RU2818856C1 - Device for measuring parameters of radio signals of a spatially distributed system of radio transmitters using an unmanned aerial vehicle - Google Patents

Abstract

FIELD: measurement.

SUBSTANCE: invention relates to devices for measuring, using unmanned aerial vehicles (UAV), characteristics of electromagnetic field generated by a set of electromagnetic radiation sources, in particular, it can be used to measure parameters of radio signals of spatially distributed systems (SDS) of radio transmitters (RT), simultaneously emitting at a single operating frequency incoherent special signals with the same spectrum width. Essence of the disclosed solution consists in the fact that the device additionally includes a unit for spatial separation of signals, a unit for calculating directions, control unit and a removable protected machine data carrier; M onboard antennas, M tunable band-pass filters, into which an additional input is introduced, are used; onboard data storage device additionally includes N inputs, M>N, having connections to each other.

EFFECT: providing the possibility of measuring at a given point of the working space not only the total power of the set of all incoherent signals of the RT SDS, but also the amplitudes of each of the incoherent partial signals of RT included in the RT SDS.

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Description

The invention relates to devices for measuring, using unmanned aerial vehicles (UAVs), the characteristics of the electromagnetic field created by a set of sources of electromagnetic radiation, in particular, it can be used to measure the parameters of radio signals from spatially distributed systems (SDS) of radio transmitters (RPD), simultaneously emitting on a single working frequency incoherent special signals with the same spectrum width.

A device for measuring the directional parameters of a transmitting antenna located on a UAV [1] is known, consisting of an on-board antenna, a tunable band-pass filter, a broadband power meter, an on-board GNSS signal receiver, an on-board information storage device, a gyroscopic sensor, a compass sensor, having connections with each other: output the onboard antenna is connected to the input of a tunable bandpass filter, the output of which is connected to the input of a broadband power meter, the output of which is connected to one of the inputs of the onboard storage device, the output of the gyroscopic sensor is connected to another input of the information storage device, the output of the onboard GNSS signal receiver is connected to the third input of the information storage device, The output of the compass sensor is connected to the fourth input of the information storage device, providing:

1) measuring the power level of the received signal on board the UAV using a radio unit consisting of a series-connected receiving antenna, a tunable bandpass filter, pre-configured to transmit a signal with a given carrier frequency and spectrum width, and a broadband power meter;

2) determination of the coordinates of the UAV location and the moment of measurement at a given point on the route using a GNSS receiver, which ensures the reception of not only GNSS signals, but also differential corrections from the control and correction station (KKS) in the interests of increasing the accuracy of coordinate-time determinations;

3) determination of the angular position of the on-board antenna relative to the one under study by measuring the angular orientation of the UAV in space (heading, roll, pitch and yaw angles) using a compass sensor and a gyroscopic sensor;

4) recording the results of measuring the level of the received signal and the results of determining the angular orientation of the UAV in space, linked to the time scale and coordinates of the measurement point using an on-board information storage device for subsequent post-processing (deferred processing after landing of the UAV) using a ground-based information and computing complex.

The disadvantage of this prototype device is impossibility of measuring the amplitude of each of the incoherent partial signals with the same spectrum width created by the RPD from the PRS RPD when they simultaneously operate at a single operating frequency.

The technical result of the invention is to provide the ability to measure at a given point in the working space not only the total power of the aggregate of all incoherent RPD PRS signals, but also the amplitude of each of the incoherent partial RPD signals included in the RPD PRS.

The technical result of the measurements is achieved by the fact that the prototype device additionally includes a spatial signal separation unit, a direction calculation unit, a control unit and a removable secure computer storage medium, M on-board antennas, M tunable bandpass filters are used, into which an additional input is introduced, The on-board information storage device additionally includes N inputs, M>N, having the following connections with each other. A removable secure computer storage medium is connected through connector X1 to the input of the control unit, one output of the control unit is connected to one of the inputs of the spatial signal separation unit, another multi-channel output of the control unit is connected to the multi-channel input of the direction calculation unit, and the third output of the control unit is connected to additional inputs M tunable bandpass filters, the inputs of which are connected to the outputs of the corresponding M onboard antennas, and the outputs of the M tunable bandpass filters are connected to the M inputs of the spatial signal separation block, the output of one of the M tunable bandpass filters is additionally connected to the input of a broadband power meter, one of the inputs of the calculation block directions is connected to the output of the GNSS receiver, its other input is connected to the output of the compass sensor, and its N outputs are connected to N inputs of the spatial signal separation block, N outputs of the spatial signal separation block are connected to N inputs of the on-board information storage device, n=1, 2, …, N.

In this case, the spatial signal separation unit consists of a local oscillator, M frequency converters, M analog-to-digital converters, M quadrature frequency converters, a signal separation unit and N signal amplitude estimators having the following connections with each other. The local oscillator input is one of the inputs of the spatial signal separation block and is connected to one of the outputs of the control unit, the local oscillator output is connected to one of the inputs of each of the M frequency converters, the other inputs of which are M inputs of the spatial signal separation block and are connected to the corresponding outputs of M tunable bandpass filters, the outputs of M frequency converters are connected to the corresponding inputs of M analog-to-digital converters, the M outputs of which are connected to the corresponding inputs of M quadrature frequency converters, the outputs of M quadrature frequency converters are connected to the corresponding M inputs of a signal separation unit, the other N inputs of which are N inputs block of spatial separation of signals and are connected to the corresponding N outputs of the block for calculating directions, and N outputs of the block of signal separation are connected to the corresponding inputs of N devices for estimating the amplitude of signals, the outputs of which are N outputs of the block of spatial separation of signals and are connected to the corresponding N inputs of the on-board information storage device.

The essence of the invention is illustrated by drawings.

In fig. 1 shows a block diagram of a device for measuring the parameters of radio signals of a spatially distributed system of radio transmitters using an unmanned aerial vehicle; Fig. Figure 2 shows a block diagram of the spatial signal separation block.

A device for measuring the parameters of radio signals of a spatially distributed system of radio transmitters using an unmanned aerial vehicle consists of 1 onboard GNSS receiver 1.1, an onboard gyroscopic sensor 1.2, an onboard information storage device 1.3, an onboard compass sensor 1.4, M onboard antennas 1.5.m, m= located on the UAV. 1, 2, … M, M tunable bandpass filters 1.6.m, m=1, 2, … M, broadband power meter 1.7, spatial signal separation unit 1.8, control unit 1.9, removable secure computer storage medium 1.10, and direction calculation unit 1.11, which have the following connections with each other.

The output of the onboard GNSS receiver 1.1 is connected to one of the inputs of the onboard information storage device 1.3 and to one of the inputs of the direction calculation block 1.11. The output of the on-board gyroscopic sensor 1.2 is connected to another input of the on-board information storage device 1.3, the output of the compass sensor 1.4 is connected to the third input of the on-board information storage unit 1.3 and to another input of the direction calculation unit 1.11.

Removable secure computer storage medium 1.10 is connected via connector X1 to the input of the control unit 1.9, one output of the control unit 1.9 is connected to one of the inputs of the spatial signal separation unit 1.8, the multi-channel output of the control unit 1.9 is connected to the multi-channel input of the direction calculation unit 1.11, and the third output of the block control 1.9 is connected to additional inputs M of tunable bandpass filters 1.6.m.

The outputs of the M onboard antennas 1.5.m are connected to other inputs of the corresponding M tunable bandpass filters 1.6.m. The outputs of the M tunable bandpass filters 1.6.m are connected to the M inputs of the spatial signal separation unit 1.8. In this case, the output of one of the M tunable bandpass filters 1.6.m is additionally connected to the input of the broadband power meter 1.7.

N outputs of the direction calculation block 1.11, n=1, 2, …, N, are connected to the corresponding N inputs of the spatial signal separation block 1.8, and N outputs of the spatial signal separation block 1.8 are connected to the corresponding N inputs of the on-board information storage device 1.3.

In this case, the spatial signal separation block 1.8 consists of a local oscillator 1.8.1, M frequency converters 1.8.2.m, m=1, 2, … M, M analog-to-digital converters 1.8.3.m, m=1, 2, … M, M quadrature frequency converters 1.8.4.m, m=1, 2, … M, signal separation unit 1.8.5 and N signal amplitude estimators 1.8.6.n, n=1, 2, … N, having the following connections between each other. The local oscillator input 1.8.1 is one of the inputs of the spatial signal separation block 1.8 and is connected to one of the outputs of the control block 1.9. The output of the local oscillator 1.8.1 is connected to one of the inputs of each of the M frequency converters 1.8.2.m. Other inputs M of frequency converters 1.8.2.m are M inputs of the spatial signal separation unit 1.8 and are connected to the corresponding outputs of M tunable bandpass filters 1.6.m. The outputs M of the frequency converters 1.8.2.m are connected to the corresponding inputs of the M analog-to-digital converters 1.8.3.m, the M outputs of which are connected to the corresponding inputs of the M quadrature frequency converters 1.8.4.m. The outputs of the M quadrature frequency converters 1.8.4.m are connected to the corresponding M inputs of the signal separation unit 1.8.5. The other N inputs of the signal separation unit 1.8.5 are the N inputs of the spatial signal separation unit 1.8 and are connected to the corresponding N outputs of the direction calculation unit 1.11, and the N outputs of the signal separation unit 1.8.5 are connected to the corresponding inputs of the N signal amplitude estimation devices 1.8.6. n. The outputs of the N devices for estimating the amplitude of the signals 1.8.6.n are the N outputs of the spatial signal separation unit 1.8 and are connected to the corresponding N inputs of the on-board information storage device 1.3.

A device for measuring parameters of radio signals from a spatially distributed system of radio transmitters using an unmanned aerial vehicle operates as follows.

A spatially distributed system of radio transmitters 2, consisting of a set of N radio transmitters 2.n, n = 1, 2, ..., N, with N<M, expediently deployed on the earth's surface and simultaneously emitting incoherent special signals at a single operating frequency f ₀ with the same spectrum width Δf. Each RPD 2.n includes an antenna 2.n.1 and a generator 2.n.2, into which external information about a given carrier frequency f ₀ and the spectral width Δf of the generated signal are entered. In this case, the output of generator 2.n.2 is connected to the input of antenna 2.n.1, from the output of which a special RPD signal 2.n is emitted at an operating frequency f ₀ with a given spectrum width Δf.

Measuring the parameters of radio signals from a spatially distributed system of radio transmitters is carried out as follows.

Before launching the UAV, a secure computer storage medium 1.10 is connected to the control unit 1.9 via connector X1, which contains information about the specified carrier frequency f ₀ and the spectrum width Δf of the received signals, the specified local oscillator frequency f ₀ -f _IF and the coordinates of each RPD 2.n from composition of PRS RPD 2, which enters control unit 1.9. The control unit 1.9 sends information about the given carrier frequency f ₀ and the spectral width Δf of the received signals to the tunable bandpass filters 1.6.m, which adjust the bandpass filters 1.6.m in accordance with the accepted parameters. Control unit 1.9 sends information about the specified local oscillator frequency
f ₀ -f _IF to the local oscillator 1.8.1 of the spatial signal separation block 1.8, and information about the coordinates of each RPD 2.n from the PRS RPD 2 is sent to the direction calculation block 1.11. After this, UAV 1 moves to a given point in the working space of the RPD 2 PRS in accordance with the flight program incorporated in UAV 1.

At a given point of location of the UAV 1, the input M of onboard antennas 1.5.m, orderedly located relative to the construction axis of the UAV 1, receives the electromagnetic field (EMF) of the set of signals from all RPD 2.n, included in the PRS RPD 2, at a single operating frequency f ₀ , with a given spectrum width Δf. In the on-board antennas 1.5.m, the input EMF is converted into the corresponding electrical signals and transmitted to the corresponding M tunable bandpass filters 1.6.m, tuned to a given frequency f ₀ and a given frequency band Δf. At the outputs M of tunable bandpass filters 1.6.m, electrical signals are generated, which represent the combined signal of all RPDs 2.n. The combined signals from the outputs of M tunable bandpass filters 1.6.m are supplied to the M inputs of the spatial signal separation unit 1.8, directly to the inputs of M frequency converters 1.8.2.m.

In addition, the total signal from the output of one tunable bandpass filter 1.6.m is additionally fed to a wideband power meter 1.7. In the broadband power meter 1.7, the total power of a set of signals from all RPD 2.n included in the PRS RPD 2, emitted at a single operating frequency f ₀ , with a given spectrum width Δf, is measured. The results of measuring the total power from the output of the broadband power meter 1.7 are sent to the information storage device 1.3, where they are registered with reference to the time of measurement and the coordinates of a given point in the working space of PRS RPD 2, the values of which are supplied to the information storage device 1.3 from the GNSS receiver 1.1, as well as to the parameters of the angular orientation of the UAV 1 in space, the values of which are supplied to the information storage device 1.3 from the compass sensor 1.4 (heading angle) and from the gyroscopic sensor 1.2 (roll, pitch and yaw angles). High-precision determination of the coordinates of the UAV 1 and the moment of measurement is carried out in the GNSS receiver 1.1 on the basis of navigation signals coming from navigation spacecraft (NSV) 3 GNSS and differential correction signals coming from the control and correction station (CCS) 4.

In the block for calculating directions 1.11, based on information about the coordinates of all RPD 2.n, included in the PRS RPD 2, coming from the control unit 1.9, information about the current exact coordinates of the UAV 1, coming from the GNSS receiver 1.1, and information about the course value of the UAV 1 (the angle between the direction north and the direction of the construction axis of the UAV 1) coming from the compass sensor 1.4, the direction values α _n are calculated for each RPD 2.n, measured from the current location of the UAV 1 relative to the construction axis of the UAV 1. Calculated values of the directions α _n , n = 1, 2, …, N, from the N outputs of the direction calculation block 1.11 go to the N inputs of the spatial signal separation block 1.8, directly to the signal separation block 1.8.5.

In the spatial signal separation block 1.8, the local oscillator 1.8.1, tuned to a given frequency f ₀ -f _inverter according to information from control unit 1.9, generates a reference signal at a given frequency f ₀ -f _inverter and transmits it to the inputs M of frequency converters 1.8.2. m. Other inputs M of frequency converters 1.8.2.m receive aggregate signals from the outputs of M tunable bandpass filters 1.6.m. In M frequency converters 1.8.2.m, the aggregate signals are converted to intermediate frequency f _IF and their further transmission to M corresponding analog-to-digital converters 1.8.3.m.

In analog-to-digital converters 1.8.3.m, signals are sampled and quantized with the formation of digital samples of M aggregate signals at an intermediate frequency. The digital samples of the M aggregate signals obtained in the M analog-to-digital converters 1.8.3.m are transmitted to the corresponding M quadrature frequency converters 1.8.4.m, where the spectrum of the aggregate signals is transferred to the “zero” frequency with the formation of complex digital samples of the M aggregate signals, which then arrive at the M inputs of the signal separation block 1.8.5.

In the signal separation block 1.8.5, as a result of processing M aggregate signals coming from the outputs of M quadrature frequency converters 1.8.4.m, in accordance with the spatial signal separation algorithm [2] using information about the direction value α _n for each RPD 2. n, coming from the direction calculation block 1.11, the signals of the corresponding RPD 2.n, n = 1, 2, ..., N, are separated from the total signals.

Selected RPD 2.n signals from N outputs of the signal separation block 1.8.5 are supplied to the corresponding inputs of N signal amplitude estimators 1.8.6.n, n = 1, 2, …, N, at the N outputs of which the signal amplitude values of each RPD are generated 2.n, n = 1, 2, …, N, arriving at the N inputs of the information storage device 1.3 for their registration with reference to the time of measurement and the coordinates of a given point in the working space of the PRS RPD 2, arriving at the input of the information storage device 1.3 from the output of the GNSS receiver 1.1, as well as to the parameters of the angular orientation of the UAV 1 in space, arriving at the inputs of the information storage device 1.3 from the output of the compass sensor 1.4 (heading angle) and the gyroscopic sensor 1.2 (roll, pitch and yaw angles).

Thus, the proposed device for measuring the parameters of radio signals of a spatially distributed system of radio transmitters using an unmanned aerial vehicle provides the ability to measure at a given point in the working space of a spatially distributed system of radio transmitters not only the total power of the aggregate of all incoherent signals of radio transmitters, but also the amplitude of each of the incoherent partial signals of radio transmitters , included in the spatially distributed system, and their registration with reference to the moment of measurement, the coordinates of a given point in the working space and the parameters of the angular orientation of the UAV 1 in space.

Information sources

1. Patent No. 2626561 Russian Federation, IPC G01R 29/10 (2006.01). Method for measuring antenna directivity parameters using a UAV using the flyby method: No. 2016114365: application. 04/13/2016: publ. 07.28.2017 / Klassen V.I., Levitan B.A., Prosvirkin I.A., Topchiev S.A. – 9 p.: ill. – Text: direct.

2. Patent No. 2722413. Russian Federation, IPC G01S 3/74 (2006.01). Device and method for spatial separation of signals No. 2019132703: application. 10/16/2019: publ. 05.29.2020 / Markin V.G., Shuvaev V.A., Krasov E.M. ; applicant JSC NVP PROTEK. – 14 s. : ill. – Text: direct.

Claims (1)

A device for measuring the parameters of radio signals of a spatially distributed system (SDS) of radio transmitters (RPD) using an unmanned aerial vehicle (UAV), consisting of an on-board antenna, a tunable band-pass filter, a broadband power meter, an on-board GNSS signal receiver, an on-board information storage device, a gyroscopic sensor, a sensor - compass, characterized in that a spatial signal separation unit, a direction calculation unit, a control unit and a removable secure computer storage medium are additionally introduced, M on-board antennas, M tunable bandpass filters are used, into which an additional input is introduced, on-board information storage additionally includes N inputs, M>N, having the following connections between each other: a removable secure computer storage medium is connected to the input of the control unit via connector X1, one output of the control unit is connected to one of the inputs of the spatial signal separation unit, multi-channel output of the control unit connected to the multichannel input of the direction calculation unit, and the third output of the control unit is connected to additional inputs of M tunable bandpass filters, the inputs of which are connected to the outputs of the corresponding M onboard antennas, and the outputs of M tunable bandpass filters are connected to the M inputs of the spatial signal separation unit, the output of one of M tunable bandpass filters are additionally connected to the input of the broadband power meter, one of the inputs of the direction calculation block is connected to the output of the GNSS receiver, its other input is connected to the output of the compass sensor, and its N outputs are connected to the N inputs of the spatial signal separation block, N outputs of the block spatial signal separation are connected to N inputs of the on-board information storage device, n=1, 2, ..., N, while the spatial signal separation unit consists of a local oscillator, M frequency converters, M analog-to-digital converters, M quadrature frequency converters, a signal separation unit and N devices for estimating signal amplitude, having the following connections between each other: the local oscillator input is one of the inputs of the spatial signal separation block and is connected to one of the outputs of the control unit, the local oscillator output is connected to one of the inputs of each of the M frequency converters, whose other inputs are M inputs of the spatial signal separation block and connected to the corresponding outputs of M tunable bandpass filters, the outputs of M frequency converters are connected to the corresponding inputs of M analog-to-digital converters, M outputs of which are connected to the corresponding inputs of M quadrature frequency converters, the outputs of M quadrature frequency converters are connected to the corresponding M inputs of the signal separation block, the other N inputs of which are N inputs of the spatial signal separation block and are connected to the corresponding N outputs of the direction calculation block, and N outputs of the signal separation block are connected to the corresponding inputs of N signal amplitude estimators, the outputs of which are N outputs of the spatial separation block signals and are connected to the corresponding N inputs of the on-board information storage device.