Multi-layered coating of thin-walled envelope from polymer composite material of space antenna reflector
SUBSTANCE: multilayered coating contains three successive layers with an even thickness: a lower mirror metal radio-reflecting skin-layer of pure aluminium, an intermediate protective thermoregulatory dielectric layer of zirconium dioxide and an upper protective wear-resistant highly strong diamond-like carbon layer.
EFFECT: provision of the operation in extreme conditions of open space due to the application of a thin substrate-envelope from a polymer composite material.
3 cl, 1 dwg
The technical field
The invention relates to the field of coatings used in space vehicles, namely multi-layer composite coating of mirror space antennas with reflectors made of polymer composite materials (PCM) - carbon fiber.
The level of technology
Space antenna reflectors require protection from the space environment, exposing them to abrupt temperature changes, wear and tear from exposure to various particulate fluxes, radiative impact of a large flow of charged particles. Protect antennas from the active space environment is a specific problem, because usually the materials used to protect equipment spacecraft interfere with normal passage and the transmission of radio signals.
The urgency of improving the coverage space of the antenna reflector is dictated by the necessity of creation of reflectors for a new generation of communications satellites intended for long-term (>15 years) of service in a geostationary orbit. Upcoming satellites is to be equipped with reflectors with high stability of shape, size and radiotray characteristics (coefficient of radioterapia 0,98) when working in the frequency range from 4 to 40 GHz and having a low linear mass at the level not exceeding 2,5 kg/m2 .
When driving on a geostationary orbit reflector will fall into the Earth's shadow and cool to very low temperatures (down to -150°C) and at the exit from the shadows intensively heated by direct solar radiation (up to +150°C). The resulting temperature can be a major cause of distortion of the shape of the reflector and the violation of the beam, reducing the communication quality. To satisfy the conflicting requirements of low linear mass and high stability of shape and size of the shell of the reflector must be thin and have high rigidity. The best structural material for solving this problem is the carbon fiber. Because the use of active control systems for these ultra-light reflectors are excluded, then the only real way to maintain thermal regime of the reflector can be applied to radiotray layer reflector thermal control coatings and protective wear-resistant coatings on particulate and meteorite impacts.
Thus, it is necessary to create a multifunctional combined coating capable of providing a number of stringent technical requirements of the job reflector in the open space: transparency and radiotrain for a wide range of signals RA is iocality; expansion and wear protection, low weight. All this is practically possible to implement only through the thin multi-layer coating, where each layer has a functional specialization, and together all the layers of the coating in the hard limits affect the execution of the main radiodrama function of the antenna reflector.
In previous prior art has used various materials, meeting some of the above requirements, but not completely and not all at the same time. It was also associated with problem use of specific technologies thin (micro - and nanoscale) of the coating layers is guaranteed to provide reliable high-quality connections (cohesion, adhesion) them to each other.
Selected through a patent search on grounds offer cover for completeness prior art analogues of multilayer coatings divided into 2 groups:
analogs that are closer in composition of the coating layers and the applied technology of their application to the substrate and to each other, but not similar in their areas of application and technical tasks (RF patent 2487190 (IPC C23C 22/34 posted: 10.07.2013) on the basis of a PCT-application WO 2007121898; RF patent 2467878 (IPC B32B 15/04, published: 27.11.2012), RF patent 2360032 (IPC C23C 14/24, C23C 14/06, B32B 15/04, B82B 3/00, published: 27.06.2009));
and Vice versa: the analogues, similar parimenti in space technology, but less similar (in comparison with the first group analogues) on the composition of the layers and their application technologies (RF patent 2269146 (IPC G02B 1/10, B64G 1/58 published: 27.01.2006), RF patent 2087392 (IPC B64G 1/58 published: 20.08.1997) (U.S. patent similar US 5273815 (IPC B32B 7/02; B64G 1/58; H01Q 1/00; H01Q 1/42; H05F 1/00; H05F 1/02; (IPC1-7): B32B 15/08; B32B 27/00; B32B 9/04; H01Q 15/24 published: 28.12.1993)).
From the first group analogues closest object coatings described in the patent of the Russian Federation 2487190. The invention relates to the manufacture protected from corrosion and primarily with gloss metallic or non-metallic substrate, as well as to the most protected from corrosion and primarily with gloss metallic or non-metallic substrate and its application. Specifically in one of the many choices on offer cover can be used on non-metallic substrate (including a plastic layer of pure aluminium with mirror surface and on top of the protective layer, including Zirconia; however, one of the technologies of coatings of possible cathode sputtering (synonym: magnetron deposition of layers) in high vacuum.
However, this coating does not contain a protective wear-resistant almatadema (DLC - diamond like coating) layer, is not intended for use in space technology (the closest thing is the label provided with a coating substrate as the outer parts of the aircraft) and, accordingly, the technical problem is the preservation of the very high corrosion resistance of the substrate even under the influence of mechanical load.
RF patent 2467878 from the first group counterparts, though to protect in the first place vacuum technology magnetron sputtering layers of thermal barrier coatings on articles of copper (similar material with aluminum), but also contains the description and the heat multilayer coating of nanostructured surface layer of the product with nanostructured metal sublayer of zirconium and upper nanostructured ceramic layer of zirconium oxide and yttrium oxide from 2 at.% up to 8 at.% and having a globular grain structure. The obtained heat-shielding coating has high adhesive strength, heat resistance and resistance to cracking when the products in the conditions of thermal Cycling and high temperature. The coating can be used in aerospace and other fields.
However, this coating does not contain a protective wear-resistant almatadema (DLC) layer and is not intended for use in space technology, specifically in the shell space antenna reflectors.
In the patent of the Russian Federation 2360032 the invention is intended for the application of plasma (similar to magnetron) m is Todd superhard diamond-like (DLC) coatings on products from a variety of materials (including ceramics, plastic), before applying a layer of diamond-like film pre-applied layer of metal: aluminum, zirconium, or their oxides, or mixtures thereof. In the structure of the multilayer diamond-like coating on the original product (substrate) applied adhesive layer, then the transition layer metal-carbon, which is diamond-like film. The result is wear-resistant super hard multi-coating, which can be used in mechanical engineering, nanotechnology, etc. Increases the adhesion, wear resistance and thermal stability of diamond-like coatings.
However, this coating is not intended for use in space technology, specifically in the shell space antenna reflectors made of composite material - carbon fiber, and contains no layers of pure aluminium with mirror reflecting surface and Zirconia as the expansion of the protective layer.
From the second group of selected analogs of known protected by patents in many countries layered shell to provide thermal and electrostatic protection elements of space technology, including fairing reflector antenna of the spacecraft (RF patent 2087392, IPC B64G 1/58 published: 20.08.1997). Although the main objective is protection from hostile is Reda, minimizing the total weight of the coating is also significant. As a result, the coating is a durable material capable of thermal and electrical protection, easy and transparent for a wide range of radio frequency signals. Layered membrane that is transparent to radio frequency radiation, contains conductive layer (in the preferred embodiment, conductive layer contains a semiconductor, such as germanium) to dissipate electrostatic discharges and thermal management layer for reflecting heat radiation and reduce the effects of temperature changes on the one hand layered shell on the area on the other side.
The disadvantage of this coating is not taking into account the peculiarities of thin ultra-lightweight Foundation-substrate (parabolic shell antenna) made of polymer composite materials - carbon fiber, designed for operation in space antenna reflector with a high coefficient of radioterapia (value of 0.98) in the extreme conditions of outer space and the requirements of very low deformability complex profile of the shell due to the requirement of high quality reflector, and also wear-resistant enclosure protection from particulate flows. But this coverage provides electrostatic protection, which practically is not required for small space antenna reflector is a torus. Also in this invention does not say anything about the used technologies for the deposition of layers on each other, which does not allow to judge about the reliability of their adhesion to each other.
Finally, the known multi-layer coating for elements of space technology (patent RF 2269146, IPC G02B 1/10, B64G 1/58 published: 27.01.2006) consisting of a substrate with transparent conductive coating on the outer surface and a reflective coating on the back surface, is made in the form of a metal film with high reflectivity in the wavelength interval of 0.3...2.4 μm. Transparent conductive coating includes at least 2 layers, one layer contains a cerium oxide, and the substrate is made of polyimide polymer film. The outer layer of transparent conductive coating may be made in the form of a thin (of the order of 0.05 microns) transparent radiation-resistant and wear-resistant layer, for example of SiO2. One of the layers of transparent conductive coating may be made on the basis of tin oxide SnO2doped cerium oxide CeO2or on the basis of In2O3. The cross-section of the coating consists of a substrate, made in the form of a polymeric film, a conductive coating on the front side of the substrate, and the conductive coating may include a protective wear-resistant layer. Multilayer pokr is ment also includes on the backside of the substrate metal reflecting layer, also provided with a protective coating. A reflective layer made of metal with high reflectivity, such as aluminum. A protective coating deposited on the outer side of the reflecting layer and comprises a solid corrosion-resistant compound, metal or alloy, and the metal or alloy may be partially or fully oxidized. The conductive coating is made of optically transparent radiation resistant inorganic material-based oxide semiconductor, such as indium oxide, and may have wear-resistant inorganic layer (e.g., SiO2) on the outer surface. Multilayer coating is intended for use as a thermal control coating class ”solar reflector” when applying it using a conductive adhesive layer on the outer surface, mostly teploizolyatsii the spacecraft surface. Through the use of not less than 2 layers of conductive coatings, one of which contains cerium oxide (CeO2), increases the resistance to abrasion (due to the high hardness of the cerium oxide) and increases the stability properties of the substrate under the action of electromagnetic radiation from the Sun. Due to the implementation of conductive coatings based oxide semiconductor is provided by the high radiation is donosti coverage, and the outer layer provides a high resistance to atomic oxygen (protects the conductive coating from damage by atomic oxygen in the ascent phase of a spacecraft into orbit and when operating in low-earth orbits).
However, this coating is intended primarily as a multi-layered flexible protective cover shields a large area of space technology and therefore not suitable for use in the shell space antenna reflectors, relatively small in size, but hard and practically very multifariously shaped shell of carbon fiber. And this coverage applies adhesive technology, which is almost impossible to use when applying micro - and nanoscale layers of the multilayer coating on the carbon substrate and to each other.
The analysis of all found and selected analogues none of them can be recognized as an explicit prototype of the proposed coverage due to a mismatch collectively solve their technical problems and their application to that which was specified in the present invention.
Disclosure of inventions
The task of the invention is the development of the multi radiotracer, protective, thermal expansion and wear-resistant coatings for toncontin the x shells reflectors mirror space antennas with regard to thin the substrate-shell made of composite material carbon fiber, designed to work in extreme conditions of outer space.
The task is solved in that the proposed multi-layer coating of thin-walled shell made of composite material, primarily carbon, space antenna reflector, characterized by the presence of three consecutive layers with uniform thickness: bottom mirror metallic radiotray the skin layer of pure aluminum, an intermediate protective thermostatic dielectric layer of zirconium dioxide and the upper protective high-strength wear-resistant diamond-like (DLC), a carbon layer. Diamond-like carbon coating has getbasename and protective properties and high hardness.
For qualitative adhesion layers on the shell and on each other multilayer coating obtained by the method of "cold" magnetron sputtering in a vacuum for a single set of shell reflector in a vacuum magnetron sputtering chamber with cathode emitters all required to cover the material components.
The thickness of the shell parabolic profile of the polymer composite, mainly fibrous carbon is from 1 to 2 mm, thickness radiotracer mirror aluminum (Al) layer is about 2 μm, the thickness of armarego the dominant protective layer of zirconium dioxide (ZrO 2) - about 35 nm and the thickness of the wear-resistant layer of diamond-like (DLC) nanostructured carbon is of the order of 20 nm.
List of figures
Fig.1 - installation diagram of the deposition layers offer coatings by magnetron sputtering in a vacuum.
The implementation of the invention
This invention is located at the intersection of materials science significantly dissimilar materials with different physical-chemical properties and technology almost bezdetonatsionnoy application with the required adhesion layer coatings ultra-small thickness (nano - and micro-size) on the basis of a relatively large area (about 1 m2) in relation to the small thickness (about 1 mm) of complex geometric (first parabolic) profile, which is necessary for the proper functioning of the antenna must be saved with deviations deformation of the profile within a maximum of 0.3 mm as in the coating process and during subsequent operation in various conditions of extreme cosmic impacts, such as large temperature fluctuations (from -150 to +150°C), high exposure to ionizing radiation, corpuscular streams, and so on
In the composition of the multilayer coating included radiotray aluminum skin layer, the optimum thickness of 2 μm, thermal protective layer of zirconium dioxide ZrO2the optimal thickness of 35 nm and protective the layer of diamond-like nanostructured material, the optimum thickness of 20 nm. The result is increased reliability, multi-function protection, weight reduction and long-term resistance to the effect of space factors mirror antenna reflectors spacecraft.
The composition radiotracer coating on the substrate (the shell of the reflector) of the fibrous carbon (with conductive fibers and dielectric filler - polymer (epoxy resin): metal coating (radiotray skin layer of aluminum); thermal control coating (zirconium dioxide) and external protective diamond-like carbon coating type DLC.
When this multilayer coating obtained by the method of "cold" (up to +100°C) magnetron multi-pass spray in vacuum, so that it is almost impossible to thermally deform in the process of applying layers of geometrically ready parabolic profile carbon substrate (shell) of the antenna reflector. For qualitative adhesion layers on the shell and on each other all multilayer coating must be obtained for the desired number of passes in a single set shell reflector in a vacuum magnetron sputtering chamber with cathode emitters (magnetrons) are all required to cover the material components.
In the sputtering process over the cathode surface burning the abnormal glow discharge in the ar environment is it, oxygen and vapors of the cathode material. The ionized atoms of the discharge are accelerated near-cathode voltage and bombard the cathode surface. Under the action of the bombing, the material of the cathode of the magnetron was sprayed, and the resulting flux of sputtered atoms are deposited on the substrate. In the presence of a vacuum chamber of atoms of different gases (oxygen, nitrogen etc) sprayed material forms a film of atoms of the target material atoms of gases (oxides, nitrides, etc.). Structurally, the magnetron sputtering system consists of a vacuum chamber, a cathode target of the anode and the substrate.
In Fig.1 the numbers represent: 1, 2 - magnetrons; 3 - the flux of sputtered atoms; 4 - snap on swivel device; 5 - sample for applying (spraying) layers; 6 - ion source (ion flow is directed to the sample); 7 - vacuum chamber; 8 - base of the vacuum chamber.
The process of deposition of the layers of the proposed coating by magnetron sputtering in a vacuum is the following. After pumping the vacuum chamber to a pressure of 6.7·10-3PA sprayed coating of aluminum. The discharge current of 4 A, the time of spraying 60 minutes. Working pressure of 1.3·10-1PA. In the 58th minute of the second magnetron to clean the surface of the zirconium cathode. At the 60th minute of the magnetron with an aluminum cathode off. After that, the camera putting the desired gas mixture, m is genetron with the cathode of zirconium reaches a stable mode of deposition of Zirconia for 3 minutes. After that, the samples at a turning device to turn the magnetron and sprayed Zirconia. The time of deposition is about 2 minutes. Then put diamond-like carbon coating. The time of deposition is about 3 minutes. In all industrial processes, the residual pressure is 7·10-3up to 8·10-3PA. The working pressure during the deposition of coatings is 1.2·10-1PA. The distance from the cathode magnetrons to the substrate is 300 mm, the Deposition is carried out in inert argon gas OFS brands of 5.5 on THE 2114-006-45905715-2010. Mass fraction of argon 99,9995%. As a reactive gas using oxygen OFS THE 6-21-10-83. Mass fraction of oxygen 99,999%.
1. Multilayer coating of thin-walled shell made of composite material space antenna reflector, characterized by the presence of three consecutive layers with uniform thickness: bottom mirror metallic radiotray the skin layer of pure aluminum, an intermediate protective thermostatic dielectric layer of zirconium dioxide and the upper protective high-strength wear-resistant diamond-like (DLC), a carbon layer.
2. The floor under item 1, characterized in that it is obtained by the method of "cold" magnetron sputtering in a vacuum for a single set of shell reflector in a vacuum magnetron Kama is the cathode emitters all required to cover the material components.
3. The floor under item 1 or 2, characterized in that the shell thickness of the parabolic profile of the polymer composite, mainly fibrous carbon is from 1 to 2 mm, thickness radiotracer mirror aluminum (Al) layer of about 2 μm, the thickness expansion of the protective layer of zirconium dioxide (ZrO2about 35 nm and the thickness of the wear-resistant layer of diamond-like (DLC) nanostructured carbon of the order of 20 nm.
FIELD: process engineering.
SUBSTANCE: invention can be used in finishing and control of telescope large mirrors. Mirror is placed on indexer with rear surface upward. At locations of auxiliary elements thrust metal rings are glued to adhesive resin for aligner ring to be fitted therein and positioned at indexer and locked by clamping screws to thrust rings. Plug-in sleeves are fitted in aligner rings to glue auxiliary elements to mirror. Thereafter, aligner rings are removed therefrom after hearing and softening of glue resin.
EFFECT: simplified design and positioning, higher precision; accelerated jobs.
SUBSTANCE: method includes electroplating an aluminium alloy workpiece with a nickel alloy and finishing the working surface of the workpiece by polishing to the required roughness in several steps on a polishing stand using an abrasive composition. Dispersion of the abrasive composition is reduced at each subsequent step and a resin is used as the abrasive composition at the last step. The nickel alloy coating is removed after polishing and a reflecting layer is deposited on the inner surface of the coating.
EFFECT: providing the required smoothness of the working surface of a mirror coating without meeting strict precision requirements for the polishing tool.
SUBSTANCE: disclosed is a coating for a space mirror workpiece, which is glass of the following composition, wt %: SiO2 - 44-61; B2O3 - 8-20; Al2O3 - 5-19; CaO - 3-12; Sb2O3 - 0,3-0,7; V2O5 - 2-11; Nb2O5 - 1-7; MoO3 - 0.2-4 and F - 1.5-6.
EFFECT: composition of the material enables to obtain a high-quality optical surface directly on substrates made of silicon carbide materials.
SUBSTANCE: infrared reflector consists of a metal substrate, characterised by that it is coated with a layer of zirconium nitride and chromium nitride of general formula (ZrxCr1-x)1-yNy with x ranging from 0.15-0.7 and y ranging from 0.01 to 0.265. The method of production involves producing a metal substrate; depositing a layer of zirconium nitride and chromium nitride on said substrate by physical vapour deposition using a target which contains 15-70 wt % zirconium, with the remaining part consisting of chromium and impurities which are inevitable in the treatment process, and injecting nitrogen with a neutral carrier gas in ratio of 4/16 to 16/16 while simultaneously sputtering zirconium and chromium.
EFFECT: designing an infrared reflector, having high heat reflecting power and high resistance to high temperatures in corrosive or oxidative media.
SUBSTANCE: reflecting article includes a transparent substrate, having a first and a second base surface; a base layer formed on top of at least part of the second base surface; a primary reflecting coating formed on top of at least part of the base layer; an inorganic protective coating consisting of silicon dioxide, aluminium oxide or a mixture of silicon dioxide and aluminium oxide, formed on top of at least part of the primary reflecting coating; as well as a top coating which contain zinc stannate, formed between the primary reflecting coating and the inorganic protective coating. The base layer contains titanium dioxide with thickness of 1-3 nm.
EFFECT: higher reflecting power and longer operating life.
15 cl, 7 dwg
SUBSTANCE: unfolded large mirror reflector for spacecraft has a reflecting surface made from cells in form of mirror elements mounted on frames, an unfolding mechanism, hinges and retaining devices. The cells are in form of identically shaped lobes with identical reflecting surfaces lying radially from the centre to the round face of the reflector. In the folded position of the reflector, its lobes, inner frontal surfaces of which are parts of the cylindrical surface, lie over each other while facing the reflecting surfaces to one side. Elements of their retaining devices are connected to reciprocal parts of the retaining devices lying on a movable cylinder connected to the unfolding mechanism with an electromechanical drive, the outer diametre of which is less than the diametre of the cylindrical surface of the faces, with possibility of multiple translational and rotational transverse movements. Said movable cylinder lies inside not less than two concentric fixed uniform structures with cylindrical faces, having a surface for seating the lobes, and the first lobe is placed on the faces of the fixed structures, fixed on them in a position which corresponds to the working position.
EFFECT: high reliability, high directivity and simple technique for making the cells.
5 cl, 5 dwg
SUBSTANCE: reflector has a crystalline polymer in which crystalline and amorphous zones are adjacent, and the amorphous zone has a plurality of aligned layers which contain amorphous particles aligned in a predetermined direction. According to the method, the reflector is formed by stretching crystalline plastic material at temperature lower than the crystallisation temperature Tc of the crystalline polymer in the predetermined direction so as to form a plurality of stretched layers in the amorphous zone.
EFFECT: high reflecting power, simple technique for making the reflector, low production costs.
18 cl, 15 dwg
FIELD: physics, optics.
SUBSTANCE: invention relates to a thermally stable multilayer mirror for the extreme (short wave) ultraviolet (UV) spectral range and can be used as a heated collector mirror of a source of radiation in the extreme UV range. The multilayer mirror for reflecting radiation in the extreme UV range has multiple alternating molybdenum and silicon layers. On multiple boundary planes between the molybdenum and silicon layers there are barrier layers which contain silicon nitride or silicon boride, respectively.
EFFECT: high thermal stability, particularly stability at temperatures higher than 300°C, with high reflecting power of the multilayer mirror.
16 cl, 7 dwg
SUBSTANCE: mirror consists of a substrate and separation and reflecting layers. The substrate is made from composite material containing the following, vol. %: diamond 50-75, silicon carbide 20-45, silicon 3-20. The separation layer contains the following, vol. %: silicon carbide 10-35 and silicon 65-90. The method involves making a substrate, moulding a separation layer on its surface and optical processing of the surface and depositing a reflecting layer, wherein the separation layer is obtained by impregnating a porous carbon-fibre workpiece placed on the surface of the substrate with liquid silicon.
EFFECT: improved operational characteristics, simple technology of making the mirror.
3 cl, 1 tbl, 1 ex
SUBSTANCE: slits are made on the base of the mirror, which form elements in form of single-span beams with peripheral sections of the reflecting surface at opposite ends of the mirror. The ends of the beams are joined to the base by elastic supporting crosspieces lying at an acute angle to the optical axis of the mirror. The length of the beams, the length of the crosspieces and angle of inclination of the crosspieces are selected under the condition for conversion of thermal displacement of corresponding edges of the peripheral sections of the mirror into their translational displacement with a component which is unidirectional and comparable to the value of thermal deformation of the central part of the reflector.
EFFECT: provision for passive compensation for bending thermal deformation of the mirror when its radiation dose changes.
FIELD: process engineering.
SUBSTANCE: invention relates to a monocrystal with a garnet-type structure to be used in optical communication and laser processing devices. This monocrystal is described by general formula (Tb3-xScx)(Sc2-yAly)Al3O12-z, where 0<x<0.1; 0≤y≤0.2; 0≤z≤0/.3.
EFFECT: translucent monocrystal that can inhibit cracking at cutting.
5 cl, 3 dwg, 1 tbl, 5 ex
SUBSTANCE: invention relates to an immersion liquid which can be used in optical instrument-making for investigating optical parameters of inorganic materials and optical components, including large, irregularly shaped articles. The immersion liquid for optical investigation contains 97-99 wt % meta-bis(meta-phenoxyphenoxy)benzene and 1-3 wt % 2-naphthol. To reduce viscosity and surface tension, the immersion liquid may further contain 0.1-3 wt % dibutyl sebacate per 100 wt % of said composition.
EFFECT: disclosed immersion liquid is nontoxic, has a good refraction index nD>1,6 and high adhesion to inorganic optical materials, which enables to deposit on the entire surface of the investigated substrate or part thereof a thin immersion layer and use thereof for effective quality control of large optical articles without immersion in a cell with an immersion liquid.
2 cl, 2 dwg, 2 tbl, 2 ex
FIELD: physics, optics.
SUBSTANCE: invention relates to visible light absorbers, particularly novel azo compound monomers, particularly suitable for use in materials for implantable ophthalmic lens materials. The ophthalmic device material includes an azo compound, a device forming acrylic monomer and a cross-linking agent. The ophthalmic device is made from the ophthalmic device material and is in the form of intraocular lenses, contact lenses, keratoprostheses and corneal inlays or rings.
EFFECT: azo compounds are suitable for use as monomers which absorb part of the visible light spectrum (about 380-495 nm).
17 cl, 6 dwg, 3 tbl
SUBSTANCE: free form ophthalmic lens comprises a first optical zone portion comprising multiple voxels of polymerised crosslinkable material containing a photoabsorptive component. The optical zone portion comprises a first area having a first refraction index and a second area having a second refraction index; and a second portion comprising a layered volume of crosslinkable material polymerised beyond the gel point of the crosslinkable material.
EFFECT: obtaining ophthalmic lenses with a free form surface and areas with different refraction indices, which enable to correct vision by changing the focal distance.
18 cl, 19 dwg
FIELD: process engineering.
SUBSTANCE: invention relates to production of sandwiched materials used in thin-film instruments and devices. Proposed levelling film comprises levelling ply containing binding polymer resin and inorganic filler as components, at least, on one side of transparent polymer substrate. Note here that the number of foreign particles with mean diameter of 20-100 mcm on levelling air surface does not exceed 5 per m2.
EFFECT: decreased amount of linear defects at production of thin-film transistor on film surface.
3 cl, 1 tbl, 3 ex, 2 dwg
FIELD: physics, optics.
SUBSTANCE: group of inventions relates to producing a terbium aluminium garnet monocrystal which can be used as a Faraday rotator for optical insulators. In the terbium aluminium garnet monocrystal, a portion of aluminium is at least replaced with scandium and a portion of at least aluminium or terbium is replaced with at least one component selected from a group consisting of thulium, ytterbium and yttrium, wherein the garnet monocrystal has the general formula (Tb3-x-zSczMx) (Sc2-yMy) Al3O12 (1), where M represents at least one component selected from a group consisting of Tm, Yb and Y, and x, y and z satisfy the following relationship: 0<x+y≤0.30 and 0≤z≤0.30.
EFFECT: present monocrystal has a high light transmission factor in a wide wavelength range and a wide Faraday rotation angle with cracking-resistance.
8 cl, 3 dwg, 1 tbl, 12 ex
SUBSTANCE: invention relates to polymers for producing ionic silicone hydrogels suitable for making ophthalmic devices. Disclosed are polymers obtained from reactive components comprising at least one silicone-containing component which includes at least one trimethylsilyl group and at least one ionic component comprising at least one anionic group, which is a carboxylic acid-containing component. Also disclosed is a contact lens made from the disclosed polymers.
EFFECT: disclosed polymers demonstrate improved thermal stability and desirable protein uptake.
24 cl, 5 dwg, 10 tbl, 18 ex
SUBSTANCE: invention refers to ophthalmic devices and methods for preparing them. What is presented is a soft silicone hydrogel contact lens which possesses an ability to deliver a hydrophobic comfort-maintaining agent (phospholipid, glycolipid, glyceroglycolipid, sphingolipid, sphingoglycolipid, fatty alcohol containing 8 to 36 carbon atoms, or a mixture thereof) into the user's eye gradually releasing it from a polymer matrix consisting of hydrophobic chains formed of a silicon monomer or macromere, and hydrophilic chains formed of a hydrophilic monomer or macromere when in use. What is also presented is a method for making the above contact lens.
EFFECT: in the presented soft silicone contact lens, the hydrophobic comfort-maintaining agent is not covalently bond to the polymer matrix wherein it is distributed and can be released from the soft hydrogel contact lens into the user's eye when in use reliably for a long period of time and thereby reinforcing and stabilising a lipid layer of the lachrymal fluid film and reducing eye dryness.
16 cl, 2 tbl, 7 ex
FIELD: physics, optics.
SUBSTANCE: device has a base and a plurality of convex and concave structural elements arranged on the surface of the base with spacing which is equal to or less than the wavelength of visible light. The structural elements form a plurality of tracks and form a structure of a quadrangular or quasi-quadrangular array. In one version, each structural element has the shape of an elliptical or truncated elliptical cone, the long axis of which is parallel to the track. In another version, the ratio ((2r/P1)×100) of the diameter 2r to the spacing P1 is 127% or higher, where P1 is the spacing between structural elements on the same track, and 2r is the diameter of the lower surface of the structural element in the direction of the track. The method is carried out by forming a resist layer on the peripheral surface of a columnar or cylindrical standard mould, forming latent images via interrupted irradiation of the resist layer with a laser beam while rotating the standard mould with relative displacement of the laser beam spot parallel to its central axis, forming a resist structure via development thereof and forming structural elements by etching using the resist structure as a mask.
EFFECT: improved antireflection characteristics.
12 cl, 6 tbl, 67 dwg
SUBSTANCE: initial raw material in the form of a briquette of a powder of aluminium-magnesium spinel with stoichiometric composition, alloyed with 1 wt % of lithium fluoride is sintered in vacuum at a temperature of 1100-1500°C. The obtained briquette with a diameter equal to the diameter of the mould is loaded into the mould, with its further compression at a temperature of 1550-1600°C for 5-30 minutes under pressure of 350-500 kg/cm2, kept for 30-55 minutes and cooled.
EFFECT: obtaining a polycrystalline optical material from aluminium-magnesium spinel.
1 ex, 1 tbl
FIELD: engines and pumps.
SUBSTANCE: proposed attachment comprises rib with yoke and four extra threaded bosses with threaded ears, arc with four extra threaded bosses with threaded ears and lugs, braces, bosses, fasteners, lock nuts and clamp. Thrust plate with bolt is secured at said yoke. Threaded bush for mounting extra braces is fitted at lug threaded section and cotter-pinned thereat.
EFFECT: higher stiffness of attachment.
4 cl, 14 dwg