RU2501031C2 - Method for flight inspection of ground-based radio flight support equipment and apparatus for realising said method - Google Patents

Abstract

FIELD: radio engineering, communication.

SUBSTANCE: method for flight inspection of ground-based radio flight support equipment involves using an unmanned aerial vehicle (UAV) as the aircraft, measuring coordinates of the UAV using an optical device and simultaneously during operation of said radio equipment, generating, using onboard receivers, measurement radio navigation signals which are encoded, emitted into space, received on Earth by ground-based devices, decoded, processed together with signals from the output of the optical device; displaying and recording signal processing and measurement results. The invention describes a method and apparatus for flight inspection of output characteristics of localiser, glide-path and marker beacons, azimuth-range beacons and automatic direction finders.

EFFECT: broader functional capabilities and low cost of making flight adjustments and inspections of localiser, glide-path and marker beacons, azimuth-range beacons and automatic direction finders.

7 cl, 7 dwg

Description

FIELD OF THE INVENTION

The invention relates to radio engineering and can be used for flight settings and checks of ground-based means of radio-technical flight support:

- beacon systems (RMS) for instrumental approach of aircraft for landing (PMC7ILS and RMS / SP meter wavelength band, landing beacon group PRMG decimeter wave band), including: directional beacon (CRM), glide path beacon (GRM), marker beacon (MRM) and rangefinder channel in the PRMG;

- radio navigation systems (RNS): azimuth and rangefinder beacons of short-range navigation systems (PMA / VOR, RMD / DME and RSBN);

- automatic direction finders (ARP).

State of the art

Mentioned radio systems to confirm the output characteristics during commissioning, periodically during their operation, and in some special cases are subjected to flight tests. [one. Order of the Ministry of Transport of the Russian Federation (Ministry of Transport of Russia) dated January 18, 2005 N 1 Moscow, On the approval of the Federal Aviation Rules "Flight checks of ground-based radio-technical flight support equipment, aviation telecommunications and light-signaling equipment systems for civil aviation aerodromes", "Rossiyskaya Gazeta" - Federal issue No. 3733 dated March 31, 2005]. At the same time, as a metrological method for checking PMC / ILS, RMS / SP, and PRMG, a method is used that includes ground-based goniometric measurements of the coordinates of the aircraft’s flight path with high precision using optical instruments, and for checking PMA / VOR, RMD / DME and RSBN and ARP uses the pivot point method, i.e. a method that includes determining the coordinates of an aircraft at moments of flight over predetermined points with known geographical coordinates on the earth's surface (landmarks). For the purpose of flight inspections of ground-based radio-technical flight support equipment, a special laboratory laboratory is used, on which measuring receivers and a VHF communication radio station are installed, in the range of which the ATM operates. At the same time, the coordinates of the aircraft are measured by an optical device, and simultaneously, when radio equipment is in operation, they form radio-navigation measuring signals mounted on board the aircraft, process signals from the output of the optical device and measurement signals together, display and record the results of measurements and the results of joint signal processing. The methodology of flight inspections, the scope and frequency are set forth in the aforementioned Federal Aviation Rules. The disadvantage of this method of flight settings and checks is the need to use a specialized laboratory aircraft, which leads to high costs and, accordingly, the high cost of these works, does not allow to quickly monitor the output characteristics of the RMS, RNS and ARP in the period between scheduled inspections, making it inaccessible to conduct scientific - research work and in the educational process.

The first flight test device for directional, glide path, marker, and radio beacons is known, which contains a laboratory laboratory, a course radio beacon signal receiver, a radio beacon signal receiver, an airborne radio range finder signal receiver, a radio beacon marker signal receiver, a barometric altimeter, a trajectory measurement device and a recording device [2. Guidelines for flight testing of ground-based radio beacons instrumental landing system flight control equipment ALK-70. M. GOSNIIGA, 1976, 49 pp.]. The disadvantage of the first device is that its implementation requires an airplane laboratory, which leads to high operational costs of the first device, reduces the efficiency of flight inspections of course, glide, marker, and radio beacons.

A second device for flight verification of azimuthal and rangefinding radionavigation beacons is known, comprising an airplane laboratory, an airborne receiver of signals of the azimuthal channel of a radionavigation beacon, an airborne transceiver of a rangefinding radionavigation beacon, a barometric altimeter, an optical device for determining the instant of flight of an airplane laboratory above landmarks with known geographical coordinates [ 3. Radio beacons of a short-range navigation system. Flight test methods. GOST 26904-86. IPC. Publishing house of standards. 1997] The disadvantage of the second device is that its implementation requires an airplane laboratory, which leads to high operational costs of the first device, reduces the efficiency of flight checks of azimuth and rangefinding radio navigation beacons.

A third flight verification device for automatic direction finders is known, including an aircraft laboratory, an VHF transmitter (a connected VHF radio station), and an optical device for determining the instant of flight of an aircraft laboratory over landmarks with known geographical coordinates.

The disadvantage of the third device is that its implementation requires an airplane laboratory, which leads to high operational costs of the third device, reduces the efficiency of flight inspections of automatic direction finders.

Disclosure of invention

The proposed method of flight verification of ground-based radio-technical flight support solves the problem of increasing the efficiency of inspections of the said means, reducing the costs of performing inspections, and consists in the fact that a remotely piloted aircraft (UAV) is used as an aircraft for flight verification of the said means, it is measured with high accuracy the coordinates of the UAV with an optical device or other high-precision device and at the same time during operation of the said radio equipment form radionavigation measuring signals which are encoded, emitted into free space, received on the Earth by ground-based devices, decoded, processed together with signals from the output of the optical device, and measurements and the results of joint signal processing, displayed on board the aircraft, on-board receivers.

During flight verification of course, glide-path and marker radio beacons, the angular coordinates of UAVs are measured using ground-based trajectory measurement devices. During flight verification of azimuthal and rangefinding radionavigation beacons, a UAV span is provided over predetermined landmarks, the geographical coordinates of which are previously entered in the memory block of the ground device. The radio navigation measuring signals received on board the UAV are encoded and transmitted to Earth, where they are received, decoded and fed to the input of the calculator. At the moments of the flight of the UAV over the landmarks, which are determined by the operator of the UAV using the television transmitting camera installed on board, the operator instructs the memory unit to transmit the geographical coordinates of the corresponding landmarks to the second input of the calculator. When signals are received at both inputs of the calculator, the latter calculates the errors of the radio navigation system and transfers them to the input of the registration device.

During flight testing of automatic direction-finders by the emission of VHF transmitter signals installed onboard an UAV, the direction-finding of an UAV is measured by an automatic direction finder. This information about the bearing of the UAV comes from the ARP through the reader to the first input of the calculator. At the moments of the flight of the UAV over the given landmarks, the operator of the UAV gives a command to the memory unit to transmit the corresponding landmark to the second input of the calculator of geographic coordinates, the calculator calculates the errors of the ARP bearing and transfers them to the registration device.

The proposed first device, designed for flight verification of directional, glidepath and marker radio beacons, includes a UAV and installed onboard UAVs: a receiver signal of a directional radio beacon, a receiver of signals of a glidepath beacon, an onboard transceiver of a radio range finder, a receiver of signals of a marker beacon, a barometric altimeter, an encoding unit and a transmitting device, and on Earth: a receiving device, a decoding unit, a computer with first and second inputs and with first and second outputs, the operator console D A PLA, a trajectory measurement device and a recording device, while onboard the UAV, the outputs of the directional beacon receivers, the glide path beacon, the marker beacon, the receiver output of the radio rangefinder transceiver and the output of the barometric altimeter are connected to the corresponding inputs of the encoding unit, the output of which is connected to the input of the transmitting device; on Earth, the output of the receiving device is connected in series with the decoding unit, the first input of the computer, the first output of which is connected to the input of the UAV operator panel; the output of the trajectory measurement device is connected to the second input of the calculator; the second output of the calculator is connected to the input of the recording device.

The signals emitted by the Raman, timing, radio range finder and MRM are received onboard the UAV by the respective receivers, converted into measuring signals that are fed to the input of the coding unit and then radiated into free space. The signals received on Earth are decoded and transmitted to the first input of the calculator. The second input of the computer receives signals about the angular coordinates of the aircraft. The values of the signal currents from the receiving device and the values of the currents from the device of trajectory measurements using known methods determine the output parameters of the CRM and the timing, determines the compliance of the measured parameters with the requirements of regulatory documents. By the magnitude of the voltage at the output of the MRM receiver, the moment of flight of the aircraft over the marker beacon and its coverage area are determined.

The proposed second device, designed for flight verification of azimuthal and rangefinding radionavigation beacons, includes UAVs and installed onboard UAVs: receiver of azimuthal channel signals of a radio navigation beacon, onboard transceiver of a rangefinding radio navigation beacon, receiver of signals from a satellite navigation system, barometric altimeter, television transmitting camera a coding unit and a transmitting device, and on Earth: a receiving device, a decoding unit, a DPL operator console And with one input and two outputs, a memory block of the geographical coordinates of landmarks with a control input (memory block), a computer, a registration device; while on board the UAV, the output of the receiver of the azimuthal radio navigation beacon, the output of the receiver of the airborne transceiver of the rangefinding radio navigation beacon, the output of the receiver of the signals of the satellite navigation system, the outputs of the transmitting television camera and the barometric altimeter are connected to the corresponding inputs of the encoding unit, the output of which is connected to the input of the transmitting device; and on Earth, the output of the receiving device is connected in series with the decoding unit, the input of the operator’s panel of the UAV, the first output of which is connected to the control input of the memory unit of the geographical coordinates of landmarks, with the first input of the computer, with the registration device. In this case, the second output of the operator panel is connected to the second input of the calculator.

The third device, designed for flight testing of automatic direction finders, includes UAVs installed on board the UAV: a VHF transmitter, a transmitting television camera, a satellite navigation system signal receiver, a barometric altimeter, an encoding unit and a transmitting device and installed on Earth: a receiving device, a unit decoding, operator panel, bearing reader, memory block of geographical coordinates of landmarks, a computer with first and second inputs and outputs, device GUSTs registration; while on board the UAV, the outputs of the transmitting television camera and the barometric altimeter, the output of the satellite navigation system receiver are connected to the corresponding inputs of the encoding unit, the output of which is connected to the input of the transmitting device, and on Earth, the output of the receiving device is connected in series with the input of the decoding unit, the UAV operator panel, a memory unit for the geographical coordinates of landmarks, the first input of the calculator, and the input of the bearing reader is connected to the ATM, and the output is connected to the second direct input of the computer, the output of which is connected to the registration device.

The characteristics of the RNS and ARP are measured at the moments of the flight of the UAV over the reference points - landmarks. Errors in measuring the azimuth (bearing) and the range of the RNS and ARP are calculated by the known geographical coordinates of reference points on the earth's surface, the geographical coordinates of the positions of the antennas of the radio systems and the measured radio navigation coordinates of the UAV in the local coordinate system at the time of its flight over the reference points. A UAV flies along a predetermined route crossing on its way a number of characteristic (reference) points on the earth's surface with known geographical coordinates. The moment of flight of the UAV over the reference point is determined by the operator on a television image of a point on the earth's surface. At this moment, the operator of the UAV gives a command from the operator’s panel to the control input of the memory block about transferring the corresponding landmark to the input of the calculator of geographical coordinates. The radio navigation coordinates of the UAV are received at the second input of the computer, received from the receivers installed on its board - in the case of flight checks of the RNS or from the automatic direction finder - in the case of flight checks of the ARP. Received errors of RNS and ARP are recorded.

The application of the proposed method and devices for its implementation allows to increase the efficiency of inspections, significantly reduce the cost of performing flight settings and inspections of the CRM, Timing and MRM of radio beacon systems (RMS) of instrumental support for aircraft landing, azimuth-rangefinding radio navigation systems (RNS) and automatic direction finders ( ARP).

Reducing the costs of performing flight adjustments and checks makes them available during the development and flight testing of new models of landing systems and radio navigation systems for civil and military aviation, land and sea based, during unscheduled inspections of radio systems in connection with the comments or complaints of military pilots or civil pilots aircraft, when performing research work in the field of radio beacon landing systems for aircraft and radio navigation systems and during student training s and refresher courses for civil and military aviation specialists, the invention is illustrated further by the drawings.

Brief Description of the Drawings

Figure 1 presents a block diagram of a device for performing flight checks of ground-based means of radio flight support.

Figure 2 presents a block diagram of the equipment installed on board the UAV, the first device designed to perform flight checks of the RMS: CRM, timing and MPM.

Figure 3 presents a block diagram of the ground equipment of the first device designed to perform flight checks of the RMS: CRM, Timing and MRM.

Figure 4 presents a block diagram of the equipment installed on board the UAV, the second device designed to perform flight checks of the RNS.

Figure 5 presents a block diagram of the ground equipment of the second device, designed to perform flight checks RNS.

Figure 6 presents a block diagram of the equipment installed on board the UAV, the third device designed to perform flight inspections of the ATM.

Figure 7 presents a block diagram of the ground equipment of the third device, designed to perform flight inspections of the ATM.

The implementation of the invention

To implement the invention, one of the known variants of a remotely piloted aircraft of Russian or foreign manufacturers is used, capable of carrying a payload of more than 10 kg: GRANT (civil aviation television observer), DOZOR, Yamaxa B max, etc. They have a flight range of several tens of kilometers. To implement small-sized, low-energy-intensive units of on-board and ground-based equipment, microprocessors are used that use modern digital signal processing methods. As an example of the implementation of the blocks, the receiver of landing and navigation signals "Analyzer ILS / VOR", produced by the NPO "Radio Engineering Systems", Chelyabinsk, can serve. The mentioned device has a mass of 1.4 kg, the operating time is 6 hours from the built-in rechargeable batteries. It does not cause problems to develop instruments of the same mass and dimensions for receiving signals of the PMC and RSBN of the decimeter range. As a device for measuring angular coordinates, the "Recording Path Device - UTZ", which is in operation, or the more modern automatic trajectory measurement system ASTI can be used.

Turning now to FIG. 1, a block diagram of devices for performing flight checks of radio beacon landing systems, azimuth-rangefinding radio navigation systems and automatic direction finders in accordance with the present invention is presented. The mentioned devices include a remotely piloted aircraft 1, equipment installed on board the UAV, ground equipment.

The following are three devices of the present invention. The first device is designed to perform flight checks of the RMS: CRM, timing, MRM. The second device is designed to perform flight checks RNS.

The third device is designed to perform flight inspections of the ATM.

First device

The first device contains UAVs, equipment installed on board the UAV, and ground equipment.

The equipment installed on board the UAV, is represented by the block diagram in figure 2, contains a receiver signal CRM 4, a receiver signal GRM 5, a transceiver signals a radio range finder 6, a signal receiver marker beacon 7, a barometric altimeter 8, a coding unit 9, a transmitting device 10.

Mentioned blocks are interconnected as follows. The outputs of the receiver of signals KPM 4, the receiver of signals of the timing 5, the receiver of signals of the radio rangefinder 6, the receiver of signals of the MPM 7, barometric altimeter 8 are connected to the corresponding inputs of the coding unit 9, the output of which is connected to the input of the transmitting device 10.

The ground equipment 3 of the aforementioned first device, represented by a block diagram in FIG. 3, comprises a receiving device 11, a decoding unit 12, a calculator 13 with first and second inputs and first and second outputs, a UAV operator console 14, a trajectory measurement device 15, a recording device 16.

In ground equipment 3, the output of the receiving device 11 is connected in series with the decoding unit 12, the first input of the calculator 13, the first output of which is connected to the input of the operator’s panel 14 of the UAV; a trajectory measurement device 15 is connected to the second input of the calculator 13; the second output of the calculator 13 is connected to the input of the recording device 16.

As a UAV, one of the known variants of a remotely controlled unmanned aerial vehicle of Russian or foreign manufacturers is used: GRANT (civil aviation television observer), DOZOR, Yamaxa B max, etc. As a receiver of CRM 4 signals and a timing signal receiver 5 can serve as a receiver of landing and navigation signals "Analyzer ILS / VOR", manufactured by NPO "Radio Engineering Systems", Chelyabinsk. Similar devices can be used to receive signals of the PMC and RSBN decimeter range. As a device for measuring angular coordinates, the "Recording Path Device - UTZ" or the automatic trajectory measurement system ASTI can be used.

The device operates as follows. The operator controls the flight of the UAV from a range of 20 km along the course line while simultaneously carefully maintaining the UAV at a given angle in a vertical plane (on the glide path). In this case, the signals emitted by CRM 4, GRM 5, MPM 7 and the radio range finder 6 are received on board the UAV by the respective receivers. The receiver of signals KPM 4 generates a signal in the form of a current proportional to the angular deviation of the UAV from the plane of the course. The magnitude of this current is also directly proportional to the information parameter (RGM): the difference in modulation depths when working with the CRM of the meter wavelength range or the difference in the earshot coefficient (RRS) when working with the CRM of the decimeter wavelength range. The timing signal receiver 5 generates a signal in the form of a current proportional to the angular deviation of the UAV relative to the glide path plane. The magnitude of this current is also directly proportional to the information parameter of the RGM or cattle. The on-board current of the KRM 4 receiver and the on-board current of the GRM 5 receiver are hereinafter referred to as measuring signals. The measuring signals are fed to the input of the encoding unit 9. In addition, the signals from the receiver of the on-board transceiver of the radio range finder 6, the receiver of the marker beacon 7, and the barometric altimeter 8 are received at the input of the encoding unit 9. These signals are encoded to the input of the transmitting device 10 and then are transmitted free space. The measuring signals received on the Earth and the radio range finder signals are decoded and transmitted to the first input of the calculator 13. The signals about the angular coordinates of the aircraft from the trajectory measurement device are received at the second input of the calculator 13. By the values of the currents of the measuring signals from the receiving devices KPM 4 and GRM 5, the range and the values of the currents from the device trajectory measurements by known methods, the output parameters of the beacons are determined, the compliance of the measured parameters with the requirements of regulatory documents is determined.

During the flight of the UAV over the marker beacon, the marker receiver receives an alert signal, which is encoded and fed to the input of the transmitting device. On Earth, on the basis of the received and decoded signals, the computer determines the range of the MRM on the course and glide path lines.

Radio navigation measuring signals KPM and GRM, signals of the barometric altimeter displayed on the operator’s panel of the UAV are used by the operator to control the UAV.

The main parameters determined by flight measurements along the course channel:

- deviation of the course line from the established position,

- course curvature structure,

- the width of the course sector,

- the steepness of the characteristics of the directional radio beacon,

- asymmetry of the slope of the characteristics of the CRM,

- coverage area

- the dependence of the coefficient of audibility (for equipment PRMG) or the difference of the depth of modulation from the angular deviation,

- component of the vertical polarization of the field. The glide path channel defines:

- deviation of the glide path from the set position,

- the structure of the curvature of the glide path,

- hemisphere boundaries above and below the glide path,

- the steepness of the timing characteristics,

- asymmetry of the steepness of the timing characteristics,

- coverage area

- dependence of cattle or RGM on angular deviation,

- coverage area.

The range channel determines:

- coverage area

- range measurement error.

A barometric altimeter is used to control the height of the span above the MRM.

In another embodiment of the first device, a flashing light-signal emitter is installed on board the UAV, which is switched on by a command from the Earth when the aircraft is not visible enough, as well as when searching for an aircraft in case of emergency landing.

Second device

Now we turn to the second device, designed to perform flight checks of the RNS.

The second device consists of a UAV 1, equipment 2 installed on board an UAV, and ground equipment 3. Equipment 2 installed on board an UAV, represented by the block diagram in figure 4, contains a signal receiver of the azimuth channel 18, a signal receiver of the satellite navigation system 19 , a barometric altimeter 20, a transmitting television camera 21, an information coding unit 22, a transmitting device 23. When conducting flight checks of the RNS as part of PMA / VOR and RMD / RME or RNS RSBN, the corresponding azimuthal channel receivers are used la and onboard transceivers of radio range finders.

The above blocks of the device are interconnected as follows. The outputs of the receiver of the onboard transceiver of the radio ranging beacon 17, the signal receiver of the azimuth beacon 18, the signal receiver of the satellite navigation system 19, the barometric altimeter 20, the transmitting television camera 21, are connected to the corresponding inputs of the encoding unit 22, the output of which is connected to the input of the transmitting device 23. The axis the lens of the television camera is oriented vertically downward, which allows you to determine the moment of flight of the UAV over the reference point with known geographical coordinates .

Ground equipment 3 is represented by a block diagram in figure 5, contains a receiving device 24, a decoding unit 25, a remote control operator UAV 26 with one input and two outputs, a memory unit 27 of the geographical coordinates of landmarks, a computer 28 with two inputs and one output and a device registration 29.

In the ground equipment 3, the output of the receiving device 24 is connected in series with the decoding unit 25, the input of the operator’s UAV panel 26, the first output of which is connected to the control input of the memory unit 27 of the geographical coordinates of landmarks, with the first input of the computer 28, with the registration device 29. In this case, the second the output of the operator’s panel UAV 26 is connected to the second input of the computer 28.

Measurements of the characteristics of the RNS are made at the moments of the flight of the UAV over landmarks. Errors in measuring the azimuthal and rangefinding coordinates of UAVs are calculated from the known geographical coordinates of landmarks, the geographical coordinates of the RSN (ARP) and the measured radio navigation coordinates of the UAV in the local coordinate system (with the beginning at the point of placement of the RSN antenna) at the time of its flight over the landmarks. Examples of the implementation of the UAV and the blocks of the second device are similar to the examples presented in the first device.

The second device operates as follows. A UAV flies along a predetermined route crossing on its way a number of characteristic landmarks on the earth's surface with known geographical coordinates. It can be triangulation points, churches and other structures with clearly localized geometry and clearly visible from the height of the aircraft. The moment of flight of the UAV over a landmark is determined by the television image of the landmark on the earth's surface. At this moment, the operator of the UAV, from the operator’s remote control 26 to the memory unit 27, enters from it into the computer 28 the geographical coordinates of the corresponding landmarks. In this case, the radio navigation signals received from the UAV are received at the other input of the calculator 28. When signals are received at both inputs of the calculator 28, it determines the difference between the radio navigation and geographical coordinates of the landmarks and transmits these parameters to the registration device 29.

The signals of the satellite navigation system 19, displayed on the operator’s panel of the UAV 26, are used by the operator to control the UAV.

The barometric altimeter 20 is used to control the height of the span over landmarks and when flying along the route.

In another embodiment of the second device, a flashing light-emitting emitter is installed on board the aircraft, which is activated by a command from the Earth when the aircraft is not visible enough, as well as when searching for an aircraft in case of emergency landing.

The third device.

Now we turn to the third device, designed to perform flight inspections of the ATM. The third device consists of UAV 1, equipment 2 installed on board the UAV, and ground equipment 3.

The equipment installed on board the UAV, represented by the block diagram in Fig.6, contains a television transmitting camera 31, a signal receiver of the satellite navigation system 32, a barometric altimeter 33, an encoding unit 34, a transmitting device 35, an VHF transmitter 30.

The above blocks of the device are interconnected as follows. The outputs of the television transmitting camera 31, the signal receiver of the satellite navigation system 32, the barometric altimeter 33, the VHF transmitter 30 are connected to the corresponding inputs of the encoding unit 34, the output of which is connected to the transmitting device 35. The axis of the lens of the television camera 31 is oriented vertically downward, which allows to determine moment of flight of the UAV over the reference point with known geographical coordinates.

Ground equipment 3 is represented by the block diagram in Fig. 7, contains a receiving device 36, a decoding unit 37, a remote control operator UAV 38, a memory unit 39 of geographical coordinates of landmarks, a computer 40 with two inputs and one output, a reader 41.

In ground equipment, the output of the receiving device 36 is connected in series with the decoding unit 37, the operator panel 38 of the UAV, the memory block 39 of the geographical coordinates of landmarks, the first input of the calculator 40, the registration device 42. The input of the reader 41 is connected to the ATM 42, and its output is connected to the second the input of the calculator 40.

ARP characteristics are measured by measuring the bearing of the VHF transmitter signals mounted on the UAV. Errors in the measurement of the UAV bearing are calculated from the known geographical coordinates of landmarks, the geographical coordinates of the ARP and the measured values of the UAV bearing in the local coordinate system (with the beginning at the point of placement of the ARP antenna) at the time of its flight over the landmarks. Examples of the implementation of the UAV and the blocks of the third device are similar to the examples presented in the first device.

The third device operates as follows. A UAV flies along a predetermined route crossing a number of landmarks on its way: characteristic points on the earth's surface with known geographical coordinates. It can be triangulation points, churches and other structures with clearly localized geometry and clearly visible from the height of the aircraft. The ARP during the UAV flight measures its bearing by the VHF signals of the transmitter 30 and, using the reader 41, transmits these bearing values to the first input of the calculator 40. At the moment of the UAV flight over the landmark, which is determined by the UAV operator from the television image of the landmark on the earth’s surface, the operator gives a command to the control input of the memory unit 39 about the introduction of angular geographical coordinates of the corresponding landmark to the second input of the calculator 40. When signals are received at both inputs of the calculator 40, it calculates the difference between the UAV bearing and the angular geographical coordinate of the landmark. This error value of the ARP bearing is recorded by the registration device 42.

The signals of the satellite navigation system 32 and the barometric altimeter 33 displayed on the operator panel 38 of the UAV are used by the operator to control the UAV.

In another embodiment of the third device, a flashing light-emitting emitter is installed on board the aircraft, which is turned on by a team from the Earth when searching for the aircraft in case of emergency landing.

Application of the invention

The invention can be applied:

- during the development and flight testing of new models of landing systems and radio navigation systems for civil aviation and military aviation, land and sea based,

- during commissioning of landing systems and radio navigation systems,

- during periodic scheduled verification of radio systems,

- in case of non-scheduled verification of radio systems in connection with the comments or complaints of military pilots or pilots of scheduled civil aircraft,

- when performing research work in the field of beacon landing systems for aircraft and radio navigation systems,

- in the training of students and in continuing education courses for specialists in civil and military aviation.

Claims (7)

1. A method of flight verification of ground-based radio-technical flight support means, that they measure the coordinates of the aircraft with an optical device and simultaneously, when radio equipment is in operation, generate radio-navigation measuring signals installed on board the aircraft, together process the signals from the output of the optical device and measurement signals , display and record the measurement results and the results of joint signal processing, characterized in that as radio engineering tools use heading, glide path, marker radio beacons, azimuthal and rangefinding radio navigation beacons, automatic direction finders, as an aircraft for flight verification of the indicated radio technical means of flight use a remotely piloted aircraft (UAV), radio navigation measuring signals from the outputs of the onboard receivers , emit into free space, receive on the Earth by radio engineering means, decode. 2. The method according to claim 1, characterized in that for directional, glide path and marker beacons, the angular coordinates of the UAV are measured using radio-technical means of trajectory measurements, the radio navigation measuring signals received on board the UAV are encoded, the encoded signals are emitted into the free space using the transmitting device received on Earth signals are decoded and, by processing them together with the signals of the trajectory measurement device, converted to the output parameters of the said beacons, the result You display and record measurements and processing. 3. The method according to claim 1, characterized in that for the azimuthal and rangefinding radio navigation beacons received on board the UAV, the radio navigation measuring signals at the time of the flight of the UAV above the landmarks are encoded and using a transmitting device, the encoded signals are emitted into free space, the signals received on Earth are decoded and by joint processing with known data on the geographical coordinates of landmarks, the above-mentioned beacons are converted into output parameters, the measurement and processing results express and register. 4. The method according to claim 1, characterized in that for automatic direction finders, the angular coordinates of the UAV are measured by the direction finder at the moments of the flight of the UAV above the given landmarks, by processing the data on the geographical coordinates of the landmarks and the values of the measured bearing angles, the output parameters of the direction finder are determined, the measurement results and co-processing display and register. 5. The flight verification device for directional, glide path, marker, and radio beacons according to claim 2, comprising a directional beacon signal receiver, a glide path beacon signal receiver, a radio range finder transceiver, a marker beacon signal receiver, a barometric altimeter, a trajectory measurement device and a recording device, characterized in that additionally contains a UAV, a coding unit, a transmitting device, a receiving device, a decoding unit, a computer with first and second inputs and from the first and second outputs, remote UAV operator; wherein the outputs of the directional beacon receivers, the glide path beacon, the marker beacon, the output of the receiver of the onboard transceiver of the radio range finder and the output of the barometric altimeter are connected to the corresponding inputs of the coding unit, the output of which is connected to the input of the transmitting device, the devices being mounted onboard the UAV; and on Earth, the output of the receiving device is connected in series with the decoding unit, the first input of the calculator, the first output of which is connected to the input of the UAV operator console; the output of the trajectory measurement device is connected to the second input of the calculator; the second output of the calculator is connected to the input of the recording device. 6. A device for flight testing of azimuthal and rangefinding radio navigation beacons according to claim 3, comprising a receiver of signals of the azimuthal channel of the radio navigation beacon, an onboard transceiver of a rangefinding radio navigation beacon, a barometric altimeter, characterized in that it further comprises a UAV, a television transmitting camera, a satellite navigation signal receiver systems, coding unit and transmitting device, receiving device, decoding unit, UAV operator panel with one input and two knowing the outputs, a memory block of coordinates of landmarks, a computer, a registration device; while on board the UAV, the output of the receiver of the azimuthal radio navigation beacon, the output of the receiver of the airborne transceiver of the rangefinding radio navigation beacon, the output of the receiver of the signals of the satellite navigation system, the outputs of the transmitting television camera and the barometric altimeter are connected to the corresponding inputs of the encoding unit, the output of which is connected to the input of the transmitting device; and on Earth, the output of the receiving device is connected in series with the decoding unit, the input of the operator’s panel of the UAV, the first output of which is connected to the memory block of coordinates of landmarks, the output of which is connected to the first input of the computer, the second output of the panel of the operator of the UAV is connected to the second input of the computer, the output of which is connected with the registration device. 7. The flight verification device for automatic direction finders according to claim 4, including a VHF transmitter, a barometric altimeter, characterized in that it further comprises a UAV, a transmitting television camera, a signal receiver of a satellite navigation system, an encoding unit, a transmitting device, a receiving device, a decoding unit, operator panel, bearing reader, memory block of coordinates of landmarks, a computer with first and second inputs and outputs, a registration device; while on board the UAV, the outputs of the transmitting television camera, barometric altimeter, the output of the satellite navigation system receiver are connected to the corresponding inputs of the encoding unit, the output of which is connected to the input of the transmitting device, and on Earth, the output of the receiving device is connected in series with the input of the decoding unit, the UAV operator panel, a memory block of coordinates of landmarks, the first input of the calculator, and the input of the bearing reader is connected to the ATM, and its output is connected to the second input of the calculator an indicator, the output of which is connected to the registration device.

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