CN106019436A - Full carbon fiber composite material reflection lens for optical system and manufacturing method - Google Patents
Full carbon fiber composite material reflection lens for optical system and manufacturing method Download PDFInfo
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- CN106019436A CN106019436A CN201610607468.6A CN201610607468A CN106019436A CN 106019436 A CN106019436 A CN 106019436A CN 201610607468 A CN201610607468 A CN 201610607468A CN 106019436 A CN106019436 A CN 106019436A
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- carbon fiber
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B5/00—Optical elements other than lenses
- G02B5/08—Mirrors
Abstract
The invention discloses a full carbon fiber composite material reflection lens for an optical system and a manufacturing method. A carbon fiber composite material is used for manufacturing each component of the reflection lens, and the full carbon fiber composite material reflection lens is obtained by adhesively-bonded cocuring. The anti-deformation performance is strong, the thermal stability is good, and the temperature matching problem of the reflection lens and camera other composite material structures is solved. According to the manufacturing technology, the high precision full carbon fiber composite material reflection lens can be manufactured in a short time, and compared with a conventional reflection lens manufacturing process, the technology has the advantages of short manufacturing cycle and low manufacturing cost.
Description
Technical field
The present invention relates to a kind of optical system full carbon fiber composite material reflector and manufacture method, belong to first
Enter technical field of composite materials.
Background technology
Remote sensing is the Main Means realizing investigation real-time and round-the-clock to military target, and the level of remote sensing camera is certainly
Determine the level of modernization of a national national defence, thus since the eighties in last century, remote sensing camera is alive
Boundary each power between competitively develop, the most representative be the U.S. IKNOS, SPOT5, KH series etc. phase
Machine, its resolution has reached the level of 0.2 meter.Along with the development of remote sensing observations technology, earth observation and space
The resolution that detection requires is more and more higher, and corresponding optics bore is the most increasing.Heavy caliber, high-resolution
Reflecting mirror has become as the inexorable trend of Space Remote Sensors development.But strengthen the optics bore of spacing reflection mirror,
The increase of reflecting mirror weight and volume can be caused, and under spatial environments, thermal deformation resistant ability declines；Also simultaneously
Add launch cost.Therefore, lightweight is the inevitable choice of spacing reflection mirror, is also optical system light weight
Change the Pinch technology being badly in need of solving.
The new material using high-strength light disclosure satisfy that the design requirement of light reflection mirror.The light weight of optical system
Changing needs to manufacture material and has high intensity, high-modulus and have relatively low density simultaneously.Zerodur, SiC relatively
Deng traditional material, carbon fibre composite specific stiffness is higher, and thermal deformation coefficient is low, and heat stability is best；With
Time there is good manufacturability and designability, moulding process is ripe, it is possible to farthest realize reflecting mirror
Heavy caliber and lightweight requirements.CFRP material is applicable not only to manufacture reflecting mirror, it is achieved large caliber reflecting mirror
Lightweight；Microscope base, pedestal and supporting constructions at the same time as optical system etc. manufacture material, solve
The temperature matching of reflecting mirror and optical system other carbon fiber composite structures.
China conducts a research late in terms of carbon fiber composite material reflector, and Research foundation is poor, and abroad
Blockade on new techniques to China, brings the least difficulty to development to a certain extent.Owing to degree-of-difficulty factor is high, state
Interior progress is slow.Up to the present remain in the research of lab scale chip level reflecting mirror, also there is no ripe answering
Report；The development of large caliber reflecting mirror is especially without clear and definite project.Application foundation about the direction
Research need to be strengthened as early as possible.The material that prior art does not solve carbon fiber composite material reflector self is thermally matched
Problem, does not the most solve the thermally matched problem of itself and other lightweight composite structures of optical system.
Summary of the invention
The technical problem to be solved: for overcoming the deficiencies in the prior art, it is provided that a kind of optical system
System is by full carbon fiber composite material reflector and manufacture method, to solve the heat of carbon fiber composite material reflector
Matching problem.
The technical solution of the present invention:
A kind of full carbon fiber composite material reflector of optical system, include from top to bottom homogeneous layer, minute surface base,
Honeycomb texture, backboard and the flange of periphery parcel,
Homogeneous layer is the ultrashort carbon fibre reinforced composite of monolayer, and carbon fiber mass content is 5%～10%,
Minute surface base is high mould or the superelevation modules carbon fibre composite of ultralow fiber areal densities, and surface density is little
In 100g/m2, minute surface base laying is as the criterion isotropic laying,
Honeycomb texture, backboard and flange are same middle mold or high-modules carbon fibre composite, backboard and flange are
Multiple structure, backboard and flange laying are as the criterion isotropic laying,
Homogeneous layer, minute surface base, honeycomb texture, backboard and flange are gluedd joint by adhesive.
Homogeneous layer material is carbon nano-fiber or the cyanate ester resin composite material of CNT enhancing.
Homogeneous layer thickness is not more than 0.2mm.
The thickness in monolayer of the prepreg that homogeneous layer, minute surface base, honeycomb texture, backboard and flange are used exists
Between 0.03～0.20mm, the resin of prepreg is epoxy resin or the cyanate ester resin that hydroscopicity is less than 2%,
Resin content is between 30%～45%.
Adhesive is epoxy resin or the cyanate ester resin adhesive that hydroscopicity is less than 2%, and resin content exists
Between 30%～45%.
The reinforcement of minute surface base material is M40J, M55J or M60 carbon fiber.
The reinforcement of honeycomb texture, backboard and flange material is T800, M40J or M60 carbon fiber.
A kind of optical system by full carbon fiber composite material reflector manufacture method, concretely comprises the following steps:
(1) optical mirror plane formable layer: make mould, precision PV≤0.1 μm after die surface process, RMS
≤ 10nm, surface roughness RMS≤10nm；
Cyanate ester resin prefabricated material paving carbon nano-fiber or CNT strengthened is at die surface, at it
On by the high mould of ultralow fiber areal densities or superelevation modules carbon fibre prepreg with quasi-isotropic ply stacking-sequence paving,
Stand-by optical frames surface layer is obtained after solidification；
(2) backboard, flange molding: make backboard, flange flat plate mold, by fine to multilamellar middle mold or high mould carbon
Dimension prepreg on backboard, flange mould, obtains stand-by with quasi-isotropic ply stacking-sequence paving after solidification
Backboard and flange；
(3) glued joint: by specular layer, cementing glued membrane, honeycomb, cementing glued membrane, backboard axle center pair successively
Stack together, then flange is laid about and spacing, it is thus achieved that product to be solidified；
(4) the coating product isolating membrane to be solidified that step (3) obtained, non-porous film, airfelt, vacuum
Bag, enters solidification and obtains reflecting mirror.
In step (3), honeycomb is fabric with holes, and manufacturing material is carbon fiber reinforced cyanate composite material.
In step (1) and step (2), the condition of solidification is: low-temperature setting under the conditions of 90 DEG C～100 DEG C
Under the conditions of 120 DEG C～130 DEG C intermediate temperature setting or under the conditions of 170 DEG C～180 DEG C hot setting, during solidification
Between 3h～6h, carry out in the autoclave that pressure is 0.3MPa～0.6Mpa.
The condition of solidification is in step (4): low-temperature setting under the conditions of 90 DEG C～100 DEG C, or at 120 DEG C～
Intermediate temperature setting under the conditions of 130 DEG C, hardening time 3h～6h, at the autoclave that pressure is 0.1MPa～0.4Mpa
Inside carry out.
Present invention beneficial effect compared with prior art:
(1) carbon fibre composite is used for manufacturing each ingredient of reflecting mirror by the present invention, and glueds joint the most solid
Changing and obtain full carbon fiber composite material reflector, its anti-deformation is strong, and Heat stability is good solves reflection
Mirror and the temperature matching of other composite structures of camera, this manufacturing technology can manufacture at short notice
Go out high-precision full carbon fiber composite material reflector, the manufacturing process of relatively conventional reflecting mirror, this technology system
Cycle of making is short, low cost of manufacture；
(2) full carbon fiber honeycomb is used as mirror structure core, full carbon fiber honeycomb light weight by the present invention first
Rigidity is high, can meet the design requirement that reflecting mirror rigidity is high；
(3) present invention is that domestic trial first produces space camera system and reflect with full carbon fibre composite
Mirror, this manufacturing technology can realize the manufacture of high accuracy composite materials, it is possible to extends to whole optics
The manufacture of system mirror, expands high accuracy composite technology application in optical system.
Accompanying drawing explanation
Fig. 1 is present configuration schematic diagram；
Fig. 2 is manufacturing flow chart of the present invention.
Detailed description of the invention
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings:
Full carbon fiber composite material reflector is composite honeycomb sandwich structures, as it is shown in figure 1, from up to
Under be followed successively by homogeneous layer 1, minute surface base 2, carbon fiber honeycomb texture 3, backboard 4 and periphery parcel 5.Homogeneously
Layer 1 is the ultrashort carbon fibre reinforced composite of monolayer, and its thickness is not more than 0.2mm, carbon fiber mass content
Being 5%～10%, minute surface base 2 is high mould or the superelevation modules carbon fibre composite of ultralow fiber areal densities, as
M40J, M55J or M60, minute surface base 2 surface density is no more than 100g/m2, minute surface base 2 laying is as the criterion every
Same sex laying, honeycomb texture 3, backboard 4 and flange 5 are same middle mold or high-modules carbon fibre composite,
If T800, M40J or M60, backboard 4 and flange 5 are multiple structure, backboard 4 and flange 5 laying are as the criterion
Isotropic laying, carbon fiber honeycomb texture 3 is with holes, form of fabric.
Homogeneous layer 1 material is carbon nano-fiber or the cyanate ester resin composite material of CNT enhancing.
The list of the prepreg that homogeneous layer 1, minute surface base 2, honeycomb texture 3, backboard 4 and flange 5 are used
Layer thickness is between 0.03～0.20mm, and the resin of prepreg is epoxy resin or the cyanogen that hydroscopicity is less than 2%
Acid ester resin, resin content is between 30%～45%.
Homogeneous layer 1, minute surface base 2, honeycomb texture 3, backboard 4 and flange 5 are gluedd joint by adhesive, glue
Glutinous agent is epoxy resin or the cyanate ester resin that hydroscopicity is less than 2%, and resin content is between 30%～45%.
A kind of optical system full carbon fiber composite material reflector manufacture method, its manufacturing process are shown in Fig. 2,
Concretely comprise the following steps:
(1) optical mirror plane formable layer
Construction features according to optical mirror plane and surface precision, use high accuracy sanding and polishing at mold base work surface
Technology processes high-precision mold, and precision PV≤0.1 μm after the process of tool surface, RMS≤10nm, surface is thick
Rugosity RMS≤10nm；Mold material can be rustless steel, invar, super-low expansion coefficient glass etc.；By nanometer
The cyanate ester resin prefabricated material paving that carbon fiber or CNT strengthen is at die surface, thereon by ultralow fibre
The high mould of dimension surface density or superelevation modules carbon fibre prepreg, with quasi-isotropic ply stacking-sequence paving, obtain after solidification
To stand-by optical frames surface layer.
(2) backboard, flange molding
According to the construction features of reflecting mirror, backboard uses formpiston design, and flange uses former design, mould mould
Tool material can be rustless steel, invar etc..By multilamellar middle mold or high-modules carbon fibre prepreg with quasi-isotropic paving
Layer order paving, on backboard 4, flange 5 mould, obtains stand-by backboard 4 and flange 5 after solidification.
(3) carbon fiber composite material reflector glueds joint
Specular layer, plate core rubber knot glued membrane, carbon fiber honeycomb, plate core rubber knot glued membrane, backboard are folded successively
Put, then flange laid about, is alignd in axle center, be placed in special frock, and use pin spacing,
Ensure panel and honeycomb core not core shift in solidification process, obtain product to be solidified.
(4) step (3) is obtained coating product to be solidified auxiliary material, including isolating membrane, non-porous film,
Airfelt, vacuum bag, enter autoclave and realize the splicing co-curing of reflecting mirror, regulation curing process parameter thus
Control heat distortion amount, it is ensured that the surface precision of solidification back mirror, after co-curing, obtain full carbon fiber composite
Material reflecting mirror.
The thickness in monolayer of above-mentioned used prepreg is between 0.03～0.20mm, and resin content is 30%～45%
Between；
In step (1) and step (2) in solidification process carry out in autoclave, solidification temperature be with
Any one in lower three kinds: 1. low-temperature setting, solidification temperature at 90 DEG C～100 DEG C, 2. intermediate temperature setting,
Solidification temperature is at 120 DEG C～130 DEG C, and 3. hot setting, solidification temperature is at 170 DEG C～180 DEG C.In autoclave
Hardening time 3h～6h, hot pressing pressure inside the tank 0.3MPa～0.6Mpa.
In step (4), solidification process is carried out in autoclave, and solidification temperature is following two: 1. low temperature
Solidification, solidification temperature is at 90 DEG C～100 DEG C, and 2. intermediate temperature setting, solidification temperature is at 120 DEG C～130 DEG C；Heat
Pressure in-tank-solidification time 3h～6h, hot pressing pressure inside the tank 0.1MPa～0.4Mpa.
Specifically: the thickness in monolayer of the prepreg that minute surface base 2 is used is 0.09mm, and resin content is 40%；
The thickness in monolayer of the prepreg that backboard 4, flange 5 use is 0.14mm, and the resin of prepreg is that hydroscopicity is little
In the epoxy resin of 2%, resin content is 34%；The prepreg that carbon fiber honeycomb 3 uses, for plain weave with holes
Form of fabric, thickness in monolayer is 0.1mm, and resin content is 36%；Adhesive is the ring that hydroscopicity is less than 2%
Epoxy resin adhesive；
In in step (1) and step (2), solidification process is carried out, during solidification temperature is in autoclave
Temperature solidification, solidification temperature at 120 DEG C～130 DEG C, 4h hardening time in autoclave, hot pressing pressure inside the tank 0.6Mpa.
In step (4), solidification process is carried out in autoclave, and solidification temperature is intermediate temperature setting, solidification temperature
Degree is at 120 DEG C～130 DEG C；3h hardening time in autoclave, hot pressing pressure inside the tank 0.3Mpa.
Full carbon fiber composite material reflector manufacturing technology, is used for manufacturing reflecting mirror by carbon fibre composite each
Individual ingredient, and glued joint co-curing and obtain full carbon fiber composite material reflector.First that light weight rigidity is high
Full carbon fiber honeycomb be used as mirror structure core；Special limiting tool location is used to realize each group of reflecting mirror
Become the coaxial of part.This manufacturing technology can produce high-precision full carbon fibre composite at short notice
Reflecting mirror；The manufacturing process of relatively conventional reflecting mirror, this technology manufacturing cycle is short, low cost of manufacture.Simultaneously
It is consistent that reflecting mirror manufactures material with the microscope base of lightweight optical system, pedestal and supporting construction etc., solves
Reflecting mirror and the temperature matching of other composite structures of camera.
The present invention is not disclosed content and is known to the skilled person general knowledge.
Claims (14)
1. the full carbon fiber composite material reflector of optical system, it is characterized in that, include homogeneous layer (1), minute surface base (2), honeycomb texture (3), backboard (4) and the flange (5) of periphery parcel from top to bottom；
Homogeneous layer (1) is the ultrashort carbon fibre reinforced composite of monolayer, and carbon fiber mass content is 5%～10%；
Minute surface base (2) is high mould or the superelevation modules carbon fibre composite of ultralow fiber areal densities, and surface density is no more than 100g/m2, minute surface base (2) laying is as the criterion isotropic laying；
Honeycomb texture (3), backboard (4) and flange (5) are same middle mold or high-modules carbon fibre composite; backboard (4) and flange (5) are multiple structure, and backboard (4) and flange (5) laying are as the criterion isotropic laying；
Homogeneous layer (1), minute surface base (2), honeycomb texture (3), backboard (4) and flange (5) are gluedd joint by adhesive.
2. a kind of full carbon fiber composite material reflector of optical system as claimed in claim 1, it is characterised in that homogeneous layer (1) material is carbon nano-fiber or the cyanate ester resin composite material of CNT enhancing.
3. a kind of full carbon fiber composite material reflector of optical system as claimed in claim 1, it is characterised 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 claimed in claim 1, it is characterized in that, the thickness in monolayer of the prepreg that homogeneous layer (1), minute surface base (2), honeycomb texture (3), backboard (4) and flange (5) are used is between 0.03～0.20mm.
5. a kind of full carbon fiber composite material reflector of optical system as claimed in claim 4, it is characterised in that the resin of prepreg is epoxy resin or the cyanate ester resin that hydroscopicity is less than 2%.
6. a kind of full carbon fiber composite material reflector of optical system as claimed in claim 5, it is characterised in that prepreg resin content is between 30%～45%.
7. a kind of full carbon fiber composite material reflector of optical system as claimed in claim 1, it is characterised in that adhesive is epoxy resin or the cyanate ester resin that hydroscopicity is less than 2%.
8. a kind of full carbon fiber composite material reflector of optical system as claimed in claim 7, it is characterised in that adhesive resin content is between 30%～45%.
9. a kind of full carbon fiber composite material reflector of optical system as claimed in claim 1, it is characterised in that the reinforcement of minute surface base (2) material is M40J, M55J or M60 carbon fiber.
10. a kind of full carbon fiber composite material reflector of optical system as claimed in claim 1, it is characterised in that the reinforcement of honeycomb texture (3), backboard (4) and flange (5) material is T800, M40J or M60 carbon fiber.
11. 1 kinds of optical systems are by full carbon fiber composite material reflector manufacture method, it is characterised in that: concretely comprise the following steps:
(1) optical mirror plane formable layer: make mould, precision PV≤0.1 μm after die surface process, RMS≤10nm, surface roughness RMS≤10nm；
Cyanate ester resin prefabricated material paving carbon nano-fiber or CNT strengthened at die surface, thereon by the high mould of ultralow fiber areal densities or superelevation modules carbon fibre prepreg with quasi-isotropic ply stacking-sequence paving, obtains stand-by optical frames surface layer after solidification；
(2) backboard, flange molding: make backboard (4), flange (5) flat plate mold; by multilamellar middle mold or high-modules carbon fibre prepreg with quasi-isotropic ply stacking-sequence paving on backboard (4), flange (5) mould, obtain stand-by backboard (4) and flange (5) after solidification；
(3) glued joint: specular layer, cementing glued membrane, honeycomb, cementing glued membrane, the alignment of backboard (4) axle center successively are stacked, then laid about and spacing by flange (5), it is thus achieved that product to be solidified；
(4) the coating product isolating membrane to be solidified that step (3) obtained, non-porous film, airfelt, vacuum bag, enter solidification of hot-press tank and obtain reflecting mirror.
12. optical systems as claimed in claim 11 a kind of are by full carbon fiber composite material reflector manufacture method, it is characterised in that: in step (3), honeycomb is fabric with holes, and manufacture material is carbon fibre reinforced composite.
13. optical systems as claimed in claim 11 a kind of are by full carbon fiber composite material reflector manufacture method, it is characterized in that: in step (1) and step (2), the condition of solidification is: under the conditions of 90 DEG C～100 DEG C low-temperature setting or under the conditions of 120 DEG C～130 DEG C intermediate temperature setting or under the conditions of 170 DEG C～180 DEG C hot setting, hardening time, 3h～6h, was carried out in the autoclave that pressure is 0.3MPa～0.6Mpa.
14. optical systems as claimed in claim 11 a kind of are by full carbon fiber composite material reflector manufacture method, it is characterized in that: in step (4), the condition of solidification is: 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, was carried out in the autoclave that pressure is 0.1MPa～0.4Mpa.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106739192A (en) * | 2016-11-22 | 2017-05-31 | 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 |
| CN109581556A (en) * | 2018-11-26 | 2019-04-05 | 中国科学院长春光学精密机械与物理研究所 | A kind of carbon fiber composite material reflector preparation process |
| CN110422344A (en) * | 2019-08-12 | 2019-11-08 | 航天材料及工艺研究所 | A kind of satellite compound flywheel of large rotating inertia lightweight 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 |
| CN114030241A (en) * | 2021-10-11 | 2022-02-11 | 航天材料及工艺研究所 | Carbon fiber composite material honeycomb, preparation method and application |
| 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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| CN106739192A (en) * | 2016-11-22 | 2017-05-31 | 北京空间机电研究所 | A kind of full carbon fiber composite material reflector substrate and preparation method thereof |
| 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 |
| CN109581556A (en) * | 2018-11-26 | 2019-04-05 | 中国科学院长春光学精密机械与物理研究所 | A kind of carbon fiber composite material reflector preparation process |
| CN110422344A (en) * | 2019-08-12 | 2019-11-08 | 航天材料及工艺研究所 | A kind of satellite compound flywheel of large rotating inertia lightweight and preparation method thereof |
| 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 |
| CN114030241A (en) * | 2021-10-11 | 2022-02-11 | 航天材料及工艺研究所 | Carbon fiber composite material honeycomb, preparation method and application |
| 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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|---|---|
| CN106019436B (en) | 2018-08-31 |
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