CN104290337A - Method for realization of co-cementing of reinforcing rib web composite produced part by accurate positioning soft tooling - Google Patents
Method for realization of co-cementing of reinforcing rib web composite produced part by accurate positioning soft tooling Download PDFInfo
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- CN104290337A CN104290337A CN201410399012.6A CN201410399012A CN104290337A CN 104290337 A CN104290337 A CN 104290337A CN 201410399012 A CN201410399012 A CN 201410399012A CN 104290337 A CN104290337 A CN 104290337A
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- shaped
- bottom plate
- bogusware
- soft
- soft frock
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- 238000000034 method Methods 0.000 title claims abstract description 37
- 239000002131 composite material Substances 0.000 title claims abstract description 22
- 230000003014 reinforcing effect Effects 0.000 title abstract 3
- 239000002184 metal Substances 0.000 claims abstract description 29
- 229910052751 metal Inorganic materials 0.000 claims abstract description 29
- 238000000465 moulding Methods 0.000 claims abstract description 8
- 210000003205 muscle Anatomy 0.000 claims description 45
- 238000007493 shaping process Methods 0.000 claims description 16
- 229920001971 elastomer Polymers 0.000 claims description 15
- 239000000463 material Substances 0.000 claims description 13
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 10
- 239000004917 carbon fiber Substances 0.000 claims description 10
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 10
- 230000002787 reinforcement Effects 0.000 claims description 10
- 238000007711 solidification Methods 0.000 claims description 10
- 230000008023 solidification Effects 0.000 claims description 10
- 238000005728 strengthening Methods 0.000 claims description 5
- 229920002379 silicone rubber Polymers 0.000 claims description 3
- 238000012545 processing Methods 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 10
- 230000000694 effects Effects 0.000 abstract description 5
- 108010053481 Antifreeze Proteins Proteins 0.000 abstract 1
- 239000011162 core material Substances 0.000 description 13
- 238000010586 diagram Methods 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 239000011157 advanced composite material Substances 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 230000004807 localization Effects 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 239000010959 steel Substances 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
The invention discloses a method for realization of co-cementing of a reinforcing rib web composite produced part by accurate positioning soft tooling; a T shaped rib metal false part and a T shaped positioning device are fixed on a die bottom plate, soft tooling is paved on the surface, the outermost layer is sealed under with a vacuum bag, the soft tooling is formed in an autoclave; a gap is filled with a T shape rib prepreg, wherein the gap is formed after the T shaped rib metal false part is removed, a web is fixed on the die bottom plate, the cured soft tooling and the die bottom plate are assembled, and thermally pressed to form the reinforcing rib web composite produced part. Compared with a traditional core die molding method, according to the method, pressure applied by the autoclave can be uniformly and accurately transmitted, super poor thickness of the composite produced part can be avoided, the soft tooling is thinner in wall thickness, thermal hysteresis effect of the T shaped rib part can be avoided, the forming quality of the produced part can be effectively guaranteed by the above two points, and the qualified rate and the efficiency of production can be improved. At the same time, the T shaped positioning device can ensure that the relative position accuracy of co-cemented T shaped rib and web, and guarantee the quality of products.
Description
Technical field
The present invention relates to advanced composite material manufacturing technology field, particularly relate to the high-performance carbon fibre composite material structural member manufacture in airborne vehicle, spacecraft, automobile industry.
Background technology
Resin-based carbon fiber composite has specific strength, specific stiffness is high, designability is strong, and fatigue crack-resistant performance is good, corrosion-resistant, the performance that good stability of the dimension etc. are superior applies high performance structures material very widely in the fields such as current Aeronautics and Astronautics, traffic.In multiple molding carbon fiber composite material technique, autoclave technique has forming temperature and pressure uniform, part for different materials, profile, size and structure has good adaptability, thus becomes one of major processes of research and manufacture Aero-Space high-quality composite element.
Along with the raising day by day to composite material parts intensity, rigidity requirement, the structure of part also becomes increasingly complex, and the web wherein with T-shaped reinforcement is one of typical structure part.
Improve the needs of intensity and loss of weight for product, web often exists the element such as thickened area, lightening core, and this just requires that the relative position degree of T-shaped muscle and web is enough accurate.The common cementation process flow process of general T-shaped muscle strengthening web structural member is: the first curing molding in web part of product, then by after the prepreg pre-compacted of T-shaped muscle part, with the web cemented in place be cured under soft state, enter autoclave together, shaping at high temperature under high pressure.
Mostly use core to realize the common cementation and formation of this kind of product in current technique, core material is generally mould steel or aluminium alloy, there is positioning relation between core and die bottom plate.The effect of core is that the pressure and temperature of autoclave is passed to composite product, makes product shaping at high temperature under high pressure, and the rigidity of core can ensure that the appearance and size of T-shaped muscle meets designing requirement simultaneously.
Use the shortcoming of core to mainly contain following three aspects: (1) has certain rigidity due to core self, be just difficult to accomplish by core conduction ambient pressure all accurately even, easily cause product T-shaped muscle segment thickness overproof; (2) because core has certain thickness, according to heat-conduction effect, the heating rate of product T-shaped muscle part can be more delayed than other parts, thus affect the inside Forming Quality of product; (3) because core is metal material, deadweight is comparatively large, and it is very inconvenient to operate.The simultaneously manufacture of metal core and maintenance cost higher, reprocess or the heavy fresh processed manufacturing cycle longer.
Summary of the invention
The object of this invention is to provide a kind of in forming process, evenly accurate to product T-shaped muscle part applied pressure, the heating rate at each position of product is consistent, to ensure that the appearance and size precision of product, Forming Quality, surface quality and thickness deviation meet the manufacture method of the T-shaped muscle strengthening web product of designing requirement.
To achieve these goals, the present invention is by the following technical solutions: the soft frock in a kind of accurate location realizes the multiple material product of reinforcement web method cementing altogether, comprises the following steps:
(1) conventional thermocompression tank technological forming web is adopted; By machine-building processing and T-shaped muscle product appearance and size on all four T-shaped muscle metal bogusware and T-shaped positioner;
(2) T-shaped muscle metal bogusware and T-shaped positioner are fixed on die bottom plate, in the soft frock of surperficial paving of T-shaped muscle metal bogusware and T-shaped positioner, afterwards in outermost layer vacuum bag vacuum seal, enter the soft frock of autoclave molding, solidifying pressure is 500 ~ 800kPa, solidification temperature 160 ~ 200 DEG C, hardening time 50 ~ 80min;
(3) soft frock shaping after, remove vacuum bag, take off the soft frock of solidification, take out T-shaped muscle metal bogusware and T-shaped positioner, T-shaped muscle prepreg is packed in the gap of taking out T-shaped muscle metal bogusware, web is fixed on die bottom plate, T-shaped positioner is fixed on the position on step die bottom plate in a period of time, by the soft frock of solidification and die bottom plate matched moulds, again in skin vacuum bag vacuum seal, enter autoclave molding, namely obtain T-shaped muscle strengthening web structural composite material product.
Described soft frock comprises two-layer rubber layer and is coated on the carbon fiber prepreg enhancement layer in rubber layer.
Described rubber layer adopts silicon rubber.
The number of plies of the described carbon fiber prepreg enhancement layer be coated in rubber layer is 1 ~ 5 layer.
The mode of described T-shaped muscle metal bogusware and the finger setting of T-shaped positioner passing hole is fixed on die bottom plate.
Described T-shaped muscle metal bogusware is fixed on die bottom plate, fixes a T-shaped positioner the both sides that each T-shaped muscle metal bogusware axially overlaps are each.
The present invention compared with prior art, has following advantage:
(1) compared with conventional core mold forming method, soft frock evenly, accurately can transmit autoclave applied pressure, avoids composite product to occur the phenomenon that thickness is overproof;
(2) soft frock wall thickness is thinner, can avoid the thermo-lag effect at T-shaped muscle position, and above 2 Forming Quality that effectively can ensure product, improve the qualification rate and efficiency of producing;
(3) at soft frock mould, and composite product mould is arranged the identical T-shaped positioner of two groups of appearance and sizes and position, the accurate location between soft frock and metal die base plate can be realized, thus the strict relative position degree controlling the shaping rear T-shaped muscle of product and web, ensure the Forming Quality of product;
(4) soft frock is based on rubber, and surface has elasticity, plays the effect of an equal pressure pad simultaneously, and product shaping rear surface quality is better;
(5) soft frock can be reused, and again manufactures also more for convenience, effectively reduces production cost and manufacturing cycle.
Accompanying drawing explanation
Fig. 1 is schematic diagram T-shaped muscle metal bogusware and T-shaped positioner are fixed on die bottom plate.
Fig. 2 is the schematic diagram of the soft frock of paving.
Fig. 3 is at the vacuum-packed schematic diagram of outermost layer vacuum bag.
Fig. 4 is after being packed into T-shaped muscle prepreg, by the soft frock of solidification and the schematic diagram of die bottom plate matched moulds.
Fig. 5 is by the soft frock of solidification and the schematic perspective view of die bottom plate matched moulds.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention is described further.
First the web part of forming composite product, forming method is identical with conventional thermocompression tank technique.Because web part is solid state, shaping only for product T-shaped muscle part of soft frock, and after ensureing that product is shaping, the relative position degree of T-shaped muscle and web meets design requirement.
By the method for machine-building, process some T-shaped muscle metal boguswares, the quantity of bogusware and relative position must be consistent with the T-shaped reinforcement on composite product, therefore there is positioning relation between metal bogusware and die bottom plate.
Utilize the cavity that T-shaped muscle metal bogusware and die bottom plate are formed, the soft frock of paving.Soft frock take silicon rubber as main material, by rubber successively paving in cavity, in the middle of rubber layer, want paving carbon fiber prepreg enhancement layer as enhancement layer, to improve the integral rigidity of soft frock, the number of plies of paving rubber and carbon fiber prepreg enhancement layer depends primarily on size and the complex structure degree of composite product, and the number of plies of carbon fiber prepreg enhancement layer is generally 1 ~ 5 layer.Last in outermost layer vacuum bag vacuum seal, and according to the curing process of rubber, enter the soft frock of autoclave molding, solidifying pressure is 500 ~ 800kPa, preferably 500 ~ 600 kPa, solidification temperature 160 ~ 200 DEG C, preferably 170 DEG C ± 5 DEG C, hardening time 50 ~ 80min, preferably 60 ~ 70min, in the soft frock of high-temperature and high-pressure conditions compacted under.
In common cementation and formation technique, soft frock must possess following two functions:
1) self possess certain structural rigidity, can ensure T-shaped muscle shaping after appearance and size and spacing;
2) soft frock must possess the positioning function with die bottom plate, guarantees the relative position degree of the shaping rear T-shaped muscle of composite product and web.
Altogether in bonding process, the web part of composite product is solid state, can position with the mode of hole finger setting and die bottom plate; And T-shaped muscle partial prepreg is after pre-compacted, be filled into the relevant position of soft frock, then by soft frock and die bottom plate matched moulds, in skin vacuum bag vacuum seal, enter solidification of hot-press tank shaping.
But soft frock take rubber as main material, therefore cannot machining, hole finger setting can not be carried out with metal base plate in matched moulds process, additive method must be adopted to ensure the relative position degree of the shaping rear T-shaped muscle of product and web.
The localization method used in the present invention is: on the mould of soft frock, and corresponding each T-shaped metal bogusware, add 2 T-shaped positioners, positioner overlaps with the axis of metal bogusware, and there is assembling and positioning relation with die bottom plate, as shown in Figure 1.
When shaping soft frock, the paving scope of rubber layer and carbon fiber enhancement Layer will cover T-shaped positioner, after ensureing that soft frock is shaping, leaves the groove of same size, as Fig. 2 in the corresponding position of positioner.
After soft frock is shaping, by complexed metal mould, complete the common cementation and formation of T-shaped muscle strengthening web, flow process is as follows:
1) web is placed on die bottom plate, because web is solid state, can locating hole be drilled, carry out hole with the alignment pin on mould and sell and coordinate, ensure that the position of web on die bottom plate immobilizes.
2) mould of composite product is equally with T-shaped positioner, and the size of device, position all fit like a glove with the positioner on soft frock mould.
3) by T-shaped muscle prepreg good for pre-compacted, be filled in soft frock, again the groove in soft frock is matched with the T-shaped positioner on product mould, by the location between soft frock and mould, indirectly complete the location of composite product T-shaped muscle part and web part, as Figure 4 and 5.
After product is shaping, soft frock is separated with composite product and namely completes the demoulding.According to the difference using materials and process, soft frock can be reused for several times to tens of times, if soft frock is damaged or distortion, metal bogusware and mould can be used again to manufacture soft frock.
The above is only preferred embodiment of the present invention, not does any type of restriction to the present invention.Every above embodiment is done according to techniques and methods essence of the present invention any simple modification, equivalent variations and modification, all still belong in the scope of techniques and methods scheme of the present invention.
Claims (6)
1. accurately the soft frock in location realizes the multiple material product of a reinforcement web method cementing altogether, it is characterized in that comprising the following steps:
(1) conventional thermocompression tank technological forming web is adopted; By machine-building processing and T-shaped muscle product appearance and size on all four T-shaped muscle metal bogusware and T-shaped positioner;
(2) T-shaped muscle metal bogusware and T-shaped positioner are fixed on die bottom plate, in the soft frock of surperficial paving of T-shaped muscle metal bogusware and T-shaped positioner, afterwards in outermost layer vacuum bag vacuum seal, enter the soft frock of autoclave molding, solidifying pressure is 500 ~ 800kPa, solidification temperature 160 ~ 200 DEG C, hardening time 50 ~ 80min;
(3) soft frock shaping after, remove vacuum bag, take off the soft frock of solidification, take out T-shaped muscle metal bogusware and T-shaped positioner, T-shaped muscle prepreg is packed in the gap of taking out T-shaped muscle metal bogusware, web is fixed on die bottom plate, T-shaped positioner is fixed on the position on step die bottom plate in a period of time, by the soft frock of solidification and die bottom plate matched moulds, again in skin vacuum bag vacuum seal, enter autoclave molding, namely obtain T-shaped muscle strengthening web structural composite material product.
2. the soft frock in accurate location according to claim 1 realizes the multiple material product of reinforcement web method cementing altogether, it is characterized in that: described soft frock comprises two-layer rubber layer and is coated on the carbon fiber prepreg enhancement layer in rubber layer.
3. the soft frock in accurate location according to claim 2 realizes the multiple material product of reinforcement web method cementing altogether, it is characterized in that: described rubber layer adopts silicon rubber.
4. the soft frock in accurate location according to claim 3 realizes the multiple material product of reinforcement web method cementing altogether, it is characterized in that: described in the number of plies of carbon fiber prepreg enhancement layer that is coated in rubber layer be 1 ~ 5 layer.
5. the soft frock in accurate location according to claim 1 realizes the multiple material product of reinforcement web method cementing altogether, it is characterized in that: the mode of described T-shaped muscle metal bogusware and the finger setting of T-shaped positioner passing hole is fixed on die bottom plate.
6. the soft frock in accurate location according to claim 5 realizes the multiple material product of reinforcement web method cementing altogether, it is characterized in that: described T-shaped muscle metal bogusware is fixed on die bottom plate, fix a T-shaped positioner the both sides that each T-shaped muscle metal bogusware axially overlaps are each.
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| CN201410399012.6A CN104290337A (en) | 2014-08-14 | 2014-08-14 | Method for realization of co-cementing of reinforcing rib web composite produced part by accurate positioning soft tooling |
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| CN201410399012.6A CN104290337A (en) | 2014-08-14 | 2014-08-14 | Method for realization of co-cementing of reinforcing rib web composite produced part by accurate positioning soft tooling |
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| CN104290337A true CN104290337A (en) | 2015-01-21 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105965917A (en) * | 2016-06-20 | 2016-09-28 | 中国商用飞机有限责任公司 | Co-curing forming technological method for composite fuselage frame body with ribs added to two sides |
| CN106182825A (en) * | 2016-07-13 | 2016-12-07 | 航天海鹰(镇江)特种材料有限公司 | The localization method of soft frock in a kind of composite product forming process |
| CN107283868A (en) * | 2017-06-22 | 2017-10-24 | 中航复合材料有限责任公司 | A kind of overall localization method of the rib for being molded carbon fibre composite Material Stiffened Panel |
| CN109795135A (en) * | 2017-11-16 | 2019-05-24 | 航天海鹰(镇江)特种材料有限公司 | A kind of method that soft tooling realization large scale I-beam stiffened skin structural composite material product is total to cementation and formation |
| CN110815857A (en) * | 2019-11-26 | 2020-02-21 | 航天海鹰(镇江)特种材料有限公司 | Forming method and application of flexible tool for reinforcing rib and web plate co-bonding |
| CN112912222A (en) * | 2018-10-19 | 2021-06-04 | 采埃孚股份公司 | Vehicle component for a motor vehicle and method for producing such a vehicle component |
| CN114311759A (en) * | 2022-03-15 | 2022-04-12 | 成都飞机工业（集团）有限责任公司 | Wallboard rib forming method |
| CN114379110A (en) * | 2021-12-10 | 2022-04-22 | 航天海鹰(镇江)特种材料有限公司 | Mould-splitting paving self-adaptive soft mould forming method for super-thickness variable-curvature composite part |
| CN115071022A (en) * | 2022-06-21 | 2022-09-20 | 中国人民解放军国防科技大学 | A device and method for hot pressing of T-shaped thermoplastic composite parts |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3739753A1 (en) * | 1987-11-24 | 1989-06-08 | Dornier Gmbh | Process for producing components from fibre-reinforced plastics |
| US20010005061A1 (en) * | 1999-05-13 | 2001-06-28 | Northrop Grumman Corporation | Method and apparatus for fabricating composite structures |
| CN101327654A (en) * | 2008-07-24 | 2008-12-24 | 北京彩虹宇星科技发展有限公司 | Mould-closing bag-moulding one-shot forming technique for composite material |
| CN101351327A (en) * | 2005-12-29 | 2009-01-21 | 空客西班牙公司 | Manufacturing process for composite structures with embedded pre-cured molds |
| CN103496179A (en) * | 2013-10-10 | 2014-01-08 | 航天海鹰(镇江)特种材料有限公司 | Molding method for composite material structural member with I-shaped section |
-
2014
- 2014-08-14 CN CN201410399012.6A patent/CN104290337A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3739753A1 (en) * | 1987-11-24 | 1989-06-08 | Dornier Gmbh | Process for producing components from fibre-reinforced plastics |
| US20010005061A1 (en) * | 1999-05-13 | 2001-06-28 | Northrop Grumman Corporation | Method and apparatus for fabricating composite structures |
| CN101351327A (en) * | 2005-12-29 | 2009-01-21 | 空客西班牙公司 | Manufacturing process for composite structures with embedded pre-cured molds |
| CN101327654A (en) * | 2008-07-24 | 2008-12-24 | 北京彩虹宇星科技发展有限公司 | Mould-closing bag-moulding one-shot forming technique for composite material |
| CN103496179A (en) * | 2013-10-10 | 2014-01-08 | 航天海鹰(镇江)特种材料有限公司 | Molding method for composite material structural member with I-shaped section |
Non-Patent Citations (3)
| Title |
|---|
| 张耀等: "《航空复合材料技术成果文集》", 31 May 1993, 航空工业出版社 * |
| 赵渠森: "《先进复合材料手册》", 31 May 2003, 机械工业出版社 * |
| 赵美英，陶梅贞: "《复合材料结构力学与结构设计》", 31 December 2007, 西北工业大学出版社 * |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105965917A (en) * | 2016-06-20 | 2016-09-28 | 中国商用飞机有限责任公司 | Co-curing forming technological method for composite fuselage frame body with ribs added to two sides |
| CN105965917B (en) * | 2016-06-20 | 2018-05-11 | 中国商用飞机有限责任公司 | The co-curing moulding technique of composite material bilateral reinforcement fuselage framework |
| CN106182825A (en) * | 2016-07-13 | 2016-12-07 | 航天海鹰(镇江)特种材料有限公司 | The localization method of soft frock in a kind of composite product forming process |
| CN107283868A (en) * | 2017-06-22 | 2017-10-24 | 中航复合材料有限责任公司 | A kind of overall localization method of the rib for being molded carbon fibre composite Material Stiffened Panel |
| CN109795135A (en) * | 2017-11-16 | 2019-05-24 | 航天海鹰(镇江)特种材料有限公司 | A kind of method that soft tooling realization large scale I-beam stiffened skin structural composite material product is total to cementation and formation |
| CN112912222A (en) * | 2018-10-19 | 2021-06-04 | 采埃孚股份公司 | Vehicle component for a motor vehicle and method for producing such a vehicle component |
| CN112912222B (en) * | 2018-10-19 | 2023-02-17 | 采埃孚股份公司 | Vehicle component for a motor vehicle and method of manufacturing such a vehicle component |
| CN110815857A (en) * | 2019-11-26 | 2020-02-21 | 航天海鹰(镇江)特种材料有限公司 | Forming method and application of flexible tool for reinforcing rib and web plate co-bonding |
| CN114379110A (en) * | 2021-12-10 | 2022-04-22 | 航天海鹰(镇江)特种材料有限公司 | Mould-splitting paving self-adaptive soft mould forming method for super-thickness variable-curvature composite part |
| CN114379110B (en) * | 2021-12-10 | 2024-01-30 | 航天海鹰(镇江)特种材料有限公司 | Split-mold paving self-adaptive soft mold forming method for super-thickness variable-curvature composite material part |
| CN114311759A (en) * | 2022-03-15 | 2022-04-12 | 成都飞机工业（集团）有限责任公司 | Wallboard rib forming method |
| CN115071022A (en) * | 2022-06-21 | 2022-09-20 | 中国人民解放军国防科技大学 | A device and method for hot pressing of T-shaped thermoplastic composite parts |
| CN115071022B (en) * | 2022-06-21 | 2023-08-22 | 中国人民解放军国防科技大学 | Hot-press forming device and method for T-shaped thermoplastic composite material workpiece |
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Application publication date: 20150121 |