RU2309424C1 - Device for measurement of distance between sea vessels - Google Patents

Abstract

FIELD: aviation engineering.

SUBSTANCE: device has on-ground automated system for controlling air traffic made in a special way, interrogation unit and re-translator mounted on air vehicles and made in a special manner as well. Autonomous duplication is used for measuring distance between flying vehicles.

EFFECT: widened functional abilities.

6 dwg

Description

The proposed device relates to the field of aviation technology and is intended to determine the distance between aircraft in flight.

Known devices and systems that ensure the flight safety of aircraft (ed. Certificate of the USSR No. 293175, 926611, 1300531, 1792541; RF patents No. 211505, 2124760, 2126976, 2131622, 2134910, 2134911, 2256125; US patents No. 37.714654, 4400780, 4495580, 4789965; UK patent No. 2232316; French patent No. 2037222; EP patents No. 0283723, 0396071, 0707220; Anodina TG et al. Automation of air traffic control. - M .: Transport, 1992, p.213 -218 and others).

Of the known devices and systems closest to the proposed one is a "Device for determining the distance between aircraft" (RF patent No. 2256195, G01S 13/93, 2003), which is selected as a prototype.

The specified device is designed to prevent collision of aircraft and increase flight safety by determining the true distance between aircraft, taking into account the height of their flight. If the distance becomes less than a certain threshold value, a dispatcher warning signal is generated, calling to pay attention to the movement of aircraft (aircraft), information about which is recorded in the corresponding tracking channels.

However, the known device provides a determination of the true distance between aircraft using a ground-based automated air traffic control system. And if the distance between the aircraft becomes less than a certain threshold value, the decision is made by the dispatcher. This circumstance is associated with the so-called human factor and other negative phenomena.

In world practice, cases of unscrupulous attitude of dispatchers to their functional duties are known, when aviation accidents occurred due to the fault of the dispatch service. Therefore, the urgent task of autonomous duplication arises when determining the distance between aircraft using equipment installed on the aircraft themselves.

An object of the invention is to expand the functionality of the device by autonomous duplication in determining the distance between aircraft.

The problem is solved in that a device for determining the distance between aircraft, containing a series-connected first azimuth meter, a first adder, the second input of which is connected to the output of the second azimuth meter, a cosine calculation unit, a seventh multiplication unit, a fourth adder, a second square root calculation unit and an indicator, sequentially connected to the first height meter, the first multiplication unit, the second input of which is connected to the output of the first height meter, the second adder, second the swarm input of which is connected to the output of the second multiplication unit, the sixth multiplication unit, the second input of which is connected to the output of the third adder, and the first square root calculation block, the output of which is connected to the second input of the seventh multiplication unit, the first inclined range meter and the second multiplication unit connected in series the second input of which is connected to the output of the first slant range meter, and the output is connected to the second input of the fourth adder, the third input of which is connected through the third multiplication unit the outputs of the first and second height meters, the second height meter, the fourth multiplication unit, the second input of which is connected to the output of the second height meter, the second adder, the second input of which is connected to the output of the fifth multiplication unit, and the second inclined range meter and the fifth a multiplication unit, the second input of which is connected to the output of the second slant range meter, and the output is connected to the fourth input of the fourth adder, equipped with a request unit and a retran an amplifier, which are installed on aircraft, the request unit is made in the form of serially connected master oscillator, phase manipulator, the second input of which is connected to the output of the modulating code generator, the first mixer, the second input of which is connected to the output of the first local oscillator, amplifier of the first intermediate frequency, the first power amplifier, the first duplexer, the input-output of which is connected to the first transceiver antenna, the second power amplifier, the second mixer, the second input of which is connected with the output of the second local oscillator, the amplifier of the second intermediate frequency, the multiplier, the low-pass filter, the extreme controller and the adjustable delay unit, the second input of which is connected to the output of the phase manipulator, the first output is connected to the second input of the multiplier, and the second output is connected to the range indicator, repeater made in the form of series-connected third local oscillator, third mixer, amplifier of the third intermediate frequency, fourth power amplifier, second duplexer, input-output of which It is connected with a second transceiver antenna, and a third power amplifier, the output of which is connected to the second input of the third mixer.

A geometric arrangement of two aircraft BC ₁ and BC ₂ and a ground-based automated air traffic control system is shown in FIG. The structural diagram of a device for determining the distance between aircraft is presented in figure 2. The block diagram of the request block is shown in Fig.3. The structural diagram of the repeater is shown in Fig.4. A frequency diagram illustrating signal conversion is shown in FIG. 5. Timing diagrams explaining the operation of the request block and the relay are shown in Fig.6.

The device for determining the distance between aircraft contains a series-connected first azimuth meter 1, a first adder 7, the second input of which is connected to the output of the second azimuth meter 4, cosine calculation unit 13, seventh multiplication unit 18, fourth adder 19, second square root calculation unit 20 and indicator 21, sequentially connected to the first height meter 2, the first multiplication unit 8, the second input of which is connected to the output of the first height meter 2, the second adder 14, the second input of which is connected connected to the output of the second multiplication unit 9, the sixth multiplication unit 16, the second input of which is connected to the output of the third adder 15, and the first square root calculation unit 17, the output of which is connected to the second input of the seventh multiplication unit 18, the first inclined range meter 3 connected in series and the second block 9 multiplication, the second input of which is connected to the output of the first meter 3 of inclined range, and the output is connected to the second input of the fourth adder 19, the third input of which through the third block 10 of multiplication is connected to the output the first 2 and second 5 height meters, sequentially connected to the second flight height meter 5, a fourth multiplication unit 11, the second input of which is connected to the output of the second height meter 5, and a third adder 15, the second input of which is connected to the output of the fifth multiplication unit 12, in series a second slant range meter 6 and a fifth multiplication unit 12, the second input of which is connected to the output of the slope range meter 6, and the output is connected to the fourth input of the fourth adder 19.

The request unit contains serially connected master oscillator 22, a phase manipulator 24, the second input of which is connected to the output of the modulating code generator 23, the first mixer 26, the second input of which is connected to the output of the first local oscillator 25, an amplifier 27 of a first intermediate frequency, a first power amplifier 28, a first a duplexer 29, the input-output of which is connected to the first transceiver antenna 30, the second power amplifier 31, the second mixer 33, the second input of which is connected to the output of the second local oscillator 32, the multiplier 34 of the second intermediate accurate frequency multiplier 36, a filter 37 lowpass extreme regulator 38 and variable delay unit 39, a second input coupled to an output of the phase arm 24, a first output connected to a second input of multiplier 36 and a second output connected to an indicator 40 range.

The repeater comprises serially connected a third local oscillator 44, a third mixer 45, an amplifier 46 of a third intermediate frequency, a fourth power amplifier 47, a second duplexer 42, the input-output of which is connected to the second transceiver antenna 41, and a third power amplifier 43, the output of which is connected to the second input third mixer 45.

The device operates as follows.

On the ground-based automated air traffic control system, the first 1 and second 4 aircraft azimuth meters aircraft ₁ and aircraft ₂ determine the azimuths α ₁ and α _2, respectively (figure 1). The signal α ₁ proportional to the azimuth of the first BC ₁ is supplied to the first input of the first adder 7, the second input of which receives the signal α ₂ proportional to the azimuth of the second BC ₂ . The signal at the output of the first adder 7 is proportional to the difference in azimuths of the first BC ₁ and second BC ₂ : α ₁ -α ₂ . This signal is input to the cosine calculation unit 13, at the output of which the signal is proportional to cos (α ₁ -α ₂ ). This signal is supplied to the first input of the seventh multiplication block 18.

The first 2 and second 5 flight altitude meters BC ₁ and BC ₂ determine the flight altitudes h ₁ and h _2, respectively. The signal h ₁ proportional to the flight altitude of the first BC ₁ is supplied to the first and second inputs of the first multiplication block 8 and to the first input of the third multiplication block 10. The signal proportional to h ₁ ² from the output of the first block 8 multiplication is supplied to the first input of the second adder 14.

The signal h ₂ proportional to the flight altitude of the second aircraft ₂ , is fed to the first and second inputs of the fourth block 11 multiplication and to the second input of the third block 10 multiplication. The signal proportional to h ₂ ² from the output of the fourth block 11 multiplication is supplied to the second input of the third adder 15.

The first 3 and second 6 tilt range meters to aircraft BC ₁ and BC ₂ determine the tilt range d ₁ and d _2, respectively. The signal d ₁ proportional to the slant range to the first BC ₁ is fed to the first and second inputs of the second multiplication block 9, the output of which a signal proportional to d ₁ ² is fed to the second input of the adder 14 and to the second input of the fourth adder 19.

The signal d ₂ proportional to the slant range to the second BC ₂ is fed to the first and second inputs of the fifth multiplication block 12, the output of which a signal proportional to d ₂ ² is fed to the second input of the third adder 15 and the fourth input of the fourth adder 19.

At the output of the second adder 14, the signal is proportional to the difference of the squares of the inclined range d ₁ to the first aircraft BC ₁ and its height h ₁ : d ₂ ² -h ₂ ² . This signal is fed to the second input of the sixth multiplication unit 16, the output of which is a signal proportional to

enters the input of the first block 17 calculating the square root, the output of which is a signal proportional to

arrives at the second input of the seventh multiplication block 18, the first input of which receives a signal proportional to cos (α ₁ -α ₂ ). From the output of the seventh multiplication block 18, a signal proportional to

arrives at the first input of the fourth adder 19.

The third input of the fourth adder 19 receives a signal from the output of the third multiplication unit 10, which is proportional to the product of the height h _{1 of the} first aircraft BC ₁ and the height h _{2 of the} second aircraft BC ₂ : h ₁ · h ₂ .

The output of the fourth adder 19, the signal is proportional to the square of the distance between the first BC ₁ and the second aircraft ₂ aircraft:

This signal is fed to the input of the second block 20 calculating the square root, from the output of which the signal

proportional to the distance between the first BC ₁ and the second aircraft ₂ aircraft, enters the indicator 21 display the air situation and is displayed in the tracking form.

At the same time on the first aircraft BC ₁ or on the second aircraft BC _{2, the} master oscillator 22 generates a high-frequency oscillation (Fig.6, a)

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

where U _c , ω _s , φ _c , T _c - amplitude, carrier frequency, initial phase and duration of high-frequency oscillations,

which is fed to the first input of the phase manipulator 24, to the second input of which a modulating code M (t) is supplied (Fig. 6, b). As the latter, a pseudo-random sequence (PSP) of maximum duration or an m-sequence is used. This m-sequence is generated using a shift register encompassed by logical feedbacks. Feedback is carried out by adding modulo two output voltages of two or more stages and applying the resulting voltage to the input of the first stage. The repetition period (duration) of such a code sequence is m = 2 ⁿ -1, where n is the number of stages of the shift register.

The output of the phase manipulator 24 produces a complex signal with phase shift keying (PSK) (Fig.6, c)

u ₁ (t) = U _c cos [ω _c t + φ _k (t) + φ _c ], 0≤t≤T _c ,

where φ _k (t) = {0, π} is the manipulated component of the phase, which displays the law of phase manipulation in accordance with the modulating code M (t) (Fig.6, b), and φ _k (t) = const at kτ _Э < t <(k + 1) τ _Oe and can change abruptly at t = kτ _Oe , i.e. on the boundaries between elementary premises (k = 1, 2, ..., N);

τ _E , N - the duration and number of chips that make up a signal of duration T _C (T _C = Nτ _E ),

which is fed to the first input of the first mixer 26, to the second input of which the voltage of the first local oscillator 25

u _g1 (t) = U _g1 cos (ω _g1 t + φ _g1 ).

At the output of the first mixer 26, voltages of combination frequencies are generated. The amplifier 27 is allocated the voltage of the first intermediate (total) frequency (Fig.6, g)

u _CR1 (t) = U _CR1 cos [ω _CR1 t + φ _k (t) + φ _CR1 ], 0≤t≤T _c ,

Where

K ₁ - gear ratio of the mixer;

ω _pr1 = ω _s + ω _g1 = ω ₁ - the first intermediate (total) frequency;

φ _pr1 = φ _s + φ _g1 ,

which, after amplification in the power amplifier 28 through the duplexer 29 enters the transceiver antenna 30, is radiated by it at a frequency ω ₁ = ω _pr1 , is captured by the transceiver antenna 41 of the relay installed on another aircraft, and through the duplexer 42 and the power amplifier 43 goes to the first the input of the third mixer 45. The voltage of the third local oscillator is supplied to the second input of the mixer 45

u _g3 (t) = U _g3 cos (ω _g3 t + φ _g3 ).

At the output of the mixer 45, voltages of combination frequencies are generated. Amplifier 46 is allocated the voltage of the second intermediate (differential) frequency

u _CR2 (t) = U _CR2 cos [ω _CR2 t + φ _k (t) + φ _CR2 ), 0≤t≤T _c ,

Where

_np2 ω = ω ₁ -ω _z3 = ω ₂ - second intermediate (difference) frequency;

_WP2 cp = φ -φ _{pr1 r3}

which, after amplification in the power amplifier 47, enters through the duplexer 42 into the transceiver antenna 41, radiates it at the frequency ω ₂ , is captured by the transceiver antenna 30, and through the duplexer 29 and the power amplifier 31 enters the first input of the second mixer 33. The second input of the last voltage of the second local oscillator 32

U _g2 (t) = U _g2 cos (ω _g2 t + φ _g2 ).

At the output of the mixer 33, voltages of combination frequencies are generated. The amplifier 34 is allocated the voltage of the third intermediate (differential) frequency (Fig.6, d)

u _pr3 (t-τ _Z ) = U _pr3 cos [ω _pr3 (t-τ _Z ) -φ _to (t-τ _Z ) + φ _pr3 ], 0≤t≤T _s ,

Where

_PR3 ω = ω _z2 -ω ₂ = ω _s - third intermediate (difference) frequency;

_PR3 cp = φ -φ _{r2 WP2,}

- время запаздывания ретранслированного сигнала;

- delay time of the relayed signal;

R is the distance between the aircraft;

C is the propagation velocity of radio waves,

which is supplied to the first input of the correlator 35. The voltage u ₁ (t) (Fig. 6 c) is supplied to the second input of the last from the output of the phase manipulator 24. The voltage u _pr3 (t-τ _З ) is supplied to the first input of the multiplier 36, to the second the input of which a voltage u ₁ (t-τ) is supplied from the output of the adjustable delay unit 39, where τ is the delay time of the adjustable delay unit 39. The voltage obtained at the output of the multiplier is passed through a low-pass filter 37, at the output of which a cross-correlation function R (τ) is formed.

The extreme controller 38 connected to the output of the low-pass filter 37 acts on the adjustable delay unit 39 and maintains τ = τ _З , which corresponds to the maximum value of R (τ). The range indicator 40 associated with the adjustable delay unit 39 allows you to directly read the measured range value.

If the range (distance between aircraft) becomes less than a certain threshold, then the crew of the aircraft makes an appropriate decision to ensure flight safety.

Thus, the proposed device in comparison with the prototype provides an autonomous determination of the distance between the aircraft, thereby ensuring duplication and improving air traffic safety. Therefore, the functionality of the device is expanded.

Claims (1)

A device for determining the distance between aircraft, including a ground-based automated air traffic control system, comprising a series-connected first azimuth meter, a first adder, the second input of which is connected to the output of the second azimuth meter, cosine calculation unit, seventh multiplication unit, fourth adder, second calculation unit square root and indicator, sequentially connected to the first height meter, the first multiplication unit, the second input of which is connected to the output of the second height meter, the second adder, the second input of which is connected to the output of the second multiplication unit, the sixth multiplication unit, the second input of which is connected to the output of the third adder, and the first square root calculation unit, the output of which is connected to the second input of the seventh multiplication unit, the first connected in series slant range meter and a second multiplication unit, the second input of which is connected to the output of the first slope range meter, and the output is connected to the second input of the fourth adder, the third input to The second through the third multiplication unit is connected to the outputs of the first and second height meters, the second height meter, the fourth multiplication unit, the second input of which is connected to the output of the second height meter, and the third adder, the second input of which is connected to the output of the fifth multiplication unit, are connected in series a second slant range meter and a fifth multiplication unit, the second input of which is connected to the output of the second slant range meter, and the output is connected to the fourth input of the fourth the adder, characterized in that it is equipped with a request unit and a repeater that are installed on aircraft, the request unit is made in the form of serially connected master oscillator, phase manipulator, the second input of which is connected to the output of the modulating code generator, the first mixer, the second input of which connected to the output of the first local oscillator, the amplifier of the first intermediate frequency, the first power amplifier, the first duplexer, the input-output of which is connected to the first transceiver antenna, power amplifier, a second mixer, the second input of which is connected to the output of the second local oscillator, an amplifier of the second intermediate frequency, a multiplier, a low-pass filter, an extreme controller and an adjustable delay unit, the second input of which is connected to the output of the phase manipulator, the first output is connected to the second input of the multiplier and the second output is connected to the range indicator, the repeater is made in the form of series-connected third local oscillator, third mixer, amplifier of the third intermediate part you fourth power amplifier, a second duplexer, the input-output of which is connected with a second transceiver antenna and a third amplifier, whose output is connected to a second input of the third mixer.

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