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 PDFInfo
- 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
- Authority
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- Prior art keywords
- former
- wing
- composite
- formpiston
- counterdie
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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- 239000002131 composite material Substances 0.000 title claims abstract description 81
- 238000000465 moulding Methods 0.000 title claims abstract description 12
- 238000004519 manufacturing process Methods 0.000 claims abstract description 15
- 229920002379 silicone rubber Polymers 0.000 claims abstract description 12
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 5
- 238000000034 method Methods 0.000 claims description 24
- 230000015572 biosynthetic process Effects 0.000 claims description 19
- 238000005755 formation reaction Methods 0.000 claims description 19
- 238000000926 separation method Methods 0.000 claims description 7
- CSCPPACGZOOCGX-UHFFFAOYSA-N acetone Chemical compound 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- 238000010438 heat treatment Methods 0.000 claims description 5
- 238000007711 solidification Methods 0.000 claims description 4
- 229910001008 7075 aluminium alloy Inorganic materials 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N ethanol Chemical compound data:image/svg+xml;base64,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 data:image/svg+xml;base64,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 CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 3
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- 239000010959 steel Substances 0.000 claims description 3
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- 238000004140 cleaning Methods 0.000 abstract description 3
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- 239000002184 metal Substances 0.000 abstract description 3
- 238000007731 hot pressing Methods 0.000 abstract 1
- 238000009966 trimming Methods 0.000 abstract 1
- 238000007493 shaping process Methods 0.000 description 6
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- 210000002356 Skeleton Anatomy 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229920000297 Rayon Polymers 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 239000006082 mold release agent Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
Classifications
-
- 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
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, 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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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2562834A1 (en) * | 1984-04-12 | 1985-10-18 | Ranjon Marc | Process for manufacturing strong hollow components, especially parts of aircraft or of missiles, and components obtained thereby |
| US5112663A (en) * | 1991-04-22 | 1992-05-12 | General Dynamics Corporation, Convair Division | Method of manufacturing composite structures |
| US6117376A (en) * | 1996-12-09 | 2000-09-12 | Merkel; Michael | Method of making foam-filled composite products |
| WO2014070381A1 (en) * | 2012-10-31 | 2014-05-08 | The Boeing Company | System and method for manufacturing monolithic structures using expanding internal tools |
-
2014
- 2014-12-16 CN CN201410781517.9A patent/CN104626605B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2562834A1 (en) * | 1984-04-12 | 1985-10-18 | Ranjon Marc | Process for manufacturing strong hollow components, especially parts of aircraft or of missiles, and components obtained thereby |
| US5112663A (en) * | 1991-04-22 | 1992-05-12 | General Dynamics Corporation, Convair Division | Method of manufacturing composite structures |
| US6117376A (en) * | 1996-12-09 | 2000-09-12 | Merkel; Michael | Method of making foam-filled composite products |
| WO2014070381A1 (en) * | 2012-10-31 | 2014-05-08 | The Boeing Company | System and method for manufacturing monolithic structures using expanding internal tools |
Non-Patent Citations (1)
| Title |
|---|
| 张玉龙: "《塑料制品加工中质量控制与故障排除》", 31 January 2010 * |
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