CN109130336A - A kind of high precision high stability composite material antenna reflective face and preparation method thereof - Google Patents
A kind of high precision high stability composite material antenna reflective face and preparation method thereof Download PDFInfo
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- CN109130336A CN109130336A CN201810796653.3A CN201810796653A CN109130336A CN 109130336 A CN109130336 A CN 109130336A CN 201810796653 A CN201810796653 A CN 201810796653A CN 109130336 A CN109130336 A CN 109130336A
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- grid
- composite material
- antenna reflective
- reflective face
- gusset
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- Physics & Mathematics (AREA)
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- Fluid Mechanics (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
The present invention provides a kind of high precision high stability composite material antenna reflective faces and preparation method thereof, the antenna reflective face includes the surface metal-layer set gradually, inside panel, grid sandwich, exterior skin, the working face side of inside panel is arranged in the surface metal-layer, and the non-working surface side of inside panel is connect with grid sandwich.The cell structure of high stable is applied to the preparation of composite material antenna reflective face by the present invention, efficiently solve the problems, such as the influence of aluminum honeycomb deformation and well-matched CTE to final products surface precision in traditional aluminum honeycomb interlayer manufacturing process, compared to the reflecting surface for using aluminum honeycomb interlayer to prepare, surface precision improves 4 times；Antenna reflective face is prepared using full carbon structure, can not only improve the surface precision of reflecting surface, more significantly reduce the thermal deformation of antenna reflective face.
Description
Technical field
The present invention relates to composite structure functor and preparation method thereof, specially a kind of high precision high stability composite wood
Expect antenna reflective face and preparation method thereof.
Background technique
Composite material is widely used in spacecraft because of excellent characteristics such as its linear expansion coefficient is low, specific strength, specific stiffness height
Product scope.Wherein, antenna reflective face is the Typical Representative of structure-function integration, and the surface precision of working face directly affects
The authenticity of antenna communication signal.However, the increasing lightweight of antenna reflective face, high-precision, high stable demand, to compound
The manufacture of material high precision brings huge challenge, and superelevation surface precision micron order (RMS≤5 μm) and ultralow thermal deformation are (at -80 DEG C
RMS≤6 μm after deformation) requirement it is very harsh, manufacture may influence whether this anti-with any small factor of military service process
Penetrate the surface precision in face.
Traditional composite material reflecting surface uses the structure of composite material skin aluminum honeycomb interlayer, and aluminum honeycomb and covering expand
The difference of coefficient causes the efficiency of sandwich to be difficult to play to meet the needs of high precision high stability, in order to meet antenna-reflected
Face high precision high stability demand uses full carbon advanced grid stiffened structure to reduce product thermal deformation, is combined further with room temperature splicing
The surface precision for improving reflecting surface, meets the use demand of RMS≤6 μm after reflecting surface RMS≤5 μm, thermal deformation.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of high precision high stability composite material antenna is anti-
Face and preparation method thereof is penetrated, the surface precision of composite material antenna reflective face can be improved to micron order, reduce product thermal deformation.
The purpose of the present invention is what is be achieved through the following technical solutions:
The present invention provides a kind of high precision high stability composite material antenna reflective faces, including the surface metal set gradually
The working face side of inside panel, the non-work of inside panel is arranged in layer, inside panel, grid sandwich, exterior skin, the surface metal-layer
Make face side to connect with grid sandwich.
Preferably, the grid sandwich includes grid gusset, and the grid gusset includes more lateral grid gussets and more
The vertical mutually embedding formation groined type structure of root longitudinal grid gusset, lateral grid gusset and longitudinal grid gusset.
Preferably, slot is provided on each grid gusset；Slot and longitudinal lattice on the transverse direction grid gusset
Slot is oppositely arranged on grid gusset, and is corresponded.
Preferably, the grid gusset with a thickness of 0.5~2mm, it is each slot spacing on the transverse direction grid gusset, vertical
Each slot spacing on grid gusset is 40-60mm.
Preferably, the depth of the slot is 10~40mm, and the width of slot is 0.9~2.4mm.
Preferably, the inside panel, exterior skin, grid sandwich are all made of carbon fiber epoxy resin or carbon fiber-cyanate ester
Resin composite materials preparation；Carbon fiber volume content is 60-75% in the composite material.
Preferably, the inside panel, exterior skin, grid sandwich are all made of the preparation of autoclave process curing molding, described solid
Change condition are as follows: room temperature~120 DEG C, pressurize 0.5MPa, then 120 DEG C of heat-insulation pressure keeping 8h.
Preferably, the surface metal-layer uses metallic aluminium；The surface metal-layer with a thickness of 0.05~0.2mm.Gold
The such electromagnetic wave signal of reflectivity that reflecting surface can be improved in category aluminium layer can be just collected.
The present invention also provides a kind of preparation methods of high precision high stability composite material antenna reflective face, including following step
It is rapid:
S1, the one side of the non-working surface of inside panel and grid sandwich is glued, then by the another of exterior skin and grid sandwich
It is glued on one side, cure under pressure；
S2, through step S1 processing after, the spray metal on the working face of inside panel, then under vacuum sizing be solidified into
Type forms surface metal-layer.
Preferably, in step S1, the splicing temperature is that the pressure of 20-40 DEG C of cure under pressure is 0.1-0.2MPa；
In step S2, the cured temperature of sizing is 20-40 DEG C, pressure 0.02-0.04MPa.
Preferably, in step S1, the spray metal is metallic aluminium, partial size≤25 μm of spray metal.
Compared with prior art, the present invention have it is following the utility model has the advantages that
Cell structure is applied to the preparation of composite material antenna reflective face by the present invention, efficiently solves composite molding
Influence of the problem on deformation to final products surface precision in the manufacturing processes such as splicing, high degree improve Product Precision；Using
Full carbon structure prepares antenna reflective face, significantly reduces the thermal deformation of antenna reflective face.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is high precision high stability composite material antenna reflective face composition schematic diagram；
Fig. 2 is the structure composition schematic diagram of grid sandwich；
Wherein: 1- superhigh precision reflecting surface shaping mould；2- surface metal-layer；3- inside panel；4- grid sandwich；It is covered outside 5-
Skin；6- grid gusset；7- slot.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
Embodiment 1
The present embodiment is related to a kind of high precision high stability composite material antenna reflective face and preparation method, Fig. 1 and Fig. 2 give
Reflecting surface structure schematic diagram is gone out, including surface metal-layer 2, inside panel 3, grid sandwich 4, the exterior skin 5 set gradually；Institute
The working face side that inside panel is arranged in surface metal-layer is stated, the non-working surface side of inside panel is connect with grid sandwich.
The grid sandwich includes grid gusset, and the grid gusset includes more lateral grid gussets and the longitudinal direction Duo Gen lattice
The vertical mutually embedding formation groined type structure of grid gusset, lateral grid gusset and longitudinal grid gusset.
Slot is provided on each grid gusset；On slot and longitudinal grid gusset on the transverse direction grid gusset
Slot is oppositely arranged, and is corresponded.
The inside panel, exterior skin, grid sandwich are all made of carbon fiber-cyanate resin composite material preparation；It is described multiple
Fiber volume fraction is 60-75% in condensation material.
Specific forming method is as follows:
S1, the method combined using numerical simulation with orthogonal test carry out thermal deformation emulation, design to antenna reflective face
Material system, skin thickness, gusset thickness, slot spacing, grid direction of antenna reflective face etc.；
S2, using automatic fiber placement technology, be coated with M55J/ cyanogen on superhigh precision reflecting surface shaping mould 1 (RMS=1.5 μm)
Sour rouge hot melt prepreg, laying angle are [+45/0/-45/90]2s；To prepare reflecting surface inside panel and exterior skin；
S3, using automatic fiber placement technology, M55J/ cyanate ester hot melt prepreg, laying angle are coated on platform mold
For [+45/0/-45/90]s,；To prepare grid gusset blank；
S4, inside panel 3 obtained, exterior skin 5, grid gusset blank are utilized respectively autoclave process curing molding, Gu
Change system is equal are as follows: room temperature~120 DEG C, pressurize 0.5MPa, 120 DEG C of heat-insulation pressure keeping 8h, pressure release furnace cooling；
S5, grid gusset CAD is drawn using grid digital-to-analogue, processes grid gusset 6, grid gusset thickness referring to design template
For 0.8mm, slot spacing is 50mm, and socket depth 32.5mm, the width of slot is 1.2mm；
S6, the inside panel 3 of forming is placed on high-precision reflecting surface shaping mould 1, the grid gusset 6 that will be processed
The position smearing structure gluing for interlocking to form grid sandwich 4 by 7 intercalation of slot, and being contacted in grid with inside panel
Agent 2051, is integrally placed on inside panel；
S7, the 7 position dispensing 2051 of slot in grid sandwich 4 are smeared in grid sandwich 4 and exterior skin contact site
2051, exterior skin is closed on grid sandwich 4；
S8, product and mold are placed on to cure under pressure in autoclave, 25 DEG C of temperature, pressure 0.2MPa, the time is for 24 hours；
S9, mould surface coating aluminum layer is formed in high-precision inside panel, then 2051 resins are glued by partial size≤25 μm
In in sprayed metal layer rear mold, the overall structure after the completion of covering made from S8 and grid are glued is covered on resin,
And solidification is vacuumized, 25 DEG C of temperature, vacuum pressure 0.03MPa, the time is for 24 hours.The surface metal aluminium layer with a thickness of
0.05~0.2mm.
S10, RMS=4.3 μm of surface precision for demoulding aft antenna reflecting surface, under -80 DEG C of low temperature environment, RMS=5.2
μm。
Embodiment 2
The present embodiment is related to a kind of high precision high stability composite material antenna reflective face and preparation method, the antenna are anti-
It is substantially the same manner as Example 1 to penetrate face structure, the specific forming method is as follows:
S1, the method combined using numerical simulation with orthogonal test carry out thermal deformation emulation, design to antenna reflective face
Material system, skin thickness, gusset thickness, slot spacing, grid direction of antenna reflective face etc.；
S2, using automatic fiber placement technology, be coated with M55J/ cyanogen on superhigh precision reflecting surface shaping mould 1 (RMS=1.5 μm)
Sour rouge hot melt prepreg, laying angle are [+45/0/-45/90]2s；To prepare reflecting surface inside panel and exterior skin；
S3, using automatic fiber placement technology, M55J/ cyanate ester hot melt prepreg, laying angle are coated on platform mold
For [+45/0/-45/90]s；To prepare grid gusset blank；
S4, inside panel 3, exterior skin 5,6 blank of grid gusset are utilized respectively autoclave process curing molding, curing cycle
Are as follows: room temperature~120 DEG C, pressurize 0.5MPa, 120 DEG C of heat-insulation pressure keeping 8h, pressure release furnace cooling；
S5, grid gusset CAD is drawn using grid digital-to-analogue, processes grid gusset 6, grid gusset thickness referring to design template
For 0.5mm, slot spacing is 60mm, and socket depth 32.5mm, the width of slot is 0.9mm；
S6, the inside panel 3 of forming is placed on high-precision reflecting surface shaping mould 1, the grid gusset 6 that will be processed
The position smearing structure adhesive 2051 for interlocking to form grid sandwich 4 by 7 intercalation of slot, and being contacted in grid with inside panel,
It is integrally placed on inside panel；
S7, the 7 position dispensing 2051 of slot in grid sandwich 4 are smeared in grid sandwich 4 and exterior skin contact site
2051, exterior skin is closed on grid sandwich 4；
S8, product and mold are placed on to cure under pressure in autoclave, 40 DEG C of temperature, pressure 0.1MPa, the time is for 24 hours；
S9, mould surface coating aluminum layer is formed in high-precision inside panel, then 2051 resins are glued by partial size≤25 μm
In in sprayed metal layer rear mold, the overall structure after the completion of covering made from S8 and grid are glued is covered on resin,
And solidification is vacuumized, 40 DEG C of temperature, vacuum pressure 0.04MPa, the time is for 24 hours.The surface metal aluminium layer with a thickness of
0.05~0.2mm.
S10, RMS=4.9 μm of surface precision for demoulding aft antenna reflecting surface, under -80 DEG C of low temperature environment, RMS=5.8
μm。
Embodiment 3
The present embodiment is related to a kind of high precision high stability composite material antenna reflective face and preparation method, the antenna are anti-
It is substantially the same manner as Example 1 to penetrate face structure, the specific forming method is as follows:
S1, the method combined using numerical simulation with orthogonal test carry out thermal deformation emulation, design to antenna reflective face
Material system, skin thickness, gusset thickness, slot spacing, grid direction of antenna reflective face etc.；
S2, using automatic fiber placement technology, be coated with M55J/ cyanogen on superhigh precision reflecting surface shaping mould 1 (RMS=1.5 μm)
Sour rouge hot melt prepreg, laying angle are [+45/0/-45/90]2s；To prepare reflecting surface inside panel and exterior skin；
S3, using automatic fiber placement technology, M55J/ cyanate ester hot melt prepreg, laying angle are coated on platform mold
For [+45/0/-45/90]s；To prepare grid gusset blank；
S4, inside panel 3, exterior skin 5,6 blank of grid gusset are utilized respectively autoclave process curing molding, curing cycle
Are as follows: room temperature~120 DEG C, pressurize 0.5MPa, 120 DEG C of heat-insulation pressure keeping 8h, pressure release furnace cooling；
S5, grid gusset CAD is drawn using grid digital-to-analogue, processes grid gusset 6, grid gusset thickness referring to design template
For 2mm, slot spacing is 40mm, and socket depth 32.5mm, the width of slot is 2.4mm；
S6, the inside panel 3 of forming is placed on high-precision reflecting surface shaping mould 1, the grid gusset 6 that will be processed
The position smearing structure adhesive 2051 for interlocking to form grid sandwich 4 by 7 intercalation of slot, and being contacted in grid with inside panel,
It is integrally placed on inside panel；
S7, the 7 position dispensing 2051 of slot in grid sandwich 4 are smeared in grid sandwich 4 and exterior skin contact site
2051, exterior skin is closed on grid sandwich 4；
S8, product and mold are placed on to cure under pressure in autoclave, 20 DEG C of temperature, pressure 0.2MPa, the time is for 24 hours；
S10, mould surface coating aluminum layer is formed in high-precision inside panel, then partial size≤25 μm apply 2051 resins
Glue in sprayed metal layer rear mold, cover in resin by the overall structure after the completion of covering made from S8 and grid are glued
On, and solidification is vacuumized, 20 DEG C of temperature, vacuum pressure 0.02MPa, the time is for 24 hours.The surface metal aluminium layer with a thickness of
0.05~0.2mm.
S11, RMS=4.2 μm of surface precision for demoulding aft antenna reflecting surface, under -80 DEG C of low temperature environment, RMS=4.8
μm。
Comparative example 1
The preparation process of antenna reflective face in this comparative example are as follows:
S1, using automatic fiber placement technology, be coated on superhigh precision antenna reflective face shaping mould (RMS=1.5 μm)
M55J/ cyanate ester hot melt prepreg, laying angle are [+45/0/-45/90]2s；To prepare reflecting surface inside panel and outer illiteracy
Skin；
S2, inside and outside covering is utilized into autoclave process curing molding, curing cycle are as follows: room temperature~120 DEG C, pressurization
0.5MPa, 120 DEG C of heat-insulation pressure keeping 8h, pressure release furnace cooling；
S3, the inside panel of forming is placed on high-precision reflecting surface shaping mould, using aluminum honeycomb as sandwich, is carried out
Solidification by cement forms afterwards, briquetting pressure 0.2MPa.
S5, mould surface coating aluminum layer is formed in high-precision inside panel, then 2051 resins are glued by partial size≤25 μm
In in sprayed metal layer rear mold, the overall structure after the completion of covering made from S8 and grid are glued is covered on resin,
And solidification is vacuumized, 25 DEG C of temperature, vacuum pressure 0.02MPa, the time is for 24 hours.The surface metal aluminium layer with a thickness of
0.05~0.2mm.
S6, RMS=17.3 μm of surface precision for demoulding aft antenna reflecting surface, under -80 DEG C of low temperature environment, RMS=
27.8 μm。
Comparative example 2
The preparation process of antenna reflective face in this comparative example are as follows:
S1, using automatic fiber placement technology, be coated on superhigh precision antenna reflective face shaping mould (RMS=1.5 μm)
M55J/ cyanate ester hot melt prepreg, laying angle are [+45/0/-45/90]2s；To prepare reflecting surface inside panel and outer illiteracy
Skin；
S2, inside and outside covering is utilized into autoclave process curing molding, curing cycle are as follows: room temperature~120 DEG C, pressurization
0.5MPa, 120 DEG C of heat-insulation pressure keeping 8h, pressure release furnace cooling；
S3, the inside panel of forming is placed on high-precision reflecting surface shaping mould, using carbon fibre reinforced pipe part
As sandwich, solidification by cement is formed after progress, briquetting pressure 0.2MPa.
S4, mould surface coating aluminum layer is formed in high-precision inside panel, then 2051 resins are glued by partial size≤25 μm
In in sprayed metal layer rear mold, the overall structure after the completion of covering made from S8 and grid are glued is covered on resin,
And solidification is vacuumized, 25 DEG C of temperature, vacuum pressure 0.02MPa, the time is for 24 hours.The surface metal aluminium layer with a thickness of
0.05~0.2mm.
S5, RMS=5 μm of surface precision for demoulding aft antenna reflecting surface, under -80 DEG C of low temperature environment, RMS=7.1 μ
m。
Size of the RMS value that above-described embodiment and comparative example obtain under room temperature and -80 DEG C of environment is as shown in table 1.
The RMS value of table 1 embodiment and comparative example
| Sandwich | Room temperature RMS value (μm) | - 80 DEG C of RMS values (μm) | |
| Embodiment 1 | Grid | 4.3 | 5.2 |
| Embodiment 2 | Grid | 4.9 | 5.8 |
| Embodiment 3 | Grid | 4.2 | 4.8 |
| Comparative example 1 | Aluminum honeycomb | 17.3 | 27.8 |
| Comparative example 2 | Carbon pipe | 5 | 7.1 |
By embodiment and the result of comparative example in the above table 1 it is found that using grid sandwich structure reflecting surface surface precision
4 times are improved compared to aluminum honeycomb sandwich structure, what -80 DEG C of deformed RMS value variable quantities reduced becomes apparent.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of high precision high stability composite material antenna reflective face, which is characterized in that including set gradually surface metal-layer,
The working face side of inside panel, the inoperative of inside panel is arranged in inside panel, grid sandwich, exterior skin, the surface metal-layer
Face side is connect with grid sandwich.
2. high precision high stability composite material antenna reflective face according to claim 1, which is characterized in that the grid folder
Core includes grid gusset, and the grid gusset includes more lateral grid gussets and Duo Gen longitudinal grid gusset, lateral grid muscle
Plate mutually embedding formation groined type structure vertical with longitudinal grid gusset.
3. high precision high stability composite material antenna reflective face according to claim 1, which is characterized in that each grid
Slot is provided on gusset；Slot on the transverse direction grid gusset is oppositely arranged with slot on longitudinal grid gusset, and one
One is corresponding.
4. high precision high stability composite material antenna reflective face according to claim 2 or 3, which is characterized in that the lattice
Grid gusset with a thickness of 0.5~2mm, each slot spacing on the transverse direction grid gusset, each slot on longitudinal grid gusset
Spacing is 40-60mm.
5. high precision high stability composite material antenna reflective face according to claim 3, which is characterized in that the slot
Depth is 10~40mm, and the width of slot is 0.9~2.4mm.
6. high precision high stability composite material antenna reflective face according to claim 1, which is characterized in that the Inner Mongol
Skin, exterior skin, grid sandwich are all made of carbon fiber epoxy resin or carbon fiber-cyanate resin composite material preparation；It is described multiple
Carbon fiber volume content is 60-75% in condensation material.
7. high precision high stability composite material antenna reflective face according to claim 6, which is characterized in that the Inner Mongol
Skin, exterior skin, grid sandwich are all made of the preparation of autoclave process curing molding, the condition of cure are as follows: room temperature~120 DEG C add
0.5MPa is pressed, then 120 DEG C of heat-insulation pressure keeping 8h.
8. high precision high stability composite material antenna reflective face according to claim 1, which is characterized in that the surface gold
Belong to layer and uses metallic aluminium；The surface metal-layer with a thickness of 0.05~0.2mm.
9. a kind of preparation side of high precision high stability composite material antenna reflective face according to claim 1-8
Method, which comprises the following steps:
S1, the one side of the non-working surface of inside panel and grid sandwich is glued, then by the another side of exterior skin and grid sandwich
It is glued, cure under pressure；
S2, through step S1 processing after, then the spray metal on the working face of inside panel is glued curing molding, shape under vacuum
At surface metal-layer.
10. the preparation method of high precision high stability composite material antenna reflective face according to claim 9, feature exist
In in step S1, the splicing temperature is that the pressure of 20-40 DEG C of cure under pressure is 0.1-0.2MPa；
In step S2, the cured temperature of sizing is 20-40 DEG C, pressure 0.02-0.04MPa.
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