Device for determining distance between aircraft

FIELD: physics, navigation.

SUBSTANCE: invention is intended for determining distance between aircraft in flight. Said result is achieved due to that the device for determining distance between aircraft has two azimuth measuring devices, two slant distance measuring devices, three adders, four multiplier units, a cosine computing unit, a square root computing unit and a display, connected to each other in a certain manner.

EFFECT: simplification of the device.

2 dwg

 

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

A device for determining the distance between aircraft, containing two azimuth meter, two meters altitude flight aircraft, two meter slant range, wherein for the purpose of preventing collision between aircraft and increase aviation safety by determining the true distance between aircraft in it additionally introduced 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, a second unit for computing the square root and the indicator and 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 connection is replaced with 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 adder connected to the 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 (RF patent for the invention №2256195, M CL G01S 13/93, G01S 5/14, publ. 10.07.2005).

A disadvantage of the known device is the complexity of the technical implementation, requiring the I presence of three meters (range, azimuth and elevation). This provides continuous calculation of the true distances between aircraft, upon reaching which a certain value, a signal is generated, a warning about the possibility of collision between aircraft.

An object of the invention is the simplification of the device.

The technical result of the invention is achieved due to the fact that calculating the true distance between aircraft, upon reaching which a certain value, a signal is generated, a warning about the possibility of collision between aircraft, performed on the results of measuring two meters (range and azimuth).

The technical result is achieved in that a device for determining the distance between aircraft, containing the first and second measuring azimuths, the first and second meters slant range, first, second and third adders, the first, second, third and fourth blocks of multiplication, the unit for computing the cosine, the unit for computing the square root and the indicator, optional the output of the first meter-range connected with first and second inputs of the first unit of multiplication and the first input of the third block multiplication, the output of the second measuring range is connected with the first and second inputs of the second unit of multiplication and the second input rubs the block multiplication, the output of which is connected to the first input of the fourth block multiplication, the outputs of the first and second azimuth meter connected to respective inputs of the first adder, the output of which through the unit for computing the cosine is connected to a second input of the fourth multiplier, the output of which is connected to the first input of the second adder, the outputs of the first and second multiplier units are connected to inputs of the third adder, the output of which is connected with the second input of the second adder, the output of which through the unit for computing the square root is connected to the input of the indicator.

Device for determining the distance between aircraft, contains the first 1 and second 2 meters slant range, the first 3 and second 4 meters in azimuth, the first 5 second 6 and third 7 adders, the first 8, second 9, the third 10 and fourth 11 blocks the multiplication unit 12 compute the cosine, block 13 calculate the square root and the indicator 14, and the output of the first 1 meter distance is connected with the first and second inputs of the first 8 multiplier and the first input of the third 10 block multiplication, the output of the second 2 meter range is connected with the first and second inputs of the second 9 block multiplication, and the second input of the third 10 block multiplication, the output of which is connected to the first input of the fourth 11 block multiplication, the outputs of the first 3 and second 4 meter azimuth connect the s to the corresponding inputs of the first 5 adder, the output of which through the block 12 calculate the cosine is connected to a second input of the fourth 11 block multiplication, the output of which is connected to the first input of the second adder 6, the outputs of the first 8 and second 9 multiplier units are connected to inputs of the third adder 7, the output of which is connected with the second input of the second adder 6, the output of which through the block 13 calculation of the square root is connected to the input of the indicator 14.

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, 2, the first and second meters slant range d1d2to aircraft BC1 and BC2, respectively;

3, 4, the first and second measuring azimuths α1α2aircraft BC1 and BC2, respectively;

5, 6, 7 - the first, second and third adders;

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

12 - unit calculation of the cosine;

13 is a unit for computing the square root;

14 - indicator.

The device operates as follows.

The first 3 and second 4 meters in azimuth of the aircraft BC1 and BC2 determine azimuths α1and α2respectively. The signal α1proportional to the azimuth of the first BC1, is fed to the first input of the first adder 5, the second input of which receives the signal α2, proportionally with the actual azimuth of the second BC2. The signal at the output of the first adder 5 is proportional to the difference of the azimuths of the first BC1 and BC2 of the second: α1α2. This signal is applied to the input of the unit for computing the cosine of 12, the output of which a signal proportional to cos(α1α2). The signal cos(α1α2) arrives at the first input of the fourth 11 block multiplication.

The first 1 and second 2 meters slant range of the aircraft BC1 and BC2 determine slant range d1d2respectively. The signal d1proportional to slant range to the first BC1, is supplied to the first and second inputs of the first 8 block multiplication, the output of which a signal proportional to d12goes to the first input of the third adder 7.

The signal d2proportional to slant range to the second BC2, is supplied to the first and second inputs of the second 9 block multiplication, the output of which a signal proportional to d22comes to the second input of the third adder 7.

The output of the third adder 7 signal proportional to the sum of the squares of the slant range d1before the first aircraft BC1 and slant range d2before the second aircraft BC2 d12+d22. This signal is applied to the first input of the second adder 6.

With an output of the third 10 unit multiplying a signal proportional to 2d1 d2comes to the second input of the fourth 11 block multiplication, the output of which a signal is generated that is proportional to 2d1d2cos(α1α2), which is supplied to the second input of the second adder 6.

From the output of the second adder 6 signal proportional to d12+d22-2d1d2cos(α1α2), arrives at the input unit 13 to calculate the square root, the output of which a 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 14 and is displayed in the form of support.

Device for determining the distance between aircraft, containing the first and second measuring azimuths, the first and second meters slant range, first, second and third adders, the first, second, third and fourth blocks of multiplication, the unit for computing the cosine, the unit for computing the square root and the indicator, wherein the output of the first meter-range connected with first and second inputs of the first unit of multiplication and the first input of the third block multiplication, the output of the second measuring range is connected with the first and second inputs of the second unit of multiplication and the second input of the third block multiplication, the output of which is connected to the first input fourth block to multiply the tion, the outputs of the first and second azimuth meter connected to respective inputs of the first adder, the output of which through the power calculation of the cosine, is connected to a second input of the fourth multiplier, the output of which is connected to the first input of the second adder, the outputs of the first and second multiplier units are connected to inputs of the third adder, the output of which is connected with the second input of the second adder, the output of which through the unit for computing the square root is connected to the input of the indicator.



 

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