CN110744832A - Bonding forming method for large-opening metal end socket of composite material shell - Google Patents
Bonding forming method for large-opening metal end socket of composite material shell Download PDFInfo
- Publication number
- CN110744832A CN110744832A CN201911127421.XA CN201911127421A CN110744832A CN 110744832 A CN110744832 A CN 110744832A CN 201911127421 A CN201911127421 A CN 201911127421A CN 110744832 A CN110744832 A CN 110744832A
- Authority
- CN
- China
- Prior art keywords
- metal end
- bonding
- end socket
- molding method
- shell
- 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
-
- 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
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
-
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
- B29C70/228—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being stacked in parallel layers with fibres of adjacent layers crossing at substantial angles
-
- 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
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3097—Cosmonautical vehicles; Rockets
Abstract
The invention discloses a bonding and forming method for a large-opening metal end socket of a composite material shell, which effectively solves the problem of low-pressure explosion of the large-opening shell metal end socket, has reliable bonding structure and low cost, can be connected without fasteners, reduces the redundant quality and the production and material cost of an engine, and increases the charge space and the pressure-bearing capacity of the shell. The invention ensures the stability of the composite shell structure under complex working load, has relatively simple process route, and can meet the bearing requirements of the shell on strength and rigidity.
Description
Technical Field
The invention relates to the technical field of carbon fiber composite material solid rocket engine shells, in particular to a bonding and forming method for a large-opening metal seal head of a carbon fiber engine shell.
Background
Chinese patent "manufacturing method of high temperature resistant fiber wound composite shell", publication No. CN 104354436 a, publication No. 2015.02.18, discloses a manufacturing method of high temperature resistant fiber wound composite shell.
The carbon fiber composite engine shell has excellent performance, but the cost is higher. In the traditional carbon fiber composite shell forming process, the shell barrel section and the joint are simultaneously cured and formed, the process route is complex, the quality batch is unstable, and the sealing part needs to be additionally reinforced. Especially for a large-opening end enclosure shell, the annular strain at the edge of a polar hole is extremely large, low-pressure explosion is very easy to occur when the shell is internally pressed, the end enclosure is integrally damaged due to sudden release of the great strain energy, and the redundant quality and the production cost of the shell are increased by adopting an end enclosure reinforcement process. In the design of the shell, the stability and the reliability of the shell under various complex loads are comprehensively considered, the combustion chamber shell is used as a main pressure bearing structure of an engine, and the safety and the reliability of the shell under the working load are important, so that the overall performance of the missile is influenced. Researches show that the metal end socket of the large-opening composite material shell is formed by adopting a bonding process without connecting by fasteners, the process is simple and easy to implement, the production cost is low, the redundant quality of an engine is effectively reduced, the charge space is increased, and the pressure-bearing capacity of the shell is obviously improved compared with that of the traditional formed end socket.
Disclosure of Invention
Aiming at the problems in the prior art, the invention aims to provide the bonding and forming method of the composite material shell large-opening metal end socket, which has simple and feasible process, can effectively reduce the production cost and the redundancy quality of the shell and improve the pressure-bearing and charge capacity of the shell.
In order to achieve the purpose, the invention discloses a bonding and molding method of a large-opening metal end socket of a composite material shell, which comprises the following steps of:
s1, preparing a cylinder section of the carbon fiber composite material by adopting a core mold, and processing two coaxial radial holes at each end of the cylinder section;
s2, preparing a metal end enclosure, and processing an annular groove on the outer wall of the metal end enclosure, wherein the radial hole is communicated with the annular groove;
s3, adhesive preparation: epoxy resin according to mass ratio: curing agent 1: 1, adding a filler after uniformly mixing, and controlling the operating temperature to adjust the viscosity of the adhesive to be less than 0.4 pas.
S4, pre-curing: polishing and sandblasting the metal end socket, uniformly coating the prepared adhesive on the outer wall of the metal end socket, assembling in place under the action of a tool and a press, preserving heat at 95 ℃ for 3 hours to complete pre-curing, and ensuring that the annular groove forms a sealed cavity;
s5, injecting adhesive into the annular groove from one of the radial holes, and vacuumizing from the other radial hole until the sealing cavity is completely filled with the adhesive;
s6, standing at room temperature for at least 12h, and then preserving heat at 80 ℃ for 3h for curing;
and S7, naturally cooling after solidification, relieving the pressure of the press machine, and dismantling the tool.
Preferably, in S1, after the prepreg is cut, the prepreg is wound around the core mold, and the winding is performed alternately at 45 °, 90 °, -45 °, and 90 °, and the winding is performed alternately 5 times, where the angle is an angle between the prepreg and the axis of the core mold; after winding, starting curing, heating to 95 ℃ at the heating rate of 1-2 ℃ for heat preservation for 3h, then heating to 125 ℃ for heat preservation for 2h, then heating to 150 ℃ for heat preservation for 6h, and finally naturally cooling, curing and forming; and machining the formed cylinder section to ensure the matching size with the metal end enclosure.
Preferably, in S2, the depth of the annular groove is 0.9mm to 1.5 mm.
Preferably, in S2, if the width of the annular groove is a, and the distance from the end face of the cylinder section to the bottom face of the metal end socket is b, then a: b is 1: (1.15-1.17).
Preferably, in S4, the press continuously applies a contact pressure of 0.03MPa to 0.05MPa during the pre-curing process.
Preferably, in S5, the radial hole for injecting the adhesive faces vertically upward, and the other radial hole faces vertically downward.
Preferably, after S7, the final-cured shell is subjected to a DR non-destructive inspection to determine the structural continuity of the bonded area, which is not allowed to have continuous holes.
The invention has the beneficial effects that: the resin bonding process of the carbon fiber shell barrel section and the metal end socket effectively solves the problem of low-pressure blasting of the metal end socket of the large-opening shell, has reliable bonding structure and low cost, can be connected without fasteners, reduces the redundant quality and the production and material cost of an engine, and increases the charge space and the pressure-bearing capacity of the shell. The invention ensures the stability of the composite shell structure under complex working load, has relatively simple process route, and can meet the bearing requirements of the shell on strength and rigidity.
The manufacturability and the structural designability of the product are verified, the product has good performance in air tightness test, hydraulic test, static test and multiple ground test examinations, the bonding structure of the metal end socket is reliable, and the overall design requirement is met.
Drawings
FIG. 1 is a schematic view of the overall structure of the barrel section and the metal end socket of the present invention
FIG. 2 is an enlarged view of the point A in FIG. 1
In the figure: the cylinder section 1, the radial hole 2, the metal end enclosure 3 and the annular groove 4.
Detailed Description
The technical solutions of the present invention (including the preferred ones) are further described in detail by way of fig. 1 to 2 and enumerating some alternative embodiments of the present invention. It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without any inventive step, are within the scope of the present invention.
As shown in fig. 1 and 2, the bonding and molding method of the composite material shell large-opening metal end socket comprises the following steps:
s1, preparing a cylinder section 1 made of carbon fiber composite material on a water-soluble sand core mold, and processing two coaxial radial holes 2 at each end of the cylinder section 1; cutting the prepreg, winding the prepreg on a core mold in an alternate mode of 45 degrees, 90 degrees, -45 degrees and 90 degrees for 5 times during winding, wherein the angle is an included angle between the prepreg and the axis of the core mold; after winding, starting curing, heating to 95 ℃ at the heating rate of 1-2 ℃ for heat preservation for 3h, then heating to 125 ℃ for heat preservation for 2h, then heating to 150 ℃ for heat preservation for 6h, and finally naturally cooling, curing and forming; and machining the formed cylinder section to ensure the matching size with the metal end enclosure 3.
In this example, a total of 20 layers were wound: winding one layer at 45 degrees, winding one layer at 90 degrees in a circumferential direction, winding one layer at-45 degrees in a circumferential direction, winding one layer at 90 degrees in a circumferential direction, and winding 20 layers of prepreg in total by … … in this way. Each layer of prepreg outer layer with an acute winding angle is wound in a layer of hoop direction, and the prepreg is compacted and fixed through fiber tension. The prepregs are allowed to overlap, the overlap width not exceeding 2 mm.
S2, preparing a metal end enclosure 3, processing an annular groove 4 on the outer wall of the metal end enclosure 3, and communicating the radial hole 2 with the annular groove 4; the depth of the annular groove is 0.9 mm-1.5 mm; the width of ring channel is a, and the distance of section of thick bamboo terminal surface to the bottom surface of metal head is b, then a: b is 1: (1.15-1.17).
S3, adhesive preparation: epoxy resin according to mass ratio: curing agent 1: 1, adding a filler after uniformly mixing, and controlling the operating temperature to adjust the viscosity of the adhesive to be less than 0.4 pas.
S4, pre-curing: polishing and sandblasting the metal end socket, uniformly coating the prepared adhesive on the outer wall of the metal end socket, assembling in place under the action of a tool and a press, preserving heat at 95 ℃ for 3 hours to complete pre-curing, and ensuring that the annular groove forms a sealed cavity; the press machine continuously applies a contact pressure of 0.03MPa to 0.05MPa in the pre-curing process.
And S5, injecting adhesive into the annular groove from one radial hole, and vacuumizing from the other radial hole until the sealed cavity is completely filled with the adhesive. The radial hole for injecting the adhesive is vertically upward, and the other radial hole is vertically downward
And S6, standing at room temperature for at least 12h, and then preserving heat at 80 ℃ for 3h for curing.
And S7, naturally cooling after solidification, relieving the pressure of the press machine, and dismantling the tool.
And S8, performing DR nondestructive testing on the finally solidified and molded shell to determine the structural continuity of the bonding area, wherein the bonding area does not allow continuous holes.
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and any modification, combination, replacement, or improvement made within the spirit and principle of the present invention is included in the scope of the present invention.
Claims (7)
1. A method for bonding and molding a large-opening metal end socket of a composite shell is characterized by comprising the following steps:
s1, preparing a cylinder section of the carbon fiber composite material by adopting a core mold, and processing two coaxial radial holes at each end of the cylinder section;
s2, preparing a metal end enclosure, and processing an annular groove on the outer wall of the metal end enclosure, wherein the radial hole is communicated with the annular groove;
s3, adhesive preparation: epoxy resin according to mass ratio: curing agent 1: 1, adding a filler after uniformly mixing, and controlling the operating temperature to adjust the viscosity of the adhesive to be less than 0.4 pas;
s4, pre-curing: polishing and sandblasting the metal end socket, uniformly coating the prepared adhesive on the outer wall of the metal end socket, assembling in place under the action of a tool and a press, preserving heat at 95 ℃ for 3 hours to complete pre-curing, and ensuring that the annular groove forms a sealed cavity;
s5, injecting adhesive into the annular groove from one of the radial holes, and vacuumizing from the other radial hole until the sealing cavity is completely filled with the adhesive;
s6, standing at room temperature for at least 12h, and then preserving heat at 80 ℃ for 3h for curing;
and S7, naturally cooling after solidification, relieving the pressure of the press machine, and dismantling the tool.
2. The bonding and molding method for the large-opening metal end socket of the composite shell as claimed in claim 1, wherein the bonding and molding method comprises the following steps: in S1, cutting the prepreg, winding the prepreg on the core mold, and alternately winding for 5 times in an alternate mode of 45 degrees, 90 degrees, -45 degrees and 90 degrees, wherein the angle is an included angle between the prepreg and the axis of the core mold; after winding, starting curing, heating to 95 ℃ at the heating rate of 1-2 ℃ for heat preservation for 3h, then heating to 125 ℃ for heat preservation for 2h, then heating to 150 ℃ for heat preservation for 6h, and finally naturally cooling, curing and forming; and machining the formed cylinder section to ensure the matching size with the metal end enclosure.
3. The bonding and molding method for the large-opening metal end socket of the composite shell as claimed in claim 1, wherein the bonding and molding method comprises the following steps: in S2, the depth of the annular groove is 0.9 mm-1.5 mm.
4. The bonding and molding method for the large-opening metal end socket of the composite shell as claimed in claim 1 or 3, wherein the bonding and molding method comprises the following steps: in S2, the width of the annular groove is a, the distance from the end face of the cylinder section to the bottom face of the metal end socket is b, and a: b is 1: (1.15-1.17).
5. The bonding and molding method for the large-opening metal end socket of the composite shell as claimed in claim 1, wherein the bonding and molding method comprises the following steps: and S4, continuously applying a contact pressure of 0.03-0.05 MPa to the press machine in the pre-curing process.
6. The bonding and molding method for the large-opening metal end socket of the composite shell as claimed in claim 1, wherein the bonding and molding method comprises the following steps: in S5, the radial hole into which the adhesive is injected faces vertically upward, and the other radial hole faces vertically downward.
7. The bonding and molding method for the large-opening metal end socket of the composite shell as claimed in claim 1, wherein the bonding and molding method comprises the following steps: after S7, the final-cured shell is subjected to a DR non-destructive inspection to determine the structural continuity of the bonded area, which is not allowed to have continuous holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911127421.XA CN110744832A (en) | 2019-11-18 | 2019-11-18 | Bonding forming method for large-opening metal end socket of composite material shell |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911127421.XA CN110744832A (en) | 2019-11-18 | 2019-11-18 | Bonding forming method for large-opening metal end socket of composite material shell |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110744832A true CN110744832A (en) | 2020-02-04 |
Family
ID=69283571
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911127421.XA Pending CN110744832A (en) | 2019-11-18 | 2019-11-18 | Bonding forming method for large-opening metal end socket of composite material shell |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110744832A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113250858A (en) * | 2021-04-21 | 2021-08-13 | 西安英利科电气科技有限公司 | Winding structure and method for large-opening solid rocket combustion chamber |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620693A (en) * | 2016-01-28 | 2016-06-01 | 安阳市腾飞高分子复合材料有限公司 | Novel pressure-resistant cabin body made from carbon fiber macromolecular composite materials and manufacturing technology of novel pressure-resistant cabin body |
| CN105666855A (en) * | 2016-03-28 | 2016-06-15 | 武汉理工大学 | Glue joint connecting structure of composite round pipe |
-
2019
- 2019-11-18 CN CN201911127421.XA patent/CN110744832A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620693A (en) * | 2016-01-28 | 2016-06-01 | 安阳市腾飞高分子复合材料有限公司 | Novel pressure-resistant cabin body made from carbon fiber macromolecular composite materials and manufacturing technology of novel pressure-resistant cabin body |
| CN105666855A (en) * | 2016-03-28 | 2016-06-15 | 武汉理工大学 | Glue joint connecting structure of composite round pipe |
Non-Patent Citations (1)
| Title |
|---|
| 张国玉等: "《图解汽车维修胶粘技术》", 31 March 2004, 四川科学技术出版社 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113250858A (en) * | 2021-04-21 | 2021-08-13 | 西安英利科电气科技有限公司 | Winding structure and method for large-opening solid rocket combustion chamber |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105003355B (en) | Solid rocket engine with high thrust ratio and manufacturing method thereof | |
| EP2612749B1 (en) | Method for manufacturing a composite fan inlet housing | |
| CN110239112A (en) | A kind of processing method of composite material shape for hat Material Stiffened Panel | |
| CN111120145B (en) | Shell structure of head prefabricated secondary winding composite material | |
| CN104175568B (en) | Manufacture the production method of carbon fiber arm support for concrete pump truck | |
| CN102729482A (en) | Composite heatproof bearing cylinder and preparation method thereof | |
| CN104552692B (en) | A kind of middle-size and small-size solid propellant rocket internal insulation bulge forming frock | |
| CN110744832A (en) | Bonding forming method for large-opening metal end socket of composite material shell | |
| CN113103480A (en) | Split type metal core die for winding large solid rocket engine shell | |
| KR100831309B1 (en) | Method for reinforcement manufacturing a composite sabot applying band/hoop lamination | |
| CN112249285B (en) | Propeller and forming method | |
| CA2606808C (en) | Device for injecting a resin into at least one fibre layer of a fibre- reinforced product to be manufactured | |
| US9669570B2 (en) | Process for injection moulding a composite part | |
| CN106337758B (en) | A kind of engine chamber dividing plate heat insulating construction and preparation method | |
| CN114559686B (en) | Forming preparation method of solid rocket engine fiber composite shell | |
| CN113581361B (en) | Pressure-resistant composite structure for long-term operation in deep sea and manufacturing method thereof | |
| US9033664B2 (en) | Blade for a turbine operating in water | |
| CN112412658B (en) | Combined core mold with medicine winding function | |
| CN104552802A (en) | Flexible joint manufacturing mould device | |
| CN108948663B (en) | Preparation method of missile launching frangible cover | |
| Uhara et al. | Study on the production of the flange by the centrifugal forming method (Part 1) | |
| CN114274557B (en) | Connection design and molding method of composite material cylindrical shell and metal component | |
| CN112895503B (en) | Method for forming small-diameter large-opening solid rocket engine shell | |
| CN107866989B (en) | Composite material energy absorption box and manufacturing method thereof | |
| CN117231584B (en) | Carbon fiber hydraulic cylinder body, forming process of cylinder body and hydraulic cylinder |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200204 |