CN106273542B - Composite material is straight empennage twin beams box section entirety co-curing forming method - Google Patents
Composite material is straight empennage twin beams box section entirety co-curing forming method Download PDFInfo
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- CN106273542B CN106273542B CN201610893248.4A CN201610893248A CN106273542B CN 106273542 B CN106273542 B CN 106273542B CN 201610893248 A CN201610893248 A CN 201610893248A CN 106273542 B CN106273542 B CN 106273542B
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- wainscot
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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
- B29C70/34—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
- B29C70/342—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 using isostatic pressure
-
- 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
- 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 discloses a kind of straight empennage twin beams box section entirety co-curing forming method of composite material, for solving the technical issues of existing composite material integral forming method formed precision is poor.Technical solution is to substitute flexible core mold using protection composite bag vacuum pumping method, realizes in the curing process and product is implemented to pressurize；In order to ensure the continuity of leading edge face fiber, instead of technological design of the flexible core mold as auxiliary laying, Product Process parting surface is cancelled in mould process design, upper wall board forming die is divided into leading edge segments and back segment two parts using front-axle beam plane, it is overlapped in front-axle beam upper surface, it both ensure that fiber was not broken at leading edge locus in this way, it ensure that laying integrality, realize the whole co-curing molding of the straight empennage twin beams box section of composite material, improve formed product precision, reduce the manufacturing and processing expense of auxiliary mould again, reduce manufacture cost.
Description
Technical field
The present invention relates to a kind of straight empennage forming method of composite material, more particularly to a kind of straight empennage of composite material is double
Beam box section entirety co-curing forming method.
Background technology
Composite material has specific strength, specific modulus height, can design and be easy to many excellent specific properties such as monolithic molding, great Liang Ying
With on unmanned aerial vehicle.With the development of composite material integral shaping method, global formation has become similar to straight empennage component
Trend is compared with traditional beam rib structure (by upper and lower siding, forward and backward beam and Duo Gen ribs composition), whole twin beams box section integral into
Number of parts is reduced to one by type by multiple, simplifies the assembling process of box section, and is reduced fastener quantity and autoclave and made
With number, so as to achieve the effect that loss of weight and reduce cost.At present, the straight empennage of aircraft is whole using more beams/twin beams box section
Body structure.
It is whole that document " application publication number is the Chinese invention patent of CN103057126A " discloses a kind of large-scale composite material
Body formed blade and its moulding process.The moulding process uses resin film infusion technique, and mold uses core model as flexible core or can
Dissolubility hard cores/hard mold (external mold) combination realize pressurization during curing by the expansion of flexible core mold.But resin film infusion technique
Molding requires the thickness of component, and the skin thickness only 0.5mm of the straight empennage of unmanned plane, is not suitable for middle-size and small-size unmanned aerial vehicle
Straight empennage box section structure manufacture.And flexible core mold is difficult to control there are swell increment, and the trueness error of beam position is caused not know,
Flexible core mold molding die design simultaneously and difficulty of processing are big, costly, are not suitable for the processing of small-lot components.
Invention content
In order to overcome the shortcomings of that existing composite material integral forming method formed precision is poor, the present invention provides a kind of composite wood
Expect straight empennage twin beams box section entirety co-curing forming method.This method substitutes flexible core mold using protection composite bag vacuum pumping method,
It realizes in the curing process and product is implemented to pressurize；In order to ensure the continuity of leading edge face fiber, instead of flexible core mold conduct
The technological design of laying is assisted, Product Process parting surface is cancelled in mould process design, using front-axle beam plane by upper wall plate forming die
Tool is divided into leading edge segments and back segment two parts, is overlapped in front-axle beam upper surface, both ensure that fiber was not at leading edge locus in this way
Fracture, ensure that laying integrality, realizes the whole co-curing molding of the straight empennage twin beams box section of composite material, improves production
Product formed precision, and reduce the manufacturing and processing expense of auxiliary mould, reduce manufacture cost.
The technical solution adopted by the present invention to solve the technical problems：A kind of straight empennage twin beams box section of composite material is whole
Co-curing forming method, its main feature is that including the following steps：
(1) laying of forward and backward beam；
By the prepreg cut out in advance successively paving on forward and backward beam mould 1,11, and vacuum preloading is carried out every three layers
It is real.
(2) lower wall panels and the laying of leading edge wainscot housing；
Before laying, first lower wall board mold 6 with wainscot leading edge section die 8 is combined, prepreg and foam are laid in
The mould upper surface combined, and vacuum preloading reality is carried out every three layers.Wherein laying when it is reserved in wainscot leading edge section die 8
Two layers of prepreg is turned on the edge of wainscot leading edge section die 8, is overlapped when being combined with preceding beam mould 1.
(3) piece housing laying after wainscot；
By the successively paving of the prepreg cut out in advance and foam after wainscot on section die 9, and carried out very every three layers
Empty pre-compacted.
(4) in the pre-assembled of the enterprising cross girders of lower wall board mold；
In the edge of wainscot leading edge section die 8 according to being sequentially placed non-porous release film 3,4 and of airfelt from inside to outside
Sub- vacuum bag 5；Its neutron vacuum bag 5 is than preceding 1 long 0.5~0.6m of beam mould.In lower wall board mold 6 and wainscot leading edge section die
The mold of the good forward and backward beam 2,12 of step (1) laying is placed in 8 combination layings, using guiding and the lower wall board mold 6 of positioning pin
Pre-assembled, and fastened with fastening bolt, the overturning of two layers of prepreg and paving that step (2) is reserved are in the laying of front-axle beam 2.
(5) system vacuum bag；
The rear of section die 9 at the forward and backward beam mould 1,11 of the good prepreg of paving and after rear beam mould 11 and wainscot
Place according to being sequentially placed non-porous release film 3, airfelt 4 and sub- vacuum bag 5 from inside to outside；Its neutron vacuum bag 5 is than forward and backward beam form
1,11 0.5~0.6m of length of tool.
(6) piece housing pairing after wainscot；
Section die 9 after piece housing 10 after the good wainscot of laying and wainscot is overturn, is oriented to by positioning pin and mold is recessed
Tongue positions and 6 pairing of lower wall board mold, and is fastened with fastening bolt.
(7) female vacuum bag is made；
After wainscot on section die 9, according to being sequentially placed airfelt 4 and female vacuum bag 14 from inside to outside；
(8) vacuum bag sealing and curing；
Three sub- 5, mother's vacuum bags 14 of vacuum bag and lower wall board mold 6 are sealed into connected, three vacuum passages of formation,
Two vacuum quick-release couplings 15 are set on female vacuum bag 14 for vacuumizing, when vacuum degree is raised to 0.08~0.098Mpa,
Close vacuum, maintain 15 minutes, if meet vacuum degree was dropped by less than 0.017Mpa within 5 minutes, into autoclave into
Row curing.
(9) demoulding and deburring；
After the completion of curing, the positioning pin of forward and backward beam mould 1,11 is laid down, forward and backward beam mould 1,11 is passed through into extractor
It extracts, then lays down section die 9 after wainscot leading edge section die 8 and wainscot, straight empennage is taken from lower wall board mold 6
Under, deburring obtains whole straight empennage component.
The beneficial effects of the invention are as follows：This method substitutes flexible core mold using protection composite bag vacuum pumping method, in solidification process
Middle realize implements to pressurize to product；In order to ensure the continuity of leading edge face fiber, instead of flexible core mold as auxiliary laying
Technological design, mould process design cancel Product Process parting surface, upper wall board forming die are divided into leading edge using front-axle beam plane
Section and back segment two parts, are overlapped in front-axle beam upper surface, both ensure that fiber is not broken at leading edge locus, ensure that in this way
Laying integrality realizes the whole co-curing molding of the straight empennage twin beams box section of composite material, improves formed product precision,
Reduce the manufacturing and processing expense of auxiliary mould again, reduce manufacture cost.
It elaborates with reference to the accompanying drawings and detailed description to the present invention.
Description of the drawings
Fig. 1 is the straight empennage of the straight empennage twin beams box section entirety co-curing forming method global formation of composite material of the present invention
Structural section schematic diagram；
Fig. 2 is that the method for the present invention is laid with front-axle beam making schematic diagram；
Fig. 3 is that the method for the present invention is laid with lower wall panels and leading edge wainscot shell combination schematic diagram；
Fig. 4 is that the method for the present invention is laid with wainscot back segment body diagram；
Fig. 5 is that the method for the present invention lower wall panels combine assembling schematic diagram with leading edge wainscot housing with forward and backward beam；
Fig. 6 is the schematic diagram of the method for the present invention molding；
Fig. 7 is that the method for the present invention protection composite bag makes schematic diagram.
In figure, beam mould before 1-, 2- front-axle beams, 3- non-porous release films, 4- airfelts, 5 sub- vacuum bags, 6- lower wall board molds,
7- lower wall panels and leading edge wainscot housing, 8- wainscot leading edge section dies, section die after 9- wainscots, 10- wainscot back segment shells
Body, beam mould after 11-, the 12- back rest, 13- beam locators, mother's 14- vacuum bag, 15- vacuum quick-release couplings.
Specific embodiment
With reference to Fig. 1-7.The straight empennage twin beams box section entirety co-curing forming method preferred embodiment of composite material of the present invention,
Composite material is straight 2.15 meters of empennage length, 0.26 meter of chord length, maximum 24 millimeters of aerofoil profile height.
The raw material of composite material are carbon fiber prepreg, glass fibre prepreg and PMMI foams in the present embodiment.
Lower wall panels and piece housing 10 after leading edge wainscot housing 7, wainscot are carbon fiber, glass fibre presoaks strand foam folder
Layer structure, including outer layer of composite material, foam layer and inner layer composite material.
Forward and backward beam 2,12 is carbon fibre initial rinse laminate structure type.
It is as follows.
(1) mold prepares：With alcohol by section die after wainscot 9, wainscot leading edge section die 8, lower wall board mold 6 and
Forward and backward beam mould 1,11 removing surfaces are clean, then in all mould surface spraying hole sealing agents and releasing agent.
(2) prepreg placed：
A. the placed of forward and backward beam：Using manual paving technique, in the product type surface side of forward and backward beam mould 1,11 by design
It is required that difference paving front-axle beam 2, the back rest 12, during paving, with reference to Fig. 2, carry out process for pre-compacting to forward and backward beam 2,12, press
According to placed non-porous release film 3, airfelt 4 and sub- vacuum bag 5 carry out pre-compacted successively from inside to outside.
B. lower wall panels and the laying of piece housing after leading edge wainscot housing and wainscot：In lower wall board mold 6 and wainscot
Siding and leading edge wainscot housing 7 are put down in 8 combination die upper berth of leading edge section die, and siding is put on 9 upper berth of section die after wainscot
During laying, with reference to Fig. 2, process for pre-compacting is carried out to lower wall panels and leading edge wainscot housing 7 for piece housing 10 afterwards, according to
Placed non-porous release film 3, airfelt 4, sub- vacuum bag 5 carry out pre-compacted successively from inside to outside.Wherein in lower wall panels and leading edge
In the manufacturing process of siding housing 7, wherein laying when wainscot leading edge section die 8 reserve two layers of prepreg turn in wainscot
On the edge of leading edge section die 8, overlapped when being combined with preceding beam mould 1.
(3) it combines：
A. with reference to Fig. 5, wainscot leading edge section die 8 edge according to be sequentially placed from inside to outside non-porous release film 3,
Airfelt 4 and sub- vacuum bag 5；Its neutron vacuum bag 5 is than preceding 1 long 0.5~0.6m of beam mould.Place the front-axle beam 2 of pre-compacted and
Preceding beam mould 1 and the pre-compacted back rest 12 and rear beam mould 11 are in the lower wall panels of pre-compacted and leading edge wainscot housing 7.Its
In, forward and backward beam mould 1,11 in the beam locator 13 of lower wall panels by positioning.The preimpregnate glass reserved in step (2) b is fine
Dimension/carbon fiber overturns paving on front-axle beam 2.
B. with reference to Fig. 5, section die 9 between the good forward and backward beam mould 1,11 of placed and after rear beam mould 11 and wainscot
Rear at according to being sequentially placed non-porous release film 3, airfelt 4 and sub- vacuum bag 5 from inside to outside；Before its neutron vacuum bag 5 ratio,
Beam mould 1,11 grows 0.5~0.6m afterwards.
C. piece housing pairing after wainscot：Section die 9 after piece housing 10 after the good wainscot of laying and wainscot is overturn,
It is oriented to by positioning pin and mold tongue and groove positions and 6 pairing of lower wall board mold, and is fastened with fastening bolt.
(4) it vacuumizes：With reference to Fig. 6, by the upper side of a circle of the end of three sub- vacuum bags 5 and female vacuum bag of outside
14 are connected with sealant tape, are connected two-by-two between sub- 5 two sides of vacuum bag or between mold, and the one of the end of sub- vacuum bag 5
The downside of circle is connected with lower wall board mold 6, so as to form three vacuum passages, sets two vacuum fast on female vacuum bag 14
Connector 15 is unloaded, is vacuumized, wherein carrying out effective protection with airfelt to all locating pieces, pin and demoulding via hole.
(5) cure：Vacuum leak situation is checked before autoclave is entered, when vacuum degree is raised to 0.08~0.098Mpa,
Close vacuum, maintain 15 minutes, if meet vacuum degree was dropped by less than 0.017Mpa within 5 minutes, into autoclave into
Row curing.
(6) it demoulds：After the completion of curing, lay down and forward and backward beam mould 1,11 is passed through into extractor after the positioning pin of front and rear beam
It is pulled out from side, then lays down section die 9 after wainscot, straight empennage is removed from lower wall board mold 6.
(7) deburring：Obtain whole straight empennage component.
The straight empennage twin beams box section formed precision of the molding composite material of method using the present invention is high, technical process letter
Single, reproducible, the position of beam, bonding quality are all effectively ensured.
Claims (2)
1. a kind of straight empennage twin beams box section entirety co-curing forming method of composite material, it is characterised in that include the following steps：
Step 1: the laying of forward and backward beam；
By the prepreg cut out in advance successively paving on forward and backward beam mould (1,11), and vacuum preloading reality is carried out every three layers；
Step 2: lower wall panels and the laying of leading edge wainscot housing；
Before laying, first lower wall board mold (6) with wainscot leading edge section die (8) is combined, prepreg and foam are laid in
The mould upper surface combined, and vacuum preloading reality is carried out every three layers；Wherein laying when it is pre- in wainscot leading edge section die (8)
Two layers of prepreg is stayed to turn on the edge of wainscot leading edge section die (8), is overlapped when being combined with preceding beam mould (1)；
Step 3: piece housing laying after wainscot；
By the successively paving of the prepreg cut out in advance and foam after wainscot on section die (9), and vacuum is carried out every three layers
Pre-compacted；
Step 4: in the pre-assembled of the enterprising cross girders of lower wall board mold；
In the edge of wainscot leading edge section die (8) according to being sequentially placed non-porous release film (3), airfelt (4) from inside to outside
With sub- vacuum bag (5)；Its neutron vacuum bag (5) grows 0.5~0.6m than preceding beam mould (1)；In lower wall board mold (6) and wainscot
The mold of the good forward and backward beam (2,12) of step 1 laying is placed in leading edge section die (8) combination laying, using the guiding of positioning pin
It with lower wall board mold (6) pre-assembled, and is fastened with fastening bolt, the overturning of two layers of prepreg and paving that step 2 is reserved are preceding
In the laying of beam (2)；
Step 5: system vacuum bag；
At the forward and backward beam mould (1,11) of the good prepreg of paving and after rear beam mould (11) and wainscot after section die (9)
According to being sequentially placed non-porous release film (3), airfelt (4) and sub- vacuum bag (5) from inside to outside at edge；Its neutron vacuum bag (5)
0.5~0.6m is grown than forward and backward beam mould (1,11)；
Step 6: piece housing pairing after wainscot；
Section die (9) after piece housing (10) after the good wainscot of laying and wainscot is overturn, is oriented to by positioning pin and mold is recessed
Tongue positions and lower wall board mold (6) pairing, and is fastened with fastening bolt；
Step 7: the female vacuum bag of system；
After wainscot on section die (9), according to being sequentially placed airfelt (4) and female vacuum bag (14) from inside to outside；
Step 8: vacuum bag sealing and curing；
Three sub- vacuum bags (5), a female vacuum bag (14) and lower wall board mold (6) sealing are connected, three vacuum is formed and leads to
Road sets two vacuum quick-release couplings (15) for vacuumizing on female vacuum bag (14), when vacuum degree is raised to 0.08~
During 0.098Mpa, vacuum is closed, is maintained 15 minutes, if meet vacuum degree was dropped by less than 0.017Mpa within 5 minutes, into
Enter autoclave to be cured；
Step 9: demoulding and deburring；
After the completion of curing, the positioning pin of forward and backward beam mould (1,11) is laid down, forward and backward beam mould (1,11) is passed through into extractor
It extracts, then lays down section die (9) after wainscot leading edge section die (8) and wainscot, by straight empennage from lower wall board mold (6)
On remove, deburring obtains whole straight empennage component.
2. the straight empennage twin beams box section entirety co-curing forming method of composite material according to claim 1, feature exist
In：The sub- vacuum bag (5) is tubular vacuum bag.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610893248.4A CN106273542B (en) | 2016-10-13 | 2016-10-13 | Composite material is straight empennage twin beams box section entirety co-curing forming method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610893248.4A CN106273542B (en) | 2016-10-13 | 2016-10-13 | Composite material is straight empennage twin beams box section entirety co-curing forming method |
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| CN106273542B true CN106273542B (en) | 2018-07-06 |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107415280B (en) * | 2017-08-22 | 2023-08-01 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Mold and method for preforming and/or positioning T-stringers with wall panels |
| CN107775971B (en) * | 2017-11-21 | 2023-12-01 | 江苏美龙航空部件有限公司 | Manufacturing method and die for carbon fiber flare pipeline |
| CN107984774A (en) * | 2017-12-15 | 2018-05-04 | 江西长江化工有限责任公司 | A kind of composite material empennage technology of preparing |
| CN108248824B (en) * | 2017-12-29 | 2021-12-21 | 南京航空航天大学 | Wing surface leading edge structure of micro unmanned aerial vehicle, forming die and preparation method of wing surface leading edge structure |
| CN108688195B (en) * | 2018-06-13 | 2024-04-09 | 绍兴宝旌复合材料有限公司 | Trapezoidal skeleton structure of carbon fiber composite material and forming method thereof |
| CN110509569A (en) * | 2019-08-21 | 2019-11-29 | 西安爱生技术集团公司 | A kind of composite material orthogonal stiffeners siding integral solidifying tooling |
| CN110712324B (en) * | 2019-10-30 | 2022-06-24 | 航天特种材料及工艺技术研究所 | Integrated die for molding and assembling composite material wings |
| CN110843234A (en) * | 2019-11-08 | 2020-02-28 | 西安爱生技术集团公司 | Forming process method of unmanned aerial vehicle carbon fiber composite main beam |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103057126A (en) * | 2012-12-14 | 2013-04-24 | 内蒙古金岗重工有限公司 | Large-scale composite material integral molding blade and molding process thereof |
| CN103264513B (en) * | 2013-05-30 | 2015-10-21 | 中国商用飞机有限责任公司 | The overall co-curing moulding technique of composite many beams box section |
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