CN110128158A - Solar heat protection/heat-insulated/carrying integrated ceramic base light sandwich structure and preparation method thereof - Google Patents
Solar heat protection/heat-insulated/carrying integrated ceramic base light sandwich structure and preparation method thereof Download PDFInfo
- Publication number
- CN110128158A CN110128158A CN201910327212.3A CN201910327212A CN110128158A CN 110128158 A CN110128158 A CN 110128158A CN 201910327212 A CN201910327212 A CN 201910327212A CN 110128158 A CN110128158 A CN 110128158A
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- China
- Prior art keywords
- corrugated plating
- panel
- insulated
- composite material
- isosceles trapezoid
- Prior art date
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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
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- C—CHEMISTRY; METALLURGY
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Abstract
The present invention provides a kind of solar heat protection/heat-insulated/carrying integrated ceramic base light sandwich structures, and structure includes top panel, lower panel, corrugated plating and sandwich of layers；The top panel, lower panel and corrugated plating are each independently selected from C/SiC, quartz/quartz, Al2O3/ mullite, Al2O3/Al2O3, one of SiC/SiC or a variety of ceramic matric composite plates；The corrugated plating connection top panel and lower panel form lattice structure, the lighting structure as solar heat protection or carrying；The sandwich of layers is filled in the gap between the corrugated plating and top panel and lower panel, and the laminboard layer is selected from SiO2、Al2O3、SiOC、ZrO2With one of carbon or a variety of aerogel composites, and there is volume fraction to account for one of 4% alumina silicate, mullite or high silica fiber blanket or a variety of as reinforcement in aerogel composite.
Description
Technical field
The invention belongs to technical field of composite materials, more particularly to a kind of anti-/ heat-insulated/carrying integrated ceramic base lightweight folder
Core structure composite material light sandwich structure and preparation method.
Background technique
Hypersonic aircraft high-speed flight or the collective effect that aerodynamic loading and thermal force are born during reentering are
Guarantee aircraft contour structures are complete, while the component of aircraft interior can work normally, and thermal protection system needs full
Sufficient thermal protection, heat-insulated and structural bearing demand.The large area thermal protection system surface temperature of hypersonic aircraft is up to
1200 DEG C, therefore traditional heat insulation material such as high temperature insulating watt, flexible heat insulation felt, metal TPS structure etc. are not able to satisfy use and want
It asks.
Ceramic cover plate is a kind of novel thermal protection system, it is by high temperature conjunction part by ceramic cover plate and the main knot of fuselage
Structure is connected, and filling flexible heat insulation felt achievees the effect that heat-insulated between cover board and fuselage main structure.Compared with thermal insulation tile or felt, this
Kind structure separates the carrying of anti-insulation system and heat transmission function.The function of carrying and transmitting load is mainly by aircraft surface
Ceramic cover plate undertakes, and heat insulating function is realized by internal felt insulation.
Europe and American Studies C/SiC composite material TPS aspect research are more.In recent years, associated ultrasonic speed or Gao Chaosheng
Different degrees of use C/SiC composite material cover-plate type thermal protection system on the device of taking a flight test of fast project.Such as European ultrasound
Aircraft large area thermal protection system is using C/SiC composite material as ceramic cover plate and structure in fast flight plan (Pre-X)
(ActaAstronautica, 2005,56 (4): 453-464), if attached drawing 1 is that the windward side Pre-X uses C/SiC composite material
The signal of TPS, figure Oxford gray position are C/SiC composite material cover-plate type thermal protection system, and structural panel is compound using C/SiC
Material, high temperature conjunction part and fastener use Inconel series of high temperature alloy, and panel full-size is 0.8m × 0.5m, mainly
The test of progress reenters the heat of hot-fluid environment, power coupling measurement etc. including Mechanics Performance Testing, noise testing, simulation PRE-X,
Test has carried out 13 times altogether, and the time is more than 11000s, and test result display surface C/SiC composite material face has excellent property
Energy；Fig. 2 is C/SiC composite material TPS structural schematic diagram and material object on Pre-X.
In addition, the windward side large area thermal protection system of the USV-X reentry vehicle of Italy also uses C/SiC compound
Material cover-plate type structure.In addition to aircraft windward side, the front end solar heat protection of the nose cone and leeward of USV-X reentry vehicle is adopted
With C/SiC composite material, the total weight of C/SiC composite material face thickness 3mm, TPS structure only 105.5kg.
Anti-/heat-insulated/carrying integrated ceramic based composites sandwich structure of lightweight is hypersonic aircraft thermal protection
The developing direction of system, but anti-/ heat-insulation integrative only is realized at present, simple ceramic panel adds the combination of heat-barrier material still
Cannot bear concentrfated load in aircraft, it is therefore desirable to design improve lightweight it is anti-/ structure of heat-barrier material realizes bearing function,
Truss core structure is a research direction.
Currently, the truss core structure of polymer matrix composites and metal be easy molding, bearing capacity is strong, but temperature tolerance compared with
Difference.For example, the sandwich structure for the foamed aluminium filling carbon steel corrugated plating that CN104175623 manufactures and designs can be realized as bearing structure
Lightweight.CN104129101 design is prepared for a kind of resin-based integral reinforcing Unidirectional Fiber-reinforced Composite dot matrix folder
Core plate, core structures are pyramid, can be used for the lightweight of bearing structure, but can not be applied to hot environment.
CN205022842 then devises a kind of hypersonic aircraft titanium alloy cylindrical lightweight structure, that is, two sides titanium alloy
Covering adds medial arc plate dowel, plays good weight loss effect, but heatproof is no more than 800 DEG C.Therefore, pottery resistant to high temperature
Porcelain based composites sandwich lattice structure become solve large area thermally protective materials it is anti-/ heat-insulated/bearing function is integrated can
It can approach.CN104177110 is prepared for the corrugated plating interlayer integral flat of C/SiC composite material for the Demand Design, has
It is possibly used for thermal protection structure, but interlayer integral structure plate preparation large area support construction will make mold design and processing
Technique is extremely complex, and is not easy to realize；And interlayer carbon cloth has no enhancing, and anti-pressure ability is to be improved.
Summary of the invention
The purpose of the present invention is for composite material dot matrix structure in the prior art it is heat-resisting/solar heat protection/carrying integration performance
The defects of not being able to satisfy engineering application requirement, the composite material dot matrix structure large-area manufacturing complex process, provide a kind of solar heat protection/
Heat-insulated/carrying integrated ceramic base light sandwich structure and preparation method thereof, high temperature resistant when the light sandwich density of texture is small, long
(800~1650 DEG C), it is anti-oxidant, there are excellent mechanical performances and reusable, which is able to achieve institute
It is controllable to obtain composite material outer dimension.
Technical thought of the invention is, lattice structure gap in-situ preparation heat-barrier material to be filled up completely sandwich knot
Gap in structure is realized anti-/ heat-insulated/carrying integration and the lightweight nature of ceramic base lightweight sandwich structure, is further increased
Its globality and heat-proof quality, by the cooperation of ripple lattice structure and sandwich of layers, realize 800~1650 DEG C of heatproof solar heat protection/
Heat-insulated/integrated light sandwich structure of carrying, 18~29kg/m of surface density2, combined density can be in 0.66~1.0g/
cm3Between adjust.On the one hand it is to improve molding die on the basis of existing technology in preparation method, realizes interlayer fiber
The suture of cloth simultaneously simplifies the preparation of large area lattice structure to realize its application；Another aspect is by corrugated plating and panel point
Preparation is opened, is then mechanically connected, preparation process is greatly simplified and is able to produce, assembles large size product.
The technical scheme is that a kind of solar heat protection/heat-insulated/carrying integrated ceramic base light sandwich structure, structure packet
Include top panel, lower panel, corrugated plating and sandwich of layers；The top panel, lower panel and corrugated plating are each independently selected from C/
SiC, quartz/quartz, Al2O3/ mullite, Al2O3/Al2O3, one of SiC/SiC or a variety of ceramic matric composite plates；
The corrugated plating connection top panel and lower panel form lattice structure, the lighting structure as solar heat protection or carrying；It is described sandwich
Layer is filled in the gap between the corrugated plating and top panel and lower panel, and the laminboard layer is selected from SiO2、Al2O3、SiOC、
ZrO2With one of carbon or a variety of aerogel composites, and the silicon for thering is volume fraction to account for 4% in aerogel composite
One of sour aluminium, mullite or high silica fiber blanket are a variety of as reinforcement.
Further, above-mentioned corrugated plating is multiple continuous 30~60 ° of isosceles trapezoids, the upper lower horizontal plane of isosceles trapezoid
It is connected respectively at the top panel with lower panel；The thickness of the top panel, lower panel and corrugated plating each independently 2~
Within the scope of 3mm.
Further, the density of above-mentioned laminboard layer is 0.3~0.45g/cm3；The solar heat protection/heat-insulated/carrying integration pottery
The density of porcelain base light sandwich structure is 0.66~1.0g/cm3。
The present invention also provides above-mentioned solar heat protection/heat-insulated/carrying integrated ceramic base light sandwich structure preparation method, packets
Include following steps:
S1, selection or processing mold: using composite material dot matrix structure fiber preform combined type molding die and/or
Composite material dot matrix structure fiber preform integrally forming mould；
The molding of S2, fiber preform: fiber cloth is cut into required size, in composite material dot matrix structure fibre preforms
Body combined type molding die surface profiling is laid with 10~15 layers of fiber cloth and then carries out interlayer suture, obtains corrugated plating fiber respectively
Precast body and panel fiber preform；And/or integrally make to be laid in molding die in composite material dot matrix structure fiber preform
Then 10~15 layers of fiber cloth carry out interlayer suture, directly obtain corrugated plating lattice structure precast body；
S3, densification: molten using precursor for the corrugated plating fiber preform and panel fiber preform obtained respectively
Liquid vacuum impregnation-crosslinking curing-Pintsch process process several times or colloidal sol vacuum impregnation-drying and dewatering-high-temperature processing technology number
Secondary or chemical vapor deposition process hundreds of hours obtain corrugated plating green body and panel green body；And/or for directly obtaining wave
Card lattice structure precast body, it is true using precursor solution vacuum impregnation-crosslinking curing-Pintsch process process several times or colloidal sol
For several times or chemical vapor deposition process hundreds of hours, ceramic base composite wood is made in empty dipping-drying and dewatering-high-temperature processing technology
Expect corrugated plating lattice structure green body；
S4, processing: for corrugated plating green body and panel green body, carrying out numerical control processing, size needed for obtaining and joint face essence
The corrugated plating and panel of degree, and prefabricated connecting hole are connected using high temperature conjunction part, obtain Combined ceramic based composites ripple
Plate lattice structure；And/or for ceramic matric composite corrugated plating lattice structure green body, the processing such as trimming, surface plain grinding is carried out,
Obtain monoblock type ceramic matric composite corrugated plating lattice structure；
S5, rear densification: the Combined ceramic based composites corrugated plating lattice structure or entirety obtained for step S4
Formula ceramic matric composite corrugated plating lattice structure uses precursor solution vacuum impregnation-crosslinking curing-Pintsch process technique,
Or colloidal sol vacuum impregnation-drying and dewatering-high-temperature processing technology is for several times or chemical vapor deposition process hundreds of hours, obtains ceramics
Based composites corrugated plating lattice structure；
S6, laminboard layer preparation: by including supercritical drying or foaming but being not limited to the supercritical drying or foaming
Aeroge composite wood is prepared in situ in the gap of the resulting ceramic matric composite corrugated plating lattice structure of step S5 in the method for method
Expect heat-insulated laminboard layer, is prevented/heat-insulated/carrying integrated ceramic base composite material light sandwich structure.
Further, above-mentioned steps S6 specifically includes the following steps:
S61, paving cotton: the enhancing of fiber blanket is laid at the gap original position of ceramic matric composite corrugated plating lattice structure
Body；
S62, colloidal sol are prepared and dipping: preparing colloidal sol, the colloidal sol is SiO2、Al2O3、SiOC、ZrO2One of with carbon
Or it is a variety of, then the ceramic matric composite corrugated plating lattice structure for being laid with fiber blanket reinforcement is placed in vacuum tank,
Colloidal sol vacuum impregnation is carried out under the conditions of vacuum degree < 100Pa；
S63, aging: 48 hours are stood in a sealed container, gelation makes network skeleton continue to grow up；
S64, supercritical drying: aging is completely laid with fiber blanket reinforcement corrugated plating lattice structure be transferred to it is super
Critical drying equipment carries out supercritical drying, is prevented/heat-insulated/carrying integrated ceramic base composite material light sandwich structure.
Further, the fiber cloth in above-mentioned steps S2 is selected from carbon cloth, SiC fiber cloth, quartz fiber cloth and oxygen
Change one of aluminum fiber cloth or a variety of；For composite material dot matrix structure fiber preform combined type molding die, corrugated plating
The fiber cloth that surface is laid with uses twill or satin, and the fiber cloth that panel surface is laid with uses plain weave or twill；For
The fiber cloth of composite material dot matrix structure fiber preform integrally forming mould, laying is selected in plain weave, twill or satin
It is one or more.
Further, the precursor solution that precursor solution vacuum impregnation uses in above-mentioned steps S3 is weight ratio 1:1's
Polycarbosilane-xylene solution or weight ratio 1:1 Polycarbosilane-divinyl benzole soln；Colloidal sol in colloidal sol vacuum impregnation is adopted
With silica solution and/or Aluminum sol, wherein the mass concentration of silica and/or aluminium oxide is more than in silica solution and/or Aluminum sol
40%；12 hours vacuum-impregnated time；Being each independently for several times 3~8 times in the step S3；In the S3 step
Hundreds of hours are 300~400h.
Further, the high temperature conjunction part of above-mentioned steps S4 is C/SiC screw rod or pin；In the step S5 for several times
7~12 times each independently.
Further, the composite material dot matrix structure fiber preform integrally forming mould side of including: in above-mentioned steps S1
To control sliding rail plate, outer plate, clip plate, fixed block, trapezoidal cushion block；The direction controlling sliding rail plate is used for and trapezoidal pad
Block cooperatively forms ripple struction, including the identical plate of 2 block layouts, is provided with N+ in same horizontal line along its length on plate
1 handstand isosceles trapezoid through-hole and N number of upright isosceles trapezoid through-hole, N is positive integer, the upright isosceles trapezoid through-hole and handstand
The arrangement of isosceles trapezoid through-hole staggered relative；The quadrangle of two pieces of plates is correspondingly arranged on sliding rail plate connecting hole, for passing through sliding rail
Column makes two pieces of plates connect and fix at a distance of predetermined size；The trapezoidal cushion block is the long strip block of isosceles trapezoid cross section, is used for
It fills and connects the handstand isosceles trapezoid through-hole and upright isosceles trapezoid through-hole on the two Block directions control sliding rail plate；It is described
The outer dimension of fixed block is consistent with trapezoidal cushion block, for being placed in the outermost handstand isosceles in both ends on direction controlling sliding rail plate
In trapezoidal hole, fixed block is equipped with fixed block connecting hole to be fixedly connected with direction controlling sliding rail plate, is laid with for fixed
Corrugated plating fiber cloth；The trapezoidal cushion block and fixed block are when composite material dot matrix structure fibre preforms are body formed as dot matrix
Hollow structure supporting block in structure, i.e. graphite core mould, material are graphite；The outer plate includes two frame corresponding positions
Hollow frame equipped with frame connecting hole, for compressing the fixed block connected between described two pieces of plates of direction controlling sliding rail plate
With trapezoidal cushion block, to form the ripple struction of composite material；The clip plate includes two pieces of plates, is respectively placed in outer plate two
The inside of frame is simultaneously fixedly connected by pressing plate connecting hole with the frame of outer plate, flat in direction controlling sliding rail for compressing setting
Composite material face between two pieces of plates of plate is used to be laid with composite material to form composite material face structure；It is described fall
The long bottom edge in vertical isosceles trapezoid hole connects square through hole, and square through hole is communicated as one with handstand isosceles trapezoid through-hole, convenient for fibre
Tie up the insertion of trapezoidal cushion block and pressing mold in precast body forming process.
Further, the composite material dot matrix structure fiber preform combined type molding die in above-mentioned steps S1 includes wave
Card formpiston, corrugated plating former and panel mould；The corrugated plating formpiston, corrugated plating former and panel mould are graphite material；Institute
Stating corrugated plating formpiston is the square plate that surface intermediate parallel is arranged with the identical N isosceles trapezoid protrusion of height, the N isosceles
N-1 groove is formed between trapezoidal protrusion；The corrugated plating cavity dimension is identical as corrugated plating formpiston, corresponding arrangement among surface
There is the identical isosceles trapezoid protrusion of N+1 item height, the outside of two isosceles trapezoid protrusions of outermost is each provided with surely high block, described
Half isosceles trapezoid bottom surface is collectively formed in fixed high block and outermost protrusion seamless connection, and fixed high block overhead height is higher than described etc.
The height of the trapezoidal protrusion of waist forms N number of groove between N+1 isosceles trapezoid protrusion；It is removed in the corrugated plating female mold surfaces
The size of remaining outer protrusion of two protrusions of outermost is matched with the size of N-1 groove in corrugated plating male mold surfaces, accordingly, wave
The size of N number of protrusion is matched with the size of N groove in corrugated plating female mold surfaces in card male mold surfaces；The corrugated plating sun
The surrounding corresponding position of mould and corrugated plating former has location hole, for connecting and compressing corrugated plating formpiston and corrugated plating former；
Wherein N is the integer more than or equal to 2；The panel mould is upper and lower two pieces of plates.
Compared with the prior art, the advantages of the present invention are as follows:
(1) the lighting lattice structure that the present invention is carried using ceramic matric composite as solar heat protection, with SiO2、 Al2O3、
SiOC and carbon aerogel composite material etc. are heat-insulated laminboard layer, which has lightweight, height
By force, high temperature resistant (800~1650 DEG C), it is anti-oxidant, efficiently prevent the advantages that heat-insulated, reusable；
(2) aerogel composite core material is prepared in situ using collosol and gel-supercritical drying process in the present invention, by dot matrix
Structure is whole to be all soaked in colloidal sol, and the aeroge of generation will fill all gaps of sandwich part, avoid aeroge
Composite material it is cumbersome cut out installation process, inner space can be filled up completely, play good heat insulation；
(3) present invention uses polymer pyrolysis combination monolithic mold or sectional die technique to prepare ceramic base compound
Material light dot matrix structure, sectional die connection high-temperature technology avoids complicated mold and laying process, while numerical control adds
Work can guarantee the dimensional accuracy of light dot matrix structure；Or the one chemical conversion of light dot matrix structure is realized using monolithic mold
Type and manufacture.
To sum up ,/heat-insulated/the carrying integrated ceramic base composite material light sandwich structure of solar heat protection of the invention have lightweight,
High-strength, high temperature resistant (800~1650 DEG C), it is anti-oxidant, efficiently prevent heat-insulated, good bearing capacity and reusable advantage,
Preparation method have many advantages, such as simple process, can large area preparation, outer dimension can design and to control precision high.
Detailed description of the invention
From the detailed description with reference to the accompanying drawing to the embodiment of the present invention, these and/or other aspects of the invention and
Advantage will become clearer and be easier to understand, in which:
Fig. 1 is that the windward side Pre-X referred in background of invention uses the schematic diagram of C/SiC composite material TPS.
Fig. 2 is C/SiC composite material TPS structural schematic diagram on the Pre-X referred in background of invention.
Fig. 3 is C/SiC composite material TPS material object schematic diagram on the Pre-X referred in background of invention.
Fig. 4 is the corrugated plating of the composite material dot matrix structure fiber preform combined type molding die in the embodiment of the present invention
Formpiston schematic diagram, wherein Fig. 4 (a) is the schematic perspective view of corrugated plating formpiston, and Fig. 4 (b) is the vertical view of corrugated plating formpiston
Figure；
Fig. 5 is the corrugated plating of the composite material dot matrix structure fiber preform combined type molding die in the embodiment of the present invention
Former schematic diagram, wherein Fig. 5 (a) is the schematic perspective view of corrugated plating former, and Fig. 5 (b) is the vertical view of corrugated plating former
Figure；
The corrugated plating former of composite material dot matrix structure fiber preform integrally forming mould in Fig. 6 embodiment of the present invention
Schematic diagram；
Fig. 7 is the obtained C/SiC ceramic matric composite light dot matrix structure (nothing in interlayer gap in inventive embodiments
Filler) photo in kind；
Fig. 8 is the obtained C/SiC ceramic matric composite light sandwich structure material object photo in inventive embodiments.
Specific embodiment
In order to make those skilled in the art more fully understand the present invention, with reference to the accompanying drawings and detailed description to this hair
It is bright to be described in further detail.
Embodiment 1:
A kind of combined type composite material lattice structure fibre preforms forming die, structure is as shown in Fig. 4 and Fig. 5, packet
Include corrugated plating formpiston, corrugated plating former and panel mould；The corrugated plating formpiston, corrugated plating former and panel mould are graphite material
Matter, to be used for high-temperature process；Wherein Fig. 4 (a) is the schematic perspective view of corrugated plating formpiston, and Fig. 4 (b) is corrugated plating sun
The top view of mould, the corrugated plating formpiston are that surface intermediate parallel is arranged with the rectangular of the identical N isosceles trapezoid protrusion of height
Plate forms N-1 groove between N isosceles trapezoid protrusion；Fig. 5 (a) is the schematic perspective view of corrugated plating former, figure
5 (b) be the top view of corrugated plating former, and the corrugated plating cavity dimension is identical as corrugated plating formpiston, corresponding arrangement among surface
There is the identical isosceles trapezoid protrusion of N+1 item height, the outside of two isosceles trapezoid protrusions of outermost is each provided with surely high block, described
Half isosceles trapezoid bottom surface is collectively formed in fixed high block and outermost protrusion seamless connection, and fixed high block overhead height is higher than described etc.
The height of the trapezoidal protrusion of waist forms N number of groove between N+1 isosceles trapezoid protrusion；It is removed in the corrugated plating female mold surfaces
The size of remaining outer protrusion of two protrusions of outermost is matched with the size of N-1 groove in corrugated plating male mold surfaces, accordingly, wave
The size of N number of protrusion is matched with the size of N number of groove in corrugated plating female mold surfaces in card male mold surfaces；The corrugated plating formpiston
There is location hole with the surrounding corresponding position of corrugated plating former, for connecting and compressing corrugated plating formpiston and corrugated plating former；Its
Middle N is the integer more than or equal to 2；The panel mould is upper and lower two pieces of plates.
When making precast body using the composite material dot matrix structure fiber preform combined type molding die, in corrugated plating yin
It is laid with multi-layer fiber cloth along trapezoidal ripple body structure surface on mould, interlayer suture then is carried out to multi-layer fiber cloth, by corrugated plating sun
Mould upper trapezoid corrugated surface is placed on the corrugated plating former for be laid with fiber cloth to be molded, with graphite bolt (graphite bolt with
For subsequent high temperature treatment process) from location hole fastening corrugated plating former and corrugated plating formpiston, obtain corrugated plating fiber preform；
It is laid with fiber cloth respectively on two pieces of plates of panel mould, interlayer suture is carried out to multi-layer fiber cloth, is then suppressed, is obtained
Panel fiber preform.
Embodiment 2:
A kind of composite material dot matrix structure fiber preform integrally forming mould, structure are as shown in Figure 6, comprising: direction
Control sliding rail plate 1, outer plate 3, clip plate 4, fixed block 5, trapezoidal cushion block 6；The direction controlling sliding rail plate 1 is used for and ladder
Shape cushion block 6 cooperatively forms ripple struction, including the identical plate of 2 block layouts, sets in same horizontal line along its length on plate
It is equipped with N+1 handstand isosceles trapezoid through-hole and N number of upright isosceles trapezoid through-hole, N is positive integer, the upright isosceles trapezoid through-hole
It is arranged with handstand isosceles trapezoid through-hole staggered relative；The quadrangle of two pieces of plates is correspondingly arranged on sliding rail plate connecting hole 2, for leading to
Crossing sliding rail column makes two pieces of plates connect and fix at a distance of predetermined size；The trapezoidal cushion block 6 is the strip of isosceles trapezoid cross section
Block is logical for filling and connecting handstand isosceles trapezoid through-hole on two Block direction control sliding rail plate and upright isosceles trapezoid
Hole；The outer dimension of the fixed block 5 and trapezoidal cushion block 6 are consistent, for being placed in both ends outermost on direction controlling sliding rail plate
Handstand isosceles trapezoid through-hole in, fixed block 5 be equipped with fixed block connecting hole to be fixedly connected with direction controlling sliding rail plate, use
In the fixed corrugated plating fiber cloth being laid with；The trapezoidal cushion block 6 and fixed block 5 composite material dot matrix structure fiber preform at
As the hollow structure supporting block in lattice structure, i.e. graphite core mould when type, material is graphite；The outer plate 3 includes two
A frame corresponding position is equipped with the hollow frame of frame connecting hole 9, for compressing described 1 liang of direction controlling sliding rail plate of connection
Fixed block 5 and trapezoidal cushion block 6 between block plate, to form the ripple struction of composite material；The clip plate 4 includes two pieces flat
Plate is respectively placed in the inside of 3 two frames of outer plate and is fixedly connected by pressing plate connecting hole 8 with the frame of outer plate 3, is used for
It compresses and composite material face between 1 two pieces of plates of direction controlling sliding rail plate is set to form composite material face structure,
And for being laid with composite material；The long bottom edge in handstand isosceles trapezoid hole connects square through hole, square through hole and handstand isosceles
Trapezoidal hole is communicated as one, insertion and pressing mold convenient for cushion block 6 trapezoidal in fiber preform forming process.
Process using integrally forming mould production composite material dot matrix structure fiber preform includes the following steps:
S1, fiber cloth is cut out to design size, including panel fiber cloth trapezoidal corrugated plating fiber cloth in；
S2, on the wherein surface of one piece of clip plate lay panel fiber cloth to designing the number of plies；
S3, make the 1 two pieces of plates of direction controlling sliding rail plate being connected and fixed through sliding rail plate connecting hole 2 by sliding rail column with
The clip plate for the fiber cloth of lay panel being connected on 3 one frames of outer plate is at square crossing state, direction controlling
Upright isosceles trapezoid through-hole and handstand isosceles trapezoid through-hole on sliding rail plate 1 are located at lay panel fiber cloth clip plate fiber
Cloth surface；
S4, it is filled with trapezoidal cushion block 6 and to connect upright isosceles trapezoid in 1 two pieces of plates of direction controlling sliding rail plate logical
Hole, then the panel fiber cloth surface on lay panel fiber cloth clip plate and 6 surface of trapezoidal cushion block of upper part are laid with
Corrugated plating fiber cloth: when laying corrugated plating fiber cloth starts, corrugated plating is laid between 1 two pieces of plates of direction controlling sliding rail plate
Fixed block 5 is inserted into the starting point side of fiber cloth, and fixed block 5 is fixed on the control of two Block directions by fixed block connecting hole and is slided
To compress corrugated fiber cloth starting point on rail plate 1；Then the outer plate of another piece of not connected clip plate is installed, and outer by two pieces
Pressing plate 3 is by the connection fastening of frame connecting hole 9, to compress trapezoidal cushion block 6, fixed block 5 and the panel fiber cloth of filling；
S5, the suture that corrugated plating fiber cloth is carried out along trapezoidal 6 surface of cushion block suture it with panel fiber cloth contact position
At an entirety；The outer plate and fixed block 5 of the not connected clip plate of removal step S4 installation, suture fixed block 5 are split
The fiber cloth part blocked before removing；
After S6, suture, it is packed into parallel in the handstand isosceles trapezoid hole in two Block directions control sliding rail plate 1 surplus
Remaining trapezoidal cushion block 6；And two pieces of fixed blocks 5 are packed into most marginal handstand isosceles trapezoid through-hole through fixed block connecting hole
It is separately fixed at two Block directions control, 1 two sides of sliding rail plate；The outer plate for the not connected clip plate removed in installation steps S5, and
The outer plate is connected and fixed by pressing plate connecting hole 8 and another piece of outer plate of lay panel fiber cloth clip plate, with pressure
Tight trapezoidal cushion block 6, fixed block 5 and the panel fiber cloth and corrugated plating fiber cloth being laid with；
S7, the 6 surface lay panel fiber cloth of trapezoidal cushion block being packed into step s 6 are sutured simultaneously to the number of plies is designed
It is integral suturing the two with corrugated fiber cloth contact position；Then another piece of clip plate 4 is placed in the face of this step laying
Above plate fiber cloth and it is fixed on corresponding outer plate 3；
S8, mold is integrally spun upside down, i.e., the clip plate 4 being put into step S7 is placed in trapezoidal cushion block 6 and fixed block
The clip plate being fixedly connected in step S3 with outer plate 3 is removed in 5 lower ends, sutures to the unstitched part of panel fiber cloth,
Then the clip plate removed is installed again, the connection between two pieces of outer plates is tightened；
S9, integrally formed composite material dot matrix structure fiber preform is obtained.
As can be seen that not all operation is to strictly must sequentially carrying out in described step in above-mentioned steps S2-S9
, for example, step S3 can be first carried out in step S2 and S3, by be fixedly connected one group of clip plate and outer plate and at a distance of pre-
The two Block directions control sliding rail plate that set a distance is fixedly connected is mounted to square crossing state, then executes step S2, in clip plate
Surface lay panel fiber cloth；For another example, another piece of outer plate for being not connected to clip plate can be installed in step s3, only
It is first not fasten itself and the outer plate for being fixedly connected with lay panel fiber cloth clip plate, is connected again by frame in step s 4
Hole is connect to fasten two outer plate frames；Similarly, in step S5 can not removal step S4 installation not connected clip plate it is outer
Pressing plate, and the connection of two pieces of outer plate frames is only unclamped, with fixed block 5 easy to dismantle then to the fiber cloth blocked before it
It is sutured.Certainly, according to the habit of operator, falling on two Block directions control sliding rail plate can also be first filled in parallel
Vertical isosceles trapezoid hole is laid with after the processing such as fiber cloth, suture again filling handstand isosceles trapezoid hole in parallel, then carries out panel fiber
The laying and suture of cloth.In short, the purpose of inventive die design and use method and step description is to illustrate mould of the invention
The mutually not interlayer suture of contact position of the panel fiber cloth being laid with, corrugated plating fiber cloth may be implemented in tool, and in panel fibre
Panel fiber cloth and corrugated plating fiber cloth are stitched into an entirety with corrugated plating fiber cloth contact position by Wei Bu, realize composite wood
Expect that the integrally formed of lattice structure precast body, interlaminar strength are reinforced, lattice structure Support Position bearing capacity protrudes.Therefore, as long as
Using operating procedure be able to achieve it is above-mentioned to panel fiber cloth, corrugated plating fiber cloth mutually contact position carry out interlayer suture, with
And one entirety is stitched by panel fiber cloth and corrugated plating fiber cloth to panel fiber cloth and corrugated plating fiber cloth contact position,
And the fiber cloth of laying can be compressed in due course, fixed in process of deployment, reach the requirements such as flatness, the thickness of fiber cloth laying
It operates all consistent with target of the present invention.
Embodiment 3
A kind of solar heat protection/heat-insulated/carrying integrated ceramic base composite material light sandwich structure, the light sandwich structure is with C/
Lighting lattice structure of the SiC ceramic based composites as solar heat protection or carrying, with Al2O3Aerogel composite is heat insulation clamps
Sandwich layer, finished product photo are as shown in Figure 8.
The solar heat protection of the present embodiment/heat-insulated/carrying integration C/SiC ceramic matric composite light sandwich structure passes through following
Step is prepared:
(1) mold selects: selecting the combined type composite material lattice structure fibre preforms forming die of embodiment 1；
(2) molding of fiber preform: being cut into required size for carbon cloth, is laid with corrugated plating in female mold surfaces profiling
10 layers of twill carbon cloth of support construction, interlayer suture, formpiston molding, bolt fastening obtain corrugated plating fiber preform, etc.
The trapezoidal corrugated plating angle of waist is 60 °；10 layers of plain weave carbon fiber cloth of lay panel, interlayer suture, obtain the face 200mm × 200mm
Plate fiber preform；
(3) vacuum impregnation: by the Polycarbosilane-two of the fiber preform vacuum impregnation weight ratio 1:1 taken shape on mold
Toluene solution, vacuum degree < 200Pa, time 12h；
(4) crosslinking curing: by the precast body after vacuum impregnation in 250 DEG C of crosslinking curing 1h；
(5) Pintsch process: the precast body green body progress high-temperature heat treatment after crosslinking curing, 1400 DEG C of temperature, time 1h；
(6) it densifies: repeating vacuum impregnation-crosslinking curing-Pintsch process technique 8 times of step S3~S5, then demould,
C/SiC ceramic matric composite corrugated board blank and panel blank is made；
(7) it processes: numerical control processing being carried out to C/SiC ceramic matric composite corrugated plating and panel blank, needed for acquisition
The corrugated board blank and panel blank of size and joint face precision, and prefabricated connecting hole；
(8) it connects: being attached using C/SiC screw rod by connecting hole, obtain C/SiC ceramic matric composite lightweight knot
Structure assembly parts；The connection type can obtain smooth joint face, while being threadedly coupled high reliablity and connecting in pin, have more
Excellent antivibration and joint face tensile property.
(9) it densifies afterwards: repeating vacuum impregnation-crosslinking curing-Pintsch process technique 10 times of step S3~S5, be made
C/SiC ceramic matric composite light structures, as shown in Figure 7；The process can fill the gap of connecting portion, and it is strong to improve connection
Degree and connection reliability；
(10) it spreads cotton: being laid with alumina silicate fibre blanket in the core gap of C/SiC ceramic matric composite light structures,
Fiber volume fraction 4%；Aerogel composite is prepared separately to cut out again and be filled into during lattice structure, inevitably
Some space can not fill, and original position spreads cotton and subsequent gelation and can almost fill having time in lattice structure
Gap reduces heat bridge caused by the access of inner space.
(11) colloidal sol is prepared and is impregnated: being prepared Aluminum sol, will be laid with the C/SiC ceramic matric composite lightweight of fiber blanket
Structure is placed in vacuum tank, vacuum impregnation 4h under the conditions of vacuum degree < 100Pa；
(12) aging: 48 hours are stood in a sealed container, gelation makes network skeleton continue to grow up；
(13) supercritical drying: cotton light structures are completely spread to aging and carry out supercritical drying, obtain final C/SiC
Ceramic matric composite light sandwich structure.
Size 200mm × 200mm × 25mm of the C/SiC ceramic matric composite light sandwich structure of the present embodiment, it is comprehensive
Close density 0.99g/cm3, surface density 24.8kg/m2。
Embodiment 4
A kind of/heat-insulated/the carrying integrated ceramic base composite material light sandwich structure of solar heat protection, the light sandwich structure with
Lighting lattice structure of the SiC/SiC composite material as solar heat protection or carrying, with SiOC aerogel composite for heat-insulated sandwich
Layer.
The solar heat protection of the present embodiment/heat-insulated/carrying integrated ceramic base composite material light sandwich structure passes through following steps
It is prepared:
(1) mold selects: selecting the composite material dot matrix structure fiber preform integrally forming mould in embodiment 2；It should
Mold can be realized the integrally formed of dot matrix fiber preform, realizes interlayer suture and whole suture, improves the whole of lattice structure
Body bearing capacity；
(2) molding of fiber preform: being cut into required size for SiC fiber cloth, makes according to described in embodiment 2
Process and method are laid with corrugated plating and each 10 layers of lower panel in composite material dot matrix structure fiber preform integrally forming mould
SiC fiber cloth sutures corrugated plating and lower panel contact portion interlayer.Then interlayer seam multiplex card chamfered portion, compound
It is laid with 10 layers of carbon cloth of top panel in material dot matrix structural fibers precast body integrally forming mould, corrugated plating and top panel are connect
It is sutured between contact portion layering；
(3) vacuum impregnation: by the Polycarbosilane-two of the 5 weight ratio 1:1 of fiber preform vacuum impregnation taken shape on mold
Vinyl benzene solution, vacuum degree < 200Pa, time 12h；
(4) crosslinking curing: by the precast body after dipping in 250 DEG C of crosslinking curing 1h；
(5) Pintsch process: the precast body green body progress high-temperature heat treatment after crosslinking curing, 1200 DEG C of temperature, time 1h；
(6) it densifies: repeating vacuum impregnation-crosslinking curing-Pintsch process technique 6 times of step S3~S5, SiC/ is made
SiC ceramic based composites lattice structure blank；
(7) it processes: numerical control processing is carried out to SiC/SiC ceramic matric composite lattice structure blank；
(8) it densifies afterwards: repeating vacuum impregnation-crosslinking curing-Pintsch process technique 10 times of S3~S5, SiC/ is made
SiC ceramic base composite material light lattice structure；
(9) it spreads cotton: being laid with alumina silicate fibre blanket, fiber volume fraction 4% in the core gap of light structures；Gas
Gel complex material is prepared separately to cut out again and be filled into during lattice structure, inevitable that a part of space can not be filled out
It fills, and the in situ all gaps that spreads cotton and subsequent gelation almost and can fill in lattice structure, reduce inner space access
Caused heat bridge.
(10) colloidal sol is prepared and is impregnated: preparing SiOC precursor colloidal sol, the light structures for being laid with fiber blanket are placed in very
In empty container, vacuum impregnation 4h under the conditions of vacuum degree < 100Pa；
(11) aging: 48 hours are stood in a sealed container, gelation makes network skeleton continue to grow up；
(12) supercritical drying: cotton light structures are completely spread to aging and carry out supercritical drying, obtain organic aerogel
Skeleton；
(13) high-temperature process: 800 DEG C of high-temperature process 1h under inert atmosphere protection, organic aerogel are converted into SiOC airsetting
Glue composite material, it is final to obtain SiC/SiC ceramic matric composite light sandwich structure.
Gained SiC/SiC ceramic matric composite light sandwich structure size 200mm × 200mm ×
40mm, combined density 0.72g/cm3, surface density 28.8kg/m2。
Embodiment 5
A kind of solar heat protection/heat-insulated/carrying integrated ceramic base composite material light sandwich structure, the light sandwich structure is with C/
Lighting lattice structure of the SiC ceramic based composites as solar heat protection or carrying, with carbon aerogel composite material for heat-insulated sandwich
Layer.
Anti-/heat-insulated/carrying integration C/SiC ceramic matric composite light sandwich structure of the present embodiment passes through following step
Suddenly it is prepared:
(1) mold selects: selecting combined type composite material lattice structure fibre preforms forming die mould in embodiment 1；
(2) molding of fiber preform: being cut into required size for carbon cloth, is laid with corrugated plating in female mold surfaces profiling
10 layers of twill carbon cloth of support construction, interlayer suture, formpiston molding, bolt fastening obtain corrugated plating fiber preform；Paving
If 10 layers of plain weave carbon fiber cloth of panel, interlayer suture obtains panel fiber preform；
(3) it densifies: the fiber preform taken shape on mold is subjected to CVD SiC base in cvd furnace
C/SiC ceramic matric composite corrugated plating blank and panel blank is made in body, time 300h；
(4) it processes: numerical control processing being carried out to C/SiC ceramic matric composite corrugated plating blank and panel blank, is obtained
The corrugated plating and panel of size and joint face precision needed for obtaining, and prefabricated connecting hole；
(5) it connects: being attached using C/SiC screw rod, obtain C/SiC ceramic matric composite light structures assembly parts；
The connection type can obtain smooth joint face, while being threadedly coupled high reliablity and connecting in pin, have superior anti-
Vibration and joint face tensile property.
(6) it densifies afterwards: C/SiC ceramic matric composite light structures assembly parts is subjected to chemical gaseous phase in cvd furnace
SiC matrix is deposited, C/SiC ceramic matric composite light structures are made in time 280h；The process can fill connecting portion
Bonding strength and connection reliability are improved in gap；
(7) it spreads cotton: being laid with viscose base carbon fibre oxidization fiber felt, fiber volume fraction in the core gap of light structures
4%；Aerogel composite is prepared separately to cut out again and be filled into during lattice structure, inevitable that a part of space
It can not fill, and the in situ all gaps that spreads cotton and subsequent gelation almost and can fill in lattice structure, it reduces internal empty
Between heat bridge caused by access.
(8) colloidal sol is prepared and is impregnated: preparing carbon aerogels precursor solution, the light structures for being laid with fiber blanket are placed in
In vacuum tank, vacuum impregnation 4h under the conditions of vacuum degree < 100Pa；
(9) aging: 48 hours are stood in a sealed container, gelation makes network skeleton continue to grow up；
(10) supercritical drying: cotton light structures are completely spread to aging and carry out supercritical drying, obtain organic aerogel
Skeleton；
(11) high-temperature process: 800 DEG C of high-temperature process 1h, organic aerogel are converted into carbon aerogels under inert atmosphere protection
Composite material, it is final to obtain C/SiC ceramic matric composite light sandwich structure.C/SiC ceramic matric composite light sandwich
Structure size 200mm × 200mm × 25mm, combined density 0.89g/cm3, surface density 22.2kg/m2。
Embodiment 6
One kind preventing/heat-insulated/carrying integration quartz/quartz ceramic-base composite material light sandwich structure, the light sandwich
Structure is using quartz/quartz composite material as the lighting lattice structure of solar heat protection or carrying, with SiO2Aerogel composite is
Heat-insulated laminboard layer.
Anti-/heat-insulated/carrying integration quartz/quartz ceramic-base composite material light sandwich structure of the present embodiment by with
Lower step is prepared:
(1) mold selects: selecting the composite material dot matrix structure fiber preform integrally forming mould in embodiment 2；It should
Mold can be realized the integrally formed of dot matrix fiber preform, realizes interlayer suture and whole suture, improves the whole of lattice structure
Body bearing capacity；
(2) molding of fiber preform: quartz fiber cloth is cut into required size, according to production as described in example 2
Process and method are laid with corrugated plating and each 15 layers of quartz fiber cloth of lower panel, to corrugated plating and lower panel contact portion interlayer seam
It closes.Then interlayer seam multiplex card chamfered portion is laid with 15 layers of quartz fiber cloth of top panel in molding die, to corrugated plating and
The suture of top panel contact portion interlayer；
(3) vacuum impregnation: being 40wt.% by the fiber preform vacuum impregnation dioxide-containing silica taken shape on mold
Silica solution, vacuum degree < 200Pa, time 12h；
(4) drying and dewatering: by the precast body after dipping in 120 DEG C of crosslinking curing 12h；
(5) high-temperature process: the precast body green body progress high-temperature heat treatment after drying and dewatering, 800 DEG C of temperature, time 1h；
(6) it densifies: vacuum impregnation-crosslinking curing-Pintsch process technique 3 times of repetition step S3~S5, obtained quartz/
Quartz ceramic-base composite material lattice structure blank；
(7) it processes: numerical control processing is carried out to quartz/quartz ceramic matric composite lattice structure blank；
(8) it densifies afterwards: repeating vacuum impregnation-crosslinking curing-Pintsch process technique 3 times of S3~S5, quartz/stone is made
English ceramic matric composite light dot matrix structure；
(9) it spreads cotton: being laid with quartz fibre blanket, fiber volume fraction 4% in the core gap of light structures；Aeroge
Composite material is prepared separately to cut out again and be filled into during lattice structure, inevitable that a part of space can not fill,
And the in situ all gaps that spreads cotton and subsequent gelation almost and can fill in lattice structure, it reduces inner space access and causes
Heat bridge.
(10) colloidal sol is prepared and is impregnated: being prepared teos solution and solation, will be laid with the lightweight knot of fiber blanket
It sets up in vacuum tank, vacuum impregnation 4h under the conditions of vacuum degree < 100Pa；
(11) aging: 48 hours are stood in a sealed container, gelation makes network skeleton continue to grow up；
(12) supercritical drying: cotton light structures are completely spread to aging and carry out supercritical drying, obtain SiO2Aeroge
Composite material, it is final to obtain quartz/quartz ceramic matric composite light sandwich structure.
Gained quartz/quartz ceramic matric composite light sandwich structure size 200mm × 200mm × 25mm, synthesis are close
Spend 0.93g/cm3, surface density 23.4kg/m2。
Embodiment 7
One kind preventing/heat-insulated/carrying integrated A l2O3/Al2O3Ceramic matric composite light sandwich structure, the light sandwich
Structure is with Al2O3/Al2O3Lighting lattice structure of the composite material as solar heat protection or carrying, with Al2O3Aerogel composite is
Heat-insulated laminboard layer.
Anti-/heat-insulated/carrying integrated A l of the present embodiment2O3/Al2O3Ceramic matric composite light sandwich structure passes through
Following steps are prepared:
(1) mold is used or processed: the composite material dot matrix structure fiber preform in selection or process embodiment 2 is whole
Molding die；The mold can be realized the integrally formed of dot matrix fiber preform, realizes interlayer suture and whole suture, improves point
The integrated carrying ability of battle array structure；
(2) molding of fiber preform: by Al2O3Fiber cloth is cut into required size, according to reality in integrally forming mould
Manufacturing process described in example is applied, corrugated plating and each 10 layers of quartz fiber cloth of lower panel are laid with, to corrugated plating and lower panel contact portion
It is sutured between layering.Then interlayer seam multiplex card chamfered portion is laid with 10 layers of Al of top panel in molding die2O3Fiber cloth is right
Corrugated plating and the suture of top panel contact portion interlayer；
(3) vacuum impregnation: being 40wt.%'s by the fiber preform vacuum impregnation alumina content taken shape on mold
Aluminum sol, vacuum degree < 200Pa, time 12h；
(4) drying and dewatering: by the precast body after dipping in 120 DEG C of crosslinking curing 12h；
(5) high-temperature process: the precast body green body progress high-temperature heat treatment after drying and dewatering, 1000 DEG C of temperature, time 1h；
(6) it densifies: repeating vacuum impregnation-crosslinking curing-Pintsch process technique 3 times of step S3~S5, Al is made2O3/
Al2O3Ceramic matric composite lattice structure blank；
(7) it processes: to Al2O3/Al2O3Ceramic matric composite lattice structure blank carries out numerical control processing；
(8) it densifies afterwards: repeating vacuum impregnation-crosslinking curing-Pintsch process technique 3 times of S3~S5, Al is made2O3/
Al2O3Ceramic matric composite light dot matrix structure；
(9) it spreads cotton: being laid with Al in the core gap of light dot matrix structure2O3Fiber blanket, fiber volume fraction 4%；Gas
Gel complex material is prepared separately to cut out again and be filled into during lattice structure, inevitable that a part of space can not be filled out
It fills, and the in situ all gaps that spreads cotton and subsequent gelation almost and can fill in lattice structure, reduce inner space access
Caused heat bridge.
(10) colloidal sol is prepared and is impregnated: Aluminum sol is prepared, the light structures for being laid with fiber blanket are placed in vacuum tank,
Vacuum impregnation 4h under the conditions of vacuum degree < 100Pa；
(11) aging: 48 hours are stood in a sealed container, gelation makes network skeleton continue to grow up；
(12) supercritical drying: cotton light structures are completely spread to aging and carry out supercritical drying, obtain Al2O3Aeroge
Composite material finally obtains Al2O3/Al2O3Ceramic matric composite light sandwich structure.
Al2O3/Al2O3Ceramic matric composite light sandwich structure size 200mm × 200mm × 20mm, combined density
0.92g/cm3, surface density 18.4kg/m2。
Embodiment 8
One kind preventing/heat-insulated/carrying integrated A l2O3/ mullite ceramic base composite material light sandwich structure, lightweight folder
Cored structure is with Al2O3The lighting lattice structure of/mullite composite material as solar heat protection or carrying, with SiO2-Al2O3Aeroge
Composite material is heat-insulated laminboard layer.
Anti-/heat-insulated/carrying integrated A l of the present embodiment2O3/ mullite ceramic base composite material light sandwich structure passes through
Following steps are prepared:
(1) mold is used or processed: the composite material dot matrix structure fiber preform in selection or process embodiment 2 is whole
Molding die；The mold can be realized the integrally formed of dot matrix fiber preform, realizes interlayer suture and whole suture, improves point
The integrated carrying ability of battle array structure；
(2) molding of fiber preform: by Al2O3Fiber cloth is cut into required size, according to reality in integrally forming mould
It applies manufacturing process described in example 2 and is laid with corrugated plating and each 10 layers of quartz fiber cloth of lower panel, to corrugated plating and lower panel contact portion
It is sutured between layering, then interlayer seam multiplex card chamfered portion, 10 layers of Al of top panel is laid in molding die2O3Fiber cloth is right
Corrugated plating and the suture of top panel contact portion interlayer；
(3) vacuum impregnation: by the fiber preform vacuum impregnation aluminium oxide and chlorine dioxide content that take shape on mold and
For the aluminium silicon binary colloidal sol of 40wt.%, vacuum degree < 200Pa, time 12h；
(4) drying and dewatering: by the precast body after dipping in 120 DEG C of crosslinking curing 12h；
(5) high-temperature process: the precast body green body progress high-temperature heat treatment after drying and dewatering, 1000 DEG C of temperature, time 1h；
(6) it densifies: repeating vacuum impregnation-crosslinking curing-Pintsch process technique 3 times of step S3~S5, Al is made2O3/
Mullite ceramic base composite material dot matrix structure blank；
(7) it processes: to Al2O3/ mullite ceramic base composite material dot matrix structure blank carries out numerical control processing；
(8) it densifies afterwards: repeating vacuum impregnation-crosslinking curing-Pintsch process technique 3 times of S3~S5, Al is made2O3/ not
Carry out feldspar base composite material light lattice structure；
(9) it spreads cotton: being laid with mullite fiber blanket, fiber volume fraction 4% in the core gap of light structures；Gas
Gel complex material is prepared separately to cut out again and be filled into during lattice structure, inevitable that a part of space can not be filled out
It fills, and the in situ all gaps that spreads cotton and subsequent gelation almost and can fill in lattice structure, reduce inner space access
Caused heat bridge.
(10) colloidal sol is prepared and is impregnated: preparing aluminium silicon binary colloidal sol, the light structures for being laid with fiber blanket are placed in vacuum
In container, vacuum impregnation 4h under the conditions of vacuum degree < 100Pa；
(11) aging: 48 hours are stood in a sealed container, gelation makes network skeleton continue to grow up；
(12) supercritical drying: cotton light structures are completely spread to aging and carry out supercritical drying, obtain SiO2-Al2O3
Aerogel composite finally obtains Al2O3/ mullite ceramic base composite material light sandwich structure.
Gained Al2O3/ mullite ceramic base composite material light sandwich structure size 200mm × 200mm × 40mm, it is comprehensive
Density 0.66g/cm3, surface density 26.4kg/m2。
Various embodiments of the present invention are described above, above description is exemplary, and non-exclusive, and
It is not limited to disclosed each embodiment.Without departing from the scope and spirit of illustrated each embodiment, for this skill
Many modifications and changes are obvious for the those of ordinary skill in art field.Therefore, protection scope of the present invention is answered
This is subject to the protection scope in claims.
Claims (10)
1. a kind of solar heat protection/heat-insulated/carrying integrated ceramic base light sandwich structure, which is characterized in that its structure include top panel,
Lower panel, corrugated plating and sandwich of layers；The top panel, lower panel and corrugated plating are each independently selected from C/SiC, quartz/stone
English, Al2O3/ mullite, Al2O3/Al2O3, one of SiC/SiC or a variety of ceramic matric composite plates；The corrugated plating
It connects top panel and lower panel forms lattice structure, the lighting structure as solar heat protection or carrying；The sandwich of layers is filled in institute
The gap between corrugated plating and top panel and lower panel is stated, the laminboard layer is selected from SiO2、Al2O3、SiOC、ZrO2In carbon
One or more aerogel composites, and alumina silicate, the mullite for thering is volume fraction to account for 4% in aerogel composite
Or one of high silica fiber blanket or a variety of as reinforcement.
2. solar heat protection as described in claim 1/heat-insulated/carrying integrated ceramic base light sandwich structure, which is characterized in that described
Corrugated plating is multiple continuous 30~60 ° of isosceles trapezoids, and the upper lower horizontal plane of isosceles trapezoid is respectively at the top panel under
Panel connection；The thickness of the top panel, lower panel and corrugated plating is each independently within the scope of 2~3mm.
3. solar heat protection as described in claim 1/heat-insulated/carrying integrated ceramic base light sandwich structure, which is characterized in that described
The density of laminboard layer is 0.3~0.45g/cm3；The solar heat protection/heat-insulated/carrying integrated ceramic base light sandwich structure density
For 0.66~1.0g/cm3。
4. solar heat protection/heat-insulated/carrying integrated ceramic base light sandwich structure as described in any claim in claim 1-3
Preparation method, which comprises the following steps:
S1, selection or processing mold: using composite material dot matrix structure fiber preform combined type molding die and/or compound
Material dot matrix structural fibers precast body integrally forming mould；
The molding of S2, fiber preform: being cut into required size for fiber cloth, in composite material dot matrix structure fiber preform group
Box-like molding die surface profiling is laid with 10~15 layers of fiber cloth and then carries out interlayer suture, obtains corrugated plating fibre preforms respectively
Body and panel fiber preform；And/or composite material dot matrix structure fiber preform integrally make in molding die be laid with 10~
Then 15 layers of fiber cloth carry out interlayer suture, directly obtain corrugated plating lattice structure precast body；
S3, densification: true using precursor solution for the corrugated plating fiber preform and panel fiber preform obtained respectively
Empty dipping-crosslinking curing-Pintsch process process several times or colloidal sol vacuum impregnation-drying and dewatering-high-temperature processing technology for several times, or
Chemical vapor deposition process hundreds of hours obtain corrugated plating green body and panel green body；And/or for directly obtaining corrugated plating point
Battle array structure precast body, using precursor solution vacuum impregnation-crosslinking curing-Pintsch process process several times or colloidal sol vacuum impregnation-
For several times or chemical vapor deposition process hundreds of hours, ceramic matric composite corrugated plating is made in drying and dewatering-high-temperature processing technology
Lattice structure green body；
S4, processing: for corrugated plating green body and panel green body, carrying out numerical control processing, size needed for obtaining and joint face precision
Corrugated plating and panel, and prefabricated connecting hole are connected using high temperature conjunction part, obtain Combined ceramic based composites corrugated plating point
Battle array structure；And/or for ceramic matric composite corrugated plating lattice structure green body, the processing such as trimming, surface plain grinding is carried out, is obtained
Monoblock type ceramic matric composite corrugated plating lattice structure；
S5, rear densification: it makes pottery for the step S4 Combined ceramic based composites corrugated plating lattice structure obtained or monoblock type
Porcelain based composites corrugated plating lattice structure uses precursor solution vacuum impregnation-crosslinking curing-Pintsch process technique or colloidal sol
Vacuum impregnation-drying and dewatering-high-temperature processing technology is for several times or chemical vapor deposition process hundreds of hours, acquisition ceramic base are compound
Material corrugated plating lattice structure；
S6, laminboard layer preparation: by including supercritical drying or foaming but being not limited to the supercritical drying or foaming
Method the gap of the resulting ceramic matric composite corrugated plating lattice structure of step S5 be prepared in situ aerogel composite every
Hot laminboard layer is prevented/heat-insulated/carrying integrated ceramic base composite material light sandwich structure.
5. solar heat protection as claimed in claim 4/heat-insulated/carrying integrated ceramic base light sandwich structure preparation method, special
Sign is, the step S6 specifically includes the following steps:
S61, paving cotton: fiber blanket reinforcement is laid at the gap original position of ceramic matric composite corrugated plating lattice structure；
S62, colloidal sol are prepared and dipping: preparing colloidal sol, the colloidal sol is SiO2、Al2O3、SiOC、ZrO2With one of carbon or more
Kind, then the ceramic matric composite corrugated plating lattice structure for being laid with fiber blanket reinforcement is placed in vacuum tank, true
Colloidal sol vacuum impregnation is carried out under the conditions of reciprocal of duty cycle < 100Pa；
S63, aging: 48 hours are stood in a sealed container, gelation makes network skeleton continue to grow up；
S64, supercritical drying: aging is completely laid with fiber blanket reinforcement corrugated plating lattice structure be transferred to it is overcritical
Drying equipment carries out supercritical drying, is prevented/heat-insulated/carrying integrated ceramic base composite material light sandwich structure.
6. solar heat protection as claimed in claim 5/heat-insulated/carrying integrated ceramic base light sandwich structure preparation method, special
Sign is,
Fiber cloth in the step S2 is in carbon cloth, SiC fiber cloth, quartz fiber cloth and alumina fibre cloth
It is one or more；The fiber being laid with for composite material dot matrix structure fiber preform combined type molding die, ripple plate surface
Cloth uses twill or satin, and the fiber cloth that panel surface is laid with uses plain weave or twill；For composite dot-matrix knot
The fiber cloth of structure fiber preform integrally forming mould, laying selects one of plain weave, twill or satin or a variety of.
7. solar heat protection as claimed in claim 5/heat-insulated/carrying integrated ceramic base light sandwich structure preparation method, special
Sign is that the precursor solution that precursor solution vacuum impregnation uses in the step S3 is the Polycarbosilane-two of weight ratio 1:1
Toluene solution or weight ratio 1:1 Polycarbosilane-divinyl benzole soln；Colloidal sol in colloidal sol vacuum impregnation using silica solution and/
Or Aluminum sol, wherein the mass concentration of silica and/or aluminium oxide is more than 40% in silica solution and/or Aluminum sol；Vaccum Permeating
The 12 hours time of stain；Being each independently for several times 3~8 times in the step S3；Hundreds of hours in the S3 step are
300~400h.
8. solar heat protection as claimed in claim 5/heat-insulated/carrying integrated ceramic base light sandwich structure preparation method, special
Sign is that the high temperature conjunction part of the step S4 is C/SiC screw rod or pin；For several times each independently 7 in the step S5
~12 times.
9. solar heat protection as claimed in claim 5/heat-insulated/carrying integrated ceramic base light sandwich structure preparation method, special
Sign is that the composite material dot matrix structure fiber preform integrally forming mould in the step S1 includes: direction controlling sliding rail
Plate (1), outer plate (3), clip plate (4), fixed block (5), trapezoidal cushion block (6)；The direction controlling sliding rail plate (1) is used for
Ripple struction, including the identical plate of 2 block layouts are cooperatively formed with trapezoidal cushion block (6), same level along its length on plate
N+1 handstand isosceles trapezoid through-hole and N number of upright isosceles trapezoid through-hole are provided on line, N is positive integer, the upright isosceles ladder
Shape through-hole and the arrangement of handstand isosceles trapezoid through-hole staggered relative；The quadrangle of two pieces of plates is correspondingly arranged on sliding rail plate connecting hole
(2), for making two pieces of plates connect and fix at a distance of predetermined size by sliding rail column；The trapezoidal cushion block (6) is isosceles trapezoid
The long strip block of cross section, for filling and connecting handstand isosceles trapezoid through-hole on two Block direction control sliding rail plate and just
Vertical isosceles trapezoid through-hole；The outer dimension of the fixed block (5) and trapezoidal cushion block (6) unanimously, for being placed in direction controlling sliding rail
On plate in the outermost handstand isosceles trapezoid through-hole in both ends, fixed block (5) be equipped with fixed block connecting hole with direction controlling
Sliding rail plate is fixedly connected, for the fixed corrugated plating fiber cloth being laid with；The trapezoidal cushion block (6) and fixed block (5) are compound
As the hollow structure supporting block in lattice structure, i.e. graphite core mould, material when material dot matrix structural fibers are prefabricated body formed
For graphite；The outer plate (3) includes the hollow frame that two frame corresponding positions are equipped with frame connecting hole (9), for compressing
The fixed block (5) and trapezoidal cushion block (6) between (1) two piece of plate of the direction controlling sliding rail plate are connected, to form composite wood
The ripple struction of material；The clip plate (4) includes two pieces of plates, is respectively placed in the inside of (3) two frames of outer plate and passes through
Pressing plate connecting hole (8) is fixedly connected with the frame of outer plate (3), is arranged for compressing at (1) two piece of direction controlling sliding rail plate
Composite material face between plate is used to be laid with composite material to form composite material face structure；The handstand isosceles
The long bottom edge of trapezoidal hole connects square through hole, and square through hole is communicated as one with handstand isosceles trapezoid through-hole, is convenient for fibre preforms
The insertion of trapezoidal cushion block (6) and pressing mold during body formed.
10. solar heat protection as claimed in claim 5/heat-insulated/carrying integrated ceramic base light sandwich structure preparation method, special
Sign is, the composite material dot matrix structure fiber preform combined type molding die in the step S1 include corrugated plating formpiston,
Corrugated plating former and panel mould；The corrugated plating formpiston, corrugated plating former and panel mould are graphite material；The corrugated plating sun
Mould is the square plate that surface intermediate parallel is arranged with the identical N isosceles trapezoid protrusion of height, the N isosceles trapezoid protrusion
Between formed N-1 groove；The corrugated plating cavity dimension is identical as corrugated plating formpiston, corresponding among surface to be arranged with N+1 item height
Spend identical isosceles trapezoid protrusion, the outside of two isosceles trapezoid protrusions of outermost is each provided with surely high block, the fixed high block and
Half isosceles trapezoid bottom surface is collectively formed in the outermost protrusion seamless connection, and it is convex that fixed high block overhead height is higher than the isosceles trapezoid
The height risen forms N number of groove between N+1 isosceles trapezoid protrusion；Outermost two is removed in the corrugated plating female mold surfaces
The size of a remaining outer protrusion of protrusion is matched with the size of N-1 groove in corrugated plating male mold surfaces, accordingly, corrugated plating formpiston
The size of N number of protrusion is matched with the size of N number of groove in corrugated plating female mold surfaces on surface；The corrugated plating formpiston and corrugated plating
The surrounding corresponding position of former has location hole, for connecting and compressing corrugated plating formpiston and corrugated plating former；Wherein N be greater than
Integer equal to 2；The panel mould is upper and lower two pieces of plates.
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