Method of calibrating radar station operating on circularly polarised waves with parallel reception of reflected signals based on value of effective radar cross-section during dynamic measurement of effective radar cross-section of ballistic and space objects |
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IPC classes for russian patent Method of calibrating radar station operating on circularly polarised waves with parallel reception of reflected signals based on value of effective radar cross-section during dynamic measurement of effective radar cross-section of ballistic and space objects (RU 2477496):
                       
 Method of calibrating radar station from effective radar cross-section value during dynamic measurement of effective radar cross-section of analysed objects / 2477495
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.
 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.
 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 booster rocket (BR) with a reference reflector (RR), 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 an altitude higher than 100 km, said AR consisting of two flat radar-reflecting half-discs turned at an angle ranging from (90-Δ)° to (90+Δ)°, where Δ is determined from the ratio 0<Δ<18λ/a, λ being the wavelength of the calibrated radar station. 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. Before separating the AR from the BR, the last stage of the BR with the container is positioned by the BR control system 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 BR 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 RR from the line of sight of the radar station. 13 cl, 21 dwg
The invention relates to the field of radar and can be used when calibrating radar (radar), running on the waves of circular polarization in parallel to the reception of the reflected signals, the magnitude of the effective surface scattering (EPR) when performing dynamic measurements EPR ballistic and space objects [1, str], [2]. 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]. The closest analogue of the invention is the way in which the reference diffuser uses a straight circular cylinder. Such a cylinder is shown on orbit, and it is set to "coveritlive" movement so that its longitudinal axis 1 was oriented perpendicular Lin and sight 2 radar station 3 (see 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, 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 error in the orientation direction, 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 UHF range of the 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 width is and 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 statistical processing of measurement results, which also reduces the accuracy of the calibration of the radar largest EPR. In addition, use of a straight circular cylinder as a reference is not always possible, as this standard has considerable dimensions and weight [4, p.37], which does not allow its transportation to low earth orbit by a passing run, or to run along a ballistic trajectory together with the investigated objects [1, str]. The technical result of the invention is to improve the accuracy to which lipovci radar largest EPR by eliminating errors, due to 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 dynamic measurement of radar scattering characteristics of ballistic and space objects, including: the launch of the reflector with a known value of the EPR with the help of the launch vehicle (LV), 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 operating on the waves of circular polarization in parallel to the reception of the reflected signals, the magnitude of the EPR when performing dynamic measurements of the effective surface scattering ballistic and space objects at a height of more than 100 km with rocket 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) degrees to (90+Δ) C, where Δ is determined from the relationship: 0<Δ<18λ/a, λ - wavelength calibrated radar; ais the radius of paludica the verge of corner reflectors, (see figure 2). Before the launch, the corners of the first reflector 4 is placed in the guide cylindrical container 8, thus the longitudinal axis of the cylindrical container 9 is combined 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). Before separating the UO from the booster through the system control PH for a given program pitch implement software spread (orientation) of the last stage of the launch vehicle 11 with the guide container 8 on the radar to align the longitudinal axis of the container 9, which coincides with the bisector of the angle between the faces of the PP in the plane perpendicular to the mid-rib of the MA, with the sight line 2 calibrated radar. On a signal from the system control PH angular reflector 4 is separated from the last stage of the launch vehicle 11 along the line of sight in the direction of the radar 12 or away from the radar direction 13 so that the main lobe of the scattering phase function 14 PP 4 aims to calibrate the radar 3 (see figure 4, figure 5). Thus the maximum of the main lobe of the scattering phase function UO coincides with the line of sight of the calibrated radar with a 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 degrees to +10 degrees, and perform the spin (rotation) angle reflector around an axis coincident with the bisector of the angle 7 between the faces 4 PP in the plane perpendicular to the mid-rib of the MA (see Fig.6,Fig.7). In addition, the guide container set in the transition compartment last stage booster. In addition, the smart container is oriented in the direction of the radar with the help of the control system and steering engines (thrusters) the last stage of the booster according to the set program pitch. In addition, PP is transported fair start using PH to a height of 100 kilometers along a ballistic trajectory together with the investigated objects when performing dynamic measurements of their EPR. 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 amplitude of the reflected signals from the MA register, and then via 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 the power signal/noise ratio at the input of the radar receivers are converted to values relative power (signal/noise) reflected from the PP signals. In addition, using calibrated radar measure the slant range to Walter. In addition, each value of the relative power of the signal reflected from UO lead (count) to a fixed range, for example 100 km, according to the formula: Pi=Bi+40LogRi/100, where Bi is the unit value of the relative power reflected from the PP signal; Ri is the unit of the measured calibrated radar is the distance to the MA, corresponding to 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 values of the relative power of the reflected signals from the MA average according to the formula:
where n - number of results of single measurements on the time interval ΔT. In addition, the calculated average value of Pcp is used as the value of the relative power of the reflected signals corresponding to the reference value of the EPR angular reflector. In addition, the guide container with a corner reflector mounted on a stabilized platform system platform in three planes with what omashu respective rocket engines, which is the last stage of the rocket. In addition, the stabilized platform is separated from the last stage of the rocket after completing the main engine. In addition, stable platform standalone software provides guidance directing the container to align the longitudinal axis of the container with the line of sight of the calibrated radar. In addition, PP is separated from the stabilized platform. In addition, the signal at the Department of corner reflectors produce and form from the system software guidance stabilized platform. In addition, the separation and spin (rotation) angle of the reflector is produced at the same time. In addition, the spin (rotation) angle of the reflector to produce its separation from the PH or stable platform. In addition, ask the circular frequency of the spin ω (rotation) angle of the reflector in accordance with condition: ω>12Fradarπa/λ, where Fradarthe pulse frequency of the radiation transmitter calibrated radar; ais the radius of paludica the verge of a corner reflector; λ - wavelength calibrated radar. In addition, the spin (rotation) PP 4 are carried out either "clockwise" 15 or "counterclockwise" 16 (see Fig.6, Fig.7). In addition, aiming the second container 8 with PP is separated from the last stage of the launch vehicle or from a stable platform in the direction of the radar 12 (see Fig) or away from the radar direction 13 (see figure 9) so that the longitudinal axis of the container 9 coincides with the line of sight 2 calibrated radar 3. In addition, exercise spin guide container 8 PP 4 around the longitudinal axis of the container 9 or "clockwise" 15 or "counterclockwise" 16 (see figure 10). In addition, the angle reflector 4 push (shoot) from the rotating container 8 in the direction of the radar 17 (see 11) so that the main lobe of the scattering phase function 14 PP 4 aims to calibrate the radar 3 and the maximum of the main lobe of the scattering phase function UO coincides with the line of sight of the calibrated radar with a 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 degrees to +10 degrees. 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; ais the radius of paludica the verge of a corner reflector; λ - wavelength calibrated radar. The proposed method is illustrated by drawings, presented in figure 2-21. Figure 2 presents angular reflector 4 in the form of two faces of the square the ski radiotray of palutikof 5 and 6 radius a. Figure 3 - guide cylindrical 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, figure 5 presents options branch UO 4 from the last stage of the launch vehicle 11, where 9 is the longitudinal axis of the guide cylindrical container 8, 2 - line-of-sight calibrated radar 3, 12 - Department of PP in the direction of the radar, 13 - Department of PP in the direction opposite to the radar direction, 14 - main lobe of the scattering phase function rotating 4 PP. In Fig.6, Fig.7 - options spin 4 PP. On Fig, Fig.9 - options branch of the rotating guide cylindrical container 8 in the direction of the radar 12 or away from the radar direction 13, where 4 - rotating angle reflector, 2 - line-of-sight calibrated radar 3, 14 - main lobe of the scattering phase function rotating 4 PP. Figure 10 presents ways to twist the guide cylindrical container. Figure 11 shows ejection (ejection) PP 4 (while maintaining the rotation UO) of the rotating guide cylindrical container 8 in the direction of the radar 17. On Fig - accommodation guide cylindrical container 8 PP 4 in the transition compartment 18 of the last stage of the launch vehicle 11. On Fig shows the launch with UO to a height of 100 km Fig presents options the Department is of UO 4 in the direction of the radar 12 and away from the radar direction 13, where 14 is the main lobe of the scattering phase function rotating UO 4, 19 - maximum of the main lobe of the scattering phase function rotating 4 PP. On Fig shows the maximum permissible deviation of the maximum of the main lobe of the scattering phase function 19 rotating UO 4 from the line of sight 2 calibrated radar 4 (from -10 degrees to +10 degrees). On Fig 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, 19 - maximum of the main lobe of the scattering phase function rotating UO 4, position 20 - position PP 4 at the time corresponding to the beginning of the session measurements (calibration RLS), and the position of the 21 - 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) degrees to (90+Δ) C, where Δ is determined from the relationship: 0<Δ<18λ/a, λ - wavelength calibrated radar; ais the radius of paludica the verge of corner reflectors, rotating around the bisector of the angle between the faces In the in-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 faces in a static state (stationary); 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 planes with right angles between the faces. The proposed method is implemented as follows. Before starting booster in the transition compartment 18 of the last stage of the launch vehicle 11 post mounted in the guiding container 8 angular reflector 4 (see Fig). In this advance the longitudinal axis of the guide container combine the bisector of the angle between the faces of the PP in the plane perpendicular to the middle ribs PP. To calibrate the radar launch PH with UO to a height of 100 km (see Fig). On a given trajectory of the flight control system PH implement the orientation of the last stage of the launch vehicle with the transitional compartment and guiding the container. Orientationa stage of the launch vehicle 11 do so, to the longitudinal axis of the guide 9 of the container 8, and therefore the bisector of the angle between the faces of the PP in the plane perpendicular to the mid-rib of PP, was directed along the line of sight 2 calibrated radar 3 (see Fig). In the moment of achievement of specified provisions of the last stage of the control system of the PH signal on the branch (emission) PP. Department of EE is carried out or in the direction of the radar 12, or away from the radar direction 13 so that the main lobe of the scattering phase function 14 PP 4 aims to calibrate the radar 3 (see Fig). Additionally, the corner reflector is attached to a rotational movement around the axis 7, which coincides with the bisector of the angle between the faces of corner reflector 4 in the plane perpendicular to the mid-rib of the MA (see Fig.6, Fig.7). Rotation (spin) PP can be done either in a clockwise direction 15 or counterclockwise 16 (see Fig.6, Fig.7). Thus the maximum of the main lobe of the scattering phase function 19 corner reflector 4 is aligned with the sight line 2 calibrated radar 3 and the axis of rotation of the MA (see Fig). Deviation maximum EPR 19 corner reflector 4 from the line of sight 2 calibrated radar 3 should not exceed ±10 degrees, Fig (in the case of a right circular cylinder as standard EPR permissible deviation of line of sight RL is the direction, perpendicular to the axis of a circular cylinder (coinciding with the maximum lobe of the scattering phase function), is less than one degree). Before a session of measurements or during its holding 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 on the relative values of power (signal/noise) of the signal at the input of the receivers, radar and get the calibration graph (see Fig). Session measurements (calibration RLS) begin after the last stage of the launch vehicle, other detachable from the LV objects and PP will go a greater distance range resolution calibrated radar. Irradiated UO signals calibrated radar, receive reflected signals from UO, and record the amplitude Ai 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 20 represents the position of the PP in the time t1and the position 21 is the state the PP at a later time t 2(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 registered amplitudes Ai are converted to values relative power (signal/noise) Bi reflected signals from PP using known formulas of interpolation [6, p.14-19]. Using 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 value of the relative power of the signal reflected from the corner cube reflector; Ri is the unit of the measured value of distance to a corner cube 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 dihedral is polkovogo reflector of two flat radiotray of palutikof and setting values of the angle between the faces in the range of (90-Δ) degrees to (90+Δ) C allows "flattening" of the shape of the main lobe of the distribution of the the PP scattering in the horizontal plane. Thus, the azimuth of the main lobe of the scattering phase function UO in the horizontal plane, in which the EPR is practically unchanged, reaches ±10 degrees [3, str, RES, curves 2, 3]. Thus Δ is determined from the relationship: 0<Δ<18λ/a, where λ is wavelength calibrated radar; ais 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 in the plane perpendicular to the middle edge corner reflector, 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; ais 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, not less than 30 degrees at the level of 3 dB (assuming 2πa/λ>>1), and "flattened" shape of the main lobe of the scattering phase function 22 in the TLD the planes - vertical and horizontal (see Fig, Fig). 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 and equal to the width of the main lobe of the scattering phase function static (fixed) corner reflector in the horizontal plane 23 (see Fig, 21). Thus, the azimuth of the main lobe of the scattering phase function UO, in which the EPR is practically unchanged, and in vertical and in horizontal planes reaches 20° (degrees) (±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 From the above it follows that the proposed technical the definition solutions have advantages compared with the known methods of calibration of the radar. Namely, allow to increase the accuracy of the calibration of radar operating on the waves of circular polarization in parallel to the reception of reflected signals on the magnitude of the EPR when performing dynamic measurements EPR ballistic 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. "Soviet radio", M, 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. "Soviet radio", M, 1975, str, 144, 146, 150, 152, 235. 4. Aeiou, Saiano, Favona and others, edited by A. Leonov. Testing radar. "Radio and communications", M., 1990, p.37. 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. Mir, M., 1980, p.14-19. 7. Mckanic, edited by Aschobi. The reference radar. .1. "Soviet radio", M, 1976, str-397. 1. A method of calibrating the radar stations operating on the waves of circular polarization in parallel to the reception of the reflected signals, the magnitude of the effective surface scattering dynamic measurement of the effective surface scattering ballistic and space objects, according to which with the help of a rocket launch reflector with a known value of the effective surface scattering, is exposed to the signals of the calibrated radar station, take the reflected signal from reflector located in the far zone of the antenna of the radar to measure the amplitude of the reflected signals, wherein a height of more than 100 km with rocket transported as a reference effective surface scattering angular reflector, made in the 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 by the relation: 2. The method according to claim 1, characterized in that the guide container set in the transition compartment last stage booster. 3. The method according to claim 1, characterized in that the guide container is oriented in the direction of the radar station by using a control system and tail motors last stage of the booster, for a given program pitch. 4. The method according to claim 1, characterized in that the angle reflector convey a fair start using rocket to a height of more than 100 km along a ballistic trajectory together with the investigated objects when performing dynamic measurements of their effective surface scattering. 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, by conversion by the formula: 7. The method according to claim 1, wherein the lead is connected 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 at sensible reflector. 9. The method according to claim 1, characterized in that the separation and spin angular reflector produce at the same time. 10. The method according to claim 1, characterized in that the set of circular frequency of the spin or rotation angle ω of the reflector in accordance with condition: 11. The method according to claim 1, characterized in that the twist or rotation of the corner reflectors are carried out either "clockwise"or "counterclockwise". 12. The method according to claim 1, characterized in that exercise spin guide container with corner reflector around the longitudinal axis of the container in either "clockwise"or "counterclockwise". 13. The method according to claim 1, characterized in that the set of circular frequency of the spin or rotation ω of the container with polka the first reflector in accordance with condition:
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