CN106083122A - A kind of abnormity flange closes load frame integral forming method - Google Patents

A kind of abnormity flange closes load frame integral forming method Download PDF

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CN106083122A
CN106083122A CN201610402384.9A CN201610402384A CN106083122A CN 106083122 A CN106083122 A CN 106083122A CN 201610402384 A CN201610402384 A CN 201610402384A CN 106083122 A CN106083122 A CN 106083122A
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carbon
load frame
flange
temperature
carbon cloth
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CN106083122B (en
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张中伟
冯志海
张震
王俊山
房金铭
王捷冰
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China Academy of Launch Vehicle Technology CALT
Aerospace Research Institute of Materials and Processing Technology
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China Academy of Launch Vehicle Technology CALT
Aerospace Research Institute of Materials and Processing Technology
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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
    • 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
    • C04B35/83—Carbon fibres in a carbon matrix
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
    • C04B2235/74—Physical characteristics
    • C04B2235/77—Density
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
    • C04B2235/96—Properties of ceramic products, e.g. mechanical properties such as strength, toughness, wear resistance

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  • Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
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  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Composite Materials (AREA)
  • Inorganic Chemistry (AREA)
  • Ceramic Products (AREA)
  • Inorganic Fibers (AREA)
  • Woven Fabrics (AREA)

Abstract

A kind of abnormity flange closes load frame integral forming method, belongs to heat structure technology field of carbon/carbon compound material manufacture.The method is from the abnormity of load frame, band flange, the architectural feature of near closed hollow ring, in view of parts load characteristic, use based on cloth lamination structure, substep stitching, near-net-shape method, obtain the carbon fiber load frame fabric of integral weaving, use phase autoclave thickening technology technology and split-type graphite frock application technology, it is achieved the Deformation control of overall load frame and homogenous densification.By technology controlling and process and parameter optimization, improve the mechanical property of material, final density of material 1.85～1.95g/cm3, hot strength 200～260MPa, compression and bending strength 160～200MPa, interlaminar shear strength 15～20MPa.On the basis of ensureing material strong mechanical performance, it is achieved that abnormity, flange, closing load frame entirety dead size molding, substantially increase the carrying usefulness of parts.

Description

A kind of abnormity flange closes load frame integral forming method
Technical field
The present invention relates to a kind of abnormity flange and close load frame integral forming method, belong to heat structure carbon/carbon compound material Manufacturing technology field.
Background technology
Carbon/carbon compound material is with the high-temperature mechanical property of its excellence and thermophysical property, if height is than strong, Gao Bimo, high warm Lead, low linear expansion coefficient, designability are strong, heat shock resistance etc., always advanced country's strategic missile bullet such as termination, jet pipe, One of crucial of paramount importance material solution of heat shield member such as nacelle, control flaps.But, along with sending out of near space technology Exhibition, proposes urgent needs to large scale primary load bearing thermal structure material, it is desirable to material is double to load/solar heat protection by single solar heat protection function Weigh function, expanded to complex appearance by simple profile, and there is the combination properties such as the elevated temperature strength of excellence, rigidity, antioxidation, and Can realize large scale, complicated shape material engineering can manufacture.It it is the allusion quotation of current heat structure cabin section with frame/beam for primary load bearing skeleton Type version.The load distribution that such load frame is longitudinally sew with long stitches between beam in not only acting as cabin section and the work maintaining eyelid covering aerodynamic configuration With, also need to be connected with internal air-cooled structure, carry many critical equipment equipment；The more important thing is its also need to undertake cabin section inter-stage, Full load transmission function between bullet and vehicle.It is relatively big that heat structure load connects frame size, and structure is complicated, there is positive negative cruvature and becomes The feature such as change, band flange, near closed hollow ring.This kind of load frame overall performance has become the key factor affecting heat structure cabin section performance One of, current this kind of load frame many employings split mentality of designing, i.e. separate Compound Machining assembling by each unit part and realize The manufacture manufacture of frame.The manufacture of split frame has bigger shortcoming: (one) load frame is formed by connecting by multiple unit pieces, makes Weak link must be connected to become；(2) the integrated meeting of multiple-unit part causes fitting surface position fiber discontinuous, reduces carrying usefulness； (3) the split manufacture of multiple-unit part can be greatly improved cost, and over all Integration makes the cycle elongated.
Summary of the invention
The technology of the present invention solves problem: overcome the deficiencies in the prior art, it is provided that a kind of abnormity flange closes load frame Integral forming method, fitting surface is few, and more continuously, completely, load-carrying properties are more preferable, greatly reduce connector and unit simultaneously for fiber The quantity of part, reduces cost and cycle.
The technical solution of the present invention is: a kind of abnormity flange closes load frame integral forming method, and it includes following Step:
1) select T300-1K or T300-3K polyacrylonitrile-based carbon fibre, be woven into the carbon cloth of satin weave, plain weave or twill, compile It is 0 ° with warp yarn direction during knitting, rotates counterclockwise and form+45 ° respectively, 90 ° and-45 °, subsequently carbon cloth is pressed load It is standby that frame-type face expansion largest enveloping size is cut into carbon cloth block；
2) press load frame three-dimensional mathematical model and make mould, for realizing lay and the compression of carbon cloth；
3) by step 1) in carbon cloth block according to the ply stacking-sequence being pre-designed in step 2) mould on carry out lay, paving Putting datum level is curved surface flange or plane, carries out the carbon cloth after lay subsequently compressing and sews up, obtains fabric intermediate；
4) by step 3) in fabric intermediate carry out flange process, turn down out planar section or curved surface flange, to carbon Cloth is cut out processing, then compresses it and sew up, it is thus achieved that abnormity flange closes the integral fabric of load frame；
5) close load frame integral fabric three-dimensional dimension making material by abnormity flange is the frock of graphite, and this mould uses Split-type designs；
6) by step 4) the load frame integral fabric that obtains is positioned over step 5) graphite frock on, carry out heat treatment, go Except the prefabricated carbon fiber body forming band graphite frock after the slurry agent of fiber surface；
7) by the prefabricated carbon fiber body impregnating pitch of band graphite frock, then carrying out carbonization treatment, iterative cycles forms one Determine the carbon/carbon of density at goods；
8) by step 7) carbon/carbon carry out high-temperature heat treatment at goods；
9) by step 8) process after carbon/carbon carry out Colophonium high-pressure impregnation-carbonization treatment, impregnation pressure 50MPa at goods Above；
10) by step 9) in carbon/carbon carry out high-temperature heat treatment at goods；
11) step 9 is repeated)～step 10) carry out repeatedly density, until density of material is more than or equal to 1.85g/cm3Above, I.e. prepare abnormity flange and close carbon/carbon entirety load frame.
Described step 3) in, the ply stacking-sequence being pre-designed is 0 ° /+45 °/90 °/-45 °, 0 ° /+45 °/90 °/-45 °/ 0°、0°/90°/+45°/0°/90°/-45°、0°/+45°/90°/-45°/0°/-45°/90°/+45°/0°、0°/90°/+45°/ 0 °/90 °/-45 °/0 °/90 °, 0 °/90 ° /+45 °/0 °/0 °/-45 °/0 °/90 ° or 0 °/90 ° /+45 °/-45 °/0 °/90 °, carbon Cloth introduces fiber, fiber volume fraction 45%～55%, stitch pitch 4 according to the ply stacking-sequence being pre-designed in 45 ° of directions ～10mm.
Described step 4) in, the mode being cut out carbon cloth processing is as follows；
When carbon cloth by planar section to curvature portion flange time, carbon cloth is carried out cutting, the breach stayed after cutting is entered Row carbon cloth reinforcement solutions；
When carbon cloth by curved face part A to planar section flange time, directly by unnecessary carbon cloth cutting.
Described step 6) in heat-treating methods be: with the speed of 200～500 DEG C/h from room temperature to 1800～2300 DEG C, freely lower the temperature after insulation 2～3h.
Described step 7) in, by the implementation of the prefabricated carbon fiber body impregnating pitch of band graphite frock for for: dipping temperature Degree is 160～260 DEG C, and impregnation pressure is 0.1～3MPa, and the dwell time is 5～8h；The implementation of carbonization treatment is: with 50 ～the speed of 100 DEG C/h is from room temperature to 300 DEG C, then with the ramp of 5～50 DEG C/h to 650 DEG C, finally with 10～ The ramp of 80 DEG C/h, to after 850 DEG C, is incubated 2～5h, the most freely lowers the temperature.
Step 8) or step 10) in, the method for high-temperature heat treatment is: with the speed of 50～200 DEG C/h from room temperature to 800 DEG C, then it is warming up to 1200 DEG C with the speed of 10～50 DEG C/h from 800 DEG C, finally with the speed of 30～100 DEG C/h from 1200 DEG C it is warming up to 1800～2300 DEG C, after insulation 2～5h, carries out cooling process；When described cooling processes, rate of temperature fall is less than 100 ～200 DEG C/h, until temperature is down to 900 DEG C, freely lower the temperature for less than 900 DEG C.
Described step 9) process conditions of medium pitch high-pressure impregnation-carbonization treatment are: impregnation pressure 60～100MPa, carbonization Temperature 700～900 DEG C, the time is 15～20h.
Compared with prior art, there is advantages that
(1) the present invention is directed to abnormity flange load frame, it is proposed that one is sewed up entirety become based on cloth lamination structure, substep Type method, it is possible to achieve load frame near-net-shape, compared with the manufacture with split frame, the overall load frame that the present invention relates to is only Needing overall size processing in a small amount, fiber more continuously, completely, can give full play to the enhancing advantage of fiber, and load-carrying properties are more preferable.
(2) present invention uses the method for integral weaving to manufacture load frame, for split frame, it is no longer necessary to Duo Gedan Element connects, it is to avoid the vulnerability of split frame junction, improves the structural reliability of overall load frame, reduces cost, Shorten the manufacturing cycle simultaneously.
(3) present invention increases by 45 ° of direction fibers in fabric ply stacking-sequence, relative to only 0 ° and 90 ° of direction fibers and Speech, is conducive to the bearing capacity improving carbon/carbon compound material in all directions, it is ensured that the balance of mechanical property and coupling.
(4) present invention is during weaving textile, needs the breach after carbon cloth cutting is carried out reinforcement solutions, compensation fibre The mechanical properties decrease discontinuously caused.
(5) present invention uses split-type graphite frock, and the dimensional accuracy of load frame is effectively ensured while solving stress, Efficiently solve overall load frame to deform in compounding process the problem even ftractureed.
(6) present invention uses Colophonium phase autoclave thickening technology to be combined, and has played the advantage that Colophonium technology stress is little, Utilize the high-pressure impregnation of Colophonium, carbonation process can realize the high-compactness of load frame and the uniformity of density simultaneously.
Accompanying drawing explanation
Fig. 1 is the inventive method flow chart；
Fig. 2 is that a kind of abnormity flange closes load frame schematic diagram, and wherein (a) is front view, and (b) is sectional view；
Fig. 3 be the load frame of band graphite frock at goods schematic diagram, wherein (a) is front view, and (b) is sectional view.
Detailed description of the invention
Below in conjunction with embodiment, the invention will be further described.
The present invention is from the abnormity of load frame, band flange, the architectural feature of near closed hollow ring, it is contemplated that parts load is special Property, propose a kind of based on cloth lamination structure, substep stitching, near-net-shape method, it is thus achieved that the carbon fiber of integral weaving holds Power frame fabric.Use phase autoclave thickening technology technology and split-type graphite frock application technology, it is achieved the change of overall load frame Shape controls and homogenous densification.
As it is shown in figure 1, the present invention's concretely comprises the following steps:
1) select domestic T300-1K or T300-3K polyacrylonitrile (PAN) base carbon fibre, be woven into carbon cloth (satin weave, plain weave Or twill), it is 0 ° with warp yarn direction, rotates counterclockwise and form+45 ° respectively, 90 ° and-45 °, subsequently carbon cloth is pressed load It is standby that frame-type face expansion largest enveloping size is cut into carbon cloth block；
2) press load frame three-dimensional digital-to-analogue and make mould, it is achieved the lay of carbon cloth and pressuring action；
3) by step 1) in carbon cloth block according to design ply stacking-sequence carry out lay at mould, lay datum level can be (assuming that load frame is structure shown in Fig. 2, wherein (a) is load frame front view, and (b) is load frame section view for curved surface flange or plane Figure, then lay datum level can be curved surface flange A or plane B), carry out the carbon cloth after lay subsequently compressing sewing up, knitted Thing intermediate；
Carbon cloth is according to 0/+45/90/-45,0/+45/90/-45/0,0/90/+45/0/90/-45,0/+45/90/-45/ 0/-45/90/+45/0、0/90/+45/0/90/-45/0/90、0/90/+45/0/0/-45/0/90、0/90/+45/-45/0/90 Deng ply stacking-sequence in 45 ° of directions introducing fibers, fiber volume fraction 45%～55%, stitch pitch 4～10mm.
4) by step 3) in fabric intermediate carry out flange process, turn down out planar section or curved surface flange (with Fig. 2 As a example by shown structure, then turn down out planar section B or curved surface flange A), by rationally cutting out carbon cloth, then it is compressed And sew up, it is thus achieved that abnormity flange closes the integral fabric of frame.
The mode being cut out carbon cloth processing is as follows:
When carbon cloth by planar section to curvature portion flange time, carbon cloth is carried out cutting, the breach stayed after cutting is entered Row carbon cloth reinforcement solutions；
When carbon cloth by curved face part A to planar section flange time, directly by unnecessary carbon cloth cutting.
5) press load frame fabric three-dimensional size and make frock, material selection graphite, use split-type design, solve stress Ensure the dimensional accuracy of frame simultaneously, if load mount structure as in figure 2 it is shown, the graphite frock made is as it is shown on figure 3, wherein scheme In 3 (a) be the load frame of band graphite frock at goods front view, (b) is sectional view.
6) by step 4) in load frame fabric is anti-is placed in step 5) in graphite frock, carry out uniform temperature heat treatment, i.e. Freely lower the temperature after room temperature to 1800～2300 DEG C, insulation 2～3h with the speed of 200～500 DEG C/h, remove fiber surface Prefabricated carbon fiber body is formed after sizing agent；
7) by step 6) in the precast body impregnating pitch under a certain pressure of band graphite frock, dipping temperature be 160～ 260 DEG C, impregnation pressure is 0.1～3MPa, and the dwell time is 5～8h；Then carbonization treatment is carried out, with the speed of 50～100 DEG C/h Rate is from room temperature to 300 DEG C, then with the ramp of 5～50 DEG C/h to 650 DEG C, finally with the speed liter of 10～80 DEG C/h After warm to 850 DEG C, it is incubated 2～5h, the most freely lowers the temperature.Iterative cycles, forms the carbon/carbon of certain density at goods；
8) by step 7) in the carbon/carbon of certain density carry out high-temperature heat treatment at goods, control heat treatment temperature, simultaneously Open duct and be beneficial to next cycle density.The method of high-temperature heat treatment is: with the speed of 50～200 DEG C/h from room temperature to 800 DEG C, then with the ramp of 10～50 DEG C/h to 1200 DEG C, finally with the ramp of 30～100 DEG C/h to 1800～ 2300 DEG C, after insulation 2～5h, carry out cooling process；When described cooling processes, rate of temperature fall is less than 100～200 DEG C/h, until Temperature is down to 900 DEG C, freely lowers the temperature for less than 900 DEG C.
9) by step 8) in heat treatment after carbon/carbon carry out Colophonium high-pressure impregnation-carbonization treatment, impregnation pressure 60 at goods ～100MPa, carburizing temperature 700～900 DEG C, the time is 15～20h..
10) by step 9) in carbon/carbon carry out high-temperature heat treatment (method with 8) at goods), control heat treatment temperature；
11) step 9 is repeated)～step 10) carry out repeatedly density, until density of material reaches 1.85g/cm3Above, i.e. make Obtain special-shaped flange and close carbon/carbon entirety load frame.
Embodiment 1
As a example by the load mount structure shown in manuscript 2:
1) select domestic T300-3K PAN base carbon fibre to be woven into twill carbon cloth, be 0 ° with warp yarn direction, counterclockwise Rotate and form+45 ° respectively, 90 ° and-45 °, be cut into carbon cloth block by load frame-type face expansion largest enveloping size subsequently standby；
2) press load frame three-dimensional mathematical model and make mould, by step 1) in carbon cloth block according to the paving of 0/+45/90/-45 Layer order carries out lay on mould, and the datum level of lay selects the curved surface flange A in accompanying drawing, enters the carbon cloth after lay subsequently Row compresses to be sewed up, and stitch pitch 5mm × 5mm obtains fabric intermediate；
3) by step 2) in fabric intermediate carry out flange process, by curvature portion A to planar section B flange, carbon Leave breach after cloth cutting, carry out corresponding carbon cloth reinforcement solutions according to notch size, then it is compressed and sews up, stitch pitch 5mm × 5mm, it is thus achieved that abnormity flange closes the integral fabric of frame；
4) pressing load frame fabric three-dimensional size and make split-type graphite frock, load frame fabric is positioned in graphite frock, Carrying out heat treatment, processing technique is: with the speed of 300 DEG C/h after room temperature to 2100 DEG C, insulation 2h, freely lowers the temperature, goes Except forming precast body after the slurry agent of fiber surface.
5) by step 4) in high-temperature process after precast body be placed in impregnating autoclave and carry out bituminizing, dipping temperature 220 DEG C, pressure 1MPa, after dwell time 5h.Material after bituminizing is carried out carbonization treatment, it is thus achieved that the carbon/carbon of certain density exists Goods.Carbonization technique curve is: with the speed of 100 DEG C/h from room temperature to 300 DEG C, rise from 300 DEG C with the speed of 50 DEG C/h Temperature, to 650 DEG C, is warming up to 850 DEG C with the speed of 50 DEG C/h from 650 DEG C, it is incubated 2h when 850 DEG C, freely lowers the temperature.
6) by step 5) in carry out high-temperature heat treatment at goods after carbonization, the process curve of high-temperature process is: with 200 DEG C/speed of h rises to 800 DEG C from room temperature, is warming up to 1200 DEG C with the speed of 30 DEG C/h from 800 DEG C, with the speed of 100 DEG C/h from 1200 DEG C rise to 2300 DEG C, are incubated 2h when 2300 DEG C；Control rate of temperature fall and be less than 200 DEG C/h, until temperature is down to 900 DEG C, 900 Freely lower the temperature below DEG C.
7) by step 6) in carry out Colophonium high-pressure impregnation-carbonization treatment, more than impregnation pressure 60MPa, carbonization at goods Temperature 700 DEG C, the time is 15h；
8) step 6 is repeated), maximum heat treatment temperature is adjusted to 2000 DEG C.
9) step 7 is repeated).
10) step 8 is repeated).
11) step 7 is repeated).
12) step 6 is repeated), maximum heat treatment temperature is adjusted to 1800 DEG C.
After being combined, carbon/carbon compound material is good with graphite jig patch mould, does not finds strain cracking problem.Remove stone Ink mould after obtain carbon/carbon compound material load frame, this be domestic develop at first there is complicated shape, flange, near closed hollow ring The overall load frame of feature.Sampling and testing carbon/carbon compound material performance from load frame, wherein density of material is 1.87g/ cm3, hot strength 220MPa, compressive strength 165MPa, bending strength 182MPa, in-plane shear strength 115MPa, interlayer shear Intensity 16MPa.
Embodiment 2
As a example by the load-carrying construction shown in manuscript 2:
1) select domestic T300-1K PAN base carbon fibre to be woven into twill carbon cloth, be 0 ° with warp yarn direction, counterclockwise Rotate and form+45 ° respectively, 90 ° and-45 °, be cut into carbon cloth block by load frame-type face expansion largest enveloping size subsequently standby；
2) press load frame three-dimensional mathematical model make mould, by step 1) in carbon cloth block according to 0//90/-45/0/-45/ The ply stacking-sequence of 90/0 carries out lay on fixture, and the datum level of lay selects the planar section B in accompanying drawing, subsequently to lay after Carbon cloth carry out compress sew up, stitch pitch 8mm × 8mm, obtain fabric intermediate；
3) by step 2) in fabric intermediate carry out flange process, by planar section B to curvature portion A flange, will Unnecessary carbon cloth cutting, then it is compressed and sews up, stitch pitch 8mm × 8mm, it is thus achieved that abnormity flange closes the integral fabric of frame；
4) pressing load frame fabric three-dimensional size and make split-type graphite frock, load frame fabric is positioned in graphite frock, Carrying out heat treatment, processing technique is: with the speed of 300 DEG C/h after room temperature to 2000 DEG C, after insulation 2h, freely lower the temperature, Precast body is formed after removing the slurry agent of fiber surface.
5) by step 4) in high-temperature process after precast body be placed in impregnating autoclave and carry out bituminizing, dipping temperature 260 DEG C, pressure 2.5MPa, after dwell time 7h.Material after bituminizing is carried out carbonization treatment, it is thus achieved that the carbon/carbon of certain density At goods.Carbonization technique curve is: with the speed of 50 DEG C/h from room temperature to 300 DEG C, rise from 300 DEG C with the speed of 40 DEG C/h Temperature, to 650 DEG C, is warming up to 850 DEG C with the speed of 60 DEG C/h from 650 DEG C, it is incubated 2h when 850 DEG C, freely lowers the temperature.
6) by step 5) in carry out high-temperature heat treatment at goods after carbonization, the process curve of high-temperature heat treatment is: with 50 DEG C/speed of h rises to 800 DEG C from room temperature, is warming up to 1200 DEG C with the speed of 20 DEG C/h from 800 DEG C, with the speed of 80 DEG C/h from 1200 DEG C rise to 2300 DEG C, are incubated 2h when 2300 DEG C；Control rate of temperature fall and be less than 100 DEG C/h, until temperature is down to 900 DEG C, 900 Freely lower the temperature below DEG C.
7) by step 6) in carry out Colophonium high-pressure impregnation-carbonization treatment, more than impregnation pressure 100MPa, carbonization at goods Temperature 900 DEG C, the time is 20h；
8) step 6 is repeated), maximum heat treatment temperature is adjusted to 2100 DEG C.
9) step 7 is repeated).
10) step 8 is repeated).
11) step 7 is repeated).
12) step 8 is repeated).
13) step 7 is repeated).
14) step 6 is repeated), maximum heat treatment temperature is adjusted to 1900 DEG C.
After being combined, carbon/carbon compound material is good with graphite jig patch mould, does not finds strain cracking problem.Remove stone Ink mould after obtain carbon/carbon compound material load frame, this be domestic develop at first there is complicated shape, flange, near closed hollow ring The overall load frame of feature.Sampling and testing carbon/carbon compound material performance from load frame, wherein density of material is 1.92g/ cm3, hot strength 235MPa, compressive strength 180MPa, bending strength 202MPa, in-plane shear strength 102MPa, interlayer shear Intensity 18MPa.
The present invention is from the abnormity of load frame, band flange, the architectural feature of near closed hollow ring, it is contemplated that parts load is special Property, propose a kind of based on cloth lamination structure, substep stitching, near-net-shape method, it is thus achieved that the carbon fiber of integral weaving holds Power frame fabric.Use phase autoclave thickening technology technology and split-type graphite frock application technology, it is achieved the change of overall load frame Shape controls and homogenous densification.By technology controlling and process and parameter optimization, improve the mechanical property of material, final density of material 1.85～1.95g/cm3, hot strength 200～260MPa, compression and bending strength 160～200MPa, in-plane shear strength 100 ～130MPa, interlaminar shear strength 15～20MPa.Ensureing on the basis of material strong mechanical performance, it is achieved that abnormity, flange, Close load frame entirety dead size molding, substantially increase the carrying usefulness of parts.
Compared with split frame, load frame of the present invention uses integral forming method, and fitting surface is few, and fiber is more continuous, complete, energy Giving full play to the enhancing advantage of fiber, load-carrying properties are more preferable, greatly reduce connector and unary quantity simultaneously, improve Integrally-built reliability.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.

Claims (7)

1. a special-shaped flange closes load frame integral forming method, it is characterised in that comprise the following steps:
1) select T300-1K or T300-3K polyacrylonitrile-based carbon fibre, be woven into the carbon cloth of satin weave, plain weave or twill, wove Journey is 0 ° with warp yarn direction, rotates counterclockwise and form+45 ° respectively, 90 ° and-45 °, subsequently carbon cloth is pressed load frame-type It is standby that face expansion largest enveloping size is cut into carbon cloth block；
2) press load frame three-dimensional mathematical model and make mould, for realizing lay and the compression of carbon cloth；
3) by step 1) in carbon cloth block according to the ply stacking-sequence being pre-designed in step 2) mould on carry out lay, lay base Quasi-face is curved surface flange or plane, carries out the carbon cloth after lay subsequently compressing and sews up, obtains fabric intermediate；
4) by step 3) in fabric intermediate carry out flange process, turn down out planar section or curved surface flange, carbon cloth entered Row cuts out process, then compresses it and sew up, it is thus achieved that abnormity flange closes the integral fabric of load frame；
5) close load frame integral fabric three-dimensional dimension making material by abnormity flange is the frock of graphite, and this mould uses a point lobe Formula designs；
6) by step 4) the load frame integral fabric that obtains is positioned over step 5) graphite frock on, carry out heat treatment, remove fibre The prefabricated carbon fiber body of band graphite frock is formed after the slurry agent in dimension table face；
7) by the prefabricated carbon fiber body impregnating pitch of band graphite frock, then carrying out carbonization treatment, iterative cycles is formed the closeest Carbon/the carbon of degree is at goods；
8) by step 7) carbon/carbon carry out high-temperature heat treatment at goods；
9) by step 8) process after carbon/carbon carry out Colophonium high-pressure impregnation-carbonization treatment, more than impregnation pressure 50MPa at goods；
10) by step 9) in carbon/carbon carry out high-temperature heat treatment at goods；
11) step 9 is repeated)～step 10) carry out repeatedly density, until density of material is more than or equal to 1.85g/cm3Above, i.e. make Obtain special-shaped flange and close carbon/carbon entirety load frame.
A kind of abnormity flange the most according to claim 1 closes load frame integral forming method, it is characterised in that: described step Rapid 3), in, the ply stacking-sequence being pre-designed is 0 ° /+45 °/90 °/-45 °, 0 ° /+45 °/90 °/-45 °/0 °, 0 °/90 ° /+45 °/ 0°/90°/-45°、0°/+45°/90°/-45°/0°/-45°/90°/+45°/0°、0°/90°/+45°/0°/90°/-45°/0°/ 90 °, 0 °/90 ° /+45 °/0 °/0 °/-45 °/0 °/90 ° or 0 °/90 ° /+45 °/-45 °/0 °/90 °, carbon cloth block is according to being pre-designed Ply stacking-sequence introduce fibers, fiber volume fraction 45%～55%, stitch pitch 4～10mm in 45 ° of directions.
A kind of abnormity flange the most according to claim 1 closes load frame integral forming method, it is characterised in that: described step Rapid 4), in, the mode being cut out carbon cloth processing is as follows；
When carbon cloth by planar section to curvature portion flange time, carbon cloth is carried out cutting, the breach stayed after cutting is carried out carbon Cloth reinforcement solutions；
When carbon cloth by curved face part A to planar section flange time, directly by unnecessary carbon cloth cutting.
A kind of abnormity flange the most according to claim 1 closes load frame integral forming method, it is characterised in that: described step Rapid 6) in, heat-treating methods is: with the speed of 200～500 DEG C/h after room temperature to 1800～2300 DEG C, insulation 2～3h Freely lower the temperature.
A kind of abnormity flange the most according to claim 1 closes load frame integral forming method, it is characterised in that: described step Rapid 7) in, by the implementation of the prefabricated carbon fiber body impregnating pitch of band graphite frock for for: dipping temperature is 160～260 DEG C, Impregnation pressure is 0.1～3MPa, and the dwell time is 5～8h；The implementation of carbonization treatment is: with the speed of 50～100 DEG C/h From room temperature to 300 DEG C, then with the ramp of 5～50 DEG C/h to 650 DEG C, finally with the ramp of 10～80 DEG C/h After 850 DEG C, it is incubated 2～5h, the most freely lowers the temperature.
A kind of abnormity flange the most according to claim 1 closes load frame integral forming method, it is characterised in that: step 8) Or step 10) in, the method for high-temperature heat treatment is: with the speed of 50～200 DEG C/h from room temperature to 800 DEG C, then with 10 ～the speed of 50 DEG C/h is warming up to 1200 DEG C from 800 DEG C, finally with the speed of 30～100 DEG C/h from 1200 DEG C be warming up to 1800～ 2300 DEG C, after insulation 2～5h, carry out cooling process；When described cooling processes, rate of temperature fall is less than 100～200 DEG C/h, until Temperature is down to 900 DEG C, freely lowers the temperature for less than 900 DEG C.
A kind of abnormity flange the most according to claim 1 closes load frame integral forming method, it is characterised in that: described step Rapid 9) process conditions of medium pitch high-pressure impregnation-carbonization treatment are: impregnation pressure 60～100MPa, carburizing temperature 700～900 DEG C, the time is 15～20h.
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CN106676763A (en) * 2016-12-30 2017-05-17 宜兴市华恒高性能纤维织造有限公司 Entirely seaming molding alveolate three-dimensional fabric and preparing method thereof
CN108484198A (en) * 2018-04-03 2018-09-04 湖南南方搏云新材料股份有限公司 A kind of preparation method of carbon/carbon composite cored slab
CN108440010A (en) * 2018-04-28 2018-08-24 航天材料及工艺研究所 A kind of assorted fibre enhancing superhigh temperature anti-yaw damper composite material and preparation method
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CN112476874A (en) * 2020-11-04 2021-03-12 西安鑫垚陶瓷复合材料有限公司 S-shaped structural member mold and method for preparing S-shaped structural member by using same
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CN112479720A (en) * 2020-12-14 2021-03-12 西安鑫垚陶瓷复合材料有限公司 C/SiC composite material I-beam integral forming tool and forming process
CN113773102A (en) * 2021-09-08 2021-12-10 陕西天策新材料科技有限公司 Flange integrated carbon/carbon screen grid structure and preparation method thereof

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