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 PDF

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Publication number
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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CN
China
Prior art keywords
web
covering
edge strip
light aircraft
ultra light
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
Application number
CN201710518650.9A
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Chinese (zh)
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CN107160709B (en
Inventor
庞舒戈
邱林
李淑萍
李昂
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LIAONING RUIXIANG GENERAL AVIATION Co Ltd
Shenyang Aerospace University
Original Assignee
LIAONING RUIXIANG GENERAL AVIATION Co Ltd
Shenyang Aerospace University
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Application filed by LIAONING RUIXIANG GENERAL AVIATION Co Ltd, Shenyang Aerospace University filed Critical LIAONING RUIXIANG GENERAL AVIATION Co Ltd
Priority to CN201710518650.9A priority Critical patent/CN107160709B/en
Publication of CN107160709A publication Critical patent/CN107160709A/en
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/30Shaping 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
    • B29C70/34Shaping 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
    • B29C70/342Shaping 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
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/54Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29LINDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00Other particular articles
    • B29L2031/30Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076Aircrafts

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

The method and rudder face of a kind of composite liquid shaping ultra light aircraft rudder face
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.
CN201710518650.9A 2017-06-30 2017-06-30 A kind of method and rudder face of composite liquid molding ultra light aircraft rudder face Active CN107160709B (en)

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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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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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Cited By (2)

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Publication number Priority date Publication date Assignee Title
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
CN111923451A (en) * 2020-06-15 2020-11-13 成都飞机工业(集团)有限责任公司 Method for inhibiting composite material skin wrinkles

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN111923451A (en) * 2020-06-15 2020-11-13 成都飞机工业(集团)有限责任公司 Method for inhibiting composite material skin wrinkles
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

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