CN202088536U - Special honeycomb composite material for minitype unmanned verticraft - Google Patents
Special honeycomb composite material for minitype unmanned verticraft Download PDFInfo
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- CN202088536U CN202088536U CN2011201126687U CN201120112668U CN202088536U CN 202088536 U CN202088536 U CN 202088536U CN 2011201126687 U CN2011201126687 U CN 2011201126687U CN 201120112668 U CN201120112668 U CN 201120112668U CN 202088536 U CN202088536 U CN 202088536U
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Abstract
The utility model relates to a special honeycomb composite material for the minitype unmanned verticraft, comprising a layered composite structure of a panel and a honeycomb sandwich bonded by the adhesive, the panel comprises a layered composite structure of a outer panel, the honeycomb sandwich and an inner panel, wherein the outer panel orderly consists of an epoxy varnish, a topcoat and an outer glass fiber layer; the inner panel orderly consists of an inner glass fiber layer, a carbon fiber mixed fabric layer; the honeycomb sandwich is fixed between the outer glass fiber layer of the outer panel and the inner glass fiber layer of the inner panel and each of the layers is used thermosetting resin to splice by the die, then which forms a finished product. The composite material has high strength in integrally connection, lightweight, bending stiffness, flight wind resistance ability; the effect of sound insulation, heat insulation, and resonance effect is good; the composite material has fire protection, moistureproof, wear resistance, corrosion resistant, anti- dust, the flatness of the forming surface is high, the thermal expansion and contraction deformation is small and the honeycomb groove is not obvious.
Description
Technical field
The utility model belongs to aviation field, relates to unmanned plane, the special-purpose cellular composite material of especially a kind of SUAV.
Background technology
China's SUAV industry is started late, generally be with reference to external active service unmanned plane design aspect the equipment of profile, specification and lift-launch in the design process, but the fiberglass manufacture craft horizontal aspect design route outmoded, cause some model unmanned planes aspects such as body weight, structural design and the strength of materials with external nineties like product approximate, quantum jump too not.
In recent years, the new technology and the new material development of China's composite industry are very fast, composite is a kind of brand-new material, on aircraft, use and be in developing stage, because of its material light weight, excellent in cushion effect, temperature deformation is little (" creep " that the difference of Yin Wendu causes), anti-aging (serviceable bife prolongation), characteristics such as anticorrosion, thunder and lightning, static and various storeroom compatibility height are used very extensive in many industries.
The honeycomb composite construction is used more extensive aboard, as aerofoil, on-deck, rudder face, wallboard, floor, radome etc.; At aerospace field, as inner trim panels, radome, the guided missile wing etc., generally make cellular material with aluminium, magnesium alloy and carbon fibre material, in light weight, intensity height after the moulding.The honeycomb composite construction mainly is the layered composite structure that is become by adhesive bonds by panel (covering) and comb core, space flight and aviation industry cellular material, all be more abundant and the heavy model of material, single face is more with the panel sealing, and other industry is used more is not suitable for using.
By retrieval, do not find the open source literature identical as yet with present patent application.
The utility model content
The utility model purpose is to overcome the deficiencies in the prior art part, provides a kind of SUAV in light weight, that intensity is high, scientific structure, life-span are long, with low cost special-purpose cellular composite material.
The utility model solves its technical problem and is achieved through the following technical solutions:
The special-purpose cellular composite material of a kind of SUAV, the layered composite structure that becomes by adhesive bonds by panel and honeycomb interlayer, it is characterized in that: described panel is by outer panels, honeycomb interlayer, the layered composite structure that wainscot constituted, wherein outer panels is successively by the epoxy finishing varnish, finish paint, outer glass layer constitutes, wainscot is successively by the lining glass layer, carbon fiber shuffling layer of cloth constitutes, honeycomb interlayer be packed in the outer glass layer of outer panels and wainscot between the glass layer, it is bonding that each layer adopts thermosetting resin to carry out by mould, solidify the back finished product.
And described thermosetting resin is an epoxy resin, comprises bisphenol A type epoxy resin, bisphenol-s epoxy resin, bisphenol f type epoxy resin.
And the thickness of described glass fabric is 0.1mm-0.5mm; Carbon fiber shuffling cloth is that carbon cloth and the braiding of glass fabric longitude and latitude form its thickness 0.1mm-0.5mm; Described finish paint is ammonia ester lacquer; Described finishing varnish is a polyester lacquer class.
And described honeycomb interlayer is made of honeycomb core and comb core, and every purpose diameter of honeycomb core is 3mm, height 3mm; Comb core is aluminium foil, aramid fiber paper, glassine paper or brown paper.
And, in the honeycomb core of connecting portion, bearing position, add glass microballoon.
Advantage of the present utility model and good effect are:
1, the whole bonding strength height of this composite, light weight, bending stiffness is big, and flight Wind-Pressure Resistance ability is strong.
2, this composite sound insulation, heat insulation, anti-resonance vibration is effective.
3, this composite fire prevention, protection against the tide, wear-resisting, anticorrosive, desertification dirt.
4, this composite material forming rear surface flatness height, the distortion of expanding with heat and contract with cold is little, and the honeycomb groove is not obvious.
Description of drawings
Fig. 1 is a structure section schematic diagram of the present utility model.
The specific embodiment
The utility model is described in further detail by specific embodiment below in conjunction with accompanying drawing, and following examples are descriptive, are not determinate, can not limit protection domain of the present utility model with this.
The special-purpose cellular composite material of a kind of SUAV, referring to Fig. 1, the layered composite structure that becomes by adhesive bonds by panel and honeycomb interlayer.Wherein, panel comprises: outer panels is made of epoxy finishing varnish 1, finish paint 2, outer glass layer 3, wainscot is made of lining glass layer 5, carbon fiber shuffling layer of cloth 6, honeycomb interlayer 4 be packed in the outer glass layer of outer panels and wainscot between the glass layer.The section structure of this composite outwards is followed successively by from the lining: carbon fiber shuffling layer of cloth, lining glass layer, honeycomb core interlayer, outer glass layer, finish paint and epoxy finishing varnish.It is bonding that above-mentioned each layer adopts thermosetting resin to carry out by mould, solidify the back finished product.
In the present embodiment, the thermosetting resin of employing is an epoxy resin, comprises bisphenol A type epoxy resin, bisphenol-s epoxy resin, and bisphenol f type epoxy resin, effect is bonding or permeates bonding each material.The thickness of used glass fabric is 0.1mm-0.5mm, and effect is to connect and the increase planar strength for institutional framework.The thickness 0.1mm-0.5mm of used carbon fiber shuffling cloth is formed by carbon cloth and the braiding of glass fabric longitude and latitude, and effect is for increasing structural strength and weight reduction.The honeycomb interlayer that is adopted is made of honeycomb core and comb core, and honeycomb core is by setting the order number as required, and every purpose diameter is 3mm, height 3mm; Comb core is aluminium foil, aramid fiber paper, glassine paper and brown paper etc., installs glass microballoon additional in the honeycomb core that belongs to connecting portion, bearing position, to improve the intensity at this position.
The outstanding advantage of honeycomb sandwich construction is: light weight, bending stiffness is big.The finish paint that is adopted is ammonia ester lacquer, and effect is to beautify and prevent surface aging.The finishing varnish that is adopted is polyester lacquer class, and effect is to increase fineness and protection finish paint surface.
The SUAV of the utility model manufacturing, flexibility at the design configuration curved surface, extend and to use above the thickness more than the 3mm when laying, the density spacing of honeycomb core should be between 3-4mm, through multiple test and test, should not use almag and carbon fiber cellular material, should use the aramid fiber paper material, it and epoxy resin-matrix have fine compatibility.
In this kind of buying comb core material process, find, the product that does not also have this specification at present both at home and abroad, the model that the material of space flight and aviation industry honeycomb all is more abundant and material is heavy, single face is more with panel sealing, and other industry is used more is not suitable for using.
Can not satisfy in demand under the situation of design, we have designed drawing voluntarily, by manufacturer's this honeycomb core that this suitable SUAV " honeycomb composite construction " technology is used for I have produced specially (please note: this is not have panel to connect) of professional production cellular material.Present domestic unmanned plane industry does not also have producer to use this up-to-date comb core material.
Concise and to the point manufacturing process of the present utility model is:
(1) material is prepared:
(2) enamelled coating spray: three times finishing varnish of spray in the mould die cavity after cleaning, thickness of paint layer is controlled at 0.2-0.3mm; Directly spray finish paint then three times, and levelling makes enamelled coating even, normal temperature cure;
(3) brush epoxy resin, lay glass fabric: on enamelled coating, brush epoxy resin, lay glass cloth then, and with hairbrush glass fabric brush on epoxy resin and to be put down;
(4) lay honeycomb core, reinforcement: lay honeycomb core on glass fabric, afterwards, carry out reinforcement in the force part, as at connecting portion, bearing position, in honeycomb core, install glass microballoon additional, and then glass fabric and the fine shuffling cloth of carbon are spread, the brush ring epoxy resins, with the microballon encapsulation of honeycomb core, after the normal temperature cure, the demoulding;
(5) Vacuum shaping: the member after the above-mentioned demoulding is put into vacuum bag, put into greenhouse and vacuumize, 80-100 ℃ of greenhouse temperature, negative pressure-0.8 MPa, is taken out at 3 hours time; Vacuum bag adopts to have good ductility and high-intensity nylon membrane or similar material and makes, and bonds together with the sealing joint strip and the mould of viscosity, in product is wrapped in, vacuumizes product is exerted pressure.Usually airfelt will be placed with so that the vacuum guide passage is unobstructed in the vacuum bag.
(6) matched moulds, deburring: with two member matched moulds, interface adopts epoxy resin that interface is encapsulated with carbon fiber wire, and put into greenhouse then and solidify, 80-100 ℃ of greenhouse temperature, 3 hours time, go out shell, clear limit perforating, installing component get product.
The cellular composite material of the utility model manufacturing, by detecting, environment temperature-40 ℃～+ 55 ℃, humidity be can not produce in 95% scope distortion and " creep ", antiacid alkali, bearing vibration frequency 20Hz～2000Hz can not rupture and come unglued. and the goods appearance and size with this explained hereafter detects, and 10/packet size error in length meets relevant national standard for ± 0.01mm..
Claims (4)
1. the special-purpose cellular composite material of a SUAV, the layered composite structure that becomes by adhesive bonds by panel and honeycomb interlayer, it is characterized in that: described panel is by outer panels, honeycomb interlayer, the layered composite structure that wainscot constituted, wherein outer panels is successively by the epoxy finishing varnish, finish paint, outer glass layer constitutes, wainscot is successively by the lining glass layer, carbon fiber shuffling layer of cloth constitutes, honeycomb interlayer be packed in the outer glass layer of outer panels and wainscot between the glass layer, it is bonding that each layer adopts thermosetting resin to carry out by mould, solidify the back finished product.
2. the special-purpose cellular composite material of SUAV according to claim 1, it is characterized in that: the thickness of described glass fabric is 0.1mm-0.5mm; Carbon fiber shuffling cloth is that carbon cloth and the braiding of glass fabric longitude and latitude form its thickness 0.1mm-0.5mm; Described finish paint is ammonia ester lacquer; Described finishing varnish is a polyester lacquer class.
3. the special-purpose cellular composite material of SUAV according to claim 1, it is characterized in that: described honeycomb interlayer is made of honeycomb core and comb core, and every purpose diameter of honeycomb core is 3mm, height 3mm; Comb core is aluminium foil, aramid fiber paper, glassine paper or brown paper.
4. according to claim 1 or the special-purpose cellular composite material of 3 described SUAVs, it is characterized in that: in the honeycomb core of connecting portion, bearing position, add glass microballoon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201126687U CN202088536U (en) | 2011-04-15 | 2011-04-15 | Special honeycomb composite material for minitype unmanned verticraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201126687U CN202088536U (en) | 2011-04-15 | 2011-04-15 | Special honeycomb composite material for minitype unmanned verticraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202088536U true CN202088536U (en) | 2011-12-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011201126687U Expired - Fee Related CN202088536U (en) | 2011-04-15 | 2011-04-15 | Special honeycomb composite material for minitype unmanned verticraft |
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| Country | Link |
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| CN (1) | CN202088536U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102241166A (en) * | 2011-04-15 | 2011-11-16 | 天津全华时代航天科技发展有限公司 | Special-purposed cellular composite material used for small unmanned air vehicle |
| CN105034477A (en) * | 2015-05-20 | 2015-11-11 | 奇瑞汽车股份有限公司 | Honeycomb sandwiched plate used in vehicles and preparation method of same |
| CN108407331A (en) * | 2018-03-05 | 2018-08-17 | 成都凯迪精工科技有限责任公司 | A kind of small drone answers material rear body manufacturing method |
-
2011
- 2011-04-15 CN CN2011201126687U patent/CN202088536U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102241166A (en) * | 2011-04-15 | 2011-11-16 | 天津全华时代航天科技发展有限公司 | Special-purposed cellular composite material used for small unmanned air vehicle |
| CN105034477A (en) * | 2015-05-20 | 2015-11-11 | 奇瑞汽车股份有限公司 | Honeycomb sandwiched plate used in vehicles and preparation method of same |
| CN108407331A (en) * | 2018-03-05 | 2018-08-17 | 成都凯迪精工科技有限责任公司 | A kind of small drone answers material rear body manufacturing method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20111228 Termination date: 20170415 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |