# Device for determination of aircraft-to-aircraft distance

FIELD: aeronautical engineering; determination of aircraft-to-aircraft distance.

SUBSTANCE: aircraft-to-aircraft distance is determined by the following formula: where position of first of first aircraft is defined by azimuth α_{1}, slant range d_{1}, altitude h_{1} and position of second aircraft is determined by azimuth α_{2}, slant range d_{2} and altitude h_{2}. Proposed device includes aircraft azimuth indicators (1,4), flying altitude indicators (2,5), indicator of slant range to aircraft (3,6), adders (7, 14, 15, 19), multiplication units (8-12, 16, 18), cosine calculation unit 913), square root calculation units (17-20) and indicator (21).

EFFECT: avoidance of collision of aircraft; enhanced safety of flight due to determination of true aircraft-to-aircraft distance with altitude taken into account.

2 dwg

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

Known radar air surveillance (see Olynyk PV, V.V. Grachev Aviation radio equipment: Textbook for universities. - M.: Transport, 1989, pp. 269-277), which allow you to measure the coordinates of the aircraft. Their disadvantage is that they measure only two coordinates: slant range and azimuth of aircraft and does not determine the distance between the aircraft.

The closest to this unit is the automated system of air traffic control (ATC) (Vereshchaka A.I., Olynyk PV Aviation equipment: Textbook. for universities. - M.: Transport, 1996. P. 270-272, 280-283)containing sources of information, display equipment, and documenting information, computer system and means of communication. Sources of information are primary and secondary radar, automatic radio direction finders, which allows to determine the coordinates x, y the aircraft in airspace controlled by ATC.

Along with the task of determining the coordinates of ATC decides and task avoidance sun: allocated aircraft, following on one line, and calculates the current values of the distances between them:

d_{ki} ^{2}=(x_{k})^{2}(y_{i}-y_{k})^{2},

where i≠k.

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 the sun, which is fixed in the respective channels of support.

The disadvantage of this system is that is controlled by the distance between aircraft, following on one line, it is considered that the height of the controlled flight of the aircraft the same. However, if one aircraft, for example, gaining height, reduced or performs some other maneuver, and the second aircraft should be at a constant height, it is possible the crossing of their paths, then there may be a collision of the aircraft. To prevent collision between aircraft it is necessary to calculate and monitor the true distance between them.

The aim of the invention is to prevent collision between aircraft and increase aviation safety by determining the true distance between aircraft taking into account the heights of their flight.

Functional diagram of the device that defines the true distance between aircraft BC1 and BC2 (figure 1), presented in figure 2.

The device includes:

1, 4, the first and second measuring azimuths α_{1}that α_{2}aircraft BC1 and BC2 the meet is but;

2, 5, the first and second sensors of the flight altitude h_{1}h_{2}aircraft BC1 and BC2, respectively;

3, 6, the first and second meters slant range d_{1}d_{2}to aircraft BC1 and BC2, respectively;

7 - the first adder;

8, 9, 10, 11, 12 - the first, second, third, fourth and fifth blocks the multiplication

13 is a unit for computing the cosine;

14, 15 - second and third adders;

16 - the sixth block multiplication;

17 - the first block of the calculation of the square root;

18 - the seventh block multiplication;

19 - the fourth adder;

20 - second unit calculating a square root;

21 indicator.

The device operates as follows.

The first 1 and second 4 meters in azimuth of the aircraft BC1 and BC2 determine azimuths α_{1}and α_{2}respectively. Signal α_{1}proportional to the azimuth of the first BC1, is fed 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 BC2. The signal at the output of the first adder 7 is proportional to the difference of the azimuths of the first BC1 and BC2 of the second: α_{1}-α_{2}. This signal is applied to the input of the unit for computing the cosine of 13, the output of which a signal proportional to cos(α_{1}-α_{2}). The signal cos(α_{1}-α_{2}routed to the first input of the seventh block umngeni is 18.

The first 2 and the second 5 meters of altitude flying aircraft BC1 and BC2 determine the altitude h_{1}h_{2}respectively. The signal h_{1}proportional to the height of flight of the first BC1, is supplied to the first and second inputs of the first block multiplication 8 and to the first input of the third block multiplication 10. The signal proportional to h_{1} ^{2}with the release of the first block multiplication 8 is supplied to the first input of the second adder 14.

The signal h_{2}proportional to the altitude of the second BC2, is supplied to the first and second inputs of the fourth block multiplication 11 and to the second input of the third block multiplication 10. The signal proportional to h_{2} ^{2}with the output of the fourth unit of multiplication 11 is supplied to the second input of the third adder 15.

The first 3 and second 6 meters slant range of the aircraft BC1 and BC2 determine slant range d_{1}d_{2}respectively. The signal d_{1}proportional to slant range to the first BC1, is supplied to the first and second inputs of the second unit 9 multiplication, the output of which a signal proportional to d_{1} ^{2}, is fed to the second input of the second adder 14 and the second input of the fourth adder 19.

The signal d^{2}proportional to slant range to the second BC2, is supplied to the first and second inputs of the fifth block multiplication 12, the output of which is signal,
proportional d_{2} ^{2}comes to the second input of the third adder 15 and the fourth 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 d_{1}before the first aircraft BC1 and its height h_{1}: d_{1} ^{2}-h_{1} ^{2}. This signal is applied to the first input of the sixth block multiplication 16.

The output of the third adder 15 signal proportional to the difference of the squares of the slant range d_{2}before the second aircraft BC2 and its height h_{2}: d_{2} ^{2}-h_{2} ^{2}. This signal is applied to the second input of the sixth block multiplication 16.

From the output of the sixth block multiplication 16 signal proportional to (d_{1} ^{2}-h_{1} ^{2})(d_{2} ^{2}-h_{2} ^{2}), is fed to the input of the first unit for computing the square root of 17, the output of which a signal proportional tosupplied to the second input of the seventh block multiplication 18, at the first input of which receives a signal proportional to cos(α_{1}-α_{2}). From the output of the seventh unit umnojeniya 18 signal proportional toarrives at the first input of the fourth adder 19.

The third input of the fourth adder 19 is supplied the output signal from the third of the th block multiplication 10,
which is proportional to the product of the height h_{1}the first aircraft BC1 and height h_{2}the second aircraft BC2: h_{1}h_{2}.

The output of the fourth adder 19, the signal is proportional to the square of the distance between the first aircraft BC1 and the second aircraft BC2:

This signal is applied to the input of the second unit for computing the square root of 20, the output of which the signal

proportional to the distance between the first aircraft BC1 and the second aircraft BC2, is supplied to the indicator of the air situation display 21 and is displayed in the form of support.

Device for determining the distance between aircraft, containing two azimuth meter, two meters altitude flight aircraft, two meter slant range, characterized in that, for the purpose of preventing collision between aircraft and increase aviation safety by determining the true distance between aircraft, it added the first adder, the first, second, third, fourth and fifth blocks of multiplication, the unit for computing the cosine, second and third adders, the sixth block multiplication, the first computing unit of the square root, the seventh block multiplication, the fourth adder, W is Roy computing unit root square and indicator, moreover, the output of the first azimuth meter connected to the first input of the first adder, a second input connected to the output of the second azimuth meter, the output of the first adder is connected to the input of the unit for computing the cosine output of the unit for computing the cosine connected to the first input of the seventh block multiplication, the output of the first meter height is connected with the first and second inputs of the first block multiplication, and with the first input of the third block multiplication, the output of the second meter height is connected with the first and second inputs of the fourth block multiplication, and with the second input of the third block multiplication, the output of the third block multiplication connected with the third input of the fourth adder, the output of the first meter slant range is connected with the first and second inputs of the second block multiplication, the output of which is connected to a second input of the fourth adder and to the second input of the second adder, a first input of the second adder connected to the output of the first block multiplication, the output of the second adder connected to the first input of the sixth block multiplication, the output of the second meter slant range is connected with the first and second inputs of the fifth block multiplication, the output of which is connected to the four input of the fourth adder and to the second input of the third adder, a first input connected to the output of the fourth block multiplication, the output of the third of the second adder is connected to a second input of the sixth block multiplication the output of the sixth block multiplication is connected to the input of the first unit for computing the square root, the output of which is connected to a second input of the seventh block multiplication, the output of which is connected to the first input of the fourth adder, the output of the fourth adder connected to the input of the second unit for computing the square root, the output of which is connected to the input of the indicator.

**Same patents:**

FIELD: the invention refers to radio technique means of determination of a direction, location, measuring of distance and speed with using of spaced antennas and measuring of a phase shift or time lag of taking from them signals.

SUBSTANCE: the proposed mode of determination of coordinates of an unknown transmitter is based on the transmitter's emitting of a tracing signal to the satellite, on receiving of signals of an unknown transmitter and legimite transmitters which coordinates are known, on forming a file of clusters, on selection of the best clusters out of which virtual bases are formed for calculating coordinates of legimite and unknown transmitters according to the coordinates of legimite transmitters and the results of calculation of their coordinates one can calculate mistakes of measuring which are taken into account at calculating the coordinates of the unknown transmitter.

EFFECT: increases accuracy of determination of coordinates of an unknown transmitter in the system of a satellite communication with a relay station on a geostationary satellite.

2 dwg, 1 tbl

FIELD: radio detection and ranging, applicable in traffic control systems and prevention of collisions of transport facilities.

SUBSTANCE: the method is accomplished by radiation of a continuous frequency-modulated sounding signal, reception of the reflected signal in one or several spatial positions, multiplication of it with the radiated signal and subtraction of the matrix of the values of the correlation functions of the obtained homodyne signal and the two-dimensional (range, speed) matrix of the base signals formed of the modulating signal. The ranges and speeds of the detected objects are computed according to the number of the elements of the matrix of the correlation functions, in which the values of the correlation functions exceed the threshold level. The value of speed is specified by subtraction of the frequencies of the spectrum components of the correlation signals obtained as a sequence of values of the correlation function values during the time of signal accumulation. At reception of the reflected signal in several spatially spaced positions a three-dimensional (range, speed, angular coordinate) or four-dimensional matrix of base signals is formed for each position, and, according to the numbers of the respective matrix summary to the positions of the correlation functions, the range, angular co-correlation functions, the range, angular co-ordinates and speeds of the detected objects are determined. The system for measurement of speeds and co-ordinates of the objects has an antenna-feeder device, homodyne transceiver correlometer forming the matrices of the base signals and computing the functions of correlation and correlation signals, and a processor forming the modulating signal and computing the object speeds and coordinates.

EFFECT: enhanced accuracy of measurement of object speeds and coordinates, effective range, resolving power at provision of safety of road traffic.

24 cl, 9 dwg

FIELD: radio detection and ranging, applicable in traffic control systems and prevention of collisions of transport facilities.

SUBSTANCE: the method is accomplished by radiation of a continuous frequency-modulated sounding signal, reception of the reflected signal in one or several spatial positions, multiplication of it with the radiated signal and subtraction of the matrix of the values of the correlation functions of the obtained homodyne signal and the two-dimensional (range, speed) matrix of the base signals formed of the modulating signal. The ranges and speeds of the detected objects are computed according to the number of the elements of the matrix of the correlation functions, in which the values of the correlation functions exceed the threshold level. The value of speed is specified by subtraction of the frequencies of the spectrum components of the correlation signals obtained as a sequence of values of the correlation function values during the time of signal accumulation. At reception of the reflected signal in several spatially spaced positions a three-dimensional (range, speed, angular coordinate) or four-dimensional matrix of base signals is formed for each position, and, according to the numbers of the respective matrix summary to the positions of the correlation functions, the range, angular co-correlation functions, the range, angular co-ordinates and speeds of the detected objects are determined. The system for measurement of speeds and co-ordinates of the objects has an antenna-feeder device, homodyne transceiver correlometer forming the matrices of the base signals and computing the functions of correlation and correlation signals, and a processor forming the modulating signal and computing the object speeds and coordinates.

EFFECT: enhanced accuracy of measurement of object speeds and coordinates, effective range, resolving power at provision of safety of road traffic.

24 cl, 9 dwg