CN107187079A - The forming method of aircraft machine cover shell - Google Patents
The forming method of aircraft machine cover shell Download PDFInfo
- Publication number
- CN107187079A CN107187079A CN201710376379.XA CN201710376379A CN107187079A CN 107187079 A CN107187079 A CN 107187079A CN 201710376379 A CN201710376379 A CN 201710376379A CN 107187079 A CN107187079 A CN 107187079A
- Authority
- CN
- China
- Prior art keywords
- mould
- injecting glue
- point
- product
- die cavity
- 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.)
- Pending
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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
- B29C70/36—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 impregnating by casting, e.g. vacuum casting
-
- 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
-
- 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
- B29C33/12—Moulds or cores; Details thereof or accessories therefor with incorporated means for positioning inserts, e.g. labels
-
- 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
-
- 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
- B29C70/541—Positioning reinforcements in a mould, e.g. using clamping means for the reinforcement
-
- 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
- B29L2031/3088—Helicopters
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses a kind of forming method of aircraft machine cover shell, 1) make moulding mould special, 2) laying carbon cloth, 3) matched moulds and injecting glue, 4) vacuum pumping, 5 are carried out while injecting glue) solidification, pressurize, 6) demoulding, take out.After above method, it is ensured that the positional stability of carbon cloth, so as to ensure that the uniformity of product density, then ensure that end properties are qualified.
Description
Technical field
It is especially a kind of aircraft cover for helicopter engine the present invention relates to the technical field of carbon fiber product
The forming method of shell.
Background technology
The production requirement of aviation part is very high, should ensure its intensity, reduces its weight as far as possible again, therefore, is used for
The material requirements of aviation part is higher, most commonly acts on carbon fibre material to make, because carbon fiber has weight
Lighter than aluminium, intensity is but higher than steel, there is that corrosion-resistant, high temperature resistant, modulus are high again.At present, the manufacture method of carbon fiber product
Have a variety of, and it is to use die pressing to be best suitable for being used for make aviation part, this method is that the carbon of pre-soaked resin already is fine
Dimension material is put into metal forming mold, is overflowed unnecessary glue after pressurization and is come, then hot setting is molded, finished product after the demoulding
Just out.But, this mould of prior art with the following drawback that：Due to being provided with multiple edges in mould
Block, and generally these inserts are arranged at die cavity side, therefore, when mould matched moulds, these inserts are easily encountered
Carbon cloth, makes carbon cloth be moved, thus, it may be difficult to carbon cloth be laid smooth equilibrium, so as to influence product density
Uniformity, cause end properties unqualified.
The content of the invention
The technical problems to be solved by the invention are to provide one kind and avoid carbon cloth from being moved, so as to ensure product
The uniformity of density, then ensures the forming method of the qualified aircraft machine cover shell of end properties.
In order to solve the above technical problems, the forming method for the aircraft machine cover shell that the present invention is provided, it comprises the following steps：
1) moulding mould special is made, the mould includes upper die and lower die and pitched roof mechanism, and upper die and lower die are in matched moulds
Product die cavity is formed afterwards, and the insert formed on the forming slide and core of product die cavity is detachably connected on lower mould, oblique top
Mechanism is in upper mould, and oblique top sliding block is located in cavity surface；Mould is provided with multiple injecting glue points communicated with product die cavity,
And multiple injecting glue points are respectively positioned on mould top surface；What mould was additionally provided with that at least one communicates with product die cavity vacuumizes a little, institute
State to vacuumize and be a little located at the lower mould bottom surface corresponding with injecting glue point；
2) in lower mould and the forming slide being connected on lower mould and carbon cloth is laid in insert, completes carbon cloth
Afterwards, oblique top sliding block is positioned in mould manually；
3) matched moulds, makes to form die cavity after upper die and lower die matched moulds, and carries out injecting glue toward each injecting glue point；
4) while injecting glue, vacuumize at proceed by vacuum pumping, until sizing material riddles whole die cavity；
5) curing operation is carried out to the mobility in mould, becomes solid product；And carry out pressurize；
6) it is stripped, takes out.
Distribution of shapes of the injecting glue point along product, product is nearly rectangular profile, and injecting glue point is located at nearly rectangular profile respectively
Four edges, the long side center of center and nearly rectangular profile；One end of all injecting glue points and entering for mould
Jiao Kou is connected, and the other end of all injecting glue points is connected with product die cavity.
It is described vacuumize a little be three, respectively positioned at nearly rectangular profile one of them it is long while two ends at and another it is long while
Middle；Three one end vacuumized a little are connected with the vacuum pumping pump outside mould, and the other end is connected with product die cavity.
The step 3) in matched moulds be divided into two steps, closure pressing speed when upper mould is not in contact with carbon cloth higher than upper mould contact
Closure pressing speed after carbon cloth, and upper mould not in contact with carbon cloth when die pressure less than upper mould contact carbon cloth after
Die pressure.
After above method, the present invention compared with prior art, has the following advantages that：
1) because cavity surface is higher than the top surface of product, oblique top sliding block is located above cavity surface, is so closed in upper mould and lower mould
When mould, carbon cloth can't be produced skew by the interference of oblique top sliding block, thus it is guaranteed that the position of carbon cloth
Stability, so as to ensure that the uniformity of product density, then ensures that end properties are qualified；
2) injecting glue point is uniformly distributed, it is ensured that sizing material, which can confiscate, flows full whole product；
3) reverse side in injecting glue face, i.e., be provided with lower mould bottom surface and vacuumize a little, product is taken out very on side while marginal not glue
Sky, so contributes to material fully to be flowed in mold cavity, and product could note each place, and note more solid；
4) matched moulds quick and low pressure before not in contact with carbon cloth, can shorten the cycle and avoid sizing material from changing,
Low speed and high pressure after carbon cloth are contacted, then can avoid damaging carbon cloth, and contribute to type chamber air to discharge.
Brief description of the drawings
Fig. 1 is the structural representation of aircraft machine cover shell in the present invention.
Fig. 2 is the structural representation of the mould of aircraft machine cover shell in the present invention.
Fig. 3 is lower mould and its sliding block and the structural representation of insert of connection in the present invention.
Fig. 4 is the positional structure schematic diagram of oblique top sliding block in the present invention.
Fig. 5 is the positional structure schematic diagram of injecting glue point in the present invention.
Fig. 6 is that positional structure schematic diagram a little is vacuumized in the present invention.
Wherein, 1, aircraft machine cover shell；2nd, lower mould；3rd, upper mould；4th, forming slide；5th, insert；6th, injecting glue point；7th, oblique top is slided
Block；8th, vacuumize a little.
Embodiment
The present invention is described in more detail with reference to the accompanying drawings and detailed description.
As the structural representation of the mould used in the forming method of the aircraft machine cover shell of the present invention shown in Fig. 1~Fig. 6
Figure understands that it comprises the following steps：
1) moulding mould special is made, the mould includes upper mould 3, lower mould 2 and pitched roof mechanism, and upper die and lower die are being closed
Product die cavity is formed after mould, the insert 5 formed on the forming slide 4 and core of product die cavity is detachably connected on lower mould 2,
Pitched roof mechanism is in upper mould 3, and oblique top sliding block 7 is located in cavity surface；What mould was communicated provided with seven with product die cavity
Injecting glue point 6, and seven injecting glue points 6 are respectively positioned on the top surface of mould 3；Mould is additionally provided with three and vacuumizing that product die cavity is communicated
Point 8, it is described to vacuumize a little 8 positioned at lower mould 2 bottom surface corresponding with injecting glue point 6；Distribution of shapes of the injecting glue point 6 along product,
Product is nearly rectangular profile, and injecting glue point 6 is respectively positioned at four edges of nearly rectangular profile, center and nearly rectangular profile
Long side center；One end of all injecting glue points 6 is connected with the glue-feeder of mould, the other end and product of all injecting glue points 6
Die cavity is connected；It is described vacuumize a little 8 be three, respectively at the two ends on one of them long side of nearly rectangular profile and another grow
The middle on side；Three vacuumize a little 8 one end and are connected with the vacuum pumping pump outside mould, and the other end connects with product die cavity
It is logical.
2) in lower mould 2 and the forming slide 4 being connected on lower mould 2 and carbon cloth is laid in insert 5, completes carbon fiber
After cloth, oblique top sliding block 7 is positioned in mould manually；
3) matched moulds, makes to form die cavity after mould 3 and the lower 2-in-1 mould of mould, and carries out injecting glue toward each injecting glue point 6；Matched moulds is divided into
Two steps, closure pressing speed when upper mould is not in contact with carbon cloth contacts the closure pressing speed after carbon cloth, and upper mould higher than upper mould
Die pressure during not in contact with carbon cloth contacts the die pressure after carbon cloth less than upper mould；
4) while injecting glue, vacuumize and a little proceed by vacuum pumping at 8, until sizing material riddles whole die cavity；
5) curing operation is carried out to the mobility in mould, becomes solid product；And carry out pressurize；
6) it is stripped, takes out.
It is described above, only it is preferable feasible implementation example of the invention, it is impossible to therefore the i.e. interest field of the limitation present invention,
For those skilled in the art, it is all make with technical scheme and technical concept other are various corresponding
Change should all belong within the protection domain of the claims in the present invention.
Claims (4)
1. a kind of forming method of aircraft machine cover shell, it is characterised in that：It comprises the following steps：
1) moulding mould special is made, the mould includes upper mould (3), lower mould (2) and pitched roof mechanism, and upper die and lower die are being closed
Product die cavity is formed after mould, the insert (5) formed on the forming slide (4) and core of product die cavity is detachably connected to lower mould
(2) on, pitched roof mechanism is in upper mould (3), and oblique top sliding block (7) is located in cavity surface；Mould is provided with multiple and product
The injecting glue point (6) that die cavity is communicated, and multiple injecting glues point (6) is respectively positioned on mould (3) top surface；Mould be additionally provided with least one with
What product die cavity was communicated vacuumizes point (8), and the point (8) that vacuumizes is positioned at lower mould (2) bottom surface corresponding with injecting glue point (6)；
2) in lower mould (2) and the forming slide (4) being connected on lower mould (2) and carbon cloth is laid in insert (5), completes carbon
After fiber cloth, oblique top sliding block (7) is positioned in mould manually；
3) matched moulds, makes to form die cavity after mould (3) and lower mould (2) matched moulds, and carries out injecting glue toward each injecting glue point (6)；
4) while injecting glue, vacuumize point (8) place and proceed by vacuum pumping, until sizing material riddles whole die cavity；
5) curing operation is carried out to the mobility in mould, becomes solid product；And carry out pressurize；
6) it is stripped, takes out.
2. the forming method of aircraft machine cover shell according to claim 1, it is characterised in that：The injecting glue point (6) is along product
Distribution of shapes, product is nearly rectangular profile, injecting glue point (6) respectively positioned at four edges of nearly rectangular profile, center with
And the long side center of nearly rectangular profile；One end of all injecting glue points (6) is connected with the glue-feeder of mould, all injecting glue points
(6) the other end is connected with product die cavity.
3. the forming method of aircraft machine cover shell according to claim 2, it is characterised in that：The point (8) that vacuumizes is three
It is individual, respectively positioned at nearly rectangular profile one of them it is long while two ends at and another it is long while middle；Three vacuumize point (8)
One end connected with the vacuum pumping pump outside mould, the other end is connected with product die cavity.
4. the forming method of aircraft machine cover shell according to claim 1, it is characterised in that：The step 3) in matched moulds point
For two steps, closure pressing speed when upper mould is not in contact with carbon cloth contacts the closure pressing speed after carbon cloth higher than upper mould, and on
Die pressure when mould is not in contact with carbon cloth contacts the die pressure after carbon cloth less than upper mould.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710376379.XA CN107187079A (en) | 2017-05-18 | 2017-05-18 | The forming method of aircraft machine cover shell |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710376379.XA CN107187079A (en) | 2017-05-18 | 2017-05-18 | The forming method of aircraft machine cover shell |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107187079A true CN107187079A (en) | 2017-09-22 |
Family
ID=59874838
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710376379.XA Pending CN107187079A (en) | 2017-05-18 | 2017-05-18 | The forming method of aircraft machine cover shell |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107187079A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107627628A (en) * | 2017-09-28 | 2018-01-26 | 江苏恒神股份有限公司 | The more ear multi-cavity structures of composite and its manufacture method of RTM technique global formations |
| CN107745532A (en) * | 2017-10-31 | 2018-03-02 | 深圳市惠程电气股份有限公司 | A kind of RTM production methods of shell |
| CN108100230A (en) * | 2017-12-01 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter horizontal tail wing box |
| CN110948906A (en) * | 2019-12-09 | 2020-04-03 | 宁波市益普乐模塑有限公司 | Manufacturing process of carbon fiber automobile door outer panel |
| CN112174544A (en) * | 2020-09-03 | 2021-01-05 | 江苏铁锚玻璃股份有限公司 | Method for forming glass waterproof glue and mold applied to forming glass waterproof glue |
| CN112261177A (en) * | 2019-07-22 | 2021-01-22 | Oppo广东移动通信有限公司 | Shell, manufacturing method of shell and electronic device |
| CN115107201A (en) * | 2022-07-01 | 2022-09-27 | 北京玻钢院复合材料有限公司 | Aviation composite material window frame cushion block die and window frame cushion block forming method |
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| CN104527088A (en) * | 2014-12-05 | 2015-04-22 | 东莞市海旭新材料技术有限公司 | Preparation method of cubing |
| CN205651609U (en) * | 2016-05-17 | 2016-10-19 | 群达模具(深圳)有限公司 | Forming die of notebook face -piece |
| CN106476179A (en) * | 2016-11-30 | 2017-03-08 | 上海晋飞新材料科技有限公司 | A kind of composite shaping large mold for carrying heating, cooling system |
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- 2017-05-18 CN CN201710376379.XA patent/CN107187079A/en active Pending
Patent Citations (3)
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| CN104527088A (en) * | 2014-12-05 | 2015-04-22 | 东莞市海旭新材料技术有限公司 | Preparation method of cubing |
| CN205651609U (en) * | 2016-05-17 | 2016-10-19 | 群达模具(深圳)有限公司 | Forming die of notebook face -piece |
| CN106476179A (en) * | 2016-11-30 | 2017-03-08 | 上海晋飞新材料科技有限公司 | A kind of composite shaping large mold for carrying heating, cooling system |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107627628A (en) * | 2017-09-28 | 2018-01-26 | 江苏恒神股份有限公司 | The more ear multi-cavity structures of composite and its manufacture method of RTM technique global formations |
| CN107745532A (en) * | 2017-10-31 | 2018-03-02 | 深圳市惠程电气股份有限公司 | A kind of RTM production methods of shell |
| CN108100230A (en) * | 2017-12-01 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter horizontal tail wing box |
| CN112261177A (en) * | 2019-07-22 | 2021-01-22 | Oppo广东移动通信有限公司 | Shell, manufacturing method of shell and electronic device |
| CN110948906A (en) * | 2019-12-09 | 2020-04-03 | 宁波市益普乐模塑有限公司 | Manufacturing process of carbon fiber automobile door outer panel |
| CN112174544A (en) * | 2020-09-03 | 2021-01-05 | 江苏铁锚玻璃股份有限公司 | Method for forming glass waterproof glue and mold applied to forming glass waterproof glue |
| CN115107201A (en) * | 2022-07-01 | 2022-09-27 | 北京玻钢院复合材料有限公司 | Aviation composite material window frame cushion block die and window frame cushion block forming method |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170922 |
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| RJ01 | Rejection of invention patent application after publication |