CN104626605A - Composite material wing integral molding technological method and composite material wing integral molding tool - Google Patents

Composite material wing integral molding technological method and composite material wing integral molding tool Download PDF

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Publication number
CN104626605A
CN104626605A CN201410781517.9A CN201410781517A CN104626605A CN 104626605 A CN104626605 A CN 104626605A CN 201410781517 A CN201410781517 A CN 201410781517A CN 104626605 A CN104626605 A CN 104626605A
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China
Prior art keywords
former
wing
composite
formpiston
counterdie
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CN201410781517.9A
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Chinese (zh)
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CN104626605B (en
Inventor
杨铁江
赵景丽
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Northwestern Polytechnical University
Xian Aisheng Technology Group Co Ltd
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Northwestern Polytechnical University
Xian Aisheng Technology Group Co Ltd
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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/30Shaping 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
    • B29C70/34Shaping 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
    • B29C70/342Shaping 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
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/54Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing

Abstract

The invention discloses a composite material wing integral molding technology method and a composite material wing integral molding tool. A metal female mold and a silicon rubber male mold are assisted in molding. The composite material wing integral molding technology method comprises the following steps: firstly, manufacturing the female mold, and manufacturing a male mold by utilizing the female mold; cleaning a demolding agent sprayed on the upper and lower molded surfaces of the female mold; paving upper and lower wing panels of the composite material wing respectively on the upper and lower molded surfaces of the female mold; arranging the male mold and the wing front edge part on the lower wing panel of the wing; folding the upper mold and the lower mold of the female mold; putting the folded female mold and male mold and a composite material wing product into a hot pressing tank, and curing; demolding after curing, and trimming to obtain the composite material wing. Therefore, the composite material wing with relatively small size is molded integrally, the integral weight of the composite material wing is reduced, and the structure intensity of the composite material wing is improved. The integrally molded composite material wing is good in interior quality, the size of the external wing type molded surface is accurate, meanwhile the thickness of a paving layer of the composite material wing product can be strictly controlled, and the integral molding quality of the composite material wing is stable and reliable.

Description

A kind of composite wing integral forming technique method and frock
Technical field
The invention belongs to System for aircraft manufacturing technology equipment technology field, specifically, relate to a kind of composite wing integral forming technique method and frock, be applicable to the global formation of reduced size composite wing.
Background technology
The designability of composite is strong, lightweight, specific strength is high, corrosion-resistant and unique electromagnetic penetration function admirable, makes it be widely used in the middle of aeronautical product structure member.Wherein aircraft wing one of parts adopting composite structure the earliest especially.Traditional composite structure wing adopts upper and lower covering respectively shaping, then by assembly tooling by involutory for upper and lower covering, and and skeleton glued joint to have come the manufacture of composite wing.This method manufacturing processes is complicated, and the viscose glue used when upper and lower covering and skeleton glued joint can increase the construction weight of airfoil member greatly, and the cementing structure intensity of covering directly can affect the assembly structure intensity of whole airfoil member up and down.
By for many years grope test, composite product integral shaping method is ripe gradually and is progressively applied in the middle of actual production.Composite product integral shaping method, while simplification production process, reduces assembly tooling quantity, alleviates the construction weight of composite material structural member, improve its overall construction intensity.
After disclosing the paving of one " integrated forming method of closed composite material taper fairing " this forming method employing formpiston in patent of invention CN101811571A, transfer to the process that former adds vacuum-bag process.This forming method is mainly applicable to profile precision prescribed higher, shaping to shape in enclosed construction and the less demanding composite product of structural member overlay thickness., built-in function limited space less for overall dimensions, and product shape face, interior profile and overlay thickness are all had to the composite product of strict control overflow, adopt this forming method not produce to meet the composite product product that product technology requires.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes a kind of composite wing integral forming technique method and frock.This integral forming technique Method and process equipment solves composite wing because overall dimensions is less, built-in function limited space, cannot adopt the pressurization of placement vacuum bag at interiors of products and cause the technical problem that in product, outer mold surface and overlay thickness all cannot accurately ensure.Moulding technique can prepare that internal soundness is good, outer mold surface size precisely and strictly can control the composite wing of product overlay thickness.
The technical solution adopted for the present invention to solve the technical problems is: a kind of composite wing integral forming technique method, is characterized in that comprising the following steps:
Step 1. adopts digital control processing to complete former manufacture, utilizes former to manufacture formpiston; Difference paving composite layer on former patrix and former counterdie profile, and by former patrix and former counterdie involutory, pour into a mould silicon rubber mixed liquor at the composite wing internal cavities of involutory rear formation and carry out normal temperature cure, the demoulding after cured, deburring obtains formpiston;
Step 2. uses alcohol or acetone to clear up former patrix and former counterdie profile, and sprays releasing agent in profile;
Step 3. is the upper and lower aerofoil laying of difference paving composite wing on former patrix and former counterdie profile, adopt vacuum to take out pressure mode and pre-compacted is carried out to upper and lower aerofoil laying, paving separation layer in upper and lower aerofoil laying, wherein, lower aerofoil laying need successively reserve at the leading edge of a wing position prepreg length and top airfoil involutory time overlap joint, top airfoil laying need successively reduce at the leading edge of a wing position prepreg length and lower aerofoil involutory time overlap joint;
Step 4. places formpiston and leading edge of a wing part in composite wing lower aerofoil laying, the prepreg length of lower aerofoil laying in step 3 is overturn also paving at the upper and lower aerofoil laying overlap of the leading edge of a wing;
Former patrix overturns by step 5., involutory with former counterdie under the location of guide finger, and tightens up with fastening bolt;
Involutory former, formpiston and composite wing are put into autoclave by step 6., carry out heating cure by composite material forming curing process, and silicon rubber formpiston expands after heating, for briquetting pressure required during upper and lower aerofoil laying solidification;
Step 7. curing and demolding, and the silicon rubber formpiston removed in composite wing and separation layer, carry out deburring to product and obtain composite wing parts.
A kind of wing global formation frock for composite wing integral forming technique method, comprise former patrix, former counterdie, guide finger, fastening bolt, formpiston, it is characterized in that: adopt former and formpiston assistant formation, described former is upper and lower mold framework structure, former patrix and former counterdie both side edges there is multiple screw, wherein, former counterdie one upper lateral part is provided with guide finger, former patrix and former counterdie die body involutory time, adopt the profile of the upper and lower mould of guide finger location former involutory, former patrix and former counterdie die body are tightened up by fastening bolt; Described formpiston is overall structure, die body adopt silastic material, formpiston profile is the interior profile of composite wing, and in former profile curing molding; Former die body material is No. 45 steel or 7075 aluminium alloys.
Beneficial effect
The composite wing integral forming technique method that the present invention proposes and frock, adopt metal d ie and silicon rubber formpiston assistant formation; First processing and manufacturing former, and utilize former to manufacture formpiston; The cleaning upper and lower model face of former, and spray releasing agent; The upper and lower aerofoil of difference paving composite wing in former patrix, former counterdie profile; Under the wings of an airplane aerofoil is placed formpiston and leading edge of a wing part; By former patrix and former counterdie involutory; Former after involutory, formpiston and composite wing product put into solidification of hot-press tank; Curing and demolding, obtains integral composite wing product through deburring.Solve composite wing because whole interior bulk is less, built-in function limited space, cannot the pressurization of placement vacuum bag be adopted at interiors of products and cause the technical problem that in product, outer mold surface and overlay thickness all cannot accurately ensure, achieve the global formation of reduced size composite wing.Compared with traditional forming method, alleviate the overall weight of composite wing, improve its structural strength; The composite wing internal soundness of global formation is good, and outer airfoil molding surface size is accurate, can strictly control product overlay thickness simultaneously.
Composite wing integral forming technique method of the present invention and frock, be applicable to the global formation of reduced size composite wing, and shaped article steady quality is reliable.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of composite wing integral forming technique method of the present invention and frock are described in further detail.
Fig. 1 is integral forming technique method flow diagram of the present invention.
Fig. 2 is the wing laying schematic diagram of integral forming technique method of the present invention.
Fig. 3 is the former upper and lower mould frame-type die body structural representation of global formation frock of the present invention.
Fig. 4 is integral forming technique of the present invention equipment formpiston structural representation.
In figure
1. lower aerofoil laying overlap 6. top airfoil laying 7. former patrix 8. former counterdie 9. guide finger 10. fastening bolt 11. formpiston on releasing agent 2. separation layer 3. lower aerofoil laying 4. leading edge of a wing 5.
Detailed description of the invention
The present embodiment is a kind of composite wing integral forming technique method and frock.
The present embodiment is used in certain type reduced size composite wing global formation, and composite machine chord is 1.65 meters, and largest chord strong point is 0.26 meter, and maximum aerofoil profile height is 24 millimeters.Because composite aerofoil profile accessory size is less, inner space is narrow, is difficult to carry out paving operation from inside; But to outer mold surface precision in wing during product technology requires, part thickness all proposes high requirement, and requiring necessary global formation, as adopted conventional shaping method, being difficult to meet above-mentioned technical requirement.
Composite wing integral forming technique is equipped, and adopts former and formpiston assistant formation method; Former is divided into former patrix 7 and former counterdie 8 two parts according to airfoil chord plane, former is upper and lower mold framework structure, former patrix 7 and former counterdie 8 both side edges there is multiple screw, wherein, former counterdie 8 one upper lateral part is provided with guide finger 9, former patrix 7 die body and former counterdie 8 die body involutory time, adopt guide finger 9 to locate former patrix profile and former drag in the face of closing, former patrix 7 and former counterdie 8 die body are tightened up by fastening bolt 10.Former die body material is No. 45 steel or 7075 aluminium alloys.Formpiston 11 is overall structure, formpiston 11 die body adopt silastic material, formpiston 11 profile is the interior profile of composite wing, and in former profile curing molding;
Composite wing integral forming technique method, comprises the following steps:
(1) technological equipment manufacture: adopt digital control processing means to complete former manufacture, then paving composite wing actual products thick layer in the profile of former patrix 7 and former counterdie 8, and by involutory to former patrix 7, former counterdie 8 and composite wing product, in the composite wing interiors of products cavity of involutory rear formation, pour into a mould silicon rubber mixed liquor and carry out normal temperature cure, to be solidified complete after, the demoulding, deburring, obtain formpiston 11; Integral forming technique equipment adopts the global formation mode of metal d ie patrix 7, former counterdie 8 and silicon rubber formpiston 11 assistant formation; Wherein, formpiston 11 is shaping in former patrix 7 and former counterdie 8.
(2) prepare before producing: use alcohol or acetone cleaning former patrix 7 profile, former counterdie 8 profile and involutory surface, and smear water-soluble mold-release agent 1 in all profiles.
(3) upper lower aerofoil laying: by the requirement of product laying on former patrix 7 and former counterdie 8 profile, carry out the paving work of top airfoil laying 6 and lower aerofoil laying 3 respectively, in laying process, vacuum need be adopted to take out pressure mode pre-compacted is carried out to top airfoil laying 6 and lower aerofoil laying 3, finally paving separation layer 2 in top airfoil laying 6 and lower aerofoil laying 3; Wherein, the needs of overlap joint when lower aerofoil laying 3 successively need reserve prepreg length to meet involutory with top airfoil at leading edge of a wing position; The needs of overlap joint top airfoil laying 6 successively need reduce prepreg length to meet involutory with lower aerofoil during at leading edge of a wing position.
(4) place formpiston: in composite wing lower aerofoil laying 3, place formpiston 11 and the leading edge of a wing 4, and prepreg length reserved for lower aerofoil laying in step (3) 3 is overturn also paving on the upper lower aerofoil laying overlap 5 of the leading edge of a wing 4; By former patrix 7 under the location of guide finger 9 accurately and former counterdie 8 involutory, make accurately to overlap in top airfoil laying 6 and lower aerofoil laying 3 upper lower aerofoil laying overlap 5 region on the leading edge of a wing 4, ensure the continuity of whole product composite fiber, improve composite wing overall construction intensity.
(5) former upper and lower mould is involutory: overturn by former patrix 7, accurately involutory with former counterdie 8 under the location of guide finger 9, the top airfoil laying 6 making paving good and lower aerofoil laying 3 accurately overlap in upper lower aerofoil laying overlap 5 region on the leading edge of a wing 4, and tighten up former patrix 7 and former counterdie 8 die body with fastening bolt 10.
(6) solidify: former patrix 7, former counterdie 8, formpiston 11 and the composite wing product after involutory is put into autoclave when carrying out heating cure, the expansive force expanding generation after utilizing silicon rubber formpiston 11 to heat, as briquetting pressure required when ensureing that top airfoil laying 6 and lower aerofoil laying 3 are solidified, ensure that the global formation quality of composite wing.
(7) demoulding, deburring: cool to room temperature after solidification, is separated former patrix 7 with former counterdie 8, and the silicon rubber formpiston 11 removed in composite wing product and separation layer 2, obtain integral composite wing after carrying out deburring to product.

Claims (2)

1. a composite wing integral forming technique method, is characterized in that comprising the following steps:
Step 1. adopts digital control processing to complete former manufacture, utilizes former to manufacture formpiston; Difference paving composite layer on former patrix and former counterdie profile, and by former patrix and former counterdie involutory, pour into a mould silicon rubber mixed liquor at the composite wing internal cavities of involutory rear formation and carry out normal temperature cure, the demoulding after cured, deburring obtains formpiston;
Step 2. uses alcohol or acetone to clear up former patrix and former counterdie profile, and sprays releasing agent in profile;
Step 3. is the upper and lower aerofoil laying of difference paving composite wing on former patrix and former counterdie profile, adopt vacuum to take out pressure mode and pre-compacted is carried out to upper and lower aerofoil laying, paving separation layer in upper and lower aerofoil laying, wherein, lower aerofoil laying need successively reserve at the leading edge of a wing position prepreg length and top airfoil involutory time overlap joint, top airfoil laying need successively reduce at the leading edge of a wing position prepreg length and lower aerofoil involutory time overlap joint;
Step 4. places formpiston and leading edge of a wing part in composite wing lower aerofoil laying, the prepreg length of lower aerofoil laying in step 3 is overturn also paving at the upper and lower aerofoil laying overlap of the leading edge of a wing;
Former patrix overturns by step 5., involutory with former counterdie under the location of guide finger, and tightens up with fastening bolt;
Involutory former, formpiston and composite wing are put into autoclave by step 6., carry out heating cure by composite material forming curing process, and silicon rubber formpiston expands after heating, for briquetting pressure required during upper and lower aerofoil laying solidification;
Step 7. curing and demolding, and the silicon rubber formpiston removed in composite wing and separation layer, carry out deburring to product and obtain composite wing parts.
2. the composite wing global formation frock for claim 1, comprise former patrix, former counterdie, guide finger, fastening bolt, formpiston, it is characterized in that: adopt former and formpiston assistant formation, described former is upper and lower mold framework structure, former patrix and former counterdie both side edges there is multiple screw, wherein, former counterdie one upper lateral part is provided with guide finger, former patrix and former counterdie die body involutory time, adopt the profile of the upper and lower mould of guide finger location former involutory, former patrix and former counterdie die body are tightened up by fastening bolt; Described formpiston is overall structure, die body adopt silastic material, formpiston profile is the interior profile of composite wing, and in former profile curing molding; Former die body material is No. 45 steel or 7075 aluminium alloys.
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Cited By (17)

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Publication number Priority date Publication date Assignee Title
CN105500730A (en) * 2015-12-24 2016-04-20 中航复合材料有限责任公司 High-precision forming mold and method for thickly-laid composite material boxes
CN106965464A (en) * 2016-01-13 2017-07-21 哈尔滨飞机工业集团有限责任公司 A kind of shaping pressure method of solution R angles gum deposit
WO2018014735A1 (en) * 2016-07-18 2018-01-25 深圳光启高等理工研究院 Female moulding method for composite material workpiece
CN107696522A (en) * 2017-09-29 2018-02-16 江西昌河航空工业有限公司 A kind of carbon fibre fabric method for forming parts at band R angles
CN108891040A (en) * 2018-06-21 2018-11-27 西安爱生技术集团公司 A kind of small and medium size unmanned aerial vehicles composite horizontal empennage manufacturing method
CN108995246A (en) * 2018-06-20 2018-12-14 西北工业大学 A kind of small-sized wing integrally forming mould and forming method based on VARTM
CN109304876A (en) * 2018-11-16 2019-02-05 中航复合材料有限责任公司 A kind of RTM forming method of composite material blade
CN109605777A (en) * 2018-12-03 2019-04-12 江西洪都航空工业集团有限责任公司 A kind of prefabricated manufacturing method of solid core composite material edge strip
CN109849362A (en) * 2019-01-12 2019-06-07 航天神舟飞行器有限公司 A kind of unmanned plane winglet manufacturing method
CN109927315A (en) * 2019-01-17 2019-06-25 福建振丰矿物新材料有限公司 A kind of heat pressing forming device and technique of composite material
CN110303693A (en) * 2019-06-21 2019-10-08 江西洪都航空工业集团有限责任公司 A kind of compression-moulding methods of small-sized aerofoil Composite Sandwich part
CN110682544A (en) * 2019-10-08 2020-01-14 江西洪都航空工业集团有限责任公司 Gluing mold and gluing method for thin-wall composite material leading edge fairing
CN110789147A (en) * 2018-08-01 2020-02-14 杭州飞鹰船艇有限公司 Method for manufacturing racing boat oar frame
CN110843236A (en) * 2019-11-25 2020-02-28 北京航空航天大学 Preparation method of carbon fiber composite hollow blade
CN111688238A (en) * 2020-05-27 2020-09-22 长春三友智造科技发展有限公司 Method for forming thermosetting polymer fiber composite material part
CN112454943A (en) * 2020-11-06 2021-03-09 无锡向维新材料科技有限公司 Carbon fiber aramid fiber composite material and integrated forming preparation method thereof
CN112477192A (en) * 2020-10-22 2021-03-12 南京东聚碳纤维复合材料研究院有限公司 Forming method of high-rigidity conical-structure carbon fiber composite material pipe

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Cited By (20)

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Publication number Priority date Publication date Assignee Title
CN105500730A (en) * 2015-12-24 2016-04-20 中航复合材料有限责任公司 High-precision forming mold and method for thickly-laid composite material boxes
CN105500730B (en) * 2015-12-24 2020-06-09 中航复合材料有限责任公司 High-precision forming die and method for thick-layer composite material box
CN106965464A (en) * 2016-01-13 2017-07-21 哈尔滨飞机工业集团有限责任公司 A kind of shaping pressure method of solution R angles gum deposit
WO2018014735A1 (en) * 2016-07-18 2018-01-25 深圳光启高等理工研究院 Female moulding method for composite material workpiece
CN107696522A (en) * 2017-09-29 2018-02-16 江西昌河航空工业有限公司 A kind of carbon fibre fabric method for forming parts at band R angles
CN108995246A (en) * 2018-06-20 2018-12-14 西北工业大学 A kind of small-sized wing integrally forming mould and forming method based on VARTM
CN108891040A (en) * 2018-06-21 2018-11-27 西安爱生技术集团公司 A kind of small and medium size unmanned aerial vehicles composite horizontal empennage manufacturing method
CN110789147A (en) * 2018-08-01 2020-02-14 杭州飞鹰船艇有限公司 Method for manufacturing racing boat oar frame
CN109304876B (en) * 2018-11-16 2020-10-20 中航复合材料有限责任公司 RTM (resin transfer molding) method for composite material blade
CN109304876A (en) * 2018-11-16 2019-02-05 中航复合材料有限责任公司 A kind of RTM forming method of composite material blade
CN109605777A (en) * 2018-12-03 2019-04-12 江西洪都航空工业集团有限责任公司 A kind of prefabricated manufacturing method of solid core composite material edge strip
CN109849362A (en) * 2019-01-12 2019-06-07 航天神舟飞行器有限公司 A kind of unmanned plane winglet manufacturing method
CN109927315A (en) * 2019-01-17 2019-06-25 福建振丰矿物新材料有限公司 A kind of heat pressing forming device and technique of composite material
CN110303693A (en) * 2019-06-21 2019-10-08 江西洪都航空工业集团有限责任公司 A kind of compression-moulding methods of small-sized aerofoil Composite Sandwich part
CN110303693B (en) * 2019-06-21 2021-08-20 江西洪都航空工业集团有限责任公司 Compression molding method for small-sized airfoil composite sandwich piece
CN110682544A (en) * 2019-10-08 2020-01-14 江西洪都航空工业集团有限责任公司 Gluing mold and gluing method for thin-wall composite material leading edge fairing
CN110843236A (en) * 2019-11-25 2020-02-28 北京航空航天大学 Preparation method of carbon fiber composite hollow blade
CN111688238A (en) * 2020-05-27 2020-09-22 长春三友智造科技发展有限公司 Method for forming thermosetting polymer fiber composite material part
CN112477192A (en) * 2020-10-22 2021-03-12 南京东聚碳纤维复合材料研究院有限公司 Forming method of high-rigidity conical-structure carbon fiber composite material pipe
CN112454943A (en) * 2020-11-06 2021-03-09 无锡向维新材料科技有限公司 Carbon fiber aramid fiber composite material and integrated forming preparation method thereof

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