RU2295742C1 - Aviation meteorological complex of active influencing on clouds - Google Patents

Abstract

FIELD: the invention refers to the field of technical means used for active influencing on clouds and cloud systems with the view of artificial increasing of precipitations and prevention of hail hitting.

SUBSTANCE: the aviation meteorological complex has located aboard an aircraft means of active influencing on clouds, equipment for measuring parameters of atmospheric environment and also mated with it an airborne automatic system of receiving and telecasting of data having a radio station and connected to it a radio modem, a control block mating with airborne means of active influencing on clouds. At that the control block has a processor with a color video terminal and a control panel. On the ground station of controlling the flight and active influencing there are in-series inserted a meteoradiolocator, a calculator and an arrangement of receiving and telecasting data including a radio station and connected with it a radio modem.

EFFECT: increases noise immunity and reliability of data exchange between an aircraft and the ground station of controlling the flight and active influencing on clouds.

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Description

The proposed complex relates to the field of technical means used for active impacts on clouds and cloud systems in order to artificially increase precipitation and prevent hail.

Various technical means are known for active impacts on clouds and cloud systems, which are mainly stationary anti-hail missile systems located at the points of impact, which are controlled from a command post via a radio channel both in automatic and in semi-automatic mode (Bibilashvili N.Sh., Burtsev II, Seregin Yu.A. Guidelines for the organization and conduct of anti-hail works .-- L. Gidrometeoizdat, 1981, p. 37-48; RF patent No. 2083999, 1997). These systems are widely used both in our country and abroad to control the active effects on hail clouds using rocket technology. However, the functionality of such systems is limited. So, for example, with the existing composition and software, they can only be used to control active impacts on clouds using stationary rocket impact points.

Known aviation meteorological complex IL-18D "Cyclone", created on the basis of a serial aircraft IL-18D, containing active means and on-board meteorological equipment for measuring atmospheric parameters, as well as an on-board automated system for recording and processing measurements on board (Multipurpose airplane - IL-18D "Cyclone" meteorological laboratory. Avenue of VDNH - Obninsk, VNIIGMI-WDC - 7 pp.). This aeronautical meteorological complex is intended for scientific research of atmospheric processes and development of methods for artificial precipitation in the interests of the national economy. The composition of the research equipment includes a large complex of measuring equipment. In the cabin there are 19 stands with 34 jobs for members of the scientific crew. ASO-2I and KDS-155 automatic pyro cartridge cartridges are used as a means of active influence on the clouds, as well as a system for the dosed release of a reagent into the atmosphere, for example, solid carbon dioxide granules.

Along with the advantages, this complex has a number of significant disadvantages, which are that the complex is intended mainly for research work. It does not provide automatic control of active means, as it is intended for registration and automated processing of measurements of atmospheric parameters by airborne instruments. For this reason, it is technically impossible to affect hail clouds due to the lack of radar data on the sowing sites, which can only be obtained from ground-based radar stations. In this regard, active effects are carried out only on rain clouds in order to increase precipitation. In this case, pyroelements are fired at the top of the cloud when the aircraft moves above the upper edge, and the reagent introduction zone is determined and the impact results are evaluated visually. These shortcomings limit the scope of the complex and reduce the effectiveness of its use for active impacts on clouds and cloud systems of various types.

Also known are complexes for active effects on clouds (RF patents Nos. 2084922, 2111646, 2172969, 2213984 and others).

Of the known complexes, the closest to the proposed one is the "Aviation meteorological complex for active impact on the clouds" (RF patent No. 2213984, G 01 W 1/08, 2002), which is selected as a prototype.

The specified complex contains active means and equipment placed on board the aircraft for measuring atmospheric parameters, as well as an onboard automated system for recording and processing measurement results associated with it. On board there is also a data reception and television transmission system containing a radio station and a radio modem, an airborne control unit for actively affecting the clouds. The control unit contains a processor with a color video terminal and a control panel. The aeronautical meteorological complex also contains a ground-based station for controlling flight and active actions, including a weather radar and a functional calculator connected to it, the output of which is connected to a data reception and transmission system.

An object of the invention is to increase the noise immunity and reliability of data exchange between an airplane and a ground-based flight control station and active actions via a duplex radio channel using complex signals with phase shift keying.

The problem is solved in that in an aeronautical meteorological complex for active impacts on clouds, containing active impact means placed on board the aircraft, equipment for measuring atmospheric parameters, as well as an onboard automated system for recording and processing measurement results, a reception and television transmission system , a control unit interfaced with on-board means of actively influencing the clouds, the control unit comprising a processor with a color video terminal and the control panel, the data reception and transmission system and the satellite coordinate determiner are connected respectively to the first and second input of the processor, and the output of the on-board automated system for recording and processing measurement results is connected to its third input, each control output of the processor is connected to a corresponding control channel containing in series digital-to-analog converter and power amplifier, the output of the power amplifier of each control channel is connected to the input of the complementary mechanism of the appropriate means of active influence, the meteorological radar, the computer and the device for receiving and transmitting data, the system for receiving and transmitting data located on board the aircraft, sequentially connected to the first master oscillator, the first phase manipulator, placed on the ground control station for flight and active actions the second input of which is connected to the first output of the processor, the first mixer, the second input of which is connected to the output of the first a local oscillator, an amplifier of the first intermediate frequency w _pr1 , a first power amplifier, a first isolation element, the input-output of which is connected to the first transceiver antenna, a second power amplifier, a second mixer, the second input of which is connected to the output of the second local oscillator, the first amplifier of the second intermediate frequency w _pr2 the first multiplier, the second input of which is connected to the output of the first local oscillator, the first bandpass filter and the first phase detector, the second input of which is connected to the output of the second local oscillator, and the output is and the data receiving and transmitting system is connected to the processor, the data receiving and transmitting system located on the ground flight and active control station contains a second master oscillator, a second phase manipulator, the second input of which is connected to the output of the computer, the third mixer, the second whose input is connected with the output of a third oscillator, an intermediate frequency amplifier w _pr third power amplifier, the second isolation member, an input-output of which is connected with the second moperedayuschey antenna, the fourth power amplifier, a fourth mixer, a second input coupled to an output of a fourth local oscillator, the second power of the second intermediate frequency w _np2, the second multiplier, a second input coupled to an output of a third oscillator, the second bandpass filter and a second phase detector, a second input of which connected to the output of the fourth local oscillator, and the output is the output of the reception system and data and TV connected to the calculator, and the frequencies _G1 w, w and _T2 of the first and second, third and chetvertog oscillators spaced apart by a second intermediate frequency

w _G2 -w _G1 = w _pr2 ,

reception system and data telecast placed on board an aircraft emits complex signals with a phase shift keying at the frequency w ₁ = w _pr1 = w _T2, and receives at frequency w ₂ = w _ave = w _G1, reception system and data telecast placed on the ground the flight and active control station, on the contrary, emits complex signals at a frequency of w ₂ , and receives at a frequency of w ₁ .

The block diagram of the complex is presented in figure 1. The structural diagram of a system for receiving and transmitting data transmitted on board an aircraft is shown in FIG. The block diagram of the reception and transmission of data located on the ground control station flight and active influences, is presented in figure 3. The present diagram illustrating frequency conversion of signals is depicted in FIG. 4. Timing diagrams explaining the operation of data reception and transmission systems are shown in FIGS. 5 and 6.

The aeronautical meteorological complex for active actions on the clouds contains equipment 2 located on board the aircraft 1 for measuring atmospheric parameters and an on-board automated system 3 associated with it for recording and processing the measurement results, as well as a ground control and flight control station 23.

On board the aircraft are also placed series-connected systems 4 for receiving and transmitting data, containing a radio station 5 and a radio modem 6 connected to it, an airborne active impact control unit 7 and airborne means 8, 9 and 10 of active effects on the clouds. The number and composition of the means of exposure may be different depending on the technology used. In this case, an airborne missile launcher 8, a system for automatically firing squibs and a device 10 for introducing solid carbon dioxide granules into the cloud are placed on board the aircraft.

The control unit 7 means of active actions includes a processor 11 with a color video terminal (not shown) and a remote control 12. A digital-to-analog converter 13 and a power amplifier 14 connected to an actuator 15 for controlling the rocket launcher 8 are connected in series to the first control output of the processor 11. A second digital-to-analog converter 16 and a second power amplifier 17 are connected to the second control output of the processor 11 and connected to the input by its output the actuator 18 of the system 9 automatic shooting of the squibs. And finally, to the third control output of the processor 11, a third digital-to-analog converter 19 and a third power amplifier 20 are connected in series, which, in turn, is connected to the actuator 21 of the amplifier 10 for introducing solid carbon dioxide granules into the cloud. At the same time, a radio modem 6 of the data reception and transmission system 4 is connected to the first input of the processor 11, and a satellite coordinate determiner 22 is connected to its second input. A third-party automated system 3 for recording and processing measurement results is connected to the third input of the processor 11.

The flight and active control ground station 23 includes meteorological radars 24, a calculator 25, and a data receiving and transmitting device 26, including a radio station 27 and an associated radio mode 28. The ground and active control missions 23 provides generation of action commands, determining safe flight routes and aiming aircraft at the target, and also provides control over the results of exposure and determines the flight program after seeding.

Placed on board the aircraft 1, the active action control unit 7 is connected via duplex radio communication channels to the ground control and active impact control station 23.

The system 4 for receiving and transmitting data, located on board the aircraft 1, contains serially connected the first master oscillator 29, the first phase manipulator 30, the second input of which is connected to the output of the processor 11, the first mixer 32, the second input of which is connected to the output of the first local oscillator 31, an amplifier 33 of the first intermediate frequency w _pr1 , the first power amplifier 34, the first isolation element 35, the input-output of which is connected to the first transceiver antenna 36, the second power amplifier 37, the second mixer 39, the second input of which is dinene with the output of the second local oscillator 38, the first amplifier 40 of the second intermediate frequency w _pp2 , the first multiplier 41, the second input of which is connected to the output of the local oscillator 31, the first bandpass filter 42 and the first phase detector 43, the second input of which is connected to the output of the local oscillator 38, and the output is the output of the system 4 receiving and transmitting data and is connected to the processor 11.

The system 26 for receiving and transmitting data transmitted to the ground station 23 for controlling flight and active actions includes a second master oscillator 44, a second phase manipulator 45, the second input of which is connected to the output of the computer 25, and the third mixer 47, the second input of which is connected to the output the third local oscillator 46, the intermediate frequency amplifier 48 w _pr , the third power amplifier 49, the second isolation element 50, the input-output of which is connected to the second transceiver antenna 51, the fourth amplifier 52 is powerfully a fourth mixer 54, the second input of which is connected to the output of the fourth local oscillator 53, the second amplifier 55 of the second intermediate frequency w _pr2 , the second multiplier 56, the second input of which is connected to the output of the local oscillator 46, the second band-pass filter 57 and the second phase detector 58, the second input which is connected to the output of the local oscillator 53, and the output is the output of the system 26 for receiving and transmitting data and is connected to the computer 25.

Moreover, the frequencies w _G1 and w _{G2 of the} first 31 and second 38, third 46 and fourth 53 local oscillators are spaced at the second intermediate frequency

w _G2 -w _G1 = w _pr2 ,

systems 4 for receiving and transmitting data, located on board the aircraft 1, emit complex signals with phase shift keying at a frequency w ₁ = w _pr1 = w _G2 , and receive at a frequency w ₂ = w _pr = w _G1 , system 26 for receiving and transmitting data, located on the ground flight control and active control station 23, on the contrary, emits complex signals with phase shift keying at a frequency w ₂ , and receives at a frequency w ₁ .

The aeronautical meteorological complex for active impact on the clouds works as follows.

The weather radar 24 provides an overview of three-dimensional space with a given frequency, analog-to-digital conversion, averaging and input of signals to the computer 25 with the suppression of local objects. The calculator 25 calculates the radar reflectivity and characteristics of the clouds, as well as the formation of cloud patterns and sowing areas.

At the same time, on-board aircraft 1, the first master oscillator 29 generates a harmonic oscillation (figure 5, a)

u _c1 (t) = U _c1 · cos (w _c t + φ _c1 ), 0≤t≤T _c1 ,

where U _c1 , w _c , φ _c1 , T _c1 is the amplitude, carrier frequency, initial phase and duration of the oscillation, which is supplied to the first input of the phase manipulator 30, the second input of which is supplied with the modulating code M ₁ (t) (Fig. 5, b) from the output of the processor 11. The modulating code M ₁ (t) characterizes the current coordinates of the aircraft 1 and other necessary meteorological data that are received at the input of the processor 11 from the on-board automated system 3 connected with it for recording and processing the measurement results.

At the output of the phase manipulator 30, a complex signal with phase shift keying (QPSK) is generated (Fig. 5, c)

u ₁ (t) = U _c1 · cos [w _c t + φ _k1 (t) + φ _c1 ], 0≤t≤T _c1 ,

where φ _k1 (t) = {0, π} is the manipulated component of the phase that displays the law of phase manipulation in accordance with the modulating code M ₁ (t) (Fig. 5, b), and φ _k1 (t) = const at kτ _e <t <(k + 1) τ _e and can change abruptly at t = kτ _e , i.e. at the boundaries between elementary premises (k = 1, 2, ..., N-1).

τ _e , N - the duration and number of chips that make up a signal of duration T _s1 (T _c1 = τ _e · N),

which is supplied to the first input of the first mixer 32, the second input of which is supplied with the voltage of the first local oscillator 31

u _Г1 (t) = U _Г1 · cos (w _Г1 t + φ _Г1 ).

At the output of the mixer 32, voltage of combination frequencies is generated. The amplifier 33 is allocated the voltage of the first intermediate (total) frequency (figure 5, g)

Where

To ₁ - gear ratio of the mixer;

w _CR1 = w _c + w _G1 - the first intermediate (total) frequency;

φ _pr1 = φ _c1 + φ _G1 .

This voltage after amplification in the power amplifier 34 through the first isolation element 35 enters the transceiver antenna 36 and is radiated by it at a frequency w ₁ = w _pr1 = w _G2 (Fig. 4), it is captured by the transceiver antenna 51 of the system 26 for receiving and transmitting data, located at the ground control and flight control station 23, and through the second isolation element 50 and the fourth power amplifier 52, is supplied to the first input of the fourth mixer 54. The voltage u _Г2 (t) of the local oscillator 53 is applied to the second input of the mixer 54. At the output of the mixer 54, Raman voltages are generated. The amplifier 55 is allocated the voltage of the second intermediate (differential) frequency (figure 5, d)

Where

w _CR2 = w _CR1 -w _G1 - the second intermediate (difference) frequency;

φ _CR2 = φ _CR1 -φ _G1 ,

which is supplied to the first input of the multiplier 56. The voltage of the local oscillator 46 is supplied to the second input of the multiplier 56

u _Г2 (t) = U _Г2 · cos (w _Г2 t + φ _Г2 ).

At the output of the multiplier 56, an intermediate frequency voltage is generated (Fig. 5, e)

Where

K ₂ is the transmission coefficient of the multiplier;

w _{pr r1} = w = w -w _{np2 T2} - intermediate frequency,

which is allocated by the band-pass filter 57 and fed to the information input of the phase detector 58, to the reference input of which the voltage u _Г1 (t) (Fig. 5, g) of the local oscillator 53 is applied. At the output of the phase detector 58, a low-frequency voltage is generated (Fig. 5, h)

u _H1 (t) = U _H1 cosφ _k1 (t), 0≤t≤T _c1 ,

Where

To ₃ - the transfer coefficient of the phase detector, proportional to the modulating code M ₁ (t) (Fig.5, b).

This voltage is supplied to the calculator 25.

Taking into account the information received about the current coordinates of aircraft 1 and other meteorological data, a cloud map with sowing areas is formed in the calculator 25 of the ground station 23 for controlling the flight and active influences, and the position of aircraft 1 is displayed against the background of this cloudy map with the sowing areas drawings not shown).

All this information on duplex radio channels through the systems 26 and 4 of reception and television transmission is transmitted on board the aircraft 1 with a given refresh rate.

To this end, the master oscillator 44 of the system 26 for receiving and transmitting data is generated harmonic oscillation (Fig.6, a)

u _c2 (t) = U _c2 cos (w _c t + φ _c2 ), 0≤t≤T _c2 ,

which is supplied to the first input of the phase manipulator 45, the second input of which is supplied with a modulating code M ₂ (t) (Fig.6, b) from the output of the computer 25. The modulating code M ₂ (t) contains information about the cloud map with sowing areas and The background of this cloud map with sowing sites displays the position of the aircraft 1.

At the output of the phase manipulator 45, a complex QPSK signal is generated (Fig.6, c)

u ₂ (t) = U _c2 · cos [w _c t + φ _k2 (t) + φ _c2 ], 0≤t≤T _c2 ,

which is supplied to the first input of the mixer 47, to the second input of which the voltage u _Г2 (t) of the local oscillator 46 is applied. At the output of the mixer 47, the frequencies of the combination frequencies are generated. The amplifier 48 is allocated an intermediate frequency voltage (Fig.6, g)

Where

w _CR = w ₂ = w _Г2 -w _с - intermediate frequency;

φ _pr3 = φ _Г2 -φ _с2 ,

This voltage after amplification in the power amplifier 49 through the decoupling element 50 enters the transceiver antenna 51, is radiated by it at a frequency w ₂ = w _pr = w _G1 , is captured by the transceiver antenna 36 of the data reception and transmission system 4 located on board the aircraft 1, and through the isolation element 35 and the power amplifier 37 is supplied to the first input of the mixer 39. The voltage u _Г2 (t) of the local oscillator 38 is supplied to the second input of the mixer 39. At the output of the mixer 39, the frequencies of the combination frequencies are generated. The amplifier 40 is allocated the voltage of the second intermediate (differential) frequency (Fig.6, d)

Where

_np2 = w w -w _{T2, etc.} - a second intermediate (difference) frequency;

φ _CR4 = φ _G2 -φ _CR3 ,

which is supplied to the first input of the multiplier 41, the second input of which is supplied with a voltage u _Г1 (t) of the local oscillator 31. A voltage is generated at the output of the multiplier 41 (Fig. 6, e)

Where

w _G2 = w _CR1 = w _CR2 + w _G1 - the first intermediate frequency,

which is allocated by the band-pass filter 42 and fed to the information input of the phase detector 43, the reference input of which is supplied with the voltage u _Г2 (t) (Fig.6, g) of the local oscillator 38. A low-frequency voltage is generated at the output of the phase detector 43 (Fig.6, h)

u _H2 (t) = U _H2 cosφ _k2 (t), 0≤t≤T _c2 ,

пропорциональное модулирующему коду M₂(t) (фиг.6, б).Where

proportional to the modulating code M ₂ (t) (Fig.6, b).

This voltage is supplied to the processor 11, where it is processed accordingly and displayed in color on the color video terminal in the form of a dynamic picture, allowing the operator to visually observe the flight route of aircraft 1 against the background of the cloud and sowing areas, as well as to influence the clouds in both automatic and and in semi-automatic modes.

In the automatic exposure mode, in the calculator 25 of the ground station 23 for controlling the flight and active actions, depending on the type of cloud, a corresponding command for the action is generated. In this case, the relative position of the sowing area and aircraft 1, as well as the speed of their movement in space, are taken into account. The approach of aircraft 1 to the sowing site is carried out strictly according to a given optimal route against the background of a cloud map. Depending on the type of clouds and the technology of exposure, an appropriate technical means of exposure is activated. For example, when a hail cloud is exposed to a hail cloud, aircraft 1, moving along a given route, approaches the sowing area. When the plane 1 reaches the set point, the signal from the processor 11 is fed sequentially to the digital-to-analog converter 13, the power amplifier 14 and the corresponding actuator 15, which drives the onboard rocket launcher 8.

If the effect on the clouds is carried out for the purpose of artificial precipitation, then other technical means are used, for example, an automatic shooting system for pyro cartridge 9, or a device 10 for introducing solid carbon dioxide granules into the cloud.

In special cases, when the effect is on clouds that are not fixed by the weather radar 24, the inclusion of the means of influence in the operating mode is carried out in semi-automatic mode from the control panel 12. At the same time, the operator, observing the situation visually, evaluates the situation and, using the control panel 12, enters the processor 11 with the appropriate commands to turn on certain means of influence.

The aeronautical meteorological complex for active actions on the clouds has increased functionality and high efficiency, which is achieved due to the complete automation of all processes associated with the control of meteorological conditions and active influences.

Thus, the proposed complex in comparison with the prototype provides increased noise immunity and reliability of the exchange of data between the aircraft and the ground-based flight control station and active influences via a duplex radio channel. This is achieved by using complex phase shift keyed signals.

At the same time, the data reception and television transmission system placed on board the aircraft emits complex PSK signals at a frequency of w ₁ and receives at a frequency of w ₂ . A data reception and television transmission system located at a ground-based flight and active control station, on the contrary, emits complex PSK signals at a frequency of w ₂ , and receives at a frequency of w ₁ .

Complex QPSK signals open up new possibilities in the technique of transmitting and receiving discrete information. These signals allow the use of a new type of selection - structural selection. This means that there is a new opportunity to separate signals operating in the same frequency band and at the same time intervals. In principle, one can abandon the traditional method of dividing the operating frequencies of the used range between airplanes and a ground-based flight control station and active actions and selecting them on the receiving side using frequency filters. It can be replaced by a new method based on the simultaneous operation of each aircraft in the entire frequency range with phase-shift signals with the isolation of the FMN signal receiving device of the required aircraft through its structural selection.

Among other problems, the solution of which to a large extent depends on the further progress of duplex radio communications, should include the problems of establishing reliable exchange of discrete information between airplanes and a ground station in the presence of multipath propagation of radio waves. The latter circumstance leads to a distortion of the received signals, which complicates the reception and reduces the reliability of the transmission of information.

Attempts to overcome the harmful effects of multipath have been made for a long time. These include: diversity reception, signal selection by time and angle of arrival, corrective coding, and some other methods. However, all of them do not provide a fundamental solution to the problem.

Due to its good correlation properties, a complex FMN signal can be “folded” into a narrow pulse, the duration of which is inversely proportional to the used bandwidth. Choosing a frequency band so that the duration of the “convoluted” pulse is shorter than the delay time, it is possible to separately receive pulses arriving at the receiving point in various ways, and by summing their energy, it is also possible to increase the noise immunity of complex QPSK signals. Thus, the indicated problem gets a fundamental solution.

From the point of view of detection, complex QPSK signals have high energy and structural secrecy.

The energy secrecy of these signals is due to their high compressibility in time and spectrum with optimal processing, which reduces the instantaneous radiated power. As a result, a complex QPSK signal at the receiving point may be masked by fogs and noise. Moreover, the energy of a complex QPSK signal is by no means small; it is simply distributed over the time-frequency domain so that at each point of this region the signal power is less than the power of noise and interference.

The structural secrecy of complex QPSK signals is caused by a wide variety of their shapes and significant ranges of parameter changes, which makes it difficult to optimize or at least quasi-optimal processing of complex QPSK signals with an a priori unknown structure in order to increase the sensitivity of the receiver.

Claims (1)

An aeronautical meteorological complex for active actions on clouds containing active means on board an aircraft, equipment for measuring atmospheric parameters, as well as an on-board automated system for recording and processing measurement results, a data reception and transmission system containing a radio station and connected to a radio modem, a control unit coupled with on-board means of actively influencing the clouds, the control unit comprising a processor with a color video terminal and a control panel, respectively, a data reception and transmission system and a satellite coordinate determiner are connected to the first and second input of the processor, and the output of the on-board automated system for recording and processing measurement results is connected to its third input, each control output of the processor is connected to the corresponding control channel, containing sequentially placed digital-to-analog converter and power amplifier, the output of the power amplifier of each channel is controlled is connected to the input of the actuator of the appropriate means of active influence, a weather radar, a computer and a device for receiving and transmitting data, including a radio station and an associated radio modem, characterized in that the system for receiving and transmitting data, placed on board the aircraft, contains in series included the first master oscillator, the first phase manipulator, the second input of which union of a first output terminal of the first mixer, a second input coupled to an output of the first oscillator amplifier first intermediate frequency w _pr1, the first power amplifier, the first element isolation, input-output of which is connected to a first transceiving antenna, a second power amplifier, a second mixer, a second input coupled to an output of the second oscillator, a first amplifier of the second intermediate frequency w _np2, the first multiplier, a second input coupled to an output of the first oscillator, a first bandpass filter and n the first phase detector, the second input of which is connected to the output of the second local oscillator, and the output is the output of the data reception and television transmission system and connected to the processor, the data reception and television transmission system located on the ground flight and active control station contains a second master oscillator connected in series, the second phase manipulator, the second input of which is connected to the output of the calculator, the third mixer, the second input of which is connected to the output of the third local oscillator, an intermediate hour amplifier Ota w _pr third power amplifier, the second element isolation, an input-output is connected to the second reception antenna, the fourth power amplifier, a fourth mixer, a second input coupled to an output of a fourth local oscillator, the second power of the second intermediate frequency w _np2, the second multiplier, a second the input of which is connected to the output of the third local oscillator, the second bandpass filter and the second phase detector, the second input of which is connected to the output of the fourth local oscillator, and the output is the output of the reception system and telepere Aci data and connected to the calculator, and the frequencies w and w _{T1 T2} of the first and second, third and fourth oscillators spaced apart by a second intermediate frequency w -w _{T2 T1} = w _np2, reception system and data telecast placed on board an aircraft emits complex signals with phase shift keying at a frequency w ₁ = w _pr1 = w _G2 , a receives at a frequency w ₂ = w _pr2 = w _G1 , a data reception and television transmission system located at a ground-based flight and active control station, on the contrary, emits complex signals at a frequency w ₂ , a takes on the frequency w ₁ .

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