CN109203511A - Aerospace carbon fibre composite cabinet shaping mould and its shaping box body technology - Google Patents
Aerospace carbon fibre composite cabinet shaping mould and its shaping box body technology Download PDFInfo
- Publication number
- CN109203511A CN109203511A CN201811174648.5A CN201811174648A CN109203511A CN 109203511 A CN109203511 A CN 109203511A CN 201811174648 A CN201811174648 A CN 201811174648A CN 109203511 A CN109203511 A CN 109203511A
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- forming module
- inner cavity
- mold core
- mold
- carbon fibre
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- 238000007493 shaping process Methods 0.000 title claims abstract description 33
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 23
- 229910052799 carbon Inorganic materials 0.000 title claims abstract description 23
- 239000000835 fiber Substances 0.000 title claims abstract description 23
- 239000002131 composite material Substances 0.000 title claims abstract description 22
- 238000005516 engineering process Methods 0.000 title claims abstract description 10
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 19
- 239000004917 carbon fiber Substances 0.000 claims abstract description 19
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 19
- 238000005086 pumping Methods 0.000 claims abstract description 11
- 229910001095 light aluminium alloy Inorganic materials 0.000 claims abstract description 10
- 238000001816 cooling Methods 0.000 claims abstract description 4
- 210000003205 muscle Anatomy 0.000 claims description 22
- 238000003825 pressing Methods 0.000 claims description 17
- 239000000463 material Substances 0.000 claims description 4
- 238000005253 cladding Methods 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 12
- 230000015572 biosynthetic process Effects 0.000 abstract 1
- 238000000465 moulding Methods 0.000 description 14
- 230000000694 effects Effects 0.000 description 6
- 241000233855 Orchidaceae Species 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000005474 detonation Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 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
- 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
- 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)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The present invention relates to a kind of aerospace carbon fibre composite cabinet shaping mould and its shaping box body technology, technique includes firstly, support member and inner cavity forming module B are assembled, one formpiston to match with box parts inner cavity of formation；Secondly, the pre-buried aircraft aluminum connector on formpiston, and the carbon fiber prepreg paving of needs is tamped on mold；Then, external forming module C is mounted on carbon fiber prepreg, external forming module C is connected by rear fender, the location hole on front pressuring plate, positioning pin and inner cavity forming module B corresponding position, positioning；Subsequently, the mold assembled is sent into autoclave, and carries out vacuum pumping, is evacuated to -100KPa, 800KPa compressed air is filled in autoclave, and heat until carbon fiber prepreg completion of cure；Finally, successively dismantling external forming module C, inner cavity forming module B one by one, obtaining whole box parts cooling mold.
Description
Technical field
The invention belongs to aerospace components forming fields, are related to aerospace and are formed with composite products, specifically
It is related to a kind of aerospace carbon fibre composite cabinet shaping mould and its shaping box body technology.
Background technique
Box parts are the common components in aerospace field, are mainly used for electric appliance member on aerospace flight vehicle
The integrated and function integration of part, therefore these box parts have not required nothing more than higher intensity, lighter quality equally will also have
Higher precision.
It is existing, generally use carbon fiber to cooperate aircraft aluminum connector aerospace flight vehicle upper box moulding process
It is separately formed into the surrounding component of cabinet, then constitutes cabinet with the method assembling both ends flange component for being glued, riveting.In this way,
The cabinet moulding process arrived is not only cumbersome, but also obtained cabinet due to being glued again, staking process, and dimensional accuracy not can guarantee,
Structural strength is poor.In addition the load elements such as setting electric elements in cabinet, will increase additional weight when the later period assembles, these electricity
Device element by cabinet with aerospace flight vehicle navigates by water when due to Airborne Inertial etc. effect, can constantly generate random vibration,
Therefore there need be high structural strength to aerospace cabinet after molding.
Summary of the invention
It is an object of the present invention to provide a kind of aerospace carbon fibre composite cabinet shaping mould and its molding cabinet works
Skill, one-pass molding aerospace flight vehicle upper box avoid existing aerospace carbon fibre composite cabinet packing from leading
The problem that the structural strength of cause is poor, dimensional accuracy is low, quality is heavy, obtained box parts product structure intensity height, dimensional accuracy
High and quality is also relatively light.
In order to achieve the goal above, the technical solution adopted by the present invention are as follows:
A kind of aerospace carbon fibre composite cabinet shaping mould, including support member, the setting of support member inside
Inner cavity forming module B, the support member constitute the formpiston to match with cabinet molded part inner cavity with inner cavity forming module B,
External forming module C is set on the outside of support member；
The support member includes the upper ledge of upper and lower Parallel Symmetric arrangement, lower frame, the left frame of left and right Parallel Symmetric arrangement,
Right frame, the upper ledge, lower frame, left frame, right frame surround the first square cartridge structure, and lock ring is arranged positioned at the both ends of the first square cartridge structure
Plate；
The inner cavity forming module B includes the first upper mold core for being located above left and right flush arrangement, the second upper mold core, position
It is leveled up and down upper left mold core, the lower left mold core of arrangement in left, is leveled up and down the upper right mold core of arrangement, lower right mould positioned at right
Core, and be located below the lower mold core of arrangement, it is first upper mold core, the second upper mold core, upper left mold core, lower left mold core, upper right
Mold core, lower right mold core, lower mold core surround the second square cartridge structure, are arranged with forward flange, rear method positioned at the both ends of the second square cartridge structure
Orchid, the left and right inner wall for being close to forward flange positioned at the inside of forward flange are arranged with muscle before left front muscle, the right side；
The external forming module C includes top board, the lower platen of upper and lower Parallel Symmetric arrangement, left and right Parallel Symmetric cloth
Left side pressing plate, the right side pressing plate set, front pressuring plate, the rear fender of front and back Parallel Symmetric arrangement, the top board, lower platen, a left side
Side plate, right side pressing plate, front pressuring plate, rear fender surround sealing side's chamber.
Further, the lock ring plate includes the folded plate that is sequentially arranged of four corners positioned at the first square cartridge structure, and four
The folded plate in a corner is tightly attached to the corner where it.
Further, the front pressuring plate, location hole and/or positioning pin, the external molding are set on rear fender
Module C is connect by front pressuring plate, the location hole on rear fender and/or positioning pin with inner cavity forming module B.
Further, pre-buried aircraft aluminum connector in the formpiston, refills carbon fibre composite.
The present invention also provides a kind of aerospace carbon fibre composite cabinet shaping mould shaping box body technologies, including with
Lower step:
Firstly, support member and inner cavity forming module B are assembled, a sun to match with box parts inner cavity is formed
Mould；
Secondly, the pre-buried aircraft aluminum connector on formpiston, and the carbon fiber prepreg paving of needs is filled out on mold
It is real；
Then, external forming module C is mounted on carbon fiber prepreg, external forming module C passes through rear fender, preceding pressure
Location hole, positioning pin and inner cavity forming module B corresponding position on plate connect, positioning；
Subsequently, the mold assembled is sent into autoclave, and carries out vacuum pumping, is evacuated to -100KPa, hot pressing
It is filled with 800KPa compressed air in tank, and heats until carbon fiber prepreg completion of cure；
Finally, successively dismantling external forming module C, inner cavity forming module B one by one, obtaining whole cooling mold
Box parts.
Further, the groove part by the carbon fiber prepreg paving of needs including the lower mold core on formpiston on mold
And the equal paving of groove part of muscle is tamped before left front muscle, the right side.
Further, the vacuum pumping is sent into before the mold assembled is sent into autoclave, or in mold
Autoclave operates simultaneously.
Further, the vacuum pumping, which is used, installs vacuum bag additional in mold exterior, setting cladding in vacuum bag
The soft gas permeable felt of carbon fiber prepreg.
Further, when dismantling inner cavity forming module B, forward flange, rear flange are first dismantled, then dismantles muscle before left front muscle, the right side,
The second square cartridge structure is dismantled again.
The technical effects of the invention are that: the box parts product obtained using present invention production, one-pass molding are solidified into
All features of molding box body are not necessarily to subsequent assembling, improve the structural strength of box parts product to greatest extent；And box parts produce
Product interior shape is consistent with mold, and dimensional accuracy reaches 0.1mm；Reduce simultaneously existing using volume needed for the processes such as riveting
External reinforcement position weight and nut weight.
Detailed description of the invention
Fig. 1 is the detonation configuration figure of shaping mould of the invention；
Fig. 2 is the main view of shaping mould of the invention；
Fig. 3 is the rearview of shaping mould of the invention；
Fig. 4 is the backsight structural representation that shaping mould of the invention removes rear fender and rear flange；
Appended drawing reference in figure: top board 1, cabinet molded part 2, upper ledge 3, left frame 4, rear fender 5, right frame 6, lower frame 7, right side
Pressing plate 8, lower platen 9, it is right before muscle 10, upper left mold core 11, lower mold core 12, lower right mold core 13, forward flange 14, front pressuring plate 15, lock ring
Plate 16, lower left mold core 17, upper right mold core 18, left front muscle 19, left side pressing plate 20, the second upper mold core 21, the first upper mold core 22, rear method
Orchid 23.
Specific embodiment
Referring to attached drawing, a kind of aerospace carbon fibre composite cabinet shaping mould, including support member A, support portion
Setting inner cavity forming module B, the support member A and inner cavity forming module B are constituted and 2 inner cavity of cabinet molded part on the inside of part A
External forming module C is arranged in the formpiston to match, the outside support member A；
The support member A includes upper ledge 3, the lower frame 7 of upper and lower Parallel Symmetric arrangement, a left side for left and right Parallel Symmetric arrangement
Frame 4, right frame 6, the upper ledge 3, lower frame 7, left frame 4, right frame 6 surround the first square cartridge structure, positioned at the two of the first square cartridge structure
End setting lock ring plate 16；
The inner cavity forming module B includes the first upper mold core 22, the second upper mold core for being located above left and right flush arrangement
21, it is leveled up and down upper left mold core 11, the lower left mold core 17 of arrangement positioned at left, is leveled up and down the upper right mold core of arrangement positioned at right
18, lower right mold core 13, and it is located below the lower mold core 12 of arrangement, first upper mold core 22, the second upper mold core 21, upper left mould
Core 11, lower left mold core 17, upper right mold core 18, lower right mold core 13, lower mold core 12 surround the second square cartridge structure, are located at the second square tube knot
The both ends of structure are arranged with forward flange 14, rear flange 23, and the left and right inner wall for being close to forward flange 14 positioned at the inside of forward flange 14 sets up separately
Have left front muscle 19, it is right before muscle 10；
The external forming module C includes top board 1, the lower platen 9 of upper and lower Parallel Symmetric arrangement, left and right Parallel Symmetric
Left side pressing plate 20, the right side pressing plate 8 of arrangement, front pressuring plate 15, the rear fender 5 of front and back Parallel Symmetric arrangement, the top board 1,
Lower platen 9, left side pressing plate 20, right side pressing plate 8, front pressuring plate 15, rear fender 5 surround sealing side's chamber.
Further, the lock ring plate 16 includes the folded plate being sequentially arranged positioned at the four corners of the first square cartridge structure,
The folded plate of four corners is tightly attached to the corner where it.
Further, the front pressuring plate 15, location hole and/or positioning pin be set on rear fender 5, the outside at
Pattern block C is connect by front pressuring plate 15, the location hole on rear fender 5 and/or positioning pin with inner cavity forming module B.
Further, pre-buried aircraft aluminum connector in the formpiston, refills carbon fibre composite.
Following cabinet products, box parts, box parts product are that the present invention needs molding product -- cabinet.
Referring to Fig.1, cabinet molded part 2 of the present invention is cabinet product, is the electric appliance box of the equipment such as Aeronautics and Astronautics, adopts
It is carbon fiber T700 prepreg, through the invention mold heat-pressure curing one-pass molding in autoclave with material.
Fig. 1 is the explosive view of actual working state of the present invention, and the body formed part 2 of figure raising middle flask is made box parts, on
Frame 3, left frame 4, right frame 6, lower frame 7, lock ring plate 16 constitute support member A；Muscle 10, upper left mold core 11, lower mold core 12, lower right before the right side
Mold core 13, forward flange 14, lower left mold core 17, upper right mold core 18, left front muscle 19, the second upper mold core 21, the first upper mold core 22, rear method
Orchid 23 constitutes inner cavity forming module B；Lower platen 9, top board 1, rear fender 5, right side pressing plate 8, front pressuring plate 15, left side pressing plate 20,
Constitute external forming module C.
When being made to cabinet molded part 2, firstly, support member A and inner cavity forming module B are assembled, formed one with
The formpiston that box parts inner cavity matches；Secondly, the pre-buried aircraft aluminum connector on formpiston, and by the carbon fibre initial rinse of needs
Paving is expected on mold, the groove of muscle 10 before the groove part and left front muscle 19, the right side here including the lower mold core 12 on formpiston
Part paving is tamped；Here illustrate lower aircraft aluminum connector, be the connection position position on box parts with electric elements,
It is located at these positions on formpiston and reserves corresponding fixation hole for the placement of aircraft aluminum connector；Then external forming module C is installed
On carbon fiber prepreg (i.e. cabinet molded part 2), external forming module C by rear fender 5, the location hole on front pressuring plate 15,
Positioning pin connect realization positioning with inner cavity forming module B corresponding position；Then the mold assembled is sent into autoclave, and is carried out
Vacuum pumping, here, vacuum pumping can be before the mold assembled be sent into autoclave, or can also send in mold
Enter autoclave while operating；Here the purpose vacuumized under illustrating, since carbon fiber prepreg paving is that there are materials on mold
Expect that paving is imprecise, the especially paving of the groove structure material of such as groove part of lower mold core 12, the application uses
Mold exterior installs vacuum bag additional and pumping accessories for vacuum (including cladding carbon fiber prepreg, namely coats cabinet molded part 2
Soft gas permeable felt, and mouth, connector are connect positioned at vacuumizing for vacuum bag both ends；The effect one that soft gas permeable felt is arranged is logical
The air hole crossed thereon plays the role of air guide, and vacuum bag film is avoided to be placed directly against the smooth part face of carbon fiber prepreg, occurs taking out true
It is empty uneven, lead to 2 molding effect deviation of cabinet molded part, plays so that reaching identical vacuum degree in vacuum bag, further
The uniform molding effect of the body formed part 2 of guard box；Secondly and the angle rib that avoids mold from having puncture vacuum bag, cause to vacuumize
The problem of effect is bad or even fails.) be evacuated to -100KPa, be filled with 800KPa compressed air in autoclave, and heat until
Carbon fiber prepreg completion of cure；Finally, cooling mold is successively dismantled external forming module C (here according to demoulding one by one
Habit successively dismantles external forming module C, such as successively dismantles front pressuring plate 15, rear fender 5, top board 1, lower platen 9, left side pressing plate
20, right side pressing plate 8) inner cavity forming module B (similarly here according to demoulding habit successively dismantle inner cavity forming module B, such as first tear open
Forward flange 14, rear flange 23 are unloaded, then dismantles muscle 10 before left front muscle 19, the right side, then successively dismantle the second square cartridge structure), obtain entirety
Box parts.
In addition, the plate processing of inventive die is processed using high-precision numerical control machining center, guarantee mold body essence
Degree；And disengaging section is needed to be added to drafting angle, demoulding is simple.
Support member A of the present invention, inner cavity forming module B, outside forming module C are all made of partitioned organization, the structure of piecemeal
It is easy that form can make demoulding, and can repair to mold piecemeal, and the processing is simple.
Based on above-mentioned, of the invention forming die structure, by internally positioned support member A and inner cavity forming module B,
External forming module C composition.Support member A provides structural support for mold, so that inner cavity forming module B is accurately positioned, in heat
It presses in tank and solidifies in pressure process, support die does not collapse under 800KPa positive pressure, -100KPa condition of negative pressure.Inner cavity shaping mould
Block B forms all structure features in cabinet parts product inner cavity, and guarantees its shape, position precision；External forming module C shaping box
Body parts product outer shape feature, and pressure is transmitted, make part that there is good compactness.
The box parts product obtained using present invention production, one-pass molding, all features of curing molding cabinet, after being not necessarily to
Continuous assembling, improves the structural strength of box parts product to greatest extent；And box parts interiors of products shape is consistent with mold,
Dimensional accuracy reaches 0.1mm, and cooperates vacuum pumping that can further reach high dimensional accuracy；Reduce existing adopt simultaneously
Additional reinforcing position weight and nut weight needed for the processes such as riveting.
Claims (9)
1. a kind of aerospace carbon fibre composite cabinet shaping mould, it is characterised in that: including support member (A), support
Inner cavity forming module (B) is set on the inside of component (A), the support member (A) and inner cavity forming module (B) constitute and cabinet at
External forming module (C) is arranged in the formpiston that type part (2) inner cavity matches, support member (A) outside；
The support member (A) includes upper ledge (3), the lower frame (7) of upper and lower Parallel Symmetric arrangement, left and right Parallel Symmetric arrangement
Left frame (4), right frame (6), the upper ledge (3), lower frame (7), left frame (4), right frame (6) surround the first square cartridge structure, are located at the
Lock ring plate (16) are arranged in the both ends of one square cartridge structure；
The inner cavity forming module (B) includes the first upper mold core (22), the second upper mold core for being located above left and right flush arrangement
(21), it is leveled up and down upper left mold core (11), the lower left mold core (17) of arrangement positioned at left, is leveled up and down the upper of arrangement positioned at right
Right mould core (18), lower right mold core (13), and it is located below the lower mold core (12) of arrangement, first upper mold core (22), second
Upper mold core (21), upper left mold core (11), lower left mold core (17), upper right mold core (18), lower right mold core (13), lower mold core (12) surround
Second square cartridge structure is arranged with forward flange (14), rear flange (23) positioned at the both ends of the second square cartridge structure, is located at forward flange (14)
Inside be close to forward flange (14) left and right inner wall be arranged with left front muscle (19), it is right before muscle (10)；
The external forming module (C) includes top board (1), the lower platen (9) of upper and lower Parallel Symmetric arrangement, and left and right is parallel right
Claim left side pressing plate (20), the right side pressing plate (8) of arrangement, front pressuring plate (15), the rear fender (5) of front and back Parallel Symmetric arrangement are described
Top board (1), lower platen (9), left side pressing plate (20), right side pressing plate (8), front pressuring plate (15), rear fender (5) surround sealing side
Chamber.
2. aerospace according to claim 1 carbon fibre composite cabinet shaping mould, it is characterised in that: described
Lock ring plate (16) includes the folded plate being sequentially arranged positioned at the four corners of the first square cartridge structure, and the folded plate of four corners is tightly attached to
Corner where it.
3. aerospace according to claim 1 or 2 carbon fibre composite cabinet shaping mould, it is characterised in that: institute
Location hole is set on the front pressuring plate (15) stated, rear fender (5) and/or positioning pin, the external forming module (C) pass through preceding pressure
Plate (15), the location hole on rear fender (5) and/or positioning pin are connect with inner cavity forming module (B).
4. aerospace according to claim 3 carbon fibre composite cabinet shaping mould, it is characterised in that: described
Pre-buried aircraft aluminum connector, refills carbon fibre composite in formpiston.
5. the carbon fibre composite cabinet shaping mould shaping box of aerospace described in a kind of any one of claim 1-4
Body technology, which comprises the following steps:
Firstly, support member (A) and inner cavity forming module (B) is assembled, a sun to match with box parts inner cavity is formed
Mould；
Secondly, the pre-buried aircraft aluminum connector on formpiston, and the carbon fiber prepreg paving of needs is tamped on mold；
Then, external forming module (C) is mounted on carbon fiber prepreg, external forming module (C) by rear fender (5),
Location hole, positioning pin and inner cavity forming module (B) corresponding position on front pressuring plate (15) connect, positioning；
Subsequently, the mold that assembles is sent into autoclave, and carries out vacuum pumping, is evacuated to -100KPa, in autoclave
It is filled with 800KPa compressed air, and is heated until carbon fiber prepreg completion of cure；
Finally, successively dismantling external forming module (C), inner cavity forming module (B) one by one, obtaining whole cooling mold
Box parts.
6. aerospace according to claim 5 carbon fibre composite cabinet shaping mould shaping box body technology, special
Sign is, includes groove part and the left side of the lower mold core (12) on formpiston on mold by the carbon fiber prepreg paving of needs
The equal paving of groove part of muscle (10) is tamped before preceding muscle (19), the right side.
7. aerospace according to claim 5 carbon fibre composite cabinet shaping mould shaping box body technology, special
Sign is that the vacuum pumping is sent into autoclave simultaneously before the mold assembled is sent into autoclave, or in mold
Operation.
8. the carbon fibre composite cabinet shaping mould shaping box body technology of the aerospace according to claim 5 or 7,
It is characterized in that, the vacuum pumping, which is used, installs vacuum bag additional in mold exterior, setting cladding carbon fibre initial rinse in vacuum bag
The soft gas permeable felt of material.
9. aerospace according to claim 5 carbon fibre composite cabinet shaping mould shaping box body technology, special
Sign is, when dismantling inner cavity forming module B, first dismantles forward flange (14), rear flange (23), then dismantle left front muscle (19), it is right before
Muscle (10), then dismantle the second square cartridge structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811174648.5A CN109203511A (en) | 2018-10-09 | 2018-10-09 | Aerospace carbon fibre composite cabinet shaping mould and its shaping box body technology |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811174648.5A CN109203511A (en) | 2018-10-09 | 2018-10-09 | Aerospace carbon fibre composite cabinet shaping mould and its shaping box body technology |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109203511A true CN109203511A (en) | 2019-01-15 |
Family
ID=64983459
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811174648.5A Pending CN109203511A (en) | 2018-10-09 | 2018-10-09 | Aerospace carbon fibre composite cabinet shaping mould and its shaping box body technology |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109822942A (en) * | 2019-01-28 | 2019-05-31 | 广东国立科技股份有限公司 | A method of exempting from vacuum bag autoclave and prepares carbon fibre composite |
| CN110936524A (en) * | 2019-11-19 | 2020-03-31 | 龚建叶 | Forming die and method for carbon fiber box |
| CN111113951A (en) * | 2020-01-03 | 2020-05-08 | 中国电子科技集团公司第十四研究所 | Integral forming manufacturing method of lightweight carbon fiber case |
| CN114248473A (en) * | 2021-12-20 | 2022-03-29 | 中国电子科技集团公司第十四研究所 | Carbon fiber machine case shaping mold core structure |
| CN114932643A (en) * | 2022-04-11 | 2022-08-23 | 重庆力昇特装科技有限公司 | Box forming die |
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| CN111113951B (en) * | 2020-01-03 | 2021-11-23 | 中国电子科技集团公司第十四研究所 | Integral forming manufacturing method of lightweight carbon fiber case |
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| CN114932643A (en) * | 2022-04-11 | 2022-08-23 | 重庆力昇特装科技有限公司 | Box forming die |
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