CN108407335B - Integral forming method for cap-shaped reinforced wall plate made of composite material - Google Patents
Integral forming method for cap-shaped reinforced wall plate made of composite material Download PDFInfo
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- CN108407335B CN108407335B CN201810268781.0A CN201810268781A CN108407335B CN 108407335 B CN108407335 B CN 108407335B CN 201810268781 A CN201810268781 A CN 201810268781A CN 108407335 B CN108407335 B CN 108407335B
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- vacuum bag
- shaped
- hat
- stringer
- wall plate
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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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
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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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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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
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
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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
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3082—Fuselages
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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
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
Abstract
The invention belongs to the field of composite material forming, and relates to an integral forming method of a composite material hat-shaped reinforced wall plate. According to the invention, the support core mold vacuum bag barrel is adopted to be unfolded in the inner cavity of the hat-shaped stringer, so that the hat-shaped stiffened wall plate is integrally formed by utilizing the vacuum bag barrel, the support core mold can enable the vacuum bag to be well unfolded in the inner cavity of the hat-shaped stringer, bridging of the vacuum bag in a narrow space is avoided, and the later quality risk is reduced. The cost of the vacuum bag and the supporting core mould is far lower than that of the air bag and the rubber core mould, and the cost of the supporting core mould is lower and can be repeatedly used, so that the integral forming and manufacturing cost of the cap-shaped reinforced wall plate is greatly reduced. Because the supporting core mould is taken out before the hat-shaped reinforced wall plate is cured, the bridging in the curing process is avoided. Compared with the traditional scheme, the vacuum bag is very easy to pull out from the cap-shaped stringer after the manufacturing is finished, the demolding difficulty and risk are greatly reduced, and the integral molding and manufacturing of the large-size cap-shaped stiffened wall plate are realized.
Description
Technical Field
The invention belongs to the field of composite material forming, and relates to an integral forming method of a composite material hat-shaped reinforced wall plate.
Background
With the development of aviation manufacturing technology, the amount of composite materials on a new generation of large passenger aircraft exceeds 50%, and the composite materials are transited from the traditional non-bearing part and the secondary bearing part to the main bearing part. The hat-shaped reinforced wall plate is greatly used on the airframe, the wings and other parts of the airplane due to higher rigidity and weight reduction efficiency. The hat-shaped stiffened wall plate has a hollow structure of hat-shaped long purlins, and is greatly different from the integral forming method of the traditional structure, and the difficulty is also higher.
The traditional cap-shaped stiffened plate is generally formed by an air bag method or a rubber core die method. But neither solution meets the requirements for low cost and reliable manufacturing of composite materials. The air bag method adopts a forming scheme that a rubber air bag is used as a pressure transmission medium, and has the defects of higher manufacturing cost, poor reliability, extremely low repeated utilization rate and risk of damage and air leakage in the using process of the air bag. After solidification and forming, the air bag is difficult to pull out and is not suitable for forming large-size composite material components. The rubber core mold method is a scheme of taking a solid rubber core mold as a cap-shaped stringer supporting core mold and pulling out the core mold after curing. The defects are that the rubber core mold is easy to generate larger deformation under high temperature and pressure when the wallboard is formed, the size of the molded surface of a product is poorer, and the core mold has poor pressure transmission effect, the stressed effect of a skin area is poor, and the product quality is poor.
For the demanding aviation industry, the above two solutions obviously cannot meet the high quality requirements of the aviation aircraft for the product.
Disclosure of Invention
The invention aims at the integral forming requirement of the cap-shaped stiffened wall plate, and provides a forming scheme for assisting a vacuum bag by using a support core mould so as to realize direct pressure forming of the cap-shaped stiffened wall plate by the vacuum bag.
The technical solution of the present invention comprises the following steps:
(1) manufacturing prepreg on a stringer tool to form hat-shaped stringers, and cutting the stringer size according to the actual size;
(2) cutting a vacuum bag cylinder according to the length of the hat-shaped stringer, reserving packaging allowance, putting a support core mould into a vacuum bag to open the vacuum bag, attaching four corners of the support core mould to an inner cavity of the hat-shaped stringer, and directly putting the vacuum bag with a demoulding layer into the cavity of the hat-shaped stringer; for the vacuum bag without the demolding layer, demolding materials are wrapped outside the vacuum bag or demolding agents are coated outside the vacuum bag, and the support core mold is of a hollow thin-wall tubular structure;
(3) positioning and packaging the hat-shaped stringer on the skin, and then vacuumizing to compact the stringer on the skin;
(4) the support core mold is pulled out, the vacuum bag is left in the cap-shaped long cavity, and then auxiliary material laying and vacuum bag making packaging are carried out;
(5) and (4) feeding the mixture into an autoclave for integral molding, and pulling out the vacuum bag and other demolding materials after curing to finish the manufacture.
The prepreg is a fiber reinforced resin-based prepreg, the fiber is carbon fiber, glass fiber or aramid fiber, and the resin is epoxy resin, bismaleimide resin, polyimide resin, phenolic resin or cyanate resin.
The hat stringers are uncured, pre-cured or cured.
The support core mold is made of plastic, rubber, metal or composite materials.
The autoclave integral molding comprises co-curing molding, co-adhesive molding and secondary adhesive molding.
The invention has the advantages and beneficial effects that: according to the invention, the support core mold vacuum bag barrel is adopted to be unfolded in the inner cavity of the hat-shaped stringer, so that the hat-shaped stiffened wall plate is integrally formed by utilizing the vacuum bag barrel, the support core mold can enable the vacuum bag to be well unfolded in the inner cavity of the hat-shaped stringer, bridging of the vacuum bag in a narrow space is avoided, and the later quality risk is reduced. The cost of the vacuum bag and the supporting core mould is far lower than that of the air bag and the rubber core mould, and the cost of the supporting core mould is lower and can be repeatedly used, so that the integral forming and manufacturing cost of the cap-shaped reinforced wall plate is greatly reduced. Because the supporting core mould is taken out before the hat-shaped reinforced wall plate is cured, the bridging in the curing process is avoided. Compared with the traditional scheme, the vacuum bag is very easy to pull out from the cap-shaped stringer after the manufacturing is finished, the demolding difficulty and risk are greatly reduced, and the integral molding and manufacturing of the large-size cap-shaped stiffened wall plate are realized.
Drawings
Fig. 1 is a schematic view showing an implementation step of a method for manufacturing a hat-type stiffened wall panel using a support core mold and a cylindrical vacuum bag.
Detailed Description
(1) Manufacturing prepreg on a stringer tool to form hat-shaped stringers, and cutting the stringer size according to the actual size;
(2) cutting the vacuum bag barrel according to the length of the stringer, reserving packaging allowance, putting the support core mould into a vacuum bag to open the vacuum bag, and directly putting the vacuum bag with a demoulding layer into a cap-shaped stringer mould cavity; for vacuum bags without release layers, release materials can be wrapped outside the vacuum bags or release agents can be coated outside the vacuum bags;
(3) positioning the hat-shaped stringer on the skin, and then vacuumizing to compact the stringer on the skin, so that the stringer does not slide and dislocate in subsequent operation;
(4) the supporting core mould is pulled out, and the vacuum bag is left in the cap-shaped long cavity;
(5) and (5) curing in an autoclave, and then pulling out the vacuum bag and other demolding materials to finish the manufacture.
Example 1
The length of the unmanned aerial vehicle wing made of the large-size composite material hat-shaped stiffened wall plate is 12.5 meters, and an integral forming scheme that hat-shaped stringers are firstly cured and then co-bonded with a cured skin is selected. The material is carbon fiber reinforced intermediate temperature epoxy resin prepreg. A cylindrical vacuum bag RBG500 produced by AIRTEK company is selected, and a hollow thin-wall pipe made of polypropylene is selected as a support core mold. The prepreg is firstly laid on a hat-shaped stringer molding die to be subjected to autoclave curing molding, and the stringer is processed to the nominal size after demolding. Then the support core mould is placed into a vacuum bag to open the vacuum bag, and the redundant vacuum bag is fixed on the side edge of the support core mould. And putting the support core mold into the inner cavity of the clean hat-shaped stringer. And then filling filler and paving adhesive films, and performing vacuum bag leakage test inspection after the filling and the adhesive film paving are finished. And after the vacuum bag is ensured to be damaged and leaked, positioning the cap-shaped stringer on the well-laid skin, vacuumizing to fix the cap-shaped stringer on the skin, and extracting the support core mold. And laying auxiliary materials and making a vacuum bag for packaging. After the co-bonding is completed, the RBG500 vacuum bag in the hat stringer is pulled out, and the part manufacturing is completed.
Example 2
The verification piece of the fuselage panel after certain hat-shaped reinforcement is 3.6 meters in length, and an integral forming scheme of co-curing the stringer and the skin is selected. The material is carbon fiber reinforced high temperature bismaleimide resin prepreg. A sheet vacuum bag DPT1000 produced by AIRTEK company is selected, a GS-213 sealing rubber strip is made into a cylinder shape, and a hollow pipe made of silicon rubber is selected as a support core mold. The prepreg is firstly laid on a hat-shaped stringer forming die to form a blank, and the blank is cut to the nominal size of the stringer. And then putting the stringer blank into a forming concave die for compaction. And (4) putting the support core mold into a vacuum bag to open the vacuum bag, and fixing the redundant vacuum bag on the side edge of the support core mold. And putting the support core mold into the inner cavity of the hat-shaped stringer blank. And then filling filler and paving adhesive films, and performing vacuum bag leakage test inspection after the filling and the adhesive film paving are finished. And after the vacuum bag is ensured to be free from damage and leakage, positioning the stringer forming die and the cap type stringer on the well-laid skin, vacuumizing to fix the cap type stringer on the skin, and pulling out the support core die. And laying auxiliary materials and making a vacuum bag for packaging. And after the co-curing is finished, pulling out the vacuum bag of the DPT1000 in the hat-shaped stringer, and finishing the part manufacturing.
Example 3
A typical verification piece is used for a hat-shaped stiffened middle fuselage panel 1:1, the length is 4.6 meters, and an integral molding scheme of co-bonding a pre-cured stringer and a cured skin is selected. The material is carbon fiber reinforced high temperature epoxy resin prepreg. A sheet vacuum bag DPT1000 manufactured by AIRTEK company is selected, a GS-213 sealing rubber strip manufactured by AIRTEK company is manufactured into a cylinder shape, and a hollow pipe made of polypropylene is selected as a support core mold. The prepreg is firstly laid on a hat-shaped stringer forming die to form a blank, and the blank is cut to the nominal size of the stringer. And then putting the stringer blank into a forming concave die for compaction, and putting the stringer blank into an autoclave for precuring at the curing temperature of 140 ℃ for 1.5 hours. And (4) putting the support core mold into a vacuum bag to open the vacuum bag, and fixing the redundant vacuum bag on the side edge of the support core mold. And putting the support core mold into the inner cavity of the hat-shaped stringer blank. And then filling filler and paving adhesive films, and performing vacuum bag leakage test inspection after the filling and the adhesive film paving are finished. And after the vacuum bag is ensured to be free from damage and leakage, positioning the stringer forming die and the cap type stringer on the well-laid skin, vacuumizing to fix the cap type stringer on the skin, and pulling out the support core die. And laying auxiliary materials and making a vacuum bag for packaging. And after the co-curing is finished, pulling out the vacuum bag of the DPT1000 in the hat-shaped stringer, and finishing the part manufacturing.
Claims (5)
1. The integral forming method of the composite hat-shaped reinforced wall plate is characterized by comprising the following steps of: comprises the following steps: (1) manufacturing prepreg on a stringer tool to form hat-shaped stringers, and cutting the stringer size according to the actual size;
(2) cutting a vacuum bag cylinder according to the length of the hat-shaped stringer, reserving packaging allowance, putting a support core mould into a vacuum bag to open the vacuum bag, attaching four corners of the support core mould to an inner cavity of the hat-shaped stringer, and directly putting the vacuum bag with a demoulding layer into the cavity of the hat-shaped stringer; for the vacuum bag without the demolding layer, demolding materials are wrapped outside the vacuum bag or demolding agents are coated outside the vacuum bag, and the support core mold is of a hollow thin-wall tubular structure; the support core mold is used for enabling a vacuum bag to be unfolded in the inner cavity of the cap-shaped stringer so as to avoid bridging of the vacuum bag in a narrow space;
(3) positioning and packaging the hat-shaped stringer on the skin, and then vacuumizing to compact the stringer on the skin;
(4) the support core mold is pulled out, the vacuum bag is left in the cap-shaped long cavity, and then auxiliary material laying and vacuum bag making packaging are carried out;
(5) the vacuum bag and other demoulding materials are pulled out after the hot pressing tank is integrally formed and solidified, and then the manufacture can be finished; the treatment mode of taking out the support core mold before the cap-shaped reinforced wall plate is cured is adopted, so that bridging in the curing process is avoided.
2. The method of integrally forming a hat-shaped stiffened wall panel of composite material as claimed in claim 1, wherein: the prepreg is a fiber reinforced resin-based prepreg, the fiber is carbon fiber, glass fiber or aramid fiber, and the resin is epoxy resin, bismaleimide resin, polyimide resin, phenolic resin or cyanate resin.
3. The method of integrally forming a hat-shaped stiffened wall panel of composite material as claimed in claim 1, wherein: the hat stringers are uncured, pre-cured or cured.
4. The method of integrally forming a hat-shaped stiffened wall panel of composite material as claimed in claim 1, wherein: the support core mold is made of plastic, rubber, metal or composite materials.
5. The molding method according to claim 1, wherein: the autoclave integral molding comprises co-curing molding, co-adhesive molding and secondary adhesive molding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201810268781.0A CN108407335B (en) | 2018-03-28 | 2018-03-28 | Integral forming method for cap-shaped reinforced wall plate made of composite material |
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| CN201810268781.0A CN108407335B (en) | 2018-03-28 | 2018-03-28 | Integral forming method for cap-shaped reinforced wall plate made of composite material |
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| CN108407335A CN108407335A (en) | 2018-08-17 |
| CN108407335B true CN108407335B (en) | 2020-10-20 |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109573332B (en) * | 2018-12-25 | 2020-11-06 | 义乌市鼎莎针织有限公司 | Engine packing box |
| CN111152482A (en) * | 2019-12-17 | 2020-05-15 | 中国航空制造技术研究院 | Preparation method of cap-shaped reinforced wall plate preform suitable for RFI (radio frequency interference) process |
| CN112571815B (en) * | 2020-10-29 | 2022-06-14 | 成都飞机工业（集团）有限责任公司 | Rib positioning method of reinforced wall plate |
| WO2022099707A1 (en) * | 2020-11-16 | 2022-05-19 | 中国商用飞机有限责任公司 | Core mold for producing hat-shaped reinforcement member |
| CN114506095B (en) * | 2020-11-16 | 2024-01-26 | 中国商用飞机有限责任公司 | Core mould for manufacturing cap-shaped reinforcing member |
| CN112659418B (en) * | 2020-11-23 | 2022-09-23 | 航天特种材料及工艺技术研究所 | Integrated forming die and manufacturing method for composite material curved surface stiffened wall plate |
| CN114147994B (en) * | 2021-11-24 | 2023-05-05 | 航天特种材料及工艺技术研究所 | Integral forming method for composite cabin structure |
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| CN103640231B (en) * | 2013-12-17 | 2016-02-10 | 沈阳飞机工业（集团）有限公司 | Composite vacuum bag external position device and localization method thereof |
| US10293552B2 (en) * | 2015-11-17 | 2019-05-21 | The Boeing Company | Heat shrinkable film tube and method for manufacturing hollow composite parts |
| CN106799851B (en) * | 2016-12-27 | 2019-07-30 | 中国商用飞机有限责任公司 | The moulding manufacture method of composite material hat Material Stiffened Panel based on piddler technology |
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