127 results about "Space optics" patented technology

The invention provides a composite detection method for a large-diameter non-spherical reflector with large deviation in a polishing process, and belongs to the technical field of space optics. The composite detection method solves the problem that in an existing zero compensation detection technology, part of interference fringes of a large-diameter non-spherical reflector with large deviation are lost. The method includes the first step of designing and manufacturing an optical compensator, the second step of setting up and calibrating an interference zero compensation detection optical path, the third step of establishing and adjusting a hartmann-splicing detection optical path, the fourth step of carrying out hartmann-splicing detection, the fifth step of conducting non-spherical multicycle processing and hartmann-splicing detection, the sixth step of carrying out combined detection and analysis and the seventh step of conducting non-spherical multicycle processing and combined detection. The method overcomes a difficulty of surface shape missing at an interference detection stage of the large-diameter non-spherical reflector with large deviation, and a zero compensation method and a hartmann-splicing detection method can be mutually contrasted and verified at a finishing polish stage finally so that accuracy and reliability of detection can be guaranteed.

This invention relates to a diversity receiving system for total digitalized space optical communication array signals including a host receiver and multiple under communication receivers mounted on the rotation unit of each universal shaft, each receiver includes a following module and a communication receiving module, the host receiver includes a host signal process module, each under communication receiver scans and follows signal sources on the total space angles independently and communicates with it, which can be used in the rigorous spacial laser channels including atmosphere sea channels of satellite and sea channels for under water target.

The invention provides a measuring and calculating method for a modulation transfer function of a satellite-borne camera, and relates to the technical field of space optics. According to the method,the problem that according to an existing method that a modulation transfer function is measured and calculated through point light sources, a parametric model is needed for approximation and fitting. Firstly, multiple point light source targets are laid before satellite transit, then images corresponding to point light sources are intercepted in captured images, after the background luminance value is removed, a two-dimensional point spread function is directly solved by the adoption of a regularization solving method according to an imaging mathematical model, and finally a modulation transfer function is calculated through the point spread function. The measuring and calculating method is easy to implement, the data processing process is simple, convenient and precise, and the method has a great significance in imaging quality assessment of the satellite-borne camera and has broad application prospects.

The invention relates to an optical system of an ultraviolet multi-band panoramic imaging instrument, relating to the technical field of space optics and solving the problem that an optical system of a conventional ultraviolet limb annular imaging instrument cannot realize imaging of a 360-degree annular field of view. The optical system is composed of a reflecting and refracting lens, a relay lens group, an optical filter and an area array detector, wherein the optical system is made of an ultraviolet material with the waveband scope of 250 nm to 380 nm; and the multi-waveband imaging is realized by selecting optical filter with different central wavelengths. The aperture diaphragm of the system is located in the relay lens group; the entrance beam of the 360-degree annular field of view becomes a virtual image through the reflecting and refracting lens; the image surface of the virtual image is located in the reflecting lens; the relay lens group images the virtual image of the reflecting and refracting lens for the second time, and finally forms an image on the area matrix detector. As a reflecting surface and a refracting surface are combined together, the optical system is relatively small and compact in structure, is suitable to be used as an optical system for ultraviolet limb panoramic imaging on a satellite, and is applied to the fields, such as atmospheric remote sensing for aerospace and aviation, earth observation and the like.

The invention discloses a high-specific stiffness supporting structure of a space optical remote sensor, and belongs to the technical field of space optics. The supporting structure solves the problems that in the prior art, a supporting structure of the space optical remote sensor is heavy, poor in stability and low in inherent frequency. The supporting structure comprises a carbon fiber front cylinder, a carbon fiber rear cylinder, a secondary mirror embedded part, a carbon fiber secondary mirror support, a carbon fiber supporting ring, a plurality of supporting ring embedded parts, truss rod connectors, a plurality of carbon fiber truss rods, truss embedded parts, a carbon fiber matrix, primary mirror assembly embedded parts, a three-mirror embedded part and a carbon fiber rear cover. The carbon fiber front cylinder is connected to the carbon fiber rear cylinder, the secondary mirror embedded part adheres to the middle of the carbon fiber secondary mirror support, the supporting ring embedded parts are circumferentially and uniformly distributed on the carbon fiber supporting ring, the front ends of the carbon fiber truss rods are connected to the back surface of the carbon fiber supporting ring, the rear ends of the carbon fiber truss rods are connected to the truss embedded parts of a main backboard assembly, and the carbon fiber rear cover, the truss assembly embedded parts, the three-mirror assembly embedded part and the primary mirror assembly embedded parts are connected to the carbon fiber matrix.

The invention relates to a coaxial aspheric surface four-reflecting mirror optical system with a long focal length short structure, and belongs to the optical system in the technical field of space optics. The invention aims at providing the coaxial aspheric surface four-reflecting mirror optical system with the long focal length short structure. The technical scheme is as follows: the coaxial aspheric surface four-reflecting mirror optical system comprises a primary mirror, a secondary mirror, a diaphragm, a third mirror, a fourth mirror, a planar reflecting mirror and a detector image surface, wherein the primary mirror and the secondary mirror are double-curved surface mirrors, and the third mirror and the fourth mirror are high-order aspheric surface mirrors. The primary mirror, the secondary mirror, the third mirror and the fourth mirror are coaxial, the secondary mirror is placed on a reflection light path of the primary mirror, the third mirror is placed on the reflection light path of the secondary mirror, the fourth mirror is placed on the reflection light path of the third mirror, the planar reflecting mirror is placed on the reflection light path of the fourth mirror, and the off-axis angle of the planar reflecting mirror against the detector image surface is minus 49 degrees. The aperture diaphragm is fixedly connected on a mirror frame of the secondary mirror, and the system adopts a field bias design. The system can get high pixel resolution and larger field of view and has compact structure and great application potential in the field of the space optics.

The invention provides a telecentric imaging system with field of view of 15 degrees and three coaxial reflectors, belongs to the space optics technical field, and relates to a telecentric off-axis three-reflector imaging system. A technical problem to be solved is providing a telecentric imaging system with field of view of 15 degrees and three coaxial reflectors. A technical scheme is as follows: the imaging system comprises a main mirror, a second mirror, a third mirror, an aperture diaphragm and an imaging surface, the main mirror, the second mirror, the third mirror and the aperture diaphragm are coaxial, and the main mirror and the third mirror are coplanar; the second mirror is placed on a reflected light path of the main mirror, the third mirror is placed on a reflected light pathof the second mirror, and the aperture diaphragm is placed on a mirror plane edge of the second mirror; in order to realize telecentric image space, a distance from the aperture diaphragm to the third mirror is half of a summit radius of curvature length of the third mirror; in order to realize wide field of view of 15 degrees, the second mirror is a convex spherical mirror, and the main mirror and the third mirror are concave quarticsurface mirrors; a distance from the second mirror to the third mirror is larger than half of a system image space focal length. According to the system, abundant ground resource information is obtained, and the system has low processing and adjusting difficulty.

The invention discloses an optimized and fused simulation space optics-electromagnetic shielding environment composite darkroom which is of a six-face square framework structure. Extinction microwave absorbing wedges (5) are spread over the inner sides of four side walls and the position below a ceiling in a mounted mode through a joist-frame carrier method, namely, the inner side of a six-face square framework is provided with a grid frame carrier (6) composed of a main joist (9) and an auxiliary joist (2), microwave absorbing bases (4) are densely distributed on the grid frame carrier (6) in a light-proof and mounted mode, and the extinction microwave absorbing wedges (5) are installed on the microwave absorbing bases (4). All visible surfaces of the extinction microwave absorbing wedges (5) are provided with extinction coatings (12). The optimized and fused simulation space optics-electromagnetic shielding environment composite darkroom can be used for measuring various characteristic parameters of microwave/infrared double-module products at the same time, and the space optics environment simulation and the space electromagnetic shielding environment simulation can be fused completely, the extinction ratio in a working area is improved to more than 95 percent from 90 percent, the electromagnetic shielding effectiveness is high, and the shielding effectiveness of the darkroom electrical property to 2GHZ-18GHZ microwave signals is 90dB.

The invention provides an oversized view field off-axis reflection system used for an imaging spectrometer and relates to the technical field of space optics. The oversized view field off-axis reflection system used for the imaging spectrometer solves the problems that an existing spectrometer is not large enough in view field and covering width and is long in return visit period. The oversized view field off-axis reflection system used for the imaging spectrometer comprises a first parasitic light eliminating diaphragm, a first reflector, a second parasitic light eliminating diaphragm, a depolarizer, an aperture diaphragm, a second reflector and an entrance slit. Parallel beams which are emitted by a target penetrate the first reflector through the first parasitic light eliminating diaphragm, are reflected and focused on the second parasitic light eliminating diaphragm through the first reflector, penetrates the second reflector through the depolarizer and the aperture diaphragm after leaving the second parasitic light eliminating diaphragm, and are focused and imaged to the entrance slit through the second reflector. Due to the adoption the optics system, the imaging spectrometer is oversized in view field, small in size, light in weight, free from blocking, small in parasitic light, high in deliver function, and wide in applicative wave band. The oversized view field off-axis reflection system used for the imaging spectrometer are applied in aerospace atmospheric remote sensing field, ocean water color sensing field, territorial resource sensing field and the like.

The invention relates to a flexible support frame for a small high-stability multifunctional optical reflector, and belongs to the technical field of space optics. The problems that the conventional supporting mechanism is only applicable to reflectors made of the same material, and the purposes and the size of the conventional supporting mechanism are limited are solved. The flexible support frame has a rectangular structure comprising a hollow circle, mechanical connecting platforms which are equal in width and have rectangular bump structures are processed on two sides of the flexible support frame, two mechanical connectors are respectively processed at two ends of each mechanical connecting platform, an optical machine connecting platform which has an annular bump structure is processed along the hollow circle, a recess structure is processed at the bottom of the optical machine connecting platform, an unloading base plate which has a sinking structure is processed between each mechanical connecting platform and the optical machine connecting platform, and an unloading slit which has a circular topological structure is processed on each unloading base plate. The flexible support frame is designed integrally, and is wide in application range and high in applicability, and the safety and the reliability of the flexible support can be increased.

The invention provides a periphery supporting mechanism of a reflecting mirror in a space remote sensing camera, and belongs to the periphery supporting mechanism of the reflecting mirror related in the technical field of space optics. The technical problem to be solved is to provide the periphery supporting mechanism of the reflecting mirror in the space remote sensing camera. The supporting mechanism comprises a mirror cell, flexible supporting slices and a bottom supporting plate, wherein the three flexible supporting slices are positioned between the mirror cell and the bottom supporting plate; the bottom of each flexible supporting slice is fixedly connected with the bottom supporting plate; the upper part of each flexible supporting slice is fixedly connected with the mirror cell; the three flexible supporting slices form a triangle structure opposite to the middle part of the mirror cell and the bottom supporting plate; the three flexible supporting slices are of class spring sheet structure in the form of a structure having thick upper side and thin lower side with the same width. The structure can pass large-magnitude vibration tests and can effectively reduce influence of temperature change and the like on surface figure precision on the premise of ensuring the surface figure precision of optical elements.

The invention discloses an optical system of a two-channel common-path minimized broadband imaging spectrometer, and relates to the technical field of space optics, solving the problems that an optical system of a conventional broadband imaging spectrometer is complex in structure and large in size and weight. The system comprises a first broadband pass filter, a second broadband pass filter, a first aperture diaphragm, a second aperture diaphragm, a telescope, an incidence slit, a first collimating mirror, a second collimating mirror, a plane grating, an imaging mirror and a detection image surface, wherein a light beam emitted from one same target is split into two channels through the first broadband pass filter and the second broadband pass filter, transmitted to the telescope through the first aperture diaphragm and the second aperture diaphragm, and subsequently imaged to the inclination slit through the telescope; after being emitted through the inclination slit, the light beam is transmitted to different areas of the plane grating through the first collimating mirror and the second collimating mirror, subjected to plane grating dispersion, transmitted to the imaging mirror, and subsequently imaged on one same detector image surface through the imaging mirror. The system is used in the aerospace and aviation atmospheric remote sensing field.

The invention relates to a photoinduced deformation thin film reflector surface shape control and measurement device, and belongs to the technical field of space optics. In order to solve the problems that an existing photoinduced deformation thin film reflector surface shape control and measurement device is complex in system, a surface shape control system is low in reliability, and the surface shape control accuracy is poor, the photoinduced deformation thin film reflector surface shape control and measurement device is characterized in that lasers transmitted by a laser device pass through a first laser collimating mirror to obtain collimating lasers, then adjustment on the polarization direction and the polarization state is completed through a free space optical isolation device and a polarization state controller to obtain single-polarization-state collimating lasers, the collimating lasers enter a liquid crystal space modulator through a laser splitter prism to conduct small-angle deflection, the deflecting directions of the collimating lasers are changed through a polarization rotator, then the collimating lasers are scanned by a birefringent prism to be output to the surface of a photoinduced deformation thin film to complete thin film tensile deformation, the lasers are scattered back through the photoinduced deformation thin film to enter a second laser collimating mirror through the birefringent prism, the polarization rotator, the liquid crystal space modulator and the laser splitter prism, and the lasers can be gathered through the second laser collimating mirror to reach a photoelectric detector.

The invention provides a telecentric off-axis three-mirror anastigmatic imaging system with three coaxial reflectors at an angle of field of view of 10 degrees, and belongs to the telecentric off-axis three-mirror anastigmatic imaging system relating to the technical field of space optics, aiming at providing the telecentric off-axis three-mirror anastigmatic imaging system with three coaxial reflectors at the angle of field of view of 10 degrees. The system is characterized by comprising a main mirror, a secondary mirror, a third mirror and an aperture stop which are coaxial, wherein the secondary mirror is placed on a reflecting optical path of the main mirror, the third mirror is placed on a reflecting optical path of the secondary mirror, and the aperture stop is placed on the edge ofthe front surface of the secondary mirror; in order to realize telecentric image, the distance from the aperture to the third mirror is half length of the radius of curvature to the top of the third mirror; in order to realize wide field of view of 10 degrees, the secondary mirror is a convex spherical mirror, the main mirror and the third mirror are concave quadric surface mirrors; and the distance from the secondary mirror to the third mirror is more than half length of the image focus of the system. The system has a coaxial structure, can acquire rich ground resource information amount, and has small difficulty in processing and debugging.

The invention discloses a triple reflection type optical system with a large view field, ultra low distortion and multiple spectrums and relates to the technical field of space optics. The system comprises a main reflecting mirror, a secondary reflecting mirror, an aperture diaphragm, a third aspherical reflecting mirror and a detector phase surface, wherein the optical axis of the main reflecting mirror, the optical axis of the second reflecting mirror, the optical axis of the third aspherical reflecting mirror and the optical axis of the detector are in parallel; the main reflecting mirror, the secondary reflecting mirror and the third aspherical reflecting mirror form a triangle; the main reflecting mirror and the third aspherical reflecting mirror are symmetrically arranged along the optical axis of the secondary reflecting mirror; the detector phase surface is arranged in right front of the third aspherical reflecting mirror; and the position of the aperture diaphragm coincides with the position of the secondary reflecting mirror. The system has the advantages of small volume and light weight, and the three reflecting mirrors are all made of a special base material; the space among all the reflecting mirrors are reasonable in design and can suppress stray light; and the system also has the advantages of low imaging distortion and small graph deformation and meets the requirement on low distortion of a system adopting a TDI (Time Delay Integration) imaging array detector.

The invention discloses a dual-channel common-path prism dispersion broadband imaging spectrometer optical system, and relates to the technical field of space optics, aiming at solving the problems of complex structure, large volume and heavy weight of the existing broadband imaging spectrometer optical system. The dual-channel common-path prism dispersion broadband imaging spectrometer optical system comprises a first aperture diaphragm, a second aperture diaphragm, a telescope, an entrance slit, a first collimating mirror, a second collimating mirror, a dispersion prism, a first imaging mirror, a second imaging mirror and a detector image plane; light beams emitted by a same objective, passing through the first aperture diaphragm and the second aperture diaphragm, are respectively reflected onto the telescope through a first channel and a second channel, imaged on the entrance slit through the telescope, reflected onto the dispersion prism through the first collimating mirror and the second collimating mirror, dispersed by the dispersion prism, and are imaged on the detector image plane through the first imaging mirror and the second imaging mirror. The optical system disclosed by the invention is applicable to aeronautic and astronautic atmospheric remote sensing, earth observation and other fields.

A rectangular large-field distortion-eliminated off-axis three-mirror anastigmat (TMA) optical system belongs to the technical field of space optics and solves the problem that the existing off-axis TMA optical system is small in field and large in distortion. The technical scheme is that the optical system comprises incident light, a primary reflecting mirror, a secondary reflecting mirror, a third reflecting mirror, an optical axis and an image receiver. The incident light is irradiated on the primary reflecting mirror, and then is reflected to the secondary reflecting mirror through the primary reflecting mirror and reflected to the third reflecting mirror through the secondary reflecting mirror to be received by the image receiver. The secondary reflecting mirror is arranged at a position of a system aperture diaphragm, the distance between the primary reflecting mirror and the secondary reflecting mirror is equal to that between the secondary reflecting mirror and the third reflecting mirror, the secondary reflecting mirror is a secondary aspheric surface, the primary reflecting mirror is a high-order aspheric surface containing an 11-order item and a-15 order item, and the third reflecting mirror is a high-order aspheric surface containing a 9-order item and a 15-order item. The rectangular large-field distortion-eliminated off-axis TMA optical system provides reference and practical reference values for designs of a large-field high resolution-ratio imaging spectrometer and a target analogue simulation system.

The invention discloses a method and device for fabrication of a frequency degenerate multi-photon entangled source using an integrated waveguide. The method comprises the following steps that (1), two pulsed light beams with different frequencies are obtained; (2), intensity of the two pulsed light beams is amplified; (3), relative time delay of the two pulsed light beams is adjusted to synchronize the two pulsed light beams, and the polarization directions of the two pulsed light beams are adjusted to be consistent; and (4), the two pulsed light beams are introduced into a Sagnac loop, eachpulsed light beam is divided into two beams of light orbiting in different directions and generates photon pairs under the spontaneous four-wave mixing of a third-order nonlinear medium, the pulsed light beams returning from different directions are combined and elicited from the Sagnac loop, and the frequency degenerate multi-photon entangled source is obtained. The method has higher stability and expansibility, can achieve complexity which is difficult to achieve in space optics, and has a high application prospect.

The invention discloses a grinding wheel home position automation shaping and milling processing method of an off-axis aspheric reflector, and relates to the advanced manufacturing field of space optics systems. The grinding wheel home position automation shaping and milling processing method of the off-axis aspheric reflector solves the problem that an existing single point oblique axis grinding method is low in processing efficiency. The grinding wheel home position automation shaping and milling processing method of the off-axis aspheric reflector includes: establishing a computer aided design (CAD) analysis model of the off-axis aspheric reflector; calculating processing residence time and a processing path of a current grinding point on the surface of a cambered grinding wheel; calculating variable quantity of a current Z axis following coordinate of the cambered grinding wheel on the Z axis direction, which is caused by variation of the current grinding point on the surface of the cambered grinding wheel; producing a post processor file and converting the post processor file into a five axis linkage numerical control processing program; fixing a work piece at the center of a five axis linkage machine tool rotary table, and using ultrasonic vibration to assist the cambered grinding wheel in swing processing according to the five axis linkage numerical control processing program. The grinding wheel home position automation shaping and milling processing method of the off-axis aspheric reflector enables each point on the surface of the grinding wheel to participate in grinding through low speed reciprocating swings of the cambered grinding wheel, homogenizes total wearing capacity of the grinding wheel onto the whole cambered surface of the grinding wheel, achieves home position automation shaping and shape preserving functions of the cambered grinding wheel, and is low in cost and short in processing cycle.

The invention discloses an optical mixer and a method for demodulating a signal through the optical mixer. The optical mixer comprises two cubic unpolarized beam splitters (BS) and two cubic polarized beam splitters (PBS), wherein a cuboid block is formed by the two BSs and the two PBSs, the beam splitting interfaces of the two BSs are located in a first plane, the beam splitting interfaces of the two PBSs are located in a second plane, and the first plane is perpendicular to the second plane. According to the embodiment, the planar optical waveguide PLC technology is not used in the optical mixer, demodulation to the modulated signal is achieved through the two cubic unpolarized BSs and the two cubic PBSs, and the BSs and the PBSs are lower in cost, smaller in insertion loss, higher in temperature stability and based on space optics. Therefore, the cost of the optical mixer is reduced, the insertion losses of the optical mixer are reduced, and the temperature stability of the optical mixer is improved.

The invention discloses an spaceborne calibration light source LED (light emitting diode) light emitting performance testing device, relates to the field of space optics, and solves the problem that the traditional spaceborne calibration light source LED light emitting performance testing device only can detect the optical performance of a single LED. The testing device comprises an LED driving circuit, a mounting bracket, a rotary disc, a rotary disc driving system, a fixed support, a spectrograph, an optical fiber, an integration sphere and a computer control system; the LED driving circuit and the rotary disc are fixed on the mounting bracket; the rotary disc is provided with an LED testing and mounting hole; the integration sphere is arranged at the corresponding position of the LED testing and mounting hole; a light emergent hole of the integration sphere is connected with one end of the optical fiber, and the other end of the optical fiber is connected with the spectrograph; the rotary disc driving system is arranged at the bottom of the rotary disc and fixed to the fixed support; and the computer control system is respectively connected with the rotary disc driving system and the spectrograph. The testing device provided by the invention is applied to the spaceborne calibration light source LED screening and testing of a space camera.

The invention provides a radiation resistant and ultraviolet filtering film for space optic quartz glass and a manufacturing method thereof, comprising a quartz glass substrate and a multi-layer film, wherein the multi-layer film is plated on the quartz glass substrate by means of a vacuum thermal evaporation coating method and a magnetron sputtering film coating method; the multi-layer film is a L1 layer/H layer/L2 layer structure; the L1 layer is a SiO2 layer or SiO layer; the L2 layer is a SiO2 layer or SiO layer; and the H layer is a CeO2 layer or ZnO layer. The radiation resistant and ultraviolet filtering film for space optic quartz glass and the manufacturing method thereof provided by the invention have the advantage that the radiation resistant property of the material is improved by using a composite structure composed of a quartz glass substrate and a multi-layer film; according to the results of irradiation test, the radiation resistant property of the material composed of a common quartz and a film is far superior to that of doped quartz; the average value T of spectrum through rate in the working section (400 to 1000 nm) after the irradiation of an integrating dose of 5*108 Rad(Si) is not less than 90%, and the T of doping material is not less than 70%.

The invention discloses a small lightweight long-focus distortion elimination coaxial total-reflection space camera optical system, and belongs to the technical field of space optics. The small lightweight long-focus distortion elimination coaxial total-reflection space camera optical system solves the problems in the prior art. The optical system comprises a primary mirror, a secondary mirror, a folded axis mirror and a third mirror, wherein the secondary mirror is arranged on a reflection light path of the main mirror, the folded axis mirror is arranged on a reflection light path of the secondary mirror, the third mirror is arranged on a reflection light path of the folded axis mirror, a curvature folded axis mirror is arranged on a reflection light path of the third mirror, the curvature folded axis mirror is a concave spherical mirror, distortion optical aberration generated by the curvature folded axis mirror is opposite to the total distortion optical aberration generated by the secondary mirror and the third mirror in sign, and distortion optical aberration of the secondary mirror and the third mirror can be offset. The optical system can meet the requirements of small lightweight optical remote sensing satellites for multispectral imaging, high-precision stereoscopic plotting and the like.