CN114198223A - One-step curing molding full-composite engine spray pipe - Google Patents
One-step curing molding full-composite engine spray pipe Download PDFInfo
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- CN114198223A CN114198223A CN202111430166.3A CN202111430166A CN114198223A CN 114198223 A CN114198223 A CN 114198223A CN 202111430166 A CN202111430166 A CN 202111430166A CN 114198223 A CN114198223 A CN 114198223A
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- winding
- layer
- composite material
- insulation layer
- throat
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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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
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/56—Winding and joining, e.g. winding spirally
- B29C53/566—Winding and joining, e.g. winding spirally for making tubular articles followed by compression
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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
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/56—Winding and joining, e.g. winding spirally
- B29C53/58—Winding and joining, e.g. winding spirally helically
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/974—Nozzle- linings; Ablative coatings
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- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention relates to a one-step curing molding full composite material engine nozzle, which comprises a throat lining, a convergence section, a heat insulation layer, an inner ablation layer and a composite material shell, wherein the throat lining is used as an initial surface layer, the convergence section, the ablation layer, the heat insulation layer and the composite material shell are sequentially formed into the nozzle in a rotating mode from inside to outside, and the whole body is subjected to one-step hot-pressing curing molding after all winding operations are finished; the convergence section is formed by integrally winding a carbon fiber cloth tape prepreg; the ablation layer is formed by winding fibers or cloth belts on the throat liner and the mold; the thermal insulation layer is formed by obliquely winding fiber or cloth tape prepreg on the outer side of the ablation layer; the composite material shell is formed by laying or winding fibers or cloth tapes on the outer side of the heat insulation layer. The invention completes the curing of different structures and functional layers of the composite material spray pipe at one time through the co-curing technology of the transition structure resin, and the interface has no chemical structural mutation, thereby improving the interface strength, having no debonding risk and simultaneously shortening the production period of the full composite material spray pipe.
Description
Technical Field
The invention relates to the technical field of solid rocket engines, in particular to a one-step curing-molded all-composite engine jet pipe.
Background
The engine jet pipe is the worst part of the working environment of the solid rocket engine, and more than 80% of faults of the solid rocket engine appear in the jet pipe according to incomplete statistics. The engine jet pipe needs to bear the scouring and ablation of high temperature of more than 3000 ℃, pressure of hundreds of atmospheres and high temperature, pressure and high speed gas of several Mach in the working process, so the engine jet pipe is a structural component (needing to bear extremely high pressure) and a functional component (needing to resist the scouring and ablation of high temperature, high pressure and high speed gas). For the reasons mentioned above, the solid rocket engine nozzle is very complex and consists of a functional layer (throat lining, convergent section, ablation layer and thermal insulation layer) and a structural layer (bearing shell), wherein the functional layer mainly plays a role in ablation resistance and thermal insulation, and the structural layer mainly plays a role in structural bearing.
The functional layer and the structural layer of the traditional engine nozzle are formed by adopting an assembly mode, and the traditional engine nozzle mainly comprises 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 bonding. On one hand, the forming mode has more assembly gaps, so that the air leaping in the working process of the spray pipe 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 invention discloses a manufacturing method for replacing an assembled nozzle with an integral nozzle, and provides a manufacturing method for replacing the assembled nozzle with the integral nozzle in CN 106979095A. The Z-direction reinforcement and convergent section erosion protection of integrally molded composite nozzles is further described using new patents ZL 201721734657.6 and ZL 201820739442.1. However, these integrally formed systems have a multi-step curing process, which can cause the integrally formed composite nozzle to suffer from the following two disadvantages:
(1) in the later curing process of multi-step curing, the thermal expansion coefficients of the previously cured functional structure layers are different, and a larger thermal stress exists in the later curing process, so that the interface layer is damaged;
(2) because the time consumption of curing and processing in the production process of the spray pipe is very large, the production efficiency of the spray pipe is greatly reduced due to the increase of curing and processing procedures.
In view of the disadvantages of multi-step curing processes, it is desirable to find a new curing process to optimize the manufacturing process and improve the operational reliability of the engine nozzle.
Disclosure of Invention
Aiming at the problem of multistep curing and multistep processing of the existing integrally-formed composite material spray pipe, the invention adopts the co-curing technology of the transition structure resin to finish curing of different structures and functional layers of the composite material spray pipe at one time, thereby avoiding the problems of thermal expansion stress and unreliable curing interface caused by repeated curing of the full composite material spray pipe, simultaneously reducing the production period of the full composite material spray pipe, and greatly improving the production capacity and the working reliability of the full composite material spray pipe.
In order to achieve the purpose, the invention provides a one-step curing-formed all-composite engine nozzle which comprises a throat lining, a convergence section, a heat insulation layer, an inner ablation layer and a composite material shell, wherein the throat lining is used as an initial surface layer, the convergence section, the ablation layer, the heat insulation layer and the composite material shell are sequentially formed into the nozzle from inside to outside in a rotating mode, and after all winding (laying) 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 a carbon fiber cloth tape prepreg;
the ablation layer is formed by winding fibers or cloth belts on the throat liner and the mold;
the thermal insulation layer is formed by obliquely winding fiber or cloth tape prepreg on the outer side of the ablation layer;
the composite material shell is formed by laying or winding fibers or cloth tapes on the outer side of the heat insulation layer.
After all winding work is finished, the spray pipe is subjected to integral hot-pressing curing molding, the curing temperature is preferably 160-170 ℃, and the curing time is 7.5-8.5 hours.
The resin matrix of the carbon fiber cloth tape prepreg used in the convergence section is phenolic resin, the resin matrix of the cloth tape prepreg used in the ablation layer is phenolic resin, the resin matrix of the high-silica cloth prepreg used in the thermal insulation layer is phenolic resin, and the resin matrix of the cloth tape prepreg used in the composite material shell is epoxy modified phenolic resin; the phenolic resin and the epoxy modified phenolic resin mutually permeate and diffuse during curing to form a gradient interface of the phenolic-epoxy modified phenolic resin.
Preferably, the throat diameter of the nozzle is 5-500mm, and the outer diameter of the outlet is 50-2000 mm.
Preferably, the convergent section is formed by flat-lay winding of prepreg tapes or by diagonal lay winding at a winding angle of 5 ° to 15 °.
Preferably, the ablation layer is formed by flat-lay winding of prepreg tapes or by oblique-lay winding at a winding angle of 5 ° to 15 °.
Preferably, the insulation layer is formed by winding prepreg tapes in a flat stack or in an oblique stack at a winding angle of 5 ° to 15 °.
Preferably, the density of the throat insert is 1.70g/cm3To 1.90g/cm3The throat diameter is 10-500 mm.
Preferably, one side of the composite material shell close to the inlet end of the spray pipe is provided with a flange.
The once-formed all-composite material spray pipe provided by the invention has the following beneficial effects:
(1) the spray pipe is formed by one-step curing, the production process is simple, the production period is short, and no structural defect exists;
(2) the spray pipe is cured only once in the production process, so that the defect that the thermal stress of all parts of the full-composite spray pipe is not matched due to multiple curing is avoided, a multiple-curing interface is not generated, and the safety coefficient is improved; through verification, the failure coefficient of a segmented curing interface of the spray pipes made of the same material is 0.5, and if the one-time co-curing method is adopted, the failure coefficient of the interface is reduced to 0.2, and the safety is improved by 2.5 times.
(3) The interface layer adopts a co-curing technology of transition resin, the interface is made of gradient resin materials, the resin matrix used by the inner structure is phenolic resin, the resin matrix adopted by the composite shell is epoxy modified phenolic resin, and the phenolic resin and the epoxy modified phenolic resin mutually permeate and diffuse during curing to form a phenolic-epoxy modified phenolic resin gradient interface without chemical structural mutation, so that the interface strength is improved, and the debonding risk is avoided. According to verification, under the condition of bearing the same pressure of 6MPa, the failure coefficient of the interface shear direction of the phenolic structure and the epoxy structure of the spray pipe prepared by adopting the sectional curing at the same position point is 0.7, while the failure coefficient of the interface shear direction of the spray pipe prepared by the invention is 0.4, so that the safety is improved by 1.75 times.
Drawings
FIG. 1 is a schematic view of the throat insert, convergent section and core assembly of the present invention;
FIG. 2 is a schematic illustration of ablation layer winding;
FIG. 3 is a schematic view of insulation wrap;
FIG. 4 is a schematic of composite shell layup.
Description of the symbols: 1-winding core mould, 2-throat liner, 3-convergence section, 4-ablation layer, 5-thermal insulation layer and 6-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.
It should be noted that in the description of the present invention, the terms "lateral", "longitudinal", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. The position of the flange, the winding angle, and other relevant conditions can be adjusted accordingly as required, and the illustrated position of the flange, the winding angle, and other conditions are not to be construed as limiting the present invention.
The once-cured and molded all-composite engine nozzle comprises a throat insert, a convergence section, a heat insulation layer, an inner ablation layer and a composite material shell, wherein as shown in figures 1-4, 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 lining is used as an initial surface layer, the convergent section, the ablation layer, the heat insulation 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-time hot-pressing curing forming through an autoclave;
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, as shown in fig. 1, the resin matrix used by the carbon fiber cloth tape prepreg is phenolic resin; the convergent section is formed by flat-lapping winding of prepreg tapes or obliquely lapping winding at a winding angle of 5-15 degrees, and the winding angle of the convergent section is 10 degrees in the embodiment.
The ablation layer is formed by winding carbon fiber cloth tape prepreg on the throat liner and the mould, and the resin matrix used by the carbon fiber cloth tape prepreg of the ablation layer is phenolic resin; as shown in fig. 2, the ablation layer is wound in a direction starting from the convergent section and winding to the right. The ablation layer is formed by flat-lapping winding of prepreg tapes or obliquely lapping winding at a winding angle of 5-15 degrees, and the winding angle of the ablation layer is 10 degrees in the embodiment.
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; as shown in fig. 3, the insulation layer is wound in a direction from right to left gradually approaching the convergent section. The thermal insulation layer is formed by winding prepreg cloth tapes in a flat-overlapping mode or winding the prepreg cloth tapes in a diagonal-overlapping mode at a winding angle of 5-15 degrees, and the winding angle of the thermal insulation layer is 10 degrees in the embodiment.
The composite material shell is formed by laying or winding fibers or cloth tapes on the outer side of the thermal insulation layer, as shown in fig. 4, the resin matrix used by the carbon fiber cloth tape prepreg is epoxy modified phenolic resin. The composite material shell is wound and formed at a winding angle of 50-70 degrees. Through shaping with certain winding angle, influence each direction's mechanical distribution, the low longitudinal strength of winding angle is high, and the high annular strength of winding angle is high. And a flange is arranged on one side of the composite material shell close to the inlet end of the spray pipe.
After all winding work is finished, the spray pipe is subjected to integral hot-pressing curing molding, the maximum curing temperature is 160-170 ℃, and the curing time is 7.5-8.5 hours. The curing temperature of the present example was 165 ℃ and the curing time was 8 hours.
The throat diameter of the spray pipe is 5-500mm, 300mm is selected in the embodiment, the outer diameter of the outlet is 50-2000mm, and 1000mm is selected in the embodiment.
The density of the throat insert is 1.70g/cm3 to 1.90g/cm3In this example, the throat insert density is 1.8g/cm3The throat diameter is 10-500mm, and the throat diameter of the throat insert in the embodiment is 300 mm.
Experiments prove that the sectional curing interface failure coefficient of the spray pipes made of the same material is 0.5, and if the one-time co-curing preparation method disclosed by the invention is adopted, the interface failure coefficient is reduced to 0.2, and the safety is improved by 2.5 times.
Experiments prove that the failure coefficient of the interface shear direction of the phenolic structure and the epoxy structure of the spray pipe prepared by adopting the segmented curing is 0.7 at the same position point under the condition of bearing the same pressure of 6MPa, while the failure coefficient of the interface shear direction of the spray pipe prepared by the invention is 0.4, so that the safety is improved by 1.75 times.
Claims (8)
1. The once-cured and molded all-composite engine nozzle is characterized by comprising a throat lining, a convergence section, a heat insulation layer, an inner ablation layer and a composite material shell, wherein the throat lining is used as an initial surface layer, the convergence section, the ablation layer, the heat insulation layer and the composite material shell are sequentially formed into the nozzle in a rotating mode from inside to outside, and the whole nozzle is subjected to once hot-pressing curing molding after all winding operations are completed;
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 a carbon fiber cloth tape prepreg;
the ablation layer is formed by winding fiber or cloth tape prepreg on the throat liner and the head reinforcing layer;
the thermal insulation layer is formed by obliquely winding fiber or cloth tape prepreg on the outer side of the ablation layer;
the composite material shell is formed by laying or winding a fiber or cloth tape prepreg on the outer side of the thermal insulation layer;
and after all winding work is finished, integrally carrying out one-time hot-pressing curing molding on the spray pipe.
2. The once cured and formed all-composite engine nozzle according to claim 1, wherein the resin matrix of the carbon fiber tape prepreg used in the convergent section is phenolic resin, the resin matrix of the tape prepreg used in the ablation layer is phenolic resin, the resin matrix of the high-silica cloth prepreg used in the thermal insulation layer is phenolic resin, and the resin matrix of the tape prepreg used in the composite shell is epoxy modified phenolic resin.
3. The once cured all composite engine nozzle of claim 1, wherein the nozzle has a throat diameter of 5-500mm and an outlet outer diameter of 50-2000 mm.
4. An erosion resistant composite engine nozzle as defined in claim 1, wherein said convergent section is formed by lay flat winding of prepreg tapes or lay diagonal winding at a winding angle of 5 ° to 15 °.
5. The once cured fully composite engine nozzle of claim 1, wherein said ablative layer is formed by lay-up winding of prepreg tapes flat or at a winding angle of 5 ° to 15 ° diagonal.
6. The once cured fully composite engine nozzle of claim 1, wherein the insulation layer is formed by lay-up winding of prepreg tapes flat or at a winding angle of 5 ° to 15 ° diagonal.
7. The once cured full composite engine nozzle of claim 1, wherein said throat insert has a density of 1.70g/cm3To 1.90g/cm3The throat diameter is 10-500 mm.
8. The one-shot all composite engine nozzle of any one of claims 1 to 7, wherein the composite housing is flanged on a side adjacent to the nozzle inlet end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111430166.3A CN114198223B (en) | 2021-11-29 | 2021-11-29 | One-step curing formed full composite material engine spray pipe |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111430166.3A CN114198223B (en) | 2021-11-29 | 2021-11-29 | One-step curing formed full composite material engine spray pipe |
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| CN114198223A true CN114198223A (en) | 2022-03-18 |
| CN114198223B CN114198223B (en) | 2023-09-15 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114876673A (en) * | 2022-04-12 | 2022-08-09 | 西安零壹空间科技有限公司 | Low-cost ablation-resistant embedded spray pipe and machining method thereof |
| CN115450798A (en) * | 2022-10-31 | 2022-12-09 | 北京中科宇航技术有限公司 | Long-time working solid rocket engine and long tail jet pipe thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1198491A (en) * | 1967-07-17 | 1970-07-15 | Hitco | Unitary Bodies an Method of Making the Same |
| CN208364259U (en) * | 2018-05-18 | 2019-01-11 | 湖北航泰科技有限公司 | The all- composite engine jet pipe of protection against erosion |
| 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 |
-
2021
- 2021-11-29 CN CN202111430166.3A patent/CN114198223B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1198491A (en) * | 1967-07-17 | 1970-07-15 | Hitco | Unitary Bodies an Method of Making the Same |
| CN208364259U (en) * | 2018-05-18 | 2019-01-11 | 湖北航泰科技有限公司 | The all- composite engine jet pipe of protection against erosion |
| 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 |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114876673A (en) * | 2022-04-12 | 2022-08-09 | 西安零壹空间科技有限公司 | Low-cost ablation-resistant embedded spray pipe and machining method thereof |
| CN114876673B (en) * | 2022-04-12 | 2024-03-29 | 西安零壹空间科技有限公司 | Low-cost ablation-resistant embedded spray pipe and processing method thereof |
| CN115450798A (en) * | 2022-10-31 | 2022-12-09 | 北京中科宇航技术有限公司 | Long-time working solid rocket engine and long tail jet pipe thereof |
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|---|---|
| CN114198223B (en) | 2023-09-15 |
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