RU2627683C1 - Helicopter radiotechnical complex for detecting "black box" with alarm of crashed airplane - Google Patents

Abstract

FIELD: radio engineering, communication.

SUBSTANCE: helicopter radiotechnical complex comprises onboard equipment and the "black box" with the alarm, and the onboard equipment comprises an antenna device, a receiver, a bearing device, an analyzer of received signal parameters, a device of memorizing and processing the received information, a telemetry device, receiving devices, adjustment units, local oscillators, mixers, the first intermediate frequency amplifiers, an engine, a reference generator, a detector, a delay line, the second intermediate frequency amplifier, multipliers, narrowband filters, delay lines, phase detectors, lowpass filters, phase shifters at 90°, squarers, an adder, a threshold unit, phase meters, wherein the "black box" contains a GPS-signal receiver, a receiving antenna, a duplexer, a local oscillator, a mixer, an intermediate frequency amplifier, a demodulator, multipliers, a narrowband filter, a lowpass filter, a computing unit, a modulating code shaper, a delay line, a pseudorandom sequence generator, an adder, a phase manipulator and a power amplifier at 65. The listed means are implemented in a certain way and connected to each other.

EFFECT: increasing the efficiency and reliability of detecting an aircraft that has suffered a catastrophe, by using two additional direction-finding channels and a "black box" with alarm.

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Description

The proposed helicopter radio engineering complex relates to the field of aviation and can be used to search, detect and determine the location of the "black box" with the signaling of an airplane that crashed.

During a catastrophe, along with the plane, the “black box” falls to the ground and when it hits the ground, its components fail, which are then restored with great difficulty. And if the plane crashed over the sea, then the “black box” with the plane falls into the sea, which cannot be found in the depths of the sea without the appropriate signaling.

This happened when the A-330 crashed over the sea. The search for the "black box" was carried out by touch, since it did not emit any signals for the search. And for this reason, the search was unsuccessful.

A similar negative situation arises during an airplane crash in the mountains and in inaccessible places.

Helicopter radio engineering complexes are known (RF patent No. 2.150.178, 2.275.746, 2.321.177, 2.419.991, 2.465.733; US patents No. 3.806.926, 3.891.989, 3.896.439, 4.328.496, 5.841 .872, 7.318.368; UK patent No. 2.180.728; German patents No. 2.538.014, 3.346.155; French patent No. 2.447.041 and others).

Of the known systems and devices closest to the proposed is the "Radio control station" (RF patent No. 2,465.733, H04K 3/00, 2011), which is selected as a prototype.

An object of the invention is to increase the efficiency and reliability of the detection of an airplane that crashed by using two additional direction-finding channels and a black box with an alarm.

The problem is solved in that a helicopter radio complex for detecting a "black box" with the signaling of a crashed aircraft, containing, in accordance with the closest analogue, a series-connected antenna device, a receiver, an analyzer of the parameters of the received signal, a device for storing and processing the received information, the second whose input through the direction finding device is connected to the output of the antenna device, and a telemetry device, the output of which is the output of the complex, p and the receiver is made in the form of a series-connected receiving antenna, a first mixer, the second input of which through the first local oscillator is connected to the output of the tuning unit, the amplifier of the first intermediate frequency, the detector, the second input of which is connected to its output through the first delay line, a key, the second input of which connected to the output of the first intermediate frequency, the second mixer, the second input of which is connected to the output of the second local oscillator, and the amplifier of the second intermediate frequency, the output of which is the output of the control input of the tuning unit is connected to the detector output, which is made in the form of a first intermediate frequency of the third delay line, a fourth multiplier connected in series to the amplifier output of the first intermediate frequency, the second input of which is connected to the output of the first intermediate frequency amplifier, the first low-pass filter, the first quadrator, adder and a threshold unit, the second input of which through the first delay line is connected to its output, and the output is connected to the control input of the tuning unit and the key to the first input а, connected to the output of the amplifier of the first intermediate frequency of the first phase shifter 90 °, the fifth multiplier, the second input of which is connected through the second phase shifter 90 ° to the output of the third delay line, the second low-pass filter and the second quadrator, the output of which is connected to the second input of the adder , the direction-finding device is made in the form of two direction-finding channels, each of which consists of a series-connected receiving antenna, a mixer, the second input of which is connected to the output of the first Goethe one amplifier of the first intermediate frequency, a multiplier, the second input of which is connected to the output of the amplifier of the second intermediate frequency, and a narrow-band filter, the third multiplier is connected in series to the output of the first narrow-band filter, the second input of which is connected to the output of the second narrow-band filter, the third narrow-band filter and the first phase meter , to the output of the second narrow-band filter, a second delay line is connected in series, the first phase detector, the second input of which is connected to the output of the second filter strip and the second phase meter, the second inputs of the phase meters are connected to the output of the reference generator, and the outputs are connected to a device for storing and processing the received information, the antenna device contains three receiving antennas, the receiving antenna of the receiver is located above the helicopter rotor hub, the receiving antennas of the direction-finding device are located at the ends the first and second blades of the rotor of the helicopter, the engine is kinematically connected with the rotor of the helicopter and the reference generator, differs from the closest analogue in that it is equipped with wives two additional direction-finding channels and a “black box” with alarm, each of the additional direction-finding channels consists of a series-connected receiving antenna, a mixer, the second input of which is connected to the output of the first local oscillator, an amplifier of the first intermediate frequency, a multiplier, the second input of which is connected to the output an amplifier of the second intermediate frequency, and a narrow-band filter, the sixth multiplier, the second input of which is connected in series to the output of the fourth narrow-band filter о is connected to the output of the fifth narrow-band filter, the sixth narrow-band filter and the third phase meter, the fourth delay line, the second phase detector, the second input of which is connected to the output of the fifth narrow-band filter, and the fourth phase meter, the second inputs of the third and fourth phase meters are connected in series to the output of the fifth narrow-band filter connected to the output of the reference generator, and the outputs are connected to a device for storing and processing the received information, receiving antennas of additional direction finding channels are placed at the ends of the third and fourth rotor blades, a “black box” with an alarm system that is thrown out of the compartment with a parachute in the event of a crash and lands or is brought down on the sea surface, while emitting electromagnetic waves and sound signals, is placed in the tail section of the aircraft and it is ejected automatically, while during the opening of the parachute the crane opens and through the air pipe from the chamber the compressed air enters the rubber chamber, which is inflated and turns into a shock absorber electromagnetic radiation and sound signals emitted from the black box are also emitted at a depth, the black box contains a duplexer connected in series, the input-output of which is connected to the transceiver antenna, a mixer, the second input of which is connected to the local oscillator output, an intermediate frequency amplifier, and a second a multiplier, the second input of which is connected to the output of the low-pass filter, a narrow-band filter, the first multiplier, the second input of which is connected to the output of the intermediate-frequency amplifier, a low-pass filter, numeral block forming unit modulating code, the delay line, an adder, a second input coupled to an output of the pseudorandom sequence generator, the phase manipulator, a second input coupled to an output of the narrowband filter and a power amplifier whose output is connected to the second input of the duplexer.

The geometric arrangement of the receiving antennas on the helicopter is shown in FIG. 1. The block diagram of the black box with alarm is shown in FIG. 2. Timing diagrams explaining the operation of the “black box” with alarm are shown in FIG. 3. The block diagram of the onboard equipment of the helicopter is shown in FIG. four.

The “black box” with alarm 47 contains a duplexer 50 connected in series, the input-output of which is connected to the transceiver antenna 49, a mixer 52, the second input of which is connected to the output of the local oscillator 51, an intermediate frequency amplifier 53, and a second multiplier 56, the second input of which is connected to the output low-pass filter 58, narrow-band filter 52, first multiplier 55, the second input of which is connected to the output of the intermediate-frequency amplifier 53, low-pass filter 58, computing unit 59, modulating code generating unit 60, line 61 delays, an adder 63, the second input of which is connected to the output of the pseudo-random sequence generator (PSP) 62, a phase manipulator 64, the second input of which is connected to the output of the narrow-band filter 57, and a power amplifier 65, the output of which is connected to the second input of the duplexer 56.

Multipliers 55 and 56, a narrow-band filter 52, and a low-pass filter 58 form a PSK demodulator 54.

The mixer 52, the local oscillator 51, the intermediate frequency amplifier 53 and the PSK signal demodulator 54 form a GPS signal receiver 48.

The helicopter’s on-board equipment contains an antenna device 1, a receiver 2, an analyzer 4 of the parameters of the received signal, a device 5 for storing and processing the received information, the second input of which is connected through the direction finding device 3 to the output of the antenna device 1, and the telemetry device 6, the output of which is the output complex.

The receiver 2 contains a receiving antenna 7 connected in series, a first mixer 12, the second input of which through the first local oscillator 11 is connected to the output of the tuning unit 10, an intermediate frequency amplifier 17, a detector 20, the second input of which is connected to its output through the first delay line 21, the key 22 the second input of which is connected to the output of the intermediate frequency amplifier 17, the second mixer 24, the second input of which is connected to the output of the second local oscillator 23, and the second intermediate frequency amplifier 25, the output of which is the output nick 2 and connected to the analyzer input signal 4 received parameters.

In this case, the detector 20 is made in the form of series-connected to the output of the amplifier 17 of the first intermediate frequency of the third delay line 37, the fourth multiplier 38, the second input of which is connected to the output of the amplifier 17 of the first intermediate frequency, the first low-pass filter 41, the first quadrator 43, the adder 45 and threshold unit 46, the second input of which is connected through the first delay line 21 to its output, and the output is connected to the control input of the tuning unit 10 and to the first input of the key 22, connected in series to the output amplifier 17 of the first intermediate frequency of the first phase shifter 36 by 90 °, the fifth multiplier 40, the second input of which through the second phase shifter 36 by 90 ° is connected to the output of the third delay line 37, the second low-pass filter 42 and the second quadrator 44, the output of which is connected to the second input adder 45.

The direction-finding device 3 contains four direction-finding channels, each of which contains a receiving antenna 8 (9, 66, 67) connected in series, a mixer 13 (14, 68, 69), the second input of which is connected to the output of the first local oscillator 1, amplifier 18 (19, 70, 71) of the first intermediate frequency, a multiplier 26 (27, 72, 73), the second input of which is connected to the output of the amplifier 25 of the second intermediate frequency, and a narrow-band filter 28 (29, 74, 75). At the same time, the third multiplier 30 is connected in series to the output of the first narrow-band filter 28, the second input of which is connected to the output of the second narrow-band filter 29, the third narrow-band filter 32 and the first phase meter 34, the second delay line 31, the first phase detector, are connected in series to the output of the second narrow-band filter 29 33, the second input of which is connected to the output of the second narrow-band filter 29, and the second phase meter 35. The sixth multiplier 76, the second is connected in series to the output of the fourth narrow-band filter 74 the course of which is connected to the output of the fifth narrow-band filter 75, the sixth narrow-band filter 78 and the third phase meter 80. A fourth delay line 77, a second phase detector 79, the second input of which is connected to the output of the fifth narrow-band filter 75, and the fourth are connected to the output of the fifth narrow-band filter 75 phase meter 81. The second inputs of the phase meters 34, 35, 80 and 81 are connected to the output of the reference generator 16, and the outputs are connected to a device 5 for storing and processing the received information.

Antenna device 1 contains five receiving antennas 7-9, 66 and 67, receiving antenna 7 of receiver 2 is located above the rotor hub of the helicopter, receiving antennas 8 and 9, 66 and 67 of direction finding device 3 are located at the ends of the rotor blades of the helicopter (Fig. 1) . The engine 15 is kinematically connected with the helicopter propeller and the reference generator 16.

A helicopter radio engineering complex for detecting a "black box" with the signaling of an airplane in a crash works as follows.

When an airplane crashes, a black box with an alarm system and a parachute is thrown out of its compartment located in the rear part. When the “black box” reaches a certain height from the ground or from the surface of the sea, the parachute automatically opens and the receiver 47 of GPS signals is turned on, and the rubber chamber is filled with compressed air. The camera inflates and turns into a shock absorber-pillow when the black box lands on the ground, and when brought to sea, the rubber chamber will serve as a float for the black box and will keep it afloat. A parachute and a rubber chamber are not shown in the drawings.

When the "black box" is thrown out of the aircraft compartment, its power is turned on and a complex signal with phase shift keying (FMN) is received, emitted by the GPS satellite

U ₁ (t) = V ₁ cos [ω ₁ t + ϕ _K1 (t) + ϕ ₁ ], 0≤t≤T ₁ ,

where V ₁ , ω ₁ , ϕ ₁ , T ₁ - amplitude, carrier frequency, initial phase and signal duration;

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 (t) (Fig 3.a), and ϕ _K1 (t) = const for kτ _e <t <( k + 1) τ and can change stepwise at t = kτ _e , i.e. at the borders between elementary premises (k = 1, 2, ..., N-1);

τ _e , N is the duration and number of chips that make up a signal of duration T ₁ (T ₁ = N⋅τ _e , for the GPS system N = (023)), which from the output of the antenna 49 through the duplexer 50 goes to the input of the mixer 52 , the second input of which a local oscillator voltage 51 is applied.

U _Г (t) = V _Г ⋅cos (ω _Г t + ϕ _Г ).

At the output of the mixer 52, a voltage of combination frequencies is generated. The amplifier 53 is allocated the voltage of the intermediate frequency (Fig. 3.b)

U _pr (t) = V _pr ⋅cos [ω _pr t + ϕ _K1 (t) + ϕ _pr ], 0≤t≤T ₁ ,

;Where

;

ω _CR = ω ₁ -ω _G - intermediate (difference) frequency;

ϕ _ol = ϕ ₁ -ϕ _G ,

which is supplied to the first inputs of the multipliers 55 and 56. The second input of the first multiplier 55 is supplied with a reference voltage from the output of the narrow-band filter 57 (Fig. 3.c)

U ₀ (t) = V ₀ ⋅cos (ω _pr t + ϕ _pr ).

At the output of the multiplier 55, a voltage is generated

U ₂ (t) = V _n ⋅sosϕ _K1 (t) + V _n ⋅cos [2ω _pr t + ϕ _K1 (t) + 2U _pr ],

,Where

,

from which the low-frequency voltage is allocated by the low-pass filter 58 (Fig. 3.d)

U _n (t) = V _n ⋅cosϕ _K1 (t), 0≤t≤T ₁ ,

proportional to the modulating code M (t) (Fig. 3.a). This voltage is supplied to the input of the computing unit 59, where, based on information from other GPS satellites, the coordinates (longitude and latitude) of the black box are determined, which are generated in the form of a modulating code M ₁ (t) in the modulating code generator 60.

The voltage U _n (t) from the output of the low-pass filter 58 is simultaneously supplied to the second input of the second multiplier 56, at the output of which a voltage is generated

U ₀ (t) = V ₂ ⋅cos (ω _pr t + ϕ _pr ) + V ₂ ⋅cos [(ω _pr t + 2ϕ _K1 (t) + ϕ _pr ] = 2V ₂ ⋅cos (ω _pr t + ϕ _pr ) = V ₀ ⋅cos (ω _pr t + ϕ _pr ),

; V₀=2V₂;Where

; V ₀ = 2V ₂ ;

2U _k1 (t) = {0, 2π}.

The modulating code M ₁ (t) enters through the delay line 61 to the first input of the adder 63, to the second input of which a modulating code M ₂ (t) is supplied from the output of the pseudo-random sequence generator (PSP) 62. The output of the adder 63 is formed by the total code (Fig. 3, d)

M _Σ (t) = M ₁ (t) + M ₂ (t).

Moreover, the delay time τ _{s of} the delay line 61 is selected equal to the duration T _{1 of the} modulating code M ₁ (t) (τ _s = T ₁ ).

The modulating code M ₂ (t) is the black box identification number and contains all the necessary information about the plane that crashed.

The total modulating code M _Σ (t) (Fig. 3.e) is fed to the second input of the phase manipulator 64, the first input of which is fed into harmonic oscillation U ₀ (t) (Fig. 3.e) from the output of the narrow-band filter 57. At the output phase manipulator 64 a complex signal is generated with phase manipulation (Fig. 3.e)

U ₂ (t) = V ₂ ⋅ [ω ₂ (t) + ϕ _K2 (t) + ϕ ₂ ], 0≤t≤T ₂ ,

where ω ₂ = ω _CR ; ϕ ₂ = ϕ _ol

ϕ _K2 (t) = {0, π} is the manipulated component of the phase, which displays the law of phase manipulation in accordance with the total modulating code M _Σ (t) (Fig. 3.e).

This signal after amplification in the power amplifier 65 through the duplexer 50 enters the transceiver antenna 49, is radiated by it, is captured by the receiving antennas 7-9, 66, 67 of the helicopter:

U ₃ (t) = V ₃ ⋅cos [ω ₂ ± Δω) t + ϕ _K2 (t) + ϕ ₃ ],

,

,

,

,

,

,

, 0≤t≤T₂,

, 0≤t≤T ₂ ,

where - V ₃ -V ₇ - the amplitude of the signal,

± Δω - instability of the carrier frequency of the signal due to the Doppler effect and other destabilizing factors;

R is the radius of the circle on which the antennas 8, 9, 66, 67 are placed;

λ is the wavelength;

Ω = 2πR is the rotation speed of the receiving antennas 8, 9, 66, 67 around the receiving antenna 7 (rotational speed of the helicopter rotor);

α, β — azimuth and elevation angle of the black box of the NW (Fig. 1).

The specified signal is supplied to the first inputs of the mixers 12-14, 68, 69, the second inputs of which are supplied with the voltage of the first local oscillator 11 of a ramp frequency

U _G1 (t) = V _G1 ⋅cos (ω _D1 (t) + πγt ² + φ _r1], 0≤t≤T _P,

- скорость изменения частоты гетеродина.Where

- rate of change of the local oscillator frequency.

It should be noted that the search for PSK signals emitted by "black box" in a predetermined frequency band D1 is performed via adjustment assembly 10, which are periodically with period T _n sawtooth _G1 changes the frequency ω LO 11. The first can be used as the adjustment unit 10 sawtooth voltage generator.

It should also be noted that the search for FMN signals emitted by the "black box" is carried out in the area of the alleged crash site of the aircraft, where the helicopter is directed.

At the output of the mixers 12-14, 68 and 69, a voltage of combination frequencies is generated. Amplifiers 17-19, 70 and 71 distinguish the voltage of the first intermediate frequency:

U _CR1 (t) = V _CR1 ⋅cos [(ω _CR1 ± Δω) t + ϕ _K (t) -πγt ² + γ _CR1 ],

,

,

,

,

,

,

, 0≤t≤T₂,

, 0≤t≤T ₂ ,

;Where

;

;

;

;

;

;

;

;

;

ω _CR1 = ω ₂ -ω _G1 - the first intermediate frequency;

ϕ _pr1 = ϕ ₃ -ϕ _G1 ;

voltage U _CR1 (t) can be represented as follows:

U _pr1 (t) = V _pr1 ⋅cos [(ω _pr1 ± Δω) t + ϕ _K (t) -πγt ² + ϕ _pr1 ] = V _pr1 ⋅M _Σ (t) ⋅cos [(ω _pr1 ± Δω) t -πγt ² + ϕ _pr1 ],

where M _Σ (t) is the total modulating code, in accordance with which the phase of harmonic oscillation is manipulated.

This voltage is applied to the input of the detector 20, namely, to the input of the delay line 37, the multiplier 38, and the phase shifter 36 by 90 °. The output of the latter forms a voltage

U _CR6 (t) = V _CR1 ⋅M (t) ⋅cos [(ω _CR1 ± Δω) t-πγt ² + ϕ _CR1 + 90 °] = V _CR1 ⋅M (t) ⋅sin [(ω _CR1 ± Δω) t-πγt ² + ϕ _pr1 ],

which is fed to the first input of the multiplier 40.

A voltage is generated at the output of the delay line 37

U _CR7 (t) = V _{CR1 ⋅} M (t-τ ₁ ) ⋅cos [(ω _CR1 ± Δω) (t-τ ₁ ) -πγ (t-τ) ² + ϕ _CR1 ],

where τ ₁ is the delay time of the delay line 37.

The delay time τ _{1 of} the delay line 37 is selected from the following considerations:

τ ₁ <τ ₇ , (ω _pr1 ± Δω) τ ₁ = 2πK, K = 1, 2, 3,

where τ ₇ - the duration of the elementary parcels (clock period).

The _delayed voltage U _CR7 (t) is supplied to the input of the second phase shifter 39 by 90 °, at the output of which a voltage is generated

U _CR8 (t) = V _{CR1 ⋅} M (t-τ ₁ ) ⋅sin [(ω _CR1 ± Δω) (t-τ ₁ ) -πγ (t-τ) ² + ϕ _CR1 ].

This voltage is supplied to the second input of the multiplier 40. The result of the multiplication of the voltages U _CR1 (t) and U _CR7 (t), U _CR6 (t) and U _CR8 (t) are complex vibrations, of which the following low-frequency filters are allocated 41 and 42 voltage:

U _H1 (t) = V _H ⋅ M (t) ⋅ M (t-τ ₁ ) ⋅cos [(ω _pr1 ± ω) τ ₁ ],

U _H2 (t) = V _H ⋅ M (t) ⋅ M (t-τ ₁ ) ⋅sin [(ω _pr1 ± ω) τ ₁ ],

.Where

.

These voltages after squares 43 and 44 take the following form:

,

,

,

,

and enter the two inputs of the adder 45, the output of which is formed by the total voltage:

,

,

which is fed to the input of the threshold block 46, where it is compared with a threshold voltage V _then and if it is exceeded, a decision is made to detect the PSK signal.

Upon detection of the PSK signal of the "black box" at the output of the detector 20, a constant voltage is generated, which is supplied to the control input of the tuning unit 10, turning it off, to the control input of the key 22, opening it, and to the input of the delay line 21. The key 22 is always in the initial state The delay time x _{3 of} the delay line 21 is selected so that it is possible to fix the detected PSK signal and analyze its parameters.

When you turn off the tuning unit 10 amplifiers 17-19, 70 and 71 the following voltages are allocated:

U _pr9 (t) = V _pr1 ⋅cos [(ω _pr1 ± Δω) t + ϕ _K (t) + ϕ _pr1 ],

,

,

,

,

,

,

, 0≤t≤T₂.

, 0≤t≤T ₂ .

The voltage U _pr9 (t) from the output of the amplifier 17 of the first intermediate frequency through the public key 22 is supplied to the first input of the mixer 24, the second input of which is supplied with the voltage of the second local oscillator 23 with a stable frequency ω _Г2

U _Г2 (t) = V _Г2 ⋅cos (ω _Г2 t + ϕ _Г2 ).

At the output of the mixer 24, voltages of combination frequencies are generated. Amplifier 25 isolates the voltage of the second intermediate frequency

U _pr14 (t) = V _pr14 ⋅cos [(ω _pr2 ± Δω) t + ϕ _K (t) + ϕ _pr2 ],

;Where

;

ω _CR2 = ω _CR1- ω _G2 - the second intermediate frequency;

ϕ _CR2 = ϕ _CR1 -ϕ _G2 ,

which is fed to the input of the analyzer 4 parameters of the received FMN signal, where the duration τ _{e of the} elementary packages from which the FMN signal is composed, their number N (Tc = N⋅τ _e ) and the phase-shift law in accordance with the total modulating code M _Σ (t ) This allows you to evaluate the identity of the aircraft in a crash, and its location.

The voltage U _pr14 (t) from the output of the amplifier 25 of the second intermediate frequency is simultaneously supplied to the second inputs of the multipliers 26, 27, 72 and 73 of direction-finding channels, the first inputs of which receive the voltage U _pr10 (t), U _pr11 (t), U _pr12 ( t) and U _pr13 (t) from the outputs of amplifiers 18, 19, 70 and 71, of the first intermediate frequency, respectively. At the outputs of the multipliers 26, 27, 72 and 73, phase-modulated (FM) voltages are formed at a stable frequency ω _{Г2 of the} second local oscillator 23:

,

,

,

,

,

,

, 0≤t≤T₂,

, 0≤t≤T ₂ ,

;Where

;

;

;

;

;

;

;

which are distinguished by narrow-band filters 28, 29, 74 and 75 with a tuning frequency of ω _H = ω _G2 .

и

соответствуют диаметрально противоположным расположениям антенн 8 и 9, 66 и 67 на концах лопастей несущего винта вертолета.The signs "+" and "-" before the quantities

and

correspond to diametrically opposite locations of the antennas 8 and 9, 66 and 67 at the ends of the rotor blades of the helicopter.

Therefore, useful information about the azimuth α and the elevation angle β of the black box is transferred to the stable frequency ω _{Г2 of the} second local oscillator 23. Therefore, the instability ± Δω of the carrier frequency caused by the Doppler effect and other destabilizing factors, and the type of modulation (manipulation) of the received FMN signal, emitted by the "black box" do not affect the result of direction finding, thereby increasing the accuracy of determining the location of the "black box".

и называемая индексом фазовой манипуляции, характеризует максимальное значение отклонения фазы сигналов, принимаемых антеннами 8 и 9, 66 и 67, относительно фазы сигнала, принимаемого неподвижной антенной 7.Moreover, the value that is part of these fluctuations

and called the phase shift keying index, characterizes the maximum phase deviation of the signals received by antennas 8 and 9, 66 and 67, relative to the phase of the signal received by the fixed antenna 7.

Direction finding device 3 is all the more sensitive to changes in angles α and β, the larger the relative size of the measuring base R / λ. However, with increasing R / λ, the values of the angular coordinates α and β decrease at which the phase difference exceeds 2π, i.e. there is an ambiguity in the reading of the angles α and β.

Therefore, for R / λ> 1/2, the ambiguity of the reference angles α and β occurs. The elimination of this ambiguity by reducing the R / λ ratio usually does not justify itself, since the main advantage of a wide-base system is lost. In addition, in the range of meter and especially decimeter waves, it is partially impossible to take small values of R / λ due to design considerations.

To increase the accuracy of direction finding of the "black box" in the horizontal (azimuthal) and vertical (angular-linear) planes, receiving antennas 8 and 9, 66 and 67 are placed at the ends of the rotor blades of the helicopter. The displacement of signals from two diametrically opposite antennas 8 and 9, 66 and 67, located at the same distance R from the axis of rotation of the rotor, causes phase modulation, obtained using two receiving antennas rotating in a circle, the radius R _{1 of} which is twice as large ( R ₁ = 2R).

Indeed, at the output of multipliers 30 and 76, harmonic voltages are formed:

U ₁₂ (t) = V ₁₂ ⋅cos (Ω-α) t,

U ₁₃ (t) = V ₁₃ ⋅cos (Ω-α) t,

;Where

;

;

;

with phase modulation index

, R₁=2R,

, R ₁ = 2R,

which are allocated by narrow-band filters 32, 78 and are fed to the first input of the phase meters 34 and 80, the second input of which is supplied with the voltage of the reference generator 16

U ₀ (t) = V ₀ ⋅cosΩt.

Phasometers 34 and 80 provide an accurate but ambiguous measurement of azimuth α and elevation angle β. To eliminate the ambiguities in the reading of the angles α and β, it is necessary to reduce the phase modulation index without decreasing the R / λ ratio. This is achieved by using autocorrelators consisting of delay lines 31 and a phase detector 33, from a delay line 77 and a phase detector 79, which is equivalent to reducing the phase modulation index to

,

,

where d ₁ <R

At the output of the autocorrelators, voltages are formed:

U ₁₄ (t) = V ₁₂ ⋅cos (Ω-α) t,

U ₁₅ (t) = V ₁₃ ⋅cos (Ω-α) t,

with a phase modulation index Δϕ _w2 , which are supplied to the first input of the phase meters 35 and 81, respectively, to the second input of which the voltage U ₀ (t) of the reference oscillator 16. The phase meters 35 and 81 provide a rough but unambiguous measurement of azimuth α and elevation angle β.

From the measured values of the azimuth α and elevation angle β, knowing the height h of the helicopter flight, the location of the black box of the plane that crashed is easily determined (Fig. 1).

The telemetry device 6 is designed to transmit the received information to the rescue service, where certain measures are taken to remove the "black box".

After the time τ _{s, the} constant voltage from the output of the delay line 21 is supplied to the control input of the detector 20 (threshold block 46) and resets its contents to zero. In this case, the key 22 is closed, and the telemetry unit 10 is turned on, i.e. they are translated into their original positions.

When the next black box is discovered in the crash area of another aircraft, the operation of the proposed complex occurs in a similar way.

Thus, the proposed complex in comparison with the prototype and other technical solutions of a similar value provides an increase in the efficiency and reliability of the detection of an airplane that crashed. This is achieved by using two additional direction finding channels and a black box with alarm.

Moreover, two additional direction-finding channels make it possible to determine the elevation angle β of the “black box”. By measuring the azimuth α and elevation angle β and knowing the altitude h of the helicopter, you can determine the location of the black box. And the presence of an alarm allows you to do this quickly and reliably.

In this case, the direction-finding device placed on board the helicopter is invariant to the type of modulation (manipulation) and instability of the carrier frequency of the received FMN signals emitted by the black box.

Claims (1)

A helicopter radio engineering complex for detecting a “black box” with the signaling of a crashed aircraft, containing an antenna device, a receiver, an analyzer of parameters of the received signal, a device for storing and processing received information, the second input of which is connected to the output of the antenna device through a direction finding device, and a telemetry a device whose output is the output of the complex, while the receiver is made in the form of a series-connected receiving ant of the first mixer, the second input of which is connected through the first local oscillator to the output of the tuning block, the amplifier of the first intermediate frequency, the detector, the second input of which is connected to its output through the first delay line, the key, the second input of which is connected to the output of the amplifier of the first intermediate frequency, second a mixer, the second input of which is connected to the output of the second local oscillator, and an amplifier of the second intermediate frequency, the output of which is the output of the receiver, the control input of the tuning unit is connected to the output of an external amplifier, which is made in the form of a first intermediate frequency of the third delay line, a fourth multiplier, connected in series to the output of the amplifier, the second input of which is connected to the output of the amplifier of the first intermediate frequency, the first low-pass filter, the first quad, adder and threshold block, the second input of which is through the first the delay line is connected to its output, and the output is connected to the control input of the tuning unit and to the first key input, connected in series to the amplifier output of the first industrial daily frequency of the first phase shifter 90 °, the fifth multiplier, the second input of which through the second phase shifter 90 ° is connected to the output of the third delay line, the second low-pass filter and the second quadrator, the output of which is connected to the second input of the adder, the direction finding device is made in the form of two direction finding channels, each of which consists of a series-connected receiving antenna, a mixer, the second input of which is connected to the output of the first local oscillator, an amplifier of the first intermediate frequency, a multiplier, the second input of which is connected to the output of the amplifier of the second intermediate frequency and the narrow-band filter, the third multiplier is connected in series to the output of the first narrow-band filter, the second input of which is connected to the output of the second narrow-band filter, the third narrow-band filter and the first phase meter, the second are connected in series to the output of the second narrow-band filter delay lines, the first phase detector, the second input of which is connected to the output of the second narrow-band filter, and the second phase meter, the second input of the first and Each phase meter is connected to the output of the reference generator, and the outputs are connected to a device for storing and processing the received information, the antenna device contains three receiving antennas, the receiving antenna of the receiver is located above the rotor hub of the helicopter, the receiving antennas of the direction-finding device are located at the ends of the first and second rotor blades of the helicopter, the engine is kinematically connected with the helicopter rotor and the reference generator, characterized in that it is equipped with two additional direction finding channels and a “black box” m ”with synchronization, and each of the additional direction-finding channels consists of a series-connected receiving antenna, a mixer, the second input of which is connected to the output of the first local oscillator, an amplifier of the first intermediate frequency, a multiplier, the second input of which is connected to the output of the amplifier of the second intermediate frequency, and a narrow-band filter , the sixth multiplier is connected to the output of the fourth narrow-band filter, the second input of which is connected to the output of the fifth narrow-band filter, the sixth narrow filter and the third phase meter, the fourth delay line, the second phase detector, the second input of which is connected to the output of the fifth narrow-band filter, and the fourth phase meter, the second inputs of the third and fourth phase meters are connected to the output of the reference oscillator, and the outputs are connected to the output of the fifth narrow-band filter to the device for storing and processing the received information, receiving antennas of additional direction finding channels are located at the ends of the third and fourth rotor blades, “black box ”with an alarm system that, in the event of an airplane crash, is thrown with a parachute from the compartment and lands or lands on the sea surface, emitting electromagnetic waves and sound signals, is placed in the compartment in the tail section of the aircraft and is automatically thrown, while opening the parachute the crane and through the intake pipes from the chamber, compressed air enters the rubber chamber, which is inflated and turns into a shock absorber - a pillow, electromagnetic waves emitted by the “black box” and sound New signals are also emitted at a depth, the “black box” contains a duplexer connected in series, the input-output of which is connected to the transceiver antenna, a mixer, the second input of which is connected to the local oscillator output, an intermediate frequency amplifier, a second multiplier, the second input of which is connected to the output of the lower filter frequencies, a narrow-band filter, a first multiplier, the second input of which is connected to the output of an intermediate-frequency amplifier, a low-pass filter, a computing unit, a modulating code generating unit, a delay line, an adder, the second input of which is connected to the output of the pseudo-random sequence generator, a phase manipulator, the second input of which is connected to the output of the narrow-band filter, and a power amplifier, the output of which is connected to the second input of the duplexer.

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