CN109435275A - The curved composite element integral manufacturing method of the double S in large scale space - Google Patents
The curved composite element integral manufacturing method of the double S in large scale space Download PDFInfo
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- CN109435275A CN109435275A CN201811194040.9A CN201811194040A CN109435275A CN 109435275 A CN109435275 A CN 109435275A CN 201811194040 A CN201811194040 A CN 201811194040A CN 109435275 A CN109435275 A CN 109435275A
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- Prior art keywords
- composite element
- double
- composite
- male mould
- mold
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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
- 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
-
- 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
- B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
-
- 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
- B29C33/56—Coatings, e.g. enameled or galvanised; Releasing, lubricating or separating agents
- B29C33/60—Releasing, lubricating or separating agents
-
- 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
- B29C33/56—Coatings, e.g. enameled or galvanised; Releasing, lubricating or separating agents
- B29C33/68—Release sheets
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
- Mounting, Exchange, And Manufacturing Of Dies (AREA)
Abstract
The invention discloses the curved composite element integral manufacturing methods of the double S in large scale space, propose the functions such as the processing of inexpensive master mold+shell composite male mould structure type composite molding die union forming surface, heat distribution test, the detection of type face degree of finish, form structure-function integration mold, solves the problems such as composite element dimension precision requirement is high, inside surface roughness class requirement is high, molding die heat distribution test, proposition uses shell composite male mould as the molding die of composite element；Composite element shape is curved in the double S in space, Curvature varying is big, height dimension is big, without drafting angle, for blank entirety demoulding difficult problem caused by the above structure feature, and consider to overcome the problem on deformation in knockout course, after the surface treatment of shell composite male mould, the removing layer by layer that mold can be achieved on component blank is removed, and knockout course is without external force, to component blank without impact injury.
Description
Technical field
The invention belongs to civil aircraft composite element manufacturing process technology fields, and in particular to a kind of double S in large scale space
Curved composite element integral manufacturing method.
Background technique
Composite material structural member has many advantages, such as that light-weight, intensity and toughness is high, good moulded manufacturability, in civil aircraft
Field has been more and more widely used, especially large-scale composite material structural member.
The double curved composite elements of S in large scale space are the channel of disembarking of C919 airliner, belong to seaworthiness class part, molding
Mold heat distribution test requirements document need to meet civil aircraft process specification requirements；Shape is curved in the double S in space, and Curvature varying is big, height dimension
Greatly, it is demoulded using classical production process difficult；Belong to shell cavity type parts, and inside and outside shape dimension precision requirement is high, technological equipment
Manufacture and design and requires height.
The domestic research made in one piece in relation to composite element be mainly used in size is smaller, Curvature varying gently
Airplane intake manufacture etc., and manufacture and require without seaworthiness, the tradition such as the split type formpiston method of thin-wall metal, water-soluble die methods
Method of manufacturing technology can solve.
Summary of the invention
Goal of the invention
The present invention provides a kind of curved composite element integral manufacturing methods of the double S in large scale space, solve composite wood
Expect in molding component manufacture, the integrally formed manufacture due to caused by product height dimension is big, the double S in space are curved, Curvature varying is big is stranded
The problems such as hardly possible, molding die uniform heat distribution problem, molding die manufacturing cost are high, the lead time is long.
Inventive technique solution
In order to achieve the above-mentioned object of the invention, the present invention uses following technical solutions:
The curved composite element integral manufacturing method of the double S in large scale space, which comprises the steps of:
Step 1: selecting lower cost materials as master mold material, master mold blank is carried out vacuumizing compacting in an oven, so
The Roughing and fine machining master mold outer mold surface on numerically-controlled machine tool afterwards forms the forming surface in the inner mold face of shell composite male mould, to master mold
Outer mold surface is detected；
Step 2: shell composite male mould is formed in master mold outer mold surface, after solidification, numerical control processing shell is compound
Material formpiston outer mold surface forms the forming surface in composite element inner mold face, examines to shell composite male mould outer mold surface
It surveys；
Step 3: master mold being dismantled, shell composite male mould is retained, accuracy detection is carried out to formpiston outer mold surface；
Step 4: heat distribution test being carried out to shell composite male mould, after test passes through, as composite element
Molding die；
Step 5: in the accurate paving composite element blank of shell composite male mould outer mold surface, composite element hair
After base forming and hardening, composite element blank border is accurately processed on numerically-controlled machine tool；
Step 6: removing layer by layer being carried out to shell composite male mould and is removed, forms blank, shape after cutting spraying after removing
At composite element；
Step 7: accuracy detection being carried out to composite element inner mold face, and is carried out non-destructive testing.
Preferably, it is carried out between step 1 and 2: master mold outer mold surface is surface-treated, uniformly coated in outer mold surface de-
Mold layer, realization are isolated with shell composite male mould inner surface.
Preferably, carried out between step 4 and 5: shell composite male mould outer mold surface be surface-treated, paving every
From film, inner surface is isolated when formation is formed with composite element blank.
Preferably, steps 1 and 2, using three coordinate measuring machine carry out Surface inspection in 3,7.
Preferably, master mold includes master mold die body, and master mold die body is double S types and one end face area is greater than the other end face face
Product；Master mold die body big end end face is removably connected with support plate.
Preferably, shell composite male mould includes force block, and force block is double S type both ends opens and hollow structure, and one
End opening area is greater than other end opening area, and force block big end end face is removably connected with support plate, and big end end face side is set
It is equipped with reinforcing frame.
Preferably, support plate outer peripheral surface, the top surface of reinforcing frame and outer peripheral surface are provided with several hanging rings.
Preferably, support plate is square, and is additionally provided with locating piece at four angles of support plate top surface.
Preferably, master mold die body is made of wood materials.
Preferably, composite element puts force block accumbency when solidifying in shell composite male mould in step 5
It sets, small end adjustment frame is set in force block small end, big end adjustment frame, small end adjustment frame and big end adjustment are set in force block big end
Frame upper end is set to force block inner top surface, makes force block small end port in autoclave towards airflow direction, port cross-sectional is vertical
In horizontal plane.Since formpiston inner cavity is hollow perforation, the mold modes of emplacement of this horizontal type can guarantee composite element
Blank air-flow in solidification is unimpeded, and mold is heated evenly.
Advantages of the present invention
The present invention has the advantages that
1) applied widely, it is applicable to the whole manufacture of various large scales, deep camber variation composite element.
2) mould design and manufacture is at low cost, and the lead time is short.
3) product stripping process reduces the deformation during product stripping without external force.
Detailed description of the invention
Fig. 1 is the curved composite element integral manufacturing method flow chart of the double S in large scale space of the invention.
Fig. 2 is master mold main view.
Fig. 3 is master mold top view.
Fig. 4 is master mold three-dimensional structure view.
Fig. 5 is shell composite male mould main view.
Fig. 6 is shell composite male mould top view.
Fig. 7 is shell composite male mould three-dimensional structure view.
Fig. 8 is main view of the composite element blank when solidifying in shell composite male mould.
Fig. 9 is 3-D view of the composite element blank when solidifying in shell composite male mould.
In figure: 1- anti-loosing screw；2- master mold die body；3- support plate；4- hanging ring；5- locating piece；6- force block；7- small end tune
Whole frame；8- big end adjustment frame；9- reinforcing frame.
Specific embodiment
In conjunction with summary of the invention general introduction and attached drawing, the specific embodiment that the present invention will be described in detail.
The curved composite element integral manufacturing method of the double S in large scale space, includes the following steps:
Step 1: selecting lower cost materials as master mold material, master mold blank is carried out vacuumizing compacting in an oven, so
The Roughing and fine machining master mold outer mold surface on numerically-controlled machine tool afterwards forms the forming surface in the inner mold face of shell composite male mould, uses three
Coordinate measuring machine detects master mold outer mold surface；
Step 2: shell composite male mould is formed in master mold outer mold surface, after solidification, numerical control processing shell is compound
Material formpiston outer mold surface forms the forming surface in composite element inner mold face, using three coordinate measuring machine to shell composite material
Formpiston outer mold surface is detected；
Step 3: master mold being dismantled, retains shell composite male mould, using three coordinate measuring machine to formpiston external form
Face carries out accuracy detection；
Step 4: heat distribution test being carried out to shell composite male mould, after test passes through, as composite element
Molding die；
Step 5: in the accurate paving composite element blank of shell composite male mould outer mold surface, composite element hair
After base forming and hardening, composite element blank border is accurately processed on numerically-controlled machine tool；
Step 6: removing layer by layer being carried out to shell composite male mould and is removed, forms blank, shape after cutting spraying after removing
At composite element；
Step 7: accuracy detection being carried out to composite element inner mold face using three coordinate measuring machine, and carries out lossless inspection
It surveys.
It is carried out between step 1 and 2: master mold outer mold surface is surface-treated, uniformly coat release layer in outer mold surface, it is real
Now it is isolated with shell composite male mould inner surface.
It is carried out between step 4 and 5: shell composite male mould outer mold surface is surface-treated, paving isolation film, shape
It is isolated at inner surface when being formed with composite element blank.
In order to solve, composite element dimension precision requirement is high, inside surface roughness class requirement is high, molding die heat
The problems such as distribution test, proposition uses shell composite male mould as the molding die of composite element；Composite material structure
Part shape is curved in the double S in space, and Curvature varying is big, and height dimension is big, no drafting angle, for blank caused by the above structure feature
Whole demoulding difficult problem, and consider to overcome the problem on deformation in knockout course, after the surface treatment of shell composite male mould,
The removing layer by layer that mold can be achieved on component blank is removed, and knockout course is without external force, to component blank without impact injury；
In order to realize the molding manufacture of shell composite male mould, select inexpensive master mold as its molding die.It is analyzed based on above,
Propose inexpensive master mold+shell composite male mould structure type composite molding die.
Master mold includes master mold die body 2, and master mold die body 2 is double S type solid constructions and one end face area is greater than other end end
Face area；2 big end end face of master mold die body is removably connected with the support plate 3 of plate structure.2 small end of master mold die body is provided with several
Anti-loosing screw 1.
Shell composite male mould includes force block 6, and force block 6 is double S type both ends opens and hollow structure, force block 6
Outer mold surface is mutually fitted with moulding surface structure in composite element, and area open at one end is greater than other end opening area, 6 big end of force block
End face is removably connected with the support plate 3 of plate structure, and big end end face side is provided with reinforcing frame 9.6 small end of force block is provided with
Several anti-loosing screws 1.
3 outer peripheral surface of support plate, the top surface of reinforcing frame 9 and outer peripheral surface are provided with several hanging rings 4.
Support plate 3 is square, and is additionally provided with locating piece 5 at the angle of support plate 3 top surface four.
Master mold die body 2 is made of wood materials.
Composite element is placed 6 accumbency of force block, when solidifying in shell composite male mould in sun in step 5
Small end adjustment frame 7 is arranged in 6 small end of die body, and big end adjustment frame 8, small end adjustment frame 7 and big end adjustment frame is arranged in 6 big end of force block
8 upper ends are set to 6 inner top surface of force block, make force block small end port in autoclave towards airflow direction, port cross-sectional is vertical
In horizontal plane.
The composite element size manufactured in the present embodiment are as follows: height 1600mm, interior chamber size 800mm × 800mm.
Claims (10)
1. the curved composite element integral manufacturing method of the double S in large scale space, which comprises the steps of:
Step 1: selecting lower cost materials as master mold material, master mold blank is carried out vacuumizing compacting in an oven, then be existed
Roughing and fine machining master mold outer mold surface on numerically-controlled machine tool forms the forming surface in the inner mold face of shell composite male mould, to master mold external form
It is detected in face；
Step 2: shell composite male mould, after solidification, numerical control processing shell composite material are formed in master mold outer mold surface
Formpiston outer mold surface forms the forming surface in composite element inner mold face, detects to shell composite male mould outer mold surface；
Step 3: master mold being dismantled, shell composite male mould is retained, accuracy detection is carried out to formpiston outer mold surface；
Step 4: heat distribution test is carried out to shell composite male mould, after test passes through, the molding as composite element
Mold；
Step 5: in the accurate paving composite element blank of shell composite male mould outer mold surface, composite element blank at
After type solidifies, composite element blank border is accurately processed on numerically-controlled machine tool；
Step 6: removing layer by layer being carried out to shell composite male mould and is removed, blank is formed after removing, is formed after cutting spraying multiple
Condensation material component；
Step 7: accuracy detection being carried out to composite element inner mold face, and is carried out non-destructive testing.
2. the curved composite element integral manufacturing method of the double S in large scale space as described in claim 1, which is characterized in that
It is carried out between step 1 and 2: master mold outer mold surface is surface-treated, uniformly coat release layer in outer mold surface, realized multiple with shell
The isolation of condensation material formpiston inner surface.
3. the curved composite element integral manufacturing method of the double S in large scale space as described in claim 1, which is characterized in that
It carries out: shell composite male mould outer mold surface being surface-treated, paving isolation film between step 4 and 5, formation and composite wood
Expect the isolation of inner surface when the molding of component blank.
4. the curved composite element integral manufacturing method of the double S in large scale space as described in claim 1, which is characterized in that step
Surface inspection is carried out using three coordinate measuring machine in rapid 1,2,3,7.
5. the curved composite element integral manufacturing method of the double S in large scale space as described in claim 1, which is characterized in that female
Mould includes master mold die body, and master mold die body is double S types and one end face area is greater than the other end face area；Master mold die body big end end
Face is removably connected with support plate.
6. the curved composite element integral manufacturing method of the double S in large scale space as claimed in claim 5, which is characterized in that thin
Shell composite male mould includes force block, and force block is double S type both ends opens and hollow structure, and area open at one end is greater than another
End opening area, force block big end end face are removably connected with support plate, and big end end face side is provided with reinforcing frame.
7. the curved composite element integral manufacturing method of the double S in large scale space as claimed in claim 6, which is characterized in that branch
Fagging outer peripheral surface, the top surface of reinforcing frame and outer peripheral surface are provided with several hanging rings.
8. the curved composite element integral manufacturing method of the double S in large scale space as claimed in claim 6, which is characterized in that branch
Fagging is square, and is additionally provided with locating piece at four angles of support plate top surface.
9. the curved composite element integral manufacturing method of the double S in large scale space as described in claim 1, which is characterized in that female
Mould die body is made of wood materials.
10. the curved composite element integral manufacturing method of the double S in large scale space as claimed in claim 6, which is characterized in that step
Composite element blank places force block accumbency when solidifying in shell composite male mould in rapid 5, in force block small end
Small end adjustment frame is set, big end adjustment frame is set in force block big end, small end adjustment frame and big end adjustment frame upper end are set to sun
Die body inner top surface makes force block small end port in autoclave towards airflow direction, and port cross-sectional is perpendicular to horizontal plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811194040.9A CN109435275B (en) | 2018-10-12 | 2018-10-12 | Integral manufacturing method of large-size space double-S-bend composite material component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811194040.9A CN109435275B (en) | 2018-10-12 | 2018-10-12 | Integral manufacturing method of large-size space double-S-bend composite material component |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109435275A true CN109435275A (en) | 2019-03-08 |
| CN109435275B CN109435275B (en) | 2020-11-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201811194040.9A Active CN109435275B (en) | 2018-10-12 | 2018-10-12 | Integral manufacturing method of large-size space double-S-bend composite material component |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5773108A (en) * | 1996-06-14 | 1998-06-30 | Lockheed Martin Corporation | Self-coiling composite band |
| CN201525132U (en) * | 2009-09-08 | 2010-07-14 | 国营江北机械厂 | Detachable core die |
| CN202846881U (en) * | 2012-08-29 | 2013-04-03 | 天津鹏翎胶管股份有限公司 | Combined core rod of cloth-winded hose for automobile |
| CN105314092A (en) * | 2014-07-16 | 2016-02-10 | 波音公司 | Adaptive composite structure using shape memory alloys |
| CN106393743A (en) * | 2016-11-30 | 2017-02-15 | 江西洪都航空工业集团有限责任公司 | Composite material intake way forming mold |
| CN106553357A (en) * | 2016-11-09 | 2017-04-05 | 江苏恒神股份有限公司 | Hollow multi-cavity abnormal shape surface composite material complex structural member integral forming technique |
| CN108527732A (en) * | 2018-03-14 | 2018-09-14 | 天津爱思达航天科技有限公司 | A kind of composite material mould and its manufacturing method |
-
2018
- 2018-10-12 CN CN201811194040.9A patent/CN109435275B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5773108A (en) * | 1996-06-14 | 1998-06-30 | Lockheed Martin Corporation | Self-coiling composite band |
| CN201525132U (en) * | 2009-09-08 | 2010-07-14 | 国营江北机械厂 | Detachable core die |
| CN202846881U (en) * | 2012-08-29 | 2013-04-03 | 天津鹏翎胶管股份有限公司 | Combined core rod of cloth-winded hose for automobile |
| CN105314092A (en) * | 2014-07-16 | 2016-02-10 | 波音公司 | Adaptive composite structure using shape memory alloys |
| CN106553357A (en) * | 2016-11-09 | 2017-04-05 | 江苏恒神股份有限公司 | Hollow multi-cavity abnormal shape surface composite material complex structural member integral forming technique |
| CN106393743A (en) * | 2016-11-30 | 2017-02-15 | 江西洪都航空工业集团有限责任公司 | Composite material intake way forming mold |
| CN108527732A (en) * | 2018-03-14 | 2018-09-14 | 天津爱思达航天科技有限公司 | A kind of composite material mould and its manufacturing method |
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| CN109435275B (en) | 2020-11-13 |
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