43 results about "Optical telescope" patented technology

The invention discloses a large-view-field compound eye telescopic system suitable for daytime observation, and belongs to the technical field of optical system design. The system comprises a primary mirror, a compound eye optical unit, a refraction correction mirror group unit and a photoelectric detector unit which are sequentially arranged along an optical axis. The compound eye optical unit adopts a light splitting reflection cube-corner prism structure, and divides a focal plane of a primary lens into X paths of sub-view fields; the refraction correction lens group unit comprises n correction lens groups with built-in field diaphragms; a concentric annular light barrier group is arranged on the inner wall of the primary mirror chamber. Large-view-field observation is realized through optical splicing of a compound eye structure, strong background stray light in the daytime is remarkably inhibited by utilizing a built-in view field diaphragm and combining multiple scattering absorption of a light barrier group, and the stray light coefficient of the system is lower than 1.11 * 10 <-7 >. The technical problem that an existing optical telescope cannot carry out high-contrast large-view-field observation in the daytime is solved, and all-weather monitoring of near-earth celestial bodies is achieved.

This invention provides an optical system and method for free-space quantum key distribution. The optical telescope employs a transmission-type telescope and a simplified rear optical path terminal, effectively avoiding secondary mirror obstruction and vignetting. The optical telescope system has a smaller axial dimension and is lighter than a Cassette-type reflecting telescope of the same aperture, making it more suitable for large-scale use in short-range free-space quantum communication. It can be carried and deployed by a single person and has all-day quantum key distribution capabilities. Furthermore, the transmitting and receiving telescopes are interchangeable, meaning the system can function as both a transmitter and a receiver, extending quantum communication coverage to areas inaccessible by fiber optics and satellites, and enabling rapid deployment in various emergency and unforeseen circumstances.

A kind of telescope active optical correction system correction accuracy testing device, including laser interferometer, multidimensional adjusting table, wave aberration measurement component and plane mirror, laser interferometer is placed in the outside of optical telescope for emitting test light to the inside of optical telescope, to detect the wave aberration data of multiple fields of view;Multidimensional adjusting table is used to adjust the position, angle of optical element in optical telescope, to simulate the situation that telescope imaging quality drops;Wave aberration measurement component is set at the image plane of telescope for measuring the wave aberration after optical telescope imaging quality drops, and plane mirror is used to reflect test light.The present application relates to a kind of telescope active optical correction system correction accuracy testing method, the displacement amount and rotation angle of optical element when comparing when simulating image quality drop and when correcting judge the correction accuracy of active optical correction system, compare wave aberration before simulating image quality drop and after correction, judge whether the image quality after correction reaches the image quality before simulating image quality drop.

The invention discloses an optical telescope primary mirror assembly and an anti-backlash close-fitting method thereof. The primary mirror assembly comprises a telescope primary mirror, a primary mirror mounting seat, a central mandrel, a pressing ring and a plurality of copper sheets. The primary mirror mounting seat is coaxially connected with the central mandrel through a screw and a positioning pin; the primary mirror of the telescope is embedded in the primary mirror mounting seat, and the central spindle penetrates through the central through hole of the primary mirror to finish coarse positioning of the primary mirror in the primary mirror mounting seat. A plurality of equal-thickness copper sheets are inserted into a circular gap between the central mandrel and the central through hole of the primary mirror at equal intervals, so that accurate positioning of the primary mirror in the primary mirror mounting seat is completed while the gap is eliminated. And a ball fastener is screwed into the threaded through hole in the side wall of the central mandrel, and the head of the fastener abuts against the corresponding copper sheet to realize interference fit. According to the design method, the assembled primary mirror assembly can be completely stable, the stress in all directions is uniform, the extrusion stress can be well conducted after the gravity posture is changed, and the good surface precision of the primary mirror is maintained.

The application discloses a large dynamic range imaging device and method, relates to the technical field of remote sensing imaging, and the device is characterized in that a rotating scanning component moves to a corresponding position according to a rotating instruction, and sends received radiation into an optical telescope component, and then converges to a light splitting component; the light splitting component divides the radiation into visible light and infrared rays, and respectively sends the visible light and the infrared rays into a visible light component and an infrared component; the visible light component focuses received visible light and obtains visible light signal data through multi-channel faint light detection; the infrared component collimates, focuses and multi-channel infrared detects received infrared rays to obtain infrared radiation signal data; a controller amplifies and processes the visible light signal data and the infrared radiation signal data, and obtains a ground object target image through data fusion, then determines corresponding ground object target line-of-sight angle information based on the ground object target image, and then generates a rotating instruction and sends the rotating instruction to the rotating scanning component. The application can obtain a remote sensing image with rich and complete data information under low illumination.

There are provided: a light source to generate a laser beam; an optical modulator to superimpose a communication signal on the laser beam; an OHPA to amplify the laser beam; a collimator including a fiber connector and a collimator lens to convert the laser beam amplified into spatial light, and emit the spatial light; an optical telescope to enlarge a beam width of the spatial light and emit the spatial light to a spatial transmission path; a drive mechanism capable of adjusting a focal length of the collimator lens; and a drive controller to determine a drive amount of the drive mechanism in such a manner that a product of a free space loss calculated from a distance between the spatial optical communication transceiver and a spatial optical communication transceiver and a transmission gain determined by a beam spread angle of the spatial light is constant.

an LEO satellite includes a light projecting element that emits emission light to another LEO satellite, an optical telescope, an optical phased array, a light receiving element that receives incident light from the other LEO satellite, a distance measurement unit that measures a distance to the other LEO satellite based on at least one of the emission light and the incident light, and a control unit. The control unit captures the other LEO satellites by scanning emission light using the optical telescope and receives incident light from the other LEO satellites for the other LEO satellites on the same orbital plane, and captures the other LEO satellites by scanning emission light using the optical phased array and receives incident light from the other LEO satellites for the other LEO satellites on different orbital planes.

The utility model provides a laser telegraph telescope system with image acquisition and display functions, which comprises a laser telegraph assembly, an image acquisition and processing assembly, an industrial lens, an industrial lens focusing mechanism, an image acquisition unit and an image processing and output unit, and the image acquisition and processing assembly is arranged at the rear end of an eyepiece of the laser telegraph assembly. The industrial lens is coaxially arranged at the rear end of the laser electric eyepiece, the industrial lens focusing mechanism is arranged outside the industrial lens and used for adjusting the focal length of the industrial lens, the image acquisition unit is connected to the rear end of the industrial lens and used for acquiring image data output by the industrial lens, and the image processing and output unit is arranged at the rear end of the image acquisition unit and used for outputting the image data. The image processing unit is electrically connected with the image acquisition unit and is used for processing and outputting image data; and the image display unit is electrically connected with the output end of the image processing unit and is used for displaying the image data. According to the utility model, telescope image acquisition and processing are added on the basis of the original laser telegraph, and are displayed through the display, so that operators can observe conveniently.

The application discloses a three-dimensional geomagnetic space information measuring total station, which comprises physical sensors, magnetic flux gate sensors, optical telescopes and a host computer, wherein the physical sensors and the magnetic flux gate sensors are connected with the host computer, the physical sensors comprise magnetic sensor probes, horizontal angle sensors, vertical angle sensors and distance measuring sensors; the host computer is composed of a WINCE system, the magnetic flux gate sensors convert analog signals into digital signals through AD converters, the physical sensors, the magnetic flux gate sensors and a single-chip microcomputer in the host computer communicate through a 6-pin RS-232 interface, and the application can utilize multidisciplinary comprehensive magnetic force sensors and electronic angle measuring total stations to integrate, establish a data calculation relationship model of three-dimensional geomagnetic space magnetic declination, magnetic inclination, magnetic north azimuth and magnetic north direction angle and develop a geomagnetic space information one-station automatic measuring instrument, i.e., a total station, on the basis of a geomagnetic space information measuring principle, considering a geodetic survey geometric element measuring method and an environment.

The present application relates to the technical field of laser communication, in particular to a kind of interstellar laser communication failure guide adjustment remote control system, including optical telescope module, laser transmitter module, control module and fault diagnosis repair module, optical telescope module is connected with control module, laser transmitter module is connected with control module, fault diagnosis repair module is connected with control module;After interstellar communication handshaking fails, laser transmitter module emits N laser beams, optical telescope module receives laser beam and uploads to control module, fault diagnosis repair module automatically detects and diagnoses fault reason, and generates corresponding measures, measure instruction is uploaded to control module, control module is recontrolled and adjusted according to the received instruction to controlled object, the stability and reliability of interstellar laser communication are maximized to guarantee.

1. The name of the design product: the base of space optical telescope. 2. The use of the design product: the base of space optical telescope. 3. The design points of the design product: in shape. 4. The picture or photo that can best show the design points: perspective view.

The present application relates to the field of optical telescope technology, and proposes a kind of spectroscopic popular science telescope, including frame body, field lens ocular lens, cemented ocular lens, display screen and ridge prism are connected from top to bottom on frame body respectively;Half house cemented prism is fixedly connected between one side of ridge prism and frame body, and the inside of frame body is connected with light splitting focusing module, and light splitting focusing module includes relay lens large lens, relay lens middle lens and relay lens small lens;Light splitting focusing module is composed of three relay lenses of relay lens large lens, relay lens middle lens and relay lens small lens, and light splitting focusing module is arranged on original observation light path, and original observation light path is divided into the following two ways: one way is observation light path, directly conducted to field lens ocular lens for user naked eye observation;Another way is imaging acquisition light path.Through the above technical scheme, the problem that the existing telescope exists prism observation and imaging light path coincides, sometimes there will be shielding interference, which will affect the user's judgment.

A weatherized optical observing system includes components that include an optical telescope, a gimbal, and an integrated controller. The optical telescope includes an imaging device configured to capture telescope images. The gimbal is configured to move the optical telescope in at least two axes. The integrated controller configured to wirelessly transmit the telescope images, wirelessly receive instructions, identify local weather data, actuate the gimbal based on the instructions, and control the optical telescope based on at least one of the instructions or the local weather data.

The present invention relates to an optical telescope device (1), comprising: - a mirror (2) having a first concave reflective outer face (2a) and a first flat inner face (2b) opposite the first outer face (2a), the first outer face (2a) being polished; - a reinforcement structure (3) fixed to the mirror (2), the reinforcement structure (3) having a second flat inner face (3b) and a second free outer face (3a), the second inner face (3b) being in contact with the first inner face (2b) along a fixing plane; the second free outer face (3a) being concave, the mirror (2) and the reinforcement structure (3) being symmetrical with respect to the fixing plane. Figure for the abstract: Fig. 1

The invention discloses a method for improving daytime detection capability of a foundation photoelectric detection telescope. According to the method, by measuring a signal of a detection target, calculating a relation between a multi-frame accumulated signal-to-noise ratio and a single-frame accumulated signal-to-noise ratio of the detection target, and comprehensively considering measurement errors caused by atmospheric disturbance and servo tracking, a data model about detectability improvement quantity and a ratio of the multi-frame signal-to-noise ratio to the single-frame signal-to-noise ratio is established; therefore, the relation between the detectability improvement amount and the accumulated frame number is obtained. The invention provides a method for improving the daytime detection capability of a ground-based optical telescope based on multi-frame accumulation. The detection capability of the ground-based optical telescope on a dark space target in the daytime can be effectively improved.

A binocular electro-optical telescope, relating to the technical field of optical devices, comprising a first lens barrel and a second lens barrel connected to each other, and a magnification adjustment assembly and a focusing structure located between the first lens barrel and the second lens barrel. An operating part of the magnification adjustment assembly and an operating part of the focusing structure are both at least partially exposed on a same side of the telescope for operation. The binocular electro-optical telescope provided in the present application improves the convenience of focusing and magnification adjustment operations by users, and enables a more rational overall layout of components.

A dual-light telescope capable of adjusting the screen display angle comprises a telescope body, an eyepiece is installed at the front end of the telescope body, a screen display support is connected to the tail of the telescope body, a screen display groove is formed in the surface of the screen display support, a screen display is arranged in the screen display groove, the upper end of the screen display is rotationally connected with the screen display support, an inner groove is machined in the surface of the screen display groove, and a supporting rod is rotationally arranged in the inner groove. A plurality of supporting grooves are formed in the back face of the screen display, and the supporting rods are inserted into the supporting grooves to adjust the angle of the screen display. Compared with the prior art, according to the dual-light telescope capable of adjusting the screen display angle, the screen display angle can be adjusted by inserting the supporting rod into the supporting groove, reflection of an external light source is reduced, and imaging is clearer.

This invention provides a design method for a flexible hinge supporting a large-aperture optical telescope. The method involves parametric processing of the flexible hinge structure in a CAD model, establishing a finite element model of the primary mirror and supporting structure assembled with the initial flexible hinge structure; setting multiple working conditions to obtain nodal displacement data; and acquiring the rigid body displacement and surface RMS values ​​of the primary mirror through numerical fitting. An automated workflow is established to iteratively generate a mathematical substitution model; based on the mathematical substitution model, target values ​​are iteratively calculated, and the output target values ​​are evaluated to select the optimal structural parameter target values ​​as the dimensional parameters of the flexible hinge structure. The design method proposed in this invention has the advantages of being faster and more accurate, significantly saving computation time and labor costs. Compared with traditional optimization methods that focus on deformation and stress, it has a more direct and mechanical advantage, more accurately and comprehensively reflecting the working state of the structure, thus obtaining better optimization results.

The invention relates to a super-elastic and super-tough mechanical shutter blade compounded by carbon fibers and a polyimide film, and belongs to the technical field of mechanical shutters of large optical telescopes. A polyimide film material is pasted on single-layer carbon fiber cloth, or a polyimide film is clamped between two layers of carbon fiber cloth, so that a sandwich structure is formed. And the fiber direction of the carbon fiber cloth and the edge straight line of the blade are staggered at 45 degrees. A resin matrix, carbon fiber cloth and a polyimide film are consolidated in a high-temperature hot pressing forming mode, and the shutter blade front end with super-strong elasticity is manufactured. Due to the addition of the polyimide film material, the carbon fiber cloth at the front end of the carbon fiber mechanical blade has the characteristic of tear resistance and is more tough, and the front end of the blade with a large-size plane of 620 mm * 50 mm is still not broken or damaged under the super-strong elasticity of being bent by nearly 90 degrees.

This application relates to the field of optical system design technology, and discloses a design method, device, and electronic device for an optical telescope based on a stitched primary mirror. The method includes: determining the current aspherical surface parameters of aspherical stitched sub-mirrors in different layers of the optical system according to the optical system constraints of the stitched primary mirror; iteratively optimizing the current aspherical surface parameters according to a pre-constructed comprehensive evaluation function; obtaining optimized aspherical surface parameters of the aspherical stitched sub-mirrors in different layers that satisfy the design requirements of the comprehensive evaluation function within the target field of view; and the best-fit sphere corresponding to the optimized aspherical surface parameters; and outputting the optimization results. This invention can reduce the manufacturing difficulty and cost of the stitched sub-mirrors, avoid the introduction of complex aberration correction optical elements, and ensure the versatility, multifunctionality, and scalability of the overall system.

The application discloses a moving target calculation tracking imaging method based on high-frame-frequency image shift superposition, which comprises high-frame-frequency continuous image acquisition and pretreatment; estimation of the visual position of a moving target on an image plane to obtain a measurement coordinate prediction value of the moving target in multiple images; registration of the translation of the image sequence of the moving target on a sub-pixel scale based on the measurement coordinate prediction value to obtain an image after superposition enhancement; star image detection processing on the image after superposition enhancement; track correlation processing based on the star image detection result, and screening of a moving target sequence based on a preset speed range; and output of the information of the moving target. The method can effectively solve the problem that a moving target in a field of view cannot be tracked and imaged in a non-tracking imaging mode of an optical telescope, effectively accumulates a moving target signal and improves a signal-to-noise ratio in software algorithm, and finally realizes effective detection of a dark and weak moving target and high-precision positioning and light measurement of the moving target.

1. Name of the product in this design: LED light strip for a space optical telescope. 2. Purpose of this design: The entire product is used to optically magnify the light reflected from objects placed on a table or the light emitted from an external monitor, forming a distant virtual image, which is then displayed through a window; a portion of this product is used as an LED light strip in a space optical telescope. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model. 5. Other matters requiring explanation: This design patent seeks to protect the partial design of the product; the part covered by the light pink mask is the part not for which protection is sought; the enlarged view of part A is a partial enlarged view of part A in the bottom view; the enlarged view of part B is a partial enlarged view of part B in the front view.

This invention relates to the field of optical telescope technology and discloses a Cassegrain telescope, including a primary mirror assembly, a secondary mirror assembly, a connecting assembly, a telescope top plate, and a telescope base plate; the primary mirror assembly is located on the side of the telescope base plate, and the secondary mirror assembly is located on the side of the telescope top plate. Both the primary and secondary mirrors are made of microcrystalline glass, resulting in minimal surface deformation under environmental changes and maintaining stable optical performance. The carbon fiber support rod of the connecting assembly is made of carbon fiber, which has a low coefficient of thermal expansion and high length stability, thus preventing deformation of the primary and secondary mirror surfaces and relative position shifts caused by environmental temperature changes. The leveling triangle plate is fixed to the telescope base plate, and the secondary mirror fixing plate is fixed to the telescope top plate using locking screws. The clamps of the carbon fiber rod assembly, once locked, limit the relative distance between the primary and secondary mirrors. This multi-stage fixing structure ensures the overall stability of the telescope structure and effectively prevents position shifts during use.

The present invention provides a method for detecting the seeing of a large-aperture, large-field active optical telescope camera, comprising the following steps: S1. Performing short-time exposure on a specific sky area to obtain a defocused star image in the specific sky area. S2. Constructing a low-order phase-difference defocused star image template based on the defocused star image in the specific sky area. S3. Correlating the low-order phase-difference defocused star image template with the defocused star image obtained in step S1, and regarding the position corresponding to the highest correlation as the center of the defocused star image to achieve positioning selection of the star image. S4. Ignoring the influence of low-order aberrations, utilizing the basic principle of curvature sensing to extract the aberration of the star image, and decomposing it onto a multi-order Zernike polynomial basis, synthesizing the obtained low-order information with the high-order information, and comparing it with the actual defocused star image to calculate the difference result. The present invention clarifies the mechanism of the influence of camera seeing on the final sky survey detection, as well as the boundary of its accuracy influence.

The invention discloses a target-independent automatic image stacking method and device for an optical sparse aperture imaging system, and belongs to the technical field of optical telescopes, and the method comprises the steps: collecting an initial degraded image; applying the same inclination amount to the inclination controller of each sub-aperture, collecting N modulated images, and sequentially subtracting the initial degraded images from the N modulated images in pairs to obtain N difference images; n low-frequency difference images are obtained, one low-frequency difference image is used as a reference image, the remaining low-frequency difference images are subjected to cross-correlation operation in phase parts, local k-time up-sampling calculation is carried out in a neighborhood range of a cross-correlation power spectrum peak position, and refined cross-correlation power spectrum peak offset is obtained; and outputting the relative sub-pixel level offset of the residual low-frequency difference image, and controlling the relative sub-pixel level offset through a tilt controller of a corresponding sub-aperture to realize automatic image stacking of the N-aperture sparse aperture imaging primary mirror in any scene. According to the invention, the complexity of the optical path of the optical synthetic aperture imaging tilt error correction module is reduced.

The present invention relates to the field of optoelectronic imaging, in particular to the field of ultra-high spatial resolution imaging. The present invention discloses a chessboard constellation optical pupil interferometry high-resolution computational imaging method. The method adopts a chessboard constellation high-density data acquisition system to achieve high-density sampling of the modulus G of the complex coherence coefficient μ(u, v) of the object light, and then combines the phase recovery (also known as phase recovery) algorithm and the image reconstruction algorithm to obtain a clear image of the object light. For ultra-large aperture optical telescopes that far exceed the rocket envelope, low, medium and high frequency cameras can be placed on different rocket satellite platforms, launched into orbit in batches, and reorganized in orbit to obtain an equivalent large optical aperture imaging optical system. Its equivalent aperture breaks through the rocket envelope limit and can be expanded to 10 meters, or even larger.

The invention relates to a satellite orbit transaction detection method based on optical observation, and belongs to the field of space situation awareness. The method comprises the steps of observing image fixed star and space target centroid extraction; recognizing a fixed star map of the observation image; resolving the attitude of the optical telescope; detecting an observation image space target; screening candidate space target data in a satellite ephemeris database; projecting a candidate space target image; and satellite orbit abnormal movement detection. According to the invention, an integrated process from image observation to space target trajectory transaction detection is completed, so that the system becomes a space target transaction detection system applying optical observation. On the premise that the ground-based optical telescope has no azimuth and pitching information, the attitude of the telescope can be solved by utilizing star map recognition. The space target transaction detection method can be suitable for various optical observations, can be used after being implanted into optical equipment, is simple and convenient, low in cost and high in universality, can be automatically completed in a programmed form, and is relatively high in automation degree.

The application relates to a shipborne optical telescope image despin angular velocity calculation method, which comprises the following steps: 1. based on the ship body pitch angle, the ship body azimuth angle, the ship body roll angle, the camera mounting platform pitch rotation angle and the camera mounting azimuth rotation angle output by a shipborne inertial navigation device, an attitude matrix of a camera coordinate system relative to a geographic coordinate system is established; 2. the attitude matrix of the camera coordinate system relative to the geographic coordinate system established in step 1 is calculated to obtain an attitude matrix of a lens coordinate system at a current time of the camera relative to a lens coordinate system at a previous sampling time, and the obtained attitude matrix of the lens coordinate system relative to the lens coordinate system at the previous sampling time is used to calculate the rotation angular velocity of the image; and 3. the rotation angular velocity of the image obtained in step 2 is subjected to noise reduction processing to remove the angle measurement noise of the inertial navigation device and the angle measurement noise of the rotating mechanism. The application ensures that the reference coordinate systems of each frame of image in the continuously shot images are consistent.