CN106019436B - A kind of optical system full carbon fiber composite material reflector and manufacturing method - Google Patents
A kind of optical system full carbon fiber composite material reflector and manufacturing method Download PDFInfo
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- CN106019436B CN106019436B CN201610607468.6A CN201610607468A CN106019436B CN 106019436 B CN106019436 B CN 106019436B CN 201610607468 A CN201610607468 A CN 201610607468A CN 106019436 B CN106019436 B CN 106019436B
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- G02B5/00—Optical elements other than lenses
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Abstract
The invention discloses a kind of optical system full carbon fiber composite material reflectors and its manufacturing method, by carbon fibre composite for manufacturing each component part of speculum, and it is glued co-curing and obtains full carbon fiber composite material reflector, its anti-deformation is strong, thermal stability is good, solves the temperature matching of other composite structures of speculum Yu camera, this manufacturing technology can produce high-precision full carbon fiber composite material reflector in a short time, the manufacturing process of opposite conventional mirror, this technology manufacturing cycle is short, and manufacturing cost is low.
Description
Technical field
The present invention relates to a kind of optical system full carbon fiber composite material reflectors and manufacturing method, belong to advanced composite
Field of material technology.
Background technology
Remote sensing is to realize that real-time to military target and round-the-clock investigation main means, the level of remote sensing camera determine one
The modernization level of a country's national defence, thus since the eighties in last century, remote sensing camera is competing between each power of the world
Mutually develop, most representative is the cameras such as IKNOS, SPOT5, KH series in the U.S., and resolution ratio is up to 0.2 meter of level.
With the development of remote sensing observations technology, the resolution ratio that earth observation and space exploration require is higher and higher, corresponding optics bore
Also increasing.Heavy caliber, high-resolution speculum have become the inexorable trend of Space Remote Sensors development.However increase space
The optics bore of speculum, can cause speculum weight and volume increase and space environment under thermal deformation resistant ability decline；
Also add launch cost simultaneously.Therefore, lightweight is that the inevitable choice of spacing reflection mirror and optical system lightweight are badly in need of
The Pinch technology of solution.
It disclosure satisfy that the design requirement of light reflection mirror using the new material of high-strength light.The lightweight of optical system needs
There is manufacture material high intensity, high-modulus to have lower density simultaneously.The traditional materials such as opposite Zerodur, SiC, carbon fiber
Composite material specific stiffness is higher, and thermal deformation coefficient is low, and thermal stability is best；There is good craftsmanship and designability simultaneously,
Moulding process is ripe, can farthest realize the heavy caliber and lightweight requirements of speculum.CFRP materials are applicable not only to
Speculum is manufactured, realizes the lightweight of large caliber reflecting mirror；At the same time as the microscope base, pedestal and support construction of optical system
Etc. manufacture materials, solve the temperature matching of other carbon fiber composite structures of speculum Yu optical system.
China conducts a research late in terms of carbon fiber composite material reflector, and Research foundation is poor, and foreign countries are to China
Technology blockage, bring not small difficulty to development to a certain extent.Due to degree-of-difficulty factor height, Domestic Research Progress is slow.It arrives
The research for remaining in lab scale chip level speculum so far, there are no the reports of maturation application；The development of large caliber reflecting mirror
Even more without clear project.Applied basic research about the direction need to be reinforced as early as possible.The prior art does not solve carbon fiber
The thermally matched problem of material of composite materials itself does not solve itself and optical system other lightweight composite material knots yet
The thermally matched problem of structure.
Invention content
The technical problems to be solved by the invention：In order to overcome the deficiencies of the prior art, it is complete to provide a kind of optical system use
Carbon fiber composite material reflector and manufacturing method, to solve the problems, such as the thermally matched of carbon fiber composite material reflector.
Technical solution of the invention：
A kind of full carbon fiber composite material reflector of optical system includes homogeneous layer, minute surface base, honeycomb knot from top to bottom
The flange of structure, backboard and periphery package,
Homogeneous layer is the ultrashort carbon fibre reinforced composite of single layer, and carbon fiber mass content is 5%~10%,
Minute surface base be ultralow fiber areal densities high mould or superelevation modules carbon fibre composite material, surface density be no more than
100g/m2, isotropic laying subject to minute surface base laying,
Honeycomb, backboard and flange are same middle mould or high-modules carbon fibre composite material, and backboard and flange are multilayer knot
Isotropic laying subject to structure, backboard and flange laying,
Homogeneous layer, minute surface base, honeycomb, backboard and flange are glued by adhesive.
Homogeneous layer material is carbon nano-fiber or the cyanate ester resin composite material that carbon nanotube enhances.
Homogeneous layer thickness is not more than 0.2mm.
The thickness in monolayer of prepreg used in homogeneous layer, minute surface base, honeycomb, backboard and flange 0.03~
Between 0.20mm, the resin of prepreg is the epoxy resin or cyanate ester resin that hydroscopicity is less than 2%, resin content 30%~
Between 45%.
Adhesive is epoxy resin or cyanate ester resin adhesive of the hydroscopicity less than 2%, resin content 30%~
Between 45%.
The reinforcement of minute surface blank material material is M40J, M55J or M60 carbon fiber.
The reinforcement of honeycomb, backboard and flange material is T800, M40J or M60 carbon fiber.
A kind of full carbon fiber composite material reflector manufacturing method of optical system, the specific steps are：
(1) optical mirror plane formable layer：Make mold, precision PV≤0.1 μm after die surface processing, RMS≤10nm, surface
Roughness RMS≤10nm；
The prefabricated material paving of cyanate ester resin that carbon nano-fiber or carbon nanotube are enhanced will surpass on it in die surface
The high mould or superelevation modules carbon fibre prepreg of low fiber areal densities are obtained for use with quasi-isotropic ply stacking-sequence paving after solidification
Optical mirror plane layer；
(2) backboard, flange molding：Make backboard, flange flat plate mold, by mould in multilayer or high-modules carbon fibre prepreg with
Quasi-isotropic ply stacking-sequence paving obtains for use backboard and flange on backboard, flange mold after solidification；
(3) it is glued：Specular layer, cementing be aligned with glued membrane, honeycomb, cementing glued membrane, backboard successively axle center are stacked, then will
Flange is placed around it and is limited, and product to be solidified is obtained；
(4) coating product isolation film to be solidified, non-porous film, airfelt, the vacuum bag for obtaining step (3), into curing
To speculum.
Honeycomb is fabric with holes in step (3), and manufacture material is the cyanate composite material of fibre reinforced.
Cured condition is in step (1) and step (2)：Under the conditions of 90 DEG C~100 DEG C low-temperature setting or 120 DEG C~
Intermediate temperature setting or hot setting under the conditions of 170 DEG C~180 DEG C, hardening time 3h~6h are in pressure under the conditions of 130 DEG C
It is carried out in the autoclave of 0.3MPa~0.6Mpa.
Cured condition is in step (4)：Low-temperature setting under the conditions of 90 DEG C~100 DEG C, or in 120 DEG C~130 DEG C items
Intermediate temperature setting under part, hardening time 3h~6h are carried out in the autoclave that pressure is 0.1MPa~0.4Mpa.
The advantageous effect of the present invention compared with prior art：
(1) present invention is used for carbon fibre composite to manufacture each component part of speculum, and is glued co-curing and obtains
Full carbon fiber composite material reflector, anti-deformation is strong, and thermal stability is good, solves speculum and other composite woods of camera
Expect the temperature matching of structure, it is anti-that this manufacturing technology can produce high-precision full carbon fibre composite in a short time
Mirror is penetrated, the manufacturing process of opposite conventional mirror, this technology manufacturing cycle is short, and manufacturing cost is low；
(2) full carbon fiber honeycomb is used as mirror structure core material by the present invention for the first time, and the complete light rigidity of carbon fiber honeycomb is high,
Speculum rigidly high design requirement can be met；
(3) present invention attempts to produce the full carbon fiber composite material reflector of space camera system for the first time to be domestic, this
Item manufacturing technology can realize the manufacture of high-precision composite materials, can extend to the system of entire optical system mirror
It makes, expands application of the high-precision composite technology in optical system.
Description of the drawings
Fig. 1 is schematic structural view of the invention；
Fig. 2 is manufacturing flow chart of the present invention.
Specific implementation mode
The present invention is described in further detail in the following with reference to the drawings and specific embodiments：
Full carbon fiber composite material reflector is composite honeycomb sandwich structures, as shown in Figure 1, being followed successively by from top to bottom
Homogeneous layer 1, minute surface base 2, carbon fiber honeycomb 3, backboard 4 and periphery package 5.Homogeneous layer 1 is the ultrashort fibre reinforced of single layer
Composite material, thickness are not more than 0.2mm, and carbon fiber mass content is 5%~10%, and minute surface base 2 is ultralow fiber areal densities
High mould or superelevation modules carbon fibre composite material, such as M40J, M55J or M60,2 surface density of minute surface base is no more than 100g/m2, mirror
Isotropic laying subject to 2 laying of dough, honeycomb 3, backboard 4 and flange 5 are same middle mould or high-modules carbon fibre composite wood
Material, such as T800, M40J or M60, backboard 4 and flange 5 are multilayered structure, isotropic laying subject to 5 laying of backboard 4 and flange,
Carbon fiber honeycomb 3 is with holes, form of fabric.
1 material of homogeneous layer is carbon nano-fiber or the cyanate ester resin composite material that carbon nanotube enhances.
The thickness in monolayer of prepreg used in homogeneous layer 1, minute surface base 2, honeycomb 3, backboard 4 and flange 5 exists
Between 0.03~0.20mm, the resin of prepreg is epoxy resin or cyanate ester resin that hydroscopicity is less than 2%, and resin content exists
Between 30%~45%.
Homogeneous layer 1, minute surface base 2, honeycomb 3, backboard 4 and flange 5 are glued by adhesive, and adhesive is hydroscopicity
Epoxy resin less than 2% or cyanate ester resin, resin content is between 30%~45%.
A kind of full carbon fiber composite material reflector manufacturing method of optical system, manufacturing process are shown in Fig. 2, specific steps
For：
(1) optical mirror plane formable layer
According to the design feature and surface precision of optical mirror plane, added using high-precision sanding and polishing technology in mold base working face
Work goes out high-precision mold, precision PV≤0.1 μm after tool surface treatment, RMS≤10nm, surface roughness RMS≤10nm；Mold material
Matter can be stainless steel, invar, super-low expansion coefficient glass etc.；The cyanate ester resin that carbon nano-fiber or carbon nanotube are enhanced is pre-
System material paving in die surface, on it by the high mould of ultralow fiber areal densities or superelevation modules carbon fibre prepreg with standard respectively to same
Property ply stacking-sequence paving, obtains for use optical mirror plane layer after solidification.
(2) backboard, flange molding
According to the design feature of speculum, backboard is designed using formpiston, and flange is designed using former, and mold mold material can
For stainless steel, invar etc..By mould in multilayer or high-modules carbon fibre prepreg with quasi-isotropic ply stacking-sequence paving backboard 4,
On 5 mold of flange, for use backboard 4 and flange 5 are obtained after solidification.
(3) carbon fiber composite material reflector is glued
By specular layer, plate core it is cementing with glued membrane, carbon fiber honeycomb, plate core is cementing is stacked successively with glued membrane, backboard, then by side
Circle place its around, axle center is aligned, is placed in special tooling, and limited using pin, ensure solidification process in panel and
Honeycomb core not core shift, obtains product to be solidified.
(4) the coating product auxiliary material to be solidified for obtaining step (3), including it is isolation film, non-porous film, airfelt, true
Empty bag realizes the splicing co-curing of speculum into autoclave, adjusts curing process parameter to control heat distortion amount, ensures solidification
The surface precision of back mirror obtains full carbon fiber composite material reflector after co-curing.
It is above-mentioned used in prepreg thickness in monolayer between 0.03~0.20mm, resin content 30%~45% it
Between；
Middle solidification process carries out in autoclave in step (1) and step (2), and solidification temperature is in following three kinds
Any one：1. low-temperature setting, solidification temperature is at 90 DEG C~100 DEG C, 2. intermediate temperature setting, solidification temperature at 120 DEG C~130 DEG C,
3. hot setting, solidification temperature is at 170 DEG C~180 DEG C.Hardening time 3h~6h in autoclave, hot pressing pressure inside the tank 0.3MPa~
0.6Mpa。
Solidification process carries out in autoclave in step (4), and solidification temperature is following two：1. low-temperature setting, Gu
Change temperature at 90 DEG C~100 DEG C, 2. intermediate temperature setting, solidification temperature is at 120 DEG C~130 DEG C；Hardening time 3h~6h in autoclave,
Hot pressing pressure inside the tank 0.1MPa~0.4Mpa.
Specifically：The thickness in monolayer of prepreg used in minute surface base 2 is 0.09mm, and resin content is 40%；Backboard 4,
The thickness in monolayer for the prepreg that flange 5 uses is 0.14mm, and the resin of prepreg is the epoxy resin that hydroscopicity is less than 2%, tree
Fat content is 34%；The prepreg that carbon fiber honeycomb 3 uses is plain cloth form with holes, thickness in monolayer 0.1mm, resin
Content is 36%；Adhesive is the epoxy resin adhesive that hydroscopicity is less than 2%；
Middle solidification process carries out in autoclave in step (1) and step (2), and solidification temperature is intermediate temperature setting, Gu
Change temperature at 120 DEG C~130 DEG C, hardening time 4h in autoclave, hot pressing pressure inside the tank 0.6Mpa.
Solidification process carries out in autoclave in step (4), and solidification temperature is intermediate temperature setting, and solidification temperature is 120
DEG C~130 DEG C；Hardening time 3h in autoclave, hot pressing pressure inside the tank 0.3Mpa.
Full carbon fiber composite material reflector manufacturing technology, by carbon fibre composite for manufacturing each composition of speculum
Part, and be glued co-curing and obtain full carbon fiber composite material reflector.The high full carbon fiber honeycomb of light rigidity is used for the first time
Make mirror structure core material；It is positioned using special limiting tool and realizes the coaxial of each component part of speculum.This manufacturing technology can
To produce high-precision full carbon fiber composite material reflector in a short time；The manufacturing process of opposite conventional mirror, this
The technology manufacturing cycle is short, and manufacturing cost is low.Microscope base, pedestal and the support construction etc. of speculum and lightweight optical system simultaneously
Manufacture material is consistent, solves the temperature matching of other composite structures of speculum Yu camera.
The present invention is not disclosed content and is known to the skilled person common sense.
Claims (13)
1. a kind of full carbon fiber composite material reflector of optical system, which is characterized in that from top to bottom include homogeneous layer (1),
The flange (5) of minute surface base (2), honeycomb (3), backboard (4) and periphery package；
Homogeneous layer (1) is the ultrashort carbon fibre reinforced composite of single layer, and carbon fiber mass content is 5%~10%；
Minute surface base (2) is the high mould or superelevation modules carbon fibre composite material of ultralow fiber areal densities, and surface density is no more than 100g/
m2, isotropic laying subject to minute surface base (2) laying；
Honeycomb (3), backboard (4) and flange (5) are same middle mould or high-modules carbon fibre composite material, backboard (4) and flange
(5) it is multilayered structure, isotropic laying subject to backboard (4) and flange (5) laying；
Homogeneous layer (1), minute surface base (2), honeycomb (3), backboard (4) and flange (5) are glued by adhesive.
2. a kind of full carbon fiber composite material reflector of optical system as described in claim 1, which is characterized in that homogeneous layer
(1) material is carbon nano-fiber or the cyanate ester resin composite material that carbon nanotube enhances.
3. a kind of full carbon fiber composite material reflector of optical system as described in claim 1, which is characterized in that homogeneous layer
(1) thickness is not more than 0.2mm.
4. a kind of full carbon fiber composite material reflector of optical system as described in claim 1, which is characterized in that homogeneous layer
(1), the thickness in monolayer of prepreg used in minute surface base (2), honeycomb (3), backboard (4) and flange (5) 0.03~
Between 0.20mm.
5. a kind of full carbon fiber composite material reflector of optical system as claimed in claim 4, which is characterized in that prepreg
Resin be hydroscopicity be less than 2% epoxy resin or cyanate ester resin.
6. a kind of full carbon fiber composite material reflector of optical system as claimed in claim 5, which is characterized in that prepreg
Resin content is between 30%~45%.
7. a kind of full carbon fiber composite material reflector of optical system as described in claim 1, which is characterized in that adhesive
It is less than 2% epoxy resin or cyanate ester resin for hydroscopicity.
8. a kind of full carbon fiber composite material reflector of optical system as described in claim 1, which is characterized in that minute surface base
(2) reinforcement of material is M40J, M55J or M60 carbon fiber.
9. a kind of full carbon fiber composite material reflector of optical system as described in claim 1, which is characterized in that honeycomb knot
The reinforcement of structure (3), backboard (4) and flange (5) material is T800, M40J or M60 carbon fiber.
10. a kind of full carbon fiber composite material reflector manufacturing method of optical system, it is characterised in that：The specific steps are：
(1) optical mirror plane formable layer：Make mold, precision PV≤0.1 μm after die surface processing, RMS≤10nm, rough surface
Spend RMS≤10nm；
The prefabricated material paving of cyanate ester resin that carbon nano-fiber or carbon nanotube are enhanced is in die surface, on it by ultralow fibre
The high mould or superelevation modules carbon fibre prepreg of dimension surface density obtain for use light with quasi-isotropic ply stacking-sequence paving after solidification
Learn specular layer；
(2) backboard, flange molding：Backboard (4), flange (5) flat plate mold are made, by mould in multilayer or high-modules carbon fibre prepreg
With quasi-isotropic ply stacking-sequence paving on backboard (4), flange (5) mold, for use backboard (4) and flange are obtained after solidification
(5)；
(3) it is glued：Specular layer, cementing be aligned with glued membrane, honeycomb, cementing glued membrane, backboard (4) successively axle center are stacked, then will
Flange (5) is placed around it and is limited, and product to be solidified is obtained；
(4) coating product isolation film to be solidified, non-porous film, airfelt, the vacuum bag for obtaining step (3), into solidification of hot-press tank
Obtain speculum.
11. a kind of optical system full carbon fiber composite material reflector manufacturing method, feature as claimed in claim 10
It is：Honeycomb is fabric with holes in step (3), and manufacture material is carbon fibre reinforced composite.
12. a kind of optical system full carbon fiber composite material reflector manufacturing method, feature as claimed in claim 10
It is：Cured condition is in step (1) and step (2)：The low-temperature setting or 120 DEG C~130 under the conditions of 90 DEG C~100 DEG C
Intermediate temperature setting or hot setting under the conditions of 170 DEG C~180 DEG C under the conditions of DEG C, hardening time 3h~6h are 0.3MPa in pressure
It is carried out in the autoclave of~0.6Mpa.
13. a kind of optical system full carbon fiber composite material reflector manufacturing method, feature as claimed in claim 10
It is：Cured condition is in step (4)：Low-temperature setting under the conditions of 90 DEG C~100 DEG C, or under the conditions of 120 DEG C~130 DEG C
Intermediate temperature setting, hardening time 3h~6h are carried out in the autoclave that pressure is 0.1MPa~0.4Mpa.
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106739192B (en) * | 2016-11-22 | 2018-12-21 | 北京空间机电研究所 | A kind of full carbon fiber composite material reflector substrate and preparation method thereof |
| CN106956443A (en) * | 2017-03-20 | 2017-07-18 | 航天材料及工艺研究所 | The small thickness composite curved-surface structure of micron order type face precision and its forming method |
| CN109581556B (en) * | 2018-11-26 | 2020-07-21 | 中国科学院长春光学精密机械与物理研究所 | Preparation process of carbon fiber composite reflector |
| CN110422344B (en) * | 2019-08-12 | 2021-06-11 | 航天材料及工艺研究所 | Large-rotational-inertia light composite flywheel for satellite and preparation method thereof |
| CN111505752A (en) * | 2020-04-17 | 2020-08-07 | 中国科学院西安光学精密机械研究所 | Carbon fiber composite material reflector and manufacturing method thereof |
| CN113858656A (en) * | 2021-09-24 | 2021-12-31 | 成都佳驰电子科技股份有限公司 | Integrated forming process of sawtooth-shaped hollow-structure composite wave-absorbing component |
| CN114030241B (en) * | 2021-10-11 | 2024-05-14 | 航天材料及工艺研究所 | Carbon fiber composite honeycomb, preparation method and application |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US4875766A (en) * | 1986-07-18 | 1989-10-24 | Mitsubishi Denki Kabushiki Kaisha | Fiber reinforced plastic reflector |
| JPH11198260A (en) * | 1998-01-20 | 1999-07-27 | Mitsubishi Electric Corp | Honeycomb sandwich panel |
| CN2501068Y (en) * | 2001-10-16 | 2002-07-17 | 中国科学院上海技术物理研究所 | Low-expansion super-light large diameter composite reflector for space camera |
| CN2585250Y (en) * | 2002-12-18 | 2003-11-05 | 中国科学院西安光学精密机械研究所 | Speculum made of carbon fiber composite material and of honeycomb structure type |
| CN1327252C (en) * | 2005-05-20 | 2007-07-18 | 中国科学院上海技术物理研究所 | Light weight large-bore compound reflector |
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