Method for photonic location of aerial object

IPC classes for russian patent Method for photonic location of aerial object (RU 2497079):

G01C21/24 - specially adapted for cosmonautical navigation

Another patents in same IPC classes:

Method for determining failures of gyroscopic metre of vector of angular speed of space vehicle, and device for its implementation / 2495379

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.

Device to select astronomic objects of surveillance from orbital spacecraft / 2495378

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.

Device for selecting astronomical objects for observation from orbital spacecraft / 2488077

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.

Board for selecting observation objects from orbital spacecraft / 2482451

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.

Method for ephemeral provisioning of process for controlling global navigation satellite system spacecraft / 2477836

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.

Method of monitoring continuity of navigation field of global navigation satellite system / 2477835

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.

Device to select objects of surveillance from orbital spacecraft / 2471150

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.

Angle measurement device / 2470258

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 0.5^x.

Board for selecting observation objects from orbital spacecraft / 2469274

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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Method of autonomous measurement of angular speed vector / 2282826

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Sun attitude pickup / 2308005

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Method for autonomous navigation and orientation of spacecrafts / 2318188

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Coherent transponder of phase synchronization / 2319931

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FIELD: physics.

SUBSTANCE: 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.

EFFECT: providing passive location of aerial objects without on-board UV transmitters, by receiving and processing weak photon radiation from the nose and tail parts of the moving aerial objects using two spaced apart groups of UV detectors synchronously scanning space.

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The invention relates to the field of detection of air targets, as well as to the areas of automated control systems and processing, optics, satellite navigation and computer engineering and can be used for automated detection and tracking.

Widely known method of radiolocation IN (Dictionary of ham, M., "Energy", 1966, str), characterized by the reception of waves, which allows to detect and track IN. The known method, despite the very wide use, has a number of disadvantages, which primarily include:

- a relatively large complexity and cost of the radar;

- the vulnerability of the fashion radar for military use, because, radiating radio, radar reveals his whereabouts;

the relatively low efficiency of the method of radiolocation in the face of many modern defenses (radioactive suppression spray masking substances and elements, coated IN special substances and materials that make IN invisible and others).

The closest to the technical nature of the claimed invention is a method described in the invention "Complexional universal weatherproof method for identifying and landing aircraft..." (patent is 2441203 IPC ⁷G01C 21/24 2010), including the location in space with the aid of ultraviolet receiver (UFP) of photon radiation IN the processing of the received signal in OFP, and then in the computer and the coordinates of the location IN space at the appropriate time common timing system (CTS), with reference to the common coordinate system and to the NORTH is carried out using local control and correction station (LCCS), receiving in addition to photon radiation IN using UFP from navigation satellites (NS) operating global navigation systems periodic radiopacity containing the IDs of the current values SOWING at the time of radiation of radiopodarok relevant NS, and the data for the exact calculation of the coordinates of the dislocation LCCS and its UFP, which are processed by a group of satellite receivers and transmitter LCKS.

The disadvantage of this method is the relatively small range detection and tracking IN the order of 10 km)that were dictated by the specific task of working near the runway and landing IN without using a special antenna means with the masts needed for more distant locations. But the most important thing is that the known method, oriented to receive relatively strong ultraviolet radiation from Bartova the ultraviolet transmitter, does not allow for passive location IN without such on-Board transmitters (and missile), and also when they are shutdown and malfunction.

In recent years a highly sensitive AFP (such receiving tube has the applicant of the present invention)that capture even single photons at a distance of 100 km from the source, allowing you to take on such distances relatively weak ultraviolet radiation from any moving IN generating such radiation from the nose and tail areas due to shock and temperature of the gas is ionized. However, with such a high sensitivity WFP and when such relatively large distances, the challenge is the selection of the useful signal in the multiple photon interference.

The technical result and the purpose of the invention is to enhance the functionality of the prototype, i.e. the provision of passive location, does not have on-Board UV transmitters, by receiving and processing weak photon radiation from the nose and tail parts moving IN with spaced apart two synchronously scanning the space groups UFP.

The technical result and the goal is achieved that the method of photon locations of air object (VO), characterized by the detection of ultravio etopim receiver (UFP) of photon radiation, the processing of the received signal in OFP, and then in the computer to determine a position IN space at the appropriate time common timing system (CTS), with reference to the common coordinate system and to the NORTH is carried out using local control and correction station (LCCS), receiving in addition to photon radiation IN using UFP from navigation satellites (NS) operating global navigation systems periodic radiopacity containing the IDs of the current values of the NORTH at the time of radiation of radiopodarok relevant NS, and the data for the exact calculation of the coordinates of the dislocation LCCS and its UFP that handled by a group of satellite receivers and transmitter LCCS, as well as the fact that the detection of photon radiation IN the source region of ionization of gases near the tip and nozzle moving IN, is performed using the first and second groups UFP placed respectively on the first and second vertical synchronous and in-phase mechanically rotating around its axis in the azimuthal plane poles spaced from each other on the base distance, and with each group UFP detection of photon radiation IN at any given time carried out from all directions 90 - degree elevation plane for MF is t uniform distribution the optical axes UFP each group at 90 degrees with a narrow directivity UFP in the azimuthal plane, and due to the rotation of the masts on each 360 - degree review - consistently from all directions 180 - degree elevation plane, take each group UFP radiation IN if any transform in each UFP into a digital code, and then recorded in the memory of the calculator separately for each mast arrangement for each of the detected radiation with the fixation of the obtained azimuth angle and elevation angle, and azimuth angle for each mast is calculated by the middle of the sector continuously received radiation generated as a result of rotation of the mast, and elevation for each mast is calculated by the middle of the sector continuously received radiation corresponding set of adjacent WFP simultaneously with the obtained angles of azimuth and place for each radiation for each mast in memory of the transmitter register corresponding data reference SOWING and calculated according to the obtained angles the values of the distance and height, then for the current review identified separately obtained counts for each mast on their General traits of angles, distance and height at specific coordinates of a particular detected IN, which are specified on the next and subsequent review on the grounds specified angles, distance and height, and also for appearing more General terms, speed, maneuver and directions on what to achieve.

In figure 1, 2 and 3 present, respectively, sketches, explain the operation of the process showing the main elements of the implementation aspects of the azimuthal and elevation planes.

The figures shows the first mast 1 with the first group OFP 2, the second mast 3 with the second group UFP 4, point 5 and 6 installation of the first and second masts and base 7 of them explode, 8, ultraviolet radiation 9, LCCS 10 with a transmitter 11, as well as additional theoretical point 12 and 13, forming in the azimuthal plane two similar right-angled triangle 5-12-6 and 5-8-13 (figure 2), and 14 and 15 forming the elevation plane of the two similar right-angled triangle 5-14-6 and 5-8-15.

Figure 2 shows the azimuthal angles X1 and x2 of rotation of the first group OFP 2 and the second group UFP 4, respectively, relative to base line 7 explode masts 1 and 3, and figure 3 is an elevation angles U1 and U2, respectively, between lines connecting AT 8 with UV P2 and 8 with UV A4, and the projections of these lines in the azimuthal plane.

The way the photon location of air object (IN) 8, characterized by ultraviolet detection receivers (UFP) 2 and 4 photon radiation 9 IN this, the processing of the received signal in OFP 2 and 4, and then the transmitter 11 LCCS 10 and determining the position IN space at the appropriate time common timing system (CTS), while binding to a single is the first coordinate system and to the NORTH is carried out using LCCS 10, receiving in addition to photon radiation from 9 IN 8 using OFP 2 and 4 from the navigation satellites (NS) operating global navigation systems (NS Fig. not shown, because it is beyond the scope of this application) periodic radiopacity containing the IDs of the current values of the NORTH at the time of radiation of radiopodarok relevant NS, and the data for the exact calculation of the coordinates of the dislocation LCCS 10 and its component OFP 2 and 4, which are processed by a group of satellite receivers and transmitter LCCS, and the fact that the detection of photon radiation from 9 IN 8, the sources of which are the regions of ionization of gases near the tip and nozzle moving IN 8, is performed using the first and second groups OFP 2 and 4, placed respectively on the first 1 and the second 3 vertical synchronous and in-phase mechanically rotating around their axes 5 and 6 in the azimuthal plane poles spaced from each other by a base length 7, and with the help of each group OFP 2 and 4 detection of photon radiation from 9 IN 8 in every the moment in time carried out from all directions 90 - degree elevation plane due to the uniform distribution of the optical axes UFP each group 2 and 4 at 90 degrees with a narrow directivity UFP in the azimuthal plane, and due to the rotation of the mast 1 and 3 on each 360 - degree is bore - consistently from all directions 180 - degree elevation plane, take each group OFP 2 and 4 photon radiation from 9 IN 8 if any transform in each UFP into a digital code, and then recorded in the memory of the computer 11 separately for each of the mast 1 and 3 orderly for each detected radiation 9 with fixing the obtained azimuthal angle X1 (x2) and angle U1 (U2), and azimuthal angle for each mast is calculated by the middle of the sector continuously received radiation 9, formed as a result of rotation of the mast 1 and 3, and elevation for each the mast is calculated by the middle of the sector continuously received radiation corresponding set of adjacent OFP 2 and 4, simultaneously with the received azimuth angles X1 (x2) and designated U1 (U2) for each radiation 9 for each of the mast 1 and 3 in the memory of the computer 11 register corresponding data reference SOWING and calculated according to the obtained angles the values of the distance and height, then for the current review identified separately obtained counts for each mast 1 and 3 according to their common characteristics of angles, distance and height at specific coordinates of a particular detected IN, which are specified on the next and subsequent reviews features refined angles, distance and height, and also for appearing more General terms, speed, maneuver, and eg is the exercise movement.

The method is as follows.

Suppose the rotation of the first 1 and second 3 mast placed on them, respectively, the first 2 and second 4 groups UFP (1, 2) is in the azimuthal plane (parallel to the earth surface) synchronously and in phase (at the same speed, in one direction, for example, one revolution/sec, in a clockwise direction and with the same initial reference azimuthal angles X1 and x2 from a straight line coincident with the base line 7) and let each mast 1 and 3 is set to 18 (n=18) narrow-angle 5-degree WFP covering together 90 degrees elevation plane (orthogonal to the azimuthal plane) by sequential shift pattern (or optical axis) of each adjacent WFP otnositelnoj the nearest 5 degrees. Let all UPP in the azimuthal plane are also 5-degree directional pattern.

Then by rotating masts 1 and 3 at the hit of the continuous radiation from 9 IN 8 in 5-degree sector of the perception of some UFP (first one group of 2 or 4, and then the other, depending on which side of the base 7 is IN 8, except sudaev, when 8 is on the base line 7, i.e. on the same azimuth) perceiving WFP convert parallel analog signal radiation 9 into digital form using an analog-to-digital Converter (ADC), four is irua on the output of each of the perceiver WFP pack related digital samples (typically 5-10 times, depending on the pattern WFP and speed of rotation of the mast 1 and 3), which are then recorded in the memory of the computer 11 separately for each of the mast 1 and 3 with fixation of the azimuthal angle X1 (x2) and simultaneously tilt N1 (N2), as in this example, when using 18 WFP, dispersed in the elevation plane, perceiving radiation 9 WFP indicate elevation U1 (U2). The azimuthal angle X1 (x2) for each of the mast 1 and 3 use a calculator 11 calculates in the middle of the sector continuously received radiation 9 - in the middle of the pack adjacent digital samples, and the angle designated U1 (U2) in the middle of the sector perceives radiation 9 together adjacent OFP 2 (4). Simultaneously with the obtained angles of azimuth and place on each mast 1 (3) separately for each radiation given IN 8 (for others IN the same way) when they register register counts the NORTH.

On the obtained angles in the transmitter 11 at a known distance of the base 7 and the known value of the angles XI and x2 calculated value IN a range of up to 8 point 5 and point 6, as well as its height. For a right triangle 5-12-6 through the cosine X1 and sinus X1 receive side 5-12 and 6-12, and then through the proportions of similar right-angled triangles 5-12-6 and 5-8-13 at a known angle x2 are determined by any side of the triangle 5-8-13, including side 5-8, representing a projection of the slant range to the azimuthal plane. Similarly, C is th the angles U1 and U2 and the value base 7, elevation plane determine the amount of cut 8-15, i.e. the height IN 8 and size 5-8, i.e. inclined IN the range of up to 8 from point 5. After that, for the current review (one complete revolution of the masts 1 and 3) identify separately the received samples for each mast on their General traits of angles, distance and height at specific coordinates of a particular detected IN 8, which are specified on the next and subsequent review on the grounds specified angles, distance and height, as well as additional signs of speed, maneuver and movement.

In order to reduce the number UFP in groups 2 and 4 is used on each mast m wide OFP 2 and 4, covering together 90 degrees in elevation, for example, two WFP (m=2) with the pattern every 45 degrees. Additionally, each mast 1 and 3 apply d narrow-angle WFP, for example, one 5-degree UFP (d=1), which activate at a specific azimuth detection radiation 9 specific wide-angle WFP, and activate in the appropriate 45-degree sector to Refine the angle designated by mechanical or electronic scanning narrow-angle UFP. The gain in value of the product (instead of n=18 is used only three UFP) at the expense of lengthening the processing time due to the need to clarify the values of the elevation angle.

For maximum gains in the time of reception and processing of radiation 9 (due to the substantial appreciation of the product) both groups OFP 2 and 4 are placed on the two hemispheres, ensuring the reception of radiation from all directions at once.

1. The way the photon location of air object (VO), characterized by ultraviolet detection receiver (UFP) of photon radiation, the processing of the received signal in OFP, and then in the computer to determine a position IN space at the appropriate time common timing system (CTS), with reference to the common coordinate system and to the NORTH is carried out using local control and correction station (LCCS), receiving in addition to photon radiation IN using UFP from navigation satellites (NS) operating global navigation systems periodic radiopacity containing the IDs of the current values of the NORTH at the time of radiation radiopodarok relevant NS, and the data for the exact calculation of the coordinates of the dislocation LCCS and its UFP, which are processed by a group of satellite receivers and transmitter LCCS, characterized in that the detection of photon radiation IN the source region of ionization of gases near the tip and nozzle moving IN, is performed using the first and second groups UFP placed respectively on the first and second vertical synchronous and in-phase mechanically rotating around its axis in the azimuthal plane poles spaced apart one from the other by a base length, moreover, with each group UFP detection of photon radiation IN at any given time carried out from all directions 90-degree elevation plane due to the uniform distribution of the optical axes UFP each group on these 90° with narrow directivity UFP in the azimuthal plane, and by rotating masts on each 360-degree review - consistently from all directions 180-degree elevation plane, take each group UFP radiation, if any transform in each UFP into a digital code, and then recorded in the memory of the calculator separately for each mast, for orderly each detected radiation with fixing the obtained azimuth angle and elevation angle, and azimuth angle for each mast is calculated by the middle of the sector continuously received radiation generated as a result of rotation of the mast, and elevation for each mast is calculated by the middle of the sector continuously received radiation corresponding set of adjacent WFP, simultaneously with the obtained angles of azimuth and place for each radiation for each mast in memory of the transmitter register corresponding data reference SOWING and calculated according to the obtained angles the values of the distance and height, then for the current review identified separately obtained atsche the s on each mast on their General traits of the corners, the distance and height at specific coordinates of a particular detected IN, which are specified on the next and subsequent review on the grounds specified angles, distance and height, and also for appearing more General terms, speed, maneuver and movement.

2. The method according to claim 1, characterized in that the detection of photon radiation IN the corner of the place is carried out using n narrow in the elevation plane WFP, each of which each mast is installed with a corresponding angular offset of 90°/n, for each detection of the source of photon radiation simultaneously determine the angles of azimuth and places, allowing rotation of the mast carried out with the greatest possible speed for mechanical systems rotation about one revolution per second.

3. The method according to claim 1, characterized because the detection of photon radiation IN the azimuth angles and locations is carried out by electronic scanning space by WFP distributed with the corresponding angular displacements of the elevation angles and azimuth and placed on the surfaces of the two hemispheres, associated respectively with the first and second masts.

4. The method according to claim 1, characterized in that the detection of photon radiation IN the exercise by each mast m UFP with wide angle directed the TEW, which together cover 90° elevation plane and d UPP with narrow-angle orientation of the overlapped by electronic or mechanical scanning 90° elevation angle and narrow-angle WFP activate upon detection of photon radiation at a specific azimuth angle to clarify the appropriate elevation angle.