Method of calibrating radar station from effective radar cross-section value during dynamic measurement of effective radar cross-section of analysed objects |
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IPC classes for russian patent Method of calibrating radar station from effective radar cross-section value during dynamic measurement of effective radar cross-section of analysed objects (RU 2477495):
                  
 Radar high-frequency frequency-modulated doppler signal simulator / 2469348
Radar high-frequency frequency-modulated Doppler signal simulator is meant for use in complex signal generators, as well as in modulating systems for testing and investigating radio engineering systems. The system includes two phase modulators, a balanced modulator, a phase detector, a controlled high-frequency signal generator, a directional coupler, a controlled attenuator, connected to each other in a certain manner.
 Method of calibrating active phased antenna array / 2467346
Invention relates to antenna equipment and is meant for calibrating active phased antenna arrays. The method of calibrating an active phased antenna array, in which in order to calibrate the receiving part of the transmit-receive channel, a control signal is transmitted to the input of the receiving part of each channel; parameters of the received signal are measured; adjusting coefficients which are used to adjust parameters of the receiving part of the channel are formed based on the measurements; to calibrate the transmitting part of the transmit-receive channel, a control signal is transmitted to the input of the transmitting part of each channel; parameters of the transmitted signal are measured; adjusting coefficients which are then used to adjust parameters of the transmitting channel are formed based on the measurements; calibration of the receiving part of the transmit-receive channels is carried out in pairs in receive mode, wherein the control signal is picked up from the output of the receiving part of the transmit-receive channels; calibration of the transmitting part of the transmit-receive channels is carried out in pairs in transmit mode, wherein part of the signal power tapped from the output of the corresponding transmit-receive channel and passing through the receiving part of that channel is used for calibration; during calibration, phase shift and amplitude difference of the signal from the output of the calibrated channel relative the reference channel are determined; the same reference channel is used for calibrating all channels.
 System for built-in control and calibration of monopulse radar station / 2459219
During control, a portion of probing signal power, which is fed to a circuit signal simulator and through a circulator to an adder with a heterodyne simulator signal, is output from a monopulse radar station; the resultant signal is fed to a mixer, conveyed at an intermediate frequency and is fed to a recirculation circuit, which is built on series-connected second adder and delay line, where the damped batch of delayed pulses returns to the mixer, where it is conveyed at carrier frequency using the heterodyne signal, passes through the circulator to series-connected valve, test antenna and radio communication channel to the antenna of the monopulse radar station. The processor of the monopulse radar station controls the process of built-in control in signal search, capture and tracking modes; measurement of bearing characteristics takes place based on target search results with scanning of the antenna system; capturing and tracking results are used to determine coordinates of the simulated target, controlled parameters of the transmitter, the receiver and signal of the detector; by comparing the controlled parameters with rated values, the processor determines accuracy of the monopulse radar station and deviation of calibration, which it then stores and takes into account when measuring coordinates of targets during combat.
 Method of calibrating mobile shortwave direction finder with multielement antenna array / 2451948
Invention can be used to calibrate radio signal source direction finders, particularly mobile shortwave (SW) direction finders with a multielement antenna array (AA). The method involves measuring the required number of positions of the radiator for control measurements, the distance between the position of the control radiator (CR) and the closest antenna component (AC) and the coordinate of the positions for installing the CR; receiving a control signal for an N-element distributed AA; frequency selection and measurement of the phase of the received signal pulses; selection of a reference AC, after which CR are successively installed at each given position; determining the initial disparity of measurements of phase difference between each (N-1)-th and the reference AC; and the mean-square deviation (MSD) of the measurement results is calculated; through successive iterations, adjustments are made to the estimate of true coordinates of the AC and the estimated phase defects of feeders and the disparity of phase difference between each (N-1)-th and the reference AC for each position of the CR is re-determined, thereby achieving the minimum attainable MSD of measurement results; and the coordinate values of phase centres of the AC and allowable values of phase offset of the AA feeders, needed for measuring bearings, with minimum error, to signal sources monitored by the mobile direction finder, are determined.
 Radar systems power supply control device / 2449343
Device to control power supply to radar systems comprises the following: a clock pulse oscillator; a reprogrammable logic circuit (PLIC); comprising a logical device; four tumblers; three power supply sources; three relays; three generators of bit commands; three light diode indicators; and eight noise eliminators included into the PLIC, each including two pulse counters, an inverter, a trigger; and links between them.
 Imitator of moving objects / 2449308
Imitator of moving objects comprises a synchroniser, a unit of signal imitation control, three frequency modulators, a pseudorandom signal generator, a low pass filter, two generators of movable strobes, two strobing units, six controlled attenuators, a controlled noise generator, a controlled delay element, a summator, two phase commutators and three amplifiers of intermediate frequency that are connected to each other in a certain manner.
 Calibration method of decametric radio direction-distance finder / 2422846
On the basis of additional information obtained as a result of identification and extraction of signals of beams of common and non-common polarisation, increase in content of calibration information to two segments of calibration data, which differ by polarisation, and use of formation technology of base of calibration data of ionospheric waves on the basis of combination of measurements made on actual direction finder and its dummy corrected as to actual ionospheric signals.
 Radar target simulator / 2412449
Before combat mission, simulator is calibrated. Signal received from scanning radar is attenuated by first attenuator before conversion into intermediate frequency and delay thereon, by appropriate magnitude that sets maximum signal at digital delay circuit input. Before inverse conversion of delayed signal into carrier frequency, it is attenuated by second attenuator by magnitude equal to difference between signal attenuation in radio line radar - target and the sum of signal attenuation in first attenuator and constant losses in simulator. To set attenuation of first attenuator in calibration, first attenuator output signal is detected, and digitised. Mismatching of digitised signal maximum is determined in each scanning cycle relative to tolerable level used by computer to adjust signal attenuation for mismatch decrease till it becomes lower than tolerance.
 Adjusting tower / 2406066
Adjusting tower comprises board, where ancillary antenna, optical radiator and geodesic mark are installed. Source of optical radiation and geodesic mark are located at the distances from phase centre of ancillary antenna that are accordingly equal to displacements of optoelectronic and infrared direction finders from centre of radio direction finder antenna opening. Geodesic mark is represented by infrared radiator. Imitator of moving target is installed near ancillary antenna. Board is installed on three-coordinate drive providing for board rotation by tilt angle, azimuth and heel.
 Imitator of stage radar signal / 2403587
Serial reflection of flat wave of signal radiated by radar station antenna in near zone, from fixed and movable mirrors arranged between radar station antenna and antennas of echo signals. Adjustment of inclination angle of movable mirror provides for radiation of echo signals antennas only at rated angles of RS antenna sighting. At the same time number of antennas and imitators of echo signals is not more than maximum number of targets simultaneously radiated with a directivity pattern of RS antenna in the whole sector of scanning.
 Method of adjustment of optical axis of viewfinder and electrical axis of aerial / 2252427
Viewfinder is disposed at specific distance from mechanical axis of aerial. Viewfinder is tightly connected with antenna aperture plane. Optical axis of viewfinder is directed in parallel to mechanical axis of aerial. Then electrical axis of aerial is guided to phase center of ancillary aerial which is disposed together with geodetic mark onto post. Optical axis of viewfinder is guided onto geodetic mark. Geodetic mark is tied to angular position detectors and stays apart from phase center of ancillary aerial for distance being equal to shift of viewfinder from mechanical axis of aerial to the plane of normal optical axis of viewfinder. Optical axis of viewfinder is guided onto center of aperture of ancillary aerial. Difference in coordinates is determined by angle of location of initial and final position of viewfinder optical axis. Sword is turned around axis being perpendicular to plane of sword and crossing center of ancillary aerial aperture by angle determined by the relation given in the description of the invention. Electrical axis of aerial is guided onto phase center of ancillary aerial and optical axis of viewfinder is guided onto geodetic mark.
 Target fluctuating signal generator / 2253129
The device having a control panel, storage unit, synchrosignal generator, first, second and third on-line memories, unit for formation of target relative coordinates, unit for formation of the maximum target signal intensity, first, second, third and fourth synchronizers, unit for formation of the current intensity of the target signal, digital-to-analog converter, noise generator, adder uses also a correlator, first and second detectors, first and second multiplier units, first and second random number generators, which provides for formation of amicably fluctuating and quickly fluctuating bursts of pulses reflected from the radar targets, internal noise of the receiver and synchronizing signals at the output of the radar receiver in the rate of radar functioning and with due account made for motion of the ship-carrier.
 Generator of reflected radar signals from disturbed sea surface / 2253130
The device has a control panel, memory unit, preliminary recording control unit, unit for formation of carrier relative coordinates, readout and synchronizing unit, on-line memory unit, unit for formation of video signal, unit for formation of carrier polar coordinates, noise formation unit.
 Mode of controlling working capacity of airborne receiver indicator of satellite radio navigational system / 2254591
The mode is that the altitude HRA of the flight of a flying vehicle is measured with the help of installed on it a radio altimeter (RA), the altitude hr of an area above which a flying vehicle flies at the moment of the altitude measuring using for this purpose data about planned coordinates from the output of the receiver indicator of the satellite radio navigational system and digital map of an area, an absolute altitude Ha= HRA +hr, is calculated and compared with the altitude HRI, taking from the output of the receiver indicator and a signal of its working capacity is formed if |Ha- HRI| is smaller than the installed threshold Th.
 Radio-signal dynamic memory device having series binary fiber- optic system / 2255426
In order to enhance identity of copy generation while retaining ability of controlling input radio signal replication process, proposed device is provided with newly introduced (N -1) fiber-optic four-terminal networks, each of them incorporating Y-type internal adding and separating fiber-optic directional couplers.
 Radio engineering training device / 2260193
Device has radio-location station, first high-frequency generator, modulator, first counter, scanning generator, second counter, heterodyne, first mixer, first intermediate frequency amplifier, first amplitude detector, video-amplifier, third counter, cathode-ray tube, second, third and fourth high-frequency generators, first and second adders, switches, phase-rotators and on 90°, second mixer, second intermediate frequency amplifier, multiplier, narrow-band filter, second amplitude detector, key and frequency converter.
 Method for adjustment of radiolocation station antenna / 2262117
Method includes using auxiliary antenna and geodesic mark, linked with indicators of angular position of target antenna, viewfinder is positioned near opening of subject antenna, rigidly linked to opening plane of subject antenna. Flat metallic screen is inserted, to which emission from auxiliary antenna is directed, auxiliary antenna and geodesic mark as light source are positioned behind subject antenna at remote zone distance. Electric axis of subject antenna is directed using its rotation gear according to one of minimum methods to phase center of auxiliary antenna, screen is mounted so, that beams, falling o it from auxiliary antenna and geodesic mark, were reflected respectively to whole plane of opening of target antenna and inlet eye of viewfinder. Angular deflection of optical axis of viewfinder from direction to center of image of geodesic mark on screen determines adjustment of target antenna.
 Radar target simulator / 2267798
The radar target simulator has a super high frequency module consisting of successively connected arrangements: an automatic regulator of power, an impulse modulator, an amplitude modulator, a switch of the power level and a digital attenuator, a communication line, a horn antenna, a group of keys, the first semiconductor storage, an interface of a multiplex bus, a synthesizer of Doppler frequencies, a second semiconductor storage and a multiplying digital-analogue converter. The increasing of the accuracy of the installation of the output power is provided due to possibility of its correction by way of changing the intensity of the amplitude modulation of the super high signal for each meaning of the value of fading.
 Emulation device of an active response radar connected with a surveillance radar / 2268477
It is also used for instruction and training of the operators of the surveillance facilities connected with an active response radars in the conditions of the presence of a great number of targets moving on complex trajectories. The essence of the invention is in that the arrangement holds an oscillator of the signals of the targets including the targets carrying responders. In it there is a control panel of the active response radar, a selector of characteristics of response signals, a synchronizer of response signals, an operating response signals storage device, a decoder of the characteristics of response signals, a counter of tact impulses, a former of identification markers and an adder unit with their connections that provides emulation of the operation of the active response radar connected with the surveillance radar at changing their modes of operations in the process of obtaining radar information about common and individual characteristics of the target carrying a responder in the zone of operations of the mentioned radar facilities with the purpose of verification of their terminal facilities of the secondary processing of radar information, instruction and training of the operators of the surveillance radar.
 Method of controlling of an airborne mono impulse radar station with a built-in unit and an arrangement for its realization / 2268478
The essence is in that in the reference point of the bearer of the rocket or of the streamlined antenna cover a sound is installed. It is made in the shape of a half-wave antenna whose arms are linked up to a nonlinear element. At receiving the order «Control» the transmitter of the airborne mono pulse radar station forming super high frequency vibrations on the carrier frequency fc is connected with the power detector and its power is evaluated, vibrations on the super high frequency fo which is in n times less than the frequency fc are created and delayed in time relatively to the super high signals of the transmitter of the frequency fc and the sound reradiating the signal on the frequency fc is exposed to them. These signals are received and processed with standard facilities of the airborne mono impulse radar station, the imitated distance, the angle α of the azimuth and the place β are measured and compared with the specified parameters and decision about the efficiency of the airborne mono impulse radar station is accepted if the power of the transmitter is no less than admissible and the differences of the specified and the measured angles α and β do not exceed the admissible meanings.
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FIELD: radio engineering, communication. SUBSTANCE: invention can be used when calibrating radar stations from the effective radar cross-section (ERC) value. The disclosed method involves launching a reflector with a known ERC value to an orbit around the Earth, irradiating the reflector with radar signals, receiving and measuring the amplitude of the reflected signals. As an ERC reference, an angle reflector (AR) is transported to a satellite orbit, said AR consisting of two flat radar-reflecting half-discs turned at an angle ranging from (90-Δ)° to (90+Δ)°. Before launching, the AR is put into a guiding container, while aligning the longitudinal axis of the container with the bisector of the angle between faces of the AR. The container is mounted on-board the spacecraft. The spacecraft is positioned such that the longitudinal axis of the container is directed along the line of sight of the radar station. The AR is separated from the spacecraft on the line of sight of the radar station such that the main lobe of the scattering indicatrix of the AR is directed towards the radar station, and its maximum coincides with the line of sight of the radar station. The AR is also spun around an axis which coincides with the bisector of the angle between its faces. EFFECT: high accuracy of calibrating a radar station by eliminating errors caused by deviation of the maximum of the ERC of the reference reflector from the line of sight of the radar station. 12 cl, 16 dwg
The invention relates to the field of radar and can be used in the calibration of radar stations (RS) the magnitude of the effective surface scattering (EPR) when performing dynamic measurements the EPR of the studied objects. A known method of calibrating the radar station, which consists in the following. Launch an artificial Earth satellite (AES) spherical shape, is exposed to the signals of the calibrated radar, and take measure of the amplitude reflected from the satellite signals, which is used as an appropriate reference value ESR reflector, [1], str-213. The disadvantage of this method is the impossibility of its use for calibration largest ESR radars operating on the waves of circular polarization in parallel to the reception of the reflected signals, as for such radar reflector spherical invisible, [3], str. Another disadvantage of the method using a spherical reflector as standard EPR, for a radar operating on the waves of horizontal, vertical and circular polarization in the orthogonal reception of the reflected signals is small EPR sphere [3], str. In addition, to make the field of large dimensions with high accuracy is extremely difficult, and to put into orbit is almost impossible, [4], p.51. The closest analogue invented the self is the way, in which the reference scatterer is used straight circular cylinder [1], str-213. Such a cylinder is shown in low-earth orbit and to him is given "coveritlive" movement so that its longitudinal axis 1 was oriented perpendicular to the line of sight 2 radar station 3 (see figure 1). Irradiate the cylinder signals calibrated radar, receive the reflected signals and performs the measurements of the amplitudes of the reflected signals when the orientation of a right circular cylinder in the vicinity of this area (see figure 1), which may allow to Refine the calibration of the radar station, [1], str-213. However, this method has low accuracy, so as in the direction normal to the axis of the cylinder, a straight circular cylinder has a narrow petal scattering phase function, [1], p.19-20, [3], str. However, the sector angles used to calibrate radar largest EPR, near the maximum lobe of the scattering phase function of a right circular cylinder in this direction even more narrow. Any slight deviation of the axis of a right circular cylinder normal to the line of sight radar direction entails a reduction of power, and, consequently, the amplitude of the signal reflected from a right circular cylinder, which leads to errors in the calibration of radar largest EPR. Thus, the orientation error on the management, normal to the axis of a right circular cylinder with a diameter of 1.2 m and a length of 3 m relative to the line of sight of the radar station at 1.5 degrees in the decimeter range radar, leads to errors in the calibration of radar largest EPR 5 dB, [1], str. With decreasing wavelength radar (in the centimeter range with the same size of cylinder) the width of the main lobe of the scattering phase function in the direction perpendicular to the axis of a right circular cylinder, is significantly narrowed, [1], str. And, therefore, the error of the orientation of the longitudinal axis of a right circular cylinder in the direction perpendicular to the line of sight radar, leads to more significant errors in the calibration of radar largest EPR. In this case, the calibration session is very short. For example, when the period of "tumbling" of a right circular cylinder 10 minutes (600 seconds), [1], str, the time during which it is possible to carry out the calibration session, i.e., near the direction of the axis of the cylinder perpendicular to the direction of the calibrated radar, in the decimeter wavelength range is less than two seconds, and in the centimeter - less than one second. Such a time interval of session calibration does not allow for a sufficient number of single measurements of the signal reflected from the corner cube reflector to perform statistical processing of measurement results, which is also Nigam calibration accuracy radar largest EPR. In addition, use of a straight circular cylinder as a reference is not always possible, as this standard has considerable size and weight, [4], p.37 that does not allow its transportation to low earth orbit passing runs, [1], str. The technical result of the invention is to improve the accuracy of the calibration of the radar largest EPR by eliminating errors caused by the deviation of the maximum EPR reference reflector from the line of sight of the station. This technical result is achieved in that in the method of calibrating the radar largest EPR when performing dynamic measurements the EPR of the studied objects, including: the launch of the reflector with a known value of the EPR on the orbit of an artificial Earth satellite (AES), the radiation reflector signals calibrated radar, reception and measurement of the amplitude of the reflected signals from a reflector located in the far field of the radar antenna, is new is that for the calibration of radar largest EPR, on the orbit of the satellite is transported as a reference EPR angular reflector 4, is designed as two faces of the flat radiotray of palutikof 5 and 6 deployed at a fixed angle, the values of which lie in the range of (90-Δ)° - (90+Δ)°, where Δ is determined by the relation: 0<Δ<18λ/a, λ - wavelength calibrated RL is; a is the radius of paludica the verge of corner reflectors, (see figure 2). Before launching into orbit of the satellite angular reflector 4 is placed in the guide cylindrical container 8 so that the longitudinal axis of the container 9 coincides with the bisector of the angle 7 between the faces of the MA in the plane perpendicular to the mid-rib of the MA (see figure 3). Then, the guide cylindrical container 8 with a corner reflector mounted on Board the spacecraft 10. In memory of the onboard computer of the spacecraft enter the data on the coordinates of the calibrated radar in the geodetic coordinate system. Along with this, in the memory of the onboard computer enter the data on the coordinates installation and spatial orientation (position) of the longitudinal axis of the guide container in the associated coordinate system KA, as well as information about the direction of the Department of EE (velocity vector) from CA. With receivers, navigation systems such as GLONASS and/or GPS and on-Board computers make the determination of the position of the center of mass of the spacecraft relative to the location of the calibrated radar. Then calculate and determine the spatial position of the longitudinal axis of the guide container relative to the line of sight of the calibrated radar at the current time. Estimated onboard you ikitelli machine using system orientation of the spacecraft carry out the combination of the longitudinal axis of the guide 9 of the container 8 with the sight line 2 calibrated radar 3 (see figure 4). With their combination signal generated on-Board computing machine, angular reflector 4 is separated from the space vehicle 10 along the sight line 2 in the direction of the radar 11 or away from the radar direction 12 so that the main lobe of the scattering phase function UO 14 seeks to calibrate the radar (see figure 4). Thus the maximum of the main lobe of the scattering phase function 20 MA 4 coincides with the line of sight 2 calibrated radar 4 maximum value of deviation of the angle between the maximum of the main lobe of the distribution of the scattering angle of the reflector and the line-of-sight radars in the range from -10° to +10° and implement spin (rotation) UO around an axis coincident with the bisector of the angle 7 between the faces of corner reflector 4 in the plane perpendicular to the mid-rib of the MA (see figure 5, 6). In addition, the separation and spin angular reflector produce at the same time. In addition, the twist angle of the reflector to produce its separation from the spacecraft. In addition, the frequency of the spin (rotation) ω corner reflectors are set in accordance with condition: ω>12Fradarπa/λ, where Fradarthe pulse frequency of the radiation transmitter calibrated radar; a is the radius of paludica the verge of a corner reflector; λ - wavelength calibrated radar. <> In addition, before a session of the measurement or during the time of the meeting, conduct the calibration of the radar receivers using calibrated generators connected to the high frequency input receivers, radar, register dependence of the values of the amplitudes of the signal at the output of the radar receivers on the relative values of power (signal/noise) of the signal at the input of the receivers, radar and get the calibration graph.In addition, the measured amplitude of the reflected signals from the angular reflector register, and then via a calibration curve according to the values of the amplitudes of the signal at the output of the radar receivers on the relative values of power (signal/noise) at the input of the radar receivers are converted to values relative power (signal/noise) reflected from the corner cube reflector signals. In addition, using calibrated radar measured slant range to the corner cube reflector. In addition, the value of the relative power reflected from the corner cube reflector count signals (lead) to a fixed range, for example 100 km, according to the formula: Pi=Bi+40LogRi/100, where Bi is the unit of the measured value of the relative power of the signal reflected from the corner cube reflector; Ri is the unit of the measured calibrated radar is slant range to the corner reflectors correspond to the her this Bi. In addition, carry out the calibration of the radar largest effective surface scattering (perform session measurements) on the time interval ΔT: ΔT=t2-t1, where t1- the session start time measurement (calibration RLS); t2- the end time of the session measurements (calibration RLS); and ∆ T can take values in the range from 10 to 600 seconds. In addition, reduced to a fixed range of unit values relative power reflected from the corner cube reflector signal average by the formula:
where n - number of results of single measurements on the time interval ΔT. In addition, the average value of Pcpused as the value of the relative power of the reflected signals corresponding to the reference value of the effective surface scattering angle of the reflector. In addition, the spin (rotation) angle of the reflector 4 are carried out either "clockwise" 15 or "counterclockwise" 16 (see figure 5, 6), relative to the direction of the Department of corner reflectors. In addition, the guide container 8 with a corner reflector 4 is separated from the space vehicle 10 in the direction of the radar 11 or away from the radar direction 12 so that the longitudinal axis of the container has been directed along the line of sight 2 calibre the Oh radar (see Fig.7). In addition, exercise spin guide container 8 with a corner reflector 4 around the longitudinal axis of the container 9 or "clockwise" 17 or "counterclockwise" 18 (see Fig). In addition, the angle reflector 4 push (shoot) from the rotating container 8 in the direction of the radar 19 so that the main lobe of the distribution of the scattering angle of the reflector is directed to the calibrated radar (see figure 9, 7), and the maximum of the main lobe of the distribution of the scattering angle of the reflector coincides with the line of sight of the calibrated radar maximum value of deviation of the angle between the maximum of the main lobe of the distribution of the scattering angle of the reflector and the line-of-sight radars in the range from -10° to +10°. In addition, ask the circular frequency of the spin ω (rotation) of the container with a corner reflector in accordance with condition: ω>12Fradarπa/λ, where Fradarthe pulse frequency of the radiation transmitter calibrated radar; a is the radius of paludica the verge of a corner reflector; λ - wavelength calibrated radar. The proposed method is illustrated by drawings presented on figure 2 - Fig. Figure 2 presents angular reflector 4 in the form of two faces of the flat radiotray of palutikof 5 and 6 radiusa. Figure 3 - guide cylinder is static container 8, PP 4, wherein the longitudinal axis of the container 9 is aligned with the bisector of the angle 7 between the faces of the MA in the plane perpendicular to the middle ribs 4 PP. Figure 4 presents the options branch of the PP 4 of 10 KA, where 9 is the longitudinal axis of the guide cylindrical container 8, 2 - line-of-sight calibrated radar, 11 - Department of PP in the direction of the radar, 12 - Department of PP in the direction opposite to the radar direction, 14 - main lobe of the scattering phase function rotating UO 4, 20 - maximum of the main lobe of the scattering phase function rotating 4 PP. Figure 5, 6 - options spin 4 PP. Figure 7 presents the options branch of the rotating guide cylindrical container 8 in the direction of the radar 11 or away from the radar direction 12, where 4 is the angle reflector, 2 - line-of-sight radar, 14 - main lobe of the scattering phase function rotating UO 4, 20 - maximum of the main lobe of the scattering phase function rotating 4 PP. On Fig presents ways to twist the guide cylindrical container. Figure 9 shows ejection (ejection) PP 4 (while maintaining the rotation UO) of the rotating guide cylindrical container 8 in the direction of the radar station 19. Figure 10 shows the maximum permissible deviation of the maximum of the main lobe of the scattering phase function 20 rotating UO 4 from the line of sight 2 calibrated radar 4 (-10° to +1°). Figure 11 presents the calibration graph of the values of the amplitudes of the signal Ai at the output of the radar receivers on the relative values of power Bi signal at the input of the radar receivers. On Fig presents the scheme of carrying out of session of measurements (calibration RLS), where 2 - line-of-sight calibrated radar 3, 20 - maximum of the main lobe of the scattering phase function 20 rotating UO 4, item 21 - position PP 4 at the time corresponding to the beginning of the session measurements (calibration RLS), and the position 22 to position PP 4, corresponding to the time the session ends of measurements (calibration RLS). On Fig given angular reflector, made in the form of two faces of the flat radiotray of palutikof deployed at a fixed angle in the range of (90-Δ)° - (90+Δ)°, where Δ is determined from the relationship: 0<Δ<18λ/a, λ - wavelength calibrated radar; a is the radius of paludica the verge of corner reflectors, rotating around the bisector of the angle between the faces of the PP in the plane perpendicular to the middle ribs PP. On Fig presents-sectional planes XOY and XOZ of the main lobe of the spatial distribution of the scattering angle of the reflector depicted in Fig. For comparison presents: Fig angular reflector, made in the form of two faces of the flat radiotray of palutikof right angle between the faces in a static state (stationary); on Fig sectional planes XOY and XOZ of the main lobe of the spatial distribution of the scattering static (fixed) angular reflector, made in the form of two faces of the flat radiotray of palutikof right angle between faces. The proposed method is implemented as follows. On Board the SPACECRAFT 10 is placed is installed in the container 8 angular reflector 4 (see figure 4). In memory of the onboard computer of the spacecraft enter the data on the coordinates of the calibrated radar in the geodetic coordinate system. In addition, in the memory of the onboard computer enter the data on the coordinates installation and spatial orientation (position) of the longitudinal axis of the guide container 8 in the associated coordinate system of the spacecraft, as well as information about the direction of the Department (the velocity vector 11 or 12) corner reflector 4 from the space vehicle 10 (see figure 4). Using receivers, navigation systems such as GLONASS and/or GPS and on-Board computers make the determination of the position of the center of mass of the spacecraft relative to the location of the calibrated radar. Using on-Board computers KA calculate and determine the spatial position of the longitudinal axis of the guide container relative to the line of sight calibrated the radar at the current time. Estimated on-Board computer system with the orientation of the spacecraft carry out the combination of the longitudinal axis of the guide 9 of the container 8 with the sight line 2 calibrated radar. With their combination signal generated on-Board computing machine spacecraft angular reflector 4 is separated from the space vehicle 10 along the sight line 2 in the direction of the radar 11 or away from the radar direction 12. Department of PP produced so that the main lobe of the scattering phase function 14 corner reflector 4 is directed to the calibrated radar (see figure 4), and the maximum of the main lobe of the scattering phase function 20 corner reflectors 4 coincides with the line of sight 2 calibrated radar 4 maximum value of deviation of the angle between the maximum of the main lobe of the scattering phase function UO and line-of-sight radars in the range from -10° to +10° (see figure 10). Optional corner reflector 4 is attached to a rotational movement around an axis coincident with the bisector of the angle 7 between the faces of corner reflector in the plane perpendicular to the middle edge corner reflectors (see figure 5, 6). Rotation (spin) PP can be done either in the direction "clockwise" 15, or against "clockwise" 16 (see figure 5, 6). Before the session maintenance is, or at the time of the meeting calibrate receivers radar one of the known methods for the calibration of radio engineering devices, [1], str; [5], using a calibrated generator connected to the high frequency input receivers, radar [2]. Register dependence of the values of the amplitudes of the signal at the output of the radar receivers from the relative values of signal power at the input of the receivers, radar and get the calibration graph (see 11). Session measurements (calibration RLS) begin after the AC and UO will go a greater distance range resolution calibrated radar. Irradiated UO signals calibrated radar, receive reflected signals from UO, and record the amplitude of the reflected signals from UO and measure them at the time interval ΔT: ΔT=t2-t1, where t1- the session start time measurement (calibration RLS); t2- the end time of the session measurements (calibration RLS). Moreover, ΔT can take values in the range from 10 to 600 seconds (item 21 is the position of the PP in the time t1and position 22 is the position PP at a later time t2(see Fig). Then a calibration curve according to the values of the amplitudes of the signal at the output of the radar receivers from the relative values of signal power at the input of the radar receivers are converted to values relative power (signal/noise) of the reflected signals from PP using known formulas interpolation [6], p.14-19. With p the power of the calibrated radar measured slant range to UO. The value of the relative power of the signal reflected from the PP count (lead) to a fixed range, for example 100 km, according to the formula: Pi=Bi+40LogRi/100, where Bi is the unit of the measured value of the relative power of the reflected signal; Ri is the unit of the measured value range of the calibrated radar to the reflector, corresponding to Bi. "Reduced" to a fixed range of values of the relative power of the reflected signals from corner reflectors are average by the formula:
where n - number of results of single measurements on the time interval ΔT. The obtained average value of Pcpuse when measuring the EPR ballistic and space objects as the value of the relative power of the reflected signals corresponding to the reference value of the EPR angular reflector. The use of corner reflectors are made in the form of two faces of the flat radiotray of palutikof, and the setting values of the angle between the faces in the range of (90-Δ)° - (90+Δ)° allow to achieve a "flattening" of the shape of the main lobe of the scattering phase function UO in the horizontal plane. Thus, the sector angles of light scattering indicatrix PP in the horizontal plane, in which the EPR is practically unchanged, reaches ±10°, [3], str, RES, curves 2, 3. Thus Δ is allocated from the relation: 0<Δ<18λ/a, where λ is wavelength calibrated radar; a is the radius of paludica the verge of corner reflectors. The use of rotating corner cube reflector around an axis coincident with the bisector of the angle between the faces of the PP in the plane perpendicular to the middle ribs PP, allows you to keep the orientation of the main lobe of the scattering phase function and to provide a constant value of EPR corner reflector in the direction of the radar during the whole session parameters (session calibration radar largest EPR). The application of the twist angle of the reflector 4 with a circular frequency ω>12Fradarπa/λ, where Fradarthe pulse frequency of the radiation transmitter calibrated radar; a is the radius of paludica the verge of a corner reflector; λ - wavelength calibrated radar, allows to obtain an effective reflector with a relatively wide scattering indicatrix 18, not less than 30° at - 3dB (assuming 2πa/λ>>1 and "flattened" shape of the main lobe of the scattering phase function in two planes - vertical and horizontal (see Fig, 14). Moreover, the width of the main lobe of the scattering phase function of the rotating angle of a reflector around an axis coincident with the bisector of the angle between the faces in the plane perpendicular to the mid-rib of the MA in vertical and horizontal planes, - the same who and and thus equal to the width of the main lobe of the scattering phase function static (fixed) corner reflector in the horizontal plane 24 (see Fig, 16). Thus, the azimuth of the main lobe of the scattering phase function UO, in which the EPR is practically unchanged and in vertical and horizontal planes, up to 20° (±10°) (see Fig)that can significantly increase the time interval of the calibration session. Carrying out conversion values relative power to the standard range eliminates the dependence of the performed measurements from changes in the distance between the radar and PP during the session parameters (session calibration radar largest EPR). The resulting aggregation of single measurements Pcpessentially the exact singular values of Pi, namely, the random error will decrease to Small volume occupied by the container with a corner reflector, when calibrating the radar in the centimeter and millimeter wavelength ranges can be installed on the SPACECRAFT to the desired number and calibrate the radar as necessary (see figure 4, 7). From the above it follows that the proposed technical solutions have advantages compared with the known methods of calibration of the radar, as it will help to improve the accuracy of the calibration of the radar largest EPR when performing dynamic measurements the EPR ballistics the x and space objects. For application materials, the company has conducted modeling of radar calibration when performing dynamic measurements EPR upholding the achievement of the above-mentioned technical result. Sources of information 1. Entisols, Vahtangovu, edited by Mahlasela, Measurement of scattering characteristics of radar targets, M.: Soviet radio, 1972, p.19-20, str-145, str-179, str-194, str-213. 2. Olin (I.D.Olin), Dynamic measurement of radar cross-sections, TIER, 1965, t, No. 8. 3. Wohlbach, edited by Oneandthesame, Radar reflectors, M.: Soviet radio, 1975, str, 144, 146, 150, 152, 235. 4. Aeiou, Saiano, Favona and others, edited by A.I. Leonov, Testing radars, M.: Radio and communication, 1990, p.37, p.51. 5. Verification of measuring instruments. The collection of instructions, edition of the official. Standarts, 1961. 6. Njohnson, Flin, Statistics and experimental design in engineering and science. Methods of data processing, M.: Mir, 1980, p.14-19. 7. Mckanic, edited by Aschobi, Handbook of radar, T.1, M.: Soviet radio, 1976, str-397. 1. A method of calibrating the radar largest effective surface scattering when performing dynamic measurements of the effective surface scattering of the studied objects, according to cat the rum into Earth orbit launch reflector with a known value of the effective surface scattering, irradiate its signals calibrated radar station, take the reflected signal from reflector located in the far zone of the antenna of the radar to measure the amplitude reflected from the reflector signals, characterized in that orbit around the Earth aboard the spacecraft is transported as a reference effective surface scattering angular reflector, made in the form of two faces of the flat radiotray of palutikof deployed at a fixed angle in the range of (90-Δ)° - (90+Δ)°, where Δ is determined from the relation: 2. The method according to claim 1, characterized in that the separation and spin or rotation angle of the reflector is produced at the same time. 3. The method according to claim 1, characterized in that the twist or rotation angle of the reflector to produce its separation from the spacecraft. 4. The method according to claim 1, characterized in that the set frequency of the spin or rotation angle ω of the reflector in accordance with condition: 5. The method according to claim 1, characterized in that by using calibrated radar measured slant range to the corner cube reflector. 6. The method according to claim 1, characterized in that the value of the relative power reflected from the corner cube reflector signals lead to a fixed range, for example 100 km, through allocation by the formula: 7. The method according to claim 1, characterized in that preveden the e to a fixed range of unit values relative power reflected from the corner cube reflector signal average by the formula: 8. The method according to claim 7, characterized in that the average value of Pcfused as the value of the relative power of the reflected signals corresponding to the reference value of the effective surface scattering angle of the reflector. 9. The method according to claim 2 and 3, characterized in that the twist or rotation of the corner reflectors are carried out either "clockwise"or "counterclockwise" direction of the Department of corner reflectors. 10. The method according to claim 1, characterized in that you are doing the twist or rotation of the guide container with corner reflector around an axis of the container in either "clockwise"or "counterclockwise". 11. The method according to claim 10, wherein the corner cube reflector is separated from the space vehicle by pushing or firing of the rotating container in the direction of the radar so that the main lobe of the distribution of the scattering angle of the reflector is directed to the calibrated radar station, and the maximum of the main lobe of the distribution of the scattering angle of the reflector coincides with the line of sight of the calibrated radar station with the maximum permissible value of the deviation angle between the Maxi is the mind of the main lobe of the distribution of the scattering angle of the reflector and the line-of-sight radars in the range from -10° to +10°. 12. The method according to claim 10, wherein the set of circular frequency of the spin or rotation ω of the container with a corner reflector in accordance with condition:
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