CN109278316A - A kind of T junction component technology for mould-pressing forming of carbon fibre material - Google Patents
A kind of T junction component technology for mould-pressing forming of carbon fibre material Download PDFInfo
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- CN109278316A CN109278316A CN201710597617.XA CN201710597617A CN109278316A CN 109278316 A CN109278316 A CN 109278316A CN 201710597617 A CN201710597617 A CN 201710597617A CN 109278316 A CN109278316 A CN 109278316A
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- Prior art keywords
- carbon
- compacted
- carbon fiber
- prefix
- mould
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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
-
- 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 kind of T junction component technology for mould-pressing forming of carbon fibre material, including following four step: preparing carbon fiber built-in fitting；Prepare pre-compacted carbon beam；Carbon fiber built-in fitting and pre-compacted carbon beam are formed into assembling structure；Increase T prefix covering, is formed by mould pressing process co-curing.The specific method is as follows: carbon fiber built-in fitting, at the quasi-isotropic laying of interlaced arrangement, is formed using fiber filament by carbon fiber and epoxy prepreg co-curing, and moulding process uses mould pressing process.The pre-compacted carbon beam laying parallel with tension direction using fiber filament, there are contracting amounts for upper end surrounding, and carbon fiber built-in fitting and pre-compacted carbon beam are glued.T prefix covering uses Carbon Fiber/Epoxy Composite, from outsourcing from pre-compacted carbon beam upper end side contracting amount, around from other side wraparound and being closed after T prefix, formed by mould pressing process co-curing, fiber filament direction is consistent with the prefix tension direction T, can effectively increase T prefix position mechanical strength.
Description
Technical field
The present invention relates to a kind of technology for mould-pressing forming, the T junction component of especially a kind of carbon fibre material is molded into
Type process.
Background technique
Carbon fiber is as a kind of new material, because its density is low, intensity is high, modulus is high, corrosion-resistant, endurance etc. is many excellent
Point is widely used in the fields such as defence and military, aerospace, automobile toy, sports equipment.But carbon fiber has very strong direction
Dependence, referred to as anisotropic material, carbon fiber structural part is especially high in the direction intensity parallel with fiber filament, other directions
Intensity is lower, and T junction component is widely used in all trades and professions, traditional molding side as a kind of common support construction form
Method is glued in joint, although this process is simple, the intensity of joint depends primarily on the intensity of glue, by
It is influenced very greatly in glue by factors such as temperature, agings, therefore this moulding technique will lead to joint intensity deficiency, it is difficult to full
Sufficient engineering demand.
Summary of the invention
It is an object of that present invention to provide a kind of T junction component technology for mould-pressing forming of carbon fibre material, solve existing
Carbon fibre material T junction component joint intensity it is insufficient, be unable to satisfy the problem of engineering demand.
A kind of specific steps of the T junction component technology for mould-pressing forming of carbon fibre material are as follows:
The first step prepares carbon fiber built-in fitting
Carbon fiber built-in fitting, at 45o interlaced arrangement, passes through carbon fiber wire and epoxy prepreg co-curing using carbon fiber wire
Molding, moulding process use mould pressing process.
Second step prepares pre-compacted carbon beam
Pre-compacted carbon beam makes precompressed using the fiber filament laying parallel with tension direction using the anisotropy feature of carbon fiber
Real carbon beam withstands more force load, and left and right sides local crowning uses symmetrical equilibrium laying, precompressed at the top of pre-compacted carbon beam
One layer of plain weave carbon cloth of paving after reality, pre-compacted carbon beam upper end surrounding have contracting amount, are T prefix covering slot milling.
Third step is integrally formed by carbon fiber built-in fitting and pre-compacted carbon beam formation assembling structure
Carbon fiber built-in fitting is carried out with pre-compacted carbon beam with J47 glue be bonded.
4th step increases T prefix covering, is formed by mould pressing process co-curing
T prefix covering uses Carbon Fiber/Epoxy Composite, carries out symmetrical equilibrium laying, contracts from pre-compacted carbon beam upper end side
Outsourcing at amount around from other side wraparound and being closed after T prefix, and is formed by mould pressing process co-curing, due to fiber filament side
To consistent with the T prefix Tensile direction that falls off, T prefix position mechanical strength can be effectively increased.
So far, the T junction component compression molding of carbon fibre material is completed.
Present method solves in the compression molding of the T junction component of carbon fibre material, according to conventional molding process method, lead
The problem of causing intensity deficiency at T connector, being unable to satisfy engineering demand, is formed by mould pressing process co-curing, effectively increases T
Prefix position mechanical strength.
Detailed description of the invention
Composite material embedded part structure described in a kind of T junction component technology for mould-pressing forming of carbon fibre material of Fig. 1
Figure；
Pre-compacted carbon beam structure chart described in a kind of T junction component technology for mould-pressing forming of carbon fibre material of Fig. 2；
T prefix stressed-skin construction figure described in a kind of T junction component technology for mould-pressing forming of carbon fibre material of Fig. 3；
A kind of T junction component of carbon fibre material of Fig. 4 is pressed and molded structural schematic diagram.
1. 2. pre-compacted carbon beam 3.T prefix covering of carbon fiber built-in fitting.
Specific embodiment
A kind of specific steps of the T junction component technology for mould-pressing forming of carbon fibre material are as follows:
The first step prepares carbon fiber built-in fitting
Carbon fiber built-in fitting 1, at 45o interlaced arrangement, passes through carbon fiber wire and epoxy prepreg co-curing using carbon fiber wire
Molding, moulding process use mould pressing process.
Second step prepares pre-compacted carbon beam
Pre-compacted carbon beam 2 makes precompressed using the fiber filament laying parallel with tension direction using the anisotropy feature of carbon fiber
Real carbon beam 2 withstands more force load, and left and right sides local crowning uses symmetrical equilibrium laying, precompressed at the top of pre-compacted carbon beam
One layer of plain weave carbon cloth of paving after reality, 2 upper end surrounding of pre-compacted carbon beam have contracting amount, are 3 slot milling of T prefix covering.
Third step is integrally formed by carbon fiber built-in fitting and pre-compacted carbon beam formation assembling structure
Carbon fiber built-in fitting 1 is carried out with pre-compacted carbon beam 2 with J47 glue be bonded.
4th step increases T prefix covering, is formed by mould pressing process co-curing
T prefix covering 3 uses Carbon Fiber/Epoxy Composite, symmetrical equilibrium laying is carried out, from 2 upper end side of pre-compacted carbon beam
Outsourcing at contracting amount around from other side wraparound and being closed after T prefix, and is formed by mould pressing process co-curing, due to fiber filament
Direction and T prefix the Tensile direction that falls off are consistent, can effectively increase T prefix position mechanical strength.
So far, the T junction component compression molding of carbon fibre material is completed.
Claims (3)
1. a kind of T junction component technology for mould-pressing forming of carbon fibre material, it is characterised in that specific steps are as follows:
The first step prepares carbon fiber built-in fitting
Carbon fiber built-in fitting (1) uses carbon fiber wire interlaced arrangement, and passes through carbon fiber wire and epoxy prepreg co-curing
Molding, moulding process use mould pressing process；
Second step prepares pre-compacted carbon beam
Pre-compacted carbon beam (2) is made pre- using the anisotropy feature of carbon fiber using the fiber filament laying parallel with tension direction
Compacting carbon beam (2) withstands more force load, and left and right sides local crowning uses symmetrical equilibrium laying at the top of pre-compacted carbon beam,
One layer of plain weave carbon cloth of paving after pre-compacted, pre-compacted carbon beam (2) upper end surrounding have contracting amount, reserve sky for T prefix covering (3)
Between；
Third step is integrally formed by carbon fiber built-in fitting and pre-compacted carbon beam formation assembling structure
Carbon fiber built-in fitting (1) is carried out with pre-compacted carbon beam (2) with glue be bonded；
4th step increases T prefix covering, is formed by mould pressing process co-curing
T prefix covering (3) uses Carbon Fiber/Epoxy Composite, symmetrical equilibrium laying is carried out, from pre-compacted carbon beam (2) upper end
Outsourcing at side contracting amount around from other side wraparound and being closed after T prefix, and is formed by mould pressing process co-curing, due to fibre
Dimension silk direction and T prefix the Tensile direction that falls off are consistent, can effectively increase T prefix position mechanical strength；
So far, the T junction component compression molding of carbon fibre material is completed.
2. the T junction component technology for mould-pressing forming of carbon fibre material as described in claim 1, it is characterised in that the carbon
Fiber filament is at 45o interlaced arrangement.
3. the T junction component technology for mould-pressing forming of carbon fibre material as claimed in claim 1 or 2, it is characterised in that institute
State carbon fiber built-in fitting (1) carried out with pre-compacted carbon beam (2) with J47 glue it is be bonded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710597617.XA CN109278316B (en) | 2017-07-21 | 2017-07-21 | Compression molding process method for T-shaped structural part made of carbon fiber material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710597617.XA CN109278316B (en) | 2017-07-21 | 2017-07-21 | Compression molding process method for T-shaped structural part made of carbon fiber material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109278316A true CN109278316A (en) | 2019-01-29 |
| CN109278316B CN109278316B (en) | 2021-04-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710597617.XA Active CN109278316B (en) | 2017-07-21 | 2017-07-21 | Compression molding process method for T-shaped structural part made of carbon fiber material |
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| CN (1) | CN109278316B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114872329A (en) * | 2022-06-14 | 2022-08-09 | 中国船舶重工集团公司第七二五研究所 | Method for connecting integrally-formed composite material skin and framework |
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| CN101189118A (en) * | 2005-06-07 | 2008-05-28 | 空中客车德国有限公司 | Method for manufacturing a reinforced shell for forming component parts for aircraft and shell for component parts for aircraft |
| JP4425647B2 (en) * | 2004-01-23 | 2010-03-03 | ユニバーサル造船株式会社 | FRP molded product having joint ends, manufacturing method thereof, and FRP molded product obtained by joining metal structures |
| CN102248678A (en) * | 2010-03-22 | 2011-11-23 | 维斯塔斯风力系统集团公司 | Method for manufacturing a blade sparfor a wind turbine |
| CN105196620A (en) * | 2015-10-20 | 2015-12-30 | 南京航空航天大学 | Partially-enhanced X-cor foam core sandwich T-joint structure and molding method |
| US10576723B2 (en) * | 2013-05-30 | 2020-03-03 | Airbus Operations S.L. | Hybrid tool for curing pieces of composite material |
-
2017
- 2017-07-21 CN CN201710597617.XA patent/CN109278316B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4425647B2 (en) * | 2004-01-23 | 2010-03-03 | ユニバーサル造船株式会社 | FRP molded product having joint ends, manufacturing method thereof, and FRP molded product obtained by joining metal structures |
| CN101189118A (en) * | 2005-06-07 | 2008-05-28 | 空中客车德国有限公司 | Method for manufacturing a reinforced shell for forming component parts for aircraft and shell for component parts for aircraft |
| CN102248678A (en) * | 2010-03-22 | 2011-11-23 | 维斯塔斯风力系统集团公司 | Method for manufacturing a blade sparfor a wind turbine |
| US10576723B2 (en) * | 2013-05-30 | 2020-03-03 | Airbus Operations S.L. | Hybrid tool for curing pieces of composite material |
| CN105196620A (en) * | 2015-10-20 | 2015-12-30 | 南京航空航天大学 | Partially-enhanced X-cor foam core sandwich T-joint structure and molding method |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114872329A (en) * | 2022-06-14 | 2022-08-09 | 中国船舶重工集团公司第七二五研究所 | Method for connecting integrally-formed composite material skin and framework |
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| CN109278316B (en) | 2021-04-09 |
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