CN101227029B - Composite material satellite antenna reflection surface and manufacturing process thereof - Google Patents
Composite material satellite antenna reflection surface and manufacturing process thereof Download PDFInfo
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- CN101227029B CN101227029B CN2008100567219A CN200810056721A CN101227029B CN 101227029 B CN101227029 B CN 101227029B CN 2008100567219 A CN2008100567219 A CN 2008100567219A CN 200810056721 A CN200810056721 A CN 200810056721A CN 101227029 B CN101227029 B CN 101227029B
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Abstract
The invention relates to the technology field of communication and observation control, which provides a composite material satellite antenna reflection plane and the method for preparation. The composite material satellite antenna reflection plane adopts 3D glass fiber felt as core material, and adopts carbon fiber composite as covering sandwich type composite material satellite antenna reflection plane. Compared with the prior art, the invention has the following advantages: 1. shaped surface accuracy of the satellite antenna reflection plane is high and satellite signal gain is great, 2. quality of the reflection plane is light, and is fit for transportation, in particular to fitting for vehicle satellite antenna and portable satellite antenna, 3. integrality of the reflection plane isgood, hardness is great, thereby being capable of preferably retaining the shaped surface accuracy and bearing more wind load and impact load, 4. adopting the 3D glass fiber felt as the core material, the invention inaugurates a new technology of the sandwich composite material satellite antenna reflection plane, the technology is capable of producing heavy caliber satellite antenna reflection plane, and which is simple in manufacturing technology comparatively and low in the cost.
Description
Technical field
The present invention relates to communication and observation and control technology field, particularly relate to a kind of composite material satellite antenna reflection surface and manufacture method thereof.
Background technology
Carbon fibre composite (CFRP) is with its minimum coefficient of linear expansion, very high specific strength, than modulus of elasticity, and the designability of physics, mechanical property and the extremely favor of Aeronautics and Astronautics department.Simultaneously the ratio that amasss because of its modulus of elasticity and density, coefficient of linear expansion is higher than metal material far away, and is described as desirable antenna structure material by the antenna brainstrust.
Along with the continuous progress of aerospace flight technology, industrial relatively advanced country has just developed the forming technique of CFRP as far back as the seventies, and CFRP is widely used in spacecraft, and the structural material of satellite antenna has been that CFRP rules all the land at present.Along with people are more and more higher to the requirement of communication quality, the CFRP parabolic antenna has been used to the millimeter wave of the various bores in ground, the high accuracy of submillimeter wave, the satellite antenna of high stability.The extensive use of CFRP and to the research of its application technology has promoted further developing of high accuracy parabolic antenna.
The version of composite material antenna reflective face can be divided into two kinds basically: a kind of is shell structure, and another kind is a sandwich.No matter adopt what version, all be to guarantee that antenna has higher profile precision, satisfy technical indicators such as the desired strength and stiffness of Service Environment being prerequisite.The Antenna Reflector Based on Carbon Fibre Composites plate of thin board type structure is thin, heat conduction is fast, the temperature gradient of face, the back of the body and side that the sunlight uneven irradiation is caused is little, thermal stress deformation is little, more help the maintenance of adverse circumstances mo(u)ld bottom half surface accuracy, but technical difficulty is bigger in the thin shell type antenna reflective face forming process, has hindered the development of thin shell type composite material antenna reflective face.The antenna of sandwich is that honeycomb or the foamed material with exterior skin in certain thickness and lightweight is that sandwich forms the thicker structure in cross section, be characterized in light weight, good rigidly has the ability of resisting strain deformation preferably, is to ensure antenna profile precision one of version preferably.
The core of present sandwich composite material antenna surface mainly is divided into foam core and cellular sandwich.Foam core can be after the moulding of reflecting surface shell is finished, foam and obtain foam sandwich construction in shell structure, injecting resin and blowing agent, also can finish by in advance foam core material being made, carry out back processing then, put into shell structure again, with adhesive foam and shell being sticked together obtains foam sandwich construction.It is inhomogeneous that the former is prone to foaming, and processing and forming second time of foaming easily takes place after finishing, and causes the reduction of antenna reflective face profile precision, influences communication quality.The latter is in the secondary processing process of foam core material, and very difficult core is worked into shell matches, thereby causes the core filled composite material structure defective to occur.
Adopt the composite material antenna surface of cellular sandwich to have very high integral rigidity, be widely applied to composite material antenna surface field at present, but because aluminium cellular sandwich production and processing difficulty, its core need be through loaded down with trivial details technologies such as surface treatment and seal glue, and because there is very big difficulty in the aluminium honeycomb when making curved-surface structure, particularly when making the satellite antenna reflection surface of large curved surface, must adopt piecemeal aluminium honeycomb to splice, caused like this fault of construction having occurred in the cellular sandwich composite inner, though between aluminium honeycomb joint, carried out gluing, but the coefficient of linear expansion that is used for carbon fibre composite is extremely low, and often the coefficient of linear expansion of adhesive is all bigger, this makes the reflecting surface covering possibly and deforms because expand with heat and contract with cold, and reduces the profile precision, influences communication quality.
Summary of the invention
In view of above defective, the object of the present invention is to provide a kind of composite material satellite antenna reflection surface and manufacture method thereof, this manufacture method is simple, its profile precision height of prepared composite material satellite antenna reflection surface, the integral rigidity height can also be made bigbore antenna reflective face easily by this manufacture method.
In order to reach above purpose, this kind composite material satellite antenna reflection surface provided by the invention, it is and adopts the 3D glass mat is core, adopts the sandwich type composite material satellite antenna reflection surface of carbon fibre composite as covering.
Wherein said carbon fibre composite is the composition of carbon fiber and resin, and described carbon fiber can be carbon fibre fabric or unidirectional carbon fiber dimension etc., described resin can be resins such as epoxy resin, unsaturated polyester resin, bimaleimide resin or cyanate ester resin wherein one or more.
3D braided glass fibre felt is a kind of novel composite material core that occurs recently, have only a few peoples that it is applied in the manufacturing of bullet train and yacht both at home and abroad, its special structure and excellent performance have been given with the many characteristics of its composite material as sandwich, have also solved the insurmountable problem of many other cores.The present invention adopts this kind 3D glass mat as core, has obtained profile precision height, the composite material satellite antenna reflection surface that integral rigidity is high.
The present invention also provides this kind composite material satellite antenna reflection surface manufacture method, and it mainly may further comprise the steps:
A. make the antenna reflective face mould;
The carbon fiber shop that b. will cut is in advance applied at die surface, and release cloth, flow-guiding cloth and vacuum bag etc. are applied in the shop in the above then, and the blended rubber band coheres vacuum bag and mould;
C. with vacuum pump the air of vacuum bag the inside is extracted out as far as possible, after keeping 5 to 10 minutes, the resin that is added with curing agent is injected vacuum bag by pipeline, after all being full of resin in the whole vacuum bag, cut off resin supply line and vacuum pipe, keep the vacuum bag internal pressure;
D. mould is pushed between curing, temperature is controlled at 40-80 ℃ between curing, releases between curing after being heating and curing 2-8 hour again, sloughs above-mentioned vacuum bag, flow-guiding cloth and release cloth after the cooling, obtains the carbon fibre composite covering;
E. apply the 3D glass mat on above-mentioned composite material skin upper berth, on the 3D glass mat, apply the resin that has added curing agent with brush, and with roller that resin-coating is even;
F. push mould between curing once more, curing temperature is 40-80 ℃, solidify and release between curing after 2-6 hour, apply carbon fiber then in the 3D glass mat upper berth of having solidified, release cloth, flow-guiding cloth and vacuum bag etc. are applied in the shop thereon again, the blended rubber band coheres vacuum bag and mould, and repeating step c and steps d successively promptly obtain composite material satellite antenna reflection surface then.
The present invention has following advantage compared with prior art:
1. satellite antenna reflection surface profile precision height, the satellite-signal gain is big;
2. the reflecting surface light weight more is applicable to transportation, is specially adapted to vehicle-mounted satellite antenna and portable satellite antenna;
3. reflecting surface good integrity, rigidity is big, and the maintenance surface accuracy can bear bigger wind load and shock loading better;
4. the 3D glass mat of the present invention's employing has been opened up the new technology of core filled composite material satellite antenna reflection surface as core, adopts this technology, can make bigbore satellite antenna reflection surface, and manufacture method is simple relatively, and cost reduces.
Description of drawings
Fig. 1 is a kind of composite material satellite antenna reflection surface schematic partial cross-sectional view provided by the invention;
Fig. 2 is the preferred embodiment flow chart of a kind of composite material satellite antenna reflection surface manufacture method provided by the invention.
Embodiment
Below in conjunction with Figure of description and embodiment the technical scheme of inventing is further specified:
As shown in Figure 1, this kind composite material satellite antenna reflection surface provided by the invention, it is a sandwich, wherein adopts carbon fibre composite as covering 101, adopting the 3D glass mat is core 102.
Again as shown in Figure 2, this kind composite material satellite antenna reflection surface manufacture method provided by the invention, its preferred embodiment specifically may further comprise the steps:
S201. calculate by electricity, design the profile of antenna reflective face;
S202. according to the reflecting surface profile equation that designs, adopt the Pro/E 3 d modeling software to make the virtual product of the mould of antenna reflective face, and check repeatedly, up to reaching design effect;
S203. the virtual product according to the antenna reflective face mould produces the antenna reflective face mould;
S204. mould is carried out suitable surface treatment, to satisfy the requirement of the reflecting surface profile precision and the demoulding;
S205. apply release agent at die surface;
S206. the carbon fibre fabric that will cut in advance applies at die surface according to layer design shop, shop, spreads in the above successively then and applies release cloth, flow-guiding cloth and vacuum bag etc., and the blended rubber band coheres vacuum bag and mould;
S207. with vacuum pump the air of vacuum bag the inside is extracted out as far as possible, check whether vacuum bag leaks gas, after confirming under the gastight prerequisite of vacuum bag, keeping about 10 minutes, the epoxy resin that has added curing agent is injected vacuum bag by pipeline, after all being full of resin in the whole vacuum bag, cut off resin supply line and vacuum pipe, keep the vacuum bag internal pressure, curing agent is 4,4 '-two amido p-phenylenediamine (PPD), the consumption of curing agent are the 20wt.% of content of epoxy resin;
S208. mould is pushed between curing, heating makes its curing, and temperature is controlled at 50 ℃ between curing, after the about 4 hours resin full solidification, mould is released between curing, sloughs above-mentioned vacuum bag, flow-guiding cloth and release cloth after the cooling, obtains the carbon fibre composite covering;
S209. apply the 3D glass mat on the carbon fibre composite covering upper berth of forming, the thickness of 3D glass mat is 20mm, on the 3D glass mat, apply the epoxy resin that has added curing agent with brush, and it is resin-coating is even with roller, curing agent is 4,4 '-two amido p-phenylenediamine (PPD), the consumption of curing agent are the 20wt.% of content of epoxy resin;
S210. push mould between curing once more, curing temperature is 60 ℃, be 5 hours curing time, after treating that resin solidification finishes, between solidifying, release mould, can spread deposited carbon fibre fabric in the above, spread in the above successively then and apply release cloth, flow-guiding cloth and vacuum bag etc., the blended rubber band coheres vacuum bag and mould;
S211. with vacuum pump the air of vacuum bag the inside is extracted out as far as possible, check whether vacuum bag leaks gas, after confirming under the gastight prerequisite of vacuum bag, keeping about 10 minutes, the epoxy resin that has added curing agent is injected vacuum bag by pipeline, after all being full of resin in the whole vacuum bag, cut off resin supply line and vacuum pipe, keep the vacuum bag internal pressure, curing agent is 4,4 '-two amido p-phenylenediamine (PPD), the consumption of curing agent are the 20wt.% of content of epoxy resin;
S212. mould pushes between curing again, heating makes its curing, temperature is controlled at 50 ℃ between curing, after the about 4 hours resin full solidification, between mould release solidified, can obtain sandwich that the 3D glass mat is a core, carbon fibre composite composite material satellite antenna reflection surface after the cooling and demolding as covering.
The 1.5 nano composite material satellite antenna reflection surface profile precision height that adopt the present invention to make, integral rigidity is good.Adopt the partial parameters of the satellite antenna that this reflecting surface makes as follows:
1. transmitting gain (dB) 45.9
2. receiving gain (dB) 44.3
Directional diagram emission port beamwidth (°) 0.9-3 dB
1.9 -15?dB
4. cross polarization isolation (dB) 〉=38 axial point
〉=35 1dB point
5. weight (kg) 14.5
Working temperature (℃)-25-60
7. working relative humidity 0%-97%
Storage temperature (℃)-40-70
9. store humidity 0% 100%
Work wind resistance (km/h) 〉=72
11. store wind resistance (km/h) 〉=128
Below its summary of the invention has been done to elaborate.For persons skilled in the art, any conspicuous change of under the prerequisite that does not deviate from the principle of the invention it being done can not exceed the protection range of the application's claims.
Claims (6)
1. a composite material satellite antenna reflection surface manufacture method is characterized in that, may further comprise the steps:
A. make the antenna reflective face mould;
The carbon fiber shop that b. will cut is in advance applied at die surface, and release cloth, flow-guiding cloth and vacuum bag etc. are applied in the shop in the above then, and the blended rubber band coheres vacuum bag and mould;
C. with vacuum pump the air of vacuum bag the inside is extracted out as far as possible, after keeping 5 to 10 minutes, the resin that is added with curing agent is injected vacuum bag by pipeline, after all being full of resin in the whole vacuum bag, cut off resin supply line and vacuum pipe, keep the vacuum bag internal pressure;
D. mould is pushed between curing, temperature is controlled at 40-80 ℃ between curing, releases between curing after being heating and curing 2-8 hour again, sloughs above-mentioned vacuum bag, flow-guiding cloth and release cloth after the cooling, obtains the carbon fibre composite covering;
E. apply the 3D glass mat on above-mentioned composite material skin upper berth, on the 3D glass mat, apply the resin that has added curing agent with brush, and with roller that resin-coating is even;
F. push mould between curing once more, curing temperature is 40-80 ℃, solidify and release between curing after 2-6 hour, apply carbon fiber then in the 3D glass mat upper berth of having solidified, release cloth, flow-guiding cloth and vacuum bag etc. are applied in the shop thereon again, the blended rubber band coheres vacuum bag and mould, and repeating step c and steps d successively promptly obtain composite material satellite antenna reflection surface then.
2. a kind of composite material satellite antenna reflection surface manufacture method according to claim 1 is characterized in that described step a specifically may further comprise the steps:
(1). calculate by electricity, design the profile of antenna reflective face;
(2). according to the reflecting surface profile equation that designs, adopt the Pro/E 3 d modeling software to make the virtual product of the mould of antenna reflective face, and check repeatedly, up to reaching design effect;
(3). the virtual product according to the antenna reflective face mould produces the antenna reflective face mould;
3. a kind of composite material satellite antenna reflection surface manufacture method according to claim 1 is characterized in that, may further comprise the steps between described step a and the step b again:
(1). mould is carried out suitable surface treatment, to satisfy the requirement of the reflecting surface profile precision and the demoulding;
(2). apply release agent at die surface.
4. a kind of composite material satellite antenna reflection surface manufacture method according to claim 1 is characterized in that, the carbon fiber among the described step b be carbon fibre fabric or unidirectional carbon fiber dimension wherein any one.
5. a kind of composite material satellite antenna reflection surface manufacture method according to claim 1 is characterized in that described resin is one or more in epoxy resin, unsaturated polyester resin, bimaleimide resin or the cyanate ester resin.
6. a kind of composite material satellite antenna reflection surface manufacture method according to claim 1, it is characterized in that the curing agent among the described step c is preferably 4,4 '-two amido p-phenylenediamine (PPD), described resin is preferably epoxy resin, and the consumption of described curing agent is the 20wt.% of content of epoxy resin.
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| CN2008100567219A CN101227029B (en) | 2008-01-24 | 2008-01-24 | Composite material satellite antenna reflection surface and manufacturing process thereof |
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| CN2008100567219A CN101227029B (en) | 2008-01-24 | 2008-01-24 | Composite material satellite antenna reflection surface and manufacturing process thereof |
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| CN101227029B true CN101227029B (en) | 2010-11-10 |
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Cited By (1)
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| CN103042697A (en) * | 2012-12-31 | 2013-04-17 | 北京玻钢院复合材料有限公司 | Integral forming process of carbon fiber antenna reflecting surface |
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| JP平4-166310A 1992.06.12 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103042697A (en) * | 2012-12-31 | 2013-04-17 | 北京玻钢院复合材料有限公司 | Integral forming process of carbon fiber antenna reflecting surface |
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