CN104626605B - 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 PDFInfo
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- CN104626605B CN104626605B CN201410781517.9A CN201410781517A CN104626605B CN 104626605 B CN104626605 B CN 104626605B CN 201410781517 A CN201410781517 A CN 201410781517A CN 104626605 B CN104626605 B CN 104626605B
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- former
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- formpiston
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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
- B29C70/34—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
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
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
Technical field
The invention belongs to System for aircraft manufacturing technology equipment technology field, specifically, it is related to a kind of composite wing overall
Moulding technique and frock are it is adaptable 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,
It is made to be widely used in the middle of aeronautical product structure member.Wherein aircraft wing is even more the part adopting composite structure earliest
One of.Traditional composite structure wing is molded respectively using upper and lower covering, then passes through assembly tooling by upper and lower covering pair
Close, and glued joint to complete the manufacture of composite wing with skeleton.This method manufacturing processes complexity, upper and lower covering and bone
The viscose glue that frame uses when glueing joint can greatly increase the construction weight of airfoil member, and the cementing structure intensity of upper and lower covering can be directly
Affect the assembling structure intensity of whole airfoil member.
Tested by groping for many years, composite product integral shaping method is gradually ripe and is progressively applied to reality
In the middle of border produces.Composite product integral shaping method, while simplifying production process, reduces assembly tooling quantity, mitigates
The construction weight of composite material structural member, improves its overall construction intensity.
A kind of " closed composite material taper fairing global formation side is disclosed in patent of invention CN101811571A
After this forming method of method " adopts formpiston paving, transfer to the process that former adds vacuum-bag process.This forming method is mainly fitted
For higher to profile precision prescribed, to shape in enclosed construction and the less demanding composite product of structural member overlay thickness
Shaping.For overall dimensions are less, built-in function limited space, and product shape face, inner mold face and overlay thickness are all had sternly
Lattice control the composite product requiring, and can not produce the composite meeting product technology requirement using this forming method
Product product.
Content of the invention
The deficiency existing in order to avoid prior art, the present invention proposes a kind of composite wing integral forming technique method
And frock.This integral forming technique method and technological equipment solve composite wing because overall dimensions are less, internal behaviour
Make limited space it is impossible to cause outer mold surface and overlay thickness in product all cannot in interiors of products using placing vacuum bag pressurization
The technical problem accurately ensureing.Moulding technique can prepare that internal soundness is good, outer mold surface size control can precisely and strictly
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 side
Method is it is characterised in that comprise the following steps:
Step 1. completes former manufacture using digital control processing, manufactures formpiston using former；Mould and mould under former on former
Difference paving composite layer on type face, and by mould pairing under mould on former and former, the composite machine of formation after pairing
Wing internal cavities cast silicon rubber mixed liquor simultaneously carries out normal temperature cure, the demoulding after cured, and deburring obtains formpiston；
Step 2. uses mould and former drag face on alcohol or acetone cleaning former, and sprays releasing agent on type face；
Step 3. mould and difference paving composite wing upper and lower aerofoil laying on former drag face on former, adopt
Take out pressure mode with vacuum and pre-compacted is carried out to upper and lower aerofoil laying, paving separation layer in upper and lower aerofoil laying, wherein, bottom wing
Overlap when face laying need to successively reserve prepreg length and top airfoil pairing at leading edge of a wing position, top airfoil laying is before wing
Overlap joint when prepreg length and lower aerofoil pairing need to successively be reduced in edge position；
Step 4. places formpiston and leading edge of a wing part in composite wing lower aerofoil laying, by bottom wing in step 3
The prepreg length of face laying overturns simultaneously paving in the upper and lower aerofoil laying overlap of the leading edge of a wing；
Mould on former is overturn by step 5., with mould pairing under former under the positioning of guide finger, and is fastened with fastening bolt；
Step 6. puts into the former of pairing, formpiston and composite wing in autoclave, by composite forming and hardening
Technique carries out heating cure, and silicon rubber formpiston expands after heating, required shaping pressure when solidifying for upper and lower aerofoil laying
Power；
Step 7. curing and demolding, and remove silicon rubber formpiston and the separation layer in composite wing, product is carried out
Deburring obtains composite wing part.
A kind of wing global formation frock for composite wing integral forming technique method, including mould on former,
Mould under former, guide finger, fastening bolt, formpiston it is characterised in that:Using former and formpiston assistant formation, described former be upper,
Low mold frame frame structure, former has multiple screws in mould and mould both side edges under former, wherein, under former, mould one upper lateral part is provided with and leads
To pin, on former, mould, closes using faced by the type of the guiding upper and lower mould of finger setting former, on former during mould die body pairing with former
Mould is fastened by fastening bolt with mould die body under former；Described formpiston is overall structure, and die body adopts silastic material, formpiston type
Face is the inner mold face of composite wing, and curing molding in former type face；Former die body material is No. 45 steel or 7075 aluminium
Alloy.
Beneficial effect
Composite wing integral forming technique method proposed by the present invention and frock, using metal d ie and silicon rubber sun
Mould assistant formation；Fabricate former first, and manufacture formpiston using former；Cleaning former upper and lower model face, and spray the demoulding
Agent；Mould, the upper and lower aerofoil of paving composite wing respectively on former drag face on former；Place on aerofoil under the wings of an airplane
Formpiston and leading edge of a wing part；By mould on former and mould pairing under former；Former after pairing, formpiston and composite wing produce
Product put into solidification of hot-press tank；Curing and demolding, obtains integral composite wing product through deburring.Solve composite machine
The wing is because whole interior bulk is less, built-in function limited space is it is impossible to be pressurizeed using placing vacuum bag in interiors of products
And cause technical problem that outer mold surface and overlay thickness in product all cannot accurately ensure it is achieved that reduced size composite machine
The global formation of the wing.Compared with traditional forming method, alleviate the overall weight of composite wing, improve its structure strong
Degree；The composite wing internal soundness of global formation is good, and outer airfoil molding surface size precisely, can strictly control product to spread simultaneously
Thickness degree.
Composite wing integral forming technique method of the present invention and frock, are applied to reduced size composite wing
Global formation, shaped article steady quality is reliable.
Brief description
Below in conjunction with the accompanying drawings with embodiment to a kind of present invention composite wing integral forming technique method and frock
It is 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 equips formpiston structural representation for integral forming technique of the present invention.
In figure
1. lower aerofoil laying overlap 6. on releasing agent 2. separation layer 3. lower aerofoil laying 4. leading edge of a wing 5.
Mould 9. guide finger 10. fastening bolt 11. formpiston under mould 8. former on top airfoil laying 7. former
Specific embodiment
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, composite wing a length of 1.65
Rice, largest chord strong point is 0.26 meter, and maximum aerofoil profile height is 24 millimeters.Because composite aerofoil profile accessory size is less, internal
Narrow space, is difficult to carry out paving operation from inside；But the interior outer mold surface precision to wing, part thickness in product technology requirement
All propose high requirement, and require necessary global formation, such as adopt conventional shaping method, be difficult to meet above-mentioned technical requirements.
Composite wing integral forming technique is equipped, using former and formpiston assistant formation method；Former is according to wing
String plane is divided into mould 8 two parts under mould 7 and former on former, and former is upper and lower mold framework structure, under mould 7 and former on former
Multiple screws are had, wherein, under former, mould 8 one upper lateral part is provided with guide finger 9, under mould 7 die body and former on former in mould 8 both side edges
During mould 8 die body pairing, using model face on guide finger 9 positioning former with former drag in the face of closing, under mould 7 and former on former
Mould 8 die body is fastened 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 adopts silastic material, and formpiston 11 type face is the inner mold face of composite wing, and solidifies in former type face
Shaping；
Composite wing integral forming technique method, comprises the following steps:
(1) technological equipment manufacture:Complete former manufacture using digital control processing means, then under mould 7 and former on former
Paving composite wing actual products thick layer on the type face of mould 8, and by mould 8 and composite machine under mould on former 7, former
Wing product pairing, pours into a mould silicon rubber mixed liquor and carry out normal temperature after pairing in the composite wing interiors of products cavity being formed
Solidification, to be solidified after the completion of, the demoulding, deburring, obtain formpiston 11；Integral forming technique equipment is using mould 7, former on metal d ie
Lower mould 8 and the global formation mode of silicon rubber formpiston 11 assistant formation；Wherein, in mould 8 under formpiston 11 mould 7 and former on former
Shaping.
(2) prepare before producing:Using mould 7 type face on alcohol or acetone cleaning former, mould 8 type face and involutory surface under former,
And water-soluble mold-release agent 1 is smeared on all models face.
(3) upper lower aerofoil laying:By product laying requirement on mould 8 type face under mould 7 and former on former, carry out respectively on
The paving work of aerofoil laying 6 and lower aerofoil laying 3, during laying, need to take out pressure mode to top airfoil laying 6 using vacuum
Carry out pre-compacted with lower aerofoil laying 3, finally paving separation layer 2 in top airfoil laying 6 and lower aerofoil laying 3；Wherein, bottom wing
The needs that face laying 3 need to successively reserve prepreg length to overlap when meeting with top airfoil pairing at leading edge of a wing position；Upper limb
The needs that face laying 6 need to successively reduce prepreg length to overlap when meeting with lower aerofoil pairing at leading edge of a wing position.
(4) place formpiston:Place formpiston 11 and the leading edge of a wing 4 in composite wing lower aerofoil laying 3, and by step
(3) the prepreg length that in, lower aerofoil laying 3 is reserved overturns and paving is on the upper lower aerofoil laying overlap 5 of the leading edge of a wing 4；
By mould on former 7 under the positioning of guide finger 9 mould 8 pairing accurately and under former, make top airfoil laying 6 and lower aerofoil laying 3
In upper lower aerofoil laying overlap 5 region on the leading edge of a wing 4 accurately overlap joint it is ensured that the company of whole product composite fiber
Continuous property, improves composite wing overall construction intensity.
(5) former upper and lower mould pairing:Mould on former 7 is overturn, accurately right with mould under former 8 under the positioning of guide finger 9
Close, make the good top airfoil laying 6 of paving and lower aerofoil laying 3 in upper lower aerofoil laying overlap 5 region on the leading edge of a wing 4
Accurately overlap, and with mould 8 die body under mould 7 on fastening bolt 10 fastening former and former.
(6) solidify:Mould 8, formpiston 11 and composite wing product under mould 7 on former after pairing, former are put into heat
When carrying out heating cure in pressure tank, the expansive force expanding generation by the use of silicon rubber formpiston 11 after heating is as guarantee top airfoil
Required briquetting pressure when laying 6 and lower aerofoil laying 3 solidification is it is ensured that the global formation quality of composite wing.
(7) demoulding, deburring:It is cooled to room temperature after solidification, mould 8 under mould on former 7 and former is separated, and removes composite wood
Silicon rubber formpiston 11 in material wing product and separation layer 2, carry out obtaining integral composite wing after deburring to product.
Claims (2)
1. a kind of composite wing integral forming technique method is it is characterised in that comprise the following steps:
Step 1. completes former manufacture using digital control processing, manufactures formpiston using former；Mould and former drag face on former
Upper paving composite layer respectively, and by mould on former and mould pairing under former, in the composite wing being formed after pairing
Portion's cavity cast silicon rubber mixed liquor simultaneously carries out normal temperature cure, the demoulding after cured, and deburring obtains formpiston；
Step 2. uses mould and former drag face on alcohol or acetone cleaning former, and sprays releasing agent on type face；
Step 3. mould and difference paving composite wing upper and lower aerofoil laying on former drag face on former, using true
Sky is taken out pressure mode and is carried out pre-compacted to upper and lower aerofoil laying, paving separation layer in upper and lower aerofoil laying, and wherein, lower aerofoil spreads
Overlap joint when layer need to successively reserve prepreg length and top airfoil pairing at leading edge of a wing position, top airfoil laying is in leading edge of a wing portion
Overlap joint when prepreg length and lower aerofoil pairing need to successively be reduced in position；
Step 4. places formpiston and leading edge of a wing part in composite wing lower aerofoil laying, and lower aerofoil in step 3 is spread
The prepreg length of layer overturns simultaneously paving in the upper and lower aerofoil laying overlap of the leading edge of a wing；
Mould on former is overturn by step 5., with mould pairing under former under the positioning of guide finger, and is fastened with fastening bolt；
Step 6. puts into the former of pairing, formpiston and composite wing in autoclave, by composite forming and hardening technique
Carry out heating cure, silicon rubber formpiston expands after heating, required briquetting pressure when solidifying for upper and lower aerofoil laying；
Step 7. curing and demolding, and remove silicon rubber formpiston and the separation layer in composite wing, deburring is carried out to product
Obtain composite wing part.
2. a kind of composite wing global formation frock for claim 1, including mould, guiding under mould on former, former
Pin, fastening bolt, formpiston it is characterised in that:Using former and formpiston assistant formation, described former is upper and lower mold framework structure,
Multiple screws are had in mould and mould both side edges under former, wherein, under former, mould one upper lateral part is provided with guide finger, mould on former on former
, close using faced by the type of the guiding upper and lower mould of finger setting former during mould die body pairing with former, mould and mould mould under former on former
Body is fastened by fastening bolt；Described formpiston is overall structure, and die body adopts silastic material, and formpiston type face is composite machine
The inner mold face of the wing, and curing molding in former type face；Former die body material is No. 45 steel or 7075 aluminium alloys.
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| CN201410781517.9A CN104626605B (en) | 2014-12-16 | 2014-12-16 | Composite material wing integral molding technological method and composite material wing integral molding tool |
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| CN201410781517.9A CN104626605B (en) | 2014-12-16 | 2014-12-16 | Composite material wing integral molding technological method and composite material wing integral molding tool |
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| CN104626605A CN104626605A (en) | 2015-05-20 |
| CN104626605B true CN104626605B (en) | 2017-02-22 |
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| US6117376A (en) * | 1996-12-09 | 2000-09-12 | Merkel; Michael | Method of making foam-filled composite products |
| US9498903B2 (en) * | 2012-10-31 | 2016-11-22 | The Boeing Company | System and method for manufacturing monolithic structures using expanding internal tools |
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