CN102225703A - Manufacturing method of integral glass fiber reinforced plastic unmanned aerial vehicle wing - Google Patents
Manufacturing method of integral glass fiber reinforced plastic unmanned aerial vehicle wing Download PDFInfo
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- CN102225703A CN102225703A CN2011100910785A CN201110091078A CN102225703A CN 102225703 A CN102225703 A CN 102225703A CN 2011100910785 A CN2011100910785 A CN 2011100910785A CN 201110091078 A CN201110091078 A CN 201110091078A CN 102225703 A CN102225703 A CN 102225703A
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Abstract
A manufacturing method of an integral glass fiber reinforced plastic unmanned aerial vehicle wing comprises the following steps: A. a three-time vacuum-pumping solidification method for molding of an upper and a lower wall panels; B. assembly of a beam and a rib; C. adhesive bonding of the wall panel, the beam and the rib, that is performing adhesive bonding of the beam, the rib and the lower wall panel with a thermoset epoxy adhesive, and then performing adhesive bonding by covering the upper wall panel, which is referred as a twice adhesive bonding method. The advantages of the invention are that: 1. molding, assembling, and inspection are integrated, which not only reduces manufacturing cost, but also prevents one-side wall panels from deformation due to mold stripping; 2. a mode of directly spraying gel-coating resin on a mold is adopted, and the wall panel is paved before complete solidification; the gel-coating resin fills up honeycomb lattice patterns well, and the honeycomb lattice patterns disappear completely after mold stripping.
Description
Technical field
The present invention relates to a kind of method for making of unmanned plane wing, relate in particular to a kind of method for making of integral glass steel unmanned plane wing.
Background technology
Wing is the vitals that miniature self-service drives an airplane, and plays dual parts to produce lift, carrying aerodynamic force, and enough intensity, rigidity and lighter weight not only will be arranged, and smooth, streamline, profile accurately will be arranged.Therefore, the wing of an excellent performance needs to take all factors into consideration from material, structure and manufacturing process.
General wing design is segmentation structure, and this structure needs both wings are connected, and also has the frangibility problem, and weight also increases more for aviette.At present, certain type machine wing adopts the new structure of integral type wing in design audaciously, and this kind structure is connected as a single entity the left and right sides wing, has improved the every performance and the aesthetics of aircraft.The integral type wing is not only novel in design, and domestic on manufacturing technology do not have a data of can using for reference yet.Compare the sectional type wing, the integral type wing is had higher requirement to forming process in the flatness of spanwise.For the new structure of the light-duty aircraft wing of such integral type, need develop the comparatively perfect fabrication scheme of a cover, setting about improving from frock is a good breakthrough point.
Summary of the invention
The object of the present invention is to provide a kind of method for making of integral glass steel unmanned plane wing, whole glass-felt plastic wing is made up of parts such as upper and lower wallboard, beam, ribs.Upper and lower wallboard is a frp honeycomb sandwich structure, and the beam of I shape, rib are made of U font aluminium chassis and lightweight wood laminate, and beam, rib and last lower wall panels adopt room temperature setting adhesives to glued joint.
The present invention is achieved like this, and making step is:
A. upper and lower wallboard forming adopts and vacuumizes solidification method three times: lower wall panels is solidified earlier, then honeycomb is glued to lower wall panels and carries out regelate, connect wallboard in the honeycomb gluing at last and carry out three curing, cover equal pressing plate in the wainscot splicing process, the pressure of clamp evenly is delivered to each point, guarantee that pressurized is even everywhere, upper and lower wallboard is not thrown off with mould in whole process all the time, guarantees the flatness of wallboard;
B. the assembling of beam, rib: beam, rib adopt a phantom of moulding and assembling to assemble, and pre-install coordination earlier, after guaranteeing to glued joint the gap, arrange riveting, riveter, by eliminating distortion from the centre to the mode of both sides riveter nail;
C. wallboard and beam, rib glued joint, and adopt thermoset epoxy glue earlier beam, rib and lower wall panels to be gluedd joint, and cover wainscot again and glued joint, be i.e. the second bonding method.
What the upper and lower wallboard of described wing was selected for use is paper wasp nest frp sandwich construction, takes on mould the directly mode of spray gel coating resin, before complete curing not, just spreads wallboard.
Described gel coating resin should mix with resin with upper and lower wallboard.
All tolerance clearances are controlled in the 0.2mm scope in the pre-assy process.
Advantage of the present invention is: moulding, assembling, check are integrated, have not only reduced manufacturing cost, and prevented the distortion that the single face wallboard produces because of molding; 2, take on mould the directly mode of spray gel coating resin, before complete curing not, just spread wallboard, gel coating resin has better remedied honeycomb lattice seal, and honeycomb lattice seal is eliminated fully behind the delivery.
The specific embodiment
The wing length overall is more than 4 meters, and the not enough 100mm of cross-sectional height is the representative type thin-plate element, guarantee that its exhibition to indeformable, needs to consider the flatness of upper and lower wallboard, the problems such as coordination of the assembling of metallic framework and skeleton and wallboard.For this reason, the structure that we have adopted forming mould and assembly jig to unite two into one, according to this design, only need two wallboard forming moulds, have the installation clamp of beam, rib and the catch gear of each accessory on one of the wallboard forming mould therein, the workman just can be tested when making wallboard, can more in time control the wallboard profile more accurately.
(1) tool structure
According to general frock design, the manufacturing of whole wing will be adopted upper and lower wallboard forming mold forming, and the assembling of wallboard and beam, rib needs special assembly jig.What we used at present is the structure that forming mould and assembly jig unite two into one, and adopts moulding and assembling one mode structure, and wallboard is not thrown off with mould in whole technological process all the time, guarantees the flatness of wallboard.The assembling of metallic framework is put on the forming die, metallic framework is holed by the part prepackage from the middle part to both sides, cut off the location, the exhibition that guarantees is to warpage not, carry out pre-assy earlier in the splicing front panel, guarantee that the each point gap is even, cover equal pressing plate in the wainscot splicing process, the pressure of clamp evenly is delivered to each point, guarantees that pressurized is even everywhere.
(2) material selection
From the constructional feature of whole wing as can be seen, aerofoil profile is a double curved surface, span length is 4 meters, stick with glue agent by clamp bonding one-tenth composite components such as wallboard, beam, ribs, because glass-felt plastic and metal piece thermal expansion coefficient are bigger, and wooden pieces is relative less owing to working accuracy when part is made with the glass covering, obtain the failure-free bonding quality, and the selection of adhesion agent is quite important.On probation by multiple glue, selected thermoset epoxy class formation glue glueds joint plate-cored structure, and it is good that it has a screening characteristics, the characteristics that adhesive property is high.For guaranteeing the weight requirement, in adhesion agent, add glass microsphere and improve consistence.What reinforcing material was selected for use is alkali-free plain weave glass woven fabric, and what sandwich material was selected for use is the papery honeycomb.
(3) technological process
Wing is made phenomenons such as having oad instability, honeycomb skew, honeycomb contraction in the process in examination, by analyzing and the technology adjustment, determines that finally the moulding scheme is as follows:
A. upper and lower wallboard forming adopts and vacuumizes solidification method three times: lower wall panels is solidified earlier, then honeycomb is glued to lower wall panels and carries out regelate, connect wallboard in the honeycomb gluing at last and carry out three curing, cover equal pressing plate in the wainscot splicing process, the pressure of clamp evenly is delivered to each point, guarantee that pressurized is even everywhere, upper and lower wallboard is not thrown off with mould in whole process all the time, guarantees the flatness of wallboard;
B. the assembling of beam, rib: beam, rib adopt a phantom of moulding and assembling to assemble, and pre-install coordination earlier, after guaranteeing to glued joint the gap, arrange riveting, riveter, by eliminating distortion from the centre to the mode of both sides riveter nail;
C. wallboard and beam, rib glued joint, and adopt thermoset epoxy glue earlier beam, rib and lower wall panels to be gluedd joint, and cover wainscot again and glued joint, be i.e. the second bonding method.
(4) technological process measure of control
A. profile control
The whole wing span is long 4 meters, and inside be metallic framework, and to control to flatness and oad be an emphasis controlling element opening up on the technology.This programme is controlled by the following aspects:
1. mould structure: adopt moulding and assembling one mode structure, wallboard is not thrown off with mould in whole technological process all the time, guarantees the flatness of wallboard.
2. the assembling of metallic framework is put on the forming die, guarantees to make the conformability of foundation.
3. metallic framework from the middle part to both sides by part prepackage boring, cut off the location, the exhibition that guarantees is to warpage not.
4. carry out pre-assy earlier in the splicing front panel, guarantee that the each point gap is even.
5. cover equal pressing plate in the wainscot splicing process, the pressure of clamp evenly is delivered to each point, guarantee that pressurized is even everywhere.
B. surface quality control
For guaranteeing weight, what wing wallboard was selected for use is paper wasp nest frp sandwich construction, and the covering of wallboard is very thin, and honeycomb prints from panel surfaces, and is fairly obvious.Adopt common mode of spraying paint, for the amount of taking care of yourself can not Puttying, only can topcoating, enamelled coating surface, spray back honeycomb lattice are difficult to eliminate, and for this reason, take on mould the directly mode of spray gel coating resin on the technology, before complete curing not, just spread wallboard.Gel coating resin has better remedied honeycomb lattice seal, and honeycomb lattice seal is eliminated fully behind the delivery.In addition, in the selection of gel coating resin, should select and wallboard resin intermiscibility type preferably.
Claims (4)
1. the method for making of an integral glass steel unmanned plane wing is characterized in that making step is:
A. upper and lower wallboard forming adopts and vacuumizes solidification method three times: lower wall panels is solidified earlier, then honeycomb is glued to lower wall panels and carries out regelate, connect wallboard in the honeycomb gluing at last and carry out three curing, cover equal pressing plate in the wainscot splicing process, the pressure of clamp evenly is delivered to each point, guarantee that pressurized is even everywhere, upper and lower wallboard is not thrown off with mould in whole process all the time, guarantees the flatness of wallboard;
B. the assembling of beam, rib: beam, rib adopt a phantom of moulding and assembling to assemble, and pre-install coordination earlier, after guaranteeing to glued joint the gap, arrange riveting, riveter, by eliminating distortion from the centre to the mode of both sides riveter nail;
C. wallboard and beam, rib glued joint, and adopt thermoset epoxy glue earlier beam, rib and lower wall panels to be gluedd joint, and cover wainscot again and glued joint, be i.e. the second bonding method.
2. the method for making of integral glass steel unmanned plane wing according to claim 1, what it is characterized in that the upper and lower wallboard of described wing selects for use is paper wasp nest frp sandwich construction, take on mould the directly mode of spray gel coating resin, before complete curing not, just spread wallboard.
3. the method for making of integral glass steel unmanned plane wing according to claim 2 is characterized in that described gel coating resin should mix with resin with upper and lower wallboard.
4. the method for making of integral glass steel unmanned plane wing according to claim 1 is characterized in that all tolerance clearances are controlled in the 0.2mm scope in the pre-assy process.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011100910785A CN102225703A (en) | 2011-04-12 | 2011-04-12 | Manufacturing method of integral glass fiber reinforced plastic unmanned aerial vehicle wing |
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| CN2011100910785A CN102225703A (en) | 2011-04-12 | 2011-04-12 | Manufacturing method of integral glass fiber reinforced plastic unmanned aerial vehicle wing |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102848579A (en) * | 2012-03-09 | 2013-01-02 | 昌河飞机工业（集团）有限责任公司 | Manufacturing method of double-sided honeycomb sandwich composite material product |
| CN103192527A (en) * | 2013-04-24 | 2013-07-10 | 哈尔滨飞机工业集团有限责任公司 | Secondary bonding forming method of structural part with curvature |
| CN103963961A (en) * | 2013-02-01 | 2014-08-06 | 哈尔滨飞机工业集团有限责任公司 | Tail beam fairing molding anti-deformation manufacturing method |
| CN104626548A (en) * | 2015-01-13 | 2015-05-20 | 哈尔滨飞机工业集团有限责任公司 | Composite-material vertical fin combination method of unmanned aerial vehicle |
| CN106584886A (en) * | 2016-12-28 | 2017-04-26 | 中航沈飞民用飞机有限责任公司 | Process for controlling thickness of glued rubber layer by using self-made rubber cover plate |
| CN109605019A (en) * | 2018-11-30 | 2019-04-12 | 上海航天精密机械研究所 | Carrier rocket empennage glue riveting assembly technique |
| CN110757838A (en) * | 2019-10-30 | 2020-02-07 | 航天特种材料及工艺技术研究所 | Composite material wing and forming and assembling integrated forming method |
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| JP2004034314A (en) * | 2002-06-28 | 2004-02-05 | Hitachi Housetec Co Ltd | Improved manufacturing method for patterned plastic molded product and molded product |
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- 2011-04-12 CN CN2011100910785A patent/CN102225703A/en active Pending
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| JP2004034314A (en) * | 2002-06-28 | 2004-02-05 | Hitachi Housetec Co Ltd | Improved manufacturing method for patterned plastic molded product and molded product |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102848579A (en) * | 2012-03-09 | 2013-01-02 | 昌河飞机工业（集团）有限责任公司 | Manufacturing method of double-sided honeycomb sandwich composite material product |
| CN103963961A (en) * | 2013-02-01 | 2014-08-06 | 哈尔滨飞机工业集团有限责任公司 | Tail beam fairing molding anti-deformation manufacturing method |
| CN103192527A (en) * | 2013-04-24 | 2013-07-10 | 哈尔滨飞机工业集团有限责任公司 | Secondary bonding forming method of structural part with curvature |
| CN104626548A (en) * | 2015-01-13 | 2015-05-20 | 哈尔滨飞机工业集团有限责任公司 | Composite-material vertical fin combination method of unmanned aerial vehicle |
| CN106584886A (en) * | 2016-12-28 | 2017-04-26 | 中航沈飞民用飞机有限责任公司 | Process for controlling thickness of glued rubber layer by using self-made rubber cover plate |
| CN106584886B (en) * | 2016-12-28 | 2019-04-09 | 中航沈飞民用飞机有限责任公司 | The technique for being glued bondline thickness using self-control rubber cover board control |
| CN109605019A (en) * | 2018-11-30 | 2019-04-12 | 上海航天精密机械研究所 | Carrier rocket empennage glue riveting assembly technique |
| CN110757838A (en) * | 2019-10-30 | 2020-02-07 | 航天特种材料及工艺技术研究所 | Composite material wing and forming and assembling integrated forming method |
| CN110757838B (en) * | 2019-10-30 | 2021-12-24 | 航天特种材料及工艺技术研究所 | Composite material wing and forming and assembling integrated forming method |
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Application publication date: 20111026 |