CN114013063A - Heat-insulating composite material formed by winding prepreg tape and preparation method thereof - Google Patents
Heat-insulating composite material formed by winding prepreg tape and preparation method thereof Download PDFInfo
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- CN114013063A CN114013063A CN202111276761.6A CN202111276761A CN114013063A CN 114013063 A CN114013063 A CN 114013063A CN 202111276761 A CN202111276761 A CN 202111276761A CN 114013063 A CN114013063 A CN 114013063A
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- 238000004804 winding Methods 0.000 title claims abstract description 105
- 239000002131 composite material Substances 0.000 title claims abstract description 63
- 238000002360 preparation method Methods 0.000 title abstract description 15
- 239000004744 fabric Substances 0.000 claims abstract description 129
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 108
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 108
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims abstract description 77
- -1 phenolic aldehyde Chemical class 0.000 claims abstract description 42
- 238000000034 method Methods 0.000 claims abstract description 35
- 239000000377 silicon dioxide Substances 0.000 claims abstract description 31
- 238000009413 insulation Methods 0.000 claims abstract description 27
- 239000005011 phenolic resin Substances 0.000 claims abstract description 18
- 229920001568 phenolic resin Polymers 0.000 claims abstract description 18
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims abstract description 15
- 239000003365 glass fiber Substances 0.000 claims abstract description 11
- 238000004519 manufacturing process Methods 0.000 claims abstract description 11
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 10
- 239000004917 carbon fiber Substances 0.000 claims abstract description 10
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 10
- 239000007787 solid Substances 0.000 claims abstract description 9
- 238000003754 machining Methods 0.000 claims abstract description 8
- 238000002791 soaking Methods 0.000 claims abstract description 8
- 238000005520 cutting process Methods 0.000 claims abstract description 5
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 claims description 20
- RCHKEJKUUXXBSM-UHFFFAOYSA-N n-benzyl-2-(3-formylindol-1-yl)acetamide Chemical compound C12=CC=CC=C2C(C=O)=CN1CC(=O)NCC1=CC=CC=C1 RCHKEJKUUXXBSM-UHFFFAOYSA-N 0.000 claims description 2
- 238000009991 scouring Methods 0.000 abstract description 17
- 238000002679 ablation Methods 0.000 abstract description 9
- OBNDGIHQAIXEAO-UHFFFAOYSA-N [O].[Si] Chemical compound [O].[Si] OBNDGIHQAIXEAO-UHFFFAOYSA-N 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 230000010354 integration Effects 0.000 abstract 1
- 230000008569 process Effects 0.000 description 21
- 229910052814 silicon oxide Inorganic materials 0.000 description 10
- 230000000052 comparative effect Effects 0.000 description 8
- 239000000835 fiber Substances 0.000 description 6
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 5
- 229910052760 oxygen Inorganic materials 0.000 description 5
- 239000001301 oxygen Substances 0.000 description 5
- 229920005989 resin Polymers 0.000 description 5
- 239000011347 resin Substances 0.000 description 5
- 229910052710 silicon Inorganic materials 0.000 description 5
- 239000010703 silicon Substances 0.000 description 5
- 239000000853 adhesive Substances 0.000 description 4
- 230000001070 adhesive effect Effects 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 238000007599 discharging Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 229920000742 Cotton Polymers 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000011065 in-situ storage Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000037303 wrinkles Effects 0.000 description 2
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- 241001391944 Commicarpus scandens Species 0.000 description 1
- 229910052788 barium Inorganic materials 0.000 description 1
- DSAJWYNOEDNPEQ-UHFFFAOYSA-N barium atom Chemical compound [Ba] DSAJWYNOEDNPEQ-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 229910052796 boron Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 230000032798 delamination Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010285 flame spraying Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000004745 nonwoven fabric Substances 0.000 description 1
- 229920001343 polytetrafluoroethylene Polymers 0.000 description 1
- 239000004810 polytetrafluoroethylene Substances 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/32—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
Abstract
The invention discloses a prepreg tape winding and forming heat insulation composite material and a preparation method thereof, which are mainly used for a heat insulation layer of a tail nozzle of a solid rocket engine and comprise the following preparation steps: (1) respectively soaking the carbon fiber cloth and the high silica glass fiber cloth in phenolic resin to obtain carbon cloth/phenolic aldehyde and high silica cloth/phenolic aldehyde prepreg; (2) respectively cutting carbon cloth/phenolic aldehyde and high silica cloth/phenolic aldehyde prepreg into narrow prepreg tapes; (3) obliquely overlapping and winding a carbon cloth prepreg tape on the core mold; (4) vacuumizing the carbon layer blank at room temperature; (5) winding a high silica cloth prepreg tape on the surface of the carbon layer in parallel; (6) and (3) integrally curing the carbon cloth/phenolic aldehyde and the high silica cloth/phenolic aldehyde, and machining to obtain the heat-insulating composite material. Compared with the prior art, the invention has the following beneficial effects: the carbon layer and the high silicon-oxygen layer of the composite material prepared by the method have better integration, do not need to be glued, and reduce the production period; the composite material has better ablation resistance and scouring resistance.
Description
Technical Field
The invention belongs to the technical field of forming of composite material structural parts, relates to a heat-insulating composite material formed by winding a prepreg tape and a preparation method thereof, and particularly relates to a heat-insulating composite material for a tail nozzle of a solid rocket engine and a preparation method thereof.
Background
The anti-ablation layer of the long tail nozzle of the existing solid rocket engine is mainly formed by compression molding of chopped carbon fiber/phenolic aldehyde, the heat insulation layer is formed by winding high silica glass fiber/phenolic aldehyde prepreg tapes, the two layers form an integral structure through secondary bonding, and the anti-ablation, anti-scouring and heat insulation functions are jointly exerted. However, in the prior art, the chopped fiber/phenolic aldehyde molded part has poor anti-scouring performance and high ablation amount, and cannot be pressed into a structural part with a large length-diameter ratio; and the "secondary bonding" efficiency is low, the bonding surface strength between the carbon layer and the high silicon oxide layer is low, and the integrity is poor.
For example: chinese patent publication No. CN103770338A, published as 2014, 5, 7, entitled "winding method for two-layer composite material for rotary body" discloses a winding method for two-layer composite material for rotary body, but the two layers of composite material mentioned in the patent document are all parallel overlapping winding method, which changes the sequence of winding inner and outer layers, and improves the quality of the inner and outer layers of the two-layer composite material, but the method used in the patent document is different from the winding method in the patent, and a structural member with large length-diameter ratio cannot be realized.
The Chinese patent document with the publication number of CN105736177A and the publication number of 2016, 7, 6 and the name of 'a double-layer integrally-formed composite material tail nozzle heat-insulating structure' discloses a double-layer integrally-formed composite material tail nozzle heat-insulating structure, which improves the reliability of long-time operation of a tail nozzle, but in the patent document, a carbon fiber molded piece and a heat-insulating layer are adopted as a burning-resistant layer, the carbon fiber molded piece and the heat-insulating layer are formed by winding, 3 molded pieces need to be formed by gluing, and then the heat-insulating layer is wound on the outer side of the glued molded piece. The method has low forming efficiency and poor anti-scouring effect of the mould pressing piece.
Based on this, it is desirable to obtain a method for preparing a thermal insulation composite material, which can prepare a structural member having a large aspect ratio by improving the prepreg tape winding manner. The oblique lapping winding anti-scouring performance is better, the ablation amount is lower, and the problems of weak adhesive joint surfaces and low forming efficiency of the carbon layer and the high silicon oxide layer can be effectively solved by an integrated curing mode.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a heat insulation composite material formed by winding a prepreg tape and a preparation method thereof. The method breaks through the conventional process means, realizes the integrated preparation of the anti-scouring, ablation-resistant and heat-insulating composite material, and improves the production efficiency.
The purpose of the invention is realized by the following technical scheme:
the invention provides a preparation method of a heat insulation composite material formed by winding a prepreg tape, which comprises the following steps:
step S1: soaking the carbon cloth in phenolic resin to obtain carbon cloth/phenolic prepreg; soaking the high silica glass fiber cloth in phenolic resin to obtain high silica cloth/phenolic prepreg;
step S2: respectively cutting the carbon cloth/phenolic aldehyde prepreg and the high silica cloth/phenolic aldehyde prepreg into prepreg tapes;
step S3: obliquely overlapping and winding a carbon cloth/phenolic aldehyde prepreg tape on the core mould to form a carbon layer;
step S4: vacuumizing the carbon layer blank obtained in the step S3 at room temperature;
step S5: winding high silica cloth/phenolic aldehyde prepreg tapes on the surface of the carbon layer in parallel; the high silica cloth prepreg tape is parallel to a core mold bus;
step S6: the carbon cloth/phenolic aldehyde and the high silica cloth/phenolic aldehyde are integrally cured through composite winding, and the heat insulation composite material is obtained through machining; in the system of the invention, the carbon layer and the high silicon oxide layer are compositely wound and integrally cured without cementing. In the integrated heat insulation composite material, the carbon layer is an ablation-resistant and anti-scouring layer (generally an inner layer and a contact flame); the high silicon oxygen layer is a heat insulation layer (generally an outer layer and is not contacted with flame); compared with other glass fiber cloth (high strength, alkali-free and the like), the high silica glass fiber cloth has higher melting temperature and good heat insulation and anti-scouring performance, and is more suitable for preparing heat insulation and anti-scouring parts in an engine spray pipe.
The phenolic resin comprises barium phenolic resin, boron phenolic resin and the like.
In step S3, an included angle between the carbon cloth/phenolic aldehyde prepreg tape and the axis of the core mold is 10-30 degrees; the 10-30 degrees are selected mainly because the prepreg tape with a certain width can deform in the angle range, and if the angle is too large, the prepreg tape can not deform into a spiral sector; if the angle is too small, the included angle between the bus and the angle is reduced, and the anti-scouring performance of the bus is reduced; the smaller the diameter of the winding heat insulation layer is, the wider the width of the prepreg cloth tape is, and a smaller included angle is selected; conversely, a larger included angle is selected.
Preferably, the angle of the carbon layer prepreg tape is +/-45 degrees, and the included angle between the prepreg tape and the core mold bus is 15 degrees. The used carbon cloth is usually 0/90-degree woven plain cloth with the width of 1 m; the prepreg tape with a certain width is cut at an angle of +/-45 degrees, and after the prepreg tape is stressed, two sides of the cloth tape deform uniformly and deform more easily, so that the shape of the fan-shaped cloth tape is formed.
In step S5, the prepreg tape is wound in parallel to the surface of the carbon layer in a rectangular shape with the same width in the parallel winding process, and the carbon layer is stacked in a multi-layer circulation manner to be spirally wound or wound in situ.
In step S1, the carbon cloth/phenolic prepreg is prepared by impregnating carbon fiber scrim with phenolic resin; the high silica cloth/phenolic aldehyde prepreg is prepared by soaking high silica glass fiber plain cloth in phenolic aldehyde resin.
As an embodiment, in step S3, the carbon cloth prepreg tape width D1 is D1/sin β, and the winding step amount F is a/sin β, where D1 is the carbon layer blank thickness in mm; beta is an oblique folding angle (namely an included angle between the prepreg tape and the axis of the core mold), and the unit is an angle; a is the thickness of the carbon cloth prepreg tape, and the unit is mm.
Further, in step S3, the carbon cloth/phenolic prepreg tape is of the same width.
Further, in step S3, the carbon cloth/phenolic prepreg tape with the same width in the oblique folding and winding process is subjected to tension, temperature and guide rollers, the length of the tape on one side contacting the core mold is not deformed, the length of the tape on the other side is increased, the whole tape is changed from a long rectangular tape into a spiral sector, and then the tape is continuously wound on the core mold, and the winding and stacking mode is as follows: a plurality of frusto-conical rotors are stacked.
Preferably, the tension is that each 10mm width of the cloth belt is required to bear 30-50N of tension, and the tension is adjusted in the tension range according to the spiral deformation and the winding and adhering conditions of the winding cloth belt in the winding process; the temperature is 80 +/-5 ℃, and the temperature is correspondingly adjusted according to whether the carbon cloth/phenolic aldehyde prepreg tape is easy to deform or not (the temperature is increased if the carbon cloth/phenolic aldehyde prepreg tape is not easy to deform).
As one embodiment, in step S5, the prepreg tape is wound in parallel to the surface of the carbon layer in a uniform width and rectangular shape during parallel winding, stacked in multiple cycles, spirally wound or wound in situ. Preferably, the high silicon oxide layer is spirally wound, the band width is 20-50 mm, and the winding stepping amount is half of the band width.
Preferably, in step S3, the vacuum is applied for 1-2h to exhaust the gas between the winding layers to tighten the winding layers.
The invention also relates to a heat insulation composite material formed by winding a prepreg tape, which comprises the following components in percentage by weight:
the carbon layer is formed in an inclined overlapping and winding mode, and a certain included angle is formed between the carbon cloth prepreg tape and the axis of the core mold;
and the high silicon oxide layer is formed in a parallel winding mode, and the high silicon oxide cloth prepreg tape is parallel to the core mould bus (without an included angle).
As an embodiment, the high silicon oxide layer may also be wound in a bias stack.
As an embodiment, the carbon cloth/phenolic prepreg has a gel content of 33% to 42%.
As an embodiment, the high silica cloth/phenolic prepreg has a gel content of 33% to 40%.
The gel content refers to the mass content of the resin in the prepreg. The fiber plays roles of reinforcing, scouring resistance and the like in the composite material, and the resin plays roles of combining, fixing the fiber, insulating heat and the like. If the resin content is too high, the anti-scouring capability of the heat insulating layer is reduced; if the bonding force between the fibers is too low, the bonding force between the fibers is reduced, a heat insulation layer product cannot be formed, and the defects of layering, looseness and the like easily occur between the fiber layers;
the resin content range is a long-term experience accumulation result, and the mechanical and thermal properties of the prepared composite material product are in an optimal state.
The carbon cloth prepreg tape and the mandrel bus form a certain included angle, the mandrel is required to be provided with an auxiliary tool, and the tool angle is consistent with the oblique folding angle.
The invention relates to application of the heat insulation composite material in serving as a heat insulation layer of a tail nozzle of a solid rocket engine. The length/inner diameter of the product is more than or equal to 10.
As one embodiment, the inner cavity of the carbon layer is directly contacted with the flame sprayed when the solid rocket engine works, and the carbon layer is obliquely wound in the same direction as the flame spraying direction of the solid rocket engine.
Compared with the prior art, the invention provides the heat-insulating composite material formed by winding the prepreg tapes and the preparation method thereof by using two winding modes of the two prepreg tapes, and the heat-insulating composite material has the following beneficial effects:
1) the production efficiency is high, and the pre-impregnated tapes in two different forms are wound and formed, so that the 'gluing' process is omitted;
2) the material has good integrity, the high silica thermal insulation layer is directly wound outside the carbon fiber ablation-resistant layer, the resin system is consistent, and no adhesive is used;
3) the carbon layer pre-dip belt has excellent anti-scouring performance and low ablation amount, the direction between the layers of the carbon layer pre-dip belt which is obliquely wound and the flame scouring direction form a certain included angle, only the edge of the pre-dip belt is ablated, and the situation that the pre-dip belt is peeled off can not occur.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural view of a prepreg tape-wound insulating composite material according to the present invention;
FIG. 2 is a schematic view of a core mold and an auxiliary tool according to the present invention;
FIG. 3 is a schematic diagram illustrating the deformation principle of the carbon cloth prepreg tape of the present invention;
fig. 4 is a schematic view of the winding principle of the carbon cloth prepreg tape of the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The embodiment relates to a heat insulation composite material formed by winding a prepreg tape and a preparation method thereof, and the heat insulation composite material comprises the following steps:
1) respectively soaking the carbon fiber cloth and the high silica glass fiber cloth in phenolic resin to prepare prepreg;
2) calculating the bandwidth of the carbon cloth prepreg tape according to a formula;
3) cutting the wide prepreg into a narrower prepreg tape;
4) winding a carbon cloth prepreg tape on a core mould through a cloth tape winding machine, wherein the carbon cloth prepreg tape and the axis of the core mould form a certain included angle (oblique folding angle), and the oblique folding and winding direction of a carbon layer is consistent with the flame ejection direction of a solid rocket engine;
5) vacuumizing the carbon layer blank at room temperature;
6) winding the high silica prepreg tape to the surface of the carbon layer in parallel by a cloth tape winding machine;
7) and wrapping the prepared blank with an adhesive absorption layer, preparing a vacuum bag, curing by an autoclave, and machining to obtain the integrated heat insulation composite material.
The bandwidth calculation formula of the carbon cloth prepreg tape is as follows: d1 ═ D1/sin beta, and winding step F ═ A/sin beta, wherein D1 is the carbon layer blank thickness and the unit is mm; beta is the angle of fold, in degrees; a is the thickness of the prepreg tape and the unit is mm.
FIG. 1 is a schematic structural view of a prepreg tape winding-molded heat-insulating composite material of the present invention, and FIG. 2 is a schematic view of a core mold and an auxiliary tool of the present invention; FIG. 3 is a schematic diagram illustrating the deformation principle of the carbon cloth prepreg tape of the present invention; fig. 4 is a schematic view of the winding principle of the carbon cloth prepreg tape of the present invention.
See in particular the following examples:
example 1
Thermal insulation composite material: the inner diameter of the product is 28mm, the oblique stack angle is 15 degrees, the thickness of the carbon layer is 8mm, the thickness of the high silicon oxide layer is 6mm, and the length is 400 mm.
The plain-woven carbon fiber cloth and the high-silica glass fiber cloth are respectively soaked in barium-phenolic resin to prepare a prepreg, wherein the content of carbon cloth/phenolic resin (the mass percentage of the barium-phenolic resin in the plain-woven carbon fiber cloth prepreg) is 38.3%, the content of high-silica cloth/phenolic resin (the mass percentage of the barium-phenolic resin in the high-silica glass fiber cloth prepreg) is 37.5%, the thickness of the carbon cloth/phenolic resin prepreg is 0.2mm, and the thickness of the high-silica/phenolic resin prepreg is 0.25 mm.
According to the calculation formula of the bandwidth of the carbon cloth prepreg tape, D1 is 8/sin (15 degrees) approximately equal to 31mm, the winding step quantity F is 0.2/sin (15 degrees) approximately equal to 0.773mm, the ratio of the deformed outer edge to the deformed inner edge of the tape is delta (28+ 8) approximately equal to 2)/28 approximately equal to 1.57 (the larger the value is, the larger the change of the length of the outer edge in the tape deformation process is, the more difficult the tape is to be attached and wound in the winding process is, and when the value is 1, the deformation of the outer edge in the tape is consistent). The winding tool comprises a winding core mold and an auxiliary tool, and the cone angle of the auxiliary tool is consistent with the oblique folding angle (15 degrees), as shown in fig. 2. The carbon cloth prepreg tape is attached to the conical surface of the auxiliary tool by means of a tape winding machine, one side of the tape deforms after tension is applied, and the other side of the tape does not deform. The single helical unwinding of the winding is shown in fig. 3 and continues on the mandrel helical winding as shown in fig. 4 until the desired length of winding is 470mm (the overlap ends are cut off).
And (3) integrally wrapping a layer of polytetrafluoroethylene glass demolding cloth on the surface of the carbon layer blank, then preparing a vacuum bag, and vacuumizing for 2h at room temperature.
Removing a vacuum bag and demolding cloth, winding a high-silicon oxygen layer on the surface of the carbon layer, wherein the width of the high-silicon oxygen prepreg tape is 20mm, the tape cutting angle (0/90) is 10mm, the winding stepping amount is 10mm, the high-silicon oxygen layer is spirally wound to the surface of the carbon layer in parallel, the winding thickness of the high-silicon oxygen layer is 8mm (2 mm is more than the processing allowance), the winding length is 410mm, and the high-silicon oxygen layer is wound in a circulating and reciprocating manner.
Wrapping 2 layers of non-woven fabrics on the surface of the blank as an adhesive absorption layer, preparing a vacuum bag, curing in an autoclave at the curing temperature of 160 ℃ for 2h, wherein the pressing point is 105 ℃ and the pressure is 1.1 MPa. And (4) discharging the blank out of the furnace, and machining to obtain the required heat-insulating composite material. The properties are as follows:
example 2
Thermal insulation composite material: the inner diameter of the product is 23.5mm, the oblique folding angle is 10 degrees, the thickness of the carbon layer is 15mm, the thickness of the high silicon oxide layer is 6mm, and the length is 400 mm.
For the winding layer with small inner diameter and large thickness, small-angle winding (10 degrees) is preferably selected, so that the larger width of the winding cloth belt can be obtained, the deformation difference between one side of the cloth belt contacting with the die and the other side of the cloth belt in the winding process is small in opposite-phase large-angle winding, and the spiral deformation and the winding attachment of the cloth belt in the winding process are facilitated. According to the calculation formula of the bandwidth of the carbon cloth prepreg tape, D1 is 15/sin (10 degrees) and is approximately equal to 58mm, the winding step quantity F is 0.2/sin (10 degrees) and is approximately equal to 1.152mm, and the external edge ratio in tape deformation is delta (23.5+ 15) and 23.5 and is approximately equal to 2.28. The carbon cloth/phenolic aldehyde prepreg and the high silica cloth/phenolic aldehyde prepreg are the same as those in example 1, the carbon cloth/phenolic aldehyde winding tool and the winding mode are the same as those in example 1 (the vacuumizing time after winding is prolonged to 2 hours because the carbon layer is thick), the high silica cloth/phenolic aldehyde winding layer is the same as that in example 1, and the curing mode is the same as that in example 1. And (4) discharging the blank out of the furnace, and machining to obtain the required heat-insulating composite material.
The performance of the composite material is equivalent to that of the composite material in example 1 (only tested item), but the compactness of a carbon layer and the uniformity (no wrinkles) of a carbon cloth layer are both good, and the winding process is stable; because the area between the carbon cloth layers is larger, the anti-gas scouring capability is better.
Example 3
Thermal insulation composite material: the inner diameter of the product is 105mm, the oblique folding angle is 30 degrees, the thickness of the carbon layer is 20mm, the thickness of the high silica layer is 10mm, and the length is 400 mm.
For the winding layer with large inner diameter and large thickness, large-angle winding (30 degrees) is preferred, and the width of the winding cloth belt can be smaller. Because the winding internal diameter is bigger, reduced big winding angle to the cotton tape at the winding in-process contact one side of mould with the deflection difference of another side, can realize the requirement that big angle winding warp and laminating to the cotton tape. According to the calculation formula of the bandwidth of the carbon cloth prepreg tape, D1 is 20/sin (30 degrees) and is approximately equal to 40mm, the winding step quantity F is 0.2/sin (30 degrees) and is approximately equal to 0.4mm, and the external edge ratio in tape deformation is delta (105+20 and 2)/105 and is approximately equal to 1.38 ". The carbon cloth/phenolic aldehyde prepreg and the high silica cloth/phenolic aldehyde prepreg are the same as those in the example 1, the carbon cloth/phenolic aldehyde winding tool and the winding mode are the same as those in the example 1, the high silica cloth/phenolic aldehyde winding layer is the same as that in the example 1, and the curing mode is the same as that in the example 1. And (4) discharging the blank out of the furnace, and machining to obtain the required heat-insulating composite material.
The performance of the composite material is equivalent to that of the composite material in example 1 (only tested item), but the compactness of a carbon layer and the uniformity (no wrinkles) of a carbon cloth layer are both good, and the winding process is stable; in the actual working process, the anti-scouring performance is better.
Comparative example 1
This comparative example relates to a process for the preparation of a heat insulating composite wound from a prepreg tape and a composite prepared thereby, the process steps being essentially the same as in example 1 except that the carbon cloth prepreg tape has no included angle with the mandrel generatrix.
The winding mode of the carbon layer/phenolic aldehyde is consistent with that of the high silicon oxide phenolic aldehyde, narrow-band spiral winding with the bandwidth of 20mm is adopted, and multiple layers of winding are needed to meet the requirement of the whole thickness. The disadvantages are that: the carbon cloth layer is internally provided with a plurality of winding layers, the carbon cloth between each layer is discontinuous, the structure of a continuous cloth belt in the thickness direction in the original winding mode carbon cloth layer is damaged, and the carbon cloth layer is easy to peel off layer by layer in the gas scouring process; the multiple winding layers reduce the winding efficiency.
Comparative example 2
This comparative example relates to a process for the preparation of a heat insulating composite wound from a prepreg tape and a composite prepared thereby, the process steps being essentially the same as in example 1 except that the carbon cloth prepreg tape has no included angle with the mandrel generatrix.
The carbon layer/phenolic aldehyde adopts the whole cloth belt, the width of the cloth belt is consistent with the length of the product, and the carbon cloth layer is parallel to the generatrix of the core mould. The disadvantages are that: the winding forming of longer products cannot be realized; the requirements for the cloth belt transmission and the tension control of the winding equipment are too high, and the realization is difficult.
Comparative example 3
This comparative example relates to a process for the preparation of a prepreg tape wound into a shaped insulating composite and a composite prepared therefrom, the process steps being essentially the same as in example 1 except that the carbon cloth prepreg tape forms an angle of 50 ° with the mandrel generatrix and, taking the product size in example 1 as an example, the prepreg tape width D1 ═ 8/sin (50 °) ≈ 10.5mm, the winding step F ═ 0.2/sin (50 °) ≈ 0.261mm, and the tape deformation outer-inner edge ratio δ ═ 28+8 ≈ 2)/28 ≈ 1.57 are calculated. The cloth tape winding is difficult to realize (the cloth tape is easy to break) because the width of the cloth tape is only 10.5 mm; in addition, too large a winding angle makes it more difficult for the winding arrangement shown in fig. 1 to achieve device mechanization (tape approach perpendicular to the mandrel generatrix).
Comparative example 4
This comparative example relates to a process for the preparation of a prepreg tape-wound insulating composite and a composite prepared thereby, the product structure being the same as in example 1, the carbon cloth/phenolic layer and the high silica cloth/phenolic layer being the same as in example 1 except that the carbon layer and the high silica layer are cured non-integrally.
The implementation process is as follows: after the carbon cloth/phenolic aldehyde layer is wound, curing is carried out according to the curing process in the embodiment 1, and then the outer surface auxiliary layer is removed; the high silica cloth/phenolic layer was then wound and cured again. The properties of the carbon cloth/phenolic layer and the high silica cloth/phenolic layer were not significantly different from those of example 1 (item tested only), but the disadvantages were: a. the curing of the primary carbon layer is increased, and the production cost is increased (the cost of the auxiliary layer material, the curing, the machining process and the like); b. because the carbon layer needs to be processed to remove the auxiliary layer, the winding thickness must be increased during winding, compared with the loss of materials, the cost is increased; c. the carbon cloth/phenolic aldehyde layer and the high silica cloth/phenolic aldehyde layer are cured twice, and have interfaces with weaker interface bonding force, and the curing process is easy to generate the defects of glue accumulation, delamination and the like, so that the reliability of the composite material in the high-temperature gas working process is not facilitated.
It should be noted that the prior art in the protection scope of the present invention is not limited to the examples given in the present application, and all the prior art which is not inconsistent with the technical scheme of the present invention, including but not limited to the prior patent documents, the prior publications and the like, can be included in the protection scope of the present invention.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A method for preparing a heat insulation composite material formed by winding a prepreg tape, which is characterized by comprising the following steps:
step S1: soaking the carbon cloth in phenolic resin to obtain carbon cloth/phenolic prepreg; soaking the high silica glass fiber cloth in phenolic resin to obtain high silica cloth/phenolic prepreg;
step S2: respectively cutting the carbon cloth/phenolic aldehyde prepreg and the high silica cloth/phenolic aldehyde prepreg into prepreg tapes;
step S3: obliquely overlapping and winding a carbon cloth/phenolic aldehyde prepreg tape on the core mould to form a carbon layer;
step S4: vacuumizing the carbon layer blank obtained in the step S3 at room temperature;
step S5: winding high silica cloth/phenolic aldehyde prepreg tapes on the surface of the carbon layer in parallel; the high silica cloth prepreg tape is parallel to a core mold bus;
step S6: the carbon cloth/phenolic aldehyde and the high silica cloth/phenolic aldehyde are integrally cured through composite winding, and the heat insulation composite material is obtained through machining;
in step S3, the included angle between the carbon cloth/phenolic aldehyde prepreg tape and the axis of the core mold is 10-30 degrees.
2. The method of making a heat insulating composite according to claim 1, wherein: in step S1, the carbon cloth/phenolic prepreg is prepared by impregnating carbon fiber scrim with phenolic resin; the high silica cloth/phenolic aldehyde prepreg is prepared by soaking high silica glass fiber plain cloth in phenolic aldehyde resin.
3. The method of making a heat insulating composite according to claim 1, wherein: in step S3, the width D1 of the carbon cloth/phenolic prepreg tape is D1/sin β, and the winding step amount F is a/sin β, where D1 is the thickness of the carbon layer blank and the unit is mm; beta is the angle of fold, in degrees; a is the thickness of the carbon cloth prepreg tape, and the unit is mm.
4. The method of making a heat insulating composite according to claim 1, wherein: in step S3, the carbon cloth/phenolic prepreg tape is of the same width.
5. The method of making a thermally insulating composite as claimed in claim 4, wherein: in step S3, the carbon cloth/phenolic prepreg tape with the same width is wound onto the core mold continuously in a winding and stacking mode of stacking a plurality of truncated cone-shaped rotators, wherein the length of the tape on one side contacting the core mold is not deformed and the length of the tape on the other side is increased by the action of tension, temperature and guide rollers, and the tape is changed from a long rectangular shape to a spiral sector shape.
6. The method of making a thermally insulating composite as claimed in claim 5, wherein: in step S3, the tension is 30-50N per 10mm width of cloth belt, and the temperature is 80 +/-5 ℃.
7. The method of making a heat insulating composite according to claim 1, wherein: in step S4, the vacuumizing time is 1-2 h.
8. A composite material produced by the production method according to any one of claims 1 to 7.
9. Use of the composite material of claim 8 in thermal insulation of a solid rocket engine tail pipe.
10. Use according to claim 9, characterized in that: the carbon layer obliquely-stacked winding direction is consistent with the flame ejection direction of the solid rocket engine.
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101450533A (en) * | 2007-11-30 | 2009-06-10 | 航天材料及工艺研究所 | Carbon fiber reinforcement resin base composite material lattice structural-component conforming die and method |
| JP2011000750A (en) * | 2009-06-17 | 2011-01-06 | Ihi Aerospace Co Ltd | Rocket nozzle and manufacturing method therefor |
| CN103770338A (en) * | 2012-10-19 | 2014-05-07 | 湖北三江航天红阳机电有限公司 | Winding forming method for double-layer composite material of rotator |
| CN109454894A (en) * | 2018-10-31 | 2019-03-12 | 航天特种材料及工艺技术研究所 | A kind of compound layer of resistance to ablative thermal protection of effectively insulating and preparation method thereof |
| US20190160760A1 (en) * | 2017-11-29 | 2019-05-30 | Arianegroup Sas | Method and an installation for winding a pre-impregnated fabric strip onto a sloping surface |
| CN110481062A (en) * | 2019-08-02 | 2019-11-22 | 湖北三江航天江北机械工程有限公司 | A kind of outer heat shield winding, molding method of Solid Rocket Motor combustion chamber shell |
| CN110509572A (en) * | 2019-09-03 | 2019-11-29 | 长春长光宇航复合材料有限公司 | A kind of full composite material jet pipe and quick molding method |
| CN111016004A (en) * | 2019-12-26 | 2020-04-17 | 上海复合材料科技有限公司 | Heat-proof structure of fairing and forming method thereof |
| CN112223856A (en) * | 2020-12-17 | 2021-01-15 | 北京玻钢院复合材料有限公司 | Heat insulation layer structure of long tail nozzle of solid rocket engine and preparation method thereof |
| CN113320129A (en) * | 2021-05-25 | 2021-08-31 | 西安英利科电气科技有限公司 | End-fired solid rocket long tail pipe winding structure and winding method |
-
2021
- 2021-10-29 CN CN202111276761.6A patent/CN114013063A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101450533A (en) * | 2007-11-30 | 2009-06-10 | 航天材料及工艺研究所 | Carbon fiber reinforcement resin base composite material lattice structural-component conforming die and method |
| JP2011000750A (en) * | 2009-06-17 | 2011-01-06 | Ihi Aerospace Co Ltd | Rocket nozzle and manufacturing method therefor |
| CN103770338A (en) * | 2012-10-19 | 2014-05-07 | 湖北三江航天红阳机电有限公司 | Winding forming method for double-layer composite material of rotator |
| US20190160760A1 (en) * | 2017-11-29 | 2019-05-30 | Arianegroup Sas | Method and an installation for winding a pre-impregnated fabric strip onto a sloping surface |
| CN109454894A (en) * | 2018-10-31 | 2019-03-12 | 航天特种材料及工艺技术研究所 | A kind of compound layer of resistance to ablative thermal protection of effectively insulating and preparation method thereof |
| CN110481062A (en) * | 2019-08-02 | 2019-11-22 | 湖北三江航天江北机械工程有限公司 | A kind of outer heat shield winding, molding method of Solid Rocket Motor combustion chamber shell |
| CN110509572A (en) * | 2019-09-03 | 2019-11-29 | 长春长光宇航复合材料有限公司 | A kind of full composite material jet pipe and quick molding method |
| CN111016004A (en) * | 2019-12-26 | 2020-04-17 | 上海复合材料科技有限公司 | Heat-proof structure of fairing and forming method thereof |
| CN112223856A (en) * | 2020-12-17 | 2021-01-15 | 北京玻钢院复合材料有限公司 | Heat insulation layer structure of long tail nozzle of solid rocket engine and preparation method thereof |
| CN113320129A (en) * | 2021-05-25 | 2021-08-31 | 西安英利科电气科技有限公司 | End-fired solid rocket long tail pipe winding structure and winding method |
Non-Patent Citations (6)
| Title |
|---|
| 冷兴武等: "缠绕工艺", 31 May 1995, 武汉工业大学出版社, pages: 193 - 199 * |
| 刘雄亚等: "复合材料工艺及设备", 31 May 1997, 武汉工业大学出版社, pages: 195 - 199 * |
| 史耀耀;李海宁;余强;唐虹;: "数控布带缠绕机设计与控制技术研究", 中国机械工程, no. 12 * |
| 史耀耀;肖颖;常丽丽;: "数控布带缠绕机机构实现及工艺方法研究", 机械科学与技术, no. 03 * |
| 梁瑜;郭亚林;张;: "固体火箭发动机喷管用树脂基烧蚀防热材料研究进展", 宇航材料工艺, no. 02, pages 1 - 5 * |
| 肖颖;史耀耀;常丽丽;: "复合材料缠绕成形工艺研究", 电加工与模具, no. 05, pages 56 - 60 * |
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