CN115320132A - Interface flexible processing method of integrally-formed composite material spray pipe - Google Patents
Interface flexible processing method of integrally-formed composite material spray pipe Download PDFInfo
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- CN115320132A CN115320132A CN202210928359.XA CN202210928359A CN115320132A CN 115320132 A CN115320132 A CN 115320132A CN 202210928359 A CN202210928359 A CN 202210928359A CN 115320132 A CN115320132 A CN 115320132A
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- composite material
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- 239000002131 composite material Substances 0.000 title claims abstract description 51
- 239000007921 spray Substances 0.000 title claims abstract description 25
- 238000003672 processing method Methods 0.000 title claims description 7
- 238000009413 insulation Methods 0.000 claims abstract description 35
- 238000004804 winding Methods 0.000 claims abstract description 29
- 238000000034 method Methods 0.000 claims abstract description 17
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims abstract description 15
- 229920001971 elastomer Polymers 0.000 claims abstract description 13
- 239000000463 material Substances 0.000 claims abstract description 12
- 229920001568 phenolic resin Polymers 0.000 claims abstract description 11
- 239000005011 phenolic resin Substances 0.000 claims abstract description 11
- 239000003822 epoxy resin Substances 0.000 claims abstract description 5
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 5
- 239000004744 fabric Substances 0.000 claims description 14
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 11
- 239000004917 carbon fiber Substances 0.000 claims description 11
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 9
- 238000000465 moulding Methods 0.000 claims description 9
- 238000007731 hot pressing Methods 0.000 claims description 5
- 229920002943 EPDM rubber Polymers 0.000 claims description 4
- 229920000459 Nitrile rubber Polymers 0.000 claims description 4
- 229920002379 silicone rubber Polymers 0.000 claims description 4
- 239000004945 silicone rubber Substances 0.000 claims description 3
- 239000011159 matrix material Substances 0.000 abstract description 10
- 229920005989 resin Polymers 0.000 abstract description 10
- 239000011347 resin Substances 0.000 abstract description 10
- 239000004593 Epoxy Substances 0.000 abstract description 9
- 230000008646 thermal stress Effects 0.000 abstract description 7
- 238000005516 engineering process Methods 0.000 abstract description 4
- LNEPOXFFQSENCJ-UHFFFAOYSA-N haloperidol Chemical compound C1CC(O)(C=2C=CC(Cl)=CC=2)CCN1CCCC(=O)C1=CC=C(F)C=C1 LNEPOXFFQSENCJ-UHFFFAOYSA-N 0.000 abstract description 2
- 239000012466 permeate Substances 0.000 abstract description 2
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 abstract description 2
- 239000010410 layer Substances 0.000 description 59
- 239000000047 product Substances 0.000 description 20
- 238000002679 ablation Methods 0.000 description 9
- 230000037303 wrinkles Effects 0.000 description 7
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000035882 stress Effects 0.000 description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 239000002346 layers by function Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000035772 mutation Effects 0.000 description 2
- 239000002344 surface layer Substances 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- CREMABGTGYGIQB-UHFFFAOYSA-N carbon carbon Chemical group C.C CREMABGTGYGIQB-UHFFFAOYSA-N 0.000 description 1
- 239000011203 carbon fibre reinforced carbon Substances 0.000 description 1
- 230000005465 channeling Effects 0.000 description 1
- 238000005229 chemical vapour deposition Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 239000013013 elastic material Substances 0.000 description 1
- 239000003733 fiber-reinforced composite Substances 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000009941 weaving Methods 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
- B29C70/30—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
-
- 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
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2023/00—Tubular articles
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
Abstract
The invention relates to an interface flexible treatment method of an integrated composite material spray pipe, wherein the spray pipe comprises a heat insulation layer, a flexible layer and a composite material shell, the heat insulation layer is formed by winding a phenolic resin matrix composite material, the composite material shell is an epoxy resin matrix material laying or winding type, the flexible layer is laid between the heat insulation layer and the composite material shell, and the flexible layer is made of a heat insulation elastic rubber material; the interface layer adopts a filling flexible layer co-curing technology, the resin matrix used by the inner structure is phenolic resin, the resin matrix used by the composite shell is epoxy modified phenolic resin, the epoxy modified phenolic resin and the flexible layer mutually permeate and diffuse during curing to form a phenolic-rubber-epoxy gradient interface, and the flexible rubber well compensates gaps caused by different thermal expansion coefficients and curing temperature intervals of the phenolic and epoxy resins and folds caused by thermal stress, so that the interface strength is improved, and the debonding risk is avoided.
Description
Technical Field
The invention relates to the technical field of solid rocket engines, in particular to an interface flexible processing method of an integrally-formed composite material spray pipe.
Background
The functional layers and structural layer components of the traditional engine nozzle are formed in an assembling mode, and mainly comprise a throat liner, a convergence section, a back lining, a diffusion section and a structural layer which are formed respectively and then are matched with a lathe for gluing. On one hand, the forming mode has more assembly gaps, so that the air leap in the working process of the nozzle is easy to cause failure and disintegration; on the other hand, the mode adopts a metal structure layer, the specific strength is low, the weight of the whole spray pipe is high, and the integral carrying capacity of the rocket is reduced. The integrated forming composite material spray pipe is an effective method for solving the problems, the integral spray pipe is used for replacing a manufacturing method of an assembled spray pipe, the composite material structure layer is used for replacing a metal structure layer, the overall weight of the spray pipe is greatly reduced, and the risk of air channeling possibly caused by assembly is well solved by adopting the integrated forming method. For example, patent CN114198223A proposes a one-step curing molding full composite material, which comprises a throat liner, a convergence section, a thermal insulation layer, an inner ablation layer and a composite material shell, wherein the throat liner is used as an initial surface layer, the convergence section, the ablation layer, the thermal insulation layer and the composite material shell are sequentially formed into a spray pipe from inside to outside in a rotating manner, a co-curing technology of transition structure resin is adopted to form a gradient interface of phenolic-epoxy modified phenolic resin, and the gradient interface undergoes a one-step curing process, so that a defect that thermal stress of each part of the full composite material spray pipe is not matched due to multiple curing is avoided.
However, the curing in the integrated molding manner also has the problems that the resin-based fiber reinforced composite material generates large thermal stress and deformation in the structure due to the complex internal temperature gradient in the curing process, the phenolic resin composite material adopted by the thermal insulation layer of the nozzle pipe and the epoxy composite material adopted by the structural layer have different thermal expansion coefficients and different viscoelasticity, elastic modulus and the like of different polymer matrixes, the thermal stress is different in the curing process to cause wrinkles, and the interface stress is concentrated in the loading process after curing;
in view of the advantages of the integral curing molding and the problem caused by the uneven distribution of the thermal stress at the interface, a method for eliminating the stress concentration at the interface is needed to improve the reliability of the nozzle.
Disclosure of Invention
Aiming at the problem that the co-curing interface of the existing integrally-formed composite material spray pipe generates thermal stress and deformation, the interface flexible treatment technology is adopted, the interface layer uses elastic rubber materials capable of insulating heat, such as ethylene propylene diene monomer, nitrile rubber, silicon rubber and the like, the curing of different structures and functional layers of the composite material spray pipe is completed at one time, the problems of interface wrinkles, interface gaps and stress concentration of the fully-composite material spray pipe caused by co-curing of different structural layer materials are avoided, and the working reliability of the fully-composite material spray pipe is greatly improved.
In order to achieve the purpose, the invention provides an interface flexible processing method of an integrally-formed composite material spray pipe, wherein the spray pipe comprises a heat insulation layer, a flexible layer and a composite material shell, the heat insulation layer is formed by winding a phenolic resin-based composite material, the composite material shell is made of an epoxy resin-based material in a laying or winding mode, the flexible layer is laid between the heat insulation layer and the composite material shell, and the flexible layer is made of a heat insulation elastic rubber material; and after all winding work is finished, carrying out integral hot-pressing curing molding on the spray pipe.
Further, the heat-insulating elastic rubber material comprises any one of nitrile rubber, ethylene propylene diene monomer or silicone rubber.
Furthermore, the curing temperature of the hot-pressing curing molding is 160-170 ℃, and the curing time is 7-8.5 hours.
Further, the thermal insulation layer is formed by obliquely winding carbon fiber prepregs or cloth tape prepregs.
Further, the composite material shell is formed by laying or winding carbon fiber prepreg or cloth tape prepreg on the outer side of the thermal insulation layer.
Further, the thickness of the flexible layer is 0.2mm-2mm.
Further, the thermal insulation layer is formed by winding the prepreg cloth tape in a flat-folded mode or winding the prepreg cloth tape in a diagonal-folded mode at a winding angle of 5-15 degrees.
Further, a flange is arranged on one side, close to the inlet end of the spray pipe, of the composite material shell.
By adopting the technical scheme, the invention has the following beneficial effects:
the interface layer adopts a filling flexible layer co-curing technology, the resin matrix used by the inner structure is phenolic resin, the resin matrix used by the composite shell is epoxy modified phenolic resin, the epoxy modified phenolic resin and the flexible layer mutually permeate and mutually diffuse during curing to form a phenolic-rubber-epoxy gradient interface, and the flexible rubber well compensates gaps caused by different thermal expansion coefficients and different curing temperature intervals of the phenolic and epoxy resins and folds caused by thermal stress, has no chemical structural mutation and no material rigidity mutation, so that the interface strength is improved, and the debonding risk is avoided.
Drawings
FIG. 1 is a schematic view of insulation wrap;
FIG. 2 is a schematic view of the flexible layer lay-up;
FIG. 3 is a schematic representation of composite shell layup;
FIG. 4 is a photograph of a cut surface of a product with a flexible layer (rubber) added;
FIG. 5 is a photograph of a cut surface of a product without the addition of a flexible layer (rubber);
1-winding mandrel, 2-throat liner, 3-convergence section, 4-ablation layer, 5-thermal insulation layer, 6-flexible layer and 7-composite shell.
Detailed Description
The invention is further described with reference to specific embodiments.
It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The invention provides a flexible processing method for an interface of a once-cured and molded full-composite engine nozzle, which comprises a throat insert, a convergence section, a heat insulation layer, an inner ablation layer and a composite shell, wherein the throat insert is arranged on a winding core mold, and the outer profile of the mold is matched with the inner profile of the nozzle; the throat insert is used as an initial surface layer, the convergence section, the ablation layer, the heat insulation layer, the flexible layer and the composite material shell are sequentially formed into a spray pipe in a rotating mode from inside to outside, and after all winding work is finished, the whole body is subjected to one-step hot-pressing curing forming;
the throat insert is a carbon-carbon composite material which is prepared by weaving carbon fibers, integrally forming the carbon fibers into a prefabricated part and then carrying out a chemical vapor deposition process; the convergence section is formed by integrally winding carbon fiber cloth tape prepreg, and the resin matrix used by the carbon fiber cloth tape prepreg is phenolic resin; the ablation layer is formed by winding a carbon fiber cloth tape prepreg on the throat liner and the mould, and a resin matrix used by the carbon fiber cloth tape prepreg of the ablation layer is phenolic resin; the ablation layer is wound in a direction starting from the convergent section and winding to the right. As shown in fig. 1, the thermal insulation layer is formed by obliquely winding fiber or cloth tape prepreg on the outer side of the ablation layer, and the resin matrix used by the high silica cloth prepreg is phenolic resin; the winding direction of the heat insulation layer is gradually close to the convergence section from right to left for winding.
As shown in fig. 2, a flexible layer with heat insulation performance is added on the outer side of the heat insulation layer, namely, after the heat insulation layer is wound, a layer of heat insulation elastic material such as nitrile rubber, ethylene propylene diene monomer or silicone rubber is paved on the surface of the heat insulation layer; as shown in fig. 3, finally, the composite material shell is formed by laying or winding fibers or cloth tapes on the outer side of the flexible layer, and the resin matrix used by the carbon fiber cloth tape prepreg is epoxy modified phenolic resin.
After all the paving and pasting work is finished, the spray pipe is subjected to integral hot-pressing curing molding, wherein the curing temperature is 170 ℃ in the embodiment, and the curing time is 7 hours.
Actual comparison pieces of two products were made according to the above-mentioned manufacturing method, and the test comparison conditions of the two products were as follows:
(1) The two products have the same specification;
(2) The two products use raw materials with the same specification and batch;
(3) The two products use winding and laying processes with the same specification;
(4) 824 rubber with the thickness of 0.5mm is paved between the heat insulation layer of one product and the composite material shell, and the other product is directly wound on the composite material shell at the outer side of the heat insulation layer without paving the rubber;
(5) Curing the two products in the same furnace under the same curing condition;
through comparison of actual manufacturing experiments, the two products are cut after curing, the cut surfaces of the two products are observed, the cut surfaces of the products added with the flexible layer (rubber) are shown in figure 4, and the products can be seen to have flat surfaces and no obvious deformation; the section of the product without the flexible layer is shown in figure 5, and the surface of the product is in an uneven wrinkle shape and is obviously deformed; the wrinkles (bulges) generated by the deformation are directly measured by a ruler, the maximum wrinkle deformation of a product without the flexible layer is measured to be 2mm, and the wrinkle deformation of a product with the flexible layer is only 0.8mm.
The experiment shows that the deformation of the product added with the flexible layer is 50% less than that of the product without the flexible layer, and proves that the flexible layer is laid on the heat insulation layer and the composite material shell, so that gaps and wrinkles generated by curing are greatly weakened, the deformation degree of the cured material is reduced, the interface strength is improved, and the working reliability of the spray pipe is ensured.
Claims (8)
1. The interface flexible treatment method of the integrally-formed composite material spray pipe comprises a thermal insulation layer, a flexible layer and a composite material shell, and is characterized in that the thermal insulation layer is formed by winding a phenolic resin-based composite material, the composite material shell is formed by laying or winding an epoxy resin-based material, the flexible layer is laid between the thermal insulation layer and the composite material shell, and the flexible layer is made of a thermal insulation elastic rubber material; and after all winding and laying work is finished, carrying out integral hot-pressing curing molding on the spray pipe.
2. The method of claim 1, wherein the thermally insulating elastomeric rubber material comprises any one of nitrile rubber, ethylene propylene diene monomer, or silicone rubber.
3. The interface flexible treatment method of the integrated molding composite nozzle according to claim 1, wherein the curing temperature of the hot-press curing molding is 160-170 ℃, and the curing time is 7-8.5 hours.
4. The interface flexibility processing method of the integrally formed composite nozzle as claimed in claim 1, wherein the thermal insulation layer is formed by obliquely winding a carbon fiber prepreg or a cloth tape prepreg.
5. The interface flexibility processing method of the integrally formed composite nozzle according to claim 1, wherein the composite shell is formed by laying or winding a carbon fiber prepreg or a cloth tape prepreg on the outer side of the thermal insulation layer.
6. The method of claim 1, wherein the thickness of the flexible layer is 0.2mm to 2mm.
7. The method for interfacial flexibility of an integrally molded composite nozzle of claim 4, wherein the thermal insulation layer is formed by winding prepreg tapes in a flat stack or winding prepreg tapes in an inclined stack at a winding angle of 5-15 °.
8. The method of claim 1, wherein the composite shell is flanged on a side of the composite shell adjacent to the inlet end of the nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210928359.XA CN115320132A (en) | 2022-08-03 | 2022-08-03 | Interface flexible processing method of integrally-formed composite material spray pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210928359.XA CN115320132A (en) | 2022-08-03 | 2022-08-03 | Interface flexible processing method of integrally-formed composite material spray pipe |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115320132A true CN115320132A (en) | 2022-11-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210928359.XA Pending CN115320132A (en) | 2022-08-03 | 2022-08-03 | Interface flexible processing method of integrally-formed composite material spray pipe |
Country Status (1)
| Country | Link |
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| CN (1) | CN115320132A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118046592A (en) * | 2024-04-15 | 2024-05-17 | 上海复合材料科技有限公司 | Pipe array structure and manufacturing method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111136935A (en) * | 2019-12-19 | 2020-05-12 | 航天特种材料及工艺技术研究所 | Strain coordination layer for integrated integral molding of ablation and heat protection structure, preparation method and application thereof |
| CN114198223A (en) * | 2021-11-29 | 2022-03-18 | 湖北航泰科技有限公司 | One-step curing molding full-composite engine spray pipe |
| CN114311870A (en) * | 2021-12-31 | 2022-04-12 | 湖北三江航天红阳机电有限公司 | Heat-proof and heat-insulating double-gradient functional composite material and preparation method thereof |
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2022
- 2022-08-03 CN CN202210928359.XA patent/CN115320132A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111136935A (en) * | 2019-12-19 | 2020-05-12 | 航天特种材料及工艺技术研究所 | Strain coordination layer for integrated integral molding of ablation and heat protection structure, preparation method and application thereof |
| CN114198223A (en) * | 2021-11-29 | 2022-03-18 | 湖北航泰科技有限公司 | One-step curing molding full-composite engine spray pipe |
| CN114311870A (en) * | 2021-12-31 | 2022-04-12 | 湖北三江航天红阳机电有限公司 | Heat-proof and heat-insulating double-gradient functional composite material and preparation method thereof |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118046592A (en) * | 2024-04-15 | 2024-05-17 | 上海复合材料科技有限公司 | Pipe array structure and manufacturing method thereof |
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Effective date of registration: 20221223 Address after: 444200 Wangjia Industrial Park, Yichang City, Hubei Province Applicant after: HUBEI HANGTAI TECHNOLOGY Co.,Ltd. Applicant after: THE GENERAL DESIGNING INSTITUTE OF HUBEI SPACE TECHNOLOGY ACADEMY Address before: 444200 Wangjia Industrial Park, Yichang City, Hubei Province Applicant before: HUBEI HANGTAI TECHNOLOGY Co.,Ltd. |