CN107160709B - A kind of method and rudder face of composite liquid molding ultra light aircraft rudder face - Google Patents
A kind of method and rudder face of composite liquid molding ultra light aircraft rudder face Download PDFInfo
- Publication number
- CN107160709B CN107160709B CN201710518650.9A CN201710518650A CN107160709B CN 107160709 B CN107160709 B CN 107160709B CN 201710518650 A CN201710518650 A CN 201710518650A CN 107160709 B CN107160709 B CN 107160709B
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- web
- edge strip
- covering
- rudder face
- lower edge
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Classifications
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- 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
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention belongs to composite material process planning technical fields, specially a kind of method of composite liquid molding ultra light aircraft rudder face, make the upper of beam, lower edge strip, the components such as web, after being vacuumized curing molding, it is put into the structure that aluminium sheet carries out laying composition beam, by carrying out secondary vacuumizing importing resin to it, solidify demoulding and obtains the structure of beam, it remanufactures, after lower covering, it is assembled with beam, the hollow part of upper and lower covering is supported with fine sand or inflation when assembling, fine sand or inflation will be discharged after bonding after curing molding, based on this process, the present invention also provides a kind of ultra light aircraft rudder faces simultaneously.Advantage is: being penetrated into web and lower edge strip by resin and completes injecting glue, the vacuum for solving complicated 3D shape imports.Make inner stuffing with sack package fine sand, not only ensure that the bonding quality of covering at high temperature under high pressure, but also solve the problems, such as the taking-up of filler in hollow covering, residue is not present.
Description
Technical field:
The invention belongs to aerospace composite material process planning technical fields, and in particular to a kind of composite liquid at
The method of type ultra light aircraft rudder face, and a kind of ultra light aircraft rudder face is additionally provided based on the method.
Background technique:
Advanced composite material has the superiority such as the identity of high specific strength, high ratio modulus, endurance, material and structure
Can, since the sixties in last century, advanced composite material is widely applied quickly, become one of big material of aerospace four,
The moulding process of composite material is varied.Vehicle rudder structure generally comprises the structures such as covering, lower covering and beam, internal
Structure is complex, particularly with complicated 3D shape, such as web and lower edge strip part, curing molding it is more troublesome.
Summary of the invention:
In consideration of it, the present invention provides a kind of method of composite liquid molding ultra light aircraft rudder face, including it is as follows
Step:
Step 1: preparing aluminium sheet, carbon cloth and web mold, be applied with setting agent to carbon fiber, will be applied using blanking machine
The carbon cloth for having smeared setting agent cuts out the upper edge strip of middle Cheng Liang, lower edge strip, leading web, median ventral plate and trailing web；
Step 2: the upper edge strip obtained through step 1, lower edge strip, leading web, median ventral plate and trailing web are laid in aluminium sheet
On assembled, leading web, median ventral plate and trailing web and web mold cooperatively form c-type, are installed in edge strip and lower edge strip
Between, it is inserted in vacuum bag after assembling, the vacuum bag is equipped with vacuum tube, passes through vacuum tube vacuumize process；
Step 3: after vacuumize process, then be heating and curing it is preforming, stop heating after, keep vacuum state cool
It is dismantled again to room temperature, upper and lower edge strip and each web after obtaining curing molding；
Step 4: upper edge strip, lower edge strip, leading web, trailing web, the median ventral plate after curing molding are placed on aluminium sheet over-assemble
The structure of Cheng Liang: lower edge strip is placed on bottom, contacts with aluminium sheet；Each web, the leading web are sequentially placed between upper and lower edge strip
It is supported filled with foam in cavity in cavity between median ventral plate and between median ventral plate and trailing web；
Step 5: laying is successively carried out on the upper edge strip of the girder construction by step 4 assembling, is sequentially consisted of
Demoulding cloth and flow-guiding screen are integrally packed into after laying inside vacuum bag after carrying out vacuumize process and import resin to there is carbon cloth
Place；
Step 6: after importing resin, intermediate temperature setting, solidification temperature 120-145 degree, solidification are carried out to the whole of vacuum state
Time is 50-70 minutes, and vacuum state is kept to cool to after room temperature 20-30 degree, demoulding, and the foam of the inside is plucked out, and is obtained
The structure of beam；
Step 7: the upper covering and lower covering of wing are made, while by beam obtained in upper covering, lower covering and step 6
After being assembled, intermediate-temperature glue is added between upper and lower covering and beam contact position, wraps up Liang Yushang outside with vacuum bag later
After lower covering, curing molding after carrying out gluing is vacuumized to it.
Further, in step 5, when importing resin, a diversion pipe will be installed by an injecting glue seat on vacuum bag, taken out true
It is empty simultaneously to open diversion pipe, resin is imported into vacuum bag from diversion pipe, when having resin outflow in gas-guide tube, is closed
Diversion pipe is closed, while spending pumping gas-guide tube 8-12 minutes.
Further, in the step 7, after upper covering, lower covering and beam are assembled, with sack enwrapped granule object
Make inner stuffing or inflation, is placed at the cavity formed between beam, upper and lower covering and supports.
Further, in step 6, before solidifying to the entirety under vacuum state, diversion pipe and gas-guide tube are pulled out
Afterwards, it is cased with one layer of vacuum bag again outside, carries out vacuumizing curing molding.
Further, in step 1, the dosage of setting agent is controlled less than 12 grams/m^2.
Further, in step 3, after vacuumizing, the technique for the preforming processing that be heating and curing is heating temperature
110-130 degree, heating time 50-70 minute stop heating, keep vacuum state to cool to room temperature 20-30 degree, then dismantle.
The method for forming ultra light aircraft rudder face by the above composite liquid, the present invention also provides a kind of microlight-types
Aircraft rudder surface.
Present invention has an advantage that first, web and lower edge strip are penetrated by resin in the present invention and complete injecting glue, is solved
The vacuum of complicated 3D shape imports.Make inner stuffing with sack enwrapped granule object or inflation, outside with vacuum bag later
The method that package composite material skin vacuumizes bonding, not only ensure that the bonding quality of covering at high temperature under high pressure, but also solve
The taking-up problem of filler in hollow covering is not present residue, alleviates the weight of rudder face.
Detailed description of the invention:
Fig. 1 is ply angles sectional view when importing resin；
Fig. 2 is the assembly structure diagram of upper covering, lower covering and beam；
Appended drawing reference is respectively as follows: edge strip 1, lower edge strip 2, leading web 3, trailing web 4, median ventral plate 5, aluminium sheet 6, foam in figure
7, supporting block 8, release cloth 9, flow-guiding screen 10, vacuum bag 11, upper covering 12, lower covering 13, fine sand 14；
Specific embodiment:
The present invention is further explained below in conjunction with specific embodiment, but the not limitation present invention.
In order to complete ultra light aircraft rudder face complexity three-dimensional structure importing resin forming, the present invention provides a kind of
Invention provides a kind of method of composite liquid molding ultra light aircraft rudder face, includes the following steps:
Step 1: prepare aluminium sheet 6, carbon cloth and web mold, setting agent is applied with to carbon fiber, setting agent here is adopted
With ES-T321 preporm epoxy setting agent.The dosage of setting agent is controlled less than 12 grams/m^2.It will be applied using blanking machine
The carbon cloth for having smeared setting agent cuts out the upper edge strip 1 of middle Cheng Liang, lower edge strip 2, leading web 3, median ventral plate 5 and trailing web 4；
Step 2: the upper edge strip 1 obtained through step 1, lower edge strip 2, leading web 3, median ventral plate 5 and trailing web 4 are laid in
It is assembled on aluminium sheet 6, leading web 3, median ventral plate 5 and trailing web 4 and web mold cooperatively form c-type, are installed in edge strip 1
It between lower edge strip 2, is inserted in after assembling in vacuum bag 11, the vacuum bag 11 is equipped with vacuum tube, is vacuumized by vacuum tube
Processing；
Step 3: after vacuumize process, then preforming, the technique for the preforming processing that be heating and curing that be heating and curing
It is 120 degree of heating temperature, heating time 60 minutes, stops heating, keep vacuum state to cool to room temperature 20-30 degree, then dismantle
Upper and lower edge strip and each web after obtaining curing molding；
Step 4: as shown in Figure 1, by upper edge strip 1, lower edge strip 2, leading web 3, trailing web 4, median ventral plate after curing molding
5 are placed on the structure of 6 over-assemble Cheng Liang of aluminium sheet: lower edge strip 2 is placed on bottom, contacts with aluminium sheet 6；Between upper edge strip 1 and lower edge strip 2
It is sequentially placed each web, leading web 3, median ventral plate 4 and trailing web 5 are followed successively by from left to right, between leading web 3 and median ventral plate 4
It is supported filled with foam 7 in cavity and in the cavity between median ventral plate 4 and trailing web 5；Leading web 3 left side and after
The right side of web 4 can add a supporting block 8 respectively to support.Supporting block 8 herein can use foam or aluminium block.
Step 5: laying is successively carried out on the upper edge strip 1 of the girder construction by step 4 assembling, is sequentially consisted of
Demoulding cloth 9 and flow-guiding screen 10 are integrally packed into after laying inside vacuum bag 11 after carrying out vacuumize process and import resin to there is carbon fiber
Tie up the place of cloth；When importing resin, a diversion pipe will be installed by an injecting glue seat on vacuum bag 11, vacuumized while by diversion pipe
It opens, resin is imported into vacuum bag from diversion pipe, when having resin outflow in gas-guide tube, close diversion pipe, simultaneously
Cross pumping gas-guide tube 10 minutes.
Step 6: after importing resin, before solidifying to the entirety under vacuum state, diversion pipe and gas-guide tube are first pulled out
Afterwards, it is cased with one layer of vacuum bag 11 again outside, then is once vacuumized, to the entirety being cased under two layers of vacuum bag state at this time
Intermediate temperature setting, solidification temperature 120-145 degree are carried out, curing time is 50-70 minutes, and vacuum state is kept to cool to room temperature 20-
After 30 degree, demoulding, and the foam of the inside 7 is plucked out, obtain the structure of beam；
Step 7: as shown in Fig. 2, the upper covering 12 and lower covering 13 of production wing, while by upper covering 12, lower covering 13
After being assembled with beam obtained in step 6, intermediate-temperature glue is added between upper and lower covering and beam contact position, later with true
After empty bag 11 wraps up beam and upper covering 12, lower covering 13 outside, after vacuumizing to it, curing molding after gluing is carried out, wherein solid
Changing molding technique parameter is, solidification temperature is 110 degree, and the time is 1 hour.
As the improvement of scheme, in the step 7, after upper covering 12, lower covering 13 and beam are assembled, sack is used
Enwrapped granule object makees inner stuffing or inflation, is placed at the cavity formed between beam, upper and lower covering and supports.Here particle
We can take thinner fine sand 14 to fill to object, be placed between beam and upper and lower covering and support, both ensure that covering
Bonding quality at high temperature under high pressure, and solve the problems, such as the taking-up of filler in hollow covering, residue is not present, alleviates
The weight of rudder face.The method for forming ultra light aircraft rudder face by the above composite liquid, it is super that the present invention also provides one kind
Light aerocraft rudder face.In the present invention, vacuum bag specification used is the pressure of an atmospheric pressure.
The above is merely a preferred embodiment of the present invention, and protection scope of the present invention is not limited to this, any to be familiar with being somebody's turn to do
The personnel of technology it is presently disclosed it is any transform or replace, should all cover within the scope of the present invention.
Claims (6)
1. a kind of method of composite liquid molding ultra light aircraft rudder face, which comprises the steps of:
Step 1: prepare aluminium sheet, carbon cloth and web mold, setting agent is applied with to carbon fiber, will have been smeared using blanking machine
The carbon cloth of setting agent cuts out upper edge strip, lower edge strip, leading web, median ventral plate and the trailing web of middle Cheng Liang；
Step 2: it is enterprising that the upper edge strip obtained through step 1, lower edge strip, leading web, median ventral plate and trailing web are laid in aluminium sheet
Row assembling, leading web, median ventral plate and trailing web and web mold cooperatively form c-type, are installed between edge strip and lower edge strip,
It is inserted in vacuum bag after assembling, the vacuum bag is equipped with vacuum tube, passes through vacuum tube vacuumize process；
Step 3: after vacuumize process, then being heated, and heating temperature is 110-130 degree, heating time 50-70 minute, solidification
It is preforming, after stopping heating, keeps vacuum state to cool to room temperature 20-30 degree and dismantle again, the upper and lower edge after obtaining curing molding
Item and each web；
Step 4: upper edge strip, lower edge strip, leading web, trailing web, the median ventral plate after curing molding are placed on aluminium sheet over-assemble Cheng Liang
Structure: lower edge strip is placed on bottom, contacts with aluminium sheet；Each web is sequentially placed between upper and lower edge strip, the leading web is in
It is supported filled with foam in cavity between web and in the cavity between median ventral plate and trailing web；
Step 5: laying is successively carried out on the upper edge strip of the girder construction by step 4 assembling, sequentially consists of demoulding
Cloth and flow-guiding screen are integrally packed into after laying after carrying out vacuumize process inside vacuum bag and import resin；
Step 6: after importing resin, intermediate temperature setting is carried out to the whole of vacuum state, the technological parameter of intermediate temperature setting is solidification temperature
120-145 degree is spent, curing time is 50-70 minutes, stops heating, demoulds after keeping vacuum state to cool to room temperature 20-30 degree；
It is cool and to pluck out the foam of the inside to carrying out demoulding after room temperature, obtain the structure of beam；
Step 7: the upper covering and lower covering of wing are made, while beam obtained in upper covering, lower covering and step 6 being carried out
After assembling, intermediate-temperature glue is added between upper and lower covering and beam contact position, wrap up beam outside with vacuum bag later and covers up and down
Pi Hou vacuumizes curing molding after carrying out gluing to it.
2. a kind of method of composite liquid molding ultra light aircraft rudder face as described in claim 1, it is characterised in that: step
In rapid five, when importing resin, a diversion pipe will be installed by an injecting glue seat on vacuum bag, vacuumizes while opening diversion pipe,
Resin is imported into vacuum bag from diversion pipe, when having resin outflow in gas-guide tube, closes diversion pipe, while crossing to take out and lead
Tracheae 8-12 minutes.
3. a kind of method of composite liquid molding ultra light aircraft rudder face as described in claim 1, it is characterised in that: institute
It states in step 7, after upper covering, lower covering and beam are assembled, makees inner stuffing or inflation with sack enwrapped granule object,
It is placed between beam, upper and lower covering and is supported at cavity.
4. a kind of method of composite liquid molding ultra light aircraft rudder face as described in claim 1, it is characterised in that:
In step 6, before solidifying to the entirety under vacuum state, after pulling out diversion pipe and gas-guide tube, it is cased with one layer again outside very
Empty bag carries out vacuumizing curing molding.
5. a kind of method of composite liquid molding ultra light aircraft rudder face as described in claim 1, it is characterised in that:
In step 1, the dosage of setting agent is controlled less than 12 grams/m^2.
6. a kind of ultra light aircraft rudder face manufactured according to method a method as claimed in any one of claims 1 to 5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710518650.9A CN107160709B (en) | 2017-06-30 | 2017-06-30 | A kind of method and rudder face of composite liquid molding ultra light aircraft rudder face |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710518650.9A CN107160709B (en) | 2017-06-30 | 2017-06-30 | A kind of method and rudder face of composite liquid molding ultra light aircraft rudder face |
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| Publication Number | Publication Date |
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| CN107160709A CN107160709A (en) | 2017-09-15 |
| CN107160709B true CN107160709B (en) | 2019-08-13 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110744835A (en) * | 2019-10-31 | 2020-02-04 | 中航通飞华南飞机工业有限公司 | Sand grain pressurizing auxiliary method for composite material fiber ship body |
| CN111452953B (en) * | 2020-04-01 | 2023-04-07 | 中国商用飞机有限责任公司 | Box type structure suitable for constructing airplane wing surface |
| CN111923451B (en) * | 2020-06-15 | 2021-11-30 | 成都飞机工业（集团）有限责任公司 | Method for inhibiting composite material skin wrinkles |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB9211263D0 (en) * | 1992-05-28 | 1992-07-15 | British Aerospace | Manufacture of articles from composite material |
| US20030019567A1 (en) * | 2001-07-26 | 2003-01-30 | Burpo Steven J. | Vacuum assisted resin transfer method for co-bonding composite laminate structures |
| CN100418720C (en) * | 2005-06-10 | 2008-09-17 | 中国航空工业第一集团公司北京航空材料研究院 | Preparation method of liquid state shaping composite material preshaped body |
| GB2475523B (en) * | 2009-11-20 | 2012-09-05 | Gkn Aerospace Services Ltd | Dual-skin structures |
| CN102990940B (en) * | 2012-12-05 | 2016-12-28 | 中国商用飞机有限责任公司 | Composite stiffened liquid molding device and method |
| CN104057648A (en) * | 2013-03-18 | 2014-09-24 | 空客(北京)工程技术中心有限公司 | Mixed sandwich structure, reinforcer and processing method thereof |
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