushing or spary technique, deck panels up and down are impregnated repeatedly and are knitted
Object.The hydrophilic ceramic presoma can be aluminium oxide, silica, mullite, zirconium oxide, carbonization silica solution or a variety of groups
Part any combination.0.5~5h is handled under the conditions of 600~1000 DEG C, removes middle layer heat insulation felt hydrophobic organic, panel material
Part ceramic obtains above-mentioned surface antiscour flexibility heat-insulation composite material.Material obtained progress surrounding machine is added, guarantees to produce
Product size.
Surface antiscour flexibility heat-insulation composite material is a kind of surface antiscour flexible insulant material, is sandwich interlayer knot
Structure, middle layer are high temperature resistant heat insulation felt, and upper and lower panel is the ceramic panel material of fabric enhancing.The middle layer is heat-insulated
Felt is high-temperature fibre precast body, passes through dry method (or wet process) laying, needling process preparation molding.The fiber preform, system
After standby molding, need to be filled processing using hydrophobic organic.The hydrophobic organic is methyltrimethoxysilane or first
The organic reagents such as base, ethyl, phenyl, the hydrophobic types resin such as silicone resin, polystyrene.The high-temperature fibre precast body can be height
Silica fiber, quartz fibre, alumina fibre, Zirconium oxide fibre, mullite fiber, silicon carbide fibre are prepared.On described
Deck panels are prepared by high-temperature-resistant fiber fabric composite ceramics sill.The high-temperature-resistant fiber fabric is 2.5d structure shape
Formula, or be the forms such as twill, satin.High-temperature fibre used in the high-temperature-resistant fiber fabric is quartz fibre, aluminium oxide fibre
Dimension, mullite fiber, high silica fiber, Zirconium oxide fibre, silicon carbide fibre etc..The ceramic matrix material is aluminium oxide, oxygen
SiClx, mullite, zirconium oxide, silicon carbide or Multicomponent any combination.The high temperature resistant middle layer heat insulation felt is with a thickness of 3-
110mm (preferably 5-25mm), density 0.05-0.60g/cm3.The upper and lower deck panels are with a thickness of 0.1-5mm (upper layer panel
It is preferred that 0.5-2mm, the preferred 0.2-0.5mm of lower layer's panel), density 1.2-2.4g/cm3。
Compared with prior art, the present invention has the advantages that：
1) for surface antiscour flexibility heat-insulation composite material is made, present invention employs the different enhancings of at least two density
Body, the big reinforcement of density is for being made surface anti-impact brush layer, and the small reinforcement of density is for being made thermal insulation layer the experiment has found that
It is respectively 0.05-0.60g/cm when using density3And 1.0-1.6g/cm3Two reinforcements when, precursor structure obtained is more
Dipping object is not easy to immerse to another reinforcement when adding reliably, and carrying out densification to a reinforcement.When densification,
Due to the presence of density variation and dipping difference, the active force that two reinforcements are subject to is different, occurs therebetween opposite
Displacement, the present invention are 10 × 10-50 × 50mm by control suture needle distance, make two reinforcements on the basis of being reliably connected,
There is also moveable spaces between each other, to avoid connection structure and damage with adaptability to changes, to ensure that table
Face antiscour flexibility heat-insulation composite material reliability of structure, optimizes material property.
2) surface antiscour flexibility heat-insulation composite material panel controllable precise prepared by the present invention avoids a large amount of panel potteries
Porcelain basal body penetrates into middle layer heat insulation felt, improves structural stability, reliability.
3) surface antiscour flexibility heat-insulation composite material operational sequence prepared by the present invention is simple, has designability, from
And reduce technique and require complexity, the outer heat shield of different use environment high-speed aircrafts can be met extensively.
Detailed description of the invention
Fig. 1 is the preparation technology flow chart of surface antiscour flexibility heat-insulation composite material of the invention.
Specific embodiment
It in order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below will be to the technology in embodiment
Scheme is clearly and completely described, and the following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention..
Embodiment 1
1) selecting density is 0.20g/cm3, with a thickness of 20mm mullite fiber felt be middle layer, using methyl trimethoxy oxygen
Base silane carries out hydrophobic pretreatment.
2) selecting density is 0.90g/cm3, with a thickness of the 2.5d quartz textile of 2mm be top panel, density is
0.90g/cm3, with a thickness of 0.4mm 2.5d quartz textile be lower panel, using suture way by middle layer, top panel,
Lower panel carries out integrated suture, and suture is aluminium oxide suture, 30 × 30mm of suture needle distance, and suture line density is
400tex, and it is non-twist, obtain sandwich precast body.
3) sandwich precast body is placed on platform, by silica solution by spraying method impregnate it is compound up and down deck panels, 60
4 hours dry under the conditions of DEG C, dipping is until rate of body weight gain is lower than 2% repeatedly.
4) material made from step (3) is handled to 0.5~5h under the conditions of 600~1000 DEG C, makes part ceramic.
5) material surrounding machine made from step (4) is added, guarantees product size.
Embodiment 2
1) selecting density is 0.20g/cm3, with a thickness of 20mm mullite fiber felt be middle layer, using aminomethyl phenyl silicon
Resin solution carries out hydrophobic pretreatment.
2) selecting density is 0.90g/cm3, with a thickness of the 2.5d quartz textile of 2mm be top panel, density is
0.90g/cm3, with a thickness of 0.4mm 2.5d quartz textile be lower panel, using suture way by middle layer, top panel,
Lower panel carries out integrated suture, and suture is aluminium oxide suture, 30 × 30mm of suture needle distance, and suture line density is
400tex, and it is non-twist, obtain sandwich precast body.
3) sandwich precast body is placed on platform, by silica solution by spraying method impregnate it is compound up and down deck panels, 60
4 hours dry under the conditions of DEG C, dipping is until rate of body weight gain is lower than 2% repeatedly.
4) material made from step (3) is handled to 0.5~5h under the conditions of 600~1000 DEG C, makes part ceramic.
5) material surrounding machine made from step (4) is added, guarantees product size.
Embodiment 3
1) selecting density is 0.20g/cm3, with a thickness of 20mm mullite fiber felt be middle layer, using methyl trimethoxy oxygen
Base silane carries out hydrophobic pretreatment.
2) selecting density is 0.90g/cm3, with a thickness of 2mm 2.5d aluminium oxide fabric be top panel, density 0.90g/
cm3, with a thickness of the 2.5d quartz textile of 0.4mm be lower panel, using suture way by middle layer, top panel, lower panel
Integrated suture is carried out, suture is aluminium oxide suture, and 30 × 30mm of suture needle distance, suture line density is 400tex, and
It is non-twist, obtain sandwich precast body.
3) sandwich precast body is placed on platform, by silica solution by spraying method impregnate it is compound up and down deck panels, 60
4 hours dry under the conditions of DEG C, dipping is until rate of body weight gain is lower than 2% repeatedly.
4) material made from step (3) is handled to 0.5~5h under the conditions of 600~1000 DEG C, makes part ceramic.
5) material surrounding machine made from step (4) is added, guarantees product size.
Embodiment 4
1) selecting density is 0.20g/cm3, with a thickness of 20mm mullite fiber felt be middle layer, using methyl trimethoxy oxygen
Base silane carries out hydrophobic pretreatment.
2) selecting density is 0.90g/cm3, with a thickness of the 2.5d quartz textile of 2mm be top panel, density is
0.90g/cm3, with a thickness of 0.4mm 2.5d quartz textile be lower panel, using suture way by middle layer, top panel,
Lower panel carries out integrated suture, and suture is aluminium oxide suture, 10 × 10mm of suture needle distance, and suture line density is
400tex, and it is non-twist, obtain sandwich precast body.
3) sandwich precast body is placed on platform, by silica solution by spraying method impregnate it is compound up and down deck panels, 60
4 hours dry under the conditions of DEG C, dipping is until rate of body weight gain is lower than 2% repeatedly.
4) material made from step (3) is handled to 0.5~5h under the conditions of 600~1000 DEG C, makes part ceramic.
5) material surrounding machine made from step (4) is added, guarantees product size.
Embodiment 5
1) selecting density is 0.20g/cm3, with a thickness of 20mm mullite fiber felt be middle layer, using methyl trimethoxy oxygen
Base silane carries out hydrophobic pretreatment.
2) selecting density is 0.90g/cm3, with a thickness of the 2.5d quartz textile of 2mm be top panel, density is
0.90g/cm3, with a thickness of 0.4mm 2.5d quartz textile be lower panel, using suture way by middle layer, top panel,
Lower panel carries out integrated suture, and suture is aluminium oxide suture, 10 × 10mm of suture needle distance, and suture line density is
800tex, and it is non-twist, obtain sandwich precast body.
3) sandwich precast body is placed on platform, by silica solution by spraying method impregnate it is compound up and down deck panels, 60
4 hours dry under the conditions of DEG C, dipping is until rate of body weight gain is lower than 2% repeatedly.
4) material made from step (3) is handled to 0.5~5h under the conditions of 600~1000 DEG C, makes part ceramic.
5) material surrounding machine made from step (4) is added, guarantees product size.
Comparative example 1
The difference from embodiment 1 is that without hydrophobic pretreatment process in step 1).
Comparative example 2
The difference from embodiment 1 is that suture needle distance is 5 × 5mm.
Comparative example 3
The difference from embodiment 1 is that suture needle distance is 60 × 60mm.
Test example 1
This test example has carried out performance detection to final product made from above-described embodiment and comparative example, the results are shown in Table 1.
Table 1
As shown in Table 1, the global density of product made from embodiment 1-5, compressive strength are below comparative example 1, thus may be used
Know, in embodiment 1-5, the dipping object for impregnation surface anti-impact brush layer fibrofelt does not immerse to thermal insulation layer fibrofelt, and
In comparative example 1, the dipping object for impregnation surface anti-impact brush layer fibrofelt is immersed to thermal insulation layer fibrofelt.Embodiment 1-5 is made
Room temperature thermal conductivity be lower than comparative example 1, i.e. heat-proof quality is better than comparative example 1, it follows that in embodiment 1-5, for impregnating
The dipping object of surface anti-impact brush layer fibrofelt does not immerse to thermal insulation layer fibrofelt, and in comparative example 1, since there is no hydrophobic place
Step is managed, therefore in impregnation surface anti-impact brush layer fibrofelt, it is fine that thermal insulation layer fibrofelt can be used for impregnation surface anti-impact brush layer
The dipping object dipping for tieing up felt, so as to cause heat-proof quality reduction, even if thermal insulation layer fibrofelt be used to impregnate in subsequent handling
The dipping object of thermal insulation layer fibrofelt impregnates, and can not improve heat-proof quality well.
Through other test discoveries, product made from embodiment 1 does not occur lamination still by the long period, and comparative example
2 and comparative example 3 made from product by the short period i.e. will appear lamination, it follows that the suture needle distance system of embodiment 1
The surface antiscour flexibility heat-insulation composite material structural reliability obtained is higher.
The present invention is described in detail, of the invention its object is to which those skilled in the art can understand
Content is simultaneously implemented, and it is not intended to limit the scope of the present invention, what all Spirit Essences according to the present invention were done etc.
Changes or modifications are imitated, should be covered by the scope of protection of the present invention.
Claims (10)
1. a kind of preparation method of surface antiscour flexibility heat-insulation composite material, which is characterized in that including：
(1) the first reinforcement is mutually laminated and is sutured at least one second reinforcement and connect, suture needle distance be 10 × 10-50 ×
50mm, the density of the first reinforcement are 0.05-0.60g/cm3, the density of the second reinforcement is 1.0-1.6g/cm3, obtain prefabricated
Body；
(2) it is at least partly dried after for the dipping object of densification dipping on precast body, obtains heat-insulated composite wood
Material.
2. a kind of preparation method of surface antiscour flexibility heat-insulation composite material according to claim 1, which is characterized in that
In step (1), the line density of the first reinforcement and the second reinforcement seam binder fibers is 190-1200tex, twist 0-220
Twirl/10cm.
3. a kind of preparation method of surface antiscour flexibility heat-insulation composite material according to claim 1, which is characterized in that
In step (1), the first reinforcement and the second reinforcement seam binder fibers are hydrophilic fibers, including quartz fibre, alumina fibre.
4. a kind of preparation method of surface antiscour flexibility heat-insulation composite material according to claim 1, which is characterized in that
In step (1), the density of the first reinforcement is 0.20-0.60g/cm3, with a thickness of 3-110mm, preferred thickness 5-25mm；The
The density of two reinforcements is 1.2-1.6g/cm3。
5. a kind of preparation method of surface antiscour flexibility heat-insulation composite material according to claim 1, which is characterized in that
In step (1), the first reinforcement is fibre, and the raw material of fibre includes high silica fiber, quartz fibre, aluminium oxide fibre
Dimension, Zirconium oxide fibre, mullite fiber, silicon carbide fibre；Second reinforcement is fibre, and the raw material of fibre includes stone
English fiber, alumina fibre, mullite fiber, high silica fiber, Zirconium oxide fibre, silicon carbide fibre, the structure of fibre
Form is 2.5d, twill or satin weave.
6. a kind of preparation method of surface antiscour flexibility heat-insulation composite material according to claim 1, which is characterized in that
In step (1), hydrophobic treatment first is carried out to the first reinforcement, then the first reinforcement is connected with the second reinforcement, step (2)
In, including at least the part of the second reinforcement through dipping object dipping on precast body；Hydrophobing agent used in hydrophobic treatment includes methyl
Trimethoxy silane, methylsiloxane resin, ethyl organic siliconresin, phenyl organic siliconresin.
7. a kind of preparation method of surface antiscour flexibility heat-insulation composite material according to claim 1, which is characterized in that
In step (2), dipping object includes ceramic base precursor, and ceramic base presoma includes alumina sol, silica sol, mullite
The combination of one or more of colloidal sol, zirconia sol, carbonization silica solution；Impregnation method includes vacuum impregnation, brushing or spray
Brush.
8. a kind of preparation method of surface antiscour flexibility heat-insulation composite material according to claim 1, which is characterized in that
In step (2), after dry, 0.5~5h is handled under the conditions of 600~1000 DEG C.
9. the preparation method of -8 any a kind of surface antiscour flexibility heat-insulation composite materials according to claim 1, special
Sign is, in step (1), by the first reinforcement and two second enhancings for being respectively arranged on the two sides that the first reinforcement is oppositely arranged
Body is mutually laminated and sutures through same fiber and connects；The second reinforcement set on the first reinforcement side is with a thickness of 0.1-5mm, preferably
With a thickness of 0.5-2mm；The second reinforcement set on the other side that the first reinforcement is oppositely arranged is preferably thick with a thickness of 0.1-5mm
Degree is 0.2-0.5mm.
10. a kind of using surface antiscour flexibility heat-insulation composite material made from any preparation method of claim 1-9.
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