CN110757830A - Thermal diaphragm forming method and preparation system of hat-shaped stringer - Google Patents
Thermal diaphragm forming method and preparation system of hat-shaped stringer Download PDFInfo
- Publication number
- CN110757830A CN110757830A CN201810835173.3A CN201810835173A CN110757830A CN 110757830 A CN110757830 A CN 110757830A CN 201810835173 A CN201810835173 A CN 201810835173A CN 110757830 A CN110757830 A CN 110757830A
- Authority
- CN
- China
- Prior art keywords
- material sheet
- thermal
- thermal diaphragm
- diaphragm
- tool
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3082—Fuselages
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention relates to the technical field of composite material forming processes, and discloses a thermal diaphragm forming method and a preparation system of a hat-shaped stringer, wherein the thermal diaphragm forming method comprises the following steps: s1, placing the material sheet and the isolating film paved at the bottom of the material sheet on a thermal diaphragm tool, and performing thermal diaphragm preforming on the material sheet; s2, placing the thermal diaphragm tool, the isolating film and the preformed material sheet on a pre-pumping process platform, and forming the preformed material sheet; s3, placing the thermal diaphragm tool, the isolating film and the formed material sheet on a curing process platform, and curing the formed material sheet; and S4, demolding the solidified web. The thermal diaphragm forming method of the hat-shaped stringer can prevent the material sheet from being adhered to the thermal diaphragm tool, the material sheet is shaped along with the thermal diaphragm tool, the material sheet can be well compacted in place, and the bridging is prevented. The preparation system of the hat-shaped stringer disclosed by the invention has the advantages that the prepared product is good in quality, and the bridging condition can not occur.
Description
Technical Field
The invention relates to the technical field of composite material forming processes, in particular to a thermal diaphragm forming method and a preparation system of a hat-shaped stringer.
Background
The composite hat stringers are the primary support structure for the composite fuselage, and the hat stringers are cured with the fuselage skin by co-bonding or co-curing. The cap stringers account for more than 90% of the total fuselage stringer count, and therefore how to efficiently and qualitatively complete the fabrication of the cap stringers becomes critical to the fabrication of composite fuselages.
The thermal diaphragm process is characterized in that under the condition of vacuumizing, fiber laying layers in a stringer plane material sheet heated to a certain temperature are driven to slide between layers by utilizing the extension of a diaphragm material, the plane material sheet is bent into a cross section of a hat-shaped stringer on a hat-shaped stringer tool, and the hat-shaped stringer thermal diaphragm process forming is completed. The heat diaphragm equipment can be used for forming a plurality of hat-shaped stringers at one time, and has high production efficiency.
However, the cross-sectional dimension of the hat-shaped stringer is small, and particularly the included angle between the hat waist and the edge strip (hereinafter referred to as the R angle of the thermal diaphragm tool) is small, so that when the existing thermal diaphragm process method is adopted, the R angle area of the stringer under the thermal diaphragm tool is seriously bridged, and cannot be compacted in place, and the curing quality of parts at the later stage is seriously influenced.
Disclosure of Invention
The invention aims to provide a thermal diaphragm forming method and a preparation system of a hat-shaped stringer, which can be compacted in place, and the phenomenon of bridging of the stringer at an R-angle area material sheet under thermal diaphragm tooling can be avoided.
In order to achieve the purpose, the invention adopts the following technical scheme:
a method of forming a thermal membrane for a hat stringer, comprising:
s1, placing the material sheet and the isolating film paved at the bottom of the material sheet on a thermal diaphragm tool, and performing thermal diaphragm preforming on the material sheet;
s2, placing the thermal diaphragm tool, the isolating film and the preformed material sheet on a pre-pumping process platform, and forming the preformed material sheet;
s3, placing the thermal diaphragm tool, the isolating film and the formed material sheet on a curing process platform, and curing the formed material sheet;
and S4, demolding the solidified web.
According to the thermal diaphragm forming method of the hat-shaped stringer, the isolating film is paved at the bottom of the material sheet, so that the material sheet cannot be adhered to the thermal diaphragm tool, the material sheet is shaped along with the thermal diaphragm tool, and the material sheet can be compacted in place through the forming treatment of the material sheet in S2, so that the bridging is prevented.
As a preferable mode of the above-described method for forming a thermal membrane of a hat stringer, the performing a thermal membrane preform on a web in S1 includes:
and covering a diaphragm on the outer side of the preformed material sheet, fixing the diaphragm on a thermal diaphragm equipment platform, heating the material sheet, and vacuumizing the thermal diaphragm equipment platform.
As a preferable example of the method for forming the thermal diaphragm of the hat stringer, a thermal diaphragm tool is placed on a thermal diaphragm equipment platform before S1, and the thermal diaphragm equipment platform is subjected to a preheating treatment.
As a preferable mode of the method for forming the thermal diaphragm of the hat stringer, the temperature of the preheating treatment is 60 ℃ to 90 ℃.
As a preferable mode of the above-mentioned method for forming a thermal diaphragm of the hat stringer, the separation film is applied to the bottom of the web at a position corresponding to the lower R-angle of the thermal diaphragm tool in S1.
As a preferable mode of the above-described method for forming a thermal membrane of a hat stringer, the step of forming a preformed web in S2 includes:
and covering a pre-extraction process cover plate above the preformed material sheet, and vacuumizing the pre-extraction process platform to enable the pre-extraction process cover plate to compact the preformed material sheet.
As a preferable mode of the above-described method for forming a thermal membrane of a hat stringer, the step of curing the formed web in S3 includes:
and vacuumizing the curing process platform, and curing through an autoclave.
As a preferable scheme of the method for forming the thermal diaphragm of the hat-shaped stringer, in S3, after the thermal diaphragm tool, the isolation film and the formed material sheet are placed on the curing process platform, the pre-extraction process cover plate on the formed material sheet is removed, the formed material sheet is covered with the curing process cover plate, and then the curing treatment is performed.
A preparation system of the hat stringer adopts the thermal diaphragm forming method of the hat stringer. The product quality that this preparation system of cap type stringer prepared is good, can not appear the condition of bridging.
The invention has the beneficial effects that:
according to the thermal diaphragm forming method for the hat-shaped stringer, the isolating film is laid at the bottom of the material sheet, so that the material sheet cannot be adhered to the thermal diaphragm tool, the material sheet is matched with the thermal diaphragm tool, the material sheet can be well compacted in place through the forming treatment of the material sheet in S2, and the bridging condition is prevented.
According to the preparation system of the hat-shaped stringer, the prepared product is good in quality, and the bridging condition cannot occur.
Drawings
FIG. 1 is a schematic diagram of a preparation for a thermal membrane forming process provided by the present invention;
FIG. 2 is a schematic illustration of a thermal diaphragm preforming process for the thermal diaphragm forming method provided by the present invention;
FIG. 3 is a schematic view of a forming process of the thermal diaphragm forming method provided by the present invention;
FIG. 4 is a schematic view of a curing process of the thermal diaphragm forming method provided by the present invention;
in the figure:
1. a thermal diaphragm device platform; 2. a thermal diaphragm tool; 3. a web; 4. an isolation film; 5. a fixed mount; 6. a heating device; 7. a diaphragm; 8. pre-pumping a process cover plate; 9. vacuum bag; 10. a vacuum nozzle; 11. a putty strip;
1', a pre-pumping process platform; 1', curing process platform; 8', and curing the process cover plate.
Detailed Description
The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings.
The embodiment provides a thermal diaphragm forming method of a hat type stringer, which comprises the following steps: fig. 1 is a schematic diagram of a thermal membrane forming process according to the present invention, as shown in fig. 1,
and S1, placing the material sheet 3 and the isolating film 4 laid at the bottom of the material sheet 3 on the thermal diaphragm tool 2, and performing thermal diaphragm preforming on the material sheet 3.
Firstly, placing a thermal diaphragm tool 2 on a thermal diaphragm equipment platform 1, and carrying out preheating treatment on the thermal diaphragm equipment platform 1, wherein the temperature of the preheating treatment is preferably 60-90 ℃. In this embodiment, the heating is performed by a heating device 6, the heating device 6 is a heating lamp, and the heating lamp is disposed right above the thermal diaphragm device platform 1.
Fig. 2 is a schematic diagram of a thermal diaphragm preforming process of the thermal diaphragm forming method provided by the invention, as shown in fig. 2, a material sheet 3 and an isolation film 4 laid on the bottom of the material sheet 3 are placed on a thermal diaphragm tool 2, a diaphragm 7 covers the outer side of the preformed material sheet 3, the diaphragm 7 is hermetically fixed on a thermal diaphragm equipment platform 1 through a fixing frame 5, a heating device 6 carries out heating treatment on the material sheet 3 according to a set program, when the heating device 6 is heated to a preset temperature, the thermal diaphragm equipment platform 1 is vacuumized, and the material sheet 3, the isolation film 4 and the diaphragm 7 realize shape following with the thermal diaphragm tool 2. In the process, due to the arrangement of the isolating film 4, the bonding between the material sheet 3 and the thermal diaphragm tool 2 is prevented, and the material sheet 3 is shaped along with the thermal diaphragm tool 2. In this embodiment, the isolation film 4 is made of a heat-resistant plastic material.
In this embodiment, the material sheet 3 is laid and cut by using an automatic tape-assisting machine and an ultrasonic cutting machine. In the embodiment, the isolation film 4 is laid on the bottom of the material sheet 3 and at the lower R-angle position of the thermal diaphragm tool 2.
And S2, placing the thermal diaphragm tool 2, the isolating film 4 and the preformed material sheet 3 on the pre-extraction process platform 1', and carrying out forming treatment on the preformed material sheet 3.
Fig. 3 is a schematic diagram of a forming process of the thermal diaphragm forming method provided by the present invention, and as shown in fig. 3, the thermal diaphragm tool 2, the isolation film 4 and the preformed material sheet 3 are removed from the thermal diaphragm equipment platform 1 and transferred to the pre-extraction process platform 1 ', the pre-extraction process cover plate 8 is covered above the preformed material sheet 3, then the vacuum bag 9 is covered outside the pre-extraction process cover plate 8 and is sealed and fixed on the pre-extraction process platform 1' through the putty strip 11, and vacuum is performed through the vacuum nozzle 10 of the vacuum bag 9 to compact the material sheet 3 through the pre-extraction process cover plate 8, so as to achieve forming of the material sheet 3.
S3, the thermal diaphragm tool 2, the separator 4, and the formed web 3 were placed on the curing stage 1 ″, and the formed web 3 was subjected to a curing treatment.
Fig. 4 is a schematic view of the curing process of the thermal diaphragm forming method according to the present invention, as shown in fig. 4, the pre-drawn process cover plate 8 on the forming web 3 is removed, and the curing process cover plate 8 ' is covered on the forming web 3, then the vacuum bag 9 is covered outside the curing process cover plate 8 ', and is sealed and fixed on the curing process platform 1 ' by the putty strip 11, vacuum is drawn through the vacuum nozzle 10 of the vacuum bag 9, and then curing is performed by the autoclave.
S4, the solidified web 3 is demolded.
The cured web 3 was demolded to obtain a cured and molded web 3.
The cap-shaped stringer is small in cross-sectional size, particularly the included angle between the cap waist and the edge strip (namely the lower R angle of the thermal diaphragm tool 2) is small, the thermal diaphragm forming method of the cap-shaped stringer can enable the material sheet 3 not to be adhered to the thermal diaphragm tool 2 by paving the isolating film 4 at the bottom of the material sheet 3, the material sheet 3 is shaped along with the thermal diaphragm tool 2, the material sheet 3 is formed in S2, the material sheet 3 can be well compacted in place, the bridging is prevented, and the curing quality of the material sheet 3 is guaranteed.
The embodiment also provides a preparation system of the hat stringer, and the hot diaphragm forming method of the hat stringer is adopted. The product quality that this preparation system of cap type stringer prepared is good, can not appear the condition of bridging.
The system for preparing hat stringers, as shown in fig. 1-4, comprises:
the device comprises a thermal diaphragm equipment platform 1, a thermal diaphragm tool 2 and a heating device 6 arranged on the thermal diaphragm equipment platform 1;
a membrane assembly comprising a membrane 7 and a support frame 5 for securing the membrane 7 to the thermal membrane device platform 1;
vacuum-pumping assembly, comprising a vacuum bag 9 and a fixing member, wherein the vacuum bag 9 is used for covering the pre-pumping process platform 1 'or the components on the curing process platform 1', the edge is fixed on the pre-pumping process platform 1 'or the curing process platform 1' by the fixing member, and a vacuum nozzle 10 is arranged on the vacuum bag 9 for connecting with the vacuum-pumping equipment. In this embodiment, the fixing member is a putty strip 11.
Further comprising: the pre-pumping process cover plate 8 and the curing process cover plate 8 ', the pre-pumping process cover plate 8 and the curing process cover plate 8 ' are matched with the shape of the thermal diaphragm tool 2, and the pre-pumping process platform 1 ' is used for compacting the material sheet 3 in the forming process; the curing process cover plate 8' serves to maintain the shape of the web 3 during the curing process.
Note that the above is only a preferred embodiment of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.
Claims (9)
1. A method of forming a thermal membrane for a hat stringer, comprising:
s1, placing the material sheet and the isolating film paved at the bottom of the material sheet on a thermal diaphragm tool, and performing thermal diaphragm preforming on the material sheet;
s2, placing the thermal diaphragm tool, the isolating film and the preformed material sheet on a pre-pumping process platform, and forming the preformed material sheet;
s3, placing the thermal diaphragm tool, the isolating film and the formed material sheet on a curing process platform, and curing the formed material sheet;
and S4, demolding the solidified web.
2. The method of claim 1, wherein the step of performing a thermo-membrane pre-form on the web in S1 comprises:
and covering a diaphragm on the outer side of the preformed material sheet, fixing the diaphragm on a thermal diaphragm equipment platform, heating the material sheet, and vacuumizing the thermal diaphragm equipment platform.
3. The method of claim 1, wherein the thermal membrane tool is placed on a thermal membrane equipment platform and the thermal membrane equipment platform is preheated before S1.
4. The method of claim 3, wherein the pre-heat treatment is performed at a temperature of 60 ℃ to 90 ℃.
5. The method of forming a thermal diaphragm for hat stringer according to any one of claims 1 to 4, wherein a release film is applied to the bottom of the web at a position corresponding to the lower R-angle of the thermal diaphragm tool in S1.
6. The method of forming a thermal membrane module of a hat stringer according to any one of claims 1 to 4, wherein the step of forming the preformed web in S2 comprises:
and covering a pre-extraction process cover plate above the preformed material sheet, and vacuumizing the pre-extraction process platform to enable the pre-extraction process cover plate to compact the preformed material sheet.
7. The method of claim 6, wherein the curing the formed web in S3 comprises:
and vacuumizing the curing process platform, and curing through an autoclave.
8. The method of claim 7, wherein the pre-drawn process cover plate is removed from the formed web and covered with the curing process cover plate, and then the curing process is performed after the thermal membrane tool, the isolation film and the formed web are placed on the curing process platform in step S3.
9. A system for making hat stringers wherein a method of forming a thermal membrane for hat stringers as claimed in any one of claims 1 to 8 is used.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810835173.3A CN110757830B (en) | 2018-07-26 | 2018-07-26 | Thermal diaphragm forming method for hat-shaped stringer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810835173.3A CN110757830B (en) | 2018-07-26 | 2018-07-26 | Thermal diaphragm forming method for hat-shaped stringer |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110757830A true CN110757830A (en) | 2020-02-07 |
| CN110757830B CN110757830B (en) | 2022-07-26 |
Family
ID=69327644
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810835173.3A Active CN110757830B (en) | 2018-07-26 | 2018-07-26 | Thermal diaphragm forming method for hat-shaped stringer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110757830B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112590240A (en) * | 2020-11-17 | 2021-04-02 | 海鹰空天材料研究院(苏州)有限责任公司 | Thermal diaphragm preforming method suitable for cap-shaped structure composite material |
| CN114986936A (en) * | 2022-06-01 | 2022-09-02 | 沈阳飞机工业（集团）有限公司 | Automatic manufacturing tool and process for composite stringer and beam structural part |
Citations (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5407610A (en) * | 1990-02-06 | 1995-04-18 | Honda Giken Kogyo Kabushiki Kaisha | Method for molding fiber-reinforced resin |
| US5648109A (en) * | 1995-05-03 | 1997-07-15 | Massachusetts Institute Of Technology | Apparatus for diaphragm forming |
| WO2009027684A1 (en) * | 2007-08-30 | 2009-03-05 | Gkn Aerospace Services Limited | Composite structure and releted method to obtain it |
| CN101484289A (en) * | 2006-07-06 | 2009-07-15 | 空中客车德国有限公司 | Method for producing a fibre composite component for aerospace |
| CN101541513A (en) * | 2006-11-20 | 2009-09-23 | 波音公司 | Apparatus and methods for forming hat stiffened composite parts using thermally expansive tooling cauls |
| JP2010221487A (en) * | 2009-03-23 | 2010-10-07 | Universal Shipbuilding Corp | Intersection structure for frp sandwich panel |
| US20110254207A1 (en) * | 2008-10-29 | 2011-10-20 | Per Hallander | Hot drape forming by means of a stiffness controlled vacuum bag |
| CN102501389A (en) * | 2011-11-15 | 2012-06-20 | 中国航空工业集团公司北京航空材料研究院 | Method for preparing composite material lamination structure through interlamination heat slip |
| CN202934814U (en) * | 2012-11-05 | 2013-05-15 | 安徽宁国优立信橡塑密封技术有限公司 | Rubber cloth diaphragm |
| US20130344291A1 (en) * | 2012-06-24 | 2013-12-26 | The Boeing Company | Composite Hat Stiffener, Composite Hat-Stiffened Pressure Webs, and Methods of Making the Same |
| US20140027048A1 (en) * | 2010-11-12 | 2014-01-30 | The Boeing Company | Method of laying up prepreg plies on contoured tools using a deformable carrier film |
| CN104395504A (en) * | 2012-07-13 | 2015-03-04 | 乌德诺拉股份公司 | Insulating frame with corner expansion joints for electrolysis cells |
| CN104441697A (en) * | 2014-11-17 | 2015-03-25 | 上海飞机制造有限公司 | Performing method of composite material C-shaped component |
| CN104441677A (en) * | 2014-09-16 | 2015-03-25 | 沈阳飞机工业（集团）有限公司 | R angle folding and molding method of large-thickness composite material workpiece |
| CN104816491A (en) * | 2015-02-04 | 2015-08-05 | 中航复合材料有限责任公司 | Preparation method for RTM preforms with angular structures |
| CN105073370A (en) * | 2013-01-18 | 2015-11-18 | 三菱重工业株式会社 | Method for producing composite material |
| CN105252786A (en) * | 2015-10-14 | 2016-01-20 | 哈尔滨飞机工业集团有限责任公司 | Method for preventing collapse of honeycombs of sandwich parts |
| US20160214329A1 (en) * | 2013-09-10 | 2016-07-28 | Bombardier Inc. | Method of forming a composite member and assembly therefor |
| CN106142587A (en) * | 2016-07-27 | 2016-11-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The double bag hot barrier film preformation method of a kind of composite |
| US20170072647A1 (en) * | 2014-04-16 | 2017-03-16 | Hexcel Reinforcements Sas | Method of manufacturing a composite part |
| CN106799851A (en) * | 2016-12-27 | 2017-06-06 | 中国商用飞机有限责任公司 | The moulding manufacture method of the composite hat Material Stiffened Panel based on piddler technology |
| US20170197370A1 (en) * | 2016-01-07 | 2017-07-13 | The Boeing Company | Edge breathers for composite products |
| CN107214976A (en) * | 2017-07-07 | 2017-09-29 | 沈阳斯塔娜航空科技有限公司 | A kind of moulding process for the composite for substituting autoclave |
| CN107253334A (en) * | 2017-04-28 | 2017-10-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The mould and technique of a kind of forming composite T-shaped stringer Material Stiffened Panel |
-
2018
- 2018-07-26 CN CN201810835173.3A patent/CN110757830B/en active Active
Patent Citations (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5407610A (en) * | 1990-02-06 | 1995-04-18 | Honda Giken Kogyo Kabushiki Kaisha | Method for molding fiber-reinforced resin |
| US5648109A (en) * | 1995-05-03 | 1997-07-15 | Massachusetts Institute Of Technology | Apparatus for diaphragm forming |
| CN101484289A (en) * | 2006-07-06 | 2009-07-15 | 空中客车德国有限公司 | Method for producing a fibre composite component for aerospace |
| CN101541513A (en) * | 2006-11-20 | 2009-09-23 | 波音公司 | Apparatus and methods for forming hat stiffened composite parts using thermally expansive tooling cauls |
| WO2009027684A1 (en) * | 2007-08-30 | 2009-03-05 | Gkn Aerospace Services Limited | Composite structure and releted method to obtain it |
| US20110254207A1 (en) * | 2008-10-29 | 2011-10-20 | Per Hallander | Hot drape forming by means of a stiffness controlled vacuum bag |
| JP2010221487A (en) * | 2009-03-23 | 2010-10-07 | Universal Shipbuilding Corp | Intersection structure for frp sandwich panel |
| US20140027048A1 (en) * | 2010-11-12 | 2014-01-30 | The Boeing Company | Method of laying up prepreg plies on contoured tools using a deformable carrier film |
| CN102501389A (en) * | 2011-11-15 | 2012-06-20 | 中国航空工业集团公司北京航空材料研究院 | Method for preparing composite material lamination structure through interlamination heat slip |
| US20130344291A1 (en) * | 2012-06-24 | 2013-12-26 | The Boeing Company | Composite Hat Stiffener, Composite Hat-Stiffened Pressure Webs, and Methods of Making the Same |
| CN104395504A (en) * | 2012-07-13 | 2015-03-04 | 乌德诺拉股份公司 | Insulating frame with corner expansion joints for electrolysis cells |
| CN202934814U (en) * | 2012-11-05 | 2013-05-15 | 安徽宁国优立信橡塑密封技术有限公司 | Rubber cloth diaphragm |
| CN105073370A (en) * | 2013-01-18 | 2015-11-18 | 三菱重工业株式会社 | Method for producing composite material |
| US20160214329A1 (en) * | 2013-09-10 | 2016-07-28 | Bombardier Inc. | Method of forming a composite member and assembly therefor |
| US20170072647A1 (en) * | 2014-04-16 | 2017-03-16 | Hexcel Reinforcements Sas | Method of manufacturing a composite part |
| CN104441677A (en) * | 2014-09-16 | 2015-03-25 | 沈阳飞机工业（集团）有限公司 | R angle folding and molding method of large-thickness composite material workpiece |
| CN104441697A (en) * | 2014-11-17 | 2015-03-25 | 上海飞机制造有限公司 | Performing method of composite material C-shaped component |
| CN104816491A (en) * | 2015-02-04 | 2015-08-05 | 中航复合材料有限责任公司 | Preparation method for RTM preforms with angular structures |
| CN105252786A (en) * | 2015-10-14 | 2016-01-20 | 哈尔滨飞机工业集团有限责任公司 | Method for preventing collapse of honeycombs of sandwich parts |
| US20170197370A1 (en) * | 2016-01-07 | 2017-07-13 | The Boeing Company | Edge breathers for composite products |
| CN106142587A (en) * | 2016-07-27 | 2016-11-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The double bag hot barrier film preformation method of a kind of composite |
| CN106799851A (en) * | 2016-12-27 | 2017-06-06 | 中国商用飞机有限责任公司 | The moulding manufacture method of the composite hat Material Stiffened Panel based on piddler technology |
| CN107253334A (en) * | 2017-04-28 | 2017-10-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The mould and technique of a kind of forming composite T-shaped stringer Material Stiffened Panel |
| CN107214976A (en) * | 2017-07-07 | 2017-09-29 | 沈阳斯塔娜航空科技有限公司 | A kind of moulding process for the composite for substituting autoclave |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112590240A (en) * | 2020-11-17 | 2021-04-02 | 海鹰空天材料研究院(苏州)有限责任公司 | Thermal diaphragm preforming method suitable for cap-shaped structure composite material |
| CN112590240B (en) * | 2020-11-17 | 2022-07-22 | 海鹰空天材料研究院(苏州)有限责任公司 | Thermal diaphragm preforming method suitable for cap-shaped structure composite material |
| CN114986936A (en) * | 2022-06-01 | 2022-09-02 | 沈阳飞机工业（集团）有限公司 | Automatic manufacturing tool and process for composite stringer and beam structural part |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110757830B (en) | 2022-07-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108407335B (en) | Integral forming method for cap-shaped reinforced wall plate made of composite material | |
| CN110815875B (en) | Forming method of composite material honeycomb sandwich structure part | |
| CN106863874B (en) | A kind of honeycomb method for shaping of complex-curved honeycomb sandwich construction | |
| CN113681937B (en) | Composite material cap-shaped stringer wallboard structure and preparation method | |
| CN110757830B (en) | Thermal diaphragm forming method for hat-shaped stringer | |
| CN105172164B (en) | A kind of frock and manufacture method for manufacturing variable cross-section class drum composite product | |
| CN107415280B (en) | Mold and method for preforming and/or positioning T-stringers with wall panels | |
| US9050757B1 (en) | System and method for curing composites | |
| CN110356018A (en) | A kind of unmanned plane integrated machine head-shield co-curing manufacture mold and process | |
| CN116394545B (en) | Leading edge skin forming method and leading edge skin | |
| CN108943766A (en) | Co-bonding forming process for T-shaped reinforced wall plate made of composite material | |
| CN216636802U (en) | Hat type stringer wallboard, preforming frock structure and co-curing packaging structure | |
| JP6384213B2 (en) | Composite material manufacturing method and composite material manufacturing apparatus | |
| CN110091521A (en) | A kind of forming method and composite element of composite element | |
| CN112829161B (en) | Foaming glue filling method for composite material honeycomb sandwich structure | |
| CN112757663A (en) | Automatic filament-laying forming method for continuous fiber reinforced thermoplastic composite material | |
| CN112606426B (en) | Curing furnace forming process for full-length composite wing beam | |
| CN207594159U (en) | A kind of mold for manufacturing glass fibre three-way pipeline | |
| CN110089784A (en) | A kind of underwear mold cup production method and its producing device | |
| CN109228400A (en) | The moulding process of sandwich structure carbon fibre composite stringer | |
| CN112848368B (en) | Thermal diaphragm preforming method | |
| CN109605780B (en) | Method for integrally forming composite material structure of unmanned aerial vehicle | |
| CN113644151B (en) | Photovoltaic module and method for manufacturing same | |
| CN109435273A (en) | A kind of Varying-thickness composite material skeleton and covering adhering method and adhesive mould | |
| US11794420B2 (en) | Advanced single vacuum bag process and assembly for polymer composite manufacturing and repair |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |