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
- Publication number
- 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
- Authority
- CN
- China
- Prior art keywords
- composite material
- layer
- winding
- flexible
- interface
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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)
- Application Of Or Painting With Fluid Materials (AREA)
- Laminated Bodies (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 |
Family
ID=83922130
Family Applications (1)
| 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 |
|---|---|
| CN (1) | CN115320132A (en) |
-
2022
- 2022-08-03 CN CN202210928359.XA patent/CN115320132A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11208904B2 (en) | Method for manufacturing a vane from a composite material with a fitted metal leading edge for a gas turbine | |
| JP5931906B2 (en) | Method of forming a composite structure with a flange | |
| US9248612B2 (en) | Containment case and method of manufacture | |
| KR101565191B1 (en) | Method of producing a nozzle or a divergent nozzle element made of a composite | |
| EP1092529A1 (en) | Selectively flexible caul | |
| US7922957B2 (en) | Method for forming composite components and tool for use therein | |
| CN112265347A (en) | Structural bearing-ablation heat-proof integrated composite material and preparation method thereof | |
| WO2008056161A2 (en) | Foamed tools | |
| CN109822949B (en) | Preparation method of light sandwich structure long row cover for rocket | |
| CN112249285B (en) | Propeller and forming method | |
| US20220402223A1 (en) | Method for closing an injection-moulding mould using anti-nip tapes | |
| JPWO2019188195A1 (en) | Manufacturing method of fiber reinforced plastic | |
| CN114198223B (en) | One-step curing formed full composite material engine spray pipe | |
| CN113427793A (en) | High-strength high-temperature-resistant composite material air inlet channel and forming method thereof | |
| CN111086128A (en) | Core mold for manufacturing solid rocket engine and forming method thereof | |
| CN115320132A (en) | Interface flexible processing method of integrally-formed composite material spray pipe | |
| RU2599752C1 (en) | Cylindrical casing and method of making cylindrical casing | |
| CN109849370B (en) | Processing method of rocket/missile engine interstage connection structure | |
| CN112277209A (en) | Forming method for repairing process of fiber-wound engine shell body model | |
| CN114055865B (en) | Forming method of fiber preform of longitudinal corrugated heat shield made of ceramic matrix composite | |
| CN114670470A (en) | Bismaleimide resin carbon fiber winding, curing and forming process | |
| US10906267B2 (en) | Composite structure | |
| CN113669558B (en) | Heat insulation tile based on resin-based carbon foam and preparation method thereof | |
| CN110293691B (en) | Manufacturing method of impact-resistant carbon fiber composite machine head cover | |
| US20230366467A1 (en) | Method of producing flexible seals and flexible seals produced therefrom |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
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. |
|
| TA01 | Transfer of patent application right |