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Angle measurement device comprises a lens, a matrix radiation receiver, a calculation unit and a channel of geometric reference, comprising the following components optically coupled with the lens of the lighting unit, having three sources of light arranged at the angle of 120° to each other, a collimator unit including three input and three output point diaphragms, and a mirror-prism unit, forming a monoblock with diaphragms applied on it and rigidly connected to the reference plane of the angle measurement device. The mirror-prism monoblock is made of six side mirror faces and parallel refracting bases that limit them, the larger hexagonal of which with applied outlet point diaphragms faces the lens, besides, its adjacent ribs are arranged at the angle 120° to each other. The monoblock is made with three additional refracting faces, placed between large bases and appropriate side mirror face, making a sharp angle with the large base and placed in front of the output point diaphragm, each additional face is equipped with an input point diaphragm, and angles between the large base and three additional refracting faces and three side mirror faces, arranged in front of three input point diaphragms, are equal to 90°. |
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Active ultraviolet solar sensor for orientation systems of small-size spacecraft Active ultraviolet solar sensor for orientation systems of small-size spacecraft includes a natural diamond-based photodetector at the entrance window of which solar energy falls and a low-noise preamplifier. The natural diamond-based photodetector functionally combines both an ultraviolet optical filter and an ultraviolet photodetector. Selective separation of the ultraviolet region from the solar spectrum and conversion thereof to an electrical signal is carried out in the natural diamond-based photodetector and signal amplification is carried out in the low-noise preamplifier. |
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Sensor includes a wide-field input optical element, a coding mask, a light filter, a protective shield and a matrix photodetector. The input optical element is in form of a composite monoblock and has the shape of a quadrangular prism. The monoblock comprises a central prism in form of a quadrangular truncated regular pyramid, lateral faces of which have an absorbent coating and four identical lateral prisms in form of quadrangular irregular pyramids. One of the faces of each lateral prism has a mirror coating and that face is connected to the corresponding absorbent face of the central prism. The composite monoblock rests on the surface of the coding mask in which there is a central identification marker which is aligned with the axis of symmetry of the central prism and four identification markers which are symmetrically arranged around the central marker. |
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Method is realised by a hybridisation device comprising a bank of Kalman filters, each working out a hybrid navigation solution from inertial measurements calculated by a virtual platform and raw measurements of signals emitted by a constellation of satellites supplied by a satellite-positioning system (GNSS), and comprises steps of: determination for each satellite of at least one probability ratio between a hypothetical breakdown of given type of the satellite and a hypothetical absence of breakdown of the satellite, declaration of a breakdown of given type on a satellite based on the probability ratio associated with this breakdown and of a threshold value, estimation of the impact of the breakdown declared on each hybrid navigation solution, and correction of hybrid navigation solutions according to the estimation of the impact of the breakdown declared. |
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Result is achieved due to arrangement of elementary photosensitive elements in the space, forming a multi-element photodetector and extraction of information on two angular coordinates of the glowing reference points from their signal values and serial numbers, the value of angular pitch and the angle of inclination of axes of directivity patterns. At the same time the device of the multiple-element photodetector comprises elementary photodetectors arranged with the specified angular pitch relative to a certain axis. The number of elementary photodetectors is at least seven, axes of directivity patterns of elementary photodetectors are arranged at a certain angle different to the straight one and zero one to the axis, relative to which the elementary photodetectors are arranged. |
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Telescope has in a first channel a main mirror, a secondary mirror, a lens corrector, a recording device mounted in the focal plane of the telescope, and in a second channel a flat slanted elliptical mirror for observing stars, which is mounted in the plane of intersection of the first and second channels. The central part of the surface of the main mirror which faces the secondary mirror and on which light from the Earth falls is coated with a green reflecting light filter. In the central area of the cross-section of the second channel there is a circular diaphragm which prevents that part of light from stars which does not fall on the flat slanted elliptical mirror from falling into the first channel. The part of the surface of the recording device facing the lens corrector is coated with a red transmitting light filter. |
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During movement there determined are parameters of a model of measurement errors of accelerometers of a driven inertial navigation system (INS) as per measurements of a reference INS based on measurement of apparent accelerations of a carrier object moving in inertial space and a separable object related to it. Those measurements are made by means of accelerometers of the reference inertial navigation system in a basic inertial system of coordinates (BISC) and by means of accelerometers of the driven inertial navigation system in an instrument inertial system of coordinates (IISC). |
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For that purpose, in the course of determination of parameters of a measurement error model of accelerometers of inertial navigation systems (INS) as per measurements of satellite navigation that includes measurements of a vector of apparent acceleration of an object moving in inertial space, as per measurements of INS accelerometers and corrections to a speed vector at different time moments, which are obtained as per measurements of navigation space vehicles of GLONASS and GPS systems, there determined are errors of moduli of vectors of apparent speed, which are accumulated at several movement intervals of controlled moving objects differing by mutually noncollinear directions of vectors of apparent speed. |
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Onboard equipment for inter-satellite measurements Onboard equipment for inter-satellite measurements consists of a radio transmitter, a circulator, a transceiving antenna, an input receiver amplifier, a radio receiver, a modular master controller, a radio signal former, a logic and switching unit, which also enables self-contained operation of the satellite constellation, increases accuracy of ephemeral and time-and-frequency support of system, real-time delivery of information from all navigation spacecraft, transmission of command-program information and reception of telemetric information, real-time monitoring of integrity of the space system, transmission of data navigation spacecraft of the unified space system, reduction of load on computer equipment of the ground-based control system. |
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Method for photonic location of aerial object Method for photonic location of an aerial object is characterised by using a ultraviolet (UV) detector to detect photon radiation of the aerial object, processing the received signal in the UV detector and then in a computer, and determining spatial coordinates of said aerial object at the corresponding moment of a universal time system (UTS), wherein tying to a unified coordinate system and the UTS is carried out with a local control-correction station (LCCS) which, besides photon radiation of the aerial object, also receives from navigation satellites of active global navigation systems periodic radio messages containing codes of current values of the UTS at the moment of emission of the radio messages by the corresponding navigation satellites, as well as data for accurate calculation of dislocation coordinates of the LCCS and the UV detector included therein, which are processed by a group of satellite receivers and the LCCS computer, characterised by that detection of photon radiation of the aerial object, sources of which are regions of ionisation of gases near the nose and the nozzle of the moving aerial object, is carried out using a first and a second group of UV detectors, arranged respectively on first and second masts vertically synchronous and in-phase mechanically rotating about their axes in the azimuthal plane, spaced from each other by a base distance, wherein using each group of UV detectors, detection of photon radiation of the aerial object at each given moment in time is carried out from all directions of the 90-degree elevation plane through uniform distribution of optical axes of the UV detectors of each group by said 90 degrees with a narrow beam pattern of the UV detectors in the azimuthal plane, and through rotation of the mast at each 360-degree view - successively for all directions of the 180-degree elevation angle, radiation received by each group of UV detectors is converted in each UV detector to a digital code, and then recorded in computer memory separately for each mast in an orderly manner for each detection radiation while recording the obtained azimuthal angle and elevation angle, wherein the azimuthal angle at each mast is calculated at the middle of the sector of the continuously received radiation, formed as result of turning the mast, and the elevation angle at each mast is calculated at the middle of the sector of radiation continuously received by a corresponding set of adjacent UV detectors, the obtained azimuth and elevation angles for each radiation for each mast are simultaneously recorded in computer memory with corresponding UTS readings and range and altitude values calculated from the obtained angles, after which for the current view, the separately obtained readings for each mast for common angle features thereof, range and altitude are identified at specific coordinates of specific detected aerial objects, which are corrected at the next views based on features of the corrected angles, range and altitude of the aerial object, as well as an additional common feature of velocity, manoeuvre and direction of the aerial object. |
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According to the proposed method, five threshold signals, signals of norms of gyroquaternions, signals of norms of bases, and a signal of norm of astroquaternion; speeds of change of output signals of each gyroscope are determined, and when they exceed the first threshold signal, the second failure signal is shaped; signals of differences of signals of gyroquaternions of bases are determined, and when they exceed the second threshold signal, the third failure signal is shaped. After at least one failure signal is received, difference signal is determined between signal of norm of gyroquaternion of working basis and signal of norm of astroquaternion, and when it exceeds the third threshold signal, L fourth failure signal is shaped; occasionally, at the time interval equal to five minutes there determined are difference signals of signals of gyroquaternions of signals and bases and signal of astroquaternion, and when it exceeds the fourth threshold signal, the fifth failure signal is shaped; occasionally, within four seconds, after the third failure signal is received, a control loop of a space vehicle is opened, a test signal is supplied to the actuating device input, output signals of gyroscopes are measured, and when they exceed the fifth threshold signal, the sixth failure signal is shaped. In addition, a device for the method's implementation includes three OR circuits, fourteen non-linear units, six adders, four shapers of signal of norm of gyroquaternion and a shaper of signal of norm of astroquaternion; output of astrodetector is connected through the shaper of astroquaternion norm signal to the first inputs of the fifth, the sixth, the seventh and the eighth adders; output of the shape of norm signal of astroquaternion is connected through the ninth adder to input of the fifth non-linear unit; output of the first shaper of basis is connected through in-series connected first shaper of norm signal of gyroquaternion, the fifth adder and the sixth non-linear unit to the first input of the first OR circuit, output of the second shaper of basis is connected through in-series connected second shaper of norm signal of gyroquaternion, the sixth adder and the seventh non-linear unit to the second input of the first OR circuit; output of the third shaper of basis is connected to the third input of the first OR circuit through in-series connected third shaper of norm signal of gyroquaternion, the seventh adder and the eighth non-linear unit, output of the fourth shaper of basis is connected to the fourth input of the first OR circuit through in-series connected fourth shaper of norm signal of gyroquaternion - the eighth adder and the ninth non-linear unit, output of the third shaper of norm signal of gyroquaternion is connected through the tenth adder to input of the tenth non-linear unit, output of the fourth shaper of norm signal of gyroquaternion is connected to the second input of the tenth adder, output of the first gyroscope is connected through the eleventh non-linear unit to the first input of the second OR circuit and through in-series connected first differentiating device and the twelfth non-linear unit to the first input of the third OR circuit, output of the second gyroscope is connected through the thirteenth non-linear unit to the second input of the second OR circuit, and through in-series connected second differentiating device and the fourteenth non-linear unit to the second input of the third OR circuit, output of the third gyroscope is connected through the fifteenth non-linear unit to the third input of the second OR circuit, and through in-series connected third differentiating link and the sixteenth non-linear unit to the third input of the third OR circuit, output of the fourth gyroscope is connected through the seventeenth non-linear unit to the fourth input of the second OR circuit, and through in-series connected fourth differentiating device and the eighteenth non-linear unit to the fourth input; the third OR circuit, outputs of the third OR circuit, the tenth non-linear unit, the fifth non-linear unit, the first OR circuit, the second OR circuit are the second, the fourth, the fifth and the sixth outputs of the device respectively. |
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Device to select astronomic objects of surveillance from orbital spacecraft Device to select astronomic objects of surveillance from an orbital spacecraft (SC), includes a globe with an applied sky map, two rings covering the globe, centres of which are matched with the centre of the globe, an element with a circular contour, the projection of which to the surface of the globe forms a circumference that limits the segment of the globe surface with an angle of semi-opening counted from the direction from the centre of the globe to the centre of the specified segment of the globe surface, equal to the angle of semi-opening of a disc visible from the SC in the planet located in the centre of the near-circular orbit of the SC, and an arc element connected with the specified element with the circular contour. The first ring is fixed above points of globe poles with the possibility to rotate a ring around the axis of globe rotation. The second ring is fixed on the first ring. The plane of the second ring makes an angle with the plane of the globe equator equal to the angle of SC orbit inclination. In addition the size of the arc element arc measured from the centre of the globe is equal to 180°-Q, where Q - angle of semi-opening of the planet disc visible from the SC orbit. The arc element with its end point is rigidly connected with the edge of the element with the circular contour. The arc element and element with the circular contour are made as detachable and equipped with a facility of their fixation on the globe in positions, in which the free end point of the arc element and the centre of the element with circular contour are at the same diameter of the globe. |
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Device for selecting astronomical objects for observation from orbital spacecraft Invention relates space engineering. Proposed device comprises celestial globe with starry sky plotted thereon, two rings covering said globe with their centres aligned with that of the globe, and circular element, its projection on globe surface making a circle confining globe surface circular segment with angle of semi-span graduated from globe centre to that of said segment and equal to angle of semi-span of disc planet located at the centre of visible from spacecraft nearly circular orbit and visible from spacecraft. First ring is secured above globe pole points to allow revolution of said first ring about globe rotation axis. Second ring is secured to first ring. Second ring plane makes with globe equator plane the angle equal to that of spacecraft orbit inclination. Besides, guide pin is added to proposed device to envelop the globe, its centre being aligned with globe centre, and fitted along ecliptic line marked on globe surface, as well as means to fix the position of circular element with circular contour relative to circular guide pin. |
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Board for selecting observation objects from orbital spacecraft Invention can be used to determine and select observation objects onboard an orbital spacecraft moving on a near-circular orbit. The board for selecting observation objects from an orbital spacecraft has a flexible tape with a map of the earth's surface, a semitransparent plate placed over said tape having an image of half the orbit pass of the spacecraft between ascending and descending nodes, and a device for moving the tape along the plate with two rollers spaced apart and mounted parallel to each other. The tape is stretched onto the rollers with possibility of movement thereof along the equator line. The map of the earth's surface is divided into two parts on the equator line. Part of the map with the image of the northern hemisphere and part of the map with the image of the southern hemisphere are arranged in series on the tape. The equator line of the part of the map with the image of the northern hemisphere is a continuation of the equator line of the part of the map with the image of the southern hemisphere. The device for moving the tape along the plate has processor rollers placed in parallel between the first and second rollers. The tape is stretched onto said rollers and the newly introduced process rollers. The size of the tape and the plates along the direction perpendicular to the equator is equal to the length of the latitude line of the map showing one of the hemispheres. |
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Invention can be used for ephemeral provisioning of a process for controlling global navigation satellite system (GNSS) spacecraft. A low-orbiting spacecraft fitted with apparatus for synchronising the on-board time scale with the system time scale, apparatus for determining orbit parameters from ground-based radio beacons and consumer navigation equipment is taken to an orbit. During orbit flight thereof, the on-board time scale is synchronised with the system time scale of the GNSS; orbit parameters are determined from radio beacon signals; a GNSS spacecraft navigation message signal is received; Doppler frequency shift of the message signal is measured. Orbit parameters of the low-orbiting spacecraft and the measured values of the Doppler frequency shift of the message signal on-board the low-orbiting spacecraft are used to determine the orbit of navigation GNSS spacecraft and then transmitted for reception thereof at the GNSS spacecraft. |
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Method of monitoring continuity of navigation field of global navigation satellite system Invention can be used for rapid monitoring of continuity of the navigation field of the global navigation satellite system (GNSS). Continuity if monitored on a low-orbiting spacecraft fitted with consumer navigation apparatus. During orbital flight, navigation messages of visible GNSS spacecraft are continuously received; navigational sighting is carried out; some of the received navigation messages are used and several sets of consumer coordinates are obtained. By processing redundant navigation information, the quality of navigation signals of all visible GNSS spacecraft are analysed. Upon detection of malfunction of a certain GNSS spacecraft, a fault feature is rapidly generated and transmitted, which is received in on-board control systems of the GNSS spacecraft and the fault feature is entered into the system log. |
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Device to select objects of surveillance from orbital spacecraft Device comprises a globe with a planet surface map applied on it, a spiral element that models an orbit of a spacecraft (SC), a facility to lock the spiral element on the axis of globe rotation. The spiral element is arranged in the form of an orbit turn with a positive incline of the SC. The start of the orbit turn shall be a point of the orbit located beyond the quarter of the SC circulation period to the ascending unit of the orbit. The end of the orbit turn shall be a point of the orbit that is distant by the quarter of the SC circulation period after the next ascending unit of the orbit. The facility for fixation of the spiral element on the axis of globe rotation is arranged in the form of two connection elements, the angular size of every of which, measured from the centre of the globe, is equal to 90°-i, where i - orbit inclination. |
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Angle measurement device comprises a lens hood, a channel of a non-detuned geometric reference in the form of a lighting unit, a unit of a beam divider, a flat mirror installed on a basic plane and a non-detuned mirror-prism unit, a lens, a photodetector and a computing unit. The beam divider unit - an optical element glued from a lens and mirror-lens system, in the area of gluing producing an inclined beam-dividing face, in which: the first input surface is arranged in the lens system and is arranged as flat with a dot diaphragm applied on it; the second output surface is arranged in the mirror-lens system is arranged as flat with an adhered plano-convex lens with a mirror spherical surface, at the same time the second surface is input for radiation reflected with the mirror spherical surface; the third output surface is arranged in the mirror-lens system, is arranged in the form of a concave spherical surface, the front focus point of which is matched with the image of the dot diaphragm from the mirror spherical surface, at the same time the third surface is also an input surface for radiation reflected with a flat mirror; the fourth output surface in the lens system is a convex spherical surface. For radiation reflected with a flat mirror, the third and fourth surfaces operate as a telescopic system with angular magnitude of 0.5x. |
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Board for selecting observation objects from orbital spacecraft Board for selecting a ground surveillance object from an orbital spacecraft refers to space engineering. The board for selecting ground surveillance objects from an orbital spacecraft has a flexible belt with a map of the surface of the plane, a semitransparent plate placed on top and a device for enabling movement of the belt with the map along the semitransparent plate from two shafts spaced apart and mounted parallel each other. The semitransparent plate consists of two parts. One edge of the first part of the semitransparent plate is curvilinear and has the shape of the curved line of the orbit of the spacecraft between ascending and descending nodes and the other edge is directed along the equator line of the map. One edge of the second part of the semitransparent plate is curvilinear and has the shape of the curved line of the orbit of the spacecraft between ascending and descending nodes and the other edge is directed along the latitude line of the map. Both parts of the semitransparent plate are mounted with superposition of the outermost points of the curvilinear edge of one part of the semitransparent plate with the outermost points of the curvilinear edge of the other part of the semitransparent plate and with possibility of each part of the semitransparent plate turning about an axis directed along the equator line of the map. |
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Device comprises a lens, a matrix photodetector device (PDD), a calculation unit and a channel of a geometric reference in the form of a lighting unit, a collimator unit and a mirror-prism unit that introduces radiation from the lighting unit into the lens. The lighting unit is arranged in the form of three sources of light installed in front of input diaphragms and arranged at the angle of 120° to each other. The collimator unit is arranged in the form of three input and three output point diaphragms arranged on the rear face of the mirror-prism unit, which faces the lens, outside its inlet pupil, and is rigidly connected to the support surface of the device. The mirror-prism unit is a single monoblock in the form of parallel smaller front and larger rear hexagonal faces, adjacent ribs of which are arranged at the angle of 120° to each other and form six side mirror faces. The front face is arranged as capable of reflecting rays developed by a lighting unit and input holes of the collimator unit. The lens on the sensitive site of the PDD generates dot element images of the geometric reference channel, and additionally dot element images received from beams reflected by the front face of the mirror-prism unit. |
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Measuring device and calculation and indication unit are installed on the weapon. Measurement of the measuring device data, calculation of current values of azimuth angle and elevation angle of weapon in the calculation and indication unit, indication of values of azimuth angle and elevation angle and turning of weapon to the required values of guidance angles as to azimuth and elevation is performed. Measuring device is represented with two-antenna satellite navigation system installed on the weapon parallel to weapon axis of sight with guidance of antennae to upper hemisphere. Measurement of coordinates of antenna location is performed with frequency of not less than 1 Hz. Calculation in calculation and indication unit is carried out as per measured antenna location coordinates. |
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Board for selecting observation objects from orbital spacecraft Board for selecting observation objects from orbital spacecraft includes a plate with a map of the earth's surface, a semitransparent plate placed on top of the map of the planet, and means of facilitating displacement of the semitransparent plate along the equatorial line on the map. One edge of the semitransparent plate is curvilinear and has the shape of the curved line of the path of the orbit pass of the spacecraft. The semitransparent plate is placed with superposition of points of said curvilinear edge of the plate, which simulate node points, with the equatorial line on the map of the planet and with location of the edge of the plate, opposite said curvilinear edge of the plate, over one of said hemispheres of the map of the planet. There is a means of facilitating displacement of the semitransparent plate to a position where the edge of the plate, opposite said curvilinear edge of the plate, lies over the other of the hemispheres of the map of the planet with superposition of points of said curvilinear edge of the plate, which simulate node points, with the equatorial line on the map of the planet. The technical result is achieved through the proposed changes to the shape and size of the semitransparent plate, the proposed installation of the semitransparent plate and introduction into the board of the proposed means of facilitating displacement of the semitransparent plate to a new proposed position. |
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During flight of spacecraft in the visibility range of control and measurement stations (CMS), pseudorange to the CMS is measured on navigation radio signals of unmanned spacecraft based on the signal time delay. Doppler shift is determined and the measurements are transmitted to the computation centre of the main CMS. Based on the obtained values of predicted coordinates at fixed reference time instants with a defined interval, ephemerides are determined, which are then loaded onto the unmanned spacecraft using transmitting antennae of the CMS network, and then sent to users in form of a navigation message. Knowing matched ephemerides of the unmanned spacecraft at reference time instants, the user determines the coordinates of the unmanned spacecraft at an arbitrary moment in time by integrating equations of the model of the motion of the unmanned spacecraft. |
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Device for recording particles of space garbage and micrometeoroids Device for recording particles of space garbage and micrometeoroids consists of two or three video cameras equally located in the space through the base length. Video cameras are mounted along one line and blocks with solar batteries, objective lenses with charge-coupled device matrixes and blends. Blocks are connected to each other by means of a moving telescopic rod about which a cylinder in the form of metal-dielectric-metal film structure is located. In one of the optic blocks there installed is bottle with chemical hardener; each of optic blocks is equipped with magnetic control system in the form of one magnetometer and three electromagnets, as well as solar sensor, GPS-receiver, photodiodes located on side surfaces and onboard computer. |
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Method of navigating spacecraft based on celestial periodic radiation sources Method of navigating spacecraft based on pulsed radiation of pulsars involves determination of a set of intervals of pulses from pulsars independently on on-board and ground-based telescope on a coordinated epoch of observations on set dates, which are then used to correct values of the observed period on the ground-based telescope and deviation of the observed period from the average value on the on-board telescope; the obtained values of the observed period are used to calculate deviation of intervals of pulses from pulsars, observed on the on-board and ground-based telescopes; the difference between deviation of intervals on the on-board and ground-based telescopes is used to determine the radius vector of the true location of the spacecraft relative the calculated trajectory point and vector values of velocity and acceleration of the spacecraft, from which a decision to perform an adjustment manoeuvre to approach the true and calculated trajectory of the spacecraft is made. By associating the location of the spacecraft with the observed intervals of highly stable period radiation of pulsars, high accuracy of determining the vector of navigation state and control of results of performing adjustment manoeuvres of the spacecraft is achieved. |
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System for real-time location of mobile objects Method is realised through combined operation of the Global Navigation Satellite System (GLONASS) and a WiMAX network. GLONASS receivers are mounted on the mobile objects and control station to provide communication with satellites. Connections between base stations and mobile objects are provided through broadband wireless access using installed WiMAX telecommunication equipment. Connections between the control station and base stations are provided through SDH equipment and an optical link. Using a geoinformation system, coordinates of mobile objects obtained from satellites, calculated differential coordinate corrections and time synchronisation of GLONASS with WiMAX equipment, the information processing unit of the control station determines the exact location of a mobile object in real time using software. |
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Celestial angle measurement device FIELD: measurement equipment. SUBSTANCE: device comprises a light input unit which lets the light enter the stellar lens, and the stellar lens itself. A matrix light receiver is located in the focal plane of the lens. The receiver is connected to the computer unit. The stellar lens forms the first bitmap image from the astronomical light source on the matrix light receiver. The light input unit and the stellar lens form the second bitmap image from the said astronomic source o the matrix light receiver. EFFECT: device reliability increase while design complexity remains the same; the device still cannot decalibrate; mass and size reduction. 6 cl, 3 dwg |
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Radio signals of navigation satellites (NS) are received successively through an antenna module, a radio signal distributor and a group of receivers. Each receiver performs amplification of NS radio signals, selection of the useful component from a mixture with interference and noise, conversion of the cleaned high-frequency radio signal into an intermediate using a radio-frequency module. Further, radio signals undergo functional transformation by providing support for basic modes for generating parameters and characteristics of an integrated navigation environment during aircraft landing. |
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Method of increasing guidance accuracy of development steps for various purposes Spatial correcting effects are generated during movement of DS in a plane close to the "plane of the ballistic horizon". Generation of correcting effects is carried out on intervals for determining the initial orientation of the instrument coordinate system relative the base coordinate system. Vector matching of the coordinate for guiding the DS to the target is used. Each of the generated correcting effects is used as the initial condition for solving navigation tasks and switch the gyro-stabilised platform of the DS carrier to gyroscopic stabilisation mode. |
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Device for choosing astronomical objects under observations from orbital space vehicle Device for choosing astronomical objects under observation from orbital space vehicle (SV) includes global map with star map applied to it, two rings enveloping the global map, the centres of which are aligned with centre of global map and element the outline projection of which to global map surface forms the circle. The first ring is fixed above points of poles of global map with possibility of ring rotation around global map rotation axis. The second ring is fixed on the first ring at cross points of the first ring with equator plane of global map with possibility of rotation of the second ring till the position in which the plane of the second ring forms together with global map equator plane the angle equal to inclination angle of SV orbit. Peculiar feature of the device is that the element in the form of half of the ring, which is fixed on the second ring with possibility of its movement, is introduced to it. The element the outline projection of which to the global map surface forms the circle restricts the segment of global map surface with angle of the planet disc observed from SV. |
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System comprises receiving antenna of navigation signal, two digital receivers of navigation signal, two selectors of measurements, two filters of random error component, signal splitter, analyser of synchronism and computer. At that navigation signal is received from one receiving antenna by two navigation receivers via navigation signal splitter. Then random component of measurements error is identified, and synchronism of random measurements error component is analysed, which is excluded from subsequent processing, if phases of measurement signal error are in-phase. If phases of measurement signal error are not in-phase, then measurement signal is averaged, and pseudorange is measured to spacecraft of satellite navigation system. |
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Complex of technical facilities to detect and measure spills of oil or oil products Substance of invention consists in using air carrier as platform in proposed complex of technical facilities of detection and measurement of oil or oil products spills, besides, radiometric microwave sensor used in complex comprises double-frequency double-polarisation microwave receiving device, composition of which includes scanning combined double-frequency double-polarisation antenna device and two radiometric receivers of according ranges, and controller, and additional passive sensor consists of structure that combines radiometric receiving device of infrared range and television chamber, and controller. Besides, complex includes receiver OP8 and analyser of data, generating information message, containing generalised results of control and additional information including data of time and geographic reference and conditions of carrier navigation. |
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Method and device for measuring angular coordinates of stars Method involves projection of an image of a section of the starry sky and calibration marks through a lens onto the photosensitive area of a photodetector, measurement of linear coordinates of centres of star images and linear coordinates of centres of images of calibration marks on the photosensitive area of the photodetector and converting linear coordinates of centres of star images into angular coordinates of stars in a basic instrument coordinate system taking into account measurement results of linear coordinates of centres of images of calibration marks. When projecting calibration marks and measuring linear coordinates of centres of their images, the signal accumulation time in the photodetector is set K times shorter than working on stars. The factor for shortening the accumulation time K and reducing illumination of images of calibration marks is selected such that, the signal at the output of the photodetector from the brightest working star is less than the signal from the calibration marks. Further, amplitude selection of signals of calibration marks based on the criterion for exceeding a preset threshold level is carried out. The device has a blind, a geometrical reference channel (GRC), a lens, a charge accumulation matrix photodetector whose photosensitive area lies in the focal plane of the lens, a ADC unit, a digital processing and control unit and a control unit for the matrix photodetector. The device also has a unit for generating variable exposure time. The digital processing and control unit has amplitude signal selector, a unit for picking up useful signals from noise, a unit for identifying stars, a synchronisation unit and a computing device for determining angular coordinates of stars taking into account coordinates of calibration marks of the GRC. |
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Method for ephemeral control of spacecraft global navigation satellite system Low-orbiting spacecraft fitted with apparatus for synchronising onboard time scale with system time scale, apparatus for determining orbit parametres from terrestrial television signals and onboard apparatus for inter-satellite measurements is taken to an orbit. During orbital flight of the spacecraft, its onboard time scale is synchronised with the system time scale of the global navigation satellite system. Orbit parametres of the spacecraft are determined from television signals. A navigation message containing orbit parametres of the spacecraft is sent. Inter-satellite measurements are taken, during which motion parametres of the spacecraft navigation system relative the low-orbiting spacecraft are measured. Inter-satellite measurements and orbit parametres of the low-orbiting spacecraft in onboard control systems of the spacecraft navigation system are used to determine orbit parametres and ephemerides. |
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Vector inertial navigation system (vins) Invention relates to instrument making and can be used in inertial navigation systems. To achieve the result, the vector inertial navigation system has an accelerometre - octahedral all-aspect vector accelerometre (OAVA), a gyroscopic device - directional gyroscope with four degrees of freedom (DGFDF) and a computer. The octahedral all-aspect vector accelerometre determines the magnitude and direction of the force and acceleration vector acting on the aircraft body in a three-dimensional Cartesian coordinate system relative the sides of the aircraft body. The octahedral all-aspect vector accelerometre is a hollow sphere from which gas has been pumped out and in the inner walls of which six momentum measuring devices (MMD) are embedded in the vertices of the octahedron inscribed in the given sphere. Vertices of the octahedron of the momentum measuring devices are strictly aligned relative the sides of the aircraft body. A momentum measuring device is placed in each vertex of the octahedron conditionally inscribed in the sphere. Each momentum measuring device consists of a rod attached to the inner wall of the accelerometre on a cardan joint. There is a spring on the said rod. |
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Method of space navigation and device to this end Invention relates to instrument making and can be used in space navigation systems to determine aircraft position coordinates. To this end, artificial Earth satellites (AES) are used as celestial reference points. Note here that zenith angle of AES being fixed is measured to be referenced to central zenith angle, aircraft position coordinates are determined from measured and referenced angle and AES coordinates. |
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Invention relates to navigation instrument making. The set problem is solved by that, conditions are created in which substantial connection appears and is used on a section of a ballistic trajectory between error models of inertial measurement modules when solving the problem of orientation and navigation. This connection appears and can be used in providing the following conditions: presence of fast rotation around a longitudinal axis and coning motion of precession of the control object about the centre of mass or only rotation of the object around a longitudinal axis on a ballistic trajectory; placing a unit of accelerometres of inertial measurement modules and a reception antenna for the satellite navigation system at a certain distance (basically on a transverse axis) from the centre of mass of the control object; solving the problem of orientation and navigation in the inertial measurement modules at the point of placing the unit of accelerometres at high frequency - approximately an order higher than frequency of rotation of the control object (due to necessity of generation of dynamic components in navigation parametres without distortions); formation of measured values of primary navigation parametres in the reception apparatus of the satellite navigation system where the reception antenna is placed using tracking measuring devices with bandwidth greater than the frequency of rotation of the control object. Also values of primary navigation parametres are calculated in the computer of the inertial measurement modules and these values are also used in the feedback in the reception apparatus of the satellite navigation system for narrowing the frequency band in tracking systems of carrier frequency and code delay. |
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Method for building of orbit-based functional addition to global navigation system Invention is related to satellite navigation and may be used to build orbit-based functional addition to global navigation satellite system (GLONASS). Substance of method consists in the fact that on board of low-orbit spacecraft navigation equipment of user is installed, which is used to receive navigation messages, as well as additional equipment used to receive signals of on-air television of ground stationary television radio stations, bearing frequencies of two or more television channels are separated, on the basis of which Doppler shift of bearing frequencies is detected, orbit parametres are detected, calculating ephemerids of spacecraft, and navigation messages are formed in accordance with specified structure of navigation message, then radio navigation signals are broadcasted in direction of navigation information consumer location. |
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Device for choosing objects to be observed from orbiting spacecraft Device for choosing objects to be observed from an orbiting spacecraft (SC). Device for choosing objects to be observed from an orbiting spacecraft comprises a globe with a map on it, two rings embracing the globe; the first ring is fixed above the globe pole points and can be rotated around the globe rotation axis and the second one is set in the globe equator plane and fixed at the first ring in the points of its crossing the globe equator plane. Following units are additionally mounted: an element in the form of a spiral turn simulating an orbit turn of the SC moving around the planet with the planet map being represented on the globe and an element with its outline projection on the globe surface forming a circle which is limiting a segment with a half-angle on the globe surface. The element with its outline projection on the globe surface forming a circle is made as a semitransparent spherical segment with a slot from the spherical segment edge to its centre. |
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Chart board to select observation objects aboard orbital spacecraft Chart board designed for selecting observation objects aboard the orbital spacecraft comprises a semi-transparent plate depicting a curvilinear spacecraft trajectory, a flexible tape arranged behind the said plate with two copies of the Earth surface maps wherein the end points of equator of the first map are aligned with the start points of equator of the second map, and a device designed to move the tape with maps along the plate made up of two shafts spaced apart and linked up in parallel, the enclosed tape being arranged so as to move along equators of both maps. Note that, in compliance with this invention, the proposed chart board comprises additionally a flexible semi-transparent tape with two celestial maps, including ecliptic line, wherein the end points of equator of the first map are aligned with the start points of equator of the second map, and a device designed to move the tape with celestial maps along the plate made up of at least two spaced apart and linked up in parallel shafts whereon a new tape is located so as to move along the equators, second semi-transparent tape depicting curvilinear lines everyone being made in the scale of the celestial maps axes and being formed by the points spaced apart by an equal angular distance equal to half an opening of a planet disk visible from the spacecraft, and a device designed to move second plate relative to the first one along the axes perpendicular to the maps equators. Note that the scales of celestial maps and the width of the tapes with celestial maps are identical to the scales of the Earth surface maps and the tapes with the Earth surface maps and that both maps scales equatorial axes are represented at the ration of 1:K where K is the factor of compliance of the scales of equatorial scales defined from the formula K=1-tω/(2π+Δ Ω), where T is the spacecraft period, ω is the Earth angular speed of revolution in inertial space, Δ Ω is the helical orbit precession in the inertial coordinate system. Note here that the width of the second plate complies with that of the first plate, the former being determined from the formula L = arccos([cosQ-sin ε sin i]/[cos ε cos i])Ls/2π, where Ls is the length of equatorial scale of one celestial map, Q is the angle of half-opening of planet disk visible aboard the spacecraft, ε, i are the angles of inclination of the planes of ecliptic and spacecraft orbit to the equator plane, respectively. |
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Map-board for selection of object for observation from orbital spacecraft Map-board for selection of object for observation from orbital spacecraft (SC) includes flexible tape with two copies of planet surface map applied on it with aligning the Equator end point of the first map copy with the Equator start point of the second map copy, device providing map tape movement from two spaced and secured in parallel shafts. At that, the tape is looped and located on shafts with possibility of its circular motion along equator line of the maps. Additionally following is introduced: translucent tape with the image of continuous line of route for at least three sequential aircraft orbit passes, device providing movement of the tape with image of orbit along the tape with maps from two spaced and secured in parallel shafts and device for synchronisation of movement of the tape with maps and the tape with orbit image. At that, the tape with orbit image is looped and located on shafts of device providing movement of the tape with orbit image with possibility of its circular movement along equator line of the maps. Length of the tape with orbit image is made equal to overall length of represented orbit passes as measured along the equator direction, length of the tape with maps is made equal to total length of equators of plotted on the tape maps, and width of the tape with orbit image and width of the tape with maps are made in the ratio equal to ratio of orbit inclination angle to 90°, at that diameter of shafts of devices providing movement of the tape with orbit image is made equal to diameter of shafts of device providing movement of the tape with maps and constitutes value not exceeding one-fourth of difference between length of the tape with orbit image and length of the tape with maps. |
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Accelerometer assembly and angular velocity sensor unit are mounted on platform in biaxial Cardan suspension. Platform is stabilised around Cardan suspension axes using signals generated by angular velocity sensor, and torque meters mounted on Cardan suspension axes. Apparent accelerations of platform are measured using signals generated by accelerometers. Absolute angular velocity of platform is measured using signals formed by angular velocity sensor. Angular position of object body is measured concerning platform using signals generated angle-data transmitter mounted on suspension axes of platform. Received signals are computer processed and navigation parameters of object is calculated in reference coordinate system. |
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Choice plotter for objects under observation from orbital spacecraft Choice plotter of objects under observation from orbital spacecraft (SC) includes translucent plate with image of SC orbit pass curve, flexible belt located under the plate and containing two applied copies of planet surface map with aligned equator end point of the first copy of map and equator start point of the second copy of map, and map belt shift device along the plate from two spaced and parallel interconnected shafts on which closed belt radially moving along the map equator lines is mounted. In addition there are introduced flexible translucent belt with object image of two copies of stellar map, including ecliptic line with aligned equator end point of the first copy of map with equator start point of the second copy of map, and stellar map object image belt shift device along the plate from at least two spaced and parallel interconnected shafts on which newly introduced belt moving along map equator line. Along the axes perpendicular to map equators, stellar map scale and belt width with stellar maps coincides respectively with terrestrial map scale and belt width with terrestrial map. Along equatorial axes, stellar and terrestrial surface map scales are executed in ratio 1:K. Stellar map object image belt shift device is executed in the form of two spaced and parallel interconnected shafts. The radius of shafts of stellar map object image belt shift device is more or equal to radius of shafts of terrestrial surface map belt shift device. Distance between shaft axes of stellar map object image belt shift device exceeds total distance between shaft axes of terrestrial surface map belt shift device and radiuses of all four shafts of both belt shift devices Width of plate with orbit line image and width of belts are provided in relation equal or more than relation of orbit dip angle to 90°. |
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Choice device of astronomical objects under observation from orbital spacecraft Choice device of astronomical objects under observation from orbital spacecraft (SC) includes stellar globe, ring embracing the globe with aligned ring and globe centres and fixed over globe poles and rotating round globe rotation axis, the second ring embracing the globe with aligned second ring and globe centres and fixed on the first ring in crosspoints of the first ring and globe equator plane and rotating to position of the angle between second ring and globe equator plane equal to the angle of SC orbit dip angle. Additionally there are two elements with contour projection to globe surface forming circles and globe centre direction forming straight line passing through globe centre and perpendicular to the second ring plane, the angle equal 90° minus one-half angle of planet disk visible from SC round which SC moving in semi-circular orbit turns. Elements are fixed over globe surface from its opposite sides with one or more arches connecting introduced elements with the second ring. In addition each newly introduced element is designed in the form of translucent spherical segment one-half angle of which angle is equal 90° minus one-half angle of planet disk visible from SC, with slot provided from spherical segment edge to its centre arch length of which is equal or more then one-half angle of spherical segment minus SC orbit dip angle. Spherical segments centres lay on straight line passing through globe centre and perpendicular to the second ring plane with aligned centre of sphere forming spherical segments and globe centre. Slots in spherical segments are opposite to different globe poles. In addition each newly introduced element is constructed as ring placed on ruptured element contour. Ring segments opposite different globe are removed within ring rupture points. |
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Device for selection of observation object from space vehicle Device relates to space technology. The device consists of a globe with a map on it, two rings bracing the globe, the centres of which coincide with the centre of the globe, an element in the form of spiral coil, corresponding to the average turns of orbits of the space vehicle moving in an almost circular orbit, starting from the ascending node of the turns of the orbit, given in the right Cartesian coordinate system OXYZ, the centre of which coincides with the centre of the globe and the OZ axis is directed on the axis of rotation of the globe, with coordinates calculated from the formulae: x = r(cos (Δλu / (2π) ) cos u - sin (Δλu / (2π)} sin u cos i), y = r(sin (Δλu / (2π)) cos u + cos (Δλu / (2π)) sin u cos i), z = r sin u sin i, where i is the inclination of the orbit; r is the radius of the second ring; Δλu is the angular inter-turn distance of the orbit on the equatorial scale of the map; u is a parameter assuming values from 0 to 2π. The first ring is fixed over the terminal points of the globe with provision for rotation of the ring around the axis of rotation of the globe. The second ring is installed in the plane of the equator of the globe and is fixed on the first ring at the point of intersection of the first ring with the plane of the equator of the globe. The element in the form of a spiral coil is fixed to the second ring at the point of intersection of the second and first rings, by its middle point, corresponding to the value of the parameter u, which equals π. The technical outcome is the determination and selection of observation objects. |
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Plane table for observation object selection from an orbiting space vehicle Invention pertains to devices for space navigation and is directed at providing for the possibility of selecting under conditions of a space vehicle, observation objects with simultaneous consideration of the stipulated conditions, related to objects on the earth's surface and in the celestial sphere. This result is provided for due to that, the plane table for selection of the observation object from an orbiting space vehicle consists of a plate with a map of the earth's surface, a semitransparent plate with an image of the curved line of the orbit pass of the space vehicle from its ascending node, installed over the map of the earth's surface with provision for displacement along the equator of the earth, a semi transparent plate with an image of the objects on the stellar map, installed over the map of the earth's surface with provision for movement along the earth's equator line, and a device providing for mutual displacement of plates along the equator line. On the axes, perpendicular to the equator, the scale of the stellar map and the corresponding size of the plates with the given map coincide with the scale of the map of the earth's surface and the corresponding size of the plate with the map of the earth's surface, and on the equatorial axes, the scale of the stellar map and the map of the earth's surface have a ratio of 1:K, where K is the coefficient of concordance for the scales of the equatorial scales, defined from the formula K=1-Tω/(2π+Δ Ω), where T is the orbiting period of the space vehicle around the earth, ω is the angular velocity of rotation of the earth in the inertial space, Δ Ω is the turning precession orbit in the inertial coordinate system. The maps are made with the longitudinal dial of the earth's surface in the range from 0 to 4π+Δ Ω-Tω and the straight ascendancy scale of the stellar map in the range from 0 to 4π+Δ Ω, and the size of the plates with orbit and with maps of the earth's surface and the celestial sphere along the equatorial axes are in the ratio (2π+Δ Ω-Tω):(4π+Δ Ω-Tω):(4π+Δ Ω-Tω-2πTω/(2π+Δ Ω)). |
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Plot board for ground surveillance object selection from orbital space vehicle Plot board for ground surveillance object selection from orbital space vehicle refers to space technology. The plot board for ground surveillance object selection from orbital space vehicle includes flexible tape with the ground map printed on it, and semitransparent plate above the tape. Two halves of the space vehicle's orbit pass are drawn on the plate in such a way that the ascending node in the beginning of the first half of the orbit pass and the descending node in the beginning of the second half of the orbit pass are superimposed. The plot board also comprises a device for the tape map transport along the plate with orbit pass image; the transport device comprising two shafts that are spaced-apart and interconnected in parallel. The map printed on the tape has the equator beginning and ending points superimposed, and the tape is made in the form of a ring and pulled on the shafts so as to move along the map equator line. The distance between the shaft axes and size of the plate with the orbit pass image along the equator direction are equal to (L-d)/2, where L - is the map equator length; d - is absolute distance between passes measures in linear units along the map equator; shaft radius equals to d/(2π). The stated above gives the effect of decreased plot board size. |
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Coherent transponder of phase synchronization Coherent transponder of phase synchronization has a radio receiving set, a radio transmitting set, an airborne standard of frequency (H-maser) and also a logic and commutation block. The radio transmitting so as the radio receiving set consists of two half-sets. The radio receiving set has a radio receiver module of the amplifier of a very high frequency, a preliminary amplifier of intermediate frequencies, a block of phase automatic adjustment of the frequency, the amplifier of the reference signal 2▾ and the secondary source of feeding.▾- nominal frequency. The coherent transponder of the phase synchronization provides transformation of the input signal in diapason 961▾ into an answer signal in the diapason 1120▾ used for synchronization of the airborne thermostating controlled generator. For reducing the drift of the phase of the answer signal the system of transformations of frequencies is built on the principle of complete matching of tracts of multiplying of the radio transmitting set and the heterodynes of the radio receiving set. |
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Method for autonomous navigation and orientation of spacecrafts Method for autonomous navigation and orientation of spacecrafts includes computer calculation of position in three-dimensional space of ort of radius-vector of support (calculated, a priori assumed) orbit, rigid attachment of optical-electronic device on the body of spacecraft and measurement of coordinates and brightness of stars, which are in the field of view during navigational sessions, in it. |
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The Sun attitude pickup has an optical system made in the form of a wide-angle lens including an inlet and outlet plano-convex lenses with a diaphragm placed between them, an optical element is positioned in its holes, matrix photodetector, and a unit for processing of information and computation of coordinates. The refractive indices of the optical components are selected proceeding from the relation: n1≥n2<n3, where n1 - the refractive index of the inlet plano-convex lens; n2 - the refractive index of the optical element; n3 - the refractive index of the outlet plano-convex lens. |
Another patent 2528741.