RU2750133C1 - Method for measuring the level of radio observability and apparatus for implementation thereof - Google Patents

Abstract

FIELD: measuring.SUBSTANCE: group of inventions relates to means for measuring the level of radio observability. Substance: useful signals from navigation spacecrafts (NS) emitting navigation signals are detected from one or more deployed global navigation satellite systems. Three-dimensional registration of the signal reception point is performed. The approximate parameters of the orbit and the coordinates of the NS are determined based on almanacs. Criterial selection of the NS is performed. The value of the elevation coordinate of the selected NS relative to the reception point is determined based on ephemerides. The NS signal amplitude is calculated. The dependence of the calculated signal amplitude on the elevation coordinate is plotted. Compliance with the condition of reaching the maximum coordinates of the NS is verified. The level of radio observability is calculated on the based on the plotted dependence of the signal amplitude on the elevation coordinate. The apparatus for measuring the level of radio observability is comprised of an antenna (A) and a receiver (1) for receiving signals from navigation spacecrafts of a global navigation satellite system, a navigation and computing unit (2) for measuring the amplitude and relative positioning of the navigation spacecrafts and the receiver, a computing and recording unit (3) for calculating the level of radio observability. A navigation spacecraft from the deployed global navigation satellite system is used as the signal source. Search and detection of the navigation signal, three-dimensional registration of the reception point, processing of almanacs, criterial selection of navigation spacecrafts, processing of ephemerides and signal amplitude of the navigation spacecrafts, tracking of the navigation spacecrafts and issuance of the relative coordinates of the navigation spacecrafts and the signal amplitude to the computing and recording unit (3) are conducted in the navigation and computing unit (2).EFFECT: simplification of tools for measuring the level of radio observability.3 cl, 4 dwg

Description

The invention relates to radio engineering, namely to applied issues of operation of radio equipment (RTS), and can be used to measure the levels of radio engineering, radar and radio communication observability, respectively - radio engineering, radar and radio communication means of sea (ship) and shore-based, as well as studies of the refractive parameters of the troposphere.

The essence of the invention lies in the fact that in the known method of implementing the interference method for assessing the level of radio observability (consisting of a microwave signal source, antenna, receiver, navigation system and computational and recording unit), the carrier, the microwave signal source and the navigation system are excluded, and as a carrier and The source of the microwave signal is incidentally used by a navigation spacecraft (NSA) from the existing global navigation satellite system (GNSS), which emits navigation signals. A device for measuring the level of radio observability, consisting of an antenna, a receiver, a navigation-computing unit and a computing-registration unit of FIG. 1. Moreover, the navigation-computing unit searches for and detects the signal, three-dimensional fixation, processing of almanacs, criterion selection of the satellite, processing the ephemeris and the signal amplitude of the satellite, tracking the satellite with the issuance of the relative coordinates of the satellite and the signal amplitude to the computational and registration unit.

The technical result of using the invention is to simplify the method and structural design of the device, to reduce operating costs.

Under radio observability (hereinafter - RN) it is customary to understand the value of the ratio of the actual operating range in specific conditions to the formal operating range of a radio equipment, usually expressed in points. In the general case, of a number of external factors influencing the launch vehicle, the decisive factor is atmospheric, and specifically for land-based (sea, coastal) radio-technical means (RTS) - tropospheric refraction [1]. To take into account refraction, one of the following parameters of the propagation medium (troposphere) can be used: the equivalent radius of the earth, the gradient of the refractive index, the ratio of the radius of curvature of the beam to the radius of the earth. The listed parameters are uniquely related to each other and the type of refraction, so they can be used to assess the pH level [2, p.264].

Known model-meteorological methods [3, p.99] for measuring the effective radius of the earth, and hence the level of the launch vehicle, based on ground (surface) measurements of the primary parameters of the atmosphere (humidity, temperature and pressure) using appropriate sensors. Next, the calculation method determines the value of the refractive index at the earth's surface, on the basis of which, using known models of the atmosphere (for example, linear, exponential, biexponential, Hopfield and other models for interpolating the altitude profile of the atmosphere), the vertical profile of the refractive index is restored and the effective radius of the earth is calculated, which means and the pH level.

The disadvantages of this method and the ways of its implementation are:

The RN assessment is carried out at a specific geographic point - the point of measurement of atmospheric parameters. Thus, there is no possibility of assessing the launch vehicle in the directions of the wave propagation path.

The used models of the atmosphere may not coincide with the real state of the atmosphere, which causes an error in the measurement of the RN. In particular, the models do not take into account the complex nature of the vertical profile of the refractive index, for example, the presence of raised and surface waveguides.

The known method of radioacoustic sounding of the atmosphere [4] in which an acoustic pulse packet is emitted, which is irradiated with electromagnetic pulses. From the phase difference and frequencies of the Doppler displacements of electromagnetic pulses, the altitude profile of humidity and temperature is determined, and the altitude profile of the refractive index is also calculated. Based on the refractive index, the pH level is found.

The disadvantage of this method is that the measurement of the RN level is carried out at a specific geographic point - the point where radioacoustic sounding of the atmosphere is carried out. Thus, there is no possibility of measuring the level of the carrier in the directions of the wave propagation path.

The known method of gradient meteorological measurements (the so-called methods of sounding [5, 6]) and methods of its implementation [7 ... 13]. The method is based on direct measurements of the altitude profiles of the primary parameters of the atmosphere (humidity, temperature and pressure) using appropriate meteorological sensors. Further, on the basis of the measured altitude profiles, the refractive parameters of the atmosphere are reconstructed by the calculation method and the level of the launch vehicle is calculated. At the same time, according to the type of sensor carrier, methods are distinguished: balloon, rocket and aviation (using aircraft, helicopters and UAVs) sounding, as well as sounding using a stationary mechanical lift. If there is a transceiver on board the carrier for radio transmission of signals from sensors to a ground processing point, this type of sounding is called radio sounding. In contrast to the model-meteorological method, the altitude profile of the atmospheric parameters is directly measured, and not interpolated on the basis of one of the atmospheric models.

The disadvantage of this method and the ways of its implementation is:

Sounding (and hence the LV assessment) is carried out in a specific geographic zone, limited by the autonomy (flight time) of the carrier, as well as by the range of radio communication (during radio sounding).

Due to the uncontrolled flight with aerostatic and rocket sounding, there is a limited opportunity for the number of readings of the altitude profile. This limits the ability to measure the LV in the directions of the wave propagation path that do not coincide with the sounding area.

During airborne sounding in the area where the carrier is located, the air is disturbed by the carrier's engines, which introduces an error when restoring the altitude profile of the metrological parameters.

In the case of balloon and rocket sensing, due to the effect of wind disturbances on the carrier, an error arises in determining the altitude profiles of the atmospheric parameters, and hence the launch vehicle.

When sounding with the help of a mechanical lift, sounding is carried out at one geographical point of the location of this lift. Thus, there is no possibility of measuring the RN in different azimuthal directions of the wave propagation path.

A common disadvantage of the method of gradient meteorological measurements is the inertia of meteorological sensors, and, consequently, a significant time of sounding during the flight or moving the sensors.

The need for an infrastructure for the operation of sensor carriers, which limits the possibilities of implementing the methods, in particular, for assessing the launch vehicle of sea (ship) radars. For example, the operation of aircraft carriers requires runways (sites), as well as infrastructure for storage and maintenance.

A known method for determining the average values of the refractive index of air (and hence the level of the PH), angles of lateral and vertical refraction and a device for its implementation [14]. The essence of the method lies in the fact that the determination of the averaged values of the gradient of the refractive index of air is carried out on the basis of measurements of the vertical component of the fluctuation of the angle of arrival of laser radiation in the focal plane of the receiving lens. To implement the method, you need a transceiving laser device with the ability to fix the angle of arrival of the laser beam, and the so-called. “Target” - a specialized object or device (lens) with a high reflectance, stationary on the propagation path.

The disadvantages of this method are:

High weather dependence of the method on atmospheric precipitation associated with the use of laser radiation.

The use of a specialized device (the so-called "target") limits the possibility of measuring the LV in different azimuthal directions of the wave propagation path, i.e. PH level measurement is possible only in the azimuthal direction of the “target” location.

The method is intended primarily for geodetic measurements [14]. High values of absorption and scattering of laser radiation in atmospheric gases limit the range, and hence the ability to assess the launch vehicle in the directions of the wave propagation path.

Known radiometric method [5] (and methods of its implementation) in which an experimental study of radio-thermal (radio brightness) radiation of the atmosphere-sea system is carried out. The method is based on measurements of the elevation profile of the radio brightness temperature, on the basis of which the refractive index is reconstructed by the calculation method, and therefore the level of the PH is measured. In the methods for implementing this method, a specialized station for receiving thermal radio radiation and an antenna are used, which, in the general case, has the ability to navigate in the azimuthal plane, and therefore estimate the level of the launch vehicle on propagation paths in any azimuthal direction. The advantage of this method is the promptness of measurements due to the lack of use of sensors for atmospheric parameters and their carriers.

The disadvantage of this method and the ways of its implementation is:

Large error of the method associated with the blurring of the radio-brightness-temperature boundary of the atmosphere-sea environments due to the agitation of the sea surface.

The need for radio-thermal receiving equipment and an antenna of considerable size: for example, in [5, p.113], the method is implemented using a parabolic antenna with dimensions of about 3 m), which limits the possibilities of implementing the method for assessing the launch vehicle of shipborne radars.

Sea roughness leads to the rocking of the ship, and hence the antenna, leading to instability of its orientation, which leads to an error in the measurement results of the elevation profile of the radio brightness temperature for ship-based means.

There is a known method for assessing the level of refraction (and methods of its implementation) by the amount of attenuation in the diffraction zone [5], in the implementation of which the amplitude of the microwave signal emitted by a specialized source referred to the diffraction zone is measured. In addition to the equipment itself for receiving the signal, for the implementation of this method, information is needed about the current position of the microwave signal source in space (in particular, the range and height), and the source itself must move in a certain way - along a given trajectory horizontally. As a result of moving the source, the equipment fixes the amplitude of the received signal and restores the diffraction dependence of the signal amplitude on the range. On the basis of this dependence, the refractive index is reconstructed by the calculation method, and hence the pH level. Due to the use of a specialized microwave signal source, rather than a radio-thermal background of natural origin (as in the radiometric method), the influence of the underlying surface on the measurement results is excluded.

The disadvantage of this method and the ways of its implementation is

The need for a specialized microwave signal source and its carrier.

The need for equipment for recording information about the position of the microwave signal source or equipment for transmitting this information to the ground.

The need for an infrastructure for the operation of launch vehicles, which limits the possibilities of implementing methods for assessing the launch vehicle, for example, a shipborne radar.

High measurement error, determined by a limited number of measurements due to the small length of the refractive zone in the microwave range.

High measurement error due to the strong influence on the result of the linear attenuation of the microwave signal in the troposphere.

Known interference method for assessing the level of refraction [5], and hence the level of RN (and methods of its implementation), based on the analysis of the spatial distribution of the interference field. When implementing the method, the amplitude of the microwave signal (receiver) emitted by a specialized source referred to the interference zone is estimated. Moreover, the source and receiver of the signal can be swapped depending on the ease of implementation and practical considerations, which does not affect the result. To implement the method, information about the current position of the microwave signal source in space is required, and the source itself must move accordingly - along a given trajectory. As a result of the movement of the source, ground-based equipment fixes the amplitude of the received signal and restores the interference dependence. On the basis of these dependencies, the refractive index, and hence the pH level, is reconstructed by the calculation method. Moreover, in contrast to the method for assessing the level of refraction by the amount of attenuation in the diffraction zone, it is not the dependence of the linear attenuation on the range that is evaluated, but the spatial shape of the interference lobes (maxima or minima), and thus the error in measuring the PH level due to the weakening of the microwave signal in the atmosphere is eliminated.

The methods for implementing the method differ in the type of media. The carrier is either an aircraft carrier (aircraft, helicopter, UAV), or a stationary device mounted on the earth's surface, providing vertical movement of the source. In particular, in [5, p.121] the implementation of the method is given, in which the carrier is a stationary telescopic mast, with the ability to move the receiver antenna in a vertical plane, located at a distance of 7.7 km. The methods for implementing the method based on a stationary carrier have the following disadvantages:

Inability to measure the PH level in directions other than the direction to the stationary carrier.

The length of the LV level measurement in the direction of the track is limited by the stationary location of the carrier.

The height at which it is possible to carry out the analysis of the interference field is limited by the design height, mechanical strength and the ability to withstand wind loads of the stationary carrier. This reduces the quality of the study of the interference field, and therefore leads to an error in determining the level of the RN.

Inapplicability in sea and coastal conditions (on sea propagation routes) due to the complexity of the stationary location of the carrier on the sea surface.

The need for a specialized microwave signal source and its carrier.

) от наземного источника 1 (включающего передатчик 2 и антенну А1) регистрируется приемным устройством (состоящим из антенны А2 и приемника 4), установленным на авиационном носителе 3 фиг.2. Информация о текущем положении носителя относительно источника (в частности, текущие дальность

и высота полета

) выдается навигационной системой 5 в вычислительно-регистрационный блок 6 для обработки совместно с текущей величиной амплитуды

. В результате перемещения носителя 3 в направлении трассы распространения в вычислительно-регистрационном блоке 6 фиксируются напряженность интерференционного поля, определяются направления характерных точек (например, минимумов сигнала) и далее, на основании известной высоты полета, определяется эффективный радиус или уровень РН. При необходимости полет осуществляется в ином азимутальном направлении и на любой высоте. В данном способе источник сигнала располагается на поверхности, а приемник на носителе. The closest in technical essence and the achieved result is a method of implementing the interference method for assessing the level of refraction (effective radius, level of the launch vehicle) using an aircraft carrier [5]. When implementing this method, the amplitude of the received radiation (

) from a ground source 1 (including transmitter 2 and antenna A1) is recorded by a receiving device (consisting of antenna A2 and receiver 4) installed on the aircraft carrier 3 of Fig. 2. Information about the current position of the carrier relative to the source (in particular, the current range

and flight altitude

) is issued by the navigation system 5 to the computing and registration unit 6 for processing together with the current amplitude value

... As a result of the movement of the carrier 3 in the direction of the propagation path in the computing and registration unit 6, the intensity of the interference field is fixed, the directions of characteristic points (for example, signal minima) are determined, and then, based on the known flight altitude, the effective radius or level of the launch vehicle is determined. If necessary, the flight is carried out in a different azimuth direction and at any altitude. In this method, the signal source is located on the surface, and the receiver on the carrier.

) и о текущем взаимном расположении источника и приемника (определяемую величинами

,

) необходимо накапливать отдельно (соответственно на земле и на носителе) и далее обрабатывать специальным образом.According to the theorem (principle) of reciprocity, the reciprocal position of the source and receiver of the signal is allowed and does not affect the result. However, in the case of an aircraft carrier, the reverse relative positioning is less convenient from a practical point of view, since in this case, information about the current signal amplitude (

) and on the current relative position of the source and receiver (determined by the quantities

,

) must be accumulated separately (on the ground and on the carrier, respectively) and further processed in a special way.

(на основании которой рассчитывается уровень РН) в вычислительно-регистрационном блоке происходит следующим образом [5, с.120]: в процессе горизонтального полета измеряются дальности

на которых фиксируются

-е интерференционные минимумы сигнала, а затем графическим либо расчетным способом согласно (1) определяется величина эквивалентного радиуса земли

. На основании найденной величины

вычисляется искомое значение РН.Calculating the effective radius

(on the basis of which the level of the launch vehicle is calculated) in the computational and registration unit occurs as follows [5, p.120]: in the course of horizontal flight, the ranges are measured

on which the

-th interference minima of the signal, and then graphically or by calculation according to (1) the value of the equivalent earth radius is determined

... Based on the found value

the required pH value is calculated.

, (

=1, 2,…), где (1)

, (

= 1, 2, ...), where (1)

и

- высоты расположения корреспондирующих пунктов: антенны наземного источника и авиационного носителя соответственно,

and

- the heights of the location of the corresponding points: the antennas of the ground source and the aircraft carrier, respectively,

- длина волны источника сигнала,

- the wavelength of the signal source,

учитывает влияние рефракции, задается графически в [16] или [17, с.102], причем:The first factor of expression (1) is an interference factor and is a direct consequence of the simplified formula of Vvedensky [15], the second is

takes into account the influence of refraction, is set graphically in [16] or [17, p.102], and:

, где

- расстояние между приёмником и передатчиком;

where

- distance between receiver and transmitter;

.

...

по (1) анализу подвергаются несколько первых интерференционных минимумов, т. е.

=1…3. Refractive phenomena in the troposphere have an effective influence on several (usually up to 3) first interference lobes. Therefore, in the process of calculating the quantity

according to (1), several first interference minima are analyzed, i.e.

= 1 ... 3.

This method was adopted as a prototype.

The main disadvantages of the prototype are:

The need for a specialized microwave signal source and its carrier.

The need for an infrastructure for the operation of launch vehicles, which limits the possibilities of implementing methods for assessing the launch vehicle, for example, for shipborne radars.

The aim (technical result) of the invention is to simplify the method and structure of the device for measuring the PH level, as well as to reduce operating costs when implementing the method.

The goal (technical result) is achieved by the fact that a navigation spacecraft (NSA) from the deployed (operating) GNSS constellation [18, 19, 20], which emits navigation signals in the microwave range, is used as a specialized source and its carrier. Moreover, information about the coordinate of the satellite is generated based on the processing of the navigation signal. This eliminates the need for a signal source, a carrier and infrastructure for its operation, as well as equipment providing information about the position of the carrier (source). The absence of a specialized signal source and its carrier, as well as the absence of the need for infrastructure for the operation of the carrier, reduces the costs of operating and implementing the device.

The method and the device are united by a single inventive concept based on the general principle of performing measurements and the general principle of calculating the measured value.

The essence of the invention and the principle of operation is illustrated by the drawing Fig. 1, which shows a block diagram of a device for implementing a method for measuring the level of the PH.

и угле места

сопровождаемого спутника HKA_i из состава группировки 4. Далее на основе данной информации в вычислительно-регистрационном блоке 3 фиксируется зависимость

, на основании которой вычисляется уровень РН.The device consists of a receiving antenna A, receiver 1, navigation-computing unit 2 and computing-registration unit 3. The receiving device (consisting of antenna A and receiver 1) receives signals from the satellite from the GNSS space constellation 4. Navigation-computing unit 2 generates digital signals containing amplitude information

and the angle of the place

of the accompanied satellite HKA _i from the constellation 4. Further, on the basis of this information in the computational and registration block 3, the dependence

, on the basis of which the pH level is calculated.

Let us give a rationale explaining the feasibility of the invention, the technical features of the device for its implementation and the algorithm of its operation.

GNSS satellites deployed in orbit are medium-altitude earth satellites, the orbit of which is not stationary. This allows each satellite to be considered as a moving source that moves, including in the interference zone of the receiving device.

Antenna A and receiver 1 of Fig. 1 for receiving signals from the satellite are typical devices of most navigation receivers (navigators), the technical implementation of which is currently trivial.

относительно точки приёма на основе полученных эфемерид. Выходными информационными сигналами навигационно-вычислительного блока являются амплитуда сигнала в точке прима

и угломестная координата НКА

относительно точки приема. Функциональные блоки 1, 2, 3, 5 являются типовыми блоками большинства навигационных приемников (навигаторов), техническая реализация которых тривиальна. Задачи, решаемые функциональными блоками 4 и 6 являются типовыми задачами систем автоматического управления и сбора данных, поэтому также технически реализуемы.The operation algorithm of the navigation-computing unit 2 is illustrated by the block diagram shown in Fig. 3. The signals from the NSA from the output of the receiver are fed to the functional block 1 in which the search, detection and digitization of useful signals is carried out. The digitized signals are sent to functional blocks 2 and 3 in which three-dimensional fixation of the receiving point is carried out (the navigation problem of determining the coordinates of the receiving point is solved) and the processing of almanacs to determine the approximate parameters of the orbit and coordinates of the satellite from the GNSS constellation. Further, on the basis of the known coordinates of the receiving point, as well as the parameters of the orbit and coordinates of the satellite in block 4, a criterial selection of one of the satellite is made. Then, in block 5 for the selected satellite, the exact value of the elevation coordinate is determined

relative to the receiving point based on the received ephemeris. The output information signals of the navigation-computing unit are the signal amplitude at the prima point

and the elevation coordinate of the satellite

relative to the receiving point. Functional blocks 1, 2, 3, 5 are typical blocks of most navigation receivers (navigators), the technical implementation of which is trivial. The tasks solved by functional blocks 4 and 6 are typical tasks of automatic control and data collection systems, therefore, they are also technically feasible.

In the computing and registration unit 3 of FIG. 1, the calculation of the PH level is carried out, the technical feasibility is justified by the mathematical calculations below.

It is known that the field strength from a moving source at the time of radio entry (or radio sunrise) has a complex (interference) structure, determined by the expression [2]:

, где (2)

where (2)

- напряженность сигнала в свободном пространстве (нормирующим множитель);

- signal strength in free space (normalizing factor);

- нормированная диаграмма направленности приемника;

- normalized receiver directional diagram;

- коэффициент, описывающий влияние волнения моря в функции средних квадратических высот морских волн

, волнового числа

и угла скольжения

;

- coefficient describing the influence of sea waves as a function of the rms heights of sea waves

, wave number

and sliding angle

;

- комплексный коэффициент отражения Френеля для морской поверхности;

- complex Fresnel reflectance for the sea surface;

- коэффициент, характеризующий сферическую расходимость волн;

- coefficient characterizing the spherical divergence of waves;

.

...

,

,

,

и их взаимосвязь поясняется на фиг.4 , причем

и

- высоты расположения корреспондирующих пунктов приема и передачи: антенны наземного приемника и носителя (НКА) соответственно. The meaning of quantities

,

,

,

and their relationship is illustrated in figure 4, and

and

- the heights of the location of the corresponding receiving and transmitting points: the antenna of the ground receiver and the carrier (NSA), respectively.

. Путь поводится наблюдение сигнала на входе приемника

. Тогда величина

, соответствующая максимальной степени коррелированности функций

и найденной по (2) функции

, является искомой величиной, на основании которой находится уровень РН.In real conditions, the shape and position of the interference lobes changes depending on the level of refraction, determined by the value

... The path is led observation of the signal at the input of the receiver

... Then the quantity

corresponding to the maximum degree of correlation of functions

and the function found by (2)

, is the desired value, on the basis of which the PH level is found.

, а именно - интерференционных минимумов. В предлагаемом способе, как и в способе-прототипе, дальность на которой фиксируется

-й интерференционный минимум, будет следующей:By analogy with the prototype method, it is possible to find the PH level by identifying characteristic points of dependence

, namely, interference minima. In the proposed method, as in the prototype method, the range at which is fixed

-th interference minimum will be as follows:

, (

=1, 2,…), (3)

, (

= 1, 2, ...), (3)

. В ином случае следует пользоваться дифракционными формулами.This expression is similar to expression (1) and is valid for

... Otherwise, the diffraction formulas should be used.

The computing and registration unit, which calculates the PH level on the basis of the above mathematical expressions, like the similar unit shown in the description of the prototype, can be implemented in a modern microprocessor version or on the basis of an electronic computer.

The operation algorithm of the device for implementing the invention can be as follows:

1. Detection of useful signals from the satellite;

2. Three-dimensional fixation of the signal receiving point;

3. Determination of approximate parameters of the orbit and coordinates of the satellite from the GNSS constellation based on almanacs;

4. Criteria selection of NCA based on the results of items 2..3;

выбранного НКА относительно точки приёма на основе эфемерид;5.Determination of the elevation coordinate value

the selected satellite relative to the receiving point based on ephemeris;

;6. Calculation of the signal amplitude from the NSA

;

на основе данных по пп 5 и 6;7.Fixing (building) dependencies

based on the data on PP 5 and 6;

8. Verification of the condition for reaching the limiting coordinates of the satellite. If the condition is not met, go to step 5;

;9.Calculation of the pH level based on the dependence

;

10. Go to item 3.

Tests of the prototype of the device showed a high degree of correlation (according to [21, 22]) between the results of measuring the level of the launch vehicle and the results of the operation of radio engineering and radar stations.

Due to the influence of a variety of random factors on the results of measuring the pH level, the proposed method is characterized by a certain measurement error. The random component of the LV level measurement error of the proposed method can be minimized by averaging the results of LV level measurements [23] over several satellite spacecraft deployed GNSS. Thus, the error in measuring the pH level is reduced.

Information sources

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Claims (3)

1. A method for measuring the level of radio observability, which consists in detecting useful signals from navigation spacecraft (NSA) emitting navigation signals from one or more deployed global navigation satellite systems, three-dimensional fixation of the signal receiving point, determining the approximate parameters of the orbit and coordinates of the satellite on based on almanacs, criterial selection of the satellite, determining the value of the elevation coordinate of the selected satellite relative to the receiving point based on ephemeris

, calculating the amplitude of the signal from the NSC

, building dependencies

, checking the condition for reaching the limiting coordinates of the satellite, calculating the level of radio observability based on the dependence

... 2. The method according to claim 1, characterized in that in the case of using navigation devices from several global navigation satellite systems, the results of measuring the level of radio observability are averaged. 3. A device for measuring the level of radio observability, containing an antenna and a receiver for receiving signals from navigation spacecraft of the global navigation satellite system, a navigation-computing unit for measuring the amplitude and relative position of navigation spacecraft and a receiver, a computing-registration unit for calculating the level of radio observability, which differs by the fact that a navigation spacecraft from the deployed (existing) global navigation satellite system is used as a signal source, and the navigation-computing unit searches for and detects the navigation signal, three-dimensional fixation of the receiving point, processing almanacs, criterial selection of navigation spacecraft, processing ephemeris and signal amplitudes of navigation spacecraft, tracking of navigation spacecraft with the issuance of relative coordinates of navigation spacecraft and signal amplitude la in the computing and registration unit.

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