CN102529131A - Manufacture method of launch tube - Google Patents
Manufacture method of launch tube Download PDFInfo
- Publication number
- CN102529131A CN102529131A CN2010106115316A CN201010611531A CN102529131A CN 102529131 A CN102529131 A CN 102529131A CN 2010106115316 A CN2010106115316 A CN 2010106115316A CN 201010611531 A CN201010611531 A CN 201010611531A CN 102529131 A CN102529131 A CN 102529131A
- Authority
- CN
- China
- Prior art keywords
- mould
- resin matrix
- prepreg
- die surface
- groove
- 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
Landscapes
- Moulding By Coating Moulds (AREA)
Abstract
The invention provides a manufacture method of an integrally-formed launch tube, which specifically comprises the steps of: firstly, manufacturing a columnar module which is provided with a lug boss or groove on the surface according to an inner cavity structure of the launch tube; secondly, filling fiber fabric resin matrix prepreg in the groove of the mould or spreading and coating the fiber fabric resin matrix prepreg on the outer surface of the mould until reaching the height slightly larger than the height of the lug boss on the mould; thirdly, winding and forming by using the fiber fabric resin matrix prepreg; fourthly, curing; and fifthly, demoulding. The manufacture method can be used for forming composite material cavity type parts, thus parts forming efficiency is increased.
Description
Technical field
The invention belongs to the preparation method of the launching tube of the technology of preparing of launching tube, particularly a kind of composite.
Background technology
Composite has been compared following advantage with metal material, little like density, and intensity is high, specific modulus is high, and damping vibration attenuation property is good, endurance, and fail-safety is good, and structure can integral one-step molding etc.Especially composite has anisotropy, makes material have good designability, can extensive use in multi-field.
General composite launching tube comprises cavity and internal structure, and forming method is that cavity and its inner structural members are separated manufacturing, again the two is assembled the structure that links into an integrated entity by certain required precision.Because cavity and inner structural members are separately made, and hand assembled, so complex forming technology separately, and the parts quality conformance can not get assurance, so there is following shortcoming in this kind process: 1. more, the complex process of operation, production efficiency are low; 2. consistency of product is poor, percent defective high; 3. there is accumulated error in assembling process, is difficult to satisfy the high precision design requirement; 4. for the less cavity type parts of internal diameter, assembly manipulation can't be realized in the inner operating space that does not have assembling.
Need increase the composite launching tube of coating for cavity inner surface, general adopt separately moulding after, the process of application inside coating again.Because the application uniformity is difficult for guaranteeing that so the cavity type component coating on inner surface that utilizes this kind process to produce is of poor quality, and adhesion property is lower that again owing to inside cavity structure and size restrictions, the application inside coating is difficult.
Summary of the invention
For solving the problem that composite emission cylindrical shell and its internal structure are separated manufacturing, multistep molding existence, the invention provides a kind of preparation method of launching tube of integrated molding.Concrete technical scheme is: the first step, according to the inner-cavity structure of launching tube, make the columnar mould that a surface has boss or groove; In second step, fill the deposited mold outer surface of groove or shop on the mould with fabric resin matrix prepreg, until reaching and a little more than the boss on the mould; The 3rd step, Wrapping formed with fabric resin matrix prepreg; In the 4th step, solidify; The 5th step, the demoulding.
For the composite cavity type component that need increase coating at cavity inner surface, second step after die surface apply to promote demoulding material at die surface application inside coating, and curing or semi-solid preparation.
Adopt that operation significantly reduces behind the integrated molding, technology is simple, product cavity structure and size are replicated in mould, and high conformity need not to carry out the machined assembling, has reduced product cost, and effect is good.
Coating and cavity type component take integrated molding not exist the application coating to receive the problem of inside cavity structure and size restrictions, and because of Wrapping formed thrust effect, the coating surface quality is replicated in die surface fully, and surface quality is high, strong adhesion.
Description of drawings
Fig. 1 is a double helix guide rail composite launching tube structure in the band;
Fig. 2 is the cylindrical shell cross sectional representation after mould twines.
The specific embodiment
Double helix guide rail composite cylindrical shell and coated inside integral preparation method in 1 one kinds of bands of embodiment
Double helix guide rail composite launching tube body structure is as shown in Figure 1 in the band, comprises cylindrical shell 1 and double helix guide rail structure 2.Adopt the cylindrical shell cross section after mould of the present invention twines as shown in Figure 2, inner 3 is the mold sections shape, and dash area is the cross sectional shape of cylindrical shell 1; Cylindrical shell is about 3000mm, internal diameter 177mm, external diameter 185mm; Linearity is 0.15mm/1500mm, and cylindrical shell has 2 spiral-shaped guides along inwall, helicity 10 degree 30 minutes; Pitch 2203.6mm, guide rail spacing 130.5mm, the similar fillet in guide rail cross section is trapezoidal.The cylindrical shell guide rail adopts mould molding, guarantees shape face structure, size and positional precision in the launching tube by mould.Concrete preparation flow:
The first step is according to interior shape face design, the mfg. moulding die of cavity part, the cylinder that is shaped as band helical guideway groove of mould;
Second step, at the even brushing releasing agent of die surface, treat to smear next time again after a preceding releasing agent parches, be coated with altogether three times;
In the 3rd step, treat that releasing agent solidifies back application inside coating, at first about heating mould to 70 degree; And insulation a period of time; Make the entire die temperature evenly and reach 65 degree, at the even application one deck of die surface inside coating, coating layer thickness requires to confirm according to parts; Defectives such as the intact material of coating, bubble, pore; The mould of just application coating pushes curing oven and is cured then, solidify accomplish the back with 80 purpose sand paper with the fireproof paint outer surface scutching on the mould, the adhesion of raising raising itself and cylinder material;
The 4th step formed fabric resin matrix prepreg with high-strength glass fibre yarn or cloth impregnating resin, was paved with the guide-track groove of core with high-strength glass fibre textile resins matrix prepreg, and made the deposited prepreg in shop a little more than the mould periphery;
The 5th step; It is Wrapping formed on mould, to carry out part by the parts size precision requirement with material prepreg, at first twines with the dried yarn hoop of single bundle high-strength glass fibre, after an end twines the other end, twines Hui Yiduan from the other end again; Prepreg hoop with impregnating resin twines on the mould again then; Twine richly in the other end from an end, at last the high intensity glass fiber cloth of doing is twined richly to cylindrical shell, next circle presses the position of center line of a circle; Repeat to twine according to said sequence, up to reaching thickness requirement and reserving the following process surplus;
The 6th step, winding product and mould are sent into curing oven be cured, with the solidification temperature of 50-80 degree be cured 1-3 hour hardening time, make cylindrical cavity and internal guide rail one-body molded;
The 7th step, the core of one and Wrapping formed cylindrical shell are put into ingot stripper carry out the demoulding, by dimensional requirement double helix guide rail composite cylindrical shell in being with is carried out fine finishining again after the demoulding.
Claims (8)
1. the preparation method of a launching tube is characterized in that, specifically comprises:
The first step according to the inner-cavity structure of launching tube, is made the columnar mould that a surface has boss or groove;
In second step, fill the deposited mold outer surface of groove or shop on the mould with fabric resin matrix prepreg, until reaching and a little more than the boss on the mould;
The 3rd step, Wrapping formed with fabric resin matrix prepreg;
In the 4th step, solidify;
The 5th step, the demoulding.
2. the method for claim 1 is characterized in that, before second step, is coated with releasing agent at die surface.
3. method as claimed in claim 2 is characterized in that, before second step, after the die surface release agent application, evenly scribbles three layers of heat-resistant paint at die surface.
4. method as claimed in claim 3 is characterized in that, before die surface applies heat-resistant paint, mold heated to 70 is spent and maintenance a period of time.
5. method as claimed in claim 3 is characterized in that, die surface apply heat insulation material and solidify the back with 80 purpose sand paper with the fireproof paint outer surface scutching on the mould.
6. the method for claim 1 is characterized in that, fabric resin matrix prepreg is to form in resin matrix through the high strength glass fiber textile impregnation.
7. method as claimed in claim 6 is characterized in that, at first twines with the dried yarn hoop of single bundle high-strength glass fibre, and the prepreg hoop with impregnating resin twines on the mould again then, at last the high intensity glass fiber cloth hoop of doing is twined rich to cylindrical shell.
8. the method for claim 1 is characterized in that, the 4th step solidification temperature is the 50-80 degree, and be 1-3 hour hardening time.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010106115316A CN102529131A (en) | 2010-12-28 | 2010-12-28 | Manufacture method of launch tube |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010106115316A CN102529131A (en) | 2010-12-28 | 2010-12-28 | Manufacture method of launch tube |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102529131A true CN102529131A (en) | 2012-07-04 |
Family
ID=46337752
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010106115316A Pending CN102529131A (en) | 2010-12-28 | 2010-12-28 | Manufacture method of launch tube |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102529131A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103395194A (en) * | 2013-08-05 | 2013-11-20 | 河北东恒宇功能材料新技术有限公司 | Manufacture method for composite-material launch canister of high-altitude fire-extinguishing rocket |
| CN106152874A (en) * | 2016-07-12 | 2016-11-23 | 北京航天发射技术研究所 | Sandwich full composite material launching tube |
| CN110315778A (en) * | 2019-07-12 | 2019-10-11 | 北京航天新风机械设备有限责任公司 | A kind of forming method of high-precision great surface quality thermal protective coating |
| CN111023894A (en) * | 2019-12-04 | 2020-04-17 | 天津爱思达新材料科技有限公司 | Missile launching canister and preparation method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5054224A (en) * | 1990-11-19 | 1991-10-08 | The United States Of America As Represented By The Secretary Of The Army | Apparatus and method for a composite polymer rifling disposable gun tube |
| CN1106513A (en) * | 1994-02-07 | 1995-08-09 | 刘敬 | Laminated resin and fibre pipe and its mfg. method |
| US20040244257A1 (en) * | 2003-06-04 | 2004-12-09 | Degerness Michael K. | Composite structural member |
| US20050017056A1 (en) * | 2001-12-07 | 2005-01-27 | Yann Guilmard | Method for setting a protective coating on the inner wall of a tube, tube and in particular weapon tube obtained by said method |
| TW200615503A (en) * | 2004-11-02 | 2006-05-16 | Chung Shan Inst Of Science | Composite material launch tube with rifling and manufacturing method thereof |
| CN1837741A (en) * | 2006-03-17 | 2006-09-27 | 哈尔滨玻璃钢研究院 | Fiber reinforced plastic cylinder with interior spiral reinforcing bar and method for manufacturing the same |
| US20080251060A1 (en) * | 2007-01-08 | 2008-10-16 | Glen Mitchell Thurber | Carbon/aluminum paintball barrel with built in silencer |
-
2010
- 2010-12-28 CN CN2010106115316A patent/CN102529131A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5054224A (en) * | 1990-11-19 | 1991-10-08 | The United States Of America As Represented By The Secretary Of The Army | Apparatus and method for a composite polymer rifling disposable gun tube |
| CN1106513A (en) * | 1994-02-07 | 1995-08-09 | 刘敬 | Laminated resin and fibre pipe and its mfg. method |
| US20050017056A1 (en) * | 2001-12-07 | 2005-01-27 | Yann Guilmard | Method for setting a protective coating on the inner wall of a tube, tube and in particular weapon tube obtained by said method |
| US20040244257A1 (en) * | 2003-06-04 | 2004-12-09 | Degerness Michael K. | Composite structural member |
| TW200615503A (en) * | 2004-11-02 | 2006-05-16 | Chung Shan Inst Of Science | Composite material launch tube with rifling and manufacturing method thereof |
| CN1837741A (en) * | 2006-03-17 | 2006-09-27 | 哈尔滨玻璃钢研究院 | Fiber reinforced plastic cylinder with interior spiral reinforcing bar and method for manufacturing the same |
| US20080251060A1 (en) * | 2007-01-08 | 2008-10-16 | Glen Mitchell Thurber | Carbon/aluminum paintball barrel with built in silencer |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103395194A (en) * | 2013-08-05 | 2013-11-20 | 河北东恒宇功能材料新技术有限公司 | Manufacture method for composite-material launch canister of high-altitude fire-extinguishing rocket |
| CN106152874A (en) * | 2016-07-12 | 2016-11-23 | 北京航天发射技术研究所 | Sandwich full composite material launching tube |
| CN106152874B (en) * | 2016-07-12 | 2017-12-01 | 北京航天发射技术研究所 | Sandwich full composite material launching tube |
| CN110315778A (en) * | 2019-07-12 | 2019-10-11 | 北京航天新风机械设备有限责任公司 | A kind of forming method of high-precision great surface quality thermal protective coating |
| CN111023894A (en) * | 2019-12-04 | 2020-04-17 | 天津爱思达新材料科技有限公司 | Missile launching canister and preparation method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104608915B (en) | Multilayer grid loaded cylinder and preparation method thereof | |
| JP6386185B2 (en) | 3D printing manufacturing method of short fiber reinforced thermosetting resin composite product | |
| CN103042804B (en) | Method for preparing composite material honeycomb sandwich pipe | |
| CN102529131A (en) | Manufacture method of launch tube | |
| DE102013106876A1 (en) | Mold core and method for producing fiber-reinforced structural hollow components | |
| CN107987302B (en) | Surface enhanced resin matrix composite reinforcing rib and preparation method thereof | |
| CN110757845B (en) | Equipment and method for preparing continuous fiber reinforced composite material | |
| DE102012004942A1 (en) | Process for producing a preform and a fiber composite prefabricated component produced therefrom | |
| CN101728036A (en) | Method for preparing solid core rod of one-step molded high-voltage composite insulator | |
| CN105090305A (en) | Composite material hollow spring, manufacturing method and manufacturing die | |
| CN102135178B (en) | Dry yarn winding forming method for pressure container | |
| JP5993342B2 (en) | Composite container manufacturing method and composite container manufacturing system | |
| CN101733937B (en) | Method for forming internal threads of composite material | |
| JP5609249B2 (en) | High pressure tank manufacturing method, high pressure tank manufacturing apparatus, and high pressure tank | |
| CN104261671A (en) | Fiberglass-reinforced plastic septic tank cylinder/bracing ring integrated winding technique | |
| CN1837741B (en) | Fiber reinforced plastic cylinder with interior spiral reinforcing bar and method for manufacturing the same | |
| CN103707561B (en) | A kind of laminboard layer composite lamp stand and quick molding method thereof | |
| CN101348012B (en) | Opening reinforcement method and reinforcement sheet of fiber reinforcement resin composite material member | |
| CN203651004U (en) | Preforming device for manufacturing reinforced plastic rod | |
| CN111844801B (en) | Grid rib forming method | |
| CN110588013B (en) | Composite forming method of multifunctional integrated composite material | |
| JP5993343B2 (en) | Composite container manufacturing method and composite container manufacturing system | |
| CN106182817A (en) | Pultrusion is wound around composite molding and prepares composite | |
| CN106003760A (en) | Composite hollow profile prepared through pultrusion-winding composite molding | |
| CN114436670A (en) | Winding forming-based high-strength carbon-carbon cylinder preparation method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C53 | Correction of patent of invention or patent application | ||
| CB02 | Change of applicant information |
Address after: 100854 Yongding Road, Beijing, No. 52, No. Applicant after: Beijing Aerospace Xinfeng Machinery Equipment Co., Ltd. Address before: 100854 Yongding Road, Beijing, No. 52, No. Applicant before: Beijing Xinfeng Machinery Factory |
|
| COR | Change of bibliographic data |
Free format text: CORRECT: APPLICANT; FROM: BEIJING XINFENG MACHINERY FACTORY TO: BEIJING AEROSPACE XINFENG MACHINERYEQUIPMENT CO., LTD. |
|
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120704 |