CN109849367A - A kind of processing method of big thickness composite skirt - Google Patents
A kind of processing method of big thickness composite skirt Download PDFInfo
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- CN109849367A CN109849367A CN201910213177.2A CN201910213177A CN109849367A CN 109849367 A CN109849367 A CN 109849367A CN 201910213177 A CN201910213177 A CN 201910213177A CN 109849367 A CN109849367 A CN 109849367A
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Abstract
The present invention relates to resin base fiber reinforced composite material prepreg autoclave molding technical field, especially a kind of processing method of big thickness composite skirt comprising following steps: prepare material；Mold prepares；Laying；Assemble envelope；Solidification；Demoulding；It is characterized in that, after the composite material of laying preset thickness, integrally carrying out pre-compacted to composite material and mold in lay-up process.In processing method provided by the invention, during laying, pre-compacted is carried out to composite material, the bubble of composite material interlayer can be effectively eliminated, improve layers cementing quality, keep the compacting of composite material blank even closer.So as to improve the quality of composite skirt.
Description
Technical field
The present invention relates to resin base fiber reinforced composite material prepreg autoclave molding technical fields, especially a kind of big
The processing method of thickness composite skirt.
Background technique
Rocket/missile engine case will realize connection or the connection with other components between grade, it is necessary to by between shell grade
Composite skirt realizes, effectively to realize the transmitting of thrust between grade.Composite skirt receiving be axially stretched, be compressed axially, ring
To a variety of load such as stretching, bending, shearing, load working condition is complicated；Composite material have density is small, specific strength is high, specific modulus is high,
The advantages that good corrosion resistance, is widely used in aerospace field.Autoclave method is to prepare high-performance aerospace composite wood
The main method of material；This method has been successfully applied to the molding of rocket/missile propulsive plant composite skirt；It is lesser for thickness
During which composite skirt typically directly uses room temperature to vacuumize pre- as needed with prepreg laying to the product of expectation thickness
Product and mold are put into autoclave simultaneously after envelope, in certain temperature, pressure to improve prepreg interlayer quality by the method for pumping
With curing molding under the time；For the composite skirt of big thickness (thickness >=10mm), due to passing through in prepreg laid course
The method that room temperature vacuumizes pre- pumping is limited to the compaction of laying, and will lead to the inside after product solidifies, hole occur more,
Even there is biggish lamination defect；In addition, the insufficient regions curing preceding thickness of compacting is partially thick, during solidification of hot-press tank,
Under the effect of hot pressing pressure tank, it is compacted the defects of insufficient region is easy to appear recess, internal fiber fold, product surface quality
Difference, fiber fold also result in product mechanical property decline, and stable product quality is poor.Therefore, effective, stable to improve big thickness
The compacting situation spent between composite skirt prepreg overlay becomes the key for improving big thickness composite skirt interiors of products quality.
Summary of the invention
Goal of the invention of the invention is: being directed to big thickness composite skirt stable product quality of the existing technology
Poor problem provides a kind of simple process, can be improved compaction between big thickness composite skirt product prepreg overlay,
It reduces interiors of products porosity and lamination defect, product surface quality is effectively ensured, prevent internal fiber fold and lead to mechanics
Performance decline.
To achieve the goals above, the technical solution adopted by the present invention are as follows:
A kind of processing method of big thickness composite skirt, comprising the following steps: prepare material；Mold prepares；Laying；Group
Fill envelope；Solidification；Demoulding；It is characterized in that, in lay-up process, after the composite material of laying preset thickness, to composite material
Pre-compacted is integrally carried out with mold.In processing method provided by the invention, during laying, precompressed is carried out to composite material
It is real, the bubble of composite material interlayer can be effectively eliminated, improve layers cementing quality, step up the compacting of composite material blank more
It is close.So as to improve the quality of composite skirt.
As a preferred solution of the present invention, the pre-compacted includes room temperature pre-compacted and/or hot pre-compacted；The room temperature is pre-
Compacting includes following operation: mold and laying being integrally put into vacuum bag film, vacuum system is formed, is taken out to the vacuum system true
It is empty；The hot pre-compacted includes following operation: mold and laying being integrally put into autoclave, vacuum is applied, applies pressure and carries
Lotus and temperature loading.Pre-compacted is carried out by above-mentioned mode.In actual operation, for can be according to the thickness of composite skirt
Degree and quality requirement, selection using room temperature pre-compacted operation, hot pre-compacted operation, can also not only carry out the operation of room temperature pre-compacted but also
Carry out hot pre-compacted operation.
As a preferred solution of the present invention, in room temperature pre-compacted operation, which is vacuumized, until true
Reciprocal of duty cycle is not less than -0.09bar.In the operation of room temperature pre-compacted, by guaranteeing vacuum degree, guarantees the intensity of pre-compacted, guarantee multiple
Condensation material interlayer bubble is eliminated.
As a preferred solution of the present invention, during laying, room temperature pre-compacted is carried out to first laying.In first paving
It after the completion of layer is laid with, i.e., is once compacted, can make to be bonded between laying and mold closely, to guarantee composite skirt
Surfacing.
As a preferred solution of the present invention, subsequent every several layings after carrying out room temperature pre-compacted to first laying
Carry out a room temperature pre-compacted.
As a preferred solution of the present invention, subsequent to carry out a room temperature pre-compacted every three layings.By aforesaid operations,
Room temperature pre-compacted of each three layers of progress, can while eliminating interlayer spacings, guarantee each layer all relatively evenly by
The compaction force of room temperature pre-compacted.
As a preferred solution of the present invention, in the hot pre-compacted operation, mold and laying are applied in autoclave
Vacuum, until vacuum degree is not less than -0.09bar, the size for applying pressure loading is 6.8bar-7.2bar, applies temperature loading
Size be 75 DEG C to 85 DEG C, the action time range of temperature loading is 60min-90min.In the operation of hot pre-compacted, pass through
Certain pressing force is being acted on by vacuum degree, is adding pressure loading, and auxiliary is compressed.It is multiple by applying temperature loading
Laminate resin matrix can generate a degree of softening and flowing, be conducive to eliminate the gap between composite plys, pass through
Apply vacuum, the gas between composite plys can be taken away, eliminates interlayer bubble；It, can be further by applying pressure
Compressed composite material laying allows more closely knit between composite plys.
As a preferred solution of the present invention, the composite material of every laying 8mm-12mm carries out primary hot pre-compacted operation.
As a preferred solution of the present invention, the composite material of every laying 10mm carries out primary hot pre-compacted operation.In laying
After certain thickness composite material, a hot compaction operation is carried out, layers cementing quality can either be effectively improved, and can be avoided
Hot compaction number is excessive and causes operation excessively complicated.
As a preferred solution of the present invention, it in laying step, completes to continue to spread on blank after the operation of hot pre-compacted
If remaining composite plys.
In conclusion by adopting the above-described technical solution, the beneficial effects of the present invention are:
In processing method provided by the invention, during laying, pre-compacted is carried out to composite material, can effectively be disappeared
Except the bubble of composite material interlayer, improve layers cementing quality, keeps the compacting of composite material blank even closer, so as to mention
The quality of high composite skirt.It is particularly suitable for the processing of big thickness composite skirt.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of composite skirt provided in an embodiment of the present invention and mold.
Fig. 2 is the structural schematic diagram of composite skirt provided in an embodiment of the present invention.
Fig. 3 is the structural schematic diagram of mold provided in an embodiment of the present invention.
Fig. 4 is the schematic diagram of precompression step in processing method provided by the invention.
Fig. 5 is the partial enlarged view in the portion C in Fig. 4.
Schematic diagram when Fig. 6 is the assembling envelope in processing method provided by the invention.
Fig. 7 is the partial enlarged view in the portion D in Fig. 6.
Icon: 1- composite skirt；22- die body；21- cover board；4- has hole isolation film；5- airfelt；6- vacuum bag film；7-
Non-porous release film；2- mold；8- sealing joint strip.
Specific embodiment
With reference to the accompanying drawing, the present invention is described in detail.
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that described herein, specific examples are only used to explain the present invention, not
For limiting the present invention.
Embodiment 1
Please refer to Fig. 1-7.The embodiment of the invention provides a kind of processing methods of big thickness composite skirt 1.It is this multiple
The processing method of condensation material skirt 1 the following steps are included:
S1. prepare material: composite material sheet is thawed, and carry out cutting for composite material sheet.
S2. mold 2 prepares: cleaning mold 2, release agent of constructing on mold 2.So that after processing is completed, can facilitate
Ground carries out demoulding processing.
S3. laying: laying step includes:
S31. laying scheme is designed；
S32. composite material is routed on mold 2 by laying scheme.
It is specific:
S31. it designs laying scheme: first passing through the threedimensional model that 3 d modeling software establishes composite skirt 1, then analyze
The design feature and load working condition of composite skirt 1 design laying side according to the design feature of composite skirt 1 and load working condition
Case.
In the modified part of the thickness of composite skirt 1, for example, at cone section, the length of composite plys by
Gradual change, so that the thickness of composite skirt 1 gradually changes.
The laying of composite material is carried out according to above-mentioned laying scheme, the composite skirt 1 enabled to has relatively strong
Bearing capacity, work in-process is not likely to produce deformation and warpage.
S32. composite layer is laid with by laying scheme: in the present embodiment, referring to Fig. 3, used mold 2 includes
Die body 22 and cover board 21.Cover board 21 is used to be arranged the top of die body 22, it may be assumed that mold 2 and composite material are integrally being put into heat
When pressing in tank, cover board 21 is located at the top of die body 22.The upper surface of die body 22 and cover board 21 cooperate.In step S22, laying
Height of the composite material on die body 22 is higher than the upper surface of die body 22.So that cooperating in the upper surface of cover board 21 and die body 22
When, the meeting of cover board 21 applies pressure to the upper surface of die body 22.
During laying, if there are errors for the size of composite material sheet and the size of composite skirt 1, so that compound
Material piece is dimensioned slightly smaller than size required for composite skirt 1, so that there are small between composite material sheet and mold 2
Gap, then during cured, the resin of composite material interlayer can overflow and fill the gap.
In S32, after the composite material of laying preset thickness, it is also necessary to whole to composite material and mold 2 to carry out precompressed
It is real.In the present embodiment, pre-compacted operation is room temperature pre-compacted.The room temperature pre-compacted includes following operation: by mold 2 and paving
Layer is whole to be put into vacuum bag film 6, is formed vacuum system, is vacuumized to the vacuum system.
Referring to Fig. 4, specifically, in the operation of room temperature pre-compacted, in 2 surface adhering and sealing adhesive tape 8 of mold, at this time close
Seal strip 8 is arranged in a staggered manner with composite material blank, with have hole isolation film 4 cover the composite skirt 1, on having hole isolation film 4
Airfelt 5 is placed, then with 6 mulching composite skirt 1 of vacuum bag film and Nian Jie with sealing joint strip 8, other than composite skirt 1
Vacuum quick-release connector is installed in region, forms good vacuum system after assembling envelope；Vacuum system is vacuumized, until being
Vacuum degree in system is greater than -0.90bar, by vacuumizing the pressure to be formed to each paving of 1 composite material blank of composite skirt
Layer is compacted.
It carries out a room temperature pre-compacted after first laying is laid to operate, subsequent every laying 3-layer composite material laying,
Carry out a room temperature pre-compacted operation.
S4. it assembles envelope: please referring to Fig. 6 and Fig. 7, be bonded refractory seals adhesive tape 8 on the surface of mold 2, high temperature resistant is close
Seal strip 8 is arranged in a staggered manner with composite material blank, with 7 mulching composite blank of non-porous release film, puts in non-porous release film 7
Airfelt 5 is set, finally with 6 mulching composite skirt 1 of vacuum bag film resistant to high temperature and Nian Jie with sealing joint strip 8, in composite material
Vacuum quick change tieing is installed in region other than skirt 1, after assembling envelope, forms closed good vacuum system.
S5. solidify: mold 2 and composite skirt 1 are transferred in autoclave, apply vacuum, pressure according to cure parameter
And temperature, composite skirt 1 can be solidified.
S6. it demoulds: removal vacuum bag film 6, airfelt 5, non-porous release film 7, sealing joint strip 8, then by composite skirt 1
It is removed from mold 2.
The beneficial effect of processing method provided by the invention is:
1. in processing method provided by the invention, in laying, for the first time after laying and subsequent each three layers of composite wood
Expect laying, carry out a room temperature pre-compacted operation, the bubble of composite material interlayer can be effectively eliminated, improve layers cementing matter
Amount, keeps the compacting of composite material blank even closer, so as to improve the quality of composite skirt 1, is particularly suitable for big thickness
Spend the processing of composite skirt 1；
2. in processing method provided by the invention, cover board 21 is used, and when cover board 21 is connected with die body 22, cover board 21 is right
Material applies pressure, is conducive to after the pressurizing, be kept suitable volume in material, avoids material solidification rear surface smooth.
Embodiment 2
The embodiment of the invention provides a kind of processing method of big thickness composite skirt 1, this processing method and implementation
The processing method provided in example 1 is essentially identical, and difference is: in embodiments of the present invention, in lay-up process, using hot pressing
The method of pre-compacted carries out the pre-compacted of composite skirt 1.
Specifically, the processing method of composite skirt 1 provided in an embodiment of the present invention includes:
S1. prepare material: composite material sheet is thawed, and carry out cutting for composite material sheet.
S2. mold 2 prepares: cleaning mold 2, release agent of constructing on mold 2.So that after processing is completed, can facilitate
Ground carries out demoulding processing.
S3. laying: laying step includes:
S31. laying scheme is designed；
S32. composite material is routed on mold 2 by laying scheme.
In step s 32, every preset thickness, the hot pre-compacted operation of once-combined material is carried out.The hot precompressed practical operation
Work includes: in 2 surface adhering and sealing adhesive tape 8 of mold, and sealing joint strip 8 at this time is arranged in a staggered manner with composite material blank, with there is hole
Isolation film 4 covers the composite skirt 1, and airfelt 5 is placed on having hole isolation film 4, then covers composite wood with vacuum bag film 6
Material skirt 1 is simultaneously Nian Jie with sealing joint strip 8, installs vacuum quick-release connector in composite skirt 1 with exterior domain, is formed after assembling envelope good
Good vacuum system；Vacuum system is vacuumized, until the vacuum degree in system is greater than -0.90bar, by vacuumizing shape
At pressure each laying of 1 composite material blank of composite skirt is compacted.Mold 2 and laying are integrally put into autoclave
In, apply vacuum until vacuum degree is not less than -0.09bar, the size for applying pressure loading is 7bar, and the size of temperature loading is
80℃.The action time range for maintaining temperature loading is 60min-90min.
After temperature loading action time, 60 DEG C are cooled to hereinafter, pressure loading and vacuum are then drawn off, by composite wood
Material base material and mold 2 are transferred in clean room together, and removal vacuum bag film 6, airfelt 5 have hole isolation film 4 and sealing joint strip 8
Auxiliary material continues the composite material that laying is not laid with.
S4. it assembles envelope: please referring to Fig. 6 and Fig. 7, be bonded refractory seals adhesive tape 8 on the surface of mold 2, high temperature resistant is close
Seal strip 8 is arranged in a staggered manner with composite material blank, with 7 mulching composite blank of non-porous release film, puts in non-porous release film 7
Airfelt 5 is set, finally with 6 mulching composite skirt 1 of vacuum bag film resistant to high temperature and Nian Jie with sealing joint strip 8, in composite material
Vacuum quick change tieing is installed in region other than skirt 1, after assembling envelope, forms closed good vacuum system.
S5. solidify: mold 2 and composite skirt 1 are transferred in autoclave, apply vacuum, pressure according to cure parameter
And temperature, composite skirt 1 can be solidified.
S6. it demoulds: removal vacuum bag film 6, airfelt 5, non-porous release film 7, sealing joint strip 8, then by composite skirt 1
It is removed from mold 2.
On the basis of the beneficial effect for the processing method that embodiment 1 provides, processing side's method provided in this embodiment is also
It has the advantages that
During pre-compacted, apply pre-compacted pressure by vacuumizing first, then by applying pressure loading into one
Step increases pre-compacted pressure, meanwhile, also by application temperature loading, the composite material in compacting operation is enable to soften, thus
Further increase consolidation effect.
Embodiment 3
In the processing method for present embodiments providing a kind of big thickness composite skirt 1, this processing method and embodiment 1
The processing method of offer is essentially identical, and difference is: in embodiments of the present invention, in lay-up process, using room temperature precompressed
Two methods of real and hot pressing pre-compacted carry out the pre-compacted of composite skirt 1.
Specifically, the processing method of composite skirt 1 provided in an embodiment of the present invention includes:
S1. prepare material: composite material sheet is thawed, and carry out cutting for composite material sheet.
S2. mold 2 prepares: cleaning mold 2, release agent of constructing on mold 2.So that after processing is completed, can facilitate
Ground carries out demoulding processing.
S3. laying: laying step includes:
S31. laying scheme is designed；
S32. composite material is routed on mold 2 by laying scheme.
It is specific:
S31. it designs laying scheme: first passing through the threedimensional model that 3 d modeling software establishes composite skirt 1, then analyze
The design feature and load working condition of composite skirt 1 design laying side according to the design feature of composite skirt 1 and load working condition
Case.
In the modified part of the thickness of composite skirt 1, for example, at cone section, the length of composite plys by
Gradual change, so that the thickness of composite skirt 1 gradually changes.
The laying of composite material is carried out according to above-mentioned laying scheme, the composite skirt 1 enabled to has relatively strong
Bearing capacity, work in-process is not likely to produce deformation and warpage.
S32. composite layer is laid with by laying scheme: in the present embodiment, referring to Fig. 3, used mold 2 includes
Die body 22 and cover board 21.Cover board 21 is used to be arranged the top of die body 22, it may be assumed that mold 2 and composite material are integrally being put into heat
When pressing in tank, cover board 21 is located at the top of die body 22.The upper surface of die body 22 and cover board 21 cooperate.In step S22, laying
Height of the composite material on die body 22 is higher than the upper surface of die body 22.So that cooperating in the upper surface of cover board 21 and die body 22
When, the meeting of cover board 21 applies pressure to the upper surface of die body 22.
During laying, if there are errors for the size of composite material sheet and the size of composite skirt 1, so that compound
Material piece is dimensioned slightly smaller than size required for composite skirt 1, so that there are small between composite material sheet and mold 2
Gap, then during cured, the resin of composite material interlayer can overflow and fill the gap.
In S32, a room temperature pre-compacted is carried out after the completion of laying for the first time, subsequent every laying 3-layer composite material carries out
Room temperature pre-compacted.The every increase 10mm of laying depth carries out primary hot pre-compacted.
Room temperature pre-compacted includes following operation: mold 2 and laying is integrally put into vacuum bag film 6, vacuum system is formed,
The vacuum system is vacuumized.
Specifically, in the operation of room temperature pre-compacted, in 2 surface adhering and sealing adhesive tape 8 of mold, sealing joint strip 8 at this time with
Composite material blank is arranged in a staggered manner, and with there is hole isolation film 4 to cover the composite skirt 1, places airfelt on having hole isolation film 4
5, then with 6 mulching composite skirt 1 of vacuum bag film and Nian Jie with sealing joint strip 8, composite skirt 1 with exterior domain installation very
Empty quick-release connector forms good vacuum system after assembling envelope；Vacuum system is vacuumized, until the vacuum in system
Degree is greater than -0.90bar, is compacted by vacuumizing the pressure to be formed to each laying of 1 composite material blank of composite skirt.
Hot pre-compacted operation includes: sealing joint strip 8 and composite wood material base at this time in 2 surface adhering and sealing adhesive tape 8 of mold
Material is arranged in a staggered manner, and with there is hole isolation film 4 to cover the composite skirt 1, airfelt 5 is placed on having hole isolation film 4, then with true
6 mulching composite skirt 1 of empty bag film is simultaneously Nian Jie with sealing joint strip 8, installs the fast changing-over of vacuum in composite skirt 1 with exterior domain
Head forms good vacuum system after assembling envelope；Vacuum system is vacuumized, until system in vacuum degree be greater than-
0.90bar is compacted each laying of 1 composite material blank of composite skirt by vacuumizing the pressure to be formed.By mold 2
It is integrally put into autoclave with laying, applies vacuum until vacuum degree is not less than -0.09bar, the size for applying pressure loading is
7bar, the size of temperature loading are 80 DEG C.The action time range for maintaining temperature loading is 60min-90min.
After temperature loading action time, 60 DEG C are cooled to hereinafter, pressure loading and vacuum are then drawn off, by composite wood
Material base material and mold 2 are transferred in clean room together, remove auxiliary material, continue the composite material that laying is not laid with.
S4. it assembles envelope: please referring to Fig. 6 and Fig. 7, be bonded refractory seals adhesive tape 8 on the surface of mold 2, high temperature resistant is close
Seal strip 8 is arranged in a staggered manner with composite material blank, with 7 mulching composite blank of non-porous release film, puts in non-porous release film 7
Airfelt 5 is set, finally with 6 mulching composite skirt 1 of vacuum bag film resistant to high temperature and Nian Jie with sealing joint strip 8, in composite material
Vacuum quick change tieing is installed in region other than skirt 1, after assembling envelope, forms closed good vacuum system.
S5. solidify: mold 2 and composite skirt 1 are transferred in autoclave, apply vacuum, pressure according to cure parameter
And temperature, composite skirt 1 can be solidified.
S6. it demoulds: removal vacuum bag film 6, airfelt 5, non-porous release film 7, sealing joint strip 8, then by composite skirt 1
It is removed from mold 2.
On the basis of the beneficial effect for the processing method that embodiment 1 provides, processing side's method provided in this embodiment is also
It has the advantages that
The compacting for carrying out composite material is combined by the operation of room temperature pre-compacted and the operation of hot pre-compacted, can either be guaranteed big
The Forming Quality of thickness composite skirt 1, but it is excessively complicated to can be avoided operating process.It is particularly suitable for the big thickness of 10mm or more
Spend the processing of composite skirt 1.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (10)
1. a kind of processing method of big thickness composite skirt, comprising the following steps:
Prepare material；
Mold prepares；
Laying；
Assemble envelope；
Solidification；
Demoulding；
It is characterized in that, after the composite material of laying preset thickness, integrally being carried out to composite material and mold in lay-up process
Pre-compacted.
2. processing method according to claim 1, which is characterized in that the pre-compacted includes room temperature pre-compacted and/or heat
Pre-compacted；
The room temperature pre-compacted includes following operation: mold and laying is integrally put into vacuum bag film, vacuum system is formed, it is right
The vacuum system vacuumizes；
The hot pre-compacted includes following operation: mold and laying being integrally put into autoclave, vacuum is applied, applies pressure and carries
Lotus and temperature loading.
3. processing method according to claim 2, which is characterized in that in room temperature pre-compacted operation, to the vacuum
System vacuumizes, until vacuum degree is not less than -0.09bar.
4. processing method according to claim 2 or 3, which is characterized in that during laying, carried out to first laying
Room temperature pre-compacted.
5. processing method according to claim 4, which is characterized in that after carrying out room temperature pre-compacted to first laying, after
It is continuous to carry out a room temperature pre-compacted every several layings.
6. processing method according to claim 5, which is characterized in that subsequent to carry out a room temperature precompressed every three layings
It is real.
7. processing method according to claim 2, which is characterized in that in the hot pre-compacted operation, in autoclave
Vacuum is applied to mold and laying, until vacuum degree is not less than -0.09bar, the size for applying pressure loading is 6.8bar-
7.2bar, the size for applying temperature loading is 75 DEG C to 85 DEG C, and the action time range of temperature loading is 60min-90min.
8. processing method according to claim 7, which is characterized in that the composite material of every laying 8mm-12mm carries out one
Secondary hot pre-compacted operation.
9. processing method according to claim 8, which is characterized in that the composite material of every laying 10mm carries out primary heat
Pre-compacted operation.
10. processing method according to claim 9, which is characterized in that in laying step, complete to operate in hot pre-compacted
Afterwards, continue to be laid with remaining composite plys on blank.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112123810A (en) * | 2020-07-23 | 2020-12-25 | 山西平阳重工机械有限责任公司 | Process method for improving forming quality of large-thickness composite material rudder |
| CN113290884A (en) * | 2021-04-22 | 2021-08-24 | 上海复合材料科技有限公司 | Composite material plate shell with thickness gradient area and forming device and method thereof |
| CN115302814A (en) * | 2022-10-09 | 2022-11-08 | 成都泰格尔航天航空科技股份有限公司 | Forming method of cap-shaped reinforced wall plate of high-aspect-ratio wing |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2692500A1 (en) * | 2011-03-31 | 2014-02-05 | Mitsubishi Heavy Industries, Ltd. | Molding method and molding device for composite material hollow part |
| CN103660311A (en) * | 2013-11-29 | 2014-03-26 | 北京卫星制造厂 | Integral forming method of changeable-thickness complex-structure composite connector |
| CN105643951A (en) * | 2015-09-29 | 2016-06-08 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Pre-forming method for large-thickness composite material structure |
| CN106891546A (en) * | 2017-03-31 | 2017-06-27 | 成都联科航空技术有限公司 | A kind of forming method for becoming wall thickness composite skirt |
-
2019
- 2019-03-20 CN CN201910213177.2A patent/CN109849367A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2692500A1 (en) * | 2011-03-31 | 2014-02-05 | Mitsubishi Heavy Industries, Ltd. | Molding method and molding device for composite material hollow part |
| CN103660311A (en) * | 2013-11-29 | 2014-03-26 | 北京卫星制造厂 | Integral forming method of changeable-thickness complex-structure composite connector |
| CN105643951A (en) * | 2015-09-29 | 2016-06-08 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Pre-forming method for large-thickness composite material structure |
| CN106891546A (en) * | 2017-03-31 | 2017-06-27 | 成都联科航空技术有限公司 | A kind of forming method for becoming wall thickness composite skirt |
Non-Patent Citations (1)
| Title |
|---|
| F.C.坎贝尔: "《先进复合材料的制造工艺》", 31 December 2016, 上海交通大学出版社 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112123810A (en) * | 2020-07-23 | 2020-12-25 | 山西平阳重工机械有限责任公司 | Process method for improving forming quality of large-thickness composite material rudder |
| CN112123810B (en) * | 2020-07-23 | 2022-07-19 | 山西平阳重工机械有限责任公司 | Process method for improving forming quality of large-thickness composite material rudder |
| CN113290884A (en) * | 2021-04-22 | 2021-08-24 | 上海复合材料科技有限公司 | Composite material plate shell with thickness gradient area and forming device and method thereof |
| CN115302814A (en) * | 2022-10-09 | 2022-11-08 | 成都泰格尔航天航空科技股份有限公司 | Forming method of cap-shaped reinforced wall plate of high-aspect-ratio wing |
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Application publication date: 20190607 |