Device for measurement of distance between sea vessels

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

 

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

Known devices and systems that ensure the safety of aircraft (ed. mon. The USSR№№293175, 926611, 1300531, 1792541; patents of the Russian Federation№№2111505, 2124760, 2126976, 2131622, 2134910, 2134911, 2256125; U.S. patent No. 3.714654, 4400780, 4495580, 4789965; UK patent No. 2232316; French patent No. 2037222; patent EP No. 0283723, 0396071, 0707220; Anodina YEAR and other automation of air traffic control. - M.: Transport, 1992, s-218, etc.).

Of the known devices and systems closest to the proposed 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 a collision between aircraft and increase aviation safety by determining the true distance between aircraft with the height of their flight. If the distance becomes less than a certain threshold value, then a signal is generated to alert the Manager calling to pay attention to the movement of aircraft)on which information is recorded in the respective channels of support.

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

In world practice there are known cases of unfair relationship managers to their functional duties, when the fault dispatch service was an aviation disaster. There is thus an urgent task of the Autonomous duplication in determining the distance between aircraft using equipment installed on the aircraft.

An object of the invention is to expand the functional capabilities of the device by means of an Autonomous duplication when determining distances between aircraft.

The problem is solved in that the device for determining the distance between aircraft, containing series-connected first azimuth meter, the first adder, a second input connected to the output of the second azimuth meter, the unit for computing the cosine, the seventh block multiplication, the fourth adder, a second unit for computing the square root and the indicator consistently included the first meter of height, the first block multiplication, a second input connected to the output of the first meter high is you, a second adder, a second input connected to the output of the second block multiplication, the sixth block multiplication, a second input connected to the output of the third adder, and the first unit for computing the square root, the output of which is connected to a second input of the seventh block multiplication of series-connected first meter slant range and the second block multiplication, a second input connected to the output of the first meter slant range, and the output connected to the second input of the fourth adder, the third entrance through which the third block multiplication is connected to the outputs of the first and second meter height, cascaded second meter height, the fourth block multiplication, a second input connected to the output of the second meter height, and the third adder, a second input connected to the output of the fifth block multiplication, and cascaded second meter slant range and the fifth block multiplication, a second input connected to the output of the second meter slant range, and the output connected to the fourth input of the fourth adder, provided the request block and relay that are installed on aircraft, the block query is executed in the form of cascaded oscillator, the phase manipulator, a second input connected to what hodom generator modulating code, a first mixer, a second input connected to the output of the first local oscillator, amplifier first intermediate frequency, a first amplifier, a first duplexer, the input-output of which is connected with the first transmitting antenna, the second amplifier, a second mixer, a second input connected to the output of the second local oscillator, the amplifier of the second intermediate frequency, multiplier, lowpass filter, extreme regulator and adjustable delay unit, a second input connected to the output of the phase manipulator, a first output connected to a second input of the multiplier, and a second output connected to the indicator range, the relay is made in the form of series-connected third lo, the third mixer, the amplifier of the third intermediate frequency, the fourth amplifier, the second duplexer, the input-output of which is connected with the second transmitting-receiving antenna, and the third amplifier, the output of which is connected to a second input of the third mixer.

The geometric arrangement of the two aircraft BC1and g2and ground-based automated system of air traffic control is depicted in figure 1. The structural scheme of the device for determining the distance between aircraft is presented in figure 2. Structural block circuit diagram of the query image is the wife of figure 3. Block diagram of the repeater shown in figure 4. Frequency chart illustrating the conversion of the signals shown in figure 5. Timing diagrams explaining the operation request block and relay shown in Fig.6.

Device for determining the distance between the aircraft contains consistently included the first 1 meter azimuth, the first adder 7, a second input connected to the output of the second meter 4 azimuth, block 13 compute the cosine, the seventh block 18 multiplication, the fourth adder 19, the second block 20 calculate the square root and the indicator 21, consistently included the first 2 meter height, the first multiplication unit 8, a second input connected to the output of the first 2 meter height, the second adder 14, a second input connected to the output of the second unit 9 multiplication, the sixth block 16 multiplication, the second input is connected to the output of the third adder 15, and the first block 17 calculate the square root, the output of which is connected to a second input of the seventh block 18 multiplication, consistently included the first 3 meter slant range and the second unit 9 multiplication, a second input connected to the output of the first 3 meter slant range, and the output connected to the second input of the fourth adder 19, the third entrance through which the third block 10 multiplication connected with in the course of the first 2 and the second 5 meter height, cascaded second 5 meter altitude, the fourth block 11 multiplication, a second input connected to the output of the second 5 meter height, and the third adder 15, a second input connected to the output of the fifth block 12 multiplication of series-connected second 6 meter slant range and the fifth block 12 multiplication, a second input connected to the output of the 6 meter slant range, and the output connected to the fourth input of the fourth adder 19.

The request block contains cascaded master oscillator 22, the phase arm 24, a second input connected to the output of the generator 23 modulating code, the first mixer 26, a second input connected to the output of the first local oscillator 25, the amplifier 27, the first intermediate frequency, a first amplifier 28 power, the first duplexer 29, the input-output of which is connected with the first transmitting-receiving antenna 30, a second amplifier 31 power, a second mixer 33, a second input connected to the output of the second local oscillator 32, a multiplier 34, a second intermediate frequency, a multiplier 36, a filter 37 of the lower frequencies, extreme regulator 38 and the block 39 adjustable delay, a second input connected to the output of the phase manipulator 24, a first output connected to a second input of multiplier 36, and a second output connected to the indicator 40 DALnet is.

The repeater contains cascaded third local oscillator 44, a third mixer 45, the amplifier 46 to a third intermediate frequency, the fourth amplifier 47 power, a second duplexer 42, the input-output of which is connected with the second transmitting-receiving antenna 41, and the third amplifier 43 power, the output of which is connected to a second input of the third mixer 45.

The device operates as follows.

For ground-based automated system of air traffic control the first 1 and second 4 meters azimuth of aircraft SU1and g2determine azimuths α1and α2respectively (figure 1). Signal α1proportional to the azimuth of the first BC1goes to the first input of the first adder 7, the second input of which receives the signal α2proportional to the azimuth of the second BC2. The signal at the output of the first adder 7 is proportional to the difference of the azimuths of the first BC1and second SU2: α12. This signal is fed to the input of block 13 compute the cosine, the output of which a signal proportional to cos(α12). This signal is fed to the first input of the seventh block 18 of the multiplication.

The first 2 and the second 5 meters altitude aircraft BC1and g2determine the altitude h1and h2respectively. Signal is l h 1proportional to the height of flight of the first BC1goes to the first and second inputs of the first multiplication unit 8 and to the first input of the third block 10 multiplication. The signal proportional to h12with the output of the first multiplication unit 8 is supplied to the first input of the second adder 14.

The signal h2proportional to the altitude of the second aircraft2goes 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 h22with the output of the fourth unit 11 of the multiplication is supplied to the second input of the third adder 15.

The first 3 and second 6 meters slant range of the aircraft BC1and g2determine the slant range d1and d2respectively. The signal d1proportional to slant range to the first BC1goes to the first and second inputs of the second unit 9 multiplication, the output of which a signal proportional to d12goes to the second input of the adder 14 and to the second input of the fourth adder 19.

The signal d2proportional to slant range to the second SU2goes to the first and second inputs of the fifth block 12 multiplication, the output of which a signal proportional to d22comes to the second input of the third adder 15 and the fourth is the input of the fourth adder 19.

The output of the second adder 14 a signal proportional to the difference of the squares of the slant range d1before the first aircraft BC1height h1: d22-h22. This signal is applied to the second input of the sixth block 16 multiplication, the output of which a signal proportional to

is fed to the input of the first unit 17 calculate the square root, the output of which a signal proportional to

supplied to the second input of the seventh block 18 multiplication, at the first input of which receives a signal proportional to cos(α12). From the output of the seventh block 18 multiplication signal proportional to

arrives at the first input of the fourth adder 19.

The third input of the fourth adder 19 is supplied the output signal of the third block 10 multiplication, which is proportional to the product of the height h1the first aircraft BC1and height h2the second aircraft BC2: h1·h2.

The output of the fourth adder 19, the signal is proportional to the square of the distance between the first BC1and the second SU2aircraft:

This signal is fed to the input of the second unit 20 calculation of root Quadrat the th, since the output of which the signal

proportional to the distance between the first BC1and the second SU2aircraft, is supplied to the indicator 21 of the air situation display and is displayed in the form of support.

At the same time the first aircraft BC1or on the second aircraft SU2the master oscillator 22 is formed of a high-frequency oscillation (Fig.6, a)

uc(t)=Uccos(ωct+ϕc), 0≤t≤Tc,

where Ucthat ωwiththat ϕcTc- amplitude, carrier frequency, initial phase, and the duration of high-frequency oscillations,

which arrives at the first input of the phase arm 24, to the second input of which is applied a modulating code M(t) (6, b). As the latter uses a pseudo-random sequence (SRP) maximum duration or m-sequence. This m-sequence is generated by using a shift register, logical covered feedbacks. Feedback is provided by adding modulo two output voltages of two or more cascades and supply the resultant voltage to the input of the first stage. The repetition period (duration) of such code sequence m=2n-1, where n is the number of stages of the shift register.

The output phase is th manipulator 24 is formed a complex signal with phase shift keying (QPSK) (6, in)

u1(t)=Uccos[ωct+ϕk(t)+ϕc], 0≤t≤Tc,

where ϕk(t)={0, π} - manipulated component phases, reflecting the law of phase manipulation in accordance with the modulating code M(t) (6, b), and ϕk(t)=const kτE<t<(k+1)τEand may change abruptly at t=kτEi.e. at the boundaries between elementary parcels (K=1, 2, ..., N);

τEN - the length and number of basic assumptions which form the signal duration TC(TWith=NτE),

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

uG1(t)=UG1cos(ωG1t+ϕG1).

The output of the first mixer 26 are formed voltage Raman frequencies. The amplifier 27 is allocated to the first intermediate voltage (total) frequency (6, g)

uPR1(t)=UPR1cos[ωPR1t+ϕk(t)+ϕPR1], 0≤t≤Tc,

where

K1the gain of the mixer;

ωPR1withG11- first interim (total) frequency;

ϕPR1withG1,

which after amplification in the amplifier 28 power through the duplex is 29 is fed to transmitting antenna 30, radiates it into the air at a frequency of ω1PR1received transmitting-receiving antenna 41 of the relay installed on another aircraft, and through the duplexer 42 and the amplifier 43 power is supplied to the first input of the third mixer 45. To the second input of the mixer 45 is energized and the third lo

uG3(t)=UG3cos(ωG3t+ϕG3).

At the output of the mixer 45 is formed voltage Raman frequencies. The amplifier 46 is allocated to the second intermediate voltage (differential) frequency

uAC2(t)=UAC2cos[ωAC2t+ϕk(t)+ϕAC2), 0≤t≤Tc,

where

ωAC21G32the second intermediate (differential) frequency;

ϕAC2PR1G3,

which after amplification in the amplifier 47 power is supplied via the duplexer 42 in the transmitting-receiving antenna 41, radiates it into the air at a frequency of ω2received transmitting antenna 30 and through the duplexer 29 and the amplifier 31 is supplied to the first input of the second mixer 33. To the second input of the latter is energized and the second local oscillator 32

UT2(t)=UT2cos(ωT2t+ϕT2).

At the output of mixer 33 is formed voltage Raman frequencies. The amplifier 34 is allocated atragene third intermediate (differential) frequency (6, d)

uAC3(t-τC)=UAC3cos[ωAC3(t-τC)-ϕto(t-τC)+ϕAC3], 0≤t≤Twith,

where

ωAC3T22withthe third intermediate (differential) frequency;

ϕAC3T2AC2,

the time lag retransmitted signal;

R is the distance between aircraft;

C is the speed of propagation of radio waves,

which is supplied to the first input of the correlator 35. To the second input of the last voltage u1(t) (6 in) from the output of the phase manipulator 24. The voltage uAC3(t-τCrouted to the first input of the multiplier 36, to the second input of which a voltage u1(t-τ) from the output of the block 39 adjustable delay, where τ - time delay unit 39 adjustable delay. Obtained at the output of the multiplier voltage is passed through a filter 37 of the lower frequencies, the output of which is formed mutual-correlation function R(τ).

Extreme controller 38 connected to the output of the filter 37 of the lower frequencies, the effect on the block 39 adjustable delay and supports τ=τCthat corresponds to the maximum value of R(τ). Indicator range 40 associated with the block 9 adjustable delay, you can directly read the measured value range.

If range (the distance between the aircraft becomes less than a certain threshold, the aircraft crew will make the decision on the safety of flight.

Thus, the proposed device is compared with the prototype provides an Autonomous definition of the distance between aircraft, thus providing redundancy and increase air traffic safety. Therefore, the functionality of the device is expanded.

Device for determining the distance between aircraft, including ground-based automated system of air traffic control, containing series-connected first azimuth meter, the first adder, a second input connected to the output of the second azimuth meter, the unit for computing the cosine, the seventh block multiplication, the fourth adder, a second unit for computing the square root and the indicator consistently included the first meter of height, the first block multiplication, a second input connected to the output of the first meter of height, a second adder, a second input connected to the output of the second block multiplication, the sixth block multiplication, a second input connected to the output of the third adder and first the unit calculate the square root, the output of which is connected to a second input of the seventh block multiplication of series-connected first meter slant range and the second block multiplication, a second input connected to the output of the first meter slant range, and the output connected to the second input of the fourth adder, the third entrance through which the third block multiplication is connected to the outputs of the first and second meters height, cascaded second meter height, the fourth block multiplication, a second input connected to the output of the second meter height, and the third adder, a second input connected to the output of the fifth block multiplication of series-connected second meter slant range and the fifth block multiplication, a second input connected to the output of the second meter slant range, and the output connected to the fourth input of the fourth adder, characterized in that it is provided with a request block and relay that are installed on aircraft, the block query is executed in the form of cascaded oscillator, the phase manipulator, a second input connected to the output of the generator modulation code, a first mixer, a second input connected to the output of the first local oscillator, amplifier first intermediate frequency, a first power amplifier is STI, the first duplexer, the input-output of which is connected with the first transmitting antenna, the second amplifier, a second mixer, a second input connected to the output of the second local oscillator, the amplifier of the second intermediate frequency, multiplier, lowpass filter, extreme regulator and adjustable delay unit, a second input connected to the output of the phase manipulator, a first output connected to a second input of the multiplier, and a second output connected to the indicator range, the relay is made in the form of series-connected third local oscillator, a third mixer, amplifier of the third intermediate frequency, the fourth amplifier, the second duplexer, the input-output which associated with the second transceiver antenna, and the third amplifier, the output of which is connected to a second input of the third mixer.



 

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