CN104441677A - R angle folding and molding method of large-thickness composite material workpiece - Google Patents
R angle folding and molding method of large-thickness composite material workpiece Download PDFInfo
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- CN104441677A CN104441677A CN201410470566.0A CN201410470566A CN104441677A CN 104441677 A CN104441677 A CN 104441677A CN 201410470566 A CN201410470566 A CN 201410470566A CN 104441677 A CN104441677 A CN 104441677A
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- product
- frock
- formpiston
- workpiece
- laying
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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
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
Abstract
The invention relates to an R angle folding and molding method of a large-thickness composite material, which is suitable for relatively thick composite materials. The R angle folding and molding method comprises the following steps: 1) folding the composite material twice, and reserving the other half for later use; 2) processing reference lines of an axial line and rib lines by using a male die tool; 3) etching the axial line, the rib lines and positioning holes in the allowance area of a workpiece of the former folded half; 4) placing the male die tool of the workpiece on a heat insulating film heating platform, and overlapping the axial line with a center line; 5) positioning the workpiece on the male die tool through the positioning hole; 6) closing and operating heat insulating film equipment; 7) repeating the step 3 on the other half workpiece, then transferring the other half workpiece onto the former half folding workpiece of the male die tool, and clamping and operating; 8) demolding the entire workpiece and taking out the same after the program is completed to finish the workpiece forming process. The method can be used for molding composite materials with different lengths and different R angle radiuses and ensuring the outline size and internal quality of the R angle of the composite material workpiece.
Description
Technical field
The present invention relates to a kind of laying and forming method of heavy thickness composite product R angle, belong to the field shaping technique of composite product.
Background technology
Thermoforming process is needed before many load composite product solidifications in aircraft, as beam, rib, long purlin etc.These structures all also exist a large amount of R angular zones, and wherein the laying at R angle place and Forming Quality have great importance to the mechanical property of composite product and internal soundness, therefore need to adopt effective process to improve laying and the Forming Quality at R angle.
Existing composite product R angle forming technique is by artificial laying method directly laying in formpiston frock, adopt the method for vacuum bag compacting shaping, this forming method can meet quality requirement for thinner composite product, but easily build bridge in the R angle obtained for the manual laying of thicker composite product, this bridge formation can not eliminate and solidify after vacuum debulk after product R angle surface of poor quality, often there is fold in the fiber seen from section, has a strong impact on internal soundness and the mechanical property of product.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of laying and forming method of heavy thickness composite product R angle, the method can meet different length, the composite product of different R angular radius is shaping, appearance and size and the internal soundness at composite product R angle can be ensured, especially standby advantage is had more for thicker composite product.
For overcoming the above problems, concrete technical scheme of the present invention is as follows: a kind of laying of heavy thickness composite product R angle and forming method, comprise the following steps:
1) adopt dull and stereotyped frock and carry out laying according to the laying information of design, completing the half of laying sum, second half being completed final vacuum and encapsulate stand-by;
2) the formpiston frock of product is processed the reference lines of axis and rib line, and make at formpiston frock upper surface two ends the locating dowel that diameter is φ 8 respectively;
3) adopt numerical control ultrasonic cut technology, at the surplus district of the product of the first half laying delineation axis and rib line, and make the locating hole of two φ 8 respectively on both sides, rib line is consistent with the definition of formpiston frock with the position of locating hole;
4) the formpiston frock of product is placed on hot barrier film heating platform, formpiston frock axis and heating platform center line are overlapped;
5) by each for the two sides of the first half product coated one deck non-porous release film, utilize locating hole to be positioned in formpiston frock by product, and ensure that product axis and rib line overlap with the axis of formpiston frock and the tag line of rib line;
6) after hot membrane apparatus closes film, the program of the setting that brings into operation, in temperature retention time section, product curves under the vacuum pressures, sturdy with formpiston frock, when temperature is down to room temperature, program end of run;
7) second half product is repeated step 3, then transfer on formpiston frock the first half laying product, adopt locating hole, rib line and axis to position equally, again utilize hot membrane apparatus to run identical program;
8), after program end of run, the whole product demoulding is taken out, completes product forming process.
The laying at this heavy thickness composite product R angle and the advantage of forming method are: the sharp processing axis of product part and the mark of rib line and drive locating hole and adopt numerical control ultrasonic cut technology, ensure machining accuracy and the accurate positioning of product.Product is positioned by locating hole and tag line in formpiston frock, can ensure that card product upper/lower positions is accurate.By the product that hot diaphragm forming obtains, R angle inside/outside diameter size is accurate, and fiber seamlessly transits, and avoids the generation of bridge formation, ensure that the internal soundness at product R angle place.
Accompanying drawing explanation
Fig. 1 is the axis of heavy thickness composite product, rib line and locating hole schematic diagram.
Fig. 2 is formpiston tool structure schematic diagram.
Fig. 3 is hot diaphragm forming encapsulation schematic diagram.
1 be locating hole, 2 be wherein rib line, 3 be axis, 4 be surplus line, 5 be part edge line, 6 be surplus district, 7 be alignment pin, 8 be product, 9 be non-porous release film, 10 be rubber membrane, 11 be male mould forming frock, 12 for hot barrier film heating platform.
Detailed description of the invention
The laying at heavy thickness composite product R angle and a forming method, comprise the following steps:
1) adopt dull and stereotyped frock and carry out laying according to the laying information of design, completing the half of laying sum, second half being completed final vacuum and encapsulate stand-by; The laying of product adopts automated tape-laying technology, can the appearance and size of strict guarantee product and internal soundness, gets rid of the impact of human factor, constant product quality.
2) as shown in Figure 2, the formpiston frock of product is processed the reference lines of axis and rib line, and make at formpiston frock upper surface two ends the locating dowel that diameter is φ 8 respectively;
3) adopt numerical control ultrasonic cut technology, at the surplus district of the product of the first half laying delineation axis and rib line, and make the locating hole of two φ 8 respectively on both sides, rib line is consistent with the definition of formpiston frock with the position of locating hole, as shown in Figure 1;
4) the formpiston frock of product is placed on hot barrier film heating platform, formpiston frock axis and heating platform center line are overlapped;
5) by each for the two sides of the first half product coated one deck non-porous release film, utilize locating hole to be positioned in formpiston frock by product, and ensure that product axis and rib line overlap with the axis of formpiston frock and the tag line of rib line;
6) as shown in Figure 3, after hot membrane apparatus closes film, the program of the setting that brings into operation, in temperature retention time section, product curves under the vacuum pressures, sturdy with formpiston frock, when temperature is down to room temperature, program end of run;
7) second half product is repeated step 3, then transfer on formpiston frock the first half laying product, adopt locating hole, rib line and axis to position equally, again utilize hot membrane apparatus to run identical program;
8), after program end of run, the whole product demoulding is taken out, completes product forming process.
Claims (1)
1. the laying at heavy thickness composite product R angle and a forming method, is characterized in that comprising the following steps:
1) adopt dull and stereotyped frock and carry out laying according to the laying information of design, completing the half of laying sum, second half being completed final vacuum and encapsulate stand-by;
2) the formpiston frock of product is processed the reference lines of axis and rib line, and make at formpiston frock upper surface two ends the locating dowel that diameter is φ 8 respectively;
3) adopt numerical control ultrasonic cut technology, at the surplus district of the product of the first half laying delineation axis and rib line, and make the locating hole of two φ 8 respectively on both sides, rib line is consistent with the definition of formpiston frock with the position of locating hole;
4) the formpiston frock of product is placed on hot barrier film heating platform, formpiston frock axis and heating platform center line are overlapped;
5) by each for the two sides of the first half product coated one deck non-porous release film, utilize locating hole to be positioned in formpiston frock by product, and ensure that product axis and rib line overlap with the axis of formpiston frock and the tag line of rib line;
6) after hot membrane apparatus closes film, the program of the setting that brings into operation, in temperature retention time section, product curves under the vacuum pressures, sturdy with formpiston frock, when temperature is down to room temperature, program end of run;
7) second half product is repeated step 3, then transfer on formpiston frock the first half laying product, adopt locating hole, rib line and axis to position equally, again utilize hot membrane apparatus to run identical program;
8), after program end of run, the whole product demoulding is taken out, completes product forming process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410470566.0A CN104441677A (en) | 2014-09-16 | 2014-09-16 | R angle folding and molding method of large-thickness composite material workpiece |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410470566.0A CN104441677A (en) | 2014-09-16 | 2014-09-16 | R angle folding and molding method of large-thickness composite material workpiece |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104441677A true CN104441677A (en) | 2015-03-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410470566.0A Pending CN104441677A (en) | 2014-09-16 | 2014-09-16 | R angle folding and molding method of large-thickness composite material workpiece |
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| CN (1) | CN104441677A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106142587A (en) * | 2016-07-27 | 2016-11-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The double bag hot barrier film preformation method of a kind of composite |
| CN106696308A (en) * | 2016-12-14 | 2017-05-24 | 中航飞机股份有限公司西安飞机分公司 | Technological method for fixing and molding composite stringer and beam-like part through heat membrane |
| CN108327320A (en) * | 2018-03-07 | 2018-07-27 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of spar mold |
| CN109353035A (en) * | 2018-09-25 | 2019-02-19 | 成都飞机工业（集团）有限责任公司 | A kind of composite structure adhering method without technology nail positioning |
| CN110654040A (en) * | 2019-09-27 | 2020-01-07 | 珂尔默(东莞)制造技术有限公司 | Thermal diaphragm preforming device for composite material shell and working method of thermal diaphragm preforming device |
| CN110757830A (en) * | 2018-07-26 | 2020-02-07 | 中国商用飞机有限责任公司 | Thermal diaphragm forming method and preparation system of hat-shaped stringer |
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| CN103817953A (en) * | 2013-12-18 | 2014-05-28 | 中航复合材料有限责任公司 | Method for automatically laying tapes to manufacture composite material beam |
| CN103950205A (en) * | 2014-03-18 | 2014-07-30 | 沈阳飞机工业（集团）有限公司 | Molding method of composite material part with T-shaped cross section annular revolving body structure |
| CN104029397A (en) * | 2014-06-09 | 2014-09-10 | 中航复合材料有限责任公司 | Preparation device of aircraft composite material fuselage wall panels and preparation method thereof |
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Patent Citations (3)
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| CN103817953A (en) * | 2013-12-18 | 2014-05-28 | 中航复合材料有限责任公司 | Method for automatically laying tapes to manufacture composite material beam |
| CN103950205A (en) * | 2014-03-18 | 2014-07-30 | 沈阳飞机工业（集团）有限公司 | Molding method of composite material part with T-shaped cross section annular revolving body structure |
| CN104029397A (en) * | 2014-06-09 | 2014-09-10 | 中航复合材料有限责任公司 | Preparation device of aircraft composite material fuselage wall panels and preparation method thereof |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106142587A (en) * | 2016-07-27 | 2016-11-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The double bag hot barrier film preformation method of a kind of composite |
| CN106696308A (en) * | 2016-12-14 | 2017-05-24 | 中航飞机股份有限公司西安飞机分公司 | Technological method for fixing and molding composite stringer and beam-like part through heat membrane |
| CN108327320A (en) * | 2018-03-07 | 2018-07-27 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of spar mold |
| CN110757830A (en) * | 2018-07-26 | 2020-02-07 | 中国商用飞机有限责任公司 | Thermal diaphragm forming method and preparation system of hat-shaped stringer |
| CN109353035A (en) * | 2018-09-25 | 2019-02-19 | 成都飞机工业（集团）有限责任公司 | A kind of composite structure adhering method without technology nail positioning |
| CN110654040A (en) * | 2019-09-27 | 2020-01-07 | 珂尔默(东莞)制造技术有限公司 | Thermal diaphragm preforming device for composite material shell and working method of thermal diaphragm preforming device |
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Application publication date: 20150325 |
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