CN111055517A - XPS extruded sheet inner core and epoxy resin composite material glider wing and preparation method thereof - Google Patents
XPS extruded sheet inner core and epoxy resin composite material glider wing and preparation method thereof Download PDFInfo
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- CN111055517A CN111055517A CN201911108300.0A CN201911108300A CN111055517A CN 111055517 A CN111055517 A CN 111055517A CN 201911108300 A CN201911108300 A CN 201911108300A CN 111055517 A CN111055517 A CN 111055517A
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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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/70—Completely encapsulating inserts
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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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/681—Component parts, details or accessories; Auxiliary operations
- B29C70/683—Pretreatment of the preformed part, e.g. insert
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
- C08J5/00—Manufacture of articles or shaped materials containing macromolecular substances
- C08J5/04—Reinforcing macromolecular compounds with loose or coherent fibrous material
- C08J5/0405—Reinforcing macromolecular compounds with loose or coherent fibrous material with inorganic fibres
- C08J5/043—Reinforcing macromolecular compounds with loose or coherent fibrous material with inorganic fibres with glass fibres
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- 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
- B29L2031/3085—Wings
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
- C08J2363/00—Characterised by the use of epoxy resins; Derivatives of epoxy resins
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K7/00—Use of ingredients characterised by shape
- C08K7/02—Fibres or whiskers
- C08K7/04—Fibres or whiskers inorganic
- C08K7/14—Glass
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Abstract
The invention belongs to the technical field of glider wing manufacturing, and provides an XPS extruded sheet inner core and epoxy resin composite material glider wing and a preparation method thereof. The composite material is prepared by taking an XPS extruded sheet as an inner core and a glass fiber reinforced D80 epoxy resin composite material skin through vacuum cold press molding. The composite material wing of the glider is manufactured by taking the XPS extruded sheet as the inner core of the wing and the glass fiber reinforced D80 epoxy resin composite material as the outer skin of the wing through a vacuum cold pressing curing molding process, and the glider of one composite material wing is successfully tried to fly. The XPS extruded sheet has a completely closed-cell foaming chemical structure and a cellular physical structure, so that the XPS extruded sheet has the characteristics of light weight, high compressive strength and high impact resistance, and has good stability and corrosion resistance in a long-term use process; glass fibers have characteristics such as insulation, heat resistance, and mechanical strength. The whole weight of the glider is reduced, and the flying efficiency and the mechanical strength are improved.
Description
Technical Field
The invention belongs to the technical field of glider wing manufacturing, and particularly relates to an XPS extruded sheet inner core and an epoxy resin composite material glider wing and a preparation method thereof, wherein the preparation method comprises the application of a vacuum cold pressing curing forming process in the manufacturing of a glass fiber reinforced D80 epoxy resin composite material.
Background
As a new material, a composite material has excellent properties such as high specific strength, high specific modulus, and high tensile modulus, and is widely used in various fields such as aviation, automobiles, ships, buildings, vehicles, and machinery. Among them, fiber-reinforced composite materials are widely used in the field of aviation. The composite material reinforcement is of various types, including glass fiber cloth, plant fiber and high-performance carbon fiber. Glass fiber cloth is widely used because of its advantages of good fire resistance, good corrosion resistance, high tensile strength, small elongation at break, good thermal and chemical stability, good electrical insulation, low coefficient of thermal expansion, etc. The matrix material of the fiber reinforced composite material has the functions of bonding fibers and transferring load, and is divided into resin, metal and ceramic according to the purpose. As an important thermosetting resin, the epoxy resin has the advantages of good mechanical property, high bonding strength, small curing shrinkage, good manufacturability, excellent stability and the like. The high-performance epoxy resin is used as a matrix and is compounded with a high-performance fiber reinforced material, so that a composite material with excellent performance can be obtained. Compared with the traditional material, the glass fiber reinforced epoxy resin material effectively improves the mechanical properties of the composite material such as bending, impact, compression and the like.
At present, the commonly used manufacturing modes of glider composite material wings comprise processes such as die forming, vacuum cold pressing solidification forming and the like, wherein the die forming requires higher die forging precision and cost; the vacuum cold pressing solidification forming process has the characteristics of simple process, low forming pressure, uniform heating, no need of special equipment and the like, and can form large-size composite material plates. The product is solidified under pressure and has finer structure by adopting a vacuum cold pressing solidification forming process, and the mechanical property of the composite material is improved.
Disclosure of Invention
The invention provides an XPS extruded sheet inner core and epoxy resin composite material glider wing and a preparation method thereof.
The invention adopts the following technical scheme: an XPS extruded sheet inner core and an epoxy resin composite material glider wing are prepared by taking an XPS extruded sheet as an inner core and a glass fiber reinforced D80 epoxy resin composite material skin through vacuum cold press molding.
The method for preparing the XPS extruded sheet inner core and the epoxy resin composite material glider wing comprises the following specific steps:
(1) preparing an inner core of the wing: firstly, cutting an XPS extruded sheet inner core: drawing a wing section diagram by using Profile according to the geometrical parameters of the wing, and cutting an XPS extruded sheet inner core; sequentially polishing the wing tips by 500-1500-mesh sand paper, and ensuring the smooth surface of the inner core; marking the position with the maximum thickness as the position of the beam, and then uniformly paving T700S 12K carbon filaments on the upper surface and the lower surface of the beam by using 3M77 glue spraying, wherein the paving thickness of the carbon filaments is 0.05mm, and the paving width of the carbon filaments is 15mm, as shown in figure 3; preparing 5g of D80 epoxy resin, uniformly coating the D80 epoxy resin on the T700S 12K carbon filament, and standing for 10 hours to solidify the D80 epoxy resin;
(2) preparing the glass fiber/D80 epoxy resin composite material skin:
a. cutting glass fiber cloth and PVC: cutting PVC and glass fiber cloth with the same size; cutting 2 PVC films which are 3mm larger than the inner core tightly attached to the upper surface and the lower surface of the inner core, marking the upper surface and the lower surface, and spraying paint; standing for 1 day, and air drying;
b. preparing an epoxy resin: precisely weighing D80 epoxy resin according to the weight ratio of the D80 epoxy resin to the curing agent of 100:30, and precisely dripping the curing agent; stirring for 50-100s, standing for 2min, and pouring into a tray to prepare for brushing glue;
c. hand pasting and layering: placing PVC on the bottom layer, laying glass fiber cloth with the thickness of 0.06 mm above the PVC film at an angle of 0 degree, and brushing epoxy resin on the glass fiber cloth to soak the glass fiber cloth; cutting off the redundant glass fiber cloth after reserving a 3mm allowance along the edge of the PVC, and leaving no drawn wire; finally, filling epoxy resin on the cut PVC; brushing epoxy resin on the beam, the front edge and the rear edge of the inner core to enable the beams, the front edge and the rear edge to be soaked; wrapping the inner core with PVC, and fixing the position of the adhesive tape; wrapping the fixed inner core with a layer of toilet paper;
d. and (3) vacuum cold pressing and curing: packaging the whole kernel by using a vacuum bag, placing a wing bed above and below the vacuum bag, placing a weight of 4.5-5.5kg on the upper wing bed for shaping, and curing for 10 hours when the air exhaust pressure reaches 0.7 psi;
(3) polishing and trimming the cut edges to finish the product; and (4) unsealing a vacuum bag, taking out the inner core, trimming and trimming, and polishing by using sand paper to soak water in sequence to obtain the XPS extruded sheet inner core and the epoxy resin composite material glider wing.
The airfoil of the wing is MH 43. The geometrical parameters of the airfoil are shown in the following table:
and (3) sequentially polishing by using 400-2000-mesh sand paper.
The thickness of the PVC is 0.3 mm; the thickness of the glass fiber cloth is 0.06 mm.
The composite material wing of the glider is manufactured by taking the XPS extruded sheet as the inner core of the wing and the glass fiber reinforced D80 epoxy resin composite material as the outer skin of the wing and by means of a vacuum cold pressing and curing molding process.
The composite material wing of the glider is manufactured by taking the XPS extruded sheet as the inner core of the wing and the glass fiber reinforced D80 epoxy resin composite material as the outer skin of the wing through a vacuum cold pressing curing molding process, and the glider of one composite material wing is successfully tried to fly. Compared with wood, the XPS extruded sheet has the characteristics of light weight, high compressive strength and high impact resistance due to a completely closed cell type foaming chemical structure and a cellular physical structure, and has good stability and corrosion resistance in a long-term use process; glass fibers have characteristics such as good insulation properties, heat resistance, and high mechanical strength, compared to glass fiber reinforced plastics. The wings are made of light materials and composite materials, so that the whole weight of the glider is reduced, and the flying efficiency and the mechanical strength are improved.
Drawings
FIG. 1 is a flow chart of a process for fabricating a composite glider wing;
FIG. 2 is a cross-sectional view of an airfoil of MH 43;
FIG. 3 is a position diagram of carbon filament placement.
Detailed Description
To further illustrate the technical solution of the present invention, the present invention will be further described with reference to specific embodiments.
As shown in fig. 1, the fabrication of a composite glider wing includes the following steps:
(1) manufacturing an inner core of the wing:
firstly, cutting an XPS extruded sheet inner core: cutting the XPS extruded sheet core according to the specific geometrical parameters in Table 1 and a profile drawing of an airfoil profile MH43 using Profile; sequentially polishing the wing tips by 500-1500-mesh sand paper, and ensuring the smooth surface of the inner core; the position of the maximum thickness is marked as the position of the beam, and then 3M77 is used for spraying glue to evenly lay T700S 12K carbon wires on the upper surface and the lower surface of the beam, wherein the laying thickness of the carbon wires is 0.05mm, and the width of the carbon wires is 15mm, as shown in figure 3. Preparing about 5g of D80 epoxy resin, uniformly coating the D80 epoxy resin on the T700S 12K carbon filament, and standing for 10 hours to solidify the D80 epoxy resin;
TABLE 1
(2) Preparing the glass fiber/D80 epoxy resin composite material skin:
the preparation process of the composite material skin comprises the following steps:
a. cutting glass fiber cloth and PVC: and cutting PVC and glass fiber cloth with the same size. And cutting 2 PVC films which are slightly larger than the inner core by 3mm closely to the upper surface and the lower surface of the inner core, and spraying paint after marking the upper surface and the lower surface. Standing for about 1 day and air drying;
b. preparing an epoxy resin: placing the electronic scale on a horizontal desktop, resetting and calibrating, then placing the disposable paper cup on the electronic scale, and resetting; accurately controlling the amount of D80 epoxy resin, and pouring the resin into a paper cup; accurately dropping a proper amount of curing agent by using a rubber head dropper according to the weight ratio of the D80 epoxy resin to the curing agent of about 100: 30; taking off the paper cup, turning off the electronic scale, stirring for about 1min, and standing for 2 min. Finally pouring the mixture into a tray for preparing glue brushing;
c. hand pasting and layering: placing PVC with the thickness of 0.3mm on the bottom layer, laying glass fiber cloth with the thickness of 0.06 mm on the PVC film at an angle of 0 degree, and brushing epoxy resin on the glass fiber cloth to soak the glass fiber cloth; and (5) cutting off the redundant glass fiber cloth after reserving a 3mm allowance along the edge of the PVC, and paying attention to no residual drawn wires. Finally, supplementing a little epoxy resin on the cut PVC; brushing a proper amount of epoxy resin on the beam, the front edge and the rear edge of the inner core to enable the beams, the front edge and the rear edge to be soaked; wrapping the inner core with PVC, and fixing the position with adhesive tape; wrapping the fixed inner core with a layer of toilet paper;
d. and (3) vacuum cold pressing and curing: packaging the whole inner core by using a vacuum bag, placing a wing bed above and below the bag, placing a weight of about 5kg on the upper wing bed for shaping, wherein the air exhaust pressure reaches 0.7psi, and curing for 10 hours;
(3) polishing, trimming and trimming edges, and finally finishing the product:
the vacuum bag is unsealed, the inner core is taken out, the cut edge is trimmed, and the sand paper with 400-mesh and 2000-mesh is sequentially used for soaking and polishing;
the above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations are also considered to be within the protective scope of the present invention.
Claims (5)
1. The utility model provides a XPS extruded sheet kernel and epoxy composite material glider wing which characterized in that: the composite material is prepared by taking an XPS extruded sheet as an inner core and a glass fiber reinforced D80 epoxy resin composite material skin through vacuum cold press molding.
2. A method of making an XPS extruded sheet inner core and epoxy composite glider wing according to claim 1, wherein: the method comprises the following specific steps:
(1) preparing an inner core of the wing: firstly, cutting an XPS extruded sheet inner core: drawing a wing section diagram by using Profile according to the geometrical parameters of the wing, and cutting an XPS extruded sheet inner core; sequentially polishing the wing tips by 500-1500-mesh sand paper, and ensuring the smooth surface of the inner core; marking the position with the maximum thickness as the position of the beam, and then uniformly paving T700S 12K carbon filaments on the upper surface and the lower surface of the beam by using 3M77 glue spraying, wherein the paving thickness of the carbon filaments is 0.05mm, and the paving width of the carbon filaments is 15 mm; preparing 5g of D80 epoxy resin, uniformly coating the D80 epoxy resin on the T700S 12K carbon filament, and standing for 10 hours to solidify the D80 epoxy resin;
(2) preparing the glass fiber/D80 epoxy resin composite material skin:
a. cutting glass fiber cloth and PVC: cutting PVC and glass fiber cloth with the same size; cutting 2 PVC films which are 3mm larger than the inner core tightly attached to the upper surface and the lower surface of the inner core, marking the upper surface and the lower surface, and spraying paint; standing for 1 day, and air drying;
b. preparing an epoxy resin: precisely weighing D80 epoxy resin according to the weight ratio of the D80 epoxy resin to the curing agent of 100:30, and precisely dripping the curing agent; stirring for 50-100s, standing for 2min, and pouring into a tray to prepare for brushing glue;
c. hand pasting and layering: placing PVC on the bottom layer, laying glass fiber cloth with the thickness of 0.06 mm above the PVC film at an angle of 0 degree, and brushing epoxy resin on the glass fiber cloth to soak the glass fiber cloth; cutting off the redundant glass fiber cloth after reserving a 3mm allowance along the edge of the PVC, and leaving no drawn wire; finally, filling epoxy resin on the cut PVC; brushing epoxy resin on the beam, the front edge and the rear edge of the inner core to enable the beams, the front edge and the rear edge to be soaked; wrapping the inner core with PVC, and fixing the position of the adhesive tape; wrapping the fixed inner core with a layer of toilet paper;
d. and (3) vacuum cold pressing and curing: packaging the whole kernel by using a vacuum bag, placing a wing bed above and below the vacuum bag, placing a weight of 4.5-5.5kg on the upper wing bed for shaping, and curing for 10 hours when the air exhaust pressure reaches 0.7 psi;
(3) polishing and trimming the cut edges to finish the product; and (4) unsealing a vacuum bag, taking out the inner core, trimming and trimming, and polishing by using sand paper to soak water in sequence to obtain the XPS extruded sheet inner core and the epoxy resin composite material glider wing.
3. The method of making an XPS extruded sheet inner core and epoxy composite glider wing according to claim 2, wherein: the airfoil of the wing is MH 43; the geometrical parameters of the airfoil are shown in the following table:
4. the method of making an XPS extruded sheet inner core and epoxy composite glider wing according to claim 2, wherein: and (3) sequentially polishing by using 400-2000-mesh sand paper.
5. The method of making an XPS extruded sheet inner core and epoxy composite glider wing according to claim 2, wherein: the thickness of the PVC is 0.3 mm; the thickness of the glass fiber cloth is 0.06 mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911108300.0A CN111055517B (en) | 2019-11-13 | 2019-11-13 | XPS extruded sheet inner core and epoxy resin composite material glider wing and preparation method thereof |
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| CN201911108300.0A CN111055517B (en) | 2019-11-13 | 2019-11-13 | XPS extruded sheet inner core and epoxy resin composite material glider wing and preparation method thereof |
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| CN111055517A true CN111055517A (en) | 2020-04-24 |
| CN111055517B CN111055517B (en) | 2021-06-11 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112140593A (en) * | 2020-09-09 | 2020-12-29 | 长安大学 | On-site forming device and method for non-linear FRP (fiber reinforced plastic) ribs |
| CN114368169A (en) * | 2022-01-11 | 2022-04-19 | 河北福莱卡航空科技有限公司 | Rapid forming process for light airplane |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100065689A1 (en) * | 2008-09-17 | 2010-03-18 | Eads Deutschland Gmbh | Load introducing element |
| CN105416567A (en) * | 2015-11-13 | 2016-03-23 | 中国人民解放军国防科学技术大学 | Skin, unmanned aerial vehicle wing, manufacturing method of unmanned aerial vehicle wing, empennage and manufacturing method of empennage |
| CN109968693A (en) * | 2019-03-15 | 2019-07-05 | 安徽云翼航空技术有限公司 | A kind of processing method of 150kg grades or less Fixed Wing AirVehicle shell |
-
2019
- 2019-11-13 CN CN201911108300.0A patent/CN111055517B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100065689A1 (en) * | 2008-09-17 | 2010-03-18 | Eads Deutschland Gmbh | Load introducing element |
| CN105416567A (en) * | 2015-11-13 | 2016-03-23 | 中国人民解放军国防科学技术大学 | Skin, unmanned aerial vehicle wing, manufacturing method of unmanned aerial vehicle wing, empennage and manufacturing method of empennage |
| CN109968693A (en) * | 2019-03-15 | 2019-07-05 | 安徽云翼航空技术有限公司 | A kind of processing method of 150kg grades or less Fixed Wing AirVehicle shell |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112140593A (en) * | 2020-09-09 | 2020-12-29 | 长安大学 | On-site forming device and method for non-linear FRP (fiber reinforced plastic) ribs |
| CN114368169A (en) * | 2022-01-11 | 2022-04-19 | 河北福莱卡航空科技有限公司 | Rapid forming process for light airplane |
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