CN104385626A - Composite material thin-wall housing preparation method based on intermittent stacking - Google Patents
Composite material thin-wall housing preparation method based on intermittent stacking Download PDFInfo
- Publication number
- CN104385626A CN104385626A CN201410522000.8A CN201410522000A CN104385626A CN 104385626 A CN104385626 A CN 104385626A CN 201410522000 A CN201410522000 A CN 201410522000A CN 104385626 A CN104385626 A CN 104385626A
- Authority
- CN
- China
- Prior art keywords
- layer
- laying
- composite material
- thin
- polytetrafluoroethylene
- 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
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
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/386—Automated tape laying [ATL]
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Robotics (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention relates to a composite material thin-wall housing preparation method based on intermittent stacking, and belongs to the technical field of composite material structure design and composite material processing technology. A composite material thin-wall housing prepared by using the preparation method is small in deformation, and has the maximum deformation of 0.5 mm or less under the room temperature condition, and the maximum deformation not exceeding 0.5 mm is of great importance to guarantee surface obstruction ratio, modulation transfer function (MTF) and veiling glare index of a space remote sensing system. The composite material thin-wall housing is simple in structural form, tedious structures such as ribs and the like are saved, and also structure weight is mitigated. The composite material thin-wall housing is high in technology maturity, simple in tools and molds, relatively good in adaptability to curing equipment and short in production period.
Description
Technical field
The present invention relates to a kind of preparation method of the composite material thin wall housing based on interruption laying, belong to composite structure design and composite processing technology field.
Background technology
Advanced composite material has that quality is light, specific strength and the advantage such as specific modulus is high, endurance, damping characteristics are good, performance can design, and just progressively substitutes the critical material that original metal material becomes Space Remote Sensors structure.From technical maturity and practical ranges, take high-performance fiber as the preferred material that the polymer matrix composites of reinforcement have become Space Remote Sensors structure, and carbon fibre composite (CFRP), aramid fiber reinforced composite (AFRP) occupy leading position wherein.
Some Space Remote Sensors parts, such as, inner cover etc. on primary mirror or secondary mirror, usually adopt thin-wall case structure, wall thickness is generally not more than 1mm, and even thinner only have 0.3mm.The same with conventional composites materials structure, also there is problem on deformation after this type component curing molding, and it is often relevant to laying rigidity, plate length-width ratio, thickness of slab, boundary condition etc. to be out of shape size.Even if after the press cure of common symmetric layups is shaping, also there will be certain distortion, this may be because the reason such as difference of the slippage of the difference of fiber and matrix, thermograde, laying error and solidification process, composite and mold materials causes.The general more complicated of problem on deformation of composite, in practical engineering application, often adopts increase muscle or rib to improve the method for rigidity Reducing distortion.But for Space Remote Sensors structure, muscle or rib not only increase weight, also can the face the ratio of obstruction, modulation transfer function (MTF), coefficient of stray light etc. of influential system.
There is moderate finite deformation in the cover body 2 in prior art after curing molding, the trend that the arc transition position of quadrangle has curvature to diminish, and causes the planar section between connection two circular arcs to deform, maximum distortion △ δ close to 5mm, as shown in Figure 3;
End and the reinforcement 3 of cover body 2 adopt adhesive bonding integral after, Leading Edge Deformation makes moderate progress, but is out of shape still comparatively large in the middle part of cover body 2, cannot meet the instructions for use of camera subsystem.
Summary of the invention
The object of the invention is for the yielding problem of Space Remote Sensors fiber-reinforced resin matrix compound material thin-wall case, a kind of interruption laying method is proposed, fiber-reinforced resin matrix compound material thin-wall case prepared by the method is not yielding, the face the ratio of obstruction of Space Remote Sensors, modulation transfer function (MTF) and coefficient of stray light can be ensured, structural design and moulding process can be simplified simultaneously.
The object of the invention is to be achieved through the following technical solutions.
The preparation method of a kind of composite material thin wall housing based on interruption laying of the present invention, this thin-wall case is a tunnel like structure, and this tunnel like structure vertically any one cross section is quadrangle, and four angles of quadrangle all adopt arc transition;
Thin-wall case adopts fiber-reinforced resin matrix compound material laminar structure, and amount to n layer, n >=2, n is natural number; The reinforcing material of thin-wall case is aramid fiber, carbon fiber or glass fibre;
The method is for being interrupted laying method, and step is:
The first step, Mould design and manufacturing
The mould of design and manufaction thin-wall case, mould adopts metal material, and mold surface shape is consistent with housing; Before using, at external coating one deck releasing agent of mould, releasing agent tolerable temperature is generally not less than 140 DEG C, and dries.
Second step, prepared by prepreg
Prepreg needed for preparation, prepreg can adopt the form of fabric or one-way tape; Particular type according to resin matrix carries out the process of prepreg B rankization, and namely heating makes resin softening but incomplete fusion, has certain viscosity, is convenient to the laying of operation below.
3rd step, prepreg cutting
Profile cutting prepreg after launching according to thin-wall case.
4th step, laying
According to order from inside to outside, interior one deck is designated as ground floor, be followed successively by the second layer, third layer ... kth layer ... n-th layer; Ground floor to kth layer is complete laying, and (k+1) layer disconnects 5 ~ 10mm at the arc transition position of quadrangle, and (k+2) disconnects every side, position uninterrupted length along last layer and increase 5 ~ 10mm again, and rule is until n-th layer according to this; K≤n/2.
According to order from outside to inside, outermost one deck is designated as ground floor, be followed successively by the second layer, third layer ... kth layer ... n-th layer; Ground floor to kth layer is complete laying, and (k+1) layer disconnects 5 ~ 10mm at the arc transition position of quadrangle, and (k+2) layer disconnects every side, position uninterrupted length along last layer and increases 5 ~ 10mm again, and rule is until n-th layer according to this; K≤n/2.
After every laying one deck prepreg, paving covers one deck polytetrafluoroethylene film, then progressively rolls with rubber rollers and electric iron, makes densification between layers but corrugationless.
5th step, solidification
Repair the flash cutting lay-up process, clean the glue of die surface.
Paving is covered polytetrafluoroethylene (PTFE) barrier film, is inhaled glue-line, polytetrafluoroethylene (PTFE) barrier film, the equal pressing plate of technique and airfelt, adhesive seal adhesive tape encapsulated vacuum nylon film successively.Vacuum bag-autoclave method or vacuum bag-Oven Method is adopted to complete solidification.Curing process is determined according to the particular type of resin matrix, the material of mould, the size of goods and thickness, and should be cooled to less than 60 DEG C after shutdown can come out of the stove.
6th step, the demoulding and finishing
Remove vacuum nylon film, airfelt, the equal pressing plate of technique, polytetrafluoroethylene (PTFE) barrier film, inhale glue-line and polytetrafluoroethylene (PTFE) barrier film, goods are deviate from from mould.
Repair and cut flash and burr.
7th step, detects deflection
Slide measure, straight edge ruler and light face feeler gauge is adopted to detect the deflection of goods.
Beneficial effect
(1) composite material thin wall housing distortion of the present invention is little, and maximum distortion is no more than 0.5mm at ambient temperature, and this is to guaranteeing that the face the ratio of obstruction of space remote sensing system, modulation transfer function (MTF) and coefficient of stray light are most important.
(2) composite material thin wall shell structure form of the present invention is simple, eliminates the loaded down with trivial details structure such as muscle or rib, also mitigates construction weight.
(3) composite material thin wall housing technical maturity of the present invention is high, and moulds of industrial equipment are simple, better to curing apparatus applicability, with short production cycle.
Accompanying drawing explanation
Fig. 1 is the structural representation of Space Remote Sensors inner cover in prior art;
Fig. 2 is the structural representation of cover body in Fig. 1;
Fig. 3 is the distortion schematic diagram of cover body in Fig. 1;
Fig. 4 is the structural representation of thin-wall case of the present invention;
Fig. 5 is laying schematic diagram from inside to outside;
Fig. 6 is laying schematic diagram from outside to inside.
Detailed description of the invention
Below in conjunction with drawings and Examples, the invention will be further described.
Comparative example
Panchromatic multispectral quick camera primary mirror inner cover (hereinafter referred to as inner cover) is thin-wall construction, is made up of, as shown in Figure 1 light barrier 1, cover body 2 and reinforcement 3;
Wherein cover body 2 comprises a regular tunnel like structure and irregular tunnel like structure two parts, and any one cross section is quadrangle vertically, and four angles of quadrangle all adopt arc transition; The theoretical wall thickness 0.3mm of cover body 2; The surface of rule tunnel like structure has
group hole and width are 0.5mm groove, and end and the light barrier 1 of regular tunnel like structure adopt adhesive bonding integral; End and the reinforcement 3 of irregular tunnel like structure adopt adhesive bonding integral, as shown in Figure 2;
Embodiment 1
Cover body 2 adopts and is interrupted laying method, enormously simplify the version of inner cover, effectively controls its maximum distortion, save the reinforcement 3 of cover body 2 far-end simultaneously.Without the cover body 2 of reinforcement 3 structural representation as shown in Figure 4.
The first step, manufactures and designs the mould of cover body 2, and mould is formpiston, and mould adopts metal material, and die boundary dimensions is consistent with the inner chamber of cover body 2; Before using, at mold working surface brushing one deck fluorocarbons releasing agent, and dry; Fluorocarbons releasing agent can be not less than other releasing agents replacement of 140 DEG C with tolerable temperature; If desired, can by mold heated to 50 ~ 60 DEG C.
Second step, prepare the Kevlar49/8D-1 plain cloth prepreg of nominal thickness 0.1mm, prepreg resin content controls 42 ± 5%, and volatile content requires to be not more than 3%.
3rd step, the theoretical profile cutting prepreg after launching according to cover body 2.
4th step, cover body 2 adopts three layers of Kevlar49-120 type plain cloth prepreg laying to form; According to order from inside to outside, as shown in Figure 5, employing interruption laying implementation method is:
1) interior one deck is complete laying, and overlapping mode is taked at splicing position, and lap width is 5mm;
2) in the middle of, one deck disconnects 10mm at the arc transition position of quadrangle;
3) outermost one deck the arc transition position of quadrangle disconnect 30mm, fracture and middle one deck fracture symmetrical;
4) according to order from inside to outside on mould after laying, surface paving covers one deck polytetrafluoroethylene film, then progressively rolls with rubber rollers and electric iron, makes densification between layers but corrugationless.
5th step, paving is covered polytetrafluoroethylene (PTFE) barrier film, is inhaled glue-line, polytetrafluoroethylene (PTFE) barrier film, the equal pressing plate of technique, airfelt, adhesive seal adhesive tape encapsulated vacuum nylon film successively.Vacuum bag-autoclave method or vacuum bag-Oven Method is adopted to complete solidification.Curing process in the present embodiment is: evacuated pressure is not more than-0.094MPa, be warming up to 70 ± 3 DEG C to keep adding after 0.5 hour being depressed into 0.2MPa outward, continue to be warming up to 120 ± 3 DEG C to add and be depressed into 0.4MPa outward, continue to be warming up to 140 ± 3 DEG C and keep shutdown after 3 hours, be down to after below 60 DEG C until temperature and go out tank.
Goods are deviate from from mould small end by the 6th step, repair and cut flash and burr.
7th step, adopts slide measure, straight edge ruler and light face feeler gauge to detect the deflection of goods, and the extreme value of its distortion △ δ is 0.5mm.
Embodiment 2
Cover body 2 adopts and is interrupted laying method, enormously simplify the version of inner cover, effectively controls its maximum distortion, save the reinforcement 3 of cover body 2 far-end simultaneously.Without the cover body 2 of reinforcement 3 structural representation as shown in Figure 4.
The first step, manufactures and designs the mould of cover body 2, and mould is former, and mould adopts metal material, and dies cavity shape is consistent with the outer surface of size and cover body 2; Before using, at mold working surface brushing one deck fluorocarbons releasing agent, and dry; Fluorocarbons releasing agent can be not less than other releasing agents replacement of 140 DEG C with tolerable temperature; If desired, can by mold heated to 50 ~ 60 DEG C.
Second step, prepare the Kevlar49/8D-1 plain cloth prepreg of nominal thickness 0.1mm, prepreg resin content controls 42 ± 5%, and volatile content requires to be not more than 3%.
3rd step, the theoretical profile cutting prepreg after launching according to cover body 2.
4th step, cover body 2 adopts three layers of Kevlar49-120 type plain cloth prepreg laying to form; According to order from outside to inside, as shown in Figure 6, employing interruption laying implementation method is:
1) outermost one deck is complete laying, and overlapping mode is taked at splicing position, and lap width is 5mm;
2) in the middle of, one deck disconnects 10mm at the arc transition position of quadrangle;
3) interior one deck the arc transition position of quadrangle disconnect 30mm, fracture and middle one deck fracture symmetrical;
4), cover one deck polytetrafluoroethylene film inner surface paving, then progressively roll with rubber rollers and electric iron after laying according to order from outside to inside on mould, make densification between layers but corrugationless.
5th step, paving is covered polytetrafluoroethylene (PTFE) barrier film, is inhaled glue-line, polytetrafluoroethylene (PTFE) barrier film, the equal pressing plate of technique, airfelt, adhesive seal adhesive tape encapsulated vacuum nylon film successively.Vacuum bag-autoclave method or vacuum bag-Oven Method is adopted to complete solidification.Curing process in the present embodiment is: evacuated pressure is not more than-0.094MPa, be warming up to 70 ± 3 DEG C to keep adding after 0.5 hour being depressed into 0.2MPa outward, continue to be warming up to 120 ± 3 DEG C to add and be depressed into 0.4MPa outward, continue to be warming up to 140 ± 3 DEG C and keep shutdown after 3 hours, be down to after below 60 DEG C until temperature and go out tank.
Goods are deviate from from the large end of mould, are repaiied and cut flash and burr by the 6th step.
7th step, adopts slide measure, straight edge ruler and light face feeler gauge to detect the deflection of goods, and the extreme value of its distortion △ δ is 0.5mm.
Claims (7)
1., based on a preparation method for the composite material thin wall housing of interruption laying, it is characterized in that step is:
The first step, manufactures the mould of thin-wall case;
Second step, prepares prepreg;
3rd step, the profile cutting prepreg after launching according to thin-wall case;
4th step, the prepreg on mould prepared by the first step after the reduction of laying the 3rd step;
Carry out laying according to order from inside to outside, interior one deck is designated as ground floor, be followed successively by the second layer, third layer ... kth layer ... n-th layer; Ground floor to kth layer is complete laying, and (k+1) layer disconnects 5 ~ 10mm at the arc transition position of quadrangle, and (k+2) disconnects every side, position uninterrupted length along last layer and increase 5 ~ 10mm again, and rule is until n-th layer according to this; K≤n/2; N is the lamination number of plies of thin-wall case, n >=2, and n is natural number;
After every laying one deck prepreg, paving covers one deck polytetrafluoroethylene film, then progressively rolls with rubber rollers and electric iron;
5th step, paving is covered polytetrafluoroethylene (PTFE) barrier film, is inhaled glue-line, polytetrafluoroethylene (PTFE) barrier film, the equal pressing plate of technique and airfelt, adhesive seal adhesive tape encapsulated vacuum nylon film successively; Vacuum bag-autoclave method or vacuum bag-Oven Method is adopted to complete solidification;
6th step, removes vacuum nylon film, airfelt, the equal pressing plate of technique, polytetrafluoroethylene (PTFE) barrier film, inhales glue-line and polytetrafluoroethylene (PTFE) barrier film, deviate from by goods from mould.
2., based on a preparation method for the composite material thin wall housing of interruption laying, it is characterized in that step is:
The first step, manufactures the mould of thin-wall case;
Second step, prepares prepreg;
3rd step, the profile cutting prepreg after launching according to thin-wall case;
4th step, the prepreg on mould prepared by the first step after the reduction of laying the 3rd step;
According to order from outside to inside, outermost one deck is designated as ground floor, be followed successively by the second layer, third layer ... kth layer ... n-th layer; Ground floor to kth layer is complete laying, and (k+1) layer disconnects 5 ~ 10mm at the arc transition position of quadrangle, and (k+2) layer disconnects every side, position uninterrupted length along last layer and increases 5 ~ 10mm again, and rule is until n-th layer according to this; K≤n/2; N is the lamination number of plies of thin-wall case, n >=2, and n is natural number;
After every laying one deck prepreg, paving covers one deck polytetrafluoroethylene film, then progressively rolls with rubber rollers and electric iron;
5th step, paving is covered polytetrafluoroethylene (PTFE) barrier film, is inhaled glue-line, polytetrafluoroethylene (PTFE) barrier film, the equal pressing plate of technique and airfelt, adhesive seal adhesive tape encapsulated vacuum nylon film successively; Vacuum bag-autoclave method or vacuum bag-Oven Method is adopted to complete solidification;
6th step, removes vacuum nylon film, airfelt, the equal pressing plate of technique, polytetrafluoroethylene (PTFE) barrier film, inhales glue-line and polytetrafluoroethylene (PTFE) barrier film, deviate from by goods from mould.
3. the preparation method of a kind of composite material thin wall housing based on interruption laying according to claim 1 and 2, it is characterized in that: this thin-wall case is a tunnel like structure, this tunnel like structure vertically any one cross section is quadrangle, and four angles of quadrangle all adopt arc transition.
4. the preparation method of a kind of composite material thin wall housing based on interruption laying according to claim 1 and 2, is characterized in that: thin-wall case adopts fiber-reinforced resin matrix compound material laminar structure.
5. the preparation method of a kind of composite material thin wall housing based on interruption laying according to claim 1 and 2, is characterized in that: the reinforcing material of thin-wall case is aramid fiber, carbon fiber or glass fibre.
6. the preparation method of a kind of composite material thin wall housing based on interruption laying according to claim 1 and 2, it is characterized in that: the first step, prepare the external coating one deck releasing agent at mould after mould, releasing agent tolerable temperature is not less than 140 DEG C, and dries.
7. the preparation method of a kind of composite material thin wall housing based on interruption laying according to claim 1 and 2, is characterized in that: prepreg adopts the form of fabric or one-way tape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410522000.8A CN104385626B (en) | 2014-09-30 | 2014-09-30 | Preparation method based on the composite material thin wall housing being interrupted laying |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410522000.8A CN104385626B (en) | 2014-09-30 | 2014-09-30 | Preparation method based on the composite material thin wall housing being interrupted laying |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104385626A true CN104385626A (en) | 2015-03-04 |
| CN104385626B CN104385626B (en) | 2016-07-27 |
Family
ID=52603624
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410522000.8A Active CN104385626B (en) | 2014-09-30 | 2014-09-30 | Preparation method based on the composite material thin wall housing being interrupted laying |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104385626B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110625963A (en) * | 2019-09-17 | 2019-12-31 | 成都飞机工业（集团）有限责任公司 | Manufacturing method of composite material component with variable thickness and corner characteristics |
| CN110948909A (en) * | 2019-12-11 | 2020-04-03 | 江苏新扬新材料股份有限公司 | Forming method of square equal-section large-size composite material box |
| CN111483156A (en) * | 2020-04-08 | 2020-08-04 | 北京航天新风机械设备有限责任公司 | Large thin-wall reinforced half-cover layering method for composite material |
| CN114800601A (en) * | 2022-04-06 | 2022-07-29 | 北京长空动力科技有限公司 | Flexible and resilient movable joint and manufacturing method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1547756A1 (en) * | 2003-12-24 | 2005-06-29 | Airbus UK Limited | Method of manufacturing aircraft components |
| CN101254652A (en) * | 2007-12-28 | 2008-09-03 | 西安交通大学 | In-situ consolidation fibre laying method and device for producing resin-based compound material component |
| CN102092135A (en) * | 2010-12-13 | 2011-06-15 | 中国航空工业集团公司北京航空材料研究院 | Method for improving rigidity of wing surface structure of composite material |
| CN102729486A (en) * | 2012-06-05 | 2012-10-17 | 东华大学 | Preparation method of thermoplastic resin/corn husk composite material |
-
2014
- 2014-09-30 CN CN201410522000.8A patent/CN104385626B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1547756A1 (en) * | 2003-12-24 | 2005-06-29 | Airbus UK Limited | Method of manufacturing aircraft components |
| CN101254652A (en) * | 2007-12-28 | 2008-09-03 | 西安交通大学 | In-situ consolidation fibre laying method and device for producing resin-based compound material component |
| CN102092135A (en) * | 2010-12-13 | 2011-06-15 | 中国航空工业集团公司北京航空材料研究院 | Method for improving rigidity of wing surface structure of composite material |
| CN102729486A (en) * | 2012-06-05 | 2012-10-17 | 东华大学 | Preparation method of thermoplastic resin/corn husk composite material |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110625963A (en) * | 2019-09-17 | 2019-12-31 | 成都飞机工业（集团）有限责任公司 | Manufacturing method of composite material component with variable thickness and corner characteristics |
| CN110948909A (en) * | 2019-12-11 | 2020-04-03 | 江苏新扬新材料股份有限公司 | Forming method of square equal-section large-size composite material box |
| CN110948909B (en) * | 2019-12-11 | 2021-03-16 | 江苏新扬新材料股份有限公司 | Forming method of square equal-section large-size composite material box |
| CN111483156A (en) * | 2020-04-08 | 2020-08-04 | 北京航天新风机械设备有限责任公司 | Large thin-wall reinforced half-cover layering method for composite material |
| CN114800601A (en) * | 2022-04-06 | 2022-07-29 | 北京长空动力科技有限公司 | Flexible and resilient movable joint and manufacturing method thereof |
| CN114800601B (en) * | 2022-04-06 | 2024-04-19 | 北京长空动力科技有限公司 | Flexible resilient movable joint and manufacturing method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104385626B (en) | 2016-07-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9073270B2 (en) | Method of manufacturing a wind turbine blade by embedding a layer of pre-cured fibre reinforced resin | |
| CN104385626B (en) | Preparation method based on the composite material thin wall housing being interrupted laying | |
| CN105034403B (en) | Method for manufacturing composite shell | |
| CN105128355A (en) | Auxiliary integral forming method for composite material bearing cylinder soft mould with light baffle ring | |
| US9782958B2 (en) | Method and device for manufacturing composite material parts | |
| CN104162996B (en) | The manufacturing process of the U-shaped part of carbon fibre composite | |
| CN104385624B (en) | Forming method for composite material barrel shell employing horizontal installation | |
| US20150174844A1 (en) | Three-dimensional reuseable curing caul for use in curing integrated composite components and methods of making the same | |
| CN106313378B (en) | A kind of fiber reinforcement " cap " type rib molding soft mode method of preparation and use | |
| JP6785866B2 (en) | Composite material molding method and composite material molding jig | |
| JP2007118598A (en) | Method and apparatus for manufacturing preform | |
| CN106273539A (en) | A kind of shape for hat Material Stiffened Panel co-curing moulding technique | |
| EP2969496A2 (en) | System and method for maneuvering thin ply technology complexes | |
| CN104385625A (en) | Composite material thin-wall housing preparation method based on unloading hole | |
| JP2009274248A (en) | Method for manufacturing frp | |
| CN109591319A (en) | Contain casing moulding process and its manufactured outer culvert casing outside a kind of new engine | |
| KR101447136B1 (en) | Method for Forming Fiber Reinforced Plastic Composite | |
| CN110588020A (en) | Automatic tape laying method for hexagonal hole of composite material | |
| CN107553933A (en) | A kind of antarafacial π types carbon fibre composite joint forming method | |
| CN110481058B (en) | Method for forming light cable cover embedded in winding shell | |
| CN107696522A (en) | A kind of carbon fibre fabric method for forming parts at band R angles | |
| CN110948909B (en) | Forming method of square equal-section large-size composite material box | |
| EP3124220A1 (en) | A method of moulding a composite article and mould | |
| US11110671B2 (en) | Layup support configured to provide support for laying up composite material | |
| CN103802329A (en) | Integrated forming method for large-length-diameter-ratio composite tubular member |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20180416 Address after: 102628, 7, Haixin Road, Huangcun Town, Beijing, Daxing District Patentee after: Beijing Aerospace Hezhong Technology Development Co., Ltd. Address before: 100076 Beijing, Fengtai District, South Road, No. 9201, box office, box 1, 5 Patentee before: Beijing Research Institute of Space Mechanical & Electrical Technology |
|
| TR01 | Transfer of patent right |