CN106976187B - A kind of more curved surfaces close corner structure technique for aircraft composite forming parts tooling - Google Patents
A kind of more curved surfaces close corner structure technique for aircraft composite forming parts tooling Download PDFInfo
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- CN106976187B CN106976187B CN201710239904.3A CN201710239904A CN106976187B CN 106976187 B CN106976187 B CN 106976187B CN 201710239904 A CN201710239904 A CN 201710239904A CN 106976187 B CN106976187 B CN 106976187B
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- module
- seperated
- seperated module
- curved surfaces
- corner structure
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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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/30—Mounting, exchanging or centering
- B29C33/301—Modular mould systems [MMS], i.e. moulds built up by stacking mould elements, e.g. plates, blocks, rods
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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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
- B29C33/3835—Designing moulds, e.g. using CAD-CAM
-
- 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
-
- 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
Abstract
The invention belongs to technical field of composite material manufacturing, it is related to a kind of more curved surfaces and closes corner structure technique for aircraft composite forming parts tooling.Forming frock is divided into five seperated modules by the present invention, support base is first closed corner structure technique for aircraft composite part and preceding seperated module from more curved surfaces, left seperated module, middle seperated module, right seperated module, unloaded in rear seperated module by knockout course after alloing forming parts, middle seperated module is taken out from unitary mould using crowbar again, then left seperated module and right seperated module are removed, preceding seperated module and rear seperated module are taken out from part finally, complete the demoulding of part.This die design method can solve almost all of complexity and close the release problems of corner structure composite material parts, while guarantee the quality of part after the operability and molding of part manufacturing process.
Description
Technical field
The invention belongs to technical field of composite material manufacturing, it is related to a kind of more curved surfaces and closes corner structure technique for aircraft composite part
Forming frock.
Background technique
Composite material is due to its high specific strength, and high specific stiffness, designability are strong, fatigue crack-resistant performance is good, corrosion-resistant, ruler
The advantages that very little stability is good and is convenient for large area monolithic molding, it has also become one of the present age most important Aircraft Structure Materials.It is multiple
The position and dosage that condensation material is applied aboard have become one of the outstanding feature for measuring aircaft configuration advance.With compound
The continuous improvement of material dosage and composite material parts design level aboard, composite material parts also by original " C " type,
The conventional shapes such as " L " type, " I " type, T-shape continue to develop, and more curved surfaces occur and close the irregular shapes such as corner structure, this is to compound
More stringent requirements are proposed for the molding of material.Composite material shaping mould includes metal die, composite material mould, rubber at present
Mold, foam mold, gypsum mold and soluble polymer mold etc..The manufacture of traditional irregular shape structural composite material part
The forming parts such as rubber shrinking die, foam, gypsum can be used can obtain part, but these moulds by way of destroying mold later
Tool is only applicable to form once or several times, is unfavorable for producing in batches, and using the composite material component port of these molds manufacture
Face precision, quality etc. are generally not so good as metal die.Corner structure composite material parts are closed with the more curved surfaces of metals mold manufacturing, are needed
Split mold is designed, and can guarantee parts quality, the Split mold for being easy to demould and structure design, the accuracy of manufacture and cooperation are positioned
Suffer from higher requirement.
Summary of the invention
The purpose of the present invention is to provide it is a kind of design rationally, the accuracy of manufacture it is high for a kind of more curved surfaces close corner structure fly
The molding metal die of machine composite material parts, at the same solve more curved surfaces close corner structure technique for aircraft composite part molding and
Release problems.
The technical scheme is that
More curved surfaces close corner structure technique for aircraft composite forming parts tooling include preceding seperated module, left seperated module, in point
Module, right seperated module, rear seperated module and support base, preceding fission module, left seperated module, middle seperated module, right point
The outer mold surface of unitary mould and more curved surfaces close the inner mold of corner structure technique for aircraft composite part after module, rear seperated block combiner
Face is consistent, loaded on support bottom after preceding fission module, left seperated module, middle seperated module, right seperated module, rear seperated module cooperation
It is positioned on seat, the assembly after the left seperated module, middle seperated module, right seperated block combiner divides with preceding seperated module
It is 90 ° of 75 °≤α < from the angle α of face and support base plane, after left fission module, middle seperated module, right seperated block combiner
Assembly with the parting surface of rear seperated module and the angle β of support base plane be 75 °≤β≤90 °；Middle fission module is to fall
T shape, left fission module and middle seperated module there are two parting surfaces, i.e. lower-left parting surface and left parting surface, lower-left parting surface and
The plane of support base is parallel, and the angle of left parting surface and lower-left parting surface is θ, and the angle θ is closed corner structure aircraft greater than more curved surfaces and answered
1 °~20 ° of angle between condensation material part transverse center section and horizontal plane, there are two with middle seperated module for right fission module
Parting surface, i.e. bottom right parting surface and right parting surface, bottom right parting surface is parallel with the plane of support base, right parting surface and bottom right point
Angle from face is 180 ° of-θ.
The described left seperated module on the contact surface of middle seperated module, stay that there are two demoulding notches, when for demoulding
The separation of left fission module and middle seperated module.
The described right seperated module on the contact surface of middle seperated module, stay that there are two demoulding notches, when for demoulding
The separation of right fission module and middle seperated module.
Preceding seperated module, left seperated module, middle seperated module, right seperated module, rear seperated module and a branch
Support pedestal is all made of numerical control processing manufacture.
All mold materials all use Steel material or aluminum material.
Unitary mould after the combination can be used for part laying and the thermoforming of fiber-reinforced resin base prepreg.
During demoulding first by support base from more curved surfaces close corner structure technique for aircraft composite part and preceding seperated module,
Left fission module middle seperated module, right seperated module, unloads in rear seperated module, then middle seperated module is taken out, and then removes
Left fission module and right seperated module, preceding seperated module and rear seperated module are finally removed, complete the de- of part from part
Mold process.
This programme the utility model has the advantages that
The present invention solves the molding and release problems that more curved surfaces close corner structure technique for aircraft composite part, compared to traditional mould
Have, the outer dimension precision for guaranteeing part is cooperated by rigid Split mold, while designing and taking off using reasonable drafting angle
Mould mode solves the release problems that more curved surfaces close corner structure, the knockout course after alloing forming parts first by support base from
More curved surfaces close corner structure technique for aircraft composite part and preceding seperated module, left seperated module, middle seperated module, right seperated module,
Unloaded in seperated module afterwards, then middle seperated module taken out from unitary mould using crowbar, then remove left seperated module and
Preceding seperated module and rear seperated module are finally taken out from part, complete the demoulding of part by right fission module.This mold is set
Meter method can solve almost all of complexity and close the release problems of corner structure composite material parts, while guarantee part manufacturing mistake
The quality of part after the operability and molding of journey.
Present invention is mainly used for the manufactures that more curved surfaces close corner structure technique for aircraft composite part.More curved surfaces of the invention close angle
Structure technique for aircraft composite forming parts tooling uses Split mold and compounding technique, using five pieces of Split molds and a pedestal
Unitary mould is combined into as prepreg laying mold, can guarantee mould by five pieces of Split molds and the bit combination of support base
Have position, control element precision；Split pattern can be dismantled simultaneously, the release problems after solving forming parts.
Detailed description of the invention
Fig. 1 is that more curved surfaces that are used for of the invention close corner structure technique for aircraft composite forming parts tooling schematic diagram, wherein 1
It is preceding seperated module, 2 be left seperated module, and 3 be middle seperated module, and 4 be right seperated module, and 5 be rear seperated module, and 6 be support
Pedestal.
Fig. 2 is that of the invention close corner structure technique for aircraft composite forming parts tooling base for more curved surfaces and separate is illustrated
Figure, wherein the assembly being made of preceding seperated module, left seperated module, middle seperated module, right seperated module, rear seperated module
Mo(u)ld bottom half face is consistent with the type face of pedestal die cavity.
Fig. 3 is the side closed after corner structure technique for aircraft composite forming parts tooling removing pedestal for more curved surfaces of the invention
View, wherein 7 be assembly after left seperated module, middle seperated module, right seperated block combiner and the separation of preceding seperated module
Face, 8 be assembly after left seperated module, middle seperated module, right seperated block combiner and the parting surface of seperated module afterwards, and 9 are
Support base plane, α are assembly after left seperated module, middle seperated module, right seperated block combiner and preceding seperated module
The angle of parting surface and support base plane, β are the assembly after left seperated module, middle seperated module, right seperated block combiner
With the angle of the parting surface of rear seperated module and support base plane.
Fig. 4 be it is of the invention for more curved surfaces close corner structure technique for aircraft composite forming parts tooling left seperated module,
Mold after middle fission module, right seperated block combiner and the parting surface cross-sectional view of preceding seperated module, 10 for left fission module and
The lower-left parting surface of middle fission module, 11 be the left parting surface of left seperated module and middle seperated module, angle θ.12 be the right side
The bottom right parting surface of seperated module and middle seperated module, 13 be the right parting surface of right seperated module and middle seperated module, angle
For (180 ° of-θ).14 be the crowbar mouth on left separation module, and 15 be the crowbar mouth on right separation module.
Specific embodiment
It elaborates with reference to the accompanying drawing to the present invention.
More curved surfaces close corner structure technique for aircraft composite forming parts tooling include preceding seperated module 1, left seperated module 2, in
Seperated module 3, right seperated module 4,5 and 6 support base of rear seperated module.When in use, first by preceding seperated module 1, left fission
Module 2, middle seperated module 3, right seperated module 4, rear seperated module 5 are combined, and are then placed in 6 support bases and are determined
Position then carries out laying encapsulation and solidification in unitary mould.
Knockout course after forming parts, can first by support base 6 from part and preceding seperated module 1, left seperated module 2,
Middle fission module 3, right seperated module 4 unload in rear seperated module 5, then pass through the crowbar mouth 14 on left separation module, the right side point
From the crowbar mouth 15 in module, by middle seperated module 3 along left seperated module and the left parting surface 11 of middle seperated module and right fission
Module is taken out with right 13 faces that separate of middle seperated module, then removes left seperated module 2 and right seperated module 4, finally from part
Seperated module 1 and rear seperated module 5, are finally completed the knockout course of part before taking out.
In above-mentioned technical proposal, seperated module before described 1,2 left seperated modules, seperated module in 3,4 right seperated modules,
Seperated module and 6 support bases are all made of metal material Q235A steel numerical control processing manufacture to guarantee high temperature, high-pressure molding mistake after 5
The rigidity and precision of journey mould structure, it can be ensured that the Forming Quality and precision of part.
Claims (7)
1. a kind of more curved surfaces close corner structure technique for aircraft composite forming parts tooling, which is characterized in that more curved surfaces close corner structure and fly
Machine composite material parts forming frock includes preceding fission module, left seperated module, middle seperated module, right seperated module, rear fission
Module and support base, it is whole after preceding fission module, left seperated module, middle seperated module, right seperated module, rear seperated block combiner
The outer mold surface of mould is consistent with the inner mold face that more curved surfaces close corner structure technique for aircraft composite part, preceding fission module, left fission
It is loaded in support base and positions after module, middle fission module, right seperated module, rear seperated module cooperation, the left split pattern
Assembly after block, middle seperated module, right seperated block combiner and the folder of the parting surface of preceding seperated module and support base plane
Angle α is 90 ° of 75 °≤α <, the assembly after left fission module, middle seperated module, right seperated block combiner and seperated module afterwards
Parting surface and the β of support base plane included angle are 75 °≤β≤90 °；It is middle fission module be inverted T-shaped, it is left fission module with it is middle seperated
For module there are two parting surfaces, i.e. lower-left parting surface and left parting surface, lower-left parting surface is parallel with the plane of support base, a left side point
Angle from face and lower-left parting surface is θ, the angle θ be greater than more curved surfaces close corner structure technique for aircraft composite part transverse center section with
1 °~20 ° of angle between horizontal plane, there are two parting surfaces, i.e. bottom right parting surface and the right side point with middle seperated module for right fission module
From face, bottom right parting surface is parallel with the plane of support base, and the angle of right parting surface and bottom right parting surface is 180 ° of-θ.
2. a kind of more curved surfaces as described in claim 1 close corner structure technique for aircraft composite forming parts tooling, which is characterized in that
The described left seperated module on the contact surface of middle seperated module, stay there are two demoulding notch, left split pattern when for demoulding
The separation of block and middle seperated module.
3. a kind of more curved surfaces as described in claim 1 close corner structure technique for aircraft composite forming parts tooling, which is characterized in that
The described right seperated module on the contact surface of middle seperated module, stay there are two demoulding notch, right split pattern when for demoulding
The separation of block and middle seperated module.
4. a kind of more curved surfaces as described in claim 1 close corner structure technique for aircraft composite forming parts tooling, which is characterized in that
The described preceding seperated module, left seperated module, middle seperated module, right seperated module, rear seperated module and a support base are equal
It is manufactured using numerical control processing.
5. a kind of more curved surfaces as described in claim 1 close corner structure technique for aircraft composite forming parts tooling, which is characterized in that
All mold materials all use Steel material or aluminum material.
6. a kind of more curved surfaces as described in claim 1 close corner structure technique for aircraft composite forming parts tooling, which is characterized in that
Unitary mould after the combination can be used for part laying and the thermoforming of fiber-reinforced resin base prepreg.
7. a kind of more curved surfaces as described in claim 1 close corner structure technique for aircraft composite forming parts tooling, which is characterized in that
Support base is first closed into corner structure technique for aircraft composite part and preceding seperated module, left split pattern from more curved surfaces during demoulding
Block middle seperated module, right seperated module, unloads in rear seperated module, then middle seperated module is taken out, and then removes left split pattern
Block and right seperated module, preceding seperated module and rear seperated module are finally removed, complete the knockout course of part from part.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710239904.3A CN106976187B (en) | 2017-04-13 | 2017-04-13 | A kind of more curved surfaces close corner structure technique for aircraft composite forming parts tooling |
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| CN201710239904.3A CN106976187B (en) | 2017-04-13 | 2017-04-13 | A kind of more curved surfaces close corner structure technique for aircraft composite forming parts tooling |
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| CN106976187B true CN106976187B (en) | 2019-02-15 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109352877A (en) * | 2018-12-07 | 2019-02-19 | 江西洪都航空工业集团有限责任公司 | A kind of sectional type S shaped cylindrical composite material structural member forming frock structure |
| CN112092402B (en) * | 2020-08-26 | 2023-02-03 | 中国航空制造技术研究院 | Forming tool and forming method for composite material foam sandwich structure |
| CN112549590B (en) * | 2020-11-20 | 2022-11-18 | 昌河飞机工业（集团）有限责任公司 | Forming tool for waist drum-shaped molded part |
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| CN101973130A (en) * | 2010-08-27 | 2011-02-16 | 上海晋飞复合材料科技有限公司 | Emulsion liner auxiliary pre-impregnating mould pressing prepared integrated front fork mould and method thereof |
| CN105252790A (en) * | 2015-11-26 | 2016-01-20 | 中国航空工业集团公司基础技术研究院 | Composite material forming mould |
| CN105269721A (en) * | 2015-11-26 | 2016-01-27 | 中国航空工业集团公司基础技术研究院 | Forming mould for composite material part of box type closed-angle structure |
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2017
- 2017-04-13 CN CN201710239904.3A patent/CN106976187B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101973130A (en) * | 2010-08-27 | 2011-02-16 | 上海晋飞复合材料科技有限公司 | Emulsion liner auxiliary pre-impregnating mould pressing prepared integrated front fork mould and method thereof |
| CN105252790A (en) * | 2015-11-26 | 2016-01-20 | 中国航空工业集团公司基础技术研究院 | Composite material forming mould |
| CN105269721A (en) * | 2015-11-26 | 2016-01-27 | 中国航空工业集团公司基础技术研究院 | Forming mould for composite material part of box type closed-angle structure |
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| CN106976187A (en) | 2017-07-25 |
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