CN107160709A - The method and rudder face of a kind of composite liquid shaping ultra light aircraft rudder face - Google Patents
The method and rudder face of a kind of composite liquid shaping ultra light aircraft rudder face Download PDFInfo
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- CN107160709A CN107160709A CN201710518650.9A CN201710518650A CN107160709A CN 107160709 A CN107160709 A CN 107160709A CN 201710518650 A CN201710518650 A CN 201710518650A CN 107160709 A CN107160709 A CN 107160709A
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- light aircraft
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- 239000002131 composite material Substances 0.000 title claims abstract description 19
- 239000007788 liquid Substances 0.000 title claims abstract description 15
- 238000007493 shaping process Methods 0.000 title claims abstract description 6
- 239000011347 resin Substances 0.000 claims abstract description 20
- 229920005989 resin Polymers 0.000 claims abstract description 20
- 238000000034 method Methods 0.000 claims abstract description 16
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 15
- 239000004411 aluminium Substances 0.000 claims abstract description 15
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminum Chemical compound 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[Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 15
- 238000000465 moulding Methods 0.000 claims abstract description 12
- 239000003292 glue Substances 0.000 claims abstract description 8
- 238000007711 solidification Methods 0.000 claims abstract description 6
- 239000004744 fabric Substances 0.000 claims description 15
- 238000010438 heat treatment Methods 0.000 claims description 12
- OKTJSMMVPCPJKN-UHFFFAOYSA-N carbon Chemical compound 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[C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 11
- 229910052799 carbon Inorganic materials 0.000 claims description 11
- 239000003795 chemical substances by application Substances 0.000 claims description 11
- 239000006260 foam Substances 0.000 claims description 8
- 239000008187 granular material Substances 0.000 claims description 4
- 238000004026 adhesive bonding Methods 0.000 claims description 3
- 238000010276 construction Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 claims 1
- 239000004576 sand Substances 0.000 abstract description 5
- 239000000945 filler Substances 0.000 abstract description 3
- 239000011157 advanced composite material Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000004593 Epoxy Substances 0.000 description 1
- 210000003491 Skin Anatomy 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 125000003700 epoxy group Chemical group 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—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
Abstract
The invention belongs to composite material process planning technical field, the method that specially a kind of composite liquid is molded ultra light aircraft rudder face, make the upper of beam, lower edge strip, the parts such as web, vacuumized after curing molding, it is put into aluminium sheet and carries out the structure that laying constitutes beam, by carrying out secondary vacuumizing importing resin to it, the solidification demoulding obtains the structure of beam, remanufacture, after lower covering, it is assembled with beam, the hollow position of covering up and down is supported with fine sand or inflation during assembling, fine sand or inflation will be discharged by being bonded after solidify afterwards shaping, based on this process, present invention also offers a kind of ultra light aircraft rudder face simultaneously.Advantage is：Web and lower edge strip are penetrated into by resin and complete injecting glue, the vacuum for solving the 3D shape of complexity is imported.Make inner stuffing with sack parcel fine sand, both ensure that the bonding quality of covering at high temperature under high pressure, the taking-up of filler in hollow covering has been solved the problems, such as again, in the absence of residue.
Description
Technical field：
The invention belongs to Aero-Space composite material process planning technical field, and in particular to a kind of composite liquid into
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 technology：
Advanced composite has the superiority such as the homogeneity of high specific strength, high ratio modulus, endurance, material and structure
Can, since the sixties in last century, advanced composite obtains extensive use quickly, as one of big material of Aero-Space four,
The moulding process of composite is varied.Vehicle rudder structure generally comprises the structures such as covering, lower covering and beam, internal
Structure is complex, and particularly with complicated 3D shape, such as web and lower edge strip part, curing molding are cumbersome.
The content of the invention：
In consideration of it, the invention provides a kind of method that composite liquid is molded ultra light aircraft rudder face, it is including as follows
Step：
Step one:Prepare aluminium sheet, carbon cloth and web mold, setting agent is applied to carbon cloth, will be applied using blanking machine
The carbon cloth for having smeared setting agent cuts out middle Cheng Liang upper edge strip, lower edge strip, leading web, median ventral plate and trailing web；
Step 2：The upper edge strip obtained through step one, lower edge strip, leading web, median ventral plate and trailing web are laid in aluminium sheet
Upper to be 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 after assembling in vacuum bag, the vacuum bag is provided with vacuum tube, passes through vacuum tube vacuumize process；
Step 3：After vacuumize process, then be heating and curing preforming, stop after heating, keep vacuum state to cool
Taken apart again to room temperature, obtain the upper and lower edge strip after curing molding and each web；
Step 4：Upper edge strip after curing molding, lower edge strip, leading web, trailing web, median ventral plate are placed on aluminium sheet over-assemble
Cheng Liang structure：Lower edge strip is placed on bottom, is contacted with aluminium sheet；Each web, the leading web are sequentially placed between upper and lower edge strip
Supported in cavity in cavity between median ventral plate and between median ventral plate and trailing web filled with foam；
Step 5：Laying is carried out successively on the upper edge strip of the girder construction assembled by step 4, is sequentially consisted of
Integrally load after demoulding cloth and flow-guiding screen, laying inside vacuum bag and imported after vacuumize process resin to there is carbon cloth
Place；
Step 6：Import after resin, intermediate temperature setting, solidification temperature 120-145 degree, solidification are carried out to the overall of vacuum state
Time is 50-70 minutes, keeps vacuum state 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 the beam that will be obtained in upper covering, lower covering and step 6
After being assembled, up and down intermediate-temperature glue is being added between covering and beam contact position, afterwards with vacuum bag outer wrapping beam with it is upper
After lower covering, the gluing solidify afterwards shaping of progress is vacuumized to it.
Further, in step 5, when importing resin, a mozzle will be installed by injecting glue seat on vacuum bag, takes out true
It is empty simultaneously to open mozzle, resin is imported into vacuum bag from mozzle, when having resin outflow in airway tube, closed
Mozzle is closed, airway tube is taken out 8-12 minutes while crossing.
Further, in the step 7, after upper covering, lower covering and beam are assembled, with sack enwrapped granule thing
Make inner stuffing or inflation, be placed at the cavity formed between beam, upper and lower covering and support.
Further, in step 6, before solidifying to the entirety under vacuum state, mozzle and airway tube are pulled out
Afterwards, it is cased with one layer of vacuum bag again outside, progress vacuumizes curing molding.
Further, in step one, the consumption of setting agent is controlled less than 12 grams/m^2.
Further, in step 3, after vacuumizing, carry out be heating and curing preforming processing technique be heating-up temperature
110-130 degree, heat time 50-70 minute, stops heating, keeps vacuum state to cool to room temperature 20-30 degree, then take apart.
The method of ultra light aircraft rudder face is molded by above composite liquid, present invention also offers a kind of microlight-type
Aircraft rudder surface.
Advantage of the invention is that：First, web and lower edge strip are penetrated into by resin in the present invention and complete injecting glue, solved
The vacuum of complicated 3D shape is imported.Make inner stuffing with sack enwrapped granule thing or inflation, with vacuum bag outside afterwards
The method that parcel composite material skin vacuumizes bonding, both ensure that the bonding quality of covering at high temperature under high pressure, had solved again
The taking-up problem of filler in hollow covering, in the absence of residue, alleviates the weight of rudder face.
Brief description of the drawings：
Ply angles profile when Fig. 1 is importing resin；
Fig. 2 is the assembly structure diagram of upper covering, lower covering and beam；
Reference is respectively in figure：Upper edge strip 1, lower edge strip 2, leading web 3, trailing web 4, median ventral plate 5, aluminium sheet 6, foam
7th, support block 8, release cloth 9, flow-guiding screen 10, vacuum bag 11, upper covering 12, lower covering 13, fine sand 14；
Embodiment：
The present invention is further explained below in conjunction with specific embodiment, but does not limit to the present invention.
In order to complete the importing resin forming of the complicated three-dimensional structure of ultra light aircraft rudder face, the invention provides one kind originally
Invention provides a kind of method that composite liquid is molded ultra light aircraft rudder face, comprises the following steps：
Step one:Prepare aluminium sheet 6, carbon cloth and web mold, setting agent is applied to carbon cloth, setting agent here is adopted
With ES-T321 preporms epoxy setting agent.The consumption 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 middle Cheng Liang upper edge strip 1, 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 one, lower edge strip 2, leading web 3, median ventral plate 5 and trailing web 4 are laid in
Assembled on aluminium sheet 6, leading web 3, median ventral plate 5 and trailing web 4 cooperatively form c-type with web mold, are installed in edge strip 1
Between lower edge strip 2, it is inserted in after assembling in vacuum bag 11, the vacuum bag 11 is provided 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
For 120 degree of heating-up temperature, 60 minutes heat times, stop heating, keep vacuum state to cool to room temperature 20-30 degree, then take apart
Obtain the upper and lower edge strip after curing molding and each web；
Step 4：As shown in figure 1, by the upper edge strip 1 after curing molding, lower edge strip 2, leading web 3, trailing web 4, median ventral plate
5 are placed on the over-assemble Cheng Liang of aluminium sheet 6 structure：Lower edge strip 2 is placed on bottom, is contacted with aluminium sheet 6；Between upper edge strip 1 and lower edge strip 2
Each web is sequentially placed, 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
Supported in cavity and in the cavity between median ventral plate 4 and trailing web 5 filled with foam 7；The left side of leading web 3 and after
The right side of web 4 can add a support block 8 respectively to support.Support block 8 herein can use foam or aluminium block.
Step 5：Laying is carried out successively on the upper edge strip 1 of the girder construction assembled by step 4, is sequentially consisted of
Integrally load the inside of vacuum bag 11 after demoulding cloth 9 and flow-guiding screen 10, laying and imported after vacuumize process resin to there is carbon fibre
Tie up the place of cloth；When importing resin, a mozzle will be installed by injecting glue seat on vacuum bag 11, vacuumized mozzle simultaneously
Open, resin is imported into vacuum bag from mozzle, when having resin outflow in airway tube, close mozzle, simultaneously
Cross and take out airway tube 10 minutes.
Step 6：Import after resin, before solidifying to the entirety under vacuum state, first pull out mozzle and airway tube
Afterwards, it is cased with one layer of vacuum bag 11 again outside, then is once vacuumized, to the entirety being now cased with two layers of vacuum bag state
Intermediate temperature setting, solidification temperature 120-145 degree are carried out, hardening time is 50-70 minutes, keeps vacuum state to cool to room temperature 20-
After 30 degree, demoulding, and the foam 7 of the inside is plucked out, obtain the structure of beam；
Step 7：As shown in Fig. 2 make upper covering 12 and the lower covering 13 of wing, while by upper covering 12, lower covering 13
After being assembled with the beam that is obtained in step 6, intermediate-temperature glue is being added between covering and beam contact position up and down, afterwards with true
Empty bag 11 is after outer wrapping beam and upper covering 12, lower covering 13, after being vacuumized to it, gluing solidify afterwards shaping 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 are assembled with beam, sack is used
Enwrapped granule thing 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 thing, be placed between beam and upper and lower covering to support, both ensure that covering
Bonding quality at high temperature under high pressure, solves the problems, such as the taking-up of filler in hollow covering again, in the absence of residue, alleviates
The weight of rudder face.The method of ultra light aircraft rudder face is molded by above composite liquid, it is super present invention also offers one kind
Light aerocraft rudder face.In the present invention, vacuum bag specification used is the pressure of an atmospheric pressure.
Described above, only the preferred embodiments of the present invention, protection scope of the present invention is not limited to this, and any be familiar with should
The personnel of technology should be covered within the scope of the present invention in presently disclosed any conversion or replacement.
Claims (8)
1. a kind of method that composite liquid is molded ultra light aircraft rudder face, it is characterised in that comprise the following steps：
Step one:Prepare aluminium sheet, carbon cloth and web mold, setting agent is applied to carbon cloth, will have been smeared using blanking machine
The carbon cloth of setting agent cuts out middle Cheng Liang upper edge strip, lower edge strip, leading web, median ventral plate and trailing web；
Step 2：The upper edge strip obtained through step one, lower edge strip, leading web, median ventral plate and trailing web are laid in aluminium sheet enterprising
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 after assembling in vacuum bag, the vacuum bag is provided with vacuum tube, passes through vacuum tube vacuumize process；
Step 3：After vacuumize process, then be heating and curing preforming, stop after heating, keep vacuum state to cool to room
Temperature is taken apart again, obtains the upper and lower edge strip after curing molding and each web；
Step 4：Upper edge strip after curing molding, lower edge strip, leading web, trailing web, median ventral plate are placed on aluminium sheet over-assemble Cheng Liang
Structure：Lower edge strip is placed on bottom, is contacted with aluminium sheet；Each web is sequentially placed between upper and lower edge strip, the leading web is with
Supported in cavity between web and in the cavity between median ventral plate and trailing web filled with foam；
Step 5：Laying is carried out successively on the upper edge strip of the girder construction assembled by step 4, sequentially consists of demoulding
Integrally load after cloth and flow-guiding screen, laying after carrying out vacuumize process inside vacuum bag and import resin；
Step 6：Import after resin, intermediate temperature setting carried out to the overall of vacuum state, it is cool to carrying out demoulding after room temperature, and will be inner
The foam in face is plucked out, and obtains the structure of beam；
Step 7：The upper covering and lower covering of wing are made, while the beam obtained in upper covering, lower covering and step 6 is carried out
After assembling, up and down intermediate-temperature glue is being added between covering and beam contact position, afterwards with vacuum bag in outer wrapping beam with covering up and down
Pi Hou, the gluing solidify afterwards shaping of progress is vacuumized to it.
2. the method that a kind of composite liquid as claimed in claim 1 is molded ultra light aircraft rudder face, it is characterised in that：Step
In rapid five, when importing resin, on vacuum bag by injecting glue seat one mozzle of installation, it will vacuumize and simultaneously open mozzle,
Resin is imported into vacuum bag from mozzle, when having resin outflow in airway tube, mozzle is closed, is led while crossing to take out
Tracheae 8-12 minutes.
3. the method that a kind of composite liquid as claimed in claim 1 is molded ultra light aircraft rudder face, it is characterised in that：Institute
State in step 7, after upper covering, lower covering and beam are assembled, inner stuffing or inflation made with sack enwrapped granule thing,
It is placed between beam, upper and lower covering and is supported at cavity.
4. the method that a kind of composite liquid as claimed in claim 1 is molded ultra light aircraft rudder face, it is characterised in that：
In step 6, before solidifying to the entirety under vacuum state, mozzle is pulled out true with after airway tube, being cased with one layer again outside
Empty bag, progress vacuumizes curing molding.
5. the method that a kind of composite liquid as claimed in claim 1 is molded ultra light aircraft rudder face, it is characterised in that：
In step one, the consumption of setting agent is controlled less than 12 grams/m^2.
6. the method that a kind of composite liquid as claimed in claim 1 is molded ultra light aircraft rudder face, it is characterised in that：
In step 3, after vacuumizing, carry out be heating and curing preforming processing technique be heating-up temperature 110-130 degree, heat time 50-
70 minutes, stop heating, keep vacuum state to cool to room temperature 20-30 degree, then take apart.
7. the method that a kind of composite liquid as claimed in claim 1 is molded ultra light aircraft rudder face, it is characterised in that：
In step 6, the technological parameter of intermediate temperature setting is solidification temperature 120-145 degree, and hardening time is 50-70 minutes, stops heating,
Vacuum state is kept to cool to after room temperature 20-30 degree the demoulding.
8. a kind of ultra light aircraft rudder face of method manufacture according to as described in claim 1-7 is any.
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